(2)  
Check that the gear warning horn stays on and that the GEAR WARN MUTE annunciator light is not lit,

L.  Retract the flaps and leave the gear up for 5 minutes. The pump motor should not operate at any time. If the pump should operate during the 5 minute period, search for a leak in the “UP” line or a malfunctioning component in the system.
M.  Position the BATT Mastr switch oFf.
N.  Close both throttles
O.  Pull the emergency gear release knob. All of the gear should return to their down and locked position, with the down latches engaged.
P.  Move the gear selector switch to the down position.
Q.  Push in the emergency gear release knob.
R.  Position the BATT Mastr switch on. The three green safe lights should come on with the red unsafe light and warning horn off.
S.  To disengage the squat switch on the left main gear, do one of the following: (See Figure 32-22.)
(1)  
Remove the torque link connecting bolt and rotate the upper half so the switch tang is free; or,

(2)  
Loosen the squat switch adjustment screws and rotate the switch until the tang is free; or,

(3)  
Partially compress the left main gear shock absorber so that the squat switch operating tang is free.

T.  With the squat micro switch activated, move the gear selector switch to its up position. The warning horn and red unsafe light should come on with the three green safe lights remaining on. The pump should not run.
A.  Depress gear warning mute switch.
B.  The horn should continue to SOUND
32-30-00 Page 32-61 Revised: December 6, 2002
THE NEW PIPER AIRCRAFT, INC.
PA-44-180
AIRPLANE MAINTENANCE MANUAL

U.  Move the throttles to their mid travel position. The red unsafe light and warning horn should stay on.
V.  Move the gear selector switch to its down position. Both the red warning light and horn should be off.
W.  Restore the squat switch to the condition existing before step S, above.
X.  Manually disengage (open) the left main gear downlock. The pump motor should operate with the appropriate green safe light out, and the red unsafe light on without the gear horn.
Y.  Repeat Step X with the right gear downlock.
Z.  With the throttles still at mid travel, move the gear selector switch to the up position, and position the landing lights on. The pump motor should operate and the gear should retract in less then 10 seconds. The three green safe lights should go out. The red unsafe light should go on till all gears are up, at which time the pump should shut off. The warning horn should not sound. The GEAR WARN MUTE annunciator light should not be lit,
AA. Move the gear selector switch down. The pump motor should operate till all gears are down and locked. The three green safe lights should come on with the unsafe light and warning horn off.
— Note —
If a blinking of the red and/or green lights occurs after the down locks are engaged, check for a maladjusted microswitch.
BB. Position the navigation lights on. Check that the three safe lights remain on, but dim.
CC. Switch all switches off and remove aircraft from jacks.
MAIN GEAR ACTUATING CYLINDER.
REMOVAL OF MAIN GEAR ACTUATING CYLINDER.

1.  
Place the airplane on jacks. (Refer to Jacking, Chapter 7.)

2.  
Disconnect the hydraulic lines from the actuating cylinder and cover the open line ends to prevent contamination.

3.  
Disconnect the gear downlock spring from the swivel fitting at the upper end of the spring.

4.  
Remove the downlock spring swivel fitting and disconnect the cylinder operating rod end from the upper side brace retraction fitting by removing the attaching nut, washer and bolt.

5.  
Disconnect the cylinder from its attachment by removing nut and bolt.

6. Remove the cylinder from the wheel well. DISASSEMBLY OF MAIN GEAR ACTUATING CYLINDER. (Refer to Figure 32-13.)
1.  
With the cylinder removed from the airplane, push the piston rod (by hand) toward the clevis to remove oil from the unit.

2.  
Put clevis in a soft jaw vise and clamp against the clevis bearing.

3.  
If no pipe fitting is installed in the port of the end gland, install a fitting (1/8 - 27) into the port. This fitting need not be tight as it will be used for leverage only.

32-30-00 Page 32-62 Revised: December 6, 2002
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THE NEW PIPER AIRCRAFT, INC.
PA-44-180
AIRPLANE MAINTENANCE MANUAL

32-30-00 Page 32-63 Revised: December 6, 2002
　
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