Airworthiness Directives; General Electric Company Turbofan Engines, 3182-3184 [2022-01141]
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3182
Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Rules and Regulations
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(4) Before installing the main driveshaft
following paragraph (g)(3) of this AD, and
with the engine adapter installed in the end
of the engine output shaft, inspect the
alignment of the main driveshaft installation
between the transmission input drive quill
coupling and the engine output shaft adapter
by following ‘‘6–24. Alignment—Main
Driveshaft,’’ paragraphs c. through g. on
pages 6–21 through 6–23, including ‘‘Figure
6–7. Transmission Positioning for Driveshaft
Alignment’’ on page 6–2 (Figure 6–7), and
‘‘Figure 6–8. Tool Application—Use of
Alignment Tool Set (T47)’’ on page 6–3
(Figure 6–8), of TM 55–1520–210–23–1 C 42.
If there is misalignment, before further flight,
adjust the alignment by following ‘‘6–24.
Alignment—Main Driveshaft,’’ paragraphs h.
through j. on page 6–23, including Figure 6–
7 and Figure 6–8, of TM 55–1520–210–23–1
C 42.
(5) Within 300 hours TIS after the effective
date of this AD, and thereafter within
intervals not to exceed 300 hours TIS, with
the main driveshaft installed, accomplish the
actions in paragraphs (g)(3)(i) through (iv) of
this AD.
(6) As an optional terminating action for
the requirements of this AD, you may install
KAflex main driveshaft P/N SKCP3303–1.
(7) As an option to accomplishing the
actions by following the specified portions in
TM 55–1520–210–23–1 C 42 in paragraphs
(g)(3) and (4) of this AD, you may accomplish
the actions by following those specified
portions in Headquarters, Department of the
Army, Aviation Unit and Intermediate
Maintenance Instructions Army Model UH–
1H/V/EH–1H/X Helicopters, Technical
Manual TM 55–1520–210–23–1, Change No.
47, dated September 20, 2005 (TM 55–1520–
210–23–1 C 47), and disregard exceptions to
refer to Figure 1 and see Figure 2 to the
introductory text of paragraph (g)(3) of this
AD, instead refer to ‘‘Figure 6–12.2. Main
Driveshaft Installation & Removal Tool’’ and
see ‘‘Figure 6–12.3. Work Aid Tool Installed
on Main Driveshaft,’’ on page 6–27 of TM 55–
1520–210–23–1 C 47 as instructed in TM 55–
1520–210–23–1 C 47.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, DSCO Branch, 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 certification office,
send it to the attention of the person
identified in paragraph (i) of this AD.
Information may be emailed to: 9-ASW-190COS@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.
(i) Related Information
For more information about this AD,
contact Ameet Shrotriya, Aerospace
Engineer, Delegation Oversight Section,
DSCO Branch, Compliance & Airworthiness
VerDate Sep<11>2014
16:23 Jan 20, 2022
Jkt 256001
Division, FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone (817) 222–5525;
email ameet.shrotriya@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) Headquarters, Department of the Army,
Aviation Unit and Intermediate Maintenance
Instructions Army Model UH–1H/V/EH–1H/
X Helicopters, Technical Manual TM 55–
1520–210–23–1, Change No. 42, dated April
14, 2003:
(A) ‘‘Figure 4–9. Engine Air Inlet Filter
Installation,’’ page 4–16;
(B) Page 4–17;
(C) ‘‘Figure 6–7. Transmission Positioning
for Driveshaft Alignment,’’ page 6–2;
(D) ‘‘Figure 6–8. Tool Application—Use of
Alignment Tool Set (T47),’’ page 6–3; and
(E) Pages 6–21 through 6–24.
