N765DA

Part: GIRT BAR — DISCONNECTED (PAX DOOR) · airframe 76,506 hrs · 16,089 cycles

DOOR 3L CABIN DOOR HARD TO OPEN OR CLOSE - GIRT BAR HAS TO BE MANUALLY PLACED IN RETAINER WHEN CLOSED, CORRECTIVE ACTION REATTACHED GIRT BAR IN HOOK LOCK ASSEMBLIES DOOR OPERATES NORMALLY AND ARMS DISARMS NORMALLY

Part: UNKNOWN — ODOR (ROW 22) · airframe 75,032 hrs · 15,526 cycles

F/A REPORTED THAT ON APPROACH A BURNING SMELL WAS AROUND ROW 22. INVESTIGATED CABIN GALLEY AND SERVICE AREAS ABOVE AND BELOW FLOOR LEVEL. RAN ALL PNEUMATIC ELECTRIC AND GALLEY SYSTEMS, ALL OPNS GOOD.

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 74,866 hrs · 15,471 cycles

POWER SUPPLY FOR EMERGENCY ESCAPE PATH LIGHTING SYSTEM ONLY LAST 1 MINUTE.

Part: SPOILER PANEL — DEPLOYED (LT WING) · airframe 74,719 hrs · 15,407 cycles

SPLR PANELS NR 1 AND NR 3 ON LT WING DEPLOYED ON T/O. NO INDICATIONS IN COCKPIT, LOCKED UP, WILL NOT COME DOWN. ABORTED T/O AT 100 KTS. REPLACED BELL CRANK AT SPOILER MIXER FOR FROZEN BEARING.

Part: UNKNOWN — ODOR (CABIN)

ODOR APPEARED IN CABIN DURING LAST 5 - 10 MINUTES OF FLIGHT PRIMARILY IN THE REAR OF B-ZONE. FORWARD TO MCO AND PLAC PER MEL 25-99-06. FLIGHT ATTENDANTS REPORTED AN ELECTRICAL ODOR. CHECKED CABIN LIGHTING SYS, ALL OK. CHECKED MID AND AFT GALLEY EQUIPMENT. NO ODOR NOTED. CHECKED PA AND CABIN INTERPHONE SYS AND VIDEO SYS OPERATION, ALL OK. NO ODOR NOTED IN CABIN. PERFORMED PSS/PES SYS TEST. PSS TEST OK, PES SYS FAILED ALL SEAT ROWS AFT OF ROW 28 B-ZONE. DISABLED PSS/PES SYS, PULLED AND CLAMPED C/B 2D11 AND C/B F14 AT CABIN OVERHEAD PNL (CB4).

Part: BULKHEAD WEB — DAMAGED (BS 416)

TOOLING DAMAGE WAS FOUND ON THE NLG WHEEL WELL BULKHEAD AT APPROX FS 416, RBL 22 ON THE LWR SURFACE O/B FILLET RADIUS INSIDE THE RT ECS COMPT (NLG BLKHD WEB CAP). DAMAGE DEPTH IS APPROX 0.060 BY 1 IN LENGTH (FWD/AFT) BY 0.5 (VERT). REPAIRED PER ERA 333433-14, REV B.

Part: RIB — CRACKED (WS 555)

LT AND RT WING UPPER RIB CAP AT IWS 555 FOUND CRACKED DURING ROUTINE INSPECTION ERA 333431-14 REV B.

Part: MODULE — FAILED (NR 2 ENG)

AFTER DROPPING GEAR, 3 GREEN GEAR LIGHTS. C-SYS PRESSURE STARTED DECREASING, FLUID LOSS INDICATED. DOOR LIGHTS FOR MAIN GEAR REMAINED OPEN. WENT THRU CHECK LIST. TURNED ENG /ATM PUMPS ON, C-SYS OFF.

Part: BLADE — LACK OF LUBE (NR 2 ENGINE)

NR 2 ENGINE HAD HIGH FAN VIBS BOTH A AND B CHANNELS, SHOWED APPROX 2.7 UNITS. FAN VIBS INCREASED WHEN THROTTLES RETARTED TO IDLE. SHUT DOWN NUMBER TWO ENGINE PER POM. LUBED BLADES, PERFORMED VIB RUN, WITHIN M/M LIMITS.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

ON LAYOVER, CHECK FOUND AFT LEFT HAND OVERHEAD EMERGENCY LIGHTS WON'T TEST. REPLACED ASSOCIATED BATTERY PACK AT 2L AND ADDITIONAL PACK AT 3R. ALL EMER LIGHTS TEST GOOD.

