Airworthiness Directives; Bombardier Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), CL-600-2D15 (Regional Jet Series 705), and CL-600-2D24 (Regional Jet Series 900) Airplanes, 8441-8443 [06-1406]
Download as PDF
Federal Register / Vol. 71, No. 33 / Friday, February 17, 2006 / Rules and Regulations
thereafter at intervals not to exceed 4,000
flight hours.
Note 2: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
(1) Before accumulating 4,000 total flight
hours on the inboard flap trunnion since
new.
(2) Within 4,000 flight hours after
accomplishing paragraph (f) of this AD.
(3) Within 600 flight hours after the
effective date of this AD.
No Reporting Requirement
(h) Although Airbus Service Bulletin
A320–57–1133, dated July 28, 2005, specifies
to submit certain information to the
manufacturer, this AD does not include that
requirement.
Compliance Times
(i) Where Airbus Service Bulletin A320–
57–1133, dated July 28, 2005, specifies
replacing the sliding panel at the next
opportunity, replace it within 600 flight
hours after the inspection required by
paragraph (g) of this AD. If the trunnion is
found damaged during any inspection
required by paragraph (g) of this AD, do the
corrective actions specified in the service
bulletin before further flight. Where the
service bulletin specifies contacting the
manufacturer for a grace period assessment
after replacing the trunnion or flap, contact
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA, or
´ ´
Direction Generale de l’Aviation Civile
(DGAC) for the grace period assessment.
Alternative Methods of Compliance
(AMOCs)
(j)(1) 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.
(2) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
wwhite on PROD1PC61 with RULES
Related Information
(k) French airworthiness directive F–2005–
139, dated August 3, 2005, also addresses the
subject of this AD.
Material Incorporated by Reference
(l) You must use Airbus Service Bulletin
A320–27–1117, Revision 02, dated January
18, 2000; and Airbus Service Bulletin A320–
57–1133, excluding Appendix 01, dated July
28, 2005, as applicable, to perform the
actions that are required by this AD, unless
the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
VerDate Aug<31>2005
18:49 Feb 16, 2006
Jkt 208001
Airbus Service Bulletin A320–57–1133,
excluding Appendix 01, dated July 28, 2005,
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) On January 8, 2001 (65 FR 75603,
December 4, 2000), the Director of the
Federal Register approved the incorporation
by reference of Airbus Service Bulletin
A320–27–1117, Revision 02, dated January
18, 2000.
(3) Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France, for a
copy of this service information. You may
review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street, SW., room PL–401,
Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at the NARA,
call (202) 741–6030, or go to https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on February
6, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–1405 Filed 2–16–06; 8:45 am]
BILLING CODE 4910–13–P
8441
interfering with an inboard rudder
pedal, which could reduce directional
controllability of the airplane.
This AD becomes effective
March 24, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of March 24, 2006.
DATES:
You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., Nassif Building, room PL–401,
Washington, DC.
Contact Bombardier, Inc., Canadair,
Aerospace Group, P.O. Box 6087,
Station Centre-ville, Montreal, Quebec
H3C 3G9, Canada, for service
information identified in this AD.
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
Daniel Parrillo, Aerospace Engineer,
Systems and Flight Test Branch, ANE–
172, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, suite 410, Westbury, New York
11590; telephone (516) 228–7305; fax
(516) 794–5531.
DEPARTMENT OF TRANSPORTATION
SUPPLEMENTARY INFORMATION:
Federal Aviation Administration
Examining the Docket
14 CFR Part 39
[Docket No. FAA–2005–22872; Directorate
Identifier 2005–NM–198–AD; Amendment
39–14490; AD 2006–04–09]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model CL–600–2C10 (Regional Jet
Series 700, 701, & 702), CL–600–2D15
(Regional Jet Series 705), and CL–600–
2D24 (Regional Jet Series 900)
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Bombardier Model CL–600–2C10
(Regional Jet Series 700, 701, & 702),
CL–600–2D15 (Regional Jet Series 705),
and CL–600–2D24 (Regional Jet Series
900) airplanes. This AD requires
replacing the Camloc fasteners on the
sidewall of the center pedestal. This AD
results from reports of the Camloc
fasteners on the sidewall of the center
pedestal disengaging and interfering
with an inboard rudder pedal. We are
issuing this AD to prevent these
fasteners from disengaging and
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Bombardier Model CL–
600–2C10 (Regional Jet Series 700, 701,
& 702), CL–600–2D15 (Regional Jet
Series 705), and CL–600–2D24 (Regional
Jet Series 900) airplanes. That NPRM
was published in the Federal Register
on November 9, 2005 (70 FR 67946).
