JASC 5530

Service difficulty reports · 2,534

Reports filed under 5530 · Vertical Stabilizer, newest first.

Query with SQL
duckdb -csv -c "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 jasc_code = '5530'
  ORDER BY difficulty_date DESC"

Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.

SDR SWAA114786Stabilizer · crackedDURING SCHEDULED 20Y CHECK, FOUND VERTICAL STABILIZER CRACKED AT FWL 107. REPAIRED STABILIZER EPR SRM.Jul 4, 2011 · N521SW · Boeing 7375H4SDR DALA1140429019Skin · crackedDURING PSV VISIT IN MSP JUN2011, A CRACK WAS FOUND ON THE FUSELAGE SKIN AT APPROX STA 1437 JUST ABOVE L3R. THE CRACK EMANATES FROM AN EXISTING LOWER MOST FASTENER HOLE ALONG THE STA 1437 SHEAR TIE. SUBJECT FUSELAGE SKIN MADE FROM 0.063 INCH THICK 2024-T3 CLAJun 14, 2011 · N919DE · Doug MD88SDR UALA2011050902265Panel · damagedELONGATED HOLE ON VERTICAL STAB PANEL 324 GZ. FABRICATED AND INSTALLED NEW DOOR PANEL P/N 172N1500-31 ON PEMCO NR 2529N00495 PER EA PD57-55-001.May 7, 2011 · N563UA · Boeing 757222SDR CA110407005Bolt · sheared(CAN) VERTICAL FIN AFT ATTACH BOLT, 1 OF 4, WAS FOUND SHEARED DURING 100 HOUR INSPECTION. VERTICAL FIN ATTACH BRACKET INSPECTION COMPLETED & VERTICAL FIN ATTACH BOLTS REPLACED WITH NEW.Apr 7, 2011 · Cessna 152SDR ASAA1149723Bushing · galledLEFT FORWARD VERTICAL STABILIZER BOLT FORWARD ATTACH LUG BUSHING IS GALLED. REPAIRED BUSHING PER ASA EA 400 55EA 05422.Apr 6, 2011 · N778AS · Boeing 7374Q8SDR DALA1124326304Seal · wornFUSELAGE SKIN AND RT VERT STAB SEAL INTERFACE HAVE WEAR. STA 2521-2628. MAX DEPTH: 0.014" BLEND OUT, MEASURE AND RECORD SIZE, CHECK LIMITS PER SRM 53-00-0 1 ALLOWABLE DAMAGE1. 515462 LIU CHUN FU 149342. PER ER/A 489971-14AD BLEND OUT THE WORN AND DAMAGE IS WMar 30, 2011 · N664US · Boeing 747451SDR DALA1124316304Seal · wornFUSELAGE SKIN AND VERT STAB RT SEAL INTERFACE HAVE WEAR STA 2280-2416. MAX DEPTH: 0.005" BLEND OUT, MEASURE AND RECORD SIZE, CHECK LIMITS PER SRM 53-00-0 1 ALLOWABLE DAMAGE 1. 515462 LIU CHUN FU 149342 PER ER/A 489971-14AD BLEND OUT THE WORN. AND DAMAGE IS WITMar 30, 2011 · N664US · Boeing 747451SDR DHLA201100052Hinge Fitting · wornVERTICAL STABILIZER REAR SPAR NR 1 HINGE FITTING SHOWS WEAR. STA ZR 103.000. PERFORMED MAJOR REPAIR IAW SRM 55-1-0 PG 1. REMOVED FITTING IAW M 20-16-0 PG 201-207. CLEANED, TREATED AND PRIMED AREA IAW SRM 51-1-8B. NDT INSPECTED NEW FITTING IAW NDT SPM PART 06-Mar 29, 2011 · N805DH · Doug DC873FSDR FDEA201103231284Beam · crackedVERTICAL STABILIZER LT FIXED T/E BEAM IS CRACKED AT RUD STA 97.354 SDR ENTERED IN ERROR. CONSIDERED MINOR REPAIRMar 23, 2011 · N926FD · Boeing 7572S7SDR MASA2011032202208Elevator · damagedDAMAGE LT ELEV L O/B CORNER. C/W RO FOR 300 FH.Mar 19, 2011 · N513MJ · Cndair CL6002C10SDR DALA1121740960Bushing · corrodedBUSHINGS RUSTED ON LT STAB INBD ATTACH LUG AT TOP OF VERT STAB NR 77. REPLACED PER EA 09-073278-12 AD REV G.Mar 17, 2011 · N960DL · Doug MD88SDR FDEA201103171052Support Fitting · corrodedVERTICAL STABILIZER INTERIOR, RUDDER HINGE NR 4 SUPPORT FITTING AT REAR SPAR, RIB-13 HAS CORROSION ON BOTTOM EDGE , ABOUT 10 SQUARE INCHES. R & R NR 4 RUDDER HINGE SUPPORT FITTING AT REAR SPAR RIB 13 IAW A310 SRM 51-72-10, PGS 1-3.Mar 17, 2011 · N443FE · Airbus A310203SDR ASOA201100419Drag Angle · crackedLEFT VERTICAL STAB DRAG ANGLE CRACKED AT AFT END. COMPLIED WITH EC/TC REO 670-55-31-018 IAW REO 670-55-31-018.Mar 4, 2011 · N754EV · Cndair CL6002C10SDR ASOA201100402Drag Angle · crackedLEFT VERTICAL STAB DRAG ANGLE CRACKED AT AFT END. PERFORMED EDDY CURRENT INSP ON LT SIDE FWD VERTICAL STAB DRAG ANGLE IAW NDT INSP PROCEDURES ET-2. VERIFIED DRAG ANGLE IS CRACKED AT AFT ENG. CRACK IS .65IN IN LENGTH. CUT AND REMOVED DAMAGE AT LT VERTICALFeb 28, 2011 · N754EV · Cndair CL6002C10SDR UIEA2011020700043Structure · damagedVERTICAL STABILIZER L/E CAP AT L/E STA 133.581 RT SIDE DAMAGED OUT OF LIMIT IAW SRM 55-30-01 DEPTH FOUND TO BE 0.018". TRIMMING OUT OF DAMAGED LEADING EDGE ASSY SKIN CARRIED OUT AS PER SRM 55-3003 FIGURE 2 REV 118. PREPARATION OF DOUBLERS AND FILLER CARRIED Feb 7, 2011 · N355MC · Boeing 747341SDR DALA1503969235Attach Angle · crackedCRACK REPAIR ON LEFT DORSAL FIN ATTACH ANGLE IAW SRM 53Jan 27, 2011 · N935DN · Doug MD9030SDR DALA1106530919Structure · damagedLOWER FIXED L/E NUMEROUS HOLES WORN. REPAIRED IAW SRM 55-03D, FIG 30.Jan 27, 2011 · N919DL · Doug MD88SDR IPXA1564502Skate Angle · brokenINSPECTION TYPE:C4, VERTICAL STAB TO FUSELAGE - RT SIDE - AFT SKATE ANGLE - AFT END OF SKATE ANGLE BROKEN OFF. REPLACED ANGLE IAW SRM 51-40-05-0G, SRM 51-40-08-0G, AND SRM 51-40-02-0G AND SRM 51-10-02-0G, STEP 9.Jan 24, 2011 · N417UP · Boeing 75724APFSDR DALA1105459864Fitting · crackedAFT ACCESORY COMPARTMENT STA 1258 VERTICAL STAB. RT SIDE FITTING CRACKED. RECEIVED NEW FITTING IAW TRAVELER 2311NO21922, OK TO TREAT HOLES. TREATED AND PRIMED HOLES IAW SRM 51-10-3. INSTALLED NEW FITTING IAW SRM 51-30-1 AND SRM 51-30-5. REQUIRED INSPECTIJan 21, 2011 · N773NC · Doug DC951SDR FDEA201101060028Fitting · corrodedVERTICAL STABILIZER RT FWD MOUNT FITTING OUTER FACE HAS CORROSION JUST AT SKIN EDGE AREA ABOUT 0.5 SQ INCHES. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530-145557.Jan 6, 2011 · N443FE · Airbus A310203SDR FDEA201101060027Structure · corrodedVERTICAL STABILIZER RT CHORD BETWEEN RIB 18 AND RIB 25 HAS SURFACE CORROSION AROUND NUTPLATES, 3 PLACES, APPROX 3 SQ INCHES. