N369QS

Part: DOOR — MALFUNCTIONED (NLG) · airframe 13,749 hrs · 9,139 cycles

NLG DOOR: CRUISING AT FL410 THE NOSE GEAR LANDING UNLOCK LIGHT CAME ON FOR ABOUT 1 SECOND AND A LOUD AND ABRUPT CLOSING OR OPENING AND CLOSING OF THE NOSE GEAR DOORS OCCURRED. CORRECTIVE ACTION; COMPLIED WITH MULTIPLE GEAR SWINGS WITH NO ISSUES NOTED. COMPLIED WITH THE TS GUIDE FOR A BUMP AND ALL CHECKS GOOD. STRUT MEASUREMENT IS CORRECT, MANUAL RELEASE CABLE IS RIG PROPERLY. DURING GEAR SWINGS COMPLIED WITH MANUAL RELEASE WITH NO ISSUES. ALL WORK DONE PER 680 AMM 32-00-00. NO FURTHER MAINTENANCE REQUIRED AT THIS TIME.

Part: STARTER GEN — FAILED (ZONE 400) · airframe 13,543 hrs · 8,973 cycles

DURING CLIMB DC EMER BUSCAS R ILLUMINATED AT APPROX 23000 FT. ALSO AMBER MESSAGES HYDRAULIC VOLUME LOW, ENGINE CONTROL FAULT R, FUEL MOTIVE VLV FAIL R, PUTCH/ROLL DISCONNECT AND DC GEN OFF R MESSAGES ILLUMINATED. REMOVED AND REPLACED R/H STARTER/GEN !WITH AN "OVERHAULED" UNIT AW AMM 80-10-00. THIS DID NOT FIX THE NO START ISSUE HOWEVER, WE FOUND THAT CONNECTOR "PE002" ON THE R/H ENGINE PYLON HAD MULTIPLE BENT PINS AND SIGNS OF ARCING. REPLACED CONNECTOR PE002 IAW AMM 20-10-75, 20-30-20 AND 20-30-25.

Part: SPAR CAP — CORRODED (VERTICAL STAB) · airframe 13,524 hrs · 8,953 cycles

BLENDED TWO CORRODED AREAS OF THE RH AFT SPAR CAP OF THE VERTICAL STABILIZER, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED AND PRIMED BLENDED AREAS PER REQUEST FOR TECHNICAL SERVICES REPORT.

Part: COUNTERBALANCE — BROKEN (MAIN DOOR) · airframe 13,504 hrs · 8,936 cycles

MAIN DOOR CABLE: LEFT HAND CABLE COUNTER BALANCE MECHANISM BROKE. UNABLE TO RAISE THE DOOR FROM THE INSIDE. REMOVED MAIN CABIN DOOR STEPS. LUBED THE MAIN DOOR HANDLE. INSTALLED MAIN CABIN DOOR STEPS. OPS CHECK GOOD. NO DEFECTS NOTED, REF CESSNA 560XL AMM 12·20-40 AND 52-10-17

Part: STRINGER — CORRODED (ACM BAY) · airframe 13,504 hrs · 8,935 cycles

CORROSION FOUND ON THE UPPER FUSELAGE STRINGER JUST FORWARD AND AFT OF THE ACM. CORROSION ALSO ON RIVETS THAT SUPPORT THE DOUBLER FOR THE SKIN AROUND THE ACM. REPAIR TAIL CONE STRINGER PER ERO-977739. BLENDED AND REMOVED CORROSION FROM STRINGER 2R. THE REMAINING THICKNESS WAS OUT OF LIMITS PER SRM 51-70-02 AND REQUIRED SUBMITTAL TO AQRD FOR REPAIR. COMPLIED WITH AQRD ERO-977739 REV A. ALL WORK DONE IAW SRM 51-70-02, AQRD ERO 977739 REV IR, & FORM 8110-3. PERFORMED AN EDDY CURRENT INSP FOR CRACKS & REMAINING CORROSION ON BLENDED AREAS COMMON TO UPPER SKIN & BONDED STRINGER IAW NDTM REV 9, PART 6_TASK 20-00-02, NO CRACKS OR CORROSION NOTED. PERFORMED AN ULTRASONIC INSP FOR REMAINING MATERIAL THICKNESS ON BLENDED AREAS IAW PART 4_TASK 20-00-01. PERFORMED AN EDDY CURRENT INSP FOR CRACKS & REMAINING CORROSION ON BLENDED AREAS FASTENER HOLES, & INNER BONDED STRINGER FLANGE, IAW NDTM REV 9, PART 6_TASK 20-00-02, & AQRD ERO-977739 STEP 6, NO CRACKS OR CORROSION NOTED. PERFORMED AN ULTRASONIC INSPN FOR REMAINING MATERIAL THICKNESS ON BLENDED AREAS IAW PART 4_TASK 20-00-01.

