Light Twin, Engine Failure at 300 ft, and a Question You Should Have Answered on the Ground

Available gradient: 220 fpm at about 105 kt (10,640 ft/min) = 220 / 10,640 = 2.1 percent - about 21 ft of climb per 1,000 ft of horizontal travel.

What the failure costs: 300 ft AGL minus 250 ft lost during identify-verify-feather leaves roughly 50 ft AGL by the time the propeller is feathered and the airplane is stabilized on one engine.

What the obstacle demands: if the airplane is stabilized at 50 ft AGL and roughly 1,600 ft from a 350-ft obstacle (2,500 ft minus the distance covered during feathering), the required gradient is (350 - 50) / 1,600 = about 19 percent.

2.1 percent available against 19 percent required. The airplane will arrive at the obstacle roughly 300 ft too low. This is not a marginal case - it is a guaranteed collision with terrain.

The lesson: the departure was decided on the ground. At 4,200 lb, 1,200 ft elevation, and 25 degrees C, the single-engine climb capability of this airplane is essentially flat, and no amount of pilot skill at 300 ft fixes that. The takeoff should have been rejected during planning, or the weight and temperature should have been changed until the one-engine-inoperative gradient cleared the obstacle with real margin.

With no V1, the manufacturer gives accelerate-stop distance and a single-engine takeoff distance over 50 ft, but the pilot must build the decision point from those numbers plus the runway environment.

Brief it in three parts:

1. Before the decision point (speed and runway remaining): if the engine fails, retard both throttles, maintain directional control with rudder, and stop on the remaining runway. You must know the accelerate-stop distance and mark a physical point on the runway - a taxiway, a crack, a sign - by which you will either be at your target speed or aborting.

2. After the decision point: you are committed. Pitch for blue line (Vyse), positive rate, gear up, and fly the airplane - but only if the pre-takeoff performance analysis showed the one-engine-inoperative gradient clears the obstacles. In this case it did not, so the decision point was effectively never reached: the takeoff should not have been started.

3. The published single-engine takeoff distance assumes a pilot at the top of their game, an engine that fails at the worst possible moment, and a propeller that feathers promptly. Treat it as a demonstration, not a guarantee.

The point of the briefing is that the answer to "what do I do if it quits at 300 ft" must be decided at the hold-short line, when you can still change the outcome.

Service ceiling is the altitude at which the airplane can still climb at 100 fpm with one engine inoperative. At 6,200 ft, level flight at 11,500 ft is impossible on one engine - the airplane cannot even hold altitude, let alone the MEA.

What happens: the airplane will drift down. At Vyse, the rate of descent in the early part of the driftdown is modest (a few hundred fpm), so the altitude loss to the MEA is manageable - from 11,500 to 9,000 is 2,500 ft, which at 300 fpm is about eight minutes and roughly 20 nm of forward travel. Below 9,000 ft you are below the MEA and below the terrain.

The real problem is the 8,000-ft terrain: your driftdown floor must be above the terrain plus a margin, not above the MEA. If the single-engine absolute ceiling in the conditions of the day is near 8,000 ft, there is a genuine possibility of not being able to outclimb the terrain at all.

So the correct plan, made before departure and re-evaluated in cruise: know the single-engine service ceiling for the actual weight and temperature, choose a route whose terrain allows a driftdown to a safe altitude, identify the nearest suitable airport at each point along the route, and treat crossing high terrain in a light twin as a decision that must be justified by the numbers rather than assumed.