TM 1-1520-238-T-7
11–244
11–28.
DASE – WIRING INTERCONNECT DIAGRAM (BUCS ACTIVATED) (cont)
11–28
NOTES:
HIGHWAY USE: THE ALPHA CHARACTER IDENTIFIES A SPECIFIC LINE, AND THE NUMBER IN
PARENTHESIS IDENTIFIES THE SHEET NUMBER WHERE THE SIGNAL TERMINATES.
1.
RELAY ACTUATED BY SQUAT SWITCH S350. ON GROUND - CONTACTS B2 AND B3 CLOSED, SQUAT RELAY DE - ENERGIZED.
2.
WITH AIRCRAFT ON GROUND. AIRBORNE CONDITION SIMULATED WHEN SQUAT SWITCH FIXTURE IS INSTALLED.
3.
0 VAC AT MID TRAVEL: 10 VAC WITH COLLECTIVE STICK FULL UP OR FULL DOWN.
4.
0 VAC AT MIDTRAVEL: 10 VAC WITH CYCLIC STICK FULL FORWARD OF FULL AFT.
5.
0 VAC AT MIDTRAVEL: 10 VAC WITH DIRECTIONAL PEDALS FULL LEFT OR RIGHT.
6.
0 VAC AT MIDTRAVEL: 10 VAC WITH CYCLIC STICK FULL LEFT OR RIGHT.
7.
0 VAC AT MIDTRAVEL : 5 VAC AT MAXIMUM TRAVEL.
8.
MAGNETIC SWITCHES: SOLENOID HOLDS SWITCH ON WHEN MANUALLY SET TO ON.
9.
28 VDC IN ONLY WHEN BUCS SELF TEST SWITCH IS HELD IN PLT OR CPG POSITION.
10.
± 4 MA MAXIMUM CURRENT VARIATION.
11.
0 VAC MIDTRAVEL: 2.5 VAC AT MAXIMUM TRAVEL.
12.
BUCS TST SWITCH PLT - CONTACTS 1-2 AND 4-5 CLOSED CENTER - CONTACTS 2-3 AND 4-5 CLOSED
CPG - CONTACTS 2-3 AND 5-6 CLOSED.
13.
ELECTRICAL SYSTEM (TM 1-1520-238-T-6).
14.
HS DESIGNATES A HARD SPLICE WHICH CANNOT BE DISCONNECTED.
M DESIGNATES A SOFT SPLICE WHICH MAY BE DISCONNECTED FOR A WIRING CHECK.
15.
HYDRAULIC SYSTEM (TM 1-1520-238-T-5).
16.
PRESENT AT FORCE TRIM RELEASE.
17.
WITH PILOT OR CPG FORCE TRIM SWITCH AT FORCE TRIM RELEASE POSITION.
18.
WITH PILOT FORCE TRIM SWITCH AT FORCE TRIM ON POSITION.
19.
SHOWN AT FORCE TRIM ON POSITION SPRING LOADED FROM FORCE TRIM RELEASE
POSITION TO FORCE TRIM ON POSITION.
SWITCH POSITION
TERMINALS CONNECTED
FORCE TRIM OFF
5 TO 6.8 TO 9, 11 TO 12
FORCE TRIM RELEASE
4 TO 5.7 TO 8, 10 TO 11
(MOMENTARY RELEASE)
FORCE TRIM ON (NORMAL)
4 TO 5.8 TO 9, 10 TO 11
20. PUSHBUTTON SWITCH USED ONLY FOR FORCE TRIM RELEASE.
21. ABOVE 60 KNOTS PROVIDES AUTOMATIC TURN COORDINATION
± 2.6 VDC MINIMUM.
22.
ASE INDICATORS LIGHT WHEN 28 VDC IS REMOVED.
23.
VARIES FROM APPROXIMATELY 0.5 VDC TO 5.0 VDC. 5 VDC WITH NO CHANGE AT SOURCE.
24.
VARIES BETWEEN LIMITS SHOWN. DEPENDS ON AIRSPEED CHANGE DATA.
25.
REFER TO PARAGRAPH 11-89. STABILATOR - WIRING INTERCONNECT DIAGRAM.
26.
AVIONICS CONFIGURATION - HEADING ATTITUDE REFERENCE SYSTEM (HARS) (TM 11-1520-238-23-2).
27.
REFER TO PARAGRAPH 11-13. FLIGHT CONTROL SYSTEM - WIRING INTERCONNECT DIAGRAM.
M70-327-29A
SHEET 29 OF 29
