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BAE SYSTEMS (Operations) Limited, Prestwick International Airport, Ayrshire, KA9 2RW, ScotLand.
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
TRANSMITTAL FOR INSPECTION SERVICE BULLETIN REVISION SERVICE BULLETIN No.ISB.53-152 DATE: 08-OCT-1998 TITLE: TO INSPECT FOR CRACKING IN BORE AND ALONG FACE OF THE
RETRACTION JACK ATTACHMENT BOSS IN THE LEFT HAND NOSE LANDING GEAR SIDEWALL.
REVISION: 8 DATE: 19-FEB-2018
ACTIONS
(1) Remove and discard Inspection Service Bulletin (ISB) at revision 7.
(2) Insert ISB at revision 8.
REASONS FOR REVISION
(1) Para 1. (A). (1) amended to 'ALL BAe 146 and AVRO 146-RJ Series aircraft"
(2) Para 1.D amended to refer to revision 8 of ISB.
(3) Para 1.D. (1). (a) amended to change inspection periods to 7375 flights and 625 flights.
(4) Para 1.(D). (1). (b) deleted (not highlighted).
(5) Para 1.D. (2) amended to include reference to para.2.G - Closing Action.
(6) Para 1.D. (2). (a) amended for aircraft that have inspected their sidewalls in accordance with (the now deleted) para.2.A (Pin In).
(7) Para 1.D. (2). (b) amended for those aircraft that have inspected their sidewalls in accordance with para.2.B.
(8) Para 2.G title amended to add reference to Drawing 3 and Table 1.
(9) Para 2.G Table 1 amended to add "(FLIGHTS)" to fourth and fifth column headings.
(10) Drawing 3 revised.
(11) Editorial (not highlighted).
INCORPORATION OF THIS REVISION DOES NOT REQUIRE REWORK OF THE
INSPECTION CONDUCTED IN ACCORDANCE WITH EARLIER REVISIONS OF THIS INSPECTION SERVICE BULLETIN.
Date: 08-0CT-1998 REVISION TRANSMITTAL SHEET ISB.53-152 Revision: 8 19-FEB-2018 Page 1 of 2 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
TRANSMITTAL FOR INSPECTION SERVICE BULLETIN REVISION SERVICE BULLETIN No.ISB.53-152 This Page Is Intentionally Left Blank.
Date: 08-0CT-1998 REVISION TRANSMITTAL SHEET ISB.53-152 Revision: 8 19-FEB-2018 Page 2 of 2 Printed in England
BAE SYSTEMS (Operations) Limited, Prestwick International Airport, Ayrshire, KA9 2RW, ScotLand.
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT TITLE: TO INSPECT FOR CRACKING IN BORE AND ALONG FACE OF THE
RETRACTION JACK ATTACHMENT BOSS IN THE LEFT HAND NOSE LANDING GEAR SIDEWALL.
1.PLANNING INFORMATION A.Effectivity
(1) Aircraft Aircraft affected are:- AlL BAe 146 and AVRO 146-RJ Series aircraft.
This Inspection Service Bulletin (ISB) is only applicable to aircraft Pre modification HCM20011A or HCM20012A or HCM20013A or HCM20313A or HCM20314A or HCM20315A.
(2) Spares Inspect any spare sidewalls.
B. Reason Evidence of cracking has been found on several in service aircraft in the bore and along the face of the retraction jack attachment boss on the left hand nose landing gear (NLG) sidewall which in some circumstances has led to replacement of the sidewall.
C .Description
(1) It is necessary to perform the following Inspection:
(a) Non Destructive tests (NDT) with NLG retraction jack attachment pin removed to locate cracks (Ref. Drawing 2):
NOTE: In accordance with the guidelines laid out in FAA AC 120-93, Sections 207 and 208b, BAE SYSTEMS have reviewed the repair data defined in this Inspection Service Bulletin. A Damage Tolerance Evaluation has been performed which demonstrates compliance with the FAA Final Rule 14 CFR 26.41 - 26.49 'Damage Tolerance Data for Repairs and Alterations'.
