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Mooney M20R Airplane Flight Manual Supplement

Bendix/king kfc 225 automatic flight control system
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See also: Service Maintenance Manual , Pilot Operating Handbook
Model ____________________________________________________
Reg. No.__________________________________________________
Serial No._________________________________________________
This supplement must be attached to the FAA Approved Airplane Flight Manual
when the Bendix/King KFC 225 Automatic Flight Control System is installed in
accordance with Mooney Aircraft Corporation Drawing No. 830139. The information
contained herein supplements or supersedes the basic manual only in those areas
listed herein. For limitations, procedures, and performance information not
contained in this supplement; consult the basic Airplane Flight Manual.
FAA APPROVED:____________________________________________
Michele M. Owsley - Manager
Aircraft Certification Office
DOT/FAA ASW -150
2601 Meacham Boulevard
Fort Worth, Texas 76137-0150
Date of Approval: - 2 November, 1999
Revision A - 15 August, 2000
MOONEY AIRCRAFT CORPORATION
LOUIS SCHREINER FIELD
KERRVILLE, TEXAS
FAA APPROVED
AIRPLANE FLIGHT MANUAL SUPPLEMENT
M20M, M20R, M20S
BENDIX/KING KFC 225
AUTOMATIC FLIGHT CONTROL SYSTEM
78028
FOR
WITH
Page 1 of 20

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Summary of Contents for Mooney M20R

  • Page 1 This supplement must be attached to the FAA Approved Airplane Flight Manual when the Bendix/King KFC 225 Automatic Flight Control System is installed in accordance with Mooney Aircraft Corporation Drawing No. 830139. The information contained herein supplements or supersedes the basic manual only in those areas listed herein.
  • Page 2 MOONEY AIRCRAFT CORPORATION LOUIS SCHREINER FIELD KERRVILLE, TEXAS 78028 LOG OF REVISIONS Rev. Revised Description Date Pages of Revision Approved Log of Revision page entry 8/15/00 Added information on Altitude Capture Alert annunciation. The revised portions of affected pages are indicated by vertical black lines in the margin.

  • Page 3: Table Of Contents

    TABLE OF CONTENTS SECTION PAGE GENERAL .................... 4 LIMITATIONS ..................6 IIIA EMERGENCY PROCEDURES ............6 IIIB ABNORMAL PROCEDURES ............... 8 NORMAL PROCEDURES ..............10 PERFORMANCE ................20 WEIGHT & BALANCE ................ 20 AIRPLANE & SYSTEM & DESCRIPTION .......... 20 VIII HANDLING, SERVICING &...

  • Page 4: General

    Bendix/King KFC 225 Automatic Flight Control System. The limitations presented are pertinent to the operation of the KFC 225 system as installed in the Mooney M20M, M20R, and M20S airplane; the Autopilot must be operated within the limitations herein specified.
  • Page 5 LABEL FUNCTION COMPUTER Supplies power to the KFC 225 Computer. SERVO Supplies power to the autopilot pitch, roll and pitch trim servos. ALERT Supplies sonalert power for autopilot disconnect tone and separate TRIM/FAIL annunciator when installed. Supplies power to the KCS 55A Compass System. ENCDR Supplies power to the Altitude Encoder.

  • Page 6: Limitations

    SECTION II — LIMITATIONS A. The entire preflight test procedure outlined under Section 4, paragraph A of this supplement, including steps 1 through 7, must be successfully completed prior to each flight. Use of the autopilot or manual electric trim system is prohibited prior to completion of these tests.\ B.
  • Page 7 NOTE: The RADIO MASTER switch may be used as an alternate means of removing all power from the autopilot and electric trim systems. If necessary, perform Steps 1 through 3 above, then turn the AVIONICS MASTER switch OFF before locating the SERVOS circuit breaker.

