[Federal Register Volume 69, Number 48 (Thursday, March 11, 2004)]
[Proposed Rules]
[Pages 11554-11556]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-5520]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-163-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 440) Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Bombardier Model CL-600-
2B19 (Regional Jet Series 100 & 440) airplanes. This proposal would 
require performing an inspection of the electrical harnesses of the 
spoiler and the brake pressure sensor unit on both sides of the wing 
root to detect any chafing or wire damage, and repairing or replacing 
any damaged or chafed harness or wire with a new harness, as 
applicable. This action is necessary to detect and correct chafing of 
the electrical cables of the spoiler and brake pressure sensor unit on 
both sides of the wing root, which could result in loss of flight 
control system and consequent reduced controllability of the airplane. 
This action is intended to address the identified unsafe condition.

DATES: Comments must be received by April 12, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-163-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2003-NM-163-AD'' in the subject line and need not 
be submitted

[[Page 11555]]

in triplicate. Comments sent via the Internet as attached electronic 
files must be formatted in Microsoft Word 97 or 2000 or ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 
6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada. This 
information may be examined at the FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York 
Aircraft Certification Office, 1600 Stewart Avenue, suite 410, 
Westbury, New York.

FOR FURTHER INFORMATION CONTACT: Wing Chan, 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) 228-7311; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:

     Organize comments issue-by-issue. For example, 
discuss a request to change the compliance time and a request to change 
the service bulletin reference as two separate issues.
     For each issue, state what specific change to 
the proposed AD is being requested.
     Include justification (e.g., reasons or data) 
for each request.

    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2003-NM-163-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2003-NM-163-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    Transport Canada Civil Aviation (TCCA), which is the airworthiness 
authority for Canada, notified the FAA 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 three reports of 
chafing of the electrical cables of the spoiler and brake pressure 
sensor unit (BPSU) on both sides of the wing root. The chafing 
condition occurred where electrical cables (harnesses) are routed 
through two misaligned adjacent lightening holes in the wing box of 
both wings at station 545. The condition can exist due to tight routing 
of the harness in this location and movement of the harnesses due to 
wing flex and vibration. These conditions, if not corrected, could 
result in loss of flight control system and consequent reduced 
controllability of the airplane.

Explanation of Relevant Service Information

    Bombardier has issued Alert Service Bulletin A601R-27-101, Revision 
`A', dated October 26, 2001. The service bulletin describes, among 
other actions, procedures for performing a general visual inspection of 
the electrical harnesses of the spoiler and the BPSU on both sides of 
the wing root to detect any chafing or wire damage, and repairing or 
replacing any damaged or chafed harness or wire with a new harness, as 
applicable. TCCA classified this service bulletin as mandatory and 
issued Canadian airworthiness directive CF-2003-14, dated May 15, 2003, 
to ensure the continued airworthiness of these airplanes in Canada.

FAA's Conclusions

    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. The FAA has examined the findings of 
TCCA, reviewed all available information, and determined that AD action 
is necessary for products of this type design that are certificated for 
operation in the United States.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would require accomplishment of 
the actions specified in the service bulletin described previously, 
except as discussed below.

Difference Between Proposed AD and Referenced Service Bulletin

    Operators should note that, although the Accomplishment 
Instructions of the referenced service bulletin describe procedures for 
completing and submitting to the manufacturer a comment sheet related 
to service bulletin quality and a sheet recording compliance with the 
service bulletin, this proposed AD would not require those actions. The 
FAA does not need this information from operators.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

Cost Impact

    The FAA estimates that 191 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 1 work 
hour per airplane to accomplish the proposed inspection, and that the 
average labor rate is $65 per work hour. Based on these figures, the 
cost impact of the proposed AD on U.S. operators is estimated to be 
$12,415, or $65 per airplane, per inspection cycle.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the proposed requirements of 
this AD action, and that no operator would accomplish those actions in 
the future if this AD were not adopted. The cost impact figures 
discussed in AD rulemaking actions represent only the time necessary to 
perform the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

[[Page 11556]]

Regulatory Impact

    The regulations proposed herein 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. Therefore, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this 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) if promulgated, 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. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new 
airworthiness directive:

Bombardier, Inc. (Formerly Canadair): Docket 2003-NM-163-AD.

    Applicability: Model CL-600-2B19 (Regional Jet Series 100 & 440) 
airplanes, serial numbers 7003 through 7067 inclusive, and 7069 
through 7351 inclusive, certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct chafing of the electrical cables of the 
spoiler and brake pressure sensor unit (BPSU) on both sides of the 
wing root, which could result in loss of flight control system and 
consequent reduced controllability of the airplane, accomplish the 
following:

Initial and Repetitive Inspections

    (a) Within 500 flight hours after the effective date of this AD, 
do a general visual inspection of the electrical harnesses of the 
spoiler and the BPSU on both sides of the wing root to detect any 
chafing or wire damage, in accordance with Part A of the 
Accomplishment Instructions of Bombardier Alert Service Bulletin 
A601R-27-101, Revision `A', dated October 26, 2001. Repeat the 
inspection thereafter at intervals not to exceed 4,000 flight hours.

    Note 1: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

Corrective Actions

    (b) If any damaged or chafed electrical harness or wire is found 
during any inspection required by paragraph (a) of this AD, before 
further flight, do either paragraph (b)(1) or (b)(2) of this AD.
    (1) Replace any damaged or chafed harness or wire with a new 
harness, in accordance with Part C or Part D of the Accomplishment 
Instructions of Bombardier Alert Service Bulletin A601R-27-101, 
Revision `A', dated October 26, 2001, as applicable.
    (2) Repair any damaged or chafed electrical harness in 
accordance with Part B of the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A601R-27-101, Revision `A', dated 
October 26, 2001. Within 4,000 flight hours after the repair is 
done, do paragraph (b)(1) of this AD.

Credit for Earlier Service Bulletin

    (c) Replacements and repairs accomplished before the effective 
date of this AD in accordance with Bombardier Alert Service Bulletin 
A601R-27-101, Initial Issue, dated April 17, 2000, are acceptable 
for compliance with the requirements of paragraph (b) of this AD.

Exception to Service Bulletin

    (d) Although the service bulletin referenced in this AD 
specifies to submit certain information to the manufacturer, this AD 
does not include such a requirement.

Alternative Methods of Compliance

    (e) In accordance with 14 CFR 39.19, the Manager, New York 
Aircraft Certification Office, FAA, is authorized to approve 
alternative methods of compliance for this AD.

    Note 2: The subject of this AD is addressed in Canadian 
airworthiness directive CF-2003-14, dated May 15, 2003.


    Issued in Renton, Washington, on March 2, 2004.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-5520 Filed 3-10-04; 8:45 am]
BILLING CODE 4910-13-P