N428QS
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| NETJETS AVIATION, INC. (DXTA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
UPON PARKING AND DOING THE SHUTDOWN CHECKLIST NOTICED SOME OF THE EMER LIGHTS STAYED ON WHEN THE SWITCH WAS IN THE OFF/ARM POSITION. IF YOU TURN THE SWITCH TO THE ON POSITION ALL EMER LIGHTS COME ON. THEY EXTINGUISH AFTER 5 MINUTES. DISCOVERED MAIN ENTRY DOOR COURTESY LIGHT SWITCH STUCK IN DEPRESSED POSITION. COCKPIT COURTESY LIGHT SWITCH OPERATIONAL. ADJUSTED MED COURTESYLIGHT SWITCH AND AFFECTED LIGHTS NO LONGER ACTIVATING. MED COURTESYLIGHT SWITCH INTERNALLY BROKEN AND REQUIRES REPLACEMENT. NOTIFIED MCC, PLACED SWITCH ON ORDER, AND ISSUED. GAINED ACCESS TO FAULTYSWITCH AND SOLDERED IN NEW SWITCH. REPORTED LIGHTS NO LONGERCOMING ON UNLESS COMMANDED. CHARGED EMER BATTERIES AND COMPLIED WITH EMER LIGHTS OP CK WITH NO ISSUES. SYS OP CK GOOD IN REF TO EMB-505S AMM 33-26-00. SWITCH PN: 8121183ZGE22 / SN: N/A.
WHILE OPENING THE MAIN DOOR, VERY LOUD "BANG" FOLLOWED BY FULL WEIGHT OF DOOR. UPON INSPECTION NOTICED CABLE SYSTEM THAT ASSISTS DOOR WAS SLACK. COULD NOT IDENTIFY IF CABLE WAS BROKEN OR JUMPED TRACK. INSTALLED NEW BALANCE CABLES ONTO BALANCE DRUM IAW AMM 52-13-22/400. PERFORMED MAIN DOOR OPENING SPEED ADJUSTMENT IAW AMM 52-10-00-820-804-A. ADJUSTMENT SATISFACTORY. REINSTALLED ALL ACCESS PANELS AND LH SIDE LEDGE.
FLOOR EMERG EXIT LIGHT: ONE WHITE EMERGENCY LIGHT IN AISLE IS INOP CORRECTIVE ACTION; REPLACED LED FLOOR PROXIMITY LIGHT ASSY PN: 0434LS00-01 SN: N/A IAW PHENOM 300 AMM 33-52-11. PERFORMED THE OPERATIONAL TEST OF THE FLOOR PROXIMITY LIGHTS IAW PHENOM 300 AMM 33-52-00 WITH NO FURTHER FAULTS NOTED..
FLAP FAIL YELLOW CAS: FLAP FAIL YELLOW CAS DISPLAYED ON APPROACH AFTER SELECTING FLAPS 1 AT APPROXIMATELY 160KIAS. FLAPS FAILED AT THE "0" POSITION. REPEAT WRITE UP. CORRECTIVE ACTION; REPLACE SUSPECT FAULTY FLAP PDU IAW PHENOM 300 MM 27-51-07. REPLACED SUSPECT FAULTY LH FLAP POSITION SENSOR P/N 457310-1001 S/N 1067 IAW PHENOM 300 MM 27-53-03. REPLACED SUSPECT FAULTY RH FLAP POSITION SENSOR P/N 457310-1001 S/N 1068. PERFORMED FLAP SYSTEM RIGGING PROCEDURE REF PHENOM 300 MM 27-50-00. OPS CHECK GOOD, NO DEFECTS NOTED.
