[Federal Register Volume 81, Number 109 (Tuesday, June 7, 2016)]
[Rules and Regulations]
[Pages 36443-36447]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-12056]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-7533; Directorate Identifier 2015-NM-080-AD; 
Amendment 39-18528; AD 2016-11-01]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A330-200 and -300 series airplanes, Model A330-200 
Freighter series airplanes, and Model A340-541 and A340-642 airplanes. 
This AD was prompted by a report of an under-torqued forward engine 
mount bolt. This AD requires a one-time torque check of the forward and 
aft engine mount bolts and corrective actions if necessary. We are 
issuing this AD to detect and correct improperly torqued engine mount 
bolts, which could lead to detachment of the engine from the airplane 
during flight and consequent damage to the airplane and injury to 
persons on the ground.

DATES: This AD is effective July 12, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of July 12, 
2016.

ADDRESSES: For service information identified in this final rule, 
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.[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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
7533.

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-2015-
7533; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (telephone 
800-647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus Model A330-
200 and -300 series airplanes, Model A330-200 Freighter series 
airplanes, and Model A340-541 and A340-642 airplanes. The NPRM 
published in the Federal Register on December 29, 2015 (80 FR 81216) 
(``the NPRM''). The NPRM was prompted by a report of an under-torqued 
forward engine mount bolt. The NPRM proposed to require a one-time 
torque check of the forward and aft engine mount bolts, and corrective 
actions if necessary. We are issuing this AD to detect and correct 
improperly torqued engine mount bolts, which could lead to detachment 
of the engine from the airplane during flight and consequent damage to 
the airplane and injury to persons on the ground.
    The European Aviation Safety Agency, which is the Technical Agent 
for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0082, dated May 11, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on certain Airbus Model 
A330-200 and -300 series airplanes, Model A330-200 Freighter series 
airplanes, and Model A340-541 and A340-642 airplanes. The MCAI states:

    In 2013, during a pre-delivery test on an A330 aeroplane fitted 
with Pratt & Whitney (PW) PW4170 engines, an issue with N1 [low 
pressure spool] vibrations level on [engine] ENG1 was identified. 
While performing an engine removal, one forward engine mount bolt 
was found improperly torqued. The investigation concluded this was 
due to a production line engine installation quality issue. Further 
analysis showed that some aeroplanes, delivered between June 2006 
and January 2014, may have had the rear (AFT) and forward (FWD) 
engine mount bolts improperly torqued.
    This condition, if not detected and corrected, could ultimately 
lead to an in-flight detachment of the engine from the aeroplane, 
possibly resulting in damage to the aeroplane and/or injury to 
persons on the ground.
    Prompted by these findings, Airbus issued four Alert Operators 
Transmissions (AOT) A71L004-14 (for A330 aeroplanes fitted PW 
engines), AOT A71L006-14 (for A330 aeroplanes fitted with General 
Electric (GE) engines), AOT A71L005-14 (for A330 aeroplanes fitted 
with Rolls Royce (RR) Trent 700 engines) and AOT A71L008-14 (for 
A340 aeroplanes fitted with RR Trent 500 engines) to provide torque 
check instructions.
    For the reasons described above, this [EASA] AD requires a one-
time torque check of the FWD and AFT engine mount bolts and, 
depending on findings, re-torque of the affected [engine mount] 
bolt(s) and/or replacement of all four [engine mount] bolts and 
associated nuts.

    Findings (or discrepancies) include one engine mount bolt that is 
loose or able to rotate, two or more engine mount bolts that are loose 
or able to rotate, or one or more engine mount bolts that are fully 
broken. Corrective actions include re-torqueing the affected engine 
mount bolt(s), and replacing all engine mount bolts and associated nuts 
with new engine mount bolts and nuts on the engine where the loose or 
fully broken engine mount bolt(s) were detected. This AD specifies 
reporting of all findings (including no discrepancies). The corrective 
actions include re-torqueing loose engine mount bolts before further 
flight. 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-2015-7533.

