Airworthiness Directives; Pratt & Whitney Turbofan Engines, 64419-64421 [2013-25459]
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Federal Register / Vol. 78, No. 209 / Tuesday, October 29, 2013 / Proposed Rules
legitimate domestic objective, such as
the protection of safety, and does not
operate in a manner that excludes
imports that meet this objective. The
statute also requires consideration of
international standards and, where
appropriate, that they be the basis for
U.S. standards. The FAA assessed the
potential effect of the AD and
determined that because it addresses an
immediate safety issue the AD is not
considered an unnecessary obstacle to
the foreign commerce of the United
States.
Unfunded Mandates Assessment
Title II of the Unfunded Mandates
Reform Act of 1995 (Pub. L. 104–4)
requires each Federal agency to prepare
a written statement assessing the effects
of any Federal mandate in a proposed or
final agency rule that may result in an
expenditure of $100 million or more (in
1995 dollars) in any one year by State,
local, and tribal governments, in the
aggregate, or by the private sector; such
a mandate is deemed to be a ‘‘significant
regulatory action.’’ The FAA currently
uses an inflation-adjusted value of
$143.1 million in lieu of $100 million.
The AD does not contain such a
mandate; therefore, the requirements of
Title II of the Act do not apply.
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Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this IRFA. Send your comments to an
address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2013–0393; Directorate Identifier 2012–
CE–025–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the IRFA as related to the AD
action. The most helpful comments will
reference a specific portion of the IRFA
or related rulemaking document,
explain the reason for any
recommended change, and include
supporting data.
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 the AD.
Issued in Kansas City, Missouri, on
October 22, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2013–25526 Filed 10–28–13; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Examining the AD Docket
Federal Aviation Administration
You may examine the AD docket on
the Internet at https://
www.regulations.gov; 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:
Robert Morlath, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: 781–238–7154; fax: 781–238–
7199; email: robert.c.morlath@faa.gov.
SUPPLEMENTARY INFORMATION:
14 CFR Part 39
[Docket No. FAA–2013–0740; Directorate
Identifier 2013–NE–24–AD]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all Pratt
& Whitney (PW) PW2037, PW2037D,
PW2037M, PW2040, PW2040D,
PW2043, PW2146, PW2240, PW2337,
PW2643, and F117–PW–100 turbofan
engines. This proposed AD was
prompted by a rupture of the diffuserto-high-pressure turbine (HPT) case
flange. This proposed AD would require
a one-time eddy current inspection (ECI)
of affected engines with certain diffuser
and HPT cases installed. This AD also
proposes to require a fluorescentpenetrant inspection (FPI) of the
diffuser case rear flange and HPT case
front flange. We are proposing this AD
to prevent failure of the diffuser-to-HPT
case flange, which could lead to
uncontained engine failure and damage
to the airplane.
DATES: We must receive comments on
this proposed AD by December 30,
2013.
SUMMARY:
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, 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.
ADDRESSES:
PO 00000
Frm 00012
Fmt 4702
Sfmt 4702
Comments Invited
We invite 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–
2013–0740; Directorate Identifier 2013–
NE–24–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
We received a report of an engine
event in October 2011 that resulted in
a rupture of the engine diffuser-to-HPT
case flange. The rupture caused the
engine cowl doors to break open, which
resulted in damage to the underside of
the airplane’s wing. Subsequent
investigation revealed that the root
cause of this rupture was a crack that
originated in HPT case M-flange
boltholes (the forward flange of the HPT
case that mates with the rear outer
flange of the diffuser case). This
condition, if not corrected, could result
in failure of the diffuser-to-HPT case
flange, which may cause an
uncontained engine failure and damage
to the airplane.
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Federal Register / Vol. 78, No. 209 / Tuesday, October 29, 2013 / Proposed Rules
Relevant Service Information
We reviewed PW Service Bulletin
(SB) No. PW2000 72–763, Revision 1,
dated August 30, 2013, and PW PW2000
Series Engine Manual part number
1A6231. The SB describes procedures
for inspecting the flanges of the HPT
case and the diffuser case.
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 require an
on-wing ECI of the diffuser case and
HPT case flanges. This proposed AD
would also require an FPI of all engine
diffuser cases and all HPT cases.
Regulatory Findings
Differences Between the Proposed AD
and the Service Information
PW SB No. PW2000 72–763, Revision
1, dated August 30, 2013, requires that
operators complete an on-wing ECI by
August 31, 2013. We are proposing that
the ECI be performed within 100 flight
cycles or 30 days after the effective date
of this AD, whichever is earlier.
