N361FE
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.
109 reports on file, 2003-07-21 – 2015-09-07.
Part: PUSHROD — OUT OF ADJUST (SPOILER) · airframe 827 hrs · 29,970 cycles
AILERONS APPEAR TO BE OUT OF RIG. WING LEVEL HAS THE CAPTAINS YOKE DISPLACED TO RIGHT, FIRST OFFICERS 10* RIGHT. ALSO REQUIRES 2 - 3* RT AILERON TRIM, ACFT HAD 3* AILERON TRIM ON PREFLIGHT. NOTED WITH HYDRO ON & AILERON TRIM SET TO ZERO, AILERONS ARE FAIRED & YOKES ARE CENTERED. SYNOPTIC PAGE INDICATION AGREES. TROUBLE SHOT IAW FIM 27-10-00-2-810-801, FOUND LEFT SPOILERS 1 & 5 SLIGHTLY FLOATING. ADJUSTED SPOILER PUSHRODS CE FOR SPOILER 1L & CA FOR SPOILER 5L, SPOILERS FAIR INTO WING & OPERATIONS NORMAL IAW AMM 27-67-01-2 3 B 17-24 & SECTION 4 ALSO AMM 27-60-00-5 FIGS 504SH1 & SH4. AILERON SYS OPERATIONS NORMAL IAW AMM 27-10-00-2.
Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 825 hrs · 29,850 cycles
ON TAXI OUT, AIR SYS 2 OFF, ALERT FOLLOWED SHORTLY BY LEVEL 2, AIR MANIFOLD 2 FAIL, ALERT. SHUTDOWN NR 2 ENG. TROUBLE SHOT, RETURNED NR 2 PNEUMATICS TO NORMAL CONFIG. TROUBLE SHOT IAW FIM TASK 36-23-00-810-804, NO DEFECTS NOTED. PERFORMED NR 2 PNEUMATIC SYS PRESS DECAY CHECK USING APU AIR IAW AMM 36-00-01, 25 SEC & USING ENG BLEED AIR IAW AMM 36-00-02, 48 SEC AT 100 DEG. ALL DECAY TEST PASSED. PERFORMED ENTIRE FUNCTIONAL TEST OF PNEUMATIC SYS NR 2 IAW AMM 36-00-03-5, NO DEFECTS NOTED WITHIN NR 2 PNEUMATIC SYS. PNEUMATIC SYS NR 2 OK FOR SERVICE.
Part: SCREW — LOOSE (R1 DOOR) · airframe 819 hrs · 29,548 cycles
DOOR R1 CLOSED WITHOUT SWITCH BEING TOUCHED. FOUND DISARM LIGHT CAPSULE RETAINING SCREW LOOSE & SHORTING ACROSS DOOR SWITCH CONTACTS. REINSTALLED RETAINING SCREW. OPERATIONS CHECKED NORMAL.
Earlier reports · 2003–2014 · 106 reports
2014
Part: ANGLE — CRACKED (RT WING) · airframe 80,957 hrs · 28,999 cycles
FOUND APPROX 1 INCH CRACK IN TEE ANGLE AT INBD CORNER OF RT WING FUEL DOOR CUT OUT IAW WRI 57-30 1474. VERIFIED CRACK IN TEE ANGLE WITH HFEC IAW NTM 20-30-00 PT 6. INSTALLED TEE AND FORMER REPAIR IAW EA 8-5730-T0308673. MAJOR REPAIR.
Part: SKIN — CRACKED (RT WING) · airframe 80,957 hrs · 28,999 cycles
FUEL PANEL DOOR CUT OUT HAS A CRACK INDICATION BETWEEN TWO FASTENERS. A .75 INCH BLACK SMOKE LINE & PAINT CHIPPING AWAY IN A STRAIGHT LINE FROM SKIN EDGE. WIPED AWAY, STILL HAS A SLIGHT APPEARANCE OF A CRACK. PERFORMED HFEC INSPECTION IAW NTSPM 06-10-01.001. REMOVED DAMAGED SKIN IAW SRM 57-10-00 FIGURE 68 USING .5 INCH RADIUS. VERIFIED REMOVAL OF CRACK WITH HFEC IAW NTM 20-30-00 PT 6. NO CRACK REMAINS.
2013
Part: PRESSURE SWITCH — FAILED (N/A) · airframe 80,229 hrs · 28,589 cycles
DURING CRUISE FL 340, SYS 1 MANIFOLD FAILURE. SYSTEM DEPRESSURIZED, FOLLOWED ORH, LANDING UNEVENTFULLY. REMOVED AND REPLACED LEFT WING MANIFOLD FAILURE DETECTION PRESSURE SWITCH IAW AMM 36-23-03-5.
Part: VENT — FAILED (PAX DOOR) · airframe 80,095 hrs · 28,520 cycles
UPON ARRIVAL AT IND, FOUND ACCESS DOOR FOR CTR CARGO VENT HANDLE MISSING FROM FAIRING. BLENDED MINOR DAMAGE ON FAIRING. PAINTED IAW SRM. INSTALLED VENT HANDLE ACCESS DOOR ASSY 152RT. INSPECTED UPPER AFT FUSELAGE RT SIDE, RT HORIZ STAB TOP SIDE AND NR 2 ENG INLET. NO FURTHER DAMAGE NOTED. FINAL CLOSED.
Part: STRUCTURE — DAMAGED (L1 DOOR) · airframe 79,817 hrs · 28,361 cycles
AFTER ON LOAD, CREW CLOSED MAIN CARGO DOOR, REPORTED A PIECE OF L1 DOOR FELL OFF. DAMAGED PIECE FROM L1 DOOR IS FROM THE LOWER DOOR ACCESS PANEL BELOW LIFT BAR AFT END, MAGNETIC STRIKE LATCH BRACKET BROKE FROM THE COMPOSITE PORTION OF THE PANEL. INSTALLED AFT MAGNETIC LATCH ON L1 DOOR LOWER COVER IAW SMP.
Part: WARNING LIGHT — FALSE ACTIVATION (NR 2 ENGINE) · airframe 79,775 hrs · 28,335 cycles
WHEN PM SET TAKEOFF POWER ENG 2 N1 WAS 5 PERCENT ABOVE ENG 1 & 3. REJECTED TAKE OFF DUE TO ENG 2 EXCEEDANCE ALERT AT 189KTS. N2 PEAKED AT 101.1 PERFORMED BORESCOPE INSPECTION OF THE NR 2 ENGINE HIGH PRESSURE COMPRESSOR AND HIGH PRESSURE TURBINE IAW AMM 72-00-00-6-1 PARA 2C.(1)(B) AND (C). NO LIMITING DEFECTS NOTED. COMPLIED WITH INSPECTION PROCEDURES AMM 72-00-00-6-1. PARA C FOR CORE ENGINE N2 OVERSPEED. INSPECTED INTAKE AND EXHAUST, NO FAULTS FOUND. COMPLIED WITH MEC VSV FEEDBACK STATIC RIG CHECK, NO FAULTS FOUND. REF AMM 73-20-01-2. BOROSCOPE COMPLIED WITH. RUN AND LEAK CHECKED GOOD REFERENCE JRH. AIRCRAFT OK FOR CONTINUED SERVICE.
