sakharamg/AviationCorpus · Datasets at Hugging Face

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His multiengine training had begun 3 days before the accident, and he had accrued 1.5 hours of multiengine experience, all of which was in the accident airplane.
AIRCRAFT INFORMATION According to FAA airworthiness records, the airplane was manufactured in 1963 and was powered by Lycoming O-540-A1D5, 250-horsepower engines.
Its most recent annual inspection was completed March 5, 2021, at 6,866.16 total aircraft hours.
After the accident, statements were provided by pilots who had flown, or attempted to fly, the accident airplane during the week before the accident.
They each described the left engine either stopping or running roughly both on the ground and in the air with the fuel selector in the left inboard tank position.
When the fuel selector was moved to the left outboard tank position, the engine could be restarted, or smooth, continuous operation would be restored.
Each said that these power-loss events were reported to maintenance for correction.
On April 2, 2021, a flight instructor could not start or sustain power on the left engine with the inboard tank selected but started and ran the engine continuously on the outboard tank.
He then demonstrated the discrepancy to company maintenance personnel before he rejected the airplane for his scheduled flight.
According to the Owner’s Handbook, the airplane’s take off run was 750 ft and 1,100 ft over a 50-ft barrier.
There was no accelerate/stop distance published, but the published landing roll was 900 ft.WRECKAGE AND IMPACT INFORMATION The airplane was examined and photographed by two FAA aviation safety inspectors.
Examination of the photographs revealed that the cockpit and cabin areas were destroyed by impact and came to rest inverted.
The wings were mostly separated, but remained attached by cabling and sheet metal.
The engines were in their nacelles, and the propeller blades of the left engine appeared undamaged and in what approximated a feathered position.
The propeller blades of the right engine displayed similar twisting, bending, leading edge gouging, chordwise scratching, and tip curling.
The wreckage was recovered from the accident site for further examination.
Control continuity was confirmed from the flight controls, through several breaks, to the flight control surfaces.
All breaks and fractures displayed features consistent with overstress.
The right wing fuel tank appeared intact, the thermos-style fuel cap was secure in its receptacle, and the tank contained about 15 to 20 gallons of fuel.
The fuel pick-up was clear of obstruction and its filter screen was intact.
The right side gascolator contained debris, and the filter screen was obstructed with rust and other materials.
No fuel was noted in the left gascolator, its filter screen was not installed; and the gascolator securement was not safety wired.
Examination of the aluminum gascolator bowl revealed deep, corrosive pitting.
The pitted areas displayed fresh scribe marks consistent with recent cleaning of oxidized material from the pitted areas.
The left wing inboard fuel tank was breached, contained trace amounts of fuel, and the thermos-style fuel cap fit loosely in its fuel port.
Once removed, the ribbed, expandable rubber gasket of the cap was uniformly coated with a white, adhesive residue.
A 12-inch length of white adhesive duct tape was observed loose inside the tank.
Once removed, the adhesive side of the tape revealed a rubbery residue consistent with that of the fuel cap gasket.
The adhesive-coated area of the rubber gasket matched the dimension of the tape strip.
The fuel pickup was clear of obstruction, but its filter screen was not installed.
Fuel system continuity was confirmed visually and with low-pressure compressed air.
The right engine propeller remained attached to the crankshaft flange.
The spark plugs and valve rocker covers were removed, and the engine crankshaft was rotated by turning the propeller.
Continuity of the crankshaft to the rear gears and to the valve train was observed.
Compression and suction were observed from all six cylinders.
The interiors of the cylinders were observed using a lighted borescope and no anomalies observed.
Both magnetos remained attached to the engine.
No damage was noted and both produced spark from all ignition towers when rotated by hand.
The carburetor displayed impact damage to control arms and cabling, and disassembly revealed trace amounts of fuel and no damage to brass floats or other internal components.
The fuel pump operated when actuated by hand.
A cursory examination of the left engine was performed prior to shipment for a test run at the manufacturer’s facility.
The spark plugs and valve rocker covers were removed, and the engine crankshaft was rotated.
Continuity of the crankshaft to the rear gears and to the valve train was observed.
Compression and suction were observed from all six cylinders.
The interiors of the cylinders were observed using a lighted borescope and no anomalies observed.
The oil suction screen was removed, and no debris observed.
The oil pressure screen was removed and about ¼ teaspoon of particulate matter observed in the screen.
Some of the matter could be attracted to a magnet.
The particulate matter was bagged and left to be shipped to the manufacturer along with the engine.
The propeller was removed.
The oil suction screen, oil pressure screen, rocker covers, and spark plugs were reinstalled, and the engine set aside for shipment.
Due to the metal contamination, disassembly was performed instead of the engine test run.
Removal of the Nos.
2, 4, and 6 cylinders revealed the Nos.
1 and 2 intake tappets and the No.
3 exhaust tappet were spalled.
The Nos.
1 and 2 intake lobes and the No.