Costs of Compliance
We estimate that this proposed AD
will affect 638 engines installed on
airplanes of U.S. registry. Of the 638
engines, we estimate that about 58
engines will be subject to ECI and all
engines will be subject to the FPI. We
also estimate that it would take about 5
hours to perform the ECI and 3 hours to
perform the FPI required by this
proposed AD. Materials cost for the FPI
will be about $20 per engine. The
average labor rate is $85 per hour. Based
on these figures, we estimate the total
cost of this proposed AD to U.S.
operators to be $200,100.
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.
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]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Pratt & Whitney: Docket No. FAA–2013–
0740; Directorate Identifier 2013–NE–
24–AD.
(a) Comments Due Date
We must receive comments by December
30, 2013.
(b) Affected ADs
We 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) 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:
None.
(c) Applicability
This AD applies to all Pratt & Whitney
(PW) PW2037, PW2037D, PW2037M,
PW2040, PW2040D, PW2043, PW2146,
PW2240, PW2337, PW2643, and F117–PW–
100 turbofan engines.
(d) Unsafe Condition
This AD was prompted by a rupture of the
diffuser-to-high-pressure turbine (HPT) case
flange. We are issuing this AD to prevent
failure of the diffuser-to-HPT case flange,
which could lead to uncontained engine
failure and damage to the airplane.
(e) Compliance
Unless already done, comply with this AD
within the compliance times specified.
(1) For diffuser and HPT cases identified
by serial number (S/N) in Table 1 to
paragraph (e) of this AD:
(i) Within 100 flight cycles or 30 days after
the effective date of this AD, whichever is
earlier, eddy current inspect the diffuser case
and the HPT case M-flange.
(ii) For engines installed on the aircraft,
use paragraphs 3.G. through 3.L. in the ‘‘For
Engines Installed on the Aircraft’’ section of
the Accomplishment Instructions of PW
Service Bulletin (SB) No. PW2000 72–763,
Revision 1, dated August 30, 2013, to
perform the inspection.
(iii) For engines removed from the aircraft,
use paragraphs 3.B. through 3.G. in the ‘‘For
Engines Removed From the Aircraft’’ section
of the Accomplishment Instructions of PW
Service Bulletin (SB) No. PW2000 72–763,
Revision 1, dated August 30, 2013, to
perform the inspection.
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TABLE 1 TO PARAGRAPH (e)—DIFFUSER AND HPT CASE P/NS AND SERIAL NUMBERS
Diffuser case part No. (P/N)
Diffuser case S/N
1B7407–001 ...................................
1B7407 ...........................................
1B7407 ...........................................
1B7407 ...........................................
1B7407–001 ...................................
1B3055–001 ...................................
1B7461 ...........................................
DGUSAA0114 ...............................
WE2452 ........................................
DGUSAA0097 ...............................
DGUSAA0670 ...............................
DGUSAA0622 ...............................
DGUSAA0247 ...............................
DGGUAK1308 ..............................
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Frm 00013
HPT case P/N
Fmt 4702
1A9030
1B2440
1B2440
1B2440
1B2440
1B2440
1B2440
Sfmt 4702
HPT case S/N
.........................................
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DKLBC00030
DKLBC07691
DKLBDB5108
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Federal Register / Vol. 78, No. 209 / Tuesday, October 29, 2013 / Proposed Rules
64421
TABLE 1 TO PARAGRAPH (e)—DIFFUSER AND HPT CASE P/NS AND SERIAL NUMBERS—Continued
Diffuser case part No. (P/N)
Diffuser case S/N
1B7461 ...........................................
1B7461 ...........................................
1B7477 ...........................................
1B7477 ...........................................
1B7477 ...........................................
1B7477 ...........................................
1B4091–001 ...................................
1B4091–002 ...................................
1B4091–005 ...................................
1B7461 ...........................................
1B7477 ...........................................
1B7407 ...........................................
1B7407 ...........................................
1B7477 ...........................................
1B7477 ...........................................
1B7407–001 ...................................
1B7407 ...........................................
DGGUAK1306 ..............................
DGGUAK1356 ..............................
DGGUAL1445 ...............................
DGGUAL1492 ...............................
DGGUAL1501 ...............................
DGGUAL1597 ...............................
RT6356 .........................................
ST2044 .........................................
PF3203 .........................................
DGGUAK1377 ..............................
DGGUAL1548 ...............................
DGGUAK0189 ..............................