TAXING OUT AT KVGT EXPERIENCED L & R BRAKES GRABBING EXCESSIVELY WITH LITTLE BRAKE PRESSURE APPLIED ON L & R PEDALS. BRAKES CAUSING JERKING TO L & R. STOPPED AIRCRAFT DISCUSSED WITH MAINTENANCE THEN PERFORMED A COMPLETE POWER DOWN & REBOOT OF COMPUTER SYSTEM. AFTER STARTUP, STILL FEELING GRABBING BUT NOT AS EXTREME. ACCOMPLISHED CMC; ENGINE, FOQA, AND CVDR DOWNLOADS. BEGAN PERFORMING AM AND INSPECTED ALL BRAKES, TIRES, HYD RESERVOIR & ACCUMULATOR LEVELS, BRAKE PIN WEAR, TREAD DEPTH, TIRE PRESSURES, ETC IAW FIM, FOUND RT MAIN TIRE WORN TO 1/32. FOUND AFTER BLEED DOWN, EMERGENCY PARKING BRAKE ACCUMULATOR, ACCUMULATOR PRESSURE WOULD RISE BACK UP TO 1850 PSI ON ITS OWN. THIS NOT NORMAL. RECOMMEND CARRY OUT EMERGENCY PARKING-BRAKE SYS OPS CHECK IAW AMM MPP TASK 32-43COM10·801-A, FOUND NO DEFECTS. UNDESIRED YAW TENDENCY, COMPLETED STEPS 1, 2, & 3 OF BLOCK DIAGRAM SUB TASK 810-107-A. STEP 4 REQUIRES ACFT TO BE PLACED ON JACKS FOR COMPLETE BLEEDING OF MAIN HYD SYS THAT WILL INCLUDE BLEEDING THE UPLOCKS, GEAR SWINGS, REMOVED ANO REPLACED WORN RH MLG WHEEL ASSY. REPAIRED MLG WHEEL ASSY IAW AMM 32-45-01. MAIN HYDRAULIC SYSTEM - BLEED OF AFT - NO DEFECTS NOTED IAW 29-10'00:860·JI01·A. REINSTALLED L/H EDP PUMP TW-TL-104422 IAW 29-12-01/400 A TAXI CHECK WILL. NEED TO BE COMPLETED FOR FUNC CHECK OF ORG DISC. THE NC WILL BE MOVING FROM HANGER SPACE BACK TO LINE WHERE RUN UPS AND TAXI CHECK.CAN BE COMPLETED. TAXI CHECK COMPLETE . ENG CHECKS COMPLETE, NO DEFECTS NOTED . ORIG SUB: 7/22/2024
EMERGENCY LIGHTING SYSTEM LIGHTS FLASHING IN THE ARM POSITION. TESTED SYSTEM ON GROUND AND DUPLICATED WHAT WE SAW IN FLIGHT. ALL EMERGENCY LIGHTS FLASHING IN THE ARMED POSITION. //SIGNOFF//REMOVED AND REPLACED FWD AND AFT EMERGENCY BATTERY PACKS REF. PHENOM 300 AMM 33-52-01. OPS CHECK GOOD.FWD EMERGENCY BATTERY.
WORN BRAKES: BRAKES RUMBLE/VIBRATE/GRIND WHEN APPLIED. OCCURS WHEN EITHER BRAKE PEDAL IS DEPRESSED, AND STOPS WHEN BRAKES PEDAL PRESSURE IS RELEASED. // SIGNOFF// INSPECTED LH AND RH MLG BRAKES AND WEAR PINS NO ISSUES OR LEAKS NOTED, BLED BOTH MLG BRAKES AS REQUIRED AND TAXI CHECKED AIRCRAFT ALL OPS AND TAXI CHECKS GOOD. IAW PHENOM 300 AMM 32-40-00 AND 32-41-00,
