Airworthiness Directives; The Boeing Company Airplanes, 4775-4778 [2016-31959]
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Federal Register / Vol. 82, No. 10 / Tuesday, January 17, 2017 / Rules and Regulations
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–01–06 Airbus: Amendment 39–18773;
Docket No. FAA–2016–9110; Directorate
Identifier 2015–NM–196–AD.
(a) Effective Date
This AD is effective February 21, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A319–
115, A319–132, A320–214, A320–232, A321–
211, A321–213, and A321–231 airplanes,
certificated in any category, as identified in
Airbus Service Bulletin A320–52–1167,
dated August 6, 2015.
(d) Subject
Air Transport Association (ATA) of
America Code 52, Doors.
(e) Reason
This AD was prompted by a report of
certain tie rod assemblies installed on the
hinged fairing assembly of the main landing
gear (MLG) with no cadmium plating on the
rod end threads. We are issuing this AD to
detect and correct the absence of cadmium
plating on the rod end threads of the tie rod
assemblies. The absence of cadmium plating
could lead to galvanic corrosion of the tie rod
end threads, resulting in rod end failure, loss
of a MLG door, and consequent damage to
the airplane.
sradovich on DSK3GMQ082PROD with RULES
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection and Corrective Action
Within 80 months after the airplane’s first
flight, do a detailed inspection of each tie rod
assembly having a part number (P/N)
D52840212000 or D52840212002 at the MLG
hinged fairing for the presence of cadmium
plating (gold colored threads), in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–52–1167,
dated August 6, 2015. If during the
inspection any tie rod assembly is found that
does not have cadmium plating, before
further flight, replace the tie rod assembly
with a serviceable part having the same part
number and cadmium plating, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–52–1167,
dated August 6, 2015.
(h) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
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Jkt 241001
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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) 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.
(i) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0234, dated
December 8, 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–2016–9110.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320–52–1167,
dated August 6, 2015.
(ii) Reserved.
(3) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
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4775
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
December 23, 2016.
Thomas Groves,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–31961 Filed 1–13–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–7419; Directorate
Identifier 2015–NM–189–AD; Amendment
39–18769; AD 2017–01–02]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 787–8 and
787–9 airplanes. This AD was prompted
by a report that some inboard and
outboard trailing edge flap rotary
actuators may have been assembled
with an incorrect no-back brake rotorstator stack sequence during
manufacturing. This AD requires
inspecting the trailing edge flap rotary
actuator, and replacing the rotary
actuator or doing related investigative
and corrective actions if necessary. We
are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective February 21,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of February 21, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC
SUMMARY:
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Federal Register / Vol. 82, No. 10 / Tuesday, January 17, 2017 / Rules and Regulations
110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; 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. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
7419.
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–
7419; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Fnu
Winarto, Aerospace Engineer, Systems
and Equipment Branch, ANM–130S,
FAA, Seattle Aircraft Certification
Office (ACO), 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–
917–6659; fax: 425–917–6590; email:
fnu.winarto@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 787–8 and 787–9 airplanes. The
NPRM published in the Federal
Register on July 12, 2016 (81 FR 45070)
(‘‘the NPRM’’). The NPRM was
prompted by a report that some inboard
and outboard trailing edge flap rotary
actuators may have been assembled
with an incorrect no-back brake rotorstator stack sequence during
manufacturing. The NPRM proposed to
require an inspection of the inboard and
outboard flap trailing edge rotary
actuator for any discrepant rotary
actuator. For discrepant rotary actuators,
the NPRM proposed to require replacing
the rotary actuator, or alternatively,
determining the flight cycles on the
rotary actuator, and doing related
investigative and corrective actions if
necessary. We are issuing this AD to
detect and replace rotary actuators
having incorrect assembly, which could
cause accelerated unit wear that will
eventually reduce braking performance.
This degradation could lead to loss of
no-back brake function and reduced
controllability of the airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response. Boeing stated that it
supported the NPRM. United Airlines
(UAL) stated that it supported the
compliance time in the NPRM.
Request for the Manufacturer To ReEvaluate Its Warranty Policy
UAL requested that Boeing reevaluate its warranty policy. UAL stated
that an incorrect stack sequence
occurred during the manufacturing
process and that operators should not be
penalized for having to perform the test
and replacement of the rotary actuators.
