The information contained in this publication transmittal complies with the Authority

of Design Organisation Approval Number EASA.21J.O47. The technical accuracy of

this information has been verified and certified correct.

BAE SYSTEMS 2000. All rights reserved

BAE SYSTEMS (Operations) Limited,

Prestwick International Airport, Ayrshire,

KA9 2RW, Scotland

Signed:

Date: Dec 18/12

CAA Approval No.: DAI/1011/55

JAR Approval No.: EASA Part 21 Approval No. EASA.21J.047

PUBLICATION TRANSMITTAL

JETSTREAM 3200 SERIES AIRCRAFT MAINTENANCE MANUAL

Revision 29, Dec 15/12

AMM 3200/360

This revision is introduced into the manual to include the latest information.

Please remove and insert the affected pages as indicated and record the incorporation of

this revision on the Record of Revisions page.

Record the removal of any Temporary Revisions on the Record of Temporary Revisions

page.

CHECK THAT ALL PREVIOUS REVISIONS HAVE BEEN INCORPORATED

If any have not been received, please advise Technical Publications at BAE SYSTEMS, Prestwick International

Airport, Ayrshire KA9 2RW, Scotland.

The introduction of data by revisions or amendments or temporary revision or amendments not certified in accordance with Authority

of Design Organisation Approval Number EASA.21J.047, will invalidate the initial certification on the title page of the manual relative to

the part revised. Revisions or amendments or temporary revisions embodied in this manual and certified by an appropriate Approved

Organisation, other than that applicable to the initial certification, must be recorded on separate record sheets.

Page 1

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Revision Highlights

Pageblock Reasons for Change

05-10-05-0001 Introduce changes already subject

to AD action via SB 05-JA-090143

05-50-10-0601 Editorial / Effectivity change

06-00-13-0001 WAS 25404 STRM/GEN/4632

22-11-00-0501 Editorial / Effectivity change

32-10-11-0401 Editorial / Effectivity change

LETTER OF TRANSMITTAL

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Incorporation Instructions

Chapter/Section Remove Pages Insert Pages

05 LEP 001-005 001-005

05 TOC 001-002 001-002

05-10-05 001-073 001-075

05-50-10 601-610 601-606

06 LEP 001-002 001-002

06-00-13 001-019 001-015

22 LEP 001-003 001-003

22-11-00 519-520 519-520

32 LEP 001-017 001-017

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32-10-11 407-408 407-408

LETTER OF TRANSMITTAL

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CHAPTER 05

LIST OF EFFECTIVE PAGES

CHAPTER/SECTION/SUBJECT PAGE DATE

CONTENTS 1 Dec 15/12

CONTENTS 2 Apr 15/08

CONTENTS 3 Apr 15/08

CONTENTS 4 Apr 15/08

5 Apr 15/08

05-00-00 601 Oct 30/98

05-10-00 1 Oct 30/98

05-10-05 1 Dec 15/12

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CHAPTER 05

TABLE OF CONTENTS

SUBJECT CH/SE/SU PAGE EFFECTIVITY

TIME LIMITS/MAINTENANCE CHECKS -

GENERAL

05-00-00 ALL

INSPECTION CHECK 601

AIRWORTHINESS LIMITATIONS 05-10-00 ALL

DESCRIPTION AND OPERATION 1

General 1

AIRWORTHINESS LIMITATIONS 05-10-05 ALL

DESCRIPTION AND OPERATION 1

General 1

2

39

ONCE ONLY MANDATORY SERVICE BULLETINS

AND MODIFICATIONS

05-10-06 ALL

DESCRIPTION AND OPERATION 1

General 1

RECURRING MANDATORY SERVICE BULLETINS 05-10-07 ALL

DESCRIPTION AND OPERATION 1

General 1

SCHEDULED MAINTENANCE CHECKS 05-20-00 ALL

05-CONTENTS

Page 1

Dec 15/12 mm360

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SUBJECT CH/SE/SU PAGE EFFECTIVITY

DESCRIPTION AND OPERATION 1

General 1

UNSCHEDULED MAINTENANCE CHECKS 05-50-00 ALL

DESCRIPTION AND OPERATION 1

General 1

CHECK AIRFRAME RIGGING AND SYMMETRY 05-50-05 ALL

INSPECTION CHECK 601

Check Airframe Rigging and Symmetry 601

CHECK AFTER HEAVY OR ABNORMAL LANDING 05-50-10 ALL

INSPECTION CHECK 601

Check After Heavy or Abnormal

landing

601

CHECK AFTER LIGHTNING STRIKE 05-50-15 ALL

DESCRIPTION AND OPERATION 1

General 1

Preliminary Check 2

Comprehensive Check 3

De-magnetizing after Lightning

Strike

6

CHECK AFTER EXCESS BRAKING 05-50-20 ALL

DESCRIPTION AND OPERATION 1

General 1

05-CONTENTS

Page 2

Apr 15/08 mm360

Printed in the U.K.
** For Aircraft ALL**

AIRWORTHINESS LIMITATIONS

DESCRIPTION AND OPERATION

1. General

A. Approval

This Airworthiness Limitation Section is approved by EASA

and variations must also be approved by EASA (CS-23 Appendix

G Paragraph G23.4).

The FAA specified maintenance required under paragraphs

43.16 and 91.403 of the Federal Aviation Regulations must be

in accordance with manufacturers published data, unless an

alternative programme has been FAA approved.

Any such approved alternative must contain, in full, the

requirements of this Chapter.

NOTE : Where there is a conflict of information for an

inspection requirement defined against more than one

airworthiness directive of EASA or the airworthiness

authority of the state of design, the most severe

inspection requirement must be observed.

Applicable limitations are given in the following tables.

Airworthiness limitations (Airframe - Structures), (Ref.

Section 2.)

- Cleared Fatigue Lives, (Ref. Table 1)

- Life Extension Fatigue Lives, (Ref. Table 2)

- Landing Gear, (Ref. Table 3)

- Doors, (Ref. Table 4)

- Fuselage, (Ref. Table 5)

- Stabilizers, (Ref. Table 6)

- Wings, (Ref. Table 7).

05-10-05

Page 1

Dec 15/12 mm360

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Airworthiness limitations (Airframe - Systems), (Ref.

Section 3.)

- Electrical Power, (Ref. Table 8)

- Fying Controls, (Ref. Table 9)

- Ice and Rain Protection, (Ref. Table 10) and (Ref. Table

11)

- Lighting, (Ref. Table 12).

2. Airworthiness limitations (Airframe - Structures)

CAUTION - IT IS THE OPERATORS RESPONSIBILITY TO MAKE SURE TIME

LIMITS OR LIFE LIMITS FOR ITEMS COVERED BY THE

STATEMENT IN THIS CHAPTER ARE NOT EXCEEDED.

CAUTION -

A. Fatigue Lives

(1) Cleared Fatigue Lives

The current cleared fatigue lives of Jetstream Civil

Role major structural components are:-

Table No. 1

COMPONENT AIRCRAFT TYPE LIFE REMARKS

Wing Jetstream 3200 45000 landings

Fuselage Jetstream 3200 46200 landings

Fin Jetstream 3200 55500 landings

Tailplane Jetstream 3200 45000 landings

Engine mounting Jetstream 3200 53000 landings

Flap system Jetstream 3200 Universal joint

life:

15000 landings Fenner

05-10-05

Page 2

Dec 15/12 mm360

Printed in the U.K.
COMPONENT AIRCRAFT TYPE LIFE REMARKS

18000 landings Mollart

Unrestricted Post Mod 5323.

All lives are subject to component inspection defined

in the Maintenance Schedule.

Major structural modifications required to cover the

cleared lives have been given where applicable.

(2) Life Extension Fatigue Lives

If an aircraft in the Jetstream Civil Role is operating

beyond the current cleared fatigue lives of the major

structural components listed in (Ref. Table 1) then the

maintenance tasks defined in (Ref. Table 4), (Ref.

Table 5), (Ref. Table 6) and (Ref. Table 7) will be

superseded by the Supplemental Structural Inspections

Document, (Ref JS/SSID/01) at original issue or later.

The SSID is introduced through Service Bulletin 05-

JM8229, (complete with relevant log book insert).

The SSID quotes maintenance tasks, and initial and

repeat not exceed frequencies. All maintenance tasks in

the SSID are classified as Airworthiness Limitations.

The SSID is subject to EASA Airworthiness Directive.

When the aircraft is maintained in accordance with the

SSID the cleared fatigue lives of the major structural

components are defined in (Ref. Table 2).

Table No. 2

COMPONENT AIRCRAFT TYPE LIFE REMARKS

Wing Jetstream 3200 67000 landings

Fuselage Jetstream 3200 67000 landings

Fin Jetstream 3200 67000 landings

05-10-05

Page 3

Dec 15/12 mm360

Printed in the U.K.
COMPONENT AIRCRAFT TYPE LIFE REMARKS

Tailplane Jetstream 3200 67000 landings

Engine mounting Jetstream 3200 67000 landings

Flap system Jetstream 3200 Universal joint

life:

15000 landings Fenner

18000 landings Mollart

Unrestricted Post Mod 5323.

B. Landing Gear

The current cleared fatigue lives of Jetstream Civil Role

landing gear components are given in SB 32-JA981042: Landing

Gear - Main and Nose Landing Gears - To Introduce Life

Limitations and Provide Means of Establishing Total Flight

Cycles Since New for Critical Components, at Revision 8 or

later approved revision.

