Oh-58D Ch.5

Front 1

Transmission Oil Pressure

Back 1

30 PSI Minimum
30-70 PSI Normal
70 PSI Maximum

Front 2

Transmission Oil Temperature

Back 2

15 C Minimum
15-110 C Normal
110 C Maximum

Front 3

Engine Oil Temperature

Back 3

0 C Min
0-107 Norm
107 C Max

Front 4

Engine Oil Pressure

Back 4

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

Front 5

Fuel Quantity

Back 5

0-100 LBS Low Fuel

Hint 5

Note: Fuel Low Caution Message comes on at 97.5 LBS

Front 6

NG

Back 6

63-105% Continuous
105% Max Continuous
106% ten second transient

Front 7

Engine Torque

Back 7

0-100% Cont
100-112% 30 min limit
112-121% 10 sec transient
121-131% 2 sec transient

Front 8

Airspeed

Back 8

0-125 KIAS normal operation
125 KIAS max VNE refer to fig. 5.2

Hint 8

Note: Airspeed indication system is unreliable below 20 knots

Front 9

NR

Back 9

93% Min
100% Norm
107% Max
Autorotation:
90% Min
107% Max
Transient:
107-125% 5 sec transient

Front 10

NP

Back 10

71-91% transient operation only
100% Norm
107% Max
107-112% 15 sec transient

Front 11

TGT

Back 11

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

Front 12

Mast Torque

Back 12

0-100% Cont
100-116% 10 sec transient no more than 10 sec accumulated per flight hour

Front 13

Engine Limitations Caution

Back 13

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.

Front 14

Fuel Operation Limits

Back 14

Standard operating fuel is JP-8, no restrictions are imposed.

Front 15

Starter Limits Note

Back 15

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.

Front 16

Starter Limits

Back 16

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.

Front 17

Weight Limitations

Back 17

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.

Front 18

Airspeed Limitations

Back 18

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.

Front 19

Sideward/Rearward Airspeed Limits

Back 19

Condition A: 35 kts sideward and rearward
Condition B: 35 kts sideward, 20 kts rearward
Condition C: 20 kts sideward and rearward

Front 20

Flight With Doors Removed

Back 20

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.

Front 21

Prohibited Maneuvers Warning

Back 21

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.

Front 22

Prohibited Maneuvers

Back 22

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.

Front 23

Slope Limitations

Back 23

Nose downslope: 5 degrees
Nose upslope, left skid, right skid: Condition A, 8 degrees. Conditions B and C, 5 degrees.

Front 24

Environmental Restrictions

Back 24

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.

Front 25

Wind Limitations

Back 25

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.

Front 26

Turbulence

Back 26

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.