[Federal Register Volume 89, Number 6 (Tuesday, January 9, 2024)]
[Proposed Rules]
[Pages 1038-1042]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-00309]
========================================================================
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. 6 / Tuesday, January 9, 2024 /
Proposed Rules
[[Page 1038]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-2523; Project Identifier AD-2023-01086-E]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Pratt & Whitney (PW) Model PW1519G, PW1521G, PW1521GA,
PW1521G-3, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G,
PW1922G, PW1923G, and PW1923G-A engines. This proposed AD was prompted
by an updated 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 engine shutdown and aborted takeoff.
This proposed AD would require performing an angled ultrasonic
inspection (AUSI) of certain high-pressure turbine (HPT) 1st-stage
hubs, HPT 2nd-stage hubs, and HPC 8th-stage disks for cracks and,
depending on the results of the inspections, replacing the HPT 1st-
stage hubs, HPT 2nd-stage hubs, or HPC 8th-stage disks. This proposed
AD would also require accelerated replacement of certain HPC 7th-stage
rotors, HPC 8th-stage disks, HPC rear hubs, HPT 1st-stage hubs, HPT
2nd-stage hubs, HPT 1st-stage air seals, HPT 2nd-stage air seals, HPT
1st-stage blade retaining plates, and HPT 2nd-stage blade retaining
plates. 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 February 8,
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-2023-2523; 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 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.
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-2023-2523; Project Identifier
AD-2023-01086-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.
[[Page 1039]]
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. The analysis also concluded
that there is an increased risk of failure for additional nickel
powdered metal parts in certain nickel powdered metal production
campaigns, and these parts are susceptible to failure much earlier than
previously determined. As a result, the FAA is proposing additional
AUSIs for certain affected nickel powdered metal parts and removal from
service of certain affected nickel powdered metal parts. Certain PW
Model PW1519G, PW1521G, PW1521GA, PW1521G-3, PW1524G, PW1524G-3,
PW1525G, PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A
engines are among the products affected by this condition. This
condition, if not addressed, could result in uncontained disk 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 the following service information:
PW Alert Service Bulletin (ASB) PW1000G-A-72-00-0196-00A-
930A-D, Issue No: 002, dated November 30, 2023, and PW ASB PW1000G-A-
72-00-0141-00B-930A-D, Issue No: 002, dated November 30, 2023. This
service information specifies a list of affected HPT 1st-stage hubs and
HPT 2nd-stage hubs that are identified by serial number (S/N) and
installed on certain PW engines; and instructions for performing an
AUSI on affected HPT 1st-stage hubs and HPT 2nd-stage hubs.
PW ASB PW1000G-A-72-00-0197-00A-930A-D, Issue No: 004,
dated November 30, 2023, and PW ASB PW1000G-A-72-00-0142-00B-930A-D,
Issue No: 004, dated November 30, 2023. This service information
specifies a list of affected HPC 8th-stage disks that are identified by
S/N and installed on certain PW engines; and instructions for
performing an AUSI on affected HPC 8th-stage disks.
PW ASB PW1000G-A-72-00-0204-00A-930A-D Issue No: 001,
dated November 30, 2023, and PW ASB PW1000G-A-72-00-0150-00B-930A-D
Issue No: 001, dated November 30, 2023, which specifies procedures for
performing repetitive AUSIs on affected HPC 8th-stage disks.
PW ASB PW1000G-A-72-00-0205-00A-930A-D, Issue No: 001,
dated November 30, 2023, and PW ASB PW1000G-A-72-00-0151-00B-930A-D,
Issue No: 001, dated November 30, 2023, which specify procedures for
performing repetitive AUSIs on affected HPT 1st-stage hubs and HPT 2nd-
stage hubs.
PW Special Instruction No. 240F-23, dated November 30,
2023, which specifies a list of affected HPT 1st-stage hubs and HPT
2nd-stage hubs that are identified by S/N and installed on certain PW
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, HPT 2nd-stage hubs, and HPC 8th-stage disks for cracks
and, depending on the results of the inspections, replacing the HPT
1st-stage hubs, HPT 2nd-stage hubs, or HPC 8th-stage disks. This
proposed AD would also require accelerated replacement of certain HPC
7th-stage rotors, HPC 8th-stage disks, HPC rear hubs, HPT 1st-stage air
seals, HPT 2nd-stage air seals, HPT 1st-stage hubs, HPT 2nd-stage hubs,
HPT 1st-stage blade retaining plates, and HPT 2nd-stage blade retaining
plates.
