
[Federal Register Volume 79, Number 43 (Wednesday, March 5, 2014)]
[Proposed Rules]
[Pages 12414-12420]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04892]


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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.

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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, which would terminate the repetitive inspections 
for any modified bogie beam. The NPRM also proposed to allow optional 
methods of compliance for certain actions. The NPRM was prompted by 
reports of thin paint coats and paint degradation on enhanced MLG bogie 
beams, as well as reports that some airplanes have been inspected too 
early

[[Page 12415]]

and not re-inspected as needed. This action revises the NPRM by 
revising the compliance times and adding a one-time inspection for 
airplanes that have been inspected too early. We are proposing this 
supplemental NPRM (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, which could result 
in damage to the airplane and injury to the occupants. Since these 
actions impose an additional burden over that proposed in the NPRM, 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 April 21, 2014.

ADDRESSES: You may send comments using the procedures found in 14 CFR 
11.43 and 11.45, 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 Airbus service information identified in this proposed 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. For Messier-Dowty service information identified 
in this proposed 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 http://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; 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 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued an NPRM to amend 14 CFR part 39 by adding an AD that 
would apply to certain Airbus Model A330-200 and -300 series airplanes; 
and Model A340-200 and -300 series airplanes. The NPRM was published in 
the Federal Register on September 25, 2013 (78 FR 58978). The NPRM 
proposed to supersede AD 2009-15-17, Amendment 39-15980 (74 FR 37523, 
July 29, 2009), to require actions intended to address the unsafe 
condition for the specified products.

Actions Since Previous NPRM Was Issued

    Since we issued the NPRM (78 FR 58978, September 25, 2013), we have 
received reports that some airplanes were initially inspected too early 
(before 4.5 years since the airplane's first flight with a bogie beam 
installed or since the bogie was installed after overhaul) and have not 
been re-inspected. The European Aviation Safety Agency (EASA), which is 
the Technical Agent for the Member States of the European Community, 
has issued EASA Airworthiness Directive 2013-0267, dated November 6, 
2013 (referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for the 
specified products. 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 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 [for damage to protective 
treatments or corrosion], which allows extension of the compliance 
time for the MLG bogie beam modification [for improved protection 
from corrosion] from 15 years to 21 years.

[[Page 12416]]

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 4.5 years 
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.

    This proposed AD also provides optional methods of compliance for 
inspections for corrosion and damage to the protective treatment, 
repairs, and modification, of both MLG bogie beams. You may examine the 
MCAI in the AD docket on the Internet at http://regulations.gov by 
searching and locating it in Docket No. FAA-2013-0828.

Relevant Service Information

    Airbus has issued the following service bulletins. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI.
     Airbus Mandatory Service Bulletin A330-32-3225, Revision 
02, dated October 26, 2012.
     Airbus Mandatory Service Bulletin A330-32-3237 (for Model 
A330 series airplanes), Revision 01, dated October 14, 2011.
     Airbus Mandatory Service Bulletin A340-32-4268, Revision 
03, dated January 14, 2013.
     Airbus Mandatory Service Bulletin A340-32-4279 (for Model 
A340 series airplanes), Revision 01, dated October 14, 2011.
    Messier Dowty has issued the following service bulletins. The 
actions described in this service information are intended to correct 
the unsafe condition identified in the MCAI.
     Messier Dowty Service Bulletin A33/34-32-271, Revision 1, 
dated November 16, 2007.
     Messier-Dowty Service Bulletin A33/34-32-278, including 
Appendices A and B, Revision 1, dated August 24, 2011.
     Messier-Dowty Service Bulletin A33/34-32-283, including 
Appendix A, Revision 1, dated July 10, 2012.
     Messier-Dowty Service Bulletin A33/34-32-284, including 
Appendix A, Revision 1, dated July 10, 2012.

Comments

    We gave the public the opportunity to comment on the NPRM (78 FR 
58978, September 25, 2013). The following presents the comments 
received on the NPRM and the FAA's response to each comment.