We partially agree with the request.
We agree that this is a manufacturing
issue. However, we have not revised
this final rule in this regard because we
do not regulate Boeing’s warranty
policy.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
as proposed, except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin B787–81205–SB270032–00,
Issue 001, dated November 3, 2015. The
service information describes
procedures for an inspection of the
inboard and outboard flap rotary
actuator for any discrepant rotary
actuator, and procedures for replacing
the rotary actuator, or determining the
flight cycles on the rotary actuator and
doing applicable related investigative
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.
Costs of Compliance
We estimate that this AD affects 5
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
Inspection ................................
1 work-hour × $85 per hour = $85 .........................................
$0
$85
$425
We estimate the following costs to do
any necessary on-condition actions that
will be required based on the results of
the inspection. We have no way of
determining the number of aircraft that
might need this replacement:
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ON-CONDITION COSTS
Cost per
product
Action
Labor cost
Check to determine flight cycles on the rotary actuator.
Functional test ..............................................................
Replacement .................................................................
1 work-hour × $85 per hour = $85 ...............................
$0
$85
2 work-hours × $85 per hour = $170 ...........................
2 work-hours × $85 per hour = $170 ...........................
$0
$0
$170
$170
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Parts cost
17JAR1
Federal Register / Vol. 82, No. 10 / Tuesday, January 17, 2017 / Rules and Regulations
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
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
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.
sradovich on DSK3GMQ082PROD with RULES
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
VerDate Sep<11>2014
16:30 Jan 13, 2017
Jkt 241001
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
2017–01–02 The Boeing Company:
Amendment 39–18769; Docket No.
FAA–2016–7419; Directorate Identifier
2015–NM–189–AD.
(a) Effective Date
This AD is effective February 21, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 787–8 and 787–9 airplanes,
certificated in any category, as identified in
Boeing Alert Service Bulletin B787–81205–
SB270032–00, Issue 001, dated November 3,
2015.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Control Systems.
(e) Unsafe Condition
This AD was prompted by a report that
some inboard and outboard trailing edge flap
rotary actuators may have been assembled
with an incorrect no-back brake rotor-stator
stack sequence during manufacturing. We are
issuing this AD to detect and replace rotary
actuators having incorrect assembly, which
could cause accelerated unit wear that will
eventually reduce braking performance. This
degradation could lead to loss of no-back
brake function and reduced controllability of
the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection and Other Actions
Within 60 months after the effective date
of this AD, do an inspection of the inboard
and outboard trailing edge flap rotary
actuator for any discrepant rotary actuator, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
B787–81205–SB270032–00, Issue 001, dated
November 3, 2015. If any discrepant rotary
actuator is found, within 60 months after the
effective date of this AD, do the actions
specified in paragraph (g)(1) or (g)(2) of this
AD, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
B787–81205–SB270032–00, Issue 001, dated
November 3, 2015.
(1) Replace the discrepant rotary actuator.
(2) Check the maintenance records to
determine the flight cycles of each discrepant
rotary actuator and, within 60 months after
the effective date of this AD, do all applicable
related investigative and corrective actions.
(h) 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,
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4777
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 (i) 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,
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
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) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
paragraphs (h)(4)(i) and (h)(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. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. 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.
(i) Related Information
For more information about this AD,
contact Fnu Winarto, Aerospace Engineer,
Systems and Equipment Branch, ANM–130S,
FAA, Seattle ACO, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–917–
6659; fax: 425–917–6590; email:
fnu.winarto@faa.gov.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin B787–
81205–SB270032–00, Issue 001, dated
November 3, 2015.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet https://
www.myboeingfleet.com.
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Federal Register / Vol. 82, No. 10 / Tuesday, January 17, 2017 / Rules and Regulations
(4) 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
December 27, 2016.
Jeffrey E. Duven,
Manager,Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2016–31959 Filed 1–13–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0797; Directorate
Identifier 2013–NM–007–AD; Amendment
39–18776; AD 2017–01–09]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 767–300
and 767–300F series airplanes. This AD
was prompted by reports of
malfunctions in the flight deck display
units, which resulted in blanking,
blurring, or loss of color on the display.
