Airworthiness Directives; Airbus Model A300-600R Series Airplanes; and Model A310-300 Series Airplanes, 53933-53935 [E7-18435]

Download as PDF Federal Register / Vol. 72, No. 183 / Friday, September 21, 2007 / Rules and Regulations Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Seattle 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, 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. (4) AMOCs approved previously in accordance with AD 2007–18–51 are approved as AMOCs for the corresponding provisions of this AD. Material Incorporated by Reference (i) None. Issued in Renton, Washington, on September 10, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–18436 Filed 9–20–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration [Docket No. FAA–2007–28374; Directorate Identifier 2007–NM–067–AD; Amendment 39–15199; AD 2007–19–08] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300–600R Series Airplanes; and Model A310–300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ebenthall on PROD1PC69 with RULES 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: VerDate Aug<31>2005 15:32 Sep 20, 2007 Jkt 211001 While they were gaining access to the THS (trimmable horizontal stabilizer) fuel tank for maintenance check, several operators have found one or several of the 8 THS hoist point fitting bases cracked or broken-off. The breakage resulted in metallic debris being released within the Trim Tank. The origin of the damage is most probably due to interference with the THS hoisting lugs that are stowed in the hoist point fittings in the reverse position, being screwed too deep inside the THS hoist fittings. Damaged hoist point fittings could cause the release of metallic debris within the THS fuel system. * * * Compliance with the requirements of this AD will also eliminate potential contributing factor[s] to ignition risks. point fittings damage as well as any fuel leak. Compliance with the requirements of this AD will also eliminate potential contributing factor[s] to ignition risks. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective October 26, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 26, 2007. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.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. 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. Tom Stafford, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Conclusion FOR FURTHER INFORMATION CONTACT: Discussion 14 CFR Part 39 53933 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 18, 2007 (72 FR 33409). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: While they were gaining access to the THS (trimmable horizontal stabilizer) fuel tank for maintenance check, several operators have found one or several of the 8 THS hoist point fitting bases cracked or broken-off. The breakage resulted in metallic debris being released within the Trim Tank. The origin of the damage is most probably due to interference with the THS hoisting lugs that are stowed in the hoist point fittings in the reverse position, being screwed too deep inside the THS hoist fittings. Damaged hoist point fittings could cause the release of metallic debris within the THS fuel system. This Airworthiness Directive (AD) requires the repair of any damaged THS hoist point fittings to prevent any risk of further hoist PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 The corrective action is an inspection of the internal base of the THS hoist point fittings for signs of score, cracks, perforation or other damage; and an inspection of the hoist point fittings base inside the fuel tank for structural damage, as applicable, and applicable corrective actions (repair damaged fittings and install new plastic plugs). You may obtain further information by examining the MCAI in the AD docket. Clarification of Compliance We have revised paragraphs (f)(3), (f)(4), (f)(5), and (f)(6) of this final rule to clarify that those actions are required before further flight following the inspection required by paragraph (f)(2) of the AD. Additionally, we have removed the references to doing corrective actions ‘‘before return to revenue service’’ throughout the AD. We reviewed the available data and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance Based on the service information, we estimate that this AD affects about 137 products of U.S. registry. We also estimate that it takes about 10 workhours per product to comply with the E:\FR\FM\21SER1.SGM 21SER1 53934 Federal Register / Vol. 72, No. 183 / Friday, September 21, 2007 / Rules and Regulations basic requirements of this AD. The average labor rate is $80 per work-hour. Required parts cost about $332 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these costs. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of this AD on U.S. operators to be $155,084, or $1,132 per product. ebenthall on PROD1PC69 with RULES 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://dms.dot.gov; or in VerDate Aug<31>2005 15:32 Sep 20, 2007 Jkt 211001 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 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 2007–19–08 Airbus: Amendment 39–15199. Docket No. FAA–2007–28374; Directorate Identifier 2007–NM–067–AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 26, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A310– 300 and A300–600R series airplanes; certificated in any category; all serial numbers fitted with a THS (trimmable horizontal stabilizer) containing fuel on which, during production Airbus Modifications 04801 and 04802 have been embodied, and Airbus Modification 06549 has not been embodied; except aircraft on which Airbus Modification 13191 has been embodied in production, or Airbus Service Bulletin A310–55–2042 or A300–55–6041 has been incorporated in service. Subject (d) Air Transport Association (ATA) of America Code 55: Stabilizers. Reason (e) The mandatory continuing airworthiness information (MCAI) states: While they were gaining access to the THS (trimmable horizontal stabilizer) fuel tank for maintenance check, several operators have found one or several of the 8 THS hoist point fitting bases cracked or broken-off. The breakage resulted in metallic debris being released within the Trim Tank. The origin of PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 