Airworthiness Directives; Pratt & Whitney JT9D Series Turbofan Engines, 66300-66302 [05-21804]
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66300
Proposed Rules
Federal Register
Vol. 70, No. 211
Wednesday, November 2, 2005
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
• By fax: (781) 238–7055.
• By e-mail: 9-aneadcomment@faa.gov.
You may examine the AD docket at
the FAA, New England Region, Office of
the Regional Counsel, 12 New England
Executive Park, Burlington, MA.
DEPARTMENT OF TRANSPORTATION
FOR FURTHER INFORMATION CONTACT:
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98–ANE–47–AD]
RIN 2120–AA64
Kevin Donovan, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803–5299; telephone (781) 238–7743,
fax (781) 238–7199.
SUPPLEMENTARY INFORMATION:
Airworthiness Directives; Pratt &
Whitney JT9D Series Turbofan Engines
Comments Invited
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
We invite you to submit any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No. 98–
ANE–47–AD’’ in the subject line of your
comments. If you want us to
acknowledge receipt of your mailed
comments, send us a self-addressed,
stamped postcard with the docket
number written on it; we will datestamp your postcard and mail it back to
you. We specifically invite comments
on the overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. If a person contacts us
verbally, and that contact relates to a
substantive part of this proposed AD,
we will summarize the contact and
place the summary in the docket. We
will consider all comments received by
the closing date and may amend the
proposed AD in light of those
comments.
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) for Pratt & Whitney (PW)
JT9D series turbofan engines. That 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. This
proposed AD would modify 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. The mandatory
inspections are needed to identify those
critical rotating parts with conditions,
which if allowed to continue in service,
could result in uncontained failures. 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 any comments
on this proposed AD by January 3, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD:
• By mail: Federal Aviation
Administration (FAA), New England
Region, Office of the Regional Counsel,
Attention: Rules Docket No. 98–ANE–
47–AD, 12 New England Executive Park,
Burlington, MA 01803–5299.
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16:45 Nov 01, 2005
Jkt 208001
Examining the AD Docket
You may examine the AD Docket
(including any comments and service
information), by appointment, between
8 a.m. and 4:30 p.m., Monday through
Friday, except Federal holidays. See
ADDRESSES for the location.
Discussion
On April 12, 2002, we issued AD
2002–08–11, Amendment 39–12719 (67
FR 19663, April 23, 2002), to require
revisions to the JT9D series engines ALS
of the manufacturer’s Instructions for
Continued Airworthiness to include
required enhanced inspection of
selected critical life-limited parts at
each piece-part opportunity.
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Fmt 4702
Sfmt 4702
New Inspection Procedures
Since we issued AD 2002–08–11, PW
has added mandatory eddy current
inspections (ECIs) for web cooling holes
in high pressure turbine (HPT) stage 1
disks, installed in engine models JT9D–
7R4, –7R4D1, –7R4E, –7R4E1 engines,
and for HPT stage 2 disks installed in
JT9D–7, –7A, –7H, –7AH, –7F, –7J, –20,
and –20J engines. The mandatory
inspections are needed to identify those
critical rotating parts with conditions,
which if allowed to continue in service,
could result in uncontained failures.
FAA’s Determination and Requirements
of the Proposed AD
Since an unsafe condition has been
identified that is likely to exist or
develop on other products of this same
type design, the proposed AD would
supersede AD 2002–08–11 to require:
• Adding ECIs for web cooling holes
in HPT stage 1 disks installed in engine
models JT9D–7R4, –7R4D1, –7R4E,
–7R4E1 engines; and
• Adding ECIs for web cooling holes
in HPT stage 2 disks installed in JT9D–
7, –7A, –7H, –7AH, –7F, –7J, –20, and
–20J engines; and
• Clarification of the inspections
listed in the Inspection column of the
Mandatory Inspections Table in this AD.
