[Federal Register Volume 81, Number 24 (Friday, February 5, 2016)]
[Proposed Rules]
[Pages 6185-6190]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-02161]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0828; Directorate Identifier 2012-NM-036-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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

SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for certain Airbus Model A330-200 and -300 series airplanes; and 
Model A340-200 and -300 series airplanes. The NPRM proposed to 
supersede AD 2009-15-17 to continue to require inspections for damage 
to the protective treatments or any corrosion of all main landing gear 
(MLG) bogie beams, application of protective treatments, and corrective 
action if necessary. The NPRM also proposed to require modification of 
the MLG bogie beams, to allow optional methods of compliance for 
certain actions, and to add airplanes to the applicability. The first 
supplemental notice of proposed rulemaking (SNPRM) proposed to revise 
the compliance times and add a one-time inspection for certain 
airplanes. The NPRM was prompted by reports of thin paint coats and 
paint degradation on enhanced MLG bogie beams. This second SNPRM 
proposes to clarify the required actions and the specific 
configurations to which the actions must be applied. We are proposing 
this second SNPRM to detect and correct damage or corrosion of the MLG 
bogie beams, which could cause a runway excursion event, bogie beam 
detachment from the airplane, or MLG collapse, and could result in 
damage to the airplane and injury to the occupants. Since these actions 
impose an additional burden over those proposed in the first SNPRM, we 
are reopening the comment period to allow the public the chance to 
comment on these proposed changes.

DATES: We must receive comments on this SNPRM by March 21, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
    <bullet> Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For Airbus service information identified in this NPRM, 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: <a href="/cdn-cgi/l/email-protection#97f6fee5e0f8e5e3fffef9f2e4e4b9d6a4a4a7bad6a4a3a7d7f6fee5f5e2e4b9f4f8fa"><span class="__cf_email__" data-cfemail="f0919982879f828498999e958383deb1c3c3c0ddb1c3c4c0b0919982928583de939f9d">[email protected]</span></a>; Internet: 
http://www.airbus.com.
    For Messier-Dowty service information identified in this NPRM, 
contact Messier-Dowty: Messier Services Americas, Customer Support 
Center, 45360 Severn Way, Sterling, VA 20166-8910; telephone 703-450-
8233; fax 703-404-1621; Internet: https://techpubs.services/messier-dowty.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-2013-
0828; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (telephone: 800-647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; 
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-2013-0828; 
Directorate Identifier 2012-NM-036-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

[[Page 6186]]

will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued an SNPRM to amend 14 CFR part 39 by adding an AD that 
would apply to certain Airbus Model A330-200 Freighter series 
airplanes, Model A330-200 and A330-300 series airplanes, and Model 
A340-200 and A340-300 series airplanes. The SNPRM published in the 
Federal Register on March 5, 2014 (79 FR 12414).
    We preceded the SNPRM with a notice of proposed rulemaking (NPRM) 
that published in the Federal Register on September 25, 2013 (78 FR 
58978). The NPRM was prompted by reports of thin paint coats and paint 
degradation on enhanced MLG bogie beams. The NPRM proposed to supersede 
AD 2009-15-17, Amendment 39-15980 (74 FR 37523, July 29, 2009), to 
continue to require inspections for damage to the protective treatments 
or any corrosion of all MLG bogie beams, application of protective 
treatments, and corrective action if necessary. The NPRM also proposed 
to require modification of the MLG bogie beams, which would terminate 
the repetitive inspections for any modified bogie beam. In addition, 
the NPRM proposed to allow optional methods of compliance for certain 
actions, and to add Airbus Model A330-200 Freighter series airplanes to 
the applicability.
    The SNPRM (79 FR 12414, March 5, 2014) (``the first SNPRM'') 
proposed to revise the compliance times and add a one-time inspection 
for airplanes that were inspected too early.

