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## Landing Gear Control Selected Up, Single-Engine Climb Performance Inadequate 

When operating near or above the single-engine ceiling and an engine failure is experienced shortly after lift-off, a landing must be accomplished on whatever essentially lies ahead. [Figure 12-12]  There is also the option of continuing ahead, in a descent at V$_{YSE}$ with the remaining engine producing power, as long as the pilot is not tempted to remain airborne beyond the airplane’s performance capability. Remaining airborne and bleeding off airspeed in a futile attempt to maintain altitude is almost invariably fatal. Landing under control is paramount. The greatest hazard in a single-engine takeoff is attempting to fly when it is not within the performance capability of the airplane to do so. An accident is inevitable. 

Analysis of engine failures on takeoff reveals a very high success rate of off-airport engine inoperative landings when the airplane is landed under control. Analysis also reveals a very high fatality rate in stall spin accidents when the pilot attempts flight beyond the performance capability of the airplane. 

As mentioned previously, if the airplane’s landing gear retraction mechanism is dependent upon hydraulic pressure from certain engine-driven pump, failure of that engine can mean a loss of hundreds of feet of altitude as the pilot either windmills the engine to provide hydraulic pressure to raise the gear or raises it manually with a backup pump. 

## Landing Gear Control Selected Up, Single-Engine Climb Performance Adequate 

If the single-engine rate of climb is adequate, the procedures for continued flight should be followed. [Figure 12-13] There are four areas of concern: control, configuration, climb, and checklist. 

## Control 

The first consideration following engine failure during takeo ff is to maintain control of the airplane. Maintaining direct ional control with prompt and often aggressive rudder application and STOPPING THE YAW is critical to the safety of flight. Ensure that airspeed stays above V$_{MC}$ If the yaw cannot be controlled with full rudder applied, reducing thrust on the 

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