Proposed Rule2023-28693
Airworthiness Directives; International Aero Engines, LLC Engines
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
December 28, 2023
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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 those 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.
Full Text
<html>
<head>
<title>Federal Register, Volume 88 Issue 248 (Thursday, December 28, 2023)</title>
</head>
<body><pre>
[Federal Register Volume 88, Number 248 (Thursday, December 28, 2023)]
[Proposed Rules]
[Pages 89627-89632]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2023-28693]
========================================================================
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. 88, No. 248 / Thursday, December 28, 2023 /
Proposed Rules
[[Page 89627]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-2401; Project Identifier AD-2023-01278-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 those 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 17,
2024.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> 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.
<bullet> 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 <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2023-2401; 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:
<bullet> For Pratt & 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:
<a href="/cdn-cgi/l/email-protection#375f525b470503774740194243541954585a"><span class="__cf_email__" data-cfemail="2149444d5113156151560f5455420f424e4c">[email protected]</span></a>; website: <a href="http://connect.prattwhitney.com">connect.prattwhitney.com</a>.
<bullet> 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: <a href="/cdn-cgi/l/email-protection#026163706d6e2c6c65777b676c426463632c656d74"><span class="__cf_email__" data-cfemail="77141605181b591910020e12193711161659101801">[email protected]</span></a>.
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-2023-2401; Project Identifier
AD-2023-01278-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.
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
<a href="http://regulations.gov">regulations.gov</a>, 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),
[[Page 89628]]
for certain IAE LLC Model PW1122G-JM, PW1124G1-JM, PW1124G-JM,
PW1127G1-JM, PW1127GA-JM, PW1127G-JM, PW1129G-JM, PW1130G-JM, PW1133GA-
JM, and 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 agency 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.
Previous NPRM
To address the unsafe condition, the FAA issued an NPRM (Docket No.
FAA-2023-2237; Project Identifier AD-2023-01057-E) to supersede AD
2022-19-15 and AD 2023-16-07, which was published in the Federal
Register on December 12, 2023 (88 FR 86088). However, since that NPRM
was issued, the FAA has received information from PW that an error was
inadvertently included in the NPRM compliance times for some of the HPT
1st-stage and 2nd-stage hubs, which would have required removal
significantly later than necessary. Because the removal timeframe
needed to be shortened, the FAA determined it is necessary to withdraw
the NPRM and issue a new NPRM for the unsafe condition with the correct
compliance times.
The FAA received comments on the previous NPRM (Docket No. FAA-
2023-2237; Project Identifier AD-2023-01057-E), which will be copied to
Docket No. FAA-2023-2401 and addressed in the final rule.
Since the requirements in this proposed AD are similar to those
proposed in the withdrawn NPRM, and because the comment period on the
withdrawn NPRM was 30 days, we have good cause to make the comment
period for this proposed AD 20 days.
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:
<bullet> 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;
<bullet> 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;
<bullet> 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.
<bullet> 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;
<bullet> 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
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, however, 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
[[Page 89629]]
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 would need replacement of the HPT 1st-stage
hub; 351 engines would need replacement of the HPT 2nd-stage hub; 408
engines would need replacement of the HPC IBR-7; 368 engines would need
replacement of the HPC IBR-8; 283 engines would need replacement of the
HPC rear hub; and 206 engines would 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:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts cost
Action Labor cost (average pro- Cost per Cost on U.S.
rated cost) product operators
----------------------------------------------------------------------------------------------------------------
AUSI of HPT 1st-stage hub, HPT 2nd- 80 work-hours x $85 per $0 $6,800 $2,924,000
stage hub, HPC IBR-7, and HPC IBR-8 hour = $6,800.
for cracks.
Replace HPT 1st-stage hub............ 10 work-hours x $85 per 56,000 56,850 20,807,100
hour = $850.
Replace HPT 2nd-stage hub............ 10 work-hours x $85 per 62,000 62,850 22,060,350
hour = $850.
Replace HPC IBR-7.................... 10 work-hours x $85 per 82,000 82,850 33,802,800
hour = $850.
Replace HPC IBR-8.................... 10 work-hours x $85 per 93,000 93,850 34,536,800
hour = $850.
Replace HPC rear hub................. 10 work-hours x $85 per 132,000 132,850 37,596,550
hour = $850.
Replace HPT 1st-stage air seal, HPT 20 work-hours x $85 per 35,000 36,700 7,560,200
1st-stage blade retaining plate, HPT hour = $1,700.
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 64156, October 24, 2022; corrected October 24, 20 (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-2023-2401; Project
Identifier AD-2023-01278-E.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by January 17, 2024.
