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Limits
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Warning/Caution/Note
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100
NG (Gas Producer)
63-105% Continuous. 105% Maximum Continuous. 105-106% 10-Sec Transient.
100
Minimum Rate of Decent/Maximum Glide Distance Airspeeds
The power-off minimum rate of descent is attained at an indicated airspeed of 55 knots and 100% NR/The power-off maximum glide distance is attained at an indicated airspeed of 80 knots and 100% NR
100
Minimum Crew Requirements
The minimum crew required to fly the helicopter is one pilot whose station is in the right seat. An additional qualified crewmember is required when aircraft mission equipment is employed.
100
Reduced Rotor RPM (Note)
Reduced rotor RPM will be accompanied by a proportional reduction in tail rotor RPM which may adversley affect dirrectional control, particularly at high density altitude and high gross weight conditions.
100
ENGINE/FUSELAGE FIRE – LOW/ CRUISE ALTITUDE
a. If power-on landing: 1. LAND AS SOON AS POSSIBLE. 2. EMER SHUTDOWN after landing. b. If power-off landing: 1. AUTOROTATE. 2. EMER SHUTDOWN. Accomplish during descent if time permits.
200
TRQ (Mast Torque)
0-100% Continuous. 100-116% 10-Sec Transient. (no more than 10 seconds accumulated per flight hour)
200
SMOKE AND FUME ELIMINATION
1. VENT PULL knobs — PULL. 2. R and L DEFOG BLWR switches — ON. 3. COMPT BLWR switch — ON.
200
Slope Landing or Takeoff Limitations
a. Nose downslope — 5°. b. Left skid, right skid, or nose upslope — Limits are dependent on lateral CG condition as determined by tables 6-3 and 6-4. For Condition A, 8°; for Conditions B & C, 5°.
200
Starter Limits (Note)
Engine starting difficulties (longer cranking times and/or higher TGT) may be encountered at ambient temperatures below +5 °C (41 °F).
200
CLUTCH FAILS TO DISENGAGE/CLUTCH FAILS TO RE-ENGAGE
1. Throttle — Open. 2. LAND AS SOON AS POSSIBLE 1. AUTOROTATE. 2. EMER SHUTDOWN
300
Transmission Oil Pressure & Temperature
Pressure 30 PSI Minimum 30-70 PSI Normal 70 PSI Maximum Temperature 15*C Minimum 15-110*C Normal 110*C Maximum
300
ENGINE UNDERSPEED
1. Collective — Adjust to establish rotor RPM within limits. 2. Throttle — Check open. 3. RPM ± trim switch — Increase (+). If underspeed condition still exists: 4. FADEC MANUAL Operation — Perform.
300
EXCEEDING OPERATIONAL LIMITS.
Anytime an operational limit is exceeded, an appropriate entry shall be made on DA Form 2408-13- 1 and 2408-13-1E. Entry shall state what limit or limits were exceeded and any additional data (i.e., range and time beyond limits) that would aid maintenance personnel in performing the required maintenance action.
300
Prohibited Maneuvers (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.
300
HYDRAULIC POWER FAILURE
1. Airspeed — Adjust as necessary to attain the most comfortable level of control movements. 2. HYD SYS circuit breaker — Out; check for restoration of hydraulic power. If hydraulic power is not restored: 3. HYD SYS circuit breaker — In. 4. HYD SYS switch — OFF. 5. LAND AS SOON AS PRACTICABLE at an area which will permit a run-on landing at an airspeed slightly above effective translational lift.
400
% RPM-NR (Rotor)
Powered Flight 93% Minimum 100% Normal 107% Maximum Autorotation 90% Minimum 107% Maximum Transient 107% to 125% 5-Sec Transient.
400
LEFT IMCPU/RIGHT IMCPU FAILURE
GROUND=1. MCPU L/R circuit breaker — Out. 2. MCPU L/R circuit breaker — In. Check MFD for MCPU caution message. If IMCPU is not recovered: 3. Maintenance action is required to recover failed IMCPU prior to flight. IN-FLIGHT=An IMCPU failure will be evidenced when LEFT MCPU FAIL or RIGHT MCPU FAIL displays on the unaffected MFD. An automatic reset function provides a built-in reset in the event of a right IMCPU failure. If the right IMCPU fails and does not reset, perform the following: LAND AS SOON AS PRACTICABLE. The left IMCPU does not have an automatic in-flight reset function. If the left IMCPU fails in flight, perform the following: LAND AS SOON AS POSSIBLE.
