Airworthiness Directives; Airbus Airplanes, 64781-64785 [2011-26257]

Download as PDF 64781 Rules and Regulations Federal Register Vol. 76, No. 202 Wednesday, October 19, 2011 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0264; Directorate Identifier 2009–NM–244–AD; Amendment 39–16837; AD 2011–21–14] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) that applies to certain Model A300 B4– 600, B4–600R, and F4–600R series airplanes, and Model C4–605R Variant F airplanes (collectively called A300–600 series airplanes). This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: [T]he FAA has published SFAR 88 (Special Federal Aviation Regulation 88).* * * Under this regulation, all holders of type certificates for passenger transport aeroplanes * * * are required to conduct a design review against explosion risks. The replacement of some types of P-clips and improvement of the electrical bonding of the equipment in the fuel tanks [were] are rendered mandatory. * * * sroberts on DSK5SPTVN1PROD with RULES * * * * * Subsequently, an internal review * * * led * * * to * * * an additional check [for blue coat] of the bonding points in the centre tank. * * * More recently, another internal review [introduced] additional work [installing bonding points] for aeroplanes under Configuration 03 * * * and additional work [bonding the fuel jettison system—blanking VerDate Mar<15>2010 15:51 Oct 18, 2011 Jkt 223001 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on April 6, 2011 (76 FR 18960), and proposed to supersede AD 2008– 03–04, Amendment 39–15353 (73 FR 5731, January 31, 2008). That NPRM (76 FR 18960, April 6, 2011) proposed to correct an unsafe condition for the specified products. The MCAI states: more, or a payload capacity of 3,402 kg (7,500 lbs) or more which have received their certification since 01 January 1958, are required to conduct a design review against explosion risks. The replacement of some types of P-clips and improvement of the electrical bonding of the equipment in the fuel tasks are rendered mandatory by this AD. Initially, EASA AD 2006–0325, which addressed the same unsafe condition, also applied to A300–600 aeroplanes. Airbus subsequently introduced additional work at Revision 1 of SB A300–28–6064 [dated April 3, 2007] applicable to A300–600 aeroplanes. As a result, EASA AD 2006–0325 was revised to remove A300–600 aeroplanes from the applicability, and concurrently EASA AD 2007–0233 was issued, applicable to A300– 600 aeroplanes. Unfortunately, the ‘Applicability’ section of EASA AD 2007– 0233 was not correctly defined, erroneously deleting one modification in the combination that would exclude aeroplanes from having to comply. Consequently, the AD 2007–0283 was issued, requiring the same actions as AD 2007–0233, which was superseded, but expanded the group of aeroplanes to which AD 2007–0283 applied [FAA AD 2008–03–04 (73 FR 5731, January 31, 2008) corresponds with EASA AD 2007–0283]. Subsequently, an internal review of Airbus SB A300–28–6064 led the manufacturer to correct the figures of the SB. In particular, an additional check [for blue coat] of the bonding points in the centre tank was introduced in Revision 03 of Airbus SB A300–28–6064 [dated December 15, 2008], prompting EASA to issue AD 2009–0143. More recently, another internal review of Airbus SB A300–28–6064 again resulted in corrected figures in the SB. Additional work on the center tank [installing bonding points] for aeroplanes under Configuration 03 (as defined in the SB [Service Bulletin A300–28– 6064, Revision 04, dated August 24, 2009]) and additional work [bonding the fuel jettison system—blanking plates] on the wing tanks for aeroplanes under Configuration 07 have been introduced in Revision 04 of Airbus SB A300–28–6064 [dated August 24, 2009]. For the reason described above, this new AD retains the requirements of EASA AD 2009–0143, which is superseded, and requires the additional work introduced in Revision 04 of Airbus SB A300–28–6064 [dated August 24, 2009]. [T]he FAA has published SFAR 88 (Special Federal Aviation Regulation 88). In their letters referenced 04/00/02/07/01–L296, dated 04 March 2002, and 04/00/02/07/03– L024, dated 03 February 2003, the JAA recommended the application of a similar regulation to the National Aviation Authorities (NAA). Under this regulation, all holders of type certificates for passenger transport aeroplanes with either a passenger capacity of 30 or The unsafe condition is damage to wiring in the wing, center, and trim fuel tanks, due to failed P-clips used for retaining the wiring and pipes, which could result in a possible fuel ignition source in the wing, center, or trim fuel tanks. The required actions also include checking the electrical bonding points of certain equipment in the center fuel tank for the presence of a blue coat and plates] on the wing tanks for aeroplanes under Configuration 07. * * * The unsafe condition is damage to wiring in the wing, center, and trim fuel tanks, due to failed P-clips used for retaining the wiring and pipes, which could result in a possible fuel ignition source in the wing, center, or trim fuel tanks. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective November 23, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 23, 2011. The Director of the Federal Register approved the incorporation by reference of certain other publications as of March 6, 2008 (73 FR 5731, January 31, 2008). ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 E:\FR\FM\19OCR1.SGM 19OCR1 64782 Federal Register / Vol. 76, No. 202 / Wednesday, October 19, 2011 / Rules and Regulations doing related investigative and corrective actions if necessary. The related investigative action is to measure the electrical resistance between the equipment and structure, if a blue coat is not present. The corrective action is to electrically bond the equipment, if the measured resistance is greater than 10 milliohms. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received. sroberts on DSK5SPTVN1PROD with RULES Request for Extension of Compliance Time UPS and FedEx requested an extension to the 8-month compliance time specified in the NPRM (76 FR 18960, dated April 6, 2011) in order to accomplish the additional actions. FedEx requested that the compliance time for the additional actions be at the latest of the 40-month compliance time specified in AD 2008–03–04, Amendment 39–15353 (73 FR 5731, January 31, 2008), any alternative methods of compliance that extend that compliance time or within 12 months after the effective date of the new AD. UPS requested that the compliance time be extended to 60 months. UPS stated that the two additional bonding points specified in the NPRM are no more unsafe than the original 264 bonding points required in AD 2008–03–04. UPS noted that it schedules tank entry checks at 60 months and that the original issue of the service information allowed for a 60-month compliance time. We agree with extending the compliance time and have determined that extending the compliance time to 30 months is appropriate. In developing an appropriate compliance time for this action, we considered the safety implications, parts availability, and normal maintenance schedules for the timely accomplishment of the modification. In consideration of these items, we have determined that a 30month compliance time will ensure an acceptable level of safety and allow the modifications to be done during scheduled maintenance intervals for most affected operators. We have also coordinated with European Aviation Safety Agency (EASA) on this issue. We have changed the compliance time in paragraph (h) of this AD to ‘‘within 30 months after the effective date of this AD.’’ VerDate Mar<15>2010 15:51 Oct 18, 2011 Jkt 223001 Request for Change to Cost of Compliance Work-Hours FedEx stated that they averaged 800 work-hours versus the 632 work-hours listed in the NPRM (76 FR 18960, dated April 6, 2011) to accomplish the existing modifications. FedEx also stated that 9 work-hours, as specified for the additional actions, may be adequate if done in conjunction with the other modifications; however, additional work-hours will be required for airplanes that have been previously been modified. We infer that FedEx is requesting that we increase the work-hours estimate to accomplish the existing and new modifications. We do not agree to revise the work-hours. Work-hours may vary among operators. Our estimate is based on the information provided in the relevant service information. We have not changed this AD in this regard. Request for Material Substitutions FedEx requested that we add wording to the NPRM (76 FR 18960, dated April 6, 2011) that material substitutions supplied by Airbus are approved for use and do not require an alternative method of compliance (AMOC). FedEx stated that the kits specified in Airbus Service Bulletins A300–28–6064, Revision 01, dated April 3, 2007; A300– 28–6068, dated July 20, 2005; and A300–28–6077, Revision 01, dated October 26, 2006; might contain parts that are not listed in the kit description specified in the service information. We do not agree with the request to revise the AD to include wording that material substitutions are approved for use. Airbus Service Bulletins A300–28– 6064, Revision 01, dated April 3, 2007; A300–28–6068, dated July 20, 2005; and A300–28–6077, Revision 01, dated October 26, 2006; contain language in the ‘‘Standard Practices’’ section of paragraph 3.A. ‘‘General’’ of the Accomplishment Instructions that specifies which alternative materials are allowed. We have not changed this AD in this regard. Request To Update Service Information to Latest Revision FedEx stated that Airbus has issued Mandatory Service Bulletin A300–28– 6064, Revision 05, dated September 27, 2010, and requested that we update our references in the NPRM (76 FR 18960, dated April 6, 2011). We agree with the request and have updated the references in paragraphs (c)(1), (g)(4), and (h) of this AD to include Airbus Mandatory Service Bulletin A300–28–6064, Revision 05, dated September 27, 2010. Airbus PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Mandatory Service Bulletin A300–28– 6064, Revision 05, dated September 27, 2010, provides clarifications of the actions and materials but contains no substantive changes. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect about 125 products of U.S. registry. The actions that are required by AD 2008–03–04 Amendment 39–15353 (73 FR 5731, January 31, 2008) and retained in this AD take about 632 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $6,870 per product. Based on these figures, the estimated cost of the currently required actions is $60,590 per product. We estimate that it will take about 9 work-hours per product to comply with the new basic requirements of this AD. The average labor rate is $85 per workhour. Required parts will cost about $100 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these parts. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $108,125, or $865 per product. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue E:\FR\FM\19OCR1.SGM 19OCR1 Federal Register / Vol. 76, No. 202 / Wednesday, October 19, 2011 / Rules and Regulations 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 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 this AD: 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 AD and placed it in the AD docket. sroberts on DSK5SPTVN1PROD with RULES Adoption of the Amendment Reason Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: (e) The mandatory continuing airworthiness information (MCAI) states: [T]he FAA has published SFAR 88 (Special Federal Aviation Regulation 88). * * * Under this regulation, all holders of type certificates for passenger transport aeroplanes * * * are required to conduct a design review against explosion risks. The replacement of some types of P-clips and improvement of the electrical bonding of the equipment in the fuel tanks [were] are rendered mandatory * * *. 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 FAA amends § 39.13 by removing Amendment 39–15353 (73 FR 5731, January 31, 2008) and adding the following new AD: ■ 2011–21–14 Airbus: Amendment 39–16837. Docket No. FAA–2011–0264; Directorate Identifier 2009–NM–244–AD. Effective Date (a) This airworthiness directive (AD) becomes effective November 23, 2011. Affected ADs (b) This AD supersedes AD 2008–03–04, Amendment 39–15353 (73 FR 5731, January 31, 2008). List of Subjects in 14 CFR Part 39 Applicability (c) This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD. (1) Airbus Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes (without trim tank), all serial numbers, certificated in any category, except airplanes on which Airbus Modifications 12226, 12365, 12490, and 12308 have been incorporated in production, or on which the service bulletins listed in paragraphs (c)(1)(i) and (c)(1)(ii) of this AD have been performed in service. (i) Airbus Mandatory Service Bulletin A300–28–6064, Revision 04, dated August 24, 2009; or Revision 05, dated September 27, 2010. (ii) Airbus Service Bulletin A300–28–6068, dated July 20, 2005. (2) Airbus Model A300 B4–605R, B4–622R, F4–605R, and F4–622R airplanes and A300 C4–605R Variant F airplanes (fitted with a trim tank), all serial numbers, certificated in any category, except airplanes on which Airbus Modifications 12226, 12365, 12490, 12308, 12294, and 12476 have been incorporated in production, or on which the service bulletins listed in paragraphs (c)(2)(i), (c)(2)(ii), and (c)(2)(iii) of this AD have been performed in service. (i) Airbus Mandatory Service Bulletin A300–28–6064, Revision 03, dated December 15, 2008. (ii) Airbus Service Bulletin A300–28–6068, dated July 20, 2005. (iii) Airbus Service Bulletin A300–28– 6077, dated July 25, 2005; or Revision 01, dated October 26, 2006. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Subject (d) Air Transport Association (ATA) of America Code 28: Fuel. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM (76 FR 18960, dated April 6, 2011), the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. VerDate Mar<15>2010 15:51 Oct 18, 2011 Jkt 223001 64783 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 * * * * Subsequently, an internal review * * * led * * * to * * * an additional check [for blue coat] of the bonding points in the centre tank. * * * More recently, another internal review [introduced] additional work [installing bonding points] for aeroplanes under Configuration 03 * * * and additional work [bonding the fuel jettison system—blanking plates] on the wing tanks for aeroplanes under Configuration 07 * * *. The unsafe condition is damage to wiring in the wing, center, and trim fuel tanks, due to failed P-clips used for retaining the wiring and pipes, which could result in a possible fuel ignition source in the wing, center, or trim fuel tanks. Compliance (f) 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 2008– 03–04, Amendment 39–15353 (73 FR 5731, January 31, 2008) With Revised Service Information Actions and Compliance (g) For airplanes identified in paragraphs (g)(1) and (g)(2) of this AD: Within 40 months after March 6, 2008 (the effective date of AD 2008–03–04, Amendment 39–15353 (73 FR 5731, January 31, 2008)), unless already done, do the applicable actions required by paragraphs (g)(3), (g)(4), and (g)(5) of this AD. (1) Airbus Model A300 B4–600 series airplanes (without trim tank), all serial numbers, except airplanes on which Airbus Modifications 12226, 12365, 12490, and 12308 have been incorporated in production, or Airbus Service Bulletins A300–28–6064, Revision 01, dated April 3, 2007; and A300– 28–6068, dated July 20, 2005; have been performed in service. (2) Airbus Model A300 B4–600R, A300 C4– 600R, and A300 F4–600R series airplanes (fitted with a trim tank), all serial numbers, except airplanes on which Airbus Modifications 12226, 12365, 12490, 12308, 12294, and 12476 have been incorporated in production, or on which the service bulletins listed in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD have been performed in service. (i) Airbus Service Bulletin A300–28–6064, Revision 01, dated April 3, 2007. (ii) Airbus Service Bulletin A300–28–6068, dated July 20, 2005. E:\FR\FM\19OCR1.SGM 19OCR1 64784 Federal Register / Vol. 76, No. 202 / Wednesday, October 19, 2011 / Rules and Regulations (iii) Airbus Service Bulletin A300–28– 6077, dated July 25, 2005; or A300–28–6077, Revision 01, dated October 26, 2006. (3) Remove NSA5516–XXND or NSA5516– XXNJ type P-clips, used in the wing and center fuel tanks to retain wiring and pipes, and replace them by NSA5516–XXNF type Pclips in accordance with the instructions of Airbus Service Bulletin A300–28–6068, dated July 20, 2005. (4) Check the electrical bonding points in the center tank and do all applicable related investigative and corrective actions, and install additional bonding leads and electrical bonding points in the wing and center fuel tanks in accordance with the instructions of Airbus Service Bulletin A300– 28–6064, Revision 01, dated April 3, 2007; Airbus Mandatory Service Bulletin A300–28– 6064, Revision 02, dated March 10, 2008; Airbus Mandatory Service Bulletin A300–28– 6064, Revision 03, dated December 15, 2008; Airbus Mandatory Service Bulletin A300–28– 6064, Revision 04, dated August 24, 2009; or Airbus Mandatory Service Bulletin A300–28– 6064, Revision 05, dated September 27, 2010. Do all applicable related investigative and corrective actions before further flight. As of the effective date of this AD, only use Airbus Mandatory Service Bulletin A300–28–6064, Revision 05, dated September 27, 2010. (5) For airplanes fitted with a trim tank, in addition to the actions defined in paragraphs (g)(3) and (g)(4) of this AD, install bonding leads and electrical bonding points in the trim tanks, in accordance with the instructions of Airbus Service Bulletin A300– 28–6077, Revision 01, dated October 26, 2006. (6) Actions done before March 6, 2008, in accordance with Airbus Service Bulletin A300–28–6064, dated July 28, 2005, for aircraft under configuration 05, as defined in Airbus Service Bulletin A300–28–6064, dated July 28, 2005, are considered acceptable for compliance with the requirements of paragraph (g)(4) of this AD. (7) Actions done before March 6, 2008, in accordance with Airbus Service Bulletin A300–28–6077, dated July 25, 2005, for aircraft under configuration 05, as defined in Airbus Service Bulletin A300–28–6077, dated July 25, 2005, are considered acceptable for compliance with the requirements of paragraph (g)(5) of this AD. sroberts on DSK5SPTVN1PROD with RULES New Requirments of This AD Additional Actions (h) Within 30 months after the effective date of this AD, do the applicable actions required by paragraphs (h)(1), (h)(2), and (h)(3) of this AD. (1) For airplanes that have been modified before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 28–6064, dated July 28, 2005, or Revision 01, dated April 3, 2007; or Airbus Mandatory Service Bulletin A300–28–6064, Revision 02, dated March 10, 2008: Do the additional work on the center tank specified in Airbus Mandatory Service Bulletin A300–28–6064, Revision 03, dated December 15, 2008 (i.e., a check for blue coat at additional bonding points and all applicable related investigative and corrective actions), in accordance with VerDate Mar<15>2010 15:51 Oct 18, 2011 Jkt 223001 the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–28–6064, Revision 03, dated December 15, 2008; Revision 04, dated August 24, 2009; or Revision 05, dated September 27, 2010. Do all applicable related investigative and corrective actions before further flight. (2) For configuration 03 airplanes, as defined in Airbus Mandatory Service Bulletin A300–28–6064, Revision 04, dated August 24, 2009; or Revision 05, dated September 27, 2010; that have been modified before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 28–6064, Revision 01, dated April 3, 2007; or Airbus Mandatory Service Bulletin A300–28– 6064, Revision 02, dated March 10, 2008, or Revision 03, dated December 15, 2008: Do the additional work on the center tank (i.e., install bonding points), in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–28–6064, Revision 04, dated August 24, 2009; or Revision 05, dated September 27, 2010. (3) For configuration 07 airplanes, as defined in Airbus Mandatory Service Bulletin A300–28–6064, Revision 04, dated August 24, 2009; or Revision 05, dated September 27, 2010; that have been modified before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 28–6064, dated July 28, 2005; or Revision 01, dated April 3, 2007; or Airbus Mandatory Service Bulletin A300–28–6064, Revision 02, dated March 10, 2008, or Revision 03, dated December 15, 2008: Do the additional work on the wing tanks (i.e., bond the fuel jettison system—blanking plates), in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–28–6064, Revision 04, dated August 24, 2009; or Revision 05, dated September 27, 2010. