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), 2469-2475 [E7-715]

Download as PDF 2469 Federal Register / Vol. 72, No. 12 / Friday, January 19, 2007 / Proposed Rules TABLE 2.—COMPLIANCE TIME FOR TERMINATING MODIFICATION For model Compliance time (1) A310–203, –204, –221, and –222 airplanes. (2) A310–304, –322, –324, and –325 airplanes. Before the accumulation of 40,000 flight cycles since the date of issuance of the original French Certificate or the date of issuance of the original French Export Certificate of Airworthiness, or tion required by paragraph (l) of this AD, whichever occurs later. Before the accumulation of 35,000 flight cycles since the date of issuance of the original French Certificate or the date of issuance of the original French Export Certificate of Airworthiness, or tion required by paragraph (l) of this AD, whichever occurs later Earlier Revision of Service Bulletins (p) Actions done before the effective date of this AD in accordance with the service standard Airworthiness during the next inspecstandard Airworthiness during the next inspec- bulletins identified in Table 3 of this AD, are acceptable for compliance with the corresponding requirements of this AD. TABLE 3.—EARLIER REVISION OF SERVICE BULLETINS Revision level Airbus service bulletin (1) A310–53–2017 ........................................................................................................................................... (2) A310–53–2017 ........................................................................................................................................... Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (q)(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) Alternative methods of compliance, approved previously in accordance with AD 98–16–06 are approved as alternative methods of compliance with the corresponding provisions of paragraphs (f) through (m) of this AD. (3) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Federal Aviation Administration Related Information (r) French airworthiness directives 1991– 132–124(B) R1, dated November 29, 2000, and F–2004–103, dated July 7, 2004, also address the subject of this AD. Issued in Renton, Washington, on January 8, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–702 Filed 1–18–07; 8:45 am] jlentini on PROD1PC65 with PROPOSAL BILLING CODE 4910–13–P VerDate Aug<31>2005 18:23 Jan 18, 2007 Jkt 211001 14 CFR Part 39 [Docket No. FAA–2007–26856; Directorate Identifier 2006–NM–125–AD] 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: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all Airbus Model A300–600 series airplanes. The existing 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. The existing AD also provides for optional terminating action for certain inspections. This proposed AD would retain all requirements of the existing AD, mandate the previously optional terminating action, reduce the applicability of the existing AD, and add repetitive inspections behind scuff plates for certain affected airplanes. This proposed AD results from a determination that further rulemaking is necessary to improve the fatigue PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 7 08 Date February 25, 1992. September 7, 2000. behavior of the cabin door surroundings. We are proposing 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: We must receive comments on this proposed AD by February 20, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, Room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed 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: E:\FR\FM\19JAP1.SGM 19JAP1 2470 Federal Register / Vol. 72, No. 12 / Friday, January 19, 2007 / Proposed Rules Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA–2007–26856; Directorate Identifier 2006–NM–125– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion On July 24, 1998, we issued AD 98– 16–05, amendment 39–10680 (63 FR 40812, July 31, 1998), for all 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). That AD 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. That AD resulted from reports indicating that corrosion was found behind the scruff plates at exit and cargo doors, and fatigue cracks originated from certain fastener holes located in adjacent structure. We issued that AD to detect and correct such corrosion and fatigue cracking, which could result in reduced structural integrity of the door surroundings. Other Relevant Rulemaking We have previously issued AD 97– 11–03, amendment 39–10032 (62 FR 28325, May 23, 1997), applicable to all Airbus Model A300 series airplanes. That AD 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 requires modification of the passenger/ crew door frames, which terminates certain inspections. We also previously issued AD 98–16– 06, amendment 39–10682 (63 FR 40819, July 31, 1998), for all Airbus Model A310 series airplanes. That AD 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. We are considering further rulemaking to mandate the optional terminating action. Actions Since Existing AD Was Issued Since we issued AD 98–16–05, the ´ ´ Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, issued French airworthiness directives 1991–132– 124(B) R1, dated November 29, 2000 (to replace French airworthiness directive 91–132–124(B), dated June 26, 1991, which is referred to in AD 98–16–05), and F–2004–103, dated July 7, 2004. The DGAC advises that further rulemaking is necessary to improve the fatigue behavior of the cabin door surroundings on certain Airbus Model A300–600 series airplanes and to remove certain airplanes from the applicability of the existing AD that are no longer subject to the existing requirements. Corrosion between the scuff plates at exit and cargo doors and fatigue cracks originating from certain fastener holes located in adjacent structure, if not corrected, could result in reduced structural integrity of the door surroundings. After the DGAC issued French airworthiness directive 1991–132– 124(B) R1 on November 29, 2000, we determined at that time that further rulemaking was not necessary, because the changes to AD 98–16–05 would be relieving in nature. However, since French airworthiness directive F–2004– 103 mandates the previously optional modification, we now agree with the DGAC that further rulemaking is indeed necessary to improve the fatigue behavior of the cabin door surroundings, and this proposed AD follows from that determination. Relevant Service Information Airbus has issued and revised the service bulletins in the following table: SERVICE BULLETINS jlentini on PROD1PC65 with PROPOSAL Airbus Service Bulletin— Describes procedures for— A300–53–6011, Revision 07, dated January 24, 2005 (Revision 3, dated February 4, 1991, of the service bulletin was referenced in AD 98– 16–05 as an appropriate source of service information). A300–53–6022, Revision 04, dated January 24, 2005 (the original issue, dated February 4, 1991, of the service bulletin was referenced in AD 98–16–05 as an appropriate source of service information). Doing initial inspections for cracks and corrosion of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door, and repairing any cracked or corroded part or contacting Airbus. The inspection