N608AW

Part: FRAME — CRACKED (FUSELAGE)

SUB FRAME CRACK ON ATTACH FLANGE FRAME 33BY BETWEEN STR 11 AND 12 LT. MAINTENANCE REQUESTED REPAIR FROM BAE SYSTEMS REF AVMAX FAX 6008-2049004.

Part: SKIN — SCRATCHED (FUSELAGE)

SKIN SCRATCH LT FUSELAGE BELOW CABIN WINDOW BETWEEN FRAMES 30 AND 31 JUST ABOVE STR 14L. MAINTENANCE REQUESTED REPAIR FROM BAE SYSTEMS REF AVMAX FAX 608-2049005.

Part: SKIN — DAMAGED (LT WING)

CHAFE DAMAGE TO THE LT WING UPPER SKIN MAX DEPTH OF DAMAGE IS .028 INCH. MAINTENANCE REQUESTED REPAIR FROM AVMAX FAX 608-2049001.

Part: BOTTLE — DISCHARGED (PAX OXYGEN SYS)

FOUND FORWARD CABIN BULKHEAD PASSENGER OXYGEN BOTTLE EMPTY. REMOVED AND REPLACED BOTTLE. (M)

Part: AXLE — VIBRATION (MLG)

AIRCRAFT EXPERIENCED VIBRATION AFTER LANDING. MAINTENANCE REMOVED AND REPLACED RT MLG AXLE.

Part: HINGE BRACKET — BROKEN (RT MLG DOOR)

RIGHT MLG DOOR HINGE BROKEN MAINTENANCE REPLACED RIGHT MLG DOOR AFT HINGE BRACKET. RETRACTION CK COMPLIED WITH ON W/C. (M)

Part: RIVET — BROKEN (FUSELAGE)

6TH RIVET ABOVE PAX WINDOW AT FRAME STATION 755.48, RIVET MISSING HEAD. MAINTENANCE INSTALLED BLIND CHERRY-MAX FASTENER. (M)

Part: CONTROLLER — MALFUNCTIONED (CABIN PRESSURE)

PRESSURIZATION WAS ABNORMAL AFTER TAKEOFF, UNABLE TO CONTROL. CORRECTIVE ACTION IN PROGRESS.

Part: FUEL CONTROL — MALFUNCTIONED (NR 2 ENGINE)

NR 2 ENGINE FLAMED OUT DURING CRUISE FLIGHT. EMERGENCY CHECKLIST COMPLIED WITH. ENGINE WINDMILLED FOR 10 TO 15 MINUTES. REMVOED AND REPLACED FUEL CONTROL IAW AMM 73-20-01-401. REMOVED AND REPLACED OVERSPEED VALVE, UNDER FURTHER INVESTIGATION. (M)

Part: SKIN — DENTED (AIR BRAKE)

DENT IN LT AND RT AIR BRAKE OUT OF LIMITS OF SRM. REPAIR REQUESTED FROM BAE SYSTEMS REF AVMAX FAX 1538-6080004. (M)

Part: SKIN — DENTED (WING)

DENT MAPPING 8 DENT OUT OF LIMITS OF SRM. REPAIR REQUESTED FROM BAE SYSTEMS, REF AVMAX FAX 1538-6080002. (M)

Part: FLAP TRACK — WORN (NR 1)

FLAP TRACK WEAR NR 2 RIGHT, NR 1 RIGHT AND LEFT NR 1. REPAIR REQUESTED FROM BAE SYSTEMS REF AVMAX FAX 1538-6080003. (M)

Part: FUSE — MALFUNCTIONED (HYD SYSTEM)

RIGHT MLG FAILED TO RETRACT ON TAKEOFF. RECYCLED 3 TIMES. MAINTENANCE REPLACED RIGHT HYDRAULIC FUSE. (M)

Part: FLAP — BLOCKED (LEFT)

ZERO FLAP LANDING. REF FLAP FAULT WARNING. TOUCHDOWN SPEED, 157. BRAKES APPLIED, 100, BRAKE TEMPS , 470, BRAKE FANS OPERATING, NORMAL BRAKES WERE APPLIED, 70,000 LBS LANDING WEIGHT. MAINTENANCE FOUND LT SIDE BLOCKED, CLEARED BLOCKED CONDITION WITH BUMP BOX, OP CHECK GOOD.

