EASA AD No.: 2011-0096 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0096 

Date: 25 May 2011 

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 EC 1702/2003, Part 21A.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 Airworthiness Directive applies, except in accordance with the requirements of that Airworthiness Directive 

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]. 

Type 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 57 Wings – Wing Rear Spar – 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: Four cracks were found on a wing rear spar by an operator during a fuel 

leak investigation. The cracks were located between ribs 6 and 7, 

immediately inboard of the inboard engine rib. The cracks initiated at 

adjacent fastener bores in the rear spar upper boom and progressed 

downwards, diagonally, into the rear spar web. 

Such cracking in the rear spar, if not detected and corrected, could 

propagate to a critical length, possibly affecting the structural integrity of the 

area and/or resulting in a fuel tank rupture, and consequent damage to the 

aeroplane and injury to its occupants. 

For the reasons described above, this AD requires a one-time inspection of 

the rear face of the wing rear spar and the accomplishment of the 

associated corrective actions, depending on findings.

Effective Date: 08 June 2011. 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 300 flight hours after the effective date of this AD or before next 

flight, in case a fuel leak is detected in the vicinity of a wing rear spar, 

whichever occurs first, inspect the rear face of the wing rear spars in 
EASA AD No.: 2011-0096 

EASA Form 110 Page 2/2 

accordance with the instructions of paragraph 2.A. of BAE Systems 

(Operations) Ltd Alert Service Bulletin (ASB) 

J41-A57-029. 

(2) If, during the inspection required by paragraph (1) of this AD, any 

cracks, corrosion or other defects are found, before next flight, 

accomplish the associated corrective action defined in Table 1 of this 

AD: 

Table 1 

Damage found: Corrective action: 

within the criteria as 

specified in BAE Systems 

(Operations) Ltd Jetstream 

4100 Structural Repair 

Manual (SRM) 57-00-00 

Repair in accordance with the 

repair instructions of BAE 

Systems (Operations) Ltd 

Jetstream 4100 SRM 57-00-00. 

exceeds the criteria as 

specified in BAE Systems 

(Operations) Ltd Jetstream 

4100 SRM 57-00-00 

Repair the damage in 

accordance with a BAE 

Systems approved repair 

scheme or contact BAE 

Systems (Operations) Ltd. for 

approved repair instructions 

and accomplish those 

instructions accordingly. 

(3) Within 10 days after the inspection required by paragraph (1) of this 

AD, report all findings, including no defects, to BAE Systems 

(Operations) Ltd in accordance with the instructions of paragraph 

2.A.(7) of ASB J41-57-029. 

Ref. Publications: 

BAE Systems (Operations) Limited Alert Service Bulletin J41-A57-029, 

Original issue, dated 6 May 2011. 

Jetstream 4100 Structural Repair Manual Revision 30 dated 15 April 2007. 

The use of later approved revisions of these documents 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. 

2. The required actions and the risk allowance have granted the issuance 

of a Final AD with Request for Comments, postponing the public 

consultation process after publication. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research 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.