and repair are essentially identical to those specified in Revision 3 of the service bulletin. Revision 07 also revises the effectivity by adding additional airplanes. Doing repetitive inspections for cracks and corrosion of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door, and repairing any cracked/corroded part or contacting Airbus. The inspection and repair are essentially identical to those specified in original issue of the service bulletin. Revision 04 also revises the effectivity by adding additional airplanes. VerDate Aug<31>2005 18:23 Jan 18, 2007 Jkt 211001 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 E:\FR\FM\19JAP1.SGM 19JAP1 2471 Federal Register / Vol. 72, No. 12 / Friday, January 19, 2007 / Proposed Rules SERVICE BULLETINS—Continued Airbus Service Bulletin— Describes procedures for— A300–53–6018, Revision 03, dated July 26, 2006, including Appendix 01 (Revision 1, dated April 29, 1992, of the service bulletin was referenced in AD 98–16–05 as an appropriate source of service information). A300–53–6002, Revision 06, dated May 17, 2004 (Revision 3, dated February 22, 1992, of the service bulletin was referenced in AD 98–16–05 as an appropriate source of service information). Doing repetitive inspections for cracks/corrosion of the holes of the corner doublers, the failsafe ring, and the door frames of the passenger/crew door structures, and repairing any cracked/corroded part or contacting Airbus. The inspection and repair are essentially identical to those specified in Revision 1 of the service bulletin. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The DGAC mandated the service information to ensure the continued airworthiness of these airplanes in France. FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. We have examined the DGAC’s findings, evaluated all pertinent information, and determined that AD action is necessary for airplanes of this type design that are certificated for operation in the United States. This proposed AD would supersede AD 98–16–05, retain the requirements of the existing AD, mandate the previously optional terminating action, reduce the applicability of the existing AD, and add repetitive inspections behind scuff plates for certain affected airplanes. This proposed AD would also require accomplishing the actions specified in service information described previously. Modifying the passenger/crew door structures, which ends the repetitive inspections of the holes of the corner doublers specified in Airbus Service Bulletin A300–53–6018, the fail-safe ring, and the door frames for certain airplanes. The modification includes cold expansion of fastener holes; a ROTO test; repair of any crack; repair of any crack that cannot be eliminated per Airbus; installation of new oversize fasteners and modified brackets; and installation of an additional steel doubler. The modification is essentially identical to that specified in Revision 3 of the service bulletin. Difference Between French Airworthiness Directive and This Proposed AD The applicability of French airworthiness directive 1991–132– 124(B) R1 excludes Airbus Model A300–600 series airplanes on which Airbus Service Bulletin A300–53–6002, Revision 2, dated May 6, 1991 (or any other later approved revision), has been accomplished in service. However, we have not excluded those airplanes in the applicability of this proposed AD; rather, this proposed AD includes a requirement to accomplish the actions specified in Revision 06 of that service bulletin. This requirement would ensure that the actions specified in the service bulletin and required by this proposed AD are accomplished on all affected airplanes. Operators must continue to operate the airplane in the configuration required by this proposed AD unless an alternative method of compliance is approved. The service bulletins specify to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions using a method that we or the European Aviation Safety Agency (EASA) (or its delegated agent) approve. In light of the type of repair that would be required to address the unsafe condition, and consistent with existing bilateral airworthiness agreements, we have determined that, for this proposed AD, a repair we or the EASA approve would be acceptable for compliance with this proposed AD. Change to Existing AD This proposed AD would retain all requirements of AD 98–16–05. Since AD 98–16–05 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table: REVISED PARAGRAPH IDENTIFIERS Corresponding requirements in this proposed AD Requirement in AD 98–16–05 Paragraph Paragraph Paragraph Paragraph Paragraph Paragraph Paragraph (a) ............ (b) ............ (c) ............ (d) ............ (e) ............ (f) ............. (g) ............ Paragraph (f). Paragraph (g). Paragraph (h). Paragraph (i). paragraph (j). Paragraph (k). Paragraph (l). The DGAC revised the applicability of French airworthiness directives 1991– 132–124(B) R1 and F–2004–103 to exclude Model A300–600 series airplanes on which Airbus Modification 5068, 6514, 7201, and 7298 have been incorporated in production. Therefore, the applicability of the proposed AD parallels the French airworthiness directives in that regard. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD. The average labor rate per work hour is $80. ESTIMATED COSTS jlentini on PROD1PC65 with PROPOSAL Action Work hours Repetitive inspections behind scuff 37 .......................... plates. Repetitive inspections of corner dou- Between 1 and 51 blers, fail-safe ring, and door frames. VerDate Aug<31>2005 18:23 Jan 18, 2007 Jkt 211001 PO 00000 Frm 00008 Number of U.S.registered airplanes Parts Cost per airplane None ..................... $2,960 ................... 129 $381,840. None ..................... Between $80 and $4,080. 129 Between $10,320 and $526,320. Fmt 4702 Sfmt 4702 E:\FR\FM\19JAP1.SGM 19JAP1 Fleet cost 2472 Federal Register / Vol. 72, No. 12 / Friday, January 19, 2007 / Proposed Rules ESTIMATED COSTS—Continued Action Work hours Parts Terminating modification for repetitive inspection of corner doublers, failsafe ring, and door frames. Between 8 and 67, depending on kit purchased. Between $580 and $11,273, depending on 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. jlentini on PROD1PC65 with PROPOSAL Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the 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 proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. VerDate Aug<31>2005 18:23 Jan 18, 2007 Jkt 211001 Cost per airplane Number of U.S.registered airplanes Between $1,220 and $16,633. 129 Fleet cost Between $157,380 and $2,145,657. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Requirements of AD 98–16–05 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: (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. PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–10680 (63 FR 40812, July 31, 1998) and adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2007–26856; Directorate Identifier 2006–NM–125–AD. Comments Due Date (a) The FAA must receive comments on this AD action by February 20, 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. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Initial Inspection Behind Scuff Plates and Repair if Necessary 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. E:\FR\FM\19JAP1.SGM 19JAP1 Federal Register / Vol. 72, No. 12 / Friday, January 19, 2007 / Proposed Rules (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, 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. 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 2473 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, dated November 27, 2000: Prior to further flight, repair the crack in accordance with a method approved by the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate. New Requirements of This AD New Revision of Service Bulletins (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 REVISION OF SERVICE BULLETINS Do the action(s) required by— In accordance with the Accomplishment Instructions of Airbus Service Bulletin— (1) Paragraph (f) of this AD ...................................................................... (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. jlentini on PROD1PC65 with PROPOSAL 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 VerDate Aug<31>2005 18:23 Jan 18, 2007 Jkt 211001 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 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 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. E:\FR\FM\19JAP1.SGM 19JAP1 2474 Federal Register / Vol. 72, No. 12 / Friday, January 19, 2007 / Proposed Rules TABLE 2.—COMPLIANCE TIME INITIAL INSPECTION BEHIND SCUFF PLATE FOR ADDITIONAL AIRPLANES For airplanes on which— Compliance time (whichever occurs later) And on which— Threshold (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. (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. (3) Modification 5382S6526 (for forward doors) and Modification 5382D4485 (for all other doors) have not been done before 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 dated 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. (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. jlentini on PROD1PC65 with PROPOSAL 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. VerDate Aug<31>2005 18:23 Jan 18, 2007 Jkt 211001 Grace period None ........................................ Within 108 months after first flight. Within 12 months after the effective date of this AD. None ........................................ Within 108 months after first flight. Within 12 months after 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. The actions specified in Airbus SIL A300–53–033, Revision 2 (for all doors), dated November 23, 1984, have been done. The actions specified in Airbus SIL A300–53–033, Revision 2, dated November 23, 1984, have not been done. Within 60 months after accomplishing the actions specified in the SIL. 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. 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. 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. (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 PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 Within 12 months after the effective date of this AD. 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 E:\FR\FM\19JAP1.SGM 19JAP1 2475 Federal Register / Vol. 72, No. 12 / Friday, January 19, 2007 / Proposed Rules 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 Airbus Service Bulletin (1) A300–53–6002 ........................................................................................................................................... (2) A300–53–6002 ........................................................................................................................................... (3) A300–53–6002 ........................................................................................................................................... (4) A300–53–6011 ........................................................................................................................................... (5) A300–53–6011 ........................................................................................................................................... (6) A300–53–6011 ........................................................................................................................................... (7) A300–53–6018, excluding Appendix 01 .................................................................................................... (8) A300–53–6022 ........................................................................................................................................... (9) A300–53–6022 ........................................................................................................................................... (10) A300–53–6022 ......................................................................................................................................... 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. Issued in Renton, Washington, on January 8, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–715 Filed 1–18–07; 8:45 am] jlentini on PROD1PC65 with PROPOSAL BILLING CODE 4910–13–P VerDate Aug<31>2005 18:23 Jan 18, 2007 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–26864; Directorate Identifier 2006–NM–228–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–200, –300, –400, –500, –600, –700, –800, and –900 Series Airplanes; Boeing Model 757–200 and –300 Series Airplanes; and McDonnell Douglas Model DC–10–10, DC–10–10F, DC–10– 30, DC–10–30F, DC–10–40, MD–10– 30F, MD–11, and MD–11F Airplanes; Equipped With Reinforced Flight Deck Doors Installed in Accordance With Supplemental Type Certificate (STC) ST01335LA, STC ST01334LA, and STC ST01391LA, Respectively Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain transport category airplanes identified above. The existing AD currently requires modification of the reinforced flight deck door and other actions related to the reinforced flight deck door. Those other actions include modifying the door, inspecting and modifying wiring in the area, and revising the maintenance program to require more frequent testing of the decompression panels of the flight deck door. This proposed AD would add airplanes to the existing requirement of a one-time inspection for chafing of wire Jkt 211001 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 03 4 05 04 05 06 02 01 02 03 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. November 12, 2002. bundles in the area of the flight deck door and corrective actions if necessary. This proposed AD would remove certain airplanes from the applicability. This proposed AD results from a report of smoke and fumes in the cockpit of a Model 737–300 series airplane. We are proposing this AD to prevent inadvertent release of the decompression latch and consequent opening of the decompression panel in the flight deck door, or penetration of the flight deck door by smoke or shrapnel, any of which could result in injury to the airplane flightcrew. We are also proposing this AD to detect and correct wire chafing, which could result in arcing, fire, and/or reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by March 5, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207; Boeing Commercial Airplanes, Long Beach E:\FR\FM\19JAP1.SGM 19JAP1