Table No. 3

ITEM REF. AND

DESCRIPTION

MAINTENANCE

TASK

NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

32-20-009

NLG Retract

actuator

Replace

actuator

Pre-mod 5387 or

pre-SB

32-JM5387

10,000 landings 10,000 landings

Replace

actuator

Post-mod 5387

or post-SB

32-JM5387

On condition On condition

05-10-05

Page 4

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE

TASK

NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

32-40-001

Nose wheel hub

(Qty 2)

(a) Crack

detection.

(b) Detail

visual.

(c) Check

pressure.

Refer to

applicable CMM.

At each tyre

change

At each tyre

change

32-40-002

Main wheel hub

(Qty 2)

(a) Crack

detection.

(b) Detail

visual.

(c) Check

pressure.

Refer to

applicable CMM.

At each tyre

change

At each tyre

change

32-40-216

MLG radius rod

mounting shaft

assemblies

Replace MLG

radius rod

mounting shaft

assemblies p/n

1373025B403 and

p/n 1373025B404

(Ref. SB 05-

JA090143).

31,038 landings

See Note 7

31,038 landings

See Note 7

05-10-05

Page 5

Dec 15/12 mm360

Printed in the U.K.
C. Doors

Table No. 4

ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

52-11-001 (a) Detail visual

of structure

as visible.

(b) Detail visual

of door

structure with

trim and steps

removed.

Refer to SB

52-A-JA 930901 and

FAA AD 95-02-05.

(a) 800 flying

hrs

(b) 1,800

flying hrs

(a) 800 flying

hrs

(b) 1,800

flying hrs

52-20-002 (a) Detail visual

of structure

as visible.

(b) Detail visual

of structure

with trim

panels

removed.

(a) 2,000

flying hrs

(b) 4,000

flying hrs

(a) 2,000

flying hrs

(b) 4,000

flying hrs

05-10-05

Page 6

Dec 15/12 mm360

Printed in the U.K.
D. Fuselage

Table No. 5

ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-00-004 Detail visual

inspection of

front fuselage

frame at STN 52,

(Ref. Figure 1),

(views A, B, C

and D).

32,400 landings 10,400 landings

53-00-005 Internal detail

visual of:

(a) NLG

attachment

brackets.

(b) Downlock

attachment

brackets.

(c) Uplock

attachment

brackets.

(d) FPB web.

(e) FPB

stiffeners.

1,200 flying hrs 1,200 flying hrs

05-10-05

Page 7

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-00-006 Detail visual

inspection and

torque check of

NLG

trunnion-fitting

to vertical post

attachment bolts

(Where stiffnuts

are fitted),

(Ref. Figure 2),

(view A), (Ref.

Chap. 20-00-00).

13,800 landings 4,600 landings

Front pressure

bulkhead (FPB)

forward face

53-10-001 Detail visual

inspection of

the FPB forward

face

intercostals

(Ref. Figure 3),

(Ref.SB 51-

JA020940,

Appendix 1, Part

1).

14,700 landings 5,800 landings

05-10-05

Page 8

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-10-002 Detail visual

inspection of

the FPB forward

face vertical

channels, left

and

right (Ref. Figure 3)

(Ref.SB 51-

JA020940,

Appendix 1, Part

2).

23,800 landings 17,700 landings

53-10-003 (a) Detail

visual

inspection

of

attachment

bolts.

(b) Torque check

of

attachment

bolts (Ref.

Chap.

32-20-51).

(a) 3,500

landings

(b) 3,500

landings

(a) 200 landings

(b) 1,600

landings

Front pressure

bulkhead (FPB)

rear face

05-10-05

Page 9

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-10-011 Detail visual

inspection of

the FPB rear

face horizontal

stiffeners and

FPB

web (Ref. Figure 4),

(Ref.SB 51-

JA020940,

Appendix 1, Part

3).

8,000 landings 5,400 landings

53-10-013 Detail visual

inspection of

all FPB rear

face stringer

attachment

cleats left and

right (Ref. Figure 4),

(Ref.SB 51-

JA020940,

Appendix 1, Part

4).

10,500 landings 7,900 landings

53-10-014 Detail visual

inspection of

flying control

system brackets

attached to FPB.

4,000 flying hrs 4,000 flying hrs

Fuselage frames

05-10-05

Page 10

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-10-022 Detail visual

inspection of

frame at STN

75.15 including

stringer cleats,

shear plates and

vertical

ties (Ref. Figure 5),

(Ref.SB 51-

JA020940,

Appendix 1, Part

5).

17,100 landings 6,600 landings

53-10-025 Detail visual

inspection of

external skin

and rivets on

the frame at STN

75.15 (Ref. Figure 5),

(Ref.SB 51-

JA020940,

Appendix 1, Part

6).

33,300 landings 12,600 landings

53-10-032 Detail visual

inspection of

stringer cleats

attached to

frame STN

89.15 (Ref. Figure 6).

31,500 landings 9,800 landings

05-10-05

Page 11

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-10-033 Detail visual

inspection of

external skin

and rivets on

the frame at STN

89.15 (Ref. Figure 6),

(Ref.SB 51-

JA020940,

Appendix 1, Part

7).

31,500 landings 9,800 landings

53-10-042 Detail visual

inspection of

stringer cleats

on the frame at

STN 109.75

(Ref. Figure 6),

(Ref.SB 51-

JA020940,

Appendix 1, Part

8).

24,600 landings 11,000 landings

53-10-045 Detail visual

inspection of

external skin

and rivets on

the frame at STN

109.75 (Ref. Figure 6),

(Ref.SB 51-

JA020940,

Appendix 1, Part

9).

34,700 landings 11,000 landings

Flight Deck

05-10-05

Page 12

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-10-063 Detail visual

inspection of

all windshield

frame attachment

fittings at

frame STN 89.15

including

attachment

bolts (Ref. Figure 7).

24,700 landings 2,500 landings

53-10-065 Torque check of

the canopy

attachment bolts

at frame STN

89.15 (Ref. Figure 7),

(Ref.SB 51-

JA020940,

Appendix 1, Part

10).

28,600 landings 2,500 landings

53-10-067 Detailed visual

inspection of

the coaming at

frame STN

89.15 (Ref. Figure 7),

(Ref.SB 51-

JA020940,

Appendix 1, Part

11).

28,600 landings 2,500 landings

05-10-05

Page 13

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-10-069 Torque check of

the coaming

attachment bolts

at frame STN

109.75 (Ref. Figure 8),

(Ref.SB 51-

JA020940,

Appendix 1, Part

12).

28,600 landings 2,500 landings

Passenger cabin

53-10-077 Detail visual

inspection of

escape hatch

surround

structure and

external skin

cut-out(s) as

visible with

hatch(es)

removed.

4,000 flying hrs 4,000 flying hrs

53-10-079 Detail visual

inspection of

escape hatch

surround

structure, left

and right,

(Ref. Figure 9),

(Ref.SB 51-

JA020940,

Appendix 1, Part

13).

29,000 landings 8,700 landings

05-10-05

Page 14

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-10-080 NDI inspection

of fuselage skin

at window

cut-outs, (Ref. Figure 10),

(view B), (Ref.

NDI manual,

Chap. 53-10-15

high frequency

eddy current).

25,800 landings

or 10 years

4,400 landings or

2 years

53-10-081 NDI inspection

of all window

pans

(Ref. Figure 10),

(view B), (Ref.

NDI manual,

Chap. 53-10-15

low frequency

eddy current),

(Ref.SB 51-

JA020940,

Appendix 1, Part

14).

25,800 landings

or 10 years

4,400 landings or

2 years

53-10-083 Detail visual

inspection of

the intercostals

at the passenger

window cut-out

(Ref. Figure 10),

(view A),

(Ref.SB 51-

JA020940,

Appendix 1, Part

15).

25,800 landings

or 10 years

4,400 landings or

2 years

05-10-05

Page 15

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-10-086 External detail

visual of window

cut-outs.

4,000 flying hrs 4,000 flying hrs

Rear fuselage

53-11-002 Detail visual

inspection of

the passenger

door surround

frames at STN’s

345 and 381

lintel and

threshold (Ref. Figure 11),

(Ref.SB 51-

JA020940,

Appendix 1, Part

16).

30,400 landings 4,800 landings

53-11-004 Detail visual

inspection of

the passenger

door surround

external skin

(Ref. Figure 11),

(Ref.SB 51-

JA020940,

Appendix 1, Part

17).

30,400 landings 4,800 landings

Rear pressure

bulkhead (RPB)

forward face

05-10-05

Page 16

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-11-011 Detail visual

inspection of

horizontal and

vertical

stiffeners

(Ref. Figure 12),

(views A and B),

(Ref. Figure 13),

(views C, D E

and F).

9,600 landings 2,400 landings

53-11-012 Detail visual

inspection of

all fuselage

stringer cleats

attached to RPB

boundary angle

(Ref. Figure 14),

(views A and B).

28,800 landings 7,300 landings

53-11-014 NDI inspection

of RPB boundary

angle (Ref. NDI

manual, Chap.

53-10-07,

X-ray).

32,900 landings 4,000 landings

Rear equipment

bay

05-10-05

Page 17

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-11-021 Detail visual

inspection of

the angles

attaching

intercostals

between RPB and

APU surround

structure (Ref. Figure 15),

(Ref.SB 51-

JA020940,

Appendix 1, Part

18).

32,000 landings 8,800 landings

53-11-022 Detail visual

inspection of

RPB vertical

posts,

(Ref. Figure 16),

(view B).

4,000 flying hrs 4,000 flying hrs

53-11-023 Detail visual

inspection of

all RPB stringer

cleats,

(Ref. Figure 16)

(view A).

28,600 landings 12,800 landings

05-10-05

Page 18

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-11-024 (a) Detail

visual

inspection

of vertical

stabilizer

forward

joint plate

in rear

equipment

bay,

(Ref. Figure 17),

(view C).

