[Federal Register Volume 84, Number 250 (Tuesday, December 31, 2019)]
[Proposed Rules]
[Pages 72254-72257]
[FR Doc No: 2019-27978]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0404; Product Identifier 2015-SW-066-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters (Previously
Eurocopter France)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2008-24-04 for Eurocopter France (now Airbus Helicopters) Model AS355E,
AS355F, AS355F1, AS355F2, and AS355N helicopters. AD 2008-24-04
requires repetitively inspecting the lubricating pump and checking the
magnetic chip detector plug (chip detector) and the main gearbox (MGB)
oil-sight glass. Since the FAA issued AD 2008-24-04, Airbus Helicopters
has developed an alteration of the MGB oil flow distribution that
corrects the unsafe condition. This proposed AD would retain the
requirements of AD 2008-24-04 and would allow the option of altering
the MGB oil flow distribution as a terminating action for the
inspections. The actions of this proposed AD are intended to address an
unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by March 2,
2020.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
     Fax:<PHONE_NUMBER>.
     Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0404; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this proposed AD, the European Aviation Safety Agency (EASA) AD, the
economic evaluation, any comments received and other information. The
street address for Docket Operations is listed above. Comments will be
available in the AD docket shortly after receipt.
    For service information identified in this proposed rule, contact
Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052;
telephone<PHONE_NUMBER> or<PHONE_NUMBER>; fax<PHONE_NUMBER>; or at https://www.airbus.com/helicopters/services/technical-support.html.
    You may view the referenced service information at the FAA, Office
of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room
6N-321, Fort Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: Jignesh Patel, Aerospace Engineer,
Safety Management Section, Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy, Fort Worth, TX 76177; telephone<PHONE_NUMBER>; email
<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to participate in this rulemaking by submitting
written comments, data, or views. The FAA also invites comments
relating to the economic, environmental, energy, or federalism impacts
that might result from adopting the proposals in this document. The
most helpful comments reference a specific portion of the proposal,
explain the reason for any recommended change, and include supporting
data. To ensure the docket does not contain duplicate comments,
commenters should send only one copy of written comments, or if
comments are filed electronically, commenters should submit only one
time.
    The FAA will file in the docket all comments received, as well as a
report summarizing each substantive public contact with FAA personnel
concerning this proposed rulemaking. Before acting on this proposal,
the FAA will consider all comments received on or before the closing
date for comments. The FAA will consider comments filed after the
comment period has closed if it is possible to do so without incurring
expense or delay. The FAA may change this proposal in light of the
comments received.

Discussion

    The FAA issued AD 2008-24-04, Amendment 39-15744 (73 FR 71530,
November 25, 2008) (``AD 2008-24-04'') for Eurocopter France (now
Airbus Helicopters) Model AS355E, AS355F, AS355F1, AS355F2, and AS355N
helicopters. AD 2008-24-04 requires repetitive checks of the chip
detector and the MGB oil-sight glass and repetitive inspections of the
lubricating pump. AD 2008-24-04 also requires replacing the MGB and
pump with an airworthy MGB and pump if necessary. AD 2008-24-04 was
prompted by cases of MGB lubricating pump deterioration. The actions of
AD 2008-24-04 are intended to implement improved procedures to detect a
failing MGB oil pump, prevent failure of the MGB oil pump, seizure of
the MGB, loss of drive to an engine and main rotor, and subsequent loss
of control of the helicopter.

Actions Since AD 2008-24-04 Was Issued

    Since the FAA issued AD 2008-24-04, Airbus Helicopters has issued
service information to provide procedures for Airbus Helicopters
modification (MOD) 077222, which improves the distribution of the oil
flow between the accessory modules of the combiner gearbox and the MGB.
Subsequently, EASA, which is the Technical Agent for the Member States
of the European Union, issued EASA AD No. 2007-0209R1, dated September
11, 2015. EASA advises that Airbus Helicopters MOD 077222 provides the
same level of safety as the MGB pump inspections. Accordingly, the EASA
AD applies to Airbus Helicopters Model AS355E, AS355F, AS355F1,
AS355F2, and AS355N helicopters with a lubrication pump part number
355A32-0700-01, 355A32-0700-02, or 355A32-0701-00 installed, except
those with Airbus Helicopters MOD 077222 installed, and requires
repetitive MGB pump inspections and chip detector and MGB oil-sight
glass checks, and allows MOD 077222 as optional terminating action for
the repetitive inspections.

FAA's Determination

    These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA of the
unsafe condition described in its AD. The FAA is proposing this AD
after evaluating all known relevant information and determining that an
unsafe condition is likely to exist or develop on other helicopters of
the same type designs.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Eurocopter Alert Service Bulletin (ASB) No.
05.00.51, Revision 0, dated July 9, 2007 (ASB 05.00.51 Rev 0), and
Airbus Helicopters ASB No. 05.00.51, Revision 1, dated July 29, 2015.
This service information contains procedures for monitoring the MGB oil
pump for wear. Revision 1 of this service information omits helicopters
with MOD 077222 installed.
    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.

