N516MC
Registered owner: PJK AVIATION LLC, NY (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| TALON AIR, LLC (OZTA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
AFTER PUSHBACK FLIGHT ENGINEER FOUND THE CROTCH SEATBELT MISSING FROM FIRST OBSERVER'S SEAT. AIRCRAFT CAME BACK TO GATE AND MAINTENANCE DEFERRED THE FIRST OBSERVER'S SEAT IAW MEL 25-23-1.
WITH NR 2 ENGINE FIRE LOOP "B" ON DEFERRAL AND APPROXIMATELY 140NM OUT OF ICN AT FL29 LOOP "A" FIRE DETECTOR LIGHT AND FAULT LIGHT ILLUMINATED FOLLOWED BY FIRE WARNING BELLS. THE ENGINE WAS SHUTDOWN AND FIRE HANDLE PULLED WITH OUT DISCHARGING BOTTLES. OIL PRESSURE WAS MAINTAINED AT JUST OVER 4 PSI, 10 PERCENT N1; 7 PERCENT N2 NAC TEMP 2.0. MAINT FOUND THE DUCT FOR THE PRESSURE RELIEF VALVE LEAKING AND REPLACED SAME. ALSO, THE FORWARD AND AFT UPPER FIRE DETECTORS WERE REPLACED.
ON TAKEOFF, NR 2 ENGINE FLAMED OUT. ENGINE HAD SUCCESSFUL RESTART. INLET AND EXHAUST FEELING AND COMPRESSOR CHECKED SATIS NR 2 FUEL TANK WAS SUMPED THEN REPLACED NR 2 ENGINE FUEL FILTER. NO FURTHER PROBLEMS.
M/D BS 1740 S-13R-S14R FRAME FOUND CRACKED AND DEFORMED. M/D BS 1740 S13R-S14R DAMAGE FRAME REPAIRED FROM S11R TO S15R/16R AS PER BOEING MSG 1-309862807-8.
M/DECK R3 DOOR AFT UPPER CORNER AREA BEAR STRAP DELAMINATED. DELAMINATED BEAR STRAP CORROSION REMOVED, OUT OF LIMIT, REPAIRED AS PER BOEING MSG 1-30886570-4.
KEEL BEAM PANEL NR 191KK CRACKED AT RT FWD HINGE CUT-OUT AS MARK. CRACKED HINGE CUT-OUT SKIN REPAIRED AS PER SRM 51-40-02.
KEEL BEAM PNL NR 191KK EXTERNAL AND INTERIOR SURFACE CORROSION REVEALED. KEEL BEAM PANEL NR 191KK OUT OF LIMIT HINGE AREA REPAIRED AS PER SRM 51-40-03 FIG 1 AND SKIN REPAIRED AS PER SRM 51-40-02 FIG 1.
KEEL BEAM PNL NR 191HH EXTERNAL AND INTERIOR SURFACE CORROSION REVEALED. KEEL BEAM PANEL NR 191HH HINGE ATTACHMENT AREA OUT OF LIMIT, REPAIRED AS PER SRM 51-40-03 FIG 1.
M/DECK L3 DOOR AFT UPPER CORNER AREA DELAMINATED BEAR STRAP. OUT OF LIMIT DELAMINATION BEAR STRAP REPAIRED AS PER BOEING MSG 1-309886570-4.
EMP LT HORIZ STAB HINGE FTG AREA FOUND NR 25 HOLE CRACK AT REAR SPAR UPPER CHORD APPROX 3/16" RUNNING O/B LOWER DIRECTION. REPAIRED AS PER BOEING MSG 1-305519321-7.
M/DECK LT MED NR 3 CUT-OUT AFT UPPER CORNER SMALL STEEL DOUBLER 1 HOLE CRACK AT BEAR STRAP APPROX 0.030" LONG (AFTER CORNER REMOVED). CRACKED HOLE REPAIRED AS PER BOEING MSG 1-309886570-4, WORK DETAILS REF N.R C51491.
RT STAB ACCESS PANEL 344 QBR OUTBOARD AFT CORNER PANEL SUPPORT FOUND CRACKED. REPLACED OUTBOARD AFT CORNER SUPPORT CHANNEL PER BOEING MESSAGE 1-307272180-2.
LT S14 AREA FRAME CRACKED. CRACKED FRAME WEB REPAIRED AS PER SRM 51-40-03 FIG 1.
LT STAB 344QBL PANEL AFT SUPPORT AREA FOUND CRACKED. REPLACED SUPPORT CHANNEL PER BOEING MESSAGE 1-307217093-2.
KEEL BEAM PNL NR 191JJ INTERIOR SURFACE CORROSION REVEALED AT SEVERAL LOCATIONS. KEEL BEAM PANEL NR 191JJ INTERIOR SUPPORT REPLACED AS PER SRM 51-10-01 PP AND INSTALLED AS PER SRM 51-30-02.
FX - AIR COND BAY FAIRING SUPPORT FOUND CORRODED AT BS 1160, LBL58-LBL68. CORROSION OUT OF LIMIT, FAIRING SUPPORT CHORD REPLACED AS PER SRM 51-10-01 PP AND INSTALL AS PER SRM 81-30-02.
FAIRING SUPPORT FRAME AT STA 880 LWR SIDE LBL 2 AND RBL 2 FOUND CORRODED. OUT OF LIMIT LWR CHORD REPAIRED AS PER SRM 53-50-04.
