[Federal Register Volume 60, Number 154 (Thursday, August 10, 1995)]
[Proposed Rules]
[Pages 40782-40783]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-19774]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-75-AD]


Airworthiness Directives; Beech Model 400A 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 
airplanes. This proposal would require an inspection to verify if the 
securing rivet is installed on the rod end of the control push rods of 
the spoiler flight control system, an inspection to verify if the jam 
nut is secure on the opposite end of the rod end, and repair of any 
discrepancy. This proposal is prompted by a report of loss of roll 
control on the co-pilot's control wheel shortly after takeoff due to a 
rivet missing from the control push rod. The actions specified by the 
proposed AD are intended to ensure that the push rod rivets are 
installed. Missing control push rod rivets could result in the 
disengagement of the push rod end from the push rod tube; this could 
lead to loss of roll control and subsequent reduced controllability of 
the airplane after takeoff.

DATES: Comments must be received by September 19, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-75-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, Wichita Aircraft 
Certification Office, Small Airplane Directorate, 1801 Airport Road, 
Room 100, Mid-Continent Airport, Wichita, Kansas.

FOR FURTHER INFORMATION CONTACT: Larry Engler, Aerospace Engineer, 
Airframe Branch, ACE-118W, FAA, Wichita Aircraft Certification Office, 
Small Airplane Directorate, 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 95-NM-75-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-75-AD, 1601 Lind Avenue SW., Renton, Washington 98055-
4056.

Discussion

    The FAA has received a report of loss of roll control on the co-
pilot's control wheel on a Beech Model 400A airplane shortly after 
takeoff. Investigation revealed that the rod end of the control push 
rod of the co-pilot's spoiler flight control system had disengaged from 
the threaded end of the push rod tube at the center bellcrank. Further 
investigation revealed that a rivet was missing from both the pilot's 
and co-pilot's control push rod; this rivet secures the rod end that is 
threaded onto the control push rod. Additionally, the rod end on the 
opposite end of the control push rod was loose. These conditions, if 
not corrected, could result in disengagement of the push rod end from 
the push rod tube. This could lead to reduced controllability of the 
airplane after takeoff.
    The FAA has reviewed and approved Beechcraft Safety Communique 
400A-113, dated March 1995, which describes procedures for a one-time 
detailed visual inspection to verify if the securing rivet is installed 
on the control push rods of the spoiler flight control system, and an 
inspection to verify if the jam nut is secure on the opposite control 
rod end.
    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 one-time detailed visual inspection to 
verify if the securing rivet is installed on the push rods of the 
spoiler flight control system, and an inspection to verify if the jam 
nut is secure on the opposite rod end. The actions would be required to 
be accomplished in accordance with the safety communique described 
previously. If any discrepancy is found, the repair would be required 
to be accomplished in accordance with a method approved by the FAA.
    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 

[[Page 40783]]
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 96 Model 400A airplanes of the affected 
design in the worldwide fleet. The FAA estimates that 73 airplanes of 
U.S. registry would be affected by this proposed AD, that it would take 
approximately 8 work hours per airplane to accomplish the proposed 
actions, and that the average labor rate is $60 per work hour. Based on 
these figures, the total cost impact of the proposed AD on U.S. 
operators is estimated to be $35,040, or $480 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-75-AD.

    Applicability: Model 400A airplanes, serial numbers RK-1 through 
RK-96 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 after 
takeoff, accomplish the following:
    (a) Within 50 hours time-in-service after the effective date of 
this AD, perform a detailed visual inspection to verify if the 
securing rivet is installed on the control push rods of the spoiler 
flight control system, and an inspection to verify if the jam nut is 
secure on the opposite rod end, in accordance with Beechcraft Safety 
Communique 400A-113, dated March 1995. If any discrepancy is found, 
prior to further flight, repair in accordance with a method approved 
by the Manager, Wichita Aircraft Certification Office (ACO), FAA, 
Small Airplane Directorate.
    (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 ACO. 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 4, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-19774 Filed 8-9-95; 8:45 am]
BILLING CODE 4910-13-U