Request To Replace Modification 58896 With Modification 54500

    Delta Air Lines Inc. and US Airways requested that paragraph (h) of 
the NPRM (78 FR 58978, September 25, 2013) be changed to replace 
Modification 58896 with Modification 54500. The commenters stated that 
paragraph (h) of the NPRM specifies doing repetitive inspections on 
airplanes having all serial numbers, except airplanes on which 
Modification 58896 has been embodied in production; however, paragraph 
(g) of the NPRM and AD 2009-15-17, Amendment 39-15980 (74 FR 37523, 
July 29, 2009) are not applicable to airplanes with Modification 54500 
embodied in production.
    We agree with the commenters for the reasons provided. We have 
revised the affected airplanes specified in paragraph (g) of this SNPRM 
(paragraph (h) of the NPRM (78 FR 58978, September 25, 2013)). 
Paragraph (g) of this SNPRM affects airplanes and MLGs having one of 
the configurations specified below:
     Airbus Modification 54500 not embodied in production.
     Airbus Service Bulletin A330-32-3212; or A340-32-4256 not 
embodied in service.
     Airbus Service Bulletin A330-32-3222; or A340-32-4265 
embodied in service.

Request To Require Reporting Requirements Only For Positive Findings

    Delta Air Lines Inc. (Delta) requested that reporting be mandated 
only for positive findings, specifically for the findings beyond the 
applicable component maintenance manual repair limits.
    We disagree with the request to report only positive findings. All 
findings (positive and negative) must be reported to provide the 
manufacturer with information regarding the extent of the problem in 
the affected fleet, and to help determine whether a design change of 
the affected airplane part is needed. No change has been made to this 
SNPRM in this regard.

Request To Extend the Compliance Time for Reporting Requirements

    Delta requested that we extend the compliance time for reporting 
from 90 days to 180 days to allow findings to be batched together for a 
grouped report, and to preclude undue compliance issues related to late 
reporting.
    We do not agree with the request to extend the compliance time for 
reporting. Prompt reporting will ensure the timely update of the 
operator's maintenance documentation. However, under the provisions of 
paragraph (q) of this SNPRM, we will consider requests for approval of 
an extension of the compliance time if sufficient data are submitted to 
substantiate that the new compliance time would provide an acceptable 
level of safety. No change has been made to this SNPRM in this regard.

Request To Allow Use of Reporting Sheet in Messier-Dowty Service 
Bulletin A33/34-32-278, dated February 17, 2010

    Delta stated that the NPRM (78 FR 58978, September 25, 2013) 
specifies using the reporting sheet in Airbus Service Bulletin A330-32-
3237, dated January 18, 2011; however, this service bulletin does not 
have a reporting sheet included. Delta requested that we allow the use 
of the reporting sheet included in Messier-Dowty Service Bulletin A33/
34-32-278, dated February 17, 2010 instead.
    We disagree with the request. Airbus Service Bulletin A330-32-3237, 
Revision 01, dated October 14, 2011, includes a reporting sheet that is 
required by this AD. No change has been made to this SNPRM in this 
regard.

Other Changes to This SNPRM

    We have revised the affected airplanes for paragraph (k) of this 
SNPRM (paragraph (i) in the NPRM (78 FR 58978, September 25, 2013)). 
All airplanes are affected by the actions specified by paragraph (k) of 
this SNPRM.

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 the same 
type design.
    Certain changes described above expand the scope of the NPRM (78 FR 
58978, September 25, 2013). 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.

[[Page 12417]]

Differences Between This SNPRM and the MCAI or Service Information

    This SNPRM differs from the MCAI and/or service information as 
follows: 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 those actions. Paragraph (j)(2) of this SNPRM 
specifies 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. In addition, we refer to 
Messier-Dowty Service Bulletin A33/34-32-272, Revision 1, including 
Appendices A, B, C, and D, dated September 22, 2008, in paragraph 
(j)(1) of this AD for applying the protective treatments. This has been 
coordinated with Airbus.

Costs of Compliance

    We estimate that this SNPRM affects 51 airplanes of U.S. registry.
    We also estimate that it would take up to 34 work-hours per product 
to comply with the basic requirements of this SNPRM. The average labor 
rate is $85 per work-hour. Required parts would cost about $2,890 per 
product. Based on these figures, we estimate the cost of this SNPRM on 
U.S. operators to be $147,390, or $2,890 per product.
    In addition, we estimate that the optional modification would take 
about 10 work-hours and require parts costing $0, for a cost of $850 
per product. We have no way of determining the number of aircraft that 
might need the corrective action.

