Airworthiness Directives; Airbus Model A310 Series Airplanes, 66745-66747 [E8-25767]

Download as PDF Federal Register / Vol. 73, No. 219 / Wednesday, November 12, 2008 / Rules and Regulations authority to approve AMOCs for this AD, if requested using 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, 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. Material Incorporated by Reference (j) You must use Boeing Special Attention Service Bulletin 727–55–0092, dated June 4, 2007, 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, P.O. Box 3707, Seattle, Washington 98124–2207; telephone 206– 544–9990; fax 206–766–5682; e-mail DDCS@boeing.com; Internet https:// www.myboeingfleet.com. (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 202–741–6030, or go to: https:// www.archives.gov/federal_register/code_of_ federal_regulations/ibr_locations.html. Issued in Renton, Washington, on October 9, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–25686 Filed 11–10–08; 8:45 am] mstockstill on PROD1PC66 with RULES BILLING CODE 4910–13–P VerDate Aug<31>2005 18:26 Nov 10, 2008 Jkt 217001 66745 DEPARTMENT OF TRANSPORTATION Discussion Federal Aviation Administration 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 August 7, 2008 (73 FR 45891). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: 14 CFR Part 39 [Docket No. FAA–2008–0849; Directorate Identifier 2008–NM–080–AD; Amendment 39–15709; AD 2008–22–13] RIN 2120–AA64 Airworthiness Directives; Airbus Model A310 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: Two operators of A300 aircraft fitted with General Electric (GE) CF6–50 engine series have reported cracks on the lower side of Rib 5 in the pylon box. * * * * * Investigations disclosed that these cracks are due to the stresses resulting from the pressure applied by the thrust reverser cowl bumpers. * * * * * Cracking of the engine pylons could result in reduced structural integrity of the engine support structure. We are issuing this AD to require actions to correct the unsafe condition on these products. This AD becomes effective December 17, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 17, 2008. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: DATES: PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 Two operators of A300 aircraft fitted with General Electric (GE) CF6–50 engine series have reported cracks on the lower side of Rib 5 in the pylon box. The concerned area is similar on A310 aircraft fitted with GE CF6–80A or CF6–80C series engines. Investigations disclosed that these cracks are due to the stresses resulting from the pressure applied by the thrust reverser cowl bumpers. As a result of the A310 Extended Service Goal (ESG) study, an inspection programme of this area is required by this Airworthiness Directive (AD). A similar inspection programme is being contemplated for A300 and A300–600 series aircraft. Cracking of the engine pylons could result in reduced structural integrity of the engine support structure. Corrective actions include modifying the Rib 5 in the pylon box. 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. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. 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. E:\FR\FM\12NOR1.SGM 12NOR1 66746 Federal Register / Vol. 73, No. 219 / Wednesday, November 12, 2008 / Rules and Regulations Costs of Compliance We estimate that this AD will affect about 33 products of U.S. registry. We also estimate that it will take about 8 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 $21,120, or $640 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 responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket VerDate Aug<31>2005 18:26 Nov 10, 2008 Jkt 217001 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. A similar inspection programme is being contemplated for A300 and A300–600 series aircraft. Cracking of the engine pylons could result in reduced structural integrity of the engine support structure. Corrective actions include modifying the Rib 5 in the pylon box. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Actions and Compliance 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 adding the following new AD: ■ 2008–22–13 Airbus: Amendment 39–15709. Docket No. FAA–2008–0849; Directorate Identifier 2008–NM–080–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 17, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A310– 203, –204, and –304 airplanes, all serial numbers, certificated in any category; excluding airplanes that have received Airbus Modification 11110 during production or that have been modified in service in accordance with Airbus Service Bulletin A310–54–2032 (Airbus Modification 11109). Subject (d) Air Transport Association (ATA) of America Code 54: Nacelles/Pylons. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Two operators of A300 aircraft fitted with General Electric (GE) CF6–50 engine series have reported cracks on the lower side of Rib 5 in the pylon box. The concerned area is similar on A310 aircraft fitted with GE CF6–80A or CF6–80C series engines. Investigations disclosed that these cracks are due to the stresses resulting from the pressure applied by the thrust reverser cowl bumpers. As a result of the A310 Extended Service Goal (ESG) study, an inspection programme of this area is required by this Airworthiness Directive (AD). PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 (f) Unless already done, do the following actions. (1) Perform a high frequency eddy current (HFEC) inspection and a detailed visual inspection on the lower side of Rib 5 of the left-hand and right-hand pylons, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310–54–2036, Revision 02, dated September 28, 2007. Do the inspections at the times specified in paragraph (f)(1)(i) or (f)(1)(ii) of this AD, as applicable. (i) For Model A310–203 and –204 airplanes: Inspect at the later of the times specified in paragraphs (f)(1)(i)(A) and (f)(1)(i)(B) of this AD. (A) Prior to the accumulation of 40,000 total flight cycles or 60,000 total flight hours, whichever occurs first. (B) Within 250 flight hours after