
[Federal Register Volume 82, Number 100 (Thursday, May 25, 2017)]
[Rules and Regulations]
[Pages 24039-24043]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10282]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8849; Directorate Identifier 2015-NM-174-AD; 
Amendment 39-18892; AD 2017-10-18]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A330-223F, -223, -321, -322, and -323 airplanes. This AD 
was prompted by fatigue load analysis that determined the need for 
reduced inspection intervals and updated torque values of the bolts. 
This AD requires repetitive torque checks of the forward engine mount 
bolts, an inspection of the forward mount assembly, and replacement of 
the bolts or repair of the forward mount assembly as necessary. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective June 29, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 29, 
2017.

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.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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
8849.

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-
8849; 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 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 all Airbus Model A330-223F, 
-223, -321, -322, and -323 airplanes. The NPRM published in the Federal 
Register on August 30, 2016 (81 FR 59535). The NPRM was prompted by 
fatigue load analysis that determined the need for reduced inspection 
intervals (for torque checks required by AD 2013-14-04, Amendment 39-
17509 (78 FR 68352, November 14, 2013) (``AD 2013-14-04'')) and updated 
torque values of the bolts. The NPRM proposed to require repetitive 
torque checks to determine if there are any loose or broken forward 
engine mount bolts, and, if necessary, replacement of all four forward 
engine mount bolts and associated nuts, inspection of the forward mount 
assembly, and repair. We are issuing this AD to detect and correct 
loose and broken bolts, which could lead to engine detachment in flight 
and damage to the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2015-0214, dated October 19, 2015 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus Model A330-223F, -223, -321, 
-322, and -323 airplanes. The MCAI states:

    The forward mount engine pylon bolts, Part Number (P/N) 51U615, 
fitted on Airbus A330 aeroplanes with Pratt & Whitney (PW) PW4000 
engines, are made from MP159 material. Analysis made by PW 
identified that MP159 material pylon bolts do not meet the full life 
cycle torque check interval requirement, in a bolt-out condition. 
Consequently, PW issued Alert Service Bulletin (ASB) PW4G-100-A71-
32, and the U.S. Federal Aviation Administration (FAA), as Engine 
Certification Authority, issued FAA AD 2006-16-05 [Amendment 39-
14705 (71 FR 44185, August 4, 2006) (``AD 2006-16-05'')] to require 
repetitive torque checks of MP159 material forward mount pylon bolts 
fitted on certain PW4000 series engines.
    However, the engine mount system is considered to be part of 
aeroplane certification rather than the engine certification. 
Following further fatigue load analysis by Airbus of the A330 engine 
mount system, it was determined that the torque check interval for 
MP159 material forward mount pylon bolts, as required by FAA AD 
2006-16-05 (2,700 flight cycles (FC)), provided an insufficient 
level of safety for Airbus A330 aeroplanes.
    This condition, if not detected and corrected, could ultimately 
lead to detachment of the engine from the aeroplane, possibly 
resulting in damage to the aeroplane and/or injury to persons on the 
ground.
    Consequently, EASA issued AD 2012-0094 [which corresponds to FAA 
AD 2013-14-04] to require accomplishment of repetitive torque checks 
of the forward mount pylon bolts installed on affected A330 
aeroplanes and, depending on findings, replacement of all four bolts 
and associated nuts, in accordance with PW ASB PW4G-100-A71-32 
Revision 01 and Airbus Service Bulletin (SB) A330-71-3028.
    Since that AD was issued, it has been concluded that a new 
torque value must be applied.
    Consequently, Airbus issued SB A330-71-3028 Revision 02 and PW 
issued ASB PW4G-100-A71-32 Revision 02 to update the torque value. 
Additional forward mount inspections are also provided in case of 
one or more forward engine mount bolts is found loose, broken or 
missing.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2012-0094, which is superseded, introduces a 
new torque value, and requires additional inspections and, depending 
on findings, corrective action(s).

    Corrective actions include repetitive torque checks to determine if 
there are any loose or broken forward engine mount bolts on both 
engines, and, if necessary, replacement of all four forward engine 
mount bolts and associated nuts, inspection of the forward mount 
assembly, and repair. 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-2016-8849.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The

[[Page 24040]]

following presents the comments received on the NPRM and the FAA's 
response to each comment.

Request To Correct Typographical Error

    American Airlines (AA) requested that we correct the reference to 
the FAA AD in paragraph (g)(1) of the proposed AD, which incorrectly 
identified AD 2013-13-05. The correct AD number for this terminating 
action is 2013-14-04.
    We agree and have revised paragraph (g)(1) of this AD accordingly.

