[Federal Register Volume 65, Number 8 (Wednesday, January 12, 2000)]
[Proposed Rules]
[Pages 1836-1838]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-599]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-372-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon (Beech) Model 400A and 400T
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Raytheon (Beech) Model
400A and 400T series airplanes. This proposal would require replacement
of temperature switch assemblies of the wing ice protection system with
new, improved parts. This proposal is prompted by reports of electrical
continuity problems with solder joints on the temperature switches of
the wing ice protection system. The actions specified by the proposed
AD are intended to prevent detachment or breakage of wires in the
temperature switch assemblies of the wing ice protection system. Such
detachment or breakage of wires could result in the flightcrew not
being advised of an over-temperature situation on the leading edge of
the wing, which could result in structural damage to the wing.
DATES: Comments must be received by February 28, 2000.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-372-AD, 1601 Lind Avenue, SW.,
[[Page 1837]]
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Raytheon Aircraft Company, Manager Service Engineering,
Beechjet/Premier Technical Support Department, P.O. Box 85, Wichita,
Kansas 67201-0085. This information may be examined at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the FAA, Small Airplane Directorate, Wichita Aircraft
Certification Office, 1801 Airport Road, Room 100, Mid-Continent
Airport, Wichita, Kansas.
FOR FURTHER INFORMATION CONTACT: Philip Petty, Aerospace Engineer,
Systems and Propulsion Branch, ACE-116W, FAA, Small Airplane
Directorate, Wichita Aircraft Certification Office, 1801 Airport Road,
Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316)
946-4139; fax (316) 946-4407.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 99-NM-372-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 99-NM-372-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received a report indicating that a technician on the
production line for Raytheon (Beech) Model 400A and 400T series
airplanes found electrical continuity problems with solder joints on
temperature switches of the wing ice protection system. Those
electrical continuity problems have been attributed to the use of
solder that melts at a temperature at or below that encountered during
normal operating conditions in the area of the wing where the
temperature switches are installed. Subsequent to the discovery of the
electrical continuity problem, the manufacturer implemented a
production change to correct the problem. However, broken wire strands
at the connection of the lead wire to the temperature switch terminals
were found on temperature switch assemblies incorporating the
production change. Either condition (i.e., detachment or breakage of
wires in the temperature switch assemblies of the wing ice protection
system), if not corrected, could result in the flightcrew not being
advised of an over-temperature condition on the leading edge of the
wing, which could result in structural damage to the wing.
Explanation of Relevant Service Information
The FAA has reviewed and approved Raytheon Service Bulletin 30-
3008, Revision 1, dated August 1999, which describes procedures for
replacement of temperature switch assemblies of the wing ice protection
system with new, improved assemblies. The new assemblies use high
temperature wire and incorporate improved connection of the lead wires
to the temperature switch terminals. Accomplishment of the action
specified in the service bulletin is intended to adequately address the
identified unsafe condition.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would require accomplishment of the actions specified in
the service bulletin described previously.
Cost Impact
There are approximately 404 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 366 airplanes of U.S. registry
would be affected by this proposed AD, that it would take approximately
30 work hours per airplane to accomplish the proposed replacement, and
that the average labor rate is $60 per work hour. Required parts would
be provided by the manufacturer at no cost to the operators. Based on
these figures, the cost impact of the proposed AD on U.S. operators is
estimated to be $658,800, or $1,800 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed 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 proposed herein would 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 proposal would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (14 CFR part 39) as
follows:
[[Page 1838]]
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:
Raytheon Aircraft Company (Formerly Beech): Docket 99-NM-372-AD.
Applicability: Model 400A series airplanes, having serial
numbers RK-01 through RK-188 inclusive; Model 400T (T-1A) series
airplanes, having serial numbers TT-01 through TT-180 inclusive; and
Model 400T (TX) series airplanes, having serial numbers TX-01
through TX-09 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 (c) 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 detachment or breakage of wires in the temperature
switch assemblies of the wing ice protection system, which could
result in the flightcrew not being advised of an over-temperature
situation on the leading edge of the wing, and consequent structural
damage to the wing, accomplish the following:
Replacement
(a) At the next scheduled inspection, but no later than 200
flight hours after the effective date of this AD, replace
temperature switch assemblies of the wing ice protection system with
new, improved temperature switch assemblies, in accordance with
Raytheon Service Bulletin 30-3008, Revision 1, dated August 1999.
Note 2: Replacements accomplished prior to the effective date of
this AD in accordance with Raytheon Service Bulletin 30-3008, dated
March 1999, are considered acceptable for compliance with the
applicable action specified in this AD.
Spares
(b) As of the effective date of this AD, no person shall
install, on any airplane, a temperature switch assembly having a
part number listed in the ``Old Part Number'' column of the table in
2.D. of Raytheon Service Bulletin 30-3008, Revision 1, dated August
1999.
Alternative Methods of Compliance
(c) 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, Wichita Aircraft Certification Office
(ACO), FAA, Small Airplane Directorate. Operators shall submit their
requests through an appropriate FAA Principal Maintenance Inspector,
who may add comments and then send it to the Manager, Wichita ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita ACO.
Special Flight Permits
(d) 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.
Issued in Renton, Washington, on January 5, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 00-599 Filed 1-11-00; 8:45 am]
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