## EASA EASA A D N o .: 20 15- 0 061 

## AIRWORTHINESS DIRECTIVE AD N o. : 2015-0061 Date : 20 April 20 1 5 Note : Th i s Airworthiness Dir ect ive (AD ) i s issued by EAS A , a cti ng i n a cco rdan ce with Reg ulation (EC) No 216/2008 on b eh al f of t he E u r opean C omm u n ity , its Member States and of the E uropean t hird count rie s that participate in t he activities of EASA under A rticle 66 of th at Regu lation . Thi s AD is iss ued i n a ccor d a nce with EU 74 8/ 201 2, Part 2 1 .A . 3B . In a c corda nce with EU 1321/20 1 4 A n nex I , Part M A.301 , the conti nui ng airworthiness of an aircraft shall be ens u red by accomplishing any applicable ADs . Consequently , no person may o perate a n a ircr aft to wh ich an AD ap pl i es , ex cept in acco rda nce with th e r eq u i re me nts of that AD , un less oth erwis e speci fi ed by the Ag enc y [EU 132 1/ 20 14 An nex I , Part M . A. 303) or agr eed wi th the Authorit y of th e State of Regis try [EC 216/2008, Article 1 4 (4) exemption) . 

### Design Approval Holder's Name: Type/ Mod e l designation(s) : BAE SYSTEMS (Operations) Ltd Jetstream Series 3100 and 3200 aeroplanes T C DS Number: Foreign AD : Supersedure : 

### ATA32 Manufacturer(s): Applicabil ity : Reason :

Effective Date : EASA.A . 191 Not applicable None 

### Landing Gear- Main Land ing Gear Trunnion Cap Tension BoltsI nspectio n Brit i sh Aerospace pic , British Aerospace (Commercial Aircraft) Ltd, Brit i sh Aerospace Regional Aircraft Ltd , Jetstream Aircraft Ltd and British Aerospace (Operati ons) Ltd . Jetstream 3100 and 3200 aeroplanes , all models, all serial numbers . The review of the BA E production drawing for main landing gear (MLG) fitting installation identified a risk of omitti ng installation of a countersunk washer under the head of the MLG trunnion cap tension bolts, potentially causing fatigue in the bolt shank under the head of such tension bolt(s) . This cond ition , if not detected and co r rected , could lead to fa i lure of the bolt(s) , thereby compromising the structural integrity of the other MLG tension bolts hold i ng the M LG i n place , possibly resulting in collapse of the MLG on take -off or landing with consequent damage to the aeroplane and inj ury to occ u pants . Although so far , no in-service bolt head fai lu res have been reported since entry in to service of the type design in 1986 , to address this potential unsafe condition , BAE Systems {Operations) Ltd issued Servi ce Bulletin (SB) 57- JA120141 to provide inspection instructions. For the reasons described above , this AD r equires inspection and, depending on findings , replacement of the MLG trunnion cap tension bolts . 04 May 2015

