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, 58631-58634 [05-20271]
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58631
Federal Register / Vol. 70, No. 194 / Friday, October 7, 2005 / Proposed Rules
testing requirements, in accordance with the
service information listed in the Table 2 of
this AD, prior to the effective date of this AD,
is acceptable for compliance with the
requirements of paragraph (h) of this AD.
TABLE 2.—PREVIOUS ACCOMPLISHMENT
Boeing service information
Revision
Special Attention Service Bulletin 737–25–1438 ...........................................................................................
Special Attention Service Bulletin 737–25–1439 ...........................................................................................
Special Attention Service Bulletin 737–25–1439 ...........................................................................................
Service Bulletin 737–25–1439 .......................................................................................................................
Special Attention Service Bulletin 747–25–3264 ...........................................................................................
Special Attention Service Bulletin 747–25–3275 ...........................................................................................
Special Attention Service Bulletin 757–25–0238 ...........................................................................................
Special Attention Service Bulletin 757–25–0238 ...........................................................................................
Special Attention Service Bulletin 767–25–0297 ...........................................................................................
Special Attention Service Bulletin 777–25–0180 ...........................................................................................
Original ........
Original ........
1 ..................
2 ..................
Original ........
Original ........
Original ........
1 ..................
Original ........
Original ........
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) An AMOC that provides an acceptable
level of safety may be used for any
replacement required by this AD, if it is
approved by an Authorized Representative
for the Boeing Commercial Airplanes
Delegation Option Authorization
Organization who has been authorized by the
Manager, Seattle ACO, to make those
findings. For a repair method to be approved,
the repair must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
Issued in Renton, Washington, on
September 28, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–20270 Filed 10–6–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22632; Directorate
Identifier 2005–NM–158–AD]
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: Notice of proposed rulemaking
(NPRM).
AGENCY:
VerDate Aug<31>2005
16:34 Oct 06, 2005
Jkt 208001
SUMMARY: The FAA proposes to adopt 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 proposed AD
would require repetitive inspections for
cracking or fracturing of the output links
of the power control unit (PCU) for the
ailerons, and related investigative and
corrective actions if necessary. This
proposed AD results from reports of
fractured output links of the aileron
PCU. We are proposing this AD to
prevent failure of an output link of the
aileron PCU, which, if both links on one
aileron fail, could result in reduced
lateral control of the airplane.
DATES: We must receive comments on
this proposed AD by November 7, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Bombardier, Inc., Canadair,
Aerospace Group, P.O. Box 6087,
Station Centre-ville, Montreal, Quebec
H3C 3G9, Canada, for service
information identified in this proposed
AD.
PO 00000
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Fmt 4702
Sfmt 4702
Dated
March 15, 2001.
March 15, 2001.
August 2, 2001.
December 19, 2001.
March 15, 2001.
March 15, 2001.
March 15, 2001.
November 15, 2001.
March 15, 2001.
March 15, 2001.
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:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2005–22632; Directorate
Identifier 2005–NM–158–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
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58632
Federal Register / Vol. 70, No. 194 / Friday, October 7, 2005 / Proposed Rules
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Discussion
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, notified us that an
unsafe condition may exist on 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. TCCA advises that
fractured output links of the power
control unit (PCU) for the ailerons have
been found on in-service Bombardier
Model CL–600–2B19 (Regional Jet
Series 100 & 440) airplanes. Cracking or
fracture of an output link of the aileron
PCU, if not corrected, could result in
failure of the link. Failure of one link
may be a dormant (undetected) failure.
However, failure of both output links on
one aileron could result in reduced
lateral control of the airplane.
The output links of the aileron PCU
on 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 are similar to those
on the affected Bombardier Model CL–
600–2B19 (Regional Jet Series 100 &
440) airplanes. Therefore, those
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 may be subject to the
unsafe condition revealed on the
Bombardier Model CL–600–2B19
(Regional Jet Series 100 & 440)
airplanes.