(b) Detail

visual and

torque check

of all

forward

joint plate

bolts,

(Ref. Figure 17),

(view C),

(Ref. Chap.

20-00-00).

(a) 4,000 flying

hrs

(b) 20,000

landings

(a) 4,000 flying

hrs

(b) 3,000

landings

53-11-028 Detail visual

inspection of

vertical

stabilizer

attachment plate

drag angle, left

and right, and

joint plate

bolts,

(Ref. Figure 17),

(views A and B).

20,000 landings 3,000 landings

05-10-05

Page 19

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-11-032 Detail visual

inspection of

rudder lower

hinge fitting.

4,000 flying hrs 4,000 flying hrs

53-11-033 Detail visual

inspection of

vertical

stabilizer rear

attachment

assembly.

4,000 flying hrs 4,000 flying hrs

Lower centre

fuselage

53-11-041 Internal detail

visual

inspection zone

C/S 500

05-10-05

Page 20

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

(a) Fuselage

skin joint

at frame STN

223.

(b) Front spar

frame STN

199.

(c) Main spar

frame STN

223.

(d) Rear spar

frame STN

257.8.

(e) Front spar

fitting and

spigot assy.

(f) Main spar

scarf joint.

(g) Rear spar

fitting

attachment

lug.

(a) 4,000 flying

hrs

(b) 4,000 flying

hrs

(c) 4,000 flying

hrs

(d) 4,000 flying

hrs

(e) 4,000 flying

hrs

(f) 4,000 flying

hrs

(g) 4,000 flying

hrs

(a) 4,000 flying

hrs

(b) 4,000 flying

hrs

(c) 4,000 flying

hrs

(d) 4,000 flying

hrs

(e) 4,000 flying

hrs

(f) 4,000 flying

hrs

(g) 4,000 flying

hrs

53-11-049 Torque check of

bolts at wing

stub spigot post

assembly at

frame 199, (Ref

SB 57-JA020740).

4,000 flying hrs 4,000 flying hrs

Tuned

visco-elastic

frame dampers

05-10-05

Page 21

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-20-001 Detail visual

inspection for

cracking and

distortion

adjacent to each

pair of dampers,

with dampers in

position.

(a) Between STR

0° and 7° RH

only.

(b) Between STR

42° and 50°

LH and RH.

(c) Between STR

50° and 56°

LH and RH.

(d) Between STR

96° and 102°

LH and RH.

2,400 flying hrs

or 1 year from

date of

embodiment of

Mod 2728

2,400 flying hrs

or 1 year

05-10-05

Page 22

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-20-002 Detail visual

inspection for

cracking and

distortion

adjacent to each

pair of dampers,

with dampers in

position.

(a) Between STR

0° and 7° RH

only.

(b) Between STR

42° and 50°

LH and RH.

(c) Between STR

50° and 56°

LH and RH.

(d) Between STR

96° and 102°

LH and RH.

2,400 flying hrs

or 1 year from

date of

embodiment of

Mod 2728

2,400 flying hrs

or 1 year

Acoustic

insulation

05-10-05

Page 23

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-20-011 (a) Detail

visual

inspection

of all

chemi-milled

pockets

between

stringers

35° and

135°, LH and

RH, for

overall

integrity of

sound

damping tape

attachment

to the skin.

(b) Remove

acoustic

tape from

the

chemi-milled

pocket

immediately

below each

cabin window

and inspect

for

corrosion.

Renew the

acoustic

tape.

2,400 flying hrs

or 1 year from

date of

embodimanet of

mod 2728.

Repeat inspection

frequency to be

determined after

results of

initial

inspection have

been evaluated by

the manufacturer

05-10-05

Page 24

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY REPEAT

53-20-012 Detail visual

inspection of

all stringers

35° to 135°, LH

and RH, for

overall

integrity of

sound damping

tape attachment

to stringers

2,400 flying hrs

or 1 year from

date of

embodiment of

mod 2728.

Repeat inspection

frequency to be

determined after

results of

initial

inspection have

been evaluated by

the manufacturer

53-20-013 Detail visual

inspection of

seat rail

support

structure, over

the flanged

lightning holes

in the vertical

and horizontal

webs, LH and RH.

2,400 flying hrs

or 1 year from

date of

embodiment of

mod 2728.

Repeat inspection

frequency to be

determined after

results of

initial

inspection have

been evaluated by

the manufacturer

Fuselage

external

53-30-001 Detail visual

inspection of

edge sealant.

800 flying hrs 800 flying hrs

05-10-05

Page 25

Dec 15/12 mm360

Printed in the U.K.
E. Stabilizers

Table No. 6

ITEM REF. AND

DESCRIPTION

MAINTENANCE

TASK

NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

55-10-010

Horizontal

stabilizer

attachment

fittings

Detail visual

inspection of

attachment

fittings, (Ref

SB 55-

JA020543).

Access panels

V6 and V10.

4,000 flying

hrs or 8 years

See note: 3

4,000 flying

hrs or 8 years

See note: 3

55-10-011

Horizontal

stabilizer

attachment

bolts

Remove each

bolt in turn

and inspect for

corrosion and

cracks (Ref.

NDI manual

Chapter 55-20-

00 Magnetic

Particle).

Carry out a

detail visual

inspection of

the bore from

which each bolt

has been

removed.

8 years 8 years

55-20-001

Elevator/

Horizontal

stabilizer

hinges

Detail visual

inspection of

hinges. Access

panels H7, H10,

H11, H14, H17

and H18.

4,000 flying

hrs

4,000 flying

hrs

05-10-05

Page 26

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE

TASK

NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

55-20-002

Elevator hinge

bolts

Detail visual

inspection of

bore. NDI

inspection of

bolts (Ref.

Chap. 27-30-31

and NDI manual,

Chap. 55-20-00,

Magnetic

Particle).

Access panels

H5, H6, H7, H8,

H11, H12, H14,

and H15.

6 years 6 years

55-30-001

Vertical

stabilizer

attachment

fittings

Detail visual

inspection of

attachment

fittings (Ref.

SB 55-

JA020543).

8 years or

4,000 flying

hrs, See note:

3

8 years or

4,000 flying

hrs, See note:

3

55-40-004

Rudder/Vertical

stabilizer

hinges

Detail visual

inspection of

top, centre and

bottom hinges.

Access panel

V12, (Ref.

Chap.

27-20-11).

4,000 flying

hrs

4,000 flying

hrs

05-10-05

Page 27

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE

TASK

NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

55-40-005

Rudder top and

centre hinge

bolts.

Remove and

inspect for

corrosion and

cracks, (Ref

NDI manual,

Chap. 55-40-05,

Magnetic

Particle).

Detail visual

inspection of

the bore from

which the

particular bolt

has been taken,

(Ref. Chap.

27-20-11).

6 years 6 years

F. Wings

Table No. 7

ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

57-10-006 Detail visual

inspection of flap

and aileron hinge

brackets left and

right, including

angles and upper

support brackets

(Ref. AMM 57-20-

07).

2,400 flying

hrs

1,200 flying

hrs

05-10-05

Page 28

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

57-10-007 NDI inspection of

the flap/wing and

aileron/wing hinge

lugs, bolts and

nuts

(Ref. Figure 18)

and

(Ref. Figure 19),

(Ref. SB 51-

JA020940 Appendix

2, Part 1).

15,000 flying

hrs

15,000 flying

hrs

57-10-024 Internal detail

visual inspection

of main spar to

stringer joint at

STN 169 left

and right

(Ref. Figure 20),

(view A).

20,000 landings 3,000 landings

57-10-030 Internal detail

visual inspection

of attachment

bolts wing main

spar vertical post

to fuselage frame

STN 223 left and

right

(Ref. Figure 21),

(view A).

23,700 landings 6,000 landings

05-10-05

Page 29

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

57-10-211 Detail visual

inspection of the

top skin/main spar

cleat at wing

root (Ref. Figure 22),

(Ref. SB 51-

JA020940 Appendix

2, Part 2).

24,600 landings 23,600 landings

57-10-213 NDI inspection of

the leading edge

attachment rib

(rib 36), (Ref. SB

51-JA020940

Appendix 2, Part

3).

25,500 landings 3,600 landings

57-10-215 Detail visual

inspection of the

rib 115/skin

attachments (Ref. Figure 23),

(Ref. SB 51-

JA020940 Appendix

2, Part 4).

23,900 landings 6,400 landings

57-10-217 NDI inspection of

main spar access

panel cut-outs

STN’s 36 to 83

(Ref NDI manual

Chap. 57-10-17,

high frequency

eddy current).

38,000 landings 10,500 landings

05-10-05

Page 30

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

57-10-219 Detail visual

inspection of the

sealing angle,

main undercarriage

cut-out at STN’s

83 to 99

(Ref. Figure 24),

(Ref. SB 51-

JA020940 Appendix

2, Part 5).

33,600 landings 40,900 landings

57-10-235 NDI inspection

wing front spar

lower boom between

STN’s 150 and 190.

(Ref. NDI manual

57-10-35, high

frequency eddy

current).

38,000 landings 3,000 landings

57-30-004 NDI inspection of

wing lower skin,

wing STN 85 around

water drain valve,

left and right.

(Ref. NDI manual

Chap. 57-30-004,

high frequency

eddy current).

21,700 landings 3,000 landings

05-10-05

Page 31

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

57-30-005 NDI inspection of

wing lower skin,

wing STN 115 to

151 at main spar

fasteners left and

right (Ref. NDI

manual Chap.

57-30-005, high

frequency eddy

current).