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: The MCAI provides a compliance time of 8 months to do the actions specified in paragraph (h) of this AD. This AD requires that the actions specified in paragraph (h) of this AD be done within 30 months. Other FAA AD Provisions (i) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. AMOCs approved previously in accordance with AD 2008–03–04, Amendment 39–15353 (73 FR PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 5731, January 31, 2008), are approved as AMOCs for the corresponding provisions of this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. Related Information (j) Refer to MCAI EASA Airworthiness Directive 2010–0074, dated April 16, 2010, and the following service information, for related information. (1) Airbus Mandatory Service Bulletin A300–28–6064, Revision 03, dated December 15, 2008. (2) Airbus Mandatory Service Bulletin A300–28–6064, Revision 04, dated August 24, 2009. (3) Airbus Mandatory Service Bulletin A300–28–6064, Revision 05, dated September 27, 2010. (4) Airbus Service Bulletin A300–28–6068, dated July 20, 2005. (5) Airbus Service Bulletin A300–28–6077, Revision 01, dated October 26, 2006. Material Incorporated by Reference (k) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference (IBR) under 5 U.S.C. 552(a) and 1 CFR Part 51 of the following service information on the date specified. (1) Airbus Mandatory Service Bulletin A300–28–6064, Revision 03, dated December 15, 2008, approved for IBR November 23, 2011. (2) Airbus Mandatory Service Bulletin A300–28–6064, Revision 04, dated August 24, 2009, approved for IBR November 23, 2011. (3) Airbus Mandatory Service Bulletin A300–28–6064, Revision 05, dated September 27, 2010, approved for IBR November 23, 2011. (4) Airbus Service Bulletin A300–28–6068, dated July 20, 2005, approved for IBR on March 6, 2008 (73 FR 5731, January 31, 2008). (5) Airbus Service Bulletin A300–28–6077, Revision 01, dated October 26, 2006, approved for IBR on March 6, 2008 (73 FR 5731, January 31, 2008). (6) For service information identified in this AD, contact Airbus SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet https:// www.airbus.com. (7) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (8) You may also review copies of the service information that is incorporated by E:\FR\FM\19OCR1.SGM 19OCR1 Federal Register / Vol. 76, No. 202 / Wednesday, October 19, 2011 / Rules and Regulations reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on October 3, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–26257 Filed 10–18–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39s [Docket No. FAA–2011–0312; Directorate Identifier 2010–NM–159–AD; Amendment 39–16838; AD 2011–21–15] RIN 2120–AA64 www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on April 19, 2011 (76 FR 21822). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: This [Brazilian] AD results from reports of cracking in the firewall of the auxiliary power unit (APU). This AD is being issued to detect and correct this cracking, which could result in reduced structural integrity of the fuselage and empennage in the event that a fire penetrates through the firewall of the APU. Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: * * * * * We are adopting a new airworthiness directive (AD) for certain Model EMB–135ER, –135KE, –135KL, and –135LR airplanes; and Model EMB– 145, –145ER, –145MR, –145LR, –145MP, and –145EP airplanes. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: The required actions include repetitive detailed inspections for cracking of the rearward and forward face of the APU firewall, and repair if necessary. You may obtain further information by examining the MCAI in the AD docket. This [Brazilian] AD results from reports of cracking in the firewall of the auxiliary power unit (APU). This AD is being issued to detect and correct this cracking, which could result in reduced structural integrity of the fuselage and empennage in the event that a fire penetrates through the firewall of the APU. EMBRAER and ExpressJet Airlines requested that we reference EMBRAER Service Bulletin 145–53–0062, Revision 07, dated May 27, 2011, in the NPRM (76 FR 21822, April 19, 2011) as it is the most current. We agree that the latest service information should be referenced in this AD. We have changed references in paragraphs (h) and (l) of this AD to include EMBRAER Service Bulletin 145–53–0062, Revision 07, dated May 27, 2011. The effectivity of Revision 07 was changed to add serial numbers that were inadvertently omitted in EMBRAER Service Bulletin 145–53– 0062, Revision 06, dated August 11, 2010. (The applicability of this final rule remains unchanged.) In addition, we have added EMBRAER Service Bulletin SUMMARY: sroberts on DSK5SPTVN1PROD with RULES * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective November 23, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 23, 2011. ADDRESSES: You may examine the AD docket on the Internet at https:// VerDate Mar<15>2010 15:51 Oct 18, 2011 Jkt 223001 Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received. Request To Reference Latest Revision of Embraer Service Bulletin 145–53–0062 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 64785 145–53–0062, Revision 06, dated August 11, 2010, to ‘‘Table 1—Credit Service Bulletins’’ of this AD. Request To Remove Date and Revision Level of the Airplane Maintenance Manual (AMM) or Allow for Later Revisions American Eagle Airlines requested that we remove the date and revision level of the AMM specified in paragraph (g) of the NPRM (76 FR 21822, April 19, 2011), or allow for future revisions to the AMM. The commenter noted that if either of the AMM sections is updated by the manufacturer, the operators would be required to accomplish an obsolete task. We disagree with removing the date and revision level of the AMM because all documents incorporated by reference are required to have the date and revision level in accordance with the Office of the Federal Register regulations for approval of materials ‘‘incorporated by reference’’ in rules. See 1 CFR 51.1(f). We also disagree with allowing the use of ‘‘future’’ revisions to the AMM. When referring to a specific service document in an AD, using the phrase, ‘‘or later FAA-approved revisions,’’ violates Office of the Federal Register regulations for approval of materials ‘‘incorporated by reference’’ in rules. See 1 CFR 51.1(f). In general terms, we are required by these OFR regulations to either publish the service document contents as part of the actual AD language; or submit the service document to the OFR for approval as ‘‘referenced’’ material, in which case we may only refer to such material in the text of an AD. The AD may refer to the service document only if the OFR approved it for ‘‘incorporation by reference.’’ See 1 CFR part 51. However, because a later revision of the AMM has been issued since the NPRM (76 FR 21822, April 19, 2011) was published, we have revised paragraphs (g) and (l), and Note 2 of this AD to refer to EMBRAER EMB145 Aircraft Maintenance Manual, Part II, AMM–145/1124, Revision 54, dated April 28, 2011. We have also added new paragraph (i) (and re-identified subsequent paragraphs accordingly) to this AD to give credit for EMBRAER EMB145 Aircraft Maintenance Manual, Part II, AMM–145/1124, Revision 53, dated October 28, 2010, which was referenced as the appropriate source of service information for certain actions specified in the NPRM. However, operators may request approval of an AMOC to use later revisions of this AMM under the provisions of paragraph (k) of this AD. No changes have been made to the AD in this regard. E:\FR\FM\19OCR1.SGM 19OCR1

