Airworthiness Directives; International Aero Engines, LLC Engines, 86088-86092 [2023-27047]
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Federal Register / Vol. 88, No. 237 / Tuesday, December 12, 2023 / Proposed Rules
Issued on December 4, 2023.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2023–27099 Filed 12–11–23; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–2237; Project
Identifier AD–2023–01057–E]
RIN 2120–AA64
Airworthiness Directives; International
Aero Engines, LLC Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede Airworthiness Directive (AD)
2022–19–15, which applies to certain
International Aero Engines, LLC (IAE
LLC) Model PW1100G series engines;
and AD 2023–16–07, which applies to
certain IAE LLC Model PW1100G series
engines and PW1400G series engines.
AD 2022–19–15 requires an angled
ultrasonic inspection (AUSI) of the
high-pressure turbine (HPT) 1st-stage
disk and HPT 2nd-stage disk, and
replacement if necessary. AD 2023–16–
07 requires an AUSI of the HPT 1ststage hub (also known as the HPT 1ststage disk) and HPT 2nd-stage hub (also
known as the HPT 2nd-stage disk) for
cracks, and replacement if necessary,
which is terminating action for AD
2022–19–15. Since the FAA issued
these two ADs, an investigation
determined an increased risk of powder
metal anomalies for all powder metal
parts in certain powder metal
production campaigns, which are
susceptible to failure significantly
earlier than previously determined. This
proposed AD would retain the AUSI
requirement for certain HPT 1st-stage
and HPT 2nd-stage hubs from AD 2023–
16–07. This proposed AD would also
require performing an AUSI of the HPT
1st-stage hub, HPT 2nd-stage hub, highpressure compressor (HPC) 7th-stage
integrally bladed rotor (IBR–7), and HPC
8th-stage integrally bladed rotor (IBR–8)
for cracks and replacement if necessary.
This proposed AD would also require
accelerated replacement of the HPC
IBR–7, HPC IBR–8, HPC rear hub, HPT
1st-stage hub, HPT 1st-stage air seal,
HPT 1st-stage blade retaining plate, HPT
2nd-stage hub, HPT 2nd-stage blade
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SUMMARY:
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retaining plate, and HPT 2nd-stage rear
seal. The FAA is proposing this AD to
address the unsafe condition on these
products.
DATES: The FAA must receive comments
on this proposed AD by January 11,
2024.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
regulations.gov. Follow the instructions
for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2023–2237; 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 NPRM, any comments
received, and other information. The
street address for Docket Operations is
listed above.
Material Incorporated by Reference:
• For Pratt and Whitney (PW) service
information identified in this NPRM,
contact International Aero Engines, LLC,
400 Main Street, East Hartford, CT
06118; phone: (860) 565–0140; email:
help24@pw.utc.com; website:
connect.prattwhitney.com.
• You may view this service
information at the FAA, Airworthiness
Products Section, Operational Safety
Branch, 1200 District Avenue,
Burlington, MA 01803. For information
on the availability of this material at the
FAA, call (817) 222–5110.
FOR FURTHER INFORMATION CONTACT:
Carol Nguyen, Aviation Safety Engineer,
FAA, 2200 South 216th Street, Des
Moines, WA 98198; phone: (781) 238–
7655; email: carol.nguyen@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2023–2237; Project Identifier AD–
2023–01057–E’’ at the beginning of your
comments. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
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supporting data. The FAA will consider
all comments received by the closing
date and may amend the proposal
because of those comments.
The FAA has been informed that PW
has done some outreach with affected
operators regarding the proposed
corrective actions for this unsafe
condition. As a result, affected operators
are already aware of the proposed
corrective actions and, in some cases,
have already begun planning for
replacement of the affected parts.
Therefore, the FAA has determined that
a 30-day comment period is appropriate
given the particular circumstances
related to the proposed correction of
this unsafe condition.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to
regulations.gov, including any personal
information you provide. The agency
will also post a report summarizing each
substantive verbal contact received
about this NPRM.
Confidential Business Information
CBI is commercial or financial
information that is both customarily and
actually treated as private by its owner.
Under the Freedom of Information Act
(FOIA) (5 U.S.C. 552), CBI is exempt
from public disclosure. If your
comments responsive to this NPRM
contain commercial or financial
information that is customarily treated
as private, that you actually treat as
private, and that is relevant or
responsive to this NPRM, it is important
that you clearly designate the submitted
comments as CBI. Please mark each
page of your submission containing CBI
as ‘‘PROPIN.’’ The FAA will treat such
marked submissions as confidential
under the FOIA, and they will not be
placed in the public docket of this
NPRM. Submissions containing CBI
should be sent to Carol Nguyen,
Aviation Safety Engineer, FAA, 2200
South 216th Street, Des Moines, WA
98198. Any commentary that the FAA
receives which is not specifically
designated as CBI will be placed in the
public docket for this rulemaking.
Background
The FAA issued AD 2022–19–15,
Amendment 39–22184 (87 FR 59660,
October 3, 2022; corrected October 24,
2022 (87 FR 64156)) (AD 2022–19–15),
for certain IAE LLC Model PW1122G–
JM, PW1124G1–JM, PW1124G–JM,
PW1127G1–JM, PW1127GA–JM,
PW1127G–JM, PW1129G–JM,
PW1130G–JM, PW1133GA–JM, and
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Federal Register / Vol. 88, No. 237 / Tuesday, December 12, 2023 / Proposed Rules
PW1133G–JM engines. AD 2022–19–15
was prompted by an analysis of an event
involving an International Aero Engines
AG V2533–A5 model turbofan engine,
which experienced an uncontained
failure of an HPT 1st-stage disk that
resulted in high-energy debris
penetrating the engine cowling. AD
2022–19–15 requires performing an
AUSI of the HPT 1st-stage disk and HPT
2nd-stage disk and, depending on the
results of the inspections, replacing the
HPT 1st-stage disk or HPT 2nd-stage
disk. The FAA issued AD 2022–19–15
to prevent failure of the HPT 1st-stage
disk and HPT 2nd-stage disk.
