Airworthiness Directives; Pratt & Whitney JT9D Series Turbofan Engines, 10350-10352 [E7-4139]
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10350
Federal Register / Vol. 72, No. 45 / Thursday, March 8, 2007 / Rules and Regulations
Corporation Ltd Model 750XL airplanes.
AD 2007–04–01 requires you to inspect
the rivets in the fuselage roof at STN
180.85, BL 19.67, WL 86.2, and replace
undersize rivets. Current language in
§ 39.13 [Amended] of AD 2007–04–01
references ‘‘* * *’’ instead of ‘‘2007–
04–01.’’
Need for the Correction
This correction is needed to specify
the correct AD number (2007–04–01) for
AD 2007–04–01.
Correction of Publication
Accordingly, the publication of
February 14, 2007 (72 FR 6931), of
Amendment 39–14932; AD 2007–04–01,
which was the subject of FR Doc. E7–
2318, is corrected as follows:
I
Section 39.13 [Corrected]
On page 6932, in the second column,
in § 39.13 [Amended], in the third line,
remove ‘‘* * *’’ and add ‘‘2007–04–01’’
in its place.
I Action is taken herein to correct this
reference in AD 2007–04–01 and to add
this AD correction to section 39.13 of
the Federal Aviation Regulations (14
CFR 39.13).
The effective date remains March 21,
2007.
I
Issued in Kansas City, Missouri, on March
2, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E7–4130 Filed 3–7–07; 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; Amendment 39–
14978; AD 2007–05–17]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney JT9D Series Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
pwalker on PROD1PC71 with RULES
AGENCY:
SUMMARY: The FAA is superseding 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
VerDate Aug<31>2005
18:23 Mar 07, 2007
Jkt 211001
include required enhanced inspection of
selected critical life-limited parts at
each piece-part opportunity. This AD
modifies 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. 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 lifelimited rotating engine part failure,
which could result in an uncontained
engine failure and damage to the
airplane.
DATES: This AD becomes effective April
12, 2007.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in Room PL–401 on the
plaza level of the Nassif Building, 400
Seventh Street, SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Mark Riley, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803–
5299; telephone (781) 238–7758, 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 JT9D series turbofan
engines. We published the proposed AD
in the Federal Register on November 2,
2005 (70 FR 66300). That action
proposed to 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. PW has added mandatory
eddy current inspections (ECIs) for the
web cooling holes in high pressure
turbine (HPT) stage 1 disks installed in
engine models JT9D–7R4D, –7R4D1,
–7R4E, and –7R4E1, and for web tie-rod
holes in HPT stage 2 disks installed in
JT9D–3A, –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.
Examining the AD Docket
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the Docket Management
Facility Docket Office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The Docket
Office (telephone (800) 647–5227) is
located on the plaza level of the
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Department of Transportation Nassif
Building at the street address stated in
ADDRESSES. Comments will be available
in the AD docket shortly after the DMS
receives them.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Delete ECIs for JT9D–59A,
–70A, –7Q, and –7Q3 Engines
One commenter, Japan Airlines,
requests that we delete the ECIs for
JT9D–59A, –70A, –7Q, and –7Q3
engines from the table in the proposed
AD compliance section. The commenter
points out that the proposed AD
preamble paragraph entitled ‘‘FAA’s
Determination and Requirements of the
Proposed AD’’ does not include ECIs for
JT9D–59A, –70A, –7Q, and –7Q3
engines.
We do not agree. We inadvertently
omitted listing the requirement of ECI of
the HPT stage 1 disk web cooling holes
on JT9D–59A, –70A, –7Q, and –7Q3
engines, under the proposed AD
preamble paragraph entitled ‘‘FAA’s
Determination and Requirements of the
Proposed AD’’. The proposed AD
compliance section and the compliance
section in this AD, correctly list those
engine models. We did not change the
AD.
Request To Wait To Issue the AD
Japan Airlines requests that we wait
to issue the AD until Pratt & Whitney
provides the ECI procedure to the
operators. The commenter states that the
JT9D–7 Engine Manual Section 72–51–
02, Inspection 05, has not been
published yet.
We do not agree. Although the ECI
procedure was not published in the
JT9D–7 Engine Manual as of December
26, 2005 when the comment was sent,
it was incorporated into the JT9D–7
Engine Manual on February 15, 2006.
We do not need to wait to issue the AD.