Interim Action
The FAA considers this AD to be an interim action. This 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 160 engines would need the AUSI of the HPT 1st-stage
hub, HPT 2nd-stage hub, and HPC 8th-stage disk; 218 engines would need
replacement of the HPT 1st-stage hub; 226 engines would need
replacement of the HPT 2nd-stage hub; 231 engines would need
replacement of the HPC 7th-stage rotor; 231 engines would need
replacement of the HPC 8th-stage disk; 231 engines would need
replacement of the HPC rear hub; 231 engines would need replacement of
the HPT 1st-stage air seal; 233 engines would need replacement of the
HPT 2nd-stage air seal; 232 engines would need replacement of the HPT
1st-stage blade retaining plate; and 231 engines would need replacement
of the HPT 2nd-stage blade retaining plate.
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
----------------------------------------------------------------------------------------------------------------
Perform AUSI of HPT 1st-stage hub, HPT 60 work-hours x $85 per $0 $5,100 $816,000
2nd-stage hub, and HPC 8th-stage disk. hour = $5,100.
Replace HPT 1st-stage hub............... 10 work-hours x $85 per 49,500 50,350 10,976,300
hour = $850.
Replace HPT 2nd-stage hub............... 10 work-hours x $85 per 25,500 26,350 5,955,100
hour = $850.
Replace HPC 7th-stage rotor............. 10 work-hours x $85 per 48,000 48,850 11,284,350
hour = $850.
Replace HPC 8th-stage disk.............. 10 work-hours x $85 per 35,500 36,350 8,396,850
hour = $850.
Replace HPC rear hub.................... 10 work-hours x $85 per 83,000 83,850 19,369,350
hour = $850.
Replace HPT 1st-stage air seal.......... 10 work-hours x $85 per 21,000 21,850 5,047,350
hour = $850.
Replace HPT 2nd-stage air seal.......... 10 work-hours x $85 per 36,000 36,850 8,586,050
hour = $850.
Replace HPT 1st-stage blade retaining 10 work-hours x $85 per 34,000 34,850 8,085,200
plate. hour = $850.
[[Page 1040]]
Replace HPT 2nd-stage blade retaining 10 work-hours x $85 per 13,000 13,850 3,199,350
plate. hour = $850.
----------------------------------------------------------------------------------------------------------------
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:
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:
Pratt & Whitney: Docket No. FAA-2023-2523; Project Identifier AD-
2023-01086-E.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by February 8, 2024.
(b) Affected ADs
None.
(c) Applicability
Pratt & Whitney (PW) Model PW1519G, PW1521G, PW1521GA, PW1521G-
3, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G,
PW1922G, PW1923G, and PW1923G-A 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 updated analysis of an event
involving an International Aero Engines, LLC Model PW1127GA-JM
engine, which experienced a high-pressure compressor (HPC) 7th-stage
integrally bladed rotor separation 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, and HPC 8th-stage disk. 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
possible loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) For PW1500G engines with an installed HPC 8th-stage disk
having part number (P/N) 30G7208, at the next HPC engine shop visit,
except as required by paragraph (g)(3) of this AD, perform an angled
ultrasonic inspection (AUSI) of the affected HPC 8th-stage disk for
cracks in accordance with the Accomplishment Instructions, paragraph
8., of PW Alert Service Bulletin (ASB) PW1000G-A-72-00-0197-00A-
930A-D, Issue No: 004, dated November 30, 2023.
(2) For PW1500G engines with an installed HPT 1st-stage hub
having P/N 30G8501 or an installed HPT 2nd-stage hub having P/N
30G7202, at the next engine shop visit, except as required by
paragraph (g)(3) 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 8.A. or
8.B., of PW ASB PW1000G-A-72-00-0196-00A-930A-D, Issue No: 002,
dated November 30, 2023.
(3) For PW1500G engines with an installed part, P/N and serial
number (S/N) listed in Table 1 to paragraph (g)(3) of this AD with
no AUSI performed prior to the effective date of this AD, within the
applicable compliance time listed in Table 1 to paragraph (g)(3) of
this AD or within 100 flight cycles (FCs) after the effective date
of this AD, whichever occurs later, perform an AUSI of the affected
part for cracks in accordance with the applicable service bulletin
listed in Table 1 to paragraph (g)(3) of this AD.
Table 1 to Paragraph (g)(3)--AUSI Compliance Times
----------------------------------------------------------------------------------------------------------------
Applicable service
Part Applicable S/N listing Compliance time bulletin (see paragraph
(m)(2) of this AD)
----------------------------------------------------------------------------------------------------------------
HPC 8th-stage disk................... Table 1 of PW ASB Next HPC engine shop Accomplishment
P/N 30G7208.......................... PW1000G-A-72-00-0197-0 visit not to exceed Instructions,
0A-930A-D. 10,000 part cycles paragraph 8., of PW
since new (CSN). ASB PW1000G-A-72-00-
0197-00A-930A-D.