2012
Part: SMOKE DETECTOR — FALSE ACTIVATION (CARGO BAY) · airframe 78,430 hrs · 27,599 cycles
DUE TO PREVIOUS PDIS LEVEL 3 ALERT "CARGO FIRE LWR FWD". COMPLIED WITH QRH AND DISCHARGED AGENT- R & R 4EA COMPARTMENT SMOKE DETECTORS PRECAUTIONARY. PARTS ON R & R LWR CARGO BAY NR 1 FIRE BOTTLE. IAW MM 26-22-01-4-1 STEPS 1 THRU 2E4. R & R BOTTLE AND SQUIB.
Part: SHEAR TIE — CORRODED (ZONE 100) · corrosion level 2 · airframe 78,221 hrs · 27,490 cycles
AT APPROX STA 1767, 48R- FASTENER HEAD MISSING, BULGING IN AREA. REMOVED BROKEN FASTENER. REMOVED CORRODED SHEAR TIE. CLEANED CORROSION ON INBD SKIN IAW SRM 51-21-01, VOL 2. PROCESSED NEW SHEAR TIE IAW SRM 51-00-01, VOL 2. ALODINE AND PRIME IAW SRM 51-21-00, VOL 2. INSTALLED SHEAR TIE IAW SRM 51-31-01, VOL 2.
Part: BULKHEAD — CRACKED (ZONE 100) · airframe 78,221 hrs · 27,490 cycles
LEFT WHEEL WELL INBD BULKHEAD CRACKED, APPROX 8 INCHES FWD OF AFT BULKHEAD AND 4 INCHES BELOW HORIZONTAL PRESSURE PANEL. COMPLIED WITH HFEC IAW NDT SPM 06. FOUND CRACK TO 2.50" LONG, CRACK RUN VERTICALLY. BS 1521. REPAIRED CRACK BULKHEAD AREA IN REF TO SRM 53-00-01, FIG 4.
Part: LONGERON CLIP — CRACKED (ZONE 100) · airframe 78,221 hrs · 27,490 cycles
AFT CARGO BAY BS 1907-1927 APROX LONGERON 47 LT HAS A CRACK. R & R LONGERON CLIP IAW SRM 51-31-01, VOL II.
Part: SHEAR TIE — CRACKED (ZONE 100) · corrosion level 2 · airframe 78,221 hrs · 27,490 cycles
DURING C-CHECK- FOUND SUNKEN FASTENERS AND BULGING SKIN AT APPROX STA 1887, 47R. REMOVED SHEAR TIE AT STA 1887 47R REF SRM 51-00-01, VOL I. CLEANED AREA NO CORROSION NOTED REF SRM 51-21-01, VOL II. OK TO TREATED AND PRIME AREA REF SRM 51-21-01. TREATED AND PRIMED AREA REF SRM 51-21-01. INSPECTED SKIN NO BULGING NOTED REF SRM 51-80-01, VOL II. OK TO INSTALL SHEAR TIE. INSTALLED SHEAR TIE REF 51-00-01, VOL I.
Part: SHEAR TIE — CRACKED (ZONE 100) · corrosion level 2 · airframe 78,221 hrs · 27,490 cycles
DURING C-CHECK, FOUND CRACKED SHEAR TIE AT BS 1921 S43R. REMOVED CRACKED SHEAR TIE IAW SRM 51-31-00. FABRICATED NEW SHEAR TIE IAW REF DWG AGA7016. HEAT TREATED TO 7075T6, INSTALLED NEW SHEAR TIE IAW SRM 51-00-01.
Part: SHEAR TIE — CRACKED (BS 1902) · airframe 78,221 hrs · 27,490 cycles
DURING C-CHECK, FOUND A CRACK ON SHEAR TIE AT AFT CARGO BAY BS 1902, S43R. REMOVED SHEAR TIE S41-47R, FABRICATED NEW SHEAR TIE IAW REF DWG AGA7017. HEAT TREATED TO T6. INSTALLED NEW SHEAR TIE IAW SRM 51-00-01.
2011
Part: OXYGEN MASK — DAMAGED (COCKPIT) · airframe 76,857 hrs · 26,758 cycles
F/O'S 02 MASK BROKE UPON REMOVAL FROM IN FLIGHT USE. REPLACED F/O OXYGEN MASH AND STORAGE BOX THAT WAS FOUND BROKEN IAW 35-13-3 AMD 35-13-04-4-0.
2010
Part: CONTROLLER — FAILED (HYD SYSTEM) · airframe 76,044 hrs · 26,338 cycles
DURING CLIMB RECIEVED A LEVEL NR3 HYD PUMP OFF ,10 MIN LATER LEVEL 1 HYD 3 OFF , TEMP WENT TO 104C. ACFT PERFORMED AIR TURNBACK. HSC LAST LEG FAULTED 3R PUMP, THEN 11 MINUTES LATER 3L PUMP , THEN HSC FAULT AFTER BOTH PUMPS OFF. INSPECTED FILTER BY-PASS INDICATORS ON ENGINE AND ON MANIFOLD. ALL INDICATE NORMAL. INTERROGATED MCDU FOR HSC NR3 ENG FAULTS. FOUND LEG1, 3L, 3R PUMPS OFF ALERT THEN ALL OTHER LEGS HSC. R & R HSC. RAN SYS 1,2,3 WITH AUX PUMPS ALL INDICATIONS OK. RAN ENGINES 1 AND 3 IDLE RUN AND SWITCHED LT AND RT PUMPS ON/OFF. ALL INDICATIONS CORRECT. RTS TEST OK. NO FAULTS. RETURN TO SERVICE.
Part: SKIN — DELAMINATED (NR 2 SPOILER) · airframe 75,748 hrs · 26,174 cycles
LT WING NR 2 SPOILER UPPER SURFACE IS DELAMINATED. REPAIRED THE LT WING NR 2 SPOILER PN NRC 6048-503N; SN MTM-368 BY FABRICATING AND BONDING SKINS; DOUBLERS; TRIPPLERS; RIBS; CORE AND FITTING CLOSE OUTS IAW SRM 57-10-00, VOL I.
Part: SUPPORT — CRACKED (FUSELAGE) · airframe 75,748 hrs · 26,174 cycles
2 HOLES REAMED IAW EO 8-5340-7-3305 PART 3, STEP 8-B. INDICATED CRACKED WITH EDDY CURRENT. LT SIDE X=41.76; Y=2122.881. HOLES ARE LOWEST (2) HOLES COMMON TO THE UPPER TORQUE BOX. SECONDARY SUPPORT AND ANGLE AJC7616-1. BOTH CIRCLES IN RED ON SECONDARY SUPPORT.
Part: FLOOR PANEL — CORRODED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
FWD PIT FLOOR PANEL 123 ND IS CORRODED AND BROKEN. REPAIRED FWD PIT FLOOR PANEL 123 ND BY FABRICATING A NEW FLOOR PANEL USING THE OLD FLOOR PANEL AS A TEMPLATE IAW DWG SRZ 25-005, REV "H".
