Airworthiness Directive · Amendment 39-18937 · Doors
Airbus Airplanes
This AD applies to the Airbus airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, all manufacturer serial numbers.
(1) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(2) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
(3) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
We are adopting a new airworthiness directive (AD) for all Airbus Model A319, A320, and A321 series airplanes. This AD was prompted by a report that a main landing gear (MLG) door could not be closed due to rupture of the actuator fitting. This AD requires repetitive inspections for cracking of the MLG door actuator fitting and its components, and corrective actions if necessary. This AD also requires eventual replacement of all affected MLG door actuator fittings with new monoblock fittings, which would terminate the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
For airplanes equipped with MLG door actuator fittings having part number (P/N) D52880224000 or P/N D52880224001 that were installed before the first flight of the airplane on MLG doors identified in paragraphs (g)(1) and (g)(2) of this AD: Within 500 flight hours since the most recent high frequency eddy current (HFEC) inspection done as specified in Airbus Service Bulletin A320-52A1086, Revision 01, dated September 10, 1999, or within 30 days after the effective date of this AD, whichever occurs later, perform an HFEC inspection for cracking of the MLG door fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52A1086, Revision 01, dated September 10, 1999. Repeat the inspection thereafter at intervals not to exceed 500 flight hours, except as provided by paragraphs (i), (j), and (k) of this AD.
(1) Left-hand MLG doors with serial numbers (S/Ns) 1206 through 1237 inclusive, 1239 through 1247 inclusive, and 1249 through 1251 inclusive.
(2) Right-hand MLG doors with S/Ns 1208 through 1239 inclusive, 1241 through 1249 inclusive, and 1251.
For airplanes equipped with MLG door actuator fittings having P/N D52880224000, P/N D52880224001, P/N D52880235000, or P/N D52880235001 that were installed before the first flight of the airplane on MLG doors identified in paragraphs (h)(1) and (h)(2) of this AD: Within 400 flight cycles after the effective date of this AD, or before the accumulation of 9,000 total flight cycles since first flight of the airplane, whichever occurs later, perform an HFEC inspection of both hinge and nerve areas of the MLG doors for cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1096, Revision 02, dated July 12, 2006. Repeat the inspection thereafter at intervals not to exceed 800 flight cycles, except as provided by paragraphs (i)(1), (j), and (k) of this AD.
(1) Left-hand MLG doors with S/Ns 1206 through 1510 inclusive, 1548, 1564, and 2000 through 2065 inclusive.
(2) Right-hand MLG doors with S/Ns 1208 through 1519 inclusive, 1551, and 2000 through 2065 inclusive.
(1) If any crack is found during any inspection required by paragraph (g) or (h) of this AD: Before further flight, replace the affected MLG door actuator fittings with new monoblock fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1073, Revision 05, dated September 28, 2006. Accomplishing this replacement terminates the repetitive inspections required by paragraphs (g) and (h) of this AD.
(2) If, during any HFEC inspection required by paragraph (g) of this AD, no crack is found: Before further flight, perform a low frequency eddy current (LFEC) inspection to determine the grain direction of the raw material of each MLG actuator fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52A1086, Revision 01, dated September 10, 1999.
(i) If the grain direction of the raw material is correct, the repetitive inspections required by paragraph (g) of this AD may be terminated.
(ii) If the grain direction of the raw material is incorrect, repeat the HFEC inspection required by paragraph (g) of this AD at the time specified in paragraph (g) of this AD. Replacement of the MLG door actuator fittings with new monoblock fittings as specified in paragraph (i)(1) of this AD terminates the repetitive inspections required by paragraphs (g) and (i)(2)(ii) of this AD.
For airplanes equipped with any MLG door actuator fitting having P/N D52880102000, P/N D52880102001, P/N D52880220000, P/N D52880220001, P/N D52880224000, P/N D52880224001, P/N D52880235000, or P/N D52880235001: At the later of the times specified in paragraphs (j)(1) and (j)(2) of this AD, replace the MLG door actuator fittings with new monoblock fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1073, Revision 05, dated September 28, 2006. Accomplishing this replacement terminates the repetitive inspections required by paragraphs (g) and (h) of this AD.
(1) Before the accumulation of 48,000 total flight cycles or 96,000 total flight hours on the MLG door, whichever occurs first.
(2) Within 30 days after the effective date of this AD.
Replacement of the MLG door actuator fittings with new monoblock fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1073, Revision 04, dated August 10, 1999; or Airbus Service Bulletin A320-52-1073, Revision 05, dated September 28, 2006; terminates the repetitive inspections required by paragraphs (g) and (h) of this AD.
(1) For airplanes on which Airbus Modification 24903, or Airbus Modification 25372, or Airbus Modification 36979 has been embodied in production, no action is required by this AD, provided that no MLG door actuator fitting having any part number identified in paragraph (j) of this AD has been reinstalled on the airplane since first flight; except the requirements of paragraph (m) of this AD remain applicable to post-mod 24903, post-mod 25372 and post-mod 36979 airplanes.
(2) Modification of an airplane by installing a version (P/N) of the MLG door actuator fitting approved after the effective date of this AD is acceptable for compliance with the requirements in paragraph (j) of this AD, provided the conditions specified in paragraphs (l)(2)(i) and (l)(2)(ii) are met.
(i) The MLG door actuator fitting (P/N) must be approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
(ii) The modification must be accomplished in accordance with instructions approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; EASA; or Airbus's EASA DOA.
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.
