Boeing-Vertol 234

Service difficulty reports · 117

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duckdb -csv -c "SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy
  FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet'
  WHERE aircraft_model_key = '234'
  ORDER BY difficulty_date DESC"

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SDR CHIR201604082347Ring · crackedDURING A VISUAL INSPECTION FOR O/H OF THE UPPER RING ASSY, A HAIR LINE CRACK WAS NOTICED ON THE MAIN BEARING RETENTION SHOULDER OF THE UPPER RING ASSY. NDT PERFORMED A PENETRANT INSPECTION AND CONFIRMED THE RING WAS CRACKED. THIS CRACK FOLLOWED A RADIAL LINEApr 6, 2016 · Boeing 234 · Main Rotor Mast/SwashplateSDR CHIR201603312325Manifold · leakingNR 1 ENGINE FIRE WARNING IN-FLIGHT AT END OF DAYS OPERATIONS AT HOVER. MECHANIC CONFIRMED FIRE AFTER ACFT WAS SET DOWN. FIRE AT 12:00 ON TOP AND BACK OF BURNER CAN. AFTER ENGINE WAS SHUTDOWN, THE FIRE WENT OUT. ENGINE WAS INSPECTED. NO EVIDENCE OF CRACKINGMar 31, 2016 · N242CH · Boeing 234 · Fuel Controlling SystemSDR CHIR201511172182Bolt · brokenDURING DISASSEMBLY OF COMPONENT, SCUFFING ON BOTH THE SPIRAL BEVEL GEAR AND PINION GEAR WAS NOTED. THE CUSTOMER HAD REPORTED A SINGLE BOLT BROKEN UPON ON-WING TORQUE CHECK INSPECTION AND NO OTHER BOLTS APPEAR CRACKED AFTER DISASSEMBLY. NDT PENDING RESULTS. Nov 11, 2015 · N242CH · Boeing 234 · Main Rotor Transmission MountSDR CHIR2017082300057Bolt · crackedENGINEERING DEPARTMENT, THE THEN CURRENT BOLTS WERE REPLACED WITH PREVIOUS FASTENERS. IN THE INTERVENING 5 MONTHS, NO FURTHER ERRORS HAVE BEEN DETECTED. THESE ASSEMBLIES ARE INSPECTED AT 50 HR. INTERVALS IAW SB 234-63-0001 R0. Aug 28, 2015 · Boeing 234 · Main Rotor GearboxSDR CHIR2015090102057Bolt · crackedDURING DISASSEMBLY OF COMPONENT IT WAS NOTICED THERE IS SEVERE SCUFFING ON BOTH THE SPIRAL BEVEL RING GEAR AND THE SPIRAL BEVEL PINION GEAR. AT DISASSEMBLY, 2 BOLTS WERE FOUND CRACKED AFTER FAILING TORQUE CHECK ON WING. THIS BOLTED JOINT HAS NOT HAD THE UPDAAug 28, 2015 · Boeing 234 · Main Rotor Drive SystemSDR CHIR201509012098Bolt · crackedCREW REPORTED FAILED BOLTED JOINT INSPECTION. WHEN DISASSEMBLED IT WAS DISCOVERED THERE WERE 2 BROKEN BOLTS AND SEVERE SCUFFING ON SPIRAL BEVEL RING GEAR AND SPIRAL BEVEL PINION GEAR. THE FIRST STAGE SUN GEAR HAD ONE SPALLED GEAR TOOTH CAUSING COMPLETE DISASSEAug 28, 2015 · Boeing 234 · Main Rotor Drive SystemSDR CHIR2015062500001Housing · crackedA POST REPAIR FLOURESCENT PENETRANT INSPECTION WAS PERFORMED ON A PITCH HOUSING AFTER SOME MINOR BLENDING TO REMOVE PITTING. AN INDICATION OF A CRACK WAS DISCOVERED ON THE OTBD RADIUS OF THE TT PIN BORE.Jun 24, 2015 · N242CH · Boeing 234 · Main Rotor HeadSDR CHIR201508241959Strap · crackedSTRAP WAS FOUND