[Federal Register Volume 60, Number 174 (Friday, September 8, 1995)]
[Rules and Regulations]
[Pages 46765-46766]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-21256]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-31-AD; Amendment 39-9352; AD 95-18-04]


Airworthiness Directives; Beech Model 400 and 400A Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Beech Model 400 and 400A airplanes, that requires 
modification of the autopilot and rudder boost interlock. This 
amendment is prompted by a report indicating that the rudder boost 
system installed on these airplanes does not operate correctly during 
deployment of a thrust reverser. The actions specified by this AD are 
intended to prevent incorrect operation of the rudder boost system 
during deployment of a thrust reverser and to prevent the autopilot 
from exceeding certain bank angle limits; these conditions could result 
in reduced controllability of the airplane.

DATES: Effective October 10, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 10, 1995.

ADDRESSES: The service information referenced in this AD 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 Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Wichita Aircraft Certification Office, Small 
Airplane Directorate, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dale Vassalli, Aerospace Engineer, 
Systems and Equipment Branch, ACE-130W, FAA, Wichita Aircraft 
Certification Office, Small Airplane Directorate, 1801 Airport Road, 
Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 
946-4132; fax (316) 946-4407.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Beech Model 400 and 400A 
airplanes was published in the Federal Register on May 4, 1995 (60 FR 
22013). That action proposed to require modification of the autopilot 
and rudder boost interlock.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public. 
The FAA has determined that air safety and the public interest require 
the adoption of the rule as proposed.
    There are approximately 92 Model 400 and 400A series airplanes of 
the affected design in the worldwide fleet. The FAA estimates that 69 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 24 work hours per airplane to accomplish the 
required actions, and that the average labor rate is $60 per work hour. 
Required parts will be provided by the manufacturer at no cost to 
operators. Based on these figures, the total cost impact of the AD on 
U.S. operators is estimated to be $99,360, or $1,440 per airplane.
    The total cost impact figure discussed above is based on 
assumptions that no operator has yet accomplished any of the 
requirements of this AD action, and that no operator would accomplish 

[[Page 46766]]
those actions in the future if this AD were not adopted.
    The regulations adopted herein will 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 final 
rule does 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) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 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:

95-18-04  Beech Aircraft Corporation: Amendment 39-9352. Docket 95-
NM-31-AD.

    Applicability: Model 400 airplanes, serial RJ-61; and Model 400A 
airplanes, serials RK-1 through RK-77 inclusive, and RK-79 through 
RK-92 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) of this AD 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 prevent reduced controllability of the airplane, accomplish 
the following:
    (a) At the next scheduled inspection, but no later than 200 
hours time-in-service after the effective date of this AD, install 
an autopilot and rudder boost improvement kit in accordance with 
Beechcraft Service Bulletin No. 2533, dated October 1994.
    (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.
    (d) The installation shall be done in accordance with Beechcraft 
Service Bulletin No. 2533, dated October 1994. This incorporation by 
reference was approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be 
obtained from Beech Aircraft Corporation, Commercial Service 
Department, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the FAA, Wichita Aircraft 
Certification Office, Small Airplane Directorate, 1801 Airport Road, 
Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office 
of the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.
    (e) This amendment becomes effective on October 10, 1995.

    Issued in Renton, Washington, on August 22, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-21256 Filed 9-7-95; 8:45 am]
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