N277QS

Part: REGULATOR VALVE — BINDING (CABIN AIR FLOW) · airframe 13,024 hrs · 8,093 cycles

LOW AIRFLOW FROM OVERHEAD AIR GASPERS. RAN AIRCRAFT AND THOUGHT IT WAS LOW OUTPUT FROM AIR COOLING TURBINE. SWAPPED AIR COOLING TURBINE WITH LIKE UNIT FROM ANOTHER AIRCRAFT. RAN AIRCRAFT AGAIN, RESULTS WERE THE SAME. TROUBLE SHOT SYSTEM AND FOUND GASPER PRESSURE REGULATION VALVE WAS STUCK IN THE ALMOST FULLY CLOSED POSITION. REMOVED VALVE FROM AIRCRAFT AND FOUND EXCESSIVE CORROSION ON THE VALVE ASSEMBLY. REPLACED VALVE, REINSTALLED ORIGINAL COOLING TURBINE UNIT, RAN AIRCRAFT, SYSTEM OPERATES NORMALLY. RETURNED AIRCRAFT TO SERVICE.

Part: PROXIMITY SWITCH — UNSERVICEABLE (MLG) · airframe 12,184 hrs · 7,562 cycles

MAIN LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF. REMOVED PROXIMITY SWITCH, 5GBC, PN: D22858000-1, SN: B931 DUE TO INTERNAL FAILURE. INSTALLED REPAIRED PROXIMITY SWITCH AS STATED ABOVE IAW F2000 MM 32-61-49-900-801. REMOVED PCB CARD, 415JE, PN: C1381, SN: 3305 DUE TO INTERNAL FAILURE AND INSTALLED NEW PCB CARD AS STATED ABOVE IRW F2000 MM 32-30-00-720-801. REMOVED PCB CARD, 417JE, PN: FE422, SN: 18920 DUE TO INTERNAL FAILURE AND INSTALLED NEW PCB CARD AS STATED ABOVE IRW F2000 MM 32-30-00-720-801. RIGGING/ADJUSTMENT OF PROXIMITY SWITCHES 5GBC AND 5GBD ARE REQUIRED. ADJUSTED PROXIMITY SWITCHES 5GBC AND 5GBD IAW F2000 MM 32-61-49-900-80. TESTING OF THE PROXIMITY SWITCHES 5GBC AND 5GBD, AND FUNCTIONAL TEST OF EXTENSION AND RETRACTION OF LANDING GEARS AND DOORS ARE REQUIRED. TESTED PROXIMITY SWITCHES 5GBC & 5GBD IAW F2000 MM 32-61-49-900-801 AND FUNCTIONAL TEST OF EXTENSION AND RETRACTION OF LANDING GEARS AND DOORS IAW F2000 MM 32-30-00-720-801. FUNCTIONAL TESTS WERE SATISFACTORY, OK FOR SERVICE. PARTS REMOVED: CIRCUIT BOARD, PN: FE422, SN: 18920, CIRCUIT BOARD, PN: C1381, SN: 3305, PROXIMITY SWITCH, PN: D22858000-1, SN: B931.

Part: UNKNOWN — SPARKS (C/B PANEL) · airframe 11,366 hrs · 7,029 cycles

LIGHTNING STRIKE CAUSED SPARKS IN COCKPIT WHICH TRIPPED THE ANTI COLLISION FIN CIRCUIT BREAKER & WINGS CIRCUIT BREAKER. LEFT BLACK SINGE MARKS ON PANEL. BURNED ODOR IN COCKPIT & CABIN, NO FIRE OR SMOKE PRESENT. COMPLIED WITH AMM TASK 05-50-00-200-803. ACCESSED THE ANTI-COLLISION CIRCUIT WIRING IN VERTICAL STAB, INSPECTED, NO DEFECTS NOTED. ACCESSED COCKPIT OVERHEAD SWITCH PANEL & CIRCUIT BREAKER PANEL. REPLACED ANTI-COLLISION SWITCH, WINGS ANTI-ICE SWITCHES, WIRING FROM ANTI-COLLISION. SWITCH TO .180' CONNECTOR, 10 AMP VERTICAL ANTI-COLLISION LIGHT CIRCUIT BREAKER & 5 AMP WINGS ANTI-ICE CIRCUIT BREAKER IAW TASK 20-95-00-910-802. OPS CHECKED ANTI-COLLISION LIGHT GOOD IAW TASK 33-40-00-710-801.

