N8873Z

Part: SLAT — CRACKED (# 5) · airframe 61,825 hrs · 40,760 cycles

REPAIRED 1.5 INCH CRACK IN #5 L/E SLAT I/B RIB AT ACTUATOR ROD END PER M/M 57-54-000-8 PER ERA 382382-14 REV ORG

Part: LIGHT — INOPERATIVE (CABIN) · airframe 60,390 hrs · 39,822 cycles

EMERGENCY EXIT LIGHT AT ROW 32 INOP. REPLACED LIGHT RACK.

Part: BATTERY PACK — INOPERATIVE (CABIN) · airframe 60,318 hrs · 39,765 cycles

AFT OVERWING EMERGENCY LIGHT INOP. BATTERY PACK WAS FOUND TO BE BAD. REMOVED AND REPLACED SAME.

Part: BATTERY PACK — NOT SEATED (CABIN) · airframe 60,088 hrs · 39,606 cycles

BATTERY PACK OVER ROWS 20-25 WAS FOUND UNSEATED CAUSING SECTION OF EMERGENCY LIGHTS TO NOT WORK. SECURED BATTERY PACK.

Part: HARNESS — DAMAGED (CABIN) · airframe 59,785 hrs · 39,408 cycles

SEAT 30D EMERGENCY LIGHT INOP.// FOUND DAMAGED WIRING HARNESS, REPLACED HARNESS SECTION. OPS CK OK.

Part: SKIN — PUNCTURED (FUSELAGE) · airframe 59,686 hrs · 39,336 cycles

THE FUSELAGE SKIN WAS PUNCTURED BY GROUND EQUIPMENT AT FS 1100 BETWEEN STRINGERS 19L & 20L. THE DAMAGE WAS REMOVED WITH A CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUMDOUBLER INSTALLED PER ER/A 380183-14, REV A.

Part: ROD — BROKEN (NR 3 ENGINE) · airframe 58,462 hrs · 38,515 cycles

A/C WAS IN CRUISE AT FL 280 WHEN A LOSS OF THRUST CONTROL OCCURRED ON NR 3 ENGINE. ENG DID NOT RESPOND TO ANY THROTTLE INPUTS. IN-FLT SHUTDOWN WITH ENGINE AT 2.65 EPR N1 101 N2 100 EGT 630. FOUND BROKEN CONTROL ROD= PYLON QUADRANT TO CROSS OVERSHAFT. REPLACED SAME.

Part: STIFFENER — CRACKED (LT WING) · airframe 58,250 hrs · 38,368 cycles

FOUND AT A1 LTR CK, VERTICAL SPAR STIFFENER CRACKED O/B OF I/B TRACK AT NR 7 SLAT. REPAIRED PER ERA 377979-14.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 58,246 hrs · 38,366 cycles

FOUND AT A-1 LTR CK, .25 INCH VISIBLE CRACK IN 870 I/B VERTICAL CHORD. TIME LIMITED REPAIR INSTALLED PER B-727 DRD 53-10-9D FIG 806D.

Part: PUMP — LEAKING (HYDRAULIC SYS) · airframe 58,193 hrs · 38,332 cycles

COMPLETE LOSS OF SYSTEM B HYDRAULICS IN FLIGHT. FOUND NR 1 B-SYSTEM ELEC PUMP LEAKING FROM PUMP DRAIN. CHECKED/REPLACED BOTH PRESSURE AND CASE DRAIN FILTERS, FOUND CLEAN. REPLACED NR 1 B-SYSTEM ELEC HYD PUMP. LEAK CHECK OF PUMP AND FILTERS OK.

Part: ENGINE — STALLED (NR 3) · airframe 57,906 hrs · 38,134 cycles

DURING TAKEOFF ROLL FLT ATTENDANT AND PASSENGER REPORTED HEARING COMPRESSOR STALL NR 3 ENG. NO ABNORMAL ENGINE INDICATIONS WERE NOTICED. INSPECTED INTAKE AND EXHAUST, CHECKED GOOD. RAN ALL THREE ENG''S TO TAKEOFF PWR PER PFHB. ALL CHECKED GOOD. WINDS SHIFTED AT TIME OF TAKEOFF ROLL.

