Airworthiness Directives; General Electric Company Turbofan Engines, 61445-61450 [2022-22061]
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61445
Rules and Regulations
Federal Register
Vol. 87, No. 196
Wednesday, October 12, 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.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
DEPARTMENT OF TRANSPORTATION
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:
Federal Aviation Administration
Background
14 CFR Part 39
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 (lifelimited 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.
[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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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,
SUMMARY:
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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
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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:
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ESTIMATED COSTS
Action
Labor cost
Revise ALS of EM and the operator’s existing approved
maintenance or inspection program.
1 work-hour × $85 per hour =
$85.
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Cost per
product
Parts cost
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$0
12OCR1
$85
Cost on U.S.
operators
$33,150
Federal Register / Vol. 87, No. 196 / Wednesday, October 12, 2022 / Rules and Regulations
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.
(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:
■
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:
■
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
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–
61447
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
Part
name
Part No.
Spool,
Stage
6–10.
2628M56G01 For part serial
numbers listed in Table 1 of
GEnx–1B SB 72–0484, latest
revision.
2628M56G01 For part serial
numbers listed in Table 2 of
GEnx–1B SB 72–0484, latest
revision.
Spool,
Stage
6–10.
Life cycles
–1B58/P2
–1B64/P2
–1B67/P2
–1B70/P2
Life cycles
–1B54/P2
Life cycles
–1B70/72/P2
–1B70/75/P2
–1B74/75/P2
–1B75/P2
Life cycles
–1B70C/P2
Life cycles
–1B76/P2
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Life cycles
–1B78/P2
10,300
10,300
10,300
10,300
8,500
8,500
8,500
5,700
5,700
5,700
5,700
4,800
4,800
4,800
(ii) For CDP seal, P/N 2383M82P03, insert
the information in Table 2 to paragraph
(g)(1)(ii) of this AD.
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–1B76A/P2
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Federal Register / Vol. 87, No. 196 / Wednesday, October 12, 2022 / Rules and Regulations
TABLE 2 TO PARAGRAPH (g)(1)(ii)—CDP SEAL, P/N 2383M82P03
Part
name
Seal,
CDP.
Seal,
CDP.
Seal,
CDP.
Life cycles
–1B58/P2
–1B64/P2
–1B67/P2
–1B70/P2
Life cycles
–1B54/P2
Part No.
2383M82P03 For part serial
numbers listed in Table 3 of
GEnx–1B SB 72–0484, latest
revision.
2383M82P03 For part serial
numbers listed in Table 4 of
GEnx–1B SB 72–0484, latest
revision.
2383M82P03 For part serial
numbers listed in Table 5 of
GEnx–1B SB 72–0484, latest
revision.
Life cycles
–1B70/72/P2
–1B70/75/P2
–1B74/75/P2
–1B75/P2
Life cycles
–1B70C/P2
Life cycles
–1B76/P2
Life cycles
–1B76A/P2
Life cycles
–1B78/P2
6,100
6,100
6,100
6,100
5,300
5,300
5,300
13,400
13,400
13,400
13,400
9,300
9,300
9,300
3,600
3,600
3,600
3,600
2,900
2,900
2,900
(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
Part
name
Part No.
Seal,
Interstage.
2383M85P04 For part serial
numbers listed in Table 6 of
GEnx–1B SB 72–0484, latest
revision.
2383M85P04 For part serial
numbers listed in Table 7 of
GEnx–1B SB 72–0484, latest
revision.
2383M85P04 For part serial
numbers listed in Table 8 of
GEnx–1B SB 72–0484, latest
revision.
Seal,
Interstage.
Seal,
Interstage.
Life cycles
–1B58/P2
–1B64/P2
–1B67/P2
–1B70/P2
Life cycles
–1B54/P2
Life cycles
–1B70/72/P2
–1B70/75/P2
–1B74/75/P2
–1B75/P2
Life cycles
–1B70C/P2
Life cycles
–1B76/P2
Life cycles
–1B76A/P2
Life cycles
–1B78/P2
10,500
10,500
10,500
10,500
6,400
6,400
6,400
15,000
15,000
15,000
15,000
10,500
10,500
10,500
5,500
5,500
5,500
5,500
2,800
2,800
2,800
(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
Part
name
Part No.
Disk,
Stage
2.
2383M86P02 For part serial
numbers listed in Table 9 of
GEnx–1B SB 72–0484, latest
revision.
2383M86P02 For part serial
numbers listed in Table 10 of
GEnx–1B SB 72–0484, latest
revision.
