
[Federal Register Volume 81, Number 40 (Tuesday, March 1, 2016)]
[Proposed Rules]
[Pages 10540-10544]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-04290]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-3984; Directorate Identifier 2014-NM-119-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2013-10-
03, for all Airbus Model A330-200, -200 Freighter, and -300 series 
airplanes; and Model A340-200, -300, -500, and -600 series airplanes. 
AD 2013-10-03 currently requires one-time inspections for deformation 
and damage of the bogie beams of the main landing gear (MLG); 
repetitive inspections for damage and corrosion of the sliding piston 
sub-assembly on certain airplanes; and related investigative and 
corrective actions if necessary. Since we issued AD 2013-10-03, we have 
determined that certain one-time inspections are no longer necessary, 
certain compliance times may be extended, and an optional terminating 
action should be provided. This proposed AD would remove Model A340-
500, and -600 series airplanes from the applicability, remove certain 
one-time inspections of the MLG bogie beams and the sliding piston sub-
assembly; revise certain compliance times and provide, for certain 
airplanes, an optional terminating action for the repetitive actions. 
We are proposing this AD to detect and correct damage or corrosion 
under the bogie stop pad of both MLG bogie beams, which could result in 
a damaged bogie beam and consequent detachment of the beam from the 
airplane, or collapse of the MLG and departure of the airplane from the 
runway.

DATES: We must receive comments on this proposed AD by April 15, 2016.

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 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: airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
3984; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: 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-2016-3984; 
Directorate Identifier 2014-NM-119-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On May 13, 2013, we issued AD 2013-10-03, Amendment 39-17456 (78 FR 
31386, May 24, 2013). AD 2013-10-03 requires actions intended to 
address an unsafe condition on all Airbus Model A330-200, -200 
Freighter, and -300 series airplanes; and Model A340-200, -300, -500, 
and -600 series airplanes. (AD 2013-10-03 superseded AD 2010-02-10, 
Amendment 39-16181 (75 FR 4477, January 28, 2010)).
    Since we issued AD 2013-10-03, Amendment 39-17456 (78 FR 31386, May 
24, 2013), we have determined that certain one-time inspections are no 
longer necessary, certain compliance times may be extended, and an 
optional terminating action should be provided.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2014-0120R1, dated August 31, 2015 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus Model A330-200, -200 
Freighter, and -300 series airplanes; and Model A340-200, -300, -500, 
and -600 series airplanes. The MCAI states:

    During a scheduled maintenance inspection on the Main Landing 
Gear (MLG), the bogie stop pad was found deformed and cracked. Upon 
removal of the bogie stop pad for replacement, the bogie beam was 
also found cracked.
    The results of a laboratory investigation indicated that an 
overload event had occurred and no fatigue propagation of the crack 
was evident.
    A second bogie beam crack was subsequently found on another 
aeroplane, located under a bogie stop pad which only had superficial 
paint damage.
    This condition, if not detected and corrected, could lead to 
landing gear bogie detachment from the aeroplane, or landing gear 
collapse, or a runway excursion,

[[Page 10541]]

possibly resulting in damage to the aeroplane and injury to the 
occupants.
    To address this potential unsafe condition, EASA issued * * * 
[an earlier AD] to require accomplishment of a one-time detailed 
inspection under the bogie stop pad of both MLG bogie beams.
    As a result of the one-time inspection required by that [earlier 
EASA] AD, applicable to A330, A340-200 and A340-300 aeroplanes, 
numerous bogie stop pad were found corroded and a few cracked.
    The one-time inspection was retained in EASA AD 2011-0211 
[http://ad.easa.europa.eu/blob/easa_ad_2011_0211_superseded.pdf/AD_2011-0211_1] [which corresponds to FAA AD 2013-10-03, Amendment 
39-17456 (78 FR 31386, May 24, 2013)], which superseded * * * [an 
earlier EASA AD], applicable to all A330 and A340 aeroplanes, which 
also introduced repetitive inspections for A330, A340-200 and A340-
300 aeroplanes, but not for the A340-500/-600 aeroplanes.
    Since issuance of EASA AD 2011-0211, further investigation 
accomplished by Airbus led to the conclusion that the one-time 
inspection in accordance with Airbus Service Bulletin (SB) A330-32-
3220, or Airbus SB A340-32-4264, or Airbus SB A340-32-5087, as 
applicable, is no longer necessary and, for those aeroplanes, only 
the inspections (initial and repetitive) in accordance with Airbus 
SB A330-32-3248 or Airbus SB A340-32-4286, as applicable, must 
remain.
    In addition, Airbus also determined that repetitive inspections 
of the MLG in accordance with Airbus SB A340-32-5112 are necessary 
for A340-500/-600 aeroplanes.
    Consequently, EASA issued * * * [another AD], which partially 
retained the requirements of EASA AD 2011-0211, which was 
superseded, and introduced repetitive detailed inspections of the 
MLG for A340-500 and A340-600 aeroplanes.
    Since that [EASA] AD was issued, it was determined that 
repetitive inspections of the MLG are not necessary on the A340-500/
-600 aeroplanes and that the threshold for the inspection of MLG P/N 
10-210 series can be delayed. In addition, Airbus developed a mod of 
the MLG P/N 10-210 series that can be embodied both in production 
through mod 204421 and in service with Airbus SB A330-32-3268 or SB 
A340-32-4300, as applicable. This modification constitutes a 
terminating action for the repetitive inspections for aeroplanes 
equipped with MLG P/N 10-210 series.
    For the reasons described above, this [EASA] AD is revised and 
requires inspection of the MLG (with an amended threshold for MLG P/
N 10-210 series) and introduces an option to terminate the 
repetitive inspection with a modification of the MLG P/N 10-210 
series.

