EASA AD No : 2009-0014 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0014 

Date: 21 January 2009 

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: None 

ATA 57 Wings – Fixed Wing Leading Edge and Front Spar Structure – 

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. 

Reason: 

During the removal of the wing removable leading edge on a BAe 146 aircraft 

for a repair (not related to the subject addressed by this AD), corrosion was 

found on the wing fixed leading edge structure. The investigation determined 

that the existing scheduled environmental and fatigue inspections would not 

have detected the corrosion or fatigue damage. 

Corrosion or fatigue damage in this area, if not detected and corrected, could 

lead to degradation of the structural integrity of the wing. 

For the reason described above, this AD requires repetitive inspections of the 

wing fixed leading edge and front spar structure for corrosion and/or fatigue 

damage and repair, depending on findings. 

Effective Date: 04 February 2009 
EASA AD No : 2009-0014 

EASA Form 110 Page 2/3 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within the thresholds defined in paragraph 1.D.(1) of BAE Systems 

(Operations) Limited Inspection Service Bulletin ISB.57-072 (the ISB), 

except where modified by this paragraph, accomplish the initial 

environmental/fatigue inspections, in accordance with paragraph 2.C. 

(Method 1) or paragraph 2.D. (Method 2) of the ISB. Where paragraph 

1.D.(1) of the ISB states “within 2 years from the initial issue of this 

inspection service bulletin” this shall be read as “within 18 months from the 

effective date of this AD”. Similarly, where paragraph 1.D.(1) of the ISB 

states “within 1 year from the initial issue of this inspection service bulletin” 

this shall be read as “within 6 months from the effective date of this AD”. 

Note 1: At the discretion of the aircraft owner/operator, enhanced corrosion 

protection may then be embodied on those areas subject to a detailed visual 

inspection (DVI) in accordance with paragraph 2.E. or paragraph 2.F. of the ISB. 

Embodiment of enhanced corrosion protection in accordance with paragraph 

2.E. of the ISB allows the interval of the repetitive inspection (as required by 

paragraph (2) of this AD) to be extended in the area(s) of application. 

(2) After the initial inspection as required by paragraph (1) of this AD, within 

the intervals defined in paragraph 1.D.(2)(a) of the ISB, accomplish the 

repetitive environmental inspections in accordance with paragraph 2.C. 

(Method 1) or paragraph 2.D. (Method 2) of the ISB. Where previously 

applied, enhanced corrosion protection may then be re-applied, as desired, 

in accordance with paragraph 2.E. of the ISB. Re-application (or not) 

determines the interval for the next repetitive inspection. 

(3) After the initial inspection as required by paragraph (1) of this AD, within 

the intervals defined in paragraph 1.D.(2)(b) of the ISB, accomplish the 

repetitive fatigue inspections in accordance with paragraph 2.C. (Method 1) 

or paragraph 2.D. (Method 2) of the ISB. 

(4) When defects 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. 

Note 2: The inspections required by this AD supersede the Maintenance 

Review Board Report (MRBR), Maintenance Planning Document (MPD), 

Corrosion Prevention and Control Programme (CPCP) and Supplemental 

Structural Inspection Document (SSID) inspections defined in paragraph 1.C.(3) 

of the ISB. 

Note 3: Where the ISB refers to a Visual Inspection (VI), this term describes an 

inspection using visual inspection equipment as defined in Appendix 3 of the 

ISB. In other BAE Systems instructions for continued airworthiness, including 

the Maintenance Planning Document and the Corrosion Protection & Control 

Programme, such an inspection is referred to as a 'Special Detailed Inspection' 

(SDI). Later Revisions of the ISB will refer to SDIs where applicable. 

Ref. Publications: 

BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-072 Initial 

Issue dated 22 February 2008. 

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 published on 05 January 2009 as PAD 09-002 for consultation 

until 19 January 2009. The Comment Response Document can be found at 

http://ad.easa.europa.eu/. 
EASA AD No : 2009-0014 

EASA Form 110 Page 3/3 

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 (0)1292 675207, Facsimile +44 (0)1292 675704 

E-mail: RApublications@baesystems.com