Airworthiness Directives; General Electric Company Turbofan Engines, 78513-78515 [2022-27835]
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78513
Rules and Regulations
Federal Register
Vol. 87, No. 245
Thursday, December 22, 2022
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2022–0978; Project
Identifier AD–2022–00460–E; Amendment
39–22276; AD 2022–25–20]
The Code of Federal Regulations is sold by
the Superintendent of Documents.
RIN 2120–AA64
DEPARTMENT OF ENERGY
Airworthiness Directives; General
Electric Company Turbofan Engines
10 CFR Parts 429 and 431
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
[EERE–2017–BT–TP–0031]
RIN 1904–AE06
Energy Conservation Program: Test
Procedure for Air-Cooled, ThreePhase, Small Commercial Package Air
Conditioning and Heating Equipment
With a Cooling Capacity of Less Than
65,000 Btu/h and Air-Cooled, ThreePhase, Variable Refrigerant Flow Air
Conditioners and Heat Pumps With a
Cooling Capacity of Less Than 65,000
Btu/h
Correction
In rule document 2022–26418,
appearing on pages 77298 through
77328 in the issue of Friday, December
16, 2022, make the following correction:
Appendix F to Subpart F of Part 431
[Corrected]
On page 77327, in Appendix F to
Subpart F of Part 431, in the first
column, in amendatory instruction 13,
the appendix head should read:
■
lotter on DSK11XQN23PROD with RULES1
The FAA is adopting a new
airworthiness directive (AD) for certain
General Electric Company (GE) GEnx–
1B and GEnx–2B model turbofan
engines. This AD was prompted by a
manufacturer investigation that revealed
that certain high-pressure turbine (HPT)
stage 2 disks, forward seals, and stages
6–10 compressor rotor spools were
manufactured from powder metal
material suspected to contain iron
inclusion. This AD requires replacement
of the affected HPT stage 2 disks,
forward seals, and stages 6–10
compressor rotor spools. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective January 26,
2023.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov by searching
for and locating Docket No. FAA–2022–
0978; 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:
Alexei Marqueen, Aviation Safety
Engineer, ECO Branch, FAA, 1200
District Avenue, Burlington, MA 01803;
phone: (781) 238–7178; email:
Alexei.T.Marqueen@faa.gov.
SUPPLEMENTARY INFORMATION:
SUMMARY:
Appendix F to Subpart F of Part 431—
Uniform Test Method for the
Measurement of Energy Consumption of
Air-Cooled, Three-Phase, Small
Commercial Package Air Conditioning
and Heating Equipment With a Cooling
Capacity of Less Than 65,000 Btu/h and
Air-Cooled, Three-Phase, Variable
Refrigerant Flow Multi-Split Air
Conditioners and Heat Pumps With a
Cooling Capacity of Less Than 65,000
Btu/h
[FR Doc. C1–2022–26418 Filed 12–21–22; 8:45 am]
BILLING CODE 0099–10–P
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
VerDate Sep<11>2014
16:02 Dec 21, 2022
Jkt 259001
PO 00000
Frm 00001
Fmt 4700
Sfmt 4700
part 39 by adding an AD that would
apply to certain GEnx–1B64, GEnx–
1B64/P1, GEnx–1B64/P2, GEnx–1B67,
GEnx–1B67/P1, GEnx–1B67/P2, GEnx–
1B70, GEnx–1B70/75/P1, GEnx–1B70/
75/P2, GEnx–1B70/P1, GEnx–1B70/P2,
GEnx–1B70C/P1, GEnx–1B70C/P2,
GEnx–1B74/75/P1, GEnx–1B74/75/P2,
GEnx–1B76/P2, GEnx–1B76A/P2
(GEnx–1B), GEnx–2B67, GEnx–2B67B,
and GEnx–2B67/P (GEnx–2B) model
turbofan engines. The NPRM published
in the Federal Register on September 9,
2022 (87 FR 55328). The NPRM was
prompted by a manufacturer
investigation that revealed that certain
HPT stage 2 disks, forward seals, and
stages 6–10 compressor rotor spools
were manufactured from powder metal
material suspected to contain iron
inclusion. Further investigation by the
manufacturer determined that the iron
inclusion is attributed to deficiencies in
the manufacturing process. The
investigation by the manufacturer also
determined that certain GEnx–1B and
GEnx–2B HPT stage 2 disks, forward
seals, and stages 6–10 compressor rotor
spools made from billets manufactured
using the same process may have
reduced material properties and a lower
fatigue life capability due to iron
inclusion, which may cause premature
fracture and uncontained failure. In the
NPRM, the FAA proposed to require
replacement of certain HPT stage 2
disks, forward seals, and stages 6–10
compressor rotor spools with parts
eligible for installation. 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
four commenters. The commenters were
Air Line Pilots Association,
International (ALPA), American
Airlines, GE Aviation, and The Boeing
Company (Boeing). ALPA, American
Airlines, and Boeing supported the
proposed AD without change. GE
Aviation requested a change to the
proposed AD. The following presents
the comments received on the NPRM
and the FAA’s response to each
comment.