the effective date of this AD. (ii) For Model A310–304 airplanes: Inspect at the later of the times specified in paragraphs (f)(1)(ii)(A) and (f)(1)(ii)(B) of this AD. (A) Prior to the accumulation of 35,000 total flight cycles or 60,000 total flight hours, whichever occurs first. (B) Within 250 flight hours after the effective date of this AD. (2) If no crack is found during any inspection required by paragraph (f)(1) of this AD: Repeat the inspections thereafter at intervals not to exceed 15,000 flight hours. (3) If any crack is found during any inspection required by paragraph (f)(1) of this AD: Before further flight, modify Rib 5 in the pylon box in accordance with the Accomplishment Instructions of Airbus Service Bulletins A310–54–2032, Revision 01, dated October 8, 2007. Accomplishment of this modification ends the repetitive inspections required by this AD. (4) Accomplishment of the HFEC and detailed visual inspections before the effective date of this AD in accordance with Airbus Service Bulletin A310–54–2036, Revision 01, dated September 14, 1999, meets the corresponding requirements of paragraph (f) of this AD. (5) Accomplishment of the modification before the effective date of this AD in accordance with Airbus Service Bulletin A310–54–2032, dated May 29, 1996, meets the corresponding requirements of paragraph (f) of this AD. (6) Submit the initial inspection results specified in Appendix 01 of Airbus Mandatory Service Bulletin A310–54–2036, Revision 02, dated September 28, 2007, at the time specified in paragraph (f)(6)(i) or (f)(6)(ii) of this AD. (i) If the inspections were done after the effective date of this AD: Within 30 days after accomplishing the inspections required by paragraph (f)(1) of this AD. E:\FR\FM\12NOR1.SGM 12NOR1 Federal Register / Vol. 73, No. 219 / Wednesday, November 12, 2008 / Rules and Regulations (ii) If the inspections were done prior to the effective date of this AD: Within 30 days after the effective date of this AD. FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: Although the MCAI allows further flight after cracks are found during compliance with the required action, this AD requires that you repair the crack(s) before further flight. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, 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. (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. mstockstill on PROD1PC66 with RULES Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2008–0066, dated March 31, 2008; Airbus Service Bulletin A310–54–2032, Revision 01, dated October 8, 2007; and Airbus Mandatory Service Bulletin A310–54– 2036, Revision 02, dated September 28, 2007; for related information. Material Incorporated by Reference (i) You must use Airbus Service Bulletin A310–54–2032, Revision 01, dated October 8, 2007; and Airbus Mandatory Service Bulletin A310–54–2036, including Appendix 01, Revision 02, dated September 28, 2007; as applicable; 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; telephone +33 5 61 93 33 33; Internet https://www.airbus.com. (3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind VerDate Aug<31>2005 18:26 Nov 10, 2008 Jkt 217001 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: https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on October 9, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–25767 Filed 11–10–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION 66747 of certain publications listed in this AD as of December 17, 2008. You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. ADDRESSES: FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. Federal Aviation Administration SUPPLEMENTARY INFORMATION: 14 CFR Part 39 Discussion [Docket No. FAA–2008–0667; Directorate Identifier 2008–NM–009–AD; Amendment 39–15717; AD 2008–22–20] 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 June 24, 2008 (73 FR 35603). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–200, A330–300, and A340–300 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: During fatigue tests (EF3) on the A340–600, damages were found in longitudinal doubler at VTP [vertical tail plane] attachment cutout between Frame (FR) 80 and FR86. This damage occurred between 58341 and 72891 simulated Flight Cycles (FC). Due to the higher Design Service Goal and different design (e.g., doubler thickness) [of the] A330–200/–300 and A340–300 aircraft series, the damage assessment concluded [there was] potential impact on [the airplanes specified in the] applicability. * * * * * The unsafe condition is crack propagation in the VTP attachment cutout, which could reduce airplane structural integrity in the tail section. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective December 17, 2008. The Director of the Federal Register approved the incorporation by reference PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 During fatigue tests (EF3) on the A340–600, damages were found in longitudinal doubler at VTP [vertical tail plane] attachment cutout between Frame (FR) 80 and FR86. This damage occurred between 58341 and 72891 simulated Flight Cycles (FC). Due to the higher Design Service Goal and different design (e.g., doubler thickness) [of the] A330–200/–300 and A340–300 aircraft series, the damage assessment concluded [there was] potential impact on [the airplanes specified in the] applicability. [T]o allow early detection of cracks, which could [prevent] possible crack propagation and consequently to maintain the structural integrity of the upper shell structure between FR80 and FR86, this Airworthiness Directive (AD) mandates an inspection program [for cracking] of this area using a high frequency eddy current (HFEC) method, and a modification to improve the upper shell structure. The unsafe condition is crack propagation in the VTP attachment cutout, which could reduce airplane structural integrity in the tail section. Corrective actions include doing eddy current inspections for cracking of certain fastener rows, and contacting Airbus for repair instructions and repairing. 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. E:\FR\FM\12NOR1.SGM 12NOR1