Other Relevant Rulemaking
We previously issued AD 2005–03–
13, amendment 39–13969 (70 FR 7845,
February 16, 2005). AD 2005–03–13
requires doing repetitive inspections for
fractures and cracks of the links of the
aileron PCU; replacing any fractured/
cracked link; and doing applicable
related investigative and corrective
actions, if necessary. The actions
required by that AD, which applies to
certain Bombardier Model CL–600–
VerDate Aug<31>2005
15:27 Oct 06, 2005
Jkt 208001
2B19 (Regional Jet Series 100 and 440)
airplanes, are similar to those that
would be required by this proposed AD
for 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.
Relevant Service Information
Bombardier has issued Alert Service
Bulletin A670BA–27–023, including
Appendix A, Revision A, dated May 18,
2005. The service bulletin describes
procedures for repetitive detailed
inspections for cracking or fracturing of
the output links of the aileron PCU, and
related investigative and corrective
actions if necessary. If any fractured or
cracked link is found, the service
bulletin specifies a corrective action of
replacing the fractured/cracked link
with a new link. The service bulletin
also describes related investigative
actions and corrective actions that must
be done if any fractured or cracked link
is found, which include:
• Measuring the torque value of the
forward and aft attachment bolts for
both the damaged PCU output link and
the adjacent PCU output link installed
on the same aileron.
• For any damaged PCU output link,
testing and measuring, as applicable, to
determine if there is any mismatch
between the PCU output link and the
aileron lugs.
• For any damaged PCU output link,
performing an eddy current inspection
for cracking of the aileron lugs and
flange bushings of the aileron lugs.
• If any damage (including but not
limited to cracking) of an aileron lug or
flange bushing is found, contacting the
manufacturer for instructions.
• Reporting results of all inspections,
measurements, and tests, to the
manufacturer.
TCCA mandated the service
information and issued Canadian
airworthiness directive CF–2005–23,
dated June 29, 2005, to ensure the
continued airworthiness of these
airplanes in Canada.
FAA’s Determination and Requirements
of the Proposed AD
These airplane models are
manufactured in Canada and are type
certificated for operation in the United
States under the provisions of section
21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement. Pursuant to this bilateral
airworthiness agreement, TCCA has
kept the FAA informed of the situation
described above. We have examined
TCCA’s findings, evaluated all pertinent
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
information, and determined that we
need to issue an AD for airplanes of this
type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD,
which would require accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Difference
Among the Proposed AD, Canadian
Airworthiness Directive, and Service
Information.’’ The proposed AD would
also require sending the inspection
results to the manufacturer.
Difference Among the Proposed AD,
Canadian Airworthiness Directive, and
Service Information
The Canadian airworthiness directive
and service bulletin specify to contact
the manufacturer for instructions on
how to disposition certain damaged
parts. This proposed AD would require
you to disposition those parts using a
method that we or TCCA (or its
delegated agent) approve. In light of the
type of action that would be required to
address the unsafe condition, and
consistent with existing bilateral
airworthiness agreements, we have
determined that, for this proposed AD,
disposition of a damaged part in a
manner that we or TCCA approve would
be acceptable for compliance with this
proposed AD.
Clarification of Inspection Terminology
The Canadian airworthiness directive
specifies performing a ‘‘detailed visual’’
inspection for cracking or fracturing of
the output links of the aileron PCU. We
refer to this inspection as a ‘‘detailed
inspection.’’ We have included the
definition for a detailed inspection in a
note in the proposed AD. (This
terminology is consistent with the
terminology used in the service
information.)
Interim Action
We consider this proposed AD
interim action. The inspection reports
that are required by this AD will enable
the manufacturer to obtain better insight
into the nature, cause, and extent of the
cracking, and eventually to develop
final action to address the unsafe
condition. Once final action has been
identified, we may consider further
rulemaking.
