109s Faa Ch4 Ampi

0B-B-04-00-00-00A-001H-A

0B-A-AMPI-00-P

A109S

Maintenance planning information

Chapter 04

Airworthiness limitations section

EASA approved on behalf of FAA

Third issue : 2009-06-22

Change 2 : 2011-06-20

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Effectivity: VERSION - G - FAA approved 0B-B-04-00-00-00A-002H-A

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C = Changed module N = New moduleD = Deleted module R = Revised module

(*) The asterisks identify the modules changed, revised, added or deleted with this issue

End of data module

List of effective pagesDates of issue and changes are:

Third issue 2009-06-22

Change 1 and 2 2011-06-20

The Third Issue of this chapter, after the insertion of Change 1 and 2, includes the modules that follow:

Document identifier Page Date Effectivity

0B-B-04-00-00-00A-001H-A 2 R 2011-06-20 * VERSION - G - FAA approved


0B-B-04-00-00-00A-003H-A 2 R 2009-06-22 VERSION - G - FAA approved


0B-B-04-00-00-00A-009H-A 2 R 2009-06-22 VERSION - G - FAA approved

0B-B-04-00-00-00A-018A-A 2 C 2011-01-25 * VERSION - G - FAA approved



0B-B-04-20-00-00A-000A-A 2 C 2009-06-22 VERSION - G - FAA approved

0B-B-04-30-00-00A-000A-A 6 C 2009-06-22 VERSION - G - FAA approved

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Change record

ChangeNo.

Incorporateddate by (signature)

ChangeNo.

Incorporateddate by (signature)

1 26

2 27

3 28

4 29

5 30

6 31

7 32

8 33

9 34

10 35

11 36

12 37

13 38

14 39

15 40

16 41

17 42

18 43

19 44

20 45

21 46

22 47

23 48

24 49

25 50


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Effectivity: VERSION - G - FAA approved


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End of data module

HighlightsThe listed changes are introduced with Change 1 and Change 2

Document Identifier Reason for update

0B-B-04-00-00-00A-018A-A CHANGED - Added FAA statement

0B-B-04-00-00-00A-021A-A CHANGED - Added approval of Change 1 and Change 2

0B-B-04-10-00-00A-000A-A CHANGED - Added part number


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2009-06-22 Page 1

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End of data module

Table of contents

Technical Name Information Name Document Identifier Effectivity

- Title page 0B-B-04-00-00-00A-001H-A VERSION - G - FAA approved

- List of effective pages 0B-B-04-00-00-00A-002H-A VERSION - G - FAA approved

- Change record 0B-B-04-00-00-00A-003H-A VERSION - G - FAA approved

- Highlights 0B-B-04-00-00-00A-004H-A VERSION - G - FAA approved

- Table of contents 0B-B-04-00-00-00A-009H-A VERSION - G - FAA approved

Airworthiness limitations section Introduction 0B-B-04-00-00-00A-018A-A VERSION - G - FAA approved

Airworthiness limitations section Airworthiness Authority approval

0B-B-04-00-00-00A-021A-A VERSION - G - FAA approved

Retirement lives General 0B-B-04-10-00-00A-000A-A VERSION - G - FAA approved

Mandatory inspections General 0B-B-04-20-00-00A-000A-A VERSION - G - FAA approved

Certification maintenance requirements

General 0B-B-04-30-00-00A-000A-A VERSION - G - FAA approved


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Effectivity: VERSION - FAA approved - G 0B-B-04-00-00-00A-018A-A

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End of data module

0B-B-04-00-00-00A-018A-AAirworthiness limitations section – Introduction

Originat or:-PB-----Notes: 1. E-MAIL TPS 000026

Table of contentsReferences ................................................................................................................................... 11 Airworthiness limitations..................................................................................................... 12 Engine airworthiness limitations ......................................................................................... 1

List of tables1 References ......................................................................................................................... 1

References

Description

1 Airworthiness limitationsThis chapter gives the airworthiness limitations applicable to the A109S helicopter.

The airworthiness limitations are approved by FAA and cannot be changed without approval.Refer to 0B-B-04-00-00-00A-021A-A.

The airworthiness limitations section is FAA approved and specifies inspections and othermaintenance required under para 43.16 and 91.403 of the Federal Aviation Regulations unlessan alternative program has been FAA approved.

