Airworthiness Directives; Airbus Airplanes, 78085-78088 [2016-26521]
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Federal Register / Vol. 81, No. 215 / Monday, November 7, 2016 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA– 2016–9305; Directorate
Identifier 2016–NM–073–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2012–22–
12, for all Airbus Model A330–243,
–243F, –341, –342, and –343 airplanes.
AD 2012–22–12 currently requires
inspecting piccolo tubes, piccolo tube
mount links, the aft side of the forward
bulkhead, and outer boundary angles
(OBAs) for cracks, fractures, and broken
links, and doing corrective actions if
necessary. Since we issued AD 2012–
22–12, we have received reports of loose
and missing attachment rivets of the
inner boundary angles (IBA) and OBA of
the forward bulkhead. This proposed
AD would retain certain requirements of
AD 2012–22–12, and add repetitive
inspections for pulled, loose, and
missing attachment rivets of the IBA
and OBA of the forward bulkhead, and
related investigative and corrective
actions if necessary. We are proposing
this AD to detect and correct degraded
structural integrity of the engine nose
cowl, which in the case of forward
bulkhead damage in conjunction with a
broken piccolo tube, could lead to
damage to the engine and operation in
icing conditions with reduced thermal
anti-ice (TAI) performance.
DATES: We must receive comments on
this proposed AD by December 22,
2016.
SUMMARY:
You may send comments 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
p.m., Monday through Friday, except
Federal holidays.
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ADDRESSES:
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For Airbus 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.
For Rolls-Royce service information
identified in this NPRM, contact RollsRoyce Plc, Technical Publications, P.O.
Box 31, Derby, DE24 8BJ, United
Kingdom; telephone 44 (0) 1332 245882;
fax 44 (0) 1332 249936; Internet https://
www.Rolls-Royce.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–
9305; 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–2016–9305; Directorate Identifier
2016–NM–073–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
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78085
substantive verbal contact we receive
about this proposed AD.
Discussion
On October 26, 2012, we issued AD
2012–22–12, Amendment 39–17248 (77
FR 67263, November 9, 2012) (‘‘AD
2012–22–12’’). AD 2012–22–12 requires
actions intended to address an unsafe
condition on all Airbus Model 330–243,
–243F, –341, –342, and –343 airplanes.
Since we issued AD 2012–22–12, we
have received reports of loose or
missing attachment rivets of the IBA
and OBA of the forward bulkhead.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive, 2016–0086R1, dated May 13,
2016 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model 330–243, –243F, –341, –342, and
–343 airplanes. The MCAI states:
During shop visit, cracks were found in
several primary structural parts of Rolls
Royce (RR) Trent 700 engine air intake cowls,
specifically in the forward bulkhead web,
web stiffeners and outer boundary angles
(OBA). In addition, several attachment links
were found severely worn, and some became
detached. In two cases, the thermal anti-ice
(TAI) piccolo tube was found fractured.
Investigation results show that the cracks are
most likely due to acoustic excitation and
vibration.
A broken piccolo tube, if not detected and
corrected, in conjunction with forward air
intake cowl bulkhead damage, could lead to
in-flight detachment of the outer barrel,
possibly resulting in damage to the engine or
reduced control of the aeroplane.
To address this potential unsafe condition,
Airbus issued Service Bulletin (SB) A330–
71–3025, making reference to RR SB RB.211–
71–AG416, to provide inspection
instructions, and, depending on findings,
accomplishment of applicable corrective
action(s).
Consequently, EASA issued AD 2011–0062
[https://ad.easa.europa.eu/blob/easa_ad_
2011_0062_superseded.pdf/AD_2011-0062_
1] [which corresponds to FAA AD 2012–22–
12] to require repetitive special detailed
inspections (SDI) [borescope] of the piccolo
tube and affected mount links, the aft side of
forward bulkhead, inner boundary angles
(IBA) and OBA of the RR Trent 700 air intake
cowl assemblies, and, depending on findings,
accomplishment of applicable corrective
action(s).
