b.
Maximum airspeed for autorotation at a gross weight of 16,825 pounds or less is 150 KIAS.
c.
Maximum airspeed for autorotation at a gross weight of greater than 16,825 pounds is 130 KIAS.
d.
Sideward/rearward .ight limits. Hovering in winds greater than 45 knots (35 knots with external ERFS) from the sides or rear is prohibited. Sideward/rearward .ight into the wind, when combined with windspeed, shall not exceed 45 knots (35 knots with external ERFS). .
e.
SAS inoperative airspeed limits:
(1)
One SAS inoperative -170 KIAS.
(2)
Two SAS inoperative -150 KIAS.
(3)
Two SAS inoperative in IMC -140 KIAS.
f.
Hydraulic system inoperative limits:
(1)
One hydraulic system inoperative -170 KIAS.
(2)
Two hydraulic systems inoperative -150 KIAS.
(3)
Two hydraulic systems inoperative in IMC -140 KIAS.
g.
Searchlight and landing light airspeed limits.
(1)
Landing light. If use is required, the landing light must be extended prior to reaching a maximum forward airspeed of 130 KIAS. With landing light extended, air-speed is limited to 180 KIAS.
(2)
Searchlight(s). If use is required, searchlight(s) must be extended prior to reaching a maximum forward
airspeed of 100 KIAS. With searchlight extended, airspeed is limited to 180 KIAS.
5.19 FLIGHT WITH CABIN DOOR(S)/WINDOW(S) OPEN.
The following airspeed limitations are for operating the helicopter in forward .ight with the cabin doors/window open:
a. Cabin doors
(1)
Cabin doors may be fully open up to 100 KIAS with soundproo.ng installed aft of station 379.
(2)
Cabin doors may be fully open up to 145 KIAS with soundproo.ng removed aft of station 379 or with soundproo.ng secured properly.
(3)
The doors will not be intentionally moved from the fully open or closed position in .ight. The cabin doors may be opened or closed during hovering .ight. The cabin doors must be closed or fully opened and latched before forward .ight. Should the door inadvertently open in .ight, it may be secured fully open or closed.
b.
Flight with cockpit door(s) removed is prohibited.
5.20 AIRSPEED LIMITATIONS FOLLOWING FAIL-URE OF THE AUTOMATIC STABILATOR CON-TROL SYSTEM.
a. Manual control available. If the automatic stabilator control system fails in .ight and operation cannot be re-stored:
(1)
The stabilator shall be set full down at speeds below 40 KIAS.
(2)
The stabilator shall be set at zero degrees at speeds above 40 KIAS.
(3)
Autorotation airspeed shall be limited to 120 KIAS at all gross weights.
b.
Manual control not available. The placard airspeed limits shall be observed as not-to-exceed speed (powered .ight and autorotation), except in no case shall the autoro-tation limit exceed 120 KIAS.
AIRSPEED OPERATING LIMITATIONS AIRCRAFT WITHOUT ESSS INSTALLED 100% RPM R
EXAMPLE WANTED
MAX IAS FOR VARIOUS TEMPS, PRESSURE ALTITUDE AND GROSS WEIGHTS
KNOWN
FAT = . 20oC PRESSURE ALTITUDE = 4,000 FEET. GROSS WEIGHT = 18,000 POUNDS.
METHOD
ENTER FAT AT .20oC. MOVE RIGHT TO PRESSURE ALTITUDE 4,000 FEET. MOVE DOWN TO 18,000 POUNDS GROSS WEIGHT OR MACH LIMIT FAT WHICHEVER IS ENCOUNTERED FIRST, IN THIS CASE 18,000 POUNDS IS ENCOUNTERED FIRST. MOVE LEFT TO READ 186 KNOTS.
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