ATTACHMENT 6_Ku Band BLOSDD_DHC-8 Aircraft

ATTACHMENT 6 – HSBP1012R0018

DHC-8 Aircraft (200 and 300 series) Overview Model 202

Aircraft Dimensions The overall aircraft dimensions are as follows:

· Wing span — 85 feet

· Length — 73 feet

· Height — 24 feet 7 inches

· Main fuselage height — 10 feet 5 inches

· Fuselage diameter – 8 feet 10 inches

· Maximum cabin width – 8 feet 3 inches

· Cabin length – 29 feet 10 inches Structural Weight Limits

· Maximum Ramp Weight: 33,200 lbs

· Maximum Zero Fuel Weight: 32,000 lbs (Maximum weight that the aircraft can weight before fuel is added to the fuel banks)

· Maximum takeoff weight: 33,000 lbs

· Maximum Landing weight: 33,000 lbs

· Minimum structural Design Weight: 21,400 lbs

Center of Gravity Limits

Performance

· Maximum Operating Altitude: 25,000 ft MSL

· Maximum Operating Altitude for takeoff and Landing: 10,000 ft MSL

· Maximum Runway Slopes for takeoff and landing are 2 degrees (uphill and downhill)

· Maximum Tailwind component (measured at a height of 10 meters) for takeoff and landing: 10 kts

· Maximum Crosswind component (measured at a height of 10 meters) for takeoff and landing on a hard, dry runway: 36 kts

Airspeed limitations

The airspeed limitations and associated definitions are as follows

NOTE

The airspeed limitations apply to all weights up to 36,500 lb gross weight unless otherwise stated

KNOTS IAS

Maximum Operating speed (VMO) 0 to 14,000 ft…………………………..242

15,000 ft……………………………….239

20,000 ft……………………………….223

25,000 ft……………………………….207

This speed limit must not be deliberately exceeded in any regime of flight (climb, cruise, or descent) unless a higher speed is authorized for flight test or pilot training. VMO varies linearly between the given altitudes.

Maximum airspeed for flight in severe turbulence: 180 kts.

Operating ambient temperature limits, flight and ground are:

Maximum: 48.9°C or ISA +35°C

Minimum: -54°C

Electrical system

The Ac electrical system of the aircraft uses two engine driven generators to provide 115 volt, three-phase, variable frequency AC power. The avionics system, as well as a few other instruments, use fixed frequency AC power, which is created using three solid-state static inverters. These are powered by the 28 VDC system and create output of 11VAC at 400 Hz, as well as 26 volt 400Hz AC for some applications

AC Power – Variable Frequency

The AC generators supply power varying between 333-528 Hz, depending on propeller speed. The power is supplied to the associated left and right variable frequency AC buses, which are integral with the variable frequency circuit breaker in the flight compartment. Three solid state inverters supply fixed frequency AC power at 115 volts, 400 Hz. The inverters operate using 28 VDC power from the left essential DC bus, right essential DC bus, and left main DC bus.

DC System

DC power is produced from two nickel-cadmium batteries, two starter-generators driven by the engine and two transformer/rectifier units (TRUs).

The main (right) battery has a capacity of 40 ampere-hours and the auxiliary (left) has a capacity of 15 ampere-hours. Each variable frequency AC bus feeds the TRU through a circuit breaker with 115 volt, three-phase, variable frequency AC power. AC input is then converted to 28 VDC output, although depending on secondary DC load, the output voltage may range from 25 to 29.5 volts.

Air Conditioning and Pressurization

· Normal Cabin pressure differential limit: 5.5 ±-0.3 psi

· Maximum cabin pressure differential limit: 5.95 psi

· Maximum cabin pressure differential limit during taxiing, takeoff and landing: 0.5 psi

· Maximum cabin altitude (pressurized flight): 8,000 ft

Model 300

Aircraft Dimensions

The overall aircraft dimensions are as follows:

· Wing span — 90 feet

· Length — 84 feet 3 inches

· Height — 24 feet 7 inches

· Main fuselage height — 10 feet 5 inches.

· Fuselage diameter – 8 feet 10 inches

· Maximum cabin width – 8 feet 3 inches

· Cabin length – 41 feet 4 inches Structural Weight Limits (for Model 300)

· Maximum Ramp Weight: 41,300 lbs

· Maximum Zero Fuel Weight: 37,200 lbs (Maximum weight that the aircraft can weight before fuel is added to the fuel banks)

· Maximum takeoff weight: 41,100 lbs

· Maximum Landing weight: 40,000 lbs

Performance

· Maximum Operating Altitude: 25,000 ft MSL

· Maximum Operating Altitude for takeoff and Landing: 10,000 ft MSL

· Maximum Runway Slopes for takeoff and landing are 2 degrees (uphill and downhill)

· Maximum Tailwind component (measured at a height of 10 meters) for takeoff and landing: 10 kts

· Maximum Crosswind component (measured at a height of 10 meters) for takeoff and landing on a hard, dry runway: 36 kts

Airspeed limitations

The airspeed limitations and associated definitions are as follows

NOTE

The airspeed limitations apply to all weights up to 41,100 lb gross weight unless otherwise stated

KNOTS IAS

Maximum Operating speed (VMO) 0 to 17,000 ft…………………………..243

20,000 ft……………………………….232

25,000 ft……………………………….214

This speed limit must not be deliberately exceeded in any regime of flight (climb, cruise, or descent) unless a higher speed is authorized for flight test or pilot training. VMO varies linearly between the given altitudes.

Maximum airspeed for flight in severe turbulence: 188 kts.

Operating ambient temperature limits, flight and ground are:

Maximum: 48.9°C or ISA +35°C

Minimum: -54°C Electrical system

The AC electrical system of the aircraft uses two engine driven generators to provide 115 volt, three-phase, variable frequency AC power. The avionics system, as well as a few other instruments, use fixed frequency AC power, which is created using three solid-state static inverters. These are powered by the 28 VDC system and create output of 11VAC at 400 Hz, as well as 26 volt 400Hz AC for some applications

AC Power – Variable Frequency

The AC generators supply power varying between 333-528 Hz, depending on propeller speed. The power is supplied to the associated left and right variable frequency AC buses, which are integral with the variable frequency circuit breaker in the flight compartment. Three solid state inverters supply fixed frequency AC power at 115 volts, 400 Hz. The inverters operate using 28 VDC power from the left essential DC bus, right essential DC bus, and left main DC bus.

DC System

DC power is produced from two nickel-cadmium batteries, two starter-generators driven by the engine and two transformer/rectifier units (TRUs).

The main (right) battery has a capacity of 40 ampere-hours and the auxiliary (left) has a capacity of 15 ampere-hours. Each variable frequency AC bus feeds the TRU through a circuit breaker with 115 volt, three-phase, variable frequency AC power. AC input is then converted to 28 VDC output, although depending on secondary DC load, the output voltage may range from 25 to 29.5 volts.

Air Conditioning and Pressurization

· Normal Cabin pressure differential limit: 5.5 ±-0.3 psi

· Maximum cabin pressure differential limit: 5.95 psi

· Maximum cabin pressure differential limit during taxiing, takeoff and landing: 0.5 psi

· Maximum cabin altitude (pressurized flight): 8,000 ft