Airworthiness Directives; General Electric Company Turbofan Engines, 19022-19024 [2016-07377]
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19022
Federal Register / Vol. 81, No. 64 / Monday, April 4, 2016 / Rules and Regulations
of 1982, secs. 117(a), 132, 133, 134, 135, 137,
141, 145(g), 148, 218(a) (42 U.S.C. 10137(a),
10152, 10153, 10154, 10155, 10157, 10161,
10165(g), 10168, 10198(a)); 44 U.S.C. 3504
note.
DEPARTMENT OF TRANSPORTATION
■
2. In § 72.214, Certificate of
Compliance No. 1014 is revised to read
as follows:
[Docket No. FAA–2015–4023; Directorate
Identifier 2015–NE–29–AD; Amendment 39–
18445; AD 2016–06–14]
§ 72.214 List of approved spent fuel
storage casks.
RIN 2120–AA64
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Certificate Number: 1014.
Initial Certificate Effective Date: May
31, 2000.
Amendment Number 1 Effective Date:
July 15, 2002.
Amendment Number 2 Effective Date:
June 7, 2005.
Amendment Number 3 Effective Date:
May 29, 2007.
Amendment Number 4 Effective Date:
January 8, 2008.
Amendment Number 5 Effective Date:
July 14, 2008.
Amendment Number 6 Effective Date:
August 17, 2009.
Amendment Number 7 Effective Date:
December 28, 2009.
Amendment Number 8 Effective Date:
May 2, 2012, as corrected on November
16, 2012 (ADAMS Accession No.
ML12213A170); superseded by
Amendment Number 8, Revision 1, on
February 16, 2016.
Amendment Number 8, Revision 1,
Effective Date: February 16, 2016.
Amendment Number 9 Effective Date:
March 11, 2014, superseded by
Amendment Number 9, Revision 1, on
March 21, 2016.
Amendment Number 9, Revision 1,
Effective Date: March 21, 2016.
Safety Analysis Report (SAR)
Submitted by: Holtec International.
SAR Title: Final Safety Analysis
Report for the HI–STORM 100 Cask
System.
Docket Number: 72–1014.
Certificate Expiration Date: May 31,
2020.
Model Number: HI–STORM 100.
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Dated at Rockville, Maryland, this 30th day
of March, 2016.
For the Nuclear Regulatory Commission.
Cindy Bladey,
Chief, Rules, Announcements, and Directives
Branch, Division of Administrative Services,
Office of Administration.
[FR Doc. 2016–07618 Filed 4–1–16; 8:45 am]
BILLING CODE 7590–01–P
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Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; General
Electric Company Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
General Electric Company (GE) CF6–
80E1 turbofan engines with rotating
compressor discharge pressure (CDP)
seal, part number (P/N) 1669M73P02,
installed. This AD was prompted by
reports from the manufacturer of cracks
in the teeth of two rotating CDP seals
found during engine shop visits. This
AD requires stripping of the coating,
inspecting, and recoating the teeth of
the affected rotating CDP seals. We are
issuing this AD to prevent cracking of
the CDP seal teeth, uncontained part
release, damage to the engine, and
damage to the airplane.
DATES: This AD is effective May 9, 2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 9, 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 service information at the
FAA, Engine & Propeller Directorate,
1200 District Avenue, Burlington, MA.
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–2015–4023.
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–2015–
4023; 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
PO 00000
Frm 00002
Fmt 4700
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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:
Herman Mak, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 1200 District
Avenue, Burlington, MA 01803; phone:
781–238–7147; fax: 781–238–7199;
email: herman.mak@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 CF6–80E1 turbofan
engines with rotating CDP seal, P/N
1669M73P02, installed. The NPRM
published in the Federal Register on
November 17, 2015 (80 FR 71747). The
NPRM was prompted by reports of
cracks in the teeth of two rotating CDP
seals found during engine shop visits.
The NPRM proposed to require
stripping of the coating, inspecting, and
recoating the teeth of the affected
rotating CDP seals. We are issuing this
AD to prevent cracking of the CDP seal
teeth, uncontained part release, damage
to the engine, and damage to the
airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (80 FR 71747,
November 17, 2015) (‘‘the NPRM’’) and
the FAA’s response to each comment.
Request To Clarify Definition
Qantas, Air France, KLM Royal Dutch
Airlines (KLM), and GE Aviation
requested that the shop visit definition
be clarified to allow for randomly
occurring exemptions. Including
exemptions would not increase the time
between full shop visits.
