Airworthiness Directives; Pratt & Whitney Canada Corp. Turboshaft Engines, 11565-11567 [2013-03412]
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Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations
(f) Borescope Inspections
(1) Borescope-inspect to verify the
presence of a retaining ring securing the PT
baffle located near the second stage PT disk,
as follows:
(i) For engines with 2,200 PT cycles or
more on the effective date of this AD, inspect
within 100 operating hours or 150 PT cycles,
whichever occurs first.
(ii) For engines with more than 1,400 PT
cycles but fewer than 2,200 PT cycles on the
effective date of this AD, inspect within 250
operating hours, 350 PT cycles, or before
exceeding 2,350 PT cycles, whichever occurs
first.
(iii) For engines with 1,400 PT cycles or
fewer on the effective date of this AD, inspect
within 500 operating hours, 750 PT cycles, or
before exceeding 1,750 PT cycles, whichever
occurs first.
(2) Thereafter, repetitively borescopeinspect to verify the presence of the retaining
ring securing the PT baffle located near the
second stage PT disk, on or before an
additional 600 flight hours or 900 PT cycles,
whichever occurs first.
(3) Use P&WC Alert SB No. PT6C–72–
A41060, Revision 3, dated October 11, 2012,
paragraphs 3.A.(1) through 3.A.(6) to do the
borescope inspections required by this AD.
(4) If the retaining ring is missing or the PT
baffle is out of position, then remove the
engine from service before further flight.
(g) Optional Terminating Action
Performing the engine improvement
modifications in P&WC SB No. PT6C–72–
41056, Revision 5, dated January 17, 2013,
paragraphs 3.A. through 3.C.(12) and 3.E.(1)
through 3.E.(15), is an optional terminating
action to the repetitive inspections required
by this AD.
sroberts on DSK5SPTVN1PROD with RULES
(h) Credit for Previous Actions
(1) If you performed the initial borescope
inspection before the effective date of this AD
using P&WC Special Instruction No. 45–
2011R2, dated July 27, 2011, or P&WC Alert
SB No. PT6C–72–A41060, dated August 12,
2011, or Revision 1, dated September 29,
2011, or Revision 2, dated February 10, 2012,
you met the requirements of paragraph (f)(1)
of this AD.
(2) If you performed the engine
modification before the effective date of this
AD using P&WC SB No. PT6C–72–41056,
dated April 1, 2011, or Revision 1, dated June
17, 2011, or Revision 2, dated October 6,
2011, or Revision 3, dated February 3, 2012,
or Revision 4, dated February 13, 2012, you
met the requirements of this AD and no
further action is required.
(i) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
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 Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
VerDate Mar<15>2010
15:41 Feb 15, 2013
Jkt 229001
email: james.lawrence@faa.gov; phone: 781–
238–7176; fax: 781–238–7199.
(2) Refer to Transport Canada AD CF–
2012–24, dated August 2, 2012, for related
information.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Pratt & Whitney Canada Corp (P&WC)
Alert Service Bulletin (SB) No. PT6C–72–
A41060, Revision 3, dated October 11, 2012.
(ii) P&WC SB No. PT6C–72–41056,
Revision 5, dated January 17, 2013.
(3) For service information identified in
this AD, contact Pratt & Whitney Canada
Corp., 1000 Marie-Victorin, Longueuil,
Quebec, Canada, J4G 1A1; phone: 800–268–
8000; fax: 450–647–2888; Web site: https://
www.pwc.ca.
(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.
(5) You may view this service information
at the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
February 1, 2013.
Colleen M. D’Alessandro,
Assistant Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2013–03266 Filed 2–15–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0942; Directorate
Identifier 2012–NE–24–AD; Amendment 39–
17355; AD 2013–03–21]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney Canada Corp. Turboshaft
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
serial number Pratt & Whitney Canada
Corp. PW206B, PW206B2, PW206C,
PW207C, PW207D, PW207D1,
PW207D2, and PW207E turboshaft
engines. This AD was prompted by the
SUMMARY:
PO 00000
Frm 00015
Fmt 4700
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11565
discovery that certain power turbine
(PT) disks were made to specific heat
codes that may not achieve the
maximum in-service life. This AD
requires re-identification of the PT disk
to a part number (P/N) with a lower life
limit. We are issuing this AD to prevent
possible uncontained PT disk failure
and loss of helicopter control.