Agencies

[Federal Register Volume 76, Number 202 (Wednesday, October 19, 2011)]
[Rules and Regulations]
[Pages 64781-64785]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-26257]



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Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
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Federal Register / Vol. 76, No. 202 / Wednesday, October 19, 2011 / 
Rules and Regulations

[[Page 64781]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0264; Directorate Identifier 2009-NM-244-AD; 
Amendment 39-16837; AD 2011-21-14]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
that applies to certain Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model C4-605R Variant F airplanes (collectively called 
A300-600 series airplanes). This AD results from mandatory continuing 
airworthiness information (MCAI) originated by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    [T]he FAA has published SFAR 88 (Special Federal Aviation 
Regulation 88).* * *
    Under this regulation, all holders of type certificates for 
passenger transport aeroplanes * * * are required to conduct a 
design review against explosion risks. The replacement of some types 
of P-clips and improvement of the electrical bonding of the 
equipment in the fuel tanks [were] are rendered mandatory. * * *
* * * * *
    Subsequently, an internal review * * * led * * * to * * * an 
additional check [for blue coat] of the bonding points in the centre 
tank. * * *
More recently, another internal review [introduced] additional work 
[installing bonding points] for aeroplanes under Configuration 03 * 
* * and additional work [bonding the fuel jettison system--blanking 
plates] on the wing tanks for aeroplanes under Configuration 07. * * 
*

The unsafe condition is damage to wiring in the wing, center, and trim 
fuel tanks, due to failed P-clips used for retaining the wiring and 
pipes, which could result in a possible fuel ignition source in the 
wing, center, or trim fuel tanks. We are issuing this AD to require 
actions to correct the unsafe condition on these products.

DATES: This AD becomes effective November 23, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 23, 
2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications as of March 6, 2008 (73 FR 
5731, January 31, 2008).

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on April 6, 2011 (76 FR 
18960), and proposed to supersede AD 2008-03-04, Amendment 39-15353 (73 
FR 5731, January 31, 2008). That NPRM (76 FR 18960, April 6, 2011) 
proposed to correct an unsafe condition for the specified products. The 
MCAI states:

    [T]he FAA has published SFAR 88 (Special Federal Aviation 
Regulation 88). In their letters referenced 04/00/02/07/01-L296, 
dated 04 March 2002, and 04/00/02/07/03-L024, dated 03 February 
2003, the JAA recommended the application of a similar regulation to 
the National Aviation Authorities (NAA).
    Under this regulation, all holders of type certificates for 
passenger transport aeroplanes with either a passenger capacity of 
30 or more, or a payload capacity of 3,402 kg (7,500 lbs) or more 
which have received their certification since 01 January 1958, are 
required to conduct a design review against explosion risks. The 
replacement of some types of P-clips and improvement of the 
electrical bonding of the equipment in the fuel tasks are rendered 
mandatory by this AD.
    Initially, EASA AD 2006-0325, which addressed the same unsafe 
condition, also applied to A300-600 aeroplanes. Airbus subsequently 
introduced additional work at Revision 1 of SB A300-28-6064 [dated 
April 3, 2007] applicable to A300-600 aeroplanes. As a result, EASA 
AD 2006-0325 was revised to remove A300-600 aeroplanes from the 
applicability, and concurrently EASA AD 2007-0233 was issued, 
applicable to A300-600 aeroplanes. Unfortunately, the 
`Applicability' section of EASA AD 2007-0233 was not correctly 
defined, erroneously deleting one modification in the combination 
that would exclude aeroplanes from having to comply. Consequently, 
the AD 2007-0283 was issued, requiring the same actions as AD 2007-
0233, which was superseded, but expanded the group of aeroplanes to 
which AD 2007-0283 applied [FAA AD 2008-03-04 (73 FR 5731, January 
31, 2008) corresponds with EASA AD 2007-0283].
    Subsequently, an internal review of Airbus SB A300-28-6064 led 
the manufacturer to correct the figures of the SB. In particular, an 
additional check [for blue coat] of the bonding points in the centre 
tank was introduced in Revision 03 of Airbus SB A300-28-6064 [dated 
December 15, 2008], prompting EASA to issue AD 2009-0143.
    More recently, another internal review of Airbus SB A300-28-6064 
again resulted in corrected figures in the SB. Additional work on 
the center tank [installing bonding points] for aeroplanes under 
Configuration 03 (as defined in the SB [Service Bulletin A300-28-
6064, Revision 04, dated August 24, 2009]) and additional work 
[bonding the fuel jettison system--blanking plates] on the wing 
tanks for aeroplanes under Configuration 07 have been introduced in 
Revision 04 of Airbus SB A300-28-6064 [dated August 24, 2009].
    For the reason described above, this new AD retains the 
requirements of EASA AD 2009-0143, which is superseded, and requires 
the additional work introduced in Revision 04 of Airbus SB A300-28-
6064 [dated August 24, 2009].

