Airworthiness Directive · Amendment 39-16686 · Fuselage
Airbus Model A310-203, -204, -222, -304, -322, and -324 Airplanes
This AD applies to Model A310-203, -204, -222, -304, -322, and -324 airplanes, certificated in any category, all serial numbers, except airplanes on which Airbus modification 06146 has been done in production.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within the applicable time specified in Table 1 of this AD, do the inspections of the lower tail plane cut-out area in the tail cone specified in paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), and (g)(6) of this AD, as applicable, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008. Certain compliance times are applicable to short-range use (i.e., average flight time (AFT) equal to or less than 4 flight hours), or long-range use (i.e., AFT exceeding 4 flight hours). Inspection areas are specified in Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
Note 1: To establish the average flight time, take the accumulated flight time (counted from the take-off up to the landing) and divide by the number of accumulated flight cycles. This gives the average flight time per flight cycle.
| Airplanes | Inspection areas | Compliance time (whichever occurs later) | |
| Model A310-203, A310-204, and A310-222 airplanes | 1 and 2 | Prior to the accumulation of 18,000 total flight cycles or 36,000 total flight hours, whichever occurs first | Within 1,500 flight cycles or 3,000 flight hours, whichever occurs first, after the effective date of this AD. |
| Model A310-203, A310-204, and A310-222 airplanes | 3 | Prior to the accumulation of 24,000 total flight cycles or 48,000 total flight hours, whichever occurs first | Within 1,500 flight cycles or 3,000 flight hours, whichever occurs first, after the effective date of this AD. |
| Model A310-304, A310-322, and A310-324 short range airplanes | 1 and 2 | Prior to the accumulation of 12,000 total flight cycles or 33,750 total flight hours, whichever occurs first | Within 1,200 flight cycles or 3,300 flight hours, whichever occurs first, after the effective date of this AD. |
| Model A310-304, A310-322, and A310-324 short range airplanes | 3 | Prior to the accumulation of 18,000 total flight cycles or 50,500 total flight hours, whichever occurs first | Within 1,200 flight cycles or 3,300 flight hours, whichever occurs first, after the effective date of this AD. |
| Model A310-304, A310-322, and A310-324 long range airplanes | 1 and 2 | Prior to the accumulation of 7,500 total flight cycles or 37,500 total flight hours, whichever occurs first | Within 750 flight cycles or 3,750 flight hours, whichever occurs first, after the effective date of this AD. |
| Model A310-304, A310-322, and A310-324 long range airplanes | 3 | Prior to the accumulation of 11,250 total flight cycles or 56,000 total flight hours, whichever occurs first | Within 750 flight cycles or 3,750 flight hours, whichever occurs first, after the effective date of this AD. |
(1) For areas 1, 2, and 3: Do a detailed inspection for cracking and corrosion of the lower horizontal stabilizer cutout longeron, the corner fitting, the skin strap, and the skin, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(i) If any corrosion is found, before further flight, repair in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(ii) If any cracking is found, before further flight, contact Airbus for repair instructions and do the repair.
(2) For areas 1, 2, and 3 on which cracking is not found during the inspection required by paragraph (g)(1) of this AD: Do a detailed inspection for damaged sealant; and, if any damaged sealant is found, before further flight, replace the sealant; in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(3) For area 1: Do an eddy current inspection for cracking in area 1; and, if no cracking is found, before further flight, apply sealant and corrosion compound, as applicable; in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(i) If cracking is equal to or less than 2.0 mm (0.079 inch) long and not more than 2 cracks with a minimum distance of 50.0 mm (1.969 inch) between the cracks: Before further flight, remove any cracking and do an eddy current inspection for cracking of the reworked area, in accordance with the Accomplishment Instructions of the Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008. If no cracking is found, before further flight, shot peen the reworked area, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(A) If cracking is found and the radius of the rework is less than 20.0 mm (0.787 inch), before further flight, increase the radius and do an eddy current inspection for cracking of the reworked area, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008. If no cracking is found, before further flight, shot peen the reworked area, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(1) If any cracking is found in the outer skin, before further flight, contact Airbus for repair instructions and do the repair.
(2) If any cracking is found in the corner fitting and area 3 has not been cold expanded, before further flight, install new corner fitting, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008, and do the rotating probe inspection in area 3 specified in paragraph (g)(5) of this AD.
(3) If any cracking is found in the corner fitting and area 3 has been cold expanded, before further flight, do the eddy current inspection of the longeron and outer skin specified in paragraph (g)(6) of this AD.
(B) If cracking is found and the radius of the rework is 20.0 mm (0.787 inch) or more, before further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or the European Aviation Safety Agency (EASA) (or its delegated agent)
(ii) If cracking is greater than 2.0 mm (0.079 inch) long or there are more than 2 cracks; or if there are more than 2 cracks with less than a minimum distance of 50.0 mm (1.969 inch) between the cracks: Before further flight, remove the corner fitting, and do the applicable actions specified in paragraph (g)(3)(ii)(A) or (g)(3)(ii)(B) of this AD.
(A) If any cracking is found and area 3 has not been cold expanded, before further flight, install a new corner fitting, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008; and do the rotating probe inspection in area 3 specified in paragraph (g)(5) of this AD.
(B) If any cracking is found and area 3 has been cold expanded, before further flight, do the eddy current inspection of the longeron and outer skin specified in paragraph (g)(6) of this AD.
