Airworthiness Directives; Pratt & Whitney PW4077D, PW4084D, PW4090, and PW4090-3 Turbofan Engines, 49335-49337 [E6-13909]
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Federal Register / Vol. 71, No. 163 / Wednesday, August 23, 2006 / Rules and Regulations
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Terminating Action
(g) The repetitive inspections required by
this AD may be terminated if all ballasts
installed on the airplane have P/N BR9000–
21, installed in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–33–51, Revision ‘A,’ dated
49335
April 20, 2005 (to replace ballast P/N
BA08006–1), or 8–33–52, dated April 15,
2005 (to replace ballast P/N BA08006–28–1).
Ballasts installed before the effective date of
this AD are also acceptable if done in
accordance with Bombardier Service Bulletin
8–33–51, dated August 16, 2002.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Parts Installation
(h) As of the effective date of this AD: No
person may install a ballast P/N BA08006–1
or BA08006–28–1 on any airplane.
Related Information
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, New York ACO, FAA,
has the authority to approve AMOCs for this
AD, if requested in accordance with the
procedures found in 14 CFR 39.19.
(j) Canadian airworthiness directive CF–
2004–26R1, dated September 28, 2005, also
addresses the subject of this AD.
Material Incorporated by Reference
(k) You must use the service information
identified in Table 2 of this AD to perform
the actions that are required by this AD,
unless the AD specifies otherwise.
TABLE 2.—MATERIAL INCORPORATED BY REFERENCE
de Havilland Temporary Revision—
To the de Havilland DASH 8 Series—
MRB–146, dated August 31, 2004 ...........................................................
MRB–147, dated May 3, 2005 .................................................................
MRB 2–24, dated August 31, 2004 ..........................................................
MRB 2–25, dated May 3, 2005 ................................................................
MRB 3–155, dated August 31, 2004 ........................................................
MRB 3–156, dated May 3, 2005 ..............................................................
sroberts on PROD1PC70 with RULES
(Page 2 of de Havilland Temporary
Revision MRB–147, dated May 3, 2005,
incorrectly refers to Series 300 airplanes; that
reference should be to Series 100.) If the
terminating action is accomplished, you must
use Bombardier Service Bulletin 8–33–51,
Revision ‘A,’ dated April 20, 2005; or
Bombardier Service Bulletin 8–33–52, dated
April 15, 2005, as applicable, to perform the
optional terminating action specified in this
AD. The Director of the Federal Register
approved the incorporation by reference of
these documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact
Bombardier, Inc., Bombardier Regional
Aircraft Division, 123 Garratt Boulevard,
Downsview, Ontario M3K 1Y5, Canada, for a
copy of this service information. You may
review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street, SW., Room PL–401,
Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at the NARA,
call (202) 741–6030, or go to https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on August
14, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–13829 Filed 8–22–06; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24034; Directorate
Identifier 2006–NE–05–AD; Amendment 39–
14729; AD 2006–17–08]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney PW4077D, PW4084D, PW4090,
and PW4090–3 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 Pratt &
Whitney (PW) PW4077D, PW4084D,
PW4090, and PW4090–3 turbofan
engines that were reassembled with
certain previously used high pressure
compressor (HPC) exit brush seal
assembly parts and certain new or
refurbished HPC exit diffuser air seal
inner lands. This AD requires replacing
the HPC exit inner and outer brush seal
packs with new brush seal packs, or
replacing the HPC exit brush seal
assembly with a new HPC exit brush
seal assembly. This AD results from a
report of oil leaking into the high
pressure turbine (HPT) interstage cavity
and igniting, leading to an engine case
penetration and engine in-flight
shutdown. Although liberated engine
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Manual
Manual
Manual
Manual
Manual
Manual
PSM
PSM
PSM
PSM
PSM
PSM
1–8–7.
1–8–7.
1–82–7.
1–82–7.
1–83–7.
