Boeing 717-200

Service difficulty reports · 18,756

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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 aircraft_model_key = '717200'
  ORDER BY difficulty_date DESC"

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SDR DALA2026012700609Longeron · corrodedCORROSION UNDER BATTERY TRAYS, LONGERON. REMOVED AND REPLACED THE LONGERON IAW DWG 5911401. (0855196)Mar 13, 2025 · N925AT · Boeing 717200 · Fuselage Main, Longeron/StringerSDR DALA2025031401969Longeron · crackedCRACK ON INTERNAL AREA OF LONGERON 5L STA Y=1022 AT PASSENGER CABIN. SUMMARY OF NRC 00432: CRACK ON INTERNAL AREA OF LONGERON 5L STA Y=1022 AT PASSENGER CABIN WAS REPAIRED PER B717-200 SRM 53-00-05-2R PROCEDURE 2 REPAIR 2. (LP #0856135)Mar 13, 2025 · N938AT · Boeing 717200 · Fuselage Main, Longeron/StringerSDR DALA2025031401971Skin · gougedBANANA FAIRING ATTACH SCREWS HAVE GOUGED INTO THE L/H STABILIZER SKIN PANEL. MAINTENANCE REPLACED LH VERT STAB SKIN TIP PER B717 SRM 51-40. (LP #6408784)Mar 12, 2025 · N961AT · Boeing 717200 · Vertical Stabilizer, Plate/SkinSDR DALA2025031301960Skin · corroded-AD- CORROSION FOUND DURING INSPECTION OF RH WING AFT LOWER SKIN. CONTACT LIAISON ENGINEERING FOR REPAIR PROCEDURES PRIOR TO FURTHER FLIGHT PER INSPECTION FC5720-01103. SUMMARY SEE NRC 004-0001:5720-01103- 01B/001 00001: COMPLIED WITH PRI 624368-14AD REV 0, PRMar 12, 2025 · N603AT · Boeing 717200 · Wing, Plate/SkinSDR DALA2025031201904Frame · crackedCRACK AT FRAME 1037 CROSSING WITH L17L INTERNAL STRUCTURE FUSELAGE. SUMMARY OF NRC 00638: FRAME 1037 CROSSING WITH L17L INTERNAL STRUCTURE FUSELAGE WAS REPAIRED PER B717-200 SRM 53-20-07-2R PROCEDURE 4. (LP #0853086)Mar 11, 2025 · N998AT · Boeing 717200 · Fuselage Main, FrameSDR DALA2025031201903Stringer · corrodedCORRODED STR 30 IN MAIN E&E JUST UNDER BATTERY TRAYS. CLEANED CORROSION ON LONGERON REF: B717-200 SRM 53-00-05-2R REPAIR 3. LONGERON (HAT SECTION) REPAIR. LOCAL BLEND OUT REPAIR. UNABLE TO REPAIR, REPLACED LONGERON REF: DACDWG 5911401. (LP #0853025)Mar 11, 2025 · N925AT · Boeing 717200 · Fuselage Main, Longeron/StringerSDR DALA2025031201902Skin · dentedDENT ON EXTERNAL FUSELAGE SKIN BTW STA Y=229-237 BTW ANG LONG 17LH TO 18LH (DECAL LP 4245810). SUMMARY OF NRC 00844: EXTERNAL FUSELAGE SKIN BTW STA Y=229-237 BTW ANG LONG 17LH TO 18LH WAS REPAIRED PER B717-200 SRM 53-10-01-2R, PROCEDURE 10, REPAIR 10, FIGURE 2Mar 11, 2025 · N998AT · Boeing 717200 · Fuselage Main, Plate/SkinSDR DALA2025031201901Skin · dentedDENT ON EXTERNAL FUSELAGE