Airworthiness Directives; Pratt & Whitney Division Turbofan Engines, 32500-32502 [2014-13024]
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32500
Proposed Rules
Federal Register
Vol. 79, No. 108
Thursday, June 5, 2014
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0072; Directorate
Identifier 2013–NE–04–AD]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney Division Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
airworthiness directive (AD) 2013–15–
09, which applies to all Pratt & Whitney
Division (PW) PW4074, PW4074D,
PW4077, PW4077D, PW4084D,
PW4090, and PW4090–3 turbofan
engine models with certain second-stage
high-pressure turbine (HPT) air seals,
installed. AD 2013–15–09 currently
requires initial and repetitive
inspections for cracks in second-stage
HPT air seals. Since we issued AD
2013–15–09, we received reports of
cracking in the original location on two
additional part numbers (P/Ns) as well
as reports of through-cracks in a new
location in the second-stage HPT air
seal. PW has developed a redesigned
second-stage HPT air seal that addresses
the cracking condition in both locations.
This proposed AD would expand the
applicability of AD 2013–15–09 to
include additional P/Ns, require
replacement of the mating hardware if
the second-stage HPT air seal is found
with a through-crack, and add
mandatory terminating action to the
repetitive inspections. We are proposing
this AD to prevent failure of the secondstage HPT air seal, which could lead to
uncontained engine failure and damage
to the airplane.
DATES: We must receive comments on
this proposed AD by August 4, 2014.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
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SUMMARY:
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11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://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 proposed AD, contact Pratt &
Whitney Division, 400 Main St., East
Hartford, CT 06108; phone: (860) 565–
8770; fax: (860) 565–4503. You may
view this service information at the
FAA, Engine & Propeller Directorate, 12
New England Executive Park,
Burlington, MA. For information on the
availability of this material at the FAA,
call (781) 238–7125.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2013–
0072; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: (800) 647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
James Gray, Aerospace Engineer, Engine
Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: (781) 238–7742; fax: (781) 238–
7199; email: james.e.gray@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2013–0072; Directorate Identifier
2013–NE–04–AD’’ at the beginning of
your comments. We specifically invite
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comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On July 19, 2013, we issued AD 2013–
15–09, Amendment 39–17525 (78 FR
49111, August 13, 2013), (‘‘AD 2013–
15–09’’), for all PW PW4074, PW4074D,
PW4077, PW4077D, PW4084D,
PW4090, and PW4090–3 turbofan
engine models with second-stage HPT
air seal, P/N 54L041, installed. AD
2013–15–09 requires initial and
repetitive inspections for cracks in
second-stage HPT air seals and
replacement of air seals that fail
inspection. AD 2013–15–09 resulted
from the discovery of cracks in secondstage HPT air seals. We issued AD
2013–15–09 to prevent failure of the
second-stage HPT air seal, which could
lead to uncontained engine failure and
damage to the airplane.
Actions Since AD 2013–15–09 Was
Issued
Since we issued AD 2013–15–09, we
received multiple reports of throughcracks in a different location on secondstage HPT air seal, P/N 50L041, and
reports of cracking in the original
location in two additional second-stage
HPT air seal P/Ns, 50L960 and 50L976.
The cracking in the two additional P/Ns
requires that they be added to the
applicability of this proposed AD. PW
has developed a redesigned secondstage HPT air seal that corrects the
cracking condition in both locations.
The new cracking location in the
second-stage HPT air seal, P/N 50L041,
is in the front forward fillet radius. PW
determined that through-cracks in the
front forward fillet radius increase the
stresses in the mating hardware in the
HPT rotor and that increased stress
reduces the life of the first-stage HPT
hub, second-stage HPT hub, and secondstage HPT blade retaining plate.
Therefore, the first-stage HPT hub,
second-stage HPT hub, and second-stage
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05JNP1
Federal Register / Vol. 79, No. 108 / Thursday, June 5, 2014 / Proposed Rules
HPT blade retaining plate must be
removed from service if the secondstage HPT air seal, P/N 50L041, is found
with a through-crack.