Request To Clarify Compliance Time

    AA requested that we clarify the compliance time for airplanes with 
an average flight time (AFT) of more than 132 minutes for the second 
cycle interval (1,851-2,700 flight cycles). AA proposed that we revise 
the second row of table 1 to paragraph (g) of the proposed AD by 
referring to the specified compliance times since accomplishing actions 
in AD 2013-14-04.
    We agree that clarification is necessary. The compliance times for 
the initial and repetitive torque checks required by AD 2013-14-04 are 
identified in table 1 to paragraph (g)(1) of this AD (table 1 to 
paragraph (g) of the proposed AD). The compliance times include 
specified flight cycles since the last torque check specified in Pratt 
& Whitney Alert Service Bulletin PW4G-100-A71-32, which operators might 
have accomplished to comply with AD 2013-14-04. Paragraph (g)(1) of 
this AD requires that the next torque check be done in accordance with 
Airbus Service Bulletin A330-71-3028, Revision 02, dated August 31, 
2015 (``A330-71-3028, R02''). Accomplishment of the torque check 
required by paragraph (g)(1) of this AD terminates the requirements of 
AD 2013-14-04. We have not changed this AD regarding this issue.

Request To Clarify Terminating Action

    Paragraph (h) of the proposed AD stated that accomplishment of the 
actions specified by paragraph (g) of the proposed AD ``constitutes 
compliance with'' the requirements specified in paragraph (g) of AD 
2006-16-05. AA requested that we revise paragraph (h) of the proposed 
AD to specifically state that the new AD would also ``terminate'' the 
inspection specified in AD 2006-16-05.
    We agree with the commenter. We have revised paragraph (h) of this 
AD to state that accomplishment of the actions required by paragraph 
(g) of this AD terminates the requirements of paragraph (g) of AD 2006-
16-05.

Request To Allow Use of Higher Torque Values

    AA requested that we revise paragraph (j) of the proposed AD to 
specifically allow early compliance with the AD upon its release and 
prior to the effective date of the AD, using Airbus Service Bulletin 
A330-71-3028, R02. AA stated that this would allow operators to 
immediately begin using the higher torque values specified in Airbus 
Service Bulletin A330-71-3028, R02. AA stated that as written, the AD 
would not allow operators to immediately use the higher torque values 
specified in Airbus Service Bulletin A330-71-3028, R02, because AD 
2013-14-04 specifies the use of Airbus Service Bulletin A330-71-3028, 
Revision 01, dated February 12, 2012, which contains lower torque 
values. AA stated that this would preclude the need for a request for 
an alternative method of compliance (AMOC) against AD 2013-14-04 to 
allow the use of the higher torque values, and that this change would 
streamline the compliance revision process.
    We acknowledge the request and agree that clarification is 
necessary. Because AD 2013-14-04 requires using Airbus Service Bulletin 
A330-71-3028, Revision 01, dated February 12, 2012, operators need 
approval to use Airbus Service Bulletin A330-71-3028, R02, as an AMOC 
for the requirements of AD 2013-14-04. We have issued global AMOC ANM-
116-17-243, dated April 4, 2017, approving the use of Airbus Service 
Bulletin A330-71-3028, R02, for compliance with the requirements of AD 
2013-14-04. Therefore, no changes to this AD are necessary regarding 
this issue.

Request To Limit Requirements for Certain Approvals

    Delta Air Lines (Delta) requested that we revise the statement in 
paragraph (g)(2) of the proposed AD to remove the requirement to obtain 
FAA, EASA, or Airbus Design Organization Approval (DOA) approval for 
any instance where Airbus Service Bulletin A330-71-3028, R02, specifies 
contacting Airbus. Delta requested that we instead require these 
approvals only for damage that exceeds the allowable limits in the 
airplane maintenance manual (AMM); component maintenance manual (CMM); 
or cleaning, instruction and repair (CIR) manual. Delta stated that 
Airbus Service Bulletin A330-71-3028, R02, specifies contacting Airbus 
any time a bolt is found out of tolerance regardless whether any damage 
is found. As such, this would effectively require FAA, EASA, or Airbus 
DOA approval any time a bolt is found with a torque out of limits, even 
if there is no damage to the forward mount assembly, or if the damage 
is within the AMM, CMM, or CIR allowable limits. Delta agreed with the 
required approvals, but only when there is damage that exceeds those 
limits. Delta stated that this change would limit the number of AMOC 
requests, and reduce airplane out-of-service times while maintaining 
the acceptable level of safety.
    We disagree with the commenter's request to change the corrective 
action requirement in paragraph (g)(2) of this AD. The requirements of 
this AD correspond with those specified in the MCAI. The MCAI refers to 
Airbus Service Bulletin A330-71-3028, R02, which specifies that when 
any bolt is found with a torque out of limits, corrective actions must 
be done. We have determined that these actions are necessary to address 
the identified unsafe condition. However, under the provisions of 
paragraph (k)(1) of this AD, we will consider requests for approval of 
alternative corrective actions if sufficient data are submitted to 
substantiate that the alternative actions would provide an acceptable 
level of safety. We have not changed this AD regarding this issue.