Since the FAA issued AD 2022–19–
15, an Airbus Model A320neo airplane
powered by IAE LLC Model
PW1127GA–JM engines experienced a
failure of the HPC IBR–7 that resulted in
an engine shutdown and an aborted
take-off. Following this event, the
manufacturer conducted a records
review of production and field-returned
parts and then re-evaluated their
engineering analysis methodology. The
new analysis identified HPT 1st-stage
hubs and HPT 2nd-stage hubs that are
susceptible to failure significantly
earlier than previously determined. On
August 4, 2023, PW issued service
information with procedures for an
AUSI to detect cracks and prevent
premature failure. The manufacturer’s
updated analysis also identified
PW1400G series engines that contain
HPT 1st-stage hubs and HPT 2nd-stage
hubs that are also subject to the unsafe
condition. The FAA determined that the
new service information necessitated
action much earlier than the compliance
time mandated in AD 2022–19–15 and
that the additional engines should also
be subject to these actions. As a result,
the FAA issued AD 2023–16–07,
Amendment 39–22526 (88 FR 56999,
August 22, 2023) (AD 2023–16–07) for
certain IAE LLC Model PW1122G–JM,
PW1124G1–JM, PW1124G–JM,
PW1127G–JM, PW1127G1–JM,
PW1127GA–JM, PW1129G–JM,
PW1130G–JM, PW1133G–JM,
PW1133GA–JM, PW1428G–JM,
PW1428GA–JM, PW1428GH–JM,
PW1431G–JM, PW1431GA–JM, and
PW1431GH–JM engines. AD 2023–16–
07 requires performing an AUSI of the
HPT 1st-stage hub (also known as the
HPT 1st-stage disk) and HPT 2nd-stage
hub (also known as the HPT 2nd-stage
disk) for cracks and, depending on the
results of the inspections, replacing the
HPT 1st-stage hub or HPT 2nd-stage
hub, which was terminating action for
the requirements of AD 2022–19–15.
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16:23 Dec 11, 2023
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The FAA issued AD 2023–16–07 to
prevent failure of the HPT 1st-stage hub
and HPT 2nd-stage hub.
Actions Since the Previous ADs Were
Issued
Since the FAA issued AD 2023–16–
07, additional manufacturer analysis
found that the failure of the HPC IBR–
7 was caused by a powder metal
anomaly, similar in nature to the
anomalies outlined in AD 2022–19–15.
The analysis also concluded that there
is an increased risk of failure for
additional powder metal parts in certain
powder metal production campaigns,
specifically the HPC IBR–7 and HPC
IBR–8, and that all affected parts are
susceptible to failure significantly
earlier than previously determined. The
condition, if not addressed, could result
in uncontained hub failure, release of
high-energy debris, damage to the
engine, damage to the airplane, and loss
of the airplane.
FAA’s Determination
The FAA is issuing this NPRM after
determining that the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design.
Related Service Information Under 1
CFR Part 51
The FAA reviewed the following
service information:
• PW Alert Service Bulletin (ASB)
PW1000G–C–72–00–0224–00A–930A–
D, Issue No: 001, dated November 3,
2023, which specifies procedures for
performing an AUSI for cracks on
affected HPC IBR–7 and HPC IBR–8;
• PW ASB PW1000G–C–72–00–
0225–00A–930A–D Issue No: 001, dated
November 3, 2023, which specifies
procedures for performing an AUSI for
cracks on affected HPT 1st-stage hubs
and HPT 2nd-stage hubs;
• PW Service Bulletin PW1000G–C–
72–00–0188–00A–930A–D, Issue No:
002, dated July 8, 2022, which was
previously approved for incorporation
by reference on November 7, 2022 (87
FR 59660, October 3, 2022; corrected
October 24, 2022 (87 FR 64156)). This
service information specifies procedures
for performing an AUSI for cracks on
affected HPT 1st-stage hubs and HPT
2nd-stage hubs;
• PW Special Instruction (SI) NO.
149F–23, dated August 4, 2023, which
was previously approved for
incorporation by reference on August
28, 2023 (88 FR 56999, August 22,
2023). This service information specifies
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the list of affected HPT 1st-stage hubs
and HPT 2nd-stage hubs, identified by
part number and serial number,
installed on certain IAE LLC engines;
and
• PW SI NO. 198F–23, dated
November 3, 2023, which specifies the
list of affected HPT 1st-stage hubs and
HPT 2nd-stage hubs, identified by part
number and serial number, installed on
certain IAE LLC engines.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in ADDRESSES.
Proposed AD Requirements in This
NPRM
This proposed AD would retain none
of the requirements of AD 2022–19–15,
but it would retain certain requirements
of AD 2023–16–07. This proposed AD
would require performing an AUSI of
the HPT 1st-stage hub and HPT 2ndstage hub and replacing as necessary.
This proposed AD would also require
performing an AUSI of the HPC IBR–7
and HPC IBR–8 for cracks and replacing
as necessary. This proposed AD would
also require accelerated replacement of
the HPC IBR–7, HPC IBR–8, HPC rear
hub, HPT 1st-stage hub, HPT 1st-stage
air seal, HPT 1st-stage blade retaining
plate, HPT 2nd-stage hub, HPT 2ndstage blade retaining plate, and HPT
2nd-stage rear seal.
Interim Action
The FAA considers this proposed AD
to be an interim action. The unsafe
condition is still under investigation by
the manufacturer and, depending on the
results of that investigation, the FAA
may consider further rulemaking action.
Costs of Compliance
The FAA estimates that this AD, if
adopted as proposed, would affect 430
engines installed on airplanes of U.S.
registry. The FAA estimates that 366
engines will need replacement of the
HPT 1st-stage hub; 351 engines will
need replacement of the HPT 2nd-stage
hub; 408 engines will replacement of
the HPC IBR–7; 368 engines will need
replacement of the HPC IBR–8; 283
engines will need replacement of the
HPC rear hub; and 206 engines will
need replacement of the HPT 1st-stage
air seal, HPT 1st-stage blade retaining
plate, HPT 2nd-stage blade retaining
plate, and HPT 2nd-stage rear seal.
The FAA estimates the following
costs to comply with this proposed AD:
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Federal Register / Vol. 88, No. 237 / Tuesday, December 12, 2023 / Proposed Rules
ESTIMATED COSTS
Labor cost
AUSI of HPT 1st-stage hub,
HPT 2nd-stage hub, HPC
IBR–7, and HPC IBR–8 for
cracks.
Replace HPT 1st-stage hub ...
80 work-hours × $85 per hour
= $6,800.
$0
$6,800 ....................................
$2,924,000
× $85 per hour
56,000
56,850 ....................................
20,807,100
× $85 per hour
62,000
62,850 ....................................
22,060,350
× $85 per hour
82,000
82,850 ....................................
33,802,800
× $85 per hour
93,000
93,850 ....................................
34,536,800
× $85 per hour
132,000
132,850 ..................................
37,596,550
× $85 per hour
35,000
36,700 ....................................
7,560,200
Replace HPT 2nd-stage hub
Replace HPC IBR–7 ..............
Replace HPC IBR–8 ..............
Replace HPC rear hub ...........
Replace HPT 1st-stage air
seal, HPT 1st-stage blade
retaining plate, HPT 2ndstage blade retaining plate,
and HPT 2nd-stage rear
seal.
10 work-hours
= $850.
10 work-hours
= $850.
10 work-hours
= $850.
10 work-hours
= $850.
10 work-hours
= $850.
20 work-hours
= $1,700.
The FAA has included all known
costs in its cost estimate. According to
the manufacturer, however, some of the
costs of this AD may be covered under
warranty, thereby reducing the cost
impact on affected operators.
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.
