Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes), 41109-41113 [E6-11412]

Download as PDF Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23690; Directorate Identifier 2004–NM–133–AD; Amendment 39–14684; AD 2006–15–04] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes; and 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. AGENCY: The FAA is superseding two existing airworthiness directives (AD) that apply to certain Airbus Model A300 B2, A300 B4, and A300–600 series airplanes. One AD currently requires an inspection for cracks of the lower outboard flange of gantry No. 4 in the main landing gear (MLG) bay area, and repair if necessary. The other AD currently requires, among other actions, repetitive inspections of the gantry lower flanges, and repair if necessary. This new AD requires new repetitive inspections for cracks in the lower flange of certain gantries, and repair if necessary, which ends the existing inspection requirements. This new AD also provides for optional terminating actions for the new repetitive inspections. This AD results from a report of a large fatigue crack along the outboard flange of beam No. 4 and a subsequent determination that existing inspections are inadequate. We are issuing this AD to detect and correct fatigue cracks in the lower flanges of gantries 1 through 5 inclusive in the MLG bay area, which could result in reduced structural integrity of the fuselage, and consequent rapid decompression of the airplane. DATES: This AD becomes effective August 24, 2006. The Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300–53– 0379, Revision 01, excluding Appendix 01, dated October 4, 2005; and Airbus Service Bulletin A300–53–6152, Revision 01, excluding Appendix 01, dated October 4, 2005; listed in the AD as of August 24, 2006. On October 19, 2004 (69 FR 55329, September 14, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus wwhite on PROD1PC76 with RULES SUMMARY: VerDate Aug<31>2005 16:42 Jul 19, 2006 Jkt 208001 Service Bulletin A300–53–6128, excluding Appendix 01, dated March 5, 2001. On January 22, 2004 (69 FR 867, January 7, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A300–53A0371, Revision 01, dated September 10, 2003; and Airbus All Operators Telex A300– 53A6145, Revision 01, dated September 10, 2003. On July 30, 1998 (63 FR 34589, June 25, 1998), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex (AOT) 53–11, dated October 13, 1997. ADDRESSES: You may examine the AD docket on the Internet at https:// 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: Thomas Stafford, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; 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 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 street address stated in the ADDRESSES section. Discussion The FAA issued a supplemental notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2003–26–10, amendment 39–13408 (69 FR 867, January 7, 2004), and AD 2004–18–13, amendment 39–13792 (69 FR 55329, dated September 14, 2004). The existing ADs apply to certain Airbus Model A300 B2 and A300 B4 series airplanes, and 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 supplemental NPRM was published in the Federal Register on May 17, 2006 (71 FR 28615). That PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 41109 supplemental NPRM proposed to continue to require an inspection for cracks of the lower outboard flange of gantry No. 4 in the main landing gear (MLG) bay area, and repair if necessary. That supplemental NPRM also proposed to continue to require repetitive inspections of the gantry lower flanges, and repair if necessary. In addition, that supplemental NPRM proposed to require new repetitive inspections for cracks in the lower flange of certain gantries, and repair if necessary, which ends the existing inspection requirements. That supplemental NPRM also proposed optional terminating actions for the new repetitive inspections. That supplemental also revised the original NPRM by including additional airplanes that were excluded from the applicability. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment that has been received on the supplemental NPRM. Request To Refer to Latest Service Bulletin Airbus states that it has issued Service Bulletins A300–53–0360, Revision 01, dated May 31, 2006; and A300–53– 6132, Revision 01, dated June 7, 2006; whose original issues are listed in paragraph (m)(2) of the supplemental NPRM. We infer that Airbus is requesting that Revision 01 of Service Bulletins A300– 53–0360 and A300–53–6132 be referred to in paragraph (m)(2) of the AD. We agree. We have reviewed Revision 01 of both service bulletins. Revision 01 of both service bulletins revises three illustrations. The reinforcement procedures in Revision 01 of both service bulletins are identical to that in the original issues of the service bulletins. No additional work is required for airplanes modified in accordance with the original issues of the service bulletins. Therefore, we have revised paragraph (m)(2) of this AD to refer to Revision 01 of both service bulletins and added a new paragraph (p) to the AD (subsequent paragraphs have been redesignated) to give credit for accomplishing the original issues of both service bulletins. Explanation of Change Made to the Supplemental NPRM Paragraphs (g), (i)(4), and (n) of the supplemental NPRM specify making repairs using a method approved by ´ ´ either the FAA or the Direction Generale de l’Aviation Civile (DGAC) (or its delegated agent). The European E:\FR\FM\20JYR1.SGM 20JYR1 41110 Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations Aviation Safety Agency (EASA) has assumed responsibility for the airplane modes that would be subject to this AD. Therefore, we have revised those paragraphs of this AD to specify making repairs using a method approved by either the FAA, the DGAC (or its delegated agent), or the EASA (or its delegated agent). on any operator nor increase the scope of the AD. Conclusion We have carefully reviewed the available data, including the comment that has been received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden Costs of Compliance This AD will affect about 165 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this AD. Not all actions must be completed on all airplanes. ESTIMATED COSTS FOR REQUIRED ACTIONS Action Average labor rate per hour Work hours One-time inspection (required by AD 2003–26–10). One-time inspection (required by AD 2004–18–13). Repetitive inspections (required by AD 2004–18–13). Repetitive inspections (new proposed actions). Parts Cost per airplane Number of U.S.