**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 Dec 15/12
mm360 Printed in the U.K.

### Page left intentionally blank

### 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 Page 3 Dec 15/12
mm360 Printed in the U.K.

### Page left intentionally blankIncorporation 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 32-10-11 401-402 401-402 32-10-11 407-408 407-408



# LETTER OF TRANSMITTAL Page 1 Dec 15/12
mm360 Printed in the U.K.

### Page left intentionally blankCHAPTER 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 2 Dec 15/12 3 Dec 15/12 4 Dec 15/12 5 Dec 15/12 6 Dec 15/12 7 Dec 15/12 8 Dec 15/12 9 Dec 15/12 10 Dec 15/12 11 Dec 15/12 12 Dec 15/12 13 Dec 15/12 14 Dec 15/12 15 Dec 15/12 16 Dec 15/12 17 Dec 15/12 

# 05-LEP Page 1 Dec 15/12
mm360 Printed in the U.K.CHAPTER/SECTION/SUBJECT PAGE DATE
18 Dec 15/12 19 Dec 15/12 20 Dec 15/12 21 Dec 15/12 22 Dec 15/12 23 Dec 15/12 24 Dec 15/12 25 Dec 15/12 26 Dec 15/12 27 Dec 15/12 28 Dec 15/12 29 Dec 15/12 30 Dec 15/12 31 Dec 15/12 32 Dec 15/12 33 Dec 15/12 34 Dec 15/12 35 Dec 15/12 36 Dec 15/12 37 Dec 15/12 38 Dec 15/12 39 Dec 15/12 40 Dec 15/12 41 Dec 15/12 42 Dec 15/12 43 Dec 15/12 44 Dec 15/12 45 Dec 15/12 46 Dec 15/12 47 Dec 15/12 48 Dec 15/12 49 Dec 15/12 

# 05-LEP Page 2 Dec 15/12
mm360 Printed in the U.K.CHAPTER/SECTION/SUBJECT PAGE DATE
50 Dec 15/12 51 Dec 15/12 52 Dec 15/12 53 Dec 15/12 54 Dec 15/12 55 Dec 15/12 56 Dec 15/12 57 Dec 15/12 58 Dec 15/12 59 Dec 15/12 60 Dec 15/12 61 Dec 15/12 62 Dec 15/12 63 Dec 15/12 64 Dec 15/12 65 Dec 15/12 66 Dec 15/12 67 Dec 15/12 68 Dec 15/12 69 Dec 15/12 70 Dec 15/12 71 Dec 15/12 72 Dec 15/12 73 Dec 15/12 74 Dec 15/12 75 Dec 15/12

05-10-06 1 Oct 30/98

05-10-07 1 Oct 30/98

05-20-00 1 Oct 30/98 

# 05-LEP Page 3 Dec 15/12
mm360 Printed in the U.K.CHAPTER/SECTION/SUBJECT PAGE DATE

05-50-00 1 Oct 30/98 2 Oct 30/98

05-50-05 601 Oct 30/98 602 Oct 30/98 603 Oct 30/98 604 Oct 30/98

05-50-10 601 Dec 15/12 602 Dec 15/12 603 Dec 15/12 604 Dec 15/12 605 Dec 15/12 606 Dec 15/12

05-50-15 1 Dec 15/99 2 Dec 15/99 3 Feb 15/01 4 Feb 15/01 5 Feb 15/01 6 Feb 15/01 7 Feb 15/01

05-50-20 1 Oct 30/98

05-50-21 1 Oct 30/98

05-50-25 601 Feb 15/01

05-50-26 1 Oct 30/98



# 05-LEP Page 4 Dec 15/12
mm360 Printed in the U.K.CHAPTER/SECTION/SUBJECT PAGE DATE
05-50-30 1 Oct 30/98

05-50-35 601 Oct 15/05 602 Oct 15/05 603 Oct 15/05

05-50-40 601 Oct 30/98 602 Oct 30/98

05-50-45 601 Oct 15/07 602 Oct 15/07

05-50-50 1 Oct 30/98

05-50-55 601 Dec 15/99
05-50-60 601 Apr 15/05 602 Apr 15/05 603 Apr 15/05 604 Apr 15/05 605 Apr 15/05 606 Apr 15/05 607 Apr 15/05 608 Apr 15/05 609 Apr 15/05 610 Apr 15/05 611 Apr 15/05 612 Apr 15/05 613 Apr 15/05 614 Apr 15/05



# 05-LEP Page 5 Dec 15/12
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### Page left intentionally blankCHAPTER 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 Printed in the U.K.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 Printed in the U.K.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 protectionTable 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 systemApply 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 Printed in the U.K.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 21-30-00, page block 201 ). j0550001.tif



# 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) thru (Ref. Figure 6) 3612b.tif
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 Printed in the U.K.Access Panels - Power Plant Cowlings Figure 6 

# 06-00-13 Page 15 Dec 15/12
mm360 Printed in the U.K.

### Page left intentionally blankCHAPTER 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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22-11-00 501 May 15/04 502 May 15/04 503 Oct 15/04 504 Oct 15/04 505 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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# 22-LEP Page 3 Dec 15/12
mm360 Printed in the U.K.

### Page left intentionally blankSTEP 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
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### Page left intentionally blankCHAPTER 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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# 32-LEP Page 17 Dec 15/12
mm360 Printed in the U.K.

### Page left intentionally blank** 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 O-ring seals. 4993b.tif 4996b.tif 4994b.tif



# 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 Page 407 Dec 15/12
mm360 Printed in the U.K.(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 Page 408 Sep 15/11
mm360 Printed in the U.K.