# Rolls-Royce 250-C30S

- Type: Engine model (FAA registry)
- Registry code: 54012
- Manufacturer (registry): ROLLS-ROYC
- Model: 250-C30S
- Engine type: Turbo-shaft
- Power: 650 hp
- Data sheet: [TCDS E1GL](https://openairdocs.org/tcds/E1GL) (OpenAirDocs)
- Holder: Rolls-Royce Corporation
- Installed in: 2 registered aircraft
- Page: https://openairdocs.org/engine/rolls-royce-250-c30s

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 2006-20-07](https://openairdocs.org/ad/2006-20-07): Adds an additional life limit for third- and fourth-stage turbine wheels · Rolls-Royce 250-C30, 250-C30G, 250-C30G/2 and 11 more. Effective Nov 2, 2006
- [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 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 88-17-01](https://openairdocs.org/ad/88-17-01): Fuel Controls · Rolls-Royce 250-B17, 250-B17B, 250-B17C and 26 more. Effective Mar 1, 1989
- [AD 88-07-06](https://openairdocs.org/ad/88-07-06): Gas Producer Support Pressure Oil Tube Assembly · Rolls-Royce 250-C30, 250-C30M, 250-C30P and 2 more. Effective Mar 30, 1988
- [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 86-19-12](https://openairdocs.org/ad/86-19-12): Gas Producer Turbine Rotor · Rolls-Royce 250-C30, 250-C30G, 250-C30G/2 and 7 more. Effective Oct 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 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 84-24-54 R2](https://openairdocs.org/ad/84-24-54-R2): Gas Producer Turbine Rotor · Rolls-Royce 250-C30, 250-C30P, 250-C30R (T703-AD-700) and 1 more. Effective Jan 6, 1986
- [AD 85-06-51](https://openairdocs.org/ad/85-06-51): Magnetic Plugs · Rolls-Royce 250-C30 and 250-C30S. Effective May 10, 1985
- [AD 84-17-51](https://openairdocs.org/ad/84-17-51): Turbine Rotor Assembly · Rolls-Royce 250-C30 and 250-C30S. Effective Dec 26, 1984
- [AD 81-13-12 R1](https://openairdocs.org/ad/81-13-12-R1): 4th Stage Turbine Nozzle Assembly · Rolls-Royce 250-C30, 250-C30P and 250-C30S. Effective Sep 26, 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 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

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 (2)

- [N5415X](https://openairdocs.org/aircraft/N5415X): [Connecticut Air And Space Center](https://openairdocs.org/faa-owner/CONNECTICUT%20AIR%20AND%20SPACE%20CENTER), [Stratford, CT](https://openairdocs.org/faa-place/CT/Stratford), built 1981, S/N 760199
- [N90EV](https://openairdocs.org/aircraft/N90EV): [Tvpx Aircraft Solutions Inc Trustee](https://openairdocs.org/faa-owner/TVPX%20AIRCRAFT%20SOLUTIONS%20INC%20TRUSTEE), [North Salt Lake, UT](https://openairdocs.org/faa-place/UT/North%20Salt%20Lake), built 1984, S/N 760264

## NTSB investigations

None matched to aircraft with this engine model.

## FAA accident and incident reports

None matched to aircraft with this engine model.

## Service difficulty reports (449, newest 50)

As reported by operators and repair stations, by the model named in the report.

