Airworthiness Directives; Airbus Airplanes, 81216-81220 [2015-32547]
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Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules
catalogs, and in other product
advertising literature.
Original equipment manufacturer or
OEM means any person who produces
or assembles a unit of a covered product
or covered equipment. Only one OEM is
responsible for the manufacture
(production or assembly) of a particular
unit.
■ 3. Section 429.5 is amended by adding
paragraph (c) to read as follows:
number (depending on the certification
method) for each brand must be
submitted. For commercial HVAC, WH,
and refrigeration equipment, an
individual model number may be
identified as a ‘‘private model number’’
if it meets the requirements of
§ 429.7(b).
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■ 6. Section 429.500 is added to read as
follows:
§ 429.5
§ 429.500.
Imported products.
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(c) Any person importing a unit of a
covered product or covered equipment
subject to an applicable energy
conservation standard set forth in parts
430 or 431 of this chapter for entry into
the United States on or after [2 YEARS
AFTER DATE OF PUBLICATION OF
FINAL RULE IN THE FEDERAL
REGISTER], whether the unit is a
component part of another product or a
final product, must provide a
certification of admissibility to the
Secretary in accordance with § 429.500.
■ 4. Section 429.7 is amended by
revising paragraph (b) to read as follows:
§ 429.7
Confidentiality.
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(b) An individual model number is
public information unless:
(1) The individual model number is a
unique model number of a commercial
packaged boiler, commercial water
heating equipment, commercial HVAC
equipment or commercial refrigeration
equipment that was developed for an
individual customer,
(2) The individual model number is
not displayed on product literature, and
(3) Disclosure of the individual model
number would reveal confidential
business information as described at
§ 1004.11 of this title—in which case,
under these limited circumstances, a
manufacturer may identify the
individual model number as a private
model number on a certification report
submitted pursuant to § 429.12(b)(6).
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■ 5. Section 429.12 is amended by
revising paragraph (b)(6) to read as
follows:
§ 429.12. General requirements applicable
to certification reports.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
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(b) * * *
(6) For each brand, the basic model
number and the individual model
number(s) in that basic model with the
following exceptions: For walk-in
coolers, the basic model number for
each brand must be submitted. For
distribution transformers, the basic
model number or kVA grouping model
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Certification of admissibility.
(a) A certification of admissibility
submitted pursuant to § 429.5(c) must
meet the provisions of this section.
(b) The certification must be
submitted through the Automated
Commercial Environment (ACE) of the
U.S. Customs and Border Protection
(CBP) before the entry of the unit(s) at
the port of arrival.
(c) The certification must include
whether the basic model of the product
or equipment being imported has been
certified to DOE as compliant with all
applicable energy conservation
standards;
(d) If the importer has not submitted
a certification report for the basic model
of the product or equipment being
imported pursuant to § 429.12, the
certification of admissibility must
include:
(1) The type of product or equipment
(using a three-digit code corresponding
to the applicable section in 10 CFR part
429, subpart B);
(2) The brand name of the covered
product or equipment;
(3) The individual model number of
the covered product or equipment;
(4) Whether the covered product or
equipment being imported is a final
product or a component of a final
product and, if the covered product or
equipment is a component, the brand
name and individual model number of
the final product;
(5) The original equipment
manufacturer (OEM) of the covered
product or equipment being imported as
defined in § 429.2 and, in the case of
electric motors, the Compliance
Certification number; and
(6) A contact name and email address
of the importer of record.
(e) If the importer has submitted a
certification report for the basic model
of the product or equipment being
imported pursuant to § 429.12, the
certification of admissibility must
include:
(1)The CCMS ticket number of the
most recent certification submission;
(2)The CCMS attachment
identification number assigned to the
certification submission;
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(3) The line number in the submission
corresponding to the basic model
certified; and
(4) If the covered product or
equipment is a component of a final
product, the brand name and individual
model number of the final product.
[FR Doc. 2015–32796 Filed 12–28–15; 8:45 am]
BILLING CODE 6450–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–7533; Directorate
Identifier 2015–NM–080–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A330–200 and –300 series
airplanes, Model A330–200 Freighter
series airplanes, and Airbus Model
A340–541 and A340–642 airplanes.
