[Federal Register Volume 87, Number 196 (Wednesday, October 12, 2022)]
[Rules and Regulations]
[Pages 61445-61450]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-22061]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
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.
The Code of Federal Regulations is sold by the Superintendent of Documents.
========================================================================
Federal Register / Vol. 87, No. 196 / Wednesday, October 12, 2022 /
Rules and Regulations
[[Page 61445]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0467; Project Identifier AD-2022-00174-E;
Amendment 39-22196; AD 2022-20-12]
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 the detection of melt-related
freckles in the forgings and billets, which may reduce the life of
certain compressor discharge pressure (CDP) seals, interstage seals,
high-pressure turbine (HPT) rotor stage 2 disks, and stages 6-10
compressor rotor spools. This AD requires revising the airworthiness
limitations section (ALS) of the applicable GEnx-1B and GEnx-2B Engine
Manual (EM) and the operator's existing approved maintenance program or
inspection program, as applicable, to incorporate reduced life limits
for these parts. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective November 16, 2022.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov by
searching for and locating Docket No. FAA-2022-0467; 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 GEnx-1B54/
P2, GEnx-1B58/P2, GEnx-1B64/P2, GEnx-1B67/P2, GEnx-1B70/P2, GEnx-1B70C/
P2, GEnx-1B70/72/P2, GEnx-1B70/75/P2, GEnx-1B74/75/P2, GEnx-1B75/P2,
GEnx-1B76/P2, GEnx-1B76A/P2, and GEnx-1B78/P2 (GEnx-1B) and GEnx-2B67,
GEnx-2B67B, and GEnx-2B67/P (GEnx-2B) model turbofan engines. The NPRM
published in the Federal Register on June 1, 2022 (87 FR 33071). The
NPRM was prompted by the engine manufacturer notifying the FAA of the
detection of melt-related freckles in the forgings and billets, which
may reduce the life of certain CDP seals, interstage seals, HPT rotor
stage 2 disks, and stages 6-10 compressor rotor spools (life-limited
parts (LLPs)). The manufacturer's investigation determined that, as a
result of such freckles forming in the forgings and billets, certain
LLPs may have undetected subsurface anomalies that developed during the
manufacturing process, resulting in reduced material properties and a
lower fatigue life capability. Reduced material properties may cause
premature LLP fracture, which could result in uncontained debris
release. As a result of its investigation, the manufacturer determined
the need to reduce the life limits of certain LLPs. To reflect these
reduced life limits, the manufacturer revised the ALS of the affected
GEnx-1B and GEnx-2B EMs. In the NPRM, the FAA proposed to require
operators to update the ALS of the applicable GEnx-1B and GEnx-2B EM
and the operator's existing approved maintenance program or inspection
program, as applicable, to incorporate reduced life limits for certain
LLPs. 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 seven commenters. The commenters
were Air China, Air Line Pilots Association, International (ALPA),
American Airlines (AAL), GE, The Boeing Company (Boeing), TUI Airways,
and United Airlines Powerplant Engineering (United Airlines). ALPA,
Boeing, and United Airlines supported the proposed AD without change.
AAL supported the proposed AD, with one comment relating to the service
information. Three commenters, Air China, GE, and TUI Airways,
requested changes to the proposed AD. The following presents the
comments received on the NPRM and the FAA's response to each comment.
Request To Update Service Information
AAL and GE noted that the preamble of the NPRM refers to service
information that has been superseded. GE published GE GEnx-1B Service
Bulletin (SB) 72-0484 R01, dated March 17, 2022 (GE GEnx-1B SB 72-0484
R01), and GE GEnx-2B SB 72-0423 R01, dated March 17, 2022 (GE GEnx-2B
SB 72-0423 R01). The revisions contain corrections to serial number
errors published in the original service information. GE requested that
the FAA update the service information to reflect the current revisions
to avoid confusion among the operators.
The FAA agrees and updated the Related Service Information
paragraph in the preamble of this final rule to reference GE GEnx-1B SB
72-0484 R01 and GE GEnx-2B SB 72-0423 R01. This change places no
additional burden on operators who are required to comply with this AD.