SKIN BTW STA Y=229-237 BTW ANG LONG 17LH TO 18LH (DECAL LP 4245810). SUMMARY OF NRC 00844: EXTERNAL FUSELAGE SKIN BTW STA Y=229-237 BTW ANG LONG 17LH TO 18LH WAS REPAIRED PER B717-200 SRM 53-10-01-2R, PROCEDURE 10, REPAIR 10, FIGURE 2Mar 11, 2025 · N998AT · Boeing 717200 · Fuselage Main, Plate/SkinSDR DALA2025031101891Pan · crackedCRACKS ON INNER PAN AT BEAM 5 (AFT EDGE) AND BEAM 3 (FWD EDGE) AT FWD CARGO DOOR WERE FOUND. SUMMARY OF NRC 00501: INNER PAN AT BEAM 5 (AFT EDGE) AND BEAM 3 (FWD EDGE) AT FWD CARGO DOOR WERE REPAIRED PER B717-200 SRM 52-30-02-2R PROCEDURE 7 REPAIR 7, 52-30-02-Mar 11, 2025 · N998AT · Boeing 717200 · Fuselage Miscellaneous StructureSDR DALA2025031101890Beam · crackedCRACK WAS FOUND ON BEAM 5 AND INNER PAN (FWD EDGE) AT AFT CARGO DOOR. SUMMARY OF NRC 00574: BEAM 5 AND INNER PAN (FWD EDGE) AT AFT CARGO DOOR. WERE REPAIRED PER PRI 624316-14 REV 3 AND ERA 624316-14 REV ORIGINAL SECTION I PERMANENT REPAIR. ASSOCIATED ER/A 14-6Mar 11, 2025 · N955AT · Boeing 717200 · Fuselage Main, StructureSDR DALA2025031101889Frame · crackedCRACK AT FRAME STA 1037 AND L17R INTERNAL STRUCTURE OF FUSELAGE. SUMMARY OF NRC 00644: FRAME STA 1037 AND L17R INTERNAL STRUCTURE OF FUSELAGE WAS REPAIRED PER B717-200 SRM 53-20-07-2R PROCEDURE 4. (LP #0851423)Mar 11, 2025 · N998AT · Boeing 717200 · Fuselage Main, FrameSDR DALA2025100807322Skin · corrodedEXFOLIATING CORROSION FOUND ON RIGHT WING REAR SPAR LOWER CAP AT APPROXIMATELY STATION XRS=164. (6925752)Mar 10, 2025 · N603AT · Boeing 717200 · Trailing Edge FlapsSDR DALA2025031101892Skin · corroded-AD- CORROSION ON AFT EDGE LOWER SKIN OF WING BOX STA Y=747 X=15-25 RH AT RH MLG W/W AREA. SUMMARY OF NRC 00670: CORROSION LEVEL 1. CORROSION ON AFT EDGE LOWER SKIN OF WING BOX STA Y=747 X=15-25 RH AT RH MLG WAS REPAIRED PER ER/A 624679-14AD REV ORIGINAL SECTIMar 10, 2025 · N998AT · Boeing 717200 · Fuselage Main, Plate/SkinSDR DALA2025031101888Skin · corrodedCORROSION ON INNER SKIN PANEL FROM STA Y=657 TO Y=636 BTW L29L AND L29R, STA Y=588 L30 AT FWD CARGO COMPARTMENT. SUMMARY OF NRC 00183: CORROSION LEVEL 2. INNER SKIN PANEL FROM STA Y=657 TO Y=636 BTW L29L AND L29R, STA Y=588 L30 AT FWD CARGO COMPARTMENT WAS REPMar 10, 2025 · N955AT · Boeing 717200 · Fuselage Main, Plate/SkinSDR DALA2025031101887Longeron · crackedCRACKS ON LONGERONS STA 1022 AND L6L, L5L AND L4L INTERNAL STRUCTURE FUSELAGE. SUMMARY OF NRC 00652: CRACKS ON LONGERONS STA 1022 AND L6L, L5L AND L4L INTERNAL STRUCTURE FUSELAGE WERE REPAIRED PER B717-200 SRM 53-00-05-2R PROCEDURE 2 REPAIR 2 