E:\FR\FM\22DER1.SGM
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78514
Federal Register / Vol. 87, No. 245 / Thursday, December 22, 2022 / Rules and Regulations
Request To Add Alternate Part
Numbers to AD Applicability
GE Aviation requested that the FAA
add alternate part numbers (P/Ns) to
Table 1 to paragraph (c) of this AD. GE
Aviation explained that the forward seal
and stages 6–10 compressor rotor spool
may have reworked P/Ns that occur
after entry into service. While the P/Ns
provided in the NPRM are the best
information available as to current P/Ns,
GE requested that the FAA add certain
alternate P/Ns to Table 1 to paragraph
(c), Applicability, of this final rule to
ensure compliance.
The FAA agrees for the reasons
provided and has revised Table 1 to
paragraph (c), Applicability, of this AD
as requested by GE Aviation.
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 NPRM.
None of the changes will increase the
economic burden on any operator.
Related Service Information
The FAA reviewed GE GEnx–1B
Service Bulletin 72–0505, Revision 02,
dated April 5, 2022. The FAA also
reviewed GE GEnx–2B Service Bulletin
72–0444, Revision 02, dated April 5,
2022. This service information describes
procedures for removing the HPT stage
2 disk, forward seal, and stages 6–10
compressor rotor spool. These
documents are distinct since they apply
to different engine models.
Costs of Compliance
The FAA estimates that this AD
affects 3 engines installed on airplanes
of U.S. registry. The FAA estimates that
0 engines installed on airplanes of U.S.
registry require replacement of the
forward seal or HPT stage 2 disk.
The FAA estimates the following
costs to comply with this AD:
ESTIMATED COSTS
Cost on U.S.
operators
Labor cost
Parts cost
Replace stages 6–10 compressor rotor
spool.
Replace forward seal ..................................
Replace HPT stage 2 disk ..........................
8 work-hours × $85 per hour = $680 .......
$846,519 (pro-rated)
$847,199
$2,541,597
8 work-hours × $85 per hour = $680 .......
8 work-hours × $85 per hour = $680 .......
364,558 (pro-rated)
363,424 (pro-rated)
365,238
364,104
0
0
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
lotter on DSK11XQN23PROD with RULES1
Cost per
product
Action
VerDate Sep<11>2014
16:02 Dec 21, 2022
Jkt 259001
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
1. The authority citation for part 39
continues to read as follows:
■
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
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:
■
2022–25–20 General Electric Company:
Amendment 39–22276; Docket No.
FAA–2022–0978; Project Identifier AD–
2022–00460–E.
(a) Effective Date
This airworthiness directive (AD) is
effective January 26, 2023.
(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric
Company GEnx–1B64, GEnx–1B64/P1,
GEnx–1B64/P2, GEnx–1B67, GEnx–1B67/P1,
GEnx–1B67/P2, GEnx–1B70, GEnx–1B70/75/
P1, GEnx–1B70/75/P2, GEnx–1B70/P1,
GEnx–1B70/P2, GEnx–1B70C/P1, GEnx–
1B70C/P2, GEnx–1B74/75/P1, GEnx–1B74/
75/P2, GEnx–1B76/P2, GEnx–1B76A/P2,
GEnx–2B67, GEnx–2B67B, and GEnx–2B67/P
model turbofan engines with an installed
high-pressure turbine (HPT) stage 2 disk,
forward seal, or stages 6–10 compressor rotor
spool with a part number (P/N) and serial
number (S/N) identified in Table 1 to
paragraph (c) of this AD.