Other Related Service Information

    The FAA reviewed Airbus Helicopters Service Bulletin No. AS355-
63.00.25, Revision 1, dated July 29, 2015, and Revision 2, dated June
22, 2017. This service information contains procedures for altering the
lubrication system to increase oil flow between the accessory modules
of the combiner gearbox and the MGB. This service information also
specifies using mineral oil 0-155 in the combiner gearbox instead of
synthetic oil 0-156 after completing the alteration. Airbus Helicopters
identifies this alteration as MOD 077222. Revision 2 of this service
information clarifies a procedure and updates a work card.
    The FAA also reviewed Eurocopter Emergency Alert Service Bulletin
No. 05.00.40, Revision 3, dated July 9, 2007. This service information
specifies inspecting the MGB magnetic plug for sludge and oil sight for
color. If there is sludge or if the oil is dark or dark purple, this
service information specifies removing the lubrication pump and
inspecting it for certain conditions, and replacing it as necessary.
Revision 3 of this service information informs operators that this
service information is superseded by ASB 05.00.51 Rev 0.

Proposed AD Requirements

    This proposed AD would retain the requirements of AD 2008-24-04 and
add an option to alter the lubrication system (MOD 077222) as a
terminating action for the repetitive inspections. For those
helicopters that incorporate Mod 077222, using mineral oil 0-155 in the
combiner gearbox instead of synthetic oil 0-156 would be required. This
proposed AD would also exclude helicopters with MOD 077222 from the
applicability.
    An owner/operator (pilot) may perform the proposed visual checks
and

must enter compliance with that paragraph into the helicopter
maintenance records in accordance with Title 14 Code of Federal
Regulations (14 CFR) Sec. Sec.  43.9(a)(1) through (4) and 14 CFR
91.417(a)(2)(v). A pilot may perform this check because it involves
only a visual check and can be performed equally well by a pilot or a
mechanic. This check is an exception to the FAA's standard maintenance
regulations.

Differences Between This Proposed AD and the EASA AD

    The EASA AD requires that the initial and repetitive MGB oil
inspections be conducted after the last flight of each day without
exceeding 10 flight hours between two successive checks. This proposed
AD would require those inspections before the first flight of each day
and at intervals not to exceed 10 hours time-in-service.

Costs of Compliance

    The FAA estimates that this proposed AD affects 46 helicopters of
U.S. Registry. Labor costs are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates that operators may incur the following
costs in order to comply with this AD.
     Checking the MGB oil and chip detector condition would
take about 0.25 work-hour for an estimated cost of about $21 per
helicopter and $966 for the U.S. fleet per check.
     Inspecting the lubricating pump would take about 1 work-
hour for an estimated cost of $85 per helicopter and $3,910 for the
U.S. fleet per inspection.
     Replacing the MGB and pump would take about 8 work-hours
and cost about $64,000 (overhauled) in parts for an estimated cost of
$64,680 per helicopter.
     Altering the lubrication system (optional MOD 077222)
would take about 4 work-hours and cost about $2,335 in parts for an
estimated cost of $2,675 per helicopter.

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.
    The FAA is 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

    The FAA 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, I certify this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order
12866,
    2. Will not affect intrastate aviation in Alaska to the extent that
it justifies making a regulatory distinction, and
    3. 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.
    The FAA prepared an economic evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.

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)
2008-24-04, Amendment 39-15744 (73 FR 71530, November 25, 2008), and
adding the following new AD:

Airbus Helicopters (previously Eurocopter France): Docket No. FAA-
2017-0404; Product Identifier 2015-SW-066-AD.

(a) Applicability

    This AD applies to Airbus Helicopters (previously Eurocopter
France) Model AS355E, AS355F, AS355F1, AS355F2, and AS355N
helicopters, certificated in any category, with a main gearbox (MGB)
lubrication pump (pump) part number 355A32-0700-01, 355A32-0700-02,
or 355A32-0701-00, except helicopters with Modification (MOD) 077222
installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as insufficient lubrication
within an MGB. This condition, if not detected and corrected, could
result in failure of the MGB pump, seizure of the MGB, loss of drive
to an engine and main rotor, and subsequent loss of helicopter
control.

(c) Affected ADs

    This AD replaces AD 2008-24-04, Amendment 39-15744 (73 FR 71530,
November 25, 2008).

(d) Comments Due Date

    The FAA must receive comments by March 2, 2020.

(e) Compliance

    You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.

