AD 2015-22-05

[Federal Register Volume 80, Number 218 (Thursday, November 12, 2015)]
[Rules and Regulations]
[Pages 69846-69852]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2015-27449]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2461; Directorate Identifier 2013-NM-202-AD; 
Amendment 39-18310; AD 2015-22-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding 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 
required 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. This new AD requires revising the maintenance 
or inspection program to incorporate new maintenance requirements and 
airworthiness limitations. 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.

DATES: This AD becomes effective December 17, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 17, 
2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of October 
27, 2009 (74 FR 48143, September 22, 2009).

ADDRESSES: You may examine the AD docket on the Internet at http://

[[Page 69847]]

www.regulations.gov/#!docketDetail;D= FAA-2015-2461; or in person at 
the Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC.
    For service information identified in this 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 <a href="/cdn-cgi/l/email-protection#402123232f352e346e212932372f3234286d252133002129322235336e232f2d"><span class="__cf_email__" data-cfemail="9dfcfefef2e8f3e9b3fcf4efeaf2efe9f5b0f8fceeddfcf4efffe8eeb3fef2f0">[email&#160;protected]</span></a>; Internet <a href="http://www.airbus.com">http://www.airbus.com</a>. 
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. It 
is also available on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by 
searching for and locating Docket No. FAA-2015-2461.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2009-18-15, Amendment 39-16011 (74 FR 48143, 
September 22, 2009). AD 2009-18-15 applied to 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). The NPRM published in the Federal Register on July 
14, 2015 (80 FR 40942).
    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 
[<a href="http://ad.easa.europa.eu/blob/easa_ad_2007_0092.pdf/AD_2007-0092">http://ad.easa.europa.eu/blob/easa_ad_2007_0092.pdf/AD_2007-0092</a>] 
[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 <a href="http://www.regulations.gov/#!documentDetail">http://www.regulations.gov/#!documentDetail</a>;D=FAA-2015-2461-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 40942, July 14, 
2015) or on the determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed, except for 
minor editorial changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (80 FR 40942, July 14, 2015) for correcting the unsafe condition; 
and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 40942, July 14, 2015).

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information. ``Sub-part 1-
2: Life Limits'' and ``Sub-part 1-3: Demonstrated fatigue lives'' of 
Part 1, ``Safe Life Airworthiness Limitation Items,'' in each of these 
documents describe procedures for revising the maintenance or 
inspection program to incorporate new maintenance requirements and 
airworthiness limitations.
    <bullet> For Model A300 series airplanes: Part 1, ``Safe Life 
Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013, 
of the Airbus Model A300 Airworthiness Limitations Section.
    <bullet> 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): Part 1, ``Safe Life 
Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013, 
of the Airbus Model A300-600 Airworthiness Limitations Section.
    <bullet> For Model A310 series airplanes: 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 
AD.

Costs of Compliance

    We estimate that this AD affects 177 airplanes of U.S. registry.
    The retained 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 takes about 1 work-hour per product to 
comply with the new ALS revision of this AD. The average labor rate is 
$85 per work-hour. Based on these figures, we estimate the cost of this 
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.

[[Page 69848]]

Regulatory Findings

    We 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 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov/#!docketDetail">http://www.regulations.gov/#!docketDetail</a>;D=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 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    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 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:

2015-22-05 Airbus: Amendment 39-18310. Docket No. FAA-2015-2461; 
Directorate Identifier 2013-NM-202-AD.

(a) Effective Date

    This AD becomes effective December 17, 2015.

(b) Affected ADs

    (1) This AD replaces AD 2009-18-15, Amendment 39-16011 (74 FR 
48143, September 22, 2009).
    (2) Accomplishing certain requirements of paragraph (g) of this 
AD satisfies the requirements of paragraph A. of AD 84-02-04, 
Amendment 39-4795 (49 FR 2746, January 23, 1984).

(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 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 (49 FR 2746, January 23, 1984).
    (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

[[Page 69849]]

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: 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
            Designation                      A300              A310       A300-600                     Start date                    date'')
                                   -------------------------------------------------     P/N                           ---------------------------------
                                              X                 X            X                                           Landings       Calendar time
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                    MAIN LANDING GEAR
--------------------------------------------------------------------------------------------------------------------------------------------------------
Aft pintle pin....................  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.
                                    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.
Half ball housing (Fwd pintle       A32140036200xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
 bearing).                          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.
                                    A32140042200xx.......           X   ...........           X   December 13, 2007...      13,500  9 years.
                                    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.
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.
                                                                                                                       ---------------------------------

[[Page 69850]]

 
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.
                                    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.

