N316DL

Part: SKIN — CRACKED (FUSELAGE) · airframe 56,868 hrs · 42,594 cycles

THE FUSELAGE SKIN AND UNDERLYING BEARSTRAP WERE FOUND CRACKED AT THE LOWER FWD CORNER OF THE R2 DOOR CUTOUT. THE CRACK WAS REMOVED WITH A 2.5 INCH CUTOUT IN THE SKIN AND BEARSTRAP. THE TRIMOUT WAS REPAIRED WITH 3 EXTERNAL ALUMINUM REPAIR DOUBLERS PER ER/A 397450-14, REV C.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 55,781 hrs · 41,797 cycles

FOUND ON W-2 LETTER CHECK STRINGER 27 LEFT CORRODED STA 967-1006. REPAIRED PER SRM 53-10-3 FIG 1.

Part: FRAME — CORRODED (FUSELAGE) · airframe 55,781 hrs · 41,797 cycles

FOUND ON W-2 LETTER CHECK CORROSION LOWER FRAME INBOARD OF STR 27L AT STA 1006. REPAIRED PER SRM 53-10-4 FIG 10.

Part: POWER SUPPLY — FAILED (EMERGENCY LIGHT) · airframe 55,506 hrs · 41,583 cycles

EMERGENCY INSEAT LIGHTING SEATS 21-24 INOP. REPLACED FUSE IN PWR SUPPLY M9013. CHECKS OK.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 55,165 hrs · 41,311 cycles

EMERGENCY PATH LIGHTS AT ROWS 22-25D INOP. REMOVED AND REPLACED POWER SUPPLY.

Part: CONTROL PANEL — SMOKE (COCKPIT OVERHEAD) · airframe 54,224 hrs · 40,597 cycles

PRIOR TO PUSHBACK FLT 1111 CREW SMELLED ELEC BURNING ODOR IN COCKPIT THEN NOTICED SMOKE COMING FRM F/O EYEBROW WINDOW AREA. FOUND SMOKE TO COMING FROM ENG/WING ANTI-ICE PANEL. REPLACED PANEL.

Part: WIRE — INOPERATIVE (EMERGENCY LIGHT) · airframe 53,937 hrs · 40,374 cycles

SEAT MOUNTED EMERGENCY LIGHTS INOPERATIVE AT ROWS 18-21. REPAIRED WIRING NOW OPS, NORMAL.

Part: WARNING SYSTEM — MALFUNCTIONED (COCKPIT) · airframe 50,348 hrs · 38,859 cycles

UPON INITIAL T/O ROLL EWR, AUTOBRAKE DISARM LIGHT ILLUMINATED. CYCLED RTO SWITCH AND THE AUTOBRAKE LIGHT ILLUMINATED AGAIN. PERFORMED AUTOBRAKE TEST PER M/M. UNABLE TO DUPLICATE.

Part: AUTOTHRUST SYS — MALFUNCTIONED (COCKPIT) · airframe 50,348 hrs · 38,859 cycles

T/O ROLL NOTICED ENGINE PARAMETERS FLUCTUATING. T/O ABORTED AUTOTHROTTLES WERE ENGAGED. MAINT OPERATED ENGS AT T/O PWR PER PFHB WITH OUT AUTOTHROTTLES ALL PARAMETERS CK NML. RAN ENGS AT T/O PWR AGAIN WITH AUTOTHROTTLES ENGAGED PER PFHB - NTF

Part: AIR DUCT — LEAKING (CABIN) · airframe 49,906 hrs · 38,672 cycles

FUMES IN CABIN AND COCKPIT. STRONGEST SMELL IN FIRST 5 ROWS OR SO. SMELLED LIKE RUBBER BURNING. NOTICED AT 2500 FT ABOUT 2 MINUTES AFTER DEPARTURE. FOUND GASPER AIR DUCT LEAKING AND RETAPED.

Part: HEATER — FAULTY (AFT LAVATORY) · airframe 49,103 hrs · 38,332 cycles

A/C DIVERTED TO CHS.SMOKE /ELECTRICAL SMELL IN AFT LAV/GALLEY FOLLOWED POM. PULLED C/B SMELL DISIPATED. FOUND SOURCE TO BE AFT LAV WATER HEATER

Part: STRINGER — CORRODED (FUSELAGE) · airframe 49,031 hrs · 38,301 cycles

CORROSION WAS FOUND ON STR 26 RT AT APPROXIMATLEY FS 500+12. THE AFTMOST END OF THE STRINGER WAS CUT OFF AND A NEW SECTION WAS SPLICED IN. THE CORROSION WAS FOUND AT HMV.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 49,031 hrs · 38,301 cycles

CORROSION WAS FOUND ON THE BS 1016 PRESSURE BULKHEAD WEB AT BL 0. REPAIR WAS ACCOMPLISHED PER S/B 737-53A1075. THE DAMAGE WAS FOUND DURING HMV.

