Airworthiness Directives; Pratt & Whitney JT9D Series Turbofan Engines, 72130-72132 [2011-30062]
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72130
Federal Register / Vol. 76, No. 225 / Tuesday, November 22, 2011 / Proposed Rules
(2) Contact Alan Strom, Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; phone: (781) 238–7143; fax: (781)
238–7199; email: alan.strom@faa.gov, for
more information about this AD.
(3) For service information identified in
this AD, contact Thielert Aircraft Engines
GmbH, Platanenstrasse 14 D–09350,
Lichtenstein, Germany, phone: +49–37204–
696–0; fax: +49–37204–696–2912; email:
info@centurion-engines.com. You may
review copies of the referenced 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
November 10, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
Examining the AD Docket
[FR Doc. 2011–30059 Filed 11–21–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27023; Directorate
Identifier 98–ANE–47–AD]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney JT9D Series Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to all Pratt & Whitney (PW)
JT9D series turbofan engines. The
existing AD currently requires revisions
to the Airworthiness Limitations
Section (ALS) of the manufacturer’s
Instructions for Continued
Airworthiness (ICA) to include required
enhanced inspection of selected critical
life-limited parts at each piece-part
opportunity. Since we issued that AD,
PW has added mandatory inspections
for certain critical life-limited parts.
This proposed AD would require
additional revisions to the JT9D series
engines ALS sections of the
manufacturer’s ICA. This proposed AD
results from the need to require
enhanced inspection of selected critical
life-limited parts of JT9D series engines.
We are proposing this AD to prevent
critical life-limited rotating engine part
failure, which could result in an
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SUMMARY:
VerDate Mar<15>2010
13:44 Nov 21, 2011
Jkt 226001
uncontained engine failure and damage
to the airplane.
DATES: We must receive comments on
this proposed AD by January 23, 2012.
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.
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:
Stephen Sheely, Aerospace Engineer,
Engine & Propeller Directorate, FAA, 12
New England Executive Park,
Burlington, MA 01803; phone: (781)
238–7750; fax: (781) 238–7199; email:
stephen.k.sheely@faa.gov.
substantive verbal contact we receive
about this proposed AD.
Discussion
On March 1, 2007, we issued AD
2007–05–17, Amendment 39–14978 (72
FR 10350, March 8, 2007), for all PW
JT9D series turbofan engines. That AD
requires revisions to the ALS of the
manufacturer’s ICA to include required
enhanced inspection of selected critical
life-limited parts at each piece-part
opportunity. We issued that AD to
prevent critical life-limited rotating
engine part failure, which could result
in an uncontained engine failure and
damage to the airplane.
Actions Since Existing AD (72 FR
10350, March 8, 2007) Was Issued
Since we issued AD 2007–05–17, an
FAA study of in-service events
involving uncontained failures of
critical rotating engine parts has
indicated the need for additional
mandatory inspections. The mandatory
inspections are needed to identify those
critical rotating parts with conditions
which, if allowed to continue in service,
could result in uncontained engine
failures. This proposal would require
revisions to the JT9D series engines ALS
sections of the manufacturer’s manuals
and an air carrier’s approved continuous
airworthiness maintenance program to
incorporate additional inspection
requirements.
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.
SUPPLEMENTARY INFORMATION:
Proposed AD Requirements
Comments Invited
This proposed AD would retain all of
the requirements of AD 2007–05–17 (72
FR 10350, March 8, 2007). This
proposed AD would supersede AD
2007–05–17 to require the following
additional inspections:
• Adding eddy current inspections
(ECIs) for web cooling holes in highpressure turbine (HPT) stage 1 disks
installed in engine models JT9D–3A, –7,
–7A, –7AH, –7F, –7H, –7J, –20, and –20J
engines;
• Adding ECIs for web cooling holes
and tierod holes in HPT stage 2 disks
installed in JT9D–59A and –70A
engines;
• Adding ECIs for web cooling holes
and tierod holes in HPT stage 2 disks
installed in JT9D–7Q and –7Q3 engines;
• Adding ECIs for web cooling holes
in HPT stage 2 disks, and for fan hub
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–27023; Directorate Identifier
98–ANE–47–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
PO 00000
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Fmt 4702
Sfmt 4702
E:\FR\FM\22NOP1.SGM
22NOP1
Federal Register / Vol. 76, No. 225 / Tuesday, November 22, 2011 / Proposed Rules
slots, installed in JT9D–7R4 engines;
and
• Adding ECIs for web cooling holes
and tierod holes in HPT stage 2 disks
installed in JT9D–7R4D, –7R4D1,
–7R4E, and –7R4E1 engines.
