N33506
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.
96 reports on file, 1995-04-16 – 2000-10-28.
Part: JACKSCREW — WORN (HORIZONTAL STAB) · airframe 56,693 hrs · 43,592 cycles
HORIZONTAL STAB JACKSCREW WORN.
Part: FLOORBOARD — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A 1 INCH CRACK FS 579 - 680 BL 0-24 LEFT. INSTALLED REPAIR DOUBLER.
Part: FLOORBOARD — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A 1 INCH CRACK FLOOR PANEL FS 579 - 680 BL 0-24 LT. INSTALLED REPAIR DOUBLER.
Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
A 21 X 1 INCH CORRODED AREA ON SEAT TRACK. INSTALLED SEAT TRACK SPLICE.
Part: FRAME — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
TWO EACH 2 INCH DIAMETER HOLES WITH CRACKS AT BL 22 LT TO 44 LT. INSTALLED REPAIR DOUBLERS.
Part: FLOOR PANEL — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A 20 INCH CRACK FS 237 BL 0 TO BL 22 LT FLOOR PANEL. REMOVED AND FABRICATED NEW FLOOR PANEL.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
SIX INCHES OF FLOOR SUPPORT CHANNEL CORRODED. R2 DEFECTED AREA WITH IDENTICAL PART.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
CORRODED AREA .5 INCH DIAMETER AREAS 6 PLACES ON FLOOR SUPPORT AT STATION 2. REMOVED CORRODED ANGLE, FITTED AND DRILLED NEW EXTRUSION, TREATED AND PRIMED AREA.
Part: ROD END — CORRODED (LT MLG) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
ROD END CORRODED 2 INCH SECTION ON LT MLG FLYING DOOR. REMOVED AND REPLACED ROD END.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
CORROSION AT FS 198 UNDER DOOR PAN ON SKIN UNDER ENTIRE LENGTH OF DOOR PAN. REPAIRED CUSP AND WEB AND FLOOR SUPPORT ANGLE.
Part: LONGERON — GOUGED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A .5 INCH GOUGE ON LONGERON 7 LT FS 918. REMOVED DAMAGED AREA SPLICED IN REPAIR.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
A 1.75 X 42 INCH CORRODED AREA ON SUPPORT CHANNEL. REMOVED CORROSION INSTALLED NEW EXTRUSION.
Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
A 36 X 1 INCH CORRODED AREA ON SEAT TRACK. REMOVED AND REPLACED SEAT TRACK.
Part: FLOOR PANEL — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A 1 INCH CRACK AT FS 293 BL 44L FLOOR PANEL. INSTALLED REPAIR DOUBLERS.
Part: FRAME — GOUGED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A .375 X 1 INCH AREA GOUGED AT FS 756 AT LONGERON 18/FRAME. BLENDED GOUGE WITHIN LIMITS.
Part: ANGLE — CRACKED (PAX DOOR) · airframe 43,234 hrs · 55,740 cycles
A .375 INCH CRACK ON SEAL FORMER FWD LWR CORNER OF PAX DOOR. REMOVED AND REPLACED ANGLE.
Part: LONGERON — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A .75 INCH CRACK FS 160 LONGERON 4 LT. SPLICED IN NEW LONGERON REPAIR.
Part: FLOORBEAM — GOUGED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A .75 INCH GOUGE TOP OF FLOORBEAM BL 20.5 RT FS 639 - 658. BLENDED AREA WITHIN LIMITS. TREATED AND PRIMED.
Part: FLOOR PANEL — CRACKED (CABIN) · airframe 43,234 hrs · 55,740 cycles
TWO CRACKS 1 INCH LONG ON FLOOR PANEL. INSTALLED REPAIR DOUBLER.
Part: FLOORBOARD — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
PANEL EDGE CRACKED 1 INCH CRACK AT FS 579 - 680 BL 44 - 48 LT. INSTALLED REPAIR DOUBLER.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
A 2 X 4 INCH CORRODED AREA FS 200 -X50 Z 0 MEMBRANE. REMOVED AND REPLACED DAMAGED SECTION OF FLOOR MEMBRANE.
Part: LONGERON — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A 1 INCH CRACK LONGERON 6 LT AT FS 718. REMOVED AND REPLACED LONGERON.
Part: SUPPORT BRACKET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
CORRODED AREA 1 X 2 INCH AREA STATION 996 RT X 30 Z 0. CORRODED AREA REMOVED IAW EO AA10612.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
A 4 X 30 INCH CORREDED AREA BETWEEN FS 965 TO 996 X20 Z0. REMOVED AND REPLACED PANEL.
