Airworthiness Directives; General Electric Company Turbofan Engines, 70925-70928 [2016-24795]
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Federal Register / Vol. 81, No. 199 / Friday, October 14, 2016 / Rules and Regulations
Qinfiltration_83 = Qs_83 + Q 83
Where:
Qinfiltration_95 and Qinfiltration_83 = total
infiltration air heat in cooling mode,
calculated at the 95 °F and 83 °F drybulb outdoor conditions in Table 1 of
this appendix, in Btu/h.
Qs_95 and Qs_83 = sensible heat added to the
room by infiltration air, calculated at the
95 °F and 83 °F dry-bulb outdoor
conditions in Table 1 of this appendix,
in Btu/h.
Ql_95 and Ql_83 = latent heat added to the
room by infiltration air, calculated at the
95 °F and 83 °F dry-bulb outdoor
conditions in Table 1 of this appendix,
in Btu/h.
*
*
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*
*
[FR Doc. 2016–24869 Filed 10–13–16; 8:45 am]
BILLING CODE 6450–01–P
FARM CREDIT ADMINISTRATION
12 CFR Chapter VI
Farm Credit Administration Board
Policy Statements
Farm Credit Administration.
Notice of policy statements and
AGENCY:
ACTION:
index.
The Farm Credit
Administration (FCA), as part of its
annual public notification process, is
publishing for notice an index of the 18
Board policy statements currently in
existence. Most of the policy statements
remain unchanged since our last
Federal Register notice on November 2,
2015, except for one as discussed below
on Equal Employment Opportunity and
Diversity.
DATES: October 14, 2016.
FOR FURTHER INFORMATION CONTACT:
Dale L. Aultman, Secretary to Board,
Farm Credit Administration, 1501
Farm Credit Drive, McLean, Virginia
22102–5090, (703) 883–4009, TTY
(703) 883–4056; or
Mary Alice Donner, Senior Counsel,
Office of General Counsel, Farm
Credit Administration, 1501 Farm
Credit Drive, McLean, Virginia
22102–5090, (703) 883–4020, TTY
(703) 883–4020.
SUPPLEMENTARY INFORMATION: A list of
the 18 FCA Board policy statements is
set forth below. FCA Board policy
statements may be viewed online at
www.fca.gov/handbook.nsf.
On August 8, 2016, the FCA Board
updated FCA–PS–62 on, ‘‘Equal
Employment Opportunity and
Diversity.’’ The policy was published in
the Federal Register on August 12, 2016
(81 FR 53482). The policy was slightly
edited at the Equal Employment
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SUMMARY:
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Opportunity Commission’s
recommendation to indicate that FCA
begins prompt, thorough, and impartial
investigations within 10 days of
receiving notice of harassment
allegations.
The FCA will continue to publish
new or revised policy statements in
their full text.
DEPARTMENT OF TRANSPORTATION
FCA Board Policy Statements
Airworthiness Directives; General
Electric Company Turbofan Engines
FCA–PS–34 Disclosure of the Issuance
and Termination of Enforcement
Documents
FCA–PS–37 Communications During
Rulemaking
FCA–PS–41 Alternative Means of
Dispute Resolution
FCA–PS–44 Travel
FCA–PS–53 Examination Philosophy
FCA–PS–59 Regulatory Philosophy
FCA–PS–62 Equal Employment
Opportunity and Diversity
FCA–PS–64 Rules for the Transaction
of Business of the Farm Credit
Administration Board
FCA–PS–65 Release of Consolidated
Reporting System Information
FCA–PS–67 Nondiscrimination on the
Basis of Disability in Agency
Programs and Activities
FCA–PS–68 FCS Building Association
Management Operations Policies
and Practices
FCA–PS–71 Disaster Relief Efforts by
Farm Credit Institutions
FCA–PS–72 Financial Institution
Rating System (FIRS)
FCA–PS–77 Borrower Privacy
FCA–PS–78 Official Names of Farm
Credit Institutions
FCA–PS–79 Consideration and
Referral of Supervisory Strategies
and Enforcement Actions
FCA–PS–80 Cooperative Operating
Philosophy—Serving the Members
of Farm Credit System Institutions
FCA–PS–81 Ethics, Independence,
Arm’s-Length Role, Ex Parte
Communications and Open
Government
Dated: October 6, 2016.