Part: ENGINE — FLUCTUATES (NR 3) · airframe 57,471 hrs · 37,844 cycles

A/C RETURNED FROM CRUISE WITH ALL FLUCTUATING PARAMETERS ON ALL THREE ENGINES. VERSILUBED FUEL CONTROLS ON ALL THREE ENGS. TESTED FUEL WITH TEST KIT AND NO CONTAMINANTS FOUND. RAN ENGS PER PFHD AND NORMAL. FUEL TANKS DRAINED AND FRESH FUEL ADDED PRECAUTIONARILY.

Part: INDICATOR — MALFUNCTIONED (TE FLAP)

AFTER T/O UPON SELECTION/RETRACTION OF FLAPS TO 2 DEG. O/B FLAPS RETRACTED TO 4 DEG I/B FLAPS TO 2 DEG. STARTED APPROACH CHECK LIST. O/B FLAPS THEN RETRACTED TO THE SELECTED POSITION 2 DEG. DISCONTINUED CHECK LIST. FLAPS OPERATED NORMAL FOR REMAINDER OF FLIGHT. LUBED OUTBOARD FLAPS. CK OIL LEVELS ON FLAP TRANSMISSIONS. REPLACED OUTBOARD INDICATOR, CKS GOOD.

Part: FUEL CAP — WORN (LEFT WING)

AIR TURNBACK, FUEL LEAK FROM THE OVERWING REFUELING CAP LEFT WING. REPLACED CAP, LEAK CHECKED OK.

Part: FUEL PORT — CORRODED (WING)

FUEL LEAK FROM OVERWING REFUEL CAP ON LEFT WING. REPLACED OVERWING FUEL PORT ASSY.

Part: BATTERY PACK — DISCHARGED (CABIN)

EMERGENCY LIGHT ABOVE R2 DOOR INOP. REPLACED BATTERY PACK, OPS NORMAL.

Part: CONTROL VALVE — FAILED (LEFT PACK)

LOST CABIN ALTITUDE WHILE CRUISING AT FLIGHT LEVEL 250. LOSS OF CABIN PRESSURE PROCEDURES ACCOMPLISHED. CHANGED LT PACK CONTROL VALVE PER MM, LEAKS CKS GOOD.

Part: BATTERY — DISCHARGED (CABIN)

DURING STBY PWR CK, THE EMERGENCY EXIT LIGHTS OVER THE RT WING EXIT DOORS FLASHED ON/OFF CONTINUOSLY. REPLACED RACK AND BATTERY ASSY M1086 NOW CKS OK.

Part: SPAR — CRACKED (TE MIDFLAP)

DURING ACCOMPLISHMENT OF PREVENTATIVE MODIFICATION OF MIDFLAP REAR SPAR ATTACH HOLES PER EO 4-58705-3AD, A FATIGUE CRACK WAS FOUND IN ONE OF THE MOD HOLES IN THE REAR SPAR CHORD. THE HOLE WAS REAMED UP FROM .1875 DIA TO .25 INCH DIA TO REMOVE CRACK INDICATION. AUTHORIZED COLD WORK OF FASTENER HOLE AND INSTALLATION OF OVERSIZED FASTENER.

Part: POWER SUPPLY — INOP (CABIN)

DURING FIRST FLT DAY NOTED EMERGENCY EXIT LIGHT ON ALL SEATS IN FIRST CLASS AND TWO ROW IN COACH CLASS INOP. REPLACED POWER SUPPLY.

Part: FUSE — BLOWN (ROW 1-11)

FOUND E-PATH LIGHTS INOP AT ROWS 1 THROUGH 11. FOUND FUSE IN BATTERY RACK BLOWN. REPLACED FUSE, OPS NORMAL.

Part: SKIN — WORN (NR 1 TE MID FLAP)

DURING SHOP INSPECTION, THE THE L/E SKIN WAS FOUND WORN ON THE I/B END OF THE FLAP, APP 6 LONG AREA. REPAIRED PER M/M.

Part: SKIN — GOUGED (BS 950)

SEVERAL GOUGES WERE FOUND IN THE FUSELAGE SKIN AT BS 950E ABOVE S19R. REPAIRED PER ERA 333124-14, REV B.

Part: STRINGER — CRACKED (WS 171.5)

THE AFT RIB TO STRINGER ATTACH TAB AT WS 171.5 S18 OF THE RT WING WAS FOUND CRACKED. REPAIRED PER ERA 333161-14, REV B.

