Airworthiness Directives; Pratt & Whitney (PW) JT9D-7 Series Turbofan Engines, 14458-14460 [E9-6749]
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14458
Federal Register / Vol. 74, No. 60 / Tuesday, March 31, 2009 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
DATES: This AD becomes effective May
5, 2009. The Director of the Federal
Register approved the incorporation by
reference of certain publications listed
in the regulations as of May 5, 2009.
ADDRESSES: You can get the service
information identified in this AD from
Pratt & Whitney, 400 Main St., East
Hartford, CT 06108; telephone (860)
565–8770; fax (860) 565–4503.
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:
Kevin Dickert, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: kevin.dickert@faa.gov;
telephone (781) 238–7117, fax (781)
238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to PW models JT9D–7, –7A,
–7AH, –7H, –7F, and –7J turbofan
engines. We published the proposed AD
in the Federal Register on July 10, 2008
(73 FR 39627). That action proposed to
require an initial and repetitive
borescope inspection of the 2nd stage
HPT vane assembly.
Federal Aviation Administration
Examining the AD Docket
PART 585—PROHIBITED SERVICE AT
SAVINGS AND LOAN HOLDING
COMPANIES
1. The authority citation for 12 CFR
part 585 continues to read as follows:
■
Authority: 12 U.S.C. 1462, 1462a, 1463,
1464, 1467a, and 1829(e).
2. Revise § 585.100(b)(2) introductory
text to read as follows
■
§ 585.100 Who is exempt from the
prohibition under this part?
*
*
*
*
*
(b) Temporary exemption. * * *
(2) This exemption expires on
September 30, 2009, unless the savings
and loan holding company or the person
files an application seeking a case-bycase exemption for the person under
§ 585.110 by that date. If the savings and
loan holding company or the person
files such an application, the temporary
exemption expires on:
*
*
*
*
*
Dated: March 25, 2009.
By the Office of Thrift Supervision.
Scott M. Polakoff,
Acting Director.
[FR Doc. E9–7202 Filed 3–30–09; 8:45 am]
BILLING CODE
14 CFR Part 39
[Docket No. FAA–2008–0759; Directorate
Identifier 2008–NE–02–AD; Amendment 39–
15824; AD 2009–04–18]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney (PW) JT9D–7 Series Turbofan
Engines
tjames on PRODPC61 with RULES
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for PW
models JT9D–7, –7A, –7AH, –7H, –7F,
and –7J turbofan engines. This AD
requires initial and repetitive borescope
inspections of the 2nd stage highpressure turbine (HPT) rotor and stator
assembly. This AD results from an
uncontained failure of a 2nd stage HPT
rotor disk that caused the engine to
separate from the airplane. We are
issuing this AD to prevent failure of the
2nd stage HPT rotor disk, which could
result in uncontained engine failure,
damage to the airplane, and the engine
separating from the airplane.
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14:33 Mar 30, 2009
Jkt 217001
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 (telephone
(800) 647–5527) is provided in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment received.
One commenter asks us to change the
compliance time from ‘‘cycles-sinceoverhaul’’ to ‘‘cycles-since-last
installation of the second stage HPT
vanes.’’ The commenter states that
second stage HPT vanes might be
removed and replaced at times other
than module overhaul, such as for
module repair.
We agree. We changed paragraph (f) of
the proposed AD from ‘‘Within 100
cycles-in-service (CIS) after the effective
date of this AD, or within 1,000 CIS
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
after the last HPT module overhaul
* * *’’ to ‘‘Within 100 cycles-in-service
(CIS) after the effective date of this AD,
or within 1,000 CIS after the last
installation of the second stage HPT
vanes * * *’’
Conclusion
We have carefully reviewed the
available data, including the comment
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect
240 engines installed on airplanes of
U.S. registry. We also estimate that it
will take about 5 work-hours per engine
to perform the proposed actions, that
each engine might require two
inspections, and that the average labor
rate is $80 per work-hour. Based on
these figures, we estimate the total cost
of the AD to U.S. operators to be
$192,000.
