Airworthiness Directives; General Electric Company Turbofan Engines, 7859-7862 [2023-02512]
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Federal Register / Vol. 88, No. 25 / Tuesday, February 7, 2023 / Rules and Regulations
(i) Verification/Replacement of Pitch Trim
Switches for Airplanes With S/Ns 20501 and
Subsequent With Certain Control Wheel P/Ns
83912156 and 83912157
For airplanes with S/Ns 20501 and
subsequent with leather-covered control
wheels, pilot control wheel P/N 83912156, or
co-pilot control wheel P/N 83912157: Within
200 flight hours or 6 months, whichever
occurs first, from the effective date of this
AD, remove and inspect both the pilot and
co-pilot pitch trim switches to determine the
part number of the pitch trim switch in
accordance with Section 2.B. of the
Accomplishment Instructions of Bombardier
Service Bulletin 350–27–011, dated March
21, 2022.
(1) If pitch trim switch P/N 83452541 or P/
N 83452548 is found installed in either the
pilot or the co-pilot control wheel, before
further flight, replace the pitch trim switch
with pitch trim switch P/N 83452548, serial
number 02000 and subsequent, in accordance
with Section 2.B. of the Accomplishment
Instructions of the applicable service
information identified in figure 1 to
paragraph (h) of this AD.
(2) Before further flight thereafter perform
the operational test in accordance with
Section 2.C. of the Accomplishment
Instructions of Bombardier Service Bulletin
350–27–011, dated March 21, 2022.
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(j) Parts Installation Prohibition
As of the effective date of this AD, no
person may install, on any airplane, a trim
switch P/N 83452548 or P/N 83452541 with
any serial number listed in figure 2 to
paragraph (h) of this AD.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York ACO
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
responsible Flight Standards Office, as
appropriate. If sending information directly
to the manager of the certification office,
send it to ATTN: Program Manager,
Continuing Operational Safety, FAA, New
York ACO Branch, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone
516–228–7300. Before using any approved
AMOC, notify your appropriate principal
inspector, or lacking a principal inspector,
the manager of the responsible Flight
Standards Office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, New York ACO Branch,
FAA; or Transport Canada Civil Aviation
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(l) Additional Information
(1) Refer to Transport Canada AD CF–
2022–24, dated May 2, 2022, for related
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17:54 Feb 06, 2023
Jkt 259001
information. This Transport Canada AD may
be found in the AD docket at regulations.gov
under Docket No. FAA–2022–1251.
(2) For more information about this AD,
contact Thomas Niczky, Aerospace Engineer,
Avionics and Electrical Systems Section,
FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590;
telephone 516–228–7347; email 9-avs-nyacocos@faa.gov.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Bombardier Service Bulletin 350–27–
011, Basic Issue, dated March 21, 2022.
(ii) Bombardier Service Bulletin 100–27–
21, Basic Issue, dated March 21, 2022.
(3) For service information identified in
this AD, contact Bombardier Business
Aircraft Customer Response Center, 400 Coˆte
Vertu Road West, Dorval, Que´bec H4S 1Y9,
Canada; telephone 1–514–855–2999; email
ac.yul@aero.bombardier.com; internet
bombardier.com.
(4) You may view this 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.
(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:
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on January 18, 2023.
Christina Underwood,
Acting Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2023–02525 Filed 2–6–23; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0766; Project
Identifier 2019–NE–23–AD; Amendment 39–
22312; AD 2023–02–05]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
8C1, CF34–8C5, CF34–8C5A1, CF34–
8C5B1, CF34–8C5A2, CF34–8C5A3,
CF34–8E2, CF34–8E2A1, CF34–8E5,
CF34–8E5A1, CF34–8E5A2, CF34–8E6,
and CF34–8E6A1 model turbofan
engines. This AD was prompted by a
predicted reduction in the cyclic life of
the combustion chamber assembly aft
flange. This AD requires revisions to the
airworthiness limitations section (ALS)
of the existing engine manual (EM) and
the operator’s existing approved
maintenance or inspection program, as
applicable, to incorporate initial and
repetitive fluorescent penetrant
inspections (FPIs) of the combustion
chamber assembly. The FAA is issuing
this AD to address the unsafe condition
on these products.
This AD is effective March 14,
2023.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 14, 2023.
DATES:
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov by searching
for and locating Docket No. FAA–2019–
0766; 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.
Material Incorporated by Reference:
• For GE service information
identified in this final rule, contact
General Electric Company, 1 Neumann
Way, Cincinnati, OH 45215; phone:
(513) 552–3272; email:
aviation.fleetsupport@ge.com; website:
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 regulations.gov by searching
for and locating Docket No. FAA–2019–
0766.