FIG 201 AND (ET) Mar 10, 2025 · N998AT · Boeing 717200 · Fuselage Main, Longeron/StringerSDR DALA2025031001823Skin · crackedCRACK EVIDENCE ON FUSELAGE SKIN LOCATED ON STA Y=1037 AND L-14L. SUMMARY OF NRC 0180: AREA WAS REPAIRED ON FUSELAGE SKIN LOCATED ON STA Y=1037 AND L-14L PER PRI 624765-14 REV 2 AND PER ER/A 624765-14 REV ORIG SECTION I. REPAIR APPROVAL IS LIMITED TO 24 MONTHS Mar 10, 2025 · N928AT · Boeing 717200 · Fuselage Main, Plate/SkinSDR DALA2025031101893Hinge Fitting · corrodedRIGHT WING INBOARD FLAP HINGE FITTING LOWER OUTBOARD STUD ON AFT SPAR HAS HEAVY RUST/PITTING. SUMMARY SEE NRC 004-0001:5720-01103-01B/006 00006: CORROSION LEVEL 2. REPLACED 4 EA MOUNTING STUDS PER B717 AMM 57-55-25-300-801. (LP #0849083)Mar 9, 2025 · N603AT · Boeing 717200 · Trailing Edge FlapsSDR DALA2025031001822Elec Connector · damagedTHE EMERGENCY LIGHT DOES NOT TURN ON IN THE AFT ACCESSORY VENTRAL WALKWAY. SUMMARY OF NRC 00219: CONNECTOR P1-260 OF BATTERY PACK B5-250 AND CONNECTOR P1-116 OF BATTERY PACK B5-116 WAS CONNECTED CORRECTLY PER B717 WDM 33-51-11 AND PERFORMED TEST PER B717 AMM 3Mar 8, 2025 · N928AT · Boeing 717200 · Light System WiringSDR DALA2025031001821Longeron · crackedCRACK AT LONGERON 6R STA 1022 INTERNAL STRUCTURE FUSELAGE. SUMMARY OF NRC 00794: CRACK AT LONGERON 6R STA 1022 INTERNAL STRUCTURE FUSELAGE WAS REPAIRED PER B717-200 SRM 53-00-05-2R PROCEDURE 2 REPAIR 2. (LP #0847702)Mar 8, 2025 · N998AT · Boeing 717200 · Fuselage Main, Longeron/StringerSDR DALA2025031001820Cusp Web · corrodedCORROSION OUT OF LIMITS, IN REF TO NRC 0642: CORROSION ON RH CUSP WEB STA Y=660-665, ORIGINAL THICKNESS OF 0.020 IN AND MINIMUM REMAINING THICKNESS IS 0.010 IN, PER B717-200 SRM 53-00-55-1A-1 PROCEDURE 1 ALLOWABLE DAMAGE 1 PAR. 4. A. FIG 101. SUMMARY OF NRC 00Mar 8, 2025 · N998AT · Boeing 717200 · Fuselage Miscellaneous StructureSDR DALA2025031101886Frame · damagedSTA 1225 CANTED FRAME: TAILCONE ALIGNMENT PIN AND CANTED FRAME DAMAGED AT APPROX 7 O'CLOCK POSITION -MARKED-. THIS COULD PREVENT THE PROPER OPERATION OF THE ESCAPE PATH AND IT IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. SUMMARY SEE NRC 001-0586:5300-2004/00Mar 7, 2025 · N925AT · Boeing 717200 · Fuselage Main, FrameSDR DALA2025031001819Frame · crackedCRACK ON FRAME STA Y=1037 LONG 17 LH. SUMMARY OF NRC 00189: FRAME STA Y=1037 LONG 17 LH WAS REPAIRED PER B717-200 SRM 53-20-07-2R PROCEDURE 4 REPAIR 4. (LP #0845545)Mar 7, 2025 · N928AT · Boeing 717200 · Fuselage Main, FrameSDR DALA2025030701776Controller · faultedSHIP 9585 -MISC/DE- THE