[Federal Register Volume 72, Number 236 (Monday, December 10, 2007)]
[Rules and Regulations]
[Pages 69601-69604]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-23673]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27257; Directorate Identifier 2006-NM-131-AD; 
Amendment 39-15297; AD 2007-25-15]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 Series Airplanes and 
Model A300-600 Series Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus Model A300 series airplanes; and all Airbus Model A300-600 
series airplanes. This AD requires inspecting to determine the part 
number of the sliding rods of the main landing gear (MLG) retraction 
actuators. For MLG retraction actuators equipped with

[[Page 69602]]

sliding rods having certain part numbers, the AD also requires 
inspecting for discrepancies, including but not limited to cracking, of 
the sliding rod; and performing corrective actions if necessary. This 
AD also requires returning affected sliding rods to the manufacturer. 
This AD results from a report of a failure of a sliding rod of the MLG 
retraction actuator before the actuator reached the life limit 
established by the manufacturer. We are issuing this AD to prevent 
failure of the sliding rod of the MLG retraction actuator, which could 
result in reduced structural integrity of the MLG.

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

ADDRESSES: For service information identified in this AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
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 received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Thomas 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

    The FAA issued a supplemental notice of proposed rulemaking (NPRM) 
to amend 14 CFR part 39 to include an AD that would apply to all Airbus 
Model A300-600 series airplanes. That supplemental NPRM was published 
in the Federal Register on September 19, 2007 (72 FR 53489). That 
supplemental NPRM proposed to require inspecting to determine the part 
number of the sliding rods of the main landing gear (MLG) retraction 
actuators. For MLG retraction actuators equipped with sliding rods 
having certain part numbers, the supplemental NPRM also proposed to 
require inspecting for discrepancies, including but not limited to 
cracking, of the sliding rod; and performing corrective actions if 
necessary. The supplemental NPRM also proposed to require returning 
affected sliding rods to the manufacturer.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been received on the 
supplemental NPRM or on the determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed 
in the supplemental NPRM.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD, at an average labor rate of $80 per work hour, 
per inspection cycle.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Number of U.S.-
                  Action                    Work          Parts           Cost per     registered     Fleet cost
                                            hours                         airplane      airplanes
----------------------------------------------------------------------------------------------------------------
Inspection to determine part number......       1  None...............          $80             168      $13,440
Inspections for discrepancies............      11  None...............          880             168      147,840
----------------------------------------------------------------------------------------------------------------

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 have 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):


[[Page 69603]]


2007-25-15 Airbus: Amendment 39-15297. Docket No. FAA-2007-27257; 
Directorate Identifier 2006-NM-131-AD.

Effective Date

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

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A300 series airplanes; 
and all Airbus Model A300-600 series airplanes; certificated in any 
category.

Unsafe Condition

    (d) This AD results from a report of a failure of a sliding rod 
of the main landing gear (MLG) retraction actuator before the 
actuator reached the life limit established by the manufacturer. We 
are issuing this AD to prevent failure of the sliding rod of the MLG 
retraction actuator, which could result in reduced structural 
integrity of the MLG.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Service Bulletin Reference

    (f) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of the service bulletins identified in 
paragraphs (f)(1) and (f)(2) of this AD, as applicable.
    (1) For Model A300 series airplanes: Airbus Service Bulletin 
A300-32-0450, Revision 01, excluding Appendix 01, dated May 10, 
2006.
    (2) For Model A300-600 series airplanes: Airbus Service Bulletin 
A300-32-6097, Revision 01, excluding Appendix 01, dated May 10, 
2006.

    Note 1: The Airbus service bulletins refer to Messier-Dowty 
Special Inspection Service Bulletin 470-32-806, dated October 27, 
2005, as an additional source of service information for performing 
detailed and high-frequency eddy current (HFEC) inspections to 
detect discrepancies of the sliding rod.

Inspection To Determine Part Number (P/N) of Sliding Rod

    (g) At the applicable time specified in paragraph (g)(1) or 
(g)(2) of this AD, do a one-time inspection to determine the part 
number of the sliding rod of the MLG retraction actuator, in 
accordance with the applicable service bulletin. If no sliding rod 
having P/N C69029-2 or C69029-3 is installed, no further action is 
required by this paragraph. A review of airplane maintenance records 
is acceptable in lieu of this inspection if the part number of the 
sliding rod of the MLG retraction actuator can be conclusively 
determined from that review.
    (1) For airplanes that have accumulated less than 27,000 total 
flight cycles on the MLG retraction actuator as of the effective 
date of this AD: After accumulating total 27,000 flight cycles on 
the MLG retraction actuator, do the inspection within the next 1,000 
flight cycles or 12 months, whichever occurs first.
    (2) For airplanes that have accumulated 27,000 or more total 
flight cycles on the MLG retraction actuator as of the effective 
date of this AD: Do the inspection within 1,000 flight cycles or 12 
months, whichever occurs first, after the effective date of this AD.

