[Federal Register Volume 74, Number 182 (Tuesday, September 22, 2009)]
[Rules and Regulations]
[Pages 48143-48151]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-21033]


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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; 
Amendment 39-16011; AD 2009-18-15]
RIN 2120-AA64


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

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Airbus Model A300 and A310 series 
airplanes. That AD currently requires replacement of the nose landing 
gear drag strut upper attachment pin. This new AD requires revising the 
Airworthiness Limitations section (ALS) 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 also expands the applicability. This AD results from 
revisions to the ALS of the 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.

DATES: This AD becomes effective October 27, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of October 27, 
2009.

ADDRESSES: For service information identified in this 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: [email protected]; Internet http://www.airbus.com.

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

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Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

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: 

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 87-16-06, amendment 39-
5692 (52 FR 28241, July 29, 1987). The existing AD applies to certain 
Airbus Model A300 and A310 series airplanes. That NPRM was published in 
the Federal Register on April 1, 2009 (74 FR 14751). That NPRM proposed 
to continue to require replacement of the nose landing gear drag strut 
upper attachment pin. That NPRM also proposed to require revising the 
Airworthiness Limitations section (ALS) 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.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Request To Add Grace Period

    TradeWinds Airlines requests that we add a ``grace period'' to the 
life limit placed on the nose landing gear (NLG) shock absorber bottom, 
part number (P/N) C62037-1, listed in Table 1 of the NPRM, as 
referenced in paragraph (h)(1)(i) of the NPRM. TradeWinds explains that 
this component was not listed in Chapter 5 of the Airbus A300 Airplane 
Maintenance Manual (AMM) and had no corresponding FAA AD issued against 
it. Therefore, for U.S. operators, there was never a requirement to 
track the life limit. TradeWinds suggests a grace period of the next 
NLG overhaul or restoration be added so this internal component can be 
replaced without unscheduled removal from the airplane.
    We do not agree that it is necessary to add a grace period based on 
the operator's next overhaul or restoration. Maintenance schedules vary 
among operators; there is no assurance that the overhaul or restoration 
would occur within the maximum interval of time allowable for the 
affected airplanes to operate safely. However, under the provisions of 
paragraph (l) of this AD, we will consider requests for adjustments to 
the compliance time if data are submitted to substantiate that such an 
adjustment would provide an acceptable level of safety. We have not 
changed the AD in this regard.

Request To Clarify Purpose of Service Information Letter (SIL)

    TradeWinds Airlines requests that we clarify the purpose of Airbus 
Service Information Letter (SIL) 32-118, Revision 02, dated October 24, 
2007, as referenced in paragraph (j) of the NPRM. TradeWinds requests a 
note or some clarification to describe the use or application of the 
SIL as it pertains to the AD.
    We agree with the request to clarify the purpose of the SIL. We 
have added Note 2 to the AD to include the following information from 
page 1 of the SIL:

    Note 2:
    Airbus Service Information Letter 32-118, Revision 02, dated 
October 24, 2007, provides operators with guidance on the means to 
assign a conservative calculated life to parts whose history of 
accumulated landings is partial or unknown; and to select the 
limitations applicable to parts whose history of application details 
(aircraft type, aircraft model, weight variant, etc.) is partial or 
unknown.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the change described 
previously. We have determined that this change will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

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

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

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

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

2009-18-15 Airbus: Amendment 39-16011. Docket No. FAA-2009-0292; 
Directorate Identifier 2008-NM-011-AD.

Effective Date

    (a) This AD becomes effective October 27, 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.

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 applicable 
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 05, ``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 No. (P/N)                                              Part name
----------------------------------------------------------------------------------------------------------------
P/N C61643-2, P/N C61643-4, P/N       Main landing gear (MLG) shock absorber end fitting.
 C61643-5.
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.


[[Page 48146]]


    Note 2: Airbus Service Information Letter 32-118, Revision 02, 
dated October 24, 2007, provides operators with guidance on the 
means to assign a conservative calculated life to parts whose 
history of accumulated landings is partial or unknown; and to select 
the limitations applicable to parts whose history of application 
details (aircraft type, aircraft model, weight variant, etc.) is 
partial or unknown.

