N309WA

Part: SKIN — CRACKED (FUSELAGE) · airframe 50,034 hrs · 34,094 cycles

FUSELAGE SKIN CRACKED AT CHEM MILL LINE AT STA 727E BETWEEN STR 23L AND 25L. REPAIRED IAW 091565-14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 50,034 hrs · 34,094 cycles

FUSELAGE SKIN CRACKED AT STA 767 AND STR 22R AT A CHEM MILL LOCATION. REPAIRED IN ACCORDANCE WITH ERA 091533-14.

Part: PSU — INOPERATIVE (19DEF) · airframe 49,491 hrs · 33,809 cycles

PAX SEAT 19DEF 02 MASKS DID NOT DEPLOY WHEN SWITCH IN COCKPIT PUSHED. REPLACED PSU.

Part: WIRE — SHORTED (GALLEY OVEN) · airframe 49,272 hrs · 33,683 cycles

AFT OVEN RIGHT SIDE DOUBLE HAD SMOKE COMING FROM BEHIND OVEN CONTROL. REMOVED OVEN, FOUND BURNED WIRES. REPAIRED SAME.

Part: FITTING — MISALIGNED (VERTICAL STAB) · airframe 47,102 hrs · 32,401 cycles

VERTICAL STABILIZER REAR TERMINAL FITTING LUGS WERE DETERMINED TO HAVE UNDERGONE PREVIOUS REWORK WHICH LEFT THE LUG THICKNESS LESS THAN BLUEPRINT SPECIFICATIONS AT EACH OF THE FOUR LUGS. AREA INSPECTED AND NEW BUSHINGS WERE FABRICATED PER DAL ER/A 384672-14 TO COMPENSATE FOR THE REWORK.

Part: SKIN — GOUGED (FUSELAGE) · airframe 47,102 hrs · 32,401 cycles

DURING HMV INSPECTIONS, THREE (3) DENTS WERE FOUND IN THE FUSELAGE SKIN BETWEEN FS 757 AND 767 IN THE BAY BETWEEN STRINGERS 20R AND 21R. ADDITIONALLY, FOUR (4) DENTS WERE FOUND BETWEEN FS 757 AND 767 IN THE BAY BETWEEN STRINGERS 21R AND 22R. ALL DENTS WERE WITHIN SRM LIMITS EXCEPT ONE (1) DENT JUST ABOVE STRINGER 22R, WHICH WAS CUTOUT. THE THREE (3) REMAINING DENTS BETWEEN S21R AND 22R WERE REWORKED AND A DOUBLER WAS INSTALLED OVER THE FOUR (4) DAMAGE LOCATIONS BETWEEN S21R AND 22R PER DAL ER/A 412529-14.

Part: SKIN — DENTED (FUSELAGE) · airframe 47,102 hrs · 32,401 cycles

REPAIR OF DENTA DENT WAS FOUND IN THE FUSELAGE SKIN BETWEEN STRINGER 17L AND 18L AT STA 360. THE DENTED MATERIAL WAS CUT OUT AND TWO EXTERNAL ALUMINUM DOUBLERS WERE INSTALLED PER ER/A 384678-14.

Part: SKIN — DENTED (FUSELAGE) · airframe 47,102 hrs · 32,401 cycles

A DENT WAS FOUND IN THE FUSELAGE SKIN BETWEEN STA 1000 AND 1016 AND BETWEEN STRINGERS 13L AND 14L THE DENT IS CUT OUT AND EXTERNAL DOUBLER AND FILLER ARE INSTALLED SIMILAR TO B737-200 SRM 53-30-3, FIG 48 BUT IN ACCORDANCE WITH ER/A 384711-14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,102 hrs · 32,401 cycles

DURING ACCOMPLISHMENT OF PERMANENT REPAIR OF FUSELAGE SKIN/DOUBLER CRACKING, ADDITIONAL CRACK WAS FOUND IN BOTH. THE DAMAGE WAS TRIMMED OUT AND TWO EXTERNAL DOUBLERS WERE INSTALLED WITH SOLID FASTENERS PER ER/A 366481-14, REV C.

Part: SKIN — WORN (FUSELAGE) · airframe 47,102 hrs · 32,401 cycles

THE FUSELAGE SKIN WITH AN AREA OF WEAR BETWEEN FS 857 & 877 NEAR STRINGER 1. THE DAMAGE WAS BLENDED SMOOTH AND AN AREA CUTOUT. THE DAMAGE WAS REPAIRED WITH AN ALUMINUM EXTERNAL REPAIR DOUBLER PER ER/A 384701-14, REV A.

