N312DL

Part: LINE — CHAFED (NR 2 ENG HYD SYS) · airframe 56,821 hrs · 42,523 cycles

A SYSTEM HYDRAULIC FAILURE ON FINAL, PRESSURE AND QUANTITY WENT TO ZERO. FOUND NR 2 ENGINE HYDRAULIC PUMP PRESSURE LINE CHAFED THROUGH. REPLACED LINE.

Part: SKIN — CRACKED (FUSELAGE) · airframe 56,538 hrs · 42,289 cycles

THE FUSELAGE SKIN WAS FOUND WITH A 2.5 INCH CRACK JUST BELOW STRINGER 18R AT FS 750. THE CRACK WAS REMOVED WITH A CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER ER/A 385880-14, REV A.

Part: BULKHEAD — CRACKED (AFT FUSELAGE) · airframe 56,538 hrs · 42,289 cycles

A SMALL CRACK WAS FOUND EMANATING FROM A FASTENER HOLE IN THE FS 1016 AFT P-DOME WEB AT BL 0, WL 244. THE CRACK EMANATED IN 2 DIRECTIONS FROM THE HOLE AND WAS TOTAL OF .625 INCH LONG (INCLUDING HOLE DIA). THE CRACK WAS REPAIRED WITH AN ALUMINUM REPAIR DOUBLER PER ER/A 385883-14, REV A.

Part: WEDGE — DENTED (L/E SLAT) · airframe 56,535 hrs · 42,285 cycles

FOUND ON W-1 LETTER CK, REPAIR LIFTING NUMBER 6 L/E SLAT T/E WEDGE 6 INCHES FROM O/B EDGE. REPAIRED PER SRM 51-40-20 AND OPERATION 1000.

Part: PANEL — DELAMINATED (VERTICAL STAB) · airframe 56,535 hrs · 42,285 cycles

FOUND ON W-1 LETTER CHECK, VERTICAL STAB COMPOSITE T/E PANEL DELAMINATED 2 PLACES LEFT SIDE, 1 PLACE RIGHT SIDE. REPAIRED PER SRM 55-30-3 FIG 3.

Part: ODOR — DETECTED (CABIN) · airframe 54,286 hrs · 40,975 cycles

BURNING SMELL FILLS AIRCRAFT WHILE GASPER FAN IS ON OR OFF. A/C FILLED WITH SMOKE AT GATE. ALL ELECTR POWER REMOVED AND SMOKE STOPPED. COCKPIT ELECTR LOAD CENTER (CB'S,RELAYS,FEEDER CABLES ETC), NO DISCREPANCIES NOTED. INSP E/E COMPT FOR FLUID LEAKS, NONE FOUND, ALSO INSP WIRING AND RACKS FOR ELECTRICAL MALF, NONE NOTED. INSP LT/RT A/C BAYS AND PLENUM AREA, ALL CKS OK. RAN A/C PACKS WITH APU AND ENG AIR, BOTH A/C PACK OPS NORMAL. PERF POWER RUN OF 01/02 ENGS PER PFHB, ALL SYS CK NORMAL UNDER VARYING ELECT/PNEU LOADS. R&R COALESCER BAGS.

Part: SKIN — CRACKED (FS 727, S-19R) · airframe 54,285 hrs · 40,974 cycles

FUSELAGE / SKIN / FS 727 / STRG. 19R : CRACK REPAIR THE FUSELAGE SKIN WAS FOUND WITH A 2.5" CRACK ALONG THE BONDED DOUBLER LINE AT STRINGER 19R. THE CRACK IS TYPICAL OF THOSE NOTED IN BAC S/B 737-53A1210. THE CRACK WAS REMOVED WITH A CUTOUT IN THE SKIN AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER THE B737 SRM AND PER ER/A 384189-14.

Part: HYDRAULIC LINE — BLOWN (NLG) · airframe 53,297 hrs · 40,546 cycles

LOSS OF A-HYD SYS WHEN LANDING GEAR HANDLE WAS LOWERED. BOTH LOW PRESS A-SYS LIGHTS ILLUM AND HYD QTY GAUGE WENT TO ZERO. LOUD BANG WAS HEARD WHEN GEAR WAS LOWERED. FOUND NOSE GEAR MAIN ACTUATOR PRESS LINE BLOWN. INSTALLED REPLACEMENT HYD LINE PER MM, HYD SERVICED TO FULL. CYCLED GEAR HANDLE. NO LEAKS, PRESS GOOD.