the damage is most probably due to interference with the THS hoisting lugs that are stowed in the hoist point fittings in the reverse position, being screwed too deep inside the THS hoist fittings. Damaged hoist point fittings could cause the release of metallic debris within the THS fuel system. This Airworthiness Directive (AD) requires the repair of any damaged THS hoist point fittings to prevent any risk of further hoist point fittings damage as well as any fuel leak. Compliance with the requirements of this AD will also eliminate potential contributing factor[s] to ignition risks. The corrective action is an inspection of the internal base of the THS hoist point fittings for signs of score, cracks, perforation or other damage; and an inspection of the hoist point fittings base inside the fuel tank for structural damage, as applicable, and applicable corrective actions (repair damaged fittings and install new plastic plugs). Actions and Compliance (f) Unless already done, within 60 months after the effective date of this AD, do the actions specified in paragraphs (f)(1) through (f)(6) of this AD in accordance with the instructions given in Airbus Service Bulletin A300–55–6041 or A310–55–2042, both dated September 13, 2006, as applicable. (1) Remove the 8 THS metallic hoisting lugs. (2) Do a detailed visual inspection of the internal base of the 8 THS hoist point fittings in order to detect visible signs of score, cracks, perforation or other damage. (3) In case of no finding, before further flight install the new plastic plugs. (4) In case of any finding, before further flight, entry into the fuel trim tank is required to do a detailed visual inspection for structural damage of the hoist point fittings base inside the fuel tank. (5) If structural damage is not confirmed, before further flight blend-out/protect the scoring area of the fitting internal base and install the new plastic plugs. (6) If structural damage is confirmed, before further flight repair the damaged fittings and install the new plastic plugs. 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: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; 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 E:\FR\FM\21SER1.SGM 21SER1 53935 Federal Register / Vol. 72, No. 183 / Friday, September 21, 2007 / Rules and Regulations 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 Airworthiness Directive 2007– 0024, dated January 25, 2007; and Airbus Service Bulletins A300–55–6041 and A310– 55–2042, both dated September 13, 2006; for related information. Material Incorporated by Reference (i) You must use the service information specified in Table 1 of this AD 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. TABLE 1.—MATERIAL INCORPORATED BY REFERENCE Airbus service bulletin Revision A300–55–6041 ..................................................................................................................................... A310–55–2042 ..................................................................................................................................... Original ............. Original ............. Issued in Renton, Washington, on September 10, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–18435 Filed 9–20–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28365; Directorate Identifier 2007–NE–26–AD; Amendment 39–15185; AD 2007–18–05] RIN 2120–AA64 Airworthiness Directives; Societe de Motorisations Aeronautiques (SMA) SR305–230 and SR305–230–1 Reciprocating Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. ebenthall on PROD1PC69 with RULES AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from Mandatory Continuing Airworthiness Information (MCAI) provided by the aviation authority of France to identify and correct an unsafe condition on SMA SR305–230 and SR305–230–1 reciprocating engines. The MCAI states the following: Several occurrences of cracks on the exhaust collector assembly have been reported in service. Failure of the engine primary exhaust can lead to a loss of engine manifold pressure and may result in a loss VerDate Aug<31>2005 15:32 Sep 20, 2007 Jkt 211001 Date September 13, 2006. September 13, 2006. of engine power. In some recent occurrences, cracking has appeared near the weld of the Turbine Inlet Temperature (TIT) probe support. This eventually led to an open hole in the exhaust collector assembly. The resulting loss of engine power was not compatible with the continuation of the flight and an immediate landing was necessary. received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. We are issuing this AD to prevent failure of the engine primary exhaust, which could result in loss of engine power and inability to maintain safe flight. DATES: This AD becomes effective October 9, 2007. We must receive comments on this AD by October 22, 2007. ADDRESSES: You may send comments by any of the following methods: • DOT Docket Web Site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. • Federal eRulemaking Portal: https:// www.regulations.gov. Follow the instructions for submitting comments. FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: christopher.spinney@faa.gov; telephone (781) 238–7175; fax (781) 238–7199. Examining the AD Docket You may examine the AD docket on the Internet at https://dms.dot.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 regulatory evaluation, any comments PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 SUPPLEMENTARY INFORMATION: 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 2007–0127, dated May 7, 2007, to correct an unsafe condition for the specified products. The EASA AD states: Several occurrences of cracks on the exhaust collector assembly have been reported in service. Failure of the engine primary exhaust can lead to a loss of engine manifold pressure and may result in a loss of engine power. In some recent occurrences, cracking has appeared near the weld of the Turbine Inlet Temperature (TIT) probe support. This eventually led to an open hole in the exhaust collector assembly. The resulting loss of engine power was not compatible with the continuation of the flight and an immediate landing was necessary. You may obtain further information by examining the EASA AD in the AD docket. E:\FR\FM\21SER1.SGM 21SER1

