Airworthiness Directives; Dassault-Aviation Model FALCON 2000 and FALCON 2000EX Airplanes, 28465-28469 [2010-11358]
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Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations
Note 2: Guidance on revising Chapter 5 of
the BAE SYSTEMS (Operations) Limited
BAe146 Series/Avro146–RJ Series AMM,
Revision 97, dated July 15, 2009, can be
found in the applicable sub-chapters listed in
Table 1 of this AD.
TABLE 1—APPLICABLE AMM SUBCHAPTERS
AMM Subchapter
Subject
05–10–01 .......
Airframe Airworthiness Limitations before Life Extension Programme.
Airframe Airworthiness Limitations, Life Extension
Programme Landings Life
Extended.
Airframe Airworthiness Limitations, Life Extension
Programme Calendar Life
Extended.
Aircraft Equipment Airworthiness Limitations.
Power Plant Airworthiness
Limitations.
Critical Design Configuration
Control Limitations
(CDCCL)—Fuel System
Description and Operation.
Scheduled Maintenance.
Airframe Scheduled Maintenance—Before Life Extension Programme.
Airframe Scheduled Maintenance—Life Extension
Programme Landings Life
Extended.
Airframe Scheduled Maintenance—Life Extension
Programme Calendar Life
Extended.
Aircraft Equipment Scheduled Maintenance.
05–10–05 1 .....
05–10–10 2 .....
05–10–15 .......
05–10–17 .......
05–15–00 .......
05–20–00 3 .....
05–20–01 .......
05–20–05 1 .....
05–20–10 2 .....
05–20–15 .......
1 Applicable only to airplanes post-modification
HCM20011A
or
HCM20012A
or
HCM20013A.
2 Applicable only to airplanes post-modification HCM20010A.
3 Paragraphs 5 and 6 only, on the Corrosion
Prevention and Control Program (CPCP) and
the Supplemental Structural Inspection Document (SSID).
cprice-sewell on DSK8KYBLC1PROD with RULES
Note 3: Sub-chapter 05–15–00 of the BAE
SYSTEMS (Operations) Limited BAe146
Series/Avro146–RJ Series AMM, is the
CDCCL.
Note 4: Within Sub-chapter 05–20–00 of
the BAE SYSTEMS (Operations) Limited
BAe146 Series/Avro146–RJ Series AMM, the
relevant issues of the support documents are
as follows: BAE SYSTEMS (Operations)
Limited BAe 146 Series/Avro 146–RJ
Corrosion Prevention and Control Program
Document CPCP–146–01, Revision 3, dated
July 15, 2008, including BAE SYSTEMS
(Operations) Limited Temporary Revision
(TR) 2.1, dated December 2008; and BAE
SYSTEMS (Operations) Limited BAe146
Series Supplemental Structural Inspection
Document SSID–146–01, Revision 1, dated
June 15, 2009.
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12:54 May 20, 2010
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Note 5: Within Sub-chapter 05–20–01 of
the BAE SYSTEMS (Operations) Limited
BAe146 Series/Avro146–RJ Series AMM, the
relevant issue of BAE SYSTEMS (Operations)
Limited BAe 146/Avro 146–RJ Maintenance
Review Board Report Document MRB 146–
01, Issue 2, is Revision 15, dated March 2009
(mis-identified in EASA AD 2009–0215,
dated October 7, 2009, as being dated May
2009).
Note 6: Notwithstanding any other
maintenance or operational requirements,
components that have been identified as
airworthy or installed on the affected
airplanes before the revision of the ALS, as
required by paragraph (g) of this AD; or
before revision of Chapter 5 of the AMM, as
required by paragraph (h) of this AD; do not
need to be reworked in accordance with the
CDCCLs. However, once the ALS or AMM
has been revised, future maintenance actions
on these components must be done in
accordance with the CDCCLs.
(i) Except as specified in paragraph (k) of
this AD: After the actions specified in
paragraph (g) or (h) of this AD have been
accomplished, no alternative inspections or
inspection intervals may be approved for the
structural elements specified in the
documents listed in paragraph (g) or (h) of
this AD.
(j) Modifying the main fittings of the main
landing gear in accordance with MessierDowty Service Bulletin 146–32–171, dated
August 11, 2009, extends the safe limit of the
main landing gear main fitting from 32,000
landings to 50,000 landings on the main
fitting.
Alternative Methods of Compliance
(AMOCs)
(k) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Todd Thompson, Aerospace
Engineer, International Branch, ANM–116,
FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–4056; telephone (425) 227–1175; fax
(425) 227–1149. Before using any approved
AMOC on any airplane to which the AMOC
applies, notify your principal maintenance
inspector (PMI) or principal avionics
inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight
Standards District Office. The AMOC
approval letter must specifically reference
this AD.
Related Information
(l) EASA Airworthiness Directive 2009–
0215, dated October 7, 2009; and MessierDowty Service Bulletin 146–32–171, dated
August 11, 2009; also address the subject of
this AD.
