Airworthiness Directives; Airbus Model A310-221, -222, -322, -324, and -325 Airplanes, and Model A300B4-620, B4-622, B4-622R, F4-605R, and F4-622R Airplanes, Equipped With Pratt & Whitney PW4000 or JT9D-7R4 Series Engines, 34516-34518 [E9-16942]

Download as PDF 34516 Federal Register / Vol. 74, No. 135 / Thursday, July 16, 2009 / Proposed Rules original issue date on this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (i) Where Boeing Alert Service Bulletin 767–53A0193, Revision 1, dated April 9, 2009, specifies to contact Boeing for appropriate action, accomplish applicable actions before further flight using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (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, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and the approval must specifically refer to this AD. Report (j) At the applicable time specified in paragraph (j)(1) or (j)(2) of this AD: Submit a report of the findings (both positive and negative) of the inspections required by paragraph (g) of this AD. Operators may use the reporting form contained in Appendixes B and C, as applicable, of Boeing Alert Service Bulletin 767–53A0193, Revision 1, dated April 9, 2009. Send the report to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. The report must contain, at a minimum, the inspection results, a description of any discrepancies found, the airplane serial number, and the number of flight cycles and flight hours on the airplane. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. Issued in Renton, Washington, on July 2, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–16872 Filed 7–15–09; 8:45 am] erowe on DSK5CLS3C1PROD with PROPOSALS-1 Credit for Actions Accomplished Previously (k) Actions accomplished previously in accordance with Boeing Alert Service Bulletin 767–53A0193, dated November 25, 2008, are considered acceptable for compliance with the applicable actions specified in this AD. Alternative Methods of Compliance (AMOCs) (l)(1) The Manager, Seattle Aircraft Certification Office (ACO), 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: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 917–6577; fax (425) 917–6590. Or, e-mail information to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (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 principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. VerDate Nov<24>2008 15:08 Jul 15, 2009 Jkt 217001 BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0613; Directorate Identifier 2009–NM–013–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A310–221, –222, –322, –324, and –325 Airplanes, and Model A300B4–620, B4– 622, B4–622R, F4–605R, and F4–622R Airplanes, Equipped With Pratt & Whitney PW4000 or JT9D–7R4 Series Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed 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: During the year 2000, life extension exercise programs were launched for Airbus A310 and A300–600 aircraft. Certification of Extended Service Goal (ESG) is based on analysis, except for fan cowl and thrust reverser (T/R) latches, which are always certified by tests. * * * testing of the T/R door centre latch has shown that this does not meet the requirements for ESG. * * * * * The unsafe condition is possible failure of the T/R latch and detachment of the T/R from the airplane, which could result in structural damage and consequent reduced controllability of the airplane. The proposed AD would PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by August 17, 2009. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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 W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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. You may review copies of the referenced 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. 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 this proposed AD, 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. 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the E:\FR\FM\16JYP1.SGM 16JYP1 Federal Register / Vol. 74, No. 135 / Thursday, July 16, 2009 / Proposed Rules section. Include ‘‘Docket No. FAA–2009–0613; Directorate Identifier 2009–NM–013–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. ADDRESSES Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2008–0226, dated December 19, 2008 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: erowe on DSK5CLS3C1PROD with PROPOSALS-1 During the year 2000, life extension exercise programs were launched for Airbus A310 and A300–600 aircraft. Certification of Extended Service Goal (ESG) is based on analysis, except for fan cowl and thrust reverser (T/R) latches, which are always certified by tests. Currently, the Airworthiness Limitation Item (ALI) task 54–50–28 for engine pylon T/ R hinges requires inspection every 1,200 Flight Cycles (FC). An analysis performed by Airbus shows that forward and aft T/R door latches have been demonstrated successful for ESG, with inspection task every 1,200 FC. However, testing of the T/R door centre latch has shown that this does not meet the requirements for ESG. For the reason described above, this EASA AD requires the replacement of the T/R centre latches with serialized latches on LH [left hand] and RH [right hand] engines and repetitive inspections [for cracking] of the serialized latches. In addition, this AD introduces a life limit of 18,000 FC for the serialized centre latches. The unsafe condition is possible failure of the T/R latch and detachment of the T/R from the airplane, which could result in structural damage and consequent reduced controllability of the airplane. The corrective action includes replacing the T/R latch if any surface crack is found during any inspection. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Mandatory Service Bulletins A300–78–6029 and A310–78– 2030, both including Appendix 1, both dated October 3, 2008. The actions described in this service information are VerDate Nov<24>2008 15:08 Jul 15, 2009 Jkt 217001 intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. 