FLIGHT CREW DECLARED AN EMERGENCY WITH ATC DUE TO A "TAIL ANTI-ICE MANIFOLD FAIL" MESSAGE ILLUMINATING ABOUT 20 MINUTES FROM LANDING. CORRECTIVE ACTION: MAINTENANCE REPLACED THE PODS CONTROLLER PER B717 AMM 36-23. RTS TEST WAS GOOD. FOUMar 6, 2025 · N985AT · Boeing 717200 · Fire Protection SystemSDR DALA2025030601772Longeron · corrodedCORROSION ON LONGERON 29R, FWD OF STA. 370. "M" AND PIC ATTACHED. SUMMARY SEE NRC 001-0513:5331-2007/001 00558: CORROSION LEVEL 2. CMOR CLEANED CORROSION ON LONGERON REF B717-200 SRM 53-00-05-2R REPAIR 3. LONGERON (HAT SECTION) REPAIR. LOCAL BLEND OUT REPAIR. Mar 6, 2025 · N925AT · Boeing 717200 · Fuselage Main, Longeron/StringerSDR DALA2025030601745Cusp Web · corrodedCORROSION OUT OF LIMITS, IN REF TO NRC 0642: CORROSION ON RH CUSP WEB STA Y=777-780, PER B717 SRM 51-10-02-0G PAR 8.F.(1). SUMMARY OF NRC 00832: CORROSION LEVEL 2. RH CUSP WEB STA Y=777-780 WAS REPAIRED PER B717-200 SRM 53-00-55-2R, PROCEDURE 4, REPAIR 4. (LP Mar 6, 2025 · N998AT · Boeing 717200 · Fuselage Miscellaneous StructureSDR DALA2025030601744Battery Pack · no testTHE EMERGENCY LIGHT SERVICE CHECK FOUND THE LIGHTED SIGNS ABOVE THE AFT OVERWING EXITS ON LEFT & RIGHT SIDES TO BE INOPERATIVE. MAINTENANCE TROUBLESHOT IN REF WITH B717 WDM 33-51-11 PG 4 SHEET 3 OF 3, DELTA AVIONICS JOB AIDS TO EMERGENCY LIGHT BATTERY PACK B5-Mar 5, 2025 · N993AT · Boeing 717200 · Emergency LightingSDR DALA2025030501714Cusp Web · corrodedCORROSION OUT OF LIMITS, IN REF TO NRC 0642. CORROSION ON RH CUSP WEB STA Y=262-270, ORIGINAL THICKNESS OF 0.020 IN AND MINIMUM REMAINING THICKNESS IS 0.010 IN, PER B717-200 SRM 53-00-55-1A-1 PROCEDURE 1 ALLOWABLE DAMAGE 1 PAR 4. A. FIG 101. SUMMARY OF NRC 008Mar 5, 2025 · N998AT · Boeing 717200 · Fuselage Miscellaneous StructureSDR DALA2025030501713Cusp Web · corrodedCORROSION OUT OF LIMITS, IN REF TO NRC 0642: CORROSION ON RH CUSP WEB STA Y=389, ORIGINAL THICKNESS OF 0.020 IN AND MINIMUM REMAINING THICKNESS IS 0.010 IN, PER B717-200 SRM 53-00-55-1A-1 PROCEDURE 1 ALLOWABLE DAMAGE 1 PAR. 4. A. FIG. 101. SUMMARY OF NRC 00830Mar 5, 2025 · N998AT · Boeing 717200 · Fuselage Miscellaneous StructureSDR DALA2025030501712Cusp Web · crackedCRACK ON CUSP WEB BTW STA Y=717 -X=44 RH SIDE AT MID PASSENGER CABIN. SUMMARY OF NRC 00650: CUSP WEB BTW STA Y=717 -X=44 RH SIDE AT MID PASSENGER CABIN WAS REPAIRED PER B717 SRM 53-00-55-2R REPAIR 4 FIGURE 221. (LP #0841317)Mar 5, 2025 · N998AT · Boeing 717200 · Fuselage Miscellaneous StructureSDR DALA2025030501715Valve · stiffSHIP 9519 -ATB/FUME/DE- DURING