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%), turbine gas temperature (TGT), and rpm (NG and
NP). Additionally, excessive torque or TGT will be
indicated by associated WARNING messages on External Battery Starts
MFD’s, these messages, peak values, and duration are
recorded in CDS memory. 40 sec ON 60 sec ON
30 sec OFF 60 sec OFF
40 sec ON 60 sec ON 5-8. FUEL OPERATION LIMITS.
30 sec OFF 60 sec OFF
Standard fuel is JP-8; no restrictions are imposed. 40 sec ON 60 sec ON
30 min OFF 30 min OFF
NOTE
(cool down) (cool down)
Engine starting difficulties (longer cranking
t i m e s a n d / o r h i g h e r TGT) may be
encountered at ambient temperatures below
+ 5 °C (41 °F).
SECTION IV. LOADING LIMITS
5-10. CENTER-OF-GRAVITY LIMITS. 5-11. WEIGHT LIMITATIONS.
Center-of-gravity limits for the aircraft to which this
manual applies and instructions for computation of the a. Maximum Gross Weight. The maximum gross
center of gravity are contained in Chapter 6. weight for the helicopter is 5500 pounds.
b. Towing Weight Limitations. The spread
restraint strap must be installed at gross weights above
4100 pounds over rough terrain and above 4500
pounds over smooth, prepared surfaces.
c. Cargo Hook Load Limitations. Maximum cargo
hook structural loading is 1300 pounds.
SECTION V. AIRSPEED LIMITS
5-12. AIRSPEED LIMITATIONS. 5-13. FLIGHT WITH DOORS REMOVED.
a. Forward The speed for any and all maneuvers a. The helicopter shall not be flown with only one
shall not exceed the level flight velocities as stated on crew door removed.
the airspeed operating chart (fig. 5-2).
b. Sideward and rearward Maximum sideward b. The helicopter shall not be flown with either
and rearward airspeed is 35 knots; however, this may avionics compartment access door removed.
be reduced by lateral CG imbalances. Lateral CG
condition is determined by tables 6-5 and 6-6 and c. For flight with crew doors removed, Vne is 110
applied to wind limitations on figure 5-3. KIAS (fig. 5-2).
5-4
TM 1-1520-248-10
Figure 5-2. Airspeed Operating Limits
5-5
TM 1-1520-248-10
5-14. EXTERNAL CARGO LOAD AIRSPEED NOTE
LIMITATIONS.
Information on cargo hook is provided for
information only and will not be applicable
WARNING until use is authorized.
a. For flight with external load on cargo hook, Vne
is 80 KIAS.
Actual airspeed limitation for a given
external load will be determined by b. Lightweight, high drag loads require a swivel
handling characteristics affected by size, connector between the cargo hook and the sling to
weight and shape of cargo. prevent unstable oscillations in flight above 20 KIAS.
Figure 5-3. Sideward and Rearward Airspeed/Wind Limits
SECTION VI. MANEUVERING LIMITS
5-15. PROHIBITED MANEUVERS. a. Flight maneuvers causing a negative “g” load
are prohibited.
WARNING b. The speed for any and all maneuvers shall not
exceed the level flight velocities as stated on the
airspeed operating limits chart (fig. 5-2).
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.
5-6
TM 1-1520-248-10
c. Aerobatic maneuvers are prohibited. 5 - 1 6 . SLOPE LANDING OR TAKEOFF
LIMITATIONS.
NOTE a. Nose downslope 5 degrees.
b. Left or right skid, or nose, Upslope - limits are
Aerobatic f l i g h t i s defined to be any dependent on lateral CG condition as determined by
intentional maneuver involving an abrupt tables 6-5 and 6-6. for Area A, 10 degrees; for Area B
change in the a i r c r a f t ’ s attitude, an & C, 5 degrees.
abnormal attitude (pitch or roll angles
g r e a t e r t h a n ± 30 o r ± 60 degrees
respectively), or abnormal acceleration not
necessary for normal flight.
d. Main rotor torque is limited to 95% in forward
flight above 60 Kts. airspeed.
SECTION VII. ENVIRONMENTAL RESTRICTIONS
5-17. ENVIRONMENTAL RESTRICTIONS. imbalances. Lateral CG condition is determined by
tables 6-5 and 6-6 and applied to wind limitations on
a. This helicopter is restricted to visual flight figure 5-3.
conditions.
c. Maximum tailwind for hover without inlet blast
b. Intentional f l i g h t into icing conditions i s shields installed is 20 knots.
prohibited.
d. Heading hold engaged 35 knots maximum.
c. Cover plate shall be installed for flight when
MMS i s removed regardless of environmental
conditions. 5-19. TURBULENCE.
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OPERATOR’S MANUAL FOR ARMY OH-58D HELICOPTER 2(56)