Part: SPAR — CORRODED (ZONE 300)

EXFOLIATION CORROSION FOUND ON THE LH AND RH LOWER VERTICAL SPAR CAPS.

Part: SPAR — CORRODED (ZONE 300) · airframe 13,504 hrs · 8,935 cycles

EXFOLIATION CORROSION FOUND ON THE LH AND RH LOWER VERTICAL SPAR CAPS. ADDITIONAL TIME FOR REASSEMBLY OF THE VERT STAB REAR SPAR IAW TEXTRON FR-680-0081-12979. REMOVED FASTENERS AND BLENDED VISIBLE CORROSION FROM THE LH AND RH VERTICAL STABILIZER LOWER AFT SPAR CAPS. THE REMAINING THICKNESS OF THE BLENDED AREA IS ACCEPTABLE PER TEXTRON FR-680-0081-12979 REV "-" DATED DEC. 19 2023. REINSTALLED FASTENERS AND RESTORED PROTECTIVE FINISHES IN THE WORKED AREAS. ALL WORK DONE IAW TEXTRON FR-680-0081-12979 REV "-" DATED DEC. 19 2023, FORM 8100-9 DATED DEC. 20 2023, CESSNA 680 SRM 51-40-03, AND SPM 51-30-10. THIS IS CONSIDERED A MAJOR REPAIR. PERFORMED AN EDDY CURRENT INSPECTION FOR CRACKS AND REMAINING CORROSION ON BLENDED AREAS LOCATED ON THE LH AND RH LOWER VERTICAL SPAR CAPS IN RUDDER CHANNEL, IN ACCORDANCE WITH CESSNA 680 NDTM (REV 9 JUN 15, 2021), PART 6_TASK 20-00-02, NO CRACKS NOR CORROSION NOTED. PERFORMED AN ULTRASONIC INSPECTION FOR REMAINING MATERIAL THICKNESS ON BLENDED AREAS IN ACCORDANCE WITH PART 4_TASK 20-00-01, MAPPED MEASUREMENTS ON BLENDED SURFACE

Part: RIB — CORRODED (ZONE 500) · corrosion level 2 · airframe 13,504 hrs · 8,935 cycles

CORROSION FOUND AROUND MULTIPLE HI-LOKS FASTENERS FOR THE LH AND RH OUTBOARD WHEEL WELL WING RIBS. REMOVED ALL SIGNS OF CORROSION FROM THE LH AND RH OUTBOARD WHEEL WELL WING RIBS AT WS 67.25. REMOVED AND REPLACED FASTENERS IAW CESSNA 680 SRM 51-40-03. RESTORED PROTECTIVE COATINGS TO INNER WHEEL WELL LOCATIONS IAW CESSNA 680 SRM 51-20-01. THE REMAINING THICKNESS OF THE LH AND RH WS 67.25 RIBS ARE ACCEPTABLE IAW TEXTRON MINOR MEMO DQ42485M1 DATED 12/20/2023. THIS IS A MINOR REPAIR.

Part: DOOR — CORRODED (THRUST REVERSER) · corrosion level 2 · airframe 13,504 hrs · 8,935 cycles

DURING THE 3C INSPECTION, FOUND THE LH UPPER T/R BUCKET AFT EDGE CORRODED. REPAIRED DAMAGE IN ACCORDANCE WITH NORDAM FIELD ENGINEERING DISPOSITION NTRSD-23TP-124, CORROSION REMOVAL ON LH UPPER TR DOOR CLOSEOUT, DATED 25 MAY 2023. THIS IS A MINOR REPAIR. SEE DUNCAN AVIATION WORK ORDER R5SXA SQUAWK 104 FOR DETAILS.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · corrosion level 2 · airframe 13,504 hrs · 8,935 cycles

