BEECHCRAFT Sundowner 180 C23 (M-1285 and After) Emergency Procedures

MAXIMUM GLIDE CONFIGURATION 1. Flaps - UP 2. Airspeed - 78 kts/90 mph Glide distance (Zero Wind Condition) is approximately 1.7 I nautical miles (2 statute miles) per 1000 feet of altitude above the terrain. December, 1991 3-7 Section III Emergency Procedures seECHCRAFT Sundowner 180 C23 (M-1285 and After) LANDING EMERGENCIES LANDING WITHOUT POWER When assured of reaching the landing site selected, and on final approach: 1. Airspeed - 68 kts/78 mph 2. Fuel Selector Valve - OFF 3. Mixture - IDLE CUT-OFF 4. Magneto/Start Switch - OFF 5. Flaps - AS REQURIED 6. Battery Switch, Alternator Switch, and Fuel Boost Switch - OFF 7. Upper Cabin Door Latch - OPEN (if installed) SYSTEMS EMERGENCIES STARTER ENGAGED WARNING LIGHT I ILLUMINATED (IF INSTALLED) The STARTER ENGAGED warning light illuminates when- ever the starter is engaged. If this light remains illuminat- ed after Magneto/Start Switch is released from the START position, the starter relay is still energized. Con- sequently, electrical power is still being supplied to the starter, and it remains engaged. Continuing to supply power to the starter will eventually result in the complete loss of electrical system power, substantial starter dam- age, and possible damage to other electrical system com- ponents. If light remains illuminated on the ground: 1. Battery Switch and Alternator Switch - OFF 2. Do Not Take Off. 3-8 December, 1991 BEECHCRAFT Sundowner 180 C23 (M-1285 and After) Section III Emergency Procedures If light remains illuminated in flight after air start: 1. Battery Switch and Alternator Switch - OFF 2. Land As Soon As Practical. ALTERNATOR-OUT P'ROCEDURE An inoperative alternator will place the entire electrical operation of the airplane on the battery. Alternator mal- function will be indicated by a fluctuation of the ammeter needle, or by a discharge indication. If this condition de- velops: 1. Alternator Switch - OFF MOMENTARILY, THEN ON (this resets overvoltage relay) If alternator-out condition persists: 2. Alternator Switch - OFF 3. Nonessential Electrical Equipment - OFF to con- serve battery power. I WARNING I Deactivation of the battery switch, al- ternator switch, or alternator circuit breaker during flight is prohibited, ex- cept as required by an actual emer- gency. UNSCHEDULED ELECTRIC STABILATOR TRIM 1. Airplane Attitude - MAINTAIN using stabilator con- trol. 2. Stabilator Trim Thumb Switch (On Control Wheel) - MOVE IN DIRECTION OPPOSITE UNSCHEDULED PITCH TRIM to open circuit breaker. 3. Stabilator Trim ON-OFF Switch (On Instrument Pan- el) - OFF December, 1991 3-9 Section III Emergency Procedures seeCHCRAFT Sundowner 180 C23 (M-1285 and After) 4. Manual Stabilator Trim Control Wheel - RETRIM AS DESIRED. EMERGENCY STATIC AIR SOURCE SYSTEM THE EMERGENCY STATIC AIR SOURCE SHOULD BE USED FOR CONDITIONS WHERE THE NORMAL STATIC SOURCE HAS BEEN OBSTRUCTED. When the airplane has been exposed to moisture and/or icing conditions (especially on the ground), the possibility of obstructed static ports should be considered. Partial obstructions will result in the rate of climb indication being sluggish during a climb or descent. Verification of suspected obstruction is possible by switching to the emergency system and noting a sudden sustained change in rate of climb. This may be accompanied by abnormal indicated airspeed and altitude changes beyond normal calibration differences. Whenever any obstruction exists in the Normal Static Air System or the Emergency Static Air System is desired for use: 1. Pilot's Emergency Static Air Source - Switch to ON EMERGENCY. 2. For Airspeed Calibration and Altimeter Correction, refer to PERFORMANCE section. Be certain the emergency static air valve is in the NORMAL position when system is not needed. UNLATCHED DOOR IN FLIGHT If the cabin door is not locked it may come unlatched in flight. This may occur during or just after take-off. The door will trail in a position approximately 3 inches open. 3-10 December, 1991 BEECHCRAFT Sundowner 180 C23 (M-1285 and After) Section III Emergency Procedures A buffet may be encountered with the door open in flight. Return to the field in a norma' manner. If practicable, dur- ing the landing flare-out, have a passenger hold the door to prevent it from swinging open. SPINS I WARNING I Intentional spins are prohibited when operating in the Normal Category. In- tentional spins are also prohibited in the Utility Category unless the air- plane is approved for spins and equipped with a spin kit, or if the air- plane is approved for operation in the Acrobatic Category. Refer to Service Instructions No. 0619-090. The airplane will not spin if orthodox entry is used, but will enter a spiral dive. Speed builds rapidly in a spiral dive, requiring high pullout loads. Therefore, if a spiral is inadvertently entered, recovery from the spiral is to be initiated within two turns. ENTRY Stall the airplane with the control column hard back, throttle in idle position, flaps up, carburetor heat as re- quired and with the nose about 150 above the horizon. At the stall, apply full rudder in the direction required to spin. A slight rudder application immediately before the stall will assure the direction of spin. The airplane nose will drop and rotate towards the applied rudder. When the wings are 900 to the horizon, apply full aileron against the December, 1991 3-11 Section III Emergency Procedures BEECHCRAFT Sundowner 180 C23 (M-1285 and After) intended direction of spin. The airplane will go slightly in- verted and enter a normal spin. If aileron against the direction of spin is not applied or ap- plied too late, the airplane will enter a rapid spiral dive, and recovery must be initiated by the second turn. If the full back stick is not applied and held, the airplane may spiral. Again, recovery must be initiated not later than the second turn. If aileron is applied too early, the airplane will not rotate and merely remain in a straight stalled condition. RECOVERY If a spin is entered inadvertently: Immediately move the control column full forward and si- multaneously apply full rudder opposite to the direction of the spin; continue to hold this control position until rota- tion stops and then neutralize all controls and execute a smooth pullout. Ailerons should be neutral and throttle in idle position at all times during recovery. 3-12 December, 1991