Part: HINGE FITTING — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 75,748 hrs · 26,174 cycles
RT WING OTBD FLAP; OTBD HINGE AT LOCATION NR 8 INBD LUG FACE IS CORRODED. REMOVED CORROSION IAW CMM 57-44-09. ACCOMPLISHED HFEC IAW NTW 51-00-17. ETCHED, ROTO-PEENED, CLEANED, CALCULATED AMP HRS, CAD PLATED AND ADHESION TESTED IAW BSOPM 20-10-02. PRIMED IAW CMM 57-44-09.
Part: HINGE FITTING — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 75,748 hrs · 26,174 cycles
RT WING OTBD FLAP; OTBD HINGE AT LOCATION NR 8 INBD LUG FACE IS CORRODED. REMOVED CORROSION IAW CMM 57-44-09. ACCOMPLISHED HFEC IAW NTW 51-00-17. ETCHED, ROTO-PEENED, CLEANED, CALCULATED AMP HRS, CAD PLATED AND ADHESION TESTED IAW BSOPM 20-10-02. PRIMED IAW CMM 57-44-09.
Part: FAIRING — CRACKED (NR 3 PYLON) · airframe 75,748 hrs · 26,174 cycles
NR 3 PYLON PANEL 488 CL IS CRACKED AT THE EDGE OF THE HINGE CUTOUT. FABRICATED REPAIR DOUBLER IAW SRM 54-00- 01, FIG 2-B, SHEET 2, VOL I. INSTALLED REPAIR DOUBLER IAW SRM 54-00-01, FIG 2-B, SHEET 2, VOL I.
Part: RIB — CHAFED (NR 6 SLAT TRACK) · airframe 75,748 hrs · 26,174 cycles
RT WING NR 6 SLAT TRACK OTBD CLOSURE RIB IS CHAFED AT 2 LOCATIONS BY THE TRACK FWD OF THE FWD UPPER ROLLER. ACCOMPLISHED EA 8-5720-123350.
Part: FITTING — CORRODED (LT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
LT WING - OTBD FLAP; OTBD HINGE; LOAD SIDE FITTING INBD BARREL NUT BOLE HAS SURFACE CORROSION. REMOVED DAMAGED -3 SIDE LOAD FITTING AND REPLACED WITH A NEW -3 FITTING IAW SRM 51-31-01, VOL II. ALODINED AND PRIMED NEW FITTING IAW SRM 51-21-01, VOL II.
Part: FITTING — CORRODED (RT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
RT OTBD FLAP; INBD HINGE FITTINGS AND LUGS HAVE SEVERAL AREAS OF BARE METAL IS CORRODED. PRIMED BARE AREAS IAW SOPM 20-11-02.
Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
LOWER CTR CARGO FLOOR PANEL NR 183 QF HAS AN INSERT BROKEN OUT. FABRICATED NEW LOWER CTR CARGO FLOOR PANEL 183 QF IAW DWG SRZ 25-005, REV "H".
Part: FITTING — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 75,748 hrs · 26,174 cycles
RT OTBD FLAP; INBD HINGE LOCATION NR 4 OTBD LUG FACE IS CORRODED. VERIFIED THICKNESS AND REMOVED CORROSION IAW CMM 57-44-08. ETCHED; CLEANED; CALCULATED AMP-HRS; PREPPED; CAD PLATED AND ADHESION TESTED IAW BSOPM 20-10- 02. PRIMED IAW CMM 57-44-08.
Part: STRUCTURE — WORN (NR 2 PYLON) · airframe 75,748 hrs · 26,174 cycles
NR 2 ENG PYLON PANEL 457 CL UPPER LATCH CONTACT AREA IS WORN. REPAIRED AREA IAW SRM 54-32-01, VOL III AND SRM 51-35-01, VOL II. ALODINED AND PRIMED REPAIR IAW SRM 51-21-01, VOL II. WORK WAS COMPLETED IAW DWG AUB 7332.
Part: LUG — CORRODED (LT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
LT OTBD FLAP; OTBD HINGE LOCATION NR 3 OTBD LUG FACE OUTER SURFACE IS CORRODED. REPAIRED NR3 LOCATION LUG FACE IAW CMM 57-44-09.
Part: FLOOR PANEL — DAMAGED (BS 570) · airframe 75,748 hrs · 26,174 cycles
MAIN CABIN FLOOR PANEL AT BS 570; LBL 75 HAS A SOFT SPOT. FABRICATED MAIN CABIN FLOOR PANEL AT BS 570 / LBL 75 IAW DWG SRZ 25-005, REV "H" INSTALLED FABRICATED FLOOR PANEL AT BS 570; LBL 75 IAW SRM 51-31-01, VOL II AND AMM 53-21-08-2.
Part: FITTING — CORRODED (LT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
LT OTBD FLAP; OTBD HINGE LOCATION NR 3 INBD BORE IS CORRODED. VERIFIED BORE SIZE AND REMOVED CORROSION IAW CMM 57-44-09. ROTO-PEENED; ETCHED; CALCULATED AMP-HRS; CAD PLATED AND ADHESION TESTED IAW BSOP 20-10-02. PRIMED IAW CMM 57-44-09.
Part: FITTING — CORRODED (LT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
LT OTBD FLAP; INBD HINGE LOCATION NR 4 BORE IS CORRODED. REMOVED BUSHING. VERIFIED BORE DIAMETER. REMOVED CORROSION. ETCHED BORE. FLAP-PEENED BORE. CAD PLATED BORE. PRIMED BORE. MATERIAL ID FOR REPAIR BUSHING. MACHINED REPLACEMENT BUSHING. CAD PLATED REPLACEMENT BUSHING. INSTALLED BUSHING. MACHINED BUSHING TO FINAL DIAMETER IAW CMM 57-44-08, REP 1-1.
Part: FITTING — CORRODED (LT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
LT OTBD FLAP; INBD HINGE LOCATION SIDE LOAD FITTING MOUNTING SURFACE IS CORRODED. REPAIRED SIDE LOAD FITTING MOUNTING SURFACE IAW CMM 57-44-08.
Part: FITTING — CORRODED (RT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
RT OTBD FLAP; OTBD HINGE LOCATION NR 7 SIDE LOAD FITTING MOUNTING SURFACE IS CORRODED. REPAIRED IAW CMM 57-44-09. VERIFIED LUG THICKNESS. REMOVED CORROSION. ETCHED SURFACE. ROTO-PEENED SURFACE. CAD PLATED SURFACE. PRIMED SURFACE. MATERIAL ID FOR SHIM. MACHINED SHIM. PRIMED SHIM AND BONDED SHIM.
Part: FITTING — CORRODED (LT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
LT OTBD FLAP; OTBD HINGE LOCATION NR3 MOUNTING SURFACE IS CORRODED. VERIFIED LUG THICKNESS AND REMOVED CORROSION IAW CMM 57-44-09. ETCHED; FLAP- PEENED; CLEANED; CALCULATED AMP-HRS; CAD PLATED AND ADHESION TESTED IAW BSOPM 20-10-01. PRIMED SURFACE; MATERIAL ID SHIM; MACHINED SHIM; PRIMED SHIM AND ATTACHED SHIM IAW CMM 57-44-09.
