Airworthiness Directives; Dassault Model Falcon 10 Series Airplanes, 8241-8243 [05-2844]
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Federal Register / Vol. 70, No. 33 / Friday, February 18, 2005 / Rules and Regulations
indicated that, after selecting flaps for
landing, the flaps indication display did not
indicate the flap setting, requiring the
airplane to land in alternate flap mode. We
are issuing this AD to prevent disconnection
of autoland/autopilot functions and loss of
primary flaps control and flaps indication
display due to disengagement of all three flap
control units (FCUs) at the same time, which
could lead to a non-normal high speed
landing with the flaps retracted, increased
pilot workload, and possible runway
departure at high speeds during landing.
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.
Replace FCU
(f) At the earliest of the times specified in
paragraphs (f)(1), (f)(2), and (f)(3) of this AD:
Replace at least one FCU having P/N
285U0011–207 with a new or modified FCU
having P/N 285U0011–208 in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–27A2386,
dated March 13, 2003.
(1) Within 60 months after the effective
date of this AD.
(2) Within 25,000 flight hours after the
effective date of this AD.
(3) Within 4,000 flight cycles after the
effective date of this AD.
Note 1: Boeing Alert Service Bulletin 747–
27A2386, dated March 13, 2003, refers to
Boeing Component Service Bulletin
285U0011–27–06, dated March 13, 2003, as
an additional source of service information
for modifying an FCU having P/N 285U0011–
207 to P/N 285U0011–208.
Actions Required Before or Concurrently
With Paragraph (f)
(g) For airplanes identified in Boeing
Service Bulletin 747–27–2319, dated January
24, 1991: Before or concurrent with the
accomplishment of paragraph (f) of this AD,
replace the three FCUs having P/N
285U0011–205 or 285U0011–206 with new
or modified FCUs having P/N 285U0011–207
in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747–
27–2319, dated January 24, 1991.
Note 2: Boeing Service Bulletin 747–27–
2319, dated January 24, 1991, refers to Boeing
Component Service Bulletin 285U0011–27–
04, dated January 24, 1991, as an additional
source of service information for modifying
the FCUs having P/N 285U0011–205 or
285U0011–206 to P/N 285U0011–207.
Parts Installation
(h) As of the effective date of this AD, no
person may install on any airplane an FCU
having P/N 285U0011–205 or –206.
Alternative Methods of Compliance
(AMOCs)
(i) The Manager, Seattle Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
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Material Incorporated by Reference
(j) You must use Boeing Alert Service
Bulletin 747–27A2386, dated March 13,
2003; and Boeing Service Bulletin 747–27–
2319, dated January 24, 1991; as applicable;
to perform the actions that are required by
this AD, unless the AD specifies otherwise.
The Director of the Federal Register approves
the incorporation by reference of these
documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. For copies of the
service information, contact Boeing
Commercial Airplanes, PO Box 3707, Seattle,
Washington 98124–2207. For information on
the availability of this material at the
National Archives and Records
Administration (NARA), call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html. You may view the AD
docket at the Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street SW., room PL–401, Nassif
Building, Washington, DC.
Issued in Renton, Washington, on February
3, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–2843 Filed 2–17–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19177; Directorate
Identifier 2002–NM–202–AD; Amendment
39–13974; AD 2005–04–02]
RIN 2120–AA64
Airworthiness Directives; Dassault
Model Falcon 10 Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Dassault Model Falcon 10 series
airplanes. This AD requires a temporary
change to the airplane flight manual
(AFM) to provide procedures to the
flightcrew for touchdown using the
main landing gear to avoid a three-point
landing. This AD also requires repetitive
inspections of the piston rod of the drag
strut actuator of the nose landing gear
(NLG) for cracks, which would
terminate the AFM revision, and
corrective actions if necessary. In
addition, this AD provides for a
terminating modification, which would
end the repetitive inspections. This AD
is prompted by reports of failure of the
piston rod of the drag strut actuator of
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8241
the NLG. The cause of such failure has
been attributed to fatigue cracking
caused by corrosion in the piston rod of
the drag strut actuator. We are issuing
this AD to prevent cracking and/or
fracture of the piston rod of the drag
strut actuator of the NLG, which could
result in a gear-up landing, structural
damage, and possible injury to
passengers and crew.