This proposed AD was prompted by a
report of an under-torqued forward
engine mount bolt. This proposed AD
would require a one-time torque check
of the forward and aft engine mount
bolts, and corrective actions if
necessary. We are proposing 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: We must receive comments on
this proposed AD by February 12, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
SUMMARY:
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Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed 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 https://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.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
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–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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2015–7533; Directorate Identifier
2015–NM–080–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety
Agency, which is the Technical Agent
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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 Airbus 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
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 inflight 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 Pratt
& Whitney (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, [corrective actions]
re-torque of the affected bolt(s) and/or
replacement of all four bolts and associated
nuts.
Findings (or discrepancies) include
one bolt that is loose or able to rotate,
two or more bolts that are loose or able
to rotate, or one or more pylon bolts that
are fully broken. Corrective actions
include re-torqueing the affected bolt(s),
and replacing all bolts and associated
nuts with new bolts and nuts on the
engine where the loose or fully broken
bolt(s) were detected. This proposed AD
specifies reporting of all findings
(including no discrepancies). The
corrective actions include re-torqueing
loose bolts before further flight. The
compliance times for replacing loose or
fully broken bolts ranges, depend on
airplane configuration, and range from
before further flight if more than one
bolt rotates or is fully broken to no later
than 2,350 flight cycles or 24,320 flight
hours since first flight of the airplane, if
only one bolt rotates. You may examine
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the MCAI in the AD docket on the
Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2015–7533.
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 pylon bolts at four
positions at the forward engine pylon 1
and pylon 2 of Airbus Model A330
series airplanes having Pratt and
Whitney 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 pylon
bolts at four positions at the forward
engine pylon 1 and pylon 2 of Airbus
Model A330 series airplanes having
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 onetime torque check to determine if there
are any loose or fully broken engine
mount pylon 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 pylon
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 of
this NPRM.
Other Related Rulemaking
On June 21, 2013, we issued AD
2013–14–04, Amendment 39–17509 (78
FR 68352, November 14, 2013). AD
2013–14–04 requires a torque check of
forward engine mount bolts, and
replacement if necessary on all Airbus
Model A330–223F, –223, –321, –322,
and –323 airplanes. AD 2013–14–04 was
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Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules
prompted by a fatigue load analysis that
determined that the inspection interval
for certain pylon bolts must be reduced.
We issued AD 2013–04–04 to detect and
correct loose or broken bolts, which
could lead to engine detachment inflight, and damage to the airplane.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
Costs of Compliance
We estimate that this proposed AD
affects 55 airplanes of U.S. registry.
We also estimate that it would take
about 12 work-hours per product to
comply with the basic requirements of
this proposed AD, and 1 work-hour per
product to report torque check findings.
The average labor rate is $85 per workhour. Based on these figures, we
estimate the cost of this proposed AD on
U.S. operators to be $60,755, or $1,105
per product.
In addition, we estimate that any
necessary follow-on actions would 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
OMB control number. The control
number for the collection of information
required by this proposed AD is 2120–
0056. The paperwork cost associated
with this proposed 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 proposed
AD is mandatory. Comments concerning
the accuracy of this burden and
suggestions for reducing the burden
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should be directed to the FAA at 800
Independence Ave. SW., Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2015–7533;
Directorate Identifier 2015–NM–080–AD.
(a) Comments Due Date
We must receive comments by February
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 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
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jstallworth on DSK7TPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules
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 Airbus
Service Bulletin A330–71–3028, Revision 01,
dated February 20, 2012, 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
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 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, retorque the affected bolt, and, within 2,350
flight cycles or 24,320 flight hours since first
flight of the airplane, whichever occurs first,
replace the 4 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 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 bolt, and within 2,350 flight cycles
or 24,320 flight hours since first flight of the
airplane, whichever occurs first, replace the
4 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 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 bolt and
within 2,140 flight cycles or 6,600 flight
hours since first flight of the airplane,
whichever occurs first, replace the 4 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
bolts and associated nuts in accordance with
the instructions of Section 4.2.3, ‘‘Findings,’’
of AOT A71L004–14, Revision 01, dated
April 7, 2014.