FX - STRINGER FOUND CORROSION CRACKED AT STA2260-S-51L. CORROSION CRACKED STRINGER, REPAIRED AS PER SRM 53-10-02.
M/DECK BS 1241-1250 LBL 75-97 CLOSE-OUT PANEL NEAR TRIM AIR DUCT FOUND CRACK. TRIM AIR DUCT CLOSE-OUT PANEL. REPLACED AS PER SRM 53-23-29 PART IV.
UPPER DECK STATION 685 RBL 27 SEAT TRACK CORRODED AS MARKED. REMOVED CORROSION PER SRM 53-10-05
FX - AIR COND BAY FAIRING SUPPORT FOUND CORRODED AT BS 1050 LBL 12, LBL 28 (191AL FRG ATTACH AREA). OUT OF LIMIT FAIRING SUPPORT LWR CHORD LWR FLANGE REPAIRED AS PER SRM 53-50-06 FIG 2.
M/D BS 940 LT TENSION TIE STEEL PLATE FASTENER HOLE 1 FOUND SHORT EDGE MARGIN. M/D BS 940 LT TENSION TIE STEEL PLATE REPAIRED AS PER BOEING MSG 1-30-3983211-2-1 AND 4 FIG 3.
RT BS 900 TENSION TIE AREA HOLE NR 5 FOUND CRACKED AT FRAME DOUBLER, INSULATION BLANKET HOLE FOUND CRACKED AT FRAME DOUBLER BETWEEN S-8R TO S-9R AND S-10R TO S-10AR. FRAME DOUBLER REPAIRED AS PER BOEING MSG 1-306586780-2.
M/DECK BS940 RT TENSION TIE STEEL PLATE FASTENER HOLE 2 FOUND SHORT EDGE MARGIN AT UPPER ROW MOST O/B. REPAIRED AS PER BOEING MSG 1-303983211-1-2, FIG 3.
BS 360 LT S24A STRINGER CUT-OUT CRACKED. CRACKED FRAME WEB REPAIRED AS PER BOEING MSG 1-307193755-1-2.
NR 4 ENG LT LOWER SPAR CHORDS (SIDE COWL HINGE AREA) AFT AREA FOUND DAMAGED. DAMAGED WEB REPAIRED AS PER BOEING MSG 1-308420578-2.
RT BS 900 TENSION TIE AREA NR 5 HOLE FOUND CRACK AT FRAME WEB THRU THICKNESS RUNNING I/B AND NR 10 HOLE FOUND CRACK AT FRAME WEB APPROX 0.060" IN LENGTH RUNNING DOWNWARD. CRACKED FRAME WEB REPAIRED AS PER BOEING MSG 1-306586780-2.
UPPER DECK STATION 740 STRINGER 6R FRAME CUTOUT CRACKED. REPAIRED STRINGER CUTOUT PER SRM 53-10-04 FIG 54.
CABIN FLR SUPPORT BS 1283 RBL 117 CORROSION. OUT OF LIMIT, SUPPORT REPAIRED AS PER BOEING 1-310385513-2.
M/D STA 360 S-23R FRAME STRINGER CUT-OUT CRACK. CRACKED FRAME REPAIRED AS PER BOEING MSG 1-307825515-2-1.
EMP LT STAB T/E RIB AT STAB BL421.5 WEB FOUND CRACKED. CRACKED WEB REPAIRED AS PER SRM 55-10-06 FIG 4.
RT BS 940 TENSION TIE AREA HOLE NR 16 FOUND CRACKED AT AFT CHANNEL APPROX 0.060" RUNNING INBOARD LWR. CRACKED AFT CHANNEL REPAIRED AS PER BOEING MSG 1-303983211-2-2-4.
RHW NR 23 VC FLAP I/B ARM ROTARY ATT RIB AT OLES 1278 I/B FACE FOUND CRACKED AT "D" HOLE FWD STIFFENER AREA. CRACKED RIB "D" HOLE REPAIRED AS PER BOEING MSG 1-308409234-2.
MAIN DECK STATION 2000 STRINGER 13R FRAME INNER FLANGE FOUND DEFORMED. REPAIRED FLANGE PER SRM 51-40-03 FIG 1.
M/D STA270 S-R13A AREA FRAME CRACK. CRACKED FRAME WEB REPAIRED AS PER BOEING MSG 1-307196918-1-2.
MAIN DECK STATION 1960 STRINGER 13R FRAME INNER FLANGE FOUND DEFORMED. REPAIRED PER SRM 51-40-03 FIG 1.
AFTER REMOVAL OF PAX DECK SPLICE FITTING AT STATION 1416 LBL 2 IN THE BLG WHEEL WELL IS FOUND CRACKED. REPLACED FITTING PER SRM 51-10-01 PAGE 9.
RT NR 1 MED NR 9 DOOR STOP FTG AREA FOUND CRACK AT BS 488 FRAME WEB TOOLING HOLE APPROX 1/16" AND 1/8" LONG. RT NR 1 MED NR 9 DOORS STOP FTG AREA CRACK WEB REPAIRED AS PER SRM 53-10-04 FIG 121.
M/D LT BS 200 FRAME INNER CHORD IS FOUND CRACKED AT 1 FASTENER HOLE BETWEEN S13L AND S14L. CRACKED INNER CHORD REPAIRED AS PER SRM 51-40-03 FIG 1.
EMP LT HORIZ STAB C/S STAB HINGE NR 28 HOLE FOUND CRACK AT HINGE FTG 11 O/C POSITION APPROX 1/8" LONG. REPAIRED AS PER BOEING MSG 1-305519321-7.
