Additional Participating Entities:
Federal Aviation Administration / Flight Standards District Office; Nashville, Tennessee
Lycoming Engines; Atlanta, Georgia
Aviation Accident Final Report - National Transportation Safety Board: https://app.ntsb.gov/pdf
Investigation Docket - National Transportation Safety Board: https://dms.ntsb.gov/pubdms
Aviation Accident Data Summary - National Transportation Safety Board: https://app.ntsb.gov/pdf
http://registry.faa.gov/N1299J
Location: Dayton, TN
Accident Number: ERA16LA226
Date & Time: 06/20/2016, 1240 EDT
Registration: N1299J
Aircraft: ROCKWELL INTERNATIONAL 112A
Aircraft Damage: Substantial
Defining Event:
Injuries: 1 Serious
Flight Conducted Under: Part 91: General Aviation - Personal
Analysis
While en route, about 5,500 ft mean sea level, the private pilot heard a "pop," followed by a total loss of engine power. He unsuccessfully attempted to restart the engine, and then he chose to land in a field. During the forced landing, the airplane impacted trees and the ground, which resulted in substantial damage to the fuselage, wings, and empennage.
Postaccident examination of the engine revealed that the engine-driven fuel pump was nonfunctional. Metallurgical examination of the fuel pump revealed that it had failed internally; however, the reason for the failure could not be determined due to all the observed damage caused by the failure.
Probable Cause and Findings
The National Transportation Safety Board determines the probable cause(s) of this accident to be:
A total loss of engine power due to the failure of the engine-driven fuel pump.
Findings
Aircraft
Fuel pumps - Failure (Cause)
Environmental issues
Tree(s) - Contributed to outcome
Factual Information
On June 20, 2016, about 1240 eastern daylight time, a Rockwell International 112A, N1299J, impacted trees during a forced landing following a total loss of engine power near Dayton, Tennessee. The private pilot was the only occupant and received serious injuries. Visual meteorological conditions prevailed and no flight plan was filed for the personal flight. The flight was conducted under the provisions of Title 14 Code of Federal Regulations Part 91. The flight originated from Whiteside County Airport – Jos H Bittorf Field (SQI), Rock Falls, Illinois, with an intended destination of Pickens County Airport (JZP), Jasper, Georgia.
In an interview with a Federal Aviation Administration (FAA) inspector, the pilot stated that while en route, about 5,500 feet mean sea level, he heard a "pop" and the engine lost total power. He unsuccessfully attempted to restart the engine twice, and then he elected to land in a field. During the forced landing, the airplane impacted trees and subsequently the ground, which resulted in substantial damage to the fuselage, wings, and empennage.
A postaccident examination by a FAA Inspector revealed that the wings, rudder, and horizontal stabilizer had separated from the fuselage. The engine remained attached to the fuselage and the propeller remained attached to the engine. Two of the three propeller blades were bent aft and the third blade was bent forward. Furthermore, an odor similar to aviation fuel was noted on scene.
According to FAA records, the airplane was issued an airworthiness certificate on 1975, and registered to the corporation in 2003. It was equipped with a Lycoming IO-360-C1D6, a 180-hp, engine. According to the airframe maintenance logbook, the most recent annual inspection was performed on August 5, 2015, at a total time of 3,958.3 hours. At the time of the accident, the airplane had accumulated 4,046.7 total hours.
The engine remained attached to the firewall through the engine mounts. It was partially disassembled to facilitate examination. The propeller rotated without anomaly and crankshaft continuity was confirmed to the accessory section of the engine. Compression and suction was confirmed from all cylinders. The interior of each cylinders was examined with no anomalies noted. The fuel servo was partially impact damaged, the fuel servo throttle arm was in the full throttle position, and the servo mixture control arm was in a full rich position. The servo fuel inlet screen was removed and unobstructed. The fuel flow divider remained attached to the engine, no damaged was noted, was disassembled, and the fuel diaphragm was intact with no debris noted. The fuel injector nozzles were removed and were unobstructed. The engine-driven fuel pump remained attached to the engine and was removed for further examination. When the engine-driven fuel pump was placed in a bucket of water and operated by hand, no water was expelled from the outlet port.