1–83–7.
parts did not penetrate the engine
nacelle, we are issuing this AD to
prevent uncontained engine failure,
damage to the airplane, and injury to
passengers.
This AD becomes effective
September 27, 2006. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulations as
of September 27, 2006.
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 in
Room PL–401 on the plaza level of the
Nassif Building, 400 Seventh Street,
SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Antonio Cancelliere, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803; telephone (781)
238–7751; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed airworthiness directive (AD).
The proposed AD applies to Pratt &
Whitney (PW) PW4077D, PW4084D,
PW4090, and PW4090–3 turbofan
engines that were reassembled with
certain previously used HPC exit brush
seal assembly parts and certain new or
refurbished HPC exit diffuser air seal
DATES:
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49336
Federal Register / Vol. 71, No. 163 / Wednesday, August 23, 2006 / Rules and Regulations
inner lands. We published the proposed
AD in the Federal Register on April 19,
2006 (71 FR 20042). That action
proposed to require replacing the HPC
exit inner and outer brush seal packs
with new brush seal packs, or replacing
the HPC exit brush seal assembly with
a new HPC exit brush seal assembly.
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.
sroberts on PROD1PC70 with RULES
Request to More Accurately Describe
the Unsafe Condition
The Boeing Company requests that we
more accurately describe the unsafe
condition. They propose that we state
the unsafe condition as ‘‘This AD results
from a report of oil leaking into the high
pressure turbine (HPT) interstage cavity
and igniting, leading to an engine case
penetration and engine in-flight
shutdown. Although liberated engine
parts did not penetrate the engine
nacelle, we are proposing this AD to
prevent uncontained engine failure,
damage to the airplane, and injury to
passengers.’’
We agree and adopted the suggested
language.
Request for Clarification
Japan Airlines requests clarification of
the compliance on whether ‘‘cyclessince-last-overhaul (CSLO)’’ applies to
the engine’s last shop visit or if it
applies to overhaul of the HPC diffuser
assembly only.
We agree we need to clarify the
compliance. The CSLO applies to
overhaul of the HPC diffuser assembly
only. As a result of the comment, we
reworded compliance paragraphs (g)(1)
and (g)(2) to read as follows:
‘‘(1) By 3,000 cycles-in-service (CIS)
since a used HPC exit inner brush seal
pack and a new or refurbished HPC exit
diffuser air seal land were installed in
the engine, or by March 31, 2007,
whichever occurs later; however
VerDate Aug<31>2005
17:06 Aug 22, 2006
Jkt 208001
(2) If on March 31, 2007, the used
HPC exit inner brush seal pack coupled
with a new or refurbished HPC exit
diffuser air seal inner land assembly has
not accumulated 3,000 CIS, then by
3,000 CIS, or December 31, 2008,
whichever occurs first.’’
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 AD will affect
76 PW PW4077D, PW4084D, PW4090,
and PW4090–3 turbofan engines
installed on airplanes of U.S. registry.
We also estimate that it will take about
9 work-hours per engine to perform the
parts replacement, and that the average
labor rate is $80 per work-hour.
Required parts will cost about $100,017
per engine. Based on these figures, we
estimate the total cost of the AD to U.S.
operators to be $7,656,012.
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.
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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, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
I
2006–17–08 Pratt & Whitney: Amendment
39–14729. Docket No. FAA–2006–24034;
Directorate Identifier 2006–NE–05–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective September 27, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Pratt & Whitney
(PW) PW4077D, PW4084D, PW4090, and
PW4090–3 turbofan engines that were:
(1) Reassembled with a previously used
high pressure compressor (HPC) exit inner
brush seal pack, part number (P/N) 50J894–
01; and
(2) Reassembled with a new or refurbished
HPC exit diffuser air seal inner land, P/N
55H869.
(d) These engines are installed on, but not
limited to, Boeing 777 airplanes.
