[Federal Register Volume 60, Number 158 (Wednesday, August 16, 1995)]
[Proposed Rules]
[Pages 42479-42481]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-20274]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-CE-32-AD]


Airworthiness Directives; Beech Aircraft Corporation 90, 99, 100, 
and 200 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to adopt a new airworthiness directive 
(AD) that would apply to certain Beech Aircraft Corporation (Beech) 90, 
99, 100, and 200 series airplanes. The proposed action would require 
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 where the left main landing gear collapsed on one of 
the affected airplanes prompted the proposed action. Investigation 
revealed that the roll pin hole was not completely drilled through both 
walls of the drag leg lock link. The actions specified by the proposed 
AD are intended to prevent main landing gear collapse caused by drag 
leg lock link failure, which, if not detected and corrected, could 
result in loss of control of the airplane.

DATES: Comments must be received on or before October 20, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket No. 95-CE-32-AD, Room 1558, 601 E. 
12th Street, Kansas City, Missouri 64106. Comments may be inspected at 
this location between 8 a.m. and 4 p.m., Monday through Friday, 
holidays excepted.
    Service information that applies to the proposed AD may be obtained 
from the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 
67201-0085. This information also may be examined at the Rules Docket 
at the address above.

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:

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 should 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 that summarizes 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 No. 95-CE-32-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, Central Region, Office of the Assistant Chief Counsel, 
Attention: Rules Docket No. 95-CE-32-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.

Discussion

    The FAA received a report of an incident where the left main 
landing gear collapsed on a Beech Model 99 airplane. Investigation of 
this incident revealed that the hole for the roll pin was not 
completely drilled through both walls of the drag leg lock link.
    Further investigation shows that spare drag leg lock links were 
delivered to the field with the roll pin hole only drilled halfway 
through the link. When drilled only halfway through the link, the roll 

[[Page 42480]]
pin will not hold the pivot pin secure in the drag leg lock link. In 
this scenario, the drag leg lock link does not hold the landing gear in 
the down position, which could cause main landing gear collapse. These 
drag leg lock links may be installed on certain Beech 90, 99, 100, and 
200 series airplanes.
    Beech has issued Service Bulletin No. 2607, Revision 1, dated April 
1995, which specifies procedures for inspecting the main landing gear 
drag leg lock link on Beech 90, 99, 100, and 200 series airplanes to 
ensure that the roll pin hole is drilled through both walls of the 
link.
    After examining the circumstances and reviewing all available 
information related to the incident described above, the FAA has 
determined that AD action should be taken to prevent main landing gear 
collapse caused by drag leg lock link failure, which, if not detected 
and corrected, could result in loss of control of the airplane.
    Since an unsafe condition has been identified that is likely to 
exist or develop in other Beech 90, 99, 100, and 200 series airplanes 
of the same type design, the proposed AD would 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 
lock link. Accomplishment of the proposed inspection would be in 
accordance with Beech Service Bulletin No. 2607, Revision 1, dated 
April 1995. The possible replacement would be accomplished in 
accordance with the applicable maintenance manual.
    The FAA estimates that 2,229 airplanes in the U.S. registry would 
be affected by the proposed AD, that it would take approximtely 5 work 
hours per airplane to accomplish the proposed 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 the proposed 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 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 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) 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 has been placed 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 U.S.C. 106(g); 40101, 40113, 44701.


Sec. 39.13  [Amended]

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

Beech Aircraft Corporation: Docket No. 95-CE-32-AD.

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

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               Models                            Serial Nos.            
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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 use the authority 
provided in paragraph (d) 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 aircraft from the applicability of this AD.

    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, if not detected and corrected, 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 
section 21.197 and 21.199 of 

[[Page 42481]]
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 
(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.

    (e) All persons affected by this directive may obtain copies of 
the document referred to herein upon request to the Beech Aircraft 
Corporation, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine 
this document at the FAA, Central Region, Office of the Assistant 
Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 
64106.

    Issued in Kansas City, Missouri, on August 10, 1995.
Gerald W. Pierce,
Acting Manger, Small Airplane, Aircraft Certification Service.
[FR Doc. 95-20274 Filed 8-15-95; 8:45 am]
BILLING CODE 4910-13-M