AIRWORTHINESS DIRECTIVE
CAA-AD-T-047/2000
Date of issue: May 10, 2000
AIRCRAFT - AFT ENGINE MOUNT LINKS (ATA 71) - INSPECTION/REPLACEMENT
Applicability: AIRBUS INDUSTRIE A310 and A300-600 aircraft, all certified models and all serial numbers, equipped with General Electric CF6-80C2 engines, on which AIRBUS INDUSTRIE modification No. 12271 in production (AIRBUS INDUSTRIE Service Bulletin A310-71-2030 or A300-71-6025 in service) has not been embodied.
Effective date: Upon receipt
Compliance: Required as indicated in DGAC AD 2000-165-307(B).
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 ref.: 2000-165-307(B)
AIRBUS INDUSTRIE
A310 and A300-600 aircraft
RH and LH aft engine mount links on CF6-80C2 engines (ATA 71)1. APPLICABILITY:AIRBUS INDUSTRIE A310 and A300-600 aircraft, all certified models and all serial numbers, equipped with General Electric CF6-80C2 engines, on which AIRBUS INDUSTRIE modification No. 12271 in production (AIRBUS INDUSTRIE Service Bulletin A310-71-2030 or A300-71-6025 in service) has not been embodied.
2. REASON:
An operator reported a crack at the upper end of the LH link on the aft engine mount assembly of a CF6-80A3 engine during a scheduled engine removal (which could result in a failure of the mount itself, leading to engine pivoting or, in the worst case, its separation).
Subsequent analyses showed that the same phenomenon could affect the CF6-80C2 engine. Thus a non-repetitive inspection of the LH aft attachment of the CF6-80C2 engines was rendered mandatory by Airworthiness Directive 98-504-274(B), dated December 16,1998.
A thorough analysis of these events revealed that the premature initiation of structural fatigue cracks is due to bearing race migration, as well as internal bearing frictions.
It is thus necessary to introduce a program of repetitive inspections and extend the inspection zone to the RH engine mount.
3. ACTION:
3.1. Within 400 flights from the effective date of this Airworthiness Directive, unless already accomplished, take the actions of the General Electric Aircraft Engines Alert Service Bulletin CF6-80C2 72-A964, Revision 02 dated January 24, 2000.
3.2. Repeat the actions of paragraph 3.1. above at intervals not exceeding 400 flights or install new engine mount links, in accordance with the instructions of AIRBUS INDUSTRIE SB A310-71-2030 or A300-71-6025.
No further action is required in accordance with this AD, once AIRBUS INDUSTRIE SB A310-71-2030 or A300-71-6025 has been applied.
REF.:
General Electric Aircraft Engines Alert Service Bulletin
CF6-80C2 S/B 72-A964 revision 02 dated January 24, 2000
AIRBUS INDUSTRIE SB A310-71-2030 or A300-71-6025
(original issue or any later approved revision)
EFFECTIVE DATE: APRIL 29, 2000