b) Set BITE switch to ARM. ON OFF
c) Press LAMP TEST switch and hold. 8 ON ON
d) Release LAMP TEST switch 0 ON OFF
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STEP TEST NO. OBSERVE LIGHTS PASS FAIL
Test 1 - Rate Gyro Filter a) Engage yaw damper and ensure hydraulics are on. b) Press GO switch. Observe after 1 second. 1 ON OFF
3) Test 2 - Engage Nulla) Engage yaw damper and ensure hydraulics are on (from Test 1). b) Press GO switch. Observe after 6 seconds. 2 ON OFF
4) Test 3 - Rate to Rudder (Displacement) a) Ensure yaw damper is engaged and hydraulics are on (from Test 2). b) b) Press GO switch. Observe after 1 second. 3 ON OFF
5) Test 4 - Rate to Rudder (Integral) a) Ensure yaw damper is engaged and hydraulics are on from Test 3). b) Press GO switch. Observe after 45 seconds 4 ON OFF
6) Test 5 - Trim Meter a) Ensure yaw damper is engaged and hydraulics are on (from Test 4). b) Press GO switch. Observe after 8 seconds. 5 ON OFF
7) Test 6 - Disengage Synchronization a) Disengage yaw dampers and ensure hydraulics are off. b) Press GO switch. Observe after 6 seconds. 6 ON OFF
8) Test 7 - Rate Gyro a) Ensure yaw dampers are disengaged and hydraulics are off (from Test 6). b) Press GO switch. Observe after 1 second. 7 ON OFF
9) Return BITE switch to OFF.
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(C) Yaw Damper (Coupler P/N 4030952-906) OBSERVE LIGHTS
TEST PASSSTEP NO. FAIL
1) BITE Self Test Arm a) Ensure yaw damper is disengaged. b) Set BITE switch to ARM. c) Press LAMP TEST switch and hold, d) Release LAMP TEST switch. 8 0 ON ON ON OFF ON OFF
2) Test 1 - Gyro Filter 1 a) Engage yaw damper and ensure hydraulics
are on.
b) Press GO switch. Observe after 1 second 1 ON OFF
3) Test 2 - Engage Null a) Engage yaw damper and ensure hydraulics are on (from Test 1). b) Press GO switch. Observe after 5 seconds. 2 ON OFF
4) Test 3 - Rate to Rudder (Displacement) a) Ensure yaw damper is engaged and hydraulics are on (from Test 2). b) Press GO switch. Observe after 1 second. 3 ON OFF
5) Test 4 - Rate to Rudder (Integral) a) Ensure yaw damper is engaged and hydraulics are on (from Test 3). b) Press GO switch. Observe after 40 seconds. 4 ON OFF
6) Test 5 - Disengage Synchronization a) Disengage yaw dampers and ensure hydraulics are off. b) Press GO switch. Observe after 5 seconds. 5 ON OFF
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STEP OBSERVE
TEST LIGHTS NO. PASS FAIL
7) Test 6 - Derived Accel. First Stage a) Ensure yaw damper is disengaged and hydraulics are off (from Test 5) b) Press GO switch. Observe after 6 ON OFF 1 second.
8) Test 7 - Rate Gyro Filter 2 a) Ensure yaw damper is disengaged and hydraulics are off.(from Test 6). b) Press GO switch. Observe 7 ON OFF after 1 second.
9) Test 8 - Rate Gyro
a) Ensure yaw dampers are disengaged and hydraulics are off (from Test 7).
b) Press GO switch. Observe after 8 ON OFF 1 second.
10) Return BITE switch to OFF.
D. Restore Airplane to Normal Configuration
(1)
Disengage yaw damper.
(2)
Disconnect pressure source from pitot static system. Refer to Chapter 34, Air Data Instruments.
(3)
Determine whether there is further need for electrical power on airplane; if not, remove external power.
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AUTOPILOT/FLIGHT DIRECTOR SYSTEM - DESCRIPTION AND OPERATION
EFFECTIVITY
SA ZS-SIA and on SD ST-AIB and on WA N235WA-N241WA GJ B-2509 and B-2510
1. General
A. The SP177 autopilot/Flight Director (AP/FD) system is an integrated autopilot and flight director system using common computational components. Two independent AP/FD channels are provided. Flight director indications for the captain are from auto flight control system (AFCS) computer A; flight director indications for the first officer are from AFCS computer B. No flight director switching between A and B systems is available for the captain and first officer; flight director command signals are connected directly to the attitude director indicators (ADI's) on the P1 and P3 panels (Fig. 1). The AFCS computers use either analog or digital input signals which are digitally processed to provide guidance commands for the autopilot and flight director systems (Fig. 2). Either autopilot A and/or autopilot B can be engaged for autopilot control of the airplane to pilot selected guidance commands on the AFCS control panel. Both autopilot channels may be engaged simultaneously to accomplish automatic approaches to CAT IIIA requirements. Control wheel steering (CWS) is used for manual control of the airplane thru the autopilot system. The ALTITUDE ALERT system computation and control is performed in the AFCS computers. Autopilot actuators for pitch and roll are connected to the appropriate control system linkage (Fig. 3 and 4).
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