Agencies

[Federal Register Volume 72, Number 12 (Friday, January 19, 2007)]
[Proposed Rules]
[Pages 2469-2475]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-715]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-26856; Directorate Identifier 2006-NM-125-AD]
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: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to all Airbus Model A300-600 series
airplanes. The existing 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. The existing AD also provides for optional terminating
action for certain inspections. This proposed AD would retain all
requirements of the existing AD, mandate the previously optional
terminating action, reduce the applicability of the existing AD, and
add repetitive inspections behind scuff plates for certain affected
airplanes. This proposed AD results from a determination that further
rulemaking is necessary to improve the fatigue behavior of the cabin
door surroundings. We are proposing 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: We must receive comments on this proposed AD by February 20,
2007.

ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this proposed 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:

[[Page 2470]]

Comments Invited

We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2007-26856; Directorate Identifier 2006-NM-125-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit https://dms.dot.gov.

Examining the Docket

You may examine the AD docket on the Internet at https://
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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.

Discussion

On July 24, 1998, we issued AD 98-16-05, amendment 39-10680 (63 FR
40812, July 31, 1998), for all 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). That AD 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. That AD resulted from
reports indicating that corrosion was found behind the scruff plates at
exit and cargo doors, and fatigue cracks originated from certain
fastener holes located in adjacent structure. We issued that AD to
detect and correct such corrosion and fatigue cracking, which could
result in reduced structural integrity of the door surroundings.

