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), 30961-30966 [E7-10671]

Download as PDF Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations (2) Damper ring, part number CRS85–167– 31 or CRS85–167–33. (3) Seal carrier, part number CRS85–167– 21. Credit for Actions Done Using Previous Service Information (k) Modifications accomplished before the effective date of this AD in accordance with Bombardier Service Bulletin 8–32–144, dated August 10, 1998, which includes MessierDowty Service Bulletin M–DT SBDHC8–32– 82, dated March 9, 1998, are considered acceptable for compliance with the corresponding actions specified in this AD. Alternative Methods of Compliance (AMOCs) accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Related Information (m) Canadian airworthiness directive CF– 2006–14, dated June 14, 2006, also addresses the subject of this AD. Material Incorporated by Reference (l)(1) The Manager, New York Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in (n) You must use Bombardier Service Bulletin 8–32–144, Revision ‘A,’ dated April 29, 2002, which includes Messier-Dowty 30961 Service Bulletin M–DT SBDHC8–32–82, Revision 1, dated July 5, 2001; and the task cards identified in Table 2 of this AD; to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, 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. TABLE 2.—TASK CARDS INCORPORATED BY REFERENCE Task card— Dated— de Havilland Dash 8 Series 100 Maintenance Task Card 3210/15 ...................................................... de Havilland Dash 8 Series 200 Maintenance Task Card 3210/15 ...................................................... de Havilland Dash 8 Series 300 Maintenance Task Card 3210/15 ...................................................... June 22, 2005 ................. June 22, 2005 ................. November 29, 2005 ........ Issued in Renton, Washington, on May 25, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–10670 Filed 6–4–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–26856; Directorate Identifier 2006–NM–125–AD; Amendment 39–15082; AD 2007–12–04] RIN 2120–AA64 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) Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. cprice-sewell on PROD1PC71 with RULES AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) that applies to all Airbus Model A300– 600 series airplanes. That AD currently requires inspections of the lower door surrounding structure to detect cracks and corrosion; inspections to detect cracking of the holes of the corner VerDate Aug<31>2005 15:27 Jun 04, 2007 Jkt 211001 doublers, the fail-safe ring, and the door frames of the door structures; and repair if necessary. That AD also provides for optional terminating action for certain inspections. This new AD retains all requirements of the existing AD, mandates the previously optional terminating action, reduces the applicability of the existing AD, and adds repetitive inspections behind scuff plates for certain affected airplanes. 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. DATES: This AD becomes effective July 10, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of July 10, 2007. On September 4, 1998 (63 FR 40812, July 31, 1998), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 To the de Havilland program support manual— 1–8–7. 1–82–7. 1–83–7. of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 98–16–05, amendment 39–10680 (63 FR 40812, July 31, 1998). The existing AD applies to all Airbus Model A300–600 series airplanes. That E:\FR\FM\05JNR1.SGM 05JNR1 30962 Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations NPRM was published in the Federal Register on January 19, 2007 (72 FR 2469). That NPRM proposed to continue the requirements of AD 98–16–05. These requirements are inspections of the lower door surrounding structure to detect cracks and corrosion; inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair if necessary. That NPRM also proposed to mandate the previously optional terminating action, reduce the applicability of the existing AD, and add repetitive inspections behind scuff plates for certain affected airplanes. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been received on the NPRM. Request To Give Credit for Previous Inspections FedEx concurs with the NPRM, but requests that we give credit for previous inspections accomplished in accordance with AD 98–16–05. FedEx points out that this credit should be given for actions in paragraphs (f), (g), (j), (k), (n), and (r) of the NPRM. We partially agree with the request. We agree that it is necessary for the AD to give credit for inspections accomplished previously in accordance with AD 98–16–05. We disagree that it is necessary to change the AD in this regard. Paragraph (e) of the AD states ‘‘You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.’’ Therefore, the AD already gives credit for required actions that were accomplished according to AD 98–16– 05. Request To Allow Previously Granted Alternate Methods of Compliance (AMOCs) FedEx also suggests that AMOCs issued per AD 98–16–05 be granted as applicable to the NPRM. We agree that we should approve AMOCs for this AD that were approved previously in accordance with AD 98– 16–05. We disagree with changing the AD in this regard. Paragraph (t)(2) of both the NPRM and the AD already approves previous AMOCs. Request To Address Repairs Outside Limits FedEx requests that we add wording to paragraphs (l)(2) and (t) of the NPRM to address repairs outside the applicable service bulletins or that exceed the service bulletin limits. (Airbus Service Bulletin A300–53–6018, Revision 1, dated April 29, 1992; or Revision 02, dated November 27, 2000; are the applicable service bulletins for paragraph (l)(2); and paragraph (t) is the AMOC paragraph.) FedEx suggests the following wording: ‘‘If any crack or corrosion is detected during any inspection required by this AD and the applicable service bulletin specifies to contact the manufacturer for disposition of corrective actions: Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM–116, or DGAC/EASA, or its delegated agent.’’ We disagree with the request to add the suggested words. There are no limits specified in the service bulletins. We cannot approve repairs that exceed the limits of the service bulletin unless the excess limits are defined. However, affected operators may request approval of AMOCs, under the provisions of paragraph (t) of the AD. Conclusion We have carefully reviewed the available data, including the comments that have been submitted, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this AD. The average labor rate per work hour is $80. ESTIMATED COSTS Number of U.S.-registered airplanes Action Work hours Parts Cost per airplane Repetitive inspections behind scuff plates. Repetitive inspections of corner doublers, failsafe ring, and door frames. Terminating modification for repetitive inspection of corner doublers, fail-safe ring, and door frames. 37 ................................ None ............................ $2,960 ......................... 129 $381,840. Between 1 and 51 ....... None ............................ Between $80 and $4,080. 129 Between $10,320 and $526,320. Between 8 and 67, depending on kit purchased. Between $580 and $11,273, depending on kit purchased. Between $1,220 and $16,633. 129 Between $157,380 and $2,145,657. cprice-sewell on PROD1PC71 with RULES Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that VerDate Aug<31>2005 15:27 Jun 04, 2007 Jkt 211001 section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Fleet cost Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: E:\FR\FM\05JNR1.SGM 05JNR1 Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–10680 (63 FR 40812, July 31, 1998) and by adding the following new airworthiness directive (AD): I 2007–12–04 Airbus: Amendment 39–15082. Docket No. FAA–2007–26856; Directorate Identifier 2006–NM–125–AD. Effective Date (a) This AD becomes effective July 10, 2007. Affected ADs (b) This AD supersedes AD 98–16–05. cprice-sewell on PROD1PC71 with RULES Applicability (c) 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. Unsafe Condition (d) 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 VerDate Aug<31>2005 15:27 Jun 04, 2007 Jkt 211001 result in reduced structural integrity of the door surroundings. Compliance (e) 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 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 30963 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, FailSafe Ring, and Door Frames (j) Perform an inspection to detect cracking of the holes of the corner doublers, the failsafe 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. E:\FR\FM\05JNR1.SGM 05JNR1 30964 Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations 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 ...................................................... (2) Paragraphs (g) through (i) of this AD .................................. (3) Paragraphs (j), (k), and (l)(1) of this AD ............................. A300–53–6011, Revision 07, dated January 24, 2005. A300–53–6022, Revision 04, dated January 24, 2005. 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 Compliance time (whichever occurs later) For airplanes on which— And on which— cprice-sewell on PROD1PC71 with RULES Threshold (1) Modification 5382S6526 (for None ............................................. 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. (2) Modification 5382S6180 (for None ............................................. 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. (3) Modification 5382S6526 (for The actions specified in Airbus forward doors) and Modification Service Information Letter (SIL) 5382D4485 (for all other doors) A300–53–033, Revision 2 (for have not been done before the all doors), dated November 23, effective date of this AD. 1984, have been done. VerDate Aug<31>2005 15:27 Jun 04, 2007 Jkt 211001 PO 00000 Frm 00010 Fmt 4700 Grace period Within 108 months after first flight Within 12 months after the effective date of this AD. Within 108 months after first flight Within 12 months after the effective date of this AD. Within 60 months after accomplishing the actions specified in the SIL. Within 12 months after the effective date of this AD. Sfmt 4700 E:\FR\FM\05JNR1.SGM 05JNR1 30965 Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations TABLE 2.—COMPLIANCE TIME INITIAL INSPECTION BEHIND SCUFF PLATE FOR ADDITIONAL AIRPLANES—Continued Compliance time (whichever occurs later) For airplanes on which— And on which— Threshold Grace period (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. (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 (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. The actions specified in Airbus SIL A300–53–033, Revision 2, dated November 23, 1984, have not been done. 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 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. 