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commanded to lock. The WING UNLK caution will not be removed until both wings are locked (both
beer cans down). Once the wings are spread and locked, the ailerons will droop to the position
scheduled by the FCCs based on FLAP switch position.
The wings can be stopped in an intermediate position by placing the WINGFOLD switch to HOLD.
If the wings are spread, selecting HOLD unlocks the wings without folding, allowing full time NWS HI
to be engaged for operations in the carrier environment. This function is useful when NWS HI is
desired but wingfold is not, e.g., dearming wingtip missiles after carrier arrestment.
With the wings spread and locked, wingfold is commanded by placing the WINGFOLD switch to
FOLD. In order for the wings to unlock, ground power must be applied or the aircraft must be WonW
(left main). The initial FOLD command electrically unlocks the wings (beer cans extended, WING
UNLK caution displayed) and fairs the ailerons. When the FCCs determine that (1) weight is on
wheels, (2) airspeed is less than 100 KCAS accelerating or 66 KCAS decelerating, (3) the ailerons are
faired, and (4) both wings are unlocked, the FOLD command is sent to the electric drive units to fold
the wings. When each wing reaches the completely folded position, power is removed to that electric
drive unit
2.8.3 WINGFOLD Switch. The WINGFOLD switch, located on the lower right main instrument
panel, is lever-locked in all three positions. The switch has a barrier guard to prevent inadvertent
actuation.
FOLD
(& unlock)
Unlocks the wings (WING UNLK caution displayed), fairs the ailerons, and, when
allowed by the FCCs, folds the wings.
HOLD
(& unlock)
Stops wing movement in an intermediate position. If spread, unlocks the wings.
SPREAD
(& lock)
Spreads and locks the wings. (WING UNLK caution removed when both wings are
locked).
Ensure the WINGFOLD switch is lever-locked in the SPREAD position
during takeoff checks. If the wings are commanded to unlock or fold
during a catapult shot, the wings will unlock, the ailerons will fair, the
wings may fold partially, and the aircraft will settle.
2.8.4 Wingfold Overheat Cutout Protection. The wingfold electric drive units are designed to meet
the following duty cycle requirements: two (2) fold-spread cycles followed by a twelve (12) minute
cooldown period. If wingfold operation exceeds this duty cycle, overheat cutout protection may
shutdown wingfold operation to prevent actuator damage. Once overheat cutout protection has been
activated, normal wingfold operation is not restored until actuator temperature drops within limits;
however, the wings can still be unlocked, folded, or spread manually.
A1-F18EA-NFM-000
I-2-56 ORIGINAL
2.9 FCS - FLIGHT CONTROL SYSTEM
The flight control system (FCS) is a fly-by-wire, full authority control augmentation system (CAS).
The FCS provides four basic functions: aircraft stability, aircraft control, departure resistance, and
structural loads management. Since the basic airframe is statically neutral to slightly unstable, a
primary function of the FCS is to maintain aircraft stability at all flight conditions. The FCS also
provides full authority control of the aircraft by implementing the basic flight control laws which
determine aircraft response to pilot inputs. Pilot inputs from the stick and rudder pedals send
electrical commands to two quad-redundant, digital flight control computers (FCC A and FCC B).
There is no mechanical linkage between the stick and rudder pedals and the flight control surfaces.
FCC software determines what commands are sent to the various flight control surfaces to exercise
pitch, roll, and yaw control of the aircraft. Additionally, the FCS provides departure resistance by
either refusing to accept or by tailoring pilot inputs that would otherwise lead to an aircraft departure.
Lastly, the FCS provides structural loads management by limiting g-available to prevent an aircraft
overstress or by retracting flight control surfaces at airspeeds that would otherwise exceed the
structural limits of the airframe. See figure 2-18 for a functional diagram of the flight control system.
2.9.1 Flight Control Surfaces. The aircraft has 12 primary flight control surfaces including leading
edge flaps (LEFs), trailing edge flaps (TEFs), ailerons, twin rudders, horizontal stabilators, and
spoilers. LEFs, TEFs, ailerons, and stabilators can be moved both symmetrically or differentially for
pitch and roll control. Flight control surface deflection limits are shown in figure 2-19.
Pitch control is accomplished with symmetric stabilators and, in some conditions, with rudder toe-in
or rudder flare. Roll control is accomplished with combinations of ailerons, differential stabilators,
　
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本文鏈接地址：NATOPS Flight Manual 飛行手冊 1(58)