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Airworthiness directives › 98-08-20

AD 98-08-20 Airworthiness Directives; AlliedSignal Aerospace Bendix/King Model KSA 470 Autopilot Servo Actuators, Part Numbers 065-0076-10 Through 065-0076-15

1998-06-02
1998-04-17
39-10469
97-CE-74-AD
Appliance
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Makes named: bendix. Read the applicability below — it usually turns on serial or part numbers too.

Applicability*9

Bendix/King Model KSA 470 Autopilot Servo Actuators; part numbers 065-0076-10 through 065-0076-15; serial numbers 0001 through 3081; that are installed on, but not limited to, the following aircraft, certificated in any category: Note 1: This subject is addressed in AlliedSignal Bendix/King Service Bulletin No. SB KSA 470-3, dated May 1997. This service bulletin references serial number 3082. Regardless of this reference, serial number 3082 is not affected by this AD. ---------------------------------------------------------------------------------------------------------------- KSA 470 part Aircraft FD/AP system No. Location ---------------------------------------------------------------------------------------------------------------- Raytheon 400 Series.................... KFC 400....................... 065-0076-11 Yaw Axis. 065-0076-15 Roll Axis. Raytheon 200 Series.................... KFC 400....................... 065-0076-11 Yaw Axis. Raytheon 300 Series.................... KFC 400....................... 065-0076-15 Yaw Axis. Dassault Falcon 20..................... KFC 400....................... 065-0076-15 Pitch Axis. 065-0076-15 Roll Axis. Fairchild C26A/C26B.................... KFC400........................ 065-0076-11 Yaw Axis. Fairchild SA227-AC/AT/BC/CC/DC KFC400........................ 065-0076-15 Roll Axis. Learjet 31A............................ KFC 3100...................... 065-0076-12 Pitch Axis. 065-0076-14 Yaw Axis. 065-0076-15 Roll Axis. Lockheed S-2 Tracker................... KFC 325....................... 065-0076-10 Special. Piper 400LS and PA-42-1000............. KFC 400....................... 065-0076-15 Yaw Axis. ---------------------------------------------------------------------------------------------------------------- Note 2: This AD applies to each airplane identified in the preceding applicability provision that has one of the affected actuators installed, 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 (d) 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 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent the servo actuator roll pins from becoming loose; falling out; becoming lodged in the output shaft clutch mechanism; and preventing this mechanism from disengaging, which could result in increased effort by the pilot to control the aircraft and possible loss of control of the affected flight control axis, accomplish the following: (a) Replace the autopilot servo actuator with an actuator that incorporates Mod 3 in accordance with the applicable maintenance manual. This modification changes the size of the servo actuator roll pin holes to assure that the pins do not become loose and fall out. (b) As of the effective date of this AD, no person may install, on aircraft, one of the affected servo actuators that does not incorporate Mod 3. (c) 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. (d) An alternative method of compliance or adjustment of the compliance times 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 3: 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 documents referred to herein upon request to AlliedSignal Aerospace, Technical Publications, Department 65-70, P.O. Box 52170, Phoenix, Arizona 85072-2170; or may examine these documents at the FAA, Central Region, Office [[Page 19178]] of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (f) This amendment becomes effective on June 2, 1998. Issued in Kansas City, Missouri, on April 8, 1998. Marvin R. Nuss, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-10053 Filed 4-16-98; 8:45 am] BILLING CODE 4910-13-U

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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1