# Allison 250-C28B - Type: Engine model (FAA registry) - Registry code: 03114 - Manufacturer (registry): ALLISON - Model: 250-C28B - Engine type: Turbo-shaft - Power: 500 hp - Data sheet: [TCDS E1GL](https://openairdocs.org/tcds/E1GL) (OpenAirDocs) - Holder: Rolls-Royce Corporation - Installed in: 5 registered aircraft - Page: https://openairdocs.org/engine/allison-250-c28b Model codes come from the FAA registry's reference file. ## ADs that may apply (OpenAirDocs) Matched to this engine model by model name and maker. Each AD's applicability may narrow it by serial number, part number or equipment. - [AD 2018-13-01](https://openairdocs.org/ad/2018-13-01): Turbine Governor · Rolls-Royce 250-C10 (T63-A-5), 250-C18, 250-C18A and 24 more. Effective Aug 16, 2018 - [AD 2006-16-04](https://openairdocs.org/ad/2006-16-04): Inspection of the fuel nozzle screen · Rolls-Royce 250-B15A, 250-B15E, 250-B15G and 43 more. Effective Sep 7, 2006 - [AD 2005-20-11](https://openairdocs.org/ad/2005-20-11): Airfoils at the hub and shroud of third-stage turbine wheels · Rolls-Royce 250-C28, 250-C28B and 250-C28C. Effective Oct 18, 2005 - [AD 2004-14-02](https://openairdocs.org/ad/2004-14-02): SN third-stage turbine wheels · Rolls-Royce 250-C28, 250-C28B and 250-C28C. Effective Jul 26, 2004 - [AD 2002-06-08](https://openairdocs.org/ad/2002-06-08): Third Stage Turbine Wheels · Rolls-Royce 250-C28, 250-C28B and 250-C28C. Effective Apr 26, 2002 - [AD 98-24-28](https://openairdocs.org/ad/98-24-28): Main Fuel Control Bellows · Rolls-Royce 250-B15A, 250-B15E, 250-B15G and 36 more. Effective Jan 7, 1999 - [AD 96-19-01](https://openairdocs.org/ad/96-19-01): Superior Air Parts Manufacture Approval (PMA) Bearings · Rolls-Royce 250-B15G, 250-B17F, 250-B17F/1 and 17 more. Effective Sep 26, 1996 - [AD 89-23-12](https://openairdocs.org/ad/89-23-12): Turbine Nozzle Assembly · Rolls-Royce 250-C28B and 250-C28C. Effective Oct 29, 1989 - [AD 86-20-13](https://openairdocs.org/ad/86-20-13): External Splines · Rolls-Royce 250-C28B, 250-C28C, 250-C30 and 9 more. Effective Dec 3, 1986 - [AD 85-25-07 R1](https://openairdocs.org/ad/85-25-07-R1): Outer Combustion Case Assembly · Rolls-Royce 250-C28, 250-C28B, 250-C28C and 10 more. Effective Aug 15, 1986 - [AD 86-16-03](https://openairdocs.org/ad/86-16-03): Scavenge Line Air/Oil Centrifugal Separator Assembly · Rolls-Royce 250-C28B and 250-C28C. Effective Aug 13, 1986 - [AD 85-25-12](https://openairdocs.org/ad/85-25-12): Turbine-To-Compressor-Coupling · Rolls-Royce 250-C28B and 250-C28C. Effective Jan 6, 1986 - [AD 85-25-09](https://openairdocs.org/ad/85-25-09): Turbine Shafts And Couplings · Rolls-Royce 250-C28B and 250-C28C. Effective Jan 6, 1986 - [AD 85-25-08](https://openairdocs.org/ad/85-25-08): Compressor Mount Assembly · Rolls-Royce 250-C28B, 250-C28C, 250-C30 and 2 more. Effective Jan 6, 1986 - [AD 83-01-04](https://openairdocs.org/ad/83-01-04): Turbine Assemblies · Rolls-Royce 250-C28B and 250-C28C. Effective Jan 24, 1983 - [AD 82-24-05](https://openairdocs.org/ad/82-24-05): Control Assembly and Power Turbine Governor Assembly · Rolls-Royce 250-B15A, 250-B15E, 250-B15G and 43 more. Effective Nov 26, 1982 - [AD 82-03-02](https://openairdocs.org/ad/82-03-02): N2 (Electronic) Overspeed Control System · Rolls-Royce 250-C28B. Effective Feb 4, 1982 - [AD 79-16-06](https://openairdocs.org/ad/79-16-06): Accessory Drive Gearbox · Rolls-Royce 250-C28, 250-C28B, 250-C28C and 10 more. Effective Jan 11, 1980 - [AD 79-18-13](https://openairdocs.org/ad/79-18-13): Third Stage Turbine Wheel · Rolls-Royce 250-C28B and 250-C28C. Effective Sep 6, 1979 - [AD 79-06-05](https://openairdocs.org/ad/79-06-05): Overspeed Control System · Rolls-Royce 250-C28B and 250-C30. Effective Mar 26, 1979 - [AD 78-26-01](https://openairdocs.org/ad/78-26-01): Engine Electrical System · Rolls-Royce 250-C28B. Effective Nov 3, 1978 Historical (superseded or no longer in force): - [AD 2004-24-09](https://openairdocs.org/ad/2004-24-09) (historical): Fuel nozzle · Rolls-Royce 250-B15A, 250-B15E, 250-B15G and 40 more. Effective Jan 5, 2005 ## Registered aircraft (5) - [N1171](https://openairdocs.org/aircraft/N1171): [Agricultural Air Services LLC](https://openairdocs.org/faa-owner/AGRICULTURAL%20AIR%20SERVICES%20LLC), [Jupiter, FL](https://openairdocs.org/faa-place/FL/Jupiter), built 1979, S/N 45234 - [N249TH](https://openairdocs.org/aircraft/N249TH): [Timberland Helicopters Inc](https://openairdocs.org/faa-owner/TIMBERLAND%20HELICOPTERS%20INC), [Ashland, OR](https://openairdocs.org/faa-place/OR/Ashland), built 1980, S/N 45459 - [N395AE](https://openairdocs.org/aircraft/N395AE): [Air Evac Ems Inc](https://openairdocs.org/faa-owner/AIR%20EVAC%20EMS%20INC), [O Fallon, MO](https://openairdocs.org/faa-place/MO/O%20Fallon), S/N 45551 - [N52PL](https://openairdocs.org/aircraft/N52PL): [Paratus Air DBA](https://openairdocs.org/faa-owner/PARATUS%20AIR%20DBA), [Auburn, IN](https://openairdocs.org/faa-place/IN/Auburn), S/N 45744 - [N76DC](https://openairdocs.org/aircraft/N76DC): [Advanced Trucking LLC](https://openairdocs.org/faa-owner/ADVANCED%20TRUCKING%20LLC), [Kalispell, MT](https://openairdocs.org/faa-place/MT/Kalispell), built 1980, S/N 45471 ## NTSB investigations (2) From the NTSB's public API. Aircraft are matched to registry aircraft by N-number and event date, checked against the reported serial number, make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. - [NTSB ERA19LA152](https://openairdocs.org/ntsb/ERA19LA152), Apr 15, 2019: Bell 206 (N395AE), Dublin, GA, substantial damage. Probable cause: A partial loss of engine power on takeoff due to separation of the diffuser assembly as a result of incomplete braze joint surfaces on the vane airfoils. - [NTSB ANC13CA041](https://openairdocs.org/ntsb/ANC13CA041), May 1, 2013: Bell Helicopter Textron 206L-1 (N1171), Anaktuvuk Pass, AK, substantial damage. Probable cause: The pilot's failure to maintain lateral control while hovering over an area