Chart D-1. Army aircraft characteristics.
|
A AIRCRAFT |
OH-6A |
OH-58A |
OH-58C |
CH-47A |
CH-47B |
CH-47C |
CH-47D |
|
B NORMAN CREW |
1+(OBS) |
1+(OBS) |
1+(OBS) |
4 |
4 |
4 |
4 |
|
C OPERATIONAL CHARACTERISTICS 2,3,4 (1) MAX ALLOWABLE GROSS |
2400 |
3000 |
3200 |
33,000 |
40,000 |
46,000 |
50,000 |
|
(2) BASIC WEIGHT |
1163 |
1586 |
1896 |
18,153 |
19,591 |
20,481 |
22,499 |
|
(3) USEFUL LOAD |
1237 |
1417 |
1302 |
14,888 |
20,445 |
23,380 |
27,501 |
|
(4) PAYLOAD/NORMAL |
650 8 |
760 8 |
837 8 |
10,000 |
15,000 |
18,200 |
20,206 |
|
(5) FUEL CAPACITY 9 |
400/615 |
475/73 |
465/715 |
4036/621 |
7351/1131 |
6695/1030 |
8794/1353 |
|
(6) FUEL CONSUMPTION RATE 9 |
143/22 |
189/29 |
175/27 |
2120/342 |
2780/427 |
3038/467 |
2600/400 |
|
(7) NORMAL CRUISE SPEED |
121 |
120 |
120 |
120 |
150 |
155 |
155 |
|
(8) ENDURANCE AT CRUISE |
3+15 |
3+30 |
3+00 |
1+30 |
1+00 |
2+00 |
2+30 |
|
(9) GRADE OF FUEL |
JP-4 |
JP-4 |
JP-4 |
JP-4 |
JP-4 |
JP-4 |
JP-4 |
|
D PASSENGER CAPACITY (1) TROOP SEATS |
3 |
4 |
4 |
33 |
33 |
33 |
33 |
|
(2) NORMAL CAPACITY |
3 |
4 |
4 |
33 |
33 |
33 |
33 |
|
(3) TOTAL CAPACITY W/CREW |
4 |
4 |
4 |
37 |
37 |
37 |
37 |
|
(4) LITTERS & AMBULATORY |
N/A |
2/4 |
2 |
24 |
24 |
24 |
24 |
|
E EXTERNAL CARGO |
N/A |
N/A |
N/A |
16,000 |
20,000 |
20,000 |
28,000 |
|
(2) RESCUE HOIST CAPACITY |
N/A |
N/A |
N/A |
600 |
600 |
600 |
600 |
|
(3) CARGO WINCH CAPACITY |
N/A |
N/A |
N/A |
3000 |
3000 |
3000 |
3000 |
|
F DIMENSIONS |
23'-0" |
32'-3.5" |
32'-8.8" |
51'-0" |
51'-0" |
51'-0" |
51'-0" |
|
(2) LENGTH - BLADES |
30'-4" |
40'-11.8" |
40'-11.8" |
98'-3" |
99'-0" |
99'-0" |
99'-0" |
|
(3) LENGTH - BLADES |
23'-0" |
N/A |
N/A |
51'-0" |
51'-0" |
51'-0" |
51'-0" |
|
(4) WIDTH - BLADES FOLDED |
5'-6" |
N/A |
N/A |
12'-5" |
12'-5" |
12'-5" |
12'-5" |
|
(5) WIDTH - TREAD |
6'-9" |
6'-3.5" |
6'-5.4" |
11'-11" |
11'-11" |
11'-11" |
11'-11' |
|
(6) HEIGHT - EXTREME |
8'-3" |
9'-6.5" |
12'-0" |
18'-6" |
18'-8" |
18'-8" |
18'-8" |
|
(7) DIAMETER - MAIN OR |
24'-4" |
35'-4" |
35'-4" |
59'-1" |
60'-0" |
60'-0" |
60'-0" |
|
(8) DIA. TAIL OR REAR ROTOR |
4'-3" |
5'-2" |
59'-1" |
60'-0" |
60'-0" |
60'0" |
60'-0" |
|
(9) WING SPAN |
N/A |
N/A |
N/A |
N/A |
N/A |
N/A |
N/A |
|
G CARGO DOOR (1) DIMENSIONS - WIDTH |
41x34.5 |
40x35 |
40x35 |
90x78 |
90x78 |
90x78 |
90x78 |
|
(2) LOCATION - SIDE OF FUSELAGE |
LEFT & RIGHT |
LEFT & RIGHT |
LEFT & RIGHT |
REAR |
REAR |
REAR |
REAR |
|
H CARGO COMPARTMENT (1) FLOOR - ABOVE GROUND |
14.5" |
22.5" |
22.5" |
30" |
31.2" |
31.2" |
31.2" |
|
(2) USABLE LENGTH |
69" |
39" |
39" |
360" |
360" |
362" |
362" |
|
(3) FLOOR WIDTH |
38" |
50" |
50" |
90" |
90" |
90" |
90" |
|
(4) USABLE HEIGHT |
38" |
50" |
50" |
78" |
78" |
78" |
78" |
|
(5) MAXIMUM CARGO SPACE |
40 |
20 |
20 |
1474 |
1474 |
1474 |
1474 |
|
I WEAPONS 10 |
SM-27E-1 |
SM-27E-1 |
N/A |
M-24 XM-41 |
M-24 XM-41 |
M-24 XM-1 |
M-24 XM-41 |
|
A AIRCRAFT |
CH-54A |
CH-54B |
UH-1C/M |