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 Within 12 months after the effective date of this AD. the inspection thereafter at intervals not to exceed 60 months or 6,000 landings, whichever occurs first. Terminating Modification for Repetitive Inspection of Corner Doublers, Fail-Safe Ring, and Door Frames 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. (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 Revision level cprice-sewell on PROD1PC71 with RULES Airbus Service Bulletin (1) (2) (3) (4) (5) (6) (7) (8) (9) A300–53–6002 ........................................................................................................................................ A300–53–6002 ........................................................................................................................................ A300–53–6002 ........................................................................................................................................ A300–53–6011 ........................................................................................................................................ A300–53–6011 ........................................................................................................................................ A300–53–6011 ........................................................................................................................................ A300–53–6018, excluding Appendix 01 ................................................................................................. A300–53–6022 ........................................................................................................................................ A300–53–6022 ........................................................................................................................................ VerDate Aug<31>2005 15:27 Jun 04, 2007 Jkt 211001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\05JNR1.SGM 3 .................. 4 .................. 05 ................ 04 ................ 05 ................ 06 ................ 02 ................ 01 ................ 02 ................ 05JNR1 Date February 22, 1992. July 13, 1992. September 7, 2000. July 2, 1996. September 7, 2000. November 12, 2002. November 27, 2000. July 2, 1996. September 7, 2000. 30966 Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations TABLE 3.—EARLIER REVISIONS OF SERVICE BULLETINS—Continued Airbus Service Bulletin Revision level (10) A300–53–6022 ...................................................................................................................................... 03 ................ 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 Date November 12, 2002. 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. (u) French airworthiness directives 1991– 132–124(B) R1, dated November 29, 2000, TABLE 4.—ALL MATERIAL INCORPORATED BY REFERENCE Airbus Service Bulletin Revision level A300–53–6002 ............................................................................................................................................. A300–53–6011 ............................................................................................................................................. A300–53–6011 ............................................................................................................................................. A300–53–6018 ............................................................................................................................................. A300–53–6018, excluding Appendix 01 ...................................................................................................... A300–53–6018, excluding Appendix 01 ...................................................................................................... A300–53–6022 ............................................................................................................................................. A300–53–6022 ............................................................................................................................................. 06 ................ 3 .................. 07 ................ 1 .................. 02 ................ 03 ................ Original ........ 04 ................ (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in Table 5 of Date May 17, 2004. February 4, 1991. January 24, 2005. April 29, 1992. November 27, 2000. July 26, 2006. February 4, 1991. January 24, 2005. this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. TABLE 5.—NEW MATERIAL INCORPORATED BY REFERENCE Revision level Airbus Service Bulletin A300–53–6002 ............................................................................................................................................. A300–53–6011 ............................................................................................................................................. A300–53–6018, excluding Appendix 01 ...................................................................................................... A300–53–6018, excluding Appendix 01 ...................................................................................................... A300–53–6022 ............................................................................................................................................. (2) On September 4, 1998 (63 FR 40812, July 31, 1998), the Director of the Federal Register approved the incorporation by 06 07 02 03 04 ................ ................ ................ ................ ................ Date May 17, 2004. January 24, 2005. November 27, 2000. July 26, 2006. January 24, 2005. reference of the service information listed in Table 6 of this AD. TABLE 6.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE Revision level A300–53–6011 ............................................................................................................................................. A300–53–6018 ............................................................................................................................................. A300–53–6022 ............................................................................................................................................. cprice-sewell on PROD1PC71 with RULES Airbus Service Bulletin 3 .................. 1 .................. Original ........ (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 VerDate Aug<31>2005 15:27 Jun 04, 2007 Jkt 211001 material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal-register/ cfr/ibr-locations.html. PO 00000 Fmt 4700 Sfmt 4700 February 4, 1991. April 29, 1992. February 4, 1991. 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 Frm 00012 Date E:\FR\FM\05JNR1.SGM 05JNR1