Part: CONNECTOR — DIRTY (RT MLG UPLOCK)

RIGHT MLG UPLOCK INDICATOR ILLUMINATED IN FLIGHT, CYCLED GEAR PER MX CONTROL, LIGHT REMAINED ON. CLEANED ELECTRICAL CONNECTOR ON RIGHT MLG UPLOCK ASSY, C/W 3 GEAR SWINGS, NO DEFECTS NOTED. (M)

Part: PIN — CRACKED (NOSE GEAR RAM)

MAGNETIC PARTICLE INSPECTION OF NOSE GEAR RAM ATTACHMENT PIN FOUND TO BE CRACKED. REMOVED AND REPLACED PIN AND INNER BOLT. (M)

Part: PIN — CRACKED (MLG)

PERFORMED MAG PARTICLE INSPECTION OF NOSE GEAR RAM ATTACHMENT PIN AND FOUND TO BE CRACKED. REMOVED AND REPLACED PIN AND INNER BOLT. (M)

Part: FUEL CONROL — FAILED (NR 2 ENGINE)

COS/DEN - FLT 5568 - UNCOMMANDED ROLL BACK ON NR 2 ENGINE, ABORTED TAKEOFF. REMOVED AND REPLACED NR 2 FUEL CONTROL UNIT. FUEL CONTROL UNIT TSR 3166 CSR 3553. PART TOTAL CYCLES, 19,244. (X)

Part: B-NUT — LOOSE (APU)

AT GATE BEFORE DEPARTURE, WHEN CREW DID PREFLIGHT, STRONG FUEL SMELL IN CABIN AND COCKPIT WITH APU BLEED AIR ON. FOUND APU FUEL SOLENOID B-NUT LOOSE, LEAKING FUEL, TIGHTENED PERFORMED PACK BURNOUT. NO SMELL NOTED. (M)

Part: AIR DIST — ODOR (CABIN)

CAUSTIC FUMES IN CABIN WITH BLEED AIR SUPPLYING PACKS, NO NOTICEABLE ON APU AIR. PERFORMED PACK BURNOUT PER MM. RAN PACKS WITH ENGINE AIR, NO NOTICEABLE SMELL. (M)

Part: LIGHT — ILLUMINATED (RUDDER)

DEN - FLT 5669 - AFTER TAKEOFF, RUDDER LIMITER LIGHT ILLUMINATED ON MWS PANEL. LIGHT EXTINGUISHED ON SHORT FINAL. PERFORMED OPS CHECK OF AIR SPEED SWITCH IAW BAE AMM 27-21-61.

Part: TMS COMPUTER — FAILED (NR 1 ENGINE)

FLT 5581 - NR 1 ENGINE FAILED IN FLIGHT. ZERO OIL PRESSURE ALONG WITH RELATED MWS ANNUN, 15 MINUTE WINDMILL. N1 22.5 PERCENT N2 12 PERCENT, OIL TEMP AND QTY AND OTHER RELATED ENGINE INSTRUMENTS APPEARED NORMAL. REMOVED AND REPLACED TMS COMPUTER, HP FUEL FILTER INSPECTED AND REPLACED PER AMM. (M)

Part: WARNING HORN — MALFUNCTIONED (COCKPIT)

DEN - FLT 439 - ON TAKEOFF, LANDING GEAR HORN SOUNDED ON RETRACTION. AFTER RECEIVING CLE, RT MLG SHOWED UNLOCKED, GEAR EXTENDED NORMALLY, AND DOWN INDICATION WAS NORMAL. INSPECTED, SWUNG GEAR, COULD NOT DUPLICATE. REPLACED PCB GJ21 AND GJ23 AS A PRECAUTION. OPS CHECKED GOOD.

