EASA 

EASA AD No.: 2015-0061 

AIRWORTHINESS DIRECTIVE 

AD No.: 2015-0061 

Date: 20 April 2015 

(EC) 

Note: 

No 

This 

216/2008 

Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation 

European 

on behalf of the European Community, its Member States and of the 

Regu

third countries that participate in the activities of EASA under Article 66 of that 

lation. 

This AD is issued in accordance with EU 748/201 2, Part 21.A.3B. In accordance with EU 1321/2014 Annex I, Part M A.301 , the 

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an 

aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [EU 

1321/2014 Annex I, Part M.A.303) or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption). 

Design Approval Holder's Name: Type/Model designation(s): 

BAE SYSTEMS (Operations) Ltd Jetstream Series 3100 and 3200 aeroplanes 

TCDS Number: 

Foreign AD: 

Supersedure: 

ATA32 

Manufacturer(s): 

Applicability: 

Reason: 

Effective Date: 

EASA.A.191 

Not applicable 

None 

Landing Gear- Main Landing Gear Trunnion Cap Tension BoltsInspection 

British Aerospace pic, British Aerospace (Commercial Aircraft) Ltd, British 

Aerospace Regional Aircraft Ltd, Jetstream Aircraft Ltd and British Aerospace 

(Operations) Ltd. 

Jetstream 3100 and 3200 aeroplanes, all models, all serial numbers. 

The review of the BAE production drawing for main landing gear (MLG) fitting 

installation identified a risk of omitting 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 condition, if not detected and corrected, could lead to failure of the bolt(s), 

thereby compromising the structural integrity of the other MLG tension bolts 

holding the MLG in place, possibly resulting in collapse of the MLG on take-off 

or landing with consequent damage to the aeroplane and injury to occupants. 

Although so far, no in-service bolt head failures 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 Service Bulletin (SB) 57-

JA 120141 to provide inspection instructions. 

For the reasons described above, this AD requires inspection and, depending 

on findings, replacement of the MLG trunnion cap tension bolts. 

04 May 2015 

TE.CAP.00 110·004 © European Aviation Safety Agency. All rights reserved. 1/3 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/lntranet. 
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 paragraph (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 

replacement 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 required 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-JA120141 . 

(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 

Bolt P/N 'Old' Bolt P/N 'New' 

MS21134H07045 MS21134H07046, or MS21250H07046 

MS21134H07059 MS21134H07060, or MS21250H07060 

TE.CAP.OOll0-004 © European Aviation Safety Agency. All rights reserved. 

Propr

2/3 ietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/lntranet. 
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 flight, reinstall crack-free bolts, or install replacement 

bolts, having a PIN identified as 'new' in Table 3 of this AD, and install a 

countersunk washer PIN PKS1000-7-2-S under each bolt, in accordance 

with the instructions of the BAE Systems {Operations) Ltd SB 57-

JA120141 . 

(7) If, 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 the instructions of the BAE Systems (Operations) Ltd SB 57-

JA120141 . 

Table 3 - Replacement Parts 

Bolt PIN '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 revisions of this document is acceptable for 

compliance with the requirements of this AD. 

1. If requested and appropriately substantiated, 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 the Safety Information 

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 International Airport, Ayrshire, 

KA9 2RW, Scotland, United Kingdom: Telephone +44 1292 675207, 

Facsimile +44 1292 675704; E-mail: RApublications@baesystems.com. 

TE.CAP.00110· 004 ©European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Confirm revision status through the E.ASA· lnternet/lntranet.