N840VA
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
51 reports on file, 2012-01-15 – 2023-11-03.
Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 37,848 hrs · 12,612 cycles
OPS TEST OF CABIN EMERGENCY LIGHTING FAILED. GROUNDED - YES. PERFORMED INTERFACE/POWER UP TEST OF THE CIDS AND OPERATIONAL CHECK OF THE EPSU THRU BITE CHECK AND OPS TEST OF THE EMERGENCY LIGHTING IN CABIN IAW A320 AMM 31-51-00-710-008-A, 23-73-00-740-005-B AND TSM 33-51-00-810-834-A. ALL TESTS GOOD.
Part: FRAME — DAMAGED · airframe 37,839 hrs · 12,607 cycles
GOGO 2KU DEMOD FRAME SPLICE REPAIR FR54, S-3R - S-4R. GROUNDED - YES. ACCOMPLISHED EA A320-44EO-00591-39 REV 0.
Part: CROSSBEAM — CORRODED · corrosion level 2 · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN CROSSBEAM AT FR65, Y = -508.5 HAS CORROSION. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN CROSSBEAM AR FR65 TO FR67, Y = -508.5 TO Y = 1736 IAW EA A320-53EO-01113-04.
Part: SKIN — DAMAGED · airframe 37,839 hrs · 12,607 cycles
L/WING SLAT 5 HAS ONE BURN MARK ON TOP SKIN L/E APPROX. 1.5" OUTBD OF TRACK 11. GROUNDED - YES. ACCOMPLISHED CATEGORY "A" MAJOR REPAIR ON L/H WING SLAT 5 L/E SKIN AT TRACK 11 IAW EA CMPT-57EA-01716 AND A320 SRM 57-40-00-300216.
Part: SKIN — UNKNOWN · airframe 37,839 hrs · 12,607 cycles
L/WING SLAT 5 HAS THREE BURN MARKS ON TOP SKIN APPROX. 9" AND 7.5" OUTBD. GROUNDED - YES. ACCOMPLISHED CATEGORY "A" MAJOR REPAIR ON L/WING SLAT 5 L/E SKIN AT TRACK 11 IAW EA CMPT-57EA-01716 AND SRM 57-40-00-300-216.
Part: FLOOR SUPPORT — CORRODED · corrosion level 2 · airframe 37,838 hrs · 12,607 cycles
AFT CARGO FLOOR SUPPORT BEAM AT FR56, Y765 HAS CORROSION GROUNDED - YES. REMOVED AND REPLACED FLOOR SUPPORT BEAM AT FR56, Y765 IAW A320 SRM 51-42-11/001
Part: FLOOR SUPPORT — BENT · airframe 37,838 hrs · 12,607 cycles
AFT CARGO FLOOR SUPPORT BEAM AT FR56 BETWEEB Y765 AND T1292 IS BENT GROUNDED - YES. REMOVED AND REPLACED FLOOR SUPPORT BEAM AT FR56 BETWEEN Y765 AND Y1292 IAW A320 SRM 51-42-11/001
Part: WEB — CORRODED · corrosion level 2 · airframe 37,839 hrs · 12,607 cycles
FWD CARGO FLOOR SUPPORT WEB AT FR58 Y=765 HAS SEVERAL AREAS OF CORROSION. GROUNDED - YES. REMOVED AND REPLACED FLOOR SUPPORT WEB AT FWD CARGO COMPT. FR28 Y=765 IAW A320 SRM 51-42-11/001.
Part: WEB — CORRODED · corrosion level 2 · airframe 37,839 hrs · 12,607 cycles
FWD CARGO FLOOR SUPPORT WEB AT FR28 Y=765 HAS SEVERAL AREAS OF CORROSION GROUNDED - YES. REMOVED AND REPLACED FLOOR SUPPORT WEB AT FWD CARGO COMPT FR28 Y=765 IAW A320 SRM 51-42-11/001.