DATES: This AD becomes effective
March 25, 2005.
The incorporation by reference of
certain publications listed in the AD is
approved by the Director of the Federal
Register as of March 25, 2005.
ADDRESSES: For service information
identified in this AD, contact Dassault
Falcon Jet, P.O. Box 2000, South
Hackensack, New Jersey 07606.
You can examine this information 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/
code_of_federal_regulations/
ibr_locations.html.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can examine the 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 U.S. Department of Transportation,
400 Seventh Street SW., room PL–401,
Washington, DC. This docket number is
FAA–2004–19177; the directorate
identifier for this docket is 2002–NM–
202–AD.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1137;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
an AD for all Dassault Model Falcon 10
series airplanes. That action, published
in the Federal Register on September
28, 2004 (69 FR 57886), proposed to
require a temporary change to the
airplane flight manual (AFM) to provide
procedures to the flightcrew for
touchdown using the main landing gear
to avoid a three-point landing. That
action also proposed to require
repetitive inspections of the piston rod
of the drag strut actuator of the nose
landing gear (NLG) for cracks, which
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Federal Register / Vol. 70, No. 33 / Friday, February 18, 2005 / Rules and Regulations
would terminate the AFM revision, and
corrective actions if necessary. In
addition, the proposed AD provided a
terminating modification, which would
end the repetitive inspections.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been submitted on the proposed AD.
Request To Revise Paragraph (h),
Repetitive Inspections
One commenter requests that the
proposed AD be revised to allow
operators to replace a cracked drag strut
actuator with an actuator having the
same part number. The commenter
states that this should be allowed only
once, and that the operators would still
have to perform the repetitive
inspections specified in paragraph (h)(2)
of the proposed AD. The commenter is
concerned that there may be a shortage
of new, improved drag strut actuators
since the parallel French airworthiness
directive, 2002–137(B), dated March 20,
2002, does not mandate the replacement
of a cracked drag strut actuator with a
new, improved actuator.
We agree with the commenter’s
request. We have revised paragraph
(h)(1) of this AD to specify that
operators may replace a cracked drag
strut actuator with a part having the
same part number, or do the terminating
modification specified in paragraph (i)
of this AD.
Request To Revise Paragraph (m), Part
Installation
Two commenters, the airplane
manufacturer and one of its
subsidiaries, request that paragraph (m)
of the proposed AD be revised to specify
that only drag strut actuators, part
number (P/N) 747721, that fail an
ultrasonic inspection as specified in
paragraph (h) of the proposed AD may
not be reinstalled on the airplane.
Specifically, the commenters request to
include the text ‘‘* * * which has
failed the ultrasonic inspection of the
piston rod for cracks in accordance with
Dassault Service Bulletin F10–294,
dated March 20, 2002.’’ The
commenters state that if the piston rod
passes an ultrasonic inspection it is
acceptable to the airplane manufacturer
to allow that drag strut actuator to
remain in service on the airplane. The
commenters note that, after reading
paragraph (m) of the proposed AD, a
person could conclude that it is
unacceptable to reinstall any drag strut
actuator, P/N 747721, if the actuator is
removed from the airplane for any
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Jkt 205001
reason. One of the commenters states
that the additional text is necessary to
ensure a suitable number of spare parts
are available to operators upon
publication of the AD.
We agree with the intent of the
commenters’ requests. Instead of
revising the Parts Installation paragraph
included in the proposed AD, we are
omitting that paragraph from this AD.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been submitted, 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
This AD affects about 154 airplanes of
U.S. registry.