That NPRM proposed to require
replacing the Camloc fasteners on the
sidewall of the center pedestal.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the single comment
received.
E:\FR\FM\17FER1.SGM
17FER1
8442
Federal Register / Vol. 71, No. 33 / Friday, February 17, 2006 / Rules and Regulations
Request To Allow Use of Alternative
Parts
The commenter agrees with the
proposed 5,500-flight-hour compliance
time. But the commenter requests that
we allow installation of operatorsupplied hardware with operatorfabricated gang-nut plates in lieu of the
parts specified in the referenced service
bulletin. The commenter states that this
will facilitate compliance with the
proposed AD because operators will not
be dependent on parts availability.
We do not agree with the commenter’s
request. We have discussed the question
of parts availability with the
manufacturer, and the manufacturer
states that there is no problem with
availability of the kit needed to
complete the requirements of this AD.
Therefore, parts availability does not
justify allowing operators to install parts
other than those specified in the service
bulletin. Also, it is not appropriate to
address such a request in an AD. We
recommend that the commenter apply
for approval of an alternative method of
compliance (AMOC) and provide
specific information about the hardware
proposed in the comment. Operators
who choose to submit an AMOC request
should include data supporting that the
proposed alternative hardware will
provide an acceptable level of safety.
We have not changed the final rule in
this regard.
Conclusion
We have carefully reviewed the
available data, including the comment
received, and determined that air safety
and the public interest require adopting
the AD as proposed.
Costs of Compliance
This AD affects about 209 airplanes of
U.S. registry. The required actions will
take about 2 work hours per airplane, at
an average labor rate of $65 per work
hour. Required parts will cost between
$141 and $150 per airplane. Based on
these figures, the estimated cost of this
AD for U.S. operators is between
$56,639 and $58,520, or between $271
and $280 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in subtitle VII,
part A, subpart III, section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2006–04–09 Bombardier, Inc. (Formerly
Canadair): Amendment 39–14490.
Docket No. FAA–2005–22872;
Directorate Identifier 2005–NM–198–AD.
Effective Date
(a) This AD becomes effective March 24,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes
identified in Table 1 of this AD, certificated
in any category.
TABLE 1.—APPLICABILITY
Bombardier models
Serial Nos.
10003 through 10218 inclusive.
15001 through 15047 inclusive.
Unsafe Condition
wwhite on PROD1PC61 with RULES
CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes ...................................................
CL–600–2D15 (Regional Jet Series 705) airplanes, CL–600–2D24 (Regional Jet Series 900)
airplanes.
Compliance
(d) This AD results from reports of the
Camloc fasteners on the sidewall of the
center pedestal disengaging and interfering
with an inboard rudder pedal. We are issuing
this AD to prevent these fasteners from
disengaging and interfering with an inboard
rudder pedal, which could reduce directional
controllability of the airplane.
(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.
center pedestal, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 670BA–25–037, Revision A,
dated August 25, 2005.
VerDate Aug<31>2005
18:49 Feb 16, 2006
Jkt 208001
Replacement of Fasteners
(f) Within 5,500 flight hours after the
effective date of this AD, replace, with screws
and nut plate assemblies, the Camloc
fasteners on the left and right sidewalls of the
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
Actions Accomplished Previously
(g) Replacing fasteners before the effective
date of this AD in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 670BA–25–037, dated June
E:\FR\FM\17FER1.SGM
17FER1
Federal Register / Vol. 71, No. 33 / Friday, February 17, 2006 / Rules and Regulations
23, 2005, is acceptable for compliance with
the requirements of paragraph (f) of this AD.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, New York Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Related Information
(i) Canadian airworthiness directive CF–
2005–31, dated August 17, 2005, also
addresses the subject of this AD.