Costs of Compliance
This proposed AD would affect about
205 airplanes of U.S. registry. The
proposed inspection would take about 1
work hour per airplane, per inspection
cycle, at an average labor rate of $65 per
work hour. Based on these figures, the
estimated cost of this proposed
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Federal Register / Vol. 70, No. 194 / Friday, October 7, 2005 / Proposed Rules
inspection for U.S. operators is $13,325,
or $65 per airplane, per inspection
cycle.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in subtitle VII,
part A, subpart III, section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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 the proposed regulation:
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 proposed 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, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
15:27 Oct 06, 2005
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 Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Bombardier, Inc. (Formerly Canadair):
Docket No. FAA–2005–22632;
Directorate Identifier 2005–NM–158–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by November 7, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the Bombardier
airplanes identified in Table 1 of this AD,
certificated in any category.
TABLE 1.—APPLICABILITY
Bombardier airplane models
Regulatory Findings
VerDate Aug<31>2005
PART 39—AIRWORTHINESS
DIRECTIVES
Jkt 208001
Serial
Nos.
CL–600–2C10 (Regional Jet
Series 700, 701, & 702).
CL–600–2D15 (Regional Jet
Series 705).
CL–600–2D24 (Regional Jet
Series 900).
10003 and
subsequent.
15001 and
subsequent.
15001 and
subsequent.
Unsafe Condition
(d) This AD results from reports of
fractured output links of the power control
unit (PCU) for the ailerons. We are issuing
this AD to prevent failure of an output link
of the aileron PCU, which, if both links on
one aileron fail, could result in reduced
lateral control 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.
Repetitive Inspections, Related Investigative
Actions, and Corrective Actions
(f) Prior to the accumulation of 2,000 total
flight hours, or within 550 flight hours after
the effective date of this AD, whichever is
later: Do a detailed inspection for cracking or
fracturing of the output links of the aileron
PCU and do all related investigative and
corrective actions, as applicable, in
accordance with the Accomplishment
Instructions of Bombardier Alert Service
Bulletin A670BA–27–023, including
Appendix A, Revision A, dated May 18,
2005, except as provided by paragraph (g) of
this AD. Thereafter, repeat the inspection and
applicable related investigative and
corrective actions at intervals not to exceed
1,000 flight hours. Any applicable related
investigative and corrective actions must be
done before further flight after the inspection.
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
58633
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Exception to Corrective Action Instructions
(g) If any cracking or other damage is found
on an aileron lug or flange bushing during
any inspection required by this AD, and the
service bulletin recommends contacting
Bombardier for appropriate action: Before
further flight, disposition and replace the
cracked or damaged aileron lug or flange
bushing with a new part, in accordance with
a method approved by the Manager, New
York Aircraft Certification Office (ACO),
FAA; or Transport Canada Civil Aviation
(TCCA) (or its delegated agent).
Reporting
(h) Submit a report of the findings (both
positive and negative) of the inspections
required by paragraph (f) of this AD to
Bombardier Aerospace; Attention: Christian
Holzl, dept. 508; Location S666 1422 024;
13100 Highway 50; Mirabel, Quebec, Canada,
J7M 3C6; fax (450) 476–7321. Submit the
report at the applicable time specified in
paragraph (h)(1) or (h)(2) of this AD. The
report must include the airplane serial
number, the total accumulated flight cycles
and flight hours on the airplane, the date of
the inspection, the total accumulated flight
cycles and flight hours at the last ‘‘C’’ check,
the serial number of each PCU, and the
results of all inspections, tests, and
measurements done in accordance with
paragraph (f) of this AD. Submitting
Appendix A of Bombardier Alert Service
Bulletin A670BA–27–023, including
Appendix A, Revision A, dated May 18,
2005, is an acceptable means of complying
with this requirement. Under the provisions
of the Paperwork Reduction Act of 1980 (44
U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements contained in this AD and has
assigned OMB Control Number 2120–0056.
(1) If the inspection was done after the
effective date of this AD: Submit the report
within 30 days after the inspection.
(2) If the inspection was done prior to the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
Actions Accomplished Previously
(i) Inspections and corrective actions done,
and reports submitted, before the effective
date of this AD in accordance with
Bombardier Alert Service Bulletin A670BA–
27–023, including Appendix A, dated May 3,
2005, are acceptable for compliance with the
corresponding requirements of paragraphs (f)
and (h) of this AD.