Dale L. Aultman,
Secretary, Farm Credit Administration Board.
[FR Doc. 2016–24680 Filed 10–13–16; 8:45 am]
BILLING CODE 6705–01–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–5872; Directorate
Identifier 2016–NE–11–AD; Amendment 39–
18681; AD 2016–20–15]
RIN 2120–AA64
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
General Electric Company (GE) GEnx–
1B64/P2, –1B67/P2, –1B70/P2, –1B70C/
P2, –1B70/75/P2, and –1B74/75/P2
turbofan engines with engine assembly,
part number (P/N) 2447M10G01 or P/N
2447M10G02, installed. This AD was
prompted by a report of a significant fan
rub event. This AD requires rework of
the engine fan stator module assembly.
We are issuing this AD to prevent
failure of the fan blades and the load
reduction device, loss of power to one
or more engines, loss of thrust control,
and loss of the airplane.
DATES: This AD is effective November
18, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 18, 2016.
ADDRESSES: For service information
identified in this final rule, contact
General Electric Company, GE Aviation,
Room 285, 1 Neumann Way, Cincinnati,
OH 45215; phone: 513–552–3272; email:
aviation.fleetsupport@ge.com. You may
view this referenced service information
at the FAA, Engine & Propeller
Directorate, 1200 District Avenue,
Burlington, MA 01803. For information
on the availability of this material at the
FAA, call 781–238–7125. It is also
available on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
5872.
SUMMARY:
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–
5872; 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
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Docket Office (phone: 800–647–5527) is
Document 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:
Christopher McGuire, Aerospace
Engineer, Engine Certification Office,
FAA, Engine & Propeller Directorate,
1200 District Avenue, Burlington, MA
01803; phone: 781–238–7120; fax: 781–
238–7199; email: chris.mcguire@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 all GE GEnx–1B64/P2, –1B67/
P2, –1B70/P2, –1B70C/P2, –1B70/75/P2,
and –1B74/75/P2 turbofan engines with
engine assembly, P/N 2447M10G01 or
P/N 2447M10G02, installed. The NPRM
published in the Federal Register on
May 10, 2016 (81 FR 28777). The NPRM
was prompted by a report of a
significant fan rub event. The NPRM
proposed to require rework of the
engine fan stator module assembly. We
are issuing this AD to prevent failure of
the fan blades and the load reduction
device, loss of power to one or more
engines, loss of thrust control, and loss
of the airplane.
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Request To Add Terminating Action
Japan Airlines and United Airlines
requested that the airplane flight
manual (AFM) limitations mandated by
AD 2016–08–12, Amendment 39–18488
(81 FR 23581, April 22, 2016) (‘‘AD
2016–08–12’’), be removed from an
aircraft that has complied with the fan
case grind procedure mandated in this
AD. They reason that once the fan case
grind is completed on both engines
installed on an airplane, there is no
longer an unsafe condition.
We agree. Once the fan case grind has
been completed on both engines
installed on an airplane, the unsafe
condition no longer exists. With
agreement from the Transport Airplane
Directorate (TAD), we added a
terminating action paragraph to this AD.
Request To Add Compliance Methods
Japan Airlines requested that alternate
service documents be approved as
compliance to AD 2016–06–08,
Amendment 39–18439 (81 FR 14704,
March 18, 2016) (‘‘AD 2016–06–08’’).
They reason that the service documents
provide the same procedure and the
same post-rework configuration.
We disagree. AD 2016–06–08 is a
separate AD issued by the TAD, which
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includes aircraft-level corrective
actions. The commenter must contact
the TAD to request a change to AD
2016–06–08. We did not change this
AD.
Request To Change Applicability
GE requested that the applicability
explicitly state that engine assembly, P/
N 2447M10G03, is not applicable to this
AD. They reason that engine assembly,
P/N 2447M10G03, is a new production
part that does not contain the unsafe
condition.
