[Federal Register Volume 75, Number 96 (Wednesday, May 19, 2010)]
[Proposed Rules]
[Pages 27956-27959]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-11902]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0478; Directorate Identifier 2008-NM-090-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and 
F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes 
(Collectively Called A300-600 Series Airplanes); and Model A300 and 
A310 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed 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: Two cases of complete nose landing gear (NLG) shock 
absorber bolts failure were reported to the manufacturer. In both 
cases, the crew was unable to retract the gear and was forced to an In 
Flight Turn Back. In one case, the aircraft experienced a low speed 
runway excursion. The root cause of the bolts failure has been 
identified

[[Page 27957]]

being due to a bolt(s) over-torque. The investigation has highlighted 
that the design of the NLG shock absorber was not tolerant to the over-
torque, and an inspection plan has been developed to track any NLG 
shock absorber-to-main barrel attachment bolts status. The proposed AD 
would require actions that are intended to address the unsafe condition 
described in the MCAI.

DATES: We must receive comments on this proposed AD by July 6, 2010.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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.
    <bullet> Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; e-mail: <a href="/cdn-cgi/l/email-protection#f796949498829983d9969e85809885839fda929684b7969e85958284d994989a"><span class="__cf_email__" data-cfemail="056466666a706b712b646c77726a77716d2860647645646c776770762b666a68">[email protected]</span></a>; Internet http://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington. For information on the availability of 
this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.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 proposed AD, 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.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0478; 
Directorate Identifier 2008-NM-090-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We have lengthened the 30-day comment period for proposed ADs that 
address MCAI originated by aviation authorities of other countries to 
provide adequate time for interested parties to submit comments. The 
comment period for these proposed ADs is now typically 45 days, which 
is consistent with the comment period for domestic transport ADs.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

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 2008-0052R1, dated June 30, 2008 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Two cases of complete nose landing gear (NLG) shock absorber 
bolts failure were reported to the manufacturer. In both cases, the 
crew was unable to retract the gear and was forced to an In Flight 
Turn Back. In one case, the aircraft experienced a low speed runway 
excursion. The root cause of the bolts failure has been identified 
being due to a bolt(s) over-torque. The investigation has 
highlighted that the design of the NLG shock absorber was not 
tolerant to the over-torque, and an inspection plan has been 
developed to track any NLG shock absorber-to-main barrel attachment 
bolts status. The preliminary inspection plan, required by DGAC 
France Airworthiness Directive (AD) F-2004-075 and F-2004-076, has 
allowed limiting the number of findings: High at the initial 
inspection, it has decreased following the repetitive inspections.
    This new AD retains the requirements of those ADs, which are 
superseded, and requires a repetitive torque check of the NLG shock 
absorber-to-main barrel attachment bolts with new thresholds and 
intervals. This new AD also refers to an optional modification as 
terminating action.
* * * * *

The optional modification involves modifying the shock absorber-to-
barrel attachment to increase over-torque tolerances. The actions to 
address the unsafe condition also include inspecting the NLG shock 
absorber-to-main barrel attachment bolts and doing corrective actions. 
The corrective actions include replacing bolts, screws, nuts, washers, 
and cotter pins; contacting Airbus for repair and doing the repair; and 
modifying the shock absorber; as applicable. The inspection of the NLG 
shock absorber-to-main barrel attachment bolts is repeated at intervals 
not to exceed 400 flight hours or 1,000 flight cycles, depending on the 
inspection results and corrective actions performed. You may obtain 
further information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued the following service information:
    <bullet> All Operator Telexes A300-32A0447, A300-32A6093, and A310-
32A2132, all dated April 22, 2004;
    <bullet> Mandatory Service Bulletins A300-32-0447, A300-32-6093, 
and A310-32-2132, all Revision 01, all including Appendix 01, all dated 
June 1, 2007; and
    <bullet> Service Bulletins A300-32-0453, A300-32-6099, and A310-32-
2135, all dated June 1, 2007.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

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.

