Airworthiness Directives; Pratt & Whitney (PW) JT9D-7R4 Series Turbofan Engines, 48549-48551 [E7-16665]
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Federal Register / Vol. 72, No. 164 / Friday, August 24, 2007 / Rules and Regulations
amendments because the Board for good
cause determined that delaying
implementation of the new primary and
secondary credit rates in order to allow
notice and public comment would be
unnecessary and contrary to the public
interest in fostering price stability and
sustainable economic growth. For these
same reasons, the Board also has not
provided 30 days prior notice of the
effective date of the rule under section
553(d).
List of Subjects in 12 CFR Part 201
For the reasons set forth in the
preamble, the Board is amending 12
CFR Chapter II to read as follows:
I
Authority: 12 U.S.C. 248(i)–(j), 343 et seq.,
347a, 347b, 347c, 348 et seq., 357, 374, 374a,
and 461.
2. In § 201.51, paragraphs (a) and (b)
are revised to read as follows:
I
(a) Primary credit. The interest rates
for primary credit provided to
depository institutions under § 201.4(a)
are:
Effective
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17,
17,
17,
17,
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2007.
2007.
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2007.
(b) Secondary credit. The interest
rates for secondary credit provided to
depository institutions under 201.4(b)
are:
rfrederick on PROD1PC67 with RULES
Federal Reserve
Bank
Rate
Boston ................
6.25
Effective
August 17, 2007.
1 The primary, secondary, and seasonal credit
rates described in this section apply to both
advances and discounts made under the primary,
secondary, and seasonal credit programs,
respectively.
VerDate Aug<31>2005
12:50 Aug 23, 2007
Jkt 211001
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17,
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2007.
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. FAA–2006–23742; Directorate
Identifier 2005–NE–53–AD; Amendment 39–
15180; AD 2007–17–21]
RIN 2120–AA64
§ 201.51 Interest rates applicable to credit
extended by a Federal Reserve Bank.1
August
August
August
August
August
August
August
August
August
August
August
August
*
August
August
August
August
August
August
August
August
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August
Federal Aviation Administration
1. The authority citation for part 201
continues to read as follows:
I
5.75
5.75
5.75
5.75
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6.25
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BILLING CODE 6210–02–P
PART 201—EXTENSIONS OF CREDIT
BY FEDERAL RESERVE BANKS
(REGULATION A)
Boston ................
New York ...........
Philadelphia ........
Cleveland ...........
Richmond ...........
Atlanta ................
Chicago ..............
St. Louis .............
Minneapolis ........
Kansas City ........
Dallas .................
San Francisco ....
New York ...........
Philadelphia ........
Cleveland ...........
Richmond ...........
Atlanta ................
Chicago ..............
St. Louis .............
Minneapolis ........
Kansas City ........
Dallas .................
San Francisco ....
Effective
By order of the Board of Governors of the
Federal Reserve System, August 20, 2007.
Jennifer J. Johnson,
Secretary of the Board.
[FR Doc. E7–16764 Filed 8–23–07; 8:45 am]
Authority and Issuance
Rate
Rate
*
Banks, Banking, Federal Reserve
System, Reporting and recordkeeping.
Federal Reserve
Bank
Federal Reserve
Bank
Airworthiness Directives; Pratt &
Whitney (PW) JT9D–7R4 Series
Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for PW
JT9D–7R4 series turbofan engines. This
AD requires removing reduced cooling
flow 2nd stage high pressure turbine
(HPT) vane assemblies, part numbers
(P/Ns) 797282, 796972, 800082, 800072,
803182, 803282, and 822582, installed
in 2nd stage HPT vane cluster
assemblies P/Ns 797592, 797372,
799872, 799782, and 822572. It also
requires a visual and a fluorescent
penetrant inspection (FPI) of the 2nd
stage HPT air seal assembly, P/N
815097. This AD results from a report of
an uncontained failure of the 2nd stage
HPT air seal assembly, caused by the air
seal assembly brace disengaging from
the air seal, due to insufficient cooling
air flow. We are issuing this AD to
prevent uncontained failure of the 2nd
stage HPT air seal assembly, leading to
engine in-flight shutdown and damage
to the airplane.
