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recommended increase the initial pitch rate but do not increase the reference AOA. If stabilator trim
is less than 6.5°, the CK TRIM caution will be set when the throttles are advanced above 27° THA
(FLAP switch FULL).
c. External fuel tank quantities - CHECK
Do not catapult with partially full external fuel tank(s) (£2,700 lbs). Fuel
sloshing may cause structural damage to the tanks, pylons, and/or
airframe.
8.2.4 Catapult Trim. See figure 8-1.
A1-F18EA-NFM-000
III-8-2 ORIGINAL
CATAPULT TRIM CALCULATIONS
1. Enter with:
Example
Gross Weight _______ (66K)
CG from Form-F _______ (19.6)
Lateral Weight Asymmetry _______ (0)
2. Using Gross Weight and Table A, determine type of launch (MIL or MAX)
Catapult Power Setting Requirements
Weight Board
(1,000 lb)
Power Setting
64 to 66 MAX only
58 to 63
Max (MIL optional only if
ambient temperature is
£ 90°F)
46 to 56 MIL (MAX optional)
32 to 45 MIL only
Table A
Example
Type Launch ______ (MAX)
To reduce engine susceptibility to hot gas reingestion and compressor
stalls, transition from MIL to MAX during the catapult stroke shall
not be performed except in an emergency.
Figure 8-1. Launch Trim (Sheet 1 of 5)
A1-F18EA-NFM-000
III-8-3 ORIGINAL
3. Using Gross Weight and Asymmetry, determine expected endspeed. Use Table B if symmetric or
the higher endspeed of Tables B and C if asymmetric.
Catapult Launch Endspeed
(Symmetrical Loading)
GW
(1,000)
Endspeed (MIN +15)
(KCAS)
MIL MAX
66 - 161
65 - 159
64 - 158
63 165 156
62 163 154
61 161
60 158
59 156 153
58 154
£ 57 153
Table B
Catapult Launch Endspeed
(Asymmetric Loading)
Asymmetry
(1,000 ft-lb)
Endspeed (MIN +15)
(KCAS)
2 153
4 156
6 159
8 161
10 162
12 163
14 165
16 166
18 167
20 168
22 169
Table C
Example
Expected
Endspeed _______ (161)
Figure 8-1. Launch Trim (Sheet 2 of 5)
A1-F18EA-NFM-000
III-8-4 ORIGINAL
Catapult Launch Trim MIL or MAX Power - Charts A and B
Figure 8-1. Launch Trim (Sheet 3 of 5)
Example: Baseline Longitudinal Trim - _______ (14°)
4. Determine required baseline longitudinal trim using Chart A (MIL Power) or Chart B (MAX
Power). Enter with Form-F CG. Move vertical to Expected Endspeed line, interpolating between
lines if required. Move horizontal to required longitudinal trim, rounding to nearest whole degree.
A1-F18EA-NFM-000
III-8-5 ORIGINAL
5. Longitudinal trim MUST be adjusted for the aft CG shift that occurs during normal fuel burn.
The CG can shift aft by as much as 3% MAC (F/A-18E) or 1% MAC (F/A-18F) when Tank 2 fuel
drops to approximately 2,100 lb and Tank 1 fuel drops to approximately 1,000 lb. This CG shift can
affect longitudinal trim by as much as 7° and must be accounted for to prevent catapult with a
significant mis-trim. Once Tank 1 has dropped to approximately 1,000 lb, fuel scheduling maintains
the CG at an essentially neutral position. Table D is a rule-of-thumb for decreasing longitudinal trim
based solely on Tank 1 Fuel quantity. Decrease baseline longitudinal trim by the ``Trim Delta'' value
down to but in no case less than 7° TEU stabilator.
Trim Adjustments for Normal
Fuel Burn
Tank 1 Fuel
Quantity (lb)
Trim Delta - (°)
F/A-18E F/A-18F
2,400 -1 -
2,000 -3 -
1,500 -5 -1
1,000 -7 -2
Table D
Example
Adjusted
Longitudinal Trim
_______ (11°)
(e.g., 0+30, 800 lb burn)
NOTE
If longitudinal trim must be adjusted after differential stabilator has
been input for a lateral weight asymmetry, push the T/O TRIM
button, adjust longitudinal trim and re-input differential stabilator
Figure 8-1. Launch Trim (Sheet 4 of 5)
A1-F18EA-NFM-000
III-8-6 ORIGINAL
6. If asymmetric, determine required differential stabilator (lateral trim) from Chart C. Input
differential stabilator after longitudinal trim has been set, trimming into the light wing (unloaded
wing down).
Example
Differential
Stabilator _______ (0°)
Failure to input differential stabilator trim for catapult launches with
asymmetric stores can aggravate aircraft controllability, particularly
following a single engine failure.
Figure 8-1. Launch Trim (Sheet 5 of 5)
Catapult Launch Differential Stabilator - Chart C
A1-F18EA-NFM-000
III-8-7 ORIGINAL
8.2.5 Taxi. The canopy should be down with oxygen mask on and the ejection seat armed prior to
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NATOPS Flight Manual 飞行手册 1(145)