NWW RT VERTICAL BEAM WEB AT BS 280 WL 170-180 LOWER STAND OFF HOLE FOUND CRACK APPROX 1/8" LONG. CRACK WEB REPAIRED AS PER SRM 51-40-02 FIG 1.
LT BS 200 FRAME IS FOUND CRACKED AT 11EA FASTENER HOLES BETWEEN S13L AND S14L. CRACKED FRAME WEB REPAIRED AS PER SRM 51-40-03 FIG 1.
RT BS 860 TENSION TIE AREA HOLE NR 6 FOUND CRACKED AT AFT CHANNEL APPROX 0.060" IN LENGTH RUNNING UPWARD. RT BS 860 TENSION TIE CRACKED AFT CHANNEL, REPAIRED AS PER BOEING MSG 1-306486452-2.
RT BS 860 TENSION TIE AREA HOLE NR 5 FOUND CRACKED AT FWD CHANNEL APPROX 0.030" ON LENGTH RUNNING UPWARD. CRACKED TENSION TIE FWD CHANNEL REPAIRED AS PER BOEING MSG 1-306484452-2.
CABIN TIE DOWN TRACK FLANGE CORRODED AT BS 1440-1480 RBL33. CORROSION SEAT TRACK REPAIRED AS PER SRM 53-10-05 FIG 25.
AIR-CONDITIONING BAY FAIRING SUPPORT FOUND CORRODED AS MARKED AT STA 1110 LBL 12 (191EL FAIRING ATTACH AREA). REMOVED CORROSION AND REPAIRED PER SRM 53-50-04 FIG 2.
M/D STA 340-360 S-26R FLR WEB CRACK AT SKIN ATT AREA. CRACKED FLOOR WEB REPAIRED AS PER SRM 51-40-03 FIG 3.
NR 2 PYLON CAP SKIN OUTBOARD LOWER ATTACH ANGLE FOUND CRACKED AS MARKED. REPAIRED AS PER SRM 54-11-02 FIG 7.
LEFT FUSE TO WING LOWER PANEL 191KL FAIRING SUPPORT FRAME AT STA 1241 FOUND CRACKED. FAIRING SUPPORT FRAME REPAIRED IAW SRM 51-40-03.
M/D STA 360-380 S26R FLOOR WEB CRACK AT SKIN ATT AREA. CRACKED FLOOR WEB REPAIRED AS PER SRM 51-40-03 FIG 3.
M/D LT BS 840 FRAME TO TENSION TIE CONNECTION FOUND NR 4 HOLE CRACK AT TENSION TIE FWD CHANNEL. CRACK FWD CHANNEL REPAIRED AS PER BOEING MSG 1-303978264-2.
M/D RT BS 880 FRAME TO TENSION TIE CONNECTION FOUND NR 6 HOLE CRACK AT TENSION TIE FWD CHANNEL. CRACKED AFT CHANNEL REPAIRED AS PER BOEING MSG 1-303986330-2.
M/D RT BS 840 FRAME TO TENSION TIE CONNECTION FOUND NR 8 HOLE CRACK AT TENSION TIE AFT CHANNEL. CRACKED AFT CHANNEL REPAIRED AS PER BOEING MSG 1-303978264-2.
M/D LT BS 840 FRAME TO TENSION TIE CONNECTION FOUND NR 5 HOLE CRACK AT TENSION TIE AFT CHANNEL. M/D LT BS 840 FRAME TO TENSION TIE CONNECTION TENSION TIE AFT CRACKED CHANNEL REPAIRED AS PER BOEING MSG 1-303978264-2.
NR 3 PYLON AIR VALVE INDICATES 10-PSI IN CRUISE WITH 95 PERCENT N1 SET IS NOT REGULATING CORRECTLY WITH ISOLATION VALVE OPEN. THE LEFT AND RIGHT MANIFOLD PRESSURE ONLY INDICATE 26-PSI. LEAK CHECK FOUND NO FAULT ON ENGINE AREA. SUSPECT CRACKED DUCT ON THE WING CAUSED PRESSURE LOW. AFTER REMOVED AND REPLACED DUCT ENGINE RAN CHECK NORMAL AS PER MM 36-11-01 AND 71-00-00.
ON DESCENT, NR 2 ENGINE EGT WENT TO ZERO WITH A VISIBLE BARBER POLE. CLEANED CONNECTOR ON FORWARD LEAD GROUND, OPS CHECKED PER 77-21-00, CHECKED OKAY.
AIRCRAFT DIVERTED TO JFK DUE TO NR 3 ENGINE GEN BUS TIE OPEN, FIELD OFF LIGHT ON. ZERO VOLTAGE ZERO FREQS. THEN NR 4 BUS TIE GEN OPEN FIELD OFF LIGHT ON, VOLTS AND FREQS NORMAL. REPLACED NR 3 GCU AND REPLACED THE RT BPCU BOTH ENGINES, OPS CHECKED OKAY AND ALL PARAMETERS NORMAL.
UNABLE TO MAKE COMPUTED T/O N1 FOR NR 2 ENGINE. REMOVED AND REPLACED NR 2 ENGINE CIT SENSOR IAW MM 73-21-02. CHECKED CDP LINE FOR BLOCKAGE. ACCOMPLISHED VSV/VBV RIG CHECK IAW MM 75-30-00. LEAK CHECK GOOD.
