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OIL ODOR COMING FROM THE AIR VENTS WHEN APU IS ON.. GAINED ACCESS TO APU. REMOVED APU BLEED AIR DUCT AND INSPECTED FOR EVIDENCE OF OIL, NONE WAS FOUND. INSPECTED DOWN STREAM OF REMOVED BLEED AIR DUCT WITH BORESCOPE, NO EVIDENCE OF OIL WAS FOUND. INSTALLED PREVIOUSLY REMOVED APU BLEED AIR DUCT. REMOVED WATER SEPARATOR ASSY, FOUND TO BE OILY & DIRTY. CLEANED WATER SEPARATOR ASSY WITH DEGREASER & WASHED SOCK IN MILD DETERGENT. ASSEMBLED WATER SEPARATOR & INSTALLED. RAN APU, COMPLIED WITH LEAK CHK. FAINT ODOR COULD BE OBSERVED WITH APU BLEED AIR ON. STARTED NR 1 & 2 ENGS, TURNED OFF APU BLEED AIR & PREVIOUS FAINT ODOR DISSIPATED. TURNED APU BLEED AIR ON, RAN CABIN & COCKPIT TEMPS TO FULL HOT ALLOWED SUPPLY TEMPS TO INCREASE & STABILIZE, RAN TEMPS TO FULL COLD & ALLOWED SUPPLY TEMPS TO DECREASE & STABILIZE ODOR SEEMS TO HAVE DISAPPEARED. NOTIFIED MAINT CONTROL & THEY REQUESTED TO REPLACE CONDENSER SOCK & CLEAN OZONE CONVERTER. INSTALLED SPRING & CHAIN IN NEW COALESCER/CONDENSER SOCK. INSTALLED SOCK IN WATER SEPARATOR ASSY. RAN APU, LEAK CHECK & OPS CHECKS ARE SATIS, NO ODOR WAS NOTED. ALL WORK DONE IAW MM 21-51-00 & 49-10-00. REMOVED LT OZONE CONVERTER , REMOVED RT OZONE CONVERTER CLEANED OZONE CONVERTERS WITH PHOSPHATE FREE DETERGENT & COMPRESSED AIR IAW MM 12-19-02. INSTALLED OZONE CONVERTERS, RAN ENGINES, OPS CHK & LEAK CHKS SATIS AT THIS TIME. WORK DONE IAW 21-11-00.

AP STAB TRIM FAIL AND PRI STAB TRIM FAIL DURING FLIGHT. HORIZONTAL STABILIZER PRIMARY TRIM ACTUATOR MOTOR BRAKE ASSEMBLY, REMOVED AND REPLACED WITH REPAIRED UNIT SUPPLIED BY CUSTOMER. OPS CHKD COMPLETED WITH NO DISCREPANCIES NOTED. OPS CHECK GOOD. WORK COMPLETED IAW AMM 27-41-09. ACCESS PANEL 346BR HORIZONTAL STAB BULLET FAIRING ACCESS PANEL REMOVED FOR R & R OF PRIMARY STABILIZER TRIM MOTOR REPLACEMENT. PANEL RE-INSTALLED AND TORQUED. WORK COMPLETED IAW AMM 55-30-21.

SUSPECTED BURNING SMELL. MX C/A: PERFORM A GENERAL VISUAL INSPECTION OF THE #2 CDU AND ALL FOUR ADF’S FOR VISIBLE DAMAGE AND SECURITY. PROVIDED PROTECTION TO #1 PDU GROUND TERMINAL. RAN ENG FOR 10 MINUTES. RAN APU AND HAD COCKPIT AVIONIC UNITS POWER UP FOR 1 HOUR NO SIGNS OF ELECTRICAL SMELL AT THIS TIME ON GROUND. PERFORM AN OPERATIONAL CHECK OF THE #1 CDU PER AMM 34-61-05-710-801. COMPLIED WITH AQRD ENGINEERING ERO-989061 PROCEDURES. OPEN AND INSTALL A CIRCUIT BREAKER COLLAR ON C/B A4 CDU #2 (DISABLING THE SYS, R&R CDU W/IN 20 DAYS).

CLIMBING THROUGH 12,000FT THE CABIN ALT WARNING ANNUNCIATOR CAME ON. MEMORY ITEMS WERE CARRIED OUT AND AN EMERGENCY DECLARED WITH A RETURN TO KPBI. COMPLIED WITH PRESSURIZATION OPERATIONAL CHECKS, CONFIRMED OPERATIONAL CHECKS WERE GOOD IN AIR MODE AND NO FAULTS FOUND. ALL WORK DONE REF CE560XL MM 21-30-00. NO OTHER DEFECTS NOTED AT THIS TIME. PER CUSTOMER REQUEST COMPLY WITH THE CABIN PRESSURE CONTROLLER BIT TEST, COMPLIED WITH BIT TEST AS REQUIRED AND SYSTEM TEST CHECKS GOOD WITH NO DEFECTS. ALL WORK DONE REF CE560XL MM 21-30-00. NO OTHER DEFECTS NOTED AT THIS TIME.