Part: WEB — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
CRACKS 1 EA 3 INCH, 1 EA 4 INCHES, 1 EA 3.5 INCHES AT CUSP WEB LONGERON 18 RT FS 698 TO FS 617. REMOVED AND REPLACED CUSP WEB.
Part: WEB — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A 1 INCH CRACK FS 207 AT LONGERON 15 LEFT. INSTALLED DOUBLER REPAIR.
Part: BRACKET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
CORRODED BRACKET 1 X 1 INCH, 6 INCH DIAMETER SKIN. REMOVED AND REPLACED BRACKET AND REMOVED CORROSION FROM SKIN, REMOVAL WITHIN LIMITS.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
A 2 X 2 INCH AREA OF CORROSION ON CABIN FLOOR FS 200 BL 45 RT. REMOVED AND REPLACED FLOOR SUPPORT.
Part: FLOOR PANEL — CRACKED (CABIN) · airframe 43,234 hrs · 55,740 cycles
TWO CRACKS APPROX 1 INCH LONG ON FLOOR PANEL. INSTALLED REPAIR DOUBLER.
Part: FRAME — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A 3 INCH CRACK FS 639 BL 58.5 FRAME CRACKED BETWEEN STRINGER 18 AND 19. REMOVED AND REPLACED MAIN FRAME.
Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A 2 INCH CRACK 2 PLACES AT FS 755 BL 30 LT 1 INCH X 6 INCH ABOVE WHEEL WELL (INTERCOSTAL). DYE PENETRANT AREA FOUND DEEP TOOL MARKS, BLENDED WITHIN LIMITS.
Part: PAN — CRACKED (DOOR) · airframe 43,234 hrs · 55,740 cycles
A .375 INCH WIDE CIRCUMFERRENTIAL CRACK APB DOOR UPPER RT AFT CORNER AT BLIND NUT (PAN). REPAIRED DOOR.
Part: PULLEY BRACKET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
A .5 INCH CORRODED AREA STATION 965 X20 Z0 PULLEY BRACKET. REMOVED AND REPLACED PULLEY BRACKET.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
A 4 X 6 INCH CORRODED AREA AT STATION 180 FLOOR SECTION MEMBRANE. REMOVED DAMAGED AREA AND INSTALLED NEW SECTION OF MEMBRANE.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,506 hrs · 55,740 cycles
CORROSION 5 PLACES .5 INCH J ANGLE AT FS 200 BL 0 TO 24 RT. R2 ANGLE.
Part: PAN — CORRODED (SERVICE DOOR) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
CORRODED AREA FS 174 - 178 2 SPOTS ON DOOR FRAME. R2 SERVICE DOOR PAN.
Part: FRAME — MISDRILLED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A 3'' AREA WITH DOUBLE DRILLED HOLES. REMOVED AND REPLACED DAMAGED SECTION AT FS 389 BETWEEN LONGERON 7 AND 8 RT.
Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
A 10 X 1 INCH CORRODED AREA ON SEAT TRACK. SPLICED IN NEW SECTION OF SEAT TRACK.
Part: FLOORBOARD — CRACKED (CABIN) · airframe 43,234 hrs · 55,740 cycles
A 1 INCH CRACK UPPER SURFACE OF FLOORBOARD FS 832. INSTALLED REPAIR DOUBLER UPPER SURFACE.
Part: LONGERON — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A 1 INCH CRACK FS 160 LONGERON 2 LT. REMOVED CRACKED SECTION, INSTALLED DOUBLER REPAIR.
Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
CORRODED AREA 1 X 6 INCH STATION 996 RT X35 Z-0 FLOORBEAM. REPAIRED WITH ANGLE.
Part: LONGERON — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A 1 INCH CRACK STA 218 LONGERON 3 RT. SPLICED IN 18.6 INCHES ON LONGERON AT FS 214 TO FS 232.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
CORRODED AREA .5 INCH DIA 7 PLACES AT FS 164 ATTACH ANGLE. R2 CABIN FLOOR SUPPORT ANGLE.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
A 8 X 9 INCH CORRODED AREA AT FS 200 TO 209 SUBFLOOR MEMBRANE. REPAIRED CORRODED AREA.
Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
A 19 X 1 INCH CORRODED AREA ON SEAT TRACK. SPLICED IN REPAIR.