Part: SKIN — CORRODED (BS 950-1070)

MULTIPLE SKIN REPAIRS HAVE BEEN ACCOMPLISHED ON THE LOWER FUSE SKIN BETWEEN BS 950 TO 1070. DUE TO THIS, THE LWR SKIN WILL BE REPLACED AT THIS VISIT. REPLACED AND SPLICE SKIN PER ERA 333076-14.

Part: SKIN — TORN (R1 DOORWAY)

THE FUSELAGE SKIN WAS FOUND TORN AT THE LWR HINGE CUTOUT FOR THE R1 DOOR. REPAIRED PER ERA 333131-14, REV A.

Part: RIB — CRACKED (LT WING)

INNER SKIN CUT TO GAIN ACCESS TO RIBS. SKIN REPAIRED PER M/M 57-54-0 FIG 801.

Part: FITTING — CORRODED (RT MLG)

DURING RTN INSP OF THE RT MLG BEAM FWD SUPPORT FITTING, CORROSION WAS FOUND ON THE INNER SURFACE OF THE MLG ATTACHMENT BOLT BORE. FINAL DIAMETER OF 1.875 WAS NEEDED TO REMOVE ALL DAMAGE. REPAIRED PER ERA 333106-14, REV A.

Part: STRINGER — CRACKED (VERT STAB)

VERT STAB S7 WAS FOUND CRACKED AT STA 157.2 DURING INSPECTIONS PER SI 4-59253-12AD. REPAIRED PER ERA 333133-14AD.

Part: STRINGER — CRACKED (BS 940)

A 4 INCH CRACK WAS FOUND IN THE VERT FLANGE (SKIN ATTACH) OF S18A AT APPROX BS 941. REPAIRED PER ERA 333079-14, REV A.

Part: ANGLE — CRACKED (LT TE MID FLAP)

DURING SHOP INSPECTION, THE AFT LOWER CHORD ANGLE WAS FOUND CRACKED 47 FROM THE IB END OF THE MIDFLAP. THE ANGLE WAS REPAIRED PER 727 MM 57-52-0, FIG 802.

Part: ANGLE — CRACKED (LT TE MID FLAP)

DURING SHOP INSPECTION, THE AFT LOWER CHORD ANGLE WAS FOUND CRACKED 32 FROM THE IB END OF THE MIDFLAP. THE ANGLE WAS REPAIRED PER 727 MM 57-52-0, FIG 802.

Part: SKIN — DENTED (LT TE MID FLAP)

DURING SHOP INSPECTION, THE COVE SKIN WAS FOUND DENTED AND WORN 20 FROM OB END OF FLAP. THE SKIN WAS REPAIRED PER MM 57-52-0, FIG 809.

Part: SKIN — DAMAGED (RT TE FLAP)

TEMP REPAIR L/E SKIN O/B END OF FLAP. REPAIRED PER M/M 57-52-0 FIG 803.

Part: SKIN — DAMAGED (RT TE FLAP)

TEMP REPAIR L/E SKIN I/B END OF FLAP. REPAIRED PER M/M 57-52-0 FIG 803.

Part: BRACKET — CRACKED (NR 8 LE SLAT ACT)

REF E - 2 LETTER CHECK TPA, NR 8 SLAT ACT MOUNT BRACKETS CRACKED AT I/B AND O/B SIDES. INSTALLED DOUBLERS PER M/M 57-20-21.

Part: BATTERIES — DISCHARGED (CABIN)

2L DOOR OVERHEAD EMERGENCY LIGHT INOP. REPLACED BATTERIES.

Part: BEAM — CHAFED (LT WING)

MLG STRUT DOOR CHAFING ON MLG BEAM 4 FEET I/B OF MLG STRUT. REPAIRED PER MM 57-43-0 PG 801.

Part: WEB — CRACKED (BS 1235)

A 1 IN CRACK AT RT TORQUE BOX VERTICAL WEB AT LWR LIGHTENING HOLE STA 1235. REPAIRED PER M/M 53-11-0.

Part: ANGLE — CRACKED (NR 7 LE SLAT)

A 3 INCH CRACK IN NR 7 SLAT AT INBD TRACK UPSTOP PAD COVE ANGLE. REPAIRED PER M/M 57-54-0 AND ERA 363224-14.

