Airworthiness Directive · Amendment 39-15406 · Airbus Model A318, A319, A320, and A321 Airplanes
Airbus Model A318, A319, A320, and A321 Airplanes
This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes on which Airbus Modification 26495 has been incorporated in production.
(2) All Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
The FAA is superseding an existing AD that applies to certain Airbus Model A318, A319, A320, and A321 airplanes. That AD currently requires repetitive detailed inspections of the inboard flap trunnions for any wear marks and of the sliding panels for any cracking at the long edges, and corrective actions if necessary. This new AD adds airplanes that were recently added to the type certificate data sheet and changes the inspection type. This AD results from reports of wear damage to the inboard flap trunnions after incorporation of the terminating modification. We are issuing this AD to detect and correct wear of the inboard flap trunnions, which could lead to loss of flap surface control and consequently result in the flap detaching from the airplane. A detached flap could result in damage to the tail of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
For Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, and -131 airplanes; except those on which Airbus Modification 26495 has been accomplished in production: Within 18 months after January 8, 2001 (the effective date of AD 2000-24-02, amendment 39-12009), modify the sliding panel driving mechanism of the flap drive trunnions, in accordance with Airbus Service Bulletin A320-27-1117, Revision 02, dated January 18, 2000; or Revision 04, dated November 6, 2001. As of the effective date of this AD, only Revision 04 may be used.
Note 1: Accomplishment of the modification required by paragraph (f) of this AD before January 8, 2001, in accordance with Airbus Service Bulletin A320-27-1117, dated July 31, 1997; or Revision 01, dated June 25, 1999; is acceptable for compliance with that paragraph.
For Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, and -131 airplanes: At the latest of the applicable times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, do a detailed inspection of the inboard flap trunnions for any wear marks and of the sliding panels for any cracking at the long edges, and do any corrective actions, as applicable, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A320-57-1133, dated July 28, 2005; Revision 01, dated August 7, 2006; or Revision 03, dated July 3, 2007, except as provided by paragraph (n) of this AD. As of the effective date of this AD, only Revision 03 may be used. Any corrective actions must be done at the compliance times specified in Figures 5 and 6, as applicable, of the service bulletin; except as provided by paragraphs (k), (l), and (m) of this AD. Repeat the inspection thereafter at intervals not to exceed 4,000 flight hours until the inspection required by paragraph (h) of this AD is done.
Note 2: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”
(1) Before accumulating 4,000 total flight hours on the inboard flap trunnion since new.
(2) Within 4,000 flight hours after accomplishing paragraph (f) of this AD.
(3) Within 600 flight hours after March 24, 2006 (the effective date of AD 2006-04-06).
For all airplanes: At the time specified in paragraph (h)(1) or (h)(2) of this AD, as applicable, do a general visual inspection of the inboard flap trunnions for any wear marks and of the sliding panels for any cracking at the long edges, and do all applicable corrective actions by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A320-57-1133, Revision 03, dated July 3, 2007; except as provided by paragraphs (i) and (o) of this AD. All corrective actions must be done at the compliance times specified in Figures 5 and 6, as applicable, of the service bulletin; except as provided by paragraphs (l), (m), and (n) of this AD. Repeat the inspection thereafter at intervals not to exceed 4,000 flight hours. Accomplishing the general visual inspection required by this paragraph terminates the detailed inspection requirement of paragraph (g) of this AD.
Note 3: For the purposes of this AD, a general visual inspection is: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.”
(1) For airplanes on which the detailed inspection required by paragraph (g) of this AD has been done before the effective date of this AD: Inspect before accumulating 4,000 total flight hours on the inboard flap trunnion since new, or within 4,000 flight hours after accomplishing the most recent inspection required by paragraph (g) of this AD, whichever occurs later.
(2) For airplanes other than those identified in paragraph (h)(1) of this AD: Inspect at the latest of the applicable times specified in paragraphs (h)(2)(i), (h)(2)(ii), and (h)(2)(iii) of this AD.
(i) Before accumulating 4,000 total flight hours on the inboard flap trunnion since new.
(ii) Within 4,000 flight hours after accomplishing paragraph (f) of this AD.
(iii) Within 600 flight hours after the effective date of this AD.
(i) Where Airbus Service Bulletin A320-57-1133, Revision 03, dated July 3, 2007, specifies to contact the manufacturer for instructions on how to repair certain conditions: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent), or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent).
Accomplishing the modification required by paragraph (f) of this AD before the effective date of this AD, in accordance with Airbus Service Bulletin A320-27-1117, Revision 03, dated August 24, 2001, is acceptable for compliance with the requirements of that paragraph.
(k) Accomplishing the inspections and corrective actions required by paragraphs (g) and (h) of this AD before the effective date of this AD, in accordance with Airbus Service Bulletin A320-57-1133, dated July 28, 2005; Revision 01, dated August 7, 2006; or Revision 02, dated December 12, 2006; is acceptable for compliance with the requirements of that paragraph.
Where Airbus Service Bulletin A320-57-1133, Revision 03, dated July 3, 2007, specifies replacing the sliding panel at the next opportunity if damaged, replace it within 600 flight hours after the inspection required by paragraph (g) or (h) of this AD, as applicable.
(m) If any damage to the trunnion is found during any inspection required by paragraph (g) or (h) of this AD, before further flight, do the corrective actions specified in Airbus Service Bulletin A320-57-1133, Revision 03, dated July 3, 2007.
Where Airbus Service Bulletin A320-57-1133, Revision 03, dated July 3, 2007, specifies contacting the manufacturer for a grace period assessment after replacing the trunnion or flap, contact the Manager, International Branch, ANM-116; or the Direction Générale de l'Aviation Civile (or its delegated agent) for the grace period assessment.
Although Airbus Service Bulletin A320-57-1133, Revision 03, dated July 3, 2007, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
For Model A321-211 and -231 airplanes that have not been modified in accordance with Airbus Modification 26495, or on which the actions specified in Airbus Service Bulletin A320-27-1117, Revision 04, dated November 6, 2001, have not been done as of the effective date of this AD: Do the inspections specified in Airbus Service Bulletin A320-27-1108, Revision 04, dated November 22, 1999; at the applicable time specified in paragraph 1.E., “Compliance” of the service bulletin; except, where the service bulletin specifies a compliance time after the date of French airworthiness directive 96-271-092(B), this AD requires compliance within the specified compliance time after the effective date of this AD. Do all applicable corrective actions before further flight. Do the actions in accordance with the Accomplishment Instructions of the service bulletin.
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.
