Cessna Cardinal RG User manual

Serial Number 177RG0073
Speed in Knots

PERFORMANCE - SPECIFICATIONS
-------------------------------------------------------------------------------------------------- * Cardinal RG -
GROSS WEIGHT ..........................................................................................2800 lbs
SPEED, BEST POWER MIXTURE:
Top Speed at Sea Level ..................................................153 kts
Cruise, 75% Power at 7000 ft .................................144 kts
RANGE, NORMAL LEAN MIXTURE:
Cruise, 75% Power at 7000 ft .....................................664 nm
50 Gal., No Reserve .......................................................4. 6 hours
143 kts
Optimum Range at 10, 000 ft ..........................................777 nm
50 Gal., No Reserve ......................................................6.6 hours
117 kts
RATE OF CLIMB AT SEA LEVEL .................................860 fpm
SERVICE CEILING ..........................................................16, 900 ft
TAKE-OFF:
Ground Run .....................................................................................890 ft
Total Distance Over 50-Foot Obstacle1 .......................585 ft
LANDING:
Ground Roll ...........................................................................730 ft
Total Distance Over 50-Foot Obstacle .............................1350 ft
STALL SPEEDS:
Flaps Up, Power Off ..........................................................................57 kts
Flaps Down, Power Off ...........................................49 kts
EMPTY WEIGHT: (Approximate) ............................................1630 lbs
USEFUL LOAD .............................................................................................1170 lbs
BAGGAGE .....................................................................................................120 lbs
WING LOADING: Pounds/Sq Foot ..................................................16.1
POWER LOADING: Pounds/HP ......................................................14.0
FUEL CAPACITY: .................................................................51.0 gal.
OIL CAPACITY ................................................................................8 qts.
PROPELLER: Constant Speed (Diameter) ................78 inches
ENGINE:
Lycoming Fuel Injection Engine .................................................IO-360-A1B6
200 rated HP at 2700 RPM
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* This manual covers operation of the Cardinal RG which is certificated as Model 177RG under FAA
Type Certificate No. A20CE.

CONGRATULATIONS ...
Welcome to the ranks of Cessna owners! Your Cessna
has been designed and constructed to give you the most
in performance, economy, and comfort. It is our
desire that you will find flying it, either for business or
pleasure, a pleasant and profitable experience.
This Owner's Manual has been prepared as a guide to
help you get the most pleasure and utility from your
Cardinal RG. It contains information about your
Cessna's equipment, operating procedures, and perfor-
mance; and suggestions for its servicing and care. We
urge you to read it from cover to cover, and to refer to
it frequently.
Our interest in your flying pleasure has not ceased with
your purchase of a Cessna. World-wide, the Cessna
Dealer Organization backed by the Cessna Service
Department stands ready to serve you. The following
services are offered by most Cessna Dealers:
FACTORY TRAINED PERSONNEL to provide
you with courteous expert service.
FACTORY APPROVED SERVICE EQUIPMENT
to provide you with the most efficient and
accurate workmanship possible.
A STOCK OF GENUINE CESSNA SERVICE
PARTS on hand when you need them.
THE LATEST AUTHORITATIVE
INFORMATION FOR SERVICING CESSNA
AIRPLANES, since Cessna Dealers have all of
the Service Manuals and Parts Catalogs, kept
current by Service Letters and Service News
Letters, published by Cessna Aircraft Company.
We urge all Cessna owners to use the Cessna Dealer
Organization to the fullest.
A current Cessna Dealer Directory accompanies your
new airplane. The Directory is revised frequently, and
a current copy can be obtained from your Cessna
Dealer. Make your Directory one of your cross-
country flight planning aids; a warm welcome awaits
you at every Cessna Dealer.
i

ii

TABLE OF CONTENTS
------------------------------------------------------------------------------Page
SECTION I - OPERATING CHECK LIST.......1-1
SECTION II - DESCRIPTION AND
OPERATING DETAILS ...................2-1
SECTION III - EMERGENCY PROCEDURES .3-1
SECTION IV - OPERATING IMITATIONS.. . 4-1
SECTION V - CARE OF THE AIRPLANE.......5-1
OWNER FOLLOW-UP SYSTEM......5-11
SECTION VI - OPERATIONAL DATA ...........6-1
SECTION VII - OPTIONAL SYSTEMS .........7-1
ALPHABETICAL INDEX ....................................Index-1
iii