Actions Since the First SNPRM Was Issued

    Since we issued the first SNPRM, we have determined that it is 
necessary to clarify the required actions and the specific 
configurations to which the actions must be applied. The European 
Aviation Safety Agency (EASA), which is the Technical Agent for the 
Member States of the European Union, has issued EASA AD 2013-0267R1, 
dated March 4, 2014, Corrected May 8, 2014 (referred to after this as 
the Mandatory Continuing Airworthiness Information, or ``the MCAI''), 
to correct an unsafe condition on certain Airbus Model A330-200 
Freighter, -200, and -300 series airplanes; and Model A340-200 and -300 
series airplanes. The MCAI states:

    The operator of an A330 aeroplane (which has a common bogie beam 
with the A340) reported a fracture of the Right Hand (RH) main 
landing gear (MLG) bogie beam, which occurred while turning during 
low speed taxi maneuvers. The bogie fractured aft of the pivot point 
and remained attached to the sliding tube by the brake torque 
reaction rods. After this RH bogie failure, the aeroplane continued 
for approximately 40 meters on the forks of the sliding member 
before coming to rest on the taxiway.
    The investigations revealed that this event was due to corrosion 
pitting occurring on the bore of the bogie beam.
    This condition, if not detected and corrected, could lead to a 
runway excursion event or to detachment of the bogie from the 
aeroplane, or to MLG collapse, possibly resulting in damage to the 
aeroplane and injury to the occupants.
    To enable early detection and repair of corrosion of the 
internal surfaces, EASA issued EASA AD 2007-0314 [http://ad.easa.europa.eu/ad/2007-0314R1] to require a one-time inspection 
of all MLG bogie beams, except Enhanced MLG bogie beams, and the 
reporting of the results to Airbus. EASA AD 2007-0314 was revised 
and later superseded by EASA AD 2008-0093 [http://ad.easa.europa.eu/ad/2008-0093], reducing the inspection threshold period.
    The results of subsequent investigations showed thin paint coats 
and paint degradation, confirmed as well on Enhanced MLG bogie 
beams. To address this additional concern, EASA issued AD 2011-0141 
[http://ad.easa.europa.eu/ad/2011-0141] [which was not mandated by 
the FAA], retaining the requirements of EASA AD 2008-0093, which was 
superseded, to require a one-time visual inspection of all MLG bogie 
beams, including a visual examination of the internal diameter for 
corrosion or damage to protective treatments of the bogie beam and 
measurement of the paint thickness on the internal bore, 
accomplishment of the applicable corrective actions and a 
modification of the MLG bogie beam to improve the coat paint 
application method, and application of corrosion protection.
    Prompted by in-service requests, EASA issued EASA AD 2012-0015 
[http://ad.easa.europa.eu/ad/2012-0015] [corresponds with FAA NPRM 
(78 FR 58978, September 25, 2013)] retaining the requirements of 
EASA AD 2011-0141, which was superseded, and introducing repetitive 
inspections of the MLG bogie beams, which allows extension of the 
compliance time for the MLG bogie beam modification from 15 years to 
21 years. Modification of a MLG bogie beam constitutes terminating 
action for the repetitive inspections for that MLG bogie beam.
    Reports on inspection results provided to Airbus show that some 
aeroplanes were initially inspected too early (before 4 years and 6 
months since aeroplane first flight with bogie beam installed/
installed after overhaul) and have not been re-inspected as 
required.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2012-0015, which is superseded, and 
redefines the inspection periodicity. This [EASA] AD also introduces 
a specific one-time inspection for aeroplanes that have been 
inspected too early.
    Prompted by operator comments, this [EASA] AD is revised to 
clarify the required actions and the specific configurations to 
which the actions must be applied. Appendix 1 of this [EASA] AD has 
been amended accordingly.
    This [EASA] AD is republished to editorially correct paragraph 
(4).

    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-2013-
0828.