This proposed AD would also add the
Engine Manual Inspection Task and Sub
Task Number references for these
inspections.
Identifying the Part Nomenclatures and
Inspections Added
For reference, the part nomenclatures
and inspections added to the table in
the compliance section of this proposed
AD are identified by two asterisks (**)
that precede the part nomenclature.
Costs of Compliance
We estimate that 438 JT9D series
engines are installed on airplanes of
U.S. registry and would be affected by
this proposed AD. We also estimate that
about 4 work hours per engine are
needed to perform the proposed actions,
and that the average labor rate is $85 per
work hour. Since this is an added
inspection requirement that will be part
of the normal maintenance cycle, no
additional parts costs are involved.
Based on these figures, we estimate the
total cost of the proposed AD to U.S.
operators to be $148,920.
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
erowe on DSK2VPTVN1PROD with PROPOSALS
Engine model
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
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, 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.
§ 39.13
Pratt & Whitney: Docket No. FAA–2007–
27023; Directorate Identifier 98–ANE–
47–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by January 23, 2012.
(b) Affected ADs
This AD supersedes AD 2007–05–17,
Amendment 39–14978 (72 FR 10350, March
8, 2007).
(c) Applicability
This AD applies to Pratt & Whitney (PW)
JT9D–3A, –7, –7A, –7H, –7AH, –7F, –7J,
–20J, –59A, –70A, –7Q, –7Q3, –7R4D,
–7R4D1, –7R4E, –7R4E1, –7R4E4, –7R4G2,
and –7R4H1 series turbofan engines.
(d) Unsafe Condition
This AD results from the need to require
enhanced inspection of selected critical lifelimited parts of JT9D series turbofan engines.
We are issuing this AD to prevent critical
life-limited rotating engine part failure,
which could result in an uncontained engine
failure and damage to the airplane.
(e) Compliance
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Comply with this AD within the
compliance times specified, unless already
done.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
Within the next 30 days after the effective
date of this AD, add the following section to
the Airworthiness Limitations Section (ALS)
of your copy of the manufacturer’s
Instructions for Continued Airworthiness
(ICA) and, for air carrier operations, to your
continuous airworthiness air carrier
maintenance program:
‘‘MANDATORY INSPECTIONS’’
(1) Inspect the following life-limited parts
at each piece-part opportunity in accordance
with the instructions provided in the
applicable manual provisions:
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.
Engine manual part No.
(P/N)
(f) Inspections
Part nomenclature
59A/70A ...........................754459 ...........................All Fan Hubs ...........................................................
All HPC Stage 5–15 Disks and Rear Compressor
Drive Turbine Shafts.
All HPT Stage 1–2 Disks and Hubs .......................
13:44 Nov 21, 2011
Jkt 226001
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2007–05–17, Amendment 39–14978 (72
FR 10350, March 8, 2007), and adding
the following new AD:
3A/7/7A/7AH/7F/7H/7J/20/ *646028 (or the equiva- All Fan Hubs ...........................................................
20J.
lent customized
versions, 770407 and
770408).
All HPC Stage 5–15 Disks and Rear Compressor
Drive Turbine Shafts.
All HPT Stage 1–2 Disks and Hubs .......................
**All HPT Stage 1 Disk Web Cooling Holes ...........
All HPT Stage 2 Disk Web Tierod Holes ................
All LPT Stage 3–6 Disks and Hubs ........................
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72131
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Fmt 4702
Sfmt 4702
E:\FR\FM\22NOP1.SGM
Inspect per
manual section
Inspection/check
72–31–04 Inspection-02.
72–35–00 Inspection-03.
72–51–00
72–51–02
72–51–02
72–52–00
Inspection-03.
Inspection-06.
Inspection-05.
Inspection-03.
72–31–00 Check-00.
72–35–00 Check-00.
72–51–00 Check-03.
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72132
Federal Register / Vol. 76, No. 225 / Tuesday, November 22, 2011 / Proposed Rules
Engine model
Engine manual part No.
(P/N)
Inspect per
manual section
Part nomenclature
Inspection/check
...................................................................................All HPT Stage 1 Disk Web Cooling Holes ..............
**All HPT Stage 2 Disk Tierod and Web Cooling
Holes.
