[Federal Register Volume 69, Number 58 (Thursday, March 25, 2004)]
[Rules and Regulations]
[Pages 15233-15234]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-6501]



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 Rules and Regulations
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  Federal Register / Vol. 69, No. 58 / Thursday, March 25, 2004 / Rules 
and Regulations  

[[Page 15233]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-120-AD; Amendment 39-13534; AD 2004-06-08]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-401 and -402 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Bombardier Model DHC-8-401 and -402 airplanes, 
that requires modifying the wiring of the rudder trim switch, 
inspecting all wiring on the back of the aileron/rudder trim control 
panel for chafing, and replacing any chafed wiring with new wiring. 
This action is necessary to prevent a short circuit on the aileron/
rudder trim control panel that could cause a runaway condition of the 
rudder trim actuator, which could result in reduced controllability of 
the airplane. This action is intended to address the identified unsafe 
condition.

DATES: Effective April 29, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 29, 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; at the FAA, New York Aircraft Certification 
Office, 1600 Stewart Avenue, Westbury, New York; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Douglas Wagner, Aerospace Engineer, 
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, 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-8-401 
and -402 airplanes was published in the Federal Register on November 
17, 2003 (68 FR 64825). That action proposed to require modifying the 
wiring of the rudder trim switch, inspecting all wiring on the back of 
the aileron/rudder trim control panel for chafing, and replacing any 
chafed wiring with new wiring.

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 Previous Revisions of Service Information

    While the commenter states that it has no objection to the proposed 
AD, it requests that the proposed AD be revised to give credit for 
actions accomplished previously per the original issue of Bombardier 
Alert Service Bulletin A84-27-13, dated January 2, 2002; or per 
Revision ``A'' of that service bulletin, dated January 9, 2002. 
(Paragraph (a) of the proposed AD refers to Bombardier Alert Service 
Bulletin A84-27-13, Revision ``B,'' dated January 12, 2002, as the 
appropriate source of service information for the actions required by 
that paragraph.) The commenter states that the original issue and 
Revision ``A'' of the service bulletin accomplish the same intent as 
Revision ``B.'' The commenter notes that this change to the proposed AD 
would prevent operators from having to request approval of an 
alternative means of compliance with the proposed AD.
    We partially concur with the commenter's request. We note that 
paragraph (b) of this AD states that actions accomplished before the 
effective date of this AD per Bombardier Alert Service Bulletin A84-27-
13, Revision ``A,'' are acceptable for compliance with paragraph (a) of 
this AD. However, with respect to the commenter's request that we also 
give credit for use of the original issue of the service bulletin, we 
note that the Accomplishment Instructions of the original issue of the 
service bulletin omit several steps, including steps pertaining to 
rework of wiring of spare trim panels and marking the new part number 
on modified trim panels. We find that these missing instructions could 
allow improper modification of the affected panels and improper rework 
of the wiring. Thus, we find that it is not appropriate to give credit 
for actions accomplished per the original issue of the service 
bulletin. We have made no change to the final rule.

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 12 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 1 work hour per 
airplane to accomplish the required actions, and that the average labor 
rate is $65 per work hour. Based on these figures, the cost impact of 
this AD on U.S. operators is estimated to be $780, or $65 per airplane.
    The cost impact figure discussed above is 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.

[[Page 15234]]

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.
    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:

2004-06-08 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 
39-13534. Docket 2002-NM-120-AD.

    Applicability: Model DHC-8-401 and -402 airplanes; certificated 
in any category; serial numbers 4005, 4006, 4008 through 4016 
inclusive, and 4018 through 4058 inclusive.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent a short circuit on the aileron/rudder trim control 
panel that could cause a runaway condition of the rudder trim 
actuator, which could result in reduced controllability of the 
airplane, accomplish the following:

Modification, Inspection, and Corrective Action

    (a) Within 90 days after the effective date of this AD, do the 
actions in paragraphs (a)(1) and (a)(2) of this AD, per the 
Accomplishment Instructions of Bombardier Alert Service Bulletin 
A84-27-13, Revision ``B,'' dated January 12, 2002.
    (1) Modify the wiring of the rudder trim switch.
    (2) Before further flight after accomplishing the modification 
required by paragraph (a)(1) of this AD: Perform a one-time general 
visual inspection of all wiring on the back of the aileron/rudder 
trim control panel for chafing. Before further flight, replace any 
chafed wiring with new wiring.

    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.''

Previously Accomplished Actions

    (b) Modifications and inspections accomplished before the 
effective date of this AD per Bombardier Alert Service Bulletin A84-
27-13, Revision ``A,'' dated January 9, 2002, are acceptable for 
compliance with the corresponding actions required by paragraph (a) 
of this AD.

Parts Installation

    (c) As of the effective date of this AD, no person may install 
aileron/rudder trim control panel having part number 82410608-005 on 
any airplane, unless the control panel has been modified and 
inspected per the requirements of this AD.

Alternative Methods of Compliance

    (d) 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

    (e) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Bombardier Alert Service Bulletin A84-27-13, 
Revision ``B,'' dated January 12, 2002. 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; at the FAA, New York 
Aircraft Certification Office, 1600 Stewart Avenue, Westbury, New 
York; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.

    Note 2: The subject of this AD is addressed in Canadian 
airworthiness directive CF-2002-15, dated February 20, 2002.

Effective Date

    (f) This amendment becomes effective on April 29, 2004.

    Issued in Renton, Washington, on March 12, 2004.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-6501 Filed 3-24-04; 8:45 am]
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