Part: ANGLE — CRACKED (FRAME 36)

FRAME 36 AFT CARGO BAY FREIGHT ANGLE IS CRACKED AND ALSO CORRODED ON RIGHT SIDE. REMOVED AND REPLACED FREIGHT ANGLE ON FRAME 36 RIGHT SIDE IN AFT CARGO BAY. (M)

Part: DOOR — CRACKED (NR 2 ENG COWL)

NR 2 ENGINE AFT OUTBOARD COWL DOOR INNER TITANIUM BAFFLE IS CRACKED AT FORWARD UPPER ATTACH RIVET, CRACKED AT FORWARD LOWER ATTACH RIVETS AND CRACKED AT AFT LOWER ATTACH RIVET. REPAIRED SAID CRACKS BY PATCHING IAW AIR WIS/BAE SRM CHAPTER 54 NACELLES/PYLONS. (M)

Part: SKIN — LIGHTNING STRIKE (FUSELAGE)

REF FAX DJR/RJO841-97, LIGHTNING STRIKE SKIN DAMAGE DETAILED IN AWAC FAC LM244-97 TO BE REPAIRED 35375 TCA OR NEXT HEAVY CHECK RUBBINGS SUBMITTED AVRO 11-24-97. REPAIRED LIGHTNING STRIKE DAMAGE FRAMES 10, 12 AND 16. ALL OTHER AREAS HAVE BEEN P/C/W. GEN W/C TO REINSPECT AT FRAME 16 AND 26. REF FAX JM/RJ0348-98 ISS 2. W/C GEN FOR CONDUCTIVITY CHECKS AND EDDY CURRENT TESTS AROUND AREAS FRAME 48-98 ISS 2. W/C GEN FOR CONDUCTIVITY CHECKS AND EDDY CURRENT TESTS AROUND AREAS. (M)

Part: FRAME — CRACKED (LT WING/FUS)

LEFT WINGROOT FORWARD FAIRING SUPPORT FRAME CRACKED IN FLANGE AT FRAME 26. C/W SRM 51-71, REPAIR TO CRACKED CORNER FLANGE USING .040 2024-T3 AN 8 AD RIVETS. (M)

Part: SKIN — DENTED (FUSELAGE)

REF AVRO FAX DJR/RJ1182-96, C/W DV INSPECTION OF TWO SHALLOW DENTS ON FORWARD RIGHT FUSELAGE AT FRAME 8, 55 INCHES BELOW HORIZONTAL DATUM. REINSPECTED EVERY 3000 CYCLES, REPORT ANY ADVERSE FINDINGS TO BAE PRIOR TO FLT. CURRENT TC 34450, DUE BY 37450 TC. REPAIRED DENTS IAW BAE FAX REF DJH/RJO335-98 AND BAE SRM 53-10-12 FIG 202. (M)

Part: SKIN — LIGHTNING STRIKE (FUSELAGE)

REPAIR CRACK FROM LIGHTNING STRIKE DAMAGE ON LEFT FUSELAGE SKIN JUST AFT OF FRAME 26 JUST UNDER JACK PAD. REPAIR WITHIN 590 CYCLES OF ORIG FINDING. DUE AT 35337, CURRENT TAC 34779. BLENDED CRACK IAW BAE FAX, REF DJR/RJO325-98. W/C GEN FOR CONTINUED INSPECTION AT 400 FLT INTERVALS. PERFORMED ET ABOVE BLENDED AREA. (M)

Part: SKIN — LIGHTNING STRIKE (FUSELAGE)

PERFORM DV INSPECTION OF LIGHTNING STRIKE DAMAGE CRACK AT LEFT FUSE FRAME 26 JUST UNDER JACK PAD. REF FAX DJR/RJO134-98, REPORTING ADVERSE FINDINGS TO RDO BEFORE FLIGHT. DUE EACH 60 CYCLES, CURRENT CYCLES 35012, DUE BY 35072. BLENDED CRACK IAW BAE FAX DJR/RJO325-98. W/C GEN FOR CONTINUED INSPECTION AT 400 FLT INTVLS. PERFORMED ET ON ABOVE BLENDED AREA. (M)