Part: FITTING — CORRODED (RT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
RT OTBD FLAP; INBD LOCATION NR 4 INBD LUG FACE IS CORRODED. VERIFIED LUG THICKNESS AND REMOVED CORROSION IAW BAC CMM 57-44-08. ETCHED; ROTO- PEENED; CLEANED; CALCULATED AMP-HRS; PREPPED; CAD PLATED AND ADHESION TESTED IAW BSOPM 20-10-02. PRIMED IAW CMM 57-44-08.
Part: FITTING — CORRODED (LT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
LT OTBD FLAP; INBD HINGE LOCATION NR 4 OTBD LUG FACE IS CORRODED. REPAIRED NR 4 LUG FACE IAW CMM 57-44-08.
Part: FITTING — CORRODED (LT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
LT WING OTBD FLAP; OTBD HINGE LOCATION NR 7 BORES (2 EA) ARE CORRODED INSIDE. REMOVED CORROSION FROM BORES. BORE FOUND TO BE WITHIN LIMITS. ETCHED BORES. CAD PLATED BORES. PRIMED BORES IAW CMM 57-44-09.
Part: FITTING — CORRODED (LT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
LT OTBD FLAP; OTBD HINGE LOCATION NR 7 SIDE LOAD FITTING MOUNTING SURFACE IS CORRODED. VERIFIED LUG THICKNESS. REMOVED CORROSION; ETCHED; ROTO-PEENED; CAD PLATED; PRIMED SURFACE. MATERIAL ID FOR REPAIR SHIM; MACHINED REPAIR SHIM; PRIMED REPAIR SHIM AND BONDED REPAIR SHIM IAW BAC CMM 57-44-09, REP 1-1.
Part: FITTING — CORRODED (ZONE 600) · corrosion level 2 · airframe 75,748 hrs · 26,174 cycles
RT OTBD FLAP; OTBD HINGE LOCATION NR 5 OTBD LUG FACE IS CORRODED. REMOVED CORROSION IAW 57-44-09. ACOMPLISHED HFEC IAW NTW 51-00-17. ETCHED; ROTO- PEENED; CLEANED; CALCULATED AMP-HRS; CAD PLATED AND ADHESION TESTED IAW BSOPM 20-10-02. PRIMED IAW CMM 57-44-09.
Part: FITTING — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 75,748 hrs · 26,174 cycles
RT OTBD FLAP; INBD LOCATION NR 2 MOUNTING SURFACE IS CORRODED. REMOVED CORROSION AND SOLD LIMITS IAW CMM 57-44-08. ETCHED; FLAP-PEENED; CLEANED; CAD PLATED AND ADHESION TESTED IAW BSOPM 20-11-01 AND BSOPM 20-10-02. PRIMED SURFACE; MATERIAL ID FOR SHIM; FABRICATED; PRIMED AND INSTALLED SHIM IAW CMM 57-44-08.
Part: STRUCTURE — CORRODED (RT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
RT OTBD FLAP; INBD HINGE BARREL NUT HOLE IS CORRODED. REPAIRED BARREL NUT HOLE IAW CMM 57-44-08.
Part: FITTING — CORRODED (RT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
RT OTBD FLAP; OTBD HINGE LOCATION NR 2 JUST AFT OF MOUNTING SURFACE IS CORRODED. REMOVED CORROSION AND ETCHED IAW BAC CMM 57-44-09. FLAP-PEENED; CALCULATED AMP-HRS; CAD PLATED AND ADHESION TESTED IAW BSOP 20-10-02. PRIMED IAW CMM 57- 44-09.
Part: FITTING — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 75,748 hrs · 26,174 cycles
RT OTBD FLAP; OTBD HINGE LOCATION NR 3 OTBD LUG FITTING IS CORRODED. REMOVED COROSION AND ACID ETCHED IAW CMM 57-44-09. ROTO-PEENED; CLEANED; CALCULATED AMP-HRS; CAD PLATED AND ADHESION TESTED IAW BSOP 20-10-02. PRIMED SURFACE IAW CMM 57-44-09.
Part: FITTING — CORRODED (LT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
LT OTBD FLAP; INBD HINGE LOCATION NR 3 MOUNTING SURFACE IS CORRODED. REMOVED CORROSION AND SOLD LIMITS IAW CMM 57-44-08. ETCHED; FLAP PEENED; CLEANED; CADMIUM PLATED AND ADHESION TESTED IAW BSOP 20-11-01. AND BSOP 20-10-02. PRIMED SURFACE; MATERIAL ID SHIMS; FABRICATED; PRIMED AND INSTALLED SHIMS IAW CMM 57-44-08.
Part: FITTING — CORRODED (LT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
LT OTBD FLAP; INBD HINGE; INBD BARREL NUT HOLE IS CORRODED. REPAIRED BARREL NUT HOLE IAW CMM 57-44-08.
Part: FITTING — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 75,748 hrs · 26,174 cycles
RT OTBD FLAP; INBD LOCATION NR 3 MOUNTING SURFACE IS CORRODED. REMOVED CORROSION AND SOLD LIMITS IAW CMM 57-44-08. ETCHED; FLAP-PEENED; CLEANED; CAD PLATED AND ADHESION TESTED IAW BSOPM 20-11-01 AND BSOPM 20-10-02. PRIMED SURFACE; MATERIAL ID FOR SHIMS; FABRICATED; PRIMED AND INSTALLED SHIMS IAW CMM 57-44-08.
Part: FITTING — CRACKED (RT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
RT OTBD FLAP; OTBD HINGE LOCATION NR 2 BORE HAS CRACK INDICATION. REMOVED CRACK INDICATION IAW CMM 57-44-09. ACCOMPLISHED HFEC IAW NTW 51-00-17. ETCHED AND ROTO-PEENED BORE; CALCULATED AMP-HRS; CAD PLATED AND ADHESION TESTED BORE IAW BSOPM 20-10-01. PRIMED BORE IAW CMM 57-44-09.
Part: PANEL — WORN (NR 2 NACELLE) · airframe 75,748 hrs · 26,174 cycles
NR 2 ENG PYLON PANEL 457 CL LOWER LATCH CONTACT AREA IS WORN. INTERNAL DOUBLER BEING REPLACED ON NON-ROUTINE N00442. NO FURTHER MX REQUIRED , COPY ATTACHED. ALSO SEE SDR TRACKING NR 10-1226.
Part: FITTING — CORRODED (RT WING TE FLAP) · airframe 75,748 hrs · 26,174 cycles
RT OTBD FLAP; OTBD HINGE LOCATION NR 3 MOUNTING SURFACE IS CORRODED. REPAIRD IAW CMM 57-44-09. VERIFIED LUG THICKNESS. REMOVED CORROSION. ETCHED SURFACE. ROTO-PEENED SURFACE. FLAP PEENED SURFACE. CAD PLATED SURFACE. MATERIAL ID FOR SHIM. MACHINED SHIM. PRIMED SHIM AND BONDED SHIM.
