N301FE

Part: PULLEY — CORRODED (LT AILERONS) · airframe 78,206 hrs · 24,419 cycles

INTERMITTENTLY, THE LEFT OUTBOARD AILERON WILL NOT GO FULL DEFLECTION WHEN UNLOCKED. REMOVED AND REPLACED OB AILERON PULLEY AT WRAP AROUND FOR CABLE RUNS 7G AND 8G AND PERFORMED ADJUSTMENT/TEST IAW AMM 27-10-00-5.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 78,203 hrs · 24,415 cycles

AFT LOWER PIT STA 1841 FLOORBEAM IS CORRODED FROM LBL 20 TO RBL 20. AFTER CORROSION REMOVAL, FOUND OUT OF REPAIR LIMIT IAW SRM 53-00-01, REMOVED FLOORBEAM AND REPLACED NEW FLOORBEAM IAW SRM 51-31-01, CLASSIFIED AS MAJOR REPAIR.

Part: SEAT TRACK — GOUGED (ZONE 100) · airframe 78,203 hrs · 24,415 cycles

MAIN CARGO COMPARTMENT SEAT TRACK HAS GOUGED AREA AT F/S 1380-1400 LBL 75 REMOVED DAMAGE AREA IAW SRM 53-70-00. FABRICATED SPLICE HAT AND PLATE ON TRAVELER NR T8/740011. SEAT TRACK ON TRAVELER NR T8/740012. INSTALLED NEW SEAT TRACK, SPLICE HAT AND PLATE IAW SRM 53-70-00.

Part: SQUAT SWITCH — INACTIVE (MLG) · airframe 77,463 hrs · 24,168 cycles

AFTER T/O RAISED GEAR AND NOSE GEAR REMAINED UNSAFE, BOTH PRIMARY AND SECONDARY INDICATIONS. RAN QRH CHECKLIST, CYCLED GEAR AND GOT GOOD UP AND LOCKED INDICATIONS, SO CONTINUED ON FLIGHT. WHILE GEAR WAS UNSAFE ALSO GOT PITOT AND TAT PROBE HEAT OFF INDICATIONS, SO WEIGHT OFF WHEELS SWITCH WAS NOT ACTIVATED. REPACKED NLG STRUT REF MM 32-21-01-8. SERVICED REF 32-21-01-3. PERFORMED RETRACTION CHECK. ALL INDICATIONS CK GOOD. A/C OK FOR SERVICE.

Part: VALVE — FAILED (PNEUMATIC SYS) · airframe 77,276 hrs · 24,105 cycles

NEAR TOP OF CLIMB, NR 3 AIR SYS OFF LIGHT ILLUMINATED. NR 3 DUCT DISPLAYED RED MOMENTARILY UNTIL AUTO SHUTDOWN. DIVERTED DUE TO INABILITY TO USE WING ANTI-ICE VALVE - INOP CLOSED. DO NOT USE NR 3 PNEUMATIC SUPPLY SYSTEM." DECAY CHECK C/W PER M/M 36-00-01-5 PASS PER LIMITS CHECKED FAULT ISOLATION PANEL NO BALLS TRIP, ONLY FAULT WAS PRV. RELEASED FOR SERVICE PER MEL/CDL: 36-12-01-A CATEGORY: C EXPIRATION: 25DEC07 "MEL 36-12-01-A: NR 3 PNEUMATIC PRESS REGULATOR VALVE.

Part: CHANNEL — GOUGED (ZONE 600) · airframe 71,271 hrs · 22,060 cycles

COMPLY WITH EA8-7832-55467, EXHAUST-TR-ASSY BLENDING OF CHAFED AREA ON CLOSOUT CHANNEL. CLOSEING ACTION ON 04/15/05. ON N/R S00010. COMPLIED WITH EA 8-7832-55467.

Part: TEE FITTING — CORRODED (ZONE 500) · airframe 71,271 hrs · 22,060 cycles

COMPLY WITH EA 8-5340-55468, FUSELAGE-CORROSION IN WING-TO-FUSE TEE ATTACH HOLE. CLOSING ACTION ON 04/12/05. ON N/R S00011. COMPLIED WITH EA8-5340-55468

Part: HINGE — CORRODED (T/E FLAP) · airframe 71,271 hrs · 22,060 cycles

FLAP MOUNTED HINGE PIVOT BORE CORROSION REPAIR P/NARC2513-1. COMPLIED WITH EA 8-5750-55462.