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530-145551.Jan 6, 2011 · N443FE · Airbus A310203SDR FDEA201101060026Structure · corrodedVERTICAL STABILIZER REAR SPAR LT CHORD, RIB 10 TO RIB 16 HAS CORROSION AT 11 EA NUT PLATES LOCATIONS. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530-145551.Jan 6, 2011 · N443FE · Airbus A310203SDR FDEA201101060022Fitting · corrodedUPON REMOVAL OF LOWER WEB AT VERTICAL STAB FOUND CORROSION ON AFT FITTING AT LT ATTACH POINT. REMOVED CORROSION ON AFT TRAVERSE FITTING ON VERT STAB AT REAR SPAR IAW SRM 51-74-10, PG 5. BEFORE THICKNESS 0.557, AFTER 0.448. LOSS OF 0.069 IS OUT OF LIMITS IAWJan 6, 2011 · N443FE · Airbus A310203SDR FDEA201101060021Plate · corrodedVERTICAL STABILIZER RIB 1, STRINGER 2LT TO 5LT, REAR LOWER PLATE LOWER SURFACE CORRODED APPROX 2 IN WIDE X 4 IN LENGTH JUST ABOVE LT AFT STABILZER HINGE. COMPLIED WITH EA 6-5530-145557.Jan 6, 2011 · N443FE · Airbus A310203SDR FDEA201101050016Plate · corrodedVERTICAL STABILIZER, RIB 1, STRINGER 2RT - 5RT REAR LOWER PLATE. LOWER SURFACE CORRODED APPROX 1IN WIDE X 2IN LENGTH JUST ABOVE RT AFT STABILIZER HINGE. R & R VERTICAL STAB RIB 1AFT LOWER PLATE IAW SRM 51-72-10, PGS 1-3.Jan 5, 2011 · N443FE · Airbus A310203SDR IPXA1564172Angle · chafedINSPECTION TYPE:C1, VERT STAB SLAT ANGLE. LT SIDE, FWD AND AFT END OF SKATE ANGLE CHAFED AT BOTTOM OF PANEL 324AL. R & R SKATE ANGLE IAW SRM 51-40-02-0G AND AMM 51-21-10-7.Jan 4, 2011 · N440UP · Boeing 75724APFSDR DALA1102469864Fitting · crackedAFT ACCESSORY COMPARTMENT, STA 1258, VERTICAL STABILIZER, CTR FITTING IS CRACKED AT LOWER END CORNER. REMOVED CTR FITTING IN AFT ACC COMP STA 1258 IAW SRM 51-30-5. RECEIVED NEW MATERIAL IAW DWG 9911840-115. HEAT TREATED NEW FITTING TRAVELER NR2311N02296 TREATDec 28, 2010 · N773NC · Doug DC951SDR DALA1053580917Hinge Fitting · corrodedVERTICAL TO HORIZ STAB HINGE PLATES CORROSION ERA 488232-14, REV ORIG REF NRS 14-17 AND FINAL ERA SIGNED ON NR 5.Dec 14, 2010 · N917DL · Doug MD88SDR N93A10282010Angle · crackedDURING INSP OF ACFT FOR CONDITION SURVEY IT WAS NOTED THAT THE 793 BULKHEAD CAP ANGLE WAS CRACKED.Oct 28, 2010 · N499QS · Gulstm GIVSDR IPXA0M63579Panel · damagedINSPECTION TYPE:4C, VERTICAL L/E PANEL NR571KL HAS 1EA FASTENER HOLE ENLONGATED. TRIMMED OUT DAMAGE AT VERTICAL L/E PANEL NR371KL AT ENLONGATED HOLE BETWEEN ZFS553 AND ZFS560. FABRICATED STRAIGHT SHANK FREEZE PLUG AND INSTALLED REPAIR BUSHING REF EO MD11-55Oct 21, 2010 · N284UP · Doug MD11FSDR C2XA10SH314Housing · damagedSHV - DURING C-CHECK VERTICAL STABILIZER RT SPERICAL BEARING HOUSING FOUND TO BE OUT OF LIMITS. MAINTENANCE PERFORMED REPAIR ON RT SPERICAL BEARING HOUSING IAW ETD 2010-145/084787. THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.Sep 20, 2010 · N14945 · Emb EMB145EPSDR UALA2010091403415Panel · delaminatedVERTICAL STAB LT SIDE FWD TORQUE BOX SCI N PANEL 322CL (177W3102) HAS DELAMINATION. INSPECTED AREA FOR MOISTURE, COVERED DELAMINATED SKIN WITH DOUBLE LAYER OF SPEED TAPE REF UA-E VA-80083. TO BE REPAIRED 150 FLIGHT HOURS AND TAPE TO BE CHECKED PRIOR TO EACH DSep 11, 2010 · N791UA · Boeing 777222SDR IPXA10562803Support Angle · damagedINSPECTION TYPE:C3, VERT STAB L/E AUX SPAR LT SUPPORT ANGLE HAS MISDRILLED HOLES FROM NUTPLATE AT AFT END WHERE PANEL 3212L, ATTACHES FABRICATE NE L/E SPLICE STRAP IAW EO B757-5310-39844-A.Sep 8, 2010 · N424UP · Boeing 75724APFSDR IPXA10562785Strap · damagedINSPECTION TYPE:C3, VERT STAB 321CL HAS MISDRILLED NUTPLATE AT AFT END 3RD NUTPLATE FROM AFT END LT SIDE. R & R SPLICE STRAP IAW SRM 51-40-02-0G, DWG 174N1201 SHT 1, REV "C"Sep 8, 2010 · N424UP · Boeing 75724APFSDR FDEA201009043274Web · crackedLOWER VERTICAL STABILIZER AT PANEL NR 363QL INTERIOR AREA, WEB FOUND CRACKED. REPAIR CARRIED OUT AS PER SRM 55-30-02 FIGURE 201 REPAIR 2, REVISION 44 AND EA 1-5530-143725, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100, REVISION 111.Sep 4, 2010 · N595FE · Doug MD11FSDR IPXA10562636Angle · chafedINSPECTION TYPE:C3, VERTICAL STABLIZER ANGLE IS CHAFED AT FWD MATING SURFACE OF PANEL 322AL. R & R IAW SRM 51-40-02-0GSep 3, 2010 · N425UP · Boeing 75724APFSDR ASOA201001097Strake · crackedAFT DORSAL STAKE FOUND WITH 1" CRACK DEFECT MARKED WITH RED TAPE. REPAIRED CRACK AT AFT DORSAL STRAKE IAW SRM 51-75-16-001-A01. REPAIR OF AFT DORSAL FULLY CURED IAW SRM 51-75-16-001-A01. PRIMED AND PAINTED IAW SRM 51-25-01-001-A01.Aug 12, 2010 · N738EV · Cndair CL6002C10SDR FDEA201007212634Support Angle · corrodedDORSAL FIN RIGHT SIDE; AFT SUPPORT ANGLE IS CORRODED. REMOVED CORROSION WITH MORE THAT 50% MATERIAL LOSS, OUT OF LIMITS IAW A310-200 SRM 51-74-10. REMOVED AFT SUPPORT ANGLE AND DRILLED UP NEW SUPPORT ANGLE; DEBURRED, INSTALLLED, SEALED AND PAINTED IAW A31Jul 21, 2010 · N417FE · Airbus A310222SDR QXEA2010072100427Drag Angle · crackedRT V-STAB TO FUSELAGE ATTACHMENT DRAG ANGLE IS POSSIBLY CRACKED. APPROX STA 1240 HFEC INSPECTED SUSPECTED CRACK IAW NDTM PART 6, 53-00-000-250-A01. CRACK INDICATION NOTED, APPROX 1.2" LONG. REMOVED FASTENERS AND CUT OUT DAMAGE ON ATTACHMENT DRAG ANGLE IAW REJul 20, 2010 · N612QX · Cndair CL6002C10SDR IPXA10561206Beam · chafedINSPECTION