EASA AD No.: 2013-0208

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0208

Date: 10 September 2013

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, A rticle 14(4) exemption].



### Design Approval Holder’s Name: BAE SYSTEMS (OPERATIONS) LTD Type/Model designation(s):
HP 137 Jetstream MK 1, Jetstream Series 200 and 3100 aeroplanes

TCDS Number: UK BA4 and EASA.A.191

Foreign AD: Not applicable

Supersedure: This AD supersedes UK CAA AD G-003-01- 86.



### ATA 32 Landing Gear – Main Landing Gear – Inspectio n / Replacement

Manufacturer(s): British Aerospace PLC, British Aer ospace (Commercial Aircraft) Ltd, British Aerospace Regional Aircraft Ltd, Jetstream Aircraft Ltd and British Aerospace (Operations) Ltd.

Applicability: HP 137 Jetstream MK 1, Jetstream Ser ies 200 and 3100 aeroplanes all models, all serial numbers.

Reason: Prompted by occurrences of the main landing gear (MLG) yoke pintle housing cracking, the United Kingdom Civil Aviation Authori ty (UK CAA) issued AD G-003-01-86 to require repetitive inspections to id entify any crack in the yoke pintle housing on MLG fitted to Jetstream 3100 aero planes in accordance with BAE Systems (Operations) Ltd Service Bulletin (SB) 32-A-JA851226, and depending on findings, corrective action. After tha t AD was issued, an occurrence of Jetstream 3100 MLG failure was report ed after landing. The subsequent investigation revealed stress corrosion cracking of the MLG yoke pintle housing as a root cause of the MLG failure. Furthermore, the investigation report recommended a review of the ef fectiveness of UK CAA AD G-003-01-86 in identifying cracks in the yoke pintl e housing on MLG fitted to Jetstream 3100 aeroplanes.
Degradation of the surface protection by abrasion c an occur when the forward face of the yoke pintle rotates against the pintle bearing, which introduces corrosion pits and, consequently, stress corrosion cracking.
This condition, if not detected and corrected, coul d lead to structural failure of the MLG, possibly resulting in loss of control of t he aeroplane during take-off or landing runs.EASA AD No.: 2013-0208

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. To provide protection of the affected area of the M LG assembly spigot housing, BAE Systems (Operations) Ltd issued SB 32-JM7862 to provide instructions for installation of a protective washer, fitted at the forward spigot on both, left hand (LH) and right hand (RH), MLG. Consequently, BAE Sy stems (Operations) Ltd issued SB 32-A-JA851226 at Revision 5 to provide ad ditional accomplishment instructions for Non-destructive testing inspection (NDT) of MLG equipped with the protective washer installed in accordance with BAE Systems (Operations) Ltd SB 32-JM7862 and to introduce reference to MLG manufacturer APPH Ltd SB 32-19 at Revision 4, providing instructions for re-protection of the yoke pintle.
For the reasons described above, this AD retains th e requirements of AD G-003-01-86, which is superseded, and requires impl ementation of revised inspection requirements, and depending on findings, corrective action. This AD introduces an optional modification, which constitu tes terminating action for the inspections required by this AD.

Effective Date: 24 September 2013

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:
(1) For aeroplanes that, before the effective date of t his AD, have never been inspected in accordance with the instructions of paragraph 2.B. Part A of BAE Systems (Operations) Ltd SB 32-A-JA85 1226:
Within the compliance time defined in Table 1 of th is AD, as applicable, and, thereafter, at intervals not to exceed 1 200 M LG flight cycles (FC) or 12 months, whichever occurs first, accomplish a NDT inspection of each MLG assembly cylinder attachment spigot housing in accordance with the accomplishment instructions of paragraph 2.B. Part A of BAE Systems (Operations) Ltd SB 32-A-JA851226 at Revision 5.
Table 1 Inspection threshold

Compliance time (whichever occurs first A or B)

A Within 300 MLG FC or 3 month after the effective date of this AD, whichever occurs first