of snow-covered terrain, in flat light conditions, which resulted in a dynamic rollover. ## FAA accident and incident reports (3) From the FAA Accident/Incident Data System. Reports are matched to registry aircraft by N-number and event date, checked against the reported make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. - [Accident 20190415002849A](https://openairdocs.org/incident/20190415002849A), Apr 15, 2019: Bell Helicopter Textron 206L-1 (N395AE), Dublin, GA, Substantial damage. On April 15, 2019 at approximately 0345, N395AE, a Bell 206-L1+ helicopter conducting a part 135 flight, was involved in an accident at coordinates 32°29?45… - [Accident 20130430006769A](https://openairdocs.org/incident/20130430006769A), Apr 30, 2013: Bell Helicopter Textron 206L-1 (N1171), Umiat, AK, Substantial damage. Pilot entered low visability snow squall. Decided to set down and wait out weather. Upon landing, lost sight of ground due to blowing snow from rotor, lt skid… - [Incident 20020419020749I](https://openairdocs.org/incident/20020419020749I), Apr 19, 2002: Bell 206L1 (N3195P), Fourchon, LA, Minor damage. (-23) The pilot reported that he heard a bang followed by a yaw to the left, and subsequent loss of engine power. He also heard the engine out warning horn. He… ## Service difficulty reports (286, newest 50) As reported by operators and repair stations, by the model named in the report. - [SDR 2021FA0000190](https://openairdocs.org/sdr/2021FA0000190), Jun 30, 2021: PINION GEAR. FLAKING. AIRCRAFT OWNER EXPERIENCED THREE TRANSMISSION CHIP LIGHT WARNING INDICATIONS. THE TWO CHIP DETECTORS WERE PULLED AND METAL SLIVERS WERE FOUND ON THE LOWER CHIP - [SDR EVCA20151125001](https://openairdocs.org/sdr/EVCA20151125001), Nov 24, 2015: ACTUATOR. INOPERATIVE. POWER EXCURSION DURING APPLICATION. POST POWER ON AUTO ROTATION FLARE. TORQUE APPLIED THROUGH 40% FROM 0 AT WHICH POINT TORQUE VARIED 40%-70 &-45%-60% WITH 0 CO - [SDR 2014FA0000572](https://openairdocs.org/sdr/2014FA0000572), Sep 29, 2014: STRAP. SEPARATED. DURING O/H OF M/R HUB ASSY, TT STRAP ASSY SCRAPPED DUE TO SEPARATION OF PLASTIC AROUND BUSHING HOLES WITH TT: 771.9 AND TIME IN SERVICE 14 MONTHS. THIS PART HAS - [SDR EVCA2014071700063](https://openairdocs.org/sdr/EVCA2014071700063), Jan 25, 2014: MOUNT. CORRODED. WHEN DISASSEMBLY OF ACFT AFTER IT WAS DECOMMISSION, MECHANIC FOUND ENG MOUNT SUPPORT LEG CORRODED THROUGH. - [SDR AC2A201311080004](https://openairdocs.org/sdr/AC2A201311080004), Oct 26, 2013: BLADE. DAMAGED. ON POST FLIGHT INSPECTION, PILOT FOUND FOD DAMAGE ON TAIL ROTOR BLADE APPEARING TO BE FROM A BOLT. - [SDR 2013FA0000494](https://openairdocs.org/sdr/2013FA0000494), Aug 26, 2013: NOZZLE. BROKEN. PILOT NOTED A +5 DEGREE ON POWER CHECK AND AT TIMES DID NOT FEEL THAT THE ENGINE WAS PRODUCING FULL POWER. UPON REMOVING THE ENGINE INLET COWLING A 1.7500" PIEC - [SDR EVCA2012091200035](https://openairdocs.org/sdr/EVCA2012091200035), Sep 8, 2012: CHIP DETECTOR. BROKEN. TRANSMISSION