DURING REMOVAL OF RH ELEVATOR WEDGE PANEL FOUND SPOTS OF CORROSION ON TOP AND BOTTOM OF STAB T/E WHERE WEDGE PANEL CONNECTS.. REPAIRED RH HORIZONTAL STABILIZER TRAILING EDGE RIB AT RBL 8.8 PER TEXTRON FIELD REPAIR FR-680-0081-11971 REV- DATED 26 MAY 2023, "FIELD REPAIR - CORROSION, HORIZONTAL STABILIZER, RH UPPER AND LOWER SKIN BOND ASSEMBLIES AND RIB, NEAR HSS 29." THIS IS A MAJOR REPAIR.

Part: DOOR — CORRODED (MLG) · corrosion level 2 · airframe 13,504 hrs · 8,935 cycles

DURING INSPECTION 3A, FOUND CORROSION AROUND THE RIVETS ON THE LOWER SIDE OF THE RH MLG DOOR. REPAIRED CORROSION BY BLENDING ON RH MLG DOOR IN ACCORDANCE WITH AQRD RFTS-108314 N369QS (680-0081) RIGHT HAND MLG DOOR CORROSION REV 0, DATED 06 JUNE 2023. THIS IS A MINOR REPAIR.

Part: NONE — NONE · airframe 12,338 hrs · 8,207 cycles

MAIN DOOR: MAIN DOOR IS NOT TENSIONED PROPERLY. THE LAST 40% OF TRAVEL, WHILE CLOSING, TAKES QUITE A BIT OF FORCE TO CLOSE. // SIGNOFF// ADJUSTED MAIN DOOR TENSION IAW CE-680 AMM 52-10-50

Part: NOT REPORTED — NOT REPORTED · airframe 12,185 hrs · 8,111 cycles

CABIN EMERG LIGHT: FORWARD, FLOOR LEVEL EMERGENCY LIGHT AT THE GALLEY AREA IS INOP. LIGHT ASSEMBLY MUST HAVE BEEN KICKED. IT IS LAYING ON THE CARPET OUT OF ITS RECESSED, HIDDEN POSITION. THE REMAINING FLOOR EMER LIGHTS ARE OPERQTIONAL "CORRECTIVE ACTION" REMOVED AND REPLACED FWD R/H DROP ISLE LIGHT THAT WAS FOUND DAMAGED AND INOP WITH NEW ASSEMBLY, OPERATIONAL CHECKS GOOD, ALL WORK PERFORMED IAW CE 680 AMM 33-20-00. NO FURTHER ACTION REQUIRED.

Part: SPAR CAP — CORRODED (VERTICAL STAB) · airframe 11,178 hrs · 7,457 cycles

FOUND CORRODED AREA ON LT SPAR CAP EXTRUSION OF THE VERTICAL STABILIZER REAR SPAR. REMOVED RIVET OR ACCESS, MECHANICALLY BLENDED CORRODED AREA, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED REPAIR AREA AND INSTALLED NEW RIVET, PER TEXTRON REPAIR MEMO.

Part: TRACK — DEFECTIVE (LAVATORY DOOR) · airframe 11,130 hrs · 7,417 cycles

LEFT SIDE LAV DOOR IS OFF TRACK AND STUCK IN PARTIALLY EXTENDED POSITION. SIGN OFF. INSTALLED A NEW POPUP CARRIER TRACK AND A NEW POPDOWN CARRIER TRACK IN THE LEFT AFT DIVIDER POCKET DOOR. MX IAW CE-680 MM 25-20-10, OPS CHECK GOOD.

Part: DOWNLOCK SWITCH — FAILED (LT MLG) · airframe 10,640 hrs · 7,092 cycles

LEFT MLG LANDING GEAR RETRACTION DID NOT RETRACT - ON GEAR RETRACTION LEFT MAIN GREEN DOWN LIGHT STAYED ON. NO OTHER LIGHTS ON. GEAR EXTENSION WAS THEN NORMAL. JACKED AIRCRAFT AND RETRACKED GEAR LMG GREEN LIGHT REMAINED ON. REMOVED CONNECTOR ON LMG AND CHECKED SWITCH FOUND DOWNLOCK SWITCH FAULTY. REPLACED LEFT GEAR DOWN AND LOCKED SWITCH WITH NEW IAW CE-680 MM CH 32-60-00. PERFORMANCED GEAR SWINGS WITH NO DEFECTS NOTED.