Since EASA AD 2011–0062 was issued,
some occurrences were reported of finding
attachment rivets of the IBA and OBA either
pulled, loose, or missing during inspection.
It was determined that the affected IBA and
OBA rivets may not have been previously
inspected if operators accomplished the
required inspection in accordance with the
instructions of RR SB RB.211–71–AG416 at
original issue.
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Federal Register / Vol. 81, No. 215 / Monday, November 7, 2016 / Proposed Rules
To address this potentially missed
inspection, Airbus published SB A330–71–
3033, providing instructions for a one-time
detailed inspection of the IBA and OBA
attachment rivets, to be accomplished if the
previous inspection was accomplished using
the instructions of RR SB RB.211–71–AG416
at original issue. Airbus also published SB
A330–71–3025 Revision 2, adding an
inspection of the IBA and OBA attachment
rivets, to be used if the previous inspection
was accomplished using RR SB RB.211–71–
AG416 at issue 1 or later. Airbus also
published SB A330–71–3032 to introduce a
modification (mod) that would eliminate the
need for repetitive inspections.
For the reasons described above, this
[EASA] AD partially retains the requirements
of EASA AD 2011–0062, which is
superseded, and requires an additional
[special] detailed inspection [borescope] of
IBA and OBA forward bulkhead attachment
rivets. This [EASA] AD also introduces an
optional terminating action (Airbus mod
204615, embodied in production, which can
be embodied in service with Airbus SB
A330–71–3032) for the repetitive inspections
required by this [EASA] AD.
This [EASA] AD is revised to improve
clarity, including Airbus and RR SB
references and inserting Notes to identify the
Part Numbers (P/N) of the affected engine air
intake nose cowl assemblies.
Related investigative actions include
inspecting for cracked or fractured
piccolo tubes and for broken piccolo
tube links. Corrective actions include
replacing the engine air intake cowl
assembly and repair of pulled, loose, or
missing rivets.
supporting structure on the engine air
intake cowl assemblies.
Airbus has issued Service Bulletin
A330–71–3033, dated December 14,
2015. This service information describes
procedures for doing an inspection for
pulled, loose, and missing attachment
rivets of the IBA and OBA of the
forward bulkhead of the forward
bulkhead, and corrective actions.
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.
The compliance times for the related
investigative and corrective actions
range from before further flight to
within 100 flight cycles, depending on
the findings of the inspections.
The repetitive inspection interval for
the IBA, OBA, and forward bulkhead
varies depending on inspection
findings, and ranges between 200 and
5,000 flight cycles. The repetitive
inspection interval for the piccolo tubes
and links is 2,500 flight cycles.
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–
9305.
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.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A330–71–3025, Revision 02, including
Appendices 01 and 02, dated December
9, 2015. This service information
describes procedures for doing
inspections of the piccolo tube and
mount links, the aft side of the forward
bulkhead, the IBA, OBA, and the
forward bulkhead on the engine air
intake cowl assemblies; and related
investigative and corrective actions.
Airbus has issued Service Bulletin
A330–71–3032, dated December 10,
2014. This service information describes
procedures for doing a modification that
improves the air intake primary
structure and adds a new piccolo tube
Costs of Compliance
We estimate that this proposed AD
affects 47 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
Inspections (new proposed action) .................
12 work-hours × $85 per hour = $1,020 per
inspection cycle.
$0
$1,020 per
inspection
cycle
$47,940 per
inspection
cycle.
ESTIMATED COSTS FOR OPTIONAL ACTIONS
Action
Labor cost
Parts cost
Modification ........
Up to 142 work-hours × $85 per hour = $12,070 ..................................
[1]
Cost per product
Up to $12,070.
[1] We
have received no definitive data that would enable us to provide material cost estimates for the optional actions specified in this proposed AD.
