Proposed Rule2021-13709
Airworthiness Directives; Pratt & Whitney Turbofan Engines
Primary source
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Published
June 29, 2021
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to adopt a new airworthiness directive (AD) for all Pratt & Whitney PW1500G and PW1900G series turbofan engines with a certain high-pressure turbine (HPT) 1st-stage hub or HPT rotor 1st-stage blade retaining plate installed. This proposed AD was prompted by a report from the manufacturer who determined that the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate fail to meet the published life-cycle limits for each part. This proposed AD would require removal and replacement of the HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate prior to reaching certain cycle limits. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 86 Issue 122 (Tuesday, June 29, 2021)</title>
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[Federal Register Volume 86, Number 122 (Tuesday, June 29, 2021)]
[Proposed Rules]
[Pages 34166-34168]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2021-13709]
[[Page 34166]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0515; Project Identifier AD-2021-00191-E]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney Turbofan 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 all Pratt & Whitney PW1500G and PW1900G series turbofan engines
with a certain high-pressure turbine (HPT) 1st-stage hub or HPT rotor
1st-stage blade retaining plate installed. This proposed AD was
prompted by a report from the manufacturer who determined that the HPT
1st-stage hub and HPT rotor 1st-stage blade retaining plate fail to
meet the published life-cycle limits for each part. This proposed AD
would require removal and replacement of the HPT 1st-stage hub and HPT
rotor 1st-stage blade retaining plate prior to reaching certain cycle
limits. 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 June 29,
2021.
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="https://www.regulations.gov">https://www.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.
For service information identified in this NPRM, contact Pratt &
Whitney, 400 Main Street, East Hartford, CT 06118; phone: (800) 565-
0140; fax: (860) 565-5442; email: <a href="/cdn-cgi/l/email-protection#b9d1dcd5c98b8df9c9ce97cccdda97dad6d4"><span class="__cf_email__" data-cfemail="cba3aea7bbf9ff8bbbbce5bebfa8e5a8a4a6">[email protected]</span></a>; website: <a href="https://fleetcare.pw.utc.com">https://fleetcare.pw.utc.com</a>. 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 (781) 238-7759.
Examining the AD Docket
You may examine the AD docket at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by
searching for and locating Docket No. FAA-2021-0515; 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.
FOR FURTHER INFORMATION CONTACT: Mark Taylor, Aviation Safety Engineer,
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone:
(781) 238-7229; fax: (781) 238-7199; email: <a href="/cdn-cgi/l/email-protection#82cfe3f0e9acd6e3fbeeedf0c2e4e3e3ace5edf4"><span class="__cf_email__" data-cfemail="bff2decdd491ebdec6d3d0cdffd9dede91d8d0c9">[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-2021-0515; Project Identifier
AD-2021-00191-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.
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="https://www.regulations.gov">https://www.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 Mark
Taylor, Aviation Safety Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803. 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 received a report from the manufacturer, who determined
after recalculating life limits using a thermal match model and other
life-calculation methodology updates, the HPT 1st-stage hub and HPT
rotor 1st-stage blade retaining plate failed to meet the published
life-cycle limits for each part. This condition, if not addressed,
could result in the release of the HPT 1st-stage hub or HPT rotor 1st-
stage blade retaining plate, damage to the engine, and damage to the
aircraft.
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
The FAA reviewed Pratt & Whitney Service Bulletin (SB) PW1000G-A-
72-00-0115-00B-930A-D, Issue No. 001, dated April 26, 2021, and Pratt &
Whitney SB PW1000G-A-72-00-0168-00A-930A-D, Issue No. 001, dated April
26, 2021. These SBs describe procedures for removing and replacing the
HPT 1st-stage hub and HPT rotor 1st-stage blade retaining plate.
