TM 1-1510-223-10 Change 3          9-7 before retracting the landing gear. Retract the flaps only as  safe  airspeed  permits  (APPROACH  position  until ^Vref ), then up. Perform single-engine go-around as fol- lows: 1.   Power — Maximum allowable. 2.   Landing gear — UP. 3.   Flaps — UP. 4.   Airspeed — V yse. 5.   LANDING lights — OFF. 9-16.   TWO ENGINES INOPERATIVE/OFF AIRFIELD LANDING. NOTE With propellers feathered, there is less drag and the aircraft will have a tendency to overshoot the planned touchdown point. NOTE When  landing  on  rough  terrain  or  unprepared surfaces,  the  landing  gear  will  absorb  landing energy during touchdown, if extended. Select landing gear up or down as best suits the con- ditions of the landing site. If gear-up, follow gear-up land- ing procedure. If gear-down, make a normal touchdown and use brakes as required. 9-17.   LOW OIL PRESSURE. In the event of a low oil pressure indication, perform procedures as applicable: 1.   Oil pressure below 90 PSI and above 60 PSI: Torque — As required (54% maximum). 2.   Oil  pressure  below  60  PSI:  Perform  engine shutdown, or land as soon as practicable using minimum power to ensure safe arrival. 9-18.   CHIP  DETECTOR  WARNING  ANNUNCIATOR ILLUMINATED. If the L CHIP DETECTOR or R CHIP DETECTOR warning annunciator illuminates, and safe single engine flight can be maintained. 1.   Perform engine shutdown. 2.   Land as soon as practicable. 9-19.   DUCT OVERTEMP CAUTION ANNUNCIATOR ILLUMINATED. Ensure  the  cabin  floor  outlets  are  open  and  unob- structed, then perform the following steps in sequence until the annunciator is extinguished. Allow approximate- ly 30 seconds after each adjustment for the system tem- perature to stabilize. The overtemperature condition is considered corrected at any point during the procedure that the annunciator extinguishes. 1.   CABIN AIR control — In. 2.   CABIN AIR MODE SELECT switch — AUTO. 3.   CABIN AIR TEMP CONTROL — DECREASE. 4.   FWD VENT BLOWER switch — HIGH. 5.   CABIN AIR MODE switch — MAN COOL. 6.   CABIN  AIR  MANUAL  TEMP  switch  —  DE- CREASE (hold). 7.   LEFT  ENVIRO  &  PNEU  BLEED  AIR    valve switch — PNEU ONLY. 8.   Light still illuminated after 30 seconds: LEFT ENVIRO & PNEU BLEED AIR valve switch — ON. 9.   RIGHT ENVIRO & PNEU BLEED AIR valve switch — PNEU ONLY. 10.   Light still illuminated after 30 seconds: RIGHT ENVIRO & PNEU BLEED AIR valve switch — ON. NOTE If the DUCT OVERTEMP annunciator has not extinguished after completing the above proce- dure, the warning system has malfunctioned. 9-20.   ENGINE ANTI-ICE FAILURE. Ice vane failure is indicated by the illumination of the amber #1 or #2 VANE FAIL caution annunciator lights. If the ice vanes fail to operate, perform the following: 1.   ICE VANE POWER SELECT switch — STBY. 2.   VANE    FAIL    annunciator    —    Check    extin- guished. 9-21.   ENGINE BLEED AIR SYSTEM MALFUNCTION. a.   BL AIR FAIL Annunciator Illuminated. Steady illu- mination of the warning annunciator in flight indicates a possible ruptured bleed air line aft of the engine firewall. The annunciator will remain illuminated for the remainder of flight. Perform the following: NOTE BLEED AIR FAIL annunciators may momentari- ly illuminate during simultaneous surface deice and brake deice operation at low N 1 speed. 1.   BRAKE DEICE switch — Off. 2.   TGT and torque — Monitor (note readings). 3.   ENVIRO  &  PNEU  BLEED  AIR  valve  switch (affected side) — Off.