(ii) Headquarters, Department of the Army,
Aviation Unit and Intermediate Maintenance
Instructions Army Model UH–1H/V/EH–1H/
X Helicopters, Technical Manual TM 55–
1520–210–23–1, Change No. 47, dated
September 20, 2005:
(A) ‘‘Figure 4–9. Engine Air Inlet Filter
Installation,’’ page 4–16;
(B) Page 4–17;
(C) ‘‘Figure 6–7. Transmission Positioning
for Driveshaft Alignment,’’ page 6–2;
(D) ‘‘Figure 6–8. Tool Application—Use of
Alignment Tool Set (T47),’’ page 6–3;
(E) Pages 6–21 through 6–24; and
(F) ‘‘Figure 6–12.2. Main Driveshaft
Installation & Removal Tool’’ and ‘‘Figure 6–
12.3. Work Aid Tool Installed on Main
Driveshaft,’’ page 6–27.
(3) For service information identified in
this AD, contact U.S. Army Materiel
Command Logistics Data Analysis Center
(USAMC LDAC), ATTN: Equipment
Publication Control Officers (EPCOs),
Building 3305, Redeye Road, Redstone
Arsenal, AL 35898–7466; telephone (256)
955–7716 or 1–866–211–3367; email
usarmy.redstone.ldac.mbx.logetm@mail.mil;
or at https://enterprise.armyerp.army.mil.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(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,
email: fr.inspection@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on December 10, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022–00991 Filed 1–20–22; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0949; Project
Identifier AD–2021–00115–E; Amendment
39–21915; AD 2022–02–18]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
General Electric Company (GE) CF6–
80C2A1, CF6–80C2A2, CF6–80C2A3,
CF6–80C2A5, CF6–80C2A5F, and CF6–
80C2A8 model turbofan engines with an
installed left-hand rear mount link
assembly, part number (P/N)
1846M23G01. This AD was prompted
by the manufacturer reducing the life
limit for the affected left-hand rear
mount link assembly. This AD requires
revising the airworthiness limitations
section (ALS) of the existing engine
maintenance manual and the operator’s
existing approved continuous
airworthiness maintenance program
(CAMP). The FAA is issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
DATES:
This AD is effective February 25,
2022.
For service information
identified in this final rule, contact
General Electric Company, 1 Neumann
Way, Cincinnati, OH 45215; phone:
(513) 552–3272; email:
aviation.fleetsupport@ae.ge.com;
website: https://www.ge.com. You may
view this service information at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 1200 District
Avenue, Burlington, MA 01803. For
information on the availability of this
material at the FAA, call (817) 222–
5110. It is also available at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0949.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0949; or in person at Docket
Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
final rule, any comments received, and
other information. The address for
Docket Operations is U.S. Department of
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Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Rules and Regulations
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Scott Stevenson, Aviation Safety
Engineer, ECO Branch, FAA, 1200
District Avenue, Burlington, MA 01803;
phone: (781) 238–7132; fax: (781) 238–
7199; email: Scott.M.Stevenson@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all GE CF6–80C2A1, CF6–
80C2A2, CF6–80C2A3, CF6–80C2A5,
CF6–80C2A5F, and CF6–80C2A8 model
turbofan engines with an installed lefthand rear mount link assembly, P/N
1846M23G01. The NPRM published in
the Federal Register on November 5,
2021 (86 FR 61086). The NPRM was
prompted by a report from the
manufacturer reducing the life limit for
the affected left-hand rear mount link
assembly. The left-hand rear mount link
assembly was redesigned and certified
in 1999, and the FAA subsequently
issued AD 2000–12–08 (65 FR 39536,
June 27, 2000), mandating the
replacement of the affected left-hand
rear mount link assembly with a part
eligible for installation. Later, analysis
from the aircraft manufacturer of stress
loads in their extended service goal
mission profile revealed loads during
the take-off phase that were not
included at certification. These
additional loads result in a reduced life
limit on the left-hand rear mount link
assembly. In the NPRM, the FAA
proposed to require revising the ALS of
the GE CF6–80C Engine Manual,
GEK92451, as applicable to each
affected engine model, and the
operator’s existing approved CAMP to
incorporate a reduced life limit for the
affected left-hand rear mount link
assembly, P/N 1846M23G01. The FAA
is issuing this AD to address the unsafe
condition on these products.
Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from
one commenter, FedEx Express, who
supported the NPRM without change.