Agencies

[Federal Register Volume 72, Number 107 (Tuesday, June 5, 2007)]
[Rules and Regulations]
[Pages 30961-30966]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10671]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-26856; Directorate Identifier 2006-NM-125-AD; 
Amendment 39-15082; AD 2007-12-04]
RIN 2120-AA64


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)

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) that applies to all Airbus Model A300-600 series airplanes. That 
AD currently requires inspections of the lower door surrounding 
structure to detect cracks and corrosion; inspections to detect 
cracking of the holes of the corner doublers, the fail-safe ring, and 
the door frames of the door structures; and repair if necessary. That 
AD also provides for optional terminating action for certain 
inspections. This new AD retains all requirements of the existing AD, 
mandates the previously optional terminating action, reduces the 
applicability of the existing AD, and adds repetitive inspections 
behind scuff plates for certain affected airplanes. 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.

DATES: This AD becomes effective July 10, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of July 10, 2007.
    On September 4, 1998 (63 FR 40812, July 31, 1998), the Director of 
the Federal Register approved the incorporation by reference of certain 
other publications listed in the AD.

ADDRESSES: You may examine the AD docket on the Internet at http://
dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 98-16-05, amendment 39-
10680 (63 FR 40812, July 31, 1998). The existing AD applies to all 
Airbus Model A300-600 series airplanes. That

[[Page 30962]]

NPRM was published in the Federal Register on January 19, 2007 (72 FR 
2469). That NPRM proposed to continue the requirements of AD 98-16-05. 
These requirements are inspections of the lower door surrounding 
structure to detect cracks and corrosion; inspections to detect 
cracking of the holes of the corner doublers, the fail-safe ring, and 
the door frames of the door structures; and repair if necessary. That 
NPRM also proposed to mandate the previously optional terminating 
action, reduce the applicability of the existing AD, and add repetitive 
inspections behind scuff plates for certain affected airplanes.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Request To Give Credit for Previous Inspections

    FedEx concurs with the NPRM, but requests that we give credit for 
previous inspections accomplished in accordance with AD 98-16-05. FedEx 
points out that this credit should be given for actions in paragraphs 
(f), (g), (j), (k), (n), and (r) of the NPRM.
    We partially agree with the request. We agree that it is necessary 
for the AD to give credit for inspections accomplished previously in 
accordance with AD 98-16-05. We disagree that it is necessary to change 
the AD in this regard. Paragraph (e) of the AD states ``You are 
responsible for having the actions required by this AD performed within 
the compliance times specified, unless the actions have already been 
done.'' Therefore, the AD already gives credit for required actions 
that were accomplished according to AD 98-16-05.

Request To Allow Previously Granted Alternate Methods of Compliance 
(AMOCs)

    FedEx also suggests that AMOCs issued per AD 98-16-05 be granted as 
applicable to the NPRM.
    We agree that we should approve AMOCs for this AD that were 
approved previously in accordance with AD 98-16-05. We disagree with 
changing the AD in this regard. Paragraph (t)(2) of both the NPRM and 
the AD already approves previous AMOCs.

Request To Address Repairs Outside Limits

    FedEx requests that we add wording to paragraphs (l)(2) and (t) of 
the NPRM to address repairs outside the applicable service bulletins or 
that exceed the service bulletin limits. (Airbus Service Bulletin A300-
53-6018, Revision 1, dated April 29, 1992; or Revision 02, dated 
November 27, 2000; are the applicable service bulletins for paragraph 
(l)(2); and paragraph (t) is the AMOC paragraph.) FedEx suggests the 
following wording: ``If any crack or corrosion is detected during any 
inspection required by this AD and the applicable service bulletin 
specifies to contact the manufacturer for disposition of corrective 
actions: Prior to further flight, repair in accordance with a method 
approved by either the Manager, International Branch, ANM-116, or DGAC/
EASA, or its delegated agent.''
    We disagree with the request to add the suggested words. There are 
no limits specified in the service bulletins. We cannot approve repairs 
that exceed the limits of the service bulletin unless the excess limits 
are defined. However, affected operators may request approval of AMOCs, 
under the provisions of paragraph (t) of the AD.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been submitted, and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD. The average labor rate per work hour is $80.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                 Number of U.S.-
           Action                Work hours         Parts           Cost per       registered       Fleet cost
                                                                    airplane        airplanes
----------------------------------------------------------------------------------------------------------------
Repetitive inspections        37.............  None...........  $2,960.........             129  $381,840.
 behind scuff plates.
Repetitive inspections of     Between 1 and    None...........  Between $80 and             129  Between $10,320
 corner doublers, fail-safe    51.                               $4,080.                          and $526,320.
 ring, and door frames.
Terminating modification for  Between 8 and    Between $580     Between $1,220              129  Between
 repetitive inspection of      67, depending    and $11,273,     and $16,633.                     $157,380 and
 corner doublers, fail-safe    on kit           depending on                                      $2,145,657.
 ring, and door frames.        purchased.       kit purchased.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:

