[Federal Register Volume 70, Number 219 (Tuesday, November 15, 2005)]
[Proposed Rules]
[Pages 69291-69293]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-22590]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22873; Directorate Identifier 2005-NM-197-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 440) 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-600-2B19 (Regional Jet Series 100 & 
440) airplanes. This proposed AD would require replacing the Camloc 
fasteners on the sidewall of the center pedestal. This proposed 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 proposing this AD to prevent these fasteners from 
disengaging and interfering with an inboard rudder pedal, which could 
reduce directional controllability of the airplane.

DATES: We must receive comments on this proposed AD by December 15, 
2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://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-
22873; Directorate Identifier 2005-NM-197-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 http://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

[[Page 69292]]

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 
http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://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-600-2B19 (Regional Jet Series 100 & 440) 
airplanes. TCCA advises that it has received several reports of the 
Camloc fasteners on the sidewall of the center pedestal fully 
disengaging and interfering with an inboard rudder pedal. In one 
incident, the rudder jammed during an approach due to a disengaged 
Camloc fastener that restricted movement of the pilot's inboard rudder 
pedal and tow brake. This condition, if not corrected, could reduce 
directional controllability of the airplane.

Relevant Service Information

    Bombardier has issued Service Bulletin 601R-31-030, Revision F, 
dated September 1, 2005. The service bulletin describes procedures for 
replacing, with screws and nut plate assemblies, the Camloc fasteners 
on the left and right sidewalls of the center pedestal. Accomplishing 
the actions specified in the service information is intended to 
adequately address the unsafe condition. TCCA mandated the service 
information and issued Canadian airworthiness directive CF-2004-23R1, 
dated July 18, 2005, to ensure the continued airworthiness of these 
airplanes in Canada.

FAA's Determination and Requirements of the Proposed AD

    This airplane model is manufactured in Canada 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, 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.

Costs of Compliance

    This proposed AD would affect about 718 airplanes of U.S. registry. 
The proposed actions would take about 1 work hour per airplane, at an 
average labor rate of $65 per work hour. Required parts would cost 
about $135 per airplane. Based on these figures, the estimated cost of 
the proposed AD for U.S. operators is $143,600, or $200 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 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-2005-22873; 
Directorate Identifier 2005-NM-197-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by December 
15, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 440) airplanes, certificated in any category, 
serial numbers 7003 through 7986 inclusive.

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

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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 601R-31-030, Revision F, dated September 1, 2005.

Actions Accomplished Previously

    (g) Replacing fasteners before the effective date of this AD in 
accordance with the Accomplishment Instructions of one of the issues 
of Bombardier Service Bulletin 601R-31-030 identified in Table 1 of 
this AD is acceptable for compliance with the requirements of 
paragraph (f) of this AD.

 Table 1.--Previous Service Bulletin Revisions Acceptable for Compliance
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 Issue of Bombardier service bulletin
              601R-31-030                             Date
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Original..............................  June 22, 2004.
Revision A............................  Oct. 6, 2004.
Revision B............................  Nov. 4, 2004.
Revision C............................  Dec. 15, 2004.
Revision D............................  June 16, 2005.
Revision E............................  July 7, 2005.
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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-2004-23R1, dated July 
18, 2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on November 4, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-22590 Filed 11-14-05; 8:45 am]
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