Part: CONTROL UNIT — CONTAMINATED (STAB TRIM) · airframe 10,003 hrs · 6,621 cycles

PRIMARY STAB TRIM FAIL ON CLIMB OUT. CREW ACTIVATED SECONDARY TRIM AND RETURNED FOR LANDING. REMOVED AND REPLACED THE HORIZONTAL TRIM ACTUATOR AND HORIZONTAL TRIM ACTUATOR CONTROL UNIT IAW 680 AMM 27-40-00, OPERATIONAL AND TRAVEL CHECK GOOD.

Part: BULB — INOPERATIVE (MLG INDICATOR) · airframe 9,627 hrs · 6,385 cycles

RIGHT MLG EXTENSION DID NOT EXTEND, ON GEAR EXTENSION, THE GREEN RT LIGHT DID NOT ILLUMINATE. THE LANDING GEAR WILL NOT EXTEND CHECKLIST WAS REFERENCED AND COMPLETED, BUT THE RT GREEN LIGHT REMAINED OFF. THE LANDING GEAR PORTION OF THE ROTARY TEST WAS THEN SELECTED, WHICH ALSO DID NOT ILLUMINATE THE RT LIGHT OR THE GEAR UNSAFE HORN. THE FLAPS WERE THEN SELECTED TO 35 DEGREES WITH THE THROTTLES AT IDLE, WHICH ALSO DID NOT TRIGGER THE UNSAFE HORN. THE CONTROL TOWER STATED THAT ALL THREE GEAR APPEARED TO BE DOWN. A LANDING WAS ACCOMPLISHED WITH NO PROBLEMS. FOUND THE RT LANDING GEAR DOWN ANNUNCIATOR BULBS TO BE INOPERATIVE. REPLACED BOTH BULBS IAW AMM 33-10-00, OPS CHECKED GOOD.

Part: UNKNOWN — MALFUNCTIONED (NLG) · airframe 9,314 hrs · 6,161 cycles

NLG LANDING GEAR RETRACTION DID NOT RETRACT - AFTER TAKEOFF UPON GEAR RETRACTION IT FELT AND SOUNDED LIKE THE NOSE WHEEL GEAR WOULD NOT RETRACT. THE UNSAFE RED LIGHT FLASHED ALONG WITH A BANGING NOISE AND POUNDING FROM THE NOSE COMPARTMENT. EXTENDED THE GEAR WITH NO ISSUES AND RETURNED TO LAND. WE FOUND NOTHING WRONG WITH A VISUAL INSPECTION AT THE RAMP. COULD NOT DUPLICATE ANY NOSE LANDING GEAR DISCREPANCIES.

Part: SKIN — CORRODED (LT WING) · airframe 8,935 hrs · 5,904 cycles

LEFT WING LOWER SKIN CORRODED. REPAIRED IAW DOCUMENT DQ10493M1.

Part: SKIN — CORRODED (LT WING)

LEFT WING LOWER CENTER SKIN CORRODED. REPAIRED IAW ENGINEERING LETTER DQ10596M1.

Part: STRINGER — CHAFED (LT WING) · airframe 8,935 hrs · 5,904 cycles

LT WING LOWER OUTBOARD STRINGER 11, WS 37. REPAIRED IAW IAW DQ10484M1 .

Part: SKIN — CORRODED (LT WING) · airframe 8,935 hrs · 5,904 cycles

LEFT UPPER WING SKINS CORRODED. REPAIRED IAW S-680-0081/14RD, MAJOR REPAIR.

Part: SKIN — CORRODED (BS 268-509) · airframe 8,935 hrs · 5,904 cycles

RT AND LT AFT FUSELAGE SKIN CORRODED BS 268 - 509. REPAIRED IAW ENGINEERING LETTER DQ10372M1.

Part: SKIN — CORRODED (FUSELAGE) · airframe 8,935 hrs · 5,904 cycles

FUSELAGE SKIN CORRODED

Part: SKIN — CORRODED (ZONE 200) · airframe 8,935 hrs · 5,904 cycles

UPPER FUSELAGE SKIN CORRODED. REPAIRED IAW ENGINEERING LETTER DQ10372M5R1.