Unsafe Condition
(e) This AD results from a report of oil
leaking into the high pressure turbine (HPT)
interstage cavity and igniting, leading to an
engine case penetration and engine in-flight
shutdown. Although liberated engine parts
did not penetrate the engine nacelle, we are
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23AUR1
Federal Register / Vol. 71, No. 163 / Wednesday, August 23, 2006 / Rules and Regulations
issuing this AD to prevent uncontained
engine failure, damage to the airplane, and
injury to passengers.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Compliance
(f) You are responsible for having the
actions required by this AD performed at the
following compliance times, unless the
actions have already been done.
(g) Replace the HPC exit inner and outer
brush seal packs with new HPC exit inner
and outer brush seal packs, or replace the
HPC exit brush seal assembly with a new
HPC exit brush seal assembly as follows:
(1) By 3,000 cycles-in-service (CIS) since a
used HPC exit inner brush seal pack and a
new or refurbished HPC exit diffuser air seal
land were installed in the engine, or by
March 31, 2007, whichever occurs later;
however,
(2) If on March 31, 2007, the used HPC exit
inner brush seal pack coupled with a new or
refurbished HPC exit diffuser air seal inner
land assembly has not accumulated 3,000
CIS, then by 3,000 CIS, or December 31,
2008, whichever occurs first.
(h) Use the Accomplishment Instructions
of PW Service Bulletin No. PW4G–112-A72–
280, Revision 1, dated March 21, 2006, to do
the inner and outer brush pack replacements.
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) None.
Material Incorporated by Reference
sroberts on PROD1PC70 with RULES
(k) You must use Pratt & Whitney Service
Bulletin No. PW4G–112–A72–280, Revision
1, dated March 21, 2006, to perform the
replacements required by this AD. The
Director of the Federal Register approved the
incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Contact Pratt & Whitney,
400 Main St., East Hartford, CT 06108;
telephone (860) 565–8770; fax (860) 565–
4503, for a copy of this service information
for a copy of this service information. You
may review copies at the FAA, New England
Region, Office of the Regional Counsel, 12
New England Executive Park, Burlington,
MA; or at the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
August 14, 2006.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E6–13909 Filed 8–22–06; 8:45 am]
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14 CFR Part 39
[Docket No. FAA–2006–25657; Directorate
Identifier 2006–NM–187–AD; Amendment
39–14735; AD 2006–17–14]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model CL–600–2B19 (Regional Jet
Series 100 & 440) Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to certain Bombardier
Model CL–600–2B19 (Regional Jet
Series 100 & 440) airplanes. The existing
AD currently requires inspecting
contactors 1K4XD, 2K4XD, and K4XA to
determine the type of terminal base
plate, and applying sealant on the
terminal base plates, if necessary. This
new AD revises the effective date of the
existing AD. This AD results from
incidents of short circuit failures of
certain alternating current (AC)
contactors located in the avionics bay.
We are issuing this AD to prevent short
circuit failures of certain AC contactors,
which could result in arcing and
consequent smoke or fire.
DATES: This AD becomes effective
September 7, 2006.
On August 9, 2006 (71 FR 45364,
August 9, 2006), the Director of the
Federal Register approved the
incorporation by reference of
Bombardier Service Bulletin 601R–24–
122, Revision A, dated July 13, 2006.
We must receive any comments on
this AD by October 23, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
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49337
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Bombardier, Inc., Canadair,
Aerospace Group, P.O. Box 6087,
Station Centre-ville, Montreal, Quebec
H3C 3G9, Canada, for service
information identified in this AD.
You may examine the contents of the
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Room PL–401, on the plaza level
of the Nassif Building, Washington, DC.
This docket number is FAA–2006–
25657; the directorate identifier for this
docket is 2006–NM–187–AD.
