757 AMM 飞机维护手册 自动飞行 AUTOFLIGHT 1(175)

曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者

 3)  The multi-channel engage logic one enables the generation of runway align engage when roll angle and delta ground track are less than 10 degrees and 2 degrees, respectively, and the LOC LINEAR logic is one.
 (c) Rollout Engage 1) Rollout directional control engage logic is generated when radio height is five feet. This maintains delta runway engage and delta runway path at logic one while runway align engage goes to zero. Delta LOC deviation distance, which was synchronized to zero, is now increased, at a rate limited to 2 ft/sec, to the current value of filtered LOC deviation distance. This is converted into deg/sec and applied to the rudder integral command signal chain. 2) When rollout directional control engage becomes logic one, additional feedback is added. Body yaw rate is summed with pseudo body rate computed from ground speed and rudder position, and multiplied by a linear constant. This eleminates nose wheel skid on touchdown and thus ensures effective nose wheel steering as soon as the nose wheel touches the ground. As ground speed reduces, rudder control becomes less effective and nose wheel steering provides primary rollout direction control.
 3)  When ground speed reduces to below 25 ft/sec, inverse gain schedules cause increased command response as rollout speed reduces thus improving LOC centerline tracking.
 (d) Rollout Command Processing
 1)  Runway alignment command in degrees of roll is summed with LOC proportional command. The result is applied to the roll flight director. This signal is also differentiated and added to the LOC integral command. This combined signal is the roll attitude command integrator input in the ROLLOUT engage mode.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 22-13-00
 ALL  ú ú 04 Page 48 ú Jan 20/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

 2)  Aileron or wheel position and ALCS servo position are summed to generate the roll equalization signal. This signal is limited to |2 degrees and converted into a deg/sec roll command. At MCHENG the equalization roll rate signal is added to the roll command signal. This signal modifies the response of an FCC coming online at MCHENG to compensate for electrical and mechanical hysteresis which results in small variations of LVDT outputs for the same surface position.
 3)  At MCHENG |40 degrees becomes the reference for max/min select limiters. The aileron is also limited to servo command |40 degrees. These larger control limits are required at lower speeds during approach when rapid airplane response is necessary.
 (25) Roll Go-Around Mode (Fig. 18)
 (a) Significant MCP Features
 1)  GUN 001-050, 052-999; the MCP may show any of the following switch dot-bar matrices illuminated before entry into the go-around mode: HDG HOLD, LNAV, LOC APP, CMD. The F/D switches may be ON or OFF. The HDG display shows selected runway heading before G/A and MCP selected heading during G/A.
 2)  GUN 051; the MCP may show any of the following switch dot-bar matrices illuminated before entry into the go-around mode: HDG HOLD, LNAV, LOC APP. The F/D switches may be ON or OFF. The HDG display shows selected runway heading before G/A and MCP selected heading during G/A.
 (b) Roll Go-Around Flight Path
 1)  The sequence of events if G/A is selected during an ILS approach is shown. Position A indicates pre-go-around conditions. The airplane is on final approach; G/S and flare are engaged; flaps less than 20 degrees. The EADI displays rollout white as the rolled armed mode since that would normally be the next mode.
 2)  Position B shows the G/A select conditions. Go-around is initiated by pressing the G/A switch on the thrust levers. The ILS guidance and annunciation are discontinued; G/A is shown as the roll engaged mode (with no roll armed mode annunciation); and G/A thrust, pitch-up commands and roll commands are generated. The AFDS status remains the same as before G/A thrust. The flight director is shown on the EADI during G/A, with the F/D switch in the ON or OFF position, for any channel not CMD engaged.
 3)  Position C indicates the G/A climbout. The EADI displays G/A green as the roll and pitch engaged modes. The G/A mode will be retained until cancelled by the selection of a conflicting pitch or roll mode.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
　
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：757 AMM 飞机维护手册 自动飞行 AUTOFLIGHT 1(175)