Airworthiness Directives; International Aero Engines, AG Engines, 7636-7639 [2024-02205]
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7636
Proposed Rules
Federal Register
Vol. 89, No. 24
Monday, February 5, 2024
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2024–0041; Project
Identifier AD–2024–00032–E]
RIN 2120–AA64
Airworthiness Directives; International
Aero Engines, AG Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain International Aero Engines, AG
(IAE AG) Model V2500 engines. This
proposed AD was prompted by an
analysis of an event involving an
International Aero Engines, LLC (IAE
LLC) Model PW1127GA–JM engine,
which experienced a high-pressure
compressor (HPC) 7th-stage integrally
bladed rotor (IBR–7) separation that
resulted in an aborted takeoff. This
proposed AD would require performing
an angled ultrasonic inspection (AUSI)
of certain high-pressure turbine (HPT)
1st-stage hubs and HPT 2nd-stage hubs
for cracks and replacing if necessary.
This proposed AD would also require
accelerated replacement of certain HPT
1st-stage hubs and HPT 2nd-stage hubs.
The FAA is proposing this AD to
address the unsafe condition on these
products.
SUMMARY:
The FAA must receive comments
on this proposed AD by March 6, 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
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DATES:
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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–2024–0041; 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 & Whitney (PW) and IAE
AG service information identified in
this NPRM, contact International Aero
Engines, AG, 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–2024–0041; Project Identifier AD–
2024–00032–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 this 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
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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
On December 24, 2022, 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 aborted take-off. Following this
event, the manufacturer conducted a
records review of production and fieldreturned parts and re-evaluated their
engineering analysis methodology. The
new analysis found that the failure of
the HPC IBR–7 was caused by a nickel
powdered metal anomaly, similar in
nature to an anomaly previously
observed on March 18, 2020, when an
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Federal Register / Vol. 89, No. 24 / Monday, February 5, 2024 / Proposed Rules
Airbus Model A321–231 airplane,
powered by IAE AG Model V2533–A5
engines, experienced an uncontained
HPT 1st-stage hub failure that resulted
in high-energy debris penetrating the
engine cowling. The analysis also
concluded that there is an increased risk
of failure for a subpopulation of HPT
1st-stage hubs and HPT 2nd-stage hubs
that were manufactured from the same
production campaign (a batch of nickel
powdered metal) as the HPT 1st-stage
hub that failed on March 18, 2020; these
parts have a higher likelihood of
containing the nickel powdered metal
anomaly and are susceptible to failure
much earlier than previously
determined. As a result, the FAA is
proposing an accelerated AUSI for
certain HPT 1st-stage hubs and HPT
2nd-stage hubs and, depending on the
results of the inspections, replacing the
HPT 1st-stage hubs or HPT 2nd-stage
hubs. This proposed AD would also
require accelerated replacement of
certain HPT 1st-stage hubs and HPT
2nd-stage hubs. Certain IAE AG Model
V2522–A5, V2524–A5, V2525–D5,
V2527–A5, V2527E–A5, V2527M–A5,
V2528–D5, V2530–A5, V2531–E5, and
V2533–A5 engines are among the
products affected by this condition,
which, if not addressed, could result in
hub failure, release of high-energy
debris, damage to the engine, damage to
the airplane, and possible 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 IAE AG NonModification Service Bulletin (NMSB)
V2500–ENG–72–0720, dated November
20, 2023; and PW Special Instruction
NO. 189F–23, dated November 20, 2023
which only applies to the IAE AG
V2531–E5 Model engine. This service
information specifies procedures for
performing an AUSI for cracks on
affected HPT 1st-stage hubs and HPT
2nd-stage hubs. This service
information also 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 AG 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 require
performing an AUSI of certain HPT 1ststage hubs and HPT 2nd-stage hubs and,
depending on the results of the
inspections, replacing the HPT 1st-stage
hubs or HPT 2nd-stage hubs. This
proposed AD would also require
accelerated replacement of certain HPT
1st-stage hubs and HPT 2nd-stage hubs.