The airworthiness limitations include the data modules that follow:

– The retirement lives (0B-B-04-10-00-00A-000A-A)– The mandatory inspections (0B-B-04-20-00-00A-000A-A)– The certification maintenance requirements (0B-B-04-30-00-00A-000A-A).

2 Engine airworthiness limitationsRefer to the latest issue of the Engine Maintenance Manual for the airworthiness limitationsapplicable to the Pratt & Whitney Canada PW207C engine.

Table 1 References

Data Module Title

0B-B-04-00-00-00A-021A-A Airworthiness limitations section – Airworthiness Authority approval

0B-B-04-10-00-00A-000A-A Retirement lives – General

0B-B-04-20-00-00A-000A-A Mandatory inspections – General

0B-B-04-30-00-00A-000A-A Certification maintenance requirements – General


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End of data module

0B-B-04-00-00-00A-021A-AAirworthiness limitations section – Airworthiness Authority approval

Originat or:-PB-----Notes:

Table of contentsReferences ................................................................................................................................... 11 Record of Airworthiness Authority approvals ..................................................................... 1

List of tables1 References ......................................................................................................................... 12 Record of Airworthiness Authority approvals ..................................................................... 1

References

Description

1 Record of Airworthiness Authority approvalsRefer to Table 2.

Table 2 Record of Airworthiness Authority approvals

Table 1 References

Data Module Title

No references

Change number Subject FAA approval

First issue - - Type Certificate Data Sheet (TCDS) No HZEU amended 20 July 2006

Second Issue See Highlights page (0B-B-04-00-00-00A-004H-A)

August 2, 2007 November 26, 2007

Third Issue See Highlights page (0B-B-04-00-00-00A-004H-A)

NDC 109-MM-004 18 June 2009

Change 1 See Highlights page (0B-B-04-00-00-00A-004H-A)

EASA D(2011)/MMA/SSI/10005456 EASA D(2011)/MMA/SSI/10005458Dated 20 June 2011

Change 2 See Highlights page (0B-B-04-00-00-00A-004H-A)

EASA D(2011)/MMA/SSI10009600

Dated 17 June 2011


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0B-B-04-10-00-00A-000A-ARetirement lives – General

Originat or:-PB-----Notes:

Table of contentsReferences ................................................................................................................................... 11 Introduction......................................................................................................................... 12 List of affected parts ........................................................................................................... 22.1 Part column ........................................................................................................................ 22.2 Part number column ........................................................................................................... 22.3 Retirement life column........................................................................................................ 2

List of tables1 References ......................................................................................................................... 12 Retirement lives - List of affected parts .............................................................................. 33 Cargo hook operation - Life penalty coefficient .................................................................. 64 Rescue hoist operation - Life penalty coefficient................................................................ 7

References

Description

1 IntroductionThe parts listed in this section must be mandatorily retired from service when the indicatedretirement life is reached. When retiring from service (if the life limit is reached or for otherreasons) the parts contained in the airworthiness limitation schedules, all the non-serializedstandard parts which connect the identified assembly / component shall be also replaced.

The retirement life specified for any given part number contained in this section applies toindicated and all successive dash numbers for that item, if not differently specified.

All retirement lives are expressed in Flight Hours (FH), if not differently specified. Flight hours aredefined as those hours accumulated from take-off to landing.

The retirement lives of some parts are expressed in “landings” because their life is dependentupon the rotor start-stop cycles and the helicopter ground-air-ground cycles.

If not differently specified, the retirement lives are based on the following assumptions:

– 600 landings in 100 flight hours, including 400 rotor start-stop cycles– 1200 external load cycles in 100 flight hours– 320 rescue hoist lifts in 100 flight hours.

Any mission profile using more cycles per hour than those listed above requires the retirementlives to be recalculated and approved by FAA.

If parts with the same part number can be interchanged between different A109/A119 variants,the retirement life of the part must be restricted to the lowest value between those variants.