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 AD is 2120-
0056. The paperwork cost associated with this 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 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.

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. Amend 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 April 21, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and 
-313 airplanes; certificated in any category; all manufacturer 
serial numbers, except those airplanes on which Airbus Modification 
58896 has been embodied in production.

(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. 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, which 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 and MLGs having one of the configurations 
specified in paragraphs (g)(1), (g)(2), or (g)(3) of this AD: 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 do a detailed 
inspection for corrosion and damage to the protective treatments, 
and measure the paint thickness on the internal bore of the internal 
surfaces of the LH and RH MLG bogie beams, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-32-3225, 
Revision 02, dated October 26, 2012; or Airbus Service Bulletin 
A340-32-4268, Revision 03, dated January 14, 2013; as

[[Page 12418]]

applicable. Repeat the inspections thereafter at intervals of no 
less than 54 months, but no more than 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 bogie beam, as required by this paragraph, is 
between 54 months and 72 months after that overhaul.
    (1) Airbus Modification 54500 not embodied in production.
    (2) Airbus Service Bulletin A330-32-3212; or A340-32-4256 not 
embodied in service.
    (3) Airbus Service Bulletin A330-32-3222; or A340-32-4265 
embodied in service.

(h) 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, 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 its first flight after its last 
overhaul, as applicable.

(i) One-Time Specific Inspection for Certain Airplane Configurations

    For airplanes on which the modification specified in paragraph 
(k) or (m)(2) of this AD, or the inspection specified in paragraph 
(m)(1) of this AD, has not been done as of the effective date of 
this AD, and on which a LH or RH MLG bogie beam has been inspected 
earlier than 4.5 years since first flight of the affected MLG bogie 
beam, or since the bogie beam's first flight after the bogie beam's 
last overhaul, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A330-32-3225 or A340-32-4268: At the 
applicable time specified in paragraph (i)(1), (i)(2), or (i)(3) of 
this AD, clean the internal bore and do a detailed inspection of 
internal surfaces of the LH and RH MLG bogie beams to detect 
corrosion, damage to the protective treatments, and to measure the 
paint thickness on the internal bore, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-32-3225, 
Revision 02, dated October 26, 2012; or Airbus Service Bulletin 
A340-32-4268, Revision 03, dated January 14, 2013; as applicable.
    (1) For MLG bogie beams having the configurations specified in 
both paragraphs (i)(1)(i) and (i)(1)(ii) of this AD: Do the one-time 
specific inspection specified in paragraph (i) of this AD within 9 
months after the effective date of this AD.
    (i) MLG bogie beams having between 4.5 years and 10 years since 
first flight on an airplane, or since first flight on an airplane 
since overhaul.
    (ii) MLG bogie beam on which the first inspection was done after 
4 years and 3 months and before 4 years and 6 months since first 
flight of the MLG bogie beam, or since the bogie beam's first flight 
after last overhaul, as applicable.
    (2) For MLG bogie beams having the configurations specified in 
both paragraphs (i)(2)(i) and (i)(2)(ii) of this AD: Do the one-time 
specific inspection specified in paragraph (i) of this AD within 3 
months after the effective date of this AD.
    (i) MLG bogie beams having between 4.5 and 10 years since first 
flight on an airplane, or since first flight on an airplane since 
overhaul.
    (ii) MLG bogie beams on which the first inspection was done 
after 3 years and 9 months and before 4 years and 3 months inclusive 
since first flight of the MLG bogie beam, or since the bogie beam's 
first flight after the bogie beam's last overhaul, as applicable.
    (3) For bogie beams having the configurations specified in both 
paragraphs (i)(3)(i) and (i)(3)(ii) of this AD: Do the one-time 
specific inspection specified in paragraph (i) of this AD within 3 
months after the effective date of this AD.
    (i) Bogie beams having between 4.5 and 8 years since first 
flight on an airplane or since first flight on an airplane since 
overhaul.
    (ii) Bogie beams on which the first inspection was done before 4 
years and 3 months since first flight of the MLG bogie beam, or 
since the bogie beam's first flight after the bogie beam's last 
overhaul.
    (4) For bogie beams having the configurations specified in both 
paragraphs (i)(4)(i) and (i)(4)(ii) of this AD: Do the one-time 
specific inspection specified in paragraph (i) of this AD within 1 
month after the effective date of this AD.
    (i) Bogie beams having between 8 and 10 years since first flight 
on an airplane, or since first flight on an airplane since overhaul.
    (ii) Bogie beams on which the first inspection was done before 3 
years and 9 months since first flight of the MLG bogie beam, or 
since the bogie beam's first flight after the bogie beam's last 
overhaul, and the bogie beam has accumulated more than 8 years as of 
the effective date of this AD.
    (5) After accomplishment of the one-time specific inspection 
specified in paragraph (i) of this AD, repeat the actions specified 
in paragraph (g) of this AD at the times specified in paragraph (g) 
of this AD.