We estimate the following costs to do
any necessary repairs that would be
required based on the results of the
proposed inspection. We have no way of
determining the number of aircraft that
might need these repairs:
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ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per
product
Repairs .....................
16 work-hours × $85 per hour = $1,360 ..........................................................................
[2]
$1,360
[2] We
have received no definitive data that would enable us to provide material cost estimates for the on-condition actions specified in this proposed AD.
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Federal Register / Vol. 81, No. 215 / Monday, November 7, 2016 / Proposed Rules
Authority for This Rulemaking
§ 39.13
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.
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2012–22–12, Amendment 39–17248 (77
FR 67263, November 9, 2012), and
adding the following new AD: Airbus:
Docket No. FAA–2016–9305; Directorate
Identifier 2016–NM–073–AD.
(a) Comments Due Date
We must receive comments by December
22, 2016.
(b) Affected ADs
This AD replaces AD 2012–22–12,
Amendment 39–17248 (77 FR 67263,
November 9, 2012) (‘‘AD 2012–22–12’’).
(c) Applicability
This AD applies to Airbus Model A330–
243, –243F, –341, –342, and –343 airplanes,
certificated in any category, all serial
numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 71, Powerplant.
(e) Reason
This AD was prompted by reports of
cracking of air intake cowls on Rolls-Royce
Trent engines, worn and detached
attachment links, and fractured thermal antiice (TAI) piccolo tubes, and loose, or missing
attachment rivets of the inner boundary
angles (IBA) and the outer boundary angles
(OBA) of the forward bulkhead. We are
issuing this AD to detect and correct
degraded structural integrity of the engine
nose cowl, which in the case of forward
bulkhead damage in conjunction with a
broken piccolo tube, could lead to damage to
the engine and operation in icing conditions
with reduced thermal anti-ice (TAI)
performance.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Affected Engine Air Intake Nose Cowl
Assemblies
The engine air intake nose cowl assemblies
affected by this AD have part number (P/N)
SJ30020, P/N SJ30361, P/N SJ30687, P/N
SJ30810, and P/N SJ30811, as specified in
Rolls-Royce Service Bulletin RB.211–71–
H205, dated July 7, 2014.
(1) The engine air intake nose cowl
assemblies having P/N SJ30020, P/N SJ30361,
and P/N SJ30687 can be modified (reworked
and re-identified as P/N SJ30810 (for P/N
SJ30020, P/N SJ30361) and P/N SJ30811 (for
P/N SJ30687)), as specified in Rolls-Royce
Service Bulletin RB.211–71–H205, dated July
7, 2014.
(2) The engine air intake nose cowl
assemblies having P/N SJ30810 and P/N
SJ30811 can be modified (reworked and reidentified as P/N SJ30820 and P/N SJ30821,
respectively), as specified in Rolls-Royce
Service Bulletin RB.211–71–H847, dated
December 2, 2014.
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(h) Inspections, Related Investigative
Actions, and Corrective Actions
For airplanes in pre-Airbus Modification
204615 and pre-Airbus Service Bulletin
A330–71–3032 configuration: At the
applicable times specified in paragraph (h)(1)
or (h)(2) of this AD, do a special detailed
inspection of the piccolo tube and affected
mount links, the aft side of the forward
bulkhead, and the IBA and OBA of the
affected engine air intake cowl assemblies
specified in paragraph (g) of this AD; and do
all applicable related investigative and
corrective actions; in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–71–3025, Revision 02,
including Appendices 01 and 02, dated
December 9, 2015, except as required by
paragraph (i) of this AD. Do all applicable
related investigative and corrective actions at
the applicable time specified in paragraph
1.E., ‘‘Compliance,’’ of Airbus Service
Bulletin A330–71–3025, Revision 02,
including Appendices 01 and 02, dated
December 9, 2015. Repeat the inspections of
the piccolo tube and affected mount links,
the aft side of the forward bulkhead, and the
IBA and OBA of the engine air intake cowl
assemblies thereafter at the applicable
intervals specified in paragraph 1.E.,
‘‘Compliance,’’ of Airbus Service Bulletin
A330–71–3025, Revision 02, including
Appendices 01 and 02, dated December 9,
2015. Accomplishment of corrective actions
does not constitute terminating action for the
repetitive inspections required by this
paragraph.