Table 1 References

Data Module Title

0B-B-04-20-00-00A-000A-A Mandatory inspections – General


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2 List of affected partsRefer to Table 2. Each column of the table has a heading that gives the data that follows:

2.1 Part columnThis column gives the part description.

2.2 Part number columnThis column gives the part number.

2.3 Retirement life columnThis column gives the retirement life of the part.


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Table 2 Retirement lives - List of affected parts

Part Part number Retirement life

25 - EQUIPMENT/FURNISHING

Rescue hoist cable BL-9149 1500 lifts or 4 years. Use limit that occurs first (Note 5)

Hoist connecting plate assembly 109-0718-11-113 181000 lifts (Note 5)

32 - LANDING GEAR

Nose landing gear strut 109-0503-44-103 40000 landings

55 - STABILIZER

Left elevator 109-0200-02-601 3000

Right elevator 109-0200-02-602 6900

Torque tube clamp assembly 109-0210-03-13 4000

62 - MAIN ROTOR

Blade (composite material) 709-0104-01-111 8800 (Note 3)

Elastomeric bearing 109-0111-04-101 46000 landings or on conditions. Use limit that occurs first (Note 1)

Fixed swashplate assembly 109-0110-63-5 19000

Hub 109-0111-03-109/-113 89000 landings

Lower fixed half-scissor 109-0110-60-1 20000

Rotating swashplate 109-0134-03-105 2300

Rotating swashplate greasing bolt 109-0110-90-107 1000

Rotating swashplate locking ring 109-0134-11-103 1200

Sleeve 109-0110-21-3 15000

Spherical sleeve 109-0110-04-1 12000

Swashplate support 109-0110-05-101 1000

Swashplate support 109-0134-29-101 24000

Upper fixed half-scissor 109-0110-54-1 48000

Upper fixed half-scissor fitting 109-0110-38-1 3400

63 - MAIN ROTOR DRIVE

Aft rod 109-0325-03-113 13000 (Note 3)

Case assembly 109-0442-01-17 3300

Flange adapter 109-0425-01-3 40000 landings (Note 3)


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Forward rod 109-0325-02-107 16000 (Note 3)

Lower fitting 109-0325-08-109 41000 (Note 3)

Lower fixed half-scissor support 109-0110-53-1 17000

Main rotor shaft assembly 109-0405-76-107 10000 (Notes 3 and 4)

Planetary carrier 109-0405-10-3 100000 landings

Shaft assembly 109-0425-41-1 134000 landings (Note 3)

Upper case assembly 109-0402-45-101 9800 (Note 3)

64 - TAIL ROTOR

Blade 709-0160-48-101 10000

Elastomeric bushing 709-0160V01-101 On condition (Note 2)

Control lever 109-0040-48-117 26000 (Notes 3 and 4)

Hub assembly 109-0131-06-101 12000 landings

Link assembly 109-0040-47-1 26000 (Notes 3 and 4)

Retention strap assembly 109-8131-07-1 7200 landings

Retention strap bolt 709-0160-47-101 22000 landings

Retention strap bolt 709-0160-57-101 49000 landings

Strap plug 109-8131-06-1 20000 landings

Strap pin 109-8131-08-1 20000 landings

Support 109-0040-49-5 26000 (Notes 3 and 4)

Lever 109-0130-21-103 16000

Shaft 109-0130-33-1 16000

Double lever 109-0130-62-1 16000

Rod 109-0133-04-109 16000

Lever assembly 109-0130-43-113 16000

Lever 109-0130-60-3 16000

65 - TAIL ROTOR DRIVE

90-degree gearbox gear 109-0443-01-103 41000 (Note 3)

90-degree gearbox pinion 109-0433-01-107 30000 (Note 3)

Sleeve mounting 109-0435-31-1 3300

Tail rotor shaft assembly 109-0445-08-113 50000

Shaft assembly 109-8412-02-1/-3 78000 landings (Note 3)



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67 - ROTOR FLIGHT CONTROL

Main rotor servo actuator 109-0110-42-134/-135/-136 8000

Main rotor servo actuator attachment 28007GR90 1000

Tail rotor servo actuator 109-0040-51-103 26000 (Notes 3 and 4)

Note

1 Each 50 FH, inspect elastomeric bearing. Refer to 0B-B-04-20-00-00A-000A-A.

2 Each 200 FH, inspect elastomeric bushing. Refer to 0B-B-04-20-00-00A-000A-A.

3 Cargo hook operation penalty. For this part a life penalty must be mandatorily applied whenevera cargo hook operation is performed. The penalty of this part is listed in Table 3. To calculate theaccumulated life, multiply the flight hours or the landings (based on the retirement life type) by thepenalty coefficient of Table 3. The flight hours must be calculated from Take Off to Landing. TheCargo Hook operations must be in accordance with the assumption of maximum 12 external loadcycles in 1 hour. (Example for the main rotor blade: Flight time = 2 hours. Number of Cargo Hookoperations = between 1 and 12 per flight hour. Total accumulated flight hours = 2 x 2 = 4).

