CPL - 5

The performance tables of an aircraft for takeoff and climb are based on

• true altitude

• cabin altitude

• pressure/density altitude

To determine pressure altitude prior to takeoff, the altimeter should be set to

• the current altimeter setting

• 29.92" Hg and the altimeter indication noted

• the field elevation and the pressure reading in the altimeter setting window noted

At higher elevation airports the pilot should know that indicated airspeed

• should be increased to compensate for the thinner air

• will be unchanged, but groundspeed will be faster

• will be higher, but groundspeed will be unchanged

What effect does an uphill runway slope have on takeoff performance?

• Decreases takeoff distance

• Increases takeoff distance

• Increases takeoff speed

Which maximum range factor decreases as weight decreases?

• Altitude

• Angle of Attack

• Airspeed

When computing weight and balance, the basic empty weight includes the weight of the airframe, engine(s), and all installed optional equipment. Basic empty weight also includes

• all usable fuel, full oil, hydraulic fluid, but does not include the weight of pilot, passengers, or baggage.

• all usable fuel and oil, but does not include any radio equipment of instruments that were installed by someone other than the manufacturer.

• the unusable fuel, full operating fluids, and full oil.

The CG of an aircraft can be determined by which of the following methods?

• Dividing total moments by total weight

• Multiplying total arms by total weight

• Dividing total arms by total moments

If all index units are positive when computing weight and balance, the location of the datum would be at the

• centerline of the main wheels.

• centerline of the nose or tailwheel, depending on the type of airplane.

• nose, or out in front of the airplane

GIVEN:
Pressure Altitude .....................................................12,000 ft
True air temperature ..............................................+50 F

Find the approximate density altitude

• 11,900 ft

• 18,150 ft

• 14,130 ft

GIVEN:

Aircraft weight ............................................................. 3,400 lb

Airport pressure altitude ........................................... 4,000 ft

Temperature at 4,000 ft ............................................. 21 C

Using a normal climb under given conditions, how much fuel would be used from engine start to a pressure altitude of 12,000 feet?

• 46 pounds

• 30 pounds

• 37 pounds