TYPE:C2, VERT STAB LWR T/E BEAM CHAFED. R & R LWR T/E BEAM.Jul 10, 2010 · N412UP · Boeing 75724APFSDR A6WA201040604Support Angle · gougedLOWER VISOR SUPPORT ANGLE ON LT SIDE OF VERTICAL STAB GOUGED BLENDED OUT GOUGED AREAS ON SUPPORT ANGLE IN AREAS B, C.Jun 25, 2010 · N406AW · Cndair CL6002B19SDR USAA2010070291335Fitting · wornSAL - C6 - MAJOR REPAIR - EXCESSIVE PLAY ON NR 3 RUDDER HINGE ARM FITTING. REPLACED NR 3 RUDDER HINGE ARM FITTING IAW A319 SRM 51-72-11 & AMM 55-36-41.Jun 19, 2010 · N831AW · Airbus A319132SDR USAA2010070291334Fitting · wornSAL - C6 - MAJOR REPAIR - EXCESSIVE PLAY ON NR 4 RUDDER HINGE ARM FITTING. REPLACED NR 4 RUDDER HINGE ARM FITTING IAW A319 SRM 51-72-11 & AMM 55-36-41.Jun 19, 2010 · N831AW · Airbus A319132SDR FDEA201006142005Bearing · corrodedVERTICAL STABILIZER TO RUDDER ATTACH FITTING NR 2 HINGE; BEARING IS CORRODED AND BINDING. RUDDER HINGE ARM NR 2 REMOVED PER AMM 55-36-44-4. RUDDER HINGE ARM MODIFIED PER WORK STEPS OF SB A300-55-6022 REV 03, PARA 3-F(2),(B) 2. PER E A 6-5540-136664, RUDDJun 14, 2010 · N730FD · Airbus A300B4622RSDR DALA1013310922Structure · damagedVERT STAB REMOVABLE L/E UPPER EDGE HOLES DAMAGED, REPAIRED IAW ERA 483240-14.Jun 9, 2010 · N922DL · Doug MD88SDR 5APR577Y38Skin · crackedDURING AN ANNUAL INSPECTION, DISCOVERED A 46MM LONG CRACK IN THE SKIN ON THE RT SIDE OF THE VERTICAL STABILIZER. THE CRACK IS ROUGHLY 55MM FROM THE TOP OF THE SKIN AND 250MM FWD OF THE REAR END OF THE SKIN. SUBMITTED A DEFECT REPORT TO THE MFG AND RECEIVED AN May 25, 2010 · N729AF · Pilats PC1247SDR ASOA201000818Drag Angle · crackedPERFORMED EDDY CURRENT INSP OF RT VERT STAB TO FUSELAGE ATTACH DRAG ANGLE IAW MAC NDT INSP PROCEDURE ET-2. DRAG ANGLE IS CONFRIMED CRACKED AND END OF CRACK IS MARKED. REMOVED RT AFT DRAG ANGLE IAW SRM 51-42-27-001-001-A01, 51-42-21-001-A01 & 51-42-13-001-001-May 24, 2010 · N748EV · Cndair CL6002C10SDR ASOA201000817Drag Angle · crackedPERFORMED EDDY CURRENT INSP OF LT VERTICAL STAB TO FUSELAGE ATTACH DRAG ANGLE IAW MAC NDT INSP PROCEDURE ET-2, DRAG ANGLE IS CONFIRMED CRACK AND END OF CRACK IS MARKED. REMOVED LT SIDE AFT DRAG ANGLE & LOCATED HOLES IN NEW DRAG ANGLE IAW SRM 51-42-27-001-001-May 24, 2010 · N748EV · Cndair CL6002C10SDR DLM88101255Splice · wornREMOVABLE L/E OF VERTICAL SCREW ATTACH HOLES AND COUNTERSINKS WORN UPPER SPLICE REPAIRED ON ERA 482407-14, NR 128.May 19, 2010 · N936DL · Doug MD88SDR DLM88101230Structure · damagedVERTICAL STAB HOLES WORN ON LT SIDE CHORD COMMON TO L/E PANEL STRUCTURE WAS REPAIRED IAW ERA 481678-14.May 14, 2010 · N929DL · Doug MD88
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