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Federal Register / Vol. 70, No. 194 / Friday, October 7, 2005 / Proposed Rules
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, New York ACO, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
Related Information
(k) Canadian airworthiness directive CF–
2005–23, dated June 29, 2005, also addresses
the subject of this AD.
Issued in Renton, Washington, on
September 30, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–20271 Filed 10–6–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Dassault Falcon Jet, P.O. Box
2000, South Hackensack, New Jersey
07606, for service information identified
in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1137;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Federal Aviation Administration
Comments Invited
14 CFR Part 39
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2005–22633; Directorate
Identifier 2005–NM–155–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
[Docket No. FAA–2005–22633; Directorate
Identifier 2005–NM–155–AD]
RIN 2120–AA64
Airworthiness Directives; Dassault
Model Falcon 2000 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Dassault Model Falcon 2000
airplanes. This proposed AD would
require an inspection for the presence of
fail-safe pins, nuts, and washers on each
engine, and replacement of the fail-safe
fastener assembly with a new assembly
if necessary. This proposed AD results
from a report of a missing pin of a failsafe fastener. We are proposing this AD
to prevent reduced structural integrity
of an engine mount due to a missing pin
of a fail-safe fastener, and possible
separation of an engine from the
airplane during flight.
DATES: We must receive comments on
this proposed AD by November 7, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
VerDate Aug<31>2005
15:27 Oct 06, 2005
Jkt 208001
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Discussion
´ ´
The Direction Generale de l’Aviation
Civile (DGAC), which is the
airworthiness authority for France,
notified us that an unsafe condition may
exist on certain Dassault Model Falcon
2000 airplanes. The DGAC advises that
the inner pin of a fail-safe fastener,
which ensures the link between the rear
of the engine and the fuselage, has been
found missing on an in-service airplane.
Lack of clarity in a production
procedure is suspected to be the cause
of this event. A missing pin of a fail-safe
fastener, if not corrected, could result in
reduced structural integrity of an engine
mount, and possible separation of an
engine from the airplane during flight.
Relevant Service Information
Dassault has issued Service Bulletin
F2000–301, dated February 2, 2005. The
service bulletin describes procedures for
a detailed inspection for the presence of
fail-safe pins, nuts, and washers on each
engine, and replacement of the fail-safe
fastener assembly with a new assembly
if necessary. Accomplishing the actions
specified in the service information is
intended to adequately address the
unsafe condition. The DGAC mandated
the service information and issued
French airworthiness directive F–2005–
018, dated February 2, 2005, to ensure
the continued airworthiness of these
airplanes in France.
FAA’s Determination and Requirements
of the Proposed AD
This airplane model is manufactured
in France and is type certificated for
operation in the United States under the
provisions of section 21.29 of the
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement. Pursuant to
this bilateral airworthiness agreement,
the DGAC has kept the FAA informed
of the situation described above. We
have examined the DGAC’s findings,
evaluated all pertinent information, and
determined that we need to issue an AD
for airplanes of this type design that are
certificated for operation in the United
States.
Therefore, we are proposing this AD,
which would require accomplishing the
actions specified in the service
information described previously,
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07OCP1
]]>Agencies
[Federal Register Volume 70, Number 194 (Friday, October 7, 2005)]
[Proposed Rules]
[Pages 58631-58634]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-20271]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22632; Directorate Identifier 2005-NM-158-AD]
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: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt 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 proposed AD would require
repetitive inspections for cracking or fracturing of the output links
of the power control unit (PCU) for the ailerons, and related
investigative and corrective actions if necessary. This proposed AD
results from reports of fractured output links of the aileron PCU. We
are proposing this AD to prevent failure of an output link of the
aileron PCU, which, if both links on one aileron fail, could result in
reduced lateral control of the airplane.
DATES: We must receive comments on this proposed AD by November 7,
2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087,
Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for service
information identified in this proposed 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:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2005-
22632; Directorate Identifier 2005-NM-158-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit https://dms.dot.gov.