CLIMB OUT AT ABOUT 10K FEET, THE FLIGHT CREW DECLARED AN EMERGENCY WITH ATC AND RETURNED TO MEM DUE TO UNKNOWN ODOR THROUGHOUT THE CABIN. CORRECTIVE ACTION: MAINTENANCE DISCOVERED THAT THE BUFFER AIR VALVE ON THE #2 ENGINE WAS VEMar 4, 2025 · N960AT · Boeing 717200 · Engine Cooling SystemSDR DALA2025030501711Hinge Fitting · damagedAN ELONGATED HOLE WAS FOUND AT THE RH WING FLAP HINGE FITTING #3 PIVOT POINT. SUMMARY OF NRC 00535: RH WING FLAP HINGE FITTING #3 WAS REPAIR PER PRI 624272-14 REV 1 AND ER/A 624272-14 REV ORIGINAL. ASSOCIATED ER/A 14-624272 ADDED FOR AC 9514. (LP #0840814)Mar 4, 2025 · N955AT · Boeing 717200 · Trailing Edge FlapsSDR DALA2025030501710Hinge Fitting · corrodedAN ELONGATED HOLE INBD ON INBD FACE ON HINGE FLAP #3 AT LH WING, ALONG WITH CORROSION ON BOTH HOLES INBD/OUTBD HINGE. SUMMARY OF NRC 00543: HINGE FLAP #3 AT LH WING WAS REPAIRED PER PRI 624271-14 REV 1 AND ER/A 624271-14 REV ORIGINAL. ASSOCIATED ER/A 14-624271Mar 4, 2025 · N955AT · Boeing 717200 · Trailing Edge FlapsSDR DALA2025030501709Frame · corrodedCORROSION ON FRAME BTW STA Y=1022 L28L TO L28R AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00177: CORROSION LEVEL 2. FRAME BTW STA Y=1022 L28L TO L28R AT AFT CARGO COMPARTMENT WAS REPAIRED PER B717-200 SRM 53-20-07-2R PROCEDURE 3, REPAIR 3. PERFORM A DETAIL VISUAMar 4, 2025 · N955AT · Boeing 717200 · Fuselage Main, FrameSDR DALA2025030401650Shear Tie · corrodedFRAME CLIP STA 1022 BTW LONG 28RH TO 28LH, AFT CARGO COMPARTMENT, WAS FOUND CORRODED OUT OF LIMITS WITH MINIMUM REMAINING THICKNESS 0.048 IN PER B717-200 SRM 53-00-01-1A ALLOWABLE DAMAGE PAR 4.C.(2) FIG 103. SUMMARY OF NRC 00633: CORROSION LEVEL 2. FRAME CLIP Mar 3, 2025 · N955AT · Boeing 717200 · Fuselage Internal Mounting StructureSDR DALA2025030401649Skin · wornWEAR ON EXTERNAL SKIN, NEAR CUT OUT OF HOOK, AT PASSENGER DOOR L1. SUMMARY OF NRC 00036: DAMAGE ON EXTERNAL SKIN, NEAR CUT OUT OF HOOK, AT PASSENGER DOOR L1 WAS REPAIRED PER ER/A 624489-14 REV ORIGINAL SECTION I: PERMANENT REPAIR AND PRI 624489-14 REV 1. ASSOCMar 3, 2025 · N928AT · Boeing 717200 · Passenger/Crew DoorsSDR DALA2025030401652Pcdu · faultedSHIP 9516 -MISC/DE- THE FLIGHT CREW DECLARED AN EMERGENCY WITH ATC FOLLOWING A "RIGHT DC BUS FAILURE" INDICATION. THE RESULT OF THAT WAS A NO FLAP, NO SLAT LANDING. CORRECTIVE ACTION: MAINTENANCE REPLACED THE RIGHT PCDU AND THE LEFT POWER CONTACTOR RELAY. PERFMar 1, 2025 · N957AT · Boeing 717200 · Electrical Power SystemSDR DALA2025030301648Pan · corrodedCORROSION ON AFT CARGO DOOR JAMB PAN