E:\FR\FM\22DER1.SGM
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78515
Federal Register / Vol. 87, No. 245 / Thursday, December 22, 2022 / Rules and Regulations
TABLE 1 TO PARAGRAPH (c)—AFFECTED HPT STAGE 2 DISKS, FORWARD SEALS, AND STAGES 6–10 COMPRESSOR
ROTOR SPOOLS
Part name
P/N
HPT stage 2 disk .....................................................................................................................................................
2300M84P02
Forward seal ............................................................................................................................................................
2417M60P02
or
2759M04P01
Stages 6–10 compressor rotor spool ......................................................................................................................
2357M30G02
or
2340M36G01
2439M35G01
or
2610M90G01
Stages 6–10 compressor rotor spool ......................................................................................................................
Stages 6–10 compressor rotor spool ......................................................................................................................
(d) Subject
Joint Aircraft System Component (JASC)
Code 7230, Turbine Engine Compressor
Section; 7250, Turbine Section.
(e) Unsafe Condition
This AD was prompted by a manufacturer
investigation that revealed that certain HPT
stage 2 disks, forward seals, and stages 6–10
compressor rotor spools were manufactured
from powder metal material suspected to
contain iron inclusion. The FAA is issuing
this AD to prevent fracture and potential
uncontained failure of certain HPT stage 2
disks, forward seals, and stages 6–10
compressor rotor spools. The unsafe
condition, if not addressed, could result in
uncontained debris release, damage to the
engine, and damage to the aircraft.
lotter on DSK11XQN23PROD with RULES1
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Before exceeding 600 flight cycles after
the effective date of this AD, remove the
affected HPT stage 2 disk, forward seal, and
stages 6–10 compressor rotor spool from
service and replace with a part eligible for
installation.
(2) For affected engines not in service,
before further flight, remove the affected HPT
stage 2 disk, forward seal, and stages 6–10
compressor rotor spool and replace with a
part eligible for installation.
(h) Definitions
(1) For the purpose of this AD, a ‘‘part
eligible for installation’’ is any HPT stage 2
disk, forward seal, or stages 6–10 compressor
VerDate Sep<11>2014
16:02 Dec 21, 2022
Jkt 259001
rotor spool with a P/N and S/N not identified
in Table 1 to paragraph (c) of this AD.
(2) For the purpose of this AD, ‘‘engines
not in service’’ are engines that are in longterm or short-term storage as of the effective
date of this AD.
(i) Installation Prohibition
After the effective date of this AD, do not
install an HPT stage 2 disk, forward seal, or
stages 6–10 compressor rotor spool with a P/
N and S/N identified in Table 1 to paragraph
(c) of this AD onto any engine.
(j) 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 (k) of this AD and
email 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.
(k) Related Information
For more information about this AD,
contact Alexei Marqueen, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: (781)
238–7178; email: Alexei.T.Marqueen@
faa.gov.
(l) Material Incorporated by Reference
None.
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
2439M35G02
S/N
TMT4AF08
TMT4AF10
TMT4AF11
TMT4AF12
VOLF1931
VOLF1933
VOLF1942
VOLF1977
VOLF1993
VOLF2014
GWN0R86N
GWN0RCKT
GWN0R62G
GWN0R86J
GWN0R5EK
GWN0R6EH
GWN0R7K1
GWN0R89A
GWN0RA89
GWN0R6K9
GWN0R7G9
GWN0R7K4
GWN0R752
GWN0R98P
Issued on December 2, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022–27835 Filed 12–21–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2022–1054; Project
Identifier AD–2022–00278–T; Amendment
39–22255; AD 2022–24–15]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2017–18–
05, which applied to all The Boeing
Company Model 747–100, 747–100B,
747–100B SUD, 747–200B, 747–200C,
747–200F, 747–300, 747–400, 747–
400D, 747–400F, 747SR, and 747SP
series airplanes. AD 2017–18–05
required repetitive replacement or
inspection of certain fuse pins, and
applicable on-condition actions. This
AD was prompted by a report of damage
found at the lower trailing edge panels
SUMMARY:
E:\FR\FM\22DER1.SGM
22DER1
]]>Agencies
[Federal Register Volume 87, Number 245 (Thursday, December 22, 2022)]
[Rules and Regulations]
[Pages 78513-78515]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-27835]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0978; Project Identifier AD-2022-00460-E;