Part: CIRCUIT BOARD — FAILED (MLG) · airframe 10,280 hrs · 6,359 cycles

AFTER TAKEOFF, NOSE GEAR WOULD NOT RETRACT. MAIN GEAR RETRACTED & GEAR DOORS REMAINED OPEN. JACKED ACFT, CLEARED ALL FAULTS. CYCLED GEAR SEVERAL TIMES, RT BRAKE & RT STEERING INDICATORS RED. DOWNLOADED FAULTS & FOUND FAULT CODE 433 TO COME BACK CONSISTENTLY. JACKED NOSE UP & DOWN MULTIPLE TIMES TO ENSURE FULL STRUT EXTENSION EACH TIME, STRUT EXTENDED TO 284 MM EACH TIME. REMOVED MLG CONTROL PCB & FOUND SIGNS OF OVERHEATING. TROUBLESHOT THE LANDING GEAR CONTROL PCB FOUND SEVERAL VOLTAGES READING INCORRECT THAT INCLUDED OUTPUT SIGNALS. INSTALLED NEW MLG PCB 10GW, PERFORMED TROUBLESHOOTING PROCEDURE & FOUND ALL VOLTAGES TO BE READING CORRECT. PERFORMED FUNCTIONAL CHECK OF EXTENSION & RETRACTION OF MLG & DOORS WITH NO DEFECTS NOTED. ALIGNED IRS'S & RESET INDICATORS, NO LT & RT RED BRAKE INDICATIONS NOTED. LT & RT BSCU OPS CHECKED GOOD. SWUNG GEAR MULTIPLE TIMES & ALL MLG FUNCTIONS ARE NORMAL.

Part: LANDING GEAR — FAILED (NLG) · airframe 6,824 hrs · 4,169 cycles

AFTER NORMAL TAXI AND TAKEOFF, GEAR HANDLE WOULD NOT RELEASE (MULTIPLE ATTEMPTS). RETURNED FOR LANDING WITH "AUTOSLATS" ANNUCIATOR. APPEARED TO HAVE NOSEWHEEL STEERING UP TO CLEARING RUNWAY, AT K5, RAN OUT OF STEERING. LAST 1000 FT OF ROLLOUT, PLANE SHUTTERED. ACFT HAD TO BE TOWED RAMPSIDE. ALL 4 BSCU AND STEERING WERE RED. NLG ASSY FOUND TO BE UNSERVICEABLE. REMOVED NLG ASSY. INSTALLED "INSPECTED" NLG ASSY IAW MM 32-203. OPS AND LEAK CK'D GD.

Part: APU — ODOR · airframe 6,371 hrs · 3,902 cycles

WITH APU RUNNING AND BLEED AIR IN AUTO THERE IS A STRONG ODOR OF OIL. THERE IS ALSO MULTIPLE DROPS OF OIL ON THE FWD SERVICE COMP FLOOR JUST AHEAD OF THE FLY AWAY KIT BAGS. REMOVED APU DUE TO INTERNAL OIL LEAK AND INSTALLED A REPAIRED UNIT. IAW MM 49-000 ALL OPS/LEAK CHECKS GOOD AT THIS TIME.

Part: COOLING FAN — MALFUNCTIONED (COCKPIT) · airframe 5,752 hrs · 3,523 cycles

UPON LANDING, RED TEMP FOR CAPTIANS MFD DISPLAYED. IN ADDITION A SLIGHT SMELL OF ELECTRICAL SMOKE WAS EVIDENT UPON SHUTDOWN OF AVIONICS. T/S FOUND PILOTS MFD COOLING FAN INOP. REMOVED INOP FAM AND INSTALLED A NEW FAN. OPS CHECK GOOD I/A/W DA2000 MM 34-001.