(1) For any engine air intake cowl assembly
that has accumulated fewer than 5,000 flight
cycles since its first installation on an
airplane as of the effective date of this AD:
Inspect within 24 months after the engine air
intake cowl assembly has accumulated 5,000
total flight cycles.
(2) For any engine air intake cowl assembly
that has accumulated 5,000 or more flight
cycles since its first installation on an
airplane as of the effective date of this AD:
Inspect within 24 months after the effective
date of this AD.
(i) Service Information Exception
Where Airbus Service Bulletin A330–71–
3025, Revision 02, including Appendices 01
and 02, dated December 9, 2015, specifies to
contact Bombardier Aerospace-Shorts for
instructions, 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).
(j) Optional Terminating Action
Modification of an airplane in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–71–3032,
dated December 10, 2014, constitutes
terminating action for the repetitive
inspections required by paragraph (h) of this
AD for the modified airplane only.
(k) Parts Installation Limitation
As of the effective date of this AD, any preAirbus modification 204615 part may be
installed on any airplane provided that, at
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Federal Register / Vol. 81, No. 215 / Monday, November 7, 2016 / Proposed Rules
the earlier of the applicable times specified
in paragraphs (h)(1) and (h)(2) of this AD
following installation, the actions required by
paragraph (h) of this AD have been
accomplished on the pre-Airbus Modification
204615 part.
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(l) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (h) of this AD, if those
actions were performed before the effective
date of this AD using Airbus Service Bulletin
A330–71–3025, dated January 10, 2011; or
Airbus Service Bulletin A330–71–3025,
Revision 01, dated October 24, 2012;
provided that, within 1,050 flight cycles after
the effective date of this AD, a special
detailed inspection for pulled, loose, and
missing attachment rivets of the IBA and
OBA of the forward bulkhead is
accomplished; and all applicable corrective
actions are done; in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–71–3033, dated
December 14, 2015. Do all applicable
corrective actions before further flight.
Accomplishment of corrective actions does
not constitute terminating action for the
repetitive inspections required by paragraph
(h) of this AD.
(m) 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.
(i) 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.
(ii) AMOCs approved previously in
accordance with 2012–22–12 are not
approved as AMOCs with 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
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) Required for Compliance (RC): If any
service information contains procedures or
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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.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0086R1, dated
May 13, 2016, 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–
2016–9305.
(2) For Airbus 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.A330A340@airbus.com; Internet https://
www.airbus.com.
(3) For Rolls-Royce service information
identified in this AD, contact Rolls-Royce
Plc, Technical Publications, P.O. Box 31,
Derby, DE24 8BJ, United Kingdom; telephone
44 (0) 1332 245882; fax 44 (0) 1332 249936;
Internet https://www.Rolls-Royce.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on October
28, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–26521 Filed 11–4–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2015–7115; Airspace
Docket No. 15–ANM–30]
Proposed Amendment of Class E
Airspace, Trinidad, CO
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
modify Class E surface area airspace,
and Class E airspace extending upward
from 700 feet above the surface, at Perry
Stokes Airport, Trinidad, CO. Airspace
SUMMARY:
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redesign is necessary to accommodate
new Area Navigation (RNAV) Standard
Instrument Approach Procedures at the
airport due to the decommissioning of
the Trinidad Non-Directional Radio
Beacon (NDB) and cancellation of
associated approaches. This action
would ensure the safety, efficiency, and
management of Instrument Flight Rules
(IFR) operations at the airport.
Additionally, the airport’s geographic
coordinates would be updated to match
the FAA’s aeronautical database.
