F18. FLIGHT MANUAL (2008) - page 37

 

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F18. FLIGHT MANUAL (2008) - page 37

 

 

A1-F18EA-NFM-200
Figure 5-160. Single Engine Specific Range - 35,000 Feet - 34,000 Pounds
XI-5-170
ORIGINAL
A1-F18EA-NFM-200
Figure 5-161. Combat Specific Range - Stabilized Level Flight - 42,000 Pounds (Sheet 1 of 4)
XI-5-171
ORIGINAL
A1-F18EA-NFM-200
Figure 5-161. Combat Specific Range - Stabilized Level Flight - 42,000 Pounds (Sheet 2 of 4)
XI-5-172
ORIGINAL
A1-F18EA-NFM-200
Figure 5-161. Combat Specific Range - Stabilized Level Flight - 42,000 Pounds (Sheet 3 of 4)
XI-5-173
ORIGINAL
A1-F18EA-NFM-200
Figure 5-161. Combat Specific Range - Stabilized Level Flight - 42,000 Pounds (Sheet 4 of 4)
XI-5-174
ORIGINAL
A1-F18EA-NFM-200
Figure 5-162. Combat Fuel Flow - Stabilized Level Flight - 42,000 Pounds (Sheet 1 of 4)
XI-5-175
ORIGINAL
A1-F18EA-NFM-200
Figure 5-162. Combat Fuel Flow - Stabilized Level Flight - 42,000 Pounds (Sheet 2 of 4)
XI-5-176
ORIGINAL
A1-F18EA-NFM-200
Figure 5-162. Combat Fuel Flow - Stabilized Level Flight - 42,000 Pounds (Sheet 3 of 4)
XI-5-177
ORIGINAL
A1-F18EA-NFM-200
Figure 5-162. Combat Fuel Flow - Stabilized Level Flight - 42,000 Pounds (Sheet 4 of 4)
XI-5-178
ORIGINAL
A1-F18EA-NFM-200
Figure 5-163. Constant Altitude/Long Range Cruise (Sheet 1 of 2)
XI-5-179
ORIGINAL
A1-F18EA-NFM-200
Figure 5-163. Constant Altitude/Long Range Cruise (Sheet 2 of 2)
XI-5-180
ORIGINAL
A1-F18EA-NFM-200
BINGO
DRAG INDEX 0 COUNTS - FLAPS AUTO
REMARKS
• ALL ALTITUDES - x1000 FEET
• ALL FUEL REQD - x1000 LBS
• ALL DISTANCES IN NAUTICAL MILES
• ENGINE(S): (2) F414-GE-400
• SINGLE ENGINE: INOPERATIVE ENGINE WINDMILLING
DATE: 29 OCTOBER 1999
U.S. STANDARD DAY, 1962
FUEL GRADE: JP-5
DATA BASIS: FLIGHT DERIVED
FUEL DENSITY: 6.8 LB/GAL
SEA LEVEL
CONFIGURATION
CRUISE
DESCEND
FUEL REQD WITH HEADWIND (knots)
CRUISE
INBD
LDG
ENGINE
ALT
KCAS
DIST
0
50
100
150
KCAS
FUEL
DIST
GEAR
Dual
Up
43
237
81
3.7
3.9
4.2
4.7
307
5.9
Dual
Down
32
222
27
5.7
6.4
7.4
8.8
251
8.9
200
Single
Up
33
269
54
4.0
4.3
4.7
5.1
282
5.3
Single
Down
18
209
14
6.9
7.8
9.3
11.3
228
8.6
Dual
Up
43
237
81
3.5
3.8
4.0
4.4
307
5.5
Dual
Down
32
221
27
5.3
6.0
6.8
8.2
251
8.1
180
Single
Up
33
269
54
3.8
4.1
4.4
4.9
281
4.9
Single
Down
18
211
14
6.4
7.2
8.4
10.2
227
7.9
Dual
Up
43
237
81
3.4
3.6
3.8
4.2
306
5.0
Dual
Down
32
221
27
5.0
5.6
6.3
7.5
250
7.4
160
Single
Up
32
269
52
3.6
3.9
4.2
4.6
280
4.6
Single
Down
18
211
14
5.9
6.6
7.6
9.2
226
7.1
Dual
Up
43
237
81
3.2
3.4
3.7
4.0
306
4.6
Dual
Down
30
222
25
4.7
5.1
5.8
6.9
250
6.7
140
Single
Up
32
269
52
3.4
3.7
3.9
4.3
280
4.2
Single
Down
18
211
14
5.4
6.0
6.9
8.2
225
6.4
Dual
Up
43
237
81
3.1
3.2
3.5
3.8
305
4.2
Dual
Down
30
222
25
4.3
4.7
5.4
6.3
249
6.0
120
Single
Up
30
271
48
3.3
3.4
3.7
4.0
279
3.9
Single
Down
18
211
14
4.9
5.4
6.2
7.3
224
5.7
Dual
Up
39
258
71
2.9
3.1
3.3
3.6
305
3.8
Dual
Down
30
222
25
4.0
4.3
4.9
5.7
249
5.3
100
Single
Up
28
269
45
3.1
3.2
3.5
3.8
279
3.5
Single
Down
17
213
13
4.4
4.9
5.5
6.5
223
5.1
Dual
Up
34
274
58
2.8
2.9
3.1
3.3
304
3.4
Dual
Down
29
223
24
3.6
3.9
4.4
5.2
248
4.6
80
Single
Up
23
269
36
2.9
3.0
3.2
3.5
279
3.2
Single
Down
16
214
13
4.0
4.3
4.9
5.7
221
4.4
Dual
Up
28
280
46
2.6
2.7
2.9
3.1
303
3.0
Dual
Down
26
229
21
3.3
3.5
3.9
4.6
247
3.9
60
Single
Up
14
278
22
2.6
2.8
2.9
3.2
278
2.9
Single
Down
12
216
9
3.5
3.8
4.2
4.9
220
3.7
Dual
Up
19
283
30
2.4
2.5
2.6
2.8
303
2.6
Dual
Down
19
226
15
2.9
3.1
3.4
4.0
247
3.2
40
Single
Up
9
279
14
2.4
2.5
2.6
2.9
278
2.5
Single
Down
4
219
3
2.9
3.2
3.5
4.1
219
3.1
Dual
Up
10
292
16
2.1
2.2
2.3
2.5
302
2.2
Dual
Down
7
232
6
2.4
2.6
2.8
3.3
246
2.6
20
Single
Up
2
279
3
2.1
2.2
2.3
2.5
277
2.2
Single
Down
1
218
1
2.4
2.5
2.8
3.3
217
2.5
PROFILES:
• DUAL ENGINE AND GEAR UP: 515
KCAS TO 0.85
IMN
•SINGLE ENGINE AND GEAR UP: 310
KCAS TO
0.68
IMN
• DUAL ENGINE AND GEAR DOWN: 250 KCAS TO 0.45 IMN
•SINGLE ENGINE AND GEAR DOWN: 195 KCAS TO 0.42 IMN
DATA BASED ON:
• INITIAL ALTITUDE IS SEA LEVEL
• FUEL REQUIRED INCLUDES 1800 POUNDS RESERVE FUEL
• ZERO FUEL WEIGHT IS 34,000 POUNDS
• MILITARY THRUST CLIMB TO INDICATED ALTITUDE
• SEA LEVEL INCLUDES 25 KNOT HEADWIND
• 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED)
Figure 5-164. Bingo - Flaps Auto - Drag Index 0 Counts
XI-5-181
CHANGE 1
A1-F18EA-NFM-200
BINGO
DRAG INDEX 50 COUNTS - FLAPS AUTO
REMARKS
• ALL ALTITUDES - x1000 FEET
• ALL FUEL REQD - x1000 LBS
• ALL DISTANCES IN NAUTICAL MILES
• ENGINE(S): (2) F414-GE-400
• SINGLE ENGINE: INOPERATIVE ENGINE WINDMILLING
DATE: 29 OCTOBER 1999
U.S. STANDARD DAY, 1962
FUEL GRADE: JP-5
DATA BASIS: FLIGHT DERIVED
FUEL DENSITY: 6.8 LB/GAL
SEA LEVEL
CONFIGURATION
CRUISE
DESCEND
FUEL REQD WITH HEADWIND (knots)
CRUISE
INBD
LDG
ENGINE
ALT
KCAS
DIST
0
50
100
150
KCAS
FUEL
DIST
GEAR
Dual
Up
43
242
72
3.9
4.2
4.6
5.0
298
6.2
Dual
Down
32
218
26
5.9
6.6
7.7
9.2
246
9.2
200
Single
Up
30
258
44
4.3
4.6
5.1
5.6
277
5.7
Single
Down
15
213
11
7.2
8.3
9.9
12.2
225
9.0
Dual
Up
43
242
72
3.7
4.0
4.3
4.7
298
5.8
Dual
Down
32
218
26
5.5
6.2
7.1
8.5
246
8.5
180
Single
Up
30
257
44
4.1
4.4
4.8
5.3
277
5.3
Single
Down
15
213
11
6.7
7.6
8.9
10.9
223
8.2
Dual
Up
43
242
72
3.6
3.8
4.1
4.5
297
5.3
Dual
Down
32
217
26
5.2
5.7
6.6
7.8
245
7.7
160
Single
Up
30
257
44
3.9
4.1
4.5
4.9
276
4.9
Single
Down
15
212
11
6.1
6.9
8.1
9.7
222
7.5
Dual
Up
43
242
72
3.4
3.6
3.9
4.2
296
4.9
Dual
Down
31
218
25