Part: FLOORBOARD — CRACKED (CABIN) · airframe 43,234 hrs · 55,740 cycles
CORNER OF FLOOR PANEL CRACKED APPROX 1.5 INCH AT FS 579 TO 613 BL 24R TO 44R. INSTALLED REPAIR DOUBLER.
Part: ATTACH ANGLE — CRACKED (RT PYLON) · airframe 43,234 hrs · 55,740 cycles
RIGHT HAND PYLON AFT BULKHEAD ATTACH ANGLE O/B END CRACKED. FABRICATED NEW REPAIR, TREATED AND PRIMED AND INSTALLED REPAIR.
Part: PULLEY BRACKET — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
CORRODED AREA ON PULLEY BRACKET STATION 995 X 24 Z0. REMOVED AND REPLACED PULLEY BRACKET.
Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A 3 INCH CRACK AT FS 700 BL 24 RT 6 INCHES ABOVE WHEEL WELL. INSTALLED DOUBLER REPAIR.
Part: SEAT TRACK — CORRODED (COCKPIT) · airframe 43,234 hrs · 55,740 cycles
SEVERAL ELONGATED HOLES IN TOP RAIL ON CO-PILOTS SEAT TRACK. R2 TOP RAIL DOUBLER.
Part: ATTACH FITTING — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A 3 INCH CRACK AT FS 680 BL 45 RT ABOVE CENTER WING. REPLACED WITH IDENTICAL PART, MAJOR REPAIR.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
SUPPORT CORRODED AT STATION 164 - 200 -X45, Z 0. REMOVED AND REPLACED DEFECTIVE PART.
Part: FLOORBOARD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
SERVRAL AREAS OF CORROSION AT STATION 965 30 RT ON FLOOR PANEL. REPLACED FLOOR PANEL.
Part: SUPPORT BRACKET — CRACKED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A 1 INCH CRACK AT FS 988 X20, 20 ON SUPPORT. INSTALLED REPAIR CHANNEL.
Part: SEAT TRACK — DAMAGED (COCKPIT) · airframe 43,234 hrs · 55,740 cycles
SEVERAL ELONGATED HOLES IN TOP RAIL OF SEAT TRACK. R2 TOP RAIL PILOTS SEAT. REPLACED TOP RAIL DOUBLER.
Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
A 24 X 1 INCH CORRODED AREA ON SEAT TRACK. SPLICED IN REPAIR.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
A 1.5 X 6 INCH AREA CORRODED AT STATION 164 BL 0 TO 24 RT ON FLOOR SUPPORT. REPAIRED AS PER TIMCO DRAWING OOTOO5M011.
Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
A 20 X 1 INCH CORRODED AREA AT FS 542 - 562 BL 44 LT SEAT TRACK. INSTALLED SEAT TRACK PLUG.
Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
FLOORBEAM CORRODED AT FS 996, X20 TO X50, Z0 SEVERAL 1 TO 2 INCH AREAS. REMOVED AND FABRICATED NEW FLOORBEAM ANGLE.
Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,234 hrs · 55,740 cycles
CORRODED AREAS 1 X 1 INCH AREAS 6 PLACES. REMOVED CORROSION OUT OF LIMITS. R2 UPPER CAP ON FLOORBEAM AT FS 980.
Part: FLOORBEAM — CHAFED (FUSELAGE) · airframe 43,234 hrs · 55,740 cycles
A .75 INCH CHAFED AREA 6 PLACES AT FS 598 BL 7, 10, 14, LT ON TOP OF FLOORBEAM. BLENDED AREA AND FOUND WITHIN LIMITS.
Part: SEAT TRACK — DAMAGED (COCKPIT) · airframe 43,234 hrs · 55,740 cycles
SEVERAL ELONGATED .25 INCH HOLES IN CO-PILOTS SEAT TRACK O/B AFT SIDE. R2 TOP RAIL REPAIR DOUBLER.
Part: SEALANT — MISSING (WINDSHIELD) · airframe 55,766 hrs · 43,248 cycles
FLT 19 RETURNED TO FIELD AFTER LOUD OUTSIDE NOISE WAS NOTICED DURING T/O. RESEALED GAP IN WINDSHIELD AT SPLICE FRAME AND RETORQUED SCREWS. RETURNED TO SERVICE.
Earlier reports · 1995–1999 · 33 reports
1999
Part: JAMB — CORRODED (CARGO DOORWAY)
INSPECTION FOUND CORROSION AT FORWARD BAGGAGE COMPARTMENT LOWER CUTOUT WHERE THRESHOLD MOUNTS. THE FORWARD LOWER CUTOUT WAS REMOVED. THE LOWER CARGO DOOR JAMB PAN WAS CUT OUT AND A NEW PAN WAS INSTALLED IAW SRM 51-10-3, PAGE 1, 51-30-2, PAGE1, AND 53-05, PAGE 113.
