GE CF6-80C2A5F

Service difficulty reports · 263

Newest first. General aviation reporting is voluntary.

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 engine_model_key = 'CF680C2A5F'
  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 FDEA201010124010Carriage · misalignedRT WING T/E FLAP NR 6 FRONT CARRIAGE UPPER BRIDGE WAS FOUND SHIM MIGRATION. EA 6-2750-141636 REPAIR ACCOMPLISHED. THE REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.Oct 12, 2010 · N686FE · Airbus A300F4605R · Trailing Edge FlapsSDR FDEA201010124012Carriage · misalignedRT WING T/E FLAP NR3 FRONT CARRIAGE UPPER BRIDGE WAS FOUND SHIM MIGRATION. EA 6-2750-141636 REPAIR ACCOMPLISHED. THE REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.Oct 12, 2010 · N686FE · Airbus A300F4605R · Trailing Edge FlapsSDR FDEA201010124013Carriage · misalignedRT WING T/E FLAP NR4 FRONT CARRIAGE UPPER BRIDGE WAS FOUND SHIM MIGRATION. EA 6-2750-141636 REPAIR ACCOMPLISHED THE REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.Oct 12, 2010 · N686FE · Airbus A300F4605R · Trailing Edge FlapsSDR FDEA201010124014Carriage · misalignedRT WING T/E FLAP NR 5 FRONT CARRIAGE UPPER BRIDGE WAS FOUND SHIM MIGRATION. EA 6-2750-141636 REPAIR ACCOMPLISHED. GMM 6-2-100 REPAIR CLASSIFIED AS MINOR.Oct 12, 2010 · N686FE · Airbus A300F4605R · Trailing Edge FlapsSDR FDEA201010063951Skin · crackedLT WING T/E UPPER SKIN SUPPORT WEB CRACKED AT NR 4 SPOILER OTBD HINGE NEARBY. FABRICATED LT SUPPORT SKIN I.AW AB6F DWG NR A57240194 (PN A57240194200). INSTALLED THE SUPPORT SKIN WITH FASTENER IAW AB6F SRM 51-40-21. THE REPAIR CLASSIFIED AS MINOR IAW GMM Oct 6, 2010 · N686FE · Airbus A300F4605R · Wing, Plate/SkinSDR FDEA201010063952Door · crackedLT MLG DOOR OTBD EDGE GOT IMPACT DAMAGED AT CTR AREA. DAMAGE EDGE AREA REPAIRED IAW EA NR 6-5280-141635 . THE REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.Oct 6, 2010 · N686FE · Airbus A300F4605R · Landing Gear DoorsSDR FDEA201010063953Rib · crackedFASTENER HOLES WERE FOUND CRACKED AT RIB25A OF LEFT WING INBD FLAP IAW EO E6-5750-7-5003, PT1. THE REPAIR CLASSIFIED AS MINOR GMM 6-2-100.Oct 6, 2010 · N686FE · Airbus A300F4605R · Trailing Edge FlapsSDR FDEA201010053950Skin · crackedLT WING T/E UPPER SKIN SUPPORT WEB GOT CRACK AT NR 3 SPOILER INBD HINGE NEARBY. FABRICATED LT SUPPORT SKIN IAW AB6F DWG NR A57240194 (PN A57240194201). INSTALLED THE SUPPORT SKIN WITH FASTENER IAW AB6F SRM 51-41-21. THE REPAIR CLASSIFIED AS MINOR IAW GMM 6Oct 5, 2010 · N686FE · Airbus A300F4605R · Wing, Plate/SkinSDR FDEA201009293785Floor Support · crackedMAIN CABIN FLOOR SUPPORT IS CRACKED AT FRAME 48-FRAME 48. REMOVED CRACKED FLOOR SUPPORT AT FRAME 48 AND INSTALLED NEW LINK SUPPORT FITTING PN A5381206720100, PO 692522.1 IAW SRM 51-40-21, PG 1.Sep 29, 2010 · N672FE · Airbus A300F4605R · Fuselage Miscellaneous StructureSDR FDEA201009293786Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED FROM FRAME 54 TO FRAME 55, RBL 38. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL THICKNESS IS 0.140 IAW SRM 51-31-20. REMAINING THICKNESS 0.111. MATERIAL LOSS 0.029 FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16. ALODINED IAW Sep 29, 2010 · N672FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201009293787Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED FROM FRAME 55 TO FRAME 56, RBL 38. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL THICKNESS IS 0.140 IAW SRM 51-31-20. REMAINING THICKNESS 0.105. MATERIAL LOSS 0.035 FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16. ALODINED IAW SSep 29, 2010 · N672FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201009293788Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED FROM FRAME 52 TO FRAME 53, LBL 76. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL THICKNESS IS 0.140 IAW SRM 51-31-20. REMAINING THICKNESS 0.133. MATERIAL LOSS 0.007 FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16. ALODINED IAW Sep 29, 2010 · N672FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201009293789Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED FROM FRAME 49 TO FRAME 50, LBL 58. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL THICKNESS IS 0.140 IAW SRM 51-31-20. REMAINING THICKNESS 0.126. MATERIAL LOSS 0.014 FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16. ALODINED IAW SSep 29, 2010 · N672FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201009233673Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED AT BS 1979, BL 0. REMOVED CORROSION IAW SRM 51-74-10. MAXIMUN MATERIAL LOSS IS 0.040. REMOVED 0.022. REMAINING MATERIAL IS WITHIN ALLOWABLE LIMITS IAW SRM 53-10-16. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-2310. PAISep 23, 2010 · N672FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201009233676Seat Track · corrodedMAIN CABIN CROSS TRACK IS CORRODED AT FRAME 28; RBL 32. REMOVED CORROSION IAW SRM 51-74-10. MAXIMUM ALLOWABLE MATERIAL LOSS IS 0.024. REMOVED 0.013. REMAINING MATERIAL IS WITHIN ALLOWABLE LIMITS IAW SRM 53-10-16. ALODINED IAW SRM 51-21-10. PRIMED IAW SRSep 23, 2010 · N672FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201009233677Seat Track · corrodedMAIN CABIN CROSS TRACK IS CORRODED AT FRAME 29; RBL 32. REMOVED CORROSION IAW SRM 51-74-10. MAXIMUM ALLOWABLE MATERIAL LOSS IS 0.040 AND 0.025. REMOVED 0.012 AND .014. REMAINING MATERIAL IS WITHIN ALLOWABLE LIMITS IAW SRM 53-10-16. ALODINED IAW SRM 51-Sep 23, 2010 · N672FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201009233681Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED FROM FRAME 30 - 31; LBL 45. REMOVED CORROSION IAW SRM 51-74-10 TO WITHIN ALLOWABLE LIMITS IAW SRM 53-10-16. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-23-10. PAINTED IAW SRM 51-75-10. MAXIMUM ALLOWABLE MATERIAL LOSS ISep 23, 2010 · N672FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201009233672Floorboard · damagedFWD CARGO COMPARTMENT FLOORBOARD 131 QC HAS EDGE DAMAGE AT MULTIPLE PLACES. DAMAGE REPAIRED IAW DWG SRZ 25-005, REV "H".Sep 23, 2010 · N672FE · Airbus A300F4605R · Fuselage Floor PanelSDR FDEA201009223628Floor Panel · damagedFLOOR PANEL 242 MF IS DAMAGED. FABRICATED NEW FLOOR PANEL 242 MF IAW DWG SRZ 25-005, REV "H".Sep 22, 2010 · N672FE · Airbus A300F4605R · Fuselage Floor PanelSDR FDEA201009223629Floor Panel · damagedMAIN CABIN FLOOR PANEL 