We disagree. Since engine assembly,
P/N 2447M10G03, is not listed in the
applicability of this AD, it is not
applicable to this AD. We did not
change this AD.
Request To Change Compliance Method
GE requested that another procedure
included within a new service bulletin,
GE GEnx–1B Service Bulletin (SB) 72–
0317 R00, dated June 29, 2016, be added
as a means of compliance to this AD.
They reason that this new procedure
achieves the same configuration as the
proposed procedure.
We agree. The new procedure in GE
GEnx–1B SB 72–0317 R00, dated June
29, 2016, also corrects the unsafe
condition addressed in this AD. We
added GE GEnx–1B SB 72–0317 R00,
dated June 29, 2016, as a means of
compliance in this AD.
Request To Change Compliance Time
GE requested that we move the action
specified in paragraph (f) Credit for
Previous Action, to compliance
paragraph (e) of this AD. They reason
that this action is an equivalent method
of performing the fan case rework.
We agree. The action is equivalent to
the current compliance, but located
within a different service document. We
revised paragraph (f) and paragraph (e)
of this AD accordingly.
Request To Change Affected ADs
United Airlines requested that we list
AD 2016–06–08 and AD 2016–08–12 in
this AD. They reason that AD 2016–06–
08 and AD 2016–08–12 address the
same unsafe condition as this AD and
also mandate a fan case rework.
We agree. AD 2016–06–08 and AD
2016–08–12 address the same unsafe
condition as this AD. We list AD 2016–
06–08 and AD 2016–08–12 in paragraph
(h) of this AD.
Request To Change Affected ADs
United Airlines requested that we
supersede AD 2016–08–12 with this AD.
They reason that AD 2016–06–08 and
AD 2016–08–12 address the same
unsafe condition of the engine and
mandate a fan case rework procedure.
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We disagree. An AD that mandates
engine-level corrective actions, ‘‘this
AD’’, cannot supersede an AD, ‘‘AD
2016–08–12’’ that mandates aircraftlevel corrective actions. AD 2016–08–12
mandates aircraft limitations in addition
to the engine rework procedure that can
only be mandated at the aircraft level,
not the engine level. We did not change
this AD.
Request To Change Operating
Procedures
United Airlines requested that we
revise the operating procedures that
require the ice removal procedure to be
done every 5 minutes, rather than the
preferred every 5 minutes or less,
allowing the pilot to do the procedure
prior to 5 minutes after Engine
Indication and Crew Alerting System
(EICAS) notification. United Airlines
suggests the 5 minute requirement does
not allow pilots to effectively manage
the cockpit within reasonable
parameters or room to operate.
We disagree. The AFM operating
procedures are mandated by aircraftlevel AD 2016–06–08 and AD 2016–08–
12, which were issued by the TAD. The
commenter must contact the TAD to
request a change to AD 2016–06–08 or
AD 2016–08–12. We did not change this
AD.
Request To Change Compliance Time
United Airlines requested that we
allow installation of engine assembly, P/
N 2477M10G03, by using GE GEnx–1B
SB 72–0317 to modify the engine
instead of using the fan grind rework
procedure as compliance to AD 2016–
08–12. They reason that the procedure
in GE GEnx–1B SB 72–0317 achieves
the same engine outcome as the
currently mandated compliance.
We disagree. AD 2016–08–12 was
issued by the TAD. The commenter
must contact the TAD to request a
change to AD 2016–08–12. We did not
change this AD.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously.
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.
We also determined that these
changes will not increase the economic
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Federal Register / Vol. 81, No. 199 / Friday, October 14, 2016 / Rules and Regulations
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
We reviewed GE GEnx–1B SB 72–
0314 R00, dated April 1, 2016. The SB
describes procedures for increasing the
clearance of the fan stator module
assembly. We also reviewed GE GEnx–
1B SB 72–0309 R00, dated March 11,
2016. That SB describes procedures for
increasing the clearance of the fan stator
module assembly. We also reviewed GE
GEnx–1B SB 72–0317 R00, dated June
29, 2016. That SB releases a new fan
stator module assembly. This service
information is reasonably available
because the interested parties have
access to it through their normal course
of business or by the means identified
in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 89
engines installed on airplanes of U.S.
registry. We also estimate that it will
take about 40 hours per engine to
comply with this AD. The average labor
rate is $85 per hour. Based on these
figures, we estimate the total cost of this
AD to U.S. operators to be $302,600.