No additional Damage Tolerance Inspections are required for the repair data defined within this Inspection Service Bulletin.
Date: 08-0CT-1998 ISB.53-152 Revision: 8 19-FEB-2018 Page 1 of 20 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT D. Compliance This ISB at revision 8 is the subject of EASA Airworthiness Directive consultation; this may result in the revision of EASA AD No. 2007-0305.
(1) The initial inspection is to be in accordance with para.2.B (Attachment Boss Not Bushed) or para.2.C (Attachment Boss Bushed), the inspection periods are:-
(a) For aircraft which have completed more than 7375 flights, inspect within 625 flights from receipt of this bulletin.
Aircraft inspected to earlier revisions of this bulletin, have satisfied the requirements of the inspection in para.1.D.(1).
(2) The following subsequent inspections are required where the attachment boss is not bushed until a terminating action/repair (see para.2.G) is embodied. The inspection should be in accordance with para.2.B.
(a) Those aircraft that have inspected their sidewalls in accordance with (the now deleted) para.2.A (Pin In).
Inspect to para.2.B within 2600 flights. Thereafter, repeat the inspection specitied in para.z.B every 6/00 flights until a termination action/repair (see para.2.G) is embodied. Aircraft which were allowed to continue to operate with one crack, in accordance with the requirements of para.1.D. (2). (a) of this ISB, at Revision 7, or earlier, must accomplish a terminating action/repair (see para.2.G) within 2600 flights of the last inspection.
OR
(b) Those aircraft that have inspected their sidewalls in accordance with para.2.B. Repeat the inspection specified in para.2.B every 6700 flights until a terminating action/repair (see para.2.G) is embodied. Aircraft which were allowed to continue to operate with one crack, in accordance with the requirements of para.1.D. (2).(b) of this ISB, at Revision 7, or earlier, must accomplish a terminating action/repair (see para.2.G) within 260C flights of the last inspection.
(3) The following subsequent inspections are required where the attachment boss has been bushed in accordance with RIL HC537R9410 Repair No's 1, 2, 3 or 4, or Modification Service Bulletin 53-152-016726, until a terminating action/repair is embodied. The inspection should be in accordance with Date: 08-0CT-1998 ISB.53-152 Revision: 8 19-FEB-2018 Page 2 of 20 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT para.2.C; it should be noted that the inspection period may vary depending on any findings.
(4) Table 1 and the associated flow chart (Ref. Drawing 3), illustrate the repair options and associated threshold and repeat inspection intervals.
E. Approval The technical content of this document is approved under the authority of DOA Ref.EASA.21J.047.
F. Manpower To inspect as defined in para.2.B - 2 man-hours.
This man-hour estimate does not include time for gaining access to and cleaning the inspection area.
G.Materials-Cost/ Availability Not applicable.
H.Tooling-Cost/ Availability By arrangement between BAE SYSTEMS and the operator.
I.weight and Balance Not applicable.
J. References
(1) Aircraft Maintenance Manual, AMM Chapter 32-20-14, page block
201. AMM Chapter 32-32-11, page block 201.
(2) Illustrated Parts Catalogue, IPC 32-21-01-05.
(3) Non Destructive Testing Manual (NTM), PART 6 - Eddy Current, NDT 53-10-15.
(4) Structural Repair Manual, SRM 51-20-11.
K.Publications Affected Aircraft Maintenance Manual.
L.Electrical Load Data Not applicable.
Date: 08-0CT-1998 ISB.53-152 Revision: 8 19-FEB-2018 Page 3 of 20 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT This Page Is Intentionally Left Blank.
Date: 08-0CT-1998 ISB.53-152 Revision: 8 19-FEB-2018 Page 4 of 20 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
2.ACCOMPLISHMENT INSTRUCTIONS NOTE: Before dismantling any items note wire locking and split pin installation details.
Refer to Drawing 1 and Drawing 2.
A.Non Destructive Inspection With Attachment Pin Fitted (Pin In)
(1) Pin in inspection option now removed from service bulletin.
B.Non Destructive Inspection With Attachment Pin Removed (Attachment Boss Not Bushed)
(1) Preparation:
(a) Observe appropriate safety precautions in AMM.