All LPT Stage 3–6 Disks and Hubs ........................
72–51–02 Check-03.
72–51–02 Check-04.
7Q/7Q3 .............................777210 ...........................All Fan Hubs ...........................................................
All HPC Stage 5–15 Disks and Rear Compressor
Drive Turbine Shafts.
All HPT Stage 1–2 Disks and Hubs All HPT Stage
1 Disk Web Cooling Holes.
**All HPT Stage 2 Disk Tierod and Web Cooling
Holes.
All LPT Stage 3–6 Disks and Hubs ........................
72–31–00 Inspection-03.
72–35–00 Inspection-03.
7R4 ALL ...........................785058, 785059, and
789328.
All Fan Hubs ...........................................................
72–31–00 Inspection/Check-03.
**All Fan Hub Slots .................................................
All HPC Stage 5–15 Disks and Rear Compressor
Drive Turbine Shafts.
All HPT Stage 1–2 Disks and Hubs .......................
All LPT Stage 3–6 Disks and Hubs ........................
**All HPT Stage 2 Disk Tierod and Web Cooling
Holes.
72–31–01 Inspection/Check-02.
72–35–00 Inspection/Check 03.
7R4D/D1/E/E1 ..................785058 and 785059 .......All HPT Stage 1 Disk Web Cooling Holes ..............
**All HPT Stage 2 Disk Tierod and Web Cooling
Holes.
72–51–06 Inspection/Check-02.
72–51–07 Inspection/Check-02.
72–52–00 Check-03.
72–51–00 Inspection-03.
72–51–06 Inspection-03.
72–51–07 Inspection-03.
72–52–00 Inspection-03.
72–51–00 Inspection/Check 03.
72–52–00 Inspection/Check 03
72–51–07 Inspection/Check-02.
* P/N 770407 and 770408 are customized versions of P/N 646028 engine manual.
** Two asterisks identify the part nomenclatures and inspections added to the table.
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(2) For the purposes of these mandatory
inspections, piece-part opportunity means:
(i) The part is considered completely
disassembled when disassembly is in
accordance with the disassembly instructions
in the manufacturer’s engine shop manual;
and
(ii) The part has accumulated more than
100 cycles-in-service since the last piece-part
opportunity inspection, provided that the
part was not damaged or related to the cause
for its removal from the engine.’’
(g) Except as provided in paragraph (h) of
this AD, and notwithstanding contrary
provisions in section 43.16 of the Federal
Aviation Regulations (14 CFR 43.16), these
mandatory inspections shall be performed
only in accordance with the ALS of the
manufacturer’s ICA.
(g) Alternative Methods of Compliance
(AMOC)
(1) You must perform these mandatory
inspections using the ALS of the ICA and the
applicable Engine Manual, unless you
receive approval to use an AMOC under
paragraph (h)(2) of this AD. Section 43.16 of
the Federal Aviation Regulations (14 CFR
43.16) may not be used to approve alternative
methods of compliance or adjustments to the
times in which these inspections must be
performed.
(2) 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.
(h) Maintaining Records of the Mandatory
Inspections
(1) You have met the requirements of this
AD when you revise your copy of the ALS
VerDate Mar<15>2010
13:44 Nov 21, 2011
Jkt 226001
of the manufacturer’s ICA as specified in
paragraph (f) of this AD. For air carriers
operating under part 121 of the Federal
Aviation Regulations (14 CFR part 121), you
have met the requirements of this AD when
you modify your continuous airworthiness
air carrier maintenance program as specified
in paragraph (f) of this AD. You do not need
to record each piece-part inspection as
compliance to this AD, but you must
maintain records of those inspections
according to the regulations governing your
operation. For air carriers operating under
part 121, you may use either the system
established to comply with section 121.369
or an alternative accepted by your principal
maintenance inspector if that alternative:
(i) Includes a method for preserving and
retrieving the records of the inspections
resulting from this AD;
(ii) Meets the requirements of section
121.369(c); and
(iii) Maintains the records either
indefinitely or until the work is repeated.
(2) These record keeping requirements
apply only to the records used to document
the mandatory inspections required as a
result of revising the ALS of the
manufacturer’s ICA as specified in paragraph
(f) of this AD. These record keeping
requirements do not alter or amend the
record keeping requirements for any other
AD or regulatory requirement.
(i) Related Information
For more information about this AD,
contact Stephen Sheely, Aerospace Engineer,
Engine & Propeller Directorate, FAA, 12 New
England Executive Park, Burlington, MA
01803; phone: (781) 238–7750; fax: (781)
238–7199; email: stephen.k.sheely@faa.gov.