Relevant Service Information
We reviewed PW Alert Service
Bulletin (ASB) No. PW4G–112–A72–
330, Revision 2, dated July 11, 2013,
which describes procedures for
inspecting the second-stage HPT air seal
for cracks and PW Service Bulletin (SB)
No. PW4G–112–72–332, Revision 2,
dated April 9, 2014, which describes
procedures for replacing the secondstage HPT air seal.
FAA’s Determination
We are proposing this AD because we
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 expand the
population of affected P/Ns, require
removal from service of two newly
identified P/Ns, require replacement of
the mating hardware if the second-stage
HPT air seal is found with a throughcrack, and add mandatory terminating
action to the repetitive inspection
requirements.
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Costs of Compliance
We estimate that this proposed AD
would affect 116 engines installed on
airplanes of U.S. registry. We also
estimate that it would take about 5
hours to perform the inspection
required by this proposed AD. The
average labor rate is $85 per hour. We
estimate that two engines will also
require replacement of the first-stage
HPT hub, second-stage HPT hub, and
second-stage HPT blade retaining plate.
We estimate that parts would cost about
$698,920 per engine. Based on these
figures, we estimate the total cost of this
proposed AD to U.S. operators to be
$23,420,020.
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.
We are 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
VerDate Mar<15>2010
14:56 Jun 04, 2014
Jkt 232001
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This proposed
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
We have 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) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska to the extent that it justifies
making a regulatory distinction, and
(4) 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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
32501
(b) Affected ADs
This AD supersedes AD 2013–15–09,
Amendment 39–17525 (78 FR 49111, August
13, 2013).
(c) Applicability
This AD applies to all Pratt & Whitney
Division (PW) PW4074, PW4074D, PW4077,
PW4077D, PW4084D, PW4090, and PW4090–
3 turbofan engine models with second-stage
high-pressure turbine (HPT) air seal, part
number (P/N) 54L041, 50L960, or 50L976,
installed.
(d) Unsafe Condition
This AD was prompted by additional
reports of cracking in the second-stage HPT
air seal. We are issuing this AD to prevent
failure of the second-stage HPT air seal,
which could lead to uncontained engine
failure and damage to the airplane.
(e) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(1) At the next piece-part exposure after the
effective date of this AD, do the following:
(i) Remove from service second-stage HPT
air seals, P/N 50L960, 50L976, and 50L041.
(ii) Fluorescent-penetrant inspect (FPI)
second-stage HPT air seal, P/N 50L041, for a
through-crack in the front forward fillet
radius.
(iii) If a through-crack in the front forward
fillet radius is found, remove the first-stage
HPT hub, second-stage HPT hub, and secondstage HPT blade retaining plate from service.
Do not reinstall the first-stage HPT hub,
second-stage HPT hub, or second-stage HPT
blade retaining plate into any engine.
(2) For engines with second-stage HPT air
seals, P/N 50L041, installed, perform initial
and repetitive inspections for cracks on-wing
until the part is removed from the engine as
follows:
(i) Perform an initial eddy current
inspection (ECI) for cracks prior to reaching
2,200 cycles-since-new or within 100 cyclesin-service after the effective date of this AD,
whichever occurs later.
(ii) Thereafter, repeat the ECI every 1,200
cycles since last inspection, or fewer,
depending on the results of the inspection.
(iii) Use section 4.0 of the appendix of PW
Alert Service Bulletin (ASB) No. PW4G–112–
A72–330, Revision 2, dated July 11, 2013, to
perform the inspection and use paragraph 8
of the Accomplishment Instructions of PW
ASB No. PW4G–112–A72–330, Revision 2,
dated July 11, 2013, to disposition the results
of the inspection.
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2013–15–09, Amendment 39–17525 (78
FR 49111, August 13, 2013), and adding
the following new AD:
(f) Installation Prohibition
After the effective date of this AD, do not
install any second-stage HPT air seal P/N
50L041, P/N 50L960, or P/N 50L976 into any
engine.
