[Federal Register Volume 60, Number 228 (Tuesday, November 28, 1995)]
[Proposed Rules]
[Pages 58583-58584]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-28958]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-CE-82-AD]
Airworthiness Directives; Beech Aircraft Corporation Model C90A
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to certain Beech Aircraft Corporation (Beech)
Model C90A airplanes equipped with an optional Beech electric trim
system or a Collins autopilot system. The proposed action would require
modifying the elevator electric trim tab actuator assembly. Failure of
the elevator electric trim tab system on a Beech Model C90A prompted
the proposed AD action. The actions specified by the proposed AD are
intended to prevent possible failure of the elevator electric trim tab
system, which, if not detected and corrected, could cause loss of
airplane maneuverablity and possible loss of control of the airplane.
DATES: Comments must be received on or before January 29, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 95-CE-82-AD, Room 1558, 601 E.
12th Street, Kansas City, Missouri 64106. Comments may be inspected at
this location between 8 a.m. and 4 p.m., Monday through Friday,
holidays excepted.
Service information that applies to the proposed AD may be obtained
from Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-
0085. This information also may be examined at the Rules Docket at the
address above.
FOR FURTHER INFORMATION CONTACT: Harvey E. Nero, Aerospace Engineer,
FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room
100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-
4137, facsimile (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 should 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 that summarizes 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 No. 95-CE-82-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, Central Region, Office of the Assistant Chief Counsel,
Attention: Rules Docket No. 95-CE-82-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
Investigation of an inoperative electric elevator trim system on a
Beech Model C90A airplane revealed that the trim cable had moved out of
its groove, twisted on top of the next groove, and stopped the actuator
cable drum from moving. This airplane had a pin-type cable guard
actuator assembly (part number (P/N) 33-524023-51) installed. These
installations involve both the optional Beech electric trim system and
the Collins autopilot system. Investigation shows the pin-type cable
guard allows the trim cable to come out of the actuator grooves of the
actuator cable drum when the elevator trim system is at maximum travel.
This situation could cause the actuator cable drum to bind, thus
causing the actuator motor to stall, and causing the actuator assembly
to jam. Beech has changed the design to a shroud-type cable guard
actuator assembly (P/N 33-524023-77 or P/N 33-524023-79). The shroud-
type cable guard does not allow the trim cable to travel out of the
grooves of the actuator cable drum and prevents failure of the actuator
assembly.
The pin-type cable guards were installed on some airplanes starting
at Beech Model C90A serial number LJ-1111. Beech changed to the shroud-
type cable guard at some point between LJ-1111 and LJ-1410. After
serial number LJ-1410, Beech manufactured the Model C90A airplanes with
the shroud-type cable guard actuator assembly exclusively in the
elevator electric trim system and the Collins autopilot system.
Beech Service Bulletin (SB) number (No.) 2631, Issued: June 1995,
Revised: September 1995, specifies procedures for modifying the
elevator electric trim tab actuator assembly.
After examining the circumstances and reviewing all available
information related to the incidents described above, the FAA has
determined that AD action should be taken to prevent possible failure
of the elevator electric trim tab system, which, if not detected and
corrected, could result in loss of airplane maneuverablity and possible
loss of control of the airplane.
Since an unsafe condition has been identified that is likely to
exist or develop in other Beech C90A airplanes of the same type design,
the proposed AD would require modifying the elevator electric trim tab
actuator assembly from the pin-type actuator cable guard to the shroud-
type actuator cable guard. Accomplishment of the proposed action would
be in accordance with Beech SB No. 2631, Issued: June 1995, Revised:
September 1995.
The FAA estimates that 300 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 6
workhours per airplane to accomplish the proposed action, and
[[Page 58584]]
that the average labor rate is approximately $60 an hour. Parts are
estimated to be $160 per airplane. Based on these figures, the total
cost impact of the proposed AD on U.S. operators is estimated to be
$156,000 or $520 per airplane. Beech has informed FAA that no parts
have been distributed to owners/operators for this modification;
therefore, this figure is based on the assumption that no owners/
operators have accomplished the proposed inspection and modification.
The regulations proposed herein would 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
proposal would 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) 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 has been placed 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:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
Beech Aircraft Corporation: Docket No. 95-CE-82-AD.
Applicability: The following Model C90A airplanes, certificated
in any category, that are equipped with an optional Beech electric
trim system or a Collins autopilot system:
(1) Serial numbers LJ-1111 through LJ-1410 that were equipped at
manufacturer with a pin-type cable guard actuator assembly (P/N 33-
524023-51) on the elevator electric trim tab actuator assembly.
(2) All serial numbers (except LJ-1 through LJ-1110) equipped
with a pin-type cable guard actuator assembly (P/N 33-524023-51)
installed through field approval.
Note 1: Steps 1 through 4 of the ACCOMPLISHMENT INSTRUCTIONS
section of Beech Service Bulletin (SB) No. 2631, Issued: June 1995,
Revised: September 1995, provide procedures for determining which
assembly is installed.
Note 2: 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 follows, unless already accomplished:
(1) Within 150 hours time-in-service (TIS) after the effective
date of this AD; or
(2) Upon installation of an optional Beech elevator electric
trim tab system or a Collins autopilot system.
To prevent possible failure of the optional Beech electric trim
system or the Collins autopilot system, which, if not detected and
corrected, could cause loss of airplane maneuverablity and possible
loss of control of the airplane, accomplish the following:
(a) Modify all elevator electric trim tab actuator assemblies,
part number (P/N) 33-524023-51 to the P/N 33-524023-77 or P/N 33-
524023-79 level, by accomplishing the procedures in the
ACCOMPLISHMENT INSTRUCTIONS section of Beech Service Bulletin SB No.
2631, Issued: June 1995, Revised: September 1995.
(b) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviations Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
(c) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be
approved by the Manager, Wichita Aircraft Certification Office, 1801
Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas
67209. The request shall be forwarded through an appropriate FAA
Maintenance Inspector, who may add comments and then send it to the
Manager, Wichita Aircraft Certification Office.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita Aircraft Certification Office.
(d) All persons affected by this directive may obtain copies of
the document referred to herein upon request to Beech Aircraft
Corporation, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine
this document at the FAA, Central Region, Office of the Assistant
Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri
64106.
Issued in Kansas City, Missouri, on November 20, 1995.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 95-28958 Filed 11-27-95; 8:45 am]
BILLING CODE 4910-13-U
