ENGINEERING ORDER N° IM A319/A320-32/1555webapp.ifrskeyes.com/GED/AMSFSKUPRD/(1555)...

ENGINEERING ORDER N° IM A319/A320-32/1555

WORK ORDER: …………….

ITEM NUMBER: …………….

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PART LIST

ITEM QTY PART NUMBER DESCRIPTION REMARK

01 1 LB VV-P-236A Pure Mineral Vaseline Or Petrolatum CONF 002 and 010

02 1 LB Finish F69 Blue Electrical Bonding Coating (Blue Color) CONF 002 and 010

03 1 LT MIL-PRF-680 Dry Cleaning Solvent(Varsol/White Spirit) CONF 002 and 010 04 01 321346A01R02 Kit (Bundle, placard set, LGCIU plate, C/B)

Rela), fasteners CONF 002 and 010

05 01 321346A03R01 Kit (Placard) CONF 002

06 01 321346A06R00 Kit (Placard) CONF 010

07 01 321346A11R00 Kit (Bundle) CONF 002 and 010

08 01 EN3155-017F1616 Socket-Contact CONF 002 and 010

OR EN3155-017F1216 Socket-Contact I/W ITEM 08 (Part list)

TOOL LIST

ITEM QTY PART NUMBER DESCRIPTION REMARK

NOT REQUIRED

TABLE 1

MSN REGISTRATION COMPLY PRIOR TO MSN REGISTRATION COMPLY PRIOR TO

1400 CC-ABV 27-oct-16 2378 CC-AIB 27-oct-16

1523 CC-ABW 27-oct-16 2380 CC-AIC 27-oct-16

2119 CC-AHC 27-oct-16 2436 CC-AID 27-oct-16

2129 CC-AFY 27-oct-16 2460 CC-AHD 27-oct-17

2214 CC-AIY 27-oct-16 2548 CC-AHE 27-oct-16

2249 CC-AJF 27-oct-16 3171 CC-AMP 27-oct-17

2251 CC-AFZ 27-oct-16 3331 CC-AJG 27-oct-17

2283 CC-AFX 27-oct-16




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NOTE 1: ELECTRICAL LOAD

(1) Direct Current (DC) Load Changes - Circuit Breaker: 58GA (New)

Designation: LGCIU/BAT SPLY/SYS 1 Busbar: 701PP Nominal Power: 103.8W Electrical Load Delta: +103.8W

- Circuit Breaker: 59GA (New) Designation: LGCIU/BAT SPLY/SYS 2 Busbar: 702PP Nominal Power: 69.8W Electrical Load Delta: +69.8W

During power interrupts battery will be loaded at 1.5A, plus an extra permanent load 0f 2 x 100mA to supply the relays 60GA and 61GA.

NOTE 2: AFFECTED DOCUMENT

Aircraft Schematic Manual (ASM) 31-54-00

Aircraft Wiring Manual (AWM)

24-68-12 24-68-13 31-54-94 32-31-02 32-31-03 32-31-04 32-31-09 32-31-10 32-31-11 93-01-21

Illustrated Parts Catalog (IPC) 32-31-08 Maintenance Planning Document (MPD) 323000




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REVISION RECORD

N° REVISION ITEM DESCRIPTION DATE

0

ALL

ORIGINAL RELEASE

APR 04-2014 (D.S)

01

PART II

CHANGE FROM CONF 004 AIRCRAFT´s MSN´s 0406 & 0447 TO CONF 010 AIRCRAFT´s MSN´s 3171 & 3331

JAN 28-2016 (D.S) PART LIST

AMENDMENT OF PART LIST IN ACCORDANCE WITH CONF 010 ADDED

SUMMARY CHANGE IN APPLICABILITY OF PART II

TABLE I CHANGE IN AIRCRAFTS MSN´s 0406 & 0447

BY MSN´s 3171 & 3331

02

SUMMARY ONLY TO REFER. FAA AD 2016-01-08 FEB 10-2016 (D.S)




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ACCOMPLISHMENT INSTRUCTIONS

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE

CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION, REFER TO ESPM 20-55-00.

A. GENERAL (ALL CONFIGURATIONS)

(a) For the specification of the material numbers (Mat. No.) that you must use in this

Service Bulletin, refer to the Consumable Material List (CML). (b) For the frames (FR) identification, refer to AMM 06-31-53, Page Block 001.

(c) For the identification of the access panels, refer to AMM 06-41-53, Page Block 001.

(d) Tag all the parts you must remove and retain to make the subsequent installation

easier.

(e) Put all the retained hardware in identified plastic bags and attach the bags to the related unit.

(f) If you find part numbers of hardware components in the related kit(s) which you

cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to the Standards Manual (SM). The SM will give you the correct part number to part number relationship.

(g) Drill and deburr the holes (Refer to SRM 51-44-11). (h) Remove/install the fasteners (Refer to SRM 51-42-11).

(i) Torque the standard threaded fasteners (Refer to AMM 20-21-11, Page Block 201).




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(j) To torque tighten the electrical component fasteners, refer to AMM 20-21-15, Page

Block 001.

(k) Do the electrical bonding (Refer to AMM 20-28-00, Page Block 201) with Pure Mineral

Vaseline Or Petrolatum VV-P-236A As required And

Electrical Bonding Coating Finish F69 Blue As required (Blue Color)

(l) For the installation of the placards, refer to AMM 11-00-00, Page Block 201. (m) Clean the surfaces at the location of the placards with Dry Cleaning

Solvent(Varsol/White MIL-PRF-680 As required Spirit)

(n) Obey the instructions for the general installation of electrical wire harness (Refer to

ESPM 20-33-00). (o) Put blanking caps on the disconnected electrical connectors. (p) To install new wires, cut them to the necessary length, crimp the terminals and

connect them. (q) Route the new wires with the wires that are in the aircraft. (r) Use existing spare conduits to route wires in locations difficult to get access to. (s) Do a continuity test of the modified and the new wires (Refer to ESPM 20-52-21). (t) For the cable tie application and tooling (Refer to ESPM 20-33-44 and ESPM 20-25-

51).

B. PREPARATION (ALL CONFIGURATIONS) (1) JOB SET-UP

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-

869-002) and put access platform(s) in position.

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(2) REMOVE/OPEN FOR ACCESS

(a) Open the FWD passenger/crew door 831 (Refer to AMM Task 52-10-00-010-001). (b) Open the access doors 811, 812 and 822 (Refer to AMM Task 52-41-00-010-001). (c) In the cockpit, remove the sidewall panels 212JW and 212HW (Refer to AMM Task

25-13-41-000-001). (d) In the cockpit, remove the ceiling panels 212FC and 211HC (Refer to AMM Task 25-

13-41-000-001). (e) In the cockpit, remove the third occupant seat 14MM (Refer to AMM Task 25-11-41-

000-001).

(3) DE-ENERGIZE ELECTRICAL NETWORK (a) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(b) Make sure that there is (are) warning notice(s) on the external power receptacle to tell persons not to connect an external power source.

(c) Make sure that the EMER EXIT LT pushbutton switch on 25VU is on the OFF

position.

(d) In the cockpit, on the overhead panel 35VU release the BAT pushbutton switches.

(e) Put a warning notice on the panel 35VU to tell persons not to operate the batteries.

(f) Put a warning notice on the refuel/defuel panel 800VU to tell persons not to opérate the NORMAL BATTERY switch.

(g) Put a warning notice in the cockpit to tell persons not to start the Auxiliary Power

Unit (APU).

(h) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2.