23,200 landings 6,000 landings

57-30-210 NDI inspection of

the MLG cut-out

lower forward

doubler, skin and

repair strap

between wing STN’s

46 and 67 (Ref. SB

51-JA020940

Appendix 2, Part

12).

36,800 landings 7,400 landings

57-30-211 NDI inspection of

the wing lower

skin, at inboard

end of auxiliary

spar boom and MLG

cut-out doubler

between STN’s2 64

and 70, (Ref SB

57-JA021140).

20,000 landings 20,000 landings

05-10-05

Page 32

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

57-30-213 Detail visual

inspection of the

lower skin MLG

cut-out at STN’s

67 to

115 (Ref. Figure 24),

(Ref SB 51-

JA020940 Appendix

2, Part 6.

20,000 landings 20,000 landings

57-30-215 NDI inspection of

the wing bottom

skin at landing

gear bay left and

right, (Ref SB

57-JA930640).

10,000 landings 10,000 landings

57-30-217 Detail visual

inspection of the

top skin flap

shroud (Ref. Figure 25),

(Ref SB 51-

JA020940 Appendix

2, Part 7).

33,700 landings 39,000 landings

57-30-219 Detail visual

inspection of the

lower skin/front

spar between STN’s

115 and 133.

40,500 landings 9,300 landings

57-30-221 Detail visual

inspection of the

lower skin access

panel cut-out

between STN’s 115

and 133.

39,800 landings 5,400 landings

05-10-05

Page 33

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

57-30-223 NDI inspection of

the top skin rib

36 butt strap (Ref

NDI manual Chap.

57-30-23, low

frequency eddy

current).

44,900 landings 3,400 landings

57-40-001 Detail visual

inspection of main

spar attachment

fitting,

attachment lug and

fuselage vertical

post left and

right (Ref. Figure 26).

Access F21 and

F22.

4,000 flying

hrs

4,000 flying

hrs

57-40-002 Torque check of

landing gear hinge

fitting attachment

bolts to rear

spars left and

right (Ref. Chap.

57-40-07).

14,000 landings 7,000 landings

57-40-003 Detail visual

inspection of the

main landing gear

radius rod

attachment

brackets left and

right

1,200 flying

hrs

1,200 flying

hrs

05-10-05

Page 34

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

57-40-004 Detail visual

inspection of

engine mounting,

attachment

fittings at STN 99

and 115 and front

spar behind

fireshield left

and right. Access

panels E8, E9 and

E11 removed,

(Ref. Figure 27),

(Ref. Chapter

71-20-00).

9,000 flying

hrs

4,000 flying

hrs

57-40-005 Detail visual

inspection with

particular

attention to lug

ends left and

right

(Ref. Figure 28),

(view A).

9,300 landings 9,300 landings

57-40-006 Detail visual

inspection with

particular

attention to lug

end left and right

(Ref. Figure 28),

(view B).

30,200 landings 5,800 landings

05-10-05

Page 35

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

57-40-007 Detail visual

inspection with

particular

attention to lug

end left and right

(Ref. Figure 28),

(view C).

22,800 landings 5,800 landings

57-40-008 Detail visual

inspection and

torque check of

bolts attaching

inboard flap hinge

bracket to wing

(Ref. Figure 29)

and (Ref. Chap.

20-00-00).

22,500 landings 8,000 landings

57-40-211 NDI inspection of

front spar spigot

plate (Ref. SB

57-JA921144).

Refer to SB

57-JA921144 for

the initial

frequency of

this

maintenance

task.

64,000 landings

05-10-05

Page 36

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

57-50-001 Remove all bolts

individually.

Inspect for

corrosion and

cracks, (Ref. NDI

manual Chap. 57-

50-05 and 57-50-

07, magnetic

particle). Detail

visual inspection

of the bore from

which the

particular bolt

has been taken,

(Ref. Chap.

27-10-11 and

27-50-31).

6 years 6 years

57-50-002 Remove all bolts

individually.

Inspect for

corrosion and

cracks, (Ref. NDI

manual Chap. 57-

50-05 and 57-50-

07, magnetic

particle).

Detail visual

inspection of the

bore from which

the particular

bolt has been

taken, (Ref.

Chapter 27-10-11

and Chapter

27-50-31).

6 years 6 years

05-10-05

Page 37

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE TASK NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

57-50-007 NDI inspection of

the flap operating

lever bolt, nut

and

lug (Ref. Figure 30),

(Ref SB 51-

JA020940 Appendix

2, Part 8).

15,000 flying

hours

15,000 flying

hours

57-50-021 Detail visual

inspection of the

aileron upper and

lower spar

boom (Ref. Figure 31),

(Ref SB 51-

JA020940 Appendix

2, Part 9).

22,500 landings 7,500 landings

57-50-023 Detail visual

inspection of the

aileron upper and

lower skin at the

spar

positions (Ref. Figure 31),

(Ref SB 51-

JA020940 Appendix

2, Part 10).

22,500 landings 1,600 landings

57-50-027 NDI inspection of

the aileron

operating lever

bolt, nut and

lug (Ref. Figure 32),

(Ref SB 51-

JA020940 Appendix

2, Part 11).

15,000 flying

hours

15,000 flying

hours

05-10-05

Page 38

Dec 15/12 mm360

Printed in the U.K.
NOTE : 1. Refer to SB 51-JA020940 for grace period of this

maintenance task. Ref. AD G-2004-0017 or superseding

AD.

NOTE : 2. Refer to SB 57-JA020740 for grace period of this

maintenance task. Ref. AD 006-02-2003 or superseding

AD.

NOTE : 3. Refer to SB 55-JA020543 for grace period of this

maintenance task. Ref. AD 004-10-2002 or superseding

AD.

NOTE : 4. Refer to SB 57-JA920540 for grace period of this

maintenance task. Ref. AD 001-09-92 or superseding

AD.

NOTE : 5. Refer to SB 57-JA021140 for grace period of this

maintenance task. Ref. AD 005-06-2003 or superseding

AD.

NOTE : 6. Refer to SB 57-JA930640 for grace period of this

maintenance task. Ref. AD 004-09-93 or superseding

AD.

NOTE : 7. Refer to SB 05-JA090143 for grace period of this

maintenance task (Ref. AD No. 2010-0162).

3. Airworthiness limitations (Airframe - Systems)

CAUTION - IT IS THE OPERATORS RESPONSIBILITY TO MAKE SURE TIME

LIMITS OR LIFE LIMITS FOR ITEMS COVERED BY THE

STATEMENT IN THIS CHAPTER ARE NOT EXCEEDED.

A. Electrical Power

The item reference number given against the following

maintenance tasks refer to the item reference numbers used

in the Maintenance Schedule.

05-10-05

Page 39

Dec 15/12 mm360

Printed in the U.K.
Table No. 8

ITEM REF. AND

DESCRIPTION

MAINTENANCE

TASK

NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

24-00-001

Electrical

power

distribution

STN 130 left

and right

(a) Detail

visual with

panels

removed,

zone F130.

(b) Torque

check heavy

duty

connections,

(Ref. Chap.

20-10-00).

4,000 flying

hours

4,000 flying

hours

24-00-002

Electrical

power

distribution

box nose

equipment bay

(a) Detail

visual with

cover

removed,

zone F120,

access

panel F3.

(b) Torque

check heavy

duty

connections

(Ref. Chap.

20-10-00).

4,000 flying

hours

4,000 flying

hours

24-00-004

Generator/

Starter lead

attachments

(a) General

visual

(Chafing).

(b) Torque

check

connections.

4,000 flying

hours

4,000 flying

hours

24-30-203

Generator line

contactors (Qty

2)

Torque check

heavy duty

connections

(Ref. Chap.

24-00-03).

4,000 flying

hours

4,000 flying

hours

05-10-05

Page 40

Dec 15/12 mm360

Printed in the U.K.
B. Flying Controls

Table No. 9

ITEM REF. AND

DESCRIPTION

MAINTENANCE

TASK

NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

27-20-010

Pre Mod 5301

only: Rudder

pedal/brake

master cylinder

attachment

brackets (Qty

4), Part Nos.

137317E401/402

or

A137317E401/402

Detail visual

inspection for

cracks. Refer

to SB

27A-JA880145 (Ref. Figure 33)

3,000 landings 400 landings

27-70-000

Gust lock

system

Functional

check of gust

lock system.

Detail visual

for engagement/

disengagement

and clearances,

(Ref. Chap.

27-70-00).

1,200 flying

hours

1,200 flying

hours

C. Ice and rain protection

Table No. 10

ITEM REF. AND

DESCRIPTION

MAINTENANCE

TASK

NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

30-42-002

Wiper arm

assemblies

Detailed visual

inspection of

the wiper arm

assemblies

(Ref. Chap.

30-42-02 and SB

30-JA950641).

4 Years 4 Years

05-10-05

Page 41

Dec 15/12 mm360

Printed in the U.K.
ITEM REF. AND

DESCRIPTION

MAINTENANCE

TASK

NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

30-60-000

Propeller blade

de-icing system

Apply Icex

*Whenever icing

conditions are

likely to be

encountered,

(Ref. Chap.

12-30-07).

*50 flying

hours

*50 flying

hours

Table No. 11

PART NUMBER DESCRIPTION MANDATORY LIFE LIMITS

MS20073-03-04 Wiper attachment bolt 2 Years

AN3CH4A Wiper attachment bolt 8 Years

2314M17-15 Wiper arm assembly 8 years

XW20437121850-B4 Wiper arm assembly 8 years

D. Lighting

Table No. 12

ITEM REF. AND

DESCRIPTION

MAINTENANCE

TASK

NOT EXCEED

FREQUENCY

INITIAL

NOT EXCEED

FREQUENCY

REPEAT

33-20-000

Cabin lights

Inspection of

cabin

fluorescent

lighting and

power unit

wiring. Refer

to SB 33-A-JA

891240 for

applicability.