-registered airplanes Fleet cost 1 $80 None ........... $80 ........................ 23 $1,840. 4 80 None ........... $320 ...................... 43 $13,760. 12 80 None ........... $960, per inspection cycle. 78 $74,880, per inspection cycle. 16 80 None ........... $1,280, per inspection cycle. 78 $99,840, per inspection cycle. ESTIMATED COSTS FOR OPTIONAL ACTIONS Average labor rate per hour Work hours Reinforcement specified in Airbus Service Bulletin A300–53–0380, dated August 5, 2005. Reinforcement specified in Airbus Service Bulletin A300–53–6153, dated August 24, 2005. Reinforcement specified in Airbus Service Bulletin A300–53–0360, Revision 01, dated May 31, 2002. Reinforcement specified in Airbus Service Bulletin A300–53–6132, Revision 01, dated June 7, 2006. wwhite on PROD1PC76 with RULES Optional action 807 .................................... Cost per airplane $80 Between $87,100 and $121,560 depending on kit purchased. Between $151,660 and $186,120 depending on airplane configuration. 23 807 .................................... 80 Between $82,460 and $87,070 depending on kit purchased. Between $147,020 and $151,630 depending on airplane configuration. 120 Between 24 and 128 depending on airplane configuration. 80 Between $250 and $1,000 depending on kit purchased. Between $2,170 and $11,240 depending on airplane configuration. 23 109 .................................... 80 Between $260 and $950 depending on kit purchased. Between $8,980 and $9,670 depending on airplane configuration. 120 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 VerDate Aug<31>2005 Number of U.S.-registered airplanes Parts 16:42 Jul 19, 2006 Jkt 208001 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 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 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: (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 E:\FR\FM\20JYR1.SGM 20JYR1 Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations 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. 5 inclusive in the main landing gear (MLG) bay area, which could result in reduced structural integrity of the fuselage, and consequent rapid decompression of the airplane. (1) If any cracking is detected, prior to further flight, repair in accordance with the AOT. (2) If no cracking is detected, no further action is required by this paragraph. Compliance Repetitive Inspections and Corrective Actions (i) For Model A300 B4–601, B4–603, B4– 605R, B4–620, B4–622R, C4–605R Variant F airplanes, and F4–605R airplanes, on which Airbus Modification 12169 has not been done in production: Perform the requirements of paragraphs (i)(1), (i)(2), (i)(3), and (i)(4) of this AD, in accordance with Airbus Service Bulletin A300–53–6128, dated March 5, 2001. (1) At the later of the times specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD, perform initial ultrasonic inspections or high-frequency eddy current (HFEC) inspections for cracks of the lower flanges of gantries 3, 4, and 5 between fuselage frames FR47 and FR54, in accordance with the Accomplishment Instructions, including the Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, of the service bulletin. (i) In accordance with the thresholds specified in the Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, of the service bulletin; or (ii) Within 200 flight cycles after October 19, 2004 (the effective date AD 2004–18–13). (2) Perform repetitive ultrasonic inspections or high-frequency eddy current inspections for cracks of the lower flanges of gantries 3, 4, and 5 between fuselage frames FR47 and FR54, in accordance with the thresholds and Accomplishment Instructions, including the Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, of the service bulletin. (3) Perform repairs and reinforcements, in accordance with the thresholds and the Accomplishment Instructions, including the Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, of the service bulletin, except as specified in paragraph (i)(4) of this AD. (4) If a new crack is found during any action required by paragraph (i)(1), (i)(2) or (i)(3) of this AD and the Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, of the service bulletin specifies to contact Airbus for appropriate action: Prior to further flight, repair per a method approved by the Manager, International Branch, ANM– 116; the DGAC (or its delegated agent); or the European Aviation Safety Agency (EASA) (or its delegate agent). (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. Restatement of Requirements of AD 2003– 26–10 Adoption of the Amendment One-Time Inspection Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: (f) For airplanes on which Airbus Modification 10147 has not been done: At the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD: Do a one-time detailed inspection for cracking of the lower outboard flange of gantry No. 4 in the MLG bay area per paragraph 4.2.1 of Airbus All Operators Telex (AOT) A300–53A0371, Revision 01 (for Model A300 B2 and B4 series airplanes); or AOT A300–53A6145, Revision 01 (for Model A300–600 series airplanes); both dated September 10, 2003; as applicable. (1) Before the accumulation of 8,000 total flight cycles since the date of issuance of the original Airworthiness Certificate or the date of issuance of the Export Certificate of Airworthiness, whichever is first. (2) Within 30 days after January 22, 2004 (the effective date AD 2003–26–10). Note 1: For the purposes of this AD, a detailed inspection is defined as: ‘‘An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.’’ 