ARM_A318_A319_A320_A321_20090701

@AIRBUSA318/A319/A320/A321

AIRCRAFT RECOVERY MANUAL

ARM

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© AIRBUS S.A.S. 2005. All rights reserved.

AIRBUS S.A.S.Customer Services

Technical Data Support and Services31707 Blagnac Cedex

FRANCE

Issue: Jun 01/08 Rev: Jul 01/09

@A318/A319/A320/A321AIRCRAFT RECOVERY MANUAL

HIGHLIGHTS

Revision No. 2 - Jul 01/09

LOCATIONS CHGCODE

DESCRIPTIONS OF CHANGE

CHAPTER 01

Subject 01-20-01

DESC 01-20-01-002-A01 R

CHAPTER 02

Subject 02-00-00

DESC 02-00-00-001-A01 R UPDATED DEFINITION OF SECONDARYDAMAGE

Subject 02-30-01

TASK 02-30-01-200-801-A01 R CROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETED

TASK 02-30-01-481-801-A01 R TOOL P/N AND/OR DESIGNATIONADDED/REVISED/DELETED

TASK 02-30-01-867-802-A01 R TOOL P/N AND/OR DESIGNATIONADDED/REVISED/DELETED

CHAPTER 03

Subject 03-00-00

TASK 03-00-00-558-801-A01 R

FIGURE 03-00-00-991-002-D01 R

Subject 03-20-02

TASK 03-20-02-970-801-A01 R UPDATED AMM TASKCROSS REFERENCED MANUAL(S)ADDED/REVISED/DELETED

Subject 03-50-01

TASK 03-50-01-558-809-A01 R ADDED CAPACITY DATA IN THE TABLE

TASK 03-50-01-558-811-A01 R ADDED NOTE AND CORRECTIVECLERICAL ERRORNOTE AMENDED

TASK 03-50-01-558-811-B01 R ADDED NOTE AND CORRECTIVECLERICAL ERRORNOTE AMENDED

HIGHLIGHTSPage 1

Jul 01/09


LOCATIONS CHGCODE


TASK 03-50-01-558-811-C01 R ADDED NOTE AND CORRECTIVECLERICAL ERRORNOTE AMENDED

Subject 03-60-01

DESC 03-60-01-001-A01 R CROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETED

CHAPTER 04

Subject 04-20-00

TASK 04-20-00-588-801-A01 R

Subtask 04-20-00-588-001-A01 R

FIGURE 04-20-00-991-001-A01 N ILLUSTRATION ADDED

FIGURE 04-20-00-991-001-B01 N ILLUSTRATION ADDED

FIGURE 04-20-00-991-001-C01 N ILLUSTRATION ADDED

FIGURE 04-20-00-991-001-D01 N ILLUSTRATION ADDED

CHAPTER 05

Subject 05-40-02

TASK 05-40-02-650-801-A01 R WARNING CAUTIONADDED/REVISED/DELETED

CHAPTER 06

Subject 06-00-00

DESC 06-00-00-002-A01 N


FIGURE 06-00-00-991-001-B01 N ILLUSTRATION ADDED

FIGURE 06-00-00-991-001-C01 N ILLUSTRATION ADDED

Subject 06-10-00

TASK 06-10-00-970-801-A01 R

TASK 06-10-00-970-803-A01 R

Subject 06-30-00

DESC 06-30-00-001-A01 R ADDED PERMISSIBLE WIND SPEEDWARNING CAUTIONADDED/REVISED/DELETED


HIGHLIGHTSPage 2

Jul 01/09


LOCATIONS CHGCODE


DESC 06-30-00-001-B01 R ADDED PERMISSIBLE WIND SPEEDWARNING CAUTIONADDED/REVISED/DELETED


DESC 06-30-00-001-C01 R ADDED PERMISSIBLE WIND SPEEDWARNING CAUTIONADDED/REVISED/DELETED


DESC 06-30-00-001-D01 R ADDED PERMISSIBLE WIND SPEEDWARNING CAUTIONADDED/REVISED/DELETED


TASK 06-30-00-581-802-A01 R TOOL P/N AND/OR DESIGNATIONADDED/REVISED/DELETEDWARNING CAUTIONADDED/REVISED/DELETED

Subtask 06-30-00-581-003-A01 R CAUTION DELETED AS NOT APPLICABLEWARNING CAUTIONADDED/REVISED/DELETED

TASK 06-30-00-581-801-A01 R UPDATED REFERENCE TO AIRCRAFTSTABILITY ON JACKSCROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETEDWARNING CAUTIONADDED/REVISED/DELETEDNOTE AMENDED

Subtask 06-30-00-581-002-A01 R CROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETED

Subject 06-40-00

HIGHLIGHTSPage 3

Jul 01/09


LOCATIONS CHGCODE


DESC 06-40-00-002-A01 R DELETED INFORMATION RELATED TOFUSELAGE LIFTING WITH PNEUMATICLIFTING BAGSADDED REFERENCE TO LEVELING ANDLIFTING PROCEDURES ON WING ANDFUSELAGECROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETED

DESC 06-40-00-001-A01 N

DESC 06-40-00-003-A01 N



TASK 06-40-00-581-801-A01 R CROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETEDWARNING CAUTIONADDED/REVISED/DELETEDNOTE AMENDED

Subtask 06-40-00-581-001-A01 R UPDATED PROCEDURE TITLE LAYOUTAND TECHNICAL CONTENTCROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETED

Subject 06-50-00

TASK 06-50-00-581-803-A01 R

TASK 06-50-00-581-802-A01 R

TASK 06-50-00-581-801-A01 R TOOL P/N AND/OR DESIGNATIONADDED/REVISED/DELETEDCROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETEDWARNING CAUTIONADDED/REVISED/DELETEDNOTE AMENDED

Subtask 06-50-00-581-001-A01 R CROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETED

CHAPTER 07 R

Subject 07-00-00

HIGHLIGHTSPage 4

Jul 01/09


LOCATIONS CHGCODE



Section 07-20 N

Subject 07-20-00 N

DESC 07-20-00-001-A01 N


Section 07-40 R

Subject 07-40-00 R

DESC 07-40-00-001-A01 R Added of debogging definition

Subject 07-40-01

TASK 07-40-01-584-801-A01 R

Subject 07-40-02

TASK 07-40-02-584-801-A01 R CROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETEDTOOL P/N AND/OR DESIGNATIONADDED/REVISED/DELETED

TASK 07-40-02-584-802-A01 R CROSS REFERENCED DOCUMENTARYUNIT ADDED/REVISED/DELETEDCONSUMABLE MATERIAL DATAUPDATEDTOOL P/N AND/OR DESIGNATIONADDED/REVISED/DELETED

Subject 07-60-02


CHAPTER 09

Subject 09-20-01

DESC 09-20-01-002-A01 R

FIGURE 09-20-01-991-006-A01 R

FIGURE 09-20-01-991-008-A01 R

FIGURE 09-20-01-991-010-A01 R

FIGURE 09-20-01-991-012-A01 R

FIGURE 09-20-01-991-015-A01 R

FIGURE 09-20-01-991-016-A01 D ILLUSTRATION DELETED

HIGHLIGHTSPage 5

Jul 01/09


LOCATIONS CHGCODE


Subject 09-50-01

FIGURE 09-50-01-991-007-A01 R

HIGHLIGHTSPage 6

Jul 01/09


LIST OF EFFECTIVE CONTENT

Revision No. 2 - Jul 01/09

CONTENT CHGCODE

LAST REVISIONDATE

CHAPTER 01

Subject 01-00-00

DESC 01-00-00-001-A01 Jun 01/08

DESC 01-00-00-002-A01 Jun 01/08

Subject 01-00-02

DESC 01-00-02-001-A01 Nov 01/08

FIGURE 01-00-02-991-001-A01 Jun 01/08

FIGURE 01-00-02-991-002-A01 Jun 01/08

DESC 01-00-02-002-A01 Jun 01/08

DESC 01-00-02-003-A01 Jun 01/08

DESC 01-00-02-004-A01 Jun 01/08

Subject 01-00-03

DESC 01-00-03-001-A01 Jun 01/08

Subject 01-10-01

DESC 01-10-01-002-A01 Jun 01/08

DESC 01-10-01-001-A01 Jun 01/08

Subject 01-20-01

DESC 01-20-01-001-A01 Jun 01/08

DESC 01-20-01-002-A01 R Jul 01/09

DESC 01-20-01-002-B01 Jun 01/08

DESC 01-20-01-002-C01 Jun 01/08

DESC 01-20-01-002-D01 Jun 01/08

CHAPTER 02

Subject 02-00-00

DESC 02-00-00-001-A01 R Jul 01/09

FIGURE 02-00-00-991-001-A01 Jun 01/08

L.E.C.Page 1

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

Subject 02-10-01

DESC 02-10-01-001-A01 Jun 01/08

DESC 02-10-01-002-A01 Jun 01/08

Subject 02-20-01

TASK 02-20-01-285-801-A01 Jun 01/08

Subtask 02-20-01-284-001-A01 Jun 01/08

Subtask 02-20-01-680-001-A01 Jun 01/08

Subtask 02-20-01-862-001-A01 Jun 01/08

Subtask 02-20-01-869-001-A01 Jun 01/08

Subject 02-20-02

TASK 02-20-02-285-801-A01 Jun 01/08

Subtask 02-20-02-285-001-A01 Jun 01/08

Subtask 02-20-02-285-002-A01 Jun 01/08

Subtask 02-20-02-500-001-A01 Jun 01/08

Subtask 02-20-02-869-001-A01 Jun 01/08

Subject 02-30-01

TASK 02-30-01-200-801-A01 R Jul 01/09

Subtask 02-30-01-867-001-A01 Nov 01/08

Subtask 02-30-01-867-003-A01 Nov 01/08

Subtask 02-30-01-867-004-A01 Nov 01/08

FIGURE 02-30-01-991-001-A01 Jun 01/08

FIGURE 02-30-01-991-002-A01 Jun 01/08

TASK 02-30-01-481-801-A01 R Jul 01/09

Subtask 02-30-01-481-003-A01 Jun 01/08

Subtask 02-30-01-481-004-A01 Jun 01/08

FIGURE 02-30-01-991-020-A01 Jun 01/08

FIGURE 02-30-01-991-021-A01 Jun 01/08

TASK 02-30-01-867-802-A01 R Jul 01/09

Subtask 02-30-01-869-001-A01 Jun 01/08

L.E.C.Page 2

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

Subtask 02-30-01-581-001-A01 Nov 01/08

Subtask 02-30-01-581-002-A01 Nov 01/08

Subtask 02-30-01-581-003-A01 Nov 01/08

FIGURE 02-30-01-991-019-A01 Jun 01/08

FIGURE 02-30-01-991-022-A01 Jun 01/08

FIGURE 02-30-01-991-023-A01 Jun 01/08

Subject 02-40-01

DESC 02-40-01-001-A01 Jun 01/08

CHAPTER 03

Subject 03-00-00

TASK 03-00-00-558-801-A01 R Jul 01/09

Subtask 03-00-00-558-001-A01 Nov 01/08

Subtask 03-00-00-558-001-B01 Nov 01/08

Subtask 03-00-00-558-001-C01 Nov 01/08

Subtask 03-00-00-558-001-D01 Nov 01/08

Subtask 03-00-00-970-001-A01 Jun 01/08

FIGURE 03-00-00-991-002-A01 Jun 01/08

FIGURE 03-00-00-991-002-B01 Jun 01/08

FIGURE 03-00-00-991-002-C01 Jun 01/08

FIGURE 03-00-00-991-002-D01 R Jul 01/09

Subject 03-20-01

DESC 03-20-01-001-A01 Nov 01/08

FIGURE 03-20-01-991-001-A01 Nov 01/08

DESC 03-20-01-002-A01 Nov 01/08

Subject 03-20-02

TASK 03-20-02-970-801-A01 R Jul 01/09

Subtask 03-20-02-869-001-A01 Nov 01/08

Subtask 03-20-02-970-001-A01 Jun 01/08

FIGURE 03-20-02-991-001-A01 Jun 01/08

L.E.C.Page 3

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE 03-20-02-991-001-B01 Jun 01/08

FIGURE 03-20-02-991-002-A01 Jun 01/08

Subject 03-50-01

DESC 03-50-01-001-A01 Jun 01/08

TASK 03-50-01-558-801-A01 Nov 01/08

Subtask 03-50-01-558-001-A01 Nov 01/08

TASK 03-50-01-558-801-B01 Nov 01/08

Subtask 03-50-01-558-018-A01 Nov 01/08

FIGURE 03-50-01-991-003-A01 Jun 01/08

FIGURE 03-50-01-991-004-A01 Jun 01/08

TASK 03-50-01-558-801-C01 Nov 01/08

Subtask 03-50-01-558-019-A01 Nov 01/08

FIGURE 03-50-01-991-005-A01 Jun 01/08

FIGURE 03-50-01-991-006-A01 Jun 01/08

TASK 03-50-01-558-801-D01 Nov 01/08

Subtask 03-50-01-558-020-A01 Nov 01/08

FIGURE 03-50-01-991-007-A01 Jun 01/08

FIGURE 03-50-01-991-008-A01 Jun 01/08

TASK 03-50-01-558-802-A01 Nov 01/08

Subtask 03-50-01-558-002-A01 Jun 01/08

TASK 03-50-01-558-803-A01 Nov 01/08

Subtask 03-50-01-558-003-A01 Jun 01/08

TASK 03-50-01-558-804-A01 Nov 01/08

Subtask 03-50-01-558-004-A01 Nov 01/08

TASK 03-50-01-558-805-A01 Nov 01/08

Subtask 03-50-01-558-005-A01 Jun 01/08

TASK 03-50-01-558-806-A01 Nov 01/08

Subtask 03-50-01-558-006-A01 Nov 01/08

TASK 03-50-01-558-807-A01 Nov 01/08

L.E.C.Page 4

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

Subtask 03-50-01-558-007-A01 Jun 01/08

TASK 03-50-01-558-808-A01 Nov 01/08

Subtask 03-50-01-558-008-A01 Jun 01/08

TASK 03-50-01-558-809-A01 R Jul 01/09

Subtask 03-50-01-558-009-A01 Nov 01/08

TASK 03-50-01-558-810-A01 Nov 01/08

Subtask 03-50-01-558-010-A01 Nov 01/08

TASK 03-50-01-558-810-B01 Nov 01/08

Subtask 03-50-01-558-012-A01 Nov 01/08

TASK 03-50-01-558-810-C01 Nov 01/08

Subtask 03-50-01-558-013-A01 Nov 01/08

TASK 03-50-01-558-810-D01 Nov 01/08

Subtask 03-50-01-558-014-A01 Nov 01/08

TASK 03-50-01-558-811-A01 R Jul 01/09

Subtask 03-50-01-558-011-A01 Nov 01/08

TASK 03-50-01-558-811-B01 R Jul 01/09

Subtask 03-50-01-558-015-A01 Nov 01/08

TASK 03-50-01-558-811-C01 R Jul 01/09

Subtask 03-50-01-558-016-A01 Nov 01/08

Subject 03-60-01

DESC 03-60-01-001-A01 R Jul 01/09

CHAPTER 04

Subject 04-00-00

DESC 04-00-00-001-A01 Jun 01/08

Subject 04-20-00

TASK 04-20-00-588-801-A01 R Jul 01/09

Subtask 04-20-00-588-001-A01 R Jul 01/09

FIGURE 04-20-00-991-001-A01 N Jul 01/09

L.E.C.Page 5

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE 04-20-00-991-001-B01 N Jul 01/09

FIGURE 04-20-00-991-001-C01 N Jul 01/09

FIGURE 04-20-00-991-001-D01 N Jul 01/09

Subject 04-30-00

DESC 04-30-00-001-A01 Nov 01/08

FIGURE 04-30-00-991-001-A01 Jun 01/08

FIGURE 04-30-00-991-002-A01 Jun 01/08

FIGURE 04-30-00-991-002-B01 Jun 01/08

FIGURE 04-30-00-991-002-C01 Jun 01/08

FIGURE 04-30-00-991-002-D01 Jun 01/08

FIGURE 04-30-00-991-003-A01 Jun 01/08

TASK 04-30-00-556-801-A01 Nov 01/08

Subtask 04-30-00-556-001-A01 Nov 01/08

Subtask 04-30-00-556-002-A01 Jun 01/08

FIGURE 04-30-00-991-004-A01 Jun 01/08

FIGURE 04-30-00-991-005-A01 Jun 01/08

FIGURE 04-30-00-991-006-A01 Jun 01/08

FIGURE 04-30-00-991-007-A01 Jun 01/08

Subject 04-40-00

DESC 04-40-00-001-A01 Jun 01/08

Subject 04-50-00

DESC 04-50-00-001-A01 Jun 01/08

CHAPTER 05

Subject 05-00-00

DESC 05-00-00-001-A01 Nov 01/08

Subject 05-10-00

DESC 05-10-00-001-A01 Nov 01/08

FIGURE 05-10-00-991-004-A01 Nov 01/08

Subject 05-20-00

L.E.C.Page 6

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

DESC 05-20-00-001-A01 Nov 01/08

DESC 05-20-00-002-A01 Nov 01/08

FIGURE 05-20-00-991-013-A01 Nov 01/08

FIGURE 05-20-00-991-013-B01 Nov 01/08

FIGURE 05-20-00-991-001-A01 Nov 01/08

FIGURE 05-20-00-991-001-B01 Nov 01/08

FIGURE 05-20-00-991-002-A01 Nov 01/08

FIGURE 05-20-00-991-002-B01 Nov 01/08

DESC 05-20-00-004-A01 Nov 01/08

FIGURE 05-20-00-991-014-A01 Nov 01/08

FIGURE 05-20-00-991-015-A01 Nov 01/08

Subject 05-30-00

TASK 05-30-00-650-801-A01 Nov 01/08

Subtask 05-30-00-869-001-A01 Nov 01/08

Subtask 05-30-00-650-003-A01 Nov 01/08

Subject 05-40-00

DESC 05-40-00-001-A01 Nov 01/08

Subject 05-40-01

TASK 05-40-01-650-801-A01 Nov 01/08

Subtask 05-40-01-869-001-A01 Nov 01/08

Subtask 05-40-01-650-003-A01 Nov 01/08

Subject 05-40-02

TASK 05-40-02-650-801-A01 R Jul 01/09

Subtask 05-40-02-869-001-A01 Nov 01/08

Subtask 05-40-02-650-002-A01 Nov 01/08

FIGURE 05-40-02-991-004-A01 Nov 01/08

Subject 05-40-03

TASK 05-40-03-650-802-A01 Nov 01/08

Subtask 05-40-03-869-001-A01 Nov 01/08

L.E.C.Page 7

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

Subtask 05-40-03-010-001-A01 Nov 01/08

Subtask 05-40-03-010-001-B01 Nov 01/08

Subtask 05-40-03-650-002-A01 Nov 01/08

FIGURE 05-40-03-991-001-A01 Nov 01/08

Subject 05-50-00

DESC 05-50-00-005-A01 Nov 01/08

Subject 05-50-01

DESC 05-50-01-005-A01 Nov 01/08

Subject 05-60-00

DESC 05-60-00-001-A01 Nov 01/08

CHAPTER 06

Subject 06-00-00

DESC 06-00-00-001-A01 Jun 01/08

DESC 06-00-00-002-A01 N Jul 01/09

FIGURE 06-00-00-991-001-A01 N Jul 01/09

FIGURE 06-00-00-991-001-B01 N Jul 01/09

FIGURE 06-00-00-991-001-C01 N Jul 01/09

Subject 06-10-00

TASK 06-10-00-970-801-A01 R Jul 01/09

Subtask 06-10-00-970-001-A01 Nov 01/08

Subtask 06-10-00-869-001-A01 Jun 01/08

FIGURE 06-10-00-991-001-A01 Nov 01/08

FIGURE 06-10-00-991-002-A01 Jun 01/08

TASK 06-10-00-970-802-A01 Nov 01/08

Subtask 06-10-00-970-002-A01 Jun 01/08

TASK 06-10-00-970-803-A01 R Jul 01/09

Subtask 06-10-00-970-003-A01 Nov 01/08

Subtask 06-10-00-970-004-A01 Nov 01/08

FIGURE 06-10-00-991-003-A01 Jun 01/08

L.E.C.Page 8

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE 06-10-00-991-004-A01 Jun 01/08

Subject 06-30-00

DESC 06-30-00-001-A01 R Jul 01/09

FIGURE 06-30-00-991-006-A01 Jun 01/08

FIGURE 06-30-00-991-010-A01 N Jul 01/09

DESC 06-30-00-001-B01 R Jul 01/09

FIGURE 06-30-00-991-007-A01 Jun 01/08

FIGURE 06-30-00-991-011-A01 N Jul 01/09

DESC 06-30-00-001-C01 R Jul 01/09

FIGURE 06-30-00-991-008-A01 Jun 01/08

FIGURE 06-30-00-991-012-A01 N Jul 01/09

DESC 06-30-00-001-D01 R Jul 01/09

FIGURE 06-30-00-991-009-A01 Jun 01/08

FIGURE 06-30-00-991-013-A01 N Jul 01/09

DESC 06-30-00-002-A01 Jun 01/08

TASK 06-30-00-581-802-A01 R Jul 01/09

Subtask 06-30-00-581-003-A01 R Jul 01/09

FIGURE 06-30-00-991-004-A01 Jun 01/08

TASK 06-30-00-581-801-A01 R Jul 01/09

Subtask 06-30-00-581-002-A01 R Jul 01/09

Subject 06-40-00

DESC 06-40-00-002-A01 R Jul 01/09

DESC 06-40-00-001-A01 N Jul 01/09

DESC 06-40-00-003-A01 N Jul 01/09

FIGURE 06-40-00-991-001-A01 N Jul 01/09

FIGURE 06-40-00-991-003-A01 N Jul 01/09

TASK 06-40-00-581-801-A01 R Jul 01/09

Subtask 06-40-00-581-001-A01 R Jul 01/09

Subject 06-50-00

L.E.C.Page 9

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

DESC 06-50-00-001-A01 Nov 01/08

FIGURE 06-50-00-991-020-A01 Nov 01/08

TASK 06-50-00-581-803-A01 R Jul 01/09

Subtask 06-50-00-581-002-A01 Nov 01/08

Subtask 06-50-00-581-003-A01 Nov 01/08

FIGURE 06-50-00-991-014-A01 Nov 01/08

FIGURE 06-50-00-991-015-A01 Jun 01/08

FIGURE 06-50-00-991-021-A01 Nov 01/08

TASK 06-50-00-581-802-A01 R Jul 01/09

Subtask 06-50-00-010-001-A01 Nov 01/08

Subtask 06-50-00-581-004-A01 Nov 01/08

Subtask 06-50-00-581-005-A01 Nov 01/08

FIGURE 06-50-00-991-013-A01 Jun 01/08

FIGURE 06-50-00-991-016-A01 Jun 01/08

FIGURE 06-50-00-991-017-A01 Nov 01/08

FIGURE 06-50-00-991-018-A01 Nov 01/08

TASK 06-50-00-581-801-A01 R Jul 01/09

Subtask 06-50-00-581-001-A01 R Jul 01/09

CHAPTER 07

Subject 07-00-00

DESC 07-00-00-002-A01 R Jul 01/09

Subject 07-20-00

DESC 07-20-00-001-A01 N Jul 01/09

FIGURE 07-20-00-991-001-A01 N Jul 01/09

Subject 07-40-00

DESC 07-40-00-001-A01 R Jul 01/09

Subject 07-40-01

TASK 07-40-01-584-801-A01 R Jul 01/09

Subtask 07-40-01-500-001-A01 Nov 01/08

L.E.C.Page 10

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CONTENT CHGCODE

LAST REVISIONDATE

Subtask 07-40-01-500-002-A01 Nov 01/08

Subtask 07-40-01-869-001-A01 Jun 01/08

Subtask 07-40-01-584-001-A01 Jun 01/08

Subtask 07-40-01-869-002-A01 Jun 01/08

FIGURE 07-40-01-991-001-A01 Jun 01/08

FIGURE 07-40-01-991-002-A01 Jun 01/08

TASK 07-40-01-584-802-A01 Nov 01/08

Subtask 07-40-01-500-003-A01 Jun 01/08

Subtask 07-40-01-500-004-A01 Jun 01/08

Subtask 07-40-01-869-003-A01 Jun 01/08

Subtask 07-40-01-584-002-A01 Jun 01/08

Subtask 07-40-01-869-004-A01 Jun 01/08

Subject 07-40-02

TASK 07-40-02-584-801-A01 R Jul 01/09

Subtask 07-40-02-500-001-A01 Jun 01/08

Subtask 07-40-02-500-002-A01 Nov 01/08

Subtask 07-40-02-500-003-A01 Nov 01/08

Subtask 07-40-02-584-001-A01 Jun 01/08

Subtask 07-40-02-869-001-A01 Jun 01/08

FIGURE 07-40-02-991-001-A01 Jun 01/08

FIGURE 07-40-02-991-002-A01 Jun 01/08

FIGURE 07-40-02-991-003-A01 Jun 01/08

TASK 07-40-02-584-802-A01 R Jul 01/09

Subtask 07-40-02-500-004-A01 Jun 01/08

Subtask 07-40-02-020-001-A01 Nov 01/08

Subtask 07-40-02-500-006-A01 Nov 01/08

Subtask 07-40-02-584-002-A01 Jun 01/08

Subtask 07-40-02-869-002-A01 Jun 01/08

Subtask 07-40-02-500-007-A01 Nov 01/08

L.E.C.Page 11

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE 07-40-02-991-004-A01 Jun 01/08

FIGURE 07-40-02-991-005-A01 Jun 01/08

FIGURE 07-40-02-991-006-A01 Jun 01/08

FIGURE 07-40-02-991-007-A01 Jun 01/08

Subject 07-40-03

TASK 07-40-03-584-801-A01 Nov 01/08

Subtask 07-40-03-584-001-A01 Jun 01/08

Subtask 07-40-03-584-002-A01 Jun 01/08

Subject 07-40-04

DESC 07-40-04-001-A01 Nov 01/08

FIGURE 07-40-04-991-001-A01 Jun 01/08

FIGURE 07-40-04-991-002-A01 Jun 01/08

FIGURE 07-40-04-991-003-A01 Jun 01/08

Subject 07-60-00

DESC 07-60-00-001-A01 Nov 01/08

Subject 07-60-01

DESC 07-60-01-001-A01 Nov 01/08

FIGURE 07-60-01-991-002-A01 Nov 01/08

FIGURE 07-60-01-991-003-A01 Nov 01/08

Subject 07-60-02

DESC 07-60-02-001-A01 R Jul 01/09

Subject 07-60-03

DESC 07-60-03-001-A01 Nov 01/08

CHAPTER 08

Subject 08-00-00

DESC 08-00-00-001-A01 Jun 01/08

CHAPTER 09

Subject 09-00-00

DESC 09-00-00-001-A01 Jun 01/08

L.E.C.Page 12

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

Subject 09-10-01

DESC 09-10-01-002-A01 Jun 01/08

DESC 09-10-01-001-A01 Jun 01/08

Subject 09-10-02

DESC 09-10-02-001-A01 Jun 01/08

DESC 09-10-02-003-A01 Jun 01/08

DESC 09-10-02-002-A01 Nov 01/08

FIGURE 09-10-02-991-001-A01 Jun 01/08

Subject 09-10-03

DESC 09-10-03-001-A01 Nov 01/08

FIGURE 09-10-03-991-001-A01 Jun 01/08

FIGURE 09-10-03-991-002-A01 Jun 01/08

DESC 09-10-03-001-B01 Nov 01/08

FIGURE 09-10-03-991-003-A01 Jun 01/08

FIGURE 09-10-03-991-004-A01 Jun 01/08

DESC 09-10-03-001-C01 Nov 01/08

FIGURE 09-10-03-991-005-A01 Jun 01/08

FIGURE 09-10-03-991-005-B01 Jun 01/08

FIGURE 09-10-03-991-006-A01 Jun 01/08

DESC 09-10-03-001-D01 Nov 01/08

FIGURE 09-10-03-991-007-A01 Jun 01/08

FIGURE 09-10-03-991-008-A01 Jun 01/08

Subject 09-10-04

DESC 09-10-04-001-A01 Nov 01/08

FIGURE 09-10-04-991-001-A01 Jun 01/08

FIGURE 09-10-04-991-001-B01 Jun 01/08

FIGURE 09-10-04-991-001-C01 Jun 01/08

FIGURE 09-10-04-991-001-D01 Jun 01/08

Subject 09-10-05

L.E.C.Page 13

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

DESC 09-10-05-001-A01 Nov 01/08

FIGURE 09-10-05-991-001-A01 Jun 01/08

FIGURE 09-10-05-991-001-B01 Jun 01/08

FIGURE 09-10-05-991-001-C01 Jun 01/08

FIGURE 09-10-05-991-001-D01 Jun 01/08

Subject 09-10-06

DESC 09-10-06-001-A01 Jun 01/08

FIGURE 09-10-06-991-001-A01 Jun 01/08

FIGURE 09-10-06-991-001-B01 Jun 01/08

FIGURE 09-10-06-991-001-C01 Jun 01/08

FIGURE 09-10-06-991-001-D01 Jun 01/08

Subject 09-10-08

DESC 09-10-08-001-A01 Nov 01/08

FIGURE 09-10-08-991-001-A01 Jun 01/08

FIGURE 09-10-08-991-001-B01 Jun 01/08

Subject 09-10-09

DESC 09-10-09-001-A01 Nov 01/08

FIGURE 09-10-09-991-001-A01 Jun 01/08

Subject 09-10-10

DESC 09-10-10-001-A01 Jun 01/08

DESC 09-10-10-002-A01 Nov 01/08

FIGURE 09-10-10-991-001-A01 Jun 01/08

FIGURE 09-10-10-991-001-B01 Jun 01/08

FIGURE 09-10-10-991-001-C01 Jun 01/08

FIGURE 09-10-10-991-001-D01 Jun 01/08

FIGURE 09-10-10-991-002-A01 Jun 01/08

FIGURE 09-10-10-991-003-A01 Jun 01/08

FIGURE 09-10-10-991-003-B01 Jun 01/08

FIGURE 09-10-10-991-003-C01 Jun 01/08

L.E.C.Page 14

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE 09-10-10-991-003-D01 Jun 01/08

FIGURE 09-10-10-991-004-A01 Jun 01/08

DESC 09-10-10-003-A01 Nov 01/08

FIGURE 09-10-10-991-006-A01 Jun 01/08

FIGURE 09-10-10-991-006-B01 Jun 01/08

FIGURE 09-10-10-991-006-C01 Jun 01/08

FIGURE 09-10-10-991-006-D01 Jun 01/08

DESC 09-10-10-004-A01 Nov 01/08

FIGURE 09-10-10-991-010-A01 Jun 01/08

DESC 09-10-10-005-A01 Nov 01/08

FIGURE 09-10-10-991-011-A01 Jun 01/08

FIGURE 09-10-10-991-011-B01 Jun 01/08

FIGURE 09-10-10-991-011-C01 Nov 01/08

FIGURE 09-10-10-991-011-D01 Jun 01/08

DESC 09-10-10-006-A01 Nov 01/08

FIGURE 09-10-10-991-014-A01 Jun 01/08

Subject 09-10-11

DESC 09-10-11-001-A01 Nov 01/08

FIGURE 09-10-11-991-001-A01 Jun 01/08

FIGURE 09-10-11-991-002-A01 Jun 01/08

FIGURE 09-10-11-991-003-A01 Jun 01/08

FIGURE 09-10-11-991-004-A01 Jun 01/08

FIGURE 09-10-11-991-005-A01 Jun 01/08

FIGURE 09-10-11-991-006-A01 Jun 01/08

FIGURE 09-10-11-991-007-A01 Jun 01/08

DESC 09-10-11-001-B01 Nov 01/08

FIGURE 09-10-11-991-014-A01 Jun 01/08

FIGURE 09-10-11-991-015-A01 Jun 01/08

FIGURE 09-10-11-991-016-A01 Jun 01/08

L.E.C.Page 15

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE 09-10-11-991-017-A01 Jun 01/08

FIGURE 09-10-11-991-018-A01 Jun 01/08

FIGURE 09-10-11-991-019-A01 Jun 01/08

FIGURE 09-10-11-991-020-A01 Jun 01/08

DESC 09-10-11-001-C01 Nov 01/08

FIGURE 09-10-11-991-021-A01 Jun 01/08

FIGURE 09-10-11-991-022-A01 Jun 01/08

FIGURE 09-10-11-991-023-A01 Jun 01/08

FIGURE 09-10-11-991-024-A01 Jun 01/08

FIGURE 09-10-11-991-025-A01 Jun 01/08

FIGURE 09-10-11-991-026-A01 Jun 01/08

FIGURE 09-10-11-991-027-A01 Jun 01/08

DESC 09-10-11-001-D01 Nov 01/08

FIGURE 09-10-11-991-028-A01 Jun 01/08

FIGURE 09-10-11-991-029-A01 Jun 01/08

FIGURE 09-10-11-991-030-A01 Jun 01/08

FIGURE 09-10-11-991-031-A01 Jun 01/08

FIGURE 09-10-11-991-032-A01 Jun 01/08

FIGURE 09-10-11-991-033-A01 Jun 01/08

FIGURE 09-10-11-991-034-A01 Jun 01/08

Subject 09-10-12

DESC 09-10-12-001-A01 Nov 01/08

FIGURE 09-10-12-991-001-A01 Jun 01/08

FIGURE 09-10-12-991-001-B01 Jun 01/08

FIGURE 09-10-12-991-001-C01 Jun 01/08

FIGURE 09-10-12-991-001-D01 Jun 01/08

DESC 09-10-12-002-A01 Jun 01/08

FIGURE 09-10-12-991-002-A01 Jun 01/08

FIGURE 09-10-12-991-003-A01 Jun 01/08

L.E.C.Page 16

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE 09-10-12-991-014-A01 Jun 01/08

DESC 09-10-12-003-A01 Jun 01/08

FIGURE 09-10-12-991-004-A01 Jun 01/08

DESC 09-10-12-004-A01 Jun 01/08

FIGURE 09-10-12-991-008-A01 Nov 01/08

FIGURE 09-10-12-991-009-A01 Jun 01/08

FIGURE 09-10-12-991-015-A01 Jun 01/08

DESC 09-10-12-005-A01 Jun 01/08

FIGURE 09-10-12-991-010-A01 Jun 01/08

DESC 09-10-12-006-A01 Jun 01/08

FIGURE 09-10-12-991-013-A01 Jun 01/08

FIGURE 09-10-12-991-013-B01 Jun 01/08

Subject 09-10-13

DESC 09-10-13-001-A01 Jun 01/08

FIGURE 09-10-13-991-001-A01 Jun 01/08

Subject 09-10-14

DESC 09-10-14-001-A01 Nov 01/08

FIGURE 09-10-14-991-007-A01 Nov 01/08

FIGURE 09-10-14-991-008-A01 Nov 01/08

FIGURE 09-10-14-991-009-A01 Nov 01/08

DESC 09-10-14-001-B01 Nov 01/08

FIGURE 09-10-14-991-010-A01 Nov 01/08

FIGURE 09-10-14-991-011-A01 Nov 01/08

DESC 09-10-14-001-C01 Nov 01/08

FIGURE 09-10-14-991-013-A01 Nov 01/08

FIGURE 09-10-14-991-014-A01 Nov 01/08

FIGURE 09-10-14-991-015-A01 Nov 01/08

DESC 09-10-14-001-D01 Nov 01/08

FIGURE 09-10-14-991-016-A01 Nov 01/08

L.E.C.Page 17

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE 09-10-14-991-017-A01 Nov 01/08

FIGURE 09-10-14-991-018-A01 Nov 01/08

Subject 09-10-15

DESC 09-10-15-001-A01 Nov 01/08

FIGURE 09-10-15-991-001-A01 Jun 01/08

FIGURE 09-10-15-991-001-B01 Jun 01/08

FIGURE 09-10-15-991-001-C01 Jun 01/08

FIGURE 09-10-15-991-001-D01 Jun 01/08

Subject 09-10-16

DESC 09-10-16-001-A01 Nov 01/08

FIGURE 09-10-16-991-001-A01 Jun 01/08

FIGURE 09-10-16-991-001-B01 Jun 01/08

FIGURE 09-10-16-991-001-C01 Jun 01/08

FIGURE 09-10-16-991-001-D01 Jun 01/08

FIGURE 09-10-16-991-002-A01 Jun 01/08

FIGURE 09-10-16-991-003-A01 Jun 01/08

FIGURE 09-10-16-991-004-A01 Jun 01/08

Subject 09-20-01

DESC 09-20-01-001-A01 Jun 01/08

DESC 09-20-01-002-A01 R Jul 01/09

FIGURE 09-20-01-991-001-A01 Jun 01/08

FIGURE 09-20-01-991-002-A01 Jun 01/08

FIGURE 09-20-01-991-003-A01 Jun 01/08

FIGURE 09-20-01-991-004-A01 Jun 01/08

FIGURE 09-20-01-991-005-A01 Jun 01/08

FIGURE 09-20-01-991-006-A01 R Jul 01/09

FIGURE 09-20-01-991-007-A01 Jun 01/08

FIGURE 09-20-01-991-008-A01 R Jul 01/09

FIGURE 09-20-01-991-009-A01 Jun 01/08

L.E.C.Page 18

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE 09-20-01-991-010-A01 R Jul 01/09

FIGURE 09-20-01-991-011-A01 Jun 01/08

FIGURE 09-20-01-991-012-A01 R Jul 01/09

FIGURE 09-20-01-991-013-A01 Jun 01/08

FIGURE 09-20-01-991-014-A01 Jun 01/08

FIGURE 09-20-01-991-015-A01 R Jul 01/09

FIGURE 09-20-01-991-016-A01 D Jul 01/09

DESC 09-20-01-004-A01 Jun 01/08

DESC 09-20-01-005-A01 Jun 01/08

FIGURE 09-20-01-991-020-A01 Jun 01/08

TASK 09-20-01-869-801-A01 Jun 01/08

Subtask 09-20-01-869-001-A01 Jun 01/08

Subtask 09-20-01-869-002-A01 Jun 01/08

Subject 09-20-02

DESC 09-20-02-001-A01 Jun 01/08

Subject 09-30-01

DESC 09-30-01-001-A01 Jun 01/08

DESC 09-30-01-002-A01 Nov 01/08

Subject 09-30-02

DESC 09-30-02-001-A01 Nov 01/08

Subject 09-30-03

DESC 09-30-03-001-A01 Nov 01/08

DESC 09-30-03-002-A01 Nov 01/08

Subject 09-50-01

DESC 09-50-01-001-A01 Nov 01/08

FIGURE 09-50-01-991-001-A01 Jun 01/08

FIGURE 09-50-01-991-002-A01 Jun 01/08

FIGURE 09-50-01-991-003-A01 Jun 01/08

FIGURE 09-50-01-991-004-A01 Jun 01/08

L.E.C.Page 19

Jul 01/09


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE 09-50-01-991-005-A01 Jun 01/08

FIGURE 09-50-01-991-006-A01 Jun 01/08

FIGURE 09-50-01-991-007-A01 R Jul 01/09

FIGURE 09-50-01-991-008-A01 Jun 01/08

FIGURE 09-50-01-991-009-A01 Jun 01/08

FIGURE 09-50-01-991-010-A01 Jun 01/08

FIGURE 09-50-01-991-011-A01 Jun 01/08

FIGURE 09-50-01-991-012-A01 Jun 01/08

FIGURE 09-50-01-991-013-A01 Jun 01/08

FIGURE 09-50-01-991-014-A01 Jun 01/08

L.E.C.Page 20

Jul 01/09


TABLE OF CONTENTS

01 INTRODUCTION

01-00-00 INTRODUCTION01-00-00-001-A01 General01-00-00-002-A01 Important Notice to Users of this Document

01-00-02 SEQUENCE OF THE DOCUMENT

01-00-02-001-A01 General01-00-02-002-A01 Task Oriented ARM01-00-02-003-A01 Content01-00-02-004-A01 Effectivity Management

01-00-03 DEFINITIONS01-00-03-001-A01 General

01-10-01 RELATED DATA01-10-01-002-A01 Airbus Data01-10-01-001-A01 Other Data

01-20-01 GENERAL AIRCRAFT CHARACTERISTICS01-20-01-001-A01 General Aircraft Description

01-20-01-002-A01 General Aircraft Data01-20-01-002-B01 General Aircraft Data01-20-01-002-C01 General Aircraft Data01-20-01-002-D01 General Aircraft Data

02 SURVEY

02-00-00 SURVEY02-00-00-001-A01 General

02-10-01 CHARTS AND GUIDES02-10-01-001-A01 Aircraft Recovery Process

02-10-01-002-A01 Aircraft Recovery Logic Chart

02-20-01 INITIAL AIRCRAFT SURVEY02-20-01-285-801-A01 Initial Aircraft Survey

T.O.C.Page 1

Jul 01/09


02-20-02 INITIAL SITE SURVEY02-20-02-285-801-A01 Initial Site Survey

02-30-01 LANDING GEAR02-30-01-200-801-A01 Landing Gear Survey

02-30-01-481-801-A01 Installation of the Safety Device on Landing Gears

02-30-01-867-802-A01 Jacking for Wheel Change

02-40-01 HEALTH AND SAFETY ISSUES02-40-01-001-A01 General

03 WEIGHT AND CG MANAGEMENT

03-00-00 WEIGHT AND CG MANAGEMENT03-00-00-558-801-A01 General

03-20-01 FUEL LOAD AND CG CONTROL03-20-01-001-A01 General03-20-01-002-A01 Tables

03-20-02 MANUAL FUEL QUANTITY INDICATION

03-20-02-970-801-A01 Use of Magnetic Level Indicators (MLI)

03-50-01 MANAGING AIRCRAFT WEIGHT AND CG03-50-01-001-A01 Introduction03-50-01-558-801-A01 Cargo and Baggage Remaining Effect

03-50-01-558-801-B01 Cargo and Baggage Remaining Effect

03-50-01-558-801-C01 Cargo and Baggage Remaining Effect

03-50-01-558-801-D01 Cargo and Baggage Remaining Effect

03-50-01-558-802-A01 Total Traffic Load Remaining Effect

03-50-01-558-803-A01 Ballast Added Effect03-50-01-558-804-A01 Waste Water Remaining Effect

03-50-01-558-805-A01 Non OEW Catering Equipment Added Effect

03-50-01-558-806-A01 Potable Water Removed Effect03-50-01-558-807-A01 Cockpit and Cabin Crew Removed Effect

03-50-01-558-808-A01 Catering Equipment Removed Effect

03-50-01-558-809-A01 Hydraulic Fluid Removed Effect

03-50-01-558-810-A01 Large Components Removed / Missing

03-50-01-558-810-B01 Large Components Removed / Missing

T.O.C.Page 2

Jul 01/09


03-50-01-558-810-C01 Large Components Removed / Missing

03-50-01-558-810-D01 Large Components Removed / Missing

03-50-01-558-811-A01 Large Components Movement Effect

03-50-01-558-811-B01 Large Components Movement Effect

03-50-01-558-811-C01 Large Components Movement Effect

03-60-01 REFERENCE FOR CALCULATION03-60-01-001-A01 Information Required and Source Data

04 PREPARATION

04-00-00 PREPARATION04-00-00-001-A01 General

04-20-00 STABILIZING THE AIRCRAFT04-20-00-588-801-A01 Stabilizing the Aircraft

04-30-00 TETHERING THE AIRCRAFT04-30-00-001-A01 General04-30-00-556-801-A01 Mooring

04-40-00 GROUND ANCHORS04-40-00-001-A01 General

04-50-00 SOIL STABILITY04-50-00-001-A01 General

05 WEIGHT REDUCTION

05-00-00 WEIGHT REDUCTION05-00-00-001-A01 General

05-10-00 DEFUELING05-10-00-001-A01 General

05-20-00 FUEL SYSTEM DESCRIPTION05-20-00-001-A01 Fuel System Basic Description

05-20-00-002-A01 Tanks05-20-00-004-A01 Fuel Quantity Indicating System

T.O.C.Page 3

Jul 01/09


05-30-00 MOVING FUEL FOR CG CONTROL05-30-00-650-801-A01 Fuel Transfer

05-40-00 DEFUEL SCENARIOS05-40-00-001-A01 Defuel Scenarios

05-40-01 DEFUEL SCENARIO 1 NORMAL PRESSURE DEFUEL WITH ALLAIRCRAFT SYSTEMS SERVICEABLE

05-40-01-650-801-A01 Normal Pressure Defuel With All Aircraft Systems Serviceable

05-40-02 DEFUEL SCENARIO 2 DRAIN REMAINING FUEL05-40-02-650-801-A01 Drain Remaining Fuel

05-40-03 DEFUEL SCENARIO 3 DEFUEL USING AN EXTERNAL WIRINGHARNESS

05-40-03-650-802-A01 Defuel Using an External Wiring Harness

05-50-00 CARGO COMPARTMENTS05-50-00-005-A01 General

05-50-01 CARGO REMOVAL05-50-01-005-A01 Cargo Removal

05-60-00 REMOVAL OF LARGE COMPONENTS05-60-00-001-A01 General

06 LEVELING AND LIFTING

06-00-00 LEVELING AND LIFTING06-00-00-001-A01 General06-00-00-002-A01 Leveling/Lifting Obstructions

06-10-00 LOAD DETERMINATION06-10-00-970-801-A01 Vertical Loads Determination06-10-00-970-802-A01 Side loads on Jack Fittings

06-10-00-970-803-A01 Arc Movement Calculation

06-30-00 USE OF JACKS06-30-00-001-A01 General06-30-00-001-B01 General06-30-00-001-C01 General

T.O.C.Page 4

Jul 01/09


06-30-00-001-D01 General06-30-00-002-A01 Type of Jacks

06-30-00-581-802-A01 Jacking

06-30-00-581-801-A01 General Preparation and Instructions for Leveling and Lifting the Aircraftwith Jacks

06-40-00 USE OF PNEUMATIC LIFTING BAGS06-40-00-002-A01 General06-40-00-001-A01 Pneumatic Lifting Bags on Fuselage

06-40-00-003-A01 Pneumatic Lifting Bags on Wings

06-40-00-581-801-A01 General Preparation and Instructions for Leveling and Lifting the Aircraftwith Pneumatic Lifting Bags

06-50-00 USE OF CRANES06-50-00-001-A01 General06-50-00-581-803-A01 Forward Fuselage Crane Lifting

06-50-00-581-802-A01 Wing Rib Attachment Tool

06-50-00-581-801-A01 General Preparation and Instructions for Leveling and Lifting the Aircraftwith Cranes

07 MOVING THE AIRCRAFT

07-00-00 MOVING THE AIRCRAFT07-00-00-002-A01 General Preparation

07-20-00 PREPARING A ROADWAY07-20-00-001-A01 General

07-40-00 TOWING AND DEBOGGING07-40-00-001-A01 General

07-40-01 TOWING FROM THE NOSE LANDING GEAR07-40-01-584-801-A01 Towing on the NLG with a Towbar

07-40-01-584-802-A01 Towing on the NLG with a Towbarless Tractor

07-40-02 TOWING FROM THE MAIN LANDING GEAR07-40-02-584-801-A01 Towing with the Main Gear from the Front

07-40-02-584-802-A01 Towing with the Main Gear from the Rear

07-40-03 TOWING WITH DEFLATED TIRES

T.O.C.Page 5

Jul 01/09


07-40-03-584-801-A01 Towing with Deflated Tires

07-40-04 TOWING LOAD LIMITS07-40-04-001-A01 Load and Angle Limits

07-60-00 MOVING DAMAGED AIRCRAFT07-60-00-001-A01 General

07-60-01 MOVING DAMAGED AIRCRAFT ON TRAILERS07-60-01-001-A01 Moving Damaged Aircraft on Trailers

07-60-02 MOVING DAMAGED AIRCRAFT WITH CRANES07-60-02-001-A01 Moving Damaged Aircraft with Cranes

07-60-03 MOVING DAMAGED AIRCRAFT WITH SPECIALIZED EQUIPMENT

07-60-03-001-A01 Moving Damaged Aircraft with Specialized Vehicles

08 POST RECOVERY CORRECTIVE ACTIONS

08-00-00 POST RECOVERY CORRECTIVE ACTIONS08-00-00-001-A01 General

09 APPENDIX

09-00-00 APPENDIX09-00-00-001-A01 Introduction

09-10-01 UNITS AND CONVERSIONS09-10-01-002-A01 Units of Measurements09-10-01-001-A01 Conversion Tables

09-10-02 GLOSSARY OF TERMS09-10-02-001-A01 Definition of Terms09-10-02-003-A01 Abbreviations09-10-02-002-A01 Aircraft Reference Axes

09-10-03 AIRCRAFT DIMENSIONS09-10-03-001-A01 General09-10-03-001-B01 General09-10-03-001-C01 General09-10-03-001-D01 General

T.O.C.Page 6

Jul 01/09


09-10-04 AIRCRAFT STRUCTURAL SECTIONS09-10-04-001-A01 General

09-10-05 COMPOSITE MATERIALS09-10-05-001-A01 General

09-10-06 FUSELAGE FRAMES AND H-ARM TABLE09-10-06-001-A01 General

09-10-08 WING RIBS AND STATIONS09-10-08-001-A01 Wing Ribs and Stations

09-10-09 HORIZONTAL STABILIZERS RIBS AND STATIONS09-10-09-001-A01 General

09-10-10 DOOR SIZES AND LOCATIONS09-10-10-001-A01 General09-10-10-002-A01 Passenger/Crew Doors and Emergency Exit Doors

09-10-10-003-A01 Cargo Compartment Doors

09-10-10-004-A01 Nose Landing Gear Doors

09-10-10-005-A01 Main Landing-Gear Doors

09-10-10-006-A01 APU Doors

09-10-11 AIRCRAFT GROUND CLEARANCES09-10-11-001-A01 General09-10-11-001-B01 General09-10-11-001-C01 General09-10-11-001-D01 General

09-10-12 AIRCRAFT GROUND SERVICE CONNECTIONS09-10-12-001-A01 General09-10-12-002-A01 Hydraulic System

09-10-12-003-A01 Electrical System

09-10-12-004-A01 Fuel System

09-10-12-005-A01 Potable Water System

09-10-12-006-A01 Waste Water Disposal-System

09-10-13 AIRCRAFT GROUNDING POINTS09-10-13-001-A01 General

T.O.C.Page 7

Jul 01/09


09-10-14 CARGO COMPARTMENTS09-10-14-001-A01 General09-10-14-001-B01 General09-10-14-001-C01 General09-10-14-001-D01 General

09-10-15 LOCATION OF HAZARDOUS MATERIALS09-10-15-001-A01 General

09-10-16 LANDING GEARS09-10-16-001-A01 General

09-20-01 QUICK REFERENCE DATA

09-20-01-001-A01 General09-20-01-002-A01 Aircraft Recovery Logic Chart

09-20-01-004-A01 Airline Aircraft Recovery Process Document

09-20-01-005-A01 Off Runway Incident Reporting Proforma

09-20-01-869-801-A01 IATA Aircraft Recovery Quick Reference Check List

09-20-02 RECOVERY TEAM09-20-02-001-A01 Composition of the Recovery Team

09-30-01 AIRCRAFT RECOVERY EQUIPMENT TOOLING AND MATERIALS

09-30-01-001-A01 General09-30-01-002-A01 Airbus Specific Recovery Tools

09-30-02 AIRCRAFT RECOVERY TOOLING09-30-02-001-A01 General

09-30-03 IATP AIRCRAFT RECOVERY KITS09-30-03-001-A01 General09-30-03-002-A01 Example of IATP Recovery Kit

09-50-01 WEIGHT AND CG CALCULATION WORKSHEETS09-50-01-001-A01 Worksheets

T.O.C.Page 8

Jul 01/09


INTRODUCTION

01-00-00 INTRODUCTION

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 01-00-00-001-A01

General

1. This document is intended to provide, for areas which are under Airbus responsibility, aircraftcomprehensive details relative to the procedures, planning, equipment and tooling to effectivelyrecover the A318, A319, A320 or A321 aircraft. The airlines and airport authorities can use thisinformation as a planning tool for aircraft recovery preparations.Aircraft recovery is an operation that is the result of an unplanned incident and as such, advancepreparations should be made. These preparations should include the establishment of an AircraftRecovery Team, aircraft recovery training, listings of aircraft recovery equipment availability and thedevelopment of an internal Aircraft Recovery Process Document.These are general procedures and will vary according to the individual incident and the equipmentavailable. In most cases the recovery will be carried out under abnormal conditions of both weatherand aircraft attitude.Country and state rules and regulations have to be followed, even though they may impede therecovery operation. Make sure that the relevant authorities have formally released the aircraft, beforestarting the aircraft recovery process. For further information on aircraft accident and incidentinvestigation see ICAO Annex 13.Personal safety and prevention of secondary damage are emphasized in this document.The data provided in this document is based on a serviceable aircraft in a normal attitude (exceptwhere specified). If the aircraft is in a different condition, the data will have to be adjustedaccordingly.Procedures for aircraft recovery from water are not covered by this document.It is recommended that the individual airlines share their aircraft recovery experiences with theaircraft manufacturer and groups such as the International Airline Transport Association (IATA),Aircraft Recovery Task Force (ARTF) and the International Airline Technical Pool (IATP). TheInternational Airline Technical Pool as well as some airports and airlines could provide AircraftRecovery Kits, at strategic locations around the world. Information about these groups is available atthe following web sites:- http://www.iata.org- http://www.iatp.com

NOTE : IATP website and recovery kits are available for IATP members only.

NOTE : This chapter gives references to web sites for information only. Airbus shall not be heldliable for web site or document content and for update or change of addresses.

01-00-00Page 1

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**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 01-00-00-002-A01

Important Notice to Users of this Document

1. GeneralThe technical data contained in this Aircraft Recovery Manual (ARM) is intended only for generalplanning, preparations and establishing procedures for the recovery of a disabled A318, A319, A320or A321 aircraft with consideration given for return to service.Airbus recommends that A318, A319, A320 or A321 operators and airport authorities use the data inthis manual to develop recovery schemes based on various scenarios, using the equipment available,typical situations and the recommendations included in the ATA specification.Airbus strongly recommends that all data and actions related to the recovery are recorded to ensurethat all necessary corrective actions are taken prior to release to service of the aircraft.The data given in this document is accurate at the date of publication. In case of any conflict, theAircraft Technical Specification shall take precedence.This manual does not include data with regards to any optional modifications. These additions mayhave an impact on the weight and CG position calculations, defueling and cargo loading procedures.Contact Airbus for further information.

2. DisclaimerTHE USER HEREBY WAIVES, RELEASES AND RENOUNCES ALL WARRANTIES,OBLIGATIONS AND LIABILITIES OF AIRBUS AND RIGHTS, CLAIMS AND REMEDIES OF THEUSER AGAINST AIRBUS, EXPRESS OR IMPLIED, ARISING BY LAW OR OTHERWISE, WITHRESPECT TO ANY NON-CONFORMITY OR DEFECT IN THIS DOCUMENT, INCLUDING BUTNOT LIMITED TO:- ANY WARRANTY AGAINST HIDDEN DEFECTS;- ANY IMPLIED WARRANTY OF MERCHANTABILITY OR FITNESS;- ANY IMPLIED WARRANTY ARISING FROM COURSE OF PERFORMANCE, COURSE OF

DEALING OR USAGE OF TRADE;- ANY OBLIGATION, LIABILITY, RIGHT, CLAIM OR REMEDY, WHETHER CONTRACTUAL

OR DELICTUAL AND WHETHER OR NOT ARISING FROM AIRBUS’S NEGLIGENCE,ACTUAL OR IMPUTED, AND

- ANY OBLIGATION, LIABILITY, RIGHT, CLAIM OR REMEDY FOR LOSS OR DAMAGE TOPROPERTY.

AIRBUS SHALL HAVE NO OBLIGATION OR LIABILITY, HOWSOEVER ARISING, FOR LOSS OFUSE, REVENUE OR PROFIT OR FOR ANY OTHER DIRECT, INCIDENTAL ORCONSEQUENTIAL DAMAGES WITH RESPECT TO ANY NON-CONFORMITY OR DEFECT INTHIS DOCUMENT.AIRBUS SHALL HAVE NO OBLIGATION OR LIABILITY WITH RESPECT TO THE BEHAVIOROF TOOLING USED FOR THE RECOVERY OF THE AIRCRAFT.

01-00-00Page 2

Jul 01/09


01-00-02 SEQUENCE OF THE DOCUMENT

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 01-00-02-001-A01

General

1. This manual obeys the ATA iSpec 2200 specification format.

2. This document uses a three-part identification reference (XX-XX-XX), in which each pair of digitmeans : CHAPTER, SECTION and SUBJECT.

3. The ARM contains two categories of data.

A. DescriptionThis part gives the general description of the aircraft or systems, data related to aircraftrecovery (recovery team, recovery charts, landing gear, fuel ...) and worksheets.For details about the numbering of the description topics, see FIGURE 01-00-02-991-001-A.

B. TaskFor details on the task oriented ARM, see DESC 01-00-02-002-A01.For details about the numbering of the tasks, see FIGURE 01-00-02-991-002-A.

4. Warnings, Cautions and Notes.- WARNING: Calls attention to use of materials, processes, methods, procedures or limits that

must be carefully obeyed to prevent injury or death.- CAUTION: Calls attention to methods and procedures that must be obeyed to prevent damage to

equipment.- NOTE: Calls attention to methods that make the work easier or gives explanations.

5. AbbreviationsAll the abbreviations used in this manual are detailed in 09-10-02.

6. Revision bars.The revision bars show that the content is either new or revised.

7. This manual recommends that the recovery team makes and issues records to help aircraft return toservice and carefully monitors the implementation of corrective actions.See 08-00-00.

01-00-02Page 1

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

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01-00-02Page 2

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

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01-00-02Page 3

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 01-00-02-002-A01

Task Oriented ARM

1. GeneralIn the ARM, the procedures are contained in tasks.The task is a logical sequence of the procedure steps and is broken down into subtasks.The subtask gives all the details of the significant steps of the procedure.For task numbering, see DESC 01-00-02-001-A01.

2. Function CodesEach task and subtask has a function code related to its subject.

FunctionCode

Definition Task/Subtask

000 Removal Task

010 Remove/Open For Access Task/Subtask

020 Remove Unit/Component/Disconnect/Loosen/Remove Item Task/Subtask

040 Deactivation Task/Subtask

081 Remove Safety Locks Task/Subtask

200 Inspection/Check Task

284 Inspection of damage Subtask

285 Survey Damage and Terrain Task/Subtask

481 Install Safety Locks Task/Subtask

500 Material and Aircraft Handling Task/Subtask

556 Mooring Task/Subtask

558 Weight and CG Management Task/Subtask

581 Leveling/Lifting Task/Subtask

582 Moving the Aircraft Task/Subtask

583 Shoring Task/Subtask

584 Towing Task/Subtask

585 Taxiing Task/Subtask

586 Lowering Task/Subtask

587 Debogging Task/Subtask

588 Stabilizing Task/Subtask

650 Fueling/Defueling Task/Subtask

680 Drain Fluid Task/Subtask

862 De-energize Electrical Network Task/Subtask

01-00-02Page 4

Jul 01/09


FunctionCode

Definition Task/Subtask

866 Flight Control Surfaces Movement Task/Subtask

867 Landing Gear Movement Task/Subtask

869 Miscellaneous Task/Subtask

970 Data Recording/Calculating Task/Subtask

972 Damage Recording Subtask

980 Manual Operation or Positioning Subtask

Task/Subtask Function Codes Definition

TABLE 1

3. Task StructureEach recovery task is broken down into the paragraphs that follow:

A. Task Supporting Data

(1) GeneralThis paragraph gives general information and a short description of the procedure.

(2) InspectionThis paragraph gives instructions to do a preliminary inspection if necessary.

(3) Job Set Up DataThis paragraph collects all the generic data which are not in the Job Set Up Informationand are necessary to do the actions described in the procedure.

(4) Job Set Up InformationThis paragraph collects all materials, tools and referenced information necessary to do theactions described in the procedure.

B. ProcedureThis paragraph is broken down into subtasks.

(1) SubtasksThe Subtasks contain actions/instructions to do the procedure.

C. FiguresThis part contains all illustrations related to the procedure.

01-00-02Page 5

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 01-00-02-003-A01

Content

1. MANUAL FRONT MATTERThis part of the manual contains the preliminary pages.Items in this part are:

A. The manual front page.

B. The highlights which give the description of changes at subtask and figure level.

C. The list of effective content which gives for each task, subtask and figure the last revision datewith a change code (which is also used in the highlights):- blank: no changes- R: revised content- N: new content- D: deleted content.

D. The table of contents which is the list of chapters, subjects, tasks and descriptions contained inthe manual.

2. Chapter 01 - INTRODUCTIONThis chapter gives general data and information on the A318, A319, A320 or A321 aircraft.Items in this chapter are:

A. A list of related documents in which it is possible to find more information.

B. A general aircraft description.

3. Chapter 02 - SURVEYThis chapter gives the information that follow for areas which are under Airbus responsibility:

A. An aircraft recovery logic chart, which has been developed for the Aircraft Recovery Managerand his team, to help obey the necessary steps of the recovery process. It is used with a specificCHAPTER/SECTION/SUBJECT of the ARM.

B. Details on initial inspection, site survey, soil stability, weather conditions and equipment.

C. Health and safety issues related to aircraft recovery.

4. Chapter 03 - WEIGHT AND CG MANAGEMENTThis chapter contains the items that follow:

A. Weight, H-arm, Y-arm and Z-arm management, with general and specific information foroperations such as calculation of the NRW, associated H-arm, Y-arm and Z-arm locations andCG.

B. The names of documents where it is possible to find aircraft weight and balance data.

C. The effect of different elements on the CG, such as large aircraft components, fuel, payload…

01-00-02Page 6

Jul 01/09


5. Chapter 04 - PREPARATIONThis chapter contains the details that follow:

A. The tasks which are necessary before leveling/lifting the aircraft (manual operation of flightcontrol surfaces, tethering, ground anchoring, check of weight, H-arm and Y-arm, etc.).

B. The tethering procedure.

C. General information and instructions for the manual operation of different units or equipmentssuch as landing gears, flaps, flight controls, cargo doors…

6. Chapter 05 - WEIGHT REDUCTIONThis chapter gives:

A. Detailed information on the aircraft fuel system.

B. The way to manually find the fuel quantity.

C. Various defueling scenarios.

D. Detailed information on payload removal.

E. The removal procedure of the major components.

7. Chapter 06 - LEVELING AND LIFTINGThis chapter gives details on:

A. The basic means of leveling/lifting the aircraft.

(1) Jacks,

(2) Pneumatic Lifting Bags,

(3) Cranes.

B. The method to calculate expected load, travel range and arc movement based on aircraftattitude, NRW and CG calculated in Chapter 03.

C. Detailed leveling/lifting scenarios.

8. Chapter 07 - MOVING THE AIRCRAFTThis chapter gives:

A. Debogging or towing methods and aircraft limits.

B. Procedures to be implemented to return a damaged aircraft to the hard surface.

9. Chapter 08 - POST RECOVERY CORRECTIVE ACTIONSThis chapter gives:

A. A link to the post recovery AMM inspection.

B. An explanation about the need of recording and monitoring corrective actions during therecovery operation.

10. Chapter 09 - APPENDIXThe appendices give general information on:

A. Units and Measurements.

01-00-02Page 7

Jul 01/09


B. Glossary of terms and list of abbreviations.

C. General aircraft description.

D. Recovery preparation.

E. Tooling and equipment.

F. Calculation worksheets.

01-00-02Page 8

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**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 01-00-02-004-A01

Effectivity Management

1. The Aircraft Recovery Manual is issued to give the necessary data for A318, A319, A320 or A321aircraft which are necessary to accomplish a recovery.The configuration is managed at the aircraft level:- A318-100- A319-100- A320-100- A320-200- A321-100- A321-200

01-00-02Page 9

Jul 01/09


01-00-03 DEFINITIONS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 01-00-03-001-A01

General

1. Terms DefinitionsChapter DESC 09-10-02-001-A01 gives the definition of terms related to aircraft recovery.

2. Abbreviations DefinitionsChapter DESC 09-10-02-003-A01 gives the definitions of abbreviations related to aircraft recovery.

01-00-03Page 1

Jul 01/09


01-10-01 RELATED DATA

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 01-10-01-002-A01

Airbus Data

1. GeneralIf necessary, you can find additional information/data in the documents that follow:- A318, A319, A320 or A321 Aircraft Characteristics (AC)- A318, A319, A320 or A321 Aircraft Maintenance Manual (AMM)- A318/A319/A320/A321 Illustrated Parts Catalog (IPC)- A318, A319, A320 or A321 Structural Repair Manual (SRM)- A318, A319, A320 or A321 Maintenance Facility Planning Manual (MFP)- A318, A319, A320 or A321 Weight and Balance Manual (WBM)- A318/A319/A320/A321 Illustrated Tool and Equipment Manual (TEM)- A319/A320/A321 Cargo Loading System Manual (CLS)- List of Radioactive and Hazardous Elements Manual (LRE)- CFM56 Engine Manual- IAE V2500 Engine Manual (A319, A320 or A321 only)- PW 6000 Engine Manual (A318 only)- Airn@v, AirbusWorld, …

01-10-01Page 1

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**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 01-10-01-001-A01

Other Data

1. Web SitesThis topic gives references to web sites for information only. This list is not exhaustive and is madefrom the data available to Airbus at issue of the ARM.- http://www.iata.org- http://www.iatp.com



2. Publications - Manuals - DocumentsThis topic gives references to non-Airbus manuals or documents for information only. This list is notexhaustive and is made from the data available to Airbus at issue of the ARM. Airbus shall not beheld liable for document content.- Country Regulation- ICAO Annex 14- ICAO Annex 13- ICAO 9137 Part 5- FAA AC 150/5200-31A- FAR 139.325 Airport Emergency Plan- JAR/FAR 145

3. Airline DocumentsThis topic gives references to airline documents for information only. This list is not exhaustive.- Airline Aircraft Recovery Process Documents (see DESC 09-20-01-004-A01)- Airline Load and Trim Sheet Document- Airline Weight and Balance Manual- Airline Aircraft Modification Record

01-10-01Page 2

Jul 01/09


01-20-01 GENERAL AIRCRAFT CHARACTERISTICS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 01-20-01-001-A01

General Aircraft Description

1. The A320 Family of aircraft are subsonic single-aisle aircraft. These aircraft are suitable forpassengers and cargo commercial transport.They have two turbofan engines under the wings:- CFM 56-5 engine,- IAE V2500 engine (A319, A320 or A321)- PW 6000 engine (A318 only).The A320 Family aircraft have:- A standard configuration of 3 main fuel tanks (1 tank per wing and a center tank in the center

wing box). One or more Additional Center Tanks (ACT) can be installed in the cargocompartments, depending on the airline configuration.

- 1 standard 2.5 in refuel/defuel coupling under the wing and 1 gravity refuel cap on each wing(related to the aircraft configuration),

- 2 twin-wheel main landing gears (standard configuration) or 2 four-wheel bogies MLG (optional,on A320 only),

- 1 nose landing gear with two wheels,- 1 potable water tank in the pressurized section of the fuselage,- A waste water tank,- A lower deck forward cargo compartment,- A lower deck aft cargo compartment,- A lower deck bulk cargo compartment (related to the aircraft configuration).

2. The appendix gives detailed aircraft description.See 09-00-00.

01-20-01Page 1

Jul 01/09


**ON A/C A318-100

DESC 01-20-01-002-A01

General Aircraft Data

1. This section gives general data (weight, payload, fuel capacity, ...) related to the A318-100 aircraft.Refer to the operator’s documentation for accurate values related to the specific aircraft.

Weight Variant WV000 WV001 WV002 WV003 WV004

Maximum RampWeight (MRW)Maximum TaxiWeight (MTW)

59400 kg(130955 lb)

61900 kg(136466 lb)

63400 kg(139773 lb)

64900 kg(143080 lb)

66400 kg(146387 lb)

Maximum TakeoffWeight (MTOW)

59000 kg(130073 lb)

61500 kg(135584 lb)

63000 kg(138891 lb)

64500 kg(142198 lb)

66000 kg(145505 lb)

Maximum LandWeight (MLW)

56000 kg(123459 lb)

56000 kg(123459 lb)

57500 kg(126766 lb)

57500 kg(126766 lb)

57500 kg(126766 lb)

Maximum ZeroFuel Weight(MZFW)

53000 kg(116845 lb)

53000 kg(116845 lb)

54500 kg(120152 lb)

54500 kg(120152 lb)

54500 kg(120152 lb)

Operating EmptyWeight (OEW) -Typical

With CFM Engines : 38818 kg (85579 lb)With PW Engines : 38661 kg (85233 lb)

Maximum Payloadwith CFM Engines

14182 kg(31266 lb)

15682 kg(34573 lb)

Maximum Payloadwith PW Engines

14339 kg(31612 lb)

15839 kg(34919 lb)

Accommodation Typical Single Class Layout : 136 Seats

23859 l (6303 US gal)Usable FuelCapacity(Density = 0.785kg/l)

18729 kg (41290 lb)

Volume of CargoCompartments

22.84 m3

(806.59 ft3)

Aircraft Data

TABLE 1

01-20-01Page 2

Jul 01/09


Weight Variant WV005 WV006 WV007 WV008


68400 kg(150796 lb)

56400 kg(124341 lb)

61400 kg(135364 lb)

64400 kg(141978 lb)


68000 kg(149914 lb)

56000 kg(123459 lb)

61000 kg(134482 lb)

64000 kg(141096 lb)


57500 kg(126766 lb)

56000 kg(123459 lb)

56000 kg(123459 lb)

56000 kg(123459 lb)


54500 kg(120152 lb)

53000 kg(116845 lb)

53000 kg(116845 lb)

53000 kg(116845 lb)


With CFM Engines : 38818 kg (85579 lb)With PW Engines : 38661 kg (85233 lb)


15682 kg(34573 lb)

14182 kg(31266 lb)

Maximum Payloadwith PW Engines

15839 kg(34919 lb)

14339 kg(31612 lb)


23859 l (6303 US gal)Usable FuelCapacity(Density = 0.785kg/l)

18729 kg (41290 lb)


22.84 m3

(806.59 ft3)

Aircraft Data

TABLE 2

01-20-01Page 3

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**ON A/C A319-100

DESC 01-20-01-002-B01





64400 kg(141978 lb)

70400 kg(155205 lb)

75900 kg(167331 lb)

68400 kg(150796 lb)


64000 kg(141096 lb)

70000 kg(154324 lb)

75500 kg(166449 lb)

68000 kg(149914 lb)

Maximum LandWeight(MLW)

61000 kg(134482 lb)

61000 kg(134482 lb)

62500 kg(137789 lb)

61000 kg(134482 lb)

Maximum Zero FuelWeight(MZFW)

57000 kg(125663 lb)

57000 kg(125663 lb)

58500 kg(128970 lb)

57000 kg(125663 lb)


With CFM Engines : 39725 kg (87579 lb)With IAE Engines : 39826 kg (87801 lb)


17275 kg(38085 lb)

18775 kg(41392 lb)

17275 kg(38085 lb)

Maximum Payloadwith IAE Engines

17174 kg(37862 lb)

18674 kg(41169 lb)

17174 kg(37862 lb)


23859 l(6303 US gal)Usable Fuel Capacity

(Density = 0.785kg/l) 18729 kg

(41290 lb)

Volumeof CargoCompartments

27.66 m3

(976.80 ft3)

Aircraft Data

TABLE 1

01-20-01Page 4

Jul 01/09




68400 kg(150796 lb)

70400 kg(155205 lb)

73900 kg(162922 lb)

75900(167331 lb)


68000 kg(149914 lb)

70000 kg(154324 lb)

73500 kg(162040 lb)

75500 kg(166449 lb)


62500 kg(137789 lb)

62500 kg(137789 lb)

62500 kg(137789 lb)

61000 kg(134482 lb)

Maximum Zero FuelWeight (MZFW)

58500 kg(128970 lb)

58500 kg(128970 lb)

58500 kg(128970 lb)

57000 kg(125663 lb)




18775 kg(41392 lb)

17275 kg(38085 lb)


18674 kg(41169 lb)

17174 kg(37862 lb)




(41290 lb)


27.66 m3

(976.80 ft3)

Aircraft Data

TABLE 2



64400(141978 lb)

66400(141978 lb)

66400(141978 lb)

62400(137568 lb).


