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required.
8-14
TM 1-1520-248-10
Figure 8-2. Power Assurance Charts (T703-AD-700A/250-C30R)(Sheet 1 of 2)
8-15
TM 1-1520-248-10
Figure 8-2. Power Assurance Charts (250-C30R/3)(Sheet 2 of 2)
5. MMS OFF.
8-31. AFTER LANDING CHECK.
6. (CDS4) IDM Shut down.
1. Landing light OFF as required.
7. Throttle Reduce to idle for 2 minutes.
2. Transponder STBY as required.
8. BATT 1/BATT 2 Check as follows:
3. ASE Set as required.
a. MPD SEL Select RECT LD %/ S GEN
8-32. ENGINE SHUTDOWN. LD %.
1. Flight controls Cyclic centered, pedals b. BATT 1 switch OFF.
neutral, collective down.
c. MPD Check S GEN LD % and note
2. FORCE TRIM switch FORCE TRIM. indication.
3. Present position Store or record as O d. BATT 2 switch OFF. Check S GEN LD %
required. for a decrease which should not exceed 3%.
O 4. AVTR STOP. e. BATT 1 switch BATT 1. Check S GEN LD
% increase should not exceed 3%.
NOTE
NOTE
To prevent loss of MMS volatile data, place
MMS mode select switch to OFF before Fluctuations of 3% or less indicate a fully
reducing the throttle to idle. charged battery.
O 9. AC GEN switch OFF.
8-16
TM 1-1520-248-10
d. Throttle Closed by 30% NG.
10. FUEL BOOST switch OFF.
CAUTION
O 11. ASE Off as follows:
a. RADAR DETR switch DETR (OFF). If TGT rises above 400 °C (indicating a
residual fire in the engine) engage
b. RADAR WARN switch WARN (OFF). START switch until TGT is less than 200
°C.
c. IR JAMMER XMTR switch IR JAMMER
(OFF). 19. Throttle Closed and monitor TGT.
12. Standby attitude indicator Caged. 20. Overhead switches Set; off except battery,
required lights, and the following:
13. SCAS PWR OFF.
a. COMPT BLWR switch AUTO.
14. (CDS2) DTS/ MDU Mission store as
desired. b. ESNTL BUS switch START when NG is
less than 10%.
15. (CDS2) ENGINE MONITOR/ FADEC
MONITOR and ENGINE HISTORY pages 21. IGN circuit breaker switch OFF.
Check and record faults or values that exceed
limitations. NOTE
16. (OH-58D) ESC Check as follows: Do not proceed with the following steps
until NG is indicating zero percent, or the
a. INIT switch Press. FADEC HMU pistons may not park.
b. FDL MENU key Press. 22. Battery and light switches OFF, when main
rotor blades stop turning.
c. BIT key Press.
23. Ignition keylock switch OFF, remove key
d. DIGITAL fuel control overspeed test button as required.
Press and release.
CAUTION
e. BIT codes Record if any and notify
maintenance To prevent damage to honeycomb panel
under crew member doorframe, do not
O 17. AVTR MANUAL UNTHREAD, as required. drop seat belt against side of aircraft.
NOTE O 24. Doors Close immediately after exiting
aircraft.
Successful completion of OS TEST will
result in engine shutdown.
8-33. BEFORE LEAVING HELICOPTER.
18. OS TEST Perform (first flight of the
day) as follows: 1. Walk-around Complete, Checking the
following:
a. INIT key Press.
O a. Ejector rack pins Installed.
b. FDL MENU key Press.
O b. Weapons systems Check, v e r i f y
c. OS TEST key Press (two times within 15 ammunition load status.
seconds).
c. Check aircraft for damage, fluid leaks, fluid
levels, and bypass indicators.
8-17
TM 1-1520-248-10
O d. AVTR tape Remove as desired. b. Operation within 200 NM of a volcanic area.
e. DTS/MDU cartridge Remove as required. c. Operation in heavy rain.
2. DA Forms Complete as required to include
the following conditions: 3. Main rotor blades Tie down as required.
a. Operation within 10 NM of salt water. 4. Secure helicopter as required.
SECTION III. INSTRUMENT FLIGHT
8-34. INSTRUMENT FLIGHT GENERAL. This helicopter is restricted to visual flight conditions.
Flight into instrument meteorological conditions will be
WARNING conducted on an emergency basis only. Flight handling,
stability characteristics, and range are the same during
instrument flight as for visual flight.
Flight into instrument meteorological
conditions has not been demonstrated in
this aircraft.
SECTION IV. FLIGHT CHARACTERISTICS
8-35. FLIGHT CHARACTERISTICS. vibrations through the airframe and flight controls. If
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OPERATOR’S MANUAL FOR ARMY OH-58D HELICOPTER 2(79)