BOWED AND HAD NINE BROKEN PLATES.May 13, 2015 · N245CH · Boeing 234 · Main Rotor HeadSDR CHIR201410151754Case · crackedCASE ASSEMBLY AT WEB OR LINER 247 HAS INDICATION OF A CRACK APPROXIMATELY 1.5" LONG. CRACK AT HOUSING IN PREVIOUS WELD REPAIR LOCATED NEAR ROTOR BRAKE HOUSING SUPPORT BORE. CRACK IS LOCATED ON OUTSIDE OF HOUSING.Oct 14, 2014 · N242CH · Boeing 234 · Rotorcraft Cooling Fan SystemSDR CHIR201409191728Liner · crackedDURING NDT PROCESS OF 234 AFT VERTICAL SHAFT BEARING HOUSING, CRACK FOUND ON BEARING LINER LAND AT 3 O`CLOCK POSITION, APPROXIMATELY .2500" LONG.Sep 18, 2014 · Boeing 234 · Main Rotor Drive SystemSDR CHIR20140530001Attach Fitting · crackedDURING SCHEDULED D CHECK INSPECTION, FOUND CRACK IN LT & RT LG SHOCK STRUT ATTACHMENT FITTING. PN 114S3807-1 & 114S3807-2. 1 CRACK ON EACH FITTING, APPROXIMATELY .250 INCH. LOCATION OF FITTINGS STATION 483, WL 1, BL 56L & BL 56R. REPLACED THE LT AND RT ATTMay 27, 2014 · N246CH · Boeing 234 · Fuselage, Landing Gear Attach FittingsSDR CHIR201405141535Impeller · damagedCREW REMOVED ENGINE FOR FAILURE TO PASS POWER ASSURANCE. HOT END OF ENGINE WAS REMOVED AND PLASMA SPRAY WAS NOTED COMING FROM AIR DIFFUSER. EXCESSIVE DAMAGE WAS OBSERVED THROUGHOUT GP SECTION INCLUDING BURNING OF SECOND STAGE NOZZLE AND LOSS OF MULTIPLE FIRMay 9, 2014 · Boeing 234 · Engine (Turbine/Turboprop)SDR CHIR20140425001Panel · crackedDURING A SCHEDULED B5 INSPECTION FOUR EACH C34S2187-9 FITTING SUPPORT PANEL ASSEMBLIES WERE DISCOVERED TO EACH HAVE ONE 1 INCH CRACK, FOUR CRACKS TOTAL. THE LOCATIONS OF THE FITTING SUPPORT PANEL ASSEMBLIES ARE AS FOLLOWS, FS 220, WL 5, BL 49L, FS 60, WL 5, BApr 23, 2014 · N246CH · Boeing 234 · Fuselage Miscellaneous StructureSDR CHIR201412120057Case · overtempTHE ENGINE WAS ORIGINALLY REMOVED FOR HIGH PTIT. HIGH PTIT WAS CONFIRMED IN THE TEST CELL. DURING DISASSEMBLY IT WAS NOTED THAT THERE WAS EVIDENCE OF PLASMA SPRAY EXITING THE AIR DIFFUSER. FURTHER DISASSEMBLY REVEALED A COMPLETE SECTION OF PLASMA REPAIR MISDec 9, 2013 · Boeing 234 · Engine (Reciprocating)SDR CHIR201310071464Impeller · damagedTHE ENGINE WAS ORIGINALLY REMOVED FOR HIGH PTIT. HIGH PTIT WAS CONFIRMED IN THE TEST CELL. DURING DISASSEMBLY IT WAS NOTED THAT THERE WAS EVIDENCE OF PLASMA SPRAY EXITING THE AIR DIFFUSER. FURTHER DISASSEMBLY REVEALED A COMPLETE SECTION OF PLASMA REPAIR MISSOct 3, 2013 · Boeing 234 · Turbine Engine Compressor SectionSDR CHIR20131609001Inverter · out of adjustOPERATOR HAS EXPERIENCED ISSUES WITH MALADJUSTED TORQUE INVERTER, SIGNAL CONDITIONERS, ALSO KNOWN AS RATIO DETECTOR POWER SUPPLY, RDPS, ASSOCIATED WITH THE ENGINE TORQUE INDICATING SYSTEM. THE FAULT IS ASSOCIATED WITH THE IMPROPER VOLTAGE OUTPUT FROM THE RDPS Sep 12, 2013 · N246CH · Boeing 234 · Engine