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From the PDF’s text layer: layout, tables and figures are lost. The PDF is the document. © Safran. Filed by the FAA in regulations.gov docket FAA-2020-1113; AD 2021-11-18 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
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SAFRAN LANDING SYSTEMS SAS CAGE: F0189 Inovel Parc Sud - 7, rue Général Valérie André 78140 VELIZY-VILLACOUBLAY – FRANCE Telephone: +33 (0) 1 46 29 81 00 www.safran-landing-systems.com
SERVICE BULLETIN
LANDING GEAR - MAIN LANDING GEAR
INSPECTION O F BARREL / HINGE ARM PIN
1. P LANNING INFORMATION A. Effectivity
(1) Component sa f f e c t e d
(a) Hinge A rm Pin P/N:
C66441 C66441-2 C66441-20 B. Concurrent Requirements Accomplishment of this Service Bulletin requires prior or simultaneous accomplishment of Service Bulletin 470-32-841.
C. Reason
(1) Local out of roundness of the hinge arm pins (P/Ns mentioned in the para Effectivity) have been reported during visual inspection in service.
(2) This Service Bulletin provides an inspection procedure to detect local out of roundness of the hinge arm pins of the Main Landing Gear Barrel (P/Ns mentioned in the para Effectivity).
D. Desc ription
(1) The accomplishment of this Inspection Service Bulletin consists in carrying out an inspection in workshop to detect local out of roundness of the pins.
(2) Safran Landing Systems informs the operators to complete the reporting sheet mentioned in Appendix 3 of this Service Bulletin. The reporting form with the results of the inspection must be sent to the address mentioned in paragraph 3.F.
The technical data in this document (or file) may contain US data and be controlled for export under the Export Administration Regulations (EAR), 15 CFR Parts 730-774, ECCN: 9E991. Violations of these laws may be subject to fines and penalties under the Export Administration Act.
©S AFRAN LANDING SYSTEMS (AND SUBSEQUENT REVISION PAGE DATES) This document and all information contained herein is the sole property of Safran Landing Systems. No intellectual property rights are granted by the deliv ery of this document or the disclosure of its content. This document shall not be reproduced to a third party w ithout the express written consent of Safran Landing Systems.
Modification No. NA Service Bulletin No. 470-32-840 Initial Issue: Dec 03/19 P a g e1o f 9 Revision No. 00 Dec 03/19
SAFRAN LANDING SYSTEMS SAS CAGE: F0189
SERVICE BULLETIN E. Compliance
(1) Classi fication Mandatory.
(2) Accomplishment Timescale:
S e r v i c eB u l l e t i nt ob ea c c o m p l i s h e dw i t h i n3 0d a y sf r o mV S B4 7 0 - 3 2 - 8 4 1e m b o d i m e n t .
Inspection results report sending to Safran Landing Systems to be performed:
Case 1 - Within 15 days from pin inspection if no findings, Case 2 - Within 24 hours in case of finding on the measurements.
Safran Landing Systems will provide load assessment based on inspection results within 5 business days from the receipt of inspection results report.
This Service Bulletin has been classi fied Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued to con firm this classification. It is anticipated that the AD will confi rm the timescales given above but reference should be made to the AD for con firmation of the mandated accomplishment timescale.
F. Approva l The inspection procedures described in this SB are reviewed and technically accepted by Airbus to applyt ot h eA i r b u sfleet affected.
This SB does not contain any change information that revises the equipment de finition covered by Airbus approved modi fications.
G. Manpower Estimated time required for the accomplishment of this Service Bulletin in workshop:
(1) Required manpower: 1
(2) Man- hours: 4 hours
(3) Elapsed time: 4 hours NOTE: It is assumed that the equipment has been placed in a maintenance status. The man-hours estimated do not include time to prepare and administrative functions.
H. Weight and Balance None.
I. El ectrical Load Data Not changed.
Service Bulletin No. 470-32-840 P a g e2o f 9 Dec 03/19
SAFRAN LANDING SYSTEMS SAS CAGE: F0189
SERVICE BULLETIN J. Software Acco mplishment Summary Not applicable.
K. References – Safran Landing System Component Maintenance Manual 32-12-14, Barrel.
– Safran Landing System Component Maintenance Manual 32-14-12, Barrel.
– Safran Landing System Component Maintenance Manual 32-14-15, Barrel.
