[Federal Register Volume 66, Number 57 (Friday, March 23, 2001)]
[Rules and Regulations]
[Pages 16114-16116]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-6788]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-32-AD; Amendment 39-12154; AD 2001-06-07]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B19 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Bombardier Model CL-600-2B19 series airplanes. 
This action requires a one-time inspection to find chafing or damage of 
the integrated drive generator cables of the cable harness assembly of 
the engines, and follow-on actions. This action is necessary to prevent 
such chafing or damage, which could result in electrical arcing between 
the cable and an engine cowl door, creating a possible ignition source 
and consequent fire and/or loss of electrical power on the airplane. 
This action is intended to address the identified unsafe condition.

DATES: Effective April 9, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 9, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before April 23, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-32-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 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 the Internet must contain 
``Docket No. 2001-NM-32-AD'' in the subject line and need not be 
submitted in triplicate. Comments sent via fax or the Internet as 
attached electronic files must be formatted in Microsoft Word 97 for 
Windows or ASCII text.
    The service information referenced in this AD 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, 10 Fifth Street, Third Floor, Valley Stream, New York.

FOR FURTHER INFORMATION CONTACT: Luciano Castracane, Aerospace 
Engineer, ANE-172, FAA, New York Aircraft Certification Office, 10 
Fifth Street, Third Floor, Valley Stream, New York 11581; telephone 
(516) 256-7535; fax (516) 568-2716.

SUPPLEMENTARY INFORMATION: Transport Canada Civil Aviation (TCCA), 
which is the airworthiness authority for Canada, recently notified the 
FAA that an unsafe condition may exist on certain Bombardier Model CL-
600-2B19 series airplanes. TCCA advises that electrical arcing between 
the integrated drive generator (IDG) cable and an engine cowl door has 
been reported. Such arcing has been attributed to chafing of the IDG 
cable against the structure and engine cowl doors, due to wear. This 
condition, if not corrected, could result in a possible ignition source 
and consequent fire and/or loss of electrical power on the airplane.

Explanation of Relevant Service Information

    The manufacturer has issued Bombardier Alert Service Bulletin 
A601R-24-103, Revision B, dated January 26, 2001, which describes 
procedures for the following:
     Part A of the Accomplishment Instructions: A visual 
inspection to find chafing or damage of the IDG cables between the 
service pylon connections to the cable harness assembly of the left and 
right engines, and follow-on actions (below).
     Part B of the Accomplishment Instructions: Installation of 
a protective conduit on the IDG cable harness assembly if there is no 
damage found or if there is damage to the outer core of the cable only.
     Part C of the Accomplishment Instructions: Replacement of 
damaged (inner core damage, or damaged/broken conductor strands) IDG 
cables with new cables.

[[Page 16115]]

    Accomplishment of the actions specified in the service bulletin is 
intended to adequately address the identified unsafe condition. The 
TCCA classified this service bulletin as mandatory and issued Canadian 
airworthiness directive CF-2001-02, dated January 17, 2001, in order to 
assure 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 
Sec. 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 the 
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 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, this AD is being issued to prevent chafing or 
damage of the IDG cables, which could result in electrical arcing 
between the cable and an engine cowl door, creating a possible ignition 
source and consequent fire and/or loss of electrical power on the 
airplane. This AD requires a one-time general visual inspection to find 
chafing or damage of the IDG cables between the service pylon 
connections to the cable harness assembly of the engines, and follow-on 
actions. The actions are required to be accomplished per the service 
bulletin described previously.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    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 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 rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-32-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 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:

2001-06-07  Bombardier, Inc. (Formerly Canadair): Amendment 39-
12154. Docket 2001-NM-32-AD.

    Applicability: Model CL-600-2B19 series airplanes, serial 
numbers 7003 through 7462 inclusive; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance per paragraph (d) of this AD. The 
request should include an assessment of the effect of the 
modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless done previously.
    To prevent chafing or damage of the integrated drive generator 
(IDG) cables of the cable harness assembly of the engines, which 
could result in electrical arcing between the cable and an engine 
cowl door, creating a possible ignition source and consequent fire 
and/or loss of electrical power on the airplane; do the following:

Inspection/Repair/Replacement

    (a) Within 50 flight hours after the effective date of this AD: 
Do a one-time general visual

[[Page 16116]]

inspection of the IDG cables between the service pylon connections 
to the cable harness assembly of the left and right engines to find 
chafing or damage, per Part A of the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A601R-24-103, Revision B, dated 
January 26, 2001.

    Note 2: 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 under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, 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.''

    (1) If no chafing or damage to any cable is found, do the 
installation required by paragraph (b) of this AD at the time 
specified.
    (2) If chafing or damage is found on the outer core of any 
cable, and the inner core of the cable is not damaged, before 
further flight, repair per Part A, or replace per Part C of the 
Accomplishment Instructions of the service bulletin.
    (3) If any damaged cable (inner core damage, or damaged/broken 
conductor strands) is found, before further flight, replace with a 
new cable per part C of the Accomplishment Instructions of the 
service bulletin.

Installation of Protective Conduit

    (b) If no chafing or damage of any IDG cable is found, or there 
is outer core damage to the cable only, within 550 flight hours 
after doing paragraph (a) of this AD: Install a protective conduit 
on the IDG cable harness assembly per Part B of the Accomplishment 
Instructions of Bombardier Alert Service Bulletin A601R-24-103, 
Revision B, dated January 26, 2001.

    Note 3: Inspections, repairs, or replacements done before the 
effective date of this AD per Bombardier Alert Service Bulletin 
A601R-24-103, dated December 28, 2000, or Revision A, dated January 
18, 2001; are considered acceptable for compliance with the 
applicable actions specified in this AD.

Reporting Requirement

    (c) Within 30 days after doing the inspection required by 
paragraph (a) of this AD: Submit a report of any findings of chafing 
or damage to Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 
6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada. 
Information collection requirements contained in this regulation 
have been approved by the Office of Management and Budget (OMB) 
under the provisions of the Paperwork Reduction Act of 1980 (44 
U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-
0056.

Alternative Methods of Compliance

    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, New York Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, New York ACO.


    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the New York ACO.

Special Flight Permits

    (e) Special flight permits may be issued per Secs. 21.197 and 
21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 
21.199) to operate the airplane to a location where the requirements 
of this AD can be accomplished.

Incorporation by Reference

    (f) The actions shall be done per Bombardier Alert Service 
Bulletin A601R-24-103, Revision B, dated January 26, 2001. This 
incorporation by reference was approved by the Director of the 
Federal Register per 5 U.S.C. 552(a) and 1 CFR part 51. Copies may 
be obtained from Bombardier, Inc., Canadair, Aerospace Group, P.O. 
Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada. 
Copies may be inspected at the FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York 
Aircraft Certification Office, 10 Fifth Street, Third Floor, Valley 
Stream, New York; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.


    Note 5: The subject of this AD is addressed in Canadian 
airworthiness directive CF-2001-02, dated January 17, 2001.

Effective Date

    (g) This amendment becomes effective on April 9, 2001.

    Issued in Renton, Washington, on March 13, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-6788 Filed 3-22-01; 8:45 am]
BILLING CODE 4910-13-U