FOR FURTHER INFORMATION CONTACT:
The FAA is adopting a new
airworthiness directive (AD) for all
General Electric Company (GE) CF34–
SUMMARY:
7859
Scott Stevenson, Aviation Safety
Engineer, ECO Branch, FAA, 1200
District Avenue, Burlington, MA 01803;
phone: (781) 238–7132; email:
Scott.M.Stevenson@faa.gov.
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Federal Register / Vol. 88, No. 25 / Tuesday, February 7, 2023 / Rules and Regulations
Request To Add the Date of the Task in
Paragraph (g)(3)
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a supplemental
notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an
AD that would apply to all GE CF34–
8C1, CF34–8C5, CF34–8C5A1, CF34–
8C5B1, CF34–C5A2, CF34–8C5A3,
CF34–8E2, CF34–8E2A1, CF34–8E5,
CF34–8E5A1, CF34–8E5A2, CF34–8E6,
and CF34–8E6A1 (CF34–8C and GE
CF34–8E) model turbofan engines,
including engine models marked on the
engine data plate as CF34–8C5/B, CF34–
8C5/M, CF34–8C5A1/B, CF34–8C5A1/
M, CF34–8C5B1/B, CF34–8C5A2/B, and
CF34–8C5A2/M. The SNPRM published
in the Federal Register on October 07,
2022 (87 FR 60944). The SNPRM was
prompted by a predicted reduction in
the cyclic life of the combustion
chamber assembly aft flange. As a result,
the manufacturer incorporated
temporary revisions (TRs) into the GE
CF34–8C and GE CF34–8E EMs for a
scheduled maintenance check. In the
SNPRM, the FAA proposed to require
revisions to the ALS of the existing EM
and the operator’s existing approved
maintenance or inspection program, as
applicable, to incorporate initial and
repetitive FPIs of the combustion
chamber assembly. 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
three commenters. The commenters
were Horizon Air, Japan Airlines (JAL),
and SkyWest Airlines (SkyWest). The
following presents the comments
received on the SNPRM and the FAA’s
response to each comment.
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Request To Replace ‘‘ESM’’ Reference
With ‘‘EM’’ Reference
Horizon Air requested that the FAA
replace all references of ‘‘ESM’’ with
‘‘EM’’ in this final rule. Horizon Air
reasoned that the SNPRM only defines
the acronym ‘‘EM,’’ and both acronyms
are used interchangeably in the SNPRM.
The FAA clarifies that the reference to
‘‘ESM’’ is not an acronym defined by the
FAA in the proposed AD and used
interchangeably with ‘‘EM.’’ ‘‘ESM’’ is
part of GE’s chapter title within each
task reference and must be used for an
accurate reference. The FAA did not
change this AD as a result of this
comment.
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17:54 Feb 06, 2023
Jkt 259001
Horizon Air requested that the FAA
include the task revision date for
‘‘TASK 05–21–03–200–801,’’ referenced
in paragraph (g)(3)(ii) of the SNPRM.
Horizon Air reasoned that adding the
task revision date would make the
wording consistent with the dates of the
tasks in paragraphs (g)(1)(ii) and (2)(ii)
of the SNPRM.
The FAA established a shorthand
notation in paragraph (g)(2)(ii) of the
SNPRM, which contains the full
citation, including the task revision
date, followed by the shorthand
notation ‘‘TASK 05–21–03–200–801.’’
The FAA then used the established
shorthand notation to reference the task
in paragraph (g)(3)(ii) of the SNPRM.
The FAA did not change this AD as a
result of this comment.
Request To Revise Paragraph (g)(1)(ii),
(2)(ii), and (3)(ii) of the AD
Horizon Air requested that the FAA
revise paragraphs (g)(1)(ii), (2)(ii), and
(3)(ii) of the AD, as those paragraphs do
not clearly include that performance of
the inspection within 2,200 cycles from
the effective date of this AD is only
applicable to those combustion chamber
assemblies that have exceeded the
inspection threshold specified in the
tables referenced in TASK 05–21–03–
200–801. Similarly, JAL requested that
the FAA revise paragraph (g)(1)(ii) for
the same reasons articulated by Horizon
Air.
In response to these comments, the
FAA has revised the language in
paragraphs (g)(1)(ii), (2)(ii), and (3)(ii) of
this AD to clarify that where the notes
to Tables 801, 802, 803, 804, and 805,
included in TASK 05–21–03–200–801,
specify to perform the inspection within
2,200 cycles from the issuance date of
the TR, this AD requires performing the
inspection within 2,200 cycles from the
effective date of this AD. The FAA
further clarifies that the notes are part
of the task, and therefore, has removed
‘‘including the notes.’’
Request To Correct an Incorrect
Reference to a Task in Paragraph
(g)(2)(i)
SkyWest requested that the FAA
correct an incorrect reference in
paragraph (g)(2)(i) of this AD. SkyWest
noted that Table 802 does not exist in
TASK 05–11–25–200–801, which is
specific to GE CF34–8C5 model turbofan
engines with/B minor model
designation.