– Safran Landing System Component Maintenance Manual 32-14-39, Barrel.
– Safran Landing System Component Maintenance Manual 32-14-43, Barrel.
– Safran Landing System Component Maintenance Manual 32-14-47, Barrel.
– Safran Landing System Component Maintenance Manual 32-14-50, Barrel.
– Safran Landing System Component Maintenance Manual 32-14-52, Barrel.
– Safran Landing System Component Maintenance Manual 32-14-54, Barrel.
– Safran Landing System Component Maintenance Manual 32-14-59, Barrel.
– Safran Landing System Component Maintenance Manual 32-14-85, Barrel.
L. Publications Affected Not applicable.
M. Interc hangeability Not applicable.
Service Bulletin No. 470-32-840 P a g e3o f 9 Dec 03/19
SAFRAN LANDING SYSTEMS SAS CAGE: F0189
SERVICE BULLETIN
2. M ATERIAL INFORMATION A. Material - Price and Availability Not applicable.
B. Industry Support Information Not applicable.
C. List of com ponents Not applicable.
D. Subcomponents to be re-identi fied Not applicable.
E. Tooling None.
F. Special Tools None.
Service Bulletin No. 470-32-840 P a g e4o f 9 Dec 03/19
SAFRAN LANDING SYSTEMS SAS CAGE: F0189
SERVICE BULLETIN
3. A CCOMPLISHMENT INSTRUCTIONS A. General
(1) The work described in this VSB deals with the inspection of the removed pin.
B. Preparatio n Not applicable C. Procedure
(1) Perform local out of roundness checks of the hinge arm pin according to Appendix 1 within the timescale defined in paragraph 1.E.(2).
(2) Dependin g on the results from the previous checks, two cases are possible:
(a) CASE 1: No finding 1 The reporting forms in Appendix 1 and Appendix 3 have to be completed and sent to Safran Landing Systems within the timescale defined in paragraph 1.E.(2).
2 The inspected hinge arm pin must be scrapped without further actions.
(b) CASE 2: Finding on measurement 1 Step 1 a The reporting forms in Appendix 1 and Appendix 3 have to be completed and sent to Safran Landing Systems within the timescale defined in paragraph 1.E.(2).
b Safran Landing Systems will provide load assessment based on reported forms within the timescale defined in paragraph 1.E.(2).
– Either the concerned MLG requires no further action and the inspected hinge arm pin must be scrapped.
–Or the concerned MLG may have suffered an overload that requires to be removed and sent to MRO shop for a Hard Landing inspection (refer to paragraph
3.C.(2).(b).2).
2 Step 2 a Safran Landing Systems will provide you with a dedicated inspection plan (including inspections of the hinge arm pins requested in Appendix 1) to be performed on the MLG.
Service Bulletin No. 470-32-840 P a g e5o f 9 Dec 03/19
SAFRAN LANDING SYSTEMS SAS CAGE: F0189
SERVICE BULLETIN b Safran Landing Systems will then provide a de finitive technical statement on the MLG, once complete inspection reports are received.
c The inspected hinge arm pin must then be scrapped.
D. Re-identi fication of equipment
(1) After the wo rk is performed, write the Service Bulletin number 470-32-840 in the applicable landing gear records.
E. Test Not applicable.
F. Close-up
(1) Send the d uly filled reporting form to Safran Landing Systems Product Support Engineering team and to your regional Customer Support Center (CSC).
(a) Safran Landing Systems Product Support Engineering team: pselgi.vel.sls@safrangroup.com
(b) Regional CSC:
Europe, Africa and Middle East : eamecsc.sls@safrangroup.com N o r t h&S o u t hA m e r i c a : americascsc.sls@safrangroup.com Asia : asiacsc.sls@safrangroup.com
(2) All scrapped hinge arm pins further to the VSB 470-32-840 inspection results analysis must be justified to Safran Landing Systems by sending duly filled scrap certificate to relevant regional CSC.
Service Bulletin No. 470-32-840 P a g e6o f 9 Dec 03/19
SAFRAN LANDING SYSTEMS SAS CAGE: F0189
SERVICE BULLETIN SB-470-32-840-01-00
LOCAL OUT OF ROUNDNESS CHECK OF BARREL / HINGE ARM PIN AT SECTION 1,2 & 3 ON CHROMIUM PLATING 0° 22° 45° 67° 90° 112° 135° 157° CRITERIA TO BE MET:
NOTE: SCHEME ABOVE IS NOT A SCALE DRAWING.