Part: SKIN — CRACKED (FUSELAGE) · airframe 47,102 hrs · 32,401 cycles

THE FUSELAGE SKIN WAS FOUND DENTED AND CRACKED AT THE LOWER FWD CORNER OF THE C2 DOOR OPENING. THE DAMAGE WAS REMOVED WITH A 1.5 X 1 INCH CUTOUT TO THE CORNER THROUGH THE BONDED SKIN ASSY AND UNDERLYING BEAR STRAP. THE CORNER WAS REPAIRED WITH MULTIPLE ALUMINUM REPAIR DOUBLERS PER ER/A 384702-14.

Part: SKIN — DENTED (FUSELAGE) · airframe 47,102 hrs · 32,401 cycles

THE FUSELAGE SKIN WAS FOUND DENTED NEAR FS 470 BETWEEN STRINGERS 22L & 23L. THE DENT WAS REMOVED WITH A 7 INCHES CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER ER/A 384681-14, REV A.

Part: FITTING — CORRODED (NR 2 PYLON) · airframe 47,102 hrs · 32,401 cycles

THE AFT LUG OF THE CROWN BEAM FITTING ON THE NR 2 ENGINE PYLON WAS FOUND WITH CORROSION IN THE HOLE BORE. THE BORE WAS OVERSIZED TO 3.10 INCH TO REMOVE THE CORROSION. A STEEL REPAIR BUSHING WAS INSTALLED AND THEN A NEW BEARING. THE REPAIR WAS ACCOMPLISHED PER ER/A 384677-14.

Part: PROXIMITY SENSOR — FAULTY (CARGO DOOR) · airframe 45,209 hrs · 31,233 cycles

FWD CARGO DOOR LIGHT CAME ON DURING T/O AT 130 KTS. CONTINUED T/O AND RETURNED TO AIRPORT. CARGO DOOR IND LIGHT INTERMITTENT. REPLACED FWD CARGO DOOR SENSOR PER M/M, DOOR IND OPS NORMAL.

Part: BUSHING — WORN (NR 1 PYLON) · airframe 40,798 hrs · 28,425 cycles

THE STRUT CROWN BEAM ON THE NR 1 ENGINE PYLON WAS FOUND WITH A MIGRATED BUSHING. THE BUSHING WAS REMOVED AND WEAR DAMAGE DISCOVERED IN THE BORE. THE BORE WAS OVERSIZED TO REMOVE ALL DAMAGE AND AN OVERSIZE BUSHING INSTALLED. THE REPAIR WAS ACCOMPLISHED PER ER/A 378329-14, REV A.

Part: SKIN — CRACKED (BS 380)

FUSELAGE SKIN WAS FOUND CRACKED AROUND THE AFT EDGE OF THE E/E COMPT COOLING AIR EXHAUST DUCT CUTOUT AT BS 380, BL 0.0. THE CRACK EXTENDS AFT FROM THE EDGE OF CUTOUT. REPAIRED PER ERA 366476-14, REV B.

Part: BULKHEAD WEB — CRACKED (BS 178)

BS 178 BLKHD WEB WAS FOUND WITH 6 CRACKS, MAX CRACK CUTOUT WAS 1.6 BY 1. REPAIRED PER ERA 332820-14.

Part: INTERCOSTAL — CRACKED (BS 334)

R1 DOOR INTERCOSTAL AT STRINGER 8A FOUND CRACKED AT STA 334. CRACK REPAIRED PER S/B 737-53A1108 (REF ERA 332823-14AD). ACTION TAKEN, 332823-14AD.

Part: SKIN — CRACKED (NR 1 PYLON)

CRACK IN NR 1 PYLON STRUT SKIN AT THE ACCESS OPENING 5727L. ACTION TAKEN, 332810-14.

Part: OVEN CONTROLLER — MALFUNCTIONED (GALLEY)

ELECTRICAL SMELL AND SMOKE EMITTING FROM F/C GALLEY. COTNTRACT MTC CHECKING SAME. REPLACED BOTH CONTROLLERS.

Part: TRACK LIGHTS — INOPERATIVE (CABIN)

ON AIRCRAFT ARRIVAL, EMERGENCY PATH TRACK LIGHTING INOP. CONTRACT MTC CALLED OUT, PARTS SENT BUT WERE UNABLE TO CORRECT PROBLEM. FLIGHT FERRIED TO DFW. REPLACED AFT CABIN FLOOR TRACK LIGHTING POWER SUPPLY AND BATTERIES, REPLACED BOTH AFT EMRGENCY LIGHTING POWER SUPPLY AND BATTERIES, OPERATION NORMAL.