Part: STRINGERS — CRACKED (VERT STAB)

FOUR STRINGERS CRACKED IN THE VERT STABILIZER AT INBD RIB ATTACHMENT TABS. DAMAGED STRINGERS ARE AS FOLLOWS: STR 9R AT VERT STAB STA 180.6, STR 10L AT VERT STAB STA 133.8, STR 9R AT VERT STAB STA 157.2 AND STR 10L AT VERT STAB STA 180.6. STOP DRILLED CRACKS; REPAIRED EACH STR LOCATION PER DAL 727 M/M 53-30-0, FIG 803.

Part: HINGE — WORN (HORIZ STAB)

HORIZON STAB ELEV INBOARD HINGE WORN, ALSO FRETTING CORROSION ON FITTING OUTBOARD SIDE. REMOVED CORROSION PER SRM 51-10-6 SPOT FACED INSIDE FACED TO REMOVE WEAR WITHIN M/M 55-50-0 LIMITS. ROTO PEENED AREA. TREATED AND PAINTED AREA. INSTALLED SPACERS PER M/M 55-50-0.

Part: WEB — CRACKED (VERT STAB)

INSIDE VERTICAL STAB AT FUSELAGE STA 1303 VERTICAL WEB CRACKED AT BOTH LOWER CORNERS. REMOVED T-ANGLE SUPORT AND ANTI-ICE DUCT TO GAIN ACCESS TO AREA. DRILLED OUT FASTENERS IN WEB REPAIR AREA. FABRICATED ROUGH DEMINSION DOUBLERS. INSTALLED DOUBLERS PER SRM 53-10-4 FIG 14. RE-INSTALLED ANTI-ICE DUCT AND T-ANGLE SUPPORT.

Part: MOUNT — CRACKED (NR 5 LE FLAP)

NR 5 K FLAP ACTUATOR MOUNT CRACKED. REMOVED ACTUATOR MOUNT AND STARTED REPAIR PER M/M 57-20-21 FIG 807. REPAIRED PER DAL M/M 57-20-21 FIG 807. INSTALLED ACTUATOR MOUNT.

Part: STRINGER — CRACKED (VERT STAB)

STRINGER 10, LT SIDE AT FIN STA 180.6 INSIDE VERTICAL STAB, 5TH BAY IS CRACKED. BEGAN M/M REPAIR PER M/M 55-30-0 FIG 803. INSTALLED REPAIR PER M/M 55-30-0 FIG 803.

Part: STRINGER — CRACKED (VERT STAB)

FOUND AT MV2 IN ATL, CRACKED STR 10 LT SIDE AT FIN STA 133.8 INSIDE VERTICAL STAB, 3RD BAY UP. ACCOMPLISHED REPAIR PER M/M 53-30-0 FIG 803.

Part: STRINGER — CRACKED (VERT STAB)

DURING MID VISIT, FOUND STRINGER CRACKED STR 9 RT SIDE AT FIN STA 157.2, INSIDE VERTICAL STAB 4TH BAY UP. REPAIRED PER M/M 55-30-0 FIG 803.

Part: LIGHT — INOPERATIVE (L2 DOOR)

L-2 DOOR EMERGENCY EXIT LIGHT INOP. REPLACED LIGHT/BATTERY ASSY, OPS OK.

Part: TRANSVERSE BEAM — CRACKED (BS 1263)

THERE IS A CRACK IN THE ANGLE OF THE FWD TRANSVERSE BEAM OF THE RT TORQUE BOX AT FS 1263. THIS AREA OF THE TORQUE BOX IS THE SUBJECT OF AD 94-07-08, WHICH REQUIRES INSPECTION PER S/B 53-0129. THIS REPLACEMENT DOES NOT TERMINATE THE REPETITIVE INSPECTION REQUIREMENTS. TERMINATING ACTION WIL BE PROVIDED BY EO 4-61071-3.

Part: SKIN — CRACKED (RT ELEVATOR)

1.25 INCH CRACK IN ELEVATOR LOWER SKIN AFT OF NR 2 RT BALANCE BOARD ACCESS PANEL. FOUND DURING C-LETTER CHECK. REPAIRED PER SRM 55-20-3, FIG 4.