Part: SKIN — DENTED (FRAME 35)

REINSPECT FUSELAGE DENT 6 INCHES FORWARD OF FRAME 35, AT STRIGNER 22 RIGHT, JUST BELOW FLEET NUMBER, CURRENTLY A CLASS A DENT. REINSPECTED EVERY 3000 FLIGHTS. CURRENT TCA 33234. REINSPECT BY 36234. REPAIRED DENT IAW BAE SRM 53-00-12 FIGURE 202. NO FURTHER REINSPECTS REQ'D. (M)

Part: SKIN — DENTED (CARGO DOOR)

REPAIR DENTS IN FORWARD CARGO DOOR WITHIN 500 CYCLES. CURRENT TAC 34819, DUE AT 35319 TAC. REPAIRED DENTS IN FORWARD CARGO DOOR PER BAE FAX DJH/RJ0311-98 AND SRM 52-32-11 FIG 201. GEN W/C TO ACCESS OTHER DENTS ON FORWARD CARGO DOOR. (M)

Part: BRACKET — CRACKED (FRAME)

TWO BRACKETS, CRACKED IN 2 CORNERS EACH, LOCATED UNDER FLOOR BETWEEN FRAMES 40 AND 41 AND SUPPORT BOXES FOR RED LIGHTS FOR DOOR OPEN AND CLOSED. BLENDED OUT CRACKED AREA, INSTALLED DOUBLER AT EACH LOCATION IAW BAE SRM. (M)

Part: FLOORBEAM — CORRODED (FRAME 12-18)

DV INSPECTION FLOORBEAMS AND SUPPORT STRUCTURE FRAME 12 TO 18 W/VEST FLOOR PANELS ONLY REMOVED SII. REPORT FINDINGS FORM M046 (SII 53-10-128) ACCESS 221DF, 221EF, 221FF, 221HF222AF. PERFORMED DV INSPECTION FLOORBEAMS AND SUPPORT STRUCTURE FRAME 12-18, FOUND CORROSION ON FORWARD PAX DOOR SILL PLATES 1ST SCREWHOLE AND CORROSION 2 GUSSET PLATE. (M)

Part: CRACKED (RT WING)

RIGHT WING TOP SKIN INBOARD STIFFENER CRACKED AT FORWARD END BETWEEN RIBS 8/9. REPLACED RIGHT WING TOP SKIN STIFFENER BETWEEN RIBS 8/9. (M)

Part: RIB — CRACKED (NR 1 PYLON)

NR 1 PYLON INBOARD RIB NR 1 NUTPLATE AREA CRACKED. REPAIRED ABOVE DAMAGE TO INBOARD NR 1 PYLON NUTPLATE MOUNT STRIP FOR PANEL 451AT PER RIL HC546H9017, SEE WO BX5024 FOR REPAIR PIECE HEAT TREAT AND PLATING. (M)

Part: SILL — BROKEN (FRAME 44)

AFT VESTIBULE FLOOR SUPPORT STRUCTURE ON LEFT SIDE UNDER TOILET HAS THE AFT END OF THE SILL PLATE NEAR FRAME 44 CORRODED AND BROKEN. REMOVED AND REPLACED SILL PLATE, LEFT SIDE UNDER LAV MODULE BETWEEN FRAME STRINGER 43/44. (M)

Part: SKIN — DENTED (FUSELAGE)

REF SRM 53-00-00 PAGE 104 FIG 101 ZONE B. REINSPECTED DENT BETWEEN FRAME 19 AND 20 ON RIGHT FUSELAGE ABOVE LAP JT EACH 300 CYCLES. CURRENT CYCLES 35012, DUE BY 35312. REPAIRED IAW BAE SRM 53-00-12 FIG 202. DENT AT FRAME 20-20A. NO FURTHER REINSPECTION REQ'D. (M)

Part: FLOORBEAM — CORRODED (FRAME 41-44)

