Airworthiness Directives; Dassault Model Falcon 2000 Airplanes Equipped With CFE Company CFE738-1-1B Turbofan Engines, 73577-73579 [05-23829]
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73577
Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations
Effective Date
(a) This AD becomes effective January 17,
2006.
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
Affected ADs
(b) This AD supersedes AD 2004–15–02,
Amendment 39–13736.
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
removing Amendment 39–13736 (69 FR
44925, August 12, 2004) and by adding
a new airworthiness directive,
Amendment 39–14404, to read as
follows:
I
2005–25–11 Rolls-Royce plc: Amendment
39–14404. Docket No. 2003–NE–38–AD.
Applicability
(c) This AD applies to Rolls-Royce plc (RR)
models RB211 Trent 875–17, Trent 877–17,
Trent 884–17, Trent 884B–17, Trent 892–17,
Trent 892B–17, and Trent 895–17 turbofan
engines, with low pressure (LP) compressor
fan blades, part number FW18548 installed.
These engines are installed on, but not
limited to, Boeing 777 series airplanes.
Unsafe Condition
(d) This AD results from a number of new
production LP compressor blades found with
surfaces formed outside of design intent. We
are issuing this AD to prevent possible
multiple uncontained LP compressor fan
blade failure, due to cracking in the blade
root caused by increased stresses in the shear
key slots.
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.
Actions Required for LP Compressor Fan
Blades
(f) Replace LP compressor fan blades with
new or previously reworked LP compressor
blades before accumulating the specified
cycles-since-new (CSN) in the following
Table 1, or rework the existing blades as
specified in paragraph (g) of this AD.
TABLE 1.—LP COMPRESSOR FAN BLADE REPLACEMENT OR REWORK SCHEDULE
Airplane
maximum gross
weight
(times 1,000
pounds)
Boeing 777 Series:
.......................................................................................................................
.......................................................................................................................
.......................................................................................................................
.......................................................................................................................
.......................................................................................................................
.......................................................................................................................
.......................................................................................................................
.......................................................................................................................
.......................................................................................................................
(g) Rework LP compressor fan blades at or
before accumulating the specified CSN in
Table 1 of this AD. Follow paragraphs 3.B.(1)
through 3.B.(22) of Accomplishment
Instructions of RR service bulletin (SB) No.
RB.211–72–E044, Revision 2, dated October
8, 2004, to do the blade rework.
(h) For engines moved between
configurations, calculate the cycles
remaining using either of the following:
(1) Subtract the total CSN from the most
limiting configuration’s limit from Table 1 of
this AD; or
(2) Calculate the cycles remaining using
the following equation:
X X
X
X r = Lc 1 − 1 + 2 + 3 + .....
L1 L 2 L3
Where:
Xr = Cycles remaining in current
configuration.
Lc = Cyclic limit of current configuration
from Table 1 of this AD.
Xn = Cycles accumulated in configuration n.
Ln = Cyclic limit in configuration n from
Table 1 of this AD.
(i) Information on the source life of the
cycle limits in Table 1 of this AD can be
found in RR Alert SB No. RB.211–72–AE055,
Revision 3, dated May 28, 2004.
VerDate Aug<31>2005
16:47 Dec 12, 2005
Jkt 208001
660, 632.5
656
648
632.5
632.5
555
545
535
506
–884, –892, –884B
–892, –895
–892, –892B
–892B
–892
–884
–877
–875
–875
Replace or
rework LP
compressor fan
blades before
accumulating:
2,400
2,400
3,200
3,200
4,100
4,100
4,100
4,100
4,100
CSN.
CSN.
CSN.
CSN.
CSN.
CSN.
CSN.
CSN.
CSN.
Alternative Methods of Compliance
(j) 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.
Issued in Burlington, Massachusetts, on
December 5, 2005.
Carlos Pestana,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–23834 Filed 12–12–05; 8:45 am]
Material Incorporated by Reference
(k) You must use Rolls-Royce plc Service
Bulletin No. RB.211–72–E044, Revision 2,
dated October 8, 2004, to perform the blade
rework 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. You can get a copy from
Rolls-Royce plc, PO Box 31, Derby, England,
DE248BJ; telephone: 011–44–1332–242424;
fax: 011–44–1332–245418. You can review a
copy 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.