The unsafe condition is damage to wiring in the wing, center, and trim 
fuel tanks, due to failed P-clips used for retaining the wiring and 
pipes, which could result in a possible fuel ignition source in the 
wing, center, or trim fuel tanks. The required actions also include 
checking the electrical bonding points of certain equipment in the 
center fuel tank for the presence of a blue coat and

[[Page 64782]]

doing related investigative and corrective actions if necessary. The 
related investigative action is to measure the electrical resistance 
between the equipment and structure, if a blue coat is not present. The 
corrective action is to electrically bond the equipment, if the 
measured resistance is greater than 10 milliohms. You may obtain 
further information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

Request for Extension of Compliance Time

    UPS and FedEx requested an extension to the 8-month compliance time 
specified in the NPRM (76 FR 18960, dated April 6, 2011) in order to 
accomplish the additional actions. FedEx requested that the compliance 
time for the additional actions be at the latest of the 40-month 
compliance time specified in AD 2008-03-04, Amendment 39-15353 (73 FR 
5731, January 31, 2008), any alternative methods of compliance that 
extend that compliance time or within 12 months after the effective 
date of the new AD. UPS requested that the compliance time be extended 
to 60 months. UPS stated that the two additional bonding points 
specified in the NPRM are no more unsafe than the original 264 bonding 
points required in AD 2008-03-04. UPS noted that it schedules tank 
entry checks at 60 months and that the original issue of the service 
information allowed for a 60-month compliance time.
    We agree with extending the compliance time and have determined 
that extending the compliance time to 30 months is appropriate. In 
developing an appropriate compliance time for this action, we 
considered the safety implications, parts availability, and normal 
maintenance schedules for the timely accomplishment of the 
modification. In consideration of these items, we have determined that 
a 30-month compliance time will ensure an acceptable level of safety 
and allow the modifications to be done during scheduled maintenance 
intervals for most affected operators. We have also coordinated with 
European Aviation Safety Agency (EASA) on this issue. We have changed 
the compliance time in paragraph (h) of this AD to ``within 30 months 
after the effective date of this AD.''

Request for Change to Cost of Compliance Work-Hours

    FedEx stated that they averaged 800 work-hours versus the 632 work-
hours listed in the NPRM (76 FR 18960, dated April 6, 2011) to 
accomplish the existing modifications. FedEx also stated that 9 work-
hours, as specified for the additional actions, may be adequate if done 
in conjunction with the other modifications; however, additional work-
hours will be required for airplanes that have been previously been 
modified.
    We infer that FedEx is requesting that we increase the work-hours 
estimate to accomplish the existing and new modifications. We do not 
agree to revise the work-hours. Work-hours may vary among operators. 
Our estimate is based on the information provided in the relevant 
service information. We have not changed this AD in this regard.

Request for Material Substitutions

    FedEx requested that we add wording to the NPRM (76 FR 18960, dated 
April 6, 2011) that material substitutions supplied by Airbus are 
approved for use and do not require an alternative method of compliance 
(AMOC). FedEx stated that the kits specified in Airbus Service 
Bulletins A300-28-6064, Revision 01, dated April 3, 2007; A300-28-6068, 
dated July 20, 2005; and A300-28-6077, Revision 01, dated October 26, 
2006; might contain parts that are not listed in the kit description 
specified in the service information.
    We do not agree with the request to revise the AD to include 
wording that material substitutions are approved for use. Airbus 
Service Bulletins A300-28-6064, Revision 01, dated April 3, 2007; A300-
28-6068, dated July 20, 2005; and A300-28-6077, Revision 01, dated 
October 26, 2006; contain language in the ``Standard Practices'' 
section of paragraph 3.A. ``General'' of the Accomplishment 
Instructions that specifies which alternative materials are allowed. We 
have not changed this AD in this regard.

Request To Update Service Information to Latest Revision

    FedEx stated that Airbus has issued Mandatory Service Bulletin 
A300-28-6064, Revision 05, dated September 27, 2010, and requested that 
we update our references in the NPRM (76 FR 18960, dated April 6, 
2011).
    We agree with the request and have updated the references in 
paragraphs (c)(1), (g)(4), and (h) of this AD to include Airbus 
Mandatory Service Bulletin A300-28-6064, Revision 05, dated September 
27, 2010. Airbus Mandatory Service Bulletin A300-28-6064, Revision 05, 
dated September 27, 2010, provides clarifications of the actions and 
materials but contains no substantive changes.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of the AD.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect about 125 products of U.S. 
registry.
    The actions that are required by AD 2008-03-04 Amendment 39-15353 
(73 FR 5731, January 31, 2008) and retained in this AD take about 632 
work-hours per product, at an average labor rate of $85 per work-hour. 
Required parts cost about $6,870 per product. Based on these figures, 
the estimated cost of the currently required actions is $60,590 per 
product.
    We estimate that it will take about 9 work-hours per product to 
comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $100 per 
product. Where the service information lists required parts costs that 
are covered under warranty, we have assumed that there will be no 
charge for these parts. As we do not control warranty coverage for 
affected parties, some parties may incur costs higher than estimated 
here. Based on these figures, we estimate the cost of this AD to the 
U.S. operators to be $108,125, or $865 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue

[[Page 64783]]

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 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 this AD:
    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 AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM (76 FR 18960, dated April 6, 
2011), the regulatory evaluation, any comments received, and other 
information. The street address for the Docket Operations office 
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

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 FAA amends Sec.  39.13 by removing Amendment 39-15353 (73 FR 
5731, January 31, 2008) and adding the following new AD:

2011-21-14 Airbus: Amendment 39-16837. Docket No. FAA-2011-0264; 
Directorate Identifier 2009-NM-244-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
23, 2011.

