# Service difficulty reports: N443UA

A list on [N443UA](https://openairdocs.org/aircraft/N443UA.md).

Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.

Page 1 of 3 · 126 reports

- [SDR CALA2026091119377](https://openairdocs.org/sdr/CALA2026091119377.md): Unknown · odor · Sep 9, 2026 · N443UA · Airbus A320232 · Air Distribution System
  > MOMENTARY BURNING ODOR WITH INTERMENT FLASHING MASTER WARNING LIGHT NO ECAM. INSPECTED FLIGHT DECK AND ELECTRONICS BAY, NO EVIDENCE OF BURNING ODOR FOUND, SUSPECTED RELATED TO SDAC FAILURE REF TO LOG PAGE 3287185.
- [SDR CALA2026091119373](https://openairdocs.org/sdr/CALA2026091119373.md): Sdac · faulted · Sep 9, 2026 · N443UA · Airbus A320232 · Central Warning
  > BLUE/YELLOW HYD PRESSURE DOUBLE AMBER XS ONSD PAGE. FLT CTL SD PAGE SHOWING ONLY G SYS. ISOLATED SDAC 2, CIRCUIT BREAKERS PULLE D FOR TROUBLESHOOTING, ALL HYD INDS RETURNED TO NORMAL. REPLACED BOTH SDACS & RAN GROUND SCANNING OF THE CENTRAL WARNING SYS IAW A
- [SDR CALA2026060216757](https://openairdocs.org/sdr/CALA2026060216757.md): Battery · faulty · May 31, 2026 · N443UA · Airbus A320232 · Emergency Lighting
  > WHILE PERFORMING CABIN EMERGENCY LIGHTING. FOUND EPSU BATTERY EMER R FAULTING. REMOVED AND REPLACED EMEMGENY PSU BATTERY REF AMM 33-51-38.OPS CHECK GOOD AT THIS TIME.PARTS USED: 18-3351-3-0001,QTY:1
- [SDR CALA2026033114968](https://openairdocs.org/sdr/CALA2026033114968.md): Landing Light · damaged · Mar 30, 2026 · N443UA · Airbus A320232 · Exterior Lighting
  > RIGHT WING LANDING LIGHT BULB ASSY AND CLAMP MISSING REMOVED AND REPLACED LANDING LIGHT IAW AMM TASK 33-42-11,. OPS CHECK OK CHECK THE AREA NO ACFT DAMAGE FOUND.
- [SDR CALA2026032014715](https://openairdocs.org/sdr/CALA2026032014715.md): Fuel Cap · missing · Mar 17, 2026 · N443UA · Airbus A320232 · Fuel Storage
  > FUEL CAP MISSING ON ARRIVAL. REPORTED BY FLIGHT CREW, LOG PAGE 8245214 FOR MX ACTION. ITEM PLACED ON CDL.
- [SDR CALA2025081507842](https://openairdocs.org/sdr/CALA2025081507842.md): Battery · no test · Aug 15, 2025 · N443UA · Airbus A320232 · Emergency Lighting
  > ALL 4 EPSU BATTERIES REQUIRE REPLACEMENT. REMOVED AND REPLACED THE EPSU BATTERIES IAW AMM 33-51-38-400-002-A. OPS CHECKED GOOD.
- [SDR CALA2025070806323](https://openairdocs.org/sdr/CALA2025070806323.md): Handle · binding · Jul 4, 2025 · N443UA · Airbus A320232 · Passenger/Crew Doors
  > AFT EMERGENCY DOOR HANDLES ON INTERIOR FA REPORTS HANDLES HAVE R ESTRICTED MOVEMENT. CHECKED BOTH AFT PASS DOORS ARMING AND DID ARMING WIRH NO ISSUES, CHKD OPEN AND CLOSE AND NO ISSUES, THRESHOLD IS CLEAR, REF AMM 52-13-11.
