Engine Failure on the Runway 07 Departure

Total power loss at 400 ft AGL, the instinct to turn back, and why the impossible turn is unrecoverable

Cessna 172R · Albert Whitted Airport (KSPG) · Private · Takeoff / Initial Climb

The scenario

• {'label': 'Field', 'value': 'KSPG · Albert Whitted'}
• {'label': 'Runways', 'value': '7/25 · 18/36'}
• {'label': 'Elevation', 'value': '7 ft'}
• {'label': 'Aircraft', 'value': 'C172R'}
• {'label': 'Dominant phase', 'value': 'Landing / Takeoff'}

The decision

Before we get into the decision tree — what do you know about engine failure immediately after takeoff and the 'impossible turn'? (Pick all that apply; this records your baseline.)

What the record shows

What the NTSB files show

Key lesson — Total engine power loss at 400 ft AGL over Tampa Bay on the Runway 07 departure leaves only one survivable option: accept the forward landing and execute a controlled ditching. A 180° turn back to the runway requires 600–800 ft of altitude; at 400 ft AGL, you will be too low to land safely. Attempting a steep turn to make the runway invites a stall-spin at 100 ft AGL — unrecoverable and fatal. Maintain wings level, establish 65 KIAS best glide, and commit to the ditching. Doors unlatched, master off before impact, flaps for slowest touchdown speed. Survival rate in a controlled ditching is high; survival rate in a stall-spin is zero.

Debrief — teaching points

The 'impossible turn' is impossible because the airplane does not have enough altitude.

A 180° turn in a C172R at best glide speed (65 KIAS) requires a minimum of 600–800 ft of altitude to complete safely and return to the runway. At 400 ft AGL, you will lose 400–600 ft of altitude during the turn and arrive at the runway threshold at 0–200 ft AGL — too low to land. The turn itself is not the problem; the lack of altitude is. Attempting to steepen the bank to tighten the turn increases descent rate and stall risk. At 100 ft AGL in a steep turn, a stall is unrecoverable.

Stall speed increases in a bank; a steep turn at low altitude is a stall trap.

In level flight, the C172R stalls at 44 KIAS (clean). In a 15° bank, stall speed is roughly 45 KIAS. In a 25° bank, stall speed is 46 KIAS. In a 45° bank, stall speed is 52 KIAS. At 400 ft AGL in a steep turn, you are flying at 70–79 KIAS — above stall speed, but the margin is thin. If you pull back on the yoke to stretch the glide (a natural instinct), the airspeed decays and you stall. A stall at 100 ft AGL is unrecoverable.

Accept the forward landing. A controlled ditching is survivable; a stall-spin is not.

When total engine power is lost at 400 ft AGL and the runway is not reachable, the correct decision is to accept the forward landing. Maintain wings level, establish 65 KIAS best glide, and prepare for a controlled ditching. Doors unlatched before water contact, master off just before impact, flaps for slowest possible touchdown speed (impact energy rises with the square of speed). Survival rate in a controlled ditching is significantly higher than in an uncontrolled impact or a stall-spin. The NTSB data is clear: pilots who attempted steep turns back to the runway at low altitude did not survive. Pilots who accepted the forward landing did.

Off Runway 07 at KSPG, the off-field environment is Tampa Bay — open water.

The runway 07 departure heading is 062°. The off-field environment in that direction is open water — Tampa Bay. There is no alternate landing surface ahead. A road or field to the left or right is possible, but dense development with power lines and buildings makes those options high-risk. A controlled ditching in open water is the safest option. Know the off-field environment for each runway before you depart. At KSPG, Runway 07 and Runway 18 both have open water off their departure ends. Runway 25 and Runway 36 have dense development. This knowledge should inform your runway selection and your emergency response.

Preflight fuel check is non-negotiable; fuel exhaustion is preventable.

NTSB ERA12LA294 (2012 C172R) lost engine power due to fuel exhaustion during climb. The probable cause was inadequate fuel management and failure to supervise the student's preflight inspection. The fuel tanks were not properly filled or checked. A thorough preflight fuel check — visually confirming fuel level in both tanks, checking the fuel selector is on BOTH, and confirming fuel quantity on the gauges — takes 2 minutes and prevents a preventable engine failure. If you are not certain the fuel is there, do not fly.

Engine failure can occur for reasons beyond your control — but your response is within your control.

NTSB ANC18LA013 (2017 C172R) experienced total engine power loss for reasons that could not be determined despite postaccident examination. WPR18LA039 (2017 C172R) experienced crankshaft fatigue fracture. ERA14LA142 (2014 C172R) experienced improper vacuum pump installation. These failures are rare, but they happen. You cannot prevent them. What you can control is your response: accept the forward landing, maintain wings level, establish best glide speed, and execute a controlled ditching if necessary. The pilot's decision-making in the first 60 seconds after engine failure determines survivability.

Built from the real accident record

Scenario built from NTSB ANC18LA013 (2017 C172R total power loss, undetermined cause), WPR18LA039 (2017 C172R crankshaft fatigue fracture during climb), ERA14LA142 (2014 C172R vacuum pump installation failure, power loss on approach), and ERA12LA294 (2012 C172R fuel exhaustion during climb). Regional precedents: WPR17FA152 (2017 Pazmany PL-2, engine failure / stall-spin on attempted return), LAX93LA048 (1992 Rans S-10, power loss / stall at 150–200 ft), ERA14FA123 (2014 Sonex, partial power loss / 180° turn stall-spin), SEA90LA162 (1990 SA102 Cavalier, power loss / spin). Localized to KSPG.

NTSB reports: ANC18LA013 · WPR18LA039 · ERA14LA142 · ERA12LA294 · WPR17FA152 · LAX93LA048 · ERA14FA123 · SEA90LA162

ACS tasks: PA.I.F — Weather Information · PA.I.G — Cross-Country Flight Planning · PA.IX.C — Emergency Approach and Landing · PA.I.H — Human Factors · PA.II.A — Preflight Assessment · PA.II.B — Engine Starting / Systems Preflight

Relevant FARs: §91.3 · §91.13 · §91.185

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