Airworthiness Directive · Amendment 39-18489 · Wings
Airbus Airplanes
This AD applies to Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes, certificated in any category, all manufacturer serial numbers, except those on which Airbus modification (mod) 24591 has been embodied in production.
We are superseding Airworthiness Directive (AD) 2004-19-11 for certain Airbus Model A320 series airplanes. AD 2004-19-11 required modification of the inner rear spar web of the wing, cold expansion of the attachment holes of the forward pintle fitting and the actuating cylinder anchorage of the main landing gear (MLG), repetitive ultrasonic inspections for cracking of the rear spar of the wing, and corrective action if necessary. AD 2004-19-11 also provided optional terminating action for the repetitive inspections. This new AD retains the requirements of AD 2004-19-11, and requires the previously optional terminating action. This AD was prompted by a determination that the previously optional terminating action is necessary to address the unsafe condition. We are issuing this AD to prevent fatigue cracking of the inner rear spar, which may lead to reduced structural integrity of the wing and the MLG.
This paragraph restates the requirements of paragraph (a) of AD 2004-19-11, with a change to acceptable service information. For airplanes having manufacturer's serial numbers (MSNs) 003 through 008 inclusive, and 010 through 021 inclusive, except airplanes modified as specified in 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: 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 (58 FR 27923, May 12, 1993)), 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. As of the effective date of this AD, only Airbus Service Bulletin A320-57-1004, Revision 2, dated June 14, 1993, may be used for the actions required by this paragraph.
This paragraph restates the requirements of paragraph (b) of AD 2004-19-11, with a change to acceptable service information. For airplanes having MSNs 002 through 051 inclusive, except airplanes modified as specified in 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: 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 (59 FR 1903, January 13, 1994)), whichever occurs later, accomplish the requirements of paragraphs (h)(1) and (h)(2) of this AD in accordance with Airbus Service Bulletin A320-57-1060, dated December 8, 1992; Revision 1, dated April 26, 1993; or Revision 2, dated December 16, 1994. As of the effective date of this AD, only Airbus Service Bulletin A320-57-1060, Revision 2, dated December 16, 1994, may be used for the actions required by this paragraph.
(1) Perform a cold expansion of all the attachment holes for the forward pintle fitting of the main landing gear (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.
This paragraph restates the requirements of paragraphs (c), (d), and (e) of AD 2004-19-11, with no changes. Except for airplanes modified as specified in 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: Do the actions specified in paragraphs (i)(1) and (i)(2) of this AD.
(1) 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 Airbus Service Bulletin A320-57-1088, Revision 04, dated August 6, 2001, except as required by paragraphs (i)(1)(i) and (i)(1)(ii) of this AD.
(i) For any airplane that has not been inspected but has exceeded the applicable specified compliance time in paragraph 1.E. of Airbus Service Bulletin A320-57-1088, Revision 04, dated August 6, 2001, as of November 5, 2004 (the effective date of AD 2004-19-11): Inspect within 18 months after November 5, 2004.
(ii) For any airplane that has been inspected before November 5, 2004 (the effective date of AD 2004-19-11): Repeat the inspection within 3,600 flight cycles after the most recent inspection.
(2) Repeat the inspection required by paragraph (i)(1) 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 (k) of this AD have been done.
This paragraph restates the requirements of paragraph (f) of AD 2004-19-11, with specific delegation approval language. If any crack is found during any inspection required by paragraph (i)(1) or (i)(2) 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 Générale de l'Aviation Civile (or its delegated agent); or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Accomplishment of a repair as required by this paragraph does not constitute terminating action for the repetitive inspections required by paragraph (i)(2) of this AD.
Before exceeding 48,000 flight cycles or 96,000 flight hours, whichever occurs first since first flight of the airplane: Modify all specified fastener holes in the inner rear spar of the wing, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1089, Revision 03, dated February 9, 2001; except, where Airbus Service Bulletin A320-57-1089, Revision 03, dated February 9, 2001, specifies to contact Airbus for certain conditions, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. Modification of all specified fastener holes in the rear spar of the wing terminates the initial and repetitive inspections required by paragraphs (i)(1) and (i)(2) of this AD. If the modification is done both before the airplane accumulates 12,000 total flight cycles and before the effective date of this AD, the modification also terminates the actions required by paragraphs (g) and (h) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