4.8
5.3
6.0
7.2
245
6.9
140
Single
Up
29
257
42
3.6
3.9
4.2
4.6
275
4.5
Single
Down
15
212
11
5.6
6.3
7.2
8.7
221
6.7
Dual
Up
43
242
72
3.2
3.4
3.6
4.0
296
4.4
Dual
Down
30
219
24
4.4
4.9
5.5
6.5
244
6.2
120
Single
Up
28
257
40
3.4
3.6
3.9
4.3
275
4.1
Single
Down
15
211
11
5.1
5.7
6.5
7.7
219
6.0
Dual
Up
40
248
65
3.0
3.2
3.4
3.7
294
4.0
Dual
Down
30
219
24
4.1
4.5
5.0
5.9
244
5.4
100
Single
Up
27
257
39
3.2
3.4
3.6
4.0
274
3.7
Single
Down
15
211
11
4.6
5.0
5.7
6.8
218
5.3
Dual
Up
35
264
54
2.9
3.0
3.2
3.5
293
3.6
Dual
Down
29
220
23
3.7
4.0
4.5
5.3
243
4.7
80
Single
Up
23
262
33
3.0
3.1
3.3
3.6
274
3.3
Single
Down
15
211
11
4.1
4.5
5.0
5.9
217
4.6
Dual
Up
29
267
43
2.7
2.8
3.0
3.2
292
3.1
Dual
Down
26
224
20
3.3
3.6
4.0
4.7
243
4.0
60
Single
Up
17
269
24
2.7
2.9
3.0
3.3
273
3.0
Single
Down
13
211
10
3.5
3.9
4.3
5.0
212
3.9
Dual
Up
20
274
29
2.4
2.6
2.7
2.9
291
2.7
Dual
Down
19
222
14
2.9
3.1
3.5
4.0
242
3.3
40
Single
Up
11
270
15
2.5
2.6
2.7
2.9
272
2.6
Single
Down
6
215
4
3.0
3.2
3.6
4.2
206
3.2
Dual
Up
8
286
11
2.2
2.3
2.4
2.6
290
2.3
Dual
Down
7
228
5
2.4
2.6
2.9
3.3
242
2.6
20
Single
Up
2
273
3
2.1
2.2
2.4
2.5
272
2.2
Single
Down
1
203
1
2.4
2.6
2.8
3.3
200
2.6
PROFILES:
• DUAL ENGINE AND GEAR UP: 490 KCAS TO 0.83
IMN
•SINGLE ENGINE AND GEAR UP:
300 KCAS TO 0.64 IMN
• DUAL ENGINE AND GEAR DOWN: 250 KCAS TO 0.45 IMN
•SINGLE ENGINE AND GEAR DOWN:
195 KCAS TO 0.40 IMN
DATA BASED ON:
• INITIAL ALTITUDE IS SEA LEVEL
• FUEL REQUIRED INCLUDES 1800 POUNDS RESERVE FUEL
• ZERO FUEL WEIGHT IS 34,000 POUNDS
• MILITARY THRUST CLIMB TO INDICATED ALTITUDE
• SEA LEVEL INCLUDES 25 KNOT HEADWIND
• 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED)
Figure 5-165. Bingo - Flaps Auto - Drag Index 50 Counts
XI-5-182
CHANGE 1
A1-F18EA-NFM-200
BINGO
DRAG INDEX 100 COUNTS - FLAPS AUTO
REMARKS
• ALL ALTITUDES - x1000 FEET
• ALL FUEL REQD - x1000 LBS
• ALL DISTANCES IN NAUTICAL MILES
• ENGINE(S): (2) F414-GE-400
• SINGLE ENGINE: INOPERATIVE ENGINE WINDMILLING
DATE: 29 OCTOBER 1999
U.S. STANDARD DAY, 1962
FUEL GRADE: JP-5
DATA BASIS: FLIGHT DERIVED
FUEL DENSITY: 6.8 LB/GAL
SEA LEVEL
CONFIGURATION
CRUISE
DESCEND
FUEL REQD WITH HEADWIND (knots)
CRUISE
INBD
LDG
ENGINE
ALT
KCAS
DIST
0
50
100
150
KCAS
FUEL
DIST
GEAR
Dual
Up
42
235
63
4.2
4.5
4.9
5.4
291
6.6
Dual
Down
31
217
23
6.1
6.9
8.0
9.7
240
9.6
200
Single
Up
28
246
37
4.6
5.0
5.5
6.1
274
6.1
Single
Down
15
211
11
7.5
8.7
10.4
13.0
221
9.4
Dual
Up
42
235
63
4.0
4.3
4.6
5.1
290
6.1
Dual
Down
31
216
23
5.7
6.4
7.4
8.9
240
8.8
180
Single
Up
28
246
37
4.4
4.7
5.1
5.7
273
5.6
Single
Down
15
210
11
7.0
8.0
9.4
11.6
219
8.6
Dual
Up
42
235
63
3.8
4.0
4.4
4.8
289
5.6
Dual
Down
31
216
23
5.3
5.9
6.8
8.1
239
7.9
160
Single
Up
28
246
37
4.1
4.4
4.8
5.3
272
5.2
Single
Down
15
210
11
6.4
7.2
8.5
10.3
218
7.8
Dual
Up
42
235
63
3.6
3.8
4.1
4.5
288
5.1
Dual
Down
31
216
23
4.9
5.5
6.2
7.4
239
7.1
140
Single
Up
28
246
37
3.9
4.1
4.5
4.9
272
4.8
Single
Down
15
209
11
5.8
6.6
7.6
9.1
217
7.0
Dual
Up
42
234
63
3.4
3.6
3.9
4.2
287
4.6
Dual
Down
30
217
23
4.6
5.0
5.7
6.7
238
6.4
120
Single
Up
27
249
35
3.6
3.8
4.1
4.5
271
4.3
Single
Down
15
209
11
5.3
5.9
6.8
8.0
212
6.2
Dual
Up
40
241
59
3.2
3.4
3.6
3.9
286
4.2
Dual
Down
30
216
23
4.2
4.6
5.2
6.1
238
5.6
100
Single
Up
26
251
34
3.4
3.6
3.8
4.2
270
3.9
Single
Down
15
208
11
4.7
5.2
6.0
7.0
206
5.5
Dual
Up
36
256
51
3.0
3.2
3.4
3.7
285
3.7
Dual
Down
29
217
22
3.8
4.1
4.6
5.4
237
4.8
80
Single
Up
23
257
30
3.1
3.3
3.5
3.8
270
3.5
Single
Down
14
207
10
4.2
4.6
5.2
6.1
205
4.7
Dual
Up
28
257
38
2.8
2.9
3.1
3.4
283
3.2
Dual
Down
26
219
19
3.4
3.7
4.1
4.8
237
4.1
60
Single
Up
17
262
22
2.8
3.0
3.2
3.4
269
3.1
Single
Down
12
205
8
3.6
4.0
4.4
5.2
203
4.0
Dual
Up
19
272
25
2.5
2.6
2.8
3.0
282
2.8
Dual
Down
19
219
14
2.9
3.2
3.5
4.1
236
3.4
40
Single
Up
12
264
15
2.5
2.6
2.8
3.0
268
2.7
Single
Down
6
211
4
3.1
3.3
3.7
4.3
201
3.3
Dual
Up
8
280
10
2.2
2.3
2.4
2.6
281
2.3
Dual
Down
7
224
5
2.4
2.6
2.9
3.3
236
2.6
20
Single
Up
3
267
4
2.2
2.3
2.4
2.6
268
2.3
Single
Down
0
199
0
2.4
2.6
2.9
3.3
199
2.6
PROFILES:
• DUAL ENGINE AND GEAR UP: 475
KCAS TO 0.82
IMN
•SINGLE ENGINE AND GEAR UP:
280 KCAS TO 0.60 IMN
• DUAL ENGINE AND GEAR DOWN: 250 KCAS TO 0.45 IMN
•SINGLE ENGINE AND GEAR DOWN:
190 KCAS TO 0.38 IMN
DATA BASED ON:
• INITIAL ALTITUDE IS SEA LEVEL
• FUEL REQUIRED INCLUDES 1800 POUNDS RESERVE FUEL
• ZERO FUEL WEIGHT IS 34,000 POUNDS
• MILITARY THRUST CLIMB TO INDICATED ALTITUDE
• SEA LEVEL INCLUDES 25 KNOT HEADWIND
• 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED)
Figure 5-166. Bingo - Flaps Auto - Drag Index 100 Counts
XI-5-183
CHANGE 1
A1-F18EA-NFM-200
BINGO
DRAG INDEX 150 COUNTS - FLAPS AUTO
REMARKS
• ALL ALTITUDES - x1000 FEET
• ALL FUEL REQD - x1000 LBS
• ALL DISTANCES IN NAUTICAL MILES
• ENGINE(S): (2) F414-GE-400
• SINGLE ENGINE: INOPERATIVE ENGINE WINDMILLING
DATE: 29 OCTOBER 1999
U.S. STANDARD DAY, 1962
FUEL GRADE: JP-5
DATA BASIS: FLIGHT DERIVED
FUEL DENSITY: 6.8 LB/GAL
SEA LEVEL
CONFIGURATION
CRUISE
DESCEND
FUEL REQD WITH HEADWIND (knots)
CRUISE
INBD
LDG
ENGINE
ALT
KCAS
DIST
0
50
100
150
KCAS
FUEL
DIST
GEAR
Dual
Up
43
226
59
4.4
4.7
5.1
5.7
285
6.9
Dual
Down
31
214
22
6.3
7.1
8.3
10.1
236
9.9
200
Single
Up
26
244
31
5.0
5.4
6.0
6.7
269
6.5
Single
Down
14
203
9
7.9
9.2
11.2
14.1
207
9.8
Dual
Up
43
226
59
4.2
4.5
4.9
5.4
284
6.4
Dual
Down
31
214
22
5.9
6.6
7.7
9.2
236
9.0
180
Single
Up
26
244
31
4.7
5.1
5.6