PO 00000
Frm 00005
Fmt 4702
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Issued in Burlington, Massachusetts, on
November 15, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 2011–30062 Filed 11–21–11; 8:45 am]
BILLING CODE 4910–13–P
FEDERAL TRADE COMMISSION
16 CFR Part 301
Regulations Under The Fur Products
Labeling Act
Federal Trade Commission.
Announcement of public
hearing.
AGENCY:
ACTION:
The Federal Trade
Commission (‘‘FTC’’ or ‘‘Commission’’)
will hold a public hearing on December
6, 2011, as part of the congressionally
mandated review of its Fur Products
Name Guide. The hearing will allow
interested parties to present views on
whether the Commission should amend
the Fur Products Name Guide.
DATES: The hearing will be held on
Tuesday, December 6, 2011, from 9 a.m.
to 1 p.m. at the FTC’s Satellite Building
Conference Center, located at 601 New
Jersey Avenue NW., Washington, DC
20001.
REGISTRATION INFORMATION: The hearing
is open to the public, and there is no fee
for attendance. If resources are available
SUMMARY:
E:\FR\FM\22NOP1.SGM
22NOP1
]]>Agencies
[Federal Register Volume 76, Number 225 (Tuesday, November 22, 2011)]
[Proposed Rules]
[Pages 72130-72132]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-30062]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27023; Directorate Identifier 98-ANE-47-AD]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney JT9D Series Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to all Pratt & Whitney (PW) JT9D series turbofan
engines. The existing AD currently requires revisions to the
Airworthiness Limitations Section (ALS) of the manufacturer's
Instructions for Continued Airworthiness (ICA) to include required
enhanced inspection of selected critical life-limited parts at each
piece-part opportunity. Since we issued that AD, PW has added mandatory
inspections for certain critical life-limited parts. This proposed AD
would require additional revisions to the JT9D series engines ALS
sections of the manufacturer's ICA. This proposed AD results from the
need to require enhanced inspection of selected critical life-limited
parts of JT9D series engines. We are proposing this AD to prevent
critical life-limited rotating engine part failure, which could result
in an uncontained engine failure and damage to the airplane.
DATES: We must receive comments on this proposed AD by January 23,
2012.
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.
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: Stephen Sheely, Aerospace Engineer,
Engine & Propeller Directorate, FAA, 12 New England Executive Park,
Burlington, MA 01803; phone: (781) 238-7750; fax: (781) 238-7199;
email: stephen.k.sheely@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
27023; Directorate Identifier 98-ANE-47-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On March 1, 2007, we issued AD 2007-05-17, Amendment 39-14978 (72
FR 10350, March 8, 2007), for all PW JT9D series turbofan engines. That
AD requires revisions to the ALS of the manufacturer's ICA to include
required enhanced inspection of selected critical life-limited parts at
each piece-part opportunity. We issued that AD to prevent critical
life-limited rotating engine part failure, which could result in an
uncontained engine failure and damage to the airplane.
Actions Since Existing AD (72 FR 10350, March 8, 2007) Was Issued
Since we issued AD 2007-05-17, an FAA study of in-service events
involving uncontained failures of critical rotating engine parts has
indicated the need for additional mandatory inspections. The mandatory
inspections are needed to identify those critical rotating parts with
conditions which, if allowed to continue in service, could result in
uncontained engine failures. This proposal would require revisions to
the JT9D series engines ALS sections of the manufacturer's manuals and
an air carrier's approved continuous airworthiness maintenance program
to incorporate additional inspection requirements.
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 retain all of the requirements of AD 2007-
05-17 (72 FR 10350, March 8, 2007). This proposed AD would supersede AD
2007-05-17 to require the following additional inspections:
Adding eddy current inspections (ECIs) for web cooling
holes in high-pressure turbine (HPT) stage 1 disks installed in engine
models JT9D-3A, -7, -7A, -7AH, -7F, -7H, -7J, -20, and -20J engines;
Adding ECIs for web cooling holes and tierod holes in HPT
stage 2 disks installed in JT9D-59A and -70A engines;
Adding ECIs for web cooling holes and tierod holes in HPT
stage 2 disks installed in JT9D-7Q and -7Q3 engines;
Adding ECIs for web cooling holes in HPT stage 2 disks,
and for fan hub
[[Page 72131]]
slots, installed in JT9D-7R4 engines; and
Adding ECIs for web cooling holes and tierod holes in HPT
stage 2 disks installed in JT9D-7R4D, -7R4D1, -7R4E, and -7R4E1
engines.