3 exhaust lobe of the camshaft were severely spalled.
Both magnetos remained attached to the engine.
No damage was noted and both produced spark from all ignition towers when rotated by hand.
The carburetor displayed impact damage to control arms and cabling, and disassembly revealed trace amounts of fuel and no damage to brass floats or other internal components.
The fuel pump operated when actuated by hand.
ADDITIONAL INFORMATION The most recent engine field overhauls were completed on 12/09/1997, more than 23 years before the date of the accident.
Lycoming Service Instruction No.
1009BE stated: All engine models are to be overhauled within twelve (12) calendar years of the date they first entered service or of last overhaul.
This calendar year time period TBO is to mitigate engine deterioration that occurs with age, including corrosion of metallic components and degradation of non-metallic components such as gaskets, seals, flexible hoses and fuel pump diaphragms.
CAUTION CALENDAR YEAR TBO IS BASED ON ACCELERATED TESTING AND OVERALL FLEET SERVICE DATA.
LOCAL CLIMATE CONDITIONS, STORAGE CONDITIONS, FREQUENT EXTENDED PERIODS OF INACTIVITY, PRESERVATION TECHNIQUES USED DURING INACTIVE PERIODS, AND FREQUENCY OF OIL CHANGES CAN AFFECT CORROSION OF METALS AND DEGRADATION OF NON-METALS.
For FAA Part 91 or EASA Part NCO (non-commercial) or equivalent operations, only an appropriately rated and qualified maintenance person (or international equivalent) can allow the twelve (12) calendar year TBO to be exceeded with concurrence from the controlling civil aviation authority to verify agreement with this provision and after thoroughly examining the engine for corrosion and degradation in accordance with 14 CFR 43 Appendix D (or international equivalent) and determining that the engine remains in an airworthy condition.
This inspection is to be repeated annually or as necessary to ensure continued airworthiness.
The twelve (12) calendar year TBO must not be exceeded if the engine is affected by AD 2012-19-01 and not in compliance with AD 2012-19-01.
Damage and impact signatures to the left propeller were consistent with the left propeller at or near the feathered position, with no power and little or no rotation at impact.
The left propeller governor appeared intact and undamaged.
It was bench tested and met all factory specifications except for the low rpm setting, which did not prevent normal operation.
There were no discrepancies noted on the propeller components examined that would have prevented normal operation.
The most recent propeller overhauls were performed December 13, 1999.
According to Hartzell Propeller, Inc.
Service Letter HC-SL-61-61Y, the overhaul periods and service life limits for this propeller installation was 2000 flight hours or 60 calendar months.
Airframe examination revealed that the position of the main and nose landing gear, and their respective actuators were consistent with the gear in the “down” position.
The landing gear handle was in the “down” position.
The Airplane Flying Handbook (FAA-H-8083-3C), Chapter 6: Takeoffs and Departure Climbs, Rejected Takeoff/Engine Failure: Prior to takeoff, the pilot should identify a point along the runway at which the airplane should be airborne.
If that point is reached and the airplane is not airborne, immediate action should be taken to discontinue the takeoff.
When properly planned and executed, the airplane can be stopped on the remaining runway without using extraordinary measures, such as excessive braking that may result in loss of directional control, airplane damage, and/or personal injury.
The POH/AFM ground roll distances for take-off and landing added together provide a good estimate of the total runway needed to accelerate and then stop.
Vmc (velocity – minimum controllable) was previously defined in 14 CFR part 23, section 23.149 as the calibrated airspeed at which, when the critical engine is suddenly made inoperative, it is possible to maintain control of the airplane with that engine still inoperative, and thereafter maintain straight flight at the same speed with an angle of bank of not more than 5 degrees.
This definition still applies to airplanes certified under that regulation.
There is no requirement under either determination that the airplane be capable of climbing at this airspeed.
VMC only addresses directional control.
Flying Light Twins Safely (FAA-P-8740-66), Minimum Control Speed: Loss of directional control may be experienced at speeds almost 20 knots above published Vmc when the wings are held level.
Flight test pilots’ determination of Vmc in airplane certification is solely concerned with the minimum speed for directional control under one very specific set of circumstances.
Vmc has nothing to do with climb performance, nor is it the optimum airplane attitude, bank angle, ball position, or configuration for best climb performance.
Many light twins will not maintain level flight near Vmc with OEI (one engine inoperative).
The student pilot said that he was too fast and had touched down too long on the runway when he realized the airplane would not be able to stop in the distance remaining.
He applied full power to go around and the airplane became airborne at the end of the runway with an airspeed of about 55 knots.
The airplane's wing struck trees at the airport boundary, causing the pilot to lose directional control.
The airplane continued about 300 feet to the left of the runway centerline before impacting terrain and other obstructions and coming to rest in the back yard of a residence.
There was an immediate postimpact fire.
The National Transportation Safety Board determines the probable cause(s) of this accident to be:The student pilot’s delayed decision to execute a go-around.
The pilot was conducting a local sightseeing flight at the time of the accident.