APU FAILED TO START ON PAST 2 APPROACHES. CYAN APU SHUTDOWN CAS POSTED. ON SUBSEQUENT ATTEMPT AFTER LANDING THERE WAS A VERY STRONG SMELL OF FUEL IN THE CABIN. MX C/A: INSPECTED APU INLET AND APU IGNITER, APU INLET WAS CLEAR AND APU IGNITER WAS WITHIN LIMITS BUT SHOWED SIGNS OF WEAR. PERFORMED 4 SATISFACTORY STARTS OVER TWO HOURS WITH NO DEFECTS OR SMELLS NOTED. RECOMMEND CHECKING OIL PRESSURE SWITCH WIRING. NO DEFECTS NOTED AT THIS TIME. WORK PERFORMED IN REF TO HONEYWELL GTC56-150BD LMM 49-40-33. BOMBARDIER CL350 AMM 49-00-00.

MEL 21-52-00-02 (CAT A NO EXT) R PACK FAIL AMBER CAS MESSAGE - SMOKE APPEARS IN THE CABIN NEAR R2 THEN 10 MINUTES LATER THE R PACK FAIL. MX C/A: RH AIR CYCLE MACHINE (ACM) REMOVED AND REPLACED.

DURING T/O AT KDAL, CREW REPORTED OF HEARING A LOUD BANG DURING ROTATION PHASE, AFTER CLIMBING TO A SAFE ALTITUDE AND APPLICATION OF DORDAR (DECISION PROCESS) THEY SUSPECTED OF A BLOWN LH TIRE DURING TAKEOFF, AFTER THE EVENT, NO EVIDENCE OF BLOWN TIRES, NOR DAMAGES WERE FOUND BY THE CREW. HONEYWELL RECOMMENDED BORESCOPE LT ENGINE, WE ARE CURRENTLY REPLACING NR 1 ENGINE AS PER ITS RESULTS (COMPRESSOR STALL).

CREW REPORTS A CYAN ELECTRICAL FAULT FOLLOWED BY BATTERIES AND GENERATORS DROPPING OFFLINE. THE ELECTRICAL PANEL KEPT FLICKERING ON AND OFF. REMOVED AND REPLACED LEFT DC POWER CENTER IAW AMM 24-61-01. COMPLIED WITH BOMBARDIER RIL BD-0069-GENERATOR LOAD TEST PROCEDURE. OPS CHECK GOOD. NO DISCREPANCIES NOTED.

LATERAL CONTROL HYD. OFF AMBER MESSAGE REPOSTED DURING MAINTENANCE CHECK FLIGHT. FOUND BOTH WIRES OF TWISTED SHIELDED PAIR FROM AIRFRAME TO FORCE LINK SENSOR BROKEN AT ADEL CLAMP AT LH AILERON ACTUATOR. CRIMPED ON NEW SPLICES/ENVIRONMENTAL SEALS. REFERENCE G450 WDM 20-00-00. WIRE ROUTING COMPLETED REFERENCING G450 AMM 27-11-17 AILERON FORCE LINKS -REMOVAL/INSTALLATION. FOLLOW ON CHECKS COMPLETE REF G450 AMM 27-11-17.

LOW BRAKE PRESS & ANTI-SKIP INOPERATIVE LIGHTS ILLUMINATED & FLASHED DURING TAXI. BRAKES APPLIED & NO RESPONES DURING TAXI, EMERGENCY BRAKE HANDLE APPLIED TO STOP THE ACFT. R & R BRAKE SYS C/B, BRAKE MOTOR CONTROL RELAY, & BRAKE SYS MOTOR. BRAKE SYS AND ANTI-SKID SYS OPS CKS GOOD.

CREW REPORTS ON DESCENT PASSING 8000 FT WE NOTICED A STRONG PETROCHEMICAL ODOR. APU WASN’T SELECTED ON UNTIL 5000 FT. NOXIOUS FUMES WAS EVIDENT IN ENTIRE AIRCRAFT (NOTE: NO PAX ONBOARD, PIC/SIC DONNED O2 MASKS). OPEN ERTS 12/19 AT THIS TIME. SUSPECT APU SEAL, TBD.

LEVELING OFF @ FL430, AMBER WOW FAIL AND CYAN PROX SYS FAULT. MX C/A: R&R PSEU, OPS TEST OF GEAR EXTENSION AND RETRACTION GOOD, NO DISCREPANCIES DENOTED AT THIS TIME. (REF. CH300 AMM 32-61-09, 32-30-00)

AIRPLANE IS TRANSITIONING FROM AIR TO GROUND MODE TRIGGERING MULTIPLE CAS MESSAGES. WOW FAIL TO START. MX C/A: R&R PSEU, FUNCTIONAL CHECKS GOOD, NO DEFECTS NOTED.

