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AD Notice of Proposed Rulemaking
 Federal Register Information
Header Information
Preamble Information
 Regulatory Information
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39-AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13 [Amended]
2. Section 39.13 is amended by removing amendment AD 39-10851 (63 FR 56542, October 22, 1998), and by adding a new airworthiness directive (AD), to read as follows:
Airbus: Docket 2002-NM-177-AD. Supersedes AD 98-22-05, Amendment 39-10851.
Applicability: Model A320 series airplanes, certificated in any category, on which Airbus Modification 22418 (reference Airbus Service Bulletin A320-57-1043) has not been done.
Compliance: Required as indicated, unless accomplished previously.
To prevent fatigue cracking of the lower surface panel on the wing center box, which could result in reduced structural integrity of the airplane, accomplish the following:
Restatement of Requirements of AD 98-22-05
Repetitive Inspections
(a) Except as provided by paragraph (e) of this AD: Prior to the accumulation of 20,000 total flight cycles, or within 60 days after November 27, 1998 (the effective date of AD 98-22-05, amendment 39-10851), whichever occurs later, perform a high frequency eddy current inspection to detect fatigue cracking of the lower surface panel on the wing center box, in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997, or Revision 03, dated April 30, 2002. Repeat the eddy current inspection thereafter at intervals not to exceed 7,500 flight cycles until the actions required by paragraph (c) of this AD are accomplished.
Repair
(b) Except as provided by paragraph (d) of this AD: If any cracking is detected during any inspection required by paragraph (a) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997, or Revision 03, dated April 30, 2002. Accomplishment of the repair constitutes terminating action for the repetitive inspections for the repaired area only.
Inspection/Modification/Repair
(c) Prior to the accumulation of 25,000 total flight cycles, or within 60 days after November 27, 1998, whichever occurs later: Perform a high frequency eddy current inspection to detect fatigue cracking of the lower surface panel on the wing center box, in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997, or Revision 03, dated April 30, 2002.
(1) If no cracking is detected: Prior to further flight, modify the lower surface panel on the wing center box, in accordance with Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997, or Revision 05, dated April 30, 2002. Accomplishment of the modification constitutes terminating action for the requirements of paragraph (a) of this AD.
(2) Except as provided by paragraph (d) of this AD, if any cracking is detected: Prior to further flight, repair in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997, or Revision 03, dated April 30, 2002; and modify any uncracked area in accordance with Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997, or Revision 05, dated April 30, 2002. Accomplishment of the repair of cracked area(s) and modification of uncracked area(s) constitutes terminating action for the requirements of paragraph (a) of this AD.
(d) If any cracking is detected during any inspection required by paragraph (b) or (c)(2) of this AD, and 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) The actions required by paragraph (a) of this AD are not required to be accomplished if the requirements of paragraph (c) of this AD are accomplished at the time specified in paragraph (a) of this AD.
New Requirements of This AD
Initial Inspection
(f) For airplanes on which the inspection required by paragraph (a) of this AD has not been done before the effective date of this AD: Perform a high frequency eddy current inspection to detect fatigue cracking of the lower surface panel on the wing center box, in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997; or Revision 03, dated April 30, 2002; at the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD. Accomplishment of the inspections required by this paragraph terminates the requirements of paragraph (a) of this AD.
(1) Prior to the accumulation of 13,200 total flight cycles or 39,700 total flight hours, whichever is first.
(2) Prior to the accumulation of 20,000 total flight cycles, or within 3,500 flight cycles after the effective date of this AD, whichever is first.
Repetitive Inspections
(g) If no cracking is detected during the inspection required by paragraph (a) or (f) of this AD: Repeat the inspection at the applicable time specified in paragraph (g)(1) or (g)(2) of this AD.
(1) For airplanes on which the inspections required by paragraph (a) of this AD have been done before the effective date of this AD: Do the next inspection within 5,700 flight cycles after accomplishment of the last inspection, or within 1,800 flight cycles after the effective date of this AD, whichever is later. Repeat the inspection thereafter at intervals not to exceed 5,700 flight cycles.
(2) For airplanes on which no inspection required by paragraph (a) of this AD has been done before the effective date of this AD: Do the next inspection within 5,700 flight cycles after accomplishment of the inspection required by paragraph (f) of this AD. Repeat the inspection thereafter at intervals not to exceed 5,700 flight cycles.
Repair/Modification
(h) If any cracking is detected during any inspection required by paragraph (f) or (g) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A320-57-1082, Revision 01, dated December 10, 1997; or Revision 03, dated April 30, 2002; and modify any uncracked area in accordance with Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997; or Revision 05, dated April 30, 2002. Where Service Bulletin A320-57-1082 specifies to contact Airbus for an appropriate repair 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 (DGAC) (or its delegated agent). Accomplishment of the repair of cracked area(s) and modification of uncracked area(s) constitutes terminating action for the requirements of this AD.
Actions Done per Previous Issues of Service Bulletins
(i) Accomplishment of inspections and repairs before the effective date of this AD in accordance with Airbus Service Bulletin A320-57-1082, Revision 02, dated July 26, 1999; and accomplishment of the modification before the effective date of this AD in accordance with Airbus Service Bulletin Airbus Service Bulletin A320-57-1043, dated February 16, 1993; Revision 01, dated June 14, 1996; Revision 03, dated October 24, 1997; or Revision 04, dated March 15, 1999; are considered acceptable for compliance with the applicable actions specified in this AD.
Alternative Methods of Compliance
(j) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, is authorized to approve alternative methods of compliance for this AD.
Note 1: The subject of this AD is addressed in French airworthiness directive 2002-342(B), dated June 26, 2002.
Footer Information
Issued in Renton, Washington, on January 29, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 04-2481 Filed 2-5-04; 8:45 am]
BILLING CODE 4910-13-P
Comments
Not Applicable
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