(b) Disconnect nose gear undercarriage doors (Ref. AMM 32-20-14, page block 201). Gain access to NLG undercarriage bay -
(c) Refer to AMM 32-32-11, page block 201 and remove NLG retraction jack from aircraft.
(d) Gain access to both sides of sidewall and remove NLG retraction jack attachment pin from sidewall.
(e) Clean area to be inspected (boss face, bore of hole, etc.)
including any extruded sealant.
(2) Equipment and Materials:
(a) Refer to NTM Part 6, 53-10-15 Para 4, Part A for details of equipment and materials required to carry out this inspection.
(3) Inspection (Ref. Drawing 2):
(a) Refer to NTM Part 6, 53-10-15, Part A for details of the eddy current inspection required of the jack attachment boss- C_ Non Destructive Inspection With Attachment Pin Removed (Attachment Boss Bushed)
(1) Preparation:
(a) Observe appropriate safety precautions in AMM.
(b) Disconnect nose gear undercarriage doors (Ref. AMM Date: 08-0CT-1998 ISB.53-152 Revision: 8 19-FEB-2018 Page 5 of 20 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT 32-20-14, page block 201). Gain access to NLG undercarriage bay -
(c) Refer to AMM 32-32-11, page block 201 and remove NLG retraction jack from aircraft.
(d) Gain access to both sides of sidewall and remove NLG retraction jack attachment pin from sidewall.
(e) Clean area to be inspected (bore face, etc.) including any extruded sealant.
(2) Equipment and Materials:
(a) Refer to NTM Part 6, 53-10-15 Para 4, Part B for details of equipment and materials required to carry out this inspection.
(3) Inspection (Ref. Drawing 2):
(a) Refer to NTM Part 6, 53-10-15, Part B for details of the eddy current inspection required of the jack attachment boss (inspection is at the edge of the bush).
D.Rectification
(1) After performing inspection para.2.B. (Attachment Boss Not Bushed) .
(a) It more than one crack is evident in the sidewall, or it one crack exceeds 0.67 in. (17.0 mm.) from bore, then repair or replace sidewall before next flight. Refer to Table 1 for repair options.
(b) If no cracks are evident in the sidewall, or if only one crack is evident and it does not exceed 0.67 in. (17.0 mm.)
from bore 0.10 in. (2.54 mm.) from pin head, then repair options and closing actions are to be considered. Continued operation is allowed if subsequent inspections are conducted in accordance with para.1.D. Refer to Table 1 for repair options.
(2) After performing inspection para.2.C. (Attachment Boss Bushed).
(a) If one or more crack is evident in the sidewall irrespective of length of crack then replace sidewall before next flight. Refer to Table 1 for repair options.
(3) Treat all bare and re-worked material to SRM 51-20-11.
Date: 08-0CT-1998 ISB.53-152 Revision: 8 19-FEB-2018 Page 6 of 20 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
(4) Re-installing pin and NLG retraction jack.
(a) Refer to Drawing 1 - Section C-C.
(Refer to IPC 32-21-01-05 for ref only).
plate bolt. Torque tighten pin hut to pin nut, locking plate and 67 Lbf. ft. (9.08 mdaN) (mod. HCM01641A).
Re-wirelock plate bolt to pin nut as noted (Ref. Drawing
1).
(b) Refer to AMM 32-32-11, page block 201.
Re-install NLG retraction jack.
Torque tighten pin bolt to 8 lbf.ft. (1.08 mdaN) (mod.
HCM01641A) .
(c) For other wire locking, split pin and all other installation details refer to AMM 32-32-11, page block 201.
E.Close up
(1) Re-connect nose gear undercarriage doors (Ref. AMM 32-20-14, page block 201).
(2) Close undercarriage doors.
F. Reporting
(1) Record the accomplishment of this inspection in the aircraft's technical records.
(2) When para.2.D. (4) has been completed record the embodiment of Mod HCM01641A (torque tightening) in the aircraft's technical records.
