Document ID: FAA-2009-0292-0002
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Model A300, A310, and A300-600 Series Airplanes
Posted Date: 2009-04-01T04:00Z

[Federal Register: April 1, 2009 (Volume 74, Number 61)]
[Proposed Rules]               
[Page 14751-14759]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01ap09-17]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0292; Directorate Identifier 2008-NM-011-AD]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A300, A310, and A300-600 
Series Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Airbus Model A300 and A310 
series airplanes. The existing AD currently requires replacement of the 
nose landing gear drag strut upper attachment pin. This proposed AD 
would require revising the Airworthiness Limitations section (ALS)

[[Page 14752]]

of the Instructions for Continued Airworthiness (ICA) to require 
additional life limits and/or replacements for certain main landing 
gear and nose landing gear components, and would also expand the 
applicability. This proposed AD results from revisions to the ALS of 
the ICA to include new or more restrictive life limits and/or 
replacements. We are proposing this AD to ensure the continued 
structural integrity of these airplanes.

DATES: We must receive comments on this proposed AD by May 1, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     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.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, 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: account.airworth-eas@airbus.com; 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 or 425-227-1152.

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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket 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: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; 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-2009-0292; 
Directorate Identifier 2008-NM-011-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 because of those comments.
    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

    On July 21, 1987, we issued AD 87-16-06, amendment 39-5692 (52 FR 
28241, July 29, 1987), for certain Airbus Model A300 and A310 series 
airplanes. That AD requires replacement of the nose landing gear drag 
strut upper attachment pin. That AD resulted from reports of pins which 
were found to be improperly manufactured. We issued that AD to prevent 
failure of the pin and collapse of the nose landing gear.

Actions Since Existing AD Was Issued

    Since we issued AD 87-16-06, the manufacturer has revised the 
Airworthiness Limitations Section (ALS) of the Instructions for 
Continued Airworthiness (ICA) to include new or more restrictive life 
limits and replacements for the main landing gear and the nose landing 
gear. These new limits affect the replacement of the upper attachment 
pin for the nose landing gear drag strut that was the subject of AD 87-
16-06.
    In addition, European Aviation Safety Agency (EASA) Airworthiness 
Directive 2007-0293, dated November 29, 2007, which is parallel to this 
proposed AD, includes Model A300-600 series airplanes. Those airplane 
models were not included in AD 87-16-06.

Relevant Service Information

    Airbus has issued the following revisions to the ALS of the ICA. 
These documents provide each mandatory replacement time, structural 
inspection interval, and related structural inspection procedures or 
other procedures (e.g., modifications).
     For Model A300 Series Airplanes: ``Sub-part 1-2: Life 
Limits,'' and ``Sub-part 1-3: Demonstrated fatigue lives'' of Part 1, 
``Safe Life Airworthiness Limitation Items,'' dated September 6, 2007.
     For Model A300-600 Series Airplanes: ``Sub-part 1-2: Life 
Limits,'' and ``Sub-part 1-3: Demonstrated fatigue lives'' of Part 1, 
``Safe Life Airworthiness Limitation Items,'' dated December 21, 2006.
     For Model A310 Series Airplanes: ``Sub-part 1-2: Life 
Limits,'' and ``Sub-part 1-3: Demonstrated fatigue lives'' of Part 1, 
``Safe Life Airworthiness Limitation Items,'' dated December 21, 2006.
    Airbus has also issued Section 05-10-00, Revision 28, dated 
February 27, 1998, of Chapter 5, ``Service Life Limits and Maintenance 
Checks,'' of the A300 Aircraft Maintenance Manual. Section 05-10-00 
includes life limit values for the nose and main landing gears. This 
document is an alternate source for the life limits defined in Part 1, 
``Safe Life Airworthiness Limitation Items,'' dated September 6, 2007, 
of the ALS, for Model A300 series airplanes.
    Airbus has also issued Service Information Letter (SIL) 32-118, 
Revision 02, dated October 24, 2007. This SIL gives instructions for 
calculating the life limit of main or nose landing gear parts where the 
history of accumulated landings is partial or unknown, or where the 
history of application details (airplane type, model, weight variant, 
etc.) is partial or unknown.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. EASA mandated the 
service information and issued Airworthiness Directive 2007-0292, dated 
November 29, 2007, to ensure the continued airworthiness of these 
airplanes in the European Union.

