AIRSPEED OPERATING LIMITATIONS AIRCRAFT WITH EXTERNAL STORES SUPPORT SYSTEM INSTALLED 100% RPM R
.2 0 2 4 6 8 10121416182022
AA1251B
DENSITY ALTITUDE ~ 1000 FEET
SA
Section VI MANEUVERING LIMITS
5.21 PROHIBITED MANEUVERS.
a.
Hovering turns greater than 30° per second are pro-hibited. Intentional maneuvers beyond attitudes of 630° in pitch or over 60° in roll are prohibited.
b.
Simultaneous moving of both ENG POWER CONT levers to IDLE or OFF (throttle chop) in .ight is prohib-ited.
c.
Rearward ground taxi is prohibited.
5.22 RESTRICTED MANEUVERS.
5.22.1 Manual Operation of the Stabilator. Manual operation of the stabilator in .ight is prohibited except as required by formal training and maintenance test .ight re-quirements, or as alternate stabilator control in case the AUTO mode malfunctions.
5.22.2 Downwind Hovering. Prolonged rearward .ight and downwind hovering are to be avoided to prevent accu-mulation of exhaust fumes in the helicopter and heat dam-age to windows on open cargo doors.
5.22.3 Maneuvering Limitations.
NOTE
Maneuvers entered from a low power setting may result in transient droop of 5% RPM R or greater.
a.
The maneuvering limits of the helicopter, other than as limited by other paragraphs within this section, are al-ways de.ned by main rotor blade stall. Stall has not been encountered in one G .ight up to the airspeeds shown in Figure chart Figure 5-3 for aircraft without ESSS installed and 5-4 for aircraft with ESSS installed.
b.
The blade stall chart (Figure 5-5) while not an air-
craft limitation, provides the level .ight angle of bank at which blade stall will begin to occur as a function of air-speed, gross weight, pressure altitude and temperature. When operating near blade stall, any increase in airspeed, load factor (bank angle), turbulence, or abrupt control in-puts will increase the severity of the stall. Fully developed stall will be accompanied by heavy four per rev vibration, increasing torque, and loss of altitude. Recovery is always accomplished by reducing the severity of the maneuver, that is by reducing collective, reducing airspeed, and/or re-
ducing the angle of bank. Maneuvering .ight which results in severe blade stall and signi.cant increase in 4 per rev vibration is prohibited.
5.22.3.1 High Speed Yaw Maneuver Limitation.
Above 80 KIAS avoid abrupt, full pedal inputs to prevent excess tail rotor system loading.
5.22.3.2 Limitations for Maneuvering With Sling Loads. Maneuvering limitations with a sling load is lim-ited to a maximum of 30° angle of bank in forward .ight (Figure 5-6). Side .ight is limited by bank angle and is decreased as airspeed increases. Rearward .ight with sling load is limited to 35 knots.
5.22.3.3 Limitations for Maneuvering With Rescue Hoist Loads. Maneuvering limitations with a rescue hoist load is limited to maximum of 30° angle of bank in forward .ight (Figure 5-6). Side .ight is limited by bank angle and is decreased as airspeed is increased. Rearward .ight with hoist load is limited to 35 knots. Rate of descent is limited to 1,000 feet-per-minute.
5.22.3.4 Bank Angle Limitation. Bank angles shall be limited to 30° when a PRI SERVO PRESS caution light is on.
5.23 LANDING GEAR LIMITATIONS.
Do not exceed a touchdown sink rate of 540 feet-per-minute on level terrain and 360 feet-per-minute on slopes with gross weights of up to 16,825 pounds; above 16,825 pounds gross weight 300 feet-per-minute on level terrain and 180 feet-per-minute on slopes.
5.24 LANDING SPEED LIMITATIONS.
Maximum forward touchdown speed is limited to 60 knots ground speed on level terrain.
5.25 SLOPE LANDING LIMITATIONS.
The following slope limitations apply regardless of gross weight or CG, with or without ESSS/ERFS.
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