In response to this comment, the FAA
has revised paragraph (g)(2)(i) of this AD
from ‘‘Table 801 in TASK 05–11–05–
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Frm 00022
Fmt 4700
Sfmt 4700
200–801 and Table 802 in TASK 05–11–
25–200–801, dated November 3, 2020,
from ESM 05–11–25 Static Structures—
BJ Life Limits (TASK 05–11–25–200–
801)’’ to ‘‘Tables 801 (for –8C1) and 802
(for –8C5) in TASK 05–11–05–200–801,
dated March 4, 2021, from ESM 05–11–
05 Static Structures—Life Limits (TASK
05–11–05–200–801).’’
Conclusion
The FAA reviewed the relevant data,
considered any comments received, and
determined that air safety requires
adopting this AD as proposed.
Accordingly, the FAA is issuing this AD
to address the unsafe condition on these
products. Except for minor editorial
changes, and any other changes
described previously, this AD is
adopted as proposed in the SNPRM.
None of the changes will increase the
economic burden on any operator.
Related Service Information Under 1
CFR Part 51
The FAA reviewed the following
tasks:
• TASK 05–11–05–200–801, dated
March 4, 2021, from ESM 05–11–05
Static Structures—Life Limits, of GE
CF34–8C EM GEK105091, Rev 51, dated
April 1, 2022;
• TASK 05–11–05–200–801, dated
March 4, 2021, from ESM 05–11–05
Static Structures—Life Limits, of GE
CF34–8E EM GEK112031, Rev 43, dated
April 1, 2022; and
• TASK 05–11–25–200–801, dated
November 3, 2020, from ESM 05–11–25
Static Structures—BJ Life Limits, of GE
CF34–8C EM GEK105091, Rev 51, dated
April 1, 2022.
These tasks, differentiated by GE
CF34–8 turbofan engine model, identify
the combustion chamber assembly part
number, life limit cycles, and revised
inspections.
The FAA also reviewed the following
tasks:
• TASK 05–21–03–200–801, dated
April 1, 2019, from ESM 05–21–03
Airworthiness Limitations—Mandatory
Inspection 001, of GE CF34–8C EM
GEK105091, Rev 51, dated April 1,
2022; and
• TASK 05–21–03–200–801, dated
April 1, 2019, from ESM 05–21–03
Airworthiness Limitations—Mandatory
Inspection 001, of GE CF34–8E EM
GEK112031, Rev 43, dated April 1,
2022.
These tasks, differentiated by GE
CF34–8 turbofan engine model, describe
revised inspection threshold limits and
re-inspection interval limits for the
combustion chamber assembly.
This service information is reasonably
available because the interested parties
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Federal Register / Vol. 88, No. 25 / Tuesday, February 7, 2023 / Rules and Regulations
have access to it through their normal
course of business or by the means
identified in ADDRESSES.
Costs of Compliance
The FAA estimates that this AD
affects 1,633 GE CF34–8C turbofan
engine models and 857 GE CF34–8E
7861
turbofan engine models installed on
airplanes of U.S. registry.
The FAA estimates the following
costs to comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Revise the ALS of the EM and operator’s existing approved maintenance or inspection program (GE
CF34–8C and CF34–8E).
1 work-hour × $85 per hour = $85 ..
Authority for This Rulemaking
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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
ddrumheller on DSK120RN23PROD with RULES
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.
VerDate Sep<11>2014
17:54 Feb 06, 2023
Jkt 259001
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:
■
2023–02–05 General Electric Company:
Amendment 39–22312; Docket No.
FAA–2019–0766; Project Identifier
2019–NE–23–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective March 14, 2023.
(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric
Company (GE) CF34–8C1, CF34–8C5, CF34–
8C5A1, CF34–8C5B1, CF34–8C5A2, CF34–
8C5A3, CF34–8E2, CF34–8E2A1, CF34–8E5,
CF34–8E5A1, CF34–8E5A2, CF34–8E6, and
CF34–8E6A1 model turbofan engines,
including engine models marked on engine
data plate as CF34–8C5/B, CF34–8C5/M,
CF34–8C5A1/B, CF34–8C5A1/M, CF34–
8C5B1/B, CF34–8C5A2/B, and CF34–8C5A2/
M.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7240, Turbine Engine Combustion
Section.
(e) Unsafe Condition
This AD was prompted by a predicted
reduction in the cyclic life of the combustion
chamber assembly aft flange. The FAA is
issuing this AD to prevent failure of the
combustion chamber assembly. The unsafe
condition, if not addressed, could result in
combustion chamber assemblies failing
before reaching their published life limit,
uncontained release of the combustion
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Sfmt 4700
Cost per
product
Parts cost
$0
$85
Cost on U.S.
operators
$211,650
chamber assembly, damage to the engine, and
damage to the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
Within 90 days after the effective date of
this AD, revise the airworthiness limitations
section (ALS) of the existing engine manual
(EM) and the operator’s existing approved
maintenance or inspection program, as
applicable, to incorporate the following
requirements for fluorescent penetrant
inspections of the combustion chamber
assembly aft flange.