(j) Corrective Actions

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

(k) Inspection and Corrective Actions for All Airplanes

    For all airplanes: Before the accumulation of 252 months on a 
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) 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 01, 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 01, both dated October 14, 2011, as 
applicable.
    (2) 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 01, 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 is 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 Terminating Action

    Modification of both MLG bogie beams 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 that modified MLG bogie beam.

(m) Optional Methods of Compliance

    (1) Inspections for corrosion and damage to the protective 
treatment of both bogie beams, and repairs, done in accordance with 
Messier-Dowty Service Bulletin A33/34-32-278, including appendices A 
and B, Revision 1, dated August 24, 2011, are acceptable methods of 
compliance with the requirements of paragraph (k)(1) of this AD.
    (2) Modification of both 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 
requirements of paragraph (k)(2) of this AD.

(n) Parts Installation Limitations

    (1) After modification of an airplane as required by paragraph 
(k) of this AD, or as specified in paragraphs (m)(1) and (m)(2) of 
this AD, do not install a MLG bogie beam unless it is in compliance 
with the requirements of paragraph (n)(1)(i), (n)(1)(ii), or 
(n)(1)(iii) of this AD.
    (i) That 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 01, 
both dated October 14, 2011, as applicable.
    (ii) That MLG bogie beam has been inspected and corrected in 
accordance with the Accomplishment Instructions of Messier-

[[Page 12419]]

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) That 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 (n)(1) of this AD, installation of a MLG bogie beam on an 
airplane is allowed, provided that following the installation it is 
inspected and corrected in accordance with the requirements of this 
AD.

(o) Reporting Requirement

    (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 Service Bulletin A330-32-3237; or A340-32-
4279; both dated January 18, 2011, at the applicable time specified 
in paragraph (o)(1)(i) or (o)(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 (i) 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 
(o)(2)(i) or (o)(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.

(p) Credit for Previous Actions

    (1) This paragraph provides credit for the corresponding 
inspections and corrective actions done on a 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 01, dated October 30, 2008; 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 its last 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 01, 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 a 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 01, dated October 30, 2008; or Revision 02, 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 its last overhaul, as applicable. Airbus Mandatory 
Service Bulletin A340-32-4268, dated November 21, 2007; and Revision 
02, dated October 26, 2012; are not incorporated by reference in 
this AD. Airbus Mandatory Service Bulletin A340-32-4268, Revision 
01, 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 (h) 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 (h) and (j) 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 Appendices 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), (n)(1)(i), and (o) 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), (n)(1)(i), and (o) 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), (m)(2), (n)(1)(ii), and (n)(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), (m)(2), (n)(1)(ii), and (n)(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 (m)(1) and (n)(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 Appendices A 
and B, dated February 17, 2010, which is not incorporated by 
reference in this AD.

(q) 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: 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. 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer, use these actions if they 
are FAA-approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or by the Design Approval Holder with a State of 
Design Authority's design organization approval). For a repair 
method to be approved, the repair approval must specifically refer 
to this AD. You are required to ensure the product is airworthy 
before it is returned to service.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a 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 OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are 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.

(r) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA

[[Page 12420]]

Airworthiness Directive 2013-0267, dated November 6, 2013, for 
related information. You may examine the MCAI in the AD docket on 
the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-
2013&-0828-0001.
    (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 airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com. 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. 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 February 19, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-04892 Filed 3-4-14; 8:45 am]
BILLING CODE 4910-13-P