- [SDR YTRA2021090700001](https://openairdocs.org/sdr/YTRA2021090700001), Sep 4, 2021: INDICATION SYS. READS HIGH. PILOT REPORTED THAT IN CRUISE FLIGHT THE T5 INDICATION HIGHER THAN THE #2 ENGINE AND THE ENGINE FAILED THE TREND CHECK.
- [SDR CA160226008](https://openairdocs.org/sdr/CA160226008), Feb 21, 2016: COMBUST CHAMBER. CRACKED. (CAN) COMBUSTION CAN FOUND CRACKED DURING 300 HR ENGINE INSPECTION. CRACK FOUND IN ARMPIT AREA EXTENDING INTO BRAZED PATCH.
- [SDR CA160105002](https://openairdocs.org/sdr/CA160105002), Dec 27, 2015: SWITCH. FAILED. (CAN) MEDIC`S VHF RADIO STATION AND SAT PHONE REPORTED FOR TEMPORARILY POWER LOSS DURING FLIGHT. DURING MAINTENANCE TROUBLESHOOTING, TESTING OF THE SYSTEMS RESU
- [SDR CA151009004](https://openairdocs.org/sdr/CA151009004), Oct 8, 2015: THROTTLE CABLE. BROKEN. (CAN) ON ATTEMPTING START ON NR 2 ENGINE THE PILOT NOTICED NO T5 RISE. UPON FURTHER INVESTIGATION IT WAS REVEALED THAT WHEN THROTTLE CABLE WAS MOVED THERE WAS N
- [SDR CA150311005](https://openairdocs.org/sdr/CA150311005), Mar 8, 2015: LINER. DEBONDED. (CAN) DURING TAIL ROTOR DRIVESHAFT BEARING CHANGE. THE BEARING LINERS, WHICH ARE GLUED ONTO THE TAIL ROTOR DRIVESHAFT BECAME DISBANDED.
- [SDR CA141028006](https://openairdocs.org/sdr/CA141028006), Oct 26, 2014: BLADE. CRACKED. (CAN) A VISUAL INSPECTION OF THE ROOT END AREA OF THE SPAR WAS CARRIED OUT BEFORE THE RE-INSTALLATION OF THE BLADE DURING MAINTENANCE. A HAIR LINE CRACK WAS DIS
- [SDR CA141020004](https://openairdocs.org/sdr/CA141020004), Oct 18, 2014: GOVERNOR. MALFUNCTIONED. (CAN) IN A DESCENT, TORQUE SPLIT OCCURRED, NR 2 ENGINE LEADING WITH 83 PERCENT, T5 798, N2 106 PERCENT, NR 106. ENGINE NR 1 TQ 20 PERCENT, N1 AND T5 LOW, AS WEL
- [SDR Y3AR2014FA0000401](https://openairdocs.org/sdr/Y3AR2014FA0000401), Jun 18, 2014: COMBUSTION CASE. LEAKING. OUTER COMBUSTION CASE FOUND TO BE LEAKING AT WIRE MESH PATCH COVERING BUTT WELD DURING OUTER COMBUSTION CASE PRESSURE TEST.
- [SDR 2014FA0000402](https://openairdocs.org/sdr/2014FA0000402), Jun 18, 2014: COMBUSTION CASE. CRACKED. OUTER COMBUSTION CASE FOUND TO BE LEAKING AT WIRE MESH PATCH COVERING BUTT WELD DURING OUTER COMBUSTION CASE PRESSURE TEST.
- [SDR CA140402011](https://openairdocs.org/sdr/CA140402011), Apr 1, 2014: SHIELD. FAILED. (CAN) DURING APPROACH, THE FLIGHT CREW NOTICED A HIGHER THAN USUAL T5 INDICATION THAT LIMITED THE NR 2 ENGINE TORQUE. THE ACFT LANDED WITHOUT INCIDENT. A 5" X 3
- [SDR CA130614012](https://openairdocs.org/sdr/CA130614012), Jun 12, 2013: SHAFT. VIBRATION. (CAN) PTO SHAFT, PN: 76361-09103-104, DURING SHAFT REMOVAL FOR NR 2 ENGINE LUBRICATION OF ENGINE OUTPUT FLANGE SPLINES THE SHAFT WAS DISCOVERED SHEARED WHEN THE
- [SDR CA120823011](https://openairdocs.org/sdr/CA120823011), Aug 15, 2012: HOSE. LEAKING. (CAN) NR 2 SERVO LIGHT "ON", NR 2 HYDRAULIC PRESURE "0" INDICATION WAS NOTICED DURING LANDING. A BURST HYDRAULIC HOSE ASSY, PN:SS48C2C165000 WAS FOUND. REPLACED
