[Federal Register Volume 69, Number 183 (Wednesday, September 22, 2004)]
[Rules and Regulations]
[Pages 56682-56683]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-21174]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-185-AD; Amendment 39-13801; AD 2004-19-07]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-102 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Bombardier Model DHC-8-102 airplanes, that 
requires modification of the electrical power circuit. This action is 
necessary to prevent component failure in the radar indicator, 
resulting in an overcurrent condition and consequent overheating or 
burning of an internal component or the ribbon cable. This could lead 
to smoke in the cockpit, resulting in incapacitation of the flight crew 
and loss of control of the airplane. This action is intended to address 
the identified unsafe condition.

DATES: Effective October 27, 2004.
    The incorporation by reference of a certain publication listed in 
the regulations is approved by the Director of the Federal Register as 
of October 27, 2004.

ADDRESSES: 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 Federal Aviation Administration 
(FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, 
SW., Renton, Washington; or at the FAA, New York Aircraft Certification 
Office (ACO), 1600 Stewart Ave., suite 410, Westbury, New York; or at 
the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, call (202) 
741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Doug Wagner, Aerospace Engineer, 
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft 
Certification Office, 1600 Stewart Ave., suite 410, Westbury, New York 
11590; telephone (516) 228-7306; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Bombardier Model DHC-8-102 
airplanes was published in the Federal Register on April 7, 2004 (69 FR 
18306). That action proposed to require modification of the electrical 
power circuit.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.

Request To Give Credit for Modification Using Alternate Service 
Information

    The commenter, an operator, requests that a paragraph be added to 
the proposed AD giving credit for reconfiguring the circuit breaker 
wiring as specified in Allied Signal RDS-86 Weather Radar System Manual 
006-05996-0005, Revision 5 or higher. The commenter states that it has 
operated the affected Model DHC-8-102 airplanes continually since 1986, 
and that the performance of the RDS-86 weather radar system made 
consultation with the airplane and equipment manufacturers necessary. 
In 1996, the commenter reconfigured certain circuit breakers for the 
weather radar system per the equipment manufacturer's recommendations. 
The commenter notes that the airplane manufacturer did not provide 
documentation for this change until 2002, when it issued Bombardier 
Modification Summary Package (ModSum) IS8Q3450000, Revision A, dated 
October 15, 2002, which the proposed AD references as the appropriate 
source of service information for the proposed requirements.
    The FAA does not agree. It is important to maintain proper 
configuration of airplane wiring to ensure proper airplane maintenance 
by operators. The final rule requires modification of the power circuit 
per ModSum IS8Q3450000, Revision A. The ModSum identifies three 
installation configurations, and the ModSum installation instructions 
identify the correct interface buses to be modified and wires to be 
reconfigured. The Allied Signal RDS-86 Weather Radar System Manual 
shows only pin connections of the indicator and receiver/transmitter 
without any details of unique airplane interconnections. Such limited 
information provides no means of showing that appropriate wiring 
changes have been made and is insufficient to demonstrate that the 
unsafe condition has been addressed properly. We have not changed the 
final rule in this regard. However, under the provisions of paragraph 
(b) of the final rule, we may consider requests for approval of an 
alternative method of compliance if sufficient data are submitted to 
substantiate that such a design change would provide an acceptable 
level of safety.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    The FAA estimates that 48 airplanes of U.S. registry will be 
affected by this AD, that it will take between 3 work hours and 9 work 
hours per airplane to accomplish the required actions, and that the 
average labor rate is $65 per work hour. Required parts will cost 
approximately $150 per airplane. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be between $16,560 
and $35,280, or between $345 and $735 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the 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.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect on the States, on the relationship between

[[Page 56683]]

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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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

0
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

0
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]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2004-19-07 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 
39-13801. Docket 2003-NM-185-AD.

    Applicability: Model DHC-8-102 airplanes, serial numbers 023 
through 392 inclusive; certificated in any category; equipped with 
an RDS86 Weather Radar System, excluding those airplanes equipped 
with option CR834CH00284.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent component failure in the radar indicator, resulting 
in an overcurrent condition and consequent overheating or burning of 
an internal component or the ribbon cable, which could lead to smoke 
in the cockpit, resulting in incapacitation of the crew and loss of 
control of the airplane; accomplish the following:

Modification

    (a) Within 12 months after the effective date of this AD, modify 
the electrical power circuit by accomplishing all the actions in the 
Accomplishment Instructions of Bombardier Modification Summary 
Package (ModSum) IS8Q3450000, Revision A, dated October 15, 2002; as 
applicable. Do the actions per the ModSum.

Alternative Methods of Compliance

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

Incorporation by Reference

    (c) The actions shall be done in accordance with Bombardier 
Modification Summary Package IS8Q3450000, Revision A, dated October 
15, 2002. (The date of the Modification Summary Package only appears 
on the first page of the document.) 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, New York Aircraft 
Certification Office (ACO), 1600 Stewart Ave., suite 410, Westbury, 
New York; or at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Note 1: The subject of this AD is addressed in Canadian 
airworthiness directive CF-2003-13, effective June 20, 2003.

Effective Date

    (d) This amendment becomes effective on October 27 2004.

    Issued in Renton, Washington, on September 14, 2004.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-21174 Filed 9-21-04; 8:45 am]
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