[Federal Register Volume 61, Number 36 (Thursday, February 22, 1996)]
[Rules and Regulations]
[Pages 6768-6770]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-2588]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-CE-32-AD; Amendment 39-9510; AD 96-03-13]


Airworthiness Directives; Beech Aircraft Corporation 90, 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 Beech Aircraft Corporation (Beech) 90, 99, 100, and 200 
series airplanes. This action requires inspecting the main landing gear 
drag leg lock link to ensure that the hole for the roll pin is drilled 
completely through both walls of the main landing gear drag leg lock 
link and, if not drilled completely through both link walls, replacing 
any main landing gear drag leg lock link. An incident in which the left 
main landing gear collapsed on one of the affected airplanes prompted 
this action. Investigation revealed that the roll pin hole was not 
completely drilled 

[[Page 6769]]
through both walls of the drag leg lock link. The actions specified by 
this AD are intended to prevent main landing gear collapse caused by 
drag leg lock link failure, which could result in loss of control of 
the airplane.

DATES: Effective April 1, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 1, 1996.

ADDRESSES: Service information that applies to this AD may be obtained 
from 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, Attention: Rules Docket 95-CE-32-AD, 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. Steve Potter, Aerospace Engineer, 
Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4124; 
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 Beech Aircraft Corporation 90, 99, 100, and 200 series airplanes was 
published in the Federal Register on August 16, 1995 (60 FR 42479). The 
action proposed to require inspecting the main landing gear drag leg 
lock link to ensure that the hole for the roll pin is drilled through 
both walls of the link and, if not drilled completely through both link 
walls, replacing any main landing gear drag leg lock link. 
Accomplishment of the proposed action would be in accordance with Beech 
Service Bulletin No. 2607, Revision 1, dated April 1995.
    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.
    After careful review of all available information related to the 
subject presented above, the FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. The FAA has determined that these minor 
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 2,229 airplanes in the U.S. registry will be 
affected by this AD action, that it will take approximately 5 work 
hours per airplane to accomplish this action, and that the average 
labor rate is approximately $60 an hour. Parts cost approximately $100 
per airplane. Based on these figures, the total cost impact of this AD 
on U.S. operators is estimated to be $891,600. This figure is based on 
the assumption that all of the affected airplanes have incorrectly 
drilled drag leg lock links and that none of the owners/operators of 
the affected airplanes have replaced the incorrectly drilled links.
    Beech has informed the FAA that parts have been distributed to 
equip approximately 648 airplanes. Assuming that these distributed 
parts are incorporated on the affected airplanes, the cost of the 
proposed AD would be reduced by $259,200 from $891,600 to $632,400. In 
addition, the FAA believes that a majority of the affected airplanes 
will not have incorrectly drilled links, thereby further reducing the 
cost impact of the proposed AD upon the public.
    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. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
(AD) to read as follows:

AD No.96-03-13 Beech Aircraft Corporation: Amendment 39-9510; Docket 
No. 95-CE-32-AD.

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

------------------------------------------------------------------------
                  Models                           Serial Numbers       
------------------------------------------------------------------------
F90.......................................  LA-2 through LA-236.        
99, 99A, A99A, B99, and C99...............  U-1 through U-239.          
100 and A100..............................  B-1 through B-94 and B-100  
                                             through B-247.             
B100......................................  BE-1 through BE-137.        
200 and B200..............................  BB-2, BB-6 through BB-1157, 
                                            BB-1159 through BB-1166, and
                                            BB-1168 through BB-1192.    
200T and B200T............................  BT-1 through BT-30.         
200C and B200C............................  BL-1 through BL-72.         
200CT and B200CT..........................  BN-1 through BN-4.          
65-A90-2(RU-21B)..........................  LS-1 through LS-3.          
65-A90-3(RU-21C)..........................  LT-1 through LT-2.          
200 (A100-1)..............................  BB-3 through BB-5.          
A100 (U-21F)..............................  B-95 through B-99.          
A200 (C-12A and C-12C)....................  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-12H)...........................  GR-14 through GR-19.        
A200CT (RC-12G)...........................  FC-1 through FC-3.          
------------------------------------------------------------------------

    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 request approval for an 
alternative method of compliance in accordance with paragraph (d) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not 

[[Page 6770]]
been eliminated, the request should include specific proposed actions 
to address it.
    Compliance: Required within the next 100 hours time-in-service 
(TIS) after the effective date of this AD, unless already 
accomplished.
    To prevent main landing gear collapse caused by drag leg lock 
link failure, which could result in loss of control of the airplane, 
accomplish the following:
    (a) Inspect the main landing gear drag leg lock link to ensure 
that the hole for the roll pin is drilled completely through both 
walls of the link in accordance with the ACCOMPLISHMENT INSTRUCTIONS 
section of Beech Service Bulletin No. 2607, Revision 1, dated April 
1995.
    (b) Prior to further flight, replace any drag leg lock link that 
does not have the roll pin hole drilled through both walls of the 
link. Accomplish this replacement in accordance with the applicable 
maintenance manual.
    (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) 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, FAA, 
1801 Airport Road, 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 Aircraft Certification Office.
    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita Aircraft Certification Office.
    (e) The inspections and replacements required by this AD shall 
be done in accordance with Beech Service Bulletin No. 2607, Revision 
1, dated 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 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., 
7th Floor, suite 700, Washington, DC.
    (f) This amendment (39-9510) becomes effective on April 1, 1996.
    Issued in Kansas City, Missouri, on January 31, 1996.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 96-2588 Filed 2-21-96; 8:45 am]
BILLING CODE 4910-13-P