The AFM revision takes about 1 work
hour per airplane, at an average labor
rate of $65 per work hour. Based on
these figures, the estimated cost of the
AFM revision required by this AD for
U.S. operators is $10,010, or $65 per
airplane.
The inspection takes about 1 work
hour per airplane, at an average labor
rate of $65 per work hour. Based on
these figures, the estimated cost of the
inspection required by this AD for U.S.
operators is $10,010, or $65 per
airplane, per inspection cycle.
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
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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. 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:
n
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
n
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 (AD):
n
2005–04–02 Dassault Aviation [Formerly
Avions Marcel Dassault-Breguet
Aviation (AMD/BA)]: Amendment 39–
13974. Docket No. FAA–2004–19177;
Directorate Identifier 2002–NM–202–AD.
Effective Date
(a) This AD becomes effective March 25,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Dassault Model
Falcon 10 series airplanes, certificated in any
category.
Unsafe Condition
(d) This AD was prompted by reports of
failure of the piston rod of the drag strut
actuator of the nose landing gear (NLG). We
are issuing this AD to prevent cracking and/
or fracture of the piston rod of the drag strut
E:\FR\FM\18FER1.SGM
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Federal Register / Vol. 70, No. 33 / Friday, February 18, 2005 / Rules and Regulations
actuator of the NLG, which could result in a
gear-up landing, structural damage, and
possible injury to passengers and crew.
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.
with an airworthy part having the same part
number, or do the terminating modification
specified in paragraph (i) of this AD.
(2) If no crack is found: Repeat the
inspection thereafter at intervals not to
exceed 700 landings on the drag strut
actuator.
Terminating Modification
(i) Accomplishment of the modification of
the drag strut actuator in accordance with
Dassault Service Bulletin F10–297, dated
October 1, 2003, and prior or concurrent
accomplishment of the related modification
in accordance with Messier-Hispano-Bugatti
Falcon 10 Service Bulletin 511–32–26, dated
November 9, 1979, ends the repetitive
inspections required by paragraph (h)(2) of
this AD.
Airplane Flight Manual (AFM) Revision
(f) Within 5 days after the effective date of
this AD: Revise the Limitations Section of the
Falcon 10 AFM by incorporating Dassault
Temporary Change (TC) 24, dated March 1,
2002, into the AFM. That TC provides
procedures to the flightcrew for touchdown
using the main landing gear to avoid a threepoint landing. Thereafter, operate the
airplane in accordance with the limitations
specified in the AFM revision.
(g) When the information in TC 24 has
been included in general revisions of the
AFM, the TC may be removed from the AFM,
provided the relevant information in the
general revision is identical to that in TC 24.
Additional Source of Service Information
(j) Messier-Dowty Service Bulletin 747721–
32–057, dated February 5, 2003, is referenced
in Dassault Service Bulletin F10–294 as an
additional source of service information for
replacing the drag strut actuator rod.
Repetitive Inspections
(h) Within 7 months after the effective date
of this AD: Do an ultrasonic inspection of the
piston rod of the drag strut actuator of the
NLG for cracks in accordance with Dassault
Service Bulletin F10–294, dated March 20,
2002. After the initial inspection has been
done, the TC required by paragraph (f) of this
AD may be removed from the AFM.
(1) If any crack is found: Before further
flight, replace the cracked drag strut actuator
Actions Not Required
(k) Dassault Service Bulletin F10–294
recommends returning the drag strut actuator
to the component repair agent for
replacement if a crack is found, but this AD
requires doing the terminating modification
specified in paragraph (i) of this AD.
(l) Dassault Service Bulletins F10–294 and
F10–297 recommend submitting certain
inspection results to the manufacturer. This
AD does not require those actions.
8243
Alternative Methods of Compliance
(AMOCs)
(m) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
Related Information
(n) French airworthiness directive 2002–
137(B) dated March 20, 2002, also addresses
the subject of this AD.