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.
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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.
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13:00 Oct 13, 2016
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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 to the extent that it justifies
making a regulatory distinction, 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.
(i) Use paragraphs 3.B.(1) through 3.B.(6) or
3.C.(1) through 3.C.(6) of the
Accomplishment Instructions of GE GEnx–1B
Service Bulletin (SB) 72–0314 R00, dated
April 1, 2016, to do the modification.
(ii) Use paragraphs 3.B.(1) through 3.B.(6)
or 3.C.(1) through 3.C.(6) of the
Accomplishment Instructions of GE GEnx–1B
SB 72–0309 R00, dated March 11, 2016, to do
the modification.
(iii) Use paragraph 3.A. of the
Accomplishment Instructions of GE GEnx–1B
SB 72–0317 R00, dated June 29, 2016, to do
the modification.
(2) Reserved.
List of Subjects in 14 CFR Part 39
Compliance with this AD constitutes
terminating action for AD 2016–06–08,
Amendment 39–18439 (81 FR 14704, March
18, 2016) (‘‘AD 2016–06–08’’) and AD 2016–
08–12, Amendment 39–18488 (81 FR 23581,
April 22, 2016) (‘‘AD 2016–08–12’’),
provided that all of the airplanes within the
operator’s fleet that have engines identified
in paragraph (c) of this AD are modified as
specified in paragraph (e) of this AD. After
fleet incorporation of this AD, do not install
any engine listed in paragraph (c) of this AD
unless the engine is modified as specified in
paragraph (e) of this AD, or AD 2016–06–08,
or AD 2016–08–12.
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
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):
■
2016–20–15 General Electric Company:
Amendment 39–18681; Docket No.
FAA–2016–5872; Directorate Identifier
2016–NE–11–AD.
(a) Effective Date
This AD is effective November 18, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all General Electric
Company (GE) GEnx–1B64/P2, –1B67/P2,
–1B70/P2, –1B70C/P2, –1B70/75/P2, and
–1B74/75/P2 turbofan engines with engine
assembly, part number (P/N) 2447M10G01 or
P/N 2447M10G02, installed.
(d) Unsafe Condition
This AD was prompted by a report of a
significant fan rub event. We are issuing this
AD to prevent failure of the fan blades and
the load reduction device, loss of power to
one or more engines, loss of thrust control,
and loss of the airplane.
(e) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(1) Modify the fan stator module assembly,
with one of the following methods, before
December 31, 2016.
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(f) Terminating Action
(g) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
FAA, may approve AMOCs to this AD. Use
the procedures found in 14 CFR 39.19 to
make your request. You may email your
request to: ANE-AD-AMOC@faa.gov.
(h) Related Information
(1) For more information about this AD,
contact Christopher McGuire, Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 1200 District
Avenue, Burlington, MA 01803; phone: 781–
238–7120; fax: 781–238–7199; email:
chris.mcguire@faa.gov.
(2) AD 2016–06–08 and AD 2016–08–12
pertain to the subject of this AD.
(i) 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) General Electric Company (GE) GEnx–
1B Service Bulletin (SB) 72–0309 R00, dated
March 11, 2016.
(ii) GE GEnx–1B SB 72–0314 R00, dated
April 1, 2016.
(iii) GE GEnx–1B SB 72–0317 R00, dated
June 29, 2016.
(3) For GE service information identified in
this AD, contact General Electric Company,
GE Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215; phone: 513–552–3272;
email: aviation.fleetsupport@ge.com.
(4) You may view this service information
at FAA, Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA. For
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information on the availability of this
material at the FAA, call 781–238–7125.
(5) You may view this service information
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 Burlington, Massachusetts, on
September 30, 2016.