Part: POWER SUPPLY — INOPERATIVE (2R DOOR)

ON LAYOVER, FOUND EMERGENCY BATTERY PACK NOT CHARGING. REPLACED EMERGENCY LIGHT BATTERY PACK.

Part: ENGINE — FAILED (NR 1)

ON T/O, THE NR 1 ENG GAVE LOUD BANG. VIBES PEGGED OUT AT 5 PLUS AND EGT LT CAME ON. SHUT NR 1 ENG DOWN AND LANDED ATL. REPLACE NUMBER ONE ENGINE.

Part: COUNTERBALANCE — INOPERATIVE (L3 DOOR)

AIRCRAFT ARRIVED WITH L3 EMERGENCY HANDLE PARTIALLY OPEN. REPLACED COUNTERBALANCE AND RIGGED DOOR.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

OVERHEAD EMER ESCAPE PATH LIGHTS FAILED TO OPERATE DURING TEST. REPLACE POWER SUPPLY.

Part: SKIN — CRACKED (WS 248)

THE LOWER CENTER BOX SKIN ON THE LT WING WAS FOUND CRACKED AT THE S-14 RUNOUT AT WS 248. THE CRACK RUNS FORE AND AFT THROUGH THE OUTBOARD MOST FASTENERS OF S-14 AND IS APPROX 2 IN LENGTH. STOP DRILL CRACK WITH A .5 HOLE LOCATING THE HOLE .25 AHEAD OF THE CRACK TIP IF CRACK DOES NOT END IN FASTENER HOLE. FABRICATED REPAIR PARTS AND DRILLED FASTENER HOLES PER ATTACHED FIGURE TO ER/A.

Part: FRAME — CORRODED (BS 983)

DURING ACCOMPLISHMENT OF SI 7-63916-12AD PART II, A 2 INCH LONG CRACK WAS FOUND IN THE WEB OF THE RIGHT HAND FS 983 FRAME. THE CRACK RUNS VERTICALLY IN THE WEB OF THE FRAME AND ACROSS THE UPPER INTEGRAL STIFFENER AS SHOWN IN FIGURE 1 OR ER/A. ACCORDING TO AD 91-21-51 AND L1011 S/B 093-53-264 (FIGURE 1,SHEET 3) THIS SINGLE CRACK IS ALLOWED PROVIDED THAT ADDITIONAL REPETITIVE INSPECTIONS ARE PERFORMED. NO OTHER CRACKS WERE FOUND IN THE INSPECTION AREA. REPAIRED PER ERA 362822-14 REV A.

Part: SKIN — PUNCTURED (BS 539-639)

EXTENSIVE DAMAGE WAS INCURRED TO THE FUSELAGE SKIN PANEL BETWEEN STA 539 AND 639 BETWEEN STR 42 AND 48. THE DAMAGE CONSISTED OF FOUR LARGE SKIN PUNCTURES, TWO DENTED FRAME TO SKIN CLIPS, AND A DENTED STRINGER. THE DAMAGED FRAME TO SKIN CLIPS ARE LOCATED AT STA 569 BETWEEN STR 47 AND 48, STA 589 BETWEEN STR 46 AND 47. STRINGER 45 WAS DAMAGED BETWEEN STA 579 AND 599. THE FRAME TO SKIN ATTACH CLIPS WERE REPAIRED PER SRM 53-12-00, FIGURE 82. THE STRINGER WAS SPLICED PER L1011 SRM 53-13-00, FIGURE 803 OR 804. THE SKIN PUNCTURES WERE REPAIRED WITH A DOUBLER.

Part: VALVE — LEAKING (NR 3 PACK)

AREA E OVERHEAT ON CLIMB-OUT. RETURNED TO BASE. FOUND NR 3 PACK VALVE LEAKING AT AFT END. REPLACED NR 3 PACK VALVE. VALVE P/N 217002711 OFF KC16803 ON 065.

Part: RCCB — FAILED (AVIONICS COMPT)

COULD NOT SHUT OFF 2R INBOARD BOOST PUMP. DIVERTED TO JFK. REPLACED 2R INBD PUMP RCCB, OPS CK OK.