DATES: Comments must be received on
or before December 22, 2016.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, 1200
New Jersey Avenue SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590; telephone: 1–
800–647–5527, or (202) 366–9826. You
must identify FAA Docket No. FAA–
2015–7115; Airspace Docket No. 15–
ANM–30, at the beginning of your
comments. You may also submit
comments through the Internet at https://
www.regulations.gov. You may review
the public docket containing the
proposal, any comments received, and
any final disposition in person in the
Dockets Office between 9:00 a.m. and
5:00 p.m., Monday through Friday,
except Federal holidays.
FAA Order 7400.11A, Airspace
Designations and Reporting Points, and
subsequent amendments can be viewed
online at https://www.faa.gov/air_traffic/
publications/. For further information,
you can contact the Airspace Policy
Group, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC, 20591;
telephone: 202–267–8783. The Order is
also available for inspection at the
National Archives and Records
Administration (NARA). For
information on the availability of FAA
Order 7400.11A at NARA, call 202–741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federalregulations/ibr_locations.html.
FAA Order 7400.11, Airspace
Designations and Reporting Points, is
published yearly and effective on
September 15.
FOR FURTHER INFORMATION CONTACT: Tom
Clark, Federal Aviation Administration,
Operations Support Group, Western
Service Center, 1601 Lind Avenue SW.,
Renton, WA 98057; telephone (425)
203–4511.
SUPPLEMENTARY INFORMATION:
Authority for This Rulemaking
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
E:\FR\FM\07NOP1.SGM
07NOP1
]]>Agencies
[Federal Register Volume 81, Number 215 (Monday, November 7, 2016)]
[Proposed Rules]
[Pages 78085-78088]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-26521]
[[Page 78085]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA- 2016-9305; Directorate Identifier 2016-NM-073-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-22-
12, for all Airbus Model A330-243, -243F, -341, -342, and -343
airplanes. AD 2012-22-12 currently requires inspecting piccolo tubes,
piccolo tube mount links, the aft side of the forward bulkhead, and
outer boundary angles (OBAs) for cracks, fractures, and broken links,
and doing corrective actions if necessary. Since we issued AD 2012-22-
12, we have received reports of loose and missing attachment rivets of
the inner boundary angles (IBA) and OBA of the forward bulkhead. This
proposed AD would retain certain requirements of AD 2012-22-12, and add
repetitive inspections for pulled, loose, and missing attachment rivets
of the IBA and OBA of the forward bulkhead, and related investigative
and corrective actions if necessary. We are proposing this AD to detect
and correct degraded structural integrity of the engine nose cowl,
which in the case of forward bulkhead damage in conjunction with a
broken piccolo tube, could lead to damage to the engine and operation
in icing conditions with reduced thermal anti-ice (TAI) performance.
DATES: We must receive comments on this proposed AD by December 22,
2016.
ADDRESSES: You may send comments 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 p.m., Monday
through Friday, except Federal holidays.
For Airbus 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.
For Rolls-Royce service information identified in this NPRM,
contact Rolls-Royce Plc, Technical Publications, P.O. Box 31, Derby,
DE24 8BJ, United Kingdom; telephone 44 (0) 1332 245882; fax 44 (0) 1332
249936; Internet https://www.Rolls-Royce.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-
9305; 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-2016-9305;
Directorate Identifier 2016-NM-073-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 October 26, 2012, we issued AD 2012-22-12, Amendment 39-17248
(77 FR 67263, November 9, 2012) (``AD 2012-22-12''). AD 2012-22-12
requires actions intended to address an unsafe condition on all Airbus
Model 330-243, -243F, -341, -342, and -343 airplanes.