DGUSAA0443 ...............................
DGGUAL1441 ...............................
DGGUAL1560 ...............................
DGUSAA0329 ...............................
DGUSAA0334 ...............................
(2) For all diffuser and HPT cases:
(i) At the next piece part exposure and
every piece part exposure thereafter, perform
a high sensitivity fluorescent-penetrant
inspection (FPI) of the entire diffuser case
rear flange (M-flange) and bolt holes.
(ii) At the next piece part exposure and
every piece part exposure thereafter, perform
a high sensitivity FPI of the entire HPT case
forward flange (M-flange) and bolt holes.
(f) Prohibition Statement
After the effective date of this AD, do not
install any engine with a diffuser or HPT case
with serial number listed in Table 1 to
paragraph (e) of this AD, onto any aircraft,
that was not inspected per paragraph (e) of
this AD.
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(g) Credit for Previous Actions
If you performed an eddy current
inspection of the diffuser case and HPT case
M-flange using paragraphs 3.G. through 3.L.
in the ‘‘For Engines Installed on the Aircraft’’
section or paragraphs 3.B. through 3.G. in the
‘‘For Engines Removed from the Aircraft’’
section of the Accomplishment Instructions
of PW SB PW2000 72–763, dated March 22,
2013, you met the requirements of paragraph
(e)(1) of this AD.
(h) 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.
HPT case P/N
1B2440
1B2440
1A9030
1A9030
1A9030
1A9030
1B2440
1A9030
1A9030
1B2440
1B2440
1B2440
1B2440
1B2440
1A9030
1B2440
1B2440
1B2440
1B2440
1B2440
1B2440
1B2440
1B2440
1B2440
1B2440
1B2440
1B2440
Issued in Burlington, Massachusetts, on
October 7, 2013.
Colleen M. D’Alessandro,
Assistant Directorate Manager, Engine &
Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2013–25459 Filed 10–28–13; 8:45 am]
(i) Related Information
(1) For more information about this AD,
contact Robert Morlath, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
VerDate Mar<15>2010
16:26 Oct 28, 2013
Jkt 232001
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Executive Park, Burlington, MA 01803;
phone: 781–238–7154; fax: 781–238–7199;
email: robert.c.morlath@faa.gov.
(2) Pratt & Whitney Engine Manual, part
number 1A6231, Chapter 72–41–00,
Inspection/Check-02, (Task 72–41–00–230–
002) and Chapter 72–52–00, Inspection/
Check-02 (Task 72–52–00–230–000), which
are not incorporated by reference in this AD,
can be obtained from Pratt & Whitney, using
the contact information in paragraph (i)(3) of
this AD.
(3) For service information identified in
this AD, contact Pratt & Whitney, United
Technologies Corporation, 400 Main St., East
Hartford, CT 06108; phone: 860–565–8770;
fax: 860–565–4503.
(4) 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.
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HPT case S/N
DKLBDB5153
DKLBDU3358
RM6353
PD3348
PD3280
ND5644
DKLBBP0225
DKLBBR3621
PD3290
WG6904
WV1807
WX2639
WZ4057
WX2664
RM6359
DKLBCM8956
DKLBCM0214
DKLBDB5069
DKLBB02548
DKLBDC7336
DKLBDU3372
WM6913
DKLBBF6606
DKLBBB2861
DKLBCT1660
DKLBB94641
DKLBBX8092
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0766; Directorate
Identifier 2013–NE–26–AD]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney Canada Corp. Turboprop
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all Pratt
& Whitney Canada Corp. (P&WC) PT6A–
114 and PT6A–114A turboprop engines.
This proposed AD was prompted by
several incidents of compressor turbine
(CT) blade failure, including two
fatalities, resulting in power loss and inflight shutdown (IFSD) of the engine.
This proposed AD would require initial
and repetitive borescope inspections
(BSIs) of CT blades, and the removal
from service of blades that fail
inspection. We are proposing this AD to
prevent failure of CT blades, which
could lead to damage to the engine or
to the airplane.
DATES: We must receive comments on
this proposed AD by December 30,
2013.