(A) 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) 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) Model A330–200 Freighter series
airplanes having accumulated 2,140 flight
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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 bolts are found that rotate: Before
further flight, replace the 4 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
pylon bolts are found fully broken: Before
further flight, replace the 4 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
bolt is found that rotates: Before further
flight, re-torque the affected bolt, and replace
the 4 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
bolts are found that rotate: Before further
flight, replace the 4 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
pylon bolts are found fully broken: Before
further flight, replace the 4 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.
(i) Concurrent Actions
AD 2013–14–04, Amendment 39–17509
(78 FR 68352, November 14, 2013), requires
a torque check of forward 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 within the compliance
times specified in paragraph (g) of the FAA
AD 2013–14–04 using Airbus Service
Bulletin A330–71–3028, Revision 01, dated
February 20, 2012, perform the torque check
of the AFT engine mount bolts at the same
time.
(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
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Fmt 4702
Sfmt 4702
81219
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
bolts, as applicable, and their associated nuts
with new 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 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
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
pylon 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 bolt
is found that rotates: Before further flight, retorque 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 bolts and
associated nuts with new 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
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
pylon 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,
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Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules
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 bolt rotates, two or more
bolts rotate, or one or more 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.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
(l) Action for Airbus Model A340–541 and
–642 Airplanes Equipped With Rolls-Royce
Trent 500 Engines
(1) For Airbus Model A340–541 and –642
airplanes equipped with Rolls-Royce 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 bolt rotates, two or more
bolts rotate, or one or more 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, dated September 29, 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 pylon 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
VerDate Sep<11>2014
15:26 Dec 28, 2015
Jkt 238001
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 Pratt
and Whitney 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
Rolls-Royce 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
Rolls-Royce Trent 500 Engines), which is not
incorporated by reference in this AD.
(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 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-116AMOC-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. 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
the European Aviation Safety Agency
(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
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Frm 00022
Fmt 4702
Sfmt 4702
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
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0082, dated
May 11, 2015, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2015–7533.
(2) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You may
view this service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
Issued in Renton, Washington, on
December 18, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–32547 Filed 12–28–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–7531; Directorate
Identifier 2015–NM–052–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 787–8
airplanes. This proposed AD was
SUMMARY:
E:\FR\FM\29DEP1.SGM
29DEP1
]]>Agencies
[Federal Register Volume 80, Number 249 (Tuesday, December 29, 2015)]
[Proposed Rules]
[Pages 81216-81220]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-32547]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-7533; Directorate Identifier 2015-NM-080-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Airbus Model A330-200 and -300 series airplanes, Model A330-200
Freighter series airplanes, and Airbus Model A340-541 and A340-642
airplanes. This proposed AD was prompted by a report of an under-
torqued forward engine mount bolt. This proposed AD would require a
one-time torque check of the forward and aft engine mount bolts, and
corrective actions if necessary. We are proposing 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: We must receive comments on this proposed AD by February 12,
2016.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5
[[Page 81217]]
p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed 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 https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-7533;
Directorate Identifier 2015-NM-080-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
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 Airbus 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
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 Pratt &
Whitney (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, [corrective actions] re-torque of the
affected bolt(s) and/or replacement of all four bolts and associated
nuts.
Findings (or discrepancies) include one bolt that is loose or able
to rotate, two or more bolts that are loose or able to rotate, or one
or more pylon bolts that are fully broken. Corrective actions include
re-torqueing the affected bolt(s), and replacing all bolts and
associated nuts with new bolts and nuts on the engine where the loose
or fully broken bolt(s) were detected. This proposed AD specifies
reporting of all findings (including no discrepancies). The corrective
actions include re-torqueing loose bolts before further flight. The
compliance times for replacing loose or fully broken bolts ranges,
depend on airplane configuration, and range from before further flight
if more than one bolt rotates or is fully broken to no later than 2,350
flight cycles or 24,320 flight hours since first flight of the
airplane, if only one bolt rotates. You may examine the MCAI in the AD
docket on the Internet at https://www.regulations.gov by searching for
and locating Docket No. FAA-2015-7533.