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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, 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.

Material Incorporated by Reference

    (n) You must use the service information contained in Table 2 of 
this AD to do the actions required by this AD, unless the AD 
specifies otherwise.

               Table 2--Material Incorporated by Reference
------------------------------------------------------------------------
           Document               Revision               Date
------------------------------------------------------------------------
Section 05-10-00 of Chapter    28...........  February 27, 1998.
 05, ``Service Life Limits
 and Maintenance Checks,'' of
 the Airbus A300 Aircraft
 Maintenance Manual.
Airbus A300 Airworthiness      Original.....  September 6, 2007.
 Limitations Section, ALS
 Part 1, ``Safe Life
 Airworthiness Limitations
 Items''.
Airbus A300-600 Airworthiness  Original.....  December 21, 2006.
 Limitations Section, ALS
 Part 1, ``Safe Life
 Airworthiness Limitations
 Items''.
Airbus A310 Airworthiness      Original.....  December 21, 2006.
 Limitations Section, ALS
 Part 1, ``Safe Life
 Airworthiness Limitation
 Items''.
Airbus Service Bulletin A300-  1............  July 15, 1986.
 32-374.
Airbus Service Bulletin A310-  2............  November 14, 1986.
 32-2023.
------------------------------------------------------------------------

    Airbus Service Bulletin A300-32-374, Revision 1, dated July 15, 
1986, has the following effective pages:

------------------------------------------------------------------------
                                   Revision
           Page No.              level shown       Date shown on page
                                   on page
------------------------------------------------------------------------
1, 3-8, 11....................  1............  July 15, 1986.
2.............................  Original.....  April 16, 1986.
------------------------------------------------------------------------

    (Airbus Service Bulletin A300-32-374, Revision 1, dated July 15, 
1986 does not contain pages 9 and 10.)
    Airbus Service Bulletin A310-32-2023, Revision 2, dated November 
14, 1986, has the following effective pages:

------------------------------------------------------------------------
                                   Revision
           Page No.              level shown       Date shown on page
                                   on page
------------------------------------------------------------------------
1, 5-9........................  2............  November 14, 1986
2, 4..........................  1............  July 15, 1986
3.............................  Original.....  April 16, 1986
------------------------------------------------------------------------

    Chapter 05 of Airbus A300 Aircraft Maintenance Manual has the 
following effective pages:

[[Page 48151]]



                                             List of Effective Pages
----------------------------------------------------------------------------------------------------------------
      Page title/description             Page No.(s)            Revision No.           Date shown on page(s)
----------------------------------------------------------------------------------------------------------------
AMM Title Page....................  None shown...........  None shown *.........  February 27, 1998.
Chapter 05 Record of Revisions....  1-2..................  28...................  February 27, 1998.
Chapter 05 Effective Pages........  1-4..................  None shown *.........  February 27, 1998.
Chapter 05 Table of Contents......  1-4..................  None shown *.........  February 27, 1998.
Section 05-10-00..................  1....................  None shown *.........  February 27, 1998.
----------------------------------------------------------------------------------------------------------------
* The revision number is indicated only in the Record of Revisions section of Chapter 05.

    (The List of Effective Pages (LOEP) for Chapter 05 of the Airbus 
A300 Aircraft Maintenance Manual contains the following errors: 
Transmittal Letter page, page 4 of the LOEP and Table of Contents 
sections, page 2 of Subsection 05-00-01, page 1 of Subsection 05-11-
11, and Subsection 05-10-00, are not listed in the LOEP; and the 
LOEP also does not specify a date for the Record of Revisions page. 
In addition, the LOEP identifies three pages for Subsection 05-11-
00, Configuration 5; however, only one page exists. The LOEP 
identifies three pages for Subsection 05-11-00, Configuration 9; 
however, those pages do not exist.)
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this 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: [email protected]; 
Internet http://www.airbus.com.
    (3) You may review copies of the 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.
    (4) You may also review copies of the service information that 
is incorporated by reference 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/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on August 24, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-21033 Filed 9-21-09; 8:45 am]
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