Airworthiness Directives; Airbus Airplanes, 59535-59539 [2016-20681]
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Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules
(h) Repair of the Skin Inner Surface
If any damage is found during any
inspection required by paragraph (g) of this
AD, before further flight, do all applicable
related investigative and correction actions,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2878, dated May 19, 2016, except as
required by paragraph (k)(2) of this AD.
(i) Terminating Action
Modification or repair of the inner skin
surfaces in accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2878, May 19, 2016,
terminates the repetitive inspections required
by paragraph (g) of this AD.
(j) Post Repair Inspection and Repairs
For airplanes on which a repair or
modification has been done in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–53A2878,
dated May 19, 2016: Except as required by
paragraph (k)(1) of this AD, at the applicable
time specified in table 3 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2878, dated May 19, 2016,
do detailed inspections to detect damage of
the repaired or modified areas, and do all
applicable corrective actions, in accordance
with Part 5 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2878, May 19, 2016, except as
required by paragraph (k)(2) of this AD. Do
all applicable corrective actions before
further flight. Repeat the inspections
thereafter at intervals not to exceed the
applicable time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2878, dated May 19, 2016.
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(k) Exceptions
(1) Where Boeing Alert Service Bulletin
747–53A2878, May 19, 2016, specifies a
compliance time ‘‘after the original issue date
of this service bulletin,’’ this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(2) If any cracking or corrosion is found
during any inspection required by this AD,
and Boeing Alert Service Bulletin 747–
53A2878, May 19, 2016, specifies to contact
Boeing for appropriate action: Before further
flight, repair the cracking or corrosion using
a method approved in accordance with the
procedures specified in paragraph (l) of this
AD.
(l) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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 manager of the ACO, send it to the
attention of the person identified in
paragraph (m)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
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17:56 Aug 29, 2016
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or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (k)(1)
and (k)(2) of this AD: For service information
that contains steps that are labeled as
Required for Compliance (RC), the provisions
of paragraphs (l)(4)(i) and (l)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. An AMOC is required
for any deviations to RC steps, including
substeps and identified figures.
(ii) Steps not labeled 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 RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(m) Related Information
(1) For more information about this AD,
contact Nathan Weigand, Aerospace
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle ACO, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–917–
6428; fax: 425–917–6590; email:
nathan.p.weigand@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.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.
Issued in Renton, Washington, on August
18, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–20683 Filed 8–29–16; 8:45 am]
BILLING CODE 4910–13–P
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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]
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 all
Airbus Model A330–223F, –223, –321,
–322, and –323 airplanes. The proposed
AD was prompted by fatigue load
analysis that determined the need for
certain reduced inspection intervals and
updated torque values of the forward
mount pylon bolts. This proposed AD
would 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 proposing this AD to detect and
correct loose or broken bolts, which
could lead to engine detachment in
flight, and damage to the airplane.
DATES: We must receive comments on
this proposed AD by October 14, 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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Airbus SAS,
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone: +33 5 61 93
36 96; fax: +33 5 61 93 45 80; email:
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
SUMMARY:
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Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules
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–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 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:
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Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–8849; Directorate Identifier
2015–NM–174–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
On June 21, 2013, we issued AD
2013–14–04, Amendment 39–17509 (78
FR 68352, November 14, 2013) (‘‘AD
2013–14–04’’). AD 2013–14–04 requires
actions intended to address the unsafe
condition identified in this NPRM on all
Airbus Model A330–223F, –223, –321,
–322, and –323 airplanes.
Since we issued AD 2013–14–04, we
have determined that it is necessary to
update the torque values of the forward
mount pylon bolts.
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,
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17:56 Aug 29, 2016
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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 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.
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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–2016–
8849.
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 to determine if
there are any 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.
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 the same
type design.
Costs of Compliance
We estimate that this proposed 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 proposed 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 proposed 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:
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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,
59537
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
certificated in any category, all manufacturer
serial numbers.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Air Transport Association (ATA) of
America Code 71, Powerplant.
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
(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 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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
(d) Subject
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2016–8849;
Directorate Identifier 2015–NM–174–AD.
(a) Comments Due Date
We must receive comments by October 14,
2016.
(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,
Comply with this AD within the
compliance times specified, unless already
done.
(g) Torque Check and Replacement
(1) At the applicable compliance time
specified in table 1 to paragraph (g) 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) 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 AD
terminates the requirements of AD 2013–14–
05.
TABLE 1 TO PARAGRAPH (g) OF THIS AD
Airplane models
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Model A330–321, –322,
and –323 airplanes with
AFT more than 132
minutes; and Model
A330–223 airplanes.
Model A330–321, –322,
and –323 airplanes with
AFT more than 132
minutes; and Model
A330–223 airplanes.
