C172 Procedures Flashcards

1
Q

Fire in flight

A
Mixture ø
Fuel ø
Master ø
Cabin Heat/Air ø
Airspeed 100
Emergency Landing
How well did you know this?
1
Not at all
2
3
4
5
Perfectly
2
Q

Electrical fire in flight

A

Master ø
All switches ø
Vents Air/Heat ø
Fire Extinguisher

After discharging
Master ON
Circuit CHECK
Avionics ON
Radio/Electrical ON
Vents Air/Heat ON
How well did you know this?
1
Not at all
2
3
4
5
Perfectly
3
Q

Fire in Cabin

A

Master ø
Vents Air/Heat ø
Fire Extinguisher

After discharging
Ventilate
Land ASAP

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
4
Q

Wing fire

A
Navigation Light ø
Pitot heat ø
Strobe light ø
Sideslip
Land ASAP
How well did you know this?
1
Not at all
2
3
4
5
Perfectly
5
Q

Icing

A
"Pitot Heat ON
Turn back/Altitude
Cabin Heat FULL
Throttle FULL
Carb Heat AS REQ

Land
(nearest airport/ASAP)

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
6
Q

Balked Landing

A
Throttle FULL
Carb Heat ø
Flaps 20
Level until 55kt
Flaps 10
Flaps ø @ 60
How well did you know this?
1
Not at all
2
3
4
5
Perfectly
7
Q

Début vent arrière

A
Primer LOCKED
Master ON
Magnetos BOTH
Carb Heat ON
Mixture RICH
Fuel BOTH
Brake CHECK
2200 RPM
How well did you know this?
1
Not at all
2
3
4
5
Perfectly
8
Q

Fin vent arrière

A

˜1800 RPM
Vi 70kts
Flaps 10

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
9
Q

Landing after icing

A
Stall Speed!!
Wing Flaps ø
Left Window OPEN
Airspeed 65-75
Land Level
How well did you know this?
1
Not at all
2
3
4
5
Perfectly
10
Q

Rule of thumb for Gusts and Approach speed

A

Add half of gust factor to approach speed.
e.g 10G30kt
Gust factor = 30/2 = 15
Approach speed + 15kt

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
11
Q

What is the Lift formula?

A

L = CL (1/2 ρV²) S

L = Resultant lift
CL = Coefficient of Lift (determined by AoA and design of airfoil)
ρ = Air density
V = TAS
S = Surface Area of the wing (modified by flaps)
How well did you know this?
1
Not at all
2
3
4
5
Perfectly
12
Q

explain each parameter of

L = CL (1/2 ρV²) S

A
L = Resultant lift
CL = Coefficient of Lift (determined by AoA and design of airfoil)
ρ = Air density
V = TAS
S = Surface Area of the wing (modified by flaps)
How well did you know this?
1
Not at all
2
3
4
5
Perfectly
13
Q

Does temperature affect TAS?

A

High temperature will increase TAS → higher roll for climb

How well did you know this?
1
Not at all
2
3
4
5
Perfectly