EASA AD No : 2008-0168 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2008-0168 

Date: 02 September 2008 

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 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]. 

Type Approval Holder’s Name : 

BAE Systems (Operations) Ltd 

Type/Model designation(s) : 

BAe 146 and AVRO 146-RJ aircraft 

TCDS Number : EASA.A.182 

Foreign AD : Not applicable 

Supersedure : This AD supersedes United Kingdom (UK) CAA AD 015-08-91 

ATA 57 Wings – Wing Centre Section Top Skin and Joint Strap at Rib 0 – 

Inspection / Repair 

Manufacturer(s): 

BAE Systems (Operations) Ltd, British Aerospace plc, British Aerospace 

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

Regional Aircraft Ltd, British Aerospace Regional Aircraft trading as Avro 

International Aerospace. 

Applicability: 

BAe 146 and AVRO 146-RJ aircraft, all models, all serial numbers, except 

aircraft for which the instructions contained in the applicable BAE Systems 

(Operations) Ltd Supplemental Structural Inspection Document (SSID) have 

been incorporated into the approved aircraft maintenance programme. 

Reason: 

In 1991, the UK Civil Aviation Authority (CAA) issued AD 015-08-91, requiring 

the accomplishment of inspections of, and in case of crack findings, corrective 

actions on, the wing top skin at rib ‘0’ of pre-modification HCM00851C BAe 146 

series aircraft in accordance with British Aerospace Service Bulletin (SB) 57-41 

dated 26 July 1991. Recently, BAE Systems (Operations) Ltd has determined 

that a revised inspection programme for the wing top skin and joint strap at rib ‘0’ 

on all BAe 146 and AVRO 146-RJ aircraft is necessary to assure the continued 

structural integrity of this area. Cracking of the wing centre section top skin, if 

undetected, could lead to structural failure and consequent loss of the aircraft. 

For the reasons described above, this new EASA AD supersedes UK CAA AD 

015-08-91 and requires repetitive high-frequency eddy current (HFEC), 

radiographic, ultrasonic, and detailed visual inspections of the wing top skin and 

joint strap at rib ‘0’, the reporting of all inspection results to BAE Systems and, in 

case of findings, the accomplishment of corrective actions.

Effective Date: 16 September 2008 
EASA AD No : 2008-0168 

EASA Form 110 Page 2/2 

Required 

Action(s) and 

Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

Note: The instructions of BAE Systems (Operations) Limited Inspection Service 

Bulletin ISB.57-070 (the ISB), which is the subject of this AD, are divided in two 

parts; consequently, the statement in paragraph 1.C. of the ISB that there are 

three parts is incorrect and can be disregarded. 

(1) Within the threshold and intervals defined in paragraph 1.D.(1) of the ISB, 

accomplish the initial and repetitive inspections, in accordance with 

paragraph 2.C. (Part 1) of the ISB, except that for the purpose of this AD, 

where paragraph 1.D.(1)(b) of the ISB specifies to inspect within 4 000 

flights of receipt of the ISB, that instruction must be read as “within 3 000 

flights after the effective date of this AD”. 

(2) Within the threshold and intervals defined in paragraph 1.D.(2) of the ISB, 

accomplish the initial and repeat inspections in accordance with paragraph 

2.C. (Part 2) of the ISB. 

(3) Within 30 days after each inspection as required by paragraph (1) and (2) of 

this AD, report the inspection results to BAE Systems (Operations) Ltd in 

accordance with paragraph 2.F. of the ISB. 

(4) When cracks or corrosion are found during any inspection as required by 

this AD, before next flight, repair any damage, either in accordance with the 

applicable Structural Repair Manual or in accordance with an approved BAE 

Systems repair. 

(5) Accomplishment of any repair does not constitute terminating action for the 

inspection requirements of this AD.

Ref. Publications: 

BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-070 Initial 

Issue dated 15 October 2007. 

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. 

2. This AD was posted on 31 July 2008 as PAD 08-088 for consultation until 28 

August 2008. No comments were received during the consultation period. 

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 questions 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