[Federal Register: September 19, 2007 (Volume 72, Number 181)]
[Proposed Rules]
[Page 53489-53491]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr19se07-21]
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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]
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: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
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SUMMARY: The FAA is revising an earlier NPRM for an airworthiness
directive (AD) that applies to all Airbus Model A300 airplanes; and all
Airbus Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4-622, A300
B4-605R, A300 B4-622R, A300 F4-605R, A300 F4-622R, and A300 C4-605R
Variant F airplanes. The original NPRM would have required 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 original NPRM would
also have required inspecting for discrepancies, including but not
limited to cracking, of the sliding rod; and performing corrective
actions if necessary. The original NPRM resulted 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. This
action revises the original NPRM by proposing to require the return of
affected sliding rods to the manufacturer. We are proposing this
supplemental NPRM to prevent failure of the sliding rod of the MLG
retraction actuator, which could result in reduced structural integrity
of the MLG.
DATES: We must receive comments on this supplemental NPRM by October
15, 2007.
ADDRESSES: Use one of the following addresses to submit comments on
this supplemental NPRM.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.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.
Fax: (202) 493-2251.
Hand Delivery: Room W12-140 on the ground floor of the
West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this proposed AD.
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:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this supplemental NPRM. Send your comments to an
address listed in the ADDRESSES section. Include the docket number
``FAA-2007-27257; Directorate Identifier 2006-NM-131-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of this
supplemental NPRM. We will consider all comments received by the
closing date and may amend this supplemental NPRM in light of those
comments.
We will post all comments submitted, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this supplemental NPRM. Using the search function
of that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit http://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at http://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
Docket Operations office (telephone (800) 647-5527) is located on the
ground floor of the West Building at the DOT street address stated in
the ADDRESSES section. Comments will be available in the AD docket
shortly after the Docket Management System receives them.
Discussion
We proposed to amend 14 CFR part 39 with a notice of proposed
rulemaking (NPRM) for an airworthiness directive (AD) (the ``original
NPRM''). The original NPRM applies to all Airbus Model A300 airplanes;
and all Airbus Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4-
622, A300 B4-605R, A300 B4-622R, A300 F4-605R, A300 F4-622R, and A300
C4-605R Variant F airplanes. The original NPRM was published in the
Federal Register on February 14, 2007 (72 FR 6977). The original 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 original NPRM also proposed to require inspecting for
discrepancies, including but not limited to cracking, of the sliding
rod; and performing corrective actions if necessary.
Comments
We have considered the following comments on the original NPRM.
Request To Require That Retraction Actuator Sliding Rods Be Returned
Airbus, the airplane manufacturer, requests that we require that
retraction actuator sliding rods be returned to the part manufacturer
when the life limit threshold of 32,000 flight cycles is reached.
Airbus states that because the reported failure of the sliding rod of
the MLG retraction actuator was before the life limit of 32,000 flight
cycles, the part manufacturer has been requested to identify the root
cause. Airbus states that for this purpose, the part manufacturer must
be provided with any removed retraction actuator sliding rod.
We agree with the commenter for the reasons stated by the
commenter. We have added paragraph (i) to this supplemental NPRM to
require returning the sliding rods to the part manufacturer when the
life limit is reached for the first replacement cycle only. We have
also reidentified subsequent paragraphs.
Request To Allow Records Review
UPS requests that we allow operators to do a records review instead
of the inspection specified in paragraph (g) of the original NPRM. UPS
states that if the
[[Page 53490]]
records review can conclusively determine whether or not the part is
installed, it will be an equivalent level of safety to the proposed
inspection.
We agree with the comment for the reasons stated by the commenter.
We have revised paragraph (g) of this supplemental NPRM to allow
operators to do a records review instead of the inspection.
Request To Revise Compliance Time
An anonymous commenter requests that we revise the compliance time
specified in paragraph (g) of the original NPRM to match the compliance
time specified in the corresponding European Aviation Safety Agency
(EASA) airworthiness directive. The commenter states that the EASA
airworthiness directive 2006-0075 R2, dated January 4, 2007, specifies
doing the inspection at the accumulation of 27,000 flight cycles within
1,000 flight cycles or one year, whichever occurs first. The commenter
points out that the original NPRM would require the inspection be done
before the accumulation of 27,000 total flight cycles. The commenter
notes that the original NPRM would result in a threshold of 26,999
flight cycles whereas the EASA airworthiness directive specifies that
the inspection be done between 27,000 flight cycles and 28,000 flight
cycles.
We agree with the commenter to revise the compliance time. We
intended to match the compliance times specified in EASA airworthiness
directive. We have revised paragraphs (g) and (h) of this supplemental
NPRM to match the intent of the EASA airworthiness directive. We have
also added new paragraph (k) to this supplemental NPRM to ensure that
any replaced parts are inspected at the compliance time specified in
paragraph (h) of this supplemental NPRM.
Explanation of Changes to NPRM
We have revised the applicability of this supplemental NPRM to
identify model designations as published in the most recent type
certificate data sheet for the affected models.
We have also revised this action to clarify the appropriate
procedure for notifying the principal inspector before using any
approved AMOC on any airplane to which the AMOC applies.
FAA's Determination and Proposed Requirements of the Supplemental NPRM
Certain changes discussed above expand the scope of the original
NPRM; therefore, we have determined that it is necessary to reopen the
comment period to provide additional opportunity for public comment on
this supplemental NPRM.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this supplemental NPRM, at an average labor rate of $80
per work hour, per inspection cycle.
Estimated Costs
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Number of U.S.-
Action Work hours Parts Cost per registered Fleet cost
airplane airplanes
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Inspection to determine part 1 None............. $80 168 $13,440
number.
Inspections for discrepancies 11 None............. 880 168 147,840
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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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this supplemental NPRM 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2007-27257; Directorate Identifier 2006-NM-
131-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by October
15, 2007.
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
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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 flight
cycles on the MLG retraction actuator as of the effective date of
this AD: After accumulating 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 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 flight
cycles on the MLG retraction actuator as of the effective date of
this AD: After accumulating 27,000 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 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.
Issued in Renton, Washington, on September 10, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-18448 Filed 9-18-07; 8:45 am]
BILLING CODE 4910-13-P