Airworthiness Directive · Amendment 39-13805 · Airbus Model A320 Series Airplanes
Airbus Model A320 Series Airplanes
Superseded. A later AD replaced this one: AD 2016-08-13. Comply with the one in force.
Model A320 series airplanes, certificated in any category, except those modified in accordance with Airbus Modification 24591 (Airbus Service Bulletin A320-57-1089, dated December 22, 1996; Revision 01, dated April 17, 1997; Revision 02, dated November 6, 1998; or Revision 03, dated February 9, 2001).
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that currently requires modification of the rear spar web of the wing, cold expansion of certain attachment holes for the forward pintle fitting and certain holes at the actuating cylinder anchorage of the main landing gear (MLG), repetitive inspections for fatigue cracking in certain areas of the rear spar of the wing, and corrective action if necessary. That AD also provides for optional terminating action for the requirements of the AD. This amendment revises certain compliance times for the inspection. The actions specified by this AD are intended to detect and correct fatigue cracking, which may lead to reduced structural integrity of the wing and the MLG. This action is intended to address the identified unsafe condition.
To detect and correct fatigue cracking in certain areas of the rear spar of the wing, which may lead to reduced structural integrity of the wing and the main landing gear (MLG), accomplish the following:
(a) For airplanes having manufacturer's serial numbers (MSN) 003 through 008 inclusive, and 010 through 021 inclusive: Prior to the accumulation of 12,000 total flight cycles, or within 500 flight cycles after June 11, 1993 (the effective date of AD 93-08-15, amendment 39-8563), whichever occurs later, modify the inner rear spar web of the wing in accordance with Airbus Service Bulletin A320-57-1004, Revision 1, dated September 24, 1992; or Revision 2, dated June 14, 1993.
(b) For airplanes having MSNs 002 through 051 inclusive: Prior to the accumulation of 12,000 total flight cycles, or within 2,000 flight cycles after February 14, 1994 (the effective date of AD 93-25-13, amendment 39-8777), whichever occurs later, accomplish the requirements of paragraphs (b)(1) and (b)(2) of this AD in accordance with Airbus Service Bulletin A320-57-1060, dated December 8, 1992; or Revision 2, dated December 16, 1994.
(1) Perform a cold expansion of all the attachment holes for the forward pintle fitting of the MLG, except for the holes that are for taper-lok bolts.
(2) Perform a cold expansion of the holes at the actuating cylinder anchorage of the MLG.
Note 1: Accomplishment of the cold expansion in accordance with Airbus Service Bulletin A320-57-1060, Revision 1, dated April 26, 1993, is also acceptable for compliance with the requirements of paragraph (b) of this AD.
(c) Do an ultrasonic inspection for cracking of the rear spar of the wing, in accordance with Airbus Service Bulletin A320-57-1088, Revision 04, dated August 6, 2001. Inspect at the applicable time specified in paragraph 1.E. of the service bulletin, except as required by paragraphs (c)(1) and (c)(2) of this AD.
(1) For any airplane that has not been inspected but has exceeded the applicable specified compliance time in paragraph 1.E. of the service bulletin as of the effective date of this AD: Inspect within 18 months after the effective date of this AD.
(2) For any airplane that has been inspected before the effective date of this AD: Repeat the inspection within 3,600 flight cycles after the most recent inspection.
(d) An inspection done before the effective date of this AD in accordance with Airbus Service Bulletin A320-57-1088, Revision 02, dated July 29, 1999; or Revision 03, dated February 9, 2001; is acceptable for compliance with the requirements of the initial inspection required by paragraph (c) of this AD.
(e) Repeat the inspection required by paragraph (c) of this AD at intervals not to exceed 3,600 flight cycles or 6,700 flight hours, whichever occurs first, until the requirements of paragraph (g) have been done.
(f) If any crack is found during any inspection required by paragraph (c) or (e) of this AD: Before further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Ge ne rale de l'Aviation Civile (or its delegated agent).
(g) Modification of all specified fastener holes in the rear spar of the wing terminates the initial and repetitive inspections required by paragraphs (c) and (e) of this AD, if the modification is done in accordance with Airbus Service Bulletin A320-57-1089, Revision 02, dated November 6, 1998; or Revision 03, dated February 9, 2001. If done before the airplane accumulates 12,000 total flight cycles, the modification also terminates the actions required by paragraphs (a) and (b) of this AD.
(h) Unless otherwise specified in this AD, the actions must be done in accordance with the service bulletins listed in Table 1 of this AD.
| Service bulletin | Revision level | Date |
|---|---|---|
| Airbus Service Bulletin A320-57-1004 | 1 | September 24, 1992. |
| Airbus Service Bulletin A320-57-1004 | 2 | June 14, 1993. |
| Airbus Service Bulletin A320-57-1060 | Original | December 8, 1992. |
| Airbus Service Bulletin A320-57-1060 | 2 | December 16, 1994. |
| Airbus Service Bulletin A320-57-1088 | 04 | August 6, 2001. |
(1) The incorporation by reference of Airbus Service Bulletin A320-57-1088, Revision 04, dated August 6, 2001, is approved by the Director of the Federal Register as of November 5, 2004.
(2) The incorporation by reference of Airbus Service Bulletin A320-57-1004, Revision 2, dated June 14, 1993; and Airbus Service Bulletin A320-57-1060, Revision 2, dated December 16, 1994; was approved previously by the Director of the Federal Register as of June 30, 2000 (65 FR 34069, May 26, 2000).
(3) The incorporation by reference of Airbus Service Bulletin A320-57-1060, dated December 8, 1992, was approved previously by the Director of the Federal Register as of February 14, 1994 (59 FR 1903, January 13, 1994).
(4) The incorporation by reference of Airbus Service Bulletin A320-57-1004, Revision 1, dated September 24, 1992, was approved previously by the Director of the Federal Register as of June 11, 1993 (58 FR 27923, May 12, 1993).
(5) Copies may be obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Note 2: The subject of this AD is addressed in French airworthiness directive 2001-249(B), dated June 27, 2001.