RIGHT HYDRAULIC SYSTEM QUANTITY WENT TO ZERO MID-FLGHT AT CRUISE ALTITUDE. WHEN FLAPS EXTENDED FOR LANDING AMBER CAS MESSAGE RT HYD SYS PRESS LOW. USED ALTERNATE FLAP EXTENSION PER QRH. DECLARED EMERGENCY. LANDED NORMAL WITH PARTIAL SPOILERS, ONE REVERSER, AND SOFT-FEELING BRAKES. FOUND RT HYDRAULIC SYSTEM DC PUMP PRESSURE LINE FITTING LOOSE. TIGHTENED FITTING IAW CL-350 AMM 29-12-03. SERVICED HYDRAULIC SYSTEM TO FULL IAW CL-350 AMM 12-12-00. BLED SYSTEM IAW CL-350 AMM 29-10-00. OPS CHECK GOOD.

ELECTRICAL FAULT IN AMBER ON GROUND. POWER DOWN RESTART CLEARED FAULT. IN AIR MESSAGE RETURNED & STAYED ON EVEN ON GROUND. HAPPENED MULTIPLE TIMES. AT 43,000 SUDDEN VERY LOUD GARBLED WIND NOISE, WHITE NOISE OR STATIC SOUND HEARD THOUGHT ENTIRE ACFT. VERY LOUD RINGING HIGH PITCH NOISE FOLLOWED & REMAINED ON UNTIL PARKED & AC / DC POWER REMOVED. AFTER SELECTING POWER OFF HIGH PITCH CONTINUED FOR A FEW SECONDS BEFORE GOING AWAY. SUBWOOFER FOUND TO BE DAMAGED WHILE CHECKING THE AUDIO SYSTEM. R & R SUBWOOFER FRONT CABIN IAW SMM 44-10-01. OPS CHECK SATISFACTORY. AS PRECAUTION, R & R RT DC HALL EFFECT SENSOR IAW AMM 24-61-41. OPS CHECK GOOD, AS PRECAUTION, R & R PCB 2 IAW AMM 24-61-77. OPS CHECK GOOD. AS PRECAUTION, R & R AUDIO, VIDEO MODULE IAW SMM 44-10-01. OPS CHECK GOOD. MX CHECK FLT COMPLETED SATISFACTORILY.

NOSE GEAR DOOR UNLOCK CAS AT 11000FT AT 280 KTS B3-007497 AND B3-007493. MX C/A: R&R RH & LH NLG FWD DOOR HINGE BOLTS WITH NEW. C/W SUCCESSFUL RH & LH NLG DOOR PROX SWITCH RIGGING, SWUNG GEAR SEVERAL TIMES WITH SATISFACTORY RESULTS IAW CL-300 AMM 32-22-00, 32-22-01 AND 32-61-00. (RII C/W)

LEFT HYDRAULIC SYSTEM INDICATING A FLUID LEAK DURING FLIGHT. FOUND DUMP VALVE STILL OPEN FROM PREVIOUS EMERGENCY EXTENSION, FOUND HYDRAULIC LEAK COMING FROM RT NOSE VENT FOR EMERGENCY PNEUMATIC EXTENSION LINES. CLOSED DUMP VALVE & SEATED SHUTTLE VALVES IAW AMM 32-29-00. REMOVED LANDING GEAR SELECTOR, DUMP VALVE, INSTALLED OVERHAULED LG SELECTOR, DUMP VALVE IAW ACTUATION SYSTEMS FAA FORM 8130-3, REF AMM 32-30-03. JACKED AIRCRAFT IAW AMM 07-10-00. C/W SATIS LANDING GEAR CYCLING, OPS TEST.IAW AMM 32-00-00. C/W SATIS LANDING GEAR EMERGENCY EXTENSION SYSTEM FUNCTIONAL CHK IAW AMM 32-39-00. NO LEAKS NOTED. DOWN JACKED AIRCRAFT IAW AMM 07-10-00.

L COCKPIT WINDSHIELD FRACTURE. MX C/A: REMOVED FRACTURED LH FRONT WINDSHIELD AND INSTALLED A NEW FRONT WINDSHIELD. PN OFF/ON: 1159SCB102-13, SN OFF: 17150H7350, SN ON: 25184H9590, WINDSHIELD PROVIDED BY GULFSTREAM AEROSPACE CORPORATION, AUTHORIZATION NO: ODA-511131-CE, DATED: 16/JUL/2025, UNDER FTN: 20250716101807. REMOVED AND INSTALLED A NEW WINDSHIELD HEAT CONTROL UNIT NO. 1, PN OFF/ON: 1042-1, SN OFF: 3935, SN ON: 5666. TEMPERATURE CONTROLLER PROVIDED BY GULFSTREAM AEROSPACE CORPORATION, AUTHORIZATION NO: ODA-511131-CE, DATED: 29/APR/2024, UNDER FTN:20240429125731. OPS/ SECURITY/LEAK CHECKS GOOD. NO DISCREPANCIES NOTED.