6.2
268
6.0
Single
Down
14
203
9
7.3
8.4
10.0
12.4
205
8.9
Dual
Up
43
226
59
3.9
4.2
4.6
5.0
283
5.9
Dual
Down
31
214
22
5.5
6.1
7.1
8.4
235
8.2
160
Single
Up
26
244
31
4.4
4.7
5.2
5.7
267
5.5
Single
Down
14
203
9
6.7
7.6
9.0
11.0
202
8.1
Dual
Up
43
226
59
3.7
4.0
4.3
4.7
282
5.3
Dual
Down
31
213
22
5.1
5.6
6.5
7.7
234
7.4
140
Single
Up
26
244
31
4.1
4.4
4.8
5.3
267
5.0
Single
Down
14
203
9
6.1
6.9
8.0
9.7
200
7.3
Dual
Up
42
229
57
3.5
3.7
4.0
4.4
281
4.8
Dual
Down
30
215
21
4.7
5.2
5.9
6.9
234
6.5
120
Single
Up
24
251
28
3.8
4.1
4.4
4.9
266
4.6
Single
Down
14
202
9
5.5
6.2
7.1
8.5
199
6.4
Dual
Up
41
233
55
3.3
3.5
3.7
4.1
280
4.3
Dual
Down
30
215
21
4.3
4.7
5.3
6.2
233
5.7
100
Single
Up
23
252
27
3.5
3.8
4.0
4.4
265
4.1
Single
Down
14
202
9
4.9
5.5
6.2
7.4
199
5.6
Dual
Up
36
246
47
3.1
3.3
3.5
3.8
279
3.8
Dual
Down
29
215
21
3.9
4.2
4.7
5.6
233
5.0
80
Single
Up
22
254
26
3.2
3.4
3.7
4.0
265
3.6
Single
Down
13
201
9
4.3
4.8
5.4
6.3
200
4.9
Dual
Up
29
247
36
2.8
3.0
3.2
3.5
279
3.3
Dual
Down
26
216
18
3.4
3.7
4.2
4.9
232
4.2
60
Single
Up
17
258
20
2.9
3.1
3.3
3.6
264
3.2
Single
Down
11
198
7
3.7
4.1
4.6
5.4
201
4.1
Dual
Up
21
264
25
2.6
2.7
2.9
3.1
278
2.8
Dual
Down
21
216
14
3.0
3.2
3.6
4.2
232
3.4
40
Single
Up
9
261
10
2.6
2.7
2.9
3.1
263
2.7
Single
Down
4
207
3
3.1
3.4
3.8
4.4
202
3.4
Dual
Up
6
275
7
2.2
2.3
2.5
2.7
277
2.3
Dual
Down
7
220
5
2.5
2.6
2.9
3.4
231
2.7
20
Single
Up
2
261
2
2.2
2.3
2.4
2.6
263
2.3
Single
Down
0
202
0
2.5
2.6
2.9
3.4
202
2.6
PROFILES:
• DUAL ENGINE AND GEAR UP: 420 KCAS TO 0.79
IMN
•SINGLE ENGINE AND GEAR UP:
255
KCAS TO 0.58 IMN
• DUAL ENGINE AND GEAR DOWN: 250 KCAS TO 0.45 IMN
•SINGLE ENGINE AND GEAR DOWN:
185
KCAS TO 0.37 IMN
DATA BASED ON:
• INITIAL ALTITUDE IS SEA LEVEL
• FUEL REQUIRED INCLUDES 1800 POUNDS RESERVE FUEL
• ZERO FUEL WEIGHT IS 34,000 POUNDS
• MILITARY THRUST CLIMB TO INDICATED ALTITUDE
• SEA LEVEL INCLUDES 25 KNOT HEADWIND
• 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED)
Figure 5-167. Bingo - Flaps Auto - Drag Index 150 Counts
XI-5-184
CHANGE 1
A1-F18EA-NFM-200
BINGO
DRAG INDEX 200 COUNTS - FLAPS AUTO
REMARKS
• ALL ALTITUDES - x1000 FEET
• ALL FUEL REQD - x1000 LBS
• ALL DISTANCES IN NAUTICAL MILES
• ENGINE(S): (2) F414-GE-400
• SINGLE ENGINE: INOPERATIVE ENGINE WINDMILLING
DATE: 29 OCTOBER 1999
U.S. STANDARD DAY, 1962
FUEL GRADE: JP-5
DATA BASIS: FLIGHT DERIVED
FUEL DENSITY: 6.8 LB/GAL
SEA LEVEL
CONFIGURATION
CRUISE
DESCEND
FUEL REQD WITH HEADWIND (knots)
CRUISE
INBD
LDG
ENGINE
ALT
KCAS
DIST
0
50
100
150
KCAS
FUEL
DIST
GEAR
Dual
Up
40
238
51
4.8
5.2
5.7
6.4
292
7.5
Dual
Down
29
223
21
7.0
8.0
9.4
11.6
240
10.6
200
Single
Up
20
265
23
5.7
6.3
7.0
8.0
274
7.2
Single
Down
10
214
7
8.9
10.6
13.2
17.5
227
10.7
Dual
Up
40
238
51
4.5
4.9
5.4
6.0
291
6.9
Dual
Down
29
222
21
6.5
7.3
8.6
10.5
239
9.7
180
Single
Up
20
265
23
5.3
5.8
6.5
7.3
273
6.6
Single
Down
10
214
7
8.2
9.6
11.7
14.9
226
9.7
Dual
Up
40
237
51
4.3
4.6
5.0
5.5
291
6.3
Dual
Down
29
222
21
6.0
6.8
7.8
9.4
238
8.7
160
Single
Up
20
265
23
5.0
5.4
6.0
6.7
272
6.1
Single
Down
10
213
7
7.5
8.6
10.3
12.9
225
8.8
Dual
Up
40
237
51
4.0
4.3
4.7
5.2
290
5.7
Dual
Down
29
221
21
5.5
6.2
7.1
8.5
238
7.8
140
Single
Up
20
265
23
4.6
5.0
5.5
6.1
271
5.5
Single
Down
10
213
7
6.8
7.7
9.1
11.1
223
7.8
Dual
Up
40
237
51
3.8
4.0
4.3
4.8
289
5.1
Dual
Down
29
221
21
5.1
5.6
6.4
7.6
237
6.9
120
Single
Up
19
264
21
4.2
4.6
5.0
5.5
271
5.0
Single
Down
10
212
7
6.1
6.8
8.0
9.6
221
6.9
Dual
Up
38
246
48
3.5
3.7
4.0
4.4
288
4.6
Dual
Down
28
221
20
4.6
5.1
5.7
6.8
237
6.1
100
Single
Up
18
264
20
3.9
4.1
4.5
4.9
270
4.4
Single
Down
9
213
6
5.4
6.0
6.9
8.2
220
6.1
Dual
Up
35
249
43
3.3
3.5
3.7
4.0
287
4.0
Dual
Down
26
222
19
4.1
4.5
5.1
6.0
236
5.2
80
Single
Up
17
263
19
3.5
3.7
4.0
4.4
269
3.9
Single
Down
8
214
5
4.7
5.2
5.9
6.9
217
5.2
Dual
Up
28
250
33
3.0
3.1
3.4
3.7
287
3.5
Dual
Down
24
222
17
3.6
3.9
4.4
5.2
235
4.4
60
Single
Up
12
266
13
3.1
3.3
3.5
3.9
269
3.4
Single
Down
6
216
4
4.0
4.4
4.9
5.7
215
4.3
Dual
Up
18
272
21
2.7
2.8
3.0
3.2
286
2.9
Dual
Down
19
223
13
3.1
3.4
3.7
4.4
235
3.5
40
Single
Up
7
269
8
2.7
2.9
3.0
3.3
268
2.9
Single
Down
3
212
2
3.3
3.5
4.0
4.6
208
3.5
Dual
Up
7
282
8
2.3
2.4
2.5
2.7
285
2.4
Dual
Down
7
225
5
2.5
2.7
3.0
3.5
234
2.7
20
Single
Up
1
268
1
2.3
2.4
2.5
2.7
268
2.4
Single
Down
0
201
0
2.5
2.7
3.0
3.5
201
2.7
PROFILES:
• DUAL ENGINE AND GEAR UP: 380 KCAS TO 0.76
IMN
•SINGLE ENGINE AND GEAR UP:
235
KCAS TO 0.55 IMN
• DUAL ENGINE AND GEAR DOWN: 250 KCAS TO 0.45 IMN
•SINGLE ENGINE AND GEAR DOWN:
185
KCAS TO 0.36 IMN
DATA BASED ON:
• INITIAL ALTITUDE IS SEA LEVEL
• FUEL REQUIRED INCLUDES 1800 POUNDS RESERVE FUEL
• ZERO FUEL WEIGHT IS 38,000 POUNDS
• MILITARY THRUST CLIMB TO INDICATED ALTITUDE
• SEA LEVEL INCLUDES 25 KNOT HEADWIND
• 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED)
Figure 5-168. Bingo - Flaps Auto - Drag Index 200 Counts
XI-5-185
CHANGE 1
A1-F18EA-NFM-200
BINGO
DRAG INDEX 250 COUNTS - FLAPS AUTO
REMARKS
• ALL ALTITUDES - x1000 FEET
• ALL FUEL REQD - x1000 LBS
• ALL DISTANCES IN NAUTICAL MILES
• ENGINE(S): (2) F414-GE-400
• SINGLE ENGINE: INOPERATIVE ENGINE WINDMILLING
DATE: 29 OCTOBER 1999
U.S. STANDARD DAY, 1962
FUEL GRADE: JP-5
DATA BASIS: FLIGHT DERIVED
FUEL DENSITY: 6.8 LB/GAL
SEA LEVEL
CONFIGURATION
CRUISE
DESCEND
FUEL REQD WITH HEADWIND (knots)
CRUISE
INBD
LDG
ENGINE
ALT
KCAS
DIST
0
50
100
150
KCAS
FUEL
DIST
GEAR
Dual
Up
40
