N329DL

Part: FLOORBEAM — CRACKED (BS 660) · airframe 53,427 hrs · 42,058 cycles

THE RBL 24 LONGITUDINAL OVERWING FLOORBEAM HAS BEEN PREVIOUSLY MODIFIED PER 3-056673-3AD. THE C-CHANNEL INSTALLED PER THIS EO DOES NOT MEET EXISTING AD REQUIREMENTS. CRACKS WERE FOUND IN THE UPPER CHORD, BEAM AFT WEB, AND WEB DOUBLERS. THE C-CHANNEL WAS REPLACED, WEB DOUBLER WAS REPLACED, WEB WAS REPAIRED AND UPPER CHORD WAS REPAIRED PER ER/A 451091-14AD.

Part: FLOORBEAM — CRACKED (BS 660) · airframe 53,427 hrs · 42,058 cycles

THE LBL 24 LONGITUDINAL OVERWING FLOORBEAM WAS MODIFIED USING A PREVIOUSLY ACCEPTALBE C-CHANNEL THAT IS NOT ACCEPTABLE PER AD 2001-17-18. CRACKS WERE FOUND IN THE BEAM AFT WEB AND WEB DOUBLER. C-CHANNEL WAS REPLACED. WEB REPAIR DOUBLER WAS INSTALLED, AND CRACKS WERE REMOVED PER ER/A 451073-14AD.

Part: SHEAR BEAM — CRACKED (S-, FS) · airframe 51,103 hrs · 40,347 cycles

A 1 INCH CRACK WAS FOUND EMANATING FROM A FASTENER HOLE AT THE AFT END OF THE STRINGER 18A SHEAR BEAM WEB AT FS 727 ON THE LT SIDE OF THE AIRCRAFT. THE CRACK EXTENDED TO THE AFT EDGE OF THE PART AND FWD OF THE END FASTENER HOLE. THE CRACK WAS REPAIRED WITH AN ALUMINUM CHANNEL AND RADIUS BLOCK PER ER/A 094762-14, REV A.

Part: RELIEF VALVE — FAILED (HYD RESERVOIR) · airframe 49,560 hrs · 39,184 cycles

DURING APPROACH PHASE AFTER PLACING THE FLAP LEVER TO 5 SYSTEM A PRESSURE WENT TO ZERO WITH ASSOCIATED SYSTEM A LOW PRESSURE LIGHTS ILLUMINATED. REPLACED SEVERAL LINES AND RESERVOIR PRESSURE RELIEF VALVE.

Part: REGULATOR — LEAKING (HYD RESERVOIR) · airframe 49,448 hrs · 39,097 cycles

LOSS OF A-SYSTEM HYDRAULIC PRESSURE. FOUND NO RESERVOIR HEAD PRESSURE. REPLACED RESERVOIR PRESSURE REGULATOR AND BOTH CHECK VALVES.

Part: INSULATION — OUT OF POSITION (CARGO BAY) · airframe 48,135 hrs · 38,050 cycles

SMOKE SMELL IN AFT CABIN. FOUND INSULATION TOUCHING APU BLEED DUCT CAUSING SMELL. REPOSITIONED INSUL. FWD APU AIR TO MCO AND PLAC AS PRECAUTION.

Part: FRAME — CRACKED (FUSELAGE) · airframe 47,956 hrs · 37,890 cycles

MTC FOUND CRACKS IN THE FRAME AT S6L, 3L, 2L, 1, 2R, AND 3R EXTENDING FROM THE STRINGER PASS THRU CUTOUTS. THE CRACKS WERE CUTOUT AND A REPAIR SIMILAR TO B737-200 SRM 53-10-04, F14, WAS INSTALLED TO EXTEND FROM O/B OF STR 6L TO O/B OF STR 4R. FUSELAGE SKIN WAS CUT AT EACH STRINGER/FRAME INTERSECTION AND STRINGERS 6L THRU 4R WERE CUT AND SRM STYLE REPAIRS WERE INSTALLED TO PROVIDE ACCESS FOR INSTALLATION OF FRAME REPAIR PER DAL ER/A 384937-14.