Request To Allow Replacement Instead of Repair

    Delta stated that paragraph (g)(2) of the proposed AD, which 
applies to the airplane (not the engine mount), would require repair 
before further flight. Delta interpreted this to mean the proposed AD 
would require repair of the forward engine mount before the airplane 
could return to flight. Delta requested that we revise the proposed AD 
to include a statement that explicitly allows replacement of damaged 
engine mounts, allowing the airplane to return to service as quickly as 
possible.
    We partially agree with the commenter's request. We agree that 
replacement of an affected forward engine mount might be allowed as a 
corrective action and that a different compliance time may be 
acceptable. We have revised paragraph (g)(2) of this AD by replacing 
the proposed requirement to repair before further flight with the 
requirement to contact the FAA, EASA, or Airbus's EASA DOA before 
further flight to obtain applicable corrective action instructions 
approved by the FAA, EASA, or Airbus's EASA DOA, and to do applicable 
corrective actions within the compliance time specified in those 
instructions.

[[Page 24041]]

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these 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

    Airbus has issued Service Bulletin A330-71-3028, Revision 02, dated 
August 31, 2015. The service information describes procedures for 
repetitive torque checks for loose or broken forward engine mount bolts 
on both engines, replacement of all four forward engine mount bolts and 
associated nuts, and inspection of the forward mount assembly. 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 41 airplanes of U.S. registry.
    We also estimate that it would take about 3 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts would cost about $6,747 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $287,082, or $7,002 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 1 work-hour and require parts costing $6,747, for a cost of 
$6,832 per product. We have no way of determining the number of 
aircraft that might need these actions.

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
    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):

2017-10-18 Airbus: Amendment 39-18892; Docket No. FAA-2016-8849; 
Directorate Identifier 2015-NM-174-AD.

(a) Effective Date

    This AD is effective June 29, 2017.

(b) Affected ADs

    This AD affects AD 2006-16-05, Amendment 39-14705 (71 FR 44185, 
August 4, 2006) (``AD 2006-16-05''); and AD 2013-14-04, Amendment 
39-17509 (78 FR 68352, November 14, 2013) (``AD 2013-14-04'').

(c) Applicability

    This AD applies to Airbus Model A330-223F, -223, -321, -322, and 
-323 airplanes, certificated in any category, all manufacturer 
serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by fatigue load analysis that determined 
the need for certain reduced inspection intervals and updated torque 
values of the forward engine mount pylon bolts. We are issuing this 
AD to detect and correct loose or broken bolts, which could lead to 
engine detachment in flight and damage to the airplane.

(f) Compliance

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

(g) Torque Check, Replacement, and Terminating Action for AD 2013-14-04

    (1) At the applicable compliance time specified in table 1 to 
paragraph (g)(1) of this AD, do a torque check to determine if there 
are any loose or broken forward engine mount bolts (4 positions/
engine) on both engines, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-71-3028, Revision 02, 
dated August 31, 2015. Repeat the torque check at the applicable 
time intervals not to exceed the values specified in table 1 to 
paragraph (g)(1) of this AD. For the purposes of this AD, the 
average flight time (AFT) is defined as a computation of the number 
of flight hours divided by the number of flight cycles accumulated 
since the most recent torque check or since the airplane's first 
flight, as applicable. Accomplishment of the initial torque check 
required by this paragraph terminates the requirements of AD 2013-
14-04.

[[Page 24042]]