- [SDR CALA2024021300410](https://openairdocs.org/sdr/CALA2024021300410.md): Skin · corroded · Feb 6, 2024 · N443UA · Airbus A320232 · Nacelle/Pylon, Plate/Skin
  > DOT 86-58 #1 PYLON IB SAIL TAIL PANEL HAS CORROSION &HEAT DAMAGE AROUOND LOWER RIVETS ()
- [SDR CALA2024020500320](https://openairdocs.org/sdr/CALA2024020500320.md): Skin · corroded · Feb 3, 2024 · N443UA · Airbus A320232 · Fuselage Main, Plate/Skin
  > AFT FUSELAGE TOILET WASTE DISPOSAL VENT/EXHAUST IS CORRODED 204- 05. () REPAIRED AFT TOILET WASTE VENT AREA BY DOUBLER IAW SRM 53-41-11- 300-004 MAJOR REPAIR CAT A 44-0008 ATTACHED. WORK A CCOMPLISHED AT ST ENGINEERING OF MOBILE AT BFM ON NR#: 85591
- [SDR CALA2024020500316](https://openairdocs.org/sdr/CALA2024020500316.md): Skin · corroded · Feb 1, 2024 · N443UA · Airbus A320232 · Nacelle/Pylon, Plate/Skin
  > CORROSION NOTED ON THE RH PYLON AFT FIXED FAIRING I/B SKIN
- [SDR CALA2023121103624](https://openairdocs.org/sdr/CALA2023121103624.md): Eec · faulty · Dec 7, 2023 · N443UA · Airbus A320232 · Fuel Controlling System
  > ENG2 SENSOR FAULT CREW ALSO INDICATED THE ENG2 DID ROLL BACK AND RECOVERED. ATTACHING PFR TO LOG SFOEP INFO: ECM SHOWS SHIFT IN PB PLS RPL THE EEC AND PB FLEX LI NE AT THE EEC SEE IPC 73-22-49-89C OR IF PRE SB 73-0198 THEN IPC 73-22-49-89-A. ADD FAULT: PBSTL
- [SDR CALA2022053001403](https://openairdocs.org/sdr/CALA2022053001403.md): Intake Valve · corroded · May 30, 2022 · N443UA · Airbus A320232 · Fuselage Main, Frame
  > CORROSION FOUND ON LH AVIONICS VENTILATION AIR INTAKE VALVE BETWEEN FR21-22 STGR 31L-32L. -A23F-53-12879-00-FINAL, COVERED BY ECRA5311-02818. CLASSIFIED A 02818.INITIATE DTA DIP FOR REINSPECT AS FOLLOWS: "ON OR BEFORE FOR AVIONICS INLET VALVE PER PART 2 OF THE
- [SDR CALA2022053001372](https://openairdocs.org/sdr/CALA2022053001372.md): Coupling · corroded · May 27, 2022 · N443UA · Airbus A320232 · Standard Practices/Structures
  > FR 64 STRG 44 AND 43R COUPLINGS REMOVAL OF STRINGER COUPLINGS LOCATED AT STRG 43R-44 UNDER FR 64 REQUIRED FOR CORROSION EVALUATION ON FR 64 BUTTSTRAP AFT SIDE BETWEEN STRG 43R-44. AS NOTED ON LTPR NR# 5001146904-0030. EVALUATED CORROSION ON COUPLINGS ON STR''S
- [SDR CALA2022053001370](https://openairdocs.org/sdr/CALA2022053001370.md): Fitting · gouged · May 27, 2022 · N443UA · Airbus A320232 · Fuselage Main, Frame
  > GOUGE ON WINDSHIELD LWR FITTING & SPLICE. UPON REMOVAL OF FOWARD SKIN PANEL AND FALSE FRAME, GOUGE FOUND ON WINDSHIELD LOWER FITTING AND SPLICE. EVALUATION IS REQUIRED. AS NOTED ON LTPR NR# 5001142616-0060. REPAIRED THE LWR FITTING & SPLICE GOUGES AT LH WINDSH
- [SDR CALA2022053001369](https://openairdocs.org/sdr/CALA2022053001369.md): Beam · corroded · May 27, 2022 · N443UA · Airbus A320232 · Fuselage Main, Attach Fittings
  > DURING INSPECTION OF CABIN FLOOR AFT ENTRANCE AREA FOUND CORROSION ON L2 DOOR SILL BEAM AT FR68. PREVIOUSLY REPAIRED. EVALUATE IAW A320 SRM CURRENT REVISION. SEQ#1980,ZONE:200 AS NOTED ON LTPR NR#5001143284-0010. PERFORMED BY LTPR BQN. REPAIR TO BE PERFORMED I
