
[Federal Register Volume 80, Number 134 (Tuesday, July 14, 2015)]
[Proposed Rules]
[Pages 40942-40947]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-17201]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2461; Directorate Identifier 2013-NM-202-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2009-18-
15 for all Airbus Model A300, A310, and A300 B4-600, B4-600R, and F4-
600R series airplanes, and Model A300 C4-605R Variant F airplanes 
(collectively called Model A300-600 series airplanes). AD 2009-18-15 
currently 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. Since we issued AD 2009-18-15, 
we have determined that existing maintenance requirements and 
airworthiness limitations are inadequate to ensure the structural 
integrity of the airplane. This proposed AD would require revising the 
maintenance or inspection program to incorporate new maintenance 
requirements and airworthiness limitations. We are proposing this AD to 
prevent failure of certain system components, which could result in 
reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by August 28, 2015.

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, 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, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com.
    You may view this referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 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 by searching for and locating Docket No. FAA-2015-
2461; 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 
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, WA 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-2015-2461; 
Directorate Identifier 2013-NM-202-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 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 August 24, 2009, we issued AD 2009-18-15, Amendment 39-16011 (74 
FR 48143, September 22, 2009). AD 2009-18-15 requires actions intended 
to address an unsafe condition for all Airbus Model A300, A310, and 
A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-
605R Variant F airplanes (collectively called Model A300-600 series 
airplanes).
    Since we issued AD 2009-18-15, Amendment 39-16011 (74 FR 48143, 
September 22, 2009), we have determined that more restrictive 
maintenance requirements and airworthiness limitations are necessary.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0248, dated October 14, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Model A300, A310, 
and A300-600 series airplanes. The MCAI states:

    The airworthiness limitations for Airbus aeroplanes are 
currently published in Airworthiness Limitations Section (ALS) 
documents.
    The mandatory instructions and airworthiness limitations 
applicable to the Aging Systems Maintenance (ASM) are specified in 
Airbus A310 or A300-600 ALS Part 4 documents, which are approved by 
the European Aviation Safety Agency (EASA). EASA AD 2007-0092 
[http://ad.easa.europa.eu/blob/easa_ad_2007_0092.pdf/AD_2007-0092] 
[which corresponds to FAA AD 2009-06-06, Amendment 39-15842 (74 FR 
12228, March 24, 2009)] was issued to require compliance to the 
requirements as specified in these documents.
    The revision 02 of Airbus A310 and Airbus A300-600 ALS Part 4 
documents introduces more restrictive maintenance requirements and/
or airworthiness limitations. Failure to comply with the 
instructions of ALS Part 4 could result in an unsafe condition 
[reduced structural integrity of the airplane.]
    For the reasons described above, this new [EASA] AD retains the 
requirements of EASA AD 2007-0092, which is superseded, and requires 
the implementation of the new or more restrictive maintenance 
requirements and/or airworthiness limitations as specified in Airbus 
A310 ALS Part 4, Revision 02, or Airbus A300-600 ALS Part 4, 
Revision 02, as applicable to aeroplane type/model.

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2461.

[[Page 40943]]

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information, which 
describes procedures for revising the maintenance or inspection program 
to incorporate new maintenance requirements and airworthiness 
limitations.
     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,'' Revision 01, dated 
September 5, 2013, of the Airbus Model A300 Airworthiness Limitations 
Section.
     For Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model A300 C4-605R Variant F airplanes (collectively 
called 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,'' Revision 01, dated September 5, 2013, 
of the Airbus Model A300-600 Airworthiness Limitations Section.
     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,'' Revision 01, dated 
September 5, 2013, of the Airbus Model A310 Airworthiness Limitations 
Section.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business, or by the means identified in the ADDRESSES section of this 
NPRM.

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.