DV INSPECTION FLOORBEAMS AND SUPPORT STRUCT FRAME 41-44. ACCESS UNDER FLOOR THROUGH 181HL/181HR EVIDENCE OF LEAKAGE APPARENT UNDER TOILET/GALLEY, INSPECTION THROUGH 25 1AF/DF/EF/FF, 252AF/BF/CF/DF. SII REPORT FINDS FORM M046 (SII 53-30-154). PERFORMED DV INSPECTION FLOORBEAMS, SUPPORT STRUCTURE FRAME 41-44. FOUND SILL PLATE LEFT SIDE NEAR FRAME 44 CORRODED AND BROKEN. (M)

Part: TIRE — FAILED (NR 3 MLG)

NR 3 MLG TIRE TREAD DEPARTED ON TAKEOFF FROM DEN CAUSING DAMAGE TO RT MLG DOOR TRAILING EDGE AND VARIOUS IMPACT POINTS ON UNDERSIDE OF WING AND AFT FUSELAGE. A/C FERRY TO ATW FOR REPAIRS. (M)

Part: ANGLE — CRACKED (FUSELAGE)

ECS BAY LEFT SIDE AT FRAME 47 AT STRINGERS 8 AND 9, THE SHEAR ANGLE HAS A CRACK AT THE LOWER END IN THE BAND RADIUS THAT IS APPROXIMATELY .1562 INCH LONG. C/W REPAIR PER FAX REF JM/RJ0250-97 AND REPAIR DRAWINGS HC539H9014, SHEETS 1 THROUGH 4.

Part: ANGLE — CRACKED (FUSELAGE)

ECS BAY RT SIDE AT FRAME 48 BETWEEN STRINGERS 8 AND 11, THERE ARE THREE SHEAR ANGLES WITH CRACKS IN THEIR LOWER ENDS IN THE BEND RADIUS. CRACK NEAR STR 9 IS APPROXIMATELY .50 INCH LONG, CRACK NEAR STR 10 IS APPROXIMATELY .4372 LONG, AND THE CRACK NEAR STR 11 IS APPROXIMATELY .3437 INCH LONG. C/W REPAIR PER FAX REF JM/RJ0250-97 AND REPAIR DRAWINGS HC53.

Part: ANGLE — CRACKED (FUSELAGE)

ECS BAY RIGHT SIDE AT FRAME 47 BETWEEN STR 8 AND STR 9, THE SHEAR ANGLE HAS A CRACK AT ITS LOWER END IN THE BEND RADIUS THAT MEASURES APPROXIMATELY .1737 INCH LONG. C/W REPAIR PER FAX REF JM/RJ0250-97 AND REPAIR DRAWINGS HC539H9014 SHEETS 1 THROUGH 4.

Part: DOOR — CRACKED (PASSENGER COMPT)

REAR PASSENGER ENTRANCE DOOR, REAR EDGE MEMBER, SMALL CRACK INSIDE NEAR DAMPENER. REPAIRED SMALL CRACK IN SAID LOCK BY BLENDING IAW BAE FAX REF.JM/RF0215-97 DATED 2-27-97. PROTECTED BARE BLENDED METAL IAW STEP 3 OF ABOVE STATED FAX. NDT OF BLENDED REPAIR AREA ACCOMPLISHED ALT REPAIR GUIDE LINES AS OUTLINED IN FAX JM/RJ0326-95, DJR/RJ0345-95 AND POINT 2 FAX MS/RJ0475-93.

Part: RIVETS — MISSING (FUSELAGE)

FOUND ON LEFT SIDE OF AIRCRAFT FRAME 36 STR 20 AND STR 21, 5 RIVETS MISSING. INSTALLED HILOK FASTENERS AT FR 36 IAW BAE 146 SRM AND ATTACHED FAX JM/RJ0249-97.

Part: OXYGEN MASKS — CRACKED (CREW)

FORWARD VEST OXYGEN BOTTLES, 2 EACH, MASKS HAVE CRACKS IN MOUTH PIECE. REMOVED AND REPLACED MASKS IAW MM.