CABIN EMERG LIGHT: REPEAT WRITE-UP. IN THE ARMED SWITCH POSITION IN FLIGHT, CABIN EMERGENCY LIGHTS WILL ILLUMINATE, THEN START FLASHING ON AND OFF. // SIGNOFF// RESOLUTION: HAD AIRCRAFT REPOSITIONED TO ATLANTIC AVIATION. POWERED AIRCRAFT AND EMERGENCY LIGHTS ON GPU POWER AS REQUIRED NOTING IN THE ARM POSITION ALL EMERGENCY LIGHTS ILLUMINATE. ALLOWED AIRCRAFT EMERGENCY BATTERY'S TO CHARGE FOR 1 HOUR THEN PERFORMED EMERGENCY LIGHTS OPERATIONAL TEST, IAW PHENOM 300 MM CH 33-52- 00-710-801-A NOTING ALL EMERGENCY LIGHTS ILLUMLNATE WITH SWITCH IN ARM POSITION. POWERED DOWN AIRCRAFT, AND GAINED ACCESS TO# 2 (AFT) EMERGENCY BATTERY. DISCONNECTED #2 (AFT) EMERGENCY BATTERY CONNECTOR, POWERED AIRCRAFT AND SELECTED EMERGENCY LIGHTS SWITCH TO ARM, NOTING NO ILLUMINATION OF ANY EMERGENCY LIGHTS. SELECTED EMERGENCY LIGHTS SWITCH TO ON NOTING STILL NO EMERGENCY LIGHTS ILLUMINATE. POWERED DOWN AIRCRAFT, RECONNECTED # 2 (AFT) EMERGENCY BATTERY, AND GAINED ACCESS TO IT 1 {FWD) EMERGENCY BATTERY. DISCONNECTED CONNECTOR FROM# 1 (FWD) EMERGENCY BATTERY, POWERED AIRCRAFT AND SELECTED EMERGENCY LIGHTS SWITCH TO ARM, NOTING ALL EMERGENCY LIGHTS ILLUMINATE MOMENTARILY THEN CYCLE OFF. SELECTED SWITCH TO ON NOTING ALL EMERGENCY LIGHTS ILLUMINATED. SELECTED SWITCH BACK TO ARM, LIGHTS WENT OUT AND REMOVED POWER FROM AIRCRAFT NOTING ALL EMERGENCY LIGHTS ILLUMINATE. SELECTED EMERGENCY LIGHTS OFF AND REMOVED TT 1 {FWD} EMERGENCY BATTERY P/N 6450LS-00 S/N 000869 IAW PHENOM 300 MM 33-52-01-000-801-A AND INSTALLED NEW EMERGENCY BATTERY P/N 7450LS-00 S/N 005912 IN# 1 (FWD) POSITION IAW PHENOM 300 MM 33-52-01-400-801-A. PERFORMED EMERGENCY LIGHTS OPERATIONAL TEST IAW PHENOM 300 MM 33-52-00-710-801-A WITH NO DEFECTS NOTED. POWERED DOWN AIRCRAFT AND HAD AIRCRAFT MOVED OUTSIDE. PERFORMED ENGINE RUNS REF: PHENOM 300 AFM AND PERFORMED OPERATIONAL CHECK OF EMERGENCY LIGHTS WITH NO DEFECTS NOTED. POWERED DOWN AIRCRAFT AND CLOSED ALL ACCESS PANELS,
EMER LT NOT ARM YELLOW CAS: ON CLIMB EMER LT NOT ARM CAS MESSAGE ILLUMINATED. THE EMER LIGHTS WERE ON IN THE BACK AND AFTER A FEW MINUTES STARTED FLASHING.// SIGNOFF// POWRED UP . AND VERIFIED DISCREPANCY GAINED ACCESS NUMBER 1 EMER BATTTERY AND NUMBER 2 EMER BATTERY. COMPLIED WITH SL 505-33-0005, FOUND AFT BATTERY AT FAULT NOTIFIED MCC: OF FINDINGS (BC-1-19-2022) TOP CHARGED EMER. BATTERLES WITH THE EXTERNAL POWER. C/W OPS CHECKS OF EMERGENCY LIGHTS WITH SAME RESULTS AFT BATTERY WILL NEED TO BE REPLACED RECIEVED CUSTOMER SUPPLIED NEW EMERGENCY BATTERY. ACCESSED AFT BATTERY. REMOVED AND REPLACED BATTERY C/W OPS CHECK ALL CHECKS GOOD CLOASED ACCESS AS NEEDED REF EMB 505S AMM 33-52-01.