Part: SKIN — CORRODED (FUSELAGE) · airframe 49,031 hrs · 38,301 cycles

CORROSION WAS FOUND IN THE FUSELAGE SKIN AND BEAR STRAP AT FS 490 BETWEEN STR 27R/28R. THE DAMAGE WAS CUT OUT AND A REPAIR DOUBLER INSTALLED. THE DAMAGE WAS FOUND AT HMV.

Part: FRAME — CORRODED (FUSELAGE) · airframe 49,031 hrs · 38,301 cycles

LOWER LOBE FRAME AT FS 500 WAS FOUND CORRODED AT THE INBD FLANGE BETWEEN STR 25R/26R. THE FLANGE WAS CUT OUT AND A REPAIR ANGLE INSTALLED. THE DAMAGE WAS FOUND AT HMV.

Part: FRAME — CRACKED (FUSELAGE) · airframe 49,031 hrs · 38,301 cycles

A CRACK WAS FOUND IN THE FS 492 FRAME AT STR 24 RT IN THE FLANGE. THE LENGTH OF THE CRACK IS 2.05 INCHES. THE CRACK WAS CUTOUT AND A REPAIR WAS INSTALLED PER SRM 51-40-3. THE DAMAGE WAS FOUND AT HMV.

Part: FITTING — CORRODED (FUSELAGE) · airframe 49,031 hrs · 38,301 cycles

THE LT MLG STRUT SUPPORT FITTING FRAME INSTALLATION HAD CORROSION LOCATED IN THE BORE. THE FITTING IS LOCATED AT FS 695, LBL 68.5 AND WL 188.5. THE CORROSION WAS REMOVED AND A REPAIR SLEEVE INSTALLED. THE DAMAGE WAS FOUND AT HMV.

Part: FITTING — CORRODED (HORIZOTAL STAB) · airframe 49,031 hrs · 38,301 cycles

CORROSION WAS FOUND ON THE LT AND RT HORIZONTAL STABILIZER ATTACH FITTINGS ON BOTH THE BORES AND FACES. THE CORROSION WAS REMOVED AND NEW BUSHINGS INSTALLED PER 397372-14 AT HMV.

Part: STRAP — CRACKED (HORIZONTAL STAB) · airframe 49,031 hrs · 38,301 cycles

CRACKS WERE FOUND AT THE CUTOUT IN THE FUSELAGE FOR THE HORIZONTAL STABILIZER SIMILIAR TO THE TYPICAL CRACKS OF S/B 737-53-1134. CRACKS WERE FOUND IN THE LT & RT STINGER 12 STRAP, FS 1140, AND THE LT & RT FS 1138 FRAME STRAPS. THE DAMAGE WAS REPAIRED PER SRM 53-00-01, FIGURE 22 AND 53-30-3, FIG. 30.

Part: FITTING — CORRODED (FUSELAGE) · airframe 49,031 hrs · 38,301 cycles

CORROSION WAS FOUND IN THE BORE AND FACES OF THE LT AND RT FUSELAGE CLEVIS LUGS FOR THE HORIZONTAL STABILIZER. THE CORROSION WAS REMOVED AND NEW BUSHINGS WERE INSTALLED PER ERA 397371-14AD AT HMV.

Part: ATTACH FITTING — CORRODED (FUSELAGE) · airframe 49,031 hrs · 38,301 cycles

THE LT MLG STRUT SUPPORT FITTING FRAME AT FS 685 HAD CORROSION AT THE SIDE STRUT ATTACH LUG LOCATED AT LBL 68.5 AND WL 188.5. CORROSION WAS FOUND IN THE BORE AND BOTH FACES. CORROSION WAS REMOVED AND A REPAIR SLEEVE INSTALLED.THE DAMAGE WAS FOUND AT HMV.

Part: FITTING — CORRODED (REAR SPAR) · airframe 49,031 hrs · 38,301 cycles

CORROSION WAS FOUND IN A FASTENER HOLE OF THE UPPER ROW COMMON TO THE REAR SPAR UPPER CAP OF THE MLG SUPPORT BEAM O/B AFT FITTING. ANOTHER FASTENER HOLE WAS MISDRILLED WHILE REPLACING THE AFT FITTING. THE FASTENER HOLES WERE OVERSIZED AND BUSHED PER ERA 397386-14 AT HMV.