[[Page 36444]]

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Changes to the NPRM

    Paragraphs (h)(1)(ii) and (i) of the proposed AD refer to the 
accomplishment of Airbus Service Bulletin A330-71-3028, Revision 01, 
dated February 20, 2012. However, operators might also accomplish 
Airbus Service Bulletin A330-71-3028, Revision 02, dated August 31, 
2015. Therefore, we have revised paragraphs (h)(1)(ii) and (i) of this 
AD to refer to the actions specified in ``Airbus Service Bulletin A330-
71-3028.''
    Paragraph (m)(1) of the proposed AD refers to Airbus AOT A71L008-
14, dated September 29, 2014, and is an exception to the service 
information specified in paragraph (l) of the proposed AD. However, 
paragraph (l) of the proposed AD refers to Airbus AOT A71L008-14, 
Revision 01, dated December 18, 2014. We have revised paragraph (m)(1) 
of this AD to refer to Airbus AOT A71L008-14, Revision 01, dated 
December 18, 2014.
    For consistency, we have also replaced the words ``bolt(s)'' and 
``pylon bolt(s)'' in this AD with ``engine mount bolt(s)'' in order to 
match the language in the MCAI. In the service information referenced 
in this AD, the term ``pylon'' is also used in some sentences to 
describe the engine mount bolts.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD with the changes described 
previously and except for minor editorial changes. We have determined 
that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We have reviewed the following service information.
     Airbus AOT A71L004-14, Revision 01, dated April 7, 2014. 
The service information describes procedures for doing a one-time 
torque check to determine if there are any loose or fully broken engine 
mount bolts at four positions at the forward engine pylon 1 and pylon 2 
of Airbus Model A330 series airplanes having PW engines, doing 
corrective actions, and reporting all findings.
     Airbus AOT A71L005-14, Revision 01, dated December 11, 
2014. The service information describes procedures for doing a one-time 
torque check to determine if there are any loose or fully broken engine 
mount bolts at four positions at the forward engine pylon 1 and pylon 2 
of Airbus Model A330 series airplanes having RR Trent 700 engines, 
doing corrective actions, and reporting all findings.
     Airbus AOT A71L006-14, dated July 22, 2014. The service 
information describes procedures for doing a one-time torque check to 
determine if there are any loose or fully broken engine mount bolts at 
five FWD and four AFT positions at the forward engine pylon 1 and pylon 
2 of Airbus Model A330 series airplanes having GE engines, doing 
corrective actions, and reporting all findings.
     Airbus AOT A71L008-14, Revision 01, dated December 18, 
2014. The service information describes procedures for doing a one-time 
torque check to determine if there are any loose or fully broken engine 
mount bolts at four positions at the forward engine pylon 1 and pylon 2 
of Airbus Model A340 series airplanes having Trent 500 engines, doing 
corrective actions, and reporting all findings.
    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.

Costs of Compliance

    We estimate that this AD affects 55 airplanes of U.S. registry.
    We also estimate that it will take about 12 work-hours per product 
to comply with the basic requirements of this AD, and 1 work-hour per 
product to report torque check findings. The average labor rate is $85 
per work-hour. Based on these figures, we estimate the cost of this AD 
on U.S. operators to be $60,755, or $1,105 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 20 work-hours and require parts costing $90,200 for a cost 
of $91,900 per product. We have no way of determining the number of 
aircraft that might need these actions.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid Office of Management and Budget 
(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 AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and

[[Page 36445]]

    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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2016-11-01 Airbus: Amendment 39-18528. Docket No. FAA-2015-7533; 
Directorate Identifier 2015-NM-080-AD.

(a) Effective Date

    This AD is effective July 12, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes specified in paragraphs 
(c)(1) through (c)(5) of this AD, certificated in any category, from 
manufacturer serial number (MSN) 0715 through MSN 1507 inclusive, 
and MSN 1509, except airplanes on which all engines have been 
removed and/or replaced since the date of the first flight of the 
airplane.
    (1) Airbus Model A330-201, -202, -203, -223, and -243 airplanes.
    (2) Airbus Model A330-223F and -243F airplanes.
    (3) Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -
342, and -343 airplanes.
    (4) Airbus Model A340-541 airplanes.
    (5) Airbus Model A340-642 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by a report of an under-torqued forward 
engine mount bolt. We are issuing this AD to detect and correct 
improperly torqued engine mount bolts, which could lead to 
detachment of the engine from the airplane during flight, and 
consequent damage to the airplane and injury to persons on the 
ground.

