Airworthiness Directives; General Electric Company Turbofan Engines, 75918-75920 [2022-26831]
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<![CDATA[
75918
Federal Register / Vol. 87, No. 237 / Monday, December 12, 2022 / Rules and Regulations
the initial inspection required by paragraph
(i) of this AD has been done. Although BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.32–156, Revision 1,
dated July 3, 2001, specifies to report certain
information to the manufacturer, this AD
does not require a report.
(1) If the number of flight cycles
accumulated on the side stay can be
positively determined: Inspect before the
accumulation of 2,000 total flight cycles on
the side stay, or within 500 flight cycles after
May 2, 2005 (the effective date of AD 2005–
06–14), whichever occurs later.
(2) If the number of flight cycles
accumulated on the side stay cannot be
positively determined: Inspect within 500
flight cycles after May 2, 2005 (the effective
date of AD 2005–06–14).
(h) Retained Optional Terminating Action
for Paragraph (g) of This AD, With No
Changes
This paragraph restates the optional
terminating action of paragraph (g) of AD
2005–06–14, with no changes. Relocation of
each affected grease nipple to the upper
surface of the outer link of the MLG side
stays terminates the repetitive inspections
required by paragraph (g) of this AD, if the
relocation action is done in accordance with
paragraph 2.C. of the Accomplishment
Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.32–
156, Revision 1, dated July 3, 2001.
(i) New Requirements
Except as specified in paragraph (j) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, United Kingdom Civil
Aviation Authority AD G–2022–0018, dated
October 18, 2022 (U.K. CAA AD G–2022–
0018).
(j) Exceptions to U.K. CAA AD G–2022–0018
(1) Where U.K. CAA AD G–2022–0018
refers to its effective date, this AD requires
using the effective date of this AD.
(2) The ‘‘Remarks’’ section of U.K. CAA AD
G–2022–0018 does not apply to this AD.
(3) Where paragraph (2) of U.K. CAA AD
G–2022–0018 refers to ‘‘discrepancies (i.e.
cracks or other adverse findings),’’ replace
the text ‘‘discrepancies (i.e. cracks or other
adverse findings),’’ with ‘‘any cracking.’’
(4) Where U.K. CAA AD G–2022–0018
refers to ASB.32–A189, this AD requires
using BAE Systems (Operations) Limited
Alert Service Bulletin ASB.32–A189, dated
September 16, 2022.
lotter on DSK11XQN23PROD with RULES1
(k) No Reporting Requirement
Although BAE Systems (Operations)
Limited Alert Service Bulletin ASB.32–A189,
dated September 16, 2022, specifies to
submit certain information to the
manufacturer, this AD does not include that
requirement.
(l) Additional AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Validation Branch, FAA, has the authority to
approve AMOCs for this AD, if requested
VerDate Sep<11>2014
16:04 Dec 09, 2022
Jkt 259001
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 International Validation Branch, send
it to the attention of the person identified in
paragraph (n) of this AD. Information may be
emailed to: 9-AVS-AIR-730-AMOC@faa.gov.
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, International Validation
Branch, FAA; or the United Kingdom Civil
Aviation Authority (U.K. CAA); or BAE
Systems (Operations) Limited’s U.K. CAA
Design Organization Approval (DOA). If
approved by the DOA, the approval must
include the DOA-authorized signature.
(m) Additional Information
For more information about this AD,
contact Todd Thompson, Aerospace
Engineer, Large Aircraft Section, FAA,
International Validation Branch, 2200 South
216th St., Des Moines, WA 98198; telephone
206–231–3228; email todd.thompson@
faa.gov.
(n) 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 this AD specifies otherwise.
(3) The following service information was
approved for IBR on December 27, 2022.
(i) BAE Systems (Operations) Limited Alert
Service Bulletin ASB.32–A189, dated
September 16, 2022.
(ii) Messier-Dowty Service Bulletin 146–
32–147, dated May 29, 2001.
(iii) United Kingdom Civil Aviation
Authority (U.K. CAA) AD G–2022–0018,
dated October 18, 2022.
(4) The following service information was
approved for IBR on May 2, 2005 (70 FR
15574, March 28, 2005; corrected April 14,
2005 (70 FR 19681)).
(i) BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.32–156,
Revision 1, dated July 3, 2001.
(ii) [Reserved]
(5) For BAE Systems (Operations) Limited
service information identified in this AD,
contact BAE Systems (Operations) Limited,
Customer Information Department, Prestwick
International Airport, Ayrshire, KA9 2RW,
Scotland, United Kingdom; telephone +44
1292 675207; fax +44 1292 675704; email
RApublications@baesystems.com; website
baesystems.com/Businesses/
RegionalAircraft/index.htm.
