AD 2007-11-12 Airworthiness Directives; Airbus Model A310 Series Airplanes

Models named: A310 series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A310 series airplanes; certificated in any category; excluding those airplanes on which Airbus Modifications 5068, 7201, and 7298 have been incorporated in production.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Requirements of AD 98-16-06 Initial Inspection Behind Scuff Plates and Repair if Necessary With Revised Affected Doors (f) Perform an initial inspection of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door to detect cracks and corrosion, in accordance with Airbus Service Bulletin A310-53-2030, Revision 5, dated March 6, 1991, at the applicable time specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD. If any crack or corrosion is found during this inspection, prior to further flight, repair in accordance with the service bulletin. Accomplishment of this inspection is not required for the aft passenger/crew doors if a steel doubler that covers the entire inspection area is installed. (1) For any door on which Modification 5382 and Modification 5382D4741 for all other doors have been accomplished: Perform the initial inspection within 9 years since airplane manufacture, or within 1 year after September 4, 1998 (the effective date of AD 98-16-06), whichever occurs later. (2) For any door on which Modification 5382 and Modification 5382D4741 for all other doors have not been accomplished, and on which the procedures described in Airbus Service Bulletin A310-53-2004, Revision 2, dated June 17, 1985; or Airbus Service Information Letter 53-033, Revision 2, dated November 23, 1984; have been accomplished: Perform the initial inspection within 5 years since airplane manufacture, or within 1 year after September 4, 1998, whichever occurs later. (3) For any door on which Modification 5382 and Modification 5382D4741 for all other doors have not been accomplished, and on which the procedures described in Airbus Service Bulletin A310-53-2004, Revision 2, dated June 17, 1985; or Airbus Service Information Letter 53-033, Revision 2, dated November 23, 1984; have not been accomplished: Perform the initial inspection within 4 years since airplane manufacture, or within 1 year after September 4, 1998, whichever occurs later. Repetitive Inspections Behind Scuff Plates (g) Perform repetitive inspections of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door to detect cracks and corrosion, in accordance with Airbus Service Bulletin A310-53-2041, Revision 02, dated July 2, 1996, at the applicable times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. Accomplishment of these inspections is not required for the aft passenger/crew doors if a steel doubler that covers the entire inspection area is installed. (1) For the forward passenger/crew doors, the bulk cargo door, and the aft passenger/crew doors, except the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler, on all Model A310-200 and -300 series airplanes: Perform the first inspection within 5 years after accomplishing the inspection required by paragraph (f) of this AD; and repeat the inspection thereafter at intervals not to exceed 5 years. (2) For the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler of the aft passenger/crew door on all Model A310-200 series airplanes: Perform the first inspection within 5 years or 12,000 landings after accomplishing the inspection required by paragraph (f) of this AD, whichever occurs first; and repeat the inspection thereafter at intervals not to exceed 5 years or 12,000 landings, whichever occurs first. (3) For the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler of the aft passenger/crew door on all Model A310-300 series airplanes: Perform the first inspection within 5 years or 7,000 landings after accomplishing the inspection required by paragraph (f) of this AD, whichever occurs first; and repeat the inspection thereafter at intervals not to exceed 5 years or 7,000 landings, whichever occurs first. Repair of Scuff Plates if Necessary (h) If any crack is found during any inspection required by paragraph (g) or (n) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A310-53-2041, Revision 02, dated July 2, 1996. Thereafter, perform the repetitive inspections required by paragraph (g) of this AD at the applicable times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. (i) If any corrosion is found during any inspection required by paragraph (g) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A310-53-2041, Revision 02, dated July 2, 1996. Thereafter, perform the repetitive inspections required by paragraph (g) of this AD at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD. (1) For Model A310-200 series airplanes: Inspect at intervals not to exceed 5 years or 9,600 landings, whichever occurs first. (2) For Model A310-300 series airplanes: Inspect at intervals not to exceed 5 years or 5,600 landings, whichever occurs first. (j) Accomplishment of the actions required by paragraph (g), (h), or (i) of this AD in accordance with Airbus Service Bulletin A310-53-2041, dated December 5, 1990; or Revision 01, dated March 6, 1991; prior to September 4, 1998, is acceptable for compliance with that paragraph. Initial Inspection of Corner Doublers, Fail-Safe Ring, and Door Frames (k) Perform an inspection to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the left- and right-hand forward, mid, and aft passenger/crew door structures, in accordance with Airbus Service Bulletin A310-53-2037, Revision 1, dated April 29, 1992, and at the applicable times specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD. (1) For the upper corners of the forward doors: Inspect prior to the accumulation of 20,000 total landings, or within 2,000 landings after September 4, 1998, whichever occurs later. (2) For the lower corners of the forward doors: Inspect prior to the accumulation of 20,000 total landings, or within 4,000 landings after September 4, 1998, whichever occurs later. (3) For the upper and lower corners of the aft doors, and for the parts underneath the corners of the upper door frames: Inspect prior to the accumulation of 20,000 total landings, or within 4,000 landings after September 4, 1998, whichever occurs later. Repetitive Inspections of Corner Doublers, Fail-Safe Ring, and Door Frames (l) Repeat the inspections required by paragraph (k) of this AD at the applicable times specified in paragraphs (l)(1), (l)(2), (l)(3), (l)(4), and (l)(5). (1) For the upper corners of the forward doors: Inspect at intervals not to exceed 6,000 landings. (2) For