Colleen M. D’Alessandro,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 2016–24795 Filed 10–13–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–6551; Directorate
Identifier 2013–SW–070–AD; Amendment
39–18682; AD 2016–21–01]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Bell Helicopter Textron (Bell) Model
430 helicopters. This AD requires
establishing a life limit for a certain
main rotor hub attachment bolt (bolt)
and removing from service each bolt
that has met or exceeded its life limit.
This AD was prompted by a
documentation error that omitted the
life limit of a certain part-numbered bolt
from the Airworthiness Limitations
section of the maintenance manual. The
actions of this AD are intended to
establish a life limit for a certain partnumbered bolt to prevent failure of a
bolt, failure of a main rotor hub, and
subsequent loss of control of a
helicopter.
SUMMARY:
This AD is effective November
18, 2016.
ADDRESSES: For service information
identified in this final rule, contact Bell
Helicopter Textron Canada Limited,
12,800 Rue de l’Avenir, Mirabel, Quebec
J7J1R4; telephone (450) 437–2862 or
(800) 363–8023; fax (450) 433–0272; or
at https://www.bellcustomer.com/files/.
You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy, Room 6N–321,
Fort Worth, TX 76177.
ehiers on DSK5VPTVN1PROD with RULES
DATES:
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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–
6551; or in person at the Docket
Operations Office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this AD, the Transport Canada
AD, the economic evaluation, any
comments received, and other
information. The street address for the
Docket Operations Office (phone: 800–
647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Matt
Fuller, Senior Aviation Safety Engineer,
Safety Management Group, Rotorcraft
Directorate, FAA, 10101 Hillwood
Pkwy, Fort Worth, TX 76177; telephone
(817) 222–5110; email matthew.fuller@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On May 10, 2016, at 81 FR 28766, the
Federal Register published our notice of
proposed rulemaking (NPRM), which
proposed to amend 14 CFR part 39 by
adding an AD that would apply to
certain serial-numbered Bell Model 430
helicopters with bolt part number (P/N)
MS21250–08083 installed. The NPRM
proposed to require, within 10 hours
time-in-service (TIS), revising the
Airworthiness Limitations section of the
applicable maintenance manual or
Instructions for Continued
Airworthiness (ICA) by establishing a
life limit of 5,000 hours TIS for each
bolt P/N MS21250–08083, determining
the number of hours TIS for each bolt
and using the helicopter’s hours if the
hours TIS of a bolt is unknown, and
removing from service each bolt that has
reached or exceeded its life limit. The
proposed requirements were intended to
establish a life limit for the bolt to
prevent failure of a bolt, failure of a
main rotor hub, and subsequent loss of
control of a helicopter.
Transport Canada, which is the
aviation authority for Canada, has
issued Canadian AD No. CF–2013–26,
dated September 24, 2013, to correct an
unsafe condition for certain serialnumbered Bell Model 430 helicopters.
Transport Canada advises that bolt P/N
MS21250–08083, which replaced bolt
P/N 20–065–08083 in 2009, has a
retirement life of 5,000 hours. However,
the retirement life for the replacement
bolt was inadvertently omitted from the
limitations section of the Bell 430
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maintenance manual. Transport Canada
advises that this situation, if not
corrected, could result in failure of a
bolt and loss of control of the helicopter.
Transport Canada AD No. CF–2013–26
requires reviewing the helicopter
records to determine if bolt P/N
MS21250–08083 is installed, creating a
historical service record, and
establishing an airworthiness life of
5,000 hours air time.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM (81 FR 28766, May 10, 2016).
FAA’s Determination
These helicopters have been approved
by the aviation authority of Canada and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with Canada, Transport
Canada, its technical representative, has
notified us of the unsafe condition
described in its AD. We are issuing this
AD because we evaluated all
information provided by Transport
Canada and determined the unsafe
condition exists and is likely to exist or
develop on other helicopters of the same
type design and that air safety and the
public interest require adopting the AD
requirements as proposed.
Differences Between This AD and the
Transport Canada AD
This AD requires compliance within
10 hours TIS, while the Transport
Canada AD requires compliance within
60 days.