64000 kg(141096 lb)

66000 kg(145505 lb)

66000 kg(145505 lb)

62000 kg(136687 lb)

01-20-01Page 5

Jul 01/09




62500 kg(137789 lb)

62500 kg(137789 lb)

61000 kg(134482 lb)

61000 kg(134482 lb)


58500 kg(128970 lb)

58500 kg(128970 lb)

57000 kg(125663 lb)

57000 kg(125663 lb)




18775 kg(41392 lb)

17275 kg(38085 lb)


18674 kg(41169 lb)

17174 kg(37862 lb)




(41290 lb)


27.66 m3

(976.80 ft3)

Aircraft Data

TABLE 3

01-20-01Page 6

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**ON A/C A320-100 A320-200

DESC 01-20-01-002-C01


**ON A/C A320-100


Weight Variant WV000 WV001 WV002

Maximum Ramp Weight(MRW)Maximum Taxi Weight(MTW)

68400 kg(150796 lb)

66400 kg(146387 lb)

68400 kg(150796 lb)

Maximum Takeoff Weight(MTOW)

68000 kg(149914 lb)

66000 kg(145505 lb)

68000 kg(149914 lb)

Maximum Land Weight(MLW)

63000 kg (138891 lb)


59000 kg (130073 lb)

Operating Empty Weight(OEW) - Typical

With CFM Engines : 41244 kg (90927 lb)


17756 kg(39145 lb)

18556 kg(40909 lb)


23667 l (6252 US gal)Usable Fuel Capacity(Density = 0.785 kg/l) 18578 kg (40957 lb)


37.42 m3 (1321.47 ft3)

Aircraft Data

TABLE 1

**ON A/C A320-200


01-20-01Page 7

Jul 01/09




73900 kg(162922 lb)

68400 kg(150796 lb)

70400 kg(155205 lb)

75900 kg(167331 lb)


73500 kg(162040 lb)

68000 kg(149914 lb)

70000 kg(154324 lb)

75500 kg(166449 lb)


64500 kg (142198 lb)


60500 kg (133380 lb)




19256 kg(42452 lb)


19155 kg(42230 lb)


23859 l (6303 US gal)26759 l (7069 US gal) with 1 ACT - 29659 l (7835 US gal) with 2 ACT

Usable FuelCapacity(Density = 0.785kg/l)

18729 kg (41290 lb)21005 kg (46308 lb) with 1 ACT - 23282 kg (51328 lb) with 2 ACT


37.42 m3 (1321.47 ft3)

Aircraft Data

TABLE 2



71900 kg(158512 lb)

67400 kg(148592 lb)

66400 kg(146387 lb)

77400 kg(170638 lb)


71500 kg(157630 lb)

67000 kg(147710 lb)

66000 kg(145505 lb)

77000 kg(169756 lb)


64500 kg (142198 lb)

01-20-01Page 8

Jul 01/09




60500 kg (133380 lb)




19256 kg(42452 lb)

19256 kg(42452 lb)


19155 kg(42230 lb)

19155 kg(42230 lb)






37.42 m3 (1321.47 ft3)

Aircraft Data

TABLE 3



73900 kg(162922 lb)

75900 kg(167331 lb)

77400 kg(170638 lb)

75900 kg(167331 lb)


73500 kg(162040 lb)

75500 kg(166449 lb)

77000 kg(169756 lb)

75500 kg(166449 lb)


64500 kg(142198 lb)

66000 kg(145505 lb)


61000 kg(134482 lb)

62500 kg(137789 lb)




19756 kg(43555 lb)

21256 kg(46861 lb)

01-20-01Page 9

Jul 01/09




19655 kg(43332 lb)

21155 kg(46639 lb)






37.42 m3 (1321.47 ft3)

Aircraft Data

TABLE 4



77400 kg(170638 lb)

71900 kg(158512 lb)

73900 kg(162922 lb)

78400 kg(172842 lb)

73900 kg(162922 lb)


77000 kg(169756 lb)

71500 kg(157630 lb)

73500 kg(162040 lb)

78000 kg(171961 lb)

73500 kg(162040 lb)


66000 kg(145505 lb)

64500 kg(142198 lb)


62500 kg(137789 lb)

61000 kg(134482 lb)

61500 kg(135584 lb)

61000 kg(134482 lb)

62500 kg(137789 lb)




21256 kg(46861 lb)

19756 kg(43555 lb)

20256 kg(44657 lb)

19756 kg(43555 lb)

21256 kg(46861 lb)


21155 kg(46639 lb)

19655 kg(43332 lb)

20155 kg(44434 lb)

19655 kg(43332 lb)

21155 kg(46639 lb)





01-20-01Page 10

Jul 01/09




37.42 m3 (1321.47 ft3)

Aircraft Data

TABLE 5

01-20-01Page 11

Jul 01/09


**ON A/C A321-100 A321-200

DESC 01-20-01-002-D01


**ON A/C A321-100




83400 kg(183865 lb)

85400 kg(188275 lb)

83400 kg(183865 lb)

85400 kg(188275 lb)

78400 kg(172842 lb)


83000 kg(182984 lb)

85000 kg(187393 lb)

83000 kg(182984 lb)

85000 kg(187393 lb)

78000 kg(171961 lb)


73500 kg(162040 lb)

73500 kg(162040 lb)

74500 kg(164244 lb)

74500 kg(164244 lb)

73500 kg(162040 lb)


69500 kg(153221 lb)

69500 kg(153221 lb)

70500 kg(155426 lb)

70500 kg(155426 lb)

69500 kg(153221 lb)




22644 kg(49921 lb) TBD

23644 kg(52126 lb)

22644 kg(49921 lb)


22541 kg(49694 lb) TBD

23541 kg(51899 lb)

22541 kg(49694 lb)






51.72 m3 (1826.47 ft3)

Aircraft Data

TABLE 1

01-20-01Page 12

Jul 01/09




83400 kg(183865 lb)

78400 kg(172842 lb)

80400 kg(177252 lb)

89400 kg(197093 lb)


83000 kg(182984 lb)

78000 kg(171961 lb)

80000 kg(176370 lb)

89000 kg(196211 lb)


75000 kg(165347 lb)

74500 kg(164244 lb)

73500 kg(162040 lb)

75000 kg(165347 lb)


71000 kg(156528 lb)

70500 kg(155426 lb)

69500 kg(153221 lb)

71500 kg(157630 lb)




24144 kg(53228 lb)

23644 kg(52126 lb)

22644 kg(49921 lb)

24644 kg(54331 lb)


24041 kg(53001 lb)

23541 kg(51899 lb)

22541 kg(49694 lb)

24541 kg(54104 lb)






51.72 m3 (1826.47 ft3)

Aircraft Data

TABLE 2

**ON A/C A321-200




89400 kg(197093 lb)

93400 kg(205912 lb)

89400 kg(197093 lb)

91400 kg(201502 lb)

01-20-01Page 13

Jul 01/09




89000 kg(196211 lb)

93000 kg(205030 lb)

89000 kg(196211 lb)

91000 kg(200621 lb)


75500 kg(166449 lb)

77800 kg(171520 lb)

77800 kg(171520 lb)

77800 kg(171520 lb)


71500 kg(157630 lb)

73800 kg(162701 lb)

73800 kg(162701 lb)

73800 kg(162701 lb)



MaximumPayloadwith CFM Engines

24644 kg(54331 lb)

26944 kg(59401 lb)

MaximumPayloadwith IAE Engines

24541 kg(54104 lb)

26841 kg(59174 lb)






51.72 m3 (1826.47 ft3)

Aircraft

TABLE 3



87400 kg(192684 lb)

85400 kg(188275 lb)

83400 kg(183865 lb)

83400 kg(183865 lb)


87000 kg(191802 lb)

85000 kg(187393 lb)

83000 kg(182984 lb)

83000 kg(182984 lb)


75500 kg(166449 lb)

75500 kg(166449 lb)

75500 kg(166449 lb)

73500 kg(162040 lb)


71500 kg(157630 lb)

71500 kg(157630 lb)

71500 kg(157630 lb)

69500 kg(153221 lb)

01-20-01Page 14

Jul 01/09






69500 kg(153221 lb)

22644 kg(49921 lb)


24541 kg(54104 lb)

22541 kg(49694 lb)






51.72 m3 (1826.47 ft3)

Aircraft Data

TABLE 4



80400 kg(177252 lb)

78400 kg(172842 lb)

85400 kg(188275 lb)

93900 kg(207014 lb)


80000 kg(176370 lb)

78000 kg(171961 lb)

85000 kg(187393 lb)

93500 kg(206132 lb)


73500 kg(162040 lb)

73500 kg(162040 lb)

77800 kg(171520 lb)

77800 kg(171520 lb)


69500 kg(153221 lb)

69500 kg(153221 lb)

73800 kg(162701 lb)

73800 kg(162701 lb)




22644 kg(49921 lb)

26944 kg(59401 lb)

01-20-01Page 15

Jul 01/09




22644 kg(49921 lb)

26841 kg(59174 lb)






51.72 m3 (1826.47 ft3)

Aircraft Data

TABLE 5

01-20-01Page 16

Jul 01/09


SURVEY

02-00-00 SURVEY

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 02-00-00-001-A01

General

1. IntroductionThe objective is to define a recovery scenario based on a recovery plan and implement it:- Without causing secondary damage,- By ensuring traceability of actions performed.The recovery must be set up and controlled according to a recovery process.If a recovery contributing factor (see FIGURE 02-00-00-991-001-A) changes or is not as expected,each section must be reviewed to reconsider the recovery process.The recovery process is detailed in chapter 02-10-01 and is valid when there is no worldwide recoverystandard procedure for events of an infinite variety, even if there are basic leveling techniques:- Use of Jacks (see 06-30-00),- Use of Pneumatic Lifting Bags (see 06-40-00),- Use of Cranes (see 06-50-00).The ARM planning chart, aircraft recovery logic chart or the IATA aircraft recovery quick referencechecklist could be used to support this recovery process (see 09-20-01).

2. Recovery Secondary DamageThe objective of a successful aircraft recovery operation is to move the aircraft from the incident oraccident site to a repair area or facility without causing any secondary damage.The secondary damage is a damage which is not due to the initial event, and can increase the repairtime. However, due to time or cost constraints, secondary damage will be accepted from involvedparties. In that case make sure that the time saving is acceptable in comparison with the cost.The insurance underwriters can probably contest any secondary damage. Therefore every step of therecovery process must be continually monitored with appropriate action taken to prevent it.

NOTE : The damage on airport infrastructure or field can be considered as secondary damage ifadequate action is not done in due time.

02-00-00Page 1

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

LOCATION OF RECOVERY AIRCRAFT SECURITY

MISCELLANEOUS

TOWING / DEBOGGING

AIRCRAFT LEVELING

AIRCRAFT LIFTING

AIRCRAFT TETHERING

TERRAIN ANALYSIS

AIRCRAFT AND TOOLINGSTABILITY

REPAIR TO ENABLERECOVERY

AIRCRAFT WEIGHT ANDBALANCE MANAGEMENT

INTENTIONALSECONDARY DAMAGE

OPERATION CONTROL−MONITORING REPORTING

POST RECOVERYACTIONS DUE TO

RECOVERY SCENARIO

AIRCRAFT RELEASEFROM INVESTIGATIVE

AUTHORITY− PLANNING− LEAD TIME− LOGISTICS− CONTRACT

RECOVERYSCENARIO

TOOLING AVAILABILITY

AIRCRAFT DAMAGEASSESSMENT FOR

RECOVERY PURPOSE

N_AR_020000_1_0010101_01_01

Recovery ProcessContributing Factors

FIGURE-02-00-00-991-001-A01

02-00-00Page 2

Jul 01/09


02-10-01 CHARTS AND GUIDES

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 02-10-01-001-A01

Aircraft Recovery Process

1. GeneralThe recovery methods used are specific to each recovery operation, are dependent on multiple driversand constraints, including non aircraft specific drivers, as well as the individual aircraft recoveryconsiderations.The recovery process can be divided into five basic sections:- Survey,- Planning,- Preparation,- Recovery,- Reporting.

A. Survey

(1) Before you get access to the incident or accident site and while waiting for release of theaircraft from the Investigative Authorities, some preliminary tasks can be carried out.Some general issues are:- Get and record the initial incident or accident data,- Secure the site: fire, theft and access control,- Confirm that members of the Aircraft Recovery Team are available,- Arrange delivery of any local aircraft recovery equipment,- Make communication with airport and Investigative Authorities,- Identify the hazardous materials which are on board,- Get an airport plan to assess aircraft or recovery team travel path difficulty, etc.

(2) After access to the incident or accident site, you must do a detailed inspection and arecord of the items that follow:- Integrity of the aircraft structure and landing gear,- Survey of the soil conditions,- Local weather conditions,- Personnel health and safety issues,- Environmental concerns.

(3) The other issues to consider if the incident took place at a secondary or internationalairport are:- Transportation of personnel and equipment,- Visas, passports and vaccinations certificates,- Hotels and local transport.

B. PlanningThe main planning issues are (not in order of importance) :

02-10-01Page 1

Jul 01/09


- Identification of your recovery drivers,- Adverse weather conditions or critical forecast which can have an impact on material

required, recovery plan and recovery team operation, etc.- Limitation of airport use with the disabled aircraft,- Type of leveling, lifting or removal plan,- Aircraft weight and balance management operation, if necessary,- Unserviceable aircraft systems,- Storage of removed fuel,- Aircraft movement possibility and path,- Compilation of all corrective actions, necessary logistics and planning,- Necessary tooling.

C. PreparationThe main preparation issues are (not necessary in the applicable order) :- Control weight and CG by removal or transfer of the required amount of fuel and payload,- Make the aircraft stable,- Assemble the required equipment for the leveling/lifting method that you will use,- Remove components which are damaged,- Remove components to help the weight reduction,- Test and stabilize the soil if necessary.

D. RecoveryThe main recovery issues are (in priority order) :- Obey the safety conditions for personnel,- Monitor and record load when you level, lift and move the aircraft,- Level the aircraft as required,- Lift the aircraft as required,- Move the aircraft.

E. ReportingIt is necessary to do the recovery records. The Recovery Manager must hand these records overto the maintenance team. They will be used to do the necessary corrective action and releasethe aircraft back to service, for systems and structure.

02-10-01Page 2

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 02-10-01-002-A01

Aircraft Recovery Logic Chart

1. GeneralThe Aircraft Recovery Logic Charts (see DESC 09-20-01-002-A01) are an aid for the AircraftRecovery Manager and his team. The recovery charts describe the necessary steps of the recoveryprocess and can be used as a checklist by ticking off the boxes when completed. Although detailed,the chart must be used with the complete ARM. These charts give the specific areas of the ARMwhere you can find additional and more detailed data on a specific subject.

02-10-01Page 3

Jul 01/09


02-20-01 INITIAL AIRCRAFT SURVEY

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 02-20-01-285-801-A01

Initial Aircraft Survey

1. GeneralA detailed aircraft condition report must be completed as soon as possible to help the basic approachto the recovery process, to ensure safety of the personnel and to anticipate the repairs. Theinspection and the subsequent report do not need to be as detailed for the recovery as for repair ofthe aircraft.Photographs, sketches, measurements, notes, etc. can complete the documentation. Digital cameras,video recorders and pocket audio recorders can help to record the data.The documentation will help engineering staff, insurance surveyors and manufacturer representativesto discuss the details of the recovery scenarios/options. This information will be helpful to fill in areport when the recovery is completed.The future airworthiness of the aircraft can be dependent on the accuracy of the data recorded duringthe recovery operation. These records must include accurate figures on all loads applied to theaircraft during the recovery.In most cases, the accident investigation will be more important than the aircraft recovery process.The objective of the accident investigation is to determine the cause of the incident or accident andprovide details to prevent the re-occurrence of such an event.Keep in mind that the time between the notification of the event and release of the aircraft by theInvestigative Authorities can be several hours.If the Investigative Authority asks for removal of the Aircraft Flight Data and Cockpit VoiceRecorders, qualified personnel must do it and obey AMM procedures. These units are to be handedover to the Investigative Authority. In return, the Investigative Authority will give you a receipt withthe aircraft registration and the serial numbers of the removed units.It is necessary to note current and forecast weather.

2. InspectionsIt is necessary to estimate the fuel quantity, the cargo on board.It is also necessary to identify and quantify hazardous materials with any required personnelprotective equipment.

3. Job Setup ReferencesNot Applicable.

02-20-01Page 1

Jul 01/09


4. Job Set-up Information

A. Referenced Information

REFERENCE DESIGNATIONAMM

Referenced Information

TABLE 1

5. Procedure

WARNING : DO NOT CLIMB ON, GO INTO OR GO BELOW THE AIRCRAFT UNTIL THEAIRCRAFT IS STABLE.

WARNING : MAKE SURE THAT THE AIRCRAFT IS CORRECTLY GROUNDED.

NOTE : The information or principle contained in this chapter are given as a guide to assist anaircraft recovery.

Subtask 02-20-01-284-001-A01

A. Inspection of Damage

(1) Without climbing on, going into or going below the aircraft, identify and record all obviousand visible damage. Note the location on the fuselage with frame (station) and stringernumbers, and on the wing with rib and station numbers.

(2) The types of damage include cracked, creased, distorted or torn fuselage and wing skinpanels and also missing or broken fasteners (bolts, rivets…) and fittings.

(3) These types of damage are signs of failed structural components and must be considered assuspect. These failed structural components cannot be relied on to carry their designedloads. It is necessary to do a more detailed inspection on these areas prior to leveling,lifting or moving the aircraft.

(4) It is necessary to record any evidence of fire or overheating.

(5) It is also necessary to identify missing and damaged components such as landing gear, flapsections and non-structural fairings. Broken fairings can be a sign of hidden damage toother structural areas.

(6) It is necessary to do a more detailed inspection on these areas prior to leveling, lifting ormoving the aircraft.

Subtask 02-20-01-680-001-A01

B. Fluid Leaks

(1) Fluid leaks must be identified.

02-20-01Page 2

Jul 01/09


(2) These fluid leakages can be fuel, hydraulic fluid, lavatory waste water, potable water andany fluid transported in the cargo compartments.At the first indication of a fluid leak, the airport or Investigative Authorities must call for ahazardous materials response company to contain these leaking fluids.

(3) Cap lines and manually close valves to stop or control fluid leaks. Or temporarily plug holesor openings to stop the flow. If there is a fuel leak, defueling must be a primary task.

NOTE : This step can be required at any point during the initial aircraft survey.

Subtask 02-20-01-862-001-A01

C. Batteries

(1) If there is any structural damage on the fuselage or wings, it is necessary to remove orisolate the aircraft batteries as soon as the aircraft is stable.

NOTE : This step can be required at any point during the initial aircraft survey.

(2) It is possible to keep the batteries connected if there is no structural or system damage.This can be useful later for the recovery process. This decision can be re-examined duringthe survey and recovery.

NOTE : At this point, it is possible to try to make the aircraft stable and safe so that it ispossible to do a detailed inspection in and below the aircraft.

Subtask 02-20-01-869-001-A01

D. Landing Gear

WARNING : MAKE SURE THAT LANDING GEAR DOWNLOCK PINS ARE INSTALLED IFTHEIR INSTALLATION IS POSSIBLE.

(1) If a landing gear malfunction caused the event, it can be possible to continue to use theaircraft landing gear to move the aircraft when lifted. It is necessary to make sure that thestructure and landing gear (when extended) can support the aircraft weight. Examples are:- One or more landing gear(s) remained retracted at touchdown,- One or more landing gear(s) collapsed after touchdown due to downlock failures,- One or more landing gear(s) folded or collapsed when the aircraft left the runway and

bogged down in mud, snow or sand.

(2) In these cases, it can be possible to extend and lock the landing gear down after lifting theaircraft and after carrying out temporary repairs to strengthen or brace damaged parts. Ifrepairs are necessary, it is usually less difficult and less time consuming to do these repairsthan to have secondary damage when moving the aircraft on a trailer or a recoverytransport vehicle.

(3) Make sure that spare landing-gear assemblies are available to replace damaged or missingones, if required.

02-20-01Page 3

Jul 01/09


02-20-02 INITIAL SITE SURVEY

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 02-20-02-285-801-A01

Initial Site Survey

1. GeneralThis procedure gives details on how to do a full survey of the incident site around the aircraft.

2. InspectionsNot Applicable.

3. Job Setup ReferencesGet an airport map from the airport authority (we recommend a topographical map, which includessubterranean infrastructure localization) of the incident area.

4. Procedure


Subtask 02-20-02-285-001-A01

A. Terrain

(1) If the ground is sufficiently flat, the recovery process can be more direct. It will be moredifficult to move the aircraft on a rolling terrain with hills and it can be necessary to gradethe ground.You can report on the airport site plan the position of the aircraft, the flatness, slopes,hills, width and depth of any ditches or culverts and surrounding vegetation. You canexamine the area to know if there is any animal life (rodents and snakes).

Subtask 02-20-02-285-002-A01

B. Soil Characteristics

(1) The load bearing capacity is very important. This information is necessary to set up thesupport equipment to level, lift or move the aircraft.It is also necessary to do the selection of the type of tethering. The type of ground anchorsis dependent on the soil properties.

(2) The type of soil can be noted in addition to the substrate. It is possible to use the rutsmade by the landing gear to identify the subsurface soil type.

(3) Subterranean airport infrastructure must be known.Signs of recent excavations must be noted. The airport site plan must be amended toindicate any of these areas. Signs of recent excavations usually show soft and unstableground.

02-20-02Page 1

Jul 01/09


This information is very important, as it will influence the path to move the aircraft duringthe recovery.

(4) One of the standards used to compare different soil conditions is the California BearingRatio or CBR.This test measures the load necessary to make a plunger of a standard area penetrate asoil sample. The information is recorded on a standard graph and the plot of the test givesthe CBR result of the soil test.The CBR is a procedure to put a figure on the inherent strength of the soil. The soil musthave a homogeneous CBR rating through a sufficient depth. For more details, you can referto a ground engineer.

(5) The possible effect of rainfall on the ground load bearing capabilities can change with thesurface hardness, smoothness or drainage.Use pumps to remove standing water and dig drainage ditches from the work area.

Subtask 02-20-02-500-001-A01

C. Access Routes

(1) Access routes to the incident site can be planned with the airport site map. In most cases,it is necessary to go across active runways.The air traffic control service must plan and control these routes.

(2) Carefully review of the path of the aircraft from the runway to the resting point.The distance to runways, taxiways and aprons, the type of soil, rut depth and terrain willall influence in which direction the aircraft will be moved once the actual recovery starts.

(3) Pavement requirements for the particular aircraft are derived from the static analysis ofloads imposed on the main landing gear struts.These main landing gear loads are used as the point of entry to the pavement designcharts (See AC-07-00-00).Make sure that the surfaces you will move the aircraft on are able to support these loads.

(4) Make sure that the specific ground tooling or road used to level, lift or move the aircraftare able to support aircraft load.

(5) Make sure that the loads applied to the aircraft are not more than aircraft allowable loads.

Subtask 02-20-02-869-001-A01

D. Weather

(1) Weather conditions can play a major role during aircraft recovery operations. Generalmeteorological conditions (temperature, wind speed and precipitation) must be recorded.

(2) Temperature, both extreme heat and extreme cold, will determine the type of clothing,meals and liquid intake for the manpower involved in the recovery. The need for shelterfrom heat or cold will also have to be determined.

02-20-02Page 2

Jul 01/09


(3) Forecast conditions must be acquired and recorded. The forecast will help to prepare thetype of personal protective clothing and to determine the recovery plan.

(4) Make sure that the required tooling can be used within forecast conditions.

(5) Wind and projected wind gust speeds will determine the amount of tethering and willinfluence any attempts at lifting the aircraft.

(6) Any type of precipitation will have consequences in the grading, soil support and generalrecovery operation.

02-20-02Page 3

Jul 01/09


02-30-01 LANDING GEAR

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 02-30-01-200-801-A01

Landing Gear Survey

1. General

WARNING : LET THE BRAKES AND THE WHEELS BECOME COOL BEFORE YOU GO NEARTHE LANDING GEAR. DO NOT APPLY A LIQUID OR GAS FIRE EXTINGUISHERDIRECTLY ON A HOT WHEEL OR BRAKE UNIT. IF YOU DO NOT OBEY THESEPRECAUTIONS, THERE IS A RISK OF EXPLOSION.

WARNING : MAKE SURE THAT THE LANDING GEAR AND DOOR TRAVEL RANGES ARECLEAR. MOVEMENT OF THE LANDING GEAR AND DOORS CAN CAUSE INJURYAND/OR DAMAGE.

WARNING : MAKE SURE THAT THE LANDING GEAR IS UPLOCKED BEFORE YOU OPENTHE GEAR DOORS MANUALLY. IF THE GEAR IS NOT UPLOCKED, THEWEIGHT OF THE GEAR CAN BE ON THE DOORS. IF YOU OPEN THE DOORS INTHIS CONDITION, THERE IS A RISK THAT THE LANDING GEAR WILL EXTENDBY GRAVITY AND CAUSE INJURY.

The principles outlined in this chapter are provided as a guide to assist aircraft recovery.The chapter gives the general inspections required to find the extent of any damage to the landinggear and the recommended steps required to recover the aircraft.You must do the applicable inspections before moving the aircraft.For the description of the landing gears, see 09-10-16.



REFERENCE DESIGNATIONTASK 02-30-01-481-801-A01 TASK 02-30-01-481-801-A01-Installation of the Safety Devices

on Landing Gears

09-10-16 09-10-16-LANDING GEARS04-20-00 04-20-00-STABILIZING THE AIRCRAFT07-60-00 07-60-00-MOVING DAMAGED AIRCRAFT07-40-03 07-40-03-TOWING WITH DEFLATED TIRES07-40-00 07-40-00-TOWING AND DEBOGGING06-00-00 06-00-00-LEVELING AND LIFTINGAMM 29-10-00-864AMM 24-41-00-862AMM 32-51-00-040AMM 32-40-00-040

02-30-01Page 1

Jul 01/09


REFERENCE DESIGNATIONFIGURE 02-30-01-991-001-A FIGURE 02-30-01-991-001-A-Landing Gear

FIGURE 02-30-01-991-002-A FIGURE 02-30-01-991-002-A-Landing Gear


TABLE 1

3. Procedure

Subtask 02-30-01-867-001-A01

A. Safety Precautions

(1) Make sure that the aircraft is stable, see 04-20-00.

(2) Make sure that the Ground Lock Pins are installed on the landing gear where possible, seeTASK 02-30-01-481-801-A01.

(3) Make sure that the MLG and NLG wheels are chocked where possible.

(4) Make sure that the Landing Gear Control Lever (6GA) is in the DOWN position and put awarning notice to tell people not to operate the landing gear.

(5) On the center pedestal, make sure that the Free-Fall Control-Handle is in normal positionand safe, see FIGURE 02-30-01-991-001-A.

(6) If the aircraft wheel brake hydraulic circuits are serviceable:

(a) On the center pedestal, see FIGURE 02-30-01-991-002-A, set the PARK BRK switchto the ON position.

(b) On the center panel, see FIGURE 02-30-01-991-002-A, make sure that the pressureindication on the triple-indicator is correct. The indicator must be in the Green area.

(c) Make sure that the Green and Yellow hydraulic systems are depressurized, see AMM29-10-00-864.

(d) Make sure that the aircraft electrical circuits are de-energised, see AMM24-41-00-862.

(7) Put safety barriers around the Landing Gear(s) that are not correctly extended anddownlocked.

Subtask 02-30-01-867-003-A01

B. Landing Gear Positions

(1) A Landing Gear can be found in the following conditions:

(a) Fully extended and downlocked.

(b) Not fully extended or retracted.

(c) Retracted and uplocks released (Landing Gear Doors closed).

02-30-01Page 2

Jul 01/09


(d) Retracted and uplocked.

(e) Collapsed or missing.

(f) Bogged.

WARNING : IF THE LANDING GEAR DOES NOT FULLY EXTEND WHEN THE AIRCRAFTIS LEVEL, SAFETY THE LANDING GEAR TO PREVENT UNWANTEDMOVEMENT.

(2) Before doing the inspection, make sure you know the position of the Landing Gear.

(a) Landing Gear fully extended and downlocked, see TASK 02-30-01-481-801-A01:

1 Do the applicable inspection for that Landing Gear (NLG or MLG).

(b) Landing Gear not fully extended or retracted:

1 See 06-00-00 for the procedure to level and lift the aircraft.

2 It will be necessary to secure the Landing Gear to prevent it travelling furtherand becoming a danger to anyone or to the recovery operations.

3 To support the gear, put a hydraulic lifting platform (lifting capacity 7 tonnes)under the Landing Gear to be supported. Make sure that the lifting surface iscovered with support materials, such as tires or foam, to protect the LandingGear from damage.

4 To further support the gear, raise the platform until the support materials makegood contact with the Landing Gear to prevent accidental movement of the gearduring the inspection.

5 You must make sure that all other ground lock pins are installed, then in thecockpit, rotate the free-fall extension-handle for three revolutions to clockwise.This will open the hydraulic system to RETURN and allow the unlocked leg tobe lifted. See FIGURE 02-30-01-991-001-A.


(c) Landing Gear Retracted and uplocked:

1 If the NLG is retracted and uplocked, it must be lowered and downlocked beforean inspection can be done, see TBD for the manual extension procedure.

2 If the MLG is retracted and uplocked, it must be lowered and downlocked beforean inspection can be done, see TBD for the manual extension procedure.

(d) Landing Gear Retracted and uplocks released (Landing Gear Doors closed) :

1 If the NLG is retracted with the Landing Gear Doors closed, see TBD for theprocedure to manually extend the gear, then do the applicable inspection.

2 If the MLG is retracted with the Landing Gear Doors closed, see TBD for theprocedure to manually extend the gear, then do the applicable inspection.

02-30-01Page 3

Jul 01/09


(e) Landing Gear Collapsed or missing:If a Landing Gear is collapsed, missing or unusable, see 07-60-00 for the procedure tomove a damaged aircraft using special recovery vehicles.

(f) Landing Gear locked down and bogged down:


2 See TBD for the debogging procedure.

Subtask 02-30-01-867-004-A01

C. Landing Gear Inspection

(1) Main Landing Gear

(a) Do a visual inspection of the Main Landing Gear, the attachments to the Airframe,the doors. Look for signs of distortions, cracks and ruptures. If this type of damage isfound on a component, it must be replaced before you move the aircraft.

(b) The following components can be removed if they are not usable or if they willimpede the recovery operation:- The wheel brake components, see AMM 32-40-00-040 for information on the

deactivation of brake components before you remove them- The Main Door- The Hinged and Fixed Fairings.

(c) If the repair or replacement of damaged components is not possible because of generalarea damage, the aircraft must be recovered on specialist recovery vehicles, see07-60-00.

(d) Do a visual inspection of the tires. If there are deflated tires, see 07-40-03 for theapplicable limitations.

(2) Nose Landing Gear

(a) Do a visual inspection of the Nose Landing Gear, the attachments to the Airframe,the two Forward and two Aft Doors. Look for signs of distortions, cracks andruptures. If this type of damage is found on a component, it must be replaced beforeyou move the aircraft.

(b) The following components can be removed if they are not usable or if they willimpede the recovery operation:- The Forward Doors- The Aft Doors- The Nosewheel Steering components.

(c) See AMM 32-51-00-040 for the procedure to deactivate the NWS.

(d) If the repair or replacement of damaged components is not possible because of generalarea damage, the aircraft must be recovered on specialized recovery vehicles, see07-60-00.

02-30-01Page 4

Jul 01/09


(e) If the NLG is bogged, see TBD. If the NLG is on a hard surface see 07-40-00

(f) Do a visual inspection of the tires. If there are deflated tires, see 07-40-03 for theapplicable limitations.

02-30-01Page 5

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

L/G EXTENSION/RETRACTION LEVER

L/G MANUAL EXTENSION HANDLE

N_AR_023001_1_0010101_01_00

G R A V I T Y

GEARE X T N

TURN

A

B

A

P U L L

GEAR R

AEG

B

Landing GearLG Control Lever and Free-Fall Control Handle

FIGURE-02-30-01-991-001-A01

02-30-01Page 6

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_023001_1_0020101_01_00

P S I x 1 0 0 0BRAKES

0

13

13

40

ACCU PRESS

PARKING BRK OFF

PARK BRKON

A

B

A

B

Landing GearBrakes - Indication and ControlFIGURE-02-30-01-991-002-A01

02-30-01Page 7

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 02-30-01-481-801-A01

Installation of the Safety Device on Landing Gears

1. General


WARNING : MAKE SURE THAT THE LANDING GEAR AND DOOR TRAVEL RANGES ARECLEAR. MOVEMENT OF THE LANDING GEAR AND DOORS CAN CAUSE INJURYAND/OR DAMAGE.

WARNING : MAKE SURE THAT, IF THE LANDING GEAR DOORS ARE OPEN, THEY ARESAFETIED BEFORE YOU INSTALL THE LANDING GEAR SAFETY-DEVICES. IFTHE LANDUNG GEAR DOORS ARE OPEN BUT NOT SAFETIED THERE IS ARISK THAT THEY VCAN CLOSE AND CAUSE INJURY.

WARNING : MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES AREIN POSITION BEFORE YOU START A TASK ON OR NEAR THE FLIGHTCONTROLS, THE FLIGHT CONTROL SURFACES, THE LANDING GEARS ANDRELATED DOORS AND COMPONENTS THAT MOVE. MOVEMENT OFCOMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND CAN CAUSEDAMAGE.

The chapter gives the recommended steps to install the safety devices on the landing gears andlanding gear doors prior to recover the aircraft.For the description of the landing gears, see 09-10-16.


3. Job Setup References

A. Safety PrecautionsMake sure that the aircraft is stable, see 04-20-00.Make sure that the MLG and NLG wheels are chocked where possible.Make sure that the Landing Gear Control Lever (6GA) is in the DOWN position and put awarning notice to tell people not to operate the landing gear.On the center pedestal, make sure that the Free-Fall Control-Handle is in normal position andsafe.

02-30-01Page 8

Jul 01/09



A. Fixtures, Tools, Test and Support

REFERENCE DESIGNATIOND23080000 PIN-GROUND LOCK, NLG

MZ23080000 PIN - NLG DOWNLOCK SAFETYDRT68031 SLEEVE - GROUND LOCKDRT68923 SLEEVE-GROUND LOCK460005833 GROUND LOCK SLEEVE460007280 SLEEVE-GROUNDLOCK460005835 GROUND LOCK SLEEVEDAH602734 GROUND LOCK SLEEVE98D32203502000 SAFETY PIN - NLG DOOR

Fixtures, Tools, Test and Support

TABLE 1

B. Referenced Information

REFERENCE DESIGNATION09-10-16 09-10-16-LANDING GEARS04-20-00 04-20-00-STABILIZING THE AIRCRAFTAMM 32-12-00-010-001AMM 32-22-00-010-001


TABLE 2

5. Procedure

Subtask 02-30-01-481-003-A01

A. Installation of the Safety Devices on the Landing Gears

(1) To install the left and right Main Landing Gear Safety Locks:

(a) If a landing gear door is open, make sure:- the ground door-opening handle is in the open position- the ground door-safety lock is installed, see SUBTASK 02-30-01-481-004-A01.

(b) Make sure that the piston rod of each lock stay actuating cylinder is clean.

NOTE : There are four alternative tools that can be used for this task:- DRT68031 SLEEVE - GROUND LOCK- DRT68923 SLEEVE-GROUND LOCK- 460005833 GROUND LOCK SLEEVE- 460007280 SLEEVE-GROUNDLOCK

02-30-01Page 9

Jul 01/09


(c) Remove the pin and open the GROUND LOCK SLEEVE.

(d) Make sure that the GROUND LOCK SLEEVE is clean and in the correct condition.

(e) Put the GROUND LOCK SLEEVE in position on the piston rod of each lock stayactuating cylinder.

(f) Close the GROUND LOCK SLEEVE and install the pin from the inboard side.

(g) Make sure that the flag is in view.

(2) To install the Nose Landing Gear Safety Lock:

(a) If a landing gear door is open, make sure:- the ground door-opening handle is in the open position- the ground door-safety lock is installed, see SUBTASK 02-30-01-481-004-A01.

(b) Make sure that the holes in the NLG lock stay are aligned.

NOTE : There are two alternative tools that can be used for this task:- D23080000 PIN-GROUND LOCK, NLG- MZ23080000 PIN - NLG DOWNLOCK SAFETY

(c) Make sure that the D23080000 PIN-GROUND LOCK, NLG or the MZ23080000 PIN -NLG DOWNLOCK SAFETY is in a clean and correct condition.

(d) Install the D23080000 PIN-GROUND LOCK, NLG or the MZ23080000 PIN - NLGDOWNLOCK SAFETY in the holes in the NLG lock stay.

(e) Make sure that the flag is in view.

Subtask 02-30-01-481-004-A01

B. Installation of the Safety Devices on the Landing Gears Doors

(1) To install the safety devices on the main landing gear doors:

(a) Open the applicable MLG door(s). See AMM 32-12-00-010-001.

1 Make sure that the piston rod of the MLG door actuating cylinder is clean.

(b) Remove the pins (1) and open the 460005835 GROUND LOCK SLEEVE or theDAH602734 GROUND LOCK SLEEVE.

(c) Make sure that the ground lock sleeve is in a clean and correct condition.

(d) Put a ground lock sleeve in position on the piston rod of each of the MLG dooractuating cylinders.

(e) Close the ground lock sleeve and install the pins (1) from the top.

(f) Make sure that the flag is in view.

(2) To install the safety devices on the nose landing gear doors:

(a) Open the NLG doors. See AMM 32-22-00-010-001.

(b) Make sure that the holes in the NLG doors and the hinges are aligned.

02-30-01Page 10

Jul 01/09


(c) Make sure that each 98D32203502000 SAFETY PIN - NLG DOOR is in a clean andcorrect condition.

(d) Install a 98D32203502000 SAFETY PIN - NLG DOOR through the holes in each NLGdoor and hinge.

(e) Make sure that the flag is in view.

02-30-01Page 11

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

FLAG

LOCKSTAYACTUATING

CYLINDER

N_AR_023001_1_0200101_01_00

LOCKSTAYACTUATINGCYLINDER

GROUND LOCK SLEEVE

FLAG

DOWNLOCKSAFETY PIN

LOCKSTAY

A

B

A

B

Landing GearInstallation of the Safety DevicesFIGURE-02-30-01-991-020-A01

02-30-01Page 12

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DOORACTUATINGCYLINDER

FLAG

DOOR HINGE

NLG DOOR

NLG DOORSAFETY PIN

FLAG

FOR DETAIL B, PROXIMITY SENSORS OMITTED FOR CLARITYNOTE:

MAIN DOOR

N_AR_023001_1_0210101_01_00

MLG DOORACTUATINGCYLINDER

1

A

LH SYMETRICAL

B

A

RH SHOWN

B

Landing Gear DoorsInstallation of the Safety DevicesFIGURE-02-30-01-991-021-A01

02-30-01Page 13

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 02-30-01-867-802-A01

Jacking for Wheel Change

1. General


WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLYINSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTEDMOVEMENT OF THE LANDING GEAR.

CAUTION : DO NOT DO THIS JACKING FOR WHEEL CHANGE PROCEDURE DURINGREFUELING OR DEFUELING PROCEDURES. IF THE AIRCRAFT IS ON JACKSAND IF A FIRE OR IMPORTANT FUEL SPILLAGE OCCURS IT WILL NOT BEPOSSIBLE TO MOVE THE AIRCRAFT.

This procedure gives details for the replacement of a wheel with deflated tires.


3. Job Setup ReferencesYou can lift the aircraft at its maximum weight.

Hydraulic Jack Data Capacity (min) Closed Height (max) Hydraulic Stroke (min)

Nose Gear 10000 daN (22481 lbf) 130 mm (5.12 in) 171 mm (6.73 in)

Nose Gear (usingInclined Blocks)

10000 daN (22481 lbf) 200 mm (7.87 in) 171 mm (6.73 in)

Main Gear (TwinWheel)

35000 daN (78683 lbf) 215 mm (8.46 in) 334 mm (13.15 in)

Main Gear (Four WheelBogie)

35000 daN (78683 lbf) 125 mm (4.92 in) 255 mm (10.04 in)

Hydraulic Jack Specifications

TABLE 1

NOTE : If both tires of the nose landing gear are deflated at the same time, the maximum closedheight of the hydraulic jack must be 128 mm (5.04 in). Use specific tool TMHCP07-00-00WHEEL CHANGE AXLE JACK.

02-30-01Page 14

Jul 01/09




REFERENCE DESIGNATIONGSE WHEEL CHANGE JACKTMHCP07-00-00 WHEEL CHANGE AXLE JACK


TABLE 2


REFERENCE DESIGNATIONAMM 32-41-12PB401AMM 05-51-15-200-001AMM 32-41-11PB401FIGURE 02-30-01-991-019-A FIGURE 02-30-01-991-019-A-Nose Landing Gear

FIGURE 02-30-01-991-022-A FIGURE 02-30-01-991-022-A-Nose Landing Gear

FIGURE 02-30-01-991-023-A FIGURE 02-30-01-991-023-A-Jacking for Wheel Change


TABLE 3

5. Procedure

Subtask 02-30-01-869-001-A01

A. Safety Precautions

(1) Make sure that the wheels are on the aircraft axis.

(2) Make sure that there is sufficient space around the aircraft.

(3) Make sure that the aircraft is clear to lift.

(4) Make sure that the aircraft is stable.

(5) Make sure that the jack adapter is in correct condition.

Subtask 02-30-01-581-001-A01

B. Jacking of the Nose Landing Gear

(1) See FIGURE 02-30-01-991-019-A.See TABLE 1 for hydraulic jack specifications.

(2) Install the wheel chocks on the main landing-gear wheels.

02-30-01Page 15

Jul 01/09


(3) Put the GSE WHEEL CHANGE JACK so that its adapter touches the ball-pad of the shockabsorber.

NOTE : If both tires of the nose landing gear are deflated at the same time, themaximum closed height of the hydraulic jack must be 128 mm (5.04 in). Usespecific tool TMHCP07-00-00 WHEEL CHANGE AXLE JACK.

(4) Make sure that the wheel jack is stable and in the vertical position.

(5) Make sure that this assembly is level.

(6) Operate the jack to lift the tire off the ground.

(7) Change the wheel, see AMM 32-41-12PB401.

(8) Operate the control of the hydraulic jack slowly to lower the aircraft. Do not lower theaircraft on its wheels suddenly.

(9) When the aircraft is on its wheels, remove the hydraulic jack.

Subtask 02-30-01-581-002-A01

C. Towing of the NLG on Inclined Blocks Before Jacking

(1) This procedure is necessary when the height of the closed jack is more than the heightbetween the ground and the jacking dome. See FIGURE 02-30-01-991-022-A.

Inclined Block Angle (max) Height (min)

Nose Gear 5 degrees 100 mm (3.94 in)

Inclined Blocs Specifications

TABLE 4

The inclined blocks must have sufficient strength to support the aircraft weight.The inclined blocks can be made from:- Heavy timbers or railroad crossties,- Plywood sheets covered with a steel plate of 6 mm (0.24 in) minimum thickness,- Plywood sheets covered with a light-alloy sheet of 20 mm (0.79 in) minimum thickness.

(2) Tow the aircraft a small distance to make sure that the nose wheels turn freely.

(3) Do the inspection after a tire burst or thread throw or wheel failure, see AMM05-51-15-200-001.

(4) Make sure that GSE WHEEL CHANGE JACK and the INCLINED BLOCKS are in correctcondition.

(5) Put one inclined block below each nose wheel. Make sure that:- The axes of the inclined block are aligned with the A/C centerline,- The position of the inclined block lets you install the hydraulic jack below the jacking

dome.

02-30-01Page 16

Jul 01/09


(6) For the towing on the inclined blocks, there must be one person in the cockpit to operatethe brakes if necessary, and two persons to monitor the wing tips.

(7) Pull or push the aircraft on the top flat area of the inclined block.

(8) Put the wheel chocks in position in front of and behind the MLG wheels.

(9) Remove the towbar from the NLG fitting.

(10) Set the PARKING BRK control switch to OFF.

(11) Put the GSE WHEEL CHANGE JACKin position and adjust the jack until its adaptertouches the jacking dome of the shock absorber.


(13) Operate the jack to lift the tire off the inclined block.

(14) Remove the inclined block.




Subtask 02-30-01-581-003-A01

D. Jacking of the Main Landing Gear

(1) See FIGURE 02-30-01-991-023-A.See TABLE 1 for hydraulic jack specifications.

(2) Install the wheel chocks on the main landing-gear that is not necessary to change.Install the wheel chocks on the nose landing-gear.

(3) Put the GSE WHEEL CHANGE JACK so that its adapter touches the ball-pad of the shockabsorber.


(5) Operate the jack to lift the tire off the ground.




02-30-01Page 17

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

25.4

mm

301 mm

40 m

m A

PP

RO

X

9°

198

mm

(1 in

)

(11.85 in)

(1.5

7 in

)

(7.7

9 in

)

128

mm

(5.0

4 in

)

JAC

KIN

G P

OIN

T

N_A

R_0

2300

1_1_

0190

101_

01_0

0

A

A

AA

Nose Landing GearJacking for Wheel Change

FIGURE-02-30-01-991-019-A01

02-30-01Page 18

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_023001_1_0220101_01_00

9°

198 mm(7.79 in)

(7.87 in)

(3.93 in)

INCLINED BLOCK

INCLINED BLOCK

DIMENSION "D" MUST BE MORE THAN HYDRAULIC JACK WIDTH.

==

D

5° MAX

200 mm MIN (APPROX.)

100 mm MIN

NOTE:

A

A

FLAT AREA

A A

Nose Landing GearInclined Blocks

FIGURE-02-30-01-991-022-A01

02-30-01Page 19

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_A

R_0

2300

1_1_

0230

101_

01_0

0

FO

RK

25.4

mm

MIN

CO

NT

OU

R O

F T

IRE

S O

N G

RO

UN

D

563 mm

927.

10 m

m

TW

IN W

HE

EL

TR

AC

K

6.5°

(22.16 in)

(36.

5 in

)

(1 in

)

655

mm

(25.

78 in

)JA

CK

ING

PO

INT

LH S

HO

WN

RH

SY

MM

ET

RIC

AL

(1 in

)25

.4 m

m M

IN25

.4 m

m (

1 in

)

Jacking for Wheel ChangeTwin Wheel Main Landing Gear (Sheet 1 of 2)

FIGURE-02-30-01-991-023-A01

02-30-01Page 20

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

CA

NT

ILE

VE

R A

RM

CA

NT

ILE

VE

R A

RM

CO

NT

OU

R O

F T

IRE

S O

N G

RO

UN

D

FO

RK

(1 in

)(1

4.96

in)

(30.

70 in

)

(1 in

)

25.4

mm

380

mm

780

mm

25.4

mm

MIN

JAC

KIN

G P

OIN

TS

LH S

HO

WN

RH

SY

MM

ET

RIC

AL

N_A

R_0

2300

1_1_

0230

102_

01_0

0

(1 in

)25

.4 m

m M

IN

(14.

96 in

)38

0 m

m(1

in)

25.4

mm

Jacking for Wheel ChangeFour Wheel Bogie Main Landing Gear (Sheet 2 of 2)

FIGURE-02-30-01-991-023-A01

02-30-01Page 21

Jul 01/09


02-40-01 HEALTH AND SAFETY ISSUES

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 02-40-01-001-A01

General

1. The emphasis during all aircraft recovery operations is SAFETY. All necessary precautions must betaken to avoid injury to personnel and the occurrence of secondary damage to the aircraft. Not onlythe members of aircraft recovery team, but everyone at the incident site must know all the safetyissues as they evolve. A number of different factors must be taken into account to make sure thesafety issue is properly controlled.Make sure that adherence to a recovery close loop process is ensured to control and set up mitigationplan if needed. By definition this implies that recovery plan engineering, tooling capability andpersonnel qualification or expertise are correctly assessed.Paragraphs are not in order of importance.

A. CommunicationMake sure sufficient and correct communication equipment is available for communication atthe recovery site. Communication equipment can include two-way radios and cell phones. Voiceactivated, lightweight headsets with microphones are ideal for recovery operations. Extrabatteries or a power supply must be available.A direct link with the air traffic control service will most likely be required, depending on thelocation of the incident site. The main problem will be to cross active runways and taxiways inorder to access the incident or accident site. In most cases the local air traffic control servicewill provide an alternative access route to the site in order to reduce the amount ofcommunication.It is absolutely mandatory that lines of communication are established and kept open betweenall groups at the site, including the recovery team, fire department, Investigative Authority,police, airport personnel and any contracted assistance.Short briefing sessions must be held between all groups and parties involved with the recoveryprocess. These briefings will alert personnel to the upcoming steps, and to any possible hazardsand dangers.

B. PersonnelIt should be understood that the aircraft is by definition not under normal maintenance oroperational status. Therefore its recovery involves multiple personnel/parties competencies,which have not necessarily worked previously together and do not know each other’sconstraints-outcomes. As parties have incompatible goals it is of prime importance that therecovery manager ensure that information, caution, etc. are well understood and put in practiceby all.All personnel at the incident site must have proper and adequate personal protective clothingand equipment. This will change greatly if the existing climate and weather conditions change.Examples: Safety boots, personal breathing mask, rainwear, parkas and gloves, etc.

02-40-01Page 1

Jul 01/09


Personnel must be kept at a safe distance during any leveling/lifting operation. The recoverymanager must make sure that the personnel knows the dangers of steel cable during pulling andwinching operations, as well as dangers arising due to the nature of the corrective actionsembodimentMake sure that everyone knows the dangers of going into, climbing-on or going below theaircraft until it is stable and or adequately shored.First-aid kits must be available at the site to cope with minor injuries. Detailed information onhow to contact and arrange for emergency medical attention must be available.

WARNING : MAKE SURE THAT THE AIRCRAFT IS CORRECTLY GROUNDED.

WARNING : MAKE SURE THAT THE AIRCRAFT ELECTRICAL NETWORK IS DE-ENERGIZEDBEFORE YOU DISCONNECT THE EXTERNAL POWER CONNECTOR. IF YOUDISCONNECT THE EXTERNAL POWER CONNECTOR WHEN THE ELECTRICALNETWORK IS ENERGIZED, DANGEROUS ARCING CAN OCCUR.

WARNING : OPEN, SAFETY/LOCK AND TAG THE CIRCUIT BREAKERS RELATED TO THEBLUE HYDRAULIC SYSTEM ELECTRIC PUMP. THIS PUMP RUNSAUTOMATICALLY WHEN THE AIRCRAFT ELECTRICAL NETWORK ISENERGIZED AND THE NLG LEG EXTENDED

CAUTION : MAKE SURE THAT THE AIRCRAFT ELECTRICAL NETWORK IS DE-ENERGIZEDBEFORE YOU DISCONNECT THE EXTERNAL POWER CONNECTOR. IF YOUDO NOT DO SO, THERE IS A RISK OF ARCING AND THIS CAN CAUSEDAMAGE TO THE AIRCRAFT.

C. Electrical SystemsIf you took the decision to leave the aircraft with the batteries connected, do an investigationbefore you energize the circuits. Leaving the batteries connected can help during the differentsteps of the recovery process.Before you use external aircraft power-supply to help the recovery operations, make sure thatthe systems are serviceable.If the aircraft structure is damaged, it is better to disconnect the batteries and not to tryenergize the aircraft with the external supply.

WARNING : MAKE SURE THAT YOU OBEY ALL THE APPLICABLE SAFETY PRECAUTIONSWHEN YOU WORK ON THE OXYGEN SYSTEM OR WITH OXYGEN EQUIPMENT.

D. Oxygen SystemsWhen the aircraft is stable and it is possible to get into the aircraft, make sure that the oxygenbottle valves in the cockpit and cabin are closed. If they are not, close them manually. Ifpossible, remove the bottles from the aircraft. Take the decision as to remove or secure theoxygen generators. As this is a time-consuming task, this decision will be based on the currentdangers involved, the condition of the aircraft and the time available.

02-40-01Page 2

Jul 01/09


WARNING : MAKE SURE THAT YOU OBEY ALL THE APPLICABLE SAFETY PRECAUTIONSWHEN YOU REMOVE FUEL OR WHEN YOU WORK IN AN ENVIRONMENTWHERE THERE IS FUEL.

WARNING : MAKE SURE THAT THE TANKER AND THE AIRCRAFT ARE CONNECTED TOAN APPROVED GROUND AND THAT ELECTRICAL BONDING BETWEEN THEAIRCRAFT AND THE TANKER IS CONNECTED. ONLY IF THESE CONDITIONSARE MET, YOU CAN CONNECT FUEL HOSES OR ADAPTERS BETWEEN THEAIRCRAFT AND THE FUEL TANKER.

E. DefuelingMake sure that only qualified and approved personnel is near the aircraft during the defuelprocess. Steps should be taken to have the Fire Department stand by until the end of thisprocess.If there is any sign of fuel leaks, a hazardous materials team must try to contain any fuelleakage.

F. EquipmentMake sure that contracted assistance, such as heavy-equipment operators, become part of thegroup safety team approach and are briefed on all relative safety issues. Keep in mind that mostheavy-equipment operators never worked near an aircraft. It is necessary give them relevantsafety issues. Discuss with these operators the concerns of overloading equipment and thesubsequent possible dangers. Most heavy-equipment operators know these concerns but not asthey relate to the aircraft. These discussions can include areas such as maximum lifting loadsduring crane lifts. Maximum jacking point loads and pneumatics lifting bags loading figures andcharts must be available.

G. Recovery OperationsMake sure that all equipment in use is properly rated for the loaded anticipated. Make sure thatthe aircraft is stable during all the recovery actions and that tooling used will not cause aircraftinstability. Adherence to maximum wind speeds is required during lifting and leveling operations.AIRBUS recommends that all loads imposed on the aircraft during a recovery operation must berecorded. If it is not possible to record the loads, record all the steps used to make sure that youdo not exceed maximum loads. This will have a direct impact on corrective actions to do forreturn to service.

02-40-01Page 3

Jul 01/09


WEIGHT AND CG MANAGEMENT

03-00-00 WEIGHT AND CG MANAGEMENT

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 03-00-00-558-801-A01

General

1. GeneralThe aim is to calculate the weight of the aircraft and the CG location in order to anticipate aircraftstability changes.The weight of the aircraft and the CG location are the basic data used to calculate the expectedloads and to select a recovery technique (selection of tooling and equipment).The choice of a leveling/lifting scenario (see TBD) and the use of the logic chart (see DESC09-20-01-002-A01) will help to control aircraft weight and CG.


3. Job Setup ReferencesUse aircraft reference axes, glossary of terms (see 09-10-02) and the aircraft reference OEW or DOW.

A. Worksheet PrincipleThe worksheets are used to calculate the NRW and moments.Chapter 03-60-01 gives the source of the specific data used to complete the ”interimworksheets” and calculate the final NRW.The NRW and CG worksheet indicates in front of each item which ARM chapter will giverelevant data to allow completion of ”interim worksheets” and final NRW calculation.It is understood that NRW, CG position and calculation of expected loads will not be accurate ifgeneric data is used for the OEW, H-arm and Y-arm data.It should be noted that the OEW or DOW and the H-arm and Y-arm apply to a specific aircraftwith all landing gears extended, flight controls retracted and thrust reversers in stowed position.See DESC 09-50-01-001-A01 for the calculation worksheets.



REFERENCE DESIGNATIONDESC 09-20-01-002-A01 DESC 09-20-01-002-A01-Aircraft Recovery Logic Chart

DESC 09-50-01-001-A01 DESC 09-50-01-001-A01-Worksheets09-10-02 09-10-02-GLOSSARY OF TERMS03-60-01 03-60-01-REFERENCE FOR CALCULATION09-50-01 09-50-01-WEIGHT AND CG CALCULATION WORKSHEETSFIGURE 03-00-00-991-002-A FIGURE 03-00-00-991-002-A-CG Conversion Principle

FIGURE 03-00-00-991-002-B FIGURE 03-00-00-991-002-B-CG Conversion Principle

03-00-00Page 1

Jul 01/09


REFERENCE DESIGNATIONFIGURE 03-00-00-991-002-C FIGURE 03-00-00-991-002-C-CG Conversion Principle

FIGURE 03-00-00-991-002-D FIGURE 03-00-00-991-002-D-CG Conversion Principle


TABLE 1

5. Procedure

WARNING : MAKE SURE THAT ALL PERSONNEL IS AT A SAFE DISTANCE DURING THEREMOVAL OF FUEL, CARGO OR LARGE COMPONENTS. AN UNEQUALREMOVAL OF FUEL OR CARGO OR THE REMOVAL OF LARGE COMPONENTSCAN CHANGE THE CG AND THE LONGITUDINAL AND LATERAL STABILITY OFTHE AIRCRAFT. DEATH OR SERIOUS INJURY MAY RESULT IF THE AIRCRAFTFALLS ON RECOVERY PERSONNEL.

WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURING THERECOVERY PROCESS.

NOTE : It is important to use accurate data for the calculation related to the recovery process.Some of the necessary data is the responsibility of the operator and to be accurate, it mustbe applicable to the specific MSN involved. Data supplied by the manufacturer as genericdata is not necessarily accurate for a specific MSN. Refer to the operator’s documentationfor precise calculations.If some of the necessary data is not available or if it is not possible to get it, then it is theresponsibility of the recovery manager to decide to use estimated data and to continue withthe process.

**ON A/C A318-100

Subtask 03-00-00-558-001-A01

A. CG Conversion Principle

(1) The CG location (in the longitudinal axis) can be expressed in % of the Reference Chord(%RC) or in lever arm distance (H-arm). See FIGURE 03-00-00-991-002-A.In this manual, the lever arm distance (H-arm and Y-arm) is used to calculate the CGlocation calculation.

(a) Use the formula that follows to convert the CG expressed in %RC from other manualsinto H-arm.- H-arm (in meters) = (%RC × 0.041935) + 15.4139- H-arm (in inches) = (%RC × 1.651) + 606.847

(b) Use the formula that follows to convert H-arm into %RC.- %RC = (H-arm -- 15.4139) / 0.041935 (H-arm in meters)

03-00-00Page 2

Jul 01/09


- %RC = (H-arm -- 606.847) / 1.651 (H-arm in inches)

**ON A/C A319-100

Subtask 03-00-00-558-001-B01


(1) The CG location (in the longitudinal axis) can be expressed in % of the Reference Chord(%RC) or in lever arm distance (H-arm). See FIGURE 03-00-00-991-002-B.In this manual, the lever arm distance (H-arm and Y-arm) is used to calculate the CGlocation calculation.


(b) Use the formula that follows to convert H-arm into %RC.- %RC = (H-arm -- 16.2016) / 0.041935 (H-arm in meters)- %RC = (H-arm -- 637.858) / 1.651 (H-arm in inches)

**ON A/C A320-100 A320-200

Subtask 03-00-00-558-001-C01


(1) The CG location (in the longitudinal axis) can be expressed in % of the Reference Chord(%RC) or in lever arm distance (H-arm). See FIGURE 03-00-00-991-002-C.In this manual, the lever arm distance (H-arm and Y-arm) is used to calculate the CGlocation calculation.



03-00-00Page 3

Jul 01/09


**ON A/C A321-100 A321-200

Subtask 03-00-00-558-001-D01


(1) The CG location (in the longitudinal axis) can be expressed in % of the Reference Chord(%RC) or in lever arm distance (H-arm). See FIGURE 03-00-00-991-002-D.In this manual, the lever arm distance (H-arm and Y-arm) is used to calculate the CGlocation calculation.



**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Subtask 03-00-00-970-001-A01

B. Principle of the NRW and Related CG Position Calculation

NOTE : All calculations are based on OEW or DOW aircraft configuration and related CG. Theweight differences between the OEW or DOW and the real status of the aircraft arethen recorded on calculation worksheets. The data on these worksheets is used tocalculate the NRW and CG location of the aircraft.

(1) Find the weight and calculate the related H-arm moment of a known aircraft configuration(OEW or DOW).

NOTE : For the OEW or DOW configuration, the Y-arm = 0.

(2) Record the values on the NRW and CG worksheet (see 09-50-01) applicable to theconfiguration (OEW or DOW) that you will use for the calculation.

(3) For each item on the NRW and CG worksheet, use the related chapter and related interimworksheet to record the weight, the H-arm moment and the Y-arm moment of each itemwhich remains on the aircraft, which is removed or missing from the aircraft and which hasan effect on the known OEW or DOW.

NOTE : It is considered that the Y-arm of components located inside the fuselage isnegligible for the calculation made, therefore they are ignored.

NOTE : The ARM gives all necessary data (for each scenario) to allow completion ofinterim worksheet.

03-00-00Page 4

Jul 01/09


(4) Use the ”NRW and Related H and Y Moment” worksheet (see 09-50-01) to find the NRW,the total H-arm moment and the total Y-arm moment.NET RECOVERABLE WEIGHT =TOTAL H-ARM MOMENT =TOTAL Y-ARM MOMENT =

(5) Divide the ”total H-arm moment” value by the NRW value to find the longitudinal CGposition (XG).(LONGITUDINAL CG POSITION) XG =

(6) Divide the ”total Y-arm moment value” by the NRW value to find the lateral CG position(YG).(LATERAL CG POSITION) YG =

03-00-00Page 5

Jul 01/09


**ON A/C A318-100

2.54

0 m

(100

in)16

.462

m(6

48.1

1 in

)

RE

FE

RE

NC

E C

HO

RD

4.19

35 m

(16

5.10

in)

25%

RC

7.00

0 m

(275

.591

in)

FU

SE

LAG

ED

AT

UM

LIN

E

0

Z

X

H−ARM= 0

15.4

139

m(6

06.8

47 in

)

N_A

R_0

3000

0_1_

0020

101_

01_0

0

CG Conversion PrincipleReference Chord Data - A318

FIGURE-03-00-00-991-002-A01

03-00-00Page 6

Jul 01/09


**ON A/C A319-100

2.54

0 m

(100

in)

17.2

50 m

(679

.13

in)

RE

FE

RE

NC

E C

HO

RD

4.19

35 m

(16

5.10

in)

25%

RC

7.00

0 m

(275

.591

in)F

US

ELA

GE

DA

TU

M L

INE

0

Z

X

H−ARM= 0

16.2

016

m(6

37.8

60 in

)

OP

TIO

NA

L

N_A

R_0

3000

0_1_

0020

201_

01_0

0


FIGURE-03-00-00-991-002-B01

03-00-00Page 7

Jul 01/09


**ON A/C A320-100 A320-200

2.54

0 m

(100

in)

18.8

50 m

(742

.13

in)

RE

FE

RE

NC

E C

HO

RD

4.19

35 m

(16

5.10

in)

25%

RC

7.00

0 m

(275

.591

in)

0

Z

X

H−ARM= 0

17.8

015

m(7

00.8

5 in

)

FU

SE

LAG

ED

AT

UM

LIN

E

N_A

R_0

3000

0_1_

0020

301_

01_0

0

CG Conversion PrincipleReference Chord Data - A320FIGURE-03-00-00-991-002-C01

03-00-00Page 8

Jul 01/09


**ON A/C A321-100 A321-200

2.54

0 m

(100

in)

23.1

17 m

(910

.12

in)

RE

FE

RE

NC

E C

HO

RD

4.19

35 m

(16

5.10

in)

25%

RC

7.00

0 m

(275

.591

in)

0Z

X

H−ARM= 0

FU

SE

LAG

ED

AT

UM

LIN

E

22.0

687

m(8

68.8

5 in

)

N_A

R_0

3000

0_1_

0020

401_

01_0

1


FIGURE-03-00-00-991-002-D01

03-00-00Page 9

Jul 01/09


03-20-01 FUEL LOAD AND CG CONTROL

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 03-20-01-001-A01

General

1. To safely level or lift a damaged aircraft so that it can be moved on it’s own Landing Gear (or on asuitable ground equipment trailer) you must establish the weight and center of gravity (CG) of theaircraft.This chapter contains the method and calculations needed to establish the effect of the fuel load onthe position of the aircraft CG. The weight and CG positions of the aircraft will change due to thequantity of fuel in each tank. To find the changes in weight and CG position, calculate:- The H-arm dimension along the longitudinal plane from nose to tail

(H-arm is a dimension from the CG of an item/component to the horizontal reference datumplane)

- The Y-arm dimension along the lateral plane from wing tip to wing tip(Y-arm is a dimension from the CG of an item/component to the lateral arm reference datumplane).

The tables (see DESC 03-20-01-002-A01) in this chapter contain fuel weight and CG data forselected incremental fuel volumes for each fuel tank and for each scenario.

NOTE : Fuel density used in calculations is: 0.785 kg/liter and 1.7306138 lb/liter

03-20-01Page 1

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

AIR

CR

AF

TW

EIG

HT

CE

NT

ER

TA

NK

WE

IGH

T

OU

TE

R T

AN

KW

EIG

HT

INN

ER

TA

NK

WE

IGH

TO

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ER

TA

NK

WE

IGH

T

LIF

TIN

GLO

AD

CE

NT

ER

TA

NK

WE

IGH

T(I

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ST

ALL

ED

)

AD

DIT

ION

AL

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ER

TA

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WE

IGH

T

MO

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NT

S T

AK

EN

AT

CO

NT

AC

T P

OIN

T

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R_0

3200

1_1_

0010

101_

01_0

3

Aircraft LoadsType and Position of Loads Acting on the Aircraft

FIGURE-03-20-01-991-001-A01

03-20-01Page 2

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 03-20-01-002-A01

Tables

1. GeneralTo find the weight and associated CG of remaining fuel on board, you must know the quantity of fuelremaining in each tank. If you do not know the quantity of fuel remaining in each tank see 03-20-02for information about how to assess the fuel quantity without serviceable aircraft systems.Using the fuel quantity, you must determine the weight and moment (generated by H-arm and Y-arm) of the fuel, using the table for the given scenario.When you have found the data from the relevant tables, enter this data in the fuel remaining onboardeffect ’worksheet’ boxes (see DESC 09-50-01-001-A01 for calculation worksheets) with the weight,the H-arm moment and the Y-arm moment values for the remaining fuel in each tank.For information on defuel procedures see 05-10-00.

NOTE : The tables that follow give estimated values to help you estimate the CG position. Thevalues are calculated without any pitch or roll angle of the aircraft. Accurate data arerelated to your aircraft configuration.

**ON A/C A318-100

2. TablesThe table that follow gives the H-arm and Y-arm related to important fuel capacities.

Capacity Weight H-arm Harm Moment Y-arm Y-arm Moment

200 l(53 US gal)

157 kg(346 lb)

15.4 m(606.30 in)

2418 kgm(209780 lb.in)

2.183 m(85.94 in)

343 kgm(29735 lb.in)

1/41800 l(476 US gal)

1413 kg(3115 lb)

15.386 m(605.75 in)

21740 kgm(1886911 lb.in)

2.775 m(109.25 in)

3921 kgm(340314 lb.in)

1/23400 l(898 US gal)

2669 kg(5884 lb)

15.489 m(609.80 in)

41340 kgm(3588063 lb.in)

3.151 m(124.06 in)

8410 kgm(729969 lb.in)

3/45200 l(1374 USgal)

4082 kg(8999 lb)

15.642 m(615.83 in)

63851 kgm(5541854 lb.in)

3.629 m(142.87 in)

14814 kgm(1285687 lb.in)

Full

6925 l(1829 USgal)

5436 kg(11984 lb)

16.012 m(630.39 in)

87043 kgm(7554594 in)

4.535 m(178.54 in)

24653 kgm(54347 lb.in)

Inner Cell

TABLE 1

03-20-01Page 3

Jul 01/09



1/4200 l(53 US gal)

157 kg(346 lb)

18.622 m(733.15 in)

2924 kgm(253.670 lb.in)

10.502 m(413.46 in)

1649 kgm(143057 lb.in)

1/2400 l(106 US gal)

314 kg(692 lb)

18.706 m(736.46 in)

5874 kgm(509630 lb.in)

10.751 m(423.27 in)

3376 kgm(292903 lb.in)

3/4600 l(159 US gal)

471 kg(1038 lb)

18.786 m(739.61 in)

8848 kgm(767715 lb.in)

10.966 m(431.73 in)

5165 kgm(448136 lb.in)

Full880 l(232 US gal)

691 kg(1523 lb)

18.943 m(745.79 in)

13086 kgm(1135838 lb.in)

11.364 m(447.40 in)

7850 kgm(681390 lb.in)

Outer Cell

TABLE 2


200 l(53 US gal)

157 kg(346 lb)

15.47 m(609.06 in)

2429 kgm(210735 lb.in)

- -

1/42200 l(581 US gal)

1727 kg(3807 lb)

15.195 m(598.23 in)

26242 kgm(2277462 lb.in)

- -

1/24200 l(1110 USgal)

3297 kg(7269 lb)

15.053 m(592.64 in)

49630 kgm(4307900 lb.in)

- -

3/46200 l(1638 USgal

4867 kg(10730 lb)

15.005 m(590.75 in)

73029 kgm(6338748 lb.in)

- -

Full

8250 l(2179 USgal)

6476 kg(14277 lb)

14.968 m(589.29 in)

96937 kgm(8413293 lb.in)

- -

Center Tank

TABLE 3

**ON A/C A319-100



200 l(53 US gal)

157 kg(346 lb)

16.188 m(637.32 in)

2542 kgm(220513 lb.in)

2.183 m(85.94 in)

343 kgm(29735 lb.in)

1/42000 kg(4409 lb)

1570 kg(3461 lb)

16.187 m(637.28 in)

25414 kgm(2205626 lb.in)

2.827 m(111.30 in)

4438 kgm(385209 lb.in)

03-20-01Page 4

Jul 01/09



1/23600 kg(7937 lb)

2826 kg(6230 lb)

16.291 m(641.38 in)

46038 kgm(3995797)

3.194 m(125.75 in)

9026 kgm(783423 lb.in)

3/45200 l(1374 USgal)

4082 kg(8999 lb)

16.43 m(646.85 in)

67067 kgm(5821003 lb.in)

3.629 m(142.87 in)

14814 kgm(1285687 lb.in)

Full

6925 l(1829 USgal)

5436 kg(11984 lb)

16.8 m(661.42 in)

91325 kgm(7926457 lb.in)

4.535 m(178.54 in)

24652(2139623 lb.in)

Inner Cell

TABLE 4


1/4200 l(53 US gal)

157 kg(346 lb)

19.41 m(764.17 in)

3047 kgm(264403 lb.in)

10.502 m(413.46 in)

1649 kgm(143057 lb.in)

1/2400 l(106 US gal)

314 kg(692 lb)

19.494 m(767.48 in)

6121 kgm(531096 lb.in)

10.751 m(423.27 in)

3376 kgm(292903 lb.in)

3/4600 l(159 US gal)

471 kg(1038 lb)

19.574 m(770.63 in)

9219 kgm(799914 lb.in)

10.966 m(431.73 in)

5165 kgm(448136 lb.in)


691 kg(1523 lb)

19.731 m(776.81 in)

13634 kgm(1183082 lb.in)

11.364 m(447.40 in)

7853 kgm(681390 lb.in)

Outer Cell

TABLE 5


200 l(53 US gal)

157 kg(346 lb)

16.258 m(640.08 in)

2553 kgm(221468 lb.in)

- -

1/42200 l(581 US gal)

1727 kg(3807 lb)

15.959 m(628.31 in)

27561 kgm(2391976 lb.in)

- -

1/24200 l(1110 USgal)

3297 kg(7269 lb)

15.834 m(623.39 in)

52205 kgm(4531422 lb.in)

- -

3/46200 l(1638 USgal)

4867 kg(10730 lb)

15.79 m(621.65 in)

76850 kgm(6670305 lb.in)

- -

03-20-01Page 5

Jul 01/09



Full

8250 l(2179 USgal)

6476 kg(14277 lb)

15.756 m(620.31 in)

102036 kgm(8856166 lb.in)

- -

Center Tank

TABLE 6

**ON A/C A320-100 A320-200



200 l(53 US gal)

157 kg(346 lb)

17.79 m(700.39 in)

2793 kgm(242335 lb.in)

2.179 m(85.79 in)

342 kgm(29683 lb.in)

1/42000 kg(4409 lb)

1570 kg(3461 lb)

17.784 m(700.16 in)

27921 kgm(2423254 lb.in)

2.815 m(110.83 in)

4420 kgm(383583 lb.in)

1/23600 kg(7937 lb)

2826 kg(6230 lb)

17.885 m(704.13 in)

50543 kgm(4386730 lb.in)

3.175 m(125.00 in)

8973 kgm(778750 lb.in)

3/45200 l(1374 USgal)

4867 kg(10730 lb)

18.012 m(709.13 in)

73525 kgm(7608965 lb.in)

3.579 m(140.91 in)

14609 kgm(1511964 lb.in)

Full

6984 l(1845 USgal)

5482 kg(12086 lb)

18.372 m(723.31 in)

100715 kgm(8741925 lb.in)

4.469 m(175.94 in)

24499 kgm(2126411 lb.in)

Inner Cell

TABLE 7


1/4200 l(53 US gal)

157 kg(346 lb)

21.01 m(827.17 in)

3299 kgm(286201 lb.in)

10.502 m(413.46 in)

1649 kgm(143057 lb.in)

1/2400 l(106 US gal)

314 kg(692 lb)

21.094 m(830.47 in)

6624 kgm(574685 lb.in)

10.751 m(423.27 in)

3376 kgm(292972 lb.in)

3/4600 l(159 US gal)

471 kg(1038 lb)

21.174 m(833.62 in)

9973 kgm(865298 lb.in)

10.966 m(431.73 in)

5165 kgm(448136 lb.in)

03-20-01Page 6

Jul 01/09




691 kg(1523 lb)

21.331 m(839.80 in)

14740 kgm(1279015 lb.in)

11.364 m(447.40 in)

7853 kgm(681390 lb.in)

Outer Cell

TABLE 8


200 l(53 US gal)

157 kg(346 lb)

17.858 m(703.07 in)

2804 kgm(243262 lb.in)

- -

1/42200 l(581 US gal)

1727 kg(3807 lb)

17.559 m(691.30 in)

30324 kgm(2631779 lb.in)

- -

1/24200 l(1110 USgal)

3297 kg(7269 lb)

17.434 m(686.38 in)

57480 kgm(4989296 lb.in)

- -

3/46200 l(1638 USgal)

4867 kg(10730 lb)

17.39 m(684.65 in)

84637 kgm(7346295 lb.in)

- -

Full

8250 l(2179 USgal)

6476 kg(14277 lb)

17.362 m(683.54 in)

110092 kgm(9758901 lb.in)

- -

Center Tank (A320-200 only)

TABLE 9

**ON A/C A321-100 A321-200



200 l(53 US gal)

157 kg(346 lb)

22.056 m(868.35 in)

3463 kgm(300449 lb.in)

2.181 m(85.87 in)

342 kgm(29711 lb.in)

1/42000 l(528 US gal)

1570 kg(3461 lb)

22.039 m(867.68 in)

34601 kgm(3003041 lb.in)

2.789 m(109.80 in)

4379 kgm(380018 lb.in)

1/24000 l(1057 USgal)

3140 kg(6923 lb)

22.174 m(872.99 in)

69626 kgm(6043710 lb.in)

3.204 m(126.14 in)

10061 kgm(873267 lb.in)

3/46000 l(1585 USgal)

4710 kg(10384 lb)

22.43 m(883.07 in)

105645 kgm(9169799 lb.in)

3.9 m(153.54 in)

18369 kgm(1594359 lb.in)

03-20-01Page 7

Jul 01/09



Full

7745 l(2046 USgal)

6080 kg(13404 lb)

22.883 m(900.91 in)

139129 kgm(12.075768 lb.in)

4.973 m(195.79 in)

30236 kgm(2624369 lb.in)

Wing Tank

TABLE 10


200 l(53 US gal)

157 kg(346 lb)

22.069 m(868.86 in)

3465 kgm(300626 lb.in)

- -

1/42000 l(528 US gal)

1570 kg(3461 lb)

21.785 m(857.68 in)

34202 kgm(2968431 lb.in)

- -

1/24000 l(1057 USgal)

3140 kg(6923 lb)

21.672 m(853.23 in)

68050 kgm(5906911 lb.in)

- -

3/46000 l(1585 USgal)

4710 kg(10384 lb)

21.634 m(851.73 in)

101896 kgm(8844364 lb.in)

- -

Full

8210 l(2169 USgal)

6445 kg(14209 lb)

21.596 m(850.24 in)

139186 kgm(12081060 lb.in)

- -

Center Tank

TABLE 11

03-20-01Page 8

Jul 01/09


03-20-02 MANUAL FUEL QUANTITY INDICATION

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 03-20-02-970-801-A01

Use of Magnetic Level Indicators (MLI)

1. GeneralThe Magnetic Level Indicators (MLI) are used on ground to calculate the fuel quantity in the wingand center tanks.See AMM 12-11-28-650-007 for detailed procedure.This procedure is valid only when the aircraft attitude is between minus 1.5˚ and plus 1.5˚ roll andminus 1.5˚ and plus 1.5˚ pitch.