Part: VALVE — STICKING (ANTI ICE SYS) · airframe 70,856 hrs · 21,894 cycles

DURING CRUISE, SELECTED ENGINE ANTI-ICE ON, ENGINE NR 2 ANTI-ICE WOULD NOT OPEN, RECEIVED LEVEL 1 ALERT - ENGINE NR 2 ANTI-ICE DISAGREE. CONTACTED MX VIA ACARDS, MX SUGGESTED A RESET OF C/B ON MX PANEL UPPER MX R-25. PULLED AND RESET C/B, NO CHANGE. FOUND NR 2 COWL ANTI-ICE VALVE STICKING. REPLACED VALVE PER MD-10-30 M/M 30-22-02-2. ALSO REPLACED LOW PRESSURE SWITCH S1-1046 AND HI-PRESSURE SWITCH S1-108 8 AS PRECAUTIONARY. LEAK CHECK AND OP CHECKS GOOD ON GROUND RUN PER JRH.

Part: WARNING LIGHT — ILLUMINATED (ANTI-SKID SYSTEM) · airframe 69,587 hrs · 21,364 cycles

UPON LOWERING GEAR FOR LANDING, GOT "ANTI SKID L FAIL" ALERT, WENT MISSED APPROACH AND RAISED GEAR. LOWERED GEAR A SECOND TIME AND GOT SAME ALERT. FOLLOWED CHECKLIST BY TURNING ANTI-SKID OFF, THEN BACK TO ARM. ALERT WENT OUT. TESTED ANTI-SKID AND ALERT STAYED OFF. RETESTED ANTI-SKID ON GROUND AND TESTED OK. PERFORMED PHYSICAL INSPECTION ON MLG, NO DEFECTS NOTED, TIRE PRESSURES NORMAL PER SERVICE CHECK WORK CARDS. PERFORMED ANTI-SKID SYSTEM OPS TEST PER MM 32-45-00-2 WITH PASSING RESULTS. NO DEFECTS NOTED.

Part: LINE — LEAKING (MAIN HYD SYSTEM) · airframe 68,052 hrs · 20,703 cycles

HYD SYSTEM NR 1 FAILED. NOTE: DUE TO LOSS OF HYD FLUID. FOUND HYD LINES CHAFED TOGETHER JUST AFT OF 1-3 REVERSIBLE MOTOR PUMP IN CENTER W/W CHANGED LINE, LEAK CHECK OK.

Part: INDICATOR — FALSE ACTIVATION (MLG) · airframe 67,140 hrs · 20,344 cycles

UPON TAKEOFF FROM ORD, LEFT MAIN GEAR INDICATED UNSAFE ON BOTH PRIMARY AND SECONDARY INDICATIONS AFTER RAISING GEAR HANDLE. RAN CHECK LIST-RECYCLED GEAR DOWN THEN BACK UP- BOTH PRIMARY AND SECONDARY INDICATIONS SHOWED GEAR UP AND LOCKED. CONTINUED TO ANC. UPON APPROACH INTO ANC GEAR EXTENSION WAS NORMAL- GOOD INDICATIONS BOTH PRIMARY AND SECONDARY. ** S/D ** R/R LT MLG RETRACT CYLINDER.

Part: FRAME — CRACKED (LT WING) · airframe 66,046 hrs · 19,886 cycles

LEFT MAIN LANDING GEAR RETRACT CYLINDER SUPPORT FRAME IS CRACKED AT APEX LUG TO THE RADIUS AFT SIDE. REMOVED AND REPLACED SUPPORT BRACKET RETRACT ACTUATOR REF 8-5740-7-4312.

Part: BOLT — SHEARED (RT MLG) · airframe 66,046 hrs · 19,886 cycles

RIGHT MAIN GEAR W/W SHEARED AT VERTICAL FITTING TO TRAPEZOIDAL PANEL AT OM SIDE OF W/W BS 1381. INSTALLED NEW BOLT PER AOL 10-20088.

Part: HINGE — CORRODED (T/E FLAP) · airframe 66,046 hrs · 19,886 cycles

PLI STACK LOOSE AND RUST EMITTING FROM RIGHT O/B FLAP I/B FWD HINGE AT AFT SPAR ATTACHMENT, O/B LWR STUD. REMOVED AND REPLACED HINGE & FLAP ASSY PER MM 27-50-00.

