Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes, 69593-69595 [E7-23682]

Download as PDF Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Rules and Regulations bulletin specifies a compliance time after the date on the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. Repair of Certain Conditions (g) If any crack is found during any inspection required by paragraph (f) of this AD and Boeing Alert Service Bulletin MD80– 53A298, dated August 1, 2006, specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD. Corrective Action for Configuration 4 Airplanes (h) For airplanes identified as Configuration 4 in Boeing Alert Service Bulletin MD80–53A298, dated August 1, 2006: Within 90 days after the effective date of this AD, repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD. mstockstill on PROD1PC66 with RULES Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD. Material Incorporated by Reference (j) You must use the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–53A298, dated August 1, 2006, 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 Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024). (3) You may review copies of the service information incorporated by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call VerDate Aug<31>2005 16:20 Dec 07, 2007 Jkt 214001 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 29, 2007. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–23687 Filed 12–7–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–29249; Directorate Identifier 2007–NM–112–AD; Amendment 39–15294; AD 2007–25–12] RIN 2120–AA64 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new 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: After a push back from the gate, an A320– 200 aircraft was preparing to initiate taxi, when a NLG (nose landing gear) uncommanded retraction occurred, and then the aircraft abruptly hit the ground. * * * Untimely unlocking and/or retraction of the NLG, while on the ground, could cause injury to ground personnel and significant structural damage to the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective January 14, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 14, 2008. 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: Tim Dulin, Aerospace Engineer, PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 69593 International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; 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 September 20, 2007 (72 FR 53699). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: After push back from the gate, an A320– 200 aircraft was preparing to initiate taxi, when a NLG (nose landing gear) uncommanded retraction occurred, and then the aircraft abruptly hit the ground. Investigations revealed that the retract condition is caused by a combination of a faulty MLG (main landing gear) proximity switch, a power interruption to LGCIUs (Landing Gear Control and Interface Units) and an internal hydraulic leak through the LG (landing gear) selector valve 40GA. The internal hydraulic leak through the LG selector valve 40GA was due to a broken seal in one of the end cap chambers for the valve spool. As a corrective action, a duplicate inspection (DI or DI–BE) for these valves has been introduced in production, and the Component Maintenance Manual (CMM) has been revised. Untimely unlocking and/or retraction of the NLG, while on the ground, could cause injury to ground personnel and significant structural damage to the aircraft. This Airworthiness Directive (AD) mandates the inspections of the LG selector valve 40GA and the LG door selector valve 41GA, to identify a possible hydraulic leak. The corrective action includes replacing the LG selector valve 40GA and/or the LG door selector valve 41GA if necessary. 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 received no comments on the NPRM or on the determination of the cost to the public. Editorial Change We have revised paragraphs (f)(1), (f)(2), and (f)(3) of this AD by removing the phrase ‘‘if necessary’’ and adding the phrase ‘‘as applicable,’’ in order to clarify that the replacement must be done if leaking is found. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD with the changes described previously. E:\FR\FM\10DER1.SGM 10DER1 69594 Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Rules and Regulations 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 653 products of U.S. registry. We also estimate that it will take about 7 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $365,680, or $560 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. mstockstill on PROD1PC66 with RULES 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 VerDate Aug<31>2005 16:20 Dec 07, 2007 Jkt 214001 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. (1) Manufacturer serial numbers (MSNs) 2389, 2392, 2393, 2396, 2398, 2403, 2405, 2407, 2409, 2410, 2411, 2413 through 2439, 2441, and MSNs above 2441, on which no replacement of the landing gear (LG) selector valve 40GA or the LG door selector valve 41GA has been performed since aircraft delivery from Airbus. (2) Aircraft on which LG selector valve 40GA and LG door selector valve 41GA have been stamped to indicate that a duplicate inspection has been done. If the duplicate inspection has been done, the amendment plates on the valves will be stamped with letters ‘‘DI’’ or ‘‘DI–BE.’’ 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. Reason (e) The mandatory continuing airworthiness information (MCAI) states: ‘‘After push back from the gate, an A320– 200 aircraft was preparing to initiate taxi, when an NLG (nose landing gear) uncommanded retraction occurred, and then the aircraft abruptly hit the ground. Investigations revealed that the retract condition is caused by a combination of a faulty MLG (main landing gear) proximity switch, a power interruption to LGCIUs (Landing Gear Control and Interface Units) and an internal hydraulic leak through the LG (landing gear) selector valve 40GA. The internal hydraulic leak through the LG selector valve 40GA was due to a broken seal in one of the end cap chambers for the valve spool. As a corrective action, a duplicate inspection (DI or DI–BE) for these valves has been introduced in production, and the Component Maintenance Manual (CMM) has been revised. Untimely unlocking and/or retraction of the NLG, while on the ground, could cause injury to ground personnel and significant structural damage to the aircraft. This Airworthiness Directive (AD) mandates the inspections of the LG selector valve 40GA and the LG door selector valve 41GA, to identify a possible hydraulic leak.’’ The corrective action includes replacing the LG selector valve 40GA and/or the LG door selector valve 41GA if necessary. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I 2007–25–12 Airbus: Amendment 39–15294. Docket No. FAA–2007–29249; Directorate Identifier 2007–NM–112–AD. Effective Date (a) This Airworthiness Directive (AD) becomes effective January 14, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A318, A319, A320, and A321 series airplanes, certificated in any category, except those identified in paragraphs (c)(1) and (c)(2) of this AD. PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 Subject (d) Air Transport Association (ATA) of America Code 32: Landing Gear. Actions and Compliance (f) Unless already done, do the following actions. (1) For aircraft that have accumulated up to and including 20,000 total flight cycles as of the effective date of this AD: Within 4,500 flight cycles after the effective date of this AD, but not exceeding 20,800 total flight cycles, inspect for hydraulic leaking of the LG selector valve 40GA and the LG door selector valve 41GA and, as applicable, replace the LG selector valve 40GA and the LG door selector valve 41GA before further flight in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1290, Revision 01, dated November 10, 2006. (2) For aircraft that have accumulated over 20,000 total flight cycles as of the effective date of this AD: Within 800 flight cycles after the effective date of this AD, inspect for hydraulic leaking of the LG selector valve E:\FR\FM\10DER1.SGM 10DER1 Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Rules and Regulations 40GA and the LG door selector valve 41GA and, as applicable, replace the LG selector valve 40GA and the LG door selector valve 41GA before further flight in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1290, Revision 01, dated November 10, 2006. (3) For all airplanes: Repeat the inspection specified in paragraph (f)(1) or (f)(2) of this AD, as applicable, thereafter at intervals not to exceed 20,000 flight cycles, or 89 months, whichever occurs first, and, as applicable, (i.e., if any leakage is found) replace the LG selector valve 40GA and the LG door selector valve 41GA before further flight, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 32–1290, Revision 01, dated November 10, 2006. (4) For all airplanes: From the effective date of this AD, the installation of LG selector valve 40GA or LG door selector valve 41GA, that do not have the duplicate inspection ‘‘DI’’ or ‘‘DI-BE’’ recorded on their amendment plates, is possible provided that it is inspected within 800 flight cycles after installation, in accordance with the instructions given in Airbus Service Bulletin A320–32–1290, Revision 01, dated November 10, 2006. Repeat the inspection thereafter as given in paragraph (f)(3) of this AD. (5) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A320–32–1290, dated May 2, 2006, are acceptable for compliance with the corresponding actions of this AD. FAA AD Differences mstockstill on PROD1PC66 with RULES Note: This AD differs from the MCAI and/ or service information as follows: No differences. Other FAA AD Provisions (g) 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: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; 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. (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 FAAapproved 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 VerDate Aug<31>2005 16:20 Dec 07, 2007 Jkt 214001 69595 requirements and has assigned OMB Control Number 2120–0056. of Italy, with which we have a bilateral agreement, states in the MCAI: Related Information (h) Refer to MCAI EASA Airworthiness Directive 2007–0065R1, dated June 12, 2007, and Airbus Service Bulletin A320–32–1290, Revision 01, dated November 10, 2006, for related information. Field reports have shown that the Agusta AB/AW139’s Tailpipe Assembly is prone to cracks. To prevent any cracks from developing into failure of the exhaust tailpipe assembly * * * Material Incorporated by Reference (i) You must use Airbus Service Bulletin A320–32–1290, Revision 01, excluding Appendix 01, dated November 10, 2006, 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, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. (3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on November 21, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–23682 Filed 12–7–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0285; Directorate Identifier 2007–SW–15–AD; Amendment 39– 15296; AD 2007–25–14] RIN 2120–AA64 Airworthiness Directives; Agusta S.p.A. Model AB139 and AW139 Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: We are superseding an existing airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB139 helicopters. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority to identify and correct an unsafe condition on an aviation product. The aviation authority PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 This AD retains the requirements of the existing AD, but expands the applicability to include the Agusta Model AW139 helicopters and includes modification procedures to strengthen certain cracked areas that are outside the cowling and are within certain allowable limits. This AD requires actions that are intended to address the unsafe condition of cracks in the tailpipe assembly. DATES: This AD becomes effective December 26, 2007. The Director of the Federal Register approved the incorporation by reference of Agusta Bollettino Tecnico No. 139– 069, Revision A, dated November 8, 2006, as of December 26, 2007. We must receive comments on this AD by February 8, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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 this AD, the economic 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. FOR FURTHER INFORMATION CONTACT: Ed Cuevas, Aerospace Engineer, Safety Management Office, FAA, Rotorcraft Directorate, Fort Worth, Texas 76193– 0111, telephone (817) 222–5355, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: E:\FR\FM\10DER1.SGM 10DER1