FOR FURTHER INFORMATION CONTACT:
Wing Chan, Aerospace Engineer,
Systems and Flight Test Branch, ANE–
172, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, suite 410, Westbury, New York
11590; telephone (516) 228–7311; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
On July 31, 2006, the FAA issued AD
2006–16–07, amendment 39–14707 (71
FR 45364, August 9, 2006). That AD
applies to certain Bombardier Model
CL–600–2B19 (Regional Jet Series 100 &
440) airplanes. That AD requires
inspecting contactors 1K4XD, 2K4XD,
and K4XA to determine the type of
terminal base plate, and applying
sealant on the terminal base plates, if
necessary. That AD resulted from
incidents of short circuit failures of
certain alternating current (AC)
contactors located in the avionics bay.
The actions specified in that AD are
intended to prevent short circuit failures
of certain AC contactors, which could
result in arcing and consequent smoke
or fire.
Actions Since AD Was Issued
Since we issued that AD, we have
determined that the effective date of that
AD was inadvertently specified as the
same date as the publication date. The
effective date of the AD should be 15
days after the date of publication in the
Federal Register
FAA’s Determination and Requirements
of This AD
This airplane model is manufactured
in Canada and is type certificated for
operation in the United States under the
provisions of section 21.29 of the
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement. Pursuant to
this bilateral airworthiness agreement,
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
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]]>Agencies
[Federal Register Volume 71, Number 163 (Wednesday, August 23, 2006)]
[Rules and Regulations]
[Pages 49335-49337]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-13909]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24034; Directorate Identifier 2006-NE-05-AD;
Amendment 39-14729; AD 2006-17-08]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney PW4077D, PW4084D,
PW4090, and PW4090-3 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
Pratt & Whitney (PW) PW4077D, PW4084D, PW4090, and PW4090-3 turbofan
engines that were reassembled with certain previously used high
pressure compressor (HPC) exit brush seal assembly parts and certain
new or refurbished HPC exit diffuser air seal inner lands. This AD
requires replacing the HPC exit inner and outer brush seal packs with
new brush seal packs, or replacing the HPC exit brush seal assembly
with a new HPC exit brush seal assembly. This AD results from a report
of oil leaking into the high pressure turbine (HPT) interstage cavity
and igniting, leading to an engine case penetration and engine in-
flight shutdown. Although liberated engine parts did not penetrate the
engine nacelle, we are issuing this AD to prevent uncontained engine
failure, damage to the airplane, and injury to passengers.
DATES: This AD becomes effective September 27, 2006. The Director of
the Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of September 27, 2006.
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 in Room PL-401 on the plaza level of the Nassif Building, 400
Seventh Street, SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Antonio Cancelliere, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803;
telephone (781) 238-7751; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed airworthiness directive (AD). The proposed AD applies
to Pratt & Whitney (PW) PW4077D, PW4084D, PW4090, and PW4090-3 turbofan
engines that were reassembled with certain previously used HPC exit
brush seal assembly parts and certain new or refurbished HPC exit
diffuser air seal
[[Page 49336]]
inner lands. We published the proposed AD in the Federal Register on
April 19, 2006 (71 FR 20042). That action proposed to require replacing
the HPC exit inner and outer brush seal packs with new brush seal
packs, or replacing the HPC exit brush seal assembly with a new HPC
exit brush seal assembly.
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 More Accurately Describe the Unsafe Condition
The Boeing Company requests that we more accurately describe the
unsafe condition. They propose that we state the unsafe condition as
``This AD results from a report of oil leaking into the high pressure
turbine (HPT) interstage cavity and igniting, leading to an engine case
penetration and engine in-flight shutdown. Although liberated engine
parts did not penetrate the engine nacelle, we are proposing this AD to
prevent uncontained engine failure, damage to the airplane, and injury
to passengers.''
We agree and adopted the suggested language.
Request for Clarification
Japan Airlines requests clarification of the compliance on whether
``cycles-since-last-overhaul (CSLO)'' applies to the engine's last shop
visit or if it applies to overhaul of the HPC diffuser assembly only.
