N507MC

Part: STRUCTURE — CORRODED (FUSELAGE)

DURING THE RECENT C-CHECK, THE UPPER CHORD AT BS 1840 WAS FOUND CORRODED BETWEEN LBL 75 AND 98 ON THE HORIZONTAL SURFACE AND EXTENDED DOWN ONTO THE VERTICAL SIDE. CORRODED SECTION WAS REMOVED, REPLACED AND REPAIR ANGLES WERE INSTALLED. REWORKED AREA EXTENDS FROM LBL 65 AND 105. REPAIR APPROVED PER BOEING TELEX. (M)

Part: SKIN — CORRODED (RT WING)

DURING THE RECENT C-CHECK, THE R/W EXTERNAL SKIN WAS CORRODED AT WS 320 COMMON TO STRINGER 15 AND WBL 179. CORROSION REMOVED, AREA BLENDED, TREATED AND REFINISHED IAW 57-30-01 FIG 2. (M)

Part: SPAR — CORRODED (WING)

DURING THE RECENT C-CHECK, THE REAR SPAR (OUTSIDE SURFACE) WAS FOUND CORRODED IN THE VICINITY OF THE NR 2 INBOARD FUELING VALVE MOUNT BOLT HOLES AT WS 562.50. FUELING EQUIPMENT AND MOUNT BOLT REMOVED. AREA REWORKED BY SPOT FACING CORRODED AREA, BLENDED, TREATED AND FINISHED PER BOEING TELEX. FUELING EQUIPMENT AND MOUNT HARDWARE REINSTALLED. (M)

Part: CYLINDER — CORRODED (LANDING GEAR)

DURING THE RECENT C-CHECK, THE LEFT OUTER CYLINDER SPUD BOSS WAS FOUND CORRODED IN THE AREA OF CHROME LOSS. AREA CLEANED OF CORROSION, TREATED, CHECKED FOR HEAT RELATED DAMAGE. REWORK AREA IS 5MM IN DIAMETER WITH MISSING CHROME AND MATERIAL LOSS OF .4 MM AFTER CORROSION CLEAN UP. ATLAS AIR EO 4732A014 ISSUED FOR REWORK AND FOLLOW UP INSPECTION. (M)

Part: FRAME — CRACKED (BS 360)

BS 360 LT, FOUND CRACK IN FUSELAGE (MID) FRAME AT STR 14E DURING SECTION 41 INSPECTION. CRACK RUNS FROM CUT-OUT TO NEAREST FASTENER HOLE BELOW FORMED CHORD. REPAIRED FRAME PER ACC KLM DFX 99-133 REV 1. FORM 8110-3 ISSUED. (X)

Part: FRAME — CRACKED (BS 420)

BS 420 LT, FOUND CRACK IN FUSELAGE FRAME AT STR 14E DURING SECT 41 INSPECTION. CRACK RUNS FROM STRINGER CUT-OUT TO INBOARD. REPAIRED FRAME WEB PER ACC KLM DFX 99-134 REV 2, FORM 8110-3. (X)

Part: SPAR WEB — CORRODED (CENTER WING)

LEFT WING GEAR WHEEL, SPOT CORROSION FOUND ON CENTER TANK REAR SPAR WEB BEHIND THE BS 1241 LT BULKHEAD FITTING. REF: AD 98-26-23 AND SB 747-57-2263R2. CORROSION REMOVED IAW SB 747-57 2263 REV R2 AND FAX KLM TLS 99-0008H. FORM 8110-3 ISSUED.

Part: FRAME — CRACKED (BS 520)

BS 520 LT, FOUND CRACK IN FUSELAGE FRAME FLANGE BETWEEN STR 9 AND STR 11. ALSO, SHEAR DOUBLER CRACKED IN CUT-OUT TO NEAREST FASTENER HOLE DURING SECTION 41 INSPECTION. REPAIRED STR 9 PER SRM 53-10-04, FIG 85. REPAIRED FRAME AT STR 10 PER ACC KLM DFX 99-126 REV 1. SHEAR DOUBLER AT STR 11 REPAIRED PER ACC KLM DFX 99-123. FORM 8110-3 ISSUED. (X)

Part: FRAME — DENTED (BS 1840)

FRAME DENTED AT STA 1840 RT TWO PLACES, FIRST BETWEEN STR 12 AND STR 13, SECOND BETWEEN STR 10 AND STR 11. FRAME REPAIRED BETWEEN STR 12/13 PER SRM 53-10-04 FIG 87. FRAME REPAIRED BETWEEN STR 10/11 PER ACC KLM DFX 99-127 REV 2. (X)

Part: FRAME — CRACKED (BS 510)