(1) For combustion chamber assemblies
with part numbers (P/Ns) 4145T11G08,
4145T11G09, 4180T27G01, or 4180T27G03
installed on GE CF34–8E model turbofan
engines:
(i) Replace Table 801, Static Structures—
Life Limits (Table 801), with the revised
Table 801 in TASK 05–11–05–200–801,
dated March 4, 2021, from ESM 05–11–05
Static Structures—Life Limits (TASK 05–11–
05–200–801), of GE CF34–8E EM
GEK112031, Rev 43, dated April 1, 2022 (GE
CF34–8E EM GEK112031), and
(ii) Add TASK 05–21–03–200–801, dated
April 1, 2019, from ESM 05–21–03
Airworthiness Limitations—Mandatory
Inspection 001 (TASK 05–21–03–200–801),
of GE CF34–8E EM GEK112031. Where the
notes to Tables 801 and 802, included in
TASK 05–21–03–200–801 of GE CF34–8E EM
GEK112031, specify to perform the
inspection within 2,200 cycles from the
issuance date of the temporary revision (TR),
this AD requires performing the inspection
within 2,200 cycles from the effective date of
this AD.
(2) For combustion chamber assemblies
with P/Ns 4126T87G04, 4126T87G05,
4126T87G07, 4126T87G08, 4180T27G04,
4923T82G01, or 4923T82G02 installed on GE
CF34–8C1 model turbofan engines, or with P/
Ns 4145T11G08, 4145T11G10, 4180T27G02,
4180T27G04, or 4923T82G02 installed on GE
CF34–8C5, CF34–8C5/M, CF34–8C5A1,
CF34–8C5A1/M, CF34–8C5A2, CF34–8C5A2/
M, CF34–8C5A3, or CF34–8C5B1 model
turbofan engines:
(i) Replace Tables 801 (for –8C1) and 802
(for –8C5) Static Structures—Life Limits
(Table 801 and Table 802), with the revised
Tables 801 and 802 in TASK 05–11–05–200–
801, dated March 4, 2021, from ESM 05–11–
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Federal Register / Vol. 88, No. 25 / Tuesday, February 7, 2023 / Rules and Regulations
05 Static Structures—Life Limits (TASK 05–
11–05–200–801), of GE CF34–8C EM
GEK105091, Rev 51, dated April 1, 2022 (GE
CF34–8C EM GEK105091); and
(ii) Add TASK 05–21–03–200–801, dated
April 1, 2019, from ESM 05–21–03
Airworthiness Limitations—Mandatory
Inspection 001 (TASK 05–21–03–200–801),
of GE CF34–8C EM GEK105091. Where the
notes to Tables 801, 802, 803, 804, and 805,
included in TASK 05–21–03–200–801 of GE
CF34–8C EM GEK105091, specify to perform
the inspection within 2,200 cycles from the
issuance date of the TR, this AD requires
performing the inspection within 2,200
cycles from the effective date of this AD.
(3) For combustion chamber assemblies
with P/Ns 4145T11G08, 4145T11G10,
4180T27G02, 4180T27G04, or 4923T82G02
installed on GE CF34–8C5B1/B, CF34–8C5/B,
CF34–8C5A1/B, or CF34–8C5A2/B model
turbofan engines:
(i) Replace Table 801 (for/B –8C5) Static
Structures—Life Limits with the revised
Table 801 in TASK 05–11–25–200–801, of GE
CF34–8C EM GEK105091; and
(ii) Add TASK–05–21–03–200–801, of GE
CF34–8C EM GEK105091. Where the notes to
Tables 801, 802, 803, 804, and 805, included
in TASK 05–21–03–200–801 of GE CF34–8C
EM GEK105091, specify to perform the
inspection within 2,200 cycles from the
issuance date of the TR, this AD requires
performing the inspection within 2,200
cycles from the effective date of this AD.
(4) After performing the actions required
by paragraphs (g)(1) through (3) of this AD,
except as provided in paragraph (i) of this
AD, no alternative life limits may be
approved.
(h) Credit for Previous Actions
You may take credit for revising the ALS
of the existing EM and the operator’s existing
approved maintenance or inspection
program, as applicable, required by
paragraphs (g)(1) through (3) of this AD if the
actions were completed before the effective
date of this AD using GE CF34–8E EM TR
05–0085, dated February 21, 2019; GE CF34–
8C TR 05–0141, dated February 21, 2019; GE
CF34–8C TR 05–0143, dated February 13,
2019; GE CF34–8E TR 05–0086, dated
February 13, 2019; or GE CF34–8C TR 05–
0142, dated February 13, 2019.
