[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: [email protected]; 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:
[email protected], 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: [email protected].
(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: [email protected];
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