[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