N135CC is a 2019 Textron Aviation 208B. It is a fixed-wing single-engine aircraft with 12 seats, powered by a P&W Canada PT6A-140 rated at 867 horsepower. The registration is active, with the registrant based in Miami, FL. Its standard airworthiness certificate was issued in Mar 2019. It has been registered to its current owner since May 2019. This page also carries 1 NTSB event.
- 7 years old
- 1 of 216 Textron Aviation 208B
2019
That's everything on file so far — TailWiki checks the FAA registry daily and adds new entries as N135CC's record changes.
On May 2, 2010, about 2016 eastern daylight time (EDT), a JetProp DLX Piper PA-46-350P, N135CC, sustained substantial damage on impact with terrain near New Albany, Indiana. Instrument meteorological conditions prevailed at the time of the accident. The private pilot and passenger were fatally injured. The 14 CFR Part 91 personal flight was operating on an instrument rules (IFR) flight plan. The flight departed from Barkley Regional Airport (PAH), Paducah, Kentucky, about 1836 central daylight time (CDT) and was en route to Bowman Field Airport (LOU), Louisville, Kentucky.
About 1800 CDT, an employee of a fixed base operator at PAH stated that he directed the parking of the airplane. The pilot requested 40 gallons of fuel per side. The employee did not see any leaks from the airplane, and the airplane looked to be in “real good shape.”
About 1801-1805 CDT, the Washington Automated Flight Service Station, WS030 position, provided a weather briefing to a caller who had represented N135CC. The caller requested to be provided with “just a metar” at Louisville so he could see if he needed to go under visual flight rules (VFR) or IFR. When asked by the briefer if the caller was leaving soon, the caller said “yes.” The conversation continued and WS030 stated:
“uh looks like you’ll have to go i f r *(louisville’s) callin it wind one seventy at five nine miles light rain ceiling nine hundred broken one thousand one hundred overcast temperature an dew point both twenty one… however at standiford they have six miles moderate rain an mist uh one thousand three hundred broken an one thousand nine hundred overcast”
The caller then filed an IFR flight plan with a “filed off” time of “twenty minutes thirty minutes,” an altitude of “two one zero,” direct to “louisville bowman,” and a time en route of 45 minutes. The alternate airport was Louisville International Airport-Standiford Field (SDF), Louisville, Kentucky.
WS030 stated, “an ya got the airmet sierra for i f r ceilings below a thousand visibilities below three precipitation an *(mist) an uh conditions are forecast to continue through o three hundred both for turbulence an the i f r”
At 1826 CDT, N135CC requested an IFR clearance to LOU from PAH air traffic control. The clearance was, “cleared to bowman airport at filed maintain three thousand expect flight level two one zero within one zero minutes….” At 1833 CDT, N135CC was cleared for takeoff.
A transcription of transmissions by N135CC and Louisville/Standiford Air Traffic Control Tower, Departure One Radar, at the following times, states, in part:
2002:30 EDT, N135CC, “louisville approach jet prop one three five charlie charlie with you one three thousand for one one thousand”
2002:36 EDT, DR1, “november one three five charlie charlie lousiville approach information romeo is current at bowman expect a v o r approach runway two four
2002:43 EDT, N135CC, “five charlie charlie has romeo now sir
2002:46 EDT, DR1, november five charlie charlie roger
2004:26 EDT, DR1, november five charlie charlie descend and maintain seven thousand
2004:30 EDT, N135CC, (unintelligible) thousand five charlie charlie
2009:20 EDT, DR1, november five charlie charlie descend and maintain four thousand
2009:23 EDT, N135CC, four thousand for five charlie charlie
2010:35 EDT, DR1, november five charlie charlie fly heading zero five zero it’ll be vectors north of Louisville international
2010:39 EDT, N135CC, zero five zero on the heading five charlie charlie
2014:17 EDT, DR1, novenber five charlie uh sierra is now current at bowman they just went i f r uh i believe the ceiling was eight hundred it’ll be coming out here shortly on my system you can go ahead and pick up uh sierra if you like
2014:30 EDT, N135CC, five charlie charlie getting sierra
2016:54 EDT, DR1, (unintelligible) five charlie charlie uh fly heading zero six zero descend and maintain three thousand
There were no further recorded transmissions by N135CC.