Part: SKIN — WORN (BS 870-890)

FUSELAGE SKIN (0.036 CLAD 2024-T3) UNDERNEATH THE VERTICAL STABILIZER FORWARD FAIRING FROM FS 870 TO 890 WAS FOUND WORN BEYOND B737-300 SRM 53-00-01 LIMITATIONS. THE WEAR WAS FOUND TO HAVE A MAXIMUM DEPTH OF APPROXIMATELY 0.012. ER/A WILL REPAIR THE DAMAGED AREA BY INSTALLING AN EXTERNAL DOUBLER. IT IS NOT NECESSARY TO CUTOUT THE DAMAGED AREA DUE TO MAXIMUM DAMAGED AREA OF 0.012 STILL LEAVES 66 PERCENT OF SKIN THICKNESS.

Part: ENGINE — FOD (NR 2 ENGINE)

SHORTLY AFTER T/O, AN ELEC ODOR DEVELOPED IN THE CABIN. COMPLIED WITH CHECKLIST. REMOVED SMALL AMOUNT OF COMPUTER PAPER FROM NR 2 ENG. RAN ENGINE PER PFHB, NO ODOR PRESENT. RAN ALL ELEC SYS AND A/C PACKS, NO PROBLEM FOUND. INSPECTED ENG PER M/M.

Part: FIRE DETECTOR — SHORTED (FWD LAV)

LAV FIRE WARNING LIGHT AND CHIME CAME ON TWICE DURING FLIGHT WITHOUT CAUSE. REPLACED FORWARD LAV DETECTOR UNIT, OPERATIONAL TEST NORMAL.

Part: SEAT TRACK — CORRODED (FS 328-344)

FOUND AT H.M.V. RT CTR SEAT TRACK CORRODED BETWEEN STA 328 AND 344. REPAIRED PER SRM 53-00-52 PG 202.

Part: SEAT TRACK — CORRODED (FS 328)

FOUND AT H.M.V. RT I/B SEAT TRACK CORRODED AT FS 328. REPAIRED PER SRM 53-00-52 PG 202.

Part: FLOOR SUPPORT — CRACKED (FS 727)

AT HMV, FOUND AFT B/B FLOOR SUPPORT CRACKED AT TIE DOWN FITTING STA 727B LT AND 727D RT. REPAIRED PER SRM 53-00-53 FIG 202.

Part: SKIN — DENTED (INBD SPOILER)

DURING ROUTINE INSPECTION, SEVERAL SMALL DENTS AND ONE SKIN PUNCTURE WERE FOUND ON INSIDE SKIN OF I/B SPOILER. DAMAGE WAS CAUSED FROM DEBRIS THROWN FROM THE MAIN LANDING GEAR. REPAIRED THE DAMAGE PER SRM 57-50-5.

Part: SKIN — CRACKED (LT ELEVATOR)

LT ELEVATOR TAB HINGE OPENINGS CRACKED SEVERAL PLACES. FOUND AT H.M.V. REPAIRED PER SRM 55-20-01.

Part: FLOOR SUPPORT — CORRODED (FS 947-967)

FLOOR SUPPORT CORRODED LBL 25 FS 947-967. FOUND AT H.M.V. REPAIRED PER SRM 53-00-52 FIG 204.

Part: FLOOR BEAM — CORRODED (FS 328)

FOUND AT HMV, FLOOR BEAM CORRODED AT FS 328. CORROSION AT BL 0 AND RIGHT OF BL. REPAIRED PER SRM 53-00-51 FIG 205.

Part: SEAT TRACK — CORRODED (FS 947)

LT I/B SEAT TRACK CORRODED AT F.S. 947. FOUND AT H.M.V. REPAIRED PER SRM 53-00-52.

Part: SKIN — DAMAGED (RT ELEVATOR)

FOUND AT H.M.V. RT ELEVATOR HAS SCAB PATCH ON BOTTOM SURFACE OF COMPOSITE. REPAIRED PER SRM 51-70-17.

Part: SKIN — DAMAGED (RT ELEVATOR)

RT ELEVATOR TAB HAS COMPOSITE BROKEN OUT AT HINGE OPENINGS. FOUND AT H.M.V. REPAIRED PER SRM 51-40-15.

Part: TE SKIN — DAMAGED (LT ELEVATOR)

LT ELEVATOR HAS INBOARD TRAILING EDGE DAMAGED. FOUND AT H.M.V. REPAIRED PER SRM 55-20-01. PART DAMAGED DURING ROUTING.

Part: WEDGE — DELAMINATED (TE FLAP)

AT HMV, FOUND FLAP TRAILING EDGE WEDGE DELAMINATED AT ITS OUTBOARD END. REPAIRED PER SRM 57-53-02.

Part: LE SKIN — WORN (NR 1 FOREFLAP)

NR 1 FOREFLAP, L/E WORN 14 INCHES FROM O/B END AND 56 INCHES FROM I/B END. REPAIRED PER SRM 57-53-01 FIG 201, AT HMV SHOP INSPECTION.