2. InspectionsNot Applicable

3. Job Setup ReferencesOn A318, A319 and A320, there are five MLI in each wing tank and one in the center tank.On A321, there are seven MLI in each wing tank and one in the center tank.See FIGURE 03-20-02-991-001-AFIGURE 03-20-02-991-001-B.



REFERENCE DESIGNATION98A28104000000 PURGER WATER DRAIN


TABLE 1


REFERENCE DESIGNATIONAMM 12-11-28-650-007AMM 12-11-28-650-001AMM 12-11-28-650-002AMM 12-32-28-281-001FIGURE 03-20-02-991-001-A FIGURE 03-20-02-991-001-A-Magnetic Level Indicators

FIGURE 03-20-02-991-001-B FIGURE 03-20-02-991-001-B-Magnetic Level Indicators

FIGURE 03-20-02-991-002-A FIGURE 03-20-02-991-002-A-Attitude Monitor


TABLE 2

03-20-02Page 1

Jul 01/09


5. Procedure

WARNING : THIS PROCEDURE IS FOR INFORMATION ONLY TO HELP YOU PREPARE THERECOVERY OPERATION. TO DO THE PROCEDURE, YOU MUST REFER TO THEOPERATORS CUSTOMIZED DOCUMENTATION.


CAUTION : DO NOT LET THE MLI’S FALL FREELY.

CAUTION : RETRACT THE MLI’S AS SOON AS POSSIBLE. YOU CAN EASILY CAUSEDAMAGE TO AN EXTENDED MLI.

Subtask 03-20-02-869-001-A01

A. Preparation

(1) Safety Precaution

(a) You must obey the refuel/defuel safety precautions. See AMM 12-11-28-650-001 andAMM 12-11-28-650-002.

(b) Put the safety barriers in position.

(2) Fuel Sampling

(a) Use the 98A28104000000 PURGER WATER DRAIN to get a fuel sample from theaircraft. See AMM 12-32-28-281-001.

(b) Measure the Specific Gravity (SG) of the fuel sample.

(3) Get Access

(a) Put an access platform below the applicable MLI.

(b) Open the access door 192MB, see FIGURE 03-20-02-991-002-A.

(4) Aircraft Attitude

(a) Find and write down the aircraft attitude (pitch and roll). See TBD.

(b) Or, if installed, read the aircraft attitude shown by the bubble on the attitudemonitor, see FIGURE 03-20-02-991-002-A.See TABLE 3 to convert the attitude angles and grid square letters on the attitudemonitor.

Pitch Ref Roll Ref- 1.5˚ 1 - 1.5˚ A- 1.0˚ 2 - 1.0˚ B- 0.5˚ 3 - 0.5˚ C0.0˚ 4 0.0˚ D

03-20-02Page 2

Jul 01/09


Pitch Ref Roll Ref+ 0.5˚ 5 + 0.5˚ E

+ 1.0˚ 6 + 1.0˚ F

+ 1.5˚ 7 + 1.5˚ G

Aircraft Attitude

TABLE 3

Subtask 03-20-02-970-001-A01

B. Use of the Magnetic Level Indicators (MLI)

(1) Use a screwdriver to push the applicable MLI and turn it through 90 deg.

(2) Hold and carefully lower the MLI fully. Then carefully lift the MLI until you feel themagnets engage.

(3) Read the units mark nearest to the bottom-skin of the wing and write down the number.

(4) Retract the MLI and use a screwdriver to turn it through 90 deg. to lock it.

(5) Find the volume of fuel in each tank:

(a) Use the applicable MLI stick number and the applicable aircraft attitude grid-squareletter to find the corresponding fuel quantity table. See AMM 12-11-28-650-007 forthe fuel quantity tables.

(b) Find the applicable MLI unit number row and the applicable A/C attitude (grid-square letter and number) in the table.Find the intersection of the applicable rows to give the correct volume of fuel in thetank.

(c) Multiply the total volume of the fuel by the specific gravity (SG) of the fuel to obtainthe mass of the fuel.

NOTE : The MLI are accurate to +/- 5 % of their indication.

03-20-02Page 3

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200

N_AR_032002_1_0010101_01_00

RIB2

RIB6

RIB10

RIB12

RIB21

CL

CTRSTICK

STICK No 1 STICK No 2

EXTERNAL VIEW OF RETRACTEDAND LOCKED M.L.I.

INDICATOR ROD EXTENDED

STICK No 3

STICK No 4STICK No 5

Magnetic Level IndicatorsLocation - A318/A319/A320

FIGURE-03-20-02-991-001-A01

03-20-02Page 4

Jul 01/09


**ON A/C A321-100 A321-200

EXTERNAL VIEW OF RETRACTEDAND LOCKED M.L.I.

INDICATOR ROD EXTENDED

N_AR_032002_1_0010201_01_00

RIB2

RIB6

RIB10

RIB12

RIB21

CL

CTRSTICK

STICK No 1 STICK No 2STICK No 3

STICK No 4

STICK No 7STICK No 5

STICK No 6

Magnetic Level IndicatorsLocation - A321

FIGURE-03-20-02-991-001-B01

03-20-02Page 5

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_032002_1_0020101_01_00

A

192MB

ATTITUDE MONITOR

A1BCDEFG

2 3 4 5 6 7

A

39QM

Attitude MonitorLocation

FIGURE-03-20-02-991-002-A01

03-20-02Page 6

Jul 01/09


03-50-01 MANAGING AIRCRAFT WEIGHT AND CG

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 03-50-01-001-A01

Introduction

1. GeneralManagement of the aircraft weight and related CG is one of the key issues of the recovery plan andoperation. It has a direct impact on aircraft stability, calculation of expected loads and the loadsrecorded for a given recovery process.

2. PurposeFor a given aircraft attitude (See TBD), it is necessary first to calculate the aircraft NRW and CG(See 03-00-00) to make the calculations of the expected loads, based on the leveling/liftingtechniques that will be used.These expected loads, and then the applied loads must be in the limits that follow:- Aircraft allowable loads,- Tooling capabilities.If these loads are not in the limits, it will be necessary:- To find an alternative leveling/lifting procedure to make sure that the aircraft, tooling and

equipment support loads are not more than the allowable loads,- To manage aircraft weight and related CG to bring the expected loads in the allowable loads,- To use other tooling, if the tool cannot support the expected loads.

NOTE : The tooling should not only be able to support expected loads, but should also beappropriate for the travel range, arc movement, aircraft stability, ground stability, etc.…

NOTE : It is important to make sure that the aircraft is stable before and during theimplementation of the recovery phase/steps.

The installation of ballast or the removal of equipment, payload, fuel, etc. can help to change theaircraft weight and CG location.Every effort should be made to reduce the Total Weight of the aircraft to the minimum possible byremoval of significant amounts of payload. The easiest way to remove quickly large amounts ofweight can be fuel and cargo removal.In some cases, it may be necessary to remove major aircraft components that are damaged. Beforeremoval of these components, it is important to do a careful study because it may be better to securethem in place temporarily.Galley catering units (trolleys, etc.) have a significant weight and every effort should be made toremove them. If they remain on board, carefully evaluate their weight when you make the H-armcalculations.Food in the catering units can deteriorate quickly. During a long recovery operation, it may become apriority to remove the catering units for health reasons.Draining of potable water and lavatory waste and removal of the escape slides and slide rafts can alsoreduce the weight.

03-50-01Page 1

Jul 01/09


It is not necessary to drain the fluids, such as hydraulic fluid, from closed systems unless there issignificant leakage that it is not possible to contain.As every aircraft recovery is different, it will be necessary to decide what and how much must beremoved. These decisions will be based on access, time, cost and the actual ability to do the task.The records made during the damage survey of the aircraft should include all major components thatare missing or that it is necessary to remove because of damage. It is necessary to include the weightchanges related to these components in the calculation of the aircraft weight and CG location.Removal of any aircraft components and equipment should be done in accordance with the AircraftMaintenance Manual (AMM), and recorded with the data collected during the aircraft survey.

3. Calculation IterationThe calculation iteration from NRW and CG up to expected loads, travel range, arc movement shouldbe continued until aircraft stability, expected loads, travel range, arc movement etc.… are in theacceptable limits.Changes to the different inputs used in the calculations can help to get satisfactory value related tothe settings of a recovery scenario.

4. List of Item Used for NRW and CG CalculationSee the related topic or task for the related item weight input.

Weight Inputs See

OEW 03-00-00DOW 03-00-00Fuel Remaining on Board Effect 03-20-01

Cargo and Baggage Remaining Effect TASK 03-50-01-558-801-A01TASK 03-50-01-558-801-B01TASK 03-50-01-558-801-C01TASK 03-50-01-558-801-D01

Total Traffic Load Remaining Effect TASK 03-50-01-558-802-A01

Ballast Added Effect TASK 03-50-01-558-803-A01Waste Water Remaining Effect TASK 03-50-01-558-804-A01

Non OEW Catering Equipment Added Effect TASK 03-50-01-558-805-A01

Large Component Movement Effect TASK 03-50-01-558-811-A01TASK 03-50-01-558-811-B01TASK 03-50-01-558-811-C01

Potable Water Removed Effect TASK 03-50-01-558-806-A01Cockpit and Cabin Crew Removed Effect TASK 03-50-01-558-807-A01

Catering Equipment Removed Effect TASK 03-50-01-558-808-A01

03-50-01Page 2

Jul 01/09


Weight Inputs See

Large Component Removed /Missing Effect TASK 03-50-01-558-810-A01TASK 03-50-01-558-810-B01TASK 03-50-01-558-810-C01TASK 03-50-01-558-810-D01

Hydraulic Fluids Removed Effect TASK 03-50-01-558-809-A01

List of Item Used for NRW and CG Calculation

TABLE 1

03-50-01Page 3

Jul 01/09


**ON A/C A318-100

TASK 03-50-01-558-801-A01

Cargo and Baggage Remaining Effect

1. GeneralThe aircraft has three cargo compartments.- The FWD cargo compartment (N˚1) in zone 130,- The aft cargo compartment (N˚4) in zone 150,- The bulk cargo compartment (N˚5) in zone 160.

NOTE : For location see 09-10-14


3. Job Setup ReferencesThe tables that follow are built with a standard configuration. If the cargo compartments contain adifferent configuration, use the value given in the standard combination or in your WBM to find theapplicable H-arm and Y-arm.

A. Forward Cargo CompartmentThe forward cargo compartment is designed for the transport of bulk cargo and baggage.See your WBM to determine applicable Y-arm.

Section Frame Station RemainingWeight

Average H-ArmMoment to add

1124A to 28

10.430 m(410.63 in)

1228 to 34

11.748 m(462.52 in)

Total24A to 34

11.078 m(436.14 in)

FWD Cargo Compartment Remaining Weight and Related H-arm

TABLE 1

B. Aft Lower Cargo CompartmentThe aft cargo compartment is designed for the transport of bulk cargo and baggage.See your WBM to determine applicable Y-arm.


Average H-Arm Moment to add

4147/54 to 57

19.698 m(775.51 in)

03-50-01Page 4

Jul 01/09



Average H-Arm Moment to add

4257 to 60

21.374 m(841.50 in)

Total47/54 to 60

20.498 m(807.01 in)


TABLE 2

C. Bulk Cargo CompartmentThe aft cargo compartment is designed for the transport of bulk cargo and baggage.See your WBM to determine applicable Y-arm.

Section Frame StationRemaining

WeightAverage H-Arm Moment to add

5160 to 62

22.708 m(894.02 in)

5162 to 65

24.062 m(947.32 in)

Total60 to 65

23.528 m(926.30 in)


TABLE 3



REFERENCE DESIGNATIONDESC 09-50-01-001-A01 DESC 09-50-01-001-A01-Worksheets09-10-14 09-10-14-CARGO COMPARTMENTS


TABLE 4

03-50-01Page 5

Jul 01/09


5. Procedure



WARNING : IF CARGO AND BAGGAGE ARE NOT - OR CANNOT BE - REMOVED, MAKESURE THAT THEY ARE SAFELY FASTENED AND THAT LOADS ARE ASSYMMETRICAL AS POSSIBLE BEFORE YOU START THE RECOVERY PROCESS.


Subtask 03-50-01-558-001-A01

A. How to Find the Effect of Cargo and Baggage Remaining

(1) Use the tables in Job Setup References to determine H-arm moments and Y-arm momentsby reporting the masses of each container or pallet.

(2) Record the calculated values on FWD Cargo Compartment (in Zone 130) , Aft CargoCompartment (in Zone 150) , Bulk Cargo Compartment (in Zone 160) into boxes of theCargo and Baggage Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01Page 6

Jul 01/09


**ON A/C A319-100

TASK 03-50-01-558-801-B01


1. GeneralThe aircraft has two cargo compartments.- The FWD cargo compartment (N˚1) in zone 130,- The aft cargo compartment (N˚4) in zone 150 and the aft cargo compartment (N˚5) in zone

160.




A. Forward Cargo CompartmentThe forward cargo compartment is designed for the transport of bulk cargo and baggage or thefollowing unit load devices:- 2 x half size containers LD3-46 (NAS 3610-2K2C, IATA contour AKG)- 2 x full size containers LD3-46W (NAS 3610-2K2C, IATA contour AKH)- 2 x 60.4x61.5 in pallets LD3-46P (NAS 3610-2K3P)See your WBM to determine applicable Y-arm.



1124A to 28

10.744 m(422.99 in)

1228 to 34

12.371 m(487.05 in)

Total24A to 34

11.436 m(450.24 in)

Bulk Cargo in FWD Cargo Compartment Remaining Weight and Related H-arm

TABLE 1

Position ULD Remaining Weight Average H-Arm Moment to add

11 10.700 m(421.26 in)

03-50-01Page 7

Jul 01/09



12 12.272 m(483.15 in)

Containers and Pallets in FWD Cargo Compartment Remaining Weight and Related H-arm

TABLE 2

B. Aft Cargo Compartment n˚4The aft cargo compartment n˚4 is designed for the transport of bulk cargo and baggage or thefollowing unit load devices:- 2 x half size containers LD3-46 (NAS 3610-2K2C, IATA contour AKG)- 2 x full size containers LD3-46W (NAS 3610-2K2C, IATA contour AKH)- 2 x 60.4x61.5 in pallets LD3-46P (NAS 3610-2K3P)See your WBM to determine applicable Y-arm.



4147/51 to 54

20.485 m(806.50 in)

4254 to 59

22.695 m(893.50 in)

Total47/51 to 59

21.819 m(859.02 in)

Bulk Cargo in Aft Cargo Compartment Remaining Weight and Related H-arm

TABLE 3


41 20.475 m(806.10 in)

42 22.047 m(867.99 in)

Containers and Pallets in Aft Cargo Compartment Remaining Weight and Related H-arm

TABLE 4

C. Aft Cargo Compartment n˚5The aft cargo compartment n˚5 is designed for the transport of bulk cargo and baggage.See your WBM to determine applicable Y-arm.

03-50-01Page 8

Jul 01/09




5159 to 65

25.649 m(1009.80 in)


TABLE 5





TABLE 6

5. Procedure





03-50-01Page 9

Jul 01/09


Subtask 03-50-01-558-018-A01



(2) Record the calculated values on FWD Cargo Compartment (in Zone 130) , Aft CargoCompartment (in Zone 150) , Aft Cargo Compartment (in Zone 160) into boxes of theCargo and Baggage Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01Page 10

Jul 01/09


**ON A/C A319-100

N_AR_035001_1_0030101_01_00

1.430 m(56.30 in)

2.630 m(103.54 in)

1.21

3 m

(47.

76 in

)0.

051

m(2

.00

in)

IATA CODEAKG

1.16

8 m

(46.

60 in

)

2.451 m(96.50 in)

1.562 m(61.50 in)

1.534 m(60.40 in)

NAS 3610−2K2CLD3−46IATA CODE AKG

2.007 m(79.00 in)

1.534 m(60.40 in)

1.562 m(61.50 in)

IATA CODEAKH

NAS 3610−2K2CLD3−46WIATA CODE AKH

1.562 m(61.50 in)

1.534 m

(60.40 in)

1.16

8 m

(46.

60 in

)

1.16

8 m

(46.

60 in

)

PALLETNAS 3610−2K3PLD3−46P

FWDCARGODOOR

11 12

FR24 FR34

A

A

FWD Cargo Compartment ArrangementPallets and Containers

FIGURE-03-50-01-991-003-A01

03-50-01Page 11

Jul 01/09


**ON A/C A319-100

N_AR_035001_1_0040101_01_00

FWDCARGODOOR

41 42

1.430 m(56.30 in)

2.630 m(103.54 in)

1.21

3 m

(47.

76 in

)0.

051

m(2

.00

in)

FR59FR47/51

A

IATA CODEAKG

1.16

8 m

(46.

60 in

)

2.451 m(96.50 in)

1.562 m(61.50 in)

1.534 m(60.40 in)

NAS 3610−2K2CLD3−46IATA CODE AKG

2.007 m(79.00 in)

1.534 m(60.40 in)

1.562 m(61.50 in)

IATA CODEAKH

NAS 3610−2K2CLD3−46WIATA CODE AKH

1.562 m(61.50 in)

1.534 m

(60.40 in)

1.16

8 m

(46.

60 in

)

1.16

8 m

(46.

60 in

)

PALLETNAS 3610−2K3PLD3−46P

A

Aft Cargo Compartment ArrangementPallets and Containers

FIGURE-03-50-01-991-004-A01

03-50-01Page 12

Jul 01/09


**ON A/C A320-100 A320-200

TASK 03-50-01-558-801-C01


1. GeneralThe aircraft has three cargo compartments.- The FWD cargo compartment (N˚1) in zone 130,- The aft cargo compartment (N˚4) in zone 150,- The bulk cargo compartment (N˚5) in zone 160.




A. Forward Cargo CompartmentThe forward cargo compartment is designed for the transport of bulk cargo and baggage or thefollowing unit load devices:- 3 x half size containers LD3-46 (NAS 3610-2K2C, IATA contour AKG)- 3 x full size containers LD3-46W (NAS 3610-2K2C, IATA contour AKH)- 3 x rectangular container LD3-46R (NAS 3610-2K2C, IATA contour AKJ)- 3 x 60.4x61.5 in pallets LD3-46P (NAS 3610-2K3P)See your WBM to determine applicable Y-arm.



1124A to 28

10.744 m(422.99 in)

1228 to 31

12.433 m(489.49 in)

1331 to 34

13.971 m(550.04 in)

Total24A to 34

12.283 m(483.58 in)


TABLE 1

03-50-01Page 13

Jul 01/09



11 10.700 m(421.26 in)

12 12.272 m(483.15 in)

13 13.844 m(545.04 in)


TABLE 2

B. Aft Lower Cargo CompartmentThe forward cargo compartment is designed for the transport of bulk cargo and baggage or thefollowing unit load devices:- 3 x half size containers LD3-46 (NAS 3610-2K2C, IATA contour AKG)- 3 x full size containers LD3-46W (NAS 3610-2K2C, IATA contour AKH)- 3 x rectangular container LD3-46R (NAS 3610-2K2C, IATA contour AKJ)- 3 x 60.4x61.5 in pallets LD3-46P (NAS 3610-2K3P)See your WBM to determine applicable Y-arm.



4147 to 50

22.085 m(869.49 in)

4250 to 52A/53

23.762 m(935.51 in)

4353 to 56

25.362 m(998.50 in)

4456 to 59

26.962 m(1061.50 in)

Total47 to 59

27.762 m(1092.99 in)


TABLE 3


41 22.084 m(869.45 in)

42 23.656 m(931.34 in)

03-50-01Page 14

Jul 01/09



43 25.229 m(993.27 in)

44 26.801 m(1055.16 in)


TABLE 4




5159 to 60

28.029 m(1103.50 in)

5260 to 62

28.829 m(1135.00 in)

5362 to 65

30.182 m(1188.27 in)

Total59 to 65

29.382 m(1156.77 in)


TABLE 5





TABLE 6

03-50-01Page 15

Jul 01/09


5. Procedure





Subtask 03-50-01-558-019-A01




03-50-01Page 16

Jul 01/09


**ON A/C A320-100 A320-200

FWDCARGODOOR

11 12

1.430 m(56.30 in)

2.630 m(103.54 in)

1.21

3 m

(47.

76 in

)0.

051

m(2

.00

in)

1.16

8 m

(46.

60 in

)

2.451 m(96.50 in)

1.562 m(61.50 in)

1.534 m(60.40 in)

CONTAINERSLD3−46

2.007 m(79.00 in)

1.534 m(60.40 in)

1.562 m(61.50 in)

CONTAINERSLD3−46W

1.562 m(61.50 in)

1.534 m

(60.40 in)

1.16

8 m

(46.

60 in

)

1.16

8 m

(46.

60 in

)

PALLET60.4 x 41.5 in

1.562 m(61.50 in)

1.534 m

(60.40 in)

1.16

8 m

(46.

60 in

)

CONTAINERSLD3−46R

13

FR24A FR34

A

N_AR_035001_1_0050101_01_00

A


FIGURE-03-50-01-991-005-A01

03-50-01Page 17

Jul 01/09


**ON A/C A320-100 A320-200

FWDCARGODOOR

41 42

1.430 m(56.30 in)

2.630 m(103.54 in)

1.21

3 m

(47.

76 in

)0.

051

m(2

.00

in)

1.16

8 m

(46.

60 in

)

2.451 m(96.50 in)

1.562 m(61.50 in)

1.534 m(60.40 in)

CONTAINERSLD3−46

2.007 m(79.00 in)

1.534 m(60.40 in)

1.562 m(61.50 in)

CONTAINERSLD3−46W

1.562 m(61.50 in)

1.534 m

(60.40 in)

1.16

8 m

(46.

60 in

)

1.16

8 m

(46.

60 in

)

PALLET60.4 x 41.5 in

1.562 m(61.50 in)

1.534 m

(60.40 in)

1.16

8 m

(46.

60 in

)

CONTAINERSLD3−46R

43 44

FR47 FR59

A

A

N_AR_035001_1_0060101_01_00


FIGURE-03-50-01-991-006-A01

03-50-01Page 18

Jul 01/09


**ON A/C A321-100 A321-200

TASK 03-50-01-558-801-D01


1. GeneralThe aircraft has three cargo compartments.- The FWD cargo compartment (N˚1 and 2) in zone 130,- The aft cargo compartment (N˚ 3 and 4) in zone 150,- The bulk cargo compartment (N˚5) in zone 160.




A. Forward Cargo CompartmentThe forward cargo compartment is designed for the transport of bulk cargo and baggage or thefollowing unit load devices:- 5 x half size containers LD3-46 (NAS 3610-2K2C, IATA contour AKG)- 5 x full size containers LD3-46W (NAS 3610-2K2C, IATA contour AKH)- 5 x 60.4x61.5 in pallets LD3-46P (NAS 3610-2K3P)See your WBM to determine applicable Y-arm.



1124A to 28

10.744 m(422.99 in)

1228 to 31

12.433 m(489.49 in)

2131 to 34

14.034 m(552.52 in)

2234 to 35.2

15.634 m(615.51 in)

2335.2 to 35.5

17.712 m(697.32 in)

03-50-01Page 19

Jul 01/09




Total24A to 35.5

13.883 m(546.57 in)


TABLE 1


11 10.700 m(421.26 in)

12 12.272 m(483.15 in)

21 13.844 m(545.04 in)

22 15.416 m(606.93 in)

23 16.988 m(668.82 in)


TABLE 2

B. Aft Lower Cargo CompartmentThe forward cargo compartment is designed for the transport of bulk cargo and baggage or thefollowing unit load devices:- 5 x half size containers LD3-46 (NAS 3610-2K2C, IATA contour AKG)- 5 x full size containers LD3-46W (NAS 3610-2K2C, IATA contour AKH)- 5 x 60.4x61.5 in pallets LD3-46P (NAS 3610-2K3P)See your WBM to determine applicable Y-arm.



3147.2 to 47.5

27.419 m(1079.49 in)

3247.5 to 50

29.096 m(1145.51 in)

3350 to 52A/53

30.696 m(1208.50 in)

4152A/53 to 56

32.296 m(1271.50 in)

03-50-01Page 20

Jul 01/09




4256 to 59

33.896 m(1334.49 in)

Total47.2 to 59

30.619 m(1205.47 in)

Bulk Cargo in Aft FWD Cargo Compartment Remaining Weight and Related H-arm

TABLE 3


31 27.445 m(1080.51 in)

32 29.017 m(1142.40 in)

33 30.589 m(1204.29 in)

41 32.161 m(1266.18 in)

42 33.733 m(1328.07 in)


TABLE 4




5159 to 60

34.963 m(1376.50 in)

5260 to 62

35.764 m(1408.03 in)

5362 to 65

37.123 m(1461.54 in)

03-50-01Page 21

Jul 01/09




Total59 to 65

36.322 m(1430.00 in)

Bulk Cargo in Aft FWD Cargo Compartment Remaining Weight and Related H-arm

TABLE 5





TABLE 6

5. Procedure





03-50-01Page 22

Jul 01/09


Subtask 03-50-01-558-020-A01

A. How to Find the Effect of Cargo and Baggage Remaining on the Deck



03-50-01Page 23

Jul 01/09


**ON A/C A321-100 A321-200

FWDCARGODOOR

11 12

1.430 m(56.30 in)

2.630 m(103.54 in)

1.21

3 m

(47.

76 in

)0.

051

m(2

.00

in)

21 22 23

A

A

ULD

CONTAINERWIDEBODYCOMPATIBLE

NAS3610 2K2CLD3−45IATA CODE AKG

PALLETWIDEBODYCOMPATIBLE

PALLETNSA3610 2K2P

CONTAINERFULL WIDTH

NAS3610 2K2CLD3−45IATA CODE AKH

N_AR_035001_1_0070101_01_00

FR24 FR35.5


FIGURE-03-50-01-991-007-A01

03-50-01Page 24

Jul 01/09


**ON A/C A321-100 A321-200

FWDCARGODOOR

31 32

1.430 m(56.30 in)

2.630 m(103.54 in)

1.21

3 m

(47.

76 in

)0.

051

m(2

.00

in)

33 41 42

A

ULD

CONTAINERWIDEBODYCOMPATIBLE

NAS3610 2K2CLD3−45IATA CODE AKG

PALLETWIDEBODYCOMPATIBLE

PALLETNSA3610 2K2P

CONTAINERFULL WIDTH

NAS3610 2K2CLD3−45IATA CODE AKH

A

N_AR_035001_1_0080101_01_00

FR47.1 FR59


FIGURE-03-50-01-991-008-A01

03-50-01Page 25

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 03-50-01-558-802-A01

Total Traffic Load Remaining Effect

1. GeneralThere are overhead stowage compartments for hand baggage and coats along the full length of thepassenger compartments, above the passenger seats.





REFERENCE DESIGNATIONDESC 09-50-01-001-A01 DESC 09-50-01-001-A01-Worksheets


TABLE 1

5. Procedure



Subtask 03-50-01-558-002-A01

A. How to Find the Effect of Traffic Load Remaining

(1) Use data from the Weight and Balance Manual and/or from your specific aircraftconfiguration data to find the weight, H-arm values and related moment of traffic loadremaining.

(2) Calculate H-arm moments generated by the traffic load and record it on the Traffic LoadRemaining Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01Page 26

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 03-50-01-558-803-A01

Ballast Added Effect

1. GeneralBallast is any heavy material that you use to add weight if you want to stabilize the aircraft with theCG change method.Ballast can be non recovery kit stock items (such as sand bags, drums filled with water, livestock feedsacks, etc.) that you can buy in-situ. It is important that the ballast is easily transportable to the site,easily managed by the personnel on site and that, if there is a shift in the aircraft CG, no secondarydamage will occur if the ballast moves inside the aircraft or when it is necessary to transport theaircraft.





REFERENCE DESIGNATIONDESC 09-50-01-001-A01 DESC 09-50-01-001-A01-Worksheets09-10-06 09-10-06-FUSELAGE FRAMES AND H-ARM TABLE09-10-08 09-10-08-WING RIBS AND STATIONS


TABLE 1

5. Procedure



03-50-01Page 27

Jul 01/09


Subtask 03-50-01-558-003-A01

A. How to find the Effect of Added Ballast

(1) To find the effect of added ballast, you need to find the H-arm and, if applicable, the Y-arm of the zone in which you added ballast.To calculate the necessary average H-arm and Y-arm:- See 09-10-06 for ballast added inside of fuselage,- See 09-10-08 for ballast added on the wing,

(2) Calculate the H-arm and Y-arm moments generated by the weight of ballast you use andrecord them on the Ballast Added Effect Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01Page 28

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 03-50-01-558-804-A01

Waste Water Remaining Effect

1. GeneralThe aircraft is equipped with a vacuum system.The waste water from the lavatories and galleys is stored in 1 waste tank (See DESC 09-10-12-006-A01 for tank capacity and pre-charged chemical fluid quantities).The waste tank is installed in the pressurized underfloor area in the aft fuselage.



Item Remaining Weight H-arm Moment to add

Tank N˚1 - A318 25.928 m (1020.79 in)

Tank N˚1 - A319 28.316 m (1114.80 in)

Tank N˚1 - A320 32.050 m (1261.81 in)

Tank N˚1 - A321 38.984 m (1534.80 in)

Waste Water Remaining Weight and Relevant H-arm

TABLE 1



REFERENCE DESIGNATIONDESC 09-10-12-006-A01 DESC 09-10-12-006-A01-Waste Water Disposal System

DESC 09-50-01-001-A01 DESC 09-50-01-001-A01-Worksheets


TABLE 2

5. Procedure


03-50-01Page 29

Jul 01/09



Subtask 03-50-01-558-004-A01

A. How to Find the Effect of Waste Water Remaining

(1) To find the effect of waste water remaining, you must know the weight of the waste waterremaining into tanks minus the pre-load. The generated H-arm moments must becalculated with the data given in the table in Job Setup References .

NOTE : The assumptions are that:- After a flight, 2/3 of the potable water is in the waste tank and the volume

of water remaining in the potable water tank is negligible,- At take off, the potable water tank are full.

(2) Calculate the H-arm moments generated by the waste water and report them on the WasteWater Remaining Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01Page 30

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 03-50-01-558-805-A01

Non OEW Catering Equipment Added Effect

1. GeneralIf your Weight and CG calculation is based on OEW, you need to include the NON-OEW CateringEquipment effect.







TABLE 1

5. Procedure



Subtask 03-50-01-558-005-A01

A. How to Find the Effect of NON-OEW Catering Equipment Added

(1) Use data from the Weight and Balance Manual and/or from your specific aircraftconfiguration data to find the weight and H-arm values and related moments of NON-OEW catering equipment, which was removed.

(2) Calculate H-arm moments generated by the NON-OEW Catering Equipment and recordthem on the NON-OEW Catering Equipment Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01Page 31

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 03-50-01-558-806-A01

Potable Water Removed Effect

1. GeneralThe aircraft is equipped with a pressurized potable water system.Potable water for the toilets and galleys is stored in 1 tank, which is installed in the pressurizedunderfloor area.See DESC 09-10-12-005-A01 for potable water tanks capacities.

NOTE : The number of items of equipment can change with the customer.


3. Job Setup ReferencesThe table that follow gives the average H-arm, from standard aircraft configuration.

Item Remaining Weight Average H-arm Moment to subtract

Tank N˚ 1 - A318 25.663 m (1010.35 in)

Tank N˚1 - A319 28.051 m (1104.37 in)

Tank N˚1 - A320 31.785 m (1251.38 in)

Tank N˚1 - A321 38.719 m (1524.37 in)

Average H-arm

TABLE 1



REFERENCE DESIGNATIONDESC 09-10-12-005-A01 DESC 09-10-12-005-A01-Potable Water System



TABLE 2

5. Procedure


03-50-01Page 32

Jul 01/09



Subtask 03-50-01-558-006-A01

A. How to Find the Effect of Potable Water Removed

(1) Weight and CG calculation is based on OEW or DOW, which include full potable watertank.

(2) To find the effect of removed potable water, you must know the weight of the potablewater which was moved to the waste tank during flight or manually removed on recoverysite. The generate H-arm moments have to be calculated with data provided in the table inJob Setup References .

NOTE : The assumptions are that:- After a flight, 2/3 of the potable water is in the waste tank and the volume

of water remaining in the potable water tank is negligible,- At take off, the potable water tank are full.

(3) Calculate H-arm moments generated by the Potable Water Removed and record it on thePotable Water Removed Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01Page 33

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 03-50-01-558-807-A01

Cockpit and Cabin Crew Removed Effect

1. GeneralWeight and CG calculation is based on OEW or DOW, which include cockpit and cabin crew.







TABLE 1

5. Procedure



Subtask 03-50-01-558-007-A01

A. How to Find the Effect of Removed Cockpit and Cabin Crew

(1) Use data from Weight and Balance Manual and/or from your specific aircraft configurationdata to find weight, H-arm value and related moment of cockpit and cabin crew included inthe OEW or in the DOW, which were removed.

(2) Calculate H-arm moments generated by the cockpit and cabin crew removed and report iton the Cockpit and Cabin Crew Removed interim worksheet (See DESC 09-50-01-001-A01).

03-50-01Page 34

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 03-50-01-558-808-A01

Catering Equipment Removed Effect

1. GeneralWeight and CG calculation is based on OEW or DOW, which include catering equipment.

NOTE : For Non-OEW Catering Equipment Effect, see TASK 03-50-01-558-805-A01.





REFERENCE DESIGNATIONTASK 03-50-01-558-805-A01 TASK 03-50-01-558-805-A01-Non OEW Catering Equipment

Added EffectDESC 09-50-01-001-A01 DESC 09-50-01-001-A01-Worksheets


TABLE 1

5. Procedure



Subtask 03-50-01-558-008-A01

A. How to find the Effect of Catering Equipment Removed

(1) Use data from the Weight and Balance Manual and/or from your specific aircraftconfiguration data to find the weight, H-arm and Y-arm and related moments of cateringequipment which was removed from OEW or DOW configuration.

03-50-01Page 35

Jul 01/09


(2) Calculate H-arm and Y-arm moments generated by the Catering Equipment Removed andreport it on the Catering Equipment Removed Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01Page 36

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 03-50-01-558-809-A01

Hydraulic Fluid Removed Effect

1. GeneralThe aircraft has 3 hydraulic circuits. See DESC 09-10-12-002-A01 for hydraulic circuit details.


3. Job Setup ReferencesThe tables that follow give the average H-arm from standard aircraft configuration, with HydraulicFluid removed. Use these values with the total weight of Hydraulic Fluid.The Weights are based on an Hydraulic Fluid density of 1.002 kg per liter.

Hydraulic System - A318

Item Capacity Remaining Weight H-arm Moment tosubtract

Green Tank 14 l (3.70 US gal) 16.594 m (653.31in)

Yellow Tank 12 l (3.17 US gal) 15.944 m (627.72in)

Blue Tank 6 l (1.59 US gal) 20.294 m (798.98in)

Systems 147 l (38.83 USgal)

16.708 m (657.80in)

A/C Total 202 l (53.36 USgal)

16.769 m (660.20in)

Hydraulic Fluid Tank Remaining Weight and Relevant H-arm - A318

TABLE 1






03-50-01Page 37

Jul 01/09





18.462 m (726.85in)


18.350 m (722.44in)


TABLE 2







20.168 m (794.02in)


20.040 m (788.98in)


TABLE 3







24.150 m (950.79in)

03-50-01Page 38

Jul 01/09





24.079 m (947.99in)


TABLE 4



REFERENCE DESIGNATIONDESC 09-10-12-002-A01 DESC 09-10-12-002-A01-Hydraulic System



TABLE 5

5. Procedure



Subtask 03-50-01-558-009-A01

A. How to Find the Effect of Hydraulic Fluid Removed

(1) Weight and CG calculation is based on OEW or DOW which include hydraulic fluid.

(2) Use the table in Job Setup References to calculate H-arm moment to subtract.

(3) Calculate H-arm moments generated by the hydraulic fluids removed and record them onthe Hydraulic Fluids Removed Interim Worksheet. (See DESC 09-50-01-001-A01).

03-50-01Page 39

Jul 01/09


**ON A/C A318-100

TASK 03-50-01-558-810-A01

Large Components Removed / Missing

1. GeneralThe equipment or aircraft parts that follow may have a significant effect on weight and balancemanagement for the recovery.- APU and tail cone- APU- Pax doors- Cargo doors- Radome- Pylon- Thrust reversers- Bare engines- Complete power plant- Rudders- VTP equipped- HTP equipped- Elevators- Slats- Flaps- Ailerons- Spoilers- Winglet / wingtip- Landing gear equipped- Landing gear Leg Fairing- Wheels- BrakesIf you need to remove some of these large components during recovery or if some of these largecomponents are missing when you start the recovery process, use the data that follow and calculationtables to determine the effect on NRW and the CG position.



A. Wing Equipment Table

Item Weight H-Arm H-Arm Moment

Slat 1 43 kg(95 lb)

14.092 m(554.80 in)

605.956 kgm(52706 lb.in)

03-50-01Page 40

Jul 01/09



Slat 2 30 kg(66 lb)

16.064 m(632.44 in)

481.920 kgm(41741.04 lb.in)

Slat 3 28 kg(62 lb)

17.412 m(685.51 in)

487.536 kgm(42501.62 lb.in)

Slat 4 25 kg(55 lb)

18.698 m(736.14 in)

467.45 kgm(40487.7 lb.in)

Slat 5 24 kg(53 lb)

19.912 m(783.94 in)

477.888 kgm(41548.82 lb.in)

Inner Flap 107 kg(236 lb)

18.331 m(721.69 in)

1961.417 kgm(170318.84 lb.in)

Outer Flap 120 kg(265 lb)

19.466 m(766.38 in)

2335.92 kgm(203090.7 lb.in)

Spoiler 1 16 kg(35 lb)

18.159 m(714.92 in)

290.544 kgm(25022.2 lb.in)


18.528 m(729.45 in)

259.392 kgm(22612.95 lb.in)


19.099 m(751.93 in)

248.287 kgm(21805.97 lb.in)


19.671 m(774.45 in)

236.052 kgm(22459.05 lb.in)


20.258 m(797.56 in)

283.612 kgm(24724.36 lb.in)

Aileron 24 kg(53 lb)

21.231 m(835.87 in)

509.544 kgm(44301.11 lb.in)

Wing Tip and Winglet 26 kg(57 lb)

21.504 m(846.61 in)

559.104 kgm(48256.77 lb.in)

Equipment on Wing

TABLE 1

B. Fuselage Equipment Table


Forward Passenger/Crew Door 98 kg(216 lb)

7.579 m(298.39 in)

742.742 kgm(64452.24 lb.in)

Aft Passenger/Crew Door 96 kg(212 lb)

25.960 m(1022.05 in)

2492.16 kgm(216674.6 lb.in)

Emergency Exit 13 kg(29 lb)

15.430 m(607.48 in)

200.59 kgm(17616.92 lb.in)

03-50-01Page 41

Jul 01/09



Forward Cargo Door 91 kg(201 lb)

10.433 m(410.75 in)

949.403 kgm(82560.75 lb.in)

Aft Cargo Door 103 kg(227 lb)

21.507 m(846.73 in)

2215.221 kgm(192207.71 lb.in)

Radome 26 kg(57 lb)

3.300 m(129.92 in)

85.8 kgm(7405.44 lb.in)

APU and Tailcone 470 kg(1036 lb)

31.862 m(1254.41 in)

14975.14 kgm(1299568.76 lb.in)

APU 139 kg(306 lb)

32.032 m(1261.10 in)

4452.448 kgm(385896.6 lb.in)

Fuselage Equipment

TABLE 2

C. Vertical Stabilizer Equipment Table


Box 270 kg(595 lb)

30.519 m(1201.54 in)

8240.13 kgm(714916.3 lb.in)

Rudder 95 kg(209 lb)

31.621 m(1244.92 in)

3003.995 kgm(260188.28 lb.in)

Removable Leading Edge 75 kg(165 lb)

29.296 m(1153.39 in)

2197.2 kgm(190309.35 lb.in)

Tip 20 kg(44 lb)

32.549 m(1281.46 in)

650.98 kgm(56384.24 lb.in)

Fuselage Fairing 11 kg(24 lb)

29.832 m(1174.49 in)

328.152 kgm(28187.76 lb.in)

VTP Equipment

TABLE 3

D. Horizontal Stabilizer Equipment Table


Box 417 kg(919 lb)

30.413 m(1197.36 in)

12682.221 kgm(1100373.84 lb.in)

Elevator 96 kg(212 lb)

31.909 m(1256.26 in)

3063.264 kgm(266327.12 lb.in)


30.219 m(1189.72 in)

2538.396 kgm(220098.2 lb.in)

03-50-01Page 42

Jul 01/09



Tip 6 kg(13 lb)

32.355 m(1273.82 in)

194.13 kgm(16559.66 lb.in)

Tailplane Fuselage Fairing 7 kg(15 lb)

31.135 m(1225.79 in)

217.945 kgm(18386.85 lb.in)

HTP Equipment

TABLE 4

E. Power Plant Equipment Table


Inlet Cowl 138 kg(304 lb)

11.960 m(470.87 in)

1650.48 kgm(143144.48 lb.in)

Fan Cowl LH 37 kg(82 lb)

12.820 m(504.72 in)

474.34 kgm(41387.04 lb.in)

Fan Cowl RH 42 m(1654 in)

12.820 m(504.72 in)

538.44 kgm(834806.88 lb.in)

Thrust Reverser LH 193 kg(425 lb)

13.943 m(548.94 in)

2691 kgm(233299.5 lb.in)

Thrust Reverser RH 212 kg(467 lb)

13.943 m(548.94 in)

2955.916 kgm(256354.98 lb.in)

Bare Engine 2778 kg(6124 lb)

13.541 m(533.11 in)

3766.898 kgm(3264765.64 lb.in)

Complete Power Plant 3501 kg(7718 lb)

13.565 m(534 in)

47491.065 kgm(4121412 lb.in)

Pylon 593 kg(1307 lb)

15.118 m(595.20 in)

8964.974 kgm(777926.4 lb.in)

Power Plant Equipment - CFM 56 Engine

TABLE 5



11.921 m(469.33 in)

1513.967 kgm(131412.4 lb.in)

Fan Cowl 90 kg(198 lb)

12.803 m(504.06 in)

1152.27 kgm(99803.88 lb.in)

Thrust Reverser 579 kg(1276 lb)

13.290 m(523.23 in)

7694.91 kgm(667641.48 lb.in)

03-50-01Page 43

Jul 01/09




13.640 m(537.01 in)

36064.16 kgm(3130231.229 lb.in)


13.673 m(538.31 in)

48771.591 kgm(4233269.84 lb.in)


15.227 m(599.49 in)

8770.752 kgm(761352.3 lb.in)

Power Plant Equipment - PW 6000 Engine

TABLE 6

F. Landing Gear Equipment Table


Nose Landing Gear Complete 327 kg(721 lb)

7.600 m(299.21 in)

2485.2 kgm(215730.41 lb.in)

Wheel with Tire 35 kg(77 lb)

7.605 m(299.41 in)

266.175 kgm(23054.57 lb.in)

NLG Equipment

TABLE 7


MLG Leg Fairing 16 kg(35 lb)

17.225 m(678.15 in)

275.6 kgm(23735.25 lb.in)

Main Landing Gear Complete 1010 kg(2227 lb)

17.670 m(695.67 in)

17846.7 kgm(1549257.09 lb.in)


17.862 m(703.23 in)

2411.37 kgm(209562.54 lb.in)

Brake 69 kg(152 lb)

17.862 m(703.23 in)

1232.478 kgm(106890.96 lb.in)

MLG Equipment

TABLE 8

03-50-01Page 44

Jul 01/09






TABLE 9

5. Procedure



WARNING : YOU MUST CONTACT AIRBUS BEFORE YOU MANUALLY OPERATE A SYSTEMOR REMOVE A COMPONENT WHEN THE AIRCRAFT IS IN AN ABNORMALATTITUDE OR DISABLED. THE AMM PROCEDURES ARE APPLICABLE ON ANAIRCRAFT IN A LEVEL CONFIGURATION ONLY.


Subtask 03-50-01-558-010-A01

A. How to find the Effect of Large Components Removed / Missing

(1) See the tables in Job Setup References to determine the weight, H-arm, Y-arm and Z-armMoment.

(2) Record Weight, H-arm, Y-arm and Z-arm moment into the relevant boxes of the LargeComponent Removed / Missing Effect Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01Page 45

Jul 01/09


**ON A/C A319-100

TASK 03-50-01-558-810-B01







Slat 1 43 kg(95 lb)

14.092 m(554.80 in)

605.956 kgm(52706 lb.in)

03-50-01Page 46

Jul 01/09



Slat 2 30 kg(66 lb)

16.064 m(632.44 in)

481.92 kgm(41741.04 lb.in)

Slat 3 28 kg(62 lb)

17.412 m(685.51 in)

487.536 kgm(42501.62 lb.in)

Slat 4 25 kg(55 lb)

18.698 m(736.14 in)

467.45 kgm(40487.7 lb.in)

Slat 5 24 kg(53 lb)

19.912 m(783.94 in)

477.888 kgm(41548.82 lb.in)


18.331 m(721.69 in)

1961.41 kgm(170318.84 lb.in)


19.466 m(766.38 in)

2335.92 kgm(203090.7 lb.in)


18.159 m(714.92 in)

290.544 kgm(25022.2 lb.in)


18.528 m(729.45 in)

259.392 kgm(22612.95 lb.in)


19.099 m(751.93 in)

248.287 kgm(21805.97 lb.in)


19.671 m(774.45 in)

236.052 kgm(20135.7 lb.in)


20.258 m(797.56 in)

283.612 kgm(24724.36 lb.in)


21.231 m(835.87 in)

509.544 kgm(44301.11 lb.in)


21.504 m(846.61 in)

559.104 kgm(48256.77 lb.in)

Equipment on Wing

TABLE 1




7.579 m(298.39 in)

742.742 kgm(64452.24 lb.in)


28.351 m(1116.18 in)

2721.696 kgm(236630.16 lb.in)

Emergency Exit (Optional) 15 kg(33 lb)

15.371 m(605.16 in)

230.57 kgm(19970.28 lb.in)

03-50-01Page 47

Jul 01/09




16.217 m(638.46 in)

243.255 kgm(31069.18 lb.in)


13.240 m(521.26 in)

1482.88 kgm(128751.22 lb.in)


25.635 m(1009.25 in)

2871.12 kgm(249284.75 lb.in)

Radome 26 kg(57 lb)

3.300 m(129.92 in)

85.8 kgm(7405.44 lb.in)


34.241 m(1348 in)

15750.86 kgm(1366872 lb.in)

APU 137 kg(302 lb)

34.420 m(1355.12 in)

4715.54 kgm(409246.24 lb.in)

Fuselage Equipment

TABLE 2



Box 270 kg(595 lb)

32.117 m(1264.45 in)

8671.59 kgm(752347.75 lb.in)


33.963 m(1337.13 in)

3090.633 kgm(268763.13 lb.in)


30.894 m(1216.30 in)

2378.838 kgm(206771 lb.in)

Tip 10 kg(22 lb)

34.176 m(1345.51 in)

341.76 kgm(29601.22 lb.in)


31.440 m(1237.80 in)

471.6 kgm(40847.4 lb.in)

VTP Equipment

TABLE 3



Box 417 kg(919 lb)

32.800 m(1291.34 in)

13677.6 kgm(1186741.46 lb.in)


34.296 m(1350.24 in)

3292.416 kgm(286250.88 lb.in)

03-50-01Page 48

Jul 01/09




32.606 m(1283.70 in)

2738.904 kgm(237484.5 lb.in)

Tip 6 kg(13 lb)

34.742 m(1367.80 in)

208.452 kgm(17781.4 lb.in)


33.522 m(1319.76 in)

234.654 kgm(19796.4 lb.in)

HTP Equipment

TABLE 4




12.748 m(501.89 in)

1759.224 kgm(152574.56 lb.in)


13.608 m(535.75 in)

503.496 kgm(43931.5 lb.in)


13.608 m(535.75 in)

571.536 kgm(886130.5 lb.in)


14.731 m(579.96 in)

2843.083 kgm(246440.5 lb.in)


14.731 m(579.96 in)

3122.972 kgm(270841.32 lb.in)


14.329 m(564.13 in)

39805.962 kgm(3454732.12 lb.in)


14.353 m(565.08 in)

50249.853 kgm(4361287.44 lb.in)


15.906 m(626.22 in)

9432.258 kgm(818469.54 lb.in)


TABLE 5



12.479 m(491.30 in)

1509.959 kgm(131177.1 lb.in)


13.577 m(534.53 in)

1330.546 kgm(115458.48 lb.in)

03-50-01Page 49

Jul 01/09




15.005 m(590.75 in)

7772.59 kgm(674636.5 lb.in)


14.366 m(565.59 in)

38285.39 kgm(3322841.25 lb.in)


14.454 m(569.06 in)

50878.08 kgm(4415905.6 lb.in)


15.860 m(624.41 in)

9468.42 kgm(821723.56 lb.in)

Power Plant Equipment - IAE V2500 Engine

TABLE 6




7.600 m(299.21 in)

2485.2 kgm(215730.41 lb.in)


7.605 m(299.41 in)

266.175 kgm(23054.57 lb.in)

NLG Equipment

TABLE 7



18.013 m(709.17 in)

288.208 kgm(24820.95 lb.in)


18.458 m(726.69 in)

18642.58 kgm(1618338.63 lb.in)


18.650 m(734.25 in)

2517.75 kgm(218806.5 lb.in)

Brake 69 kg(152 lb)

18.650 m(734.25 in)

1286.85 kgm(111606 lb.in)

MLG Equipment

TABLE 8

03-50-01Page 50

Jul 01/09






TABLE 9

5. Procedure





Subtask 03-50-01-558-012-A01




03-50-01Page 51

Jul 01/09


**ON A/C A320-100 A320-200

TASK 03-50-01-558-810-C01







Slat 1 39 kg(86 lb)

16.470 m(648.43 in)

642.33 kgm(55764.98 lb.in)

03-50-01Page 52

Jul 01/09



Slat 2 30 kg(66 lb)

18.460 m(726.77 in)

553.8 kgm(47966.82 lb.in)

Slat 3 28 kg(62 lb)

19.790 m(779 in)

554.12 kgm(48298 lb.in)

Slat 4 25 kg(55 lb)

21.070 m(829.53 in)

526.75 kgm(45624.15 lb.in)

Slat 5 23 kg(51 lb)

22.290 m(877.56 in)

512.67 kgm(44755.56 lb.in)


20.716 m(815.59 in)

2361.624 kgm(204713.09 lb.in)


21.872 m(861.10 in)

2668.384 kgm(231635.9 lb.in)


20.394 m(802.91 in)

305.91 kgm(26496.03 lb.in)


20.824 m(819.84 in)

270.712 kgm(23775.36 lb.in)


21.424 m(843.46 in)

257.088 kgm(21929.96 lb.in)


21.984 m(865.51 in)

263.808 kgm(22503.26 lb.in)


22.519 m(886.57 in)

315.266 kgm(27483.67 lb.in)


23.582 m(928.43 in)

565.968 kgm(49206.79 lb.in)

Wing Tip (A320-100) 15 kg(33 lb)

23.680 m(932.28 in)

355.2 kgm(30765.24 lb.in)

Wing Tip and Winglet(A320-200)

26 kg(57 lb)

23.960 m(943.31 in)

622.96 kgm(53768.67 lb.in)

Equipment on Wing

TABLE 1




7.579 m(298.39 in)

742.742 kgm(64452.24 lb.in)


32.085 m(1263.19 in)

3080.16 kgm(267796.28 lb.in)

03-50-01Page 53

Jul 01/09




16.971 m(668.15 in)

267.27 kgm(2248.95 lb.in)


17.818 m(701.50 in)

267.27 kgm(23149.5 lb.in)


10.700 m(421.26 in)

1294.7 kgm(265203.09 lb.in)


25.229 m(993.27 in)

3052.709 kgm(265203.09 lb.in)

Bulk Cargo Door 37 kg(82 lb)

28.859 m(1136.18 in)

1067.783 kgm(93166.76 lb.in)

Radome 26 kg(57 lb)

3.300 m(129.92 in)

85.8 kgm(7405.44 lb.in)


37.985 m(1495.47 in)

17473.1 kgm(1516406.58 lb.in)

APU 136 kg(300 lb)

38.155 m(1502.17 in)

5189.08 kgm(450651 lb.in)

Fuselage Equipment

TABLE 2



Box 365 kg(805 lb)

36.003 m(1417.44 in)

13141.095 kgm(1141039.2 lb.in)


37.702 m(1484.33 in)

3317.776 kgm(287960.02 lb.in)


35.332 m(1391.02 in)

1695.936 kgm(147448.12 lb.in)

Tip 9 kg(20 lb)

37.910 m(1492.52 in)

341.19 kgm(39850.4 lb.in)

Dorsal Fin 26 kg(57 lb)

33.067 m(1301.85 in)

859.742 kgm(74205.45 lb.in)


35.174 m(1384.80 in)

527.61 kgm(45698.4 lb.in)

VTP Equipment

TABLE 3

03-50-01Page 54

Jul 01/09




Box 418 kg(922 lb)

36.534 m(1438.35 in)

15271.212 kgm(1326158.7 lb.in)


38.030 m(1497.24 in)

3688.91 kgm(320409.36 lb.in)


36.340 m(1430.71 in)

3052.56 kgm(264681.35 lb.in)

Tip 6 kg(13 lb)

38.476 m(1514.80 in)

230.856 kgm(19692.4 lb.in)


37.256 m(1466.77 in)

260.792 kgm(22001.55 lb.in)

HTP Equipment

TABLE 4




14.453 m(569.02 in)

1994.514 kgm(172982.08 lb.in)


15.296 m(602.20 in)

565.952 kgm(49380.4 lb.in)


15.296 m(602.20 in)

642.432 kgm(996038.8 lb.in)


16.369 m(644.45 in)

3159.217 kgm(273891.25 lb.in)


16.369 m(644.45 in)

3470.228 kgm(300958.15 lb.in)


15.963 m(628.46 in)

44345.214 kgm(3848689.04 lb.in)


15.987 m(629.41 in)

55970.487 kgm(4857786.38 lb.in)


15.987 m(629.41 in)

9480.291 kgm(822638.87 lb.in)


TABLE 5

03-50-01Page 55

Jul 01/09




14.110 m(555.51 in)

1707.31 kgm(148321.17 lb.in)


15.120 m(595.28 in)

1481.76 kgm(128580.48 lb.in)


16.524 m(650.55 in)

8559.432 kgm(742928.1 lb.in)


15.975 m(628.94 in)

42573.375 kgm(3695022.5 lb.in)


16.063 m(632.40 in)

56541.76 kgm(4907424 lb.in)


17.514 m(689.53 in)

10455.858 kgm(907421.48 lb.in)


TABLE 6




7.617 m(299.88 in)

2460.291 kgm(213514.56 lb.in)


7.628 m(300.31 in)

274.608 kgm(23724.49 lb.in)

NLG Equipment

TABLE 7



19.675 m(774.61 in)

314.8 kgm(27111.35 lb.in)

Main Landing Gear Complete(Twin Wheel MLG)

931 kg(2053 lb)

20.067 m(790.04 in)

18682.377 kgm(1621952.12 lb.in)

Wheel with Tire and Brake(Twin Wheel MLG)

204 kg(450 lb)

20.250 m(797.24 in)

4131 kgm(358758 lb.in)

Main Landing Gear Complete(Optional Four Wheel BogieMLG)

1234 kg(2721 lb)

20.056 m(789.61 in)

24749.104 kgm(2148528.81 lb.in)

03-50-01Page 56

Jul 01/09



Wheel with Tire and Brake(Optional Four Wheel BogieMLG)

114 kg(251 lb)

20.266 m(797.87 in)

2310.324 kgm(200265.37 lb.in)

MLG Equipment

TABLE 8





TABLE 9

5. Procedure





03-50-01Page 57

Jul 01/09


Subtask 03-50-01-558-013-A01




03-50-01Page 58

Jul 01/09


**ON A/C A321-100 A321-200

TASK 03-50-01-558-810-D01







Slat 1 43 kg(95 lb)

20.747 m(816.81 in)

892.121 kgm(77596.95 lb.in)

03-50-01Page 59

Jul 01/09



Slat 2 31 kg(68 lb)

22.719 m(894.45 in)

704.289 kgm(60822.6 lb.in)

Slat 3 28 kg(62 lb)

24.067 m(947.52 in)

673.876 kgm(58746.24 lb.in)

Slat 4 27 kg(60 lb)

25.353 m(998.15 in)

684.531 kgm(59889 lb.in)

Slat 5 25 kg(55 lb)

26.567 m(1045.94 in)

664.175 kgm(57526.7 lb.in)


25.195 m(991.93 in)

3124.18 kgm(270796.89 lb.in)

Inner Flap Tab 85 kg(187 lb)

25.195 m(991.93 in)

2141.575 kgm(185490.91 lb.in)


26.143 m(1029.25 in)

3137.16 kgm(272751.25 lb.in)

Outer Flap Tab 80 kg(176 lb)

26.139 m(1029.09 in)

2091.12 kgm(181119.84 lb.in)


24.754 m(974.57 in)

396.064 kgm(34109.95 lb.in)


25.205 m(992.32 in)

352.87 kgm(30761.92 lb.in)


25.754 m(1013.94 in)

334.802 kgm(39404.26 lb.in)


26.267 m(1034.13 in)

315.204 kgm(26887.38 lb.in)


26.913 m(1059.57 in)

376.782 kgm(32846.67 lb.in)


27.854 m(1096.61 in)

668.496 kgm(58120.33 lb.in)


28.165 m(1108.86 in)

732.29 kgm(63205.02 lb.in)

Equipment on Wing

TABLE 1




7.579 m(298.39 in)

742.742 kgm(64452.24 lb.in)

03-50-01Page 60

Jul 01/09




39.016 m(1536.06 in)

3745.536 kgm(325644.72 lb.in)

Emergency Exit FWD RH 70 kg(154 lb)

16.384 m(645.04 in)

1146.88 kgm(99336.16 lb.in)

Emergency Exit FWD LH 81 kg(179 lb)

16.384 m(645.04 in)

1327.104 kgm(115462.16 lb.in)

Emergency Exit Aft 70 kg(154 lb)

27.331 m(1076.02 in)

1913.17 kgm(165707.08 lb.in)


10.681 m(420.51 in)

1196.272 kgm(103865.97 lb.in)


32.139 m(1265.32 in)

3599.568 kgm(312534.04 lb.in)

Bulk Cargo Door 34 kg(75 lb)

35.793 m(1409.17 in)

1216.962 kgm(105687.75 lb.in)

Radome 26 kg(57 lb)

3.300 m(129.92 in)

85.8 kgm(7405.44 lb.in)


44.923 m(1768.62 in)

20664.58 kgm(1793380.68 lb.in)

APU 145 kg(320 lb)

45.089 m(1775.16 in)

6537.905 kgm(598051.2 lb.in)

Fuselage Equipment

TABLE 2



Box 270 kg(595 lb)

42.797 m(1684.92 in)

11555.19 kgm(1002527.4 lb.in)


44.631 m(1757.13 in)

4061.421 kgm(353183.13 lb.in)


41.562 m(1636.30 in)

3200.274 kgm(278171 lb.in)

Tip 10 kg(22 lb)

44.844 m(1765.51 in)

448.44 kgm(38841.22 lb.in)

03-50-01Page 61

Jul 01/09




42.108 m(1657.80 in)

631.62 kgm(54707.4 lb.in)

VTP Equipment

TABLE 3



Box 417 kg(919 lb)

43.468 m(1711.34 in)

18126.156 kgm(1572721.46 lb.in)


44.964 m(1770.24 in)

4316.544 kgm(375.290.88 lb.in)


43.274 m(1703.70 in)

359.016 kgm(315184.5 lb.in)

Tip 6 kg(13 lb)

45.410 m(1787.80 in)

272.46 kgm(23241.4 lb.in)


44.190 kg(97.42 lb)

309.33 kgm(1461.3 lb.in)

HTP Equipment

TABLE 4




18.615 m(732.87 in)

2568.87 kgm(222792.48 lb.in)


19.475 m(766.73 in)

720.575 kgm(62871.86 lb.in)


19.475 m(766.73 in)

817.95 kgm(1268171.42 lb.in)


20.598 m(810.94 in)

3975.414 kgm(344649.5 lb.in)


20.598 m(810.94 in)

4366.776 kgm(378708.98 lb.in)


20.196 m(795.12 in)

56104.488 kgm(4869314.88 lb.in)


20.220 m(796.06 in)

70790.22 kgm(6143991.08 lb.in)

03-50-01Page 62

Jul 01/09




21.773 m(857.20 in)

12911.389 kgm(1120360.4 lb.in)


TABLE 5



18.346 m(722.28 in)

2219.866 kgm(192848.76 lb.in)


19.444 m(765.51 in)

1905.512 kgm(165350.16 lb.in)


20.872 m(821.73 in)

10811.696 kgm(938415.66 lb.in)


20.233 m(796.57 in)

53920.945 kgm(4679848.75 lb.in)


20.321 m(800.04 in)

71529.92 kgm(6208310.4 lb.in)


21.727 m(855.39 in)

12971.019 kgm(1125693.24 lb.in)


TABLE 6



Nose Landing Gear Complete 327 kg(720.91 lb)

7.600 m(299.21 in)

2485.2 kgm(215703.4811 lb.in)


7.605 m(299.41 in)

266.175 kgm(23054.57 lb.in)

NLG Equipment

TABLE 7



23.960 m(943.31 in)

551.08 kgm(48108.81 lb.in)


24.339 m(958.23 in)

28622.664 kgm(2484690.29 lb.in)

03-50-01Page 63

Jul 01/09




24.517 m(965.24 in)

4069.822 kgm(353277.84 lb.in)

Brake 93 kg(205 lb)

24.517 m(965.24 in)

2280.081 kgm(197874.2 lb.in)

MLG Equipment

TABLE 8





TABLE 9

5. Procedure





03-50-01Page 64

Jul 01/09


Subtask 03-50-01-558-014-A01




03-50-01Page 65

Jul 01/09


**ON A/C A318-100 A319-100

TASK 03-50-01-558-811-A01

Large Components Movement Effect

1. GeneralThe CG positions of the OEW or the DOW apply to specific aircraft conditions which include thelanding gear extended and the flaps and slats retracted.

NOTE : The thrust reverser extension effect is negligible on the A/C CG.



A. Landing Gear Retraction

Landing Gear Retraction H-arm Moment to Subtract

NLG 204 kgm (17706 lb.in)

MLG 801 kgm (69523 lb.in)

L/G Retraction Effect

TABLE 1

B. Droop Nose, Slats and Flaps Extension Effect

H-arm MomentsCockpit IndicationSlats / Flaps Slats Flaps Total

0 0.0 0.0 0.0

AUTOMATIC- 96.5 kgm(- 8376 lb.in) 0.0

- 96.5 kgm(- 8376 lb.in)

1- 96.5 kgm(- 8376 lb.in)

220.0 kgm(19095 lb.in)

123.5 kgm(10719 lb.in)

2- 106.0 kgm(- 9200 lb.in)

275.5 kgm(23912 lb.in)

169.5 kgm(14712 lb.in)

3- 106.0 kgm(- 9200 lb.in)

330.5 kgm(28686 lb.in)

224.5 kgm(19486 lb.in)

FULL- 118.1 kgm(- 10251 lb.in)

358.1 kgm(31082 lb.in)

240.0 kgm(20831 lb.in)

Slats and Flaps Extension Effect

TABLE 2

NOTE : Add or subtract H-arm moments in accordance with the positive or negatives values.

03-50-01Page 66

Jul 01/09






TABLE 3

5. Procedure

WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLSURFACES AND THE LANDING GEARS AND RELATED DOORS ARE CLEAR.MOVEMENT OF THE CONTROL SURFACES AND LANDING GEARS/DOORS CANCAUSE INJURY TO PERSONS AND/OR DAMAGE TO THE AIRCRAFT OREQUIPMENT.




Subtask 03-50-01-558-011-A01

A. How to Find the Effect of Large Component Movement

(1) To find the effect of large component movement, you must know the moments (generatedby H-arm and Y-arm) depending of Aircraft Landing Gear retraction and Slats and Flapsextension.

(2) To know this, see Job Setup References and record the H-arm and Y-arm moment on theLarge Component Movement Effect Interim Worksheet (See DESC 09-50-01-001-A01).

03-50-01Page 67

Jul 01/09


**ON A/C A320-100 A320-200

TASK 03-50-01-558-811-B01










L/G Retraction Effect - Twin Wheel MLG

TABLE 1




L/G Retraction Effect - Optional Four Wheel Bogie MLG

TABLE 2


H-arm MomentsCockpit IndicationSlats / Flaps Slats Flaps

Total

0 0.0 0.0 0.0

AUTOMATIC- 96.5 kgm(- 8376 lb.in) 0.0

- 96.5 kgm(- 8376 lb.in)

1- 96.5 kgm(- 8376 lb.in)

220.0 kgm(19095 lb.in)

123.5 kgm(10719 lb.in)

2- 96.5 kgm(- 8376 lb.in)

275.5 kgm(23912 lb.in)

179.0 kgm(15536 lb.in)

3- 96.5 kgm(- 8376 lb.in)

330.5 kgm(28686 lb.in)

234.0 kgm(20310 lb.in)

03-50-01Page 68

Jul 01/09


H-arm MomentsCockpit IndicationSlats / Flaps Slats Flaps

Total

FULL- 118.1 kgm(- 10251 lb.in)

358.1 kgm(31081 lb.in)

240.0 kgm(20831 lb.in)


TABLE 3

NOTE : Add or subtract H-arm moments in accordance with positive or negative values.





TABLE 4

5. Procedure





03-50-01Page 69

Jul 01/09


Subtask 03-50-01-558-015-A01




03-50-01Page 70

Jul 01/09


**ON A/C A321-100 A321-200

TASK 03-50-01-558-811-C01









MLG 1017 kgm (88271 lb.in)

L/G Retraction Effect

TABLE 1


H-arm MomentsCockpit IndicationSlats / Flaps Slats Flaps Total

0 0.0 0.0 0.0

AUTOMATIC-101.8 kgm(- 8836 lb.in) 0.0

-101.8 kgm(- 8836 lb.in)

1-101.8 kgm(- 8836 lb.in)

285.0 kgm(24737 lb.in)

183.2 kgm(15901 lb.in)

2- 111.9 kgm(- 9712 lb.in)

328.4 kgm(28504 lb.in)

216.5 kgm(18791 lb.in)

3- 111.9 kgm(- 9712 lb.in)

377.0 kgm(32722 lb.in)

265.1 kgm(23009 lb.in)

FULL-124.6 kgm(-10815 lb.in)

395.7 kgm(34345 lb.in)

271.1 kgm(23530 lb.in)


TABLE 2

NOTE : Add or subtract H-arm moments in accordance with positive or negative values.

03-50-01Page 71

Jul 01/09






TABLE 3

5. Procedure





Subtask 03-50-01-558-016-A01




03-50-01Page 72

Jul 01/09


03-60-01 REFERENCE FOR CALCULATION

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 03-60-01-001-A01

Information Required and Source Data

1. General

CAUTION : THE NRW AND CG LOCATION CAN ONLY BE AS ACCURATE AS THE DATAUSED TO CALCULATE THEM. IF ACCURATE DATA IS NOT AVAILABLE OR IFTHE DATA USED ARE EXTRAPOLATIONS, THIS WILL HAVE AN EFFECT ONTHE RESULTS THAT YOU GET.

This section gives the details on definitions related to CG management, and the source of therequired data. It also tells you how to use these data to calculate the NRW and CG location.In most cases, several sources exist to find the required data.Accurate calculations require specific data based on the specific aircraft MSN and actual airline loadand trim sheet information.In case of a serious aircraft accident and subsequent freeze of the aircraft documentation, genericaircraft type data can be used. This can also apply if it is impossible to power the onboardcomputers.

NOTE : Contact telephone numbers for the load and weight and balance office should be readilyavailable.

**ON A/C A318-100

2. OEW (Operating Empty Weight) or DOW (Dry Operating Weight) and associated H-arm:

CAUTION : IF YOU USE THE OEW GENERIC DATA TO CALCULATE THE NRW, THE CGPOSITION AND THE EXPECTED LOADS, THE RESULTS YOU GET WILL NOTBE ACCURATE.

It is possible to take the data from these sources:- Airline Load and Trim Sheet,- Onboard Computers,- Weight and Balance Manual,- The generic OEW with an associated CG at 25 %RC is about 38818 kg (85579 lb) with CFM

engines or 38661 kg (85233 lb) with PW Engines.

NOTE : The OEW or DOW and the associated H-arm are given for a specific aircraft configuration:all landing gear extended flight control retracted and thrust reversers in stored position.

03-60-01Page 1

Jul 01/09


**ON A/C A319-100




engines or 39826 kg (87801 lb) with IAE engines.


**ON A/C A320-100



It is possible to take the data from these sources:- Airline Load and Trim Sheet,- Onboard Computers,- Weight and Balance Manual,- The generic OEW with an associated CG at 25 %RC. is about 41244 kg (90927 lb) with CFM

engines.


**ON A/C A320-200





03-60-01Page 2

Jul 01/09



**ON A/C A321-100 A321-200






**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

7. Source Data

A. Flight Crew- Weight and H-arm are specific to the operator,- Use generic data from the Weight and Balance Manual.

B. Cabin Crew- Weight and H-arm are specific to the operator,- Use generic data from the Weight and Balance Manual.

C. Remaining fuel

(1) The means of extracting data that can be used:- Use data from the total fuel weight from load and trim sheet,- Use data from MCDU,- Do the measurements from dip sticks or do an estimation based on fuel load of 1/4,

1/2, 3/4 (See 03-20-02 and 03-20-01),- Do an estimation of the remaining fuel weight from the trim load sheet based on the

operator’s known fuel consumption.

(2) Find the associated H-arm and Y-arm. Theses values depend on the distribution of the fuelload. See 03-20-02 to assess the fuel quantity (dip stick, MCDU, or specific method), andassociated H-arm and Y-arm.

D. PayloadThis could be split in passengers and cargo:

03-60-01Page 3

Jul 01/09


(1) Passenger PayloadIn most cases, the passengers will have removed carry on luggage, unless an emergencyevacuation took place in which case it is necessary to take the weight of the carry onluggage into account.- Take the total passenger weight from the load and trim sheet,- H-arm: The operator should provide the H-arm relevant to its cabin sections.- H-arm should be calculated from 03-50-01.

(2) Cargo Payload- Use the total cargo payload weight from the load and trim sheet,- H-arm : the operator should give the H-arm associated to cargo compartments,- H-arm : extract generic data from the Weight and Balance Manual,- Calculate H-arm see 03-50-01- Do approximate weight and position estimations based on observation,- Ask for assistance of airline load office.

