1900 Limitations

Va, also known as design maneuvering speed, is the maximum speed at which full or abrupt control inputs can be made without risking structural damage to the aircraft. It is typically expressed in both indicated airspeed (KIAS) and calibrated airspeed (KCAS) to account for variations in air density. For the given question, the correct answer is 178 KIAS 180 KCAS as this represents the Va for the aircraft in question.

Vfe is the maximum airspeed with flaps extended, represented in both indicated airspeed (KIAS) and calibrated airspeed (KCAS). In this case, when the flaps are set at 17, the correct values are 188 KIAS and 190 KCAS.

Vfe refers to the maximum speed at which the aircraft can be safely flown with the specified configuration. In this case, with flaps set to 35, the correct Vfe speed is 154 KIAS or 155 KCAS.

Vle refers to the maximum landing gear extended speed. In this case, the correct airspeed indication is 180 Kias and 182 KCAS, which are the respective indicated airspeed and calibrated airspeed limits for landing gear extension.

Vlo refers to the maximum landing gear operating speed, which is typically around 180 Kias or 182 KCAS for most aircraft.

Vmca is the minimum airspeed at which the airplane can be safely controlled with one engine inoperative and the other at takeoff power. With flaps set to 0 degrees, the Vmca is 92 KIAS (Knots Indicated Airspeed) or 95 KCAS (Knots Calibrated Airspeed).

Vmca is the minimum control speed in the air, and with flaps 17 this speed is 92 KIAS (Knots Indicated Airspeed) and 93 KCAS (Knots Calibrated Airspeed). This speed is critical for maintaining control of the aircraft in the event of an engine failure during takeoff.

Vmo refers to the maximum operating speed of an aircraft. The correct answer provides the specific speeds at different altitudes where Vmo applies, in terms of indicated airspeed (KIAS), calibrated airspeed (KCAS), and Mach number.

Typically, pilots are advised to maintain 101 knots indicated airspeed (KIAS) when flying vs. to ensure proper control and performance.

Vso is a term commonly used in physics to refer to the orbital speed required for a satellite to maintain a stable circular orbit around the Earth. In this case, the correct Vso value is 84.

In aviation, 'Vsse' stands for 'safe single-engine speed' and it is typically equal to 105 Knots Indicated Airspeed (KIAS). This speed is important for maintaining control of an aircraft in the event of an engine failure.

Max Ramp Weight refers to the maximum weight an aircraft can have when stationary on the ground for takeoff or landing. It includes the weight of the aircraft, fuel, cargo, and passengers. In this case, the correct Max Ramp Weight is 17,230 lbs.

The correct answer provides the specific maximum takeoff weight of the aircraft, or the limitations imposed based on performance parameters. The incorrect answers are meant to confuse the respondent by offering different weight values.

The maximum landing weight of an aircraft is crucial for safe landings and is typically determined by the manufacturer's specifications and performance data to ensure the aircraft can safely land without structural damage or exceeding design limitations.

The increased Zero Fuel Weight STC allows for a maximum Zero Fuel Weight of 15,700 lbs.

The correct answer of 15,165 lbs. represents the maximum weight at which an aircraft can be loaded without any fuel on board and without a Supplemental Type Certificate (STC) approval.

The correct answer is 250lbs. It is important to adhere to weight restrictions to ensure the safety and functionality of the aircraft.

The correct answer is 100 LBS. It is important to adhere to the specified weight limit to ensure safe operations and prevent any potential hazards in the forward cabin compartment of the hangar.

The correct maximum weight allowed in the aft baggage compartment / forward section is 1000lbs, as per regulations and safety standards.

The correct answer, 630 lbs., is the maximum weight allowed in the aft baggage compartment / aft section as per aircraft regulations.

Cabin floor loading refers to the maximum weight that can be supported per square foot of the cabin floor. In this case, the correct value is 100lbs/sq.ft. which indicates the safe limit of weight that can be placed on the cabin floor without causing damage or structural issues.

The maximum cabin pressure differential refers to the difference in pressure between the inside and outside of the aircraft. It is typically set at 5.1 psi to ensure passenger comfort and safety during flight.

The correct normal operating range for pneumatic pressure Gage indicated by the green arc is 17.5 to 20 psi as per industry standards.

The correct redline pneumatic pressure Gage setting is 20 psi, not 10 psi, 30 psi, or 50 psi.

The wide green arc on the gyro suction gage typically indicates the optimal suction range for the instrument, which is usually between 4.3 to 5.9 in. HG. This range ensures that the gyro functions properly without any issues related to suction pressure.

The correct answer specifies the exact type of engines (Pratt and Whitney of Canada PT6A-67D) that power the aircraft. The incorrect options refer to engines from other manufacturers commonly found in different aircraft models.

The correct torque limit for takeoff is 3950 ft-lbs. This specific torque value is crucial to maintain safe and efficient takeoff procedures.

The correct torque limit for max continuous operation is 3750 ft-lbs. This value represents the maximum torque that can be applied continuously without causing damage or failure to the system.

The correct torque limit for cruise climb and max cruise is 3750 ft-lbs. This value is crucial for ensuring the safe operation of the aircraft during these flight phases.

Transient torque refers to the maximum torque that a system can deliver for a short duration. In this case, the correct maximum transient torque rating for 20 seconds is 5000 ft-lbs.