We agree. We changed the shop visit
definition to include specific conditions
that do not qualify as shop visits.
Request To Clarify the Shop Visit
Definition
KLM and Air France requested we
clarify the phrase ‘‘separation of pairs of
major mating engine flanges’’.
We agree. We changed the definition
for engine shop visit.
Request To Change Compliance Time
Qantas requested a more restrictive
compliance time for engines that
experience blade-out events and a less
restrictive compliance time of next part
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Federal Register / Vol. 81, No. 64 / Monday, April 4, 2016 / Rules and Regulations
exposure for all other affected engines.
Only engines that experience blade-out
conditions require urgent compliance
times.
We disagree. The compliance times in
the NPRM were derived from analysis
that includes the risks associated with
engines with and without blade-out
events. We did not change this AD.
Request To Clarify Compliance
Qantas requested that we clarify the
specific type of stationary CDP seal
repair and that we clarify what is
considered a replaced stationary CDP
seal.
We agree. We modified the
Compliance section to specify the repair
as ‘honeycomb’. We also added a
definition to define a replaced CDP seal.
Request To Change Applicability
KLM requested that the applicability
be expanded to include spare parts.
We partially agree. We agree with the
concern for accidental installation of
borazon-nickel coated rotating CDP
seals because the NPRM does not
preclude this scenario. We disagree with
expanding this AD to include spare
parts because ADs address unsafe
conditions of engines, not spare parts.
We changed this AD by adding an
installation prohibition paragraph to
address this concern.
mstockstill on DSK4VPTVN1PROD with RULES
Request To Change Credit for Previous
Action
KLM requested the Credit for Previous
Action paragraph allow for other
approved original equipment
manufacturer approved procedures for
stripping and recoating rotating CDP
seal teeth. KLM recoated two CDP seals
using a procedure approved by GE.
We disagree. It is unknown whether
previous recoating procedures are
equivalent to the procedures specified
in the Credit for Previous Action
paragraph of this AD. Any party may
submit a request for an Alternative
Method of Compliance using the
procedures listed in this AD. We did not
change this AD.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
We reviewed GE Service Bulletin (SB)
CF6–80E1 S/B 72–0529, Revision 01,
dated August 21, 2015. The SB
describes procedures for stripping,
inspecting, and replacing the seal tooth
coating on the affected rotating CDP
seals. 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.
Other Related Service Information
We reviewed GE CF6–80E1
(GEK99376) Engine Manual, Revision
42, dated March 15, 2014. The engine
manual describes acceptable repair
procedures for the seal teeth.
Costs of Compliance
We estimate that this AD will affect
10 engines installed on airplanes of U.S.
registry. We also estimate that it will
take about 7.15 hours per engine to
comply with this AD. The average labor
rate is $85 per hour. Parts would cost
about $7,835 per engine. Based on these
figures, we estimate the total cost of this
AD to U.S. operators to be $84,428.
Additional Changes
We clarified paragraphs (e)(2)(i) and
(e)(2)(ii) of this AD.
We updated the cost estimate. We
changed the Costs of Compliance
paragraph of this AD by increasing the
number of affected engines by four and
updating the costs accordingly.
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.
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.
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
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19023
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
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):
■
2016–06–14 General Electric Company:
Amendment 39–18445; Docket No.
FAA–2015–4023; Directorate Identifier
2015–NE–29–AD.
(a) Effective Date
This AD is effective May 9, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all General Electric
Company (GE) CF6–80E1 turbofan engines
with rotating compressor discharge pressure
(CDP) seals, part number (P/N) 1669M73P02,
installed.
(d) Unsafe Condition
This AD was prompted by reports from the
manufacturer of cracks in the teeth of two
rotating CDP seals found during engine shop
visits. We are issuing this AD to prevent
cracking of the CDP seal teeth, which can
lead to uncontained part release, damage to
the engine, and damage to the airplane.
(e) Compliance
(1) Comply with this AD within the
compliance times specified, unless already
done.
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04APR1
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Federal Register / Vol. 81, No. 64 / Monday, April 4, 2016 / Rules and Regulations
(2) Strip coating, inspect, and recoat the
teeth of the rotating CDP seal, P/N
1669M73P02. Use paragraph 3.C.(2) of GE
Service Bulletin (SB) CF6–80E1 S/B 72–0529,
Revision 01, dated August 21, 2015 to do the
strip coating, inspecting, and recoating, as
follows:
(i) For engines that have had stationary
CDP seal, P/N 1347M28G02, replaced or
stationary CDP seal honeycomb repaired;
strip coating, inspect, and recoat the teeth of
the rotating CDP seal at the next engine shop
visit.
