CAS increases.

difference between surrounding conditions and standard atmosphere must be known to deduce the CAS.variation.

CAS remains constant.

CAS decreases.

compressibility.

density.

instrument error.

position error.

HIGHER than ISA and the QNH IS HIGHER than 1013.25 hPa, the aircraft will be LOWER than the altimeter reading.

HIGHER than ISA and the QNH is LOWER than 1013.25 hPa, the aircraft will be LOWER than the altimeter reading.

LOWER than ISA, the aircraft will be HIGHER than the altimeter reading.

LOWER than ISA, the aircraft will be LOWER than the altimeter reading.

2, 3

1, 2, 3

1, 3

1, 2

generation of spurious signals at the commutator.

high influence of line resistance on the indication.

influence of temperature on the indication.

necessity of a power supply.

a speed probe and a phonic wheel.

three interconnected dynamos along a phonic whee

three speed probes and a phonic wheel.

a three-phase generator and a synchronous motor turning a drag-cup assembly.

100 Pascal.

10 Pascal.

100 000 Pascal.

1000 Pascal.

By saveral aneroid capsules.

By a Bourdon tube.

Electrical signal generated by a pressure sensing element in a remote location.

By bellows via mechanical sensing from a Bourdon tube.

Best rate of climb speed. Green arc.

Best angle of climb speed. White arc.

Best angle of climb speed. Blue line

Best RATE of climb speed. Blue line.

By using chemical anti icing.

By using passive anti icing.

By using thermal electric anti icing

By using thermal pneumatic anti icing.