BILLING CODE 4910–13–P
Related Information
(l) CAA airworthiness directive G–2004–
030, dated December 23, 2004, and RR Alert
SB No. RB.211–72–AE055, Revision 4, dated
December 9, 2004, pertain to the subject of
this AD.
PO 00000
Frm 00025
Fmt 4700
Sfmt 4700
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22560; Directorate
Identifier 2005–NM–061–AD; Amendment
39–14408; AD 2005–25–15]
RIN 2120–AA64
Airworthiness Directives; Dassault
Model Falcon 2000 Airplanes Equipped
With CFE Company CFE738–1–1B
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 certain
E:\FR\FM\13DER1.SGM
13DER1
ER13DE05.008</GPH>
–300
–200
–200
–200
–200
–200
–200
–200
–200
RB211 Trent Engine
Model
73578
Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations
Dassault Model Falcon 2000 airplanes
equipped with CFE Company CFE738–
1–1B turbofan engines. This AD requires
determining the serial number of the
engines installed on the airplane,
inspecting any affected engine to verify
that a spherical bearing is installed on
the attachment fitting of the engine
mount, and corrective action if
necessary. This AD results from a report
of a missing spherical bearing on the
attachment fitting of the front engine
mount on an in-service airplane, and
subsequent damage and abnormal
fatigue of the attachment fitting. We are
issuing this AD to prevent reduced
structural integrity of the engine mount,
which could result in possible
separation of an engine from the
airplane.
DATES: This AD becomes effective
January 17, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of January 17, 2006.
ADDRESSES: You may examine 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., Nassif Building, room PL–401,
Washington, DC.
Contact Dassault Falcon Jet, P.O. Box
2000, South Hackensack, New Jersey
07606, for service information identified
in this AD.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 227–1137; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply certain Dassault Model Falcon
2000 airplanes equipped with CFE
Company CFE738–1–1B turbofan
engines. That NPRM was published in
the Federal Register on September 30,
VerDate Aug<31>2005
16:47 Dec 12, 2005
Jkt 208001
2005 (70 FR 57217). That NPRM
proposed to require determining the
serial number of the engines installed
on the airplane, inspecting any affected
engine to verify that a spherical bearing
is installed on the attachment fitting of
the engine mount, and corrective action
if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the NPRM or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed.
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have changed this AD to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Costs of Compliance
This inspection affects about 7
airplanes of U.S. registry. The
inspection will take about 2 work hours
per airplane, at an average labor rate of
$65 per work hour. Based on these
figures, the estimated cost of the AD for
U.S. operators is $910, or $130 per
airplane.
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
PO 00000
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Fmt 4700
Sfmt 4700
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 regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
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 FAA 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 Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2005–25–15 Dassault Aviation:
Amendment 39–14408. Docket No.
FAA–2005–22560; Directorate Identifier
2005–NM–061–AD
Effective Date
(a) This AD becomes effective January 17,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Dassault Model
Falcon 2000 airplanes, certificated in any
category; equipped with CFE Company
CFE738–1–1B turbofan engines.
Unsafe Condition
(d) This AD results from a report of a
missing spherical bearing on the attachment
fitting of the front engine mount on an inservice airplane, and subsequent damage and
abnormal fatigue of the attachment fitting.
E:\FR\FM\13DER1.SGM
13DER1
Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations
We are issuing this AD to prevent reduced
structural integrity of the engine mount,
which could result in possible separation of
an engine from 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.
Determine Serial Number (S/N) and Inspect
if Necessary
(f) Within the applicable compliance time
specified in paragraph (f)(1), (f)(2), or (f)(3) of
this AD: Determine the serial number of the
engines installed on the airplane, as
identified in the table in paragraph 1.A.,
‘‘Effectivity,’’ of Dassault Service Bulletin
F2000–299, dated July 23, 2004; if any
affected serial number is found on any
engine, perform a borescope inspection to
verify that a spherical bearing is installed on
the attachment fitting of the front engine
mount by doing all the applicable actions
specified in the Accomplishment
Instructions of the service bulletin.
