Rotor Start and Stop Limits
Maximum wind velocity for rotor start or stop is
45 knots
from any direction
Rotor Speed Limitations
Power off (autorotation) rotor speeds up to
120% RPM R
are authorized for use by maintenance test flight pilots during autorotational RPM checks.
MAIN TRANSMISSION MODULE
LIMITATIONS
Oil pressure should remain steady during steady state forward flight or in level hover. Momentary fluctuations in oil pressure may occur during transient maneuvers (i.e. hovering in gusty wind conditions), or when flying with pitch attitudes above
+6�
. T
MAIN ROTOR OVERSPEED
o 127%
oo 137%
ooo 142%
ENGINE % RPM 1?2
12?SECOND TRANSIENT
105% ? 107%
TRANSIENT
101% ? 105%
CONTINUOUS
95% ? 101%
TRANSIENT
91% ? 95%
AVOID OPERATIONS IN 20% ? 40%
AND 60% ? 90% RANGE EXCEPT
DURING START AND SHUTDOWN
MAIN ROTOR % RPM R
*POWER ON
TRANSIENT*
101% ? 107%
CONTINUOUS
95% ? 101%
TRANSIENT
91% ? 95%
POWER OFF (AUTOROTATION)
MAXIMUM
110%
TRANSIENT
105% ? 110%
NORMAL
90% ? 105%
FUEL QUANTITY
NORMAL
200 ? 1500 LBS
PRECAUTIONARY
0 ? 200 LBS
ENGINE Ng
12?SECOND TRANSIENT
102% ? 105%
30?MINUTE LIMIT
99% ? 102%
CONTINUOUS
0 ? 99%
ENGINE OIL TEMPERATURE
30?MINUTE LIMIT
135 ?150 C
CONTINUOUS
?50 ?135 C
ENGINE OIL PRESSURE
5?MINUTE LIMIT
100 ? 120 PSI
NORMAL OPERATION
26 ? 100 PSI
IDLE *
22 ? 26 PSI
* 35 PSI MINIMUM AT 90% NG AND ABOVE
TURBINE GAS TEMPERATURE
12?SECOND TRANSIENT
903 ?949 C
2.5?MINUTES TRANSIENT (CONTINGENCY POWER)
878 ?903 C
START ABORT LIMIT
851 C
10?MINUTE LIMIT
851 ?878 C
30?MINUTE LIMIT
810 ?851 C
NORMAL
0 ?810 C
ENGINE % TRQ (Dual Engine)
ABOVE 80 KIAS
10-Sec Transient
100% ? 144%
Continuous
0% ? 100%
AT OR BELOW 80 KIAS
10-Sec Transient
120% ? 144%
Continuous
0% ? 120%
ENGINE % TRQ (Single Engine)
Any Airspeed
10-Sec Transient
135% ? 144%
Continuous
0% ? 135%
MAIN TRANSMISSION OIL TEMPERATURE
PRECAUTIONARY
105 - 140 C
CONTINUOUS
-50 - 105 C
MAIN TRANSMISSION OIL PRESSURE
PRECAUTIONARY
65 ? 130 PSI
CONTINUOUS
30 ? 65 PSI
IDLE ANDTRANSIENT
20 ? 30 PSI
Engine % RPM Limitations
Transient % RPM 1 or 2 operation in yellow range (
101% to 105%
) is not recommended as good operating practice. However, no damage to either engine or drive train is incurred by operation within this range. Momentary transients above 107% RPM 1 or 2 are
Engine Starter Limits
The pneumatic starter is capable of making the number of consecutive start cycles listed below, when exposed to the environmental conditions specified, with an interval of at least
60 seconds
between the completion of one cycle and the beginning of the ne
Engine Starter Limits (Continued)
At ambient temperatures of
15�C (59�F) and below, two consecutive start cycles may be made
, followed by a
3-minute rest period, followed by two additional consecutive start cycles
. A
30-minute
e* rest period is then required before any additional starts
PNEUMATIC SOURCE INLET LIMITS
The minimum ground-air source (pneumatic) required to start the helicopter engines is
40 psig and 30 ppm at 149�C
(300�F). The maximum ground-air source to be applied to the helicopter is
50 psig at 249�C
C *(480�F), measured at the external air connector
ENGINE START LIMITS
Crossbleed starts shall not be attempted unless the
#1 ENG ANTI-ICE ON or #2 ENG ANTI-ICE ON
advisory does not appear, and operating engine must be at
90% Ng SPEED or above and rotor speed at 100% RPM R
. When attempting single-engine starts at pressure a
ENGINE OVERSPEED CHECK LIMITATIONS
Engine overspeed check in flight is prohibited. Engine overspeed checks, on the ground, are authorized by designated maintenance personnel only.