Pratt & Whitney Division: Docket No. FAA–
2013–0072; Directorate Identifier 2013–
NE–04–AD.
(g) Definitions
(1) For the purpose of this AD, piece-part
exposure is when the second-stage HPT air
seal is removed from the engine and fully
disassembled.
(2) For the purpose of this AD, a throughcrack is a crack that has propagated through
■
(a) Comments Due Date
The FAA must receive comments on this
AD action by August 4, 2014.
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Federal Register / Vol. 79, No. 108 / Thursday, June 5, 2014 / Proposed Rules
the thickness of the part and can be seen on
both the inner diameter and outer diameter
of the front forward fillet radius.
(h) Credit for Previous Actions
(1) If you performed an ECI of the secondstage HPT air seal before the effective date of
this AD, using PW ASB No. PW4G–112–
A72–330, Revision 1, dated February 14,
2013, or earlier version, you have met the
requirements of paragraph (e)(2)(i) of this AD.
(2) If you performed an in-shop FPI of the
second-stage HPT air seal before the effective
date of this AD, you have met the
requirements of paragraph (e)(2)(i) of this AD.
(i) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
FAA, may approve AMOCs for this AD. Use
the procedures found in 14 CFR 39.19 to
make your request.
(j) Related Information
(1) For more information about this AD,
contact James Gray, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: (781) 238–7742; fax: (781) 238–7199;
email: james.e.gray@faa.gov.
(2) For service information identified in
this AD, contact Pratt & Whitney Division,
400 Main St., East Hartford, CT 06108;
phone: (860) 565–8770; fax: (860) 565–4503.
(3) You may view this service information
at the FAA, Engine & Propeller Directorate,
12 New England Executive Park, Burlington,
MA. For information on the availability of
this material at the FAA, call (781) 238–7125.
Issued in Burlington, Massachusetts, on
May 28, 2014.
Colleen M. D’Alessandro,
Assistant Directorate Manager, Engine &
Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2014–13024 Filed 6–4–14; 8:45 am]
BILLING CODE 4910–13–P
ENVIRONMENTAL PROTECTION
AGENCY
40 CFR Part 49
[EPA–HQ–OAR–2011–0151; FRL–9910–71–
OAR]
RIN 2060–AS27
Managing Emissions From Oil and
Natural Gas Production in Indian
Country
Comments must be received on
or before July 21, 2014.
DATES:
Environmental Protection
Agency (EPA).
ACTION: Advance notice of proposed
rulemaking.
rmajette on DSK2TPTVN1PROD with PROPOSALS
AGENCY:
VerDate Mar<15>2010
14:56 Jun 04, 2014
Jkt 232001
Submit your comments,
identified by Docket ID No. EPA–HQ–
OAR–2011–0151, by one of the
following methods:
• www.regulations.gov: Follow the
on-line instructions for submitting
comments.
• Email: a-and-r-docket@epa.gov.
Include Docket ID No. EPA–HQ–OAR–
ADDRESSES:
The purpose of this Advance
Notice of Proposed Rulemaking (ANPR)
is to solicit broad feedback on the most
effective and efficient means of
implementing the Environmental
SUMMARY:
Protection Agency’s (EPA) Indian
Country Minor New Source Review
program for sources in the oil and
natural gas production segment of the
oil and natural gas sector. In particular,
this ANPR discusses potential new
source permitting approaches to address
emissions from proposed new and
modified oil and natural gas production
activities. One approach is a general
permit, which could serve as a
streamlined permitting approach for
addressing emissions from new and
modified minor sources and minor
modifications at major sources under
the Indian Country Minor NSR rule.
Another approach is a Federal
Implementation Plan, which could
address emissions from new and
modified minor sources and minor
modifications at major sources. Other
possible approaches include a permit by
rule, which is another streamlined
permitting approach. The EPA is
requesting comments on all available
new source permitting approaches and
will take this feedback into
consideration in developing a notice of
proposed rulemaking for this sector
under the Indian Country Minor NSR
program.