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(i) 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 certification office,
send it to the attention of the person
identified in paragraph (j) of this AD and
email it 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.
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17:54 Feb 06, 2023
Jkt 259001
(j) Related Information
DEPARTMENT OF TRANSPORTATION
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; email: Scott.M.Stevenson@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) TASK 05–11–05–200–801, dated March
4, 2021, from ESM 05–11–05 Static
Structures—Life Limits, of GE CF34–8C EM
GEK105091, Rev 51, dated April 1, 2022.
(ii) TASK 05–11–05–200–801, dated March
4, 2021, from ESM 05–11–05 Static
Structures—Life Limits, of GE CF34–8E EM
GEK112031, Rev 43, dated April 1, 2022.
(iii) TASK 05–11–25–200–801, dated
November 3, 2020, from ESM 05–11–25
Static Structures—BJ Life Limits, of GE
CF34–8C EM GEK105091, Rev 51, dated
April 1, 2022.
(iv) TASK 05–21–03–200–801, dated April
1, 2019, from ESM 05–21–03 Airworthiness
Limitations—Mandatory Inspection 001, of
GE CF34–8C EM GEK105091, Rev 51, dated
April 1, 2022.
(v) TASK 05–21–03–200–801, dated April
1, 2019, from ESM 05–21–03 Airworthiness
Limitations—Mandatory Inspection 001, of
GE CF34–8E EM GEK112031, Rev 43, dated
April 1, 2022.
(3) For GE service information identified in
this AD, contact General Electric Company,
1 Neumann Way, Cincinnati, OH 45215;
phone: (513) 552–3272; email:
aviation.fleetsupport@ge.com; website:
ge.com.
(4) You may view this service information
at 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.
(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:
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on January 19, 2023.
Ross Landes,
Deputy Director for Regulatory Operations,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2023–02512 Filed 2–6–23; 8:45 am]
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Frm 00024
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2022–0812; Project
Identifier MCAI–2022–00445–T; Amendment
39–22208; AD 2022–21–09]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
Airbus SAS Model A300 B4–600, B4–
600R, and F4–600R series airplanes, and
Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes), and A310
series airplanes. This AD was prompted
by a determination that a new
airworthiness limitation is necessary.
This AD requires revising the existing
maintenance or inspection program, as
applicable, to incorporate a new
airworthiness limitation, as specified in
a European Union Aviation Safety
Agency (EASA) AD, which is
incorporated by reference. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective March 14,
2023.
The Director of the Federal Register
approved the incorporation by reference
of a certain publications listed in this
AD as of March 14, 2023.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2022–0812; 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, the mandatory
continuing airworthiness information
(MCAI), 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.
Material Incorporated by Reference:
• For material incorporated by
reference in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221
8999 000; email ADs@easa.europa.eu;
website easa.europa.eu. You may find
this IBR material on the EASA website
at ad.easa.europa.eu.
• You may view this material at the
FAA, Airworthiness Products Section,
SUMMARY:
E:\FR\FM\07FER1.SGM
07FER1
]]>Agencies
[Federal Register Volume 88, Number 25 (Tuesday, February 7, 2023)]
[Rules and Regulations]
[Pages 7859-7862]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-02512]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0766; Project Identifier 2019-NE-23-AD; Amendment
39-22312; AD 2023-02-05]
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) CF34-8C1, CF34-8C5, CF34-8C5A1, CF34-
8C5B1, CF34-8C5A2, CF34-8C5A3, CF34-8E2, CF34-8E2A1, CF34-8E5, CF34-
8E5A1, CF34-8E5A2, CF34-8E6, and CF34-8E6A1 model turbofan engines.
This AD was prompted by a predicted reduction in the cyclic life of the
combustion chamber assembly aft flange. This AD requires revisions to
the airworthiness limitations section (ALS) of the existing engine
manual (EM) and the operator's existing approved maintenance or
inspection program, as applicable, to incorporate initial and
repetitive fluorescent penetrant inspections (FPIs) of the combustion
chamber assembly. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective March 14, 2023.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 14,
2023.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov by
searching for and locating Docket No. FAA-2019-0766; 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.
Material Incorporated by Reference:
For GE service information identified in this final rule,
contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215;
phone: (513) 552-3272; email: ge.com">[email protected]ge.com; website:
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 regulations.gov by searching for and locating Docket
No. FAA-2019-0766.
FOR FURTHER INFORMATION CONTACT: Scott Stevenson, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803;
phone: (781) 238-7132; email: [email protected].