Agencies

[Federal Register Volume 72, Number 236 (Monday, December 10, 2007)]
[Rules and Regulations]
[Pages 69593-69595]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-23682]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-29249; Directorate Identifier 2007-NM-112-AD; 
Amendment 39-15294; AD 2007-25-12]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A318, A319, A320, and A321 
Series Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new 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:

    After a push back from the gate, an A320-200 aircraft was 
preparing to initiate taxi, when a NLG (nose landing gear) 
uncommanded retraction occurred, and then the aircraft abruptly hit 
the ground.
    * * * Untimely unlocking and/or retraction of the NLG, while on 
the ground, could cause injury to ground personnel and significant 
structural damage to the airplane.

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

DATES: This AD becomes effective January 14, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 14, 
2008.

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: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2141; 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 September 20, 2007 
(72 FR 53699). That NPRM proposed to correct an unsafe condition for 
the specified products. The MCAI states:

    After push back from the gate, an A320-200 aircraft was 
preparing to initiate taxi, when a NLG (nose landing gear) 
uncommanded retraction occurred, and then the aircraft abruptly hit 
the ground.
    Investigations revealed that the retract condition is caused by 
a combination of a faulty MLG (main landing gear) proximity switch, 
a power interruption to LGCIUs (Landing Gear Control and Interface 
Units) and an internal hydraulic leak through the LG (landing gear) 
selector valve 40GA. The internal hydraulic leak through the LG 
selector valve 40GA was due to a broken seal in one of the end cap 
chambers for the valve spool. As a corrective action, a duplicate 
inspection (DI or DI-BE) for these valves has been introduced in 
production, and the Component Maintenance Manual (CMM) has been 
revised. Untimely unlocking and/or retraction of the NLG, while on 
the ground, could cause injury to ground personnel and significant 
structural damage to the aircraft.
    This Airworthiness Directive (AD) mandates the inspections of 
the LG selector valve 40GA and the LG door selector valve 41GA, to 
identify a possible hydraulic leak.

The corrective action includes replacing the LG selector valve 40GA 
and/or the LG door selector valve 41GA if necessary. 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 received no comments on the NPRM or on the determination of 
the cost to the public.

Editorial Change

    We have revised paragraphs (f)(1), (f)(2), and (f)(3) of this AD by 
removing the phrase ``if necessary'' and adding the phrase ``as 
applicable,'' in order to clarify that the replacement must be done if 
leaking is found.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously.

[[Page 69594]]

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 653 products of U.S. 
registry. We also estimate that it will take about 7 work-hours per 
product to comply with the basic requirements of this AD. The average 
labor rate is $80 per work-hour. Based on these figures, we estimate 
the cost of this AD to the U.S. operators to be $365,680, or $560 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 adding the following new AD:

2007-25-12 Airbus: Amendment 39-15294. Docket No. FAA-2007-29249; 
Directorate Identifier 2007-NM-112-AD.

Effective Date

    (a) This Airworthiness Directive (AD) becomes effective January 
14, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A318, A319, A320, and A321 
series airplanes, certificated in any category, except those 
identified in paragraphs (c)(1) and (c)(2) of this AD.
    (1) Manufacturer serial numbers (MSNs) 2389, 2392, 2393, 2396, 
2398, 2403, 2405, 2407, 2409, 2410, 2411, 2413 through 2439, 2441, 
and MSNs above 2441, on which no replacement of the landing gear 
(LG) selector valve 40GA or the LG door selector valve 41GA has been 
performed since aircraft delivery from Airbus.
    (2) Aircraft on which LG selector valve 40GA and LG door 
selector valve 41GA have been stamped to indicate that a duplicate 
inspection has been done. If the duplicate inspection has been done, 
the amendment plates on the valves will be stamped with letters 
``DI'' or ``DI-BE.''