- [SDR CA120814007](https://openairdocs.org/sdr/CA120814007), Aug 13, 2012: ENGINE. FLAMED OUT. (CAN) DURING LANDING A LOUD BANG WAS HEARD FOLLOWED BY INDICATION OF THE NR 2 ENGINE OUT LIGHT ILLUMINATION. AIRCRAFT LANDED IN THE WATER AND SHORTLY THERE AFTE
- [SDR AC2R20101214001](https://openairdocs.org/sdr/AC2R20101214001), Dec 14, 2010: GEARBOX. MAKING METAL. (AC2R) APPROX 2 MILES FROM LANDING, THE MAIN GEARBOX CHIP LIGHT ILLUMINATED. PERFORMED THE MAIN GEARBOX CAUTION LIGHT ILLUMINATED EMERGENCY PROCEDURE AND LANDED
- [SDR ALGA12012010702AL](https://openairdocs.org/sdr/ALGA12012010702AL), Dec 1, 2010: COUPLING. DISTORTED. IN CRUISE FLIGHT, CREW FELT A SUDDEN HIGH FREQUENCY VIBRATION IN THE AIRFRAME AND HEARD A CORRESPONDING NOISE. NO ABNORMAL COCKPIT INDICATIONS WERE NOTED. CREW 
- [SDR AC2A685K](https://openairdocs.org/sdr/AC2A685K), Nov 4, 2010: WARNING LIGHT. ILLUMINATED. NR 2 ENGINE CHIP LIGHT ILLUMINATED INBD TO BASE. FOLLOWED EMERGENCY PROCEDURES CHECKLIST, PLACED NR 2 ENGINE LEVER TO IDLE AND LANDED AS SOON AS PRACTICAL. ENGI
- [SDR CA100825006](https://openairdocs.org/sdr/CA100825006), Aug 23, 2010: HOUSING. DAMAGED. (CAN) DURING MEDEVAC MISSION MASTER CAUTION LIGHT AND XMSN PRESSURE LIGHT ILLUMINATED. THE PRESSURE GAUGE WAS DROPPING RAPIDLY. PRESSURE THEN DROPPED TO ZERO. F
- [SDR CA100706010](https://openairdocs.org/sdr/CA100706010), Jun 27, 2010: DUCT. CHAFED. IN CRUISE FLIGHT, WHEN CABIN HEATER WAS TURNED ON, OIL WAS BLOWN INTO THE COCKPIT CAUSING OIL MISTING ON THE WINDSHIELD AND COCKPIT FLOOR AT THE FOOT WARMERS, T
- [SDR CA100609007](https://openairdocs.org/sdr/CA100609007), Jun 7, 2010: CIRCUIT BREAKER. SPARKS. (CAN) ACFT WAS ON POSITIONING FLIGHT IN CRUISE AT 5500 FT, FL CREW NOTED SPARKS COMING FROM VICINITY OF AFCS CB PANEL IN THE CEILING AREA OF THE COCKPIT. THIS W
- [SDR YTRA1015901](https://openairdocs.org/sdr/YTRA1015901), Jun 1, 2010: FUEL NOZZLE. MISMANUFACTURED. ON APPROACH TO LANDING AT AN OFFSHORE PLATFORM THE NR 2 ENGINE HAD A LOW POWER INDICATION. THE PILOT ABORTED THE LANDING AND RETURNED TO HIS HOME BASE. ON INSP 
- [SDR CA100429001](https://openairdocs.org/sdr/CA100429001), Apr 26, 2010: FILTER. DEBONDED. (CAN) DURING SCHEDULED FILTER REPLACEMENT, METAL END CAGE WAS FOUND DISBONDED (SEE ATTACHED PHOTO). THE SEPARATION ALLOWED UNFILTERED ENGINE OIL TO PASS THROUGH
- [SDR CA091116009](https://openairdocs.org/sdr/CA091116009), Nov 6, 2009: THRUST PLATE. DAMAGED. (CAN) CUSTOMER COMPLAINT OF METAL GENERATION. ENG WAS INDUCTION TESTED AND CUSTOMER COMPLAINT WAS CONFIRMED. UPON DISASSEMBLY OF NR 8 BRG AREA, IT WAS NOTICED P
- [SDR AC2A2009082183073](https://openairdocs.org/sdr/AC2A2009082183073), Aug 21, 2009: WARNING LIGHT. ILLUMINATED. APPROXIMATELY TWO MINUTES AFTER TAKEOFF THE NUMBER ENGINE CHIP LIGHT ILLUMINATED. PERFORMED EMERGENCY PROCEDURES WHILE RETURNING TO ICY FOR LANDING.
- [SDR CA090901001](https://openairdocs.org/sdr/CA090901001), Aug 16, 2009: PITCH HORN. CRACKED. (CAN) ROUTINE INSP REVEALED APPARENT CRACK IN T/R PITCH CHANGE BEAM (HORN, ADJACENT TO BUSHING). BEAM SN IS A067-00042. AFTER REMOVAL OF PROTECTIVE PAINT COATIN