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 amendments 39–13408 (69 FR 867, January 7, 2004) and 39–13792 (69 FR 55329, September 14, 2004, and by adding the following new airworthiness directive (AD): I 2006–15–04 Airbus: Amendment 39–14684. Docket No. FAA–2006–23690; Directorate Identifier 2004–NM–133–AD. Effective Date (a) This AD becomes effective August 24, 2006. (b) This AD supersedes ADs 2003–26–10 and 2004–18–13. Applicability (c) This AD applies to Airbus airplanes identified in Table 1 of this AD, certificated in any category. TABLE 1.—APPLICABILITY wwhite on PROD1PC76 with RULES Affected Airbus Airplanes (1) All Model A300 B2–1A, B2–1C, B2K–3C, and B2–203 airplanes. (2) All Model A300 B4–2C, B4–103, and B4– 203 airplanes. (3) All Model A300 B4–601, B4–603, B4– 620, and B4–622 airplanes. (4) All Model A300 B4–605R and B4–622R airplanes. (5) All Model A300 F4–605R and F4–622R airplanes. (6) All Model A300 C4–605R Variant F airplanes. Unsafe Condition (d) This AD results from a report of a large fatigue crack along the outboard flange of beam No. 4. We are issuing this AD to detect and correct fatigue cracks in the lower flanges of the left and right gantries 1 through VerDate Aug<31>2005 16:42 Jul 19, 2006 Jkt 208001 41111 Repair (g) Repair any cracking found during the inspection required by paragraph (f) of this AD before further flight, per a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; the Direction ´ ´ Generale de l’Aviation Civile (DGAC) (or its delegated agent); or the European Aviation Safety Agency (EASA) (or its delegate agent). Restatement of Requirements of AD 2004– 18–13 One-Time Inspection and Corrective Action (h) For Model A300 B2–1A, B2–1C, B2K– 3C, and B2–203 airplanes, and Model A300 B4–2C, B4–103, and B4–203 airplanes, on which Airbus Modification 3474 has been done: Prior to the accumulation of 16,300 total flight cycles, or within 500 flight cycles after July 30, 1998 (the effective date of AD 98–13–37), whichever occurs later, perform a one-time ultrasonic inspection for cracking of the gantry lower flanges in the MLG bay area, in accordance with Airbus AOT 53–11, dated October 13, 1997. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 Credit for Inspections Accomplished in Accordance With AOT (j) Any inspection accomplished before October 19, 2004, in accordance with Airbus AOT 53–11, dated October 13, 1997, is acceptable for compliance with the corresponding inspection specified in paragraph (i)(1) of this AD, for that inspection area only. Operators must do the applicable inspections in paragraph (i)(1) of this AD for the remaining inspection areas. New Requirements of This AD Repetitive Inspections (k) At the later of the applicable times specified in the ‘‘Threshold (FC)’’ and ‘‘Grace E:\FR\FM\20JYR1.SGM 20JYR1 41112 Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations Period’’ columns of Tables 1 and 2 in paragraph 1.E of the applicable service bulletin in Table 2 of this AD: Do an ultrasonic inspection or HFEC inspection, including rework of the pressure diaphragm, for cracks in the lower flanges of the left and right gantries 1 through 5 inclusive between FR47 and FR54, in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 2 of this AD. Repeat the inspection at the applicable times specified in the ‘‘Interval (FC)’’ column of Tables 1 and 2 in paragraph 1.E of the applicable service bulletin in Table 2 of this AD. Accomplishment of the initial inspection ends the inspections required by paragraphs (f), (h), and (i) of this AD. TABLE 2.—SERVICE BULLETINS Airbus Service Bulletin— For airplanes identified in— (1) A300–53–0379, Revision 01, dated October 4, 2005 ........................ (2) A300–53–6152, Revision 01, dated October 4, 2005 ........................ Paragraphs (c)(1) and (c)(2) of this AD inclusive. Paragraphs (c)(3) through (c)(6) of this AD inclusive. Corrective Action (l) If any crack is detected during any ultrasonic or HFEC inspection required by paragraph (k) of this AD, before further flight, repair the crack in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 2 of this AD, except as provided by paragraph (n) of this AD. Optional Terminating Actions (m) Accomplishment of the actions specified in Table 3 of this AD ends the repetitive inspections required by paragraph (k) of this AD. TABLE 3.—OPTIONAL TERMIANTING ACTIONS By doing all the actions in accordance with the Accomplishment Instructions of— Before or at the same time with— Reinforce— (1) The actions required by paragraph (k) of this AD and the action specified in paragraph (m)(2) of this AD. The flanges of the left and right portals 1 through 5 inclusive between FR47 and FR54 of the landing gear, including a rotating probe inspection for cracks of holes and repair if necessary. (2) The actions required by paragraph (k) of this AD. Portals 3, 4, and 5 of the plates/ skin. Repair of Certain Cracks (n) Where the applicable service bulletin recommends contacting Airbus for appropriate action: Before further flight, repair the crack in accordance with a method approved by the Manager, International Branch, ANM–116; the DGAC (or its delegated agent); or the European Aviation Safety Agency (EASA) (or its delegate agent). wwhite on PROD1PC76 with RULES Credit for Original Service Bulletins (o) Accomplishing the inspections and repair before the effective date of this AD in accordance with Airbus Service Bulletin A300–53–0379, dated May 9, 2005; or Airbus Service Bulletin A300–53–6152, dated May 9, 2005; as applicable; is acceptable for compliance with the corresponding requirements of paragraphs (k) and (l) of this AD. (p) Accomplishing the reinforcement before the effective date of this AD in accordance with Airbus Service Bulletin A300–53–0360, dated May 3, 2002; and Airbus Service Bulletin A300–53–6132, dated February 5, 2002; is acceptable for VerDate Aug<31>2005 16:42 Jul 19, 2006 Jkt 208001 Airbus Service Bulletin A300–53– 0380, dated August 5, 2005, except as provided by paragraph (n) of this AD. Paragraphs (c)(1) and (c)(2) of this AD inclusive. Airbus Service Bulletin A300–53– 6153, dated August 24, 2005, except as provided by paragraph (n) of this AD. Airbus Service Bulletin A300–53– 0360, Revision 01, dated May 31, 2006, except as provided by paragraph (n) of this AD. Airbus Service Bulletin A300–53– 6132, Revision 01, dated June 7, 2006, except as provided by paragraph (n) of this AD. Paragraphs (c)(3) through (c)(6) of this AD inclusive. compliance with the corresponding requirements of paragraph (m)(2) of this AD. No Inspection Report (q) Although the service bulletins in this AD specify to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (r)(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) 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 (s) French airworthiness directive F–2005– 091 R1, issued September 28, 2005, also addresses the subject of this AD. PO 00000 Frm 00018 Fmt 4700 For airplanes identified in— Sfmt 4700 Paragraphs (c)(1) and (c)(2) of this AD inclusive. Paragraphs (c)(3) through (c)(6) of this AD inclusive. Material Incorporated by Reference (t) You must use the applicable service bulletins identified in Table 4 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of the documents in Table 5 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On October 19, 2004 (69 FR 55329, September 14, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300–53–6128, excluding Appendix 01, dated March 5, 2001. (3) On January 22, 2004 (69 FR 867, January 7, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A300–53A0371, Revision 01, dated September 10, 2003; and Airbus All Operators Telex A300–53A6145, Revision 01, dated September 10, 2003. (4) On July 30, 1998 (63 FR 34589, June 25, 1998), the Director of the Federal Register approved the incorporation by reference of E:\FR\FM\20JYR1.SGM 20JYR1 41113 Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations Airbus All Operators Telex (AOT) 53–11, dated October 13, 1997. (5) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at https://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. TABLE 4.—ALL MATERIAL INCORPORATED BY REFERENCE Revision level Service Bulletin Airbus Airbus Airbus Airbus Airbus Airbus All Operators Telex A300–53A0371 .............................................................................................. All Operators Telex A300–53A6145 .............................................................................................. All Operators Telex (AOT) 53–11 .................................................................................................. Service Bulletin A300–53–0379, excluding Appendix 01 .............................................................. Service Bulletin A300–53–6128, excluding Appendix 01 .............................................................. Service Bulletin A300–53–6152, excluding Appendix 01 .............................................................. 01 ................ 01 ................ Original ........ 01 ................ Original ........ 01 ................ Date September 10, 2003. September 10, 2003. October 13, 1997. October 4, 2005. March 5, 2001. October 4, 2005. TABLE 5.—NEW MATERIAL INCORPORATED BY REFERENCE Service Bulletin Revision level Airbus Service Bulletin A300–53–0379, excluding Appendix 01 .............................................................. Airbus Service Bulletin A300–53–6152, excluding Appendix 01 .............................................................. 01 ................ 01 ................ Issued in Renton, Washington, on July 7, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–11412 Filed 7–19–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20731; Directorate Identifier 2004–NM–260–AD; Amendment 39–14685; AD 2006–15–05] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–200, –300, and –400 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. wwhite on PROD1PC76 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737–200, –300, and –400 series airplanes. This AD requires replacing the existing fueling float switch in the auxiliary fuel tank with a new, improved fueling float switch, installing a new liner system inside the float switch conduit, and performing related investigative and other specified actions. This AD results from reports of chafing of the direct-current-powered float switch wiring insulation in the center fuel tank. We are issuing this AD VerDate Aug<31>2005 16:42 Jul 19, 2006 Jkt 208001 to prevent contamination of the fueling float switch of the auxiliary fuel tank by moisture or fuel, and chafing of the float switch wiring against the float switch conduit in the fuel tank, which could present an ignition source inside the fuel tank that could cause a fire or explosion. This AD becomes effective August 24, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of August 24, 2006. ADDRESSES: You may examine the AD docket on the Internet at https:// 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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Sherry Vevea, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6514; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: DATES: Examining the Docket You may examine the airworthiness directive (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. PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 Date October 4, 2005. October 4, 2005. 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 would apply to certain Boeing Model 737–200, –300, and –400 series airplanes. That NPRM was published in the Federal Register on March 31, 2005 (70 FR 16445). That NPRM proposed to require replacing the existing fueling float switch in the auxiliary fuel tank with a new, improved fueling float switch, installing a new liner system inside the float switch conduit, and performing related investigative and other specified actions. New Relevant Service Information We have reviewed Boeing Service Bulletin 737–28A1192, Revision 2, dated April 27, 2006. (The NPRM refers to Boeing Service Bulletin 737– 28A1192, Revision 1, dated August 21, 2003, as the appropriate source of service information for the proposed actions.) Revision 2 adds a new Part B, which describes procedures for adding environmental protection to the splice and conduit. We have revised paragraph (f) of this AD to refer to Revision 2 as the appropriate source of service information for the actions required by that paragraph. Also, we have revised paragraph (h) of this AD to give credit for actions previously accomplished in E:\FR\FM\20JYR1.SGM 20JYR1

