Airworthiness Directives; Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300 B4-103, A300 B4-203, and A300 B4-2C Airplanes, 63576-63578 [E9-28797]

Download as PDF 63576 Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / 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: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on November 23, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–28798 Filed 12–3–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0055; Directorate Identifier 2008–NM–194–AD; Amendment 39–16125; AD 2009–25–06] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2–1C, A300 B2–203, A300 B2K– 3C, A300 B4–103, A300 B4–203, and A300 B4–2C Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. jlentini on DSKJ8SOYB1PROD with RULES SUMMARY: We are superseding an existing airworthiness directive (AD) for the products listed above. 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 aeroplane * * * are required to conduct a design review against explosion risks. One of the consequences of the Airbus design review is the modification of the fuel pump wiring to provide protection against chafing of the fuel pump cables. This condition, if not corrected, could generate short circuits leading to fuel pump failure and arcing. These could become a potential ignition source inside the fuel tank which, in combination with flammable fuel vapours (if present), could result in a fuel tank explosion and consequent loss of the aeroplane. To address this unsafe condition, EASA [European Aviation Safety Agency] issued AD 2007–0066 that required this modification [of the fuel pump against short circuit] in accordance with Airbus Service Bulletin (SB) A300–24–0103 Revision 01. Airbus subsequently introduced an additional modification of the electrical VerDate Nov<24>2008 17:09 Dec 03, 2009 Jkt 220001 wiring of the outer fuel pump and the landing lights of the left (LH) and the right (RH) side in Revision 02 of the SB A300–24– 0103, leading to the issuance of EASA AD 2008–0188 which superseded EASA AD 2007–0066 and required the additional work. More recently, Airbus introduced some additional protection to routes 1P and 2P harnesses in zone 571 and 671 of the aeroplane. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective January 8, 2010. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 8, 2010. ADDRESSES: You may examine the AD docket on the Internet at http:// 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 supplemental notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That supplemental NPRM was published in the Federal Register on July 6, 2009 (74 FR 31896), and proposed to supersede AD 2007–18–02, Amendment 39–15182 (72 FR 49175, August 28, 2007). That supplemental NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Further to the accident of a Boeing 747– 131 (flight TWA800), the FAA has published SFAR 88 (Special Federal Aviation Regulation 88). Subsequently, the Joint Aviation Authorities (JAA) recommended the application of a similar regulation to the National Aviation Authorities (NAA) of its member countries. Under this regulation, all holders of type certificates for passenger transport aeroplane 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 after 01 January 1958, are required to conduct a design review against explosion risks. One of the consequences of the Airbus design review is the modification of the fuel pump wiring to provide protection against chafing of the fuel pump cables. This PO 00000 Frm 00046 Fmt 4700 Sfmt 4700 condition, if not corrected, could generate short circuits leading to fuel pump failure and arcing. These could become a potential ignition source inside the fuel tank which, in combination with flammable fuel vapours (if present), could result in a fuel tank explosion and consequent loss of the aeroplane. To address this unsafe condition, EASA [European Aviation Safety Agency] issued AD 2007–0066 that required this modification in accordance with Airbus Service Bulletin (SB) A300–24–0103 Revision 01. Airbus subsequently introduced an additional modification of the electrical wiring of the outer fuel pump and the landing lights of the left (LH) and the right (RH) side in Revision 02 of the SB A300–24– 0103, leading to the issuance of EASA AD 2008–0188 which superseded EASA AD 2007–0066 and required the additional work. More recently, Airbus introduced some additional protection to routes 1P and 2P harnesses in zone 571 and 671 of the aeroplane. For the reason described above, this new AD retains the requirements of EASA AD 2008–0188, which is superseded, and requires the additional work as specified in Revision 03 of Airbus SB A300–24–0103. The additional modification will provide additional protection from chafing and will prevent intermittent operation of the fuel pump and landing lights, as well as failure of the power supply. The modification of the wiring of the outer fuel pump and the landing light on the LH side route 1P harness and RH side route 2P harness includes additional mechanical protection that includes procedures for installing new splicing on the wires, a new cable type, shrink sleeve installation on the new wiring, and an additional braided conduit sleeve (Halar), as applicable, for the fuel pumps and the landing lights. 