Phase III - Block II - Powerplants

Question 1

Describe the propeller danger area?

Answer 1

It is a ten foot arc in front of the propellers. The prop blast area extends from the outboard engines to the tail of the aircraft during maximum power.

Question 2

Describe the APU exhaust area?

Answer 2

From the APU exhaust duct to the outboard of the #1 engine. Personnel should NOT approach or depart an aircraft with the propellers turning. Personnel should walk well around the propeller areas at all times.

Question 3

When should personnel wear hearing protection?

Answer 3

It is required 100’ feet from the lateral and longitudinal center lines of the aircraft.

Question 4

What type of engines does the C-130T aircraft have?

Answer 4

The C-130 uses 4 Rolls Royce T56-A-16, turboprop, constant speed engines.

Question 5

What are the major components of the engine assembly?

Answer 5

1. Reduction Gear Assembly (RGB)
2. The torque meter assembly
3. Compressor assembly
4. Diffuser
5. Combustion Section
6. Turbine
7. Accessory drive housing

Question 6

Describe the RGB?

Answer 6

The RGB reduces the RPM of the propeller to the engine. The RGB is located between the torque meter and the propeller. It provides mounting for the starter, tachometer generator, A/C generator, hydraulic pump and gearbox oil pump and filter assembly.

Question 7

Describe the torque meter assembly?

Answer 7

It transmits torque from the engine to Reduction gearbox, and is located on the between the engine and reduction gearbox.

Question 8

Describe the compressor section?

Answer 8

It compresses air for the engine to run. The compressor is located on the forward section of the engine.

Question 9

Describe the Diffuser section?

Answer 9

It channels the air from the compressor to the combustion section. It provides mounting for engine bleed air ducts used for engine starting and pressurization and is located between the compressor and combustion.

Question 10

Describe the combustion section?

Answer 10

It is where fuel is injected into compressed air and ignited through six connected combustion chambers. The combustion section is located between the diffuser and turbine.

Question 11

Describe the turbine unit?

Answer 11

It converts heat energy into mechanical energy to drive the compressor and necessary accessories. The turbine is located aft of the combustion section.

Question 12

Describe the accessory drive housing?

Answer 12

It provides mounting pads for numerous engine driven accessories. The accessory drive is located on the lower section of the compressor.

Question 13

What type of propellers are used on the C-130T?

Answer 13

The props used by the C-130T are Hamilton Standard 54-H60-111 hydromatic, four blade, constant-speed propellers with full feathering and reversible pitch.

Question 14

Describe the prop control assembly?

Answer 14

It controls prop blade pitch at all power settings, and is comprised of the Valve housing and pump housing. It is located between the propeller and RGB.

Question 15

Describe the Dome assembly?

Answer 15

Contains the piston that changes the propeller blade angle with hydraulic power from the pump housing. A low pitch stop is located in the forward section to prevent the blades from entering the ground range in flight. The dome assembly is located forward of the blade hub assembly. Prep anti-ice/de-ice provides electrical anti-ice and de-icing of the prop. It is located on each blade, spinner, and after-body.

Question 16

Describe the fuel system of the aircraft?

Answer 16

It contains four integral main wing fuel tanks, two auxiliary tanks and two external tanks. #1 & #4 (Outboards) are located between the wing tips and the outboard engines. #2 & #3 tanks (inboards) are located between the outboard and inboard engines. Auxiliary Tanks are located between the inboard engine and the fuselage. External tanks are located on the bottom of the wings in between the outboard and inboard engines.

Question 17

What are the two methods of refueling the C-130?

Answer 17

1. Single point refueling

2. Gravity refueling

Question 18

Describe the (SPR) single point refueling?

Answer 18

The SPR panel is located aft of the right hand main wheel well.

Question 19

Describe gravity refueling?

Answer 19

It is accomplished over the wing through over the wing through a cap at the top of the tank.

Question 20

What are the low point drains?

Answer 20

They are located on each tank’s underside. Their purpose is to draw fuel from the tanks and inspect for the presence of contamination.

Question 21

Describe the refueling system?

Answer 21

It contains a refueling manifold plumbing and refueling valves for fuel to be fed into all fuel tanks either by SPR or gravity refueling.

Question 22

Describe the fuel dump system?

Answer 22

It is designed to pump fuel out of the aircraft during an in-flight emergency by using dump pumps, dump valves and dump manifold plumbing.

Question 23

Describe the fuel cross feed system?

Answer 23

It is designed to enable the crew to use fuel from any tank to feed any engine in-flight or on the ground, and consists of a cross feed manifold plumbing, cross feed valves, and boost pumps.

Question 24

Describe the fuel vent system?

Answer 24

It provides a means to equalize tank pressure and prevent purge tanks from overfilling.

Question 25

Explain the bleed air system?

Answer 25

B.A. system consists of high-pressure ducts and valves which direct compressed air to the pneumatically operated systems of the aircraft including anti-ice, air conditioning and pressurization.

Question 26

Explain the APU (Auxiliary Power Unit)?

Answer 26

APU supplies air for ground operation of the air-conditioning systems, for engine starting, and provides shaft power to drive a 40 KVA AC generator.