E. Weight and H-arm of any Missing or Removed Large Components- Take the weight of the removed units,- Use weights and moments listed in chapter 03-50-01,- Use details from the Weight and Balance Manual.

F. Weight of the operator’s equipment- Use data from the Weight and Balance Manual.- H-arm calculated in chapter 03-50-01,

G. Weight of Fluids either Removed or On Board- Use data from the Weight and Balance Manual.- H-arm calculated in 03-50-01,

H. Weight and Location of Catering Equipment and Water Remaining On Board.Weight and H-arm depend on the aircraft configuration, the operator’s route being flown andthe season of operation:- Use generic data from the Weight and Balance Manual.

J. Change of the moment with landing gear retracted or leading edge and trailing edge surfacesextended.- See 03-50-01

03-60-01Page 4

Jul 01/09


PREPARATION

04-00-00 PREPARATION

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 04-00-00-001-A01

General

1. TetheringIt is generally agreed that the aircraft must be tethered during recovery leveling and lifting operations.However, it is necessary to evaluate carefully the benefit and purpose.

A. During leveling or lifting, make sure that the aircraft is stable, and prevent uncontrolledmovement of the aircraft.This movement can be caused by:- Change of CG position during aircraft lifting/leveling- Weather conditions- Terrain conditions change: humidity, temperature, soil capability.

B. These conditions will help you decide whether to tether the aircraft or not:- Aircraft attitude- Leveling/lifting procedure used- Terrain conditions- Wind/weather condition- Increase of aircraft stability foreseen.It is necessary to do an evaluation of the tethering loads. They must be in the aircraft allowablelimits. During the tethering operation, it is necessary to continuously monitor these loads.

2. ShoringShoring of the aircraft can also be necessary to make it stable prior to remove fuel or cargo payloador to allow a change/repositioning of the recovery tooling.For the shoring operation, it is possible to use large timbers to support or stabilize the forward or aftfuselage and/or the lower wing surfaces. These supports must be placed in the correct load bearingareas and be adequately padded to prevent damage.For example, it is possible to make fuselage supports or cradles to match the contours of the fuselageframes. Adequate padding can consist of heavy felt, rubber sheets, rubber tires, mattresses or sandbags.The same conditions as above will help you decide whether to shore the aircraft or not.The shoring loads must be evaluated, be in the aircraft allowable limits and monitored. All appliedloads for allowable skin pressure and fuselage bending moment calculations must also be in the ARMlimits.

3. Lifting and Tethering MaterialSee 09-30-01.

04-00-00Page 1

Jul 01/09


04-20-00 STABILIZING THE AIRCRAFT

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 04-20-00-588-801-A01

Stabilizing the Aircraft

1. GeneralThe operations that follow are necessary to stabilize the aircraft.





REFERENCE DESIGNATIONTASK 02-30-01-200-801-A01 TASK 02-30-01-200-801-A01-Landing Gear Survey

03-50-01 03-50-01-MANAGING AIRCRAFT WEIGHT AND CG04-30-00 04-30-00-TETHERING THE AIRCRAFT05-30-00 05-30-00-MOVING FUEL FOR CG CONTROLFIGURE 04-20-00-991-001-A FIGURE 04-20-00-991-001-A-Aircraft Stability

FIGURE 04-20-00-991-001-B FIGURE 04-20-00-991-001-B-Aircraft Stability

FIGURE 04-20-00-991-001-C FIGURE 04-20-00-991-001-C-Aircraft Stability

FIGURE 04-20-00-991-001-D FIGURE 04-20-00-991-001-D-Aircraft Stability


TABLE 1

5. Procedure

Subtask 04-20-00-588-001-A01

A. General

(1) Make sure that maximum weight has been removed to make the aircraft as light aspossible.

(2) Calculate the NRW and CG position (see 03-50-01).

(3) You must also make sure that the wind speed is not more than the maximum allowablespeed. See FIGURE 04-20-00-991-001-AFIGURE 04-20-00-991-001-BFIGURE04-20-00-991-001-CFIGURE 04-20-00-991-001-D.

04-20-00Page 1

Jul 01/09


(4) Monitor visually the ground contact point of the A/C (either L/G or jack) to detect anymovement or attitude change during the leveling and lifting operation. If load cells areavailable on recovery jacks, monitor load indication shift.The monitoring of the vertical position of the shock absorber in the strut with a referenceline can be also an indicator of A/C stability.

(5) Select the method that you will use to control the CG during the leveling/lifting operationby addition or removal of ballast and transfer of fuel.

(6) Make sure the aircraft is correctly grounded.

(7) Install landing gear downlock pins in all landing gears that are extended (see TASK02-30-01-200-801-A01).

(8) Install tethers as soon as possible if the aircraft is unstable and moves in the wind (see04-30-00).

(9) Install temporary shoring timbers in relation with the tethers to help stabilize the aircraftwhen necessary.

(10) Transfer fuel from the low wing to the opposite wing to move weight and leveling/liftingload from the low wing (see 05-30-00).It is also possible to use this procedure to reduce the loads on an engine resting on theground.

(11) The shock absorber of the low wing landing gear can be inflated while the shock absorberof the landing gear on the high wing can be deflated to help raise a low wing.

(12) It is possible to operate the spoilers in strong wind conditions to help stabilize the aircraft(see TBD).

(13) Put the horizontal stabilizer to a slightly nose down position.

NOTE : You can do this only if power is available on the aircraft.

(14) Stabilize the soil around the aircraft so that cargo loading equipment and fuel tankers cancome near to the aircraft.

(15) Make sure that the aircraft CG position stays at least 500 mm (20 in) forward the aircraftbalance point (which is the aircraft support point: the main landing gear or the wing mainjacks).

NOTE : Other operations may be necessary depending on the specific recovery conditions.

(16) To determine the aircraft stability refer to FIGURE 04-20-00-991-001-AFIGURE04-20-00-991-001-BFIGURE 04-20-00-991-001-CFIGURE 04-20-00-991-001-D.

04-20-00Page 2

Jul 01/09


**ON A/C A318-100

NR

W IN

TO

NS

CG % RC10 15 20 25 30 40 45 5035

35

30

40

45

50

55

60

65

130 km/h (70 Kt)

111 km/h (60 Kt)

120 km/h (65 Kt)

102 km/h (55 Kt)

93 km/h (50 Kt)

83 km

(45

Kt)

74 km

(40

Kt)

46 km

(25

Kt)

0 km

(0 K

t)

9 km

(5 K

t)

65 km

(35

Kt)

56 km

(30

Kt)

37 km

(20

Kt)

28 km

(15

Kt) 19 km

(10

Kt)

N_AR_042000_1_0010101_01_00

Aircraft StabilityWheels on Dry Ground (Sheet 1 of 3)

FIGURE-04-20-00-991-001-A01

04-20-00Page 3

Jul 01/09


**ON A/C A318-100

NR

W IN

TO

NS

CG % RC

111 km/h (60 Kt)

102 km/h (55 Kt)

83 km/h (45 Kt)

74 km/h (40 Kt)

1510 25 30 35 40 45 502030

35

40

45

50

55

65

60

93 km/h (50 Kt)

46 km

(25

Kt)

0 km

(0 K

t)

9 km

(5 K

t)

65 km

(35

Kt)

56 km

(30

Kt)

37 km

(20

Kt)

28 km

(15

Kt)

19 km

(10

Kt)

N_AR_042000_1_0010102_01_00

Aircraft StabilityWheels on Wet Ground (Sheet 2 of 3)

FIGURE-04-20-00-991-001-A01

04-20-00Page 4

Jul 01/09


**ON A/C A318-100

NR

W IN

TO

NS

30

35

40

45

50

55

60

65

CG (% RC)

AIRCRAFT CG (% RC)

10 15 20 25 30 35 40 45 5015

Kt (

28 k

m/h

)

10 K

t (19

km

/h)

SHIFTING

0 Kt

(0 k

m/h

)

5 Kt

(9 k

m/h

)

N_AR_042000_1_0010103_01_00

Aircraft StabilityWheels on Ice Ground (Sheet 3 of 3)

FIGURE-04-20-00-991-001-A01

04-20-00Page 5

Jul 01/09


**ON A/C A319-100

35

40

45

50

55

60

65

70

75

80

1416182022 262830 3436 40 4244464812108 50

NR

W IN

TO

NS

CG %RC24 32 38

148 km/h (80 Kt)

139 km/h (75 Kt)

130 km/h (70 Kt)

120 km/h (65 Kt)

102 km/h (55 Kt)

SHIFTING

TIPPIN

G

0 km

/h (0

Kt)

93 km

/h (5

0 Kt)

83 km

/h (4

5 Kt)

65 km

/h (3

5 Kt)

56 km

/h (3

0 Kt)

46 km

/h (2

5 Kt)

37 km

/h (2

0 Kt)74

km/h

(40

Kt)28

km/h

(15

Kt)

19 km

/h (1

0 Kt)

9 km

/h (5

Kt)

WIND SPEED

111 km/h (60 Kt)

N_AR_042000_1_0010201_01_00


FIGURE-04-20-00-991-001-B01

04-20-00Page 6

Jul 01/09


**ON A/C A319-100

35

40

45

50

55

60

65

70

75

80

141618202224262830323412108

NR

W IN

TO

NS

363840 4244464850 CG % RC

65 km

/h (3

5 Kt)

56 km

/h (3

0 Kt)

46 km

/h (2

5 Kt)

37 k

m/h

(20

Kt)

28 km

/h (1

5 Kt) 19

km/h

(10

Kt)

0 km

/h (0

Kt)

SHIFTING

120 km/h (65 Kt)

111 km/h (60 Kt)

102 km/h (55 Kt)

TIPPIN

G

74 k

m/h

(40

Kt)

WIND SPEED

9 km

/h (5

Kt)

93 km/h (50 Kt)

83 km/h (45 Kt)

N_AR_042000_1_0010202_01_00


FIGURE-04-20-00-991-001-B01

04-20-00Page 7

Jul 01/09


**ON A/C A319-100

NR

W IN

TO

NS

5010 20 30 4015 25 35 4535

40

45

50

55

60

65

70

75

80

AIRCRAFT CG (% RC)

AIRCRAFT CG (% RC)20 Kt (37 km/h)

SHIFTING

15 K

t (28

km

/h)

10 K

t (19

km

/h)

0 Kt

(0 k

m/h

)

5 K

t (9

km/h

)

N_AR_042000_1_0010203_01_00


FIGURE-04-20-00-991-001-B01

04-20-00Page 8

Jul 01/09


**ON A/C A320-100 A320-200

35

40

45

50

55

60

65

70

75

80

14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 4812108 50

NR

W IN

TO

NS

CG (% RC)

SHIFTING

111 km/h (60 Kt)

102 km/h (55 Kt)

93 km/h (50 Kt)

TIPPIN

G

83 km

/h (4

5 Kt)

65 km

/h (3

5 Kt)

37 km

/h (2

0 Kt)74

km/h

(40

Kt)

83 km/h (45 Kt)

56 km

/h (3

0 Kt)

N_AR_042000_1_0010301_01_00

120 km/h (65 Kt)

130 km/h (70 Kt)

46 km

/h (2

5 Kt)

WIND SPEED


FIGURE-04-20-00-991-001-C01

04-20-00Page 9

Jul 01/09


**ON A/C A320-100 A320-200

35

40

45

50

55

60

65

70

75

80

14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 4812108 50

NR

W IN

TO

NS

CG (% RC)

SHIFTING

111 km/h (60 Kt)

102 km/h (55 Kt)

93 km/h (50 Kt)

TIPPIN

G

83 km/h (45 Kt)

74 km/h (40 Kt) 65 km/h (35 Kt)

N_AR_042000_1_0010302_01_00

65 km

/h (3

5 Kt)

56 km

/h (3

0 Kt)

37 km

/h (2

0 Kt)

46 km

/h (2

5 Kt)

WIND SPEED


FIGURE-04-20-00-991-001-C01

04-20-00Page 10

Jul 01/09


**ON A/C A320-100 A320-200

NR

W IN

TO

NS

5010 20 30 4015 25 35 45 CG (% RC)35

40

45

50

55

60

65

70

75

80

5 Kt

(9 k

m/h

)

10 Kt (19 km/h)

15 Kt (28 km/h)

SHIFTING

N_AR_042000_1_0010303_01_00


FIGURE-04-20-00-991-001-C01

04-20-00Page 11

Jul 01/09


**ON A/C A321-100 A321-200

35

40

45

50

55

60

65

70

75

80

14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 4812108 50 CG % RC

NR

W IN

TO

NS

TIPPIN

G

SHIFTING

111 km/h (60 Kt)

56 km

/h (3

0 Kt)

37 k

m/h

(20

Kt)74 k

m/h

(40

Kt)

83 k

m/h

(45

Kt)

102 km/h (55 Kt)

74 km/h (40 Kt)46

km/h

(25

Kt)

65 km

/h (3

5 Kt)

93 km/h (50 Kt)

120 km/h (65 Kt)

WIND SPEED

N_AR_042000_1_0010401_01_00


FIGURE-04-20-00-991-001-D01

04-20-00Page 12

Jul 01/09


**ON A/C A321-100 A321-200

35

40

45

50

55

60

65

70

75

80

14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 4812108 50

NR

W IN

TO

NS

CG % RC

SHIFTING

56 km/h (30 Kt)

56 k

m/h

(30

Kt)

46 km

/h (2

5 Kt)

37 k

m/h

(20

Kt)

WIND SPEED

TIPPIN

G

102 km/h (55 Kt)

93 km/h (50 Kt)

83 km/h (45 Kt)

74 km/h (40 Kt)

65 km/h (35 Kt)

N_AR_042000_1_0010402_01_00


FIGURE-04-20-00-991-001-D01

04-20-00Page 13

Jul 01/09


**ON A/C A321-100 A321-200

NR

W IN

TO

NS

5010 20 30 4015 25 35 45 CG (% RC)

AIRCRAFT CG (% RC)

35

40

45

50

55

60

65

70

75

80

5 Kt

(9 k

m/h

)0

Kt (0

km

/h)

15 Kt (28 km/h)

SHIFTING

10 Kt (19 km/h)

N_AR_042000_1_0010403_01_00


FIGURE-04-20-00-991-001-D01

04-20-00Page 14

Jul 01/09


04-30-00 TETHERING THE AIRCRAFT

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 04-30-00-001-A01

General

1. Tethering the aircraft

CAUTION : YOU MUST NOT USE THE SAME FITTING TO TETHER THE AIRCRAFT ANDTO LIFT IT AT THE SAME TIME.IF YOU USE THE SAME FITTING, THERE IS ARISK THAT THE LOADS APPLIED WILL BE MORE THAN THE ALLOWABLELOADS. THIS CAN CAUSE DAMAGE TO THE STRUCTURE.

CAUTION : YOU MUST INSTALL TENSIONING DEVICES AND A SCALE OR ADYNAMOMETER ON EACH TETHERING LINE. USE THE TENSIONING DEVICESTO ADJUST THE LENGTH OF THE LINE AND KEEP A POSITIVE LOAD.DURING THE LEVELING AND LIFTING PROCESS, YOU MUST MONITOR ANDADJUST THE TENSIONING DEVICES TO MAKE SURE THAT THE LOADSAPPLIED ARE NOT MORE THAN THE MAXIMUM LOADS.


During the lifting operations of a damaged aircraft with cranes, jacks and/or pneumatic lifting bags,you should tether the aircraft to prevent horizontal movement due to lifting side force (weight of theaircraft, wind force, etc...).You can attach the tether to fabric straps installed around the fuselage or the engine pylons or todifferent fittings such as pylon hoist fittings, fuselage fittings and vertical stabilizer fittings.To make sure that the horizontal stability is satisfactory, it is necessary to safely attach the aircrafttethering cables to heavy vehicles or to a deadman anchors tightly attached to the ground. Thetethers should make different angles with the fuselage centerline to prevent aircraft movement in allthe directions.A tensioning device should be provided for each tethering line so that tension is satisfactory at eachtether during the lifting operation.The number of tethers changes with the type of recovery operation and is related to the strength anddirection of the wind.See FIGURE 04-30-00-991-001-A for wind loads applied on the aircraft on ground.

**ON A/C A318-100 A319-100

2. Tethering Using the Mooring FittingsMooring fittings can be installed on the fuselage. See FIGURE 04-30-00-991-002-AFIGURE04-30-00-991-002-B for the location of the Mooring fittings.At each position, remove the blanking screws and the remaining sealant before you install themooring fitting.

04-30-00Page 1

Jul 01/09


Tethering Position Fitting P/N - Item

FR8 LHFR8 RH

98D07203000 MOORING FITTING - 04098D07203000 MOORING FITTING - 041

FR15 LHFR15 RH


FR21 LHFR21 RH


FR 30 LHFR 30 RH


FR 62/63 LHFR 62/63 RH


Mooring Fitting Positions

TABLE 1

**ON A/C A320-100 A320-200 A321-100 A321-200

3. Tethering Using the Mooring FittingsMooring fittings can be installed on the fuselage. See FIGURE 04-30-00-991-002-CFIGURE04-30-00-991-002-D for the location of the Mooring fittings.At each position, remove the blanking screws and the remaining sealant before you install themooring fitting.

Tethering Position Fitting P/N - Item

FR8 LHFR8 RH


FR15 LHFR15 RH


FR21 LHFR21 RH


FR 33 LHFR 33 RH


FR 62/63 LHFR 62/63 RH


Mooring Fittings Positions

TABLE 2

**ON A/C A318-100 A319-100

4. Tethering Using Straps or CablesYou can install straps or cables around the engine pylons and the fuselage main frames: FR15, 30 and62, 63.

04-30-00Page 2

Jul 01/09


You must install a protection (plywood sheet covered with thick padding) between these straps orcables and the fuselage and engine pylons. You can attach the tethers, tightly connected to theground, to these straps or cables.

**ON A/C A320-100 A320-200 A321-100 A321-200

5. Tethering Using Straps or CablesYou can install straps or cables around the engine pylons and the fuselage main frames: FR15, 32, 33and 62,63.You must install a protection (plywood sheet covered with thick padding) between these straps orcables and the fuselage and engine pylons. You can attach the tethers, tightly connected to theground, to these straps or cables.

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

6. Tether Lines InstallationThe tethering load distribution must be symmetric around the fuselage. For this purpose, you mustinstall the tethering lines on each side of the fuselage.Chapter 04-40-00 gives details on the ground anchors that you can use for tethering the aircraft.FIGURE 04-30-00-991-003-A gives an example of tethering line installation.

04-30-00Page 3

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Mx

Mz

My

Fz

Fy

Fx

CA

SE

1F

RO

NT

AL

ST

RIK

E

CA

SE

345

° S

TR

IKE

CA

SE

2S

IDE

ST

RIK

E

CA

SE

1: W

ILL

CA

US

E N

OS

E T

O R

ISE

(M

y)C

AS

E 2

: WIL

L C

AU

SE

AIR

CR

AF

T T

O R

OLL

AN

D Y

AW

(M

x +

Mz)

CA

SE

3: W

ILL

CA

US

E A

IRC

RA

FT

TO

RO

LL, Y

AW

AN

D P

ITC

H (

Mx

+ M

z +

My)

N_A

R_0

4300

0_1_

0010

101_

01_0

0

TetheringGround Wind Loads

FIGURE-04-30-00-991-001-A01

04-30-00Page 4

Jul 01/09


**ON A/C A318-100

N_AR_043000_1_0020101_01_00

A C D EB

FR8

FR15 FR21 FR30 FR63FR62

A B C

4 HOLES 7 HOLES 4 HOLES

4 HOLES

4 HOLES

DE

TetheringLocation of the Mooring FittingsFIGURE-04-30-00-991-002-A01

04-30-00Page 5

Jul 01/09


**ON A/C A319-100

A C EB

FR8

FR15 FR21 FR30 FR63FR62

A B C


4 HOLES

4 HOLES

DE

N_AR_043000_1_0020201_01_00

D

TetheringLocation of the Mooring FittingsFIGURE-04-30-00-991-002-B01

04-30-00Page 6

Jul 01/09


**ON A/C A320-100 A320-200

N_AR_043000_1_0020301_01_00

A B C


4 HOLES

4 HOLES

DE

A EB

FR8

FR15 FR21 FR63FR62

DC

FR33

TetheringLocation of the Mooring FittingsFIGURE-04-30-00-991-002-C01

04-30-00Page 7

Jul 01/09


**ON A/C A321-100 A321-200

N_AR_043000_1_0020401_01_00

A B


4 HOLES

4 HOLES

DE

A EB

FR8

FR15 FR21 FR63FR62

DC

FR33

C

TetheringLocation of the Mooring FittingsFIGURE-04-30-00-991-002-D01

04-30-00Page 8

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_043000_1_0030101_01_00

TetheringTypical Tethering Lines Installation

FIGURE-04-30-00-991-003-A01

04-30-00Page 9

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 04-30-00-556-801-A01

Mooring

1. GeneralDuring the recovery operation, you can moor the aircraft to help the tethering.

2. InspectionsMake sure that there is no damage on the landing gears.


A. PreparationMake sure that the landing gear safety devices are in position (see TASK 02-30-01-200-801-A01).Install the wheel chocks in front and behind the wheels.



REFERENCE DESIGNATION98D10203500 MOORING KIT - NLG


TABLE 1


REFERENCE DESIGNATIONTASK 02-30-01-200-801-A01 TASK 02-30-01-200-801-A01-Landing Gear Survey

04-40-00 04-40-00-GROUND ANCHORSFIGURE 04-30-00-991-004-A FIGURE 04-30-00-991-004-A-Mooring on the Nose Landing

Gear


TABLE 2

5. Procedure

Subtask 04-30-00-556-001-A01

A. Mooring of the Nose Landing Gear

(1) With the mooring kit

(a) Put the 98D10203500 MOORING KIT - NLG in position.See FIGURE 04-30-00-991-004-A.See 04-40-00 for details on the ground anchors.

04-30-00Page 10

Jul 01/09


(2) With ropes

(a) Attach the ropes (3) and (4) of a diameter of 50.8 mm (2.0 in) on the towing lug andthe debogging lug of the nose landing gear.

NOTE : If manila or sisal rope is used, make sure that there is not too much tensionon the rope because contraction can occur in wet weather.

(b) Attach the other ropes (2) of a diameter of 50.8 mm (2.0 in).

(c) Attach all the ropes on the ground with the mooring points. Put tension on thisassembly.

Subtask 04-30-00-556-002-A01

B. Mooring on the Main Landing Gears with Ropes

(1) Attach the ropes (3) and (4) of a diameter of 50.8 mm (2.0 in) on the towing lug and thedebogging lug of the main landing gear.

NOTE : If manila or sisal rope is used, make sure that there is not too much tension onthe rope because contraction can occur in wet weather.

(2) Attach the ropes on the ground with the mooring points. Put tension on this assembly.

04-30-00Page 11

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

BN_AR_043000_1_0040101_01_00

A

TOWING FITTING

GROUND ANCHOR

TOWING FITTING

B

AFWD

Mooring on the Nose Landing GearNLG Mooring Kit

FIGURE-04-30-00-991-004-A01

04-30-00Page 12

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_043000_1_0050101_01_00

A

21

GROUND ANCHOR

A

TOWING FITTING

Mooring on the Nose Landing GearInstallation of the Mooring RopesFIGURE-04-30-00-991-005-A01

04-30-00Page 13

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

DEBOGGING LUG

TOWING LUG

4

3

AFWD

N_AR_043000_1_0060101_01_00

Mooring on the Main Landing GearInstallation of the Mooring RopesFIGURE-04-30-00-991-006-A01

04-30-00Page 14

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_043000_1_0070101_01_00

SHORT ROPE FWDOF NOSE LANDING GEAR

45°

TYPICAL ALLPOSITIONS

MooringPosition of the Mooring RopesFIGURE-04-30-00-991-007-A01

04-30-00Page 15

Jul 01/09


04-40-00 GROUND ANCHORS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 04-40-00-001-A01

General

1. Ground Anchors for Tethers


There are three basic ways of supplying anchors for the tether lines:- Commercial type ground anchors,- Dead-man anchors,- Heavy vehicles.

A. Commercial Type Ground AnchorsThere are several types of commercially manufactured ground anchors on the market. Beforeinstallation of any type of ground anchor the manufacturer’s instructions must be reviewed andthe stability of the soil must be analyzed. Different sizes of these anchors are available to caterfor the various loads. Most anchor units must be hammered or turned to a necessary depthdepending on the stability of the soil. Generally longer models are required for loose soils andshorter ones for harder soils.

B. Dead-Man AnchorsDead-man anchors are those constructed on the site from available materials such as vehiclewheels complete with tires, heavy cribbing timbers or railroad ties. A hole is excavated to anadequate depth and the materials are buried after being attached to cables. The hole is thenback-filled with the cables forming an angle of approximate of 30 degrees between the wheel ortimber and the ground. Use of this type of anchors requires a good experience of their use toensure adequate strength.

C. Heavy VehiclesIt is possible to use large and/or heavy vehicles, if there is an adequate supply. Once the vehicleis used as anchor, it cannot be used for its original purpose during the recovery operation.

2. Anchor Holding Capacity

A. Anchor holding capacity is dependent on the type of soil and the depth of the anchor.

B. The holding capacity of the anchor will decrease as the moisture content of the soil increases.

C. It is necessary to test the soil stability:- Evaluate the type of anchoring method,- Determine the holding capacity of a given anchor in various soil types.

D. The soil stability can be tested in the field using a number of portable soil test probes.

04-40-00Page 1

Jul 01/09


04-50-00 SOIL STABILITY

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 04-50-00-001-A01

General

1. Soil stability is of prime importance to ensure personnel safety, avoidance of secondary damage,selection of ground corrective action or of tooling to be used to allow implementation of the recoveryprocedure.


Basically you must make sure that ground remains stable for the intended purpose and keep in mindthat load bearing capacity of soil might change with weather conditions.

04-50-00Page 1

Jul 01/09


WEIGHT REDUCTION

05-00-00 WEIGHT REDUCTION

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 05-00-00-001-A01

General

1. You must control aircraft weight.

WARNING : PUT SAFETY DEVICES ON THE CARGO DOOR OPENING MECHANISM TOPREVENT UNWANTED CLOSURE OF THE DOOR.

WARNING : YOU MUST CONTROL ALL MOVEMENT OF THE PAYLOAD DURING REMOVALTO PREVENT TAIL TIPPING.

WARNING : YOU MUST CONTROL MOVEMENT AND SPEED OF CONTAINERS ANDPALLETS TO PREVENT RAPID MOVEMENT OF PAYLOAD BECAUSE OFAIRCRAFT ATTITUDE.

WARNING : YOU MUST MONITOR CHANGE TO CG AND AIRCRAFT ATTITUDE DURINGREMOVAL OF PAYLOAD.

Aircraft weight change will affect CG, aircraft stability and expected loads. It is commonly acceptedthat NRW should be the minimum possible, which implies removal of maximum weight.Make sure that actions taken to reduce weight have an efficient effect.Make sure that you get the expected results.You can get maximum weight reduction if you remove weight from:- Fuel tanks- Cargo compartments.

NOTE : For disposition and locations of containers and pallets in the cargo compartments, see09-10-14.

Sometimes, it is not necessary to remove the cargo payload or fuel. This depends on main factorssuch as:- CG control- Weight and amount of the cargo payload on board- Need to excavate and build roadways for access- Need to stabilize the ground so that cargo loaders and fuel trucks can go near the aircraft- Expected removal: defueling time versus the time requirements to move the aircraft- Capacity of the available lifting means- Expected leveling/lifting loads- Structural limitations on allowable leveling/lifting loads- On-site storage capability of removed fuel.Fuel and cargo payload can also remain on the aircraft to be used as ballast.

05-00-00Page 1

Jul 01/09


NOTE : Always be prepared for sudden attitude changes of the aircraft as the payload or fuel, etc.is removed. The changes can affect both the longitudinal and lateral axes of the aircraft.

For Fuel Weight Reduction see 05-10-00.For Cargo Weight Reduction see 05-50-00.

05-00-00Page 2

Jul 01/09


05-10-00 DEFUELING

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 05-10-00-001-A01

General

1. DefuelingDefueling is one of the most important tasks to be carried out during an aircraft recovery operation.The importance relates not only to weight reduction, but also to control of the Center of Gravity(CG). The total mass of fuel on board the aircraft can be many tons. When the aircraft is in anabnormal attitude a significant shift in CG can take place as the aircraft is returned to a normalattitude. The procedures chosen to defuel a disabled aircraft should be made only after a thoroughinvestigation has been carried out to determine:- The aircraft attitude- The extent of damage to the structure and the functional status of the fuel and electrical

systems. The ability to energize the aircraft electrical power system through an external groundpower source (or the aircraft batteries) will reduce the total time required for the defuel process.The lack of electrical power due to an inoperative electrical system, is the most common problemassociated with the defuel process.

The defuel system uses the same valves and fuel lines as the refuel system and components of theengine feed and transfer systems. The aircraft can be defueled through one or more of the four hoseadapter couplings at the wing leading edges.The quantity of fuel removed will vary considerably dependant on the aircraft attitude and themethod used to defuel.Sufficient storage for the removed fuel must be available. This is a very important issue speciallywhen large amounts of fuel are involved. If the aircraft was involved in an incident where fuelcontamination is suspected, it is necessary to quarantine the removed fuel. Only when the applicableauthorities have made sure that this fuel is safe to use can it be used according to company and stateregulations.Remove as much fuel as is possible prior to lifting the aircraft.Large quantities of fuel can be trapped in the tanks due to abnormal aircraft attitudes. It is possiblethat this fuel cannot be removed until the aircraft is level.When one main landing gear has collapsed (or is deeply bogged in mud) the transfer of fuel from thelow wing to the opposite wing will reduce the weight of the low wing. This weight reduction will shiftthe CG of the opposite wing outboard from the main landing gear. This transfer process is onlyavailable when the fuel system is intact and power can be supplied to the fuel pumps and valves.The defuel process may have to be carried out in several steps, as the aircraft is levelled andstabilized several times.

05-10-00Page 1

Jul 01/09


Although the removal of the fuel is important, not all recovery operations will require its removal.Where relatively small quantities of fuel remain, it is not necessary to remove it. This decision canonly be made once the survey has been completed. Decisions can also be made to reduce weight onlyto the point where maximum lifting and jacking loads will not be exceeded. This is not arecommended procedure and should be evaluated thoroughly.

2. General Preparation


WARNING : DO NOT SPILL FUEL ON THE ENGINES OR THE BRAKES. IF YOU SPILL FUELON ENGINES OR BRAKES THAT ARE HOT, IT CAN CAUSES FIRE.

Before you start the defuel, you must make sure that:

A. You obey all the safety precautions applicable to refuelling/defuelling.

B. The safety area is clearly identified and the tankers are in correct position, see FIGURE05-10-00-991-004-A.

C. The aircraft is correctly grounded, see 09-10-13.

D. A ground cable connects the tanker to the MLG ground connection.

E. There are no open flames or smoking in the safety area.

F. Only personnel qualified to do the defuel operation are in the safety area.

G. All the equipment and material not necessary for the defuel procedure are moved out of thesafety area.

H. The correct safety and fire fighting equipment is in position with the qualified personnel tooperate it.

J. The escape lanes for the fuel tankers are clear of obstruction.

K. The fuel tankers have sufficient capacity for the quantity to be defueled.

L. Only the electrical equipment necessary for the defuel procedure is used.

M. You do not operate the aircraft main engines or the APU during the defuel procedure.

N. The electrical equipment you use will not create a spark.

P. Caps are installed on all damaged fuel pipes.

Q. All damaged electrical wiring and fuel pumps are isolated.

R. You only use pumps that are serviceable.

S. Do not do the defuel procedure in bad weather conditions. Lightning is dangerous.

T. Do not operate radio, radar equipment or mobile phone during the defuel procedure.

U. Immediately remove all fuel spillage in accordance with local procedures.

05-10-00Page 2

Jul 01/09


V. You have stopped all fuel leaks.

W. Trained personnel are available to contain all fuel spills.

X. If necessary put a GPU in position as far as practicable from the A/C. The GPU must have 3phases, with 115 Volts AC, 400 Hz and 20 KVA.

05-10-00Page 3

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

SAFETY AREA

THIS AREA MUST BE KEPTCLEAR TO LET THETANKER MOVE AWAY INAN EMERGENCY

NOTE: THIS AREA MUST BE KEPTCLEAR TO LET THETANKER MOVE AWAY INAN EMERGENCY

NOTE:

DIMENSIONS IN METERS(FEET IN BRACKETS)

NOTE:

NOTE: ALL SAFETY ZONECLEARANCES ARESUBJECT TO CHANGEACCORDING TO LOCALOR AIRPORTREGULATIONS

15(49)

15(49)

15(49)

15(49)

15(49)

15(49)

15(49)

15(49)

7(23)

7(23)

TANKER TANKER

N_AR_051000_1_0040101_01_00

DefuellingSafety Area

FIGURE-05-10-00-991-004-A01

05-10-00Page 4

Jul 01/09


05-20-00 FUEL SYSTEM DESCRIPTION

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 05-20-00-001-A01

Fuel System Basic Description

1. Basic DescriptionThe fuel system:- controls and supplies fuel in the correct quantities to the fuel tanks during refuel operations,- supplies fuel to the engines via the engine feed tanks during flight,- supplies fuel to the Auxiliary Power Unit (APU),- gives indications in the cockpit of system operation,- gives indications in the cockpit of a malfunction in the system that could cause an unusual

condition,- controls defuel and fuel ground transfers.See DESC 09-10-12-004-A01 for the ground service connections (refuel/defuel coupling andrefuel/defuel control panel).

05-20-00Page 1

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 05-20-00-002-A01

Tanks

**ON A/C A318-100 A319-100 A320-100 A320-200

1. The A318/A319/A320 has the following fuel tanks:

Tank Capacity

liters US GallonsOuter Wing Tank LH 880 232

Outer Wing Tank RH 880 232

Inner Wing Tank LH 6924 1829

Inner Wing Tank RH 6924 1829

Centre Tank 8250 2179Total fuel capacity 23859 6303

Tank Capacities

TABLE 1

NOTE : On A319 and A320, Additional Centre Tanks (ACT) can be installed with a capacity of2992 l (790 US gal) per tank.

**ON A/C A321-100 A321-200

2. The A321 has the following fuel tanks:

Tank Capacity

liters US GallonsWing Tank LH 7750 2047

Wing Tank RH 7750 2047

Centre Tank 8200 2166Total fuel capacity 23700 6261

Tank Capacities

TABLE 2

NOTE : On A321, Additional Centre Tanks (ACT) can be installed with a capacity of 2900 l (766US gal) per tank.

05-20-00Page 2

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

3. Each tank has one or more water drain valves. These are used to:- drain the water, which could possibly come out of the fuel in the tank- drain the fuel that remains after a defuel procedure has been completed (for maintenance).

4. All of the fuel tanks are fueled/defueled through a standard 2.5 inch fuel coupling, located in theright wing leading edge.

5. Each wing tank is vented through the vent/surge tanks.

6. The system uses the fuel transfer-pump to move the fuel.

7. The FQIC (Fuel Quantity Indication Computer) automatically controls the system, but if necessary,the system can be manually controlled in the cockpit.

8. The fuel is delivered to the engines by booster pumps (2 per tank).

05-20-00Page 3

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200

VENT/SURGE TANKVENT/SURGE TANK

CENTER TANK

OUTER TANK

INNER TANK INNER TANK

OUTER TANK

N_AR_052000_1_0130101_01_00

Fuel SystemFuel Tank General ArrangementFIGURE-05-20-00-991-013-A01

05-20-00Page 4

Jul 01/09


**ON A/C A321-100 A321-200

VENT/SURGE TANK VENT/SURGE TANK

WING TANK WING TANK

CENTER TANK

N_AR_052000_1_0130201_01_00

Fuel SystemFuel Tank General ArrangementFIGURE-05-20-00-991-013-B01

05-20-00Page 5

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200

STRAINERSTRAINER

CENTER TANKFUEL PUMP



PRESSURE SWITCH

APULP VALVE

APUFUEL PUMPPRESSURE

SWITCH

APUFUELPUMP

CROSSFEEDVALVE

DEFUELTRANSFER

VALVE

REFUELVALVE

CENTER TANKFUEL PUMPPRESSURE

SWITCH

N_AR_052000_1_0010101_01_00

CL

CENTER TANK

Fuel System SchematicCentre Tank

FIGURE-05-20-00-991-001-A01

05-20-00Page 6

Jul 01/09


**ON A/C A321-100 A321-200

JET PUMP

DIFFUSER

REFUEL VALVE

DEFUELTRANSFER VALVE

CROSSFEEDAPUFUEL PUMP

APU LP VALVE

RIB1

APU FUEL PUMPPRESSURE SWITCH

CENTERTRANSFER

TANK

CL

VALVE

CONTROL VALVE

N_AR_052000_1_0010201_01_00

Fuel System SchematicCentre Tank

FIGURE-05-20-00-991-001-B01

05-20-00Page 7

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200

STRAINER

REFUEL GALLERY

VALVE ACTUATOR (SINGLE MOTOR)

VALVE ACTUATOR (TWIN MOTOR)

JET PUMP

FLOAT VALVE

VENT SYSTEM FUEL DRAIN VALVE

WATER DRAIN VALVE

FUEL QUANTITY INDICATOR PROBE

TEMPERATURE SENSOR

HIGH LEVEL SENSOR

CHECK VALVE ( DIRECTION OF FLOW)

CLACK VALVE ( DIRECTION OF FLOW)

LEGEND

DIFFUSER

PRESSURE RELIEF VALVE

SOLENOID OPERATED VALVE

OVERPRESSURE PROTECTOR

MAGNETIC FUEL LEVEL INDICATOR (MLI)

LOW LEVEL SENSOR

SENSOR

CADENSICON

AIRRELEASE

VALVE

LP VALVE

FUEL SUPPLY PIPE

ENGINE CENTER TANK VENT PIPE

MAIN FUEL PUMPS

SEQUENCE VALVES

STRAINER

MAIN FUEL PUMPPRESSURE SWITCH

FUEL DRAINVALVE

SUCTIONVALVE

N_AR_052000_1_0020101_01_00

RIB2

RIB11RIB9

RIB8

RIB6

RIB4

RIB1

CL

Fuel System SchematicInner and Outer Wing Tanks (Sheet 1 of 2)

FIGURE-05-20-00-991-002-A01

05-20-00Page 8

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200

FROMTHE

SURGETANK

WING TANK VENT DUCT

REFUEL/DEFUEL COUPLINGR/H STANDARDL/H OPTIONAL

REFUEL VALVE

AIR INLET VALVE

OVERWING REFUEL ADAPTOR

NACA VENT INTAKE

FUEL VENTPROTECTOR

REFUELSPILLPIPE

PRESSUREHOLDING

VALVE

WING TANKVENT DUCT

RECIRCULATIONPIPE

INNER TANK

OUTER TANK

RIB17

RIB16

RIB15

RIB14

RIB16

RIB11

RIB13

RIB15

RIB17

RIB19RIB21

RIB22

RIB23RIB25RIB27

RIB14

FROM THE MAIN FUEL PUMPS

WING TANK

N_AR_052000_1_0020102_01_00

Fuel System SchematicInner and Outer Wing Tanks (Sheet 2 of 2)

FIGURE-05-20-00-991-002-A01

05-20-00Page 9

Jul 01/09


**ON A/C A321-100 A321-200

VALVE ACTUATOR (SINGLE MOTOR)

VALVE ACTUATOR (TWIN MOTOR)

JET PUMP

FLOAT VALVE

VENT SYSTEM FUEL DRAIN VALVE

WATER DRAIN VALVE

FUEL QUANTITY INDICATOR PROBE

TEMPERATURE SENSOR

HIGH LEVEL SENSOR

LOW LEVEL SENSOR

CHECK VALVE ( DIRECTION OF FLOW)

CLACK VALVE ( DIRECTION OF FLOW)

LEGEND

DUALCOMP

DIFFUSER

PRESSURE RELIEF VALVE

ULTRACOMP

SENSOR

SOLENOID OPERATED VALVE

OVERPRESSURE PROTECTOR

MAGNETIC FUEL LEVEL INDICATOR (MLI)

OVERWING REFUEL ADAPTOR

AIR INLET VALVE

REFUEL VALVE

AIR INLET PIPE

DIFFUSER

REFUEL/DEFUEL COUPLINGR/H STANDARDL/H OPTIONAL

NACA VENT INTAKE

FUEL VENT PROTECTOR

CLACK VALVE

PRESSURE HOLDING VALVE

WING TANK VENT DUCT

RECIRCULATIONPIPE

T

RIB11

RIB14

RIB16

RIB23

RIB27

RIB25RIB22

RIB21

RIB19

RIB17

RIB13

RIB15

WINGTANK

N_AR_052000_1_0020201_01_00

Fuel System SchematicWing Tanks (Sheet 1 of 2)

FIGURE-05-20-00-991-002-B01

05-20-00Page 10

Jul 01/09


**ON A/C A321-100 A321-200

STRAINER FUEL DRAINVALVE

MAIN FUEL PUMPPRESSURE SWITCH

MAIN FUEL PUMPS

STRAINER

AIRRELEASE

VALVE

LP VALVE

ENGINE

CHECK VALVE

REFUEL GALLERY

FUEL SUPPLY PIPE

CENTER TANK VENT PIPE

T

SUCTIONVALVE

RIB2

RIB1

RIB4

RIB6RIB8

RIB9

RIB11

N_AR_052000_1_0020202_01_00

CL

Fuel System SchematicWing Tanks (Sheet 2 of 2)

FIGURE-05-20-00-991-002-B01

05-20-00Page 11

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 05-20-00-004-A01

Fuel Quantity Indicating System

1. The Fuel Quantity Indicating (FQI) system measures the total quantity of fuel in the fuel tanks. Itgives indications for these areas:- The LH and RH wing tanks,

For A318, A319 and A320, it gives indications for the inner and outer tank.- The center tank,- The ACT, if installed- Fuel on board (FOB).

2. The Magnetic Level Indicator (MLI) provides a secondary method to measure the fuel quantity.See TASK 03-20-02-970-801-A01.

05-20-00Page 12

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

FUEL SYSTEMPAGE

PUSHBUTTONSWITCH

A

B

CN_AR_052000_1_0140101_01_00

ECAM SDUFUEL SYSTEM PAGE(TYPICAL DISPLAY)

LEFT RIGHT

APU

FOBF.USED 1 F.USED 2

3100 3100

5030 50302800

−11−11

CTR

FUEL

750 750

14360

KG

°C + 10 °C+ 10

ECAM CONTROL PANEL 11VU

OFF BRT

UPPER DISPLAY

LOWER DISPLAY

ECAM

OFF BRT

PRESS HYD ELEC FUEL

APU COND DOOR F/CTL WHEEL ALL

CLR STS RCL CIR

ENG BLEED

TOCONFIG CANC

B

A

C

FUEL CONTROL PANEL 40VU

FUELA

UTO

ENG 1

MODE SEL1 2

FUEL

APUX FEED

ENG 2

1 2CTR TKCTR TKL TK PUMPS R TK PUMPS

PUMP 1 PUMP 2

OFF

FAULT

OFF

FAULT

OFF

FAULT

OFF

FAULT

OFF

FAULT

OFF

FAULT

MAN

FAULT

ON

OPEN

Fuel SystemControl and Indications - Typical View

FIGURE-05-20-00-991-014-A01

05-20-00Page 13

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_052000_1_0150101_01_00

A

REFUEL/DEFUELCONTROL PANEL

NOTE: DEPENDING ON YOUR AIRCRAFT CONFIGURATION

FUELkg x 1000

QTY

RIGHTCTRLEFT

LEFT CTR RIGHT

LVLHI

OPEN

NORM

SHUT

OPEN

NORM

SHUT

REFUEL VALVESOPEN

NORM

SHUT

BATT POWERTESTHI LVL ON

OPEN LTS NORM

MODE SELECTREFUEL

OFF

DEFUEL / XFR

kg x 1000

PRESELECTED

DEC INC

ACTUALREFUEL

CKPT END

A

Refuel/Defuel Control PanelTypical View

FIGURE-05-20-00-991-015-A01

05-20-00Page 14

Jul 01/09


05-30-00 MOVING FUEL FOR CG CONTROL

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 05-30-00-650-801-A01

Fuel Transfer

1. General

WARNING : DO NOT TRY TO GET ACCESS TO THE FUEL VALVE ACTUATORS IN ALANDING GEAR BAY IF THE RELATED GEAR IS RETRACTED AND THE GEARDOORS ARE CLOSED. IN THIS CONDITION, THE WEIGHT OF THE LANDINGGEAR CAN BE ON THE GEAR DOORS. IF YOU OPEN THESE GEAR DOORS,THERE IS A RISK THAT THE LANDING GEAR WILL EXTEND BY GRAVITY.

WARNING : MAKE SURE THAT THE AIRCRAFT IS STABLE AND SAFE BEFORE YOU TRYTO GET ACCESS TO THE FUEL SYSTEM VALVES OR OTHER COMPONENTS.

WARNING : THIS PROCEDURE IS FOR INFORMATION ONLY TO HELP YOU PREPARE THERECOVERY OPERATION. TO DO THE PROCEDURE, YOU MUST REFER TO THEOPERATORS CUSTOMIZED DOCUMENTATION.

CAUTION : BEFORE YOU TRANSFER FUEL, MAKE SURE THAT THERE IS SUFFICIENTSPACE IN THE APPLICABLE TANKS FOR THE FUEL YOU WILL TRANSFER.

CAUTION : WITHOUT A SERVICEABLE ELECTRICAL SYSTEM, YOU MUST MONITOR THEQUANTITY OF FUEL IN THE TANKS AND MAKE SURE TO STOP THETRANSFER TO A TANK WHEN THE FUEL IN THE TANK IS NEAR THE HIGHLEVEL QUANTITY.THERE IS NO HIGH LEVEL PROTECTION FOR THE TANKS IF THEELECTRICAL SYSTEM IS NOT SERVICEABLE.

If the aircraft is in a wing high position, it can be necessary to transfer fuel from the low wing to thehigh wing. This helps to move the aircraft lateral CG to the correct position.Before you do a fuel transfer, you must find the fuel quantity in each fuel tank.





REFERENCE DESIGNATIONAMM 28-00-00-910-001AMM 24-41-00-861-002

05-30-00Page 1

Jul 01/09


REFERENCE DESIGNATIONAMM 31-60-00-860-001


TABLE 1

5. Procedure

Subtask 05-30-00-869-001-A01

A. Preparation

(1) Obey the fuel safety procedures when you work on the fuel system. See AMM28-00-00-910-001.

(2) Put safety barrier in position and a warning notice to tell persons not to operate the flightcontrols.

(3) Energize the aircraft electrical circuits (see AMM 24-41-00-861-002) and do an EIS startprocedure (lower ECAM DU) (see AMM 31-60-00-860-001).

(4) On the ECAM control panel push the FUEL pushbutton switch (P/BSW) to show theFUEL page.

(5) Open the access door192MB.

Subtask 05-30-00-650-003-A01

B. Fuel Transfer

(1) On the refuel/defuel panel 800VU:

(a) Hold the TEST switch in the LTS position and make sure that:- all the panels lights come on,- the FUEL QTY and REFUEL displays show figure eights.

(b) Hold the TEST switch in the HI LVL position and make sure that all the HI LVLlights change state. That is, those that were off come on and those that were on gooff.

(c) Release the TEST switch and make sure that the HI LVL lights, for the tanks whichare not full, go off.

(d) Put the MODE SELECT switch to the DEFUEL XFR position and make sure that theOPEN light comes on.

(e) To move the fuel from on of the wing tanks:- put the REFUEL VALVES switch of the tank you are to move fuel from, to the

NORM and guarded position,- put the REFUEL VALVES switch of the tank you are to move fuel into, to the

OPEN position.

05-30-00Page 2

Jul 01/09


(f) On the fuel control panel 40VU:- push the X FEED P/BSW,- make sure that the P/BSW ON and OPEN lights come on.

(g) On the ECAM SDU, make sure that the crossfeed valve shows green in-line (open).

(2) To move fuel from the wing tanks:

(a) On the fuel control panel 40VU:- push the applicable TK PUMPS P/BSWs,- make sure that the applicable P/BSW OFF lights go off.

(b) On the ECAM SDU monitor the fuel quantity indications.

(c) When the fuel quantity indications are correct, on the fuel control panel 40VU:- release the applicable P/BSW,- make sure that the applicable P/BSW OFF lights come on.

(3) To move all the fuel from a wing tank:

(a) On the fuel control panel 40VU, push the L (or R) TK PUMPS 1 and 2 P/BSWs.Make sure that the applicable P/BSW OFF lights go off.

(b) Operate the pumps until the FAULT lights of the L (or R) TK PUMPS 1 and 2P/BSW come on.

(c) Release the L (or R) TK PUMPS 1 and 2 P/BSWs. Make sure that the applicableP/BSW OFF lights come on and the applicable FAULT lights go off.

(4) To move fuel from the centre tank:

(a) On the control panel 40VU:

1 Release the MODE SEL P/BSW.

2 Make sure that the P/BSW MAN light comes on.

NOTE : You can only transfer fuel from the center tank with the centre tankpumps in manual control.

3 Push the CTR TK PUMPS 1 an 2 P/BSWs. Make sure that the P/BSW OFFlights go off.

(b) On the ECAM SDU, monitor the fuel quantity indications.

(c) When the fuel quantity indications are correct, on the fuel control panel 40VU:- release the CTR TK PUMPS 1 and 2 P/BSWs,- make sure that the P/BSW OFF lights come on and that the P/BSW FAULT

lights go off.

(5) To move all the fuel from the center tank:

(a) On the fuel control panel 40VU, push the CTR TK PUMPS 1 and 2 P/BSWs. Makesure that the P/BSW OFF lights go off.

05-30-00Page 3

Jul 01/09


(b) Operate the pumps until the FAULT lights of the CTR TK PUMPS 1 and 2 P/BSWcome on.

(c) Release the CTR TK PUMP P/BSW. Make sure that the P/BSW OFF lights comeon and the P/BSW FAULT lights go off.

05-30-00Page 4

Jul 01/09


05-40-00 DEFUEL SCENARIOS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 05-40-00-001-A01

Defuel Scenarios

1. You can use one of the procedures that follow to defuel the aircraft:

A. Normal pressure defuel (with aircraft fuel pumps), with all systems serviceable, see TASK05-40-01-650-801-A01.

B. Drain remaining fuel, see TASK 05-40-02-650-801-A01.

C. Pressure defuel, using an External Wiring Harness (EWH) to supply power to the aircraft fuelpumps, see TASK 05-40-03-650-802-A01.

05-40-00Page 1

Jul 01/09


05-40-01 DEFUEL SCENARIO 1 NORMAL PRESSURE DEFUEL WITH ALL AIRCRAFT SYSTEMSSERVICEABLE

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 05-40-01-650-801-A01

Normal Pressure Defuel With All Aircraft Systems Serviceable

1. GeneralYou can use this procedure when the aircraft fuel pumps and electrical systems are serviceable. Butonly use this procedure when there is no structural damage and all systems are serviceable.


3. Job Setup ReferencesSee DESC 05-10-00-001-A01 for general preparation before you start the defuel procedure.See DESC 09-10-12-004-A01 for the fuel system ground connections.See AMM 28-25-00-650-001 for the customized procedure.



REFERENCE DESIGNATIONTASK 05-40-02-650-801-A01 TASK 05-40-02-650-801-A01-Drain Remaining Fuel

DESC 05-10-00-001-A01 DESC 05-10-00-001-A01-GeneralDESC 09-10-12-004-A01 DESC 09-10-12-004-A01-Fuel System

AMM 28-25-00-650-001AMM 24-41-00-861-002


TABLE 1

5. Procedure



05-40-01Page 1

Jul 01/09



Subtask 05-40-01-869-001-A01

A. Preparation

(1) Make sure that the aircraft and the tanker are correctly grounded and bonded.

(2) Open the access door 192MB.

(3) Put access platforms and safety barriers in position.

(4) Remove the applicable refuel coupling cap.

(5) Make sure that the hose-coupling of the fuel tanker/pump is clean.

(6) Make sure that there is no damage on the refuel/defuel coupling. In case of any damage,contact AIRBUS.

(7) Connect the hose-coupling of the fuel tanker/pump to the A/C refuel/defuel coupling.

(8) Energize the A/C electrical circuits, see AMM 24-41-00-861-002.

(9) Start the ECAM system.On the ECAM Control Panel, push the FUEL system page P/BSW.

(10) On the refuel/defuel control panel 800VU:

(a) Make sure that the refuel valve switches are in the NORM and guarded position.

(b) Put the MODE SELECT switch to the DEFUEL XFR position and make sure that theOPEN light comes on.

(11) On the panel 40VU, push the X FEED P/BSW and make sure that the ON and OPENlights come on.

(12) On the SD FUEL page, make sure that the crossfeed valve indication is shown green in-line(valve open).

Subtask 05-40-01-650-003-A01

B. Pressure Defuel Procedure

WARNING : THIS PROCEDURE IS FOR INFORMATION ONLY TO HELP YOU PREPARETHE RECOVERY OPERATION. TO DO THE PROCEDURE, YOU MUSTREFER TO THE OPERATORS CUSTOMIZED DOCUMENTATION.

(1) On the panel 40VU:

(a) Push the MODE SEL P/BSW. Make sure that the MAN light goes off (CTR tankpumps now in automatic control).

(b) Push the applicable TK PUMPS P/BSWs. Make sure that the applicable P/BSWOFF lights go off.

(2) On the SD FUEL page, monitor the fuel quantity indications.

05-40-01Page 2

Jul 01/09


(3) When the fuel quantity has decreased to the necessary level, on panel 40VU:

(a) Release the applicable TK PUMPS P/BSWs. Make sure that the related P/BSW OFFlights comes on.

(b) Release the MODE SEL P/BSW. Make sure that the MAN light of the P/BSWcomes on (CTR tank pumps now in manual control).

(c) On the SD FUEL page, make sure that the tank contents become stable.

(4) To defuel the tanks until empty:

(a) Operate the related pumps until the related P/BSW FAULT light comes on.

(b) Release the applicable TANK PUMPS P/BSWs. Make sure that the applicableP/BSW OFF lights come on and the FAULT lights go off.

(5) Drain the remaining fuel from the tank(s), see TASK 05-40-02-650-801-A01.

05-40-01Page 3

Jul 01/09


05-40-02 DEFUEL SCENARIO 2 DRAIN REMAINING FUEL

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 05-40-02-650-801-A01

Drain Remaining Fuel

1. GeneralThis procedure can be used:- to drain the fuel that remains in the fuel tanks.- to defuel the aircraft when no other procedure can be done.


3. Job Setup ReferencesSee DESC 05-10-00-001-A01 for general preparation before you start the defuel procedure.See DESC 09-10-12-004-A01 for the fuel system ground connections.See AMM 28-25-00-650-003 for the customized procedure.To do this procedure, you can use:- 97A28002117002 PURGING TOOL for wing and center tank.

or- 98A28104000002 TOOL - PURGING for center tank only.

or- 98A28203000000 TEST EQUIPMENT JET PUMP for wing and center tank.



REFERENCE DESIGNATION98A28104000002 TOOL - PURGING


TABLE 1



on Landing Gears


AMM 28-25-00-650-003

05-40-02Page 1

Jul 01/09


REFERENCE DESIGNATIONFIGURE 05-40-02-991-004-A FIGURE 05-40-02-991-004-A-Drain Remaining Fuel


TABLE 2

5. Procedure




Subtask 05-40-02-869-001-A01

A. Preparation

(1) Make sure that the ground safety locks are installed on the landing gears, see TASK02-30-01-481-801-A01.

(2) On the panel 400VU:- Make sure that the L/G control lever is in the DOWN position.- put a warning notice in position to tell persons not to operate the landing gear.

(3) Put warning notices in position to tell persons not to operate L/G doors.

(4) Put safety barriers and access platforms in position.

(5) If the fuel temperature is less that -5 ˚C (+23.00 ˚F) and/or the water drain valves arefrozen, heat the drain valve areas with an approved hot air blower.

(6) For access to the CTR tank water drain valves, open access panels 195BB and 196BB.

Subtask 05-40-02-650-002-A01

B. Drain Fuel

WARNING : THIS PROCEDURE IS FOR INFORMATION ONLY TO HELP YOU PREPARETHE RECOVERY OPERATION. TO DO THE PROCEDURE, YOU MUSTREFER TO THE OPERATORS CUSTOMIZED DOCUMENTATION.

05-40-02Page 2

Jul 01/09


NOTE : To drain fuel from the center tank, it is recommended to use 98A28104000002 TOOL- PURGING to prevent leaks.

(1) On the PURGING TOOL, fully retract the nut (4), the screw (3) and the plunger assembly(1).

(2) Install the PURGING TOOL, see FIGURE 05-40-02-991-004-A:

(a) Put the hexagonal end of the bush (2) into the base plate of the applicable drainvalve.

(b) Turn the bush (2) through 30 degrees.

(c) Turn the nut (4) until it touches and seals against the surface (wing surface orbottom of the water drain valve).

(d) Put the end of the hose into the container.

(e) Hold the bush (2) and turn the screw (3) to the end of its travel. This causes theplunger (1) to open the drain valve and the fuel to flow.

(3) When the fuel flow stops, hold the bush (2) and turn the screw (3) until the drain valvescloses.

(4) Remove the PURGING TOOL:- Turn the nut (4) until it is clear of the surface (wing surface or bottom of the water

drain valve).- Turn the bush (2) back through 30 degrees and remove the purging tool from the

water drain valve.

(5) Examine the water drain valve for leakage. Leaks are not permitted.

NOTE : To increase the defueling rate, you can use a suction pump driven by an air drill.

05-40-02Page 3

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_054002_1_0040101_01_00

HOSE

WATER DRAIN VALVE

OUTLET

TYPICAL SUCTION PUMP

AIR DRILL

HOSE

FUEL TANKBOTTOM−SKIN

(A318/A319/A320 ONLY)23QM

21QM

25QM

95QM 94QM

(24QM)

(22QM)

(26QM)

A

A

1

2

3

4

A

Drain Remaining FuelPurging Tool Installation

FIGURE-05-40-02-991-004-A01

05-40-02Page 4

Jul 01/09


05-40-03 DEFUEL SCENARIO 3 DEFUEL USING AN EXTERNAL WIRING HARNESS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 05-40-03-650-802-A01

Defuel Using an External Wiring Harness

1. General


WARNING : MAKE SURE THAT THE AIRCRAFT CENTER OF GRAVITY STAYS CORRECTWHEN YOU DEFUEL THE AIRCRAFT. YOU MUST MONITOR THE AIRCRAFT CGAT ALL TIMES

WARNING : BEFORE YOU DO THIS PROCEDURE, MAKE SURE THAT THE AIRCRAFTELECTRICAL SYSTEM IS DE-ENERGIZED AND ISOLATED.

This procedure can be used when:- There is no structural damage to the aircraft,- The aircraft electrical system cannot be energized.


3. Job Setup ReferencesSee DESC 05-10-00-001-A01 for general preparation before you start the defuel procedure.See DESC 09-10-12-004-A01 for the fuel system ground connections.



REFERENCE DESIGNATIONTASK 05-40-02-650-801-A01 TASK 05-40-02-650-801-A01-Drain Remaining Fuel


DESC 05-20-00-001-A01 DESC 05-20-00-001-A01-Fuel System Basic Description

FIGURE 05-40-03-991-001-A FIGURE 05-40-03-991-001-A-Defuel Using An External WiringHarness


TABLE 1

05-40-03Page 1

Jul 01/09


5. Procedure

Subtask 05-40-03-869-001-A01

A. Preparation

(1) See FIGURE 05-40-03-991-001-A for details on the external wiring harness.

(2) Make sure that the aircraft electrical system is de-energized and isolated.

(3) Make sure that there is no GPU connected to the aircraft electrical system.

(4) Make sure that the aircraft and the tanker are correctly grounded and bonded.

(5) Put access platforms and safety barriers in position.

(6) Remove the applicable refuel coupling cap.

(7) Make sure that the hose-coupling of the fuel tanker/pump is clean.

(8) Make sure that there is no damage on the refuel/defuel coupling. In case of any damage,contact AIRBUS.

(9) Connect the hose-coupling of the fuel tanker/pump to the A/C refuel/defuel coupling.

**ON A/C A318-100 A319-100 A320-100 A320-200

Subtask 05-40-03-010-001-A01

B. External Wiring Harness Installation

(1) The valves that you will use to defuel the aircraft are:- the crossfeed valve 10QM,- the transfer/defuel valve 11QM,- the intercell transfer valves 27QM (29QM) or 28QM (30QM).See DESC 05-20-00-001-A01 for the fuel system description and the location of the valves.

NOTE : The valves can be operated manually if you remove their electrically operatedactuators.

(2) Open the MLG doors.

(3) Open the crossfeed valve 10QM:- Get access to the crossfeed valve actuator 5QM through the MLG door.- Remove the crossfeed valve actuator 5QM.- Engage a suitable tool in the slot of the crossfeed valve 10QM to manually open the

valve.

(4) Open the transfer/defuel valve 11QM:- Get access to the transfer/defuel valve actuator 11QU through the MLG door.- Remove the transfer/defuel valve actuator 11QU.- Engage a suitable tool in the slot of the transfer/defuel valve 11QM to manually open

the valve.

05-40-03Page 2

Jul 01/09


(5) Operate the intercell transfer valves 27QM (29QM) or 28QM (30QM):

NOTE : When you defuel an outer cell, it is sufficient to open one intercell transfer valve.

(a) Intercell transfer valve operation 27QM (29QM).

1 Remove the access panel 522JB (622JB) to get access to the intercell transfervalve actuator 9QP (10QP).

2 Find the position of the valve using the see/feel indicator on the actuator:

a If the valve is open leave, leave it in the open position.

b If the valve is closed:- Remove the actuator,- Engage a suitable tool in the slot of the drive shaft of the intercell

transfer valve to manually open the valve.

(b) Intercell transfer valve operation 28QM (30QM).

1 Remove the access panel 575DB (675DB) to get access to the intercell transfervalve actuator 11QP (12QP).

2 Find the position of the valve using the see/feel indicator on the actuator:

a If the valve is OPEN leave, leave it in the OPEN position.

b If the valve is closed:- Remove the actuator,- Engage a suitable tool in the slot of the drive shaft of the intercell

transfer valve to manually open the valve.

(6) To defuel the wing tanks, connect the external wiring harness to the pumps 25QA and21QA or 22QA and 26QA:- Remove the pump cover plates from pump 25QA and 21QA to defuel the LH wing.- Remove the pump cover plates from pump 22QA and 26QA to defuel the RH wing.- Remove the electrical plugs from the pumps.- Connect the plugs of the external wiring harness to the pumps 25QA and 21QA or

22QA and 26QA.- Connect the external wiring harness to the GPU.

(7) To defuel the center tank, connect the external wiring harness to the pumps 37QA and38QA:- Get access to the center tank pumps 37QA and 38QA.- Remove the pump cover plates from pump 37QA and 38QA.- Remove the electrical plugs from the pumps.- Connect the external wiring harness plugs to the pumps.

05-40-03Page 3

Jul 01/09


**ON A/C A321-100 A321-200

Subtask 05-40-03-010-001-B01

B. External Wiring Harness Installation

(1) The valves that you will use to defuel the aircraft are:- the crossfeed valve 10QM,- the transfer/defuel valve 11QM,- the control valves 153QM (154QM).See DESC 05-20-00-001-A01 for the fuel system description and the location of the valves.

NOTE : The valves can be operated manually if you remove their electrically operatedactuators.

(2) Open the MLG doors.

(3) Open the crossfeed valve 10QM:- Get access to the crossfeed valve actuator 5QE through the MLG door.- Remove the crossfeed valve actuator 5QE.- Engage a suitable tool in the slot of the crossfeed valve 10QM to manually open the

valve.

(4) Open the transfer/defuel valve 11QM:- Get access to the transfer/defuel valve actuator 11QU through the MLG door.- Remove the transfer/defuel valve actuator 11QU.- Engage a suitable tool in the slot of the transfer/defuel valve 11QM to manually open

the valve.

(5) Operate the control valves 153QM (154QM):

(a) Remove the access panel 195BB (196BB) to get access to the control valves actuator11QL (12QL).

(b) Find the position of the valve using the see/feel indicator on the actuator:

1 If the valve is OPEN, leave it in the OPEN position.

2 If the valve is closed:- Remove the actuator,- Engage a suitable tool in the slot of the drive shaft of the control valve

153QM ( 154QM) to manually open the valve.

(6) Connect the external wiring harness to the pumps 25QA and 21QA or 22QA and 26QA:- Remove the pump cover plates from pump 25QA and 21QA to defuel the LH wing.- Remove the pump cover plates from pump 22QA and 26QA to defuel the RH wing.- Remove the electrical plugs from the pumps.- Connect the plugs of the external wiring harness to the pumps 25QA and 21QA or

22QA and 26QA.- Connect the external wiring harness to the GPU.

05-40-03Page 4

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

Subtask 05-40-03-650-002-A01

C. Defuel Procedure

(1) On the control panel of the external wiring harness, select both pump switches to ON.

(2) Monitor the pumped fuel on the fuel tanker gauge.

(3) Operate the pump until the tank is empty (the fuel flow stops).

(4) On the control panel of the external wiring harness, select both pump switches to OFF.Do not operate the pumps when the fuel tank is empty.

(5) Drain the remaining fuel, see TASK 05-40-02-650-801-A01.

05-40-03Page 5

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

SWITCH10 AMPS

OFF

ON

OFF

ON

115VAC

A R

B Y

C B

R

Y

B

16AWG COPPER

16AWG COPPER

16AWG COPPER

P1NSA938 027E15FSN

115VAC

A R

B Y

C B

R

Y

B

P2

PANEL

WIRING DIAGRAM EXTERNAL WIRING HARNESS

EXTERNAL WIRING HARNESS

115VAC

PANEL

P1

P2

30 m (98.3 ft) MINIMUM2.5 m (8

.16 ft)

2.5 m (8.16 ft)

16AWG COPPER

16AWG COPPER

16AWG COPPER

NSA938 028E15FSN

N_AR_054003_1_0010101_01_00

Defuel Using An External Wiring HarnessExternal Wiring Harness

FIGURE-05-40-03-991-001-A01

05-40-03Page 6

Jul 01/09


05-50-00 CARGO COMPARTMENTS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 05-50-00-005-A01

General

1. See 09-10-14 for the description of the cargo compartments.For data related to the different cargo compartment doors see DESC 09-10-10-003-A01.

05-50-00Page 1

Jul 01/09


05-50-01 CARGO REMOVAL

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 05-50-01-005-A01

Cargo Removal

1. GeneralThis chapter gives data related to the removal of the cargo from the aircraft. The removal of thecargo is an important task carried out during an aircraft recovery operation. Cargo removal willremove a large amount of weight from the aircraft and can also control the Center of Gravity (CG).The procedure you select to remove the cargo during the aircraft recovery operation should only bemade after a survey has been carried out to find:- The aircraft stability and attitude.- The extent of damage to the aircraft structure and components.- The condition of the aircraft electrical systems.- The condition of the cargo loading system.- If an external ground power source is available.- If the equipment necessary to remove the cargo is available.The removal of the cargo is important but not all recovery operations will require its removal. Whena small amount of cargo is loaded it is possible that it is not necessary to remove it. This decision canonly be made once the survey has been completed. Decisions can also be made to remove the cargoonly to the point where the maximum lifting and jacking loads will not be exceeded or the aircraftrecovery operation can be completed.See the Cargo Loading Manual (CLS) for the cargo removal procedure.

05-50-01Page 1

Jul 01/09


05-60-00 REMOVAL OF LARGE COMPONENTS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 05-60-00-001-A01

General

1. Large aircraft components are not usually removed during a recovery operation.


Removal can be necessary when:- Damaged components such as flap sections, ailerons, elevators, etc. are not safely attached,- It is necessary to decrease the weight and/or to control CG,- The runway or the airport was closed because of the accident. In this case, it is necessary to

remove the vertical stabilizer. This is an unusual event which can occur only if the runway orairport would be closed for a long time,

- You used escape slides during evacuation. After the evacuation, it is necessary to carefullydisconnect and remove the escape slides,

- Landing gear and/or other components are broken.

05-60-00Page 1

Jul 01/09


LEVELING AND LIFTING

06-00-00 LEVELING AND LIFTING

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 06-00-00-001-A01

General

1. Leveling and Lifting FamiliesThere are 5 basic leveling families (see TBD).

2. Aircraft Pitch and Roll AnglesBefore you start the recovery, it is possible to find the aircraft pitch and roll angles when no electricalpower is available.The items of equipment that you can use are:- An attitude monitor (clinometer), located in the belly fairing- A spirit level, a clinometer or similar device located on the forward cargo-compartment floor

beams or on the cabin floor seat tracks.It is possible to use the same equipment to find when the aircraft is leveled.

3. Leveling/Lifting of the Aircraft

CAUTION : YOU MUST DO THE LATERAL LEVELING BEFORE YOU DO THELONGITUDINAL LEVELING.

There are three general methods to level/lift the aircraft. They are given in the chapters that follow:- Use of Jacks (see 06-30-00),- Use of Pneumatic Lifting Bags (see 06-40-00.),- Use of Cranes (see 06-50-00),- Step by step combination: use of one method and then another one.

A. The leveling/lifting items of equipment are:- Jacks,- Pneumatic lifting bags,- Cranes and slings.It is possible to use one of these items of equipment alone or more than one in any step-by-stepcombination.

B. The procedures in the chapters above describe how to level/lift the aircraft to a height at whichthe fuselage datum is 4600 mm (181.10 in) above the ground. This is the height necessary:- To put the aircraft in a hangar or on maintenance jacks,- To make the extension of the landing gear possible,- To put the aircraft, or part of it, on a mobile device.However, to replace a landing gear, the necessary height of the fuselage datum is 5210 mm(205.12 in) above the ground.

06-00-00Page 1

Jul 01/09


C. The aircraft can be in such an attitude that it is necessary to do the leveling operation beforethe lifting operation.In this case, you must keep the aircraft in a level attitude during the lifting phase.

NOTE : As each aircraft recovery situation is different, you must analyze the conditions andavailable equipment before you decide which leveling or lifting procedure you will use.

06-00-00Page 2

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 06-00-00-002-A01

Leveling/Lifting Obstructions

1. It may be necessary to remove the items that follow to make the leveling / lifting operation easier.

NOTE : The list is not exhaustive. The optional items of equipment can change as they are relatedto the customer configuration.

Name Zone IPC AMMGPS Antenna 1 & 2 220 IPC 34-36-16 AMM 34-36-16-000-001VHF 1 Antenna 220 IPC 23-12-11 AMM 23-12-11-000-001

ATC Antenna 1 & 2 (Top &Bottom)

120/230 IPC 34-52-11 AMM 34-52-11-000-001

TCAS Antenna (Top & Bottom) 130/230 IPC 34-43-11 AMM 34-43-11-000-001

DME 2 Antenna 120/130 IPC 34-51-11 AMM 34-51-11-000-002

MARKER Antenna 130 IPC 34-55-18 AMM 34-55-18-000-001Angle of Attack Sensors 127/231/232IPC 34-11-19 AMM 34-11-19-000-001

Drain Mast 130 IPC 30-71-51 AMM 30-71-51-000-001

FWD Fuselage

TABLE 1

Name Zone IPC AMMDrain Mast 150 IPC 30-71-51 AMM 30-71-51-000-001Radio Altimeter 1 & 2 150 IPC 34-42-11 AMM 34-42-11-000-001VHF 2 Antenna 150 IPC 23-12-11 AMM 23-12-11-000-001

AFT Fuselage

TABLE 2

06-00-00Page 3

Jul 01/09


**ON A/C A318-100

FR25 FR35

N_AR_060000_1_0010101_01_00

TCAS TOPATC TOP 1−2VHF 1GPS 2GPS 1

DRAIN MAST

AOA SENSOR 3 ATC BOTTOM 1−2

AOA SENSOR 1−2

DME 2

MARKER

TCAS BOTTOM

FR23

Antennas LocationFWD Fuselage (Sheet 1 of 2)

FIGURE-06-00-00-991-001-A01

06-00-00Page 4

Jul 01/09


**ON A/C A318-100

FR57 FR69

N_AR_060000_1_0010103_01_00

VHF 2 RA 1 RA 2 DRAIN MAST

Antennas LocationAFT Fuselage (Sheet 2 of 2)

FIGURE-06-00-00-991-001-A01

06-00-00Page 5

Jul 01/09


**ON A/C A319-100

FR15

FR20 FR34

N_AR_060000_1_0010201_01_00

GPS 1 GPS 2 VHF 1 ATC TOP 1−2

AOA SENSOR 1−2

TCAS TOP

ATC BOTTOM 1−2 DME 2 MARKER

AOA SENSOR 3

TCAS DRAIN MASTBOTTOM

Antennas LocationFWD Fuselage (Sheet 1 of 2)

FIGURE-06-00-00-991-001-B01

06-00-00Page 6

Jul 01/09


**ON A/C A319-100

FR53 FR62

N_AR_060000_1_0010202_01_00

DRAIN MAST VHF 2 RA 1 RA 2


FIGURE-06-00-00-991-001-B01

06-00-00Page 7

Jul 01/09


**ON A/C A320-100 A320-200 A321-100 A321-200

FR15

FR20 FR32

N_AR_060000_1_0010301_01_00

GPS 1 GPS 2 VHF 1 ATC TOP 1−2 TCAS TOP

AOA SENSOR 1−2

ATC BOTTOM 1−2

AOA SENSOR 3

DME 2 TCAS BOTTOM DRAIN MAST MARKER

Antennas LocationFWD Location (Sheet 1 of 2)

FIGURE-06-00-00-991-001-C01

06-00-00Page 8

Jul 01/09


**ON A/C A320-100 A320-200 A321-100 A321-200

FR51 FR59

N_AR_060000_1_0010302_01_00

VHF 2 DRAIN MAST RA 1 RA 2


FIGURE-06-00-00-991-001-C01

06-00-00Page 9

Jul 01/09


06-10-00 LOAD DETERMINATION

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 06-10-00-970-801-A01

Vertical Loads Determination

1. GeneralThis section gives data about the vertical loads related to aircraft leveling/lifting during the recoveryoperation and about the way to calculate them.