HPT 1st-stage hub.................... Table 2 of PW ASB Next engine shop visit Accomplishment
P/N 30G8501.......................... PW1000G-A-72-00-0196-0 not to exceed 5,000 Instructions,
0A-930A-D. part CSN. paragraph 8.A. of PW
ASB PW1000G-A-72-00-
0196-00A-930A-D
[[Page 1041]]
HPT 2nd-stage hub.................... Table 3 of PW ASB Next engine shop visit Accomplishment
P/N 30G7202.......................... PW1000G-A-72-00-0196-0 not to exceed 5,000 Instructions,
0A-930A-D. part CSN. paragraph 8.B, of PW
ASB PW1000G-A-72-00-
0196-00A-930A-D.
HPT 1st-stage hub.................... Table 4 of PW ASB Next engine shop visit Accomplishment
P/N 30G8501.......................... PW1000G-A-72-00-0196-0 not to exceed 4,000 Instructions,
0A-930A-D. part CSN. paragraph 8.A, of PW
ASB PW1000G-A-72-00-
0196-00A-930A-D.
HPT 2nd-stage hub.................... Table 5 of PW ASB Next engine shop visit Accomplishment
P/N 30G7202.......................... PW1000G-A-72-00-0196-0 not to exceed 4,000 Instructions,
0A-930A-D. part CSN. paragraph 8.B., of PW
ASB PW1000G-A-72-00-
0196-00A-930A-D.
----------------------------------------------------------------------------------------------------------------
(4) Thereafter at each piece-part exposure of the affected part
for PW1500G engines with an installed HPC 8th-stage disk having P/N
30G7208, an installed HPT 1st-stage hub having P/N 30G8501, or an
installed HPT 2nd-stage hub having P/N 30G7202, do the following:
(i) Perform an AUSI of the affected HPC 8th-stage disk for
cracks in accordance with the Accomplishment Instructions, paragraph
5.B., PW ASB PW1000G-A-72-00-0204-00A-930A-D, Issue No: 001, dated
November 30, 2023.
(ii) Perform an AUSI of the affected HPT 1st-stage hub and HPT
2nd-stage hub, as applicable, for cracks in accordance with the
Accomplishment Instructions, paragraph 7.A. or 7.B., of PW ASB
PW1000G-A-72-00-0205-00A-930A-D, Issue No: 001, dated November 30,
2023.
(5) For PW1900G engines with an installed HPC 8th-stage disk
having P/N 30G7208, at the next HPC engine shop visit, except as
required by paragraph (g)(7) of this AD, perform an AUSI of the
affected HPC 8th-stage disk for cracks in accordance with the
Accomplishment Instructions, paragraph 8., of Pratt & Whitney PW ASB
PW1000G-A-72-00-0142-00B-930A-D, Issue No: 004, dated November 30,
2023.
(6) For PW1900G engines with an installed HPT 1st-stage hub
having P/N 30G8501 or an installed HPT 2nd-stage hub having P/N
30G7202, at the next engine shop visit, except as required by
paragraph (g)(7) of this AD, perform an AUSI of the affected HPT
1st-stage hub and HPT 2nd-stage hub, as applicable, for cracks in
accordance with the Accomplishment Instructions, paragraph 8.A. or
8.B., of PW ASB PW1000G-A-72-00-0141-00B-930A-D, Issue No: 002,
dated November 30, 2023.
(7) For PW1900G engines with an installed part, P/N and S/N
listed in Table 2 to paragraph (g)(7) of this AD, with no AUSI
performed prior to the effective date of this AD, within the
compliance time listed in Table 2 to paragraph (g)(7) of this AD or
within 100 FCs after the effective date of this AD, whichever occurs
later, perform an AUSI of the affected parts for cracks in
accordance with the applicable service bulletin listed in Table 2 to
paragraph (g)(7) of this AD.
Table 2 to Paragraph (g)(7)--AUSI Compliance Times
----------------------------------------------------------------------------------------------------------------
Applicable service
Part Table S/N is listed in Compliance time bulletin (see paragraph
(m)(2) of this AD)
----------------------------------------------------------------------------------------------------------------
HPC 8th-stage disk having P/N 30G7208 Table 1 of PW ASB Next HPC engine shop Accomplishment
PW1000G-A-72-00-0142-0 visit not to exceed Instructions,
0B-930A-D. 10,000 part CSN. paragraph 8., of PW
ASB PW1000G-A-72-00-
0142-00B-930A-D.