Part: STUD — SHEARED (T/E FLAP) · airframe 66,046 hrs · 19,886 cycles

STUD SHEARED AT RIGHT O/B FLAP O/B FWD HINGE HALF AT AFT SPAR ATTACHMENT LWR O/B ATTACH POINT. REMOVED AND REPLACED ALL 4 STUDS AT AFT SPAR IAW 57-41-01-2.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,853 hrs · 63,240 cycles

FRAME CORRODED IN NR 2 AIR CONDITION BAY FWD LEFT SIDE. REMOVED AND REPLACED FRAMES PER EA 8-5310-56130 & SRM 53-12-01, 53-30-00.

Part: FRAME — CRACKED (FUSELAGE) · airframe 26,853 hrs · 63,240 cycles

FRAME HAS 1 CRACK AT FASTENER LOCATION AND 1 DOUBLE AT FASTENER. FAB, INSTALLED AND REPAIRED HOLE PER IAW EA 8-5310-56130 & DC10 SRM 53-12-01 FIG 12, SHT 1 & 53-30-00 FIG 5.

Part: FRAME — CORRODED (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

LWR FWD CORNER TO AFT CARGO DOOR OPENING, FRAME CORRODED BEYOND LIMITS. FAB DOUBLER, FILLER AND SHIMS PER IAW EA 8-5310-52551 & DC10 SRM 53-50-00.

Part: FRAME — CORRODED (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

AFT CARGO PIT FRAME CORRODED. REMOVED AND REPLACED FRAME PER IAW EA 8-5310-52551 & DC10 SRM 53-50-00 FIG 1 SHT 1.

Part: SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,853 hrs · 63,240 cycles

PANEL SUPPORT COMMON TO STANCHION HAS CORRODED. REMOVED AND REPLACED CORROSION PER IAW INSTRUCTIONS, EA 8-5310-52551 STEP 7 & DC10 SRM 53-50-00 FIG 1 & 14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

SKIN FWD OF WHERE ENG NR 2 MATES HAS CRACKS AND CORROSION WHERE THE ENG DOOR ACTUATION FLEX SHAFT GOES THRU THE SKIN. REMOVED AND REPLACED FRAME PER SRM 54-10-00, 51-31-01 & EA 8-5230-56137.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

L-ANGLE AFT CARGO, LWR DOOR SILL, INSIDE TORQUE BOX IS CORRODED. REMOVED AND REPLACED FRAME PER EA 8-5310-52551 & SRM 53-50-00.

Part: FRAME — CORRODED (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

BS 1831 LWR AFT FRAME IS CORRODED BEYOND LIMITS PER IAW DC-10 SRM 53-00-31 FIG 1B. REMOVED AND REPLACED FRAME PER IAW DAC AFA3929.

Part: FRAME — CRACKED (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

BS 410, RBL 5 INCHES CRACK COMMON TO FWD, LWR FLANGE AND BS 410, LBL 13 2. CORROSION COMMON TO SKIN. REMOVED AND REPLACED FRAME PER IAW SRM 51-35-01 & 51-33-01.

Part: BEAM — CRACKED (CARGO DOOR) · airframe 26,853 hrs · 6,324 cycles

LWR, FWD CARGO DOOR COUNTER BALANCE SNUBBER BEAM ASSY CRACKED. REMOVED AND REPLACED BEAM ASSY PER IAW AMM 52-31-07-2-1 & 52-31-07-2-1.

Part: FAIRING — CRACKED (T/R FLAP) · airframe 26,853 hrs · 6,324 cycles

LT TRAILING EDGE, FLAP, O/B, FLAP FAIRING HAS 2 CRACKS ON INSIDE 6 INCHES. REMOVED, REPLACED AND FAB PER IAW DC10 SRM 51-21-01 & 51-35-01.

Part: FRAME — CRACKED (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

AFT CARGO COMP BS 1902, CRACKS FOUND ON LONGERON 42L, & BS 1942 BETWEEN LONGERON 40L AND 41L. REMOVED AND REPLACED FRAMES PER IAW DC DPS 10.225, SRM 51-21-01 & 51-33-01.

