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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
IRANSMITTAL FOR INSPECTION SERVICE BULLETIN REVISION SERVICE BULLETIN No.ISB.57-072 DATE: 22-FEB-2008 TITLE: WING - INSPECTION OF WING FIXED LEADING EDGE AND FRONT SPAR STRUCTURE, LEFT AND RIGHT WING.
REVISION: 3 DATE: 31-AUG-2010 ACTION:
FOR THOSE OPERATORS THAT HAVE PREVIOUSLY RECEIVED THIS BULLETIN:
(1) Remove and destroy service bulletin complete Revision No. 2.
(2) Insert service bulletin complete at Revision No. 3.
OVERVIEW OF CHANGE:
Deletion of cautionary note.
INCORPORATION OF THIS REVISION DOES NOT REQUIRE REWORK OF THE
MODIFICATION(S) EMBODIED BY EARLIER REVISIONS OF THIS INSPECTION SERVICE BULLETIN.
DETAILS OF CHANGE:
Pare 2.C. (2). Cautionary note deleted regarding the need tor dummy weights (if engines have been removed) to be used when the fixed leading edges are being removed from the wing.
Date: 22-FEB-2008 REVISION TRANSMITTAL SHEET ISB.57-072 Revision: 3 31-AUG-2010 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.57-072 This Page Is Intentionally Left Blank.
Date: 22-FEB-2008 REVISION TRANSMITTAL SHEET ISB.57-072 Revision: 3 31-AUG-2010 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: WING - INSPECTION OF WING FIXED LEADING EDGE AND FRONT SPAR STRUCTURE, LEFT AND RIGHT WING.
1. Planning information A.Effectivity
(1) Aircraft Aircraft affected by this inspection are defined below :- ALL BAe 146-100, 200, 300 Series.
ALL BAe 146-301 Series.
ALL AVRO 146-RJ70, RJ85, RJ100 Series.
B.Reason During the removal of the wing removable leading edge for an unrelated repair, corrosion was found on the wing fixed leading edge structure. Investigation has established that existing scheduled structural inspections would not have detected the corrosion or fatigue damage. Corrosion or fatigue damage could result in a degradation of the structural integrity of the wing.
C. Description
(1) Inspection for corrosion is done on the left and right wing removable leading edge, the wing fixed leading edge structure and attachments and the front spar front face.
(2) There were previously two alternative inspection procedures, Method 1 was a combination of a detailed visual inspection i sual inspect ton 299.
(DVI) and a visual inspection (VI). Method 2 is a DVI.
(a) Method 1 has been deleted. Operators who accomplished Method 1 at last inspection must carry out Method 2 at next inspection as defined by Table 1 and para 1.D.
(b) Method 2. Stress jack and trestle the aircraft, then remove the inboard, centre and outboard removable wing leading edges and do a DVI.
(3) The existing fatigue and environmental inspections in the Maintenance Review Board Report and Maintenance Planning Document, Corrosion Prevention and Control Programme and Supplemental Structural Inspection Document will be superseded by this inspection service bulletin when the service bulletin is subject to EASA AD action as follows:
Date: 22-FEB-2008 ISB. 57-072 Revision: 3 31-AUG-2010 Page 1 of 22 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
(a) This inspection service bulletin supersedes the Maintenance Review Board Report SSI tasks 57-20-101 and 57-20-102, 57-40-105 (MPD tasks 572001-DVI-10000-1, S/<001-DVI-10000-2, 572002-DVI-10000-1 and 0(4005-DVI-10000-1).
(b) This inspection service bulletin supersedes the Corrosion Prevention and Control Programme task C57-520-03-00.
(c) This inspection service bulletin supersedes the Supplemental Structural Inspection Document (SSID), reference SSID S57-40-105.
(4) There are optional corrosion protection tasks in the inspection service bulletin as follows:
(a) Part A provides enhanced corrosion protection on the wing fixed leading edge and front spar structure and attachments by the application of a coating of material number 16-655 on all inspectable structure referred to in para.2.C Method
(b) Part B provides corrosion protection on the wing fixed and front spar structure and attachments by the application of a coating of material number 15-522 or 15-520 on all inspectable structure referred to in para.2.C Method 2.
This inspection service bulletin is in 3 sections, Method 2, Part A and Part B and affects the left and right wing as follows:
Work for Method 2 comprises:- Jack and trestle the aircraft.
- Remove the inboard, centre and outboard removable wing Leading edges, and do a DVI of the leading edge structure at the following locations: - Removable wing leading edge rear diaphragm and attachment Front spar front face.
- Wing fixed leading edge upper and lower skins.
- Wing fixed leading edge stiffeners and diaphragms.
- Wing fixed leading edge upper and lower spanwise members/stiffeners and attachments.
- Install the inboard, centre and outboard removable wing Leading edges.
Remove jacks and trestle.
- Do a function check.
