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sideslip limits.
With landing gear extended or in transit, abrupt rolls
and uncoordinated turns shall not be performed above
225 KCAS.
4.52 Cruise Configuration. With maneuver slats/
flaps extended, maximum allowable load factor is 6.5g
or the limits of Figure 4-5, whichever is less.
Subsonic maneuvering with roll SAS on shall not be
conducted above 15 units AOA with the landing gear
retracted.
Cross control inputs shall not be used in the area of
the flight envelope indicated in Figure 4-8.
When automatic maneuvering flaps/slats are not operating,
uncoordinatedla teral control inputs shall not be
used in the area ofthe flight envelope indicated in Figure
4-8.
4.5.3 Rolling Limits. With maneuver slats and flaps
extended,m aximum allowable load factor is 5.29 or the
limits ofFigure 4-9 (roll SAS on or roll SAS off) whichever
is less. Rolling limits are shown in Figure 4-9.
Do not initiate full lateral stick inputs
above 4.5g ifa 5.2g limit applies or above
3.5gifa4.0glimit applies. Control system
dynamics may cause load factor to increase
beyond limits.
If outboard spoilers fail with airspeed
greater than 400 KCAS and wing sweep
less than 62”, limit lateral stick deflection
to one-half pilot authority.
Note
AOA limitations shown in Figure 4-7 apply
to designated configurations.
4.5.4 Sldeslip Limits
4.5.4.1 All External Store Configurations
1. Below 0.7 TMN - Rudder inputs as required to
maneuver aircraft at high AOA.
2. Above 0.7 TMN - Rudder inputs coordinated
with lateral stick as required to educe or eliminate
the effects of adverse yaw at high AOA.
Rapid rudder inputs cause noseup pitch and
may generate snap roll departures.
3. Above 1.70 TMN - Intentional sideslips
prohibited.
pi&-(
If a supersonic engine stall and/or failure occurs,
arrest roll rate with lateral stick only.
Yaw SAS will maintain sideslip angle
within acceptable limits.
Note
Use of full available rudder is permitted at all
airspeeds if required to counteract adverse
yaw encounteredin maneuveringf light.
4.5.5 Prohibited Maneuvers. Thefollowingadditional
maneuvers are prohibited:
1. Intentional spins.
2. During afterburner operations:
a. Sustained zero to negative 0.5g flight.
b. Flight from negativeO .Sgt o negative2 .4g.s for
more than 10 seconds.
3. At MIL power or less: Zero or negative-g flight for
more than 20 seconds.
ORIGINAL 4-10
NAVAIR Ol-Fi4AAD-1
LANDING GEAR AND/OR FLAPS EXTENDED
Figure 4-6. Maximum Allowable Angle-of-Attack Rudder Deflections
4-11 ORIGINAL
NAVAIR Ql-FlUADCRUISE
CONFIGURATION
Figure 4-7. Angle-of-Attack Limits
ORIGINAL 4-12
NAVAiR WFl4AAD-1
Figure 4-8. Maneuvering Limits - Cruise Configuration
4. AIM-9 launch with landing flaps and slats
extended.
5. Fuel dumping with aftcrbumer operating or with
speedbrak~ extended.
6. Dual-engine afterburner takeoffs, waveoffs,
bolters, of catapult launches.
7. Single-engine maximum afierbumer takeoffs,
waveoffs, bolters, or catapult launches.
8. ACLS mode illA approaches.
9. Roiling maneuvers with AOA change greater than
360’ arc prohibited.
4.6 SAS LIMITS
4.6.1 Cruise Configuration
1. Pitch SAS off - LBA.
2. Yaw SAS off - 1 .O TMN.
3. Roil SAS off - 1.0 TMN (wing-mounted AIM-
54); 1.52 TMN (external tanks, fuselage AIM-54,
/VG stores); I.6 ‘I’hIN (all other configurations).
4.6.2 Approach Configuration
1. Pitch SAS off - LBA.
2. Yaw SAS off - LBA.
3. Roil SAS off - Not permitted during takeoff
and landing flap and slat transition.
Roll SAS must be let? on for carrier landings with
storea symmetryg reatert han 170,000in ch-pounds.( Example:
weapon rail at station 6 and AIM-54 missile at
station 8 equals 170,000 inch-pounds.)
4.7 TAKEOFF AND LANDING FLAP AND
SLAT TRANSITION LIMITS
4.7.1 Clean and Symmetric Stores Loading. See
Figure 4-10.
1. All transitions will be made in less than 45O bank
angle, roil SAS on.
2. All normal (flaps and slats fully down) takeoff
transitions will be initiated at a minimum altitude
of 200 feet AGL.
3. All other transitions will be made at standard field
operating altitudes, but no less than 800 feet AGL.
4-13 ORIGINAL
NAVAIR Ql-Fl4AAD-1
F-14D ROLL SAS ON
MANEUVERING ENVELOPE
DATE : SEPTEMBER ,884
DATA SASS : ESTIMATED FUGHT TEST
0.2 0.4 0.0 0.8 1.0 1.2 1.4 1.s 1.8 2.0 2.2
TRUE MAUI NUMBER
ROLLING MANEUVERS RESTMCTSO To:
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F-14D 飞行手册 Flight Manual 2(4)