A. GeneralThe theoretical calculations that follow help to find the loads necessary for leveling/lifting. Theyalso help to:- Make sure the aircraft is stable,- Do a selection of applicable methods of leveling/lifting,- Do a check of the local structural capability of the aircraft to prevent secondary damage,- Make sure the recovery procedure is applicable to the related weight condition of the

aircraft.The simplified calculations are related to the assumptions that follow:- The aircraft structure is considered as rigid. The calculations do not take into account the

flexibility in the aircraft structure,- The leveling/lifting is done at 3 points (isostatic conditions),- The calculation take into account only the vertical loads,- You do the leveling/lifting operations on solid ground conditions and the slings are without

elongation,- The calculation do not take into account the effects of wind and temperature.

B. Location of the 3 lifting points on the aircraft X and Y reference axesSee FIGURE 06-10-00-991-001-A.- For the left wing: X1 and Y1 position of the lifting point,- For the right wing: X3 and Y3 position of the lifting point,- For the fuselage: X2 and Y2 position of the lifting point.

As the fuselage lifting point is located on the aircraft centerline, Y2 = 0.

NOTE : During the leveling/lifting procedure, it can be necessary to use only one lifting point.The aircraft will then pivot around a fixed point such as a main landing gear. Forexample, with the nose landing gear collapsed, there is only one lifting point and theaircraft will pivot around main landing gears.

06-10-00Page 1

Jul 01/09




REFERENCE DESIGNATION03-00-00 03-00-00-WEIGHT AND CG MANAGEMENTFIGURE 06-10-00-991-001-A FIGURE 06-10-00-991-001-A-Load DeterminationFIGURE 06-10-00-991-002-A FIGURE 06-10-00-991-002-A-Load Determination


TABLE 1

5. Procedure

Subtask 06-10-00-970-001-A01

A. Load Calculation

NOTE : Principle for the calculation of the loads at the recovery leveling/lifting points.

(1) Find the 3 leveling/lifting points and related X and Y values, applicable to the attitude ofthe aircraft and the related scenario (see TBD).

(2) Find the values of the NRW, XG and YG (X and Y coordinates of aircraft CG position)calculated for your aircraft condition (see 03-00-00).

(3) Record these values in the load calculation worksheet (see FIGURE 06-10-00-991-002-A)and calculate the necessary intermediate values.

(4) Use the results of the load calculation worksheet (see FIGURE 06-10-00-991-002-A) to findthe values of the vertical loads (Fz) at the 3 leveling/lifting points.Fz1 = NRW × ((YG - Y2)(X2 - X3) - (XG - X2)(Y2 - Y3)) / ((X1 - X2)(Y2 - Y3) - (Y1 -Y2)(X2 - X3))Fz1 =Fz2 = NRW × ((YG - Y3)(X3 - X1) - (XG - X3)(Y3 - Y1)) / ((X2 - X3)(Y3 - Y1) - (Y2 -Y3)(X3 - X1))Fz2 =Fz3 = NRW × ((YG - Y1)(X1 - X2) - (XG - X1)(Y1 - Y2)) / ((X3 - X1)(Y1 - Y2) - (Y3 -Y1)(X1 - X2))Fz3 =

Subtask 06-10-00-869-001-A01

B. Load Distribution Compared to Allowable Loads

(1) For jacks: You must compare the vertical load directly with the allowable load.

(2) For pneumatic lifting bags:Use the formula that follows to calculate the pressure of the pneumatic lifting bag:p = Fz / (L × W)

06-10-00Page 2

Jul 01/09


L = length and W = width of the pneumatic lifting bag.This pressure must be less than or equal to:- The maximum pressure of the pneumatic lifting bag,- The maximum allowable pressure that the pneumatic lifting bag can apply to the

aircraft structure.

(3) For slings:Use the formula that follows to calculate the load on each sling:f = Fz / NN = number of slings.This load must be less than or equal to the aircraft maximum allowable load at the relatedframe.

NOTE : If loads at leveling/lifting points are not in the allowable values, it is necessary tomake new calculations for the recovery configuration, with:- A modified weight and balance,- A change in the recovery means arrangements,- The use of other applicable recovery methods,- Or any combinations of these modifications.

06-10-00Page 3

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

2540

mm

(100

in)

C L

X3

Y3

Y1

X1

−Y

+X

LIF

TIN

G P

OIN

T

X2

Y2

= 0

NO

TE

:

N_A

R_0

6100

0_1_

0010

101_

01_0

2

Load DeterminationLocation of the 3 Lifting PointsFIGURE-06-10-00-991-001-A01

06-10-00Page 4

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_061000_1_0020101_01_00

XG YGNET RECOVERABLE

X1 Y1LEVELING/LIFTING POINT 1



X2−X3 X3−X1X1−X2INTERMEDIATE

XG−X2 XG−X3XG−X1

Y2−Y3 Y3−Y1Y1−Y2

YG−Y2 YG−Y3YG−Y1

WEIGHTSEE 03−00−00

SEE 06−00−00

SEE 06−00−00

SEE 06−00−00

CALCULATIONS

Load DeterminationLoad Calculation Worksheet

FIGURE-06-10-00-991-002-A01

06-10-00Page 5

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 06-10-00-970-802-A01

Side loads on Jack Fittings

1. GeneralThis section gives data about the side loads on jack fittings related to the aircraft leveling/liftingphase during the recovery operation and about the way to calculate them.When you level the aircraft from an unusual attitude, an arc movement (horizontal translation) of thejacking point is related to the displacement.If you use a special recovery jack, the jack head can move along the arc movement. Thus, there areno related side loads applied on the jacking point.If you use a jack that cannot move along the arc movement, the jack will apply side loads to theaircraft structure. If these side loads are more than the allowable loads, they will cause damage to theaircraft structure. It is necessary to calculate the side loads for each leveling/lifting scenario.






REFERENCE DESIGNATIONTASK 06-10-00-970-801-A01 TASK 06-10-00-970-801-A01-Vertical Loads Determination03-00-00 03-00-00-WEIGHT AND CG MANAGEMENT


TABLE 1

5. Procedure

CAUTION : BE CAREFUL WHEN YOU USE A JACK THAT CANNOT MOVE ALONG THEARC MOVEMENT. THE JACK WILL APPLY SIDE LOADS TO THE AIRCRAFTSTRUCTURE. IF THESE LOADS ARE MORE THAN THE ALLOWABLE LOADS,THEY WILL CAUSE DAMAGE TO THE STRUCTURE.

Subtask 06-10-00-970-002-A01

A. Load Calculation

(1) Find the aircraft recovery configuration and a leveling/lifting method.

06-10-00Page 6

Jul 01/09


(2) Measure the aircraft pitch (β) and lateral (α) angles with one of the tools or the methodthat follow:- An attitude monitor (clinometer), in the belly fairing, 192MB,- A spirit level, a clinometer or equivalent device that can be used on the forward cargo-

compartment floor beams or on the cabin floor seat tracks,- The aircraft geometry and characteristic points.See TBD to find the applicable recovery scenario and the related typical aircraft possibleangles.

NOTE : The typical angles are given as an example. For all scenarios, you must measurethe aircraft pitch and lateral angles for each recovery operation before you startany leveling/lifting procedure. The actual angles are related to the weight andCG configuration of the recovery aircraft.

(3) Calculate the NRW and CG position (see 03-00-00) and calculate the vertical loads (Fz)(see TASK 06-10-00-970-801-A01) at the leveling/lifting point.

(4) Calculate the Fx side load (component on the X axis).Fx = tan β × Fz

(5) Calculate the Fy side load (component on the Y axis).Fy = tan α × Fz

(6) Calculate the resultant (R) of Fx and Fy:R = √(Fx2 + Fy2)

(7) Make sure the resultant R is less than the maximum allowable side load. If the side load isnot less than or equal to the maximum allowable load, you must reduce the applied verticalload until the resultant side load is less than the allowable side load. To reduce the appliedvertical load, you can reduce the weight of the aircraft.

06-10-00Page 7

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 06-10-00-970-803-A01

Arc Movement Calculation

1. GeneralThis section gives data about the arc movement of the leveling/lifting point related to the aircraftleveling/lifting during the recovery operation and about the way to calculate it.



3. Job Setup ReferencesWhen you level the aircraft, it will rotate around a fixed pivot point on the ground and this will causemovement along the X or Y axis. This movement is called Arc Movement.You must control this movement during all the recovery procedure.



REFERENCE DESIGNATIONFIGURE 06-10-00-991-003-A FIGURE 06-10-00-991-003-A-Arc Movement CalculationFIGURE 06-10-00-991-004-A FIGURE 06-10-00-991-004-A-Arc Movement Calculation


TABLE 1

5. Procedure

Subtask 06-10-00-970-003-A01

A. Arc Movement Calculation at Fuselage Leveling/Lifting Points

(1) Measurement at Aircraft Basic PositionSee FIGURE 06-10-00-991-003-A.You must make the measurements at the points that follow:- Fixed pivot point: the point around which the aircraft will rotate (X axis).- Fuselage/ground contact point: the contact point between the fuselage and the

ground. This point must be lifted to a level attitude (X axis).- Leveling/Lifting point: the point where you apply the loads and where you calculate the

arc movement (X axis).- Characteristic point: a point on the lower part of fuselage that you will use for angle

calculation (both X and Z axes).

06-10-00Page 8

Jul 01/09


(2) Arc Movement Calculation

(a) Calculate the angle:tan β = dz / dxWhere:dx is the distance from the fuselage ground contact point to the characteristic pointon the lower part of the fuselage.dz is the height from the ground to the characteristic point.

(b) Calculate the arc movement.∆X = (L - L’) - √((L - L’)2 + tan2 β × (L’2 - L2))Where:∆X is the arc movement.L is the distance from the fuselage ground contact point to the fixed pivot point (forexample: main landing gear).L’ is the distance from the fuselage ground contact point to the leveling/lifting point.

Subtask 06-10-00-970-004-A01

B. Arc Movement Calculation at Wing Leveling/Lifting Points

(1) Measurement at Aircraft Basic PositionSee FIGURE 06-10-00-991-004-A.You must make the measurements at the points that follow:- Fixed pivot point: the point around which the aircraft will rotate (Y axis).- Wing/ground contact point on the lower wing: the contact point between the wing and

the ground. This point must be lifted to a level attitude (Y axis).- Leveling/Lifting point: the point were you apply the loads and where you calculate the

arc movement (Y axis).- Characteristic point: a point on the lower part of the engine nacelle on the high wing

that you use for angle calculation (the two Y and Z axes).

(2) Arc Movement Calculation

(a) Calculate the angle.tan α = dz / dyWhere:dy is the distance from the wing ground contact point (lower wing) to thecharacteristic point on the lower part of the engine nacelle on the higher wing.dz is the height from the ground to the characteristic point.

(b) Calculate the arc movement.∆Y = (L - L’) - √((L - L’)2 + tan2 α × (L’2 - L2))Where:∆Y is the arc movement.L is the distance from the wing ground contact point to the fixed pivot point (forexample: main landing gear).L’ is the distance from the wing ground contact point to the leveling/lifting point.

06-10-00Page 9

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_A

R_0

6100

0_1_

0030

101_

01_0

0

LIF

TIN

G P

OIN

T

FU

SE

LAG

E/G

RO

UN

DC

ON

TA

CT

PO

INT

FIX

ED

PIV

OT

PO

INT

MA

IN L

AN

DIN

G G

EA

R

CH

AR

AC

TE

RIS

TIC

PO

INT

ON

FU

SE

LAG

E F

OR

AN

GLE

CA

LCU

LAT

ION

X

dzH

dx

L

L’

Arc Movement CalculationFuselage Leveling/Lifting PointFIGURE-06-10-00-991-003-A01

06-10-00Page 10

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

LIF

TIN

G P

OIN

TF

IXE

D P

IVO

T P

OIN

TM

AIN

LA

ND

ING

GE

AR

INB

OA

RD

NA

CE

LLE

/GR

OU

ND

CO

NT

AC

T P

OIN

T

CH

AR

AC

TE

RIS

TIC

PO

INT

ON

OP

PO

SIT

E W

ING

INB

OA

RD

NA

CE

LLE

FO

R A

NG

LE C

ALC

ULA

TIO

NdzY

L’

N_A

R_0

6100

0_1_

0040

101_

01_0

0

dy

L

Arc Movement CalculationWing Leveling/Lifting Point

FIGURE-06-10-00-991-004-A01

06-10-00Page 11

Jul 01/09


06-30-00 USE OF JACKS

**ON A/C A318-100

DESC 06-30-00-001-A01

General

1. Location of Primary Jacking Points

CAUTION : YOU CAN USE ALL COMBINATIONS OF THE JACKING POINTS (ONE ORMORE) TO LEVEL/LIFT THE AIRCRAFT. THE JACK LOADS AT EACH JACKINGPOINT MUST NOT BE MORE THAN THE ALLOWABLE LOADS (VERTICAL (FZ)AND HORIZONTAL (FH).

CAUTION : WHEN YOU LEVEL/LIFT THE AIRCRAFT, YOU MUST CONTINUOUSLYMONITOR AND RECORD THE LOADS AND MAKE SURE THAT THE LOADSYOU APPLY ARE NOT MORE THAN THE MAXIMUM ALLOWABLE LOADS. IFTHE LOADS ARE MORE THAN THE ALLOWABLE LOADS, THIS CAN CAUSEDAMAGE TO THE AIRCRAFT STRUCTURE.

CAUTION : DO NOT USE THE SAME FITTING FOR TETHERING AND LIFTING OF THEAIRCRAFT AT THE SAME TIME. THE LOADS ON THE FITTING WILL CAUSEDAMAGE TO THE AIRCRAFT STRUCTURE.


There are three primary jacking points on the aircraft (See FIGURE 06-30-00-991-006-A):- One under the left wing, at RIB 9- One under the right wing, at RIB 9- One on the lower forward fuselage, in front of the nose landing gear doors, at FR 8.

2. Location of Auxiliary Jacking PointsAn auxiliary jacking point for a safety stay is located on the lower aft fuselage, between FR 73 andFR 74. (See FIGURE 06-30-00-991-006-A)A jack must be installed in this position only once the aircraft is level. This point must be used tomake the aircraft stable only.

3. Maximum Jacking WeightThe maximum aircraft weight for jacking is 53000 kg (116844.97 lb).

4. Maximum LoadsSee 06-10-00 to determine the loads related to the aircraft attitude, to select the leveling/liftingprocedure.See FIGURE 06-30-00-991-010-A to determine loads on jacking pointsFz is the load applied in the vertical direction.Fh is the load applied in all horizontal directions. See TASK 06-10-00-970-802-A01 to calculate theside loads.

06-30-00Page 1

Jul 01/09


Airbus recommends that you use load cells and lifting devices with side load measuring equipmentthat can accurately record and report the jacking point side loads.

Jacking Point Fz (daN) Fz (lbf) Fh (daN) Fh (lbf)

RH Wing 28500 64070 9405 21143

LH Wing 28500 64070 9405 21143

Nose 6800 15287 2244 5045

Allowable Loads on Primary Jacking Points

TABLE 1


Safety Stay 2000 4496 660 1484

Allowable Loads on the Safety Stay

TABLE 2

5. Permissible wind speedSee FIGURE 06-30-00-991-010-A to determine permissible wind speed.

06-30-00Page 2

Jul 01/09


**ON A/C A318-100

FW

D J

AC

KIN

GP

OIN

T

SA

FE

TY

PO

INT

26.4

4 m

15.1

8 m

2.74

m(8

.99

ft)

6.5

m

C L

(49.

8 ft)

(86.

75 ft

)

WIN

G J

AC

KIN

GP

OIN

T

(21.

33 ft

)

N_A

R_0

6300

0_1_

0060

101_

01_0

0

WIN

G J

AC

KIN

GP

OIN

T

Jacking PointsLocation

FIGURE-06-30-00-991-006-A01

06-30-00Page 3

Jul 01/09


**ON A/C A318-100

70

LOA

D O

N W

ING

JA

CK

ING

PO

INT

S (

kg x

100

0)

60

50

40

30

200 3 4 5 6 7 8 9 10

NR

W (

kg x

100

0)

15

2530

3540

55

NRWA

B

D

C

21

10 20 30 4015 25 35

PERMISSIBLE WIND SPEED (Kt)

LOAD ON FORWARD FUSELAGE JACKING POINT (kg x 1000)

EXAMPLE : THE REACTION AT THE WING JACKING POINTS IS 35300 kg (17650 kg PER SIDE) AND THEREACTION AT THE FORWARD FUSELAGE JACKING POINT IS 4700 kg . IF THE AIRCRAFTMUST BE LIFTED OUTSIDE THE WIND SPEED MUST NOT BE IN EXCESS OF 29 Kt.

ASSUME AIRCRAFT WITH NRW OF 40000 kg AND CENTER OF GRAVITY AT 20% RC .A BC

D

20

30

35

45

50

55

60

65

70

40

AIRCRAFT CG (% RC)

TIP UPSECURITYMARGIN

5045

N_AR_063000_1_0100101_01_00

CG

Aircraft StabilityAircraft on Jacks

FIGURE-06-30-00-991-010-A01

06-30-00Page 4

Jul 01/09


**ON A/C A319-100

DESC 06-30-00-001-B01

General









4. Maximum LoadsSee 06-10-00 to determine the loads related to the aircraft attitude, to select the leveling/liftingprocedure.See FIGURE 06-30-00-991-011-Ato determine loads on jacking points.Fz is the load applied in the vertical direction.Fh is the load applied in all horizontal directions. See TASK 06-10-00-970-802-A01 to calculate theside loads.

06-30-00Page 5

Jul 01/09




RH Wing 28500 64070 9405 21143

LH Wing 28500 64070 9405 21143

Nose 6800 15287 2244 5045


TABLE 1


Safety Stay 2000 4496 660 1484


TABLE 2

5. Permissible Wind SpeedSee FIGURE 06-30-00-991-011-Ato determine permissible wind speed.

06-30-00Page 6

Jul 01/09


**ON A/C A319-100

28.8

3 m

(94.

59 ft

)

2.74

m(8

.99

ft)

15.9

7 m

(52.

4 ft)

6.5

m(2

1.33

ft)

N_A

R_0

6300

0_1_

0070

101_

01_0

0

WIN

G J

AC

KIN

G

FW

D J

AC

KIN

GP

OIN

TS

AF

ET

YP

OIN

T

WIN

G J

AC

KIN

G

C L

PO

INT

PO

INT


FIGURE-06-30-00-991-007-A01

06-30-00Page 7

Jul 01/09


**ON A/C A319-100



D

70

LOA

D O

N W

ING

JA

CK

ING

PO

INT

S (

kg x

100

0)

60

50

40

30

200 4 5 6 7 8 9 10

30

35

45

50

55

60

65

70

40

NR

W (

kg x

100

0)

15

3035

40

55

NRWA

B

D

C

10 20 30 4015 25 35



20

10

1 2 3

25

AIRCRAFT CG (% RC)50


45

N_AR_063000_1_0110101_01_00

CG


FIGURE-06-30-00-991-011-A01

06-30-00Page 8

Jul 01/09


**ON A/C A320-100 A320-200

DESC 06-30-00-001-C01

General








3. The maximum aircraft weight for jacking is 59000 kg (130072.70 lb).

4. Maximum LoadsSee 06-10-00 to determine the loads related to the aircraft attitude, to select the leveling/liftingprocedure.See FIGURE 06-30-00-991-012-A to determine loads on jacking points.Fz is the load applied in the vertical direction.Fh is the load applied in all horizontal directions. See TASK 06-10-00-970-802-A01 to calculate theside loads.Airbus recommends that you use load cells and lifting devices with side load measuring equipmentthat can accurately record and report the jacking point side loads.

06-30-00Page 9

Jul 01/09



RH Wing 28500 64070 9405 21143

LH Wing 28500 64070 9405 21143

Nose 6800 15287 2244 5045


TABLE 1


Safety Stay 2000 4496 660 1484


TABLE 2

5. Permissible Wind SpeedSee FIGURE 06-30-00-991-012-A to determine permissible wind speed.

06-30-00Page 10

Jul 01/09


**ON A/C A320-100 A320-200

2.74

m(8

.99

ft)

FW

D J

AC

KIN

GP

OIN

T

C L

WIN

G J

AC

KIN

GP

OIN

T

6.5

m(2

1.33

ft)

SA

FE

TY

PO

INT

WIN

G J

AC

KIN

GP

OIN

T

N_A

R_0

6300

0_1_

0080

101_

01_0

0

17.5

6 m

(57.

61 ft

)

32.5

7 m

(106

.86

ft)


FIGURE-06-30-00-991-008-A01

06-30-00Page 11

Jul 01/09


**ON A/C A320-100 A320-200



D

NR

W (

kg x

100

0)

AIRCRAFT CG (% RC)

A

B

0 4 5 6 7 8 9 10D

10 20 30 4015 25 35



3

70

LOA

D O

N W

ING

JA

CK

ING

PO

INT

S (

kg x

100

0)

60

50

40

30

20

C

15

3035

5550

45

2010

25

40


30

35

45

50

55

60

65

70

40

1 2

N_AR_063000_1_0120101_01_00

CG

NRW


FIGURE-06-30-00-991-012-A01

06-30-00Page 12

Jul 01/09


**ON A/C A321-100 A321-200

DESC 06-30-00-001-D01

General









4. Maximum LoadsSee 06-10-00 to determine the loads related to the aircraft attitude, to select the leveling/liftingprocedure.See FIGURE 06-30-00-991-013-A to determine load on jacking points.Fz is the load applied in the vertical direction.Fh is the load applied in all horizontal directions. See TASK 06-10-00-970-802-A01 to calculate theside loads.

06-30-00Page 13

Jul 01/09




RH Wing 33400 75086 11022 24778

LH Wing 33400 75086 11022 24778

Nose 6800 15287 2244 5045


TABLE 1


Safety Stay 2000 4496.18 660 1484


TABLE 2

5. Permissible Wind speedSee FIGURE 06-30-00-991-013-A to determine permissible wind speed.

06-30-00Page 14

Jul 01/09


**ON A/C A321-100 A321-200

N_A

R_0

6300

0_1_

0090

101_

01_0

0

2.74

m(8

.99

ft)

FW

D J

AC

KIN

GP

OIN

T

C L

21.8

3 m

(71.

62 ft

)

WIN

G J

AC

KIN

GP

OIN

T

6.5

m(2

1.33

ft)

WIN

G J

AC

KIN

GP

OIN

T

SA

FE

TY

PO

INT

39.5

m

(129

.56

ft)


FIGURE-06-30-00-991-009-A01

06-30-00Page 15

Jul 01/09


**ON A/C A321-100 A321-200



D

NR

W (

kg x

100

0)

A

B

0 4 5 6 7 8 9 10D

20 30

55

10 25 35



3

70

LOA

D O

N W

ING

JA

CK

ING

PO

INT

S (

kg x

100

0)

60

50

40

30

20

C

15

303580

2025

40

4045

10

30

35

45

50

55

60

40

65

75

70

80

1

AIRCRAFT CG (% RC)


4550

2

N_AR_063000_1_0130101_01_00

NRW

CG


FIGURE-06-30-00-991-013-A01

06-30-00Page 16

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 06-30-00-002-A01

Type of Jacks

1. There are three general types of jacks:

A. Special Aircraft Recovery JacksThis type of jack can move along the arc movement in the specified limits.The jack manufacturer instructions must be obeyed.There are two primary types of aircraft recovery jacks: hydraulic and low profile multi-stagejacks:- Monopole design:

This is a multi stage single ram attached to a large base plate. The jacking head can movealong the arc movement in the specified limits.

- Tripod design:This type of jack is almost the same as a hanger or maintenance tripod jack. The differenceis that it is possible to operate and control each multi-stage leg independently. Pressuregauges are installed on each leg to monitor loads independently. The operator can makesure the jack head moves in a limited arc. It is possible to operate the jack manually with alever or control it from a powered console.

B. Standard Maintenance Tripod JacksThis type of jack is can only do a very limited arc movement. We recommend you do not use astandard maintenance jack for recovery operations. When you use a standard maintenance jack,it is necessary to do the lifting operation in small steps and reposition the jack between eachstep.

C. Bottle or Wheel JacksThey can be used for initial leveling or lifting in constricted areas. They have the same limit asthe standard maintenance tripod jacks.

06-30-00Page 17

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 06-30-00-581-802-A01

Jacking

1. GeneralThis section gives the data related to the aircraft jacking for leveling or lifting.

NOTE : If you use jacks to level or lift the aircraft, you must put them in position on a satisfactorybase. The surface must be flat and the jack must be plumb in place.

2. InspectionsDo an inspection of the area of each jacking point that you will use. Make sure there is no damageand that each jacking point is serviceable.

3. Job Setup ReferencesFor jacking point locations, see DESC 06-30-00-001-A01DESC 06-30-00-001-B01DESC 06-30-00-001-C01DESC 06-30-00-001-D01.For general data on jack adaptors, see FIGURE 06-30-00-991-004-A.



REFERENCE DESIGNATION98D07103500000 JACK ADAPTER - FUSELAGE98D104000001 JACKING PAD SET (A318, A319, A320)

98D07104081000 JACKING PAD SET (A321)

98D07103000000 DYNAMOMETER - SAFETY STAY


TABLE 1


REFERENCE DESIGNATIONDESC 06-30-00-001-A01 DESC 06-30-00-001-A01-GeneralDESC 06-30-00-001-B01 DESC 06-30-00-001-B01-GeneralDESC 06-30-00-001-C01 DESC 06-30-00-001-C01-GeneralDESC 06-30-00-001-D01 DESC 06-30-00-001-D01-GeneralFIGURE 06-30-00-991-004-A FIGURE 06-30-00-991-004-A-Installation of the Jack Adaptors


TABLE 2

06-30-00Page 18

Jul 01/09


5. Procedure



CAUTION : YOU MUST NOT USE THE SAFETY STAY TO LEVEL OR LIFT THE AIRCRAFT.

CAUTION : BEFORE YOU LIFT OR YOU LOWER THE AIRCRAFT MAKE SURE THATTHERE IS NO EQUIPMENT ADJACENT TO IT THAT CAN CAUSE DAMAGE.MAKE SURE THAT NO OTHER WORK IS BEING DONE.


Subtask 06-30-00-581-003-A01

A. Installation of the jack adaptors

(1) At the FWD jacking point, FR8:See FIGURE 06-30-00-991-004-A.

(a) Examine the 98D07103500000 JACK ADAPTER - FUSELAGE (1) and make surethat there is no damage.

(b) Install the 98D07103500000 JACK ADAPTER - FUSELAGE (1) at the FWD jackingpoint.

(2) At the wing Jacking Points, RIB9:See FIGURE 06-30-00-991-004-A.

(a) Remove the blanking plugs from the wing.

(b) Install the dowels (3)

(c) Put the 98D104000001 JACKING PAD SET (A318, A319, A320) or98D07104081000 JACKING PAD SET (A321) (2) in position under the wing andinstall the bolt.

(3) At the Auxiliary Jacking Point, between FR73 and FR74:See FIGURE 06-30-00-991-004-A

(a) Install the 98D07103000000 DYNAMOMETER - SAFETY STAY (4) at the safetystay point.

06-30-00Page 19

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

LOWER SURFACE

AB

BC

01

02

03

NOTE:

FOR DETAILS, SEE SHEET 2



02

FR8

FR73FR74

2

3

1

A C01 03

B

N_AR_063000_1_0040101_01_00

RIB9

RIB9

Installation of the Jack AdaptorsGeneral (Sheet 1 of 4)

FIGURE-06-30-00-991-004-A01

06-30-00Page 20

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_063000_1_0040102_01_00

ADAPTATOR PART98A07003907200

JACK

LOAD CELL

ADAPTATOR PART98A07003906200

R 19.0 mm (0.75 in)FITTING PART98D07103500000

FR8

343A100KN2

Installation of the Jack AdaptorsForward Jacking Point (Sheet 2 of 4)

FIGURE-06-30-00-991-004-A01

06-30-00Page 21

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_063000_1_0040103_01_00

ADAPTOR

ADAPTOR

LOAD CELL343A400KN2

JACK

R 32 mm (1.26 in)

98A07003911200

98A07003907200

JACK PAD98D07104000001 (FOR A318, A319, A320)98D07104081000 (FOR A321)

Installation of the Jack AdaptorsWing jacking Point (Sheet 3 of 4)FIGURE-06-30-00-991-004-A01

06-30-00Page 22

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_063000_1_0040104_01_00

SAFETY JACK

ADAPTATOR

LOAD CELL

98D07103000000

19D53571595R 19 mm (0.75 in)

Installation of the Jack AdaptorsAuxiliary Jacking Point - Safety Stay (Sheet 4 of 4)

FIGURE-06-30-00-991-004-A01

06-30-00Page 23

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 06-30-00-581-801-A01

General Preparation and Instructions for Leveling and Lifting the Aircraft with Jacks

1. GeneralThis section gives the data related to the use of jacks to level and lift the aircraft: allowable loads,general preparation and instructions.

NOTE : If you use jacks to level or lift the aircraft, you must put them in position on a satisfactorybase. The surface must be flat and the jack must be plumb in place.



A. GeneralSee DESC 06-30-00-001-A01DESC 06-30-00-001-B01DESC 06-30-00-001-C01DESC06-30-00-001-D01 for the localization of the jacking points and allowable jacking loads.See TASK 06-30-00-581-802-A01 for data about the installation of a jack adaptor.When you lift the aircraft with three jacks, the weight of the aircraft must not be more than themaximum jacking weight. The maximum jacking weight is not applicable for leveling with oneor two jacks but the load on each jack must not be more than the maximum allowable loads.When you lift the aircraft with jacks, it is necessary to monitor the loads at the related jackingpoints.You must also make sure that the wind speed is not more than the maximum allowable speed.See DESC 06-30-00-001-A01DESC 06-30-00-001-B01DESC 06-30-00-001-C01DESC06-30-00-001-D01

B. Aircraft Jacking StabilityWhen you use jacks to level or lift the aircraft, you must put them in position on a satisfactorybase. The surface must be flat and the jack must be plumb when it is in position. The loadbearing capacity of the soil must support the loads applied at the jack footprint.You can use plywood sheets with steel plates on top to make the ground more rigid. In someconditions, it can be necessary to excavate and prepare a base of coarse gravel before you placethe plywood sheets and steel plates.



REFERENCE DESIGNATIONTASK 06-30-00-581-802-A01 TASK 06-30-00-581-802-A01-Jacking

TASK 06-10-00-970-801-A01 TASK 06-10-00-970-801-A01-Vertical Loads DeterminationTASK 06-10-00-970-803-A01 TASK 06-10-00-970-803-A01-Arc Movement CalculationTASK 06-10-00-970-802-A01 TASK 06-10-00-970-802-A01-Side loads on Jack Fittings

Determination

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REFERENCE DESIGNATIONTASK 02-20-02-285-801-A01 TASK 02-20-02-285-801-A01-Initial Site Survey

TASK 02-30-01-481-801-A01 TASK 02-30-01-481-801-A01-Installation of the Safety Deviceson Landing Gears

DESC 06-30-00-001-A01 DESC 06-30-00-001-A01-GeneralDESC 06-30-00-001-B01 DESC 06-30-00-001-B01-GeneralDESC 06-30-00-001-C01 DESC 06-30-00-001-C01-GeneralDESC 06-30-00-001-D01 DESC 06-30-00-001-D01-General04-30-00 04-30-00-TETHERING THE AIRCRAFT03-50-01 03-50-01-MANAGING AIRCRAFT WEIGHT AND CG05-50-01 05-50-01-CARGO REMOVAL05-60-00 05-60-00-REMOVAL OF LARGE COMPONENTS07-60-00 07-60-00-MOVING DAMAGED AIRCRAFTAMM 07-11-00-581-001


TABLE 1

5. Procedure

WARNING : OBEY THESE PRECAUTIONS WHEN YOU DO LEVELING/LIFTING OF THEAIRCRAFT. MAKE SURE THAT THE LIFTING EQUIPMENT IS APPLICABLE FORTHE SPECIFIC CONDITIONS. MAKE SURE THAT THE PERSONS WHO OPERATETHE LIFTING EQUIPMENT ARE CORRECTLY TRAINED AND HAVE A GOODKNWOLEDGE OF THE SYSTEM. MAKE SURE THAT THE NECESSARY SAFETYAREA IS KNOWN AND THAT PERSONS DO NOT GO IN THIS AREA DURINGTHE LEVELING/LIFTING OPERATIONS. LEVELING/LIFTING OF THE AIRCRAFTCAN BE DANGEROUS IF YOU DO NOT OBEY THESE PRECAUTIONS.

CAUTION : MAKE SURE THAT THE LOADS APPLIED AT EACH JACKING POINT ARE NOTMORE THAN THE MAXIMUM ALLOWABLE LOADS.


CAUTION : IF THE LOADS APPLIED DURING THE RECOVERY PROCEDURE ARE MORETHAN THE MAXIMUM ALLOWABLE LOADS, YOU MUST CONTACT AIRBUSFOR SPECIFIC INSPECTIONS.

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CAUTION : YOU MUST CORRECTLY TETHER THE AIRCRAFT BEFORE YOU LEVEL ORLIFT IT.


NOTE : It is the responsibility of the recovery manager to make the decision about the applicablemethod and related equipment/personnel for the leveling/lifting of the aircraft.

Subtask 06-30-00-581-002-A01

A. General

NOTE : Before you start to level or lift the aircraft with jacks, you must make sure that thepersonnel know the instructions and conditions below and that they obey theseinstructions and conditions.

(1) Do not level or lift the aircraft with jack(s) in gusty wind conditions.

(2) Do not lift the aircraft with jacks during steady wind conditions.

(3) Find the maximum allowable wind speed related to your aircraft configuration. See DESC06-30-00-001-A01DESC 06-30-00-001-B01DESC 06-30-00-001-C01DESC 06-30-00-001-D01.

(4) Correctly tether the aircraft before leveling or lifting with jacks. This is to prevent aircraftmovement that you cannot control during the leveling or lifting operation. See 04-30-00.

(5) Read the manufacturer instructions related to the special jack(s) used.

(6) Only the personnel who knows the operation of jacks and aircraft jacking procedures are incharge of the jacking operation.

(7) Confirm the NRW and CG position. See 03-50-01.

(8) Calculate the anticipated vertical load on each jacking point to be used to make sure thisload is not more than the maximum allowable load. (See TASK 06-10-00-970-801-A01 andDESC 06-30-00-001-A01DESC 06-30-00-001-B01DESC 06-30-00-001-C01DESC06-30-00-001-D01)If the necessary load on the jacking point is more than the allowable load for that jackingpoint, reduce the aircraft weight until the lifting load is less than the allowable load ormake a selection of different leveling or lifting procedure.

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(9) Make sure each available jack can support the necessary load (vertical and side), arcmovement and travel range. Also make sure it can be put in the boundaries of the fuselageor wing jacking points.To reduce the necessary lifting load, it is recommended to reduce the aircraft weight withthe removal of cargo or payload from the aircraft before a leveling or lifting operation (See05-50-01 and 05-60-00).

(10) Calculate the expected arc movement at each jacking point during the leveling operation.(See TASK 06-10-00-970-803-A01)Calculate the side load if necessary. (See TASK 06-10-00-970-802-A01)

(11) If the jack cannot move along the necessary arc movement, you must calculate theexpected side load on the jacking point and make sure the expected side load is not morethan the allowable load on the jacking point.

(12) Install fittings and/or jack pad adapters at the necessary jacking points. See TASK06-30-00-581-802-A01.

(13) If necessary, excavate a sufficiently large area to make a stable platform as a base for eachjack. Make sure that the ground/soil can support the load at each jack footprint, and thatwill stay stable during the leveling or lifting operation. See TASK 02-20-02-285-801-A01)Make a platform that is satisfactory for the jack height when in compressed position. Makesure that the platform is sufficiently large to change the position of the jack during theleveling operation if necessary. If the jack in the extended position cannot lift the aircraftsufficiently, it is necessary to make a timber platform that is sufficiently high.

(14) Put wheel chocks in front of and behind the wheels of each extended landing gear incontact with the ground.

(15) Install the landing gear downlock pins in all extended landing gears. See TASK02-30-01-481-801-A01.

(16) Put each jack in position below the jacking point and extend the jack to engage it in thefitting.

(17) Before you start the jacking operation, we recommend that you mark the values of thenecessary lifting load to be applied on the jack on each load cell indicator (use a strip ofcolored adhesive tape for example).Also, we recommend that you mark the maximum allowable load of each jacking point toprevent overload. This gives the recovery personnel better visibility from the ground.

(18) Each jack operator must have a good visibility to the person in charge of the liftingoperation.Coordination between all jack operators is very important. Two-way voice activatedheadsets are very good for this type of operation.

(19) You must use and monitor plumb bobs and levels during a leveling or lifting operation.

(20) Monitor the CG during the full leveling procedure and be prepared to control with ballast ifnecessary. See 03-50-01.

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(21) If you use tethers, they must be adjusted and the loads must be monitored when you levelor lift the aircraft.

(22) Install aft tipping protection if necessary.

(23) When you use a jack at the safety stay position to make the aircraft stable, you mustmonitor the jack and correctly adjust the loads.

(24) Make sure the loads at each jack are not more than the allowable loads and that yourecord all the loads applied. See DESC 06-30-00-001-A01DESC 06-30-00-001-B01DESC06-30-00-001-C01DESC 06-30-00-001-D01.

(25) Level the aircraft:

(a) With a special recovery jack:If you use a special recovery jack that can move along the arc movement, make surethe jack can do the necessary arc movement to level the aircraft. Include side loadscaused by the jack.If the jack cannot do the total necessary arc movement, gradually level the aircraft insmall steps and change the position of the jack between each step.

(b) With a standard jack:If the jack cannot sufficiently move along the arc movement or if you use a standardjack, gradually level the aircraft in small steps and change the position of the jackbetween each step.- Start jacking until you get the maximum jack extension or maximum arc

movement.- Lock the jack at this position and make sure the aircraft is in a stable

configuration.- At the same time, make shoring under the closest load bearing frame or frames

and make sure the loads are not more the maximum allowable loads.- Compress the jack, make the necessary stable-base platform and change the

position of the jack. Do the procedure again until the aircraft is level.

NOTE : If possible, you should use a special recovery jack. Step by step leveling isnot the recommended method to level the aircraft.

(26) It is possible to use axle jacks with shoring and timber bases at the primary jacking pointsto lift the aircraft to the height where recovery jacks can be fitted. This is not arecommended procedure because of the limited arc movement capacity of the jack.

(27) When the fuselage and wings are level, and if it is necessary to lift the aircraft, use the 3primary jacking points to lift the aircraft to the necessary height. (See AMM07-11-00-581-001)Do not lift the aircraft until all the aircraft (wings and fuselage) is in a level attitude.

(28) When the aircraft is at the necessary height:

(a) Make shoring to support the fuselage and/or wings, or leave the jacks in place as asafety measure during work on the landing gears.

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(b) Extend the landing gear(s) and install the downlock pin(s).

(c) Or repair or replace the landing gear(s).

(d) Or, if it is not possible to make the landing gear(s) serviceable, place the forwardfuselage and/or the wing(s) on a mobile device. See 07-60-00.

06-30-00Page 29

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06-40-00 USE OF PNEUMATIC LIFTING BAGS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 06-40-00-002-A01

General

1. This section gives data about the use of pneumatic lifting bags for leveling and lifting : location ofbearing areas, allowable loads, general preparation and instructions.Pneumatic lifting bags have different sizes and lifting capacities. In general, multiple-elementpneumatic lifting bags with internal drop threads are the most usual. Single-element pneumatic liftingbags (balloon bags) are not recommended as floating loads could appear. Operator must have aspecific training to operate the equipments.You must know and obey the operating instructions given by the manufacturer of the pneumaticlifting bags.For leveling and lifting on the fuselage, see DESC 06-40-00-001-A01.For leveling and lifting on wings, see DESC 06-40-00-003-A01.For general information and instruction related to the use of pneumatic lifting bags, see TASK06-40-00-581-801-A01.

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**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 06-40-00-001-A01

Pneumatic Lifting Bags on Fuselage

1. For the leveling and lifting of the fuselage with pneumatic lifting bags, contact AIRBUS.

CAUTION : MAKE SURE THAT THE PNEUMATIC LIFTING BAGS APPLY LOADS IN THEBEARING AREA ONLY. IF THE LIFTING BAGS APPLY LOADS OUT OF THELIMITS OF THE BEARING AREA, SECONDARY DAMAGE CAN OCCUR.

CAUTION : MAKE SURE THAT THE PNEUMATIC LIFTING BAGS DO NOT APPLY LOADSON THE BELLY FAIRING STRUCTURE. IF NECESSARY, REMOVE THE BELLYFAIRINGS AND THE BELLY FAIRING STRUCTURE TO GET ACCESS TO THEALLOWABLE BEARING AREA.

CAUTION : DO NOT PUT THE LIFTING BAGS UNDER PROTRUDING STRUCTURES (FLAPTRACKS,PYLON FAIRINGS, ETC.), SHARP EDGES OR ANGLES BECAUSE THEYCAN CAUSE DAMAGE TO THE LIFTING BAGS.

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**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 06-40-00-003-A01

Pneumatic Lifting Bags on Wings

1. Bearing Areas on Wing Lower Surface


CAUTION : MAKE SURE THAT THE LOADS ON THE AIRFRAME ARE LESS THAN THEALLOWABLE LOADS WHEN YOU USE SUPPORTS. THE SUPPORTS APPLYLOADS THAT DO NOT OCCUR IN NORMAL OPERATION.


This part gives data about the installation of pneumatic lifting bags under the wings.

A. LocationPneumatic lifting bags can be installed under the wing lower surfaces between Rib 1 and Rib17*, see FIGURE 06-40-00-991-001-A.

B. Restricted AreasThe limits of the allowable bearing areas for the pneumatic lifting bags are shown in FIGURE06-40-00-991-003-A.

C. Allowable Loads

Maximum Allowable PressureBearing Area

PSI hPa BarRib 1 to Rib 17 7 480 0.48

Maximum Allowable Pressure

TABLE 1

D. After you use pneumatic lifting bags on wings for leveling/lifting of the aircraft, you must do aninspection of the wing tank access panels in the contact area.Report any sign of damage.

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**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

FRONT SPAR

RIB17

RIB1

REAR SPAR

MAKE SURE THAT THE PNEUMATIC LIFTING BAGS APPLY LOADS IN THE BEARING AREA ONLY. IF THE PNEUMATIC LIFTING BAGS APPLY LOADS OUT OF THE LIMITS OF THE BEARING AREA, SECONDARY DAMAGE CAN OCCUR.

BEARING AREA ON WING LOWER SURFACE (7PSI)

CAUTION:

N_AR_064000_1_0010101_01_00

A

AFWD

RH SYMMETRICALLH SHOWN

Pneumatic Lifting Bags on WingsBearing Area on Wing Lower Surface

FIGURE-06-40-00-991-001-A01

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**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

CAUTION: IF THE PNEUMATIC LIFTING BAGS APPLY LOADS OUT OF THE LIMITS OF THE BEARING AREA, SECONDARY DAMAGE CAN OCCUR.

BEARING AREA ON WING LOWER SURFACE

FRONT SPAR

RIB17

RIB1REAR SPAR

RIB13

RIB12

RIB8

WING JACKING POINT

JACKING POINTRESTRICTED AREA

NOTE: THE TRIPOD FOOT. THE FOOTPRINT IS RELATED TO THE TYPE OF JACK. IT IS IMPORTANT TO KNOW THE FOOTPRINT OF THE JACK YOU WILL USE BEFORE YOU PUT THE LIFTING BAG(S) IN POSITION.

RIB6

THE JACK FOOTPRINT IS MEASURED FROM THE CENTERLINE OF THE JACK TO THE CENTERLINE OF

MAKE SURE THAT THE PNEUMATIC LIFTING BAGS APPLY LOADS IN THE BEARING AREA ONLY.

A

RH SYMMETRICAL

N_AR_064000_1_0030101_01_00

FWD ALH SHOWN

Pneumatic Lifting Bags on WingsWing Restricted Area

FIGURE-06-40-00-991-003-A01

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**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 06-40-00-581-801-A01

General Preparation and Instructions for Leveling and Lifting the Aircraft with Pneumatic Lifting Bags

1. GeneralThis section gives the data about the use of pneumatic lifting bags for leveling and lifting: allowableloads, general preparation and instructions.

NOTE : If you use pneumatic lifting bags to level or lift the aircraft they must be put in position ona stable base. The surface must be flat.


3. Job Setup ReferencesPneumatic lifting bag movement is related to the attitude of the aircraft. See TBD for data aboutthe applicable scenario.



REFERENCE DESIGNATIONTASK 06-10-00-970-801-A01 TASK 06-10-00-970-801-A01-Vertical Loads DeterminationTASK 06-10-00-970-803-A01 TASK 06-10-00-970-803-A01-Arc Movement CalculationTASK 02-30-01-481-801-A01 TASK 02-30-01-481-801-A01-Installation of the Safety Devices

on Landing Gears

DESC 06-00-00-002-A01 DESC 06-00-00-002-A01-Leveling/Lifting Obstructions

04-30-00 04-30-00-TETHERING THE AIRCRAFT03-00-00 03-00-00-WEIGHT AND CG MANAGEMENT05-00-00 05-00-00-WEIGHT REDUCTION06-10-00 06-10-00-LOAD DETERMINATION04-50-00 04-50-00-SOIL STABILITY03-20-01 03-20-01-FUEL LOAD AND CG CONTROL06-30-00 06-30-00-USE OF JACKS07-60-00 07-60-00-MOVING DAMAGED AIRCRAFTAMM 07-11-00-581-001


TABLE 1

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5. Procedure



CAUTION : THE STIFFNESS AND LATERAL STABILITY OF PNEUMATIC LIFTING BAG CANCHANGE DURING THE INFLATION PROCESS OF THE PNEUMATIC LIFTINGBAG STACK. IT IS THE RESPONSIBILITY OF THE PNEUMATIC LIFTING BAGMANUFACTURER TO PROVIDE ADEQUATE DATA ON THE USE OF ITSLIFTING BAGS.IT IS THE RESPONSIBILITY OF THE RECOVERY MANAGER TO MAKE SURETHAT USE OF THE PNEUMATIC LIFTING BAG WILL NOT LEAD TO AIRCRAFTMOVEMENT DUE TO THE INFLUENCE OF WIND AND/OR CHANGE OF CGPOSITION DURING AIRCRAFT LIFTING/LEVELING.




CAUTION : MAKE SURE THAT THE PNEUMATIC LIFTING BAGS DO NOT APPLY LOADSON THE BELLY FAIRING STRUCTURE. IF NECESSARY, REMOVE THE BELLYFAIRINGS AND THE BELLY FAIRING STRUCTURE TO GET ACCESS TO THEALLOWABLE BEARING AREA.

06-40-00Page 7

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Subtask 06-40-00-581-001-A01

A. General

NOTE : Before you start to level or lift the aircraft with pneumatic lifting bags, you mustmake sure that the personnel know the instructions and conditions below and thatthey obey these instructions and conditions.

(1) Read the pneumatic lifting bag manufacturer instructions applicable to the pneumaticlifting bags that you use.

(2) Only the personnel that knows the operation of pneumatic lifting bags and aircraft jackingprocedures should be in charge of the pneumatic lifting bags operation.

(3) Do not lift the aircraft with pneumatic lifting bags in gusty wind conditions. Follow themanufacturer limitations.

(4) Do not lift the aircraft with pneumatic lifting bags during steady wind conditions. Followthe manufacturer limitations.

(5) Correctly tether the aircraft before leveling or lifting with pneumatic lifting bags. This is toprevent aircraft movement that you cannot control during the leveling or lifting operation.See 04-30-00.

(6) Confirm the aircraft NRW and CG. See 03-00-00.

(7) Calculate the anticipated vertical load on each lifting bag position to be used to make surethe necessary load is not more than the maximum allowable load on the skin. See TASK06-10-00-970-801-A01.If the necessary load on the bearing area of the pneumatic lifting bag is more than theallowable load for that leveling/lifting point, reduce the aircraft weight until the lifting loadis less than the allowable load or install additional pneumatic lifting bags to increasecontact surface to reduce applied loads or make a selection of another leveling or liftingprocedure.

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(8) Calculate the total lift of each pneumatic lifting bag used. Make sure each available liftingbag can support the necessary loads (vertical and side), arc movement and travel range,and can fit in the limits of the fuselage or wing contact zone.To reduce the necessary leveling/lifting load, we recommend that you reduce the aircraftweight with the removal of cargo and/or fuel if necessary (05-00-00) from the aircraftbefore a leveling/lifting operation, see 06-10-00.

(9) Calculate the expected arc movement during the leveling/lifting operation, at the center ofthe bearing area of each pneumatic lifting bag . Also calculate the side load if necessary,see 06-10-00.

(10) Before you use pneumatic lifting bags, do an inspection of the structure to make sure thereis no damage in the leveling/lifting area. If there is damage, the pneumatic lifting bagsmust be installed at least at one non-damaged rib/fuselage frame away from the damagedarea. Remove all sharp edges from the contact area. Use a heavy tarpaulin or foam rubbermattress between the aircraft skin and the pneumatic lifting bag to prevent damage.

(11) Put the pneumatic lifting bags in the allowable bearing areas, and make sure no sharpedges or peaks (damaged skin , protruding structure, antennas ...) are in the area wherethe bags will be installed.

(12) Remove some unwanted items (antennas, ...) from the aircraft before you install thepneumatic lifting bags, see DESC 06-00-00-002-A01.

(13) If necessary, excavate a sufficiently large area to make a stable base for the pneumaticlifting bags. Make sure that the ground/soil can support the load at each lifting bagfootprint, and will stay stable during the leveling/lifting operation, see 04-50-00. Make asatisfactory base for the height of the compressed pneumatic lifting bags. Make sure thatthe base is sufficiently large to change the position of the pneumatic lifting bags during theleveling/lifting operation if necessary. If the inflated pneumatic lifting is not sufficientlyhigh to lift the aircraft, it will be necessary to make a sufficiently high platform. It ispossible to make this platform with timber or to use an inflatable type platform.

(14) The arc movement will cause a transversal translation of the aircraft. If this movement ismore than the allowable limit of the pneumatic lifting bag (see manufacturer instructions),a leveling/lifting operation with several steps is necessary to reposition the pneumatic liftingbags. The use of a secondary method of lifting (for example jacks) is necessary.

(15) If necessary, put wheel chocks in front and behind the wheels of each landing gear that isextended and in contact with the ground.

(16) If possible, install landing gear downlock pins in all landing gears that are extended.

(17) Each operator at the pneumatic-lifting bag control console must have a good visibility ofthe leveling/lifting operation. Coordination between all the console operators is veryimportant. Two-way voice headsets are recommended for this type of operation.

(18) No personnel must be in or below the aircraft during the leveling/lifting process.

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(19) Movement of fuel in the wing tanks because of aircraft leveling/lifting can cause a changein the aircraft CG position. It is thus recommended that all fuel is removed from theaircraft before leveling/lifting, see 03-20-01. This will also reduce the necessary liftingloads.

(20) Anticipate the CG movement before you start the leveling/lifting process and be preparedto control with ballast.

(21) Monitor and record the applied loads (pressure in the pneumatic lifting bags) at all timesduring the leveling/lifting process.

(22) Before the leveling/lifting operation, make an estimate of the arc movement, see TASK06-10-00-970-803-A01.During the leveling/lifting operation, you must monitor the lateral translation of theaircraft (with the use of a plumb-line) and compare it to the calculation and the pneumaticlifting bag limitations (see manufacturer instructions) to prevent any aircraft suddenmovement or sliding.

(23) Install aft tipping protection if necessary.

(24) Before you inflate the pneumatic lifting bags, make sure that you know all the warningsand safety precautions. Make sure that all equipment (such as shoring material or jacks) isprepared and available to use.

(25) Obey the manufacturer’s instructions: inflate the lifting bags slowly and adjust the tetherswhen the aircraft starts to move.

(26) When the fuselage and wing are level, and if the aircraft needs to be lifted, it isrecommended to use the 3 jacking points to lift the aircraft to the necessary height, seeAMM 07-11-00-581-001. It is mandatory that the aircraft is in a level attitude (wing andfuselage) before you lift it.

(27) When the aircraft is at the necessary height:

(a) Use shoring to support the fuselage and/or wings, or install jacks (see 06-30-00) as asafety measure during any work on the landing gears.

(b) Extend the landing gear(s) and install downlock pin(s), see TASK 02-30-01-481-801-A01,

(c) Or repair or replace the landing gear(s),

(d) Or, if it is not possible to make the landing gear(s) serviceable, place the forwardfuselage and/or the wing(s) on a mobile device, see 07-60-00.

(28) After the recovery process, do an inspection of the skin in the contact areas of thepneumatic bag for scratches, nicks and gouges caused by sand or stones trapped betweenthe contact surfaces.You must also do an inspection of the wing tank access panels in the contact area.Report any sign of damage.

06-40-00Page 10

Jul 01/09


06-50-00 USE OF CRANES

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 06-50-00-001-A01

General

1. This chapter gives detail on the use of cranes for leveling or lifting the aircraft.The lifting of an aircraft with crane is a specific lifting procedure with specific tools, accurateengineering planning and risk/hazard assessment.A process management chart gives all the steps of the crane lifting, see FIGURE 06-50-00-991-020-A.See TASK 06-50-00-581-803-A01 for lifting by the forward fuselage.See TASK 06-50-00-581-802-A01 for lifting by the wings.See TASK 06-50-00-581-801-A01 for general preparation and instruction for leveling and lifting withcranes.


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Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

CRANE LIFTING PROCESS

RECORD WEATHERCONDITIONS

CALCULATE CG AND DECREASEWEIGHT IF NECESSARY

PLAN TOOLING INSTALLATIONAND LIFTING PROCEDURE

DO THE LIFTING ASPLANNED

PLAN PREPARATION MEETING

N_AR_065000_1_0200101_01_02

CALCULATE THE LOADSTHAT WILL BE APPLIED

STRUCTURALINTEGRITY OF MOORING

FITTINGS, ATTACHMENT CABLESYSTEMS AND CARDAN PIN

EYE END OF THE LG SIDE STAYMOUNTING BRACKET

DO A CHECK OF THE

MAKE SURE THATTHE SOIL IS STABLE

Crane LiftingProcess Management Chart

FIGURE-06-50-00-991-020-A01

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**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 06-50-00-581-803-A01

Forward Fuselage Crane Lifting

1. GeneralThis section gives the data related to the leveling and lifting from the forward fuselage with cranes.


3. Job Setup ReferencesThere are two methods to lift the forward fuselage with cranes and slings:- With a spreader beam and a strap installed at FR15 or FR20, see SUBTASK 06-50-00-581-002-

A01.- With mooring fittings installed at FR15, see SUBTASK 06-50-00-581-003-A01.You can use this task in combination with the Wing Crane Lifting procedure (see TASK06-50-00-581-802-A01) or one other lifting method (jacking or use of pneumatic lifting bags).

A. Straps / slingsThe straps touch directly the aircraft fuselage skin. They must be made from soft nylon toprevent scratches and gouges.The minimum width of the straps must be 200 mm (8 in).The two ends of the straps must have adapted loops for attachment to the crane hook orspreader bar.The straps must be in good condition without broken fibers, cuts, nicks or gouges.

B. Transversal Spreader BeamIf only one crane is available, you can use a spreader beam between each end of the sling.The distance between the hook attachment points of the slings on the spreader beam must beequal to 3950 mm (155.51 in) to have a sling angle of 180˚ around the lower fuselage. SeeFIGURE 06-50-00-991-014-AIf this distance is less than 3950 mm (155.51 in), this can cause lateral loads and secondarydamage can occur on the fuselage sides.If this distance is more than 3950 mm (155.51 in), the contact surface between the fuselage andthe strap will not be sufficient and excessive loads can be applied on the lower fuselage.

C. CraneThe crane must be able to hold the maximum lifting load.It is recommended that you use a crane with at least a 11 m (433.07 in) high jib.

D. Allowable LoadsThe maximum lifting load on FR15 or Fr 20 is 6700 daN (150.62 lbf). See FIGURE06-50-00-991-021-A to find the lifting load on FR15 or FR20 related to the aircraft weight andCG position.

06-50-00Page 3

Jul 01/09




REFERENCE DESIGNATION98D07203000 MOORING FITTING


TABLE 1


REFERENCE DESIGNATIONTASK 06-50-00-581-802-A01 TASK 06-50-00-581-802-A01-Wing Crane Lifting

TASK 06-50-00-581-801-A01 TASK 06-50-00-581-801-A01-General Preparation andinstructions for Leveling and Lifting th

06-40-00 06-40-00-USE OF PNEUMATIC LIFTING BAGSFIGURE 06-50-00-991-014-A FIGURE 06-50-00-991-014-A-FWD Fuselage Crane Lifting

FIGURE 06-50-00-991-021-A FIGURE 06-50-00-991-021-A-FWD Fuselage Crane Lifting

FIGURE 06-50-00-991-015-A FIGURE 06-50-00-991-015-A-FWD Fuselage Crane Lifting


TABLE 2

5. Procedure

Subtask 06-50-00-581-002-A01

A. Strap installation at FR15 or FR20

(1) Use a strap with a minimum length of 10300 mm (405.51 in).See FIGURE 06-50-00-991-014-A for minimum dimensions of the strap and approximatelifting height.

(2) Install the strap at FR15 or FR20. The attitude of the aircraft (clearance to install strap) orthe weight and CG condition will be the basic data for the selection of the frame.

NOTE : During the lifting operation, the loads applied to FR20 will be more than the loadapplied to FR15.

(3) With one crane, the jib head must be vertically aligned with the fuselage centerline and theframe position (FR15 or FR20).With two cranes, the jib heads must be vertically aligned with each side of the fuselage andthe frame position (FR15 or FR20).

(4) Attach the slings to each crane if you use two cranes.OrAttach the spreader bar to the single crane and attache the straps to the spreader beam.

06-50-00Page 4

Jul 01/09


(5) See TASK 06-50-00-581-801-A01 for the general instructions for leveling and lifting withcranes.It is recommended to install a pneumatic lifting bag (see 06-40-00) below the aft fuselageto prevent tail tipping.

(6) Lift the aircraft very slowly and avoid any dynamic effort. If other cranes or lifting methodare used simultaneously, make sure that all the operators work at the same time. The useof a two-way speaking system is recommended.

Subtask 06-50-00-581-003-A01

B. Fitting installation at FR15

(1) At FR15, remove the blanking screw.

(2) Install the 98D07203000 MOORING FITTING - 042 at FR15 LH and 98D07203000MOORING FITTING - 043 at FR15 RH.See FIGURE 06-50-00-991-015-A.

(3) If you use one crane with the spreader beam:

(a) Attach the spreader beam to the crane.

(b) Attach the slings to the spreader beam.

(c) Put the crane in position. Make sure that the jib is directly above the fuselagecenterline.

(d) Attach the slings to the fittings at FR15 LH/RH. It is recommended that you installload cells on the slings to monitor the loads during the leveling/lifting operation.

(4) If you use two cranes:

(a) Attach the slings to each crane.

(b) Put both cranes in position. Make sure that each jib head is directly above FR15LH/RH.

(c) Attach the slings to the fittings at FR15 LH/RH. It is recommended that you installload cells on the slings to monitor the loads during the leveling/lifting operation.

(5) See TASK 06-50-00-581-801-A01 for the general instructions for leveling and lifting withcranes.It is recommended to install a pneumatic lifting bag (see 06-40-00) below the aft fuselageto prevent tail tipping.

06-50-00Page 5

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

1.97

5 m

(6.4

8 ft)

1.97

5 m

(6.4

8 ft)

6.20 m(20.34 ft)

CL

3.95 m(12.95 ft)

180° SLING ANGLE

N_AR_065000_1_0140101_01_02

FWD Fuselage Crane LiftingStrap at FR15 or FR20

FIGURE-06-50-00-991-014-A01

06-50-00Page 6

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

7 HOLES

N_AR_065000_1_0150101_01_00

A

HOISTING USING 1 CRANE: UTILISATION OFFITTING SLINGS AND HOISTING BEAM

HOISTING USING 2 CRANES: UTILISATION OFFITTING AND SLINGS

2.37

m(7

.76

ft)

3.95 m(12.95 ft)

CL

AA

FDL

= =

10.1

0 m

(31.

14 ft

)

FWD Fuselage Crane LiftingFittings at FR15

FIGURE-06-50-00-991-015-A01

06-50-00Page 7

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

30

10

20

30

40

50

60

70

80

90

100

110

22

44

66

88

110

132

154

176

198

220

242

40

80 100

50 60

140120

70

160

80

180

90

200 220

100

AIRCRAFTWEIGHT1000 kg

1000 lb

CG 15% CG 20%

CG 25%

CG 30%

CG 35%

LOADS AT FR15 OR FR20100 kg100 lb

N_AR_065000_1_0210101_01_00

MAXIMUM LOAD FOR LIFTING BY SLINGS = 6700 kg (14771 lb)

FWD Fuselage Crane LiftingReaction at FR15 or FR 20 for Lifting by Sling (Sheet 1 of 2)

FIGURE-06-50-00-991-021-A01

06-50-00Page 8

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

30

10

20

30

40

50

60

70

80

90

100

110

22

44

66

88

110

132

154

176

198

220

242

40

80 100

50 60

140120

70

160

80

180

90

200 220

100

AIRCRAFTWEIGHT1000 kg

1000 lb

CG 15% CG 20%

CG 25%

CG 30%

CG 35%

LOADS AT FR15100 kg100 lb

MAXIMUM LOAD AT FRAME 15 FOR LIFTING BY 2 FITTINGS = 6700 kg

N_AR_065000_1_0210102_01_00

(14771 lb)

FWD Fuselage Crane LiftingReaction at FR15 for Lifting by Mooring Fittings (Sheet 2 of 2)

FIGURE-06-50-00-991-021-A01

06-50-00Page 9

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 06-50-00-581-802-A01

Wing Rib Attachment Tool

1. GeneralThis task gives the procedure to install and lift the aircraft with the 7K804427D520 CRANEATTACHMENT - WING LIFTING BRACKET attachment tool.

2. InspectionsDo a detailed visual inspection of the wing and specially of the side stay mounting bracket and thecardan pin. Report any sign of damage (nick, crack, etc.).In case of damage, contact AIRBUS.

3. Job Setup ReferencesThis procedure gives details to level/lift the aircraft by the wings when one or the two main landinggear(s) or all the landing gears are retracted, collapsed or missing. See TASK 06-50-00-581-803-A01.You can use this task in combination with the Forward-Fuselage Crane Lifting procedure (see TASK06-50-00-581-803-A01) or one other lifting method (jacking or use of pneumatic lifting bags).

A. Allowable loadsThe maximum allowable lifting load on each cardan pin eye-end is 25500 daN (56200 lbf).

B. LimitationsTo do this procedure, the pitch or roll angle of the aircraft must be less than 10˚.If the pitch or roll angle is more than 10˚, lateral loads can be applied to the mounting bracketand secondary damage can occur. Contact AIRBUS to determine an alternative solution.



REFERENCE DESIGNATION7K804427D520 CRANE ATTACHMENT - WING LIFTING BRACKET


TABLE 1


REFERENCE DESIGNATIONTASK 06-50-00-581-803-A01 TASK 06-50-00-581-803-A01-Forward Fuselage Crane Lifting


TASK 06-50-00-581-801-A01 TASK 06-50-00-581-801-A01-General Preparation andinstructions for Leveling and Lifting th

03-00-00 03-00-00-WEIGHT AND CG MANAGEMENT06-10-00 06-10-00-LOAD DETERMINATION

06-50-00Page 10

Jul 01/09


REFERENCE DESIGNATIONFIGURE 06-50-00-991-016-A FIGURE 06-50-00-991-016-A-Cardan PinFIGURE 06-50-00-991-018-A FIGURE 06-50-00-991-018-A-Crane Lifting

FIGURE 06-50-00-991-013-A FIGURE 06-50-00-991-013-A-Over wing Panel


TABLE 2

5. Procedure

WARNING : BE CAREFUL WHEN YOU DO THIS PROCEDURE. OBEY THE EQUIPMENTMANUFACTURERS’ HEALTH AND SAFETY INSTRUCTIONS AND YOUR LOCALREGULATIONS. INJURY CAN OCCUR IF YOU DO NOT OBEY THESEINSTRUCTIONS.

CAUTION : BEFORE YOU USE THE WING RIB ATTACHMENT TOOL, YOU MUST DO AFULL INSPECTION OF THE WING.IF YOU FIND DAMAGE, YOU MUST NOT USE THE WING RIB ATTACHMENTTOOL TO LIFT THE AIRCRAFT.

CAUTION : THE ANGLE OF THE LIFTING CABLE AT MLG POSITION MUST NOT BE MORETHAN 10 DEGREES IN ANY DIRECTION. THIS CAN CAUSE DAMAGED TO THETOP WING SKIN AND THE STRUCTURE.

Subtask 06-50-00-010-001-A01

A. Preparation

WARNING : BEFORE YOU START WORK ON THE WINGS, PYLONS OR LANDING GEAR,YOU MUST PUT ON AND ATTACH A SAFETY HARNESS. WITHOUT ASAFETY HARNESS, YOU CAN FALL. THIS CAN KILL YOU OR CAUSE YOUINJURY.

WARNING : YOU MUST MONITOR AIRCRAFT STABILITY, WEIGHT AND CG DURINGTHE RECOVERY PROCESS.

(1) Before you start work, make sure that:- The aircraft is stable- The aircraft defueled, if necessary or possible- The electrical systems are de-energized- The hydraulic systems are de-pressurized- No weight or load is applied to the main landing gears before you disconnect the side

stay assembly. If weight or load is applied to the main landing gears, you must supportthe wings with jacks, pneumatic lifting bags, shoring cradles or a combination of these.

(2) Calculate the weight and CG of the aircraft, see 03-00-00.

06-50-00Page 11

Jul 01/09


(3) Calculate the lifting loads at each attachment position, see 06-10-00.

(4) Make sure that the lifting loads are not more than the allowable load of the cardan pineye-end.

Subtask 06-50-00-581-004-A01

B. Installation of the Crane Attachment

WARNING : THE MAIN LANDING GEAR WILL NOT SUPPORT THE WEIGHT OF THEAIRCRAFT WHEN THE SIDE-STAYS ARE DISCONNECTED. ONCE LIFTED,YOU MUST SUPPORT THE AIRCRAFT WITH JACK, PNEUMATIC LIFTINGBAGS, SHORING CRADLES OR A COMBINATION OF THESE.ALTERNATIVELY, PUT THE AIRCRAFT ON A SUITABLE ADAPTEDFLATBED TRAILER FOR TOWING AWAY FROM THE CRASH SITE.

(1) Get access to the upper cardan pin of the MLG side-stay, use one of the methods thatfollow:- Remove the overwing panel

Or- Cut an access hole in the overwing panel to the dimension of the 7K804427D520

CRANE ATTACHMENT - WING LIFTING BRACKET with sufficient clearance, seeFIGURE 06-50-00-991-013-A.

WARNING : BE CAREFUL WHEN YOU REMOVE COMPONENTS FOR ACCESS. BEFOREYOU REMOVE THE COMPONENTS, MAKE SURE THAT THE RELATEDSYSTEM(S) IS(ARE) DE-ENERGIZED/DEPRESSURIZED. IF YOU USE TOOLSTO REMOVE COMPONENTS, MAKE SURE THAT YOU DO NOT CAUSEDAMAGE TO THE ADJACENT STRUCTURE OR SYSTEMS.

(2) Remove all the pipes, ducts or electrical wirings that can touch the lifting bracket wheninstalled.

(3) Make sure that the aircraft is fully supported and no load is applied to the landing gears.

(4) Disconnect the MLG side-stay assembly from the eye-end attachment of the upper cardanpin as follow (see FIGURE 06-50-00-991-016-A):

(a) Unlock the tab washer and remove the attachment bolt.

(b) Remove the two end caps.

(c) Remove the pin from the attachment joint.

(d) Disconnect the MLG side-stay from cardan pin eye-end attachment.

WARNING : BE CAREFUL WHEN YOU HANDLE THIS EQUIPMENT. THIS EQUIPMENT ISHEAVY (MORE THAN 12KG (26.5 LB)) AND CAN CAUSE INJURY AND/ORDAMAGE.

06-50-00Page 12

Jul 01/09


(5) Put the 7K804427D520 CRANE ATTACHMENT - WING LIFTING BRACKET in positionon the eye-end of the upper cardan pin. See FIGURE 06-50-00-991-018-A.

NOTE : You can attach the bracket to the crane with the sling first to help you installthe tool on the aircraft.

(6) Install the pin on the eye-end of the cardan pin and through the lifting bracket.

NOTE : The pin dimension can change with aircraft variants. Make sure that you use thecorrect pin through the eye-end of the cardan pin and lifting bracket.The thread of the pin is 87 mm (3.43 in) for A318, A319, A320 and A321-100and is 27 mm (1.06 in) for A321-200.

(7) Install the safety bolt to safety the pin.

(8) Make sure that the MLG and its attachment are safe and will no move during the recoveryoperation.If necessary and if possible, use cable slings or other attachment system (see TASK02-30-01-481-801-A01 for the installation of the L/G safety devices) to safely attach themain landing gear and prevent sudden retraction.

(9) If it is necessary to lift the two wings of the aircraft, do again the steps for the other wing.

Subtask 06-50-00-581-005-A01

C. Lifting

WARNING : THE AIRCRAFT MUST NOT REST ON ITS MAIN LANDING GEAR WHENYOU LIFT THE WING WITH THE CRANE LIFTING BRACKET. THE MLGWILL NOT SUPPORT THE WEIGHT OF THE AIRCRAFT AND CANCOLLAPSE.

CAUTION : THE ANGLE OF THE LIFTING CABLE AT MLG POSITION MUST NOT BEMORE THAN 10 DEGREES IN ANY DIRECTION. THIS CAN CAUSEDAMAGED TO THE TOP WING SKIN AND THE STRUCTURE.

CAUTION : YOU MUST DO THE LATERAL LEVELING BEFORE YOU DO THELONGITUDINAL LEVELING.

(1) Attach the lifting cables to the mobile crane(s).

(2) Put the crane(s) in position. Make sure that the jib head of the crane is directly above thelifting bracket.

(3) Attach the lifting cables to the lifting bracket. See FIGURE 06-50-00-991-018-A for anexample of general configuration.

(4) See TASK 06-50-00-581-801-A01 for the general instructions for leveling and lifting withcranes.

(5) Level the aircraft wings.

06-50-00Page 13

Jul 01/09


(6) If necessary, level the aircraft fuselage. See TASK 06-50-00-581-803-A01.

(7) Lift the aircraft:

(a) Make sure that the aircraft is always level during the lifting operation.

(b) Make sure that the angle of the lifting cable is not more than 10 degrees from thevertical in all directions. See FIGURE 06-50-00-991-018-A.

(8) During the complete leveling and lifting operation, use load cells to monitor the loads andmake sure that the loads applied are not more than the maximum allowable loads.

(9) When the lifting is completed, install the aircraft on prepared supports (jacks, pneumaticlifting bags, recovery trailers, etc.).

06-50-00Page 14

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

610 mm(24 in)

100 mm(3.93 in)

100 mm(3.93 in)

10 mm (0.39 in) FROMAFT EDGE OF JOINT STRIP

30 mm (1.18 in) FROM CENTRE OFSTIFFENER FASTENERS, FORWARD ROW

ACCESSHOLE

EDGE OFFAIRING SEAL

AFWD

A

N_AR_065000_1_0130101_01_00

Over wing PanelAccess

FIGURE-06-50-00-991-013-A01

06-50-00Page 15

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_065000_1_0160101_01_00

A

B

B

A

REAR SPAR END CAP

SIDE STAYMOUNTINGBRACKET

CARDAN PIN

END CAP

ATTACHMENT BOLT

PIN

SIDE STAYASSEMBLY

TAB WASHER

B B

Cardan PinSide Stay Assembly

FIGURE-06-50-00-991-016-A01

06-50-00Page 16

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

10°

10°

CA

RD

AN

PIN

EY

E−

EN

D

SA

FE

TY

BO

LT

JAC

K F

ITT

ING

SID

E S

TA

Y F

ITT

ING

LIF

TIN

G B

RA

CK

ET

SH

AC

KLE

PIN

MA

XIM

UM

ALL

OW

AB

LE D

EV

IAT

ION

OF

TH

E C

RA

NE

S L

IFT

ING

CA

BLE

SF

RO

M T

HE

VE

RT

ICA

L IS

10

DE

GR

EE

SIN

ALL

DIR

EC

TIO

NS

.