2,500 flying

hours or 1 year

2,500 flying

hours or 1 year

j0510018.tif 3163b.tif j0510001.tif j0510002.tif j0510003.tif j0510027.tif j0510004.tif j0510005.tif j0510006.tif j0510019.tif j0510007.tif j0510021.tif j0510022.tif j0510023.tif j0510020.tif j0510024.tif j0510025.tif j0510009.tif j0510010.tif j0510026.tif 3178b.tif j0510011.tif j0510012.tif j0510013.tif j0510014.tif 5106b.tif 3180b.tif 3181b.tif 3182b.tif j0510015.tif j0510016.tif j0510017.tif 3161b.tif

05-10-05

Page 42

Dec 15/12 mm360

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Inspection - STN 52

Figure 1

05-10-05

Page 43

Dec 15/12 mm360

Printed in the U.K.
Inspection - NLG trunnion

Figure 2

05-10-05

Page 44

Dec 15/12 mm360

Printed in the U.K.
Inspection - front pressure bulkhead forward face

Figure 3

05-10-05

Page 45

Dec 15/12 mm360

Printed in the U.K.
Inspection - front pressure bulkhead rear face

Figure 4

05-10-05

Page 46

Dec 15/12 mm360

Printed in the U.K.
Inspection - frame 75.15

Figure 5

05-10-05

Page 47

Dec 15/12 mm360

Printed in the U.K.
Inspection - frame 89.15 and 109.75, stringer cleats and external

skin

Figure 6

05-10-05

Page 48

Dec 15/12 mm360

Printed in the U.K.
Inspection - frame 89.15

Figure 7

05-10-05

Page 49

Dec 15/12 mm360

Printed in the U.K.
Inspection - frame 109.75

Figure 8

05-10-05

Page 50

Dec 15/12 mm360

Printed in the U.K.
Inspection - escape hatch surround structure

Figure 9

05-10-05

Page 51

Dec 15/12 mm360

Printed in the U.K.
Inspection - window pans and intercostals

Figure 10

05-10-05

Page 52

Dec 15/12 mm360

Printed in the U.K.
Inspection - passenger door surround frames at stations 345 and 381

Figure 11

05-10-05

Page 53

Dec 15/12 mm360

Printed in the U.K.
Inspection - forward face of rear pressure bulkhead

Figure 12

05-10-05

Page 54

Dec 15/12 mm360

Printed in the U.K.
Inspection - forward face of rear pressure bulkhead

Figure 13

05-10-05

Page 55

Dec 15/12 mm360

Printed in the U.K.
Inspection - stringer cleats at rear pressure bulkhead

Figure 14

05-10-05

Page 56

Dec 15/12 mm360

Printed in the U.K.
Inspection - angle attachment, RPB to APU surround structure

Figure 15

05-10-05

Page 57

Dec 15/12 mm360

Printed in the U.K.
Inspection - rear face of rear pressure bulkhead

Figure 16

05-10-05

Page 58

Dec 15/12 mm360

Printed in the U.K.
Inspection - vertical stabilizer joint-plate drag-angle

Figure 17

05-10-05

Page 59

Dec 15/12 mm360

Printed in the U.K.
Inspection - flap/wing hinge lugs, bolts and nuts

Figure 18

05-10-05

Page 60

Dec 15/12 mm360

Printed in the U.K.
Inspection - aileron/wing hinge lugs, bolts and nuts

Figure 19

05-10-05

Page 61

Dec 15/12 mm360

Printed in the U.K.
Inspection - main spar to stringer joint

Figure 20

05-10-05

Page 62

Dec 15/12 mm360

Printed in the U.K.
Inspection - main spar vertical post attachment bolts

Figure 21

05-10-05

Page 63

Dec 15/12 mm360

Printed in the U.K.
Inspection - top skin/main spar cleat and wing root

Figure 22

05-10-05

Page 64

Dec 15/12 mm360

Printed in the U.K.
Inspection - skin attachment at rib 115

Figure 23

05-10-05

Page 65

Dec 15/12 mm360

Printed in the U.K.
Inspection - sealing angle main undercarriage cut-out STN 83 to 99

and lower skin MLG cut-out at STN 67 to 115

Figure 24

05-10-05

Page 66

Dec 15/12 mm360

Printed in the U.K.
Inspection - top skin flap shroud

Figure 25

05-10-05

Page 67

Dec 15/12 mm360

Printed in the U.K.
Inspection - main spar attachment fitting

Figure 26

05-10-05

Page 68

Dec 15/12 mm360

Printed in the U.K.
Inspection - engine mounting attachment fittings

Figure 27

05-10-05

Page 69

Dec 15/12 mm360

Printed in the U.K.
Inspection - engine mount attachments

Figure 28

05-10-05

Page 70

Dec 15/12 mm360

Printed in the U.K.
Inspection - inboard flap hinge attachment brackets

Figure 29

05-10-05

Page 71

Dec 15/12 mm360

Printed in the U.K.
Inspection - flap operating lever bolt, nut and lug

Figure 30

05-10-05

Page 72

Dec 15/12 mm360

Printed in the U.K.
Inspection - typical section of aileron

Figure 31

05-10-05

Page 73

Dec 15/12 mm360

Printed in the U.K.
Inspection - aileron operating lever, bolt, nut and lug

Figure 32

05-10-05

Page 74

Dec 15/12 mm360

Printed in the U.K.
Inspection - master cylinder attachment brackets

Figure 33

05-10-05

Page 75

Dec 15/12 mm360

Printed in the U.K.
Page left intentionally blank
** For Aircraft ALL**

CHECK AFTER HEAVY OR ABNORMAL LANDING

INSPECTION CHECK

1. Check After Heavy or Abnormal landing

A. General

The aircraft is designed for a vertical descent velocity of

10 ft/second (3.05 m/second) at maximum permissible landing

weight, and a vertical descent velocity of 6 ft/second (1.83

m/second) at maximum permissible take-off weight.

Do the following checks when it is suspected that the

vertical descent velocity has exceeded 10 ft/second.

Also do the checks if the pilot reports an abnormally heavy

landing, or a landing at more that the maximum permissible

landing weight when descent velocity exceeds 6 ft/second.

B. Procedure

(1) Examinations and checks

Examine the following specific areas for damage and,

where necessary, check doors, emergency exits and

access panels.

(a) Fuselage

1 Examine:

- Skin to frame attachment.

- Wing to fuselage attachments.

- Vertical post attachments at STN 199, 223 and

257.

- Rear fuselage skin for wrinkling.

- Fuel and oil leakage.

2 Check emergency exits and entrance door for

ease of operation.

3 Examine:

- Rear bulkhead fuselage STN 463 for skin

wrinkling and defective, loose or missing

rivets in web reinforcing members retaining

vertical stabilizer attachments.

- Forward pressure bulkhead for distortion or

05-50-10

Page 601

Dec 15/12 mm360

Printed in the U.K.
cracking, particularly in the area of nose

landing gear mountings.

4 Check for signs of fuel and hydraulic fluid

leakage.

5 Examine:

-

(b) Tail unit

1 Examine

- Horizontal stabilizer to vertical stabilizer

attachments.

- Vertical stabilizer to fuselage attachments

at rear pressure bulkhead, fuselage STN 421

and STN 463.

- Stabilizer skins for wrinkling and defective,

loose or missing rivets.

- Elevator hinges and horn mass balance.

- Rudder torque tube bottom bearing.

- Rudder hinges.

(c) Wings

1 Examine:

- Skin to rib attachments.

- Aileron hinges and horn mass balance.

- Aileron skin in area of mass balance arm.

- Flap hinges, particularly for cracks.

2 Check for signs of fuel and hydraulic fluid

leakage.

(d) Main landing gear (Ref. Figure 601)

1 Remove main wheel units for specialist

examination (Ref. Chapter 32-40-11, page block

201).

2 Check landing gear leg extension and pressure

in accordance with graph as detailed in Chapter

12-10-32, page block 001.

3 Do a functional test of landing gear (Ref.

Chapter 32-30-00, page block 201 ). Make sure

landing gear locks and warning systems operate

05-50-10

Page 602

Dec 15/12 mm360

Printed in the U.K.
correctly.

4 In the event of a tyre burst or shredding of a

tread, the main landing gear must be checked in

accordance with the instructions given in

Chapter 05-50-21, page block 001.

5 Examine brake units for signs of overheating in

accordance with Chapter 32-40-71, page block

201.

6 Examine wing landing gear attachments and

surrounding structure.

7 Examine yoke pintle housing on both main

landing gear attachment spigots as follows:

- Clean areas to be inspected.

- Visually inspect areas indicated

on (Ref. Figure 601) for signs of cracking.

- Protect with lanolin any areas where surface

finish has been removed.

Refer to SB 32-A-JA851226. This Service

Bulletin references BAe (Dynamics) Limited

Service Bulletin 32-19. If the main landing

gear is covered by the effectivity of Service

Bulletin 32-19, accomplish the Non-Destructive

Test specified in Section 1.M.3 of SB 32-

A-JA851226.

(e) Nose landing gear

1 Examine:

- Fuselage/nose landing gear attachments and

surrounding structure.

- Down lock and surrounding structure.

2 Remove nose wheel units for specialist

examination.

3 Check landing gear leg extension and pressure

in accordance with graph as detailed in Chapter

12-10-32, page block 001.

05-50-10

Page 603

Dec 15/12 mm360

Printed in the U.K.
4 Do a functional test of landing gear, (Ref.

