Mooney M20R, M20M, M20S Airplane Flight Manual Supplement
MOONEY AIRCRAFT CORPORATION
LOUIS SCHREINER FIELD
KERRVILLE, TEXAS 78028
FAA APPROVED
AIRPLANE FLIGHT MANUAL SUPPLEMENT
FOR
M20M, M20R, M20S
WITH
BENDIX/KING KFC 225
AUTOMATIC FLIGHT CONTROL SYSTEM
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 Page 1 of 20
MOONEY AIRCRAFT CORPORATION
LOUIS SCHREINER FIELD
KERRVILLE, TEXAS 78028
LOG OF REVISIONS
Rev. Revised Description FAA Date
No. Pages of Revision Approved
A
2
11
Log of Revision page entry
Added information on Altitude
Capture Alert annunciation.
8/15/00
The revised portions of affected pages are indicated by vertical black lines in the margin.
Rev. A 8-00
TABLE OF CONTENTS
SECTION PAGE
I GENERAL ............................................................................................ 4
II LIMITATIONS ....................................................................................... 6
IIIA EMERGENCY PROCEDURES ............................................................6
IIIB ABNORMAL PROCEDURES ............................................................... 8
IV NORMAL PROCEDURES .................................................................. 10
V PERFORMANCE ............................................................................... 20
VI WEIGHT & BALANCE ........................................................................ 20
VII AIRPLANE & SYSTEM & DESCRIPTION .......................................... 20
VIII HANDLING, SERVICING & MAINTENANCE ..................................... 20
IX SUPPLEMENTAL DATA .................................................................... 20
X SAFETY TIPS ....................................................................................20
SECTION I — GENERAL
This manual is provided to acquaint the pilot with the limitations as well as normal
and emergency operating procedures of the 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.
The KFC 225 Automatic Flight Control System is certified in this airplane with 3axis Autopilot control: pitch, roll and yaw.
The KFC 225 system provides the pilot with the following features:
pitch attitude hold (PIT), vertical speed hold (VS), altitude hold preselect (ALT
ARM), altitude capture (ALT CAP), altitude hold (ALT), altitude alerting, and go
around (GA) in pitch; roll attitude hold (ROL), heading hold (HDG), navigation
course capture (NAV ARM), navigation course tracking (NAV), approach course
capture (APR ARM), and back course approach tracking (REV) in the roll axis.
Control wheel steering (CWS) allows synching of the pitch axis modes (except
glideslope) and maneuvering the aircraft by hand if desired.
The KFC 225 system has an electric pitch trim system that provides auto-trim
during autopilot operation and manual electric trim (MET) for the pilot when the
autopilot is not engaged. Trim faults are monitored and annunciated both visually
and aurally.
An automatic preflight self-test begins with initial power application to the
autopilot. A lockout device prevents autopilot engagement and MET operation
until the system has successfully passed preflight self-tests.
The following circuit breakers are used to protect the following elements of the
KFC 225 Automatic Flight Control System:
The following conditions will cause the Autopilot to automatically disengage:
A. Electrical Power failure.
B. Internal Automatic Flight Control System failure.
C. Roll rates in excess of 14o per second except when the CWS button is
depressed.
D. Pitch rates in excess of 6o per second except when the CWS button is
depressed.
E. Pitch accelerations in excess of +1.6 g or less than +0.4g will cause only
the autopilot servo clutch to disengage, (Sustained accelerations will cause
auto pilot disengagement except when the CWS button is depressed.)
The Radio Master switch supplies power to the avionics bus bar for the radio and
autopilot circuit breakers.
The airplane MASTER switch function is unchanged and can be used in
conjunction with the alternator switches in an emergency to shut off electrical
power to all automatic flight control systems while the problem is being isolated.
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.
HSI Supplies power to the KCS 55A Compass System.
ENCDR Supplies power to the Altitude Encoder.
ANN Supplies power to the TRIM FAIL annunciation when
the original equipment annunciator panel is installed.
AUDIO Supplies power to the autopilot speaker alerting and
autopilot headphone alerting.
The following voice messages will be annunciated as conditions warrant:
1. “TRIM IN MOTION, TRIM IN MOTION...” - Elevator trim running for more than
5 seconds.
2. “CHECK PITCH TRIM” - An out of trim condition has existed for 16 seconds.
a. Airplane control Wheel - GRASP FIRMLY, press CWS and check for an
out of pitch trim condition. Manually retrim as required.
b. CWS button - RELEASE.
c. AUTOPILOT OPERATION - CONTINUE if satisfied that the out of trim
condition was temporary. DISCONTINUE if evidence indicates a failure
of the auto trim function.
The following optional voice messages will be annunciated if the system is
configured for voice messaging:
1 “ALTITUDE” - 1000 feet before approaching selected altitude.
2 “LEAVING ALTITUDE” - 200 feet away, departing selected altitude.
3 “AUTOPILOT” - Autopilot has disengaged, either through pilot action or
automatically.
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. During autopilot operation, a pilot with seat belt fastened must be seated at the
left pilot position.
C. The autopilot must be OFF during Takeoff and Landing.\
E. Autopilot maximum airspeed limitations:—— 180 KIAS.
Autopilot minimum airspeed limitation:——- 80 KIAS.
F. Altitude Select captures below 800 feet AGL are prohibited.
G. The autopilot must be disengaged below 200 feet AGL during approach
operations and below 800 feet AGL for all other phases of flight.
H. Overriding the autopilot to change pitch or roll attitude is prohibited.
(Disengage the autopilot or press CWS while maneuvering).
I. The SERVOS circuit breaker must be pulled following any in-flight illumination
of the red TRIM/FAIL warning light,but only after first completing the
Emergency Procedures (Section IIIA) paragraph A. The manual electric trim
and autopilot autotrim systems will be disabled with the circuit breaker pulled.
(The red TRIM/FAIL warning will illuminate normally during preflight self-test If
the TRIM FAIL light remains illuminate after preflight self-test, the SERVOS
circuit breaker must be PULLED. Do not operate autopilot with flaps extended
beyond the Take-Off position.)
J. Required Placards:
1. Above Radio Stack
AUTOPILOT AND
ELECTRIC TRIM
PREFLIGHT TESTS
MUST BE CONDUCTED
PRIOR TO EACH FLIGHT.
SECTION III A — EMERGENCY PROCEDURES
The four-step procedure listed under paragraph A should be among the basic
airplane emergency procedures that are committed to memory. It is important
that the pilot be proficient in accomplishing all four steps without reference to this
manual.
A. In case of Autopilot, Autopilot Trim, or Manual Electric Trim malfunction
(accomplish Item 1 & 2 simultaneously):
1. Airplane Control Wheel ................GRASP FIRMLY, regain aircraft control.
2. A/P DISC/TRIM INTER Switch ..................................... PRESS and HOLD
throughout recovery until Step 4 has been accomplished.
3. AIRCRAFT .................................................RETRIM manually as needed.
4. SERVOS circuit breaker ....................................................................PULL
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