CORROSION FOUND ON RT WING REAR EDGE BETWEEN REAR SPAR UPPER SKIN AND FWD EDGE OF FLYING PANEL. PANELS AT STA 456 AND 586. LEVEL 1 CORROSION. REPAIR CARRIED OUT PER XEO 57-112206 AND SRM 57-30-01 FIG 1.
CORROSION FOUND BETWEEN UPPER WING SKIN REAR SPAR AREA AND FLYING PANEL AT STATION 406. REPAIR CARRIED OUT IAW XEO 57-112106 AND SRM 57-30-01 FIG 1.
BLOCK TURN BACK, DUE TO SMOKE IN COCKPIT APPEARS TO BE BLEED AIR SMOKE. NR 3 PACK VALVE CLOSED ACM OUTLET TEMP 85 DEGREES C, NO TRIP. SUSPECT SMOKE CAME FROM CONTAMINATED AIR DUCT AND DUE TO ACM NR 3 ABOVE 85 DEGREES C. PERFORMED OPS TEST, AIR CONDITIONING PACK AS PER AMM 21-51-00, FIND ALL NORMAL. REMOVED AND REPLACED PACK NR 3 FLOW CONTROL VALVE AS PER AMM 21-51-03 AND PERFORMED PACK OVERHEAT SYS TEST PER AMM 21-51-00. FOUND ALL SATISFACTORY.
AIR TURN BACK DUE TO TIRE SEPARATION AFTER TO. UPON ARRIVAL MAINTENANCE FOUND ALL 4EA WHEELS ON LT BODY GEAR SEPARATED. ADDITIONAL DAMAGE FOUND TO LT BODY GEAR TRUCK ASSY, FLAP DRIVE TUBES, LOWER FUSELAGE, NR 2 VHF ANTENNA, HYDRAULIC LINES WHEEL WELL AND BODY FAIRING AFT OF BODY GEAR.(ITEM REMAINED OPEN).
ABORTED TAKEOFF, POOR ACCELERATION. A/C PULLING LEFT AFTER A/C STOPPED ON RUNWAY, ALL BRAKES LOCKED UP AND WOULD NOT RELEASE FOR APPROX 20 SECONDS. LEFT WING AND BODY,LEFT FRONT AND LEFT REAR IN RED SCALE 8+, PULLED VOICE RECORDER C/B. REMOVED AND REPLACED LEFT METERING VALVE AS PER MM 32-41-03. ACCOMPLISHED CHAPTER 5 HIGH ENERGY STOP IAW 5-51-10.
AIR TURNBACK, NR 3 LEADING EDGE FLAP LEFT WING WOULDN'T RETRACT ELECTRICALLY. PNEUMATICS WAS DISCONNECTED FOR PREVIOUS WRITE UP PAGE 597439. DUMPED 26.5 KILO OF FUEL. REMOVED AND REPLACED THE LEFT HAND NR 3 L/E PDU IAW MM 27-81-03.
MAIN DECK CARGO COMPT, SEAT TRACK IS MISSING TWO TABS BY THE MAIN CARGO DOOR BS 1800. REPLACED SEAT TRACK PER SRM 53-10-05 AND EO4753A686.
NR 6 SPOILER HAS A SMALL CRACK AT OUTBOARD SIDE OF ACTUATOR HINGE FITTING ,1ST ROW, FWD HI-LOK, FROM DOUBLER EDGE TO HI-LOK. REMOVED AND REPLACED NR 6 SPOILER PANEL ASSY AS PER 747 MM 27-62-01.
NR 3 PACK CONTROL CIRCUIT BREAKER ON P6 PANEL TRIPPED AFTER TAKEOF. STRONG ELECTRICAL ODOR DETECTED NEAR POSITION E-L. SMELL DISIPATED AFTER 3 HOURS. CIRCUIT BREAKER NOT RESET
DURING CRUISE, LOSS OF FLUID NR 4 HYD SYSTEM. SYSTEM DEPRESSURIZED AT 2.0 GALS QUALITY. EDP TO SUPPLY OFF. FOUND NR 4 RUDDER CONTROL SHUTOFF VALVE FAILED. (LEAKED) REMOVED AND REPLACED NR 4 RUDDER SHUTOFF VALVE. OPS AND LEAD CHECK GOOD IAW MM. (K)
AIRCRAFT EMERGENCY LIGHT FLICKER MOST OF THE FLIGHT. FOUND SEVERAL PUSHED BACK PINS AT CONNECTOR EMERGENCY LIGHT PANEL. ACCOMPLISHED GROUND CHECK OK PER MM 33-51-10. (M)
EMERGENCY LIGHT FLICKER DURING FLIGHT. FOUND RELAYS ON EMERGENCY LIGHTS UNSECURED, RESECURED RELAYS OPS CHECK OK IAW MM 33-51-07. REMOVED AND REPLACED BOTH RELAYS ON EMERGENCY LIGHT CNTL PANEL LIGHTS OPS OK PER MM 33-51-07. (M)
DURING INCORPORATION OF SB 747-53A2459, FOUND CRACK AND OR ELONGATED FASTENER HOLES COMMON TO FRAMES AND UPPER DECK FLOORBEAM UPPER CHORDS AT BS 340/360. FLOORBEAM UPPER CHORDS AND WEBS REPAIRED PER SRM. AT BS 340, STOP DRILLED AND REPAIRED FRAME WEB. OPEN HOLE HFEC INSPECTED IMMEDIATELY ADJACENT TO THE REWORK AREA TO CONFIRM CRACK FREE CONDITION. AT BS 360, STOP DRILLED AND REPAIRED THE SHEAR DOUBLER. TRIMMED OUT THE FLOORBEAM UPPER DECK WEB AND THE FLOORBEAM UPPER DECK CHORD. HFEC INSPECTED ALL EXISTING HOLES TO CONFIRM CRACK FREE CONDITION BEFORE INSTALLING THE SPLICE PARTS. INSTALLED STRAP P/N 141U0048-45 PER SB 747-53A2459. REPAIR IS SUBJECT TO CONTINUOUS INSPECTIONS PER SB 747-53A2265/AD 91-11-01.
