12.
SECURE ITEM 13 FUSEHOLDER TO THE FIREWALL USING ITEM 21 CLAMP.
PICKUP EXISTING AVAILABLE THREADED FASTENER OR USE ITEM 16 BOLT,
ITEM 20 NUT AND ITEM 18 WASHER. CONNECT THE BODY TERMINAL OF THE
FUSEHOLDER TO THE STARTER CONTACTOR WITH A 6.0 MAXIMUM WIRE LENGTH.
13.
THE ELECTRIC MOTOR WIRE LEAD SELECTED FOR GROUNDING ( 2RB14
CONNECTOR ATTACHED) MUST CAUSE COUNTERCLOCKWISE ROTATION (AIRBORNE
211CC VACUUM PUMP) OR CLOCKWISE ROTATION (AIRBORNE 212CW/SIGMA TEK
1U128-003 VACUUM PUMP) OR THE ELECTRIC MOTOR SHAFT WHEN LOOKING
TOWARD THE SHAFT END OF THE MOTOR. THE GROUND WIRE MUST BE
ATTACHED DIRECTLY TO THE AIRPLANE OR A JUMPER WIRE USED TO ASSURE
PROPER GOUNDING TO THE AIRPLANE.
14.
ELECTRIC SCHEMATIC SHOWN: TYPICAL. FUSED ELECTRICAL TERMINAL
SHOULD BE CONNECTED TO POWER SOURCE NEAREST CONTROL SWITCH.
(PRIMARY BUS, STARTER SOLENOID, ETC.) SELECTION SHOULD ALLOW FOR
CONTINUED ELECTRICAL POWER IN THE EVENT OF LOSS OF GENERATOR.
15.
THIS INSTALLATION ADDS AN ELECTRICAL LOAD OF 7.5 AMPS (28 VOLT
SYSTEM) 13.5 AMPS (14 VOLT SYSTEM) TO THE ELECTRICAL SYSTEM. THE
TOTAL CONTINUOUS CONNECTED LOAD SHALL BE LIMITED TO APPROXIMATELY
80 PERCENT OF THE TOTAL RATED GENERATOR/ALTERNATOR OUTPUT CAPACITY.
USE THE PROCEDURE OUTLINED BY AC 43.13 SECTION 2 PARAGRAPHS 424,
425 AND 426 TO ASSURE COMPLIANCE WITH THE 80 PERCENT LIMITATION.
16.
INSTALL ITEM 23 SWITCH AND PLACARD ITEM 29 IN AVAILABLE LOCATION
WITHIN ARE SHOWN. PROVIDE .06 CLEARANCE WITH OTHER COMPONENTS.
(MANUFACTURER'S TYPE SWITCH MAY BE USED IN LIEU OF ITEM 23.
LOCATE IN EXISTING SWITCH BANK.)
17.
LOCALLY MANUFACTURED LABEL/PLACARD OPTIONAL IN LIEU OF FURNISHED
ITEM 29. SIZE AND COLOR OF CHARACTERS TO BE .12 HIGH, BLACK ON
WHITE (WHITE ON BLACK) OR SIMILAR TO ADJACENT COMPONENT LABELING.
PLACARDS MAY BE MADE FROM GRAVOPLY (WITH PRESSURE SENSITIVE
BACKING)BY HERMES PLASTIC COMPANY OR 3-M COMPANY SCOTCHCAL PROCESS.
FILL ENGRAVED CHARACTERS WITH LUSTERLESS ENAMEL OR LACQUER.
18.
INSTALL ALL SWITCHES AND FUSEHOLDERS IN ACCORDANCE WITH THE
MANUFACTURER'S INSTRUCTIONS USING ATTACHING HARDWARE FURNISHED
WITH EACH COMPONENT. APPLY ENAMEL AND LACQUER PAINTS AND FABRICATE
AND APPLY ALL PLACARDS IN ACCORDANCE WITH THE MANUFACTURER'S
INSTRUCTIONS.
19.
APPLY TWO COATS OF ZINC CHROMATE PER NOTE 6 ABOVE TO ALL EXPOSED
STEEL AND ALUMINUM SURFACES OF FABRICATED PARTS NOT PREVIOUSLY
CADMIUM PLATED NOR ANODIZED, RESPECTIVELY
20.
THE OPTIONAL WING AND TAIL DE-ICER BOOTS WHEN INSTALLED, GETS ITS
VACUUM SOURCE WITHIN THE EXISTING PORTIONS OF THE SCHEMATIC BUT IS
NOT SPECIFICALLY SHOWN IN THIS FIGURE.
CHANGE: A 7-18-86
DATE: 11-15-83
VACUUM SYSTEM INSTALLATION
PAGE: 7 OF 8
AERO SAFE CORPORATION
DRAWN BY
D. SURSELY
DRAWING NUMBER
820501
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