Part: SHEAR TIE — CORRODED (ZONE 100) · corrosion level 2 · airframe 75,748 hrs · 26,174 cycles
CTR PIT SHEAR TIE IS CORRODED AT FS 1661; LONGERON 48R. REMOVED SHEAR TIE REF SRM 51-31-01, VOL II. REMOVED CORROSION WITH 100 PERCENT MATERIAL LOSS AND IS OUT OF LIMITS REF 53-00-01, VOL I. FABBED NEW SHEAR TIE REF DAC DWG ADA 3677, REV "B". ALODINED, PRIMED AND PAINTED REF 51-21-01, VOL II. PART MARKED REF GMM 7-0-1001. INSTALLED REF SRM 51-33-01, VOL II.
Part: HINGE — CORRODED (CARGO DOOR) · corrosion level 2 · airframe 75,748 hrs · 26,174 cycles
CTR CARGO DOOR HINGE HAS RUST. CHECKED HINGE FOUND ALL 5 SECTIONS TO BE OUT OF LIMITS REF SRM 52-10-00, VOL I. REMOVED HINGE FROM CTR CARGO DOOR REF SRM 51-31-01, VOL II. REMOVED LINER IAW AMM 52-32-02-2. RECEIVED 5 EA DOOR HINGE SECTIONS. INSTALLED 5 EA DOOR HINGE SECTIONS IAW SRM 51-31-10, VOL II. PRIMED. TOP COATED IAW SRM 51-21-01, VOL II. INSTALLED LINER IAW AMM 52-32-02-2.
Part: SHEAR TIE — CORRODED (ZONE 100) · corrosion level 2 · airframe 75,748 hrs · 26,174 cycles
FWD CARGO COMPARTMENT BILGE AREA HAS CORROSION ON A FRAME AT BS 879 BETWEEN STRINGER 47L AND STRINGER 48L. REMOVED CORROSION ON SHEAR CLIP REF SRM 51-21-02, VOL II. ORIGINAL THICKNESS 0.071 REF SRM 53-13-01, VOL I. MATERIAL REMOVED 0.040. MATERIAL REMAINING 0.031, FOUND TO BE OUT OF LIMITS. R & R SHEAR CLIP REF SRM 51-33-01 AND SRM 51-41-01, VOL II.
Part: SHEAR TIE — CORRODED (ZONE 100) · corrosion level 2 · airframe 75,748 hrs · 26,174 cycles
CTR PIT SUMP AREA SHEAR TIE CLIP IS CORRODED AT FS 1712; LONGERON 48R. REMOVED SHEAR TIE IN THE CTR PIT FS 1712, DAC DWG AFA 3901, REV F. RECEIVED HEAT TREATED PART TRACKING NR 2010-0149, PO NR 680560. FABBED LOCATED AND DRLLED UP IAW SRM 53-30-00, FIG 10, VOL I. ALODINED IAW SRM 51-21-01, PARA 31, VOL II. PRIMED IAW SRM 51-21-01, PARA 24, VOL II. PAINTED IAW SRM 51-21-07, VOL II. INSTALLED IAW SRM 51-33-01, VOL II.
Part: HINGE — WORN (CARGO DOOR) · airframe 75,748 hrs · 26,174 cycles
FWD CARGO DOOR; FWD HINGE LOBE ON THE DOOR IS OUT OF LIMITS AT 0.346. REAMED HOLE IN DOOR HINGE LOBE, FABRICATED BUSHING AND INSTALLED IAW SRM 52-10-00, VOL I AND SRM 51-39-01, VOL I.
Part: STRINGER — CORRODED (BS 1219-1239) · airframe 75,748 hrs · 26,174 cycles
STRINGER AFT END IS CORRODED FROM BS 1219 TO 1239 STR 20L. CORROSION ON ORIGINAL STRINGER WAS FOUND OUT OF LIMITS IAW SRM 53-00- 01, PG 8; VOL I. MACHINED NEW STRINGER IAW DAC DWG NR AEA0355, REV "B". ALODINED AND PRIMED IAW SRM 51-21-01, VOL II. INSTALLED NEW STRINGER IAW SRM 51-31-01, VOL II.
Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 75,748 hrs · 26,174 cycles
MAIN CABIN FLOOR PANEL HAS A SOFT SPOT AT BS 900/ LBL 48. FABRICATED MAIN CABIN FLOOR PANEL AT BS 900/ LBL 48 IAW DWG SRZ 25-005, REV "H". INSTALLED FLOOR PANEL AT BS 900; LBL 48 IAW SRM 51-31-01, VOL II AND AMM 53-21-08-2.
Part: STRINGER — CORRODED (BS 1341-1361) · airframe 75,748 hrs · 26,174 cycles
STRINGER IS CORRODED IN SEVERAL PLACES FROM BS 1341 TO 1361; STR 20L. CORROSION ON ORIGINAL STRINGER WAS FOUND OUT OF LIMITS IAW SRM 53-00-01, PG 8; VOL I. MACHINED NEW STRINGER IAW DAC DWG NR AEA 0163, REV "C". ALODINED AND PRIMED IAW SRM 51-21-01, VOL II. INSTALLED NEW STRINGER IAW SRM 51-31-01, VOL II.
Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 75,748 hrs · 26,174 cycles
MAIN CABIN FLOOR PANEL HAS A SOFT SPOT AT BS 1120/ LBL 48. FABRICATED MAIN CABIN FLOOR PANEL AT BS 1120/ LBL 48 IAW DWG SRZ 25-005, REV "H". INSTALLED FLOOR PANEL AT BS 1120; LBL 48 IAW SRM 51-31-01, VOL II AND AMM 5321-08-2.
Part: LONGERON — CORRODED (ZONE 200) · airframe 75,748 hrs · 26,174 cycles
MAIN CABIN INTERIOR LONGERON IS CORRODED FROM BS 1381 TO BS 1401; LONGERON 17L TO LONGERON 17L. REMOVED CORROSION IAW SRM 53-00-01, VOL I. ORIGINAL MATERIAL THICKNESS 0.135. REMOVED MATERIAL 0.020. REMAINING MATERIAL THICKNESS 0.115 AND FOUND TO BE WITHIN LIMITS IAW SRM 53-00-01, VOL I. ALODINED AND PRIMED IAW SRM 51-21-01, VOL II. REMOVED AND INSTALLED 2 EA RIVETS IAW SRM 51-35-01, VOL II.
Part: FITTING — LOOSE (NR 1 PYLON) · airframe 75,748 hrs · 26,174 cycles
NR 1 PYLON AFT BULKHEAD FITTING 6TH FASTENER FROM THE INBD SIDE UNDER THE CLEVIS IS LOOSE. COMPLIED WITH EA 8-5450-136646; REV "A"; "PYLONS - PYLON STRUCTURE - NR1 PYLON AFT BULKHEAD FASTENERS INSP".
Part: LONGERON — CORRODED (ZONE 200) · airframe 75,748 hrs · 26,174 cycles
MAIN CABIN INTERNAL LONGERON IS CORRODED FROM BS 1401 TO BS 1421; LONGERON 17R REMOVED 2 EA FASTENERS; REMOVED CORROSION IAW SRM 53-00-01, PG 8, VOL I. REMOVED 0.020 IAW UT GAUGE T8225I DATE 8/3/10. FOUND TO BE WITHIN LIMITS IAW SRM 53-00-01, PG 8, VOL I. ALODINED AND PRIMED IAW SRM 51-21- 01, VOL II. REINSTALLED REMOVED FASTENERS IAW SRM 51-35-01, VOL II, PRIMED AREA.