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Parts cost
(average
pro-rated
cost)
Action
The FAA determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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
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16:23 Dec 11, 2023
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Would not affect intrastate
aviation in Alaska, and
(3) Would 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 Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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
Regulatory Findings
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Cost per product
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
2022–19–15, Amendment 39–22184 (87
FR 59660; corrected October 3, 2022 (87
FR 64156)); and Airworthiness Directive
2023–16–07, Amendment 39–22526 (88
FR 56999, August 22, 2023); and
■ b. Adding the following new
airworthiness directive:
■
■
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Cost on U.S. operators
International Aero Engines, LLC: Docket No.
FAA–2023–2237; Project Identifier AD–
2023–01057–E.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by January 11,
2024.
(b) Affected ADs
(1) This AD replaces AD 2022–19–15,
Amendment 39–22184 (87 FR 59660, October
3, 2022; corrected October 24, 2022 (87 FR
64156)).
(2) This AD replaces AD 2023–16–07,
Amendment 39–22526 (88 FR 56999, August
22, 2023) (AD 2023–16–07).
(c) Applicability
This AD applies to International Aero
Engines, LLC (IAE LLC) Model PW1122G–
JM, PW1124G1–JM, PW1124G–JM,
PW1127G–JM, PW1127G1–JM, PW1127GA–
JM, PW1129G–JM, PW1130G–JM, PW1133G–
JM, PW1133GA–JM, PW1428G–JM,
PW1428GA–JM, PW1428GH–JM, PW1431G–
JM, PW1431GA–JM, and PW1431GH–JM
engines.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7230, Turbine Engine Compressor
Section; 7250, Turbine Section.
(e) Unsafe Condition
This AD was prompted by an analysis of
an event involving an IAE LLC Model
PW1127GA–JM engine, which experienced
failure of a high-pressure compressor (HPC)
7th-stage integrally bladed rotor (IBR–7) that
resulted in an engine shutdown and aborted
takeoff. The FAA is issuing this AD to
prevent failure of the high-pressure turbine
(HPT) 1st-stage hub, HPT 2nd-stage hub, HPC
IBR–7, and HPC 8th-stage integrally bladed
rotor (IBR–8). The unsafe condition, if not
addressed, could result in uncontained hub
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failure, release of high-energy debris, damage
to the engine, damage to the airplane, and
loss of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspections From AD 2023–16–
07, With No Changes
(1) This paragraph restates the
requirements of paragraph (g)(1) of AD 2023–
16–07. For Group 1 and Group 2 engines
with an installed HPT 1st-stage hub having
part number (P/N) 30G7301 and a serial
number (S/N) listed in Tables 1, 2, 3, or 4 of
Pratt & Whitney (PW) Special Instruction (SI)
NO. 149F–23, dated August 4, 2023 (PW SI
NO. 149F–23), within 30 days after August
28, 2023 (the effective date of AD 2023–16–
07), perform an AUSI of the HPT 1st-stage
hubs for cracks in accordance with the
Accomplishment Instructions, paragraph 9.A.
or 9.B., as applicable, of PW Service Bulletin
PW1000G–C–72–00–0188–00A–930A–D,
Issue No: 002, dated July 8, 2022 (PW1000G–
C–72–00–0188–00A–930A–D, Issue 002).
(2) This paragraph restates the
requirements of paragraph (g)(2) of AD 2023–
16–07. For Group 1 and Group 2 engines
with an installed HPT 2nd-stage hub having
P/N 30G6602 and an S/N listed in Tables 1,
2, 3, or 4 of PW SI NO. 149F–23, within 30
days after August 28, 2023 (the effective date
of AD 2023–16–07), perform an AUSI of the
HPT 2nd-stage hubs for cracks in accordance
with the Accomplishment Instructions,
paragraph 9.C. or 9.D., as applicable, of
PW1000G–C–72–00–0188–00A–930A–D,
Issue 002.
(h) New Required Actions
(1) For Group 1 and Group 2 engines with
an installed HPC IBR–7 having part number
(P/N) 30G2307 or 30G4407 or an installed
HPC IBR–8 having P/N, 30G5608, 30G5908 or
30G8908, at the next HPC engine shop visit
and thereafter at every HPC engine shop visit,
perform an angled ultrasonic scan inspection
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(AUSI) of the affected HPC IBR–7 or HPC
IBR–8, as applicable, for cracks in accordance
with the Accomplishment Instructions,
paragraph 4.E.(1) or 4.E.(2), of PW Alert
Service Bulletin (ASB) PW1000G–C–72–00–
0224–00A–930A–D, Issue No: 001, dated
November 3, 2023.
(2) For Group 1 and Group 2 engines with
an installed HPT 1st-stage hub having P/N
30G7301 or an HPT 2nd-stage hub having
P/N 30G6602, before exceeding the
applicable compliance time in Table 1 to
paragraph (h)(2) of this AD, except as
required by paragraphs (g)(1) and (2) and
paragraph (h)(5) of this AD, perform an AUSI
of the affected HPT 1st-stage hub or HPT
2nd-stage hub, as applicable, for cracks in
accordance with the Accomplishment
Instructions, paragraph 1.D.(7)(a) or 1.D.(7)(b)
of PW ASB PW1000G–C–72–00–0225–00A–
930A–D Issue No: 001, dated November 3,
2023 (PW ASB PW1000G–C–72–00–0225–
00A–930A–D). Thereafter, repeat the AUSI at
the applicable interval in Table 1 to
paragraph (h)(2) of this AD.
TABLE 1 TO PARAGRAPH (h)(2)—AUSI COMPLIANCE TIMES
Engine
group
AUSI performed prior
to effective date of
this AD
1 .........
No .............................
1 .........
Yes ...........................
2 .........
No .............................
2 .........
Yes ...........................
Compliance time
Repetitive interval
Before accumulating 3,800 cycles since new (CSN) or
within 100 flight cycles (FCs) after the effective date
of this AD, whichever occurs later.
At the next HPT engine shop visit, not to exceed
3,800 FCs since the previous AUSI, or within 100
FCs after the effective date of this AD, whichever
occurs later.
Before accumulating 2,800 CSN or within 100 FCs
after the effective date of this AD, whichever occurs
later.
At the next HPT engine shop visit, not to exceed
2,800 FCs since the previous AUSI, or within 100
FCs after the effective date of this AD, whichever
occurs later.
(3) For Group 1 and Group 2 engines with
an installed part listed in Table 2 to
paragraph (h)(3) of this AD, before exceeding
Thereafter at each HPT engine shop visit
exceeding 3,800 FCs from the last AUSI
fected hub, whichever occurs first.
Thereafter at each HPT engine shop visit
exceeding 3,800 FCs from the last AUSI
fected hub, whichever occurs first.
or before
of the afor before
of the af-
Thereafter at each HPT engine shop visit or before
exceeding 2,800 FCs from the last angled AUSI of
the affected hub, whichever occurs first.
Thereafter at each HPT engine shop visit or before
exceeding 2,800 FCs from the last AUSI of the affected hub, whichever occurs first.
the applicable compliance times specified in
Table 2 to paragraph (h)(3) of this AD,
remove the affected part from service and
replace with a part eligible for installation.
