[Federal Register Volume 65, Number 21 (Tuesday, February 1, 2000)]
[Rules and Regulations]
[Pages 4755-4757]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-1956]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-08-AD; Amendment 39-11525; AD 2000-02-06]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-100, -200, and -
300 Series Airplanes

AGENCY:  Federal Aviation Administration, DOT.

ACTION:  Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY:  This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Bombardier Model DHC-8-100, -200, and -300 
series airplanes. This action requires a one-time visual inspection to 
determine the part numbers of the beta back-up test

[[Page 4756]]

switches of the propeller control system, and replacement of the 
switches, if necessary. This amendment is prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The actions specified in this AD are intended 
to prevent loss of the automatic overspeed protection of the propeller 
control system, which could result in a propeller overspeed condition 
and possible damage to the engine and propeller.

DATES:  Effective February 16, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 16, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before March 2, 2000.

ADDRESSES:  Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-08-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    The service information referenced in this AD 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, Engine and Propeller 
Directorate, 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.

FOR FURTHER INFORMATION CONTACT:  James E. Delisio, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, Engine and Propeller 
Directorate, New York Aircraft Certification Office, 10 Fifth Street, 
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7521; 
fax (516) 568-2716.

SUPPLEMENTARY INFORMATION:  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. TCCA advises that a certain beta back-
up test switch is incorrectly identified as an allowable replacement in 
the wiring diagram manuals. This incorrect switch is used elsewhere on 
the aircraft and is physically interchangeable with the correct switch. 
However, the internal contacts of the incorrect switch are different. 
This difference prevents the beta back-up system of the propeller 
control system from functioning correctly if a mechanical failure of 
the propeller control system occurs. In the event of such an 
occurrence, the automatic overspeed protection could be lost. This 
condition, if not corrected, could result in a propeller overspeed 
condition and possible damage to the engine and propeller.

Explanation of Relevant Service Information

    The manufacturer has issued de Havilland Alert Service Bulletin 
S.B. A8-61-30, Revision `B,' dated December 6, 1999, which describes 
procedures for a one-time visual inspection to determine the part 
numbers of the beta back-up test switches of the propeller control 
system, and replacement of the switches with new switches, if 
necessary. Accomplishment of the actions specified in the alert service 
bulletin is intended to adequately address the identified unsafe 
condition. TCCA classified this alert service bulletin as mandatory and 
issued Canadian airworthiness directive CF-99-30, dated December 9, 
1999, 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 
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 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 loss of the 
automatic overspeed protection of the propeller control system, which 
could result in a propeller overspeed condition and possible damage to 
the engine and propeller. This AD requires accomplishment of the 
actions specified in the alert 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.
    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 2000-NM-08-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

[[Page 4757]]

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:

2000-02-06  Bombardier, Inc.

    (Formerly de Havilland, Inc.): Amendment 39-11525. Docket 2000-
NM-08-AD.

    Applicability: Model DHC-8-100, -200, and -300 series airplanes; 
serial numbers 003 through 538 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 in accordance with paragraph (b) 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 prevent loss of the automatic overspeed protection of the 
propeller control system, which could result in a propeller 
overspeed condition and possible damage to the engine and propeller, 
accomplish the following:
    (a) Within 50 flight hours after the effective date of this AD, 
perform a one-time visual inspection to determine the part numbers 
of the beta back-up test switches of the propeller control system, 
in accordance with de Havilland Alert Service Bulletin S.B. A8-61-
30, Revision `B,' dated December 6, 1999.
    (1) If all switches have the correct part number (as specified 
by the alert service bulletin), no further action is required by 
this AD.
    (2) If any switch does not have the correct part number (as 
specified by the alert service bulletin), prior to further flight, 
remove and replace the switch with a new switch having part number 
MS27407-6, in accordance with the alert service bulletin.

Alternative Methods of Compliance

    (b) 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, Engine and Propeller Directorate. 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

    (c) 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.

Incorporation by Reference

    (d) The actions shall be done in accordance with de Havilland 
Alert Service
    Bulletin S.B. A8-61-30, Revision `B,' dated December 6, 1999. 
This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Bombardier, Inc., Bombardier 
Regional Aircraft Division, 123 Garratt Boulevard, Downsview, 
Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Engine and Propeller Directorate, 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 3:  The subject of this AD is addressed in Canadian 
airworthiness directive CF-99-30, dated December 9, 1999.

    (e) This amendment becomes effective on February 16, 2000.

    Issued in Renton, Washington, on January 21, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-1956 Filed 1-31-00; 8:45 am]
BILLING CODE 4910-13-U