AD 2007-12-04 Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)

Models named: A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R, B4-622R, A300 F4-605R, F4-622R, A300 C4-605R Variant F. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; and Model A300 C4-605R Variant F airplanes; certificated in any category; excluding those airplanes on which Airbus Modification 5068, 6514, 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 98-16-05 Initial Inspection Behind Scuff Plates and Repair if Necessary (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 A300-53-6011, Revision 3, dated February 4, 1991, at the 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 mid and aft passenger/crew doors if a steel doubler that covers the entire inspection area is installed. (1) For airplanes on which Modification 5382S6526 (for forward doors) and Modification 5382D4741 (for all other doors) have been accomplished prior to delivery of the airplane: Perform the initial inspection within 9 years since date of manufacture, or within 1 year after September 4, 1998 (the effective date of AD 98-16-05), whichever occurs later. (2) For airplanes on which Modification 5382S6526 (for forward doors) and Modification 5382D4741 (for all other doors) have not been accomplished; and on which the procedures described in Airbus Service Information Letter (SIL) A300-53-033, Revision 2 (for all doors), dated November 23, 1984, have been accomplished: Perform the initial inspection within 5 years after accomplishment of the procedures described in the SIL, or within 1 year after September 4, 1998, whichever occurs later. (3) For airplanes on which Modification 5382S6526 (for forward doors), and Modification 5382D4741 (for all other doors), and the procedures described in Airbus SIL A300-53-033, Revision 2, dated November 23, 1984, have not been accomplished: Perform the initial inspection within 4 years since date of 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 A300-53-6022, dated February 4, 1991, at the applicable times specified in paragraphs (g)(1) and (g)(2) of this AD. Accomplishment of these inspections is not required for the mid and aft passenger/crew doors if a steel doubler that covers the entire inspection area is installed. (1) For the forward and mid 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: 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 doors: Perform the first inspection within 5 years or 6,000 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 6,000 landings, whichever occurs first. Repair of Scuff Plates if Necessary (h) If any crack is found during any inspection required by paragraph (g) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A300-53-6022, dated February 4, 1991. Thereafter, perform the repetitive inspections required by paragraph (g) of this AD at the applicable times specified in paragraphs (g)(1) and (g)(2) of this AD. (i) If corrosion is found during any inspection required by paragraph (g) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A300-53-6022, dated February 4, 1991. Thereafter, perform the repetitive inspections required by paragraph (g) of this AD at the applicable times specified in paragraph (i)(1) or (i)(2) of this AD. (1) For the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler of the aft passenger/crew doors, and for the mid passenger/crew door: Inspect at intervals not to exceed 5 years or 5,000 landings, whichever occurs first. (2) For the forward passenger/crew doors and bulk cargo doors: Inspect at intervals not to exceed 5 years. Initial Inspection of Corner Doublers, Fail-Safe Ring, and Door Frames (j) 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 A300-53-6018, Revision 1, dated April 29, 1992, and at the applicable time specified in paragraph (j)(1), (j)(2), (j)(3), or (j)(4) 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 mid doors: Inspect prior to the accumulation of 20,000 total landings, or within 2,000 landings after September 4, 1998, whichever occurs later. (4) 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 (k) Repeat the inspections required by paragraph (j) of this AD at the applicable times specified in paragraphs (k)(1), (k)(2), (k)(3), (k)(4), and (k)(5) of this AD. (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 mid and aft doors on which an inspection required by paragraph (j) 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 mid and aft doors on which an inspection required by paragraph (j) 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 (j) 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 (l) If any crack is found during any inspection required by paragraph (j) or (k) of this AD: Prior to further flight, accomplish the requirement of paragraph (l)(1) or (l)(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 A300-53-6018, Revision 1, dated April 29, 1992; or Revision 02, excluding Appendix 01, 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 A300-53-6018, Revision 1, dated April 29, 1992; or Revision 02, excluding Appendix 01, 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 Revisions of Service Bulletins (m) As of the effective date of this AD, use only the applicable service bulletins specified in Table 1 of this AD; except where the service bulletins recommend contacting Airbus for appropriate action, before further flight, repair the cracked part 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). Table 1.—New Revisions 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 A300-53-6011, Revision 07, dated January 24, 2005. (2) Paragraphs (g) through (i) of this AD A300-53-6022, Revision 04, dated January 24, 2005. (3) Paragraphs (j), (k), and (l)(1) of this AD A300-53-6018, Revision 03, excluding Appendix 01, dated July 26, 2006. Initial Inspection Behind Scuff Plates and Repair if Necessary for Additional Airplanes (n) 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 the Accomplishment Instructions of Airbus Service Bulletin A300-53-6011, Revision 07, dated January 24, 2005; at the applicable time specified in Table 2 of this AD. If any crack or corrosion is found during this inspection, before further flight, repair in accordance with the service bulletin. Accomplishment of this inspection is not required for the mid and aft passenger/crew doors if a steel doubler that covers the entire inspection area is installed. Table 2.