N733DS

Part: COVER — LEAKING (NR 1 ENGINE) · airframe 58,111 hrs · 26,406 cycles

OIL QTY ON NR 1 ENGINE WENT TO ZERO AND OIL PRESS DROPPED INTO RED. SHUT DOWN ENG AT 1925Z. (ENG SHUT DOWN 18 MIN PRIOR TO LANDING). OIL TEMP REMAINED THE SAME AS OTHER ENGS. FOUND OIL LEAK AT TOP OF ANGLE GEARBOX MATING SURFACE. REPLACED INPUT DRIVE COVER ASSEMBLY.

Part: BATTERY — DISCHARGED (PAX DOOR) · airframe 57,822 hrs · 26,316 cycles

EMERGENCY FLASHLIGHT BATTERY LOW AT ATTENDANT SEAT L-1. REPLACED SAME.

Part: SEAL — BLOWN (NR 2 ACM) · airframe 57,456 hrs · 26,203 cycles

ON APPROACH INTO ATL, HEAVY OIL SMELL IN COCKPIT. CREW PUT O2 MASKS ON. REPLACED NR 2 ACM FOR BLOWN SEAL ON HOUSING.

Part: ENGINE — VIBRATION (NR 2) · airframe 56,345 hrs · 25,827 cycles

NR 2 ENGINE HIGH VIBES EGT EXCEEDED WITH LOUD BANG. REPLACED ENGINE.

Part: WARNING LIGHT — ILLUMINATED (COCKPIT) · airframe 56,168 hrs · 25,763 cycles

AFTER GEAR RETRACTION DOOR AND TRANS LIGHTS ON PILOTS PANEL,LT GEAR OR DOOR LIGHT ON SECOND OFFICERS PANEL. DUMPED FUEL RETURNED TO LAX. FOUND LEFT MAIN GEAR DOOR RETRACT ACTUATOR CRACKED ON MAIN HOUSING NEAR PROX SWITCH. REPLACED SAME PER MM. OPS CHECKED OK.

Part: ENGINE — MALFUNCTIONED (NR 2)

SHUT DOWN NR 2 ENGINE IN CRUISE DUE TO FILTER PRESSURE LIGHT ON S/O PANEL AS WELL AS LOW OIL QUANTITY, QUANTITY DECREASING. REPLACED NR 2 ENG GEARBOX HIGHSPEED EXTERNAL PER OPN NR 62304, 72312, REF ITEM 4,14 THIS LOG ITEM 4. CHIP DETECTORS REMOVED AND INSTALLED ITEM 14 TESTS 1-3-9-18-20 DUE C/W ALL TEST.

Part: FIRE LOOP — FAILED (NR 2 ENGINE)

'B' LOOP PREVIOUSLY BAD. NR 2 ENG FIRE HANDLE AND NR 2 'A' LOOP ILLUMINATED IN FLIGHT. NR 2 ENG SHUT DOWN AND BOTH FIRE BOTTLES DISCHARGED POM PROCEDURES COMPLETED. WINDMILL TIME 15 MINUTES. NR 2 IDG DISCONNECTED. REPLACED FIRE LOOP ASSY AND DETECTOR CONTROL UNIT.

Part: GCU — FAILED (NR 2)

FLIGHT STATION BUS FAILURE NR 2 ON TAKEOFF. NR 2 BUS TIE BREAKER TRIP OPEN AND NR 2 BREAKER FAILED, OPEN NR 2 FIELD REMAINED CLOSED. REPLACED NR 2 GCU, RAN ENGS AND ALL GEN SYS OPS NORMAL.

Part: BULKHEAD WEB — CRACKED (BS 1212)

FUSELAGE BULKHEAD FS 1212 RBL 6, WEB CRACK REPAIR. THE FS 1212 BULKHEAD WEB WAS FOUND WITH A CRACK AT RBL 6. THE CRACK IS TYPICAL TO THOSE COVERED IN LAC S/B 093-53-277 AND AD 96-20-10. THE CRACK WAS REPAIRED PER LAC DWG. LCC-7622-385 (AS CALLED FOR IN THE S/B) AND DOCUMENTED PER ER/A 367169-14AD.

Part: PUMP — BYPASSING (NR 1 ENGINE)

EXCESSIVE OIL CONSUMPTION, NR 1 ENGINE BEGAN FLT WITH FULL OIL QTY. AT TOP OF CLIMB, NR 1 ENG QTY WAS 15 QTS. CONSUMED 2.5 QTS IN THE NEXT 1 HR 15 MIN, INDICATED AS LOW AS 9 QTS AFTER 3.5 HRS OF FLT. REPLACED SCAVENGE/LUBE PUMP ASSEMBLY. RAN ENGINE, OPS AND LEAK CHECK GOOD.