Part: WIRE — DAMAGED (CABIN)
INSPECTION FOUND EMERGENCY PATH LIGHTING IN AFT ACCESS SECTION WITH AFT LIGHT WIRING DAMAGED. THE WIRING WAS REPAIRED AND OPERATION CHECKED GOOD IAW MM 33-50-00.
Part: SKIN — DENTED (RT TE FLAP)
INSPECTION FOUND A DENT ON BOTTOM OF RT WING FLAP APPROXIMATELY 13 O/B OF I/B FOLDING VANES AREA. THE DENTED AREA WAS CUT OUT AND A REPAIR WAS INSTALLED IAW SRM 57-01, FIGURE 5 AND 51-10-2, PAGE 1.
Part: BATTERY PACK — DISCHARGED (CABIN)
INSPECTION FOUND FORWARD CABIN EMERGENCY PATH LIGHTING INOPERATIVE. THE BATTERY PACK WAS REMOVED AND REPLACED AND OPERATION CHECKED GOOD IAW MM 33-50-00.
Part: SKIN — BULGED (BS 229)
INSPECTION FOUND LT FUSELAGE SKIN BULGED AT STA 229 BETWEEN LONGERON 17L AND 18L. THE BULGED AREA OF SKIN WAS REMOVED. NEW SKIN WAS INSTALLED IAW ECRA 5330-02445.
Part: PANEL — DEBONDED (RT WING)
INSPECTION FOUND LOWER SURFACE OF RT WING UPPER TRAILING EDGE PANEL DEBONDED. THE PANEL WAS REMOVED AND REPLACED IAW SRM 51-30-2, FIGURE 4.
Part: VANE — DEBONDED (CENTER TE FLAP)
INSPECTION FOUND THE RT FLAP I/B FIXED VANE AND LT FLAP CENTER FIXED VANE DEBONDED. THE FLAP VANES WERE REMOVED AND REPLACED IAW MM 27-51-3, PAGE 201.
Part: SKIN — PUNCTURED (RUDDER)
INSPECTION FOUND RT RUDDER SKIN PUNCTURED APPROXIMATELY 30 INCHES DOWN FROM TOP EDGE. THE DAMAGED AREA WAS CUT OUT IAW SRM 55-03-00. A DOUBLER REPAIR WAS INSTALLED IAW SRM 55-03 AND 51-10-3. THE RUDDER WAS REBALANCED IAW SRM 55-40-1, PAGE 42.
Part: FUSE — FAILED (L1-L2 DOOR)
L1 AND L2 DOOR EMERGENCY EXIT LIGHTS INOP. REPLACED FUSES IN BATTERY PACK IN FORWARD O/H CEILING.
Part: LIGHT — INOPERATIVE (CABIN)
TWO RED FLOOR PROX LIGHTS AT FORWARD END INOP. RELAMPED FORWARD RED EMERGENCY PROX LIGHT. SPLICED IN NEW SOCKET FOR OTHER LIGHT. OPS CHECK NORMAL.
1998
Part: SWITCH — INOP (LT MLG DOOR)
THE GEAR DOOR OPEN LIGHT REMAINED ILLUMINATED AFTER GEAR WAS EXTENDED FOR LANDING AT IAH. THE L/H AND R/H MLG DOORS WERE DAMAGED ON LANDING. MAINTENANCE REMOVED AND REPLACED THE L/H MLG DOOR SWITCH. BOTH L/H AND R/H MLG DOORS WERE REMOVED AND REPLACED IAW MM 32-12-01. INDICATION AND OPERATIONAL CHECKS WERE GOOD.
1997
Part: BELTFRAME — CRACKED (BS 1143)
INSPECTION FOUND A 2 INCH CRACK IN BELTFRAME AT STA 1143 ON LT SIDE AT TAIL CONE INTERIOR RELEASE HANDLE. DOUBLERS WERE FABRICATED AND INSTALLED IAW SRM 53-01.
Part: SKIN — CRACKED (BS 200)
INSPECTION FOUND TWO PARALLEL SEMICIRCULAR CRACKS .25 INCH APART WITH 2 DIAMETERS IN RT FUSELAGE SKIN AT STA 200 SIX INCHES BELOW CUSP LINE. REPAIRED IAW SRM 53-04.
