AIRWORTHINESS DIRECTIVE

CAA-AD-020/1999R1

Replaces CAA-AD-020/1999

Date of issue: June 19, 2002

AIRCRAFT - FUSELAGE - FRAME (ATA 53) - INSPECTION

Applicability:

AIRBUS A310 and A300-600 aircraft, all certified models except for A300F4-605R and F4-622R models, all serial numbers, on which AIRBUS serial modification No. 06925 has been embodied.

Effective date: August 08, 2002

Compliance: Required as indicated in DGAC AD 1999-013-276(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.: 1999-013-276(B) R1

AIRBUS

A310 and A300-600 aircraft

Fuselage - Frame FR73A at the level of the aft pax door (ATA 53)

APPLICABILITY:

AIRBUS A310 and A300-600 aircraft, all certified models except for A300F4-605R and F4-622R models, all serial numbers, on which AIRBUS serial modification No. 06925 has been embodied.

REASONS:

During fatigue tests performed for the A330/A340 program, a crack was found on frame FR73A inner flange between beams 5 and 6.

Frames FR73A of A330/A340 aircraft are identical to the frames installed on the A310 and A300-600 aircraft on which AIRBUS serial modification No. 06925 has been embodied.

The propagation of such crack on the full width of the inner flange, and extending into frame FR73A web, could affect the structural integrity of the airframe.

The purpose of Revision 1 of this Airworthiness Directive (AD) specifies the Applicability paragraph.

COMPLIANCE:

Before accumulation of 18,000 flight cycles or within 3,000 flight cycles following the effective date of this AD at original issue, whichever occurs later, perform a High Frequency Eddy Current inspection (HFEC) of the inner flange of frame FR73A between beams 5 and 7, in accordance with the instructions of AIRBUS INDUSTRIE Service Bulletins (SB) A310-53-2107 or A300-53-6116.

Depending on the findings of the above mentioned inspection, perform the necessary repairs before the next flight and repeat the inspections at the intervals and in accordance with the instructions defined in SB A310-53-2107 or A300-53-6116.

All findings have to be reported to AIRBUS.

REF.: AIRBUS INDUSTRIE Service Bulletins

A310-53-2107

A300-53-6116

(Any later approved revision of these SB is acceptable).

This Revision 1 replaces original AD 1999-013-276(B) issued on January 13, 1999.

EFFECTIVE DATES:

Original AD: JANUARY 23, 1999

Revision 1: JUNE 08, 2002