Part: FRAME — CRACKED (FUSELAGE) · airframe 47,956 hrs · 37,890 cycles

THE SUBJECT DOOR FRAME WAS FOUND CRACKED AT THE INTERSECTION OF FS 440 AND STR 24R. THE FRAME WAS ORIGINALLY 0.071 INCH 7075-T6 CLAD. THE CRACK WAS TRIMMED OUT, STEEL REPAIR ANGLES WERE INSTALLED, AND TWO DOOR STOP FITTINGS WERE MODIFIED TO ALLOW FOR THE INSTALLATION OF THE REPAIR PARTS PER DAL ER/A 385003-14.

Part: ATTACH FITTING — CORRODED (FUSELAGE) · airframe 47,956 hrs · 37,890 cycles

STABILIZERS / HORIZONTAL / ATTACH FITTINGS / LT, RT AND CENTER SECTION - CORROSION: WHILE ACCOMPLISHING AN INSPECTION OF THE HORIZONTAL STABILIZER ATTACH LUGS PER EO 3-69697-3. MAINTENANCE DISCOVERED CORROSION IN ALL FUSELAGE AND STABILIZER LUGS AND ON MOST OF THE LUG FACES. ER/A 412532-14 PROVIDED INSTRUCTIONS TO MACHINE THE BORES AND LUG FACES TO REMOVE ALL CORROSION.

Part: SKIN — DENTED (FUSELAGE) · airframe 47,956 hrs · 37,890 cycles

FUSELAGE SKIN FS 344, S-19R TO S-20R - DENT: A DENT WAS REPORTED APPROXIMATELY 2 INCHES BELOW THE LOWER EDGE OF THE UPPER SKIN OF THE LAP SPLICE AT S-19R. THE DENT MEASURED 2.2 X 1.5 X 0.057 INCH DEEP. THE SKIN PANEL IS 0.036 INCH SKIN WITH A 0.036 INCH INTERNAL BONDED DOUBLER. DAL ER/A 384904-14 CUTS OUT THE DENT, WHICH AFFECTS ONLY THE 0.036 INCH SKIN (NOT THE BONDED DOUBLER), AND INSTALLS A 0.040 INCH 2024-T3 CLAD SHEET REPAIR DOUBLER THAT EXTENDS ACROSS THE S-19R LAP SPLICE.

Part: ATTACH FITTING — CORRODED (VERTICAL STAB) · airframe 47,956 hrs · 37,890 cycles

FUSELAGE ATTACH FITTINGS: VERTICAL STABILIZER CLEVIS LUGS - CORROSION. THE NR 11 CLEVIS LUG FWD FACE WAS FOUND GOUGED. THE DAMAGE WAS CLEANED UP USING A SPOTFACE, WITH A MIN REMAINING LUG THICKNESS OF 0.940 INCH IAW DAL ER/A 412535-14, INITIAL RELEASE.

Part: BLEED VALVE — MALFUNCTIONED (NR 2 ENGINE) · airframe 46,920 hrs · 37,454 cycles

SHORTLY AFTER T/O NR 2 ENGINE EGT REACHED 640 FOR 3 TO 4 SECONDS. INSPECTED INLET AND EXHAUST, NO DEFECTS. CHECKED EPR SYSTEM WITH P/S TEST BOX INDICATION GOOD. NO LEAKS. LUBED BLEED VALVES AND REPLACED PRBC PERFORMED PFHB TEST E - J AND X. TESTS GOOD. RAN ENGINE FOR 3 MINUTES EGT WITHIN LIMITS.