Affected ADs

    (b) This AD supersedes AD 2008-03-04, Amendment 39-15353 (73 FR 
5731, January 31, 2008).

Applicability

    (c) This AD applies to the airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD.
    (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes (without trim tank), all serial numbers, certificated in 
any category, except airplanes on which Airbus Modifications 12226, 
12365, 12490, and 12308 have been incorporated in production, or on 
which the service bulletins listed in paragraphs (c)(1)(i) and 
(c)(1)(ii) of this AD have been performed in service.
    (i) Airbus Mandatory Service Bulletin A300-28-6064, Revision 04, 
dated August 24, 2009; or Revision 05, dated September 27, 2010.
    (ii) Airbus Service Bulletin A300-28-6068, dated July 20, 2005.
    (2) Airbus Model A300 B4-605R, B4-622R, F4-605R, and F4-622R 
airplanes and A300 C4-605R Variant F airplanes (fitted with a trim 
tank), all serial numbers, certificated in any category, except 
airplanes on which Airbus Modifications 12226, 12365, 12490, 12308, 
12294, and 12476 have been incorporated in production, or on which 
the service bulletins listed in paragraphs (c)(2)(i), (c)(2)(ii), 
and (c)(2)(iii) of this AD have been performed in service.
    (i) Airbus Mandatory Service Bulletin A300-28-6064, Revision 03, 
dated December 15, 2008.
    (ii) Airbus Service Bulletin A300-28-6068, dated July 20, 2005.
    (iii) Airbus Service Bulletin A300-28-6077, dated July 25, 2005; 
or Revision 01, dated October 26, 2006.

Subject

    (d) Air Transport Association (ATA) of America Code 28: Fuel.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    [T]he FAA has published SFAR 88 (Special Federal Aviation 
Regulation 88). * * *
    Under this regulation, all holders of type certificates for 
passenger transport aeroplanes * * * are required to conduct a 
design review against explosion risks. The replacement of some types 
of P-clips and improvement of the electrical bonding of the 
equipment in the fuel tanks [were] are rendered mandatory * * *.
* * * * *
    Subsequently, an internal review * * * led * * * to * * * an 
additional check [for blue coat] of the bonding points in the centre 
tank. * * *
    More recently, another internal review [introduced] additional 
work [installing bonding points] for aeroplanes under Configuration 
03 * * * and additional work [bonding the fuel jettison system--
blanking plates] on the wing tanks for aeroplanes under 
Configuration 07 * * *.

The unsafe condition is damage to wiring in the wing, center, and 
trim fuel tanks, due to failed P-clips used for retaining the wiring 
and pipes, which could result in a possible fuel ignition source in 
the wing, center, or trim fuel tanks.

Compliance

    (f) 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 2008-03-04, Amendment 39-15353 (73 FR 
5731, January 31, 2008) With Revised Service Information

Actions and Compliance

    (g) For airplanes identified in paragraphs (g)(1) and (g)(2) of 
this AD: Within 40 months after March 6, 2008 (the effective date of 
AD 2008-03-04, Amendment 39-15353 (73 FR 5731, January 31, 2008)), 
unless already done, do the applicable actions required by 
paragraphs (g)(3), (g)(4), and (g)(5) of this AD.
    (1) Airbus Model A300 B4-600 series airplanes (without trim 
tank), all serial numbers, except airplanes on which Airbus 
Modifications 12226, 12365, 12490, and 12308 have been incorporated 
in production, or Airbus Service Bulletins A300-28-6064, Revision 
01, dated April 3, 2007; and A300-28-6068, dated July 20, 2005; have 
been performed in service.
    (2) Airbus Model A300 B4-600R, A300 C4-600R, and A300 F4-600R 
series airplanes (fitted with a trim tank), all serial numbers, 
except airplanes on which Airbus Modifications 12226, 12365, 12490, 
12308, 12294, and 12476 have been incorporated in production, or on 
which the service bulletins listed in paragraphs (g)(2)(i), 
(g)(2)(ii), and (g)(2)(iii) of this AD have been performed in 
service.
    (i) Airbus Service Bulletin A300-28-6064, Revision 01, dated 
April 3, 2007.
    (ii) Airbus Service Bulletin A300-28-6068, dated July 20, 2005.

[[Page 64784]]

    (iii) Airbus Service Bulletin A300-28-6077, dated July 25, 2005; 
or A300-28-6077, Revision 01, dated October 26, 2006.
    (3) Remove NSA5516-XXND or NSA5516-XXNJ type P-clips, used in 
the wing and center fuel tanks to retain wiring and pipes, and 
replace them by NSA5516-XXNF type P-clips in accordance with the 
instructions of Airbus Service Bulletin A300-28-6068, dated July 20, 
2005.
    (4) Check the electrical bonding points in the center tank and 
do all applicable related investigative and corrective actions, and 
install additional bonding leads and electrical bonding points in 
the wing and center fuel tanks in accordance with the instructions 
of Airbus Service Bulletin A300-28-6064, Revision 01, dated April 3, 
2007; Airbus Mandatory Service Bulletin A300-28-6064, Revision 02, 
dated March 10, 2008; Airbus Mandatory Service Bulletin A300-28-
6064, Revision 03, dated December 15, 2008; Airbus Mandatory Service 
Bulletin A300-28-6064, Revision 04, dated August 24, 2009; or Airbus 
Mandatory Service Bulletin A300-28-6064, Revision 05, dated 
September 27, 2010. Do all applicable related investigative and 
corrective actions before further flight. As of the effective date 
of this AD, only use Airbus Mandatory Service Bulletin A300-28-6064, 
Revision 05, dated September 27, 2010.
    (5) For airplanes fitted with a trim tank, in addition to the 
actions defined in paragraphs (g)(3) and (g)(4) of this AD, install 
bonding leads and electrical bonding points in the trim tanks, in 
accordance with the instructions of Airbus Service Bulletin A300-28-
6077, Revision 01, dated October 26, 2006.
    (6) Actions done before March 6, 2008, in accordance with Airbus 
Service Bulletin A300-28-6064, dated July 28, 2005, for aircraft 
under configuration 05, as defined in Airbus Service Bulletin A300-
28-6064, dated July 28, 2005, are considered acceptable for 
compliance with the requirements of paragraph (g)(4) of this AD.
    (7) Actions done before March 6, 2008, in accordance with Airbus 
Service Bulletin A300-28-6077, dated July 25, 2005, for aircraft 
under configuration 05, as defined in Airbus Service Bulletin A300-
28-6077, dated July 25, 2005, are considered acceptable for 
compliance with the requirements of paragraph (g)(5) of this AD.