Related Service Information Under 1 CFR Part 51

    We reviewed the following Airbus service information.
    <bullet> Airbus Mandatory Service Bulletin A330-32-3225, Revision 
2, dated October 26, 2012. The service information describes procedures 
for cleaning the internal bore and accomplishing a detailed inspection 
of internal surfaces of the left hand (LH) and right hand (RH) MLG 
bogie beams to detect any damage to the protective treatments and any 
corrosion, and measuring the paint thickness on the internal bore.
    <bullet> Airbus Mandatory Service Bulletin A330-32-3237, Revision 
1, dated October 14, 2011. The service information describes procedures 
for a detailed inspection for damage and corrosion of the internal 
bores of the LH and RH MLG bogie beam and repair, as well as 
modification and re-identification.
    <bullet> Airbus Mandatory Service Bulletin A340-32-4268, Revision 
3, dated January 14, 2013. The service information describes procedures 
for cleaning the internal bore and accomplishing a detailed inspection 
of internal surfaces of the LH and RH MLG bogie beams to detect any 
damage to the protective treatments and any corrosion, and measuring 
the paint thickness on the internal bore.
    <bullet> Airbus Mandatory Service Bulletin A340-32-4279, Revision 
1, dated October 14, 2011. The service information describes procedures 
for a detailed inspection for damage and corrosion of the internal 
bores of the LH and RH MLG bogie beam, repair, modification, and 
reidentification.
    We reviewed the following Messier-Dowty service bulletins.
    <bullet> Messier-Dowty Service Bulletin A33/34-32-271, Revision 1, 
dated November 16, 2007. The service information describes procedures 
for inspections and corrective actions on both MLG bogie beams.
    <bullet> Messier-Dowty Service Bulletin A33/34-32-272, Revision 1, 
including Appendixes A, B, C, and D, dated September 22, 2008. The 
service information describes procedures for

[[Page 6187]]

inspections and corrective actions on both MLG bogie beams.
    <bullet> Messier-Dowty Service Bulletin A33/34-32-278, including 
Appendixes A and B, Revision 1, dated August 24, 2011. The service 
information describes procedures for inspections for damage and 
corrosion to the protective treatment of the internal bores of the LH 
and RH MLG bogie beam, and repairs.
    <bullet> Messier-Dowty Service Bulletin A33/34-32-283, including 
Appendix A, Revision 1, dated July 10, 2012. The service information 
describes procedures for modification of the LH and RH MLG bogie beams.
    <bullet> Messier-Dowty Service Bulletin A33/34-32-284, including 
Appendix A, Revision 1, dated July 10, 2012. The service information 
describes procedures for modification of the LH and RH MLG bogie beams.
    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.

Change to the First SNPRM

    Since the first SNPRM was issued, the AD format has been revised, 
and certain paragraphs have been rearranged. As a result, paragraphs 
(m)(1) and (m)(2) of the proposed AD (in the first SNPRM) have been 
redesignated as paragraphs (n)(1) and (n)(2) of this proposed AD.

Comments

    We gave the public the opportunity to participate in developing 
this proposed AD. We considered the comment received.

Request To Revise Paragraph (l) of the Proposed AD (in the First SNPRM)

    Air France requested that we revise paragraph (l) of the proposed 
AD (in the first SNPRM) by changing the references to paragraphs (n)(1) 
and (n)(2) to refer to paragraphs (m)(1) and (m)(2).
    We agree that the optional terminating action paragraph should 
refer to the optional methods of compliance paragraphs, which are 
paragraphs (m)(1) and (m)(2) of the proposed AD (in the first SNPRM). 
However, no change to this proposed AD is necessary because those 
paragraphs have been redesignated as paragraphs (n)(1) and (n)(2).

FAA's Determination and Requirements of This SNPRM

    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 these 
same type designs.
    Certain changes described above expand the scope of the first 
SNPRM. As a result, we have determined that it is necessary to reopen 
the comment period to provide additional opportunity for the public to 
comment on this SNPRM.

