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26 Cards in this Set
- Front
- Back
- 3rd side (hint)
Transmission Oil Pressure
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30 PSI Minimum
30-70 PSI Normal 70 PSI Maximum |
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Transmission Oil Temperature
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15 C Minimum
15-110 C Normal 110 C Maximum |
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Engine Oil Temperature
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0 C Min
0-107 Norm 107 C Max |
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Engine Oil Pressure
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50 PSI Min
50-130 PSI Idle to 78% NG 90-130 PSI 78% - 94% NG 115-130 PSI Above 94% NG 130 PSI Max |
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Fuel Quantity
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0-100 LBS Low Fuel
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Note: Fuel Low Caution Message comes on at 97.5 LBS
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NG
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63-105% Continuous
105% Max Continuous 106% ten second transient |
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Engine Torque
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0-100% Cont
100-112% 30 min limit 112-121% 10 sec transient 121-131% 2 sec transient |
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Airspeed
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0-125 KIAS normal operation
125 KIAS max VNE refer to fig. 5.2 |
Note: Airspeed indication system is unreliable below 20 knots
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NR
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93% Min
100% Norm 107% Max Autorotation: 90% Min 107% Max Transient: 107-125% 5 sec transient |
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NP
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71-91% transient operation only
100% Norm 107% Max 107-112% 15 sec transient |
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TGT
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0-716 C Cont
716-802 C 30 min limit 802-905 C 12 sec transient Starting 843-927 C 10 sec transient 927 C max momentary peak no more than 1 sec |
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Mast Torque
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0-100% Cont
100-116% 10 sec transient no more than 10 sec accumulated per flight hour |
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Engine Limitations Caution
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Operating at FATs greater than 50 C may result in lower than predicted torque available and or engine instability, i.e. surge, stall, or flameout. Pilots should take extreme caution when operating at these temperatures and avoid rapid power transients. It is possible that engine starts in these conditions could result in a non-start or hot start.
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Fuel Operation Limits
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Standard operating fuel is JP-8, no restrictions are imposed.
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Starter Limits Note
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Engine starting difficulties (longer cranking time and or higher TGT) may be encountered at ambient temperatures below 5 C (41 F). Starter engagement shall not exceed the times in the following schedule.
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Starter Limits
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External: 40 sec on, 30 sec off, 40 sec on, 30 sec off, 40 sec on, 30 min off, cool down.
Battery: 60 sec on, 60 sec off, 60 sec on, 60 sec off, 60 sec on, 30 min off, cool down. |
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Weight Limitations
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Maximum Gross Weight: The OH-58D is restricted to a max gross weight of 5200 pounds.
Towing Weight Limitations: The spread restraint strap must be installed at gross weights above 4100 pounds over rough terrain and over 4500 pounds over smooth, prepared surfaces. |
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Airspeed Limitations
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Forward: The speed for any and all maneuvers shall not exceed the level flight velocities as specified in the airspeed operating limits chart, refer to fig 5.2
Sideward and rearward: Max sideward and rearward airspeed is 35 kts; however, this may be reduced by lateral CG imbalances. Lateral CG condition is determined by tables 6-5 and 6-6 and applied to wind limitations on figure 5-3. Inlet Shields: When operating with after panels removed, the max rearward airspeed shall be as shown on the rearward airspeed limitation diagram (fig 5.4) The envelope restricts airspeed to a max of 20 knots when relative wind is from 45 degrees either side of the tailboom. A max sideward airspeed of 35 knots is authorized, except for rocket firing, as noted elsewhere. |
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Sideward/Rearward Airspeed Limits
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Condition A: 35 kts sideward and rearward
Condition B: 35 kts sideward, 20 kts rearward Condition C: 20 kts sideward and rearward |
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Flight With Doors Removed
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a. The helicopter shall not be flown with only one crew door removed.
b. The helicopter shall not be flown with either avionics compartment access doors removed. c. For flight with crew doors removed, VNE is 100 kts. |
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Prohibited Maneuvers Warning
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WARNING: Rapid full left pedal inputs at airspeeds above 90 KIAS may induce flight control changes such that the tail rotor blades may come in contact with the tailboom. This could result in separation of the aft section of the tailboom and subsequent loss of control of the helicopter.
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Prohibited Maneuvers
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a. Flight maneuvers causing a negative "g" load are prohibited.
b. The speed for any and all maneuvers shall not exceed the level flight velocities as specified in the airspeed operating limits chart. (ref to fig. 5-2). c. Aerobatic maneuvers intentionally exceeding pitch or roll angles greater than 30 or 60 degrees respectively are prohibited. d. Mast torque is limited to 95% in forward flight above 60 kts. |
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Slope Limitations
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Nose downslope: 5 degrees
Nose upslope, left skid, right skid: Condition A, 8 degrees. Conditions B and C, 5 degrees. |
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Environmental Restrictions
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a. This helicopter is restricted to visual flight conditions.
b. Intentional flight into icing conditions is prohibited. c. Cover plate shall be installed when MMS is removed regardless of environmental conditions. d. The OH-58D has not been tested in a cold weather environment. Until such testing has been conducted, the following limitations are imposed: -If the FAT is below -17 C, external power should be used for starting the aircraft. |
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Wind Limitations
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Engine Starting: 45 kts max
Max Crosswind and Tailwind at a Hover: 35 kts, however this may be reduced by lateral CG imbalances. Determined by tables 6-5 and 6-6 and applied to wind limitations on fig 5-3. Max tailwind at a hover without inlet blast shields installed is 20 kts. Heading Hold Engaged: 35 kts max (CDS4), 20 kts max. |
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Turbulence
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a. Intentional flight into severe or extreme turbulence is prohibited.
b. Intentional flight into moderate turbulence is prohibited when the weather report or forecast is based on fixed wing aircraft above 12,500 lbs. c. Intentional flight into moderate turbulence is permitted when the weather report or forecast is based on fixed or rotary wing aircraft greater than 12,500 lbs. |
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