(f) Compliance

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

(g) Definition of Affected Engine

    For the purpose of this AD, an affected engine is an engine that 
has never been removed and/or replaced since first flight of the 
airplane.

(h) Action for Airbus Model A330 Airplanes Equipped With Pratt and 
Whitney (PW) Engines

    (1) For Airbus Model A330-200, -200 Freighter, and -300 series 
airplanes equipped with PW engines: At the earlier of the times 
specified in paragraph (h)(1)(i) and (h)(1)(ii) of this AD, 
accomplish a one-time torque check of the forward (FWD) and rear 
(AFT) engine mount bolts on each affected engine, at the locations 
specified in, and in accordance with the instructions of Section 
4.2.2, ``Inspection Requirements,'' of Airbus Alert Operators 
Transmission (AOT) A71L004-14, Revision 01, dated April 7, 2014.
    (i) Within 2,000 flight hours after the effective date of this 
AD.
    (ii) During the accomplishment of actions specified in Airbus 
Service Bulletin A330-71-3028, if done after the effective date of 
this AD.
    (2) If, during the torque check required by paragraph (h)(1) of 
this AD, only one FWD engine mount bolt is found that rotates: Do 
the actions specified in paragraph (h)(2)(i), (h)(2)(ii), 
(h)(2)(iii), or (h)(2)(iv) of this AD, as applicable.
    (i) For Airbus Model A330-200 and -300 series airplanes with an 
average flight time of greater than 132 minutes and having 
accumulated less than 2,350 flight cycles and less than 24,320 
flight hours since first flight of the airplane: Before further 
flight, re-torque the affected engine mount bolt, and, within 2,350 
flight cycles or 24,320 flight hours since first flight of the 
airplane, whichever occurs first, replace the 4 engine mount bolts 
and associated nuts, in accordance with the instructions of Section 
4.2.3, ``Findings,'' of Airbus AOT A71L004-14, Revision 01, dated 
April 7, 2014.
    (ii) For Airbus Model A330-200 and -300 series airplanes with an 
average flight time of 132 minutes or lower and having accumulated 
less than 1,950 flight cycles and less than 20,210 flight hours 
since first flight of the airplane: Before further flight, re-torque 
the affected engine mount bolt, and within 2,350 flight cycles or 
24,320 flight hours since first flight of the airplane, whichever 
occurs first, replace the 4 engine mount bolts and associated nuts, 
in accordance with the instructions of Section 4.2.3, ``Findings,'' 
of Airbus AOT A71L004-14, Revision 01, dated April 7, 2014.
    (iii) For Airbus Model A330-200 Freighter series airplanes 
having accumulated less than 2,140 flight cycles and less than 6,600 
flight hours since first flight of the airplane: Before further 
flight, re-torque the affected engine mount bolt and within 2,140 
flight cycles or 6,600 flight hours since first flight of the 
airplane, whichever occurs first, replace the 4 engine mount bolts 