Part: FLOORBEAM — CORRODED · corrosion level 2 · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN FLOOR BEAM HAS CORROSION AT FR16 LBL 10 BELOW LAV FLOOR PANEL 221PF. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR BEAM AT FR12 TO FR16, Y=503.2L TO Y=503.2L IAW A320 SRM 51-42-11.
Part: FLOOR PANEL — PUNCTURED · airframe 37,609 hrs · 12,514 cycles
MAIN CABIN FLOOR PANEL 231QF HAS SEVERAL DENTS GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 231QF PER A320 AMM 53-00-00-400-801-A
Part: FLOOR PANEL — GOUGED · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN FLOOR PANEL 221LF HAS SEVERAL GOUGES. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 221LF AT FR12 TO FR16 BL0 TO LBL 2 IAW A320 AMM 53-00-00-000-801-A.
Part: FLOOR PANEL — DENTED · airframe 37,609 hrs · 12,514 cycles
MAIN CABIN FLOOR PANEL 241JF HAS SEVERAL DENTS. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 241JF AT FR42-FR47, LBL10-LBL10 IAW A320 AMM 53-00-00-400-801-A.
Part: FLOOR PANEL — DENTED · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN FLOOR PANEL 231AF HAS SEVERAL DENTS. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR FLOOR PANEL 231AF PER A320 AMM 53-00-00-400-801-A.
Part: PLATE — CORRODED · corrosion level 2 · airframe 37,471 hrs · 12,462 cycles
CORROSION ON I/B PLATE CONNECTION OF R/H ELEVATOR T/E PROFILE. GROUNDED - YES. REMOVED AND REPLACED I/B PLATE CONNECTION ON R/H ELEVATOR PROFILE IAW A320 SRM 51-42-21-001.
Part: FLOOR PANEL — DELAMINATED · airframe 37,839 hrs · 12,607 cycles
AFT GALLEY FLOOR PANEL 261DF HAS DELAM APPROX 5" DIA IN CENTER OF FLOOR BOARD. GROUNDED - YES. REMOVED AND REPLACED AFT GALLEY FLOOR PANEL 261DF AT FR66 - FR68, LBL 28 IAW A320 AMM 53-00-00-400-801-A-2 AND AMM 53-00-00-000-801-401.
Part: FLOOR PANEL — DELAMINATED · airframe 37,609 hrs · 12,514 cycles
MAIN CABIN FLOOR PANEL 251HF HAS A PUNCTURE ON UPPER SURFACE. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 251HF PER A320 AMM 53-00-00-400-801-A.
Part: FLOOR PANEL — DELAMINATED · airframe 37,609 hrs · 12,514 cycles
MAIN CABIN FLOOR PANEL 231LF HAS 3 DENTS ON UPPER SURFACE. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 231LF PER A320 AMM 53-00-00-400-801-A.
Part: FLOOR PANEL — DENTED · airframe 37,609 hrs · 12,514 cycles
MAIN CABIN FLOOR PANEL 231NF HAS DENT ON UPPER SURFACE. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 231NF AT FR24-FR28, LBL50-LBL68 IAW A320 AMM 53-00-00-400-801-A01.
Part: SHEAR TIE — CRACKED · airframe 37,609 hrs · 12,514 cycles
MAIN CABIN FLOOR OUTBD AFT SHEAR PLATE IS CRACKED AT FR69. GROUNDED - YES. REMOVED AND REPLACED SHEAR PLATE IN MAIN CABIN FLOOR L/H SIDE OUTBD AT FR69 IAW A320 SRM 54-44-11/001 AND 51-42-11/001.
Part: FLOOR PANEL — DENTED · airframe 37,609 hrs · 12,514 cycles
MAIN CABIN FLOOR PANEL 232MF HAS SEVERAL AREAS OF DAMAGE ON UPPER SURFACE. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 232MF AT FR24-FR28 RBL41-RBL61 IAW A320 AMM 53-00-00-400-801A.
