[Federal Register Volume 60, Number 121 (Friday, June 23, 1995)]
[Rules and Regulations]
[Pages 32585-32587]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-14870]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-CE-24-AD; Amendment 39-9284; AD 95-13-03]


Airworthiness Directives; Beech Aircraft Corporation Model F90, 
and 99, 100, and 200 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Beech Aircraft Corporation (Beech) Model F90, and 
99, 100, and 200 series airplanes. This action requires installing a 
circuit breaker that will open before the landing gear power system 
motor is damaged to the point of restricting operation of the manual 
landing gear extension system. An incident where excessive current flow 
caused the electrical landing gear motor and wiring to catch fire on a 
Beech Model 200 airplane prompted this action. The actions specified by 
this AD are intended to prevent excessive current flow through the 
electrical landing gear motor, which could cause an airplane fire.

DATES: Effective July 28, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 28, 1995.

ADDRESSES: Service information that applies to this AD may be obtained 
from the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 
67201-0085. This information may also be examined at the Federal 
Aviation Administration (FAA), Central Region, Office of the Assistant 
Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 
64106; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr. Dale A. Vassalli, Aerospace 
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport 
Road, Room 100, Wichita, Kansas 67209; telephone (316) 946-4132; 
facsimile (316) 946-4407.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that would apply 
to certain Beech Model F90, and 99, 100, and 200 series airplanes was 
published in the Federal Register on December 30, 1994 (59 FR 67656). 
The action proposed to require installing a circuit breaker that will 
open before the landing gear power system motor is damaged to the point 
of restricting operation of the manual landing gear extension system. 
Accomplishment of the proposed action would be in accordance with Beech 
Service Bulletin (SB) No. 2035, Issued: February 1985; Revised August 
1990; and the instructions to the following Landing Gear Motor Circuit 
Breaker Installation Kits (as applicable): 101-3069-1 S, 101-3069-3 S, 
101-3069-5 S, and 101-3133-1 S.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposed rule or the FAA's determination of the cost to the public.
    Since issuance of the proposal, Beech has revised SB No. 2035 to 
the Revision III level (Issued: February 1985; Revised: April 1995). 
This revision adds reference to Kit No. 101-3069-7 S for the Model 
A200C airplanes, serial numbers BJ-1 through BJ-66, and incorporates 
minor editorial corrections. The FAA has determined that Beech Kit No. 
101-3069-7 S should be added to the final rule AD, as well as reference 
to Beech SB 2035, Revision III, Issued: February 1985; Revised: April 
1995.
    After careful review of all available information, the FAA has 
determined that air safety and the public interest require the adoption 
of the rule as proposed except for the addition of the installation kit 
described above, reference to the revised service bulletin, and minor 
editorial corrections. The FAA has determined that the additions and 
minor editorial corrections will not change the meaning of the AD and 
will not add any additional burden upon the public than was already 
proposed.
    The FAA estimates that 2,297 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 6 workhours 
(varies between 2 to 6 workhours depending on the airplane model) per 
airplane to accomplish the required action, and that [[Page 32586]] the 
average labor rate is approximately $60 an hour. The cost for parts 
varies by airplane model; however, for the purposes of this AD, $1,000 
is utilized. Based on these figures, the total cost impact of the AD on 
U.S. operators is estimated to be $3,123,920. This figure is based on 
the assumption that no U.S. operator of the affected airplanes has 
accomplished the proposed installation.
    Beech has informed the FAA that approximately 2,100 installation 
kits have been sold. Assuming that each of these kits is installed on 
one of the affected airplanes, the cost impact of this action on U.S. 
operators is reduced by $2,856,000 from $3,123,920 to $267,920.
    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 copy of the final 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, 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. 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 a new AD to read as follows:

95-13-03  Beech Aircraft Corporation: Amendment 39-9284; Docket No. 
94-CE-24-AD.

