Airworthiness Directives; Pratt & Whitney Turbofan Engines, 43011-43012 [2015-17710]
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Federal Register / Vol. 80, No. 139 / Tuesday, July 21, 2015 / Rules and Regulations
Done in Washington, DC, this 15th day of
July 2015.
Kevin Shea,
Administrator, Animal and Plant Health
Inspection Service.
[FR Doc. 2015–17842 Filed 7–20–15; 8:45 am]
BILLING CODE 3410–34–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–1127; Directorate
Identifier 2014–NE–16–AD; Amendment 39–
18203; AD 2015–14–05]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all Pratt
& Whitney (PW) JT8D–217C and JT8D–
219 turbofan engines. This AD was
prompted by reports of cracking in the
low-pressure turbine (LPT) shaft. This
AD requires removing affected LPT
shafts from service using a drawdown
plan. We are issuing this AD to prevent
failure of the LPT shaft, which could
lead to an uncontained engine failure
and damage to the airplane.
DATES: This AD is effective August 25,
2015.
ADDRESSES: For service information
identified in this 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.
SUMMARY:
asabaliauskas on DSK5VPTVN1PROD with RULES
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–2014–
1127; 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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
VerDate Sep<11>2014
16:53 Jul 20, 2015
Jkt 235001
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: JoAnn Theriault, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: 781–238–7105; fax: 781–238–
7199; email: jo-ann.theriault@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all PW JT8D–217C and JT8D–
219 turbofan engines. The NPRM
published in the Federal Register on
March 2, 2015 (80 FR 11140). The
NPRM was prompted by in-shop
findings of fatigue cracks on the No. 4.5
bearing thread undercut adjacent to the
oil feed holes. The cracks were
discovered during routine fluorescent
penetrant inspections (FPIs). Both shafts
had oil feed hole enlargement rework
accomplished. The root cause is
increased stress on the fillet of the
thread undercut region in front of the oil
feed holes caused by oil feed hole
rework. The increased stress reduces the
low cycle fatigue life of the shaft. The
NPRM proposed to require removing
affected LPT shafts from service using a
drawdown plan. We are issuing this AD
to prevent failure of the LPT shaft,
which could lead to an uncontained
engine failure and damage to the
airplane.
Related Service Information
We reviewed PW Service Bulletin
(SB) No. JT8D 6504, dated November 5,
2014. The SB contains additional
information regarding removal of the
LPT shaft.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (80 FR 11140,
March 2, 2015) and the FAA’s response
to each comment.
Request To Withdraw the NPRM
Delta Air Lines (DAL) and Allegiant
Air requested that the current LPT shaft
life limit of 25,000 cycles-since-new
(CSN) be retained rather than removing
the LPT shaft from service at 20,000
CSN as proposed in the NPRM. The
commenters stated that reducing the life
limit is unjustified because there has not
been an in-service LPT shaft failure of
the type addressed.
We do not agree. We determined that
an acceptable level of safety would not
be maintained if LPT shafts are allowed
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
43011
to remain in service until accumulating
25,000 CSN. We reduced the life of the
LPT shaft to 20,000 CSN to minimize
the risk of LPT shaft failure. We did not
change this AD.
Proposal To Increase Repetitive
Inspections
DAL and Allegiant Air proposed
increasing the occurrence of FPIs to
increase the opportunity of identifying
LPT shaft cracks. The commenters
stated that routine FPIs have been
successful in detecting LPT shaft cracks
in the past.
We do not agree. Recurring
inspections are not adequate as a final
corrective action. Relying on recurring
FPIs to detect cracks, rather than shaft
removal at 20,000 CSN, would likely
result in an increased number of LPT
shafts cracking in service, a greater risk
of undetected cracked shafts being
returned to service, and an unacceptable
risk of shaft failure. We determined that
long-term continued operational safety
is enhanced by a terminating action that
removes affected shafts from service
rather than by increasing the occurrence
of repetitive inspections. We did not
change this AD.