the lower corners of the forward doors: Inspect at intervals not to exceed 10,000 landings. (3) For the upper and lower corners of the aft doors on which an inspection required by paragraph (k) of this AD was accomplished using a ROTO test technique: Inspect at intervals not to exceed 8,000 landings. (4) For the upper and lower corners of the aft doors on which an inspection required by paragraph (k) of this AD was accomplished using an x-ray technique: Inspect at intervals not to exceed 3,500 landings. (5) For the areas around the fasteners in the vicinity of stringer 12 on the upper door frames of the aft doors on which an inspection required by paragraph (k) of this AD was accomplished using a visual technique: Inspect at intervals not to exceed 6,900 landings. Repair of Corner Doublers, Fail-Safe Ring, and/or Door Frames if Necessary (m) If any crack is found during any inspection required by paragraph (k) or (l) of this AD: Prior to further flight, accomplish the requirement of paragraph (m)(1) or (m)(2) of this AD, as applicable. (1) If any crack is found, and the crack can be eliminated using the method specified in Airbus Service Bulletin A310-53-2037, Revision 1, dated April 29, 1992; or Revision 02, dated November 27, 2000: Prior to further flight, repair the crack in accordance with that service bulletin. (2) If any crack is found, and the crack cannot be eliminated using the method specified in Airbus Service Bulletin A310-53-2037, Revision 1, dated April 29, 1992; or Revision 02, dated November 27, 2000: Prior to further flight, repair the crack in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. New Requirements of This AD New Revision of Service Bulletins (n) As of the effective date of this AD, use only the service bulletins specified in Table 1 of this AD. Table 1.—New Revision of Service Bulletins Do the action(s) required by— In accordance with the accomplishment instructions of Airbus Service Bulletin— (1) Paragraph (f) of this AD A310-53-2030, Revision 06, dated July 2, 1996. (2) Paragraph (k) and (m)(1) of this AD A310-53-2037, Revision 03, excluding Appendix 01, dated July 26, 2006. Terminating Modification for Repetitive Inspection of Corner Doublers, Fail-Safe Ring, and Door Frames (o) Modify the passenger/crew door structures in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2017, Revision 09, dated May 17, 2004. Do the modification at the applicable time in paragraph (o)(1) or (o)(2) of Table 2 of this AD. Accomplishment of this modification constitutes terminating action for the repetitive inspections required by paragraph (l) of this AD. The inspections required by paragraph (f) of this AD must be done before accomplishing this modification. Table 2.—Compliance Time for Terminating Modification For model— Compliance time (1) A310-203, -204, -221, and -222 airplanes Before the accumulation of 40,000 flight cycles since the date of issuance of the original French standard Airworthiness Certificate or the date of issuance of the original French Export Certificate of Airworthiness, or during the next inspection required by paragraph (l) of this AD, whichever occurs later. (2) A310-304, -322, -324, and -325 airplanes Before the accumulation of 35,000 flight cycles since the date of issuance of the original French standard Airworthiness Certificate or the date of issuance of the original French Export Certificate of Airworthiness, or during the next inspection required by paragraph (l) of this AD, whichever occurs later. Earlier Revision of Service Bulletins (p) Actions done before the effective date of this AD in accordance with the service bulletins identified in Table 3 of this AD are acceptable for compliance with the corresponding requirements of this AD. Table 3.—Earlier Revision(s) of Service Bulletins Airbus Service Bulletin Revision level Date (1) A310-53-2017 07 February 25, 1992. (2) A310-53-2017 08 September 7, 2000. (3) A310-53-2037 02 November 27, 2000. Alternative Methods of Compliance (AMOCs) (q)(1) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Alternative methods of compliance, approved previously in accordance with AD 98-16-06 are approved as alternative methods of compliance with the corresponding provisions of paragraphs (f) through (m) of this AD. (3) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (r) French airworthiness directives 1991-132-124(B) R1, dated November 29, 2000, and F-2004-103, dated July 7, 2004, also address the subject of this AD. Material Incorporated by Reference (s) You must use the service information listed in Table 4 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. Table 4.—All Material Incorporated by Reference Airbus Service Bulletin Revision level Date A310-53-2017 09 May 17, 2004. A310-53-2030 5 March 6, 1991. A310-53-2030 06 July 2, 1996. A310-53-2037 1 April 29, 1992. A310-53-2037, excluding Appendix 01 02 November 27, 2000. A310-53-2037, excluding Appendix 01 03 July 26, 2006. A310-53-2041 02 July 2, 1996. (1) The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 5 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Table 5.—New Material Incorporated by Reference Airbus Service Bulletin Revision level Date A310-53-2017 09 May 17, 2004. A310-53-2030 06 July 2, 1996. A310-53-2037 1 April 29, 1992. A310-53-2037, excluding Appendix 01 02 November 27, 2000. A310-53-2037, excluding Appendix 01 03 July 26, 2006. Airbus Service Bulletin A310-53-2037, Revision 1, dated April 29, 1992, contains the following effective pages:   Page No. Revision level shown on page Date shown on page 1, 4, 6, 11-15, 18, 29, 39-44, 46, 57 Revision 1 April 29, 1992. 2, 3, 5, 7-10, 16, 17, 19-28, 30-38, 45,47-56, 58-60 Original December 11, 1990. (2) On September 4, 1998 (63 FR 40819, July 31, 1998), the Director of the Federal Register approved the incorporation by reference of the service information listed in Table 6 of this AD. Table 6.—Material Previously Incorporated by Reference Airbus Service Bulletin Revision level Date A310-53-2030 5 March 6, 1991. A310-53-2041 02 July 2, 1996. (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on May 15, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-10028 Filed 5-29-07; 8:45 am] BILLING CODE 4910-13-P

This AD results from a determination that further rulemaking is necessary to improve the fatigue behavior of the cabin door surroundings. We are issuing this AD to prevent corrosion between the scuff plates at exit and cargo doors and fatigue cracks originating from certain fastener holes located in adjacent structure, which could result in reduced structural integrity of the door surroundings.