- [SDR CA090420005](https://openairdocs.org/sdr/CA090420005), Apr 16, 2009: GASKET. UNSERVICEABLE. (CAN) NR 2 ENGINE OIL COOLER GASKET FAILED.
- [SDR CA090206009](https://openairdocs.org/sdr/CA090206009), Jan 29, 2009: TRANSMISSION. MAKING METAL. METAL CONTAMINATION, CHIP LIGHT.
- [SDR CA081023004](https://openairdocs.org/sdr/CA081023004), Oct 16, 2008: THERMOSTAT. UNSERVICEABLE. (CAN) THERMOSTAT STUCK AND ENGINE OIL TEMP 8 EXCEEDED RED LINE LIMIT.
- [SDR HEEA119526](https://openairdocs.org/sdr/HEEA119526), Apr 24, 2008: ENGINE. FAILED. ONE SECOND INTO TAKEOFF, AFTER DP AND ROTATION, NR1 ENGINE FAILED. LOUD NOISE, CHIP LIGHT AND DECEL. FLEW TO AIRPORT AND LANDED.
- [SDR CA080528010](https://openairdocs.org/sdr/CA080528010), Apr 17, 2008: GEARSHAFT. CRACKED. (CAN) THE GEARBOX WAS RECEIVED FOR OVERHAUL. A CRACK WAS FOUND DURING THE MPI PROCESS AT THE REPAIR FACILITY. THERE ARE (2) THROUGH CRACKS IN THE REAR SEAL JOUR
- [SDR MV1R200808061](https://openairdocs.org/sdr/MV1R200808061), Apr 2, 2008: SHAFT. CRACKED. OIL LEAK FROM OUTPUT SHAFT NR 1 ENGINE. INSPECTED AREA NO DEFECTS FOUND AT THAT TIME. REPLACED SHAFT SEAL. GROUND OPS AND LEAK CHECK GOOD. AFTER FLIGHT OIL LEAK
- [SDR CA080314012](https://openairdocs.org/sdr/CA080314012), Mar 10, 2008: THERMOSTAT. STUCK. (CAN) THERMOSTAT STUCK AND ENGINE OIL TEMPERATURE INCREASED TO RED LINE. (TC NR 20080314012)
- [SDR CA080214010](https://openairdocs.org/sdr/CA080214010), Feb 9, 2008: ATTACH FITTING. FAILED. (CAN) SUBJECT AC CRASHED ON APPROACH TO LANDING. OPERATOR REPORTED TO THAT AN AFT-FACING CABIN SEAT BELT ATTACH FITTING FAILED ON IMPACT, PERMITTING THE SEAT BE
- [SDR CA080117006](https://openairdocs.org/sdr/CA080117006), Jan 16, 2008: THERMOSTAT. UNSERVICEABLE. (CAN) THERMOSTAT STUCK AND ENGINE OIL TEMP BEGAN TO RISE TO LIMIT. (TC NR 20080117006)
- [SDR HEEA118523](https://openairdocs.org/sdr/HEEA118523), Dec 19, 2007: ENGINE. FAILED. APPROXIMATELY 30-40 SECONDS AFTER COMPLETION OF CRUISE CHECKLIST AT 2750 FEET NR1 ENGINE FAILED. COMPLETED EMERGENCY CHECKLIST. DIVERTED AND LANDED WITHOUT FURT
- [SDR DXTA200702554](https://openairdocs.org/sdr/DXTA200702554), Oct 19, 2007: CONTROL SERVO. INOPERATIVE. (B) HYDRAULIC VOLUME LOW AND ILLUMINATED IN FLIGHT. REMOVED AND REPLACED THE ELEVATOR SERVO. OPS CHECKS GOOD IAW MM 22-10-01.
- [SDR CA071016020](https://openairdocs.org/sdr/CA071016020), Oct 14, 2007: HOSE. COLLAPSED. (CAN) FUEL HOSE INTERNAL COLLAPSE (TC NR 20071016020)
- [SDR HEEA117246](https://openairdocs.org/sdr/HEEA117246), Sep 6, 2007: WIRE. LOOSE. AIRCRAFT WAS PICKED UP AT BASE AND FLOWN TO MAINTENANCE. NORMAL EXTENSION AND RETRACTION. AFTER TAKEOFF, GEAR RETRACTED NORMALLY. UPON ARRIVAL, GEAR WOULD NOT E
- [SDR CA070905001](https://openairdocs.org/sdr/CA070905001), Aug 11, 2007: BEARING. DISINTEGRATED. (CAN) FLIGHT CREW ENCOUNTERED A NR 2 ENGINE CHIP WARNING LIGHT FOLLOWED BY COMPLETE ENGINE FAILURE WITHIN 1 MIN EMERGENCY LANDING EXECUTED. NR 2 ENGINE AND OIL 
