Airworthiness Directive · Amendment 39-15069 · Airbus Model A310 Series Airplanes
Airbus Model A310 Series Airplanes
This AD applies to Airbus Model A310 series airplanes; certificated in any category; excluding those airplanes on which Airbus Modifications 5068, 7201, and 7298 have been incorporated in production.
The FAA is superseding an existing airworthiness directive (AD) that applies to all Airbus Model A310 series airplanes. That AD currently requires inspections of the lower door surrounding structure to detect cracks and corrosion; inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair if necessary. That AD also currently provides for optional terminating action for certain inspections. This new AD retains all requirements of the existing AD, mandates the previously optional terminating action, and reduces the applicability of the existing AD. This AD results from a determination that further rulemaking is necessary to improve the fatigue behavior of the cabin door surroundings. We are issuing this AD to prevent corrosion between the scuff plates at exit and cargo doors and fatigue cracks originating from certain fastener holes located in adjacent structure, which could result in reduced structural integrity of the door surroundings.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Perform an initial inspection of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door to detect cracks and corrosion, in accordance with Airbus Service Bulletin A310-53-2030, Revision 5, dated March 6, 1991, at the applicable time specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD. If any crack or corrosion is found during this inspection, prior to further flight, repair in accordance with the service bulletin. Accomplishment of this inspection is not required for the aft passenger/crew doors if a steel doubler that covers the entire inspection area is installed.
(1) For any door on which Modification 5382 and Modification 5382D4741 for all other doors have been accomplished: Perform the initial inspection within 9 years since airplane manufacture, or within 1 year after September 4, 1998 (the effective date of AD 98-16-06), whichever occurs later.
(2) For any door on which Modification 5382 and Modification 5382D4741 for all other doors have not been accomplished, and on which the procedures described in Airbus Service Bulletin A310-53-2004, Revision 2, dated June 17, 1985; or Airbus Service Information Letter 53-033, Revision 2, dated November 23, 1984; have been accomplished: Perform the initial inspection within 5 years since airplane manufacture, or within 1 year after September 4, 1998, whichever occurs later.
(3) For any door on which Modification 5382 and Modification 5382D4741 for all other doors have not been accomplished, and on which the procedures described in Airbus Service Bulletin A310-53-2004, Revision 2, dated June 17, 1985; or Airbus Service Information Letter 53-033, Revision 2, dated November 23, 1984; have not been accomplished: Perform the initial inspection within 4 years since airplane manufacture, or within 1 year after September 4, 1998, whichever occurs later.
Perform repetitive inspections of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door to detect cracks and corrosion, in accordance with Airbus Service Bulletin A310-53-2041, Revision 02, dated July 2, 1996, at the applicable times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. Accomplishment of these inspections is not required for the aft passenger/crew doors if a steel doubler that covers the entire inspection area is installed.
(1) For the forward passenger/crew doors, the bulk cargo door, and the aft passenger/crew doors, except the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler, on all Model A310-200 and -300 series airplanes: Perform the first inspection within 5 years after accomplishing the inspection required by paragraph (f) of this AD; and repeat the inspection thereafter at intervals not to exceed 5 years.
(2) For the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler of the aft passenger/crew door on all Model A310-200 series airplanes: Perform the first inspection within 5 years or 12,000 landings after accomplishing the inspection required by paragraph (f) of this AD, whichever occurs first; and repeat the inspection thereafter at intervals not to exceed 5 years or 12,000 landings, whichever occurs first.
(3) For the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler of the aft passenger/crew door on all Model A310-300 series airplanes: Perform the first inspection within 5 years or 7,000 landings after accomplishing the inspection required by paragraph (f) of this AD, whichever occurs first; and repeat the inspection thereafter at intervals not to exceed 5 years or 7,000 landings, whichever occurs first.
If any crack is found during any inspection required by paragraph (g) or (n) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A310-53-2041, Revision 02, dated July 2, 1996. Thereafter, perform the repetitive inspections required by paragraph (g) of this AD at the applicable times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
(i) If any corrosion is found during any inspection required by paragraph (g) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A310-53-2041, Revision 02, dated July 2, 1996. Thereafter, perform the repetitive inspections required by paragraph (g) of this AD at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD.
(1) For Model A310-200 series airplanes: Inspect at intervals not to exceed 5 years or 9,600 landings, whichever occurs first.
(2) For Model A310-300 series airplanes: Inspect at intervals not to exceed 5 years or 5,600 landings, whichever occurs first.