Part: SKIN — CRACKED (WS 450)

A 4 INCH LONG CRACK WAS FOUND EXTENDING FROM THE AFT EDGE OF LOWER SKIN PANEL AT IWS 450. THE CRACK RAN FWD, TERMINATING UNDER THE AFT EDGE OF THE LOWER SPAR CAP. THE CRACK WAS ROUTED OUT OF THE WING SKIN PANEL. THE CUTOUT WAS REPAIRED WITH THREE EXTERNAL ALUMINUM DOUBLERS AND TWO INTERNAL ALUMINUM STRAPS. THE REPAIR WAS ACCOMPLISHED PER ER/A 365053-14, REV A.

Part: FRAME — CRACKED (BS 1163)

THE STA 1163 FUSELAGE FRAME WAS FOUND WITH THE FRAME TO SKIN ATTACH ANGLE CRACKED AT WL 201 JUST ABOVE PASSENGER FLOOR LEVEL ON THE LT SIDE OF THE FUSELAGE. THE CRACK IS APPROX 1 INCH LENGTH. THE DAMAGE WAS TRIMMED OUT AND A REPAIR DOUBLER AND FILLER INSTALLED PER ER/A 364952-14.

Part: SPAR — CRACKED (CENTER WING)

TWO CENTER WING INTERMEDIATE SPAR UPPER CAPS WERE FOUND WITH CRACKS BEYOND TYPICAL SRM REPAIR. CRACKS WERE LOCATED IN THE RT O/B END OF THE STA 1043 SPAR AND THE RT O/B END OF THE STA 1163 SPAR. THE CAPS WERE REPAIRED BY TRIMMING OFF THE O/B ENDS AND SPLICING IN A NEW SECTION WITH REPAIR ANGLES AND STRAPS PER ER/A 364936-14.

Part: MAGNA STICK — INOPERATIVE (RT WING)

IN FLT HAD 2 RT BOOST PUMPS 1/2 LOW PRESS LIGHTS ON WITH CORRESPONDING LOW QTY LEVEL LIGHT. FLT DIVERTED INTO BHM FOR ADDITIONAL FUEL. DURING FUELING FOUND NR 1 MAGNA STICK READING FULL WITH EMPTY TANK. DEFUELED TANK AND METERED IN KNOWN QTY, FUEL QTY SYS OPN NORMAL. FWD NR 1 MAGNA STICK ON RT WING TO MCO AND PLACARD.

Part: BULB — FAILED (CABIN)

EXTERIOR EMERGENCY EXIT LIGHTS AT DOOR 3L 3R AND 4R ARE INOP.

Part: ACM — REQD SERVICE (NR 3)

NR 3 PACK OVHT AT TOUCHDOWN. CABIN FILLED WITH SMOKE AND BURNING SMELL THROUGHOUT A/C. INSPECTED NR 3 PACK, FOUND NO OIL IN NR 3 ACM. LOCKED PACK VLV OUT PER MEL. FWD TO MCO AND PLAC.

Part: LOGIC CARD — FAILED (E/E COMPT)

GEAR RETRACTED ON CLIMB-OUT, RED DOOR INTRANSIT AND S/O RT GEAR OR DOOR LIGHT REMAINED ILLUMINATED. AFTER FOLLOWING PROCEDURES WITH ATL MAINT, TRUCK LIGHT REMAINED ON. DUMPED FUEL AND LANDED BACK IN HNL. TRUCK LIGHT EXTINGUISHED ON LANDING ROLL OUT. REPLACED A7 LOGIC CARD, ADJUSTED SENSOR, TEST HOP CHECKS OK.

Part: PRESSURE DECK — CORROSION (BS 348)

CORROSION WAS FOUND ON THE FWD PRESSURE DECK AT FS 348 AND RBL 20. THE RESULTING CUTOUT MEASURED 1.625 INBD/OUTBD BY 2.625 FWD/AFT. A DOUBLER WAS PLACED OVER THIS AREA. THIS REPAIR IS APPROVED BY FAA/DER FORM 8110-3 AND DER SO-889.

Part: SKATE ANGLE — CRACKED (LT PYLON)

A CRACK WAS FOUND IN ON OF THE OUTBOARD SKATE FWD ATTACH HOLES ON THE LT WING PYLON. THIS CRACK WAS LOCATED IN THE UPPER MOST FORWARD ROW OF FASTENERS AND EXTENDS HORIZONTALLY TO THE FORWARD FREE EDGE OF THE PART. THE DAMAGE WAS REMOVED.

Part: SPAR CAP — MISDRILLED (WS 306/378)

THE LT SPAR TO UPPER WEB ATTACH FASTENER HOLES WERE OVERSIZED AT TWO LOCATIONS. THE FIRST LOCATION IS AT APPRX. IWS 306. THE SECOND LOCATION IS AT APPROX IWS 378.

