*  
8. APU CONTR switch -OFF.

*  
9. AIR SOURCE HEAT/START switch -As re-quired.

*  
10. ENG FUEL SYS selectors -As required.

*  
11. SAS 1 -ON.
*12. Collective friction -As required.

NOTE

A slight amount of collective friction (ap-proximately 3 pounds) should be used to prevent pilot induced collective oscillations.
O *13. FLIR -ON, wait for self test complete, set as desired, focus 2X, and modes set.
*14. Storm scope -ON, set as desired.
N O*15. HUD -Adjust brightness, mode, barometric al-titude, pitch, and roll as necessary.

During operation of the air conditioner system, the right cabin door should re-main closed. If opening is required, the right cabin door should not remain open for more than 1 minute.
NOTE

Turning the ECS on may cause the AFCS computer CPTR capsule and the TRIM and FPS caution to illuminate. PWR ON RE-SET to clear failure.
ECS heater will operate with either backup pump or windshield anti-ice operating, but not with both at same time.
*16.  ECS panel switches -As desired.

Engine anti-ice bleed and start valve mal-
function can cause engine .ameout.

17. Engine Health Indicator Test (HIT)/Anti-Icing Check -Accomplish. Refer to ENGINE HEALTH INDICATOR TEST/ANTI-ICE CHECK IN HELICOPTER LOG BOOK. HIT/ ANTI-ICE checks while operating in adverse conditions (e.g., dust, desert, coastal beach area, dry river beds) may be deferred (maximum of 5 .ight hours) until a suitable location is reached.
*18.  FUEL BOOST PUMP CONTROL switches -ON (for all fuel types). Indicator lights check -On.

O .

AUXILIARY FUEL MANAGE-MENT panel -Test and fuel transfer check.

8.24 BEFORE TAXI.

ES When on the ground, the ejector rack
lock lever should be turned inward to al-low the pilot visual con.rmation from the
cockpit. Prior to .ight, the ejector rack
lock lever must be in the unlock (vertical)
position to allow emergency jettisoning of
the tanks in .ight.

O*1.
ES Ejector rack lock levers unlocked.
O*2. Chaff electronic module safety pin(s) -Re-move.
*3. Chocks -Removed.
*4. Doors -Secure.

8-14 Change 2
*5. PARKING BRAKE -Release. 7. Wheel brakes -Check as required.
*
6. TAIL WHEEL switch -As required.
Change 2 8-14.1/(8-14.2 Blank)

8.25 GROUND TAXI.

When performing these maneuvers, cyclic inputs should be minimized to prevent droop-stop pounding.
Landing and searchlight have less than one foot ground clearance when extended. Use caution when taxiing over rough ter-rain when landing light and/or searchlight are extended.

Increase collective and place cyclic forward of neutral to start forward movement. Minimize forward cyclic move-ment to prevent droop stop pounding. Reduce collective to minimum required to maintain forward movement. Soft or rough terrain may require additional collective pitch. The use of excessive collective pitch during taxi, especially at light gross weights, can cause the tailwheel to bounce. Regulate taxi speed with cyclic and collective and control heading with pedals. Use brakes as required.
8.26 HOVER CHECK.

1. Systems -Check for caution/advisory legends, CDU and PDU(s) for normal indication.

2.
Flight instruments -Check as required.

3.
Power -Check. The power check is done by comparing the indicated torque required to hover with the predicted values from perfor-mance charts.

8.27 BEFORE TAKEOFF.

Pitot heat and anti-ice shall be on during operations in visible moisture with ambi-ent temperature of 4°C (39°F) and below. Failure to turn on pitot heat on in icing conditions can cause the stabilator to pro-gram trailing edge down during .ight. If
TM 1-1520-253-10
this occurs, manually slew the stabilator to zero degrees.
　
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