Amendment 39-22276; AD 2022-25-20]
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
certain General Electric Company (GE) GEnx-1B and GEnx-2B model
turbofan engines. This AD was prompted by a manufacturer investigation
that revealed that certain high-pressure turbine (HPT) stage 2 disks,
forward seals, and stages 6-10 compressor rotor spools were
manufactured from powder metal material suspected to contain iron
inclusion. This AD requires replacement of the affected HPT stage 2
disks, forward seals, and stages 6-10 compressor rotor spools. The FAA
is issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective January 26, 2023.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov by
searching for and locating Docket No. FAA-2022-0978; 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: Alexei Marqueen, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803;
phone: (781) 238-7178; 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 certain GEnx-1B64,
GEnx-1B64/P1, GEnx-1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-1B67/P2,
GEnx-1B70, GEnx-1B70/75/P1, GEnx-1B70/75/P2, GEnx-1B70/P1, GEnx-1B70/
P2, GEnx-1B70C/P1, GEnx-1B70C/P2, GEnx-1B74/75/P1, GEnx-1B74/75/P2,
GEnx-1B76/P2, GEnx-1B76A/P2 (GEnx-1B), GEnx-2B67, GEnx-2B67B, and GEnx-
2B67/P (GEnx-2B) model turbofan engines. The NPRM published in the
Federal Register on September 9, 2022 (87 FR 55328). The NPRM was
prompted by a manufacturer investigation that revealed that certain HPT
stage 2 disks, forward seals, and stages 6-10 compressor rotor spools
were manufactured from powder metal material suspected to contain iron
inclusion. Further investigation by the manufacturer determined that
the iron inclusion is attributed to deficiencies in the manufacturing
process. The investigation by the manufacturer also determined that
certain GEnx-1B and GEnx-2B HPT stage 2 disks, forward seals, and
stages 6-10 compressor rotor spools made from billets manufactured
using the same process may have reduced material properties and a lower
fatigue life capability due to iron inclusion, which may cause
premature fracture and uncontained failure. In the NPRM, the FAA
proposed to require replacement of certain HPT stage 2 disks, forward
seals, and stages 6-10 compressor rotor spools with parts eligible for
installation. 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 four commenters. The commenters were
Air Line Pilots Association, International (ALPA), American Airlines,
GE Aviation, and The Boeing Company (Boeing). ALPA, American Airlines,
and Boeing supported the proposed AD without change. GE Aviation
requested a change to the proposed AD. The following presents the
comments received on the NPRM and the FAA's response to each comment.
[[Page 78514]]
Request To Add Alternate Part Numbers to AD Applicability
GE Aviation requested that the FAA add alternate part numbers (P/
Ns) to Table 1 to paragraph (c) of this AD. GE Aviation explained that
the forward seal and stages 6-10 compressor rotor spool may have
reworked P/Ns that occur after entry into service. While the P/Ns
provided in the NPRM are the best information available as to current
P/Ns, GE requested that the FAA add certain alternate P/Ns to Table 1
to paragraph (c), Applicability, of this final rule to ensure
compliance.
The FAA agrees for the reasons provided and has revised Table 1 to
paragraph (c), Applicability, of this AD as requested by GE Aviation.
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 NPRM. None of the changes will increase the economic burden on
any operator.
Related Service Information
The FAA reviewed GE GEnx-1B Service Bulletin 72-0505, Revision 02,
dated April 5, 2022. The FAA also reviewed GE GEnx-2B Service Bulletin
72-0444, Revision 02, dated April 5, 2022. This service information
describes procedures for removing the HPT stage 2 disk, forward seal,
and stages 6-10 compressor rotor spool. These documents are distinct
since they apply to different engine models.
Costs of Compliance
The FAA estimates that this AD affects 3 engines installed on
airplanes of U.S. registry. The FAA estimates that 0 engines installed
on airplanes of U.S. registry require replacement of the forward seal
or HPT stage 2 disk.
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
----------------------------------------------------------------------------------------------------------------
Replace stages 6-10 compressor 8 work-hours x $85 per $846,519 (pro- $847,199 $2,541,597
rotor spool. hour = $680. rated).
Replace forward seal............. 8 work-hours x $85 per 364,558 (pro-rated) 365,238 0
hour = $680.