 (f) Required Actions

    (1) Before the first flight of each day and at intervals not to
exceed 10 hours time-in-service (TIS), check the MGB magnetic chip
detector plug (chip detector) for any sludge. Also, check for dark
oil in the MGB oil-sight glass. The actions required by this
paragraph may be performed by an owner/operator (pilot) holding at
least a private pilot certificate and must be entered into the
aircraft records showing compliance with this AD in accordance with
Title 14 Code of Federal Regulations (14 CFR) Sec. Sec.  43.9 (a)(1)
through (4) and 14 CFR 91.417(a)(2)(v). The record must be
maintained as required by 14 CFR 91.417, 121.380, or 135.439.
``Sludge'' is a deposit on the chip detector that is typically dark
in color and in the form of a film or paste, as compared to metal
chips or particles normally found on a chip detector. Sludge may
have both metallic or nonmetallic properties, may consist of copper
(pinion bearing), magnesium (pump case), and steel (pinion) from the
oil pump, and a nonmetallic substance from the chemical breakdown of
the oil as it interacts with the metal.
    (i) Before further flight, if any sludge is found on the chip
detector, remove, open, and inspect the pump.
    (ii) Before further flight, if the oil appears dark in color
when it is observed through the MGB oil-sight glass, take an oil
sample. If the oil taken in the sample is dark or dark purple,
before further flight, remove, open, and inspect the pump.
    (2) Within 25 hours TIS, after operating both engines at normal
operating revolutions per minute (RPM) for at least 20 minutes to
ensure the MGB oil temperature has stabilized, inspect the oil pump
for wear by following the Accomplishment Instructions, paragraph
2.B.2., steps 1. through 6., of Eurocopter Alert Service Bulletin
(ASB) No. 05.00.51, Revision 0, dated July 9, 2007 (ASB 05.00.51 Rev
0), or Airbus Helicopters ASB

No. 05.00.51, Revision 1, dated July 29, 2015 (ASB 05.00.51 Rev 1).
    (i) Record the outside air temperature (OAT) and rotor speed (NR
RPM) and plot the point at which they intersect using the graph in
Figure 1 or 2 of ASB 05.00.51 Rev 0 or ASB 05.00.51 Rev 1.
    (ii) If the point on the graph at the intersection of the
recorded OAT and the NR RPM falls within:
    (A) Zone 3--Before further flight, replace the MGB and pump with
an airworthy MGB and pump.
    (B) Zone 2--At intervals not to exceed 25 hours TIS, repeat the
inspection procedures by following the Accomplishment Instructions,
paragraph 2.B.2, steps 1. through 6., of ASB 05.00.51 Rev 0 or ASB
05.00.51 Rev 1. After being classified in ``Zone 2,'' you must
obtain two successive inspections separated by at least 24 hours TIS
that fall within Zone 1 before you can begin to inspect at intervals
not to exceed 110 hours TIS by following paragraph (f)(2)(ii)(C) of
this AD for Zone 1.
    (C) Zone 1--At intervals not to exceed 110 hours TIS, repeat the
inspection procedures by following the Accomplishment Instructions,
paragraph 2.B.2., steps 1. through 6., of ASB 05.00.51 Rev 0 or ASB
05.00.51 Rev 1.
    (iii) Compliance with paragraphs (f)(2)(i) and (ii) of this AD
constitutes terminating action for the checks and inspections
required by paragraph (f)(1) of this AD.
    (3) As an optional terminating action for the requirements in
this AD, alter the lubrication system for the MGB in accordance with
the Accomplishment Instructions, paragraphs 3.B.2.a. through 3.B.3
of Airbus Helicopters Service Bulletin No. AS355-63.00.25, Revision
1, dated July 29, 2015, or Revision 2, dated June 22, 2017. Mineral
oil 0-155 is required after compliance with this alteration.

    Note 1 to paragraph (f)(3) of this AD: Airbus Helicopters
identifies alteration of the lubrication system as MOD 077222.

 (g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this AD. Send your proposal to:
Jignesh Patel, Aerospace Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy, Fort Worth,
TX 76177; telephone<PHONE_NUMBER>; email<EMAIL_ADDRESS>    (2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or lacking a principal
inspector, the manager of the local flight standards district office
or certificate holding district office before operating any aircraft
complying with this AD through an AMOC.

(h) Additional Information

    (1) Airbus Helicopters Service Bulletin No. AS355-63.00.25,
Revision 1, dated July 29, 2015, and Revision 2, dated June 22,
2017, and Eurocopter Emergency Alert Service Bulletin No. 05.00.40,
Revision 3, dated July 9, 2007, which are not incorporated by
reference, pertain to the subject of this AD. For service
information identified in this AD, contact Airbus Helicopters, 2701
N. Forum Drive, Grand Prairie, TX 75052; telephone<PHONE_NUMBER> or
800-232-0323; fax<PHONE_NUMBER>; or at https://www.airbus.com/helicopters/services/technical-support.html. You may view a copy of
the service information at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX
76177.
    (2) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) AD No. 2007-0209R1, dated September 11, 2015.
You may view the EASA AD on the internet at https://www.regulations.gov in the AD Docket.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6320, Main Rotor
Gearbox.

    Issued in Fort Worth, Texas, on December 20, 2019.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2019-27978 Filed 12-30-19; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 82, Number 100 (Thursday, May 25, 2017)]
[Rules and Regulations]
[Pages 24039-24043]
[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.

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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<EMAIL_ADDRESS>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<PHONE_NUMBER>. 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:<PHONE_NUMBER>;
fax:<PHONE_NUMBER>.

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

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.

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.

                                     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:<PHONE_NUMBER>; fax:<PHONE_NUMBER>.
Information may be emailed to<EMAIL_ADDRESS>
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

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:<PHONE_NUMBER>; fax:<PHONE_NUMBER>.
    (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<EMAIL_ADDRESS>
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<PHONE_NUMBER>, 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