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b737 auto flight
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100% found this document useful (2 votes)
387 views20 pagesB737 - Autoflight
b737 auto flight
Uploaded by
picooCopyright
© © All Rights Reserved
We take content rights seriously. If you suspect this is your content, claim it here.
Available Formats
Download as PDF or read online on Scribd
/ 20
Q 20emNve Teale ells ssa ey
“3
asl
“‘VIRYANAIR
Escaneado con Camscanner Features
FLIGHT MANAGEMENT
COMPUTER SYSTEM (FMCS)
‘The FMCS allows preplanned fight
profile control and guidance for best
performance and performance
management.
DIGITAL FLIGHT CONTROL,
‘SYSTEM (OFCS)
‘The DFCS includes these functions:
+ Autopilot
+ Flight director
Mach trim
+ Speed trim
+ Alttude alert
AUTOTHROTTLE FUNCTION
The autothrottle controls the engines
independently to get the best
performance.
BUILT-IN TEST EQUIPMENT
(BITE)
‘The BITE system gives fast and
accurate troubleshooting of the main
flight management system (FMS)
‘components.
YAW DAMPERMWHEEL TO
RUDDER INTERCONNECT
SYSTEM (WRTIS)
BED The yaw damper decreases the yaw
fates associated wih dutch ol and
turbulence. The WTRIS assists
manual tums when both A and B
hydraulic systems are in standby.
Autoflight
+ Flight Management Computer
‘System (FMCS)
+ Dual Flight Management
Compute
‘+ Digital Flight Control System
(FCs)
+ Autothrottle Function
+ Built-in Test Equipment (BITE)
+ Yaw Damper System
‘+ Whee! to Rudder Interconnect
‘System (TRIS)
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Escaneado con Camscanner Autoflight
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wes FCS and AUTOTHROTTLE. DISPLAYS ‘YAW DAMPERMVTRIS
‘Autofight Overview
‘Autoflight Systems FLIGHT MANAGEMENT AUTOTHROTTLE (AVT) SYSTEM
‘COMPUTER SYSTEM (FMCS)
‘The autofight system is made up of ‘The AT system controls the engine
these systems: The central part ofthe fight thrust levers. The FMC sends thrust
management system are the two __and speed targots to the autothrttle
+ Flight management computer fight management computers {or best overall fight performance.
system (FMCS) (FMC). ‘The autothrotle functions inside the
+ Digital fight control system flight control computer A (FCC A).
(oFcs) “The fight crow uses the control
+ Autothrotte system (A/T). display unit (CDU) to enter the route. YAW DAMPERWTRIS FUNCTION
‘and performance data forthe fight.
This group of systems operate ‘The FMCs calculate the lateral and The yaw damper gives commands to
together to decrease fight crew vertical components of the fight. It the rudder to decrease yaw rates
workload and provide automatic then sends these guidance from dutch roll and turbulence.
fight contol and automatic landing
capably, F Renige OP PFCS Io FOlOWINe Te WTRIS assists manual ums
when only the standby hydraulic
‘Autoflght status information is DIGITAL FLIGHT CONTROL system is available.
splayed on the common display SYSTEM (DFCS)
system display units and autoflight cae BUILT IN TEST EQUIPMENT
status annunciators. The DFCS includes the autopot,
flight director, altitude alert, speod ie deaton ol fhe system pent
There are wo stall management yaw trim and mach rim functions, The __f@84 accurate trouble-shooting and
dampers (SMYD) installed which FCS can use commands from the aintenance.
perform the yaw damper functions MICS or the fight crew can use the
and also the wheel to rudder DFCS mode control panel (MCP) to
interconnect system (WTRIS). control the airplane.
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Escaneado con Camscanner onic
‘OUTER
BARKER,
DESTINATION
Flight Management Computer
System (FMCS)
The flight management computer
(FMC) is the main component of the
flight management computer system.
The fight crew uses the control
display unit (CDU) to enter the route
and performance data for the
‘upcoming fight. With this fight plan
data and inputs from airplane
sensors, the FMC performs these
functions:
+ Navigation
+ Performance
+ Guidance.
‘An optional connection to the aircraft
‘communication andreportng system
(ACARS)is available, Iles the FMC.
receive fight plan data from a ground
station and send fight status fo the
Flight Management Computer System
NAVIGATION FUNCTION
The navigation data base in the FMC
‘memory includes all the navigation
data for the area of operation. This
data base is updated every 28 days.