(1) For airplanes with any engine having
850 total landings or less as of the effective
date of this AD: Before the accumulation of
880 total landings on the engine.
(2) For airplanes with any engine having
more than 850 total landings, but 1,000 total
landings or less as of the effective date of this
AD: Within 1 month after the effective date
of this AD.
(3) For airplanes with any engine having
more than 1,000 total landings as of the
effective date of this AD: Within 10 landings
after the effective date of this AD.
Corrective Action
(g) If any spherical bearing is found
missing during the inspection required by
paragraph (f) of this AD: Before further flight,
repair according to a method approved by
either the Manager, International Branch,
ANM–116, Transport Airplane Directorate,
´ ´
FAA; or the Direction Generale de l’Aviation
Civile (or its delegated agent).
No Reporting Requirement
(h) This AD does not require submitting
reporting information to the manufacturer.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, International Branch,
ANM–116, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
Related Information
(j) French airworthiness directive F–2004–
128, issued August 4, 2004, also addresses
the subject of this AD.
Material Incorporated by Reference
(k) You must use Dassault Service Bulletin
F2000–299, dated July 23, 2004, to perform
VerDate Aug<31>2005
16:47 Dec 12, 2005
Jkt 208001
the actions that are required by this AD,
unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference of this document
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Contact Dassault Falcon Jet, P.O. Box
2000, South Hackensack, New Jersey 07606,
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
December 2, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–23829 Filed 12–12–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22928; Directorate
Identifier 2005–NE–43–AD; Amendment 39–
14406; AD 2005–25–13]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
Arriel 2B and 2B1 Turboshaft Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for
Turbomeca Arriel 2B and 2B1 turboshaft
engines without modification TU22
incorporated. This AD requires initial
and repetitive visual checks of the free
turbine shield for cracks. This AD
results from reports of several free
turbine shields found with large
circumferential cracks. We are issuing
this AD to prevent failure of the free
turbine shield, leading to engine
misalignment, in-flight engine
shutdown, emergency autorotation
landing, or accident.
DATES: Effective December 28, 2005. The
Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulations as of December 28, 2005.
We must receive any comments on
this AD by February 13, 2006.
PO 00000
Frm 00027
Fmt 4700
Sfmt 4700
73579
Use one of the following
addresses to comment 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–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Turbomeca, 40220 Tarnos,
France; telephone 33 05 59 74 40 00, fax
33 05 59 74 45 15, for the service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Christopher Spinney, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803–5299; telephone
(781) 238–7175; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION: The
Direction Generale de L’Aviation Civile
(DGAC), which is the airworthiness
authority for France, notified us that an
unsafe condition might exist on
Turbomeca Arriel 2B and 2B1 turboshaft
engines without modification TU22
incorporated. The DGAC advises that on
several of these engines, large
circumferential cracks were found in the
free turbine shield at the blending
radius between the containment shield
and the rear flange. These cracks could
cause a loss of engine alignment during
maneuvering loads and lead to in-flight
engine shutdown.
ADDRESSES:
Relevant Service Information
We have reviewed and approved the
technical contents of Turbomeca Alert
Mandatory Service Bulletin No. A292 72
2821, dated June 27, 2005, that
describes procedures for visual checks
of the free turbine shield for cracks. The
DGAC classified this service bulletin as
mandatory and issued AD F–2005–162,
dated September 28, 2005, in order to
ensure the airworthiness of these Arriel
2B and 2B1 engines in France.
Bilateral Airworthiness Agreement
These Turbomeca Arriel 2B and 2B1
turboshaft engines are manufactured in
France and are type certificated for
operation in the United States under the
provisions of section 21.29 of the
E:\FR\FM\13DER1.SGM
13DER1
]]>Agencies
[Federal Register Volume 70, Number 238 (Tuesday, December 13, 2005)]
[Rules and Regulations]
[Pages 73577-73579]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23829]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22560; Directorate Identifier 2005-NM-061-AD;
Amendment 39-14408; AD 2005-25-15]
RIN 2120-AA64
Airworthiness Directives; Dassault Model Falcon 2000 Airplanes
Equipped With CFE Company CFE738-1-1B 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
certain
[[Page 73578]]
Dassault Model Falcon 2000 airplanes equipped with CFE Company CFE738-
1-1B turbofan engines. This AD requires determining the serial number
of the engines installed on the airplane, inspecting any affected
engine to verify that a spherical bearing is installed on the
attachment fitting of the engine mount, and corrective action if
necessary. This AD results from a report of a missing spherical bearing
on the attachment fitting of the front engine mount on an in-service
airplane, and subsequent damage and abnormal fatigue of the attachment
fitting. We are issuing this AD to prevent reduced structural integrity
of the engine mount, which could result in possible separation of an
engine from the airplane.
