EASA AD No.: 2014-0239

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/4 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0239

Date: 03 November 2014

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):

Jetstream Series 3100 and 3200

TCDS Number: EASA.A.191

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2013-0206 d ated 09 September 2013.



### ATA 32 Landing Gear – Main Landing Gear – Modification / I nspection / Repair / 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: Jetstream Series 3100 and 3200 aerop lanes, all models, all serial numbers.

Reason: Several cases of stress corrosion cracking of DTD 5094 standard Main Landing Gear (MLG) cylinders have been reported on Jetstrea m Series 3200 and 3100 aeroplanes.

Prompted by these findings, The United Kingdom (UK) Civil Aviation Authority (CAA) issued AD 003-01-86 to require visual and non -destructive testing (NDT) inspections of the MLG assembly cylinder attachment spigot housing in accordance with BAE Systems (Operations) Ltd SB 32- A-JA851226. In 2012 an
additional occurrence of Jetstream 3100 MLG failure after landing was reported, the subsequent investigation revealed str ess corrosion cracking of the yoke pintle housing as a root cause of the MLG fail ure. Consequently EASA issued EASA AD 2013-0208 to require inspection of t he MLG in accordance with BAE Systems (Operations) Ltd SB 32-A-JA851226 Revision 5 or later approved revisions to detect any crack, however, SB 32-A-JA851226 did not apply to aeroplanes equipped with MLG cylinders man ufactured from L161 material, since that is not susceptible to stress c orrosion. In order to prevent corrosion damage, which may lead to cracking, BAE S ystems (Operations) Ltd issued SB 32-JM7862 to address degradation of the s urface protection by placing a special washer over the forward face of t he MLG spigot housing, which rotates with the spigot housing. EASA issued AD 2013-0206 to requireEASA AD No.: 2014-0239

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/4 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. modification of the left hand (LH) and right hand ( RH) MLG in accordance with
this SB.

In 2014 a further event was reported, where the LH MLG of a Jetstream 3100 aeroplane collapsed during landing, this resulted i n the aeroplane departing from the runway. The accident is still under invest igation by the UK Air Accident Investigation Branch. Preliminary results of the in vestigation determined that cracking, which caused the MLG collapse, was initia ted from a corrosion pit at the top outer edge of the forward spigot housing an d extended along the top of the spigot housing. The spigot housing material was DTD 5094. The affected LH MLG had been modified in accordance with BAE Sys tems (Operations) Ltd SB 32-JM7862 Revision 1. Further investigation disc overed that the instructions provided in BAE Systems (Operations) Ltd SB 32-JM78 62 Revision 1 did not effectively prevent stress corrosion cracking becau se, under certain circumstances, it allows the rotation of the specia l washer and consequent damage of the end face of the spigot housing.

This condition, if not corrected, could lead to str uctural failure of the MLG, possibly resulting in loss of control of the aeropl ane during take-off or landing

runs.

To address this potential unsafe condition, BAE Sys tems (Operations) Ltd issued SB 32-JM7862 Revision 2 to clarify the orien tation of the spigot bearing cap, later revised to SB 32-JM7862 Revision 3 to en sure the spigot bearing cap is correctly positioned. Additionally, BAE Systems (Operations) Ltd issued SB 32-A-JA140940 to provide inspection instructions to detect migration of the special washer and any potential corrosion resultin g from that unwanted migration for MLG installations modified earlier in accordance with BAE Systems (Operations) Ltd SB 32-JM7862 up to Revisio n 2.

For the reasons described above, this AD partially retains the requirements of EASA AD 2013-0206, which is superseded, and require s a one-time inspection of pre-SB 32-JM7862 Revision 3 MLG installations an d, depending on findings, applicable corrective action(s).

Effective Date: 17 November 2014

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:

(1) Within the compliance time as specified in para graph 1.N of BAE Systems (Operations) Ltd SB 32-JM7862, modify the installat ion of the LH and RH MLG at the forward spigot in accordance with the in structions of BAE Systems (Operations) Ltd SB 32-JM7862 Revision 3.