Request To Revise Engine Manual
Japan Airlines requests that we
recommend to Pratt & Whitney to revise
the JT9D engine manual to remove the
specific manufacturer’s name of the ECI
equipment required to perform ECIs,
and to only list the technical
specifications required to perform the
ECIs. The commenter states that
operators may not own the ECI
equipment specified in the Pratt &
Whitney JT9D engine manual, but may
have similar equipment capable of
performing the inspections.
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Federal Register / Vol. 72, No. 45 / Thursday, March 8, 2007 / Rules and Regulations
We partially agree. This AD requires
operators to revise the Airworthiness
Limitations Section of the engine
manual to include a mandatory
opportunistic inspection. We do not
intend for the AD to specify only one
vendor’s inspection equipment to
accomplish the inspection. Nor do we
intend that this AD change the way
operators seek approval for alternative
methods of inspections. We did not
change the AD.
JT9D–3A Model Added to the
Compliance Table
Upon review of the proposed AD, we
discovered that the JT9D–3A model was
inadvertently left out of the compliance
table. We added the JT9D–3A model to
the compliance table in the AD.
Docket Number Change
We are transferring the docket for this
AD to the Docket Management System
as part of our on-going docket
management consolidation efforts. The
new Docket No. is FAA–2007–27023.
The old Docket No. became the
Directorate Identifier, which is 98–
ANE–47–AD. This AD might get logged
into the DMS docket, ahead of the
previously collected documents from
the old docket file, as we are in the
process of sending those items to the
DMS.
Upon review of the proposed AD, we
discovered that the compliance table
needs correcting in the section for the
–3A/7/7A/7AH/7F/7H/7J/20/20J engine
models. ‘‘All HPT Stage 2 Disk Web
Cooling Holes 71–51–02 Inspection-05’’
is corrected to read ‘‘All HPT Stage 2
Disk Web Tie-rod Holes 72–51–02
Inspection-05’’.
Conclusion
Regulatory Findings
We have carefully reviewed the
available data, including the comments
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.
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 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.
Update to the Costs of Compliance
Since we published the proposed AD
on November 2, 2005, the number of
engines affected and the hourly labor
rate have changed. We updated this
information in this AD preamble.
Correction to Compliance Table
pwalker on PROD1PC71 with RULES
Costs of Compliance
We estimate that 504 JT9D series
turbofan engines are installed on U.S.registered airplanes and will be affected
by this AD. We also estimate that 87
engines will require this inspection per
year and about one work-hour per
engine is needed to perform the actions,
and that the average labor rate is $80 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 annual cost of the AD to U.S.
operators to be $6,960.
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18:23 Mar 07, 2007
Jkt 211001
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, 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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
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.
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10351
§ 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,
Amendment 39–14978, to read as
follows:
I
2007–05–17 Pratt & Whitney: Amendment
39–14978. Docket No. FAA–2007–27023;
Directorate Identifier 98–ANE–47–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective April 12, 2007.
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. These
engines are installed on, but not limited to,
Boeing 747 and 767 series, McDonnell
Douglas DC–10 series, and Airbus Industrie
A300 and A310 series 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 critical life-limited rotating engine
part failure, 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 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
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10352
Federal Register / Vol. 72, No. 45 / Thursday, March 8, 2007 / Rules and Regulations
accordance with the instructions provided in
the applicable manual provisions:
Engine manual part
number (P/N)
Engine model
3A/7/7A/7AH/7F/7H/7J/
20/20J.
59A/70A ...........................
7Q/7Q3 ............................
7R4 ALL ..........................
Inspect per
manual
section
Part nomenclature
*646028 (or the equivalent customized
versions, 770407 and
770408).
All Fan Hubs .............................................................
754459 ............................
777210 ............................
785058, 785059, and
789328.
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 Tie-rod 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
72–51–02
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.
Inspection/
Check 03.
Inspection/
Check 03.
Inspection/
Check 03.
Inspection/
Check-02.
All HPC Stage 5–15 Disks and Rear Compressor
Drive Turbine Shafts.
All HPT Stage 1–2 Disks and Hubs .........................
785058 and 785059 ........
72–35–00
All LPT Stage 3–6 Disks and Hubs ..........................
7R4D/D1/E/E1 .................
Inspection/check
72–52–00
All HPT Stage 1 Disk Web Cooling Holes ...............