BMEP/Torque IndicatingSDR CHIR20130811001Angle · crackedWHILE PERFORMING AN OPPORTUNITY INSPECTION OF THE AIRSTAIR DOOR CABLE PULLEY AT BS 160, NOTED THAT THE WEB & CAP WERE MOVING .0937 WHILE OPENING AND CLOSING THE DOOR. FURTHER INSPECTION REVEALED 2 CRACKS ON INBD CAP ANGLE IN AREA OF THE LOCK FASTENERS. BS 1Aug 11, 2013 · N246CH · Boeing 234 · Fuselage Miscellaneous StructureSDR CHIR20130729001Nut · crackedAPU WAS REMOVED FROM ACFT FOR REPORTED "LOUD SCREECHING" AND OIL LEAKING FROM INLET. ONCE INLET HOUSING WAS SEPARATED FROM REDUCTION DRIVE HOUSING IT WAS NOTED THAT THE OIL SLINGER NUT WAS BROKEN & CRACKED.Jul 26, 2013 · N245CH · Boeing 234 · APU Oil SystemSDR CHIR20132703001Seat Track · damagedDURING SCHEDULED B5 INSPECTION, FOUND ELONGATED HOLE FOR COMPANION WAY OBSERVER SEAT (AFT MOUNT BOLT). MOUNT IS INTEGRATED INTO CAP ANGLE. SUSPECT CAUSE OF ELONGATED HOLE WAS NORMAL INSERVICE WEAR. SEAT MOUNT BUSHING HOLE WAS REPAIRED IAW SL 234-0074.Mar 27, 2013 · N246CH · Boeing 234 · Fuselage, Seat/Cargo Attach FittingsSDR CHIR20132903001Support · crackedDURING A SCHEDULED 500HR SIDE FACING SEAT ATTACHMENT STRUCTURE INSPECTION, NOTED CRACKS IN FITTING SUPPORT PANEL ASSY AT BS 220 LBL 49 WL 5, BS 260, LBL 49 WL 5, BS 340, LBL 49, WL 5, BS 380 LBL 49 WL5, BS 180 RBL 49 WL5, BS 220 RBL 49 WL5. SIX CRACKS TOTAMar 26, 2013 · N246CH · Boeing 234 · Fuselage Miscellaneous StructureSDR CHIR201302261206Bevel Gear · crackedENGINE TRANSMISSION SPIRAL BEVEL GEAR WAS FOUND TO BE CRACKED ACROSS GEAR TOOTH, .2500" FROM THE HEEL.Feb 25, 2013 · N242CH · Boeing 234 · Main Rotor SystemSDR CHIR201302081182Adapter · crackedNR 2 CROSS SHAFT WAS INSPECTED AT SHUTDOWN. FOUND ADAPTER CRACKED.Feb 7, 2013 · Boeing 234 · Main Rotor Drive SystemSDR CHIR20122607001Bulkhead · crackedDURING B1 INSPECTION, A WEB CRACK WAS DISCOVERED ON FUSELAGE BS 482, WL +29 TO +34, RBL 44 TO 49. REPAIRED IAW TYPE DESIGN HOLDER STRUCTURAL REPAIR MANUAL.Jul 26, 2012 · N246CH · Boeing 234 · Fuselage Main, BulkheadSDR CHIR201205212201Bolt · shearedTHE CONNECTING BOLT WAS REMOVED FROM THE ROTOR HEAD AND A HAIR LINE CRACK WAS FOUND UNDER THE HEAD OF THE BOLT DURING A VISUAL INSPECTION. THE CRACK WAS CONFIRMED BY AN NDT INSPECTION.May 21, 2012 · N242CH · Boeing 234 · Main Rotor HeadSDR CHIR2011100300001Bearing · spalledTHE TRANSMISSION SHOP WAS INSPECTING THE AFT TRANSMISSION THAT WAS IN FOR REPAIR. THE MECHANIC FOUND THE INNER RACE OF THE BEARING SPALLED BADLY. THERE WERE NO OTHER INDICATIONS OF ANY OTHER PROBLEMS WITH THE BEARING DUE TO BEING INSTALLED IMPROPERLY.Oct 3, 2011 · Boeing 234 · Main Rotor GearboxSDR CHIA0579Attach Bolt · crackedDURING THE REPAIR OF ROTOR HEAD PN 414R2002, SN A5-1460, BOLT PN 114R2201-2, SN CH-3997, SHEARED AT THE THREADED PORTION OF