In addition, while the focus of this
ANPR is on permitting approaches for
proposed new oil and natural gas
production activities, the EPA believes
that managing emissions from existing
oil and natural gas sources in Indian
country would result in greater
consistency with surrounding state
requirements. Addressing existing
sources may be particularly important
given the significant activity associated
with the sector in Indian country and
the resultant need to protect public
health, balanced with tribes’ inherent
sovereignty and interest in promoting
economic development. If the EPA
decides to address existing oil and
natural gas production sources, then we
will be interested in considering
comments regarding whether a FIP
should be the mechanism used to
establish permitting requirements for
new and existing sources, especially in
areas where surrounding states regulate
existing sources.
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2011–0151 in the subject line of the
message.
Fax: (202) 566–9744, attention Docket
ID No. EPA–HQ–OAR–2011–0151.
Mail: Attention Docket ID No. EPA–
HQ–OAR–2011–0151, EPA, Mailcode:
6102T, 1200 Pennsylvania Ave. NW.,
Washington, DC 20460. Please include a
total of two copies.
Hand Delivery: The EPA Docket
Center, Public Reading Room, EPA
West, Room 3334, 1301 Constitution
Ave. NW., Washington, DC 20460,
Attention Docket ID No. EPA–HQ–
OAR–2011–0151. Such deliveries are
only accepted during the Docket’s
normal hours of operation, and special
arrangements should be made for
deliveries of boxed information.
Instructions: Direct your comments to
Docket ID No. EPA–HQ–OAR–2011–
0151. The EPA’s policy is that all
comments received will be included in
the public docket without change and
may be made available online at
www.regulations.gov, including any
personal information provided, unless
the comment includes information
claimed to be Confidential Business
Information (CBI) or other information
whose disclosure is restricted by statute.
Do not submit information that you
consider to be CBI or otherwise
protected through www.regulations.gov
or email. The www.regulations.gov Web
site is an ‘‘anonymous access’’ system,
which means the EPA will not know
your identity or contact information
unless you provide it in the body of
your comment. If you send an email
comment directly to the EPA without
going through www.regulations.gov,
your email address will be
automatically captured and included as
part of the comment that is placed in the
public docket and made available on the
internet. If you submit an electronic
comment, the EPA recommends that
you include your name and other
contact information in the body of your
comment and with any disk or CD–ROM
you submit. If the EPA cannot read your
comment due to technical difficulties
and cannot contact you for clarification,
the EPA may not be able to consider
your comment. Electronic files should
avoid the use of special characters, any
form of encryption, and be free of any
defects or viruses. For additional
instructions on submitting comments,
go to Section I.C of the SUPPLEMENTARY
INFORMATION section of this document.
Docket: The EPA has established a
docket for this action under Docket ID
Number EPA–HQ–OAR–2011–0151. All
documents in the docket are listed in
the www.regulations.gov index.
Although listed in the index, some
information is not publicly available,
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Agencies
[Federal Register Volume 79, Number 108 (Thursday, June 5, 2014)]
[Proposed Rules]
[Pages 32500-32502]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-13024]
========================================================================
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. 79, No. 108 / Thursday, June 5, 2014 /
Proposed Rules
[[Page 32500]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0072; Directorate Identifier 2013-NE-04-AD]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney Division Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede airworthiness directive (AD) 2013-15-
09, which applies to all Pratt & Whitney Division (PW) PW4074, PW4074D,
PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engine models
with certain second-stage high-pressure turbine (HPT) air seals,
installed. AD 2013-15-09 currently requires initial and repetitive
inspections for cracks in second-stage HPT air seals. Since we issued
AD 2013-15-09, we received reports of cracking in the original location
on two additional part numbers (P/Ns) as well as reports of through-
cracks in a new location in the second-stage HPT air seal. PW has
developed a redesigned second-stage HPT air seal that addresses the
cracking condition in both locations. This proposed AD would expand the
applicability of AD 2013-15-09 to include additional P/Ns, require
replacement of the mating hardware if the second-stage HPT air seal is
found with a through-crack, and add mandatory terminating action to the
repetitive inspections. We are proposing this AD to prevent failure of
the second-stage HPT air seal, which could lead to uncontained engine
failure and damage to the airplane.