NLG LANDING GEAR EXTENSION: WHEN THE LANDING GEAR WAS EXTENDED ON FINAL APPROACH THE NOSE GEAR DID NOT EXTEND. BOTH OF THE MAINS WERE GREEN, BUT THE NOSE WAS YELLOW WITH A RED LANDING GEAR SWITCH DISAGREE CAS MESSAGE. APPROXIMATELY ONE MINUTE LATER DURING THE GO AROUND THE NOSE GEAR LOUDLY EXTENDED AND INDICATED GREEN. WE DECLARED AN EMERGENCY AND LANDED UNEVENTFULLY. // SIGNOFF// PERFORMED CONTACT CENTER RECOMMENDATIONS. PERFORMED 10 GEAR SWINGS. BLED HYDRAUUCS. NO CAS MESSAGES RELATING TO THE LANDING GEARS ACTIVE. CONTACT CENTER RECOMMENDS SIGNING OFF AND MONITORING. MCC ELECTS TO SIGN OFF PER CONTACT CENTER RECOMMENDATIONS. NO FURTHER DEFECTS NOTED. ALL WORK DONE IAW EMB-505 AMM
E2 OIL LO PRES RED CAS: ON CLIMB OUT FROM PHF, LEVELING AT 5000 FEET, E2 LOWPRESS RED CAS ILLUMINATED WITH ENGINE EXCEEDANCE WHITE CAS MESSAGE. QRH DIRECTS ENGINE SHUTDOWN. LANDED WITHOUT INCIDENT BUT 400 POUNDS OVER WEIGHT. // SIGNOFF//AFTER EMBRAER REVIEW OF THE CMC DAT A, COMPLIED WITH RECOMMENDED FIM 79-31--00-810-802-A FOR FAILURE OF THE ENGINE 2 MAIN OIL PRESSURE SENSOR. ALL WIRJNG CHECKS GOOD, VERIFIED N0 ASSOCIATED GEA2 FAILURE IN CMC AND AVIONICS STATUS SHOWING GEA2 OPERATIONAL. FIM STATES THAT THE NEXT STEP IS TO REMOVE AND REPLACE THE MAIN OIL PRESSURE SENSOR ON THE RH ENGINE. PER EMBRAER FURTHER RECOMMENDATION, COMPLIED WITH ENGINE DCU DOWNLOAD IAW EMB-505 EMM 71-00-00-760-817 SENT FILES IN FOR REVIEW PRIOR TO ORDERING MOP SENSOR. PER PWC REVIEW, THEY BELIEVE THE FAILURE TO BE THE MOP CAUSING AN INDICATION ISSUE. PER NJA PWC REP, VERIFIED OIL PRESSURE DURING ENGINE SPOOL AND PERFORMED ENGINE RUNS AT VARIOUS POWER SETTINGS, INCLUDING HIGH POWER, WITH SUSPECT MOP SENSOR STILL INSTALLED. N0 DEFECTS NOTED, REPORTED FINDINGS TO PWC REP. PWC REP CONCURS TO REPLACE MOP SENSOR. REMOVED AND REPLACED NO.2 ENGINE MOP SENSOR IA W EMB-505 AMM 79-31--05-400-801-A. COMPLIED WITH ADDITTONAL ENGINE RUNS ATV ARIO US POWER SETITNGS, ALL OIL PRESSURE PARAMETERS NOMINAL. OPS CHECK AND LEAK CHECK GOOD. ACCESS CLOSED. VERIFIED OIL LEVEL DID NOTE DECREASE AFTER ENGINE RUNS.
WITH EMERGENCY LIGHT SWITCH IN ARM POSITION, EMERGENCY LIGHTS ARE ILLUMINATED. CORRECTIVE ACTION: REMOVED FAILED FORWARD BATTERY PACK P/N 6450LS-00 S/N 002058 AND REPLACED WITH A MODIFIED BATTERY PACK P/N 6450LS-00 S/N 000869. REMOVED FAILED AFT BATTERY PACK P/N 6450LS-00 S/N 00846 AND REPLACED WITH A MODIFIED BATTERY PACK P/N 6450LS-00 S/N 000668. OPERATIONS CHECKED EMERGENCY EXIT LIGHTS NORMAL. ALL REF EMB 505 AMM 33-52-01.
DURING ACCOMPLISHMENT OF EMBRAER SB 505-55-0004 REV 01 (DATED 06/24/2020), WE NOTED THE FOLLOWING MASS BALANCE WEIGHTS BELOW TOLERANCE AT LEFT ELEVATOR: ADJUSTABLE WEIGHTS PART NUMBER PE915109-L33 (4 EACH BELOW MINIMUM OF 84G); HORN MASS WEIGHT PART NUMBER PE915109-L42 (1 EACH BELOW MINIMUM OF 1095G). ALL WEIGHTS HAVE BEEN REPLACED WITH A NEW MASS WEIGHTS AND THE ELEVATOR BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED. THE ELEVATOR WAS RE-IDENTIFIED TO PART NUMBER 505-11082-603, AS PER SB INSTRUCTIONS. WE ALSO NOTED THE FOLLOWING RIGHT ELEVATOR MASS BALANCE WEIGHTS BELOW TOLERANCE: ADJUSTABLE WEIGHTS PART NUMBER PE915109-L33 (4 EACH BELOW MINIMUM OF 84G). ALL WEIGHTS HAVE BEEN REPLACED WITH A NEW MASS WEIGHTS AND THE ELEVATOR BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED. THE ELEVATOR WAS RE-IDENTIFIED TO PART NUMBER 505-11082-604, AS PER SERVICE BULLETIN INSTRUCTIONS. THIS REPORT COMPLIES WITH FAA 14 CFR PART 135 OPERATORâS GMM REQUIREMENTS.