and associated nuts, in accordance with the instructions of Section 
4.2.3, ``Findings,'' of Airbus AOT A71L004-14, Revision 01, dated 
April 7, 2014.
    (iv) For airplanes identified in paragraphs (h)(2)(iv)(A), 
(h)(2)(iv)(B), and (h)(2)(iv)(C) of this AD: Before further flight, 
replace the 4 engine mount bolts and associated nuts in accordance 
with the instructions of Section 4.2.3, ``Findings,'' of Airbus AOT 
A71L004-14, Revision 01, dated April 7, 2014.
    (A) Airbus Model A330-200 and -300 series airplanes with an 
average flight time of greater than 132 minutes and having 
accumulated 2,350 flight cycles or more or 24,320 flight hours or 
more since first flight of the airplane.
    (B) Airbus Model A330-200 and -300 series airplanes with an 
average flight time of 132 minutes or lower and having accumulated 
1,950 flight cycles or more or 20,210 flight hours or more since 
first flight of the airplane.
    (C) Airbus Model A330-200 Freighter series airplanes having 
accumulated 2,140 flight cycles or more or 6,600 flight hours or 
more since first flight of the airplane.
    (3) If, during the torque check required by paragraph (h)(1) of 
this AD, two or more FWD engine mount bolts are found that rotate: 
Before further flight, replace the 4 engine mount bolts and 
associated nuts in accordance with the instructions of Section 
4.2.3, ``Findings,'' of Airbus AOT A71L004-14, Revision 01, dated 
April 7, 2014.
    (4) If, during the torque check required by paragraph (h)(1) of 
this AD, one or more FWD engine mount bolts are found fully broken: 
Before further flight, replace the 4 engine mount bolts and 
associated nuts in accordance with the instructions of Section 
4.2.3, ``Findings,'' of Airbus AOT A71L004-14, Revision 01, dated 
April 7, 2014, except as required by paragraph (m)(2) of this AD.
    (5) If, during the torque check required by paragraph (h)(1) of 
this AD, only one AFT engine mount bolt is found that rotates: 
Before further flight, re-torque the affected engine mount bolt, and 
replace the 4 engine mount bolts and associated nuts at the next 
engine removal, in accordance with the instructions of Section 
4.2.3, ``Findings,'' of Airbus AOT A71L004-14, Revision 01, dated 
April 7, 2014.
    (6) If, during the torque check required by paragraph (h)(1) of 
this AD, two or more AFT engine mount bolts are found that rotate: 
Before further flight, replace the 4 engine mount bolts and 
associated nuts in accordance with the instructions of Section 
4.2.3, ``Findings,'' of Airbus AOT A71L004-14, Revision 01, dated 
April 7, 2014.
    (7) If, during the torque check required by paragraph (h)(1) of 
this AD, one or more AFT engine mount bolts are found fully broken: 
Before further flight, replace the 4 engine mount bolts and 
associated nuts in accordance with the instructions of Section 
4.2.3, ``Findings,'' of Airbus AOT A71L004-14, Revision 01, dated 
April 7, 2014, except as required by paragraph (m)(2) of this AD.