Agencies

[Federal Register Volume 73, Number 219 (Wednesday, November 12, 2008)]
[Rules and Regulations]
[Pages 66745-66747]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-25767]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0849; Directorate Identifier 2008-NM-080-AD; 
Amendment 39-15709; AD 2008-22-13]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 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:

    Two operators of A300 aircraft fitted with General Electric (GE) 
CF6-50 engine series have reported cracks on the lower side of Rib 5 
in the pylon box.
* * * * *
    Investigations disclosed that these cracks are due to the 
stresses resulting from the pressure applied by the thrust reverser 
cowl bumpers.
* * * * *

Cracking of the engine pylons could result in reduced structural 
integrity of the engine support structure. We are issuing this AD to 
require actions to correct the unsafe condition on these products.

DATES: This AD becomes effective December 17, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 17, 
2008.

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

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

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on August 7, 2008 (73 
FR 45891). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Two operators of A300 aircraft fitted with General Electric (GE) 
CF6-50 engine series have reported cracks on the lower side of Rib 5 
in the pylon box.
    The concerned area is similar on A310 aircraft fitted with GE 
CF6-80A or CF6-80C series engines.
    Investigations disclosed that these cracks are due to the 
stresses resulting from the pressure applied by the thrust reverser 
cowl bumpers.
    As a result of the A310 Extended Service Goal (ESG) study, an 
inspection programme of this area is required by this Airworthiness 
Directive (AD).
    A similar inspection programme is being contemplated for A300 
and A300-600 series aircraft.

Cracking of the engine pylons could result in reduced structural 
integrity of the engine support structure. Corrective actions include 
modifying the Rib 5 in the pylon box. 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.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

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.

[[Page 66746]]

Costs of Compliance

    We estimate that this AD will affect about 33 products of U.S. 
registry. We also estimate that it will take about 8 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 $21,120, or $640 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 https://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM, 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:

2008-22-13 Airbus: Amendment 39-15709. Docket No. FAA-2008-0849; 
Directorate Identifier 2008-NM-080-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
17, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A310-203, -204, and -304 
airplanes, all serial numbers, certificated in any category; 
excluding airplanes that have received Airbus Modification 11110 
during production or that have been modified in service in 
accordance with Airbus Service Bulletin A310-54-2032 (Airbus 
Modification 11109).

Subject

    (d) Air Transport Association (ATA) of America Code 54: 
Nacelles/Pylons.