Part: OXYGEN MASK — TORN (CABIN)

OXYGEN MASK AT 2L, FACE PIECE TORN AND RE-BREATHER TORN. REPLACED MASK AT 2L, LEAK AND OPS CHECKS OK.

Part: OXYGEN BOTTLE — LOW FLOW (CABIN)

FORWARD VEST OXYGEN BOTTLE HAS LOW FLOW AT MEDIUM. REMOVED AND REPLACED OXYGEN BOTTLE. S/N OFF AW62. S/N ON AW92.

Part: CONTROL CABLE — WORN (LT AILERON)

LEFT WING AILERON INTERCONNECT SHEATHED CABLE IS WORN AND NEEDS TO BE CHANGED. REMOVED AND REPLACED LEFT WING SHEATHED CABLE, TENSIONED, AND SAFTIED. (GENERATED W/C NR 5039 FOR FUNCTIONAL CHECK OF THE AILERONS).

Part: CONTROL CABLE — WORN (RT AILERON)

SHEATH ON RT OUTER AILERON INTERCONNECT CABLE WORN FLAT, SEVERAL PLACES. REMOVED AND REPLACED RT OUTER INTERCONNECTER CABLE, TENSIONED AND SAFTIED. GENERATED W/C NR 5039 TO C/W FUNCTIONAL CHECK OF AILERONS.

Part: CONTROL CABLE — CORRODED (RT AILERON)

RIGHT WING AILERON INTERCONNECT NON-SHEATHED CABLE IS CORRODED AT THE BELLCRANK AND REQUIRES CHANGE. REMOVED AND REPLACED RIGHT WING NON-SHEATHED INTERCONNECT CABLE, TENSIONED AND SAFTIED. (GENERATED W/C NR 5039 TO C/W FUNCTION CHECK OF THE AILERONS).

Part: CONTROL CABLE — CORRODED (RT AILERON)

RIGHT AILERON CABLES CORRODED IN WING ROOT AT PULLEYS. RE-CHECK WHEN LOOSE FOR OUTER CABLE REPLACEMENT. REMOVED AND REPLACED CENTER SECTION FORWARD AND AFT INTERCONNECT CABLES, TENSIONED, AND SAFTIED. (GENERATED W/C NR 5039 FOR FUNCTIONAL CHECK OF THE AILERONS).

Part: CONTROL CABLE — CORRODED (LT AILERON)

THE LEFT MAIN AILERON CABLES ARE CORRODED ON PULLEY AT AIRCRAFT FRAME NR 24 WHERE CABLES EXIT THE FUSELAGE (CABLES REQUIRE CHANGING). REMOVED AND REPLACED BOTH LEFT CENTER FUSELAGE TO WING ROOT AILERON CABLES IAW MM. GENERATED W/C FOR FUNCTION CHECK.

Part: CONTROL CABLE — CORRODED (LT AILERON)

LEFT WING HAS TWO CORRODED AILERON CABLE ENDS AT THE CONTROL QUADRANT ON REAR SPAR BETWEEN RIBS 10 AND 11. REMOVED AND REPLACED BOTH LT OUTBOARD AILERON CABLES IAW MM. GENERATED W/C FOR FUNCTION CHECK.

Part: CONTROL CABLE — CORRODED (RT AILERON)

THE RIGHT MAIN AILERON CABLES ARE CORRODED ON PULLEY AT AIRCRAFT FRAME NR 24 WHERE CABLES EXIT THE FUSELAGE. CABLES REQUIRE CHANGING. REMOVED AND REPLACED BOTH RIGHT CENTER FUSELAGE TO WING ROOT AILERON CABLES IAW MM. GENERATED W/C FOR FUNCTION CHECK.

Part: CONTROL CABLE — CORRODED (RT AILERON)

RIGHT AILERON CABLES CORRODED AT BELLCRANKS IN OUTBOARD WING. REMOVED AND REPLACED BOTH RIGHT AILERON OUTBOARD CABLES IAW MM. GENERATED W/C FOR FUNCTION CHECK.