Material Incorporated by Reference
(o) You must use the service information
that is specified in Table 1 of this AD to
perform the actions that are required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approves the
incorporation by reference of those
documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. For copies of the
service information, contact Dassault Falcon
Jet, P.O. Box 2000, South Hackensack, New
Jersey 07606. For information on the
availability of this material at the National
Archives and Records Administration
(NARA), call (202) 741–6030, or go to
https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html. You may view the AD
docket at the Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street SW., room PL–401, Nassif
Building, Washington, DC.
TABLE 1.—MATERIAL INCORPORATED BY REFERENCE
Service information
Revision level
Dassault Service Bulletin F10–294 .........................................................
Dassault Service Bulletin F10–297 .........................................................
Dassault Temporary Change 24 to the Falcon 10 Airplane Flight Manual.
Messier-Hispano-Bugatti Falcon 10 Service Bulletin 511–32–26 ...........
Original ..........................................
Original ..........................................
Original ..........................................
Mar. 20, 2002.
Oct. 1, 2003.
Mar. 1, 2002.
Original ..........................................
Nov. 9, 1979.
Issued in Renton, Washington, on February
3, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–2844 Filed 2–17–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 97
[Docket No. 30438; Amdt. No. 3116]
Standard Instrument Approach
Procedures; Miscellaneous
Amendments
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
VerDate jul<14>2003
17:26 Feb 17, 2005
Jkt 205001
SUMMARY: This amendment establishes,
amends, suspends, or revokes Standard
Instrument Approach Procedures
(SIAPs) for operations at certain
airports. These regulatory actions are
needed because of the adoption of new
or revised criteria, or because of changes
occurring in the National Airspace
System, such as the commissioning of
new navigational facilities, addition of
new obstacles, or changes in air traffic
requirements. These changes are
designed to provide safe and efficient
use of the navigable airspace and to
promote safe flight operations under
instrument flight rules at the affected
airports.
DATES: This rule is effective February
18, 2005. The compliance date for each
SIAP is specified in the amendatory
provisions.
The incorporation by reference of
certain publications listed in the
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Date
regulations is approved by the Director
of the Federal Register as of February
18, 2005.
ADDRESSES: Availability of matters
incorporated by reference in the
amendment is as follows:
For Examination—
1. FAA Rules Docket, FAA
Headquarters Building, 800
Independence Avenue, SW.,
Washington, DC 20591;
2. The FAA Regional Office of the
region in which the affected airport is
located;
3. The Flight Inspection Area Office
which originated the SIAP; or,
4. 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/
code_of_federal_regulations/
ibr_locations.html.
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]]>Agencies
[Federal Register Volume 70, Number 33 (Friday, February 18, 2005)]
[Rules and Regulations]
[Pages 8241-8243]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-2844]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19177; Directorate Identifier 2002-NM-202-AD;
Amendment 39-13974; AD 2005-04-02]
RIN 2120-AA64
Airworthiness Directives; Dassault Model Falcon 10 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Dassault Model Falcon 10 series airplanes. This AD requires a temporary
change to the airplane flight manual (AFM) to provide procedures to the
flightcrew for touchdown using the main landing gear to avoid a three-
point landing. This AD also requires repetitive inspections of the
piston rod of the drag strut actuator of the nose landing gear (NLG)
for cracks, which would terminate the AFM revision, and corrective
actions if necessary. In addition, this AD provides for a terminating
modification, which would end the repetitive inspections. This AD is
prompted by reports of failure of the piston rod of the drag strut
actuator of the NLG. The cause of such failure has been attributed to
fatigue cracking caused by corrosion in the piston rod of the drag
strut actuator. We are issuing this AD to prevent cracking and/or
fracture of the piston rod of the drag strut actuator of the NLG, which
could result in a gear-up landing, structural damage, and possible
injury to passengers and crew.
DATES: This AD becomes effective March 25, 2005.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of March
25, 2005.
ADDRESSES: For service information identified in this AD, contact
Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606.
