Engine Failure on Initial Climb
Total power loss at 400 ft AGL over Tampa North Aero Park — the off-field environment is poor in all directions, and the decision window is measured in seconds
The scenario
Departing Tampa North Aero Park Airport (X39), Tampa, FL — Runway 14, climbing out on a 141° heading. Elevation 68 ft MSL. The runway is 3,541 ft of asphalt; you are on a touch-and-go training flight with an instructor.
It is a clear, calm Florida morning: OAT 22°C, winds light and variable, altimeter 29.98. Visibility 10 SM. The airport is non-towered (CTAF); you are in Class G airspace below 3,000 ft MSL. Above 3,000 ft MSL, you are in the overlying Tampa Class B airspace (3,000–10,000 MSL). The nearest Class D is at Brooksville (BKV), 15.5 nm away.
You are on the initial climb after a touch-and-go landing. The airplane is at 400 ft AGL, climbing at 79 KIAS (Vy, best rate of climb), heading 141°. The instructor is in the right seat. The engine has been running normally throughout the flight — no anomalies during the run-up, no issues during the landing, no rough running or instrument indications on the climb-out.
Then, at 400 ft AGL, the engine loses power completely. The tachometer drops to zero. The propeller is still turning (windmilling), but there is no power. You have roughly 30 seconds of useful decision time before altitude becomes critical.
Aircraft: Cessna 172R, dual, full fuel, within limits. Lycoming IO-360-L2A, fuel-injected, fixed-pitch prop, steam panel (vacuum-driven gyros), fuel selector on BOTH. The airplane was airworthy at departure; nothing was written up. The engine ran smoothly through the run-up and the touch-and-go landing.
Pilot: you — a Private pilot, current, roughly 250 hours total. You have 15 hours in the C172R. This is a training flight with an instructor; the instructor is experienced and will support your decision-making but will not take the controls unless you ask or the situation becomes unrecoverable.
- {'label': 'Field', 'value': 'X39 · Tampa North Aero Park'}
- {'label': 'Runways', 'value': '14/32'}
- {'label': 'Elevation', 'value': '68 ft'}
- {'label': 'Aircraft', 'value': 'C172R'}
- {'label': 'Dominant phase', 'value': 'Takeoff / Landing'}
The decision
Before we get into the decision tree — what do you already know about engine failure on initial climb in the C172R? (Pick all that apply; this records your baseline.)
What the record shows
What the NTSB files show
NTSB CEN14LA333 (2014): A Cessna 172R on an instructional cross-country flight experienced partial loss of engine power during initial climb after a touch-and-go landing. The pilot attempted to turn back to the departure runway. The airplane stalled and impacted terrain short of the runway. The probable cause was partial loss of engine power for reasons that could not be determined — postaccident engine examination revealed no mechanical anomalies that would have precluded normal operation. The pilot's decision to attempt a turn back at low altitude with degraded power was a contributing factor.
NTSB ANC18LA013 (2017): A Cessna 172R on a personal flight experienced total engine power loss shortly after takeoff during initial climb. The pilot attempted to turn back to the departure runway. The airplane stalled and impacted terrain. The probable cause was total loss of engine power for reasons that could not be determined — postaccident examination and testing revealed no mechanical failures. The stall/spin on the turn back was the fatal outcome.
NTSB WPR18LA039 (2017): A Cessna 172R experienced total engine power loss due to crankshaft fatigue fracture during climb. The instructor performed a forced landing to a field past the runway. The airplane impacted a fence. The probable cause was fatigue separation of the crankshaft — a mechanical failure that resulted in total loss of engine power. The forced landing was the correct decision; the impact with the fence was secondary to the power loss.
NTSB ERA14LA142 (2014): A Cessna 172R experienced rapid oil pressure loss during climb. The pilot returned to the departure airport and lost all engine power during an ILS approach, resulting in a forced landing on a highway. The probable cause was total loss of engine power due to improper installation of the lower vacuum pump by maintenance personnel — a post-maintenance failure.
The common thread across all these events: engine failure on initial climb in the C172R is sudden and complete. The cause is often undetermined (mechanical anomaly, maintenance error, or latent defect). The critical decision is made in the first 30 seconds: attempt to turn back to the runway (marginal at 400 ft AGL, often results in stall/spin), or land straight ahead in the best available spot (controlled landing, survivable). The real accidents cited above occurred at other airports — NOT at Tampa North Aero Park (X39). X39 has its own accident history (see field dominant patterns: loss of control in flight, 27.3%; loss of control on ground, 18.2%), but these specific NTSB cases happened elsewhere. The scenario is localized to X39 to make the off-field environment real and consequential for you as a student here.
The consistent lesson: at 400 ft AGL with total engine power loss, the turn back to the runway is marginal. The stall/spin on the turn back is the fatal trap. A controlled landing straight ahead, at best glide speed, with appropriate flap deployment, is the correct outcome. The runway is behind you; the best landing surface ahead is the one you commit to.