(6) For Messier-Dowty service information
identified in this AD, contact Messier-Dowty:
Messier Services Americas, Customer
Support Center, 45360 Severn Way, Sterling,
VA 20166–8910; telephone 703–450–8233;
PO 00000
Frm 00028
Fmt 4700
Sfmt 4700
fax 703–404–1621; website
techpubs.services/messier-dowty.com.
(7) For U.K. CAA AD G–2022–0018,
contact Civil Aviation Authority, Aviation
House, Beehive Ring Road, Crawley, West
Sussex RH6 0YR, United Kingdom; telephone
+44(0) 330 022 4401; email
continued.airworthiness@caa.co.uk; website
caa.co.uk.
(8) You may view this material 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. This material may be found
in the AD docket at regulations.gov under
Docket No. FAA–2022–1574.
(9) You may view this material 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 December 1, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022–27007 Filed 12–8–22; 4:15 pm]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2022–0989; Project
Identifier AD–2022–00468–E; Amendment
39–22236; AD 2022–23–09]
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 certain
General Electric Company (GE) GE90–
90B, GE90–94B, GE90–110B1, and
GE90–115B model turbofan engines.
This AD was prompted by a
manufacturer investigation that revealed
that certain high-pressure turbine (HPT)
stage 1 disks, HPT stage 2 disks, and
stages 7–9 compressor rotor spools were
manufactured from powder metal
material suspected to contain iron
inclusion. This AD requires the
replacement of the affected HPT stage 1
disks, HPT stage 2 disks, and stages 7–
9 compressor rotor spools. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective January 17,
2023.
SUMMARY:
E:\FR\FM\12DER1.SGM
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75919
Federal Register / Vol. 87, No. 237 / Monday, December 12, 2022 / Rules and Regulations
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov by searching
for and locating Docket No. FAA–2022–
0989; 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:
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 GE GE90–90B, GE90–
94B, GE90–110B1, and GE90–115B
model turbofan engines. The NPRM
published in the Federal Register on
September 09, 2022 (87 FR 55319). The
NPRM was prompted by a manufacturer
investigation that revealed that certain
HPT stage 1 disks, HPT stage 2 disks,
and stages 7–9 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 HPT stage 1
disks, HPT stage 2 disks, and stages 7–
9 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 the
replacement of certain HPT stage 1
disks, HPT stage 2 disks, and stages 7–
9 compressor rotor spools. 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 Air Line Pilots Association,
International, FedEx Express, and The
Boeing Company. All commenters
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. This AD is adopted as
proposed in the NPRM.
Related Service Information
The FAA reviewed the following
service information issued by GE, which
specifies procedures for removing the
affected HPT stage 2 disk from service.
These documents are distinct since they
apply to different engine models.
• GE90–100 Service Bulletin 72–0893
R01, dated November 30, 2021.
• GE90–100 Service Bulletin 72–0899
R00, dated April 29, 2022.
The FAA also reviewed GE90–100
Service Bulletin 72–0897 R00, dated
February 23, 2022. This service
information specifies procedures for
removing the affected stages 7–9
compressor rotor spool from service.
The FAA also reviewed GE90 Service
Bulletin 72–1214 R00, dated April 29,
2022. This service information specifies
procedures for removing the affected
HPT stage 1 disk and HPT stage 2 disk
from service.
Costs of Compliance
The FAA estimates that this AD
affects 1 engine installed on airplanes of
U.S. registry. The FAA estimates that 0
engines installed on airplanes of U.S.
registry require replacement of the HPT
stage 1 disk or stages 7–9 compressor
rotor spool.
The FAA estimates the following
costs to comply with this AD:
lotter on DSK11XQN23PROD with RULES1
ESTIMATED COSTS
Cost per
product
Action
Labor cost
Parts cost
Replace HPT stage 2 disk
Replace HPT stage 1 disk
Replace stages 7-9 compressor rotor spool.
8 work-hours × $85 per hour = $680 ........................
8 work-hours × $85 per hour = $680 ........................
8 work-hours × $85 per hour = $680 ........................
$459,473 (pro-rated) ........
$867,041 (pro-rated) ........
$442,204 (pro-rated) ........
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.
VerDate Sep<11>2014
16:04 Dec 09, 2022
Jkt 259001
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:
PO 00000
Frm 00029
Fmt 4700
Sfmt 4700
$460,153
867,721
442,884
Cost on U.S.
operators
$460,153
0
0
(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,
E:\FR\FM\12DER1.SGM
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75920
Federal Register / Vol. 87, No. 237 / Monday, December 12, 2022 / Rules and Regulations
§ 39.13
the FAA amends 14 CFR part 39 as
follows:
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
PART 39—AIRWORTHINESS
DIRECTIVES
2022–23–09 General Electric Company:
Amendment 39–22236; Docket No.