2383M86P02 For part serial
numbers listed in Table 11 of
GEnx–1B SB 72–0484, latest
revision.
Disk,
Stage
2.
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Disk,
Stage
2.
(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
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Life cycles
–1B58/P2
–1B64/P2
–1B67/P2
–1B70/P2
Life cycles
–1B54/P2
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Life cycles
–1B70/72/P2
–1B70/75/P2
–1B74/75/P2
–1B75/P2
Life cycles
–1B70C/P2
Life cycles
–1B76/P2
Life cycles
–1B76A/P2
Life cycles
–1B78/P2
6,900
6,900
6,900
6,900
5,100
5,100
5,100
10,400
10,400
10,400
10,400
7,500
6,800
7,500
3,800
3,800
3,800
3,800
3,000
3,000
3,000
inspection program, as applicable, by
inserting the following information into the
applicable table for their respective part
numbers:
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(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.
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61449
TABLE 5 TO PARAGRAPH (g)(2)(i)—STAGES 6–10 COMPRESSOR ROTOR SPOOL, P/N 2628M56G01
Part No.
Life cycles
–2B67
Life cycles
–2B67B
2628M56G01 For part serial numbers listed in Table 1 of GEnx–2B SB
72–0423, latest revision.
2628M56G01 For part serial numbers listed in Table 2 of GEnx–2B SB
72–0423, latest revision.
........................
........................
10,300
........................
........................
5,700
Part name
Spool, Stage 6–
10.
Spool, Stage 6–
10.
Life cycles
–2B67/P
(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
Part name
Part No.
Seal, CDP ...........
Seal, CDP ...........
Seal, CDP ...........
2383M82P03 For
72–0423, latest
2383M82P03 For
72–0423, latest
2383M82P03 For
72–0423, latest
part serial numbers listed in Table 3 of GEnx–2B SB
revision.
part serial numbers listed in Table 4 of GEnx–2B SB
revision.
part serial numbers listed in Table 5 of GEnx–2B SB
revision.
Life cycles
–2B67
Life cycles
–2B67B
Life cycles
–2B67/P
........................
........................
6,100
........................
........................
13,400
........................
........................
3,600
(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
Part name
Part No.
Seal, Interstage ...
Seal, Interstage ...
Seal, Interstage ...
2383M85P04 For
72–0423, latest
2383M85P04 For
72–0423, latest
2383M85P04 For
72–0423, latest
part serial numbers listed in Table 6 of GEnx–2B SB
revision.
part serial numbers listed in Table 7 of GEnx–2B SB
revision.
part serial numbers listed in Table 8 of GEnx–2B SB
revision.
Life cycles
–2B67
Life cycles
–2B67B
Life cycles
–2B67/P
........................
........................
10,500
........................
........................
15,000
........................
........................
5,500
(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
Part name
Part No.
Life cycles
–2B67
Life cycles
–2B67B
Disk, Stage 2 ......
2383M86P02 For part serial numbers listed in Table 9 of GEnx–2B SB
72–0423, latest revision.
2383M86P02 For part serial numbers listed in Table 10 of GEnx–2B SB
72–0423, latest revision.
2383M86P02 For part serial numbers listed in Table 11 of GEnx–2B SB
72–0423, latest revision.
........................
........................
6,900
........................
........................
10,400
........................
........................
3,800
Disk, Stage 2 ......
Disk, Stage 2 ......
jspears on DSK121TN23PROD with RULES
(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
VerDate Sep<11>2014
17:15 Oct 11, 2022
Jkt 259001
identified in paragraph (i) 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.
Avenue, Burlington, MA 01803; phone: (781)
238–7178; email: Alexei.T.Marqueen@
faa.gov.
(j) Material Incorporated by Reference
None.
(i) Related Information
For more information about this AD,
contact Alexei Marqueen, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
Life cycles
–2B67/P
E:\FR\FM\12OCR1.SGM
12OCR1
61450
Federal Register / Vol. 87, No. 196 / Wednesday, October 12, 2022 / Rules and Regulations
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
DEPARTMENT OF TRANSPORTATION
Hye
Yoon Jang, Aerospace Engineer,
Delegation Oversight Section, DSCO
Branch, Compliance & Airworthiness
Division, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone (817)
222–5190; email hye.yoon.jang@faa.gov.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
Background
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2022–0802; Project
Identifier AD–2021–01094–R; Amendment
39–22210; AD 2022–21–11]
RIN 2120–AA64
Airworthiness Directives; Bell Textron
Inc. Helicopters and Various Restricted
Category Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Bell Textron Inc. Model 204B, 205A,
and 205A–1 helicopters and various
restricted category helicopters. This AD
was prompted by a report of cracked
main rotor blades (MRBs). This AD
requires repetitive inspections of each
MRB and removing any cracked MRB
from service. The FAA is issuing this
AD to address the unsafe condition on
these products.