Intentionally Left Blank

Section I
OPERATING CHECK LIST
One of the first steps in obtaining the utmost
performance, service, and flying enjoyment from your
Cessna is to familiarize yourself with your airplane's
equipment, systems, and controls. This can best be
done by reviewing this equipment while sitting in the
airplane. Those items whose function and operation
are not obvious are covered in Section II.
Section I lists, in Pilot's Check List form, the steps
necessary to operate your airplane efficiently and
safely. It is not a check list in its true form as it is
considerably longer, but it does cover briefly all of the
points that you should know for a typical flight.
The flight and operational characteristics of your
airplane are normal in all respects. There are no
"unconventional" characteristics or operations that
need to be mastered. All controls respond in the
normal way within the entire range of operation. All
airspeeds mentioned in Sections I, n and in are
indicated airspeeds. Corresponding calibrated
airspeed may be obtained from the Airspeed Correction
Table in Section VI.
BEFORE ENTERING THE AIRPLANE.
(1) Make an exterior inspection in accordance with
figure 1-1.
1-1

1-2

1-3

BEFORE STARTING THE ENGINE.
(1) Seats, Seat Belts and Shoulder Harnesses - Adjust and lock.
(2) Fuel Shutoff Valve Handle - Check "ON" position (forward).
(3) Radios and Electrical Equipment - "OFF."
(4) Brakes - Test and set.
(5) Cowl Flaps - Open (move lever out of locking hole to
reposition).
(6) Landing Gear Position Handle - Check in "DWN" position.
STARTING THE ENGINE.
(1) Mixture - Idle cut-off (pulled full out).
(2) Propeller - High RPM.
(3) Throttle - Open 1/4 inch.
(4) Master Switch - "ON."
(5) Auxiliary Fuel Pump - "ON."
(6) Mixture - Advance to 4 to 6 gal/hr; then retard to idle cut-off.
NOTE
If the engine is warm, or flooded, omit priming
procedure step 6.
(7) Propeller Area - Clear.
(8) Ignition Switch - "START" (release to "BOTH" when
engine starts).
(9) Mixture - Advance smoothly to full rich when engine fires.
(10) Throttle - Reset to desired idle speed.
(11) Oil Pressure - Check.
(12) Auxiliary Fuel Pump - "OFF."
BEFORE TAKE-OFF.
(1) Parking Brake - Set.
(2) Flight Controls - Check for free and correct movement.
(3) Stabilator and Rudder Trim - Take-off setting
(4) Fuel Shutoff Valve Handle - "ON" (forward).
(5) Throttle Setting - 1800 RPM.
(6) Engine Instruments and Ammeter - Check.
(7) Magnetos - Check (RPM drop should not exceed 150 RPM in
either magneto or 50 RPM differential between magnetos) .
(8) Propeller - Cycle from high to low RPM; return to high RPM
(full in).
(9) Suction Gage - Check (4.6 to 5.4 inches of mercury).
(10) Flight Instruments and Radios - Set.
(11) Navigation Lights, Flashing Beacon and Optional Strobe
Lights - "ON, " as required.
(12) Optional Autopilot or Wing Leveler - "OFF."
(13) Cabin Doors - Closed and locked.
1-4

