Airworthiness Directive · Amendment 39-19519 · Doors
Airbus SAS Airplanes
This AD applies to Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes; certificated in any category; manufacturer serial numbers through 0758 inclusive.
We are superseding Airworthiness Directive (AD) 2017-22-07, which applied to certain Airbus SAS 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. AD 2017- 22-07 required repetitive inspections of the frame forks, and corrective actions if necessary. AD 2017-22-07 also included optional modifications that constituted terminating action. This AD requires modifying certain forward and aft cargo compartment doors, and related investigative and corrective actions. This AD was prompted by an evaluation done by the design approval holder indicating that certain areas of certain cargo compartment doors are subject to widespread fatigue damage, and a determination was made that a modification of the frame forks must be done. We are issuing this AD to address the unsafe condition on these products.
This paragraph restates the definition in paragraph (g) of AD 2017-22-07, with no changes. For the purpose of this AD, an “affected door” is a forward or aft cargo compartment door, having any part number listed in table 1 to paragraph (g) of this AD, except a cargo compartment door on which Airbus Service Bulletin A320-52-1042 or Airbus Service Bulletin A320-52-1170 is embodied.
This paragraph restates the requirements of paragraph (h) of AD 2017-22-07, with no changes. At the latest of the compliance times listed in paragraphs (h)(1) through (h)(4) of this AD: Do a special detailed inspection of all frame forks in the beam 4 area of any affected door as defined in paragraph (g) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, except as specified in paragraphs (l) and (m) of this AD. Repeat the inspection thereafter at intervals not to exceed 3,000 flight cycles. A review of the airplane delivery or maintenance records is acceptable to identify any affected door installed on the airplane, provided that the cargo compartment door part number can be conclusively determined from that review.
(1) Before exceeding 37,500 flight cycles since first installation of the door on an airplane.
(2) Within 900 flight cycles after January 2, 2018 (the effective date of AD 2017-22-07), without exceeding 41,950 flight cycles since first installation of the door on an airplane.
(3) Within 50 flight cycles after January 2, 2018 (the effective date of AD 2017-22-07), for a door having reached or exceeded 41,900 flight cycles since first installation on an airplane.
(4) Within 3,000 flight cycles since the last inspection of the door as specified in Airbus Service Bulletin A320-52-1032.
This paragraph restates the requirements of paragraph (i) of AD 2017-22-07, with no changes. If any crack is found during any inspection required by paragraph (h) of this AD, before further flight, do all applicable corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, except as specified in paragraphs (l) and (m) of this AD. Accomplishment of applicable corrective actions does not constitute terminating action for the repetitive inspections.
Before the accumulation of 56,300 flight cycles, but not before the accumulation of 21,700 flight cycles since first installation of the affected door on an airplane: Modify all affected doors of an airplane, including accomplishment of all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1170, Revision 01, dated June 14, 2018. Accomplishing this modification constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD for that airplane, provided that, after modification, no affected door is re-installed on that airplane.
This paragraph restates the requirements of paragraph (j) of AD 2017-22-07, with changes related to compliance.
(1) Modification of all affected doors of an airplane before the effective date of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1042, Revision 2, dated January 14, 1997 (which is incorporated by reference in AD 2017-22-07 and is not incorporated in this AD), constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD and a method of compliance for the modification required by paragraph (j) of this AD, for that airplane, provided that, after modification, no affected door is re-installed on that airplane. For airplanes not previously modified before the effective date of this AD, the modification required by paragraph (j) of this AD must be done.
(2) Modification of all affected doors of an airplane including accomplishment of all applicable related investigative and corrective actions, if done before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1170, Revision 01, dated June 14, 2018, except as specified in paragraph (l) of this AD, constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD and a method of compliance for the modification required by paragraph (j) of this AD, for that airplane, provided that, after modification, no affected door is re-installed on that airplane. For airplanes not previously modified before the effective date of this AD, the modification required by paragraph (j) of this AD must be done.
(3) Modification of all affected doors on an airplane, in case of finding damaged frame forks, as specified in an Airbus Repair Design Approval Sheet (RDAS), if done before the effective date of this AD and done in accordance with a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS's EASA Design Organization Approval (DOA); constitutes terminating action for the repetitive inspection specified in paragraph (h) of this AD and a method of compliance for the modification required by paragraph (j) of this AD, for that airplane, provided that, after modification, no affected door is re-installed on that airplane. For airplanes not previously modified before the effective date of this AD, the modification required by paragraph (j) of this AD must be done.
This paragraph restates the requirements of paragraph (k) of AD 2017-22-07, with updated service information. Where Airbus Service Bulletin A320-52-1170, dated September 5, 2016; Airbus Service Bulletin A320-52-1170, Revision 01, dated June 14, 2018; or Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017; specifies to contact Airbus for appropriate action, and specifies that action as “RC” (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (q)(2) of this AD.
This paragraph restates the provision provided in paragraph (l) of AD 2017-22-07, with no changes. Although Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, specifies to submit certain information to the manufacturer, and specifies that action as “RC,” this AD does not include that requirement.
This paragraph restates the provisions specified in paragraph (m) of AD 2017-22-07, with no changes.
(1) This paragraph provides credit for the actions required by paragraphs (h) and (i) of this AD, if those actions were performed before January 2, 2018 (the effective date of AD 2017-22-07), using Airbus Service Bulletin A320-52-1171, dated October 29, 2015, provided that it can be conclusively determined that any part number D52371000018 was also inspected as specified in paragraph (h) of this AD.
(2) This paragraph provides credit for the actions required by paragraphs (h) and (i) of this AD, if those actions were performed before January 2, 2018 (the effective date of AD 2017-22-07), using Airbus Service Bulletin A320-52-1171, Revision 01, dated September 5, 2016.
(1) This paragraph provides credit for the actions required by paragraphs (j) and (k)(2) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-52-1170, dated September 5, 2016.
(2) This paragraph provides credit for the optional terminating modification specified in paragraph (k)(1) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-52-1042, Revision 2, dated January 14, 1997.
As of the effective date of this AD, no person may install, on any airplane, an affected door specified in paragraph (g) of this AD, unless less than 56,300 flight cycles have accumulated since first installation of the door on an airplane, and unless the door has been inspected in accordance with the requirements of paragraph (h) of this AD and all applicable corrective actions have been done in accordance with paragraph (i) 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.