This proposed AD would also add the Engine Manual Inspection Task
and Sub Task Number references for these inspections.
Identifying the Part Nomenclatures and Inspections Added
For reference, the part nomenclatures and inspections added to the
table in the compliance section of this proposed AD are identified by
two asterisks (**) that precede the part nomenclature.
Costs of Compliance
We estimate that 438 JT9D series engines are installed on airplanes
of U.S. registry and would be affected by this proposed AD. We also
estimate that about 4 work hours per engine are needed to perform the
proposed actions, and that the average labor rate is $85 per work hour.
Since this is an added inspection requirement that will be part of the
normal maintenance cycle, no additional parts costs are involved. Based
on these figures, we estimate the total cost of the proposed AD to U.S.
operators to be $148,920.
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 have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing airworthiness directive
(AD) 2007-05-17, Amendment 39-14978 (72 FR 10350, March 8, 2007), and
adding the following new AD:
Pratt & Whitney: Docket No. FAA-2007-27023; Directorate Identifier
98-ANE-47-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by January 23,
2012.
(b) Affected ADs
This AD supersedes AD 2007-05-17, Amendment 39-14978 (72 FR
10350, March 8, 2007).
(c) Applicability
This AD applies to Pratt & Whitney (PW) JT9D-3A, -7, -7A, -7H, -
7AH, -7F, -7J, -20J, -59A, -70A, -7Q, -7Q3, -7R4D, -7R4D1, -7R4E, -
7R4E1, -7R4E4, -7R4G2, and -7R4H1 series turbofan engines.
(d) Unsafe Condition
This AD results from the need to require enhanced inspection of
selected critical life-limited parts of JT9D series turbofan
engines. We are issuing this AD to prevent critical life-limited
rotating engine part failure, which could result in an uncontained
engine failure and damage to the airplane.
(e) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(f) Inspections
Within the next 30 days after the effective date of this AD, add
the following section to the Airworthiness Limitations Section (ALS)
of your copy of the manufacturer's Instructions for Continued
Airworthiness (ICA) and, for air carrier operations, to your
continuous airworthiness air carrier maintenance program:
``MANDATORY INSPECTIONS''
(1) Inspect the following life-limited parts at each piece-part
opportunity in accordance with the instructions provided in the
applicable manual provisions:
--------------------------------------------------------------------------------------------------------------------------------------------------------
Engine manual part No. (P/ Inspect per
Engine model N) Part nomenclature manual section Inspection/check
--------------------------------------------------------------------------------------------------------------------------------------------------------
3A/7/7A/7AH/7F/7H/7J/20/20J........... *646028 (or the All Fan Hubs.................. 72-31-04 Inspection-02.
equivalent customized
versions, 770407 and
770408).
All HPC Stage 5-15 Disks and 72-35-00 Inspection-03.
Rear Compressor Drive Turbine
Shafts.
All HPT Stage 1-2 Disks and 72-51-00 Inspection-03.
Hubs.
**All HPT Stage 1 Disk Web 72-51-02 Inspection-06.
Cooling Holes.
All HPT Stage 2 Disk Web 72-51-02 Inspection-05.
Tierod Holes.
All LPT Stage 3-6 Disks and 72-52-00 Inspection-03.
Hubs.
--------------------------------------------------------------------------------------------------------------------------------------------------------
59A/70A............................... 754459................... All Fan Hubs.................. 72-31-00 Check-00.
All HPC Stage 5-15 Disks and 72-35-00 Check-00.
Rear Compressor Drive Turbine
Shafts.
All HPT Stage 1-2 Disks and 72-51-00 Check-03.
Hubs.
[[Page 72132]]
......................... All HPT Stage 1 Disk Web 72-51-02 Check-03.
Cooling Holes.
**All HPT Stage 2 Disk Tierod 72-51-02 Check-04.
and Web Cooling Holes.
All LPT Stage 3-6 Disks and 72-52-00 Check-03.
Hubs.
--------------------------------------------------------------------------------------------------------------------------------------------------------
7Q/7Q3................................ 777210................... All Fan Hubs.................. 72-31-00 Inspection-03.
All HPC Stage 5-15 Disks and 72-35-00 Inspection-03.