Related Service Information
We reviewed Bell Helicopter Alert
Service Bulletin 430–12–47, dated
November 14, 2012 (ASB). The ASB
states that original bolt P/N 20–065–
08083 has a retirement life of 5,000
hours but has been replaced by standard
bolt P/N MS21250–08083, which does
not have a life limit listed in the
maintenance manual. The purpose of
the ASB is to establish a life limit of
5,000 hours for the replacement bolt.
Bell specifies reviewing the aircraft
records back to January 2009 to
determine which part-numbered bolts
are installed. If a replacement bolt P/N
MS21250–08083 is installed, the ASB
specifies using data from aircraft records
to create a historical service record for
the replacement bolts and reflecting the
5,000 hours life limit. The ASB also
specifies updating the Bell 430
maintenance manual.
E:\FR\FM\14OCR1.SGM
14OCR1
]]>Agencies
[Federal Register Volume 81, Number 199 (Friday, October 14, 2016)]
[Rules and Regulations]
[Pages 70925-70928]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-24795]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-5872; Directorate Identifier 2016-NE-11-AD;
Amendment 39-18681; AD 2016-20-15]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
General Electric Company (GE) GEnx-1B64/P2, -1B67/P2, -1B70/P2, -1B70C/
P2, -1B70/75/P2, and -1B74/75/P2 turbofan engines with engine assembly,
part number (P/N) 2447M10G01 or P/N 2447M10G02, installed. This AD was
prompted by a report of a significant fan rub event. This AD requires
rework of the engine fan stator module assembly. We are issuing this AD
to prevent failure of the fan blades and the load reduction device,
loss of power to one or more engines, loss of thrust control, and loss
of the airplane.
DATES: This AD is effective November 18, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 18,
2016.
ADDRESSES: For service information identified in this final rule,
contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215; phone: 513-552-3272; email:
aviation.fleetsupport@ge.com. You may view this referenced service
information at the FAA, Engine & Propeller Directorate, 1200 District
Avenue, Burlington, MA 01803. For information on the availability of
this material at the FAA, call 781-238-7125. It is also available on
the internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2016-5872.
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-
5872; 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
[[Page 70926]]
Docket Office (phone: 800-647-5527) is Document 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: Christopher McGuire, Aerospace
Engineer, Engine Certification Office, FAA, Engine & Propeller
Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7120; fax: 781-238-7199; email: chris.mcguire@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 all GE GEnx-1B64/P2, -1B67/
P2, -1B70/P2, -1B70C/P2, -1B70/75/P2, and -1B74/75/P2 turbofan engines
with engine assembly, P/N 2447M10G01 or P/N 2447M10G02, installed. The
NPRM published in the Federal Register on May 10, 2016 (81 FR 28777).
The NPRM was prompted by a report of a significant fan rub event. The
NPRM proposed to require rework of the engine fan stator module
assembly. We are issuing this AD to prevent failure of the fan blades
and the load reduction device, loss of power to one or more engines,
loss of thrust control, and loss of the airplane.
Request To Add Terminating Action
Japan Airlines and United Airlines requested that the airplane
flight manual (AFM) limitations mandated by AD 2016-08-12, Amendment
39-18488 (81 FR 23581, April 22, 2016) (``AD 2016-08-12''), be removed
from an aircraft that has complied with the fan case grind procedure
mandated in this AD. They reason that once the fan case grind is
completed on both engines installed on an airplane, there is no longer
an unsafe condition.
We agree. Once the fan case grind has been completed on both
engines installed on an airplane, the unsafe condition no longer
exists. With agreement from the Transport Airplane Directorate (TAD),
we added a terminating action paragraph to this AD.
Request To Add Compliance Methods
Japan Airlines requested that alternate service documents be
approved as compliance to AD 2016-06-08, Amendment 39-18439 (81 FR
14704, March 18, 2016) (``AD 2016-06-08''). They reason that the
service documents provide the same procedure and the same post-rework
configuration.