DISCREPANCY: FOUND AFT EMERGENCY LIGHT BATTERY FULLY DISCHARGED AND WOULD NOT TAKE CHARGE WHEN POWER ON. CORRECTIVE ACTION: PERFORMED REPLACEMENT OF EMERGENCY LIGHTS BATTERY RIGHT HAND RACK (AFT) WITH MODIFIED UNIT IN ACCORDANCE WITH PHENOM 300 MAINTENANCE MANUAL 35-52-01. PERFORMED OPERATIONAL TEST OF EMERGENCY LIGHTS IN ACCORDANCE WITH PHENOM 300 MAINTENANCE MANUAL 33-52-00. NO DEFECTS NOTED. THIS REPORT COMPLIES WITH FAA 14 CFR PART 135 OPERATOR'S GMM REQUIREMENTS.
ON TAXI OUT WHEN THE BRAKES WERE APPLIED WE SENSED A FAINT VIBRATION. BRAKES SEEM TO FUNCTION NORMALLY OTHERWISE, SO WE CONTINUED THE FLIGHT. AFTER LANDING, BEGINNING ON THE ROLL OUT WITH BOTH BRAKES APPLIED, THE RIGHT BREAK BEGAN TO GRAB RANDOMLY AND AT TIMES WOULD SHUTTER UNTIL RELEASED. DIRECTIONAL CONTROL DURING TAXI IN WAS MADE MORE DIFFICULT WHEN BRAKES WERE APPLIED BECAUSE OF THIS. SIGN OFF. PERFORMED A VISUAL INSPECTION OF RT BRAKE AND BRAKE LINES WITH NO DEFECTS NOTED. PERFORMED BLEEDING PROCEDURE OF RT BRAKE, IAW PHENOM 300 MM CH 32-40-00 TAXIED AIRCRAFT AND PERFORMED OPERATIONAL CHECKS OF BRAKES. BRAKES OPERATE NORMALLY AT THIS TIME. SERVICED HYDRAULIC SYSTEM IAW PHENOM 300 MLM CH 12-'13-00.
NLG LANDING GEAR EXTENSION DID NOT EXTEND - AFTER SELECTING FLAPS 2 WE COMMANDED GEAR DOWN WITH LEVER DOWN . THE TWO MAIN CAME DOWN SHOWING GREEN CIRCLES ON MFD BUT THE NOSE GEAR AFTER OVER 30SEC NEVER SHOWED A GREEN CIRCLE . NOSE GEAR SYMBOL WAS INITIALLY A YELLOW DASH SQUARE THEN BECAME A RED DASH SQUARE SHORTLY AFTER WE GOT THE LANDING GEAR LEVER CAS MSG . WE EXECUTED A MISS APPROACH BY BRINGING THE GEAR LEVER UP AND FLAPS 1 . WE JOINED A DOWNWIND PATTERN AND DID A PARTIAL ABNORMAL LANDING GEAR EXTENSION THE REASON BEING IS THAT AS SOON AS WE SELECTED THE GEAR LEVER DOWN THE GEAR EXTENDED NORMALLY AND WE GOT 3 GREEN CIRCLES FAIRLY FAST . THE ABNORMAL LANDING GEAR EXTENSION WAS STOPPED AT LDG GEAR LEVER DN . FREE FALL WAS NOT NECESSARY. REMOVED & REPLACED NLG UPLOCK BOX IAW PHENOM 300 M/M 32-31-05. OPS CHK GOOD
UNABLE TO MODULATE BRAKES. ONCE BRAKES ARE WARM THERE IS NO FEEL. THEY GO FROM NOTHING TO FULL GRAB. BOTH LT AND RT BRAKES DO THE SAME THING. BOTH CAPTAIN AND COPILOTS PEDALS ARE THE SAME. NO BRAKE FEEL FROM THE PEDALS. DOES NOT MATTER HOW SLOW YOU APPLY PEDAL FORCE. NO BRAKES TO FULL BRAKES WITHOUT WARNING. INSPECTED ALL 4 BRAKES AND NO ABNORMALITIES. PERFORMED ANTI-SKID OPS CHECK AND FOUND ANTI-SKID TO OPS CHECK GOOD. PERFORMED TAXI BRAKE CHECK AND OPS CHECK GOOD. R & R ANTI-SKID CONTROL BOX IAW CMP 324264. PERFORMED ANTI-SKID SYS OPS TEST IAW GIV CMP 324204. PERFORMED TAXI CHECK WITH CREW. OPS CHECK GOOD.