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 116
engines installed on airplanes of U.S.
registry. The FAA estimates that 40
engines would need an AUSI of the HPT
1st-stage hub; 40 engines would need an
AUSI of the HPT 2nd-stage hub; 67
engines would need replacement of the
HPT 1st-stage hub; and 49 engines
would need replacement of the HPT
2nd-stage hub.
The FAA estimates the following
costs to comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
AUSI of HPT 1st-stage hub ............................
AUSI of HPT 2nd-stage hub ...........................
Replace HPT 1st-stage hub ...........................
Replace HPT 2nd-stage hub ..........................
5 work-hours × $85 per hour = $425 .............
5 work-hours × $85 per hour = $425 .............
100 work-hours × $85 per hour = $8,500 ......
100 work-hours × $85 per hour = $8,500 ......
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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
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Parts cost
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 this proposed regulation:
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$0
0
460,000
360,000
Cost per
product
$425
425
468,500
368,500
Cost on U.S.
operators
$17,000
17,000
31,389,500
18,056,500
(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:
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Federal Register / Vol. 89, No. 24 / Monday, February 5, 2024 / Proposed Rules
(c) Applicability
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
damage to the airplane, and loss of the
airplane
This AD applies to International Aero
Engines, AG (IAE AG) Model V2522–A5,
V2524–A5, V2525–D5, V2527–A5, V2527E–
A5, V2527M–A5, V2528–D5, V2530–A5,
V2531–E5, and V2533–A5 engines.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(d) Subject
[Amended]
(g) Required Actions
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
Joint Aircraft System Component (JASC)
Code 7230, Turbine Engine.
International Aero Engines, AG: Docket No.
FAA–2024–0041; Project Identifier AD–
2024–00032–E.
This AD was prompted by an analysis of
an event involving an International Aero
Engines, LLC Model PW1127GA–JM engine,
which experienced failure of a high-pressure
compressor 7th-stage integrally bladed rotor
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 and HPT 2nd-stage hub.
The unsafe condition, if not addressed, could
result in uncontained hub failure, release of
high-energy debris, damage to the engine,
■
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by March 6,
2024.
(b) Affected ADs
This AD is related to AD 2022–02–09,
Amendment 39–21906 (87 FR 7029, February
8, 2022) (AD 2022–02–09).
(e) Unsafe Condition
(1) For engines with an installed part, part
number (P/N), and serial number (S/N) listed
in Table 1 to paragraph (g)(1) of this AD, with
no angled ultrasonic inspection (AUSI)
performed or the AUSI inspected part was
installed on or after November 1, 2023, at the
next engine shop visit after the effective date
of this AD before exceeding the applicable
cycle limit specified in Table 1 to paragraph
(g)(1) of this AD, perform an AUSI of the
affected parts for cracks in accordance with
the applicable service information listed in
Table 1 to paragraph (g)(1) of this AD.
TABLE 1 TO PARAGRAPH (g)(1)—AUSI COMPLIANCE TIMES
Previously
operated in
high-thrust
model engine
Cycle limit from the
effective date
of this AD
Part
Table S/N is listed in
HPT 1st-stage hub P/N
2A5001.
Table 1 of IAE AG Non-Modification
Service Bulletin V2500–ENG–72–
0720, dated November 20, 2023
(IAE AG NMSB V2500–ENG–72–
0720).
Table 1 of Pratt & Whitney (PW)
Special Instruction NO. 189F–23,
dated November 20, 2023 (PW
SI 189F–23).
Table 1 of IAE AG NMSB V2500–
ENG–72–0720.
Yes .................
No ..................
700 FCs .......................
Table 2 of IAE AG NMSB V2500–
ENG–72–0720.
Yes .................
800 FCs .......................
No ..................
1100 FCs .....................
HPT 2nd-stage hub P/N
2A4802.
Applicable service information
100 flight cycles (FCs)
Accomplishment Instructions, paragraph 5., of IAE AG NMSB
V2500–ENG–72–0720.