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 have 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 that this AD:
E:\FR\FM\31MRR1.SGM
31MRR1
14459
Federal Register / Vol. 74, No. 60 / Tuesday, March 31, 2009 / Rules and Regulations
(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); 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 summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary at the address listed
under ADDRESSES.
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 Federal Aviation Administration
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 airworthiness
directive:
■
2009–04–18 Pratt & Whitney: Amendment
39–15824. Docket No. FAA–2008–0759;
Directorate Identifier 2008–NE–02–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective May 5, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Pratt & Whitney
(PW) JT9D–7, –7A, –7AH, –7H, –7F, and –7J
turbofan engines. These engines are installed
on, but not limited to, Boeing 747 series
airplanes.
Unsafe Condition
(d) This AD results from an uncontained
failure of a 2nd stage high-pressure turbine
(HPT) rotor disk that caused the engine to
separate from the airplane. We are issuing
this AD to prevent failure of the 2nd stage
HPT rotor disk, which could result in
uncontained engine failure, damage to the
airplane, and the engine separating from the
airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified unless the
actions have already been done.
Initial Borescope Inspection
(f) Within 100 cycles-in-service (CIS) after
the effective date of this AD, or within 1,000
CIS after the last installation of the second
stage HPT vanes, whichever occurs later, do
the following:
(1) Use the Accomplishment Instructions
of PW Alert Service Bulletin (ASB) JT9D
A6488, Revision 1, dated April 18, 2008, to
borescope-inspect the 2nd stage HPT rotor
and stator assembly either on-wing or in the
shop.
(2) If you see any damage or contact
between the 2nd stage HPT vanes and the
2nd stage HPT rotor, remove the engine from
service.
Repetitive Borescope Inspection
(g) Thereafter, within 1,000 cycles-sincelast inspection, do the following:
(1) Use the Accomplishment Instructions
of PW ASB JT9D A6488 Revision 1, dated
April 18, 2008, to borescope-inspect the 2nd
stage HPT rotor and stator assembly either
on-wing or in the shop.
(2) If you see any damage or contact
between the 2nd stage HPT vanes and the
2nd stage HPT rotor, remove the engine from
service.
Optional Terminating Action
(h) Installing the 2nd stage HPT vanes as
specified in paragraphs 1.B.(1) through
1.B.(32) of the JT9D–7 Engine Manual
Revision 122, dated February 15, 2008,
terminates the repetitive inspection
requirement specified in paragraph (g) of this
AD.
Alternative Methods of Compliance
(i) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Related Information
(j) Contact Kevin Dickert, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: kevin.dickert@faa.gov;
telephone (781) 238–7117, fax (781) 238–
7199, for more information about this AD.
Material Incorporated by Reference
(k) You must use the service information
specified in the following Table 1 to perform
the actions required by this AD. The Director
of the Federal Register approved the
incorporation by reference of the documents
listed in the following Table 1 in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Contact Pratt & Whitney, 400 Main
St., East Hartford, CT 06108; telephone (860)
565–8770; fax (860) 565–4503, for a copy of
this service information. You may review
copies at the FAA, New England Region, 12
New England Executive Park, Burlington,
MA; or 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.
TABLE 1—INCORPORATION BY REFERENCE
Page
Pratt & Whitney JT9D Engine Maintenance Manual PN 770408 .....
Total Pages—36
Pratt & Whitney PW ASB JT9D A6488, Revision 1, dated April 18,
2008.
Total Pages—21
tjames on PRODPC61 with RULES
Service information No.
1001 through 1036 ......................
122
All ................................................
1
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14:33 Mar 30, 2009
Jkt 217001
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Revision
31MRR1
Date
February 15, 2008.
April 18, 2008.
14460
Federal Register / Vol. 74, No. 60 / Tuesday, March 31, 2009 / Rules and Regulations
Issued in Burlington, Massachusetts, on
March 17, 2009.
Francis A. Favara,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. E9–6749 Filed 3–30–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0074; Directorate
Identifier 2007–NM–151–AD; Amendment
39–15863; AD 2009–07–04]
FOR FURTHER INFORMATION CONTACT: Ken
Sujishi, Aerospace Engineer, Cabin
Safety/Mechanical and Environmental
Systems Branch, ANM–150L, FAA, Los
Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood,
California 90712–4137; telephone (562)
627–5353; fax (562) 627–5210.