POWER BRAKE CB POPPED UPON ENGINE START, ANTI SKID INOP ANNUNCIATOR ILLUMINATED, RESET. DID SAME THING AGAIN ON TAXI. RETURNED TO RAMP. NOTICE BRAKES WERE VERY WEAK. ABOUT 30 SECONDS AFTER, LO BRAKE PRESS ANNUNCIATOR CAME ON. ONLY EMERGENCY BRAKES AVAIALABLE. HYDRAULIC PUDDLE FOUND UNDER NOSE GEAR. MX C/A: BLED BRAKES AND AT CUSTOMERS REQUEST PWR BRAKE CIRCUIT BREAKER WAS REMOVED AND REPLACED WITH NEW PN: S2899L15.0 IAW CESSNA CITATION MM 24-50-02

ON SHORT FINAL BELOW 500' AUDIO ALERT TOO LOW GEAR. ON FIRST GO AROUND ELECTED NOT TO RAISE GEAR ON THE DOWN THREE GREEN INDICATION. ON SECOND ATTEMPT WITH SAME ALERT ELECTED TO RAISE GEAR AND EXECUTE A NORMAL PATTERN. THIRD LANDING ATTEMPT WAS NORMAL. MX C/A: INTERROGATED MDC, FOUND NO RELATED FAULTS FOR PROXIMITY SYSTEM. CUSTOMER REQUEST TO PERFORM A TAWS OPERATIONAL CHECK. COMPLIED WITH OPS CHECK TASK 34-42-01-710-802 (2.) A-E STEPS 1-14. STEP 15 REQUIRES OPENING OF HYD CIRCUIT BREAKERS AND POSITION GEAR HANDLE UP. WILL NEED TO BE PLACED ON JACKS FOR THIS PORTION OF TEST ALONG WITH GEAR SWINGS. MCC SENT IN DOWNLOADS TO CRC FOR REVIEW. PER MCC AND CRC REPLACED LANDING GEAR CONTROL PANEL ASSEMBLY WITH CUSTOMER SUPPLIED NEW PART PER CHALLENGER 300 AMM CH 32-31-13 AND C/W TAWS OPERATIONAL CHECK TASK 34-42-01. ALL OPS CHECKS GOOD.

ON CLIMB OUT PASSING 17000FT, SMOKE OBSERVED COMING OUT FROM BETWEEN FRAME OF LEFT WINDSHIELD AND LEFT SIDE WINDOW. MX C/A: RE-TORQUED THE LH WINDSHIELD TERMINALS T1 / T2 AND S2 TO PROPER TORQUE SPECS AS REQUIRED REF GVFD5000 AMM 56-10-01-400-801 STEP F(33). PERFORMED SATISFACTORY OPERATIONAL TESTING OF THE LH WINDSHIELD AND SIDE WINDOW ANTI-ICING SYSTEM REF GVFD5000 AMM 30-41-00-710-803.

RED PACK LEAK CAS B3-007406 LEAK DETECTED IN DUCT RUNNING FROM THE LEFT FLOW CONTROL VALVE TO THE PACK INLET AND PRECOOLER CROSS VALVE. PERFORMED OPERATIONAL CHECK OF THE AC SYSTEM. NO LEAK DETECTS AND SYSTEM OPERATES NORMALLY. PERFORMED BLEED LEAK DETECTION SYSTEM TROUBLESHOOTING. NOTED LEAK DETECTED 0005 AT 67% - FS 0791 PACK LOOP A. PERFORMED RESISTANCE CHECK OF MT141 AND MT73, FOUND MT73 RESISTANCE READ 4 OHMS HIGHER THAN NORMAL. REMOVED AND REPLACED MT73 PACK LOOP SENSOR WITH CUSTOMER SUPPLIED LOOP SENSOR. OPERATIONAL CHECKED GOOD. WORK DONE IAW BD100 AMM CHAPTER 36-21-11. (RTS 5/17)