Part: BATTERY PACK — NOT SEATED (CABIN)

HALF OF THE EMERGENCY EGRESS PATH LIGHTS INOP. RESEATED BATTERY PACKS, OPS NORMAL.

Part: BATTERY — MISSING (CABIN)

FOUND CAPTAIN'S EMERGENCY FLASHLIGHT SEAL BROKEN AND BATTERY EMPTY DUE LIGHT MOUNTED 180 DEGREES WRONG. REPLACED FLASHLIGHT AND BATTERY.

Part: FITTING — CORRODED (LT MLG)

THE LT MLG ATTACH FITTING WAS FOUND CORRODED ON THE UPPER FLANGE. DURING REMOVAL, FASTENER HOLES WERE FOUND OVERSIZED AND SPOT FACED IN ACCORDANCE WITH THE SRM. SOME REQUIRED SPOT FACING DEEPER THAN THE LIMIT ALLOWED IN THE SRM. REPAIR APPROVAL PER DL ERA 271876-14.

Part: ATTACH FITTING — DAMAGED (RT MLG)

TOOLING DAMAGE WAS INCURRED DURING RE-WORK TO AN INBOARD .6250 INCH FASTENER HOLE THROUGH THE RT MAIN LDG ATTACH FITTING. REPAIRED IAW DL ERA 271908-14 AD.

Part: SKIN — SHORT EDGE DIST (BS 1363)

WHEN PICKING UP FASTENER LOCATIONS IN THE SKIN ATTACH FLANGE OF THE 1363 BULKHEAD CAP, NINE .25 INCH FASTENER HOLES ON BOTH THE LT AND RT SIDES WERE FOUND WITH SHORT EDGE DISTANCE ON THE FUSELAGE SKIN. REPAIRED IAW DL ERA 271825-14AD.

Part: BULKHEAD — OVERSIZED HOLES (BS 1363)

SEVERAL FASTENER HOLES BETWEEN STR 21 AND 22 WERE OVERSIZED TO A .25 DIAMETER. FASTENER REMOVAL ACCOMPLISHMENT OF EO 7-69959-12AD, REPAIRED PER DL ERA 271854-14AD.

Part: REAR SPAR — CRACKED (WS 319-346)

DURING THE ACCOMPLISHMENT OF EO 7-59089-3, CRACK INDICATIONS WERE FOUND EMANATING FROM TWO FASTENER HOLES COMMON TO THE UPPER WING SKIN AND THE UPPER SPAR CAP. ACCOMPLISHED REPAIRS PER DL ERA 271961-14AD.

Part: ANGLE — OVERSIZED HOLE (FS 1203)

DURING REMOVAL OF EXISTING FASTENERS AT RT 1203, THE UPPER FWD HOLE COMMON TO THE VERTICAL LEG OF THE FAIL-SAFE ANGLE, SKIN PANEL, FRAME FITTING, AND OVERWING TITANIUM TEE WAS OPENED TO .438. REPAIR APPROVAL PER DL ERA 271858-14AD.

Part: LATCH FITTINGS — CORRODED (CARGO DOOR)

THE NR 1 THROUGH NR 8 C-1A CARGO DOOR LATCH FITTINGS WERE FOUND WITH PITTING IN THE UPPER WELLS. DRAIN HOLES WILL BE DRILLED IN ALL EIGHT FITTINGS PER DL ERA 271881-14AD.

Part: ANGLE — OVERSIZED HOLES (WING/FUS)

SEVERAL FASTENERS IN THE BASE HOR FLANGE OF THE FAIL-SAFE ANGLE WERE FOUND TO BE OVERSIZED, WING TO FUSELAGE. REPAIRED PER DL ERA 271865-14 AD.

Part: LONGERON — CRACKED (FS 1860)

THE OUTER CAP ANGLE OF THE LT UPPER LONGERON IN THE FUSELAGE AFTER BODY AT STA 1860 WAS FOUND CRACKED IN THE RADIUS. REPAIRED PER DL ERA 271830-14.

Part: DOOR SILL — CORRODED (FS 901)

THE LOWER DOOR SILL INBOARD CAP FITTINGS WERE FOUND CORRODED AND REQUIRED REPLACEMENT. REPAIRED PER DL ERA 271846-14.