THE BOLT WHEN FORCE WAS APPLIED TO THE BOLT HEAD IN A LOOSENING DIRECTION. BOLT PN 114R2201-2, SN SB-138, THAT WAS REMOVED DURING THE SMar 24, 2011 · Boeing 234 · Main Rotor HeadSDR MJ01709002Trunnion · bindingDURING THE "FLIGHT CONTROLS TRAVEL AND FLIGHT BOOST SYS CHECK" AS PART OF THE PRE-FLIGHT CK, COMPANY PILOTS NOTICED ABNORMAL RESISTANCE OF LONGITUDINAL CYCLIC CONTROL MOVEMENT. AT THIS POINT THE ACFT WAS GROUNDED AND TURNED OVER TO MX. UPON FURTHER INVESTIGAAug 22, 2009 · N246CH · Boeing 234 · Rotorcraft Flight ControlSDR CHIAMJ017/09/002Actuator · restrictedDURING (FLIGHT CONTROLS TRAVEL AND FLIGHT BOOST SYS CK) AS PART OF PRE-FLIGHT CHECKS (DESCRIBED IN FLIGHT MANUAL PART 1, SECTION 2 PAGE 2-11 ITEM 29 (A)) PILOTS NOTICED ABNORMAL RESISTANCE OF LONGITUDINAL CYCLIC CONTROL MOVEMENT. AT THIS POINT ACFT WAS GROUNDAug 22, 2009 · N246CH · Boeing 234 · Rotorcraft Flight ControlSDR MJ01709001Trunnion · crackedTHIS CRACK WAS DISCOVERED WHILE PERFORMING MX ON THE RT LANDING GEAR PROXIMITY SWITCH. TRUNNION ASSY - DRAG LINKS- AFT LANDING GEAR RT. (K)Jun 6, 2009 · N246CH · Boeing 234 · Fuselage, Landing Gear Attach FittingsSDR 2006FA0000888Blade · debondedROTOR BLADE HAD A LARGE SKIN DEBOND ON THE LOWER SURFACE FROM THE TRIM TAB OB, BETWEEN STA 227 AND STA 329, APPROXIMATELY 475-500 SQUARE INCHES (ALLOWABLE REPAIR LIMITS ARE 20 INCHES SPAN WISE AND 13 INCHES CHORD WISE. UNBONDED SKIN WAS REMOVED TO EXPOSE HONEJun 8, 2006 · Boeing 234 · Main Rotor BladesSDR CHIR823CABlade · debondedROTOR BLADE HAD A LARGE SKIN DEBOND ON THE LOWER SURFACE FROM THE TRIM TAB OB, BETWEEN STA 227 AND STA 329 APPROXIMATELY 475-500 SQ INCHES (ALLOWABLE REPAIR LIMITS ARE 20 INCHES SPAN WISE AND 13 INCHES CHORD WISE. UNBONDED SKIN WAS REMOVED TO EXPOSE HONEYCOMBJun 8, 2006 · Boeing 234 · Tail Rotor BladesSDR 2005FA0000871Adapter · crackedDURING OVERHAUL OF ENGINE AWN ADAPTER, NDT FOUND .450 INCH TOTAL LENGTH CRACK IN THE BOLT HOLE OF LUG NR 1. IN THE BORE OF LUG, CRACK LENGTH IS .300 OF INCH AND ACROSS FACE OF LUG, THE CRACK LENGTH IS .150 OF INCH. ILLUSTRATION DEPICTS LOCATION AND SCHEMATICJun 8, 2005 · N242CH · Boeing 234 · Engine (Turbine/Turboprop)SDR CA050315012Vent · failed(CAN) DURING REFUELING, A LOUD BANG WAS HEARD FROM CABIN OF AIRCRAFT. FUEL WAS THEN SEEN LEAKING RAPIDLY FROM AIRCRAFT. PILOTS NOTED FUEL INSIDE CABIN SECTION BUT NOT IN COCKPIT. ENGINES WERE SHUT DOWN, ELECTRICAL SYSTEMS TURNED OFF AND PILOTS EXITED AIRCRAFTMar 10, 2005 · Boeing 234 · Fuel StorageSDR CA040410001Drive Assy · cracked(CAN) DURING INSPECTION IAW AD 2004-06-51 A CRACK WAS DETECTED IN THE UPPER EXTENSION 37 INCHES FROM THE TOP. SHAFT WAS REMOVED FROM SERVICE AND RETURNED TO MFG FOR INSPECTION. MFG IS CONDUCTING INSPECTIONS OF ALL IN-SERVICE SHAFTS AND