B. BSCU Configuration (PIN PROGRAMMING)
 (1) Principle At BSCU energization, the pin programming integrated in the BSCU is compared with the aircraft pin programming (strap connection). Any disagree results in switching the Normal braking to the Alternate mode without anti-skid regulation (ALT OFF-NWS OFF). The BSCU pin programming can be adapted by means of the BSCU menu mode, via the CFDIU. This procedure is described in 32-46-00-00. At the end of the menu mode, the system must be set to OFF then to ON to be correctly reset. Moreover, the pin programming modification must also be performed on the second BSCU system.
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 (2) BSCU configurations The various configurations available depend on the parameters below:
 -aircraft type,
 -brake type,
 -wheel type (different diameters),
 -deceleration rate in special automatic braking mode,
 -brake fan option. R
 C. Anti Skid Control
 (1) The inputs and outputs of the anti skid system are shown in the schematic (Ref. Fig. 056)
 NOTE : The Braking/Steering Control Unit is designed for use with
____ several types of brakes. The selection is made through the pin-programming integrated in the BSCU, on the wiring side of the aircraft.
 (2)
 Principle (Ref. Fig. 057) The speed of each main gear wheel is compared to the reference speed. With braking ordered, when the speed of a braked wheel decreases to below the input control speed (Vc), the anti skid system sends a brake release order. This order keeps the wheel speed value at the input control speed. A slip law function of the reference speed is introduced. The anti skid system has the corrective networks necessary to stabilize the feedback loop. The servovalve is the pressure-servoed electro-hydraulic component. The static gain of the brake is between 300 and 450 mN/bar depending on the brake type. The tachometer transforms the angular velocity of the braked wheel into a frequency. A converter transforms the input frequency into a digital signal that the microprocessor can use directly.

 (3)
 Description

 (a) Calculation of the aircraft speed
 1 In flight:
_ The reference speed is given by a fixed value Vo = 50 m/s VREF = Vo.
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 Anti Skid - Schematic
 Figure 056

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 INTENTIONALLY BLANK

 1 1
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 Anti Skid - Principle
 Figure 057

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R
R
R
2_ On impact of the main landing gears, during acceleration of
 the main gear wheels, a logic monitoring the acceleration of
 the wheels and hydroplaning determines, from the smallest of
 the highest wheel speeds per gear (VR) and from its
 derivative, the end of the wheel acceleration phase. 
(Ref. Fig. 058)
 The brakes are released as long as this phase is not over.
 During this phase, the reference speed is computed from a
 deceleration forced at 0.25 g and from VR as follows, so as to
 obtain the best reference speed evaluation for the following
 phases : 
(Ref. Fig. 058, 059)
 Vref (t)  = MAX (Vref (t-dt) - 2.5dt ; VR (t)) (in m/s)
 3_ During the roll, without braking control, the reference speed
 is obtained in the same manner as during the wheel
 acceleration phase, as a function of a deceleration forced at
 0.25 g and of VR :
 Vref (t) = MAX (Vref (t-dt) - 2.5dt ; VR (t)) (in m/s)
 4_ During braking, the reference speed is obtained from the speed
 VR and the aircraft deceleration (gamma) determined from the
 airframe longitudinal acceleration and pitch angle given by
 the ADIRUs 1 and 3.
 (Ref. Fig. 060)
 The reference speed is calculated as follows :
 Vref (t) = MAX (Vref (t-dt) + gamma (t)dt ; VR(t))  (in m/s)
 5_ The logic which modifies the reference speed calculation as a
 function of the FLIGHT/GROUND information is obtained from
 LGCIU discretes (main gear shock absorbers compressed), the
 tachometer speed VR and the ground speed V GROUND. V GROUND is
 calculated from the ground speeds delivered by the ADIRUs 1
　
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