232 FG IS DAMAGED. FABRICATED NEW FLOOR PANEL 232 FG IAW DWG SRZ 25-005, REV "H".Sep 22, 2010 · N672FE · Airbus A300F4605R · Fuselage Floor PanelSDR FDEA201009223630Floor Panel · damagedFLOOR PANEL 242 QJ IS DAMAGED. FABRICATED NEW FLOOR PANEL 242 QJ IAW DWG SRZ 25-005, REV "H".Sep 22, 2010 · N672FE · Airbus A300F4605R · Fuselage Floor PanelSDR FDEA201009223631Floor Panel · damagedFLOOR PANEL 242 WH IS DAMAGED. FABRICATED NEW FLOOR PANEL 242 WH IAW DWG SRZ 25-005, REV "H".Sep 22, 2010 · N672FE · Airbus A300F4605R · Fuselage Floor PanelSDR FDEA201009223632Floor Panel · damagedMAIN CABIN FLOOR PANEL 232 TG IS DAMAGED. FABRICATED NEW FLOOR PANEL 232 TG IAW DWG SRZ 25-005, REV "H".Sep 22, 2010 · N672FE · Airbus A300F4605R · Fuselage Floor PanelSDR FDEA201009213592Control Unit · failedON APP, AT 8,000' F/O WAS FLYING WE WERE CLEARED FOR THE ILS 25L APP. CAT3 LOX SO SECOND A/P WAS ENGAGED AFTER LAND WAS SELECTED. AFTER G/S & LOC CAPTURE AUTO PILOTS DISCONNECTED AND ALL FMA'S WENT BLANK AND ILS INFO. ATTEMPTED AGAIN WITH SAME RESULT. THEN Sep 21, 2010 · N679FE · Airbus A300F4605R · Autopilot SystemSDR FDEA201009203577Floor Panel · damagedAFT CARGO COMPARTMENT FLOOR PANEL 152 UF HAS MULTIPLE AREAS OF EDGE DAMAGE AND THE PANEL IS CRACKED. FABRICATED NEW FLOOR PANEL NR 152 UF IAW DWG SRZ 25-005, REV "H".Sep 20, 2010 · N672FE · Airbus A300F4605R · Fuselage Floor PanelSDR FDEA201009023240Seat Track · corrodedRT NR 3 SEAT TRACK CORROSION AT FR 41 POSITION. REPLACED THE DAMAGED TRACK BY NEW TRACK WITH FASTENER REF TO AB6F SRM 51-40-21. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.Sep 2, 2010 · N673FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201009023241Seat Track · corrodedCOMP'T CTR SEAT TRACK CORROSION BETWEEN FR41 AND FR44 POSITION. REPLACED THE DAMAGE TRACK BY NEW TRACK WITH FASTENER. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.Sep 2, 2010 · N673FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201009023242Seat Track · crackedRT NR 4 SEAT TRACK CRACKED AT FR 39 2". REPLACED THE SEAT TRACK BY FASTENER INSTALLED IAW AB6F, SRM 51-40-21. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.Sep 2, 2010 · N673FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201009013221Fitting · crackedLEFT THS INBD FWD HOIST POINT FITTING BASE CRACKED, REF EO 6-5510-7-5001 PT1. PERFORMED EO 6-5510-7-500/PT1 TO ACCOMPLISH THE WORK. REPAIR CLASSFIED AS MINOR IAW GMM 6-2-100.Sep 1, 2010 · N673FE · Airbus A300F4605R · Horizontal Stabilizer StructureSDR FDEA201009013222Floorbeam · corrodedBELOW LAVATORY LT NR 1 FLOORBEAM UPPER SURFACE CORROSION AT FR13B POSITION. DAMAGED FLOORBEAM WAS REPLACED. IAW SRM 51-72-10&57-40-21. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.Sep 1, 2010 · N673FE · Airbus A300F4605R · Fuselage Main, Floor BeamSDR FDEA201009013225Rib · crackedEO E6-5750-7-5003, PT1 WINGS-INBD FLAP-REINFORCEMENT OF RIB 25A. 1EA CRACK WAS FOUND AT A FASTENER HOLE OF LT WING RIB25. REPLACED DAMAGE RIB BY NEW RIB WITH FASTENERS. REF TO EO E6-5750-7-5003 PT1. (WINGS -INBD FLAP REINFORCEMENT OF RIB 25A). REPAIR CLASSep 1, 2010 · N673FE · Airbus A300F4605R · Wing, Rib/BulkheadSDR FDEA201008313212Skin · dentedTAIL SECTION EXTERNAL SURFACE GOT 1EA DENT BETWEEN S -33RS-34R, AT FR83-FR84 POSITION. RPT BY: 7084821 IAW AB6F SRM 53-19-12, THE AREA SKIN THICKNESS=0.098". MEASURED THE DENT D=0.027",A=1.600" IAW AB6F SRM 53-10-12 P117/118, WITHIN AREA RANGE, WITHIN ALLOWAug 31, 2010 · N673FE · Airbus A300F4605R · Fuselage Main, Plate/SkinSDR FDEA201008313219Skin · crackedRT WING T/E SPOILER SHROUND SUPPORT SKIN CRACKED POSITION BELLOW NR 5 SPOILER INBD SIDE. REMOVED THE CRACKED PART. FABRICATED A NEW SHROUD SUPPORT SKIN IAW DWG NR: A572.40194-200. INSTALLED THE SHROUD SUPPORT IAW AB6F SRM 51-40-21. THIS REPAIR CLASSFIED AAug 31, 2010 · N673FE · Airbus A300F4605R · Wing, Plate/SkinSDR FDEA201008313215Skin · crackedLT WING T/E SPOILER SHROUND SUPPORT SKIN GOT CRACK BELLOW NR 3 SPOILER INBD EDGE. REMOVE THE CRACKED PART. FABRICATE A NEW SHROUND SUPPORT SKIN IAW DWG NR A573.40194-201. INSTALL THE SHROUD SUPPORT IAW AB6F SRM 51-40-21. THIS REPAIR CLASSFIED AS MINOR IAWAug 31, 2010 · N673FE · Airbus A300F4605R · SpoilersSDR FDEA201008313218Skin · crackedRT WING T/E SPOILER SHROUD SUPPORT SKIN CRACKED POSITION BELLOW NR4 SPOILER OTBD SIDE. REMOVED THE OLD CRACKED PART. FABRICATED A NEW SHROUD SUPPORT SKIN IAW DWG NR:A572.40194-201. INSTALL THE SHROUD SUPPORT IAW AB6F SRM 51-40-21. THIS REPAIR CLASSIFIED ASAug 31, 2010 · N673FE · Airbus A300F4605R · Wing, Plate/SkinSDR FDEA201008112936Pressure Switch · failedTAKE-OFF POWER APPLIED & DURING ROLL. AT APPROX 60 KTS, NR 1 ENG FUEL FILTER CLOGG LIGHT ILLUMINATED WITH ECAM ALERT. TAKEOFF ABORTED, THROTTLES REDUCED. ECAM WARNING EXTINGUISHED, ALL ENGINE INDICATIONS NORMAL. SUBSEQUENT T/O NORMAL, BUT NR 1 ENG CLOG ECAM Aug 11, 2010 · N661FE · Airbus A300F4605R · Engine Fuel DistributionSDR FDEA201008082874Pitot Tube · obstructedCAPTAINS AIRSPEED ON PFD INDICATED GREATER THAN 100KTS. F/O AIRSPEED INDICATED AROUND 70KTS ON TAKEOFF ROLL. TAKEOFF WAS REJECTED. ON WALK AROUND, FOUND F/O PITOT TUBE OBSTRUCTED BY WHAT APPEARS TO BE A BEE. REMOVED PIECES OF BEE BUT SOME STILL REMAIN. WILAug 8, 2010 · N692FE · Airbus A300F4605R · Pitot/Static SystemSDR FDEA201007202623Skin Panel · crackedOPEN R 1 EA BOLT HOLE (POSITION G) WAS FOUND CRACKED AT THE R INBD 9 BOTTOM SKIN PANEL OF LT WING . IAW EO E6-5710-7 -5013. SKIN CRACK AREA REPAIRED IAW EA 6-5710-141607 (WINGS-AD 2008-06-18-EO 6-5710-5013 PT1- INSPECT AND MOD LOWER SKIN PANEL INBD OF RIB 9 Jul 20, 2010 · N661FE · Airbus A300F4605R · Wing, Plate/SkinSDR FDEA201007202625Skin Panel · crackedTPE OPEN R 1 EA CRACK WAS FOUND FROM THE FASTENER HOLE AT THE R IB 9 BOTTOM SKIN PANEL OF RT WING. THE CRACK LENGTH IS .2500" IAW EO E6-5710-7-5013 PT2. SKIN CRACK AREA REPAIRED IAW EA 6-5710-141607. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.Jul 20, 2010 · N661FE · Airbus A300F4605R · Wing, Plate/SkinSDR FDEA201007202626Skin Panel · crackedTPE OPEN R 1 EA CRACK WAS FOUND FROM THE FASTENER HOLE AT THE R IB 9 BOTTOM SKIN PANEL OF LT WING. THE CRACK LENGTH IS .5" IAW EO E6-5710-7-5013 PT1. SKIN CRACK AREA REPAIRED IAW EA 6-5710-141607. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.Jul 20, 2010 · N661FE · Airbus A300F4605R · Wing, Plate/SkinSDR FDEA201007202622Skin Panel · crackedOPEN R 1EA BOLT HOLE (POSITION G) WAS FOUND CRACK AT THE RI B 9 BOTTOM SKIN PANEL OF RT WING. IAW EO E6-5710-7-501 PT6. SKIN CRACK AREA REPAIRED IAW EA:6-5710-141607.Jul 20, 2010 · N661FE · Airbus A300F4605R · Wing, Plate/SkinSDR FDEA201007202624Skin Panel · crackedLT WING LWR SKIN PANEL INBD OF RIB 9 SUPPORT FLANGE CRACKED, JOGGLED SECTION. DAMAGED FLANGE CUT AND REPAIRED IAW E 6-5710-7-5013 PT5.Jul 20, 2010 · N661FE · Airbus A300F4605R · Wing, Plate/SkinSDR FDEA201006262199Proximity Sensor · malfunctionedAFTER TAKE OFF, GEAR SELECTED UP IN POSTION 2, MLG HANDLE WOULD NOT GO PAST NEUTRAL POSITION. SWITCHED TO POSITION 1 AND POSITIONED HANDLE TO UP AND LOCKED. BUT RT MAIN GEAR SHOWED DOOR LIGHT AND UNLOCK ON FWD INDICATOR. ALSO AT THAT TIME PITCH TRIM 2 TRIJun 26, 2010 · N656FE · Airbus A300F4605R · Landing Gear Position and WarningSDR FDEA201005031429Web · crackedNR 2 ENG /PYLON---PYLON WEB STRUCTURE IS CRACKED IN 2 PLACES AS SEEN THROUGH NACELLE ACCESS PANEL 421 CL. STOP DRILLED CRACKS IAW SRM 54-52-11. INSTALLED REPAIR IAW SRM 54-21-11, FIG 201, PGS 205 / 206, CONFIG 2 AND SRM 51-40-30. DISPLACED AND REINSTALLED WMay 3, 2010 · N658FE · Airbus A300F4605R · Nacelle/Pylon Miscellaneous StructureSDR FDEA201004131168Engine · failedDURING CLIMB OUT AT ABOUT FL270 ECAM GAVE US A ENG 2 OVERLIMIT FOLLOWED BY VIBRATION BAD ENOUGH AND ENG WINDING DOWN THAT WE HAD TO SHUT ENG DOWN, FOLLOWED QRH PROCEDURE FOR ENG FAIL. FOUND PIECES IN TAILPIPE. SUSPECT DAMAGED ENGINE. THE ENGINE IS APPROVEApr 13, 2010 · N680FE · Airbus A300F4605R · Engine (Turbine/Turboprop)SDR FDEA201004121153Web · crackedLT WING WEB A5796011424600 AT RIB 25A IS CRACKED R & R WEB REF SRM 51-40-21, PARA 7 AND SRM 51-72-10.Apr 12, 2010 · N658FE · Airbus A300F4605R · Wing Miscellaneous StructureSDR FDEA201004081105Frame · crackedLT SIDE CTR WING BOX LOWER SURFACE AT FRAME 47. ROTATING PROBE EDDY CURRENT INSP REVEALED INDICATION OF POSSIBLE CRACKS OR OTHER HOLE DAMAGE IN HOLES B, F, G, Q AND S. VISUAL INSP OF EACH HOLE REVEALS HOLE BORE DAMAGE IN AREAS OF INDICATIONS, MAKING TApr 8, 2010 · N658FE · Airbus A300F4605R · Wing, Center BoxSDR FDEA201004071090Plate · dentedFWD CARGO COMPARTMENT DOOR; FWD LOWER CORNER IS DENTED. REMOVED LOWER FWD CORNER IAW SRM 51-40-21, PARA 6. RECEIVED NEW CORNER PN A5237008120600, PO 678647.1. LOCATED AND DRILLED IAW SRM 1-40-44. INSTALLED NEW CORNER IAW SRM 51-40-21, PARA 6.Apr 7, 2010 · N658FE · Airbus A300F4605R · Cargo/Baggage DoorsSDR FDEA201004071091Support Angle · crackedAVONICS COMPARTMENT TRANSPONDER AND TCAS RACK; FWD/OTBD VERTICAL SUPPORT ANGLE IS CRACKED AT THE BASE. REMOVED PROTECTIVE COVER TO FOM IAW PMS 01-05-17. REMOVED SUPPORT ANGLE IAW SRM 51-72-10. RECEIVED NEW SUPPORT ANGLE PN A9253146900100, PO 678898.2. LOCATApr 7, 2010 · N658FE · Airbus A300F4605R · Fuselage Miscellaneous StructureSDR FDEA201004061062Floor Panel · delaminatedAFT CARGO COMPARTMENT FLOOR PANEL RT SIDE BETWEEN FRAME 59 AMD FRAME 60 IS VERY SOFT AND DELAMINATED.Apr 6, 2010 · N658FE · Airbus A300B4622R · Fuselage Floor Panel
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