(4) For area 2: Do an eddy current inspection for cracking of area 2, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008. If any cracking is found, before further flight, contact Airbus for repair instructions and do the repair.
(5) For area 3: Do a rotating probe inspection for cracking of specified fastener holes in area 3, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(i) If no cracking is found, before further flight, drill or ream fastener holes, cold expand the fastener holes and countersinks, and wet install with sealant, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008; except where this service bulletin specifies to contact Airbus if the fastener diameter does not meet specifications or if the distance between the hole center and material edge is less than specifications, before further flight, contact Airbus for repair instructions and do the repair.
(ii) If cracking is found, before further flight, drill or ream fastener holes, and do a rotating probe inspection for cracking of the fastener holes in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(A) If no cracking is found, cold expand the fastener holes and countersinks, drill or ream fastener holes, and wet install with sealant, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008; except where this service bulletin specifies to contact Airbus if the fastener diameter does not meet specifications or if the distance between the hole center and material edge is less than the specifications, before further flight, contact Airbus for repair instructions and do the repair.
(B) If cracking is found, before further flight, contact Airbus for repair instructions and do the repair.
(6) For airplanes on which cracking is found in the corner fitting during any inspection required by paragraph (g)(3) of this AD and area 3 is cold-expanded: Do an eddy current inspection for cracking of the longeron and outer skin, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(i) If no cracking is found, before further flight, install a new corner fitting and do a rotating probe inspection for cracking of the fastener holes, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(A) If no cracking is found, before further flight, drill or ream fastener holes, cold expand the fastener holes and countersinks, and wet install with sealant, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(B) If cracking is found and the hole diameter is less than the maximum oversize specification, before further flight, drill or ream holes and do a rotating probe inspection for cracking of the fastener holes, in accordance with Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(1) If no cracking is found, cold expand the fastener holes and countersinks, and wet install with sealant, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(2) If cracking is found, before further flight, contact Airbus for repair instructions and do the repair.
(C) If cracking is found and the hole diameter is equal to or greater than the maximum oversize specification, before further flight, contact Airbus for repair instructions and do the repair.
(ii) If cracking is found, before further flight, contact Airbus for repair instructions and do the repair.
Repeat the inspections for area 1 required by paragraphs (g)(1) and (g)(3) of this AD thereafter at the applicable intervals specified in Table 2 of this AD. Certain compliance times are applicable to short-range use (AFT equal to or less than 4 flight hours), or long-range use (AFT exceeding 4 flight hours). Inspection areas are specified in Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
| Affected airplanes | Interval (not to exceed) |
|---|---|
| (1) Model A310-203, A310-204, and A310-222 airplanes that have accumulated less than 30,000 total flight cycles and 60,000 total flight hours, as of the effective date of this AD | 6,000 flight cycles or 12,000 flight hours, whichever occurs first, until the airplane accumulates 30,000 total flight cycles or 60,000 total flight hours; then perform the inspections within the interval specified in paragraph (h)(2) of this AD. |
| (2) Model A310-203, A310-204, and A310-222 airplanes that have accumulated 30,000 total flight cycles or more or 60,000 total flight hours or more, as of the effective date of this AD | 3,900 flight cycles or 7,800 flight hours, whichever occurs first. |
| (3) Model A310-304, A310-322 and A310-324 short range airplanes that have accumulated less than 24,000 total flight cycles and 67,500 total flight hours, as of the effective date of this AD | 4,800 flight cycles or 13,500 flight hours, whichever occurs first, until the airplane accumulates 24,000 total flight cycles or 67,500 total flight hours; then perform the inspections within the interval specified in paragraph (h)(4) of this AD. |
| (4) Model A310-304, A310-322 and A310-324 short range airplanes that have accumulated 24,000 total flight cycles or more or 67,500 total flight hours or more, as of the effective date of this AD | 3,100 flight cycles or 8,750 flight hours, whichever occurs first. |
| (5) Model A310-304, A310-322 and A310-324 long range airplanes that have accumulated less than 15,000 total flight cycles and 75,000 total flight hours, as of the effective date of this AD | 3,000 flight cycles or 15,000 flight hours, whichever occurs first, until the airplane accumulates 15,000 total flight cycles or 75,000 total flight hours; then perform the inspections within the interval specified in paragraph (h)(6) of this AD. |
| (6) Model A310-304, A310-322 and A310-324 long range airplanes that have accumulated 15,000 total flight cycles or more or 75,000 total flight hours or more, as of the effective date of this AD | 1,950 flight cycles or 9,750 flight hours, whichever occurs first. |
(i) Repeat the inspections for area 2 required by paragraphs (g)(1) and (g)(4) of this AD thereafter at the applicable intervals specified in Table 2 of this AD. Certain compliance times are applicable to short-range use (AFT equal to or less than 4 flight hours), or long-range use (AFT exceeding 4 flight hours). Inspection areas are specified in Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
Inspections accomplished before the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A310-53-2074, Revision 03, dated October 13, 2006, are considered acceptable for compliance with the corresponding action specified in this AD.
Note 2: This AD differs from the MCAI and/or service information as follows: The MCAI and service information do not specify a corrective action if cracking is found and the radius of the rework is 20.0 mm (0.787 inch) or more. Paragraph (g)(3)(i)(B) of this AD requires repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or EASA (or its delegated agent).