His multiengine training had begun 3 days before the accident, and he had accrued 1.5 hours of multiengine experience, all of which was in the accident airplane.

AIRCRAFT INFORMATION According to FAA airworthiness records, the airplane was manufactured in 1963 and was powered by Lycoming O-540-A1D5, 250-horsepower engines.

Its most recent annual inspection was completed March 5, 2021, at 6,866.16 total aircraft hours.

After the accident, statements were provided by pilots who had flown, or attempted to fly, the accident airplane during the week before the accident.

They each described the left engine either stopping or running roughly both on the ground and in the air with the fuel selector in the left inboard tank position.

When the fuel selector was moved to the left outboard tank position, the engine could be restarted, or smooth, continuous operation would be restored.

Each said that these power-loss events were reported to maintenance for correction.

On April 2, 2021, a flight instructor could not start or sustain power on the left engine with the inboard tank selected but started and ran the engine continuously on the outboard tank.

He then demonstrated the discrepancy to company maintenance personnel before he rejected the airplane for his scheduled flight.

According to the Owner’s Handbook, the airplane’s take off run was 750 ft and 1,100 ft over a 50-ft barrier.

There was no accelerate/stop distance published, but the published landing roll was 900 ft.WRECKAGE AND IMPACT INFORMATION The airplane was examined and photographed by two FAA aviation safety inspectors.

Examination of the photographs revealed that the cockpit and cabin areas were destroyed by impact and came to rest inverted.

The wings were mostly separated, but remained attached by cabling and sheet metal.

The engines were in their nacelles, and the propeller blades of the left engine appeared undamaged and in what approximated a feathered position.

The propeller blades of the right engine displayed similar twisting, bending, leading edge gouging, chordwise scratching, and tip curling.

The wreckage was recovered from the accident site for further examination.

Control continuity was confirmed from the flight controls, through several breaks, to the flight control surfaces.

All breaks and fractures displayed features consistent with overstress.