(i) Battery de-connection:

1 For the job set-up, refer to the removal of the batteries (Refer to AMM Task 24-38-51-000-001).

2 Turn the knurled nut a quarter turn.

3 Disconnect the connectors.

4 Put blanking caps on the disconnected electrical connectors.

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(4) PREPARATION PROCEDURES

(a) Do the preparation procedure as specified in the removal of the Generator Control Units 1 and 2 (GCU 1 and 2) FIN 1XU1 and 1XU2 (if installed) (Refer to AMM Task 24-22-34-000-001).

(b) Do the preparation procedure as specified in the removal of the GCU APU FIN 1XS

(if installed) (Refer to AMM Task 24-23-34-000-001).

(c) Do the preparation procedure as specified in the removal of the Spoiler Elevator Computer 3 (SEC 3) FIN 1CE3 (if installed) (Refer to AMM Task 27-94-34-000-001).

(d) Do the preparation procedure as specified in the removal of the zone controller FIN

8HK (if installed) (Refer to AMM Task 21-63-34-000-001).

(e) Do the preparation procedure as specified in the removal of the LGCIU 1 and 2 FIN 5GA1 and 5GA2 (if installed) (Refer to AMM Task 32-31-71-000-001).

(f) Do the preparation procedure as specified in the removal of the Tire Pressure

Indicating Computer (TPIS) detection unit FIN 2GV (if installed) (Refer to AMM Task 32-49-34-000-001).

(g) Do the preparation procedure as specified in the removal of the Smoke Detection

Control Unit (SDCU) FIN 10WQ (if installed) (Refer to AMM Task 26-17-34-000-001).

(h) Do the preparation procedure as specified in the removal of the Braking/Steering

Control Unit (BSCU) FIN 10GG (if installed) (Refer to AMM Task 32-42-34-000-001).

(i) Do the preparation procedure as specified in the removal of the aft cargo heat controller FIN 10HC (if installed) (Refer to AMM Task 21-43-34-000-002).

(j) Do the preparation procedure as specified in the removal of the Auxiliary Fuel

Management Computer (AFMC) FIN 2QN (if installed) (Refer to AMM Task 28-51-35-000-001).

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PART I (CONF 002) Only for the airplanes MSN 1400 (CC-ABV), 1523 (CC-ABW), 2119 (CC-AHC), 2129 (CC-AFY), 2214 (CC-AIY), 2249 (CC-AJF), 2251 (CC-AFZ), 2283 (CC-AFX), 2378

(CC-AIB), 2380 (CC-AIC), 2436 (CC-AID), 2460 (CC-AHD), 2548 (CC-AHE).

C. PROCEDURE (1) Remove the equipment for access in the cockpit.

(a) Remove as shown in detail B:

1 Panle-RH Latera Item (28) Retain

attached with:

1 Screw Item (29) Retain

1 Nut Item (30) Retain


(b) Remove as shown in detail C:

FIN 702VU

1 Console Item (32) Retain

attached with:


4 Washer Item (34) Retain

(2) Remove the equipment for access in the avionics compartment.

(a) Remove the shelf 91VU.

1 Remove and retain the GCU 1 and 2 FIN 1XU1 and 1XU2 (if installed) (Refer to AMM Task 24-22-34-000-001).

2 Remove and retain the GCU APU FIN 1XS (if installed) (Refer to AMM Task 24-

23-34-000-001). 3 Disconnect the shelf cut-off connectors and install protective caps. 4 Disconnect the bonding strap and remove the shelf from the aircraft. NOTE: Retain the hardware.

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(b) Remove the shelf 93VU.

1 Remove and retain the SEC 3 FIN 1CE3 (if installed) (Refer to AMM Task 27-94-34-000-001).

2 Remove and retain the zone controller FIN 8HK (if installed) (Refer to AMM Task

21-63-34-000-001). 3 Remove and retain the LGCIU 1 FIN 5GA1 (if installed) (Refer to AMM Task 32-

31-71-000-001). 4 Disconnect the shelf cut-off connectors and install protective caps. 5 Disconnect the bonding strap and remove the shelf from the aircraft. NOTE: Retain the hardware.

(c) Remove the shelf 94VU.

1 Remove and retain the LGCIU 2 FIN 5GA2 (if installed) (Refer to AMM Task 32-

31-71-000-001). 2 Remove and retain the TPIS detection unit FIN 2GV (if installed) (Refer to AMM

Task 32-49-34-000-001). 3 Remove and retain the SDCU FIN 10WQ (if installed) (Refer to AMM Task 26-17-

34-000-001). 4 Remove and retain the BSCU FIN 10GG (if installed) (Refer to AMM Task 32-42-

34-000-001).

5 Remove and retain the aft cargo heat controller FIN 10HC (if installed) (Refer to AMM Task 21-43-34-000-002).

6 Remove and retain the AFMC FIN 2QN (if installed) (Refer to AMM Task 28-51-35-

000-001). 7 Disconnect the shelf cut-off connectors and install protective caps. 8 Disconnect the bonding strap and remove the shelf from the aircraft. NOTE: Retain the hardware.

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(3) Install the new grounding points in the avionics compartment at FR10.

(a) Drill 2 holes on the structure at FR10 to the dimensions given in Fig. A-FACAA Sheet 01 and Fig. A-FACAA Sheet 02.

(b) Do 2 stripping dia. 14mm (0.551in.) as shown in Fig. A-FACAA Sheet 02.

(c) Near the new holes, as shown in Fig. A-FACAA Sheet 02, bond the placards identified

1037VN and 1039VN, supplied in:

Placard Set D9100095213795 (4) Modify the equipment and the wiring in the C/B panel 121VU.

(a) Install the C/B 58GA and 59GA.

1 At position R32, install:

FIN 58GA

1 Circuit Breaker NSA931324-075 Item 1


FIN 59GA


3 Near the new C/B, bond the placards identified 58GA and 59GA, supplied in:

Placard Set D9100095213795

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(b) Replace the placard 31LM (line R)

1 Remove:

FIN 31LM

1 Placard 002053-07 Item (2) Discard

attached with:

5 Button-Rivet Plastic ASNA2080G01 Item (3) Discard or

05 Button-Rivet Plastic ASNA2080G04 Item (4) Discard 2 Install:

FIN 31LM

1 Placard D11312197A00 Item 2

attach with:

5 Button-Rivet Plastic ASNA2080G01 Item 3

or


(c) Modify the wiring.

1 Modify the connections of the wires as shown on the wiring diagram Fig. AFBAAA Sheet 01 and as given in the hook-up chart lines:

- 1 thru 4 (Refer to Fig. A-FBAAA Sheet 03).

2 Install the wires as shown on the wiring diagrams Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02 and as given in the hook-up chart lines:

- 8 thru 13 (Refer to Fig. A-FBAAA Sheet 03), supplied in:

Bundle D9000095223395

3 Do a continuity test of the new and/or modified electrical wires, refer to ESPM 20-52-21.

4 Attach the wires with:

50 Tie-Cable NSA935401-03


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(5) Modify the equipment and the wiring in the shelf 93VU.

(a) Remove the relay 48GA.

1 Remove as shown in Fig. A-FAEAA Sheet 01:

FIN 48GA

1 Relay Item (5) Discard FIN 48GAA

1 Base Item (6) Discard FIN 48GAA8

1 Retainer Assy Item (7) Discard

2 Remove the placard identified 48GA.

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(b) Modify the terminal block 217VT.

