When performing slope landings with Ex-ternal Extended Range Fuel System Tanks, ensure tank to ground clearance.

5-12 Change 4 TM 1-1520-253-10
AIRSPEED FOR ONSET OF BLADE STALL LEVEL FLIGHT 100% RPM R
EXAMPLE

WANTED

FAT OC .60 .40 .20 0
24.5 22 20
18 16
14
GROSS WEIGHT ~ 1000 LBS

240  220  200  180  160  140  120  100  80  60  40 
INDICATED AIRSPEED ~ KTS 
AA1306A 
SA 
Figure 5-5. Airspeed for Onset of Blade Stall 
5-13 

NOTE

Because of the .at pro.le of the main trans-mission and forward location of both trans-mission oil pumps, transmission oil pressure will drop during nose-up slope operations. At slope angle of 10° an indicated oil pres-sure of 30 to 35 psi is normal, and at a 15° slope angle a pressure in the range of 10 to 15 psi is normal, due to pitching of the he-licopter.
a. 15° nose-up, right wheel up or left wheel upslope. The slope limitations shall be further reduced by 2° for every 5 knots of wind.
b.
6° nose downslope. Landing in downslope conditions with tail winds greater than 15 knots shall not be conducted. A low-frequency oscillation may occur when landing nose-down on a slope with the cyclic near the aft stop.

c.
The main gearbox may be operated up to 30 minutes at a time with pressure .uctuations when the helicopter is known to be at a nose-up attitude (i.e., slope landings or hover with extreme aft CG).

SLING/RESCUE HOIST LOAD
MANEUVERING LIMITS

40 20 0 20 40 60 80 100 120 140KIAS
CROSSWIND AND SIDE FLIGHT

FORWARD FLIGHT AA0668

SA

Figure 5-6. Sling/Hoist Load Maneuvering Limitations
Section VII ENVIRONMENTAL RESTRICTIONS
5.26 FLIGHT IN INSTRUMENT METEOROLOGICAL CONDITIONS (IMC).
This aircraft is quali.ed for operation in instrument me-teorological conditions.
5.27 FLIGHT IN ICING CONDITIONS.
a. When the ambient air temperature is 4°C (39°F) or below and visible liquid moisture is present, icing may occur. Icing severity is de.ned by the liquid water content (LWC) of the outside air and measured in grams per cubic meter (g/m3).
(1)
Trace :LWC 0 to 0.25 g/m3

(2)
Light :LWC 0.25 to 0.5 g/m3

(3)
Moderate :LWC 0.5 to 1.0 g/m3

(4)
Heavy :LWC greater than 1.0 g/m3

b.
Helicopters with the following equipment installed and operational are permitted to .y into trace or light icing conditions. Flight into light icing is not recommended with-out the blade deice kit. Flight into moderate icing shall comply with paragraph 5.27 c.

(1)
Windshield Anti-ice.

(2)
Pitot Heat.

(3)
Engine Anti-ice.

(4)
Engine Inlet Anti-ice Modulating Valve.

(5)
Insulated Ambient Air Sensing Tube.

c.
For .ight into moderate icing conditions, all equip-ment in paragraph 5.27 b. and blade deice kit must be in-
stalled and operational. Flight into heavy or severe icing is prohibited.

d.
Helicopters equipped with blade erosion kit are pro-hibited from .ight into icing conditions.

5.28 ENGINE AND ENGINE INLET ANTI-ICE LIMI-TATIONS.
At engine power levels of 10% TRQ per engine and below, full anti-ice capability cannot be provided, due to engine bleed limitations. Avoid operation under conditions of extreme low power requirements such as high rate of descent (1900 fpm or greater), or ground operation below 100% RPM R, during icing conditions. The cabin heating system should be turned off before initiating a high rate of descent.
5.29 BACKUP HYDRAULIC PUMP HOT WEATHER LIMITATIONS.
During prolonged ground operation of the backup pump using MIL-H-83282 or MIL-H-5606 with the rotor system static, the backup pump is limited to the following temperature/time/cooldown limits because of hydraulic .uid overheating.
　
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