Removal Of Anti-Collision Fin Tip Beacon; Removal Of Anti-Collision Flasher; Installation Of Anti-Collision Flasher; Stall Warning Horn, Indicator And Detector - Piper Navajo Chieftain PA-31-350 Service Manual

NAVAJO CHIEFTAIN SERVICE MANUAL
11-101. REMOVAL OF ANTI-COLLISION FIN TIP BEACON. The anti-collision beacon is mounted
on the fin tip.
a. Remove screws securing fin tip to the fin.
b. Lift fin tip and disconnect electrical connector and remove ground wire from light assembly.
c. Remove screws securing socket assembly to fin tip.
d. Remove socket assembly.
NOTE
To remove bulb only, remove the screws securing the lens retainer
to the light assembly and remove lens retainer and lens. Remove
bulb.
11-102. INSTALLATION OF ANTI-COLLISION FIN TIP BEACON.
a. Install socket assembly on fin tip and secure with appropriate screws, placing ground wire on the
forward screw and securing.
b. Reconnect the electrical connector to the light assembly.
c. Install fin tip on fin and secure with appropriate screws.
11-103. REMOVAL OF ANTI-COLLISION FLASHER. The flasher unit is located on the aft side of the
bulkhead at sta. 296 on the left side of the aircraft.
a. To gain access to the flasher, remove the screws securing the access panel to the rear baggage com-
partment and remove panel.
b. Locate flasher and disconnect the electrical connector (BLINK) from the unit.
c.
Remove the two screws securing the flasher unit to the bulkhead.
d. Remove the flasher unit.
11-104. INSTALLATION OF ANTI-COLLISION FLASHER.
a. Secure flasher unit to bulkhead with two screws previously removed.
b. Reconnect the electrical connector.
c. Install aft panel in rear baggage compartment and secure with appropriate screws.
11-105. STALL WARNING HORN, INDICATOR AND DETECTOR. The stall warning system consists
of a lift detector which is electronically connected to a stall warning horn and light. As stalling conditions are
approached, the lift detector will activate the stall warning horn and light.
The lift detector is located on the leading edge of the left wing. A tab will extend beyond the leading edge at
the point where the lift detector is mounted. With the master swtich in the ON position, gently lift tab, stall
warning horn and/or light should activate.
On airplanes with a stall warning time delay, the delay unit is mounted to the channel above the access
panel at Sta. 64.5. This time delay unit assures a horn sound when the lift detector switch closes and for four
seconds after the detector switches opens.
On airplanes with Serial Nos. PA-31-8052001 and up, a heated lift detector is available with the de-ice group.
This provides heat for both the vane and plate to assure proper operation during icing conditions. A safety
switch is located on the right landing gear. (Refer to chapter 14 paragraph 14-111. for adjustment.)
11-106. REMOVAL OF LIFT DETECTOR.
NOTE
The master switch must be off prior to performing any work on the
lift detector, warning horn or light. Place reference marks on hold-
ing plate and wing skin for use when reinstalling wing.
Revised: 2/8/82
ELECTRICAL SYSTEM
3E6