Airworthiness Directive · Amendment 39-12009 · Airbus Model A319, A320, and A321 Series Airplanes
Airbus Model A319, A320, and A321 Series Airplanes
Superseded. A later AD replaced this one: AD 2006-04-06. Comply with the one in force.
Model A319, A320, and A321 series airplanes; certificated in any category; except airplanes on which Airbus Modification 26495 (reference Airbus Service Bulletin A320-27-1117) has been accomplished.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (g)(1) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that currently requires repetitive inspections to detect wear of the inboard flap trunnions, and to detect wear or debonding of the protective half-shells; and corrective actions, if necessary. This amendment requires accomplishment of the previously optional terminating action. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent chafing and resultant wear damage on the inboard flap drive trunnions or on the protective half-shells, which could result in failure of the trunnion primary load path; this would adversely affect the fatigue life of the secondary load path and could lead to loss of the flap.
To prevent chafing and resultant wear damage on the inboard flap drive trunnions or on the protective half-shells, which could result in failure of the trunnion primary load path, adversely affect the fatigue life of the secondary load path, and lead to loss of the flap, accomplish the following:
(a) For airplanes on which a protective half-shell has been installed over area 1 of the left or right inboard flap trunnion: Perform a detailed visual inspection of the protective half-shell (area 1) to detect wear or debonding, and perform a detailed visual inspection of the trunnion (area 2) to detect wear at the time specified in paragraph (a)(1), (a)(2), or (a)(3) of this AD, as applicable; in accordance with Airbus Service Bulletin A320-27-1108, Revision 01, dated July 15, 1997, Revision 02, dated April 17, 1998, or Revision 03, dated June 25, 1999.
(1) For Model A319 and Model A320 series airplanes on which Airbus Modification 22841 has been installed: Inspect prior to the accumulation of 2,500 flight hours after the incorporation of the modification, or within 500 flight hours after September 27, 1999 (the effective date of AD 99-17-11, amendment 39-11259), whichever occurs later.
(2) For Model A321 series airplanes on which Airbus Modification 23926 has been installed, or on which the repair specified in Airbus Service Bulletin A320-27-1097, dated October 5, 1996, or Revision 01, dated July 15, 1997, has been accomplished; and for Model A320 series airplanes on which the repair specified in Airbus Service Bulletin A320-27-1066, Revision 3, dated October 30, 1996, or Revision 4, dated July 15, 1997, has been accomplished: Inspect prior to the accumulation of 5,000 flight hours after incorporation of the repair or modification, or within 500 flight hours after September 27, 1999, whichever occurs later.
(3) For Airbus Model A320 series airplanes on which Airbus Modification 22881 (Airbus Service Bulletin A320-27-1050) has been accomplished, and on which Airbus Modification 22841 has not been accomplished: Inspect within 500 flight hours after the effective date of this new AD.
Note 2: Paragraph (a)(3) of AD 99-17-11 has been revised to correct the description of airplanes affected by that paragraph. Since such a revision could result in additional airplanes being affected, the compliance time has been restarted from the effective date of this AD to allow additional time to accomplish the actions required by that paragraph.
(b) For airplanes on which no protective half-shell is installed over area 1 of the left or right inboard flap trunnion: Within 500 flight hours after September 27, 1999, perform a detailed visual inspection of areas 1 and 2 of the inboard flap trunnion to detect wear on the trunnion, in accordance with Airbus Service Bulletin A320-27-1066, Revision 4, dated July 15, 1997 (for Model A320 series airplanes); or A320-27-1097, Revision 01, dated July 15, 1997, or Revision 02, dated June 25, 1999 (for Model A321 series airplanes).
(c) Except as provided by paragraph (d) of this AD: Following the accomplishment of any inspection required by either paragraph (a) or (b) of this AD, perform the follow-on repetitive inspections and/or corrective actions, as applicable, in accordance with Airbus Service Bulletin A320-27-1066, Revision 4, dated July 15, 1997 (for Model A320 series airplanes); A320-27-1097, Revision 01, dated July 15, 1997, or Revision 02, dated June 25, 1999 (for Model A321 series airplanes); or A320-27-1108, Revision 01, dated July 15, 1997, Revision 02, dated April 17, 1998, or Revision 03, dated June 25, 1999 (for Model A319, A320, and A321 series airplanes); as applicable; at the compliance times specified in the applicable service bulletin.
(d) If the applicable service bulletin specifies to contact Airbus for an appropriate action, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or the Direction Generale de l'Aviation Civile (or its delegated agent).
(e) As of the effective date of this new AD, the following service bulletin revisions must be used for accomplishment of the applicable actions required by paragraphs (a), (b), and (c) of this AD:
(1) Airbus Service Bulletin A320-27-1108, Revision 04, dated November 22, 1999.
(2) Airbus Service Bulletin A320-27-1066, Revision 5, dated June 25, 1999.
(f) Within 18 months after the effective date of this AD, 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. This modification constitutes terminating action for the repetitive inspections required by this AD.
Note 3: Accomplishment of the modification required by paragraph (f) of this AD prior to the effective date of this AD 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.
(g)(1) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116. Operators shall submit requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116.
(2) Alternative methods of compliance, approved previously in accordance with AD 99-17-11, amendment 39-11259, are approved as alternative methods of compliance with this AD.
Note 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.