DATES: This AD becomes effective
March 26, 2013. The Director of the
Federal Register approved the
incorporation by reference of a certain
publication listed in this AD as of
March 26, 2013.
ADDRESSES: The Docket Operations
office is located at Docket Management
Facility, U.S. Department of
Transportation, 1200 New Jersey
Avenue SE., West Building Ground
Floor, Room W12–140, Washington, DC
20590–0001.
FOR FURTHER INFORMATION CONTACT:
James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: 781–238–7176; fax: 781–238–
7199; email: james.lawrence@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on November 7, 2012 (77 FR
66767). That NPRM proposed to correct
an unsafe condition for the specified
products. The Mandatory Continuing
Airworthiness Information states:
Certain power turbine (PT) disks, part
number (P/N) 3044188–01, made to specific
heat codes may not achieve the established
maximum in-service life when installed in
Turbomachinery Assembly P/N 3058588. The
PT disk in-service life for engines using this
specific PT disk and compressor turbine (CT)
vane combination is reduced when operated
in a particular temperature and speed
environment.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (77
FR 66767, November 7, 2012).
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed (77 FR 66767, November 7,
2012).
Costs of Compliance
We estimate that this AD will affect
about 83 engines installed on
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11566
Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations
helicopters of U.S. registry. We also
estimate that it will take about 4 hours
per engine to comply with this AD. The
average labor rate is $85 per hour.
Prorated parts life will cost about
$8,900. Based on these figures, we
estimate the cost of this AD on U.S.
operators to be $766,920.
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 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.
sroberts on DSK5SPTVN1PROD with RULES
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
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 AD:
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); 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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
VerDate Mar<15>2010
15:41 Feb 15, 2013
Jkt 229001
other information. The street address for
the Docket Operations office (phone:
800–647–5527) is provided in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2013–03–21 Pratt & Whitney Canada Corp.:
Amendment 39–17355; Docket No.
FAA–2012–0942; Directorate Identifier
2012–NE–24–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective March 26, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Pratt & Whitney Canada
Corp. (P&WC) model PW206B, PW206B2,
PW206C, PW207C, PW207D, PW207D1,
PW207D2, and PW207E turboshaft engines.
(d) Reason
This AD was prompted by the discovery
that certain power turbine (PT) disks, part
number (P/N) 3044188–01, made to specific
heat codes that may not achieve the
established maximum in-service life when
installed in Turbomachinery Assembly P/N
3058588. The PT disk in-service life for
engines using this specific PT disk and
compressor turbine vane combination is
reduced when operated in a particular
temperature and speed environment. We are
issuing this AD to prevent possible
uncontained PT disk failure and loss of
helicopter control.
(e) Actions and Compliance
Unless already done, do the following
actions.
(f) Affected PT Disks Installed With
Turbomachinery Assembly P/N 3058588
Installation
(1) For any PT disk P/N 3044188–01 that
is listed by serial number (S/N) in Table 1 of
P&WC Alert Service Bulletin (ASB) No.
PW200–72–A28311, Revision 2, dated July
24, 2012, and, that is installed or that had
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Frm 00016
Fmt 4700
Sfmt 4700
previously been installed with
Turbomachinery Assembly P/N 3058588
installation, do the following:
(i) Remove the PT disk P/N 3044188–01
from service before it reaches 10,000 cyclessince-new (CSN).
(ii) Re-identify the PT disk to P/N
3072542–01, at the next engine shop visit,
not to exceed 10,000 CSN on the PT disk,
before reinstalling it in any engine. Use
paragraphs 3.B.(1) through 3.B.(1)(b)4 of the
Accomplishment Instructions of P&WC ASB
No. PW200–72–A28311, Revision 2, dated
July 24, 2012, to do the re-identification.