DATES: We must receive comments on this proposed AD by August 4, 2014.
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 https://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 proposed AD, contact
Pratt & Whitney Division, 400 Main St., East Hartford, CT 06108; phone:
(860) 565-8770; fax: (860) 565-4503. You may view this service
information at the FAA, Engine & Propeller Directorate, 12 New England
Executive Park, Burlington, MA. For information on the availability of
this material at the FAA, call (781) 238-7125.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2013-
0072; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: (800) 647-5527) is in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: James Gray, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; phone: (781) 238-7742;
fax: (781) 238-7199; email: james.e.gray@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0072;
Directorate Identifier 2013-NE-04-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On July 19, 2013, we issued AD 2013-15-09, Amendment 39-17525 (78
FR 49111, August 13, 2013), (``AD 2013-15-09''), for all PW PW4074,
PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engine
models with second-stage HPT air seal, P/N 54L041, installed. AD 2013-
15-09 requires initial and repetitive inspections for cracks in second-
stage HPT air seals and replacement of air seals that fail inspection.
AD 2013-15-09 resulted from the discovery of cracks in second-stage HPT
air seals. We issued AD 2013-15-09 to prevent failure of the second-
stage HPT air seal, which could lead to uncontained engine failure and
damage to the airplane.
Actions Since AD 2013-15-09 Was Issued
Since we issued AD 2013-15-09, we received multiple reports of
through-cracks in a different location on second-stage HPT air seal, P/
N 50L041, and reports of cracking in the original location in two
additional second-stage HPT air seal P/Ns, 50L960 and 50L976. The
cracking in the two additional P/Ns requires that they be added to the
applicability of this proposed AD. PW has developed a redesigned
second-stage HPT air seal that corrects the cracking condition in both
locations.
The new cracking location in the second-stage HPT air seal, P/N
50L041, is in the front forward fillet radius. PW determined that
through-cracks in the front forward fillet radius increase the stresses
in the mating hardware in the HPT rotor and that increased stress
reduces the life of the first-stage HPT hub, second-stage HPT hub, and
second-stage HPT blade retaining plate. Therefore, the first-stage HPT
hub, second-stage HPT hub, and second-stage
[[Page 32501]]
HPT blade retaining plate must be removed from service if the second-
stage HPT air seal, P/N 50L041, is found with a through-crack.
Relevant Service Information
We reviewed PW Alert Service Bulletin (ASB) No. PW4G-112-A72-330,
Revision 2, dated July 11, 2013, which describes procedures for
inspecting the second-stage HPT air seal for cracks and PW Service
Bulletin (SB) No. PW4G-112-72-332, Revision 2, dated April 9, 2014,
which describes procedures for replacing the second-stage HPT air seal.
FAA's Determination
We are proposing this AD because we 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 expand the population of affected P/Ns,
require removal from service of two newly identified P/Ns, require
replacement of the mating hardware if the second-stage HPT air seal is
found with a through-crack, and add mandatory terminating action to the
repetitive inspection requirements.
Costs of Compliance
We estimate that this proposed AD would affect 116 engines
installed on airplanes of U.S. registry. We also estimate that it would
take about 5 hours to perform the inspection required by this proposed
AD. The average labor rate is $85 per hour. We estimate that two
engines will also require replacement of the first-stage HPT hub,
second-stage HPT hub, and second-stage HPT blade retaining plate. We
estimate that parts would cost about $698,920 per engine. Based on
these figures, we estimate the total cost of this proposed AD to U.S.
operators to be $23,420,020.
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.
We are 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 proposed 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
We have 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) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction, and
(4) 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 removing airworthiness directive (AD)
2013-15-09, Amendment 39-17525 (78 FR 49111, August 13, 2013), and
adding the following new AD:
Pratt & Whitney Division: Docket No. FAA-2013-0072; Directorate
Identifier 2013-NE-04-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by August 4,
2014.
