MODEL

SMP 515 C INSPECTION PROCEDURES

382/C-130

SYSTEM LANDING GEAR CHAPTER 32

ZONE

REV DATE

700

1 DEC 05

CARD NO. C-110A 1 OF 9

LANDING GEAR OPERATIONAL CHECK

CAUTION: Note:

1.

Clear wing flaps, rudder, elevator and aileron areas of all stands and equipment before hydraulic power is applied.

Perform the following checks with the aircraft jacked free of the ground. Remove any towing fittings and jack the aircraft in accordance with the applicable maintenance manual. There should be no hydraulic leakage from the system during the test. Two men will be required to perform the test: one man will be stationed in the flight station to operate the controls; the other man will be outside the airplane to monitor the test stand and to record the time for extension and retraction of the landing gear. Maintain interphone communication between the men during this test.

Perform Normal Operation Check of the Landing Gear as follows: a.

Ensure that the NLG scissors (upper and lower torque arms) are connected to prevent damage to wheel well pres sure diaphragm. Prior to cycling of the NLG, the NLG door actuating push rods shall be properly connected at the push rod quick disconnects.

b.

Connect the hydraulic test stand to the aircraft.

WARNING:

?

Refer to the applicable maintenance manual and warnings for operation of the auxiliary hydraulic pump.

?

If the auxiliary pump is used to pressurize the utility hydraulic system, the ramp and aft cargo door manual controls must be in the neutral position before starting the auxiliary pump. Failure to neutralize the ramp and door valves can result in fatal injury to personnel and/or serious damage to equipment.

THIS MATERIAL CONTAINS P ROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICS COMPANY. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL 382/C-130

CAUTION:

SMP 515 C INSPECTION PROCEDURES

SYSTEM LANDING GEAR CHAPTER 32

ZONE

REV DATE

700

1 DEC 05

CARD NO. C-110A 2 OF 9

Prior to positioning the ground test checkout valve handle, the utility and auxiliary hydraulic systems pressure must be at 0 psi, including normal and emergency brakes. When positioning the ground test checkout valve handle, the handle must move through its full arc of travel. Failure to comply may result in damage to the hydraulic systems components.

c.

If a hydraulic test stand (approximately 17 gpm) is not available, the auxiliary hydraulic pump can also be used to provide pressure through the ground checkout valve. The times for retraction and extension of the landing gears will be considerably longer due to the lower flow (approximately 8 gpm) produced by this pump.

d.

Connect a 28-volt DC and 115/200-volt 400-Hz AC power source to the external power connections in accordance the applicable maintenance manual.

WARNING:

To ensure safety of personnel and prevent damage to equipment, a ground observer will be in a position on the interphone to clear the gear and report any problems during operational checkout of the landing gear. The observer will remain in position until released by the individual(s) operating the controls. Check the flap wells for clearance and obstructions prior to moving the flap lever. Failure to observe this warning may result in injury to personnel and damage to equipment.

e.

Place the landing gear control handle in the DOWN position, and place throttles in the TAKE OFF position.

f.

Place the flaps control lever in the UP position.

g.

Ensure that the following circuit breakers are closed and that the appropriate switches are placed in the position indicated. (1) LANDING GEAR CONTROL circuit breaker. CLOSED (2) TOUCHDOWN RELAY circuit breaker. CLOSED (3) LANDING GEAR POSITION circuit breaker. CLOSED

THIS MATERIAL CONTAINS P ROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICS COMPANY. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL 382/C-130 (4) (5) (6) (7) (8)

Note:

SMP 515 C INSPECTION PROCEDURES

SYSTEM LANDING GEAR CHAPTER 32

ZONE

REV DATE

700

1 DEC 05

LANDING GEAR WARNING circuit breaker AC INST & ENGINE FUEL CONTROL switch HYD SUCTION PUMP BOOST and UTILITY circuit breakers HYD BOOST SUCTION PUMP CONTROL circuit breaker HYD UTILITY SUCTION PUMP control circuit breaker

CARD NO. C-110A 3 OF 9 CLOSED AC GEN CLOSED CLOSED CLOSED

The suction boost pump is not required when using the auxiliary pump for checkout. (9)

CAUTION:

UTILITY and BOOSTER SUCTION BOOST PUMP switches

ON

The manual drive engage t-handle must not be operated during landing Gear operation.

h.

Verify that the gear boxes are shifted to hydraulic drive by turning the stub shafts in each direction. The shafts shall turn freely.

i.

Pressurize the hydraulic system to 2,700 PSI, and obtain a flow of 17.2 gallons per minute.

CAUTION: j.

Ensure that the gear does not strike any disconnected part during operation.