DATES: This AD becomes effective
September 28, 2007. The Director of the
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48549
Federal Register approved the
incorporation by reference of certain
publications listed in the regulations as
of September 28, 2007.
ADDRESSES: You can get the service
information identified in this AD from
Pratt & Whitney, 400 Main St., East
Hartford, CT 06108; telephone (860)
565–8770; fax (860) 565–4503.
You may examine the AD docket on
the Internet at https://dms.dot.gov or at
the U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
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.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to PW JT9D–7R4E1, –7R4E4,
–7R4G2, and –7R4H1 turbofan engines.
We published the proposed AD in the
Federal Register on February 2, 2007
(72 FR 4964). That action proposed to
require removal of reduced cooling flow
2nd stage HPT vane assemblies. It also
proposed to require a visual and an FPI
of the 2nd stage HPT air seal assembly.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains the NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is
provided in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Revise the Cost Impact
FEDEX requests that we revise the
estimated cost impact to implement the
AD because they believe that the actual
cost of modification (according to PW
Alert Service Bulletin (ASB) JT9D–7R4–
A72–596, dated September 15, 2005) for
one set of HPT 2nd stage vane
assemblies will be approximately
$23,000, instead of $5,400 projected by
the proposed AD. We do not agree. We
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48550
Federal Register / Vol. 72, No. 164 / Friday, August 24, 2007 / Rules and Regulations
provided the estimated material cost of
$5,400 per engine from the engine
manufacturer in the Costs of
Compliance section in the proposed AD.
Parts included new 2nd stage HPT vane
covers, part number (P/N) 822734, and
rivets, P/N ST1219–213, that are
required to modify the 2nd stage HPT
vane cluster assemblies, as specified in
ASB JT9D–7R4–A72–596, dated
September 15, 2005. However, based on
latest pricing information in the PW
spare parts price catalog, we increased
the estimated material cost to $6,700.
We also estimate that it will take about
65.5 work-hours per engine to perform
the actions, and that the average labor
rate is $80 per work-hour. Based on
these figures, we estimate the total cost
of the AD to be $11,940 per engine.
rfrederick on PROD1PC67 with RULES
Revise the Applicability Section
Boeing Company asks that we revise
paragraph (c) of the AD to remove the
reference to the Boeing model 747–
200B, –200C, –200F, and –300
airplanes. Boeing states that the JT9D–
7R4E1, –7R4E4, and –7R4H1 are not
used on any model Boeing 747 and the
description implies that these engines
may be installed on the Boeing 747
airplane. We partially agree. We
removed the letter designations for the
747–200 series airplanes. However, we
do not agree that the airplane listing in
paragraph (c) implies that the JT9D–
7R4E1, –7R4E4, and –7R4H1 engines
may be installed on the Boeing 747. The
airplane references in paragraph (c) are
informative only. The Type Certificate
Data Sheet for an airplane specifies the
engines that are installed on the
airplane, not the applicability paragraph
of an AD.
PW asks that we revise the
Applicability section to clarify the
affected engine models. They also
request that we add the following
aircraft to the list of airplanes that can
have these engines installed: Boeing
767–200, Airbus A300–600, and A310–
300.
We partially agree and revised the
Applicability section of the AD to add
Boeing 767–200, and Airbus A300–600
and A310–300 airplane models to
paragraph (c) of the AD. We do not agree
that we need to clarify the engine
models with Pratt & Whitney internal
model designation. We specify the
affected engines by the model
designations specified in the Type
Certificate Data Sheet for the engine.
Revise Paragraph (f) of the Compliance
Section
PW asks that we revise paragraph (f)
of the Compliance section to delete the
specific lenticular seal part number
VerDate Aug<31>2005
12:50 Aug 23, 2007
Jkt 211001
reference, as there are other lenticular
seal part numbers in the field that will
also require visual and FPI inspections
at the next HPT module exposure. We
partially agree. The specific lenticular
seal part number should be removed
from paragraph (f) of the Compliance
section of the AD because there are
other lenticular seal part numbers in the
field that will also require inspections.
However, to prevent further delay in
addressing the unsafe condition, we are
issuing this AD with the specific
lenticular seal part number listed.
Removal of the part number will expand
the number of parts requiring inspection
and we must give the public an
opportunity to comment on this change
before we can incorporate it. We will
supersede this AD to remove the
lenticular seal part number.