Date: 22-FEB-2008 ISB.57-072 Revision: 3 31-AUG-2010 Page 2 of 22 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
- Complete and return Inspection Report Form.
Work for Part A comprises:-
- Apply enhanced corrosion protection.
NOTE: Part A is optional and can only be accomplished after a DVI of the structure is done.
Work for Part B comprises:-
- Apply corrosion protection.
NOTE: Part B is optional and can only be accomplished after a DVI of the structure is done.
D. Compliance The technical content of this inspection service bulletin is the subject of EASA AIRWORTHINESS DIRECTIVE consultation.
Compliance with this inspection service bulletin is to be achieved as follows:
The initial fatigue and environmental inspection must be accomplished as shown below:
(a) For aircraft less than 9 years since entry into service at receipt of this inspection service bulletin, inspect the wing fixed leading edge and front spar structure in accordance with para.2.C Method 2 within 2 years from the initial issue of this inspection service bulletin or before the aircraft age reaches 9 years whichever is the latest.
OR
(b) For aircraft 9 years to 15 years since entry into service at receipt of this inspection service bulletin, inspect the wing fixed leading edge and front spar structure in accordance with para.2.C Method 2 within 2 years from the initial issue of this inspection service bulletin, or prior to achieving 16 years from entry into service, which ever NOTE: Operators of fleets containing 2 or more aircraft between 14 years and 15 years since entry into service can inspect those aircraft within 2 years of the initial issue date of this inspection service bulletin providing the following criteria are met (all fractional aircraft quantities to be rounded Date: 22-FEB-2008 ISB.57-072 Revision: 3 31-AUG-2010 Page 3 of 22 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT At least 50 percent of the operator's fleet between 14 years and 15 years since entry into service must be inspected within 1 year of the initial issue date of this inspection service bulletin.
No corrosion findings on any of the inspected aircraft in the operator's fleet.
If at any time the two criteria above become unachievable the initial inspection compliance under this Note reverts to 16 years from entry into service.
OR
(c) For aircraft over 15 years since entry into service at receipt of this inspection service bulletin, inspect the wing fixed leading edge and front spar structure in accordance with para.2.C Method 2 within 1 year from the initial issue of this inspection service bulletin.
NOTE: Operators of fleets containing 4 or more aircraft that have exceeded 15 years since entry into service can inspect those aircraft within 2 years of the initial issue date of this inspection service bulletin providing the following criteria are met (all fractional aircraft quantities to be rounded up) : - 1 At least 50 percent of the operator's fleet over 15 years since entry into service including at least 50 percent of the oldest quartile must be inspected within 1 year of the initial issue date of this inspection service bulletin.
(Oldest quartile describes the oldest 25 percent of the operator's fleet over 15 years since entry into service).
No corrosion findings on any of the inspected aircraft in the operator's fleet.
If at any time the two criteria above become unachievable the initial inspection compliance under this Note reverts to 1 year from the initial issue date of this inspection service bulletin.
Operators who accomplished Method 1 at last inspection do not require retrospective inspection action.
repeat fatigue and environmental inspections must be accomplished in accordance with para.2.C Method 2 at the intervals specified in Table 1 Where previously applied, Date: 22-FEB-2008 ISB.57-072 Revision: 3 31-AUG-2010 Page 4 of 22 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT check the enhanced corrosion protection for flaking, cracking and blistering. Re-apply the protection as required accordance with para.2.D Part A.
Table 1.
Area of Inspection Inspection Method Repeat Fatigue and Environmental inspection.
Part A Enhanced Corrosion Protection has been done?
YES NO Inboard Method 1 VI Not Applicable 6 years or 36000 Flights (whichever is sooner) * Inboard Method 2 DVI 12 years or 36000 6 years or 36000 Flights (whichever Flights is sooner) (whichever is sooner) Centre Method 1 VI Not Applicable 6 years or 36000 Flights (whichever is sooner) * Centre Method 2 DVI 12 years or 36000 6 years or 36000 Flights (whichever Flights is sooner) (whichever is sooner) Outboard Method 1 DVI 12 years or 36000 6 years or 36000 Flights (whichever Flights is sooner) # (whichever is sooner) * Outboard Method 2 DVI 12 years or 36000 6 years or 36000 Flights (whichever Flights is sooner) (whichever is sooner) NOTE: * Method 2 (DVI) to be accomplished within 6 years or 36000 Flights (whichever is sooner) of accomplishment of Method 1.
NOTE: # Method 2 (DVI) to be accomplished within 12 years or 36000 Flights (whichever is sooner) of accomplishment of Method 1 Date: 22-FEB-2008 ISB. 57-072 Revision: 3 31-AUG-2010 Page 5 of 22 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT E. ApprovaL The technical information contained in this document has been approved under the authority of EASA Part 21 Approval No.
EASA.21J.047.