Part: BEARING — WORN (HORIZONTAL STAB) · airframe 49,031 hrs · 38,301 cycles

WHILE PERFORMING JIC5957 FOUND PIVOT BEARING PLAY TO BE OUT OF LIMITS. IN THE PROCCESS OF REMOVING BEARING HOUSING FOUND SAFETY WIRE BROKEN AND KEEPER BACKED OFF APROX 1/4 INCH

Part: ACCESSORY UNIT — FAILED (E/E BAY) · airframe 48,344 hrs · 38,001 cycles

AT TOP OF DESCENT - ISOLATION VALVE LIGHT ILLUMINATED - THEN AFTER PLACING GEAR DOWN HAD NO GEAR LIGHTS RED OR GREEN. VISUALY CHECKED GEAR DOWN AND FOUND GEAR LIGHT C/B OUT. REPLACED LANDING GEAR ACCESSORY UNIT PER M/M

Part: BEAM — CRACKED (FUSELAGE) · airframe 46,532 hrs · 37,227 cycles

A CRACK WAS FOUND IN THE RT S18A SHEAR BEAM WEB AT BS 727. SUBJECT CRACK IS TYPICAL OF THOSE DEPICTED IN S/B 737-53-1066. THE CRACK IS LOCATED AT THE AFT, I/B MOST FASTENER LOCATION. THE SUBJECT SB IS NOT EFFECTIVE FOR AC 316. DAMAGE REPAIRED PER ERA 377513-14, REV A.

Part: WIRE — PINCHED (SEAT 1E) · airframe 45,753 hrs · 36,892 cycles

ON L/O, FOUND AISLE EMERGENCY EXIT LIGHTS INOP FWD OF WING. REPAIRED WIRING.

Part: BATTERY PACK — DISCHARGED (ROW 4, 6 & 8)

EMERGENCY LIGHTS AT ROWS 4, 6, 8 ABC OVERHEAD FAILED TO LIGHT ON TEST. REPLACED BATTERY PACK.

Part: COFFEEMAKER — FAILED (AFT GALLEY)

AFT GALLEY NR 2 COFFEEMAKER WHEN TURNED ON CAUSES SMELL OF HOT ELEC WIRES. INSPECTED CANNON PLUG, CKS OK. REPLACED COFFEEMAKER.

Part: LIGHTS — ODOR (GALLEY)

2L AFT GALLEY HAS ELECTRIC SMELL WHEN GALLEY LIGHTS ON. INSP AFT GALLEY FLUORESCENT LIGHTS AND WIRING, NO SIGNS OF BURNED WIRING. DEACTIVATED THRESHOLD AND WORK LIGHTS IN AFT GALLEY C/B PULLED AND COLLARD BEHIND CAPTS SEAT.

Part: COFFEEMAKER — MALFUNCTIONED (GALLEY)

DISCONTINUED TAKEOFF DUE TO ELECTRICAL ODOR IN AFT GALLEY. F/A REPORTED C/B PANEL WARM TO TOUCH. TURNED OFF GALLEY PWR AND RETURNED TO GATE. INSPECTED AFT GALLEY C/B PANEL AND WIRING, REPLACED BOTH COFFEEMAKERS AS A PRECAUTION. ALSO, CLEANED COFFEE RESIDUE FROM BENEATH COFFEEMAKERS. APPLIED ELECTRICAL PWR, SYS OPS NORMAL.

Part: FLOORBEAM — CRACKED (BS 660)

FUSELAGE OVERWING FLOORBEAM, UPPER CAP BL 0 FS 66, REPAIR FOR CRACKED CAP. THE OVERWING FLOORBEAM AT BL 0 WAS FOUND WITH A SEVERED UPPER CAP AT FS 662 WITH AN ADDITIONAL CRACK IN THE CAP AT FS 666. THE UPPER CAP WAS REPAIRED PER THE GUIDELINES OF BAC S/B 737-57-1210 AND DOCUMENTED PER ER/A 366316-14.

Part: HINGE — CRACKED (R1 DOOR)

THE LOWER GATE HINGE ON THE R1 DOOR WAS FOUND CRACKED. THE CRACKED HINGE WAS REMOVED AND REPLACED PER THE REQUIREMENTS OF BAC S/B 737-52A1124. THE REPAIR WAS DOCUMENTED PER ER/A 366007-14AD.

Part: SKIN — CRACKED (BS 740)

THE FUSELAGE SKIN AT FS 740 WAS FOUND WITH A 1.25 INCH LONG CRACK BELOW STRINGER 18R. THE CRACK WAS REPAIRED PER THE B737-200 SRM 53-30-3 FIG 1. THE REPAIR DOUBLER EXTENDS UNDER THE WING TO BODY FAIRING, SO INFRINGES ON SSI F-41. THE REPAIR HAS BEEN DOCUMENTED PER ER/A 366006-14 AND REQUIRES A DTA WITHIN 12 MONTHS.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

MID PATH LIGHTS INOP. REPLACED POWER SUPPLY.