Requests To Modify the Tables to Paragraph (g)
Air China noted that there is a revision to the service information
in tables 5 through 8 to paragraph (g)(2) of the proposed AD. The
commenter requested that the FAA modify the service information in the
tables from ``GEnx-2B SB 72-0423, latest revision'' to ``GEnx-2B SB 72-
0423 R01 revision.''
The FAA disagrees. Paragraph (g)(2) of this AD requires the
operator to revise the ALS of the applicable GEnx-2B EM and the
operator's existing approved maintenance program or inspection
[[Page 61446]]
program, as applicable, by inserting the information in the tables to
paragraph (g)(2) into the applicable table for their respective part
numbers. The description of the service information in the tables to
paragraph (g) of this AD is consistent with the description of the
service information in the applicable tables in the ALS. The FAA did
not change this AD as a result of this comment.
GE requested that the FAA clarify the wording in the proposed AD
regarding parts not affected or listed in GE GEnx-1B SB 72-0484 R01 and
GE GEnx-2B SB 72-0423 R01. The commenter noted that the proposed AD
includes updating the ALS language for parts not affected by the
population listed in GE GEnx-1B SB 72-0484 and GE GEnx-2B SB 72-0423.
GE requested that the FAA modify the tables to paragraph (g) of this AD
to remove the life cycles for part serial numbers not listed in GE
GEnx-1B SB 72-0484 and GE GEnx-2B SB 72-0423. If such modifications
cannot be done, GE requested that the FAA add language to clarify that
future LLP life extensions on part serial numbers not listed in the SB
populations would not require an alternative method of compliance
(AMOC).
The FAA agrees with the modification. The FAA revised the tables to
paragraph (g) of this AD to remove the entries for life cycles for part
serial numbers not listed in the service information. This change
places no additional burden on operators who are required to comply
with this AD.
Responsibility for Revising the EM
Air China commented that paragraph (g)(2) of the proposed AD states
to ``revise the ALS of the existing GEnx-2B EM.'' The commenter stated
that the responsibility for revising the EM belongs to the
manufacturer, not the operator.
The FAA disagrees. While the manufacturer does revise the engine
manuals, this AD requires the operator to revise the ALS of the
existing GEnx-2B EM and the operator's existing approved maintenance
program or inspection program, as applicable. This includes revising
the operator's copies of the EM to incorporate the reduced life limits
for certain LLPs. The FAA did not change this AD as a result of this
comment.
Request To Confirm Compliance With Previous Actions
Air China stated that it performed certain required actions
proposed in paragraph (g)(2) of the NPRM using GE GEnx-2B SB 72-0423
before the NPRM was issued:
1. For the affected LLPs that had already been installed on GEnx-
2B67/P engines of Air China, Air China listed the LLPs' time limits in
the continuous airworthiness maintenance program.
2. For the affected LLPs that were not installed on GEnx-2B67/P
engines of Air China, Air China issued engineering order documents that
prohibit the installation of affected LLPs on the Air China GEnx-2B67/P
fleet.
Air China asked if the FAA would consider these actions as being in
compliance with the proposed requirements in paragraph (g)(2) of the
proposed AD.
In response to this comment, the FAA notes that paragraph (g)(2) of
this AD requires the operator to revise the ALS of the existing GEnx-1B
EM and the operator's existing approved maintenance program or
inspection program, as applicable, by inserting the information in the
tables to paragraph (g)(2) into the applicable table for their
respective part numbers. This AD requires revising the life limits with
the entirety of the information provided in the tables to paragraph
(g)(2) of this AD, regardless of the installation of affected parts.
Additionally, this AD does not contain an installation prohibition.
Request To Allow for Pro-Rated Life Calculations
TUI Airways requested that the FAA add an allowance for pro-rated
life calculations to this AD. TUI Airways noted that paragraph (g)(3)
of the proposed AD states, ``After performing the actions required by
paragraphs (g)(1) and (2) of this AD, except as provided in paragraph
(h) of this AD, no alternative life limits may be approved for the
affected parts.'' TUI Airways suggested that this statement does not
consider parts that have or could operate at different engine ratings
or are common to two or more engine models. The commenter reasoned that
a part common to multiple engine ratings or models could have different
life cycle limits depending on the engine application, and therefore, a
pro-rated calculation (per GE EM 05-11-00) could be made to determine
the remaining cycles of the given part.