                                     Table 1 to Paragraph (g)(1) of This AD
----------------------------------------------------------------------------------------------------------------
                                            Flight cycles
                                          accumulated as of
                                        December 19, 2013 (the
                                         effective date of AD
                                       2013-14-04), since last
           Airplane models              torque check specified      Compliance time       Torque check interval
                                          in Pratt & Whitney                                 (not to exceed)
                                        Alert Service Bulletin
                                          PW4G-100-A71-32 or
                                        since airplane's first
                                        flight, as applicable
----------------------------------------------------------------------------------------------------------------
Model A330-321, -322, and -323                         0-1,850  Within 2,350 flight      2,350 flight cycles or
 airplanes with AFT more than 132                                cycles since the last    24,320 flight hours,
 minutes; and Model A330-223                                     torque check as          whichever occurs
 airplanes.                                                      specified in Pratt &     first.
                                                                 Whitney Alert Service
                                                                 Bulletin PW4G-100-A71-
                                                                 32, or since
                                                                 airplane's first
                                                                 flight, as applicable.
Model A330-321, -322, and -323                     1,851-2,700  Within 500 flight        2,350 flight cycles or
 airplanes with AFT more than 132                                cycles after December    24,320 flight hours,
 minutes; and Model A330-223                                     19, 2013 (the            whichever occurs
 airplanes.                                                      effective date of AD     first.
                                                                 2013-14-04), without
                                                                 exceeding 2,700 flight
                                                                 cycles since last
                                                                 torque check as
                                                                 specified in Pratt &
                                                                 Whitney Alert Service
                                                                 Bulletin PW4G-100-A71-
                                                                 32, or since
                                                                 airplane's first
                                                                 flight, as applicable;
                                                                 or within 3 months
                                                                 after December 19,
                                                                 2013; whichever occurs
                                                                 later.
Model A330-321, -322, and -323                         0-1,450  Within 1,950 flight      1,950 flight cycles or
 airplanes with AFT 132 minutes or                               cycles since the last    20,210 flight hours,
 less; and Model A330-321, -322, and -                           torque check performed   whichever occurs
 323 airplanes on which the AFT is                               as specified in Pratt    first.
 not calculated on a regular basis.                              & Whitney Alert
                                                                 Service Bulletin PW4G-
                                                                 100-A71-32, or since
                                                                 airplane's first
                                                                 flight, as applicable.
Model A330-321, -322, and -323                     1,451-2,700  Within 500 flight        1,950 flight cycles or
 airplanes with AFT 132 minutes or                               cycles after December    20,210 flight hours,
 less; and Model A330-321, -322, and                             19, 2013 (the            whichever occurs
 [dash]323 airplanes on which the AFT                            effective date of AD     first.
 is not calculated on a regular basis.                           2013-14-04), without
                                                                 exceeding 2,700 flight
                                                                 cycles since last
                                                                 torque check performed
                                                                 as specified in Pratt
                                                                 & Whitney Alert
                                                                 Service Bulletin PW4-
                                                                 100-A71-32, or since
                                                                 airplane's first
                                                                 flight, as applicable;
                                                                 or within 3 months
                                                                 after December 19,
                                                                 2013; whichever occurs
                                                                 later.
Model A330-223F airplanes............                      Any  Within 2,140 flight      2,140 flight cycles or
                                                                 cycles or 6,600 flight   6,600 flight hours,
                                                                 hours, whichever         whichever occurs
                                                                 occurs first since the   first.
                                                                 last torque check
                                                                 performed as specified
                                                                 in Pratt & Whitney
                                                                 Alert Service Bulletin
                                                                 PW4G-100-A71-32, or
                                                                 since airplane's first
                                                                 flight, as applicable.
----------------------------------------------------------------------------------------------------------------

    (2) If any loose or broken bolt is detected during the check 
required by paragraph (g)(1) of this AD, before further flight, do 
the actions specified by paragraphs (g)(2)(i) and (g)(2)(ii) of this 
AD, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A330-71-3028, Revision 02, dated August 31, 2015; 
except, where the service information specifies to contact the 
manufacturer for further corrective actions, before further flight 
contact 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); to 
obtain applicable corrective action instructions approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Airbus's EASA DOA; and accomplish the 
applicable corrective actions within the compliance time specified 
in those instructions.
    (i) Replace all four forward engine mount bolts and associated 
nuts, on the engine where the loose or broken bolt was detected, 
with new bolts and nuts.
    (ii) Do nondestructive inspections of the forward mount assembly 
for damage including cracks, dents, nicks, and scratches, and do all 
applicable corrective actions.
    (3) Replacement of bolts and nuts as required by paragraph 
(g)(2)(i) of this AD is not terminating action for the repetitive 
torque checks required by paragraph (g)(1) of this AD.

(h) Terminating Action for Paragraph (g) of AD 2006-16-05

    Accomplishment of the actions required by paragraph (g) of this 
AD terminates the requirements specified in paragraph (g) of AD 
2006-16-05.

(i) Parts Installation Prohibition

    As of December 19, 2013 (the effective date of AD 2013-14-04), 
no person may install, on any airplane, any forward mount pylon bolt 
made of INCO718 material and having Pratt & Whitney part number 
54T670.

(j) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g)(1) and (g)(2)(i) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A330-71-3028, dated December 16, 2011, or Airbus Service 
Bulletin A330-71-3028, Revision 01, dated February 20, 2012.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. 
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office.
    (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

[[Page 24043]]

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 (g)(2) 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.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2015-0214, dated October 19, 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-2016-8849.
    (2) For more information about this AD, 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.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(m) 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 Service Bulletin A330-71-3028, Revision 02, dated 
August 31, 2015.
    (ii) Reserved.
    (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.A330-A340@airbus.com; 
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 8, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10282 Filed 5-24-17; 8:45 am]
 BILLING CODE 4910-13-P