We agree we need to clarify the compliance. The CSLO applies to
overhaul of the HPC diffuser assembly only. As a result of the comment,
we reworded compliance paragraphs (g)(1) and (g)(2) to read as follows:
``(1) By 3,000 cycles-in-service (CIS) since a used HPC exit inner
brush seal pack and a new or refurbished HPC exit diffuser air seal
land were installed in the engine, or by March 31, 2007, whichever
occurs later; however
(2) If on March 31, 2007, the used HPC exit inner brush seal pack
coupled with a new or refurbished HPC exit diffuser air seal inner land
assembly has not accumulated 3,000 CIS, then by 3,000 CIS, or December
31, 2008, whichever occurs first.''
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 AD will affect 76 PW PW4077D, PW4084D,
PW4090, and PW4090-3 turbofan engines installed on airplanes of U.S.
registry. We also estimate that it will take about 9 work-hours per
engine to perform the parts replacement, and that the average labor
rate is $80 per work-hour. Required parts will cost about $100,017 per
engine. Based on these figures, we estimate the total cost of the AD to
U.S. operators to be $7,656,012.
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, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2006-17-08 Pratt & Whitney: Amendment 39-14729. Docket No. FAA-2006-
24034; Directorate Identifier 2006-NE-05-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective
September 27, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Pratt & Whitney (PW) PW4077D, PW4084D,
PW4090, and PW4090-3 turbofan engines that were:
(1) Reassembled with a previously used high pressure compressor
(HPC) exit inner brush seal pack, part number (P/N) 50J894-01; and
(2) Reassembled with a new or refurbished HPC exit diffuser air
seal inner land, P/N 55H869.
(d) These engines are installed on, but not limited to, Boeing
777 airplanes.
Unsafe Condition
(e) This AD results from a report of oil leaking into the high
pressure turbine (HPT) interstage cavity and igniting, leading to an
engine case penetration and engine in-flight shutdown. Although
liberated engine parts did not penetrate the engine nacelle, we are
[[Page 49337]]
issuing this AD to prevent uncontained engine failure, damage to the
airplane, and injury to passengers.
Compliance
(f) You are responsible for having the actions required by this
AD performed at the following compliance times, unless the actions
have already been done.
(g) Replace the HPC exit inner and outer brush seal packs with
new HPC exit inner and outer brush seal packs, or replace the HPC
exit brush seal assembly with a new HPC exit brush seal assembly as
follows:
(1) By 3,000 cycles-in-service (CIS) since a used HPC exit inner
brush seal pack and a new or refurbished HPC exit diffuser air seal
land were installed in the engine, or by March 31, 2007, whichever
occurs later; however,
(2) If on March 31, 2007, the used HPC exit inner brush seal
pack coupled with a new or refurbished HPC exit diffuser air seal
inner land assembly has not accumulated 3,000 CIS, then by 3,000
CIS, or December 31, 2008, whichever occurs first.
(h) Use the Accomplishment Instructions of PW Service Bulletin
No. PW4G-112-A72-280, Revision 1, dated March 21, 2006, to do the
inner and outer brush pack replacements.
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) None.
Material Incorporated by Reference
(k) You must use Pratt & Whitney Service Bulletin No. PW4G-112-
A72-280, Revision 1, dated March 21, 2006, to perform the
replacements required by this AD. The Director of the Federal
Register approved the incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108;
telephone (860) 565-8770; fax (860) 565-4503, for a copy of this
service information for a copy of this service information. You may
review copies at the FAA, New England Region, Office of the Regional
Counsel, 12 New England Executive Park, Burlington, MA; or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call 202-741-6030, or
go to: https://www.archives.gov/federal-register/cfr/ibr-
locations.html.
Issued in Burlington, Massachusetts, on August 14, 2006.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E6-13909 Filed 8-22-06; 8:45 am]
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