Accomplishment Instructions, paragraph 5., of PW SI 189F–23.
Table 2 PW SI 189F–23 .................
Table 2 of IAE AG NMSB V2500–
ENG–72–0720.
(2) For parts inspected in accordance with
paragraph (g)(1) of this AD, within 4,000 FCs
from accomplishment of the AUSI required
by paragraph (g)(1) of this AD or at the next
HPT module removal after the AUSI required
by paragraph (g)(1) of this AD, whichever
occurs first, remove the part from service and
replace with a part eligible for installation.
(3) If any crack is found during the
inspections required by paragraphs (g)(1) of
this AD, before further flight, remove the
affected part from service and replace with a
part eligible for installation.
(4) For engines with an AUSI inspected
part installed prior to November 1, 2023,
having a P/N and S/N listed in Table 2 to
Accomplishment Instructions, paragraph 5., of IAE AG NMSB
V2500–ENG–72–0720.
Accomplishment Instructions, paragraph 6., of IAE AG NMSB
V2500–ENG–72–0720.
Accomplishment Instructions, paragraph 6., of PW SI 189F–23.
Accomplishment Instructions, paragraph 6., of IAE AG NMSB
V2500–ENG–72–0720.
paragraph (g)(4) of this AD, at the next HPT
module removal after the effective date of
this AD, but before exceeding the applicable
cycle limit specified in Table 2 to paragraph
(g)(4) 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 (g)(4)—PART REPLACEMENT COMPLIANCE TIMES
Part
HPT 1st-stage hub P/N
2A5001.
HPT 2nd-stage hub P/N
2A4802.
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Previously operated in highthrust model engine
Table S/N is listed in
Table
Table
Table
Table
Table
1
1
1
2
2
of
of
of
of
of
Jkt 262001
IAE
PW
IAE
IAE
PW
AG NMSB V2500–ENG–72–0720 .................
SI 189F–23.
AG NMSB V2500–ENG–72–0720 .................
AG NMSB V2500–ENG–72–0720 .................
SI 189F–23.
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Cycle limit from
the effective
date of this AD
Yes .........................................
1,800 FCs.
No ..........................................
Yes .........................................
2,800 FCs.
3,400 FCs.
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Federal Register / Vol. 89, No. 24 / Monday, February 5, 2024 / Proposed Rules
TABLE 2 TO PARAGRAPH (g)(4)—PART REPLACEMENT COMPLIANCE TIMES—Continued
Table S/N is listed in
Previously operated in highthrust model engine
Table 2 of IAE AG NMSB V2500–ENG–72–0720 .................
No ..........................................
Part
(5) For engines with an installed part that
has a P/N and S/N listed in Table 3 to
paragraph (g)(5) of this AD, at the next HPT
module removal after the effective date of
this AD, but before exceeding the applicable
cycle limit specified in Table 3 to paragraph
Cycle limit from
the effective
date of this AD
3,800 FCs.
(g)(5) of this AD, remove the affected part
from service and replace with a part eligible
for installation.
TABLE 3 TO PARAGRAPH (g)(5)—PART REPLACEMENT COMPLIANCE TIMES
Part
HPT 1st-stage hub P/N
2A5001.
HPT 2nd-stage hub P/N
2A4802.
Table
Table
Table
Table
3
3
4
4
of
of
of
of
IAE
IAE
IAE
IAE
(h) Definitions
(1) For the purposes of this AD, a ‘‘part
eligible for installation’’ is an HPT 1st-stage
disk or HPT 2nd-stage disk having an S/N
that is not listed in IAE AG NMSB V2500–
ENG–72–0720 or PW SI 189F–23.
(2) For the purposes of this AD, an ‘‘HPT
module removal’’ is when the HPT rotor and
stator assembly are removed from the engine.
(3) For the purposes of this AD,
‘‘Previously operated in high-thrust model
engine’’ refers to HPT 1st-stage hubs or HPT
2nd-stage hubs that have previously operated
in an IAE AG Model V2527E–A5, V2527M–
A5, V2528–D5, V2530–A5, V2531–E5, or
V2533–A5 engine for any duration.