Agencies

[Federal Register Volume 71, Number 139 (Thursday, July 20, 2006)]
[Rules and Regulations]
[Pages 41109-41113]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-11412]

[[Page 41109]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23690; Directorate Identifier 2004-NM-133-AD;
Amendment 39-14684; AD 2006-15-04]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 B2 and B4 Series
Airplanes; and 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.

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SUMMARY: The FAA is superseding two existing airworthiness directives
(AD) that apply to certain Airbus Model A300 B2, A300 B4, and A300-600
series airplanes. One AD currently requires an inspection for cracks of
the lower outboard flange of gantry No. 4 in the main landing gear
(MLG) bay area, and repair if necessary. The other AD currently
requires, among other actions, repetitive inspections of the gantry
lower flanges, and repair if necessary. This new AD requires new
repetitive inspections for cracks in the lower flange of certain
gantries, and repair if necessary, which ends the existing inspection
requirements. This new AD also provides for optional terminating
actions for the new repetitive inspections. This AD results from a
report of a large fatigue crack along the outboard flange of beam No. 4
and a subsequent determination that existing inspections are
inadequate. We are issuing this AD to detect and correct fatigue cracks
in the lower flanges of gantries 1 through 5 inclusive in the MLG bay
area, which could result in reduced structural integrity of the
fuselage, and consequent rapid decompression of the airplane.

DATES: This AD becomes effective August 24, 2006.
The Director of the Federal Register approved the incorporation by
reference of Airbus Service Bulletin A300-53-0379, Revision 01,
excluding Appendix 01, dated October 4, 2005; and Airbus Service
Bulletin A300-53-6152, Revision 01, excluding Appendix 01, dated
October 4, 2005; listed in the AD as of August 24, 2006.
On October 19, 2004 (69 FR 55329, September 14, 2004), the Director
of the Federal Register approved the incorporation by reference of
Airbus Service Bulletin A300-53-6128, excluding Appendix 01, dated
March 5, 2001.
On January 22, 2004 (69 FR 867, January 7, 2004), the Director of
the Federal Register approved the incorporation by reference of Airbus
All Operators Telex A300-53A0371, Revision 01, dated September 10,
2003; and Airbus All Operators Telex A300-53A6145, Revision 01, dated
September 10, 2003.
On July 30, 1998 (63 FR 34589, June 25, 1998), the Director of the
Federal Register approved the incorporation by reference of Airbus All
Operators Telex (AOT) 53-11, dated October 13, 1997.

ADDRESSES: You may examine the AD docket on the Internet at https://
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: Thomas Stafford, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; 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 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 street address stated in the ADDRESSES section.

Discussion

The FAA issued a supplemental notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an AD that supersedes AD 2003-26-10,
amendment 39-13408 (69 FR 867, January 7, 2004), and AD 2004-18-13,
amendment 39-13792 (69 FR 55329, dated September 14, 2004). The
existing ADs apply to certain Airbus Model A300 B2 and A300 B4 series
airplanes, and 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 supplemental NPRM was published in the
Federal Register on May 17, 2006 (71 FR 28615). That supplemental NPRM
proposed to continue to require an inspection for cracks of the lower
outboard flange of gantry No. 4 in the main landing gear (MLG) bay
area, and repair if necessary. That supplemental NPRM also proposed to
continue to require repetitive inspections of the gantry lower flanges,
and repair if necessary. In addition, that supplemental NPRM proposed
to require new repetitive inspections for cracks in the lower flange of
certain gantries, and repair if necessary, which ends the existing
inspection requirements. That supplemental NPRM also proposed optional
terminating actions for the new repetitive inspections. That
supplemental also revised the original NPRM by including additional
airplanes that were excluded from the applicability.

Comments

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

Request To Refer to Latest Service Bulletin

Airbus states that it has issued Service Bulletins A300-53-0360,
Revision 01, dated May 31, 2006; and A300-53-6132, Revision 01, dated
June 7, 2006; whose original issues are listed in paragraph (m)(2) of
the supplemental NPRM.
We infer that Airbus is requesting that Revision 01 of Service
Bulletins A300-53-0360 and A300-53-6132 be referred to in paragraph
(m)(2) of the AD. We agree. We have reviewed Revision 01 of both
service bulletins. Revision 01 of both service bulletins revises three
illustrations. The reinforcement procedures in Revision 01 of both
service bulletins are identical to that in the original issues of the
service bulletins. No additional work is required for airplanes
modified in accordance with the original issues of the service
bulletins. Therefore, we have revised paragraph (m)(2) of this AD to
refer to Revision 01 of both service bulletins and added a new
paragraph (p) to the AD (subsequent paragraphs have been redesignated)
to give credit for accomplishing the original issues of both service
bulletins.