[[Page 27958]]

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 proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 229 products of U.S. registry. We also estimate that 
it would take about 2 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $38,930, or $170 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 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 this 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 proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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 FAA amends Sec.  39.13 by adding the following new AD:

Airbus: Docket No. FAA-2010-0478; Directorate Identifier 2008-NM-
090-AD.

Comments Due Date

    (a) We must receive comments by July 6, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300 B2-1A, B2-1C, B4-2C, 
B2K-3C, B4-103, B2-203, and B4-203 airplanes; Model A300 B4-601, B4-
603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R 
Variant F airplanes; and Model A310-203, -204, -221, -222, -304, -
322, -324, and -325 airplanes; all certified models, all serial 
numbers, certificated in any category; except airplanes on which 
Airbus Modification 13212 has been done in production or Airbus 
Service Bulletin A300-32-0453, A310-32-2135, or A300-32-6099 has 
been done in service.

Subject

    (d) Air Transport Association (ATA) of America Code 32: Landing 
gear.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Two cases of complete nose landing gear (NLG) shock absorber 
bolts failure were reported to the manufacturer. In both cases, the 
crew was unable to retract the gear and was forced to an In Flight 
Turn Back. In one case, the aircraft experienced a low speed runway 
excursion. The root cause of the bolts failure has been identified 
being due to a bolt(s) over-torque. The investigation has 
highlighted that the design of the NLG shock absorber was not 
tolerant to the over-torque, and an inspection plan has been 
developed to track any NLG shock absorber-to-main barrel attachment 
bolts status. The preliminary inspection plan, required by DGAC 
France Airworthiness Directive (AD) F-2004-075 and F-2004-076, has 
allowed limiting the number of findings: high at the initial 
inspection, it has decreased following the repetitive inspections.
    This new AD retains the requirements of those ADs, which are 
superseded, and requires a repetitive torque check of the NLG shock 
absorber-to-main barrel attachment bolts with new thresholds and 
intervals. This new AD also refers to an optional modification as 
terminating action.

The optional modification involves modifying the shock absorber-to-
barrel attachment to increase over-torque tolerances. The actions to 
address the unsafe condition also include inspecting the NLG shock 
absorber-to-main barrel attachment bolts and corrective actions. The 
corrective actions include replacing bolts, screws, nuts, washers, 
and cotter pins; contacting Airbus for repair and doing the repair; 
and modifying the shock absorber; as applicable.

Compliance

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

Inspection and Corrective Action

    (g) At the applicable time specified in paragraph (g)(1), 
(g)(2), or (g)(3) of this AD: Do a visual inspection to detect 
operational condition (i.e., free of corrosion and not deformed) and 
inspect rotation/torque of the NLG shock absorber-to-main barrel 
attachment bolts and do all applicable corrective actions, in 
accordance with the applicable all operators telex (AOT) identified 
in Table 1 of this AD. Do all applicable corrective actions before 
further flight. Thereafter, repeat the inspection at the applicable 
intervals, depending on inspection results and the corrective 
actions performed, as specified in the applicable AOT identified in 
Table 1 of this AD.
    (1) For airplanes on which the NLG has been overhauled (the 
bolts have been removed) as of the effective date of this AD: Within 
30 days or 1,000 flight cycles on the NLG after the effective date 
of this AD, whichever occurs later.
    (2) For airplanes on which, as of the effective date of this AD, 
the NLG has accumulated less than 1,000 total flight cycles, has not 
been overhauled (the bolts have never been removed), since 
manufacture of the NLG: Before the accumulation of 1,000 total 
flight cycles on the NLG, or within 30 days after the effective date 
of this AD, whichever occurs later.
    (3) For airplanes on which, as of the effective date of this AD, 
the NLG has accumulated 1,000 or more total flight cycles, and has 
not been overhauled since new (the bolts have never been removed): 
Within 30 days after the effective date of this AD.

