(2)  
Analog Outputs

 (a)  There are four analog servomotor generator outputs. These are SERVO CMD L-FWD and REV, and SERVO CMD R-FWD and REV. The SERVO CMD R-FWD and REV signals are not used.

 (3)  
Analog Discrete Outputs

 (a)  Analog discretes that turn on the A/T disengage light are A/T WARN 1 (normal) and A/T WARN 1 (battery). Outputs to the EICAS computer and central warning system are A/T WARN 2 (normal) and A/T WARN 2 (battery) (Ref 22-34-00).
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OPTION/CONFIGURATION  NUMBER PLUG  PIN NUMBER  PIN CONNECTION  CODE  TMS FUNCTION  MCDP READOUT TEST 57
GND  OPEN  +28V DC 
ENGINE AIRFRAME  D383A D383B  E15 C1 G11 F6 D10  X X X  X X  1 0 0 0 1  RB211-535E4 ENGINE  03 PROGRAM, 57 ENGINE 
THRUST LIMIT  D383B D383A  H10 K5 F9 F7  X X  X X  0 0 1 1  FOR CLIMB MODE FIXED PERCENTAGE DERATES  LIM OPT, 03 57 THRST 
PARITY (ENGINE AIRFRAME AND THRUST LIMIT)  D383A  D13  X  1  ODD PARITY 
 
AUTOTHROTTLE  D383A  J12 F3 H6 J10  X X  X X  1 1 0 0  OPERATION WITHOUT ANTI-ICE PROTECTION  05 CUST OPT, 57 A/T 
AIRCRAFT  D383A D383B  E14 B11 F4 F2  X X X  X  0 0 1 0  757-200  02 PROGRAM, 57 A/C 
AIRCRAFT) PARITY (AUTOTHROTTLE AND  D383A  H15  X  0  ODD PARITY 
 
CUSTOMER OPTION  D383A  D10 D12  X X  0 0  OPT, 00 57 CUST 
G8  X  0  GND GIVES FULL TIME FAST/SLOW DISPLAY 
D11  X  0  GND GIVES DOUBLE PUSH RESET 
C11  X  0  DISCRETE GND GIVES NO FMC SELECT BY 

TMC Program Pin Data
Figure 3

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L AND R EICAS COMPUTER

L A/T SERVOMOTOR GENERATOR

A/T DISENGAGE LIGHT

L AND R EICAS COMPUTERS A/T FAST/SLOW COMMANDEPR ACTUAL (2) EPR BUG DRIVE (2) EPR REFERENCE FAULT DATA GROUND TEST DATA INTFC FAULT DATA MAINTENANCE DATA MAX EPR LIMIT POWER LEVER ANGLE (2) TEMP SELECTED BLEED DISCRETES (10) OPER MODE (14) OVERTHRUST LIMIT DISCRETE A/T DISCONNECT TMC VALID TEMP DERATE STATUS ENGINE IDENT (10)

SERVO CMD
A/T WARN 1 (NORMAL)
A/T WARN 1 (BATTERY)
A/T WARN 2 (NORMAL)
A/T WARN 2 (BATTERY)

THRUST MANAGEMENT COMPUTER
TMC Systems Interface Outputs
Figure 4

RIGHT SYMBOL GENERATOR
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 L. Configuration ~................................................. | EFFECTIVITY | TMC P/N: S241T200-XXXX | ...................................................
 |GUN 001-008  | -1410  |  |
 |  |  |  |
 |GUN 009-999  |  |  -1414  |

 2......................…...........…..............1
 2. Component Details
__________________
 A. Thrust Management Computer (Fig. 5)
 (1)  
The TMC consists of 8 modules in a 6 MCU case. The weight is 16.5 pounds. The TMC uses 115 vac and 28 vdc supplied through circuit breakers on P11.

 (2)  
The TMC is a realtime, digital processor (MCP 701A). Functions are in independent physical modules which communicate via a digital bus structure. A basic description of each module is given in the following paragraphs:
　
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