Part: STIFFENER — CRACKED (MAIN CABIN DOOR)
INSPECTION FOUND A 1.5 INCH CRACK BETWEEN FORWARD TWO LIGHTENING HOLES OF THE BOTTOM ROW OF MAIN CABIN DOOR STIFFENER. A NEW STIFFENER AND FILLER WERE INSTALLED IAW SRM 51-30-2.
Part: BEAM — CRACKED (FUSELAGE)
INSPECTION FOUND A .5 INCH CRACK IN BEAM FORWARD OF SERVICE DOOR. REPAIRED IAW SRM 53-05.
Part: CIRCUMFERENTIAL — CRACKED (BS 294)
INSPECTION FOUND FOUR 1 INCH CRACKS IN CIRCUMFERENTIAL AT STA 294. THE CRACKS WERE LOCATED AT LONGERONS 27R, 30R, 28L, AND 29L. REPAIRS WERE PERFORMED IAW SRM 51-30-00.
Part: ANGLE — CRACKED (BS 983-996)
INSPECTION FOUND A 3 INCH CRACK WITH CORROSION IN FUSELAGE TO FLOOR ANGLE AT STA 983 TO 996, LONGERON 19R. THE CORRODED SECTION WAS REMOVED, FILLER AND UPPER AND LOWER ANGLE DOUBLERS WERE INSTALLED IAW SRM 53-05, FIGURE 25, SHEET 1.
Part: SKIN — CRACKED (BS 63)
INSPECTION FOUND THREE .25 INCH CRACKS FROM TWO RIVETS IN LT FUSELAGE SKIN AT STA 63 TEN INCHES BELOW CUSP LINE. THE CRACKED AREAS WERE CUT OUT, A FILLER AND DOUBLER REPAIR WAS INSTALLED IAW SRM 53-04, FIGURE 38.
Part: SKIN — CRACKED (BS 58)
INSPECTION FOUND A 2 INCH CRACK AND TWO .5 INCH CRACKS IN LT FUSELAGE SKIN AT STA 58 TWELVE INCHES BELOW CUSP LINE. THE CRACKED AREA WAS CUT OUT, A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-01, FIGURE 4.
Part: SKIN — CRACKED (BS 69)
INSPECTION FOUND A .625 INCH CRACK IN LT FUSELAGE SKIN AT STA 69 TWO FEET BELOW CUSP LINE. REPAIRED IAW SRM 53-01, FIGURE 4.
Part: CLIP — BROKEN (TAIL CONE)
THE EXTERIOR TAIL CONE RELEASE HANDLE PULLED OUT OF CLIPS AT TEN POUNDS AND 80 POUNDS WAS REQUIRED TO RELEASE TAIL CONE USING EXTERIOR HANDLE. A BROKEN CLIP ON RELEASE HANDLE WAS REPLACED, TIMING BLOCKS WERE ADJUSTED, AND TAIL CONE LATCHES WERE LUBRICATED.
1996
Part: WIRE — DAMAGED (CABIN)
INSPECTION FOUND EMERGENCY TRACK LIGHTING IN FIRST CLASS SECTION OF CABIN COMING UP AND INOPERATIVE. MAINTENANCE FOUND DAMAGED TRACK LIGHT WIRING. THE WIRING WAS REPAIRED AND THE TRACK WAS REINSTALLED.
Part: SKIN — DENTED (BS 950)
INSPECTION FOUND LT FUSELAGE EXTERIOR SKIN DENTED AT STA 950, STRINGERS 23 AND 24. THE DENT WAS REWORKED AND AN HFEC INSPECTION WAS ACCOMPLISHED WITH NO CRACKS FOUND. AN INTERNAL DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-04, FIGURE 38.
Part: SKIN — BULGED (BS 237)
INSPECTION FOUND LT FUSELAGE SKIN BULGED ABOVE CUSP LINE AT STA 237, LONGERON 15 TO 18L. THE SKIN PANEL WAS REMOVED AND THE AREA WAS CLEANED, TREATED AND PRIMED. A REPLACEMENT SKIN PANEL WAS FABRICATED AND INSTALLED IAW SRM 51-10-3, 53-30-0 AND ECRA 5330-01618.
Part: RUDDER TAB — DELAMINATED (RUDDER)
INSPECTION FOUND RUDDER TAB DELAMINATED. THE RUDDER TAB WAS REMOVED AND REPLACED PER MM 27-20-2.