Material Incorporated by Reference
(m) If you do the optional modification
specified in this AD, you must use MessierDowty Service Bulletin 146–32–171, dated
August 11, 2009, to do those actions, unless
the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
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28465
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For Messier-Dowty service information
identified in this AD, contact Messier-Dowty
Limited, Cheltenham Road, Gloucester GL2
9QH, England; telephone +44(0)1452 712424;
fax +44(0)1452 713821; Internet https://
techpubs.services.messier-dowty.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(4) You may also review copies of the
service information that is incorporated by
reference 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.
Issued in Renton, Washington, on May 3,
2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–11356 Filed 5–20–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0791; Directorate
Identifier 2008–NM–213–AD; Amendment
39–16303; AD 2010–10–24]
RIN 2120–AA64
Airworthiness Directives; DassaultAviation Model FALCON 2000 and
FALCON 2000EX Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
During the overhaul of a Main Landing
Gear (MLG) of a Falcon 2000, the sleeve on
the hydraulic flow restrictor in the shock
absorber was found displaced, because of the
rupture of its three retaining screws. * * *
Failure of the retaining screws has been
determined to be the final phase of a slow
unscrewing process under normal
operational conditions. The unsafe condition
only exists once the three screws have failed.
*
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Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations
The unsafe condition is failure of three
retaining screws of the MLG shock
absorber, which could adversely affect
the structural integrity of these
airplanes. We are issuing this AD to
require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective June
25, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 25, 2010.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1137; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
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We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on September 24, 2009 (74 FR
48668). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
During the overhaul of a Main Landing
Gear (MLG) of a Falcon 2000, the sleeve on
the hydraulic flow restrictor in the shock
absorber was found displaced, because of the
rupture of its three retaining screws. In this
situation, the energy dissipation function of
the shock absorber is lost and high loads may
be transmitted to the aircraft structure during
landing. Structural integrity may thus not be
guaranteed over the entire certified landing
conditions domain particularly in
combination of high landing weight and high
vertical speed.
Failure of the retaining screws has been
determined to be the final phase of a slow
unscrewing process under normal
operational conditions. The unsafe condition
only exists once the three screws have failed.
For the reasons described above,
Airworthiness Directive (AD) 2008–0178 had
been released to require a repetitive
borescope inspection of the flow restriction
system [for damage; such as condition of the
sleeve of the dumping device, and broken or
loose screws] and, if necessary, repair of the
shock absorber per Dassault Aviation Service
Bulletins (SB) F2000–367 and F2000EX–185
(corresponding to modification M3120)
developed with the landing gear
manufacturer’s instructions. * * *
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After qualification testing, modification
M3120 has been approved by EASA as a
definitive solution.
As a consequence, the present AD retains
the requirements of AD 2008–0178 which is
superseded and introduces M3120 as a
terminating action to the repetitive
inspections requirement, and further
mandates its embodiment no later than the
next MLG shock absorber overhaul.
The unsafe condition is failure of three
retaining screws of the MLG shock
absorber, which could adversely affect
the structural integrity of these
airplanes. The repair can include
additional inspections, modifying the
shock absorbers, and contacting the
manufacturer for repair instructions and
doing the repair. You may obtain further
information by examining the MCAI in
the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received.
Request To Extend Compliance Time
Dassault-Aviation (Dassault) asks that
we extend the compliance time for
repairing the shock absorber if any
damage is found from before further
flight to the compliance times specified
in European Aviation Safety Agency
(EASA) AD 2009–0050, dated March 5,
2009. Dassault states that requiring
immediate repair of the shock absorber
before further flight is unnecessary
because it has been established that a
two-tier approach of prompt inspection
followed by repair, if necessary, is a
more efficient means of addressing the
unsafe condition. Dassault adds that this
requirement would cause scheduling
issues at maintenance facilities with
trained personnel available to perform
the repair, and would result in
unnecessary grounding of its airplanes.
We agree with the commenter. The
compliance times referred to in EASA
AD 2009–0050, and specified in
Dassault Mandatory Service Bulletins
F2000–366, Revision 2; and F2000EX–
167, Revision 1; both dated December 1,
2008; are based on technical
information and calculations
coordinated between EASA and
Dassault. The compliance times for the
repairs are based on inspection results
showing the number of loose or broken
screws that attach the sleeve of the
damping device to the shock absorber.
If one, two, or three screws are loose
with a visible gap, the screws must be
repaired within 12 months after the
damage is found. If one screw is broken
the screw must be repaired within 6
months after the damage is found. If two
screws are broken, the screws must be
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repaired within 10 flight cycles after the
damage is found. And, if three screws
are broken and the damping device is no
longer attached, the repair must be done
before further flight. Extending the
compliance times for the repairs based
on the number of loose or broken screws
would not adversely affect airplane
safety. Therefore, we have changed the
requirements specified in paragraphs
(f)(1), (f)(2), and (f)(3) of this AD and
added a new Table 1 to allow the repair
to be done at the applicable compliance
times specified in the Accomplishment
Instructions of the applicable service
bulletin. We have reidentified
subsequent tables accordingly. In
addition, we have removed the
compliance time difference specified in
paragraph (1) under Note 1 of the
NPRM.