(3) Report all findings of this Service Bulletin, and the embodiment of all modifications using attached Inspection Report Sheet.
G.Closing Action (see Table 1 and Drawing 3) The closing action consists of either:-
(1)
(a) Embody Service Bulletin SB. 53-152-01672C.
Date: 08-0CT-1998 ISB.53-152 Revision: 8 19-FEB-2018 Page 7 of 20 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
(b) Refer to Table 1 Option B for subsequent inspection requirements.
OR
(2)
(a) Replace sidewall with post Mod HCM01672D (Part Number HC537L0002-006).
(b) Refer to Table 1 Option F for subsequent inspection requirements.
OR
(3)
(a) Repair per RIL HC537H9410 Repair no. 3.
(b) Refer to Table 1 Option C for subsequent inspection requirements.
NOTE: Installation of post mod HCM01672D sidewall panel will also enable operators to claim the terminating action for SB. 53-229. Embodiment or RIL HC537H9410 Repair No's 1, 2, 3 or 4 does not remove the requirement to perform stiffener inspections, hence there is a continuing risk of stiffener damage and possible sidewall replacement at a future date.
NOTE: Table 1 summarises the actions to be taken following inspection.
Table 1.
OPTION EVIDENCE OF ACTION REVISED INSPECTION REVISED
SIDEWALL THRESHOLD FROM INSPECTION
CRACKING - PIN REPAIR (FLIGHTS) INTERVAL
OUT (NDT) (FLIGHTS) A NO Embody RIL 20,000 4,000 HC537H9410 Repair No. 1.
Date: 08-0CT-1998 ISB.53-152 Revision: 8 19-FEB-2018 Page 8 of 20 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
OPTION EVIDENCE OF ACTION REVISED INSPECTION REVISED
SIDEWALL THRESHOLD FROM INSPECTION
CRACKING - PIN REPAIR (FLIGHTS) INTERVAL
OUT (NDT) (FLIGHTS) NO Embody Inspection is not Inspection is not SB. 53-152-01672C. due before the due before the Airframe Life Limit Airframe Life as defined in AMM Limit as defined 05-10-01. in AMM 05-10-01.
Thereafter, refer Thereafter, refer to SSID. to SSID.
YES - IN BORE Embody RIL Inspection is not Inspection is not Max HC537H9410 Repair due before the due before the permissible No. 3. Airframe Life Limit Airframe Life crack as defined in AMM Limit as defined size = 0.15 05-10-01. in AMM 05-10-01.
in. on bore Thereafter, refer Thereafter, refer to SSID. to SSID.
D YES - ALONG Embody RIL 20,000 4,000 SURFACE HC537H9410 Repair Max No. 2.
permissible crack size = 0.67 in. length size = 0.39 in. depth
YES - IN BORE Max permissible crack size = 0.15 in. on bore YES - IN BORE Embody RIL 20,000 4,000 Max HC537H9410 Repair permissible No. 4.
crack size = 0.15 in. on bore Date: 08-0CT-1998 ISB.53-152 Revision: 8 19-FEB-2018 Page 9 of 20 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
OPTION EVIDENCE OF ACTION REVISED INSPECTION REVISED
SIDEWALL THRESHOLD FROM INSPECTION
CRACKING - PIN REPAIR (FLIGHTS) INTERVAL
OUT (NDT) (FLIGHTS) YES - ALONG Replace with part Inspection is not Inspection is not SURFACE number due before the due before the Exceeds Max HC537L0002-006. Mod Airframe Life Limit Airframe Life permissible HCMO1672D. as defined in AMM Limit as defined crack size = 05-10-01. in AMM 05-10-01.
0.67 in. Thereafter, refer Thereafter, refer length size = to SSID. to SSID.
0.15 in. depth OR
YES - ALONG SURFACE Crack irrespective of length if Replace with part 20,000 4,000 boss is bushed number OR HC537L0002-000 or YES - IN BORE 002 or 004.
Exceeds Max permissible crack size =
0.15 in.
Date: 08-0CT-1998 ISB.53-152 Revision: 8 19-FEB-2018 Page 10 of 20 Printed in England