[Federal Register: March 25, 2004 (Volume 69, Number 58)]
[Rules and Regulations]
[Page 15233-15234]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr25mr04-1]
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Rules and Regulations
Federal Register
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[[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.
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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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