Airworthiness Directive · Amendment 39-18955 · Airborne auxiliary power
Airbus Airplanes
This AD applies to Airbus airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, all manufacturer serial numbers, certificated in any category.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
We are superseding Airworthiness Directive (AD) 2007-13-08, for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2007-13-08 required repetitive inspections of the auxiliary power unit (APU) starter motor, APU inlet plenum, and APU air intake for discrepancies; repetitive cleaning of the APU air intake; and applicable corrective actions. This AD expands the applicability of AD 2007-13-08, and includes an optional terminating installation for the repetitive actions. This AD was prompted by a determination that the unsafe condition could occur on additional airplanes. We are issuing this AD to address the unsafe condition on these products.
Except as provided by paragraph (i) of this AD, within 600 flight hours after July 25, 2007 (the effective date of AD 2007-13-08), or within 60 days after the effective date of this AD, whichever occurs later: Inspect the APU starter motor, APU air inlet plenum, and APU air intake of each affected APU identified in table 1 to paragraphs (g), (h), (i)(2)(ii), (j), and (k) of this AD for discrepancies; and do all applicable corrective actions before further flight; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-49-1068, Revision 01, dated February 2, 2006. Repeat the inspection thereafter at intervals not to exceed 600 flight hours.
| APU | ECB part Nos. (P/N) |
|---|---|
| APIC APS 3200 | 4500003D, 4500003E, 4500003F, 4500003G, 4500003H, or 4500003J. |
| Honeywell 131-9A | 3888394-120201, 3888394-121202, 3888394-121203, 3888394-221202, or 3888394-221203. |
| Honeywell GTCP36-300 | 307950-1, 307950-2, 307950-3, 307950-4, 304640-1, 304640-2, 304640-3, 304640-4, 304817-1, 304817-2, or 3888394-230300. |
Except as provided by paragraph (i) of this AD, prior to the accumulation of 2,400 flight hours since first flight of the airplane, or within 600 flight hours after July 25, 2007 (the effective date of AD 2007-13-08), or within 60 days after the effective date of this AD, whichever occurs latest, unless accomplished previously in accordance with Airbus Service Bulletin A320-49-1098, dated June 21, 2011: Clean the APU air intake of each affected APU identified in table 1 to paragraphs (g), (h), (i)(2)(ii), (j), and (k) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-49-1068, Revision 01, dated February 2, 2006. Repeat the cleaning task thereafter at intervals not to exceed 2,400 flight hours.
(1) For airplanes equipped with an APU and associated ECB part number identified in table 2 to paragraphs (i)(1), (i)(2)(ii), and (j) of this AD, the actions specified in paragraphs (g) and (h) of this AD are not required.
| APU | ECB Part Nos. (P/N) |
|---|---|
| APIC APS 3200 | 4500003K, 4500003L, or 4500003M. |
| Honeywell 131-9A | 3888394-121204, 3888394-121205, 3888394-221204, 3888394-221205, or 3888394-321206. |
| Honeywell GTCP36-300 | 304640-5, 304817-3, or 3888394-230301. |
(2) For airplanes on which Airbus Modification 35803, 35936, 152289, 152645, 155015, or 157848 has been embodied in production, the actions specified in paragraphs (g) and (h) of this AD are not required provided that, within 30 days after the effective date of this AD, the applicable actions specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD are done.
(i) The part number of the installed ECB is identified.
(ii) Any affected ECB identified in table 1 to paragraphs (g), (h), (i)(2)(ii), (j), and (k) of this AD that is found to be installed is replaced with an ECB having a part number identified in table 2 to paragraphs (i)(1), (i)(2)(ii), and (j) of this AD, as applicable to the APU installed on the airplane; and the replacement is done in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (i)(2)(ii)(A), (i)(2)(ii)(B), (i)(2)(ii)(C), (i)(2)(ii)(D), (i)(2)(ii)(E), or (i)(2)(ii)(F) of this AD; or using a method 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).
(A) Airbus Service Bulletin A320-49-1070, dated July 28, 2006.
(B) Airbus Service Bulletin A320-49-1075, Revision 01, dated December 1, 2006.
(C) Airbus Service Bulletin A320-49-1077, Revision 04, dated February 27, 2013.
(D) Airbus Service Bulletin A320-49-1098, dated June 21, 2011.
(E) Airbus Service Bulletin A320-49-1102, dated January 3, 2012.
(F) Airbus Service Bulletin A320-49-1107, Revision 02, dated May 10, 2016.
(3) For airplanes on which an APU ECB having a part number approved after the effective date of this AD is installed, the actions specified in paragraphs (g) and (h) of this AD are not required, provided the conditions specified in paragraphs (i)(3)(i) and (i)(3)(ii) of this AD are met.
(i) The part number must be approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(ii) The installation must be accomplished in accordance with airplane modification instructions approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
Replacing an affected ECB identified in table 1 to paragraphs (g), (h), (i)(2)(ii), (j), and (k) of this AD with an ECB having a part number identified in table 2 to paragraphs (i)(1), (i)(2)(ii), and (j) of this AD, as applicable to the APU installed on the airplane, constitutes terminating action for the repetitive inspections required by paragraphs (g) and (h) of this AD. The replacement must be done in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (i)(2)(ii)(A), (i)(2)(ii)(B), (i)(2)(ii)(C), (i)(2)(ii)(D), (i)(2)(ii)(E), or (i)(2)(ii)(F) of this AD, or using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or 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.