1 Remove from position 9, as shown in Fig. A-FAEAA Sheet 01:

FIN 217VT9

1 Module Item (10) Discard and FIN 57GA

1 Capacitor Item (9) Discard


FIN 217VT10


1 Resistor Item (8) Discard

3 Remove between positions 9 and 10, as shown in Fig. A-FAEAA Sheet 01:

FIN 217VT91

1 Plate-Module Item (11) Discard

4 Install in replacement at positions 9 and 10:

2 Module-False NSA937901FM

(c) Install the relay 62GA.

1 Install at position B23, as shown in Fig. A-FAEAA Sheet 02:

FIN 62GA

1 Relay E0217XUU001A Item 13

FIN 62GAA

1 Base E0219ASXUU Item 14 attach with:

3 Nut MS21042-04 Item 15

2 Near the new relay, bond the placard identified 62GA, supplied in:


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(d) If not installed, install the grounding module 679VG.

1 Install as shown in Fig. A-FAEAA Sheet 02:

FIN 679VG

1 Module-Grounding E0425A2001 Item 16

2 Near the new grounding module, bond the placard identified 679VG, supplied in:


(e) Modify the wiring.

1 Remove the wires as shown on the wiring diagram Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 03 and as given in the hook-up chart lines:

- 1 thru 13 (Refer to Fig. A-FBBAA Sheet 04).

2 Install the wires as shown on the wiring diagrams Fig. A-FBBAA Sheet 02 and Fig.

A-FBBAA Sheet 03 and as given in the hook-up charts lines:

- 17 thru 23 (Refer to Fig. A-FBBAA Sheet 04)

Bundle D9000095223395

Bundle D9000095224595

NOTE: For connection of wire No. 3231-0487 to relay 53GA, use:

01 E/A of Socket-Contact P/N: EN3155-017F1616 OR

01 E/A of Socket-Contact P/N: EN3155-017F1216





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(6) Modify the wiring in the shelf 94VU.

(a) Install the wire as shown on the wiring diagram Fig. A-FBCAA Sheet 01 and as given

in the hook-up chart line:

- 1 (Refer to Fig. A-FBCAA Sheet 02), supplied in:

Bundle D9000095223395

(b) If not installed, install near 652VG:

FIN 654VG

1 Module-Grounding E0425A2001 (c) Do a continuity test of the new and/or modified electrical wires, refer to ESPM 20-52-

21. (d) Attach the wire with:


50 Tie-Cable NSA935401-05 (7) Modify the equipment in the shelf 91VU.

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(a) Disconnect the draining pipe from the blanking plate Item (17).

NOTE: Discard the attachment parts.

(b) Remove as shown in Fig. A-FAFAA Sheet 01 detail B:

1 Plate-Assy D9251335500000 Item (17) Discard

attached with:

6 Screw Item (22) Discard

6 Washer Item (23) Discard

6 Nut Item (24) Discard

(c) Install as shown in Fig. A-FAFAA Sheet 02 detail C:

1 Plate-LGCIU D9251719400095 Item 21

attach with:

6 Screw NAS1801-3-8 Item 22

6 Washer NAS1149F0332P Item 23

6 Nut NSA5050-3 Item 24

NOTE: For the internal wiring of the LGCIU plate, refer to Fig. A-FBJAA Sheet 01 and Fig. A-FBKAA Sheet 01.

- Install at the rear of the new LGCIU plate Item 21:

FIN 201VCA

1 Connector-Plug EN3646A61210BW Item 36 FIN 201VCA1

1 Backshell-Connector ABS0638A12 Item 37

FIN 203VCA

1 Connector-Plug EN3646A61210BN Item 38

FIN 203VCA1


(d) Install as shown in Fig. A-FAFAA Sheet 02 detail D:

1 Mount NSA935504-01 Item 25 and

1 Clamp NSA5515-11 Item 26

attach with:




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(e) Install as shown in Fig. A-FAFAA Sheet 02 detail E:

1 Mount NSA935504-01 Item 25 and

1 Clamp NSA5515-11 Item 26

attach with:




(8) Modify the wiring between the shelves 91VU and 93VU.

(a) Install the wires as shown on the wiring diagram Fig. A-FBDAA Sheet 01 and as given in the hook-up chart lines:

- 1 thru 3 (Refer to Fig. A-FBDAA Sheet 02), supplied in:

Bundle D9000095223395

(b)Do a continuity test of the new and/or modified electrical wires, refer to ESPM 20-52-21.

(c) Attach the wires with:




(9) Modify the wiring between the shelves 91VU and 94VU.

(a) Install the wires as shown on the wiring diagram Fig. A-FBEAA Sheet 01 and as given in the hook-up chart lines:

- 1 and 2 (Refer to Fig. A-FBEAA Sheet 02), supplied in:

Bundle D9000095223395

(b) Do a continuity test of the new and/or modified electrical wires, refer to ESPM 20-52-21.

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100 Tie-Cable NSA935401-08 (10) Modify the wiring between the shelf 91VU and the avionics compartment.

(a) Install the wires as shown on the wiring diagram Fig. A-FBFAA Sheet 01 and as given

in the hook-up chart lines:

- 1 and 2 (Refer to Fig. A-FBFAA Sheet 02), supplied in:

Bundle D9000095223395

(b) Connect the bonding points, as shown in Fig. A-FAGAA Sheet 01, with:




(c) Together with the new wires, install the identification plates 1037VN and 1039VN, supplied in:

Bundle D9000095223395

(d) Do a continuity test of the new and/or modified electrical wires, refer to ESPM 20-52-21.

(e) Attach the wires with:



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(11) Modify the wiring between the rear panel 120VU and the FWD electronics rack 90VU.

(a) Remove the wire as shown on the wiring diagram Fig. A-FBGAA Sheet 01 and as given

in the hook-up chart line:

- 1 (Refer to Fig. A-FBGAA Sheet 02). (b) Install the wire as shown on the wiring diagram Fig. A-FBGAA Sheet 01 and as given in

the hook-up chart line:

- 2 (Refer to Fig. A-FBGAA Sheet 02), supplied in:

Bundle D9000095223395

(c) Do a continuity test of the new and/or modified electrical wires, refer to ESPM 20-52-21 (d) Attach the wire with:




(12) Modify the wiring between the rear panel 120VU and the shelf 91VU.

(a) Install the wires as shown on the wiring diagram Fig. A-FBHAA Sheet 01 and as given in the hook-up chart lines:

- 1 thru 4 (Refer to Fig. A-FBHAA Sheet 02), supplied in:

Bundle D9000095223395 (b) Together with the new wires, install the identification plates 201VC-A and 203VC-A,

supplied in:

Bundle D9000095223395

(c) Do a continuity test of the new and/or modified electrical wires, refer to ESPM 20-52-21.

(d) Attach the wires with:




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(13) Install the equipment removed for access in the cockpit.

(a) Install as shown in detail B:

1 Panel-RH Lateral Item (28)

attach with:

1 Screw Item (29)

1 Nut Item (30)

2 Screw Item (31)

NOTE: All these items were retained at the removal.

(b) Install as shown in detail C:

FIN 702VU

1 Console Item (32)

attach with:

4 Screw Item (33)

4 Washer Item (34)

NOTE: All these items were retained at the removal.

(14) Install the equipment removed for access in the avionics compartment.

(a) Install the shelf 91VU.

1 Install the shelf and connect the bonding straps.

NOTE: Attach with the fasteners retained at removal.

2 Install the GCU 1 and 2 FIN 1XU1 and 1XU2 (if removed) (Refer to AMM Task 24-22-34-400-001).

3 Install the GCU APU FIN 1XS (if removed) (Refer to AMM Task 24-23-34-400-001).

4 Remove the protective caps and connect the shelf cut-off connectors.

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(b) Install the shelf 93VU.