List Required Lenticular Seal
Inspections
PW asks that we revise paragraph (f)
of the Compliance section to list all of
the specific inspections required for the
lenticular seal. We agree and listed each
inspection procedure in the PW engine
manual required for the lenticular seal.
We also changed the paragraph to (g).
Revise Paragraph (g) of the Compliance
Section
PW also asks that we revise paragraph
(g) of the Compliance section to
reference the associated 2nd stage HPT
vane cluster assemblies (higher level
assembly) that have reduced cooling
flow 2nd stage HPT vane assemblies
installed, because airlines may not
recognize individual 2nd stage vane
assemblies. We agree. We revised
paragraph (g) of the Compliance section
to state the following: ‘‘At the next HPT
module exposure, remove reduced
cooling flow 2nd stage HPT vane
assemblies, P/Ns 797282, 796972,
800082, 800072, 803182, 803282, and
822582, installed in 2nd stage HPT vane
cluster assemblies, P/Ns 797592,
797372, 799872, 799782, and 822572.’’
We also designated the paragraph as (f).
Correct Errors and Remove Duplicate
P/N Reference
Boeing Company asks that we correct
typographical errors for the engine
designations in paragraph (c) in the
Applicability section. Boeing states that
the JT9D–74R4E1, –74R4E4, –74R4G2,
and –74R4H1 should be JT9D–7R4E1,
–7R4E4, –7R4G2, and –7R4H1,
respectively.
Boeing also asks that we revise
paragraph (g) in the Compliance section
to remove a duplicate reference to part
number 803182. We agree and corrected
the Applicability section and the
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Sfmt 4700
duplicate P/N reference in paragraph
(g).
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 this proposed AD
would affect 85 PW JT9D–7R4 series
turbofan engines installed on airplanes
U.S. registry. We also estimate that it
will take about 65.5 work-hours per
engine to perform the actions, and that
the average labor rate is $80 per workhour. Required parts will cost about
$6,700 per engine. Based on these
figures, we estimate the total cost of the
AD to U.S. operators to be $1,014,900.
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
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Federal Register / Vol. 72, No. 164 / Friday, August 24, 2007 / Rules and Regulations
(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
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
I
Definition
(h) For the purpose of this AD, an HPT
module exposure is defined as removing the
1st stage HPT rotor or the 2nd stage HPT
rotor from the HPT case.
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
I
2007–17–21 Pratt & Whitney: Amendment
39–15180. Docket No. FAA–2006–23742;
Directorate Identifier 2005–NE–53–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective September 28, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Pratt & Whitney
(PW) JT9D–7R4G2, –7R4E1, –7R4E4, and
–7R4H1 series turbofan engines. These
engines are installed on, but not limited to,
Boeing 747–200, –300, 767–200, and Airbus
A300–600 and A310–300 series airplanes.
rfrederick on PROD1PC67 with RULES
Unsafe Condition
(d) This AD results from a report of an
uncontained failure of the 2nd stage high
pressure turbine (HPT) air seal assembly,
caused by the air seal assembly brace
disengaging from the air seal, due to
insufficient cooling air flow. We are issuing
this AD to prevent uncontained failure of the
2nd stage HPT air seal assembly, leading to
engine in-flight shutdown and damage to the
airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed at the
next HPT module exposure after the effective
date of this AD, unless the actions have
already been done.
(f) At the next HPT module exposure,
remove reduced cooling flow 2nd stage HPT
vane assemblies part numbers (P/Ns):
797282, 796972, 800082, 800072, 803182,
VerDate Aug<31>2005
12:50 Aug 23, 2007
Jkt 211001
803282, and 822582, installed in 2nd stage
HPT vane cluster assemblies: P/Ns 797592,
797372, 799872, 799782, and 822572.
(g) For 2nd stage HPT air seals that have
operated in an engine with reduced cooling
flow HPT vane assemblies, at the next HPT
module exposure do the following:
(1) Perform a onetime visual inspection of
the 2nd stage HPT air seal assembly, P/N
815097, using instructions in JT9D–7R4
engine manual, Section 72–51–22,
Inspection/Check-01, paragraphs 1.D.(1),
1.D.(4), and 1.D.(6).