Explanation of Change Made to the Supplemental NPRM

Paragraphs (g), (i)(4), and (n) of the supplemental NPRM specify
making repairs using a method approved by either the FAA or the
Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its
delegated agent). The European

[[Page 41110]]

Aviation Safety Agency (EASA) has assumed responsibility for the
airplane modes that would be subject to this AD. Therefore, we have
revised those paragraphs of this AD to specify making repairs using a
method approved by either the FAA, the DGAC (or its delegated agent),
or the EASA (or its delegated agent).

Conclusion

We have carefully reviewed the available data, including the
comment that has been received, and determined that air safety and the
public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

This AD will affect about 165 airplanes of U.S. registry. The
following table provides the estimated costs for U.S. operators to
comply with this AD. Not all actions must be completed on all
airplanes.

Estimated Costs for Required Actions
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per airplane registered Fleet cost
rate per hour airplanes
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
One-time inspection (required by AD 1 $80 None...................... $80...................... 23 $1,840.
2003-26-10).
One-time inspection (required by AD 4 80 None...................... $320..................... 43 $13,760.
2004-18-13).
Repetitive inspections (required by AD 12 80 None...................... $960, per inspection 78 $74,880, per inspection cycle.
2004-18-13). cycle.
Repetitive inspections (new proposed 16 80 None...................... $1,280, per inspection 78 $99,840, per inspection cycle.
actions). cycle.
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------

Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
Number of
Average Cost per U.S.-
Optional action Work hours labor rate Parts airplane registered
per hour airplanes
----------------------------------------------------------------------------------------------------------------
Reinforcement specified in 807.............. $80 Between $87,100 Between $151,660 23
Airbus Service Bulletin A300- and $121,560 and $186,120
53-0380, dated August 5, 2005. depending on kit depending on
purchased. airplane
configuration.
Reinforcement specified in 807.............. 80 Between $82,460 Between $147,020 120
Airbus Service Bulletin A300- and $87,070 and $151,630
53-6153, dated August 24, depending on kit depending on
2005. purchased. airplane
configuration.
Reinforcement specified in Between 24 and 80 Between $250 and Between $2,170 23
Airbus Service Bulletin A300- 128 depending on $1,000 depending and $11,240
53-0360, Revision 01, dated airplane on kit purchased. depending on
May 31, 2002. configuration. airplane
configuration.
Reinforcement specified in 109.............. 80 Between $260 and Between $8,980 120
Airbus Service Bulletin A300- $950 depending and $9,670
53-6132, Revision 01, dated on kit purchased. depending on
June 7, 2006. airplane
configuration.
----------------------------------------------------------------------------------------------------------------

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:
(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

[[Page 41111]]

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 amendments 39-13408 (69 FR 867, January 7, 2004) and 39-13792
(69 FR 55329, September 14, 2004, and by adding the following new
airworthiness directive (AD):

2006-15-04 Airbus: Amendment 39-14684. Docket No. FAA-2006-23690;
Directorate Identifier 2004-NM-133-AD.

Effective Date

(a) This AD becomes effective August 24, 2006.
(b) This AD supersedes ADs 2003-26-10 and 2004-18-13.

Applicability

Table 1.--Applicability
------------------------------------------------------------------------

-------------------------------------------------------------------------
Affected Airbus Airplanes

(1) All Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes.
(2) All Model A300 B4-2C, B4-103, and B4-203 airplanes.
(3) All Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(4) All Model A300 B4-605R and B4-622R airplanes.
(5) All Model A300 F4-605R and F4-622R airplanes.
(6) All Model A300 C4-605R Variant F airplanes.
------------------------------------------------------------------------

Unsafe Condition

(d) This AD results from a report of a large fatigue crack along
the outboard flange of beam No. 4. We are issuing this AD to detect
and correct fatigue cracks in the lower flanges of the left and
right gantries 1 through 5 inclusive in the main landing gear (MLG)
bay area, which could result in reduced structural integrity of the
fuselage, and consequent rapid decompression of the airplane.

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.

Restatement of Requirements of AD 2003-26-10

One-Time Inspection

(f) For airplanes on which Airbus Modification 10147 has not
been done: At the later of the times specified in paragraphs (f)(1)
and (f)(2) of this AD: Do a one-time detailed inspection for
cracking of the lower outboard flange of gantry No. 4 in the MLG bay
area per paragraph 4.2.1 of Airbus All Operators Telex (AOT) A300-
53A0371, Revision 01 (for Model A300 B2 and B4 series airplanes); or
AOT A300-53A6145, Revision 01 (for Model A300-600 series airplanes);
both dated September 10, 2003; as applicable.
(1) Before the accumulation of 8,000 total flight cycles since
the date of issuance of the original Airworthiness Certificate or
the date of issuance of the Export Certificate of Airworthiness,
whichever is first.
(2) Within 30 days after January 22, 2004 (the effective date AD
2003-26-10).