(b) Affected ADs
This AD supersedes AD 2013-15-09, Amendment 39-17525 (78 FR
49111, August 13, 2013).
(c) Applicability
This AD applies to all Pratt & Whitney Division (PW) PW4074,
PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 turbofan
engine models with second-stage high-pressure turbine (HPT) air
seal, part number (P/N) 54L041, 50L960, or 50L976, installed.
(d) Unsafe Condition
This AD was prompted by additional reports of cracking in the
second-stage HPT air seal. We are issuing this AD to prevent failure
of the second-stage HPT air seal, which could lead to uncontained
engine failure and damage to the airplane.
(e) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(1) At the next piece-part exposure after the effective date of
this AD, do the following:
(i) Remove from service second-stage HPT air seals, P/N 50L960,
50L976, and 50L041.
(ii) Fluorescent-penetrant inspect (FPI) second-stage HPT air
seal, P/N 50L041, for a through-crack in the front forward fillet
radius.
(iii) If a through-crack in the front forward fillet radius is
found, remove the first-stage HPT hub, second-stage HPT hub, and
second-stage HPT blade retaining plate from service. Do not
reinstall the first-stage HPT hub, second-stage HPT hub, or second-
stage HPT blade retaining plate into any engine.
(2) For engines with second-stage HPT air seals, P/N 50L041,
installed, perform initial and repetitive inspections for cracks on-
wing until the part is removed from the engine as follows:
(i) Perform an initial eddy current inspection (ECI) for cracks
prior to reaching 2,200 cycles-since-new or within 100 cycles-in-
service after the effective date of this AD, whichever occurs later.
(ii) Thereafter, repeat the ECI every 1,200 cycles since last
inspection, or fewer, depending on the results of the inspection.
(iii) Use section 4.0 of the appendix of PW Alert Service
Bulletin (ASB) No. PW4G-112-A72-330, Revision 2, dated July 11,
2013, to perform the inspection and use paragraph 8 of the
Accomplishment Instructions of PW ASB No. PW4G-112-A72-330, Revision
2, dated July 11, 2013, to disposition the results of the
inspection.
(f) Installation Prohibition
After the effective date of this AD, do not install any second-
stage HPT air seal P/N 50L041, P/N 50L960, or P/N 50L976 into any
engine.
(g) Definitions
(1) For the purpose of this AD, piece-part exposure is when the
second-stage HPT air seal is removed from the engine and fully
disassembled.
(2) For the purpose of this AD, a through-crack is a crack that
has propagated through
[[Page 32502]]
the thickness of the part and can be seen on both the inner diameter
and outer diameter of the front forward fillet radius.
(h) Credit for Previous Actions
(1) If you performed an ECI of the second-stage HPT air seal
before the effective date of this AD, using PW ASB No. PW4G-112-A72-
330, Revision 1, dated February 14, 2013, or earlier version, you
have met the requirements of paragraph (e)(2)(i) of this AD.
(2) If you performed an in-shop FPI of the second-stage HPT air
seal before the effective date of this AD, you have met the
requirements of paragraph (e)(2)(i) of this AD.
(i) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, FAA, may approve AMOCs
for this AD. Use the procedures found in 14 CFR 39.19 to make your
request.
(j) Related Information
(1) For more information about this AD, contact James Gray,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington, MA
01803; phone: (781) 238-7742; fax: (781) 238-7199; email:
james.e.gray@faa.gov.
(2) For service information identified in this AD, contact Pratt
& Whitney Division, 400 Main St., East Hartford, CT 06108; phone:
(860) 565-8770; fax: (860) 565-4503.
(3) You may view this service information at the FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington,
MA. For information on the availability of this material at the FAA,
call (781) 238-7125.
Issued in Burlington, Massachusetts, on May 28, 2014.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2014-13024 Filed 6-4-14; 8:45 am]
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