Partial Power Loss on Runway 10 Departure
Engine degradation at 400 ft AGL over dense Tampa development — no good forced-landing site, and the clock is ticking
The scenario
Departing Tampa International Airport (KTPA), Tampa, FL — Runway 10, climbing out on a 092° heading. Field elevation 26 ft MSL. You are in Class B airspace; tower is active 24/7.
It is a warm, humid Florida morning in late July: OAT 32°C, dew point 26°C, altimeter 29.89. Scattered clouds at 3,500 ft, visibility 10 SM. High density altitude — the air is thick and the airplane will climb sluggishly. The runway is long (6,999 ft), but the climb-out environment off Runway 10 (heading 092°) is dense development: commercial buildings, parking lots, medium-density residential, and scattered wooded wetland. There is no open field, no park, no water. The off-field environment is marginal at best — mostly built-up.
You are a Private pilot with roughly 250 hours total, 40 hours in the Piper Cherokee 180. This is a familiar airplane and a familiar airport. You have filed IFR for a 200-nm flight to the north; you are cleared to climb to 3,000 ft MSL on departure.
Aircraft: Piper Cherokee 180, solo, 45 gallons usable fuel (full tanks), within weight and balance limits. The airplane was serviced yesterday; the last 100-hour inspection was 8 hours ago. Nothing was written up. The preflight was routine — you checked the mags, the engine ran smoothly, carb heat was tested, mixture was set for sea-level density altitude.
You line up on Runway 10, advance the throttle to full power, and begin the takeoff roll. The engine sounds normal. Airspeed is building. At 50 KIAS you rotate; at 60 KIAS the nose comes up and the wheels leave the pavement. You are climbing out at 70 KIAS (close to Vx, best angle of climb at 64 KIAS), gear is fixed, flaps are up. The tower clears you to climb to 3,000 ft MSL.
At 400 ft AGL — roughly 426 ft MSL — the engine begins to lose power. The tachometer is unwinding. The rate of climb is dropping. You are still over dense development. The runway is behind you. You have roughly 30 seconds before altitude becomes critical.
- {'label': 'Field', 'value': 'KTPA · Tampa'}
- {'label': 'Runways', 'value': '10/28 · 19L/01R · 19R/01L'}
- {'label': 'Elevation', 'value': '26 ft'}
- {'label': 'Aircraft', 'value': 'PA-28-180'}
- {'label': 'Dominant phase', 'value': 'Landing / Takeoff'}
The decision
Before we get into the decision tree — what do you know about partial engine power loss in the PA-28-180 on initial climb? (Pick all that apply; this records your baseline.)
What the record shows
What the NTSB files show
NTSB LAX01FA199 (2001, FATAL): A Piper PA-28-180 student pilot on a solo instructional flight selected a downwind takeoff runway and stalled during initial climb at low altitude, striking trees. The accident was attributed to inadequate airspeed management and a downwind takeoff, with contributing factors including partial engine power loss from an inoperative right magneto and high density altitude. The probable cause was the pilot's failure to maintain airspeed and his inadvertent stall during takeoff initial climb.
NTSB ANC90LA112 (1990, FATAL): A heavily loaded Piper PA-28 crashed into trees approximately 40 seconds after takeoff from a closed dirt strip after encountering a downdraft. The accident resulted from the aircraft's inability to overcome the downdraft with available power, compounded by heavy loading and engine degradation from improper maintenance. The probable cause was the airplane's encounter with a downdraft from which it could not recover with available power.
NTSB WPR21LA020 (2020): A Piper PA-28-180 experienced partial loss of engine power during cruise flight due to a stuck exhaust valve on the No. 4 cylinder. The pilot declared an emergency and made a forced landing to a highway, during which the right wing struck a barbed wire fence. The probable cause was partial loss of engine power due to failure of the No. 4 cylinder exhaust valve.
NTSB WPR13LA366 (2013): A Piper PA-28-180 lost partial engine power during takeoff and made a forced landing beyond the runway departure end. The accident resulted from separation of exhaust muffler baffling that partially blocked airflow, with contributing factors including inadequate maintenance of the exhaust system.
The real accidents cited above occurred at other airports and in other aircraft — NOT at Tampa International Airport. KTPA has its own accident history (see field dominant patterns: forced landing 22.2%, loss of control inflight 11.1%, loss of control ground 8.9%), but these specific events happened elsewhere. The scenario is localized to KTPA Runway 10 to make the off-field environment real and consequential for you as a student here.
The consistent thread across all these events: partial engine power loss in the PA-28-180 is insidious. It builds gradually, the first symptom is a dropping tachometer and reduced rate of climb (not a dramatic power cut), and by the time it is obvious, it may be too late for a comfortable recovery. The causes are varied — carburetor ice, magneto failure, exhaust system blockage, maintenance shortcuts — but the response is always the same: recognize the power loss early, apply immediate corrective action (carb heat, mixture adjustment, mag check), and if power does not restore, commit to the best available forced-landing site immediately rather than attempting to stretch the glide over unsuitable terrain.