TAKE-OFF.
NORMAL TAKE-OFF.
(1) Wing Flaps - 0° to 10° (10° preferred).
(2) Power - Full throttle (applied smoothly) and 2700 RPM.
(3) Mixture - Full rich (lean for field elevation per fuel flow
placard above 3000 feet).
(4) Aircraft Attitude - Lift nose wheel at 56 kts .
(5) Climb Speed - 65 to 74 kts .
(6) Brakes - Apply momentarily (when airborne).
(7) Landing Gear - Retract (in climb out).
(8) Wing Flaps - Retract (if extended).
MAXIMUM PERFORMANCE TAKE-OFF.
(1) Wing Flaps - 10°.
(2) Brakes - Apply.
(3) Power - Full throttle (applied smoothly) and 2700 RPM.
(4) Mixture - Lean for field elevation per fuel flow placard above
3000 feet.
(5) Brakes - Release.
(6) Aircraft Attitude - Lift nose wheel at 52 kts .
(7) Climb Speed - 62 kts until all obstacles are cleared; then set
up climb speed as shown in "MAXIMUM PERFORMANCE
CLIMB" check list.
(8) Brakes - Apply momentarily (when airborne).
(9) Landing Gear - Retract after obstacles are cleared.
(10) Wing Flaps - Retract after accelerating to at least 69 kts .
NOTE
Do not reduce power until landing gear and wing flaps
have been retracted.
CLIMB .
NORMAL CLIMB.
(1) Airspeed - 87 to 104 kts.
(2) Power - 25 inches manifold pressure, and 2500 RPM.
(3) Mixture - Full rich or leaned to 13 gal/hr.
(4) Cowl Flaps - "OPEN" as required.
MAXIMUM PERFORMANCE CLIMB.
(1) Airspeed - 82 kts at sea level to 79 kts at 10,000 feet.
(2) Power - Full throttle and 2700 RPM.
(3) Mixture - Lean for altitude per fuel flow placard.
(4) Cowl Flaps - Full "OPEN."
1-5

CRUISING.
(1) Power - 15 to 25 inches of manifold pressure and 2100 to
2500 RPM. Select combination to give no more than 75%
power.
(2) Stabilator and Rudder Trim - Adjust.
(3) Mixture - Lean for cruise fuel flow per Cessna Power
Computer or OPERATIONAL DATA, Section VI.
(4) Cowl Flaps - "CLOSED."
LET-DOWN.
(1) Mixture - Rich, (or lean for smooth engine operation).
(2) Power - As desired.
NOTE
With less than 10 inches of manifold pressure, avoid
continuous operation between 1400 and 1750 RPM.
(3) Cowl Flaps - "CLOSED."
BEFORE LANDING.
(1) Seats, Seat Belts and Shoulder Harnesses - Adjust and lock.
(2) Landing Gear - Extend (below 122 kts).
(3) Mixture - Rich.
(4) Propeller - High RPM (full-in).
(5) Airspeed - 69 to 78 kts (flaps up).
(6) Wing Flaps - As desired (0° to 10° below 130 kts, 10° to 30°
below 96 kts).
(7) Airspeed - 61 to 69 kts (flaps down).
(8) Stabilator and Rudder Trim - Adjust.
BALKED LANDING (GO-AROUND).
(1) Power - Full throttle and 2700 RPM.
(2) Wing Flaps - Retract to 20°.
(3) Upon reaching an airspeed of approximately 65 kts, retract
flaps slowly.
NORMAL LANDING.
(1) Touchdown - Main wheels first.
(2) Landing Roll - Lower nose wheel gently.
(3) Braking - Minimum required.
AFTER LANDING.
(1) Wing Flaps - Up.
(2) Cowl Flaps - "OPEN."
1-6

SECURING AIRCRAFT.
(1) Parking Brake - Set.
(2) Radios and Electrical Equipment - "OFF."
(3) Mixture - Idle cut-off (pulled full out).
(4) Ignition and Master Switch - "OFF."
(5) Control Lock - Installed.
1-7