We disagree. AD 2016-06-08 is a separate AD issued by the TAD,
which includes aircraft-level corrective actions. The commenter must
contact the TAD to request a change to AD 2016-06-08. We did not change
this AD.
Request To Change Applicability
GE requested that the applicability explicitly state that engine
assembly, P/N 2447M10G03, is not applicable to this AD. They reason
that engine assembly, P/N 2447M10G03, is a new production part that
does not contain the unsafe condition.
We disagree. Since engine assembly, P/N 2447M10G03, is not listed
in the applicability of this AD, it is not applicable to this AD. We
did not change this AD.
Request To Change Compliance Method
GE requested that another procedure included within a new service
bulletin, GE GEnx-1B Service Bulletin (SB) 72-0317 R00, dated June 29,
2016, be added as a means of compliance to this AD. They reason that
this new procedure achieves the same configuration as the proposed
procedure.
We agree. The new procedure in GE GEnx-1B SB 72-0317 R00, dated
June 29, 2016, also corrects the unsafe condition addressed in this AD.
We added GE GEnx-1B SB 72-0317 R00, dated June 29, 2016, as a means of
compliance in this AD.
Request To Change Compliance Time
GE requested that we move the action specified in paragraph (f)
Credit for Previous Action, to compliance paragraph (e) of this AD.
They reason that this action is an equivalent method of performing the
fan case rework.
We agree. The action is equivalent to the current compliance, but
located within a different service document. We revised paragraph (f)
and paragraph (e) of this AD accordingly.
Request To Change Affected ADs
United Airlines requested that we list AD 2016-06-08 and AD 2016-
08-12 in this AD. They reason that AD 2016-06-08 and AD 2016-08-12
address the same unsafe condition as this AD and also mandate a fan
case rework.
We agree. AD 2016-06-08 and AD 2016-08-12 address the same unsafe
condition as this AD. We list AD 2016-06-08 and AD 2016-08-12 in
paragraph (h) of this AD.
Request To Change Affected ADs
United Airlines requested that we supersede AD 2016-08-12 with this
AD. They reason that AD 2016-06-08 and AD 2016-08-12 address the same
unsafe condition of the engine and mandate a fan case rework procedure.
We disagree. An AD that mandates engine-level corrective actions,
``this AD'', cannot supersede an AD, ``AD 2016-08-12'' that mandates
aircraft-level corrective actions. AD 2016-08-12 mandates aircraft
limitations in addition to the engine rework procedure that can only be
mandated at the aircraft level, not the engine level. We did not change
this AD.
Request To Change Operating Procedures
United Airlines requested that we revise the operating procedures
that require the ice removal procedure to be done every 5 minutes,
rather than the preferred every 5 minutes or less, allowing the pilot
to do the procedure prior to 5 minutes after Engine Indication and Crew
Alerting System (EICAS) notification. United Airlines suggests the 5
minute requirement does not allow pilots to effectively manage the
cockpit within reasonable parameters or room to operate.
We disagree. The AFM operating procedures are mandated by aircraft-
level AD 2016-06-08 and AD 2016-08-12, which were issued by the TAD.
The commenter must contact the TAD to request a change to AD 2016-06-08
or AD 2016-08-12. We did not change this AD.
Request To Change Compliance Time
United Airlines requested that we allow installation of engine
assembly, P/N 2477M10G03, by using GE GEnx-1B SB 72-0317 to modify the
engine instead of using the fan grind rework procedure as compliance to
AD 2016-08-12. They reason that the procedure in GE GEnx-1B SB 72-0317
achieves the same engine outcome as the currently mandated compliance.
We disagree. AD 2016-08-12 was issued by the TAD. The commenter
must contact the TAD to request a change to AD 2016-08-12. We did not
change this AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously. 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.
We also determined that these changes will not increase the
economic
[[Page 70927]]
burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed GE GEnx-1B SB 72-0314 R00, dated April 1, 2016. The SB
describes procedures for increasing the clearance of the fan stator
module assembly. We also reviewed GE GEnx-1B SB 72-0309 R00, dated
March 11, 2016. That SB describes procedures for increasing the
clearance of the fan stator module assembly. We also reviewed GE GEnx-
1B SB 72-0317 R00, dated June 29, 2016. That SB releases a new fan
stator module assembly. This service information is reasonably
available because the interested parties have access to it through
their normal course of business or by the means identified in the
ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 89 engines installed on airplanes
of U.S. registry. We also estimate that it will take about 40 hours per
engine to comply with this AD. The average labor rate is $85 per hour.