72–51–06
72–51–00
* 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.’’
pwalker on PROD1PC71 with RULES
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
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18:23 Mar 07, 2007
Jkt 211001
ALS 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 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. These record
keeping requirements do not alter or amend
the record keeping requirements for any
other AD or regulatory requirement.
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Related Information
(k) Contact Mark Riley, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; telephone (781) 238–7758, fax (781)
238–7199; e-mail: mark.riley@faa.gov for
more information about this AD.
Issued in Burlington, Massachusetts, on
March 1, 2007.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–4139 Filed 3–7–07; 8:45 am]
BILLING CODE 4910–13–P
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]]>Agencies
[Federal Register Volume 72, Number 45 (Thursday, March 8, 2007)]
[Rules and Regulations]
[Pages 10350-10352]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-4139]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27023; Directorate Identifier 98-ANE-47-AD;
Amendment 39-14978; AD 2007-05-17]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney JT9D Series Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding 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 AD modifies 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. 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.
DATES: This AD becomes effective April 12, 2007.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in Room PL-401 on the plaza level of the Nassif
Building, 400 Seventh Street, SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7758, 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 JT9D series turbofan
engines. We published the proposed AD in the Federal Register on
November 2, 2005 (70 FR 66300). That action proposed to 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. PW has added mandatory
eddy current inspections (ECIs) for the web cooling holes in high
pressure turbine (HPT) stage 1 disks installed in engine models JT9D-
7R4D, -7R4D1, -7R4E, and -7R4E1, and for web tie-rod holes in HPT stage
2 disks installed in JT9D-3A, -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.
Examining the AD Docket
You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
Facility Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is located on the plaza level of the Department of
Transportation Nassif Building at the street address stated in
ADDRESSES. Comments will be available in the AD docket shortly after
the DMS receives them.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Delete ECIs for JT9D-59A, -70A, -7Q, and -7Q3 Engines
One commenter, Japan Airlines, requests that we delete the ECIs for
JT9D-59A, -70A, -7Q, and -7Q3 engines from the table in the proposed AD
compliance section. The commenter points out that the proposed AD
preamble paragraph entitled ``FAA's Determination and Requirements of
the Proposed AD'' does not include ECIs for JT9D-59A, -70A, -7Q, and -
7Q3 engines.
We do not agree. We inadvertently omitted listing the requirement
of ECI of the HPT stage 1 disk web cooling holes on JT9D-59A, -70A, -
7Q, and -7Q3 engines, under the proposed AD preamble paragraph entitled
``FAA's Determination and Requirements of the Proposed AD''. The
proposed AD compliance section and the compliance section in this AD,
correctly list those engine models. We did not change the AD.
Request To Wait To Issue the AD
Japan Airlines requests that we wait to issue the AD until Pratt &
Whitney provides the ECI procedure to the operators. The commenter
states that the JT9D-7 Engine Manual Section 72-51-02, Inspection 05,
has not been published yet.
We do not agree. Although the ECI procedure was not published in
the JT9D-7 Engine Manual as of December 26, 2005 when the comment was
sent, it was incorporated into the JT9D-7 Engine Manual on February 15,
2006. We do not need to wait to issue the AD.
Request To Revise Engine Manual
Japan Airlines requests that we recommend to Pratt & Whitney to
revise the JT9D engine manual to remove the specific manufacturer's
name of the ECI equipment required to perform ECIs, and to only list
the technical specifications required to perform the ECIs. The
commenter states that operators may not own the ECI equipment specified
in the Pratt & Whitney JT9D engine manual, but may have similar
equipment capable of performing the inspections.
[[Page 10351]]
We partially agree. This AD requires operators to revise the
Airworthiness Limitations Section of the engine manual to include a
mandatory opportunistic inspection. We do not intend for the AD to
specify only one vendor's inspection equipment to accomplish the
inspection. Nor do we intend that this AD change the way operators seek
approval for alternative methods of inspections. We did not change the
AD.
JT9D-3A Model Added to the Compliance Table
Upon review of the proposed AD, we discovered that the JT9D-3A
model was inadvertently left out of the compliance table. We added the
JT9D-3A model to the compliance table in the AD.
Update to the Costs of Compliance
Since we published the proposed AD on November 2, 2005, the number
of engines affected and the hourly labor rate have changed. We updated
this information in this AD preamble.
