Cessna 152 Flashcards
Engine
Avco Lycoming O-235-L2C Horizontally Opposed
Maximum engine power
110 BHP
Maximum engine speed
2550 RPM
Propeller
McCauley Accessory Division
Propeller Dimensions
69 inches max., 67.5 inches min., 12inches ground clearance
Wing area surface
160 ft2
Wing span
33 ft 4 in
Maximum height
8ft 6 in
Maximum width
24 ft 1 in
Service ceiling
14,700 ft
Rate of climb at sea level
715 FPM
Maximum weight
1670 LBS
Standard empty weight
1081 LBS
Maximum useful load payload and fuel
589 LBS
Maximum takeoff weight
1670 LBS
Maximum landing weight
1670 LBS
Baggage allowance, area 1 and area 2
120 LBS
Fuel capacity - standard tanks
26 gallons
Fuel Capacity - Usable
24.5 gallons
Fuel capacity - Unusable
1.5 gallons
Fuel capacity - long range tanks
39 gallons
Oil capacity:
6 quarts, 7 quarts (with filter)
Oil Grade - first 50 hours
MIL - L - 6082
Oil Grade - After 50 Hours
MIL - L - 22851
Take-off performance: ground roll
725 feet
Take off: total distance over 50ft obstacle
1340 feet
Landing performance: ground roll
475 feet
Landing: Total distance over 50ft obstacle
1200 ft
Stall speed (CAS) Flaps up, power off
48 knots
Stall speed (CAS) Flaps down, power off
43 knots
Vx
55 knots
Vy
67 knots
Maximum demonstrated crosswind
12 knots
Maneuvering speed
95 knots
Tire pressure nosewheel
30 PSI
Tire pressure mainwheel
21 PSI
Battery
24 volts, 14 ampere
Alternator
28 volt, 60 ampere
Approved fuel grade and color
100LL Blue;
100 (Former 100/130) Green
Flight load factors, flaps up
+4.4g, -1.76g
Flight load factor, flaps down
+3.5 g
Wing loading
10.5 lbs/ft2
1670 lbs / 160ft2
Power loading
15.2 lbs/hp
1670 lbs/110hp
White arc
035-085 knots
Green arc
040-111 knots
Yellow arc
111-149 knots
Red line
149 knots
Maneuver - chandelles
95
Maneuver - lazy eights
95
Maneuver - steep turns
95
Maneuver - spins
Use slow deceleration
Maximum gross weight
1670 lbs
Maximum useful weight
589 lbs
Standard Empty Weight
1081 lbs
Maximum baggage capacity
120 lbs
Fuel Capacity - Standards Tanks
26 gallons
Fuel Capacity - Optional Long range tanks
39 gallons
Standard total usable fuel
24.5 gallons
Maximum range, long range tanks - 10,000 ft
690 NM, 8.7HRS
Maximum range, standard tanks - 10,000 ft
415 NM, 5.2 HRS
Use of flaps 10
Shorten ground run by 10%
Emergency Landing without engine power
60 KIAS (flaps down), 65 KIAS (flaps up)
Ditching
Flaps 30, 300ft/m descent, 55 KIAS
Oil pressure gauge should begin to show pressure in
30 seconds in summer time and twice as long in very cold weather
Maxim speed at which you may use abrupt control travel
Va - 95 KIAS
Cruise power
1900-2550 RPM
Primary Flight Instrument for bank reference
Use heading indicator for primary check, turn coordinator for supporting check
Static RPM power check
2280 - 2380 RPM
Maximum Cruise speed, sea level
If erroneous readings of the static source instruments (airspeed, altimeter, and rate of climb) are suspected, __________________, thereby applying static pressure to these instruments from the cabin
The alternate static source valve should be pulled on
Normal take-off airspeed
65-75 KIAS
Short fiel takeoff
54 KIAS, Flaps 10, speed at 50 ft
Climb Flaps up, Normal airspeed
70 - 80 KIAS
Landing, Normal Approach Flaps up
60 - 70 KIAS
Landing, Normal Approach Flaps 30
55 - 65 KIAS
Landing, Short field approach Flaps 30
54 KIAS
Balked Landing, Maximum Power, Flaps 20
55 KIAS
Spiral dive
Adjust elevator trim control to maintain a 70 kts glide
Primary Flight Instrument for nose up and nose down reference
Altimeter for primary check, VSI for supporting check
Level the nose should restore power within _____ to raise air temp - 1/4 - 1/2
20 seconds
Change in engine oil
Every 6 months of every 100 hrs whichever comes first
Cruise speed at sea level, 75%
100 KTAS
Flight instrument for primary check for power
Use airspeed indicator for primary check, tachometer for support or confirm power settings
Prior to starting on a cold morning, it is advisable to pull the propeller through several times by hand to
“break loose” or “limber” the oil, thus conserving battery energy
If erroneous instrument readings are suspected due to water or ice in static pressure lines
The static pressure alternate source valve control knob located below the wing flap switch should be opened
Engine Failure After Take off
Flaps up - 65 KIAS
Flaps down - 60 KIAS
Max Glide - 60 KIAS