Differences Between This SNPRM and the MCAI or Service Information

    The MCAI specifies repair and corrective actions in accordance with 
Airbus Mandatory Service Bulletin A330-32-3225, Revision 02, dated 
October 26, 2012; or A340-32-4268, Revision 03, dated January 14, 2013. 
However, Airbus Mandatory Service Bulletins A330-32-3225, Revision 02, 
dated October 26, 2012; and A340-32-4268, Revision 03, dated January 
14, 2013; do not describe repair and corrective actions. Paragraphs (i) 
and (j) of this proposed AD specify repair and corrective actions in 
accordance with Messier-Dowty Service Bulletin A33/34-32-272, Revision 
1, including Appendices A, B, C, and D, dated September 22, 2008. This 
difference has been coordinated with Airbus.

Costs of Compliance

    We estimate that this proposed AD affects 51 airplanes of U.S. 
registry.
    We also estimate that it would take about 34 work-hours per product 
to comply with the new basic requirements of this proposed AD, and 1 
work-hour per product for reporting. 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 $151,725, or $2,975 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 10 work-hours, for a cost of $850 per product. We have no 
way of determining the number of aircraft that might need these 
actions.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this proposed AD 
is 2120-0056. The paperwork cost associated with this proposed AD has 
been detailed in the Costs of Compliance section of this document and 
includes time for reviewing instructions, as well as completing and 
reviewing the collection of information. Therefore, all reporting 
associated with this proposed AD is mandatory. Comments concerning the 
accuracy of this burden and suggestions for reducing the burden should 
be directed to the FAA at 800 Independence Ave. SW., Washington, DC 
20591, ATTN: Information Collection Clearance Officer, AES-200.

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.

[[Page 6188]]

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) 
2009-15-17, Amendment 39-15980 (74 FR 37523, July 29, 2009), and adding 
the following new AD:

Airbus: Docket No. FAA-2013-0828; Directorate Identifier 2012-NM-
036-AD.

(a) Comments Due Date

    We must receive comments by March 21, 2016.

(b) Affected ADs

    This AD replaces AD 2009-15-17, Amendment 39-15980 (74 FR 37523, 
July 29, 2009).

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category, all 
manufacturer serial numbers (MSN), except those on which Airbus 
modification 58896 has been embodied in production.
    (1) Airbus Model A330-223F, -243F, -201, -202, -203, -223, -243, 
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of thin paint coats and paint 
degradation on enhanced main landing gear (MLG) bogie beams, as well 
as reports that some airplanes have been inspected too early and not 
re-inspected as needed. We are issuing this AD to detect and correct 
damage or corrosion of the MLG bogie beams, which could cause a 
runway excursion event, bogie beam detachment from the airplane, or 
MLG collapse, and could result in damage to the airplane and injury 
to the occupants.

(f) Compliance

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

(g) Repetitive Inspections for Certain Airplane Configurations

    For airplanes equipped with basic MLG (201252 series), or growth 
MLG (201490 series): After 54 months at the earliest, but no later 
than 72 months since the left-hand (LH) or right-hand (RH) MLG bogie 
beam's first flight on an airplane, or since its first flight on an 
airplane after overhaul, as applicable, clean the internal bore and 
accomplish a detailed inspection of internal surfaces of the LH and 
RH MLG bogie beams to detect any damage to the protective treatments 
and any corrosion, and measure the paint thickness on the internal 
bore, in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A330-32-3225, Revision 2, dated October 
26, 2012; or Airbus Mandatory Service Bulletin A340-32-4268, 
Revision 3, dated January 14, 2013; as applicable. Repeat the 
inspections thereafter at intervals not less than 54 months, but not 
exceeding 72 months, after the most recent inspection. During 
overhaul of a MLG bogie beam, any corrosion will be removed, which 
means that the first inspection after overhaul of that MLG bogie 
beam, as required by this paragraph, is between 54 months and 72 
months since its first flight on an airplane after overhaul.