Key lesson — Engine failure on initial climb in the C172R is sudden and complete. At 400 ft AGL, the turn back to the runway is marginal — a steep bank angle required to make the runway brings you close to stall speed in the turn. The stall/spin on the turn back is the fatal outcome. The correct decision is to establish best glide speed (65 KIAS) immediately, assess the landing options ahead, and commit to a controlled landing in the best available spot — a parking lot, a road, or a cleared area. The runway is behind you; do not try to stretch the glide back to it at the cost of a stall.
Debrief — teaching points
Engine failure on initial climb is sudden and complete — there is no time for diagnosis.
The NTSB cases show that engine failure in the C172R on initial climb is often total and immediate. The cause is frequently undetermined — a mechanical anomaly, a maintenance error, or a latent defect that does not show up in postaccident testing. There is no time to troubleshoot: no time to check the fuel selector (it is already on BOTH), no time to try a restart, no time to diagnose. Your first action must be to establish best glide speed (65 KIAS) and buy time to assess landing options. Everything else is secondary.
At 400 ft AGL with total power loss, the turn back to the runway is marginal — often fatal.
The 'impossible turn' is real. At 400 ft AGL, a 180° turn back to the departure runway requires a bank angle of roughly 20–25° to make the turn in the available altitude. At that bank angle, the stall speed increases to roughly 50–55 KIAS. If you are at 79 KIAS (Vy) when power is lost, you have only 20–30 KIAS of margin before stall. A steep turn, back-pressure to maintain altitude, and the descent rate of a powerless airplane combine to bring you to the stall envelope. The stall break at 200–300 ft AGL is unrecoverable. The NTSB CEN14LA333 and ANC18LA013 cases show this pattern. Do not attempt the turn back at 400 ft AGL unless the landing site ahead is worse than certain death.
Establish best glide speed immediately — 65 KIAS in the C172R.
Best glide speed in the C172R is 65 KIAS at gross weight. This speed maximizes glide distance and gives you the most time and distance to assess landing options. At 400 ft AGL, establishing 65 KIAS immediately buys you 30–45 seconds and roughly 1,200–1,400 ft of horizontal distance. That is your decision window. Use it to assess the landing site ahead, not to attempt a marginal turn back to the runway.
Off Runway 14 at X39, the off-field environment is poor in all directions — medium development, low-density development, wooded wetland.
The USGS NLCD ground cover off Runway 14's climb-out (heading 141°) shows medium development, low-density development, and wooded wetland. There is no clear open field. A parking lot, a road, or a cleared area in the development is the best landing option. Wooded wetland is the worst option — soft ground, trees, water. Know the off-field environment before you depart. If the off-field environment is poor (as it is at X39), the turn back to the runway becomes more attractive — but only if you can make it without stalling.
Flap deployment in a forced landing is about touchdown speed, not descent rate.
In the C172R, full flaps (30°) reduce the stall speed to Vs0 (roughly 33 KIAS in landing configuration). The dominant benefit of full flaps is the slowest possible touchdown speed — impact energy rises with the square of touchdown speed. A touchdown at 50 KIAS (with full flaps) is significantly less violent than a touchdown at 65 KIAS (no flaps). The steeper descent path is secondary. In a tight parking lot landing, full flaps (85 KIAS max) or partial flaps (110 KIAS max for 10°) are both appropriate — you are well below the limits at 65 KIAS glide speed.
The C172R is fuel-injected — there is no carburetor heat, and restart procedures differ from carbureted models.
The C172R has a Lycoming IO-360-L2A, fuel-injected engine. There is no carburetor, no carburetor heat, and no carb-ice risk. Engine roughness in a fuel-injected airplane is addressed through mixture, boost pump, and hot-start technique — not carb heat. The vacuum panel (steam gauges, vacuum-driven attitude and heading indicators) is a separate system; a vacuum pump failure will cause partial-panel loss, but not engine failure. Know the systems on the airplane you are flying.
Built from the real accident record
Scenario built from NTSB CEN14LA333 (2014 C172R partial power loss on initial climb), ANC18LA013 (2017 C172R total power loss shortly after takeoff), WPR18LA039 (2017 C172R crankshaft fatigue fracture during climb), and ERA14LA142 (2014 C172R oil pressure loss and vacuum pump installation failure). Anonymized and localized to Tampa North Aero Park Airport (X39).
NTSB reports: CEN14LA333 · ANC18LA013 · WPR18LA039 · ERA14LA142
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.B — Engine Starting / Systems Preflight
Relevant FARs: §91.3 · §91.13 · §91.185
Step through the full decision tree, make the calls, and see where each choice leads — then debrief it with your CFI.
Open the interactive scenario →All sample scenarios · More Cessna 172R scenarios · More scenarios at X39