- [SDR AC2A116707](https://openairdocs.org/sdr/AC2A116707), Aug 5, 2007: SEAT BACK. CRACKED. SEAT BACK FRAME CRACKED.
- [SDR AC2A116734](https://openairdocs.org/sdr/AC2A116734), Aug 3, 2007: BEARING. ROUGH. GYRO REMOVED FOR ROUGH BEARINGS AND LOUD NOISE.
- [SDR HEEA116396](https://openairdocs.org/sdr/HEEA116396), Jul 12, 2007: TRANSMITTER. FLUCTUATES. IN CRUISE FLIGHT THE NR1 ENGINE FUEL FLOW STARTED TO FLUCTUATE BETWEEN 200 TO 300 LBS. T5 AND N2 REMAINED NORMAL. RETURNED TO BOOTHVILLE. MAINTENANCE CLEANED TH
- [SDR HEEA116405](https://openairdocs.org/sdr/HEEA116405), Jul 11, 2007: BRACKET. LOOSE. LANDING GEAR WOULD NOT RETRACT. FOUND NOSE WHEEL CENTERING PROXIMITY SWITCH BRACKET LOOSE. TIGHTENED BRACKET AND CHECKED AND ADJUSTED SWITCH GAP.
- [SDR HEEA116395](https://openairdocs.org/sdr/HEEA116395), Jul 10, 2007: HOSE. RUPTURED. AFTER TAKEOFF, LANDING GEAR FAILED TO RETRACT, RED WARNING UNSAFE GEAR LIGHT ILLUMINATED PFN COMMENCED CHECKLIST AND TROUBLESHOOTING. APPROXIMATELY 2 MINUTES LA
- [SDR HEEA116165](https://openairdocs.org/sdr/HEEA116165), Jun 28, 2007: DOOR. OBSTRUCTED. AFTER LOWERING THE GEAR HANDLE, IT TOOK MORE THAN (4) MINUTES FOR THE LT MAIN GEAR GREEN LIGHT TO COME ON. MAINTENANCE FOUND THE FLOAT LINE NOT LETTING THE GEAR
- [SDR HEEA116033](https://openairdocs.org/sdr/HEEA116033), Jun 19, 2007: FUEL CONTROL. MALFUNCTIONED. DURING CRUISE FLIGHT NR 2 ENGINE TORQUE UNCOMMANDED WENT TO 105 AND N1 WENT 100. BROUGHT ENGINE UNDER CONTROL WITH THROTTLE. 5 MINUTES AFTER THAT THE NR 1 ENGIN
- [SDR AC2A115393](https://openairdocs.org/sdr/AC2A115393), May 5, 2007: FUEL CONTROL. MALFUNCTIONED. DURING A TRAINING FLIGHT, WE WENT TO 3,500 FEET AND ENTERED AUTOROTATION BY RETARDING BOTH ENGINE LEVERS TO IDLE. AFTER ESTABLISHING A STABILIZED AUTOROTATIONAL
- [SDR HEEA113938](https://openairdocs.org/sdr/HEEA113938), Jan 31, 2007: WIRE. BROKEN. LANDING GEAR WOULD NOT GO DOWN. REPAIRED BROKEN WIRE AT DIODE CR1.
- [SDR AC2A113672](https://openairdocs.org/sdr/AC2A113672), Jan 20, 2007: COUPLING. CRACKED. COUPLING WAS FOUND CRACKED ON 110 HR, AIRFRAME INSPECTION.
- [SDR AC2A113718](https://openairdocs.org/sdr/AC2A113718), Jan 16, 2007: TAIL ROTOR. WILL NOT BALANCE. THIS BLADE WAS HEAVY, COULD NOT BALANCE ON AIRCRAFT. MARVEL AND IT TOOK 52.26 GRAMS SPANWISE TO BRING IT IN. INSPECTION REVEALED OPENING AT TRAILING EDGE BY WEI
- [SDR AC2A113446](https://openairdocs.org/sdr/AC2A113446), Jan 4, 2007: SPINDLE. CRACKED. THE SPINDLE ASSEMBLY WAS REMOVED TO REPLACE A DEFECTIVE ELASTOMERIC BEARING. WHILE CLEANING THE SPINDLE BEFORE INSTALLING THE NEW BEARING, THE SHOP TECHNICIAN D

All 449: https://openairdocs.org/engine/rolls-royce-250-c30s/reports.md

## STCs that may be installed (OpenAirDocs) (5)

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 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

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