FLAPS FAILED TO RETRACT PROPERLY ON DEPARTURE (JAMMED AT 10 DEGREES). AMBER CAS 'FLAPS FAILED' & BLUE CAS 'FLAP/STAB MAINT REQD'. MX C/A: TROUBLESHOT ISSUE. FOUND SEVERAL WORN ROLLERS ON BOTH FLAPS, QTY 4 ON RH FLAP AND QTY 2 ON LH FLAP. REMOVED FLAPS, PERFORMED FREEPLAY CHECKS OF ALL ACTUATORS. FOUND THAT RH FLAT INBOARD ACTUATOR FAILS FREEPLAY CHECK. REPLACED RH INBOARD ACTUATOR WITH A NEW UNIT. FOR RESOLUTION SEE ITEM 5,6 OF W/0: 17726, REPLACED TRAILING ROLLERS ON "B" TRACK AND "C" TRACK OF RH FLAP, REPLACED TRAILING ROLLERS ON ''B" TRACK OF LH FLAP. REINSTALLED FLAPS, PERFORMED FLAP RIGGING PROCEDURE AND AUTORIG PROCEDURE WITH NO DISCREPANCIES NOTED AT THIS TIME. OPS CHECK GOOD. REF: 6450 AMM CH: 27-50-00. [NOTE: THIS SDR WAS PREVIOUSLY SUBMITTED INCORRECTLY UNDER CONTROL # 2025FA0000232 ON 4/3.]

APU FIRE CAS MESSAGE IN FLIGHT WHEN ATTEMPTING TO START AT FL120 AND 250KTS, CREW PERFORMED SHUTDOWN PROCEDURE AND NO FURTHER ISSUES NOTED, BOTTLE DOES NOT APPEAR TO HAVE DISCHARGED. NO INDICATION OF FIRE NOTED OUTSIDE THE AIRCRAFT. MX C/A: COMPLETED RECOMMENDED FIRE LOOP RISISTANCE CHECK ON A103, A104, A105, A106, AND CONNECTOR PLUG A91PL PIN 12 AND 13, A91P2 PIN 12 AND 13. ALL WIRE CHECKED GOOD. PER SMARTFIX AND CRC SUSPECT FIREX CONTROL UNIT IS FAULTY. REMOVED FAILED FIREX CONTROL UNIT AND INSTALLED CUSTOMER SUPPLIED INSPECTED CONTROL UNIT P/N OFF/ON: 474112·1, S/N OFF: 377, S/N ON: ACW6791. OPS CHECKED GOOD, NO FURTHER DISCREPANCIES NOTED. REF: CL-300 AMM 26-11-01

N643TX-250320-1 FO PFD INSTRUMENTS FROZE AT FL400. AIRSPEED INDICATIONS INCREASED TO 450KTS (NOT ACTUAL AIRSPEED). WITH ASSICIATED AURAL WARNING. MX C/A: DRAINED ALL STATIC PORTS AND PURGED PITOT/STATIC SYSTEM, OPS AND LEAK CHECKS NORMAL AT 40000 FT AND 200 KNOTS. REFERENCE C560XL AMM 34-90-10.

ELECTRICAL SMOKE IN CABIN DURING CLIMBOUT. MX C/A: MICROWAVE REMOVED AND INSPECTED, FOUND THE CANNON CONNECTOR LOOSE. NO ARCING FOUND ON CANNON CONNECTOR ON THE AIRFRAME SIDE OF THE GALLEY OR THE MICROWAVE. MICROWAVE FAILED OPERATIONAL TEST. REMOVED MICROWAVE PN 400-1338-02-L-N SN 22-10-34146 AND INSTALLED A CUSTOMER SUPPLIED "REPAIRED" MICROWAVE PN 400-1338-02-L-N SN 22-12-34653. WORK WAS PERFORMED IAW SMM 25-30-03 AND CMM 25-30-43. OPERATIONAL CHECK SATISFACTORY. NO FURTHER DEFECTS NOTED. AIRCRAFT CREW JOINED US AND RAN THE ENGINES AND APU BLEED SOURCES INDEPENDENTLY AND VERIFIED THAT THE AIR CONDITIONING SYSTEM WAS OPERATING NORMALLY, AND NO SMOKE WAS BEING GENERATED.

LH WINDSHIELD CRACKED IN FLIGHT AT FL450. MX C/A: R&R LH WINDSHIELD ASSY, OPS AND LEAK CKS GOOD.

ON APPROACH WE GOT CAS MESSAGES "LATERAL CONTROL HYD OFF". MX C/A: PERFORMED INSPECTION OF AILERON WIRING W/IN UNDER WING FLAP BAYS. NOTED BROKEN WIRE IN LH WING MOST OUTBOARD FLAP BAY (JUST BEFORE AILERON). REPAIRED WIRE AND PERFORMED SUCCESSFUL OPS CK WITH NO FAULTS NOTED. REF. GULFSTREAM G450 AMM 20-25-07.

