Flight Controls; Ground Control; Wing Flap System; Trim Systems - Cessna Hawk XP R172K Pilot Operating Handbook

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SECTION 7
AIRPLANE
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SYSTEMS DESCRIPTIONS
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MODEL R1'!':'i
consist s of formed leading edge skins, a forward spar, aft channel, n I'
torque tube and bellcrank, left upper and lower "V" type corrugated
skins, and right upper and lower "V" type corrugated skins incorporut
ing a trailing edge cut-out for the trim tab. The elevator trim tab
COil
sists of a spar, rib, and upper and lower "V" type corrugated skins.
The leading edge of both left and right elevator tips incorporate exten
sions which contain balance weights.
FLIGHT CONTROLS
The airplane's flight control system consists of conventional ailer
on, rudder, and elevator control surfaces (see figure 7-1). The control
surfaces are manually operated through mechanical linkage using a
control wheel for the ailerons and elevator, and rudder/brake pedals for
the rudder.
TRIM SYSTEMS
Manually-operated rudder and elevator trim systems are provided.
Rudder trimming is accomplished through a bun gee connected to the
rudder control system and a trim lever, mounted on the control pedes-
tal. Rudder trimming is accomplished by lifting the trim lever up to
clear a detent, then moving it either left or right to the de sired trim
position. Moving the trim lever to the right will trim the airplane
nose-right; conversely, moving the lever to the left will trim the air-
plane nose-left. Elevator trimming is accomplished through the eleva-
tor trim tab by utilizing the vertically mounted trim control wheel.
Forward rotation of the trim wheel will trim nose-down; conversely, aft
rotation will trim nose-up.
II\lSTRUMENT PANEL
The instrument panel (see figure 7-2) is designed around the basic
"'1''' configuration. The gyros are located immediately in front of the
pilot, and arranged vertically over the control column. The airspeed
indicator and altimeter are located to the left and right of the gyros
respectively. The remainder of the flight instruments are located
around the basic "'1'''. Engine instruments and fuel quantity indicators
are near the left edge and lower portion of the instrument panel. Avio-
nics equipment is stacked approximately on the centerline of the panel,
with the right side of the panel containing space for additional instru-
ments and avionics equipment. A subpanel under the primary instru-
ment panel contains the fuel shutoff valve knob, primer, master switch,
auxiliary fuel pump and ignition switches, circuit breakers, and electri-
('I':SSNA
M()DEL R172K
SECTION 7
AIRPLANE & SYSTEMS DESCRIPTIONS
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switches on the left side, with the engine controls, light intensity
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«ntro.ls, and alternate static air control in the center, over the control
I,,'d()stal. The right side of the subpanel contains the wing I'la.p switch
I.,vm and position indicator, cabin heat and air controls, cigar lighter,
IIl1dmap compartment. A pedestal, installed below the subp ano l, con-
ill.IIlSthe elevator trim control wheel and indicator, microphone
liI'lI.eket, cowl flap control lever, and rudder trim control lever. 1'1. f uel
''''Ioctor valve handle is located at the base of the pedestal. A parking
liruke handle is mounted below the subpanel in front of the pilot.
For details concerning the instruments, switches, circuit breakers,
uud controls on this panel, refer in this section to the description of the
uvstems to which these items are related.
GROUND CONTROL
Effective ground control while taxiing is accomplished through
nose wheel steering by using the rudder pedals; left rudder pedal to
ilteer left and right rudder pedal to steer right. When a rudder pedal is
depressed, a spring-loaded steering bun gee (which is connected to the
nose gear and to the rudder bars) will turn the nose wheel through an
arc of approximately 10° each side of center. By applying either left or
right brake, the degree of turn may be increased up to 30° each si.de of
center.
Moving the airplane by hand is most easily accomplished by att-
aching a tow bar to the nose gear strut. If a tow bar is not available, or
pushing is required, use the wing struts as push points. Do not use the
vertical or horizontal surfaces to move the airplane. If the airplane is
to be towed by vehicle, never turn the nose wheel more than 30° either
side of center or structural damage to the nose gear could result.
The minimum turning radius of the airplane, using differential
braking and nose wheel steering during taxi, is approximately 27 feet
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1/2inches. To obtain a minimum radius turn during ground handl.ing,
the airplane may be rotated around either main landing gear by preas-
ing down on a tailcone bulkhead just forward of the horizontal stabiliz-
er to raise the nose wheel off the ground.
WING FLAP SYSTEM
The wing flaps are of the single-slot type (see figure 7-3), and are
extended or retracted by positioning the wing flap switch lever on the
instrument panel to the des ired flap deflection position. The switch