Subject

    (d) Air Transport Association (ATA) of America Code 32: Landing 
Gear.

Reason

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

    ``After push back from the gate, an A320-200 aircraft was 
preparing to initiate taxi, when an NLG (nose landing gear) 
uncommanded retraction occurred, and then the aircraft abruptly hit 
the ground.
    Investigations revealed that the retract condition is caused by 
a combination of a faulty MLG (main landing gear) proximity switch, 
a power interruption to LGCIUs (Landing Gear Control and Interface 
Units) and an internal hydraulic leak through the LG (landing gear) 
selector valve 40GA. The internal hydraulic leak through the LG 
selector valve 40GA was due to a broken seal in one of the end cap 
chambers for the valve spool. As a corrective action, a duplicate 
inspection (DI or DI-BE) for these valves has been introduced in 
production, and the Component Maintenance Manual (CMM) has been 
revised. Untimely unlocking and/or retraction of the NLG, while on 
the ground, could cause injury to ground personnel and significant 
structural damage to the aircraft.
    This Airworthiness Directive (AD) mandates the inspections of 
the LG selector valve 40GA and the LG door selector valve 41GA, to 
identify a possible hydraulic leak.''

The corrective action includes replacing the LG selector valve 40GA 
and/or the LG door selector valve 41GA if necessary.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) For aircraft that have accumulated up to and including 
20,000 total flight cycles as of the effective date of this AD: 
Within 4,500 flight cycles after the effective date of this AD, but 
not exceeding 20,800 total flight cycles, inspect for hydraulic 
leaking of the LG selector valve 40GA and the LG door selector valve 
41GA and, as applicable, replace the LG selector valve 40GA and the 
LG door selector valve 41GA before further flight in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1290, Revision 01, dated November 10, 2006.
    (2) For aircraft that have accumulated over 20,000 total flight 
cycles as of the effective date of this AD: Within 800 flight cycles 
after the effective date of this AD, inspect for hydraulic leaking 
of the LG selector valve

[[Page 69595]]

40GA and the LG door selector valve 41GA and, as applicable, replace 
the LG selector valve 40GA and the LG door selector valve 41GA 
before further flight in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-32-1290, Revision 01, 
dated November 10, 2006.
    (3) For all airplanes: Repeat the inspection specified in 
paragraph (f)(1) or (f)(2) of this AD, as applicable, thereafter at 
intervals not to exceed 20,000 flight cycles, or 89 months, 
whichever occurs first, and, as applicable, (i.e., if any leakage is 
found) replace the LG selector valve 40GA and the LG door selector 
valve 41GA before further flight, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-32-1290, 
Revision 01, dated November 10, 2006.
    (4) For all airplanes: From the effective date of this AD, the 
installation of LG selector valve 40GA or LG door selector valve 
41GA, that do not have the duplicate inspection ``DI'' or ``DI-BE'' 
recorded on their amendment plates, is possible provided that it is 
inspected within 800 flight cycles after installation, in accordance 
with the instructions given in Airbus Service Bulletin A320-32-1290, 
Revision 01, dated November 10, 2006. Repeat the inspection 
thereafter as given in paragraph (f)(3) of this AD.
    (5) Actions done before the effective date of this AD in 
accordance with Airbus Service Bulletin A320-32-1290, dated May 2, 
2006, are acceptable for compliance with the corresponding actions 
of this AD.

FAA AD Differences

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

Other FAA AD Provisions

    (g) 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: Tim 
Dulin, Aerospace Engineer, International Branch, ANM-116, FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-2141; 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.
    (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

    (h) Refer to MCAI EASA Airworthiness Directive 2007-0065R1, 
dated June 12, 2007, and Airbus Service Bulletin A320-32-1290, 
Revision 01, dated November 10, 2006, for related information.

Material Incorporated by Reference

    (i) You must use Airbus Service Bulletin A320-32-1290, Revision 
01, excluding Appendix 01, dated November 10, 2006, 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, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    (3) You may review copies at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call (202) 741-6030, 
or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on November 21, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-23682 Filed 12-7-07; 8:45 am]
BILLING CODE 4910-13-P