Since we issued AD 2012-22-12, we have received reports of loose or
missing attachment rivets of the IBA and OBA of the forward bulkhead.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive, 2016-0086R1, dated May 13, 2016 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model 330-
243, -243F, -341, -342, and -343 airplanes. The MCAI states:
During shop visit, cracks were found in several primary
structural parts of Rolls Royce (RR) Trent 700 engine air intake
cowls, specifically in the forward bulkhead web, web stiffeners and
outer boundary angles (OBA). In addition, several attachment links
were found severely worn, and some became detached. In two cases,
the thermal anti-ice (TAI) piccolo tube was found fractured.
Investigation results show that the cracks are most likely due to
acoustic excitation and vibration.
A broken piccolo tube, if not detected and corrected, in
conjunction with forward air intake cowl bulkhead damage, could lead
to in-flight detachment of the outer barrel, possibly resulting in
damage to the engine or reduced control of the aeroplane.
To address this potential unsafe condition, Airbus issued
Service Bulletin (SB) A330-71-3025, making reference to RR SB
RB.211-71-AG416, to provide inspection instructions, and, depending
on findings, accomplishment of applicable corrective action(s).
Consequently, EASA issued AD 2011-0062 [https://ad.easa.europa.eu/blob/easa_ad_2011_0062_superseded.pdf/AD_2011-0062_1] [which corresponds to FAA AD 2012-22-12] to require
repetitive special detailed inspections (SDI) [borescope] of the
piccolo tube and affected mount links, the aft side of forward
bulkhead, inner boundary angles (IBA) and OBA of the RR Trent 700
air intake cowl assemblies, and, depending on findings,
accomplishment of applicable corrective action(s).
Since EASA AD 2011-0062 was issued, some occurrences were
reported of finding attachment rivets of the IBA and OBA either
pulled, loose, or missing during inspection. It was determined that
the affected IBA and OBA rivets may not have been previously
inspected if operators accomplished the required inspection in
accordance with the instructions of RR SB RB.211-71-AG416 at
original issue.
[[Page 78086]]
To address this potentially missed inspection, Airbus published
SB A330-71-3033, providing instructions for a one-time detailed
inspection of the IBA and OBA attachment rivets, to be accomplished
if the previous inspection was accomplished using the instructions
of RR SB RB.211-71-AG416 at original issue. Airbus also published SB
A330-71-3025 Revision 2, adding an inspection of the IBA and OBA
attachment rivets, to be used if the previous inspection was
accomplished using RR SB RB.211-71-AG416 at issue 1 or later. Airbus
also published SB A330-71-3032 to introduce a modification (mod)
that would eliminate the need for repetitive inspections.
For the reasons described above, this [EASA] AD partially
retains the requirements of EASA AD 2011-0062, which is superseded,
and requires an additional [special] detailed inspection [borescope]
of IBA and OBA forward bulkhead attachment rivets. This [EASA] AD
also introduces an optional terminating action (Airbus mod 204615,
embodied in production, which can be embodied in service with Airbus
SB A330-71-3032) for the repetitive inspections required by this
[EASA] AD.
This [EASA] AD is revised to improve clarity, including Airbus
and RR SB references and inserting Notes to identify the Part
Numbers (P/N) of the affected engine air intake nose cowl
assemblies.
Related investigative actions include inspecting for cracked or
fractured piccolo tubes and for broken piccolo tube links. Corrective
actions include replacing the engine air intake cowl assembly and
repair of pulled, loose, or missing rivets.
The compliance times for the related investigative and corrective
actions range from before further flight to within 100 flight cycles,
depending on the findings of the inspections.
The repetitive inspection interval for the IBA, OBA, and forward
bulkhead varies depending on inspection findings, and ranges between
200 and 5,000 flight cycles. The repetitive inspection interval for the
piccolo tubes and links is 2,500 flight cycles.
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-
9305.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A330-71-3025, Revision 02,
including Appendices 01 and 02, dated December 9, 2015. This service
information describes procedures for doing inspections of the piccolo
tube and mount links, the aft side of the forward bulkhead, the IBA,
OBA, and the forward bulkhead on the engine air intake cowl assemblies;
and related investigative and corrective actions.