SID

E S

TA

YM

OU

NT

ING

BR

AC

KE

TC

AR

DA

N P

IN

BB

10°

10°

N_A

R_0

6500

0_1_

0170

101_

01_0

1

B

B

Crane AttachmentWing Lifting Bracket

FIGURE-06-50-00-991-017-A01

06-50-00Page 17

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

THE OVERWING PANELIS REMOVED OR CUTTO GAIN ACCESS

NOTE: TYPICAL ARRANGEMENT

N_AR_065000_1_0180101_01_01

Crane LiftingExample of Crane ArrangementFIGURE-06-50-00-991-018-A01

06-50-00Page 18

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 06-50-00-581-801-A01

General Preparation and Instructions for Leveling and Lifting the Aircraft with Cranes

1. GeneralThis section gives the data related to the use of crane for leveling and lifting.


3. Job Setup ReferencesCrane/sling travel range is related to the attitude of the aircraft. See TBD for information related tothe applicable scenario.



REFERENCE DESIGNATION98D07203003 FUSELAGE SHORING CRADLE98D57004031 WING SHORING CRADLE


TABLE 1


REFERENCE DESIGNATIONTASK 03-50-01-558-803-A01 TASK 03-50-01-558-803-A01-Ballast Added EffectTASK 06-50-00-581-803-A01 TASK 06-50-00-581-803-A01-Forward Fuselage Crane Lifting


DESC 06-00-00-002-A01 DESC 06-00-00-002-A01-Leveling/Lifting Obstructions

DESC 06-40-00-001-A01 DESC 06-40-00-001-A01-Pneumatic Lifting Bags on Fuselage

04-30-00 04-30-00-TETHERING THE AIRCRAFT03-50-01 03-50-01-MANAGING AIRCRAFT WEIGHT AND CG05-50-00 05-50-00-CARGO COMPARTMENTS05-60-00 05-60-00-REMOVAL OF LARGE COMPONENTS06-10-00 06-10-00-LOAD DETERMINATION05-10-00 05-10-00-DEFUELING07-20-00 07-20-00-PREPARING A ROADWAY07-40-00 07-40-00-TOWING AND DEBOGGING

06-50-00Page 19

Jul 01/09


REFERENCE DESIGNATIONAMM 07-11-00-581-001


TABLE 2

5. Procedure





CAUTION : USE ONLY RECOVERY SLINGS AND SPREADER BEAMS SPECIFIED BY AIRBUS.NON-APPROVED LIFTING DEVICES CAN CAUSE SECONDARY DAMAGE TOTHE AIRCRAFT.

CAUTION : MAKE SURE THAT THE CRANE YOU USE CAN LIFT THE ESTIMATED LOADPLUS THE WEIGHT OF THE LIFTING EQUIPMENT BEFORE YOU START TOLIFT THE AIRCRAFT.


NOTE : The information or principle contained in this chapter are given as a guide to help anaircraft recovery.

06-50-00Page 20

Jul 01/09



Subtask 06-50-00-581-001-A01

A. General

NOTE : Before you start a leveling or lifting procedure with slings/cranes, make sure that theinstructions that follow are obeyed.

(1) Do not level or lift the aircraft with cranes during gusty wind conditions.

(2) The common maximum permissible wind speed for mobile cranes is 50 km/h (27 kt) withsteady wind. Airbus recommends not to lift the aircraft if the wind speed is higher.It is also recommended not to use cranes during thunderstorm to prevent lightning.

(3) Before you start the leveling or lifting operation with cranes, you must correctly tether theaircraft. This is to prevent uncontrolled movement of the aircraft during this operationspecially in case of high wind condition (See 04-30-00).

(4) Only personnel familiar with the operating procedures of the slings, spreader beams andcranes should be in charge of the lifting operation.

(5) Calculate the NRW and CG position (See 03-50-01).

(6) Calculate the anticipated vertical load on the fuselage or fitting points and make sure thatthe necessary load is not more than the maximum allowable load.If the necessary load is more than the allowable load, you must either decrease the aircraftweight until the lifting load is less than the allowable load or use another leveling or liftingprocedure.

(7) Calculate the total lifting capacity of the slings and cranes that you use are able to hold.Make sure that each available sling or crane can hold the necessary load, and can fit withinthe boundaries of the fuselage contact zone.The crane lifting strength must be higher than the lifting loads and the jib length must besufficient to allow aircraft movement (lateral and vertical)To decrease the necessary lifting load, it is recommended to decrease the aircraft weight byremoval of cargo or payload from the aircraft before start of the leveling or liftingoperation (See 05-50-00 and/or 05-60-00).

(8) Calculate the possible arc movement during the leveling operation, at each lifting point.Also calculate the side load if necessary (See 06-10-00).

(9) For the wing lifting, make sure that the hook and slings can hold the lifting loads.

(10) The frame station and lifting points that will be used for lifting must no be damaged. Incase of damage, contact Airbus.

(11) Make sure that there are no sharp edges or peaks (skin damages, protruding structure,antenna ... ) in the zones where the fuselage recovery slings will be installed.See DESC 06-00-00-002-A01 for the list of leveling/lifting obstructions.

06-50-00Page 21

Jul 01/09


(12) If necessary, put wheel chocks in front of and behind the wheels of the main landing gearthat is extended and in contact with the ground.

(13) Install the landing gear downlock pins in all landing gears that are extended.

(14) All the persons who work on the leveling/lifting operation should be connected with mobilecommunication devices. Two-way voice activated headsets are ideal for this type ofoperation.

(15) No personnel must be in or below the aircraft during the leveling process. The personnelwho is not directly involved in the lifting operation must be at least 20 m (65 ft) far fromthe aircraft and cranes.

(16) Movement of fuel in the wing tanks caused by aircraft leveling can change the aircraft CGposition. Therefore, it is recommended to remove all fuel from the aircraft before leveling.(See 05-10-00) This will also decrease the necessary lifting loads.

(17) Monitor the CG during all the aircraft leveling process and be prepared to control withballast if necessary (See TASK 03-50-01-558-803-A01).

(18) Monitor the position of the slings carefully at all times during the leveling/lifting process.For the fuselage lifting, it is necessary to instal each sling at a frame station and all slingsmust be in the area listed in TASK 06-50-00-581-803-A01.

(19) You must monitor and record the applied loads at all times during the leveling and liftingprocess. If at one step of the process the maximum load (related to the lifting scenario) ismore than the allowable load, contact Airbus for definition of structure inspection tasks.Airbus recommends that you use load cells and monitoring equipment to record the appliedloads.

(20) Level or lift the aircraft slowly, obey the instructions given by the manufacturer of thelifting/leveling equipment and adjust the tethers as the aircraft starts to move.

(21) When the fuselage and the wing are leveled and if it is necessary to lift the aircraft, it isrecommended to use the 3 main jacking points to lift the aircraft to the necessary height.See AMM 07-11-00-581-001. The aircraft should not be lifted until the entire aircraft (wingand fuselage) is in a level attitude.

(22) When the aircraft is leveled and at the necessary height:

(a) Assemble a shoring device to support the fuselage and/or wings, or install jacks as asafety precaution if you work on the landing gear. Use shoring cradles on a preparedarea:- Under the fuselage FR9, F24-56 and FR60: 98D07203003 FUSELAGE SHORING

CRADLE,- Under the wing RIB 4, RIB 13 and RIB 22: 98D57004031 WING SHORING

CRADLE.If the above tools are not available on site, you can use wood cribbing with rubberprotections under the fuselage. In that case, the bearing area is the same as forpneumatic lifting bags installation: see DESC 06-40-00-001-A01.

06-50-00Page 22

Jul 01/09


(b) If possible on site, when the aircraft is on shoring cradles, extend the landing gear andinstall the downlock pins, see TASK 02-30-01-481-801-A01 or repair or replace thelanding gear.Then prepare a roadway (see 07-20-00) and tow the aircraft (see 07-40-00).

(c) Or place the forward fuselage and/or the wing(s) on a mobile trailers if it is notpossible to make the landing gear serviceable.

(23) After the recovery operation, you must do an inspection of the skin surface and the wingfor any sign of damage which may have been caused during the leveling/lifting.

06-50-00Page 23

Jul 01/09


MOVING THE AIRCRAFT

07-00-00 MOVING THE AIRCRAFT

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 07-00-00-002-A01

General Preparation

1. GeneralThis chapter gives the procedures for moving the aircraft to a hard surface. There are differentprocedures for moving the aircraft if the landing gear is serviceable, or if it is damaged.

A. Before moving the aircraft you must:- Do a detailed inspection of the landing gear to confirm its structural integrity. The landing

gear must be capable of supporting the weight of the aircraft during Towing/Deboggingoperations, see 02-30-01

- Do a check to make sure that the landing gear is in the downlocked position with thegroundlock pins fitted. If it is not possible to fit the groundlock pins, a more detailedinspection must be done to find the cause. See 02-30-01 for groundlock pin installationdetails.

B. Use one of the following procedures when the landing gear is damaged or missing:- Repair or replace the landing gear to make it capable of supporting the aircraft weight

during Towing/Debogging operations.- Use an aircraft recovery transport vehicle or vehicles to move the aircraft. See 07-60-00.

C. Before moving the aircraft, make sure that:- Fuel and cargo have been removed to make the aircraft as light as possible.- The weight and Center of Gravity (CG) are adequate for towing stability, seeTBD- The relevant authorities have confirmed that the aircraft can be moved.- The airport authority and fire department have been told that the recovery process has

moved to the next phase.- There are no fluid leaks.

2. Returning Undamaged Aircraft to a Hard SurfaceA planned recovery will allow the undamaged aircraft to be returned to the runway in the leastpossible time.

A. The recovery plan can include:- Confirmation that the aircraft is in the correct condition to be moved.- The need to remove fuel and cargo from the aircraft.- The type of ground over which the aircraft must be moved.- The direction in which the aircraft will be moved.- The type and quantity of ground equipment and recovery vehicles needed.

07-00-00Page 1

Jul 01/09


B. The following procedures may be necessary to return an undamaged aircraft to the runway ortaxiway:- For an aircraft that has moved onto soft ground or snow, it may be necessary to use the

Debogging procedure, TBD and the procedure to prepare a roadway 07-20-00. When aroadway is prepared, the width of the roadway must be sufficient to let the towing vehicleturn the aircraft if necessary.

- To make sure that the towing loads are not exceeded; use a load measuring tool to monitorthe loads at all times.

- To make sure that the Debogging loads are not exceeded; use a load measuring tool tomonitor the loads at all times unless the fuse assembly is being used, see TBD.

07-00-00Page 2

Jul 01/09


07-20-00 PREPARING A ROADWAY

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 07-20-00-001-A01

General

1. For each aircraft recovery, the recovery manager must contact the relevant specialists to obtaincorrect data applicable to the ground strength.If the aircraft has moved off the runway or taxiway, it may be necessary to build a roadway to movethe aircraft on.The roadway must be excavated to a depth that will let the finished roadway safely support theweight of the aircraft.The width of the roadway must let the aircraft be turned as necessary and let the routing of theaircraft be changed. The width of the roadway must let heavy recovery vehicles manoeuvre safely.


2. If the ground is soft or is not stable, you must excavate the ground along the route to the runwayand build a roadway. If the aircraft wheels have made ruts that are not too deep, the ruts can befilled with a foundation material.This material can be compacted gravel or railway ties/sleepers covered with sheet steel or thickplywood, see FIGURE 07-20-00-991-001-A.See chapter 04-50-00 for information on soil characteristics. Normally, general constructioncontractors will have sufficient knowledge and experience to make a safe roadway.Some of the materials that can be used in the construction of a roadway are:- Compacted stone, gravel and/or broken asphalt,- Railway ties/sleepers,- Sheet steel,- PlywoodSee chapter 09-30-01 for details of materials that can be used for the recovery operation. You mustmake sure that materials used for recovery are safe to be used, can cope with the forecasted weatherconditions and will not break under load or cause a change in aircraft stability.When sheet material is used on top of the compacted material, it is recommended that two layers ofsheet material are used. Lay the sheets with the joints of the bottom layer covered by the top layer,see FIGURE 07-20-00-991-001-A. When using sheet steel be careful to avoid fluid spills. Fluid spillson sheet steel can cause a loss of towing traction for the towing vehicles and will be a hazard for therecovery team.Steel or aluminum sections that can be bolted together are available commercially in most cities.Fabric matting that is made of different types of glass fibre is also available commercially. There aredifferent types, sizes and strengths of these materials.If there is not sufficient sheet material to make the roadway, the materials that the aircraft has beenmoved over can be re-used to complete the roadway.

07-20-00Page 1

Jul 01/09


If heavy timbers are used directly on the roadway, they must be covered with a layer of plywood orsteel. If this is not done, the load from individual wheels can push one of the timbers into soft groundand cause the aircraft to stop.When the ground is not level, the roadway must normally be made with a slope of 5˚ or less. Ifpossible, position the towing/winching vehicle on the runway to give maximum traction.

07-20-00Page 2

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

5° SLOPE

SHEET MATERIALOVERLAP

TYPICAL USE OFRAILWAY TIES/SLEEPERS

EXCAVATED AREA FILLEDWITH FOUNDATION MATERIAL

N_AR_072000_1_0010101_01_00

Preparing a RoadwayTypical Roadway Construction (Sheet 1 of 3)

FIGURE-07-20-00-991-001-A01

07-20-00Page 3

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

(STEEL PLATES, FIBERGLASS, ALUMINIUM, ...)RUNWAY MATING

N_AR_072000_1_0010102_01_00


FIGURE-07-20-00-991-001-A01

07-20-00Page 4

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

CONCRETE

N_AR_072000_1_0010103_01_00


FIGURE-07-20-00-991-001-A01

07-20-00Page 5

Jul 01/09


07-40-00 TOWING AND DEBOGGING

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 07-40-00-001-A01

General

1. This chapter gives the towing procedures to be used during an aircraft recovery.

WARNING : STAY IN COMMUNICATION WITH THE AIRFIELD OPERATING AUTHORITY/AIRTRAFFIC CONTROLLER DURING THIS PERIOD AND GET THEIR PERMISSIONTO MOVE THE AIRCRAFT.

- For towing load and angle limits, see 07-40-04,- For towing with the nose gear, see 07-40-01.- For towing with the main gear from the front, see TASK 07-40-02-584-801-A01,- For towing with the main gear from the rear, see TASK 07-40-02-584-802-A01,- For towing with deflated tires, see 07-40-03.For AMM towing procedure, see AMM 09-10-00PB201.

2. Debogging definition :Airbus considers that debogging is towing on soft ground, with or without slope consideration.

07-40-00Page 1

Jul 01/09


07-40-01 TOWING FROM THE NOSE LANDING GEAR

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 07-40-01-584-801-A01

Towing on the NLG with a Towbar

1. GeneralThis procedure gives details to push the aircraft rearward or to tow the aircraft forward using atowbar installed on the NLG.

2. Inspections- Make sure that the safety devices are installed on the landing gears, see TASK 02-30-01-481-801-

A01.- Make sure that the aircraft is stable, see TBD or AMM 05-57-00-200-001.- Make sure that the engine cowl are closed.

3. Job Setup ReferencesFor towing limits, see 07-40-04.



REFERENCE DESIGNATIOND23156000 PIN-SAFETY


TABLE 1



on Landing Gears

07-40-04 07-40-04-TOWING LOAD LIMITSAMM 05-57-00-200-001AMM 31-60-00-860-001AMM 29-24-00-863-001FIGURE 07-40-01-991-002-A FIGURE 07-40-01-991-002-A-Towing on the NLG

FIGURE 07-40-01-991-001-A FIGURE 07-40-01-991-001-A-Towing on the NLG


TABLE 2

07-40-01Page 1

Jul 01/09


5. Procedure

Subtask 07-40-01-500-001-A01

A. Preparation

(1) If possible, do an EIS start procedure, see AMM 31-60-00-860-001.

(2) On the N/W steering deactivation electrical-box 5GC (see FIGURE 07-40-01-991-002-A):

(a) Set the ground-towing control lever to the towing position.

(b) Install the D23156000 PIN-SAFETY.

Subtask 07-40-01-500-002-A01

B. Installation of the Towbar

CAUTION : MAKE SURE THAT THE TOW BAR AS A DAMPING SYSTEM, ACALIBRATED SHEAR PIN AND TWO CALIBRATED TURN SHEAR PINS.THIS IS TO PREVENT HIGH LOADS WHICH CAN CAUSE DAMAGE TO THELANDING GEAR.

(1) Install the towbar on the tow fitting.

(2) Connect the towbar to the tractor.See FIGURE 07-40-01-991-001-A.

Subtask 07-40-01-869-001-A01

C. Aircraft Configuration

(1) On the panel 400VU:- Make sure that the pressure indication on the yellow brake-pressure triple-indicator is

correct: 3000 psi (206.84 bar). The pointer must be in the green area. The pointermust be in the green range.

- If necessary, pressurize the yellow hydraulic system, see AMM 29-24-00-863-001.

(2) On the panel 110VU, set the PARKING-BRK control-switch to OFF.

(3) During towing, make sure that the pressure indication on the yellow brake-pressure triple-indicator is correct: 3000 psi (206.84 bar). The pointer must be in the green area. Thepointer must be in the green range.If necessary, pressurize the yellow hydraulic system, see AMM 29-24-00-863-001.

07-40-01Page 2

Jul 01/09


Subtask 07-40-01-584-001-A01

D. Towing

WARNING : DURING TOWING / TAXIING OPERATION (LOW-SPEED OPERATIONINCLUDED), EACH PERSON IN THE AIRCRAFT MUST BE IN A SEAT ANDTHE SEAT BELT MUST BE FASTENED. IF THE SEAT BELT IS NOTFASTENED, THERE IS A RISK OF INJURY IF THE AIRCRAFT STOPSSUDDENLY.

CAUTION : PUT THE PARKING BRAKE CONTROL SWITCH IN THE OFF POSITIONBEFORE YOU TOW OR PUSH BACK THE AIRCRAFT. THIS IS TOPREVENT HIGH LOADS WHICH CAN CAUSE DAMAGE TO THE NOSELANDING GEAR.

(1) Tow slowly and smoothly.During the towing operations, put:- one person in the cockpit to operate the brakes if necessary,- two persons to monitor the wing tips.

NOTE : The shock absorber reaction can cause the aircraft to move forward and rearwardwhen you stop the wheels. Because of this, make sure that there is sufficientspace around the aircraft when you tow with the nose gear.

Subtask 07-40-01-869-002-A01

E. Close-up

(1) Visual Inspection

(a) After you complete the towing operation, make sure that the nose wheels are alignedwith the aircraft centerline.

(2) Aircraft Configuration

(a) Put the wheel chocks in position in front of and behind the wheels.

(b) On the panel 110VU, set the PARKING BRK control switch to ON.

(c) On the panel 400VU, make sure that the pressure indication on the yellow brake-pressure triple-indicator is correct: 3000 psi (206.84 bar). The pointer must be in thegreen area. The pointer must be in the green range.If necessary, pressurize the yellow hydraulic system, see AMM 29-24-00-863-001.

(3) Removal of the Towbar

(a) Remove the towbar from the fitting of the NLG.

(b) Remove the tow-lever safety pin.

(c) Set the ground-towing lever to its initial position.

07-40-01Page 3

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

TORSION

PUSH PULL

TURNING POINT WITH RUBBER

B

B

A

N_AR_074001_1_0010101_01_00

Towing on the NLGTowing Attachment

FIGURE-07-40-01-991-001-A01

07-40-01Page 4

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TOWING LEVER

(NOSE WHEEL STREERING OPERATIONAL)NORMAL POSITION

(TOWING POSITION)SAFETY PIN

(NOSE WHEEL STEERING DEACTIVATED)TOWING POSITION

N_AR_074001_1_0020101_01_00

A

A

Towing on the NLGN/W-Steering Deactivation Electrical-Box

FIGURE-07-40-01-991-002-A01

07-40-01Page 5

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 07-40-01-584-802-A01

Towing on the NLG with a Towbarless Tractor

1. GeneralThis procedure gives details to push the aircraft rearward or to tow the aircraft forward using atowbarless tractor on the NLG.


A01.- Make sure that the aircraft is stable, see TBD or AMM 05-57-00-200-001.- Make sure that the engine cowl are closed.




REFERENCE DESIGNATIOND23156000 PIN-SAFETY


TABLE 1



on Landing Gears

TASK 07-40-01-584-801-A01 TASK 07-40-01-584-801-A01-Towing with the NLG with aTowbar

07-40-04 07-40-04-TOWING LOAD LIMITSAMM 05-57-00-200-001AMM 31-60-00-860-001AMM 29-24-00-863-001


TABLE 2

07-40-01Page 6

Jul 01/09


5. Procedure

WARNING : WHEN YOU TOW THE AIRCRAFT WITH A TOWBARLESS TRACTOR, THEPARKING BRAKE OR THE BRAKE PEDALS SHALL ONLY BE USED IN CASE OFEMERGENCY. IF YOU APLLY THE PARKING BRAKE OR THE BRAKE PEDALS,YOU CAN CAUSE OVERLOAD TO THE NLG, DAMAGE TO THE TOWBARLESSTRACTOR AND INJURY TO THE PERSONEL. IF THIS OCCURS, YOU MUSTCONTACT AIRBUS.

CAUTION : WHEN YOU USE A TOWBARLESS TRACTOR, MAKE SURE THAT YOU OBEYFULLY ALL THE INSTRUCTIONS IN THIS PROCEDURE. IF YOU DO NOT, THETRACTOR CAN CAUSE IMPORTANT SCRAPING OR OTHER DAMAGE TO THENLG AND TO THE AIRFRAME STRUCTURE AROUND THE NLG.

Subtask 07-40-01-500-003-A01

A. Preparation


(2) On the N/W steering deactivation electrical-box 5GC (see TASK 07-40-01-584-801-A01):



Subtask 07-40-01-500-004-A01

B. Installation of the Towbarless Tractor

CAUTION : AIRBUS STRONGLY RECOMMENDS THAT THE OPERATORS OFTOWBARLESS TRACTORS CAREFULLY ALIGNS THE CLAMPING DEVICEOF THE TRACTOR WITH THE NOSE LANDING GEAR AXIS. THE GAPBETWEEN THE CRADDLE AND THE TORQUE-LINK IS VERY SMAL AND AMISALIGNMENT CAN CAUSE DAMAGE TO THE TORQUE-LINK PIN. ASIMPLE ALIGNMENT DEVICE ON THE TRACTOR (MARKING, METALINDICATOR, ETC. SUPPLIED BY THE MANUFACTURER OF THETOWBARLESS TRACTOR OR MANUFACTURED LOCALLY) CAN HELP THEDRIVER.

(1) There are special approval procedures for towbarless tractors. Before towing, make surethat the towbarless is approved for the towing of this aircraft. For more information on thetowbarless tractors, see the SIL 090-002.

(2) Set the aircraft type on the towbarless tractor, if necessary.

(3) Align the clamping device of the tractor with the NLG axis.

(4) Lock on and lift the NLG.

07-40-01Page 7

Jul 01/09


(5) Make sure that the nose landing gear is correctly on the center of the tractor platform andcannot be disengaged from the tractor.

Subtask 07-40-01-869-003-A01

C. Aircraft Configuration

(1) On the panel 400VU:- Make sure that the pressure indication on the yellow brake-pressure triple-indicator is

correct: 3000 psi (206.84 bar). The pointer must be in the green area. The pointermust be in the green range.

- If necessary, pressurize the yellow hydraulic system, see AMM 29-24-00-863-001.

(2) On the panel 110VU, set the PARKING-BRK control-switch to OFF.

(3) During towing, make sure that the pressure indication on the yellow brake-pressure triple-indicator is correct: 3000 psi (206.84 bar). The pointer must be in the green area. Thepointer must be in the green range.If necessary, pressurize the yellow hydraulic system, see AMM 29-24-00-863-001.

Subtask 07-40-01-584-002-A01

D. Towing



(1) Tow slowly and smoothly.During the towing operations, put:- one person in the cockpit to operate the brakes if necessary,- two persons to monitor the wing tips.

NOTE : The shock absorber reaction can cause the aircraft to move forward and rearwardwhen you stop the wheels. Because of this, make sure that there is sufficientspace around the aircraft when you tow with the nose gear.

07-40-01Page 8

Jul 01/09


Subtask 07-40-01-869-004-A01

E. Close-up




(a) On the panel 110VU, set the PARKING BRK control switch to ON.

(b) On the panel 400VU, make sure that the pressure indication on the yellow brake-pressure triple-indicator is correct: 3000 psi (206.84 bar). The pointer must be in thegreen area. The pointer must be in the green range.If necessary, pressurize the yellow hydraulic system, see AMM 29-24-00-863-001.

(3) Removal of the Towbarless Tractor

(a) Remove the NLG from the towbarless tractor.

(b) Put the wheel chocks in position in front of and behind the wheels.

(c) Remove the tow-lever safety pin.

(d) Set the ground-towing lever to its initial position.

07-40-01Page 9

Jul 01/09


07-40-02 TOWING FROM THE MAIN LANDING GEAR

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 07-40-02-584-801-A01

Towing with the Main Gear from the Front

1. GeneralThis procedure gives details to tow the aircraft forward with the MLG.


A01.- Make sure that the aircraft is stable, see TBD or AMM 05-57-00-200-001.- Make sure that the engine cowl are closed.- Only tow the aircraft if the ground conditions let you. If necessary, put down the applicable

surface equipment: slopes, movable taxiway plates, etc. (see 07-20-00).Only try to turn if the ground conditions let you.Do a detail visual inspection of the towing cables, the fuse pins, the towing attachments beforeyou do this procedure.

3. Job Setup ReferencesDepending on the landing gear configuration, there are two methods of towing the aircraft from thefront with the MLG:- Using a towing strap around the MLG, see SUBTASK 07-40-02-500-002-A01,- Using two 98D09104000001 ATTACHMENT - TOWING or 98D09104002000 ATTACHMENT -

TOWING (OPTIONAL 4 WHEEL BOGIE MLG), see SUBTASK 07-40-02-500-003-A01.For towing limits, see 07-40-04.



REFERENCE DESIGNATIOND23156000 PIN-SAFETY98A09003500000 CABLE-TOWING, MLG

98D09104000001 ATTACHMENT - TOWING98D09104002000 ATTACHMENT - TOWING (OPTIONAL 4 WHEEL BOGIE

MLG)


TABLE 1

07-40-02Page 1

Jul 01/09




on Landing Gears

07-40-04 07-40-04-TOWING LOAD LIMITS07-20-00 07-20-00-PREPARING A ROADWAYAMM 05-57-00-200-001AMM 31-60-00-860-001AMM 29-24-00-863-001FIGURE 07-40-02-991-001-A FIGURE 07-40-02-991-001-A-Towing with the MLG from the

FrontFIGURE 07-40-02-991-002-A FIGURE 07-40-02-991-002-A-Towing with the MLG from the

FrontFIGURE 07-40-02-991-003-A FIGURE 07-40-02-991-003-A-Towing with the MLG from the

Front


TABLE 2

5. Procedure

WARNING : DO NOT USE A MANUAL NOSE WHEEL STEERING BAR DURING TOWINGFROM THE FRONT BECAUSE THE TOWING CABLES WILL BE NEAR THEPERSON AT THE STEERING BAR. DEATH OR INJURY CAN OCCUR IF ATOWING CABLE BREAKS.

Subtask 07-40-02-500-001-A01

A. Preparation


(2) On the N/W steering deactivation electrical-box 5GC:



Subtask 07-40-02-500-002-A01

B. Installation of the Towing Strap


07-40-02Page 2

Jul 01/09


WARNING : MAKE SURE THAT NO PERSONS ARE NEAR THE TOWING CABLES WHENTHE TRACTOR APPLIES TENSION TO THE CABLES. DEATH OR INJURYCAN OCCUR IF A CABLE BREAKS.

(1) Use a towing strap with the properties that follow:- Length 2160 mm (85 in),- Width 100 mm (4 in),- Safe Working Load 1300 daN (29225 lbf).

(2) Wind the towing strap around the bottom of the MLG shock absorber and the axles.Make sure that the towing strap does not touch the links of the MLG. See FIGURE07-40-02-991-001-A.

(3) Connect the 98A09003500000 CABLE-TOWING, MLG to the towing strap.

(4) Connect the 98A09003500000 CABLE-TOWING, MLG to the tractor.

NOTE : Airbus recommends that you install bridge cables or ropes between the towingcables to prevent unwanted cable movement if a cable breaks.

(5) Do SUBTASK 07-40-02-584-001-A01.

Subtask 07-40-02-500-003-A01

C. Installation of the Towing Attachment



(1) Install the 98D09104000001 ATTACHMENT - TOWING (see FIGURE 07-40-02-991-002-A) or 98D09104002000 ATTACHMENT - TOWING (OPTIONAL 4 WHEEL BOGIE MLG)(see FIGURE 07-40-02-991-003-A) on each MLG.

(2) Install the 98A09003500000 CABLE-TOWING, MLG on the towing attachments.



(4) Do SUBTASK 07-40-02-584-001-A01.

07-40-02Page 3

Jul 01/09


Subtask 07-40-02-584-001-A01

D. Towing




(1) Tow the aircraft slowly and smoothly.During the towing, put:- one person in the cockpit to operate the brakes if necessary,- two persons to monitor the wing tips.

WARNING : DO NOT USE A MANUAL NOSE WHEEL STEERING BAR DURING TOWINGFROM THE FRONT BECAUSE THE TOWING CABLES WILL BE NEAR THEPERSON AT THE STEERING BAR. DEATH OR INJURY CAN OCCUR IF ATOWING CABLE BREAKS.

(2) Where possible, keep the tractor aligned with the aircraft centerline. The maximum lateralposition that is permitted is the width of the aircraft.

NOTE : Airbus recommend that you install load cells on the towing cables to record andmonitor the loads applied on the MLG during the towing.

Subtask 07-40-02-869-001-A01

E. Close-up






07-40-02Page 4

Jul 01/09



(3) Removal of the Tooling

(a) Remove the towing cable.

(b) Remove the towing attachment or the towing strap from each MLG.

(c) Remove the tow-lever safety pin.

(d) Set the ground-towing lever to its initial position.

07-40-02Page 5

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_074002_1_0010101_01_00

TOWING CABLE

TOWING STRAP

A

A

Towing with the MLG from the FrontStrap Installation

FIGURE-07-40-02-991-001-A01

07-40-02Page 6

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_074002_1_0020101_01_00

A

TOWING CABLE

TOWING ATTACHMENT

A

Towing with the MLG from the FrontTowing Attachment Tool - Two Wheel MLG

FIGURE-07-40-02-991-002-A01

07-40-02Page 7

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_074002_1_0030101_01_00

TOWING CABLE

TOWING ATTACHMENT

A

A

Towing with the MLG from the FrontTowing Attachment Tool - Four Wheel Bogie MLG (Optional A320 Only)

FIGURE-07-40-02-991-003-A01

07-40-02Page 8

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 07-40-02-584-802-A01

Towing with the Main Gear from the Rear

1. GeneralThis procedure gives details to tow the aircraft rearward with the MLG.


A01.- Make sure that the aircraft is stable, see TBD or AMM 05-57-00-200-001.- Make sure that the engine cowl are closed.- Only tow the aircraft if the ground conditions let you. If necessary, put down the applicable

surface equipment: slopes, movable taxiway plates, etc. (see 07-20-00).Only try to turn if the ground conditions let you.Do a detail visual inspection of the towing cables, the fuse pins, the towing attachments beforeyou do this procedure.



A. Consumable Materials

REFERENCE DESIGNATION05-047 Anti Corrosion Compound (High Temperature Silicone Sealant)

09-016 Corrosion Inhibiting Fillet Consistency

Consumable Materials

TABLE 1

B. Fixtures, Tools, Test and Support

REFERENCE DESIGNATIOND23156000 PIN-SAFETY98D09104001000 ATTACHEMENT-TOWING98D09104002000 ATTACHMENT - TOWING (OPTIONAL 4 WHEEL BOGIE

MLG)

98A09003500000 CABLE-TOWING, MLG

98A09003000001 BAR-STEERING, NOSE WHEEL


TABLE 2

07-40-02Page 9

Jul 01/09


C. Referenced Information


on Landing Gears

07-40-04 07-40-04-TOWING LOAD LIMITS07-20-00 07-20-00-PREPARING A ROADWAYAMM 05-57-00-200-001AMM 31-60-00-860-001AMM 29-24-00-863-001FIGURE 07-40-02-991-004-A FIGURE 07-40-02-991-004-A-Towing with MLG from the Rear

FIGURE 07-40-02-991-005-A FIGURE 07-40-02-991-005-A-Towing with MLG from the Rear




TABLE 3

5. Procedure

Subtask 07-40-02-500-004-A01

A. Preparation

(1) If possible, do an EIS star procedure, see AMM 31-60-00-860-001.

(2) On the N/W steering deactivation electrical-box 5GC:



Subtask 07-40-02-020-001-A01

B. Removal of Components for Access

(1) See FIGURE 07-40-02-991-004-A.

(2) Remove the nuts (1), the washers (2) and the bolts (3).

(3) Remove the block (4).

(4) Remove the split pin (7), nut (6) and washer (5).

(5) Remove the bolt (9) and sleeve (8).

(6) Disconnect the rod end of the lower slave link sub-assembly (10).

07-40-02Page 10

Jul 01/09


Subtask 07-40-02-500-006-A01

C. Installation of the Towing Attachment



(1) Install the 98D09104001000 ATTACHEMENT-TOWING (see FIGURE 07-40-02-991-005-A) or 98D09104002000 ATTACHMENT - TOWING (OPTIONAL 4 WHEEL BOGIE MLG)(see FIGURE 07-40-02-991-006-A) on each MLG.

(2) Install the 98A09003500000 CABLE-TOWING, MLG on the towing attachments.



WARNING : BE CAREFUL WHEN YOU USE THE NOSE WHEEL STEERING-BAR DURINGTOWING OF THE AIRCRAFT. THERE IS A RISK OF INJURY IF SUDDENUNWANTED MOVEMENT OF THE AIRCRAFT OR STEERING BAR OCCURS.

(4) Install the 98A09003000001 BAR-STEERING, NOSE WHEEL on the NLG, see FIGURE07-40-02-991-007-A.

Subtask 07-40-02-584-002-A01

D. Towing



WARNING : BE CAREFUL WHEN YOU USE THE NOSE WHEEL STEERING-BAR DURINGTOWING OF THE AIRCRAFT. THERE IS A RISK OF INJURY IF SUDDENUNWANTED MOVEMENT OF THE AIRCRAFT OR STEERING BAR OCCURS.

07-40-02Page 11

Jul 01/09



(1) Tow the aircraft slowly and smoothly.During the towing, put:- one person in the cockpit to operate the brakes if necessary,- two persons to monitor the wing tips.

(2) Where possible, keep the tractor aligned with the aircraft centerline. The maximum lateralposition that is permitted is the width of the aircraft.

NOTE : Airbus recommend that you install load cells on the towing cable to record andmonitor the loads applied on the MLG during the towing.

Subtask 07-40-02-869-002-A01

E. Close-up







(3) Removal of the Tooling

(a) Remove the 98A09003000001 BAR-STEERING, NOSE WHEEL.

(b) Remove the towing cable.

(c) Remove the towing attachment of the towing strap from each MLG.

(d) Remove the tow-lever safety pin.

(e) Set the ground-towing lever to its initial position.

Subtask 07-40-02-500-007-A01

F. Install Components

(1) Put the rod end of the lower slave link sub-assembly (10) in position.See FIGURE 07-40-02-991-004-A.

07-40-02Page 12

Jul 01/09


WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 05-047 ANTI CORROSIONCOMPOUND (HIGH TEMPERATURE SILICONE SEALANT). OBEY THEMATERIAL MANUFACTURER’S INSTRUCTIONS.

(2) Apply Material No. 05-047 Anti Corrosion Compound (High Temperature Silicone Sealant)on the plain shank of the bolt (9).

(3) Install the bolt (9), the sleeve (8), the washer (5) and the nut (6). Torque the nut (6) tobetween 2.1 and 2.7 m.daN (15.48 and 19.91 lbf.ft).

(4) Install the new split (7).

(5) Make sure that the lower slave link sub-assembly (10) is free to turn around the bolt (9).

WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 09-016 CORROSIONINHIBITING FILLET CONSISTENCY. OBEY THE MATERIALMANUFACTURER’S INSTRUCTIONS.

(6) Apply Material No. 09-016 Corrosion Inhibiting Fillet Consistency on the bolt (9) and nut(6).

(7) Put the block (4) in position on the flexible hoses and loosely install bolts (3), the washers(2) and the nuts (1).

(8) Make sure that the dimension ”Y” is 150 mm (5.91 in).

(9) Torque the nuts (1) to between 0.4 and 0.45 m.daN (35.39 and 39.82 lbf.in).

07-40-02Page 13

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

1 2

3

A

YB

A

B

9

8

7

65

N_AR_074002_1_0040102_01_00

10

Towing with MLG from the RearRemoval of Lower Slave Link

FIGURE-07-40-02-991-004-A01

07-40-02Page 14

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

TOWING CABLE

N_AR_074002_1_0050101_01_00

A

Towing with MLG from the RearTowing Attachment Tool - Two Wheel MLG

FIGURE-07-40-02-991-005-A01

07-40-02Page 15

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TOWINGCABLE

TOWINGATTACHMENT

A

N_AR_074002_1_0060101_01_00

A

Towing with MLG from the RearTowing Attachment Tool - Four Wheel Bogie MLG (Optional A320 Only)

FIGURE-07-40-02-991-006-A01

07-40-02Page 16

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_074002_1_0070101_01_00

A

A

Towing with MLG from the RearManual Steering Bar

FIGURE-07-40-02-991-007-A01

07-40-02Page 17

Jul 01/09


07-40-03 TOWING WITH DEFLATED TIRES

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 07-40-03-584-801-A01

Towing with Deflated Tires

1. GeneralThis procedure gives details and limitations to tow the aircraft when one or more tires are deflated.

2. InspectionsNot Applicable

3. Job Setup ReferencesThe steering angle must be kept to a limit when you tow the aircraft with one or more tires deflatedon one or more landing gears.- For aircraft equipped with the twin wheel MLG, see SUBTASK 07-40-03-584-001-A01,- For aircraft equipped with the optional four wheel bogie MLG (A320 only), see SUBTASK

07-40-03-584-002-A01.



REFERENCE DESIGNATIONTASK 07-40-01-584-801-A01 TASK 07-40-01-584-801-A01-Towing with the NLG with a

TowbarTASK 07-40-02-584-801-A01 TASK 07-40-02-584-801-A01-Towing with the Main Gear from

the Front


TABLE 1

5. Procedure

Subtask 07-40-03-584-001-A01

A. Twin Wheel Main Landing Gear

(1) One tire is deflated on one or more gears (a maximums of three deflated tires).- Tow by the nose gear, see TASK 07-40-01-584-801-A01. The maximum permitted

lateral angle of the towbar is plus or minus 10 degrees.

(2) One tire is deflated on one main gear.- Tow by the nose gear, see TASK 07-40-01-584-801-A01. The maximum permitted


(3) Two tires are deflated on the same gear.- Tow by the main gear only, see TASK 07-40-02-584-801-A01.- The towbar must not move laterally at all.

07-40-03Page 1

Jul 01/09


Subtask 07-40-03-584-002-A01

B. Optional Four Wheel Bogie Main Landing Gear (A320 only)

(1) One tire is deflated on one or more gears (a maximum of three deflated tires).- Tow by the nose gear, see TASK 07-40-01-584-801-A01. The maximum permitted


(2) One tire or two tires (one on each axle) deflated on one main gear.- Tow by the nose gear, see TASK 07-40-01-584-801-A01. The maximum permitted


(3) Two tires on the same axle or more than two tires deflated on the same gear (with the twotires on the NLG inflated).- Tow by the main gears, see TASK 07-40-02-584-801-A01.- Steer by the NLG with the towbar or the normal steering control, see TASK

07-40-01-584-801-A01.

(a) Two tires on the same axle or three tires deflated on the same gear.- The maximum permitted steering angle of the NLG is plus or minus 50 degrees.

(b) All the four tires are deflated on the same MLG.- The towbar must not move laterally at all.- The speed must be kept to a limit of approximately 1.3 m/s (4.27 ft/s).

07-40-03Page 2

Jul 01/09


07-40-04 TOWING LOAD LIMITS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 07-40-04-001-A01

Load and Angle Limits

1. Towing

WARNING : OBEY THE SAFETY PRECAUTIONS DURING TOWING OR MOVEMENT OF THEAIRCRAFT. MAKE SURE THAT THE PATH OF THE AIRCRAFT IS CLEAR. MAKESURE THAT NO PERSONS SIT OR STAND ON THE TOW BAR OR USE THETRACTOR AS TRANSPORT, THIS IS TO PREVENT THE RISK OF INJURY.

WARNING : DURING TOWING / TAXIING OPERATION (LOW-SPEED OPERATIONINCLUDED), EACH PERSON IN THE AIRCRAFT MUST BE IN A SEAT AND THESEAT BELT MUST BE FASTENED. IF THE SEAT BELT IS NOT FASTENED,THERE IS A RISK OF INJURY IF THE AIRCRAFT STOPS SUDDENLY.

CAUTION : DO NOT TOW OR MOVE THE AIRCRAFT ON THE GROUND IF THE ENGINECOWLS ARE OPEN.MOVEMENT OF THE AIRCRAFT WITH THE COWLS OPEN CAN CAUSEDAMAGE TO THE COWLS AND THE NACELLE STRUCTURE.

It is recommended that you use a towbar with a damping system.

A. You can use the NLG towbar fitting to tow or push the aircraft:- with maximum weight,- with the engines between zero and idle.

B. You can use the MLG attachments to tow the aircraft:- with the engines stopped,- when it is bogged.

C. Do not tow the aircraft if the dimension H is more than 300 mm (11.8110 in), see FIGURE07-40-04-991-001-A). If you do so, you can cause damage to the cams that make the nose gearwheels go back to the center position.

D. Keep a minimum of 3 m (9.84 ft) separation from the nose wheels, towbar and tractor while theaircraft moves.

2. Speed LimitsThe maximum permitted towing speed changes with the aircraft configuration.

A. Doors closed and locked or removed:

(1) For a tractor with a towbar, a maximum speed of 25 km/h (15.5 mph) is permitted.

(2) For a towbarless tractor, a maximum speed of 32 km/h (19.9 mph) is permitted.

07-40-04Page 1

Jul 01/09


B. Passenger/crew doors fully open and locked and/or cargo doors open in vertical position:

(1) The maximum permitted speed is 10 km/h (6.2 mph).

C. In wind conditions, calculate the permitted towing speed before towing:

(1) Measure the wind speed.

(2) Do a check of aircraft stability, see TBD or AMM 05-57-00-200-001.

(3) Substract measured wind speed from wind speed limit shown on the stability curve. Thisgives the maximum permitted towing speed.

3. Approximate Towing LoadsSee FIGURE 07-40-04-991-002-A.

NOTE : In all the formulas, MTW = Maximum Taxi Weight.

A. When you push the aircraft rearward with the engines at idles, you must add the engine thrustresistance to the towing loads.

NOTE : The engine thrust resistance at ground idle is 400 daN (for each engine in operation).

B. Use these coefficients for the friction between the tires of the tow tractor and the ground tocalculate the tractor weight:- Dry concrete or asphalt: 0.80- Wet asphalt: 0.75- Wet asphalt: 0.57- Hard snow: 0.20- Ice: 0.05Minimum Tractor Weigh = 6% MTW / (friction coefficient)

**ON A/C A318-100 A319-100 A320-100 A320-200

4. Limit Loads and AnglesSee FIGURE 07-40-04-991-003-A.

A. In all the towing configurations, the safety pin locks the control lever on the interphone box inthe disengaged position.

B. The maximum permitted steering angle on each side of the aircraft centerline is:- +/- 95 degrees with towbar,- +/- 85 degrees without towbar.

C. During towing, the towing angle must not be more that then angle shown on the FWD NLGdoors.

D. Tow the aircraft (slowly and smoothly) with the main landing gear:- The maximum towing angle in the vertical plane is 11 degrees.- The NLG gives the limits for the maximum towing angle in the horizontal plane.

07-40-04Page 2

Jul 01/09


E. Use a towbar with:- The towing shear pins, calibration 9425 daN (21188.24 lbf) for the protection of the landing

gear against too high loads,- The safety shear pin, calibration 826 m.daN (6091.44 lbf.ft) for the protection of the

landing gear against to high torsion.

F. Use:- The tow special fork fitting and a cable to tow the main landing gear forward or rearward.

Attach these special fork fittings to the lugs at each end of the landing gear.- The safety shear pin, calibration 29000 daN (65194.58 lbf) which comes with the two-

fitting/cable net.

**ON A/C A321-100 A321-200

5. Limit Loads and AnglesSee FIGURE 07-40-04-991-003-A.

A. In all the towing configurations, the safety pin locks the control lever on the interphone box inthe disengaged position.

B. The maximum permitted steering angle on each side of the aircraft centerline is:- +/- 95 degrees with towbar,- +/- 85 degrees without towbar.

C. During towing, the towing angle must not be more that then angle shown on the FWD NLGdoors.

D. Tow the aircraft (slowly and smoothly) with the main landing gear:- The maximum towing angle in the vertical plane is 4 degrees.- The NLG gives the limits for the maximum towing angle in the horizontal plane.

E. Use a towbar with:- The towing shear pins, calibration 9425 daN (21188.24 lbf) for the protection of the landing

gear against too high loads,- The safety shear pin, calibration 826 m.daN (6091.44 lbf.ft) for the protection of the

landing gear against to high torsion.

F. Use:- The tow special fork fitting and a cable to tow the main landing gear forward or rearward.

Attach these special fork fittings to the lugs at each end of the landing gear.- The safety shear pin, calibration 29000 daN (65194.58 lbf) which comes with the two-

fitting/cable net.

07-40-04Page 3

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_074004_1_0010101_01_00

H

Towing LimitsMaximum Extension of the NLG Shock Absorber

FIGURE-07-40-04-991-001-A01

07-40-04Page 4

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_074004_1_0020101_01_00

TOWING FORCES

BREAKAWAY

ROLLING

BREAKAWAYON SLOPE

ON SLOPEROLLING

F

6% MTW

3% MTW

6% MTW+ 1% MTW PER

1% SLOPE

+ 1% MTW PER1% SLOPE

3% MTW

Towing LimitsTowing Forces

FIGURE-07-40-04-991-002-A01

07-40-04Page 5

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

GEAR LOADS

A

B 29000

9425daN

65200

21188lbf

BB

BB

A

A

MAXIMUM

MAX ANGLEWITH TOWBAR = 95° MAX ANGLE WITH

TOWBARLESS = 85°

N_AR_074004_1_0030101_01_01

Towing LimitsTowing Loads and Angles

FIGURE-07-40-04-991-003-A01

07-40-04Page 6

Jul 01/09


07-60-00 MOVING DAMAGED AIRCRAFT

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 07-60-00-001-A01

General

1. This section describes the moving of aircraft with damaged or missing landing gear.If it is possible, the aircraft must always be moved the landing gear supporting the weight of theaircraft.Before moving the aircraft, you must verify the structural integrity of the landing gear and thestructural attachments in accordance with the landing gear inspection procedure 02-30-01.For landing gears that are not correctly extended, see TBD for information on the manual extensionof the landing gear.If any of the landing gear are damaged, you must always try to repair or replace the damaged landinggear. This could include:- The repair of the existing landing gear,- The installation of a replacement landing gear,- The temporary bracing of the landing gear to support the weight of the aircraft.The repair or replacement of damaged landing gear is the recommended solution if a replacementlanding gear is available and the structural attachments for the landing gear are not damaged.If it is not possible to move the aircraft using it’s landing gears, then you must use a different supportsystem to move the aircraft, see 07-60-03. It may be necessary to use one of the following vehicles ora combination of vehicles to move the aircraft.- Flat bed trailers,- Movable cranes,- Specialist aircraft recovery transportation systems,- General purpose trucks,- Commercial transport equipment.Moving the aircraft using aircraft recovery vehicles must be the last method to be used after all othermethods have been analyzed. When aircraft recovery transport vehicles are used, secondary damage ispossible.

07-60-00Page 1

Jul 01/09


07-60-01 MOVING DAMAGED AIRCRAFT ON TRAILERS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 07-60-01-001-A01

Moving Damaged Aircraft on Trailers

1. If the Landing Gear cannot be made serviceable, the use of trailers gives a safe and correct method ofsupporting the aircraft fuselage and/or the wings.

WARNING : MAKE SURE THAT THE TRAILERS, AND ALL OTHER EQUIPMENT YOU USEWITH THE TRAILERS, ARE SAFE FOR THE WEIGHT THEY MUST SUPPORT.

CAUTION : BE CAREFUL WHEN YOU USE SUPPORTS. MAKE SURE THAT THE LOADS ONTHE AIRFRAME ARE LESS THAN THE ALLOWABLE LOADS (SKIN LOADINGLIMITS) WHEN YOU USE SUPPORTS. THE SUPPORTS APPLY LOADS THATDO NOT OCCUR IN NORMAL OPERATION.

CAUTION : SECONDARY DAMAGE CAN OCCUR WHEN YOU USE TRAILERS TO SUPPORTAND MOVE THE AIRCRAFT.

CAUTION : DO NOT APPLY LOADS TO THE ENGINE NACELLE STRUCTURE BECAUSESECONDARY DAMAGE WILL OCCUR.

CAUTION : DO NOT APPLY LOADS TO THE FLAP-TRACK FAIRING STRUCTUE BECAUSESECONDARY DAMAGE WILL OCCUR

A. See 06-40-00 for the bearing area under the fuselage and wings.

B. You must inspect the aircraft structure for damage in the bearing areas. Make sure that thestructure is capable of supporting the weight of the aircraft on the trailers.

C. You can support the forward fuselage on a turntable, this will help to turn the aircraft duringthe move. If a turntable is used, it must conform to the weight requirements and general aircraftspecifications to prevent secondary damage and assist in the removal of the aircraft.

D. Install supports between the aircraft and the trailer surface. These can be made of timber andmust be covered with padded material to avoid damage to the aircraft surfaces. The supportsthat you use must be able to support the expected loading.

E. Materials such as mattresses, rubber padding, tires, pneumatic bags and sand bags can be usedas padding. It is important that the padding is arranged to follow the contour of the aircraftsurfaces, this will helps to spread the loads on the surface and to avoid point loads. Filler foamcan be used at the support areas to fill gaps and make a correct contoured support.You must not exceed the allowable skin loading limits on the aircraft surfaces, see 06-40-00.

F. It is important that the supports (timber) and padding remain stable while you move theaircraft. It may also be necessary to tie down the aircraft structure to the trailer to preventrelative movement between the aircraft and the trailer.

07-60-01Page 1

Jul 01/09


G. Some aircraft recovery trailers have hydraulically controlled supports, that conform to thefuselage and wing contours.

H. Monitor the loads during all the moving operation.

07-60-01Page 2

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_076001_1_0020101_01_00

NOSE TRAILERWITH ADJUSTABLE

TURNTABLE

HYDRAULIC PLATFORMBOGIES FOR SMALLER

LOADS

CABLE AND CHAINCONNECTION

SOME TRAILERSHAVE HYDRAULICALLY

CONTROLLED SUPPORTS

MAXIMUM15 DEGREE TILT

Moving Damaged Aircraft on TrailersConfiguration of Trailers

FIGURE-07-60-01-991-002-A01

07-60-01Page 3

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

PA

DD

ING

MA

TE

RIA

LS(P

LYW

OO

D, P

NE

UN

AT

IC L

IFT

ING

BA

GS

, TIR

ES

, ET

C)

TIE

DO

WN

ST

RA

PF

LAT

BE

D T

RA

ILE

R

TY

PIC

AL

TU

RN

TA

BLE

FLA

TB

ED

TR

AIL

ER

N_A

R_0

7600

1_1_

0030

101_

01_0

0

Moving Damaged Aircraft on TrailersTypical Use of Trailers with Aircraft

FIGURE-07-60-01-991-003-A01

07-60-01Page 4

Jul 01/09


07-60-02 MOVING DAMAGED AIRCRAFT WITH CRANES

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 07-60-02-001-A01

Moving Damaged Aircraft with Cranes

1. General


CAUTION : BE CAREFUL WHEN YOU USE SUPPORTS. MAKE SURE THAT THE LOADS ONTHE AIRFRAME ARE LESS THAN THE ALLOWABLE LOADS (SKIN LOADINGLIMITS) WHEN YOU USE SUPPORTS. THE SUPPORTS APPLY LOADS THATDO NOT OCCUR IN NORMAL OPERATION.

CAUTION : USE ONLY RECOVERY SLINGS AND SPREADER BEAMS SPECIFIED BY AIRBUS.NON-APPROVED LIFTING DEVICES CAN CAUSE SECONDARY DAMAGE TOTHE AIRCRAFT.

CAUTION : MAKE SURE THAT THE CRANE YOU USE CAN LIFT THE ESTIMATED LOADPLUS THE WEIGHT OF THE LIFTING EQUIPMENT BEFORE YOU START TOLIFT THE AIRCRAFT.


The principles outlined in this chapter are provided as a guide to assist an aircraft recovery.See 06-50-00 for information on the use of cranes.If it is possible, damaged landing gears must be repaired or replaced. This will allow the aircraft to bemoved with it’s own landing gear supporting the weight of the aircraft.If it is not possible to repair or replace the damaged landing gear, an alternative method is to usemobile crane or crawler crane to help move the aircraft.

NOTE : You must analyze other methods of supporting and moving the aircraft before using thismethod.

If the aircraft is in this condition, then it is possible to use cranes and sling assembly to level and liftthe aircraft. The cranes can then be left in place to support and move the aircraft.Roadways must be properly prepared to support the weight of the crane and the aircraft as they aremoved, see 07-20-00.

2. Moving the Aircraft with CranesThe crane must be positioned close enough to the aircraft and the lifting point, to let the crane useits lifting capacity safely.

07-60-02Page 1

Jul 01/09


A. You must monitor and record the loads on the slings when you use this process.

B. The moveable cranes must begin to move at the same time, and must move steadily at thesame speed during the entire aircraft movement operation.

C. The person controlling the operation must be in constant contact with the cranedrivers/operators.

D. See 06-50-00 for tooling specification, procedures and limitations to level/lift the aircraft usingcranes.

07-60-02Page 2

Jul 01/09


07-60-03 MOVING DAMAGED AIRCRAFT WITH SPECIALIZED EQUIPMENT

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 07-60-03-001-A01

Moving Damaged Aircraft with Specialized Vehicles

1. Specialized recovery vehicles include sledges and patent trailer systems made by differentmanufacturers.

CAUTION : DO NOT APPLY LOADS OUT OF THE ALLOWABLE LIMITS BECAUSESECONDARY DAMAGE WILL OCCUR

CAUTION : DO NOT APPLY LOADS TO THE ENGINE NACELLE STRUCTURE BECAUSESECONDARY DAMAGE WILL OCCUR.

A. The sledge systems are simple systems that are used to support the aircraft while it is towed onsoft ground.

B. The patent trailer systems are complex systems and can be used to move damaged aircraft thathas no serviceable landing gear, see 07-60-01.This type of trailer normally:- Has hydraulically controlled supports that can conform to the fuselage and wing contours.- Has a multi-wheel steering function.- Can be linked with beams or cables to other trailers.

07-60-03Page 1

Jul 01/09


POST RECOVERY CORRECTIVE ACTIONS

08-00-00 POST RECOVERY CORRECTIVE ACTIONS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 08-00-00-001-A01

General

1. RecordsAirbus recommends that you make records on the full recovery operation.These records can help you:- To make aircraft maintenance operations easier for the return to service- To have a feedback of the recovery operation- To have traceability after the recovery.The records can include:- The aircraft inspection report- Results of loads and CG calculations- The technique used to level/lift and move the aircraft- Loads applied during the recovery operation- ...

2. Post Recovery InspectionsIf necessary, do the ”Inspection After Leaving Runway or Taxiway”, see AMM 05-51-24-200-001.

08-00-00Page 1

Jul 01/09


APPENDIX

09-00-00 APPENDIX

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-00-00-001-A01

Introduction

1. This chapter has the structure that follows:

A. General Information (09-10)

(1) General charts and formulae for metric and imperial measurement conversion.

(2) Definitions related to aircraft recovery (glossary).

(3) General aircraft dimensions, fuselage, wing and horizontal stabilizer stations, frames andribs, door sizes, ground clearances, ground service connections illustrations, etc.).

B. Recovery Preparation (09-20)

(1) Guides or planning charts not related to the aircraft type.

(2) Possible composition of the recovery team.

C. Tooling and Equipment (09-30)

(1) General aircraft recovery materials and equipment.

(2) Specific aircraft tooling and aircraft recovery kits.

(3) Aircraft Recovery Kits.

D. Calculation Worksheets (09-50)

(1) Weight and balance calculation worksheets.

09-00-00Page 1

Jul 01/09


09-10-01 UNITS AND CONVERSIONS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-01-002-A01

Units of Measurements

1. This topic gives the ISO and NON-ISO units used in this manual.

meters (m)Length

millimeters (mm)

Area square meters (m2)

Volume cubic meters (m3)

Weight kilograms (kg)

kilograms per cubic meter (kg/m3)Density

kilograms per liter (kg/l)

Force Newtons (N)

Newton-meters (N.m)Moment

product of weight and length in kilogram-meters (kgm)

Pascals (Pa)Pressure

bars (bar)

meters per second (m/s)Velocity

kilometers per hour (km/h)

Capacity and Quantity liters (l)

Temperature degrees Celsius (˚C)

radians (rad)Angle

degrees (˚)

ISO and Derived Measurement System

TABLE 1

feet (ft)Length

inches (in)

Area square feet (ft2)

Volume cubic feet (ft3)

Weight pounds (lb)

pounds per cubic foot (lb/ft3)Density

pounds per US gallon (lb/US gal)

09-10-01Page 1

Jul 01/09


Force pound-force (lbf)

pound-force feet (lbf.ft)Moment

product of weight and length in pounds-inches (lb.in)

Pressure pounds per square inch (psi)

feet per seconds (ft/s)Velocity

miles per hour (mph)

Capacity and Quantity US gallons (US gal)

Temperature degrees Fahrenheit (˚F)

radians (rad)Angle

degrees (˚)

US Customary System

TABLE 2

09-10-01Page 2

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-01-001-A01

Conversion Tables

1. This topic gives the conversion values to use for the conversion of units.

MULTIPLY BY TO OBTAIN

Meters (m)Meters (m)Millimeters (mm)Millimeters (mm)

39.370083.2808400.039370080.00328084

Inches (in)Feet (ft)Inches (in)Feet (ft)

LengthInches (in)Inches (in)Feet (ft)Feet (ft)

0.025425.40.3048304.8

Meters (m)Millimeters (mm)Meters (m)Millimeters (mm)

Square meters (m2) 10.763910 Square feet (ft2)Area

Square feet (ft2) 0.09290304 Square meters (m2)

Cubic meters (m3) 35.31466 Cubic feet (ft3)Volume

Cubic feet (ft3) 0.02831685 Cubic meters (m3)

Kilograms (kg) 2.204622 Pounds (lb)Weight

Pounds (lb) 0.4535924 Kilograms (kg)

Kilograms per liter (kg/l)Kilograms per liter (kg/l)Kilograms per cubic meter (kg/m3)Kilograms per cubic meter (kg/m3)

62.427978.34564590.062427970.0083457

Pounds per cubic foot (lb. ft3)Pounds per US gallon (lb/US gal)Pounds per cubic foot (lb. ft3)

Pounds per US gallon (lb/US gal)Density

Pounds per cubic foot (lb. ft3)Pounds per cubic foot (lb. ft3)Pounds per US gallon (lb/US gal)Pounds per US gallon (lb/US gal)

0.01601846316.0184630.119823119.8225188

Kilograms per liter (kg/l)Kilograms per cubic meter (kg/m3)Kilograms per liter (kg/l)Kilograms per cubic meter (kg/m3)

Newtons (N) 0.2248089 Pound-forces (lbf)

Pound-forces (lbf) 4.448222 Newtons (N)Force

Newtons (N)Decanewtons (daN)

100.1

Decanewtons (daN)Newtons (N)

Newton-meters (N.m) 0.7375621 Pound-force feet (lbf.ft)

Pound-force feet (lbf.ft) 1.355818 Newton-meters (N.m)Moment

Newton-meters (N.m)Decanewton-meters (daN.m)

100.1

Decanewton-meters (daN.m)Newton-meters (N.m)

09-10-01Page 3

Jul 01/09


MULTIPLY BY TO OBTAIN

Pascals (Pa)Bars (bar)

0.000145037714.50377

Pounds per square inch (psi)Pounds per square inch (psi)

PressurePounds per square inch (psi)Pounds per square inch (psi)

6894.7570.06894757

Pascals (Pa)Bars (bar)

Meters per second (m/s)Meters per second (m/s)Kilometers per hour (km/h)Kilometers per hour (km/h)

3.28083992.23690.91130.6214

Feet per second (ft/s)Miles per hour (mph)Feet per second (ft/s)Miles per hour (mph)

Feet per second (ft/s)Feet per second (ft/s)Miles per hour (mph)Miles per hour (mph)

0.30481.09730.44701.6093

Meters per second (m/s)Kilometers per hour (km/h)Meters per second (m/s)Kilometers per hour (km/h)

Knots (kt)Kilometers per hour (km/h)

1.8520.5399568

Kilometers per hour (km/h)Knots (kt)

Velocity

Knots (kt)Miles per hour (mph)

1.1500.86897

Miles per hour (mph)Knots (kt)

Liters (l) 0.264172 US gallons (US gal)CapacityQuantity US gallons (US gal) 3.785412 Liters (l)

Conversion Table

TABLE 1

Temperature conversion:- Temperature conversion from degrees Celsius (˚C) to degrees Fahrenheit (˚F):

˚F = 1.8 × ˚C + 32- Temperature conversion from degrees Fahrenheit (˚F) to degrees Celsius (˚C):

˚C = 0.5555 × (˚F - 32)

09-10-01Page 4

Jul 01/09


09-10-02 GLOSSARY OF TERMS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-02-001-A01

Definition of Terms

1. GeneralThe terms that follow are used in the ARM.

A. Aircraft RecoveryAn aircraft recovery operation is the action of moving any aircraft that is disabled and unable tomove with its power or with the standard use of a correct tow tractor and standard tow bar,but can be economically repairable.Examples of aircraft recovery incidents are:- One or more landing gears off the hard surface of a runway, taxiway or apron,- Aircraft bogged down in mud, snow or sand,- One or more landing gears retracted, collapsed, damaged, or missing.

B. Warnings, Cautions and NotesThese definition of these are as follow:- WARNING: Calls attention to the use of materials, processes, methods, procedures or limits

that must be obeyed to prevent injury or death to persons.- CAUTION: Calls attention to methods and procedures that must be obeyed to prevent

damage to equipment.- NOTE: Calls attention to methods that make the job easier or give more information.

2. Weight Terms

A. Manufacturer Empty Weight (MEW)The weight of the structure, power plant, systems, furnishings and other items of equipment,part of a special aircraft configuration, with the fluids in closed systems (e.g. hydraulic fluid).The weights of all operator items are not included.

B. Operator ItemsThese items include:- Unusable fuel,- Oil for engines, IDG and APU,- Water for galleys and lavatories,- Chemical fluids for waste tanks,- Aircraft documents and tool kits,- Passenger seats and life vests,- Galley structures and fixed equipment,- Catering,- Flight and cabin crew and their baggage,- Emergency equipment that includes:

09-10-02Page 1

Jul 01/09


Evacuation aids, life rafts, portable oxygen bottles and stowage boxes, extinguishers,megaphones, flash lights, axes, first aid kits, emergency radio beacons, fire resistant glovesand smoke goggles, demonstration kits, life vests for crew and children.

C. Operational Empty Weight (OEW)The OEW is the sum of the Manufacturer Empty Weight plus the operator items.

D. Dry Operating Weight (DOW)The DOW is the total weight of an aircraft prepared for a special type of operation without allthe usable fuel and traffic load.It is the sum of the OEW and the special items for the type of flight (e.g. catering, newspapers,pantry equipment etc.).

E. Recoverable Empty Weight (REW)The REW is the sum of the MEW and the weight of the different operator items which are partof the aircraft. The REW does not include the crew and their baggage or catering equipmentand supplies.

F. Net Recoverable Weight (NRW)The NRW is the REW of the aircraft without the missing or removed aircraft equipment andcomponents. It includes fuel, liquids and cargo remaining on board.The applicable recovery scenario is based on the NRW.

G. Payload (P/L)The payload is the weight of the passengers, cargo and baggage.

H. Center of Gravity (CG)The CG is the point where the aircraft can balance if it hangs at that point. It is the pointwhere the aircraft weight is applied.If more weight is put in a different point, it causes an unbalancing force which is the ”moment”.In case of recovery action, the position of CG has to stay within certain predefined limits toensure aircraft general stability

J. Reference Chord (RC) or Mean Aerodynamic Chord (MAC)Usually the position of the CG is defined by a percentage of Reference Chord (%RC).The Reference Chord is a reference line used in the design of the wing. Its position relative tothe wing and fuselage is accurately known. It represents the variation of position of the CG,according to the weight and balance management or other parameters. The normal position ofthe CG is considered at 25%RC. The position and dimensions of this reference are mentioned inTASK 03-00-00-558-801-A01. These dimensions are specially dedicated to an aircraft type.

K. Maximum Design Landing Weight (MLW)The MLW is the maximum permitted weight at which the aircraft can land.

L. Maximum Ramp Weight (MRW) / Maximum Taxi Weight (MTW)The MRW / MTW is the maximum permitted weight for ground maneuvers, that include taxiand run-up fuel.

09-10-02Page 2

Jul 01/09


M. Maximum Takeoff Weight (MTOW)The MTOW is the maximum permitted weight when the brakes are released for takeoff, or atthe start of the takeoff roll.

N. Maximum Zero Fuel Weight (MZFW)The MZFW is the maximum operating weight without usable fuel.

P. Actual Zero Fuel Weight (AZFW)The AZFW is the sum of the operational empty weight and payload.The AZFW must never be more the maximum design zero fuel weight (MZFW).

Q. Engineered LiftingAn engineered lifting is a lifting of the aircraft in controlled conditions, with a predefined processusing specific GSE. Before this procedure is started, it is necessary to do:- An accurate analysis of the requirements- An accurate engineering planning and a risk/hazard assessment- A lifting procedure approved by the local authority regulations.

09-10-02Page 3

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-02-003-A01

Abbreviations

1. List of AbbreviationsThe abbreviations that follow are used in the ARM.

A/C Aircraft

AC Aircraft Characteristics for Airport Planning

AD Aircraft DatumAFRP Aramid Fiber Reinforced PlasticAMM Aircraft Maintenance ManualAPU Auxiliary Power Unit

ARM Aircraft Recovery Manual

ARWG Aircraft Recovery Working Group

ATA Air Transport Association of America

AZFW Actual Zero Fuel Weight

CBR California Bearing Ratio

CFRP Carbon Fiber Reinforced PlasticCG Center of Gravity

CL Center LineCLS Cargo Loading System

CLSM Cargo Loading System Manual

CRC Crew Rest Compartment

CTR CenterDBP Drawbar PullDOW Dry Operating Weight

ECAM Electronic Centralized Aircraft Monitoring

EIS Electronic Instrument System

EWH External Wiring Harness

FDL Fuselage Datum Line

FQI Fuel Quantity Indicator

FR FrameFWD ForwardGFRP Glass Fiber Reinforced PlasticGPU Ground Power UnitIATA International Air Transport Association

IATP International Airline Technical PoolICAO International Civil Aviation Organization

09-10-02Page 4

Jul 01/09


IDG Integrated Drive Generator

INBD InboardINR InnerIPC Illustrated Parts Catalog

L/G Landing Gear

LDG Landing

LDMCR Lower Deck Mobile Crew RestLGCIU Landing Gear Control and Interface Unit

LH Left HandLRE List of Radioactive and Hazardous Elements

ManualMCDU Multipurpose Control & Display Unit

MEW Manufacturer’s Empty Weight

MFP Maintenance Facility Planning Manual

MID MiddleMLG Main Landing Gear

MLW Maximum Design Landing Weight

MMI Manual Magnetic Indicator

MRW Maximum Ramp Weight

MSN Manufacturer’s Serial NumberMTOW Maximum Design Take Off Weight

MTW Maximum Taxi Weight

MZFW Maximum Design Zero Fuel Weight

NAS Navy and Army Standard

NLG Nose Landing Gear

NRW Net Recoverable Weight

NWS Nose Wheel Steering

OEW Operating Empty Weight

OUTBD Outboard

P/BSW Push Button Switch

P/L Payload

PAX Passenger

PSU Passenger Service Unit

RC Reference ChordRCT Rear Center TankREW Recoverable Empty Weight

RH Right Hand

SRM Structural Repair Manual

09-10-02Page 5

Jul 01/09


STA StationSTGR Stringer

T TrimTBD To Be Define / Determined

TBIL To Be Issued LaterTEM Illustrated Tool and Equipment Manual

THS Trimmable Horizontal StabilizerTK TankTPIS Tire Pressure Indicating System

ULD Unit Load DeviceW&B Weight and Balance

WBM Weight and Balance Manual

XFR Transfer

List of Abbreviations

TABLE 1

09-10-02Page 6

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-02-002-A01

Aircraft Reference Axes

1. DefinitionsSee FIGURE 09-10-02-991-001-A.

A. AD (Aircraft Datum)Vertical plane (equation Y=0). It is shown as a line on XY and YZ drawings.

B. FD (Fuselage Datum)Horizontal plane (equation Z=0). It is shown as a line (FDL) on XZ and YZ drawings.

C. Fuselage Datum Line (FDL)View of FD plan on 2D drawings (XZ and YZ planes).

D. Center Line (C/L)Intersection of AD and FD planes.

E. H-armHorizontal arm from X=0 in length unit.

F. Y-armLateral arm Y=0 in length unit.

G. Z-armVertical arm Z=0 in length unit.

09-10-02Page 7

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

+Z

0

+Y

AD

+X

7.000 m(275.59 in)

N_AR_091002_1_0010101_01_00

2.540 m(100 in)

Aircraft Reference AxesGeneral

FIGURE-09-10-02-991-001-A01

09-10-02Page 8

Jul 01/09


09-10-03 AIRCRAFT DIMENSIONS

**ON A/C A318-100

DESC 09-10-03-001-A01

General

1. This chapter gives the main dimensions of the A318 aircraft:- See FIGURE 09-10-03-991-001-A and FIGURE 09-10-03-991-002-A.

09-10-03Page 1

Jul 01/09


**ON A/C A318-100

5.07 m

11.51 m

7.59 m

34.10 m

12.45 m

10.25 m

(37.76 ft)

(12.93 ft)

(16.63 ft) (32.62 ft)

(111.88 ft)

31.45 m(103.18 ft)

(40.85 ft)

30.96 m(101.57 ft)

6.62 m(21.72 ft)

NOTE: RELATED TO AIRCRAFT ATTITUDE AND WEIGHTN_AR_091003_1_0010101_01_01

Aircraft Dimensions - A318Side and Front View

FIGURE-09-10-03-991-001-A01

09-10-03Page 2

Jul 01/09


**ON A/C A318-100

30.64 m(100.52 ft)

A

A = CFM56: 8.97 m (29.43 ft)PW6000: 8.85 m (29.0 ft)

N_AR_091003_1_0020101_01_01

Aircraft Dimensions - A318Top View

FIGURE-09-10-03-991-002-A01

09-10-03Page 3

Jul 01/09


**ON A/C A319-100

DESC 09-10-03-001-B01

General


09-10-03Page 4

Jul 01/09


**ON A/C A319-100

12.45 m

5.07 m(16.63 ft)

11.04 m(36.22 ft)

34.10 m(111.88 ft)

(40.85 ft)

(12.93 ft)

(37.76 ft)

7.59 m

11.51 m

OPTIONAL

33.11 m(108.63 ft)

33.84 m(111.02 ft)

5.87 m(19.26 ft)



FIGURE-09-10-03-991-003-A01

09-10-03Page 5

Jul 01/09


**ON A/C A319-100

33.024 m(108.35 ft)

A

A = CFM56: 9.76 m (32.02 ft)IAE V2500: 9.60 m (31.5 ft)

N_AR_091003_1_0040101_01_01


FIGURE-09-10-03-991-004-A01

09-10-03Page 6

Jul 01/09


**ON A/C A320-100 A320-200

DESC 09-10-03-001-C01

General

1. This chapter gives the main dimensions of the A320 aircraft:- SeeFIGURE 09-10-03-991-005-AFIGURE 09-10-03-991-005-B and FIGURE 09-10-03-991-006-A.

