EASA AD No.: 2014-0006

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.: 2014-0006

Date: 07 January 2014

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an Community, its Member States and of the European third countries that participate in the activities 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 accor dance with the requirements of that AD, unless othe rwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, Article 14(4) exemption]. 

### Design Approval Holder’s Name :

BAE SYSTEMS (OPERATIONS) Ltd Type/Model designation(s) :

Jetstream 4100 aeroplanes

TCDS Number : EASA. A.189

Foreign AD : Not applicable

Supersedure : None



### ATA 24 Electrical Power – Earth Post – Inspection / Repair

Manufacturer(s): Jetstream Aircraft Ltd, British Ae rospace Regional Aircraft Ltd , British Aerospace (Operations) Ltd and British Aerospace (C ommercial Aircraft) Ltd

Applicability: Jetstream 4100 aeroplanes, all model s, all serial numbers

Reason: An occurrence was reported involving a Jets tream 4100 aeroplane, where a bracket, on which the earth post for the generator and propeller de-ice systems is located, failed due to overheat. Althoug h the earth post and cables were not damaged, the mounting bracket and u nderlying structure were damaged to the extent that repair of the wing front spar web was necessary. Furthermore, the aft engine cross suppor t rod, which is attached to the same bracket, was found damaged, as a result of excessive current load, and required replacement. The subsequent inve stigation determined that, due to the damage tolerance of the aft engine cross rod support, the rod does not present an airworthiness issue. Howeve r, as a consequence of overheat failure of the earth post, degradation of the wing front spar cap and/or web could affect the structural integrity of the wing.
This condition, if not detected and corrected, coul d reduce the capacity of the wing to support loads, possibly resulting in wi ng structure failure and consequent loss of the aeroplane.
To address this potential unsafe condition, BAE Sys tems (Operations) Ltd issued Service Bulletin (SB) J41-24-043 to provide inspection instructions.
For the reasons described above, this AD requires a one-time visual inspection of the affected earth posts, an electric al high current bondingEASA AD No.: 2014-0006

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. check of the bracket and, if discrepancies are dete cted, accomplishment of applicable corrective action(s).

Effective Date: 21 January 2014

Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:
(1) Within 6 months after the effective date of thi s AD, accomplish the following actions on both engines in accordance wit h the instructions of paragraph 2.B of BAE Systems (Operations) Ltd SB J4 1-24-043 at Revision 2: (1.1) Visually inspect the structure around the ear th posts EP2 and EP4, the brackets on which they are mounted and the attachment of the nacelle horizontal support (SB J4 1-24-043 paragraphs 2.B.(2)(a) and (2)(b)). (1.2) Visually inspect the generator and propeller de-ice system earth cables (SB J41-24-043 paragraph 2.B.(2)(d)). (1.3) Check, and if necessary adjust, the torque lo ad of the EP2 and EP4 earth post stiff nuts (SB J41-24-043 paragraph 2.B.(2)(e)). (1.4) Accomplish a high-current millivolts-drop tes t of the EP2 and EP4 earth bolts (SB J41-24-043 paragraph 2.B.(3)). (2) If, during the visual inspection, as required b y paragraph (1.1) of this AD, any lateral movement of the earth post or any o ther damage, as specified in BAE Systems (Operations) Ltd SB J41-24 -043, is detected, before next flight, contact BAE Systems ( Operations) Ltd to obtain approved repair instructions and accomplish those instructions accordingly (SB J41-24-043 paragraph 2.B.(2)(c)). (3) If, during the visual inspection, as required b y paragraph (1.2) of this AD, overheated cable insulation, or arcing damage, or terminal tag overheat is detected, before next flight, accomplis h the applicable corrective action(s) in accordance with the instruc tions of BAE Systems (Operations) Ltd SB J41-24-043 at Revision 2 (SB J41-24- 043 paragraph 2.B.(2)(d)). (4) If, during the high-current millivolts-drop tes t, as required by paragraph (1.4) of this AD, resistance is measured exceeding the value(s) as specified in BAE Systems (Operations) Ltd SB J41-24 -043 at Revision 2, before next flight, accomplish the applicable co rrective action(s) in accordance with the instructions of BAE Systems (Op erations) Ltd SB J41-24-043 at Revision 2 (SB J41-24-043 paragraph 2 .B (4)). (5) Within 60 days after accomplishment of the acti ons as required by paragraph (1) of this AD, report the results to BAE Systems (Operations) Ltd in accordance with BAE Systems (Op erations) Ltd SB J41-24-043 at Revision 2. (6) Inspections and corrective actions, accomplishe d before the effective date of this AD in accordance with BAE Systems (Ope rations) Ltd SB J41-24-043 at original issue, or Revision 1, are ac ceptable to comply with the requirements of this AD.

Ref. Publications: BAE Systems (Operations) Ltd SB J41-24-043 original issue dated 27 September 2011, or Revision 1 dated 16 January 2012 , or Revision 2 dated 21 August 2013.
The use of later approved revisions of this documen t 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.EASA AD No.: 2014-0006

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. 2. This AD was posted on 28 November 2013 as PAD 13 -176 for consultation until 26 December 2013. No comments we re received during the consultation period.
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, United Kingdom; Telephone +44 1292 675207, Facsimile +44 1 292 675704; E-mail: RApublications@baesystems.com

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