Request To Change the Description of
the Unsafe Condition
Dassault also asks that we revise the
NPRM to remove the language
describing the unsafe condition as
failure of three retaining screws of the
MLG shock absorber, which could result
in collapse of the landing gear during
ground maneuvers or landing. Dassault
states that, based on engineering
studies, it believes that the failure or
absence of these screws will not result
in collapse of the landing gear during
ground maneuvers or landing. Dassault
adds that, as specified in the EASA AD,
the failure of these screws would only
potentially affect the life of the airplane
structure under all landing conditions,
particularly with respect to the
combination of high landing weights
and high vertical speeds at touchdown.
Dassault notes that the current language
in the NPRM has caused needless alarm
and concern among Model Falcon 2000
and Falcon 2000EX owners and
operators.
We agree with the commenter for the
reasons provided. Based on those
reasons, we have changed the
description of the unsafe condition
throughout this AD as follows: ‘‘The
unsafe condition is failure of three
retaining screws of the MLG shock
absorber, which could adversely affect
the structural integrity of these
airplanes.’’
Explanation of Change Made to This
AD
We have changed this AD to identify
the legal name of the manufacturer as
published in the most recent type
certificate data sheet for the affected
airplane models.
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Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations
Conclusion
We 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 determined that these changes will
not increase the economic burden on
any operator or increase the scope of the
AD.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
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Explanation of Change to Costs of
Compliance
After the NPRM was issued, we
reviewed the figures we have used over
the past several years to calculate AD
costs to operators. To account for
various inflationary costs in the airline
industry, we find it necessary to
increase the labor rate used in these
calculations from $80 per work hour to
$85 per work hour. The cost impact
information, below, reflects this
increase in the specified hourly labor
rate.
Costs of Compliance
We estimate that this AD will affect
236 products of U.S. registry. We also
estimate that it will take about 25 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $85 per work-hour.
Required parts will cost about $0 per
product. Where the service information
lists required parts costs that are
covered under warranty, we have
assumed that there will be no charge for
these parts. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. Based on these
figures, we estimate the cost of this AD
to the U.S. operators to be $501,500, or
$2,125 per product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
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12:54 May 20, 2010
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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 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 this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains the NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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28467
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2010–10–24 Dassault-Aviation:
Amendment 39–16303. Docket No.
FAA–2009–0791; Directorate Identifier
2008–NM–213–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective June 25, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Dassault-Aviation
Model FALCON 2000 and FALCON 2000EX
airplanes, certificated in any category.
Subject
(d) Air Transport Association (ATA) of
America Code 32: Landing gear.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
During the overhaul of a Main Landing
Gear (MLG) of a Falcon 2000, the sleeve on
the hydraulic flow restrictor in the shock
absorber was found displaced, because of the
rupture of its three retaining screws. In this
situation, the energy dissipation function of
the shock absorber is lost and high loads may
be transmitted to the aircraft structure during
landing. Structural integrity may thus not be
guaranteed over the entire certified landing
conditions domain particularly in
combination of high landing weight and high
vertical speed.
Failure of the retaining screws has been
determined to be the final phase of a slow
unscrewing process under normal
operational conditions. The unsafe condition
only exists once the three screws have failed.
For the reasons described above,
Airworthiness Directive (AD) 2008–0178 had
been released to require a repetitive
borescope inspection of the flow restriction
system [for damage; such as condition of the
sleeve of the dumping device, and broken or
loose screws] and, if necessary, repair of the
shock absorber per Dassault Aviation Service
Bulletins (SB) F2000–367 and F2000EX–185
(corresponding to modification M3120)
developed with the landing gear
manufacturer’s instructions. * * *
After qualification testing, modification
M3120 has been approved by the European
Aviation Safety Agency (EASA), as a
definitive solution.
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21MYR1
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Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations
As a consequence, the present AD retains
the requirements of AD 2008–0178 which is
superseded and introduces M3120 as a
terminating action to the repetitive
inspections requirement, and further
mandates its embodiment no later than the
next MLG shock absorber overhaul.
The unsafe condition is failure of three
retaining screws of the MLG shock absorber,
which could adversely affect the structural
integrity of these airplanes. The repair can
include additional inspections, modifying
the shock absorbers, and contacting the
manufacturer for repair instructions and
doing the repair.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) For airplanes on which each new or
previously overhauled MLG shock absorber
has accumulated 4,200 or more total landings
since new or overhauled as of the effective
date of this AD: Within 8 months after the
effective date of this AD, inspect the shock
absorber for damage, in accordance with the
Accomplishment Instructions of Dassault
Mandatory Service Bulletin F2000–366,
Revision 2; or F2000EX–167, Revision 1; both
dated December 1, 2008; as applicable. If any
damage is found, repair the shock absorber at
the time specified in Table 1 of this AD, in
accordance with the Accomplishment
Instructions of Dassault Mandatory Service
Bulletin F2000–366, Revision 2; or F2000EX–
167, Revision 1; both dated December 1,
2008; as applicable.