Conclusion
The FAA reviewed the relevant data,
considered the comments received, and
determined that air safety requires
adopting the AD as proposed.
Accordingly, the FAA is issuing this AD
to address the unsafe condition on these
products. Except for minor editorial
changes, including the removal of the
reference to GE CF6–80C2 Engine
Manual, GEK92451, this AD is adopted
as proposed in the NPRM.
Related Service Information
The FAA reviewed GE CF6–80C2
Temporary Revision (TR) 05–0276,
dated July 13, 2021 (GE TR 05–0276),
and GE CF6–80C2 TR 05–0277, dated
July 9, 2021 (GE TR 05–0277). GE TR
05–0276 and GE TR 05–277 provide the
new life limit to be updated into the
ALS, for the affected left-hand rear
mount link assembly, in the existing
engine maintenance manual.
Costs of Compliance
The FAA estimates that this AD
affects 220 engines installed on
airplanes of U.S. registry.
The FAA estimates the following
costs to comply with this AD:
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ESTIMATED COSTS
Action
Labor cost
Revise ALS of Engine Manual and the operator’s existing approved CAMP.
2 work-hours × $85 per hour = $170 .............
Cost per
product
Parts cost
$0
Cost on U.S.
operators
$170
$37,400
Authority for This Rulemaking
Regulatory Findings
The Amendment
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.
The FAA is 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.
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) Will not affect intrastate aviation
in Alaska, and
(3) 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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
VerDate Sep<11>2014
16:23 Jan 20, 2022
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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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:
■
2022–02–18 General Electric Company:
Amendment 39–21915; Docket No.
FAA–2021–0949; Project Identifier AD–
2021–00115–E.
(a) Effective Date
This airworthiness directive (AD) is
effective February 25, 2022.
(b) Affected ADs
None.
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Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Rules and Regulations
(c) Applicability
This AD applies to General Electric
Company (GE) CF6–80C2A1, CF6–80C2A2,
CF6–80C2A3, CF6–80C2A5, CF6–80C2A5F,
and CF6–80C2A8 model turbofan engines
with an installed left-hand rear mount link
assembly, part number (P/N) 1846M23G01.
(d) Subject
BILLING CODE 4910–13–P
Federal Aviation Administration
(e) Unsafe Condition
This AD was prompted by a report from
the manufacturer on an updated analysis of
stress loads during take-off, which revealed
a stress increase with take-off phase loads
that were not included at certification. The
FAA is issuing this AD to lower the life limit
of the left-hand rear mount link assembly and
prevent the failure of the engine mount
system. The unsafe condition, if not
addressed, could result in separation of the
engine from the airplane and loss of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
Within 180 days after the effective date of
this AD, revise the airworthiness limitations
section of the existing engine maintenance
manual, and the operator’s existing approved
continuous airworthiness maintenance
program, by reducing the life limit of the lefthand rear mount link assembly, P/N
1846M23G01, from 50,000 flight cycles (FCs)
to 23,800 FCs.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, ECO Branch, 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 ECO Branch, send it to
the attention of the person identified in
paragraph (i) of this AD. You may email your
request to: ANE-AD-AMOC@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.
(i) Related Information
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[FR Doc. 2022–01141 Filed 1–20–22; 8:45 am]
DEPARTMENT OF TRANSPORTATION
Joint Aircraft System Component (JASC)
Code 7120, Engine Mount Section.
For more information about this AD,
contact Scott Stevenson, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: (781)
238–7132; fax: (781) 238–7199; email:
Scott.M.Stevenson@faa.gov.
(j) Material Incorporated by Reference
None.