    The required actions include repetitive detailed inspections for 
damage and corrosion of the sliding piston sub-assembly, and related 
investigative and corrective actions if necessary. Related 
investigative actions include a test for indications of corrosion and 
damage to the bogie assembly base material, and a magnetic particle 
inspection for cracks, corrosion, and damage of the bogie beam. 
Corrective actions include repairing affected parts.
    The optional terminating action modification of the bogie beam of 
an MLG having P/N 10-210 consists of installing a nickel under chrome 
coating, a new bogie beam stop pad, and new stop pad brackets.
    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-2016-
3984.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A330-32-3248, Revision 02, dated 
April 16, 2014. This service information describes procedures for doing 
a detailed inspection for damage and corrosion of the MLG sliding 
piston sub-assembly, bogie beam stop pad and the bogie beam under the 
stop pad; and related investigative and corrective actions.
    Airbus has also issued Service Bulletin A330-32-3268 and Airbus 
Service Bulletin A340-32-4300, both dated April 20, 2015. This service 
information describes procedures for modification of the bogie beam of 
an MLG having P/N 10-210, which includes installing a nickel under 
chrome coating, a new bogie beam stop pad, and new stop pad brackets.
    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.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which procedures and tests in the service information are 
required for compliance with an AD. Differentiating these procedures 
and tests from other tasks in the service information is expected to 
improve an owner's/operator's understanding of crucial AD requirements 
and help provide consistent judgment in AD compliance. The procedures 
and tests identified as Required for Compliance (RC) in any service 
information have a direct effect on detecting, preventing, resolving, 
or eliminating an identified unsafe condition.
    As specified in a Note under the Accomplishment Instructions of the 
specified service information, procedures and tests that are identified 
as RC in any service information must be done to comply with the 
proposed AD. However, procedures and tests that are not identified as 
RC are recommended. Those procedures and tests that are not identified 
as RC may be deviated from using accepted methods in accordance with 
the operator's maintenance or inspection program without obtaining 
approval of an alternative method of compliance (AMOC), provided the 
procedures and tests identified as RC can be done and the airplane can 
be put back in an airworthy condition. Any substitutions or changes to 
procedures or tests identified as RC will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 89 Model A330-200, -200 
Freighter, and -300 series airplanes of U.S. registry.
    We estimate that it would take about 12 work-hours per product to 
comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $90,780, or $1,020 
per product.
    Currently, there are no affected Model A340-200, or -300, series 
airplanes on the U.S. Register. However, if an affected airplane is 
imported and placed on the U.S. Register in the future, it would be 
subject to the same per-airplane cost specified above for the Model 
A330-200, -200 Freighter, and -300 series airplanes.
    In addition, we estimate that any necessary follow-on actions would 
take about 24 work-hours, and 1 work-hour for reporting, and require 
parts costing $78, for a cost of $2,203 per product. We have no way of 
determining the number of aircraft that might need these actions.
    According to the manufacturer, all of the parts costs of the 
optional

[[Page 10542]]

terminating action specified in this proposed AD may be covered under 
warranty, thereby reducing the cost impact on affected individuals. We 
do not control warranty coverage for affected individuals. We have 
received no definitive data that would enable us to provide the work-
hour cost estimates for the optional terminating action specified in 
this proposed AD.

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. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2013-10-03, Amendment 39-17456 (78 FR 31386, May 24, 2013), and adding 
the following new AD:

Airbus: Docket No. FAA-2016-3984; Directorate Identifier 2014-NM-
119-AD.

(a) Comments Due Date

    We must receive comments by April 15, 2016.

(b) Affected ADs

    This AD replaces AD 2013-10-03, Amendment 39-17456 (78 FR 31386, 
May 24, 2013).