The FAA does not agree. The intent of this AD is to revise the ALS
of the existing GEnx-1B and GEnx-2B EMs and the operator's existing
approved maintenance or inspection program with the updated life limits
provided in paragraph (g) of this AD. This AD does not prohibit pro-
rated life limit calculations, but the FAA cautions that such
calculations performed prior to the effective date of this AD may need
to be re-evaluated using the new life limits provided in paragraph (g)
of this AD. The FAA did not change this AD as a result of this comment.
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 SB 72-0484 R01, dated March 17, 2022,
and GE GEnx-2B SB 72-0423 R01, dated March 17, 2022. These SBs,
differentiated by engine model, provide the reduced life limits for
certain LLPs.
Costs of Compliance
The FAA estimates that this AD affects 390 engines installed on
airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Revise ALS of EM and the operator's 1 work-hour x $85 per $0 $85 $33,150
existing approved maintenance or hour = $85.
inspection program.
----------------------------------------------------------------------------------------------------------------
[[Page 61447]]
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:
2022-20-12 General Electric Company: Amendment 39-22196; Docket No.
FAA-2022-0467; Project Identifier AD-2022-00174-E.
(a) Effective Date
This airworthiness directive (AD) is effective November 16,
2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric Company (GE) GEnx-1B54/P2,
GEnx-1B58/P2, GEnx-1B64/P2, GEnx-1B67/P2, GEnx-1B70/P2, GEnx-1B70C/
P2, GEnx-1B70/72/P2, GEnx-1B70/75/P2, GEnx-1B74/75/P2, GEnx-1B75/P2,
GEnx-1B76/P2, GEnx-1B76A/P2, GEnx-1B78/P2, GEnx-2B67, GEnx-2B67B,
and GEnx-2B67/P model turbofan engines.
(d) Subject
Joint Aircraft System Component Code 7230, Turbine Engine
Compressor Section; 7250, Turbine Section.
(e) Unsafe Condition
This AD was prompted by the detection of melt-related freckles
in the forgings and billets, which may reduce the life of certain
compressor discharge pressure (CDP) seals, interstage seals, high-
pressure turbine (HPT) rotor stage 2 disks, and stages 6-10
compressor rotor spools. The FAA is issuing this AD to prevent
failure of the CDP seal, interstage seal, HPT rotor stage 2 disk,
and stages 6-10 compressor rotor spool. The unsafe condition, if not
addressed, could result in uncontained debris release, 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
(1) For all affected GEnx-1B model turbofan engines, within 90
days after the effective date of this AD, revise the airworthiness
limitations section (ALS) of the existing GEnx-1B Engine Manual (EM)
and the operator's existing approved maintenance program or
inspection program, as applicable, by inserting the following
information into the applicable table for their respective part
numbers:
(i) For stages 6-10 compressor rotor spool, part number (P/N)
2628M56G01, insert the information in Table 1 to paragraph (g)(1)(i)
of this AD.
Table 1 to Paragraph (g)(1)(i)--Stages 6-10 Compressor Rotor Spool, P/N 2628M56G01
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
Life cycles -
Life cycles - 1B70/72/P2 -
Part name Part No. Life cycles - 1B58/P2 -1B64/ Life cycles - 1B70/75/P2 - Life cycles - Life cycles - Life cycles -
1B54/P2 P2 -1B67/P2 - 1B70C/P2 1B74/75/P2 - 1B76/P2 1B76A/P2 1B78/P2
1B70/P2 1B75/P2
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
Spool, Stage 6-10.......................... 2628M56G01 For part serial numbers 10,300 10,300 10,300 10,300 8,500 8,500 8,500
listed in Table 1 of GEnx-1B SB 72-
0484, latest revision.
Spool, Stage 6-10.......................... 2628M56G01 For part serial numbers 5,700 5,700 5,700 5,700 4,800 4,800 4,800
listed in Table 2 of GEnx-1B SB 72-
0484, latest revision.
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(ii) For CDP seal, P/N 2383M82P03, insert the information in
Table 2 to paragraph (g)(1)(ii) of this AD.
