Mooney M20V Acclaim Ultra, Руководство по эксплуатации для пилотов

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MOONEY
M20V ACCLAIM ULTRA
SECTION VII
AIRPLANE AND SYSTEM DESCRIPTION
7 - 3
AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE - 03-16-2017
INTRODUCTION
Acquiring a working knowledge of the aircraft’s controls and equipment is one of your important
first steps in developing a fully efficient operating technique. This Airplane and Systems Section
describes location, function, and operation of systems’ controls and equipment. It is recom-
mended that you, the pilot, familiarize yourself with all controls and systems while sitting in the
pilot’s seat and rehearsing the systems operations and flight procedures portions of this manual.
AIRFRAME
The M20V is a metal/composite, low wing, high performance airplane. The fuselage has a
welded, tubular- steel cabin frame covered with non- structural composite and aluminum skin.
Access to the cabin is provided by pilot and co-pilot side doors located on each side of the fuse-
lage. A door is provided aft of the rear seat for access to the baggage compartment. The aft fuse-
lage, tailcone, is of semi- monocoque construction.
Seating in the cabin is provided for the pilot and three passengers.
The M20V has a tapered, full- cantilever, aluminum construction, laminar- flow type wing. The
airfoil varies from a NACA 63
2
- 215 at the wing root to a NACA 64
1
- 412 at the wing tip, modified
by an inboard leading edge cuff. Wrap- around stretched formed skins cover the wing; flush rivet-
ing is used on the forward, top and bottom two thirds of the wing chord to provide benefit of lami-
nar flow aerodynamics.
The empennage consists of the vertical and horizontal stabilizer assembly and the rudder and
elevator surfaces. The entire empennage pivots around attaching points on the aft fuselage to
provide pitch attitude trim.
The tricycle landing gear allows maximum vision and ground maneuvering. Hydraulic disc
brakes and a steerable nose wheel aid in directional control during taxiing and ground opera-
tions. The landing gear is electrically retracted and extended. A gear warning VOICE ALERT, a
gear position indicator on the floorboard and a green “GEAR DOWN” annunciation helps pre-
vent in advertent gear-up landings. A manual emergency gear extension system is provided in
the event of electrical failure.
FLIGHT CONTROLS DESCRIPTION
The aircraft has dual flight controls and can be flown from either the pilot or co- pilot seat. Dual
pairs of foot pedals control rudder and nose wheel steering mechanisms. Push- pull tubes actu-
ate all- metal flight control surfaces. Rod- end bearings are used through out the flight control
systems. These bearings are simple and require little maintenance other than occasional lu-
brication. Longitudinal pitch trim is achieved through a trim control system that pivots the entire
empennage around tailcone attachment points.
AILERON SYSTEM
The ailerons are of all- metal construction with beveled trailing edges. Three hinges of
machined, extruded aluminum attach each aileron to aft wing spar outboard of wing flaps. The
ailerons link to the control wheel through push- pull tubes and bellcranks. Counterweights bal-
ance the ailerons. A spring- loaded interconnect device indirectly joins aileron and rudder control
systems to balance in lateral stability during flight maneuvers.