09-10-03Page 7

Jul 01/09


**ON A/C A320-100

7.59 m(12.93 ft)

12.45 m(40.85 ft)

33.91 m(111.25 ft)

36.84 m(120.87 ft)

5.07 m(16.63 ft)

12.63 m(41.44 ft)

37.57 m(123.36 ft)

NOTE: RELATED TO AIRCRAFT ATTITUDE AND WEIGHT

5.87 m(19.26 ft)

11.51 m(37.76 ft)

N_AR_091003_1_0050101_01_01

Aircraft Dimensions - A320-100Side and Front View

FIGURE-09-10-03-991-005-A01

09-10-03Page 8

Jul 01/09


**ON A/C A320-200

7.59 m(12.93 ft)

12.45 m(40.85 ft)

34.10 m(111.88 ft)

36.84 m(120.87 ft)

5.07 m(16.63 ft)

12.64 m(41.47 ft)

37.57 m(123.36 ft)

NOTE: RELATED TO AIRCRAFT ATTITUDE AND WEIGHT

11.51 m(37.76 ft)

5.87 m(19.26 ft)

N_AR_091003_1_0050201_01_01

Aircraft Dimensions - A320-200Side and Front View

FIGURE-09-10-03-991-005-B01

09-10-03Page 9

Jul 01/09


**ON A/C A320-100 A320-200

37.57 m(123.26 ft)

A = CFM56: 11.36 m (37.27 ft)IAE V2500: 11.20 m (36.75 ft)

A

N_AR_091003_1_0060101_01_01

Aircraft Dimensions - A320-100/-200Top View

FIGURE-09-10-03-991-006-A01

09-10-03Page 10

Jul 01/09


**ON A/C A321-100 A321-200

DESC 09-10-03-001-D01

General


09-10-03Page 11

Jul 01/09


**ON A/C A321-100 A321-200

43.69 m(143.34 ft)

5.87 m(19.26 ft)

5.07 m(16.63 ft)

16.91 m(55.48 ft)

44.51 m(146.03 ft)

7.59 m(12.93 ft)11.51 m(37.76 ft)

12.45 m(40.85 ft)

34.10 m(111.88 ft)



FIGURE-09-10-03-991-007-A01

09-10-03Page 12

Jul 01/09


**ON A/C A321-100 A321-200

A

44.51 m(146.03 ft)

A = CFM56: 15.63 m (51.28 ft)IAE V2500: 15.47 m (50.75 ft)

N_AR_091003_1_0080101_01_01


FIGURE-09-10-03-991-008-A01

09-10-03Page 13

Jul 01/09


09-10-04 AIRCRAFT STRUCTURAL SECTIONS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-04-001-A01

General

1. Sections and ComponentsFor the different structural sections and components of the aircraft see FIGURE 09-10-04-991-001-AFIGURE 09-10-04-991-001-BFIGURE 09-10-04-991-001-CFIGURE 09-10-04-991-001-D.

09-10-04Page 1

Jul 01/09


**ON A/C A318-100

11/1

2

13/1

4

5121

41 42

5223 24

2229

28

27

2526

16/1

7

18

3132

19.1

36

1935

15

N_AR_091004_1_0010101_01_01

Aircraft Structural SectionsStructure Sections and Components - A318 (Sheet 1 of 2)

FIGURE-09-10-04-991-001-A01

09-10-04Page 2

Jul 01/09


**ON A/C A318-100

SECTION DESIGNATION

11/12

REAR FUSELAGE

13/14

REAR FUSELAGE

15

CONE/REAR FUSELAGE

16/17

CONE/REAR FUSELAGE

18

CENTER WING

19

OUTER WING

19.1

LEADING EDGES

21

LEADING EDGES

22

SPOILERS

23

INBOARD FLAP

24

OUTBOARD FLAP

25

AILERON

26

WING−TIP

27

VERTICAL STABILIZER

28

RUDDER

29

HORIZONTAL STABILIZER

31

ELEVATOR

32

PYLONS

35

NACELLE SECTION

36

NOSE GEAR AND DOORS

41

MAIN GEAR AND DOORS

42

NOSE FORWARD FUSELAGE

51

FORWARD FUSELAGE

52

CENTER FUSELAGE

N_AR_091004_1_0010103_01_00


FIGURE-09-10-04-991-001-A01

09-10-04Page 3

Jul 01/09


**ON A/C A319-100

11/1

2

13/1

4

51

5223 24

2229

28

27

2526

16/1

7

18

3132

19.1

36

1935

15

21

41 42

N_AR_091004_1_0010201_01_01


FIGURE-09-10-04-991-001-B01

09-10-04Page 4

Jul 01/09


**ON A/C A319-100

N_AR_091004_1_0010202_01_00

SECTION DESIGNATION

11/12

REAR FUSELAGE

13/14

REAR FUSELAGE

15

CONE/REAR FUSELAGE

16/17

CONE/REAR FUSELAGE

18

CENTER WING

19

OUTER WING

19.1

LEADING EDGES

21

LEADING EDGES

22

SPOILERS

23

INBOARD FLAP

24

OUTBOARD FLAP

25

AILERON

26

WING−TIP

27

VERTICAL STABILIZER

28

RUDDER

29


31

ELEVATOR

32

PYLONS

35

NACELLE SECTION

36

NOSE GEAR AND DOORS

41

MAIN GEAR AND DOORS

42


51

FORWARD FUSELAGE

52

CENTER FUSELAGE


FIGURE-09-10-04-991-001-B01

09-10-04Page 5

Jul 01/09


**ON A/C A320-100 A320-200

11/1

2

13/1

4

51

5223 24

2229

28

27

2526

16/1

7

18

3132

19.1

36

1935

15

21

41 42

N_AR_091004_1_0010301_01_01


FIGURE-09-10-04-991-001-C01

09-10-04Page 6

Jul 01/09


**ON A/C A320-100 A320-200

SECTION DESIGNATION

11/12

REAR FUSELAGE

13/14

REAR FUSELAGE

15

CONE/REAR FUSELAGE

16/17

CONE/REAR FUSELAGE

18

CENTER WING

19

OUTER WING

19.1

21

22

SPOILERS

23/24

INBOARD FLAP

OUTBOARD FLAP

25

AILERON

26

WING−TIP

27

VERTICAL STABILIZER

28

RUDDER

29


31

ELEVATOR

32

PYLONS

35

NACELLE SECTION

36

NOSE GEAR AND DOORS

41

MAIN GEAR AND DOORS

42


51

FORWARD FUSELAGE

52

CENTER FUSELAGE

FIXED AND MOVINGLEADING EDGES

N_AR_091004_1_0010302_01_00


FIGURE-09-10-04-991-001-C01

09-10-04Page 7

Jul 01/09


**ON A/C A321-100 A321-200

51

11/1

2

13/1

4

14A

21

42

15

16A

16/1

7

18

19

19.1

3635

3132

4152

23 2422

29

28

25

26

27

N_AR_091004_1_0010401_01_01


FIGURE-09-10-04-991-001-D01

09-10-04Page 8

Jul 01/09


**ON A/C A321-100 A321-200

N_AR_091004_1_0010402_01_00

REAR FUSELAGE

15

REAR FUSELAGE

16A

CONE/REAR FUSELAGE

16/17

CONE/REAR FUSELAGE

18

CENTER WING

19

OUTER WING

19.1

LEADING EDGES

21

LEADING EDGES

22

SPOILERS

23

INBOARD FLAP

24

OUTBOARD FLAP

25

AILERON

26

WING−TIP

27

VERTICAL STABILIZER

28

RUDDER

29


31

ELEVATOR

32

PYLONS

35

NACELLE SECTION

36

NOSE GEAR AND DOORS

41

MAIN GEAR AND DOORS

42

51

CENTER FUSELAGE

52

REAR FUSELAGE

SECTION DESIGNATION

11/12

13/14

14A


FORWARD FUSELAGE

FORWARD FUSELAGE


FIGURE-09-10-04-991-001-D01

09-10-04Page 9

Jul 01/09


09-10-05 COMPOSITE MATERIALS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-05-001-A01

General

1. Types of MaterialSome components and sections of the aircraft structure are made from composite materials seeFIGURE 09-10-05-991-001-AFIGURE 09-10-05-991-001-BFIGURE 09-10-05-991-001-CFIGURE09-10-05-991-001-D. The types of materials used are:- Carbon Fiber Reinforced Plastic (CFRP).- Glass Fiber Reinforced Plastic (GFRP).- Quartz Fiber Reinforced Plastic (QFRP).

09-10-05Page 1

Jul 01/09


**ON A/C A318-100

N_AR_091005_1_0010101_01_00

CARBON FIBER REINFORCED PLASTIC (CFRP)

GLASS FIBER REINFORCED PLASTIC (GFRP)

ARAMID FIBER REINFORCED PLASTIC (AFRP)

Composite Materials - A318Location of Composite materials on the External surfaces of the Aircraft

FIGURE-09-10-05-991-001-A01

09-10-05Page 2

Jul 01/09


**ON A/C A319-100

N_AR_091005_1_0010201_01_00





FIGURE-09-10-05-991-001-B01

09-10-05Page 3

Jul 01/09


**ON A/C A320-100 A320-200

N_AR_091005_1_0010301_01_00





FIGURE-09-10-05-991-001-C01

09-10-05Page 4

Jul 01/09


**ON A/C A321-100 A321-200

N_AR_091005_1_0010401_01_00





FIGURE-09-10-05-991-001-D01

09-10-05Page 5

Jul 01/09


09-10-06 FUSELAGE FRAMES AND H-ARM TABLE

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-06-001-A01

General

1. This chapter gives the H-Arm of each frame.The H-arm is used to calculate the CG. The H-arm is the length of the lever arm from the datumpoint to the specific station. The datum point is at 2540 mm (100 in) forward of the radome.

09-10-06Page 1

Jul 01/09


**ON A/C A318-100

2.540m(100.00in)

X = 0

CL

FR2FR4

FR6FR8FR10

FR1

FR3

FR5FR7

FR9FR11

FR12FR14

FR16FR18

FR13 FR15

FR17

FR19

FR

NOSE

1

2

3

m (in)

2.540 (100.00)

H−ARMFR

11

12

14

15

13

m (in)

5.794 (228.10)

6.053 (238.30)

6.311 (248.46)

6.570 (258.64)

6.828 (268.82)

16

H−ARM

7.087 (279.00)

FR

17

18

19

20

23

m (in)

7.318 (288.11)

7.599 (299.17)

7.830 (308.27)

8.077 (318.00)

8.966 (353.00)

H−ARM

3.500 (137.80)

3.850 (151.57)

4.090 (161.02)

4.330 (170.47)

4.546 (178.98)

4.762 (187.48)

4.967 (195.55)

5.194 (204.49)

24 9.500 (374.00)

25 10.033 (395.00)

9 5.394 (212.36)

26 10.566 (416.00)

28

29

30

34

35

11.100 (437.00)

11.633 (458.00)

11.913 (469.00)

12.446 (490.00)

12.979 (511.00)

4

5

6

7

8

FR

37

m (in)

14.021 (552.00)

H−ARM

38 14.300 (563.00)

39 14.867 (585.32)

40 15.147 (596.32)

41 15.714 (618.64)

42 16.307 (642.00)

21 8.433 (332.00)

10 5.594 (220.24)

36 13.513 (532.00)

FR20FR22

FR24 FR24A

FR21

FR25

FR26FR28

FR29

FR30FR34

FR35

FR36

FR37

FR38

FR39

FR40

FR41

FR42

22 8.700 (342.50)

24A 9.766 (384.50)

N_AR_091006_1_0010102_01_00

Fuselage Frames and H-arm - A318Frame 1 to 42 (Sheet 1 of 2)

FIGURE-09-10-06-991-001-A01

09-10-06Page 2

Jul 01/09


**ON A/C A318-100

FR42 FR44 FR46

FR54

FR43FR45

FR47

FR55

FR56

FR57

FR57A

FR58

FR59

FR60

FR61

FR62

FR63

FR64

FR65

FR66

FR67

FR68

FR69

FR70

FR71

FR72

FR73

FR74

FR75

FR76

FR77

FR78

FR79

FR80

FR81

FR82

FR83

FR84

FR85

FR86

FR87

FR

42

43

44

45

m (in)

16.307 (642.00)

H−ARMFR

60

61

63

64

62

m (in)

22.174 (873.00)

22.708 (894.00)

23.241 (915.00)

23.774 (936.00)

24.308 (957.00)

65

H−ARM

24.892 (980.00)

FR

66

67

68

69

72

m (in)

25.456 (1002.21)

25.953 (1021.77)

26.450 (1041.33)

26.975 (1062.02)

28.385 (1117.52)

H−ARM

16.840 (663.00)

17.374 (684.00)

17.907 (705.00)

18.440 (726.00)

18.974 (747.00)

19.507 (768.00)

20.041 (789.00)

20.574 (810.00)

73 28.785 (1133.27)

74 29.185 (1149.02)

57A 20.841 (820.50)

75 29.598 (1165.28)

76 30.011 (1181.54)

77

78

79

80

81

30.424 (1197.80)

30.536 (1202.21)

30.855 (1214.77)

31.174 (1227.33)

31.544 (1241.89)

46

47/54

55

56

57

FR

84

m (in)

32.824 (1292.29)

H−ARM

85 33.279 (1310.20)

86 33.734 (1328.11)

87 33.992 (1338.28)

70 27.534 (1084.02)

58 21.107 (531.00)

82 31.914 (1256.46)

71 27.934 (1099.77)

59 21.641 (852.00)

83 32.369 (1274.37)

CL

N_AR_091006_1_0010103_01_00

Fuselage Frames and H-arm - A318Frame 42 to 87 (Sheet 2 of 2)FIGURE-09-10-06-991-001-A01

09-10-06Page 3

Jul 01/09


**ON A/C A319-100

N_AR_091006_1_0010201_01_00

2.540m(100.00in)

X = 0

CL

FR1

FR2

FR3

FR4

FR5

FR6

FR7

FR8

FR9

FR10

FR11

FR12

FR13

FR14

FR15

FR16

FR17

FR18

FR19

FR20

FR

NOSE

1

2

3

m (in)

2.540 (100.00)

H−ARMFR

11

12

14

15

13

m (in)

5.794 (228.11)

6.052 (238.27)

6.311 (248.46)

6.570 (258.64)

6.828 (268.82)

16

H−ARM

7.087 (279.00)

FR

17

18

19

20

23

m (in)

7.318 (288.11)

7.599 (299.17)

7.830 (308.27)

8.077 (318.00)

8.966 (353.00)

H−ARM

3.500 (137.80)

3.850 (151.57)

4.090 (161.02)

4.330 (170.47)

4.546 (178.98)

4.762 (187.48)

4.967 (195.55)

5.194 (204.49)

24 9.500 (374.00)

25 10.033 (395.00)

9 5.394 (212.36)

26 10.566 (416.00)

27

28

29

30

34

11.100 (437.00)

11.633 (458.00)

12.167 (479.00)

12.700 (500.00)

13.233 (521.00)

4

5

6

7

8

FR

36

m (in)

14.300 (563.00)

H−ARM

37 14.808 (583.00)

38 15.088 (594.00)

39 15.655 (616.32)

40 15.934 (627.32)

41 16.501 (649.64)

21 8.433 (332.00)10 5.594 (220.24)

35 13.767 (542.00)22 8.700 (342.50)

24A 9.766 (384.50)

FR22

FR21FR23

FR24FR24A

FR25

FR26

FR27

FR28

FR29

FR30

FR31

FR34

FR35

FR36

FR37

FR38

FR39

FR40

FR41

FR42

FR43

42 17.094 (673.00)

43 17.628 (694.00)

OPTIONAL


FIGURE-09-10-06-991-001-B01

09-10-06Page 4

Jul 01/09


**ON A/C A319-100

FR

43

44

45

46

m (in)

17.628 (694.00)

H−ARMFR

58

59

61

62

60

m (in)

23.495 (925.00)

24.028 (946.00)

24.562 (967.00)

25.095 (988.00)

25.629 (1009.00)

63

H−ARM

26.162 (1030.00)

FR

64

65

66

67

70

m (in)

26.695 (1051.00)

27.280 (1074.00)

27.861 (1096.88)

28.352 (1116.22)

29.921 (1178.00)

H−ARM

18.161 (715.00)

18.694 (736.00)

19.228 (757.00)

19.761 (778.00)

20.295 (799.00)

20.828 (820.00)

21.361 (841.00)

21.895 (862.00)

71 30.321 (1193.75)

72 30.772 (1211.50)

55A 22.162 (872.50)

73 31.172 (1227.25)

74 31.572 (1243.00)

75

76

77

78

79

31.985 (1259.26)

32.398 (1275.52)

32.811 (1291.78)

32.923 (1296.19)

33.242 (1308.75)

47/51

52

53

54

55

FR

82

m (in)

34.301 (1350.44)

H−ARM

83 34.756 (1368.36)

84 35.211 (1386.27)

85 35.666 (1404.18)

68 28.843 (1135.35)

56 22.428 (883.00)

80 33.561 (1321.31)69 29.362 (1156.00)

57 22.962 (904.00)

81 33.931 (1335.87)

FR43

FR44

FR45

FR46

FR47FR51

FR52

FR53

FR54

FR55

FR55AFR56

FR57

FR58

FR59

FR60

FR61

FR62

FR63

FR64

FR65

FR66

FR67

FR68

FR69

FR70

FR71

FR72

FR73

FR74

FR75

FR76

FR77

FR78

FR79

FR80

FR81

FR82

FR83

FR84

FR85

FR86

FR87

86 36.121 (1422.10)

87 36.379 (1432.26)

N_AR_091006_1_0010202_01_00

CL

Fuselage Frames and H-arm - A319Frame 43 to 87 (Sheet 2 of 2)FIGURE-09-10-06-991-001-B01

09-10-06Page 5

Jul 01/09


**ON A/C A320-100 A320-200

N_AR_091006_1_0010301_01_00

2.540 m(100.00 in)

X = 0

CL

FR1

FR2

FR3

FR4

FR5

FR6

FR7

FR8

FR9

FR10

FR11

FR12

FR13

FR14

FR15

FR16

FR17

FR18

FR19

FR20

FR21 FR23

FR24

FR25

FR26

FR27

FR28

FR29

FR30

FR31

FR32

FR33

FR

NOSE

1

2

3

m (in)

2.540 (100.00)

H−ARMFR

11

12

14

15

13

m (in)

5.794 (228.11)

6.052 (238.27)

6.311 (248.46)

6.570 (258.66)

6.828 (268.82)

16

H−ARM

7.087 (279.02)

FR

17

18

19

20

23

m (in)

7.318 (288.11)

7.599 (299.17)

7.830 (308.27)

8.077 (317.99)

8.966 (352.99)

H−ARM

3.500 (137.80)

3.850 (151.57)

4.090 (161.02)

4.330 (170.47)

4.546 (178.98)

4.762 (187.48)

4.967 (195.55)

5.194 (204.49)

24 9.500 (374.02)

25 10.033 (395.00)

9 5.394 (212.36)

26 10.566 (415.98)

27 11.100 (437.01)

28

29

30

31

32

11.633 (457.99)

12.167 (479.02)

12.700 (500.00)

13.233 (520.98)

13.767 (542.01)

4

5

6

7

8

FR

34

m (in)

14.834 (584.02)

H−ARM

35 15.367 (605.00)

36 15.900 (625.98)

37 16.408 (645.98)

38 16.688 (657.01)

39

40

41

42

17.255 (679.33)

17.534 (690.31)

18.101 (712.64)

18.694 (735.98)

FR34FR36

FR38FR40

FR35FR37

FR39FR41

FR42

21 8.433 (332.01)10 5.594 (220.24) 33 14.300 (562.99)


FIGURE-09-10-06-991-001-C01

09-10-06Page 6

Jul 01/09


**ON A/C A320-100 A320-200

FR

42

43

44

45

m (in)

18.694 (735.98)

H−ARMFR

54

55

57

58

56

m (in)

25.095 (987.99)

25.629 (1009.02)

26.162 (1030.00)

26.695 (1050.98)

27.229 (1072.01)

59

H−ARM

27.762 (1092.99)

FR

60

61

62

63

66

m (in)

28.296 (1114.02)

28.829 (1135.00)

29.362 (1155.98)

29.896 (1177.01)

31.577 (1243.19)

H−ARM

19.228 (757.01)

19.761 (777.99)

20.295 (799.02)

20.828 (820.00)

21.361 (840.98)

21.895 (862.01)

22.426 (882.99)

22.962 (904.02)

67 32.074 (1262.76)

68 32.571 (1282.32)

51 23.495 (925.00)

69 33.096 (1302.99)

70 33.655 (1325.00)

71

72

73

74

75

34.055 (1340.75)

34.506 (1358.50)

34.906 (1374.25)

35.306 (1390.00)

35.719 (1406.26)

46

47

48

49

50

FR

78

m (in)

36.657 (1443.19)

H−ARM

79 36.976 (1455.75)

80 37.295 (1468.31)

81 37.665 (1482.87)

82 38.035 (1497.44)

83

84

85

86

38.490 (1515.35)

38.945 (1533.27)

39.400 (1551.18)

39.855 (1569.09)

64 30.429 (1197.99)52 24.028 (945.98) 76 36.132 (1422.52)

FR42FR44

FR46FR48

FR50FR52

FR54FR56

FR43FR45

FR47FR49

FR51FR53

FR55FR57

FR58FR60

FR62

FR59FR61

87 40.113 (1579.25)

65 31.013 (1220.98)53 24.562 (967.01) 77 36.545 (1438.78)

FR64

FR63

FR66FR68

FR70FR72

FR74FR76

FR78FR80

FR65FR67

FR69FR71

FR73FR75

FR77FR79

FR81FR83

FR85

FR82FR84

FR86

FR87

N_AR_091006_1_0010302_01_00

CL

Fuselage Frames and H-arm - A320Frame 42 to 87 (Sheet 2 of 2)FIGURE-09-10-06-991-001-C01

09-10-06Page 7

Jul 01/09


**ON A/C A321-100 A321-200

N_AR_091006_1_0010401_01_00

FR35

FR34

FR33

FR32

FR31

FR30

FR29

FR28

FR27

FR26

FR25

FR24FR20

FR19

FR18

FR17

FR16

FR15

FR14

FR13

FR12

FR11

FR10

FR9

FR8

FR7

FR6

FR5

FR4

FR3

FR2

FR1

FR21

FR23

FR

NOSE

1

2

3

4

6

7

5

m (in)

2.540 (100.00)

8

H−ARMFR

12

13

15

16

14

m (in)

6.052 (238.27)

6.311 (248.46)

6.570 (258.66)

6.828 (268.82)

7.087 (279.02)

17

H−ARM

7.318 (288.11)

FR

18

19

20

21

23

25

24

m (in)

7.599 (299.17)

7.830 (308.27)

8.077 (317.99)

8.433 (332.01)

8.966 (352.99)

9.500 (374.02)

10.033 (395.00)

H−ARM

3.500 (137.80)

3.850 (151.57)

4.090 (161.02)

4.330 (170.47)

4.546 (178.98)

4.762 (187.48)

4.967 (195.55)

5.194 (204.49)

26 10.566 (415.98)

27 11.100 (437.01)

9

10

11

5.394 (212.36)

5.594 (220.24)

5.794 (228.11)

28 11.633 (457.99)

29 12.167 (479.02)

30

31

32

33

34

35

12.700 (500.00)

13.233 (520.98)

13.767 (542.01)

14.300 (562.99)

14.834 (584.02)

15.367 (605.00)

2.540 m(100.00 in)

X = 0

CL


FIGURE-09-10-06-991-001-D01

09-10-06Page 8

Jul 01/09


**ON A/C A321-100 A321-200

FR

3535

135

235

3

m (in)

15.367 (605.00)

H−ARMFR

39

40

42

43

41

m (in)

21.522 (847.32)

21.801 (858.31)

22.368 (880.63)

22.962 (904.02)

23.495 (925.00)

44

H−ARM

24.025 (945.87)

FR

45

46

4747

147

2

474

473

m (in)

24.562 (967.01)

25.095 (987.01)

25.629 (1009.02)

26.162 (1030.00)

26.695 (1050.98)

27.229 (1072.01)

27.762 (1092.99)

H−ARM

15.900 (625.98)

16.433 (646.97)

16.967 (667.99)

17.501 (689.02)

18.034 (710.00)

18.567 (730.98)

19.101 (752.01)

19.634 (772.99)

475 28.296 (1114.02)

48 28.829 (1135.00)

36

37

38

20.168 (794.02)

20.676 (814.02)

20.955 (825.00)

49 29.362 (1155.98)

50 29.896 (1177.01)

51

52

53

54

55

56

30.429 (1197.99)

30.963 (1219.02)

31.496 (1240.00)

32.029 (1260.98)

32.563 (1282.01)

33.096 (1302.99)

354

355

356

357

358

FR35

FR35

FR35

FR35

FR35

FR35

FR35

FR36

FR37

FR38

FR39

FR40

FR41

FR42

FR43

FR44 FR46

FR47

FR47FR47

FR47

FR47

FR47

FR48

FR49

FR50

FR51

FR52

FR53

FR54

FR55

FR56

FR35

FR35

1

2

3

4

5

6

7

8

1

FR45

2

3

4

5

N_AR_091006_1_0010402_01_00

CL

Fuselage Frames and H-arm - A321Frame 35 to 56 (Sheet 2 of 3)FIGURE-09-10-06-991-001-D01

09-10-06Page 9

Jul 01/09


**ON A/C A321-100 A321-200

FR

56

57

58

59

m (in)

33.096 (1302.99)

H−ARMFR

67

68

70

71

69

m (in)

39.008 (1535.75)

39.505 (1555.32)

40.030 (1575.99)

40.589 (1597.99)

40.989 (1613.74)

72

H−ARM

41.440 (1631.50)

FR

73

74

75

76

77

78

m (in)

41.840 (1647.24)

42.240 (1662.99)

42.653 (1679.25)

43.066 (1695.51)

43.479 (1711.77)

43.591 (1716.18)

H−ARM

33.629 (1323.98)

34.163 (1345.00)

34.696 (1365.98)

35.230 (1387.01)

35.763 (1407.99)

36.297 (1429.02)

36.830 (1450.00)

37.363 (1470.99)

79 43.910 (1728.74)

80 44.229 (1741.30)

65

66

37.948 (1494.02)

38.511 (1516.18)

81 44.599 (1755.87)

82 44.969 (1770.43)

83

84

85

86

87

45.424 (1788.35)

45.879 (1806.26)

46.334 (1824.17)

46.789 (1842.09)

47.047 (1852.25)

60

61

62

63

64

FR56

FR57

FR58

FR59

FR60

FR61

FR62

FR63

FR64

FR65

FR66

FR67

FR68

FR69

FR70

FR71

FR72

FR73

FR74

FR75

FR76

FR77

FR78

FR79

FR80

FR81

FR82

FR83

FR84

FR85

FR86

FR87CL

N_AR_091006_1_0010403_01_00

Fuselage Frames and H-arm - A321Frame 56 to 87 (Sheet 3 of 3)FIGURE-09-10-06-991-001-D01

09-10-06Page 10

Jul 01/09


09-10-08 WING RIBS AND STATIONS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-08-001-A01

Wing Ribs and Stations

1. GeneralThis chapter gives the Wing Ribs and stations, see FIGURE 09-10-08-991-001-AFIGURE09-10-08-991-001-BThe position of each Wing Rib is identified by a station (STA). All measurements are:- At 90 degrees to Rib 1- Measured between Rib 1 and the intersection of each rib datum with the Front Spar datum at

the lower outside skin surface.

NOTE : The stations are given in centimeters with no conversion

09-10-08Page 1

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200

N_AR_091008_1_0010101_01_00

A

1868 mm(73.543 in)

STA0

STA70

STA141STA196

STA251

STA306

STA360

STA376

STA407

STA486

STA551

STA613

STA670

STA1120STA1166

STA1228

STA1287

STA1346

STA1406

RIB2

RIB1

RIB3RIB4

RIB5

RIB6

RIB7

RIB6B

RIB8RIB9

RIB10

STA1446

RIB11

RIB12

RIB13

RIB27

LH SHOWNRH SYMMETRICAL

NOTE : ALL STA NUMBERS ARE GIVEN IN cmSTATION REFERENCES GIVEN, APPLYTO THE INTERSECTION OF THE RIBDATUMS WITH THE FRONT SPAR DATUMAT THE OUTSIDE SKIN SURFACE.

A

AD

STA732

STA779STA827

STA874STA924STA970STA1020

STA1073

RIB14RIB15

RIB16RIB17RIB18

RIB20RIB21

RIB19

RIB22

RIB23

RIB24

RIB25

RIB26

WY

A

Wing Ribs and StationsA318/A319/A320

FIGURE-09-10-08-991-001-A01

09-10-08Page 2

Jul 01/09


**ON A/C A321-100 A321-200

1868 mm(73.543 in)

A

STA0

STA70

STA141STA196

STA251

STA306

STA360

STA376

STA407

STA486

STA551

STA613

STA670

STA1120STA1166

STA1228

STA1287

STA1346

STA1406

RIB2

RIB1

RIB3RIB4

RIB5RIB6

RIB7

RIB6B

RIB8RIB9RIB10

STA1446

RIB11

RIB12

RIB13

RIB27


NOTE : ALL STA NUMBERS ARE GIVEN IN cmSTATION REFERENCES GIVEN, APPLYTO THE INTERSECTION OF THE RIBDATUMS WITH THE FRONT SPAR DATUMAT THE OUTSIDE SKIN SURFACE.

A

AD

STA732

STA779STA827

STA874STA924STA970STA1020

STA1073

RIB14RIB15

RIB16RIB17

RIB18

RIB20RIB21

RIB19

RIB22

RIB23

RIB24

RIB25

RIB26

A

WY

N_AR_091008_1_0010201_01_00

Wing Ribs and StationsA321

FIGURE-09-10-08-991-001-B01

09-10-08Page 3

Jul 01/09


09-10-09 HORIZONTAL STABILIZERS RIBS AND STATIONS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-09-001-A01

General

1. This chapter gives the horizontal stabilizer ribs and stations (see FIGURE 09-10-09-991-001-A).The position of each horizontal stabilizer rib is identified with a station (STA) which is the distancebetween the rib and RIB1 datum.

NOTE : The stations are given in centimeters with no conversion.

09-10-09Page 1

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

A

STA601

STA589

STA527

STA466

STA404

STA342

STA297

STA271

STA227

STA181

STA131

STA69

CL

STA0

RIB14

RIB13

RIB12

RIB11

RIB10

RIB9

RIB8

RIB7

RIB6

RIB5

RIB3 RIB4

RIB2 RIB1


UPPER SURFACE

NOTE:ALL STA NUMBERS ARE GIVEN IN cm.

A

STA82

N_AR_091009_1_0010101_01_00

Horizontal StabilizerRibs and Stations

FIGURE-09-10-09-991-001-A01

09-10-09Page 2

Jul 01/09


09-10-10 DOOR SIZES AND LOCATIONS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-10-001-A01

General

1. This chapter gives data related to the aircraft doors. There are different types of door installed on theaircraft. The different doors are given in the sections that follow:- For the passenger/crew doors and emergency exit doors, see DESC 09-10-10-002-A01.- For the cargo compartment doors, see DESC 09-10-10-003-A01.- For the nose landing gear doors, see DESC 09-10-10-004-A01.- For the main landing gear doors, see DESC 09-10-10-005-A01.- For the APU doors, see DESC 09-10-10-006-A01.

09-10-10Page 1

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-10-002-A01

Passenger/Crew Doors and Emergency Exit Doors

1. GeneralThis section gives data related to the identification, location and clearances of the passenger/crewand emergency exit doors.

2. LocationFor the location of the passenger/crew and emergency exit doors see FIGURE 09-10-10-991-001-AFIGURE 09-10-10-991-001-BFIGURE 09-10-10-991-001-CFIGURE 09-10-10-991-001-D.

3. ClearancesFor the clearances of these doors:- FWD Pax/Crew doors, see FIGURE 09-10-10-991-002-A.- AFT Pax/Crew doors, see FIGURE 09-10-10-991-004-A.- Emergency Exits, see FIGURE 09-10-10-991-003-AFIGURE 09-10-10-991-003-BFIGURE

09-10-10-991-003-CFIGURE 09-10-10-991-003-D.

09-10-10Page 2

Jul 01/09


**ON A/C A318-100

N_A

R_0

9101

0_1_

0010

101_

01_0

0

5.02

m(1

6.5

ft)

12.8

9 m

(42.

29 ft

)

23.5

2 m

(77.

17 ft

)

FO

RW

AR

DP

AS

SE

NG

ER

/CR

EW

DO

OR

RE

AR

PA

SS

EN

GE

R/C

RE

W D

OO

RE

ME

RG

EN

CY

EX

IT

Passenger/Crew Doors and Emergency ExitsLocation - A318

FIGURE-09-10-10-991-001-A01

09-10-10Page 3

Jul 01/09


**ON A/C A319-100

N_A

R_0

9101

0_1_

0010

201_

01_0

0

5.02

m(1

6.5

ft)

12.8

3 m

(42.

1 ft)

13.6

8 m

(44.

9 ft)

25.9

1 m

(85

ft)

FO

RW

AR

DP

AS

SE

NG

ER

/CR

EW

DO

OR

RE

AR

PA

SS

EN

GE

R/C

RE

W D

OO

R

EM

ER

GE

NC

Y E

XIT

EM

ER

GE

NC

Y E

XIT

(OP

TIO

NA

L)


FIGURE-09-10-10-991-001-B01

09-10-10Page 4

Jul 01/09


**ON A/C A320-100 A320-200

N_A

R_0

9101

0_1_

0010

301_

01_0

0

5.02

m(1

6.5

ft)

14.4

3 m

(47.

34 ft

)

15.2

8 m

(50.

13 ft

)

29.6

4 m

(97.

24 ft

)

FO

RW

AR

DP

AS

SE

NG

ER

/CR

EW

DO

OR

RE

AR

PA

SS

EN

GE

R/C

RE

W D

OO

RE

ME

RG

EN

CY

EX

IT


FIGURE-09-10-10-991-001-C01

09-10-10Page 5

Jul 01/09


**ON A/C A321-100 A321-200

5.02

m(1

6.5

ft)

13.8

4 m

(45.

41 ft

)

27.4

9 m

(81.

33 ft

)

36.5

7 m

(119

.98

ft)

N_A

R_0

9101

0_1_

0010

401_

01_0

0

FO

RW

AR

DP

AS

SE

NG

ER

/CR

EW

DO

OR

RE

AR

PA

SS

EN

GE

R/C

RE

W D

OO

RE

ME

RG

EN

CY

EX

IT


FIGURE-09-10-10-991-001-D01

09-10-10Page 6

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

CL

2.54 m(100 in)

0.51 m(20.08 in)

CRITICALCLEARANCE LIMIT

0.48 m(18.9 in)

SEE 09−10−11

1.85 m(72.83 in)

0.03 m(1.18 in)

1.80 m(70.87 in)

0.81 m(31.89 in)

2.375 m(93.5 in)

CL

N_AR_091010_1_0020101_01_00

CL

Forward Passenger/Crew DoorsClearances

FIGURE-09-10-10-991-002-A01

09-10-10Page 7

Jul 01/09


**ON A/C A318-100

CL

CL

N_AR_091010_1_0030101_01_00

0.56 m

A

A

(22.05 in)

SEE 09−10−11

0.12 m(4.72 in)

0.9 m(35.43 in)

0.495 m(19.49 in)

(TOP OF FLOOR)

A A

Emergency ExitsClearances - A318

FIGURE-09-10-10-991-003-A01

09-10-10Page 8

Jul 01/09


**ON A/C A319-100

CL

CL

0.50 m

A

A

(19.68 in)

SEE 09−10−11

0.12 m(4.72 in)

0.9 m(35.43 in)

0.495 m(19.49 in)

(TOP OF FLOOR)

A AN_AR_091010_1_0030201_01_00

0.85 m(33.46 in)

OPTIONAL


FIGURE-09-10-10-991-003-B01

09-10-10Page 9

Jul 01/09


**ON A/C A320-100 A320-200

CL

CL

0.50 m

A

A

(19.68 in)

SEE 09−10−11

0.12 m(4.72 in)

0.9 m(35.43 in)

0.495 m(19.49 in)

(TOP OF FLOOR)

A A

0.85 m(33.46 in)

N_AR_091010_1_0030301_01_00


FIGURE-09-10-10-991-003-C01

09-10-10Page 10

Jul 01/09


**ON A/C A321-100 A321-200

CL

CL

0.76 m(29.92 in)

0.4 m(15.75 in)

0.43 m(16.93 in)

1.73 m(68.11 in)

0.83 m(32.68 in)

0.56 m(22.05 in)

CRITICAL CLEARANCELIMIT

CRITICAL CLEARANCELIMIT

(68.11 in)

0.83 m(32.68 in)

1.73 m

CENTER OFFREE AISLE

CENTER OFFREE AISLE

A

A

CL

0.04 m(1.57 in)

0.04 m(1.57 in)

B

B

FREE AISLE0.76 m

(29.92 in)

FREE AISLE

2.38 m(93.7 in)

1.52 m(59.84 in)

2.36 m(92.91 in)

0.39 m(15.35 in)

1.85 m(72.83 in)

A A0.39 m

(15.35 in)

2.36 m(92.91 in)

1.52 m(59.84 in)

(TOP OF FLOOR)

B B

0.56 m(22.05 in)

N_AR_091010_1_0030401_01_00


FIGURE-09-10-10-991-003-D01

09-10-10Page 11

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_091010_1_0040101_01_00

CRITICALCLEARANCELIMIT

0.58 m(22.83 in)

1.79 m(70.47 in)

0.81 m(31.89 in)

A

A

SEE 09−10−11

CL

CL

CL

0.03 m(1.18 in)

1.85 m(72.83 in)

0.60 m(23.62 in)

2.44 m(96.06 in)

A A

Aft Passenger/Crew DoorsClearances

FIGURE-09-10-10-991-004-A01

09-10-10Page 12

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-10-003-A01

Cargo Compartment Doors

1. GeneralThis section gives data related to the identification, location and clearances of the different cargocompartment doors (see FIGURE 09-10-10-991-006-AFIGURE 09-10-10-991-006-BFIGURE09-10-10-991-006-CFIGURE 09-10-10-991-006-D). There are three cargo compartment doors:- The forward cargo compartment door.- The aft cargo compartment door.- The bulk cargo compartment door (A320 and A321 only).

09-10-10Page 13

Jul 01/09


**ON A/C A318-100

N_A

R_0

9101

0_1_

0060

101_

01_0

0

7.89

m(2

5.89

ft)

18.9

6 m

(62.

2 ft)

RE

AR

CA

RG

OC

OM

PA

RT

ME

NT

DO

OR

FO

RW

AR

D C

AR

GO

CO

MP

AR

TM

EN

T D

OO

R

Cargo Compartments - A318Location (Sheet 1 of 3)

FIGURE-09-10-10-991-006-A01

09-10-10Page 14

Jul 01/09


**ON A/C A318-100

1.495 m(58.858 in)

1.24 m(48.82 in)

3.945 m(151.31 in)

A

2.9 m(114.17 in)

SEE 09−10−11

A = CFM ENGINES 0.24 m (0.78 ft)PW ENGINES 0.39 m (1.27 ft)

1.33 m(52.36 in)

CL

A A

A

A

CL

N_AR_091010_1_0060102_01_01

Cargo Compartments - A318Clearances - Forward Cargo Compartment Door (Sheet 2 of 3)

FIGURE-09-10-10-991-006-A01

09-10-10Page 15

Jul 01/09


**ON A/C A318-100

1.43 m(56.3 in)

1.23 m(48.43 in)

3.945 m(155.31 in)

SEE 09−10−111.33 m(52.36 in)

A

A

1.00 m(39.37 in)

A A

CL

CL

N_AR_091010_1_0060103_01_00

Cargo Compartments - A318Clearances - Aft Cargo Compartment Door (Sheet 3 of 3)

FIGURE-09-10-10-991-006-A01

09-10-10Page 16

Jul 01/09


**ON A/C A319-100

8.16

m(2

6.77

ft)

20.5

8 m

(67.

52 ft

)

RE

AR

CA

RG

OC

OM

PA

RT

ME

NT

DO

OR

FO

RW

AR

D C

AR

GO

CO

MP

AR

TM

EN

T D

OO

R

N_A

R_0

9101

0_1_

0060

201_

01_0

0

Cargo CompartmentsLocation (Sheet 1 of 3)

FIGURE-09-10-10-991-006-B01

09-10-10Page 17

Jul 01/09


**ON A/C A319-100

1.495 m(58.86 in)

1.24 m(48.82 in)

3.945 m(151.31 in)

A

2.71 m(106.69 in)

SEE 09−10−11

A = CFM ENGINES 0.67 m (2.20 ft)IAE ENGINES 0.51 m (1.67 ft)

1.82 m(74.65 in)

CL

A A

A

A

CL

N_AR_091010_1_0060202_01_01

Cargo CompartmentsClearances - Forward Cargo Compartment Door (Sheet 2 of 3)

FIGURE-09-10-10-991-006-B01

09-10-10Page 18

Jul 01/09


**ON A/C A319-100

1.43 m(56.3 in)

1.23 m(48.43 in)

3.945 m(155.31 in)

SEE 09−10−111.82 m(71.65 in)

A

A

1.60 m(62.90 in)

A A

CL

CL

N_AR_091010_1_0060203_01_00

Cargo CompartmentsClearances - Aft Cargo Compartment Door (Sheet 3 of 3)

FIGURE-09-10-10-991-006-B01

09-10-10Page 19

Jul 01/09


**ON A/C A320-100 A320-200

8.16

m(2

6.77

ft)

22.6

9 m

(77.

44 ft

)

27.2

7 m

(89.

46 ft

)

FO

RW

AR

D C

AR

GO

CO

MP

AR

TM

EN

T D

OO

RR

EA

R C

AR

GO

CO

MP

AR

TM

EN

T D

OO

RB

ULK

CA

RG

OC

OM

PA

RT

ME

NT

DO

OR

N_A

R_0

9101

0_1_

0060

301_

01_0

0


FIGURE-09-10-10-991-006-C01

09-10-10Page 20

Jul 01/09


**ON A/C A320-100 A320-200

1.495 m(58.86 in)

1.24 m(48.82 in)

3.945 m(155.31 in)

A

2.71 m(106.69 in)

SEE 09−10−11

A = CFM ENGINE 2.27 m (7.45 ft)V2500 ENGINE 2.11 m (6.92 ft)

1.82 m(71.65 in)

CL

A A

A

A

CL

N_AR_091010_1_0060302_01_01


FIGURE-09-10-10-991-006-C01

09-10-10Page 21

Jul 01/09


**ON A/C A320-100 A320-200

1.43 m(56.3 in)

1.23 m(48.43 in)

3.945 m(155.31 in)

SEE 09−10−111.82 m(71.65 in)

A

A

2.03 m(79.92 in)

A A

CL

N_AR_091010_1_0060303_01_00

CL


FIGURE-09-10-10-991-006-C01

09-10-10Page 22

Jul 01/09


**ON A/C A320-100 A320-200

0.89 m(35.04 in)

0.77 m(30.32 in)

SEE 09−10−11

0.95 m(37.4 in)

CL

2.19 m(86.22 in)

6.10 m(240.16 in)

CL

N_AR_091010_1_0060304_01_00

A A

A

A

Cargo CompartmentsClearances - Bulk Cargo Compartment Door (Sheet 4 of 4)

FIGURE-09-10-10-991-006-C01

09-10-10Page 23

Jul 01/09


**ON A/C A321-100 A321-200

N_A

R_0

9101

0_1_

0060

401_

01_0

0

33.2

0 m

(108

.91

ft)

29.6

2 m

(97.

18 ft

)

8.16

m(2

6.77

ft)

BU

LK C

AR

GO

CO

MP

AR

TM

EN

T D

OO

RR

EA

R C

AR

GO

CO

MP

AR

TM

EN

T D

OO

RF

OR

WA

RD

CA

RG

OC

OM

PA

RT

ME

NT

DO

OR


FIGURE-09-10-10-991-006-D01

09-10-10Page 24

Jul 01/09


**ON A/C A321-100 A321-200

1.495 m(58.86 in)

1.24 m(48.82 in)

3.945 m(155.31 in)

A

2.71 m(106.69 in)

SEE 09−10−11

A = CFM ENGINE 6.54 m (21.45 ft)V2500 ENGINE 6.38 m (20.93 ft)

1.82 m(71.65 in)

CL

A

A

A A

N_AR_091010_1_0060402_01_02


FIGURE-09-10-10-991-006-D01

09-10-10Page 25

Jul 01/09


**ON A/C A321-100 A321-200

N_AR_091010_1_0060403_01_00

1.43 m(56.3 in)

1.23 m(48.43 in)

3.945 m(155.31 in)

SEE 09−10−111.82 m(71.65 in)

A

A

4.69 m(184.65 in)

A A

CL


FIGURE-09-10-10-991-006-D01

09-10-10Page 26

Jul 01/09


**ON A/C A321-100 A321-200

0.89 m(35.04 in)

0.77 m(30.32 in)

SEE 09−10−11

A

A

0.95 m(37.4 in)

CL

2.19 m(86.22 in)

8.76 m(344.88 in)

CL

N_AR_091010_1_0060404_01_00

A A

Cargo CompartmentsClearances - Bulk Cargo Compartment Door (Sheet 4 of 4)

FIGURE-09-10-10-991-006-D01

09-10-10Page 27

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-10-004-A01

Nose Landing Gear Doors

1. GeneralThis section gives data related to the location and clearances of the nose landing gear doors. Thenose landing gear has two pair of doors, the forward NLG doors and the rear NLG doors.

2. Location and ClearancesFor the location and clearances of the nose landing gear doors see FIGURE 09-10-10-991-010-A.

09-10-10Page 28

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_091010_1_0100101_01_00

0.52 m(20.47 in)

1.50 m(59.01 in)

0.50 m(19.69 in)

1.40 m(55.19 in)

01 01

0.49 m(19.29 in)

2.13 m(83.86 in)

CG = 25% RC01

Door Sizes and LocationsNose Landing Gear Doors

FIGURE-09-10-10-991-010-A01

09-10-10Page 29

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-10-005-A01

Main Landing-Gear Doors

1. GeneralThis section gives data related to the location and clearances of the main landing-gear doors. SeeFIGURE 09-10-10-991-011-AFIGURE 09-10-10-991-011-BFIGURE 09-10-10-991-011-CFIGURE09-10-10-991-011-D.

09-10-10Page 30

Jul 01/09


**ON A/C A318-100

N_AR_091010_1_0110101_01_00

1.94 m(76.38 in)

0.485 m(19.095 in)

0.207 m(8.14 in)

0.14 m(5.51 in)

84°

1.23 m(48.43 in)

01

CG = 25% RC01

1.83 m(72.1 in)

13.97 m(550 in)

CL

GROUND LINE

1.76 m(69.29 in)

CL

A


A

Location and ClearancesMain Landing Gear Doors - A318FIGURE-09-10-10-991-011-A01

09-10-10Page 31

Jul 01/09


**ON A/C A319-100

1.94 m(76.38 in)

0.485 m(19.095 in)

0.207 m(8.14 in)

0.14 m(5.51 in)

84°

1.23 m(48.43 in)

01

CG = 25% RC01

1.83 m(72.1 in)

14.76 m(581.1in)

CL

GROUND LINE

1.76 m(69.29 in)

CL

A


A

N_AR_091010_1_0110201_01_00

Location and ClearancesMain Landing Gear Doors - A319FIGURE-09-10-10-991-011-B01

09-10-10Page 32

Jul 01/09


**ON A/C A320-100 A320-200

1.83 m(72.1 in)

16.36 m(644.09 in)

CL

N_AR_091010_1_0110301_01_00

1.94 m(76.38 in)

0.485 m(19.095 in)

0.207 m(8.14 in)

0.14 m(5.51 in)

84°

1.23 m(48.43 in)

01

CG = 25% RC01

CL

GROUND LINE

1.76 m(69.29 in)


A

A

Location and ClearancesMain Landing Gear Doors - A320 - Twin Wheel MLG (Sheet 1 of 2)

FIGURE-09-10-10-991-011-C01

09-10-10Page 33

Jul 01/09


**ON A/C A320-100 A320-200

0.485 m(19.095 in)

82.5°

1.27 m(50.0 in)

CL

0.16 m(6.3 in)

GROUND LINE

1.94 m(76.38 in)

1.76 m(69.29 in)

2.23 m(87.8 in)

16.23 m(638.98 in)

A

CL


A

N_AR_091010_1_0110302_01_02

Location and ClearancesMain Landing Gear Doors - A320 - Optional Four Wheel Bogie MLG (Sheet 2 of 2)

FIGURE-09-10-10-991-011-C01

09-10-10Page 34

Jul 01/09


**ON A/C A321-100 A321-200

1.83 m(72.1 in)

20.62 m(811.81 in)

N_AR_091010_1_0110401_01_00

1.94 m(76.38 in)

0.485 m(19.095 in)

0.207 m(8.14 in)

0.14 m(5.51 in)

84°

1.23 m(48.43 in)

01

CG = 25% RC01

CL

GROUND LINE

1.76 m(69.29 in)


A

A

CL

Location and ClearancesMain Landing Gear Doors - A321FIGURE-09-10-10-991-011-D01

09-10-10Page 35

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-10-006-A01

APU Doors

1. GeneralThis section gives data related to the location and clearances of the APU doors.

2. Location and ClearancesFor the location and clearances of the APU doors see FIGURE 09-10-10-991-014-A.

09-10-10Page 36

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

FR84

3.42 m(134.65 in)

4.05 m(159.45 in)

0101

CG = 25% RC01

FR80

CL

N_AR_091010_1_0140101_01_01

Location and ClearancesAPU Doors

FIGURE-09-10-10-991-014-A01

09-10-10Page 37

Jul 01/09


09-10-11 AIRCRAFT GROUND CLEARANCES

**ON A/C A318-100

DESC 09-10-11-001-A01

General

1. This chapter gives data related to the distance from different components/points on the aircraft tothe ground. For the basic ground clearances of the aircraft see FIGURE 09-10-11-991-001-A. Thedimensions given are approximate and can change with:- The aircraft weight.- The type of tire installed.- The aircraft attitude.- The climate conditions.For the ground clearances of the:- Extended leading edge slats see FIGURE 09-10-11-991-002-A.- Extended trailing edge flaps see FIGURE 09-10-11-991-003-A.- Extended spoilers see FIGURE 09-10-11-991-004-A.- Ailerons in the down position see FIGURE 09-10-11-991-005-A.- Ailerons in the up position see FIGURE 09-10-11-991-006-A.- Flap tracks with the flaps extended see FIGURE 09-10-11-991-007-A.

09-10-11Page 1

Jul 01/09


**ON A/C A318-100

N_AR_091011_1_0010101_01_00

J H G F M E B C A D

K2 KL

m

A

B

C

D

E (PW)

E (CFM)

F

ft

3.44 11.29

2.08 6.62

1.79 5.87

5.93 19.46

0.77 2.53

0.65 2.13

1.70 5.58

m

G

H

J

K

K2

L

M

ft

2.31 7.58

3.72 12.21

12.93 42.42

5.06 16.60

4.06 13.32

5.60 18.37

3.95 12.96

Aircraft Ground ClearancesBasic Ground Clearances

FIGURE-09-10-11-991-001-A01

09-10-11Page 2

Jul 01/09


**ON A/C A318-100

X Y Z A’ B’ C’ D’ E’ F’ G’

HEIGHT FROM GROUND

m ft

X

Y

Z

A’

B’

C’

D’

E’

F’

G’

2.55 8.36

2.97 9.74

3.06 10.03

3.36 11.02

3.61 11.84

3.86 12.66

4.10 13.45

N_AR_091011_1_0020101_01_00

3.36 11.02

3.61 11.84

3.86 12.66

Aircraft Ground ClearancesLeading Edge Slats - ExtendedFIGURE-09-10-11-991-002-A01

09-10-11Page 3

Jul 01/09


**ON A/C A318-100

C

HEIGHT FROM GROUND

m ft

A

B

C

2.05 6.72

2.77 9.08

2.81 9.21

DA

B

D 3.65 11.97

N_AR_091011_1_0030101_01_00

Aircraft Ground ClearancesTrailing Edge Flaps - ExtendedFIGURE-09-10-11-991-003-A01

09-10-11Page 4

Jul 01/09


**ON A/C A318-100

HEIGHT FROM GROUND

m ft

Q

R

4.60 15.09

4.48 14.69

S

T

U

V

W

4.35 14.27

4.21 13.81

4.07 13.35

4.01 13.15

3.75 12.30

WVTSRQ

N_AR_091011_1_0040101_01_00

U

Aircraft Ground ClearancesSpoilers - Extended

FIGURE-09-10-11-991-004-A01

09-10-11Page 5

Jul 01/09


**ON A/C A318-100

L M

HEIGHT FROM GROUND

m ft

L

M

4.19 13.74

3.84 12.60

N_AR_091011_1_0050101_01_00

Aircraft Ground ClearancesAilerons - Down

FIGURE-09-10-11-991-005-A01

09-10-11Page 6

Jul 01/09


**ON A/C A318-100

N P

N_AR_091011_1_0060101_01_00

HEIGHT FROM GROUND

m ft

N

P

4.57 15.0

4.37 14.3

Aircraft Ground ClearancesAilerons - Up

FIGURE-09-10-11-991-006-A01

09-10-11Page 7

Jul 01/09


**ON A/C A318-100

J

HEIGHT FROM GROUND

m ft

H

J

K

2.18 7.15

2.66 8.73

3.10 10.17

KH

N_AR_091011_1_0070101_01_00

Aircraft Ground ClearancesFlap Track Fairings - Flaps Extended

FIGURE-09-10-11-991-007-A01

09-10-11Page 8

Jul 01/09


**ON A/C A319-100

DESC 09-10-11-001-B01

General


09-10-11Page 9

Jul 01/09


**ON A/C A319-100

N_AR_091011_1_0140101_01_00

J H G F M E B C A D

L K

m

A

B

C (AFT)

C (FWD)

D (AFT)

D (FWD)

E (CFM)

ft

3.45 11.32

2.09 6.86

1.98 6.50

1.80 5.91

6.12 20.08

5.94 19.49

0.67 2.20

m

F

G

H

J

K

L

M

ft

1.71 5.61

2.25 7.38

3.73 12.24

12.17 39.93

4.02 13.19

5.51 18.08

3.96 12.99

NOTE: POINTS A, B, G, H, M AND P ARE MID DOOR AT FLOOR LEVEL.

OPTIONAL

E (IAE) 0.77 2.53


FIGURE-09-10-11-991-014-A01

09-10-11Page 10

Jul 01/09


**ON A/C A319-100

X Y Z A’ B’ C’ D’ E’ F’ G’

HEIGHT FROM GROUND

m ft

X

Y

Z

A’

B’

C’

D’

E’

F’

G’

2.54 8.33

2.96 9.71

3.05 10.00

4.10 13.45

3.35 10.99

3.35 10.99

3.61 11.84

3.61 11.84

3.86 12.66

3.86 12.66

N_AR_091011_1_0150101_01_00


09-10-11Page 11

Jul 01/09


**ON A/C A319-100

C

HEIGHT FROM GROUND

m ft

A

B

C

2.05 6.72

2.77 9.08

2.81 9.21

DBA

D 3.65 11.97

N_AR_091011_1_0160101_01_00


09-10-11Page 12

Jul 01/09


**ON A/C A319-100

HEIGHT FROM GROUND

m ft

Q

R

4.60 15.09

4.48 14.69

S

T

U

V

W

4.35 14.27

4.21 13.81

4.07 13.35

4.01 13.15

3.75 12.30

WU VTSRQ

N_AR_091011_1_0170101_01_00


FIGURE-09-10-11-991-017-A01

09-10-11Page 13

Jul 01/09


**ON A/C A319-100

L M

HEIGHT FROM GROUND

m ft

L

M

4.18 13.71

3.84 12.60

N_AR_091011_1_0180101_01_00


FIGURE-09-10-11-991-018-A01

09-10-11Page 14

Jul 01/09


**ON A/C A319-100

N P

N_AR_091011_1_0190101_01_00

HEIGHT FROM GROUND

m ft

N

P

4.56 14.96

4.36 14.3


FIGURE-09-10-11-991-019-A01

09-10-11Page 15

Jul 01/09


**ON A/C A319-100

J

HEIGHT FROM GROUND

m ft

H

J

K

2.09 6.86

2.59 8.49

3.04 9.97

KH

N_AR_091011_1_0200101_01_00


FIGURE-09-10-11-991-020-A01

09-10-11Page 16

Jul 01/09


**ON A/C A320-100 A320-200

DESC 09-10-11-001-C01

General


09-10-11Page 17

Jul 01/09


**ON A/C A320-100 A320-200

N_AR_091011_1_0210101_01_00

DABCENFGMHJ

NOTE: POINTS C AND D ARE HALFWAY BETWEEN NOSE AND MAIN GEARS.

LK

m

A

B

C

D

E (CFM)

E (IAE)

F

ft

3.47 11.38

2.09 6.86

1.86 6.10

6.00 19.68

0.68 2.23

0.78 2.56

1.72 5.64

m

G

H

J

K

L

M

N

ft

2.25 7.38

3.73 12.24

12.14 39.93

4.04 13.25

5.57 18.27

2.51 8.23

3.96 12.99


FIGURE-09-10-11-991-021-A01

09-10-11Page 18

Jul 01/09


**ON A/C A320-100 A320-200

W X Y Z A’ B’ C’ D’ E’ F’

HEIGHT FROM GROUND

m ft

W

X

Y

Z

A’

B’

C’

D’

E’

F’

2.57 8.43

2.98 9.78

3.07 10.07

4.09 13.42

3.36 11.02

3.61 11.84

3.86 12.66

N_AR_091011_1_0220101_01_00

3.36 11.02

3.61 11.84

3.86 12.66


09-10-11Page 19

Jul 01/09


**ON A/C A320-100 A320-200

C

HEIGHT FROM GROUND

m ft

A

B

C

2.05 6.72

2.77 9.08

2.81 9.21

DBA

D 3.64 11.94

N_AR_091011_1_0230101_01_00


09-10-11Page 20

Jul 01/09


**ON A/C A320-100 A320-200

HEIGHT FROM GROUND

m ft

P

Q

4.59 15.06

4.47 14.67

R

S

T

U

V

4.35 14.27

4.21 13.81

4.07 13.35

4.01 13.16

3.75 12.30

VT USRQP

N_AR_091011_1_0240101_01_00


FIGURE-09-10-11-991-024-A01

09-10-11Page 21

Jul 01/09


**ON A/C A320-100 A320-200

L M

HEIGHT FROM GROUND

m ft

L

M

4.17 13.68

3.83 12.57

N_AR_091011_1_0250101_01_00


FIGURE-09-10-11-991-025-A01

09-10-11Page 22

Jul 01/09


**ON A/C A320-100 A320-200

N_AR_091011_1_0260101_01_00

N P

HEIGHT FROM GROUND

m ft

N

P

4.55 14.93

4.35 14.27


FIGURE-09-10-11-991-026-A01

09-10-11Page 23

Jul 01/09


**ON A/C A320-100 A320-200

J

HEIGHT FROM GROUND

m ft

H

J

K

2.18 7.15

2.66 8.73

3.10 10.17

KH

N_AR_091011_1_0270101_01_00


FIGURE-09-10-11-991-027-A01

09-10-11Page 24

Jul 01/09


**ON A/C A321-100 A321-200

DESC 09-10-11-001-D01

General


09-10-11Page 25

Jul 01/09


**ON A/C A321-100 A321-200

N_AR_091011_1_0280101_01_00

DABCPENGFMHJ

NOTE: POINTS A, B, G, H, M, N AND P ARE MID DOOR AT FLOOR LEVEL.POINTS C AND D ARE EXTREMES OF STRAIGHT PORTION.

KL

m

A

B

C (AFT)

C (FWD)

D (AFT)

D (FWD)

E (CFM)

ft

3.46 11.35

2.08 6.82

1.99 6.53

1.80 5.91

6.13 20.11

5.94 19.49

0.68 2.23

m

G

H

J

K

L

M

N

ft

2.25 7.38

3.71 12.17

12.10 39.70

4.02 13.19

5.54 18.18

2.50 8.20

3.62 11.88

E (IAE)

F

0.79 2.59

1.72 5.64

P 3.53 11.58


FIGURE-09-10-11-991-028-A01

09-10-11Page 26

Jul 01/09


**ON A/C A321-100 A321-200

W X Y Z A’ B’ C’ D’ E’ F’

HEIGHT FROM GROUND

m ft

W

X

Y

Z

A’

B’

C’

D’

E’

F’

2.58 8.46

2.98 9.77

3.07 10.07

4.08 13.38

3.36 11.02

3.61 11.02

3.61 11.84

3.85 11.84

3.85 12.63

3.86 12.63

N_AR_091011_1_0290101_01_00


09-10-11Page 27

Jul 01/09


**ON A/C A321-100 A321-200

HEIGHT FROM GROUND

m ft

A

B

C

1.95 6.39

2.84 9.31

2.71 8.89

CD

N_AR_091011_1_0300101_01_00

AG1 B H1

D 3.74 12.27

G1 2.49 8.16

H1 3.53 11.58


09-10-11Page 28

Jul 01/09


**ON A/C A321-100 A321-200

HEIGHT FROM GROUND

m ft

P

Q

4.59 15.05

4.46 14.63

R

S

T

U

V

4.34 14.23

4.20 13.77

4.08 13.38

4.04 13.25

3.74 12.27

USRQP V

N_AR_091011_1_0310101_01_00

T


FIGURE-09-10-11-991-031-A01

09-10-11Page 29

Jul 01/09


**ON A/C A321-100 A321-200

L M

HEIGHT FROM GROUND

m ft

L

M

4.15 13.61

3.81 12.50

N_AR_091011_1_0320101_01_00


FIGURE-09-10-11-991-032-A01

09-10-11Page 30

Jul 01/09


**ON A/C A321-100 A321-200

N P

N_AR_091011_1_0330101_01_00

HEIGHT FROM GROUND

m ft

N

P

4.53 14.86

4.33 14.20


FIGURE-09-10-11-991-033-A01

09-10-11Page 31

Jul 01/09


**ON A/C A321-100 A321-200

HEIGHT FROM GROUND

m ft

H

J

K

1.91 6.26

2.31 7.57

2.96 9.71

J KH

N_AR_091011_1_0340101_01_00


FIGURE-09-10-11-991-034-A01

09-10-11Page 32

Jul 01/09


09-10-12 AIRCRAFT GROUND SERVICE CONNECTIONS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-12-001-A01

General

1. This chapter gives data about the ground service connections of the aircraft.See FIGURE 09-10-12-991-001-AFIGURE 09-10-12-991-001-BFIGURE 09-10-12-991-001-CFIGURE09-10-12-991-001-D for the ground service connections general layout.This chapter gives data about the systems that follow:- Hydraulic System, see DESC 09-10-12-002-A01,- Electrical System, see DESC 09-10-12-003-A01,- Fuel System, see DESC 09-10-12-004-A01,- Potable Water System, see DESC 09-10-12-005-A01,- Waste Water Disposal System, see DESC 09-10-12-006-A01.

09-10-12Page 1

Jul 01/09


**ON A/C A318-100

1 − EXTERNAL POWER PANEL2 − LOW PRESSURE CONDITIONED AIR CONNECTOR3 − IDG OIL FILLING4 − ENGINE OIL FILLING5 − WASTE SERVICE PANEL6 − POTABLE WATER SERVICE PANEL7 − APU OIL FILLING8 − YELLOW HYDRAULIC GROUND CONNECTOR

9 − GREEN HYDRAULIC GROUND CONNECTOR10 − BLUE HYDRAULIC GROUND CONNECTOR11 − PRESSURE REFUEL/DEFUEL COUPLING12 − HIGH PRESSURE AIR GROUND

13 − REFUEL/DEFUEL CONTROL PANEL14 − OVERWING REFUEL COUPLING

CONNECTORS FOR ENGINE STARTING

N_AR_091012_1_0010101_01_00

75

6

109

8

14

11

43

122

113

3

4

11

14

12

3 49 10

67

Ground Service ConnectionsGeneral Layout

FIGURE-09-10-12-991-001-A01

09-10-12Page 2

Jul 01/09


**ON A/C A319-100

75

6

109

8

14

11

43

122

113

3

4

11

14

12

3 49 10

67





N_AR_091012_1_0010201_01_00


FIGURE-09-10-12-991-001-B01

09-10-12Page 3

Jul 01/09


**ON A/C A320-100 A320-200





75

6

8

14

11

43

122

113

3

4

11

14

12

3 49 10

67

109

N_AR_091012_1_0010301_01_00


FIGURE-09-10-12-991-001-C01

09-10-12Page 4

Jul 01/09


**ON A/C A321-100 A321-200





75

6

109

8

14

11

43

122

113

3

4

11

14

12

3 49 10

67

N_AR_091012_1_0010401_01_00


FIGURE-09-10-12-991-001-D01

09-10-12Page 5

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-12-002-A01

Hydraulic System

**ON A/C A318-100

1. AccessThis section gives data related to the location of the ground service connections.

Position from Aircraft CenterlineAccess

Position from Aftof Nose LH Side RH Side

Height fromGround

Green HydraulicGround ConnectorsAccess Door 197CB

16.70 m (54.79 ft) 1.27 m (4.17 ft) 1.76 m (5.77 ft)

Yellow HydraulicGround connectorsAccess Door 198CB

16.70 m (54.79 ft) 1.27 m (4.17 ft) 1.76 m (5.77 ft)

Hydraulic ReservoirServicing PanelAccess Door 197EB

17.76 m (58.27 ft) 1.27 m (4.17 ft) 1.76 m (5.77 ft)

Ground Service Panels

TABLE 1

NOTE : Distances are approximate.

**ON A/C A319-100




Height fromGround


17.49 m (57.38 ft) 1.27 m (4.17 ft) 1.76 m (5.77 ft)


17.49 m (57.38 ft) 1.27 m (4.17 ft) 1.76 m (5.77 ft)

09-10-12Page 6

Jul 01/09




Height fromGround


18.55 m (60.86 ft) 1.27 m (4.17 ft) 1.76 m (5.77 ft)


TABLE 2


**ON A/C A320-100 A320-200




Height fromGround


19.08 m (62.60 ft) 1.27 m (4.17 ft) 1.76 m (5.77 ft)


19.08 m (62.60 ft) 1.27 m (4.17 ft) 1.76 m (5.77 ft)


20.15 m (66.11 ft) 1.27 m (4.17 ft) 1.76 m (5.77 ft)


TABLE 3


**ON A/C A321-100 A321-200




Height fromGround


23.35 m (76.61 ft) 1.27 m (4.17 ft) 1.76 m (5.77 ft)

09-10-12Page 7

Jul 01/09




Height fromGround


23.35 m (76.61 ft) 1.27 m (4.17 ft) 1.76 m (5.77 ft)


24.23 m (79.49 ft) 1.27 m (4.17 ft) 1.76 m (5.77 ft)


TABLE 4


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

5. Technical SpecificationsThis section gives data related to the specifications of the ground service connections.

A. Ground TestReservoir PressurizationOn each ground service panel:- One connector AE80532N (suction).- One connector AE80531K (delivery).

B. Reservoir FillingOn the Green system ground service panel:- One connection AE96993E for pressurized supply.- One handpump filling connection for unpressurized (suction) supply.

09-10-12Page 8

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

RESERVOIR FILL SYSTEMHAND PUMP FILL CONNECTION

GROUND TESTPRESSURE

CONNECTION

GROUND TESTSUCTION

CONNECTIONRESERVOIR FILLCONNECTION

AE96993GM

GROUND SUPPLY

AE80531K AE80532N

1698GM

1008GM 1007GM 1006GM

197CB

A

AN_AR_091012_1_0020101_01_00

Ground Service ConnectionsGreen System Ground Service Panel

FIGURE-09-10-12-991-002-A01

09-10-12Page 9

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

GROUND CONNECTIONSUCTION

GROUNDCONNECTION

DELIVERY

AE80531K

AE80532N

N_AR_091012_1_0030101_01_00

2006GM

2008GM

A

Z197

A

Ground Service ConnectionsBlue System Ground Service Panel

FIGURE-09-10-12-991-003-A01

09-10-12Page 10

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

GROUND TESTPRESSURE CONNECTION

GROUND TESTSUCTION CONNECTION

AE80531K AE80532N

A

A

N_AR_091012_1_0140101_01_00

3008GM 3006GM

198CB

Ground Service ConnectionsYellow System Ground Service Panel

FIGURE-09-10-12-991-014-A01

09-10-12Page 11

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-12-003-A01

Electrical System




Height fromGround

External PowerReceptacleAccess Door 121AL

2.55 m (8.37 ft) on centerline 2.00 m (6.56 ft)


TABLE 1



A. External Power Receptacles:- One MS90362-3 - 90 KVA

B. Power Supply:- Three Phases, 115 V, 400 Hz

C. Electrical Connectors for Servicing:- AC Outlets: HUBBEL 5258- DC Outlets: HUBBEL 7472- Vacuum Cleaner Outlets: HUBBEL 5258

09-10-12Page 12

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

121AL

108VU

A

N_AR_091012_1_0040101_01_00

Ground Service ConnectionsExternal Power Receptacles

FIGURE-09-10-12-991-004-A01

09-10-12Page 13

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-12-004-A01

Fuel System

**ON A/C A318-100




Height fromGround

Refuel/DefuelIntegrated PanelAccess Door 192MB

12.00 m (39.37ft)

1.80 m (5.91 ft) 1.80 m (5.91 ft)

Refuel/DefuelCoupling, LeftAccess Door 522HB(Optional)

14.80 m (48.56ft)

10.00 m (32.81 ft) 3.50 m (11.48 ft)

Refuel/DefuelCoupling, RightAccess Door 622HB

14.80 m (48.56ft)

10.00 m (32.81 ft) 3.50 m (11.48 ft)

Gravity RefuelCoupling

16.70 m (54.79ft)

12.40 m (40.68 ft) 12.40 m (40.68 ft) 3.70 m (12.14 ft)


TABLE 1


**ON A/C A319-100




Height fromGround


12.80 m (41.99ft)

1.80 m (5.91 ft) 1.80 m (5.91 ft)


15.60 m (51.18ft)

10.00 m (32.81 ft) 3.50 m (11.48 ft)

09-10-12Page 14

Jul 01/09




Height fromGround


15.60 m (51.18ft)

10.00 m (32.81 ft) 3.50 m (11.48 ft)


17.40 m (57.09ft)

12.40 m (40.68 ft) 12.40 m (40.68 ft) 3.70 m (12.14 ft)


TABLE 2


**ON A/C A320-100 A320-200




Height fromGround


14.40 m (47.24ft)

1.80 m (5.91 ft) 1.80 m (5.91 ft)


17.20 m (56.43ft)

10.00 m (32.81 ft) 3.50 m (11.48 ft)


17.20 m (56.43ft)

10.00 m (32.81 ft) 3.50 m (11.48 ft)


19.10 m (62.66ft)

12.40 m (40.68 ft) 12.40 m (40.68 ft) 3.70 m (12.14 ft)


TABLE 3


**ON A/C A321-100 A321-200


09-10-12Page 15

Jul 01/09




Height fromGround


18.70 m (61.35ft)

1.80 m (5.91 ft) 1.80 m (5.91 ft)


21.50 m (70.54ft)

10.00 m (32.81 ft) 3.50 m (11.48 ft)


21.50 m (70.54ft)

10.00 m (32.81 ft) 3.50 m (11.48 ft)


23.40 m (76.77ft)

12.40 m (40.68 ft) 12.40 m (40.68 ft) 3.70 m (12.14 ft)


TABLE 4


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


A. Refuel/Defuel Couplings:- Rigth wing: one standard ISO R45, 2.5 in.- Left wing: one optional standard ISO R45, 2.5 in.

B. Refuel Pressure:- Max. pressure: 3.45 bar (50 psi).

C. Refuel Flow:- 1400 l/minute (369.84 US gal/minute)

09-10-12Page 16

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

REFUEL/DEFUELCONTROL PANEL

NOTE: STANDARD CONFIGURATION OF REFUEL/DEFUEL PANEL.

A

N_AR_091012_1_0080101_01_01

FUELkg x 1000

QTY

RIGHTCTRLEFT

LEFT CTR RIGHT

LVLHI

OPEN

NORM

SHUT

OPEN

NORM

SHUT

REFUEL VALVESOPEN

NORM

SHUT

BATT POWERTESTHI LVL ON

OPEN LTS NORM

MODE SELECTREFUEL

OFF

DEFUEL / XFR

kg x 1000

PRESELECTED

DEC INC

ACTUALREFUEL

CKPT END

A

Ground Service ConnectionsRefuel/Defuel Panel

FIGURE-09-10-12-991-008-A01

09-10-12Page 17

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_091012_1_0090101_01_00

RIB15

RIB14

A

41QM

40QM

LEADINGEDGE

WING FRONTSPAR

A

Ground Service ConnectionsRefuel/Defuel Couplings

FIGURE-09-10-12-991-009-A01

09-10-12Page 18

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_091012_1_0150101_01_00

RIB19

RIB20

A

FWD

ADAPTER(REF ONLY)

GROUND CONNECTION(REF ONLY)

44QM

(45QM)

A

Ground Service ConnectionsGravity Refuel Couplings

FIGURE-09-10-12-991-015-A01

09-10-12Page 19

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-12-005-A01

Potable Water System

**ON A/C A318-100




Height fromGround

Potable WaterGround ServicePanelAccess Door 171AL

22.60 m (74.15 ft) 0.40 m (1.31 ft) 2.60 m (8.53 ft)

Drain PanelAccess Door 133AL

8.80 m (28.87 ft) 0.10 m (0.33 ft) 1.70 m (5.58 ft)

Drain PanelAccess Door 192NB

10.20 m (33.46 ft) 0.50 m (1.64 ft) 1.80 m (5.91 ft)


TABLE 1


**ON A/C A319-100




Height fromGround


25.00 m (82.02 ft) 0.40 m (1.31 ft) 2.60 m (8.53 ft)


9.40 m (30.84 ft) 0.10 m (0.33 ft) 1.70 m (5.58 ft)


11.00 m (36.09 ft) 0.50 m (1.64 ft) 1.80 m (5.91 ft)


TABLE 2

09-10-12Page 20

Jul 01/09



**ON A/C A320-100 A320-200




Height fromGround


28.70 m (94.16 ft) 0.40 m (1.31 ft) 2.60 m (8.53 ft)


9.40 m (30.84 ft) 0.10 m (0.33 ft) 1.70 m (5.58 ft)


12.50 m (41.01 ft) 0.50 m (1.64 ft) 1.80 m (5.91 ft)


TABLE 3


**ON A/C A321-100 A321-200




Height fromGround


38.20 m (125.33ft)

0.40 m (1.31 ft) 2.60 m (8.53 ft)


9.40 m (30.84 ft) 0.10 m (0.33 ft) 1.70 m (5.58 ft)


12.50 m (41.01 ft) 0.50 m (1.64 ft) 1.80 m (5.91 ft)


TABLE 4


09-10-12Page 21

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


A. Connections

(1) On the potable ground service panel (Access Door Access Door 171AL):- One standard 3/4 in. quick release filling connection.- One ground pressurization connection.