Part: PANEL — DELAMINATED (RT WING) · airframe 26,853 hrs · 6,324 cycles

PANEL 635 LT, RT WING O/B TRAILING LEADING EDGE HAS DELAMINATED EDGES ON (2) EDGES. REPAIRED EDGES PER IAW SRM 51-71-00.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

AFT CARGO COMP LBL 20, BS 1790 TO 1964 HAS CORROSION TOP, BOTTOM AND AROUND SCREW HOLES OF TIE DOWN TRACK. REMOVED AND REPLACED SEAT TRACK PER IAW SRM 51-31-01.

Part: DOOR FRAME — CRACKED (CARGO DOOR) · airframe 26,853 hrs · 6,324 cycles

BS 112, LBL 112, Z=+34 FWD SIDE UPPER CARGO DOOR FRAME NET ATTACH RING 2.8 CRACK AT ATTACH POINT. REMOVED AND REPLACED PER IAW EA 8-5230-56137, DC10 SRM 53-50-00 & GMM 4-1-975 FIG 5.

Part: SKIN — WORN (NR 2 NACELLE) · airframe 26,853 hrs · 6,324 cycles

SKIN FWD OF NR 2 ENG MATES TO FAN COWL WORN THRU NACELLE SKIN BS YTN138.977. REPAIRED PER IAW EA 8-5410-53241.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

L2 DOOR FRAME HAS PUNCTURE FWD UPPER. REMOVED, REPLACED AND FAB PER IAW DC10 SRM 51-21-01 & 53-00-01.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

AFT CARGO COMP SEAT TRACK BY CARGO DOOR CORRODED. REMOVED AND REPLACED PER IAW DC10 SRM 51-33-01 & 51-21-01.

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,853 hrs · 6,324 cycles

ANGLE HAS LEVEL 2 CORROSION IN NR 2 A/C BAY FWD LT SIDE PRIMARY STRUCTURE. REMOVED, REPLACED AND FAB LONGERON PER IAW DC10 SRM 51-30-01, 51-31-01, 53-12-01 FIG 24, SHT 1, & 51-41-01.

Part: NUT PLATE — CORRODED (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

AFT CARGO COMPT BS 1790=X=42 FWD VERTICAL SUPPORT BEAM CORRODED NUT PLATE. REMOVED AND REPLACED PER IAW DC10 SRM 53-00-01 & 51-21-01.

Part: CAP — CRACKED (HORIZ STAB) · airframe 26,853 hrs · 6,324 cycles

LEFT HORZ STAB SSI CARD INSP FOUND BS XFS & 166, CTR I/B LEADING EDGE ON O/B TEE CAP. REMOVED AND REPLACED TEE CAP PER IAW DC10 SRM 51-30-01.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

RIGHT SIDE AFT OF MID CARGO DOOR DAMAGE NEXT TO PRE-EXISTING DOUBLER, FRAME 20, L-39 RT. REMOVED AND REPLACED DOUBLER PER EA 8-5310-52550A.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

R-3 DOOR BS 1294-1300 AFT DOOR FRAME LWR RELIEF HOLE IN BOTTOM OF FRAME CRACK. FAB, STOP DRILL CRACK INSTALL DOUBLER PER IAW DC10 SRM 53-50-00 FIG 19.

Part: FRAME — CRACKED (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

PRIOR TO LWR SKIN REMOVAL BS 469, RBL 65, 3 INCH CRACK IN FRAME COMMON TO UPPER FLANGE. REMOVED AND REPLACED FRAME PER IAW DC10 SRM 53-30-00 FIG 11 & 51-21-01.

Part: FRAME — CRACKED (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

FWD CARGO FRAME FORMER RT HAS PRE-EXISTING CRACK BS 916 LNG 34, RBL 59. REMOVED AND REPLACED PER IAW DC10 SRM 51-50-03, 51-31-01 & 51-21-01.

Part: GUSSET — BROKEN (FUSELAGE) · airframe 26,853 hrs · 6,324 cycles

PRIOR TO LWR SKIN REMOVAL AT BS 440, LBL 27 GUSSET COMMON TO FRAME AND INTERCOSTAL BROKEN. REMOVED, REPLACED AND FAB PER IAW DC10 SRM 53-11-014, 51-21-01.

Part: BEAM — CRACKED (EXIT DOOR) · airframe 26,853 hrs · 6,324 cycles

LEFT NR 3 OVERWING EXIT DOOR UPPER AFT DOOR FRAME IS CRACKED AND BROKEN OFF. REMOVED AND REPLACED BEAM PER IAW DWG ADA3462 & SRM 52-12-01, 51-30-01.