DURING SCHEDULE MAINTENANCE, FUSELAGE SKIN DAMAGE WAS FOUND ADJACENT TO THE CARGO DOOR. THE SKIN DAMAGE WAS REMOVED BY BLENDING OUT THE DAMGAE. NO FASTENERS WRE AFFECTED BY THE BLEND OPERATION. HFEC SURFACE INSPECTED TO ENSURE NO DEFECTS EXIST. BOEING ADVISED THE REPAIR WAS STRUCTURALLY SATISFACTORY AS PERMANENT REPAIR. BOEING NOTED THE REPAIR IS OUTSIDE THE SSID AREA, AND DOES NOT IMPACT SSID INSPECTIONS. (M)
AFTER ENG START, NR 1 AND 4 LOST HYD SYSTEM QTY. REPLACED BRAKE ACCUMULATOR AS PER MM 32-41-23. OPS AND LEAK CK NORMAL. RESTARTED NR 1 AND 4, HYD SYSTEM TO PROPER LEVEL.
DURING TAXI IN, SMELL OF SMOKE FROM THE AIR CONDITIONING SYSTEM. FLIGHT DECK FAN SWITCHED OFF WITH NO FURTHER SMELL. AFTER SHUTDOWN, UNABLE TO SWITCH FAN BACK ON. CIRCUIT BREAKER PULLED AND ITEM TRANSFERRED DMI M04-064. REMOVED AND REPLACED FLIGHT COMPARTMENT RECIRCULATION FAN IAW MM. OPERATION CHECK NORMAL. GOOD FOR SERVICE.
NR 2 ENGINE INDICATED FIRE ON APPROACH, SHOT BOTH BOTTLES, INDICATIONS CONTINUED. FOLLOWED FHB PROCEDURES FOR ENGINE FIRE CHECKLISTS. DISCHARGED FIRST BOTTLE, TIMED 30 SECOND LIGHT REMAINED ON. DISCHARGED SECOND BOTTLE, LIGHT REMAINED ON. B-LOOP REMAINED OFF SCALE HIGH. INSPECTED ENGINE FOUND NO EVIDENCE OF FIRE, FOUND BOTH A AND B LOOPS SHORTED TO LOCAL GROUND. REPLACED B LOOP UPPER AND REPAIRED SHORT, OPERATION CHECK OK PER MM 26.
INFLIGHT ENGINE SHUTDOWN, NR 2 ENGINE WAS SHUTDOWN DUE TO FIRE DETECTION LIGHT AND FAULT LIGHT. NR 2 FIRE DETECTION 'A' LOOP WOULD NOT TEST. COMPLETED ENGINE SHUTDOWN CHECKLIST. HYDRAULIC SYSTEM SHUTDOWN FOR 20 MINUTES. INCIDENT TIME FRAME, AIRCRAFT DEPARTED ANC 22:15Z. IRREGULARITY OCCURRED 07:15Z. AIRCRAFT BLOCKED IN AT PVG TO 07:48Z. FOR NR 2 ENGINE FIRE DETECTION 'A' CORRECTIVE ACTION, REF WDW WIRING CHECK FOR INSULATION AND RESISTANCE, FOUND OK. CLEANED ALL ELEMENT CONNECTORS. INSTALLED BACK. GROUND TEST OK PER MM 26-11-02. (M)
DURING CURRENT C-CHECK AT SIA, FOUND NR 2 PYLON R/S SKIN WRINKLED TWO PLACES FROM 1) NAC 286 TO 300 AT STR 5, 2) NAC 300 TO 316 AT STRINGER6. REPAIR AREA (1) CUTOUT EXISTING DAMAGE IN FLAT BAY AREAS ONLY. HFEC INSPECTED ALL OPEN HOLES, CUT EDGES AND ADJACENT STRUCTURE FOR CRACKS AND TEMPER LOSS. NO DAMAGE OR TEMPER LOSS FOUND. FABRICATED ADDITIONAL DOUBLER AND TRIPLER SPLICE PLATE. INSTALLED PER SRM STANDARD PRACTICES. (2) SKIN WRINKLE IS SMOOTH AND ROUND AND DOES NOT EXCEED .050 INCH DEEP. HFEC INSPECTED AREA AS ABOVE. NO DEFECTS OR TEMPER LOSS. NO REPAIR REQUIRED IN AREA 2 BUT IT MUST BE INSPECTED AT EVER 'C' CHECK NOT TO EXCEED 18 MONTHS, REF SRM 51-10-01 AND 54-31-03. (M)
DURING CURRENT C-CHECK AT SIA, FOUND RT WING LE BEAM WEB CRACKED AT OLES 1200. CRACK REMOVED BY CUTTING THE WEB AT OLES 1190 AND DISCARDING THE INBOARD SECTION FROM OLES 1190 TO 1200. PERFORMED HFEC INSPECTION OF CUT EDGE TO ENSURE CRACK FREE CONDITION. NO ADDITIONAL CRACKING FOUND. FABRICATED REPLACEMENT WEB AND REINFORCING DOUBLERS. INSTALLED REPLACEMENT PARTS WITH REVETS PER SRM 57-20-03 FIG 7. (M)
DURING CURRENT C CHECK, FOUND LT STABILIZER REAR SPAR CORRODED AT STABILIZER B/L 372, STA 550. NO ESTABILISHED LEVEL OF CORROSION DECLARED SINCE ITEM DISCOVERED DURING ROUTINE INSPECTION. REMOVED EXISTING SPAR SPLICES LOCATED AT STAB STA. 525 AND 570. REMOVED SPAR SECTION TO EXISTING SPLICES. FABRICATED REPLACEMENT SPAR SECTION, SPLICE STRAP SEGMENTS AND FILLER STRIPS. INSTALLED REPAIR PARTS IAW SRM.
