Mooney M20V Acclaim Ultra, Руководство по эксплуатации для пилотов

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MOONEY
M20V ACCLAIM ULTRA
SECTION VII
AIRPLANE AND SYSTEM DESCRIPTION
7 - 4
AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE - 03-16-2017
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 M20V 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 spring loaded momentary switch, located above the throttle on the pilot’s
panel. The momentary switch is a safety measure that greatly reduces the possibility of a run-
away 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

. Limit switches prevent travel beyond these limits. Wing flap position is
controlled by a pre- select switch located on the lower instrument panel. The flap position indica-
tor (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.