[[Page 7860]]
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a supplemental notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an AD that would apply to all GE
CF34-8C1, CF34-8C5, CF34-8C5A1, CF34-8C5B1, CF34-C5A2, CF34-8C5A3,
CF34-8E2, CF34-8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6, and
CF34-8E6A1 (CF34-8C and GE CF34-8E) model turbofan engines, including
engine models marked on the engine data plate as CF34-8C5/B, CF34-8C5/
M, CF34-8C5A1/B, CF34-8C5A1/M, CF34-8C5B1/B, CF34-8C5A2/B, and CF34-
8C5A2/M. The SNPRM published in the Federal Register on October 07,
2022 (87 FR 60944). The SNPRM was prompted by a predicted reduction in
the cyclic life of the combustion chamber assembly aft flange. As a
result, the manufacturer incorporated temporary revisions (TRs) into
the GE CF34-8C and GE CF34-8E EMs for a scheduled maintenance check. In
the SNPRM, the FAA proposed to require revisions to the ALS of the
existing EM and the operator's existing approved maintenance or
inspection program, as applicable, to incorporate initial and
repetitive FPIs of the combustion chamber assembly. 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 three commenters. The commenters
were Horizon Air, Japan Airlines (JAL), and SkyWest Airlines (SkyWest).
The following presents the comments received on the SNPRM and the FAA's
response to each comment.
Request To Replace ``ESM'' Reference With ``EM'' Reference
Horizon Air requested that the FAA replace all references of
``ESM'' with ``EM'' in this final rule. Horizon Air reasoned that the
SNPRM only defines the acronym ``EM,'' and both acronyms are used
interchangeably in the SNPRM.
The FAA clarifies that the reference to ``ESM'' is not an acronym
defined by the FAA in the proposed AD and used interchangeably with
``EM.'' ``ESM'' is part of GE's chapter title within each task
reference and must be used for an accurate reference. The FAA did not
change this AD as a result of this comment.
Request To Add the Date of the Task in Paragraph (g)(3)
Horizon Air requested that the FAA include the task revision date
for ``TASK 05-21-03-200-801,'' referenced in paragraph (g)(3)(ii) of
the SNPRM. Horizon Air reasoned that adding the task revision date
would make the wording consistent with the dates of the tasks in
paragraphs (g)(1)(ii) and (2)(ii) of the SNPRM.
The FAA established a shorthand notation in paragraph (g)(2)(ii) of
the SNPRM, which contains the full citation, including the task
revision date, followed by the shorthand notation ``TASK 05-21-03-200-
801.'' The FAA then used the established shorthand notation to
reference the task in paragraph (g)(3)(ii) of the SNPRM. The FAA did
not change this AD as a result of this comment.
Request To Revise Paragraph (g)(1)(ii), (2)(ii), and (3)(ii) of the AD
Horizon Air requested that the FAA revise paragraphs (g)(1)(ii),
(2)(ii), and (3)(ii) of the AD, as those paragraphs do not clearly
include that performance of the inspection within 2,200 cycles from the
effective date of this AD is only applicable to those combustion
chamber assemblies that have exceeded the inspection threshold
specified in the tables referenced in TASK 05-21-03-200-801. Similarly,
JAL requested that the FAA revise paragraph (g)(1)(ii) for the same
reasons articulated by Horizon Air.
In response to these comments, the FAA has revised the language in
paragraphs (g)(1)(ii), (2)(ii), and (3)(ii) of this AD to clarify that
where the notes to Tables 801, 802, 803, 804, and 805, included in TASK
05-21-03-200-801, specify to perform the inspection within 2,200 cycles
from the issuance date of the TR, this AD requires performing the
inspection within 2,200 cycles from the effective date of this AD. The
FAA further clarifies that the notes are part of the task, and
therefore, has removed ``including the notes.''
Request To Correct an Incorrect Reference to a Task in Paragraph
(g)(2)(i)
SkyWest requested that the FAA correct an incorrect reference in
paragraph (g)(2)(i) of this AD. SkyWest noted that Table 802 does not
exist in TASK 05-11-25-200-801, which is specific to GE CF34-8C5 model
turbofan engines with/B minor model designation.
In response to this comment, the FAA has revised paragraph
(g)(2)(i) of this AD from ``Table 801 in TASK 05-11-05-200-801 and
Table 802 in TASK 05-11-25-200-801, dated November 3, 2020, from ESM
05-11-25 Static Structures--BJ Life Limits (TASK 05-11-25-200-801)'' to
``Tables 801 (for -8C1) and 802 (for -8C5) in TASK 05-11-05-200-801,
dated March 4, 2021, from ESM 05-11-05 Static Structures--Life Limits
(TASK 05-11-05-200-801).''
Conclusion
The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes, and
any other changes described previously, this AD is adopted as proposed
in the SNPRM. None of the changes will increase the economic burden on
any operator.