CHIP DETECTOR HOUSING HEAD BROKEN OFF FROM BODY. - [SDR CA120328006](https://openairdocs.org/sdr/CA120328006), Mar 27, 2012: WASHER. WORN. (CAN) DURING 100-HR PERIODIC INSPECTION IT WAS NOTICED THAT THE TAIL ROTOR BELLCRANK AT THE END OF THE TAILBOOM WHICH ACTUATES THE PITCH CHANGE MECHANISM HAD A - [SDR CA110506005](https://openairdocs.org/sdr/CA110506005), Apr 14, 2011: EROSION SHIELD. DEBONDED. ON ANNUAL INSP THE EROSION STRIP OF THE MAIN ROTOR BLADE TIP CAP ASSY WAS FOUND DEBONDED & SEPARATING ON MAIN ROTOR BLADE PN 206-015-001-107 SN A-2908. MAIN ROT - [SDR EVCA00010](https://openairdocs.org/sdr/EVCA00010), Dec 12, 2010: BLADE. LEAKING. CONSTANT WEEPING FROM THE (RED) MAIN ROTOR BLADE VENT HOLE - CONSTANT STREAK. - [SDR CA100621003](https://openairdocs.org/sdr/CA100621003), Jun 18, 2010: DRIVE SHAFT. BENT. DURING GROUND RUNS, A NOISE AND VIBRATION FELT IN THE AFT BAGGAGE COMPARTMENT, INVESTIGATION FOUND THE SHORT STEEL SHAFT TO BE BENT .007" AT THE AFT COUPLING EN - [SDR 2010FA0000218](https://openairdocs.org/sdr/2010FA0000218), Mar 8, 2010: TRANSMISSION. MAKING METAL. CHECKED TRANSMISSION CHIP DETECTOR AFTER CHIP LIGHT ILLUMINATED ON APPROACH TO LANDING. SMALL PIECE OF METAL FOUND ON CHIP DETECTOR , CLEARED BY MX, 30 MIN GROU - [SDR 2010F00056](https://openairdocs.org/sdr/2010F00056), Mar 2, 2010: SUPPORT. CRACKED. DURING THE PRELIMINARY INSP OF UNRELATED MX, THE INSPECTOR FOUND THE PILOT'S YOKE SUPPORT TO HAVE A RADIAL CRACK EXTENDING FROM THE RELIEF HOLE APPROX .3750". T - [SDR 2010F00055](https://openairdocs.org/sdr/2010F00055), Mar 2, 2010: SUPPORT. CRACKED. RADIAL CRACK WAS DISCOVERED IN THE BASE OF THE UNIT AT THE RELIEF HOLE. CRACK IS APPROX .25" LONG. THIS SUPPORT ATTACHES THE PILOT'S YOKE TO THE FLOOR OF THE AC - [SDR 2010F00062](https://openairdocs.org/sdr/2010F00062), Mar 2, 2010: SUPPORT. CRACKED. CRACK IN NECK OF PART AT RELIEF HOLE. CRACK IS 0.9" LONG. PART CONNECTS PILOT'S YOKE TO ACFT FLOOR. - [SDR CBR2010F00000](https://openairdocs.org/sdr/CBR2010F00000), Nov 16, 2009: ENGINE. POWER LOSS. WHILE IN CRUISE FLIGHT, RETURNING FROM SIGHTSEEING TOUR, PILOT NOTICED THE N2/NR LOWER THAN NORMAL. THE PILOT MADE SEVERAL COLLECTIVE ADJUSTMENTS IN AN ATTEMPT - [SDR CA090728015](https://openairdocs.org/sdr/CA090728015), Jul 6, 2009: DRIVE SHAFT. LEAKING. INPUT SEAL ON HELICOPTER MAIN TRANSMISSION LEAKED OIL WHICH WASHED MAIN DRIVESHAFT COUPLING GREASE THROUGH SHAFT AND INTO ENG COMPARTMENT. GREASE WAS DISCOVERED - [SDR CA090728016](https://openairdocs.org/sdr/CA090728016), Jul 6, 2009: CONTROL TUBE. CRACKED. (CAN) THE HELICOPTER TRANSMISSION HAD BEEN REMOVED WITH THE FLIGHT CONTROL SUPPORT INTACT AND WAS ON THE BENCH IN THE O/H SHOP. A TECH THAT WAS INSPECTING THE C - [SDR CA090325008](https://openairdocs.org/sdr/CA090325008), Mar 23, 2009: BOLT. FAILED. MEDIUM DENSITY MAGNETOMETER SURVEY ARRAY WAS INSTALLED ON THE SUBJECT AIRCRAFT PER STC SH03-32 FOR A SURVEY BEING PERFORMED. WHILE FLYING ON SURVEY ON MARCH 