SPARES TO ELIMINATE ANApr 1, 2004 · Boeing 234 · Main Rotor Drive SystemSDR CHI2003F00004Engine · making metalDURING FLIGHT NR 2 ENGINE CHIP LIGHT CAMP ON. PILOTS REF EMERGENCY CHECKLIST AND IT INSTRUCTED THEM TO MONITOR ENGINE OIL PRESSURE AND TEMP, THEN LAND AS SOON AS PRACTICAL. AFTER LANDING THE NR 2 ENGINE CHIP DETECTOR WAS INSPECTED AND 2 METALLIC SLIVERS AND Jul 27, 2003 · N246CH · Boeing 234 · Engine (Turbine/Turboprop)SDR CHI2003F00003Engine · making metalENGINE CHIP LIGHT CAME ON IN FLIGHT, PILOTS REFERENCED EMERGENCY CHECKLIST AND IT INSTRUCTED THEM TO MONITOR ENGINE TEMP AND OIL PRESSURE AND TO LAND AS SOON AS PRACTICAL. INSPECTED CHIP DETECTOR AND FOUND A SINGLE METALLIC SLIVER, ALSO MAIN OIL FILTER BUTTONJul 23, 2003 · N246CH · Boeing 234 · Engine (Turbine/Turboprop)SDR CA030716007Engine · failed(CAN) LOUD BANG, SMOKE, NR 2 ENGINE STOPPED. AIRCRAFT RETURNED TO BASE SINGLE ENGINE. SMALL PIECES OF ENGINE FOUND CONTAINED IN NACELLE THAT APPEAR TO HAVE BEEN EJECTED THROUGH BLEED BAND. ENGINE RETURNED TO OVERHAUL SHOP FOR INVESTIGATION AND REPAIR. THIRD THJun 25, 2003 · Boeing 234 · Engine (Turbine/Turboprop)SDR CHI2003F00000Bar · crackedDURING NORMAL ROTOR HEAD MAINTENANCE, THE TWO REPORTED TIE BARS WERE FOUND WITH NUMEROUS DEFECTS. THE DEFECTS CONSISTED OF SEVERAL CRACKED PLATES AT THE TIE BAR PINHOLE. THE TWO TIE BARS WERE SENT TO THE MANUFACTURER FOR EVALUATION AND AFTER DISASSEMBLY, ADDJun 4, 2003 · N239CH · Boeing 234 · Main Rotor HeadSDR CHI2003F00002Compressor Wheel · crackedTWO CRACKS WERE FOUND IN THE 1ST STAGE COMPRESSOR DISC (PN210133105) DURNG AN INSPECTION. THE CRACKS ARE LOCATED IN TWO OF THE COMPRESSOR BLADE RETENTION SLOTS. THIS IS THE SECOND TIME CRACKS HAVE BEEN FOUND EMANATING FROM THE BLADE RETENTION SLOTS OF THIS PMar 14, 2003 · N242CH · Boeing 234 · Turbine Engine Compressor SectionSDR CHI2001F00000Connector · damagedDURING A CLIMB, CRUISE SITUATION, THE NR 1 ENGINE N2 SYSTEM, BEGAN TO OSCILLATE TOWARDS THE HIGH SIDE. THE NR 1 ENGINE WAS BROUGHT BACK TO GROUND POSITION AND THE HELICOPTER WAS RETURNED TO THE SERVICE LANDING. TROUBLESHOOTING FOUND A FAULTY CANNON PLUG ATTAJun 9, 2001 · N245CH · Boeing 234 · Engine RPM Indicating SystemSDR 20010606CW006Harness · corrodedAT TAKEOFF AND INTO CRUISE FLIGHT, THE NR 2 ENGINE BEGAN OSCILLATING AND GOING TO HIGH SIDE. THE NR 2 ENGINE WAS BROUGHT BACK TO THE GROUND POSITION AND HELICOPTER WAS RETURNED TO THE SERVICE LANDING. TROUBLESHOOTING REVEALED CORROSION/ RESISTANCE IN THE NR Apr 23, 2001 · N245CH · Boeing 234 · AC Power Distribution SystemSDR CA000501009Transmission · making metal(CAN) DURING DESCENT, CHIP WARNING LITE ILLUMINATED. MAINTENANCE PERSONNEL THEN CLEANED CHIP PLUG & CHANGED FILTER. SERVICEABILITY CHECK CARRIED OUT AS