[[Page 69851]]

 
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 
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: <a href="/cdn-cgi/l/email-protection#d3eafe929d9efee2e2e5fe929e9c90fe819682869680878093b5b2b2fdb4bca5"><span class="__cf_email__" data-cfemail="3b02167a7576160a0a0d167a76747816697e6a6e7e686f687b5d5a5a155c544d">[email&#160;protected]</span></a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching 
for and locating Docket No. FAA-2015-2461-0002.

[[Page 69852]]

    (2) Service information identified in this AD that is not 
incorporated by reference in this AD is available at the addresses 
specified in paragraphs (n)(5) and (n)(6) of this AD.

(n) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
November 27, 2015.
    (i) ALS Part 1, ``Safe Life Airworthiness Limitation Items,'' 
Revision 01, dated September 5, 2013, of the Airbus Model A300 
Airworthiness Limitations Section.
    (ii) ALS Part 1, ``Safe Life Airworthiness Limitation Items,'' 
Revision 01, dated September 5, 2013, of the Airbus Model A300-600 
Airworthiness Limitations Section.
    (iii) ALS Part 1, ``Safe Life Airworthiness Limitation Items,'' 
Revision 01, dated September 5, 2013, of the Airbus Model A310 
Airworthiness Limitations Section.
    (4) The following service information was approved for IBR on 
October 27, 2009 (74 FR 48143, September 22, 2009).
    (i) Section 05-10-00 of Chapter 05, ``Service Life Limits and 
Maintenance Checks,'' of the Airbus A300 Aircraft Maintenance Manual 
(AMM), Revision 28, dated February 27, 1998.
    (A) The AMM title page; the Record of Revisions, Effective 
Pages, and Table of Content pages; and Section 05-10-00; for Chapter 
05 of Airbus A300 AMM are all dated February 27, 1998.
    (B) The revision level of Chapter 05 of the Airbus A300 AMM is 
indicated only in the Record of Revisions section of Chapter 05.
    (C) The List of Effective Pages (LOEP) for Chapter 05 of the 
Airbus A300 AMM contains the discrepancies identified in paragraphs 
(n)(4)(i)(C)(1) through (n)(4)(i)(C)(4) of this AD.
    (1) The Transmittal Letter page, page 4 of the LOEP and Table of 
Contents sections, page 2 of Subsection 05-00-01, Subsection 05-10-
00, and page 1 of Subsection 05-11-11, are not listed in the LOEP 
for Chapter 05 of the Airbus A300 AMM.
    (2) The LOEP for Chapter 05 of the Airbus A300 AMM does not 
specify a date for the Record of Revisions page.
    (3) The LOEP for Chapter 05 of the Airbus A300 AMM identifies 
three pages for Subsection 05-11-00, Configuration 5; however, only 
one page exists.
    (4) The LOEP for Chapter 05 of the Airbus A300 AMM identifies 
three pages for Subsection 05-11-00, Configuration 9; however, those 
pages do not exist.
    (ii) Airbus A300 Airworthiness Limitations Section, ALS Part 1, 
``Safe Life Airworthiness Limitations Items'' dated September 6, 
2007.
    (iii) Airbus A300-600 Airworthiness Limitations Section, ALS 
Part 1, ``Safe Life Airworthiness Limitations Items'' dated December 
21, 2006.
    (iv) Airbus A310 Airworthiness Limitations Section, ALS Part 1, 
``Safe Life Airworthiness Limitation Items'' dated December 21, 
2006.
    (5) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email <a href="/cdn-cgi/l/email-protection#adcccecec2d8c3d983ccc4dfdac2dfd9c580c8ccdeedccc4dfcfd8de83cec2c0"><span class="__cf_email__" data-cfemail="85e4e6e6eaf0ebf1abe4ecf7f2eaf7f1eda8e0e4f6c5e4ecf7e7f0f6abe6eae8">[email&#160;protected]</span></a>; Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (6) 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.
    (7) You may view this 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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on October 21, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-27449 Filed 11-10-15; 8:45 am]
BILLING CODE 4910-13-P