Off Runway 10 at KTPA, the off-field environment is dense development with no suitable forced-landing site. A power loss on that departure at low altitude is a low-margin emergency with few options. The decision window is measured in seconds — not minutes.
Key lesson — In warm, humid Florida air at high density altitude, the PA-28-180's carbureted Lycoming O-360 can accumulate serious carburetor ice even at cruise power and above-freezing temperatures. Apply full carburetor heat proactively on initial climb in conducive conditions. At low altitude over unsuitable terrain, the decision window is measured in seconds — not minutes. Off Runway 10 at KTPA, the off-field environment is dense development: a delayed response means a forced landing in a parking lot or a park, not a field landing. Commit early to the best available site.
Debrief — teaching points
Partial engine power loss in the PA-28-180 is insidious — it builds gradually.
The Lycoming O-360 in the PA-28-180 can lose power from carburetor ice, magneto failure, exhaust system blockage, or mixture control error. The first symptom is always subtle: a dropping tachometer and a reduced rate of climb. There is no dramatic bang, no vibration, no obvious failure. Pilots who are not actively monitoring the tachometer and rate of climb miss the early warning. By the time the power loss is obvious, significant degradation has occurred. Scan the tachometer and vertical speed indicator as part of your regular instrument scan, especially on initial climb in conducive conditions.
Carburetor heat on initial climb in warm, humid conditions is a proactive defense.
The PA-28-180's carbureted O-360 is susceptible to carburetor ice formation in the temperature range of roughly 15–30°C with high relative humidity. Florida summer conditions — 32°C OAT, 26°C dew point — are conducive to serious icing at reduced power. Applying carburetor heat during the climb in these conditions, before any symptom appears, is the correct proactive defense. Yes, carb heat reduces engine efficiency slightly, but the trade-off is worth it. If ice has already formed and the engine is rough, apply full carb heat immediately and expect an initial RPM drop as the heat melts the ice — that drop is expected and normal.
A preflight magneto check can miss a magneto that is failing under load.
The preflight magneto check is conducted at idle (600–700 RPM) and at 1,000 RPM. A magneto that is failing intermittently or only under full-power load may pass the preflight check and then fail on initial climb when the engine is at high power. If you suspect magneto failure (rough running, uneven power, one mag check significantly worse than the other), reduce power, apply carburetor heat, and return to the airport for a maintenance inspection. Do not continue the flight with a suspect magneto.
The PA-28-180 fuel selector is LEFT / RIGHT with NO BOTH position — active tank management is required.
Unlike Cessnas, the PA-28-180 has no BOTH position. The pilot must actively switch tanks during flight. Running a selected tank dry — or taking off on a near-empty tank — is the signature starvation trap. Establish a tank-switching protocol: switch to the right tank at 500 ft AGL on departure, alternate tanks every 30 minutes in cruise, and always confirm the fuel selector position during the pre-takeoff check. If you suspect fuel starvation (engine roughness, power loss, no improvement with carb heat or mixture adjustment), switch tanks immediately and return to the airport.
At KTPA Runway 10, the off-field environment is dense development — there is no suitable forced-landing site.
The off-field environment off Runway 10's departure end (heading 092°) is dense commercial and residential development, parks/parking lots, and scattered wooded wetland. There is no open field, no road, no water. The USGS NLCD classification is MARGINAL — the best you can hope for is a parking lot or a park. A power loss on the Runway 10 departure at low altitude is a low-margin emergency. Recognize the power loss early, apply immediate corrective action, and if power does not restore, commit to the best available forced-landing site immediately rather than attempting to stretch the glide back to the runway. A controlled forced landing in a parking lot is survivable; a stall/spin attempt to make the runway is not.
Best glide in the PA-28-180 is 65 KIAS — establish it immediately if power is lost.
Best glide speed for the PA-28-180 is 65 KIAS. This speed maximizes glide distance and gives the most time and distance to manage the emergency. At 400 ft AGL over unsuitable terrain, establishing 65 KIAS immediately maximizes your options — whether that means reaching the airport or setting up the best possible forced landing. Do not attempt to maintain climb speed (74 KIAS Vy) or angle-of-climb speed (64 KIAS Vx) if power is lost; those speeds will not give you the glide distance you need.
Built from the real accident record
Scenario built from NTSB LAX01FA199 (2001 PA-28-180 partial power loss / stall on initial climb), ANC90LA112 (1990 PA-28-180 downdraft / power loss), WPR21LA020 (2020 PA-28-180 partial power loss cruise), WPR13LA366 (2013 PA-28-180 exhaust baffling / power loss takeoff), and regional precedents MIA91LA128, CHI92DER01, CHI92DEM03, CHI89DEM10. Real events occurred at other airports and aircraft — NOT at Tampa International. Localized to KTPA Runway 10 departure environment.
NTSB reports: LAX01FA199 · ANC90LA112 · WPR21LA020 · WPR13LA366 · MIA91LA128 · CHI92DER01 · CHI92DEM03 · CHI89DEM10
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 · PA.II.C — Takeoff and Climb
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.
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