You can examine this information 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/code_of_federal_regulations/ibr_
locations.html.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. You can examine the 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 U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401,
Washington, DC. This docket number is FAA-2004-19177; the directorate
identifier for this docket is 2002-NM-202-AD.
FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1137; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with an AD for all Dassault Model Falcon 10 series airplanes. That
action, published in the Federal Register on September 28, 2004 (69 FR
57886), proposed to require a temporary change to the airplane flight
manual (AFM) to provide procedures to the flightcrew for touchdown
using the main landing gear to avoid a three-point landing. That action
also proposed to require repetitive inspections of the piston rod of
the drag strut actuator of the nose landing gear (NLG) for cracks,
which
[[Page 8242]]
would terminate the AFM revision, and corrective actions if necessary.
In addition, the proposed AD provided a terminating modification, which
would end the repetitive inspections.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
submitted on the proposed AD.
Request To Revise Paragraph (h), Repetitive Inspections
One commenter requests that the proposed AD be revised to allow
operators to replace a cracked drag strut actuator with an actuator
having the same part number. The commenter states that this should be
allowed only once, and that the operators would still have to perform
the repetitive inspections specified in paragraph (h)(2) of the
proposed AD. The commenter is concerned that there may be a shortage of
new, improved drag strut actuators since the parallel French
airworthiness directive, 2002-137(B), dated March 20, 2002, does not
mandate the replacement of a cracked drag strut actuator with a new,
improved actuator.
We agree with the commenter's request. We have revised paragraph
(h)(1) of this AD to specify that operators may replace a cracked drag
strut actuator with a part having the same part number, or do the
terminating modification specified in paragraph (i) of this AD.
Request To Revise Paragraph (m), Part Installation
Two commenters, the airplane manufacturer and one of its
subsidiaries, request that paragraph (m) of the proposed AD be revised
to specify that only drag strut actuators, part number (P/N) 747721,
that fail an ultrasonic inspection as specified in paragraph (h) of the
proposed AD may not be reinstalled on the airplane. Specifically, the
commenters request to include the text ``* * * which has failed the
ultrasonic inspection of the piston rod for cracks in accordance with
Dassault Service Bulletin F10-294, dated March 20, 2002.'' The
commenters state that if the piston rod passes an ultrasonic inspection
it is acceptable to the airplane manufacturer to allow that drag strut
actuator to remain in service on the airplane. The commenters note
that, after reading paragraph (m) of the proposed AD, a person could
conclude that it is unacceptable to reinstall any drag strut actuator,
P/N 747721, if the actuator is removed from the airplane for any
reason. One of the commenters states that the additional text is
necessary to ensure a suitable number of spare parts are available to
operators upon publication of the AD.
We agree with the intent of the commenters' requests. Instead of
revising the Parts Installation paragraph included in the proposed AD,
we are omitting that paragraph from this AD.
Conclusion
We have carefully reviewed the available data, including the
comments that have been submitted, 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
This AD affects about 154 airplanes of U.S. registry.
The AFM revision takes about 1 work hour per airplane, at an
average labor rate of $65 per work hour. Based on these figures, the
estimated cost of the AFM revision required by this AD for U.S.
operators is $10,010, or $65 per airplane.
The inspection takes about 1 work hour per airplane, at an average
labor rate of $65 per work hour. Based on these figures, the estimated
cost of the inspection required by this AD for U.S. operators is
$10,010, or $65 per airplane, per inspection cycle.
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. 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 FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2005-04-02 Dassault Aviation [Formerly Avions Marcel Dassault-
Breguet Aviation (AMD/BA)]: Amendment 39-13974. Docket No. FAA-2004-
19177; Directorate Identifier 2002-NM-202-AD.
Effective Date
(a) This AD becomes effective March 25, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Dassault Model Falcon 10 series
airplanes, certificated in any category.
Unsafe Condition
(d) This AD was prompted by reports of failure of the piston rod
of the drag strut actuator of the nose landing gear (NLG). We are
issuing this AD to prevent cracking and/or fracture of the piston
rod of the drag strut
[[Page 8243]]
actuator of the NLG, which could result in a gear-up landing,
structural damage, and possible injury to passengers and crew.