Note 1: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''

Repair

(g) Repair any cracking found during the inspection required by
paragraph (f) of this AD before further flight, per a method
approved by either the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated
agent); or the European Aviation Safety Agency (EASA) (or its
delegate agent).

Restatement of Requirements of AD 2004-18-13

One-Time Inspection and Corrective Action

(h) For Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes,
and Model A300 B4-2C, B4-103, and B4-203 airplanes, on which Airbus
Modification 3474 has been done: Prior to the accumulation of 16,300
total flight cycles, or within 500 flight cycles after July 30, 1998
(the effective date of AD 98-13-37), whichever occurs later, perform
a one-time ultrasonic inspection for cracking of the gantry lower
flanges in the MLG bay area, in accordance with Airbus AOT 53-11,
dated October 13, 1997.
(1) If any cracking is detected, prior to further flight, repair
in accordance with the AOT.
(2) If no cracking is detected, no further action is required by
this paragraph.

Repetitive Inspections and Corrective Actions

(i) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622R, C4-
605R Variant F airplanes, and F4-605R airplanes, on which Airbus
Modification 12169 has not been done in production: Perform the
requirements of paragraphs (i)(1), (i)(2), (i)(3), and (i)(4) of
this AD, in accordance with Airbus Service Bulletin A300-53-6128,
dated March 5, 2001.
(1) At the later of the times specified in paragraphs (i)(1)(i)
and (i)(1)(ii) of this AD, perform initial ultrasonic inspections or
high-frequency eddy current (HFEC) inspections for cracks of the
lower flanges of gantries 3, 4, and 5 between fuselage frames FR47
and FR54, in accordance with the Accomplishment Instructions,
including the Synoptic Chart contained in Figure 2, sheets 1 through
5 inclusive, of the service bulletin.
(i) In accordance with the thresholds specified in the Synoptic
Chart contained in Figure 2, sheets 1 through 5 inclusive, of the
service bulletin; or
(ii) Within 200 flight cycles after October 19, 2004 (the
effective date AD 2004-18-13).
(2) Perform repetitive ultrasonic inspections or high-frequency
eddy current inspections for cracks of the lower flanges of gantries
3, 4, and 5 between fuselage frames FR47 and FR54, in accordance
with the thresholds and Accomplishment Instructions, including the
Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive,
of the service bulletin.
(3) Perform repairs and reinforcements, in accordance with the
thresholds and the Accomplishment Instructions, including the
Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive,
of the service bulletin, except as specified in paragraph (i)(4) of
this AD.
(4) If a new crack is found during any action required by
paragraph (i)(1), (i)(2) or (i)(3) of this AD and the Synoptic Chart
contained in Figure 2, sheets 1 through 5 inclusive, of the service
bulletin specifies to contact Airbus for appropriate action: Prior
to further flight, repair per a method approved by the Manager,
International Branch, ANM-116; the DGAC (or its delegated agent); or
the European Aviation Safety Agency (EASA) (or its delegate agent).

Credit for Inspections Accomplished in Accordance With AOT

(j) Any inspection accomplished before October 19, 2004, in
accordance with Airbus AOT 53-11, dated October 13, 1997, is
acceptable for compliance with the corresponding inspection
specified in paragraph (i)(1) of this AD, for that inspection area
only. Operators must do the applicable inspections in paragraph
(i)(1) of this AD for the remaining inspection areas.

New Requirements of This AD

Repetitive Inspections

(k) At the later of the applicable times specified in the
``Threshold (FC)'' and ``Grace

[[Page 41112]]

Period'' columns of Tables 1 and 2 in paragraph 1.E of the
applicable service bulletin in Table 2 of this AD: Do an ultrasonic
inspection or HFEC inspection, including rework of the pressure
diaphragm, for cracks in the lower flanges of the left and right
gantries 1 through 5 inclusive between FR47 and FR54, in accordance
with the Accomplishment Instructions of the applicable service
bulletin in Table 2 of this AD. Repeat the inspection at the
applicable times specified in the ``Interval (FC)'' column of Tables
1 and 2 in paragraph 1.E of the applicable service bulletin in Table
2 of this AD. Accomplishment of the initial inspection ends the
inspections required by paragraphs (f), (h), and (i) of this AD.

Table 2.--Service Bulletins
------------------------------------------------------------------------
Airbus Service Bulletin-- For airplanes identified in--
------------------------------------------------------------------------
(1) A300-53-0379, Revision 01, dated Paragraphs (c)(1) and (c)(2) of
October 4, 2005. this AD inclusive.
(2) A300-53-6152, Revision 01, dated Paragraphs (c)(3) through
October 4, 2005. (c)(6) of this AD inclusive.
------------------------------------------------------------------------

Corrective Action

(l) If any crack is detected during any ultrasonic or HFEC
inspection required by paragraph (k) of this AD, before further
flight, repair the crack in accordance with the Accomplishment
Instructions of the applicable service bulletin in Table 2 of this
AD, except as provided by paragraph (n) of this AD.