The pilot can preselect the entire
fight pian from the navigation data
base. Also, the fight crew can have
the FMC fly an offset from the route.
‘The required time of arrival (RTA)
function is also available.
‘The FMC calculates the airplane
position as the flight continues. It
Uses the inertial reference function
‘and navigation aids, if available, to
calculate the position. The FMC
‘compares the calculated position
with the planned position. Any
deviation shows on the common
display system.
Bly eon
Autoflight
Display Unit
Ground Proximity Waring System
HUD Computer
airplane and the engines. The fight
crew enters gross weight, crise
allitude and cost index forthe fight.
‘The FMC uses this data to caleuate
thebest economy speeds, best fight
altitude and top of escent pint. The
CDU and the flight displays show the
target speeds and alftudes.
GUIDANCE FUNCTION
The FMC sends commands to the
digital fight control system (OFCS)
and the autothrottle (A/T) function.
‘The DFCS and the AT use these
signals to control the airplane in the
lateral (LNAV) and vertical (NAV)
parts of the fight plan
BUILT-IN TEST EQUIPMENT
arte)
‘The maintenance technician uses
ground station. PERFORMANCE FUNCTION the COU to operate BITE forte
‘Aporformanca data base in the FMC "
contains a performance model ofthe
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Gontrr Display FHC?
tne
Tansee
lay (2)
it
ek een
Ze
ro
FMC Source Selact Switch
‘Autofight Status Annunclator
Foo Aand 8
DED and
‘Autetvotde System (FCC A)
INAV Contol Panel 1 and 2
‘OME Inarogator and 2
Stal Management Yaw Damper and 2
Fight Data Recorder System
‘Ground roxy Waring System
HUD Computer
Fuel Quanity Procassor Unt
Flight Management Computer System Overview
Flight Management Computer
System
Duals the usual fight management
Computer system (FCS)
Configuration inthe airplane. The
‘main components are two fight
management computers (FMC), two
control display units (CDU) and two
transfer relays.
Each FMC calculates position data
with different sets of navigation aids
and ADIRU inputs. If navigation aids
are not availabe, the FMCs only use
‘separate ADIRU inputs for the
calculation. The FMCs combine thelr
calculations to caleuate a best
position. Both FMCs transmit this
(One FMCis the primary FMC and the
others the secondary. A transfer
switch controls the system
Configuration through transfer relays.
When the transfer switch isin
NORMAL or BOTH ON LEFT, FMC 1
i primary and FMC 2s secondary.
‘When the transfer switch is in BOTH
ON RIGHT, FMC 2 is primary and
FMC 1 is secondary.
‘When the transfer switch is in
NORMAL, FMC 1 sends data to all
single systems and to the number 1
system of dual systems. The data
from FMC 2.goes to the number 2
system of dual systems,
‘When the transfor switch is in BOTH
‘The output of each CDU connects to
both FMCs. The primary FMC
processes the CDU inputs and sends
{he data to the secondary FMC. The
display on both of the CDUS is from
the primary FMC.
‘The two FMCs compare inputs and G=s=
outputs at all imes. large
diference between the two causes
the secondary FMC to conditionally
fail and to alert the flight crew.
best position tothe CDS and other ONLEFT, FMC 1Is the source forall
user systems. ‘outputs, When the transfer switch in
BOTH ON RIGHT, FMC 2s the
source for all outputs.
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‘Avtoight status
ane
.
t
‘Aura Warning
Module ‘Common Display System
Digital Fight Control System
Digital Flight Control System ‘commands tothe common display For speed trim, the FCC controls the
(OFcs) system. The status and the mode of stabilizer trim electric actuator. It
‘operation of the autopilot and the moves the stabilzer to increase
‘Two independent fight control flight director show on the common _ airplane stability at low air speeds.
