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2.22.7.3 Alignment Exit. Alignment is exited whenever ALIGN is deselected (unboxed), an A/A
weapon is selected, MENU is selected, TDC priority is reassigned, ACM mode is selected, or the master
mode is changed. This removes the alignment cross from the HUD, removes the FINE option, unboxes
ALIGN, and returns the cage/uncage function to the previously assigned system.
2.22.7.4 Alignment Verification. When the HMD is in normal mode a cross is displayed on the HUD
at the reported HMD LOS. See figure 2-66. If the reported HMD LOS is outside the HUD FOV, the
cross flashes at the HUD FOV limit.
2.22.8 Navigation Master Mode. If present, the MC displays the A/A L&S with the TD box and its
associated TLL, or the A/G designation with the TD diamond and its associated TLL. However, if both
the A/A L&S and the A/G designation are present, only the A/A L&S TLL is displayed.
2.22.8.1 NAV Master Mode TDC Priority. When in NAV master mode, the TDC can be assigned
priority to the HMD by pressing the castle switch forward. This is indicated by an open aiming cross
with a dot in the center being displayed. If TDC priority is removed from the HMD, the dot is removed
from the center of the aiming cross.
2.22.9 Helmet Not Installed. When the MC determines that the HMD is not on, or the EU is not
responding to the MC via the mux bus, the MC reverts to the current no-helmet mechanization
forslaving weapons, sensors, HOTAS, and HUD display.
A1-F18EA-NFM-000
I-2-183 CHANGE 1
Figure 2-65. Fine Alignment
A1-F18EA-NFM-000
I-2-184 CHANGE 1
2.22.10 Navigation Master Mode. If present, the MC displays the A/A L&S with the TD box and its
associated TLL, or the A/G designation with the TD diamond and its associated TLL. However, if both
the A/A L&S and the A/G designation are present, only the A/A L&S TLL is displayed.
2.22.10.1 NAV Master Mode TDC Priority. When in NAV master mode, the TDC can be assigned
priority to the HMD by pressing the castle switch forward. This is indicated by an open aiming cross
with a dot in the center being displayed. If TDC priority is removed from the HMD, the dot is removed
from the center of the aiming cross.
2.22.11 Helmet Not Installed. When the MC determines that the HMD is not on, or the EU is not
responding to the MC via the mux bus, the MC reverts to the current no-helmet mechanization for
slaving weapons, sensors, HOTAS, and HUD display.
Figure 2-66. Alignment Verification
A1-F18EA-NFM-000
I-2-185 (Reverse Blank) CHANGE 1

CHAPTER 3
Service and Handling
3.1 SERVICING
Refer to A1-F18EA-NFM-600.
A1-F18EA-NFM-000
I-3-1 (Reverse Blank) ORIGINAL

CHAPTER 4
Operating Limitations
4.1 LIMITATIONS OF THE BASIC AIRCRAFT
4.1.1 Engine Operation Limitations. During normal engine operation, engine parameters (e.g., N1,
N2, and EGT) are maintained within limits by the FADEC. Refer to figure 4-1 for engine operation
limitations.
Limitations N2 (%) N1 (%) EGT
(°C)
Nozzle
(%) Oil Press (psi)
Transient (MIL / MAX) 102 103 976 − −
Steady state MAX 100 100 952 50 to 100 80 to 150 (warm oil)
MIL 932 0 to 35
Ground IDLE ³ 61 ³ 32 250 to 500 77 to 83 35 to 90 (warm oil)
Start ³ 10 − 871 − · Min 10 psi within 30 sec
· 180 psi max after 2½ min
Figure 4-1. Engine Operation Limitations
4.1.1.1 Engine Vibration Limitations. Engine vibration limitations are:
1. FAN VIB: 1.6 ips max
2. CORE VIB: 2.2 ips max
4.1.2 CG Limitations. 16.8 to 31.8% MAC
4.1.3 Airspeed Limitations. The airspeed limitations for the basic aircraft (with or without pylons)
in smooth or moderately turbulent air with the landing gear retracted and flaps in AUTO are shown
in figure 4-2. Subsystem related airspeed limitations are shown in figure 4-3.
A1-F18EA-NFM-000
I-4-1 ORIGINAL
Subsystem Position/Action Airspeed/Groundspeed
Refueling Probe
Extension/Retraction 300 KCAS
Extended 400 KCAS
Landing Gear
Extension/Retraction/Extended 250 KCAS
Emergency Extension 170 KCAS
Trailing Edge Flaps HALF-FULL 250 KCAS
Tires
Nose Gear 195 KGS
Main Gear 210 KGS
Wingfold Spread/Fold 60 knots
Canopy Open 60 knots
Figure 4-3. Subsystem Airspeed Limitations
Figure 4-2. Basic Aircraft Airspeed Limitations
A1-F18EA-NFM-000
I-4-2 ORIGINAL
4.1.4 Gross Weight and Lateral Weight Asymmetry Limitations. Refer to figure 4-4 for gross weight
and lateral weight asymmetry limitations.
Condition Gross Weight Limitation
(lbs)
Lateral Weight Asymmetry
(ft-lb)
Field takeoff 66,000 26,000
Inflight
　
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