New Requirments of This AD

Additional Actions

    (h) Within 30 months after the effective date of this AD, do the 
applicable actions required by paragraphs (h)(1), (h)(2), and (h)(3) 
of this AD.
    (1) For airplanes that have been modified before the effective 
date of this AD in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A300-28-6064, dated July 28, 2005, or 
Revision 01, dated April 3, 2007; or Airbus Mandatory Service 
Bulletin A300-28-6064, Revision 02, dated March 10, 2008: Do the 
additional work on the center tank specified in Airbus Mandatory 
Service Bulletin A300-28-6064, Revision 03, dated December 15, 2008 
(i.e., a check for blue coat at additional bonding points and all 
applicable related investigative and corrective actions), in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A300-28-6064, Revision 03, dated December 15, 2008; 
Revision 04, dated August 24, 2009; or Revision 05, dated September 
27, 2010. Do all applicable related investigative and corrective 
actions before further flight.
    (2) For configuration 03 airplanes, as defined in Airbus 
Mandatory Service Bulletin A300-28-6064, Revision 04, dated August 
24, 2009; or Revision 05, dated September 27, 2010; that have been 
modified before the effective date of this AD in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-28-6064, 
Revision 01, dated April 3, 2007; or Airbus Mandatory Service 
Bulletin A300-28-6064, Revision 02, dated March 10, 2008, or 
Revision 03, dated December 15, 2008: Do the additional work on the 
center tank (i.e., install bonding points), in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-28-6064, Revision 04, dated August 24, 2009; or Revision 05, 
dated September 27, 2010.
    (3) For configuration 07 airplanes, as defined in Airbus 
Mandatory Service Bulletin A300-28-6064, Revision 04, dated August 
24, 2009; or Revision 05, dated September 27, 2010; that have been 
modified before the effective date of this AD in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-28-6064, 
dated July 28, 2005; or Revision 01, dated April 3, 2007; or Airbus 
Mandatory Service Bulletin A300-28-6064, Revision 02, dated March 
10, 2008, or Revision 03, dated December 15, 2008: Do the additional 
work on the wing tanks (i.e., bond the fuel jettison system--
blanking plates), in accordance with the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A300-28-6064, Revision 04, 
dated August 24, 2009; or Revision 05, dated September 27, 2010.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: The MCAI provides a compliance time of 8 months to do 
the actions specified in paragraph (h) of this AD. This AD requires 
that the actions specified in paragraph (h) of this AD be done 
within 30 months.

Other FAA AD Provisions

    (i) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. Send information to ATTN: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 227-2125; fax (425) 227-1149. Before using any approved AMOC, 
notify your appropriate principal inspector, or lacking a principal 
inspector, the manager of the local flight standards district 
office/certificate holding district office. The AMOC approval letter 
must specifically reference this AD. AMOCs approved previously in 
accordance with AD 2008-03-04, Amendment 39-15353 (73 FR 5731, 
January 31, 2008), are approved as AMOCs for the corresponding 
provisions of this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

Related Information

    (j) Refer to MCAI EASA Airworthiness Directive 2010-0074, dated 
April 16, 2010, and the following service information, for related 
information.
    (1) Airbus Mandatory Service Bulletin A300-28-6064, Revision 03, 
dated December 15, 2008.
    (2) Airbus Mandatory Service Bulletin A300-28-6064, Revision 04, 
dated August 24, 2009.
    (3) Airbus Mandatory Service Bulletin A300-28-6064, Revision 05, 
dated September 27, 2010.
    (4) Airbus Service Bulletin A300-28-6068, dated July 20, 2005.
    (5) Airbus Service Bulletin A300-28-6077, Revision 01, dated 
October 26, 2006.

Material Incorporated by Reference

    (k) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise. The 
Director of the Federal Register approved the incorporation by 
reference (IBR) under 5 U.S.C. 552(a) and 1 CFR Part 51 of the 
following service information on the date specified.
    (1) Airbus Mandatory Service Bulletin A300-28-6064, Revision 03, 
dated December 15, 2008, approved for IBR November 23, 2011.
    (2) Airbus Mandatory Service Bulletin A300-28-6064, Revision 04, 
dated August 24, 2009, approved for IBR November 23, 2011.
    (3) Airbus Mandatory Service Bulletin A300-28-6064, Revision 05, 
dated September 27, 2010, approved for IBR November 23, 2011.
    (4) Airbus Service Bulletin A300-28-6068, dated July 20, 2005, 
approved for IBR on March 6, 2008 (73 FR 5731, January 31, 2008).
    (5) Airbus Service Bulletin A300-28-6077, Revision 01, dated 
October 26, 2006, approved for IBR on March 6, 2008 (73 FR 5731, 
January 31, 2008).
    (6) For service information identified in this AD, contact 
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; 
Internet https://www.airbus.com.
    (7) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (8) You may also review copies of the service information that 
is incorporated by

[[Page 64785]]

reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on October 3, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-26257 Filed 10-18-11; 8:45 am]
BILLING CODE 4910-13-P

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