- [SDR CALA2022053001368](https://openairdocs.org/sdr/CALA2022053001368.md): Stringer · corroded · May 27, 2022 · N443UA · Airbus A320232 · Standard Practices/Structures
  > STRINGER 44 CORROSION BTWN FR64-65, DURING REMOVAL OF COUPLING AT FR 64 STRG 44 FOUND CORROSION SPOT ON STRINGER 44 WEB EVALUATION IS REQUIRED AS NOTED ON LTPR NR#5001146904-0040. PREFORMED REPAIR OF THE FR64 STR44 PER ECRA 5341-1316 AND EO-A32F-53-12768-00-FI
- [SDR CALA2022053001367](https://openairdocs.org/sdr/CALA2022053001367.md): Door Seal · corroded · May 27, 2022 · N443UA · Airbus A320232 · Standard Practices/Structures
  > CORROSION ON DOOR SEAL ATTACHEMENT HOLE UNDERNEATH GIRT BAR FITTING AT FR66 R2. (A3NB-53-3-6222, SEQ#1980, ZONE 262) LTPR NR# 5001144991-0010. REF LTPR BQN LOG 5001144991-0010. FOUND CORROSION ON DOOR SILL PERFORMED REPAIR IAW A320 SRM 53-41-14-300-001 REPAIR
- [SDR CALA2022053001366](https://openairdocs.org/sdr/CALA2022053001366.md): Buttstrap · corroded · May 27, 2022 · N443UA · Airbus A320232 · Fuselage Structure (General)
  > DURING AFT CARGO INSPECTION CORROSION WAS FOUND ON THE BUTTSTRAPAT FR64, BTW STRG 44-43R AS NOTED ON LTPR NR#5001146904-0010. REWORKED CORROSION ON BUTTSTRAP FR64, STR 43-44R NDT HFEC ADDITIONAL REQUIREMENTS, REF LP 8685828 AND ROTO INSPECTED WITH NIL FINDINGS
- [SDR CALA2022053001376](https://openairdocs.org/sdr/CALA2022053001376.md): Stringer · corroded · May 27, 2022 · N443UA · Airbus A320232 · Fuselage Floor Panel
  > SEVERAL CORROSION FOUND ON FWD CRG COMP LOWER AREA FR 29-39/STGR 41 AS NOTED ON LTPR NR# 5001160885-0010. WITH NO CRACKS NOTED, LENGTH OF DAMAGE IS GREATER THAN 200MM, FR29-FR30 PER SRM 53-21-13-300-003, CAT "B" REPAIR, INSPECTION WHICHEVER COMES FIRST, SUBSEQ
- [SDR CALA2022053001375](https://openairdocs.org/sdr/CALA2022053001375.md): Panel · elongated · May 27, 2022 · N443UA · Airbus A320232 · Fuselage Floor Panel
  > DURING HMV IN BQN AFTER REMOVAL OF THE BELLY FAIRING PNL AT FR34, FOUND SEVERAL FASTENER HOLES ELONGATED. ORIGINAL HOLE DIA IS 5/32IN. REPAIR OF THE EFFECTED HOLES REQUIRED PER EO-A32F-53-12319-00-WIP COVERED BY ECRA 5321-02074 MM) HILOCK IN HOLES #3,4,5,8,15,
- [SDR CALA2022053001374](https://openairdocs.org/sdr/CALA2022053001374.md): Window Frame · cracked · May 27, 2022 · N443UA · Airbus A320232 · Fuselage Main, Frame
  > WINDSHIELD FRAME LH CONTINUITY FITTING FOUND CRACKED WINDSHIELD FRAME LH CONTINUITY FITTING REPAIRED PER ECRA 5311- 02813 CAT "A" PERMENENT REPAIR RII REQ CW U 247351
- [SDR CALA2022053001373](https://openairdocs.org/sdr/CALA2022053001373.md): Fitting · cracked · May 27, 2022 · N443UA · Airbus A320232 · Fuselage Main, Frame
  > CENTER POST LH CONTINUITY FTG FOUND CRACKED ON UPPER CORNER SEQ: 1543, LTPR NR# 5001143616-0050. REMOVED AND REPLACED BULKHEAD STIFFENER AT FR1 AFT SIDE PER SRM 51-72-11-911-001 RII REQS ARE CW U247351