VerDate Sep<11>2014
Flight cycles accumulated as of
December 19, 2013 (the effective date of AD 2013–14–04),
either since last torque check
specified in Pratt & Whitney
Alert Service Bulletin PW4G–
100–A71–32, or since airplane’s first flight, as applicable
Torque check interval
(not to exceed)
Compliance time
0–1,850 .....................................
Within 2,350 flight cycles since the last torque check
as specified in Pratt & Whitney Alert Service Bulletin PW4G–100–A71–32, or since airplane’s first
flight, as applicable.
2,350 flight cycles or
24,320 flight hours,
whichever occurs first.
1,851–2,700 ..............................
Within 500 flight cycles after December 19, 2013
(the effective date of AD 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.
2,350 flight cycles or
24,320 flight hours,
whichever occurs first.
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TABLE 1 TO PARAGRAPH (g) OF THIS AD—Continued
Airplane models
Model A330–321, –322,
and –323 airplanes with
AFT 132 minutes or
less; and Model A330–
321, –322, and –323
airplanes on which the
AFT is not calculated on
a regular basis.
Model A330–321, –322,
and –323 airplanes with
AFT 132 minutes or
less; and Model A330–
321,–322, and –323 airplanes on which the
AFT is not calculated on
a regular basis.
Model A330–223F airplanes.
Flight cycles accumulated as of
December 19, 2013 (the effective date of AD 2013–14–04),
either since last torque check
specified in Pratt & Whitney
Alert Service Bulletin PW4G–
100–A71–32, or since airplane’s first flight, as applicable
0–1,450 .....................................
Within 1,950 flight cycles since the last torque check
performed as specified in Pratt & Whitney Alert
Service Bulletin PW4G–100–A71–32, or since airplane’s first flight, as applicable.
1,950 flight cycles or
20,210 flight hours,
whichever occurs first.
1,451–2,700 ..............................
Within 500 flight cycles after December 19, 2013
(the effective date of AD 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.
Within 2,140 flight cycles or 6,600 flight hours,
whichever occurs first since the last torque check
performed as specified in Pratt & Whitney Alert
Service Bulletin PW4G–100–A71–32, or since airplane’s first flight, as applicable.
1,950 flight cycles or
20,210 flight hours,
whichever occurs first.
Any ............................................
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(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 actions, this AD
requires repair before further flight 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).
(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) Provisions for Compliance With AD
2006–16–05
Accomplishment of the actions required by
paragraph (g) of this AD constitutes
compliance with 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
any INCO718 material, forward mount pylon
VerDate Sep<11>2014
Torque check interval
(not to exceed)
Compliance time
17:56 Aug 29, 2016
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bolt having Pratt & Whitney part number
54T670 on any airplane.
(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. This service information
is not incorporated by reference in this AD.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone: 425–227–1138; fax: 425–227–
1149. Information may be emailed to: 9ANM-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.
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2,140 flight cycles or
6,600 flight hours,
whichever occurs first.
(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 Design
Organization Approval (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) 2015–
0214, dated October 19, 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–2016–8849.
(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:
E:\FR\FM\30AUP1.SGM
30AUP1
Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules
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 August
18, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–20681 Filed 8–29–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9054; Directorate
Identifier 2016–NM–081–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model DHC–8–400
series airplanes. This AD was prompted
by reports of interior emergency lights
remaining ‘‘ON’’ following routine
operational checks of the emergency
light system. We are proposing this AD
to require changing the wiring gauge for
the affected emergency lights power
supplies wiring to prevent overheating
in the wires. Overheating can damage
the wire insulation, causing a fire.
DATES: We must receive comments on
this proposed AD by October 14, 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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Bombardier, Inc., QSeries Technical Help Desk, 123 Garratt
mstockstill on DSK3G9T082PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
17:56 Aug 29, 2016
Jkt 238001
Boulevard, Toronto, Ontario M3K 1Y5,
Canada; telephone 416–375–4000; fax
416–375–4539; email thd.qseries@
aero.bombardier.com; Internet https://
www.bombardier.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–2016–
9054; 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:
Assata Dessaline, Aerospace Engineer,
Avionics and Services Branch, ANE–
172, FAA, New York Aircraft
Certification Office (ACO), 1600 Stewart
Avenue, Suite 410, Westbury, NY
11590; telephone 516–228–7301; fax
516–794–5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–9054; Directorate Identifier
2016–NM–081–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
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2016–12,
dated May 11, 2016 (referred to after
this as the Mandatory Continuing
PO 00000
Frm 00022
Fmt 4702
Sfmt 4702
59539
Airworthiness Information, or ’’the
MCAI’’), to correct an unsafe condition
for certain Bombardier, Inc. Model
DHC–8–400 series airplanes. The MCAI
states:
There have been several reports of Interior
Emergency Lights remaining ‘‘ON’’ following
routine operational checks of the Emergency
Light System. During these events, the
system could not be deactivated and the
associated circuit breaker was also found
tripped. The events were caused by the
overheating of the negative interlock and
ground wires at the Emergency Light System
Power Supplies.