Part: SKIN — DENTED (BS 360)

THE SKIN AT STA 360 BETWEEN STR 51 AND THE FLOOR LONGERON WAS FOUND WITH A DENT WHICH WAS CUTOUT ALONG WITH THE FAIL/SAFE STRAP THAT WAS BONDED TO IT. THE FAIL/SAFE STRAP WAS REPAIRED PER THE L1011 SRM 53-31-00, FIGURE 804 IN CONJUNCTION WITH THE SKIN REPAIR. THIS REPAIR WAS APPROVED PER FAA/DER FORM 8110-3 SIGNED BY DER SO-889, DTD 11-JUN-97.

Part: SKIN — DAMAGED (L3 DOORWAY)

THE FUSELAGE SKIN BELOW THE L3 DOOR CUTOUT WAS DAMAGED BY TOOLING SURROUNDING A FASTENER HOLE. THE HOLE WAS ENLARGED TO REMOVE THE TOOLING DAMAGE. DURING OVERSIZE, A NUT PLATE WAS INADVERTANTLY DAMAGED AND A CRACK EMANATED FROM THE DAMAGE. THE HOLE WAS OVERSIZED TO 0.815 THROUGHT ALL LAYERS OF SKIN TO REMOVE THE DAMAGE. THE HOLE WAS PLUGGED PER DAL L1011 SRM 53-31-00, FIG 836.

Part: SKIN — DENTED (BS 709-729)

SEVERAL DENTS WERE FOUND BETWEEN STR 21 AND THE EDGE OF THE PANEL BTWEEN THE FORWARD EDGE AND APPROX FS 735. SEVERAL REPAIR DOUBLERS WERE INSTALLED. THIS REPAIR IS APPROVED BY FAA/ DER FORM 8110-3 CO-889 DTD 6-6-97.

Part: PRESSURE DECK — CRACKED (BS 380)

THE FUSELAGE HORIZONTAL PRESSURE DECK PANEL WAS FOUND WITH A 1.0 LONG CRACK. THE CRACK IS LOCATED AT RBL 102, JUST AFT OF FS 378 AND EXTEND DIAGONALLY INBOARD AND AFT FROM THE FORWARD EDGE OF THE PANEL AT THE EXISTING FRAME CUTOUT. THE CRACK WAS TRIMMED OUT LEAVING A 1.0 BY .75 CUTOUT. A DOUBLER AND TRIPLER WAS INSTALLED AND APPROVED BY FAA/DER FORM 8110-3, DER DESGINATION SO-889, DTD 5-27-97.

Part: PRESSURE DECK — CORRODED (FS 350)

THE UPPER SURFACE OF THE NOSE LANDING GEAR PRESSURE DECK WAS FOUND CORRODED BEYOND LIMITS. THE DAMAGE IS LOCATED AT FS 350, RBL 42 DIRECTLY ABOVE AN INTEGRAL STIFFENER. CUTTING OUT THE DAMAGE RESULTS IN A 3.5 BY 1 HOLE IN THE UPPER SURFACE WHICH HAS A LOCAL THICKNESS OF 0.051. THE PRESSURE DECK IS MANUFACTURED OUT OF LS10328 EXTRUSION. FABRICATE FIVE REPAIR PARTS PER FIGURE; TWO REPAIR ANGLES FROM DAL 21202968 EXTRUSION SIZED AS SHOWN IN FIGURE.

Part: SPAR WEB — CRACKED (RT WING)

WHILE ACCOMPLISHING DAL SPECIAL INSP 7-55740-12AD, REAR SPAR WEB INSPECTION FOR FATIGUE CRACKS, ONE FASTENER HOLE WAS OVERSIZED BEYOND THE MAX LIMITS DICTATED ON LAC DWG 1642705 REVISION E. THE HOLE, WAS PREVIOUSLY OVERSIZED AT LAST INSP TO REMOVE CRACKS TO A MAX DIA OF 0.331, AFTER COLD WORKING A FINAL DIAM OF 0.342. THE CURRENT INSP REQUIRES THE HOLE TO AGAIN BE OVERSIZED .0156 TO REMOVE SURFACE SCRATCHES. REV B IS ADDED DURING THE A/C HMV VISIT IN ATL TO PROVIDE PERMANENT INST TO THIS ER/A. EO 7-56199-3 SPAR WEB REPLACEMENT MODIFICATION WILL BE ACCOMP DURING MAINTENANCE VISIT.