Correction to Compliance Table
Upon review of the proposed AD, we discovered that the compliance
table needs correcting in the section for the -3A/7/7A/7AH/7F/7H/7J/20/
20J engine models. ``All HPT Stage 2 Disk Web Cooling Holes 71-51-02
Inspection-05'' is corrected to read ``All HPT Stage 2 Disk Web Tie-rod
Holes 72-51-02 Inspection-05''.
Conclusion
We have carefully reviewed the available data, including the
comments 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 504 JT9D series turbofan engines are installed on
U.S.-registered airplanes and will be affected by this AD. We also
estimate that 87 engines will require this inspection per year and
about one work-hour per engine is needed to perform the actions, and
that the average labor rate is $80 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 annual cost of the AD to U.S.
operators to be $6,960.
Docket Number Change
We are transferring the docket for this AD to the Docket Management
System as part of our on-going docket management consolidation efforts.
The new Docket No. is FAA-2007-27023. The old Docket No. became the
Directorate Identifier, which is 98-ANE-47-AD. This AD might get logged
into the DMS docket, ahead of the previously collected documents from
the old docket file, as we are in the process of sending those items to
the DMS.
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 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, 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 removing Amendment 39-12719 (67 FR
19663, April 23, 2002), and by adding a new airworthiness directive,
Amendment 39-14978, to read as follows:
2007-05-17 Pratt & Whitney: Amendment 39-14978. Docket No. FAA-2007-
27023; Directorate Identifier 98-ANE-47-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April
12, 2007.
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.
These engines are installed on, but not limited to, Boeing 747 and
767 series, McDonnell Douglas DC-10 series, and Airbus Industrie
A300 and A310 series 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 critical life-limited
rotating engine part failure, 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 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
[[Page 10352]]
accordance with the instructions provided in the applicable manual
provisions:
----------------------------------------------------------------------------------------------------------------
Engine manual Inspect per
Engine model part number (P/ Part nomenclature manual Inspection/check
N) section
----------------------------------------------------------------------------------------------------------------
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 72-35-00 Inspection-03.
Disks and Rear
Compressor Drive
Turbine Shafts.
All HPT Stage 1-2 72-51-00 Inspection-03.
Disks and Hubs.
All HPT Stage 2 Disk 72-51-02 Inspection-05.
Web Tie-rod Holes.
All LPT Stage 3-6 72-52-00 Inspection-03.
Disks and Hubs.
59A/70A....................... 754459........... All Fan Hubs.......... 72-31-00 Check-00.
All HPC Stage 5-15 72-35-00 Check-00.
Disks and Rear
Compressor Drive
Turbine Shafts.
All HPT Stage 1-2 72-51-00 Check-03.
Disks and Hubs.
All HPT Stage 1 Disk 72-51-02 Check-03.
Web Cooling Holes.
All LPT Stage 3-6 72-52-00 Check-03.
Disks and Hubs.
7Q/7Q3........................ 777210........... All Fan Hubs.......... 72-31-00 Inspection-03.
All HPC Stage 5-15 72-35-00 Inspection-03.
Disks and Rear
Compressor Drive
Turbine Shafts.
All HPT Stage 1-2 72-51-00 Inspection-03.
Disks and Hubs.
All HPT Stage 1 Disk 72-51-06 Inspection-03.
Web Cooling Holes.
All LPT Stage 3-6 72-52-00 Inspection-03.
Disks and Hubs.
7R4 ALL....................... 785058, 785059, All Fan Hubs.......... 72-31-00 Inspection/Check-03.
and 789328.
All HPC Stage 5-15 72-35-00 Inspection/Check 03.
Disks and Rear
Compressor Drive
Turbine Shafts.
All HPT Stage 1-2 72-51-00 Inspection/Check 03.
Disks and Hubs.
All LPT Stage 3-6 72-52-00 Inspection/Check 03.
Disks and Hubs.
7R4D/D1/E/E1.................. 785058 and 785059 All HPT Stage 1 Disk 72-51-06 Inspection/Check-02.
Web 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. 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 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. These record keeping
requirements do not alter or amend the record keeping requirements
for any other AD or regulatory requirement.
Related Information
(k) Contact Mark Riley, Aerospace Engineer, Engine Certification
Office, FAA, Engine and Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; telephone (781) 238-7758, fax
(781) 238-7199; e-mail: mark.riley@faa.gov for more information
about this AD.
Issued in Burlington, Massachusetts, on March 1, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-4139 Filed 3-7-07; 8:45 am]
BILLING CODE 4910-13-P