(2) On drain panel (Access Door 133AL):- One standard 3/4 in. drain connection.

(3) On drain panel (Access Door 192NB):- One standard 3/4 in. drain connection. with back- up mechanical control.- One standard 3/4 in. overflow and discharge connection with back up mechanical

control.

B. Capacity- 200 l (52.83 US gal).

C. Filling Rate- Max Filling Pressure: 3.45 bar (50 psi).- Flow rate: 67 l/minute (17.70 US gal/minute)

09-10-12Page 22

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_091012_1_0100101_01_00

DRAIN CONNECTION

DRAIN CONNECTIONDISCHARGE ANDOVERFLOW PORT

FILL ANDDRAIN PORT

GROUND CONNECTION

PRESSURIZATION

B

C

Z133

Z171

Z138

A

BC

A

Ground Service ConnectionsPotable Water Ground Service Panel

FIGURE-09-10-12-991-010-A01

09-10-12Page 23

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-12-006-A01

Waste Water Disposal-System

**ON A/C A318-100




Height fromGround

Waste WaterGround ServicePanelAccess Door 172AR

22.90 m (75.13 ft) 0.80 m (2.62 ft) 2.80 m (9.19 ft)


TABLE 1


**ON A/C A319-100




Height fromGround


24.90 m (81.69 ft) 0.80 m (2.62 ft) 2.80 m (9.19 ft)


TABLE 2

**ON A/C A320-100 A320-200


09-10-12Page 24

Jul 01/09




Height fromGround


28.60 m (93.83 ft) 0.80 m (2.62 ft) 2.80 m (9.19 ft)

Waste WaterGround ServicePanelAccess Door 125AL(Optional)

3.40 m (11.15 ft) 1.20 m (3.94 ft) 2.40 m (7.87 ft)


TABLE 3

**ON A/C A321-100 A321-200




Height fromGround


35.50 m (116.47ft)

0.80 m (2.62 ft) 2.80 m (9.19 ft)

Waste WaterGround ServicePanelAccess Door 125AL(Optional)

3.40 m (11.15 ft) 1.20 m (3.94 ft) 2.40 m (7.87 ft)


TABLE 4

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


A. Connections- One standard 1 in. flushing connection.- One standard 4 in. drain connection.

09-10-12Page 25

Jul 01/09


B. Single Toilet Capacity- Waste: 200 l (52.83 US gal)- Chemical fluid: 10 l (2.64 US gal).

C. Flushing Pressure- Maximum flushing pressure : 2.41 bar (35 psi)

D. Flow Rate- Maximum flow rate : 38 l/min (10.04 US gal/min)

09-10-12Page 26

Jul 01/09


**ON A/C A318-100 A319-100

N_AR_091012_1_0130101_01_00

FILL AND RINSECONNECTION

TOILET DRAINCONNECTION

FR66 FR65

A

Z172

A

Ground Service ConnectionsWaste Water Ground Service Panel

FIGURE-09-10-12-991-013-A01

09-10-12Page 27

Jul 01/09


**ON A/C A320-100 A320-200 A321-100 A321-200

FILL AND RINSE CONNECTION

TOILET DRAIN CONNECTION

CONNECTIONTOILET DRAIN

CONNECTIONFILL AND RINSE

SERVICE PANELFORWARD TOILET

(OPTIONAL)

N_AR_091012_1_0130201_01_00

Z172

Z125

FR11 FR12

A

FR66 FR65

AFT TOILET SERVICE PANEL

B

B

A

Ground Service ConnectionsWaste Water Ground Service Panel

FIGURE-09-10-12-991-013-B01

09-10-12Page 28

Jul 01/09


09-10-13 AIRCRAFT GROUNDING POINTS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-13-001-A01

General

**ON A/C A318-100




Height fromGround

NLG 5.07 m (16.63 ft) On Centerline 0.94 m (3.08 ft)

LH MLG 15.32 m (50.26 ft) 3.79 m (12.43 ft) 1.07 m (3.51 ft)

RH MLG 15.32 m (50.26 ft) 3.79 m (12.43 ft) 1.07 m (3.51 ft)

Grounding Points Locations

TABLE 1


**ON A/C A319-100




Height fromGround


LH MLG 16.11 m (52.85 ft) 3.79 m (12.43 ft) 1.07 m (3.51 ft)

RH MLG 16.11 m (52.85 ft) 3.79 m (12.43 ft) 1.07 m (3.51 ft)


TABLE 2


**ON A/C A320-100 A320-200


09-10-13Page 1

Jul 01/09




Height fromGround


LH MLG 20.25 m (66.44 ft) 3.79 m (12.43 ft) 1.07 m (3.51 ft)

RH MLG 20.25 m (66.44 ft) 3.79 m (12.43 ft) 1.07 m (3.51 ft)


TABLE 3


**ON A/C A321-100 A321-200




Height fromGround


LH MLG 21.97 m (72.08 ft) 3.79 m (12.43 ft) 1.07 m (3.51 ft)

RH MLG 21.97 m (72.08 ft) 3.79 m (12.43 ft) 1.07 m (3.51 ft)


TABLE 4


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

5. Technical SpecificationsThe grounding stud on each landing gear is designed for use with a clip-on connector, such as theAppleton TGR.The grounding stud are used to connect the aircraft to approved ground connection on the ramp, inthe hangar or through a ground earth spike for:- Refuel/Defuel operations,- Maintenance operations,- Bad Weather conditions.There is an additional grounding point located over the wing near the gravity refuel coupling, seeDESC 09-10-12-004-A01.

09-10-13Page 2

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

A

A

N_AR_091013_1_0010101_01_00

NOSE LANDING GEAR MAIN LANDING GEAR

LANDING GEAR

GROUND CABLE

A

Grounding PointLocation

FIGURE-09-10-13-991-001-A01

09-10-13Page 3

Jul 01/09


09-10-14 CARGO COMPARTMENTS

**ON A/C A318-100

DESC 09-10-14-001-A01

General

1. The lower deck of the aircraft has three cargo compartments:- Forward cargo compartment,- Aft cargo compartment,- Bulk cargo compartment.The total volume of the three cargo compartments is 21.30 m3 (752.20 ft3).

NOTE : See your customized WBM for accurate data related to the aircraft configuration.

A. FWD Cargo CompartmentThe fwd cargo compartment (n˚ 1) is designed for bulk cargo and baggage.The volume of the FWD cargo compartment is 6.72 m3 (237.31 ft3).See FIGURE 09-10-14-991-007-A for location and dimensions of the FWD compartment.

B. Aft Cargo CompartmentThe aft cargo compartment (n˚ 4) is designed for bulk cargo and baggage.The volume of the aft cargo compartment is 8.87 m3 (313.24 ft3).See FIGURE 09-10-14-991-008-A for location and dimensions of the aft compartment.

C. Bulk Cargo CompartmentThe bulk cargo compartment (n˚ 5) is designed for bulk cargo.The volume of the bulk cargo compartment is 5.71 m3 (201.65 ft3).See FIGURE 09-10-14-991-009-A for location and dimensions of the bulk compartment.

09-10-14Page 1

Jul 01/09


**ON A/C A318-100

A

FR24A FR34

FR34

FR28

FR24A

FR24A

FR28

FR34 A

1.24

3 m

(4.0

7 ft)

1.429 m(4.68 ft)

2.637 m

(8.65 ft)

2.630 m(8.62 ft)

N_AR_091014_1_0070101_01_00

Forward Cargo CompartmentLocation and Dimensions

FIGURE-09-10-14-991-007-A01

09-10-14Page 2

Jul 01/09


**ON A/C A318-100

FR47

FR57A

FR60

1.429 m(4.68 ft)2.630 m(8.62 ft)

A

FR60FR47

A

3.353 m

(11.00 ft)

FR60

FR57A

FR57

FR47

N_AR_091014_1_0080101_01_00

1.24

3 m

(4.0

7 ft)

/54

/54

/54

Aft Cargo CompartmentLocation and Dimensions

FIGURE-09-10-14-991-008-A01

09-10-14Page 3

Jul 01/09


**ON A/C A318-100

A

FR60 FR65

FR60

FR62

FR63FR65

2.708 m

(8.88 ft)

A

FR65

FR63

FR60

1.558 m(5.11 ft)

N_AR_091014_1_0090101_01_00

Bulk Cargo CompartmentLocation and Dimensions

FIGURE-09-10-14-991-009-A01

09-10-14Page 4

Jul 01/09


**ON A/C A319-100

DESC 09-10-14-001-B01

General

1. The lower deck of the aircraft has two cargo compartments:- Forward cargo compartment,- Aft cargo compartment,The total volume of the two cargo compartments is 27.56 m3 (973.27 ft3).


A. FWD Cargo CompartmentThe FWD cargo compartment (n˚ 1) is designed for bulk cargo and baggage or transport ofULDs.The volume of the FWD cargo compartment is 8.51 m3 (300.53 ft3).See FIGURE 09-10-14-991-010-A for location and dimensions of the FWD compartment.

B. Aft Cargo CompartmentThe aft cargo compartment (n˚ 4 and 5) is designed for bulk cargo and baggage or transport ofULDs.The volume of the AFT cargo compartment is 19.05 m3 (672.74 ft3).See FIGURE 09-10-14-991-011-A for location and dimensions of the aft compartment.

09-10-14Page 5

Jul 01/09


**ON A/C A319-100

FR24A FR34

FR24A

FR28

FR34

A

1.24

3 m

(4.0

7 ft)

1.430 m(4.69 ft)

3.345 m

(10.97 ft)

2.630 m(8.62 ft)

A

N_AR_091014_1_0100101_01_00


FIGURE-09-10-14-991-010-A01

09-10-14Page 6

Jul 01/09


**ON A/C A319-100

FR47

1.430 m(4.69 ft)2.630 m(8.62 ft)

1.24

3 m

(4.0

7 ft)

A

4.421 m

(14.50 ft)

FR65

1.558 m(5.11 ft)

FR63

3.241 m

(10.63 ft)

7.662 m

(25.13 ft)

FR65FR47 FR59

FR59

FR55A

A

N_AR_091014_1_0110101_01_00

/51

/51


FIGURE-09-10-14-991-011-A01

09-10-14Page 7

Jul 01/09


**ON A/C A320-100 A320-200

DESC 09-10-14-001-C01

General



A. FWD Cargo CompartmentThe FWD cargo compartment (n˚ 1) is designed for bulk cargo and baggage or transport ofULDs.The volume of the FWD cargo compartment is 13.28 m3 (468.98 ft3).See FIGURE 09-10-14-991-013-A for location and dimensions of the FWD compartment.

B. Aft Cargo CompartmentThe aft cargo compartment (n˚ 3 and 4) is designed for bulk cargo and baggage or transport ofULDs.The volume of the aft cargo compartment is 18.26 m3 (644.85 ft3).See FIGURE 09-10-14-991-014-A for location and dimensions of the aft compartment.

C. Bulk Cargo CompartmentThe bulk cargo compartment (n˚ 5) is designed for bulk cargo and baggage.The volume of the bulk cargo compartment is 5.91 m3 (208.71 ft3).See FIGURE 09-10-14-991-015-A for location and dimensions of the bulk compartment.

09-10-14Page 8

Jul 01/09


**ON A/C A320-100 A320-200

1.430 m(4.69 ft)

1.24

3 m

(4.0

7 ft)

4.850 m

(15.91 ft)

A

FR24A FR34

FR34

FR31

FR28

FR24A

2.630 m(8.62 ft)

FR34

FR31

FR28

FR24A

A

N_AR_091014_1_0130101_01_00


FIGURE-09-10-14-991-013-A01

09-10-14Page 9

Jul 01/09


**ON A/C A320-100 A320-200

FR59

FR56

FR53FR52A

FR47

A

1.430 m(4.69 ft)

6.554 m

(21.50 ft)

1.24

2 m

(4.0

7 ft)

3.354 m

(11.00 ft)

3.200 m

(126.00 ft)

1.408 m(4.61 ft)

FR47

FR50

FR52A

FR53

FR56

FR59

A

FR47 FR59

2.630 m(8.62 ft)

N_AR_091014_1_0140101_01_00


FIGURE-09-10-14-991-014-A01

09-10-14Page 10

Jul 01/09


**ON A/C A320-100 A320-200

1.21

1 m

(3.9

7 ft)

1.558 m(5.11 ft)

1.408 m(4.62 ft)

2.630 m(8.62 ft)

3.241 m

(10.63 ft) 0.82

0 m

(2.6

9 ft)

0.968 m(3.17 ft)

FR65

FR63

FR59

FR59

FR63

FR65

A

FR59 FR65

N_AR_091014_1_0150101_01_00

A


FIGURE-09-10-14-991-015-A01

09-10-14Page 11

Jul 01/09


**ON A/C A321-100 A321-200

DESC 09-10-14-001-D01

General



A. FWD Cargo CompartmentThe FWD cargo compartment (n˚ 1 and 2) is designed for bulk cargo and baggage or transportof ULDs.The volume of the FWD cargo compartment is 22.81 m3 (805.53 ft3).See FIGURE 09-10-14-991-016-A for location and dimensions of the FWD compartment.

B. Aft Cargo CompartmentThe aft cargo compartment (n˚ 3 and 4) is designed for bulk cargo and baggage or transport ofULDs.The volume of the AFT cargo compartment is 22.255 m3 (785.93 ft3).See FIGURE 09-10-14-991-017-A for location and dimensions of the aft compartment.

C. Bulk Cargo CompartmentThe bulk cargo compartment (n˚ 5) is designed for bulk cargo and baggage.The volume of the bulk cargo compartment is 5.88 m3 (207.65 ft3).See FIGURE 09-10-14-991-018-A for location and dimensions of the bulk compartment.

09-10-14Page 12

Jul 01/09


**ON A/C A321-100 A321-200

A

FR24A

FR28

FR31

FR34

FR35.2

FR35.5

N_AR_091014_1_0160101_01_00

8.149 m

(26.73 ft)

3.474 m

(11.39 ft)

4.675 m

(15.33 ft)

2.630 m(8.62 ft)

1.430 m(4.69 ft)

1.24

2 m

(4.0

7 ft)

FR35.5

FR35.2

FR34

FR31

FR28

FR24A

A

FR24A FR35.5


FIGURE-09-10-14-991-016-A01

09-10-14Page 13

Jul 01/09


**ON A/C A321-100 A321-200

A

8.154 m

(26.75 ft)

2.630 m(8.62 ft)

1.430 m(4.69 ft)

1.24

2 m

(4.0

7 ft)

FR59FR47.2

FR47.2

FR52A

FR56

FR59

FR59

FR56

FR52A

FR50

FR47.5

FR47.2

N_AR_091014_1_0170101_01_00

FR53

A


FIGURE-09-10-14-991-017-A01

09-10-14Page 14

Jul 01/09


**ON A/C A321-100 A321-200

FR65FR59

FR59

FR60

FR62

FR63

FR64

FR65

FR59

FR60

FR62

FR65 A1.558 m(5.11 ft)0.968 m(3.17 ft)

1.408 m(4.61 ft)2.630 m(8.62 ft)

3.241 m

(10.63 ft)

0.82

1 m

(2.6

9 ft)

1.21

1 m

(3.9

7 ft)

A

N_AR_091014_1_0180101_01_00


FIGURE-09-10-14-991-018-A01

09-10-14Page 15

Jul 01/09


09-10-15 LOCATION OF HAZARDOUS MATERIALS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-15-001-A01

General

1. A number of items and areas on the aircraft contain Hazardous Materials.

WARNING : IDENTIFY WHICH HAZARDOUS MATERIALS WERE TRANSPORTED IN THECARGO COMPARTMENTS.

NOTE : The List of Radioactive and hazardous Element manual (LRE) gives information on thesematerials.

The FIGURE 09-10-15-991-001-AFIGURE 09-10-15-991-001-BFIGURE 09-10-15-991-001-CFIGURE09-10-15-991-001-D gives the general location of the Hazardous Materials that you can find on theaircraft.

NOTE : The number and arrangement of the portable equipment depend on the aircraftconfiguration.

09-10-15Page 1

Jul 01/09


**ON A/C A318-100

BA

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Hazardous MaterialsLocation - A318

FIGURE-09-10-15-991-001-A01

09-10-15Page 2

Jul 01/09


**ON A/C A319-100

AV

ION

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FIGURE-09-10-15-991-001-B01

09-10-15Page 3

Jul 01/09


**ON A/C A320-100 A320-200

N_A

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FIGURE-09-10-15-991-001-C01

09-10-15Page 4

Jul 01/09


**ON A/C A321-100 A321-200

N_A

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9101

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401_

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FIGURE-09-10-15-991-001-D01

09-10-15Page 5

Jul 01/09


09-10-16 LANDING GEARS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-10-16-001-A01

General

1. This chapter gives details on the landing gears.- For Landing Gear footprint, see FIGURE 09-10-16-991-001-AFIGURE 09-10-16-991-001-

BFIGURE 09-10-16-991-001-CFIGURE 09-10-16-991-001-D,- For Nose Landing Gear description, see FIGURE 09-10-16-991-002-A,- For Main Landing Gear description, see FIGURE 09-10-16-991-003-A,- For Landing Gear Doors description, see FIGURE 09-10-16-991-004-A.

09-10-16Page 1

Jul 01/09


**ON A/C A318-100

N_AR_091016_1_0010101_01_00

0.50 m(19.7 in)

10.252 m(33.64 ft)

0.927 m(36.5 in)

7.59 m(24.90 ft)

CL

FootprintLanding Gear

FIGURE-09-10-16-991-001-A01

09-10-16Page 2

Jul 01/09


**ON A/C A319-100

0.50 m(19.7 in)

11.039 m(36.22 ft)

0.927 m(36.5 in)

7.59 m(24.90 ft)

N_AR_091016_1_0010201_01_00

CL


FIGURE-09-10-16-991-001-B01

09-10-16Page 3

Jul 01/09


**ON A/C A320-100 A320-200

0.50 m(19.7 in)

12.64 m(41.47 ft)

0.927 m(36.5 in)

7.59 m(24.90 ft)

CL

N_AR_091016_1_0010301_01_00

FootprintLanding Gear - Twin Wheel MLG (Sheet 1 of 2)

FIGURE-09-10-16-991-001-C01

09-10-16Page 4

Jul 01/09


**ON A/C A320-100 A320-200

0.50 m(19.7 in)

12.64 m(41.47 ft)

0.78 m(30.7 in)

7.59 m(24.90 ft)

CL

N_AR_091016_1_0010302_01_00

1.005 m(39.5 ft)

FootprintLanding Gear - Four Wheel Bogie MLG (Optional, A320 only) (Sheet 2 of 2)

FIGURE-09-10-16-991-001-C01

09-10-16Page 5

Jul 01/09


**ON A/C A321-100 A321-200

0.50 m(19.7 in)

16.91 m(55.47 ft)

0.927 m(36.5 in)

7.59 m(24.90 ft)

CL

N_AR_091016_1_0010401_01_00


FIGURE-09-10-16-991-001-D01

09-10-16Page 6

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

ACTUATINGCYLINDER

NOSE WHEELSTEERING

SERVO CONTROL

STEERINGACTUATINGCYLINDER

TORQUE LINK

TOWINGFITTING

SHOCKABSORBER

DOWNLOCKPROXIMITY

DETECTORS

N_AR_091016_1_0020101_01_00

DescriptionNose Landing Gear

FIGURE-09-10-16-991-002-A01

09-10-16Page 7

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_091016_1_0030101_01_00

ACTUATINGCYLINDERLOCK STAY

UNLOCKACTUATOR

SIDE STAY

TORQUE LINK

SHOCKABSORBER

MAIN FITTING

DescriptionTwin Wheel MLG (Sheet 1 of 2)FIGURE-09-10-16-991-003-A01

09-10-16Page 8

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_091016_1_0030102_01_00

ACTUATING CYLINDER

DOWNLOCKACTUATOR

LOCK STAY

LEG UNIT

SHOCK ABSORBER

BRAKE BAR

TORQUE LINK

STRUT ASSEMBLY

PITCH TRIMMER

DescriptionFour Wheel Bogie MLG (Optional A320 only) (Sheet 2 of 2)

FIGURE-09-10-16-991-003-A01

09-10-16Page 9

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

FR9

FR20

LEG DOOR

AFT DOORS

ROTATING RODASSY

FITTING

FWD DOORS

CONTROL ROD

DOORACTUATINGCYLINDER

BELL CRANK DOOR UPLOCKASSENBLY

DRAG STRUTASSY

GEAR UPLOCKASSEMBLY

N_AR_091016_1_0040101_01_00

DoorsNose Landing Gear (Sheet 1 of 3)FIGURE-09-10-16-991-004-A01

09-10-16Page 10

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_091016_1_0040102_01_00

MAIN DOOR(HYDRAULICALLY OPERATED)

FIXEDRAMPS

UPLOCKROLLER

ADJUSTABLERAMP

NOTE:MAIN DOOR SHOWN OPEN IN GROUND MAINTENANCE POSITION.

STEPS

FIXEDFAIRING

HINGEDFAIRING

HINGED FAIRING(MECHANICALLY OPERATED)

PROXIMITY SENSORS

DOOR ACTUATING CYLINDER

DoorsTwin Wheel MLG (Sheet 2 of 3)FIGURE-09-10-16-991-004-A01

09-10-16Page 11

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

N_AR_091016_1_0040103_01_00

NOTE:MAIN DOOR SHOWN OPEN IN GROUND MAINTENANCE POSITION.

HINGEDFAIRING

FIXEDFAIRING

DOOR ACTUATINGCYLINDER

AJUSTABLERAMP

UPLOCKROLLER

DOORRAMPS

STEPS

MAIN DOOR

DoorsFour Wheel Bogie MLG (Optional A320 only) (Sheet 3 of 3)

FIGURE-09-10-16-991-004-A01

09-10-16Page 12

Jul 01/09


09-20-01 QUICK REFERENCE DATA

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-20-01-001-A01

General

1. This chapter is broken down as follows:

A. Aircraft Recovery Logic Charts DESC 09-20-01-002-A01.

B. Aircraft Recovery Process Document DESC 09-20-01-004-A01.

C. IATA Aircraft Recovery Quick Reference Check List TASK 09-20-01-869-801-A01.

09-20-01Page 1

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-20-01-002-A01

Aircraft Recovery Logic Chart

NOTE : The charts are not in chronological sequence for recovery. Make a selection of the chartsapplicable to each recovery scenario.

1. See DESC 02-10-01-002-A01 for description of aircraft recovery charts and the way to use them.When you use these charts, the conditions that follow are assumed:- Warnings and cautions are not included on the recovery charts.- The aircraft operator has full responsibility for all the aircraft recovery operation.- The recovery operation can only start when the local and state Investigative Authorities release

the aircraft.- All company, local and state health and safety regulations are obeyed.- All hazardous materials are identified and correctly handled.- The standard ”Aircraft Status for Maintenance” is in general not available (see AMM 00

Introduction, Item 7).- The aircraft is possibly in an unusual attitude and can be unstable.- Some of the steps listed are possibly not in chronological sequence because each recovery

operation is different and the recovery procedure must be adapted.- It is possible that some of the steps listed are completed more than one time.

09-20-01Page 2

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

CHART I

NOTE: THE CHARTS ARE NOT IN A CHRONOLOGICAL SEQUENCE FOR A RECOVERY.

INCIDENT

PERSONNEL FROM THE AIRLINE,INVESTIGATIVE AUTHORITIESAND AIRPORT TO BE ADVISED

THE AIRCRAFT OPERATORHAS FULL RESPONSIBILITY

FOR THE RECOVERY

ADVISE INTERNALLY ACCORDINGTO AIRLINE PROCESSES

BASIC INCIDENT INFORMATION:−GET AND RECORD INITIAL DATA−FUEL ON BOARD−ANY HAZARDOUS MATERIALS−AIRCRAFT STATUS −CURRENT AND FORECAST WEATHER

RECOVERY MANAGER ASSUMESRESPONSIBILITY

RECOVERY TEAM SELECTED

PREPARE PERSONALEQUIPMENT

PREPARE LOCALAIRCRAFT

RECOVERYEQUIPMENT

COMMUNICATE WITHAIRPORT AND INVESTIGATIVE

AUTHORITIES, RECORD NAMES,POSITIONS AND CONTACT

NUMBERS

REMOVE FDR AND CVR PERINVESTIGATIVE AUTHORITIES

AIRCRAFT RELEASED BYINVESTIGATIVE AUTHORITY

GO TO CHART IIA

LIAISE WITHRECOVERYMANAGER

( )

SEE 01−00−00

SEE 09−20−02

N_AR_092001_1_0010101_01_00

SEE FIGURE 09−20−01−991−002

Aircraft Recovery Logic ChartChart I

FIGURE-09-20-01-991-001-A01

09-20-01Page 3

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

ARE THERE VISIBLE FLUIDLEAKS?

DOES THE AIRCRAFT HAVETO BE STABILIZED?

INITIAL SURVEY OF AIRCRAFT

STEPA

DO A CHECK FOR OBVIOUSSTRUCTURAL DAMAGE

STEPB

STEPC

STEPD

STEPE

LANDING GEAR STATUS

STEPF

IDENTIFY SIGNS OFDISTORTION, BUCKLING,CRACKING ETC.

IDENTIFY MISSINGCOMPONENTS SUCH ASLANDING GEAR, FLAPS,ETC.

GO TO CHART IX( )

AND GO TO STEP CSEE SRM 51−11−00

GO TO CHART IV STEP A( )

GO TO STEP D

GO TO CHART VI( )

GO TO STEP E

GO TO CHART XIII( )

GO TO CHART IIBSTEP G

YES

NO

YES

NO

SEE 02−40−01 FOR HEALTH& SAFETY DETAILS


CHART IIA

SEE FIGURE 09−20−01−991−009

SEE FIGURE 09−20−01−991−004

SEE FIGURE 09−20−01−991−006

SEE FIGURE 09−20−01−991−013

N_AR_092001_1_0020101_01_01

Aircraft Recovery Logic ChartChart IIA (Sheet 1 of 2)

FIGURE-09-20-01-991-002-A01

09-20-01Page 4

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

INITIAL SURVEY OF AIRCRAFT CONT’D

STEPG

WEIGHT AND CG POSITIONMANAGEMENT

STEPH

STEPI

ARE THERE ANY STRUCTURALCONCERNS?

STEPJ

ARE THERE ANY ENVIRONMENTALCONCERNS?

STEPK

( )

APPLICABLE AND GO TO STEP I

GO TO STEP D

GO TO STEP E

INSTALL PROTECTIVE COVERS:

( )


CHART IIB

ARE HAZARDOUS MATERIALSIDENTIFIED AND ARE THEY OFCONCERN?

FOR LOCALIZATIONSEE 09−10−05 AND

SEE 09−10−15

WILL THIS BE A LENGTHYRECOVERY?

YES

NO

YES

NO

YES

NO

YES

NO

GO TO STEP J

GO TO STEP I

GO TO CHART XI

AND COMPLETE WORKSHEETS(

IF

TO STEP JADVISE HAZMAT TEAM AND GO

TEAM AND GO TO STEP KADVISE HAZMAT RESPONSE

ENGINES, PITOT HEADS, ETC.AND GO TO CHART III

AND

N_AR_092001_1_0020103_01_00

SEE SRM 51−11−00

SEE 03−00−00 SEE 09−50−01)

SEE FIGURE 09−20−01−991−003

SEE FIGURE 09−20−01−991−011

Aircraft Recovery Logic ChartChart IIB (Sheet 2 of 2)

FIGURE-09-20-01-991-002-A01

09-20-01Page 5

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

CHART III


IS AIRCRAFT ECONOMICALLY RECOVERABLE?

MAKE THE DECISION WITHINPUT FROM THE OPERATOR,INSURANCE SURVEYER ANDAIRCRAFT MANUFACTURER

NOTE:

FURTHER NOTIFICATION

PREPARE FOR RECOVERYAFTER RELEASE BY INVESTIGATIVE AUTHORITIES

WILL SECONDARY DAMAGEBE ACCEPTABLE?

WHO WILL RECOVERAIRCRAFT?

AIRLINE CONTRACTOR AIRPORT

GO TO CHART VII

END

SIGN CONTRACT, MAKE SURETHAT ARM PROCEDURES AREFOLLOWED, RELEASE FORMSAND WAIVERS

ASSIGN AIRLINEREPRESENTATIVE TOOVERSEE RECOVERY ANDOBTAIN REPORT

NO YES

PROCEED AS "YES" UNTIL

( )

SEE 02−00−00

N_AR_092001_1_0030101_01_00

SEE FIGURE 09−20−01−991−007

Aircraft Recovery Logic ChartChart III

FIGURE-09-20-01-991-003-A01

09-20-01Page 6

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


CHART IV

IDENTIFY FLUID LEAKS

MAKE SURE AIRCRAFT IS CORRECTLY GROUNDED

"B" HYDRAULICOR ENGINE OIL"A" FUEL "C" LAVATORY "D" CARGO "E" WATER

ADVISE HAZMATTEAM TO IDENTIFY,

CONTAIN ANDREMOVE

ATTEMPT SPILLCONTAINMENT

DRAIN SYSTEM

DRAIN SYSTEM IFACCESS AVAILABLE

ATTEMPT SPILLCONTAINMENTIDENTIFY SOURCE

MAKE SUREHAZMAT TEAMAWARE OF ANYGROUND SPILLAGE

ATTEMPT SPILLCONTAINMENT

CAN LINES BECAPPED, VALVESBE CLOSED, ETC?

CAPPED, VALVESBE CLOSED,

HOLES PLUGGED,ETC.?

CAN LINES BE

DEFUEL OFAIRCRAFTBECOMESPRIORITY

GO TO"C"

GO TO"B"

DRAINSYSTEM

GO TO"D"

GO TO"E"

NOYES

YESNO

GO TO CHART X

GO TO CHART IIASTEP D

ISOLATEELECTRICALPOWER (SEE

CHART IX FOR DETAILS

IDENTIFY SOURCE

)(

( )

)

N_AR_092001_1_0040101_01_00

SEE FIGURE 09−20−01−991−010

SEE FIGURE 09−20−01−991−002

SEE FIGURE 09−20−01−991−009

Aircraft Recovery Logic ChartChart IV

FIGURE-09-20-01-991-004-A01

09-20-01Page 7

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

CHART V

REMOVALCATERING

CONTROLCG DURINGOFF−LOAD

CAN CARGO DOOR BEACCESSED?

YESNO

EXCAVATE/PREPARE ROADWAY TOALLOW ACCESS

TO DOOR

CAN ELECTRICALPOWER TO THE

AIRCRAFT BEESTABLISHED?

YESNO

CONTACT AIRBUS FORFURTHER INSTRUCTIONS

CANCARGO

DOOR BEOPENED

MANUALLY

NO

HOIST DOOR TOOPEN

CAN DOOR BEUNLOCKED

AND HOISTEDWITH A CRANE?

YES

NO

MANUALLYOPERATEDOORS

YES

OPERATE DOORSNORMALLY

CAN CARGOLOADING

SYSTEM (CLS)BE USED?

YES

NO

UNLOAD CARGOCOMPARTMENTS

CONTROL CGDURING OFF−LOAD

UNLOAD ASMUCH ASPOSSIBLE

MANUALLY (MAYBE NECESSARY

TO CUTCONTAINERSFOR ACCESS)

SEE 05−50−00

SEE 05−50−00

SEE 05−50−00

GO TO CHART VI STEP G( )

REMOVAL OF CARGO


N_AR_092001_1_0050101_01_00

SEE FIGURE 09−20−01−991−006

Aircraft Recovery Logic ChartChart V

FIGURE-09-20-01-991-005-A01

09-20-01Page 8

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

STEPA

MAKE SURE AIRCRAFT ISCORRECTLY GROUNDED

STEPB

STEPC

IS THIS STRAIGHTDEBOGGING?

STEPD

IS TETHERING/SHORINGREQUIRED?

STEPE

STEPF

CALCULATE ANTICIPATEDLOADS AND CONFIRM CGLOCATION

GO TO CHART XII( )

GO TO STEP D

YES

NO


CHART VI

STABILIZE AIRCRAFT

REMOVE CARGO ANDCATERING EQUIPMENT

GO TO CHART XIV( )

GO TO STEP E

YES

NO

GO TO CHART X( )

GO TO STEP F

YES

NO

STEPG

SEE 03−00−00

SEE 04−30−00

MAKE SURE CG IS CONTROLLED

REMOVE MAJORCOMPONENTS THAT AREDAMAGED OR NECESSARYFOR WEIGHT REDUCTIONOR CG CONTROL

SEE 04−20−00

GO TO STEP B

GO TO STEP C

IS IT NECESSARY TODEFUEL OR TRANSFERFUEL?

SEE 03−50−01

GO TO CHART V( )

GO TO CHART IIA STEP E( )

SEE FIGURE 09−20−01−991−012

SEE FIGURE 09−20−01−991−014

SEE FIGURE 09−20−01−991−016

SEE FIGURE 09−20−01−991−005

SEE FIGURE 09−20−01−991−002

N_AR_092001_1_0060101_01_01

Aircraft Recovery Logic ChartChart VI

FIGURE-09-20-01-991-006-A01

09-20-01Page 9

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


CHART VII

SELECT METHOD

SELECT RECOVERY TOOLING *

LIFTING BAGSPNEUMATIC

JACKS CRANECOMBINATIONSTEP−BY−STEP

LOADS AND RECORDCALCULATE EXPECTED

LOAD RECORDSCONTROL CG AND MONITOR

GO TO CHART VIII

CONFIRM SOIL STABILITY INTEGRITY OF LIFTING CONFIRM STRUCTURAL

SEE 06−60−00

SEE 06−10−00

SEE 06−00−00

SEE 03−00−00

SEE 04−50−00 *

( )

POINTS/AREAS *

* : BEFORE CONSIDERING WHICH LEVELING /LIFTING OPTION TO USE YOU MUST MAKE AN ACCURATE WEIGHT AND CG ANALYSIS − THIS WILL GIVE YOU THE OPTIMUM POSTIONS AND LOADS FOR THE LIFTING EQUIPMENT.

PREPARE TO LEVEL/LIFT AIRCRAFT

N_AR_092001_1_0070101_01_00

SEE FIGURE 09−20−01−991−008

Aircraft Recovery Logic ChartChart VII

FIGURE-09-20-01-991-007-A01

09-20-01Page 10

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


CHART VIII

AND FOLLOW LIFTINGPROCEDURE






FUSELAGEFWD

SECTION

FUSELAGEAFT

SECTION

CONTROL CG WITH BALLAST, FUEL, TETHERING ETC.

SELECT LIFTING ENTRY POINTS

CRANE

: THE INSTALLED BELLY FAIRINGLIMITS SLING/AIRBAG LIFTING POINTS

PNEUMATICLIFTING BAGS

WING JACKPOINT


CRANE ANDSLING


FWD JACKPOINT

WING

GO TO CHART XV

SEE 06−00−00

SEE 06−30−00SEE 06−60−00

SEE 06−40−00SEE 06−60−00

SEE 06−50−00SEE 06−60−00

SEE 06−40−00SEE 06−60−00

SEE 06−30−00SEE 06−60−00

SEE 06−40−00SEE 06−60−00

( )

CAUTION

PREPARE TO LIFT AIRCRAFT

SEE FIGURE 09−20−01−991−015

AND FOLLOW LIFTINGSEE 06−50−00SEE 06−60−00PROCEDURE

N_AR_092001_1_0080101_01_02

Aircraft Recovery Logic ChartChart VIII

FIGURE-09-20-01-991-008-A01

09-20-01Page 11

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

AIRCRAFT BATTERIES

IS THERE OBVIOUS STRUCTURAL DAMAGE AND/OR FUEL LEAKING?


CHART IX

IS IT BENEFICIAL TO LEAVEBATTERIES CONNECTED?

DISCONNECT AND ISOLATE

AS SOON AS AIRCRAFT ISSTABILIZED

BATTERIES (REMOVE IF POSSIBLE).

LEAVE BATTERIES

SURE BATTERIE MASTERIS OFF UNLESS IF NEEDED

CONNECTED BUT MAKEDISCONNECT AND

SOON AS AIRCRAFT ISSTABILIZED

ISOLATE BATTERIES, AS

YES

YES

NO

NO

GO TO CHART IIA STEP B( )

N_AR_092001_1_0090101_01_00

SEE FIGURE 09−20−01−991−002

Aircraft Recovery Logic ChartChart VIX

FIGURE-09-20-01-991-009-A01

09-20-01Page 12

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


CHART X

GO TO CHART IV STEP B

DEFUEL

CONSIDER LEAVING FUEL ONBOARD FOR CG CONTROL

SERVICEABLENORMAL PRESSURE DEFUEL WITH ALL AIRCRAFT SYSTEMS

SEE 05−40−01

DRAIN REMAINING FUEL

DEFUEL USING AN EXTERNAL WIRING HARNESS (EWH)

1.

2.

3.

FOR DETAILS

SEE 05−40−02

SEE 05−10−00

SEE 05−40−03SEE FIGURE 09−20−01−991−004( )

N_AR_092001_1_0100101_01_01

Aircraft Recovery Logic ChartChart X

FIGURE-09-20-01-991-010-A01

09-20-01Page 13

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


CHART XI

WEIGHT AND CG POSITION MANAGEMENT

GET THE REQUIRED DATA TO CALCULATE NRW ANDASSOCIATED CG POSITION

GET OEW (OR DOW) AND ASSOCIATED CG POSITION

CALCULATE EFFECT OF REMAINING FUEL QTY

CALCULATE EFFECT OF REMAINING/ADDED ITEMS

CALCULATE EFFECT OF LARGE COMPONENT MOVEMENT

CALCULATE EFFECT OF REMOVED/MISSING ITEMS

CALCULATE NRW AND ASSOCIATED CG POSITION

GO TO CHART IIB STEP H( )

AND COMPLETEWORKSHEETSSEE 05−30−00

(SEE 09−50−01

AND COMPLETEWORKSHEETS (SEE 09−50−01



SEE 03−50−01


SEE 03−00−00

SEE 03−50−01

SEE 03−50−01

SEE 03−50−01

)

)

)

)

)

N_AR_092001_1_0110101_01_00

SEE FIGURE 09−20−01−991−002

Aircraft Recovery Logic ChartChart XI

FIGURE-09-20-01-991-011-A01

09-20-01Page 14

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


CHART XII

SEE 07−20−00

SEE 07−40−00

DEBOGGING

CONFIRM WEIGHT AND CG LOCATION

CONFIRM NO FUEL LEAKS AND ALL LANDING GEARS INTACT

MAKE AIRCRAFT AS LIGHT AS PRACTICAL

WILL SOIL REQUIRE STABILIZING?

CONFIRM NOROADWAYPREPARATIONREQUIRED

PREPARE ROADWAY USINGGRAVEL, STEEL PLATES,PLYWOOD OR MATS ASNECESSARY

EXCAVATE AREA AROUNDLANDING GEAR

PREPARE TO TOW OR WINCHAIRCRAFT

GO TO CHART XV STEP A

SEE 03−00−00

CONSULT AIRPORT AUTHORITY FOR RECENT EXCAVATIONS

CONFIRM SOIL STABILITY USING APPROPRIATE METHOD

NO YES

( )SEE FIGURE 09−20−01−991−015

N_AR_092001_1_0120101_01_01

SEE 07−30−00

Aircraft Recovery Logic ChartChart XII

FIGURE-09-20-01-991-012-A01

09-20-01Page 15

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


CHART XIII

LANDING GEAR

SEE 02−30−01

5

4

3

2

1 NLG RETRACTED, COLLAPSED OR MISSING

ONE MLG RETRACTED,

INSTALL LANDING GEARLOCKS

COLLAPSED OR MISSING

ALL LG RETRACTED, COLLAPSED OR MISSING

ALL MLG RETRACTED,COLLAPSED OR MISSING

NLG AND ONE MLGRETRACTED, COLLAPSED OR MISSING

CONFIRM LANDING GEARSECURE

GO TO CHART IIA STEP F( )

GO TO CHART IIA STEP F( )

SEE 06−60−01

SEE 06−60−03

SEE 06−60−02

SEE 06−60−04

SEE 06−60−05

YESNOARE ALL LANDING GEARS DOWN AND LOCKED?

N_AR_092001_1_0130101_01_00

SEE FIGURE 09−20−01−991−002

SEE FIGURE 09−20−01−991−002

Aircraft Recovery Logic ChartChart XIII

FIGURE-09-20-01-991-013-A01

09-20-01Page 16

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


CHART XIV

TETHERING / SHORING

FORDETAILS

ATTACH TETHERS TODOORWAYSFIXTURES, FLAPBEAMS AND LANDINGGEAR

PREPARE SHORING IF REQUIRED

SELECT APPROPRIATE TETHERCABLES

ATTACH FITTINGS TOAIRCRAFT

INSTALL GROUND ANCHORS

INSTALL TENSIONING DEVICESMONITOR AND RECORD LOADS

ARE TETHERING FITTINGS AVAILABLE?

GO TO CHART VI STEP E( )

SEE 04−30−00 SEE 04−30−00

SEE 04−30−00

NO YES

N_AR_092001_1_0140101_01_00

SEE FIGURE 09−20−01−991−006

Aircraft Recovery Logic ChartChart XIV

FIGURE-09-20-01-991-014-A01

09-20-01Page 17

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

YES "A" ARE ALL LANDING GEARSSERVICEABLE?


CHART XVTOWING

CALCULATE PROJECTED LOADS

ATTACH SHACKLES TO MAINLANDING GEAR TOW LUGS

PREPARE AND ATTACH CABLESFOR TOWING AND WINCHING

ARRANGE PULLEY IF REQUIRED

ATTACH DYNAMOMETER TOCABLE SYSTEM

USE APPROPRIATE MEANS TO STEER NOSE GEAR

PULL AIRCRAFT STEADILY BACKON TO HARD SURFACE

RECORD BREAK−AWAY ANDPULLING FORCES FROM

DYNAMOMETER

FOR DETAILS ON MOVINGAIRCRAFT

MOVE AIRCRAFT TOINSPECTION FACILITY

MAKE SURE SITE RETURNEDTO NORMAL

PREPARE REPORT

SEE 07−40−04

SEE 08−00−00END

NO "B"

SEE 07−60−00

SEE 07−40−00

N_AR_092001_1_0150101_01_01

Aircraft Recovery Logic ChartChart XV

FIGURE-09-20-01-991-015-A01

09-20-01Page 18

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-20-01-004-A01

Airline Aircraft Recovery Process Document

1. Airlines should consider the preparation of an internal Aircraft Recovery Process Document. Thisdocument will help the airline to prepare for an aircraft recovery, because it will contain fullinstructions about how to organize and prepare for a good recovery.It must give the steps on how each airline can do an aircraft recovery, from the time an incident isnotified, to the movement of the aircraft to an inspection or repair facility.Help to prepare a process document of this type is available if you contact the IATA AircraftRecovery Working Group at the website that follows:- http://www.iata.org


A. Proposed Coverage

(1) The goals of the Aircraft Recovery Team, these should be clearly stated. Some ideas toinclude are:- How the Recovery Team can react,- What authority the Recovery Team has,- The promotion of aircraft recovery awareness,- How to share aircraft recovery data with the manufacturer, other operators and special

interested groups,- Coordination of resources.

(2) A current and up-to-date list of the Recovery Team Managers and Recovery TeamLeaders.This must include office, home, fax, pager and cell phone numbers. The same informationshould be available for all other members of the recovery team.

(3) A list of applicable aircraft to recover by the Recovery Team.This could include aircraft owned or leased by the airline and aircraft from subsidiaryairlines and/or contracted airlines.

(4) Procedures to follow when there is a known incident.These must highlight the need to keep and record all important data.

(5) Current list of applicable government agencies with contact numbers.

(6) How each team member can prepare.This must include suggestions on what items of clothing and equipment should beavailable in a personal ”go kit”. Vaccinations and visas should also be done.

(7) A full list of airline support staff and contact numbers.This should include structural and power plant engineering staff, tooling and equipmenttechnicians, weight and balance, purchasing and logistic personnel.

09-20-01Page 19

Jul 01/09


(8) A current and full list of all company-owned aircraft recovery equipment.This should include the location, size and weight of all containers in where the equipmentis stored.

(9) A current copy of the IATP D/E pools ground handling equipment, ground maintenanceequipment and aircraft recovery kits.These data are now available at the website that follows:- http://www.iatp.com


NOTE : This chapter gives references to web sites for information only. Airbus shall notbe held liable for web site or document content and for update or change ofaddresses.

(10) A list of the local availability of general aircraft recovery materials and equipment. made bythe company.This list should include materials and equipment such as plywood and steel sheets, crushedrock, cribbing, cranes, heavy equipment etc.You can be prepare this list with the ICAO Removal of disabled aircraft Document 9137-AN/898 as a guide.

(11) An Aircraft Recovery Manual (ARM) for each fleet type operated and its storage locations.

(12) The size of the cargo doors of each fleet type operated.This will helps to move equipment if the incident is at a different airport.

(13) A list of all company-owned tooling, that includes recovery tooling such as pneumaticlifting bags, jacks, slings, etc.This can include their location and properties such as capacity, compressed and extendedheights, arc movement capability, etc.

09-20-01Page 20

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-20-01-005-A01

Off Runway Incident Reporting Proforma

1. GeneralThis ”Off-Runway” Incident Form is designed to support the evaluation of ”off runway” in-serviceincidents. It helps to make technical judgement and to decide the quickest disposition of actionsnecessary to return the aircraft landing gear to service.

09-20-01Page 21

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

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09-20-01Page 22

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

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09-20-01Page 23

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

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Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

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09-20-01Page 25

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

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Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

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Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

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: A32

0 O

NLY

− O

PT

ION

AL

01

01

01 01 01 01

01

N_A

R_0

9200

1_1_

0200

108_

01_0

0


FIGURE-09-20-01-991-020-A01

09-20-01Page 29

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DE

SC

RIP

TIO

N O

F T

NE

RE

CO

VE

RY

(S

UP

PLY

PH

OT

OG

RA

PH

S):

SE

CT

ION

6

N_A

R_0

9200

1_1_

0200

109_

01_0

0


FIGURE-09-20-01-991-020-A01

09-20-01Page 30

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TASK 09-20-01-869-801-A01

IATA Aircraft Recovery Quick Reference Check List

1. GeneralThis guide was prepared and given by the IATA Aircraft Recovery Working Group. It is a generalguide and for use as a checklist during an aircraft recovery incident.



4. Procedure

Subtask 09-20-01-869-001-A01

A. Before you are on the site

(1) Get the initial information about the incident.

(2) Contact local airline/agent/own representative.

(3) Prepare and make a selection of personnel/equipment/manuals.

(4) Check availability of IATP-kits and order if necessary.


Subtask 09-20-01-869-002-A01

B. When you are on the site

(1) Make necessary contact with local security/fire fighting brigade to secure the site, and givearea map.

(2) Give careful instructions for an aircraft recovery plan.

(3) Get necessary approval from local authorities to start the recovery operation.

(4) Make sure:

(a) Communication to/from site works correctly,

(b) Transportation to/from site is possible,

(c) Necessary accommodation and facilities can be available on site.

(5) Contact local airlines, airport authorities and local suppliers for help with.

(a) Heavy machinery/cranes, etc.

(b) Access roads, building materials.

(c) Timber/gravel/sand/steel plates, etc.

09-20-01Page 31

Jul 01/09


(d) Lighting equipment.

(6) Remove all necessary weight possible from the aircraft if needed.

(a) Make sure there are documents on restricted articles and hazardous material.

(b) Remove fuel and liquids if possible.

(c) Remove baggage and cargo if possible.

(d) Remove all unwanted and discarded material from the galleys and lavatories.

(7) Calculate the aircraft weight and CG.

(8) Make sure the recovery plan is still valid and all safety precautions have been taken.

(9) Remove all necessary aircraft components if needed.

(a) To lighten aircraft,

(b) To keep wind-induced loads to a minimum,

(c) To observe instructions from local authorities.

(10) Make preparation for

(a) Tethering/Shoring.

(b) Leveling/Lifting.

(c) Moving the aircraft.

(11) Prepare to put the aircraft in a hangar or to park it.

09-20-01Page 32

Jul 01/09


09-20-02 RECOVERY TEAM

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-20-02-001-A01

Composition of the Recovery Team

1. GeneralAirbus recommends that each airline:- Prepare an internal Aircraft Recovery Process document (see DESC 09-20-01-004-A01).- Make an Aircraft Recovery Team, with reference to this document.For this team, it is recommended:- To take the volunteers from the aircraft maintenance branch. These volunteers should have a

strong interest in the aircraft recovery process and a good technical background.- That the members of the Aircraft Recovery Team stay a part of the team (even when they have

promotions or move to different internal departments) so that their experience is not lost.

2. The ManagerAirbus recommends that each Aircraft Recovery Team have a manager to control the activities of theAircraft Recovery Team and any aircraft recovery incidents.

A. The Manager should have:- Experience as an Aircraft Maintenance Production Manager with the related responsibilities,- Experience and/or knowledge related to aircraft recovery.

B. The Manager should:- Supervise the Aircraft Recovery Team and their related activities,- Organize regular meetings and exercises with the Aircraft Recovery Team,- Be the interface with the airport, local and state authorities for aircraft recovery,- Represent his airline, on the International Airline Transport Association’s (IATA), Aircraft

Recovery Working Group (ARWG) and the International Airline Technical Pool (IATP)related to aircraft recovery.

3. Team LeadersDepending on the size of the airline, there can be one or more Team Leaders.

A. The Team Leaders should have:- Experience as an Aircraft Maintenance Production Team Leader or Foreman,- Good technical and leadership qualities,- Experience and/or knowledge of aircraft recovery,- Good knowledge of jacks, pneumatic lifting bags and cranes.

B. The Team Leaders should:- Report to the Aircraft Recovery Manager,- Control the company-owned aircraft recovery equipment and make sure that it is always

serviceable,

09-20-02Page 1

Jul 01/09


- Make recommendations and suggestions related to the purchase of aircraft recoveryequipment,

- Supervise the on-site aircraft recovery steps.

4. Structures Engineer and Systems EngineerThe Structure Engineer and Systems Engineer should:- Analyze damage to the aircraft,- Prepare the drawings necessary for temporary repairs,- Help the Recovery Manager and Team Leader with decisions related to aircraft recovery.

5. Planner or Purchasing AgentThe Planner or Purchasing Agent should:- Know how to get access to the nearest aircraft recovery kit,- Have contact information for local heavy equipment operators,- Know where to get general aircraft recovery materials,- Organize the leasing of equipment when necessary.

6. Licensed Aircraft TechniciansThe Licensed Aircraft Technicians should:- Have good technical knowledge,- Have a valid aircraft maintenance license for the specific aircraft type.- Report to the Aircraft Recovery Team Leader,- Do the specific aircraft maintenance tasks assigned by the Team Leader.

09-20-02Page 2

Jul 01/09


09-30-01 AIRCRAFT RECOVERY EQUIPMENT TOOLING AND MATERIALS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-30-01-001-A01

General

1. GeneralIt can be necessary for operators to use tools during the recovery process.There are two categories of aircraft recovery tooling and equipment:- General recovery equipment- Specialized recovery equipmentYou can get these tools at the airport (contact the Airport Authorities or IATP if you are a member),or locally (contact local vendors).

2. General Materials, Equipment and ToolingThe general materials, equipment and tooling that follow are usually available locally (this is not afull list) :- Work lights, floodlights,- Ballast bags,- Sheets of plywood, steel plate, planking, etc.,- Cribbing timber (railroad ties) to make platforms,- Stones, gravel, broken asphalt to be compacted to make roadways,- Trailers and padded materials (mattresses, rubber padding, tires, sandbags) to move damaged

aircraft,- Bulldozers, forklifts, crane, winching vehicles, excavators,- Towing tractor,- Cables, ropes, pulley blocks, ladders,- Mobile shelter-trailer, commercial transport equipment,- Wooden/steel beams,- Flatbed trucks and trailers,- Pumps, hoses and storage for fuel and/or water,- Hand pump for manual doors opening/closing,- On-site communication equipment (telephones, faxes, interphone headsets),An electrical or air power supply can be necessary for some of these tools. Thus, other equipment canbe necessary:- Mobile electrical power unit (min. 5 kW),- Mobile air power unit (min. 7 bar (102 psi)).

NOTE : The ICAO Airport Services Manual, part 5, Document 9137-AN/898, ”Removal of DisabledAircraft” gives a list of recommended materials and equipment.

3. Lifting and Tethering MaterialThe general materials, equipment and tooling that follow will be useful for the lifting and tethering ofthe aircraft.

09-30-01Page 1

Jul 01/09


A. Slings/straps - Nylon, Dacron, Carbon FiberThese slings/straps are moisture and mildew resistant. As they dry quickly, it is possible to putthem into storage a short time after use.You can get them in almost all widths and lengths with different end attachments. You can getnylon straps/slings with single or double strength with single or multiple bands.All these slings/straps help prevent damage to the aircraft skins when you lift the aircraft atareas such as the forward fuselage. But it is important to protect the straps from sharp edgesand small radiuses.Make sure that the slings/strap has a label, which gives the rate loads.Do an inspection of the straps before you use them.

B. Wire RopeUsually, a 6X19 type rope made from improved plow strength steel can be used for recoveryoperations.

C. ChainAll types of hoisting chains made from good quality material will give very good results.

D. Rope - Manila, Nylon, PolypropyleneThese are good general-purpose ropes but they are not recommended for lifting or tetheringtasks.

09-30-01Page 2

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-30-01-002-A01

Airbus Specific Recovery Tools

1. For the wing lifting procedure using cranes (see 06-50-00), Airbus developed a specific tool, seeTABLE 1.

TOOL - DESCRIPTION (PART NUMBER) QTY VENDOR

7K804427D520 CRANE ATTACHMENT - WINGLIFTING BRACKET

2

Airbus Specific Recovery Tools

TABLE 1

09-30-01Page 3

Jul 01/09


09-30-02 AIRCRAFT RECOVERY TOOLING

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-30-02-001-A01

General

1. Table 1 gives the list of tools referenced in the ARM.

NOTE : Any comparable equipment may be used provided that it satisfies the requirements of theprocedure. Other conventional suppliers of recovery material can provide items of the kitsset.

09-30-02Page 1

Jul 01/09


PART NUMBER NOMENCLATURE VENDOR/SUPPLIER REFERENCES

460005833 GROUND LOCK SLEEVE TASK 02-30-01-481-801-A01

460005835 GROUND LOCK SLEEVE TASK 02-30-01-481-801-A01

460007280 SLEEVE-GROUNDLOCK TASK 02-30-01-481-801-A01

7K804427D520 CRANE ATTACHMENT - WING LIFTING BRACKET TASK 06-50-00-581-802-A01DESC 09-30-01-002-A01

97A28002117002 PURGING TOOL TASK 05-40-02-650-801-A01

98A09003000001 BAR-STEERING, NOSE WHEEL TASK 07-40-02-584-802-A01

98A28104000000 PURGER WATER DRAIN TASK 03-20-02-970-801-A01

98A28104000002 TOOL - PURGING TASK 05-40-02-650-801-A01

98A28203000000 TEST EQUIPMENT JET PUMP TASK 05-40-02-650-801-A01

98D07103000000 DYNAMOMETER - SAFETY STAY TASK 06-30-00-581-802-A01

98D07103500000 JACK ADAPTER - FUSELAGE TASK 06-30-00-581-802-A01

98D07104081000 JACKING PAD SET (A321) TASK 06-30-00-581-802-A01

98D07203000 MOORING FITTING DESC 04-30-00-001-A01TASK06-50-00-581-803-A01

09-30-02Page 2

Jul 01/09



98D07203003 FUSELAGE SHORING CRADLE TASK 06-50-00-581-801-A01

98D09104000001 ATTACHMENT - TOWING TASK 07-40-02-584-801-A01

98D09104001000 ATTACHEMENT-TOWING TASK 07-40-02-584-802-A01

98D09104002000 ATTACHMENT - TOWING (OPTIONAL 4 WHEELBOGIE MLG)

TASK 07-40-02-584-802-A01TASK07-40-02-584-801-A01

98D10203500 MOORING KIT - NLG TASK 04-30-00-556-801-A01

98D104000001 JACKING PAD SET (A318, A319, A320) TASK 06-30-00-581-802-A01

98D32203502000 SAFETY PIN - NLG DOOR TASK 02-30-01-481-801-A01

98D57004031 WING SHORING CRADLE TASK 06-50-00-581-801-A01

98F09103500000 CABLE-TOWING, MLG TASK 07-40-02-584-802-A01TASK07-40-02-584-801-A01

D23080000 PIN-GROUND LOCK, NLG TASK 02-30-01-481-801-A01

D23156000 PIN-SAFETY TASK 07-40-02-584-802-A01TASK07-40-01-584-802-A01TASK07-40-02-584-801-A01TASK07-40-01-584-801-A01

09-30-02Page 3

Jul 01/09



DAH602734 GROUND LOCK SLEEVE TASK 02-30-01-481-801-A01

DRT68031 SLEEVE - GROUND LOCK TASK 02-30-01-481-801-A01

DRT68923 SLEEVE-GROUND LOCK TASK 02-30-01-481-801-A01

GSE WHEEL CHANGE JACK TASK 02-30-01-867-802-A01

MZ23080000 PIN - NLG DOWNLOCK SAFETY TASK 02-30-01-481-801-A01

TMHCP07-00-00 WHEEL CHANGE AXLE JACK TASK 02-30-01-867-802-A01

Tools and Equipment

TABLE 1

09-30-02Page 4

Jul 01/09


09-30-03 IATP AIRCRAFT RECOVERY KITS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-30-03-001-A01

General

1. IATP Recovery KitsThe International Airline Technical Pool provides a number of aircraft recovery kits at strategiclocations around the world.Currently, there are ten of these kits and they are maintained by provider airlines.

NOTE : The kits are also available on a rental basis to non-member operators.Information on kits content, purpose, capability, providers locations etc. should be available from:- http://www.iatp.com



2. Location of the Main KitsCurrent locations of the IATP kits and their provider are given in TABLE 1:

London, England LHR British Airways

Paris, France ORY Air France

Johannesbourg, South Africa JNB South African Airways

Tokyo, Japan NRT Japan Airlines

New York, USA JFK Delta Airlines

Chicago, USA ORD American Airlines

Los Angeles, USA LAX American Airlines

Honolulu, USA HNL United Airlines

Sydney, Australia SYD Qantas Airlines

Mumbai, India BOM Air India

IATP Recovery Kits

TABLE 1

The TABLE 2 gives details on kit suppliers and contacts.

09-30-03Page 1

Jul 01/09


COMPANY CODE KITLOCATION

GIVENNAME

FAMILYNAME

SITACODE

MAILINGADDRESS

AmericanAirlines

AA LAXORD

Julie McClain HDQTPAA American Airlines3800 N. Mingo Rd. MD523Tulsa OK 74158

Air France AF ORY Philippe Guillem ORYJOAF Air FranceOrly Sud 124F-94396 Orly AerogareCedex

Air India AI BOM KG Shekar BOMELAI Air India Line Stations,Engineering DeptOld AirportKALINA MAHARASTRA400029 INDIA

BritishAirways

BA LHR Brian Deacon LHRKEBA British Airways PLCBA Maintrol3rd Floor Europe HouseWaterside, PO Box 365HARMONDSWORTHWEST DRAYTON UB70GB

DeltaAirlines

DL JFK Terry Lucas ATLTEDL Delta AirlinesP.O. BOX 20706ATLANTA GA 30320 USA

JapanAirlines

JL NRT Satoru Arasaki TYOJPJL Japan Airlines3-5-1, HANEDAAIRPORTM1 BLDGOTA-KU TOKYO144-0041

Qantas QF SYD Jean-Marie

L’Eveille SYDEDQF Qantas Airways LtdSydneyDistribution CenterSYDSDC/1263-271 Coward RoadMascot N.S.W 2020AUSTRALIA

09-30-03Page 2

Jul 01/09


COMPANY CODE KITLOCATION

GIVENNAME

FAMILYNAME

SITACODE

MAILINGADDRESS

SouthAfrican

SA JNB Charlie Haman JNBMPSA South AfricanSouth Africa AirwaysTechnicalTechnical AreaJOHANNESBURGInternational Airport

UnitedAirlines

UA HNL Connie Showalter SFOPSUA United AirlinesS.F. Maintenance Base -SFOUSSan Fransisco InternationalAirportSAN FRANSISCO CA94128 USA

Kit Suppliers and Contacts

TABLE 2

09-30-03Page 3

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-30-03-002-A01

Example of IATP Recovery Kit

1. This section gives an example of an IATP recovery kit that can be found at main airports. It is onlyan example and does not reflect the exact content of all main IATP kits.TABLE 1 gives an example of basic recovery kit.TABLE 2 gives an example of supplementary kit.

Quantity Description

90 PNEUMATIC BAGS (SINGLE ELEMENT)

1 MASTER CONTROL CONSOLE5 REMOTE CONTROL CONSOLE5 AIR DISTRIBUTORS6 MANIFOLD (CONTROL CONSOLE)

85 PNEUMATIC HOSES6 WINCHES6 WIRE ROPES6 EARTH ANCHORS16 PLASTIC FOAM PROTECTION PADS (50 mm (2 in) thick)

1 ROLL POLYTHENE SHEET (500 gauge, 7.3 m (287 in) wide)

1 AIR COMPRESSOR2 REGENT TRIPOD CRASH JACKS

Capacity - 710 mm (28 in) to 1730 mm (68 in), 80 tonsCapacity - 1730 mm (68 in) to 3560 mm (140 in), 100 tons

1 COMPRESSOR SPARES AND BAG REPAIR KIT

Basic Recovery Kit

TABLE 1


2 PNEUMATIC BAGS2 PNEUMATIC HOSE REELS4 MANIFOLD CONTROL CONSOLE / AIR CONTROL CONSOLE WITH 10

OUTLETS4 PROTECTION PADS4 WIRE ROPE (CAPACITY OF TOWING A CODE E/F AIRCRAFT)

2 BODY LIFTING SLING (CAPACITY OF LIFTING A CODE E/F AIRCRAFT )

1 AIR COMPRESSOR (FOR SYNCRO JACKS)

2 SPREADER BARS (INCLUDES SLINGS AND SHACKLES)

09-30-03Page 4

Jul 01/09



1 AIR COMPRESSOR

Supplementary Recovery Kit

TABLE 2

09-30-03Page 5

Jul 01/09


09-50-01 WEIGHT AND CG CALCULATION WORKSHEETS

**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

DESC 09-50-01-001-A01

Worksheets

1. GeneralIt is necessary to use these worksheets in relation with chapter 03-50-01.

A. Interim Worksheet:- Fuel Remaining on Board Effect. See FIGURE 09-50-01-991-001-A.- Cargo and Baggage Remaining Effect. See FIGURE 09-50-01-991-002-A.- Total Traffic Load Remaining Effect. See FIGURE 09-50-01-991-003-A.- Ballast Added Effect. See FIGURE 09-50-01-991-004-A.- Waste Water Remaining Effect. See FIGURE 09-50-01-991-005-A.- Non OEW Catering Equipment Added Effect. See FIGURE 09-50-01-991-006-A.- Large Component Movement Effect. See FIGURE 09-50-01-991-007-A.- Potable Water Removed Effect. See FIGURE 09-50-01-991-008-A.- Cockpit and Cabin Crew Removed Effect. See FIGURE 09-50-01-991-009-A.- Catering Equipment Removed Effect. See FIGURE 09-50-01-991-010-A.- Large Component Removed/Missing Effect. See FIGURE 09-50-01-991-011-A.- Hydraulic Fluids Removed Effect. See FIGURE 09-50-01-991-012-A.

B. NRW & Related H & Y Moment Worksheets- NRW & Related H, & Y Moment Worksheet Calculation from OEW. See FIGURE

09-50-01-991-013-A.- NRW & Related H, & Y Moment Worksheet Calculation from DOW. See FIGURE

09-50-01-991-014-A.

09-50-01Page 1

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

LH OUTER TANK

LH INNER TANK

CENTER TANK

CENTER TANK

RH INNER TANK

MOMENTWeight x H−arm

(kgm or lb.in)

WEIGHT(kg or lb)

MOMENTWeight x Y−arm

(kgm or lb.in)

TO TO TO TOSUBTRACT ADD SUBTRACT ADD

TO TOSUBTRACT ADD

TOTAL

RH OUTER TANK

N_AR_095001_1_0010101_01_00

AUXILIARY

Interim WorksheetFuel Remaining on Board EffectFIGURE-09-50-01-991-001-A01

09-50-01Page 2

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TO

WEIGHT(kg or lb)

TO TO TOTO TOADDSUBTRACT SUBTRACT SUBTRACTADD ADD

TOTAL FORWARDCARGO

REMAININGEFFECT

TOTAL AFTCARGO

REMAININGEFFECT

TOTAL BULKCARGO

REMAININGEFFECT

TOTAL


(kgm or lb.in)


(kgm or lb.in)

N_AR_095001_1_0020101_01_00

Interim WorksheetCargo and Baggage Remaining Effect

FIGURE-09-50-01-991-002-A01

09-50-01Page 3

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TO

WEIGHT(kg or lb)


TOTAL TRAFFICLOAD

REMAINING

TOTAL


(kgm or lb.in)


(kgm or lb.in)

N_AR_095001_1_0030101_01_00

Interim WorksheetTotal Traffic Load Remaining Effect

FIGURE-09-50-01-991-003-A01

09-50-01Page 4

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT(kg or lb)

SUBTRACTTO TO

ADD SUBTRACTTO TO

ADD SUBTRACTTO TO

ADD

L/H WINGBALLAST

ADDED EFFECT

R/H WINGBALLAST

ADDED EFFECT

MAIN DECKBALLAST

ADDED EFFECT

FORWARD CARGOBALLAST

ADDED EFFECT

AFT CARGOBALLAST

ADDED EFFECT

BULK CARGOBALLAST

ADDED EFFECT

TOTAL


(kgm or lb.in)


(kgm or lb.in)

N_AR_095001_1_0040101_01_00

Interim WorksheetBallast Added Effect

FIGURE-09-50-01-991-004-A01

09-50-01Page 5

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WASTE WATERREMAINING

TO

WEIGHT(kg or lb)


TOTAL


(kgm or lb.in)


(kgm or lb.in)

N_AR_095001_1_0050101_01_00

Interim WorksheetWaste Water Remaining EffectFIGURE-09-50-01-991-005-A01

09-50-01Page 6

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT(kg or lb)

SUBTRACTTO TO

ADD SUBTRACTTO TO

ADD SUBTRACTTO TO

ADD

NON OEWCATERING

EQUIPMENTEFFECT

TOTAL


(kgm or lb.in)


(kgm or lb.in)

N_AR_095001_1_0060101_01_00

Interim WorksheetNon OEW Catering Equipment Added Effect

FIGURE-09-50-01-991-006-A01

09-50-01Page 7

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT(kg or lb)


(kgm or lb.in)


(kgm or lb.in)

TOSUBTRACT

TOADD

NLG RETRACTIONEFFECT

LH MAIN LGRETRACTION

EFFECT

RH MAIN LGRETRACTION

EFFECT

TOTAL

SLATS/FLAPSEXTENSION

EFFECT

N_AR_095001_1_0070101_01_01

TOSUBTRACT

TOADD

TOSUBTRACT

TOADD

Interim WorksheetLarge Component Movement Effect

FIGURE-09-50-01-991-007-A01

09-50-01Page 8

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT(kg or lb)

SUBTRACTTO

ADDTO

SUBTRACTTO

ADDTO

SUBTRACTTO

ADDTO

TOTAL

POTABLE WATERREMOVED

EFFECT


(kgm or lb.in)


(kgm or lb.in)

N_AR_095001_1_0080101_01_00

Interim WorksheetPotable Water Removed EffectFIGURE-09-50-01-991-008-A01

09-50-01Page 9

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

TO

WEIGHT(kg or lb)

TO TO TOTO TOADD

COCKPIT CREWREMOVED

EFFECT

CABIN CREWREMOVED

EFFECT

SUBTRACT SUBTRACT SUBTRACTADD ADD

TOTAL


(kgm or lb.in)


(kgm or lb.in)

N_AR_095001_1_0090101_01_00

Interim WorksheetCockpit and Cabin Crew Removed Effect

FIGURE-09-50-01-991-009-A01

09-50-01Page 10

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

SUBTRACTTO

SUBTRACTTO

SUBTRACTTO

ADDTO

ADDTO

ADDTO

CATERINGEQUIPMENT

TOTAL

WEIGHT(kg or lb)


(kgm or lb.in)


(kgm or lb.in)

N_AR_095001_1_0100101_01_00

Interim WorksheetCatering Equipment Removed Effect

FIGURE-09-50-01-991-010-A01

09-50-01Page 11

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200


(kgm or lb.in)

WEIGHT(kg or lb)


(kgm or lb.in)

SUBTRACTTO TO

ADD SUBTRACTTO TO

ADD SUBTRACTTO TO

ADD

LH WING COMPONENT

REMOVED/MISSING EFFECT

RH WING COMPONENT


FUSELAGE COMPONENT


FIN COMPONENT REMOVED/

MISSING EFFECT

THS COMPONENT REMOVED/

MISSING EFFECT

TOTAL

N_AR_095001_1_0110101_01_00

Interim WorksheetLarge Component Removed/Missing Effect

FIGURE-09-50-01-991-011-A01

09-50-01Page 12

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

WEIGHT(kg or lb)

TO TO TO TOSUBTRACT ADD SUBTRACT ADD

TOTAL HYDRAULIC

FLUIDS REMOVEDEFFECT

TOTAL

TO TOSUBTRACT ADD


(kgm or lb.in)


(kgm or lb.in)

N_AR_095001_1_0120101_01_00

Interim WorksheetHydraulic Fluids Removed EffectFIGURE-09-50-01-991-012-A01

09-50-01Page 13

Jul 01/09


**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

SUBTRACTTO TO

ADD


(kgm or lb.in)

WEIGHT(kg or lb)


(kgm or lb.in)

SUBTRACTTO TO

ADD SUBTRACTTO TO

ADD

NON OEW CATERINGEQUIPMENT ADDED

EFFECT

LARGE COMPONENTREMOVED/MISSING

EFFECT

OEW

FUEL REMAINING ONBOARD EFFECT

CARGO AND BAGGAGEREMAINING EFFECT

TOTAL TRAFFIC LOADREMAINING EFFECT

BALLAST ADDED EFFECT

WASTE WATERREMAINING EFFECT

LARGE COMPONENTMOVEMENT EFFECT

POTABLE WATERREMOVED EFFECT

COCKPIT AND CABINCREW REMOVED EFFECT

CATERING EQUIPMENTREMOVED EFFECT

HYDRAULIC FLUIDSREMOVED EFFECT

TOTAL

− − −

===

RESULTS

NRW(kg or lb)

H−arm

(kgm ormoment

Y−arm

(kgm ormoment

lb.in) lb.in)N_AR_095001_1_0130101_01_00

NRW & Related H, & Y Moment WorksheetsNRW & Related H, & Y Moment Worksheet Calculation from OEW

FIGURE-09-50-01-991-013-A01

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**ON A/C A318-100 A319-100 A320-100 A320-200 A321-100 A321-200

SUBTRACTTO TO

ADD

WEIGHT(kg or lb)

SUBTRACTTO TO

ADD SUBTRACTTO TO

ADD

DOW

= = =

RESULTS

LARGE COMPONENTREMOVED/MISSING

EFFECT

FUEL REMAINING ONBOARD EFFECT

CARGO AND BAGGAGEREMAINING EFFECT

TOTAL TRAFFIC LOADREMAINING EFFECT

BALLAST ADDED EFFECT

WASTE WATERREMAINING EFFECT

LARGE COMPONENTMOVEMENT EFFECT

POTABLE WATERREMOVED EFFECT

COCKPIT AND CABINCREW REMOVED EFFECT

CATERING EQUIPMENTREMOVED EFFECT

HYDRAULIC FLUIDSREMOVED EFFECT

TOTAL

− − −


(kgm or lb.in)


(kgm or lb.in)

NRW(kg or lb)

H−arm

(kgm ormoment

Y−arm

(kgm ormoment

lb.in) lb.in)

N_AR_095001_1_0140101_01_00

NRW & Related H, & Y Moment WorksheetsNRW & Related H, & Y Moment Worksheet Calculation from DOW

FIGURE-09-50-01-991-014-A01

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ARM_A318_A319_A320_A321_20090701

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