Costs of Compliance

    We estimate that this proposed AD affects 177 airplanes of U.S. 
registry.
    The ALS revision required by AD 2009-18-15, Amendment 39-16011 (74 
FR 48143, September 22, 2009), takes about 1 work-hour per product, at 
an average labor rate of $85 per work-hour. Based on these figures, the 
estimated cost of the actions that were required by AD 2009-18-15 is 
$85 per product.
    We also estimate that it would take about 1 work-hour per product 
to comply with the new ALS revision of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $15,045, or $85 
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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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.

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

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 FAA amends Sec.  39.13 by removing Airworthiness Directive AD 
2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009), and 
adding the following new AD:

Airbus: Docket No. FAA-2015-2461; Directorate Identifier 2013-NM-
202-AD.

(a) Comments Due Date

    We must receive comments by August 28, 2015.

(b) Affected ADs

    This AD replaces AD 2009-18-15, Amendment 39-16011 (74 FR 48143, 
September 22, 2009).

(c) Applicability

    This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-
203, B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, 
B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R 
airplanes; Model A300 F4-605R and F4-622R, and A300 C4-605R Variant 
F airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes; certificated in any category, all manufacturer 
serial numbers.

(d) Subject

    Air Transport Association (ATA) of America 32, Landing Gear.

(e) Reason

    This AD was prompted by a determination that existing 
maintenance requirements and airworthiness limitations are 
inadequate to ensure the structural integrity of the airplane. We 
are issuing this AD to prevent failure of certain system components, 
which could result in reduced structural integrity of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Revision of Airworthiness Limitation Section (ALS)

    This paragraph restates the requirements of paragraph (h) of AD 
2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). 
For Model A300, A310, and A300-600 series airplanes: Within 3 months 
after October 27, 2009 (the effective date of AD 2009-18-15), revise 
the ALS of the instructions for continued airworthiness (ICA) to 
incorporate the applicable document

[[Page 40944]]

listed in paragraph (g)(1), (g)(2), or (g)(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 (g)(1)(i) or (g)(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 to paragraph (g) of this AD are subject to the 
life limits defined in the document listed in paragraph (g)(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 to Paragraph (g) of This AD--Parts Subject to the Life Limits
 Specified in the Document Identified in Paragraph (g)(1)(ii) of This AD
------------------------------------------------------------------------
              Part No.  (P/N)                         Part name
------------------------------------------------------------------------
P/N C61643-2, P/N C61643-4, P/N C61643-5..  Main landing gear (MLG)
                                             shock 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 B4-600, B4-600R, and F4-600R series 
airplanes, and Model A300 C4-605R Variant F airplanes (collectively 
called 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.

(h) Retained Initial Compliance Times and Repetitive Inspections

    This paragraph restates the requirements of paragraph (i) of AD 
2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). Do 
the replacement at the applicable time specified in paragraph (h)(1) 
or (h)(2) of this AD, except as provided by paragraph (i) of this 
AD. The replacement must be done thereafter within the interval 
specified in the applicable document identified in paragraph (g)(1), 
(g)(2), or (g)(3) of this AD.
    (1) For any life limitation/task that has been complied with 
before October 27, 2009 (the effective date of AD 2009-18-15, 
Amendment 39-16011), in accordance with the applicable document 
listed in paragraph (g)(1), (g)(2), or (g)(3) of this AD, or in 
accordance with paragraph (g) of AD 2009-18-15, 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 October 27, 2009 (the effective date of AD 2009-18-15, 
Amendment 39-16011), in accordance with the applicable document 
listed in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, or in 
accordance with paragraph (g) of AD 2009-18-15, the initial 
compliance time starts from the date of initial entry into service 
as defined in the applicable document.

(i) Retained Special Compliance Times

    This paragraph restates the requirements of paragraph (j) of AD 
2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). 
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 to paragraph (i) 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 (g)(1), (g)(2), and (g)(3) of this AD.
    Note 1 to paragraph (i) of this AD: 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.