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 comment received. Request To Refer to Updated MCAI Airbus requests that we refer to the latest EASA AD 2009–0157, dated July 17, 2009 (which was issued after the FAA supplemental NPRM was published), to require the additional work provided in Airbus Mandatory Service Bulletin A300–24–0103, Revision 03, dated February 18, 2009. The supplemental NPRM referred to Airbus Mandatory Service Bulletin A300–24–0103, Revision 03, dated February 18, 2009, as the appropriate source of service information for the required actions. Airbus further requests that we review the supplemental NPRM in light of the new EASA AD to qualify current requirements depending on the E:\FR\FM\04DER1.SGM 04DER1 Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations airplane configuration, as specified in the latest EASA AD. We agree to refer to the latest EASA AD because it refers to the revised service information. However, we do not agree that it is necessary to revise the supplemental NPRM to qualify the requirements based on different configurations. Paragraph (g) of this AD requires that work be accomplished in accordance with Airbus Mandatory Service Bulletin A300–24–0103, Revision 03, dated February 18, 2009. The service bulletin specifies the different configurations and corresponding actions so there is no need to change the AD. Therefore, we have not changed the AD in regard to this issue. Conclusion We reviewed the available data, including the comment 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. jlentini on DSKJ8SOYB1PROD with RULES 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 13 products of U.S. registry. The actions that are required by AD 2007–18–02 and retained in this AD take about 72 work-hours per product, at an average labor rate of $80 per work hour. Required parts cost about $5,050 per product. Based on these figures, the estimated cost of the currently required actions is $10,810 per product. We estimate that it will take about 42 work-hours per product to comply with the new basic requirements of this AD. The average labor rate is $80 per workhour. Required parts will cost about $4,100 per product. Where the service information lists required parts costs that are covered under warranty, we VerDate Nov<24>2008 17:09 Dec 03, 2009 Jkt 220001 have assumed that there will be no charge for these costs. 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 $96,980, or $7,460 per product. 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 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 http:// 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, the regulatory evaluation, any comments received, and PO 00000 Frm 00047 Fmt 4700 Sfmt 4700 63577 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 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 39–15182 (72 FR 49175, August 28, 2007) and adding the following new AD: ■ 2009–25–06 Airbus: Amendment 39–16125. Docket No. FAA–2009–0055; Directorate Identifier 2008–NM–194–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 8, 2010. Affected ADs (b) This AD supersedes AD 2007–18–02, Amendment 39–15182. Applicability (c) This AD applies to Airbus Model A300 B2–1C, A300 B2–203, A300 B2K–3C, A300 B4–103, A300 B4–203, and A300 B4–2C airplanes, certificated in any category, as identified in Airbus Mandatory Service Bulletin A300–24–0103, Revision 03, dated February 18, 2009. Subject (d) Air Transport Association (ATA) of America Code 24: Electrical power. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Further to the accident of a Boeing 747– 131 (flight TWA800), the FAA has published SFAR 88 (Special Federal Aviation Regulation 88). Subsequently, the Joint Aviation Authorities (JAA) recommended the application of a similar regulation to the National Aviation Authorities (NAA) of its member countries. Under this regulation, all holders of type certificates for passenger transport aeroplane 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 after 01 January 1958, are required to conduct a design review against explosion risks. One of the consequences of the Airbus design review is the modification of the fuel E:\FR\FM\04DER1.SGM 04DER1 63578 Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations pump wiring to provide protection against chafing of the fuel pump cables. This condition, if not corrected, could generate short circuits leading to fuel pump failure and arcing. These could become a potential ignition source inside the fuel tank which, in combination with flammable fuel vapours (if present), could result in a fuel tank explosion and consequent loss of the aeroplane. To address this unsafe