- [SDR CALA2022052301308](https://openairdocs.org/sdr/CALA2022052301308.md): Fitting · loose · May 20, 2022 · N443UA · Airbus A320232 · Empennage Structure
  > RUDDER HINGE BEARINGS/FITTINGS BR2, BR3, BR4 AND BR7 HAVE EXESSIVE PLAY. LTPR NR# 5001148819-0010 RUDDER HINGE FITINGS ASSY''S BR2, BR3, BR4 & BR7 REPL''ED IAW SRM 55-36-42-300-008, CAT "A" MAJOR REPAIR, PERMANENT WITH NO ADD''L INSPECTION REQUIREMENTS RII AC
- [SDR CALA2022052301307](https://openairdocs.org/sdr/CALA2022052301307.md): Fitting · loose · May 20, 2022 · N443UA · Airbus A320232 · Empennage Structure
  > RUDDER HINGE BEARINGS/FITTINGS BR1 AND BR5 HAVE EXCESSIVE PLAY. LTPR NR# 5001148819-0010 AT 60000FC FROM TIME OF COMPONENT FIRST FLIGHT, SUBSEQUENT SRI 55-36-42-205-004 INSPECTION INTERVALS AND METHOD OF INSPECTION ARE TBD IAW RUDDER HINGE FITINGS ASSY''S BR 1
- [SDR CALA2022052001305](https://openairdocs.org/sdr/CALA2022052001305.md): None · none · May 20, 2022 · N443UA · Airbus A320232 · Empennage Structure
  > RUDDER HINGE BEARINGS/FITTINGS BR2, BR3, BR4 AND BR7 HAVE EXESSIVE PLAY. LTPR NR# 5001148819-0010 RUDDER HINGE FITINGS ASSY''S BR2, BR3, BR4 & BR7 REPL''ED IAW SRM 55-36-42-300-008, CAT "A" MAJOR REPAIR, PERMANENT WITH NO ADD''L INSPECTION REQUIREMENTS
- [SDR CALA2022052001289](https://openairdocs.org/sdr/CALA2022052001289.md): None · none · May 18, 2022 · N443UA · Airbus A320232 · Fuselage, Wing Attach Fittings
  > FR68 LHS AFT DOOR STOP FITTING #1 TO #7 HOLES FOUND BEYOND THE REQUIRED STARTING HOLE DIAMETER OF 8-1-N AS PER EA 5340-01724 REV.C, OPERATION 002 STEP 6.1 FIGURE 01 SHEET 02. ZONE 260, SEQ 1605, LTPR NR# 5001155215-0010. RPR IS CONSIDERED CAT B. REINSPECT IAW
- [SDR CALA2022052001288](https://openairdocs.org/sdr/CALA2022052001288.md): None · none · May 18, 2022 · N443UA · Airbus A320232 · Fuselage, Wing Attach Fittings
  > FR68 RHS AFT DOOR STOP FITTING #1 TO #7 HOLES FOUND BEYOND THE REQUIRED STARTING HOLE DIAMETER OF 8-1-N AS PER EA 5340-01724 REV.C, OPERATION 002 STEP 6.2 FIGURE 01 SHEET 02. ZONE 260, SEQ 1605, LTPR NR# 5001155217-0010. RPR IS CONSIDERED CAT B. REINSPECT IAW
- [SDR CALA2022052001287](https://openairdocs.org/sdr/CALA2022052001287.md): None · none · May 18, 2022 · N443UA · Airbus A320232 · Fuselage, Wing Attach Fittings
  > FR66 LHS AFT DOOR STOP FITTINGS #1 TO #7 HOLES FOUND BEYOND THE REQUIRED STARTING HOLE DIAMETER OF 8-1-N AS PER EA 5340-01724 REV.C OPERATION 001 STEP 6.1 FIGURE 01 SHEET 02. ZONE 260 SEQ:1602. LTPR NR 005001155209-0010. RPR IS CONSIDERED CAT B. REINSPECT IAW
- [SDR CALA2022052001286](https://openairdocs.org/sdr/CALA2022052001286.md): None · none · May 18, 2022 · N443UA · Airbus A320232 · Fuselage, Wing Attach Fittings