Request To Reduce Costs
DAL and Allegiant Air requested
retaining the existing life limit or
increasing the occurrence of
inspections. The commenters stated that
the life reduction in the NPRM places
an undue economic burden on the U.S.
fleet by forcing early engine removals.
We do not agree. We mitigated the
operational and financial impacts by
providing a drawdown plan rather than
requiring removal before further flight,
while providing an acceptable level of
safety. We did not change this AD.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
as proposed.
Costs of Compliance
We estimate that this AD will affect
about 744 engines installed on airplanes
of U.S. registry. The average labor rate
is $85 per hour. We estimate the prorated replacement cost would be
$28,230. We also estimate that shaft
replacement would be accomplished
during an engine shop visit at no
additional labor cost. Based on these
figures, we estimate the cost of the
proposed AD on U.S. operators to be
$21,003,120.
E:\FR\FM\21JYR1.SGM
21JYR1
43012
Federal Register / Vol. 80, No. 139 / Tuesday, July 21, 2015 / Rules and Regulations
Authority for This Rulemaking
§ 39.13
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
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 that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
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.
asabaliauskas on DSK5VPTVN1PROD with RULES
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.
VerDate Sep<11>2014
16:53 Jul 20, 2015
Jkt 235001
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
2015–14–05 Pratt & Whitney: Amendment
39–18203; Docket No. FAA–2014–1127;
Directorate Identifier 2014–NE–16–AD.
(a) Effective Date
This AD is effective August 25, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Pratt & Whitney
(PW) JT8D–217C and JT8D–219 turbofan
engines with low-pressure turbine (LPT)
shaft part numbers 783319, 783319–001,
783319–003, 783319–004, 783320, 783320–
001, 783320–003, 783320–004, 820514–001,
820514–003, 820514–004, or 820514–005,
installed.
(d) Unsafe Condition
This AD was prompted by reports of
cracking in the LPT shaft. We are issuing this
AD to prevent failure of the LPT shaft, which
could lead to an uncontained engine failure
and damage to the airplane.
(e) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(1) If the LPT shaft has 15,000 or fewer
cycles-since-new (CSN) on the effective date
of this AD, remove it from service before it
accumulates 20,000 CSN.
(2) If the LPT shaft has more than 15,000
CSN on the effective date of this AD, remove
it from service before it accumulates 5,000
additional cycles in service, or at the next
piece-part exposure after accumulating
20,000 CSN, whichever occurs first.
(3) After the effective date of this AD, do
not install any LPT shaft listed in paragraph
(c) of this AD that is at piece-part exposure
and exceeds the new life limit of 20,000 CSN,
into any engine.
(f) Definition
For the purpose of this AD, piece-part
exposure is when the LPT shaft is completely
disassembled from the engine.
(g) 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. You may email your
request to: ANE-AD-AMOC@faa.gov.
(h) Related Information
(1) For more information about this AD,
contact Jo-Ann Theriault, Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; phone: 781–238–7105; fax: 781–238–
7199; email: jo-ann.theriault@faa.gov.
(2) PW Service Bulletin No. JT8D 6504,
dated November 5, 2014, which is not
incorporated by reference in this AD, can be
obtained from PW using the contact
information in paragraph (h)(3) of this AD.
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
(3) For service information identified in
this AD, contact Pratt & Whitney, 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.
(i) Material Incorporated by Reference
None.
Issued in Burlington, Massachusetts, on
June 26, 2015.
Ann C. Mollica,
Acting Directorate Manager, Engine &
Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2015–17710 Filed 7–20–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Parts 91 and 119
[Docket No. FAA–FAA–2015–0517]
Policy Regarding Living History Flight
Experience Exemptions for Passenger
Carrying Operations Conducted for
Compensation and Hire in Other Than
Standard Category Aircraft
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of policy statement.
