[Federal Register Volume 60, Number 166 (Monday, August 28, 1995)]
[Proposed Rules]
[Pages 44449-44451]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-21257]



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[[Page 44450]]


DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-76-AD]


Airworthiness Directives; Beech Model 400, 400A, and 400T 
(Military T-1A) 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 400, 400A, and 
400T (military T-1A) airplanes. This proposal would require 
modification of the standby instrument lighting system. This proposal 
is prompted by a report that, due to the design of the standby 
instrument lighting system, the lighting for the standby instruments 
dimmed to an unacceptable level when the main electrical power was 
turned off. The actions specified by the proposed AD are intended to 
ensure that the standby instrument lighting system adequately 
illuminates the standby instrument, if normal electrical power is lost 
or is turned off as a result of fire or smoke in the cockpit.

DATES: Comments must be received by October 10, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-76-AD, 1601 Lind Avenue, SW., 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 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.

FOR FURTHER INFORMATION CONTACT: Harvey Nero, Aerospace Engineer, 
Systems and Propulsion Branch, ACE-116W, FAA, Wichita Aircraft 
Certification Office, Small Airplane Directorate, 1801 Airport Road, 
Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 
946-4137; 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 95-NM-76-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. 95-NM-76-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.
Discussion -

    The FAA has received a report indicating that, during evaluation 
checks of the cockpit lighting of Beech Model 400 airplanes, the 
lighting for the standby instruments (airspeed indicator, altimeter 
indicator, and attitude indicator) dimmed to an unacceptable level when 
the main electrical power was turned off. -
    During normal operations, the internal lighting for the standby 
instruments is provided through the dimming control of the pilot's 
instrument panel. If normal electrical power is lost, the lighting 
power is then provided through the dimming control of the co-pilot's 
instrument panel. -
    Investigation has revealed that setting the dimming control of the 
co-pilot's instrument panel to the dim position could cause the standby 
instruments to dim to an unacceptable level when normal electrical 
power is lost. The cause of the unacceptable level of lighting has been 
attributed to the design of the standby instrument lighting system. -
    If normal electrical power is lost or turned off as a result of 
fire or smoke in the cockpit, the standby instrument lighting system 
could fail to adequately illuminate the standby instrument. Lighting of 
the standby airspeed indicator, standby altimeter indicator, and 
standby attitude indicator may not be adequate for the pilot to discern 
during an emergency procedure. -
    The FAA has reviewed and approved Beechcraft Service Bulletin 2563, 
dated February 1995, which describes procedures for modification of the 
standby instrument lighting system. The modification will ensure that 
the standby instrument lights are fully illuminated in the event of 
loss of normal electrical power. -
    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 modification of the standby instrument 
lighting system. The actions would be required to be accomplished in 
accordance with the service bulletin described previously. -
    As a result of recent communications with the Air Transport 
Association (ATA) of America, the FAA has learned that, in general, 
some operators may misunderstand the legal effect of AD's on airplanes 
that are identified in the applicability provision of the AD, but that 
have been altered or repaired in the area addressed by the AD. The FAA 
points out that all airplanes identified in the applicability provision 
of an AD are legally subject to the AD. If an airplane has been altered 
or repaired in the affected area in such a way as to affect compliance 
with the AD, the owner or operator is required to obtain FAA approval 
for an alternative method of compliance with the AD, in accordance with 
the paragraph of each AD that provides for such approvals. A note has 
been included in this notice to clarify this long-standing requirement. 
-
    There are approximately 189 Model 400, 400A, and 400T airplanes of 
the affected design in the worldwide fleet. The FAA estimates that 189 
airplanes of U.S. registry would be affected by this proposed AD, that 
it would take approximately 6 work hours per airplane to accomplish the 
proposed actions, and that the average labor rate is $60 per work hour. 
The cost of the required parts could range from $21 to as much as $471 
per airplane. Based on these figures, the total cost impact of the 

[[Page 44451]]
proposed AD on U.S. operators is estimated to be between $72,009 (or 
$381 per airplane) and $157,059 (or $831 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 
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 the following new 
airworthiness directive:

Beech Aircraft Corporation: Docket 95-NM-76-AD.

    -Applicability: Model 400 airplanes, serial number RJ-61; 400A 
airplanes, serial numbers RK-1 through RK-80 inclusive; and 400T 
(military T-1A) airplanes, serial numbers TT-1 through TT-108 
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 use the authority 
provided in paragraph (b) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition; or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    -Compliance: Required as indicated, unless accomplished 
previously. -
    To ensure that the standby instrument lighting system adequately 
illuminates the standby instrument, if normal electrical power is 
lost or is turned off as a result of a fire or smoke in the cockpit, 
accomplish the following: -
    (a) Within 200 hours time-in-service after the effective date of 
this AD, modify the standby instrument lighting system in accordance 
with Beechcraft Service Bulletin 2563, dated February 1995. -
    (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 
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 August 22, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-21257 Filed 8-25-95; 8:45 am]
BILLING CODE 4910-13-U