(h) One-Time Detailed Inspection for Certain Airplane Configurations

    For airplanes equipped with basic MLG (201252 series), or growth 
MLG (201490 series) having a LH or RH MLG bogie beam that has 
already exceeded 72 months since its first flight on an airplane, or 
since its first flight on an airplane after overhaul, as applicable, 
as of the effective date of this AD; and that has been inspected as 
specified in Airbus Mandatory Service Bulletin A330-32-3225 or 
Airbus Mandatory Service Bulletin A340-32-4268, as applicable, 
earlier than 54 months since first flight of the affected MLG bogie 
beam on an airplane, or since its first flight on an airplane after 
its most recent overhaul, as applicable: Within the applicable 
compliance time indicated in paragraphs (h)(1) through (h)(4) of 
this AD, clean the internal bore and accomplish a detailed 
inspection of the internal surfaces of the LH and RH MLG bogie beams 
to detect any damage to the protective treatments and any corrosion, 
and measure the paint thickness on the internal bore, in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A330-32-3225, Revision 2, dated October 26, 2012; or Airbus 
Mandatory Service Bulletin A340-32-4268, Revision 3, dated January 
14, 2013; as applicable.
    (1) For MLG bogie beams having the configurations specified in 
both paragraphs (h)(1)(i) and (h)(1)(ii) of this AD: Do the detailed 
inspection specified in paragraph (h) of this AD within 9 months 
after the effective date of this AD.
    (i) MLG bogie beams having between 72 and 120 months since first 
flight on an airplane, or since the MLG bogie beam's first flight on 
an airplane after the MLG bogie beam's most recent overhaul, as 
applicable.
    (ii) MLG bogie beams on which the first inspection was done 
after 51 months and before 54 months since first flight of the MLG 
bogie beam on an airplane, or since the MLG bogie beam's first 
flight on an airplane after the MLG bogie beam's most recent 
overhaul, as applicable.
    (2) For MLG bogie beams having the configurations specified in 
both paragraphs (h)(2)(i) and (h)(2)(ii) of this AD: Do the detailed 
inspection specified in paragraph (h) of this AD within 3 months 
after the effective date of this AD.
    (i) MLG bogie beams having between 72 and 120 months since first 
flight on an airplane, or since the MLG bogie beam's first flight on 
an airplane after the MLG bogie beam's most recent overhaul, as 
applicable.
    (ii) MLG bogie beams on which the first inspection was done 
after 45 months and before 51 months since first flight of the MLG 
bogie beam on an airplane, or since the MLG bogie beam's first 
flight on an airplane after the MLG bogie beam's most recent 
overhaul, as applicable.
    (3) For MLG bogie beams having the configurations specified in 
both paragraphs (h)(3)(i) and (h)(3)(ii) of this AD: Do the detailed 
inspection specified in paragraph (h) of this AD within 3 months 
after the effective date of this AD.
    (i) MLG bogie beams having between 72 and 96 months since first 
flight on an airplane, or since the MLG bogie beam's first flight on 
an airplane after the MLG bogie beam's most recent overhaul, as 
applicable.
    (ii) MLG bogie beams which has accumulated, at the effective 
date of this AD, less than 96 months and on which the first 
inspection was done before 51 months since first flight of the MLG 
bogie beam on an airplane, or since the MLG bogie beam's first 
flight on an airplane after the after the MLG bogie beam's most 
recent overhaul, as applicable.
    (4) For MLG bogie beams having the configurations specified in 
both paragraphs (h)(4)(i) and (h)(4)(ii) of this AD: Do the detailed 
inspection specified in paragraph (h) of this AD within 1 month 
after the effective date of this AD.
    (i) MLG bogie beams having between 96 and 120 months since first 
flight on an airplane, or since the MLG bogie beam's first flight on 
an airplane after the MLG bogie beam's most recent overhaul, as 
applicable.
    (ii) MLG bogie beams which has accumulated, at the effective 
date of this AD, 96 months or more and on which the first inspection 
was done before 45 months since first flight of the MLG bogie beam 
on an airplane, or since the MLG bogie beam's first flight on an 
airplane after the MLG bogie beam's most recent overhaul, as 
applicable.

(i) Application of Protective Treatment

    If, during any inspection required by paragraph (g) or (h) of 
this AD, no damage or corrosion is found, before further flight, 
apply the protective treatments to the MLG bogie beam, in accordance 
with the Accomplishment Instructions of Messier-Dowty Service 
Bulletin A33/34-32-272, Revision 1, including Appendixes A, B, C, 
and D, dated September 22, 2008.