235
48
5.0
5.5
6.1
6.8
287
7.8
Dual
Down
28
221
19
7.2
8.3
9.9
12.2
237
11.0
200
Single
Up
19
260
20
6.1
6.7
7.6
8.7
269
7.7
Single
Down
10
210
6
9.3
11.1
14.1
19.4
225
11.1
Dual
Up
40
235
48
4.8
5.2
5.7
6.3
286
7.2
Dual
Down
29
220
20
6.7
7.6
9.0
10.9
237
10.0
180
Single
Up
20
259
21
5.7
6.2
7.0
7.9
268
7.0
Single
Down
10
210
6
8.6
10.0
12.4
16.1
223
10.1
Dual
Up
40
235
48
4.5
4.8
5.3
5.9
285
6.6
Dual
Down
29
220
20
6.2
7.0
8.1
9.8
236
9.0
160
Single
Up
20
259
21
5.3
5.7
6.4
7.2
267
6.4
Single
Down
10
209
6
7.8
9.0
10.9
13.7
222
9.1
Dual
Up
40
235
48
4.2
4.5
4.9
5.4
284
5.9
Dual
Down
29
219
20
5.7
6.4
7.4
8.8
235
8.1
140
Single
Up
20
258
21
4.9
5.3
5.8
6.5
266
5.8
Single
Down
10
209
6
7.0
8.1
9.5
11.7
220
8.1
Dual
Up
40
235
48
3.9
4.2
4.6
5.0
284
5.3
Dual
Down
29
219
20
5.2
5.8
6.6
7.9
234
7.2
120
Single
Up
18
258
19
4.5
4.8
5.3
5.8
265
5.2
Single
Down
9
210
6
6.3
7.1
8.3
10.1
218
7.2
Dual
Up
38
239
45
3.7
3.9
4.2
4.6
283
4.7
Dual
Down
28
219
19
4.7
5.2
5.9
7.0
233
6.2
100
Single
Up
18
257
19
4.1
4.4
4.7
5.2
264
4.6
Single
Down
8
211
5
5.6
6.2
7.2
8.6
213
6.3
Dual
Up
34
240
39
3.4
3.6
3.9
4.2
282
4.1
Dual
Down
26
219
18
4.2
4.6
5.2
6.1
232
5.3
80
Single
Up
17
257
18
3.7
3.9
4.2
4.6
263
4.1
Single
Down
7
211
4
4.8
5.3
6.1
7.2
205
5.4
Dual
Up
23
258
25
3.1
3.3
3.5
3.8
282
3.6
Dual
Down
23
219
16
3.7
4.0
4.5
5.3
231
4.5
60
Single
Up
12
261
12
3.2
3.4
3.7
4.0
263
3.5
Single
Down
6
212
4
4.1
4.5
5.0
5.9
205
4.5
Dual
Up
16
271
17
2.7
2.9
3.0
3.3
281
3.0
Dual
Down
19
219
13
3.2
3.4
3.8
4.4
231
3.6
40
Single
Up
7
263
7
2.8
2.9
3.1
3.4
262
2.9
Single
Down
2
205
1
3.3
3.6
4.0
4.7
202
3.6
Dual
Up
7
276
7
2.3
2.4
2.5
2.8
280
2.4
Dual
Down
7
222
5
2.6
2.7
3.0
3.5
230
2.7
20
Single
Up
1
261
1
2.3
2.4
2.6
2.8
261
2.4
Single
Down
0
200
0
2.6
2.8
3.1
3.5
200
2.7
PROFILES:
• DUAL ENGINE AND GEAR UP: 330 KCAS TO 0.76
IMN
•SINGLE ENGINE AND GEAR UP:
225
KCAS TO 0.52 IMN
• DUAL ENGINE AND GEAR DOWN: 250 KCAS TO 0.45 IMN
•SINGLE ENGINE AND GEAR DOWN:
180 KCAS TO 0.35 IMN
DATA BASED ON:
• INITIAL ALTITUDE IS SEA LEVEL
• FUEL REQUIRED INCLUDES 1800 POUNDS RESERVE FUEL
• ZERO FUEL WEIGHT IS 38,000 POUNDS
• MILITARY THRUST CLIMB TO INDICATED ALTITUDE
• SEA LEVEL INCLUDES 25 KNOT HEADWIND
• 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED)
Figure 5-169. Bingo - Flaps Auto - Drag Index 250 Counts
XI-5-186
CHANGE 1
A1-F18EA-NFM-200
BINGO
DRAG INDEX 300 COUNTS - FLAPS AUTO
REMARKS
• ALL ALTITUDES - x1000 FEET
• ALL FUEL REQD - x1000 LBS
• ALL DISTANCES IN NAUTICAL MILES
• ENGINE(S): (2) F414-GE-400
• SINGLE ENGINE: INOPERATIVE ENGINE WINDMILLING
DATE: 29 OCTOBER 1999
U.S. STANDARD DAY, 1962
FUEL GRADE: JP-5
DATA BASIS: FLIGHT DERIVED
FUEL DENSITY: 6.8 LB/GAL
SEA LEVEL
CONFIGURATION
CRUISE
DESCEND
FUEL REQD WITH HEADWIND (knots)
CRUISE
INBD
LDG
ENGINE
ALT
KCAS
DIST
0
50
100
150
KCAS
FUEL
DIST
GEAR
Dual
Up
39
233
43
5.3
5.8
6.4
7.2
282
8.2
Dual
Down
28
218
18
7.5
8.6
10.3
12.8
235
11.4
200
Single
Up
18
244
18
6.5
7.2
8.2
9.5
262
8.1
Single
Down
9
208
6
9.7
11.7
15.0
22.4
222
11.5
Dual
Up
39
232
43
5.0
5.4
6.0
6.7
282
7.5
Dual
Down
28
218
18
6.9
7.9
9.3
11.5
234
10.3
180
Single
Up
18
245
18
6.0
6.6
7.5
8.6
261
7.4
Single
Down
9
206
6
8.9
10.5
13.1
17.4
220
10.5
Dual
Up
39
232
43
4.7
5.1
5.6
6.2
281
6.8
Dual
Down
28
217
18
6.4
7.2
8.5
10.3
233
9.3
160
Single
Up
18
246
18
5.6
6.1
6.8
7.7
260
6.8
Single
Down
9
206
6
8.1
9.4
11.5
14.6
218
9.4
Dual
Up
39
232
43
4.4
4.7
5.2
5.7
280
6.2
Dual
Down
28
217
18
5.9
6.6
7.6
9.2
232
8.3
140
Single
Up
18
247
18
5.1
5.6
6.2
6.9
259
6.1
Single
Down
9
206
6
7.3
8.4
10.0
12.4
218
8.4
Dual
Up
39
231
43
4.1
4.4
4.8
5.2
280
5.5
Dual
Down
28
217
18
5.3
6.0
6.8
8.1
231
7.4
120
Single
Up
18
248
18
4.7
5.1
5.6
6.2
259
5.5
Single
Down
9
206
6
6.5
7.4
8.6
10.5
217
7.4
Dual
Up
37
232
40
3.8
4.0
4.4
4.8
279
4.9
Dual
Down
28
216
18
4.8
5.3
6.1
7.2
230
6.4
100
Single
Up
17
249
17
4.2
4.6
5.0
5.5
258
4.8
Single
Down
8
207
5
5.7
6.4
7.4
8.9
216
6.5
Dual
Up
34
232
36
3.5
3.7
4.0
4.3
279
4.3
Dual
Down
26
216
17
4.3
4.7
5.3
6.3
229
5.5
80
Single
Up
14
251
14
3.8
4.1
4.4
4.8
257
4.2
Single
Down
7
209
4
4.9
5.5
6.3
7.4
214
5.5
Dual
Up
28
238
29
3.2
3.3
3.6
3.9
278
3.7
Dual
Down
24
216
16
3.8
4.1
4.6
5.4
228
4.6
60
Single
Up
12
252
12
3.3
3.5
3.8
4.2
256
3.6
Single
Down
6
210
4
4.2
4.6
5.2
6.1
213
4.6
Dual
Up
17
265
17
2.8
2.9
3.1
3.4
278
3.0
Dual
Down
18
216
11
3.2
3.5
3.9
4.5
227
3.7
40
Single
Up
7
254
7
2.9
3.0
3.2
3.5
256
3.0
Single
Down
2
212
1
3.4
3.7
4.1
4.8
212
3.7
Dual
Up
7
270
7
2.3
2.4
2.6
2.8
277
2.5
Dual
Down
7
219
4
2.6
2.8
3.1
3.6
225
2.8
20
Single
Up
1
255
1
2.3
2.4
2.6
2.8
255
2.4
Single
Down
0
211
0
2.6
2.8
3.1
3.6
211
2.8
PROFILES:
• DUAL ENGINE AND GEAR UP: 300
KCAS TO 0.71
IMN
•SINGLE ENGINE AND GEAR UP:
220 KCAS TO 0.48 IMN
• DUAL ENGINE AND GEAR DOWN: 250 KCAS TO 0.45 IMN
•SINGLE ENGINE AND GEAR DOWN: 180 KCAS TO 0.34 IMN
DATA BASED ON:
• INITIAL ALTITUDE IS SEA LEVEL
• FUEL REQUIRED INCLUDES 1800 POUNDS RESERVE FUEL
• ZERO FUEL WEIGHT IS 38,000 POUNDS
• MILITARY THRUST CLIMB TO INDICATED ALTITUDE
• SEA LEVEL INCLUDES 25 KNOT HEADWIND
• 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED)
Figure 5-170. Bingo - Flaps Auto - Drag Index 300 Counts
XI-5-187
CHANGE 1
A1-F18EA-NFM-200
BINGO
DRAG INDEX 0 and 50 COUNTS - FLAPS HALF
REMARKS
• ALL ALTITUDES - x1000 FEET
• ALL FUEL REQD - x1000 LBS
• ALL DISTANCES IN NAUTICAL MILES
• ENGINE(S): (2) F414-GE-400