(4) For the purposes of this AD, an ‘‘engine
shop visit’’ is the induction of an engine into
the shop for maintenance involving the
separation of pairs of major mating engine
flanges, H–P, except for the following
situations, which do not constitute an engine
shop visit:
(i) Separation of engine flanges solely for
the purposes of transportation without
subsequent engine maintenance.
(ii) Engine removal for the purpose of
performing field maintenance activities at a
maintenance facility in lieu of performing
them on-wing.
(5) For the purposes of this AD, the date
that an AUSI inspected part was installed is
the date of the authorized release
certification for the shop visit at which the
part was first installed after the AUSI was
performed.
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(i) Terminating Action to AD 2022–02–09
Compliance with paragraph (g)(1) of this
AD satisfies the requirements of AD 2022–
02–09.
(j) 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
VerDate Sep<11>2014
17:18 Feb 02, 2024
Previously operated in highthrust model engine
Table S/N is listed in
Jkt 262001
AG
AG
AG
AG
NMSB
NMSB
NMSB
NMSB
V2500–ENG–72–0720
V2500–ENG–72–0720
V2500–ENG–72–0720
V2500–ENG–72–0720
.................
.................
.................
.................
Yes .........................................
No ..........................................
Yes .........................................
No ..........................................
Cycle limit from
the effective
date of this AD
1,800
2,800
3,400
3,800
FCs.
FCs.
FCs.
FCs.
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 (k) 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.
visit www.archives.gov/federal-register/cfr/
ibr-locations or email fr.inspection@nara.gov.
(k) Additional Information
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.
DEPARTMENT OF JUSTICE
(l) 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.
(i) International Aero Engines AG (IAE AG)
Non-Modification Service Bulletin V2500–
ENG–72–0720, dated November 20, 2023.
(ii) Pratt & Whitney (PW) Special
Instruction NO. 189F–23, dated November
20, 2023.
(3) For PW and IAE AG service information
identified in this AD, contact International
Aero Engines, AG, 400 Main Street, East
Hartford, CT 06118; phone: (860) 565–0140;
email: help24@pw.utc.com; website:
connect.prattwhitney.com.
(4) 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.
(5) You may view this material at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
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Issued on January 24, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2024–02205 Filed 1–31–24; 4:15 pm]
BILLING CODE 4910–13–P
Office of Justice Programs
28 CFR Part 94
[Docket No.: OJP (OVC) 1808]
RIN 1121–AA89
Subject: Victims of Crime Act (VOCA)
Victim Compensation Grant Program
Office for Victims of Crime,
Office of Justice Programs, Justice.
ACTION: Notice of proposed rulemaking.
AGENCY:
The Office of Justice Programs
(‘‘OJP’’), a bureau of the Department of
Justice, Office for Victims of Crime
(‘‘OVC’’) proposes adding a subpart to
its regulations to replace the existing
Victims of Crime Act (‘‘VOCA’’) Victim
Compensation Program Guidelines
(‘‘Guidelines’’), and update and codify
program requirements for the VOCA
Victim Compensation Formula Grant
Program (‘‘Victim Compensation
Program’’).
SUMMARY:
Comments must be received by
no later than 11:59 p.m., E.T., on April
5, 2024.
