AD 97-10-14

97-10-14 RAYTHEON AIRCRAFT COMPANY (formerly Beech Aircraft Corporation): Amendment 39-10026; Docket No. 96-CE-27-AD.

Applicability: Model 1900D airplanes (serial numbers UE-1 through UE-215), certificated in any category.

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 (e) 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 50 hours time-in-service (TIS) after the effective date of this AD, and thereafter as indicated in the body of this AD, unless already accomplished.

To prevent separation of the stabilons from the airplane, which could cause loss of airplane stability during flight, accomplish the following:

(a) Inspect the left and right stabilon attachment angles for proper thickness, which is .090-inch thick in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Beechcraft Mandatory Service Bulletin (MSB) No. 2651, Issued: January 1996.

(b) If the attachment angles are not the correct thickness and measure only .071-inch thick, accomplish the following in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Beechcraft MSB No. 2651, Issued: January 1996:

(1) Repetitively inspect the stabilon attachment angles for cracks, at intervals not to exceed 50 hours TIS, until cracks are visible;

(2) When cracks are visible, prior to further flight, replace the attachment angles with attachment angles of the correct thickness (.090-inch thick); and

(3) If no cracks are visible during any of the inspections required by this AD, within the next 600 hours TIS after the effective date of this AD, replace the 0.071-inch thick attachment angles with 0.090-inch thick attachment angles.

(c) Replacing the 0.071-inch thick stabilon attachment angles with 0.090-inch thick attachment angles at any time after the effective date of this AD terminates the repetitive inspection requirements of this AD.

(d) 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.

(e) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita AircraftCertification Service, 1801 Airport Rd., Rm. 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 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.

(f) The inspections and replacements required by this AD shall be done in accordance with Beechcraft Mandatory Service Bulletin No. 2651, Issued: January 1996. 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 Raytheon Aircraft Company, 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., suite 700, Washington, DC.

(g) This amendment becomes effective on July 7, 1997.