23, - [SDR CA081001007](https://openairdocs.org/sdr/CA081001007), Oct 1, 2008: CHECK VALVE. DIRTY. (CAN) AFTER A FUEL FILTER REPLACEMENT A 2 MINUTE RUN IS REQUIRED WITH BOOST PUMPS OFF TO ENSURE THERE ARE NO AIR LEAKS IN THE FUEL SYS. DURING THIS 2 MINUTE GRO - [SDR CA080528003](https://openairdocs.org/sdr/CA080528003), May 23, 2008: RING. CRACKED. (CAN) CRACK FOUND ON TAIL BOOM RING DURING ROUTINE INSPECTION. - [SDR CA080528004](https://openairdocs.org/sdr/CA080528004), May 23, 2008: FITTING. CRACKED. (CAN) CRACK DETECTED ON FITTING DURING ROUTINE INSPECTION. - [SDR CA080521002](https://openairdocs.org/sdr/CA080521002), May 13, 2008: BEARING. CRACKED. (CAN) DURING THE 100 HR INSP A SMALL CRACK WAS FOUND ON THE INBD FEATHERING BEARING ON ONE OF THE TAIL ROTOR BLADES. CRACK WAS NOTICED AS A BLACK LINE AT THE TO - [SDR EVCA200804118](https://openairdocs.org/sdr/EVCA200804118), Apr 10, 2008: LINK. BROKEN. FAILURE OF THE LT REAR TRANSMISSION LINK IN FLIGHT. HEARD NOISE AUTOROTATION TO A SAFE LANDING IN FIELD. INVESTIGATION SHOWED THE LINK HAD SEPARATED, TRANS UP S - [SDR EVCA200841008](https://openairdocs.org/sdr/EVCA200841008), Apr 10, 2008: LINK. BROKEN. FAILURE OF THE LT REAR TRANSMISSION LINK IN FLIGHT. HEARD NOISE AUTOROTATION TO A SAFE LANDING IN FIELD. INVESTIGATION SHOWED THE LINK HAD SEPARATED, TRANS UP S - [SDR EVCA200804108](https://openairdocs.org/sdr/EVCA200804108), Apr 10, 2008: LINK. BROKEN. FAILURE OF THE LT REAR TRANSMISSION LINK IN FLIGHT. HEARD NOISE AUTOROTATION TO A SAFE LANDING IN FIELD. INVESTIGATION SHOWED THE LINK HAD SEPARATED, TRANS UP S - [SDR CA071001010](https://openairdocs.org/sdr/CA071001010), Sep 22, 2007: BEARING RACE. CRACKED. (CAN) PILOT REPORTED AN INCREASE OF FORCE REQUIRED TO PUSH THE T/R PEDALS AT 100 PERCENT RPM WHICH EXCEEDED THE OPERATIONAL LIMITS. HOWEVER, AT ZERO RPM THE FOR - [SDR 75408212007](https://openairdocs.org/sdr/75408212007), Aug 21, 2007: UNKNOWN. ODOR. FUEL ODOR NOTICEABLE AFTER TAKEOFF. THE AIRCRAFT RETURNED TO BASE. MAINTENANCE INSPECTED BELLY, SUMP DRAINS, AND DRAIN PORTS, FOUND NO EVIDENCE OF LEAKS. ALSO, - [SDR CA070822006](https://openairdocs.org/sdr/CA070822006), Aug 20, 2007: TRANSMISSION. MAKING METAL. (CAN) SHORTLY AFTER TAKEOFF THE PILOT RECEIVED A CHIP LIGHT ON THE TRANSMISSION. LANDED THE AIRCRAFT. METAL WAS DISCOVERED ON THE SENSOR. THE AIRCRAFT WAS REMOV - [SDR CA070926002](https://openairdocs.org/sdr/CA070926002), Jul 26, 2007: INDICATOR. FLUCTUATES. (CAN) THE AC WAS DEPARTING FROM BASE WHEN IT WAS NOTICED THAT THE ENGINE OIL PRESSURE INDICATOR WAS FLUCTUATING. THE PILOT RADIO A PAN TO ATC AND DID A PRECAUTI - [SDR YTRR116739](https://openairdocs.org/sdr/YTRR116739), Jul 22, 2007: FUEL FILTER. CLOGGED. FUEL FILTER IMPENDING BYPASS SWITCH KEPT ILLUMINATING CAUTION LIGHT. ON INSPECTION OF FILTER NO CLOGGING WAS NOTED. FILTER WAS REPLACED AND BYPASS LIGHT ILLUMIN - [SDR HEER117233](https://openairdocs.org/sdr/HEER117233), Jun 11, 2007: BEARING. SEPARATED. DURING A DAILY