Other Relevant Rulemaking

We have previously issued AD 97-11-03, amendment 39-10032 (62 FR
28325, May 23, 1997), applicable to all Airbus Model A300 series
airplanes. That AD 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 requires modification of the passenger/crew door frames, which
terminates certain inspections.
We also previously issued AD 98-16-06, amendment 39-10682 (63 FR
40819, July 31, 1998), for all Airbus Model A310 series airplanes. That
AD 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. We are
considering further rulemaking to mandate the optional terminating
action.

Actions Since Existing AD Was Issued

Since we issued AD 98-16-05, the Direction G[eacute]n[eacute]rale
de l'Aviation Civile (DGAC), which is the airworthiness authority for
France, issued French airworthiness directives 1991-132-124(B) R1,
dated November 29, 2000 (to replace French airworthiness directive 91-
132-124(B), dated June 26, 1991, which is referred to in AD 98-16-05),
and F-2004-103, dated July 7, 2004. The DGAC advises that further
rulemaking is necessary to improve the fatigue behavior of the cabin
door surroundings on certain Airbus Model A300-600 series airplanes and
to remove certain airplanes from the applicability of the existing AD
that are no longer subject to the existing requirements. Corrosion
between the scuff plates at exit and cargo doors and fatigue cracks
originating from certain fastener holes located in adjacent structure,
if not corrected, could result in reduced structural integrity of the
door surroundings.
After the DGAC issued French airworthiness directive 1991-132-
124(B) R1 on November 29, 2000, we determined at that time that further
rulemaking was not necessary, because the changes to AD 98-16-05 would
be relieving in nature. However, since French airworthiness directive
F-2004-103 mandates the previously optional modification, we now agree
with the DGAC that further rulemaking is indeed necessary to improve
the fatigue behavior of the cabin door surroundings, and this proposed
AD follows from that determination.

Relevant Service Information

Airbus has issued and revised the service bulletins in the
following table:

Service Bulletins
------------------------------------------------------------------------
Airbus Service Bulletin-- Describes procedures for--
------------------------------------------------------------------------
A300-53-6011, Revision 07, Doing initial inspections for cracks and
dated January 24, 2005 corrosion of the areas behind the scuff
(Revision 3, dated February plates below the passenger/crew doors
4, 1991, of the service and bulk cargo door, and repairing any
bulletin was referenced in cracked or corroded part or contacting
AD 98-16-05 as an Airbus. The inspection and repair are
appropriate source of essentially identical to those specified
service information). in Revision 3 of the service bulletin.
Revision 07 also revises the effectivity
by adding additional airplanes.
A300-53-6022, Revision 04, Doing repetitive inspections for cracks
dated January 24, 2005 (the and corrosion of the areas behind the
original issue, dated scuff plates below the passenger/crew
February 4, 1991, of the doors and bulk cargo door, and repairing
service bulletin was any cracked/corroded part or contacting
referenced in AD 98-16-05 as Airbus. The inspection and repair are
an appropriate source of essentially identical to those specified
service information). in original issue of the service
bulletin. Revision 04 also revises the
effectivity by adding additional
airplanes.

[[Page 2471]]

A300-53-6018, Revision 03, Doing repetitive inspections for cracks/
dated July 26, 2006, corrosion of the holes of the corner
including Appendix 01 doublers, the fail-safe ring, and the
(Revision 1, dated April 29, door frames of the passenger/crew door
1992, of the service structures, and repairing any cracked/
bulletin was referenced in corroded part or contacting Airbus. The
AD 98-16-05 as an inspection and repair are essentially
appropriate source of identical to those specified in Revision
service information). 1 of the service bulletin.
A300-53-6002, Revision 06, Modifying the passenger/crew door
dated May 17, 2004 (Revision structures, which ends the repetitive
3, dated February 22, 1992, inspections of the holes of the corner
of the service bulletin was doublers specified in Airbus Service
referenced in AD 98-16-05 as Bulletin A300-53-6018, the fail-safe
an appropriate source of ring, and the door frames for certain
service information). airplanes. The modification includes
cold expansion of fastener holes; a ROTO
test; repair of any crack; repair of any
crack that cannot be eliminated per
Airbus; installation of new oversize
fasteners and modified brackets; and
installation of an additional steel
doubler. The modification is essentially
identical to that specified in Revision
3 of the service bulletin.
------------------------------------------------------------------------

Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The DGAC mandated
the service information to ensure the continued airworthiness of these
airplanes in France.