Part: SKIN — CRACKED (BS 914)

THE LOWER FUSELAGE BELLY SKIN WAS FOUND WITH CORROSION AND CRACKS AT FS 914 JUST O/B OF STR 34. REMOVAL OF DAMAGE IN THE SKIN ONLY RESULTED IN A CUT OUT SIZED APPROX 1.5 BY 1.5. THE SUBJECT SKIN IS MADE FROM 0.068 2024-T3 CLAD. THIS ER/A IS REVISED TO ADD PERMANENT REPAIR INSTRUCTIONS THAT IS BEING ACCOMPLISHED DURING THE AIRCRAFT'S HMV VISIT IN ATL. THE DAMAGE IS TO BE REPAIRED PER THE DAL L1011 SRM 53-31-00, FIG 820.

Part: BATTERY PACK — DISCHARGED (CABIN)

FUSE LT ILLUM ON R1 EMERG LIGHT PACK. REPLACED PACK, OPN NORMAL.

Part: BATTERY — DISCHARGED (CABIN)

EXT EMERG LIGHT AT R2 DOOR INOP. REPLACED EMERG LIGHT PWR PACK FWD OF R2 DOOR. EMERG LIGHTS CK OK.

Part: TIRE — FAILED (LT MLG)

NR 2 REAR TIRE BLEW ON TAKEOFF ROLL. UNABLE TO RAISE THE LEFT MAIN LANDING GEAR. FUEL DUMPED A/C RETURNED TO LAX. A/C REMOVED TO HGR FOR IN DEPTH INSP. INITIAL INSPECTION REVEALED NR 2 REAR TIRE FLAT, DAMAGE TO THE ACCESS PNL FWD OF THE LT INBOARD T/E FLAP, DAMAGE TO THE CENTER SKIN, INCLUDING AN INNER RIB OF THE AFT INBOARD LT T/E FLAP.

Part: BATTERY — DISCHARGED (CABIN)

F/A FLASHLIGHT AT DOOR 2R INOP.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

POWER SUPPLIES DO NOT INDICATE AMBER LIGHT CHARGING COND DURING TEST. REPLACED POWER SUPPLIES, TEST OK. LOC ADJ R1 AND L4 DOORS.

Part: FITTING — DAMAGED (FS 792)

BOTH THE FWD AND AFT FITTINGS ON THE FWD FRAME FS 792 ARE REQUIRED TO BE MFG'D TO ACCOMMODATE A FRAME REPAIR INSTALLED BY ER/A 271917-14. SUBJECT FITTINGS ARE M/F 7075-T6 DIE FORGINGS, APPROVAL PER DL ERA 271918-14 REV B.

Part: BUSHING — NOT INSTALLED (LT GEAR)

ON GEAR RETRACTION, RED DOOR AND INTRANS WITH LEFT GEAR OR DOOR ON S/O PANEL. CYCLED GEAR, SAME INDICATIONS. FOUND PHASE CONTROL VALVE INCORRECTLY INSTALLED DUE TO OMITTED BUSHING ON THE TWO ACTUATING ROD/S TWO LUGS. INSTALLED MISSING BUSHING, OPERATION NORMAL.

Part: CONTROL VALVE — MALFUNCTIONED (LEFT W/W)

AFTER T/O RAISED GEAR HANDLE, ON PILOTS PANEL RSD DOOR AND INTRANSIT LIGHT ON, ALL GREEN LIGHTS OUT. ON S/O PANEL LT GEAR OR DOOR LIGHT ON. CYCLED GEAR, NO CHANGE AND RETURNED TO LAX. REPLACED RT PHASE CONTROL VALVE, OPERATION NORMAL.

Part: SPAR CAP — CRACKED (WS 332)

DURING ACCOMPLISHMENT OF SI 7-63370-12AD, A CRACK WAS NOTED AT HOLE NR 10A BETWEEN IWS 319.83 AND IWS 346.109 IN THE RT WING REAR SPAR UPPER CAP. THE WING SKIN IS NOT DAMAGED IN THIS LOCATION. ERA272791 AUTHORIZES INSTALLATION OF A BUSHING IN THE DISCREPANT HOLE, AND PERIODIC INSPECTIONS UNTIL THE NEXT HMV.

Part: EEL BATTERY PACK — DISCHARGED (CABIN)

ON LAYOVER, FOUND FWD CABIN EMERGENCY EXIT PATH LIGHTS FAILED TEST. REPLACED BATTERY AND POWER SUPPLY, OPERATION NORMAL.

Part: EEL BATTERY PACK — DISCHARGED (CABIN)

DURING LAYOVER, EMERGENCY LIGHT INOP FWD CABIN RT SIDE. REPLACED BATTERY PACK, OPERATION NORMAL.

Part: EEL POWER SUPPLY — FAILED (CABIN)

ON LAYOVER, FOUND EMERGENCY FLOOR TRACK LIGHTS INOP IN FWD CABIN. REPLACED POWER SUPPLY, OPERATION NORMAL.