HPT 1st-stage hub having P/N 30G8501. Table 2 of PW ASB Next engine shop visit Accomplishment
PW1000G-A-72-00-0141-0 not to exceed 5,000 Instructions,
0B-930A-D. part CSN. paragraph 8.A., of PW
ASB PW1000G-A-72-00-
0141-00B-930A-D.
HPT 2nd-stage hub having P/N 30G7202. Table 3 of PW ASB Next engine shop visit Accomplishment
PW1000G-A-72-00-0141-0 not to exceed 5,000 Instructions,
0B-930A-D. part CSN. paragraph 8.B, of PW
ASB PW1000G-A-72-00-
0141-00B-930A-D.
HPT 1st-stage hub having P/N 30G8501. Table 4 of PW ASB Next engine shop visit Accomplishment
PW1000G-A-72-00-0141-0 not to exceed 4,000 Instructions,
0B-930A-D. part CSN. paragraph 8.A., of PW
ASB PW1000G-A-72-00-
0141-00B-930A-D.
HPT 2nd-stage hub having P/N 30G7202. Table 5 of PW ASB Next engine shop visit Accomplishment
PW1000G-A-72-00-0141-0 not to exceed 4,000 Instructions,
0B-930A-D. part CSN. paragraph 8.B., of PW
ASB PW1000G-A-72-00-
0141-00B-930A-D.
----------------------------------------------------------------------------------------------------------------
(8) Thereafter at each piece-part exposure of the affected part
for PW1900G engines with an installed HPC 8th-stage disk having P/N
30G7208, or an installed HPT 1st-stage hub having P/N 30G8501, or an
installed HPT 2nd-stage hub having P/N 30G7202, do the following:
(i) Perform an AUSI of the affected HPC 8th-stage disk for
cracks in accordance with the Accomplishment Instructions, paragraph
5.B., of PW ASB PW1000G-A-72-00-0150-00B-930A-D, Issue No: 001,
dated November 30, 2023.
(ii) Perform an AUSI of the affected HPT 1st-stage hub and HPT
2nd-stage hub, as applicable, for cracks in accordance with the
Accomplishment Instructions, paragraph 7.A. or 7.B., of PW ASB
PW1000G-A-72-00-0151-00B-930A-D, Issue No: 001, dated November 30,
2023.
(9) If any crack is found during the inspections required by
paragraph (g) of this AD, before further flight, remove the affected
part from service and replace with a part eligible for installation.
(10) For engines with an installed part and P/N listed in Table
3 to paragraph (g)(10) of this AD having 3,300 CSN or less on the
effective date of this AD, before the part accumulates 4,000 CSN or
at the next engine shop visit after the effective date of this AD,
whichever occurs first, remove the part from service and replace
with a part eligible for installation.
Table 3 to Paragraph (g)(10)--Part Numbers
------------------------------------------------------------------------
Part name P/N
------------------------------------------------------------------------
HPC 7th-stage rotor.......................................... 30G3307
HPC 8th-stage disk........................................... 30G3248
HPC rear hub................................................. 30G2902
HPT 1st-stage hub............................................ 30G5701
HPT 2nd-stage hub............................................ 30G5002
HPT 1st-stage air seal....................................... 30G3132
HPT 2nd-stage air seal....................................... 30G3451
HPT 1st-stage blade retaining plate.......................... 30G1692
HPT 2nd-stage blade retaining plate.......................... 30G1698
------------------------------------------------------------------------
(11) For engines with an installed part and P/N listed in Table
3 to paragraph (g)(10) of this AD having more than 3,300 CSN on the
effective date of this AD, at the next engine shop visit or within
700 FCs after the effective date of this AD, whichever occurs first,
remove the part from service and replace it with a part eligible for
installation.
(12) For engines with an installed HPT 1st-stage hub having P/N
30G8501 or an installed HPT 2nd-stage hub having P/N 30G7202 and an
S/N listed in Table 1 of PW Special Instruction (SI) No. 240F-23,
dated November 30, 2023, within 100 FCs from the effective date of
this AD, remove the hub from service and replace it with a part
eligible for installation.
(13) 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.
(h) Installation Prohibition
After the effective date of this AD, do not install an HPT 1st-
stage hub having P/N 30G8501 or an HPT 2nd-stage hub having P/N
30G7202 and an S/N listed in Table 1 of PW SI No. 240F-23, dated
November 30, 2023, in any engine.