Part: SKIN — CRACKED (FUSELAGE) · airframe 46,836 hrs · 37,415 cycles

A 1 INCH LONG CRACK WAS FOUND IN THE FUSELAGE SKIN AT FS 750 JUST ABOVE STRINGER 18R. THE CRACK WAS REMOVED WITH A CUTOUT IN THE SKIN. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER B737-200 SRM 53-30-3, FIG 17 AND ER/A 380916-14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 45,411 hrs · 36,814 cycles

THE LOWER HINGE CUTOUT OF THE FWD ENTRY DOOR CUTOUT WAS FOUND WITH A 1 INCH CRACK. THE CRACK WAS ROUTED OUT AND REPAIRED WITH AN EXTERNAL STEEL DOUBLER PER B737 SRM 53-30-3 FIG 31 AND ER/A 379680-14, REV A.

Part: POWER SUPPLY — INOPERATIVE (CABIN) · airframe 44,787 hrs · 36,541 cycles

ON MTC CK FOUND R2 OVER DOOR EMERGENCY LIGHT AND AFT EXIT LOCATOR EMERGENCY LIGHT NOT ILLUMINATING ON TEST. REPLACED POWER SUPPLY.

Part: BULKHEAD — DAMAGED (FUSELAGE) · airframe 43,674 hrs · 36,047 cycles

INSPECTIONS OF THE FS 178 BULKHEAD STRUCTURE PER AD 2000-05-19, REVEALED CRACKS IN THE BULKHEAD STRUCTURE COMMON TO THE COCKPIT FLOOR (REF. DAL ER/A 377636-14AD). IN ORDER TO ACCESS THE AREA FOR REPAIR, AN ACCESS HOLE HAD TO BE CUT IN THE BULKHEAD WEB AT LBL 23 AND RBL 23 AT WL 211. THE ACCESS HOLES WERE REPAIRED PER B737 SRM 53-10-11, FIG. 5 WITH SOME FASTENER AND SHIMMING DEVIATIONS PER ER/A 377653-14AD,REV A.

Part: WEB — CRACKED (FUSELAGE) · airframe 43,674 hrs · 36,047 cycles

WHILE ACCOMPLISHING AD 2000-05-29 INSPECTIONS OF THE FS 178 BULKHEAD AND ADJACENT STRUCTURE, A 1 INCH CRACK WAS FOUND EMANATING FROM A LIGHTNING HOLE IN THE WEB OF THE HORIZONTAL FLOOR CLOSEOUT AT WL 207 ON BOTH THE LT AND RT SIDES OF THE AIRCRAFT. THE LT WEB WAS REMOVED AND REPLACED AND THE RT WEB WAS REPAIRED WITH AN ALUMINUM DOUBLER PER ER/A 377636-14AD, REV A.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 43,674 hrs · 36,047 cycles

A TYPICAL CRACK WAS FOUND IN THE FS 178 BULKHEAD WEB AT WL 233.5, RBL 7 DURING INSPECTIONS MANDATED PER AD 2000-05-29. THE CRACK WAS REPAIRED PER B737-200 SRM 53-10-11, FIG. 1 AND DOCUMENTED PER ER/A 377622-14AD.

Part: WARNING LIGHT — FALSE INDICATION (COCKPIT) · airframe 43,160 hrs · 35,825 cycles

LEFT, RIGHT AND APU FAULT DET ILLUMINATED. REPLACED COCKPIT FIRE CONTROL PANEL. GROUND CHECKS NORMAL. REPLACED FIRE DETECTOR MODULE PRECAUTIONARY OPS NORMAL. RAN ENGS, NO FAULT DET LIGHTS. OK FOR SERVICE.

Part: TURBINE WHEEL — DAMAGED (NR 1 ENGINE)

AT APPROX 400 FT AGL, LOUD BANG, NR 1 ENGINE FAILED 700 DEGREES EGT, WINDMILLING N1 AND N2 WAS BLOF T/O DUE TO GROSS WT. FOUND 3RD STAGE OF LPT DAMAGED. REPLACED ENGINE.