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TABLE 2 TO PARAGRAPH (h)(3)—PART REPLACEMENT COMPLIANCE TIMES
Engine
group
Part name
Part No.
Compliance time
1 and 2 .....
HPC rear hub ...........................
30G4008 ...................................
1 and 2 .....
HPT 1st-stage hub ...................
30G4201 or 30G6201 ..............
At the next HPC shop visit or HPT shop visit, whichever occurs first after the effective date of this AD.
At the next HPT engine shop visit, except as required by paragraphs (h)(4) and (6) of this AD.
HPT 2nd-stage hub ..................
HPT 1st-stage front air seal .....
HPT 2nd-stage rear air seal ....
HPT 1st-stage blade retaining
plate.
HPT 2nd-stage blade retaining
plate.
HPC rear hub ...........................
HPC IBR–7 ...............................
HPC IBR–8 ...............................
30G3902 or 30G5502.
30G3994 or 30G4674.
30G2452.
30G2446.
1 ................
HPT 1st-stage hub ...................
HPT 2nd-stage hub ..................
VerDate Sep<11>2014
16:23 Dec 11, 2023
Jkt 262001
30G2447.
30G8208 ...................................
30G2307 or 30G4407 ..............
30G5608 or 30G5908 or
30G8908.
30G7301.
30G6602.
PO 00000
Frm 00026
Fmt 4702
Before accumulating 7,000 CSN or within 100 FCs after the effective date of this AD, whichever occurs later.
Sfmt 4702
E:\FR\FM\12DEP1.SGM
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86092
Federal Register / Vol. 88, No. 237 / Tuesday, December 12, 2023 / Proposed Rules
TABLE 2 TO PARAGRAPH (h)(3)—PART REPLACEMENT COMPLIANCE TIMES—Continued
Engine
group
Part name
Part No.
Compliance time
2 ................
HPC rear hub ...........................
HPC IBR–7 ...............................
HPC IBR–8 ...............................
30G8208 ...................................
30G2307 or 30G4407 ..............
30G5608 or 30G5908 or
30G8908.
30G7301.
30G6602.
Before accumulating 5,000 CSN or within 100 FCs after the effective date of this AD, whichever occurs later.
HPT 1st-stage hub ...................
HPT 2nd-stage hub ..................
ddrumheller on DSK120RN23PROD with PROPOSALS1
(4) For Group 1 and Group 2 engines with
an installed HPT 1st-stage hub having P/N
30G6201 or an HPT 2nd-stage hub having
P/N 30G5502 and an S/N listed in Tables 1,
2, 3, or 4 of PW SI NO. 149F–23 that has not
had an AUSI performed before the effective
date of the AD, before further flight, remove
the affected hub from service.
(5) For Group 1 and Group 2 engines with
an installed HPT 1st-stage hub having P/N
30G7301 or an HPT 2nd-stage hub having
P/N 30G6602 with an S/N listed in Tables 1,
2, 3, or 4 of PW SI NO. 198F–23, dated
November 3, 2023, within 100 FC after the
effective date of this AD, perform an AUSI of
the affected hub for cracks in accordance
with the Accomplishment Instructions,
paragraph 1.D.(7)(a) or 1.D.(7)(b) of PW ASB
PW1000G–C–72–00–0225–00A–930A–D.
(6) For Group 1 and Group 2 engines with
an installed HPT 1st-stage hub having P/N
30G6201 or an HPT 2nd-stage hub having
P/N 30G5502 with an S/N listed in Tables 1,
2, 3, or 4 of PW SI NO. 198F–23, dated
November 3, 2023, within 100 FC after the
effective date of this AD, remove the hub
from service and replace with a part eligible
for installation.
(7) If any crack is found during any
inspection required by this AD, before further
flight, remove the affected part from service
and replace with a part eligible for
installation.
(8) If an affected part has accumulated 100
FCs or less since the last AUSI, reinspection
is not required provided that the part was not
damaged during removal from the engine.
(i) Definitions
(1) For the purposes of this AD, ‘‘Group 1
engines’’ are IAE LLC Model PW1122G–JM,
PW1124G1–JM, PW1124G–JM, PW1127G–
JM, PW1127G1–JM, and PW1127GA–JM
engines.
(2) For the purposes of this AD, ‘‘Group 2
engines’’ are IAE LLC Model PW1129G–JM,
PW1130G–JM, PW1133G–JM, PW1133GA–
JM, PW1428G–JM, PW1428GA–JM,
PW1428GH–JM, PW1431G–JM, PW1431GA–
JM, and PW1431GH–JM engines.
(3) For the purposes of this AD, an ‘‘HPC
engine shop visit’’ is the induction of an
engine into the shop for maintenance
involving the separation of the H-flange.
(4) For the purposes of this AD, an ‘‘HPT
engine shop visit’’ is the induction of an
engine into the shop for maintenance
involving the separation of the M-flange.
(5) For the purposes of this AD, a ‘‘part
eligible for installation’’ is:
(i) An HPC IBR–7 having P/N 30G2307 or
30G4407, that has passed the AUSI required
VerDate Sep<11>2014
16:23 Dec 11, 2023
Jkt 262001
by paragraph (h)(1) of this AD or later
approved P/N.
(ii) An HPC IBR–8 having, P/N 30G5608,
30G5908, or 30G8908 that has passed the
AUSI required by paragraph (h)(1) of this AD
or later approved P/N.
(iii) An HPT 1st-stage hub having P/N
30G7301 that has passed the AUSI required
by paragraph (h)(2) of this AD or later
approved P/N.
(iv) An HPT 2nd-stage hub having P/N
30G6602 that has passed the AUSI required
by paragraph (h)(2) of this AD or later
approved P/N.
(v) An HPC rear hub, P/N 30G8208 or later
approved P/N.
(vi) An HPT 1st-stage front air seal, P/N
30G4617 or later approved P/N.
(vii) An HPT 2nd-stage rear air seal, P/N
30G4811 or later approved P/N.
(viii) An HPT 1st-stage blade retaining
plate, P/N 30G6059, 31G0018 or later
approved P/N.
(j) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraph (g)(1) and (2)
of this AD, if those actions were performed
before the effective date of this AD using PW
Service Bulletin PW1000G–C–72–00–0188–
00A–930A–D, Issue No: 001, dated
September 13, 2021. This service information
is not incorporated by reference in this AD.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, AIR–520 Continued
Operational Safety 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 AIR–520 Continued
Operational Safety Branch, send it to the
attention of the person identified in
paragraph (l)(1) of this AD.
(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.
(l) Additional Information
(1) For more information about this AD,
contact Carol Nguyen, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des
Moines, WA 98198; phone: (781) 238–7655;
email: carol.nguyen@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
PO 00000
Frm 00027
Fmt 4702
Sfmt 9990
available at the addresses specified in
paragraphs (m)(6) and (7) of this AD.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(3) The following service information was
approved for IBR on [DATE 35 DAYS AFTER
PUBLICATION OF THE FINAL RULE].
