MOONEY
M20TN - MODEL TYPE-S
SECTION VII
AIRPLANE AND SYSTEM DESCRIPTION
7 -- 4
AIRPLANE FLIGHT MANUAL
ORIGINAL ISSUE -- 04-02-2008
RUDDER SYSTEM
The rudder attaches to the aft, vertical fin spar at four hinge points. Push--pull tubes and
bellcranks link the rudder to the rudder pedals.
RUDDER TRIM SYSTEM
The M20TN is equipped with an electric rudder trim system which allows the pilot to trim out
much of the rudder force required for take off, climb, cruise and descent. The system is a
“bungee” type spring assembly, attached to the rudder control system and driven by an electric
motor. The trim system is operated by a split, toggle switch located above the throttle on the pi-
lot’s panel. The split switch is a safety measure that greatly reduces the possibility of a runaway
trim situation. Rudder force varies from negligible (with trim to the far right ) to mild (with trim set
to the third segment from the right). Cruise setting will result in the trim indicator being slightly left
of neutral. A high speed descent will result in an even more left of neutral position. The Rudder
Trim indicator is located on the Garmin GDU 10(XX) Mutli-Function Flight Display (MFD). The
indicator depicts the position (right/left) of the rudder trim setting. Actual trim position is shown
using a blue inverted triangle. The “takeoff” rudder trim position is shown in white.
ELEVATOR SYSTEM
Elevator construction is essentially the same as that of the rudder. Both elevators attach to the
horizontal stabilizer at four hinge points. Push--pull tubes and bellcranks link the elevators to the
control wheel. A down--spring located in the tailcone and a bobweight located forward of the con-
trol column help create desirable stability characteristics. A factory set, fixed trim tab spans the
length of the elevator. Counterweights balance the elevators.
PITCH TRIM SYSTEM
Pitch trim is electrically actuated with a split toggle switch on the control wheel for autopilot
equipped aircraft. The pitch trim may be manually actuated by a wheel located on the floor be-
tween the pilot and co--pilot seat. Trim actuation turns a ball screw that increases or decreases
the pitch angle of the entire empennage. The elevator trim position indicator (located on the
MFD) depicts the position (up/down) of the pitch trim setting. Trim position is shown by a blue
triangle. A white block indicates “take--off” pitch trim position.
WING FLAPS
The wing flaps are electrically operated and interconnected through a torque tube and
bellcranks. Total flap area is 17.98 square feet.
Nominal travel is 0 to 33
o
. Limit switches prevent travel beyond these limits. Wing flap position is
controlled by a pre--select switch located on the lower center console. The flap position indicator
(located on the MFD) shows the current position of the flaps. The three possible positions, up,
take-off and down are depicted in cyan as “UP,” “T/O” and “DN,” respectively. During flaps posi-
tion transition, “///” is displayed in the window. Generally, aircraft trim requirements will change
with use of the flaps. Lowering of the flaps will cause a nose down pitching condition which can be
easily corrected by application of nose up trim. Conversely, retraction of the flaps, from a
trimmed flight condition, will cause a nose up pitching condition. Use of flaps should always be
within the operational limits established in SECTION II. The flaps are very effective in lowering
landing speed and can be used to slow the aircraft to approach speeds.
INSTRUMENT PANEL
The instrument panel has been designed to incorporate the G1000 Integrated Cockpit. All Com-
munications, Navigation, Engine Instruments, and System annunciations have been integrated
into a custom design package specifically for the M20TN series aircraft.
Engine and electrical switches are located on the left side of the switch panel. Nav, strobe, recog-
nition/landing and taxi light switches are located on the overhead switch panel.
Revision B -- 11-21-2014