The proposed AD would incorporate
the additional inspection requirements
into the Airworthiness Limitations
Section of the manufacturer’s manuals
and an air carrier’s approved continuous
airworthiness maintenance program.
Costs of Compliance
About 1,978 PW JT9D series turbofan
engines of the affected design are in the
worldwide fleet. We estimate that 837 of
these engines are installed on U.S.registered airplanes and would be
affected by this proposed AD. We also
estimate that about one work hour per
engine is needed to perform the
proposed actions, and that the average
labor rate is $65 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
$54,405.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
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02NOP1
Federal Register / Vol. 70, No. 211 / Wednesday, November 2, 2005 / Proposed Rules
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.
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 proposal and placed
it in the AD Docket. You may get a copy
of this summary by sending a request to
us at the address listed under
ADDRESSES. Include ‘‘AD Docket No. 98–
ANE–47–AD’’ in your request.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify 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); and
3. Would not have a significant
economic impact, positive or negative,
PART 39—AIRWORTHINESS
DIRECTIVES
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
proposes to amend 14 CFR part 39 as
follows:
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
removing Amendment 39–12719 (67 FR
19663, April 23, 2002), and by adding
a new airworthiness directive to read as
follows:
Pratt & Whitney: Docket No. 98–ANE–47–
AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by
January 3, 2006.
66301
Affected ADs
(b) This AD supersedes AD 2002–08–11,
Amendment 39–12719.
Applicability
(c) 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,
installed on but not limited to Boeing 747
and 767 series, McDonnell Douglas DC–10
series, and Airbus Industrie A300 and A310
airplanes.
Unsafe Condition
(d) 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 failure of critical life-limited rotating
engine parts, which could result in an
uncontained engine failure and damage to
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.
(f) Within the next 180 days after the
effective date of this AD, revise the
manufacturer’s Instructions for Continued
Airworthiness Airworthiness Limitations
Section (ALS), and for air carrier operations
revise the approved continuous
airworthiness maintenance program by
adding the following:
‘‘MANDATORY INSPECTIONS
(1) Perform inspections of the following
parts at each piece-part opportunity in
accordance with the instructions provided in
the applicable manual provisions:
Inspect per
manual
section
Engine model
Engine manual part
number (P/N)
Part nomenclature
7/7A/7AH/7F, 7H/7J/20/
20J.
* 646028 (or the equivalent customized
versions, 770407 and
770408).
All Fan Hubs .......................................................
72–31–04
Inspection-02.
All HPC Stage 5—15 Disks and Rear Compressor Drive Turbine Shafts.
All HPT Stage 1—2 Disks and Hubs .................
All HPT Stage 2 Disk Web Cooling Holes .........
All LPT Stage 3—6 Disks and Hubs ..................
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 LPT Stage 3—6 Disks and Hubs ..................
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 LPT Stage 3—6 Disks and Hubs ..................
All Fan Hubs .......................................................
72–35–00
Inspection-03.
72–51–00
71–51–02
72–52–00
72–31–00
72–35–00
Inspection-03.
Inspection-05.
Inspection-03.
Check-00.
Check-00.
72–51–00
72–51–02
72–52–00
72–31–00
72–35–00
Check-03.
Check-03.
Check-03.
Inspection-03.
Inspection-03.
72–51–00
72–51–06
72–52–00
72–31–00
Inspection-03.
Inspection-03.
Inspection-03.
Inspection/Check-03.
72–35–00
Inspection/Check 03.
59A/70A .........................
7Q/7Q3 ..........................
7R4 ................................
754459 .........................
777210 .........................
785058, 785059, and
789328.
All HPC Stage 5—15 Disks and Rear Compressor Drive Turbine Shafts.
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16:45 Nov 01, 2005
Jkt 208001
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Inspection/check
66302
Federal Register / Vol. 70, No. 211 / Wednesday, November 2, 2005 / Proposed Rules
Engine model
7R4D/D1/E/E1 ...............
