Academics Flashcards
(49 cards)
Manufacturers determine VMCA under the following conditions:
COMBATS
- Critical engine inoperative
- Operating engine operating at maximum continuous power
- Maximum gross weight/Least favorable gross weight
- Bank angle up to 5 degrees
- Aft CG
- Takeoff configuration (gear up, cowl flaps closed, carb heat off)
- Standard day (59 degrees F/15 degrees C, 29.92 Hg)
What are the 4 propeller components of airframe torque?
(1) torque from the engine and propeller rotation,
(2) corkscrewing slipstream,
(3) propeller gyroscopic action, and
(4) P-Factor (asymmetric thrust created by prop)
The asymmetric thrust and drag changes that accompany engine failure affects a multiengine
aircraft in the following ways:
Pitch Down
Roll into the Failed Engine
Yaw into the Failed Engine
Which engine is critical in a twin engine aircraft w/ two clockwise rotating props and which components are responsible?
Left engine
P-Factor, Corkscrewing and Accelerated Slipstream, and Torque Reaction
VMCA may not be greater than X times stall speed with flaps in takeoff
position and gear retracted.
1.2
VMCA decreases with:
- Increased gross weight.
- Reduced power on operating engine.
- Aircraft has no critical engine (Seminole).
- Feathered prop on inoperative engine.
- Center of gravity more forward.
- Gear extended (gear acts as stabilizing force and reduces yaw/drag).
- Higher density altitude (temp/PA). Higher DA reduces asymmetric power.
- Bank up to 5 degrees into the good engine.
Loss of an engine results in a
XX percent reduction in power, but an XX percent loss of excess power.
50/80
Maximum single engine climb performance depends on four factors:
airspeed, drag, power and weight
Max takeoff weight
3,800
lbs
max ramp weight
3816 lbs
max baggage load
200 lbs
The left engine rotates X nd the right engine rotates
X
clockwise / counterclockwise
Carbureted engines are susceptible to induction icing at temperatures between
20 and 70 degrees
F
Icing may be initially indicated by
engine roughness and a drop in manifold pressure
When oil pressure is lost, the propeller will move
towards
feather due to the springs and counterweights
Acceptable fuels are
100 (green) and 100LL (blue)
Total/usable capacity for both tanks is
110 gallons,
108 of which is usable
The electric pumps are required for
engine start and turned on
to back up the engine driven pumps during takeoff, landing and fuel selector changes
The gear is held up solely by X however, X assist in gear extension
the hydraulic system / springs
The Seminole is equipped with a gear warning horn that will sound
when:
gear is not down and locked
throttle is set with manifold pressure below 15”
flaps are down 25 or 40 degrees
The brakes are activated by
an independent hydraulic system.
The flaps are spring loaded to return to the up position and detents are located at flap
extensions of
10, 25 and 40 degrees
The Seminole has a XX volt electrical system powered by two XX volt, XX amp engine driven
alternators. A XX volt, XX amp hour battery in the nose provides power when the engines are not
operating or in case of alternator failure.
14, 14, 70, 12, 35
The system is protected by overvoltage relays in each alternator that disconnect an errant
alternator from the system when output voltage exceeds
17 volts