The right wing fuel tank appeared intact, the thermos-style fuel cap was secure in its receptacle, and the tank contained about 15 to 20 gallons of fuel.

The fuel pick-up was clear of obstruction and its filter screen was intact.

The right side gascolator contained debris, and the filter screen was obstructed with rust and other materials.

No fuel was noted in the left gascolator, its filter screen was not installed; and the gascolator securement was not safety wired.

Examination of the aluminum gascolator bowl revealed deep, corrosive pitting.

The pitted areas displayed fresh scribe marks consistent with recent cleaning of oxidized material from the pitted areas.

The left wing inboard fuel tank was breached, contained trace amounts of fuel, and the thermos-style fuel cap fit loosely in its fuel port.

Once removed, the ribbed, expandable rubber gasket of the cap was uniformly coated with a white, adhesive residue.

A 12-inch length of white adhesive duct tape was observed loose inside the tank.

Once removed, the adhesive side of the tape revealed a rubbery residue consistent with that of the fuel cap gasket.

The adhesive-coated area of the rubber gasket matched the dimension of the tape strip.

The fuel pickup was clear of obstruction, but its filter screen was not installed.

Fuel system continuity was confirmed visually and with low-pressure compressed air.

The right engine propeller remained attached to the crankshaft flange.

The spark plugs and valve rocker covers were removed, and the engine crankshaft was rotated by turning the propeller.

Continuity of the crankshaft to the rear gears and to the valve train was observed.

Compression and suction were observed from all six cylinders.

The interiors of the cylinders were observed using a lighted borescope and no anomalies observed.

Both magnetos remained attached to the engine.

No damage was noted and both produced spark from all ignition towers when rotated by hand.

The carburetor displayed impact damage to control arms and cabling, and disassembly revealed trace amounts of fuel and no damage to brass floats or other internal components.

The fuel pump operated when actuated by hand.

A cursory examination of the left engine was performed prior to shipment for a test run at the manufacturer’s facility.

The spark plugs and valve rocker covers were removed, and the engine crankshaft was rotated.

Continuity of the crankshaft to the rear gears and to the valve train was observed.

Compression and suction were observed from all six cylinders.

The interiors of the cylinders were observed using a lighted borescope and no anomalies observed.

The oil suction screen was removed, and no debris observed.

The oil pressure screen was removed and about ¼ teaspoon of particulate matter observed in the screen.

Some of the matter could be attracted to a magnet.

The particulate matter was bagged and left to be shipped to the manufacturer along with the engine.

The propeller was removed.

The oil suction screen, oil pressure screen, rocker covers, and spark plugs were reinstalled, and the engine set aside for shipment.

Due to the metal contamination, disassembly was performed instead of the engine test run.

Removal of the Nos.

2, 4, and 6 cylinders revealed the Nos.

1 and 2 intake tappets and the No.

3 exhaust tappet were spalled.

The Nos.

1 and 2 intake lobes and the No.

3 exhaust lobe of the camshaft were severely spalled.

Both magnetos remained attached to the engine.

No damage was noted and both produced spark from all ignition towers when rotated by hand.

The carburetor displayed impact damage to control arms and cabling, and disassembly revealed trace amounts of fuel and no damage to brass floats or other internal components.

The fuel pump operated when actuated by hand.

ADDITIONAL INFORMATION The most recent engine field overhauls were completed on 12/09/1997, more than 23 years before the date of the accident.

Lycoming Service Instruction No.

1009BE stated: All engine models are to be overhauled within twelve (12) calendar years of the date they first entered service or of last overhaul.

This calendar year time period TBO is to mitigate engine deterioration that occurs with age, including corrosion of metallic components and degradation of non-metallic components such as gaskets, seals, flexible hoses and fuel pump diaphragms.

CAUTION CALENDAR YEAR TBO IS BASED ON ACCELERATED TESTING AND OVERALL FLEET SERVICE DATA.