SUMMARY:
E:\FR\FM\29OCP1.SGM
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Agencies
[Federal Register Volume 78, Number 209 (Tuesday, October 29, 2013)]
[Proposed Rules]
[Pages 64419-64421]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-25459]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0740; Directorate Identifier 2013-NE-24-AD]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Pratt & Whitney (PW) PW2037, PW2037D, PW2037M, PW2040, PW2040D, PW2043,
PW2146, PW2240, PW2337, PW2643, and F117-PW-100 turbofan engines. This
proposed AD was prompted by a rupture of the diffuser-to-high-pressure
turbine (HPT) case flange. This proposed AD would require a one-time
eddy current inspection (ECI) of affected engines with certain diffuser
and HPT cases installed. This AD also proposes to require a
fluorescent-penetrant inspection (FPI) of the diffuser case rear flange
and HPT case front flange. We are proposing this AD to prevent failure
of the diffuser-to-HPT case flange, which could lead to uncontained
engine failure and damage to the airplane.
DATES: We must receive comments on this proposed AD by December 30,
2013.
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, 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; 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: Robert Morlath, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; phone: 781-238-7154;
fax: 781-238-7199; email: robert.c.morlath@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite 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-2013-0740;
Directorate Identifier 2013-NE-24-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
We received a report of an engine event in October 2011 that
resulted in a rupture of the engine diffuser-to-HPT case flange. The
rupture caused the engine cowl doors to break open, which resulted in
damage to the underside of the airplane's wing. Subsequent
investigation revealed that the root cause of this rupture was a crack
that originated in HPT case M-flange boltholes (the forward flange of
the HPT case that mates with the rear outer flange of the diffuser
case). This condition, if not corrected, could result in failure of the
diffuser-to-HPT case flange, which may cause an uncontained engine
failure and damage to the airplane.
[[Page 64420]]
Relevant Service Information
We reviewed PW Service Bulletin (SB) No. PW2000 72-763, Revision 1,
dated August 30, 2013, and PW PW2000 Series Engine Manual part number
1A6231. The SB describes procedures for inspecting the flanges of the
HPT case and the diffuser case.
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 require an on-wing ECI of the diffuser case
and HPT case flanges. This proposed AD would also require an FPI of all
engine diffuser cases and all HPT cases.
Differences Between the Proposed AD and the Service Information
PW SB No. PW2000 72-763, Revision 1, dated August 30, 2013,
requires that operators complete an on-wing ECI by August 31, 2013. We
are proposing that the ECI be performed within 100 flight cycles or 30
days after the effective date of this AD, whichever is earlier.
Costs of Compliance
We estimate that this proposed AD will affect 638 engines installed
on airplanes of U.S. registry. Of the 638 engines, we estimate that
about 58 engines will be subject to ECI and all engines will be subject
to the FPI. We also estimate that it would take about 5 hours to
perform the ECI and 3 hours to perform the FPI required by this
proposed AD. Materials cost for the FPI will be about $20 per engine.
The average labor rate is $85 per hour. Based on these figures, we
estimate the total cost of this proposed AD to U.S. operators to be
$200,100.
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 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) 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 adding the following new airworthiness
directive (AD):
Pratt & Whitney: Docket No. FAA-2013-0740; Directorate Identifier
2013-NE-24-AD.
(a) Comments Due Date
We must receive comments by December 30, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Pratt & Whitney (PW) PW2037, PW2037D,
PW2037M, PW2040, PW2040D, PW2043, PW2146, PW2240, PW2337, PW2643,
and F117-PW-100 turbofan engines.
(d) Unsafe Condition
This AD was prompted by a rupture of the diffuser-to-high-
pressure turbine (HPT) case flange. We are issuing this AD to
prevent failure of the diffuser-to-HPT case flange, which could lead
to uncontained engine failure and damage to the airplane.
(e) Compliance
Unless already done, comply with this AD within the compliance
times specified.
(1) For diffuser and HPT cases identified by serial number (S/N)
in Table 1 to paragraph (e) of this AD:
(i) Within 100 flight cycles or 30 days after the effective date
of this AD, whichever is earlier, eddy current inspect the diffuser
case and the HPT case M-flange.
(ii) For engines installed on the aircraft, use paragraphs 3.G.
through 3.L. in the ``For Engines Installed on the Aircraft''
section of the Accomplishment Instructions of PW Service Bulletin
(SB) No. PW2000 72-763, Revision 1, dated August 30, 2013, to
perform the inspection.
(iii) For engines removed from the aircraft, use paragraphs 3.B.
through 3.G. in the ``For Engines Removed From the Aircraft''
section of the Accomplishment Instructions of PW Service Bulletin
(SB) No. PW2000 72-763, Revision 1, dated August 30, 2013, to
perform the inspection.