2 Install the SEC 3 FIN 1CE3 (if removed) (Refer to AMM Task 27-94-34-400-001).

3 Install the zone controller FIN 8HK (if removed) (Refer to AMM Task 21-63-34-400-001).

4 Install the LGCIU 1 FIN 5GA1 (if removed) (Refer to AMM Task 32-31-71-400-001).


(c) Install the shelf 94VU.



2 Install the LGCIU 2 FIN 5GA2 (if removed) (Refer to AMM Task 32-31-71-400-001).

3 Install the TPIS detection unit FIN 2GV (if removed) (Refer to AMM Task 32-49-34-400-001).

4 Install the SDCU FIN 10WQ (if removed) (Refer to AMM Task 26-17-34-400-001).

5 Install the BSCU FIN 10GG (if removed) (Refer to AMM Task 32-42-34-400-001).

6 Install the aft cargo heat controller FIN 10HC (if removed) (Refer to AMM Task 21-

43-34-400-002).

7 Install the AFMC FIN 2QN (if removed) (Refer to AMM Task 28-51-35-400-001).


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D. TEST (1) Energize electrical network

(a) Battery re-connection:

1 For the job set-up, refer to the installation of the batteries (Refer to AMM Task 24-

38-51-400-001).

2 Remove the blanking cap(s) from the electrical connectors. 3 Make sure that the electrical connectors are clean and in correct condition. 4 Connect the connector on the battery. 5 Turn the knurled nut a quarter turn.

(b) Remove all the warning notices. (c) Restore the systems and the aircraft to normal operating condition.

(2) Preliminary tests

(a) Preliminary tests

1 Initial conditions:

a.- On each connectors that you disconnected, do a check as defined in ESPM 20-52-10.

NOTE: The functional test and/or operational test requested by this ESPM procedure

is given hereafter.

b.- Do the operational test of the instrument and panel integral lighting (Refer to AMM Task 33-13-00-710-001).

c.- Do the operational test of the lights (Refer to AMM Task 33-14-00-710-001).

d.- Do the operational test of the system via the Multipurpose Control and Display

Unit (MCDU) (Refer to AMM Task 21-26-00-710-001).

e.- Do the operational test of the Automatic Flight System (AFS) (Refer to AMM Task 22-96-00-710-001).

f.- Do the operational test of the Electronic Instrument System (EIS) (Refer to AMM

Task 31-60-00-710-001).

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g.- Do the operational test of the Electronic Centralized Aircraft Monitoring (ECAM)

control panel (Refer to AMM Task 31-50-00-710-004).

h.- Do a ground scanning of the central warning system (Refer to AMM Task 31-50-00-710-001).

i.- Do the Land CAT3 capability test (Refer to AMM Task 22-97-00-710-001).

(b) Test of the circuit breakers:

1 Do a voltage check at pin 1 of these C/B to make sure that there is 28VDC:

NOTE (1): The location of the circuit breakers depends on the aircraft configuration

2 Do the operational test of the Circuit Breaker Monitoring System (CBMS) for the panel 121VU (Refer to AMM Task 31-50-00-710-005).

(3) Testing

(a) Tests after removal/installation of the shelves 91VU, 93VU and 94VU

1 Shelf 91VU

a.- If equipped, do the operational test of the Ground Power Control Unit (GPCU) FIN 1XG via Centralized Fault Display System (CFDS) (Refer to AMM Task 24-41-00-740-004).

b.- If equipped, do the operational test of the Ground and Auxiliary Power Control

Unit (GAPCU) FIN 24XG via CFDS (Refer to AMM Task 24-41-00-740-002).

2 Shelf 93VU

a.- Do the operational test of the SEC 3 (Refer to AMM Task 27-94-00-710-001).

b.- Do the operational test of the cockpit and cabin temperature control with CFDS/MCDU (Refer to AMM Task 21-63-00-710-004).

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3 Shelf 94VU.

a.- If the aircraft is equipped with Tire Pressure Indicating System (TPIS) Detection Unit (FIN 2GV), do the cross-check of TPIS reading and tire pressure gauge (Refer to AMM Task 32-49-00-720-001).

b.- Do the operational test of the lavatory smoke-detection system (Refer to AMM

Task 26-17-00-710-001).

c.- Do the operational check of the cargo-compartment smoke-detection by Push To Test (PTT) (Refer to AMM Task 26-16-00-710-001).

d.- Do the Built-In Test Equipment (BITE) test of the Braking and Steering Control

Unit (BSCU) (Refer to AMM Task 32-46-00-740-001).

e.- If the aircraft is equipped with the aft cargo heat controller (FIN 10HC) do the operational test of the aft cargo-compartment heating system (Refer to AMM Task 21-43-00-710-003).

(b) Test of the electrical bonding

1 Do the check of the electrical bonding (Refer to AMM Task 20-28-00-720-005). NOTE: For the maximum permissible resistance values (Refer to AMM Task 20-28-00-

720-005). (4) Preparation

(a) On the overhead panel 35GU switch the batteries ’ON’. (b) On the overhead panel 35GU switch the external power ’ON’.

(c) Put the aircraft to Flight Configurations Precautions with Electrical Power (Refer to AMM

32-00-00, Page Block 201).

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(5) Test of Battery Relief Relay 60GA

(a) Switch off LGCIU2:

Open

(b) LGCIU1 only powered from ground supply: Open

Close

(c) On the ECAM Wheel page check that the indications that follow are displayed: 1 The MLG Left, MLG Right, Nose LG symbols on the right hand side on the Wheel

page are amber ’XX’ (crosses):

refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02 for EIS 1 (Cathode Ray Display Screens)

OR

refer to Fig. A-UBAAA Sheet 04 and Fig. A-UBAAA Sheet 05 for EIS 2 (LCD Screens).

(d) Do a BITE TEST on the LGCIU1 from the MCDU, the result should be test OK (Refer to AMM Task 32-69-00-740-001).

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(e) Open

Check that the ECAM Wheel page shows all amber ’XX’ (crosses):

refer to Fig. A-UBAAA Sheet 03 for EIS 1 (Cathode Ray Display Screens)

OR

refer to Fig. A-UBAAA Sheet 06 for EIS 2 (LCD Screens). (f) Close

Check on the ECAM Wheel page that the LGCIU is on: refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02 for EIS 1 (Cathode Ray Display Screens)

OR

refer to Fig. A-UBAAA Sheet 04 and Fig. A-UBAAA Sheet 05 for EIS 2 (LCD Screens).

(g) Close

Check on the ECAM Wheel page that the LGCIU is on:


OR

refer to Fig. A-UBAAA Sheet 05 for EIS 2 (LCD Screens).




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(h) Open

Check on the ECAM Wheel page that after TEN seconds all the gear symbols are amber ’XX’ (crosses):

refer to Fig. A-UBAAA Sheet 03 for EIS 1 (Cathode Ray Display Screens) OR refer to Fig. A-UBAAA Sheet 06 for EIS 2 (LCD Screens).

(i) Open

Check that the ECAM Wheel page remains the same as above, 1GA and 52GA are already open at this stage:


OR

refer to Fig. A-UBAAA Sheet 06 for EIS 2 (LCD Screens).

(6) Test of System 2 Battery Relief Relay 61GA

(a) Close

Make sure that 59GA is still open.

Check on the ECAM Wheel page that the LGCIU2 only is energized:


OR

refer to Fig. A-UBAAA Sheet 05 or Fig. A-UBAAA Sheet 07 for EIS 2 (LCD Screens).

