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5.8.3 Engine Starter Limits.
a.
The pneumatic starter is capable of making the num-ber of consecutive start cycles listed below, when exposed to the environmental conditions speci.ed, with an interval of at least 60 seconds between the completion of one cycle and the beginning of the next cycle. A starting cycle is the interval from start initiation and acceleration of the com-pressor, from zero rpm, to starter dropout. The 60-second delay between start attempts applies when the .rst attempt is aborted for any reason, and it applies regardless of the duration of the .rst attempt. If motoring is required for an emergency, the 60-second delay does not apply.

b.
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 consecu-tive start cycles. A 30-minute rest period is then required before any additional starts.

c.
At ambient temperatures above 15° up to 52°C (59° up to 126°F), two consecutive start cycles may be made. A 30-minute rest period is then required before any additional start cycles.

5.9 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(480°F), measured at the external air connector on the fuselage.
5.10 ENGINE START LIMITS.

CAUTION
Engine start attempts at or above a pres-sure altitude of 20,000 feet could result in a Hot Start.

Crossbleed starts shall not be attempted unless the anti-ice light is off, 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 altitudes above 14,000 feet, press the start switch with the ENG POWER CONT lever OFF, until the maximum motoring speed (about 24%) is reached, before going to IDLE. Engine starts using APU source may be attempted when within the range of FAT and pressure altitude of Figure 5-2.
5.11 ENGINE OVERSPEED CHECK LIMITATIONS.
Engine overspeed check in .ight is prohibited. Engine overspeed checks, on the ground, are authorized by desig-nated maintenance personnel only.
5.12 FUEL LIMITATIONS.
When using all fuel types, both fuel boost pumps shall be on and operational, otherwise engine .ameout may re-sult.
5-6 Change 2
ENGINE START ENVELOPE

20
18
16
EXAMPLE 14

WANTED 12
IF TWO.ENGINE START CAN BE DONE AT 2900 FEET PRESSURE 10ALTITUDE AND 16OC
KNOWN 8
PRESSURE ALTITUDE=2900 FEET FREE.AIR TEMPERATURE = 16OC 6
METHOD 4
ENTER CHART AT PRESSURE ALTITUDE 2900 FEET MOVE RIGHT TO INTERSECT 2

VERTICAL TEMPERATURE LINE. IF LINES INTERSECT WITHIN DARK SHADED AREA, TWO.ENGINE START CAN BE DONE. 0
PRESSURE ALTITUDE ~ FEET X 1000

FREE.AIR TEMPERATURE ~OC 
AA9908 
SA 
Figure 5-2. Engine Start Envelope 

Section IV LOADING LIMITS
5.13 CENTER OF GRAVITY LIMITATIONS.
Center of gravity limits for the aircraft to which this manual applies and instructions for computation of the cen-ter of gravity are contained in Chapter 6.
5.14 WEIGHT LIMITATIONS.
AIRCRAFT MAXIMUM WEIGHT
UH-60Q 22,000
In addition to the above limits, maximum weight is further limited by cargo .oor maximum capacity of 300 pounds per square foot. Refer to Chapter 6.
5.15 CABIN CEILING TIEDOWN FITTINGS.
The four cabin ceiling tiedown .ttings have a limited load capability of 4,000 pounds.
5.16 CARGO HOOK WEIGHT LIMITATION.
For UH-60Q aircraft, the maximum weight that may be suspended from the cargo hook is limited to 8,000 pounds.
5.17 RESCUE HOIST WEIGHT LIMITATIONS.
The maximum weight that may be suspended from the rescue hoist is 600 pounds.
　
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