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.
Airplane Flight Manual (AFM) Revision
(f) Within 5 days after the effective date of this AD: Revise
the Limitations Section of the Falcon 10 AFM by incorporating
Dassault Temporary Change (TC) 24, dated March 1, 2002, into the
AFM. That TC provides procedures to the flightcrew for touchdown
using the main landing gear to avoid a three-point landing.
Thereafter, operate the airplane in accordance with the limitations
specified in the AFM revision.
(g) When the information in TC 24 has been included in general
revisions of the AFM, the TC may be removed from the AFM, provided
the relevant information in the general revision is identical to
that in TC 24.
Repetitive Inspections
(h) Within 7 months after the effective date of this AD: Do an
ultrasonic inspection of the piston rod of the drag strut actuator
of the NLG for cracks in accordance with Dassault Service Bulletin
F10-294, dated March 20, 2002. After the initial inspection has been
done, the TC required by paragraph (f) of this AD may be removed
from the AFM.
(1) If any crack is found: Before further flight, replace the
cracked drag strut actuator with an airworthy part having the same
part number, or do the terminating modification specified in
paragraph (i) of this AD.
(2) If no crack is found: Repeat the inspection thereafter at
intervals not to exceed 700 landings on the drag strut actuator.
Terminating Modification
(i) Accomplishment of the modification of the drag strut
actuator in accordance with Dassault Service Bulletin F10-297, dated
October 1, 2003, and prior or concurrent accomplishment of the
related modification in accordance with Messier-Hispano-Bugatti
Falcon 10 Service Bulletin 511-32-26, dated November 9, 1979, ends
the repetitive inspections required by paragraph (h)(2) of this AD.
Additional Source of Service Information
(j) Messier-Dowty Service Bulletin 747721-32-057, dated February
5, 2003, is referenced in Dassault Service Bulletin F10-294 as an
additional source of service information for replacing the drag
strut actuator rod.
Actions Not Required
(k) Dassault Service Bulletin F10-294 recommends returning the
drag strut actuator to the component repair agent for replacement if
a crack is found, but this AD requires doing the terminating
modification specified in paragraph (i) of this AD.
(l) Dassault Service Bulletins F10-294 and F10-297 recommend
submitting certain inspection results to the manufacturer. This AD
does not require those actions.
Alternative Methods of Compliance (AMOCs)
(m) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
Related Information
(n) French airworthiness directive 2002-137(B) dated March 20,
2002, also addresses the subject of this AD.
Material Incorporated by Reference
(o) You must use the service information that is specified in
Table 1 of this AD to perform the actions that are required by this
AD, unless the AD specifies otherwise. The Director of the Federal
Register approves the incorporation by reference of those documents
in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of
the service information, contact Dassault Falcon Jet, P.O. Box 2000,
South Hackensack, New Jersey 07606. For information on the
availability of this material at the National Archives and Records
Administration (NARA), call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html. You may view the AD docket at the Docket
Management Facility, U.S. Department of Transportation, 400 Seventh
Street SW., room PL-401, Nassif Building, Washington, DC.
Table 1.--Material Incorporated by Reference
------------------------------------------------------------------------
Service information Revision level Date
------------------------------------------------------------------------
Dassault Service Bulletin F10- Original.......... Mar. 20, 2002.
294.
Dassault Service Bulletin F10- Original.......... Oct. 1, 2003.
297.
Dassault Temporary Change 24 to Original.......... Mar. 1, 2002.
the Falcon 10 Airplane Flight
Manual.
Messier-Hispano-Bugatti Falcon Original.......... Nov. 9, 1979.
10 Service Bulletin 511-32-26.
------------------------------------------------------------------------
Issued in Renton, Washington, on February 3, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-2844 Filed 2-17-05; 8:45 am]
BILLING CODE 4910-13-P