4 Rescue hoist operation penalty. For this part a life penalty must be mandatorily applied whenevera rescue hoist lift is performed (refer to Note 5 for the rescue hoist lift definition). The penalty of thispart is listed in Table 4. To calculate the accumulated life, multiply the flight hours by the penaltycoefficient of Table 4. The flight hours must be calculated from Take Off to Landing. The RescueHoist operations must be in accordance with the assumption of maximum 3.2 rescue hoist lifts in1 hour. (Example for the main rotor shaft assembly: Flight time = 2 hours. Number of Rescue Hoistlifts = between 1 and 3.2 per flight hour. Total accumulated flight hours = 2 x 3.5 = 7).

5 Rescue hoist lift definition. A lift is defined as an unreeling and recovery of the cable with a loadattached to the hook, independently of the length of the cable that is deployed / recovered. Anunreeling / recovery of the cable with no load on the hook is not considered to be a lift. Any operationwhere a load is attached for half the operation (i.e. unreeling or recovery) must be considered as alift.



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Table 3 Cargo hook operation - Life penalty coefficient

Part Part number Life penalty coefficient

62 - MAIN ROTOR

Blade (composite material) 709-0104-01-111 2


Aft rod 109-0325-03-113 3.5

Flange adapter 109-0425-01-3 1.5

Forward rod 109-0325-02-107 1.5

Lower fitting 109-0325-08-109 2.5

Main rotor shaft assembly 109-0405-76-107 1.5

Shaft assembly 109-0425-41-1 1.5

Upper case assembly 109-0402-45-101 2

64 - TAIL ROTOR

Control lever 109-0040-48-117 8.5

Link assembly 109-0040-47-1 8.5

Support 109-0040-49-5 8.5

65 - TAIL ROTOR DRIVE

90-degree gearbox gear 109-0443-01-103 6.5

90-degree gearbox pinion 109-0433-01-107 8

Shaft assembly 109-8412-02-1/-3 1.5


Tail rotor servo actuator 109-0040-51-103 8.5


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End of data module

Table 4 Rescue hoist operation - Life penalty coefficient

Part Part number Life penalty coefficient


Main rotor shaft assembly 109-0405-76-107 3.5

64 - TAIL ROTOR

Control lever 109-0040-48-117 6

Link assembly 109-0040-47-1 6

Support 109-0040-49-5 6


Tail rotor servo actuator 109-0040-51-103 6


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Effectivity: VERSION - G - FAA approved 0B-B-04-20-00-00A-000A-A

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0B-B-04-20-00-00A-000A-AMandatory inspections – General

Originat or:-PB08-002--

Table of contentsReferences ................................................................................................................................... 11 Introduction......................................................................................................................... 12 List of affected parts ........................................................................................................... 12.1 Number (No) column .......................................................................................................... 12.2 Part column ........................................................................................................................ 12.3 Task column ....................................................................................................................... 12.4 Interval column ................................................................................................................... 22.5 Reference (DMC) column................................................................................................... 2

List of tables1 References ......................................................................................................................... 12 Mandatory inspections - List of affected parts.................................................................... 2

References

Description

1 IntroductionThe parts listed in this section must be mandatorily inspected when the indicated interval isreached.

2 List of affected partsRefer to Table 2. Each column of the table has a heading that gives the data that follows:

2.1 Number (No) columnThis column gives the system plus a number to identify each listed component.

2.2 Part columnThis column gives the description of the part.

2.3 Task columnThis column gives the description of the work to do.

Table 1 References

Data Module Title

0B-A-62-21-00-00A-281A-A Main rotor head - Elastomeric bearings – Scheduled inspections

0B-A-64-11-01-00A-281A-B Tail rotor blade - Elastomeric bushings – Scheduled inspections

0B-B-04-10-00-00A-000A-A Retirement lives – General

Effectivity: VERSION - G - FAA ap-proved

0B-B-04-20-00-00A-000A-A

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End of data module

2.4 Interval columnThis column gives the inspection interval for the part. If not differently specified, the inspectioninterval is in Flight Hours (FH).