This AD requires modification and
installation of components in the main
equipment center. For certain other
airplanes this AD requires modification,
replacement, and installation of flight
deck air relief system (FDARS)
components. We are issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
sradovich on DSK3GMQ082PROD with RULES
DATES:
This AD is effective February 21,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 21, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC
110–SK57, Seal Beach, CA 90740–5600;
telephone: 562–797–1717; Internet:
VerDate Sep<11>2014
16:30 Jan 13, 2017
Jkt 241001
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. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2013–
0797.
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–2013–
0797; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Francis Smith, Aerospace Engineer,
Cabin Safety and Environmental
Controls Branch, ANM–150S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6596;
fax: 425–917–6590; email:
francis.smith@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD
that would apply to certain The Boeing
Company Model 767–300 and 767–300F
series airplanes. The SNPRM published
in the Federal Register on May 27, 2016
(81 FR 33612) (‘‘the SNPRM’’). We
preceded the SNPRM with a notice of
proposed rulemaking (NPRM) that
published in the Federal Register on
September 25, 2013 (78 FR 58970) (‘‘the
NPRM’’). The NPRM proposed to
require modification and installation of
components in the main equipment
center. For certain other airplanes, the
NPRM proposed to require
modification, replacement, and
installation of FDARS components. The
NPRM was prompted by reports of
malfunctions in the flight deck display
units, which resulted in blanking,
blurring, or loss of color on the display.
The SNPRM proposed to revise the
applicability, add certain modifications,
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and clarify certain requirements. We are
issuing this AD to prevent malfunctions
of the flight deck display units, which
could affect the ability of the flight crew
to read the displays for airplane
attitude, altitude, or airspeed, and
consequently reduce the ability of the
flight crew to maintain control of the
airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the SNPRM and the FAA’s
response to each comment.
Support for the SNPRM
The Air Line Pilots Association,
International supported the intent of the
SNPRM.
Effect of Winglets on Accomplishment
of the Specified Actions
Aviation Partners Boeing stated that
the installation of winglets per
Supplemental Type Certificate (STC)
ST01920SE does not affect the
accomplishment of the manufacturer’s
service instructions.
We agree with the commenter that
STC ST01920SE does not affect the
accomplishment of the manufacturer’s
service instructions. Therefore, the
installation of STC ST01920SE does not
affect the ability to accomplish the
actions required by this AD. We have
not changed this final rule in this
regard.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
as proposed, except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the SNPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM.
Related Service Information Under 1
CFR Part 51
We reviewed the following service
information.
• Boeing Service Bulletin 767–21–
0235, dated October 8, 2009; and
Revision 1, dated July 29, 2011 (‘‘SB
767–21–0235, R1’’). The service
information describes procedures for a
relay installation and related wiring
changes (which change (modify) the 3way valve control logic for the cooling
system for the flight deck display
equipment on freighter airplanes).
E:\FR\FM\17JAR1.SGM
17JAR1
Agencies
[Federal Register Volume 82, Number 10 (Tuesday, January 17, 2017)]
[Rules and Regulations]
[Pages 4775-4778]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-31959]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-7419; Directorate Identifier 2015-NM-189-AD;
Amendment 39-18769; AD 2017-01-02]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
The Boeing Company Model 787-8 and 787-9 airplanes. This AD was
prompted by a report that some inboard and outboard trailing edge flap
rotary actuators may have been assembled with an incorrect no-back
brake rotor-stator stack sequence during manufacturing. This AD
requires inspecting the trailing edge flap rotary actuator, and
replacing the rotary actuator or doing related investigative and
corrective actions if necessary. We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective February 21, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of February 21,
2017.
ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC
[[Page 4776]]
110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; 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. It is also available on the
Internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2016-7419.
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-
7419; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Fnu Winarto, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6659; fax: 425-917-6590; email:
fnu.winarto@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain The Boeing Company
Model 787-8 and 787-9 airplanes. The NPRM published in the Federal
Register on July 12, 2016 (81 FR 45070) (``the NPRM''). The NPRM was
prompted by a report that some inboard and outboard trailing edge flap
rotary actuators may have been assembled with an incorrect no-back
brake rotor-stator stack sequence during manufacturing. The NPRM
proposed to require an inspection of the inboard and outboard flap
trailing edge rotary actuator for any discrepant rotary actuator. For
discrepant rotary actuators, the NPRM proposed to require replacing the
rotary actuator, or alternatively, determining the flight cycles on the
rotary actuator, and doing related investigative and corrective actions
if necessary. We are issuing this AD to detect and replace rotary
actuators having incorrect assembly, which could cause accelerated unit
wear that will eventually reduce braking performance. This degradation
could lead to loss of no-back brake function and reduced
controllability of the airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response. Boeing stated that it supported the NPRM. United
Airlines (UAL) stated that it supported the compliance time in the
NPRM.
