POH exam

Number of Engines

1

Engine Manufacturer

Lycoming

Engine Model Number

IO-360-B4A

Takeoff Power (BHP)

2700

Engine Type

4 cylinder, direct drive, horizontally opposed with fuel injection

Number of Propellers

1

Propeller Manufacturer

Sensenich

Number of Blades

2

Propeller Diameter in inches (Maximum)

76

Propeller Diameter in inches (Minimum)

76

Fuel Capacity

50

Useable fuel

48

Fuel Minimum Octane

100 green or 100LL blue

Oil Capacity

8

Maxinmum ramp weight

2558

Maximum takeoff weight

2550

Maximum landing weight

2550

weights in baggage compartment

200

Mineral oil is for

New engines

Ashless Dispercent is for

Normal engines

Wing loading

15.0

power loading

14.2

GS

ground speed

IAS

Indicated Airspeed

KIAS

indicated airspeed expressed in knots

TAS

true airspeed

Vo

Maximum operating maneuvering speed

Vfe

Maximum flap extended

VNE/MNE

Never exceed speed or mach Number

VNO

Maximum structural cruising speed

VS

Stalling speed

Vso

stalling speed

VX

best angle of climb speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance

VY

best rate of climb speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time

ISA

15 C (59 F) the pressure at sea level is 29.92 inches Hg (1013.2 mb)

OAT

outside air temperature

pressure altitude

altitude measured from standard sea level pressure

EGT

one of the engine istruments for exhaust gas temp

FFLOW

one of the engine istruments for fuel flow

RPM

one of the engine istruments for propeller speed

1

refers to the pilot’s side

2

refers to the co pilots side

ADAHRS

Air data, attitude and heading reference system

CAS

crew alerting system

EIS

engine indication system

FOB

fuel on board

GEA

garmin engine/airfeame processing unit

GPS

global positioning system

MFD

mult-function display

PFD

primary flight display

Accelerate-stop distance

the distance required to accelerate an airplane to a specified speed and assuming failure of an engine at the instant that speed is attained to bring the airplane to a stop

Demonstrated crosswing velocity

14 KIAS crosswing

CG

center of gravity

CG limits

the extreme center of gravity locations within wich airplane must be operated at a given weight

basic empty

standard empty weight plus optional equipment

maximum landing weight

max weight apporved for the landing touchdown

maximum ramp weight

max weight approved for ground maneuver, includes weight of start, taxi, and run up fuel

.

standard empty weight

weight of a standard airplane including unusable fuel, full operating fluids and full oil

unusable fuel

fuel remaining after a runout test has been completed in accordance with governmental regulations

usable fuel

fuel available for flight planning

never exceed speed

154 KIAS

maximum structural cruising speed

125 KIAS

max operating maneuvering speed at 2250 lbs G.W

113 KIAS

max operating maneuvering speed at 1917 lbs G.W

98 KIAS

max flaps extended speed

102 KIAS

airspeed marking indications at the red line

154 KIAS

airspeed marking indications at the yellow band

125-154 KIAS

airspeed marking indications at the green band

50-125 KIAS

airspeed marking indications at the white band

45-102 KIAS

engine operating limits for rated horsepower

180

engine operating limits for max propeller speed

2700

engine operating limits for max oil temp

245 F

engine operating limits for oil pressure min

25 PSI

engine operating limits for oil pressure max

115 PSI

engine operating limits for fuel

100 or 100LL

propeller tolerance @ ISA conditions

not above 2340 RPM and not below 2240 RPM

Tachometer in the green arc

500-2700 RPM

Tachometer in the red line

2700 RPM

Oil temp at the green band

75-245 F

Oil temp at the red line

245 F

Oil pressure at the green band

55-95 PSI

Oil pressure at the yellow band (caution range idle)

25-55 PSI

Oil pressure at the yellow band (ground warm-up)

95-115 PSI

Oil pressure at the red line min

25 PSI

Oil pressure at the red line MAX

115 PSI

alternator limiations

70 AMPS

emergency battery min limiations

23.3 volts

max ramp weight

2558

max weight

2550

max baggage

200

forward limit inches AFT of datum

88.6 and 82.0

rearward limit inches AFT of datum

93 and 93

positive load factor

3.8 G

negative load factor

-1.5 G

the airplane is approved for what operations when equipped in accordance with FAR 91 and FAR 135

day VFR

night VFR

day IFR

night IFR

non icing

the person operating this aircraft must wear a headset while in flight

ATOMATOFLAMES

Airspeed

Tachometer

Oil pressure

Manifold pressure

Altimeter

Temperature

Oil temp

Fuel quantity

Landing gear position indicator

Anticollision lights

Magnetic compass

Emergency locator transmitter

Seatbelt

FLAPS

Fues Landing lights

Anti collision lights

Position lights

Source of electrical power

Aternator failure (red)

ALTR FAIL

cause: alternator is turned ON and has failed as fetermined by voltage regulator

CO level high (red)

CO LVL HIGH

cause: CO level greater than 200 parts per million (PPM)