EASA AD No.: 2009-0074 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0074 

Date: 31 March 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) : 

ATP aeroplanes 

TCDS Number : United Kingdom BA23 

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA AD 2006-0090 dated 20 April 2006. 

ATA 51 Structures – New and Revised Inspections for Fatigue and 

Environmental Damage – Implementation 

Manufacturer(s): British Aerospace plc, British Aerospace (Commercial Aircraft) Ltd 

Applicability: ATP aeroplanes, all serial numbers. 

Reason: 

A review of the results of the final fuselage fatigue test identified the need for 

additional and revised safety-related fatigue- and environmental inspections for 

the fuselage. These additional tasks were introduced by Service Bulletin (SB) 

ATP-51-002, which supplemented and in some cases revised those previously 

published in the Aircraft Maintenance Manual (AMM) Chapter 05-10-17 and 

the Maintenance Review Board Report (MRBR). 

As it was determined that these inspections were necessary to maintain the 

structural integrity of the aeroplane, EASA AD 2006-0090 was issued to 

require the inspections and, depending on findings, corrective actions as 

defined in BAE Systems (Operations) Limited SB ATP-51-002 (the SB) at 

original issue. 

Since the original Issue of the SB, three revisions have been published. 

Revision 1 of the SB included only editorial changes. Revision 2 of the SB 

corrected the fuselage frame designations in Parts 50 and 50A and extended 

the allowable time before initial inspection. In addition, the repeat inspection 

interval in Part 43 of the SB was reduced. In the latest Revision 3 of the SB, 

the grace period for the initial inspection in Part 50 has been clarified. 

Fatigue tasks in Parts 1 through 50 of the SB, i.e. those without an “A” suffix, 

have now been replicated in AMM Chapter 05-10-17 and MRBR Section 6. In 

addition, environmental tasks, those identified with an “A” suffix, have now 
EASA AD No.: 2009-0074 

EASA Form 110 Page 2/2 

been replicated in MRBR Section 6. 

For the reasons described above, this AD retains the requirements of EASA 

AD 2006-0090, which is superseded, and requires the accomplishment of the 

inspections and, depending on findings, corrective actions as defined in BAE 

Systems (Operations) Limited SB ATP-51-002 at Revision 3. 

Effective Date: 14 April 2009 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) From 04 May 2006 [the effective date of EASA AD 2006-0090], 

accomplish the inspections and, depending on findings, corrective actions 

described in BAE Systems (Operations) Limited SB ATP-51-002. 

(2) Inspections and corrective actions accomplished prior to the effective date 

of this AD in accordance with BAE Systems (Operations) Limited SB ATP51-002 at original issue or Revision 1 or Revision 2 are acceptable to 

comply with the requirements of paragraph (1) of this AD. 

(3) Within 30 days after the effective date of this AD, amend the approved 

aircraft maintenance schedule to incorporate the inspections as defined in 

BAE Systems (Operations) Limited SB ATP-51-002 at Revision 3. 

(4) Thereafter, within the thresholds and intervals indicated in the SB, 

accomplish the inspections and, depending on findings, corrective actions 

in accordance with the instructions of BAE Systems (Operations) Limited 

SB ATP-51-002 at Revision 3. Accomplishment of corrective actions in 

accordance with the SB does not constitute terminating action for the 

repetitive inspection requirements of this AD. 

(5) Within 30 days after each inspection as required by paragraph (4) of this 

AD, send an Inspection Report to BAE Systems in accordance with the 

instructions of paragraph 2 of the SB. 

Ref. Publications: 

BAE Systems (Operations) Limited SB ATP-51-002 original issue dated 20 

December 2005, Revision 1 dated 26 February 2007, Revision 2 dated 19 

November 2007, and Revision 3 dated 3 April 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 26 February 2009 as PAD 09-047 for 

consultation until 26 March 2009. 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 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.