1-8

Section II
DESCRIPTION AND OPERATING DETAILS
The following paragraphs describe the systems and equipment
whose function and operation is not obvious when sitting in the
airplane. This section also covers in somewhat greater detail some
of the items listed in Check List form in Section I that require
further explanation.
FUEL SYSTEM.
Fuel is supplied to the engine from two integral fuel bays, one
in each wing. Usable fuel in each bay, for all flight conditions, is
25.0 gallons when completely filled (a 22 gallon marker, in the
form of a series of small holes just inside the filler neck, is
provided to facilitate fueling to reduced fuel loads). With full
cabin loading, it may be necessary to reduce the fuel load to keep
the aircraft within the approved weight limits. (Refer to Section
IV for weight and balance control procedures.)
Fuel from each wing fuel bay flows through a reservoir tank,
auxiliary fuel pump with by-pass, and fuel shutoff valve to the
fuel strainer. From there, it is routed to an engine-driven fuel
pump which delivers the fuel under pressure to the fuel injection
unit. The continuous flow type fuel injector meters the fuel in
proportion to consumed air flow, through a vented nozzle at each
cylinder intake port. Manual mixture control and idle cut-off
functions are provided.
The auxiliary fuel pump is used primarily for priming the
engine before starting. Priming is accomplished through the
regular injection system.
If the auxiliary fuel pump switch is accidentally turned "ON"
(with master switch "ON" and mixture rich) with the engine
stopped, the intake manifolds will be flooded.
The auxiliary fuel pump is also used for vapor suppression in
hot weather. Normally, momentary use will be sufficient for vapor
2-1

suppression; however, continuous operation is permissible if
required. Turning on the auxiliary fuel pump with a normally
operating engine pump will result in only a very minor enrichment
of the mixture.
It is not necessary to have the auxiliary fuel pump operating
during normal take-off and landing, since gravity and the engine-
driven pump will supply adequate fuel flow to the fuel injector unit.
2-2

In the event of failure of the engine-driven pump, use of the
auxiliary fuel pump will provide sufficient fuel to maintain flight at
maximum continuous power.
NOTE
With low fuel (l/16th bay or less) a prolonged
powered steep descent (1000 feet or more)
should be avoided with more than 10° flaps to
prevent the possibility of fuel starvation
resulting from uncovering the fuel bay outlets.
If starvation should occur, leveling the nose
and turning on the auxiliary fuel pump should
restore engine power within 30 seconds.
For fuel system servicing information, refer to Lubrication
and Servicing Procedures in Section V.
ELECTRICAL SYSTEM.
Electrical energy is supplied by a 14-volt, direct-current
system powered by an engine-driven alternator (see figure 2-3).
The 12-volt battery is located aft of the rear cabin wall. Power is
supplied to all electrical circuits through a split bus bar, one side
containing electronic system circuits and the other side having
general electrical system circuits. Both sides of the bus are on at
all times except when either an external power source is
connected or the starter switch is turned on; then a power
contactor is automatically activated to open the circuit to the
electronic bus. Isolating the electronic circuits in this manner
prevents harmful transient voltages from damaging the transistors
in the electronic equipment.
MASTER SWITCH.
The master switch is a split-rocker type switch labeled
"MASTER, " and is "ON" in the up position and "OFF" in the
down position. The right half of the switch, labeled "BAT, "
controls all electrical power to the airplane. The left half, labeled
"ALT, " controls the alternator.
Normally, both sides of the master switch should be used
simultaneously; however, the "BAT" side of the switch could be
turned "ON" separately to check equipment while on the ground.
The "ALT" side of the switch, when placed in the "OFF" position,
removes the alternator from the electrical system. With this
switch in the "OFF" position, the entire electrical load is placed on
the battery, and all non-essential electrical equipment should be
turned off for the remainder of the flight.
2-3

AMMETER.
The ammeter indicates the flow of current, in amperes, from
the alternator to the battery or from the battery to the aircraft
electrical system. When the engine is operating and the master
switch is "ON," the ammeter indicates the charging rate applied to
the battery. In the event the alternator is not functioning or the
electrical load exceeds the output of the alternator, the ammeter
indicates the discharge rate of the battery.
2-4