(2) For airplanes on which each new or
previously overhauled MLG shock absorber
has accumulated 1,900 or more total landings
and less than 4,200 total landings since new
or overhauled as of the effective date of this
AD: At the applicable compliance time
specified in paragraph (f)(2)(i) or (f)(2)(ii) of
this AD, inspect the shock absorber for
damage, in accordance with the
Accomplishment Instructions of Dassault
Mandatory Service Bulletin F2000–366,
Revision 2; or F2000EX–167, Revision 1; both
dated December 1, 2008; as applicable. If any
damage is found, repair the shock absorber at
the applicable time specified in Table 1 of
this AD, in accordance with the
Accomplishment Instructions of Dassault
Mandatory Service Bulletin F2000–366,
Revision 2; or F2000EX–167, Revision 1; both
dated December 1, 2008; as applicable.
(i) For airplanes on which 6 or more steepapproach landings have been performed
before the effective date of this AD: Within
8 months after the effective date of this AD,
do the actions required by paragraph (f)(2) of
this AD.
(ii) For airplanes on which less than or
equal to 5 steep-approach landings have been
performed before the effective date of this
AD: Within 18 months after the effective date
of this AD or 5,000 total landings since new
or overhauled, whichever occurs first, do the
actions required by paragraph (f)(2) of this
AD.
(3) For airplanes on which each new or
previously overhauled MLG shock absorber
has accumulated less than 1,900 total
landings since new or overhauled as of the
effective date of this AD: Before the
accumulation of 3,000 total landings since
new or overhauled, inspect the shock
absorber for damage, in accordance with the
Accomplishment Instructions of Dassault
Mandatory Service Bulletin F2000–366,
Revision 2; or F2000EX–167, Revision 1; both
dated December 1, 2008; as applicable. If any
damage is found, repair the shock absorber at
the time specified in Table 1 of this AD, in
accordance with the Accomplishment
Instructions of Dassault Mandatory Service
Bulletin F2000–366, Revision 2; or F2000EX–
167, Revision 1; both dated December 1,
2008; as applicable.
TABLE 1—COMPLIANCE TIMES FOR REPAIR
Damage found
Compliance time
1, 2, or 3 loose screws ...............................................................................................................
1 broken screw ...........................................................................................................................
2 or 3 broken screws ..................................................................................................................
3 broken screws with detached damping device .......................................................................
(4) Repeat the inspections required by
paragraphs (f)(1), (f)(2), and (f)(3) of this AD,
as applicable, thereafter at intervals not to
exceed 1,900 landings until accomplishment
Within 12 months after the finding.
Within 6 months after the finding.
Within 10 flight cycles after the finding.
Before further flight.
of the actions specified in paragraph (f)(6) of
this AD.
(5) Accomplishment of any inspection or
repair before the effective date of this AD in
accordance the applicable service
information specified in Table 2 of this AD
is acceptable for compliance with the
corresponding requirements of this AD.
TABLE 2—CREDIT SERVICE INFORMATION
Revision
Dassault Mandatory Service Bulletin F2000–366 ....................................................................................
Dassault Mandatory Service Bulletin F2000EX–167 ...............................................................................
Dassault Service Bulletin F2000–366 ......................................................................................................
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(6) For airplanes on which Dassault
Modification M3120 has not been embodied
as of the effective date of this AD: Before the
accumulation of 6,000 total landings or 144
months on each new or previously
overhauled MLG shock absorber, whichever
occurs first: Modify the existing left- and
right-hand MLG shock absorbers by installing
MLG shock absorbers with part number (P/
N) D23365000–4 or P/N D23366000–4 (for
Model Falcon 2000 airplanes), or P/N
D23745000–2 or P/N D23746000–2 (for
Model Falcon 2000EX airplanes), in
accordance with the Accomplishment
Instructions of Dassault Service Bulletin
F2000EX–185, Revision 2; or F2000–367,
Revision 4; both dated February 4, 2009; as
applicable. Where these service bulletins
specify contacting the manufacturer for
repair instructions, contact the manufacturer
and do the repair at the applicable
compliance times specified in the
Date
August 18, 2008.
August 18, 2008.
April 18, 2008.
Accomplishment Instructions of the
applicable service bulletin.
(7) Accomplishment of the modification
required by paragraph (f)(6) of this AD before
the effective date of this AD in accordance
with the applicable service information
specified in Table 3 of this AD is acceptable
for compliance with the corresponding
requirements of this AD.