Inspect per
manual
section
Engine manual part
number (P/N)
Part nomenclature
785058 and 785059 .....
All HPT Stage 1—2 Disks and Hubs .................
All LPT Stage 3—6 Disks and Hubs ..................
All HPT Stage 1 Disk Web Cooling Holes .........
72–51–00
72–52–00
72–51–06
Inspection/check
Inspection/Check-03.
Inspection/Check-03.
Inspection/Check-02.
* P/N 770407 and 770408 are customized versions of P/N 646028 engine manual.
(2) For the purposes of these mandatory
inspections, piece-part opportunity means:
(i) The part is considered completely
disassembled when done in accordance with
the disassembly instructions in the
manufacturer’s engine 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.’’
Issued in Burlington, Massachusetts, on
October 27, 2005.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–21804 Filed 11–1–05; 8:45 am]
Alternative Methods of Compliance
Federal Aviation Administration
(g) You must perform these mandatory
inspections using the ALS of the Instructions
for Continued Airworthiness and the
applicable Engine Manual unless you receive
approval to use an alternative method of
compliance under paragraph (h) 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.
(h) 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.
Maintaining Records of the Mandatory
Inspections
(i) You have met the requirements of this
AD when you change the manufacturer’s
Instructions for Continued Airworthiness
ALS specified in paragraph (f) of this AD,
and, for air carriers operating under part 121
of the Federal Aviation Regulations (14 CFR
part 121), when you modify your continuous
airworthiness maintenance plan to reflect
those changes. 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:
(1) Includes a method for preserving and
retrieving the records of the inspections
resulting from this AD; and
(2) Meets the requirements of section
121.369(c); and
(3) Maintains the records either
indefinitely or until the work is repeated.
(j) 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 Instructions
for Continued Airworthiness as specified in
paragraph (f) of this AD, and do not alter or
amend the record keeping requirements for
any other AD or regulatory requirement.
VerDate Aug<31>2005
16:45 Nov 01, 2005
Jkt 208001
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 92–ANE–34–AD]
RIN 2120–AA64
Airworthiness Directives; Honeywell
International Inc., (Formerly
AlliedSignal, Inc. and Textron
Lycoming) ALF502L Series and
ALF502R Series Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD), AD 95–04–11, for
Honeywell International Inc., (formerly
AlliedSignal, Inc. and Textron
Lycoming) ALF502L series and
ALF502R series turbofan engines. That
AD currently establishes stress rupture
retirement life limits for certain third
stage turbine discs used in conjunction
with certain third stage turbine nozzles.
This proposed AD would bring
requirements forward and unchanged,
from the previous AD for ALF502R
series turbofan engines. Also, this
proposed AD would establish new
reduced stress rupture retirement life
limits for certain part numbers (P/Ns) of
third stage turbine disc and shaft
assemblies installed in ALF502L series
turbofan engines. This proposed AD
would also require removing those same
parts from service using a drawdown
schedule. This proposed AD results
from a report of failure of a third stage
turbine disc and shaft assembly, leading
to turbine blade release and separation
of the exhaust nozzle. We are proposing
this AD to prevent total loss of engine
power, in-flight engine shutdown,
release of turbine blades, separation of
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Fmt 4702
Sfmt 4702
the exhaust nozzle, and possible damage
to the airplane.
DATES: We must receive any comments
on this proposed AD by January 3, 2006.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD:
• By mail: Federal Aviation
Administration (FAA), New England
Region, Office of the Regional Counsel,
Attention: Rules Docket No. 92–ANE–
34–AD, 12 New England Executive Park,
Burlington, MA 01803–5299.
• By fax: (781) 238–7055.
• By e-mail: 9-aneadcomment@faa.gov.
Contact Honeywell Engines, Systems
& Services, Customer Support Center,
M/S 26–06/2102–323, P.O. Box 29003,
Phoenix, AZ 85038–9003; telephone
(800) 601–3099, for the service
information identified in this proposed
AD.