—Compliance Time Initial Inspection Behind Scuff Plate for Additional Airplanes For airplanes on which— And on which— Compliance time (whichever occurs later) Threshold Grace period (1) Modification 5382S6526 (for forward doors) and Modification 5382D4485 (for all other doors) have been done before the date of issuance of the original French standard airworthiness certificate or the date of issuance of the original French export certificate of airworthiness None Within 108 months after first flight Within 12 months after the effective date of this AD. (2) Modification 5382S6180 (for forward doors) and Modification 5382D4741 or 5382D4485 (for all other doors) have been done before the date of issuance of the original French standard airworthiness certificate or the date of issuance of the original French export certificate of airworthiness None Within 108 months after first flight Within 12 months after the effective date of this AD. (3) Modification 5382S6526 (for forward doors) and Modification 5382D4485 (for all other doors) have not been done before the effective date of this AD The actions specified in Airbus Service Information Letter (SIL) A300-53-033, Revision 2 (for all doors), dated November 23, 1984, have been done Within 60 months after accomplishing the actions specified in the SIL Within 12 months after the effective date of this AD. (4) Modification 5382S6180 (for forward doors) and Modification 5382D4741 or 5382D4485 (for all other doors) have not been done before the effective date of this AD The actions specified in Airbus SIL A300-53-033, Revision 2 (for all doors), dated November 23, 1984, have been done Within 60 months after accomplishing the actions specified in the SIL Within 12 months after the effective date of this AD. (5) Modification 5382S6526 (for forward doors) and Modification 5382D4485 (for all other doors) have not been done before the effective date of this AD The actions specified in Airbus SIL A300-53-033, Revision 2, dated November 23, 1984, have not been done Within 48 months 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 Within 12 months after the effective date of this AD. (6) Modification 5382S6180 (for forward doors) and Modification 5382D4741 or 5382D4485 (for all other doors) have not been done before the effective date of this AD The actions specified in Airbus SIL A300-53-033, Revision 2, dated November 23, 1984, have not been done Within 48 months 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 Within 12 months after the effective date of this AD. Repetitive Inspections Behind Scuff Plates for Additional Airplanes (o) For airplanes identified in Table 2 of this AD: 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 A300-53-6022, Revision 04, dated January 24, 2005, at the applicable times specified in paragraphs (o)(1) and (o)(2) of this AD. Accomplishment of these inspections is not required for the mid and aft passenger/crew doors if a steel doubler that covers the entire inspection area is installed. (1) For the forward and mid 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: Perform the first inspection within 60 months after accomplishing the inspection required by paragraph (n) of this AD; and repeat the inspection thereafter at intervals not to exceed 60 months. (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 doors: Perform the first inspection within 60 months or 6,000 landings after accomplishing the inspection required by paragraph (n) of this AD, whichever occurs first; and repeat the inspection thereafter at intervals not to exceed 60 months or 6,000 landings, whichever occurs first. Repair of Scuff Plates if Necessary (p) If any crack is found during any inspection required by paragraph (o) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A300-53-6022, Revision 04, dated January 24, 2005. Thereafter, perform the repetitive inspections required by paragraph (o) of this AD at the applicable times specified in paragraphs (o)(1) and (o)(2) of this AD. (q) If corrosion is found during any inspection required by paragraph (o) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A300-53-6022, Revision 04, dated January 24, 2005. Thereafter, perform the repetitive inspections required by paragraph (g) of this AD at the applicable times specified in paragraph (q)(1) or (q)(2) of this AD. (1) For the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler of the aft passenger/crew doors, and for the mid passenger/crew door: Inspect at intervals not to exceed 60 months or 5,000 landings, whichever occurs first. (2) For the forward passenger/crew doors and bulk cargo doors: Inspect at intervals not to exceed 60 months. Terminating Modification for Repetitive Inspection of Corner Doublers, Fail-Safe Ring, and Door Frames (r) Before the accumulation of 30,000 total 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 (k) of this AD, whichever occurs later: Modify the passenger/crew door structures in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6002, Revision 06, dated May 17, 2004. Accomplishment of this modification constitutes terminating action for the inspections required by paragraphs (j) and (k) of this AD. The inspections required by paragraphs (f) and (n) of this AD, as applicable, must be done before accomplishing this modification. Earlier Revisions of Service Bulletins (s) 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 Revisions of Service Bulletins Airbus Service Bulletin Revision level Date (1) A300-53-6002 3 February 22, 1992. (2) A300-53-6002 4 July 13, 1992. (3) A300-53-6002 05 September 7, 2000. (4) A300-53-6011 04 July 2, 1996. (5) A300-53-6011 05 September 7, 2000. (6) A300-53-6011 06 November 12, 2002. (7) A300-53-6018, excluding Appendix 01 02 November 27, 2000. (8) A300-53-6022 01 July 2, 1996. (9) A300-53-6022 02 September 7, 2000. (10) A300-53-6022 03 November 12, 2002. Alternative Methods of Compliance (AMOCs) (t)(1) The Manager, International Branch, ANM-116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) AMOCs approved previously in accordance with AD 98-16-05 are approved as AMOCs for the corresponding provisions of paragraphs (f) through (l) 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 (u) 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 (v) 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 A300-53-6002 06 May 17, 2004. A300-53-6011 3 February 4, 1991. A300-53-6011 07 January 24, 2005. A300-53-6018 1 April 29, 1992. A300-53-6018, excluding Appendix 01 02 November 27, 2000. A300-53-6018, excluding Appendix 01 03 July 26, 2006. A300-53-6022 Original February 4, 1991. A300-53-6022 04 January 24, 2005. (1) The Director of the Federal Register approved the incorporation by reference of the service information 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 A300-53-6002 06 May 17, 2004. A300-53-6011 07 January 24, 2005. A300-53-6018, excluding Appendix 01 02 November 27, 2000. A300-53-6018, excluding Appendix 01 03 July 26, 2006. A300-53-6022 04 January 24, 2005. (2) On September 4, 1998 (63 FR 40812, 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 A300-53-6011 3 February 4, 1991. A300-53-6018 1 April 29, 1992. A300-53-6022 Original February 4, 1991. (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 25, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-10671 Filed 6-4-07; 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.