(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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MAINTENANCE MANUAL
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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