Investigation has determined that the wire
gauge of the negative interlock and ground
wiring is incompatible with the current load
experienced during the Emergency Light
System operational check and this has led to
the degradation of the wiring insulation.
This [Canadian] AD is being issued to
mandate the change of the wiring gauge from
22 to 20 American wire gauge (AWG) for the
affected Emergency Lights Power Supplies
wiring.
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–2016–
9054.
Related Service Information Under 1
CFR Part 51
We reviewed Bombardier Service
Bulletin 84–33–12, Revision A, dated
January 19, 2016. This service
information describes procedures for
changing the wiring gauge for the
affected emergency lights power
supplies wiring to prevent overheating
in the wires. This service information is
reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD
affects 52 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
E:\FR\FM\30AUP1.SGM
30AUP1
]]>Agencies
[Federal Register Volume 81, Number 168 (Tuesday, August 30, 2016)]
[Proposed Rules]
[Pages 59535-59539]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-20681]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-8849; Directorate Identifier 2015-NM-174-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 all
Airbus Model A330-223F, -223, -321, -322, and -323 airplanes. The
proposed AD was prompted by fatigue load analysis that determined the
need for certain reduced inspection intervals and updated torque values
of the forward mount pylon bolts. This proposed AD would 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 proposing this AD to detect
and correct loose or broken bolts, which could lead to engine
detachment in flight, and damage to the airplane.
DATES: We must receive comments on this proposed AD by October 14,
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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Airbus
SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93
45 80; email: 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
[[Page 59536]]
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-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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138;
fax: 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-8849;
Directorate Identifier 2015-NM-174-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
On June 21, 2013, we issued AD 2013-14-04, Amendment 39-17509 (78
FR 68352, November 14, 2013) (``AD 2013-14-04''). AD 2013-14-04
requires actions intended to address the unsafe condition identified in
this NPRM on all Airbus Model A330-223F, -223, -321, -322, and -323
airplanes.
Since we issued AD 2013-14-04, we have determined that it is
necessary to update the torque values of the forward mount pylon bolts.
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 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 https://www.regulations.gov by searching for and locating
Docket No. FAA-2016-8849.
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 to determine if there are any 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.
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 the same
type design.
Costs of Compliance
We estimate that this proposed 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 proposed 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
proposed 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:
[[Page 59537]]
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-2016-8849; Directorate Identifier 2015-NM-
174-AD.
(a) Comments Due Date
We must receive comments by October 14, 2016.
(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 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 and Replacement
(1) At the applicable compliance time specified in table 1 to
paragraph (g) 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) 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 AD terminates the requirements of AD 2013-14-05.
Table 1 to Paragraph (g) of This AD
----------------------------------------------------------------------------------------------------------------
Flight cycles
accumulated as of
December 19, 2013 (the
effective date of AD
2013-14-04), either
since last torque check Torque check interval
Airplane models specified in Pratt & Compliance time (not to exceed)
Whitney 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 cycles 2,350 flight cycles
airplanes with AFT more than 132 since the last torque or 24,320 flight
minutes; and Model A330-223 check as specified in hours, whichever
airplanes. Pratt & Whitney Alert occurs first.
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 cycles 2,350 flight cycles
airplanes with AFT more than 132 after December 19, 2013 or 24,320 flight
minutes; and Model A330-223 (the effective date of AD hours, whichever
airplanes. 2013-14-04), without occurs first.
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.
[[Page 59538]]
Model A330-321, -322, and -323 0-1,450................ Within 1,950 flight cycles 1,950 flight cycles
airplanes with AFT 132 minutes or since the last torque or 20,210 flight
less; and Model A330-321, -322, check performed as hours, whichever
and -323 airplanes on which the specified in Pratt & occurs first.
AFT is not calculated on a regular Whitney Alert Service
basis. 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 cycles 1,950 flight cycles
airplanes with AFT 132 minutes or after December 19, 2013 or 20,210 flight
less; and Model A330-321,-322, and (the effective date of AD hours, whichever
-323 airplanes on which the AFT is 2013-14-04), without occurs first.
not calculated on a regular basis. 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 cycles 2,140 flight cycles
or 6,600 flight hours, or 6,600 flight
whichever occurs first hours, whichever
since the last torque occurs first.
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 actions, this AD requires repair before
further flight 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).
(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) Provisions for Compliance With AD 2006-16-05
Accomplishment of the actions required by paragraph (g) of this
AD constitutes compliance with 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 any INCO718 material, forward mount pylon bolt
having Pratt & Whitney part number 54T670 on any airplane.
(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. This
service information is not incorporated by reference in this AD.
(k) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149.
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding district
office. The AMOC approval letter must specifically reference this
AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA Design
Organization Approval (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) 2015-0214, dated October 19, 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-
2016-8849.
(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:
[[Page 59539]]
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 August 18, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-20681 Filed 8-29-16; 8:45 am]
BILLING CODE 4910-13-P