A witness reported that the airplane approached from the southeast with a “loud” engine sound. The airplane then went “upside down” and entered a “spiral nose-dive." The witness also reported that there was no smoke or fire from the airplane.
The pilot, age 59, held a private pilot certificate with airplane single-engine land, glider, and instrument airplane ratings. On November 13, 1986, he was issued a private pilot certificate with a glider rating. On January 28, 1994, he was issued an airplane single-engine land rating. On April 28, 1998, he was issued an instrument airplane rating.
According to Federal Aviation Administration (FAA) records, on March 13, 2007, the pilot was involved in a runway incursion at Tucson International Airport, Tucson, Arizona. The pilot received an air traffic control clearance to taxi to runway 11L, which he read back correctly. The pilot stated that although he read the clearance as given, he taxied onto runway 11L expecting an immediate takeoff as he was aware of and saw air traffic on final approach for the same runway. The pilot was piloting a PA-46, N870FS, at the time of the runway incursion.
On March 8, 2010, the pilot began JetProp Factory Training, which included 7 flights and 8.5 hours of flight time in the accident airplane.
The president of JetProp stated that most of its customers received 5-10 hours of flight training, the amount of which depends on their ability. Most customers convert the airplane they have been flying so their panels are virtually the same. The pilot purchased an existing JetProp to train in, so the airplane and panel were new to him. The pilot was an average pilot with fairly good pilot skills, but he was always hunting around the panel for radios, switches, and navigation equipment. Because of this, it was recommended to the pilot that he should accumulate 25-50 hours under VFR before flying in instrument meteorological conditions without a safety pilot, to which the pilot agreed.
The JetProp Factory Training endorsement in the pilot's logbook was dated March 11, 2010. From March 12 to April 25, 2010, there were 5 entries logging flights of the accident airplane, of which only three entries had an associated flight time, which totaled 5.6 hours.
The pilot's total flight time, based upon logbook entries, was about 2,493.7 hours, which included entries for a Piper PA-46, N870FS.
The airplane was manufactured in 1999 as a Piper PA-46-350P, serial number 4636192, and was modified by Rocket Engineering Corp. under supplemental type certificate (STC) ST00541SE at a total time and Hobbs time of 354.8 hours, dated January 21, 2002. Under STC ST00541SE, the design change was for the installation of a Pratt & Whitney PT6A-34. The airplane was equipped with a Hartzell HC-E4N-3M, 4-blade composite propeller. Piper Aircraft had not provided any PA-46-350P engineering and/or flight test data to Rocket Engineering Corp. for its STC ST00541SE.
An Aircraft Registration Application by Deeems Holdings, LLC was signed by the pilot on March 8, 2010.
The airplane received its last annual inspection, dated May 21, 2009, at a Hobbs and total time of 1,396 hours. The engine received its last annual inspection, dated May 21, 2009, at a Hobbs time of 1,396 hours and a total time of 1,041.2 hours. According to aircraft and engine logbook entries, dated March 8, 2010, the Hobbs time was 1,388 hours.
A FlightSafety International JetProp DLX Pilot Training Manual recovered from the airplane states that the airspeed indicator green arc (normal operating range) is 68-172 knots indicated airspeed (KIAS) and the white arc (flaps down) is 57-117 KIAS.
The LOU automated surface observing system (ASOS), located about 10.7 nautical mile (NM) and 80. 4 degrees from the accident site at an elevation of about 546 feet mean sea level (MSL), recorded at:
2014 EDT: wind - 180 degrees from 5 knots; visibility 10 statute miles (SM); light rain; broken – 800 feet above ground level (AGL); overcast – 1,300 feet AGL; temperature - 21 degrees Celsius (C); dew point – 21 degrees C; altimeter – 29.68 inches of mercury; remarks - rain began at 2008, ceiling varied from 600-1,100 feet AGL.