Request for the Manufacturer To Re-Evaluate Its Warranty Policy
UAL requested that Boeing re-evaluate its warranty policy. UAL
stated that an incorrect stack sequence occurred during the
manufacturing process and that operators should not be penalized for
having to perform the test and replacement of the rotary actuators.
We partially agree with the request. We agree that this is a
manufacturing issue. However, we have not revised this final rule in
this regard because we do not regulate Boeing's warranty policy.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD as proposed, except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin B787-81205-SB270032-00,
Issue 001, dated November 3, 2015. The service information describes
procedures for an inspection of the inboard and outboard flap rotary
actuator for any discrepant rotary actuator, and procedures for
replacing the rotary actuator, or determining the flight cycles on the
rotary actuator and doing applicable related investigative 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.
Costs of Compliance
We estimate that this AD affects 5 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspection........................ 1 work-hour x $85 per $0 $85 $425
hour = $85.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary on-condition
actions that will be required based on the results of the inspection.
We have no way of determining the number of aircraft that might need
this replacement:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Check to determine flight cycles on the 1 work-hour x $85 per hour = $85... $0 $85
rotary actuator.
Functional test............................ 2 work-hours x $85 per hour = $170. $0 $170
Replacement................................ 2 work-hours x $85 per hour = $170. $0 $170
----------------------------------------------------------------------------------------------------------------
[[Page 4777]]
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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2017-01-02 The Boeing Company: Amendment 39-18769; Docket No. FAA-
2016-7419; Directorate Identifier 2015-NM-189-AD.
(a) Effective Date
This AD is effective February 21, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 787-8 and 787-9
airplanes, certificated in any category, as identified in Boeing
Alert Service Bulletin B787-81205-SB270032-00, Issue 001, dated
November 3, 2015.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Control Systems.
(e) Unsafe Condition
This AD was prompted by a report that some inboard and outboard
trailing edge flap rotary actuators may have been assembled with an
incorrect no-back brake rotor-stator stack sequence during
manufacturing. We are issuing this AD to detect and replace rotary
actuators having incorrect assembly, which could cause accelerated
unit wear that will eventually reduce braking performance. This
degradation could lead to loss of no-back brake function and reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection and Other Actions
Within 60 months after the effective date of this AD, do an
inspection of the inboard and outboard trailing edge flap rotary
actuator for any discrepant rotary actuator, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin B787-
81205-SB270032-00, Issue 001, dated November 3, 2015. If any
discrepant rotary actuator is found, within 60 months after the
effective date of this AD, do the actions specified in paragraph
(g)(1) or (g)(2) of this AD, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin B787-81205-SB270032-
00, Issue 001, dated November 3, 2015.
(1) Replace the discrepant rotary actuator.
(2) Check the maintenance records to determine the flight cycles
of each discrepant rotary actuator and, within 60 months after the
effective date of this AD, do all applicable related investigative
and corrective actions.
(h) 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 (i) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) 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.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair 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) For service information that contains steps that are labeled
as Required for Compliance (RC), the provisions of paragraphs
(h)(4)(i) and (h)(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. If a step or substep is labeled ``RC Exempt,'' then the
RC requirement is removed from that step or substep. 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.
(i) Related Information
For more information about this AD, contact Fnu Winarto,
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA,
Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone:
425-917-6659; fax: 425-917-6590; email: fnu.winarto@faa.gov.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin B787-81205-SB270032-00, Issue
001, dated November 3, 2015.
(ii) Reserved.
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com.
[[Page 4778]]
(4) 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on December 27, 2016.
Jeffrey E. Duven,
Manager,Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2016-31959 Filed 1-13-17; 8:45 am]
BILLING CODE 4910-13-P