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A- Interne t/l ntra net .Required Action(s) and Compliance Time(s) : EASAAD No .: 2015-0061 Required as indicated , unless accomplished previously : Within 250 flight cycles (FC) after the effective date of this AD , accomplish the actions required by paragraph (1) or (2) of this AD , depending on aeroplane configuration, except as specified in pa ragraph (3) of this AD, in accordance with the instructions of the BAE Systems (Operations) Ltd SB 57 -JA 120141 . (1) For Pre-Mod JM5218 aeroplanes : (1.1) Accomplish a Magnetic Particle Inspection (MPI) of each MLG trunnion cap tension bolt. ( 1 . 2) If , during any MPI as required by paragraph (1.1) of this AD , no crack is found , before next flight , re-install crack-free bolts , or install rep lacement bolts , having the same Part Number (P/N) , and install a countersunk washer under each bolt , having a PIN as identified in Table 1 of this AD, as applicable . (1 .3) If , during any inspection as requ ire d by paragraph ( 1.1 ) of this AD , a cracked bolt is found, before next flight, replace the bolt with a seNiceable one , including installation of a washer , as identified in Table 1 of this AD, as applicable. Table 1 -Pre-Mod JM5218 Replacement Parts Bolt P / N Washer P/N MS21250H06040 PKS1 000 -6 -2-S (washer) MS21250H07040 PKS1000 -7-2-S (washer) (2) For Post-Mod JM5218 aeroplanes, visually inspect the bolts to determine which type of bolt is installed. If installed bolts , determined as required by paragraph (2) of this AD , are PIN MS21134H07045 or PIN MS21134H07059 , before next flight (except as specified in paragraph (4) of this AD) , replace each bolt with a bolt having a P/N identified as ' new' in Table 2 of this AD , as applicable , and install a washer having P/N PKS1000-7 - 2-S under each bolt. (3) If no ' new' replacement bolt is available to comply with paragraph (2) of this AD , the 'old' bolt may be reinstalled without a countersunk washer, provided that , within 500 FC after reinstallation, and , thereafter , at inteNals not to exceed 500 FC , each affected bolt is inspected by MPI , in accordance with the instructions of the BAE Systems (Operations) Ltd SB 57-JA120 1 41 . (4) Within 2 000 FC after reinstallation of a bolt as allowed by paragraph (3) of this AD , or before next flight , in case a crack is detected during any MPI as required by paragraph (3) of this AD, replace the bolt with a bolt having a P/N identified as 'new' in Table 2 of this AD and install a countersunk washer having P/N PKS1000-7-2-S under that bolt, in accordance with the instructions of the BAE Systems (Operations) Ltd SB 57-JA120141 . Table 2- Post-Mod JM5218 Replacement Parts B o lt P /N 'O l d' B o lt P /N ' N ew' MS21134H07045 MS21134 H 07046 , or MS21250H07046 M S21134H07059 MS21134H07060 , or MS21250H07060

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### Ref. Publications :

Remarks: EASA AD No. : 2015-0061 

### (5) If installed bolts , determined as required by paragraph (2) of this AD, are PIN MS21250H07046 or PIN MS21250H07060 and no countersunk washer is installed, before next flight, accomplish an MPI of each MLG trunnion cap tension bolt , in accordance with the instructions of the BAE Systems (Operations) Ltd SB 57-JA 120141 . (6) If, during the MPI as required by paragraph (5) of this AD, no crack is detected, before next f l ight , reinsta ll crack-free bolts, or install replacement bo lts, having a PIN identified as 'new' in Table 3 of this AD , and install a countersunk washe r PIN PKS1000-7-2-S under each bolt , in accordance with the instructions of the BAE Systems {Operations) Ltd SB 57- JA120141 . (7) I f , during the MPI as required by paragraph (5) of this AD , any crack is detected , before next flight , replace each cracked bolt with a seNiceable one , having a PIN identified as 'new' Table 3 of this AD and install a countersunk washer PIN PKS1000 -7-2-S under each bolt , in accordance with t he instructions of the BAE Systems (Operations) Ltd SB 57- JA120141 . Table 3 - Replacement Parts Bol t PI N ' Old ' Bolt P / N ' New' MS21250H07046 MS21250H07046 , or MS21134H07046 MS21250H07060 MS21250H07060, or MS21134H07060 BAE Systems (Operations) Ltd SB 57-JA120141 original issue dated 31 July 2012, or Revision 1 dated 08 April 2014 . The use of later approved rev isio ns of this document is acceptable for compliance with the requirements of this AD . 1 . I f requested and appropriate ly substantiat ed , EASA can approve Alternative Methods of Compliance for this AD . 2 . This AD was posted on 19 March 2015 as PAD 15-025 for consultation until 16 April 2015 . No comments were received during the consultation period . 3 . Enquiries regarding this AD should be referred to t h e Safety I nformation Section, Certification Directorate , EASA. E-mail : ADs@easa .europa.eu . 4 . For any question concerning the technical content of the requirements in this AD , please contact: BAE Systems (Operations) Ltd , Customer Information Department, Prestwick Interna ti ona l Airpo rt , Ayrshire, KA9 2RW , Scotland, United Kingdom : Tel ephone +44 1292 675207, Facsimile +44 1292 675704; E-mail : RApublications@baesystems
.com .

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