UH-1H/V |
UH-60 |
TH/AH-1G |
AH-1S |
AH-64 14/23 |
|
B NORMAL CREW |
4 |
4 |
2 |
2 |
3 |
2 |
2 |
2 |
|
C OPERATIONAL (1) MAX ALLOWABLE GROSS |
42,000 |
47,000 |
9500 |
9500 |
20,250 |
9500 |
10,000 |
17,400 |
|
(2) BASIC WEIGHT |
20,800 |
21,200 |
4827 |
5132 |
10,500 |
5560 |
6598 |
10,505 |
|
(3) USEFUL LOAD |
21,200 |
25,800 |
4673 |
4368 |
6195 |
3940 |
3402 |
6895 |
|
(4) PAYLOAD/NORMAL |
11,650 8 |
16,250 8 |
2685 |
2900 |
3360 17 |
1785 21 |
1293 21 |
4090 21 |
|
(5) FUEL CAPACITY 9 |
8794/1353 |
8794/1353 |
1573/242 |
1358/209 |
2360/362 |
1755/270 |
1703/262 |
2405/370 |
|
(6) FUEL CONSUMPTION |
3614/556 |
4230/651 |
500/77 |
550/84 |
960/148 |
546/83.6 |
640/98 |
810/124 |
|
(7) NORMAL CRUISE SPEED |
95 |
10 |
92-140 |
90-120 |
145 |
0-190 20 |
0-190 20 |
0-161 20 |
|
(8) ENDURANCE AT CRUISE |
2+00 |
1+30 |
3+00-2+45 |
2+15 |
2+15 |
2+00 7 |
2+30 |
1+45 |
|
(9) GRADE OF FUEL |
JP-4/5 |
JP-4/5 |
JP-4/5 |
JP-4/5 |
JP-4/5/8 |
JP-4 |
JP-4 |
JP-4/5/8 |
|
D PASSENGER CAPACITY |
1 |
1 |
7 |
11 |
14 |
0 |
0 |
0 |
|
(2) NORMAL CAPACITY |
1 |
1 |
7 |
11 |
14 |
0 |
0 |
0 |
|
(3) TOTAL CAPACITY |
5 |
5 |
9 |
13 |
17 |
0 |
0 |
0 |
|
(4) LITTERS & AMBULATORY |
0 |
0 |
3 |
6 |
4/6 |
0 |
0 |
0 |
|
E EXTERNAL CARGO |
20,000 |
25,000 |
3787 |
4000 |
8000 |
N/A |
1380 19 |
6200 19 |
|
(2) RESCUE HOIST CAPACITY |
N/A |
N/A |
300 18 |
300 18 |
600 |
N/A |
N/A |
N/A |
|
(3) CARGO WINCH CAPACITY |
15,000 |
25,000 |
N/A |
N/A |
N/A |
N/A |
N/A |
N/A |
|
F DIMENSIONS |
70'-0" |
70'-0" |
42'-7" |
40'-7" |
50'-7.5" |
44'-5.2" |
44'-7" |
49'-3" |
|
(2) LENGTH - BLADES |
88'-5" |
88'-5" |
52'-10" |
57'-1" |
64'-10" |
52'-11.7" |
53'-1" |
57'-1" |
|
(3) LENGTH - BLADES |
N/A |
N/A |
N/A |
N/A |
40'-4' |
N/A |
N/A |
N/A |
|
(4) WIDTH - BLADES FOLDED |
N/A |
N/A |
N/A |
8'-7' |
9'-8.1" |
10'-4" |
10'-9" |
16'-3" |
|
(5) WIDTH - TREAD |
19'-9" |
19'-9" |
8'-4" |
8'-7" |
8'-10.2" |
7'-0" |
7'-0" |
6'-6" |
|
(6) HEIGHT - EXTREME |
24'-5" |
24'-5" |
12'-8" |
14'-6" |
17'-6" |
11'-7" |
13'-9" |
12'-6" |
|
(7) DIAMETER - MAIN OR |
72'-0" |
72'-0" |
44'-0" |
48'-0" |
53'-8" |
44'-0" |
44'-0" |
48-0"' |
|
(8) DIA. TAIL OF REAR ROTOR |
16'0" |
8'-6" |
8'-6" |
11'-0" |
8'-6" |
8'-6" |
9'-3" |
|
|
(9) WING SPAN |
N/A |
N/A |
N/A |
N/A |
N/A |
10'-4" |
10'-4" |
16'-3" |
|
G CARGO DOOR |
104.5 |
104.5 |
48x48 |
74x48 |
68x54 |
N/A |
N/A |
N/A |
|
(2) LOCATION - SIDE OF |
REAR |
REAR |
LEFT & RIGHT |
LEFT & RIGHT |
LEFT & RIGHT |
N/A |
N/A |
N/A |
|
H CARGO COMPARTMENT |
27" |
27" |
14" |
24" |
19" |
N/A |
N/A |
N/A |
|
(2) USABLE LENGTH |
329" |
329" |
60" |
92" |
110" |
N/A |
N/A |
N/A |
|
(3) FLOOR WIDTH |
104.5" |
104.5" |
80.5" |
96" |
72" |
N/A |
N/A |
N/A |
|
(4) USABLE HEIGHT |
78" |
78" |
54" |
49" |
54" |
N/A |
N/A |
N/A |
|
(5) MAXIMUM CARGO SPACE |
1552 |
1552 |
140 |
220 |
246.8 |
N/A |
N/A |
N/A |
|
I WEAPONS |
N/A |
N/A |
XM-3 |
M-23 |
M-23 |
M-18 |
M-65 |
XM-430 M-200 12 M-260 M-261 M-230 |