[[Page 36446]]

(i) Clarification of Concurrent Actions for Airbus Model A330-223F, 
A330-223, A330-321, A330-322, and A330-323 Airplanes Equipped With 
Pratt and Whitney (PW) Engines

    AD 2013-14-04, Amendment 39-17509 (78 FR 68352, November 14, 
2013), requires a torque check of FWD engine mount bolts using 
Airbus Service Bulletin A330-71-3028, Revision 01, dated February 
20, 2012. If accomplishing the torque check of FWD engine mount 
bolts, as specified in Airbus Service Bulletin A330-71-3028, within 
the compliance times specified in paragraph (g) of AD 2013-14-04, 
perform the torque check of the AFT engine mount bolts at the same 
time as required by paragraph (h)(1) of this AD.

(j) Action for Airbus Model A330 Airplanes Equipped With General 
Electric (GE) Engines

    (1) For Airbus Model A330-200, -200 Freighter, and -300 series 
airplanes equipped with GE engines: Within 2,000 flight hours after 
the effective date of this AD, accomplish a one-time torque check of 
the FWD and AFT engine mount bolts on each affected engine, at the 
locations specified in, and in accordance with the instructions of 
Section 4.2.2, ``Inspection Requirements,'' of Airbus AOT A71L006-
14, dated July 22, 2014.
    (2) If, during the torque check required by paragraph (j)(1) of 
this AD, only one FWD engine mount bolt is found that rotates: Do 
the actions specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this 
AD, as applicable.
    (i) For airplanes that have accumulated less than 4,000 flight 
cycles and less than 30,800 flight hours since first flight of the 
airplane: Before further flight, re-torque affected FWD engine mount 
bolt(s), in accordance with the instructions of Section 4.2.3, 
``Findings,'' of Airbus AOT A71L006-14, dated July 22, 2014, and, 
within 4,000 flight cycles or 30,800 flight hours since first flight 
of the airplane, whichever is first, replace the 5 engine mount 
bolts, as applicable, and their associated nuts with new engine 
mount bolts and nuts in accordance with the instructions of Section 
4.2.3, ``Findings,'' of Airbus AOT A71L006-14, dated July 22, 2014.
    (ii) For airplanes that have accumulated 4,000 flight cycles or 
more or 30,800 flight hours or more since first flight of the 
airplane: Before further flight, replace the 5 FWD engine mount 
bolts, as applicable, and their associated nuts with new engine 
mount bolts and nuts in accordance with the instructions of Section 
4.2.3, ``Findings,'' of Airbus AOT A71L006-14, dated July 22, 2014.
    (3) If, during the torque check required by paragraph (j)(1) of 
this AD, two or more FWD engine mount bolts are found that rotate: 
Repair before further flight using a method approved in accordance 
with the procedures specified in paragraph (p)(1) of this AD.
    (4) If, during the torque check required by paragraph (j)(1) of 
this AD, one or more FWD engine mount bolts are found fully broken: 
Repair before further flight using a method approved in accordance 
with the procedures specified in paragraph (p)(1) of this AD.
    (5) If, during the torque check required by paragraph (j)(1) of 
this AD, only one AFT engine mount bolt is found that rotates: 
Before further flight, re-torque the affected AFT engine mount 
bolt(s) in accordance with the instructions of Section 4.2.3, 
``Findings,'' of Airbus AOT A71L006-14, dated July 22, 2014, and, at 
the next engine removal, replace the 4 engine mount bolts and 
associated nuts with new engine mount bolts and nuts in accordance 
with the instructions of Section 4.2.3, ``Findings,'' of Airbus AOT 
A71L006-14, dated July 22, 2014.
    (6) If, during the torque check required by paragraph (j)(1) of 
this AD, two or more AFT engine mount bolts are found that rotate: 
Repair before further flight using a method approved in accordance 
with the procedures specified in paragraph (p)(1) of this AD.
    (7) If, during the torque check required by paragraph (j)(1) of 
this AD, one or more AFT engine mount bolts are found fully broken: 
Before further flight, do all applicable corrective actions in 
accordance with the instructions of Section 4.2.3, ``Findings,'' of 
Airbus AOT A71L006-14, dated July 22, 2014, except as required by 
paragraph (m)(2) of this AD.

(k) Action for Airbus Model A330 Airplanes Equipped With Rolls-Royce 
(RR) Trent 700 Engines

    (1) For Airbus Model A330-200, -200 Freighter, and -300 series 
airplanes equipped with RR Trent 700 Engines: Within 2,000 flight 
hours after the effective date of this AD, accomplish a one-time 
torque check of the FWD and AFT engine mount bolts on each affected 
engine, at the locations specified in, and in accordance with the 
instructions of Section 4.2.2, ``Inspection Requirements,'' of 
Airbus AOT A71L005-14, Revision 01, dated December 11, 2014.
    (2) If, during the torque check required by paragraph (k)(1) of 
this AD, any discrepancy is detected (one engine mount bolt rotates, 
two or more engine mount bolts rotate, or one or more engine mount 
bolts are fully broken): Within the compliance time specified in 
Airbus AOT A71L005-14, Revision 01, dated December 11, 2014, 
accomplish all applicable corrective actions in accordance with the 
instructions of Section 4.2.3, ``Findings,'' of Airbus AOT A71L005-
14, Revision 01, dated December 11, 2014, except as required by 
paragraphs (m)(1) and (m)(2) of this AD.