Chapter 32-30-00, page block 201 ). Make sure

landing gear locks and warning systems operate

correctly.

5 In the event of a tyre burst or shredding of a

tread, the nose landing gear must be checked in

accordance with the instructions given in

Chapter 05-50-21, page block 001.

(f) Power plant

1 Examine:

- Firewalls for distortion and cracking.

- Firewall mountings.

- Engine bearers, particularly for bowing.

2 Check for fuel, oil and hydraulic fluid

leakage.

(g) Propellers

Refer to Chapter 61 for examination following hazardous

incidents.

(h) Radio equipment

1 Examine radio racks and components for damage

and security of attachment.

2 Do a functional test of radio equipment.

(i) Instruments/panels

1 Examine:

- Instrument panels for damage and security of

attachment.

- Instruments for security.

2 Do a functional test of the instruments.

(j) Electrical

1 Examine:

- Batteries and battery mountings for damage

and security of attachment.

- Batteries for evidence of spilt electrolyte.

05-50-10

Page 604

Dec 15/12 mm360

Printed in the U.K.
(k) Flying controls

1 Do a functional test of the flying and trim

controls (Ref. Chapters 27-10-00, 27-20-00,

27-30-00, 27-50-00, 27-70-00, page block 201).

(l) Access panels and fairings

1 Examine panels and fairings for distortion and,

where necessary, correct fitting.

(m) Portable equipment

1 Examine for damage and security of attachment

stowages and mountings for fire extinguishers,

axes, life rafts etc.

(2) Structural damage

If structural damage is found, do the following checks

and tests:

(a) Airframe rigging check (Ref. Chapter 05-50-05, page

block 601 ).

(b) Aircraft symmetry check (Ref. Chapter 05-50-05,

page block 601 ).

(c) Pressurization system functional test (Ref. Chapter

j0550001.tif 21-30-00, page block 201 ).

05-50-10

Page 605

Dec 15/12 mm360

Printed in the U.K.
Main Landing Gear Pintle Housing - Crack Inspection

Figure 601

05-50-10

Page 606

Dec 15/12 mm360

Printed in the U.K.
CHAPTER 06

LIST OF EFFECTIVE PAGES

CHAPTER/SECTION/SUBJECT PAGE DATE

CONTENTS 1 Apr 15/08

2 Apr 15/08

06-00-00 1 Oct 30/98

2 Oct 30/98

06-00-05 1 Oct 30/98

2 Oct 30/98

3 Oct 30/98

4 Oct 30/98

06-00-07 1 Nov 15/01

2 Oct 30/98

3 Feb 15/01

4 Feb 15/01

5 Feb 15/02

6 Feb 15/02

7 Feb 15/02

8 Feb 15/02

9 Feb 15/02

06-00-09 1 Oct 30/98

2 Oct 30/98

3 Oct 30/98

4 Oct 30/98

06-00-13 1 Dec 15/12

2 Dec 15/12

3 Dec 15/12

4 Dec 15/12

06-LEP

Page 1

Dec 15/12 mm360

Printed in the U.K.
CHAPTER/SECTION/SUBJECT PAGE DATE

5 Dec 15/12

6 Dec 15/12

7 Dec 15/12

8 Dec 15/12

9 Feb 15/01

10 Dec 15/12

11 Dec 15/12

12 Feb 15/01

13 Dec 15/12

14 Dec 15/12

15 Dec 15/12

06-00-15 1 Dec 15/99

2 Dec 15/99

06-LEP

Page 2

Dec 15/12 mm360

Printed in the U.K.
** For Aircraft ALL**

ACCESS PANELS

DESCRIPTION AND OPERATION

1. General

NOTE : With regard to installation of access panels or

equipment/components removed for access purposes and

then re-installed. Maintenance personnel are to check

the affected zone for freedom from foreign objects such

as rags, tools, etc., for freedom from accidental

damage, and for freedom from any obstructions to access

panels or other such access item. This is to be carried

out as the final task before leaving the zone.

The figures and associated keys in this chapter show the

aircraft access panel locations (Ref. Figure 1)

3612b.tif thru (Ref. Figure 6)

Panel No Item/ref Access to Chapter

F1 1SN3 Weather radar antenna 34-43-15

1SN4 Weather radar transceiver 34-43-15

1RE6 Glideslope antenna 34-53-28

F2 Nicotine filter 21-30-03

1CA4 Autopilot computer 22-11-00

1CA55 Autopilot disengage unit 22-11-00

2XB4 Inverter main ac power 24-20-00

2XB12 Circuit breaker 26V AC MAIN 24-20-00

1PD1 No.1 battery 24-30-10

2HL11 Circuit breaker right windshield 30-41-00

2HL22 Capacitor 30-41-00

2HL23 Capacitor 30-41-00

2HL24 Capacitor 30-41-00

2HL10 Inverter - right windshield power 30-41-13

06-00-13

Page 1

Dec 15/12 mm360

Printed in the U.K.
Access Panels - Fuselage Upper and Lower

Figure 1

06-00-13

Page 2

Dec 15/12 mm360

Printed in the U.K.
Panel No Item/ref Access to Chapter

1CN2 Air data computer 34-10-35

1RD2 No.1 ADF receiver 34-53-34

1RD12 No.2 ADF receiver 34-53-34

2FC3 No.2 directional gyro 34-21-13

1FF3 Flight director computer 34-27-00

1SX3 No.1 ATC transponder 34-51-34

1SX6 Transponder control adapter 34-51-34

1SX9 No.2 ATC transponder 34-51-34

1RE3 No.1 VHF nav receiver 34-53-28

1RE13 No.2 VHF nav receiver 34-53-28

1RD13 No.2 ADF converter 34-53-34

Avionics junction box

F3 Nicotine filter 21-30-03

1RF2 No.1 VHF comms transceiver 23-13-25

1RF12 No.2 VHF comms transceiver 23-13-25

** For Aircraft 974-976 978-980**

1RX11 CVR relay 23-71-00

** For Aircraft ALL**

1XB3 Relay - ess inverter fail 24-00-00

1XB10 Relay - ess bus to main inverter 24-00-00

1XB11 Relay - inverter synchrophase 24-00-00

2XB3 Relay - main inverter fail 24-00-00

2XB10 Relay - main bus to ess inverter 24-00-00

1XB4 Inverter ess ac power 24-20-00

1XB12 Circuit breaker 26V AC ESS 24-20-00

DC control box 24-30-05

06-00-13

Page 3

Dec 15/12 mm360

Printed in the U.K.
Panel No Item/ref Access to Chapter

2PB2 Right generator control unit 24-30-05

1PB2 Left generator control unit 24-30-05

2PD1 No.2 battery 24-30-10

1PC6 Circuit breaker 7.5A ground power

sensing

24-50-00

1PC7 Circuit breaker 1A ground power

indication

24-40-00

1PD36 Circuit breaker 35A engine

ancillary power

24-50-00

1PD41 Circuit breaker 3A engine ancillary

control

24-50-00

1PD42 Circuit breaker 1A battery series

warning

24-50-00

1WL10 Switch - stick pusher reset 27-35-19

1HL11 Circuit breaker left windshield 30-41-00

1HL22 Capacitor 30-41-00

1HL23 Capacitor 30-41-00

1HL24 Capacitor 30-41-00

1HL10 Inverter left windshield power 30-41-13

1LD5 Relay - taxi light control 33-40-10

1PD5,

1PD6

Outside air temperature sensor

connectors

34-10-26

1FD2 No.1 vertical gyro 34-20-41

2FD2 No.2 vertical gyro 34-20-41

1FC3 No.1 directional gyro 34-21-13

1SX7 Transponder co-axial relay 34-51-34

1RA8 Marker system diplexer 34-53-28

1RE13 No.2 VHF nav receiver 34-53-28

1RD2 No.1 ADF receiver 34-53-34

1RD3 No.1 ADF converter 34-53-34

06-00-13

Page 4

Dec 15/12 mm360

Printed in the U.K.
Panel No Item/ref Access to Chapter

1RD12 No.2 ADF receiver 34-53-34

1SD2 No.2 DME transceiver 34-53-36

T1BG Terminal block

T1AE Terminal block

T1AF Terminal block

Avionics relay box

2SD2 No.2 DME transceiver 34-53-46

F4 T2AW Tail cone terminal block

F5 T2AW Tail cone terminal block

1CA10 Autopilot rudder servo-motor 22-11-00

Rudder lock unit assembly 27-70-07

F6 Entrance door 52-00-00

F7 (Ref. Figure 5)

F8 (Ref. Figure 5)

F9 (Ref. Figure 5)

F9A (Ref. Figure 5)

