HEADQUARTERS OH-58A, Technical Manual

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TM 55-1520-228-10
5-8 Change 10
SECTION IV. LOAD LIMITS
5-17. CENTER OF GRAVITY LIMITA-
TIONS.
Maintain the aircraft within the limits in the center of
gravity limitation charts in Chapter 6.
5-18. WEIGHT LIMITATIONS.
Maximum gross weight is 3200 pounds.
SECTION V. AIRSPEED LIMITS
5-19. AIRSPEED LIMITS.
a. Refer to airspeed operating limits chart (figure
5-3) for forward airspeed limits.
b. Sideward flight limits are 35 knots.
c. Rearward flight limits are 30 knots.
d. Recommend maximum indicated airspeed for
autorotation is 100 knots.
e. Maximum indicated air speed with any door re-
moved is 100 knots.
5-19.1
.
DELETED
.
5-20. COCKPIT AND CABIN DOOR
RESTRICTIONS.
a. Helicopter will not be flown without cabin doors
unless heavy duty rear electronics compartment sound-
proof blanket (P/N 206-070-893-7), or its approved
equivalent, has been installed. Helicopter will not be
flown with only one cockpit door or one cabin door re-
moved.
b. Whenever any OH-58A/C helicopter is operated
without its cabin doors:
(1) All soundproof blankets must be in service-
able condition and firmly attached. Pilot must verify.
(2) If the rear cushions (bottom and back) are
modified per MWO 55-1520-228-30-30, they may re-
main installed provided seat belts and shoulder har-
nessses are installed, properly fastened and tightened.
(3) Loose equipment or components must be
removed or secured.
c. Doors shall not be opened in flight.
5-21.
A
FLIGHT RESTRICTION WITH
FLOAT LANDING GEAR INSTALLED.
a. Airspeed Limit. Float landing gear installed -
Rearward and sideward airspeed limit is 30 knots. Fig-
ure 5-3.
b. Altitude Limitation.
(1) Maximum operating - 15,000 feet altitude.
(2) Flight to lower altitude – increase pressure
0.5 PSI per 1000 feet below base altitude, to minimum
operating altitude.
(3) Flight to higher altitude - Limit climbing flight
to 8000 feet differential pressure altitude. Above 8000
feet differential pressure altitude, reduce float pressure
0.5 PSI per 1000 feet.