Part: STRAP — CRACKED (RT HORIZ STAB)

RT HORIZ STAB LEADING EDGE PNL 3RD FROM I/B (CENTER) FOUND TOP TEE BRACKET CRACKED (XFS 172.161) APPROX 26 .75 LONG. *S/D* NEW STRAP FAB PER DWG ALC7506, REMOVED AND REPLACED PER SRM 51-33-01 VOL II.

Part: BOLT — LOOSE (LT TE FLAP)

LT WING INBD FLAP HINGE BOLT TO REAR SPAR FND LOOSE AND ABOUT A QTR OF THE NUT MATERIAL MISSING.

Part: TEE — CRACKED (HORIZ STAB)

LT HOR-STAB LEAD EDGE PNL 2ND FROM I/B (CTR I/B) FOUND TOP CAP CRACKED (XFS.166.161) APPROX 46 .375 LONG. *S/D* REMOVED AND REPLACED NEW CAP PER SRM 51-35-01 VOL II.

Part: ACTUATOR — LOOSE (LT MLG DNLOCK)

LT MAIN LANDING GEAR DOWNLOCK ACTUATOR FOUND ACTUATOR END WITH BOLT LOOSE AND NUT MISSING. *S/D* REPLACED AND TIGHTENED BUSHING AND NUT PER MM 20-50-02-2.

Part: RETRACT MECH — MALFUNCTIONED (LANDING GEAR)

LANDING GEAR WOULD NOT EXTEND, ALL LIGHTS STAYED RED, FRONT AND BACK PANEL. RAN CKLIST OK. *S/D* REMOVED AND REPLACED LANDING GEAR SEL VALVE PER DC10-30 MM 32-31-03-2, RIGGED CABLES BETWEEN LANDING GEAR CONTROL HANDLE AND SEL VALVE PER DCN -30 MM 32-31-01-5. PERF EXTENSION AND RETRACT TEST PER DC10-30 MM 32-31-03-2 NORM.

Part: PRESSURIZATION — MALFUNCTIONED (CABIN)

DURING CLIMBOUT, CABIN ALT BEGAN CLIMB AT SAME RATE AS A/C. PROBLEM START AT 5000 MSL: AUTO PRESS MODE WAS BEING USED. CABIN ALT RAPID REACH 5000 AND CONT TO CLIMB WITH A/C. USE OF SEMIAUTO STBY AND MANUAL MODES HAD NO EFFECT. CREW LEVEL OFF AT 10000 MSL CAB LVLD OFF 10000. RETURN TO IAD. INSP OUTFLOW VALVE. INSP ALL DOOR SEALS FOR DAMAGE, NO DEF FOUND. RAN ENG PER JRH AND A/C ABLE TO PRESS MANUAL. DEF AUTO AND SEMIAUTO CABIN ALT CNTRL SYS PER MEL. MX BITE CHECK SYS ON GND CHECK NORMAL. NEXT FLT CREW COMMENTED THAT FLT CHECK WAS GOOD. MX CLEARED PER CREW COMMENT AND GND CHECK NORMAL.

Part: SWITCH — MALFUNCTION (THROTTLE QUAD)

UPON RETRACTION ON TAKEOFF, THE GEAR WARNING HORN AND ALL RED GEAR LIGHTS CAME ON STEADY. GEAR HANDLE WAS CYCLED DOWN AND WARNING LIGHTS AND HORN TURNED OFF. GEAR WAS RAISED AGAIN WITH NORMAL INDICATION. CHECKED ALL THREE THROTTLE SWITCHES FOR CONTINUITY. FOUND NR 1 THROTTLE SWITCH STICKING INTERMITTENTLY. REMOVED AND REPLACED SWITCH, OPS CHECK GOOD PER AMM 76-11-04-2.

Part: SIDEWALL — CORRODED (BS 1259)

MAIN DECK TOP OF CENTER FUEL TANK RT RBL SIDEWALL STA 1259, TWO PLACES EXFOLIATED. *S/D* REMOVED 6 FASTENERS, BURNISHED CORROSION IN REF TO SRM 57-10-00, C/W MATERIAL REMOVED MAPPING REQUIRED BY ENGINEERING, REPAIRED PER EA 8-5710-31711, LEAK CK OK 10/17/96.

Part: STRAP — CRACKED (RT WING)

SNRM 00182, RIGHT O/B FLAP I/B HINGE O/B SIDE AT REAR TENSION STRAP IS CRACKED AT BOTTOM FLANGE. *S/D* COMPLIED WITH EA 8-5710-31702, INSTALLED NEW PART PER SRM 53-00-01.