Part: STRINGER — DAMAGED (LT WING) · airframe 8,935 hrs · 5,904 cycles

LEFT WING LOWER OUTBOARD STRINGER 11, WS 37. REPAIRED IAW DQ1048M1.

Part: SKIN — CORRODED (RT WING) · airframe 8,935 hrs · 5,904 cycles

RIGHT WING LOWER SKIN CORRODED. REPAIRED IAW ENGINEERING LETTER DQ10472M1.

Part: SKIN — CORRODED (BS 485-528) · airframe 8,935 hrs · 5,904 cycles

AFT FUSELAGE SKIN CORRODED, BS 485- 528. REPAIRED IAW ENGINEERING LETTER DQ10372M2.

Part: SKIN — CORRODED (FUSELAGE) · airframe 8,935 hrs · 5,904 cycles

FORWARD FUSELAGE CORROSION O2 SERVICE DOOR AND LEFT SIDE FS 316 ENGINEERING LETTER DQ10520M1 DATED DECEMBER 15, 2017.

Part: SKIN — CORRODED (ZONE 200) · airframe 8,935 hrs · 5,904 cycles

SKIN CORRODED. REPAIRED IAW ENGINEERING LETTER 10372M4R1.

Part: STRUCTURE — DAMAGED (LT WING LE) · airframe 8,935 hrs · 5,904 cycles

LEFT WING LEADING EDGE CUFF OVERSIZED ATTACH HOLES. REPAIRED IAW ENGINEERING LETTER DQ10582M1.

Part: SKIN — CORRODED (RT WING) · airframe 8,935 hrs · 5,904 cycles

RIGHT UPPER WING SKIN CORRODED. REPAIRED IAW REPORT S-680-0081/12RD.

Part: SPAR — CHAFED (VERTICAL STAB) · airframe 8,935 hrs · 5,904 cycles

VERTICAL FIN AFT SPAR CAP CHAFED. REPAIRED IAW REPORT S-680-0081/10RD.

Part: SKIN — CORRODED (VERTICAL STAB) · airframe 8,935 hrs · 5,904 cycles

VERTICAL STABILIZER LT SKIN CORRODED. REPAIRED IAW REPORT S-680-0081/11RD

Part: SKIN — CORRODED (LT WING) · airframe 8,935 hrs · 5,904 cycles

LEFT UPPER WING SKIN CORRODED.

Part: SPAR — CORRODED (VERTICAL STAB) · airframe 8,935 hrs · 5,904 cycles

REPAIR OF THE VERTICAL FIN AFT SPAR WEB CORROSION. REPORT S-680-0081/09RD, REV A.

Part: SKIN — CORRODED (FUSELAGE) · airframe 8,935 hrs · 5,904 cycles

RIGHT LT AFT FUSELAGE SKIN CORRODED, UPPER TAIL SECTION. REPAIRED IAW EL DQ10372M3 RRL.

Part: STRUCTURE — CORRODED (CARGO DOOR) · airframe 8,935 hrs · 5,904 cycles

CARGO DOOR HAD MINOR CORROSION.

Part: SKIN — CORRODED (LT WING) · airframe 8,935 hrs · 5,904 cycles

LEFT WING SKIN CORRODED. REPAIRED.

Part: SKIN — CORRODED (RT ELEVATOR) · airframe 8,610 hrs · 5,680 cycles

ACCOMPLISHED MINOR CORROSION REPAIRS TO RIGHT ELEVATOR SKINS IAW ENGINEERING LETTER DQ6553M1.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 8,610 hrs · 5,680 cycles

ACCOMPLISHED MINOR CORROSION REPAIRS TO LEFT AND RIGHT UPPER AND LOWER HORIZONTAL STABILIZER SKINS. IAW ENGINEERING LETTER DQ6550M1.

Part: SPAR — CORRODED (LT WING) · airframe 8,610 hrs · 5,680 cycles

REPAIR OF CORROSION ON CENTER SPAR WEBS NEAR WS 39.90. REF CESSNA ENGINEERING REPORT S-680-0081/RD REV A AND FAA 8100-9 DATED 3-20-2017. WORK RECORD ON FILE AT THIS FACILITY UNDER WORK ORDER 48500.