condition, EASA [European Aviation Safety Agency] issued AD 2007–0066 that required this modification in accordance with Airbus Service Bulletin (SB) A300–24–0103 Revision 01. Airbus subsequently introduced an additional modification of the electrical wiring of the outer fuel pump and the landing lights of the left (LH) and the right (RH) side in Revision 02 of the SB A300–24– 0103, leading to the issuance of EASA AD 2008–0188 which superseded EASA AD 2007–0066 and required the additional work. More recently, Airbus introduced some additional protection to routes 1P and 2P harnesses in zone 571 and 671 of the aeroplane. For the reason described above, this new AD retains the requirements of EASA AD 2008–0188, which is superseded, and requires the additional work as specified in Revision 03 of Airbus SB A300–24–0103. The additional modification will provide additional protection from chafing and will prevent intermittent operation of the fuel pump and landing lights, as well as failure of the power supply. The modification of the wiring of the outer fuel pump and the landing light on the LH side route 1P harness and RH side route 2P harness includes additional mechanical protection that includes procedures for installing new splicing on the wires, a new cable type, shrink sleeve installation on the new wiring, and an additional braided conduit sleeve (Halar), as applicable, for the fuel pumps and the landing lights. jlentini on DSKJ8SOYB1PROD with RULES Restatement of Requirements of AD 2007– 18–02, With Revised Service Information (f) Within 31 months after October 2, 2007 (the effective date of AD 2007–18–02), unless already done, modify the inner and outer fuel pump wiring, route 1P and 2P harnesses in the LH (left-hand) wing and in the RH (righthand) wing, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–24–0103, Revision 01, dated January 11, 2007; or Airbus Mandatory Service Bulletin A300–24–0103, Revision 03, dated February 18, 2009. After the effective date of this AD, use only Airbus Mandatory Service Bulletin A300–24–0103, Revision 03, dated February 18, 2009. Actions done before October 2, 2007, in accordance with Airbus Service Bulletin A300–24–0103, dated March 15, 2006, for airplanes under configuration 1 as defined in Airbus Service Bulletin A300– 24–0103, Revision 01, dated January 11, 2007; Revision 02, dated April 4, 2008; or Revision 03, dated February 18, 2009; are acceptable for compliance with the requirements of this paragraph. VerDate Nov<24>2008 17:09 Dec 03, 2009 Jkt 220001 New Requirements of This AD Actions and Compliance (g) Unless already done, within 12 months after the effective date of this AD, modify the wiring of the outer fuel pump and the landing light on the LH side route 1P harness and RH side route 2P harness in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–24– 0103, Revision 03, dated February 18, 2009. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (h) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. AMOCs approved previously in accordance with AD 2007–18–02, 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. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (i) Refer to MCAI EASA Airworthiness Directive 2009–0157, dated July 17, 2009; Airbus Service Bulletin A300–24–0103, Revision 01, dated January 11, 2007; and Airbus Mandatory Service Bulletin A300–24– 0103, Revision 03, dated February 18, 2009; for related information. Material Incorporated by Reference (j) You must use Airbus Mandatory Service Bulletin A300–24–0103, Revision 03, dated February 18, 2009, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. PO 00000 Frm 00048 Fmt 4700 Sfmt 4700 (2) 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 http:// www.airbus.com. (3) 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 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by 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: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on November 23, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–28797 Filed 12–3–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0658; Directorate Identifier 2009–NM–058–AD; Amendment 39–16115; AD 2009–24–21] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model DC–9–14, DC–9–15, and DC–9–15F Airplanes; and McDonnell Douglas Model DC–9–20, DC–9–30, DC–9–40, and DC–9–50 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD) that applies to all McDonnell Douglas Model DC–9–14, DC–9–15, and DC–9– 15F airplanes; and McDonnell Douglas Model DC–9–20, DC–9–30, DC–9–40, and DC–9–50 series airplanes. That AD currently requires repetitive inspections for cracks of the main landing gear (MLG) shock strut cylinder, and related investigative and corrective actions if necessary. This AD adds more work on airplanes that have main landing gear shock struts with certain identified part numbers. This AD results from two reports of a collapsed MLG and a report of cracks in two MLG cylinders. We are E:\FR\FM\04DER1.SGM 04DER1