The engine was equipped with an Aero Accessories engine-driven fuel pump with the Part No. AF-15473. It was manufactured in 2011 and installed on the engine during an overhaul on March 8, 2011. At the time of the accident, it had accumulated 438.6 hours of total time. According to the manufacturer, it was to be overhauled every 12 years or 2,000 hours, whichever came first. The engine-driven fuel pump was further examined at the manufacturing facility under federal oversight. Visual inspection of the exterior revealed that the lower panel that covered the bottom of the pump was impact damaged. The mechanical fuel pump arm exhibited wear in the area that contacted the engine and no anomalies were noted. The engine-driven fuel pump was mounted on a flow test bench, however, it would not flow. Further disassembly revealed that the stamp ring attached to the top of the diaphragm actuator rod of the fuel pump was deformed. In addition, the fiber spacer or washer were not located. As a result of the deformation, where the actuator met the diaphragm lift stem, the engine-driven fuel pump was unable to actuate the diaphragm element and pump fluid.
The engine-driven fuel pump was sent to the NTSB Materials Laboratory for further examination. The examination revealed that the actuator fracture was generally circular in orientation, was slanted, and had indications of localized plastic deformation adjacent to the facture surface. The retainer section, that had separated from the stamp ring but remained attached to the actuator, exhibited damage to parts of the fracture surface and was smeared, consistent with post fracture contact with the adjacent components. The undamaged areas exhibited river patterns and chevron marks. In addition, the areas not damaged were examined with a scanning electron microscope, and exhibited dimple rupture, which is consistent with an overstress fracture.
The airplane was equipped with a J. P. Instruments EDM-800, which was panel mounted and recorded up to 24 parameters related to engine operations. The unit contained non-volatile memory for data storage of the parameters recorded and calculated. The data extracted included the accident flight starting 09:38:54 and ending 12:51:47 on June 20, 2016. The data indicated that just after 1251, the fuel flow decreased to zero and the EGT and CHT values decreased as well.
History of Flight
Enroute
Powerplant sys/comp malf/fail
Loss of engine power (total)
Attempted remediation/recovery
Landing
Off-field or emergency landing
Collision with terr/obj (non-CFIT)
Pilot Information
Certificate: Private
Age: 71, Male
Airplane Rating(s): Single-engine Land; Single-engine Sea
Seat Occupied: Left
Other Aircraft Rating(s): None
Restraint Used: Unknown
Instrument Rating(s): None
Second Pilot Present: No
Instructor Rating(s): None
Toxicology Performed: No
Medical Certification: Class 3 Without Waivers/Limitations
Last FAA Medical Exam: 08/01/2014
Occupational Pilot: No
Last Flight Review or Equivalent:
Flight Time: 1913.7 hours (Total, all aircraft), 1756.6 hours (Pilot In Command, all aircraft), 8.6 hours (Last 90 days, all aircraft)
Aircraft and Owner/Operator Information
Aircraft Make: ROCKWELL INTERNATIONAL
Registration: N1299J
Model/Series: 112A A
Aircraft Category: Airplane
Year of Manufacture: 1975
Amateur Built: No
Airworthiness Certificate: Normal
Serial Number: 299
Landing Gear Type: Retractable - Tricycle
Seats: 4
Date/Type of Last Inspection: 08/05/2015, Annual
Certified Max Gross Wt.: 2950 lbs
Time Since Last Inspection: 88 Hours
Engines: 1 Reciprocating
Airframe Total Time: 4046.7 Hours at time of accident
Engine Manufacturer: LYCOMING
ELT: C91A installed, not activated
Engine Model/Series: IO-360-C1D6
Registered Owner: JKM ENTERPRISES INC
Rated Power: 180 hp