(2) Perform a fluorescent penetrant
inspection (FPI) of the 2nd stage HPT air seal
assembly for cracks, using instructions in
JT9D–7R4 engine manual, Section 71–51–00,
Inspection/Check-03.
Alternative Methods of Compliance
(i) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Related Information
(j) Pratt & Whitney Alert Service Bulletin
JT9D–7R4–A72–596, dated September 15,
2005, contains information for modifying the
reduced cooling flow 2nd stage HPT vane
assemblies.
Issued in Burlington, Massachusetts, on
August 17, 2007.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–16665 Filed 8–23–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF THE TREASURY
Internal Revenue Service
26 CFR Parts 1 and 602
[TD 9357]
RIN 1545–BE09
Elimination of Country-by-Country
Reporting to Shareholders of Foreign
Taxes Paid by Regulated Investment
Companies
Internal Revenue Service (IRS),
Treasury.
ACTION: Final regulations.
AGENCY:
SUMMARY: This document contains final
regulations that generally eliminate
country-by-country reporting by a
regulated investment company (RIC) to
its shareholders of foreign source
income that the RIC takes into account
and foreign taxes that it pays. This
change is necessary to conform the
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48551
regulations to changes in the tax law
relating to the foreign tax credit. These
final regulations will affect certain RICs
that pay foreign taxes and the
shareholders of those RICs.
DATES: Effective Date: These regulations
are effective August 24, 2007.
Applicability Date: These regulations
are applicable for RIC taxable years
ending on or after December 31, 2007.
For reporting purposes, however, a
taxpayer may rely on the current
regulations for a taxable year ending on
or after December 31, 2007, and
beginning before August 24, 2007.
FOR FURTHER INFORMATION CONTACT:
Richard C. LaFalce, (202) 622–3930 (not
a toll-free number).
SUPPLEMENTARY INFORMATION:
Paperwork Reduction Act
The collection of information
contained in these final regulations has
been reviewed and approved by the
Office of Management and Budget in
accordance with the Paperwork
Reduction Act of 1995 (44 U.S.C.
3507(d)) under control number 1545–
2035. Comments on the accuracy of the
estimated burden and suggestions for
reducing the burden should be sent to
the Internal Revenue Service, Attn: IRS
Reports Clearance Officer,
SE:W:CAR:MP:T:T:SP, Washington, DC
20224.
The collection of information in these
final regulations is in § 1.853–4(c) and
(d). A RIC is required to notify the IRS
of amounts of income received from
sources within foreign countries and
possessions of the United States and
taxes paid to each such foreign country
or possession in order that the IRS may
monitor shareholder compliance with
the foreign tax credit provisions. The
collection of information is required if
a RIC elects to pass through the benefits
of the foreign tax credit to its
shareholders.
Estimated total annual recordkeeping
burden: 80 hours.
Estimated average annual burden per
recordkeeper: 2 hours.
Estimated number of recordkeepers:
40.
Estimated frequency of recordkeeping:
Annually.
An agency may not conduct or
sponsor, and a person is not required to
respond to, a collection of information
unless it displays a valid control
number.
Books or records relating to a
collection of information must be
retained as long as their contents may
become material in the administration
of any internal revenue law. Generally,
tax returns and tax return information
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]]>Agencies
[Federal Register Volume 72, Number 164 (Friday, August 24, 2007)]
[Rules and Regulations]
[Pages 48549-48551]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-16665]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23742; Directorate Identifier 2005-NE-53-AD;
Amendment 39-15180; AD 2007-17-21]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney (PW) JT9D-7R4 Series
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for PW
JT9D-7R4 series turbofan engines. This AD requires removing reduced
cooling flow 2nd stage high pressure turbine (HPT) vane assemblies,
part numbers (P/Ns) 797282, 796972, 800082, 800072, 803182, 803282, and
822582, installed in 2nd stage HPT vane cluster assemblies P/Ns 797592,
797372, 799872, 799782, and 822572. It also requires a visual and a
fluorescent penetrant inspection (FPI) of the 2nd stage HPT air seal
assembly, P/N 815097. This AD results from a report of an uncontained
failure of the 2nd stage HPT air seal assembly, caused by the air seal
assembly brace disengaging from the air seal, due to insufficient
cooling air flow. We are issuing this AD to prevent uncontained failure
of the 2nd stage HPT air seal assembly, leading to engine in-flight
shutdown and damage to the airplane.
