# BAE Systems Inspection Service Bulletin ISB.53-152: Revision 8

- Rights: © BAE Systems. Filed by the FAA in regulations.gov docket FAA-2022-1313; AD 2023-02-10 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [BAE Systems Inspection Service Bulletin ISB.53-152](https://openairdocs.org/service-documents/bae-systems/isb53-152.md)
- Title as filed: ISB 53-152 Rev 8
- Pages: 22
- PDF: https://openairdocs.org/files/sha256/33/b4/33b4e31c89e6e23ac7640fa11a19680201f7fc52eb025434f8e7c1224e3f0262
- Page: https://openairdocs.org/service-documents/bae-systems/isb53-152/file/33b4e31c89e6

## Text

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### Page 1 (OCR)

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

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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

### Page 3 (OCR)

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
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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
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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
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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
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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
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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
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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
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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
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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
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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
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BAE SYSTEMS
INSPECTION SERVICE BULLETIN
BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
AREA TO BE INSPECTED
ON BOSS FACE
SHOWN HATCHED
CL
AREA TO
BE INSPECTED
BOSS FACE
PLATE  PIN  (AREA TO BE INSPECTED)
BOLT  LARGE
WASHER
NLG
JACK
LOCKING
WIRE
PIN
BOLT
PIN NUT
WASHER
BOSS FACE
LOCKING PLATE
(AREA TO BE INSPECTED)
SECTION 'C-C'
WITH ATTACHMENT
PIN INSTALLED
N5315201
DRAWING 1.
Date: 08-0CT-1998  ISB.53-152
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BAE SYSTEMS
INSPECTION SERVICE BULLETIN
BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
BORE
(AREA TO BE INSPECTED -
ATTACHMENT BOSS NOT BUSHED)
BOSS FACE
(AREA TO BE INSPECTED -
ATTACHMENT BOSS BUSHED
OR NOT BUSHED)
N5315202
AREA TO BE INSPECTED
DRAWING 2.
Date: 08-0CT-1998  ISB.53-152
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BAE SYSTEMS
INSPECTION SERVICE BULLETIN
BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
Initial inspection  Are cracks found
8,000 flights  WITH PIN REMOVED  YES
Inspect at 6,700
flights  NO
Do you want to
NO  improve Inspection
Threshold?
Can damage be bored
Do you want to embody  YES  out by 0.4in on DIA to
terminating action?  1.65in. DIA.
Can damage be cleared out
YES  NO  NO  by counterbore
2.69in X 0.44in deep?
Replace sidewall
Replace sidewall  HC537L0002-000
Mod HCM01672D  or 002 or 004
OPTION F  OPTION F
Embody RIL  Embody RIL
HC537H9410  HC537H9410
Repair No. 1  Refer to Table 1  Repair No. 2  YES
OPTION F
OPTION A  OPTION D
Do you want to embody
terminating action?
NO  YES
Embody RIL
Inspect at 20,000 flight threshold  HC537H9410
Repeat at 4,000 flight intervals  Repair No. 4
OPTION E
Embody Mod Bulletin
SB. 53-152-01672C  Refer to Table 1  Embody RIL
OPTION B  Refer to Table 1  HC537H9410
OPTION B  OPTION C  Repair No. 3
or MOD HCM01672D  OPTION F  OPTION F  OPTION C
N5315210
(REFER TO PARA 2.G)
DRAWING 3. (Revised)
Date: 08-0CT-1998  ISB.53-152
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BAE SYSTEMS
INSPECTION SERVICE BULLETIN
BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
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BAE SYSTEMS
INSPECTION SERVICE BULLETIN
BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
3.MATERIAL INFORMATION
Not applicable.
Date: 08-0CT-1998  ISB.53-152
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BAE SYSTEMS
INSPECTION SERVICE BULLETIN
BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
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BAE SYSTEMS
INSPECTION SERVICE BULLETIN
BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
APPENDIX 1
1.CONTINUED AIRWORTHINESS
A.Continued Airworthiness Instructions
(1) There are no continued airworthiness instructions applicable
to this Inspection Service Bulletin.
B.Scheduled maintenance
(1) None.
C.Removal Procedures
(1)  None.
D. Installation Procedures
(1)  None.
E.Test Procedures
(1)  None.
F.Troubleshooting
(1)  None .
Date: 08-0CT-1998  ISB.53-152
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INSPECTION SERVICE BULLETIN
BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
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BAE SYSTEMS
INSPECTION SERVICE BULLETIN
BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
SERVICE BULLETIN NO. ISB.53-152
TITLE: TO INSPECT FOR CRACKING IN BORE AND ALONG FACE OF THE
RETRACTION JACK ATTACHMENT BOSS IN THE LEFT HAND NOSE LANDING
GEAR SIDEWALL.
A SEPARATE COPY OF THIS ADVICE NOTE IS TO BE COMPLETED FOR EACH
AIRCRAFT THAT HAS THIS SERVICE BULLETIN EMBODIED.
The embodiment of this Service Bulletin embodies and/or removes the
following modifications
Modification  Accomplishment
MOD HCM01641A  EMBODIED
FROM (Airline):
NAME OF REPRESENTATIVE:
AIRCRAFT CONSTRUCTOR'S NUMBER:
DATE ACCOMPLISHED:
REMARKS:
Date: 08-0CT-1998  ISB.53-152
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BAE SYSTEMS
INSPECTION SERVICE BULLETIN
BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
Return this Advice Note to:-
Business Support Team,
Technical Publications,
BAE SYSTEMS (Operations) Limited,
Prestwick International Airport,
Ayrshire,
KA9 2RW,
Scotland.
Fax: +44(0) 1292 675704
E-Mail: RAPublicationsabaesystems.com
SB COMMENTS/ FEEDBACK
Please report any non technical comments or inaccuracies regarding
this SB to the above address.
Date:  08-0CT-1998  ISB.53-152
Revision: 8 19-FEB-2018  Page 20 of 20
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