Part: BEAM — CRACKED (ZONE 200) · airframe 75,748 hrs · 26,174 cycles
MCD SPOOLS -NR 2 SPOOL HAS CRACK INDICATIONS AT C HOLE. REAMED HOLE "C" TO 0.520 ' IAW SRM 53-50-00, FIG 17, VOL I. NO CRACKS NOTED. FABRICATED AND INSTALLED BUSHING IAW SRM 53-50-00, FIG 17, VOL I.
Part: BEAM — CRACKED (ZONE 200) · airframe 75,748 hrs · 26,174 cycles
MCD SPOOLS - NR 1 SPOOL HAS CRACK INDICATIONS AT C & D HOLES. REAMED HOLES "C" AND "D" TO 0.520 ' IAW SRM 53-50-00, FIG 17, VOL I. NO CRACKS NOTED. FABRICATED AND INSTALLED BUSHING IAW SRM 53-50-00, FIG 17, VOL I.
Part: BEAM — CRACKED (ZONE 100) · airframe 75,748 hrs · 26,174 cycles
MCD SPOOLS - NR 3 SPOOL HAS CRACK INDICATIONS AT HOLES C & D. REAMED HOLES "C" AND "D" TO 0.520 ' IAW SRM 53-50-00, FIG 17, VOL I. NO CRACKS NOTED. FABRICATED AND INSTALLED BUSHINGS IAW SRM 53-50-00, FIG 17, VOL I.
Part: BEAM — CRACKED (ZONE 200) · airframe 75,748 hrs · 26,174 cycles
MCD SPOOLS - NR 4 SPOOL HAS CRACK INDICATIONS AT HOLES C & D. REAMED HOLE "C" TO 0.520 ", HOLE "D" TO 0.460" IAW SRM 53-50-00, FIG 17, VOL I. NO CRACKS NOTED. FABRICATED AND INSTALLED BUSHING FOR HOLE "C" IAW SRM 53-50-00, FIG 17, VOL I. NO BUSHING REQUIRED FOR HOLE "D".
Part: SPOOL — CRACKED (CARGO DOOR) · airframe 75,747 hrs · 26,174 cycles
MCD SPOOLS - NR 7 SPOOL LOCATION HAS CRACK INDICATIONS AT A, B, C & D HOLES. REAMED HOLES "A", "B" , "C" AND "D" TO 0.520" IAW SRM 53-50-00, FIG 17, VOL I. FABRICATED AND INSTALLED BUSHINGS IN HOLES "A", "B", "C", "D" IAW SRM 53-50-00, FIG 17, VOL I. REMOVED AND REPLACED SPOOL BACK UP FITTING PN AFA 7132-1 IAW SRM 51-31-01, VOL II.
Part: FITTING — CRACKED (ZONE 200) · airframe 75,748 hrs · 26,174 cycles
MCD SPOOLS - NR 5 SPOOL LOCATION HAS CRACK INDICATIONS AT A, C & D LOCATIONS. REAMED HOLES "A", "C" AND "D" TO 0.520" IAW SRM 53-50-00, FIG 17, VOL I. FABRICATED AND INSTALLED BUSHINGS IN HOLES "A", "C" AND "D" IAW SRM 53-50-00, FIG 17, VOL I. R & R SPOOL BACK UP FITTING PN AFA 7132-1 IAW SRM 51-31-01, VOL II.
Part: SKIN — GOUGED (RT WING AILERON) · airframe 75,748 hrs · 26,174 cycles
RT WING INBD AILERON, UPPER INBD EDGE IS WORN AND GOUGED. CHECKED LIMITS AND FOUND TO BE OUT OF LIMITS (ORIGINAL 0.040; REMAINING 0.022 IAW SRM 57-00-01, VOL I. REMOVED SKIN PANEL IAW SRM 51-35-01, VOL II. FABRICATED SKIN PANEL IAW DWG ARC 1316, REV "C". PERFORMED PENETRANT INSP IAW BSOPM 20-20-02. NO DEFECTS NOTED. PRIMED IAW SRM 51-21-01, VOL II. INSTALLED SKIN PANEL IAW SRM 51-35-01, VOL II AND DWG ARC 1316, REV "C".
Part: FITTING — CRACKED (ZONE 200) · airframe 75,748 hrs · 26,174 cycles
MCD SPOOLS - NR 6 SPOOL LOCATION HAS CRACK INDICATIONS AT A, C & D LOCATIONS. REAMED HOLES "A", "C" AND "D" TO 0.520" IAW SRM 53-50-00, FIG 17, VOL I. HOLE "A" STILL SHOWS CRACK INDICATION IN THE SPOOL BACK UP FITTING. R & R SPOOL BACK UP FITTING PN AFA 7132-1 IAW SRM 51-31-01, VOL II. FABRICATED AND INSTALLED BUSHINGS IN WEBS ONLY AT HOLES "A", "C" AND "D" IAW SRM 53-50-00, FIG 17, VOL I.
Part: FLOORBOARD — DELAMINATED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
CTR CARGO COMPARTMENT BALLMAT AREA FLOORBOARD IS DELAMINATED. FABRICATED CTR CARGO FLOOR PANEL 183 PF IAW DWG SRZ 25-005, REV "H".
Part: FLOOR PANEL — CRACKED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
FWD CARGO PIT FLOOR PANEL NO. 123 XF HAS CRACK DAMAGE. FABRICATED NEW FWD CARGO PIT FLOOR PANEL 123 XF IAW DWG SRZ 25-005, REV "H".
Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
FWD CARGO PIT FLOOR PANEL NR 123 JF HAS DAMAGED INSERT. FABRICATED NEW FWD CARGO PIT FLOOR PANEL 123 JF IAW DWG SRZ 25-005, REV "H".
Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
FWD CARGO PIT FLOOR PANEL NR 123 QF HAS DAMAGED INSERT. FABRICATED NEW FWD CARGO PIT FLOOR PANEL 123 QF IAW DWG SRZ 25-005, REV "H".
Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
FWD CARGO PIT FLOOR PANEL NR 123 QD HAS DAMAGED INSERT. FABRICATED NEW FWD CARGO PIT FLOOR PANEL 123 QD, IAW DWG SRZ 25-005, REV "H".
Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
FWD CARGO PIT FLOOR PANEL NR 123 LF HAS DAMAGED INSERTS. FABRICATED NEW FWD CARGO PIT FLOOR PANEL 123 LF IAW DWG SRZ 25-005, REV "H".
Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
FWD CARGO PIT FLOOR PANEL NR 123 GF HAS DAMAGED INSERTS. FABRICATED NEW FWD CARGO PIT FLOOR PANEL 123 GF IAW DWG SRZ 25-005, REV "H".
Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
FWD CARGO PIT FLOOR PANEL NR 123 FD HAS DAMAGED INSERTS. FABRICATED NEW FWD CARGO PIT FLOOR PANEL 123 FD IAW DWG SRZ 25-005, REV "H".