(c) Applicability

    This AD applies to Airbus airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD, certificated in any category; all 
serial numbers, except those that have embodied Airbus Modification 
204421 in production.
    (1) Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, 
-302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Model A340-211, -212, -213, -311, -312, -313 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of corroded and cracked bogie 
beams under the bogie stop pad. We are issuing this AD to detect and 
correct damage or corrosion under the bogie stop pad of both main 
landing gear (MLG) bogie beams, which could result in a damaged 
bogie beam and consequent detachment of the beam from the airplane, 
or collapse of the MLG and departure of the airplane from the 
runway.

(f) Compliance

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

(g) Repetitive Inspections, Related Investigative Actions, and 
Corrective Actions

    For Model A330-200, Model A330-200 Freighter, and Model A330-300 
series airplanes; and Model A340-200, and -300 series airplanes; 
equipped with a MLG having part number (P/N) 201252 series, or P/N 
201490 series, or P/N 10-210 series: Do the applicable actions 
required by paragraph (g)(1) or (g)(2) of this AD.
    (1) For airplanes equipped, as of the effective date of this AD, 
with a MLG that has been previously inspected as specified in Airbus 
Service Bulletin A330-32-3220, Airbus Service Bulletin A330-32-3248, 
Airbus Service Bulletin A340-32-4264, or Airbus Service Bulletin 
A340-32-4286, as applicable: At applicable times specified in 
paragraphs (h)(1) and (h)(2) of this AD, do a detailed inspection 
for damage (e.g., cracking and fretting) and corrosion of the MLG 
sliding piston subassembly, bogie beam stop pad, and the bogie beam 
under the stop pad; and do all applicable related investigative and 
corrective actions; in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-32-3248, Revision 02, 
dated April 16, 2014; or Airbus Service Bulletin A340-32-4286, dated 
October 5, 2011; as applicable, except as required by paragraph (j) 
of this AD. Do all applicable related investigative and corrective 
actions before further flight. Repeat the inspection of the MLG 
sliding piston sub-assembly, bogie beam stop pad, and the bogie beam 
under the stop pad, thereafter, at intervals not to exceed 2,500 
flight cycles or 24 months, whichever occurs first.
    (2) For airplanes equipped, as of the effective date of this AD, 
with a MLG that has not been previously inspected as specified in 
Airbus Service Bulletin A330-32-3220, Airbus Service Bulletin A330-
32-3248, Airbus Service Bulletin A340-32-4264, or Airbus Service 
Bulletin, A340-32-4286, as applicable: At the applicable times 
specified in paragraphs (h)(3) and (h)(4) of this AD, do a detailed 
inspection for damage (e.g., cracking and fretting) and corrosion of 
the MLG sliding piston sub-assembly, bogie beam stop pad, and the 
bogie beam under the stop pad; and do all applicable related 
investigative and corrective actions; in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-32-3248, 
Revision 02, dated April 16, 2014; or Airbus Service Bulletin A340-
32-4286, dated October 5, 2011; as applicable, except

[[Page 10543]]

as required by paragraph (j) of this AD. Do all applicable related 
investigative and corrective actions before further flight. Repeat 
the inspection of the MLG sliding piston sub-assembly, bogie beam 
stop pad, and the bogie beam under the stop pad, thereafter, at 
intervals not to exceed 2,500 flight cycles or 24 months, whichever 
occurs first.

(h) Compliance Times for Paragraph (g) of This AD Actions

    Do the applicable actions required by paragraph (g) of this AD 
at the applicable time specified in paragraph (h)(1), (h)(2), 
(h)(3), or (h)(4) of this AD.
    (1) For airplanes identified in paragraph (g)(1) of this AD 
having an MLG P/N 201252 series and P/N 201490 series: Before the 
accumulation of 2,500 total flight cycles or 24 months, whichever 
occurs first since the later of the times specified in paragraphs 
(h)(1)(i) and (h)(1)(ii) of this AD.
    (i) Since first flight after a MLG overhaul.
    (ii) Since first flight after the most recent accomplishment of 
an inspection of the MLG as specified in Airbus Service Bulletin 
A330-32-3220; Airbus Service Bulletin A330-32-3248; Airbus Service 
Bulletin A340-32-4286; or Airbus Service Bulletin A340-32-4264; as 
applicable.
    (2) For airplanes identified in paragraph (g)(1) of this AD 
having an MLG P/N 10-210 series: Before the accumulation of 126 
months since first flight of the MLG on an airplane or since first 
flight on an airplane after the most recent inspection of the MLG as 
specified in Airbus Service Bulletin A330-32-3248, Revision 01, 
dated December 13, 2012; or Airbus Service Bulletin A330-32-3248, 
Revision 02, dated April 16, 2014; or Airbus Service Bulletin A340-
32-4286, dated October 5, 2011; as applicable.
    (3) For airplanes identified in paragraph (g)(2) of this AD 
having an MLG P/N 201252 series and P/N 201490 series: At the later 
of the times specified in paragraphs (h)(3)(i) and (h)(3)(ii) of 
this AD.
    (i) Before the accumulation of 2,500 total flight cycles or 24 
months, whichever occurs first since the later of the times 
specified in paragraphs (h)(3)(i)(A) and (h)(3)(i)(B) of this AD.
    (A) Since first flight of the MLG on an airplane.
    (B) Since first flight after a MLG overhaul.
    (ii) Within 16 months after the effective date of this AD.
    (4) For airplanes identified in paragraph (g)(2) of this AD 
having MLG P/N 10-210 series: Before the accumulation of 126 months 
since first flight of the MLG on an airplane.