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(b) Close

Check on the ECAM Wheel page that the LGCIU2 only is energized:

refer to Fig. A-UBAAA Sheet 02 for EIS 1 (Cathode Ray Display Screens) OR refer to Fig. A-UBAAA Sheet 05 or Fig. A-UBAAA Sheet 07 for EIS 2 (LCD Screens).

(c) Open

Check on the ECAM Wheel page that after TEN seconds all the gear symbols are amber ’XX’ (crosses):

refer to Fig. A-UBAAA Sheet 03 for EIS 1 (Cathode Ray Display Screens) OR refer to Fig. A-UBAAA Sheet 06 for EIS 2 (LCD Screens).

(d) Close

e) Close

NOTE: To do a BITE test on LGCIU SYS 2 the CFDS must receive a ground signal from

LGCIU1. (f) On LGCIU 2 do a ’BITE’ test from the MCDU, the test result should be test OK (Refer

to AMM Task 32-69-00-740-001). (g) Close

h) Close




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(7) Modified Safety Valve Circuit Test

NOTE: Diode 1VD 2/17 provides a feed back loop around Relay 62GA and must be tested, otherwise the Landing Gear will not retract. This test below avoids jacking the aircraft and swinging the gear.

(a) Make sure that the LG ground locks are fitted and hydraulic systems are

depressurized (Refer to AMM 32-30-00, Page Block 201).

(b) Open the connector 49GA-A LGSV (Landing Gear Safety Valve and connect a Portable Voltmeter between pin B and ground).

(c) On the overhead panel 35GU switch the external power ’ON’.

(d) Check that 28 volts appears on the Portable Voltmeter.

(e) Simulate the MLG left, MLG right and NLG to extend by:

1 For pre. Mod 37831J2877 - LGCIU P/N 664700500A4x: Enter interactive mode

LGCIU2 use MCDU, go to page 2 of the main menu and use ’LG SIMULATION MODE’.

2 For Post-Mod 37831J2877 NEW LGCIU -P/N 80-178-01-88xxx: It will be necessary

to use false targets (steel) on Prox sensors 22GA, 23GA and 25 GA to perform this simulation.

(f) Set the LG control lever 6GA to ’UP’ check that 28V remains indicated on the Portable

Voltmeter, then set the lever to ’DOWN’.

(g) Set the EXT PWR to ’OFF’

(h) Remove the Portable Voltmeter.

(i) Reconnect the 49GA-A connector to the LGSV. (8) Relay 62GA Test

(a) Perform an operational test of the safety valves (Refer to AMM Task 32-31-00-710-

005, or 32-31-00-710-005-01 or 32-31-00-710-005-02) ’Operational Check to Ensure Safety Valve Close at 260 kts’.

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E. CLOSE-UP

(1) Install/close ítems removed/opened for access

(a) In the cockpit, install the sidewall panels 212JW an 212HW (Refer to AMM Task 25-13-41-400-001).

(b) In the cockpit, install the ceiling panels 212FC and 211HC (Refer to AMM Task 25-13-41-400-001).

(c) In the cockpit, install the third occupant seat 14MM (Refer to AMM Task 25-11-41-

400-001).

(d) Close the access doors 812 and 822 (Refer to AMM Task 52-41-00-410-001).

(2) Close-up procedures

(a) Do the close-up procedure as specified after the installation of the GCU 1 and 2 FIN 1XU1 and 1XU2 (if installed) (Refer to AMM Task 24-22-34-400-001).

(b) Do the close-up procedure as specified after the installation of the GCU APU FIN 1XS

(if installed) (Refer to AMM Task 24-23-34-400-001).

(c) Do the close-up procedure as specified after the installation of the SEC 3 FIN 1CE3 (if installed) (Refer to AMM Task 27-94-34-400-001).

(d) Do the close-up procedure as specified after the installation of the zone controller FIN

8HK (if installed) (Refer to AMM Task 21-63-34-400-001).

(e) Do the close-up procedure as specified after the installation of the LGCIU 1 and 2 FIN 5GA1 and 5GA2 (if installed) (Refer to AMM Task 32-31-71-400-001).

(f) Do the close-up procedure as specified after the installation of the TPIS detection unit

FIN 2GV (if installed) (Refer to AMM Task 32-49-34-400-001).

(g) Do the close-up procedure as specified after the installation of the SDCU FIN 10WQ (if installed) (Refer to AMM Task 26-17-34-400-001).

(h) Do the close-up procedure as specified after the installation of the BSCU FIN 10GG (if

installed) (Refer to AMM Task 32-42-34-400-001).

(i) Do the close-up procedure as specified after the installation of the aft cargo heat controller FIN 10HC (if installed) (Refer to AMM Task 21-43-34-400-002).

(j) Do the close-up procedure as specified after the installation of the AFMC FIN 2QN (if


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(3) Close-up

(a) Make sure that the work areas are clean and clear of tools and other items of equipment.

(b) Remove the access platform(s). (c) Put the aircraft back to its initial configuration.

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PART II (CONF 010) Only for the airplanes MSN 3171 (CC-AMP), 3331 (CC-AJG),

C. PROCEDURE

(1) Remove the equipment for access in the cockpit.

(a) Remove as shown in detail B:

1 Panel-RH Lateral Item (28) Retain

attached with:


1 Nut Item (30) Retain


(b) Remove as shown in detail C:

FIN 702VU

1 Console Item (32) Retain

attached with:


4 Washer Item (34) Retain

(2) Remove the equipment for access in the avionics compartment.

(a) Remove the shelf 91VU.

1 Remove and retain the GCU 1 and 2 FIN 1XU1 and 1XU2 (if installed) (Refer to AMM

Task 24-22-34-000-001).

2 Remove and retain the GCU APU FIN 1XS (if installed) (Refer to AMM Task 24-23-34-000-001).

3 Disconnect the shelf cut-off connectors and install protective caps.

4 Disconnect the bonding strap and remove the shelf from the aircraft.

NOTE: Retain the hardware.

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(b) Remove the shelf 93VU.

1 Remove and retain the SEC 3 FIN 1CE3 (if installed) (Refer to AMM Task 27-94-34-

000-001).

2 Remove and retain the zone controller FIN 8HK (if installed) (Refer to AMM Task 21-63-34-000-001).

3 Remove and retain the LGCIU 1 FIN 5GA1 (if installed) (Refer to AMM Task 32-31-

71-000-001).

4 Disconnect the shelf cut-off connectors and install protective caps. 5 Disconnect the bonding strap and remove the shelf from the aircraft. NOTE: Retain the hardware.

(c) Remove the shelf 94VU.

1 Remove and retain the LGCIU 2 FIN 5GA2 (if installed) (Refer to AMM Task 32-31-

71-000-001). 2 Remove and retain the TPIS detection unit FIN 2GV (if installed) (Refer to AMM Task

32-49-34-000-001). 3 Remove and retain the SDCU FIN 10WQ (if installed) (Refer to AMM Task 26-17-34-

000-001). 4 Remove and retain the BSCU FIN 10GG (if installed) (Refer to AMM Task 32-42-34-

000-001). 5 Remove and retain the aft cargo heat controller FIN 10HC (if installed) (Refer to AMM

Task 21-43-34-000-002). 6 Remove and retain the AFMC FIN 2QN (if installed) (Refer to AMM Task 28-51-35-

000-001). 7 Disconnect the shelf cut-off connectors and install protective caps. 8 Disconnect the bonding strap and remove the shelf from the aircraft. NOTE: Retain the hardware.

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(3) Install the new grounding points in the avionics compartment at FR10.