Ensure landing gear ground safety locks are removed. Move the landing gear control handle to the UP position. Observe and record the time for nose and main gear retraction. RESULT: 1. The nose gear should retract into the uplock, and the retraction time should be 12 (±3) seconds from the time the control handle is moved to the “UP” position. 2. The main gear should retract in 16 (±3) seconds from the time the control handle is moved to the UP position.

THIS MATERIAL CONTAINS P ROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICS COMPANY. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL 382/C-130

SMP 515 C INSPECTION PROCEDURES 3.

SYSTEM LANDING GEAR CHAPTER 32

ZONE

REV DATE

700

1 DEC 05

CARD NO. C-110A 4 OF 9

The position indicators should change to the striped position as the gears start to move up. The warning light in the control handle should go on as soon as the gear unlocks and starts up. The position indicator should indicate UP and the warning light should go out when the gears are in the up and locked position.

k.

Move the throttles one by one from the TAKE OFF to the FLIGHT IDLE position and back to the TAKE OFF position. Observe the landing gear for any evidence of cycling. RESULT: As each throttle enters FLIGHT IDLE position, the warning light in the landing gear control handle should go on and the warning horn will sound. When the throttle is moved out of the FLIGHT IDLE range to TAKE OFF position, the warning light in the landing gear control handle should go out and the warning horn should be silenced.

l.

With all throttles in TAKEOFF position, slowly move the FLAPS control lever toward DOWN. The wing flap warning switch should actuate and operate the warning horn. RESULT: 1. At 60 ±5 percent of lever (L382E/G) 2. At 70 ±5 percent of lever (C-130B/E/H/H-30) 3. At 80 ±5 percent of lever (KC-130E/H/H-30)

m.

Move all throttles to the FLIGHT IDLE position and the landing gear control handle to the DOWN position. RESULT: 1. The warning horn should sound until all the gears are down and locked. The position indicators should stay in the striped position until the respective gears are down and locked, and then they should indicate DOWN. 2. The warning light should be on until all the gears are down and locked, and then it should go out. 3. All the landing gears should extend and lock in 9 to 19 seconds from the time the control handle is moved to the DOWN position.

n.

Service the auxiliary hydraulic system reservoir, and drain to the correct level if required.

THIS MATERIAL CONTAINS P ROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICS COMPANY. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL

SMP 515 C INSPECTION PROCEDURES

382/C-130 2.

SYSTEM LANDING GEAR CHAPTER 32

ZONE

REV DATE

700

1 DEC 05

CARD NO. C-110A 5 OF 9

Perform Emergency Operational Check of the Landing Gear System.

CAUTION:

Note:

a.

?

The ramp and aft cargo door manual controls shall be in the neutral position before emergency extension of the nose landing gear.

?

After extension of the nose landing gear by emergency system, do not re-service the affected hydraulic system reservoir until after the nose landing gear has been retracted by the normal system.

?

This check involves both the main and the nose gear and requires a minimum of two personnel: one in the cargo compartment to operate the hand cranks and the hand cranks and hand pump, and one outside the airplane to observe the gear operation. Before starting this check, make sure the ramp and aft cargo door control valves are in the NEUTRAL position and the safety wire has been removed from the nose landing gear emergency extension valve. Maintain communication between men during this test.

?

Prior to initiating the operational checkout, inspect the landing gear components for leakage, security, and proper lubrication, and check the normal drive engage cable adjustment.

If available, connect a hydraulic test stand to the utility pressure quick disconnect at the external hydraulic service panel on the left-hand wheel well. Keep the hose lengths between the test stand and the airplane as short as possible.

WARNING:

If the auxiliary pump is used to pressurize the utility hydraulic system, the ramp and aft cargo door manual controls must be in the neutral position before starting the auxiliary pump. Failure to neutralize the ramp and door valves can result in fatal injury to personnel and/or serious damage to equipment.

THIS MATERIAL CONTAINS P ROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICS COMPANY. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL 382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM LANDING GEAR CHAPTER 32

ZONE

REV DATE

700

1 DEC 05

CARD NO. C-110A 6 OF 9

b.

If a hydraulic test stand is not available, the auxiliary hydraulic pump can also be used to provide pressure through the ground checkout valve. The times for retraction and extension of the landing gear will be considerably longer due to the lower flow produced by this pump.

c.

Connect a 28-volt DC and 115/200-volt 400-Hz AC power source to the external power connections in accordance with the applicable maintenance manual.

Note:

When no external hydraulic power source or electrical source is available, electrical power from the air turbine motor AC generator can be used to operate the auxiliary electrically driven hydraulic pump.

d.

Apply 3,000 PSI pressure to the utility hydraulic system.

e.

Move the landing gear control handle to the UP position. RESULT: The landing gear should move to the retracted position.