Part: STRAP — CRACKED (LT WING)

SNRM 00181, LEFT O/B T/E FLAP I/B HINGE O/B SIDE AT REAR SPAR TENSION STRAP IS CRACKED AT BOTTOM FLANGE. *S/D* COMPLIED WITH EA 8-5710-31702, INSTALLED NEW PART PER SRM 53-00-01.

Part: SKIN — CRACKED (RT HORIZ STAB)

RIGHT HORIZONTAL STABILIZER, UPPER AFT SKIN PANEL CRACKED AT I/B AFT CORNER O/B OF THE OPERATION BULKHEAD, CRACK LENGTH .6250 INCH. REPAIRED UPPER AFT SKIN STAB PANEL PER EA NR 8-5510-25166. INSTALLED AND SEALED ALL ACCESS AND L/E PANELS AS REQ IAW MM 55-10-02.

Part: FITTING — CRACKED (RT TE FLAP)

RT I/B FLAP I/B ACTUATOR ATTACHMENT TO FUSELAGE BOLTS NOT SECURED. CHECKED BARREL NUTS FOR WEAR, FOUND ACT LOWER ATTACH FITTING CRACKED AT LOWER BOLT HOLES.

Part: ARM — CRACKED (FLIGHT CONTROLS)

UPON DISASSEMBLY OF CONTROLS, ARM AP NR 7202-5 WAS FOUND CRACKED AT SPLINE SHAFT MOUNT END. CRACK ORIGINATED IN CLAMP UP BOLT PLANE AND FOLLOWS GRAIN OF PART LENGTH. THIS CONDITION FOUND ON 2 OF ARMS FROM THIS A/C AND THE ARMS WERE REPLACED.

Part: SPAR — CORRODED (NR 1 PYLON)

NR 1 PYLON UPPER SPAR RT CHORD, AFT 16, HAS RUST ON TOP OF HORIZONTAL FLANGE AND INBOARD SIDE OF TOP VERTICAL FLANGE. CLEANED AND TREATED CORROSION PER SRM 51-21-01, PAGE 36.

Part: SPAR WEB — CRACKED (NR 1 PYLON)

NR 1 ENG PYLON UPPER SPAR WEB CRACKED AT O/B CORNER, APPROX 5 INCHES. REMOVED AND REPLACED SPAR WEB.

Part: SPAR WEB — CRACKED (NR 1 PYLON)

NR 1 ENG PYLON UPPER SPAR WEB CRACKED AT OUTBOARD CORNER (APPROX 5). REMOVED AND REPLACED SPAR WEB. REPAIRED PER EA 8-5410-20129. REPLACED NR 1 PYLON AFT BULKHEAD FITTING AND REPAIRED UPPER WEB. SEE EA FOR DETAILS.

Part: BULKHEAD — CRACKED (NR 1 PYLON)

NR 1 PYLON AFT SPHERICAL BEARING SUPPORT BULKHEAD, YN 417.212, HAS A 10 INCH CRACK AT INBOARD INSIDE RADIUS. CRACK WAS DISCOVERED BY AN INSPECTOR WHILE PERFORMING THE SB 54-74 INSPECTION. THE NR 3 PYLON WAS ALSO INSPECTED AND NO CRACKING WAS EVIDENT. CRACK APPEARS TO HAVE ORIGINATED AT ZN 55.692 AND PROPAGATED DOWNWARDS TO ZN 44.705. REMOVED AND REPLACED THE BULKHEAD PER EA 8-5410-20129. (NOTE: THIS IS THE FINAL C/A).

Part: BULKHEAD — CRACKED (NR 1 PYLON)

NR 1 PYLON AFT SPHERICAL BEARING SUPPORT BULKHEAD YN 417.212, HAS A 10 INCH CRACK AT I/B INSIDE RADIUS. CRACK WAS DISCOVERED BY AN INSPECTOR WHILE PERFORMING THE SB 54-74 INSPECTIOIN. THE NR 3 PYLON WAS INSPECTED AND NO CRACKING WAS EVIDENT. CRACK APPEARS TO HAVE ORIGINATED AT ZN 55.692 AND PROPAGATED DOWNWARDS TO ZN 44.705. REMOVED AND REPLACED THE BULKHEAD.