TM 1-1510-224-10 10. CONDITION lever    HIGH   IDLE.      Monitor TGT as CONDITION lever is advanced. 11. DC GPU disconnect As required. 12. GENERATOR switch RESET then  ON, for second engine battery start. * 8-19.  SECOND ENGINE START (GPU START). 1. Propeller area Clear. 2. ENG   START   switch    START-IGNITION. IGN ON annunciator should illuminate and FUEL PRESS annunciator should extinguish. 3. CONDITION lever (after N₁ RPM stabilizes    above    13%    minimum)    LOW IDLE. 4. TGT    and    N₁    Monitor    (TGT    1000°    C maximum). 5. Oil pressure Check (60 PSI minimum). 6. ENG    START    switch    OFF    after     TGT peaks. CAUTION Monitor oil temperature closely during ground operation with propellers in FEATHER due to lack of air flow over oil cooler. 7. AC and DC GPU units Disconnect (check aircraft external power and mission external power annunciators extinguished). 8. CONDITION levers  HIGH  IDLE.    Monitor TGT as CONDITION levers are advanced. 9. PROP levers HIGH RPM. 10. #1 and #2 INVERTER switches ON Check INVERTER annunciators extinguished. 11. GENERATOR   switch    (1)    RESET,    then ON. 12. Current limiters Check as indicated: a. BATTERY    CHARGE     annunciator Check    on.        BATTERY    CHARGE annunciator should extinguish within 5 minutes following a normal engine start on battery. b. # 1 and # 2 INV annunciators Check extinguished. This procedure checks   both   400   and   500   ampere current  limiters  that  tie  aircraft  bus systems together. 13. GENERATOR switch RESET, then ON. NOTE To    reset    beacon    light,    turn    OFF approximately  5  seconds,  then  DAY or NIGHT.  When voltage drops below approximately   20   volts,   the   beacon light may become inoperative. 14. BEACON    lights    switch    OFF,    then    as required. 8-20.  BEFORE TAXIING. * 1. BRAKE   deice   switch   Check   and   set   as required.  Ensure both bleed air valves are open. * 2. CABIN   AIR   MODE   and   TEMP   controls Set as desired. NOTE For maximum cooling on the ground, turn  the  PNEU  &  ENVIRO  BLEED  AIR valve switches to PNEU ONLY position.      Verify   airflow   is   present from   aft   cockpit   eyeball   outlets   to ensure  sufficient  cooling  for  mission equipment. H3.   AC/DC power Check for: (1) AC frequency 394 to 406 Hz. (2) AC voltage 104 to 124 VAC. (3) DC voltage 28 to 28.5 VDC. * 4. AUTO PLT POWER switch-ON. *5. AVIONICS MASTER POWER switch-ON. * 6. # 1 and # 2 EFIS POWER switches-ON. *7. Mission-panel Set as follows: a. 3fAC  CONTROL  switches,  #1  INV and #2 INV RESET- ON. b. MISSION     CONTROL     switch     As required. c. ELINT/COMINT    switches     (2)     As required. H 8.   Pilot's  and  copilot's  EFIS  TEST  switches As required.  (Refer to paragraph 8-9.) H 9.   Automatic flight control system-Perform as required.  (Refer to paragraph 8-9.) H 10.   Avionics Check and set as required. 11. Weather radar/LSS-SBY. 12. Flaps Check. 8-18