                                             Figure 1 to Paragraph (i) of This AD--Special Compliance Times
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                             Aircraft type applicability                                             Compliance time (whichever occurs
                                ----------------------------------------------------                                  first after the ``start date'')
          Designation                    A300            A310    A300-600                     Start date         ---------------------------------------
                                ------------------------------------------    P/N
                                           X               X         X                                                 Landings          Calendar time
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                    MAIN LANDING GEAR
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                       A32140032200xx        X                       December 13, 2007..........  13,500............  9 years.
                                       A32140056200xx        X                       December 13, 2007..........  13,500............  9 years.
                                       A32140056202xx        X                       December 13, 2007..........  13,500............  9 years.
Aft pintle pin.................        A32140057200xx        X                       December 13, 2007..........  13,500............  9 years.
                                       A32140057202xx        X                   X   December 13, 2007..........  13,500............  9 years.
                                       A32140062000xx        X                       December 13, 2007..........  13,500............  9 years.
                                       A32140063000xx        X                   X   December 13, 2007..........  13,500............  9 years.
                                       A32140036200xx        X                       December 13, 2007..........  13,500............  9 years.
                                       A32140036202xx        X                       December 13, 2007..........  13,500............  9 years.
                                       A32140036204xx        X                       December 13, 2007..........  13,500............  9 years.
                                       A32140036206xx        X                       December 13, 2007..........  13,500............  9 years.
Half ball housing (Fwd pintle          A32140042200xx        X                   X   December 13, 2007..........  13,500............  9 years.
 bearing).
                                       A32140042202xx        X                   X   December 13, 2007..........  13,500............  9 years.
                                       A32140068002xx        X                       December 13, 2007..........  13,500............  9 years.
                                       A32140068004xx        X                       December 13, 2007..........  13,500............  9 years.
                                       A32140069002xx        X                   X   December 13, 2007..........  13,500............  9 years.
                                       A32140069004xx        X                   X   December 13, 2007..........  13,500............  9 years.
Ball (Fwd pintle pin)..........        A32140012202xx        X                       December 13, 2007..........  13,500............  9 years.
                                       A32140043202xx        X                   X   December 13, 2007..........  13,500............  9 years.

[[Page 40945]]