Agencies

[Federal Register Volume 74, Number 232 (Friday, December 4, 2009)]
[Rules and Regulations]
[Pages 63576-63578]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-28797]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0055; Directorate Identifier 2008-NM-194-AD; 
Amendment 39-16125; AD 2009-25-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2-1C, A300 B2-203, 
A300 B2K-3C, A300 B4-103, A300 B4-203, and A300 B4-2C Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for the products listed above. 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 aeroplane * * * are required to 
conduct a design review against explosion risks.
    One of the consequences of the Airbus design review is the 
modification of the fuel pump wiring to provide protection against 
chafing of the fuel pump cables. This condition, if not corrected, 
could generate short circuits leading to fuel pump failure and 
arcing. These could become a potential ignition source inside the 
fuel tank which, in combination with flammable fuel vapours (if 
present), could result in a fuel tank explosion and consequent loss 
of the aeroplane.
    To address this unsafe condition, EASA [European Aviation Safety 
Agency] issued AD 2007-0066 that required this modification [of the 
fuel pump against short circuit] in accordance with Airbus Service 
Bulletin (SB) A300-24-0103 Revision 01. Airbus subsequently 
introduced an additional modification of the electrical wiring of 
the outer fuel pump and the landing lights of the left (LH) and the 
right (RH) side in Revision 02 of the SB A300-24-0103, leading to 
the issuance of EASA AD 2008-0188 which superseded EASA AD 2007-0066 
and required the additional work.
    More recently, Airbus introduced some additional protection to 
routes 1P and 2P harnesses in zone 571 and 671 of the aeroplane.
* * * * *

    We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective January 8, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 8, 
2010.

ADDRESSES: You may examine the AD docket on the Internet at http://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 supplemental notice of proposed rulemaking (NPRM) to 
amend 14 CFR part 39 to include an AD that would apply to the specified 
products. That supplemental NPRM was published in the Federal Register 
on July 6, 2009 (74 FR 31896), and proposed to supersede AD 2007-18-02, 
Amendment 39-15182 (72 FR 49175, August 28, 2007). That supplemental 
NPRM proposed to correct an unsafe condition for the specified 
products. The MCAI states:

    Further to the accident of a Boeing 747-131 (flight TWA800), the 
FAA has published SFAR 88 (Special Federal Aviation Regulation 88). 
Subsequently, the Joint Aviation Authorities (JAA) recommended the 
application of a similar regulation to the National Aviation 
Authorities (NAA) of its member countries. Under this regulation, 
all holders of type certificates for passenger transport aeroplane 
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 after 01 January 1958, are required to conduct a 
design review against explosion risks.
    One of the consequences of the Airbus design review is the 
modification of the fuel pump wiring to provide protection against 
chafing of the fuel pump cables. This condition, if not corrected, 
could generate short circuits leading to fuel pump failure and 
arcing. These could become a potential ignition source inside the 
fuel tank which, in combination with flammable fuel vapours (if 
present), could result in a fuel tank explosion and consequent loss 
of the aeroplane.
    To address this unsafe condition, EASA [European Aviation Safety 
Agency] issued AD 2007-0066 that required this modification in 
accordance with Airbus Service Bulletin (SB) A300-24-0103 Revision 
01. Airbus subsequently introduced an additional modification of the 
electrical wiring of the outer fuel pump and the landing lights of 
the left (LH) and the right (RH) side in Revision 02 of the SB A300-
24-0103, leading to the issuance of EASA AD 2008-0188 which 
superseded EASA AD 2007-0066 and required the additional work.
    More recently, Airbus introduced some additional protection to 
routes 1P and 2P harnesses in zone 571 and 671 of the aeroplane.
    For the reason described above, this new AD retains the 
requirements of EASA AD 2008-0188, which is superseded, and requires 
the additional work as specified in Revision 03 of Airbus SB A300-
24-0103.