[[Page 61448]]
Table 2 to Paragraph (g)(1)(ii)--CDP Seal, P/N 2383M82P03
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
Life cycles -
Life cycles - 1B70/72/P2 -
Part name Part No. Life cycles - 1B58/P2 -1B64/ Life cycles - 1B70/75/P2 - Life cycles - Life cycles - Life cycles -
1B54/P2 P2 -1B67/P2 - 1B70C/P2 1B74/75/P2 - 1B76/P2 1B76A/P2 1B78/P2
1B70/P2 1B75/P2
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
Seal, CDP.................................. 2383M82P03 For part serial numbers 6,100 6,100 6,100 6,100 5,300 5,300 5,300
listed in Table 3 of GEnx-1B SB 72-
0484, latest revision.
Seal, CDP.................................. 2383M82P03 For part serial numbers 13,400 13,400 13,400 13,400 9,300 9,300 9,300
listed in Table 4 of GEnx-1B SB 72-
0484, latest revision.
Seal, CDP.................................. 2383M82P03 For part serial numbers 3,600 3,600 3,600 3,600 2,900 2,900 2,900
listed in Table 5 of GEnx-1B SB 72-
0484, latest revision.
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(iii) For interstage seal, P/N 2383M85P04, insert the
information in Table 3 to paragraph (g)(1)(iii) of this AD.
Table 3 to Paragraph (g)(1)(iii)--Interstage Seal, P/N 2383M85P04
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
Life cycles -
Life cycles - 1B70/72/P2 -
Part name Part No. Life cycles - 1B58/P2 -1B64/ Life cycles - 1B70/75/P2 - Life cycles - Life cycles - Life cycles -
1B54/P2 P2 -1B67/P2 - 1B70C/P2 1B74/75/P2 - 1B76/P2 1B76A/P2 1B78/P2
1B70/P2 1B75/P2
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
Seal, Interstage........................... 2383M85P04 For part serial numbers 10,500 10,500 10,500 10,500 6,400 6,400 6,400
listed in Table 6 of GEnx-1B SB 72-
0484, latest revision.
Seal, Interstage........................... 2383M85P04 For part serial numbers 15,000 15,000 15,000 15,000 10,500 10,500 10,500
listed in Table 7 of GEnx-1B SB 72-
0484, latest revision.
Seal, Interstage........................... 2383M85P04 For part serial numbers 5,500 5,500 5,500 5,500 2,800 2,800 2,800
listed in Table 8 of GEnx-1B SB 72-
0484, latest revision.
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(iv) For HPT rotor stage 2 disk, P/N 2383M86P02, insert the
information in Table 4 to paragraph (g)(1)(iv) of this AD.
Table 4 to Paragraph (g)(1)(iv)--HPT Rotor Stage 2 Disk, P/N 2383M86P02
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
Life cycles -
Life cycles - 1B70/72/P2 -
Part name Part No. Life cycles - 1B58/P2 -1B64/ Life cycles - 1B70/75/P2 - Life cycles - Life cycles - Life cycles -
1B54/P2 P2 -1B67/P2 - 1B70C/P2 1B74/75/P2 - 1B76/P2 1B76A/P2 1B78/P2
1B70/P2 1B75/P2
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
Disk, Stage 2.............................. 2383M86P02 For part serial numbers 6,900 6,900 6,900 6,900 5,100 5,100 5,100
listed in Table 9 of GEnx-1B SB 72-
0484, latest revision.
Disk, Stage 2.............................. 2383M86P02 For part serial numbers 10,400 10,400 10,400 10,400 7,500 6,800 7,500
listed in Table 10 of GEnx-1B SB
72-0484, latest revision.
Disk, Stage 2.............................. 2383M86P02 For part serial numbers 3,800 3,800 3,800 3,800 3,000 3,000 3,000
listed in Table 11 of GEnx-1B SB
72-0484, latest revision.
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
(2) For all affected GEnx-2B model turbofan engines, within 90
days after the effective date of this AD, revise the ALS of the
existing GEnx-2B EM and the operator's existing approved maintenance
program or inspection program, as applicable, by inserting the
following information into the applicable table for their respective
part numbers:
(i) For stages 6-10 compressor rotor spool, P/N 2628M56G01,
insert the information in Table 5 to paragraph (g)(2)(i) of this AD.