DATES: This AD becomes effective September 28, 2007. The Director of
the Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of September 28, 2007.
ADDRESSES: You can get the service information identified in this AD
from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone
(860) 565-8770; fax (860) 565-4503.
You may examine the AD docket on the Internet at https://dms.dot.gov
or at the U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: 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.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to PW JT9D-7R4E1, -7R4E4, -
7R4G2, and -7R4H1 turbofan engines. We published the proposed AD in the
Federal Register on February 2, 2007 (72 FR 4964). That action proposed
to require removal of reduced cooling flow 2nd stage HPT vane
assemblies. It also proposed to require a visual and an FPI of the 2nd
stage HPT air seal assembly.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov; or in person at the Docket Operations office between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains the NPRM, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone (800) 647-5527) is provided in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Revise the Cost Impact
FEDEX requests that we revise the estimated cost impact to
implement the AD because they believe that the actual cost of
modification (according to PW Alert Service Bulletin (ASB) JT9D-7R4-
A72-596, dated September 15, 2005) for one set of HPT 2nd stage vane
assemblies will be approximately $23,000, instead of $5,400 projected
by the proposed AD. We do not agree. We
[[Page 48550]]
provided the estimated material cost of $5,400 per engine from the
engine manufacturer in the Costs of Compliance section in the proposed
AD. Parts included new 2nd stage HPT vane covers, part number (P/N)
822734, and rivets, P/N ST1219-213, that are required to modify the 2nd
stage HPT vane cluster assemblies, as specified in ASB JT9D-7R4-A72-
596, dated September 15, 2005. However, based on latest pricing
information in the PW spare parts price catalog, we increased the
estimated material cost to $6,700. We also estimate that it will take
about 65.5 work-hours per engine to perform the actions, and that the
average labor rate is $80 per work-hour. Based on these figures, we
estimate the total cost of the AD to be $11,940 per engine.
Revise the Applicability Section
Boeing Company asks that we revise paragraph (c) of the AD to
remove the reference to the Boeing model 747-200B, -200C, -200F, and -
300 airplanes. Boeing states that the JT9D-7R4E1, -7R4E4, and -7R4H1
are not used on any model Boeing 747 and the description implies that
these engines may be installed on the Boeing 747 airplane. We partially
agree. We removed the letter designations for the 747-200 series
airplanes. However, we do not agree that the airplane listing in
paragraph (c) implies that the JT9D-7R4E1, -7R4E4, and -7R4H1 engines
may be installed on the Boeing 747. The airplane references in
paragraph (c) are informative only. The Type Certificate Data Sheet for
an airplane specifies the engines that are installed on the airplane,
not the applicability paragraph of an AD.
PW asks that we revise the Applicability section to clarify the
affected engine models. They also request that we add the following
aircraft to the list of airplanes that can have these engines
installed: Boeing 767-200, Airbus A300-600, and A310-300.
We partially agree and revised the Applicability section of the AD
to add Boeing 767-200, and Airbus A300-600 and A310-300 airplane models
to paragraph (c) of the AD. We do not agree that we need to clarify the
engine models with Pratt & Whitney internal model designation. We
specify the affected engines by the model designations specified in the
Type Certificate Data Sheet for the engine.
Revise Paragraph (f) of the Compliance Section
PW asks that we revise paragraph (f) of the Compliance section to
delete the specific lenticular seal part number reference, as there are
other lenticular seal part numbers in the field that will also require
visual and FPI inspections at the next HPT module exposure. We
partially agree. The specific lenticular seal part number should be
removed from paragraph (f) of the Compliance section of the AD because
there are other lenticular seal part numbers in the field that will
also require inspections. However, to prevent further delay in
addressing the unsafe condition, we are issuing this AD with the
specific lenticular seal part number listed. Removal of the part number
will expand the number of parts requiring inspection and we must give
the public an opportunity to comment on this change before we can
incorporate it. We will supersede this AD to remove the lenticular seal
part number.
List Required Lenticular Seal Inspections
PW asks that we revise paragraph (f) of the Compliance section to
list all of the specific inspections required for the lenticular seal.
We agree and listed each inspection procedure in the PW engine manual
required for the lenticular seal. We also changed the paragraph to (g).