B At the first overhaul of the MLG after the effect ive date of this AD

(2) For aeroplanes that, before the effective date of t his AD, have already been inspected in accordance with the instructions of paragraph 2.B. Part A of BAE Systems (Operations) Ltd SB 32-A-JA85 1226 at any Revision:
Within 1 200 MLG FC or 12 months, whichever occurs first, after the last inspection and thereafter at intervals not to excee d 1 200 MLG FC or 12 months, whichever occurs first, accomplish a NDT in spection of each MLG assembly cylinder attachment spigot housing in acco rdance with the accomplishment instructions of paragraph 2.B. Part A of BAE Systems (Operations) Ltd SB 32-A-JA851226 at Revision 5.
(3) For aeroplanes that have sustained a heavy or abnor mal landing:
Within 300 MLG FC or 3 months, whichever occurs fir st after the event, accomplish a one-time NDT inspection of each MLG as sembly cylinder attachment spigot housing in accordance with the ac complishment instructions of paragraph 2.B. Part A of BAE System s (Operations) Ltd SB 32-A-JA851226 at Revision 5. (4) If, during any inspection as required by paragr aph (1) or (2) or (3) of this AD, any crack is detected, before next flight, acco mplish the applicable corrective actions in accordance with BAE Systems ( Operations) Ltd SBEASA AD No.: 2013-0208

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 32-A-JA851226 Revision 5.
(5) Within 300 MLG FC or 3 months, whichever occurs first, after accomplishment of each NDT inspection as required b y paragraph (1) or (2) of this AD, as applicable, and, thereafter, at intervals not to exceed 300 MLG FC or 3 months, whichever occurs first, acc omplish a visual inspection of each MLG in accordance with the accom plishment instructions of paragraph 2.B. Part B of BAE System s (Operations) Ltd SB 32-A-JA851226 at Revision 5. (6) If, during any visual inspection, as required b y paragraph (5) of this AD, any discrepancy is detected, before next flight, ac complish the applicable corrective actions in accordance with BAE Systems ( Operations) Ltd SB 32-A-JA851226 Revision 5.
(7) Aeroplanes with MLG incorporating a microswitch hol e: Within 10 600 MLG FC since new, and thereafter at i ntervals not to exceed 1 200 MLG FC, accomplish a NDT inspection of each M LG microswitch hole in accordance with paragraph 2.B. Part C of BA E Systems (Operations) Ltd SB 32-A-JA851226 at Revision 5. Ac complishment of an inspection, before the effective date of this AD, i n accordance with APPH Ltd SB 32-40 at Initial issue or Revision 1, consti tutes an acceptable alternative method of compliance for the initial ND T inspection required by this paragraph. (8) If, during any NDT inspection as required by pa ragraph (7) of this AD, any crack is detected, before next flight, accomplish t he applicable corrective actions in accordance with BAE Systems (Operations) Ltd SB 32-A-JA851226 Revision 5.
(9) Accomplishment of corrective actions as require d by paragraph (4) or (6) or (8) of this AD does not constitute terminating a ction for the inspections required by this AD. (10) Modification of each MLG cylinder in accordanc e with BAE Systems (Operations) Ltd SB 32-JA880340 constitutes termina ting action for the inspections required by this AD for that MLG.

Ref. Publications: BAE Systems (Operations) Ltd SB 32-A-JA851226 Revis ion 5, dated 30 April 2013, BAE Systems (Operations) Ltd SB 32-JA880340 Origina l issue, dated 6 January 1989,

APPH Ltd SB 32-40 Initial issue dated 21 June 1989 or Revision 1 dated February 2003.
The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD.
2. This AD was posted on 29 July 2013 as PAD 13-108 for consultation until 26 August 2013. The Comment Response Document can b e found at http://ad.easa.europa.eu

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: BAE Systems (Operations) Ltd, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, The United Kingdom; Telephone +44 1292 675207, Facsimile +44 1 292 675704; E-mail: RApublications@baesystems.com

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