‘computers (FCC) contro these display system.
functions: DISENGAGE WARNING
ALTITUDE ALERT
+ Autopilot There is visual and an aural
+ Flight director ‘The altude alert function uses the warning to alert the fight crew i the
+ Alitude alert altitude selected on the MCP. The autopilot disengages. A red ight on
+ Mach trim FCC alerts the fight crew when the the autofight status annunciator and
+ Speed tim. airplane approaches or departs the the waller from the aural warming
selected alitude, There is an aural module give the warning,
AUTOPILOTIFLIGHT DIRECTOR alert from the remote electronics unit
(REU) and a visual alert on the BITE
Theflightcrewuses the mode control Common display system,
ppanel (MCP) to control the autopilot ‘The flight control computer provides
and the fight director. The fight crew MACH TRIM AND SPEED TRIM accurate, reliable, and fast builtin
engage the autopilot, tums on the test (BITE) capability using the
flight director, selects the modes and Mach trim and speed trim functions control display units (CDU).
selects the targets on the MCP, ‘operate with no fight crew input
For the autopilot function, the FCC For mach trim, the FCC controls the
sends commands to the autopilot __mach trim actuator. It moves the
aileron and elevator actuators to ‘levator to increase airplane stability
contralthe fight control surfaces.For at high air speeds.
the flight director function, the FOC
py S088 ch andro guidance
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Autofight Stats
Dy Fens
\
.
‘Aural Waring
odsle
Flight Control Computer (2)
‘Common Display System
Digital Fight Control System with Category NB
Digital Flight Control System
Category IIB capability
‘The DFCS with Category IIB
Capability performs all the functions
described earlier, and it also can
operate in any weather up to and
including CATIIB weather
‘minimums.
In this way, the DFCS operates as a
fall operational system capable of
‘completing approach, flare,
‘touchdown and rollout maneuvers.
In order to be fail operational, the
flight control computers (FCC)
receive additional inertial reference
data from the integrated standby
flight display (ISFO).
In order to perform rollout
maneuvers, the FCCs send signals
toa rudder servo actuator.
Without this option activated, the
DFCS operates as a fail passive
system capable of completing
‘approach, flare and touchdown
‘maneuvers.
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PAQ)
SHYD (2)
ADRUQ)|
Autoflight
Disconnat Swiches (2)
Primary Fight Displays
‘Autothrottle System
Autothrottle + Disconnect switches disconnect red light on the autofight status
the autothrotle ‘annunciator gives a visual warring it
‘The autothrottle (A/T) system can + Mode select push-buttons on the the autothrottle disengages.
‘contro the thrust levers from takeoff MCP select thrust or speed
totouchdown.Itgives maximum fuel contro. ‘The autothrotle system has built-in
‘conservation through smooth, test. Tis lets you do fast accurate
precise thrust control. Like other The fight crewcan select the A/T __maintenance. You do the tests ofthe
fight management sub-systems, the mode with the mode select push-__autothrottle system with the CDU.
‘autothrotle design gives maximum buttons on the MCP. Usually the __-Fromthe CDU. you can selectthese
‘operational and cost benefits. digital fight control system selects functions:
the correct autothrotle mode for the
‘The AIT function isin fight control fight phase. The active autothrotle + Current status
computer A (FCC A). The mode shows on the common display + fight fauts
utothrotte operates the thrust system, + Interactive
levers through two independent + Ident’Confg
‘servomotors. The AIT controls the The AIT moves the thrust levers to
engines independently to get the control thrust or airspeed.
best performance from each
‘engines. These are the A/T controls For thrust control, the FMC
in the fight compartment: calculates the correct thrust setting
for the fight phase.
+ Atm switch on the mode contro!
panel (MCP) arms the For airspaod control, the AT accepts
autothrotle ‘mach and airspeed commands from
+ Takeotlgo-around (TOIGA) the FMC or MCP, The AIT operates
switches select the takeoff or __withthe electronic engine control to
‘go-around modes: sive improved performance.
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Escaneado con Camscanner Autoflight
‘Autoflight Displays and Controls.
‘Mode selection and system engage
switches for the autopilot, fight
director and autothrottl are on the
‘mode control panel (MCP),
The TOIGA switches select takeoff
‘and go-around modes. They are on
the thrust levers. The engage status
‘and mode of operation show on the
sisplay units.
The takeoff models a combined fight
rector and autotrotle mode. The
autothrotle sets engine thrust io the
target value calculated by the fight
management computer FMC). The
fight rector gives commands to
contol the rate of cimb and then to
contol the selected airspeed set on
the MCP.
iO} (oO)
Autofight Displays and Controls
Vertical navigation (VNAV) and
Iatoral navigation (LNAV) ae the
‘normal cruise modes. When these
‘modes are selected, the FMC sends
‘commands to the autopl, ight
director and autothrotte. The
airplane flies the FMC route atthe
airspeed and alitude forthe selected
performance. The autopilot, ight
director and autothrottle work
together in these modes.
