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
Field landing, FCLP, T&G 50,600
Catapult 66,000 22,000
Carrier landing / barricade 44,000
Figure 4-4. Gross Weight and Lateral Weight Asymmetry Limitations
4.1.4.1 Lateral Weight Asymmetry Calculations. Lateral weight asymmetry should be calculated
using the weight of asymmetric stores on stations 2 through 5 and 7 through 10 (refer to figure 4-5). The
weight of an asymmetric missile or pod on stations 1 or 11 is not included in the listed asymmetry
limitations and should not be used in this calculation for any phase of flight. The weight of asymmetric
internal wing fuel is negligible for takeoff and can be ignored inflight (with no FUEL XFER caution
displayed), but must be included for landing due to landing gear structural load limitations.
Figure 4-5. Asymmetric Stores Limitations
A1-F18EA-NFM-000
I-4-3 ORIGINAL
NOTE
· If a FUEL XFER caution is displayed and the internal wing tanks are
unbalanced, the weight of asymmetric internal wing fuel must be used
in calculating total weight asymmetry in all phases of flight. Completely
split internal wing tanks (one full and one empty) have the
potential of reaching 14,000 ft-lb of lateral weight asymmetry.
· For landing, internal wing tank asymmetry may not be a factor
depending on fuel state. For instance, with a normally operating fuel
system, the wing tanks should be completely transferred (except for a
small amount of recirculation fuel) below 9,000 lb of internal fuel. In
most cases 9,000 lb is at or below the max trap fuel weight for carrier
landings (44,000 lb GW). However, for field landings up to 50,600 lb
GW, higher fuel states are possible, and the contribution of asymmetric
internal wing fuel must be used to ensure that 26,000 ft-lb of
asymmetry is not exceeded.
· The following is a rule of thumb for calculating internal wing tank
asymmetry: pounds of fuel split x 10 (e.g., a 200 pound fuel split
equates to approximately 2,000 ft-lb of asymmetry).
· With a symmetrically loaded aircraft, jettison or normal release of an
inboard store in excess of 3,562 lb (e.g., a full 480-gal external fuel
tank) or a midboard store in excess of 2,322 lb (e.g., GBU-24) exceeds
the lateral weight asymmetry limitation and is prohibited, except in an
emergency. Release of heavy weight inboard or midboard stores in the
normal SMS release sequence may require an outboard station to be
ballasted (so as not to exceed the lateral weight asymmetry limitation).
A1-F18EA-NFM-000
I-4-4 ORIGINAL
4.1.5 AOA Limitations - Flaps AUTO. Refer to figure 4-6 for AOA limitations with flaps in AUTO.
AOA Limitations - Flaps AUTO(1)
Lateral Weight
Asymmetry
(1,000 ft-lb)
Subsonic Supersonic
£ 6
Unrestricted
£ +15°
Unrestricted
> +15°
Half lateral stick or
half rudder pedal
inputs only
> 6 to £ 8
-6 to +15°
and
Single axis inputs only (2)
> 8 to £ 12 Low or Slow
(£ 20k ft or £ 250
KCAS)
Unrestricted
High and Fast
(> 20k ft and > 250
KCAS)
£ +30°
> 12 to £ 26 -6 to +15°
and
Single axis inputs only (2)
Notes:
(1) Rolling maneuvers up to abrupt, full stick (full stick in less than 1 second) are authorized within the
AOA and acceleration limitations specified in figure 4-7.
(2) In ``Single axis inputs only'' regions, avoid rolling or yawing the aircraft while changing longitudinal stick
position. It is acceptable to pull, stop, then roll or to pull and counter any roll-off induced by the heavy
wing under g.
Figure 4-6. AOA Limitations - Flaps AUTO
4.1.6 Acceleration Limitations. With flaps in AUTO, the acceleration limitations for the basic
aircraft (with or without empty pylons) in smooth air with the landing gear retracted are shown in
figure 4-7. In moderate turbulence, reduce deliberate accelerations 2g below that shown in figure 4-7
to minimize the potential of an aircraft over-g.
Acceleration limits during landing gear extension/retraction, or with landing gear extended, are 0.0
to +2.0g (symmetrical) and +0.5 to +1.5g (rolling).
A1-F18EA-NFM-000
I-4-5 ORIGINAL
Figure 4-7. Acceleration Limitations - Basic Aircraft
(with or without empty pylons) (Sheet 1 of 2)
A1-F18EA-NFM-000
I-4-6 ORIGINAL
Figure 4-7. Acceleration Limitations - Basic Aircraft
(with or without empty pylons) (Sheet 2 of 2)
A1-F18EA-NFM-000
I-4-7 ORIGINAL
4.1.7 Limitations with Flaps HALF or FULL. Refer to figure 4-8 for flaps limitations when HALF or
FULL.
Parameter Limitation
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
NATOPS Flight Manual 飞行手册 1(123)