Part: BULKHEAD WEB — CRACKED (BS 1016)

WHILE ACCOMPLISHING LFEC INSPECTIONS OF THE AFT PRESSURE BULKHEAD WEB, A CRACK INDICATION WAS NOTED NEAR STRINGER 6R. INTERNAL HFEC INSPECTION CONFIRMED TWO CRACKED FASTENER HOLES AT THE WEB TO CAP INTERFACE AT STRINGER 6R. THE CRACKED AREA OF WEB WAS CUTOUT AND AN ALUMINUM DOUBLER INSTALLED PER ER/A 368012-14AD.

Part: SUPPORT — WORN (NR 2 ENGINE)

DURING INSP PER OPN 5264, FOUND BUSHING MIGRATED RT FWD ENG MOUNT SUPPORT FITTING. REPLACED SUPPORT FITTING PER EO 03-073535-12AD ME-04. FWD MOUNT SUPPORT ASSY PN 713701203.

Part: TIRE — FAILED (RT NLG TIRE)

EXPERIENCE NOSE WHEEL TIRE FAILURE AT ROTATION. CONTINUED TAKEOFF. INSPECTED AIRCRAFT AND FOUND RT NOSE TIRE TREAD CAP MISSING. REPLACED LEFT AND RIGHT NOSE WHEEL ASSYS PER MM. PERFORMED OVERWEIGHT LANDING INSP. NO DAMAGE TO FUSELAGE AND WINGS. ENGINE INLETS, CK OK.

Part: TIRE — FAILED (NR 2 WHEEL)

A/C BLEW NR 2 TIRE ON T/O FROM EWR. UPON LANDING IN MCO, LOST ALL 'A' SYSTEM HYDS AND HAD TO BE TOWED IN AFTER TIRE REPLACEMENT. REPLACED NR 1 AND 2 TIRES AND BRAKES, AFT FLAP, ANTI-SKID WIRING HARNESS, AND ASSOCIATED HARDWARE.

Part: COMPRESSOR — DAMAGED (NR 2 ENGINE)

DURING CRUISE AT FL370 FROM MCO-BOS, CREW EXPERIENCED HEAVY COMPRESSOR STALLS ON THE NR 2 ENGINE. CREW REDUCED POWER AND LANDED IN RDU. CONTRACT MTC INSPECTED ENGINE AND FOUND EXTENSIVE COMPRESSOR AND FAN BLADE DAMAGE. REPLACED ENGINE.

Part: FITTING — CORRODED (BS 685)

FUSELAGE LT AND RT MLG SIDE STRUT SUPPORT FITTING, BS 685. REPAIR FOR OVERSIZE LUG BORES. THE LUG BORES OF THE LT AND RT MLG SIDE STRUT SUPPORT FITTINGS AT BS 685 WERE FOUND CORRODED. THE LUG BORES WERE OPENED A MAX OF .11 IN DIAMETER. STEEL REPAIR SLEEVES WERE INSTALLED TO RESIZE THE HOLE BORES TO NOMINAL DIAMETER. THE REPAIR WAS ACCOMPLISHED PER ER/A 366342-14, REV A.

Part: ACTUATOR — FAILED (NR 5 LE SLAT)

LEADING EDGE AMBER LIGHT ON SLAT NR 5. REPLACED NR 5 SLAT AND ACTUATOR.

Part: BULKHEAD CHORD — CRACKED (BS 727)

A 0.5 INCH CRACK WAS FOUND IN THE MLG WHEEL WELL BLKHD AT STA 727. THE CRACK WAS LOCATED IN THE UPPER FLANGE OF THE COMPRESSION CHORD AT BL 0.0 AND RUNS THRU A FASTENER HOLE. REPAIRED PER ERA 365406-14.

Part: SKIN — CRACKED (R1 DOORWAY)

UPON HFEC AND LFEC INSPECTIONS OF THE UPPER AFT CORNER OF THE FWD GALLEY DOORWAY PER 3-58715-3AD, A CRACK WAS INDICATED. REPAIRED PER ERA 331849-14AD.