Part: FRAME — CRACKED (FUSELAGE)

FRAME 50, LOWER RIGHT CORNER, HAS A 1 INCH LONG CRACK AT THE RADIUS. NOTED CRACK WAS IN DIAPHRAGM AFT OF FRAME 50. REPAIRED DIAPHRAGM AFT FRAME 50, LOWER RIGHT CORNER IAW AVRO FAX DJR/RJ0122-97.

Part: PLATE — CRACKED (RT AIRBRAKE)

RIGHT AIR BRAKE TOP HINGE, TOP LONGERON HAS A CHAFE MARK ABOUT .030 INCH DEEP, 3 INCHES FROM AFT END, ALSO AFT GUSSET PLATE IS CRACKED. REPAIRED RIGHT AIR BRAKE TOP LONGERON (TOP HINGE POINT) AND GUSSET PLATE IAW AVRO FAX JM/RJ0183-97.

Part: FLOOR BEAM — CRACKED (CABIN)

MAIN LANDING GEAR FLOOR BEAMS 3, 5, 9, 15, AND 19, CRACKED AT FRAME 29, IN CABIN. REPAIRED FLOOR BEAMS IAW BAE RIL HC536H9211 AS LISTED ABOVE AT FR 29, BEAMS 3, 5, 9, 15, AND 19 AND FAX DJR/RJ0207-97.

Part: CONTROL CABLE — CORRODED (RT ELEVATOR)

THE RIGHT MAIN ELEVATOR CIRCUIT LEFT CABLE AT PULLEY JUST BELOW CABLE TENSIONED. COMPRESSOR IS BADLY CORRODED AND NEEDS TO BE REPLACED. REMOVED AND REPLACED CORRODED CABLE, TENSIONED TO PROPER SETTING AND SAFTIED. GENERATED NEW W/C TO C/W FUNCTIONAL TEST (WC NR 3048).

Part: CONTROL CABLE — CORRODED (LT ELEVATOR)

THE LEFT MAIN ELEVATOR CIRCUIT LEFT CABLE AT PULLEY JUST BELOW CABLE, COMPENSATOR IS BADLY CORRODED AND NEEDS TO BE REPLACED. REMOVED AND REPLACED CORRODED CABLE, TENSIONED TO PROPER SETTING AND SAFTIED. GENERATED NEW W/C TO C/W FUNCTIONAL TEST, WC NR 3048.

Part: O RING — LEAKING (NR 2 ENGINE)

NR 1 ENGINE, NR 2 OIL SCAVENGE LINE LEAK AT DIFFUSER, 5 O'CLOCK POSITION. REMOVED AND REPLACED O-RING. REFERENCE ENGINE INSTALLATION CHECK LIST FOR LEAK CHECK.

Part: INTERCOSTAL — CRACKED (CABIN)

SECOND INTERCOSTAL FROM RT SIDE FORWARD VESTIBULE AFT OUTBOARD ATTACH BRACKET A. STOP DRILLED .25 INCH CRACK AT BOTTOM. THIRD INTERCOSTAL A, STOP DRILLED .6250 INCH CRACK AT TOP SIDE. REPAIR AT 1,000 CYCLES. AFT INITIAL DUE AT 32,590 CYCLES. REPLACED THE CRACKED INTERCOSTAL (3RD FROM RT) WITH A NEW ONE AND REPLACED THE CRACKED ATTACH BRACKET ALSO ON THE AFT END OF SECOND INTERCOSTAL.

Part: FUEL MANIFOLD — LEAKING (NR 2 ENGINE)

NR 2 ENGINE HAS FUEL LEAKING FROM LOWER PORTIONS OF EACH MANIFOLD ON START, NOT EVIDENT DURING RUN. TRANSFERRED TO W/O BV 7244, RII.

Part: FUEL MANIFOLD — LEAKING (NR 3 ENGINE)

NR 3 ENGINE HAS FUEL LEAKING FROM LOWER PORTIONS OF EACH MANIFOLD ON START, NOT EVIDENT DURING RUN. REMOVED LT AND RT FUEL MANIFOLD. REPLACED SEALS AND INSTALLED BOTH MANIFOLDS. ENGINE ROBBED FOR ANOTHER, LEAK CHECK ON CHECKLIST RWR 2-14-97.