CIRCUIT BREAKERS AND FUSES.
Most of the electrical circuits in the airplane are protected by
"push-to-reset" circuit breakers mounted on the right side of the
instrument panel. Exceptions to this are the battery contactor
closing (external power) circuit, and clock and optional flight
hour recorder circuits all having fuses mounted near the battery.
Also, the cigar lighter is protected by a manually-reset type
circuit breaker mounted directly on the back of the lighter behind
the pedestal.
When more than one radio is installed, the radio transmitter
relay (which is a part of the radio installation) is protected by the
navigation lights circuit breaker labeled "NAV LIGHTS". If a
malfunction in the navigation lights system causes the circuit
breaker to open, de-activating the lights and transmitter relay,
turn off the navigation light switch and reset the circuit breaker.
This will re-activate the transmitter relay and permit its usage.
Do not turn the switch on again until the malfunction is corrected.
LIGHTING EQUIPMENT.
EXTERIOR LIGHTING.
Conventional navigation lights are located on the wing tips and
top of the rudder. A dual beam landing/taxi light is installed in
the left wing and a flashing beacon is mounted on top of the
vertical fin. Optional lighting includes a strobe light on each wing
tip and two courtesy lights, one under each wing, just outboard of
the cabin door. The courtesy lights are operated by a switch
located on the left rear door post. All exterior lights, except the
courtesy lights, are controlled by rocker type switches on the left
switch and control panel. The switches are "ON" in the up
position and "OFF" in the down position.
The flashing beacon should not be used when flying through
clouds or overcast; the flashing light reflected from water droplets
or particles in the atmosphere, particularly at night, can produce
vertigo and loss of orientation.
The two high intensity strobe lights will enhance anti- collision
protection. However, the lights should be turned off when taxiing
in the vicinity of other aircraft, or during flight through clouds,
fog or haze.
2-5

INTERIOR LIGHTING.
Illumination of the instrument panel is provided by four red
flood lights on the under side of the anti-glare shield, and a single
red flood light in the forward part of the overhead console. The
magnetic compass and radio equipment have integral lighting.
Two rheostat control knobs on the left switch and control panel
operate the interior lights. One knob is labeled "PANEL
LIGHTS" and controls the lights in the glare shield, overhead
console and compass; the other knob is labeled "RADIO LIGHTS"
and controls the integral radio lighting. Both knobs rotate
clockwise to increase light intensity.
A cabin dome light is located in the aft part of the overhead
console, and is operated by a switch adjacent to the light. To turn
the light on, move the switch to the right.
The instrument panel console may be equipped with an
optional courtesy light, mounted at its base, which illuminates the
forward cabin floor area. This light is controlled by the courtesy
light switch on the rear door post.
An optional map light may be mounted on the bottom of the
pilot's control wheel. The light illuminates the lower portion of the
cabin just forward of the pilot and is helpful when checking maps
and other flight data during night operations. To operate the light,
first turn on the "NAV LIGHTS" switch; then adjust the map light's
intensity with the knurled disk type rheostat control located at the
bottom of the control wheel.
LANDING GEAR SYSTEM.
The retractable tricycle landing gear is extended and retracted
by hydraulic actuators powered by an electrically-driven hydraulic
power pack. The power pack assembly is located aft of the rear
baggage compartment wall. Mechanically-actuated wheel well
doors are provided for the nose gear. They are open when the
nose gear is down and closed when it is retracted.
An over-center mechanical linkage provides a positive
mechanical up and down lock for the nose wheel. The main gear
utilizes electro-mechanical downlocks and hydraulic pressure for
positive uplock. Main gear uplock pressure is maintained
automatically by the power pack assembly. If pressure drops
below that necessary to retain uplock pressure on the main gear,
the power pack will automatically compensate.
2-6