Block I - Airframe (Specific)

Front 1

A. Safety (Ref a, b, c, d, e, f)
The propeller danger area is a ten foot arc in front of propeller. The propeller blast danger area extends from the

Back 1

outboard engines to the tail of the aircraft during maximum power.

Front 2

The APU exhaust area is from the APU exhaust duct to

Back 2

outboard of the #1 engine.

Front 3

Personnel should NOT approach or depart an aircraft with the propellers

Back 3

turning.

Front 4

Personnel should walk well around the

Back 4

propeller areas at all times.

Front 5

Hearing protection is required 100ft from

Back 5

the lateral and longitudinal
center lines of the aircraft.

Front 6

B. Engines (Ref a, b)

Back 6

The C-130 uses four Allison T56-A-16, turboprop, constant speed engines. Some of the major components include:

Front 7

Reduction Gear Assembly (RGB

Back 7

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

Front 8

The Torque Meter assembly transmits

Back 8

torque from the engine to Reduction gearbox, and is located between the engine and Reduction gearbox

Front 9

A Compressor assembly compresses air for engine to run

Back 9

The Compressor is
located on the forward section of the engine.

Front 10

The Diffuser channels the air from the compressor to the combustion section

Back 10

It provides mounting for engine bleed air ducts used for engine starting and
pressurization and is located between the Compressor and Combustion section.

Front 11

The Combustion section

Back 11

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.

Front 12

The Turbine Unit converts heat energy into

Back 12

mechanical energy to drive the
compressor and necessary accessories. The Turbine is located aft of the combustion section.

Front 13

The Accessory Drive housing provides

Back 13

mounting pads for numerous engine
driven accessories. The Accessory Drive is located on the lower section of the
compressor.

Front 14

C. Propellers (Ref a, c)
The propellers used by the C-130T are

Back 14

Hamilton Standard 54-H60-lll
hydromatic, four blade, constant-speed propellers with full feathering and reversible pitch.

Front 15

The Propeller Control Assembly controls prop blade

Back 15

and is comprised of the Valve Housing and Pump Housing.
between the propeller and reduction gearbox. all power
It is locatee

Front 16

The Dome Assembly contains the piston that changes

Back 16

the propeller blade ang
with hydraulic power from the pump housing. A Low pitch stop is located in the
forward section to prevent blades from entering ground range during flight. The
Dome Assembly is located forward of the blade hub assembly.

Front 17

Propeller anti-ice/de-ice provides

Back 17

electrical anti-ice and de-icing of the propeller. It is located on each blade, spinner, and afterbody assembly.

Front 18

D. Fuel Tanks (Ref a, d)
The fuel system contains four integral main wing fuel tanks

Back 18

two auxiliary tanks and two external tanks. #1 and #4 Tanks (Outboards) are located between the wing tips and outboard engines. #2 and #3 tanks (Inboards) are located
between the outboard and inboard engines. .

Front 19

Auxiliary Tanks are located between

Back 19

the inboard engine and fuselage

Front 20

External Tanks are located on the

Back 20

bottom of the wings in between the inboard and outboard engines

Front 21

There are two methods of refueling the C-130 -

Back 21

single point refueling The Single Point Refueling (SPR) panel is located aft of the
right hand main wheel well.

and gravity refuelingis accomplished over the wing
through a cap at the top of the tank .

Front 22

Low Point Drains are located on each tank's underside

Back 22

Their purpose is to. draw fuel from the tanks and inspect for the presence contamination.

Front 23

E. Fuel systems (Ref a, d)
The Refueling system contains refueling manifold plumbing and refueling
valves for fuel to"be

Back 23

fed into all fuel "tanks either by single point refueling c
over the wing gravity fueling.

Front 24

The Fuel Dump system is designed to pump fuel out of the aircraft during a

Back 24

in-flight emergency by using dump pumps, dump valves and dump manifold plumbing

Front 25

The Fuel Cross Feed system is designed to enable the crew to use fuel from
any tank to

Back 25

feed any engine in-flight or on the ground, and consists of cross feed manifold plumbing, cross feed valves, and boost pumps.

Front 26

The Fuel Vent system provides a means to

Back 26

equalize tank pressure and prevent purge tanks from overfilling.

Front 27

Bleed Air (Ref a, e)
The Bleed Air system consists of

Back 27

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

Front 28

G. Auxiliary Power Unit (APU) (Ref a, e)
The APU supplies

Back 28

air for ground operation of the air-conditioning systems,
for engine starting, and provides shaft power to drive a 40-KVA AC generator. It
is located forward of the port wheel well.