Operator: JKM ENTERPRISES INC
Operating Certificate(s) Held: None
Meteorological Information and Flight Plan
Conditions at Accident Site: Visual Conditions
Condition of Light: Day
Observation Facility, Elevation: CSV, 1870 ft msl
Distance from Accident Site: 26 Nautical Miles
Observation Time: 1253 EDT
Direction from Accident Site: 1°
Lowest Cloud Condition: Clear
Visibility: 10 Miles
Lowest Ceiling: None
Visibility (RVR):
Wind Speed/Gusts: 5 knots /
Turbulence Type Forecast/Actual: /
Wind Direction: 340°
Turbulence Severity Forecast/Actual: /
Altimeter Setting: 30.36 inches Hg
Temperature/Dew Point: 26°C / 13°C
Precipitation and Obscuration: No Obscuration; No Precipitation
Departure Point: STERLING/ROCKFALLS, IL (SQI)
Type of Flight Plan Filed: None
Destination: JASPER, GA (JZP)
Type of Clearance: Unknown
Departure Time:
Type of Airspace:
Wreckage and Impact Information
Crew Injuries: 1 Serious
Aircraft Damage: Substantial
Passenger Injuries: N/A
Aircraft Fire: None
Ground Injuries: N/A
Aircraft Explosion: None
Total Injuries: 1 Serious
Latitude, Longitude: 35.523611, -85.091944 (est)
Accident Number: ERA16LA226
Date & Time: 06/20/2016, 1240 EDT
Registration: N1299J
Aircraft: ROCKWELL INTERNATIONAL 112A
Aircraft Damage: Substantial
Defining Event:
Injuries: 1 Serious
Flight Conducted Under: Part 91: General Aviation - Personal
Analysis
While en route, about 5,500 ft mean sea level, the private pilot heard a "pop," followed by a total loss of engine power. He unsuccessfully attempted to restart the engine, and then he chose to land in a field. During the forced landing, the airplane impacted trees and the ground, which resulted in substantial damage to the fuselage, wings, and empennage.
Postaccident examination of the engine revealed that the engine-driven fuel pump was nonfunctional. Metallurgical examination of the fuel pump revealed that it had failed internally; however, the reason for the failure could not be determined due to all the observed damage caused by the failure.
Probable Cause and Findings
The National Transportation Safety Board determines the probable cause(s) of this accident to be:
A total loss of engine power due to the failure of the engine-driven fuel pump.
Findings
Aircraft
Fuel pumps - Failure (Cause)
Environmental issues
Tree(s) - Contributed to outcome
Factual Information
On June 20, 2016, about 1240 eastern daylight time, a Rockwell International 112A, N1299J, impacted trees during a forced landing following a total loss of engine power near Dayton, Tennessee. The private pilot was the only occupant and received serious injuries. Visual meteorological conditions prevailed and no flight plan was filed for the personal flight. The flight was conducted under the provisions of Title 14 Code of Federal Regulations Part 91. The flight originated from Whiteside County Airport – Jos H Bittorf Field (SQI), Rock Falls, Illinois, with an intended destination of Pickens County Airport (JZP), Jasper, Georgia.
In an interview with a Federal Aviation Administration (FAA) inspector, the pilot stated that while en route, about 5,500 feet mean sea level, he heard a "pop" and the engine lost total power. He unsuccessfully attempted to restart the engine twice, and then he elected to land in a field. During the forced landing, the airplane impacted trees and subsequently the ground, which resulted in substantial damage to the fuselage, wings, and empennage.
A postaccident examination by a FAA Inspector revealed that the wings, rudder, and horizontal stabilizer had separated from the fuselage. The engine remained attached to the fuselage and the propeller remained attached to the engine. Two of the three propeller blades were bent aft and the third blade was bent forward. Furthermore, an odor similar to aviation fuel was noted on scene.
