EASA AD No : 2007-0091

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2007-0091 [Corrected: 23 June 2008]

Date: 10 April 2007

Note: This Airworthiness Directive (AD) is i ssued 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 t he 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 opera te an aircraft to which an AD applies, except in accordance with the requirements of that AD unless otherwise specified by the Age ncy [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) exemptio n]. 

### Type Approval Holder’s Name :

AIRBUS SAS Type/Model designation(s) :

A300 aircraft

TCDS Number : France No. 145

Foreign AD : Not applicable

Supersedure: This AD supersedes DGAC France AD 1989-061-092(B) R4.



### ATA 53 Fuselage – Sections 13 to 18 Longitudinal Lap Joints – Inspection

Manufacturer(s): AIRBUS (formerly AIRBUS INDUSTRIE).

Applicability: AIRBUS A300 aircraft, all certified mo dels, serial number s (MSN) 0003 through 0156 included.

Reason: This Airworthiness Directive (AD) is issued in order to prevent cracks development in sections 13 to 18 of t he fuselage between rivets of longitudinal lap joints between frames 18 and 80 which c ould affect structural integrity of the fuselage if not corrected.
This new AD: - Retains the requirements of DGAC AD 1989-061-092(B)R4, which is

cancelled; - Takes into account a new inspection program as detailed in AIRBUS Service

Bulletins (SB) A300-53-0211 Revision 7, which will allow A300 aircraft to reach the Limit of Validity (LOV). This AD has been republished to correctly refer to SB A300-53-0211 in Note 2 of the Compliance section.
Effective Date: 24 April 2007

Required action(s) and Compliance Time(s): New requirements of this AD: 1. Inspect longitudinal lap joints for cracks Unless already accomplished, within 2 000 flight cycles, counted from 01 December 2006, the following actions are rendered mandatory :EASA AD No : 2007-0091

EASA Form 110 Page 2/2 1.1. In order to prevent cracks development in sections 13 to 18 of the fuselage between rivets of longitudinal lap joints, perform the inspection program on : - the non repaired longitudinal lap joints, inner skin, - the repaired or modified longitudinal joints,
in accordance with the instructions of SB A300-53-0211 revision 7 at the threshold and interval values specified either in Tables 1A, 1B, 2 of section 3.A.(3), or in Section 3.E. figure 3 of SB A300-53-0211 revision 7, as applicable.
Note 1 : an application tolerance of 2000 Flight Cycles counted from 01 December 2006 [date of release of SB A 300-53-0211 revision 7] is applicable, as long as these values do not exceed 50% of the applicable intervals.
Note 2 : for special and standard areas, the areas with an application period given in Figure 3 must be modified by accomplishment of Modification Service Bulletins when the application period has been reached. Refer to Section 3.E. figure 3 of SB A300-53-0211 revision 7.
1.2. In case of crack discovery, carry out relevant corrective actions within imposed time limits in accordance with the SB A300-53-0211 revision 7.
1.3. Send inspection results to AIRBUS, whatever they are.

Requirements of AD 1989-061-092(B)R4 2. Inspect fuselage inner doublers In order to detect debonding and corrosion, inspect from inside, the bonded inner doublers of longitudinal lap joints between frames 18 and 80, in accordance with instructions of SB A300-53-0229 revision 5, at the specified threshold and interval values. In case of debonding and/or corrosion detected during inspections, perform relevant corrective actions within imposed time limits in accordance with instructions of SB A300-53-0229 revision 5.

Ref. Publications: AIRBUS SB A300-53-0211 Revision 7 and SB A300-53-0229 Revision 5. 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 subs tantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 07 March 2007 as PAD 07-039 for consultation until 04 April 2007. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA; E-mail ADs@easa.europa.eu

. 4. For any question concerning the technica l content of the requirements in this AD, please contact: AIRBUS SAS – EAW, Airworthiness Office, Telephone + 33 5 61 93 36 96; Facsimile + 33 5 61 93 44 51.