[[Page 30963]]

    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-10680 (63 FR 40812, July 31, 1998) and by adding 
the following new airworthiness directive (AD):

2007-12-04 Airbus: Amendment 39-15082. Docket No. FAA-2007-26856; 
Directorate Identifier 2006-NM-125-AD.

Effective Date

    (a) This AD becomes effective July 10, 2007.

Affected ADs

    (b) This AD supersedes AD 98-16-05.

Applicability

    (c) 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.

Unsafe Condition

    (d) 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.

Compliance

    (e) 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.

[[Page 30964]]

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     A300-53-6018, Revision 03, excluding Appendix 01, dated July 26, 2006.
 this AD.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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
----------------------------------------------------------------------------------------------------------------
                                                                    Compliance time (whichever occurs later)
       For airplanes on which--             And on which--     -------------------------------------------------
                                                                       Threshold               Grace period
----------------------------------------------------------------------------------------------------------------
(1) Modification 5382S6526 (for        None...................  Within 108 months after  Within 12 months after
 forward doors) and Modification                                 first flight.            the effective date of
 5382D4485 (for all other doors) have                                                     this AD.
 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.
(2) Modification 5382S6180 (for        None...................  Within 108 months after  Within 12 months after
 forward doors) and Modification                                 first flight.            the effective date of
 5382D4741 or 5382D4485 (for all                                                          this AD.
 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.
(3) Modification 5382S6526 (for        The actions specified    Within 60 months after   Within 12 months after
 forward doors) and Modification        in Airbus Service        accomplishing the        the effective date of
 5382D4485 (for all other doors) have   Information Letter       actions specified in     this AD.
 not been done before the effective     (SIL) A300-53-033,       the SIL.
 date of this AD.                       Revision 2 (for all
                                        doors), dated November
                                        23, 1984, have been
                                        done.

[[Page 30965]]

 
(4) Modification 5382S6180 (for        The actions specified    Within 60 months after   Within 12 months after
 forward doors) and Modification        in Airbus SIL A300-53-   accomplishing the        the effective date of
 5382D4741 or 5382D4485 (for all        033, Revision 2 (for     actions specified in     this AD.
 other doors) have not been done        all doors), dated        the SIL.
 before the effective date of this AD.  November 23, 1984,
                                        have been done.
(5) Modification 5382S6526 (for        The actions specified    Within 48 months since   Within 12 months after
 forward doors) and Modification        in Airbus SIL A300-53-   the date of issuance     the effective date of
 5382D4485 (for all other doors) have   033, Revision 2, dated   of the original French   this AD.
 not been done before the effective     November 23, 1984,       standard airworthiness
 date of this AD.                       have not been done.      certificate or the
                                                                 date of issuance of
                                                                 the original French
                                                                 export certificate of
                                                                 airworthiness.
(6) Modification 5382S6180 (for        The actions specified    Within 48 months since   Within 12 months after
 forward doors) and Modification        in Airbus SIL A300-53-   the date of issuance     the effective date of
 5382D4741 or 5382D4485 (for all        033, Revision 2, dated   of the original French   this AD.
 other doors) have not been done        November 23, 1984,       standard airworthiness
 before the effective date of this AD.  have not been done.      certificate or the
                                                                 date of issuance of
                                                                 the original French
                                                                 export certificate of
                                                                 airworthiness.
----------------------------------------------------------------------------------------------------------------

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.

[[Page 30966]]

 
(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 Sec.  
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]
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