Agencies

[Federal Register Volume 72, Number 183 (Friday, September 21, 2007)]
[Rules and Regulations]
[Pages 53933-53935]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-18435]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28374; Directorate Identifier 2007-NM-067-AD; 
Amendment 39-15199; AD 2007-19-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300-600R Series 
Airplanes; and Model A310-300 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:

    While they were gaining access to the THS (trimmable horizontal 
stabilizer) fuel tank for maintenance check, several operators have 
found one or several of the 8 THS hoist point fitting bases cracked 
or broken-off. The breakage resulted in metallic debris being 
released within the Trim Tank. The origin of the damage is most 
probably due to interference with the THS hoisting lugs that are 
stowed in the hoist point fittings in the reverse position, being 
screwed too deep inside the THS hoist fittings. Damaged hoist point 
fittings could cause the release of metallic debris within the THS 
fuel system.
    * * * Compliance with the requirements of this AD will also 
eliminate potential contributing factor[s] to ignition risks.

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

DATES: This AD becomes effective October 26, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 26, 
2007.

ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.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: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; 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 June 18, 2007 (72 FR 
33409). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    While they were gaining access to the THS (trimmable horizontal 
stabilizer) fuel tank for maintenance check, several operators have 
found one or several of the 8 THS hoist point fitting bases cracked 
or broken-off. The breakage resulted in metallic debris being 
released within the Trim Tank. The origin of the damage is most 
probably due to interference with the THS hoisting lugs that are 
stowed in the hoist point fittings in the reverse position, being 
screwed too deep inside the THS hoist fittings. Damaged hoist point 
fittings could cause the release of metallic debris within the THS 
fuel system.
    This Airworthiness Directive (AD) requires the repair of any 
damaged THS hoist point fittings to prevent any risk of further 
hoist point fittings damage as well as any fuel leak. Compliance 
with the requirements of this AD will also eliminate potential 
contributing factor[s] to ignition risks.

The corrective action is an inspection of the internal base of the THS 
hoist point fittings for signs of score, cracks, perforation or other 
damage; and an inspection of the hoist point fittings base inside the 
fuel tank for structural damage, as applicable, and applicable 
corrective actions (repair damaged fittings and install new plastic 
plugs). 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.

Clarification of Compliance

    We have revised paragraphs (f)(3), (f)(4), (f)(5), and (f)(6) of 
this final rule to clarify that those actions are required before 
further flight following the inspection required by paragraph (f)(2) of 
the AD. Additionally, we have removed the references to doing 
corrective actions ``before return to revenue service'' throughout the 
AD.