According to FAA records, the airplane was issued an airworthiness certificate on 1975, and registered to the corporation in 2003. It was equipped with a Lycoming IO-360-C1D6, a 180-hp, engine. According to the airframe maintenance logbook, the most recent annual inspection was performed on August 5, 2015, at a total time of 3,958.3 hours. At the time of the accident, the airplane had accumulated 4,046.7 total hours.
The engine remained attached to the firewall through the engine mounts. It was partially disassembled to facilitate examination. The propeller rotated without anomaly and crankshaft continuity was confirmed to the accessory section of the engine. Compression and suction was confirmed from all cylinders. The interior of each cylinders was examined with no anomalies noted. The fuel servo was partially impact damaged, the fuel servo throttle arm was in the full throttle position, and the servo mixture control arm was in a full rich position. The servo fuel inlet screen was removed and unobstructed. The fuel flow divider remained attached to the engine, no damaged was noted, was disassembled, and the fuel diaphragm was intact with no debris noted. The fuel injector nozzles were removed and were unobstructed. The engine-driven fuel pump remained attached to the engine and was removed for further examination. When the engine-driven fuel pump was placed in a bucket of water and operated by hand, no water was expelled from the outlet port.
The engine was equipped with an Aero Accessories engine-driven fuel pump with the Part No. AF-15473. It was manufactured in 2011 and installed on the engine during an overhaul on March 8, 2011. At the time of the accident, it had accumulated 438.6 hours of total time. According to the manufacturer, it was to be overhauled every 12 years or 2,000 hours, whichever came first. The engine-driven fuel pump was further examined at the manufacturing facility under federal oversight. Visual inspection of the exterior revealed that the lower panel that covered the bottom of the pump was impact damaged. The mechanical fuel pump arm exhibited wear in the area that contacted the engine and no anomalies were noted. The engine-driven fuel pump was mounted on a flow test bench, however, it would not flow. Further disassembly revealed that the stamp ring attached to the top of the diaphragm actuator rod of the fuel pump was deformed. In addition, the fiber spacer or washer were not located. As a result of the deformation, where the actuator met the diaphragm lift stem, the engine-driven fuel pump was unable to actuate the diaphragm element and pump fluid.
The engine-driven fuel pump was sent to the NTSB Materials Laboratory for further examination. The examination revealed that the actuator fracture was generally circular in orientation, was slanted, and had indications of localized plastic deformation adjacent to the facture surface. The retainer section, that had separated from the stamp ring but remained attached to the actuator, exhibited damage to parts of the fracture surface and was smeared, consistent with post fracture contact with the adjacent components. The undamaged areas exhibited river patterns and chevron marks. In addition, the areas not damaged were examined with a scanning electron microscope, and exhibited dimple rupture, which is consistent with an overstress fracture.
The airplane was equipped with a J. P. Instruments EDM-800, which was panel mounted and recorded up to 24 parameters related to engine operations. The unit contained non-volatile memory for data storage of the parameters recorded and calculated. The data extracted included the accident flight starting 09:38:54 and ending 12:51:47 on June 20, 2016. The data indicated that just after 1251, the fuel flow decreased to zero and the EGT and CHT values decreased as well.
