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and slat system is disabled. Flaps and slats will remain
in the position they were in when failure or malfunction
occurred. The auxiliary flaps are automatically commanded
to retract. There is no asymmetry protection for
the auxiliary flaps.
2.21.2.3 Flap Wing Interlocks. The main flap and
auxiliary flap commands are interlocked electrically and
mechanically with the wing sweep to prevent flap fuselage
interference. An electrical interlock in the CADC
and a mechanical command in the wing-sweep control
box prevent wing sweep aft of 22” with auxiliary flaps
extended. In a similar manner, upon extension of the
main flaps, the wings are electrically and mechanically
limited to wing-sweep angles less than 50’. The FLAP
handle is mechanically prevented from moving to the
down position if wing position is aft of SO”. If flaps are
lowered with wings between 21” and 50°, main flaps
will extend but auxiliary flaps will remain retracted.
If flaps are extended with wings between
21° and SOD, auxiliary flap extension is
inhibited and a large nosedown pitch trim
change will occur.
Pulling the FLAP/SLAT CONTR SHUTOFF
circuit breaker (RA2) will eliminate
flap overtravel protection and could eliminate
mechanical or electrical main and
auxiliary flap interlocks and may allow
the wings to be swept with the flaps partially
or fully down in the wing-sweep
emergency mode.
2.21.2.4 Maneuver Flap and Slat Mode. The
main flaps can be extended to 10’ with the slats extended
to 7” within the altitude and Mach envelope shown in
Figure 2-51.
Maneuver flaps and slats are automatically extended
and retracted by the CADC as a function of angle of
attack and Mach number (Figure 2-52). The schedule
commands full maneuver flaps and slats as soon as the
slattedw ing maneuveringe fficiency exceedst hat of the
clean wing.
Note
CADC maneuver flap commands are automatically
reset when the flap handle is placed
down greater than 2’, wing-sweep BOMB
mode is selected, or maneuver flaps are commanded
to less than lo by the CADC because
of dynamic pressure.
The angle-of-attackin put to the CADC from the alpha
computerisinhibitedandwillretractthe~euv~devices
if they are extendedw hen the LDG GEAR hgndlei s lowered.
Thisistoensurethatthemaneuverdevicesareretracted
before lowering the FLAP handle. Maneuver
devices extended condition is indicated by a SLATS
barberpole and an intermediate (10”) flap position.
ORIGINAL 2-92
NAVAIR 9l-FMAAD-1
5
0
0.3 0.4 0.5 0.6 0.7 0.6 a.9 1.0
MACH NUMBER -TRUE
Figure2 -51. ManeuveFr lapE nvelope
@F600.2370
Figwe 2-52. ManeuveSr lat/FlapA utomaticS chedulfeo r CAJX!
2-93 ORIGINAL
NAVAIR 01.Fl4AAD-1
To avoid fuel impingement on the fuselage boattail
and nozzles, tieI dump operations are prevented with
the speedbrakese xtended.
Ifmaneuver devices are not retracted prior to
lowering the FLAP handle, a rapid reversal
of the flaps will occur with possible damage
to the flap system.
2.22 SPEEDBRAKES
The speedbrskesc onsist of threei ndividual surfaces,
one upper and two lower panels on the aft fuselage
between the engine nacelles (Figure 2-53). The speedbrakes
may be infinitely modulatedon the extension and
retraction cycle. Operating time for full deflection is
approximately 2 seconds. Hydraulic power is supplied
by the combined hydraulic system (nonisolation circuit),
and electrical power is through the essential No. 2 dc
bus with circuit overload protection on the pilot right
circuit breaker panel (SPD BK P-ROLL TRIM ENABLE)
(RBZ).
2.22.1 Speedbrake Operation. Pilotcontrolofthe
speedbrakes is effected by use of the three-position
speedbrakes witch on the inboard side of the right throttle
grip (Figure 2-54). Automatic retraction of the speedbrakes
occurs with placement of either or both thmttles
at MIL or loss of electrical power.
Note
l Loss of combined hydraulic pressure with
the speedbrakesre tractedo r extendedw ill
causet he speedbrakesto move to a floating
position.
. The speedbrake/fuel dump interlock is
electrically bypassed during a combined
hydraulic system failure, enabling the pilot
to dump Abelw hen the speedbmkesa re
floating or modulating. The electrical bypass
is enabled whenever the combined
pressure falls below 500 psi.
l Do not extend the speedbrakesin flight
within 1 minute (nominal) after terminating
fuel dump operationst o allow residual
fuel in the dump mast to drain.
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F-14D 飞行手册 Flight Manual 1(108)