Material Incorporated by Reference
(j) You must use Bombardier Service
Bulletin 670BA–25–037, Revision A, dated
August 25, 2005, to perform the actions that
are required by this AD, unless the AD
specifies otherwise. The Director of the
Federal Register approved the incorporation
by reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Bombardier, Inc., Canadair,
Aerospace Group, P.O. Box 6087, Station
Centre-ville, Montreal, Quebec H3C 3G9,
Canada, for a copy of this service
information. You may review copies at the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street SW., room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on February
6, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–1406 Filed 2–16–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22558; Directorate
Identifier 2005–NM–107–AD; Amendment
39–14491; AD 2006–04–10]
wwhite on PROD1PC61 with RULES
RIN 2120–AA64
Airworthiness Directives; Cessna
Model 500, 550, S550, 560, 560XL, and
750 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
VerDate Aug<31>2005
18:49 Feb 16, 2006
Jkt 208001
ACTION:
Final rule.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Cessna Model 500, 550, S550, 560,
560XL, and 750 airplanes. This AD
requires installing identification sleeves
on the wires for the positive and
negative terminal studs of the engine
and/or auxiliary power unit (APU) fire
extinguishing bottles, as applicable, and
re-connecting the wires to the correct
terminal studs. This AD results from a
report of mis-wired fire extinguishing
bottles. We are issuing this AD to ensure
that the fire extinguishing bottles are
activated in the event of an engine or
APU fire, and that flammable fluids are
not supplied during a fire, which could
result in an unextinguished fire in the
nacelle or APU.
DATES: This AD becomes effective
March 24, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of March 24, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, room PL–401,
Washington, DC.
Contact Cessna Aircraft Co., P.O. Box
7706, Wichita, Kansas 67277, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Robert D. Adamson, Aerospace
Engineer, Systems and Propulsion
Branch, ACE–116W, FAA, Wichita
Aircraft Certification Office, 1801
Airport Road, room 100, Mid-Continent
Airport, Wichita, Kansas 67209;
telephone (316) 946–4145; fax (316)
946–4107.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Cessna Model 500, 550,
S550, 560, 560XL, and 750 airplanes.
That NPRM was published in the
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
8443
Federal Register on September 30, 2005
(70 FR 57213). That NPRM proposed to
require installing identification sleeves
on the wires for the positive and
negative terminal studs of the engine
and/or auxiliary power unit (APU) fire
extinguishing bottles, as applicable, and
re-connecting the wires to the correct
terminal studs.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Use Parts Other Than
Factory Kit
The commenter sees the need for the
proposed AD, but does not like the fact
that it is tied to a factory service
bulletin. The commenter states that the
kits specified in the service bulletin that
are necessary to do the actions in the
NPRM are often out of stock at the
manufacturer. The commenter further
points out that the actions in the NPRM
can be accomplished without waiting
for the kit because the actions can be
done using standard items and practices
in the field. In addition, the commenter
states that the kits are much more costly
than the estimate provided in the
NPRM.
We infer that the commenter is
requesting confirmation that the factoryprovided kits are available for all
affected airplanes to accomplish the
required actions, and that the kits will
not be more costly than stated in the
NPRM. The manufacturer has assured
us that the kits are available and that the
parts costs cited in the NPRM are
correct. The manufacturer also noted
that there is no cost for kits if the
affected airplane is within its five-year
warranty period. If the commenter has
difficulty getting a kit or kits, or wishes
to use standard items and practices in
the field, the commenter can apply for
an alternative method of compliance in
accordance with the procedures in
paragraph (j) of this AD.
We have not changed the AD in this
regard.
Request To Correct Incorrect Statement
Regarding Shutoff Valves
Another commenter supports the
need for the proposed AD, but states
that the ‘‘Discussion’’ section
incorrectly indicates that the mis-wiring
will cause the shutoff valves for the
main engine fuel and hydraulic firewall
to open. The commenter suggests that
we delete this statement. The
commenter explains that the valves are
motor-operated and remain in the last
position when power is absent. They
E:\FR\FM\17FER1.SGM
17FER1
Agencies
[Federal Register Volume 71, Number 33 (Friday, February 17, 2006)]
[Rules and Regulations]
[Pages 8441-8443]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-1406]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22872; Directorate Identifier 2005-NM-198-AD;
Amendment 39-14490; AD 2006-04-09]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-2C10 (Regional
Jet Series 700, 701, & 702), CL-600-2D15 (Regional Jet Series 705), and
CL-600-2D24 (Regional Jet Series 900) Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Bombardier Model CL-600-2C10 (Regional Jet Series 700, 701, &
702), CL-600-2D15 (Regional Jet Series 705), and CL-600-2D24 (Regional
Jet Series 900) airplanes. This AD requires replacing the Camloc
fasteners on the sidewall of the center pedestal. This AD results from
reports of the Camloc fasteners on the sidewall of the center pedestal
disengaging and interfering with an inboard rudder pedal. We are
issuing this AD to prevent these fasteners from disengaging and
interfering with an inboard rudder pedal, which could reduce
directional controllability of the airplane.