INSPECTION TECHNICIAN FOUND BEARING CAGE SEPARATED AT THE RIVETS. ALSO FOUND SEALS OUT OF THEIR RESPECTIVE RETENTION GROOVES. REQUEST THAT SHAFT - [SDR CM2R747K](https://openairdocs.org/sdr/CM2R747K), May 1, 2007: BELLCRANK. BROKEN. BEARING AND BOLT FAILED IN THE ELEVATOR BELLCRANK P/N 5360801-4. CENTER BEARING THAT SUPPORTS THIS BELLCRANK FAILED. BEARING IS P/N MS27640-4. BOLT P/N AN4-14 W - [SDR CA070105004](https://openairdocs.org/sdr/CA070105004), Jan 5, 2007: COMBUSTION CASE. CRACKED. (CAN) DURING A 200 HR INSPECTION A CRACK WAS FOUND IN THE ARM PIT AREA OF THE OUTER COMBUSTION CASE. CASE REPLACED. (TC NR 20070105004) - [SDR CA070105005](https://openairdocs.org/sdr/CA070105005), Jan 5, 2007: IMPELLER. CRACKED. (CAN) 300 HR NDT FOUND CRACKS IN THE WEB AREA. PART REPLACED. (TC NR 20070105005) - [SDR CA061207004](https://openairdocs.org/sdr/CA061207004), Dec 7, 2006: OIL COOLER. LEAKING. (CAN) ON AIRCRAFT RETURNING TO BASE IT WAS NOTED THAT THERE WAS OIL ON THE TAILBOOM. ON INVESTIGATION THE SOURCE OF THE OIL WAS FOUND TO BE THE OIL COOLER. COOL - [SDR CA061124011](https://openairdocs.org/sdr/CA061124011), Nov 14, 2006: COLLECTOR. CRACKED. (CAN) DURING ENGINE MAINTENANCE, THE HORIZONTAL FIRESHIELD WAS REMOVED AND (2) CRACKS WERE NOTED AT THE 5 O`CLOCK AND 7 O`CLOCK POSTION IN THE EXHAUST COLLECTOR - [SDR HEEA109567](https://openairdocs.org/sdr/HEEA109567), Jun 1, 2006: ENGINE. MALFUNCTIONED. DURING CLIMB OUT AT APPROXIMATELY 400 FEET, 60 KNOTS, AND 80 TORQUE HEARD A LOUD BANG THAT CAME FROM THE REAR OF THE HELICOPTER. THIS WAS FOLLOWED BY A SLIGHT L - [SDR CA060504008](https://openairdocs.org/sdr/CA060504008), May 3, 2006: BLADE. OUT OF TOLERANCE. THE BLADE WAS SENT TO ROTOR BLADES INCORPORATED FOR INSPECTION AS REQUIRED BY ASB 206L-04-127 REVISION C PART 3 AND BY AD CF-2004-05R1 PART D. ROTOR BLADES INCO - [SDR CA060403010](https://openairdocs.org/sdr/CA060403010), Mar 26, 2006: TUBE. BROKEN. PILOT HEARD A BIG "BANG" FROM ENGINE AND LOST POWER. THE PILOT LANDED IN THE BUSH WITHOUT DAMAGING THE A/C. AFTER THE INSPECTION OF THE COMPRESSOR BY THE MECHAN - [SDR CA060227005](https://openairdocs.org/sdr/CA060227005), Feb 24, 2006: SUPPORT. CRACKED. ON REMOVAL OF TURBINE SECTION FROM ENGINE ASSY ONE OF THE FWD SUPPORT STUTS WAS FOUND TO BE CRACKED. TURBINE ASSY SENT FOR REPAIR. RECOMMEND BETTER VISUAL INSPE - [SDR CA060120002](https://openairdocs.org/sdr/CA060120002), Jan 17, 2006: BEARING RACE. CORRODED. (CAN) ON A SCHEDULED 1200 HR M/R CORROSION INSPECTION THE INNER RACE OF THE M/R TRUNNION BEARING WAS FOUND TO BE SEVERLY CORRODED TO THE POINT THAT THE INNER RA - [SDR ALG2006F00006](https://openairdocs.org/sdr/ALG2006F00006), Jan 4, 2006: ENGINE. FLAMED OUT. ON FIRST START OF THE DAY, ENGINE FLAMED OUT. THIS EVENT WAS FOLLOWED BY 2 MORE FAILED START ATTEMPTS. MAINTENANCE INSPECTED THE ENGINE AND ASSOCIATED SYSTEMS W - [SDR CA060105003](https://openairdocs.org/sdr/CA060105003), Dec 8, 2005: MAST. MAKING METAL. M/R MAST WAS REPLACED 