(ii) For engines that have not had
stationary CDP seal, P/N 1347M28G02,
replaced or stationary CDP seal honeycomb
repaired; strip coating, inspect, and recoat
the teeth of the rotating CDP seal at the next
part exposure of the rotating CDP seal.
(f) Installation Prohibition
After the effective date of this AD, do not
install any rotating CDP seal, P/N
1669M73P02, that has not had its seal teeth
recoated using procedures specified in ESM
72–31–10, REPAIR 002 of GE CF6–80E1
(GEK99376) Engine Manual, Revision 42,
dated March 15, 2014, into any engine.
(g) Definitions
(1) For the purpose of this AD, exposure of
the rotating CDP seal is defined as removal
of the compressor rear frame from the highpressure compressor (HPC) module.
(2) For the purpose of this AD, an engine
shop visit is defined as the induction of an
engine into the shop for maintenance
involving the separation of any major mating
engine flanges, except that the separation of
engine flanges solely for the following
purposes is not considered a shop visit:
(i) Transportation without subsequent
engine maintenance.
(ii) Removing the turbine rear frame (TRF)
for repair of TRF cracking.
(iii) Removing the top or bottom HPC case,
or both, for HPC airfoil maintenance.
(iv) Removing only the accessory gearbox
and/or transfer gearbox.
(v) Replacing the high-pressure turbine
(HPT) stage 1 blades per CF6–80E1 SB 72–
0504 ‘‘Quick-Turn Workscope Procedure to
Replace CF6–80E1 Stage 1 HPT Blades’’.
(3) For the purpose of this AD, a stationary
CDP seal is replaced if at any previous shop
visit, the seal has been removed and a
different seal is installed.
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You may take credit for the actions that are
required by paragraph (e) of this AD if the
actions were performed before the effective
date of this AD using the procedures in ESM
72–31–10, REPAIR 002 of the GE CF6–80E1
(GEK99376) Engine Manual, Revision 42,
dated March 15, 2014, or earlier versions.
Issued in Burlington, Massachusetts, on
March 16, 2016.
Ann C. Mollica,
Acting Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2016–07377 Filed 4–1–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–5193; Directorate
Identifier 2015–NE–35–AD; Amendment 39–
18464; AD 2016–07–19]
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.
Jkt 238001
Airworthiness Directives; Technify
Motors GmbH Reciprocating Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Technify Motors GmbH (type certificate
previously held by Thielert Aircraft
Engines GmbH) TAE 125–02–99 and
TAE 125–02–114 reciprocating engines.
This AD requires removal of affected
SUMMARY:
(i) Alternative Methods of Compliance
(AMOCs)
17:02 Apr 01, 2016
(k) 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 Service
Bulletin CF6–80E1 S/B 72–0529, Revision 01,
dated August 21, 2015.
(ii) Reserved.
(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
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.
RIN 2120–AA64
(h) Credit for Previous Action
VerDate Sep<11>2014
(j) Related Information
(1) For more information about this AD,
contact Herman Mak, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 1200 District Avenue,
Burlington, MA 01803; phone: 781–238–
7147; fax: 781–238–7199; email:
herman.mak@faa.gov.
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
fuel feed pumps. This AD was prompted
by reports of in-flight shutdowns on
TAE 125–02 engines. We are issuing
this AD to prevent failure of the fuel
feed pump, damage to the engine, and
damage to the airplane.
DATES: This AD becomes effective May
9, 2016.
ADDRESSES: For service information
identified in this AD, contact Technify
Motors GmbH, Platanenstrasse 14, D–
09356 Sankt Egidien, Germany; phone:
+49–37204–696–0; fax: +49–37204–
696–2912; email: support@
continentaldiesel.de. You may view this
service information at the FAA, Engine
& Propeller Directorate, 1200 District
Avenue, Burlington, MA. 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–2015–
5193.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
5193; 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 mandatory
continuing airworthiness information
(MCAI), the regulatory evaluation, any
comments received, and other
information. The address for the 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:
Philip Haberlen, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 1200 District
Avenue, Burlington, MA 01803; phone:
781–238–7770; fax: 781–238–7199;
email: philip.haberlen@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 the specified products. The
NPRM was published in the Federal
Register on January 4, 2016 (81 FR 27).
The NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
In-flight shut down occurrences have been
reported on aeroplanes equipped with TAE
125–02 engines. The initial results of the
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Agencies
[Federal Register Volume 81, Number 64 (Monday, April 4, 2016)]
[Rules and Regulations]
[Pages 19022-19024]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-07377]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-4023; Directorate Identifier 2015-NE-29-AD;
Amendment 39-18445; AD 2016-06-14]
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) CF6-80E1 turbofan engines with rotating
compressor discharge pressure (CDP) seal, part number (P/N) 1669M73P02,
installed. This AD was prompted by reports from the manufacturer of
cracks in the teeth of two rotating CDP seals found during engine shop
visits. This AD requires stripping of the coating, inspecting, and
recoating the teeth of the affected rotating CDP seals. We are issuing
this AD to prevent cracking of the CDP seal teeth, uncontained part
release, damage to the engine, and damage to the airplane.
DATES: This AD is effective May 9, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 9, 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 service information at
the FAA, Engine & Propeller Directorate, 1200 District Avenue,
Burlington, MA. 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-2015-4023.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4023; 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 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: Herman Mak, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA 01803; phone: 781-238-7147; fax: 781-
238-7199; email: herman.mak@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 CF6-80E1 turbofan
engines with rotating CDP seal, P/N 1669M73P02, installed. The NPRM
published in the Federal Register on November 17, 2015 (80 FR 71747).
The NPRM was prompted by reports of cracks in the teeth of two rotating
CDP seals found during engine shop visits. The NPRM proposed to require
stripping of the coating, inspecting, and recoating the teeth of the
affected rotating CDP seals. We are issuing this AD to prevent cracking
of the CDP seal teeth, uncontained part release, damage to the engine,
and damage to the airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (80
FR 71747, November 17, 2015) (``the NPRM'') and the FAA's response to
each comment.
Request To Clarify Definition
Qantas, Air France, KLM Royal Dutch Airlines (KLM), and GE Aviation
requested that the shop visit definition be clarified to allow for
randomly occurring exemptions. Including exemptions would not increase
the time between full shop visits.
We agree. We changed the shop visit definition to include specific
conditions that do not qualify as shop visits.
Request To Clarify the Shop Visit Definition
KLM and Air France requested we clarify the phrase ``separation of
pairs of major mating engine flanges''.
We agree. We changed the definition for engine shop visit.
Request To Change Compliance Time
Qantas requested a more restrictive compliance time for engines
that experience blade-out events and a less restrictive compliance time
of next part
[[Page 19023]]
exposure for all other affected engines. Only engines that experience
blade-out conditions require urgent compliance times.
We disagree. The compliance times in the NPRM were derived from
analysis that includes the risks associated with engines with and
without blade-out events. We did not change this AD.
Request To Clarify Compliance
Qantas requested that we clarify the specific type of stationary
CDP seal repair and that we clarify what is considered a replaced
stationary CDP seal.
We agree. We modified the Compliance section to specify the repair
as `honeycomb'. We also added a definition to define a replaced CDP
seal.
Request To Change Applicability
KLM requested that the applicability be expanded to include spare
parts.
We partially agree. We agree with the concern for accidental
installation of borazon-nickel coated rotating CDP seals because the
NPRM does not preclude this scenario. We disagree with expanding this
AD to include spare parts because ADs address unsafe conditions of
engines, not spare parts. We changed this AD by adding an installation
prohibition paragraph to address this concern.
Request To Change Credit for Previous Action
KLM requested the Credit for Previous Action paragraph allow for
other approved original equipment manufacturer approved procedures for
stripping and recoating rotating CDP seal teeth. KLM recoated two CDP
seals using a procedure approved by GE.
We disagree. It is unknown whether previous recoating procedures
are equivalent to the procedures specified in the Credit for Previous
Action paragraph of this AD. Any party may submit a request for an
Alternative Method of Compliance using the procedures listed in this
AD. We did not change this AD.
Additional Changes
We clarified paragraphs (e)(2)(i) and (e)(2)(ii) of this AD.
We updated the cost estimate. We changed the Costs of Compliance
paragraph of this AD by increasing the number of affected engines by
four and updating the costs accordingly.
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 also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed GE Service Bulletin (SB) CF6-80E1 S/B 72-0529, Revision
01, dated August 21, 2015. The SB describes procedures for stripping,
inspecting, and replacing the seal tooth coating on the affected
rotating CDP seals. 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.