 
Pin (Multiple link/Frame 50)...        A53833451200xx        X                       December 13, 2007..........  13,500............  9 years..
                                       A53833451206xx        X                       December 13, 2007..........  13,500............  9 years.
                                       A53834451200xx        X                       December 13, 2007..........  13,500............  9 years.
                                       A53834451202xx        X                   X   April 25, 2007.............  13,500............  9 years.
Pin (Drop link/Frame 50).......        A53811122200xx                  X             April 25, 2007.............  18,000............  9 years.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                   MLG Barrel Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Upper torque link pin nut......            00-200-402        X                       December 13, 2007..........  N/A...............  30 months.
                                              SL40089        X                       December 13, 2007..........  N/A...............  30 months.
                                             SL40089P        X                       December 13, 2007..........  N/A...............  30 months.
                                              SL40123        X                       December 13, 2007..........  N/A...............  30 months.
                                             SL40123P        X         X         X   April 25, 2007.............  N/A...............  30 months.
Torque link medium pin nut.....            00-200-358        X                       December 13, 2007..........  N/A...............  30 months.
                                             SL40114P        X         X             April 25, 2007.............  N/A...............  30 months.
                                              SL40132        X                       December 13, 2007..........  N/A...............  30 months.
                                             SL40132P        X                   X   April 25, 2007.............  N/A...............  30 months.
Attaching fitting pin..........              C62311-1        X                       December 13, 2007..........  13,500............  9 years.
                                            C62311-20        X                   X   April 25, 2007.............  13,500............  9 years.
Pin (Connecting rod/Upper rod).                C65815        X                       December 13, 2007..........  13,500............  9 years.
                                             C65815-1        X                       December 13, 2007..........  13,500............  9 years.
                                            C65815-20        X                       December 13, 2007..........  13,500............  9 years.
                                               C66472        X                       December 13, 2007..........  13,500............  9 years.
                                             C66472-1        X                       December 13, 2007..........  13,500............  9 years.
                                            C66472-20        X                   X   April 25, 2007.............  13,500............  9 years.
                                               D52751                  X             April 25, 2007.............  18,000............  9 years.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                               MLG Shock Absorber Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Lower torque link pin nut......            00-200-402        X                       December 13, 2007..........  N/A...............  30 months.
                                              SL40089        X                       December 13, 2007..........  N/A...............  30 months.
                                             SL40089P        X                       December 13, 2007..........  N/A...............  30 months.
                                              SL40123        X                       December 13, 2007..........  N/A...............  30 months.
                                             SL40123P        X         X         X   April 25, 2007.............  N/A...............  30 months.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Bogie beam pivot pin nut.......               SL40054        X                       December 13, 2007..........     at next removal/installation.1 2
                                             SL40054P        X                   X   April 25, 2007.............     at next removal/installation.1 2
                                             SL40413P                  X             April 25, 2007.............     at next removal/installation.1 2
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                 MLG Lock Link Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Lock link medium pin...........              C61485-1        X                       December 13, 2007..........  N/A...............  30 months.
                                            C61485-20        X                   X   April 25, 2007.............  N/A...............  30 months.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                    NOSE LANDING GEAR
--------------------------------------------------------------------------------------------------------------------------------------------------------
Pintle pin.....................        A32210079200xx        X         X         X   April 25, 2007.............  13,500............  9 years.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                              NLG Telescopic Strut Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Nut (Cylinder/Locking cylinder)                C61375        X         X             April 25, 2007.............  13,500............  9 years.
                                               D55955        X         X         X   April 25, 2007.............  13,500............  9 years.
Locking sleeve.................                C61389        X         X             December 13, 2007..........  13,200............  9 years.
                                             C61389-1        X         X         X   April 25, 2007.............  13,500............  9 years.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                   NLG Barrel Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Pin (Clevis/Telescopic strut)..              C62231-1        X                       December 13, 2007..........  13,200............  9 years.
                                             C62231-2        X                       December 13, 2007..........  13,200............  9 years.

[[Page 40946]]

