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APC will accomplish the PTO. Ifthe all stick method is
used at or inside the in-close position, the pilot must
avoid overrotation. The waveoff technique described in
Chapter 8 applies.
pi&G-,,,,,,,
A PTO initiated by APC disengagemenwt ith
large power additions prior to uncoupling
from ACLS will result in large nosedown
commands. A force-link disconnect may occur
if the control stick hits the forward stop.
Note
Routine downgrading from an ACL mode I
or IA approach by depressing the autopilot
emergency disengage paddle is not recommended
since DLC, roll SAS, and pitch SAS
will also be disengaged.
2-115 ORIGINAL
NAVAIR Ql-F14AAD-I
The ACLS mode (and autopilot) will be disengaged
automatically by loss of data-link A/P CPLR legend, no
messagef or more than 2 seoonds,o r a waveoff discrete
t?om the boat.
ACL commands control the aircraft through the
autopilot by spoiler commands in roll and by parallel
servo in pitch. Pitch commands move the control stick
See AFCS Pitch Parallel Actuator, paragraph 2.24.3.2,
for pitch actuator operation.
Note
If the pitch parallel actuator force Iii is me
chanically disconnected, the A/P REF advisory
legend indicating ACL engagement
may go out when coupling is attempted, but
the aircratl will not respond to SPN-42 commands
and the autopilot will uncouple Born
the ACL system when the first pitch commands
are received.
2.24.5 AFCS Test. Anindependenttestprogrsmand
associatedh ardwarei s in each AFCS axis computer.
2.24.5.4 AFCS OBC. Preflight indication of AFCS
performance can be obtained during poststart OBC. All
SAS switches should be engaged.A fter selecting OBC
on the MASTER TEST switch, the autopilot switch
should be placed to ENGAGE. A complete test sequencee
ncompassinga ll functions speciallya ssociated
with the selected axis (axes) will commence upon test
initiation and will cycle to OFF after completion. The
PITCH STAB 1 and 2, ROLL STAB 1 and 2, YAW
STAB OP, and YAW STAB OUT caution lights illuminate
and serve as an AFCS BIT running indication. All
other AFCS caution lights will illuminate momentarily
during BIT testing.
If the pitch parallel actuator is functioning properly,
large longitudinal control stick deflections should be
observed during OBC. An OBC with the flaps down
requires a longitudinal trim of 3O or more nose up; an
OBC with the flaps up requires not less than 0” nose. up.
A disconnectedp itch parallel actuatorf orce lii during
OBC is indicated by illumination of the AUTO PILOT
caution light, a PC acronym, and the absence of large
control stick deflections. It is possible for the force link
to be partially disconneoted, that is, disconnected mechanically
while electrical continuity is maintained. If
this has OCCW&, the AUTO PILOT caution light or PC
acronym may be absent ather OBC but no large stick
deflection will be observed. The implications of this
condition are the same as for a total disconneot.
2.2452 AFCS In-Flight BIT. AFCS in-flight BIT
provides automatic failure-initiated testing for the
AFCS pitch and roll axes only. In-flight BIT is not provided
for the yaw axis. If yaw axis faihnes occur, the
appropriatec aution light will illuminate and Sight envelope
restrictions must be observed as applicable. In-
Sight testing in the pitch and roll axes is automatically
initiated when an AFCS computer failure is de&&d.
When this failure is deteoM the affected axes will disengage,
both SAS caution lights for the affected areas
will illuminate, and BIT will automatically run for 9 to
14 seconds, depending upon the axis affected. Upon
completion of BIT, the failed channel light remains illuminated
and the other channel light goes out. WRA
failure indications can be observed in flight by the RIO
on the TID.
2.25 LANDING GEAR SYSTEMS
The aircmfi hasf blly retractable,tr icycle landing gear
operatedb y combined hydraulic pressurei n the normal
mode of operation and a stored source of pressurized
nitrogen for emergency extension. The landing gear retract
forward so that airloads and gravity assist on emergency
extension. Air-oil shock struts with oil metering
pins reduce landing loads transmitted to the airtkame,
and the shuts are fully extended with the gear in the
wells. AU landing gear doors remain open with the gear
extended.
2.25.1 Landlng Gear Handle. The landing gear
handle mechanically positions the landing gear valve for
normal operation. Pulling the handle meohanically selects
emergency extension of the gear using the pneumatic
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F-14D 飞行手册 Flight Manual 1(119)