Part: RIB — DAMAGED · airframe 7,854 hrs · 5,173 cycles

2 ASYMMETRICAL HOLES IN BOTTOM RUDDER RIB. FWD HOLE 1.5X1" AFT HOLE 1.375 X .875". 2 HOLES CONNECTED BY A CRACK.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 7,854 hrs · 5,173 cycles

CORROSION FOUND ON LT HORIZONTAL STABILIZER LOWER T/E SKIN, APPROXIMATELY 12" INBD OF ELEVATOR MIDDLE HINGE. FOUND DURING HORIZONTAL STABILIZER AFT SPAR ASSY GVI, CORROSION INSPECTION, TASK 55-10-00-210, ITEM CODE A551006.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 7,854 hrs · 5,173 cycles

CORROSION ON LEFT HORIZONTAL STABILIZER UPPER SKIN.

Part: SKIN — CORRODED (RUDDER) · airframe 7,854 hrs · 5,173 cycles

CORROSION ON LOWER L/E SKIN OF RUDDER.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 7,854 hrs · 5,173 cycles

CORROSION FOUND ON RT HORIZONTAL STABILIZER LOWER T/E SKIN, APPROXIMATELY 14" OTBD OF ELEVATOR MIDDLE HINGE.

Part: STRUCTURE — CORRODED (MLG WW) · airframe 7,854 hrs · 5,173 cycles

CORROSION IN LT AND RT MLG WHEEL WELLS. INCLUDING ON AFT SPAR.

Part: STARTER GEN — FIRE (LT NACELLE) · airframe 5,366 hrs · 3,540 cycles

AFTER APU SHUTDOWN, FLAMES WERE NOTICED COMING FROM LOWER LT ENGINE NACELLE. INSPECTED AREA AND FOUND BURN ON LOWER COWLING. FOUND GENERATOR DAMAGED, APPEARS TO HAVE CAUGHT FIRE. R & R THE LEFT STARTER GENERATOR IAW MM 80-10-00. OPS CHECKED GOOD.

Part: B-NUT — LOOSE (BLEED MANIFOLD) · airframe 5,190 hrs · 3,414 cycles

ON TAKEOFF, ON BRINGING THE POWER UP, THE AIRPLANE REQUIRED INCREASING AMOUNTS OF LEFT RUDDER UNTIL IT WAS FULL RUDDER. THE RUDDER THEN SUDDENLY SNAPPED BACK TO CENTERED. ABORTED TAKEOFF AROUND 40KTS. PERFORMED ENGINE RUNS AND VERIFIED DISCPREPANCY. PERFORMED RUDDER BIAS ACTUATOR ADJUSTMENT TEST WITH NO DEFECTS NOTED. OPENED ENGINE COWLING AND PERFORMED CHECK ON RUDDER BIAS BLEED LINES AND FOUND OUTBOARD B-NUT ON BLEED MANIFOLD LOOSE. TIGHTENED B-NUT AND PERFORMED SATISFACTORY OPS CHECK WITH NO DEFECTS NOTED. WORK DONE IN REF AMM 27-20-10.

Part: PUMP — DAMAGED

EXTENSIVE FRETTING DAMAGE ON PRIMARY JET PUMP FITTINGS AND ATTACHING LINE FITTINGS WHERE WIGGINS CLAMP W991-18DE ARE INSTALLED. DAMAGE OCCURRS TO ADJACENT PLUMBING PN 6926100-123, 6926100-13, 6926100-15, AND 6926100-76. DAMAGE HAS BEEN FOUND TO THESE MODELS DURING TANK INSPECTION 28-10-00-201 CONDITION FOUND IS DANGEROUS AND UNAIRWORTHY.

Part: ARM — WORN (FS 303.9)

UPON RT CABIN FLOOR PANEL REMOVAL (162ET) IT WAS OBSERVED THAT THERE WAS SOME FRETTING MATERIAL ON THE INSULATION BAGS AND THE SURROUNDING AREA. FURTHER INVESTIGATION REVEALED THAT THE RT (PN 6964000-16) AND LEFT (PN 6964000-15) ARMS THAT CONNECT THE BRAKE METERING VALVE TO THE BRAKE CABLE CLEVISES WERE SEVERELY WORN. THE BOLTS AND CLEVISES AT THE ATTACH POINTS ARE WEARING INTO THE BRAKE METERING VALVE ARMS. IT LOOKS LIKE THE BUSHINGS (SPACER PN NAS43DD4-16FC) WERE NEVER INSTALLED. RECOMMEND DURING A 3AEMERGENCY BATTERY SERVICE OR AN INSPECTION THAT THIS PANEL (162ET) IS REMOVED, THAT THE ARMS BE INSPECTED FOR WEAR AND THAT THE SPACER IS INSTALLED.