AGENCY:
With this document, the
Federal Aviation Administration (FAA)
cancels all previous agency policies
pertaining to the carriage of passengers
for compensation on Living History
Flight Experience (LHFE) flights. This
policy statement announces the end of
FAA moratorium on new petitions for
exemption, or amendments to
exemptions from certain sections of
Title 14, Code of Federal Regulations
(14 CFR) for the purpose of carrying
passengers for compensation or hire on
LHFE Flights.
DATES: The moratorium will end on July
21, 2015.
FOR FURTHER INFORMATION CONTACT:
General Aviation and Commercial
Division, General Aviation Operations
Branch (AFS–830), Flight Standards
Service, FAA, 800 Independence
Avenue SW., Washington, DC 20591;
telephone (202) 267–1100; 9-AFS-800Correspondence-Mail@faa.gov.
SUPPLEMENTARY INFORMATION:
SUMMARY:
Background
The FAA has historically found the
preservation of U.S. aviation history to
be in the public interest, including
preservation of certain former military
E:\FR\FM\21JYR1.SGM
21JYR1
]]>Agencies
[Federal Register Volume 80, Number 139 (Tuesday, July 21, 2015)]
[Rules and Regulations]
[Pages 43011-43012]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-17710]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-1127; Directorate Identifier 2014-NE-16-AD;
Amendment 39-18203; AD 2015-14-05]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Pratt & Whitney (PW) JT8D-217C and JT8D-219 turbofan engines. This AD
was prompted by reports of cracking in the low-pressure turbine (LPT)
shaft. This AD requires removing affected LPT shafts from service using
a drawdown plan. We are issuing this AD to prevent failure of the LPT
shaft, which could lead to an uncontained engine failure and damage to
the airplane.
DATES: This AD is effective August 25, 2015.
ADDRESSES: For service information identified in this 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 by searching for and locating Docket No. FAA-2014-
1127; 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 AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-
5527) is Document Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Jo-Ann Theriault, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; phone: 781-238-7105;
fax: 781-238-7199; email: jo-ann.theriault@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all PW JT8D-217C and JT8D-
219 turbofan engines. The NPRM published in the Federal Register on
March 2, 2015 (80 FR 11140). The NPRM was prompted by in-shop findings
of fatigue cracks on the No. 4.5 bearing thread undercut adjacent to
the oil feed holes. The cracks were discovered during routine
fluorescent penetrant inspections (FPIs). Both shafts had oil feed hole
enlargement rework accomplished. The root cause is increased stress on
the fillet of the thread undercut region in front of the oil feed holes
caused by oil feed hole rework. The increased stress reduces the low
cycle fatigue life of the shaft. The NPRM proposed to require removing
affected LPT shafts from service using a drawdown plan. We are issuing
this AD to prevent failure of the LPT shaft, which could lead to an
uncontained engine failure and damage to the airplane.
Related Service Information
We reviewed PW Service Bulletin (SB) No. JT8D 6504, dated November
5, 2014. The SB contains additional information regarding removal of
the LPT shaft.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (80
FR 11140, March 2, 2015) and the FAA's response to each comment.
Request To Withdraw the NPRM
Delta Air Lines (DAL) and Allegiant Air requested that the current
LPT shaft life limit of 25,000 cycles-since-new (CSN) be retained
rather than removing the LPT shaft from service at 20,000 CSN as
proposed in the NPRM. The commenters stated that reducing the life
limit is unjustified because there has not been an in-service LPT shaft
failure of the type addressed.
We do not agree. We determined that an acceptable level of safety
would not be maintained if LPT shafts are allowed to remain in service
until accumulating 25,000 CSN. We reduced the life of the LPT shaft to
20,000 CSN to minimize the risk of LPT shaft failure. We did not change
this AD.