VerDate Sep<11>2014
Issued on January 14, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
16:23 Jan 20, 2022
Jkt 256001
14 CFR Part 39
[Docket No. FAA–2021–0725; Project
Identifier MCAI–2020–01402–T; Amendment
39–21882; AD 2021–26–23]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2017–22–
06, which applied to certain
Bombardier, Inc., Model CL–600–2B16
(601–3A, 601–3R, and 604 Variants)
airplanes. AD 2017–22–06 required
repetitive inspections for fuel leakage at
the engine and auxiliary power unit
(APU) fuel pumps, and related
investigative and corrective actions if
necessary. This AD retains the
requirements of AD 2017–22–06, and
requires an inspection of the APU,
repair if necessary, and modification of
the engine electrical fuel pump (EFP)
installation. This AD also adds airplanes
to the applicability. This AD was
prompted by reports of fuel leaks from
the electrical connectors and conduits of
the engine and APU EFP cartridge/
canister, and the development of
additional actions to address the root
cause of the fuel leaks. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective February 25,
2022.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 25, 2022.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of November 30, 2017 (82 FR
49498, October 26, 2017).
ADDRESSES: For service information
identified in this final rule, contact
Bombardier Business Aircraft Customer
Response Center, 400 Coˆte-Vertu Road
West, Dorval, Que´bec H4S 1Y9, Canada;
telephone 514–855–2999; email ac.yul@
SUMMARY:
PO 00000
Frm 00010
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aero.bombardier.com; internet https://
www.bombardier.com. You may view
this referenced service information at
the FAA, Airworthiness Products
Section, Operational Safety Branch,
2200 South 216th St., Des Moines, WA.
For information on the availability of
this material at the FAA, call 206–231–
3195. It is also available on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0725.
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–2021–
0725; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
any comments received, and other
information. The address for Docket
Operations is 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:
Steven Dzierzynski, Aerospace
Engineer, Avionics and Electrical
Systems Section, FAA, New York ACO
Branch, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590; telephone
516–228–7367; fax 516–794–5531; email
9-avs-nyaco-cos@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued TCCA AD CF–
2016–32R4, dated October 13, 2020
(TCCA AD CF–2016–32R4); and TCCA
AD CF–2020–38, dated October 13, 2020
(TCCA AD CF–2020–38); (also referred
to as the Mandatory Continuing
Airworthiness Information, or the
MCAI), to correct an unsafe condition
for certain Bombardier, Inc., Model CL–
600–2B16 (601–3A, 601–3R, and 604
Variants) airplanes. You may examine
the MCAI in the AD docket on the
internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0725.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2017–22–06,
Amendment 39–19086 (82 FR 49498,
October 26, 2017) (AD 2017–22–06). AD
2017–22–06 applied to certain
Bombardier, Inc., Model CL–600–2B16
(601–3A, 601–3R, and 604 Variants)
airplanes. The NPRM published in the
Federal Register on September 8, 2021
(86 FR 50291). The NPRM was
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]]>Agencies
[Federal Register Volume 87, Number 14 (Friday, January 21, 2022)]
[Rules and Regulations]
[Pages 3182-3184]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-01141]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0949; Project Identifier AD-2021-00115-E;
Amendment 39-21915; AD 2022-02-18]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
General Electric Company (GE) CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6-
80C2A5, CF6-80C2A5F, and CF6-80C2A8 model turbofan engines with an
installed left-hand rear mount link assembly, part number (P/N)
1846M23G01. This AD was prompted by the manufacturer reducing the life
limit for the affected left-hand rear mount link assembly. This AD
requires revising the airworthiness limitations section (ALS) of the
existing engine maintenance manual and the operator's existing approved
continuous airworthiness maintenance program (CAMP). The FAA is issuing
this AD to address the unsafe condition on these products.
DATES: This AD is effective February 25, 2022.
