AD 98-21-35

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.

Final rule

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 Number
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, 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 ofthe 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 atthe 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.

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

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 onthe proposed rule or the FAA's determination of the cost to the public.

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 entitiesunder 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.

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