History of Flight
Enroute
Powerplant sys/comp malf/fail
Loss of engine power (total)
Attempted remediation/recovery
Landing
Off-field or emergency landing
Collision with terr/obj (non-CFIT)
Pilot Information
Certificate: Private
Age: 71, Male
Airplane Rating(s): Single-engine Land; Single-engine Sea
Seat Occupied: Left
Other Aircraft Rating(s): None
Restraint Used: Unknown
Instrument Rating(s): None
Second Pilot Present: No
Instructor Rating(s): None
Toxicology Performed: No
Medical Certification: Class 3 Without Waivers/Limitations
Last FAA Medical Exam: 08/01/2014
Occupational Pilot: No
Last Flight Review or Equivalent:
Flight Time: 1913.7 hours (Total, all aircraft), 1756.6 hours (Pilot In Command, all aircraft), 8.6 hours (Last 90 days, all aircraft)
Aircraft and Owner/Operator Information
Aircraft Make: ROCKWELL INTERNATIONAL
Registration: N1299J
Model/Series: 112A A
Aircraft Category: Airplane
Year of Manufacture: 1975
Amateur Built: No
Airworthiness Certificate: Normal
Serial Number: 299
Landing Gear Type: Retractable - Tricycle
Seats: 4
Date/Type of Last Inspection: 08/05/2015, Annual
Certified Max Gross Wt.: 2950 lbs
Time Since Last Inspection: 88 Hours
Engines: 1 Reciprocating
Airframe Total Time: 4046.7 Hours at time of accident
Engine Manufacturer: LYCOMING
ELT: C91A installed, not activated
Engine Model/Series: IO-360-C1D6
Registered Owner: JKM ENTERPRISES INC
Rated Power: 180 hp
Operator: JKM ENTERPRISES INC
Operating Certificate(s) Held: None
Meteorological Information and Flight Plan
Conditions at Accident Site: Visual Conditions
Condition of Light: Day
Observation Facility, Elevation: CSV, 1870 ft msl
Distance from Accident Site: 26 Nautical Miles
Observation Time: 1253 EDT
Direction from Accident Site: 1°
Lowest Cloud Condition: Clear
Visibility: 10 Miles
Lowest Ceiling: None
Visibility (RVR):
Wind Speed/Gusts: 5 knots /
Turbulence Type Forecast/Actual: /
Wind Direction: 340°
Turbulence Severity Forecast/Actual: /
Altimeter Setting: 30.36 inches Hg
Temperature/Dew Point: 26°C / 13°C
Precipitation and Obscuration: No Obscuration; No Precipitation
Departure Point: STERLING/ROCKFALLS, IL (SQI)
Type of Flight Plan Filed: None
Destination: JASPER, GA (JZP)
Type of Clearance: Unknown
Departure Time:
Type of Airspace:
Wreckage and Impact Information
Crew Injuries: 1 Serious
Aircraft Damage: Substantial
Passenger Injuries: N/A
Aircraft Fire: None
Ground Injuries: N/A
Aircraft Explosion: None
Total Injuries: 1 Serious
Latitude, Longitude: 35.523611, -85.091944 (est)
14 CFR Part 91: General Aviation
Accident occurred Monday, June 20, 2016 in Dayton, TN
Aircraft: ROCKWELL INTERNATIONAL 112A, registration: N1299J
Injuries: 1 Serious.
This is preliminary information, subject to change, and may contain errors. Any errors in this report will be corrected when the final report has been completed. NTSB investigators may not have traveled in support of this investigation and used data provided by various sources to prepare this aircraft accident report.
On June 20, 2016, about 1240 eastern daylight time, a Rockwell International 112A, N1299J, impacted trees during a forced landing following a total loss of engine power near Dayton, Tennessee. The private pilot was the only occupant and received serious injuries. Visual meteorological conditions prevailed and no flight plan was filed for the personal flight. The flight was conducted under the provisions of Title 14 Code of Federal Regulations Part 91. The flight originated from Whiteside County Airport – Jos H Bittorf Field (SQI), Rock Falls, Illinois, with an intended destination of Pickens County Airport (JZP), Jasper, Georgia.
In an interview with a Federal Aviation Administration inspector, the pilot stated that while en route, about 5,500 feet mean sea level, the engine lost power and he elected to land in a field. During the forced landing, the airplane impacted trees and subsequently the ground, which resulted in substantial damage to the fuselage, wings, and empennage.
A witness reported that the airplane was flying low, slow, and seemed to be flying in a circle until it impacted trees.
A postaccident examination revealed that the wings, rudder, and horizontal stabilizer had separated from the fuselage. The engine remained attached to the fuselage and the propeller remained attached to the engine. Two of the three propeller blades were bent aft and the third blade was bent forward. Furthermore, an odor similar to aviation fuel was noted on scene. The engine was retained for further examination.
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