DIA MEASUREMENT SECTION 1 (161,00 mm
(6.3386 in)) APPENDIX 1: HINGE ARM PIN MEASUREMENTS 12 3 161,00 mm
(6.3386 in) 191,00 mm
(7.5197 in) 221,00 mm
(8.7008 in)
MAX OUT OF ROUNDNESS MEASURED PER SECTION (MAX DIA - MIN DIA):
DIA MEASUREMENT SECTION 2 (191,00 mm
(7.5197 in))
DIA MEASUREMENT SECTION 3 (221,00 mm
(8.7008 in)) MAXIMUM LOCAL OUT OF ROUNDNESS MEASURED <0,060mm (0.0024 in) Service Bulletin No. 470-32-840 P a g e7o f 9 Dec 03/19
SAFRAN LANDING SYSTEMS SAS CAGE: F0189
SERVICE BULLETIN
REPORTING FORMS IN APPENDIX 1 AND APPENDIX 3
TO BE COMPLETED AND SENT
TO SAFRAN LANDING SYSTEMS
WITHIN TIMESCALE DEFINED IN PARAGRAPH 1.E.(2).
REPORTING FORMS IN APPENDIX 1 AND APPENDIX 3
TO BE COMPLETED AND SENT
TO SAFRAN LANDING SYSTEMS
WITHIN TIMESCALE DEFINED IN PARAGRAPH 1.E.(2).
SB-470-32-840-02-00
HINGE ARM PIN
RECEPTION IN SHOP APPENDIX 2: HINGE ARM PIN INSPECTION FLOWCHART
SAFRAN LANDING SYSTEMS
TO PROVIDE A DEDICATED
INSPECTION PLAN TO BE PERFORMED ON THE MLG.
SAFRAN LANDING SYSTEMS
TO PROVIDE A DEFINITIVE
TECHNICAL STATEMENT
ON THE MLG, ONCE
COMPLETE INSPECTION REPORTS RECEIVED.
HINGE ARM PIN TO BE SCRAPPED.
MLG TO BE REMOVED AND
SENT TO MRO SHOP FOR HARD LANDING INSPECTION.
NO FURTHER ACTION.
HINGE ARM PIN TO BE SCRAPPED.
WHATEVER THE INSPECTION
RESULTS ARE, THE VSB PROFORMA
MUST BE FILLED AND SENT TO SAFRAN LANDING SYSTEMS AT:
pselgi.vel.sls@safrangroup.com CASE 2:
FINDINGS ON
MEASUREMENT
PERFORM LOCAL OUT OF ROUNDNESS CHECK WITHIN TIMESCALE DEFINED IN PARAGRAPH 1.E.(2) CASE 1:
NO FINDINGS
SAFRAN LANDING SYSTEMS
LOAD ASSESSMENT ON REPORTED
FORMS WITHIN TIMESCALE
DEFINED IN PARAGRAPH
1.E.(2) Service Bulletin No. 470-32-840 P a g e8o f 9 Dec 03/19
SAFRAN LANDING SYSTEMS SAS CAGE: F0189
SERVICE BULLETIN APPENDIX 3
REPORTING FORM TO BE COMPLETED IN SHOP
LANDING GEAR - MAIN LANDING GEAR
INSPECTION OF BARREL / HINGE ARM PIN NOTE: Complete the proforma below to identify clearly each hinge arm pin of each MLG:
Operator: MSN:
Aircraft CSN: Aircraft TSN:
Aircraft CSO: Aircraft TSO:
Hinge Arm Pin LH P/N: S/N:
CSN: TSN: CSO: TSO:
H i n g eA r mP i nR H P/N: S/N:
CSN: TSN: CSO: TSO:
MLG Leg LH P/N: S/N:
CSN: TSN: CSO: TSO:
MLG Leg RH P/N: S/N:
CSN: TSN: CSO: TSO:
Date of inspection:
NOTE: All scrapped hinge arm pins further to the VSB 470-32-840 inspection results analysis must be justified to Safran Landing Systems by sending duly filled scrap certi ficate to relevant regional CSC.
Service Bulletin No. 470-32-840 P a g e9o f 9 Dec 03/19