The SDF ASOS, located about 6.9 NM and 99.8 degrees from the accident site at an elevation of about 501 feet MSL, recorded at:
1856 EDT: wind – 200 degrees at 6 knots; visibility – 10 SM; overcast – 1,100 feet AGL; temperature – 21 degrees C, dew point – 20 degrees C; altimeter setting 29.68 inches Hg; remarks – rain ended 1823.
2054 EDT: wind – 030 degrees at 5 knots; visibility – 10 SM; light rain; broken – 1,200 feet AGL, overcast – 1,900 feet AGL; temperature – 21 degrees C, dew point – 20 degrees C; altimeter – 29.69 inches Hg.
The main wreckage was located 38 degrees 11 minutes 52 seconds North, 85 degrees 53 minutes 13 seconds West at an elevation of 337 feet. The airplane was on a field in an upright position with a tail to nose heading of about 329 degrees. Ground scarring was limited to an approximate area surrounding the main wreckage, which consisted of the fuselage, wings, empennage, and engine. The area surrounding the main wreckage had a smell consistent with Jet A fuel.
The left wing and right wings were attached to the fuselage. The left wing tank was broken open and deformed outwards above and along the leading edge. The right wing was separated about mid-span and displaced aft. The right wing flap was attached to both right wing sections.
The empennage was separated from the fuselage near the aft pressure bulkhead. The vertical stabilizer was attached by its spar, and the remaining section of vertical stabilizer was displaced towards the right side of the fuselage as viewed from tail to nose.
Flight control continuity from the control surfaces to the cockpit controls was confirmed. The flaps, cockpit flap indicator, and handle were in the 10 degree extended position. The elevator trim jack screw was extended by about 10 threads, which equated to about 1/3 full nose-up trim.
The cockpit landing gear selector was in the down position. The landing gear was not in the retracted and locked position and when the airplane was lifted during recovery, the landing gear extended.
The fuel selector was positioned to the left tank. There was usable fuel quantity in the right tank and an unusable fuel quantity in the left tank. A liquid consistent in the color and smell of Jet A was present in the engine driven fuel pump.
The cockpit ignition switch was in auto position. The generator switch was in on position. The fuel pump switch was in the pump 2 position.
The top and bottom sections of the cabin entry door had their handles in the latched position. The top section had its two engagement hooks extended.
A crew oxygen bottle was found within the cabin, and its gauge indication was above the green band labeled full.
The Hobbs meter was destroyed.
Three of the four propeller blades were separated from the shank. One propeller blade was intact and the other was recovered along a road adjacent to the accident site. The remaining two propeller blades were not located. The fracture surfaces and location of the three separated propeller blades was consistent with impact damage. All four of the propeller blades/counterweights were of a similar blade angle estimated to be between low pitch and feather positions. The mounting bolts and engine attachment were intact. There were no impact marks to indicate preimpact blade angle. There were no anomalies that would have precluded normal operation.
A disassembly examination of the engine, a PT6A-34, serial number RB0137, revealed impact damage to the external engine housing. There was no evidence of fire. The engine compressor turbine, power turbine guide vane ring, interstage baffle, power turbine shroud, and power turbine displayed circumferential scoring consistent with rotation at the time of impact. There were no preimpact anomalies that would have precluded normal operation.
The pilot was issued a third class airman medical certificate on March 31, 2010, with the following limitations: “must wear lenses for distant, have glasses for near vision”.
An autopsy of the pilot was performed on May 3, 2010, and reported the cause of death was multiple blunt force injuries sustained in a small passenger aircraft mishap.
The FAA’s Final Forensic Toxicology Fatal Accident Report of the pilot stated: no carbon monoxide detected in blood, no cyanide detected in blood, no ethanol detected in blood, no drugs listed detected in blood.
Autopilot Examination
The KFC 225 autopilot system underwent a component examination at Honeywell, Olathe, Kansas, under the supervision of the FAA. The components were: configuration module, flight control computer, pitch servo, primary servo (roll servo), and the servo mount (roll).