Table 1 to Paragraph (e)--Diffuser and HPT Case P/Ns and Serial Numbers
----------------------------------------------------------------------------------------------------------------
Diffuser case part No. (P/N) Diffuser case S/N HPT case P/N HPT case S/N
----------------------------------------------------------------------------------------------------------------
1B7407-001........................... DGUSAA0114............. 1A9030................. RM6300
1B7407............................... WE2452................. 1B2440................. DKLBB40125
1B7407............................... DGUSAA0097............. 1B2440................. DKLBCH3429
1B7407............................... DGUSAA0670............. 1B2440................. DKLBCS1032
1B7407-001........................... DGUSAA0622............. 1B2440................. DKLBC00030
1B3055-001........................... DGUSAA0247............. 1B2440................. DKLBC07691
1B7461............................... DGGUAK1308............. 1B2440................. DKLBDB5108
[[Page 64421]]
1B7461............................... DGGUAK1306............. 1B2440................. DKLBDB5153
1B7461............................... DGGUAK1356............. 1B2440................. DKLBDU3358
1B7477............................... DGGUAL1445............. 1A9030................. RM6353
1B7477............................... DGGUAL1492............. 1A9030................. PD3348
1B7477............................... DGGUAL1501............. 1A9030................. PD3280
1B7477............................... DGGUAL1597............. 1A9030................. ND5644
1B4091-001........................... RT6356................. 1B2440................. DKLBBP0225
1B4091-002........................... ST2044................. 1A9030................. DKLBBR3621
1B4091-005........................... PF3203................. 1A9030................. PD3290
1B7461............................... DGGUAK1377............. 1B2440................. WG6904
1B7477............................... DGGUAL1548............. 1B2440................. WV1807
1B7407............................... DGGUAK0189............. 1B2440................. WX2639
1B7407............................... DGUSAA0443............. 1B2440................. WZ4057
1B7477............................... DGGUAL1441............. 1B2440................. WX2664
1B7477............................... DGGUAL1560............. 1A9030................. RM6359
1B7407-001........................... DGUSAA0329............. 1B2440................. DKLBCM8956
1B7407............................... DGUSAA0334............. 1B2440................. DKLBCM0214
1B2440................. DKLBDB5069
1B2440................. DKLBB02548
1B2440................. DKLBDC7336
1B2440................. DKLBDU3372
1B2440................. WM6913
1B2440................. DKLBBF6606
1B2440................. DKLBBB2861
1B2440................. DKLBCT1660
1B2440................. DKLBB94641
1B2440................. DKLBBX8092
----------------------------------------------------------------------------------------------------------------
(2) For all diffuser and HPT cases:
(i) At the next piece part exposure and every piece part
exposure thereafter, perform a high sensitivity fluorescent-
penetrant inspection (FPI) of the entire diffuser case rear flange
(M-flange) and bolt holes.
(ii) At the next piece part exposure and every piece part
exposure thereafter, perform a high sensitivity FPI of the entire
HPT case forward flange (M-flange) and bolt holes.
(f) Prohibition Statement
After the effective date of this AD, do not install any engine
with a diffuser or HPT case with serial number listed in Table 1 to
paragraph (e) of this AD, onto any aircraft, that was not inspected
per paragraph (e) of this AD.
(g) Credit for Previous Actions
If you performed an eddy current inspection of the diffuser case
and HPT case M-flange using paragraphs 3.G. through 3.L. in the
``For Engines Installed on the Aircraft'' section or paragraphs 3.B.
through 3.G. in the ``For Engines Removed from the Aircraft''
section of the Accomplishment Instructions of PW SB PW2000 72-763,
dated March 22, 2013, you met the requirements of paragraph (e)(1)
of this AD.
(h) 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.
(i) Related Information
(1) For more information about this AD, contact Robert Morlath,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington, MA
01803; phone: 781-238-7154; fax: 781-238-7199; email:
robert.c.morlath@faa.gov.
(2) Pratt & Whitney Engine Manual, part number 1A6231, Chapter
72-41-00, Inspection/Check-02, (Task 72-41-00-230-002) and Chapter
72-52-00, Inspection/Check-02 (Task 72-52-00-230-000), which are not
incorporated by reference in this AD, can be obtained from Pratt &
Whitney, using the contact information in paragraph (i)(3) of this
AD.
(3) For service information identified in this AD, contact Pratt
& Whitney, United Technologies Corporation, 400 Main St., East
Hartford, CT 06108; phone: 860-565-8770; fax: 860-565-4503.
(4) 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 October 7, 2013.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2013-25459 Filed 10-28-13; 8:45 am]
BILLING CODE 4910-13-P