F10 Flight controls 27-00-00

Hydraulics 29-00-00

F11 Flight controls 27-00-00

Hydraulics 29-00-00

F12 Brake accumulator servicing panel 29-10-00

F13 Nose jacking point 07-10-00

F14 Nose door operating rods 32-20-31

F15 Nose landing gear 32-20-11

F16 Nose landing gear 32-20-11

F17 1PC1 Ground supply plug 24-40-05

EP1A Main earth point 24-40-05

06-00-13

Page 5

Dec 15/12 mm360

Printed in the U.K.
Panel No Item/ref Access to Chapter

F18 Nose door operating rods 32-20-31

F19 1WA3 Fire detection control unit - left 26-10-15

F20 2WA3 Fire detection control unit - right 26-10-15

F21 Water separator 21-10-19

Check valve 21-10-25

Refrigeration unit 21-50-00

1HF10 Overtemperature switch 21-60-05

Jet pump 21-60-08

1HF9 Temperature control valve 21-60-09

1HF8 Duct temperature sensor 21-60-19

1DK3 Flap position transmitter 27-50-03

1CG9 Flap selector valve 27-50-11

1CG10 Lift dump selector valve 27-50-11

Flap jack 27-50-25

Flap jack thermal relief valve 27-50-27

Crossfeed cock 28-20-15

Accumulator pressure gauge 29-10-00

Check valve 29-10-23

Pressure relief valve 29-10-25

Pressure filter 29-10-27

Air/nitrogen charging valve 29-10-31

Return filter assembly 29-10-33

Case drain filter 29-10-35

Drain valve - reservoir vent system 29-10-39

Sampling valve 29-10-43

Ground test coupling 29-10-45

Check valve - hand pump 29-20-07

06-00-13

Page 6

Dec 15/12 mm360

Printed in the U.K.
Panel No Item/ref Access to Chapter

1DN4 Pressure transmitter 29-30-05

1UB17 FDR flap position potentiometer 31-38-00

1WT2 High pressure switch 29-30-07

Selector valve 32-30-21

F22 Water separator 21-10-19

Check valve 21-10-25

Refrigeration unit 21-50-00

1HF10 Overtemperature switch 21-60-05

1HF9 Temperature control valve 21-60-09

1HF8 Duct temperature sensor 21-60-19

1DK3 Flap position transmitter 27-50-03

Crossfeed cock 28-20-15

Pressure relief valve 29-10-25

Pressure filter 29-10-27

Air/nitrogen charging valve 29-10-31

Return filter assembly 29-10-33

Drain valve - reservoir vent system 29-10-39

Ground test coupling 29-10-45

Check valve - hand pump 29-20-07

1DN4 Pressure transmitter 29-30-05

1WT2 High pressure switch 29-30-07

1HR6 Pressure switch (wing) 30-10-13

Selector valve 32-30-21

F23 Flight controls 27-00-00

Hydraulics 29-00-0

F24 Hydraulic reservoir 29-10-11

F25 Oxygen charging panel 12-10-35

06-00-13

Page 7

Dec 15/12 mm360

Printed in the U.K.
Panel No Item/ref Access to Chapter

F26 Rear pressure bulkhead

1CA8 Autopilot elevator trim servo-motor 22-11-00

1CA9 Autopilot elevator servo-motor 22-11-00

** For Aircraft 974-976 978-980**

1RX2 Cockpit voice recorder 23-71-00

1RX8 CVR inertia switch 23-71-00

** For Aircraft ALL**

1RM1 Emergency locator transmitter 25-60-15

1RM3 ELT antenna connector 25-60-15

1WL17 Elevator stall warning pusher unit 27-35-05

Elevator lock nut assembly 27-70-09

1UB3 Flight data recorder 31-35-00

2LJ4 Upper anti-collision strobe power

unit

33-45-02

F27 Manifold blocks 27-50-09

F28 Manifold blocks 27-50-09

F29 Baggage pod side panels 25-51-00

F30 Baggage pod side panels 25-51-00

F31 Baggage pod side panels 25-51-00

F32 Baggage pod side panels 25-51-00

WF1 Hydraulic reservoir 29-10-11

WF2 Flap hydraulic release valve 27-50-25

WF3 Hydraulic service panel 29-10-00

WF4 Flap hydraulic release valve 27-50-25

3614b.tif

06-00-13

Page 8

Dec 15/12 mm360

Printed in the U.K.
Access Panels - Left Wing, Upper and Lower

Figure 2 06-00-13

Page 9

Feb 15/01 mm360

Printed in the U.K.
Panel No Item/ref Access to Chapter

W1 1LK3 Navigation strobe light 33-40-15

W3 Fuel filler cap 28-00-00

W5 Leading edge de-icing equipment 30-00-00

W7 1LD4 Landing light 33-40-05

W9 De-icing equipment 30-00-00

W11 LP fuel cock 28-20-07

W13 Case drain check valve 29-10-37

W15 Hydraulic pipelines 29-00-00

Engine controls 76-00-0

W17 Aileron control and hinge - inboard 57-50-07

W19 Aileron hinge - centre 57-50-07

W21 Aileron hinge - outboard 57-20-07

W23 Fuel cell 28-42-11

W25 Fuel cell 28-42-11

W27 Fuel cell 28-42-11

W29 Fuel cell 28-42-11

W31 Fuel cell 28-42-11

W33 Heatshield 21-10-13

Boost pump 28-20-11

W33A Boost pump canister 28-20-11

W35 Structure 32-00-00

W37 Flap hinge - inboard 57-20-07

W39 Flap hinge - centre 57-20-07

W41 Flap joint 57-50-05

W43 Integral tank structure and fuel

contents system

28-00-00

W45 Integral tank structure and fuel

contents system

28-00-00

06-00-13

Page 10

Dec 15/12 mm360

Printed in the U.K.
Panel No Item/ref Access to Chapter

W47 Integral tank structure and fuel

contents system

28-00-00

W49 Integral tank structure and fuel

contents system

28-00-00

W51 Flap hinge - outboard 57-20-07

W53 Integral tank structure and fuel

contents system

28-00-00

W55 Integral tank structure and fuel

contents system

28-00-00

W57 Integral tank structure and fuel

contents system

28-00-00

W59 Integral tank structure and fuel

contents system

28-00-00

W61 Integral tank structure and fuel

contents system

28-00-00

W63 Integral tank structure and fuel

contents system

28-00-00

W65 Vent tank 28-00-00

W67 Aileron final drive closing panel 27-10-12

3616b.tif

Panel No Item/ref Access to Chapter

W2 2LK3 Navigation strobe light 33-40-15

W4 Fuel filler cap 28-00-00

W6 Leading edge de-icing equipment 30-00-00

W8 2LD4 Landing light 33-40-05

W10 De-icing equipment 30-00-00

W12 LP fuel cock 28-20-07

Thermal relief valve 28-20-17

W14 Hydraulics 29-00-00

De-icing equipment 30-00-00

Engine controls 76-00-00

06-00-13

Page 11

Dec 15/12 mm360

Printed in the U.K.
Access Panels - Right Wing, Upper and Lower

Figure 3 06-00-13

Page 12

Feb 15/01 mm360

Printed in the U.K.
Panel No Item/ref Access to Chapter

W16 Release valve 27-50-00

Case drain check valve 29-10-37

W18 Aileron control and hinge - inboard 57-50-07

W20 Aileron hinge - centre 57-50-07

W22 Aileron hinge - outboard 57-20-07

W24 Fuel cell 28-42-11

W26 Fuel cell 28-42-11

W28 Fuel cell 28-42-11

W30 Fuel cell 28-42-11

W32 Fuel cell 28-42-11

W34 Heatshield 21-10-13

2QG3 Boost pump 28-20-11

W34A Boost pump canister 28-20-11

W36 Structure 32-00-00

W38 Flap hinge - inboard 57-20-07

W40 Flap hinge - centre 57-20-07

W42 Flap joint 57-50-05

W44 Integral tank structure and fuel

contents system

28-00-00

W46 Integral tank structure and fuel

contents system

28-00-00

W48 Integral tank structure and fuel

contents system

28-00-00

W50 Integral tank structure and fuel

contents system

28-00-00

W52 Flap hinge - outboard 57-20-07

W54 Integral tank structure and fuel

contents system

28-00-00

W56 Integral tank structure and fuel

contents system

28-00-0

06-00-13

Page 13

Dec 15/12 mm360

Printed in the U.K.
Panel No Item/ref Access to Chapter

W58 Integral tank structure and fuel

contents system

28-00-00

W60 Integral tank structure and fuel

contents system

28-00-00

W62 Integral tank structure and fuel

contents system

28-00-00

W64 Integral tank structure and fuel

contents system

28-00-00

V15 Tailplane attachments 55-00-00

V16 Rudder torque tube gust locks 27-70-0

V17 Tailplane attachments 55-00-00

V18 Tailplane attachments 55-00-00

V19A Tailplane attachment bolts 55-00-00

V19B Tailplane attachment bolts 55-00-00

V20 Tailplane attachment bolts 55-00-00

V21A Elevator torque tube 55-20-00

V21B Elevator torque tube 55-20-00

V22 1RE7P VOR/LOC antenna connection 34-53-28

V23 Rudder trim tab controls 27-23-11

V24 Rudder tab screwjack 27-23-11

5034b.tif

06-00-13

Page 14

Dec 15/12 mm360

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Access Panels - Power Plant Cowlings

Figure 6

06-00-13

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CHAPTER 22

LIST OF EFFECTIVE PAGES

CHAPTER/SECTION/SUBJECT PAGE DATE

CONTENTS 1 Apr 15/08

CONTENTS 2 Oct 15/04

22-00-00 1 Oct 30/98

22-00-01 1 Jun 15/01

22-11-00 1 Feb 15/01

2 Feb 15/01

3 Oct 30/98

4 Feb 15/01

5 Oct 30/98

6 Feb 15/01

7 Oct 30/98

8 Oct 30/98

9 Oct 30/98

10 Oct 30/98

11 Oct 30/98

12 Oct 30/98

13 Oct 30/98

14 Feb 15/01

15 Feb 15/01

16 Jul 15/01

17 Jul 15/01

18 Jul 15/01

19 Jul 15/01

20 Jul 15/01

22-11-00 401 Oct 30/98

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406 Oct 30/98

407 Oct 30/98

408 Oct 30/98

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410 Oct 30/98

411 Oct 30/98

22-11-00 501 May 15/04

502 May 15/04

503 Oct 15/04

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505 Oct 15/04

506 Oct 15/04

507 Oct 15/04

508 Oct 15/04

509 Oct 15/04

510 Oct 15/04

511 Oct 15/04

512 May 15/04

513 Oct 15/04

514 May 15/04

515 May 15/04

516 May 15/04

517 Oct 15/04

518 Oct 15/04

519 Dec 15/12

520 Oct 15/04

521 Oct 15/04

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526 Oct 15/04

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528 Oct 15/04

529 Oct 15/04

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STEP ACTION RESULT

(6) Engage A/P. Press GO AROUND

switch on left power lever.