(a) Drill 2 holes on the structure at FR10 to the dimensions given in Fig. A-FACAA Sheet 01 and Fig. A-FACAA Sheet 02.

(b) Do 2 stripping dia. 14mm (0.551in.) as shown in Fig. A-FACAA Sheet 02.

(c) Near the new holes, as shown in Fig. A-FACAA Sheet 02, bond the placards identified

1037VN and 1039VN, supplied in:

Placard Set D9100095213795 (4) Modify the equipment and the wiring in the C/B panel 121VU.

(a) Install the C/B 58GA and 59GA.


FIN 58GA



FIN 59GA


3 Near the new C/B, bond the placards identified 58GA and 59GA, supplied in:


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(b) Replace the placard 31LM (line R).

1 Remove:

FIN 31LM

1 Placard D11311500A00 Item (2) Discard

attached with:

5 Button-Rivet Plastic ASNA2080G01 Item (3) Discard or

5 Button-Rivet Plastic ASNA2080G04 Item (4) Discard

2 Install: FIN 31LM

1 Placard D11312090A00 Item 2

attach with:

5 Button-Rivet Plastic ASNA2080G01 Item 3 or


(c) Modify the wiring.

1 Modify the connections of the wires as shown on the wiring diagram Fig. AFBAAA Sheet 01 and as given in the hook-up chart lines:

- 1 thru 4 (Refer to Fig. A-FBAAA Sheet 03).

2 Install the wires as shown on the wiring diagrams Fig. A-FBAAA Sheet 01 and Fig. A-

FBAAA Sheet 02 and as given in the hook-up chart lines:

- 8 thru 13 (Refer to Fig. A-FBAAA Sheet 03), supplied in:

Bundle D9000095223395





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(5) Modify the equipment and the wiring in the shelf 93VU.

(a) Remove the relay 48GA.

1 Remove as shown in Fig. A-FAEAA Sheet 01:

FIN 48GA

1 Relay Item (5) Discard

FIN 48GAA

1 Base Item (6) Discard

FIN 48GAA8

1 Retainer Assy Item (7) Discard

2 Remove the placard identified 48GA.

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(b) Modify the terminal block 217VT.


FIN 217VT9


1 Capacitor Item (9) Discard 2 Remove from position 10, as shown in Fig. A-FAEAA Sheet 01:

FIN 217VT10


1 Resistor Item (8) Discard 3 Remove between positions 9 and 10, as shown in Fig. A-FAEAA Sheet 01:

FIN 217VT91

1 Plate-Module Item (11) Discard 4 Install in replacement at positions 9 and 10:

2 Module-False NSA937901FM

(c) Install the relay 62GA. 1 Install at position B23, as shown in Fig. A-FAEAA Sheet 02:

FIN 62GA

1 Relay E0217XUU001A Item 13

FIN 62GAA

1 Base E0219ASXUU Item 14

attach with:

3 Nut MS21042-04 Item 15

2 Near the new relay, bond the placard identified 62GA, supplied in:


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(d) If not installed, install the grounding module 679VG.

1 Install as shown in Fig. A-FAEAA Sheet 02:

FIN 679VG

1 Module-Grounding E0425A2001 Item 16 2 Near the new grounding module, bond the placard identified 679VG, supplied in:


(e) Modify the wiring.

1 Remove the wires as shown on the wiring diagram Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 03 as given in the hook-up chart lines:

- 1 thru 13 (Refer to Fig. A-FBBAA Sheet 04).

2 Install the wires as shown on the wiring diagrams Fig. A-FBBAA Sheet 02 and Fig.

A-FBBAA Sheet 03 and as given in the hook-up charts lines:

- 17 thru 23 (Refer to Fig. A-FBBAA Sheet 04)

Bundle D9000095223395

Bundle D9000095224595 NOTE: For connection of wire No. 3231-0487 to relay 53GA, use:

01 E/A of Socket-Contact P/N: EN3155-017F1616 OR

01 E/A of Socket-Contact P/N: EN3155-017F1216 3 Do a continuity test of the new and/or modified electrical wires, refer to ESPM 20-

52-21. 4 Attach the wires with:



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(6) Modify the wiring in the shelf 94VU.

(a) Install the wire as shown on the wiring diagram Fig. A-FBCAA Sheet 01 and as given in

the hook-up chart line:

- 1 (Refer to Fig. A-FBCAA Sheet 02), supplied in:

Bundle D9000095223395

(b) If not installed, install near 652VG:

FIN 654VG




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(a) Disconnect the draining pipe from the blanking plate Item (17).

NOTE: Discard the attachment parts.

(b) Remove as shown in Fig. A-FAFAA Sheet 01 detail B: 1 Plate-Assy D9251335500000 Item (17) Discard

attached with:

6 Screw Item (22) Discard

6 Washer Item (23) Discard

6 Nut Item (24) Discard

(c) Install as shown in Fig. A-FAFAA Sheet 02 detail C:

1 Plate-LGCIU D9251719400095 Item 21 attach with:




NOTE: For the internal wiring of the LGCIU plate, refer to Fig. A-FBJAA Sheet 01 and Fig. A-FBKAA Sheet 01.

- Install at the rear of the new LGCIU plate Item 21:

FIN 201VCA

1 Connector-Plug EN3646A61210BW Item 36

FIN 201VCA1


FIN 203VCA

1 Connector-Plug EN3646A61210BN Item 38

FIN 203VCA1


(d) Install as shown in Fig. A-FAFAA Sheet 02 detail D:

1 Mount NSA935504-01 Item 25 and 1 Clamp NSA5515-11 Item 26

attach with:




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(e) Install as shown in Fig. A-FAFAA Sheet 02 detail E:

1 Mount NSA935504-01 Item 25 and 1 Clamp NSA5515-11 Item 26

attach with:



1 Nut NSA5050-3 Item 24 (8) Modify the wiring between the shelves 91VU and 93VU.

(a) Install the wires as shown on the wiring diagram Fig. A-FBDAA Sheet 01 and as given in the hook-up chart lines:

- 1 thru 3 (Refer to Fig. A-FBDAA Sheet 02), supplied in:

Bundle D9000095223395 (b) Do a continuity test of the new and/or modified electrical wires, refer to ESPM 20-52-

21.




100 Tie-Cable NSA935401-08 (9) Modify the wiring between the shelves 91VU and 94VU.

(a) Install the wires as shown on the wiring diagram Fig. A-FBEAA Sheet 01 and as given in the hook-up chart lines:

- 1 and 2 (Refer to Fig. A-FBEAA Sheet 02), supplied in:

Bundle D9000095223395

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(b) Do a continuity test of the new and/or modified electrical wires, refer to ESPM 20-52-21. (c) Attach the wires with:




(10) Modify the wiring between the shelf 91VU and the avionics compartment.

(a) Install the wires as shown on the wiring diagram Fig. A-FWFAA Sheet 01 and as given in the hook-up chart lines:

- 1 and 2 (Refer Fig. A-FHFAA Sheet 01,), supplied in:

Bundle D9000095223395

(b) Connect the bonding points, as shown in Fig. A-FAGAA Sheet 01, with:




(c) Together with the new wires, install the identification plates 1037VN and 1039VN, supplied in:

Bundle D9000095223395

(d) Do a continuity test of the new and/or modified electrical wires, refer to ESPM 20-52-21. (e) Attach the wires with:



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(11) Modify the wiring between the rear panel 120VU and the FWD electronics rack 90VU.

