AIRWORTHINESS DIRECTIVE

CAA-AD-002/2001R1

Supersedes CAA-AD-002/2001

Date of issue: June 19, 2002

AIRCRAFT - FUSELAGE - WING ROOT (ATA 53) - INSPECTION

Applicability:

AIRBUS A310 aircraft, all certified models and all serial numbers on which AIRBUS modifications No. 08888 and No. 08889 have not been embodied in production.

Effective date: August 08, 2002

Compliance: Required as indicated in DGAC AD 2000-514-326(B) R1.

Remarks: The compliance of this AD must be recorded in Aircraft Logbook, where applicable the requirements of this AD must be integrated into Aircraft Technical Documentation. Address inquiries concerning this AD to: Civil Aviation Authority, Airworthiness Division, Ruzyne Airport, 160 08 Prague 6, Czech Republic, tel.: 420 2 33320922, fax: 420 2 20562270.

Ing. Pavel MATOUŠEK

Director of Airworthiness Division

CAA CZ

DGAC AD No.: 2000-514-326(B) R1

AIRBUS

A310 aircraft

Fuselage - Chafing plates of wing root (ATA 53)

APPLICABILITY:

AIRBUS A310 aircraft, all certified models and all serial numbers on which AIRBUS modifications No. 08888 and No. 08889 have not been embodied in production.

REASONS:

In-service experience revealed cases of corrosion and crack development around and under the chafing plates of the wing root between FR36 and FR39.

An inspection program was rendered mandatory by Airworthiness Directive (AD) 96-008-175(B) in order to prevent any degradation of the structural integrity of the airframe. This AD considered AIRBUS INDUSTRIE Service Bulletin (SB) A310-53-2070 (Modification No. 08888 and 08889) as the final action of the inspection program, which is not the case when rework is required to eliminate corrosion before application of the modification : a program of repetitive fatigue inspections then remains mandatory.

This AD, which redefines the "corrosion" and "fatigue" inspection program, deletes and supersedes AD 96-008-175(B) in order to prevent any misinterpretation of this later.

The aim of Revision 1 of this AD is to cancel the paragraph concerning adjustment for range method which is no more necessary Revision 4 of SB A310-53-2069 gives threshold and interval with FH and FC limits for fatigue inspection.

COMPLIANCE:

1. Four years after the first flight of the aircraft, or within 18 months following the effective date of this AD at original issue, whichever occurs later, perform a (corrosion + fatigue) inspection in accordance with the instructions of SB A310-53-2069 R4.

The aircraft which have already been checked in accordance with the instructions of SB A310-53-2069 R1 (or any later approved revision) are not subjected to the requirements of paragraph Actions 1 - of this AD.

2. Depending on the results of the previous inspections, perform rework or apply repair if necessary and repeat the inspections at intervals and in accordance with the instructions of SB A310-53-2069 R4.

No further inspections in accordance with the "corrosion" requirements of this AD are necessary after application of SB A310-53-2070.

No further inspections in accordance with the "fatigue" requirements of this AD are necessary after application of SB A310-53-2070, provided rework was not necessary to eliminate corrosion after an inspection in accordance with the instructions of SB A310-53-2069 R1 (or any later approved revision).

[...]

REF:

- AIRBUS INDUSTRIE Service Bulletins

A310-53-2069 R4

A310-53-2070

Any later approved revision of these SB is acceptable.

- Airworthiness Directive 96-008-175(B)

[...]

This Airworthiness Directive replaces AD 96-008-175(B), which is cancelled.

This Revision 1 replaces original AD 2000-514-326(B) dated December 13,2000.

EFFECTIVE DATE:

Original AD: DECEMBER 23, 2000

Revision 1: JUNE 08, 2002