LO OIL PRESS LIGHT R ANNUNCIATOR ILLUMINATED AND OIL PRESSURE TAPE SHOWING 0 IN FLIGHT. REMOVED & INSPECTED R ENG. OIL FILTER & REINSTALLED IAW PW 545 AMM: 79-20-01. REMOVED R. ENG COLD START VALVE, CLEANED, MADE A 1/8 ADJUSTMENT IN THE CCW DIRECTION AND REINSTALLED. PERFORMED SATISFACTORY ENGINE RUNS IAW PW 545 AMM: 71-00-00 CHPT. 13 & 17. NO DEFECTS NOTED... WE DECIDED TO KEEP ACFT DOWN FOR FURTHER TROUBLESHOOTING, ACFT STILL DOWN AT THIS TIME. WE R&R COLD START VALVE, AWAIT OPS CKS AND ENG RUNS. WE WILL PERFORM MX CHECK FLIGHT FOLLOWING ESTIMATED RTS OF 2/27.

LEFT ENGINE ROLL BACK IN PATTERN AT FLL. IGN LIGHT CAME ON SOUND OF COMPRESSOR STALL BANG AND SMELL OF SMOKE. ENGINE REGAINED POWER I LEFT ENGINE AT IDLE POWER AND LANDED. LEFT ENGINE AMBER MAINTENANCE LIGHT CAME ON. MX C/A: BSI REPORT CONFIRMS BIRD STRIKE AND DAMAGE, IN WORK TO R&R LH ENGINE.

RT HYD TEMP HIGH , ASSOCIATED WITH THE HYD ENG PUMP FAIL. EMERGENCY DECLARED. MX C/A: VERIFIED THE RH EDP FAILED CARRIED OUT THE GVI OF THE EDP AFTER DRY OPERATION. VERIFIED THE RH EDP FAILED IRW CL 300 AMM 05-51-29. REMOVED AND REPLACED THE RIGHT HAND EDP. REMOVED AND REPLACED THE CASE DRIAN FILTER MANIFOLD. SERVICED RIGHT HAND HYDRAULIC SYSTEM. OPS AND LEAK CHECK, NO DISCREPANCY NOTED AT THIS TIME IRW CL300 AMM 29-10-00 AND 29-12-01.

APU FIRE INDICATION DISPLAYED DURING APU START ON APPROACH, EMERGENCY DECLARED. R&R FIRE LOOPS AND APU EXHAUST MUFFLER ASSY, SET TO RTS SUN 1/5/25.

ON APPROACH IN TO KGKY ROUGHLY 8000 FT UNDER 248 KNOT PILOTS REPORTED WHILE ATTEMPTING TO START THE APU THEY RECEIVED AN APU FIRE WARNING. THEY PLACED THE APU START SWITCH BACK TO OFF AND NOTICED THE RPMS AT 20 PERCENT AND WARNING EXTINGUISHED. VERIFIED NO BOTTLE WAS BLOWN AND ON LANDING STARTED THE APU WITH NO ISSUES TWICE ALONGSIDE MX CONTROL. MX C/A: PERFORMED MDC DOWNLOADS AND PROVIDED TO BOMBARDIER CRC. C/W FIRE EXT SYS F/T WITH SATISFACTORY RESULTS, NO DEFECTS NOTED. C/W APU ENCLOSURE AND TAIL PIPE GVI, NO DEFECTS NOTED.

LEFT CYAN THRUST REVERSER UNLOCKED CAPTION ILLUMINATED IN FLIGHT ON DEPARTURE ACCELERATING THROUGH 200 KNOTS AT 2000 FOOT ELEVATION AGL. MX C/A: APPLIED MEL 78-31-01, DEACTIVATED LH TR IAW GL5000 GVFD AMM TASK 78-30-00-040-802.

FLAPS STUCK AT 3 DEGREES WHILE IN FLIGHT. FLAPS RESET ON GROUND BUT NEEDS FUNCTIONAL CHECK BEFORE NEXT FLIGHT. MX C/A: C/W FLAPS FUNCTIONAL CHECK IN REF CH350 TASK 27-52-00-710-802 WITH NO DISCREPANCIES NOTED. NO RECURS TO DATE.

STAB TRIM FAULT (CYAN CAS) FOLLOWED BY AP STAB TRIM FAIL (AMBER CAS). MX C/A: REMOVED AND REPLACED HST ECU WITH A REPAIRED UNIT PER CL300 AMM 27-41-21-000/400-801. ALL OPS CKS AND F/T GOOD.

DURING MX CK FLT FOLLOWING 7500L INSP, LEFT PYLON BLEED LEAK (RED CAS MESSAGE). MX C/A: LEFT PYLON BLEED LEAK (RED CAS MESSAGE). REPLACED 2 EA NEW E-SEALS AND 2 EA NEW V BAND CLAMPS LH INTERMEDIATE VALVE IAW CL 300-AMM 36-11-05-000-801, 36-11-00-790-801 AND 36-11-00-710-801. OPERATIONAL AND LEAK CHECK GOOD.

SMOKE IN CABIN. PACK FAIL. MX C/A: R&R AIR CYCLE MACHINE (ACM).

