TM 1-1510-223-10 8-28           Change 3 Section  III. INSTRUMENT FLIGHT 8-38.   GENERAL. This  aircraft  is  qualified  for  operation  under  instru- ment flight meteorological conditions. Handling charac- teristics, stability characteristics, and range are the same during instrument flight conditions as when under visual flight conditions. 8-39.   INSTRUMENT FLIGHT PROCEDURES. Refer to FM 1-240; DOD FLIP; AR 95-1; and proce- dures described in this manual or applicable foreign reg- ulations. 8-40.   INSTRUMENT TAKEOFF. NOTE If the GO AROUND button is depressed to set a 7 degree takeoff command, the yaw damper will engage. Complete the normal checks prescribed in this chap- ter. Follow takeoff procedures dictated by local condi- tions. 8-41.   AUTOPILOT COUPLED APPROACHES. The recommended airspeed for autopilot coupled ap- proaches is 130 KIAS. Section  IV. FLIGHT CHARACTERISTICS 8-42.   STALLS. A prestall warning in the form of light buffeting may be felt when approaching a stall. An aural warning is also provided by the warning horn. The warning horn will be- gin to sound approximately 5 to 19 knots above power off stall speed, depending on aircraft configuration, altitude, and power. If correct stall recovery technique is used, very little altitude will be lost during the stall recovery. For the purpose of this section, the term Power On means that both engines and propellers of the aircraft are oper- ating normally and are responsive to pilot control. The term Power Off means that both engines are operating at idle power. During practice, enter power off stalls from normal glides. Enter power on stalls by smoothly increas- ing pitch attitude to a climb attitude obviously impossible for the aircraft to maintain, and hold that attitude until the stall occurs. a.   Power On Stalls. The power on stall attitude is very steep and unless this high pitch attitude is maintained, the aircraft will generally settle or mush instead of stall. It is difficult to stall the aircraft inadvertently in any normal maneuver. A light buffet precedes the stall, and the first indication of approaching stall is generally a decrease in control effectiveness, accompanied by a tone from the stall warning horn. The stall itself is characterized by a rolling  tendency  if  the  aircraft  is  allowed  to  yaw.  The proper use of rudder will minimize the tendency to roll. A slight pitching tendency will develop if the aircraft is held in the stall, resulting in the nose dropping slightly, then pitching up toward the horizon; this cycle is repeated until recovery is made. Control is regained very quickly with little altitude loss, providing the nose is not lowered ex- cessively. Begin recovery with forward movement of the control wheel and a gradual return to level flight. The roll tendency caused by yaw is more pronounced in power on stalls, as is the pitching tendency. b.   Power Off Stalls. The rolling tendency is consider- ably less pronounced in power off stalls (in any configura- tion),  and  is  more  easily  prevented  or  corrected  by adequate rudder and aileron control, respectively. The nose will generally drop straight through with some ten- dency to pitch up again if recovery is not made immedi- ately.   The   Stall   Speed   graph   (fig.   8-2)   shows   the indicated power off stall speeds with aircraft in various configurations. Altitude loss during a full stall may be as high as 1270 feet. c.   Accelerated  Stalls.  The  aircraft  gives  noticeable stall warning in the form of buffeting when the stall oc- curs. The stall warning and buffet can be demonstrated in turns by applying excessive back pressure on the con- trol wheel. 8-43.   SPINS. Intentional spins are prohibited. If a spin is inadver- tently entered use the following recovery procedure: WARNING Spin demonstrations have not been conducted. The  recovery  technique  is  based  on  the  best available information. The first three actions should be performed as nearly simultaneously as possible. 1.   POWER levers — IDLE. 2.   Apply  full  rudder  opposite  direction  of  spin rotation. 3.   Simultaneously with rudder application, push control wheel forward and neutralize ailerons.