(iii) After re-identification of the PT disk to
P/N 3072542–01, retain the total cycles
accumulated as P/N 3044188–01. The cycles
remaining on the re-identified P/N 3072542–
01 PT disk must be calculated using the
difference between the published life limit of
P/N 3072542–01 and the total number of
cycles accumulated as P/N 3044188–01. The
maximum in-service life of PT disk, P/N
3072542–01, is 10,000 CSN.
(2) After the effective date of this AD, do
not install any PT disk, P/N 3044188–01, that
is listed in Table 1 of P&WC ASB No.
PW200–72–A28311, Revision 2, dated July
24, 2012, in any engine with Turbomachinery
Assembly P/N 3058588 installation, unless
the PT disk has been re-identified to P/N
3072542–01. Use paragraphs 3.B.(1) through
3.B.(1)(b)4 of the Accomplishment
Instructions of P&WC ASB No. PW200–72–
A28311, Revision 2, dated July 24, 2012, to
do the PT disk re-identification.
(g) Credit for Actions Accomplished in
Accordance With Previous Service
Information
You may take credit for the reidentification of the PT disk that is required
by this AD if you performed the reidentification before the effective date of this
AD using P&WC ASB No. PW200–72–
A28311, dated March 1, 2012, or P&WC ASB
No. PW200–72–A28311, Revision 1, dated
March 22, 2012.
(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 James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: 781–238–7176; fax: 781–238–7199;
email: james.lawrence@faa.gov.
(2) Refer to Transport Canada AD CF–
2012–23, dated July 26, 2012, for related
information.
(3) The Engine Maintenance Manual
(EMM) Temporary Revisions (TRs) listed in
Table 1 to paragraph (i)(3) of this AD pertain
to the subject of this AD.
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Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations
TABLE 1 TO PARAGRAPH (I)(3)—EMM
TRS
EMM P/Ns:
TR Nos.:
3071602 .................................
3043612 .................................
AL–3, AL–4
AL–12, AL–
13
AL–16
AL–18, AL–
19
AL–20
3043322 .................................
3039732 .................................
3038324 .................................
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Pratt & Whitney Canada Corp. Alert
Service Bulletin No. PW200–72–A28311,
Revision 2, dated July 24, 2012.
(ii) Reserved.
(3) For service information identified in
this AD, contact Pratt & Whitney Canada
Corp., 1000 Marie-Victorin, Longueuil,
Quebec, Canada, J4G 1A1; phone: 800–268–
8000; fax: 450–647–2888; Web site:
www.pwc.ca.
(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.
(5) You may view this service information
at the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
February 7, 2013.
Robert J. Ganley,
Acting Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2013–03412 Filed 2–15–13; 8:45 am]
BILLING CODE 4910–13–P
ACTION:
Final rule.
We are adopting a new
airworthiness directive (AD) for all
Gulfstream Aerospace LP (Type
Certificate Previously Held by Israel
Aircraft Industries, Ltd.) Model
Gulfstream G150 airplanes. This AD was
prompted by a review that determined
that the runway slope and anti-ice
corrections to V1 and take-off distances
in the Gulfstream G150 Airplane Flight
Manual (AFM) were presented in a nonconservative manner. This AD requires
revising the performance section of the
AFM to include procedures to advise
the flightcrew of certain runway slope
and anti-ice corrections and take-off
distance values. We are issuing this AD
to prevent the use of published nonconservative data, which could result in
the inability to meet the required takeoff performance, with consequent
hazard to safe operation during
performance-limited take-off operations.
DATES: This AD becomes effective
March 26, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 26, 2013.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tom
Groves, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1503;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
SUMMARY:
RIN 2120–AA64
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on September 20, 2012 (77 FR
58323). That NPRM proposed to correct
an unsafe condition for the specified
products. The Mandatory Continuing
Airworthiness Information (MCAI)
states:
Airworthiness Directives; Gulfstream
Aerospace LP (Type Certificate
Previously Held by Israel Aircraft
Industries, Ltd.) Airplanes
This [Israeli] AD mandates revised
limitations in the G150 AFM, pertaining to
the Performance Section. Each operator must
incorporate Temporary Rev. 3 to the G150
AFM.