Based on these figures, we estimate the total cost of this AD to U.S.
operators to be $302,600.
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 to the extent
that it justifies making a regulatory distinction, 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):
2016-20-15 General Electric Company: Amendment 39-18681; Docket No.
FAA-2016-5872; Directorate Identifier 2016-NE-11-AD.
(a) Effective Date
This AD is effective November 18, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all General Electric Company (GE) GEnx-1B64/
P2, -1B67/P2, -1B70/P2, -1B70C/P2, -1B70/75/P2, and -1B74/75/P2
turbofan engines with engine assembly, part number (P/N) 2447M10G01
or P/N 2447M10G02, installed.
(d) Unsafe Condition
This AD was prompted by a report of a significant fan rub event.
We are issuing this AD to prevent failure of the fan blades and the
load reduction device, loss of power to one or more engines, loss of
thrust control, and loss of the airplane.
(e) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(1) Modify the fan stator module assembly, with one of the
following methods, before December 31, 2016.
(i) Use paragraphs 3.B.(1) through 3.B.(6) or 3.C.(1) through
3.C.(6) of the Accomplishment Instructions of GE GEnx-1B Service
Bulletin (SB) 72-0314 R00, dated April 1, 2016, to do the
modification.
(ii) Use paragraphs 3.B.(1) through 3.B.(6) or 3.C.(1) through
3.C.(6) of the Accomplishment Instructions of GE GEnx-1B SB 72-0309
R00, dated March 11, 2016, to do the modification.
(iii) Use paragraph 3.A. of the Accomplishment Instructions of
GE GEnx-1B SB 72-0317 R00, dated June 29, 2016, to do the
modification.
(2) Reserved.
(f) Terminating Action
Compliance with this AD constitutes terminating action for AD
2016-06-08, Amendment 39-18439 (81 FR 14704, March 18, 2016) (``AD
2016-06-08'') and AD 2016-08-12, Amendment 39-18488 (81 FR 23581,
April 22, 2016) (``AD 2016-08-12''), provided that all of the
airplanes within the operator's fleet that have engines identified
in paragraph (c) of this AD are modified as specified in paragraph
(e) of this AD. After fleet incorporation of this AD, do not install
any engine listed in paragraph (c) of this AD unless the engine is
modified as specified in paragraph (e) of this AD, or AD 2016-06-08,
or AD 2016-08-12.
(g) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, FAA, may approve AMOCs
to this AD. Use the procedures found in 14 CFR 39.19 to make your
request. You may email your request to: ANE-AD-AMOC@faa.gov.
(h) Related Information
(1) For more information about this AD, contact Christopher
McGuire, Aerospace Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA
01803; phone: 781-238-7120; fax: 781-238-7199; email:
chris.mcguire@faa.gov.
(2) AD 2016-06-08 and AD 2016-08-12 pertain to the subject of
this AD.
(i) 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) General Electric Company (GE) GEnx-1B Service Bulletin (SB)
72-0309 R00, dated March 11, 2016.
(ii) GE GEnx-1B SB 72-0314 R00, dated April 1, 2016.
(iii) GE GEnx-1B SB 72-0317 R00, dated June 29, 2016.
(3) For GE service information identified in this AD, contact
General Electric Company, GE Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215; phone: 513-552-3272; email:
aviation.fleetsupport@ge.com.
(4) You may view this service information at FAA, Engine &
Propeller Directorate, 1200 District Avenue, Burlington, MA. For
[[Page 70928]]
information on the availability of this material at the FAA, call
781-238-7125.
(5) You may view this service information 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 Burlington, Massachusetts, on September 30, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2016-24795 Filed 10-13-16; 8:45 am]
BILLING CODE 4910-13-P