Other Relevant Rulemaking

    On January 11, 1984, we issued AD 84-02-04 (49 FR 2746, January 23, 
1984), for certain Airbus Model A300 B2 and B4 series airplanes. That 
AD requires inspection of main landing gear hinge arms for corrosion 
and cracks, and repair or modifications if needed. That AD also 
requires replacement of the main landing gear shock absorber sliding 
rod attachment fitting. That AD resulted from corrosion and cracks 
found on these components. We issued that AD to prevent landing gear 
failure.
    The actions specified in paragraph (h) of this proposed AD would 
satisfy the

[[Page 14753]]

requirements of paragraph A. of AD 84-02-04. There are no actions in 
this proposed AD that would satisfy the requirements of paragraphs B. 
and C. of AD 84-02-04.

FAA's Determination and Requirements of the 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.
    This proposed AD would supersede AD 87-16-06 and would retain the 
requirements of that existing AD. This proposed AD would also add 
airplanes to the applicability and require revising the ALS of the ICA 
to incorporate additional life limits and/or structural inspections for 
certain main landing gear and nose landing gear components.

Change to Existing AD

    This proposed AD would retain the requirements of AD 87-16-06. 
Since AD 87-16-06 was issued, the AD format has been revised. As a 
result, the corresponding paragraph identifiers have changed in this 
proposed AD, and paragraph (g) of this proposed AD corresponds to 
paragraph A. of AD 87-16-06.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                          Number of U.S.-
                         Action                             Work hours     Average labor       Parts         Cost per       registered      Fleet cost
                                                                           rate per hour                     airplane        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Replacement (required by AD 87-16-06)...................               7             $80          $3,300          $3,860              94        $362,840
Revision (new proposed action)..........................               1              80               0              80             238          19,040
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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 proposed 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.

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 
removing amendment 39-5692 (52 FR 28241, July 29, 1987) and adding the 
following new airworthiness directive (AD):

Airbus: Docket No. FAA-2009-0292; Directorate Identifier 2008-NM-
011-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by May 1, 
2009.

Affected ADs

    (b) This AD supersedes AD 87-16-06.

Applicability

    (c) This AD applies to all Airbus Model A300, A310, and A300-600 
series airplanes, certificated in any category.

Subject

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

Unsafe Condition

    (e) This AD results from revisions to the Airworthiness 
Limitations section (ALS) of the Instructions for Continued 
Airworthiness (ICA) to include new or more restrictive life limits 
and/or replacements. We are issuing this AD to ensure the continued 
structural integrity of these airplanes.

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.

    Note 1: This AD requires revisions to certain operator 
maintenance documents to include new replacements. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these replacements, the operator may not be able 
to accomplish the replacements described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according 
to paragraph (l) of this AD. The request should include a 
description of changes to the required replacements that will ensure 
the continued operational safety of the airplane.

[[Page 14754]]

Restatement of the Requirements of AD 87-16-06

    (g) For Model A300 and A310 Series Airplanes: Prior to the 
accumulation of 16,000 landings, or within the next 2,000 landings 
after September 3, 1987 (the effective date of AD 87-16-06), 
whichever occurs later, replace the nose landing gear drag strut 
upper attachment pin in accordance with Airbus Service Bulletin 
A300-32-374, Revision 1, dated July 15, 1986 (applicable to Model 
A300 airplanes); or A310-32-2023, Revision 2, dated November 14, 
1986 (applicable to Model A310 airplanes).

New Requirements of This AD

ALS Revision

    (h) For Model A300, A310, and A300-600 Series Airplanes: Within 
3 months after the effective date of this AD, revise the ALS of the 
ICA to incorporate the applicable document listed in paragraph 
(h)(1), (h)(2), or (h)(3) of this AD. Accomplishing the actions 
specified in the applicable document satisfies the requirements of 
paragraph A. of AD 84-02-04, amendment 39-4795.
    (1) For Model A300 Series Airplanes: Incorporate the document 
listed in paragraph (h)(1)(i) or (h)(1)(ii) of this AD.
    (i) Section 05-10-00, Revision 28, dated February 27, 1998, of 
Chapter 5, ``Service Life Limits and Maintenance Checks,'' of the 
Airbus A300 Aircraft Maintenance Manual, except that the parts 
listed in Table 1 of this AD are subject to the life limits defined 
in the document listed in paragraph (h)(1)(ii) of this AD.
    (ii) ``Sub-part 1-2: Life Limits,'' and ``Sub-part 1-3: 
Demonstrated fatigue lives'' of Part 1, ``Safe Life Airworthiness 
Limitation Items,'' dated September 6, 2007, of the Airbus A300 ALS.