Part: FLOOR PANEL — CRACKED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
FWD CARGO PIT FLOOR PANEL NR 123 WF HAS CRACK DAMAGE. FABRICATED NEW FWD CARGO FLOOR PANEL 123 WF IAW DWG SRZ 25-005, REV "H".
Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
FWD CARGO PIT FLOOR PANEL NR 123 DD HAS DAMAGED INSERTS. FABRICATED NEW FWD CARGO PIT FLOOR PANEL 123 DD IAW DWG SRZ 25-005, REV "H".
Part: SUPPORT — CRACKED (LT WING) · airframe 75,748 hrs · 26,174 cycles
LT WING L/E PANEL SUPPORT IS CRACKED AT WING STA XFS 455. REMOVED CRACKED SUPPORT AND INSTALLED NEW SUPPORT IAW SRM 51-35-01, PG 1, VOL II; SRM 51-33-01, PG 1, VOL II AND DAC DWG ARB 1162, REV "S". RECEIVED MATERIAL ID 7075-0 0.050 IAW DAC DWG ARB 1162, REV "S". FORMED NEW SUPPORT IAW DAC DWG ARB 1162, REV "S". RECEIVED HEAT TREATED NEW SUPPORT 7075-T6 TRACKING NR 2010-0144, PO NR 680183. FABRICATED NEW SUPPORT IAW DAC DWG ARB 1162, REV "S". APPLIED ALODINE AND PRIMER IAW SRM 51-21-01, PG 1, VOL II.
Part: RIB — CRACKED (LT WING) · airframe 75,748 hrs · 26,174 cycles
LEFT WING LEADING EDGE PANEL SUPPORT IS CRACKED. REMOVED DAMAGE BY CUT OUT IAW SRM 57-00-01, FIG 10, VOL I. FABRICATED REPAIR FILLER AND DOUBLER IAW SRM 57-00-01, FIG 10, VOL I. ALODINED AND PRIMED IAW SRM 51-1-01, VOL II. INSTALLED REPAIR FILLER AND DOUBLER IAW SRM 57-00-01, FIG 10, VOL I.
Part: FORMER — CRACKED (LT WING) · airframe 75,748 hrs · 26,174 cycles
LT WING L/E PANEL SUPPORT IS CRACKED AT WING STA XORS 770. REMOVED FORMER IAW SRM 51-33-01, VOL II. FABRICATED NEW -21 FORMER IAW DAC DWG ARB 1164, REV "M". ALODINED AND PRIMED IAW SRM 51-21-01, VOL II. INSTALLED -21 FORMER IAW SRM 51-33-01, VOL II AND DAC DWG ARB 1164, REV "M". PART MARKED IAW GMM 7-1-1001.
Part: FLOORBOARD — DELAMINATED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
AFT CARGO COMPARTMENT FLOORBOARD 187 FF IS DELAMINATED AND DENTED AT SEVERAL LOCATIONS. FABRICATED NEW AFT CARGO FLOOR PANEL 187 FF IAW DWG SRZ 25-005, REV "H" AND DWG SRZ 25-011, REV "C".
Part: FLOORBOARD — DELAMINATED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
AFT CARGO COMPARTMENT FLOORBOARD 187 FF IS DELAMINATED AND DENTED AT SEVERAL LOCATIONS. FABRICATED NEW AFT CARGO FLOOR PANEL 187 FF IAW DWG SRZ 25-005, REV "H" AND DWG SRZ 25-011, REV "C".
Part: FLOORBOARD — DELAMINATED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
AFT CARGO COMPARTMENT FLOORBOARD 187 HF IS DELAMINATED AND DENTED AT SEVERAL LOCATIONS. FABRICATED NEW AFT CARGO FLOOR PANEL, 187 HF IAW DWG SRZ 25-005, REV "H" AND DWG SRZ 25-011, REV "C".
Part: FLOORBOARD — DELAMINATED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
AFT CARGO COMPARTMENT FLOORBOARD 187 CF IS DELAMINATED AND DENTED AT SEVERAL LOCATIONS. FABRICATED NEW AFT CARGO FLOOR PANEL 187 CF IAW DWG SRZ 25-005, REV "H" AND DWG SRZ 25-011, REV "C".
Part: FLOORBOARD — DELAMINATED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
AFT CARGO COMPARTMENT FLOORBOARD 187 AF IS DELAMINATED AND DENTED AT SEVERAL LOCATIONS. FABRICATED NEW AFT CARGO FLOOR PANEL, 187 AF, IAW DWG SRZ 25-005, REV "H" AND DWG SRZ 25-011, REV "C".
Part: FLOORBOARD — DELAMINATED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
AFT CARGO COMPARTMENT FLOORBOARD 187 EF IS DELAMINATED AND DENTED AT SEVERAL LOCATIONS. FABRICATED NEW AFT CARGO FLOORBOARD, 187 EF, IAW DWG SRZ 25-005, REV "H" AND DWG SRZ 25-011, REV "C".
Part: FLOORBOARD — DELAMINATED (CARGO BAY) · airframe 75,748 hrs · 26,174 cycles
AFT CARGO COMPARTMENT FLOORBOARD 187 GF IS DELAMINATED AND DENTED AT SEVERAL LOCATIONS. FABRICATED NEW AFT CARGO FLOOR PANEL 187 GF IAW DWG SRZ 25-005, REV "H" AND DWG SRZ 25-011, REV "C".
2009
Part: INTERCOSTAL — CORRODED (ZONE 700) · corrosion level 3 · airframe 75,185 hrs · 25,906 cycles
RT MLG W/W, CORROSION AT STA 1368.650. REPLACED INTERCOSTAL REF SRM 51-31-01.
Part: SENSOR — MALFUNCTIONED (TAT PROBE HEAT) · airframe 75,106 hrs · 25,858 cycles
AFTER T/O, RECEIVED LEVEL ONE "TAT PROBE HEAT" ALERT. RETURNED TO ELP PER GOCC REQUEST. PERFORMED RTS ON MSC. RTS PASSED NO FAULTS IN FAULT HISTORY OR CURRENT FAULTS. PERFORMED ADJ TEST PER AMM 30-30-02-5 PROBE HEATER WORKS, BUT WHEN BREAKER IS PULLED TAT PROBE HEAT ALERT DOES NOT SHOW. CHECKED WIRING PER WDM 30-30-01 MSC RACK TO PROBE BACK TO RACK WIRING CHECKED GOOD. CK CONTINUITY ON PROBE (23 OHMS). CHECKED PROBE TO ACFT GROUND CK GOOD. SUSPECT BAD MSC.
2008
Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 72,715 hrs · 24,720 cycles
MCD SEAT TRACK RBL 27 STA 755 HAS A LOBE GOUGED. BLENDED DAMAGE FOUND TO BE OUT OF LIMITS IAW SRM 53-70-00. REMOVED AND INSTALLED NEW TRACK IAW SRM 53-70-00. NEW TRACK AND SPLICE FABBED ON TRAVELER T8/733018 AND T8/733020. REMOVED AND REINSTALLED AND SEALED FLOOR PANELS IAW MM 53-21-08-2. REPAIR CLASSIFIED AS A MAJOR REPAIR.
Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 72,715 hrs · 24,720 cycles
MCD SEAT TRACK RBL 77 BETWEEN STA 840 TO 920 IS IN BARE METAL AND SUPERFICAL CORROSION. REMOVED LIGHT CORROSION FOUND TO BE OUT OF LIMITS IAW SRM 53-70-00. REMOVED AND INSTALLED NEW TRACK IAW SRM 53-70-00. FABBED NEW TRACK AND SPLICE ON TRAVELERS T8/733283 AND T8/733215. CLASSIFIED AS MAJOR REPAIR.
Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 72,715 hrs · 24,720 cycles
MCD SEAT TRACK LBL 7 STA 1691 HAS TWO LOBES GOUGED BLENDED DAMAGED AREA FOUND TO BE OUT OF LIMITS IAW SRM 53-70-00. NEW TRACKED FABBED ON TRAVELER T8/732523, NEW SPLICE FABBED ON TRAVELER T8/732524. TRACK INSTALLED IAW SRM 53-70-00.
2005
Part: PANEL — CORRODED (ZONE 600) · airframe 61,821 hrs · 19,643 cycles
LT INBOARD AILERON LOWER SURFACE HAS BULGING AROUNG RIVETS, AT SEAM INBOARD EDGE TO AFT SEAM, STATION XORS 402. REMOVED DAMAGES SECTION OF SKIN AND REPAIRED LEFT INBOARD AILERON LOWER SURFACE SKIN IAW FEDEX EA 8-5710-83989, WINGS - LEFT HAND INBOARD AILERON LOWER SKIN - REPAIR, AND DAC DWG ARC1210, DC10-10 SRM 51-21-01 VOL II, 51-35-01 VCOL II, 51-35-01.
Part: SKIN — CHAFED (ZONE 500) · airframe 61,821 hrs · 19,643 cycles
LT INBOARD FLAP LOWER SKIN, INBOARD END AFT SECTION IS CHAFED. COMPLIED WITH EA 8-5710-83979 WINGS - LT INBOARD FLAP, LOWER SKIN REPLACEMENT- REPAIR.
Part: SKIN — CORRODED (ZONE 600) · airframe 61,821 hrs · 19,643 cycles
RT WING PANEL INBOARD OF OUTBOARD AILERON ISLAND ABOVE FLAP OUTBOARD TRACK HAS CORROSION AND DELAMINATION. REPAIRED TRAILING EDGE WING PANEL PART NUMBER ARC0616 IAW FEDEX EA 8-5710-83980, WINGS-RIGHTHAND UPPER SK9N, TRAILING EDGE PANEL-REPAIR.
Part: PANEL — DENTED (ZONE 500) · airframe 61,821 hrs · 19,643 cycles
LT WING, LOWER TRAILING EDGE PANEL OVER LEFT MAIN LANDING GEAR IS DENTED AND PUNCTURED. REPAIRED PANEL ARC0269 IAW EA 8-5710-8393, WINGS - LT HAND MLG FITTING TO FUSELAGE AFT UPPER PANEL - REPAIR.
Part: PANEL — DELAMINATED (ZONE 500) · airframe 61,821 hrs · 19,643 cycles
LEFT WING PANEL 541 NB HAS AREAS OF DELAMINATION. REPAIRED DELAMINATION PANEL 541NB BY FABRICATING AND BONDING NEW SKINS, DOUBLER AND CORE IAW TPS 1001 REV E AND FEDEX EA 8-5610-83986, WINGS - LEFT HAND WING PANEL 541NB- REPAIR.
Part: PANEL — DELAMINATED (ZONE 600) · airframe 61,821 hrs · 19,643 cycles
RIGHT OUTBOARD FLAP PANEL 635 HL HAS LARGE AREA OF DELAMINATION. REPAIRED IAW EA 8-5710-83085, COVER ASSY ACCESS, LOWER INBOARD FLAP, REPAIR. REFERENCE NON-ROUTINE N01042.
Part: LONGERON — CHAFED (ZONE 400) · airframe 61,821 hrs · 19,643 cycles
NUMBER 3 ENGINE INBOARD CORE CORE COWL UPPER SEAL IS CHAFFED. FOUND CORE COWL LONGERON CHAFED WHILE REMOVING CHAFE STRIP. REPAIRED LONGERON IAW FEDEX EA 8- 5410-83991, NACELLES/PYLON- NUMBER 3 ENGINE INBOARD CORE COWL UPPER LONGERON. REPAIR, REMOVED AND REPLACED CHAFE STRIP IAW DC10-10 SRM 51-21-01 VOL II. REFERENCE NON-ROUTINE N00436.
Part: PANEL — DELAMINATED (ZONE 600) · airframe 61,821 hrs · 19,643 cycles
RIGHT WING FIRE BOTTLE ACCESS PANEL TRAILING EDGE DELAMINATED. REPAIRED PANEL IAW FEDEX EA 8-5710-83990, WINGS - LEADING EDGE, ACCESS FIREX BOTTLE DOOR-REPAIR.
Part: FITTING — CRACKED (FUSELAGE) · airframe 61,821 hrs · 19,643 cycles
CRACKED LONGERON END FITTING ON LONGERON 47 RIGHT IN FRONT OF PRESSURE BULKHEAD AT FUSETAGE STATION 1129. COMPLIED WITH EA 8-5340-83987, FUSELAGE- LONGERON 47 RIGHT STATION 1129, CRACK, REPAIR. REFERENCE NON-ROUTINE N00242.
Part: SKIN — DAMAGED (T/E FLAP) · airframe 63,702 hrs · 19,643 cycles
RIGHT OUTBOARD FLAP WEDGE TOP SKIN STATION XFO 560 TO 575 HAS 3 EACH PREVIOUS REPAIRS WITH TEMPORARY FASTENERS. REMOVED DAMAGED SKIN IAW DC10 SRM 51-35-01 VOL II, FABRICATED NEW SKIN IAW DAC DWG NR ARC1953. INSTALLED SKIN IAW DC 10 SRM 51-35-01 VIL II AND FEDEX EA 8-5710-83982, WINGS RIGHT OUTBOARD FLAP WEDGE, TOP SKIN REPAIR. REFERENCE NON-ROUTINE N00341.
2004
Part: CONTROL UNIT — FAILED (ANTI SKID SYSTEM) · airframe 65,071 hrs · 21,250 cycles
ON LANDING INTO FLL, PUT THE LANDING GEAR DOWN AND RECEIVED A LEVEL 2 ALERT, (ANTI-SKID RT FAIL). PERFORMED GO-AROUND TO COMPLETE ANTI-SKID FAILED CHECKLIST. REMOVED AND REPLACED ANTI-SKID CONTROL UNIT. OPS CHECK GOOD AS PER MM CHAPTER 32-45-01-2. A/C OK FOR SERVICE.
2003
Part: ENGINE — MALFUNCTIONED (NR 3) · airframe 64,238 hrs · 20,819 cycles
NR 3 ENG HUNG DURING HIGH ALTITUDE SHUT DOWN. RELIGHT AND FAILED TO RECOVER DURING DESCENT RESULTING IN NR 3 ENG SHUT DOWN.