PER BOEING MAINTENANCE MANUAL SECTION 63-25-00 & 63-23-00 AND TRANSMISSION FOUND SERVICEABLE. HOWEVER, ROTOApr 12, 2000 · Boeing 234 · Main Rotor GearboxSDR CHIR3488Driveshaft · crackedTWO CRACKS IN OUTBOARD ADAPTER END. CRACKS GO THROUGH AN OUTBOARD RIVET HOLE AND EXTEND AT A 45 DEGREE ANGLE INBOARD AND OUTBOARD TO THE ADAPTER EDGE. P/N 114D3204-3 ADAPTER END. (X)Aug 16, 1999 · N238CH · Boeing 234 · Engine (Turbine/Turboprop)SDR CA990818003Bearing · failed(CAN) AFTER SHUTDOWN (FOLLOWING LOGGING OPERATIONS), A LOT OF BLACK GREASE AND METAL HAD BEEN SLUNG FROM THE SWASHPLATE SEAL AND PIECES OF BEARING CAGE WERE FOUND ALL OVER THE AFT SWASHPLATE AREA AND THRUST DECK. SWASHPLATE WAS REMOVED AND BEARINGS WERE EXTREAug 3, 1999 · Boeing 234 · Main Rotor Mast/SwashplateSDR CHI3212Actuator · malfunctionedPILOT ATTEMPTED TO APPLY SLIGHT AMOUNT OF AFT CYCLIC TO SLOW HELICOPTER AND EXTERNAL LOAD. THE CYCLIC WOULD NOT MOVE AFT OR FORWARD. NO SIGN OF ANYTHING BLOCKING THE CYCLIC MOTION, STILL HAD COLLECTIVE YAW AND ROLL CONTROLS, NO FORE AND AFT CONTROL. PILOT LSep 23, 1998 · N239CH · Boeing 234 · Main Rotor ControlSDR CHIA3099Pump · wornDURING TAKEOFF CHECK, PILOT NOTICED NR 2 FUEL PRESS 12 PSI LOWER THAN NR 1. THIS IS LOWER THAN IT NORMALLY OPERATES WITH ENG AT FLY AND BOTH FUEL TANK BOOST PUMPS ON. PILOT VERIFIED FUEL TANK BOOST PUMPS OPERATIONAL. VERIFIED FUEL PRESS IND READING PROPERLYJun 13, 1998 · N241CH · Boeing 234 · Engine Fuel PumpSDR CHI2077Shoulder Bolt · failedAFT ROTOR HEAD SHOULDER BOLT FAILED. SUBMITTER STATED 114R22012 IS THE IMPROVED BOLT THAT IS SUPPOSED TO PREVENT THIS TYPE OF FAILURE.Mar 17, 1998 · N241CH · Boeing 234 · Main Rotor HeadSDR CHI2012Bearing · spalledAFTER SHUTDOWN, NOTICED EXCESSIVE OIL LEAKING FROM AFT HEAD. CLOSER INSPECTION AND SUBSEQUENT REMOVAL OF RED HORIZONTAL HINGE PIN BEARING END CAP REVEALED METAL SHAVINGS COMING FROM RED LEADING HORIZONTAL BEARING. AFTER FURTHER DISASSEMBLY, FOUND A CRACKED HDec 20, 1997 · Boeing 234 · Main Rotor HeadSDR CHI1923Pump Motor · leakingAT SHUT DOWN OF AIRCRAFT WHILE STARTING APU, AGB HYDRAULIC MOTOR PUMP STARTED LEAKING AND SPRAYING HYDRAULIC OIL. AFTER SHUTTING DOWN OF APU AND CLOSER INSPECTION OF AGB PUMP, FOUND CASE HALF MOUNTING EARS CRACKED IN HALF WHICH SEPARATED BACK HALF OF PUMP FROOct 2, 1997 · Boeing 234 · Hydraulic Pump (Electric/Engine), MainSDR CHI1921Actuator · malfunctionON START-UP, PILOT WAS DOING CONTROL CHECK AND NOTICED HE COULD NOT GET THE FULL TRAVEL AFT THAT IS NORMAL WHILE DOING THE CONTROL CHECKS. TROUBLESHOOTING REVEALED THAT IF ONLY ONE HYDRAULIC SYSTEM WAS SELECTED, THE ACTUATOR WOULD START BINDING AND NOT PERMITSep 30, 1997 · N241CH · Boeing 234 · Main Rotor Control
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