(l) Action for Airbus Model A340-541 and -642 Airplanes Equipped With 
RR Trent 500 Engines

    (1) For Airbus Model A340-541 and -642 airplanes equipped with 
RR Trent 500 Engines: Within 2,000 flight hours after the effective 
date of this AD, accomplish a one-time torque check of FWD and AFT 
engine mount bolts on each affected engine, at the locations 
specified in, and in accordance with the instructions of Section 
4.2.2, ``Inspection requirements,'' of Airbus AOT A71L008-14, 
Revision 01, dated December 18, 2014.
    (2) If, during the torque check required by paragraph (l)(1) of 
this AD, any discrepancy is detected (one engine mount bolt rotates, 
two or more engine mount bolts rotate, or one or more engine mount 
bolts are fully broken): Within the compliance time specified in 
Airbus AOT A71L008-14, Revision 01, dated December 18, 2014, 
accomplish all applicable corrective actions, in accordance with the 
instructions of Section 4.2.3, ``Findings,'' of Airbus AOT A71L008-
14, Revision 01, dated December 18, 2014, except as required by 
paragraphs (m)(1) and (m)(2) of this AD.

(m) Service Information Exceptions

    (1) Where Airbus AOTs A71L005-14, Revision 01, dated December 
11, 2014; A71L006-14, dated July 22, 2014; and A71L008-14, Revision 
01, dated December 18, 2014; specify to contact Airbus for further 
actions, 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).
    (2) Where Airbus AOT A71L004-14, Revision 01, dated April 7, 
2014; AOT A71L005-14, Revision 01, dated December 11, 2014; AOT 
A71L006-14, dated July 22, 2014; and AOT A71L008-14, Revision 01, 
dated December 18, 2014, specify actions ``if one pylon bolt fully 
broken,'' this AD requires that those actions be done if one or more 
engine mount bolt is found fully broken during any torque check 
required by paragraph (h)(1), (j)(1), (k)(1) or (l)(1) of this AD.

(n) Reporting

    At the applicable time specified in paragraphs (n)(1) and (n)(2) 
of this AD: After accomplishment of any torque check required by 
paragraphs (h), (j), (k), and (l) of this AD, report all inspection 
results to Airbus, including no findings, in accordance with the 
``Reporting'' section of the applicable service information 
specified in paragraphs (h), (j), (k), and (l) of this AD.
    (1) If the torque check was done on or after the effective date 
of this AD: Submit the report within 30 days after the torque check.
    (2) If the torque check was done before the effective date of 
this AD: Submit the report within 30 days after the effective date 
of this AD.

(o) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using Airbus AOT A71L004-14, dated April 
1, 2014 (for Airbus Model A330 Airplanes Equipped with PW Engines), 
which is not incorporated by reference in this AD.
    (2) This paragraph provides credit for the actions required by 
paragraph (k) of this AD, if those actions were performed before the 
effective date of this AD using Airbus AOT A71L005-14, dated 
September 29, 2014 (for Airbus Model A330 Airplanes Equipped with RR 
Trent 700 Engines), which is not incorporated by reference in this 
AD.
    (3) This paragraph provides credit for the actions required by 
paragraph (l) of this AD, if those actions were performed before the 
effective date of this AD using Airbus AOT A71L008-14, dated 
September 29, 2014 (for Airbus Model A340 Airplanes Equipped with RR 
Trent 500 Engines), which is not incorporated by reference in this 
AD.

[[Page 36447]]

(p) 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 with14 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]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: 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 Design Organization Approval (DOA). If approved by the 
DOA, the approval must include the DOA-authorized signature.
    (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.

(q) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA AD 2015-0082, dated May 11, 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-
2015-7533.

(r) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus AOT A71L004-14, Revision 01, dated April 7, 2014.
    (ii) Airbus AOT A71L005-14, Revision 01, dated December 11, 
2014.
    (iii) Airbus AOT A71L006-14, dated July 22, 2014.
    (iv) Airbus AOT A71L008-14, Revision 01, dated December 18, 
2014.
    (3) 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. [email protected]; 
Internet http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on May 12, 2016.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-12056 Filed 6-6-16; 8:45 am]
 BILLING CODE 4910-13-P