(i) Pratt & Whitney (PW) Alert Service
Bulletin PW1000G–C–72–00–0224–00A–
930A–D, Issue No: 001, dated November 3,
2023.
(ii) PW Alert Service Bulletin PW1000G–
C–72–00–0225–00A–930A–D, Issue No: 001,
dated November 3, 2023.
(iii) PW Special Instruction NO. 198F–23,
dated November 3, 2023.
(4) The following service information was
approved for IBR on August 28, 2023 (88 FR
56999, August 22, 2023).
(i) PW Special Instruction NO. 149F–23,
dated August 4, 2023.
(ii) [Reserved]
(5) The following service information was
approved for IBR on November 7, 2022 (87
FR 59660, October 3, 2022; corrected October
24, 2022 (87 FR 64156)).
(i) PW Service Bulletin PW1000G–C–72–
00–0188–00A–930A–D, Issue No: 002, dated
July 8, 2022.
(ii) [Reserved]
(6) For PW service information identified
in this AD, contact International Aero
Engines, LLC, 400 Main Street, East Hartford,
CT 06118; phone: (860) 565–0140; email:
help24@pw.utc.com; website:
connect.prattwhitney.com.
(7) You may view this service information
at the FAA, Airworthiness Products Section,
Operational Safety Branch, 1200 District
Avenue, Burlington, MA 01803. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(8) You may view this material at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
visit www.archives.gov/federal-register/cfr/
ibr-locations or email fr.inspection@nara.gov.
Issued on December 4, 2023.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2023–27047 Filed 12–11–23; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\12DEP1.SGM
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]]>Agencies
[Federal Register Volume 88, Number 237 (Tuesday, December 12, 2023)]
[Proposed Rules]
[Pages 86088-86092]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-27047]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-2237; Project Identifier AD-2023-01057-E]
RIN 2120-AA64
Airworthiness Directives; International Aero Engines, LLC Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2022-19-15, which applies to certain International Aero Engines, LLC
(IAE LLC) Model PW1100G series engines; and AD 2023-16-07, which
applies to certain IAE LLC Model PW1100G series engines and PW1400G
series engines. AD 2022-19-15 requires an angled ultrasonic inspection
(AUSI) of the high-pressure turbine (HPT) 1st-stage disk and HPT 2nd-
stage disk, and replacement if necessary. AD 2023-16-07 requires an
AUSI of the HPT 1st-stage hub (also known as the HPT 1st-stage disk)
and HPT 2nd-stage hub (also known as the HPT 2nd-stage disk) for
cracks, and replacement if necessary, which is terminating action for
AD 2022-19-15. Since the FAA issued these two ADs, an investigation
determined an increased risk of powder metal anomalies for all powder
metal parts in certain powder metal production campaigns, which are
susceptible to failure significantly earlier than previously
determined. This proposed AD would retain the AUSI requirement for
certain HPT 1st-stage and HPT 2nd-stage hubs from AD 2023-16-07. This
proposed AD would also require performing an AUSI of the HPT 1st-stage
hub, HPT 2nd-stage hub, high-pressure compressor (HPC) 7th-stage
integrally bladed rotor (IBR-7), and HPC 8th-stage integrally bladed
rotor (IBR-8) for cracks and replacement if necessary. This proposed AD
would also require accelerated replacement of the HPC IBR-7, HPC IBR-8,
HPC rear hub, HPT 1st-stage hub, HPT 1st-stage air seal, HPT 1st-stage
blade retaining plate, HPT 2nd-stage hub, HPT 2nd-stage blade retaining
plate, and HPT 2nd-stage rear seal. The FAA is proposing this AD to
address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by January 11,
2024.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to regulations.gov. Follow
the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2023-2237; 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 NPRM, any comments received, and other
information. The street address for Docket Operations is listed above.
Material Incorporated by Reference:
For Pratt and Whitney (PW) service information identified
in this NPRM, contact International Aero Engines, LLC, 400 Main Street,
East Hartford, CT 06118; phone: (860) 565-0140; email:
[email protected]; website: connect.prattwhitney.com.
You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 1200
District Avenue, Burlington, MA 01803. For information on the
availability of this material at the FAA, call (817) 222-5110.
FOR FURTHER INFORMATION CONTACT: Carol Nguyen, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone:
(781) 238-7655; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2023-2237; Project Identifier
AD-2023-01057-E'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
the proposal because of those comments.
The FAA has been informed that PW has done some outreach with
affected operators regarding the proposed corrective actions for this
unsafe condition. As a result, affected operators are already aware of
the proposed corrective actions and, in some cases, have already begun
planning for replacement of the affected parts. Therefore, the FAA has
determined that a 30-day comment period is appropriate given the
particular circumstances related to the proposed correction of this
unsafe condition.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
regulations.gov, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to Carol
Nguyen, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des
Moines, WA 98198. Any commentary that the FAA receives which is not
specifically designated as CBI will be placed in the public docket for
this rulemaking.
Background
The FAA issued AD 2022-19-15, Amendment 39-22184 (87 FR 59660,
October 3, 2022; corrected October 24, 2022 (87 FR 64156)) (AD 2022-19-
15), for certain IAE LLC Model PW1122G-JM, PW1124G1-JM, PW1124G-JM,
PW1127G1-JM, PW1127GA-JM, PW1127G-JM, PW1129G-JM, PW1130G-JM, PW1133GA-
JM, and
[[Page 86089]]
PW1133G-JM engines. AD 2022-19-15 was prompted by an analysis of an
event involving an International Aero Engines AG V2533-A5 model
turbofan engine, which experienced an uncontained failure of an HPT
1st-stage disk that resulted in high-energy debris penetrating the
engine cowling. AD 2022-19-15 requires performing an AUSI of the HPT
1st-stage disk and HPT 2nd-stage disk and, depending on the results of
the inspections, replacing the HPT 1st-stage disk or HPT 2nd-stage
disk. The FAA issued AD 2022-19-15 to prevent failure of the HPT 1st-
stage disk and HPT 2nd-stage disk.
Since the FAA issued AD 2022-19-15, an Airbus Model A320neo
airplane powered by IAE LLC Model PW1127GA-JM engines experienced a
failure of the HPC IBR-7 that resulted in an engine shutdown and an
aborted take-off. Following this event, the manufacturer conducted a
records review of production and field-returned parts and then re-
evaluated their engineering analysis methodology. The new analysis
identified HPT 1st-stage hubs and HPT 2nd-stage hubs that are
susceptible to failure significantly earlier than previously
determined. On August 4, 2023, PW issued service information with
procedures for an AUSI to detect cracks and prevent premature failure.