    The additional modification will provide additional protection from 
chafing and will prevent intermittent operation of the fuel pump and 
landing lights, as well as failure of the power supply. The 
modification of the wiring of the outer fuel pump and the landing light 
on the LH side route 1P harness and RH side route 2P harness includes 
additional mechanical protection that includes procedures for 
installing new splicing on the wires, a new cable type, shrink sleeve 
installation on the new wiring, and an additional braided conduit 
sleeve (Halar), as applicable, for the fuel pumps and the landing 
lights. 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 comment received.

Request To Refer to Updated MCAI

    Airbus requests that we refer to the latest EASA AD 2009-0157, 
dated July 17, 2009 (which was issued after the FAA supplemental NPRM 
was published), to require the additional work provided in Airbus 
Mandatory Service Bulletin A300-24-0103, Revision 03, dated February 
18, 2009. The supplemental NPRM referred to Airbus Mandatory Service 
Bulletin A300-24-0103, Revision 03, dated February 18, 2009, as the 
appropriate source of service information for the required actions. 
Airbus further requests that we review the supplemental NPRM in light 
of the new EASA AD to qualify current requirements depending on the

[[Page 63577]]

airplane configuration, as specified in the latest EASA AD.
    We agree to refer to the latest EASA AD because it refers to the 
revised service information. However, we do not agree that it is 
necessary to revise the supplemental NPRM to qualify the requirements 
based on different configurations. Paragraph (g) of this AD requires 
that work be accomplished in accordance with Airbus Mandatory Service 
Bulletin A300-24-0103, Revision 03, dated February 18, 2009. The 
service bulletin specifies the different configurations and 
corresponding actions so there is no need to change the AD. Therefore, 
we have not changed the AD in regard to this issue.

Conclusion

    We reviewed the available data, including the comment 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 13 products of U.S. 
registry.
    The actions that are required by AD 2007-18-02 and retained in this 
AD take about 72 work-hours per product, at an average labor rate of 
$80 per work hour. Required parts cost about $5,050 per product. Based 
on these figures, the estimated cost of the currently required actions 
is $10,810 per product.
    We estimate that it will take about 42 work-hours per product to 
comply with the new basic requirements of this AD. The average labor 
rate is $80 per work-hour. Required parts will cost about $4,100 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 costs. 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 $96,980, or $7,460 per product.

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 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 http://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, 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

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 FAA amends Sec.  39.13 by removing Amendment 39-15182 (72 FR 
49175, August 28, 2007) and adding the following new AD:

2009-25-06 Airbus: Amendment 39-16125. Docket No. FAA-2009-0055; 
Directorate Identifier 2008-NM-194-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
8, 2010.

Affected ADs

    (b) This AD supersedes AD 2007-18-02, Amendment 39-15182.

Applicability

    (c) This AD applies to Airbus Model A300 B2-1C, A300 B2-203, 
A300 B2K-3C, A300 B4-103, A300 B4-203, and A300 B4-2C airplanes, 
certificated in any category, as identified in Airbus Mandatory 
Service Bulletin A300-24-0103, Revision 03, dated February 18, 2009.

Subject

    (d) Air Transport Association (ATA) of America Code 24: 
Electrical power.

Reason

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

    Further to the accident of a Boeing 747-131 (flight TWA800), the 
FAA has published SFAR 88 (Special Federal Aviation Regulation 88). 
Subsequently, the Joint Aviation Authorities (JAA) recommended the 
application of a similar regulation to the National Aviation 
Authorities (NAA) of its member countries. Under this regulation, 
all holders of type certificates for passenger transport aeroplane 
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 after 01 January 1958, are required to conduct a 
design review against explosion risks.
    One of the consequences of the Airbus design review is the 
modification of the fuel