DATES: This AD is effective November
16, 2022.
ADDRESSES: For service information
identified in this final rule, contact Bell
Textron, Inc., P.O. Box 482, Fort Worth,
TX, 76101, United States; phone: (800)
363–8023; website: bellflight.com/
support/. You may view this service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321,
Fort Worth, TX 76177. For information
on the availability of this material at the
FAA, call (817) 222–5110.
SUMMARY:
jspears on DSK121TN23PROD with RULES
Examining the AD Docket
You may examine the AD docket at
regulations.gov by searching for and
locating Docket No. FAA–2022–0802; 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.
VerDate Sep<11>2014
17:15 Oct 11, 2022
Jkt 259001
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain serial-numbered Bell
Textron Inc. Model 204B, 205A, and
205A–1 helicopters, and all restricted
category Model HH–1K, SW205A–1,
TH–1F, TH–1L, UH–1A, UH–1B, UH–
1E, UH–1F, UH–1H, UH–1L, and UH–1P
helicopters, with MRB part number (P/
N) 204–011–250–001, –005, –009, –113,
or –117 installed.
The NPRM published in the Federal
Register on June 29, 2022 (87 FR 38686).
The NPRM was prompted by reports of
chordwise cracks in MRB P/N 204–011–
250–113. The cracks originated from the
extreme trailing edge between blade
station 190 and 210; this area is
currently not inspected during routine
maintenance. In the NPRM, the FAA
proposed to require cleaning certain
areas of the upper and lower skin
surfaces of each MRB with a
cheesecloth. If the cheesecloth is
snagged or frayed while cleaning an
MRB, removing paint from the area that
caused the snagging and then either
visually or eddy current inspecting the
area for a crack would be required. The
NPRM also proposed to require wiping
each MRB with isopropyl alcohol and
immediately after the blade dries,
inspecting the area for a dark line,
which is an indication that excess
alcohol is bleeding out of a crack or
edge void. If there is a dark line,
removing paint from the area where
there is a dark line and inspecting for a
crack in the skin would be required.
Finally, the NPRM proposed to require
removing any cracked MRB from
service. 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
one commenter, Salmon River
Helicopters (SRH). SRH commented
about allowing a pilot to accomplish the
daily (before first flight of each day)
inspection. The following presents the
comment received on the NPRM and the
FAA’s response.
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
Comment Regarding the Before the First
Flight of Each Day Inspection
SRH asked whether a pilot may
accomplish the daily (before the first
flight of each day) inspection. SRH
stated that it has never had an issue
with blade cracking between blade
stations 190 and 210, and is unaware of
reported accidents due to blade cracking
within those stations. SRH further stated
that many operators, like SRH, do not
staff a mechanic every day of flight and
it would be a significant disadvantage to
do so.
The FAA partially agrees. The FAA
agrees to allow the owner/operator
(pilot) to accomplish the actions
required by paragraph (g)(1)(i) of this
AD because it only involves cleaning
with a cheesecloth and visually
checking for unsmooth areas and
surfaces that snag the cheesecloth or
cause it to fray. These actions could be
performed equally well by a pilot or a
mechanic, and is an exception to the
FAA’s standard maintenance
regulations. The FAA disagrees with a
pilot accomplishing the remaining
required actions because those actions
must be accomplished by a mechanic
that meets the requirements of 14 CFR
part 65 subpart D.
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 the following Bell
Alert Service Bulletins (ASBs), each
Revision A and dated October 12, 2018,
and for helicopters with MRB P/N 204–
011–250–001, –005, –009, –113, or
–117:
• Bell ASB 204–96–49 for Model
204B helicopters, serial numbers (S/N)
2001 through 2070 and 2196 through
2199 and
• Bell ASB 205–96–67 for Model
205A and 205A–1 helicopters, S/N
30001 through 30332.
The FAA also reviewed Bell ASB UH–
1H–18–20, dated October 23, 2018, for
all Model UH–IH helicopters with MRB
P/N 204–011–250–113 installed.
These service bulletins specify
procedures for daily wipe down
inspections and 25-hour inspections of
the MRBs for cracks.
E:\FR\FM\12OCR1.SGM
12OCR1
]]>Agencies
[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