2.5 Reference (DMC) columnThis column shows the Data Module Code which provides the instructions to do the inspection.

Table 2 Mandatory inspections - List of affected parts

No Part Task Interval Reference (DMC)

62-01 Elastomeric bearing (PN 109-0111-04-101) (Note 1)

Inspect for cracking, separation of shims, blowing, rubber powder and/or crumbs

50 0B-A-62-21-00-00A-281A-A

64-01 Elastomeric bushing (PN 709-0160V01-101)

Inspect for cracking, blowing, rubber powder and/or crumbs

200 0B-A-64-11-01-00A-281A-B

Note

1 Retirement life: 46000 landings. Refer to 0B-B-04-10-00-00A-000A-A.


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0B-B-04-30-00-00A-000A-ACertification maintenance requirements – General

Originat or:-PB08-002--Notes: 1. DM 0B-A-04-30-00-00A-000A-A/2006-09-27 -

Table of contentsReferences ................................................................................................................................... 11 Certification maintenance requirements............................................................................. 22 Certification maintenance requirement schedule ............................................................... 22.1 Number (No) column .......................................................................................................... 22.2 System column................................................................................................................... 22.3 Task column ....................................................................................................................... 22.4 Interval column ................................................................................................................... 22.5 Reference (DMC) column................................................................................................... 22.6 Initials ................................................................................................................................. 2

List of tables1 References ......................................................................................................................... 12 Certification maintenance requirements............................................................................. 3

References

Table 1 References

Data Module Title

0B-A-21-91-00-00A-320A-A Integrated environmental control system - Shutoff switches – Operation tests

0B-A-21-91-03-00A-282A-A Air conditioning unit support - Attachment bolts – Unscheduled inspections

0B-A-21-91-18-00A-282A-A Flexible duct – Unscheduled inspections

0B-A-21-91-19-00A-281A-B Tube assembly – Scheduled inspections

0B-A-24-32-00-00A-320B-A Battery power generation system - Battery relay – Operation tests

0B-A-24-61-00-00A-320B-A DC electrical load distribution system - DC ESS BUS #1, TIE and #2 circuit breakers – Operation tests

0B-A-24-61-00-00A-320C-A DC electrical load distribution system - Essential bus diodes – Operation tests

0B-A-24-61-00-00A-320D-A DC electrical load distribution system - Relay K7212 – Operation tests

0B-A-25-91-00-00A-320A-A Rescue hoist installation – Operation tests

0B-A-25-91-00-00A-320B-A Rescue hoist installation - Cable cut switch – Operation tests

0B-A-25-91-01-00A-258A-A Rescue hoist - Cable and hook assembly – Other procedures to clean

0B-A-25-91-01-00A-281A-A Rescue hoist - Bumper assembly, cable cutter and cable – Scheduled inspections

0B-A-25-91-01-00A-320A-A Rescue hoist - Handwheel assembly bearing – Operation tests


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Description

1 Certification maintenance requirementsThis section gives you the data about the mandatory maintenance checks identified during thecertification process.

The parts listed in the schedule that follows must be mandatorily inspected when the indicatedinterval is reached.

2 Certification maintenance requirement scheduleRefer to Table 2. Each column of the table has a heading that gives the data that follows:

2.1 Number (No) columnThis column gives the system plus a number to identify each listed components.

2.2 System columnThis column gives the technical name of the system.

2.3 Task columnThis column gives the description of the work to do.

2.4 Interval columnThis column gives the maintenance check interval for the component. Unless specified differently,the interval is in Flight Hours (FH). No tolerance is permitted on Certification MaintenanceRequirements.

2.5 Reference (DMC) columnThis column shows the Data Module Code which gives the instructions to do the check.

2.6 InitialsWhen you use a copy of the data module for maintenance record, this column gives the space towrite the initials of the person who did the check.

0B-A-26-11-01-00A-340A-A Number 1 sensing element – Function tests

0B-A-26-12-01-00A-340A-A Number 2 sensing element – Function tests

0B-A-32-31-00-00A-320B-A Extension and retraction system - Emergency extension circuit – Operation tests

0B-A-63-51-00-00A-320A-A Rotor brake system – Operation tests

0B-A-63-51-00-00A-320B-A Rotor brake system - Pad microswitches – Operation tests

0B-A-63-51-03-00A-282A-A Brake disc – Unscheduled inspections

Table 1 References

Data Module Title


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Table 2 Certification maintenance requirements