LOCAL CLIMATE CONDITIONS, STORAGE CONDITIONS, FREQUENT EXTENDED PERIODS OF INACTIVITY, PRESERVATION TECHNIQUES USED DURING INACTIVE PERIODS, AND FREQUENCY OF OIL CHANGES CAN AFFECT CORROSION OF METALS AND DEGRADATION OF NON-METALS.

For FAA Part 91 or EASA Part NCO (non-commercial) or equivalent operations, only an appropriately rated and qualified maintenance person (or international equivalent) can allow the twelve (12) calendar year TBO to be exceeded with concurrence from the controlling civil aviation authority to verify agreement with this provision and after thoroughly examining the engine for corrosion and degradation in accordance with 14 CFR 43 Appendix D (or international equivalent) and determining that the engine remains in an airworthy condition.

This inspection is to be repeated annually or as necessary to ensure continued airworthiness.

The twelve (12) calendar year TBO must not be exceeded if the engine is affected by AD 2012-19-01 and not in compliance with AD 2012-19-01.

Damage and impact signatures to the left propeller were consistent with the left propeller at or near the feathered position, with no power and little or no rotation at impact.

The left propeller governor appeared intact and undamaged.

It was bench tested and met all factory specifications except for the low rpm setting, which did not prevent normal operation.

There were no discrepancies noted on the propeller components examined that would have prevented normal operation.

The most recent propeller overhauls were performed December 13, 1999.

According to Hartzell Propeller, Inc.

Service Letter HC-SL-61-61Y, the overhaul periods and service life limits for this propeller installation was 2000 flight hours or 60 calendar months.

Airframe examination revealed that the position of the main and nose landing gear, and their respective actuators were consistent with the gear in the “down” position.

The landing gear handle was in the “down” position.

The Airplane Flying Handbook (FAA-H-8083-3C), Chapter 6: Takeoffs and Departure Climbs, Rejected Takeoff/Engine Failure: Prior to takeoff, the pilot should identify a point along the runway at which the airplane should be airborne.

If that point is reached and the airplane is not airborne, immediate action should be taken to discontinue the takeoff.

When properly planned and executed, the airplane can be stopped on the remaining runway without using extraordinary measures, such as excessive braking that may result in loss of directional control, airplane damage, and/or personal injury.

The POH/AFM ground roll distances for take-off and landing added together provide a good estimate of the total runway needed to accelerate and then stop.

Vmc (velocity – minimum controllable) was previously defined in 14 CFR part 23, section 23.149 as the calibrated airspeed at which, when the critical engine is suddenly made inoperative, it is possible to maintain control of the airplane with that engine still inoperative, and thereafter maintain straight flight at the same speed with an angle of bank of not more than 5 degrees.

This definition still applies to airplanes certified under that regulation.

There is no requirement under either determination that the airplane be capable of climbing at this airspeed.

VMC only addresses directional control.

Flying Light Twins Safely (FAA-P-8740-66), Minimum Control Speed: Loss of directional control may be experienced at speeds almost 20 knots above published Vmc when the wings are held level.

Flight test pilots’ determination of Vmc in airplane certification is solely concerned with the minimum speed for directional control under one very specific set of circumstances.

Vmc has nothing to do with climb performance, nor is it the optimum airplane attitude, bank angle, ball position, or configuration for best climb performance.

Many light twins will not maintain level flight near Vmc with OEI (one engine inoperative).

The student pilot said that he was too fast and had touched down too long on the runway when he realized the airplane would not be able to stop in the distance remaining.

He applied full power to go around and the airplane became airborne at the end of the runway with an airspeed of about 55 knots.

The airplane's wing struck trees at the airport boundary, causing the pilot to lose directional control.

The airplane continued about 300 feet to the left of the runway centerline before impacting terrain and other obstructions and coming to rest in the back yard of a residence.

There was an immediate postimpact fire.

The National Transportation Safety Board determines the probable cause(s) of this accident to be:The student pilot’s delayed decision to execute a go-around.

The pilot was conducting a local sightseeing flight at the time of the accident.