ADDRESSES:
Electronic comments: OVC
encourages commenters to submit all
comments electronically through the
DATES:
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]]>Agencies
[Federal Register Volume 89, Number 24 (Monday, February 5, 2024)]
[Proposed Rules]
[Pages 7636-7639]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-02205]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 89, No. 24 / Monday, February 5, 2024 /
Proposed Rules
[[Page 7636]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-0041; Project Identifier AD-2024-00032-E]
RIN 2120-AA64
Airworthiness Directives; International Aero Engines, AG Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain International Aero Engines, AG (IAE AG) Model V2500
engines. This proposed AD was prompted by an analysis of an event
involving an International Aero Engines, LLC (IAE LLC) Model PW1127GA-
JM engine, which experienced a high-pressure compressor (HPC) 7th-stage
integrally bladed rotor (IBR-7) separation that resulted in an aborted
takeoff. This proposed AD would require performing an angled ultrasonic
inspection (AUSI) of certain high-pressure turbine (HPT) 1st-stage hubs
and HPT 2nd-stage hubs for cracks and replacing if necessary. This
proposed AD would also require accelerated replacement of certain HPT
1st-stage hubs and HPT 2nd-stage hubs. 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 March 6,
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-2024-0041; 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 & Whitney (PW) and IAE AG service information
identified in this NPRM, contact International Aero Engines, AG, 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-2024-0041; Project Identifier
AD-2024-00032-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
this 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
On December 24, 2022, 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 aborted take-off.
Following this event, the manufacturer conducted a records review of
production and field-returned parts and re-evaluated their engineering
analysis methodology. The new analysis found that the failure of the
HPC IBR-7 was caused by a nickel powdered metal anomaly, similar in
nature to an anomaly previously observed on March 18, 2020, when an
[[Page 7637]]
Airbus Model A321-231 airplane, powered by IAE AG Model V2533-A5
engines, experienced an uncontained HPT 1st-stage hub failure that
resulted in high-energy debris penetrating the engine cowling. The
analysis also concluded that there is an increased risk of failure for
a subpopulation of HPT 1st-stage hubs and HPT 2nd-stage hubs that were
manufactured from the same production campaign (a batch of nickel
powdered metal) as the HPT 1st-stage hub that failed on March 18, 2020;
these parts have a higher likelihood of containing the nickel powdered
metal anomaly and are susceptible to failure much earlier than
previously determined. As a result, the FAA is proposing an accelerated
AUSI for certain HPT 1st-stage hubs and HPT 2nd-stage hubs and,
depending on the results of the inspections, replacing the HPT 1st-
stage hubs or HPT 2nd-stage hubs. This proposed AD would also require
accelerated replacement of certain HPT 1st-stage hubs and HPT 2nd-stage
hubs. Certain IAE AG Model V2522-A5, V2524-A5, V2525-D5, V2527-A5,
V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, V2531-E5, and V2533-A5
engines are among the products affected by this condition, which, if
not addressed, could result in hub failure, release of high-energy
debris, damage to the engine, damage to the airplane, and possible 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 IAE AG Non-Modification Service Bulletin (NMSB)
V2500-ENG-72-0720, dated November 20, 2023; and PW Special Instruction
NO. 189F-23, dated November 20, 2023 which only applies to the IAE AG
V2531-E5 Model engine. This service information specifies procedures
for performing an AUSI for cracks on affected HPT 1st-stage hubs and
HPT 2nd-stage hubs. This service information also 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 AG 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 require performing an AUSI of certain HPT
1st-stage hubs and HPT 2nd-stage hubs and, depending on the results of
the inspections, replacing the HPT 1st-stage hubs or HPT 2nd-stage
hubs. This proposed AD would also require accelerated replacement of
certain HPT 1st-stage hubs and HPT 2nd-stage hubs.
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 116 engines installed on airplanes of U.S. registry. The FAA
estimates that 40 engines would need an AUSI of the HPT 1st-stage hub;
40 engines would need an AUSI of the HPT 2nd-stage hub; 67 engines
would need replacement of the HPT 1st-stage hub; and 49 engines would
need replacement of the HPT 2nd-stage hub.
The FAA estimates the following costs to comply with this proposed
AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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AUSI of HPT 1st-stage hub............. 5 work-hours x $85 per $0 $425 $17,000
hour = $425.
AUSI of HPT 2nd-stage hub............. 5 work-hours x $85 per 0 425 17,000
hour = $425.
Replace HPT 1st-stage hub............. 100 work-hours x $85 per 460,000 468,500 31,389,500
hour = $8,500.
Replace HPT 2nd-stage hub............. 100 work-hours x $85 per 360,000 368,500 18,056,500
hour = $8,500.