    Applicability: The following airplane models and serial numbers, 
certificated in any category:

------------------------------------------------------------------------
               Models                           Serial numbers          
------------------------------------------------------------------------
F90................................  LA-2 through LA-225 equipped with  
                                      mechanical landing gear.          
99, 99A, A99A, and B99.............  U-1 through U-49 equipped with     
                                      mechanical landing gear and U-51  
                                      through U-164 equipped with       
                                      mechanical landing gear.          
100 and A100.......................  B-1 through B-94 and B-100 through 
                                      B-247.                            
B100...............................  BE-2 through BE-137.               
200 and B200.......................  BB-2, BB-6 through BB-1157, BB-1159
                                      through BB-1166, and BB-1168      
                                      through BB-1192.                  
200C and B200C.....................  BL-1 through BL-72.                
200T and B200T.....................  BT-1 through BT-30.                
200CT and B200CT...................  BN-1 through BN-4.                 
A100 (U-12F).......................  B-95 through B-99.                 
A100-1 (U-21J).....................  BB-3, BB-4, and BB-5.              
A200 (C-12A/C).....................  BC-1 through BC-75 and BD-1 through
                                      BD-30.                            
A200C (UC-12B).....................  BJ-1 through BJ-66.                
A200CT (C-12D).....................  BP-1, BP-22, and BP-24 through BP- 
                                      45.                               
A200CT (FWC-12D)...................  BP-7 through BP-11.                
A200CT (RC-12D)....................  GR-1 through GR-13.                
A200CT (RC-12G)....................  FC-1, FC-2, and FC-3.              
A200CT (RC-12H)....................  GR-14 through GR-19.               
------------------------------------------------------------------------

    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 (c) 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 within the next 100 hours time-in-service 
after the effective date of this AD, unless already accomplished.
    To prevent excessive current flow through the electrical landing 
gear motor, which could result in an airplane fire, accomplish the 
following:
    (a) Install a circuit breaker that will open before the landing 
gear power system motor is damaged to the point of restricting 
operation of the manual landing gear extension system by 
accomplishing the following:
    (1) Prepare the airplane by completing the ACCOMPLISHMENT 
INSTRUCTIONS section of Beech Service Bulletin No. 2035, Revision 
III: Issued: February 1985; Revised: April 1995.
    (2) Incorporate one of the following Landing Gear Motor Circuit 
Breaker Installation Kits, as applicable, in accordance with the 
instructions provided with the kits:
    (i) 101-3069-1 S for Models 200, B200, 200C, B200C, 200T, B200T, 
200CT, B200CT, A200 (C-12A/C), and A200C (UC-12B);
    (ii) 101-3069-3 S for Models 100, A100, B100, and A100-1 (U-
21J);
    (iii) 101-3069-5 S for Models F90, 99, 99A, A99A, and B99;
    (iv) 101-3069-7 S for Model A200C (UC-12B); and
    (v) 101-3133-1 S for Models A200 (C-12A/C), A200CT (C-12D), 
A200CT (FWC-12D), A200CT (RC-12D), A200CT (RC-12G), and A200CT (RC-
12H).
    (b) 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.
    (c) An alternative method of compliance or adjustment of the 
compliance time that provides an equivalent level of safety may be 
approved by the Manager, Wichita Aircraft Certification Office 
(ACO), 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, 
Kansas 67209. The request shall be forwarded through an appropriate 
FAA 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.

    (d) The installation required by this AD shall be done in 
accordance with the instructions to Landing Gear Motor Circuit 
Breaker Installation Kits 101-3069-1 S, 101-3069-3 S, 101-3069-5 S, 
101-3069-7 S, or 101-3133-1 S, as referenced in Beech Service 
Bulletin No. 2035, Revision III: Issued: February 1985; Revised: 
April 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 the Beech Aircraft 
Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be 
inspected at the FAA, Central Region, Office of the Assistant Chief 
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC. [[Page 32587]] 
    (e) This amendment (39-9284) becomes effective on July 28, 1995. 
Issued in Kansas City, Missouri, on June 13, 1995.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-14870 Filed 6-22-95; 8:45 am]
BILLING CODE 4910-13-U