Proposal To Increase Repetitive Inspections
DAL and Allegiant Air proposed increasing the occurrence of FPIs to
increase the opportunity of identifying LPT shaft cracks. The
commenters stated that routine FPIs have been successful in detecting
LPT shaft cracks in the past.
We do not agree. Recurring inspections are not adequate as a final
corrective action. Relying on recurring FPIs to detect cracks, rather
than shaft removal at 20,000 CSN, would likely result in an increased
number of LPT shafts cracking in service, a greater risk of undetected
cracked shafts being returned to service, and an unacceptable risk of
shaft failure. We determined that long-term continued operational
safety is enhanced by a terminating action that removes affected shafts
from service rather than by increasing the occurrence of repetitive
inspections. We did not change this AD.
Request To Reduce Costs
DAL and Allegiant Air requested retaining the existing life limit
or increasing the occurrence of inspections. The commenters stated that
the life reduction in the NPRM places an undue economic burden on the
U.S. fleet by forcing early engine removals.
We do not agree. We mitigated the operational and financial impacts
by providing a drawdown plan rather than requiring removal before
further flight, while providing an acceptable level of safety. We did
not change this AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD as proposed.
Costs of Compliance
We estimate that this AD will affect about 744 engines installed on
airplanes of U.S. registry. The average labor rate is $85 per hour. We
estimate the pro-rated replacement cost would be $28,230. We also
estimate that shaft replacement would be accomplished during an engine
shop visit at no additional labor cost. Based on these figures, we
estimate the cost of the proposed AD on U.S. operators to be
$21,003,120.
[[Page 43012]]
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
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 that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under 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.
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 airworthiness
directive (AD):
2015-14-05 Pratt & Whitney: Amendment 39-18203; Docket No. FAA-2014-
1127; Directorate Identifier 2014-NE-16-AD.
(a) Effective Date
This AD is effective August 25, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Pratt & Whitney (PW) JT8D-217C and JT8D-
219 turbofan engines with low-pressure turbine (LPT) shaft part
numbers 783319, 783319-001, 783319-003, 783319-004, 783320, 783320-
001, 783320-003, 783320-004, 820514-001, 820514-003, 820514-004, or
820514-005, installed.
(d) Unsafe Condition
This AD was prompted by reports of cracking in the LPT shaft. We
are issuing this AD to prevent failure of the LPT shaft, which could
lead to an uncontained engine failure and damage to the airplane.
(e) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(1) If the LPT shaft has 15,000 or fewer cycles-since-new (CSN)
on the effective date of this AD, remove it from service before it
accumulates 20,000 CSN.
(2) If the LPT shaft has more than 15,000 CSN on the effective
date of this AD, remove it from service before it accumulates 5,000
additional cycles in service, or at the next piece-part exposure
after accumulating 20,000 CSN, whichever occurs first.
(3) After the effective date of this AD, do not install any LPT
shaft listed in paragraph (c) of this AD that is at piece-part
exposure and exceeds the new life limit of 20,000 CSN, into any
engine.
(f) Definition
For the purpose of this AD, piece-part exposure is when the LPT
shaft is completely disassembled from the engine.
(g) 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. You may email your request to: ANE-AD-AMOC@faa.gov.
(h) Related Information
(1) For more information about this AD, contact Jo-Ann
Theriault, Aerospace Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New England Executive Park,
Burlington, MA 01803; phone: 781-238-7105; fax: 781-238-7199; email:
jo-ann.theriault@faa.gov.
(2) PW Service Bulletin No. JT8D 6504, dated November 5, 2014,
which is not incorporated by reference in this AD, can be obtained
from PW using the contact information in paragraph (h)(3) of this
AD.
(3) For service information identified in this AD, contact Pratt
& Whitney, 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.
(i) Material Incorporated by Reference
None.
Issued in Burlington, Massachusetts, on June 26, 2015.
Ann C. Mollica,
Acting Directorate Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2015-17710 Filed 7-20-15; 8:45 am]
BILLING CODE 4910-13-P