ADDRESSES: For service information identified in this final rule,
contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215;
phone: (513) 552-3272; email: [email protected]; website:
https://www.ge.com. You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 1200
District Avenue, Burlington, MA 01803. For information on the
availability of this material at the FAA, call (817) 222-5110. It is
also available at https://www.regulations.gov by searching for and
locating Docket No. FAA-2021-0949.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0949; or in person at
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket contains this final rule, any
comments received, and other information. The address for Docket
Operations is U.S. Department of
[[Page 3183]]
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Scott Stevenson, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803;
phone: (781) 238-7132; fax: (781) 238-7199; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to all GE CF6-80C2A1, CF6-
80C2A2, CF6-80C2A3, CF6-80C2A5, CF6-80C2A5F, and CF6-80C2A8 model
turbofan engines with an installed left-hand rear mount link assembly,
P/N 1846M23G01. The NPRM published in the Federal Register on November
5, 2021 (86 FR 61086). The NPRM was prompted by a report from the
manufacturer reducing the life limit for the affected left-hand rear
mount link assembly. The left-hand rear mount link assembly was
redesigned and certified in 1999, and the FAA subsequently issued AD
2000-12-08 (65 FR 39536, June 27, 2000), mandating the replacement of
the affected left-hand rear mount link assembly with a part eligible
for installation. Later, analysis from the aircraft manufacturer of
stress loads in their extended service goal mission profile revealed
loads during the take-off phase that were not included at
certification. These additional loads result in a reduced life limit on
the left-hand rear mount link assembly. In the NPRM, the FAA proposed
to require revising the ALS of the GE CF6-80C Engine Manual, GEK92451,
as applicable to each affected engine model, and the operator's
existing approved CAMP to incorporate a reduced life limit for the
affected left-hand rear mount link assembly, P/N 1846M23G01. The FAA is
issuing this AD to address the unsafe condition on these products.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from one commenter, FedEx Express, who
supported the NPRM without change.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety requires adopting the AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes,
including the removal of the reference to GE CF6-80C2 Engine Manual,
GEK92451, this AD is adopted as proposed in the NPRM.
Related Service Information
The FAA reviewed GE CF6-80C2 Temporary Revision (TR) 05-0276, dated
July 13, 2021 (GE TR 05-0276), and GE CF6-80C2 TR 05-0277, dated July
9, 2021 (GE TR 05-0277). GE TR 05-0276 and GE TR 05-277 provide the new
life limit to be updated into the ALS, for the affected left-hand rear
mount link assembly, in the existing engine maintenance manual.
Costs of Compliance
The FAA estimates that this AD affects 220 engines installed on
airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Revise ALS of Engine Manual and the 2 work-hours x $85 per $0 $170 $37,400
operator's existing approved CAMP. hour = $170.
----------------------------------------------------------------------------------------------------------------
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.
The FAA is 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) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The 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:
2022-02-18 General Electric Company: Amendment 39-21915; Docket No.
FAA-2021-0949; Project Identifier AD-2021-00115-E.
(a) Effective Date
This airworthiness directive (AD) is effective February 25,
2022.
(b) Affected ADs
None.
[[Page 3184]]
(c) Applicability
This AD applies to General Electric Company (GE) CF6-80C2A1,
CF6-80C2A2, CF6-80C2A3, CF6-80C2A5, CF6-80C2A5F, and CF6-80C2A8
model turbofan engines with an installed left-hand rear mount link
assembly, part number (P/N) 1846M23G01.
(d) Subject
Joint Aircraft System Component (JASC) Code 7120, Engine Mount
Section.
(e) Unsafe Condition
This AD was prompted by a report from the manufacturer on an
updated analysis of stress loads during take-off, which revealed a
stress increase with take-off phase loads that were not included at
certification. The FAA is issuing this AD to lower the life limit of
the left-hand rear mount link assembly and prevent the failure of
the engine mount system. The unsafe condition, if not addressed,
could result in separation of the engine from the airplane and loss
of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Within 180 days after the effective date of this AD, revise the
airworthiness limitations section of the existing engine maintenance
manual, and the operator's existing approved continuous
airworthiness maintenance program, by reducing the life limit of the
left-hand rear mount link assembly, P/N 1846M23G01, from 50,000
flight cycles (FCs) to 23,800 FCs.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, ECO Branch, 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
ECO Branch, send it to the attention of the person identified in
paragraph (i) of this AD. You may email your request to: [email protected].
(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.
(i) Related Information
For more information about this AD, contact Scott Stevenson,
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: (781) 238-7132; fax: (781) 238-7199;
email: [email protected].
(j) Material Incorporated by Reference
None.
Issued on January 14, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2022-01141 Filed 1-20-22; 8:45 am]
BILLING CODE 4910-13-P
