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3C2 AIM-9 TANK 4 AIM-64 TANK AIM-9
3c3 AIM-9 AIM-7 TANK 4 AIM-54 TANK AIM-7 AIM-9
3c4 AIM-7 TANK 4 AIM-54 TANK AIM-7
3c5 AIM-9 AIM-54 TANK 4 AIM-54 TANK AIM-54 AIM-9
3C6 AIM-54 TANK 4 AIM-54 TANK AIM-54
. (‘) These store conf ration limi 11~0a pply en multir 10~8 stub pylc are carric t stations 1 E 6.
. Flight operating limitations applicable to the above configurations are also applicableto down loadings, except down load
of external tank to MXU-776/777 which shall be considered as a clean store station for limitation purposes.
. For captive carriage of inert or live AIM-54, installation of ejector cartridges in LAU-132 is mandatory in order to provide
jettison capability.
l ForcaptivecarriageofinertorliveAIM-7,installationofejectorcartridgesinLAU-92ismandatoryinordertoprovidejettison
capability.Thisdoes notapplytoCATM-7F-Zmissiles usedfor ballast (refertoNAVAlR01 -F14AAD-75 Weapon Stores
Loading Manual).
l For shorebased operations all CATM-7F-1 (Sparrow training rounds) shall be configured with a modified shear wafer to
preclude inadvertent actfvation of the guidance and control unit, and subsequent ejection of the missile.
. Simultaneous loading of AIM-7 on store station 4 and AIM-54 on store station 3 and 6 is an authorized configuration.
Limitations of fuselage AIM-54 apply for carriage, individual missile limitations apply for launch/jettison.
. AIM-9 conffgurations include both LAU-7 and LAU-130 carriage.
IWARNINO)
. In all cases the center of gravity position must remain within limits. The aft limit can be
easily exceeded if stations 3 and 6 are not loaded.
l With MA ARM ON and all conditions satisfied for AIM-54 launch, an ATM-54 (training
round) will be ejected if the trigger or launch button is depressed.
l With MA ARM ON and all other conditions satisfied for AIM-7 launch, a CATM-7F-1
(Sparrow training round) will be ejected when the trigger or launch button is pressed
unlessamodifiedshearwaferisinstalled. Emergency/selectiiejettisonofaCATM-7F-1
is Still Dossible with a modified shear wafer installed.
Figure 4-1. Store Station Configuration NZtS
ORIGINAL 4-2
NAVAIR Ol-Fl4AAD-1
F 11 O-GE-400
OIL: MILL-23699 OR MIL-L-7808
FUEL: MIL-J-5624 JP5 (JP-4, JP-8 ALTERNATES)
Figure 4-2. Instrument Markings
4-3 ORIGINAL
NAVAIR Ol-Fl4AAD-1
FllO-GE-400
Figure 4-3. Engine Operating Limits
ORIGINAL 4-4
thesel.i mits shall be enteredo n the maintenancea ction
form for appropriate maintenance action.
4.2.1 Maximum Airspeeds. Maximum speeds
are presented in calibrated knots and true Mach
number. These values are derived from the positionerror-
correction curves of the production pitot-staticoperateda
irspeeda nda ltitude system.A OA is presented
utilizing the conventional indicated units AOA while
sideslip angle limits are presented in terms of degrees
rudder deflection.
Note
Unless otherwise specified, the limits presentedh
erein pertain to flight with the stability
augmentation system on.
4.2.1.1 Cruise Configuration. With wing sweep in
the MANUAL or AUTO mode, the maximum allowable
airspeedsa re shown in Figure 4-4.
In emergency wing-sweep mode, the following combination
of Mach and wing-sweep schedule must be
used:
1. <0.4TMN - 20°.
2. 5 0.7 TMN - 25’.
3. < 0.8 TMN - SO’.
4. S 0.9 TMN - 60’.
5. > 0.9 TMN - 68”.
4.2.1.2 Approach Configuration
1. Landing gear - 280 KCAS.
2. Landing flaps and slats - 225 KCAS.
With the landing gear extended or in transit,
abrupt rolls or uncoordinated turns
above 225 KCAS can cause structural
failure of the landing gear doors.
After takeoff, move the FLAP handle to
the UP position passing 180 KCAS to ensure
flap and slat airspeed limits are not
exceeded.
NAVAIR 0%Fl4AAD-1
4.2.1.3 In-Flight Refueling
1. Refueling probe - 400 KCAZVO.8 TMN.
2. In-flight refueling (cruise configuration) - 200
to 300 KCAS/0.8 TMN.
3. In-flight refueling (approach configuration) -
170 to 200 KCAS.
4.3 ACCELERATION LIMITS
Note
Limits are based on a gross weight of
49,548 pounds. See Figure 4-5 for the
variation of maximum ?oad factor with
gross weights greater than 49,548 pounds.
Coordinated turns with small rudder and
lateral stick inputs are defined as symmetrical
flight.
4.3.1 Cruise ConfiguratIon. See Figures 4-5 and
4-9.
4.3.2 Approach Configuratlon
1. Landing gear and/or landing flaps and slats - 0
to 2.Og (symmetrical or rolling).
4.4 ANGLE-OF-ATTACK LIMITS
4.4.1 Cruise Configuration. AOAislimitedbythe
　
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