[[Page 58632]]
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
Transport Canada Civil Aviation (TCCA), which is the airworthiness
authority for Canada, notified us that an unsafe condition may exist on
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. TCCA advises that fractured output links of
the power control unit (PCU) for the ailerons have been found on in-
service Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440)
airplanes. Cracking or fracture of an output link of the aileron PCU,
if not corrected, could result in failure of the link. Failure of one
link may be a dormant (undetected) failure. However, failure of both
output links on one aileron could result in reduced lateral control of
the airplane.
The output links of the aileron PCU on 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
are similar to those on the affected Bombardier Model CL-600-2B19
(Regional Jet Series 100 & 440) airplanes. Therefore, those 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 may be subject to the unsafe condition revealed on the
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes.
Other Relevant Rulemaking
We previously issued AD 2005-03-13, amendment 39-13969 (70 FR 7845,
February 16, 2005). AD 2005-03-13 requires doing repetitive inspections
for fractures and cracks of the links of the aileron PCU; replacing any
fractured/cracked link; and doing applicable related investigative and
corrective actions, if necessary. The actions required by that AD,
which applies to certain Bombardier Model CL-600-2B19 (Regional Jet
Series 100 and 440) airplanes, are similar to those that would be
required by this proposed AD for 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.
Relevant Service Information
Bombardier has issued Alert Service Bulletin A670BA-27-023,
including Appendix A, Revision A, dated May 18, 2005. The service
bulletin describes procedures for repetitive detailed inspections for
cracking or fracturing of the output links of the aileron PCU, and
related investigative and corrective actions if necessary. If any
fractured or cracked link is found, the service bulletin specifies a
corrective action of replacing the fractured/cracked link with a new
link. The service bulletin also describes related investigative actions
and corrective actions that must be done if any fractured or cracked
link is found, which include:
Measuring the torque value of the forward and aft
attachment bolts for both the damaged PCU output link and the adjacent
PCU output link installed on the same aileron.
For any damaged PCU output link, testing and measuring, as
applicable, to determine if there is any mismatch between the PCU
output link and the aileron lugs.
For any damaged PCU output link, performing an eddy
current inspection for cracking of the aileron lugs and flange bushings
of the aileron lugs.
If any damage (including but not limited to cracking) of
an aileron lug or flange bushing is found, contacting the manufacturer
for instructions.
Reporting results of all inspections, measurements, and
tests, to the manufacturer.
TCCA mandated the service information and issued Canadian
airworthiness directive CF-2005-23, dated June 29, 2005, to ensure the
continued airworthiness of these airplanes in Canada.
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in Canada and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, TCCA has kept the FAA informed of
the situation described above. We have examined TCCA's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for airplanes of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously, except as discussed under ``Difference Among the
Proposed AD, Canadian Airworthiness Directive, and Service
Information.'' The proposed AD would also require sending the
inspection results to the manufacturer.
Difference Among the Proposed AD, Canadian Airworthiness Directive, and
Service Information
The Canadian airworthiness directive and service bulletin specify
to contact the manufacturer for instructions on how to disposition
certain damaged parts. This proposed AD would require you to
disposition those parts using a method that we or TCCA (or its
delegated agent) approve. In light of the type of action that would be
required to address the unsafe condition, and consistent with existing
bilateral airworthiness agreements, we have determined that, for this
proposed AD, disposition of a damaged part in a manner that we or TCCA
approve would be acceptable for compliance with this proposed AD.
Clarification of Inspection Terminology
The Canadian airworthiness directive specifies performing a
``detailed visual'' inspection for cracking or fracturing of the output
links of the aileron PCU. We refer to this inspection as a ``detailed
inspection.'' We have included the definition for a detailed inspection
in a note in the proposed AD. (This terminology is consistent with the
terminology used in the service information.)
Interim Action
We consider this proposed AD interim action. The inspection reports
that are required by this AD will enable the manufacturer to obtain
better insight into the nature, cause, and extent of the cracking, and
eventually to develop final action to address the unsafe condition.
Once final action has been identified, we may consider further
rulemaking.
Costs of Compliance
This proposed AD would affect about 205 airplanes of U.S. registry.