Proposed AD Requirements in This NPRM
This proposed AD would require removal and replacement of the HPT
1st-stage hub and HPT rotor 1st-stage blade retaining plate prior to
reaching certain cycle limits.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 88 engines installed on airplanes of U.S. registry. The FAA
estimates that in most cases the affected HPT 1st-stage hub and the
affected HPT 1st-stage blade retaining plate will both be replaced
during the same disassembly of the engine. This cost estimate therefore
reflects the cost of replacing both parts during the same engine
disassembly.
The FAA estimates the following costs to comply with this proposed
AD:
[[Page 34167]]
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Replace HPT 1st-stage hub and HPT 300 work-hours x $85 per $86,252 $111,752 $9,834,176
rotor 1st-stage blade retaining plate hour = $25,500.
(pro-rated part cost).
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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-2021-0515; Project Identifier AD-
2021- 00191-E.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by August 13, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Pratt & Whitney PW1519G, PW1521G, PW1521G-3,
PW1521GA, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G,
PW1922G, PW1923G, and PW1923G-A model turbofan engines with a high-
pressure turbine (HPT) 1st-stage hub, part number (P/N) 30G5701, or
an HPT rotor 1st-stage blade retaining plate, P/N 30G1692,
installed.
(d) Subject
Joint Aircraft System Component (JASC) Code 7250, Turbine
Section.
(e) Unsafe Condition
This AD was prompted by a report from the manufacturer who
determined that the HPT 1st-stage hub and HPT rotor 1st-stage blade
retaining plate fail to meet the published life-cycle limits for
each part. The FAA is issuing this AD to prevent failure of the HPT
1st-stage hub or HPT rotor 1st-stage blade retaining plate. The
unsafe condition, if not addressed, could result in the release of
the HPT 1st-stage hub or HPT rotor 1st-stage blade retaining plate,
damage to the engine, and damage to the aircraft.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) For PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, and
PW1524G-3 model turbofan engines:
(i) For an affected HPT 1st-stage hub and an affected HPT rotor
1st-stage blade retaining plate with 3,000 cycles since new (CSN) or
fewer on the effective date of this AD, before the affected part
exceeds 4,700 CSN, remove the affected part, as applicable, and
replace with a part eligible for installation.
(ii) For an affected HPT 1st-stage hub and an affected HPT rotor
1st-stage blade retaining plate with greater than 3,000 CSN but
fewer than 4,960 CSN on the effective date of the AD, at the next
engine shop visit after accumulating 4,700 CSN or before the
affected part exceeds 5,260 CSN, whichever occurs first, remove the
affected part, as applicable, and replace with a part eligible for
installation.
(iii) For an affected HPT 1st-stage hub and an affected HPT
rotor 1st-stage blade retaining plate with 4,960 CSN or greater on
the effective date of the AD, at the next engine shop visit or
within 300 cycles after the effective date of this AD, whichever
occurs first, remove the affected part, as applicable, and replace
with a part eligible for installation.
(2) For PW1919G and PW1921G model turbofan engines:
(i) For an affected HPT 1st-stage hub and an affected HPT rotor
1st-stage blade retaining plate with 3,000 CSN or fewer on the
effective date of this AD, before the affected part exceeds 4,700
CSN, remove the affected part, as applicable, and replace with a
part eligible for installation.
(ii) For an affected HPT 1st-stage hub and an affected HPT rotor
1st-stage blade retaining plate with greater than 3,000 CSN but
fewer than 4,700 CSN on the effective date of the AD, at the next
engine shop visit after the affected part accumulates 4,700 CSN or
before the affected part exceeds 5,000 CSN, whichever occurs first,
remove the affected part, as applicable, and replace with a part
eligible for installation.
(iii) For an affected HPT 1st-stage hub and an affected HPT
rotor 1st-stage blade retaining plate with 4,700 CSN or greater on
the effective date of the AD, at the next engine shop visit or
within 300 cycles after the effective date of this AD, whichever
occurs first, remove the affected part, as applicable, and replace
with a part eligible for installation.