No System Task Interval Reference (DMC) Initials

21-01 Environmental control system

Do a detailed visual inspection of hot air delivery pipe for condition

2 years 0B-A-21-91-19-00A-281A-B


Do a general visual inspection of external duct

Note 1 0B-A-21-91-18-00A-282A-A


Do an operation test of 1 and 2 SHUT-OFF switches for correct operation

8800 0B-A-21-91-00-00A-320A-A


Do an operation test of shut-off valves (SOV1, SOV2 and PRSOV)

8800 0B-A-21-91-00-00A-320A-A


Do a general visual inspection of bolts that attach air conditioning unit pylon to upper deck structure

Note 2 0B-A-21-91-03-00A-282A-A

24-01 Electrical power system

Do an Operational Check of ESS1 Circuit Breaker for open circuit failure

2000 0B-A-24-61-00-00A-320B-A


Do an Operational Check of ESS2 Circuit Breaker for open circuit failure

2000 0B-A-24-61-00-00A-320B-A


Do an Operational Check of Bus Tie Circuit Breaker for open circuit failure

2000 0B-A-24-61-00-00A-320B-A


Do an Operational Check of Contacts A1/A2 of the Battery Bus for open circuit failure

2000 0B-A-24-32-00-00A-320B-A


Do an Operational Check of DC Essential Bus 1 Diode for open circuit failure

2000 0B-A-24-61-00-00A-320C-A


Do an Operational Check of DC Essential Bus 2 Diode for open circuit failure

2000 0B-A-24-61-00-00A-320C-A


Do an Operational Check of Relay K7212 to verify that the contacts are not set to the emergency position

200 RH / 1 year (use the limit that occurs first)

0B-A-24-61-00-00A-320D-A


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25-01 Rescue hoist system

Do an Operational Check of Rescue Hoist Intermediate Up and Down Limit Switches to confirm automatic speed reduction

Prior first use of day

0B-A-25-91-00-00A-320A-A


Do an Operational Check of Rescue Hoist Full-Out and Full-In Limit Switches to confirm all operations are automatically stopped


0B-A-25-91-00-00A-320A-A


Do a General Visual Inspection of Rescue Hoist Cable Cutter Cotter Pin to ensure cotter pin is correctly installed


0B-A-25-91-01-00A-281A-A


Do an Operational Check of Rescue Hoist Cable Foul Detection Circuit to ensure correct operation and that all operations are automatically stopped


0B-A-25-91-00-00A-320A-A


Do a general visual inspection of complete cable length for damage and condition


0B-A-25-91-01-00A-281A-A


Do an Operational Check of hook assembly bearing for freedom of rotation


0B-A-25-91-01-00A-320A-A


Following use in a salt water environment, wash complete cable length and hook assembly with fresh water, and dry using a clean lint free cloth

After last use of day

0B-A-25-91-01-00A-258A-A


Do an Operational Check of Cable Cut Switch to determine the existence of dormant closed circuit failures of the switch guard contact #2 and the push-button contacts #1 and #2

10000 0B-A-25-91-00-00A-320B-A


Effectivity: VERSION - G - FAA ap-proved

0B-B-04-30-00-00A-000A-A

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End of data module

26-01 Fire detection system

Do a check of pressure-transducer alarm-switch contacts for dormant open circuit failures and integrity switch contacts for closed circuit failures

1400 0B-A-26-11-01-00A-340A-A

0B-A-26-12-01-00A-340A-A

32-01 Landing gear Do an operation test of the emergency extension system

400 0B-A-32-31-00-00A-320B-A

63-01 Rotor brake system

Do a general visual inspection of rotor brake disc for damage and condition. If you find that disc is damaged, replace it

Note 3 0B-A-63-51-03-00A-282A-A


Do an operation test of pad microswitches for correct operation (4 off)

Note 4 0B-A-63-51-00-00A-320B-A


Verify that ROTOR BRAKE ON warning and ROTOR BRK caution messages are correctly generated and shown on cockpit EDU

Note 4 0B-A-63-51-00-00A-320A-A

Note

1 This task is necessary all times you do a maintenance task in the areas where the external duct isinstalled.

2 This task is necessary all times you do a maintenance task in the areas where the air conditioningunit is installed.

3 This task is necessary all times you do a maintenance task in the areas where the rotor brake isinstalled.

4 This task is necessary after 7000 FH maximum, if, during this period, the rotor brake has not beenused.



2009-06-22 Page 6

0B-A-AMPI-00-P


109s Faa Ch4 Ampi

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