Part: COVER PLATE — CRACKED (RT ELEVATOR)
RT ELEVATOR TRAILING EDGE IN BETWEEN BOTH TABS, GEAR TAB INBOARD END ROD COVER UPPER PLATE WAS FOUND CRACKED. THE OLD DOUBLER WAS REMOVED AND A NEW DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-30-2.
Part: RAZOR OUTLET — INOPERATIVE (LT LAV)
SMOKE WAS OBSERVED COMING FROM AREA OF FLUORESCENT LIGHT IN LT LAV AND THE SMOKE DETECTOR WAS SOUNDING WHILE EN ROUTE. LAV CIRCUITS WERE DEACTIVATED AND THE SMOKE CEASED. THE AIRCRAFT LANDED IN OMA WITHOUT INCIDENT. MAINTENANCE FOUND THE LT LAV RAZOR OUTLET CIRCUIT BREAKER POPPED. THE CIRCUIT BREAKER WAS RESET, BUT POPPED AGAIN WHEN OUTLET WAS USED. THE RAZOR OUTLET WAS PLACARDED INOPERATIVE AND THE CIRCUIT BREAKER WAS COLLARED. IN ADDITION, THE LAV LIGHTS AND FLUSH MOTOR WERE CHECKED WITH NO DISCREPANCIES NOTED.
Part: TURBINE BLADES — BROKEN (NR 2 ENGINE)
THE NR 2 ENGINE BEGAN TO VIBRATE WITH N1 DROPPING OFF TO 40 PERCENT DURING CLIMB-OUT OF CLE. THE AIRCRAFT WAS RETURNED TO CLE WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND METAL IN THE NR 2 ENGINE TAILPIPE. THE NR 2 ENGINE WAS REMOVED AND REPLACED. THE SDR WILL REMAIN OPEN FOR PART INFORMATION PENDING INVESTIGATION. SHOP FINDINGS REVEALED TWO BROKEN FIRST STAGE TURBINE BLADES DUE TO IMPACT.
1995
Part: SWITCH — STICKING (GEAR HANDLE)
FLT NR 1474 - IND - WHEN FLAPS WERE EXTENDED TO 25 DEGREES WITH GEAR EXTENDED AND THREE GREEN INDICATIONS, THE GEAR WARNING INDICATED GEAR NOT DOWN AND LOCKED ON APPROACH TO IND. THE FLAPS WERE PUT BACK TO FIVE DEGREES AND THE LANDING GEAR WAS CYCLED. WHEN THE FLAPS WERE EXTENDED BEYOND 15 DEGREES AGAIN, THE WARNING HORN SOUNDED. THE X33 CIRCUIT BREAKER WAS PULLED AFTER GEAR WAS CONFIRMED DOWN AND LOCKED. THEN WITH FLAPS AT 40 DEGREES, THE GROUND PROXIMITY WARNING SYSTEM ACTIVATED. THE LANDING WAS UNEVENTFUL. MAINTENANCE FOUND THE LANDING GEAR HANDLE SWITCH STICKING. THE SWITCH WAS CLEANED AND LUBRICATED. THE SWITCH WAS OPERATED SEVERAL TIMES AND ALL CHECKED GOOD PER MM 32-60-0. (M)
Part: JAMB — CRACKED (AFT VENTRAL DOOR)
HOU - INSPECTION FOUND THE AFT VENTRAL DOOR JAMB HAD A 2 INCH CRACK ON THE FORWARD SIDE OF LEFT CORNER. REPAIRED PER SRM 53-08, FIGURE 29. (X)
Part: JAMB — CRACKED (AFT VENTRAL DOOR)
HOU - A ONE INCH CRACK WAS FOUND IN THE AFT VENTRAL DOOR JAMB BEHIND THE TOP RIGHT DOOR STOP. THE DOOR JAMB WAS REPAIRED IAW ECRA 653C0116. (M)
Part: CABLES — OUT OF ADJUST (TAIL CONE)
HOU - THE TAIL CONE WOULD NOT RELEASE WHEN INTERIOR HANDLE WAS PULLED. THE CABLES WERE ADJUSTED IAW MM 53-50-3. (X)
Part: EEL BATTERIES — DISCHARGED (CABIN)
IAH - FLT 1853 - BOTH COCKPIT EMERGENCY EXIT LIGHTS WERE FOUND INOPERATIVE DURING A PREFLIGHT CHECK. THE BATTERIES WERE REMOVED AND REPLACED AND OPERATION OF THE EMERGENCY EXIT LIGHTS WAS RESTORED. (W)