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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 this 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:
[[Page 7638]]
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:
International Aero Engines, AG: Docket No. FAA-2024-0041; Project
Identifier AD-2024-00032-E.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by March 6, 2024.
(b) Affected ADs
This AD is related to AD 2022-02-09, Amendment 39-21906 (87 FR
7029, February 8, 2022) (AD 2022-02-09).
(c) Applicability
This AD applies to International Aero Engines, AG (IAE AG) Model
V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-
D5, V2530-A5, V2531-E5, and V2533-A5 engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine
Engine.
(e) Unsafe Condition
This AD was prompted by an analysis of an event involving an
International Aero Engines, LLC Model PW1127GA-JM engine, which
experienced failure of a high-pressure compressor 7th-stage
integrally bladed rotor 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 and HPT 2nd-stage hub.
The unsafe 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
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) For engines with an installed part, part number (P/N), and
serial number (S/N) listed in Table 1 to paragraph (g)(1) of this
AD, with no angled ultrasonic inspection (AUSI) performed or the
AUSI inspected part was installed on or after November 1, 2023, at
the next engine shop visit after the effective date of this AD
before exceeding the applicable cycle limit specified in Table 1 to
paragraph (g)(1) of this AD, perform an AUSI of the affected parts
for cracks in accordance with the applicable service information
listed in Table 1 to paragraph (g)(1) of this AD.
Table 1 to Paragraph (g)(1)--AUSI Compliance Times
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Previously operated Cycle limit from Applicable
Part Table S/N is in high-thrust model the effective service
listed in engine date of this AD information
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HPT 1st-stage hub P/N 2A5001... Table 1 of IAE AG Yes.................. 100 flight cycles Accomplishment
Non-Modification (FCs). Instructions,
Service Bulletin paragraph 5., of
V2500-ENG-72-0720 IAE AG NMSB
, dated November V2500-ENG-72-072
20, 2023 (IAE AG 0.
NMSB V2500-ENG-72-
0720).
Table 1 of Pratt & Accomplishment
Whitney (PW) Instructions,
Special paragraph 5., of
Instruction NO. PW SI 189F-23.
189F-23, dated
November 20, 2023
(PW SI 189F-23).
Table 1 of IAE AG No................... 700 FCs.......... Accomplishment
NMSB V2500-ENG-72- Instructions,
0720. paragraph 5., of
IAE AG NMSB
V2500-ENG-72-072
0.
HPT 2nd-stage hub P/N 2A4802... Table 2 of IAE AG Yes.................. 800 FCs.......... Accomplishment
NMSB V2500-ENG-72- Instructions,
0720. paragraph 6., of
IAE AG NMSB
V2500-ENG-72-072
0.
Table 2 PW SI 189F- Accomplishment
23. Instructions,
paragraph 6., of
PW SI 189F-23.
Table 2 of IAE AG No................... 1100 FCs......... Accomplishment
NMSB V2500-ENG-72- Instructions,
0720. paragraph 6., of
IAE AG NMSB
V2500-ENG-72-072
0.
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(2) For parts inspected in accordance with paragraph (g)(1) of
this AD, within 4,000 FCs from accomplishment of the AUSI required
by paragraph (g)(1) of this AD or at the next HPT module removal
after the AUSI required by paragraph (g)(1) of this AD, whichever
occurs first, remove the part from service and replace with a part
eligible for installation.
(3) If any crack is found during the inspections required by
paragraphs (g)(1) of this AD, before further flight, remove the
affected part from service and replace with a part eligible for
installation.
(4) For engines with an AUSI inspected part installed prior to
November 1, 2023, having a P/N and S/N listed in Table 2 to
paragraph (g)(4) of this AD, at the next HPT module removal after
the effective date of this AD, but before exceeding the applicable
cycle limit specified in Table 2 to paragraph (g)(4) of this AD,
remove the affected part from service and replace with a part
eligible for installation.