Airbus has issued Service Bulletin A330-71-3032, dated December 10,
2014. This service information describes procedures for doing a
modification that improves the air intake primary structure and adds a
new piccolo tube supporting structure on the engine air intake cowl
assemblies.
Airbus has issued Service Bulletin A330-71-3033, dated December 14,
2015. This service information describes procedures for doing an
inspection for pulled, loose, and missing attachment rivets of the IBA
and OBA of the forward bulkhead of the forward bulkhead, and corrective
actions.
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 47 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspections (new proposed action)... 12 work-hours x $85 per $0 $1,020 per $47,940 per
hour = $1,020 per inspection inspection
inspection cycle. cycle cycle.
----------------------------------------------------------------------------------------------------------------
Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Modification.......................... Up to 142 work-hours x $85 [1] Up to $12,070.
per hour = $12,070.
----------------------------------------------------------------------------------------------------------------
[1] We have received no definitive data that would enable us to provide material cost estimates for the optional
actions specified in this proposed AD.
We estimate the following costs to do any necessary repairs that
would be required based on the results of the proposed inspection. We
have no way of determining the number of aircraft that might need these
repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Repairs................................... 16 work-hours x $85 per hour = [2] $1,360
$1,360.
----------------------------------------------------------------------------------------------------------------
[2] We have received no definitive data that would enable us to provide material cost estimates for the on-
condition actions specified in this proposed AD.
[[Page 78087]]
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 removing Airworthiness Directive (AD)
2012-22-12, Amendment 39-17248 (77 FR 67263, November 9, 2012), and
adding the following new AD: Airbus: Docket No. FAA-2016-9305;
Directorate Identifier 2016-NM-073-AD.
(a) Comments Due Date
We must receive comments by December 22, 2016.
(b) Affected ADs
This AD replaces AD 2012-22-12, Amendment 39-17248 (77 FR 67263,
November 9, 2012) (``AD 2012-22-12'').
(c) Applicability
This AD applies to Airbus Model A330-243, -243F, -341, -342, and
-343 airplanes, certificated in any category, all serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 71, Powerplant.
(e) Reason
This AD was prompted by reports of cracking of air intake cowls
on Rolls-Royce Trent engines, worn and detached attachment links,
and fractured thermal anti-ice (TAI) piccolo tubes, and loose, or
missing attachment rivets of the inner boundary angles (IBA) and the
outer boundary angles (OBA) of the forward bulkhead. We are issuing
this AD to detect and correct degraded structural integrity of the
engine nose cowl, which in the case of forward bulkhead damage in
conjunction with a broken piccolo tube, could lead to damage to the
engine and operation in icing conditions with reduced thermal anti-
ice (TAI) performance.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Affected Engine Air Intake Nose Cowl Assemblies
The engine air intake nose cowl assemblies affected by this AD
have part number (P/N) SJ30020, P/N SJ30361, P/N SJ30687, P/N
SJ30810, and P/N SJ30811, as specified in Rolls-Royce Service
Bulletin RB.211-71-H205, dated July 7, 2014.
(1) The engine air intake nose cowl assemblies having P/N
SJ30020, P/N SJ30361, and P/N SJ30687 can be modified (reworked and
re-identified as P/N SJ30810 (for P/N SJ30020, P/N SJ30361) and P/N
SJ30811 (for P/N SJ30687)), as specified in Rolls-Royce Service
Bulletin RB.211-71-H205, dated July 7, 2014.
(2) The engine air intake nose cowl assemblies having P/N
SJ30810 and P/N SJ30811 can be modified (reworked and re-identified
as P/N SJ30820 and P/N SJ30821, respectively), as specified in
Rolls-Royce Service Bulletin RB.211-71-H847, dated December 2, 2014.