You may examine the AD docket at
the FAA, New England Region, Office of
the Regional Counsel, 12 New England
Executive Park, Burlington, MA.
FOR FURTHER INFORMATION CONTACT:
Robert Baitoo, Aerospace Engineer, Los
Angeles Aircraft Certification Office,
FAA, Transport Airplane Directorate,
3960 Paramount Blvd., Lakewood, CA
90712–4137; telephone: (562) 627–5245,
fax: (562) 627–5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No. 92–
ANE–34–AD’’ in the subject line of your
comments. If you want us to
acknowledge receipt of your mailed
comments, send us a self-addressed,
stamped postcard with the docket
number written on it; we will datestamp your postcard and mail it back to
you. We specifically invite comments
on the overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. If a person contacts us
verbally, and that contact relates to a
substantive part of this proposed AD,
we will summarize the contact and
place the summary in the docket. We
will consider all comments received by
E:\FR\FM\02NOP1.SGM
02NOP1
]]>Agencies
[Federal Register Volume 70, Number 211 (Wednesday, November 2, 2005)]
[Proposed Rules]
[Pages 66300-66302]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-21804]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 70, No. 211 / Wednesday, November 2, 2005 /
Proposed Rules
[[Page 66300]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 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: The FAA proposes to supersede an existing airworthiness
directive (AD) for Pratt & Whitney (PW) JT9D series turbofan engines.
That 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. This
proposed AD would modify 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. The mandatory inspections are needed to identify those
critical rotating parts with conditions, which if allowed to continue
in service, could result in uncontained failures. 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 any comments on this proposed AD by January 3,
2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
By mail: Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 98-ANE-47-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
You may examine the AD docket at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA.
FOR FURTHER INFORMATION CONTACT: Kevin Donovan, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7743, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 98-ANE-47-AD'' in the
subject line of your comments. If you want us to acknowledge receipt of
your mailed comments, send us a self-addressed, stamped postcard with
the docket number written on it; we will date-stamp your postcard and
mail it back to you. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. If a person contacts us verbally, and that contact relates to a
substantive part of this proposed AD, we will summarize the contact and
place the summary in the docket. We will consider all comments received
by the closing date and may amend the proposed AD in light of those
comments.
Examining the AD Docket
You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
Discussion
On April 12, 2002, we issued AD 2002-08-11, Amendment 39-12719 (67
FR 19663, April 23, 2002), to require revisions to the JT9D series
engines ALS of the manufacturer's Instructions for Continued
Airworthiness to include required enhanced inspection of selected
critical life-limited parts at each piece-part opportunity.
New Inspection Procedures
Since we issued AD 2002-08-11, PW has added mandatory eddy current
inspections (ECIs) for web cooling holes in high pressure turbine (HPT)
stage 1 disks, installed in engine models JT9D-7R4, -7R4D1, -7R4E, -
7R4E1 engines, and for HPT stage 2 disks installed in JT9D-7, -7A, -7H,
-7AH, -7F, -7J, -20, and -20J engines. The mandatory inspections are
needed to identify those critical rotating parts with conditions, which
if allowed to continue in service, could result in uncontained
failures.
FAA's Determination and Requirements of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would supersede AD 2002-08-11 to require:
Adding ECIs for web cooling holes in HPT stage 1 disks
installed in engine models JT9D-7R4, -7R4D1, -7R4E, -7R4E1 engines; and
Adding ECIs for web cooling holes in HPT stage 2 disks
installed in JT9D-7, -7A, -7H, -7AH, -7F, -7J, -20, and -20J engines;
and
Clarification of the inspections listed in the Inspection
column of the Mandatory Inspections Table in this AD.
The proposed AD would incorporate the additional inspection
requirements into the Airworthiness Limitations Section of the
manufacturer's manuals and an air carrier's approved continuous
airworthiness maintenance program.