WEIGHT LIMITATIONS
MAXIMUM WEIGHT
14-Lug wheels
22,000
7-Lug wheels
20,500
External Lift (See note)
23,500
Note: External lift missions above 22,000 pounds can only be flown with cargo hook loads above 8,000 pounds and up to 9,000 pounds.
STOWAGE PROVISIONS
Maximum capacity for each storage compartment is 125 pounds
CABIN CEILING TIEDOWN FITTINGS
The four cabin ceiling tiedown fittings have a limited load capability of 4,000 pounds
CARGO HOOK WEIGHT LIMITATION
MAXIMUM CARGO WEIGHT
9,000 lbs
Note: UH-60L helicopter will require an entry on DA Form 2408-13-1 requiring inspection following the first mission carrying an external cargo hook load exceeding 8,000 pounds
What is the maximum airspeed with an external load greater than 8,000 lbs and a GW greater than 22,000 lbs?
120 KIAS
What is the maximum airspeed for one engine inoperative?
130 KIAS
What are the maximum autorotation airspeeds?
Above 16,825 lbs
130 KIAS
Below 16,825 lbs
150 KIAS
with Volcano installed
100 KIAS
SAS inoperative airspeed limits
One SAS inoperative - 170 KIAS
Two SAS inoperative - 150 KIAS
Two SAS inoperative in IMC - 140 KIAS
Hydraulic system inoperative limits
One hydraulic system inoperative - 170 KIAS
Two hydraulic systems inoperative - 150 KIAS
Two hydraulic systems inoperative in IMC - 140 KIAS
Searchlight limits
If use is required, the searchlight must be
extended prior to reaching a maximum forward airspeed of 100 KIAS
. With searchlight
extended, airspeed is limited to 180 KIAS
.
Landing Light limits
If use is required, the landing light must be
extended prior to reaching a maximum forward airspeed of 130 KIAS
. With landing light
extended, airspeed is limited to 180 KIAS
.
What are the airspeed limits with the cabin doors open?
(1) Cabin doors may be fully open up to
100 KIAS
with soundproofing installed aft of station 379.
(2) Cabin doors may be fully open up to
145 KIAS
with soundproofing removed aft of station 379 or with soundproofing secured properly.
(3) The doors will not
What are the airspeed limits with the CE windows open?
Gunner's window(s) may be fully open up to 170 KIAS.
What are the limits associated with the stabilator not in the auto mode?
(1) The stabilator shall be set full down at speeds below 40 KIAS.
(2) The stabilator shall be set at 0� at speeds above 40 KIAS.
(3) Autorotation airspeed shall be limited to 120 KIAS at all gross weights.
Manual control not available: The placard airspe
PROHIBITED MANEUVERS
Hovering turns greater than 30� per second are prohibited. Intentional maneuvers beyond attitudes of +/-30� in pitch or over 60� in roll are prohibited
Simultaneous moving of both ENG POWER
CONT levers to IDLE or OFF (throttle chop) in flight is
prohibite
RESTRICTED MANEUVERS
Manual operation of the stabilator in flight is prohibited except as required by formal training and maintenance test flight requirements or as alternate stabilator control in case the AUTO mode malfunctions.