• SINGLE ENGINE: INOPERATIVE ENGINE WINDMILLING
DATE: 29 OCTOBER 1999
U.S. STANDARD DAY, 1962
FUEL GRADE: JP-5
DATA BASIS: FLIGHT DERIVED
FUEL DENSITY: 6.8 LB/GAL
SEA LEVEL
CONFIGURATION
CRUISE
DESCEND
FUEL REQD WITH HEADWIND (knots)
CRUISE
INBD
LDG
ENGINE
ALT
KCAS
DIST
0
50
100
150
KCAS
FUEL
DIST
GEAR
DRAG INDEX 0 COUNTS
Dual
Up
35
193
23
6.5
7.5
8.9
11.2
206
10.5
200
Single
Up
15
185
9
8.1
9.4
11.3
14.1
190
10.1
Dual
Up
35
193
23
6.1
7.0
8.3
10.4
206
9.6
180
Single
Up
15
185
9
7.5
8.6
10.3
12.9
190
9.2
Dual
Up
35
192
23
5.7
6.5
7.6
9.7
205
8.7
160
Single
Up
15
184
9
6.9
7.9
9.4
11.7
189
8.3
Dual
Up
35
192
23
5.3
6.0
7.0
8.9
205
7.8
140
Single
Up
15
184
9
6.2
7.1
8.4
10.6
189
7.5
Dual
Up
35
192
23
4.9
5.5
6.5
8.2
204
6.9
120
Single
Up
15
184
9
5.6
6.4
7.6
9.6
188
6.7
Dual
Up
33
192
21
4.5
5.0
5.9
7.5
204
6.1
100
Single
Up
14
183
8
5.0
5.7
6.7
8.5
188
5.8
Dual
Up
32
191
21
4.1
4.5
5.3
6.8
203
5.2
80
Single
Up
13
182
8
4.5
5.0
5.8
7.4
187
5.0
Dual
Up
28
188
18
3.6
4.0
4.7
6.0
203
4.4
60
Single
Up
8
183
5
3.8
4.3
5.0
6.4
186
4.2
Dual
Up
17
192
10
3.1
3.5
4.0
5.2
203
3.6
40
Single
Up
1
185
1
3.2
3.5
4.1
5.3
185
3.5
Dual
Up
3
198
2
2.5
2.8
3.2
4.2
202
2.7
20
Single
Up
0
184
0
2.5
2.7
3.2
4.1
184
2.7
DRAG INDEX
50
COUNTS
Dual
Up
34
196
21
6.8
7.8
9.3
11.6
203
10.8
200
Single
Up
14
181
8
8.4
9.8
11.9
14.6
188
10.4
Dual
Up
35
197
22
6.3
7.2
8.6
10.8
203
9.9
180
Single
Up
15
181
9
7.7
8.9
10.7
13.3
187
9.5
Dual
Up
35
198
22
5.9
6.7
7.9
10.0
202
8.9
160
Single
Up
15
181
9
7.1
8.1
9.7
12.1
187
8.6
Dual
Up
35
198
22
5.5
6.2
7.3
9.2
202
8.0
140
Single
Up
15
181
9
6.4
7.3
8.7
11.0
186
7.7
Dual
Up
34
196
21
5.0
5.7
6.7
8.5
201
7.1
120
Single
Up
15
181
9
5.8
6.6
7.8
9.8
186
6.8
Dual
Up
33
194
20
4.6
5.2
6.1
7.7
201
6.2
100
Single
Up
15
180
9
5.2
5.8
6.9
8.7
185
6.0
Dual
Up
32
190
20
4.2
4.7
5.4
7.0
200
5.3
80
Single
Up
13
175
7
4.6
5.1
6.0
7.6
185
5.1
Dual
Up
27
183
16
3.7
4.1
4.8
6.2
200
4.5
60
Single
Up
8
172
5
3.9
4.4
5.1
6.5
182
4.3
Dual
Up
14
188
8
3.2
3.5
4.1
5.3
199
3.6
40
Single
Up
2
178
1
3.2
3.6
4.2
5.4
175
3.5
Dual
Up
2
197
1
2.6
2.8
3.3
4.2
199
2.8
20
Single
Up
0
168
0
2.5
2.8
3.2
4.1
168
2.7
DRAG INDEX
0
PROFILES:
• DUAL ENGINE AND GEAR UP: 210 KCAS TO 0.49 IMN
•SINGLE ENGINE AND GEAR UP: 160 KCAS TO 0.34
IMN
DRAG INDEX 50 PROFILES:
• DUAL ENGINE AND GEAR UP: 200 KCAS TO 0.48 IMN
•SINGLE ENGINE AND GEAR UP: 160 KCAS TO 0.33 IMN
DATA BASED ON:
• INITIAL ALTITUDE IS SEA LEVEL
• FUEL REQUIRED INCLUDES 1800 POUNDS RESERVE FUEL
• ZERO FUEL WEIGHT IS 34,000 POUNDS
• MILITARY THRUST CLIMB TO INDICATED ALTITUDE
• SEA LEVEL INCLUDES 25 KNOT HEADWIND
• 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED)
Figure 5-171. Bingo - Flaps Half - Drag Index 0 to 300 Counts (Sheet 1 of 4)
XI-5-188
ORIGINAL
A1-F18EA-NFM-200
BINGO
DRAG INDEX 100 and 150 COUNTS - FLAPS HALF
REMARKS
• ALL ALTITUDES - x1000 FEET
• ALL FUEL REQD - x1000 LBS
• ALL DISTANCES IN NAUTICAL MILES
• ENGINE(S): (2) F414-GE-400
• SINGLE ENGINE: INOPERATIVE ENGINE WINDMILLING
DATE: 29 OCTOBER 1999
U.S. STANDARD DAY, 1962
FUEL GRADE: JP-5
DATA BASIS: FLIGHT DERIVED
FUEL DENSITY: 6.8 LB/GAL
SEA LEVEL
CONFIGURATION
CRUISE
DESCEND
FUEL REQD WITH HEADWIND (knots)
CRUISE
INBD
LDG
ENGINE
ALT
KCAS
DIST
0
50
100
150
KCAS
FUEL
DIST
GEAR
DRAG INDEX
100 COUNTS
Dual
Up
33
182
19
7.0
8.1
9.6
12.1
200
11.1
200
Single
Up
14
173
8
8.7
10.2
12.3
15.2
185
10.8
Dual
Up
34
181
20
6.5
7.5
8.9
11.2
200
10.1
180
Single
Up
14
173
8
8.0
9.3
11.2
13.9
184
9.8
Dual
Up
34
181
20
6.1
6.9
8.2
10.3
200
9.2
160
Single
Up
14
173
8
7.3
8.4
10.1
12.6
184
8.9
Dual
Up
34
181
20
5.6
6.4
7.5
9.5
199
8.2
140
Single
Up
14
173
8
6.6
7.6
9.0
11.3
183
7.9
Dual
Up
34
181
20
5.2
5.8
6.9
8.7
199
7.3
120
Single
Up
14
173
8
6.0
6.8
8.0
10.1
183
7.0
Dual
Up
33
181
19
4.7
5.3
6.2
7.9
198
6.3
100
Single
Up
14
173
8
5.3
6.0
7.1
8.9
178
6.2
Dual
Up
32
180
19
4.3
4.8
5.6
7.1
198
5.4
80
Single
Up
13
171
7
4.6
5.2
6.1
7.8
171
5.3
Dual
Up
27
178
15
3.8
4.2
4.9
6.3
197
4.5
60
Single
Up
8
171
4
4.0
4.4
5.2
6.7
170
4.4
Dual
Up
16
184
9
3.2
3.6
4.2
5.4
197
3.7
40
Single
Up
3
175
2
3.3
3.6
4.2
5.5
168
3.6
Dual
Up
2
194
1
2.6
2.8
3.3
4.2
196
2.8
20
Single
Up
0
166
0
2.5
2.8
3.2
4.2
166
2.8
DRAG INDEX
150 COUNTS
Dual
Up
32
170
18
7.3
8.4
10.0
12.5
198
11.4
200
Single
Up
13
169
7
9.0
10.5
12.8
15.7
172
11.2
Dual
Up
33
171
19
6.7
7.7
9.2
11.6
197
10.4
180
Single
Up
13
169
7
8.2
9.6
11.6
14.3
169
10.2
Dual
Up
33
172
19
6.3
7.1
8.5
10.7
197
9.4
160
Single
Up
13
169
7
7.5
8.7
10.4
12.9
171
9.2
Dual
Up
33
173
19
5.8
6.6
7.8
9.8
197
8.4
140
Single
Up
13
169
7
6.8
7.8
9.3
11.6
169
8.2
Dual
Up
33
175
19
5.3
6.0
7.1
8.9
196
7.4
120
Single
Up
13
169
7
6.1
7.0
8.2
10.4
166
7.3
Dual
Up
32
174
18
4.8
5.4
6.4
8.1
196
6.5
100
Single
Up
13
169
7
5.4
6.1
7.2
9.2
166
6.3
Dual
Up
31
174
17
4.3
4.9
5.7
7.3
195
5.5
80
Single
Up
12
168
6
4.7
5.3
6.3
8.0
167
5.4
Dual
Up
27
175
15
3.9
4.3
5.0
6.4
195
4.6
60
Single
Up
8
172
4
4.1
4.5
5.3
6.8
168
4.5
Dual
Up
14
184
7
3.3
3.6
4.2
5.4
194
3.7
40
Single
Up
2
173
1
3.3
3.7
4.3
5.5
169
3.6
Dual
Up
1
193
1
2.6
2.9
3.3
4.3
194
2.8
20
Single
Up
0
170
0
2.6
2.8
3.3
4.2
170
2.8
DRAG INDEX
100 PROFILES:
• DUAL ENGINE AND GEAR UP: 195
KCAS TO 0.48 IMN
•SINGLE ENGINE AND GEAR UP: 160
KCAS TO
0.32
IMN
DRAG INDEX 150 PROFILES:
• DUAL ENGINE AND GEAR UP: 190 KCAS TO 0.47 IMN
•SINGLE ENGINE AND GEAR UP: 160 KCAS TO 0.32 IMN
DATA BASED ON:
• INITIAL ALTITUDE IS SEA LEVEL
