Airworthiness Directives; Airbus Model A300 Series Airplanes and Model A300-600 Series Airplanes, 53489-53491 [E7-18448]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 72, Number 181 (Wednesday, September 19, 2007)]
[Proposed Rules]
[Pages 53489-53491]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-18448]



[[Page 53489]]

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

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.

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

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 https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
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 https://
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 https://dms.dot.gov.

Examining the 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 
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
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of U.S.-
            Action               Work hours          Parts           Cost per       registered      Fleet cost
                                                                     airplane        airplanes
----------------------------------------------------------------------------------------------------------------
Inspection to determine part                1  None.............             $80             168         $13,440
 number.
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 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

[[Page 53491]]

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