Part: ACTUATOR FITIING — DAMAGED (LT/RT MLG)

THE LT AND RT WING MLG ACTUATOR SUPPORT FITTING HAD THREE FASTENERS, IPC 57-14-0 FIG 1 ITEMS 280, 285, 300 ENT. THESE VERE REPLACED WITH HLT 104 BOLTS PER SRM 57-14-00 FIG 803.

Part: SKIN — DENTED (NR1 TE FLAP VANE)

AT HMV, LT WING NR 1 FLAP VANE WAS FOUND WITH DENTED SKIN ON INNER SKIN PANEL. INSTALLED REPAIR DOUBLERS PER SRM 51-50-01.

Part: SKIN — CRACKED (NR1 TE FLAP VANE)

AT HMV, LEFT WING NR 1 FLAP VANE WAS FOUND WITH UPPER SKIN CRACKED ALONG A RIB AT 40 INCHES FROM INBD END. REPAIRED PER SRM 57-53-00.

Part: SKIN — DAMAGED (NR1 TE FLAP VANE)

AT HMV, LT WING NR 1 FLAP VANE WAS FOUND WITH HEAVY WEAR DAMAGE TO OUTER SKIN AT THE INBD END OF VANE. REPAIRED PER SRM 57-53-00, FIG 805.

Part: FITTINGS — CORRODED (FS 901)

THE LOWER DOOR SILL I/B CAP FITTINGS AT FS 901 RT AND LT SIDES, WERE FOUND CORRODED AND REQUIRED REPLACEMENT. ACCOMPLISHED REPAIRS PER DL ERA 271846-14.

Part: BLKHD SKIN — CRACKED (FS 328)

ON 8-9-91 CRACKS WERE DISCOVERED IN THE FS 328 CANTED BULKHEAD STRUCTURE DURING HMV. THIS DAMAGE WAS REPAIRED BY LAC DWG 1646545 PER ER/A 226719-14. AFTER THAT, EO 7-53207-3AD WAS ISSUED TO REINFORCE THE FS 328 CANTED BULKHEAD STRUCTURE FOR ALL DAL L1011'S, PART 2 CALLED FOR INSPECTION OF PERMANENT REPAIRS FOR UNITY WITH THE EO. THE DOUBLERS OF THE BULKHEAD MOD WERE MISSING FASTENERS IN SEVERAL LOCATIONS. ACCOMPLISHED REPAIRS PER DL ERA 271850-14AD.

Part: LONGERON — CRACKED (FS 1860)

FUSELAGE, AFTERBODY, LLT LONGERON ASSY FS 1860 WL 328.942, REPAIR OF CRACKED LONGERON. THE OUTER CAP ANGLE OF THE LT UPPER LONGERON IN THE FUSELAGE AFTERBODY AT APPROX FS 1860 AND WL 328, WAS FOUND CRACKED IN THE RADIUS. THE CRACK EXTENDS FROM THE AFT END OF THE PART FWD APPROX 6 INCHES ALONG THE RADIUS OF THE PART. INSTALLED REPAIR DOUBLER PER DL ERA 271830-14.

Part: FRAME — CRACKED (BS 1363)

DURING HMV, 1363 BULKHEAD FRAME AT APPROX WL 160 ON RT SIDE IS CRACKED AT THE SECOND FASTENER FROM BOTTOM FWD ROW. INSTALLED REPAIR AS PER SRM 53-11-00 FIG 843.

Part: FLOORBEAM — CORRODED (BS 901)

DURING HMV, FS 901 FLOOR SUPPORT BEAM CORRODED AT LBL 49, 60, AND RBL 49, 70. REPLACED BEAM CAP PER SRM 53-21-00 PG 849 TO 852.

Part: FLOORBEAM — CORRODED (BS 846)

DURING HMV, UPPER SURFACE OF FLOORBEAM AND SUPPORT ANGLE CORRODED AT FS 846 AT RBL 40. REPAIRED PER SRM 53-21-00 PG 849 TO 852.

Part: COWL — WORN (NR 2 ENGINE)

AT HMV, NR 2 ENGINE RT COWL PANEL WAS FOUND WITH WEAR DAMAGE AT LOWER FORWARD CORNER OF PANEL. ACCOMPLISHED REPAIRS PER SRM 51-50-01, FIG 2.