• FUEL REQUIRED INCLUDES 1800 POUNDS RESERVE FUEL
• ZERO FUEL WEIGHT IS 34,000 POUNDS
• MILITARY THRUST CLIMB TO INDICATED ALTITUDE
• SEA LEVEL INCLUDES 25 KNOT HEADWIND
• 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED)
Figure 5-171. Bingo - Flaps Half - Drag Index 0 to 300 Counts (Sheet 2 of 4)
XI-5-189
ORIGINAL
A1-F18EA-NFM-200
BINGO
DRAG INDEX 200 and 250 COUNTS - FLAPS HALF
REMARKS
• ALL ALTITUDES - x1000 FEET
• ALL FUEL REQD - x1000 LBS
• ALL DISTANCES IN NAUTICAL MILES
• ENGINE(S): (2) F414-GE-400
• SINGLE ENGINE: INOPERATIVE ENGINE WINDMILLING
DATE: 29 OCTOBER 1999
U.S. STANDARD DAY, 1962
FUEL GRADE: JP-5
DATA BASIS: FLIGHT DERIVED
FUEL DENSITY: 6.8 LB/GAL
SEA LEVEL
CONFIGURATION
CRUISE
DESCEND
FUEL REQD WITH HEADWIND (knots)
CRUISE
INBD
LDG
ENGINE
ALT
KCAS
DIST
0
50
100
150
KCAS
FUEL
DIST
GEAR
DRAG INDEX
200 COUNTS
Dual
Up
29
188
17
8.0
9.3
11.2
13.8
204
12.2
200
Single
Up
10
193
5
10.1
12.0
14.7
17.9
193
12.1
Dual
Up
29
188
17
7.4
8.6
10.2
12.8
204
11.1
180
Single
Up
10
193
5
9.2
10.9
13.2
16.2
191
11.0
Dual
Up
30
188
17
6.8
7.8
9.3
11.7
203
10.0
160
Single
Up
10
191
5
8.4
9.8
11.8
14.6
190
9.9
Dual
Up
30
188
17
6.3
7.2
8.5
10.7
202
8.9
140
Single
Up
10
183
5
7.6
8.7
10.5
13.1
188
8.8
Dual
Up
30
188
17
5.7
6.5
7.7
9.7
201
7.9
120
Single
Up
9
180
5
6.7
7.7
9.2
11.5
187
7.8
Dual
Up
29
188
17
5.2
5.8
6.9
8.7
200
6.8
100
Single
Up
8
177
4
5.9
6.7
8.0
10.1
184
6.7
Dual
Up
28
187
16
4.6
5.2
6.1
7.8
199
5.8
80
Single
Up
8
174
4
5.1
5.8
6.8
8.6
176
5.8
Dual
Up
22
189
12
4.1
4.5
5.3
6.8
198
4.8
60
Single
Up
6
182
3
4.3
4.8
5.6
7.2
167
4.8
Dual
Up
13
186
7
3.4
3.8
4.4
5.7
197
3.8
40
Single
Up
2
174
1
3.5
3.9
4.5
5.8
165
3.8
Dual
Up
1
195
1
2.7
2.9
3.4
4.4
196
2.9
20
Single
Up
0
165
0
2.6
2.9
3.4
4.4
165
2.9
DRAG INDEX
250 COUNTS
Dual
Up
29
183
16
8.2
9.6
11.5
14.3
203
12.5
200
Single
Up
9
192
5
10.5
12.6
15.5
18.7
191
12.5
Dual
Up
29
183
16
7.6
8.8
10.6
13.2
202
11.3
180
Single
Up
9
192
5
9.6
11.4
13.9
17.0
190
11.3
Dual
Up
29
182
16
7.0
8.1
9.6
12.1
201
10.2
160
Single
Up
7
190
4
8.7
10.2
12.4
15.3
188
10.2
Dual
Up
29
182
16
6.5
7.4
8.8
11.0
199
9.1
140
Single
Up
7
190
4
7.9
9.1
10.9
13.6
186
9.1
Dual
Up
29
182
16
5.9
6.7
7.9
10.0
198
8.0
120
Single
Up
7
186
4
7.0
8.0
9.6
12.0
184
8.0
Dual
Up
29
182
16
5.3
6.0
7.1
8.9
197
7.0
100
Single
Up
7
181
4
6.1
7.0
8.2
10.4
182
6.9
Dual
Up
27
182
15
4.7
5.3
6.2
7.9
196
5.9
80
Single
Up
7
177
4
5.3
5.9
7.0
8.9
175
5.9
Dual
Up
22
186
12
4.1
4.6
5.4
6.9
195
4.9
60
Single
Up
3
178
2
4.4
4.9
5.8
7.4
167
4.9
Dual
Up
13
186
7
3.5
3.9
4.5
5.8
194
3.9
40
Single
Up
1
170
1
3.5
3.9
4.6
5.9
165
3.9
Dual
Up
1
193
1
2.7
3.0
3.4
4.4
193
2.9
20
Single
Up
0
165
0
2.7
2.9
3.4
4.4
165
2.9
DRAG INDEX
200 PROFILES:
• DUAL ENGINE AND GEAR UP: 185
KCAS TO 0.45 IMN
•SINGLE ENGINE AND GEAR UP: 160
KCAS TO
0.31
IMN
DRAG INDEX 250 PROFILES:
• DUAL ENGINE AND GEAR UP: 180 KCAS TO 0.44 IMN
•SINGLE ENGINE AND GEAR UP: 155 KCAS TO 0.30 IMN
DATA BASED ON:
• INITIAL ALTITUDE IS SEA LEVEL
• FUEL REQUIRED INCLUDES 1800 POUNDS RESERVE FUEL
• ZERO FUEL WEIGHT IS 38,000 POUNDS
• MILITARY THRUST CLIMB TO INDICATED ALTITUDE
• SEA LEVEL INCLUDES 25 KNOT HEADWIND
• 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED)
Figure 5-171. Bingo - Flaps Half - Drag Index 0 to 300 Counts (Sheet 3 of 4)
XI-5-190
ORIGINAL
A1-F18EA-NFM-200
BINGO
DRAG INDEX 300 COUNTS - FLAPS HALF
REMARKS
• ALL ALTITUDES - x1000 FEET
• ALL FUEL REQD - x1000 LBS
• ALL DISTANCES IN NAUTICAL MILES
• ENGINE(S): (2) F414-GE-400
• SINGLE ENGINE: INOPERATIVE ENGINE WINDMILLING
DATE: 29 OCTOBER 1999
U.S. STANDARD DAY, 1962
FUEL GRADE: JP-5
DATA BASIS: FLIGHT DERIVED
FUEL DENSITY: 6.8 LB/GAL
SEA LEVEL
CONFIGURATION
CRUISE
DESCEND
FUEL REQD WITH HEADWIND (knots)
CRUISE
INBD
LDG
ENGINE
ALT
KCAS
DIST
0
50
100
150
KCAS
FUEL
DIST
GEAR
DRAG INDEX 300 COUNTS
Dual
Up
28
178
15
8.5
9.9
12.0
14.8
201
12.8
200
Single
Up
5
189
2
10.9
13.1
16.3
19.5
189
12.9
Dual
Up
28
179
15
7.9
9.1
10.9
13.6
200
11.6
180
Single
Up
5
188
2
10.0
11.8
14.5
17.7
188
11.7
Dual
Up
28
179
15
7.2
8.3
10.0
12.4
199
10.5
160
Single
Up
5
188
2
9.0
10.6
12.9
15.9
186
10.5
Dual
Up
28
180
15
6.6
7.6
9.0
11.3
197
9.3
140
Single
Up
5
187
2
8.1
9.4
11.4
14.1
184
9.3
Dual
Up
28
180
15
6.0
6.8
8.1
10.2
196
8.2
120
Single
Up
5
186
2
7.2
8.3
9.9
12.4
180
8.2
Dual
Up
28
181
15
5.4
6.1
7.2
9.1
195
7.1
100
Single
Up
5
185
2
6.3
7.2
8.5
10.7
177
7.1
Dual
Up
27
181
14
4.8
5.4
6.3
8.1
193
6.0
80
Single
Up
4
181
2
5.4
6.1
7.2
9.1
174
6.0
Dual
Up
23
183
12
4.2
4.7
5.5
7.0
192
5.0
60
Single
Up
2
174
1
4.5
5.0
5.9
7.5
172
4.9
Dual
Up
13
184
7
3.5
3.9
4.5
5.8
191
3.9
40
Single
Up
0
169
0
3.6
4.0
4.7
6.0
169
3.9
Dual
Up
1
190
1
2.7
3.0
3.5
4.5
190
2.9
20
Single
Up
0
167
0
2.7
3.0
3.4
4.4
167
2.9
DRAG INDEX 300 PROFILES:
• DUAL ENGINE AND GEAR UP: 180 KCAS TO 0.43 IMN
•SINGLE ENGINE AND GEAR UP: 150 KCAS TO 0.30 IMN
DATA BASED ON:
• INITIAL ALTITUDE IS SEA LEVEL
• FUEL REQUIRED INCLUDES 1800 POUNDS RESERVE FUEL
• ZERO FUEL WEIGHT IS 38,000 POUNDS
• MILITARY THRUST CLIMB TO INDICATED ALTITUDE
• SEA LEVEL INCLUDES 25 KNOT HEADWIND
• 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED)
Figure 5-171. Bingo - Flaps Half - Drag Index 0 to 300 Counts (Sheet 4 of 4)
XI-5-191
ORIGINAL
A1-F18EA-NFM-200
5.9 MAXIMUM RANGE AOA/MAXIMUM ENDURANCE AOA CHART
Using the Maximum Range AOA/Maximum Endurance AOA Charts -
• If required, refer to the Drag Index (DI) Values chart to determine applicable DI.