Related Service Information Under 1 CFR Part 51
The FAA reviewed the following tasks:
TASK 05-11-05-200-801, dated March 4, 2021, from ESM 05-
11-05 Static Structures--Life Limits, of GE CF34-8C EM GEK105091, Rev
51, dated April 1, 2022;
TASK 05-11-05-200-801, dated March 4, 2021, from ESM 05-
11-05 Static Structures--Life Limits, of GE CF34-8E EM GEK112031, Rev
43, dated April 1, 2022; and
TASK 05-11-25-200-801, dated November 3, 2020, from ESM
05-11-25 Static Structures--BJ Life Limits, of GE CF34-8C EM GEK105091,
Rev 51, dated April 1, 2022.
These tasks, differentiated by GE CF34-8 turbofan engine model,
identify the combustion chamber assembly part number, life limit
cycles, and revised inspections.
The FAA also reviewed the following tasks:
TASK 05-21-03-200-801, dated April 1, 2019, from ESM 05-
21-03 Airworthiness Limitations--Mandatory Inspection 001, of GE CF34-
8C EM GEK105091, Rev 51, dated April 1, 2022; and
TASK 05-21-03-200-801, dated April 1, 2019, from ESM 05-
21-03 Airworthiness Limitations--Mandatory Inspection 001, of GE CF34-
8E EM GEK112031, Rev 43, dated April 1, 2022.
These tasks, differentiated by GE CF34-8 turbofan engine model,
describe revised inspection threshold limits and re-inspection interval
limits for the combustion chamber assembly.
This service information is reasonably available because the
interested parties
[[Page 7861]]
have access to it through their normal course of business or by the
means identified in ADDRESSES.
Costs of Compliance
The FAA estimates that this AD affects 1,633 GE CF34-8C turbofan
engine models and 857 GE CF34-8E turbofan engine models 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 the ALS of the EM and 1 work-hour x $85 per $0 $85 $211,650
operator's existing approved hour = $85.
maintenance or inspection program (GE
CF34-8C and CF34-8E).
----------------------------------------------------------------------------------------------------------------
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:
2023-02-05 General Electric Company: Amendment 39-22312; Docket No.
FAA-2019-0766; Project Identifier 2019-NE-23-AD.
(a) Effective Date
This airworthiness directive (AD) is effective March 14, 2023.
(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric Company (GE) CF34-8C1, CF34-
8C5, CF34-8C5A1, CF34-8C5B1, CF34-8C5A2, CF34-8C5A3, CF34-8E2, CF34-
8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6, and CF34-8E6A1
model turbofan engines, including engine models marked on engine
data plate as CF34-8C5/B, CF34-8C5/M, CF34-8C5A1/B, CF34-8C5A1/M,
CF34-8C5B1/B, CF34-8C5A2/B, and CF34-8C5A2/M.
(d) Subject
Joint Aircraft System Component (JASC) Code 7240, Turbine Engine
Combustion Section.
(e) Unsafe Condition
This AD was prompted by a predicted reduction in the cyclic life
of the combustion chamber assembly aft flange. The FAA is issuing
this AD to prevent failure of the combustion chamber assembly. The
unsafe condition, if not addressed, could result in combustion
chamber assemblies failing before reaching their published life
limit, uncontained release of the combustion chamber assembly,
damage to the engine, and damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Within 90 days after the effective date of this AD, revise the
airworthiness limitations section (ALS) of the existing engine
manual (EM) and the operator's existing approved maintenance or
inspection program, as applicable, to incorporate the following
requirements for fluorescent penetrant inspections of the combustion
chamber assembly aft flange.
(1) For combustion chamber assemblies with part numbers (P/Ns)
4145T11G08, 4145T11G09, 4180T27G01, or 4180T27G03 installed on GE
CF34-8E model turbofan engines:
(i) Replace Table 801, Static Structures--Life Limits (Table
801), with the revised Table 801 in TASK 05-11-05-200-801, dated
March 4, 2021, from ESM 05-11-05 Static Structures--Life Limits
(TASK 05-11-05-200-801), of GE CF34-8E EM GEK112031, Rev 43, dated
April 1, 2022 (GE CF34-8E EM GEK112031), and
(ii) Add TASK 05-21-03-200-801, dated April 1, 2019, from ESM
05-21-03 Airworthiness Limitations--Mandatory Inspection 001 (TASK
05-21-03-200-801), of GE CF34-8E EM GEK112031. Where the notes to
Tables 801 and 802, included in TASK 05-21-03-200-801 of GE CF34-8E
EM GEK112031, specify to perform the inspection within 2,200 cycles
from the issuance date of the temporary revision (TR), this AD
requires performing the inspection within 2,200 cycles from the
effective date of this AD.