Revise Paragraph (g) of the Compliance Section
PW also asks that we revise paragraph (g) of the Compliance section
to reference the associated 2nd stage HPT vane cluster assemblies
(higher level assembly) that have reduced cooling flow 2nd stage HPT
vane assemblies installed, because airlines may not recognize
individual 2nd stage vane assemblies. We agree. We revised paragraph
(g) of the Compliance section to state the following: ``At the next HPT
module exposure, remove reduced cooling flow 2nd stage HPT vane
assemblies, P/Ns 797282, 796972, 800082, 800072, 803182, 803282, and
822582, installed in 2nd stage HPT vane cluster assemblies, P/Ns
797592, 797372, 799872, 799782, and 822572.'' We also designated the
paragraph as (f).
Correct Errors and Remove Duplicate P/N Reference
Boeing Company asks that we correct typographical errors for the
engine designations in paragraph (c) in the Applicability section.
Boeing states that the JT9D-74R4E1, -74R4E4, -74R4G2, and -74R4H1
should be JT9D-7R4E1, -7R4E4, -7R4G2, and -7R4H1, respectively.
Boeing also asks that we revise paragraph (g) in the Compliance
section to remove a duplicate reference to part number 803182. We agree
and corrected the Applicability section and the duplicate P/N reference
in paragraph (g).
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 this proposed AD would affect 85 PW JT9D-7R4
series turbofan engines installed on airplanes U.S. registry. We also
estimate that it will take about 65.5 work-hours per engine to perform
the actions, and that the average labor rate is $80 per work-hour.
Required parts will cost about $6,700 per engine. Based on these
figures, we estimate the total cost of the AD to U.S. operators to be
$1,014,900.
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
[[Page 48551]]
(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 adding the following new airworthiness
directive:
2007-17-21 Pratt & Whitney: Amendment 39-15180. Docket No. FAA-2006-
23742; Directorate Identifier 2005-NE-53-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective
September 28, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Pratt & Whitney (PW) JT9D-7R4G2, -7R4E1,
-7R4E4, and -7R4H1 series turbofan engines. These engines are
installed on, but not limited to, Boeing 747-200, -300, 767-200, and
Airbus A300-600 and A310-300 series airplanes.
Unsafe Condition
(d) This AD results from a report of an uncontained failure of
the 2nd stage high pressure turbine (HPT) air seal assembly, caused
by the air seal assembly brace disengaging from the air seal, due to
insufficient cooling air flow. We are issuing this AD to prevent
uncontained failure of the 2nd stage HPT air seal assembly, leading
to engine in-flight shutdown and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed at the next HPT module exposure after the effective
date of this AD, unless the actions have already been done.
(f) At the next HPT module exposure, remove reduced cooling flow
2nd stage HPT vane assemblies part numbers (P/Ns): 797282, 796972,
800082, 800072, 803182, 803282, and 822582, installed in 2nd stage
HPT vane cluster assemblies: P/Ns 797592, 797372, 799872, 799782,
and 822572.
(g) For 2nd stage HPT air seals that have operated in an engine
with reduced cooling flow HPT vane assemblies, at the next HPT
module exposure do the following:
(1) Perform a onetime visual inspection of the 2nd stage HPT air
seal assembly, P/N 815097, using instructions in JT9D-7R4 engine
manual, Section 72-51-22, Inspection/Check-01, paragraphs 1.D.(1),
1.D.(4), and 1.D.(6).
(2) Perform a fluorescent penetrant inspection (FPI) of the 2nd
stage HPT air seal assembly for cracks, using instructions in JT9D-
7R4 engine manual, Section 71-51-00, Inspection/Check-03.
Definition
(h) For the purpose of this AD, an HPT module exposure is
defined as removing the 1st stage HPT rotor or the 2nd stage HPT
rotor from the HPT case.
Alternative Methods of Compliance
(i) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Related Information
(j) Pratt & Whitney Alert Service Bulletin JT9D-7R4-A72-596,
dated September 15, 2005, contains information for modifying the
reduced cooling flow 2nd stage HPT vane assemblies.
Issued in Burlington, Massachusetts, on August 17, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-16665 Filed 8-23-07; 8:45 am]
BILLING CODE 4910-13-P