The manufacturer's updated analysis also identified PW1400G series
engines that contain HPT 1st-stage hubs and HPT 2nd-stage hubs that are
also subject to the unsafe condition. The FAA determined that the new
service information necessitated action much earlier than the
compliance time mandated in AD 2022-19-15 and that the additional
engines should also be subject to these actions. As a result, the FAA
issued AD 2023-16-07, Amendment 39-22526 (88 FR 56999, August 22, 2023)
(AD 2023-16-07) for certain IAE LLC Model PW1122G-JM, PW1124G1-JM,
PW1124G-JM, PW1127G-JM, PW1127G1-JM, PW1127GA-JM, PW1129G-JM, PW1130G-
JM, PW1133G-JM, PW1133GA-JM, PW1428G-JM, PW1428GA-JM, PW1428GH-JM,
PW1431G-JM, PW1431GA-JM, and PW1431GH-JM engines. AD 2023-16-07
requires performing an AUSI of the HPT 1st-stage hub (also known as the
HPT 1st-stage disk) and HPT 2nd-stage hub (also known as the HPT 2nd-
stage disk) for cracks and, depending on the results of the
inspections, replacing the HPT 1st-stage hub or HPT 2nd-stage hub,
which was terminating action for the requirements of AD 2022-19-15. The
FAA issued AD 2023-16-07 to prevent failure of the HPT 1st-stage hub
and HPT 2nd-stage hub.
Actions Since the Previous ADs Were Issued
Since the FAA issued AD 2023-16-07, additional manufacturer
analysis found that the failure of the HPC IBR-7 was caused by a powder
metal anomaly, similar in nature to the anomalies outlined in AD 2022-
19-15. The analysis also concluded that there is an increased risk of
failure for additional powder metal parts in certain powder metal
production campaigns, specifically the HPC IBR-7 and HPC IBR-8, and
that all affected parts are susceptible to failure significantly
earlier than previously determined. The condition, if not addressed,
could result in uncontained hub failure, release of high-energy debris,
damage to the engine, damage to the airplane, and loss of the airplane.
FAA's Determination
The FAA is issuing this NPRM after determining that the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
Related Service Information Under 1 CFR Part 51
The FAA reviewed the following service information:
PW Alert Service Bulletin (ASB) PW1000G-C-72-00-0224-00A-
930A-D, Issue No: 001, dated November 3, 2023, which specifies
procedures for performing an AUSI for cracks on affected HPC IBR-7 and
HPC IBR-8;
PW ASB PW1000G-C-72-00-0225-00A-930A-D Issue No: 001,
dated November 3, 2023, which specifies procedures for performing an
AUSI for cracks on affected HPT 1st-stage hubs and HPT 2nd-stage hubs;
PW Service Bulletin PW1000G-C-72-00-0188-00A-930A-D, Issue
No: 002, dated July 8, 2022, which was previously approved for
incorporation by reference on November 7, 2022 (87 FR 59660, October 3,
2022; corrected October 24, 2022 (87 FR 64156)). This service
information specifies procedures for performing an AUSI for cracks on
affected HPT 1st-stage hubs and HPT 2nd-stage hubs;
PW Special Instruction (SI) NO. 149F-23, dated August 4,
2023, which was previously approved for incorporation by reference on
August 28, 2023 (88 FR 56999, August 22, 2023). This service
information specifies the list of affected HPT 1st-stage hubs and HPT
2nd-stage hubs, identified by part number and serial number, installed
on certain IAE LLC engines; and
PW SI NO. 198F-23, dated November 3, 2023, which specifies
the list of affected HPT 1st-stage hubs and HPT 2nd-stage hubs,
identified by part number and serial number, installed on certain IAE
LLC engines.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in ADDRESSES.
Proposed AD Requirements in This NPRM
This proposed AD would retain none of the requirements of AD 2022-
19-15, but it would retain certain requirements of AD 2023-16-07. This
proposed AD would require performing an AUSI of the HPT 1st-stage hub
and HPT 2nd-stage hub and replacing as necessary. This proposed AD
would also require performing an AUSI of the HPC IBR-7 and HPC IBR-8
for cracks and replacing as necessary. This proposed AD would also
require accelerated replacement of the HPC IBR-7, HPC IBR-8, HPC rear
hub, HPT 1st-stage hub, HPT 1st-stage air seal, HPT 1st-stage blade
retaining plate, HPT 2nd-stage hub, HPT 2nd-stage blade retaining
plate, and HPT 2nd-stage rear seal.
Interim Action
The FAA considers this proposed AD to be an interim action. The
unsafe condition is still under investigation by the manufacturer and,
depending on the results of that investigation, the FAA may consider
further rulemaking action.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 430 engines installed on airplanes of U.S. registry. The FAA
estimates that 366 engines will need replacement of the HPT 1st-stage
hub; 351 engines will need replacement of the HPT 2nd-stage hub; 408
engines will replacement of the HPC IBR-7; 368 engines will need
replacement of the HPC IBR-8; 283 engines will need replacement of the
HPC rear hub; and 206 engines will need replacement of the HPT 1st-
stage air seal, HPT 1st-stage blade retaining plate, HPT 2nd-stage
blade retaining plate, and HPT 2nd-stage rear seal.
The FAA estimates the following costs to comply with this proposed
AD:
[[Page 86090]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts cost
Action Labor cost (average pro- Cost per product Cost on U.S.
rated cost) operators
----------------------------------------------------------------------------------------------------------------
AUSI of HPT 1st-stage hub, HPT 80 work-hours x $85 $0 $6,800............. $2,924,000
2nd-stage hub, HPC IBR-7, and per hour = $6,800.
HPC IBR-8 for cracks.
Replace HPT 1st-stage hub........ 10 work-hours x $85 56,000 56,850............. 20,807,100
per hour = $850.
Replace HPT 2nd-stage hub........ 10 work-hours x $85 62,000 62,850............. 22,060,350
per hour = $850.
Replace HPC IBR-7................ 10 work-hours x $85 82,000 82,850............. 33,802,800
per hour = $850.
Replace HPC IBR-8................ 10 work-hours x $85 93,000 93,850............. 34,536,800
per hour = $850.
Replace HPC rear hub............. 10 work-hours x $85 132,000 132,850............ 37,596,550
per hour = $850.
Replace HPT 1st-stage air seal, 20 work-hours x $85 35,000 36,700............. 7,560,200
HPT 1st-stage blade retaining per hour = $1,700.
plate, HPT 2nd-stage blade
retaining plate, and HPT 2nd-
stage rear seal.
----------------------------------------------------------------------------------------------------------------
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected operators.
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
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would 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 Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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:
0
a. Removing Airworthiness Directive 2022-19-15, Amendment 39-22184 (87
FR 59660; corrected October 3, 2022 (87 FR 64156)); and Airworthiness
Directive 2023-16-07, Amendment 39-22526 (88 FR 56999, August 22,
2023); and
0
b. Adding the following new airworthiness directive:
International Aero Engines, LLC: Docket No. FAA-2023-2237; Project
Identifier AD-2023-01057-E.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by January 11, 2024.
