曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
19. D/L. - Check
20. Select assigned tiequency and ADDRESS.
21. Receive D/L messages.
8. Steering symbols.
b. TID target data.
c. Data-link messages,
10.4.8 High-Speed Dash (35,000 Feet)
22. Engineinstruments - Record.
107.7 maximum
935’
NO2 position (%)
OIL (PSI)
RPM (%)
EGT (“C)
Left Right Llmlts
50 to 60 (open)
25to65
107.7 maximum
935’
10.4.9 Descent
23. Air-to-air check
a. Radar modes
(1) PULSE.
(2) PD SRCH.
1 O-25 ORIGINAL
NAVAIR 0%FlrlAAD-1
(3) RWS.
(4) TWS AUTO.
(5) Tws&4AN.
(6) HRWS.
b. MLC switch - OUT-AUTO-IN (PD SRCH).
c. Navigation.
(1) Tacanfix - Recod(donotinitiateupdate).
A Latitude A Longitude
(2) Radar fix - Record (do not initiate up+@.
A latitude A Longltudo
(3) Visual fix - Record (do not initiete update).
A Latitude A Longltude I
d. Weapon systems checks against suitable airborne targets.
(1) Intercept targets, check operation in PD SRCH, RWS. aud TWS MAN.
(a) Observe transition to PULSE SIT.
(b) Retum to PULSE SRCH.
(c) Close to visual range end verify DD display.
(2) VSL mode - HI-LO LOCK-ON.
(3) MRL mode - Check LQCK-ON.
e. lm- Check Modes 1,2,3, and 3C.
lo-26
PROFILE
A
ABC
A
A
24. Air-to-ground check.
a. Select A/G.
b. Select CTGT mode.
(1) verify symbology.
(2) 30° dive 12,000-foot roll-in.
(3) Designate target.
(4) verify solution.
(5) Maneuver-designatorre mains on target.
(6) Complete 30° dive.
c. Select CCIP mode.
(1) verify symbology.
(2) 30° dive 12,000-foot roll-in.
(3) Fly impact point over target.
(4) Complete 30° dive.
d. Air-to-ground GUN sight.
(1) Select GUN.
(2) Dive angle greater than 15’.
(3) Check symbology.
e. Exit A/G.
25. Perform radar IBIT and record results.
26. NSV - SAHRS.
a. Pilot check HUD and VDI display and maneuver aim&.
b. Radarantennascan - Check.
10.4.10 Approach
21. Airspeed
a. Compare with pilot airspeed at 15 units AOA, record error knOts.
lo-27 ORIGINAL
NAVAIR 0%FlUD-1
ROFILE
BC
BC
10.4.11 Landing
28. lb&u - PS, or power switch - STBY.
10.4.12 In Chocks
29. INS/SAHRS and visual - Check and Update in Chcka.
a. Record closeout error.
INS
A Latitude A Longitude
SAHRS
,BC
b. Initiate 6x enable.
c. Observe ahcraft symbol shift on TID.
30. Call up maintenance current failures.
Record
18.4.13 Postflight
LBC 3 1. Walkaround inspection - Complete.
A rime Groundspeed
ORIGINAL lo-28
NAVAIR 0%F14AAD-1
PART IV
Flight Characteristics
Chapter 1 1 - Flight Characteristics
61 (ReverseB lank) ORIGINAL
NAVAIR 01-Fl4AAD-1
CHAPTER 11
Flight Characteristics
11.1 PRIMARY FLIGHT CONTROLS
Primary flight controls are devices that change the
flightpath of the aircraft. They consist of the differential
horizontal stabilizer for pitch and roll control,
the spoilers for supplementary roll control, and the
rudders for directional control. A stability augmentation
system is provided for the three axes of aircraft
motion.
11 .I.1 Pitch Control. The horizontaltail is effective
t?om under 100 knots to over Mach 2. Its effectiveness
gives the aircraft several capabilities not enjoyed by
other fighters, including low takeoff rotation speeds and
the ability to reach or exceed limit load factor over much
of the subsonic and supersonic envelope; it is also an
excellent drag device below 100 knots on landing rollout.
The major disadvantages of the large horizontal
stabilizer authority are that the pilot can generate high
enough pitch rates (particularly in the nosedown direction)
to cause coupling under certain conditions, and
that a pitch attitude sumcient to scrape tailpipes and
ventral tins can be attained on landing rollout or takeoff
rotation.
11.1.2 Roll Control. Differential deflection of the
horizontal tail surfaces provides primary roll control
throughout the flight envelope and is the only roll control
when the wings are swept beyond 62” (disabling the
spoilers).
Spoilers are very effective at low to medium AOA
for roll control, and reduce the aft fuselage torsional
loads induced by the differential tail. The spoilers are
also the primary mechanism for direct lift control and
spoiler braking.
11.1.3 Directional (Yaw) Control. Twin rudders
furnish directional control. Through strong dihedral effect
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：F-14D 飞行手册 Flight Manual 2(55)