BTW LONG 24RH TO LONG 27RH (NEW SECTION AND PRODUCTION SECTION OF PAN). SUMMARY OF NRC 00118: CORROSION LEVEL 2. CARGO DOOR JAMB PAN STA 954 LONG 28 LH AND STA 986 BTW LONG 28 RH WAS REPAIRED PER B717-200 SRM 53-20-15-2R REMar 1, 2025 · N928AT · Boeing 717200 · Fuselage Miscellaneous StructureSDR DALA2025030401651Control Module · faultedSHIP 9543 -FCNT/DE- THE FLIGHT CREW DECLARED AN EMERGENCY WITH ATC DUE TO THE TRAILING EDGE FLAPS BEIN INOPERATIVE ON APPROACH. A NORMAL LANDING WAS ACCOMPLISHED AND NO ISSUES WITH BREAKING DURING ROLLOUT. CORRECTIVE ACTION: MAINTENANCE REPLACED THE FLAP/SLAT Feb 28, 2025 · N978AT · Boeing 717200 · Trailing Edge Flap Control SystemSDR DALA2025030301647Angle · corrodedCORROSION ON ANGLE CUSP BTW STA Y=197 TO STA Y=210 OF FWD GALLAY SERVICE DOOR AT CABIN PASSENGER. SUMMARY OF NRC 00283: CORROSION LEVEL 2. ANGLE CUSP BTW STA Y=197 TO STA Y=210 OF FWD GALLEY SERVICE DOOR AT CABIN PASSENGER WAS REPAIRED PER PRI 624120-14 REV 4 Feb 28, 2025 · N955AT · Boeing 717200 · Fuselage Miscellaneous StructureSDR DALA2025030101575Door · damagedTHE RIGHT SIDE OVERWING EXIT DOOR WAS FOUND DAMAGED. THIS COULD PREVENT THE PROPER OPERATION OF THE ESCAPE PATH AND IT IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. MAINTENANCE REPLACED THE RIGHT FWD OVERWING EMERGENCY EXIT DOOR PER B717 AMM 52-21. INSPECTIONFeb 27, 2025 · N942AT · Boeing 717200 · Emergency ExitsSDR DALA2025030101574Transfer Valve · failedSHIP 9506-ATB- THE FLIGHT CREW PERFORMED AN AIR TURN BACK DUE TO A RIGHT HYDRAULIC SYSTEM FAILURE. AN EMERGENCY WAS DECLARED WITH ATC. THE LANDING WAS UNEVENTFUL EXCEPT FOR THE MAIN LANDING GEAR DOORS CONTACTING THE RUNWAY UPON ROLLOUT. CORRECTIVE ACTION: MAINFeb 27, 2025 · N946AT · Boeing 717200 · Landing Gear Retraction/Extension SystemSDR DALA2025030101573Engine · failedSHIP 9502 -ATB/IFSD/DE- THE FLIGHT CREW DECLARED AN EMERGENCY WITH ATC AND RETURNED TO ATL DUE TO SMOKE IN THE CABIN. CREW REPORTED RIGHT ENGINE OIL QTY WENT TO ZERO WITH SMOKE IN CABIN. CREW SHUTDOWN RIGHT ENGINE PER QRH. AFTER LANDING PAX EVACUATED AIRCRAFT Feb 27, 2025 · N942AT · Boeing 717200 · Engine (Turbine/Turboprop)SDR DALA2025030101571Cusp Web · crackedCRACK ON CUSP WEB (BELOW AREA) IN X=-54 AND STA 257, STA 277, STA 656, STA 674, STA 818, AND STA 937 AT CPAX. SUMMARY OF NRC 00336: CUSP WEB AT STA 277, STA 257, STA 818, STA 937 WERE REPAIRED PER B717-200 SRM 53-00-55-2R REPAIR 4, CUSP WEB BTW STA 655 TO STA Feb 27, 2025 · N955AT · Boeing 717200 · Fuselage Miscellaneous StructureSDR DALA2025022601481Skin · damagedLH ELEVATOR WAS FOUND DENTED AND SCRATCHED ON UPPER SKIN. SUMMARY OF NRC 00575: LH ELEVATOR WAS REPAIRED PER B717-200 SRM 51-70-13-2R REPAIR 2. PERFORM DECAL CONDITION INSPECTION EVERY C CHECK PER TOPP MANUAL 30-10-70 PAR I PAGE 14. LOG PAGE DEFERRED TO DECAL Feb 26, 2025 · N955AT · Boeing 717200 · Elevator, Plate/SkinSDR DALA2025022601480Cusp Web · crackedCRACK ON CUSP WEBS (LOWER AND UPPER AREA) IN X=54 AND STA 225, STA 237, STA 258, STA 655, AND STA 663. ALSO, X=58 AND STA 668, STA 807 AT CPAX WAS CRACKED. SUMMARY OF NRC 00442: CUSP WEBS IN X=54 AND STA 225, STA 237, STA 258, STA 655, STA 663, ALSO X=58 AND SFeb 25, 2025 · N955AT · Boeing 717200 · Fuselage Miscellaneous StructureSDR DALA2025022601479Angle · corrodedCORROSION ON ANGLE CUSP BTW STA Y=190 TO STA Y=200 OF FWD ENTRY DOOR AT PASSENGER CABIN. SUMMARY OF NRC 00270: CORROSION LEVEL 2. ANGLE CUSP BTW STA Y=190 TO STA Y=200 OF FWD ENTRY DOOR AT PASSENGER CABIN WAS REPAIRED PER B717-200 SRM 53-00-55-2R PROCEDURE 3 RFeb 25, 2025 · N955AT · Boeing 717200 · Fuselage Miscellaneous StructureSDR DALA2025030101570Hinge Fitting · gouged-AD- WHILE ACCOMPLISHING NDT INSPECTION PER AMDS 5720-01103-01B FOUND GOUGE IN THE RH AFT SPAR ROUGHLY 8" OUTBOARD OF FLAP HINGE. AREA MARKED. COMPLIED WITH ALL STEPS IF ER/A 624537-14AD PRI REV 1, 728756 BB. ALL WORK ACCOMPLISHED PER FINAL ER/A 624537-14AD. (Feb 23, 2025 · N919AT · Boeing 717200 · Trailing Edge FlapsSDR DALA2025022501470Fuel Cell · leaking-AD- FUEL LEAK FOUND DURING INSPECTION OF THE RH WING AFT LOWER SKIN BTW STA XRS 154 TO STA XRS 164, AFT EDGE BTW LOWER PRODUCTION DOUBLER AND LOWER WING SKIN. CONTACT LIAISON ENGINEERING FOR REPAIR PROCEDURES PRIOR TO THE FURTHER FLIGHT. SUMMARY OF NRC 00061:Feb 22, 2025 · N979AT · Boeing 717200 · Fuel StorageSDR DALA2025022501469Door Frame · corrodedCORROSION ON DOOR JAMB AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00062: CORROSION LEVEL 2. DOOR JAMB AT AFT CARGO COMPARTMENT WAS REPLACED AND INSTALLED PER B717-200 SRM 53-20-15 -2R-7. (LP #0822834)Feb 22, 2025 · N955AT · Boeing 717200 · Fuselage Main, StructureSDR DALA2025022501468Floor Support · corrodedCORROSION ON FLOOR SUPPORT BTW STA Y=194 TO STA Y=200 X=56 OF FWD ENTRY DOOR AT PASSENGER CABIN. SUMMARY OF NRC 00276: CORROSION LEVEL 2. FLOOR SUPPORT BTW STA Y=194 TO STA Y=200 X=56 OF FWD ENTRY DOOR AT PASSENGER CABIN WAS MANUFACTURATED PER DWG 9910078-173 Feb 21, 2025 · N955AT · Boeing 717200 · Fuselage Miscellaneous Structure
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