DATES: This AD becomes effective March 24, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of March 24,
2006.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., Nassif Building,
room PL-401, Washington, DC.
Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087,
Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Daniel Parrillo, Aerospace Engineer,
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New
York 11590; telephone (516) 228-7305; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to certain Bombardier
Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), CL-600-2D15
(Regional Jet Series 705), and CL-600-2D24 (Regional Jet Series 900)
airplanes. That NPRM was published in the Federal Register on November
9, 2005 (70 FR 67946). That NPRM proposed to require replacing the
Camloc fasteners on the sidewall of the center pedestal.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the single comment received.
[[Page 8442]]
Request To Allow Use of Alternative Parts
The commenter agrees with the proposed 5,500-flight-hour compliance
time. But the commenter requests that we allow installation of
operator-supplied hardware with operator-fabricated gang-nut plates in
lieu of the parts specified in the referenced service bulletin. The
commenter states that this will facilitate compliance with the proposed
AD because operators will not be dependent on parts availability.
We do not agree with the commenter's request. We have discussed the
question of parts availability with the manufacturer, and the
manufacturer states that there is no problem with availability of the
kit needed to complete the requirements of this AD. Therefore, parts
availability does not justify allowing operators to install parts other
than those specified in the service bulletin. Also, it is not
appropriate to address such a request in an AD. We recommend that the
commenter apply for approval of an alternative method of compliance
(AMOC) and provide specific information about the hardware proposed in
the comment. Operators who choose to submit an AMOC request should
include data supporting that the proposed alternative hardware will
provide an acceptable level of safety. We have not changed the final
rule in this regard.
Conclusion
We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD as proposed.
Costs of Compliance
This AD affects about 209 airplanes of U.S. registry. The required
actions will take about 2 work hours per airplane, at an average labor
rate of $65 per work hour. Required parts will cost between $141 and
$150 per airplane. Based on these figures, the estimated cost of this
AD for U.S. operators is between $56,639 and $58,520, or between $271
and $280 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2006-04-09 Bombardier, Inc. (Formerly Canadair): Amendment 39-14490.
Docket No. FAA-2005-22872; Directorate Identifier 2005-NM-198-AD.
Effective Date
(a) This AD becomes effective March 24, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes identified in Table 1 of
this AD, certificated in any category.
Table 1.--Applicability
------------------------------------------------------------------------
Bombardier models Serial Nos.
------------------------------------------------------------------------
CL-600-2C10 (Regional Jet Series 700, 701, 10003 through 10218
& 702) airplanes. inclusive.
CL-600-2D15 (Regional Jet Series 705) 15001 through 15047
airplanes, CL-600-2D24 (Regional Jet inclusive.
Series 900) airplanes.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from reports of the Camloc fasteners on the
sidewall of the center pedestal disengaging and interfering with an
inboard rudder pedal. We are issuing this AD to prevent these
fasteners from disengaging and interfering with an inboard rudder
pedal, which could reduce directional controllability of the
airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Replacement of Fasteners
(f) Within 5,500 flight hours after the effective date of this
AD, replace, with screws and nut plate assemblies, the Camloc
fasteners on the left and right sidewalls of the center pedestal, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 670BA-25-037, Revision A, dated August 25, 2005.
Actions Accomplished Previously
(g) Replacing fasteners before the effective date of this AD in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 670BA-25-037, dated June
[[Page 8443]]
23, 2005, is acceptable for compliance with the requirements of
paragraph (f) of this AD.
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, New York Aircraft Certification Office, FAA,
has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(i) Canadian airworthiness directive CF-2005-31, dated August
17, 2005, also addresses the subject of this AD.
Material Incorporated by Reference
(j) You must use Bombardier Service Bulletin 670BA-25-037,
Revision A, dated August 25, 2005, to perform the actions that are
required by this AD, unless the AD specifies otherwise. The Director
of the Federal Register approved the incorporation by reference of
this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087,
Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for a copy
of this service information. You may review copies at the Docket
Management Facility, U.S. Department of Transportation, 400 Seventh
Street SW., room PL-401, Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at the NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on February 6, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-1406 Filed 2-16-06; 8:45 am]
BILLING CODE 4910-13-P