(j) Repair and Application of Protective Treatment

    If, during any inspection required by paragraph (g) or (h) of 
this AD, any damage

[[Page 6189]]

or corrosion is found, before further flight, repair and apply the 
protective treatments to the MLG bogie beam, in accordance with the 
Accomplishment Instructions of Messier-Dowty Service Bulletin A33/
34-32-272, Revision 1, including Appendixes A, B, C, and D, dated 
September 22, 2008.

(k) Inspection and Corrective Actions

    For airplanes equipped with basic MLG (201252 series), growth 
MLG (201490 series), or enhanced MLG (10-210 series): Before the 
accumulation of 252 total months on an MLG bogie beam, or within 90 
days after the effective date of this AD, whichever occurs later, do 
the actions specified in paragraphs (k)(1) and (k)(2) of this AD 
concurrently and in sequence.
    (1) Except as provided by paragraph (k)(3) of this AD: Do a 
detailed inspection for damage and corrosion of the internal bores 
of the LH and RH MLG bogie beam, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-32-3237 or A340-32-4279, both Revision 1, both dated October 
14, 2011, as applicable. If any damage or corrosion is found, before 
further flight, repair in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-32-3237 or 
A340-32-4279, both Revision 1, both dated October 14, 2011, as 
applicable.
    (2) Except as provided by paragraph (k)(3) of this AD: Modify 
and re-identify, as applicable, the LH and RH MLG bogie beams, in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A330-32-3237 or A340-32-4279, both Revision 1, both 
dated October 14, 2011, as applicable.
    (3) The inspection requirements of paragraph (k)(1) of this AD, 
and the modification requirements only of paragraph (k)(2) of this 
AD, do not apply to any MLG bogie beam with a serial number listed 
in Appendix A of Messier-Dowty Service Bulletin A33/34-32-283 or 
A33/34-32-284, both Revision 1, both dated July 10, 2012, as 
applicable.

(l) Optional Methods of Compliance for Certain Airplane Configurations

    Inspections and corrective actions on both MLG bogie beams done 
in accordance with the instructions of Messier-Dowty Service 
Bulletin A33/34-32-271, Revision 1, dated November 16, 2007; or A33/
34-32-272, Revision 1, including Appendixes A, B, C, and D, dated 
September 22, 2008; as applicable; are acceptable methods of 
compliance for the requirements of paragraph (g) of this AD, 
provided each inspection is accomplished between 54 months and 72 
months since the first flight of the affected MLG bogie beam on an 
airplane, or since the MLG bogie beam's first flight after the MLG 
bogie beam's most recent overhaul, as applicable.

(m) Reporting

    (1) Submit a report of the findings (both positive and negative) 
of each inspection required by paragraph (g) or (k) of this AD, as 
applicable, to Airbus, Customer Service Directorate, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex, France, using the applicable 
reporting sheet in Airbus Mandatory Service Bulletin A330-32-3237, 
Revision 1, dated October 14, 2011; or Airbus Mandatory Service 
Bulletin A340-32-4279, Revision 1, dated October 14, 2011; at the 
applicable time specified in paragraph (m)(1)(i) or (m)(1)(ii) of 
this AD.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 90 days after the inspection.
    (ii) If the inspection was done before the effective date of 
this AD: Submit the report within 90 days after the effective date 
of this AD.
    (2) Submit a report of the findings (both positive and negative) 
of the inspection required by paragraph (h) of this AD to Airbus, 
Customer Service Directorate, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France, using the applicable reporting sheet in 
Airbus Service Bulletin A330-32-3237 or A340-32-4279, both dated 
January 18, 2011, at the applicable time specified in paragraph 
(m)(2)(i) or (m)(2)(ii) of this AD.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (ii) If the inspection was done before the effective date of 
this AD: Submit the report within 30 days after the effective date 
of this AD.