[[Page 63578]]

pump wiring to provide protection against chafing of the fuel pump 
cables. This condition, if not corrected, could generate short 
circuits leading to fuel pump failure and arcing. These could become 
a potential ignition source inside the fuel tank which, in 
combination with flammable fuel vapours (if present), could result 
in a fuel tank explosion and consequent loss of the aeroplane.
    To address this unsafe condition, EASA [European Aviation Safety 
Agency] issued AD 2007-0066 that required this modification in 
accordance with Airbus Service Bulletin (SB) A300-24-0103 Revision 
01. Airbus subsequently introduced an additional modification of the 
electrical wiring of the outer fuel pump and the landing lights of 
the left (LH) and the right (RH) side in Revision 02 of the SB A300-
24-0103, leading to the issuance of EASA AD 2008-0188 which 
superseded EASA AD 2007-0066 and required the additional work.
    More recently, Airbus introduced some additional protection to 
routes 1P and 2P harnesses in zone 571 and 671 of the aeroplane.
    For the reason described above, this new AD retains the 
requirements of EASA AD 2008-0188, which is superseded, and requires 
the additional work as specified in Revision 03 of Airbus SB A300-
24-0103.

    The additional modification will provide additional protection 
from chafing and will prevent intermittent operation of the fuel 
pump and landing lights, as well as failure of the power supply. The 
modification of the wiring of the outer fuel pump and the landing 
light on the LH side route 1P harness and RH side route 2P harness 
includes additional mechanical protection that includes procedures 
for installing new splicing on the wires, a new cable type, shrink 
sleeve installation on the new wiring, and an additional braided 
conduit sleeve (Halar), as applicable, for the fuel pumps and the 
landing lights.

Restatement of Requirements of AD 2007-18-02, With Revised Service 
Information

    (f) Within 31 months after October 2, 2007 (the effective date 
of AD 2007-18-02), unless already done, modify the inner and outer 
fuel pump wiring, route 1P and 2P harnesses in the LH (left-hand) 
wing and in the RH (right-hand) wing, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-24-0103, 
Revision 01, dated January 11, 2007; or Airbus Mandatory Service 
Bulletin A300-24-0103, Revision 03, dated February 18, 2009. After 
the effective date of this AD, use only Airbus Mandatory Service 
Bulletin A300-24-0103, Revision 03, dated February 18, 2009. Actions 
done before October 2, 2007, in accordance with Airbus Service 
Bulletin A300-24-0103, dated March 15, 2006, for airplanes under 
configuration 1 as defined in Airbus Service Bulletin A300-24-0103, 
Revision 01, dated January 11, 2007; Revision 02, dated April 4, 
2008; or Revision 03, dated February 18, 2009; are acceptable for 
compliance with the requirements of this paragraph.

New Requirements of This AD

Actions and Compliance

    (g) Unless already done, within 12 months after the effective 
date of this AD, modify the wiring of the outer fuel pump and the 
landing light on the LH side route 1P harness and RH side route 2P 
harness in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-24-0103, Revision 03, dated February 
18, 2009.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (h) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 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 on any airplane to which the AMOC applies, 
notify your appropriate principal inspector (PI) in the FAA Flight 
Standards District Office (FSDO), or lacking a PI, your local FSDO. 
AMOCs approved previously in accordance with AD 2007-18-02, 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.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (i) Refer to MCAI EASA Airworthiness Directive 2009-0157, dated 
July 17, 2009; Airbus Service Bulletin A300-24-0103, Revision 01, 
dated January 11, 2007; and Airbus Mandatory Service Bulletin A300-
24-0103, Revision 03, dated February 18, 2009; for related 
information.

Material Incorporated by Reference

    (j) You must use Airbus Mandatory Service Bulletin A300-24-0103, 
Revision 03, dated February 18, 2009, to do the actions required by 
this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) 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 http://www.airbus.com.
    (3) 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 or 425-227-1152.
    (4) You may also review copies of the service information that 
is incorporated by 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on November 23, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-28797 Filed 12-3-09; 8:45 am]
BILLING CODE 4910-13-P