[Federal Register Volume 66, Number 168 (Wednesday, August 29, 2001)]
[Proposed Rules]
[Pages 45653-45655]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-21752]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-112-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-100, -200, and -
300 Series 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 DHC-8-
100, -200, and -300 series airplanes. This proposal would require 
repetitive inspections of the rudder pedal adjustment fittings for 
cracks and replacement of cracked fittings with new fittings. The 
proposal would also provide an optional terminating action. This action 
is necessary to detect and correct cracking of the rudder pedal 
adjustment fittings, which could lead to deformation of the fittings, 
resulting in jammed rudder pedals and loss of rudder control, with 
consequent reduced controllability of the airplane. This action is 
intended to address the identified unsafe condition.

DATES: Comments must be received by September 28, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket Number 2001-NM-112-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. 2001-NM-112-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Bombardier, Inc., Bombardier Regional Aircraft Division, 
123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, 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: Dan Parrillo, Aerospace Engineer, ANE-
172, FAA, New York Aircraft Certification Office, 10 Fifth Street, 
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7505; 
fax (516) 568-2716.

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 2001-NM-112-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

[[Page 45654]]

Number 2001-NM-112-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 DHC-8 -100, -200, and -300 series 
airplanes. The TCCA advises that three incidents have been reported of 
stiff rudder pedal operation. These incidents were due to cracking of 
the rudder pedal adjustment fittings. If not corrected, cracking of the 
rudder pedal adjustment fittings can lead to deformation of the 
fittings, resulting in jammed rudder pedals and loss of rudder control, 
with consequent reduced controllability of the airplane.

Explanation of Relevant Service Information

    Bombardier, Inc., has issued Alert Service Bulletin A8-27-91, dated 
September 12, 2000, and Revision A, dated November 23, 2000, which 
describe procedures for a detailed visual inspection of the rudder 
pedal adjustment fittings for cracks and replacement of cracked 
fittings with new aluminum or steel fittings. New aluminum fittings 
would need to be inspected within 5,000 flight hours after installation 
and thereafter at intervals not to exceed 1,000 flight hours. 
Replacement with steel fittings would constitute terminating action for 
the purposes of this AD. 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-2001-04, dated January 25, 2001, in 
order to assure the continued airworthiness of these airplanes in 
Canada. That airworthiness directive specifies that, if there is any 
instance of stiff operation or jamming of the rudder pedals during 
flight, the rudder pedal adjustment fittings must be inspected in 
accordance with the Bombardier service bulletin prior to further 
flight.

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, the 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 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.

Cost Impact

    The FAA estimates that 188 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 $60 per work hour. Based on these figures, the 
cost impact of the proposed AD on U.S. operators is estimated to be 
$11,280, or $60 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 proposed 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.

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 de Havilland, Inc.) Docket 2001-NM-112-
AD.
    Applicability: Model DHC-8-100, -200, and -300 series airplanes, 
serial numbers 003 to 563 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 
otherwise 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 in accordance with paragraph (e) 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 accomplished 
previously.
    To detect and correct cracking of the rudder pedal adjustment 
fittings, which could lead to deformation of the fittings, resulting 
in jammed rudder pedals and loss of rudder control, with consequent 
reduced controllability of the airplane, accomplish the following:
    Inspection
    (a) Inspect the rudder pedal adjustment fittings having part 
number (P/N) 82710038-101 for cracks, in accordance with Bombardier 
Service Bulletin A8-27-91, dated September 12, 2000, or Revision A, 
dated November 23, 2000, at the times specified in paragraphs (a)(1) 
and (a)(2) of this AD.
    (1) Within 5,000 flight hours since the date of manufacture of 
the airplane or 500 flight hours after the effective date of this 
AD, whichever occurs later, and

[[Page 45655]]

    (2) Prior to further flight, whenever an instance of stiff 
operation or jamming of the rudder pedals occurs during flight.
    (b) If no cracks are detected: Repeat the inspection of the 
rudder pedal adjustment fittings having P/N 82710038-101, in 
accordance with Bombardier Service Bulletin A8-27-91, dated 
September 12, 2000, or Revision A, dated November 23, 2000, at 
intervals not to exceed 1,000 flight hours, until accomplishment of 
paragraph (d) of this AD.
    (c) If cracks are detected: Prior to further flight, replace the 
rudder pedal adjustment fittings having P/N 82710038-101 with new 
aluminum fittings having the same P/N (82710038-101), or with steel 
fittings having P/N 82710080-101, in accordance with Bombardier 
Service Bulletin A8-27-91, dated September 12, 2000, or Revision A, 
dated November 23, 2000.

Terminating Action

    (d) Replacement of the rudder pedal adjustment fittings having 
P/N 82710038-101, with steel rudder pedal adjustment fittings having 
P/N 82710080-101, constitutes terminating action for the repetitive 
inspections required by paragraphs (a) and (b) of this AD.

Alternative Methods of Compliance

    (e) 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, 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 2: 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

    (f) Special flight permits may be issued in accordance with 
sections 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.

    Note 3: The subject of this AD is addressed in Canadian 
airworthiness directive CF-2001-04, dated January 25, 2001.


    Issued in Renton, Washington, on August 22, 2001.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-21752 Filed 8-28-01; 8:45 am]
BILLING CODE 4910-13-U