DURING CURRENT C-CHECK AT SIA, FOUND BS 1241 L/S KICK FITTING AT BOLT HOLE NR 11 CRACKED IN WING SKIN ONLY. REAMED HOLE TO 1.169 INCH. NO CRACK INDICATION. FINAL REAMED HOLE TO 1.284 INCH IN WING SKIN AND CHORD. REAMED STRINGER SPLICE FITTING TO 1.126 INCH. FABRICATED INDIVIDUAL BUSHINGS FOR WING SKIN, RIB CHORD AND STRINGER FITTING. FABRICATED FILLER BLOCK TO TRAP WING SKIN BUSHING. INSTALLED BUSHINGS AND FILLER BLOCK IAW SB 747-57A2314 REV 1. REPETITIVE INSPECTION REQUIRED AT 8000 CYCLES OR 25000 HOURS WHICH EVER OCCURS FIRST. (M)
DURING INSPECTION, FOUND FRAME STATION 420 CRACKED AT STRINGER 14 (E)L AND STRINGER 15L AT THE SHEAR DOUBLER COMMON TO THE STRINGER CUTOUT. TRIMMED AWAY TWO FASTENER ROWS OF THE OUTBOARD REINFORCING ANGLE. STOP DRILLED CRACKS. FABRICATED FILLER, DOUBLERS AND REPAIR ANGLE, INSTALLED PER STANDARD PRACTICES. REINSPECT AREA PER SB 747-53A2265 AT 3000 CYCLE INTERVALS. (M)
DURING INSPECTION FOUND FRAME STATION 480 CRACKED AT STRINGER 14R COMMON TO THE CUTOUT. STOP DRILLED CRACK. FABRICATED REPAIR DOUBLER AND INSTALLED PER STANDARD PRACTICES IAW SRM 53-10-04. REINSPECTION TO BE ACCOMPLISHED AT 3000 CYCLES AND REPETITIVE AT 3000 CYCLES UNTIL 747-53-2272 IS INCORPORATED AT THE 20000 CYCLE LIMIT. (M)
DURING HFEC INSPECTION, FOUND THE LOWER AFT CARGO COMPARTMENT DOOR CUT-OUT, UPPER FORWARD CORNER SKIN CRACKED. CRACK TRIMMED AWAY. FILLER AND REPAIR DOUBLERS FABRICATED AND INSTALLED PER STANDARD PRACTICES IAW SRM 53-30-03 FIG 60, TYPE II. REINSPECTION IS REQUIRED AFTER INSTALLATION OF REPAIR AT 15,000 CYCLES INITIAL AND REPETITIVLY AT 3000 CYCLES THEREAFER. (M)
DURING INSPECTION, FOUND FRAME DOUBLER AND CLIP COMMON TO STATION 500 CRACKED AT STRINGER 10A (L) AND 11L. FABRICATED DOUBLERS AND INSTALLED PER STANDARD PRACTICES IAW SRM 53-10-04. CLIP REPLACED. REINSPECT AREA PER SB 747-53A2265 AT 3000 CYCLE INTERVALS. (M)
DURING INSPECTION, FOUND MAIN DECK FLOOR LINE INTERCOSTALS FROM STATION 340-380 LEFT CRACKED AT NUMEROUS FASTENER HOLES. TRIMMED OFF SHEAR TIES CONTAINING CRACKED FASTENER HOLES. PERFORMED HFEC INSPECTION AT CUT LINE TO ENSURE NO CRACKS. NO CRACKS FOUND. FABRICATED REPAIR ANGLES, INSTALLED PER STANDARD SRM PRACTICES. (M)
DURING INSPECTION, FOUND FRAME WEB AND DOUBLER STATION 440 CRACKED AT STRINGER 13R, CRACK ENDS IN EXISTING FASTENER LOCATION. PERFORMED OPEN HOLE HFEC INSPECTION TO ENSURE CRACK CONTAINMENT. FABRICATED DOUBLERS AND FILLERS. INSTALLED PER STANDARD PRACTICES IAW SRM 53-10-04. REINSPECT AREA PER SB 747-53A2265 AT 3000 CYCLE INTERVALS. (M)
DURING INSPECTION, FOUND FRAME WEB DOUBLER STATION 420 CRACKED AT STRINGER 16L COMMON TO THE STRINGER CUT-OUT. CRACK NOT STOP DRILLED DUE TO CRACK PROXIMITY TO EDGE OF THE PART. FABRICATED DOUBLER AND INSTALLED PER STANDARD PRACTICES IAW SRM 53-10-04. REINSPECT AREA PER SB 747-53A2265 AT 3000 CYCLE INTERVALS. (M)
DURING INSPECTION, FOUND FRAME AND DOUBLER STATION 520 CRACKED AT STRINGER 10A (L) AND 11L COMMON TO THE STRINGER CUT-OUT AT 10A(L) AND 11L. FABRICATED DOUBLERS AND INSTALLED PER STANDARD PRACTICES IAW SRM 53-10-04. CLIP REPLACED. REINSPECT AREA PER SB 747-53A2265 AT 3000 CYCLES INTERVALS. (M)
