Airworthiness Directive · Amendment 39-21950 · Fire protection
Airbus SAS Airplanes
This AD applies to the Airbus SAS airplanes identified in paragraphs (c)(1) through (4) of this AD, certificated in any category, equipped with any parts manufacturer approval (PMA) part approved for the type design forward and aft cargo compartment door seal part number (P/N) D5237106020400, including but not limited to PMA P/N D5237106020400S.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, -133, -151N, -153N, and -171N airplanes.
(3) Model A320-211, -212, -214, -215, -216, -231, -232, -233, -251N, -252N, -253N, -271N, -272N, and -273N airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, -232, -251N, -251NX, -252N, -252NX, -253N, -253NX, -271N, -271NX, -272N, and -272NX airplanes.
The FAA is superseding Airworthiness Directive (AD) 2020-16- 01, which applied to all Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2020-16-01 required repetitive cleaning and greasing of affected cargo door seals (both original equipment manufacturer (OEM) and parts manufacturer approval (PMA) parts). This AD was prompted by reports of low halon concentration in the forward and aft cargo compartments due to air leakage through cargo compartment door seals, and the FAA's determination that improved cargo door seals must be installed and that certain flight operations must be limited until the improved cargo door seals are installed. This AD retains certain actions required by AD 2020-16-01 and requires replacing certain forward and aft cargo compartment door seals with new seals and installing a placard on the cargo compartment doors; and for certain airplanes, revising the existing airplane flight manual (AFM) to implement an operational limitation for certain routes. The FAA is issuing this AD to address the unsafe condition on these products.
For the purposes of this AD, a “PMA part” is defined as any PMA part approved for the type design forward and aft cargo compartment door seal P/N D5237106020400, including but not limited to PMA P/N D5237106020400S.
This paragraph restates the requirements of paragraph (g) of AD 2020-16-01, with revised compliance language. Within 6 months after the airplane date of manufacture, or 3 months after August 19, 2020 (the effective date of AD 2020-16-01), whichever occurs later, and, thereafter, at intervals not exceeding 6 months, clean and grease each PMA part, in accordance with the instructions specified in paragraph (1) or (2) of European Union Aviation Safety Agency (EASA) AD 2021-0049, dated February 18, 2021. Accomplishing the actions required by paragraph (i) of this AD on an airplane terminates the actions required by this paragraph for that airplane only, and for the specific cargo door locations with PMA parts only.
Within 96 months after the effective date of this AD, replace the seals of the PMA part with new seals and install a placard on the cargo compartment doors, in accordance with the method specified in paragraph (i)(1) or (2) of this AD. Accomplishing the actions required by this paragraph terminates the actions required by paragraph (h) of this AD for that airplane only, and for the specific cargo door locations where PMA parts were replaced only.
(1) Do the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1195, Revision 01, dated December 15, 2020, or Airbus Service Bulletin A320-52-1196, dated October 12, 2020, as applicable, except where the procedures refer to P/N D5237106020400, those procedures must be used for the PMA part.
(2) Do the actions in accordance with the procedures specified in paragraph (m)(1) of this AD.
For Model A319 airplanes on which Airbus mod 26402, mod 34881 or mod 34882 has been embodied in production, or Airbus Service Bulletin A320-26-1066 or Airbus Service Bulletin A320-26-1076 has been embodied in service: Within 9 months or 1,600 flight hours after the effective date of this AD, whichever occurs later, revise the Limitations section of the existing AFM to incorporate the information specified in Figure 1 to paragraph (j) of this AD. This may be done by inserting a copy of figure 1 to paragraph (j) of this AD into the Limitations Section of the existing AFM. Accomplishing the modification required by paragraph (i) of this AD terminates the requirements of this paragraph, and after the modification has been done, the AFM limitation required by this paragraph must be removed from the existing AFM before further flight after the modification.
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.