Conclusion

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

Differences Between This AD and the MCAI or Service Information

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

Costs of Compliance

    Based on the service information, we estimate that this AD affects 
about 137 products of U.S. registry. We also estimate that it takes 
about 10 work-hours per product to comply with the

[[Page 53934]]

basic requirements of this AD. The average labor rate is $80 per work-
hour. Required parts cost about $332 per product. Where the service 
information lists required parts costs that are covered under warranty, 
we have assumed that there will be no charge for these costs. As we do 
not control warranty coverage for affected parties, some parties may 
incur costs higher than estimated here. Based on these figures, we 
estimate the cost of this AD on U.S. operators to be $155,084, or 
$1,132 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://
dms.dot.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:

2007-19-08 Airbus: Amendment 39-15199. Docket No. FAA-2007-28374; 
Directorate Identifier 2007-NM-067-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
26, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A310-300 and A300-600R 
series airplanes; certificated in any category; all serial numbers 
fitted with a THS (trimmable horizontal stabilizer) containing fuel 
on which, during production Airbus Modifications 04801 and 04802 
have been embodied, and Airbus Modification 06549 has not been 
embodied; except aircraft on which Airbus Modification 13191 has 
been embodied in production, or Airbus Service Bulletin A310-55-2042 
or A300-55-6041 has been incorporated in service.

Subject

    (d) Air Transport Association (ATA) of America Code 55: 
Stabilizers.

Reason

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

    While they were gaining access to the THS (trimmable horizontal 
stabilizer) fuel tank for maintenance check, several operators have 
found one or several of the 8 THS hoist point fitting bases cracked 
or broken-off. The breakage resulted in metallic debris being 
released within the Trim Tank. The origin of the damage is most 
probably due to interference with the THS hoisting lugs that are 
stowed in the hoist point fittings in the reverse position, being 
screwed too deep inside the THS hoist fittings. Damaged hoist point 
fittings could cause the release of metallic debris within the THS 
fuel system.
    This Airworthiness Directive (AD) requires the repair of any 
damaged THS hoist point fittings to prevent any risk of further 
hoist point fittings damage as well as any fuel leak. Compliance 
with the requirements of this AD will also eliminate potential 
contributing factor[s] to ignition risks.

    The corrective action is an inspection of the internal base of 
the THS hoist point fittings for signs of score, cracks, perforation 
or other damage; and an inspection of the hoist point fittings base 
inside the fuel tank for structural damage, as applicable, and 
applicable corrective actions (repair damaged fittings and install 
new plastic plugs).

Actions and Compliance

    (f) Unless already done, within 60 months after the effective 
date of this AD, do the actions specified in paragraphs (f)(1) 
through (f)(6) of this AD in accordance with the instructions given 
in Airbus Service Bulletin A300-55-6041 or A310-55-2042, both dated 
September 13, 2006, as applicable.
    (1) Remove the 8 THS metallic hoisting lugs.
    (2) Do a detailed visual inspection of the internal base of the 
8 THS hoist point fittings in order to detect visible signs of 
score, cracks, perforation or other damage.
    (3) In case of no finding, before further flight install the new 
plastic plugs.
    (4) In case of any finding, before further flight, entry into 
the fuel trim tank is required to do a detailed visual inspection 
for structural damage of the hoist point fittings base inside the 
fuel tank.
    (5) If structural damage is not confirmed, before further flight 
blend-out/protect the scoring area of the fitting internal base and 
install the new plastic plugs.
    (6) If structural damage is confirmed, before further flight 
repair the damaged fittings and install the new plastic plugs.

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: Tom 
Stafford, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1622; 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

[[Page 53935]]

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 Airworthiness 
Directive 2007-0024, dated January 25, 2007; and Airbus Service 
Bulletins A300-55-6041 and A310-55-2042, both dated September 13, 
2006; for related information.

Material Incorporated by Reference

    (i) You must use the service information specified in Table 1 of 
this AD 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: https://www.archives.gov/federal-register/cfr/ibr-
locations.html.

                                  Table 1.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
        Airbus service bulletin                    Revision                               Date
----------------------------------------------------------------------------------------------------------------
A300-55-6041..........................  Original......................  September 13, 2006.
A310-55-2042..........................  Original......................  September 13, 2006.
----------------------------------------------------------------------------------------------------------------


    Issued in Renton, Washington, on September 10, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-18435 Filed 9-20-07; 8:45 am]
BILLING CODE 4910-13-P
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