(b) Affected ADs
(1) This AD replaces AD 2022-19-15, Amendment 39-22184 (87 FR
59660, October 3, 2022; corrected October 24, 2022 (87 FR 64156)).
(2) This AD replaces AD 2023-16-07, Amendment 39-22526 (88 FR
56999, August 22, 2023) (AD 2023-16-07).
(c) Applicability
This AD applies to International Aero Engines, LLC (IAE LLC)
Model PW1122G-JM, PW1124G1-JM, PW1124G-JM, PW1127G-JM, PW1127G1-JM,
PW1127GA-JM, PW1129G-JM, PW1130G-JM, PW1133G-JM, PW1133GA-JM,
PW1428G-JM, PW1428GA-JM, PW1428GH-JM, PW1431G-JM, PW1431GA-JM, and
PW1431GH-JM engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section; 7250, Turbine Section.
(e) Unsafe Condition
This AD was prompted by an analysis of an event involving an IAE
LLC Model PW1127GA-JM engine, which experienced failure of a high-
pressure compressor (HPC) 7th-stage integrally bladed rotor (IBR-7)
that resulted in an engine shutdown and aborted takeoff. The FAA is
issuing this AD to prevent failure of the high-pressure turbine
(HPT) 1st-stage hub, HPT 2nd-stage hub, HPC IBR-7, and HPC 8th-stage
integrally bladed rotor (IBR-8). The unsafe condition, if not
addressed, could result in uncontained hub
[[Page 86091]]
failure, release of high-energy debris, damage to the engine, damage
to the airplane, and loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspections From AD 2023-16-07, With No Changes
(1) This paragraph restates the requirements of paragraph (g)(1)
of AD 2023-16-07. For Group 1 and Group 2 engines with an installed
HPT 1st-stage hub having part number (P/N) 30G7301 and a serial
number (S/N) listed in Tables 1, 2, 3, or 4 of Pratt & Whitney (PW)
Special Instruction (SI) NO. 149F-23, dated August 4, 2023 (PW SI
NO. 149F-23), within 30 days after August 28, 2023 (the effective
date of AD 2023-16-07), perform an AUSI of the HPT 1st-stage hubs
for cracks in accordance with the Accomplishment Instructions,
paragraph 9.A. or 9.B., as applicable, of PW Service Bulletin
PW1000G-C-72-00-0188-00A-930A-D, Issue No: 002, dated July 8, 2022
(PW1000G-C-72-00-0188-00A-930A-D, Issue 002).
(2) This paragraph restates the requirements of paragraph (g)(2)
of AD 2023-16-07. For Group 1 and Group 2 engines with an installed
HPT 2nd-stage hub having P/N 30G6602 and an S/N listed in Tables 1,
2, 3, or 4 of PW SI NO. 149F-23, within 30 days after August 28,
2023 (the effective date of AD 2023-16-07), perform an AUSI of the
HPT 2nd-stage hubs for cracks in accordance with the Accomplishment
Instructions, paragraph 9.C. or 9.D., as applicable, of PW1000G-C-
72-00-0188-00A-930A-D, Issue 002.
(h) New Required Actions
(1) For Group 1 and Group 2 engines with an installed HPC IBR-7
having part number (P/N) 30G2307 or 30G4407 or an installed HPC IBR-
8 having P/N, 30G5608, 30G5908 or 30G8908, at the next HPC engine
shop visit and thereafter at every HPC engine shop visit, perform an
angled ultrasonic scan inspection (AUSI) of the affected HPC IBR-7
or HPC IBR-8, as applicable, for cracks in accordance with the
Accomplishment Instructions, paragraph 4.E.(1) or 4.E.(2), of PW
Alert Service Bulletin (ASB) PW1000G-C-72-00-0224-00A-930A-D, Issue
No: 001, dated November 3, 2023.
(2) For Group 1 and Group 2 engines with an installed HPT 1st-
stage hub having P/N 30G7301 or an HPT 2nd-stage hub having P/N
30G6602, before exceeding the applicable compliance time in Table 1
to paragraph (h)(2) of this AD, except as required by paragraphs
(g)(1) and (2) and paragraph (h)(5) of this AD, perform an AUSI of
the affected HPT 1st-stage hub or HPT 2nd-stage hub, as applicable,
for cracks in accordance with the Accomplishment Instructions,
paragraph 1.D.(7)(a) or 1.D.(7)(b) of PW ASB PW1000G-C-72-00-0225-
00A-930A-D Issue No: 001, dated November 3, 2023 (PW ASB PW1000G-C-
72-00-0225-00A-930A-D). Thereafter, repeat the AUSI at the
applicable interval in Table 1 to paragraph (h)(2) of this AD.
Table 1 to Paragraph (h)(2)--AUSI Compliance Times
----------------------------------------------------------------------------------------------------------------
AUSI performed prior to
Engine group effective date of this Compliance time Repetitive interval
AD
----------------------------------------------------------------------------------------------------------------
1................ No..................... Before accumulating 3,800 cycles Thereafter at each HPT engine
since new (CSN) or within 100 shop visit or before exceeding
flight cycles (FCs) after the 3,800 FCs from the last AUSI of
effective date of this AD, the affected hub, whichever
whichever occurs later. occurs first.
1................ Yes.................... At the next HPT engine shop Thereafter at each HPT engine
visit, not to exceed 3,800 FCs shop visit or before exceeding
since the previous AUSI, or 3,800 FCs from the last AUSI of
within 100 FCs after the the affected hub, whichever
effective date of this AD, occurs first.
whichever occurs later.
2................ No..................... Before accumulating 2,800 CSN or Thereafter at each HPT engine
within 100 FCs after the shop visit or before exceeding
effective date of this AD, 2,800 FCs from the last angled
whichever occurs later. AUSI of the affected hub,
whichever occurs first.
2................ Yes.................... At the next HPT engine shop Thereafter at each HPT engine
visit, not to exceed 2,800 FCs shop visit or before exceeding
since the previous AUSI, or 2,800 FCs from the last AUSI of
within 100 FCs after the the affected hub, whichever
effective date of this AD, occurs first.
whichever occurs later.
----------------------------------------------------------------------------------------------------------------
(3) For Group 1 and Group 2 engines with an installed part
listed in Table 2 to paragraph (h)(3) of this AD, before exceeding
the applicable compliance times specified in Table 2 to paragraph
(h)(3) of this AD, remove the affected part from service and replace
with a part eligible for installation.
Table 2 to Paragraph (h)(3)--Part Replacement Compliance Times
------------------------------------------------------------------------
Engine group Part name Part No. Compliance time
------------------------------------------------------------------------
1 and 2....... HPC rear hub.... 30G4008......... At the next HPC shop
visit or HPT shop
visit, whichever
occurs first after
the effective date
of this AD.
1 and 2....... HPT 1st-stage 30G4201 or At the next HPT
hub. 30G6201. engine shop visit,
except as required
by paragraphs
(h)(4) and (6) of
this AD.