Part: SHEAR PLATE — CRACKED · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN FLOOR OUTBD AFT SHEAR PLATE IS CRACKED AT FR 69 GROUNDED - YES. REMOVED AND REPLACED SHEAR PLATE ON MAIN CABIN FLOOR L/H OUTBD SIDE AT FRAME 69 IAW A320 SRM 51-42-11/001 AND SRM 53-41-17-01-A FIG 001.
Part: FLOOR PANEL — PUNCTURED · airframe 37,609 hrs · 12,514 cycles
MAIN CABIN FLOOR PANEL 241FF HAS PUNCTURE ON LOWER SURFACE. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 241FF FR36-FR42, LBL10-LBL31 IAW A320 AMM 53-00-00-400-801-A.
Part: FLOOR PANEL — CORRODED · corrosion level 2 · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN FLOOR PANEL 262LG LOWER SKIN CORRODED. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 262LG AT FR66 - FR68, RBL28 - RBL59 IAW A320 AMM 53-00-00-000-801-A-01 AND AMM 53-00-00-000-801-A-02.
Part: FLOOR PANEL — DELAMINATED · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN FLOOR PANEL 241LF HAS DELAMINATION ON LOWER SURFACE. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 241LF AT FR42 TO FR47. LBL30 TO LBL45 IAW A320 AMM 53-00-00-400-801-A-01.
Part: FLOORBEAM — CORRODED · corrosion level 2 · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN FLOOR BEAM IS CORRODED AT FR68 LBL24. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR BEAM BETWEEN FR66 AND FR68 LBL 24 IAW A320 SRM 51-42-11/001.
Part: FLOOR PANEL — DENTED · airframe 37,609 hrs · 12,514 cycles
MAIN CABIN FLOOR PANEL 232EF HAS DENT ON UPPER SURFACE GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 232EF PER A320 AMM 53-00-00-400-801-A02
Part: FLOORBEAM — CORRODED · corrosion level 2 · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN FLOORBEAM IS CORRODED ON UPPER SURFACE AT FR68, RBL 24. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOORBEAM AT FR68, RBL 24 Y= -765 IAW A320 SRM 51-42-11.
Part: FLOOR PANEL — PUNCTURED · airframe 37,609 hrs · 12,514 cycles
MAIN CABIN FLOOR PANEL 231BF HAS 3 EA PUCTURES ON UPPER SURFACE. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 231BF PER A320 AMM 53-00-00-400-801-A
Part: FLOOR PANEL — DENTED · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN FLOOR PANEL 231KF HAS DENTS ON UPPER SURFACE. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 231KF PER A320 AMM 53-00-00-400-801-A.
Part: FLOOR PANEL — DELAMINATED · airframe 37,609 hrs · 12,514 cycles
MAIN CABIN FLOOR PANEL 231MF HAS E EA DAMAGED AREAS ON UPPER SURFACE GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 231MF PER A320 AMM 53-00-00-400-801-A02.
Part: FLOOR PANEL — DELAMINATED · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN FLOOR PANEL 261PF R/H AFT CORNER HAS INSERT PULLED OUT. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 261PF AT FR68 - FR70, RBL49 IAW A320 AMM 53-00-00-400-801-A-02 AND AMM 53-00-00-000-801-A-01.
Part: FLOOR PANEL — PUNCTURED · airframe 37,609 hrs · 12,514 cycles
MAIN CABIN FLOOR PANEL 231CF HAS A PUCTURE ON UPPER SURFACE. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 231CF PER A320 AMM 53-00-00-400-801-A
Part: FLOOR PANEL — DELAMINATED · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN FLOOR PANEL 232LF HAS SEVERAL AREAS DAMAGED AREAS ON UPPER SURFACE. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 232LF PER A320 AMM 53-00-00-400-801-A.