TABLE 3—CREDIT SERVICE INFORMATION FOR MODIFICATION
Document
Revision
Date
Dassault Service Bulletin F2000EX–185 ..................................................................................................
Dassault Service Bulletin F2000EX–185 ..................................................................................................
Dassault Service Bulletin F2000–367 ......................................................................................................
Original ..................
1 ............................
1 ............................
August 18, 2008.
December 1, 2008.
July 10, 2008.
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Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations
TABLE 3—CREDIT SERVICE INFORMATION FOR MODIFICATION—Continued
Document
Revision
Date
Dassault Service Bulletin F2000–367 ......................................................................................................
Dassault Service Bulletin F2000–367 ......................................................................................................
2 ............................
3 ............................
August 18, 2008.
December 1, 2008.
(8) Accomplishment of the modification
required by paragraph (f)(6) of this AD ends
the repetitive inspections required by
paragraph (f)(4) of this AD.
(9) As of the effective date of this AD, no
person may install on any airplane as a
replacement part, a MLG shock absorber,
unless it has been modified according to the
requirements specified in paragraph (f)(6) of
this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows:
Paragraph (1) of the MCAI requires updating
the operator’s maintenance program;
however, that action is not required by this
AD. The maintenance program does not
require FAA approval.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to Attn: Tom Rodriguez,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone (425)
227–1137; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI EASA Airworthiness
Directive 2009–0050, dated March 5, 2009,
and the service information identified in
Table 4 of this AD, for related information.
TABLE 4—SERVICE INFORMATION
Document
Dassault
Dassault
Dassault
Dassault
Revision
Mandatory Service Bulletin F2000–366 ............................................................................................
Mandatory Service Bulletin F2000EX–167 .......................................................................................
Service Bulletin F2000–367 ..............................................................................................................
Service Bulletin F2000EX–185 .........................................................................................................
Material Incorporated by Reference
(i) You must use the applicable service
information contained in Table 5 of this AD
Date
2
1
4
2
December 1, 2008.
December 1, 2008.
February 4, 2009.
February 4, 2009.
to do the actions required by this AD, unless
the AD specifies otherwise.
TABLE 5—MATERIAL INCORPORATED BY REFERENCE
Document
cprice-sewell on DSK8KYBLC1PROD with RULES
Dassault
Dassault
Dassault
Dassault
Revision
Mandatory Service Bulletin F2000–366 ............................................................................................
Mandatory Service Bulletin F2000EX–167 .......................................................................................
Service Bulletin F2000–367 ..............................................................................................................
Service Bulletin F2000EX–185 .........................................................................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Dassault Falcon Jet, P.O. Box
2000, South Hackensack, New Jersey 07606;
telephone 201–440–6700; Internet https://
www.dassaultfalcon.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
VerDate Mar<15>2010
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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.
Issued in Renton, Washington, on May 4,
2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–11358 Filed 5–20–10; 8:45 am]
BILLING CODE 4910–13–P
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2
1
4
2
December 1, 2008.
December 1, 2008.
February 4, 2009.
February 4, 2009.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0491; Directorate
Identifier 2009–SW–64–AD; Amendment 39–
16293; AD 2010–10–14]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Model AS332L2 Helicopters
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
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[Federal Register Volume 75, Number 98 (Friday, May 21, 2010)]
[Rules and Regulations]
[Pages 28465-28469]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-11358]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0791; Directorate Identifier 2008-NM-213-AD;
Amendment 39-16303; AD 2010-10-24]
RIN 2120-AA64
Airworthiness Directives; Dassault-Aviation Model FALCON 2000 and
FALCON 2000EX Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
During the overhaul of a Main Landing Gear (MLG) of a Falcon
2000, the sleeve on the hydraulic flow restrictor in the shock
absorber was found displaced, because of the rupture of its three
retaining screws. * * *
Failure of the retaining screws has been determined to be the
final phase of a slow unscrewing process under normal operational
conditions. The unsafe condition only exists once the three screws
have failed.
* * * * *
[[Page 28466]]
The unsafe condition is failure of three retaining screws of the MLG
shock absorber, which could adversely affect the structural integrity
of these airplanes. We are issuing this AD to require actions to
correct the unsafe condition on these products.
DATES: This AD becomes effective June 25, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 25,
2010.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1137; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on September 24, 2009
(74 FR 48668). That NPRM proposed to correct an unsafe condition for
the specified products. The MCAI states:
During the overhaul of a Main Landing Gear (MLG) of a Falcon
2000, the sleeve on the hydraulic flow restrictor in the shock
absorber was found displaced, because of the rupture of its three
retaining screws. In this situation, the energy dissipation function
of the shock absorber is lost and high loads may be transmitted to
the aircraft structure during landing. Structural integrity may thus
not be guaranteed over the entire certified landing conditions
domain particularly in combination of high landing weight and high
vertical speed.
Failure of the retaining screws has been determined to be the
final phase of a slow unscrewing process under normal operational
conditions. The unsafe condition only exists once the three screws
have failed.