DIRTY SOCK SMELL FROM CABIN AIR SYSTEM WHILE APU IS ON. MX C/A: FOUND APU OIL SEAL LEAK VIA BOROSCOPE INSP. R&R APU.

AMBER RIGHT GEN FAIL ON DEPARTURE ID#=B3-007769. MX C/A: SWAPPED LEFT AND RIGHT GCU'S. NO FIX. PERFORMED WIRING CHECKS PER FIM. NO FAULTS NOTED. RETURNED GCU'S TO ORIGINAL POSITIONS AND SWAPPED LEFT AND RIGHT ENGINE GENERATORS. NOTE: RIGHT GEN MAKES CLUNKING NOISE WHEN MOVED BY HAND. RAN ENGINES. RIGHT GEN OPS CHECKS GOOD. WORK DONE REF CHALLENGER 300 MM CHAPTER 24-31-05. P/N OFF - A3579-102, S/N OFF= 1476. P/N ON= A3579-103 S/N ON= 1881. NOTE: FAULT FOLLOWED GEN RIGHT TO LEFT TW = TL-106339... **R&R LH ENG GENERATOR.

RT ENG FAILURE DUE TO LOW OIL PRESSURE. RED MESSG “ RT ENG OIL PRESS LOW “ INDICATION. PICS WERE PROVIDED. MX C/A: FOUND OIL CAP CHAIN PROTRUDING FROM UNDER CAP. R&R CAP VIA SB AS907-79-9007 WITH MOD P/N 3036061-5. SERVICED OIL. REMOVED, INSPECTED, REPLACED ENGINE OIL FILTER. PERFORMED ENGINE FADEC TREND DOWNLOADS. ENGINE RUN AND LEAK CHECKS GOOD.

SMOKE IN CABIN AND COCKPIT. DECLARED AN EMERGENCY. PACK OVER HEAT EICAS ON GROUND. MX C/A: R&R AIR CYCLE MACHINE (ACM), OPS CK GOOD, NO DEFECTS.

AFTER APU START AND SEEMED STABLE PRIOR TO BLEED TRANSFER RECEIVED APU FIRE EICAS MESSAGE. JUST A FEW SECONDS LATER LIGHT WENT OUT. DID NOT USE FIRE SUPPRESSION SYSTEM. MX C/A: COMPLIED WITH BOMBARDIER RECOMMENDATIONS. GAINED ACCESS TO APU AND CHECK FOR ANY EVIDENCE OF A ACTUAL FIRE IN THE APU COMPARTMENT, NONE NOTED. COMPLIED WITH CONTINUITY TEST & INSULATION RESISTANCE TEST OF THE SENSING ELEMENTS IAW KIDDE AEROSPACE CMM 26-11-88, NO DEFECTS NOTED. AS PER ADVISORY WIRE REF AW300-26-0327, REMOVED FIRE EXTINGUISHER CONTROL UNIT AND INSTALLED A NEW CONTROL UNIT IAW CH 300 AMM 26-11-01-000-801/400-801. PERFORMED OPERATIONAL TEST OF FIRE DETECTION AND EXTINGUISHING (FIREX) SYSTEM IAW CH 300 AMM 36-11-00-710-801. OPS CHECK SATISFACTORY.

ON TAKEOFF WITH ENGINE BLEEDS ON CLIMBING OUT THE CABIN STARTED TO FILL WITH THICK SMOKE. FO RAN THE QRH AND SHUT DOWN THE ENGINE BLEEDS. SMOKE STOPPED PUMPING IN AND ONCE WE DUMPED THE CABIN THE SMOKE EVACUATED. UPON LANDING WE GOT A PACK OVERHEAT WHILE WE WERE SHUTTING THE AIRCRAFT DOWN ON PARK. MX C/A: R&R AIR CYCLE MACHINE, OPS CK GOOD.

AT 43K FEET NOTICED A SQUEEL FROM THE DOOR. THAT WENT AWAY FOR 5 MINS. THEN GOT THE RED CAS CABIN DIF 9.8. NOTICED CABIN PRESSURE WAS 12K SWITCHED TO ADC 2 NO CHANGE. PRESSURE CONTINUED TO CLIMB TO 12.5 . ALL MASKS DROPPED. DESCENDED 10K AND CABIN PRESSURE WENT TO 8.8. MX C/A: R&R MED INFLATABLE SEAL (P/N 1159SCB420-15 S/N OFF 482, ON 605). ALSO, R&R MED SEAL CONTROL VALVE (P/N 115SCH234-1 S/N OFF 460, ON V237), OPS AND LEAK CKS GOOD.