(a) Remove the wire as shown on the wiring diagram Fig. A-FBGAA Sheet 01 and as given in the hook-up chart line:

- 1 (Refer to Fig. A-FBGAA Sheet 02).

(b) Install the wire as shown on the wiring diagram Fig. A-FBGAA Sheet 01 and as given in the hook-up chart line:

- 2 (Refer to Fig. A-FBGAA Sheet 02), supplied in:

Bundle D9000095223395

(c) Do a continuity test of the new and/or modified electrical wires, refer to ESPM 20-52-21.

(d) Attach the wire with:



100 Tie-Cable NSA935401-08 (12) Modify the wiring between the rear panel 120VU and the shelf 91VU.

(a) Install the wires as shown on the wiring diagram Fig. A-FBHAA Sheet 01 and as given in the hook-up chart lines:

- 1 thru 4 (Refer to Fig. A-FBHAA Sheet 02), supplied in:

Bundle D9000095223395

(b) Together with the new wires, install the identification plates 201VC-A and 203VC-A, supplied in:

Bundle D9000095223395 (c) Do a continuity test of the new and/or modified electrical wires, refer to ESPM 20-52-21 (d) Attach the wires with:




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(13) Install the equipment removed for access in the cockpit.

(a) Install as shown in detail B:

1 Panel-RH Lateral Item (28) attach with:

1 Screw Item (29)

1 Nut Item (30)

2 Screw Item (31) NOTE: All these items were retained at the removal. (b) Install as shown in detail C: FIN 702VU

1 Console Item (32) attach with:

4 Screw Item (33)

4 Washer Item (34) NOTE: All these items were retained at the removal.

(14) Install the equipment removed for access in the avionics compartment. (a) Install the shelf 91VU.



2 Install the GCU 1 and 2 FIN 1XU1 and 1XU2 (if removed) (Refer to AMM Task 24-22-34-400-001).

3 Install the GCU APU FIN 1XS (if removed) (Refer to AMM Task 24-23-34-400-001).


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(b) Install the shelf 93VU.



2 Install the SEC 3 FIN 1CE3 (if removed) (Refer to AMM Task 27-94-34-400-001). 3 Install the zone controller FIN 8HK (if removed) (Refer to AMM Task 21-63-34-400-

001). 4 Install the LGCIU 1 FIN 5GA1 (if removed) (Refer to AMM Task 32-31-71-400-001). 5 Remove the protective caps and connect the shelf cut-off connectors.

(c) Install the shelf 94VU.


NOTE: Attach with the fasteners retained at removal. 2 Install the LGCIU 2 FIN 5GA2 (if removed) (Refer to AMM Task 32-31-71-400-001). 3 Install the TPIS detection unit FIN 2GV (if removed) (Refer to AMM Task 32-49-34-

400-001). 4 Install the SDCU FIN 10WQ (if removed) (Refer to AMM Task 26-17-34-400-001). 5 Install the BSCU FIN 10GG (if removed) (Refer to AMM Task 32-42-34-400-001). 6 Install the aft cargo heat controller FIN 10HC (if removed) (Refer to AMM Task 21-43-

34-400-002).

7 Install the AFMC FIN 2QN (if removed) (Refer to AMM Task 28-51-35-400-001). 8 Remove the protective caps and connect the shelf cut-off connectors.

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D. TEST (1) Energize electrical network

(a) Battery re-connection:

1 For the job set-up, refer to the installation of the batteries (Refer to AMM Task 24-38-51-400-001).

2 Remove the blanking cap(s) from the electrical connectors. 3 Make sure that the electrical connectors are clean and in correct condition. 4 Connect the connector on the battery. 5 Turn the knurled nut a quarter turn.

(b) Remove all the warning notices.

(c) Restore the systems and the aircraft to normal operating condition.

(2) Preliminary tests

(a) Preliminary tests

1 Initial conditions:

a.- On each connectors that you disconnected, do a check as defined in ESPM 20-52-10.

NOTE: The functional test and/or operational test requested by this ESPM procedure is given hereafter.

b.- Do the operational test of the instrument and panel integral lighting (Refer to

AMM Task 33-13-00-710-001).

c.- Do the operational test of the lights (Refer to AMM Task 33-14-00-710-001).

d.- Do the operational test of the system via the Multipurpose Control and Display Unit (MCDU) (Refer to AMM Task 21-26-00-710-001).

e.- Do the operational test of the Automatic Flight System (AFS) (Refer to AMM Task

22-96-00-710-001).

f.- Do the operational test of the Electronic Instrument System (EIS) (Refer to AMM Task 31-60-00-710-001).

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g.- Do the operational test of the Electronic Centralized Aircraft Monitoring (ECAM)

control panel (Refer to AMM Task 31-50-00-710-004).

h.- Do a ground scanning of the central warning system (Refer to AMM Task 31-50-00-710-001).

i.- Do the Land CAT3 capability test (Refer to AMM Task 22-97-00-710-001).

(b) Test of the circuit breakers:

1 Do a voltage check at pin 1 of these C/B to make sure that there is 28VDC:

NOTE (1): The location of the circuit breakers depends on the aircraft configuration. 2 Do the operational test of the Circuit Breaker Monitoring System (CBMS) for the

panel 121VU (Refer to AMM Task 31-50-00-710-005). (3) TESTING

(a) Tests after removal/installation of the shelves 91VU, 93VU and 94VU

1 Shelf 91VU

a.- If equipped, do the operational test of the Ground Power Control Unit (GPCU) FIN 1XG via Centralized Fault Display System (CFDS) (Refer to AMM Task 24-41-00-740-002).

b.- If equipped, do the operational test of the Ground and Auxiliary Power Control

Unit (GAPCU) FIN 24XG via CFDS (Refer to AMM Task 24-41-00-740-002).

2 Shelf 93VU

a.- Do the operational test of the SEC 3 (Refer to AMM Task 27-94-00-710-001).

b.- Do the operational test of the cockpit and cabin temperature control with CFDS/MCDU (Refer to AMM Task 21-63-00-710-004).

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3 Shelf 94VU.

a.- If the aircraft is equipped with Tire Pressure Indicating System (TPIS) Detection

Unit (FIN 2GV), do the cross-check of TPIS reading and tire pressure gauge (Refer to AMM Task 32-49-00-720-001).

b.- Do the operational test of the lavatory smoke-detection system (Refer to AMM

Task 26-17-00-710-001).

c.- Do the operational check of the cargo-compartment smoke-detection by Push To Test (PTT) (Refer to AMM Task 26-16-00-710-001).

d.- Do the Built-In Test Equipment (BITE) test of the Braking and Steering Control

Unit (BSCU) (Refer to AMM Task 32-46-00-740-001).

e.- If the aircraft is equipped with the aft cargo heat controller (FIN 10HC) do the operational test of the aft cargo-compartment heating system (Refer to AMM Task 21-43-00-710-003).

(b) Test of the electrical bonding

1 Do the check of the electrical bonding (Refer to AMM Task 20-28-00-720-005).

NOTE: For the maximum permissible resistance values (Refer to AMM Task 20-28-

00-720-005). (4) Preparation

(a) On the overhead panel 35GU switch the batteries ’ON’. (b) On the overhead panel 35GU switch the external power ’ON’. (c) Put the aircraft to Flight Configurations Precautions with Electrical Power (Refer to

AMM 32-00-00, Page Block 201).

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(5) Test of Battery Relief Relay 60GA

(a) Switch off LGCIU2:

Open

(b) LGCIU1 only powered from ground supply:

Open

Close

(c) On the ECAM Wheel page check that the indications that follow are displayed:

1 The MLG Left, MLG Right, Nose LG symbols on the right hand side on the Wheel page are amber ’XX’ (crosses): refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02 for EIS 1 (Cathode Ray Display Screens) OR refer to Fig. A-UBAAA Sheet 04 and Fig. A-UBAAA Sheet 05 for EIS 2 (LCD Screens).