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model MD–90–30 Airplanes
tjames on PRODPC61 with RULES
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUPPLEMENTARY INFORMATION:
Discussion
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
McDonnell Douglas Model MD–90–30
airplanes. This AD requires modifying
the auxiliary hydraulic power system
(including doing all applicable related
investigative and corrective actions).
This AD results from fuel system
reviews conducted by the manufacturer,
as well as reports of shorted wires in the
right wheel well and evidence of arcing
on the power cables of the auxiliary
hydraulic pump. We are issuing this AD
to prevent shorted wires or electrical
arcing at the auxiliary hydraulic pump,
which could result in a fire in the wheel
well; and to reduce the potential of an
ignition source adjacent to the fuel
tanks, which, in combination with
flammable fuel vapors, could result in a
fuel tank explosion and consequent loss
of the airplane.
DATES: This AD becomes effective May
5, 2009.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of May 5, 2009.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, 3855
Lakewood Boulevard, MC D800–0019,
Long Beach, California 90846–0001;
telephone 206–544–5000, extension 2;
fax 206–766–5683; e-mail
dse.boecom@boeing.com; Internet
https://www.myboeingfleet.com.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
VerDate Nov<24>2008
14:33 Mar 30, 2009
Jkt 217001
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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the 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.
The FAA issued a supplemental
notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an
AD that would apply to certain
McDonnell Douglas Model MD–90–30
airplanes. That supplemental NPRM
was published in the Federal Register
on December 19, 2008 (73 FR 77555).
That supplemental NPRM proposed to
require modifying the auxiliary
hydraulic system (including doing all
applicable related investigative and
corrective actions).
Comments
We provided the public the
opportunity to participate in the
development of this AD. No comments
have been received on the supplemental
NPRM or on the determination of the
cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed in the
supplemental NPRM.
Costs of Compliance
There are about 110 airplanes of the
affected design in the worldwide fleet.
This AD affects about 16 airplanes of
U.S. registry. The actions take between
3 and 7 work-hours per airplane,
depending on the configuration, at an
average labor rate of $80 per work-hour.
Required parts cost up to $5,343 per
airplane. Based on these figures, the
estimated cost of the AD for U.S.
operators is up to $94,448, or $5,903 per
airplane.
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
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 have 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 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); 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.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
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:
■
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31MRR1
]]>Agencies
[Federal Register Volume 74, Number 60 (Tuesday, March 31, 2009)]
[Rules and Regulations]
[Pages 14458-14460]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-6749]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0759; Directorate Identifier 2008-NE-02-AD;
Amendment 39-15824; AD 2009-04-18]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney (PW) JT9D-7 Series
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for PW
models JT9D-7, -7A, -7AH, -7H, -7F, and -7J turbofan engines. This AD
requires initial and repetitive borescope inspections of the 2nd stage
high-pressure turbine (HPT) rotor and stator assembly. This AD results
from an uncontained failure of a 2nd stage HPT rotor disk that caused
the engine to separate from the airplane. We are issuing this AD to
prevent failure of the 2nd stage HPT rotor disk, which could result in
uncontained engine failure, damage to the airplane, and the engine
separating from the airplane.
DATES: This AD becomes effective May 5, 2009. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of May 5, 2009.
ADDRESSES: You can get the service information identified in this AD
from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone
(860) 565-8770; fax (860) 565-4503.
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: Kevin Dickert, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
kevin.dickert@faa.gov; telephone (781) 238-7117, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to PW models JT9D-7, -7A, -
7AH, -7H, -7F, and -7J turbofan engines. We published the proposed AD
in the Federal Register on July 10, 2008 (73 FR 39627). That action
proposed to require an initial and repetitive borescope inspection of
the 2nd stage HPT vane assembly.
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 (telephone (800) 647-5527) is provided in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment received.
One commenter asks us to change the compliance time from ``cycles-
since-overhaul'' to ``cycles-since-last installation of the second
stage HPT vanes.'' The commenter states that second stage HPT vanes
might be removed and replaced at times other than module overhaul, such
as for module repair.