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
The unsafe condition is the use of
published non-conservative data, which
could result in the inability to meet the
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
sroberts on DSK5SPTVN1PROD with RULES
[Docket No. FAA–2012–0986; Directorate
Identifier 2012–NM–077–AD; Amendment
39–17357; AD 2013–03–23]
AGENCY:
VerDate Mar<15>2010
15:41 Feb 15, 2013
Jkt 229001
PO 00000
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11567
required take-off performance, with
consequent hazard to safe operation
during performance-limited take-off
operations. You may obtain further
information by examining the MCAI in
the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (77
FR 58323, September 20, 2012) or on the
determination of the cost to the public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (77 FR
58323, September 20, 2012) for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (77 FR 58323,
September 20, 2012).
Costs of Compliance
We estimate that this AD will affect
56 products of U.S. registry. We also
estimate that it will take about 1 workhour per product to comply with the
basic requirements of this AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the
cost of this AD to the U.S. operators to
be $4,760, or $85 per product.
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 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 AD will not
have federalism implications under
E:\FR\FM\19FER1.SGM
19FER1
]]>Agencies
[Federal Register Volume 78, Number 33 (Tuesday, February 19, 2013)]
[Rules and Regulations]
[Pages 11565-11567]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-03412]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0942; Directorate Identifier 2012-NE-24-AD;
Amendment 39-17355; AD 2013-03-21]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney Canada Corp. Turboshaft
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
serial number Pratt & Whitney Canada Corp. PW206B, PW206B2, PW206C,
PW207C, PW207D, PW207D1, PW207D2, and PW207E turboshaft engines. This
AD was prompted by the discovery that certain power turbine (PT) disks
were made to specific heat codes that may not achieve the maximum in-
service life. This AD requires re-identification of the PT disk to a
part number (P/N) with a lower life limit. We are issuing this AD to
prevent possible uncontained PT disk failure and loss of helicopter
control.
DATES: This AD becomes effective March 26, 2013. The Director of the
Federal Register approved the incorporation by reference of a certain
publication listed in this AD as of March 26, 2013.
ADDRESSES: The Docket Operations office is located at Docket Management
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.
FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; phone: 781-238-7176;
fax: 781-238-7199; email: james.lawrence@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on November 7, 2012 (77
FR 66767). That NPRM proposed to correct an unsafe condition for the
specified products. The Mandatory Continuing Airworthiness Information
states:
Certain power turbine (PT) disks, part number (P/N) 3044188-01,
made to specific heat codes may not achieve the established maximum
in-service life when installed in Turbomachinery Assembly P/N
3058588. The PT disk in-service life for engines using this specific
PT disk and compressor turbine (CT) vane combination is reduced when
operated in a particular temperature and speed environment.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (77 FR 66767, November 7,
2012).
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed (77 FR 66767,
November 7, 2012).
Costs of Compliance
We estimate that this AD will affect about 83 engines installed on
[[Page 11566]]
helicopters of U.S. registry. We also estimate that it will take about
4 hours per engine to comply with this AD. The average labor rate is
$85 per hour. Prorated parts life will cost about $8,900. Based on
these figures, we estimate the cost of this AD on U.S. operators to be
$766,920.
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 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 AD will not have federalism implications
under Executive Order 13132. This AD will 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 AD:
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); 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (phone: 800-647-5527) is provided in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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 AD:
2013-03-21 Pratt & Whitney Canada Corp.: Amendment 39-17355; Docket
No. FAA-2012-0942; Directorate Identifier 2012-NE-24-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective March 26,
2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Pratt & Whitney Canada Corp. (P&WC) model
PW206B, PW206B2, PW206C, PW207C, PW207D, PW207D1, PW207D2, and
PW207E turboshaft engines.
(d) Reason
This AD was prompted by the discovery that certain power turbine
(PT) disks, part number (P/N) 3044188-01, made to specific heat
codes that may not achieve the established maximum in-service life
when installed in Turbomachinery Assembly P/N 3058588. The PT disk
in-service life for engines using this specific PT disk and
compressor turbine vane combination is reduced when operated in a
particular temperature and speed environment. We are issuing this AD
to prevent possible uncontained PT disk failure and loss of
helicopter control.