(i) Definitions
(1) For the purposes of this AD, ``PW1500G'' engines are PW
Model PW1519G, PW1521G, PW1521GA, PW1521G-3, PW1524G, PW1524G-3,
PW1525G, and PW1525G-3 engines.
[[Page 1042]]
(2) For the purposes of this AD, ``PW1900G'' engines are PW
Model PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A engines.
(3) For the purposes of this AD, a ``part eligible for
installation'' is:
(i) Any HPC 7th-stage rotor, P/N 30G5307 or later approved P/N.
(ii) Any HPC 8th-stage disk, P/N 30G7208, that has passed the
AUSI required by paragraph (g) of this AD or later approved P/N.
(iii) Any HPC rear hub, P/N 30G7308 or later approved P/N.
(iv) Any HPT 1st-stage hub, P/N 30G8501, that has passed the
AUSI required by paragraph (g) of this AD or later approved P/N.
(v) Any HPT 2nd-stage hub, P/N 30G7202, that has passed the AUSI
required by paragraph (g) of this AD or later approved P/N.
(vi) Any HPT 1st-stage air seal, P/N 30G5195 or later approved
P/N.
(vii) Any HPT 2nd-stage air seal, P/N 30G5196 or later approved
P/N.
(viii) Any HPT 1st-stage blade retaining plate, P/N 30G5193 or
later approved P/N.
(ix) Any HPT 2nd-stage blade retaining plate, P/N 30G5194 or
later approved P/N.
(4) For the purposes of this AD, a ``piece-part exposure'' is
when the part is disassembled from the rotor assembly.
(5) 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, except for the
following situations, which do not constitute an engine shop visit.
(i) The separation of engine flanges solely for the purposes of
transportation without subsequent engine maintenance.
(ii) Fan case maintenance or replacement.
(6) For the purposes of this AD, an ``HPC engine shop visit'' is
when the HPC rotor assembly is removed from the engine.
(j) Credit for Previous Actions
This paragraph provides credit for the initial AUSI of the HPC
8th-stage disk, HPT 1st-stage hub and HPT 2nd-stage hub specified in
paragraph (g)(1), (2), (4) and (5) of this AD, if the initial AUSI
was performed before the effective date of this AD using the
following service information;
(1) PW ASB PW1000G-A-72-00-0196-00A-930A-D, Issue No: 001, dated
March 16, 2023; or
(2) PW ASB PW1000G-A-72-00-0197-00A-930A-D, Issue No: 001, dated
March 22, 2023; or
(3) PW ASB PW1000G-A-72-00-0197-00A-930A-D, Issue No: 002, dated
June 19, 2023; or
(4) PW ASB PW1000G-A-72-00-0197-00A-930A-D, Issue No: 003, dated
August 14, 2023; or
(5) PW ASB PW1000G-A-72-00-0141-00B-930A-D, Issue No: 001, dated
March 16, 2023; or
(6) PW ASB PW1000G-A-72-00-0142-00B-930A-D, Issue No: 001, dated
March 22, 2023; or
(7) PW ASB PW1000G-A-72-00-0142-00B-930A-D, Issue No: 002, dated
June 19, 2023.; or
(8) PW ASB PW1000G-A-72-00-0142-00B-930A-D, Issue No: 003, dated
August 14, 2023.
(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 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)(3) and (4) 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.
(i) Pratt & Whitney (PW) Alert Service Bulletin (ASB) PW1000G-A-
72-00-0141-00B-930A-D, Issue No: 002, dated November 30, 2023.
(ii) PW ASB PW1000G-A-72-00-0142-00B-930A-D, Issue No: 004,
dated November 30, 2023.
(iii) PW ASB PW1000G-A-72-00-0150-00B-930A-D Issue No:001, dated
November 30, 2023.
(iv) PW ASB PW1000G-A-72-00-0151-00B-930A-D, Issue No: 001,
dated November 30, 2023.
(v) PW ASB PW1000G-A-72-00-0196-00A-930A-D, Issue No: 002, dated
November 30, 2023.
(vi) PW ASB PW1000G-A-72-00-0197-00A-930A-D, Issue No: 004,
dated November 30, 2023.
(vii) PW ASB PW1000G-A-72-00-0204-00A-930A-D Issue No:001, dated
November 30, 2023.
(viii) PW ASB PW1000G-A-72-00-0205-00A-930A-D, Issue No: 001,
dated November 30, 2023.
(ix) PW Special Instruction No. 240F-23, dated November 30,
2023.
(3) 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.
(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 December 27, 2023.
Caitlin Locke,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2024-00309 Filed 1-5-24; 4:15 pm]
BILLING CODE 4910-13-P