  • Page 8: Iiib Abnormal Procedures

    following a manual electric trim malfunction is regaining control of the airplane Grasp the control wheel firmly and press and hold down the A/P DISC/TRIM INTER switch. Pull the SERVOS circuit breaker. 3. Note that the emergency procedure for any malfunction is essentially the same: —- immediately grasp the control wheel firmly to regain airplane control while pressing and holding the A/P DISC/TRIM INTER switch down,...
  • Page 9 B. A red P or R annunciation on the face of the autopilot computer. 1. A red P annunciation is an indication that the pitch axis of the autopilot has been disabled and the autopilot cannot be engaged. NOTE: If the red P lamp was the result of some abnormal accelerations on the airplane, the annunciation should extinguish within approximately one minute and normal use of the autopilot will be re-established.

  • Page 10: Normal Procedures

    3. Loss of the HSI — Heading, navigation and approach modes inoperative. 4. Loss of altitude encoding — preselect altitude captures and altitude alerting inoperative. Note a dashed altitude display will appear on the autopilot computer. SECTION IV — NORMAL PROCEDURES A.
  • Page 11 B. FLIGHT DIRECTOR OPERATION The flight director modes of operation are the same as those used for autopilot operations except that the autopilot is not engaged and the pilot must maneuver the aircraft to satisfy the flight director commands. Note that the flight director will always be in view when the autopilot is engaged.
  • Page 12 engaged as the autopilot will run the pitch trim to oppose control wheel movement. A mistrim of the airplane, with accompanying large elevator control forces, will result if the pilot manipulates the control wheel manually while the autopilot is engaged. 3.
  • Page 13 2) Airplane ..........ESTABLISH climb or descent necessary to intercept the selected altitude. Note ALT CAP annunciated during level off at the pre-selected altitude. 3) ALTITUDE SELECT MODE (ARM) button ........PUSH to automatically disarm or arm altitude capture. NOTE Pre-selected altitude captures are not recommended on non- precision approaches to capture the MDA.
  • Page 14 b. Heading Hold 1) Heading Selector Knob ............SET BUG to desired heading 2) HDG Mode Selector Button ............PRESS Note HDG mode annunciator ON. Autopilot will automatically turn the aircraft to the selected heading. c. Command Turns (Heading Hold mode ON) 1) Heading Selector Knob ...........
  • Page 15 NOTE When operating in the NAV or APR mode with VOR as the selected navigation sensor, changes in the selected course which result in a D-Bar deviation of greater than 50% may result in the autopilot not tracking the signal. It is recommended that the new course be manually captured using the heading bug and the NAV ARM or APR ARM modes.
  • Page 16 NOTE If tracking the ILS course outbound as part of the missed approach procedure is desired, use the NAV mode to prevent inadvertent GS coupling. c. AUTOPILOT-after aircraft is in trim ....ENGAGE as desired 11. Before Landing a. A/P DIS/TRIM INTER Switch ..........PRESS to disengage autopilot.
  • Page 17 1. PITCH AXIS, (P) ANNUNCIATOR — When illuminated, indicates failure of the pitch axis and will lead to disengagement of the autopilot. (Will also illuminate during short term vertical accelerations in excess of +1.6g or less than +0.4g which may not cause autopilot disengagement.) 2.
  • Page 18 continuously. If VS mode is active, the initial button press will bring up the commanded vertical speed in the display. Subsequent immediate button presses will increment the vertical speed command either up or down at the rate of 100 ft/ min per button press, or at the rate of approximately 300 ft/min per second if held continuously.
  • Page 19 16. ALTITUDE ALERT (ALERT) ANNUNCIATION —- Illuminates as a solid alert in the region of from 1000 to 200 feet from the selected altitude if the airplane was previously outside of this region. Flashes (1) for two seconds the first time the airplane crosses the selected altitude and (2) flashes continuously in the 200 to 1000 feet region if the airplane was previously inside of this region (i.e., at the selected altitude).

  • Page 20: Vperformance

    23. HEADING SELECT KNOB Positions the heading bug on the compass card. (Located on the HSI). 24. TRIM/FAIL ANNUNCIATOR — Illuminates whenever the automated pre- flight self-test detects a pitch trim fault or a continuous monitoring system detects a pitch trim fault in flight. (Located in either the system annunciator panel or the pilot’s instrument panel.

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