Other modes are available at the
‘option ofthe crew. The crew can
select modes to change and hold the
airplane altitude and to fly a radio
beam or heading. The crew uses the
‘mode control panel to select the
desired autopilot and fight director
‘mode. The autopilot o fight director
then sets the autothrotle mode that
ives the best combined
performance.
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‘Common Display System
‘The approach mode (APP) is for
landing. In the approach mode, the
fight director and the autopilot use
localizer and glideslope radio
signals. When the approach mode is
selected, you can engage both
autopiots for an automatic landing.
‘The autothrotle holds the MCP
selected airspeed in approach.
{In go-around, the autothrotte sets
the thrust levers to go-around thrust.
The fight director and, if available,
the autopilot, contro rate of climb,
airspeed and track.
The fight mode annunciator (FMA) is
on the primary fight display.
Autopilot fight director status shows
in the status fed ofthe FMA,
Autothrott, pitch, and roll modes
show in the other positions of the
FMA.
April 2013,
Escaneado con Camscanner 'DFCS BITE Index
Builtsn Test Equipment (BITE)
‘The CDU gives access to sel-
Contained in-fight monitoring and
ground test capabilties for these
systems or components:
+ Flight management computer
system - FMCS
+ Digital fight control system -
DFcs
+ Autothrotte - AT
+ Airdata inertial reference system
-ADIRS
+ Common display system - CDS
+Electronic engine control -
ENGINES
+Electronic contol unit - APU
+ Fuel quantity indicating system -
Fols.
Each component contains tests for
itself, ts sensor inputs, and other
interfaces. Also, each component
stores in-fght fault data for analysis
‘on the ground,
‘Curent Satus
Built-in Test Equipment
‘The technician selects test options
froma menu and supplies interactive
‘operator responses through the
COU. BITE does the tests and
supplies data to the technician to do
trouble-shooting. The technician
uses the verification tests to do.atest
ofthe interfaces after replacement of
alline replaceable unit (LRU).
The system allows fast, ine
maintenance fault isolation to a
single line replaceable unt.
TnFight Faults
Rigging Tests
The ENGINES prompt gives access
to engine exceedance data for
present and past fights.
‘The APU prompt gives access to
‘APU fault and system information.
The FAIS prompt gives access to
fuel quantity system faultand system
information
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Escaneado con Camscanner Autoflight
Pa
OO
Flight Contot Pane!
Yew Damper Funtion
‘eo to Rude ltrconnect Function
Yaw DamperMWTRIS System
Yaw DamperiWTRIS ‘These are the yaw damper ‘The WTRIS senses control wheel
components in the fight ‘movement and sends commands to
‘Theyawdampermovestherudderto compariment: the standby rudder powercontrolunit
crease yaw rates thal are related tomove the rudder.
to dutch rol. + Yaw damper switch
+ Yaw damper warn light Monitor circuitry in the computer
“The whee! to rudder interconnect disengages the yaw damperWTRIS
system (WTRIS) assists manual The yaw damperis available forthe for problems withthe postion =
tums when the standby hydraulic ful ight. The yaw damper and feedback or with the servo.
systemis on. WIRIS are engaged withthe yaw
damper switch on the overhead Youdo atestof the yaw damper and
‘The yan damper system connects to panel. The yaw damper war light WTRIS functions atthe stall
the main and standby rudder power goes off when the yaw damper is management yaw damper. A menu
control units to do the yaw damper engaged. lets you selec these BITE functions:
function.
‘The yaw damper uses inputs from + Existing faults
Stall management yan damper the airdata inertial reference units + Faulthistory
(SMYD) 1 connects tothe main (ADIRU)to getairplane yawrateand + Ground tests
rudder power control unit. lateral acceleration. italso uses +Other functions.
gross weight data from the fight
'SMYD 2 connects to the standby ‘management computer system
rudder power control uit (FMCS). The yaw dampers send
‘commands to the rudder power
Phe WARIS unction sonlyin SHY control unis to move the rudder and
stop the dutch rol, The rudder pedals
do not move when the yaw damper
‘moves the rudder.
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