Reason

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

    Two operators of A300 aircraft fitted with General Electric (GE) 
CF6-50 engine series have reported cracks on the lower side of Rib 5 
in the pylon box.
    The concerned area is similar on A310 aircraft fitted with GE 
CF6-80A or CF6-80C series engines.
    Investigations disclosed that these cracks are due to the 
stresses resulting from the pressure applied by the thrust reverser 
cowl bumpers.
    As a result of the A310 Extended Service Goal (ESG) study, an 
inspection programme of this area is required by this Airworthiness 
Directive (AD).
    A similar inspection programme is being contemplated for A300 
and A300-600 series aircraft.

Cracking of the engine pylons could result in reduced structural 
integrity of the engine support structure. Corrective actions 
include modifying the Rib 5 in the pylon box.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Perform a high frequency eddy current (HFEC) inspection and 
a detailed visual inspection on the lower side of Rib 5 of the left-
hand and right-hand pylons, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A310-54-2036, 
Revision 02, dated September 28, 2007. Do the inspections at the 
times specified in paragraph (f)(1)(i) or (f)(1)(ii) of this AD, as 
applicable.
    (i) For Model A310-203 and -204 airplanes: Inspect at the later 
of the times specified in paragraphs (f)(1)(i)(A) and (f)(1)(i)(B) 
of this AD.
    (A) Prior to the accumulation of 40,000 total flight cycles or 
60,000 total flight hours, whichever occurs first.
    (B) Within 250 flight hours after the effective date of this AD.
    (ii) For Model A310-304 airplanes: Inspect at the later of the 
times specified in paragraphs (f)(1)(ii)(A) and (f)(1)(ii)(B) of 
this AD.
    (A) Prior to the accumulation of 35,000 total flight cycles or 
60,000 total flight hours, whichever occurs first.
    (B) Within 250 flight hours after the effective date of this AD.
    (2) If no crack is found during any inspection required by 
paragraph (f)(1) of this AD: Repeat the inspections thereafter at 
intervals not to exceed 15,000 flight hours.
    (3) If any crack is found during any inspection required by 
paragraph (f)(1) of this AD: Before further flight, modify Rib 5 in 
the pylon box in accordance with the Accomplishment Instructions of 
Airbus Service Bulletins A310-54-2032, Revision 01, dated October 8, 
2007. Accomplishment of this modification ends the repetitive 
inspections required by this AD.
    (4) Accomplishment of the HFEC and detailed visual inspections 
before the effective date of this AD in accordance with Airbus 
Service Bulletin A310-54-2036, Revision 01, dated September 14, 
1999, meets the corresponding requirements of paragraph (f) of this 
AD.
    (5) Accomplishment of the modification before the effective date 
of this AD in accordance with Airbus Service Bulletin A310-54-2032, 
dated May 29, 1996, meets the corresponding requirements of 
paragraph (f) of this AD.
    (6) Submit the initial inspection results specified in Appendix 
01 of Airbus Mandatory Service Bulletin A310-54-2036, Revision 02, 
dated September 28, 2007, at the time specified in paragraph 
(f)(6)(i) or (f)(6)(ii) of this AD.
    (i) If the inspections were done after the effective date of 
this AD: Within 30 days after accomplishing the inspections required 
by paragraph (f)(1) of this AD.

[[Page 66747]]

    (ii) If the inspections were done prior to the effective date of 
this AD: Within 30 days after the effective date of this AD.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows: Although the MCAI allows further flight after cracks are 
found during compliance with the required action, this AD requires 
that you repair the crack(s) before further flight.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, 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.
    (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 (EASA) 
Airworthiness Directive 2008-0066, dated March 31, 2008; Airbus 
Service Bulletin A310-54-2032, Revision 01, dated October 8, 2007; 
and Airbus Mandatory Service Bulletin A310-54-2036, Revision 02, 
dated September 28, 2007; for related information.

Material Incorporated by Reference

    (i) You must use Airbus Service Bulletin A310-54-2032, Revision 
01, dated October 8, 2007; and Airbus Mandatory Service Bulletin 
A310-54-2036, including Appendix 01, Revision 02, dated September 
28, 2007; as applicable; 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; 
telephone +33 5 61 93 33 33; Internet https://www.airbus.com.
    (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: https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on October 9, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-25767 Filed 11-10-08; 8:45 am]
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