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 pylon bolts at four positions at the forward engine pylon 1 and
pylon 2 of Airbus Model A330 series airplanes having Pratt and Whitney
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 pylon bolts at four positions at the forward engine pylon 1 and
pylon 2 of Airbus Model A330 series airplanes having 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 pylon
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 pylon 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 of this
NPRM.
Other Related Rulemaking
On June 21, 2013, we issued AD 2013-14-04, Amendment 39-17509 (78
FR 68352, November 14, 2013). AD 2013-14-04 requires a torque check of
forward engine mount bolts, and replacement if necessary on all Airbus
Model A330-223F, -223, -321, -322, and -323 airplanes. AD 2013-14-04
was
[[Page 81218]]
prompted by a fatigue load analysis that determined that the inspection
interval for certain pylon bolts must be reduced. We issued AD 2013-04-
04 to detect and correct loose or broken bolts, which could lead to
engine detachment in-flight, and damage to the airplane.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 55 airplanes of U.S.
registry.
We also estimate that it would take about 12 work-hours per product
to comply with the basic requirements of this proposed 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 proposed AD on U.S. operators to be $60,755, or $1,105 per
product.
In addition, we estimate that any necessary follow-on actions would
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 OMB control number. The control
number for the collection of information required by this proposed AD
is 2120-0056. The paperwork cost associated with this proposed 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 proposed AD is mandatory. Comments concerning the
accuracy of this burden and suggestions for reducing the burden should
be directed to the FAA at 800 Independence Ave. SW., Washington, DC
20591, ATTN: Information Collection Clearance Officer, AES-200.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2015-7533; Directorate Identifier 2015-NM-
080-AD.
(a) Comments Due Date
We must receive comments by February 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 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
[[Page 81219]]
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 Airbus Service Bulletin A330-
71-3028, Revision 01, dated February 20, 2012, 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 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 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 bolt, and, within 2,350 flight cycles or 24,320 flight
hours since first flight of the airplane, whichever occurs first,
replace the 4 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 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 bolt, and within 2,350 flight cycles or 24,320 flight
hours since first flight of the airplane, whichever occurs first,
replace the 4 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 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 bolt and within 2,140 flight cycles or 6,600
flight hours since first flight of the airplane, whichever occurs
first, replace the 4 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 bolts and associated nuts in accordance with the
instructions of Section 4.2.3, ``Findings,'' of AOT A71L004-14,
Revision 01, dated April 7, 2014.
(A) 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) 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) 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 bolts are found that rotate: Before further
flight, replace the 4 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 pylon bolts are found fully broken: Before
further flight, replace the 4 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 bolt is found that rotates: Before further
flight, re-torque the affected bolt, and replace the 4 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 bolts are found that rotate: Before further
flight, replace the 4 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 pylon bolts are found fully broken: Before
further flight, replace the 4 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.
(i) Concurrent Actions
AD 2013-14-04, Amendment 39-17509 (78 FR 68352, November 14,
2013), requires a torque check of forward 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 within the compliance times specified in paragraph (g) of the
FAA AD 2013-14-04 using Airbus Service Bulletin A330-71-3028,
Revision 01, dated February 20, 2012, perform the torque check of
the AFT engine mount bolts at the same time.
(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 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 bolts, as
applicable, and their associated nuts with new 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 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 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 pylon 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 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 bolts and associated nuts with new 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 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 pylon 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,
[[Page 81220]]
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 bolt rotates, two or more
bolts rotate, or one or more 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
Rolls-Royce Trent 500 Engines
(1) For Airbus Model A340-541 and -642 airplanes equipped with
Rolls-Royce 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 bolt rotates, two or more
bolts rotate, or one or more 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, dated
September 29, 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
pylon 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 Pratt and
Whitney 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
Rolls-Royce 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
Rolls-Royce Trent 500 Engines), which is not incorporated by
reference in this AD.
(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 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. 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 the
European Aviation Safety Agency (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
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2015-0082, dated May 11, 2015,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2015-7533.
(2) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You may view this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on December 18, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-32547 Filed 12-28-15; 8:45 am]
BILLING CODE 4910-13-P