[[Page 27959]]



                  Table 1--Airbus All Operator Telexes
------------------------------------------------------------------------
      Airbus all operator telex--                    Dated--
------------------------------------------------------------------------
A300-32A0447...........................  April 22, 2004.
A300-32A6093...........................  April 22, 2004.
A310-32A2132...........................  April 22, 2004.
------------------------------------------------------------------------

Torque Load Inspection and Corrective Action

    (h) At the latest of the compliance times specified in 
paragraphs (h)(1), (h)(2), and (h)(3) of this AD, do an inspection 
of the torque load of the nuts of the NLG shock absorber-to-main 
barrel attachment bolts in accordance with the Accomplishment 
Instructions of the applicable service bulletin listed in Table 2 of 
this AD. Depending on the torque load value found during the 
inspection, before further flight: Retighten the bolt(s) or replace 
the discrepant bolt(s), or replace all bolts, in accordance with the 
applicable service bulletin listed in Table 2 of this AD. 
Thereafter, repeat the torque load inspection at intervals not to 
exceed 3,200 flight cycles or 30 months' time-in-service accumulated 
by the NLG, whichever occurs first.
    (1) Within 3,200 flight cycles or 30 months since NLG's first 
flight, whichever occurs first.
    (2) Within 3,200 flight cycles or 30 months accumulated by the 
NLG since installation of new bolts, whichever occurs first.
    (3) Within 3,200 flight cycles or 30 months after the effective 
date of this AD, whichever occurs first.

              Table 2--Service Information for Inspections
------------------------------------------------------------------------
    Airbus Mandatory Service        Revision
           Bulletin--                level--             Dated--
------------------------------------------------------------------------
A300-32-0447, including                      01  June 1, 2007.
 Appendix 01.
A300-32-6093, including                      01  June 1, 2007.
 Appendix 01.
A310-32-2132, including                      01  June 1, 2007.
 Appendix 01.
------------------------------------------------------------------------

    (i) After accomplishment of the initial inspection in accordance 
with paragraph (h) of this AD, as applicable, the repetitive 
inspections of paragraph (g) of this AD are no longer required.

Optional Terminating Action

    (j) For airplanes on which the modification of the shock 
absorber-to-barrel attachment has been done in accordance with the 
applicable service bulletin listed in Table 3 of this AD, the 
requirements of this AD are no longer required, as long as that 
modification remains installed.

      Table 3--Service Information for Optional Terminating Action
------------------------------------------------------------------------
       Airbus Service Bulletin--                     Dated--
------------------------------------------------------------------------
A300-32-0453...........................  June 1, 2007.
A300-32-6099...........................  June 1, 2007.
A310-32-2135...........................  June 1, 2007.
------------------------------------------------------------------------

Reporting Requirement

    (k) For each inspection required in paragraph (h) of this AD 
that results in re-torque or replacement of bolt(s): At the 
applicable time specified in paragraph (k)(1) or (k)(2) of this AD, 
send a report to Airbus, using Appendix 01 of the applicable service 
bulletin listed in Table 2 of this AD.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: No Differences.

Other FAA AD Provisions

    (l) 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: Dan 
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 227-2125; fax (425) 227-1149. Before 
using any approved AMOC on any airplane to which the AMOC applies, 
notify your principal maintenance inspector (PMI) or principal 
avionics inspector (PAI), as appropriate, or lacking a principal 
inspector, your local Flight Standards District Office. The AMOC 
approval letter must specifically reference this AD.
    (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 (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

Related Information

    (m) Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2008-0052R1, dated June 30, 2008; and the 
service information identified in Tables 1, 2, and 3 of this AD; for 
related information.


    Issued in Renton, Washington, on May 3, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-11902 Filed 5-18-10; 8:45 am]
BILLING CODE 4910-13-P


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