Rule2022-26831
Airworthiness Directives; General Electric Company Turbofan Engines
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
December 12, 2022
Effective
January 17, 2023
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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.
Full Text
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<title>Federal Register, Volume 87 Issue 237 (Monday, December 12, 2022)</title>
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[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-26831]
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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.
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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 <a href="http://regulations.gov">regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#06476a637e636f2852284b677477736363684660676728616970"><span class="__cf_email__" data-cfemail="bdfcd1d8c5d8d493e993f0dccfccc8d8d8d3fddbdcdc93dad2cb">[email protected]</span></a>.
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.
<bullet> GE90-100 Service Bulletin 72-0893 R01, dated November 30,
2021.
<bullet> 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
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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).
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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]
0
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
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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: <a href="/cdn-cgi/l/email-protection#14555a513955503955595b57547275753a737b62"><span class="__cf_email__" data-cfemail="662728234b27224b272b29252600070748010910">[email protected]</span></a>.
(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:
<a href="/cdn-cgi/l/email-protection#6f2e030a170a06413b41220e1d1e1a0a0a012f090e0e41080019"><span class="__cf_email__" data-cfemail="73321f160b161a5d275d3e1201020616161d331512125d141c05">[email protected]</span></a>.
(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]
BILLING CODE 4910-13-P
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