(3) For PW1525G and PW1525G-3 model turbofan engines:
(i) Before the affected HPT 1st-stage hub and affected HPT rotor
1st-stage blade retaining plate exceeds 2,800 CSN, respectively, or
within 300 cycles after the effective date of this AD, whichever
occurs later, remove the affected part, as applicable, and replace
with a part eligible for installation.
(ii) [Reserved]
(4) For PW1922G, PW1923G, and PW1923G-A model turbofan engines:
(i) Before the affected HPT 1st-stage hub and affected HPT rotor
1st-stage blade retaining plate exceeds 3,000 CSN,
[[Page 34168]]
respectively, or within 300 cycles after the effective date of this
AD, whichever occurs later, remove the affected part, as applicable,
and replace with a part eligible for installation.
(ii) [Reserved]
(h) Definition
(1) For the purpose 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 case flanges, except for
the following, which do not constitute an engine shop visit:
(i) Separation of engine flanges solely for the purposes of
transportation without subsequent maintenance does not constitute an
engine shop visit.
(ii) Separation of engine flanges solely for the purpose of
replacing the fan without subsequent maintenance does not constitute
an engine shop visit.
(2) For the purpose of this AD, a ``part eligible for
installation'' is:
(i) For PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, PW1524G-
3, PW1919G, and PW1921G model turbofan engines:
(A) Any HPT 1st-stage hub with P/N 30G5701 with 4,700 CSN or
fewer, or with a P/N not listed in this AD.
(B) Any HPT rotor 1st-stage blade retaining plate with P/N
30G1692 with 4,700 CSN or fewer, or with a P/N not listed in this
AD.
(ii) For PW1525G and PW1525G-3 model turbofan engines:
(A) Any HPT 1st-stage hub with P/N 30G5701 with 2,800 CSN or
fewer, or with a P/N not listed in this AD.
(B) Any HPT rotor 1st-stage blade retaining plate with P/N
30G1692 with 2,800 CSN or fewer, or with a P/N not listed in this
AD.
(iii) For PW1922G, PW1923G, and PW1923G-A model turbofan
engines:
(A) Any HPT 1st-stage hub with P/N 30G5701 with 3,000 CSN or
fewer, or with a P/N not listed in this AD.
(B) Any HPT rotor 1st-stage blade retaining plate with P/N
30G1692 with 3,000 CSN or fewer, or with a P/N not listed in this
AD.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, ECO Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
certification office, send it to the attention of the person
identified in Related Information. You may email your request to:
<a href="/cdn-cgi/l/email-protection#f0b1beb5ddb1b4ddb1bdbfb3b0969191de979f86"><span class="__cf_email__" data-cfemail="54151a117915107915191b17143235357a333b22">[email protected]</span></a>.
(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.
(j) Related Information
(1) For more information about this AD, contact Mark Taylor,
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: (781) 238-7229; fax: (781) 238-7199;
email: <a href="/cdn-cgi/l/email-protection#d499b5a6bffa80b5adb8bba694b2b5b5fab3bba2"><span class="__cf_email__" data-cfemail="c38ea2b1a8ed97a2baafacb183a5a2a2eda4acb5">[email protected]</span></a>.
(2) For service information identified in this AD, contact Pratt
& Whitney, 400 Main Street, East Hartford, CT 06118; phone: (800)
565-0140; fax: (860) 565-5442; email: <a href="/cdn-cgi/l/email-protection#86eee3eaf6b4b2c6f6f1a8f3f2e5a8e5e9eb"><span class="__cf_email__" data-cfemail="f8909d9488caccb8888fd68d8c9bd69b9795">[email protected]</span></a>; website:
<a href="https://fleetcare.pw.utc.com">https://fleetcare.pw.utc.com</a>. You may view this referenced 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
(781) 238-7759.
Issued on June 23, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-13709 Filed 6-28-21; 8:45 am]
BILLING CODE 4910-13-P
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