N303
Registered owner: BEHLINGS JENNIFER E, SD (owner ≠ operator)
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.
13 reports on file, 2002-01-31 – 2006-08-07.
Part: SMOKE — DETECTED (NR 3 NACELLE)
FEW SECONDS AFTER NR 3 ENG STARTER WAS ACTIVATED (BUTTON LOCKED) AND LIGHT ILLUMINATED; NOTICED SMOKE WAS COMING OUT OF THE OVERHEAD ANNUNCIATOR PANEL. ABORTED START AND START BUTTON PULLED. ALL POWER WAS TURNED OFF AND SMOKE CEASED.
Part: SPAR CAP — DAMAGED (HORIZ STAB)
DURING "C" CHECK IN SAT, AIRCRAFT SUSTAINED AN IMPACT DAMAGE TO LT HORIZONTAL STAB FWD SPAR CAP UPPER CHORD AREA, DIRECTLY ABOVE THE FOURTH (FROM INBD) ACCESS HOLE IN FWD SPAR. DAMAGE LENGTH IS APPROX 11.0" LONG. REMOVED DAMAGE FROM HORIZONTAL STAB FWD SPAR CAP UPPER CHORD PER SRM 55-20-00, PERFORMED HFEC PER NDT SPM 06-10-01.001. NO CRACKS NOTED AROUND CUTOUT AREA.
Part: FLOORBEAM — CORRODED (BS 1781)
DURING "C" CHECK IN SAT FOUND EXFOLIATED CORROSION AT FLOOR BEAM IN STA 1781 RBL 57 (CORROSION ON AFT WEB OF BEAM). FABRICATED BEAM REPAIR SECTION. TREATED,PRIMED AND INSTALLED REPAIR PARTS IAW SRM 53-00-01 FIG 9.
Part: SKIN — DAMAGED (FUSELAGE)
DURING "C" CHECK IN SAT, CENTER CARGO DOOR CUTOUT AT FS 1781 BELOW STR 42 AT EXISTING REPAIR DOUBLER AND EXISTING A/C SKIN STRUCTURE HIT AND PUSHED INTO FRAME 1781 (LOWER T/E OF DOOR CUTOUT). REMOVED HEATER TUBES FROM AFT TQ BOX FS 1781-1787 BETWEEN 538R-542R IAW SRM 51-31-01 TO FOM. REMOVED FLOOR SILL WITH ROLLER AT FS 1781-1793 RBL60 IAW SRM 51-31-01 TO FOM. REMOVED EXISTING REPAIR DOUBLER IAW SRM 51-33-01 2 DOUBLERS AND 1 FILLER, BLENDED DAMAGED AREA AT AFT SECTION OF CARGO DOOR CUTOUT IAW SRM 53-50-00 FIG 26 SHEET 1 AND 2. REMOVED LWR AFT LWR CORNER DOUBLER AND TRIPLER FOR FOM IAW SRM 51-33-01; HFEC PER NDT SPM 06-10-01.001. NO CRACKS NOTED. OK TO FAB`D DOUBLERS AND INSTALL PER EA 010-5350-11-A0296.
Part: PLATE — CORRODED (NR 1 NACELLE)
DURING "C" CHECK IN SAT FOUND NR 1 ENG LEFT FAN COWL CENTER U BOLT PLATE HAS FRETTING CORROSION. REMOVED CORROSION FROM BOLT PLATE, MATERIAL LOSS WAS 0.030 FOUND TO BE OUT OF LIMITS IAW DC10 SRM 51-00-01 FIG 1A. FABRICATED NEW BOLT PLATE, TREATED AND PRIMED. INSTALLED BOLT PLATE IAW AMM 71-13-02.
Part: REPAIR — MISINSTALLED (BS 515-535)
LEFT FUSELAGE SKIN BETWEEN STA 515-535 LONG 28 TO LONG 32 HAS A SKIN SPLICE REPAIR WITH 3EA FREEZ PLUGS INSTALLED, REQUEST TO INSTALL EXTERNAL REPAIR DOUBLER THAT WAS REMOVED, MATERIAL THIKNESS .090. FABRICATED DOUBLER PER EA 010-5320-11-A0302. TREATED, PRIMED AND INSTALLED DOUBLER PER SRM 51-31-01 AND EA 010-5320-11 A0302.
Part: RUB STRIP — CORRODED (NR 1 NACELLE)
DURING "C" CHECK IN SAT FOUND NR 1 ENG LT CORE COWL FWD RUB STRIP AND RH CORE COWL AFT RUB STRIP HAVE CORROSION. REMOVED & REPLACED NR 1 ENG LT CORE COWL FWD RUB STRIP FROM 6 TO 12 O'CLOCK POSITION AND REMOVED & REPLACED RT CORE COWL AFT RUB STRIP FROM 3 TO 6 O'CLOCK POSITION IAW SRM 51-31-01.