(a) Audible warning for 1

second.

(b) A/P DIS’G caption ON for 1

second.

(c) AP and YD ENGAGE captions

extinguish.

(7) Engage A/P. Open avionics

bus-bar circuit breaker, 115V

essential VG 1.

(a) Audible warning for 1

second.

(b) A/P DIS’G caption ON

steady.

(c) AP ENGAGE caption

extinguishes.

(d) YD ENGAGE caption ON

steady.

(8) Close avionics bus-bar circuit

breaker 115V essential VG 1.

(9) Engage A/P. Open avionics

bus-bar circuit breaker 115V

main VG 2.

(a) Audible warning for 1

second.

(b) A/P DIS’G caption ON

steady.

(c) AP ENGAGE captions

extinguish.

(d) YD ENGAGE caption

extinguishes.

(10) Close avionics bus-bar circuit

breaker 115V main VG 2.

(11) Engage A/P. Set No.1 compass

directional gyro INC-DEC

switch INC or DEC (HDG flag

shows).

(a) Audible warning for 1

second.

(b) AP DIS’G caption ON

steady.

(c) AP and YD ENGAGE captions

extinguish.

(12) Engage A/P. Open avionics

bus-bar circuit breaker 28V

main AP.

(a) Audible warning for 1

second.

(b) A/P DIS’G caption ON for 1

second.

(c) AP and YD ENGAGE captions

extinguish.

22-11-00

Page 519

Dec 15/12 mm360

Printed in the U.K.
STEP ACTION RESULT

(13) Close avionics bus-bar circuit

breaker 28V main AP.

(14) Engage A/P. Open avionics

bus-bar circuit breaker 115V

essential AP.

(a) Audible warning for 1

second.

(b) A/P DIS’G caption ON

steady.

(c) AP and YD ENGAGE captions

extinguish.

(15) Close avionics bus-bar circuit

breaker 115V essential AP.

(16) Engage A/P. Press TEST button

on A/P controller.

(a) Audible warning for 1

second.

(b) A/P DIS’G caption ON

steady.

(c) AP and YD ENGAGE captions

extinguish.

(17) Engage A/P. Activate left and

right stall warning system in

turn.

(a) Audible warning for 1

second.

(b) A/P DIS’G caption ON

steady.

(c) AP and YD captions

extinguish.

(7) Pitch rate limit test

STEP ACTION RESULT

(1) Engage A/P. Press PITCH RATE

TEST switch.

A/P disengages within 2.5 to

3.5 seconds.

(2) Release No. 2 VG. Engage A/P.

Manually tilt VG to gently

increase pitch rate to

simulate 3.5 degrees/second.

A/P disengages.

(8) Function test of the Yaw Damper

(a) Remove the bolts attaching the Directional Gyro/

22-11-00

Page 520

Oct 15/04 mm360

Printed in the U.K.
(11)De-energize aircraft ac and dc bus-bars (Ref. Chapter

24-00-00, page block 201 ).

22-11-00

Page 529

Oct 15/04 mm360

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CHAPTER 32

LIST OF EFFECTIVE PAGES

CHAPTER/SECTION/SUBJECT PAGE DATE

CONTENTS 1 Apr 15/08

CONTENTS 2 Apr 15/08

CONTENTS 3 Mar 15/11

CONTENTS 4 Mar 15/11

CONTENTS 5 Mar 15/11

CONTENTS 6 Mar 15/11

CONTENTS 7 Mar 15/11

CONTENTS 8 Mar 15/11

CONTENTS 9 Mar 15/11

CONTENTS 10 Mar 15/11

CONTENTS 11 Mar 15/11

CONTENTS 12 Mar 15/11

CONTENTS 13 Mar 15/11

CONTENTS 14 Mar 15/11

CONTENTS 15 Mar 15/11

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CONTENTS 16 Mar 15/11

CONTENTS 17 Mar 15/11

CONTENTS 18 Mar 15/11

CONTENTS 19 Mar 15/11

32-00-00 1 Dec 15/00

2 Dec 15/00

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2 Oct 30/98

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407 Dec 15/12

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603 Apr 15/08

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32-40-00 301 Apr 15/08

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** For Aircraft ALL**

MAIN GEAR LEG

REMOVAL/INSTALLATION

1. Remove Main Gear Leg Assembly

(Ref. Figure 401) (Ref. Figure 402) (Ref. Figure 403)

A. Special tools and equipment

Table No. 401

ITEM DESIGNATION

None Solvent white sprit

None Jacking equipment (Ref. Chapter

07-10-00)

B. Procedure

NOTE : The weight limit of 11,000 lb. (4990 kg) for jacking

at wing outboard positions may be increased to

11,500 lb. (5216 kg), providing aircraft cg is

forward of STN 220.7.

(1) Make sure aircraft AUW is below 11,000 lb. (4990 kg).

Using jacks at nose and wing STN 145, raise and level

aircraft (Ref. Chapter 08-00-05, page block 001 ).

Position a trestle under rear fuselage at STN 421.

(2) Release hydraulic pressure in main and brake system

(Ref. Chapter 29-10-00, page block 201 ).

(3) Disconnect lockwire and remove door link nut and door

link angled washer, securing landing gear bay door

operating rod to leg. Secure door and rod clear of leg.

(4) Disconnect and remove anti-skid unit (Ref. Chapter

32-40-51, page block 201 ).

(5) Remove main wheel (Ref. Chapter 32-40-11, page block

201 ).

32-10-11

Page 401

Dec 15/12 mm360

Printed in the U.K.
(6) Disconnect and remove brake unit, complete with shuttle

valve (Ref. Chapter 32-40-71, page block 201 ).

(7) Disconnect brake system flexible hoses from bracket on

leg yoke.

(8) Disconnect radius rod from leg and secure to landing

gear bay roof.

(9) Support leg.

(10)Restrain leg yoke. Disconnect and remove yoke bearing

half caps. Ease leg from bearing housing and carefully

remove from landing gear bay. Identify half caps for

subsequent installation.

(11)If new leg is to be installed, proceed as follows:

(a) Open gas charging valve and slowly release

pressure.

(b) Remove free and datum bearings. Clean in solvent

(white spirit) and examine for condition and wear.

(c) Disconnect rigid brake pipes from distribution

block. Install blanking caps to distribution block

and pipe ends.

(d) Disconnect rigid brake pipes mounting bracket from

leg yoke. Release pipe clamp and bracket as a unit.

(e) Disconnect flexible hoses from axle bracket and

distribution block. Slide hoses through collar on

upper toggle and remove, complete with clamp.

Install blanking caps to distribution block and

pipe ends.

(f) Disconnect and remove six unions, complete with

4993b.tif 4996b.tif 4994b.tif O-ring seals.

32-10-11

Page 402

Apr 15/06 mm360

Printed in the U.K.
3. Install Main Landing Gear Leg Assembly

(Ref. Figure 401) (Ref. Figure 403)

A. Special tools and equipment

Table No. 403

ITEM DESIGNATION

None Clinometer

B. Procedure

(1) Make sure toggles on leg face forward. Move leg into

landing gear bay and align yoke bearing spigots with

their associated housings.

(2) Make sure free bearing on rear spigot has wide flanges

facing forward, towards landing gear yoke.

(3) Position bearing half caps on their respective

bearings. Rotate each bearing, aligning scallops with

locating pins (Ref. Figure 403) .

(4) Position yoke bearings in housings and install half

caps, making sure scallops engage with locating pins.

(5) Push yoke fully home. Install four bolts, countersunk

washers, and barrel nuts. Torque bolts to 335 to 355

lbf in. (37.85 to 40.11 Nm). Safety with lockwire .

Make sure barrel nuts are positioned correctly

(Ref. Figure 403) .

32-10-11

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Dec 15/12 mm360

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(6)

(7) Remove radius rod nut and washer from leg attachment.

Release radius rod, making sure ram is fully extended

and locked. Place clinometer against inboard face of

leg sliding tube and move leg as required to hang two

degrees inboard from vertical. Adjust radius rod ram

end to achieve this angle. Connect ram end to leg and

install washer and nut. Tighten nut and safety with

split pin .

NOTE : Total allowable lateral movement at lower end of

installed main gear leg, with radius rod

correctly set, is 0.25 in. (6.4 mm).

(8) Connect flexible hoses to bracket on leg yoke. Tighten

unions.

(9) Install brake unit complete with shuttle valve (Ref.

Chapter 32-40-71, page block 201 ).

(10)Install anti-skid unit (Ref. Chapter 32-40-51, page

block 201 ).

(11)Release gas pressure and replenish main gear oleo leg

(Ref. Chapter 32-10-11, page block 301 ).

(12)Bleed and test brakes (Ref. Chapter 32-40-00, page

block 201 ).

(13)Make sure work area is clean and clear of tools and

miscellaneous items of equipment.

NOTE : Aircraft will be lowered off jacks when

Adjustment/Test procedure is complete.

(14)Adjust main landing gear (Ref. Chapter 32-10-11, page

block 501 ).

(15)Following Maintenance actions ensure that the Emergency

Selector and Release Valve is re-set (Ref. Chapter

29-20-00 pageblock 201).

32-10-11

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