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 proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 207 products of U.S. registry. We also estimate that it would take about 30 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Required parts would cost about $6,442 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 the proposed AD on U.S. operators to be $1,830,294, or $8,842 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 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 34517 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Airbus: Docket No. FAA–2009–0613; Directorate Identifier 2009–NM–013–AD. E:\FR\FM\16JYP1.SGM 16JYP1 34518 Federal Register / Vol. 74, No. 135 / Thursday, July 16, 2009 / Proposed Rules Comments Due Date (a) We must receive comments by August 17, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A310– 221, –222, –322, –324, and –325 airplanes, and Model A300B4–620, B4–622, B4–622R, F4–605R, and F4–622R airplanes, all serial numbers; certificated in any category; equipped with Pratt & Whitney PW4000 or JT9D–7R4 series engines. Subject (d) Air Transport Association (ATA) of America Code 78: Engine exhaust. erowe on DSK5CLS3C1PROD with PROPOSALS-1 Reason (e) The mandatory continuing airworthiness information (MCAI) states: During the year 2000, life extension exercise programs were launched for Airbus A310 and A300–600 aircraft. Certification of Extended Service Goal (ESG) is based on analysis, except for fan cowl and thrust reverser (T/R) latches, which are always certified by tests. Currently, the Airworthiness Limitation Item (ALI) task 54–50–28 for engine pylon T/ R hinges requires inspection every [1,200] Flight Cycles (FC). An analysis performed by Airbus shows that forward and aft T/R door latches have been demonstrated successful for ESG, with inspection task every 1200 FC. However, testing of the T/R door centre latch has shown that this does not meet the requirements for ESG. For the reason described above, this EASA AD requires the replacement of the T/R centre latches with serialized latches on LH [left hand] and RH [right hand] engines and repetitive inspections [for cracking] of the serialized latches. In addition, this AD introduces a life limit of 18000 FC for the serialized centre latches. The unsafe condition is possible failure of the T/R latch and detachment of the T/R from the airplane, which could result in structural damage and consequent reduced controllability of the airplane. The corrective action includes replacing the T/R latch if any surface crack is found during any inspection. Actions and Compliance (f) Unless already done, do the following actions. (1) Before the accumulation of 30,000 total flight cycles since first flight of the airplane, or within 1,200 flight cycles after the effective date of this AD, whichever occurs later: Replace the non-serialized T/R center latch LH (left hand) and RH (right hand) sides, having part number (P/N) 221D0029– 11 and P/N 221D0029–13, with a serialized T/R center latch having P/N 221D0029–15 in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–78–6029 or A310–78–2030, both including Appendix 1, both dated October 3, 2008; as applicable. (2) Within 1,200 flight cycles after accomplishing the replacement required by paragraph (f)(1) of this AD: Perform an VerDate Nov<24>2008 15:08 Jul 15, 2009 Jkt 217001 inspection for surface cracking of the T/R center serialized latches having P/N 221D0029–15, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–78–6029 or A310–78–2030, both including Appendix 1, both dated October 3, 2008; as applicable. If any crack is found, before further flight, replace the serialized T/R center latch with a new serialized T/R center latch in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–78–6029 or A310–78–2030, both including Appendix 1, both dated October 3, 2008; as applicable. Repeat the inspection thereafter at intervals not to exceed 1,200 flight cycles. (3) Before the accumulation of 18,000 total flight cycles since accomplishing the most recent replacement required by paragraph (f)(1) or (f)(2) of this AD: Replace the serialized T/R center latch having P/N 221D0029–15 with a new serialized T/R center latch having P/N 221D0029–15 in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–78–6029 or A310–78–2030, both including Appendix 1, both dated October 3, 2008; as applicable. Replacement of the center latches does not constitute terminating action for the repetitive inspections required by paragraph (f)(2) of this AD. FAA AD Differences Note 1: 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: 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 principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference 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 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2008– 0226, dated December 19, 2008; and Airbus Mandatory Service Bulletins A300–78–6029 and A310–78–2030, both including Appendix 1, both dated October 3, 2008; for related information. Issued in Renton, Washington, on July 2, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–16942 Filed 7–15–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25001; Directorate Identifier 2006–NM–079–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–600, –700, –700C, –800, –900 and –900ER Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. SUMMARY: We are revising an earlier proposed airworthiness directive (AD) for all Boeing Model 737–600, –700, –700C, –800, –900 and –900ER series airplanes. That supplemental NPRM would have required a one-time inspection to determine the part numbers of the aero/fire seals of the blocker doors on the thrust reverser torque boxes on the engines, and replacing affected aero/fire seals with new improved aero/fire seals. This action resulted from a report that the top 3 inches of the aero/fire seals of the blocker doors on the thrust reverser torque boxes are not fireproof. This second supplemental NPRM revises the first supplemental NPRM by changing the compliance time for the replacement. We are proposing this second supplemental NPRM to prevent a fire in the fan compartment (a fire zone) from migrating through the seal to a flammable fluid in the thrust reverser actuator compartment (a flammable fluid leakage zone), which could result in an uncontrolled fire. DATES: We must receive comments on this supplemental NPRM by August 10, 2009. E:\FR\FM\16JYP1.SGM 16JYP1