NOTE: This chart is for general reference only. Refer to the appropriate operator's manual.
1 A-Attack, C-Cargo, O-Observation, U-Utility
2 All data computed at standard conditions at sea level.
3 Detailed weight computations and characteristics taken from current 55 series TMs.
4 Data subject to change due to developmental testing.
5 Maximum load an aircraft is capable of lifting.
6 Dimensions from nose to end of tail.
7 Varies with load carried. Figure given is for normal mission profile.
8 Does not meet 200 NM range requirement of normal mission definition.
9 Aviation gas figured on 6 lbs/gal. JP-4 computed on 6.5 lbs/gal.
10 Indicates type of weapons aircraft can carry. Specific armament based on unit assignment.
11 7-round 2.75-inch rocket pod.
12 19-round 2.75-inch rocket pod.
13 (Deleted)
14 Subject to final develop configuration.
15 Without external fuel.
16 With external fuel.
17 Normal mission, internal load, probability exists to cube out before weight out. Max load on the floor is 300 lbs/sq ft.
18 UH-1 is restricted to hoist capacity of 300 lbs because of CG conditions.
19 External wing stores.
20 Due to armament configurations and flight profiles.
21 Considers gross weight minus basic weight minus 400 lbs for crew and total fuel weight.
22 Fuel consumption at 92 kts, 77 gal/hr; at 140 kts, 84 gal/hr.
23 Weapons are not applicable to UH-1V, MEDEVAC helicopters.
DEFINITIONS
Maximum Allowable Gross Weight. The maximum allowed total weight of the aircraft prior to takeoff. The "basic weight" of the aircraft plus the crew, personnel equipment, special devices, passengers and cargo, and usable fuel and oil. This is limited by structure, power available, or landing load.
Basic Weight. The empty weight of an aircraft in its basic configuration, to include all appointments, integral equipment, instrumentation, and trapped fuel and oil, but excluding passengers, cargo, crew, fuel, and oil.
Useful Load. The load-carrying capability of an aircraft, including payload, crew, oil, and usable fuel required for the mission. This is the difference between "maximum allowable gross weight" and "basic weight" as defined above. Thus, a reduction of the fuel load will reduce the endurance and increase payload. Full oil is required for all missions.
Payload. The useful load less the crew, full oil, and the required fuel for the mission.
Normal Mission. Payload available computed under following conditions:
- Fuel for 200 NM range plus 30-minute reserve.
- Flight altitude 2,000 feet MSL, standard temperature.
- Takeoff maximum gross weight (weight of crew included).
Normal Cruising Speed. The true airspeed which an aircraft can normally be expected to maintain at some standard power setting below rated military power. This speed will vary with altitude (for example for the U-8F, normal is 165 at 65 percent power at 8,000 feet).
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