FIRST LEG TEB-LGA NORMAL OPS. AFTER T/O FROM LGA LDG GEAR WOULD NOT RETRACT. NOSE GEAR NOT UP CAS POPULATED WE BROUGHT GEAR DOWN GOT 3 GREEN. TRIED GEAR AGAIN. SAME CAS NOW W NOSE DESPIN CAS. WE FOLLOWED QRH FOR THIS. DIRECTING US TO LDG GEAR FAILURE TO RETRACT CHECKLIST. COMPLETED THIS, DIVERTED SWF. MX C/A: PERFORMED LANDING GEAR HYDRAULIC SELECTOR / DUMP VALVE REMOVAL / INSTALLATION, LANDING GEAR CYCLING OPERATIONAL TEST, LANDING GEAR EMERGENCY EXTENSION SYSTEM FUNCTIONAL CHECK, HYDRAULIC SYSTEM SHUT - OFF VALVE (LEFT AND RIGHT) OPERATIONAL CHECK, HYDRAULIC SYSTEM RESERVOIR (LEFT AND RIGHT) SERVICING, LANDING GEAR EMERGENCY EXTENSION NITROGEN BLOW-DOWN BOTTLE SERVICING AND EMERGENCY LANDING GEAR SYSTEM LINES FLUSH. ALL WORK PERFORMED I.AW. GULFSTREAM G450 AMM 32-39-00, 12-33-00, 12-15-00, 29-15-00, 32-00-00 AND 32-30-03. ALL CHECKS WERE PERFORMED SATISFACTORILY. NO FURTHER DEFECTS NOTED. RII

ON DESCENT, WE HAD RIGHT ESSENTIAL BUSS FAILURE AND RIGHT BATTERY OFF. WE ASKED FOR VECTORS TO A VISUAL RUNWAY DUE TO ELECTRICAL AND NAVIGATION EQUIPMENT. EICAS RED PFD AUTO PILOT FAILURE, FLIGHT DIRECTOR FAILURE, FLIGHT MODE FAILURE... BOTH PROBE FAILURE, FLAPS FAIL, ELECTRIC FAULT, STALL PUSHER OFF, R ESS BUS FAIL, OUTBOUND BRAKE FAIL, TAWS BASIC FAIL, L HYD DC PUMP FAIL, R BATTERY OFF... KTEB CLEARED US FOR VISUAL RNWY 6 AND EMERGENCY EQUIPMENT WERE ROLLED. I STILL HAD BASIC FLIGHT INSTRUMENTS AND GEAR DID FUNCTION AND FLAPS DID EXTEND SO I LANDED THE AIRCRAFT. ON THE GROUND EMERGENCY LIGHTS, FLAPS, PARKING BRAKES WOULD NOT RETRACT OR DISENGAGE. (NOTE: ATC DECLARED EMER FOR CREW) MX C/A: REMOVED & REPLACED FAILED RH DCPC PROTECTION PCB WITH REPAIRED PCB. OPS CHECK GOOD REF BOMBARDIER CL-300 AMM 24-61-77. REMOVED PROTECTION PCB - PN: 3S5CE03Y06/SN: 817F INSTALLED PROTECTION PCB - PN: 3SSCE03Y06/SN: 461F CONDITION: REPAIRED.

PRECAUTIONARY LANDING DUE TO ODOR & LIGHT SMOKE, PACK TEMP HIGH MESSAGE POSTED ON FINAL APPROACH. MX C/A: C/W OVERWEIGHT LANDING INSP; R&R AIR CYCLE MACHINE (ACM), OPS CKS GOOD.

RED LEFT ENG. LOW OIL PRESS LIGHT AT CRUISE FL430. PRESSURE INDICATED APPROX 28 PSI, THEN WENT UP TO 35-36 PSI AND LIGHT WENT OUT. RETARDED THE LEFT THRUST LEVER TOWARDS IDLE AND LIGHT REMAINED OUT, BUT THEN CAME ON THEN BACK OFF 2 OR 3 TIMES. FINALLY IT CAME ON AND STAYED ON. SHUT ENG DOWN INFLT. MX C/A: FOUND OIL CAP REMOVED, SERVICED AND REINSTALLED. ACFT STILL IN WORK WITH STANDARD AERO EVALUATING ENGINE ALONGSIDE HONEYWELL REPS AND MX CONTROL.

DEPARTING OUT OF KJAC THE GEAR DISAGREE DISPLAYED ON THE EICAS AFTER TAKEOFF. THE LEFT GEAR WOULD NOT RETRACT. WE COULD ALSO FEEL AND HEAT THAT THE LEFT GEAR WAS STILL DOWN. RAN THE QRH CHECKLISTS, EXTENDED THE LANDING GEAR, CONFIRMED 3 GREEN “DOWN AND LOCKED” AND RETURNED TO KJAC. MX C/A: IN WORK, TROUBLESHOOTING WITH MX VENDOR AND ACCORDING TO MDC DOWNLOADS AND BAS-CRC, DOWN LOCK SENSORS NEED TO BE RIGGED. (~RTS 1/29)