WHEN BRAKE PRESSURE IS APPLIED THERE IS NO RESPONSE FOR THE FIRST 2-3 INCHES OF BRAKE PEDAL MOVEMENT THEN THE BRAKES GRAB HARD ENOUGH TO THROW PAX AND CREW FORWARD. BRAKES TEMPS LESS THAN 100 DEGREES. TROUBLESHOT, WHEN BRAKE PRESSURE IS APPLIED THERE IS NO RESPONSE FOR THE FIRST 2-3" OF BRAKE PEDAL MOVEMENT. PERFORMED HYDRO MECHANICAL ANALOG BRAKE ANTISKID CONTROL SYS OPS CHECK WITH NO DEFECTS NOTED AT THIS TIME. WORK DONE IAW GIV-MSG3, CMP 324204. WHILE PERFORMING NORMAL BRAKE SYS, OPS TEST, NOTED RT BRAKE PRESSURE WILL DROP RAPIDLY THEN FOLLOW BY LT BRAKES PRESSURE DROP. WHILE DEPRESSING BRAKE PEDALS TAPPED LIGHTLY ON BRAKE AUGMENTER VALVE ON THE WELL WALL, NOTED BRAKE PRESSURE WILL FLUCTUATE, SUSPECT BAD VALVE. WORK DONE REF GIV MSG-3 AMM 32-43-01. R & R BRAKE AUGMENTOR VALVE. REMOVED VALVE, PN 39-723-1, SN 375 AND INSTALLED O/H VALVE, PN 39-723-1, SN 341. WORK DONE IAW CMP GIV 324272. OPS AND LEAK CHECKS GOOD.
ON LANDING, DURING BRAKING, LT BRAKE PRESSURE IS APPLIED AND BRAKE GRABS EXCESSIVELY AFTER SHORT DELAY. PERFORMED INSPECTION OF TIRES, BRAKES, LANDING GEAR AND BRAKE PEDALS. NO DISCREPANCIES FOUND. PERFORMED L/H, R/H BRAKE BLEED PROCEDURE IAW GIV CMP 324265 AND 324266. FOUND MINOR AIR IN LT, RT INBD BRAKES. SERVICED BRAKES AND HYD RESERVOIR. PERFORMED HYDRO MECH. ANOLOG BRAKE OPS TEST IAW GIV CMP 324203. OPS CHECKS GOOD AT THIS TIME.
LT WINGLET CORRODED.
DURING CLIMB, LT ENGINE TGT EXCEEDANCE WAS NOTED. MX FOUND CONNECTORS 900A1P16 AND 900A1P17 LOOSE. BOTH CONNECTORS ARE LOCATED AT THE ENGINE PYLON JUST AFT OF THE FIXED COWL AND CONNECT TO THE THRUST REVERSER. RATCHETING TYPE CONNECTORS WERE SECURED AND OPS CHECKS WERE PERFORMED SATISFACTORILY.
MOST CADMIUM PLATED HARDWARE INSTALLED IN WING INTERGRAL FUEL TANKS HAVE DEVELOPED CORROSION. HARDWARE REQUIRES REPLACEMENT. MULTIPLE PART NUMBERS AFFECTED.
LT MAIN GEAR KNEE PIN CORRODED IN LOCK PIN BORE.
RUDDER TORQUE TUBE CORRODED.
FASTENERS (8EA) WERE INCORRECT LENGTH INSTALLED IN FRAME IN RUDDER TORQUES TUBE BOX.
LT MAIN GEAR KNEE PIN CORRODED IN LOCK PIN BORE.