BS 520 RT, FOUND CRACK IN FUSELAGE FRAME AT STR 11 DURING SECTION 41 INSPECTION. CRACK RUNS FROM CUT-OUT TO NEAREST FASTENER HOLE. REPAIRED FRAME PER ACC KLM DFX 99-124 REV 2. FORM 8110-3 ISSUED. (X)

Part: FRAME WEB — CRACKED (BS 1265)

BS 1265 HFEC INSPECTION PERFORMED ON LT NR 3 MAIN ENTRY DOOR FRAME. UNDER FLOOR, LINE FOUND CRACK INDICATION IN WEB. INTERIM REPAIR ACCOMPLISHED PER ACC KLM DFX 99-119 REV 2. RE-INSPECT AT 2,000 CYCLE INTERVALS. FORM 8110-3 ISSUED. (X)

Part: STRUCTURE — CRACKED (BS 1980)

BULK CARGO DOOR SKIN, DOUBLER AND TRIPLER CRACKED ON BOTTOM OF CUT-OUT AT BS 1980 RT BETWEEN STR 37 AND STR 38. CRACK IS HORIZONTAL AND MEASURES 0.500 INCHES. CRACK REPAIRED PER ACC KLM DFX 99-120. FORM 8110-3 ISSUED. (X)

Part: FRAME — CRACKED (BS 380)

BS 380 LT, FOUND TWO CRACKS IN FUSELAGE FRAME AT STR 23 DURING SECTION 41 INSPECTION. CRACK RUNS FROM STRINGER CUT-OUT TO NEAREST FASTENER HOLE, THE OTHER TO THE SKIN FLANGE. REPAIRED FRAME WEB, PER KLM DFX 99-132 REV 2, FORM 8110-3 ISSUED. (X)

Part: BATTERY CHARGER — FAILED (APU)

FLT 9603 - BTB - DURING TAXI APU BATTERY CHARGER SPARKED TWICE, THEN STARTED, FILLING THE MAIN CABIN WITH SMOKE UNTIL C/B POPPED. AIRCRAFT RETURNED TO GATE. FOUND APU BATTERY CHARGER DEFETIVE. REPLACED APU BATTERY CHARGER, OPERATIONAL CHECK NORMAL. (M)

Part: RIVET — FAILED (CARGO DOOR)

FLT NR IB9709 - VCP/EZE - ATB - AT 10,000 FEET DISCOVERED AIRCRAFT UNABLE TO PRESSURIZE. ALL DOOR LIGHTS EXTINGUISHED AND SUFFICIENT AIRFLOW IN THE AIRCRAFT. USE FHB PROCEDURE AND INSPECTED AS MUCH OF AIRCRAFT AS POSSIBLE TO DETERMINE NO HOLES AND PRESSURIZATION CONTROLLER OK. RETURNED TO VCP. AFTER ARRIVAL, MAINTENANCE FOUND AFT LOWER CARGO DOOR HANDLE RIVET SHEARED ALLOWING LOWER PORTION OF HANDLE TO OPEN CAUSING PRESSURE RELIEF DOORS TO OPEN. REPLACED SHEAR PIN AND OPERATIONAL CHECK NORMAL. (M)

Part: CLAMP — LOOSE (NR 4 ENGINE)

ATB - FLT EX9880 -DXB/DXB - NR 4 ENGINE, BOTH NACELLE TEMP INDICATORS INDICATED 8.4 ON SCALE AT CLIMB POWER CLOSED BLEED VALVE NO CHANGE. REDUCED THROTTLE TO IDLE, INDICATIONS DROPPED TO 2-2.5, SAME AS NR 1, NR 2, NR 3 ENGINE. AT HIGHER POWER INDICATIONS FOLLOW THROTTLE. FOUND NACELLE ANTI-ICE TOP ATTACHMENT CLAMP ADRIFT AND LEAKING AIR. CLAMP REMOVED AND VISUALLY INSPECTED, FOUND NO DAMAGE. CLAMP REINSTALLED AND TORQUED. LEAK CHECK, PERFORMED SATISFACTORILY. (M)

Part: SHUT-OFF VALVE — FAILED (LT ENGINE)

ON LEVEL OFF FROM A CLIMB TO F350, THE NR 4 ENGINE FLAMED OUT FOR NO APPARENT REASON. AIRCRAFT DIVERTED INTO JFK. FOUND NR 4 ENGINE FUEL SHUT OFF VALVE FAILED. REPLACED FUEL SHUT OFF VALVE ACTUATOR PER MM 76-11-04. OPS AND RUN-UP OK. ENGINE INLET, TAIL PIPE, INSPECTED OK. ACCOMPLISHED 'NO OIL PRESSURE' INSPECTION, MM 72-00-00. (X)