400
ENVIRONMENTAL RESTRICTIONS
a. This helicopter is restricted to visual flight conditions. b. Intentional flight into icing conditions is prohibited. c. Cover plate shall be installed for flight when MMS is removed regardless of environmental conditions. d. The OH-58D has not been tested in a cold weather environment. Until such testing is conducted, the following limitations apply: (1) If the free air temperature (FAT) is below -17 °C (2 °F), external power should be used for starting the aircraft.
400
Engine Oil Pressure (Note)
-During cold weather starts, engine and transmission oil pressure may exceed MPD range. If this occurs, MFD will display full scale, WRN light will flash, and an error code will be displayed. Remain at engine idle until normal range is attained (2 minutes maximum at extreem temperature). -F4 and F5 error codes indicate abnormal signal imputs. Display of these codes during start does not dictate maintenance. -Pilot monitoring of oil pressure is limited to operating in the green band of the MPD and checking pressure vs NG.
400
DC GENERATOR FAILURE – NO OUTPUT
1. DC GEN FIELD and DC GEN RESET circuit breakers — Check/Place In. Do not hold the circuit breaker(s) in. If the circuit breaker(s) trip again, leave out and proceed with step 3. 2. DC GEN switch — RESET then DC GEN. Do not hold the switch in the RESET position. If generator output is not restored, or if generator goes off line again: 3. DC GEN switch — OFF. 4. LAND AS SOON AS PRACTICABLE.
500
Engine Oil Temperature and Pressure
Temperature 0*C Minimum 0-107*C Normal 107*C Maximum Pressure 50 PSI Minimum 50-130 PSI Idle to 78% NG 90-130 PSI 78 TO 94% NG 115-130 PSI Above 94% NG 130 Maximum
500
FADEC MANUAL OPERATION
1. Throttle — Adjust not lower than index mark. 2. AUTO/MAN switch — MAN. 3. Collective — Adjust to maintain RPM within limits. 4. Throttle and collective — Adjust to maintain RPM within limits. 5. LAND AS SOON AS PRACTICABLE. If engine RPM cannot be controlled manually: 6. AUTOROTATE — When over a safe landing area. 7. EMER SHUTDOWN — Accomplish during descent if time permits
500
AIRSPEED LIMITATIONS AND AIRCRAFT SECTORS
a. Airspeed Limitations Chart. To determine the maximum operating airspeed, it is necessary to know the FAT, PA, and Gross Weight. b. Forward — The speed for any and all maneuvers shall not exceed the level flight velocities as stated on the airspeed operating chart (fig. 5-2). c. Sideward and rearward — Maximum sideward and rearward airspeed is 35 knots; however, this may be reduced by lateral CG imbalances. Lateral CG condition is determined by tables 6-3 and 6-4 and applied to wind limitations on figure 5-3. d. Inlet shields — When operating with aft panels removed, the maximum rearward airspeed shall be as shown on the rearward airspeed limitation diagram (fig. 5-4). The envelope restricts airspeed to a maximum of 20 Knots when relative wind is from 45° either side of the tailboom. A maximum sideward airspeed of 35 Knots is authorized, except for rocket firing as noted elsewhere. Forward=300*- 60* R Side= 60*- 120* Rear= 120*- 200* L Side= 200*- 300
500
Engine Limitation (Caution)
Operating at FATs greater than 50 °C may result in lower-than-predicted torque available or engine instability, i.e., surge, stall, or flameout. Pilots should take extreme caution when flying at these temperatures and avoid rapid power transients. It is possible that engine starts in these conditions will result in a non-start or a hot start.
500
Cause that result in Fadec Fail Fixed Fuel Flow/Fail to Manual Mode
a Fixed Fuel Flow include, but are not limited to: (1) ECU critical hardware failures. (2) Dual NG or NP sensor failures. (3) Failure of the PLA potentiometer(s). (4) Failure of the HMU metering valve stepper motor. System failures that will drive the FADEC to automatically switch to the manual mode are: (1) Total and complete loss of all electrical power (simultaneous failure of AC generator, DC generator, battery, and PMA, or a specific ECU internal connection failure). (2) Open or short failure of the FADEC AUTO/ MAN switch. (3) Failure of the AUTOMATIC/MANUAL solenoid valve, in the HMU