Part: FLOOR PANEL — CORRODED · corrosion level 2 · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN FLOOR PANEL 261LG UPPER AND LOWER SURFACE HAS CORROSION AT L2 DOOR. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 261LG AT FR66 - FR68, STR 23L IAW A320 AMM 53-00-00-000-801-A-02 AND AMM 53-00-00-000-801-A-01.
Part: FLOOR PANEL — DELAMINATED · airframe 37,609 hrs · 12,514 cycles
MAIN CABIN FLOOR PANEL 242HF HAS BROKEN INSERT. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 242HF PER A320 AMM 53-00-00-400-801-A.
Part: FLOORBOARD — DAMAGED · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN FLOOR BOARD 242LF 2EA CORNERS DAMAGED. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR BOARD 242LF AT FR42 TO FR52 RBL52 IAW A320 AMM 53-10-000-801-A-01 AND 53-00-00-400-801-A.
Part: FLOOR PANEL — GOUGED · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN FLOOR PANEL 221EF AT L1 DOOR HAS SEVERAL DENTS AND PUNCTURE DAMAGE. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 221EF AT L1 DOOR IAW A320 AMM 53-00-00-400-801-A.
Part: BRACKET — BROKEN · airframe 37,839 hrs · 12,607 cycles
FLOOR SUPPORT BRACKET UNDER PANEL 221DF ON FR31 IS BROKEN OFF. GROUNDED - YES. REMOVED AND REPLACED FLOOR SUPPORT BRACKET/FLOOR FITTING UNDER FLOOR PANEL 221DF AT FR19 IAW A320 SRM 51-72-11-911-001.
Part: FLOOR PANEL — DELAMINATED · airframe 37,609 hrs · 12,514 cycles
MAIN CABIN FLOOR PANEL 222EF AT R1 DOOR HAS MULTIPLE LARGE DENTS. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 222EF PER A320 AMM 53-00-00-400-801-A.
Part: GIRT BAR — CORRODED · corrosion level 2 · airframe 37,839 hrs · 12,607 cycles
MAIN CABIN R2 DOOR GIRT BAR FITTING BLANKING PLATE CORRODED. GROUNDED - YES. REMOVED AND REPLACED R2 DOOR GIRT BAR BLANKING PLATE AT FR68, STR23 IAW A320 AMM 52-13-31-400-003-A.
Earlier reports · 2012–2022 · 10 reports
2022
Part: AIRBAG — DEPLOYED (SEAT ROW 6 LEFT) · airframe 37,519 hrs · 12,481 cycles
SEATBELTS AIRBAGS WENT OFF ROW 6 LEFT. ROW 6ABC AIRBAG SEATBELTS (3 EACH) DEPLOYED AT THE GATE PRIOR TO DEPARTURE WITH PASSENGERS SEATED AND SEATBELTS FASTENED. GROUNDED - YES. REMOVED AND REPLACED SEAT ASSY TRIPLE ROW 6 A/C LEFT SIDE
Part: RUDDER — UNKNOWN (VERTICAL STABILI) · airframe 37,136 hrs · 12,327 cycles
DURING CLIMB PHASE AT 15000 MEDIUM FREQUENCY LATERAL AIRFRAME VIBRATION DETECTED IN COCKPIT AND THROUGHOUT ALL CABIN ZONES (MODERATE LEVEL) ENGINE VIBES NORMAL, VIBRATION CONTINUES UNTIL FL200 WITH AUTOPILOT ENGAGED, DISENGAGED, ALL SPEEDS BETWEEN 280KTS-330KTS, ROLL INPUTS, ELEV INPUTS AND THRUST INPUTS HAD NO EFFECT. GROUNDED - YES. REMOVED AND REPLACED RUDDER S/N TS6111 ARM BEARINGS #1,2, 3, 4, 5, AND #7 IAW A320 AMM 55-36-42-300-004 AND AMM 27-21-41-200-001-A. ALL OPS CHECK GOOD OF RUDDER SERVOS PER A320 AMM 27-34-00-200-001 AND AMM 27-34-00-710-001-A.