(b) Affected ADs
(1) This AD replaces AD 2022-19-15, Amendment 39-22184 (87 FR
64156, October 24, 2022; corrected October 24, 20 (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.
[[Page 89630]]
(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 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 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 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 Pratt & Whitney (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)(6) 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, at the next HPT
engine shop visit not to exceed the applicable cyclic limit
specified in Table 2 to paragraph (h)(3) of this AD, or 100 FCs
after the effective date of the AD, whichever occurs later, except
as required by paragraphs (h)(5) and (7) 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
----------------------------------------------------------------------------------------------------------------
AUSI performed prior
Engine group to effective date of Part name Part number Cyclic limit
this AD
----------------------------------------------------------------------------------------------------------------
1.................. Yes................. HPT 1st-stage hub... 30G4201 or 30G6201.. 3,800 FCs since last
AUSI.
No.................. HPT 1st-stage hub... 30G4201 or 30G6201.. 3,800 CSN.
Yes................. HPT 2nd-stage hub... 30G3902 or 30G5502.. 3,800 FCs since last AUSI
or 7,000 CSN whichever
comes first.
No.................. HPT 2nd-stage hub... 30G3902 or 30G5502.. 3,800 CSN.
2.................. Yes................. HPT 1st-stage hub... 30G4201 or 30G6201.. 2,800 FCs since last
AUSI.
No.................. HPT 1st-stage hub... 30G4201 or 30G6201.. 2,800 CSN.
Yes................. HPT 2nd-stage hub... 30G3902 or 30G5502.. 2,800 FCs since last AUSI
or 5,000 CSN whichever
comes first.
No.................. HPT 2nd-stage hub... 30G3902 or 30G5502.. 2,800 CSN.
----------------------------------------------------------------------------------------------------------------
[[Page 89631]]
(4) For Group 1 and Group 2 engines with an installed part
listed in Table 3 to paragraph (h)(4) of this AD, before exceeding
the applicable compliance times specified in Table 3 to paragraph
(h)(4) of this AD, remove the affected part from service and replace
with a part eligible for installation.
Table 3 to Paragraph (h)(4)--Part Replacement Compliance Times
----------------------------------------------------------------------------------------------------------------
Engine group Part name Part number 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 front air 30G3994 or 30G4674..... At the next HPT engine shop visit.
seal.
HPT 2nd-stage rear air 30G2452................
seal.
HPT 1st-stage blade 30G2446................
retaining plate.
HPT 2nd-stage blade 30G2447................
retaining plate.
1.................... HPC rear hub............ 30G8208................ Before accumulating 7,000 CSN or
within 100 FCs after the effective
date of this AD, whichever occurs
later.
HPC IBR-7............... 30G2307 or 30G4407.....
HPC IBR-8............... 30G5608 or 30G5908 or
30G8908.
HPT 1st-stage hub....... 30G7301................
HPT 2nd-stage hub....... 30G6602................
2.................... HPC rear hub............ 30G8208................ Before accumulating 5,000 CSN or
within 100 FCs after the effective
date of this AD, whichever occurs
later.
HPC IBR-7............... 30G2307 or 30G4407.....
HPC IBR-8............... 30G5608 or 30G5908 or
30G8908.
HPT 1st-stage hub....... 30G7301................
HPT 2nd-stage hub....... 30G6602................
----------------------------------------------------------------------------------------------------------------
(5) 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
this AD, before further flight, remove the affected hub from
service.
(6) 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.
(7) 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.
(8) 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.
(9) 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
[[Page 89632]]
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: <a href="/cdn-cgi/l/email-protection#8deeecffe2e1a3e3eaf8f4e8e3cdebececa3eae2fb"><span class="__cf_email__" data-cfemail="ec8f8d9e8380c2828b99958982ac8a8d8dc28b839a">[email protected]</span></a>.
(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: <a href="/cdn-cgi/l/email-protection#f29a979e82c0c6b28285dc878691dc919d9f"><span class="__cf_email__" data-cfemail="046c61687436304474732a7170672a676b69">[email protected]</span></a>; website:
<a href="http://connect.prattwhitney.com">connect.prattwhitney.com</a>.
(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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email: <a href="/cdn-cgi/l/email-protection#85e3f7abecebf6f5e0e6f1eceaebc5ebe4f7e4abe2eaf3"><span class="__cf_email__" data-cfemail="fd9b8fd394938e8d989e89949293bd939c8f9cd39a928b">[email protected]</span></a>.
Issued on December 21, 2023.
Caitlin Locke,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2023-28693 Filed 12-22-23; 4:15 pm]
BILLING CODE 4910-13-P
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on December 28, 2023.
This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.