Location of Attitude indicator

Top center

(a)  

location of airspeed indicator

(a)  

location of altitude indicator

(a)  

location of heading indicator

(a)  

required number of emergency exits for seating capacity of 15 or less

(a)  

required number of emergency exits for seating capacity of 16 - 23

(a)  

width of passenger aisle of <25 inches from the floor

(a)  

width of passenger aisle of >25 inches from the floor

(a)  

cooling test is "stabilized" if the rate of cooling is

(a)  

Aircraft operation that allows:
- Any maneuver incident to normal flying
- stalls (except whip stalls)
- Lazy eights, chandelles and steep turns

(a)  

Maximum bank angle for normal category aircraft

(a)  

aircraft category w/c allows limited acrobatic operation

(a)  

Maximum bank angle for utility category aircraft

(a)  

aircraft category w/c allows operation without restrictions

(a)  

-19,000 lbs or less (Takeoff weight)
-operation same with normal category
- pax count of 19 or less

(a)  

Maximum bank angle for commuter category aircraft

(a)  

the highest weight at which compliance with each applicable requirement

(a)  

VR for single engine landplanes must not be less than

(a)  

The takeoff path extends from a standing start to a point in the takeoff at which the airplane is (a)   above the takeoff surface at

The airplane must reach V2 before it is (a)   above the takeoff surface, and must continue at a speed as close as practical to, but not less than V2, until it is 400 feet above the takeoff surface;

Gradient of climb above 400 ft for two engine airplanes must not be less than

(a)  

Gradient of climb above 400 ft for Three engine airplanes must not be less than

(a)  

Gradient of climb above 400 ft for Four engine airplanes must not be less than

1.7%

(a)  

The takeoff flight path begins (a)   above the takeoff surface at the end of the takeoff distance

takeoff flight path gradient of climb for two engine airplane

(a)  

takeoff flight path gradient of climb for three engine airplane

(a)  

takeoff flight path gradient of climb for four engine airplane

(a)  

Steady climb gradient at sea level for landplanes

(a)  

steady climb level at sea level for seaplanes if landing gear retracted

(a)  

steady climb level at sea level for seaplanes if landing gear extended

(a)  

unless otherwise provided, the factor of safety must be at a value of (a)  

The structure must be able to support ultimate loads without failure for at least (a)  

gust velocity at sea level to 20,000 ft

(a)  

gust velocity at 50,000 ft

(a)  

rough air gust for commuter category airplanes from sea level to 20,000 ft

(a)  

rough air gusts for commuter category aircraft at 50,000 ft

(a)  

Limit load factor for utility category aircraft

(a)  

Limit load factor for acrobatic category aircraft

(a)  

Negative limit maneuvering load factor for normal,utility and commuter category aircraft may not be less than

(a)  

Negative limit maneuvering load factor for acrobatic category may not be less than

(a)  

Level landing condition for airplane with tail wheels

(a)  

Level landing condition for airplane with nose wheel

(a)  

fitting factor used in FAR part 23

(a)  

fitting factor for seat, berth, safety belt and harness

(a)  

factor of safety for hinges must have a factor of safety not less than (a)  

minimum size for cables used for primary control systems

(a)  

factor of safety for control system joints

(a)  

Buoyancy required by a main float

(a)  

Move aileron control to the right (clockwise) results to (a)  

Moving elevator control rearward results to (a)  

Pressing right rudder pedal forward results to

(a)  

Flap control forward or up results to

(a)