(d) Do a BITE TEST on the LGCIU1 from the MCDU, the result should be test OK (Refer to AMM Task 32-69-00-740-001).

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(e) Open

Check that the ECAM Wheel page shows all amber ’XX’ (crosses): refer to Fig. A-UBAAA Sheet 03 for EIS 1 (Cathode Ray Display Screens) OR refer to Fig. A-UBAAA Sheet 06 for EIS 2 (LCD Screens).

(f) Close

Check on the ECAM Wheel page that the LGCIU is on: refer to Fig. A-UBAAA Sheet 01 and Fig. A-UBAAA Sheet 02 for EIS 1 (Cathode Ray Display Screens) OR refer to Fig. A-UBAAA Sheet 04 and Fig. A-UBAAA Sheet 05 for EIS 2 (LCD Screens).

(g) Close

Check on the ECAM Wheel page that the LGCIU is on: refer to Fig. A-UBAAA Sheet 02 for EIS 1 (Cathode Ray Display Screens) OR refer to Fig. A-UBAAA Sheet 05 for EIS 2 (LCD Screens).

(h) Open

Check on the ECAM Wheel page that after TEN seconds all the gear symbols are amber ’XX’ (crosses): refer to Fig. A-UBAAA Sheet 03 for EIS 1 (Cathode Ray Display Screens) OR refer to Fig. A-UBAAA Sheet 06 for EIS 2 (LCD Screens).




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(i) Open

Check that the ECAM Wheel page remains the same as above, 1GA and 52GA are already open at this stage: refer to Fig. A-UBAAA Sheet 03 for EIS 1 (Cathode Ray Display Screens) OR refer to Fig. A-UBAAA Sheet 06 for EIS 2 (LCD Screens).

(6) Test of System 2 Battery Relief Relay 61GA

(a) Close

Make sure that 59GA is still open. Check on the ECAM Wheel page that the LGCIU2 only is energized: refer to Fig. A-UBAAA Sheet 02 for EIS 1 (Cathode Ray Display Screens) OR refer to Fig. A-UBAAA Sheet 05 or Fig. A-UBAAA Sheet 07 for EIS 2 (LCD Screens).

(b) Close

Check on the ECAM Wheel page that the LGCIU2 only is energized: refer to Fig. A-UBAAA Sheet 02 for EIS 1 (Cathode Ray Display Screens) OR refer to Fig. A-UBAAA Sheet 05 or Fig. A-UBAAA Sheet 07 for EIS 2 (LCD Screens).

(c) Open

Check on the ECAM Wheel page that after TEN seconds all the gear symbols are amber ’XX’ (crosses): refer to Fig. A-UBAAA Sheet 03 for EIS 1 (Cathode Ray Display Screens) OR refer to Fig. A-UBAAA Sheet 06 for EIS 2 (LCD Screens).

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(d) Close

(e) Close

NOTE: To do a BITE test on LGCIU SYS 2 the CFDS must receive a ground signal from LGCIU1.

(f) On LGCIU 2 do a ’BITE’ test from the MCDU, the test result should be test OK (Refer to

AMM Task 32-69-00-740-001).

(g) Close

(h) Close

(7) Modified Safety Valve Circuit Test

NOTE: Diode 1VD 2/17 provides a feed back loop around Relay 62GA and must be tested, otherwise the Landing Gear will not retract. This test below avoids jacking the aircraft and swinging the gear.

(a) Make sure that the LG ground locks are fitted and hydraulic systems are depressurized

(Refer to AMM 32-30-00, Page Block 201). (b) Open the connector 49GA-A LGSV (Landing Gear Safety Valve and connect a Portable

Voltmeter between pin B and ground). (c) On the overhead panel 35GU switch the external power ’ON’. (d) Check that 28 volts appears on the Portable Voltmeter.

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(e) Simulate the MLG left, MLG right and NLG to extend by:

1 For pre. Mod 37831J2877 - LGCIU P/N 664700500A4x: Enter interactive mode

LGCIU2 use MCDU, go to page 2 of the main menu and use ’LG SIMULATION MODE’.

2 For Post-Mod 37831J2877 NEW LGCIU -P/N 80-178-01-88xxx: It will be necessary to

use false targets (steel) on Prox sensors 22GA, 23GA and 25 GA to perform this simulation.

(f) Set the LG control lever 6GA to ’UP’ check that 28V remains indicated on the Portable

Voltmeter, then set the lever to ’DOWN’. (g) Set the EXT PWR to ’OFF’ (h) Remove the Portable Voltmeter. (i) Reconnect the 49GA-A connector to the LGSV.

(8) Relay 62GA Test

(a) Perform an operational test of the safety valves (Refer to AMM Task 32-31-00-710-005, or 32-31-00-710-005-01 or 32-31-00-710-005-02) ’Operational Check to Ensure Safety Valve Close at 260 kts’.

E. CLOSE-UP (1) Install/close ítems removed/opened for Access

(a) In the cockpit, install the sidewall panels 212JW an 212HW (Refer to AMM Task 25-13-41-400-001).

(b) In the cockpit, install the ceiling panels 212FC and 211HC (Refer to AMM Task 25-13-

41-400-001). (c) In the cockpit, install the third occupant seat 14MM (Refer to AMM Task 25-11-41-400-

001). (d) Close the access doors 812 and 822 (Refer to AMM Task 52-41-00-410-001).

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(2) Close-up procedures

(a) Do the close-up procedure as specified after the installation of the GCU 1 and 2 FIN

1XU1 and 1XU2 (if installed) (Refer to AMM Task 24-22-34-400-001). (b) Do the close-up procedure as specified after the installation of the GCU APU FIN 1XS

(if installed) (Refer to AMM Task 24-23-34-400-001). (c) Do the close-up procedure as specified after the installation of the SEC 3 FIN 1CE3 (if


(d) Do the close-up procedure as specified after the installation of the zone controller FIN 8HK (if installed) (Refer to AMM Task 21-63-34-400-001).

(e) Do the close-up procedure as specified after the installation of the LGCIU 1 and 2 FIN

5GA1 and 5GA2 (if installed) (Refer to AMM Task 32-31-71-400-001). (f) Do the close-up procedure as specified after the installation of the TPIS detection unit

FIN 2GV (if installed) (Refer to AMM Task 32-49-34-400-001). (g) Do the close-up procedure as specified after the installation of the SDCU FIN 10WQ (if

installed) (Refer to AMM Task 26-17-34-400-001). (h) Do the close-up procedure as specified after the installation of the BSCU FIN 10GG (if

installed) (Refer to AMM Task 32-42-34-400-001). (i) Do the close-up procedure as specified after the installation of the aft cargo heat

controller FIN 10HC (if installed) (Refer to AMM Task 21-43-34-400-002). (j) Do the close-up procedure as specified after the installation of the AFMC FIN 2QN (if

installed) (Refer to AMM Task 28-51-35-400-001). (3) Close-up

(a) Make sure that the work areas are clean and clear of tools and other items of equipment.

(b) Remove the access platform(s). (c) Put the aircraft back to its initial configuration.

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Deviation Record Sheet

Paragraph Observation Action Authorized by Performed by




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ENGINEERING ORDER N° IM A319/A320-32/1555webapp.ifrskeyes.com/GED/AMSFSKUPRD/(1555)...

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