Part: SKIN — DENTED (BS 400)

FUSELAGE SKIN AND BONDED DOUBLER WERE FOUND DENTED BETWEEN S17L AND 18L AT FS 400. REPAIRED PER ERA 331844-14.

Part: SKIN — DAMAGED (BS 460-480)

FUSELAGE SKIN FS 460-480 STR 27R - 28L GROUND DAMAGE REPAIR. THE FUSELAGE SKIN BETWEEN FS 460 AND 480 AND BETWEEN STRG 27R AND 28L WAS DAMAGED BY A CARGO LOADER. DAMAGE CUT OUT RESULTED IN A 4 BY 7 CUTOUT AND A 2 BY 17 CUT OUT. DOUBLER AND TRIPLER REPAIR INSTALLED PER ER/A 363007-14.

Part: COALESCER BAG — DIRTY (AC BAY)

STRONG ODOR NOTED IN COCKPIT AND CABIN. REPLACED BOTH LT AND RT WATER BAGS, RAN PACKS OFF ENG AND NO SMELLS NOTED.

Part: HYD LINE — RUPTURED (NR 2 ENGINE)

ON CLIMBOUT AT 12000, THE MASTER CAUTION AND HYD LIGHTS ILLUMINATED ON GLARESHIELD PANEL. ENG NR 2 HYD PUMP LOW PRESSURE ILLUMINATED ON OVERHEAD PANEL, QTY WENT TO 0. RETURNED TO ATLANTA. MTC IN PROGRESS, BROKEN HYD PRESS LINE RT ENG PUMP. REPLACED LINE.

Part: BURNED OUT (CABIN)

EMERGENCY LIGHTS AT 1L DOOR AND ROWS 17 ABC, 21 ABC, AND 25 ABC INOPERATIVE.

Part: BULKHEAD WEB — CRACKED (BS 178)

DURING SPECIAL INSPECTION 3-69482-12, CRACKS WERE DISCOVERED ON THE FWD FACE OF THE FS 178 BULKHEAD WEB. THE FIRST CRACK IS LOCATED NEAR THE LBL 5.7 VERTICAL STRAP AT APPROX WL 203. THE SECOND IS NEAR THE RBL 5.7 VERTICAL STRAP AT APPROX WL 203. THE 3RD IS LOCATED NEAR BL 0 AT APPROX WL 195 AND THE FOURTH IS LOCATED NEAR RBL 14 AT WBL 184.5. CUTOUTS RESULTED IN 4 CUTOUTS MEASURING 1 BY 2.5, 1 BY 4.5, 2.5 BY 2.5 AN 1 DIA HOLE. THE ERA WILL REPAIR THE WEB WITH 2 REPAIR DOUBLERS, ONE INTERNAL AND ONE EXTERNAL BAC15 05-100361 7075-T6 EXTRUSION.

Part: VALVE — LEAKING (PARKING BRAKE)

ON CLIMBOUT, LOST A/B HYDRAULIC SYSTEM PRESSURE. FLIGHT RETURNED MSP. FOUND PARKING BRAKE VALVE LEAKING. REPLACED VALVE, SERVICED SYSTEM AND OPERATION NORMAL.

Part: SKIN — DELAMINATED (RUDDER)

RUDDER DELAMINATED AT TOP LEFT SIDE T/E NEXT TO PREV REPAIR. ACCOMPLISHED REPAIRS PER SRM 51-40-9 FIG 1 AND ERA 301817-14.

Part: SKIN — DELAMINATED (NR 6 SPOILER)

NR 6 SPOILER UPPER SURFACE DELAMINATED. REPAIRED PER SRM 57-50-5 FIG 5. FOUND AT M1 LTR CK.

Part: DOOR — CRACKED (CARGO COMPT)

FWD B/B DOOR PAN CRACKED AT FWD AND AFT CORNERS INSIDE RADIUS. REPAIRED PER DL ERA 301812-14.