(n) Optional Method of Compliance

    (1) Inspections for damage and corrosion to the protective 
treatment of the internal bores of the LH and RH MLG bogie beam, and 
repairs, done in accordance with Messier-Dowty Service Bulletin A33/
34-32-278, including Appendixes A and B, Revision 1, dated August 
24, 2011, are acceptable methods of compliance with the 
corresponding requirements of paragraph (k)(1) of this AD.
    (2) Modification of the LH and RH MLG bogie beams, done in 
accordance with Messier-Dowty Service Bulletins A33/34-32-283 and 
A33/34-32-284, both including Appendix A, both Revision 1, both 
dated July 10, 2012, as applicable, is an acceptable method of 
compliance with the corresponding requirements of paragraph (k)(2) 
of this AD.

(o) Optional Terminating Action

    Modification of both LH and RH MLG bogie beams on an airplane, 
done in accordance with paragraph (k) of this AD, or as specified in 
paragraphs (n)(1) and (n)(2) of this AD, terminates the repetitive 
inspections required by paragraph (g) of this AD for this airplane.

(p) Credit for Previous Actions

    (1) This paragraph provides credit for the corresponding 
inspections and corrective actions done on an LH or RH MLG bogie 
beam required by paragraph (g) of this AD, if those actions were 
performed before the effective date of this AD using Airbus 
Mandatory Service Bulletin A330-32-3225, dated November 21, 2007; or 
Revision 1, dated October 30, 2008; provided the inspections and 
corrective actions were accomplished between 54 months and 72 months 
since first flight of the affected MLG bogie beam on an airplane, or 
since its first flight after the MLG bogie beam's most recent 
overhaul, as applicable. Airbus Mandatory Service Bulletin A330-32-
3225, dated November 21, 2007, is not incorporated by reference in 
this AD. Airbus Mandatory Service Bulletin A330-32-3225, Revision 1, 
dated October 30, 2008, was incorporated by reference in AD 2009-15-
07, Amendment 39-15980 (74 FR 37523, July 29, 2009).
    (2) This paragraph provides credit for the corresponding 
inspections and corrective actions done on an LH or RH MLG bogie 
beam required by paragraph (g) of this AD, if those actions were 
performed before the effective date of this AD using Airbus 
Mandatory Service Bulletin A340-32-4268, dated November 21, 2007; 
Revision 1, dated October 30, 2008; or Revision 2, dated October 26, 
2012; provided these inspections and corrective actions were 
accomplished between 54 months and 72 months since first flight of 
the affected MLG bogie beam on an airplane, or since its first 
flight after the MLG bogie beam's most recent overhaul, as 
applicable. Airbus Mandatory Service Bulletin A340-32-4268, dated 
November 21, 2007; and Revision 2, dated October 26, 2012; are not 
incorporated by reference in this AD. Airbus Mandatory Service 
Bulletin A340-32-4268, Revision 1, dated October 30, 2008, was 
incorporated by reference in AD 2009-15-17, Amendment 39-15980 (74 
FR 37523, July 29, 2009).
    (3) This paragraph provides credit for the corresponding actions 
required by paragraph (n)(1) of this AD, if those actions were 
performed before the effective date of this AD using Messier-Dowty 
Service Bulletin A33/34-32-271, dated September 13, 2007, which is 
not incorporated by reference in this AD.
    (4) This paragraph provides credit for the corresponding actions 
required by paragraphs (j) and (n)(1) of this AD, if those actions 
were performed before the effective date of this AD using Messier-
Dowty Service Bulletin A33/34-32-272, including Appendixes A, B, C, 
and D, dated November 16, 2007, which is not incorporated by 
reference in this AD.
    (5) This paragraph provides credit for the corresponding actions 
required by paragraphs (k), (m), and (r)(1)(i) of this AD, if those 
actions were performed before the effective date of this AD using 
Airbus Mandatory Service Bulletin A330-32-3237, dated January 18, 
2011, which is not incorporated by reference in this AD.
    (6) This paragraph provides credit for the corresponding actions 
required by paragraphs (k), (m), and (r)(1)(i) of this AD, if those 
actions were performed before the effective date of this AD using 
Airbus Mandatory Service Bulletin A340-32-4279, dated January 18, 
2011, which is not incorporated by reference in this AD.
    (7) This paragraph provides credit for the corresponding actions 
required by paragraphs (k)(3), (n)(2), (r)(1)(ii), and (r)(1)(iii) 
of this AD, if those actions were performed before the effective 
date of this AD using Messier-Dowty Service Bulletin A33/34-32-283, 
including Appendix A, dated May 11, 2010, which is not incorporated 
by reference in this AD.
    (8) This paragraph provides credit for the corresponding actions 
required by paragraphs (k)(3), (n)(2), (r)(1)(ii), and