Part: GARLOCK SEAL — LEAKING (NR 2 ENGINE) · airframe 52,233 hrs · 40,107 cycles

NR 2 ENGINE OIL QUANTITY INDICATOR SLOWLY DROPPED TO 0.0 OIL PSI. OIL TEMPERATURE REMAINED WITHIN THE NORMAL OPERATING LIMITS. OIL PRESSURE, LOW YELLOW ARC AND FLICKERING OIL FILTER BYPASS LIGHT. ENGINE SHUTDOWN. FOUND STARTER GARLOCK SEAL LEAKING. REPLACED SAME. LEAK CK GOOD

Part: SKIN — CRACKED (FUSELAGE) · airframe 51,872 hrs · 39,953 cycles

AN EXISTING DOUBLER REPAIR WAS FOUND FOR REPAIR OF CRACK CUTOUT BELOW THE STRINGER 19L LAP JOINT AT FS 500. THE REPAIR DOUBLER WAS REMOVED FOR INSTALLATION OF A BETTER FATIGUE DESIGN REPAIR. THE EXISTING CUTOUT AND FASTENER HOLES WERE INSPECTED TO ENSURE NO CRACKS. A MORE FATIGUE FRIENDLY DOUBLER AND TRIPLER REPAIR WAS INSTALLED PER ER/A 382511-14, REV A.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 51,762 hrs · 39,910 cycles

EMERGENCY SEAT LIGHTS INOP AT SEAT ROWS 5 TO 9. REPLACED BATTERY CHARGER.

Part: FUSE — OPEN (CABIN) · airframe 51,672 hrs · 39,870 cycles

EMERG LIGHTS ROW 5-9 AND LT AND RT OVERWING HATCH EXIT SIGNS INOP. REPLACED 1EA FUSE IN FWD AND AFT POWER SUPPLIES. SYS OP NOW NORMAL

Part: FITTING — CORRODED (HORIZONTAL STAB) · airframe 48,610 hrs · 38,583 cycles

THE LT AND RT HORIZONTAL STABILIZER ATTACH FITTINGS WERE FOUND CORRODED. CORROSION WAS REMOVED FROM SEVERAL BORES AND FACES. THE DAMAGE WAS REPAIRED PER ERA 396666-14 AT HMV.

Part: FITTING — CORRODED (STABILIZER) · airframe 48,610 hrs · 38,583 cycles

CORROSION WAS FOUND ON THE VERTICAL STABILIZER ATTACHMENT LUGS AND FUSELAGE LUGS. SOME OF THE BORES WERE OVERSIZED AND SOME OF THE FACES WERE BLENDED PER ERA 396619-14 AT HMV.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 48,610 hrs · 38,583 cycles

CRACKS WERE FOUND IN THE WEB OF THE LONGITUDINAL FLOORBEAM BETWEEN FS 700 AND 717. THE WEB AND CHORDS WERE INSPECTED AND REPAIRED PER S/B 737-57-1210 AT HMV.

Part: LIGHT — INOPERATIVE (ESCAPE SLIDE) · airframe 46,217 hrs · 37,532 cycles

DURING LAYOVER, FOUND L2 SLIDE LIGHT INOP. RELAMPED LIGHT, CHECKS GOOD PER MM.

Part: LINE — CRACKED (HYD SYSTEM)

ON ARRIVAL PBI B-LOW QUANTITY LIGHT ILLUMINATED WITH LOSS OF HYD FLUID. INSTALLED INTRIM LINE BETWEEN NR 1 B-PUMP AND FILTER HOUSING. REF IPC 29-14-0-5E ITEM 156 (P/N 293201291).

Part: PANEL — LOOSE (FUSELAGE)

LOUD NOISE COMING FROM RT REAR OF AIRCRAFT, FELT VIBRATION ON PEDALS DURING CRUISE AT FL 150 AND 240. NO AIRCRAFT CONTROL PROBLEMS NOTICED. NO SIGNIFICANT PRESSURIZATION PROBLEMS NOTICED. INSPECTED A/C PER MM 5-51-281. FOUND DEBRIS ON AFT PRESS RELIEF VALVE AND LOOSE INSULATION AROUND SAME. REMOVED DEBRIS AND SECURED INSULATION. ALSO, FOUND LT RAM AIR DOOR SEAL TORN, KEEL BEAM AFT W/W PANEL LOOSE AND APU RAM AIR INLET DOOR LOOSE. SECURED PANELS, REPLACED APU INLET DOOR ACT AND HARDWARE, DEFERRED LT RAM AIR INLET DOOR SEAL.

Part: TEMP BULB — FAILED (NR 1 ENGINE)

SHUT DOWN NR 1 ENGINE IN FLIGHT DUE TO HIGH OIL TEMP. FOUND NR 1 ENG OIL TEMP BULB OPEN. REPLACED TEMP BULB PER M/M, OPN CKD GOOD. LK CK GOOD. RAN ENG PER PFHB. ALL CKS GOOD.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

EMERGENCY LIGHTS FLASHING RT AISLE AND AFT BULKHEAD. REPLACED POWER SUPPLY.

Part: ELT LOCATOR — DAMAGED (COCKPIT)

DURING L/O CHECK, FOUND ELT BEACON DAMAGED. REPLACED BEACON.

Part: BATTERY PACK — DISCHARGED (CABIN)

EMERGENCY EXIT LIGHTS INOP AT ROWS 1, 2, 3. REPLACED BATTERY PACK AND POWER SUPPLY FOR CABIN LIGHTS.