Table 2 to Paragraph (g)(4)--Part Replacement Compliance Times
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Previously operated
Part Table S/N is listed in in high-thrust model Cycle limit from the
engine effective date of this AD
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HPT 1st-stage hub P/N 2A5001...... Table 1 of IAE AG NMSB Yes.................. 1,800 FCs.
V2500-ENG-72-0720.
Table 1 of PW SI 189F-23..
Table 1 of IAE AG NMSB No................... 2,800 FCs.
V2500-ENG-72-0720.
HPT 2nd-stage hub P/N 2A4802...... Table 2 of IAE AG NMSB Yes.................. 3,400 FCs.
V2500-ENG-72-0720.
Table 2 of PW SI 189F-23..
[[Page 7639]]
Table 2 of IAE AG NMSB No................... 3,800 FCs.
V2500-ENG-72-0720.
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(5) For engines with an installed part that has a P/N and S/N
listed in Table 3 to paragraph (g)(5) of this AD, at the next HPT
module removal after the effective date of this AD, but before
exceeding the applicable cycle limit specified in Table 3 to
paragraph (g)(5) of this AD, remove the affected part from service
and replace with a part eligible for installation.
Table 3 to Paragraph (g)(5)--Part Replacement Compliance Times
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Previously operated
Part Table S/N is listed in in high-thrust model Cycle limit from the
engine effective date of this AD
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HPT 1st-stage hub P/N 2A5001...... Table 3 of IAE AG NMSB Yes.................. 1,800 FCs.
V2500-ENG-72-0720. No................... 2,800 FCs.
Table 3 of IAE AG NMSB
V2500-ENG-72-0720.
HPT 2nd-stage hub P/N 2A4802...... Table 4 of IAE AG NMSB Yes.................. 3,400 FCs.
V2500-ENG-72-0720. No................... 3,800 FCs.
Table 4 of IAE AG NMSB
V2500-ENG-72-0720.
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(h) Definitions
(1) For the purposes of this AD, a ``part eligible for
installation'' is an HPT 1st-stage disk or HPT 2nd-stage disk having
an S/N that is not listed in IAE AG NMSB V2500-ENG-72-0720 or PW SI
189F-23.
(2) For the purposes of this AD, an ``HPT module removal'' is
when the HPT rotor and stator assembly are removed from the engine.
(3) For the purposes of this AD, ``Previously operated in high-
thrust model engine'' refers to HPT 1st-stage hubs or HPT 2nd-stage
hubs that have previously operated in an IAE AG Model V2527E-A5,
V2527M-A5, V2528-D5, V2530-A5, V2531-E5, or V2533-A5 engine for any
duration.
(4) For the purposes of this AD, an ``engine shop visit'' is the
induction of an engine into the shop for maintenance involving the
separation of pairs of major mating engine flanges, H-P, except for
the following situations, which do not constitute an engine shop
visit:
(i) Separation of engine flanges solely for the purposes of
transportation without subsequent engine maintenance.
(ii) Engine removal for the purpose of performing field
maintenance activities at a maintenance facility in lieu of
performing them on-wing.
(5) For the purposes of this AD, the date that an AUSI inspected
part was installed is the date of the authorized release
certification for the shop visit at which the part was first
installed after the AUSI was performed.
(i) Terminating Action to AD 2022-02-09
Compliance with paragraph (g)(1) of this AD satisfies the
requirements of AD 2022-02-09.
(j) 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 (k) 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.
(k) Additional Information
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].
(l) 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.
(i) International Aero Engines AG (IAE AG) Non-Modification
Service Bulletin V2500-ENG-72-0720, dated November 20, 2023.
(ii) Pratt & Whitney (PW) Special Instruction NO. 189F-23, dated
November 20, 2023.
(3) For PW and IAE AG service information identified in this AD,
contact International Aero Engines, AG, 400 Main Street, East
Hartford, CT 06118; phone: (860) 565-0140; email: [email protected];
website: connect.prattwhitney.com.
(4) 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.
(5) 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 January 24, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-02205 Filed 1-31-24; 4:15 pm]
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