[Federal Register Volume 63, Number 183 (Tuesday, September 22, 1998)]
[Rules and Regulations]
[Pages 50501-50503]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-25119]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-172-AD; Amendment 39-10781; AD 98-20-14]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106,
-201, -202, -301, -311, and -315 Series 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, -103, -106, -201, -
202, -301, -311, and -315 series airplanes, that requires a one-time
inspection to detect chafing of electrical wires in the cable trough
below the cabin floor; repair, if necessary; installation of additional
tie-mounts and tie-wraps; and application of sealant to rivet heads.
This amendment is prompted by issuance of mandatory continuing
airworthiness information by a foreign civil airworthiness authority.
The actions specified by this AD are intended to prevent chafing of
electrical wires, which could result in an uncommanded shutdown of an
engine during flight.
DATES: Effective October 27, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 27, 1998.
ADDRESSES: The service information referenced in this AD may be
obtained from Bombardier, Inc., Bombardier Regional Aircraft Division,
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, 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: Peter Cuneo, Senior Aerospace
Engineer, Systems and Flight Test Branch, ANE-172, FAA, Engine and
Propeller Directorate, New York Aircraft Certification Office, 10 Fifth
Street, Third Floor, Valley Stream, New York
[[Page 50502]]
11581; telephone (516) 256-7506; fax (516) 568-2716.
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, -103, -106, -201, -202, -301, -311, and -315 series airplanes was
published in the Federal Register on July 31, 1998 (63 FR 40852). That
action proposed to require a one-time inspection to detect chafing of
electrical wires in the cable trough below the cabin floor; repair, if
necessary; installation of additional tie-mounts and tie-wraps; and
application of sealant to rivet heads.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Explanation of Change Made to This Final Rule
The FAA has revised the final rule to reflect a change of the
manufacturer's name from de Havilland to Bombardier.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule with the change previously described.
The FAA has determined that this change will neither increase the
economic burden on any operator nor increase the scope of this AD.
Cost Impact
The FAA estimates that 225 airplanes of U.S. registry will be
affected by this AD.
For the 210 Model DHC-8-102, -103, -106, -201, and -202 series
airplanes affected, it will take approximately 70 work hours per
airplane to accomplish the required actions, at an average labor rate
of $60 per work hour. Required parts will be provided by the
manufacturer at no cost to the operators. Based on these figures, the
cost impact of the required AD for these airplanes on U.S. operators is
estimated to be $882,000, or $4,200 per airplane.
For the 15 Model DHC-8-301, -311, and -315 series airplanes
affected, it will take approximately 100 work hours per airplane to
accomplish the required actions, at an average labor rate of $60 per
work hour. Required parts will be provided by the manufacturer at no
cost to the operators. Based on these figures, the cost impact of the
required AD for these airplanes on U.S. operators is estimated to be
$90,000, or $6,000 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.
Regulatory Impact
The regulations adopted herein will not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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
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:
98-20-14 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-10781. Docket 98-NM-172-AD.
Applicability: Model DHC-8-102, -103, -106, -201, -202, -301, -
311, and -315 series airplanes; serial numbers 3 through 519
inclusive, excluding serial number 462; 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 chafing of electrical wires, which could result in an
uncommanded shutdown of an engine during flight, accomplish the
following:
(a) Within 36 months after the effective date of this AD,
perform a one-time visual inspection to detect chafing of electrical
wires in the cable trough below the cabin floor; install additional
tie-mounts and tie-wraps; and apply sealant to rivet heads
(reference Bombardier Modification 8/2705); in accordance with
Bombardier Service Bulletin S.B. 8-53-66, dated March 27, 1998. If
any chafing is detected during the inspection required by this
paragraph, prior to further flight, repair in accordance with the
service bulletin.
(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.
(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.
(d) The actions shall be done in accordance with Bombardier
Service Bulletin S.B. 8-53-66, dated March 27, 1998. 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, 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.
[[Page 50503]]
Note 3: The subject of this AD is addressed in Canadian
airworthiness directive CF-98-08, dated March 26, 1998.
(e) This amendment becomes effective on October 27, 1998.
Issued in Renton, Washington, on September 14, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-25119 Filed 9-21-98; 8:45 am]
BILLING CODE 4910-13-U