(h) Inspections, Related Investigative Actions, and Corrective Actions
For airplanes in pre-Airbus Modification 204615 and pre-Airbus
Service Bulletin A330-71-3032 configuration: At the applicable times
specified in paragraph (h)(1) or (h)(2) of this AD, do a special
detailed inspection of the piccolo tube and affected mount links,
the aft side of the forward bulkhead, and the IBA and OBA of the
affected engine air intake cowl assemblies specified in paragraph
(g) of this AD; and do all applicable related investigative and
corrective actions; in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-71-3025, Revision 02,
including Appendices 01 and 02, dated December 9, 2015, except as
required by paragraph (i) of this AD. Do all applicable related
investigative and corrective actions at the applicable time
specified in paragraph 1.E., ``Compliance,'' of Airbus Service
Bulletin A330-71-3025, Revision 02, including Appendices 01 and 02,
dated December 9, 2015. Repeat the inspections of the piccolo tube
and affected mount links, the aft side of the forward bulkhead, and
the IBA and OBA of the engine air intake cowl assemblies thereafter
at the applicable intervals specified in paragraph 1.E.,
``Compliance,'' of Airbus Service Bulletin A330-71-3025, Revision
02, including Appendices 01 and 02, dated December 9, 2015.
Accomplishment of corrective actions does not constitute terminating
action for the repetitive inspections required by this paragraph.
(1) For any engine air intake cowl assembly that has accumulated
fewer than 5,000 flight cycles since its first installation on an
airplane as of the effective date of this AD: Inspect within 24
months after the engine air intake cowl assembly has accumulated
5,000 total flight cycles.
(2) For any engine air intake cowl assembly that has accumulated
5,000 or more flight cycles since its first installation on an
airplane as of the effective date of this AD: Inspect within 24
months after the effective date of this AD.
(i) Service Information Exception
Where Airbus Service Bulletin A330-71-3025, Revision 02,
including Appendices 01 and 02, dated December 9, 2015, specifies to
contact Bombardier Aerospace-Shorts for instructions, 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).
(j) Optional Terminating Action
Modification of an airplane in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-71-3032,
dated December 10, 2014, constitutes terminating action for the
repetitive inspections required by paragraph (h) of this AD for the
modified airplane only.
(k) Parts Installation Limitation
As of the effective date of this AD, any pre-Airbus modification
204615 part may be installed on any airplane provided that, at
[[Page 78088]]
the earlier of the applicable times specified in paragraphs (h)(1)
and (h)(2) of this AD following installation, the actions required
by paragraph (h) of this AD have been accomplished on the pre-Airbus
Modification 204615 part.
(l) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(h) of this AD, if those actions were performed before the effective
date of this AD using Airbus Service Bulletin A330-71-3025, dated
January 10, 2011; or Airbus Service Bulletin A330-71-3025, Revision
01, dated October 24, 2012; provided that, within 1,050 flight
cycles after the effective date of this AD, a special detailed
inspection for pulled, loose, and missing attachment rivets of the
IBA and OBA of the forward bulkhead is accomplished; and all
applicable corrective actions are done; in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-71-3033,
dated December 14, 2015. Do all applicable corrective actions before
further flight. Accomplishment of corrective actions does not
constitute terminating action for the repetitive inspections
required by paragraph (h) of this AD.
(m) 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.
(i) 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.
(ii) AMOCs approved previously in accordance with 2012-22-12 are
not approved as AMOCs with 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 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) Required for Compliance (RC): 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.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2016-0086R1, dated May 13, 2016,
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-2016-9305.
(2) For Airbus 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.
(3) For Rolls-Royce service information identified in this AD,
contact Rolls-Royce Plc, Technical Publications, P.O. Box 31, Derby,
DE24 8BJ, United Kingdom; telephone 44 (0) 1332 245882; fax 44 (0)
1332 249936; Internet https://www.Rolls-Royce.com.
(4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
Issued in Renton, Washington, on October 28, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-26521 Filed 11-4-16; 8:45 am]
BILLING CODE 4910-13-P