WARNING:

To ensure safety of personnel and prevent damage to equipment, a ground observer will be in a position on the interphone to clear the gear and report any problems during operational checkout of the landing gear. The observer will remain in position until released by the individual(s) operating the controls.

f.

Dissipate hydraulic pressure from the utility system. RESULT: The main landing gear and the nose landing gear should remain retracted.

g.

Open the landing gear control, circuit breaker on the copilot’s lower circuit breaker panel.

h.

Place the landing gear handle in the DOWN position.

THIS MATERIAL CONTAINS P ROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICS COMPANY. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL 382/C-130

CAUTION: i.

SMP 515 C INSPECTION PROCEDURES

SYSTEM LANDING GEAR CHAPTER 32

ZONE

REV DATE

700

1 DEC 05

CARD NO. C-110A 7 OF 9

The main landing gear may free fall. Do not attempt to stop a free-falling main landing gear by pushing in the T-handle. Damage to the manual gearbox will result.

Remove an extension handcrank for one of the main gears from the stowed position and place it on the emergency extension stub shaft.

CAUTION:

When performing the following step, turn the handcrank slowly to allow the engage normally. Do not force an emergency T-handle out. Failure to comply may result in a bent manual gearbox lever, making it difficult or impossible to engage the manual drive.

j.

Rotating the handcrank left or right as required, pull the manual drive engage T-handle until the T-handle locks in its detent and the force required for rotation of the handcrank indicates engagement of the manual extension sys tem. Remove the handcrank. RESULT: The force required to pull out the T-handle should not exceed 120 pounds. The manual emergency drive and the handcrank should engage with the landing gear actuating mechanism.

k.

Place the torque wrench on the stub shaft and rotate the shaft just enough to break the gear loose from the up pos ition. Remove the torque wrench. RESULT: Torque required to break the gear loose should not exceed 150 inch-lbs.

l.

Replace the handcrank on the stub shaft and extend the gear to almost full down by rotating the handcrank approximately 330 turns in the direction of the arrow above the shaft. Remove the handcrank. RESULT: The main landing gear should extend to near the full down position.

m.

Place a torque wrench on the stub shaft and extend the gear into the full down position. Remove the torque wrench. RESULT: The torque required to extend the gear into the full down position should not exceed 150 inchpounds.

THIS MATERIAL CONTAINS P ROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICS COMPANY. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL 382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM LANDING GEAR CHAPTER 32

ZONE

REV DATE

700

1 DEC 05

CARD NO. C-110A 8 OF 9

n.

Repeat steps i through m for other main gear.

o.

Release the nose landing gear by pulling up the nose gear emergency release handle on the cockpit floor left of the copilot’s seat. RESULT: The force required to release the nose gear should not exceed 25 pounds. The nose landing gear should free-fall to the near down position.

p.

Rotate the handle of the nose landing gear emergency extension valve to the NLG EMER EXT POSITION.

q.

Operate either the auxiliary hydraulic system hand pump or the electric motor pump until the nose gear is extended and locked.

CAUTION:

The ramp and aft cargo door manual controls must be in the neutral position. RESULT: The nose gear should move to the down-and-locked.

r.

Check that both the main and the nose landing gear are down and locked.

s.

Return the nose landing gear emergency extension valve to NORMAL POSITION, and safety wire in that position.

t.

Return the T-handles to their normal positions by rotating them approximately one-eight turn clockwise and press firmly in.

CAUTION: u.

Verify proper positioning of the drive gears by rotating the hand crank only one turn each way. No significant force should be required to rotate the crank.

Return the hand cranks to their stowed position.

THIS MATERIAL CONTAINS P ROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICS COMPANY. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.

MODEL 382/C-130

SMP 515 C INSPECTION PROCEDURES

SYSTEM LANDING GEAR CHAPTER 32

ZONE

REV DATE

700

1 DEC 05

CARD NO. C-110A 9 OF 9

v.

Push in the LANDING GEAR CONTROL handle circuit breaker on the copilot’s control handle circuit breaker on the copilot’s lower circuit breaker panel.

w.

Retract and extend the landing gear to recycle the nose landing gear normal system and to properly reposition the nose landing gear shuttle valve, finally leaving the gear extended.

x.

Disconnect the external hydraulic and electrical power; install the ground safety gear locks.

y.

Lower the aircraft and remove the jacks in accordance with applicable maintenance manuals.

z.

Service the forward cargo door reservoir or the auxiliary hydraulic system reservoir as applicable. Drain to correct level if required.

THIS MATERIAL CONTAINS P ROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICS COMPANY. USE, COPYING AND/OR DISCLOSURE WITHOUT WRITTEN AUTHORIZATION IS PROHIBITED.