  > FR66 RHS AFT DOOR STOP FITTING #1 TO #7 HOLES FOUND BEYOND THE REQUIRED STARTING HOLE DIAMETER OF 8-1-N AS PER EA 5340-01724 REV.C OPERATION 001 STEP 6.2 FIGURE 01 SHEET 02. ZONE:260 SEQ:1602. LTPR NR# 5001155213-0010. RPR IS CONSIDERED CAT B. REINSPECT IAW SR
- [SDR CALA2022051601261](https://openairdocs.org/sdr/CALA2022051601261.md): Fitting · none · May 16, 2022 · N443UA · Airbus A320232 · Fuselage, Wing Attach Fittings
  > FR68 RHS AFT DOOR STOP FITTING #1 TO #7 HOLES FOUND BEYOND THE REQUIRED STARTING HOLE DIAMETER OF 8-1-N AS PER EA 5340-01724 REV.C, OPERATION 002 STEP 6.2 FIGURE 01 SHEET 02. ZONE 260, SEQ 1605, LTPR NR# 5001155217-0010. RPR IS CONSIDERED CAT B. REINSPECT IAW
- [SDR CALA2022051601260](https://openairdocs.org/sdr/CALA2022051601260.md): Frame · none · May 16, 2022 · N443UA · Airbus A320232 · Fuselage, Wing Attach Fittings
  > FR66 RHS AFT DOOR STOP FITTING #1 TO #7 HOLES FOUND BEYOND THE REQUIRED STARTING HOLE DIAMETER OF 8-1-N AS PER EA 5340-01724 REV.C OPERATION 001 STEP 6.2 FIGURE 01 SHEET 02. ZONE:260 SEQ:1602. LTPR NR# 5001155213-0010. RPR IS CONSIDERED CAT B. REINSPECT IAW SR
- [SDR CALA2022051601259](https://openairdocs.org/sdr/CALA2022051601259.md): Frame · none · May 16, 2022 · N443UA · Airbus A320232 · Fuselage, Wing Attach Fittings
  > FR68 LHS AFT DOOR STOP FITTING #1 TO #7 HOLES FOUND BEYOND THE REQUIRED STARTING HOLE DIAMETER OF 8-1-N AS PER EA 5340-01724 REV.C, OPERATION 002 STEP 6.1 FIGURE 01 SHEET 02. ZONE 260, SEQ 1605, LTPR NR# 5001155215-0010. RPR IS CONSIDERED CAT B. REINSPECT IAW
- [SDR CALA2022051601258](https://openairdocs.org/sdr/CALA2022051601258.md): Fitting · none · May 16, 2022 · N443UA · Airbus A320232 · Fuselage, Wing Attach Fittings
  > FR66 LHS AFT DOOR STOP FITTINGS #1 TO #7 HOLES FOUND BEYOND THE REQUIRED STARTING HOLE DIAMETER OF 8-1-N AS PER EA 5340-01724 REV.C OPERATION 001 STEP 6.1 FIGURE 01 SHEET 02. ZONE 260 SEQ:1602. LTPR NR 005001155209-0010. RPR IS CONSIDERED CAT B. REINSPECT IAW
- [SDR CALA2022050201112](https://openairdocs.org/sdr/CALA2022050201112.md): Beam · none · Apr 30, 2022 · N443UA · Airbus A320232 · Fuselage Structure (General)
  > REF ECRA 5311-02806 CROSSBEAM LAYER HOLE 8 FR16 RHS AND HOLE 26 FR20 LHS HAVE BEEN REPAIRED PER PART 1 STEP 1 ACCOMPLISH REINSPECT AS FOLLOWS - INSPECT HOLE #8 AT FR16 RHS AND HOLE 26 AT FR20 LHS ON OR BEFORE A/C 6443 REACHES 78337 TOTAL FLIGHT CYCLES PER PART
- [SDR CALA2022050201109](https://openairdocs.org/sdr/CALA2022050201109.md): Frame · none · Apr 29, 2022 · N443UA · Airbus A320232 · Fuselage Main, Structure
  > FR20 LHS DOUBLE JOGGLE HOLE #8 FOUND OVERSIZED, CHECK AS PER UAL EA 5311-02442 REV ORIG OP 003 STEP 9.1, ZONE 200, SEQ 1552, LTPR NR# 5001153054-0010. REPAIRED HOLE #8 ON THE LHS FR 20 DOUBLE JOGGLE PER ECRA 5311-02804 STEPS 1-20 WITH NO DEVEATIONS
- [SDR CALA2022050201108](https://openairdocs.org/sdr/CALA2022050201108.md): Frame · none · Apr 29, 2022 · N443UA · Airbus A320232 · Fuselage Main, Structure
