[Federal Register Volume 84, Number 105 (Friday, May 31, 2019)]
[Proposed Rules]
[Pages 25203-25205]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-11285]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0365; Product Identifier 2019-NE-12-AD]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
[[Page 25204]]
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 (PW) PW1519G, PW1521G, PW1521GA, PW1524G,
PW1525G, PW1521G-3, PW1524G-3, PW1525G-3, PW1919G, PW1921G, PW1922G,
PW1923G, and PW1923G-A model turbofan engines. This proposed AD was
prompted by corrosion found on the high-pressure compressor (HPC) front
hub, which could result in certain HPC front hubs cracking before
reaching their published life limit. This proposed AD would require
revisions to the Airworthiness Limitations Section (ALS) of the
manufacturer's Instructions for Continued Airworthiness (ICA) and air
carrier's approved Continued Airworthiness Maintenance Programs (CAMP)
to incorporate new or more restrictive airworthiness limitations. 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 July 15,
2019.
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 http://www.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.
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: [email protected]; internet: http://fleetcare.pw.utc.com. You may view this service information at the FAA,
Engine and Propeller Standards 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 on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0365; 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, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations is listed above.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Kevin M. Clark, Aerospace Engineer,
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone:
781-238-7088; fax: 781-238-7199; 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 the ADDRESSES section. Include ``Docket No. FAA-2019-0365;
Product Identifier 2019-NE-12-AD'' at the beginning of your comments.
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this NPRM. The FAA will
consider all comments received by the closing date and may amend this
NPRM because of those comments.
The FAA will post all comments received, without change, to http://www.regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact received about this NPRM.
Discussion
The FAA was notified that corrosion was found on an HPC front hub
during a routine engine overhaul. This corrosion, also found beneath
the anti-corrosion coating, reduces the low-cycle fatigue capability
and can occur even during engine downtime. As a result, PW decreased
the certified life of the affected HPC front hub. This condition, if
not addressed, could result in uncontained HPC front hub release,
damage to the engine, and damage to the airplane.
Related Service Information Under 1 CFR Part 51
The FAA reviewed PW Service Bulletin (SB) PW1000G-A-72-00-0109-00A-
930A-D, Issue No. 001, dated April 2, 2019 (``PW SB PW1000G-A-72-00-
0109-00A-930A-D''), and PW SB PW1000G-A-72-00-0058-00B-930A-D, Issue
No. 002, dated May 10, 2019 (``PW SB PW1000G-A-72-00-0058-00B-930A-
D''). PW SB PW1000G-A-72-00-0109-00A-930A-D describes the revised
maximum cycle limits of the HPC front hub for PW PW1500G engines. PW SB
PW1000G-A-72-00-0058-00B-930A-D describes the revised maximum cycle
limits of the HPC front hub for PW PW1900 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 the ADDRESSES section.
FAA's Determination
The FAA is proposing this AD because it evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require revisions to the ALS of the
manufacturer's ICA and air carrier's approved CAMP to incorporate
revised airworthiness limitations.
Costs of Compliance
The FAA estimates that this proposed AD affects 18 engines
installed on airplanes of U.S. registry.
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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Revise the ALS and CAMP............... 1 work-hour x $85 per $0 $85 $1,530
hour = $85.
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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
[[Page 25205]]
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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to engines, propellers, and
associated appliances to the Manager, Engine and Propeller Standards
Branch, Policy and Innovation Division.
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) Will not affect intrastate aviation in Alaska, and
(3) Will 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 (AD):
Pratt & Whitney: Docket No. FAA-2019-0365; Product Identifier 2019-
NE-12-AD.
(a) Comments Due Date
The FAA must receive comments by July 15, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Pratt & Whitney (PW) PW1519G, PW1521G,
PW1521GA, PW1524G, PW1525G, PW1521G-3, PW1524G-3, PW1525G-3,
PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A model turbofan
engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section.
(e) Unsafe Condition
This AD was prompted by corrosion found on the high-pressure
compressor (HPC) front hub, which could result in certain HPC front
hubs cracking before reaching their published life limit. The FAA is
issuing this AD to prevent failure of the HPC front hub. The unsafe
condition, if not addressed, could result in uncontained HPC front
hub release, damage to the engine, and damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Action
Within 90 days after the effective date of this AD, revise the
Airworthiness Limitations Section of the PW Instructions for
Continued Airworthiness, and for air carrier operations, the
approved continuous airworthiness maintenance program, with the
following maximum cycle limits for HPC front hub, part number
30G3210.
(1) For PW PW1519G, PW1521G, PW1521GA, PW1524G, PW1525G,
PW1521G-3, PW1524G-3, and PW1525G-3 model turbofan engines, use the
cycle limits established in Table 3, Revision to Table of Limits, of
PW Service Bulletin (SB) PW1000G-A-72-00-0109-00A-930A-D, Issue No.
001, dated April 2, 2019.
(2) For PW PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A
model turbofan engines, use the cycle limits established in Table 3,
Revision to Table of Limits, of PW SB PW1000G-A-72-00-0058-00B-930A-
D, Issue No. 002, dated May 10, 2019.
(h) 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 paragraph (i)(1) of this AD. You may email your
request to: [email protected].
(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.
(i) Related Information
(1) For more information about this AD, contact Kevin M. Clark,
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: 781-238-7088; fax: 781-238-7199; email:
[email protected].
(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: [email protected]; internet: http://fleetcare.pw.utc.com. You may view this referenced service
information at the FAA, Engine and Propeller Standards Branch, 1200
District Avenue, Burlington, MA 01803. For information on the
availability of this material at the FAA, call 781-238-7759.
Issued in Burlington, Massachusetts, on May 24, 2019.
Karen M. Grant,
Acting Manager, Engine & Propeller Standards Branch, Aircraft
Certification Service.
[FR Doc. 2019-11285 Filed 5-30-19; 8:45 am]
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