Applicability: A310 aircraft, all certified models.

Effective date: January 28, 1999

Compliance: Required as indicated in DGAC AD 92-106-132(B) R5.

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. : 92-106-132(B) R5
In case of any difficulty, reference should be made to the French original issue.

AIRBUS INDUSTRIE
A310 Aircraft
Structure fatigue

This Airworthiness Directive applies to AIRBUS INDUSTRIE A310 aircraft, all certified models.

In order to detect or prevent possible damage associated with a phenomenon of structural fatigue :

1. Perform the inspections and/or modifications defined in the following AIRBUS INDUSTRIE Service Bulletins, in accordance with the thresholds indicated in each of these Service Bulletins or within 1000 flights following the effective date of this Airworthiness Directive revision 3 (June 17, 1995), whichever occurs later.

1.1. S.B. A310-53-2014 Revision 5 and Change Notice 5B :
Fuselage - Center Section - Reinforce bottom joint angle fitting at FR40.

1.2. S.B. A310-53-2016 Revision 5 :
Fuselage - Center Section - FR47 and FR54 area - Provide local reinforcement.

1.3. S.B. A310-53-2054 Revision 2 :
Fuselage - Center Section - Inspect frame reinforcement angle runout of FR46 between STGR21 and 22 LH/RH.

1.4. S.B. A310-53-2057 Revision 1:
Fuselage - Center section - Inspection of the T-section connecting FR50A to the beam between FR50 and FR51 LH/RH.

1.5. S.B. A310-53-2059 Revision 1:
Fuselage - Inspect the lower side panel at the lap joint with the upper side panel at FR47 and STGR22, LH/RH.

1.6. S.B. A310-55-2002 Revision 4 :
Stabilizers - Horizontal stabilizer structure - Reinforcement of junction parts.

1.7. S.B. A310-55-2004 Revision 3 :
Stabilizers - Horizontal stabilizer structure - Inspection program after reinforcement as per Service Bulletin no A310-55-2002 embodiement.

1.8. S.B. A310-57-2002 Revision 2 :
Wings - Leading edge access panels landing - Lower skin - Inspection for cracks at bolt holes.

1.9. S.B. A310-57-2006 Revision 3 :
Wings - Holes around overwing refueling aperture at RIBS 13 -14, Inspection.

1.10 S.B. A310-57-2032 Revision 3 :
Wings - Upper skin forward of front spar - Inspection for cracks.

1.11 S.B. A310-57-2037 Revision 3 :
Wings - Bottom skin aft of rear spar inspection for cracks forward of the ailerons.

1.12 S.B. A310-57-2039 :
Wings - Center wing - Inspection of front spar web vertical posts.

1.13 S.B. A310-57-2046 Revision 6 :
Wings - Rear spar at selected bolt locations for attachment of MLG forward pick up fitting.

1.14 S.B. A310-57-2047' Revision 3 :
Wings - Center wing - Inspect rear spar internal angle and tee fitting.

1.15 S.B. A310-57-2050 and Change Notice OB :
Wings - Center wing box - Inspect treillis boom drain holes.

1.16 S.B. A310-53-2074 Revision 2 :
Fuselage - Tail cone - Inspect the lower horizontal-stabilizer cutout longeron, the corner fitting, the skin stap and the skin between FR87 and FR89 and between STGR24 and STGR27, LH and RH.

1.17 S.B. A310-57-2064 :
Fuselage - FR40 - Inspect upper corner fitting.

1.18 S.B. A310-57-2038 Revision 3 :
Wings - Stringer flanges at rib 14 wing bottom skin - Inspect for cracks.

NOTE 1:For paragraphs 1.1, 1.10, 1.11, 1.17, 1.18 comply with the instructions of above-mentioned Service Bulletins at the defined thresholds or within 1000 flight following the effective date of this Airworthiness Directive Revision 4, whichever occurs later.

2. Repeat the inspections defined in the Service Bulletins mentioned in paragraph 1/ above, in accordance with the intervals indicated in each of the Service Bulletins when applicable.

NOTE 2 : The thresholds and intervals which are established and valid for aircraft operated for an individual average airborne flight time of 96 minutes must be adjusted in accordance with the instructions given in the Service Bulletins quoted above.

Ref. : Following AIRBUS INDUSTRIE Service Bulletins, at the latest issue :

A310-53-2014, -2016, -2054, -2057, -2059, -2074,
A310-55-2002, -2004
A310-57-2002, -2006, -2032, -2037, -2038, -2039,
-2046, -2047, -2050, -2064.

This Revision 5 replaces Airworthiness Directive 92-106-132(B) R4 dated June 05, 1996.

Effective dates:
Original AD: May 09, 1992
Revision 1: May 09, 1992
Revision 2: January 28, 1995
Revision 3: June 17, 1995
Revision 4: June 15, 1996
Revision 5: November 28, 1998