• To determine Maximum Range AOA, find appropriate DI and altitude being flown. Move up
vertically in DI column until intersecting row of altitude being flown. Where DI column and
altitude row intersect is maximum range AOA. (Example: with DI of 100 and altitude of
20,000 feet, maximum range AOA is 3.5)
• To determine Maximum Endurance AOA, find appropriate DI. AOA is listed directly below
DI. (Example: with DI of 100, AOA equals 5.2)
If necessary, Maximum Range AOA and Maximum Endurance AOA can be calculated using the
following formulas:
• Maximum Range AOA = 2.4 + (0.005 x DI) + (0.03 x altitude (x1000 feet))
• Maximum Endurance AOA = 4.4 + (0.0075 x DI)
Drag Index (DI) Values
DI
Store
DI
Store
DI
Store
20.0
CL
0.0
2 AIM-9
39.0
CL + 2 pylons (standard)
17.0
2 pylons
16.8
1 I-MER
38.0
Standard + CATM-9
30.0
4 pylons
33.6
2 I-MER
83.4
Standard + 12 Mk-76
2.0
0 AIM-9
6.6
6 BDU-48
85.8
Standard + 12 BDU-48
1.0
1 AIM-9
5.4
6 Mk-76
72.6
Standard + 2 I-MER
Altitude
Maximum Range AOA
(x1000 ft)
40
3.8
3.8
3.9
4.0
4.0
4.1
4.1
4.2
4.4
4.5
4.6
35
3.6
3.7
3.7
3.9
3.9
3.9
4.0
4.1
4.2
4.3
4.5
30
3.4
3.5
3.6
3.7
3.7
3.8
3.8
3.9
4.1
4.2
4.3
25
3.3
3.4
3.4
3.6
3.6
3.6
3.7
3.8
3.9
4.0
4.2
20
3.1
3.2
3.3
3.4
3.4
3.5
3.5
3.6
3.8
3.9
4.0
15
3.0
3.1
3.1
3.2
3.3
3.3
3.4
3.5
3.6
3.7
3.9
10
2.8
2.9
3.0
3.1
3.1
3.2
3.2
3.3
3.5
3.6
3.7
5
2.7
2.8
2.8
2.9
3.0
3.0
3.1
3.2
3.3
3.4
3.6
Drag Index
25
40
50
75
80
92
100
125
150
175
200
Maximum Endurance AOA
4.6
4.7
4.8
5.0
5.0
5.1
5.2
5.3
5.5
5.7
5.9
Figure 5-172. Maximum Range AOA/Maximum Endurance AOA
XI-5-192
ORIGINAL
A1-F18EA-NFM-200
CHAPTER 6
Endurance
F414-GE-400
6.1 MAXIMUM ENDURANCE CHARTS
Maximum endurance charts are provided for two-engine (figure 6-1) and one-engine (figure 6-2)
operation. Included are separate charts for maximum endurance altitude, Mach number and airspeed,
and fuel flow and fuel required for various drag indexes at all gross weights and altitudes from sea level
to 45,000 feet.
6.1.1 Use. ALTITUDE - Enter the chart with the effective gross weight and project up to the
appropriate drag index curve, then project horizontally left to the temperature baseline and parallel
the appropriate temperature deviation guideline to the correct temperature deviation. Project
horizontally left to read maximum endurance altitude.
6.1.2 Sample Problem.
A. Effective gross weight
42,000 Lb.
B. Drag index
50
C. Temperature deviation
+10°C
from standard day
D. Maximum endurance
30,450 Ft.
altitude
XI-6-1
ORIGINAL
A1-F18EA-NFM-200
MACH NUMBER AND AIRSPEED - Enter the chart with the average gross weight and follow the
nearest guideline down to the desired bank angle. From this point, project vertically down to determine
effective gross weight. With the effective gross weight, project vertically (up or down) to intersect the
optimum endurance at the appropriate drag index line or desired altitude, then project horizontally
right to the appropriate drag index curve. From this point, project vertically up to read maximum
endurance Mach number. To find calibrated airspeed, project vertically up from the Mach number to
the endurance altitude, then project horizontally left to find the maximum corresponding endurance
calibrated airspeed.
6.1.3 Sample Problem.
A. Average gross weight
30,000 Lb.
B. Bank angle
20°
C. Effective gross weight
32,000 Lb.
D. Drag index
50
E. Endurance altitude
37,000 Ft.
F. Drag index
50
G. Mach number
0.61
H. Endurance altitude
37,000 Ft.
I. Calibrated airspeed
180 Kt.
XI-6-2
ORIGINAL
A1-F18EA-NFM-200
FUEL FLOW AND FUEL REQUIRED - Enter the chart with the effective gross weight and project
vertically up to intersect the desired altitude for endurance, then project horizontally right to the
appropriate drag index curve. From this point, project vertically down to the appropriate altitude, then
project horizontally left to the temperature baseline and parallel the appropriate temperature
deviation guideline to the correct temperature deviation. From this point, project horizontally left to
read fuel flow in pounds per hour. To find fuel required, continue to project horizontally left to
intersect the desired endurance time, then vertically down to read fuel required.
XI-6-3
ORIGINAL
A1-F18EA-NFM-200
6.1.4 Sample Problem.
A. Effective gross weight
32,000 Lb.
B. Endurance altitude
34,000 Ft.
C. Drag index
50
D. Endurance altitude
34,000 Ft.
E. Temperature deviation
+10°C
from standard day
F. Fuel flow
3250 PPH
G. Endurance time
120 Min.
H. Fuel required
8000 Lb.
6.2 MAXIMUM RANGE AOA/MAXIMUM ENDURANCE AOA CHART
The Maximum Range AOA/Maximum Endurance AOA chart (figure 6-3) shows the AOA required
to achieve maximum range or maximum endurance based on the aircraft drag index configuration.
XI-6-4
ORIGINAL
A1-F18EA-NFM-200
Figure 6-1. Maximum Endurance (Sheet 1 of 3)
XI-6-5
ORIGINAL
A1-F18EA-NFM-200
Figure 6-1. Maximum Endurance (Sheet 2 of 3)
XI-6-6
ORIGINAL
A1-F18EA-NFM-200
Figure 6-1. Maximum Endurance (Sheet 3 of 3)
XI-6-7
ORIGINAL
A1-F18EA-NFM-200
Figure 6-2. Single Engine Maximum Endurance (Sheet 1 of 3)
XI-6-8
ORIGINAL
A1-F18EA-NFM-200
Figure 6-2. Single Engine Maximum Endurance (Sheet 2 of 3)
XI-6-9
ORIGINAL
A1-F18EA-NFM-200
Figure 6-2. Single Engine Maximum Endurance (Sheet 3 of 3)
XI-6-10
ORIGINAL
A1-F18EA-NFM-200
Using the Maximum Range AOA/Maximum Endurance AOA Charts -
• If required, refer to the Drag Index (DI) Values chart to determine applicable DI.
• To determine Maximum Range AOA, find appropriate DI and altitude being flown. Move up
vertically in DI column until intersecting row of altitude being flown. Where DI column and
altitude row intersect is maximum range AOA. (Example: with DI of 100 and altitude of
20,000 feet, maximum range AOA is 3.5)
• To determine Maximum Endurance AOA, find appropriate DI. AOA is listed directly below
DI. (Example: with DI of 100, AOA equals 5.2)
If necessary, Maximum Range AOA and Maximum Endurance AOA can be calculated using the
following formulas:
• Maximum Range AOA = 2.4 + (0.005 x DI) + (0.03 x altitude (x1000 feet))
• Maximum Endurance AOA = 4.4 + (0.075 x DI)
Drag Index (DI) Values
DI
Store
DI
Store
DI
Store
20.0
CL
0.0
2 AIM-9
39.0
CL + 2 pylons (standard)
17.0
2 pylons
16.8
1 I-MER
38.0
Standard + CATM-9
30.0
4 pylons
33.6
2 I-MER
83.4
Standard + 12 Mk-76
2.0
0 AIM-9
6.6
6 BDU-48
85.8
Standard + 12 BDU-48
1.0
1 AIM-9
5.4
6 Mk-76
72.6
Standard + 2 I-MER
Altitude
Maximum Range AOA
(x1000 ft)
40
3.8
3.8
3.9
4.0
4.0
4.1
4.1
4.2
4.4
4.5
4.6
35
3.6
3.7
3.7
3.9
3.9
3.9
4.0
4.1
4.2
4.3
4.5
30
3.4
3.5
3.6
3.7
3.7
3.8
3.8
3.9
4.1
4.2
4.3
25
3.3
3.4
3.4
3.6
3.6
3.6
3.7
3.8
3.9
4.0
4.2
20
3.1
3.2
3.3
3.4
3.4
3.5
3.5
3.6
3.8
3.9
4.0
15
3.0
3.1
3.1
3.2
3.3
3.3
3.4
3.5
3.6
3.7
3.9
10
2.8
2.9
3.0
3.1
3.1
3.2
3.2
3.3
3.5
3.6
3.7
5
2.7
2.8
2.8
2.9
3.0
3.0
3.1
3.2
3.3
3.4
3.6
Drag Index
25
40
50
75
80
92
100
125
150
175
200
Maximum Endurance AOA
4.6
4.7
4.8
5.0
5.0
5.1
5.2
5.3
5.5
5.7
5.9
Figure 6-3. Maximum Range AOA/Maximum Endurance AOA
XI-6-11 (Reverse Blank)
ORIGINAL
A1-F18EA-NFM-200
CHAPTER 7
In-flight Refueling
F414-GE-400
7.1 F/A-18E TANKER RECEIVER ENVELOPE
The tanker receiver envelope is used to determine the minimum and maximum Mach numbers for
a receiver aircraft based on a closure rate of 1 knot per second, altitude, gross weight, and temperature.
Refer to figure 7-1 for the tanker receiver envelope, including ARS limits, for F/A-18E aircraft.
7.1.1 Use. Enter the chart at the desired altitude and project horizontally right until intersecting the
appropriate gross weight and temperature. Then project vertically downward to the indicated Mach
number. This is the minimum Mach number to be used by the receiver aircraft.