(2) Modification of a LH or RH MLG, before the effe ctive date of this AD, in accordance with the instructions of BAE Systems (Op erations) Ltd SB 32-JM7862 at Revision 1 or Revision 2, is acceptabl e to comply with the requirements of paragraph (1) of this AD for that M LG.

(3) For aeroplanes that, before the effective date of this AD, have been modified in accordance with the instructions of par agraph 2.B. of BAE Systems SB32-JM7862 Revision 2:

Within the compliance time as defined in Table 1 o f this AD, depending on MLG configuration, visually inspect the LH and RH M LG to detect migration of a special washer in accordance with th e instruction of Part 1 of BAE Systems SB 32-A-JA140940.EASA AD No.: 2014-0239

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 3/4 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Table 1 – Visual Inspection

MLG configuration Compliance Time
(after the effective date of this AD, whichever occurs first)

Equipped with DTD5094 cylinder 200 flight cycles (FC) or 2 months

Equipped with L161 cylinder 600 FC or 6 months

(4) If, during the inspection, as required by parag raph (3) of this AD, evidence of migration of the special washer is detected, wit hin the compliance time as defined in Table 1 of this AD, accomplish all th e actions on the MLG cylinder, LH and/or RH, as applicable, in accordanc e with the instructions of Part 2 of BAE Systems SB 32-A-JA140940.

(5) If during the inspection, as required by paragr aph (3) of this AD, no evidence of migration of the special washer is dete cted, before next flight, apply a witness paint over the special washer tab a nd onto the MLG spigot housing (LH and RH MLG) in accordance with the inst ruction of Part 1 of BAE Systems SB 32-A-JA140940.

(6) For aeroplanes that, before the effective date of t his AD, have been modified in accordance with the instructions of par agraph 2.B. of BAE System SB32-JM7862 Revision 1:

Within the compliance time as defined in Table 1 of this AD, depending on MLG configuration, accomplish all the actions on th e MLG cylinder, LH and/or RH, as applicable, in accordance with the in structions of Part 2 of BAE Systems SB 32-A-JA140940.

(7) If, during any of the actions as required by pa ragraph (4) or (6) of this AD, as applicable, any wear, corrosion or damage (as de fined in BAE Systems SB 32-A-JA140940) is detected, before next flight, accomplish all the corrective actions, including application of a witn ess paint, in accordance with the instructions of Part 2 of BAE Systems SB 3 2-A-JA140940.

(8) Within 45 days but not earlier than 30 days, or within 30 FC but not earlier than 20 FC after accomplishment of action as requir ed by paragraph (3) or (6) of this AD, whichever occurs first, inspect the witness paint applied as required by paragraph (5) or (7) of this AD in acco rdance with the instructions of Part 3 of BAE Systems SB 32-A-JA140 940.

(9) If, during the inspection as required by paragr aph (8) of this AD, damaged paint is detected, before next flight, contact BAE Systems (Operations) Ltd to obtain approved repair instructions and within t he compliance time indicated in those instructions accomplish the repa ir accordingly, including any maintenance tasks derived from the provided rep air design.

(10) From the effective date of this AD, installati on of a LH or RH MLG on an aeroplane is allowed, provided the MLG has passed t he inspections as required by this AD.

Ref. Publications: BAE Systems (Operations) Ltd 32- A-JA140940 original issue dated 03 October

2014.

BAE Systems (Operations) Ltd 32-JM7862 Revision 1 d ated 07 May 2013, or Revision 2 dated 13 June 2014, or Revision 3 dated 03 October 2014.

The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.EASA AD No.: 2014-0239

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 4/4 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD.

2. Based on the required actions and the compliance time, EASA have decided to issue a Final AD with Request for Commen ts, postponing the public consultation process until after publication

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Certification 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) L td, Customer Information Department, Prestwick International Air port, Ayrshire, KA9 2RW, Scotland, United Kingdom; Telephone +44 1292 6 75207, Facsimile +44 1292 675704; E-mail: RApublications@baesystems.com

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