Airworthiness Directive · Amendment 39-19185 · Fuselage
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2022-22-04. Comply with the one in force.
This AD applies to Airbus Model A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, 231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes; certificated in any category; all manufacturer serial numbers, except airplanes specified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD.
(1) Airplanes on which Airbus modification (Mod) 157039 has been embodied in production.
(2) Model A319 series airplanes on which Mod 28238, Mod 28162, and Mod 28342 have been embodied in production.
(3) Model A318 series airplanes on which Mod 39195 has been embodied in production or Airbus Service Bulletin A320-00-1219 has been embodied in service.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 series airplanes; Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by reports of fatigue damage in the structure for the door stop fittings on certain fuselage frames (FR). This AD requires repetitive rototest inspections for cracking of the fastener holes in certain door stop fittings, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
Within the applicable compliance times specified in table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD: Do a rototest inspection of all holes below each door stop fitting at fuselage FR66 and FR68, both left-hand (LH) and right-hand (RH) sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016; or using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Repeat the inspections thereafter at the applicable compliance times specified in table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD, until the modification specified in paragraph (i) of this AD is done. Where the “Threshold” column of table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD, specifies compliance times in “FC” (flight cycles), those compliance times are total flight cycles since the first flight of the airplane.
Inspections accomplished as specified in ALI task 534129 or task 534130 before the effective date of this AD are acceptable for compliance with the initial inspection required by paragraph (g) of this AD. As of 30 days after the effective date of this AD, repetitive inspections must be continued as required by paragraph (g) of this AD.
For airplanes on which no cracks were detected during any rototest inspection required by paragraph (g) of this AD: Modifying the affected area by cold working the fastener holes before further flight after no cracks were detected, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1290, Revision 01, dated October 3, 2016, terminates the repetitive inspections required by paragraph (g) of this AD for the modified area only.
For airplanes on which the modification specified in paragraph (i) of this AD has been done: At the compliance time specified in paragraphs (j)(1), (j)(2), or (j)(3) of this AD, as applicable, accomplish a rototest inspection of all holes at the door stop fitting locations at fuselage FR66 and FR68, both LH and RH sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016; or using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Repeat the inspection thereafter at intervals not to exceed the applicable compliance times specified in table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD.
(1) For airplanes with less than 1,800 flight cycles accumulated since first flight of the airplane at the time of accomplishing the modification specified in paragraph (i) of this AD: At the applicable initial compliance time specified in table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD.
(2) For airplanes with 1,800 flight cycles or more and less than 13,800 flight cycles accumulated since first flight of the airplane at the time of accomplishing the modification specified in paragraph (i) of this AD: Before the accumulation of 48,000 flight cycles since first flight of the airplane.
(3) For airplanes with 13,800 flight cycles or more accumulated since first flight of the airplane at the time of accomplishing the modification specified in paragraph (i) of this AD: Before the accumulation of 60,000 flight cycles since first flight of the airplane.
If, during any inspection required by paragraph (g) or (j) of this AD, any crack is detected, before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. Repair of an airplane as required by this paragraph does not constitute terminating action for the repetitive inspections required by paragraph (g) or (j) of this AD for that airplane, unless specified otherwise in instructions obtained using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA.
For an airplane that has been inspected as specified in ALI task 534129 or task 534130 and repaired before the effective date of this AD as specified in the applicable structural repair manual (SRM) or as specified in an Airbus repair design approval sheet (RDAS): Comply with the requirements of paragraphs (l)(1) and (l)(2) of this AD.
(1) For all fastener holes where no damage or cracks were detected (i.e., those not repaired), accomplish the actions required by paragraph (g) of this AD, unless the terminating action specified in paragraph (m) of this AD has been done.
(2) For all repaired fastener holes: Within 30 days after the effective date of this AD, or within a compliance time approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA, whichever occurs later, contact the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA; for inspection instructions and applicable corrective actions, and do the inspections and applicable corrective actions accordingly.
For airplanes that have been inspected, as specified in ALI task 534129 or task 534130, and repaired before the effective date of this AD, as specified in the applicable SRM, or as specified in an Airbus RDAS: Modification of the four fastener holes at door stop locations where no damage or crack was detected (i.e., door stop locations not repaired) by cold working holes before further flight after no cracks were detected, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1290, Revision 01, dated October 3, 2016, constitutes terminating action for the repetitive inspections of those four fastener holes at those door stop locations as required by paragraphs (g) or (l)(1) of this AD for that airplane.
For an airplane that has been repaired before the effective date of this AD in the areas described in this AD using an Airbus RDAS unrelated to ALI task 534129 or task 534130: Before exceeding the compliance times specified in paragraph (g) of this AD, contact the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA; for corrective action instructions and accomplish those instructions accordingly. Accomplishment of corrective action(s) on an airplane, as required by this paragraph, does not constitute terminating action for the repetitive inspections as required by paragraphs (g) or (j) of this AD for that airplane, as applicable, unless specified otherwise in the instructions.
(1) Accomplishment of inspections on an airplane, as required by paragraphs (g), (j), or (l) of this AD, as applicable, constitutes terminating action for the inspection requirements of ALI task 534129 or task 534130, as applicable, for that airplane.
(2) Modification of the four fastener holes at a door stop location of an airplane as specified in paragraphs (i) or (m) of this AD, as applicable, and subsequent initial inspection required by paragraph (j) of this AD, constitutes terminating action for the inspection requirements of ALI task 534129 or task 534130, as applicable, for those holes for that airplane. Subsequent repetitive inspections are required by paragraph (j) 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.