Inspection for Discrepancies of Sliding Rod and Corrective Actions

    (h) For MLG retraction actuators equipped with sliding rods 
having P/N C69029-2 or C69029-3: At the applicable time specified in 
paragraph (h)(1) or (h)(2) of this AD, perform detailed and HFEC 
inspections of the sliding rod of the MLG retraction actuators on 
the left-hand and right-hand MLGs, in accordance with the applicable 
service bulletin. Then, before further flight, perform all 
applicable corrective actions, in accordance with the applicable 
service bulletin.
    (1) For airplanes that have accumulated less than 27,000 total 
flight cycles on the MLG retraction actuator as of the effective 
date of this AD: After accumulating 27,000 total flight cycles on 
the MLG retraction actuator, do the inspections within the next 
1,000 flight cycles or 12 months, whichever occurs first.
    (2) For airplanes that have accumulated 27,000 or more total 
flight cycles on the MLG retraction actuator as of the effective 
date of this AD: Do the inspections within 1,000 flight cycles or 12 
months, whichever occurs first, after the effective date of this AD.

    Note 2: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''


    Note 3: Operators should note that the MLG retraction actuator 
rod must be replaced with a new or serviceable actuator rod before 
the 32,000-flight-cycle life limit specified in the applicable 
airworthiness limitations document, regardless of the inspection 
findings.

Return of MLG Retraction Actuator Sliding Rod

    (i) For airplanes having any retraction actuator sliding rods 
specified in paragraphs (i)(1) and (i)(2) of this AD: After the 
effective date of this AD, for the first replacement of the 
retraction actuator sliding rod, return the retraction actuator 
sliding rod to Messier-Dowty, SA Product Support Engineering, BP10--
78142 Velizy Cedex, France, within 30 days after the retraction 
actuator sliding rod is removed from the airplane.
    (1) Any retraction actuator sliding rod that is found to have 
cracking during the actions specified in paragraph (h) of this AD.
    (2) Any retraction actuator sliding rod, P/N C69029-2 or C69029-
3, removed that has accumulated between 27,000 total flight cycles 
and 32,000 total flight cycles.

Parts Installation for MLG Retraction Actuator Rod

    (j) As of the effective date of this AD, no person may install, 
on any airplane, an MLG retraction actuator that is equipped with a 
sliding rod having P/N C69029-2 or C69029-3, and on which the 
retraction actuator rod has accumulated 27,000 total flight cycles 
or more, unless paragraph (h) of this AD is accomplished.
    (k) As of the effective date of this AD, any MLG retraction 
actuator that is equipped with a sliding rod having P/N C69029-2 or 
C69029-3, and on which the retraction actuator rod has accumulated 
less than 27,000 total flight cycles, may be installed, on any 
airplane, provided that the inspections specified in paragraph (h) 
of this AD are accomplished at the time specified in paragraph 
(h)(1) of this AD.

Actions Accomplished According to a Previous Issue of the Service 
Bulletins

    (l) Inspections and corrective actions done before the effective 
date of this AD in accordance with the following service bulletins 
are acceptable for compliance with the corresponding requirements of 
this AD:
    (1) For Model A300 series airplanes: Airbus Service Bulletin 
A300-32-0450, excluding Appendix 01, dated December 1, 2005.
    (2) For Model A300-600 series airplanes: Airbus Service Bulletin 
A300-32-6097, excluding Appendix 01, dated December 1, 2005.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, 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.

Related Information

    (n) European Aviation Safety Agency airworthiness directive 
2006-0075R2, dated January 4, 2007, also addresses the subject of 
this AD.

Material Incorporated by Reference

    (o) You must use Airbus Service Bulletin A300-32-0450, Revision 
01, excluding Appendix 01, dated May 10, 2006; or Airbus Service 
Bulletin A300-32-6097, Revision 01, excluding Appendix 01, dated May 
10, 2006; as applicable, to perform the actions that are required by 
this AD, unless the AD specifies otherwise. The Director of the 
Federal Register approved the incorporation by reference of these 
documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for a copy of this service information. You may review 
copies at the FAA, Transport Airplane

[[Page 69604]]

Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; 
or at the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, call 202-
741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on November 29, 2007.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
[FR Doc. E7-23673 Filed 12-7-07; 8:45 am]
BILLING CODE 4910-13-P