  > FR20 RHS DOUBLE JOGGLE HOLE #5 & #6 FOUND OVERSIZED, CHECK AS PER UAL EA 5311-022442 REV ORIG. OP 004 STEP 9.1 ZONE 200 SEQ 1555, LTPR NR# 5001150764-0010. REPAIRED HOLES 5 AND 6 ON THE RHS DOUBLE JOGGLE PER ECRA 5311-02804 STEPS 1-20 WITH NO DEVEATIONS
- [SDR CALA2022042101036](https://openairdocs.org/sdr/CALA2022042101036.md): Frame · cracked · Apr 20, 2022 · N443UA · Airbus A320232 · Fuselage Main, Frame
  > FR43 FOOT LH HOLE INSPECTED FOUND CRACK, SEQ# 1564, EA 5330-6692 REV. B, LTPR NR# 5001143526-0010. FR43 LH SEGMENT AND FITTING FOUND WITH CRACK, PERFORMED REAMING UAL EA 5330-06692 REV. B, OPERATION 003, WITH REPAIR DRAWING OF HOLE TO REMOVE CRACK UP TO 9.3MM,
- [SDR CALA2022042101035](https://openairdocs.org/sdr/CALA2022042101035.md): Frame · cracked · Apr 20, 2022 · N443UA · Airbus A320232 · Fuselage Main, Frame
  > CRACK FOUND ON RH DOUBLE JOGGLE FR 16 HOLE #6, A, C SEQ#: 1549 EA 5311-02442 REV. ORIGINAL OPERATION 002. LTPR NR# 500143283-0010. CRACK FOUND ON FR16 RHS DOUBLE JOGGLE HOLES #6, #A, #C AND #E. COMPLETED REPAIR ON LEADER (CRACK) HOLES #6, #A, #C, #E AND ASSOCI
- [SDR CALA2021123002485](https://openairdocs.org/sdr/CALA2021123002485.md): Fastener · missing · Dec 30, 2021 · N443UA · Airbus A300* · Fuselage Main, Plate/Skin
  > PDA 3 FASTENER MISSING ON PANEL 191KB OUTBOARD SIDE 4 FROM THE AFT. SEE LOGPAGE 7715638 FOR DIP. PER LP 7715638 OK TO CARRY FO 30 F/C''S PER AMM 53-35-00-200-002, REQUIRES INSPECTION EVERY 10 F/C''S
- [SDR CALA2019080431297](https://openairdocs.org/sdr/CALA2019080431297.md): Pressure Panel · cracked · Aug 2, 2019 · N443UA · Airbus A320232 · Fuselage Main, Structure
  > RH PRESSURE PANEL BETWEEN FR35-36 ROTO INSP REVEALS CRACK IN PRE SSURE PANEL LAYER AT HOLE A CRACK RADIATING IN THE 6 O''CLOCK POS. REPAIRED THE R/H SIDE PRES SURE PANEL AT FR35/36 IAW ECRA 5331-02426 PART 1. ACCOMPLISHED T HE PERMANENT REPAIR AT FR35/36 LH/R
- [SDR CALA2018101502119](https://openairdocs.org/sdr/CALA2018101502119.md): Engine · making metal · Oct 15, 2018 · N443UA · Airbus A320232 · Engine (Turbine/Turboprop)
  > CREW STATED TO LOCAL MAINTENANCE THAT DURING CLIMB THRUST AT 13,00FT, 300KTS AIRSPEED HEARD A LOUD BANG FROM AN ENG1 COMPRESSOR STALL FOLLOWED BY VERY HIGH EGT TEMP OF 735+, CREW FOLLOWED QRH AND SHUT DOWN ENG AND BLEW THE FIRE BOTTLE. AIRCRAFT RETURNED TO THE
- [SDR CALA2017050501268](https://openairdocs.org/sdr/CALA2017050501268.md): Terminal · broken · May 5, 2017 · N443UA · Airbus A320232 · Light System Wiring
  > AFT SIDE OF CENTER CEILING EMERGENCY EXIT LIGHT DOES NOT ILLUMINATE. FOUND GROUND TERMINAL AT 6919VN BROKEN. REPAIRED PER AWM 33-51- 03, AND OPS CHECK GOOD PER AMM 33-51-00.
- [SDR CALA2017042801165](https://openairdocs.org/sdr/CALA2017042801165.md): Battery · discharged · Apr 28, 2017 · N443UA · Airbus A320232 · Emergency Lighting
  > EEL TEST 2 SV, FAILS EPSU BATTERY AFT L. REPLACED EPSU BATTERY AFT LEFT, REF AMM 33,51-38. EEL TEST PASS.
