EASA AD No.: 2014-0006 

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved 1/3 

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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2014-0006 

Date: 07 January 2014 

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with 

Regulation (EC) No 216/2008 on behalf of the European 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, Part 21.A.3B. In accordance with EC 2042/2003 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 

[EC 2042/2003 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 : 

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 Aerospace Regional Aircraft Ltd , British 

Aerospace (Operations) Ltd and British Aerospace (Commercial Aircraft) Ltd 

Applicability: Jetstream 4100 aeroplanes, all models, all serial numbers 

Reason: An occurrence was reported involving a Jetstream 4100 aeroplane, where a 

bracket, on which the earth post for the generator and propeller de-ice 

systems is located, failed due to overheat. Although the earth post and 

cables were not damaged, the mounting bracket and underlying structure 

were damaged to the extent that repair of the wing front spar web was 

necessary. Furthermore, the aft engine cross support rod, which is attached 

to the same bracket, was found damaged, as a result of excessive current 

load, and required replacement. The subsequent investigation determined 

that, due to the damage tolerance of the aft engine cross rod support, the 

rod does not present an airworthiness issue. However, 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, could reduce the capacity of 

the wing to support loads, possibly resulting in wing structure failure and 

consequent loss of the aeroplane. 

To address this potential unsafe condition, BAE Systems (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 electrical high current bonding 
EASA AD No.: 2014-0006 

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved 2/3 

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check of the bracket and, if discrepancies are detected, accomplishment of 

applicable corrective action(s). 

Effective Date: 21 January 2014 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 6 months after the effective date of this AD, accomplish the 

following actions on both engines in accordance with the instructions of 

paragraph 2.B of BAE Systems (Operations) Ltd SB J41-24-043 at 

Revision 2: 

(1.1) Visually inspect the structure around the earth posts EP2 and 

EP4, the brackets on which they are mounted and the

attachment of the nacelle horizontal support (SB J41-24-043 

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 load 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 test of the EP2 and 

EP4 earth bolts (SB J41-24-043 paragraph 2.B.(3)). 

(2) If, during the visual inspection, as required by paragraph (1.1) of this 

AD, any lateral movement of the earth post or any other 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 by paragraph (1.2) of this 

AD, overheated cable insulation, or arcing damage, or terminal tag 

overheat is detected, before next flight, accomplish the applicable 

corrective action(s) in accordance with the instructions 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 test, 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 corrective action(s) in 

accordance with the instructions of BAE Systems (Operations) Ltd SB 

J41-24-043 at Revision 2 (SB J41-24-043 paragraph 2.B (4)). 

(5) Within 60 days after accomplishment of the actions as required by 

paragraph (1) of this AD, report the results to BAE Systems 

(Operations) Ltd in accordance with BAE Systems (Operations) Ltd SB 

J41-24-043 at Revision 2. 

(6) Inspections and corrective actions, accomplished before the effective 

date of this AD in accordance with BAE Systems (Operations) Ltd SB 

J41-24-043 at original issue, or Revision 1, are acceptable 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 document is acceptable for 

compliance with the requirements of this AD. 

Remarks : 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 
EASA AD No.: 2014-0006 

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2. This AD was posted on 28 November 2013 as PAD 13-176 for 

consultation until 26 December 2013. No comments were received 

during the consultation period. 

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive 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.