DURING INSPECTION, FOUND FRAME WEB STATION 220 CRACKED AT STRINGER 14R, 1.2 INCH COMMON TO THE TRIANGULAR CUTOUT. STOP DRILLED CRACK. PERFORMED OPEN HOLE HFEC INSPECTION TO ENSURE CRACK CONTAINMENT IN STOP HOLE. FABRICATED DOUBLER AND INSTALLED PER STANDARD PRACTICES. REINSPECT AREA PER SB 747-53A2265 AT 3000 CYCLES INTERVALS. (M)
DURING HFEC INSPECTION, FOUND FRAME STATION 800 CRACKED AT STRINGER 17R COMMON TO THE AFT INNER CHORD AT A FASTENER HOLE. TRIMMED OUT CRACK. FABRICATED FILLER AND REPAIR STRAPS AND INSTALLED PER STANDARD PRACTICES IAW SRM 53-10-04 FIG 114. HFEC (FLAT SURFACE) REINSPECTION TO BE ACCOMPLISHED OF THE ENTIRE STACK UP AND SURROUNDING AREA AT 3000 CYCLE INTERVALS. (M)
ATB - FLT 3120 - CREW HEARD A LOUD BANG FROM RIGHT SIDE OF AIRCRAFT, THEN NR 4 ENGINE SHUTOFF. UPON RETURN TO LAX, IT WAS DISCOVERED THAT NR 4 ENGINE TURBINE SECTION HAS FAILED AND THE ENGINE HAS INTERNAL DAMAGE. SEVERAL BLADES FOUND DAMAGED DURING BORESCOPE INSPECTION. IN ADDITION, THE ENGINE CASE WAS DAMAGED. REPLACED NR 4 ENGINE AND PERFORMED ALL APPLICABLE INSPECTINS AND MAINTENANCE CHECKS. NO ABNORMALITIES OBSERVED. ENGINE RUN UP SATISFACTORY. (M)
FLT 9027 - BOM-MAA - NR 2 ENGINE FLAME OUT AT FL370. ALL ENGINE INDICATIONS WERE NORMAL AND ENGINE WAS RUNNING FINE. ACCOMPLISHED IN FLIGHT RESTART AT FL290. MAINTENANCE CHECKED ENGINE INLET AND EXHAUST AREA AND NO DEFECTS WERE FOUND. INSPECTED ENGINE TUBING AND CABLES, PUSH PULL RODS, ETC AND LL OK. REPLACED FUEL FILTER AS PRECAUTION. PERFORMED ENGINE RUN UP AND ALL OK. NO PREVIOUS HISTORY. (M)
FOUND NR 3 LEFT/RIGHT MAIN ENTRY DOOR FRAME CRACKED AT BS 1265. LEFT CRACKED 1.6875 INCH ON EACH SIDE OF RIVET. PER BOEING SB 747-53A2416 TRIMMED OUT CRACKED AREA AND FILLER REPAIRED FRAME. REFERENCE KLM DRAWING KLM-AMS-99-0913RE FOR REPAIRS UP TO 3 INCHES. (M)
RIGHT STATION 1480 BULKHEAD CORROSION REPAIR COMMON TO STRINGER 38R. FOUND HOLES NR 2, 3, 5, 7, AND NR 10 CRACKED. REAMED HOLES OVERSIZE, ALL WITHIN LIMITS PER SB 747-53A2390. OVERSIZED FASTENERS INSTALLED. (M)
LEFT STATION 1480 BULKHEAD CORROSION REPAIR COMMON TO STRINGER 38L. FOUND HOLES NR 3, 4, 7, 8, 9, 10 AND NR 11 CRACKED. REAMED HOLES OVERSIZE, AND INSTALLED BUSHING REPAIRS AT LOCATION NR 3, 7, 8, 9, 11. OVERSIZED FASTENERS INSTALLED PER SB 747-53A2390. (M)
LEFT STATION BULKHEAD CHORD SPLICE FITTING 65B14682-3 FOUND TOOLING MARKS DURING DISASSEMBLY. PER BOEING TELEX TLS-TPE-00-00047F, BLEND ALL TOOLING MARKS. ALL TOOL MARKS BLENDED. (M)
SURFACE CORROSION DETECTED CENTER SECTION REAR SPAR LEFT/RIGHT. CORROSION MAPPED, MEASURED, CLEANED AND TREATED BY BOEING FIELD TEAM. ALL WITHIN LIMITS. AREAS OF REWORK ARE; LEFT FASTENERS NR 7, 8, 9, RIGHT FASTERNERS NR 2, 3, 4, 5, 6, 7, 8, 9, 13, 14, 23 AND 25. REFERENCE SB 747-57-2263. (M)
