[Federal Register Volume 63, Number 200 (Friday, October 16, 1998)]
[Rules and Regulations]
[Pages 55528-55530]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-27604]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-CE-148-AD; Amendment 39-10843; AD 98-21-35]
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: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Raytheon Aircraft Company (Raytheon) Models A200CT, 
B200, B200C, B200CT, 200T/B200T, 300, B300, and B300C airplanes. This 
AD requires replacing the main landing gear left and right actuator 
clevis assembly. Reports of main landing gear failure on two of the 
affected airplanes prompted this action. The actions specified by this 
AD are intended to prevent failure of the actuator clevis assembly in 
the main landing gear caused by fatigue cracking of the original design 
part, which could result in loss of control of the airplane during 
landing operations.

DATES: Effective November 23, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 23, 1998.

ADDRESSES: Service information that applies to this AD may be obtained 
from the Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 625-7043 or (316) 676-4556. This information may 
also be examined at 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; 
or at the Office of the Federal Register, 800 North Capitol Street, NW, 
suite 700, Washington, DC.

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) 946-4124; 
facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

    Events Leading to the Issuance of This AD
    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to certain Raytheon 
Models A200CT, B200, B200C, B200CT, 200T/B200T, 300, B300, and B300C 
airplanes was published in the Federal Register as a notice of proposed 
rulemaking (NPRM) on May 5, 1998 (63 FR 24756). The NPRM proposed to 
require replacing the left and right main landing gear (MLG) actuator 
clevis assembly with a new actuator clevis assembly of improved design. 
Accomplishment of the proposed action as specified in the NPRM would be 
in accordance with Raytheon Aircraft Mandatory Service Bulletin No. 
2728, Issued: June, 1997, Revision No. 1, dated February, 1998.
    The NPRM was the result of reports of main landing gear failure on 
two of the affected airplanes.
    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.

[[Page 55529]]

The FAA's Determination

    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.

Cost Impact

    The FAA estimates that 897 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 5 workhours per 
airplane to accomplish this 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 this 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 this action; thereby reducing 
the total cost impact of this AD on U.S. operators by $92,505, from 
$790,257 to $697,752.

Regulatory Impact

    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:

98-21-35  Raytheon Aircraft Company (Type Certificate No. A24CE 
formerly held by the Beech Aircraft Corporation): Amendment 39-
10843; Docket No. 97-CE-148-AD.

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

------------------------------------------------------------------------
                 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.
B200T/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, and
                                         FE-35.
A200CT (RC-12Q).......................  FE-32, FE-34, and 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 assembly in the main 
landing gear caused by fatigue cracking of the original design part, 
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 (MLG) 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) The replacements required by this AD shall be done in 
accordance with Raytheon Aircraft Mandatory Service Bulletin No. 
2728, Issued: June, 1997, Revision No. 1, February, 1998. 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 Raytheon Aircraft Company, P.O. 
Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the 
FAA, Central Region, Office of the Regional 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 55530]]

    (e) This amendment becomes effective on November 23, 1998.

    Issued in Kansas City, Missouri, on October 7, 1998.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-27604 Filed 10-15-98; 8:45 am]
BILLING CODE 4910-13-U