Part: STRINGER — CRACKED (BS 727)

THE LT KEEL CHORD STR 27L WAS FOUND CORRODED AND CRACKED AT STA 727A. THE DAMAGE IS SEVERE ENOUGH THAT THE CHORD WILL HAVE TO BE REPLACED. THIS WILL REQUIRE 5 FRAMES, STA 727B THROUGH STA 807 TO BE CUT TO ALLOW REPLACEMENT OF THE CHORD.

Part: FITTING — CRACKED (LT MLG)

THE LEFT WING OUTBOARD AFT SUPPORT FITTING FOR THE MAIN LANDING GEAR BEAM WAS FOUND CRACKED. CRACKING IS TYPICAL TO THAT DESCRIBED IN BOEING SERVICE BULLETING 737-57-1216. SHIP 312 IS IDENTIFIED AS A GROUP 5 BY THE SERVICE BULLETIN. THE CRACKED FITTING WILL REMAIN IN SERVICE ON A TIME LIMITED BASIS AND WILL BE REPAIRED ACCORDING TO SERVICE BULLETIN REQUIREMENTS.

Part: ANGLE — CORRODED (L1 DOORWAY)

L-1 DOORWAY FLOOR Z- ANGLE CORROSION ENTIRE LENGTH. AUTHORIZED METHOD OF REPAIR. REPAIR PER M/M 53-21-0. CORRECTION - REMOVED DRAIN FROM Z-ANGLE. BEGAN CORROSION REMOVAL PER SRM 57-10-6. DRILLED UP NEW Z-ANGLE. TREATED/ PRIMED AREA, BEGAN INSTALLATION OF NEW Z-ANGLE. COMPLETED REPAIR OF Z-ANGLE PER M/M 53-21-0 AND REINSTALLED DRAIN.

Part: SKIN — CRACKED (L2 DOORWAY)

A CRACK WAS FOUND IN THE FUSELAGE SKIN AT THE L2 DOOR CUT-OUT IN THE UPPER AFT CORNER. THE CRACK WAS LOCATED IN THE INNER LAYER OF THE BONDED SKIN ASSEMBLY AND MEASURED APPROX. 1.75 INCHES IN LENGTH. THE CRACK WAS REPAIRED PER S/B 737-53-1149.

Part: SKIN — CRACKED (GALLEY DOORWAY)

THE R-1 DOORWAY CRACKED AT THE LOWER AFT CORNER APPROX 1.4 INCH LENGTH. THE CRACK WILL BE REPAIRED PER B737-200, SRM 53-30-3 FIG 26 WITH THE EXCEPTION OF BLIND FASTENER SUBSTITUTION TO FACILITATE MTC. ALSO, FOUND THAT THE CRACK ENDED IN A NUTPLATE HOLE WHICH WILL BE PLUGGED PER THE SRM. SINCE THE NUTPLATE HOLE IS AN ATTACH POINT FOR THE SCUFF PLATE, THE SCUFF PLATE WILL BE TRIMMED TO DELETE THE HOLE LOCATION. ALSO, THERE IS A PREVIOUS REPAIR APPROX 2 INCHES OUTBD OF WHERE THIS REPAIR WILL EXTEND.

Part: ACTUATOR — FAILED (NR 4 SLAT)

NR 4 SLAT ACTUATOR FAILED TO EXTEND ON APPROACH. REPLACED NR 4 SLAT ACTUATOR, CHECKS OK.

Part: BLKHD WEB — CRACKED (FS 178)

REF. E.O. 03-069482-12 OPN. 445. WEB IS CRACKED AT TWO LOCATIONS JUST INBOARD AND ONE LOCATION JUST OUTBOARD OF THE VERTICAL STIFFENER AT LBL 5.7 BETWEEN WL 207 AND WL 184. WEB IS CRACKED AT TWO LOCATIONS JUST INBOARD OF VERTICAL STIFFENER AT RBL 5.7 BETWEEN WL 207 AND WL 184. REPAIRED PER SRM 53-10-11. REF. E.O. 03-069482-12 OPN. 430. CRACK AT FASTENER AT RBL 15, WL 234, F.S. 178 BULKHEAD WEB. REPAIRED PER SRM 53-10-11, AND DL ERA 303106-14. REF. S/B 737-53-1173.

Part: FLOORBEAM — CRACKED (FS 663)

THE BL 0.07 FLOOR BEAM OF THE WING CENTER SECTION IS CRACKED AT STA 663, AND THE UPPER CAP OF THE BEAM IS COMPLETELY CRACKED. THE WEB AND WEB DOUBLER ARE CRACKED APPROXIMATELY 4 INCHES AT THE SAME LOCATION. THE CRACKS ARE TYPICAL PER BOEING SERVICE BULLETIN REPAIR FOR THIS CONDITION. THE 65C34537-11 REINFORCING ANGLE COULD NOT BE INSTALLED PER THE SERVICEBULLETIN, SO THE ORIGINAL REINFORCEMENT ANGLE WILL BE REINSTALLED.