 
                                            C62231-20        X         X         X   April 25, 2007.............  13,500............  9 years.
                                               D56530        X         X         X   April 25, 2007.............  13,500............  9 years.
Lower pin (Link/Clevis)........              C62268-1        X                       December 13, 2007..........  13,200............  9 years.
                                             C62268-2        X                       December 13, 2007..........  13,200............  9 years.
                                            C62268-20        X         X         X   April 25, 2007.............  13,500............  9 years.
Link (Clevis/Barrel)...........              C62230-1        X         X         X   April 25, 2007.............  13,500............  9 years.
                                               D56526        X         X         X   April 25, 2007.............  13,500............  9 years.
Upper pin (Link/Barrel)........              C62267-1        X                       December 13, 2007..........  13,200............  9 years.
                                             C62267-2        X                       December 13, 2007..........  13,200............  9 years.
                                            C62267-20        X         X         X   April 25, 2007.............  13,500............  9 years.
--------------------------------------------------------------------------------------------------------------------------------------------------------
End fitting pin nut............                D68062        X         X         X   December 13, 2007..........     at next removal/installation.\2\
                                            MS17825-6        X         X         X   December 13, 2007..........     at next removal/installation.\2\
End fitting pin................                AN6-17        X         X         X   December 13, 2007..........     at next removal/installation.\2\
                                               D61183        X         X         X   December 13, 2007..........     at next removal/installation.\2\
                                               D68063        X         X         X   December 13, 2007..........     at next removal/installation.\2\
                                          NAS1306-22D        X         X         X   December 13, 2007..........     at next removal/installation.\2\
--------------------------------------------------------------------------------------------------------------------------------------------------------
End fitting....................                C62032        X         X         X   April 25, 2007.............  13,500............  9 years.
                                             C62032-1        X         X         X   April 25, 2007.............  13,500............  9 years.
Rack...........................                C61453        X                       December 13, 2007..........  13,200............  9 years.
                                             C61453-1        X         X         X   April 25, 2007.............  13,500............  9 years.
                                            C61453-20        X         X         X   April 25, 2007.............  13,500............  9 years.
                                            C61453-40        X         X         X   April 25, 2007.............  13,500............  9 years.
                                            C61453-41        X         X         X   April 25, 2007.............  13,500............  9 years.
Torque link pin (Upper & Lower)              C62223-1        X                       December 13, 2007..........  13,200............  9 years.
                                            C62223-20        X         X         X   April 25, 2007.............  13,500............  9 years.
Torque link medium pin nut.....              SL40110P        X         X         X   April 25, 2007.............  N/A...............  30 months.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                               NLG Shock Absorber Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Wheel axle nut.................                C62879        X         X         X   April 25, 2007.............  4,000.............  24 months.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Upper cam dowel................                C62270        X         X         X   December 13, 2007..........       at next removal/installation.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Upper cam......................              C62034-1        X         X         X   April 25, 2007.............  13,500............  9 years.
Lower cam......................                C62035        X         X         X   April 25, 2007.............  13,500............  9 years.
Restrictor.....................                C62036        X                       December 13, 2007..........  13,200............  9 years.
                                             C62036-1        X                       December 13, 2007..........  13,200............  9 years.
                                             C62036-2        X                       December 13, 2007..........  13,200............  9 years.
                                               C67863        X                       December 13, 2007..........  13,200............  9 years.
                                             C67863-1        X         X         X   April 25, 2007.............  13,500............  9 years.
                                             C67863-2        X         X         X   April 25, 2007.............  13,500............  9 years.
                                             C67863-3        X                       December 13, 2007..........  13,500............  9 years.
                                             C67863-4        X         X         X   April 25, 2007.............  13,500............  9 years.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Lower cam dowel................                C62866        X         X         X   December 13, 2007..........     at next removal/installation.\2\
Nut (S/A/Barrel)...............                C64040        X                       December 13, 2007..........     at next removal/installation.1 2
                                             C64040-1        X         X         X   December 13, 2007..........     at next removal/installation.1 2
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ When the nut is temporarily removed and reinstalled for the purpose of performing maintenance outside a workshop, no replacement is required
  provided the nut's removal and reinstallation are performed on the same assembly and neither the assembly nor the nut accumulates time in service
  during the period between the removal and reinstallation.
\2\ If the removal/installation was done after the start date, but before the effective date of this AD, the compliance time is within 3 months. after
  October 27, 2009 (the effective date of AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009)).

(j) New Requirements of This AD: Maintenance Program Revision

    Within 3 months after the effective date of this AD: Revise the 
maintenance or inspection program, as applicable, to incorporate the 
applicable limitation, replacement, or inspection specified in 
paragraph (j)(1), (j)(2), or (j)(3) of this AD, as applicable. Doing 
any task required by this paragraph terminates the corresponding 
task required by paragraph (g), (h), and (i) of this AD.
    (1) For Model A300 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,'' Revision 01, 
dated September 5, 2013, of the Airbus A300 ALS.
    (2) For Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model A300 C4 605R Variant F airplanes (collectively

[[Page 40947]]

called 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,'' Revision 01, 
dated September 5, 2013, of the Airbus A300-600 ALS.
    (3) 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 Revision 
01, September 5, 2013, of the Airbus A310 ALS.

(k) New Limitation: No Alternative Actions or Intervals

    After accomplishment of the revision required by paragraph (j) 
of this AD, no alternative actions (e.g., inspections) or intervals 
may be used unless the actions or intervals are approved as an 
alternative method of compliance (AMOC) in accordance with the 
procedures specified in paragraph (l) of this AD.

(l) Other FAA AD Provisions

    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. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0248, dated October 14, 
2013, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2015-2461.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com. You may view this service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on June 25, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-17201 Filed 7-13-15; 8:45 am]
 BILLING CODE 4910-13-P


