AIRWORTHINESS DIRECTIVE
CAA-AD-020/1999
Date of issue: February 25, 1999
AIRCRAFT - FUSELAGE - INSPECTION
Applicability: AIRBUS INDUSTRIE A310 and A300-600 aircraft, all certified models, all serial numbers, on which AIRBUS INDUSTRIE serial modification No. 06925 has been embodied.
Effective date: March 25, 1999
Compliance: Required as indicated in DGAC AD 1999-013-276(B).
Remarks: Where applicable, the requirements of this AD must be integrated into the Aircraft's Logbook(s). Address inquiries concerning this AD to: Civil Aviation Authority, Airworthiness Division, Ruzyně Airport, 160 08 Prague 6, Czech Repu
blic, tel.: 420 2 324086, fax: 420 2 364112.Ing. Pavel MATOUŠEK
Director of Airworthiness Division, CAA CZ
GSAC
AIRWORTHINESS DIRECTIVE
released by DIRECTION GENERALE DE L'AVIATION CIVILE
Inspection and/or modifications described below are mandatory. No person may operate a product to which this
Airworthiness Directive applies except in accordance with the requirements of this Airworthiness Directive.
Translation of `Consigne de Navigabilité' ref. : 1999-013-276(B)
In case of any difficulty, reference should be made to the French original issue.
AIRBUS INDUSTRIE
A310 and A300-600 Aircraft
Fuselage - Frame 73A at the level of the aft pax door (ATA 53)
APPLICABILITY:
AIRBUS INDUSTRIE A310 and A300-600 aircraft, all certified models, all serial numbers, on which
AIRBUS INDUSTRIE 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 INDUSTRIE 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.
ACTIONS:
Before accumulation of 18,000 flight cycles or within 3,000 flight cycles following the effective date of this Airworthiness Directive, 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 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 AIRBUS INDUSTRIE Service Bulletin A310-53-2107 or A300-53-6116.
All findings have to be reported to AIRBUS INDUSTRIE.
REFERENCES:
AIRBUS INDUSTRIE Service Bulletins
A310-53-2107
A300-53-6116
(at their original issue or any other later approved revision)
EFFECTIVE DATE: JANUARY 23 1999