FAA–2022–0989; Project Identifier AD–
2022–00468–E.
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
(a) Effective Date
This airworthiness directive (AD) is
effective January 17, 2023.
(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric
Company GE90–90B, GE90–94B, GE90–
110B1, and GE90–115B model turbofan
engines with an installed high-pressure
turbine (HPT) stage 1 disk, HPT stage 2 disk,
or stages 7–9 compressor rotor spool with a
part number (P/N) and serial number (S/N)
identified in Table 1 to paragraph (c) of this
AD.
TABLE 1 TO PARAGRAPH (c)—AFFECTED HPT STAGE 1 DISKS, HPT STAGE 2 DISKS, AND STAGES 7–9 COMPRESSOR
ROTOR SPOOLS
Part name
HPT stage 1 disk .....................................................................................................................................................
HPT stage 2 disk .....................................................................................................................................................
HPT stage 2 disk .....................................................................................................................................................
1847M95G04
1711M47G13
1865M14P04
Stages 7–9 compressor rotor spool ........................................................................................................................
2032M23G02
S/N
GWN0R5K4
TMT5N068
TMT5P744
TMT5P745
TMT5P749
TMT5P755
TMT5P762
GWN0R5M5
Joint Aircraft System Component (JASC)
Code 7230, Turbine Engine Compressor
Section; 7250, Turbine Section.
(2) For the purpose of this AD, ‘‘affected
engines not in service’’ are affected engines
that are in long-term or short-term storage as
of the effective date of this AD.
Issued on November 1, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
(e) Unsafe Condition
(i) Installation Prohibition
[FR Doc. 2022–26831 Filed 12–9–22; 8:45 am]
This AD was prompted by a manufacturer
investigation that revealed that certain HPT
stage 1 disks, HPT stage 2 disks, and stages
7–9 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 1 disks, HPT stage 2 disks, and stages
7–9 compressor rotor spools. The unsafe
condition, if not addressed, could result in
uncontained debris release, damage to the
engine, and damage to the aircraft.
After the effective date of this AD, do not
install an HPT stage 1 disk, HPT stage 2 disk,
or stages 7–9 compressor rotor spool with a
P/N and S/N identified in Table 1 to
paragraph (c) of this AD onto any engine.
BILLING CODE 4910–13–P
(d) Subject
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Before exceeding 400 flight cycles after
the effective date of this AD, remove the
affected HPT stage 1 disk, HPT stage 2 disk,
and stages 7–9 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 1 disk, HPT stage 2 disk, and stages 7–
9 compressor rotor spool and replace with a
part eligible for installation.
lotter on DSK11XQN23PROD with RULES1
P/N
(h) Definitions
(1) For the purpose of this AD, a ‘‘part
eligible for installation’’ is any HPT stage 1
disk, HPT stage 2 disk, or stages 7–9
compressor rotor spool with a P/N and S/N
not identified in Table 1 to paragraph (c) of
this AD.
VerDate Sep<11>2014
16:04 Dec 09, 2022
Jkt 259001
(j) Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
(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.
[Docket No. FAA–2022–0712; Airspace
Docket No. 22–ACE–1]
(k) Related Information
SUMMARY:
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 00030
Fmt 4700
Sfmt 4700
RIN 2120–AA66
Amendment and Revocation of
Multiple Air Traffic Service (ATS)
Routes; Establishment of Area
Navigation (RNAV) Route; and
Revocation of the Pawnee City, NE,
Low Altitude Reporting Point in the
Vicinity of Pawnee City, NE
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This action amends Jet Route
J–64, VHF Omnidirectional Range
(VOR) Federal airways V–50, V–71, V–
216, and V–307, and Area Navigation
(RNAV) route T–286; establishes RNAV
route T–468; and revokes J–130, J–192,
V–553, and the Pawnee City, NE, low
altitude reporting point. The FAA is
taking this action due to the planned
decommissioning of the VOR portion of
the Pawnee City, NE, VOR/Tactical Air
Navigation (VORTAC) navigational aid
E:\FR\FM\12DER1.SGM
12DER1
]]>Agencies
[Federal Register Volume 87, Number 237 (Monday, December 12, 2022)]
[Rules and Regulations]
[Pages 75918-75920]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-26831]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0989; Project Identifier AD-2022-00468-E;
Amendment 39-22236; AD 2022-23-09]
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) GE90-90B, GE90-94B, GE90-110B1,
and GE90-115B model turbofan engines. This AD was prompted by a
manufacturer investigation that revealed that certain high-pressure
turbine (HPT) stage 1 disks, HPT stage 2 disks, and stages 7-9
compressor rotor spools were manufactured from powder metal material
suspected to contain iron inclusion. This AD requires the replacement
of the affected HPT stage 1 disks, HPT stage 2 disks, and stages 7-9
compressor rotor spools. The FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective January 17, 2023.
