H81751 H19066
Autopilot and Yaw Damper System Component Location  5C4 
22-11-0  Figure 1 (Sheet 1)  Jan 20/83 
Page 4 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

500  Autopilot and Yaw Damper System Component Location 
Nov 15/67  Figure 1 (Sheet 2)  22-11-0 
Page 5 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

G.  Roll axis control is provided by the roll control channel and associated components. The operating modes of the roll axis are the manual mode, including heading and roll attitude control and roll commands through control wheel steering; heading select; heading hold, localizer and omnirange control, and OMEGA steering. The roll control channel operates in conjunction with the airplane compass (directional gyro) flight instrument, vertical gyro, VOR navigation systems, OMEGA navigation system and the radio altimeter. The compass system supplies heading reference, the flight instrument system supplies preset heading and preset course signals, the vertical gyro supplies bank angle signals, the VOR navigation system supplies localizer and omnirange deviation signals, the OMEGA systems supply steering control signals and the radio altimeter supplies signals for localizer gain programming.
H.  The autopilot and yaw damper are single channel systems.
I.  Since the SP-77 automatic flight control system makes maximum use of solid state microelectronics and high level digital logic circuits, circuit functions throughout the description and operation are assigned two values (0, 1) of the binary numbers system. An active circuit is considered a 1 state and an inactive circuit is considered a 0 state. The assignment of a 1 or 0 is based on the following example: ROLL ENGAGE is 1 provided the system is roll engaged, also ROLL ENGAGE is 1 provided the system is not engaged. If the system is not engaged, ROLL ENGAGE is 0. If the system is engaged, ROLL ENGAGE is 0. Circuit symbology is standard. Boolean algebra functions are used and described as follows:
(1)  
An AND circuit requires all inputs of a logic circuit to be high to obtain a high output. A . symbol is used to designate AND.

(2)  
An OR circuit requires any one input of a logic circuit to be high to obtain a high output. A

+ symbol is used to designate OR.

(3)  
A bar over a function designates a logic inversion (NOT function), e.g., if PITCH ENGAGE = 0, PITCH ENGAGE = 1; conversely, if PITCH ENGAGE = 1, PITCH ENGAGE = 0.

(4)  
A double NOT bar over a function negates the NOT function, e.g., PITCH ENGAGE = PITCH ENGAGE.

(5)  
By definition, all functions which actuate (close) a switch or complete a circuit are considered 1 when the affected circuit is in the same state as the noted function. For example, the function ALT HOLD+G/S ENG = SWITCH CLOSED (1) when the altitude hold is selected or when glide slope beam is captured. Also the function

22-11-0 May 20/82 Page 6
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

 PITCH ENG . CWS OD = PITCH ENG + CWS OD = SWITCH CLOSED (1) when the pitch channel is not engaged or control wheel steering is not out of detent. Also the function G/S ENG . PLUS 10 SEC = G/S ENG + PLUS 10 SEC = SWITCH CLOSED (1) when the pitch channel is in the glide slope intercept mode (glide slope not engaged) or the 10 second glide slope capture period has terminated (plus 10 seconds NOT NOT). The switch will open when the pitch channel is in the glide slope engage mode (the VBS has dropped out) and the 10-second timer has not clocked 10 seconds. This function may be shown as G/S ENG . PLUS 10 SEC = SWITCH CLOSED = 0.
J.  To aid discussion of autopilot and yaw damper system operation, reference numbers are assigned to summing points and solid-state switches. Solid-state switches are presented by conventional switch symbols. The logic function opposite each switch indicates the condition(s) necessary to actuate (close) the switch. System gain adjustments, attenuation and parallel summing resistors are not shown on diagrams and schematics for clarity and simplification.
2.  Yaw Damper Components (All except coupler P/N 4084042)
NOTE: For aircraft with coupler P/N 4084042 installed (incorporating SB 27A1206), see 22-12-01.
A.  Yaw Damper Coupler
(1)  
The yaw damper coupler is installed on the E1-1 shelf of the electronic equipment racks in the electrical and electronic compartment.

(2)  
The yaw damper coupler, Part No. 4030952 contains solid-state components on modern plug-in cards with printed circuit boards. The cards and subassembly installed in the yaw coupler rack are: yaw computation, BITE, and power supply cards, and a rate sensor with yaw BITE panel subassembly. The front panel of the computer contains 2 lights (FAIL, PASS), a GO push-button for initiating each BITE test which is annunciated by a digital indicator, a LAMP TEST push-button for checking lamp continuity and a 2-position BITE toggle switch labeled OFF and ARM. Test points are on the lower portion of the panel.
　
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