For the reasons described above, Airworthiness Directive (AD)
2008-0178 had been released to require a repetitive borescope
inspection of the flow restriction system [for damage; such as
condition of the sleeve of the dumping device, and broken or loose
screws] and, if necessary, repair of the shock absorber per Dassault
Aviation Service Bulletins (SB) F2000-367 and F2000EX-185
(corresponding to modification M3120) developed with the landing
gear manufacturer's instructions. * * *
After qualification testing, modification M3120 has been
approved by EASA as a definitive solution.
As a consequence, the present AD retains the requirements of AD
2008-0178 which is superseded and introduces M3120 as a terminating
action to the repetitive inspections requirement, and further
mandates its embodiment no later than the next MLG shock absorber
overhaul.
The unsafe condition is failure of three retaining screws of the MLG
shock absorber, which could adversely affect the structural integrity
of these airplanes. The repair can include additional inspections,
modifying the shock absorbers, and contacting the manufacturer for
repair instructions and doing the repair. You may obtain further
information by examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received.
Request To Extend Compliance Time
Dassault-Aviation (Dassault) asks that we extend the compliance
time for repairing the shock absorber if any damage is found from
before further flight to the compliance times specified in European
Aviation Safety Agency (EASA) AD 2009-0050, dated March 5, 2009.
Dassault states that requiring immediate repair of the shock absorber
before further flight is unnecessary because it has been established
that a two-tier approach of prompt inspection followed by repair, if
necessary, is a more efficient means of addressing the unsafe
condition. Dassault adds that this requirement would cause scheduling
issues at maintenance facilities with trained personnel available to
perform the repair, and would result in unnecessary grounding of its
airplanes.
We agree with the commenter. The compliance times referred to in
EASA AD 2009-0050, and specified in Dassault Mandatory Service
Bulletins F2000-366, Revision 2; and F2000EX-167, Revision 1; both
dated December 1, 2008; are based on technical information and
calculations coordinated between EASA and Dassault. The compliance
times for the repairs are based on inspection results showing the
number of loose or broken screws that attach the sleeve of the damping
device to the shock absorber. If one, two, or three screws are loose
with a visible gap, the screws must be repaired within 12 months after
the damage is found. If one screw is broken the screw must be repaired
within 6 months after the damage is found. If two screws are broken,
the screws must be repaired within 10 flight cycles after the damage is
found. And, if three screws are broken and the damping device is no
longer attached, the repair must be done before further flight.
Extending the compliance times for the repairs based on the number of
loose or broken screws would not adversely affect airplane safety.
Therefore, we have changed the requirements specified in paragraphs
(f)(1), (f)(2), and (f)(3) of this AD and added a new Table 1 to allow
the repair to be done at the applicable compliance times specified in
the Accomplishment Instructions of the applicable service bulletin. We
have reidentified subsequent tables accordingly. In addition, we have
removed the compliance time difference specified in paragraph (1) under
Note 1 of the NPRM.
Request To Change the Description of the Unsafe Condition
Dassault also asks that we revise the NPRM to remove the language
describing the unsafe condition as failure of three retaining screws of
the MLG shock absorber, which could result in collapse of the landing
gear during ground maneuvers or landing. Dassault states that, based on
engineering studies, it believes that the failure or absence of these
screws will not result in collapse of the landing gear during ground
maneuvers or landing. Dassault adds that, as specified in the EASA AD,
the failure of these screws would only potentially affect the life of
the airplane structure under all landing conditions, particularly with
respect to the combination of high landing weights and high vertical
speeds at touchdown. Dassault notes that the current language in the
NPRM has caused needless alarm and concern among Model Falcon 2000 and
Falcon 2000EX owners and operators.
We agree with the commenter for the reasons provided. Based on
those reasons, we have changed the description of the unsafe condition
throughout this AD as follows: ``The unsafe condition is failure of
three retaining screws of the MLG shock absorber, which could adversely
affect the structural integrity of these airplanes.''
Explanation of Change Made to This AD
We have changed this AD to identify the legal name of the
manufacturer as published in the most recent type certificate data
sheet for the affected airplane models.
[[Page 28467]]
Conclusion
We 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 determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Explanation of Change to Costs of Compliance
After the NPRM was issued, we reviewed the figures we have used
over the past several years to calculate AD costs to operators. To
account for various inflationary costs in the airline industry, we find
it necessary to increase the labor rate used in these calculations from
$80 per work hour to $85 per work hour. The cost impact information,
below, reflects this increase in the specified hourly labor rate.
Costs of Compliance
We estimate that this AD will affect 236 products of U.S. registry.
We also estimate that it will take about 25 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts will cost about $0 per product.
Where the service information lists required parts costs that are
covered under warranty, we have assumed that there will be no charge
for these parts. As we do not control warranty coverage for affected
parties, some parties may incur costs higher than estimated here. Based
on these figures, we estimate the cost of this AD to the U.S. operators
to be $501,500, or $2,125 per product.