(i) Optional Overhaul

    For the purposes of this AD, accomplishment of an MLG overhaul 
is acceptable instead of an inspection required by paragraph (g) of 
this AD. The inspections required by paragraph (g) of this AD are 
not terminated by an MLG overhaul, but are required at the next 
applicable compliance time required by paragraph (g) of this AD.

(j) Service Information Exception

    If the applicable service information specified in paragraph (g) 
of this AD specifies to contact Messier-Dowty for instructions, or 
if any repair required by paragraph (g) of this AD is beyond the 
maximum repair allowance specified in the applicable service 
information specified in paragraph (g) of this AD: Before further 
flight, repair 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).

(k) Reporting Requirement

    After accomplishing any of the corrective actions required by 
paragraph (g) of this AD or any repair required by paragraph (j) of 
this AD: Report the results of the corrective actions or repair to 
Airbus, Customer Services Directorate, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex France; Attn: SDC32 Technical Data and 
Documentation Services; fax: +33 5 61 93 28 06; email: 
sb.reporting@airbus.com, at the applicable time specified in 
paragraph (k)(1) or (k)(2) of this AD.
    (1) If the corrective action or repair was done on or after the 
effective date of this AD: Submit the report within 90 days after 
doing corrective action or repair.
    (2) If the corrective action or repair was done prior to the 
effective date of this AD: Submit the report within 90 days after 
the effective date of this AD.

(l) Terminating Action Limitation

    Accomplishment of corrective actions as required by paragraph 
(g) of this AD does not constitute terminating action for the 
repetitive inspections required by this AD.

(m) Optional Terminating Action for Certain Airplanes

    For airplanes with any MLG having P/N 10-210 series: 
Modification on an airplane of the bogie beam of each MLG having P/N 
10-210 series as specified in the Accomplishment Instructions of 
Airbus Service Bulletin A330-32-3268, dated April 20, 2015; or 
Airbus Service Bulletin A340-32-4300, dated April 20, 2015; as 
applicable; constitutes terminating action for the requirements of 
this AD for that airplane, provided that, following in-service 
modification, the airplane remains in post-service bulletin 
configuration.

(n) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using the service information identified 
in paragraph (n)(1), (n)(2), or (n)(3), (n)(4), or (n)(5) of this 
AD.
    (1) Airbus Service Bulletin A330-32-3248, dated October 5, 2011, 
which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A330-32-3248, Revision 01, including 
Appendix 01, dated December 13, 2012, which was incorporated by 
reference in AD 2013-10-03, Amendment 39-17456 (78 FR 31386, May 24, 
2013).
    (3) Airbus Service Bulletin A330-32-3220, dated October 10, 
2008, which was incorporated by reference in AD 2010-02-10, 
Amendment 39-16181 (75 FR 4477, January 28, 2010).
    (4) Airbus Service Bulletin A330-32-3220, Revision 01, dated 
October 5, 2011, which was incorporated by reference in AD 2013-10-
03, Amendment 39-17456 (78 FR 31386, May 24, 2013).
    (5) Airbus Service Bulletin A330-32-3220, Revision 02, dated 
December 13, 2012, which was incorporated by reference in AD 2013-
10-03, Amendment 39-17456 (78 FR 31386, May 24, 2013).

(o) 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.
    (i) 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.
    (ii) AMOCs approved previously for AD 2013-10-03, Amendment 39-
17456 (78 FR 31386, May 24, 2013), are not approved as AMOCs with 
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 EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (j) of this AD: If any service information contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures or tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without obtaining approval of an AMOC, provided 
the procedures and tests identified as RC can be done and the 
airplane can be put back in an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.
    (4) 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

[[Page 10544]]

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.

(p) Special Flight Permits

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed if any crack is found during any 
inspection required by this AD.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2014-0120R1, dated August 31, 2015, 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-2016-3984.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; 
fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com. You may view this service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on February 19, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-04290 Filed 2-29-16; 8:45 am]
 BILLING CODE 4910-13-P