Part: ARM — WORN (FS303.9)

UPON RT CABIN FLOOR PANEL REMOVAL (162ET) IT WAS OBSERVED THAT THERE WAS SOME FRETTING MATERIAL ON THE INSULATION BAGS AND THE SURROUNDING AREA. FURTHER INVESTIGATION REVEALED THAT THE RT (PN 6964000-16) AND LEFT (PN 6964000-15) ARMS THAT CONNECT THE BRAKE METERING VALVE TO THE BRAKE CABLE CLEVISES WERE SEVERELY WORN. THE BOLTS AND CLEVISES AT THE ATTACH POINTS ARE WEARING INTO THE BRAKE METERING VALVE ARMS. IT LOOKS LIKE THE BUSHINGS (SPACER PN NAS43DD4-16FC) WERE NEVER INSTALLED. RECOMMEND DURING A 3AEMERGENCY BATTERY SERVICE OR AN INSPECTION THAT THIS PANEL (162ET) IS REMOVED, THAT THE ARMS BE INSPECTED FOR WEAR AND THAT THE SPACER IS INSTALLED.

Part: LANDING GEAR — MALFUNCTIONED (NOSE) · airframe 4,309 hrs · 2,871 cycles

NOSE WHEEL DOES NOT COME INTO NOSE BAY IN A TIMELY MANNER. UNLOCK LIGHT REMAINS ON FOR UP TO 10 SECONDS. LOUDER THAN NORMAL NOISE ON NOSE WHEEL RETRACTION AS GEAR IS LOCKED UP. NOSE WHEEL EXTENSION NORMAL. NORMAL OPERATION OF THE GEAR HANDLE. COMPLETED GEAR CYCLE AND INSPECTION. STRUT EXTENSION NORMAL, STEERING CENTERING NORMAL, MAIN GEAR AND DOORS OPERATE NORMAL. NOSE GEAR DOORS ARE TIGHT, ADJUSTED NOSE GEAR DOORS. GEAR CYCLE TEST NORMAL WORK IAW MM 52-80-20.

Part: MODULE — MULTIPLE FAIL · airframe 3,811 hrs · 2,508 cycles

FL 370. GPS 1 INACTIVE. BLEED AIR MONITOR FAIL LT CABIN ALT ENG CONTROL FAULT LT. EMERGENCY EXIT OPEN. BAGGAGE DOOR OPEN. WINDSHEAR FAIL. GROUND PROX FAIL. LT FUEL TOTALIZER FAILED ALL DASHED LINES. MESSAGES REMAINED ON UNTIL SHUTDOWN. REMOVED GENERIC INPUT MODULE AND INSTALLED REPLACEMENT GEN I/O MODULE. LOADED OPS FLIGHT SOFTWARE IAW MM (REV 17) CH 34-23-10 (REV 17) PERFORMED OPS CHECK. OPS CHECKED GOOD. WORK DONE IAW MM (REV 17), 34-17-00 (REV 10)

Part: STRUT — DISCHARGED (NLG) · airframe 3,723 hrs · 2,446 cycles

ON TAKE OFF, MLG WOULD NOT COME UP. HANDLE WOULD NOT MOVE, CHECKED CIRCUIT BREAKER, AND HYDRALICS, BOTH GOOD. AFTER APPROXIMATELY 1 MINUTE, THE AMBER "WOW MISCOMPARE" LIGHT CAME ON. ON LANDING NOSE WHEEL STEERING, THRUST REVERSERS WERE AVAILABLE. ACFT DEPRESSURIZED FINE. UNABLE TO DUPLICATE. RESISTANCE CHECKED GOOD ON NOSE SQUAT SWITCH AND BOTH MAIN SQUAT SWITCHES. FOUND NOSE STRUT UPPER AND LOWER BARRELS ABOUT 20 PSI LOW AND NOSE STRUT FLUID LEVEL IMPROPERLY SERVICED. SERVICED NOSE GEAR STRUT IAW MM 32-20-00. OPS CHECKED GOOD.