The proposed inspection would take about 1 work hour per airplane, per
inspection cycle, at an average labor rate of $65 per work hour. Based
on these figures, the estimated cost of this proposed
[[Page 58633]]
inspection for U.S. operators is $13,325, or $65 per airplane, per
inspection cycle.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
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 proposed 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Bombardier, Inc. (Formerly Canadair): Docket No. FAA-2005-22632;
Directorate Identifier 2005-NM-158-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by November
7, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the Bombardier airplanes identified in
Table 1 of this AD, certificated in any category.
Table 1.--Applicability
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Bombardier airplane models Serial Nos.
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CL-600-2C10 (Regional Jet Series 700, 701, 10003 and subsequent.
& 702).
CL-600-2D15 (Regional Jet Series 705)..... 15001 and subsequent.
CL-600-2D24 (Regional Jet Series 900)..... 15001 and subsequent.
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Unsafe Condition
(d) This AD results from reports of fractured output links of
the power control unit (PCU) for the ailerons. We are issuing this
AD to prevent failure of an output link of the aileron PCU, which,
if both links on one aileron fail, could result in reduced lateral
control 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.
Repetitive Inspections, Related Investigative Actions, and Corrective
Actions
(f) Prior to the accumulation of 2,000 total flight hours, or
within 550 flight hours after the effective date of this AD,
whichever is later: Do a detailed inspection for cracking or
fracturing of the output links of the aileron PCU and do all related
investigative and corrective actions, as applicable, in accordance
with the Accomplishment Instructions of Bombardier Alert Service
Bulletin A670BA-27-023, including Appendix A, Revision A, dated May
18, 2005, except as provided by paragraph (g) of this AD.
Thereafter, repeat the inspection and applicable related
investigative and corrective actions at intervals not to exceed
1,000 flight hours. Any applicable related investigative and
corrective actions must be done before further flight after the
inspection.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Exception to Corrective Action Instructions
(g) If any cracking or other damage is found on an aileron lug
or flange bushing during any inspection required by this AD, and the
service bulletin recommends contacting Bombardier for appropriate
action: Before further flight, disposition and replace the cracked
or damaged aileron lug or flange bushing with a new part, in
accordance with a method approved by the Manager, New York Aircraft
Certification Office (ACO), FAA; or Transport Canada Civil Aviation
(TCCA) (or its delegated agent).
Reporting
(h) Submit a report of the findings (both positive and negative)
of the inspections required by paragraph (f) of this AD to
Bombardier Aerospace; Attention: Christian Holzl, dept. 508;
Location S666 1422 024; 13100 Highway 50; Mirabel, Quebec, Canada,
J7M 3C6; fax (450) 476-7321. Submit the report at the applicable
time specified in paragraph (h)(1) or (h)(2) of this AD. The report
must include the airplane serial number, the total accumulated
flight cycles and flight hours on the airplane, the date of the
inspection, the total accumulated flight cycles and flight hours at
the last ``C'' check, the serial number of each PCU, and the results
of all inspections, tests, and measurements done in accordance with
paragraph (f) of this AD. Submitting Appendix A of Bombardier Alert
Service Bulletin A670BA-27-023, including Appendix A, Revision A,
dated May 18, 2005, is an acceptable means of complying with this
requirement. Under the provisions of the Paperwork Reduction Act of
1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget
(OMB) has approved the information collection requirements contained
in this AD and has assigned OMB Control Number 2120-0056.
(1) If the inspection was done after the effective date of this
AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done prior to the effective date of
this AD: Submit the report within 30 days after the effective date
of this AD.
Actions Accomplished Previously
(i) Inspections and corrective actions done, and reports
submitted, before the effective date of this AD in accordance with
Bombardier Alert Service Bulletin A670BA-27-023, including Appendix
A, dated May 3, 2005, are acceptable for compliance with the
corresponding requirements of paragraphs (f) and (h) of this AD.
[[Page 58634]]
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, New York ACO, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(k) Canadian airworthiness directive CF-2005-23, dated June 29,
2005, also addresses the subject of this AD.
Issued in Renton, Washington, on September 30, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-20271 Filed 10-6-05; 8:45 am]
BILLING CODE 4910-13-P