Agencies

[Federal Register Volume 74, Number 135 (Thursday, July 16, 2009)]
[Proposed Rules]
[Pages 34516-34518]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-16942]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0613; Directorate Identifier 2009-NM-013-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310-221, -222, -322, -
324, and -325 Airplanes, and Model A300B4-620, B4-622, B4-622R, F4-
605R, and F4-622R Airplanes, Equipped With Pratt & Whitney PW4000 or 
JT9D-7R4 Series Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed 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:

    During the year 2000, life extension exercise programs were 
launched for Airbus A310 and A300-600 aircraft. Certification of 
Extended Service Goal (ESG) is based on analysis, except for fan 
cowl and thrust reverser (T/R) latches, which are always certified 
by tests.

* * * testing of the T/R door centre latch has shown that this does 
not meet the requirements for ESG.
* * * * *

The unsafe condition is possible failure of the T/R latch and 
detachment of the T/R from the airplane, which could result in 
structural damage and consequent reduced controllability of the 
airplane. The proposed AD would require actions that are intended to 
address the unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by August 17, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://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 W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed 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. You may review copies of the referenced 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.

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 this proposed AD, 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.

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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the

[[Page 34517]]

ADDRESSES section. Include ``Docket No. FAA-2009-0613; Directorate 
Identifier 2009-NM-013-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this proposed AD. We will consider 
all comments received by the closing date and may amend this proposed 
AD based on those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2008-0226, dated December 19, 2008 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    During the year 2000, life extension exercise programs were 
launched for Airbus A310 and A300-600 aircraft. Certification of 
Extended Service Goal (ESG) is based on analysis, except for fan 
cowl and thrust reverser (T/R) latches, which are always certified 
by tests.
    Currently, the Airworthiness Limitation Item (ALI) task 54-50-28 
for engine pylon T/R hinges requires inspection every 1,200 Flight 
Cycles (FC). An analysis performed by Airbus shows that forward and 
aft T/R door latches have been demonstrated successful for ESG, with 
inspection task every 1,200 FC. However, testing of the T/R door 
centre latch has shown that this does not meet the requirements for 
ESG.
    For the reason described above, this EASA AD requires the 
replacement of the T/R centre latches with serialized latches on LH 
[left hand] and RH [right hand] engines and repetitive inspections 
[for cracking] of the serialized latches. In addition, this AD 
introduces a life limit of 18,000 FC for the serialized centre 
latches.

The unsafe condition is possible failure of the T/R latch and 
detachment of the T/R from the airplane, which could result in 
structural damage and consequent reduced controllability of the 
airplane. The corrective action includes replacing the T/R latch if any 
surface crack is found during any inspection. You may obtain further 
information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletins A300-78-6029 and 
A310-78-2030, both including Appendix 1, both dated October 3, 2008. 
The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

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 proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 207 products of U.S. registry. We also estimate that 
it would take about 30 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $80 per 
work-hour. Required parts would cost about $6,442 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 the proposed AD on U.S. operators to 
be $1,830,294, or $8,842 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Airbus: Docket No. FAA-2009-0613; Directorate Identifier 2009-NM-
013-AD.