FOUND CORROSION ON WING CTR SECTION REAR SPAR RBL 99, COMMON TO REAR BULKHEAD FITTING AND INBOARD WEB OF LEG TO TWO BOLT HOLES WHILE PERFORMING SB 747-57-2263. CLEANED, TREATED, MEASURED CORROSION. APPLIED FINISH. ALL WITHIN ACCEPTABLE LIMITS. (M)
DURING INTERNAL INSPECTION OF PYLON NR 1, NR 2, NR 3 STRUCTURE SURROUNDING THE PRECOOLER EXHAUST EXIT AREA FOUND METAL DISCOLORED AND EXTERNAL SKIN CREASED. OVER TEMPERATURE ANALYSIS INDICATED TEMPER LOSS AND HEAT RELATED DAMAGE. AFFECTED STRUCTURE AND SKIN SECTIONS REPLACED PER SB 747-54A2158 REV 2; 747-54-2163 REV 1. PYLON STRUT MOD EMBODIED. (M)
ORD/MXP - FLT AZ9163/02 - DURING CLIMB-OUT AT 4,000 FEET, NR 4 ENGINE NACELLE TEMPERATURES INDICATED 7.6 DEGREES ON BOTH 'A' AND 'B' LOOPS. TEMPERATURE DECREASED WHEN THROTTLE WAS RETARDED. CLOSED BLEED VALVE ACCORDING TO FHB PROCEDURE. AS NR 4 THROTTLE WAS ADVANCED, TEMPERATURE STARTED TO CLIMB. JETTISONED 40,000 KGS OF FUEL. RETURNED TO ORD, LANDING WAS UNEVENTFUL. MAINTENANCE INSPECTION OF NR 4 ENGINE REVEALED A FRACTURED 14TH STAGE BLEED MANIFOLD P/N 906M87G02. MANIFOLD REPLACED. ENGINE RUN-UP CHECKS NORMAL. (X)
FLT 7127 - MIA/VCP - NR 4 CSD OIL LIGHT 'ON', CSD OIL TEMPERATURE HIGH (OUT OF RANGE 150 PLUS). ATTEMPT TO DISCONNECT CSD UNSUCCESSFUL. CSD RPM '0', PMG VOLTS '70'. FOLLOWED ALL DISCONNECT PROCEDURES THEN SHUTDOWN NR 4 ENGINE. ON ARRIVAL AT VCP MAINTENANCE FOUND NR 4 CSD DEFECTIVE. REPLACED NR 4 CSD, OPERATIONAL CHECK NORMAL. (M)
DURING MAINTENANCE SERVICE AT MIA, DISCOVERED THE EGT PROBE AND WELDED BOSS AT THE 12 O'CLOCK POSITION ON NR 4 ENGINE CASE NEAR THE AFT ENGINE MOUNT WAS MISSING. EXHAUST AIR ESCAPING THROUGH THE RESULTING HOLE IN THE CASE CAUSED DAMAGE TO THE AREA AND STRUT. THERE WERE NO FIRE WARNING DISCREPANCIES DOCUMENTED IN THE AIRCRAFT MAINTENANCE LOG. REQUESTED BOEING SURVEY TEAM TO EXAMINE ENGINE/PYLON. BOEING DETERMINED THAT PYLON CHANGE WAS REQUIRED. PYLON S/N OFF RN 000124, S/N ON RN 000265, ENGINE S/N OFF 517718, S/N ON 517589. (X)
CREW REPORTS: MAINTENANCE LOG ITEM NR 1 - AFTER TAKEOFF, CAPTAIN'S AND FIRST OFFICER'S ALTIMETER SPLIT. WITH INCREASE IN ALTITUDE, THE SPLIT BECAME WORSE. CAPTAIN'S ALTIMETER 24,500 FEET, FIRST OFFICER'S ALTIMETER 20,000 FEET. MAINTENANCE LOG ITEM NR 2 - AFTER TAKEOFF, CAPTAIN'S AND FIRST OFFICER'S AIRSPEED AND MACH INDICATORS SPLIT. SPLIT BECAME WORSE WITH ALTITUDE. CAPTAIN'S 350 KNOTS, .844, FIRST OFFICER'S 300 KNOTS, .65. FOUND FIRST OFFICER'S VSI INDICATOR AT FAULT (INTERNAL LEAK). REPLACED FIRST OFFICER'S VSI INDICATOR. OPERATIONAL CHECK OF CAPTAIN'S AND FIRST OFFICER'S AIR DATA SYSTEM NORMAL. (X)
LGW/LGW - FLT BA3571/20 - AIRCRAFT ABORTED TAKEOFF, APPROXIMATELY 140 KNOTS, GROSS WEIGHT 365,000 KGS DUE MASTER FIRE WARNING AND BELL SOUND. CREW EVACUATED AIRCRAFT PER FIRE CHIEF INSTRUCTIONS DUE TO BRAKE FIRE. AIRCRAFT INSPECTION REVEALED 8 BLOWN MAIN GEAR TIRES, NR 4 ENGINE REVERSER DOORS DAMAGED. FIRE WARNING ATTRIBUTED TO RUPTURED STAGE 14 PNEUMATIC ENGINE DUCT, NR 4 ENGINE POSITION. REPLACED STAGE 14 DUCT ASSEMBLY, LT AND RT REVERSER HALVES, ALL WHEEL AND BRAKE ASSEMBLIES, 2 FIRE WARNING CARDS. AIRCRAFT OPS CHECKS OK. (X)