Prolonged rearward flight and downwind hoverin
High-Speed Yaw Maneuver Limitation
Above 80 KIAS avoid abrupt, full pedal inputs to prevent excess tail rotor system loading
Limitations for Maneuvering With Sling Loads
Maneuvering limitations with a sling load (Figure 5-9) are limited to a maximum of 30� angle of bank in forward flight. Side flight is limited by bank angle and is decreased as airspeed increases. Rearward flight with sling load is limited to 35 knots.
Bank Angle Limitation
Bank angles shall be limited to 30� when a PRI SERVO PRESS caution appears.
LANDING GEAR LIMITATIONS
Do not exceed a touchdown sink rate of
540 fpm on level terrain
and
360 fpm on slopes
with gross weights of up to 16,825 pounds; above 16,825 pounds gross weight
300 fpm on level terrain
and
180 fpm on slopes
LANDING SPEED LIMITATIONS
Maximum forward touchdown speed is limited to 60 knots ground speed on level terrain
SLOPE LANDING LIMITATIONS
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
d*.
b.
6� nose downslope
. Landing in downslope conditions with
tail winds greater than 15 knots shall not be conducted
*.
What can you expect to see the transmission oil pressure do when operating at a nose-up attitude?
NOTE: Because of the flat profile of the main transmission and forward location of both transmission oil pumps, transmission oil pressure will drop during nose-up slope
operations. At a slope angle of
10�, an indicated oil pressure of 30 to 35 psi is norm
What is required by the pilot if the fuel pressure lights illuminate while operating at a nose-down attitude?
NOTE: The low fuel pressure indicator light(s) may intermittently light when the helicopter returns to a neutral or positive attitude after extended operation at nose down attitudes with fuel boost pumps off. This may also occur during a climb to high alt
What airspeed is the ice-rate meter calibrated at?
NOTE: The ice detecting system is calibrated for 100 KIAS. When flying at airspeeds above 100 KIAS, the ice rate meter will indicate higher LWC than the actual conditions.
According to the -10, when may icing conditions begin to occur?
When the ambient air temperature is 4�C (39�F) or below and visible liquid moisture is present, icing may occur. Icing severity is defined by the liquid water content (LWC) of the outside air and measured in grams per cubic meter (g/m3).
(1) Trace: LWC 0
What equipment is required to fly into moderate icing conditions?
(1) Windshield Anti-ice.
(2) Pitot Heat.
(3) Engine Anti-ice.
(4) Engine Inlet Anti-ice Modulating Valve.
(5) Insulated Ambient Air Sensing Tube.
For flight into moderate icing conditions, all equipment in paragraph 5.28 b. and
blade deice kit must be ins
ENGINE AND ENGINE INLET ANTI-ICE LIMITATIONS
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
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 fluid overheating.
-54� - 32� - Unlimited
APU OPERATING LIMITATIONS
To prevent APU overheating, APU operation at ambient temperature of
43�C and above with engine and rotor operating is limited to 30 minutes
. With
engine and rotor not operating, the APU may be operated continuously up to an ambient temperature of 51�C
C*
WINDSHIELD ANTI-ICE LIMITATIONS
Windshield anti-ice check shall not be done when FAT is over 27�C
TURBULENCE AND THUNDERSTORM OPERATION
a. Intentional flight into severe turbulence is prohibited.
b. Intentional flight into thunderstorms is prohibited.
c. Intentional flight into turbulence with a sling load attached and an inoperative collective pitch control friction is prohibited.
GUST LOCK LIMITATIONS
a. Dual-engine operation with gust lock engaged is prohibited.
b. Single-engine operation with gust lock engaged will be performed by authorized pilot(s) at IDLE only.
c. Gust lock shall not be disengaged with engine running.