[[Page 75919]]
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov by
searching for and locating Docket No. FAA-2022-0989; 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 GE GE90-90B,
GE90-94B, GE90-110B1, and GE90-115B model turbofan engines. The NPRM
published in the Federal Register on September 09, 2022 (87 FR 55319).
The NPRM was prompted by a manufacturer investigation that revealed
that certain HPT stage 1 disks, HPT stage 2 disks, and stages 7-9
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 HPT stage 1 disks, HPT stage
2 disks, and stages 7-9 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 the replacement of certain HPT stage
1 disks, HPT stage 2 disks, and stages 7-9 compressor rotor spools. 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 Air Line Pilots Association, International, FedEx Express, and The
Boeing Company. All commenters 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. This AD is adopted as proposed in the
NPRM.
Related Service Information
The FAA reviewed the following service information issued by GE,
which specifies procedures for removing the affected HPT stage 2 disk
from service. These documents are distinct since they apply to
different engine models.
GE90-100 Service Bulletin 72-0893 R01, dated November 30,
2021.
GE90-100 Service Bulletin 72-0899 R00, dated April 29,
2022.
The FAA also reviewed GE90-100 Service Bulletin 72-0897 R00, dated
February 23, 2022. This service information specifies procedures for
removing the affected stages 7-9 compressor rotor spool from service.
The FAA also reviewed GE90 Service Bulletin 72-1214 R00, dated April
29, 2022. This service information specifies procedures for removing
the affected HPT stage 1 disk and HPT stage 2 disk from service.
Costs of Compliance
The FAA estimates that this AD affects 1 engine installed on
airplanes of U.S. registry. The FAA estimates that 0 engines installed
on airplanes of U.S. registry require replacement of the HPT stage 1
disk or stages 7-9 compressor rotor spool.
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 HPT stage 2 disk......... 8 work-hours x $85 per $459,473 $460,153 $460,153
hour = $680. (pro[dash]rated).
Replace HPT stage 1 disk......... 8 work-hours x $85 per $867,041 867,721 0
hour = $680. (pro[dash]rated).
Replace stages 7[dash]9 8 work-hours x $85 per $442,204 442,884 0
compressor rotor spool. hour = $680. (pro[dash]rated).
----------------------------------------------------------------------------------------------------------------
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,
[[Page 75920]]
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]
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2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2022-23-09 General Electric Company: Amendment 39-22236; Docket No.
FAA-2022-0989; Project Identifier AD-2022-00468-E.
(a) Effective Date
This airworthiness directive (AD) is effective January 17, 2023.
(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric Company GE90-90B, GE90-94B,
GE90-110B1, and GE90-115B model turbofan engines with an installed
high-pressure turbine (HPT) stage 1 disk, HPT stage 2 disk, or
stages 7-9 compressor rotor spool with a part number (P/N) and
serial number (S/N) identified in Table 1 to paragraph (c) of this
AD.
Table 1 to Paragraph (c)--Affected HPT Stage 1 Disks, HPT Stage 2 Disks,
and Stages 7-9 Compressor Rotor Spools
------------------------------------------------------------------------
Part name P/N S/N
------------------------------------------------------------------------
HPT stage 1 disk........................ 1847M95G04 GWN0R5K4
HPT stage 2 disk........................ 1711M47G13 TMT5N068
HPT stage 2 disk........................ 1865M14P04 TMT5P744
TMT5P745
TMT5P749
TMT5P755
TMT5P762
Stages 7-9 compressor rotor spool....... 2032M23G02 GWN0R5M5
------------------------------------------------------------------------
(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 1 disks, HPT stage 2 disks, and
stages 7-9 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 1 disks, HPT stage 2 disks, and stages
7-9 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 400 flight cycles after the effective date
of this AD, remove the affected HPT stage 1 disk, HPT stage 2 disk,
and stages 7-9 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 1 disk, HPT stage 2 disk, and stages
7-9 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 1 disk, HPT stage 2 disk, or stages
7-9 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, ``affected engines not in
service'' are affected 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
1 disk, HPT stage 2 disk, or stages 7-9 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 November 1, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-26831 Filed 12-9-22; 8:45 am]
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