[[Page 34518]]

Comments Due Date

    (a) We must receive comments by August 17, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A310-221, -222, -322, -324, 
and -325 airplanes, and Model A300B4-620, B4-622, B4-622R, F4-605R, 
and F4-622R airplanes, all serial numbers; certificated in any 
category; equipped with Pratt & Whitney PW4000 or JT9D-7R4 series 
engines.

Subject

    (d) Air Transport Association (ATA) of America Code 78: Engine 
exhaust.

Reason

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

    During the year 2000, life extension exercise programs were 
launched for Airbus A310 and A300-600 aircraft. Certification of 
Extended Service Goal (ESG) is based on analysis, except for fan 
cowl and thrust reverser (T/R) latches, which are always certified 
by tests.
    Currently, the Airworthiness Limitation Item (ALI) task 54-50-28 
for engine pylon T/R hinges requires inspection every [1,200] Flight 
Cycles (FC). An analysis performed by Airbus shows that forward and 
aft T/R door latches have been demonstrated successful for ESG, with 
inspection task every 1200 FC. However, testing of the T/R door 
centre latch has shown that this does not meet the requirements for 
ESG.
    For the reason described above, this EASA AD requires the 
replacement of the T/R centre latches with serialized latches on LH 
[left hand] and RH [right hand] engines and repetitive inspections 
[for cracking] of the serialized latches. In addition, this AD 
introduces a life limit of 18000 FC for the serialized centre 
latches.

The unsafe condition is possible failure of the T/R latch and 
detachment of the T/R from the airplane, which could result in 
structural damage and consequent reduced controllability of the 
airplane. The corrective action includes replacing the T/R latch if 
any surface crack is found during any inspection.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Before the accumulation of 30,000 total flight cycles since 
first flight of the airplane, or within 1,200 flight cycles after 
the effective date of this AD, whichever occurs later: Replace the 
non-serialized T/R center latch LH (left hand) and RH (right hand) 
sides, having part number (P/N) 221D0029-11 and P/N 221D0029-13, 
with a serialized T/R center latch having P/N 221D0029-15 in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A300-78-6029 or A310-78-2030, both including 
Appendix 1, both dated October 3, 2008; as applicable.
    (2) Within 1,200 flight cycles after accomplishing the 
replacement required by paragraph (f)(1) of this AD: Perform an 
inspection for surface cracking of the T/R center serialized latches 
having P/N 221D0029-15, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A300-78-6029 or 
A310-78-2030, both including Appendix 1, both dated October 3, 2008; 
as applicable. If any crack is found, before further flight, replace 
the serialized T/R center latch with a new serialized T/R center 
latch in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-78-6029 or A310-78-2030, both 
including Appendix 1, both dated October 3, 2008; as applicable. 
Repeat the inspection thereafter at intervals not to exceed 1,200 
flight cycles.
    (3) Before the accumulation of 18,000 total flight cycles since 
accomplishing the most recent replacement required by paragraph 
(f)(1) or (f)(2) of this AD: Replace the serialized T/R center latch 
having P/N 221D0029-15 with a new serialized T/R center latch having 
P/N 221D0029-15 in accordance with the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A300-78-6029 or A310-78-2030, 
both including Appendix 1, both dated October 3, 2008; as 
applicable. Replacement of the center latches does not constitute 
terminating action for the repetitive inspections required by 
paragraph (f)(2) of this AD.

FAA AD Differences

    Note 1:  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: 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 principal maintenance inspector (PMI) or principal 
avionics inspector (PAI), as appropriate, or lacking a principal 
inspector, your local Flight Standards District Office. The AMOC 
approval letter must specifically reference 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

    (h) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2008-0226, dated December 19, 2008; and Airbus Mandatory 
Service Bulletins A300-78-6029 and A310-78-2030, both including 
Appendix 1, both dated October 3, 2008; for related information.

    Issued in Renton, Washington, on July 2, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-16942 Filed 7-15-09; 8:45 am]
BILLING CODE 4910-13-P
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