FAA's Determination and Requirements of the Proposed AD

These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that AD action is
necessary for airplanes of this type design that are certificated for
operation in the United States.
This proposed AD would supersede AD 98-16-05, retain the
requirements of the existing AD, mandate the previously optional
terminating action, reduce the applicability of the existing AD, and
add repetitive inspections behind scuff plates for certain affected
airplanes. This proposed AD would also require accomplishing the
actions specified in service information described previously.

Difference Between French Airworthiness Directive and This Proposed AD

The applicability of French airworthiness directive 1991-132-124(B)
R1 excludes Airbus Model A300-600 series airplanes on which Airbus
Service Bulletin A300-53-6002, Revision 2, dated May 6, 1991 (or any
other later approved revision), has been accomplished in service.
However, we have not excluded those airplanes in the applicability of
this proposed AD; rather, this proposed AD includes a requirement to
accomplish the actions specified in Revision 06 of that service
bulletin. This requirement would ensure that the actions specified in
the service bulletin and required by this proposed AD are accomplished
on all affected airplanes. Operators must continue to operate the
airplane in the configuration required by this proposed AD unless an
alternative method of compliance is approved.
The service bulletins specify to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions using a method that we or the
European Aviation Safety Agency (EASA) (or its delegated agent)
approve. In light of the type of repair that would be required to
address the unsafe condition, and consistent with existing bilateral
airworthiness agreements, we have determined that, for this proposed
AD, a repair we or the EASA approve would be acceptable for compliance
with this proposed AD.

Change to Existing AD

This proposed AD would retain all requirements of AD 98-16-05.
Since AD 98-16-05 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:

Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirements
Requirement in AD 98-16-05 in this proposed AD
------------------------------------------------------------------------
Paragraph (a)............................. Paragraph (f).
Paragraph (b)............................. Paragraph (g).
Paragraph (c)............................. Paragraph (h).
Paragraph (d)............................. Paragraph (i).
Paragraph (e)............................. paragraph (j).
Paragraph (f)............................. Paragraph (k).
Paragraph (g)............................. Paragraph (l).
------------------------------------------------------------------------

The DGAC revised the applicability of French airworthiness
directives 1991-132-124(B) R1 and F-2004-103 to exclude Model A300-600
series airplanes on which Airbus Modification 5068, 6514, 7201, and
7298 have been incorporated in production. Therefore, the applicability
of the proposed AD parallels the French airworthiness directives in
that regard.

Costs of Compliance

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

Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Parts Cost per airplane registered Fleet cost
airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Repetitive inspections behind scuff 37..................... None................... $2,960................ 129 $381,840.
plates.
Repetitive inspections of corner Between 1 and 51....... None................... Between $80 and $4,080 129 Between $10,320 and
doublers, fail-safe ring, and door $526,320.
frames.

[[Page 2472]]

Terminating modification for Between 8 and 67, Between $580 and Between $1,220 and 129 Between $157,380 and
repetitive inspection of corner depending on kit $11,273, depending on $16,633. $2,145,657.
doublers, fail-safe ring, and door purchased. kit purchased.
frames.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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 proposed 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, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec. 39.13 [Amended]

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

Airbus: Docket No. FAA-2007-26856; Directorate Identifier 2006-NM-
125-AD.

Comments Due Date

(a) The FAA must receive comments on this AD action by February
20, 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.

[[Page 2473]]

(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, dated November 27,
2000: Prior to further flight, repair the crack in accordance with a
method approved by the Manager, International Branch, ANM-116, FAA,
Transport Airplane Directorate.

New Requirements of This AD

New Revision of Service Bulletins

(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 Revision of Service Bulletins
------------------------------------------------------------------------
In accordance with the
Do the action(s) required by-- 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 A300-53-6022, Revision 04,
AD. dated January 24, 2005.
(3) Paragraphs (j), (k), and (l)(1) of A300-53-6018, Revision 03,
this AD. 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.

[[Page 2474]]

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.
(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 dated of this November 23, 1984,
AD. 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

[[Page 2475]]

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
Airbus Service Bulletin level Date
------------------------------------------------------------------------
(1) A300-53-6002.............. 03 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 02 November 27, 2000.
Appendix 01.
(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 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.

Issued in Renton, Washington, on January 8, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-715 Filed 1-18-07; 8:45 am]
BILLING CODE 4910-13-P

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