Costs of Compliance
About 1,978 PW JT9D series turbofan engines of the affected design
are in the worldwide fleet. We estimate that 837 of these engines are
installed on U.S.-registered airplanes and would be affected by this
proposed AD. We also estimate that about one work hour per engine is
needed to perform the proposed actions, and that the average labor rate
is $65 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 $54,405.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue
[[Page 66301]]
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 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); and
3. Would 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 proposal and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 98-ANE-47-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration 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 Amendment 39-12719 (67 FR
19663, April 23, 2002), and by adding a new airworthiness directive to
read as follows:
Pratt & Whitney: Docket No. 98-ANE-47-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by January 3,
2006.
Affected ADs
(b) This AD supersedes AD 2002-08-11, Amendment 39-12719.
Applicability
(c) 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,
installed on but not limited to Boeing 747 and 767 series, McDonnell
Douglas DC-10 series, and Airbus Industrie A300 and A310 airplanes.
Unsafe Condition
(d) 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 failure of critical life-
limited rotating engine parts, which could result in an uncontained
engine failure and damage to 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.
(f) Within the next 180 days after the effective date of this
AD, revise the manufacturer's Instructions for Continued
Airworthiness Airworthiness Limitations Section (ALS), and for air
carrier operations revise the approved continuous airworthiness
maintenance program by adding the following:
``MANDATORY INSPECTIONS
(1) Perform inspections of the following parts at each piece-
part opportunity in accordance with the instructions provided in the
applicable manual provisions:
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspect per
Engine model Engine manual part number Part nomenclature manual Inspection/check
(P/N) section
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 2 Disk Web 71-51-02 Inspection-05.
Cooling 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.
All HPT Stage 1 Disk Web 72-51-02 Check-03.
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 LPT Stage 3--6 Disks and 72-52-00 Inspection-03.
Hubs.
7R4................................... 785058, 785059, and All Fan Hubs.................. 72-31-00 Inspection/Check-03.
789328.
All HPC Stage 5--15 Disks and 72-35-00 Inspection/Check 03.
Rear Compressor Drive Turbine
Shafts.
[[Page 66302]]
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.
7R4D/D1/E/E1.......................... 785058 and 785059........ All HPT Stage 1 Disk Web 72-51-06 Inspection/Check-02.
Cooling Holes.
--------------------------------------------------------------------------------------------------------------------------------------------------------
* P/N 770407 and 770408 are customized versions of P/N 646028 engine manual.
(2) For the purposes of these mandatory inspections, piece-part
opportunity means:
(i) The part is considered completely disassembled when done in
accordance with the disassembly instructions in the manufacturer's
engine 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.''
Alternative Methods of Compliance
(g) You must perform these mandatory inspections using the ALS
of the Instructions for Continued Airworthiness and the applicable
Engine Manual unless you receive approval to use an alternative
method of compliance under paragraph (h) 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.
(h) 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.
Maintaining Records of the Mandatory Inspections
(i) You have met the requirements of this AD when you change the
manufacturer's Instructions for Continued Airworthiness ALS
specified in paragraph (f) of this AD, and, for air carriers
operating under part 121 of the Federal Aviation Regulations (14 CFR
part 121), when you modify your continuous airworthiness maintenance
plan to reflect those changes. 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:
(1) Includes a method for preserving and retrieving the records
of the inspections resulting from this AD; and
(2) Meets the requirements of section 121.369(c); and
(3) Maintains the records either indefinitely or until the work
is repeated.
(j) 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 Instructions for Continued Airworthiness as
specified in paragraph (f) of this AD, and do not alter or amend the
record keeping requirements for any other AD or regulatory
requirement.
Issued in Burlington, Massachusetts, on October 27, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-21804 Filed 11-1-05; 8:45 am]
BILLING CODE 4910-13-P
