S 865-109

 (3)  
Remove the DO-NOT-CLOSE tag and close this circuit breaker on the panel P11.

 (a)  11G12, FSEU-1 PWR or FLAP SLAT ELEC UNIT 1 POWER
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 S 285-110
 (4)  
Make sure the R. AIL LOCK ACT/FSEU fault balls on the left and right SAMs are yellow.

 S 865-111

 (5)  
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the P11 panel:

 (a)  
11C14, FSEU-2 PWR or FLAP SLAT ELEC UNIT 2 POWER

 (b)  
11G21, FSEU-3 PWR or FLAP SLAT ELEC UNIT 3 POWER

 S 985-112
 (6)  
Push the RESET switch on the left and right SAMs.

 S 285-113

 (7)  
Make sure the R. AIL LOCK ACT/FSEU fault balls on the left and right SAMs are black.

 S 865-114

 (8)  
Open this circuit breaker on the P11 panel and attach a DO-NOT-CLOSE tag:

 (a)  11G12, FSEU-1 PWR or FLAP SLAT ELEC UNIT 1 POWER
 S 285-115
 (9)  
Make sure the R. AIL LOCK ACT/FSEU fault balls on the left and right SAMs are yellow.

 S 865-116

 (10)
 Remove the DO-NOT-CLOSE tag and close this circuit breaker on the P11 panel:

 (a)  11G12, FSEU-1 PWR or FLAP SLAT ELEC UNIT 1 POWER
 S 985-117
 (11) Push the RESET switch on the left and right SAMs.
 J. Put the Airplane Back to Its Usual Condition
 S 865-006
 (1)  Put the airplane back to the ground mode (Ref 32-09-02).
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 (2)  S 845-007Do the activation procedure for the spoilers if you did the deactivation procedure (Ref 27-61-00).
 (3)  S 985-118Set the ADC airspeed to 0 knot.
 (4)  S 985-119Set the EFC airspeed to 0 knot.
 (5)  S 985-120Set the pressure altitude to the ambient position.
 (6)  S 865-121Remove pressure from the pitot-static system.
 (7)  S 865-122Remove the DO-NOT-CLOSE tags and close circuit breakers on the P6 panel: (a) 6L15, PITOT HEAT CAPT MAIN (b) 6L22, PITOT HEAT F/O MAIN (c) 6L23, R AOA HEAT (d) 6L24, TAT PROBE HEAT
 (8)  S 865-123Remove the pressure from the hydraulic system if it is not necessary.
 (9)  S 865-124Remove electrical power if it is not necessary.

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 THRUST MANAGEMENT POWER - DESCRIPTION AND OPERATION
___________________________________________________
 1.  General (Fig. 1)_______
 A.  The Thrust Management System (TMS) computes and displays thrust limits and provides thrust lever control. The system interfaces with the engines through the servomotor generator, which drives thrust levers through "no-back" clutches. The Thrust Mode Select Panel (TMSP) and Thrust Management Computer (TMC) provide primary control of the servomotor generator.
 B.  The TMSP allows crew selection of thrust limit modes, alternate thrust limit ratings, and assumed temperature. The Engine Indication and Crew Alerting System (EICAS) (Ref 31-41-00) display unit displays the selected limit mode or rating, corresponding limits, and assumed temperature.
 C.  The TMC provides thrust limit computation and thrust lever control to Engine Pressure Ratio (EPR), airspeed, and Mach references. Minimum and maximum speed protection, thrust limit protection, and thrust lever retard during autoland are also functions of the TMC.
　
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