To determine the maximum Mach number, enter the chart at the desired altitude and project
horizontally right until intersecting either the ARS limit line or the right-most applicable temperature
line. Then project vertically downward to the indicated Mach number. This is the maximum Mach
number to be used by the receiver aircraft.
7.1.2 Sample Problem.
A. Altitude
25,000 Ft.
D. Minimum Mach number
0.51
B. Gross weight
56,000 Lb.
E. Maximum Mach number
0.80
C. Temperature
Standard day
XI-7-1
ORIGINAL
A1-F18EA-NFM-200
Figure 7-1. F/A-18E Tanker Receiver Envelope
XI-7-2
ORIGINAL
A1-F18EA-NFM-200
CHAPTER 8
Descent
F414-GE-400
8.1 NORMAL DESCENT CHARTS
These charts (figure 8-1 for two engines, figure 8-2 for one engine) provide speed, time, fuel required,
and distance data for a normal descent with speed brake retracted. Descent speed is based on aircraft
gross weight and drag index. Optimum cruise altitudes are also depicted on the time, fuel, and distance
charts.
8.1.1 Use. DESCENT SPEED - Enter the chart with the gross weight at start of descent and project
horizontally right to the appropriate drag index number, then project vertically down to read the
corresponding descent airspeed.
8.1.2 Sample Problem.
A. Gross weight
46,000 Lb.
B. Drag index number
100
C. Descent speed
240 KCAS
TIME, FUEL, AND DISTANCE REQUIRED - Presentation of these charts is identical; therefore,
they are used in the same manner. Enter the appropriate chart with the initial gross weight at start of
descent and project horizontally right to intersect the pressure altitude at the start of descent. From
this point, project vertically down to the appropriate drag index curve, then horizontally left to the
XI-8-1
ORIGINAL
A1-F18EA-NFM-200
temperature baseline and follow the appropriate temperature deviation guideline to the appropriate
temperature deviation. From this point project horizontally left to read time, fuel, and distance
required during descent.
8.1.3 Sample Problem.
A. Initial gross weight
35,000 Lb.
B. Pressure altitude
30,000 Ft.
C. Drag index
100
D. Temperature deviation
+10°C
from standard day
E. Time
9.9 Min.
F. Fuel required
310 Lb.
G. Distance
51 NM
XI-8-2
ORIGINAL
A1-F18EA-NFM-200
8.2 MAXIMUM RANGE DESCENT CHARTS
The descent charts (figure 8-3 for two engines, figure 8-4 for one engine) provide speed, time, fuel
required, and distance data for a maximum range descent at idle thrust with speedbrake retracted.
Included are separate charts for two-engine and single engine operation at various drag indexes. When
cruise airspeed is below maximum descent airspeed, descend at the cruise Mach until the maximum
range descent airspeed is reached. Optimum cruise altitudes are also depicted on the time, fuel, and
distance charts.
8.2.1 Use.
8.2.1.1
Descent Speed. Enter the chart with the initial descent gross weight and project horizontally
right to the appropriate drag index curve and then vertically down to read the corresponding descent
calibrated airspeed. If the cruise airspeed before descent is below the descent airspeed, maintain and
descend at the cruise Mach number until the descent airspeed is reached.
8.2.1.1.1
Sample Problem.
A. Initial Descent Gross Weight
35,000 Lb.
B. Drag Index
200
C. Maximum Range Descent
189 KCAS
Calibrated Airspeed
8.2.1.2
Time, Fuel, and Distance Required. Presentation of these charts is identical; therefore, they
are used in the same manner. Enter the appropriate chart with the initial gross weight at start of
descent and project horizontally right to intersect the pressure altitude at the start of descent. From
this point, project vertically down to the appropriate drag index curve, then horizontally left to read
time, fuel, and distance required during descent.
XI-8-3
ORIGINAL
A1-F18EA-NFM-200
8.2.1.2.1
Sample Problem.
A. Initial Gross Weight
35,000 Lb.
B. Pressure Altitude
30,000 Ft.
C. Drag Index
100
D. Time
10.8 Min.
E. Fuel required
260 Lb.
F. Distance
43 NM
XI-8-4
ORIGINAL
A1-F18EA-NFM-200
Figure 8-1. Normal Descent (Sheet 1 of 4)
XI-8-5
ORIGINAL
A1-F18EA-NFM-200
Figure 8-1. Normal Descent (Sheet 2 of 4)
XI-8-6
ORIGINAL
A1-F18EA-NFM-200
Figure 8-1. Normal Descent (Sheet 3 of 4)
XI-8-7
ORIGINAL
A1-F18EA-NFM-200
Figure 8-1. Normal Descent (Sheet 4 of 4)
XI-8-8
ORIGINAL
A1-F18EA-NFM-200
Figure 8-2. Single Engine Normal Descent (Sheet 1 of 4)
XI-8-9
ORIGINAL
A1-F18EA-NFM-200
Figure 8-2. Single Engine Normal Descent (Sheet 2 of 4)
XI-8-10
ORIGINAL
A1-F18EA-NFM-200
Figure 8-2. Single Engine Normal Descent (Sheet 3 of 4)
XI-8-11
ORIGINAL
A1-F18EA-NFM-200
test
Figure 8-2. Single Engine Normal Descent (Sheet 4 of 4)
XI-8-12
ORIGINAL
A1-F18EA-NFM-200
Figure 8-3. Maximum Range Descent (Sheet 1 of 4)
XI-8-13
ORIGINAL
A1-F18EA-NFM-200
Figure 8-3. Maximum Range Descent (Sheet 2 of 4)
XI-8-14
CHANGE 2
A1-F18EA-NFM-200
Figure 8-3. Maximum Range Descent (Sheet 3 of 4)
XI-8-15
ORIGINAL
A1-F18EA-NFM-200
Figure 8-3. Maximum Range Descent (Sheet 4 of 4)
XI-8-16
ORIGINAL
A1-F18EA-NFM-200
Figure 8-4. Single Engine Maximum Range Descent (Sheet 1 of 4)
XI-8-17
ORIGINAL
A1-F18EA-NFM-200
Figure 8-4. Single Engine Maximum Range Descent (Sheet 2 of 4)
XI-8-18
ORIGINAL
A1-F18EA-NFM-200
Figure 8-4. Single Engine Maximum Range Descent (Sheet 3 of 4)
XI-8-19
ORIGINAL
A1-F18EA-NFM-200
Figure 8-4. Single Engine Maximum Range Descent (Sheet 4 of 4)
XI-8-20
ORIGINAL
A1-F18EA-NFM-200
CHAPTER 9
Landing
F414-GE-400
9.1 LANDING APPROACH SPEED CHART
The landing approach speed chart (figure 9-1) provides recommended approach speeds for various
gross weights and landing configurations. In addition to providing two curves for normal landing
configurations (full and half flaps at 8.1° AOA), the chart provides two curves for landing configura-
tions with failed control.
9.1.1 Use. Enter the chart at the estimated landing gross weight and project vertically up to the
appropriate flap deflection curve. From this point, project horizontally left to read recommended
approach speed.
9.1.2 Sample Problem. Configuration - Full flaps, 8.1° AOA.
A. Estimated landing gross weight
42,900 Lb.
B. Full flaps, AOA curve
8.1°
C. Recommended approach speed
136 KCAS
9.2 LANDING DISTANCE CHART
This chart (figure 9-2) provides landing ground roll distance information for dry hard runway
conditions as well as wet runway conditions. The data presented reflect normal landing using full
anti-skid braking. Variations in ambient temperature, pressure altitude, aircraft gross weight and
effective wind parallel to runway centerline are taken into consideration.
9.2.1 Use. Enter the chart with the prevailing density ratio and project horizontally right to intersect
the appropriate gross weight curve. From this point, project vertically down to the zero wind baseline.
Parallel the nearest guideline down to the effective headwind or tailwind. From this point project
XI-9-1
ORIGINAL
A1-F18EA-NFM-200
vertically down to read flap setting (half or full). Then project horizontally to the appropriate runway
condition (dry or wet). Finally, project vertically down to obtain the landing ground roll distance. For
half flap landings at gross weights between 38,000 lb and 46,000 lb, linear interpolation of the distances
determined by the GW≤38,000 lb and GW ≥46,000 lb curves must be used.
Increase landing ground rolls by 1.7% for each knot that the approach speed exceeds that shown
(25% CG, no stores) on the landing approach speed chart (figure 9-1). To determine total distance
required from a height of 50 feet, add 720 feet for a -4° glide slope with no flare, add 820 ft for a -3.5°
glide slope with no flare, or add 1400 feet with flare.
9.2.2 Sample Problem.
A. Density ratio
0.90
B. Gross weight
46,000 Lb.
C. Wind baseline
D. Effective headwind
10 Kt.
E. Flaps
Half
Full
F. Runway condition Dry Wet
Dry Wet
G. Landing distance
(Ft.)
4900
8400
3400
5800
H. Total Distance
to clear 50 Ft.
Obstacle
5720
9220
4120
6520
(no flare, −4° glide slope)
(G + 720)
XI-9-2
ORIGINAL
A1-F18EA-NFM-200
9.3 MAXIMUM SINGLE ENGINE RECOVERY WEIGHT CHARTS
These charts (figure 9-3 for Military Thrust and figure 9-4 for Maximum Thrust) show the
maximum single engine recovery weight. The recovery weight is based on thrust setting, temperature,
optical glide slope, and headwind component.
9.3.1 Use. Enter the appropriate chart (Military Thrust or Maximum Thrust) with the current
temperature and project vertically up to intersect the appropriate curve based on optical glide slope
(-3.5° or
-4°) being used, and headwind component (15 or 30 knots). From this point, project
horizontally left to find maximum recovery gross weight.
9.3.2 Sample Problem.
Thrust setting
MIL
A. Temperature
84°F
B. Headwind Component
15 Knot
C. Optical glide slope
-3.5°
D. Maximum recovery weight
33,800 Lb.
XI-9-3
CHANGE 3

 

 

 

 

 

 

 

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