(j) Accomplishment of the actions required by paragraph (g), (h), or (i) of this AD in accordance with Airbus Service Bulletin A310-53-2041, dated December 5, 1990; or Revision 01, dated March 6, 1991; prior to September 4, 1998, is acceptable for compliance with that paragraph.
Perform an inspection to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the left- and right-hand forward, mid, and aft passenger/crew door structures, in accordance with Airbus Service Bulletin A310-53-2037, Revision 1, dated April 29, 1992, and at the applicable times specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD.
(1) For the upper corners of the forward doors: Inspect prior to the accumulation of 20,000 total landings, or within 2,000 landings after September 4, 1998, whichever occurs later.
(2) For the lower corners of the forward doors: Inspect prior to the accumulation of 20,000 total landings, or within 4,000 landings after September 4, 1998, whichever occurs later.
(3) For the upper and lower corners of the aft doors, and for the parts underneath the corners of the upper door frames: Inspect prior to the accumulation of 20,000 total landings, or within 4,000 landings after September 4, 1998, whichever occurs later.
Repeat the inspections required by paragraph (k) of this AD at the applicable times specified in paragraphs (l)(1), (l)(2), (l)(3), (l)(4), and (l)(5).
(1) For the upper corners of the forward doors: Inspect at intervals not to exceed 6,000 landings.
(2) For the lower corners of the forward doors: Inspect at intervals not to exceed 10,000 landings.
(3) For the upper and lower corners of the aft doors on which an inspection required by paragraph (k) of this AD was accomplished using a ROTO test technique: Inspect at intervals not to exceed 8,000 landings.
(4) For the upper and lower corners of the aft doors on which an inspection required by paragraph (k) of this AD was accomplished using an x-ray technique: Inspect at intervals not to exceed 3,500 landings.
(5) For the areas around the fasteners in the vicinity of stringer 12 on the upper door frames of the aft doors on which an inspection required by paragraph (k) of this AD was accomplished using a visual technique: Inspect at intervals not to exceed 6,900 landings.
If any crack is found during any inspection required by paragraph (k) or (l) of this AD: Prior to further flight, accomplish the requirement of paragraph (m)(1) or (m)(2) of this AD, as applicable.
(1) If any crack is found, and the crack can be eliminated using the method specified in Airbus Service Bulletin A310-53-2037, Revision 1, dated April 29, 1992; or Revision 02, dated November 27, 2000: Prior to further flight, repair the crack in accordance with that service bulletin.
(2) If any crack is found, and the crack cannot be eliminated using the method specified in Airbus Service Bulletin A310-53-2037, Revision 1, dated April 29, 1992; or Revision 02, dated November 27, 2000: Prior to further flight, repair the crack in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate.
As of the effective date of this AD, use only the service bulletins specified in Table 1 of this AD.
| Do the action(s) required by— | In accordance with the accomplishment instructions of Airbus Service Bulletin— |
|---|---|
| (1) Paragraph (f) of this AD | A310-53-2030, Revision 06, dated July 2, 1996. |
| (2) Paragraph (k) and (m)(1) of this AD | A310-53-2037, Revision 03, excluding Appendix 01, dated July 26, 2006. |
Modify the passenger/crew door structures in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2017, Revision 09, dated May 17, 2004. Do the modification at the applicable time in paragraph (o)(1) or (o)(2) of Table 2 of this AD. Accomplishment of this modification constitutes terminating action for the repetitive inspections required by paragraph (l) of this AD. The inspections required by paragraph (f) of this AD must be done before accomplishing this modification.
| For model— | Compliance time |
|---|---|
| (1) A310-203, -204, -221, and -222 airplanes | Before the accumulation of 40,000 flight cycles since the date of issuance of the original French standard Airworthiness Certificate or the date of issuance of the original French Export Certificate of Airworthiness, or during the next inspection required by paragraph (l) of this AD, whichever occurs later. |
| (2) A310-304, -322, -324, and -325 airplanes | Before the accumulation of 35,000 flight cycles since the date of issuance of the original French standard Airworthiness Certificate or the date of issuance of the original French Export Certificate of Airworthiness, or during the next inspection required by paragraph (l) of this AD, whichever occurs later. |
Actions done before the effective date of this AD in accordance with the service bulletins identified in Table 3 of this AD are acceptable for compliance with the corresponding requirements of this AD.
| Airbus Service Bulletin | Revision level | Date |
|---|---|---|
| (1) A310-53-2017 | 07 | February 25, 1992. |
| (2) A310-53-2017 | 08 | September 7, 2000. |
| (3) A310-53-2037 | 02 | November 27, 2000. |