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 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 this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
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 AD:
2010-10-24 Dassault-Aviation: Amendment 39-16303. Docket No. FAA-
2009-0791; Directorate Identifier 2008-NM-213-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective June 25,
2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Dassault-Aviation Model FALCON 2000
and FALCON 2000EX airplanes, certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 32: Landing
gear.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
During the overhaul of a Main Landing Gear (MLG) of a Falcon
2000, the sleeve on the hydraulic flow restrictor in the shock
absorber was found displaced, because of the rupture of its three
retaining screws. In this situation, the energy dissipation function
of the shock absorber is lost and high loads may be transmitted to
the aircraft structure during landing. Structural integrity may thus
not be guaranteed over the entire certified landing conditions
domain particularly in combination of high landing weight and high
vertical speed.
Failure of the retaining screws has been determined to be the
final phase of a slow unscrewing process under normal operational
conditions. The unsafe condition only exists once the three screws
have failed.
For the reasons described above, Airworthiness Directive (AD)
2008-0178 had been released to require a repetitive borescope
inspection of the flow restriction system [for damage; such as
condition of the sleeve of the dumping device, and broken or loose
screws] and, if necessary, repair of the shock absorber per Dassault
Aviation Service Bulletins (SB) F2000-367 and F2000EX-185
(corresponding to modification M3120) developed with the landing
gear manufacturer's instructions. * * *
After qualification testing, modification M3120 has been
approved by the European Aviation Safety Agency (EASA), as a
definitive solution.
[[Page 28468]]
As a consequence, the present AD retains the requirements of AD
2008-0178 which is superseded and introduces M3120 as a terminating
action to the repetitive inspections requirement, and further
mandates its embodiment no later than the next MLG shock absorber
overhaul.
The unsafe condition is failure of three retaining screws of the MLG
shock absorber, which could adversely affect the structural
integrity of these airplanes. The repair can include additional
inspections, modifying the shock absorbers, and contacting the
manufacturer for repair instructions and doing the repair.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) For airplanes on which each new or previously overhauled MLG
shock absorber has accumulated 4,200 or more total landings since
new or overhauled as of the effective date of this AD: Within 8
months after the effective date of this AD, inspect the shock
absorber for damage, in accordance with the Accomplishment
Instructions of Dassault Mandatory Service Bulletin F2000-366,
Revision 2; or F2000EX-167, Revision 1; both dated December 1, 2008;
as applicable. If any damage is found, repair the shock absorber at
the time specified in Table 1 of this AD, in accordance with the
Accomplishment Instructions of Dassault Mandatory Service Bulletin
F2000-366, Revision 2; or F2000EX-167, Revision 1; both dated
December 1, 2008; as applicable.
(2) For airplanes on which each new or previously overhauled MLG
shock absorber has accumulated 1,900 or more total landings and less
than 4,200 total landings since new or overhauled as of the
effective date of this AD: At the applicable compliance time
specified in paragraph (f)(2)(i) or (f)(2)(ii) of this AD, inspect
the shock absorber for damage, in accordance with the Accomplishment
Instructions of Dassault Mandatory Service Bulletin F2000-366,
Revision 2; or F2000EX-167, Revision 1; both dated December 1, 2008;
as applicable. If any damage is found, repair the shock absorber at
the applicable time specified in Table 1 of this AD, in accordance
with the Accomplishment Instructions of Dassault Mandatory Service
Bulletin F2000-366, Revision 2; or F2000EX-167, Revision 1; both
dated December 1, 2008; as applicable.
(i) For airplanes on which 6 or more steep-approach landings
have been performed before the effective date of this AD: Within 8
months after the effective date of this AD, do the actions required
by paragraph (f)(2) of this AD.
(ii) For airplanes on which less than or equal to 5 steep-
approach landings have been performed before the effective date of
this AD: Within 18 months after the effective date of this AD or
5,000 total landings since new or overhauled, whichever occurs
first, do the actions required by paragraph (f)(2) of this AD.
(3) For airplanes on which each new or previously overhauled MLG
shock absorber has accumulated less than 1,900 total landings since
new or overhauled as of the effective date of this AD: Before the
accumulation of 3,000 total landings since new or overhauled,
inspect the shock absorber for damage, in accordance with the
Accomplishment Instructions of Dassault Mandatory Service Bulletin
F2000-366, Revision 2; or F2000EX-167, Revision 1; both dated
December 1, 2008; as applicable. If any damage is found, repair the
shock absorber at the time specified in Table 1 of this AD, in
accordance with the Accomplishment Instructions of Dassault
Mandatory Service Bulletin F2000-366, Revision 2; or F2000EX-167,
Revision 1; both dated December 1, 2008; as applicable.