   Table 1--Parts Subject to the Life Limits Specified in the Document
              Identified in Paragraph (h)(1)(ii) of This AD
------------------------------------------------------------------------
           Part Number (P/N)                        Part name
------------------------------------------------------------------------
P/N C61643-2, P/N C61643-4, P/N C61643-  Main landing gear (MLG) shock
 5.                                       absorber end fitting.
P/N A32210001205xx.....................  Nose landing gear (NLG) pintle
                                          pin.
P/N C62037-1...........................  NLG shock absorber bottom.
P/N 196-0328-501.......................  Cross beam (Pratt & Whitney
                                          forward engine mount).
------------------------------------------------------------------------

    (2) For Model A310 Series Airplanes: Incorporate ``Sub-part 1-2: 
Life Limits,'' and ``Sub-part 1-3: Demonstrated fatigue lives'' of 
Part 1, ``Safe Life Airworthiness Limitation Items,'' dated December 
21, 2006, of the Airbus A310 ALS.
    (3) For Model A300-600 Series Airplanes: Incorporate ``Sub-part 
1-2: Life Limits,'' and ``Sub-part 1-3: Demonstrated fatigue lives'' 
of Part 1, ``Safe Life Airworthiness Limitation Items,'' dated 
December 21, 2006, of the Airbus A300-600 ALS.

Initial Compliance Times and Repetitive Inspections

    (i) Do the replacement at the applicable time specified in 
paragraph (i)(1) or (i)(2) of this AD, except as provided by 
paragraph (j) of this AD. The replacement must be done thereafter 
within the interval specified in the applicable document identified 
in paragraph (h)(1), (h)(2), or (h)(3) of this AD.
    (1) For any life limitation/task that has been complied with 
before the effective date of this AD in accordance with the 
applicable document listed in paragraph (h)(1), (h)(2), or (h)(3) of 
this AD, or in accordance with paragraph (g) of this AD, use the 
last accomplishment of each limitation/task as a starting point for 
accomplishing each corresponding limitation/task required by this 
AD.
    (2) For any life limitation/task that has not been complied with 
before the effective date of this AD in accordance with the 
applicable document listed in paragraphs (h)(1), (h)(2), and (h)(3) 
of this AD, or in accordance with paragraph (g) of this AD, the 
initial compliance time starts from the date of initial entry into 
service as defined in the applicable document.

Special Compliance Times

    (j) For any airplane on which the history of accumulated 
landings is partial or unknown, or where the history of application 
details (airplane type, model, weight variant, etc.) is partial or 
unknown, with or without using the information in Airbus Service 
Information Letter 32-118, Revision 02, dated October 24, 2007: 
Parts listed in Figure 1 of this AD must be replaced at the 
associated compliance time. The replacement must be done thereafter 
at the interval specified in the applicable document(s) specified in 
paragraphs (h)(1), (h)(2), and (h)(3) of this AD.
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Alternative Intervals or Limits

    (k) Except as provided by paragraph (l) of this AD, after 
accomplishing the actions specified in paragraphs (h), (i), and (j) 
of this AD, no alternative replacements, replacement intervals, or 
limitations may be used.

Alternative Methods of Compliance (AMOCs)

    (l)(1) The Manager, Manager, ANM-116, International Branch, 
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: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 227-1622; fax (425) 227-1149.
    (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 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.

Related Information

    (m) European Aviation Safety Agency (EASA) Airworthiness 
Directive 2007-0293, dated November 29, 2007, also addresses the 
subject of this AD.

    Issued in Renton, Washington, on March 12, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-7267 Filed 3-31-09; 8:45 am]

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