Part: SKIN — CRACKED (BS 960)

THE SKIN ASSY AT THE LOWER FWD CORNER OF THE AFT ENTRY DOOR WAS FOUND WITH A TYPICAL CRACK THROUGH THE SKIN, DOUBLER, AND BEAR STRAP. THE CRACK WAS REPAIRED PER B737 SRM 53-30-3 FIG 24 EXCEPT BLIND FASTENERS WERE AUTHORIZED ON A TEMPORARY BASIS. THE REPAIR WAS ACCOMPLISHED PER ER/A 365132-14, REV A.

Part: FUSE — BLOWN (CABIN)

ON SERVICE CK DURING TEST OF EMERGENCY LIGHT SYTEM, FOUND AFT SECTION OF SEAT LIGHTS INOP. FOUND BLOWN FUSE ON PWR SUPPLY CKD FOR SHORTS, NONE FOUND. REPLACED PWR SUPPLY LIGHTS, CK NORMAL.

Part: FLOORBEAM — CORRODED (BS 328)

FLOORBEAM T-CAP FS 328 CORRODED AT LBL 27 AND FROM RBL12 TO RT SIDE OF FUSELAGE, C53-107-02. REMOVED ALL HARDWARE FROM DAMAGED BEAM SECTION. COMPLETED REMOVING DAMAGED SECTION. DRILLED REPAIR PARTS AND BEGAN INSTALLING REPAIR AND REPLACEMENT T-CAP PER M/M 53-21-0 PG 806. INSTALLED FASTENERS THROUGH Z-ANGLE. COMPLETED INSTALLATION PER M/M 53-21-0 PG 806.

Part: FLOORBEAM — CORRODED (FUSELAGE)

AT MIDVISIT, THE FLOORBEAM T-CAP WAS FOUND TO BE CORRODED SEVERAL PLACES, LBL 7 TO RBL O/B END. THE CORROSION WAS REMOVED PER SRM 51-10-6, ALL OUT OF LIMITS EXCEPT RBL 48. DAMAGED SECTION REMOVED AND REPAIR PARTS AND REPLACED T-CAP, DRILLED AND INSTALLED PER MM 53-21-0 PG 806.

Part: SOLENOID — FAILED (OXYGEN DOOR)

ON OXYGEN SYSTEM TEST ROW 14ABC OXYGEN DOOR DID NOT OPEN. REPLACED DOOR LATCH ACTUATOR SOLENOID.

Part: BULKHEAD — CRACKED (BS 178)

STATION 178 BULKHEAD WAS FOUND CRACKED IN SEVERAL LOCATIONS. DAMAGE CUTOUTS ARE 1 INCH X 2 INCH AT RBL 4, WL 200 AND WL 203, AND LBL 4, WL 200, AND A 1 INCH BY 1 INCH AT RBL 7 WL 200. IN ADDITION TO THE WEB CRACKS, THE VERTICAL CHORD HAS A .50 INCH CRACK AT LBL 5.7 AT WL 190. REPAIR ACCOMPLISHED PER ERA 304326-14 REV A.

Part: WATER SEPARATOR — CONTAMINATED (CABIN)

AFTER TAKEOFF, CVG UNABLE TO PRESSURIZE. OUTFLOW VALVE WAS FULL, CLOSED BOTH BLEEDS, AND LT PACK WERE ON AS WAS ISOLATION VALVE. OPEN CBS WERE ALL IN CABIN CLIMBED AND DESCENTED WITH THE A/C. REPLACED RT PACK WATER SEPARATOR BAG.

Part: SKIN — CRACKED (R-1 DOOR CUTOUT)

THE R-2 DOOR HAS A 1.3 INCH CRACK AT THE LOWER AFT CORNER. IT WILL BE REPAIRED PER THE SRM WITH THE EXCEPTION OF BLIND FASTENER SUBSTITUTION TO FACILITATE MAINTENANCE IN MEETING THE LETTER CHECK TIME LIMIT REQUIREMENTS PER DL ERA 302921-14.

Part: EEL BULB — FAILED (CABIN)

FOUND EMERGENCY AISLE LIGHT INOP AT 21ABC. RELAMPED, CKS GOOD.

Part: EEL BATTERY PACK — DISCHARGED (CABIN)

EMERGENCY LIGHTS ON LEFT HAND AFT DOOR ARE INOP. REPLACED BATTERY PACK, CKS GOOD.

Part: LE SKIN — DENTED (VERT STAB)

DURING SHOP INSPECTION, VERTICAL STABILIZER LEADING EDGE PANEL WAS REPAIRED FOR A DENT AT 51 INCHES FROM THE LOWER END OF PANEL. DAMAGE WAS REPAIRED PER SRM 55-30-6.