[Federal Register: December 10, 2007 (Volume 72, Number 236)]
[Rules and Regulations]
[Page 69601-69604]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr10de07-15]
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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