[[Page 61449]]
Table 5 to Paragraph (g)(2)(i)--Stages 6-10 Compressor Rotor Spool, P/N 2628M56G01
----------------------------------------------------------------------------------------------------------------
Life cycles - Life cycles - Life cycles -
Part name Part No. 2B67 2B67B 2B67/P
----------------------------------------------------------------------------------------------------------------
Spool, Stage 6-10.................. 2628M56G01 For part serial .............. .............. 10,300
numbers listed in Table 1
of GEnx-2B SB 72-0423,
latest revision.
Spool, Stage 6-10.................. 2628M56G01 For part serial .............. .............. 5,700
numbers listed in Table 2
of GEnx-2B SB 72-0423,
latest revision.
----------------------------------------------------------------------------------------------------------------
(ii) For CDP seal, P/N 2383M82P03, insert the information in
Table 6 to paragraph (g)(2)(ii) of this AD.
Table 6 to Paragraph (g)(2)(ii)--CDP Seal, P/N 2383M82P03
----------------------------------------------------------------------------------------------------------------
Life cycles - Life cycles - Life cycles -
Part name Part No. 2B67 2B67B 2B67/P
----------------------------------------------------------------------------------------------------------------
Seal, CDP.......................... 2383M82P03 For part serial .............. .............. 6,100
numbers listed in Table 3
of GEnx-2B SB 72-0423,
latest revision.
Seal, CDP.......................... 2383M82P03 For part serial .............. .............. 13,400
numbers listed in Table 4
of GEnx-2B SB 72-0423,
latest revision.
Seal, CDP.......................... 2383M82P03 For part serial .............. .............. 3,600
numbers listed in Table 5
of GEnx-2B SB 72-0423,
latest revision.
----------------------------------------------------------------------------------------------------------------
(iii) For interstage seal, P/N 2383M85P04, insert the
information in Table 7 to paragraph (g)(2)(iii) of this AD.
Table 7 to Paragraph (g)(2)(iii)--Interstage Seal, P/N 2383M85P04
----------------------------------------------------------------------------------------------------------------
Life cycles - Life cycles - Life cycles -
Part name Part No. 2B67 2B67B 2B67/P
----------------------------------------------------------------------------------------------------------------
Seal, Interstage................... 2383M85P04 For part serial .............. .............. 10,500
numbers listed in Table 6
of GEnx-2B SB 72-0423,
latest revision.
Seal, Interstage................... 2383M85P04 For part serial .............. .............. 15,000
numbers listed in Table 7
of GEnx-2B SB 72-0423,
latest revision.
Seal, Interstage................... 2383M85P04 For part serial .............. .............. 5,500
numbers listed in Table 8
of GEnx-2B SB 72-0423,
latest revision.
----------------------------------------------------------------------------------------------------------------
(iv) For HPT rotor stage 2 disk, P/N 2383M86P02, insert the
information in Table 8 to paragraph (g)(2)(iv) of this AD.
Table 8 to Paragraph (g)(2)(iv)--HPT Rotor Stage 2 Disk P/N, 2383M86P02
----------------------------------------------------------------------------------------------------------------
Life cycles - Life cycles - Life cycles -
Part name Part No. 2B67 2B67B 2B67/P
----------------------------------------------------------------------------------------------------------------
Disk, Stage 2...................... 2383M86P02 For part serial .............. .............. 6,900
numbers listed in Table 9
of GEnx-2B SB 72-0423,
latest revision.
Disk, Stage 2...................... 2383M86P02 For part serial .............. .............. 10,400
numbers listed in Table 10
of GEnx-2B SB 72-0423,
latest revision.
Disk, Stage 2...................... 2383M86P02 For part serial .............. .............. 3,800
numbers listed in Table 11
of GEnx-2B SB 72-0423,
latest revision.
----------------------------------------------------------------------------------------------------------------
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, ECO Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
certification office, send it to the attention of the person
identified in paragraph (i) 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.
(i) 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].
(j) Material Incorporated by Reference
None.
[[Page 61450]]
Issued on September 19, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-22061 Filed 10-11-22; 8:45 am]
BILLING CODE 4910-13-P