(2) For combustion chamber assemblies with P/Ns 4126T87G04,
4126T87G05, 4126T87G07, 4126T87G08, 4180T27G04, 4923T82G01, or
4923T82G02 installed on GE CF34-8C1 model turbofan engines, or with
P/Ns 4145T11G08, 4145T11G10, 4180T27G02, 4180T27G04, or 4923T82G02
installed on GE CF34-8C5, CF34-8C5/M, CF34-8C5A1, CF34-8C5A1/M,
CF34-8C5A2, CF34-8C5A2/M, CF34-8C5A3, or CF34-8C5B1 model turbofan
engines:
(i) Replace Tables 801 (for -8C1) and 802 (for -8C5) Static
Structures--Life Limits (Table 801 and Table 802), with the revised
Tables 801 and 802 in TASK 05-11-05-200-801, dated March 4, 2021,
from ESM 05-11-
[[Page 7862]]
05 Static Structures--Life Limits (TASK 05-11-05-200-801), of GE
CF34-8C EM GEK105091, Rev 51, dated April 1, 2022 (GE CF34-8C EM
GEK105091); and
(ii) Add TASK 05-21-03-200-801, dated April 1, 2019, from ESM
05-21-03 Airworthiness Limitations--Mandatory Inspection 001 (TASK
05-21-03-200-801), of GE CF34-8C EM GEK105091. Where the notes to
Tables 801, 802, 803, 804, and 805, included in TASK 05-21-03-200-
801 of GE CF34-8C EM GEK105091, specify to perform the inspection
within 2,200 cycles from the issuance date of the TR, this AD
requires performing the inspection within 2,200 cycles from the
effective date of this AD.
(3) For combustion chamber assemblies with P/Ns 4145T11G08,
4145T11G10, 4180T27G02, 4180T27G04, or 4923T82G02 installed on GE
CF34-8C5B1/B, CF34-8C5/B, CF34-8C5A1/B, or CF34-8C5A2/B model
turbofan engines:
(i) Replace Table 801 (for/B -8C5) Static Structures--Life
Limits with the revised Table 801 in TASK 05-11-25-200-801, of GE
CF34-8C EM GEK105091; and
(ii) Add TASK-05-21-03-200-801, of GE CF34-8C EM GEK105091.
Where the notes to Tables 801, 802, 803, 804, and 805, included in
TASK 05-21-03-200-801 of GE CF34-8C EM GEK105091, specify to perform
the inspection within 2,200 cycles from the issuance date of the TR,
this AD requires performing the inspection within 2,200 cycles from
the effective date of this AD.
(4) After performing the actions required by paragraphs (g)(1)
through (3) of this AD, except as provided in paragraph (i) of this
AD, no alternative life limits may be approved.
(h) Credit for Previous Actions
You may take credit for revising the ALS of the existing EM and
the operator's existing approved maintenance or inspection program,
as applicable, required by paragraphs (g)(1) through (3) of this AD
if the actions were completed before the effective date of this AD
using GE CF34-8E EM TR 05-0085, dated February 21, 2019; GE CF34-8C
TR 05-0141, dated February 21, 2019; GE CF34-8C TR 05-0143, dated
February 13, 2019; GE CF34-8E TR 05-0086, dated February 13, 2019;
or GE CF34-8C TR 05-0142, dated February 13, 2019.
(i) 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
certification office, send it to the attention of the person
identified in paragraph (j) of this AD and email it 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.
(j) 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; email:
[email protected].
(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) TASK 05-11-05-200-801, dated March 4, 2021, from ESM 05-11-
05 Static Structures--Life Limits, of GE CF34-8C EM GEK105091, Rev
51, dated April 1, 2022.
(ii) TASK 05-11-05-200-801, dated March 4, 2021, from ESM 05-11-
05 Static Structures--Life Limits, of GE CF34-8E EM GEK112031, Rev
43, dated April 1, 2022.
(iii) TASK 05-11-25-200-801, dated November 3, 2020, from ESM
05-11-25 Static Structures--BJ Life Limits, of GE CF34-8C EM
GEK105091, Rev 51, dated April 1, 2022.
(iv) TASK 05-21-03-200-801, dated April 1, 2019, from ESM 05-21-
03 Airworthiness Limitations--Mandatory Inspection 001, of GE CF34-
8C EM GEK105091, Rev 51, dated April 1, 2022.
(v) TASK 05-21-03-200-801, dated April 1, 2019, from ESM 05-21-
03 Airworthiness Limitations--Mandatory Inspection 001, of GE CF34-
8E EM GEK112031, Rev 43, dated April 1, 2022.
(3) For GE service information identified in this AD, contact
General Electric Company, 1 Neumann Way, Cincinnati, OH 45215;
phone: (513) 552-3272; email: ge.com">[email protected]ge.com; website:
ge.com.
(4) You may view this service information at 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.
(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: [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on January 19, 2023.
Ross Landes,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2023-02512 Filed 2-6-23; 8:45 am]
BILLING CODE 4910-13-P