4 HOURS PREVIOUSLY. PILOT HAD A TRANSMISSION CHIP LIGHT AND NOTIFIED TOWER OF LANDING DUE TO A MX PROBLEM. ENGINEER INSPECTED F/W, TRANSMI - [SDR ALG2005F00081](https://openairdocs.org/sdr/ALG2005F00081), Oct 19, 2005: LENS. MISSING. IN CRUISE FLIGHT, FELT BUMP IN T/R PEDALS, UPON LANDING, NOTIFIED MAINTENANCE. INSPECTION OF AIRCRAFT BY MAINTENANCE FOUND THE UPPER WHITE STROBE LENS MISSING A - [SDR ALG2005F00082](https://openairdocs.org/sdr/ALG2005F00082), Oct 19, 2005: BEAM. ELONGATED. IN CRUISE FLIGHT, PILOT HEARD A NOISE IN THE AIRFRAME. UPON LANDING NOTIFIED MAINTENANCE. INSPECTION OF AIRCRAFT BY MAINTENANCE FOUND THE RT NOODLE BEAM ARM ASS - [SDR CA051005004](https://openairdocs.org/sdr/CA051005004), Oct 4, 2005: FITTING. CRACKED. (CAN) CRACKED FITTING ON TAILBOOM PN 206-033-004-045 AFMA FITTING P/N 206-031-403-005 - [SDR ALG2005F00076](https://openairdocs.org/sdr/ALG2005F00076), Sep 17, 2005: TRANSMISSION. MAKING METAL. DURING CRUISE FLIGHT, TRANSMISSION CHIP LIGHT ILLUMINATED. PILOT LANDED ASAP AND PERFORMED CHIP PLUG CHECK IAW THE OPS MANUAL PROCEDURE, WHILE IN COMMUNICATION - [SDR CA051003011](https://openairdocs.org/sdr/CA051003011), Sep 16, 2005: CLIP. DISCONNECTED. (CAN) DURING DESCENT, CNTRL N2 SPEED W/ACTUATOR TRIM SWITCH, PILOT (BEEPED) N2 SPEED DOWN. N2 SPEED REDUCED BELOW LIMITS, APPROX 70 PERCENT. AT THIS N2 SPEED EN - [SDR CA051003003](https://openairdocs.org/sdr/CA051003003), Sep 11, 2005: BLEED VALVE. MALFUNCTIONED. (CAN) TOT RUNNING TO WARM. BLEED VALVE STICKING OPEN. BLEED VALVE CHANGE PROBLEM GOES AWAY. All 286: https://openairdocs.org/engine/allison-250-c28b/reports.md ## STCs that may be installed (OpenAirDocs) (6) Approved for this engine model: the STC's model list names it on its data sheet, or a series that includes it. In force first, then newest. The registry doesn't record which STCs an aircraft has. - [STC SE00057AT](https://openairdocs.org/stc/SE00057AT): Installation of Aeronautical Accessories, Inc., Pc Safety Valve Kit. Bell Helicopter Textron Inc - [STC SE00014EN](https://openairdocs.org/stc/SE00014EN): Installation of the Pratt & Whitney Engine Services, Inc. CrossCheck Engine Monitor Kit P/N HUMS-K-071-1, Rev. A on the specified PT6A engine models and kit P/N HUMS-K-071-2 on the specified A250 engine models. Pratt & Whitney Engine Services Inc - [STC SE00026EN](https://openairdocs.org/stc/SE00026EN): Installation of Pratt & Whitney Engine Services Inc. IntelliStart Plus Electronic Control Unit (ECU), P/N DPU-K-010 on specified 250 engine models. Pratt & Whitney Engine Services Inc - [STC SE578GL](https://openairdocs.org/stc/SE578GL): Installation of a fuel flow transducer. Shadin Avionics - [STC ST00037AT](https://openairdocs.org/stc/ST00037AT): Unison igniter plugs, P/N 9044400-1. Unison Industries - [STC SQ00338AT](https://openairdocs.org/stc/SQ00338AT): Unison igniter leads, P/N9048222-101, 102, 103, 104, 105, 106. Unison Industries --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.