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SPD
5_0_0_ __f_t_._ _R_A
Runway align
starts
5_ _f_t_._ _R_A_
200 ft. RA
B__e_l_o_w _1_5_0_0_ _f_t_._ _R_A_
__________
LOC
ROLLOUT
G/S
LOC G/S
CMD
LAND 3
LAND 3
LAND 3
LOC FLARE
ROLLOUT FLARE
T_O_/_G_A_ _A_r_m_e_d_ _b_u_t_ _n_o_t_ _d_i_s_p_l_a_y_e_d_
CMD
LOC VNAV PTH
LNAV
LOC
VNAV PTH
CMD
ROLLOUT
G/S
FLARE
LAND 3
LOC FLARE
_________
ROLLOUT
IDLE
SPD
A_P_P_
heading move to selected course)
25 ft. RA
LAND 2 annunciation inhibited
(MCP heading window, PFD, and ND selected
April 01, 2001
747 Operations Manual
Automatic Flight -
System Description
Copyright © The Boeing Company. See title page for details.
D6-30151-425 4.20.15
With the first push of either TO/GA switch:
• roll and pitch activate in TO/GA
• autothrottle activates in thrust (THR) to establish a 2000 FPM climb
• if current airspeed remains above the target speed for 5 seconds, the target
airspeed is reset to current airspeed, (to a maximum of the IAS/MACH
window speed plus 25 knots)
With the second push of either TO/GA switch:
• autothrottle activates in thrust reference (THR REF) at full go–around
thrust
TO/GA level–off:
• at the set altitude, the AFDS pitch flight mode annunciation changes to
altitude hold (ALT); all autopilots, except first in CMD, disengage
• A/T remains in THR or THR REF until SPD mode is selected. Speed
protection prevents exceeding the maximum operating, gear extended, or
flap placard speed
• TO/GA remains the active roll mode until another mode is selected
TO/GA mode termination:
• below 400 feet radio altitude, disengage autopilot and turn off both flight
directors
• above 400 feet radio altitude, select a different roll or pitch mode; all
autopilots, except first in CMD, disengage
If the A/P systems are compensating for an assymmetric thrust condition when
they revert to a single A/P in CMD configuration, the rudder returns to the
trimmed position unless the pilot exerts the rudder pedal force required to
maintain the rudder position.
April 01, 2001
747 Operations Manual
Copyright © The Boeing Company. See title page for details.
4.20.16 D6-30151-425
Automatic Flight -
System Description
Automatic Flight Go–Around Profile
Automatic FlightWindshear Recovery
The AFDS provides windshear recovery guidance by means of the normal
go–around pitch and roll modes.With go–around armed, pushing a TO/GA switch
commands a pitch–up of 15 degrees or slightly below the pitch limit, whichever is
lower.
As rate of climb increases, AFDS transitions from pitch to airspeed control. The
target airspeed is IAS/MACH window airspeed or current airspeed, whichever is
greater when TO/GA is activated. If current airspeed remains above the selected
speed for 5 seconds, the selected airspeed is reset to current airspeed, (to a
maximum of the IAS/MACH window speed plus 25 knots).
SPD LNAV VNAV PATH
ABOVE 400 FT RA
ABOVE 1000 FT RA
CMD
VNAV SPD
LNAV TO/GA
TO/GA TO/GA
ALTITUDE CAPTURE
CMD
CMD
CMD
THR
THR REF LNAV
PUSH TO/GA
PUSH LNAV
PUSH VNAV
SWITCH(ES)
THR
(THRUST LIMIT
CHANGES TO CLB)
April 01, 2001
747 Operations Manual
Automatic Flight -
System Description
Copyright © The Boeing Company. See title page for details.
D6-30151-425 4.20.17
When the autopilot is not engaged when go–around is initiated, the pilot must fly
the windshear recovery following the flight director commands. If the autothrottle
is not armed, the thrust levers must be advanced manually.
Flight Envelope Protection
There are three forms of flight envelope protection:
• stall protection
• overspeed protection: maximum operating, gear extended, flap placard
• roll envelope bank angle protection
Speed protection prevents exceeding the maximum operating, gear extended, or
flap placard speed. To minimize transient speed overshoots, the FMC uses a five
knot margin. Speed reduction below the minimum maneuvering speed is also
prevented.
With the autothrottle active, speed protection is normally available for all
operations except V/S pitch mode. Autothrottle control is limited to the current
reference thrust limit (CLB, CRZ, CON, etc.) and idle.
Speed protection is also provided through the elevators in the following pitch
　
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