Part: PRESSURE SWITCH — OUT OF TOLERANCE (BRAKES) · airframe 4,946 hrs · 3,030 cycles

BRAKE PRESS ANNUNCIATOR TRIGGERED T/O CONFIG DURING TAKEOFF BEFORE 50 KTS. TROUBLESHOT BRAKE SYSTEM TO NR 2 SYSTEM BRAKE PRESSUE SWITCH. REMOVED AND REPLACED NR 2 SYSTEM BRAKE PRESSURE SWITCH WITH A (NEW) UNIT IAW MM 32-42-00.

Part: PRESSURE SWITCH — LEAKING (NR 1 HYD SYSTEM) · airframe 3,538 hrs · 2,160 cycles

TOTAL LOSS OF HYDRAULIC FLUID ON THE NR 1 HYD SYSTEM IN FLIGHT. REMOVED NR 1 HYDRAULIC SYSTEM PRESSURE SWITCH CODE (L30GI) P/N 7G979, S/N 1722 AND REPLACED WITH NEW SWITCH P/N 7G979 , S/N 2784. REMOVED NR 1 & NR 2 ENGINE HYDRAULIC PUMPS AND INSPECTED FLUID AND PUMP CONDITION. NO DEFECTS NOTED. RE-INSTALLED NR 1 & NR 2 ENGINE HYDRAULIC PUMPS. PERFORM OPERATIONAL CHECKS AND LEAK CHECKS ON NR 1 & NR 2 ENGINE HYDRAULIC SYSTEM IAW 29-104 & 29-100, NO DEFECTS NOTED. SERVICED HYDRAULIC SYSTEMS 1 & 2 TO CORRECT LEVELS WITH 5606 FLUID IAW 29-112.

Part: HYDRAULIC SYSTEM — LEAKING (NR 1) · airframe 3,486 hrs · 2,128 cycles

COMPLETE LOSS OF THE NR 1 HYDRAULIC SYSTEM IN FLIGHT AT FL410. HYD QTY DROPPED TO 15 PERCENT, PRESSURE FELL TO 100PSI. UPON LANDING HYDRAULIC FLUID NOTED ALL OVER BELLY OF ACFT AND COVERING INSIDE OF "HELLHOLE" COMPLIED WITH NORMAL AND ABNORMAL CHECKLIST PER AFM.

Part: ACTUATOR — FAILED (PITCH FEEL) · airframe 2,389 hrs · 1,485 cycles

DURING TAKEOFF ROLL WITH POWER LEVERS IN TAKEOFF FOR APPROXIMATELY 10-15 SECONDS AND AT 40 KNTS NO TAKEOFF CONFIGURATION WARNING ACTIVATED. REASON FOR WARNING CANNOT BE DETERMINED, CONFIGURATION WAS NORMAL FOR ALL SYSTEMS. REPLACED PITCH FEEL ACTUATOR IAW F2000 PROCEDURE 27-318. COMPLIED WITH OPS CHECKS IAW F2000 PROCEDURES 27-014, 31-301, 27-308, 27-309, 27-312, & 27-314, ALL CHECKS SATISFACTORY.

Part: WARNING HORN — ACTIVATED (CONFIGURATION) · airframe 2,389 hrs · 1,485 cycles

DURING T/O ROLL WITH POWER LEVERS IN T/O FOR APPROXIMATLEY 10-15 SECONDS AND AT APPROXIMATELY 40KNTS (NO TAKE OFF) CONFIG WARNING ACTIVATED REASON FOR WARNING CANNOT BE DETERMINED, CONFIGURATION WAS NORMAL FOR ALL SYSTEMS.- ITEM IS UNDER INVESTIGATION.