Part: ACCESS PANEL — CORRODED (LT WING)
DURING "C" CHECK IN SAT FOUND LEFT WING I/B T/E ACCESS PANEL 541CR HAS THREE AREAS OF CORROSION. CORROSION FOUND TO BE OUT OF LIMITS IAW SRM 57-00-01 IN ALL THREE AREAS. FABRICATED REPAIR DOUBLERS AND BONDED THE 3 AREAS IAW SRM 51-71-00. SEALED AND PRIMED REPAIR DOUBLERS ON LH WING PANEL PER SRM 51-71-00 VOL II.
Part: SKIN — CORRODED (SPOILER)
DURING "C" CHECK IN SAT FOUND RIGHT WING NR 4 SPOILER HAS LIGHT CORROSION IN SEVERAL AREAS ON UPPER SURFACE. CORROSION FOUND TO BE OUT OF LIMITS IAW SRM 57-00-01 FIG 1A, REMOVED DAMAGED AREA AND CLEANED SURFACE IAW SRM 51-71-00 PAR 4, FABRICATED REPAIR PARTS, PREPPED PARTS AND SURFACES PER SRM 51-71-00, BONDED REPAIR PARTS AT 230DEG FOR 100MIN, PRIMED AND APPLIED SEALANT PER SRM 51-71-00.
Part: NOSE COWL — CRACKED (NR 1 ENGINE)
DURING "C" CHECK IN SAT FOUND NR 1 ENG NOSE COWL UPPER RH INNER ACOUSTICAL PANEL LOWER FWD CORNER HAS A COMBINATIONOF CRACK .7" CIRCUMFERENTIAL THAT EXTENDS BEYOND 2 FASTNERS AND .6" LONGITUDINAL AND CORROSION. DAMAGE FOUND TO BE TOO EXCESSIVE PER DC10 SRM VOL I PAR 9.A. REMOVED DAMAGED NOSE COWL AND INSTALLED NEW SERVICEABLE NOSE COWL ON NR 1 ENG PER AMM 71-11-00.
Earlier reports · 2002–2005 · 3 reports
2005
Part: ENGINE — OVERHEATED (NR 1)
BRU-DAY DIVERSION TO YYZ BECAUSE OF NR 1 ENGINE HIGH EGT AND HIGH FUEL FLOW. BEGINNING/DURING DESCENT INTO YYZ THE ENGINE FIRE WARNING BEGIN FLICKERING LIGHT AND ENGINE WAS SHUTDOWN PER ENGINE FIRE/FAILURE CHECKLIST. FLICKERING LIGHT WAS IN FIRE HANDLE AND START LEVER NR 1. ABOVE 92 PERCENT N1 THE EGT WAS HIGH AND THE FUEL FLOW WOULD INCREASE IN CRUISE FLIGHT. FOUND 14TH STAGE BLEED AIR MANIFOLD DAMAGED, R/R SAME AND R/R LEFT & RIGHT THRUST REVERSERS PER DC10 MM 71-10 OPS CHECK ALL NORMAL.
Part: COUPLER — DAMAGED (NR 2 ENGINE)
AIR TURNBACK INITIAL CLIMB OBSERVED MASTER WARNING & ENG FIRE WARNING LIGHT & BELL CAME ON & THEN OFF. NR 2 ENG NACELLE TEMP 260 DEG, NR 1 & 3 160 DEG. REDUCED ENG THRUST LEVER TOWARD IDLE TEMP FOLLOWED, PUSHED LEVER FORWARD & TEMP INCREASED, TESTED FIRE WARNING, NORMAL ON NR 1 & 3 BUT NO INDICATION ON 2. ACCOMPLISHED ENG FIRE CHECKLIST AND ALL OTHER APPLICABLE CHECKLISTS. FOUND DUCT APART ABOVE HIGH STAGE VALVE, REPOSITIONED SAME, REPLACED COUPLER. RAN ENG OPS CHECK, LEAK DOWN DECAY CHECK FOUND GOOD. PRESSURE WENT FROM 40 PSI TO 30 PSI WITH SYSTEM OFF IN 38 SEC ENG TEMP READ 200DEG PNEUMATIC TEMP AFTER 10 MIN AT 80 PERCCENT N2 55 PERCENT N1 NACELLE TEMP READS 80 DEG CELCIUS. OPS CHECK NORMAL.
2002
Part: CARGO TRACK — CRACKED (FUSELAGE) · airframe 63,802 hrs · 18,881 cycles
STA 959 UPPER CARGO SEAT TRACK HAS 10 INCH CRACK C/T RADIUS AT SPLICE X-27.