[Federal Register Volume 63, Number 86 (Tuesday, May 5, 1998)]
[Proposed Rules]
[Pages 24756-24758]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-11887]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-CE-148-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company Models 
A200CT, B200, B200C, B200CT, 200T/B200T, 300, B300, and B300C 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 Raytheon Aircraft Company (Raytheon) Models 
A200CT, B200, B200C, B200CT, 200T/B200T, 300, B300, and B300C 
airplanes. The proposed action would require replacing the main landing 
gear left and right actuator clevis assembly. Reports of main landing 
gear failure on two of the affected airplanes prompted the proposed 
action. The actions specified by the proposed AD are intended to 
prevent failure of the actuator clevis assembly in the main landing 
gear, which could result in loss

[[Page 24757]]

of control of the airplane during landing operations.

DATES: Comments must be received on or before July 10, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 97-CE-148-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 Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 625-7043 or (316) 676-4556. This information 
also may be examined at the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr. Steven E. Potter, Aerospace 
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport 
Road, Room 100, Wichita, Kansas 67209; telephone (316) 946-4146; 
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. 97-CE-148-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 Regional Counsel, Attention: 
Rules Docket No. 97-CE-148-AD, Room 1558, 601 E. 12th Street, Kansas 
City, Missouri 64106.

Discussion

    The FAA has received two reports of failed main landing gear (MLG) 
on Raytheon Models B200 and B200C airplanes. Further investigation 
shows the MLG actuator clevis in these airplanes failed from fatigue 
cracking in the threaded shank portion of the clevis. The MLG actuator 
clevis assembly that is currently installed in these Raytheon airplanes 
could also fracture causing collapse of the MLG while landing.

Relevant Service Information

    Raytheon Aircraft has issued Mandatory Service Bulletin No. 2728, 
Issued: June 1997, Revision No. 1, dated February 1998, which specifies 
replacing the left and right MLG actuator clevis assmembly with a new 
MLG actuator clevis assembly of improved design.

The FAA's Determination

    After examining the circumstances and reviewing all available 
information related to the incidents described above, the FAA has 
determined that AD action should be taken to prevent failure of the 
actuator clevis assembly in the main landing gear, which, if not 
corrected, could result in loss of control of the airplane during 
landing operations.

Explanation of the Provisions of the Proposed AD

    Since an unsafe condition has been identified that is likely to 
exist or develop in other Raytheon Models A200CT, B200, B200C, B200CT, 
200T/B200T, 300, B300, and B300C of the same type design, the proposed 
AD would require replacing the left and right MLG actuator clevis 
assembly with a new actuator clevis assembly of improved design.

Cost Impact

    The FAA estimates that 897 airplanes in the U.S. registry would be 
affected by the proposed AD, that it would take approximately 5 
workhours per airplane to accomplish the proposed action, and that the 
average labor rate is approximately $60 an hour. Parts cost 
approximately $581 per airplane. Based on these figures, the total cost 
impact of the proposed AD on U.S. operators is estimated to be 
$790,257, or $881 per airplane. The manufacturer has informed the FAA 
that 105 owners/operators of these airplanes have already accomplished 
the proposed action; therefore, the total cost impact of the proposed 
AD on U.S. operators would be reduced by $92,505 from $790,257 to 
$697,752.

Regulatory Impact

    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), 40113, 44701.

Sec. 39.13  [Amended]

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

Raytheon Aircraft Company: Docket No. 97-CE-148-AD.

    Applicability: Airplane models listed below, certificated in any 
category.

[[Page 24758]]



------------------------------------------------------------------------
                  Model                             Serial No.          
------------------------------------------------------------------------
B200....................................  BB-1158, BB-1167, BB-1193     
                                           through BB-1263, BB-1265     
                                           through BB-1286, BB-1287, BB-
                                           1288, BB-1290 through BB-    
                                           1300, BB-1302 through BB-    
                                           1425, BB-1427 through BB-    
                                           1447, BB-1449, BB-1450, BB-  
                                           1453, BB-1455, BB-1456, and  
                                           BB-1458 through BB-1559.     
B200C...................................  BL-124 through BL-140.        
B200CT (FW-II)..........................  FG-1 and FG-2.                
200T/B200T..............................  BT-31 through BT-38.          
300.....................................  FA-1 through FA-230 and FF-1  
                                           through FF-19.               
B300....................................  FL-1 through FL-159.          
B300C...................................  FM-1 through FM-9 and FN-1.   
A200CT (C-12D)..........................  BP-46 through BP-51.          
A200CT (C-12F)..........................  BP-52 through BP-63.          
A200CT (RC-12K).........................  FE-1 through FE-9.            
A200CT (RC-12N).........................  FE-10 through FE-24.          
A200CT (RC-12P).........................   FE-25 through FE-31, FE-33,  
                                           FE-35.                       
A200CT (RC-12Q).........................  FE-32, FE-34, FE-36.          
B200C (C-12F)...........................  BP-64 through BP-71, BL-73    
                                           through BL-112, and BL-118   
                                           through BL-123.              
B200C (UC-12F)..........................  BU-1 through BU-10.           
B200CT (RC-12F).........................  BU-11 and BU-12.              
B200C (UC-12M)..........................  BV-1 through BV-10.           
B200C (RC-12M)..........................  BV-11 and BV-12.              
B200C (C-12R)...........................  BW-1 through BW-29.           
------------------------------------------------------------------------

    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 (c) 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 been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required within the next 200 hours time-in-service 
(TIS) after the effective date of this AD, unless already 
accomplished.
    To prevent failure of the actuator clevis rod in the main 
landing gear, which could result in loss of control of the airplane 
during landing operations, accomplish the following:
    (a) Replace the left and right main landing gear actuator clevis 
assembly with a new MLG actuator clevis assembly of improved design 
in accordance with the Accomplishment Instructions section in 
Raytheon Aircraft Mandatory Service Bulletin No. 2728, Issued: June, 
1997, Revision No. 1, February, 1998.
    (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, 1801 
Airport Road, Room 100, 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.

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

    Issued in Kansas City, Missouri, on April 29, 1998.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-11887 Filed 5-4-98; 8:45 am]
BILLING CODE 4910-13-U