[Federal Register Volume 60, Number 241 (Friday, December 15, 1995)]
[Rules and Regulations]
[Pages 64315-64316]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-30533]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-75-AD; Amendment 39-9450; AD 95-25-05]


Airworthiness Directives; Beech Model 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 400A airplanes, that requires 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 amendment 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 this 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: Effective January 16, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 16, 1996.

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: 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: 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 400A airplanes 
was published in the Federal Register on August 10, 1995 (60 FR 40782). 
That action proposed to 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. That action also proposed to require an 
inspection to verify if the jam nut is secure on the opposite rod end, 
and repair of any discrepancy.
    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 96 Model 400A airplanes of the affected 
design in the worldwide fleet. The FAA estimates that 73 airplanes of 
U.S. registry will be affected by this AD, that it will take 
approximately 8 work hours per airplane to accomplish the required 
actions, and that the average labor rate is $60 per work hour. Based on 
these figures, the cost impact of the AD on U.S. operators is estimated 
to be $35,040, or $480 per airplane.
    The 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 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 

[[Page 64316]]
``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 U.S.C. 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

95-25-05  Beech Aircraft Corporation: Amendment 39-9450. 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, 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 inspections shall be done in accordance with Beechcraft 
Safety Communique 400A-113, dated March 1995. 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 January 16, 1996.

    Issued in Renton, Washington, on November 30, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-30533 Filed 12-14-95; 8:45 am]
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