The configuration module indicated that the software load was for a KFC 225 installation on a Piper PA-46-350P. The module also recorded roll monitor fail and yaw fail errors about 51 minutes and 36 seconds and 51 minutes and 38 seconds, respectively, after power was applied to the flight computer. The roll monitor fail message is logged when the aircraft experiences roll rates in excess of +/- 14 degrees per second or a roll attitude of +/- 45 degrees. The autopilot automatically disconnects when the roll monitor is tripped, which is logged as a roll monitor fail, and all of the flight director functions are disengaged. The yaw fail message is logged when the yaw rate is in excess of 12 degree per second. When yaw fail is logged, YD mode becomes inactive without affecting the other autopilot modes.
The flight control computer was connected to a system test panel and passed the preflight test. The unit passed all functional tests that included NAV/HDG/APR/VS mode engagement, altitude preselect, ARM, trim sense, auto trim, and course/heading operation.
The pitch servo sustained impact damage and portions of its bearing were damaged/not recovered. The inside of the pitch servo cover contained two markings consistent in color with that of the motor counterweight rubbing on the cover. In preparation for functional testing, the bearing was replaced and the motor counterweight was realigned. The servo then underwent final acceptance tests and no discrepancies were noted.
The primary servo (roll servo) was connected to a system test panel and passed preflight testing. The clutch engagement and disengagement was satisfactory. The servo passed functional checks. No discrepancies were noted.
The servo mount (roll) clutch was tested in the clockwise and counter-clockwise directions. The clutch slipped at approximately 31 inch per pound in both directions. STC installation manual cites the limit for clutch slip at 22 +/-2 inches per pound.
Stall Computer Examination
The stall warning computer was examined at Safe Flight Instrument Corporation, White Plains, New York under the supervision of the FAA. The computer was tested to and passed the acceptance/functional test procedure (ATP) with a small tolerance variation which may have due to adjustment for aircraft specific capability. The lift transducer associated with the stall vane could not be tested due damage from recovery.
Engine Trend Monitor (ETM)
Engine trend monitor (ETM) data was downloaded at Shadin Avionics, St. Louis Park, Minnesota, under the supervision of the FAA. The ETM download recorded 16 records dated May 2, 2010. The record times were not correlated and the record of the last takeoff report recorded a time of 15:33:25. The last three records consisted of a power check, a shaft horsepower exceedance, and a torque exceedance. The power check report recorded:
Time: 1549:14
Outside air temperature (OAT) – 0 degrees C
Pressure altitude – 17,510 feet
Indicated airspeed (IAS) – 164 knots
Propeller Speed (Np) – 2,164 rpm
Torque – 711 ft-lb
Fuel flow – 30.7 gallons per hour (GPH)
Interstage turbine temperature (ITT) – 611 degree C
Gas generator speed (Ng) – 90.6 percent
The shaft horsepower exceedance recorded:
Time: 1614:25
OAT – 16 degrees C
Pressure altitude – 4,270 feet
IAS – 77 knots;
Maximum shaft horsepower – 596.2 horsepower
Exceedance duration – 1 second
ITT – 697 degrees C
Ng – 98.9 percent
Np – 2,158 rpm
Torque – 1451 ft-lb
Fuel flow – 40.4 GPH
The torque exceedance recorded:
Time: 1614:25
OAT – 16 degrees C
Pressure altitude – 4,270 feet
IAS – 77 knots
Maximum torque – 1,451 ft-lb
Exceedance duration – 5 seconds
IIT – 697 degrees C
Ng: 98.9 percent
Np: 2,158 rpm
Fuel flow - 40.4 GPH
Radar Data
Radar data for a time period from about 20:14:27 EDT to 20:15:00 EDT recorded N135CC at an altitude of 4,000 feet, a decreasing ground speed from about 131 knots at the beginning of the period to about 116 knots at the end of the period, and an approximate northeasterly ground track. From about 2015:04 EDT to 20:15:50 EDT , the altitude range was 3,900 feet and 3,800 feet, and the airspeed decreased from about 119 knots at the beginning of this period to about 57 knots.
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