2017
Part: SLIDE — UNSERVICEABLE (CABIN) · airframe 23,986 hrs · 7,261 cycles
IN PDX A MISSING BALL LOCK WAS DISCOVERED ON THE LEFT OVERWING SLIDE CONTAINER. THE AIRCRAFT WAS REMOVED FROM REVENUE SERVICE AND FERRIED TO SFO FOR REPAIR. THE SLIDE ASSEMBLY WAS REPLACED IN SFO AND THE AIRCRAFT WAS RETURNED TO SERVICE. ACCORDING TO THE OPERATOR`S RECORDS, ALL AIRWORTHINESS DIRECTIVES, SERVICE BULLETINS, STC`S AND PMA`S ARE IN FULL COMPLIANCE WITH THE TYPE DESIGN CERTIFICATE AND ASSOCIATED REGULATORY REQUIREMENTS.
Part: STEERING SYS — FALSE INDICATION (NLG)
NLG STEERING FAULTED IN FLIGHT, RESET ON GROUND AFTER LANDING. CREW DECLARED AN EMERGENCY, LANDED SAFELY AND THE FAULT CLEARED AFTER LANDING . PERFORMED TSM 32-51-00-81-08-26A. UNABLE TO DUPLICATE FAULT. SYSTEM TESTED OK. AFTER FURTHER TROUBLESHOOTING, THE BSCU WAS REPLACED AS A PRECAUTION.
2015
Part: GIRT BAR — FOD (R1 DOOR) · airframe 15,142 hrs · 4,593 cycles
AIRCRAFT WAS GETTING READY TO OPERATE FLIGHT WHEN R1 DOOR WOULD NOT ARM. FOUND GIRT BAR JAMMED AGAINST FLOOR FITTING. REMOVED DEBRIS STUCK BETWEEN FITTING AND GIRT BAR. DOOR ARMS OK.
2014
Part: COMPUTER — MALFUNCTIONED
DURING DESCENT, ACTUATOR PITCHED UP DRAMATICALLY ON APE 2 BETWEEN 30K FT. AND 25K FT. FAULT WAS ISOLATED TO ADD 2 AND ADR 2 WAS PLACED ON MEL. OUTBID FLIGHT HAD A 1:23 MIN DELAY. TROUBLESHOOTING AND RESOLUTION DOCUMENTED BELOW; ITS YAW AS 34-44-02, AIRS SENSORS 11FP2, TAT 2, CONTINUITY TO AIRS 2, FOUND .537 K OHMS AT PIN 8J AND 8H AT PLUG SIDE OF AIRS 2. REMOVED PLUG FROM TAT 2 AND JUMPED INSERT J AND E CONTINUES, REMOVED JUMPER FROM PLUG AT TAT 2 AND READ OPENS AT PINS 8H AND 8J OF AIRS 2. ACT RETURNED TO ORIGINAL CONFIGURATION FOR DEPARTURE. ITEM REMAINS DEFERRED. YAW TAM 22-83-00-810-874-A, INTERFACE TEST OF ADD REF AM 34-13-00-740-002 PASSED. INTERFACE TEST OF IRE SYS REF AM 34-14-00-740-001 PASSED. PERFORMED TAM 22-83-00-810-874-A. INTERFACE TEST OF ADD REF AM 34-13-00-740-002 PASSED, INTERFACE TEST OF IRE SYS REF AM 34-14-00-740-001 PASSED. PERFORMED AIRS SENSOR WIRING CHECK BETWEEN TAT 2 AND ADIEU 2 YAW AS 34-11-02 CONTINUITY AND INSULATION GOOD. THE MADDER 24367 REMAIN OPEN. TROUBLESHOOTING UPDATED ON TAX. MORE TROUBLESHOOTING NEEDED YAW TAM 34-11-810-865-A, FOUND PHC2 INOPERATIVE. R & R PHI 6DA2, YAW AM 31-31-34. GOOD OPS TEST. ADD YAW AM 34-13-00-740-003-A.