Part: STRUT — DISCHARGED (NOSE) · airframe 3,477 hrs · 2,307 cycles

AFTER TAKE OFF, GEAR RETRACTED MOST OF THE WAY, UNTIL NOSE WHEEL WAS LOCKED UP. GEAR THEN CYCLED ABOUT 6-7 TIMES SHORT UP-DOWN, FINALLY WAS UP & LOCKED. RETURNED TO FIELD, PUT GEAR DOWN GOT 3 GREEN & LANDED WITHOUT INCIDENT. AFTER LANDING, INSPECTED AND NOTHING OUT OF THE ORDINARY OBSERVED IN ANY OF THE GEAR WHEELWELLS OR TIRES. NLG STRUT FOUND N2 LOW, SERVICED STRUT. LEAK CHECKED NORMAL. OPS CHECKED NORMAL. WORK PERFORMED IAW MM 32-20-00.

Part: LANDING GEAR — MALFUNCTIONED · airframe 2,812 hrs · 1,873 cycles

AFTER TAKEOFF THE GEAR HANDLE WOULD NOT MOVE TO THE UP POSITION. SHORTLY AFTER THE WOW MISCOMPARE CAUTION CAME ON. JACKED ACFT AND PERFORMED ADJUSTMENT/TEST OF NLG AND MLG SQUAT SWITCHES IAW MM 32-60-00. SERVICED NLG OLEO STRUT WITH NITROGEN IAW MM 32-20-00. SWUNG GEAR NUMEROUS TIMES AND NO ISSUES WERE NOTED. SAFTIED SWITCHES AS REQUIRED, SWUNG GEAR AGAIN WITH SATISFACTORY RESULTS.

Part: STRUT — DISCHARGED (NLG) · airframe 2,542 hrs · 1,681 cycles

LANDING GEAR HANDLE WOULD NOT COME UP AFTER TAKE-OFF WITH ASSOCIATED "WOW MISCOMPARE" CAS MESSAGE. SERVICED NOSE GEAR STRUT IAW MM 32-20-00 PERFORMED GEAR RETRACT OPS CHECK, OPS CHECK GOOD.

Part: LINE — RUPTURED (HYD SYSTEM) · airframe 2,426 hrs · 1,606 cycles

CAS "HYD VOL LOW". HYD RESEVOIR VOL INDICATES 110 CUBIC INCHES. HYD FLUID ALL OVER NOSE GEAR AND BELLY OF ACFT. T/S SYSTEMS, FOUND NOSE GEAR FLEXIBLE EXTEND LINE RUPTURED. REMOVED & REPLACED BOTH THE EXTEND & RETRACT LINES WITH NEW IAW MM 32-30-00. SERVICED HYD RESERVOIR. SWUNG LANDING GEAR 12X, LINES LK CHK & OP CHK GOOD.

Part: UNKNOWN — UNKNOWN · airframe 2,069 hrs · 1,363 cycles

AFTER LANDING GEAR RETRACTION 8-10 LOUD BANGS WERE HEARD & VIBRATIONS WERE FELT IN THE COCKPIT FLOOR.

Part: STRUT — DISCHARGED (NLG) · airframe 2,087 hrs · 1,363 cycles

AFTER LANDING GEAR RETRACTION 8-10 LOUD BANGS WERE HEARD AND VIBRATIONS WERE FELT IN THE COCKPIT FLOOR. THE GEAR UNSAFE LIGHT REMAINED ON DURING THE ABNORMAL GEAR RETRACTION. AT APPROX. 1000 FT ABOVE THE GROUND THE GEAR FULLY RETRACTED AND THE UNSAFE LIGHT WENT OUT. GEAR EXTENDED NORMALLY UPON LDG. TROUBLESHOT TO A NOSE STRUT REQUIRES SERVICE. SERVICED NOSE STRUT IAW MM 32-20-00 REV 7 AND CYCLED GEAR TEN TIMES IAW MM 32-00-00 REV 13 WITH NO DISCREPANCIES NOTED.