[[Page 6190]]

(r)(1)(iii) of this AD, if those actions were performed before the 
effective date of this AD using Messier-Dowty Service Bulletin A33/
34-32-284, including Appendix A, dated May 11, 2010, which is not 
incorporated by reference in this AD.
    (9) This paragraph provides credit for the corresponding actions 
required by paragraphs (n)(1) and (r)(1)(ii) of this AD, if those 
actions were performed before the effective date of this AD using 
Messier-Dowty Service Bulletin A33/34-32-278, including Appendixes A 
and B, dated February 17, 2010, which is not incorporated by 
reference in this AD.

(q) Clarification of Inspection Compliance Times

    After accomplishment of the one-time detailed inspection 
required by paragraph (h) of this AD, the repetitive actions 
required by paragraph (g) of this AD remain applicable, and must be 
done within the compliance times specified in paragraph (g) of this 
AD.

(r) Parts Installation Limitations

    (1) After modification of an airplane, as required by paragraph 
(k) of this AD, or as specified in paragraphs (n)(1) and (n)(2) of 
this AD, do not install an MLG bogie beam on any airplane unless it 
is done in compliance with the requirements of paragraph (r)(1)(i), 
(r)(1)(ii), or (r)(1)(iii) of this AD.
    (i) The MLG bogie beam has been modified and re-identified in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A330-32-3237 or A340-32-4279, both Revision 1, both 
dated October 14, 2011, as applicable.
    (ii) The MLG bogie beam has been inspected and all applicable 
corrective actions have been done in accordance with the 
Accomplishment Instructions of Messier-Dowty Service Bulletin A33/
34-32-278, Revision 1, dated August 24, 2011; and modified in 
accordance with the Accomplishment Instructions of Messier-Dowty 
Service Bulletin A33/34-32-283 or A33/34-32-284, both Revision 1, 
both dated July 10, 2012.
    (iii) The MLG bogie beam has a serial number listed in Appendix 
A of Messier-Dowty Service Bulletin A33/34-32-283 or A33/34-32-284, 
both Revision 1, both dated July 10, 2012.
    (2) As of the effective date of this AD, except as specified in 
paragraph (r)(1) of this AD, installation of an MLG bogie beam on an 
airplane is allowed, provided that following the installation it is 
inspected and all applicable repairs and corrective actions have 
been done in accordance with the requirements of this AD.

(s) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency (EASA) AD 2013-0267R1, dated 
March 4, 2014, corrected March 8, 2014, 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-
2013-0828.
    (2) For Airbus 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: <a href="/cdn-cgi/l/email-protection#4a2b23383d25383e2223242f3939640b79797a670b797e7a0a2b2338283f3964292527"><span class="__cf_email__" data-cfemail="e4858d96938b96908c8d8a819797caa5d7d7d4c9a5d7d0d4a4858d96869197ca878b89">[email protected]</span></a>; 
Internet http://www.airbus.com.
    (3) For Messier-Dowty service information identified in this AD, 
contact Messier-Dowty: Messier Services Americas, Customer Support 
Center, 45360 Severn Way, Sterling, VA 20166-8910; telephone 703-
450-8233; fax 703-404-1621; Internet https://techpubs.services/messier-dowty.com.
    (4) 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 January 27, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-02161 Filed 2-4-16; 8:45 am]
 BILLING CODE 4910-13-P


</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>