Replace HPT stage 2 disk......... 8 work-hours x $85 per 363,424 (pro-rated) 364,104 0
hour = $680.
----------------------------------------------------------------------------------------------------------------
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:
2022-25-20 General Electric Company: Amendment 39-22276; Docket No.
FAA-2022-0978; Project Identifier AD-2022-00460-E.
(a) Effective Date
This airworthiness directive (AD) is effective January 26, 2023.
(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric Company GEnx-1B64, GEnx-
1B64/P1, GEnx-1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-1B67/P2, GEnx-
1B70, GEnx-1B70/75/P1, GEnx-1B70/75/P2, GEnx-1B70/P1, GEnx-1B70/P2,
GEnx-1B70C/P1, GEnx-1B70C/P2, GEnx-1B74/75/P1, GEnx-1B74/75/P2,
GEnx-1B76/P2, GEnx-1B76A/P2, GEnx-2B67, GEnx-2B67B, and GEnx-2B67/P
model turbofan engines with an installed high-pressure turbine (HPT)
stage 2 disk, forward seal, or stages 6-10 compressor rotor spool
with a part number (P/N) and serial number (S/N) identified in Table
1 to paragraph (c) of this AD.
[[Page 78515]]
Table 1 to Paragraph (c)--Affected HPT Stage 2 Disks, Forward Seals, and
Stages 6-10 Compressor Rotor Spools
------------------------------------------------------------------------
Part name P/N S/N
------------------------------------------------------------------------
HPT stage 2 disk................ 2300M84P02 TMT4AF08
TMT4AF10
TMT4AF11
TMT4AF12
Forward seal.................... 2417M60P02 VOLF1931
or VOLF1933
2759M04P01 VOLF1942
...................... VOLF1977
...................... VOLF1993
...................... VOLF2014
Stages 6-10 compressor rotor 2357M30G02 GWN0R86N
spool. or
2340M36G01
Stages 6-10 compressor rotor 2439M35G01 GWN0RCKT
spool. or GWN0R62G
2610M90G01 GWN0R86J
...................... GWN0R5EK
...................... GWN0R6EH
...................... GWN0R7K1
...................... GWN0R89A
Stages 6-10 compressor rotor 2439M35G02 GWN0RA89
spool. GWN0R6K9
...................... GWN0R7G9
...................... GWN0R7K4
...................... GWN0R752
...................... GWN0R98P
------------------------------------------------------------------------
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section; 7250, Turbine Section.
(e) Unsafe Condition
This AD was prompted by a manufacturer investigation that
revealed that certain HPT stage 2 disks, forward seals, and stages
6-10 compressor rotor spools were manufactured from powder metal
material suspected to contain iron inclusion. The FAA is issuing
this AD to prevent fracture and potential uncontained failure of
certain HPT stage 2 disks, forward seals, and stages 6-10 compressor
rotor spools. The unsafe condition, if not addressed, could result
in uncontained debris release, damage to the engine, and damage to
the aircraft.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Before exceeding 600 flight cycles after the effective date
of this AD, remove the affected HPT stage 2 disk, forward seal, and
stages 6-10 compressor rotor spool from service and replace with a
part eligible for installation.
(2) For affected engines not in service, before further flight,
remove the affected HPT stage 2 disk, forward seal, and stages 6-10
compressor rotor spool and replace with a part eligible for
installation.
(h) Definitions
(1) For the purpose of this AD, a ``part eligible for
installation'' is any HPT stage 2 disk, forward seal, or stages 6-10
compressor rotor spool with a P/N and S/N not identified in Table 1
to paragraph (c) of this AD.
(2) For the purpose of this AD, ``engines not in service'' are
engines that are in long-term or short-term storage as of the
effective date of this AD.
(i) Installation Prohibition
After the effective date of this AD, do not install an HPT stage
2 disk, forward seal, or stages 6-10 compressor rotor spool with a
P/N and S/N identified in Table 1 to paragraph (c) of this AD onto
any engine.
(j) 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 (k) of this AD and email 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.
(k) Related Information
For more information about this AD, contact Alexei Marqueen,
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: (781) 238-7178; email:
[email protected].
(l) Material Incorporated by Reference
None.
Issued on December 2, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-27835 Filed 12-21-22; 8:45 am]
BILLING CODE 4910-13-P