(e) Actions and Compliance
Unless already done, do the following actions.
(f) Affected PT Disks Installed With Turbomachinery Assembly P/N
3058588 Installation
(1) For any PT disk P/N 3044188-01 that is listed by serial
number (S/N) in Table 1 of P&WC Alert Service Bulletin (ASB) No.
PW200-72-A28311, Revision 2, dated July 24, 2012, and, that is
installed or that had previously been installed with Turbomachinery
Assembly P/N 3058588 installation, do the following:
(i) Remove the PT disk P/N 3044188-01 from service before it
reaches 10,000 cycles-since-new (CSN).
(ii) Re-identify the PT disk to P/N 3072542-01, at the next
engine shop visit, not to exceed 10,000 CSN on the PT disk, before
reinstalling it in any engine. Use paragraphs 3.B.(1) through
3.B.(1)(b)4 of the Accomplishment Instructions of P&WC ASB No.
PW200-72-A28311, Revision 2, dated July 24, 2012, to do the re-
identification.
(iii) After re-identification of the PT disk to P/N 3072542-01,
retain the total cycles accumulated as P/N 3044188-01. The cycles
remaining on the re-identified P/N 3072542-01 PT disk must be
calculated using the difference between the published life limit of
P/N 3072542-01 and the total number of cycles accumulated as P/N
3044188-01. The maximum in-service life of PT disk, P/N 3072542-01,
is 10,000 CSN.
(2) After the effective date of this AD, do not install any PT
disk, P/N 3044188-01, that is listed in Table 1 of P&WC ASB No.
PW200-72-A28311, Revision 2, dated July 24, 2012, in any engine with
Turbomachinery Assembly P/N 3058588 installation, unless the PT disk
has been re-identified to P/N 3072542-01. Use paragraphs 3.B.(1)
through 3.B.(1)(b)4 of the Accomplishment Instructions of P&WC ASB
No. PW200-72-A28311, Revision 2, dated July 24, 2012, to do the PT
disk re-identification.
(g) Credit for Actions Accomplished in Accordance With Previous Service
Information
You may take credit for the re-identification of the PT disk
that is required by this AD if you performed the re-identification
before the effective date of this AD using P&WC ASB No. PW200-72-
A28311, dated March 1, 2012, or P&WC ASB No. PW200-72-A28311,
Revision 1, dated March 22, 2012.
(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 James Lawrence,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington, MA
01803; phone: 781-238-7176; fax: 781-238-7199; email:
james.lawrence@faa.gov.
(2) Refer to Transport Canada AD CF-2012-23, dated July 26,
2012, for related information.
(3) The Engine Maintenance Manual (EMM) Temporary Revisions
(TRs) listed in Table 1 to paragraph (i)(3) of this AD pertain to
the subject of this AD.
[[Page 11567]]
Table 1 to Paragraph (i)(3)--EMM TRs
------------------------------------------------------------------------
EMM P/Ns: TR Nos.:
------------------------------------------------------------------------
3071602.................................. AL-3, AL-4
3043612.................................. AL-12, AL-13
3043322.................................. AL-16
3039732.................................. AL-18, AL-19
3038324.................................. AL-20
------------------------------------------------------------------------
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Pratt & Whitney Canada Corp. Alert Service Bulletin No.
PW200-72-A28311, Revision 2, dated July 24, 2012.
(ii) Reserved.
(3) For service information identified in this AD, contact Pratt
& Whitney Canada Corp., 1000 Marie-Victorin, Longueuil, Quebec,
Canada, J4G 1A1; phone: 800-268-8000; fax: 450-647-2888; Web site:
www.pwc.ca.
(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.
(5) You may view this service information at the National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, call 202-741-6030, or go to:
https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on February 7, 2013.
Robert J. Ganley,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2013-03412 Filed 2-15-13; 8:45 am]
BILLING CODE 4910-13-P