Part: SLIDE — NOT CHARGED (PAX DOOR)

ATW - FLT 514 - FA REPORTS THAT THE RIGHT FORWARD PASSENGER DOOR EVACUATION SLIDE CHARGE IS IN THE RED. CORRECTIVE ACTION: REMOVED AND REPLACED EVAC SLIDE, CHECKS BAD, GENERATED W/C FOR CONTINUATION OF MAINTENANCE. S/N OFF: 0397. S/N ON: 0627.

Part: ENGINE — MALFUNCTIONED (NR 1 & 2)

DSM - FLT 558 - IN ICE ABOVE 26,000 FEET, ALL 4 ENGINES ROLLED BACK TO 40-45 PERCENT. CREW SHUT DOWN NR 1 AND NR 2 DUE TO RISING TGT (APPROXIMATELY 900 DEGREES CELSIUS). NR 2 WAS RE-STARTED. NR 2, NR 3, AND NR 4 RECOVERED. LANDED WITHOUT INCIDENT DSM. MAINTENANCE TO CHARTER THE A/C IN AM.

Part: ENGINE — MALFUNCTIONED (NR 4)

PACK NR 2 EMITS A BLUE HAZE IN THE CABIN. AIRCRAFT FERRY TO ATW FOR TROUBLESHOOTING DUE TO HISTORY. REPLACED THE NR 4 ENGINE.

Part: AIR DISTR — SMOKE (CABIN)

FLIGHT ATTENDANT REPORTED SMOKE IN CABIN. WITH NR 1 A/C OFF SMOKE DISSIPATED, UNABLE TO DUP SMELL IN NR 1 OR NR 2 PACKS WITH APU OR ENGINE AIR AT THIS TIME.

Part: STIFFENER — CRACKED (BS 25.94)

BOTH INBOARD (LT/RT) STIFFENERS AT STATION 25.94 ON FRAME 29 IN HYD BAY ARE CRACKED. REPAIR STIFFENERS IAW EO E95/005/653. COMPLIED EO E95/005/653 ORIGINAL ISSUE AT LT/RT STATION 25.94 ON FRAME 29 STIFFENERS. (M)

Part: RAIL — CORRODED (AIRSTAIR DOOR)

ATW - FORWARD AIRSTAIR INBOARD RAIL FORWARD END, CORRODED BEYOND LIMITS. REMOVED AND REPLACED FORWARD AIRSTAIR INBOARD RAIL.

Part: SKIN — DENTED (FRAME 10)

REF LOG PAGE 21852/03, DENT ON LEFT SIDE OF FUSELAGE AT FRAME 10, ABOUT EVEN WITH CO-PILOT. FLOOR NEEDS PERMANENT REPAIR C/W BY 26997 TOTAL CYCLES. REF FAX AVRO NR DJR/RJ0221-95 AND DJR/RJ022295. COMPLIED WITH PERMANENT REPAIR IAW AVRO FAX REF NR DJR/RJ0224-95, SRM 53-10-12 FIG 202 AND 53-10-14 FIG 201.

Part: SKIN — DENTED (FUSELAGE LT)

DENT ON LEFT SIDE OF FUSELAGE ABOUT 1 FOOT ABOVE THE NUMERAL SIX. VISUAL INSPECTION OF SKIN, NO CRACKS NOTED, SEE LOG PG 21852 B LK 1 AND 2 FOR EDDY CURRENT INSPECTION, REF FAX DJR/RJ0221-95, DJR/RJ0222-95. AIRCRAFT OK TO CONTINUE IN SERVICE FOR 50 CYCL CURRENT 26947 CYC DUE AT 26997 CYC.

Part: DOUBLER — CORRODED (RAD ALT MOUNT)

CORROSION FOUND BETWEEN SKIN DOUBLERS ON RADIO ALTIMETER MOUNT RING AND FUSELAGE BELLY SKIN. (W)