DATES: This AD becomes effective January 17, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of January 17,
2006.
ADDRESSES: You may examine 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., Nassif Building,
room PL-401, Washington, DC.
Contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New
Jersey 07606, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1137; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply certain Dassault Model
Falcon 2000 airplanes equipped with CFE Company CFE738-1-1B turbofan
engines. That NPRM was published in the Federal Register on September
30, 2005 (70 FR 57217). That NPRM proposed to require determining the
serial number of the engines installed on the airplane, inspecting any
affected engine to verify that a spherical bearing is installed on the
attachment fitting of the engine mount, and corrective action if
necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We received no comments on the NPRM or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have changed this AD to clarify the appropriate procedure for
notifying the principal inspector before using any approved AMOC on any
airplane to which the AMOC applies.
Costs of Compliance
This inspection affects about 7 airplanes of U.S. registry. The
inspection will take about 2 work hours per airplane, at an average
labor rate of $65 per work hour. Based on these figures, the estimated
cost of the AD for U.S. operators is $910, or $130 per airplane.
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 regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
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 FAA 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2005-25-15 Dassault Aviation: Amendment 39-14408. Docket No. FAA-
2005-22560; Directorate Identifier 2005-NM-061-AD
Effective Date
(a) This AD becomes effective January 17, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Dassault Model Falcon 2000 airplanes,
certificated in any category; equipped with CFE Company CFE738-1-1B
turbofan engines.
Unsafe Condition
(d) This AD results from a report of a missing spherical bearing
on the attachment fitting of the front engine mount on an in-service
airplane, and subsequent damage and abnormal fatigue of the
attachment fitting.
[[Page 73579]]
We are issuing this AD to prevent reduced structural integrity of
the engine mount, which could result in possible separation of an
engine from 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.
Determine Serial Number (S/N) and Inspect if Necessary
(f) Within the applicable compliance time specified in paragraph
(f)(1), (f)(2), or (f)(3) of this AD: Determine the serial number of
the engines installed on the airplane, as identified in the table in
paragraph 1.A., ``Effectivity,'' of Dassault Service Bulletin F2000-
299, dated July 23, 2004; if any affected serial number is found on
any engine, perform a borescope inspection to verify that a
spherical bearing is installed on the attachment fitting of the
front engine mount by doing all the applicable actions specified in
the Accomplishment Instructions of the service bulletin.
(1) For airplanes with any engine having 850 total landings or
less as of the effective date of this AD: Before the accumulation of
880 total landings on the engine.
(2) For airplanes with any engine having more than 850 total
landings, but 1,000 total landings or less as of the effective date
of this AD: Within 1 month after the effective date of this AD.
(3) For airplanes with any engine having more than 1,000 total
landings as of the effective date of this AD: Within 10 landings
after the effective date of this AD.
Corrective Action
(g) If any spherical bearing is found missing during the
inspection required by paragraph (f) of this AD: Before further
flight, repair according to a method approved by either the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its
delegated agent).
No Reporting Requirement
(h) This AD does not require submitting reporting information to
the manufacturer.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(j) French airworthiness directive F-2004-128, issued August 4,
2004, also addresses the subject of this AD.
Material Incorporated by Reference
(k) You must use Dassault Service Bulletin F2000-299, dated July
23, 2004, to perform the actions that are required by this AD,
unless the AD specifies otherwise. The Director of the Federal
Register approved the incorporation by reference of this document in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Dassault
Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606, 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 December 2, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-23829 Filed 12-12-05; 8:45 am]
BILLING CODE 4910-13-P