Optional Terminating Actions

(m) Accomplishment of the actions specified in Table 3 of this
AD ends the repetitive inspections required by paragraph (k) of this
AD.

Table 3.--Optional Termianting Actions
----------------------------------------------------------------------------------------------------------------
By doing all the
actions in accordance For airplanes
Before or at the same time with-- Reinforce-- with the Accomplishment identified in--
Instructions of--
----------------------------------------------------------------------------------------------------------------
(1) The actions required by paragraph The flanges of the left Airbus Service Bulletin Paragraphs (c)(1) and
(k) of this AD and the action and right portals 1 A300-53-0380, dated (c)(2) of this AD
specified in paragraph (m)(2) of through 5 inclusive August 5, 2005, except inclusive.
this AD. between FR47 and FR54 as provided by
of the landing gear, paragraph (n) of this
including a rotating AD.
probe inspection for
cracks of holes and
repair if necessary.
Airbus Service Bulletin Paragraphs (c)(3)
A300-53-6153, dated through (c)(6) of this
August 24, 2005, AD inclusive.
except as provided by
paragraph (n) of this
AD.
(2) The actions required by paragraph Portals 3, 4, and 5 of Airbus Service Bulletin Paragraphs (c)(1) and
(k) of this AD. the plates/skin. A300-53-0360, Revision (c)(2) of this AD
01, dated May 31, inclusive.
2006, except as
provided by paragraph
(n) of this AD.
Airbus Service Bulletin Paragraphs (c)(3)
A300-53-6132, Revision through (c)(6) of this
01, dated June 7, AD inclusive.
2006, except as
provided by paragraph
(n) of this AD.
----------------------------------------------------------------------------------------------------------------

Repair of Certain Cracks

(n) Where the applicable service bulletin recommends contacting
Airbus for appropriate action: Before further flight, repair the
crack in accordance with a method approved by the Manager,
International Branch, ANM-116; the DGAC (or its delegated agent); or
the European Aviation Safety Agency (EASA) (or its delegate agent).

Credit for Original Service Bulletins

(o) Accomplishing the inspections and repair before the
effective date of this AD in accordance with Airbus Service Bulletin
A300-53-0379, dated May 9, 2005; or Airbus Service Bulletin A300-53-
6152, dated May 9, 2005; as applicable; is acceptable for compliance
with the corresponding requirements of paragraphs (k) and (l) of
this AD.
(p) Accomplishing the reinforcement before the effective date of
this AD in accordance with Airbus Service Bulletin A300-53-0360,
dated May 3, 2002; and Airbus Service Bulletin A300-53-6132, dated
February 5, 2002; is acceptable for compliance with the
corresponding requirements of paragraph (m)(2) of this AD.

No Inspection Report

(q) Although the service bulletins in this AD specify to submit
certain information to the manufacturer, this AD does not include
that requirement.

Alternative Methods of Compliance (AMOCs)

(r)(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) 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

(s) French airworthiness directive F-2005-091 R1, issued
September 28, 2005, also addresses the subject of this AD.

Material Incorporated by Reference

(t) You must use the applicable service bulletins identified in
Table 4 of this AD to perform the actions that are required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of the documents in Table 5 of this AD in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On October 19, 2004 (69 FR 55329, September 14, 2004), the
Director of the Federal Register approved the incorporation by
reference of Airbus Service Bulletin A300-53-6128, excluding
Appendix 01, dated March 5, 2001.
(3) On January 22, 2004 (69 FR 867, January 7, 2004), the
Director of the Federal Register approved the incorporation by
reference of Airbus All Operators Telex A300-53A0371, Revision 01,
dated September 10, 2003; and Airbus All Operators Telex A300-
53A6145, Revision 01, dated September 10, 2003.
(4) On July 30, 1998 (63 FR 34589, June 25, 1998), the Director
of the Federal Register approved the incorporation by reference of

[[Page 41113]]

Airbus All Operators Telex (AOT) 53-11, dated October 13, 1997.
(5) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France, for a copy of this service information. You may
review copies at the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.

Table 4.--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
Airbus All Operators Telex A300-53A0371. 01......................... September 10, 2003.
Airbus All Operators Telex A300-53A6145. 01......................... September 10, 2003.
Airbus All Operators Telex (AOT) 53-11.. Original................... October 13, 1997.
Airbus Service Bulletin A300-53-0379, 01......................... October 4, 2005.
excluding Appendix 01.
Airbus Service Bulletin A300-53-6128, Original................... March 5, 2001.
excluding Appendix 01.
Airbus Service Bulletin A300-53-6152, 01......................... October 4, 2005.
excluding Appendix 01.
----------------------------------------------------------------------------------------------------------------

Table 5.--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A300-53-0379, 01......................... October 4, 2005.
excluding Appendix 01.
Airbus Service Bulletin A300-53-6152, 01......................... October 4, 2005.
excluding Appendix 01.
----------------------------------------------------------------------------------------------------------------

Issued in Renton, Washington, on July 7, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-11412 Filed 7-19-06; 8:45 am]
BILLING CODE 4910-13-P

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