Other Related Service Information
We reviewed GE CF6-80E1 (GEK99376) Engine Manual, Revision 42,
dated March 15, 2014. The engine manual describes acceptable repair
procedures for the seal teeth.
Costs of Compliance
We estimate that this AD will affect 10 engines installed on
airplanes of U.S. registry. We also estimate that it will take about
7.15 hours per engine to comply with this AD. The average labor rate is
$85 per hour. Parts would cost about $7,835 per engine. Based on these
figures, we estimate the total cost of this AD to U.S. operators to be
$84,428.
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):
2016-06-14 General Electric Company: Amendment 39-18445; Docket No.
FAA-2015-4023; Directorate Identifier 2015-NE-29-AD.
(a) Effective Date
This AD is effective May 9, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all General Electric Company (GE) CF6-80E1
turbofan engines with rotating compressor discharge pressure (CDP)
seals, part number (P/N) 1669M73P02, installed.
(d) Unsafe Condition
This AD was prompted by reports from the manufacturer of cracks
in the teeth of two rotating CDP seals found during engine shop
visits. We are issuing this AD to prevent cracking of the CDP seal
teeth, which can lead to uncontained part release, damage to the
engine, and damage to the airplane.
(e) Compliance
(1) Comply with this AD within the compliance times specified,
unless already done.
[[Page 19024]]
(2) Strip coating, inspect, and recoat the teeth of the rotating
CDP seal, P/N 1669M73P02. Use paragraph 3.C.(2) of GE Service
Bulletin (SB) CF6-80E1 S/B 72-0529, Revision 01, dated August 21,
2015 to do the strip coating, inspecting, and recoating, as follows:
(i) For engines that have had stationary CDP seal, P/N
1347M28G02, replaced or stationary CDP seal honeycomb repaired;
strip coating, inspect, and recoat the teeth of the rotating CDP
seal at the next engine shop visit.
(ii) For engines that have not had stationary CDP seal, P/N
1347M28G02, replaced or stationary CDP seal honeycomb repaired;
strip coating, inspect, and recoat the teeth of the rotating CDP
seal at the next part exposure of the rotating CDP seal.
(f) Installation Prohibition
After the effective date of this AD, do not install any rotating
CDP seal, P/N 1669M73P02, that has not had its seal teeth recoated
using procedures specified in ESM 72-31-10, REPAIR 002 of GE CF6-
80E1 (GEK99376) Engine Manual, Revision 42, dated March 15, 2014,
into any engine.
(g) Definitions
(1) For the purpose of this AD, exposure of the rotating CDP
seal is defined as removal of the compressor rear frame from the
high-pressure compressor (HPC) module.
(2) For the purpose of this AD, an engine shop visit is defined
as the induction of an engine into the shop for maintenance
involving the separation of any major mating engine flanges, except
that the separation of engine flanges solely for the following
purposes is not considered a shop visit:
(i) Transportation without subsequent engine maintenance.
(ii) Removing the turbine rear frame (TRF) for repair of TRF
cracking.
(iii) Removing the top or bottom HPC case, or both, for HPC
airfoil maintenance.
(iv) Removing only the accessory gearbox and/or transfer
gearbox.
(v) Replacing the high-pressure turbine (HPT) stage 1 blades per
CF6-80E1 SB 72-0504 ``Quick-Turn Workscope Procedure to Replace CF6-
80E1 Stage 1 HPT Blades''.
(3) For the purpose of this AD, a stationary CDP seal is
replaced if at any previous shop visit, the seal has been removed
and a different seal is installed.
(h) Credit for Previous Action
You may take credit for the actions that are required by
paragraph (e) of this AD if the actions were performed before the
effective date of this AD using the procedures in ESM 72-31-10,
REPAIR 002 of the GE CF6-80E1 (GEK99376) Engine Manual, Revision 42,
dated March 15, 2014, or earlier versions.
(i) 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.
(j) Related Information
(1) For more information about this AD, contact Herman Mak,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803;
phone: 781-238-7147; fax: 781-238-7199; email: herman.mak@faa.gov.
(k) 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 Service Bulletin CF6-80E1 S/B 72-
0529, Revision 01, dated August 21, 2015.
(ii) Reserved.
(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
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 March 16, 2016.
Ann C. Mollica,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2016-07377 Filed 4-1-16; 8:45 am]
BILLING CODE 4910-13-P