Part: PACKING — DAMAGED (OIL COOLER)
AIRCRAFT PREPARING FOR DEPARTURE, HAD SMOKE IN THE COCKPIT AND CABIN AFTER SELECTING APU BLEED ON. APU WAS INSPECTED FOR LEAKS AND DEPARTED WITH NO FURTHER SMOKE ISSUES. APU WAS INSPECTED AND TROUBLESHOT ON ITS RON MAINTENANCE, FOUND THE OIL TUBE PACKING OF THE OIL COOLER DAMAGED AND LEAKING. THE OIL COOLER TUBE PACKING WAS REPLACED AND BOTH LEAK AND OPS CHECK WITH NO FURTHER ISSUES.
2012
Part: SHOCK ABSORBER — MALFUNCTIONED (NLG)
DURING ROTATION, RETRACTED GEAR AND RECEIVED NLG SHOCK ABSORBER ECAM MESSAGE. GEAR HANDLE WOULD NOT ALLOW SELECTION TO UP POSITION AFTER SECOND TRY ABOUT 10 SECONDS LATER WITH NO CHANGE CREW SENT MESSAGE VIA ACARS OF FAULT AND WERE INSTRUCTED TO RETURN TO DEPARTURE. UNEVENTFUL LANDING AT DEPARTURE, PERFORMED TSM 32-31-00-810-868A, 32-21-00-200-002A AND SERVICED NLG STRUT IAW AMM 12-12-32-611-005A. MX REPLACED NLG SHOCK ASORBER IAW AMM 32-21-13.
Part: WARNING SYSTEM — MALFUNCTIONED (COCKPIT)
DURING ROTATION AND ATTEMPTED GEAR RETRACTION, THEY RECEIVED A NLG SHOCK ABSORBER ECAM WARNING. THE GEAR HANDLE WOULD NOT ALLOW SELECTION TO THE UP POSITION DUE TO THE FAULT. IN APPROX 30 SECONDS, THE MESSAGE WENT AWAY AND A NORMAL RETRACTION WAS ACCOMPLISHED. THE CREW ACCOMPLISHED ANOTHER SUCCESSFUL RETRACTION AND EXTENSION CYCLE. RETURN TO DEPARTURE AND DECLARED AN EMERGENCY. AFTER AN UNEVENTFUL LANDING, MX MET THE ACFT AND ACCOMPLISHED TSM 32-31-00-810-868-A. THE TSD BITE DATA WAS PULLED FOR BOTH LGCIU 1 AND 2. THE 1ST AND 4TH WORDS FOR EACH LGCIU WERE CONSISTENT INDICATION THE FAULT OCCURRED DURING FLIGHT PHASE 4 AND DID NOT REQUIRE ANY FURTHER MX ACTION IAW THE TSM. THE DATA WAS ALSO SENT TO MFG AOG SUPPORT. THEY ALSO CONCLUDED THAT NO FURTHER ACTION WAS REQUIRED DUE TO TRIGGER COULD BE SLOW ROTATION. A LUBE WAS ACCOMPLISHED ON THE NLG AND DOORS. THE ACFT WAS RETURNED TO SERVICE.
Part: MECHANISM — LACK OF LUBE (L2 DOOR SLIDE) · airframe 2,497 hrs · 755 cycles
PRIOR TO DEPARTURE, THE CREW NOTIFIED MX CONTROL THAT L2 DOOR WOULD NOT ARM. THE ACFT WAS TAKEN OUT OF SERVICE AND WAS SWAPPED. MX FOUND THE SLIDE EXTENSION CONTROL MECHANISM WAS STIFF AND NOT ALLOWING FULL MOVEMENT. COMPLIED WITH LUBE OF SLIDE EMERGENCY CONTROL HANDLE MECHANISM, IAW AMM 52-13-22-05. SYS OPS CHECKED GOOD IAW AMM 52-13-22-05. ACFT RETURNED TO SERVICE.