HPT 2nd-stage 30G3902 or
hub. 30G5502.
HPT 1st-stage 30G3994 or
front air seal. 30G4674.
HPT 2nd-stage 30G2452.........
rear air seal.
HPT 1st-stage 30G2446.........
blade retaining
plate.
HPT 2nd-stage 30G2447.........
blade retaining
plate.
1............. HPC rear hub.... 30G8208......... Before accumulating
HPC IBR-7....... 30G2307 or 7,000 CSN or within
30G4407. 100 FCs after the
effective date of
this AD, whichever
occurs later.
HPC IBR-8....... 30G5608 or
30G5908 or
30G8908.
HPT 1st-stage 30G7301.........
hub.
HPT 2nd-stage 30G6602.........
hub.
[[Page 86092]]
2............. HPC rear hub.... 30G8208......... Before accumulating
HPC IBR-7....... 30G2307 or 5,000 CSN or within
30G4407. 100 FCs after the
effective date of
this AD, whichever
occurs later.
HPC IBR-8....... 30G5608 or
30G5908 or
30G8908.
HPT 1st-stage 30G7301.........
hub.
HPT 2nd-stage 30G6602.........
hub.
------------------------------------------------------------------------
(4) For Group 1 and Group 2 engines with an installed HPT 1st-
stage hub having P/N 30G6201 or an HPT 2nd-stage hub having P/N
30G5502 and an S/N listed in Tables 1, 2, 3, or 4 of PW SI NO. 149F-
23 that has not had an AUSI performed before the effective date of
the AD, before further flight, remove the affected hub from service.
(5) For Group 1 and Group 2 engines with an installed HPT 1st-
stage hub having P/N 30G7301 or an HPT 2nd-stage hub having P/N
30G6602 with an S/N listed in Tables 1, 2, 3, or 4 of PW SI NO.
198F-23, dated November 3, 2023, within 100 FC after the effective
date of this AD, perform an AUSI of the affected hub for cracks in
accordance with the Accomplishment Instructions, paragraph
1.D.(7)(a) or 1.D.(7)(b) of PW ASB PW1000G-C-72-00-0225-00A-930A-D.
(6) For Group 1 and Group 2 engines with an installed HPT 1st-
stage hub having P/N 30G6201 or an HPT 2nd-stage hub having P/N
30G5502 with an S/N listed in Tables 1, 2, 3, or 4 of PW SI NO.
198F-23, dated November 3, 2023, within 100 FC after the effective
date of this AD, remove the hub from service and replace with a part
eligible for installation.
(7) If any crack is found during any inspection required by this
AD, before further flight, remove the affected part from service and
replace with a part eligible for installation.
(8) If an affected part has accumulated 100 FCs or less since
the last AUSI, reinspection is not required provided that the part
was not damaged during removal from the engine.
(i) Definitions
(1) For the purposes of this AD, ``Group 1 engines'' are IAE LLC
Model PW1122G-JM, PW1124G1-JM, PW1124G-JM, PW1127G-JM, PW1127G1-JM,
and PW1127GA-JM engines.
(2) For the purposes of this AD, ``Group 2 engines'' are IAE LLC
Model PW1129G-JM, PW1130G-JM, PW1133G-JM, PW1133GA-JM, PW1428G-JM,
PW1428GA-JM, PW1428GH-JM, PW1431G-JM, PW1431GA-JM, and PW1431GH-JM
engines.
(3) For the purposes of this AD, an ``HPC engine shop visit'' is
the induction of an engine into the shop for maintenance involving
the separation of the H-flange.
(4) For the purposes of this AD, an ``HPT engine shop visit'' is
the induction of an engine into the shop for maintenance involving
the separation of the M-flange.
(5) For the purposes of this AD, a ``part eligible for
installation'' is:
(i) An HPC IBR-7 having P/N 30G2307 or 30G4407, that has passed
the AUSI required by paragraph (h)(1) of this AD or later approved
P/N.
(ii) An HPC IBR-8 having, P/N 30G5608, 30G5908, or 30G8908 that
has passed the AUSI required by paragraph (h)(1) of this AD or later
approved P/N.
(iii) An HPT 1st-stage hub having P/N 30G7301 that has passed
the AUSI required by paragraph (h)(2) of this AD or later approved
P/N.
(iv) An HPT 2nd-stage hub having P/N 30G6602 that has passed the
AUSI required by paragraph (h)(2) of this AD or later approved P/N.
(v) An HPC rear hub, P/N 30G8208 or later approved P/N.
(vi) An HPT 1st-stage front air seal, P/N 30G4617 or later
approved P/N.
(vii) An HPT 2nd-stage rear air seal, P/N 30G4811 or later
approved P/N.
(viii) An HPT 1st-stage blade retaining plate, P/N 30G6059,
31G0018 or later approved P/N.
(j) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraph (g)(1) and (2) of this AD, if those actions were performed
before the effective date of this AD using PW Service Bulletin
PW1000G-C-72-00-0188-00A-930A-D, Issue No: 001, dated September 13,
2021. This service information is not incorporated by reference in
this AD.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, AIR-520 Continued Operational Safety 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 AIR-520 Continued
Operational Safety Branch, send it to the attention of the person
identified in paragraph (l)(1) of this AD.
(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.
(l) Additional Information
(1) For more information about this AD, contact Carol Nguyen,
Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines,
WA 98198; phone: (781) 238-7655; email: [email protected].
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (m)(6) and (7) of this AD.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
[DATE 35 DAYS AFTER PUBLICATION OF THE FINAL RULE].
(i) Pratt & Whitney (PW) Alert Service Bulletin PW1000G-C-72-00-
0224-00A-930A-D, Issue No: 001, dated November 3, 2023.
(ii) PW Alert Service Bulletin PW1000G-C-72-00-0225-00A-930A-D,
Issue No: 001, dated November 3, 2023.
(iii) PW Special Instruction NO. 198F-23, dated November 3,
2023.
(4) The following service information was approved for IBR on
August 28, 2023 (88 FR 56999, August 22, 2023).
(i) PW Special Instruction NO. 149F-23, dated August 4, 2023.
(ii) [Reserved]
(5) The following service information was approved for IBR on
November 7, 2022 (87 FR 59660, October 3, 2022; corrected October
24, 2022 (87 FR 64156)).
(i) PW Service Bulletin PW1000G-C-72-00-0188-00A-930A-D, Issue
No: 002, dated July 8, 2022.
(ii) [Reserved]
(6) For PW service information identified in this AD, contact
International Aero Engines, LLC, 400 Main Street, East Hartford, CT
06118; phone: (860) 565-0140; email: [email protected]; website:
connect.prattwhitney.com.
(7) You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 1200
District Avenue, Burlington, MA 01803. For information on the
availability of this material at the FAA, call (817) 222-5110.
(8) You may view this material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].
Issued on December 4, 2023.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2023-27047 Filed 12-11-23; 8:45 am]
BILLING CODE 4910-13-P