- [SDR CALA2017012300174](https://openairdocs.org/sdr/CALA2017012300174.md): Battery Pack · malfunctioned · Jan 23, 2017 · N443UA · Airbus A320232 · Emergency Lighting
  > EPSU BATTERY RIGHT FAILED A TEST WITH BATTERY FAULT. REMOVED AND REPLACED THE BATTERY PACK, OP CHECKED NORMAL IAW AMM 33-51-38.
- [SDR CALA2015111794835](https://openairdocs.org/sdr/CALA2015111794835.md): Stringer · corroded · Nov 12, 2015 · N443UA · Airbus A320232 · Fuselage Main, Longeron/Stringer
  > STRINGER 41R, BETWEEN FRAME 31 - 32 HAS CORROSION. PERFORMED STINGER SPLICE REPAIR IAW SRM 53-21-13 PARA 5C FIG 203 SHEET 3. SRI53-21-13-2-003-00 TBL 204 REQUIRES INSPECTION AT 60,000C FROM ACFT 1ST FLIGHT.
- [SDR CALA2015110394784](https://openairdocs.org/sdr/CALA2015110394784.md): Door Sill · corroded · Oct 30, 2015 · N443UA · Airbus A320232 · Fuselage Miscellaneous Structure
  > L1 DOOR SILL IS CORRODED AFT GIRT BAR ATTACH HOLES, INBD & OTBD AFT & INBD FWD. SPOT FACED & INSTALLED THREE EACH REPAIR WASHERS IAW SRM 53-11-14 PARA E. HFEC CRACK FREE IN REPAIR AREA.
- [SDR CALA2015110394783](https://openairdocs.org/sdr/CALA2015110394783.md): Door Sill · corroded · Oct 30, 2015 · N443UA · Airbus A320232 · Fuselage Miscellaneous Structure
  > L1 DOOR SILL IS CORRODED FWD GIRT BAR ATTACH HOLES, INBD & OTBD AFT & OTBD FWD. SPOT FACED & INSTALLED THREE EACH REPAIR WASHERS IAW SRM 53-11-14 PARA E. HFEC CRACK FREE IN REPAIR AREA.
- [SDR CALA2015110394759](https://openairdocs.org/sdr/CALA2015110394759.md): Door Sill · corroded · Oct 30, 2015 · N443UA · Airbus A320232 · Fuselage Miscellaneous Structure
  > L1 DOOR SILL IS CORRODED AFT GIRT BAR, AT TACH HOLES, INBD & OTBD AFT, & INBD FWD. SPOT FACED & INSTALLED THREE EACH REPAIR WASHERS IAW SRM 53-11-14 PARA E. HFEC CRACK FREE IN REPAIR AREA.
- [SDR CALA2015110394780](https://openairdocs.org/sdr/CALA2015110394780.md): Door Sill · corroded · Oct 29, 2015 · N443UA · Airbus A320232 · Fuselage Miscellaneous Structure
  > R1 DOOR SILL HAS CORROSION AT FWD GIRT BAR FITTING, ATTACH HOLES ALL 4. REMOVED CORROSION IN ALL 4 HOLES & MADE FILLER WASHERS & INSTALLED IAW SRM 53-11-14 FIG 108 SRI 53-11-14-1-001-00. REQUIRED 1ST INSPECTION FROM ACFT 1ST FLIGHT AT 60000C NOT TO EXCEED 37
- [SDR CALA2015110394779](https://openairdocs.org/sdr/CALA2015110394779.md): Door Sill · corroded · Oct 29, 2015 · N443UA · Airbus A320232 · Fuselage Miscellaneous Structure
  > R1 DOOR SILL HAS CORROSION AT AFT GIRT BAR FITTING, ATTACH HOLES ALL 4. REMOVED CORROSION IN ALL 4 HOLES & MADE FILLER WASHERS & INSTALLED IAW SRM 53-11-14 FIG 108 SRI 53-11-14-1-001-00. REQUIRED INSPECTION FROM ACFT 1ST FLIGHT AT 60000C NOT TO EXCEED 37064.

Next page: https://openairdocs.org/aircraft/N443UA/reports.md?page=2

## The whole list in SQL

Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS:

```sql
SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy
FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet'
WHERE n_number = 'N443UA' AND registry_match = 'registration'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/aircraft/N443UA/reports

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