Rear Compressor Drive Turbine
Shafts.
All HPT Stage 1-2 Disks and 72-51-00 Inspection-03.
Hubs All HPT Stage 1 Disk Web 72-51-06 Inspection-03.
Cooling Holes.
**All HPT Stage 2 Disk Tierod 72-51-07 Inspection-03.
and Web Cooling Holes.
All LPT Stage 3-6 Disks and 72-52-00 Inspection-03.
Hubs.
--------------------------------------------------------------------------------------------------------------------------------------------------------
7R4 ALL............................... 785058, 785059, and All Fan Hubs.................. 72-31-00 Inspection/Check-03.
789328.
**All Fan Hub Slots........... 72-31-01 Inspection/Check-02.
All HPC Stage 5-15 Disks and 72-35-00 Inspection/Check 03.
Rear Compressor Drive Turbine
Shafts.
All HPT Stage 1-2 Disks and 72-51-00 Inspection/Check 03.
Hubs.
All LPT Stage 3-6 Disks and 72-52-00 Inspection/Check 03
Hubs.
**All HPT Stage 2 Disk Tierod 72-51-07 Inspection/Check-02.
and Web Cooling Holes.
--------------------------------------------------------------------------------------------------------------------------------------------------------
7R4D/D1/E/E1.......................... 785058 and 785059........ All HPT Stage 1 Disk Web 72-51-06 Inspection/Check-02.
Cooling Holes.
**All HPT Stage 2 Disk Tierod 72-51-07 Inspection/Check-02.
and Web Cooling Holes.
--------------------------------------------------------------------------------------------------------------------------------------------------------
* P/N 770407 and 770408 are customized versions of P/N 646028 engine manual.
** Two asterisks identify the part nomenclatures and inspections added to the table.
(2) For the purposes of these mandatory inspections, piece-part
opportunity means:
(i) The part is considered completely disassembled when
disassembly is in accordance with the disassembly instructions in
the manufacturer's engine shop manual; and
(ii) The part has accumulated more than 100 cycles-in-service
since the last piece-part opportunity inspection, provided that the
part was not damaged or related to the cause for its removal from
the engine.''
(g) Except as provided in paragraph (h) of this AD, and
notwithstanding contrary provisions in section 43.16 of the Federal
Aviation Regulations (14 CFR 43.16), these mandatory inspections
shall be performed only in accordance with the ALS of the
manufacturer's ICA.
(g) Alternative Methods of Compliance (AMOC)
(1) You must perform these mandatory inspections using the ALS
of the ICA and the applicable Engine Manual, unless you receive
approval to use an AMOC under paragraph (h)(2) of this AD. Section
43.16 of the Federal Aviation Regulations (14 CFR 43.16) may not be
used to approve alternative methods of compliance or adjustments to
the times in which these inspections must be performed.
(2) 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.
(h) Maintaining Records of the Mandatory Inspections
(1) You have met the requirements of this AD when you revise
your copy of the ALS of the manufacturer's ICA as specified in
paragraph (f) of this AD. For air carriers operating under part 121
of the Federal Aviation Regulations (14 CFR part 121), you have met
the requirements of this AD when you modify your continuous
airworthiness air carrier maintenance program as specified in
paragraph (f) of this AD. You do not need to record each piece-part
inspection as compliance to this AD, but you must maintain records
of those inspections according to the regulations governing your
operation. For air carriers operating under part 121, you may use
either the system established to comply with section 121.369 or an
alternative accepted by your principal maintenance inspector if that
alternative:
(i) Includes a method for preserving and retrieving the records
of the inspections resulting from this AD;
(ii) Meets the requirements of section 121.369(c); and
(iii) Maintains the records either indefinitely or until the
work is repeated.
(2) These record keeping requirements apply only to the records
used to document the mandatory inspections required as a result of
revising the ALS of the manufacturer's ICA as specified in paragraph
(f) of this AD. These record keeping requirements do not alter or
amend the record keeping requirements for any other AD or regulatory
requirement.
(i) Related Information
For more information about this AD, contact Stephen Sheely,
Aerospace Engineer, Engine & Propeller Directorate, FAA, 12 New
England Executive Park, Burlington, MA 01803; phone: (781) 238-7750;
fax: (781) 238-7199; email: stephen.k.sheely@faa.gov.
Issued in Burlington, Massachusetts, on November 15, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2011-30062 Filed 11-21-11; 8:45 am]
BILLING CODE 4910-13-P
