[Federal Register Volume 59, Number 27 (Wednesday, February 9, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-2916]
[[Page Unknown]]
[Federal Register: February 9, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 93-NM-202-AD]
Airworthiness Directives; Beech Aircraft Corp. Model 400A and
400T 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 Beech Model 400A and 400T
airplanes. This proposal would require inspection to detect damage of
the wire harness in the wheel well of the main landing gear (MLG), and
modification, if necessary. This proposal is prompted by reports of
damage to wire harnesses due to abrasion. The actions specified by the
proposed AD are intended to prevent loss of control of the fuel supply
to the engine or loss of control of the retraction/extension system for
the MLG and MLG door.
DATES: Comments must be received by April 5, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 93-NM-202-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Beech Aircraft Corporation, Commercial Service
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: Larry Engler, Aerospace Engineer,
Airframe Branch, ACE-115W, FAA, Small Airplane Directorate, Wichita
Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-
Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4122; 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 93-NM-202-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-103, Attention: Rules
Docket No. 93-NM-202-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
Recently, the FAA has received reports of damaged wire harnesses in
the wheel well of the main landing gear (MLG) on certain Beech Model
400A and 400T airplanes. These harnesses became abraded when they came
in contact with tires spinning in the wheel well following retraction
of the MLG. Investigation revealed that these wire harnesses were
routed and clamped incorrectly during production. The wire harness in
the wheel well of the MLG operates the boost pump, low fuel switch, up-
lock switch, gear door switch, and left-hand low fuel pressure switch
on these airplanes. Damaged wire harnesses, if not corrected, could
result in loss of control of the fuel supply to the engine or loss of
control of the retraction/extension system for the MLG and MLG door.
The FAA has reviewed and approved Beechcraft Service Bulletin 2479,
Revision 1, dated November1993, that describes procedures for
inspection to detect damage of the wire harness in the wheel well of
the MLG, and modification, if necessary. This modification entails
removing the damaged wiring, splicing in new wiring, and installing
additional clamps to ensure that tires spinning the wheel well of the
MLG do not come in contact with the wire harness. This service bulletin
references Chapter 20-00 of the Aircraft Maintenance Manual and Air
Force Technical Order P/N T.O. 1-1A-14 for further service information.
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 a general visual inspection to detect damage
of the wire harness in the wheel well of the MLG, and modification of
the damaged harness. The actions would be required to be accomplished
in accordance with the service bulletin described previously.
There are approximately 59 Model 400A and 400T airplanes of the
affected design in the worldwide fleet. The FAA estimates that 46
airplanes of U.S. registry would be affected by this proposed AD, that
it would take approximately 2 work hours per airplane to accomplish the
proposed actions, and that the average labor rate is $55 per work hour.
Based on these figures, the total cost impact of the proposed AD on
U.S. operators is estimated to be $5,060, or $110 per airplane.
The total 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.
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 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 14
CFR part 39 of the Federal Aviation Regulations as follows:
PART 39--AIRWORTHINESS DIRECTIVES -
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended] -
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Beech: Docket 93-NM-202-AD.
-Applicability: Model 400A airplanes having serial numbers RK-1
through RK-41 inclusive, and Model 400T airplanes having serial
numbers TT-2 through TT-19 inclusive; certificated in any category.
-
Compliance: Required as indicated, unless accomplished
previously. -
To prevent loss of control of the fuel supply to the engine or
loss of control of the retraction/extension system for the main
landing gear (MLG) and MLG door, accomplish the following:
(a) Within 200 hours time-in-service after the effective date of
this AD, perform a general visual inspection to detect damage of the
wire harness in the wheel well of the MLG in accordance with
Beechcraft Service Bulletin 2479, Revision 1, dated November 1993.
(1) If no damage is if found, no further action is required by
this AD.
(2) If damage is found, prior to further flight, modify the
wiring in accordance with the service bulletin.
Note 1: This service bulletin references Chapter 20-00 of the
Aircraft Maintenance Manual and Air Force Technical Order P/N T.O.
1-1A-14 for further service information regarding procedures for
modification (removal and splicing) of the wiring.
-(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, 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita ACO.
-(c) Special flight permits may be issued in accordance with
Federal Aviation Regulations (FAR) 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 February 3, 1994.
N.B. Martenson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-2916 Filed 2-8-94; 8:45 am]
BILLING CODE 4910-13-U