Table 1--Compliance Times for Repair
----------------------------------------------------------------------------------------------------------------
Damage found Compliance time
----------------------------------------------------------------------------------------------------------------
1, 2, or 3 loose screws................ Within 12 months after the finding.
1 broken screw......................... Within 6 months after the finding.
2 or 3 broken screws................... Within 10 flight cycles after the finding.
3 broken screws with detached damping Before further flight.
device.
----------------------------------------------------------------------------------------------------------------
(4) Repeat the inspections required by paragraphs (f)(1),
(f)(2), and (f)(3) of this AD, as applicable, thereafter at
intervals not to exceed 1,900 landings until accomplishment of the
actions specified in paragraph (f)(6) of this AD.
(5) Accomplishment of any inspection or repair before the
effective date of this AD in accordance the applicable service
information specified in Table 2 of this AD is acceptable for
compliance with the corresponding requirements of this AD.
Table 2--Credit Service Information
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Dassault Mandatory Service Bulletin 1................................. August 18, 2008.
F2000-366.
Dassault Mandatory Service Bulletin Original.......................... August 18, 2008.
F2000EX-167.
Dassault Service Bulletin F2000-366..... Original.......................... April 18, 2008.
----------------------------------------------------------------------------------------------------------------
(6) For airplanes on which Dassault Modification M3120 has not
been embodied as of the effective date of this AD: Before the
accumulation of 6,000 total landings or 144 months on each new or
previously overhauled MLG shock absorber, whichever occurs first:
Modify the existing left- and right-hand MLG shock absorbers by
installing MLG shock absorbers with part number (P/N) D23365000-4 or
P/N D23366000-4 (for Model Falcon 2000 airplanes), or P/N D23745000-
2 or P/N D23746000-2 (for Model Falcon 2000EX airplanes), in
accordance with the Accomplishment Instructions of Dassault Service
Bulletin F2000EX-185, Revision 2; or F2000-367, Revision 4; both
dated February 4, 2009; as applicable. Where these service bulletins
specify contacting the manufacturer for repair instructions, contact
the manufacturer and do the repair at the applicable compliance
times specified in the Accomplishment Instructions of the applicable
service bulletin.
(7) Accomplishment of the modification required by paragraph
(f)(6) of this AD before the effective date of this AD in accordance
with the applicable service information specified in Table 3 of this
AD is acceptable for compliance with the corresponding requirements
of this AD.
Table 3--Credit Service Information for Modification
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Dassault Service Bulletin F2000EX-185... Original.......................... August 18, 2008.
Dassault Service Bulletin F2000EX-185... 1................................. December 1, 2008.
Dassault Service Bulletin F2000-367..... 1................................. July 10, 2008.
[[Page 28469]]
Dassault Service Bulletin F2000-367..... 2................................. August 18, 2008.
Dassault Service Bulletin F2000-367..... 3................................. December 1, 2008.
----------------------------------------------------------------------------------------------------------------
(8) Accomplishment of the modification required by paragraph
(f)(6) of this AD ends the repetitive inspections required by
paragraph (f)(4) of this AD.
(9) As of the effective date of this AD, no person may install
on any airplane as a replacement part, a MLG shock absorber, unless
it has been modified according to the requirements specified in
paragraph (f)(6) of this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: Paragraph (1) of the MCAI requires updating the
operator's maintenance program; however, that action is not required
by this AD. The maintenance program does not require FAA approval.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to Attn: Tom
Rodriguez, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(h) Refer to MCAI EASA Airworthiness Directive 2009-0050, dated
March 5, 2009, and the service information identified in Table 4 of
this AD, for related information.
Table 4--Service Information
------------------------------------------------------------------------
Document Revision Date
------------------------------------------------------------------------
Dassault Mandatory Service 2 December 1, 2008.
Bulletin F2000-366.
Dassault Mandatory Service 1 December 1, 2008.
Bulletin F2000EX-167.
Dassault Service Bulletin 4 February 4, 2009.
F2000-367.
Dassault Service Bulletin 2 February 4, 2009.
F2000EX-185.
------------------------------------------------------------------------
Material Incorporated by Reference
(i) You must use the applicable service information contained in
Table 5 of this AD to do the actions required by this AD, unless the
AD specifies otherwise.
Table 5--Material Incorporated by Reference
------------------------------------------------------------------------
Document Revision Date
------------------------------------------------------------------------
Dassault Mandatory Service 2 December 1, 2008.
Bulletin F2000-366.
Dassault Mandatory Service 1 December 1, 2008.
Bulletin F2000EX-167.
Dassault Service Bulletin 4 February 4, 2009.
F2000-367.
Dassault Service Bulletin 2 February 4, 2009.
F2000EX-185.
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(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey
07606; telephone 201-440-6700; Internet https://www.dassaultfalcon.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(4) You may also review copies of the service information that
is incorporated by reference 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.
Issued in Renton, Washington, on May 4, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-11358 Filed 5-20-10; 8:45 am]
BILLING CODE 4910-13-P