F. Manpower To inspect as defined in para. 2 - 12 man-hours.
This man-hour estimate does not include time for gaining access to, or cleaning the inspection area or application of optional enhanced corrosion protection, or corrosion protection or the functional tests of the wing leading edge systems.
G.Materials - cost and availability None.
H.Tooling - cost and availability None.
I.Weight and balance No effect.
J. References Aircraft Maintenance Manual AMM Chapters 07-00-00, 12-00-00, 20-00-00 and 57-41-00.
Structural Repair Manual SRM Chapter 51-00-00 .
K.Publications affected Maintenance Review Board Report (MRBR).
Maintenance Planning Document (MPD).
Corrosion Prevention and Control Programme (CPCP).
Supplemental Structural Inspection Document (SSID).
NOTE: The MRBR, MPD, CPCP and SSID will be reviewed for inclusion of scheduled tasks. When the inspection requirements and procedures of this inspection service bulletin are published in the MRBR, MPD, CPCP and SSID this inspection service bulletin will be cancelled or revised to refer to the MRBR, MPD, CPCP and SSID as the EASA agreed published sources.
Date: 22-FEB-2008 ISB.57-072 Revision: 3 31-AUG-2010 Page 6 of 22 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT L.Electrical load data Not applicable.
M.Software accomplishment summary No effect.
N.Aircraft Noise Levels No effect.
Date: 22-FEB-2008 ISB.57-072 Revision: 3 31-AUG-2010 Page 7 of 22 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT This Page Is Intentionally Left Blank.
Date: 22-FEB-2008 ISB.57-072 Revision: 3 31-AUG-2010 Page 8 of 22 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT
2.Accomplishment instructions A. General
(1) The following abbreviations are used within this document :- AMM - Aircraft Maintenance Manual.
SRM - Structural Repair Manual.
VI - Visual Inspection.
DVI - Detailed Visual Inspection.
(2) Observe all WARNINGS and CAUTIONS appearing in the Aircraft Maintenance Manual (AMM) referred to in this inspection service bulletin.
(3) Care is to be taken to make certain all swarf is collected and removed from aircraft.
B. Preparation
(1) Refer to AMM 12-00-00. Remove all aircraft electrical power.
(2) Display a warning notice in the flight compartment 'DO NOT
APPLY ELECTRICAL POWER TO AIRCRAFT' C.Inspection Method 2 - The following instructions are applicable to the left wing (right wing similar) and are as follows:
(1) Refer to AMM Chapter 07-00-00. Jack and trestle the aircraft.
(2) Refer to AMM Chapter 57-41-00. Remove the inboard, centre and outboard wing leading edges.
(3) Refer to Drawing 1, Drawing 2 and Drawing 3.
(4) Do a DVI of the inboard, centre and outer removable wing leading edges rear diaphragm and attachment angles.
(5) Do a DVI of the inboard, centre and outer front spar front face.
(6) Do a DVI of the inboard, centre and outer wing fixed leading edge upper and lower skins.
(7) Do a DVI of the inboard and centre wing fixed leading edge Date: 22-FEB-2008 ISB.57-072 Revision: 3 31-AUG-2010 Page 9 of 22 Printed in England
BAE SYSTEMS
INSPECTION SERVICE BULLETIN BAe 146 SERIES/AVRO 146-RJ SERIES AIRCRAFT stiffeners and diaphragms.
(8) Do a DVI of the inboard and centre wing fixed leading edge upper and lower spanwise members and attachments.
(9) Do a DVI of the outboard wing fixed leading edge stiffeners.
(10) Do a DVI of the outboard wing fixed leading edge upper spanwise stiffeners and attachments.
(11) Refer to Drawing 4. Complete an Inspection Report Form for each of the inspections done at para.2.C.(4) through para.2.C. (10) and return by fax, mail or e-mail to BAE Systems attached to the Inspection Report (Appendix 1).
NOTE: It is NOT necessary to duplicate the defect information from the DVI Inspection MMM, Report Form into the Findings section of the Inspection Report (Appendix 1).
(12) Rectify any defects found before further flight to an approved BAE SYSTEMS repair scheme. Spanwise members/stiffeners may be repaired in accordance with RIL HC572H9527, issue 1 or later.
(13) Refer to SRM Chapter 51-00-00. Reprotect the structure as required.
(14) Apply the enhanced protection (if required) in accordance with para.2.D Part A or corrosion protection (if required) in accordance with para.2.E Part B.
NOTE: Embodiment of the enhanced corrosion protection in para. 2.D Part A increases the repeat inspection period for the environmental inspection referred to in para.1.D. (2).
Embodiment of the corrosion protection in para.2.E Part It in at Bart B does not affect the environmental repeat inspection
(15) Make certain work area is clean, and clear of tools and miscellaneous equipment.
(16) Refer to AMM Chapter 57-41-00. Install the inner, centre and outer wing leading edges left and right.
Date: 22-FEB-2008 ISB.57-072 Revision: 3 31-AUG-2010 Page 10 of 22 Printed in England