We agree. We changed paragraph (f) of the proposed AD from ``Within
100 cycles-in-service (CIS) after the effective date of this AD, or
within 1,000 CIS after the last HPT module overhaul * * *'' to ``Within
100 cycles-in-service (CIS) after the effective date of this AD, or
within 1,000 CIS after the last installation of the second stage HPT
vanes * * *''
Conclusion
We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect 240 engines installed on
airplanes of U.S. registry. We also estimate that it will take about 5
work-hours per engine to perform the proposed actions, that each engine
might require two inspections, and that the average labor rate is $80
per work-hour. Based on these figures, we estimate the total cost of
the AD to U.S. operators to be $192,000.
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 have 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 that this AD:
[[Page 14459]]
(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); 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 summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration 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:
2009-04-18 Pratt & Whitney: Amendment 39-15824. Docket No. FAA-2008-
0759; Directorate Identifier 2008-NE-02-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 5,
2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Pratt & Whitney (PW) JT9D-7, -7A, -7AH, -
7H, -7F, and -7J turbofan engines. These engines are installed on,
but not limited to, Boeing 747 series airplanes.
Unsafe Condition
(d) This AD results from an uncontained failure of a 2nd stage
high-pressure turbine (HPT) rotor disk that caused the engine to
separate from the airplane. We are issuing this AD to prevent
failure of the 2nd stage HPT rotor disk, which could result in
uncontained engine failure, damage to the airplane, and the engine
separating from the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Initial Borescope Inspection
(f) Within 100 cycles-in-service (CIS) after the effective date
of this AD, or within 1,000 CIS after the last installation of the
second stage HPT vanes, whichever occurs later, do the following:
(1) Use the Accomplishment Instructions of PW Alert Service
Bulletin (ASB) JT9D A6488, Revision 1, dated April 18, 2008, to
borescope-inspect the 2nd stage HPT rotor and stator assembly either
on-wing or in the shop.
(2) If you see any damage or contact between the 2nd stage HPT
vanes and the 2nd stage HPT rotor, remove the engine from service.
Repetitive Borescope Inspection
(g) Thereafter, within 1,000 cycles-since-last inspection, do
the following:
(1) Use the Accomplishment Instructions of PW ASB JT9D A6488
Revision 1, dated April 18, 2008, to borescope-inspect the 2nd stage
HPT rotor and stator assembly either on-wing or in the shop.
(2) If you see any damage or contact between the 2nd stage HPT
vanes and the 2nd stage HPT rotor, remove the engine from service.
Optional Terminating Action
(h) Installing the 2nd stage HPT vanes as specified in
paragraphs 1.B.(1) through 1.B.(32) of the JT9D-7 Engine Manual
Revision 122, dated February 15, 2008, terminates the repetitive
inspection requirement specified in paragraph (g) of this AD.
Alternative Methods of Compliance
(i) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Related Information
(j) Contact Kevin Dickert, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
kevin.dickert@faa.gov; telephone (781) 238-7117, fax (781) 238-7199,
for more information about this AD.
Material Incorporated by Reference
(k) You must use the service information specified in the
following Table 1 to perform the actions required by this AD. The
Director of the Federal Register approved the incorporation by
reference of the documents listed in the following Table 1 in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Contact
Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone
(860) 565-8770; fax (860) 565-4503, for a copy of this service
information. You may review copies at the FAA, New England Region,
12 New England Executive Park, Burlington, MA; or 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.
Table 1--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Service information No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
Pratt & Whitney JT9D Engine 1001 through 1036...... 122 February 15, 2008.
Maintenance Manual PN 770408.
Total Pages--36
Pratt & Whitney PW ASB JT9D A6488, All.................... 1 April 18, 2008.
Revision 1, dated April 18, 2008.
Total Pages--21
----------------------------------------------------------------------------------------------------------------
[[Page 14460]]
Issued in Burlington, Massachusetts, on March 17, 2009.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. E9-6749 Filed 3-30-09; 8:45 am]
BILLING CODE 4910-13-P
