N304AW

Part: CONNECTOR — DIRTY (AUTOPILOT SYS) · airframe 44,472 hrs · 31,557 cycles

SPEED TRIM FAIL LIGHT ILLUMINATED DURING FLIGHT. PLACED ON MEL 22-10. CLEANED AND RESECURED CANNON PLUG ON FCC PER MM 22-11-33. PERFORMED BITE TEST PER MM 22-11-01. TEST PASSED. CLEARED MEL.

Part: COMPUTER — MALFUNCTIONED (AUTOTHROTTLE) · airframe 44,213 hrs · 31,381 cycles

AUTO THROTTLE DISCONNECTED ON TAKEOFF ROLL. REMOVED AUTO THROTTLE COMPUTER AFTER TROUBLESHOOTING. REINSTALLED AUTO THROTTLE COMPUTER AND PERFORMED BITE TEST PER MM 22-10-04. OPS CHECKED NORMAL.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 44,192 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK CORROSION WAS FOUND ON FLOOR SUPPORT BEAM AND NUTPLATES IN THE AFT CARGO COMPARTMENT AT BS 727+6, LBL 2.5. MAINTENANCE REMOVED CORROSION AND FOUND MATERIAL LOSS BEYOND LIMITS IAW B737 300 SRM 53-60-53, FIG 101, SHT 8. FABRICATED 2 EACH REPAIR ANGLES FROM 7075-0-.071, 7075-0-.081, HEAT TREATED AND PRIMED, AND INSTALLED REPAIR PARTS AT BS 727+6, LBL 2.5 IAW B737-300 SRM 53-00-53, FIG. 201, PG. 203.

Part: SKIN — DENTED (HORIZ STAB) · airframe 44,192 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK A DENT WAS FOUND ON RT HORIZONTAL STABILIZER AT STAB STA 144 MID SPAN. FABRICATED A DOUBLER, FILLER AND INSTALLED REPAIR PARTS IAW B737-300 SRM.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 44,192 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK CORROSION WAS FOUND ON FLOOR SUPPORT BEAM AND NUTPLATE IN THE AFT CARGO COMPARTMENT AT BS 860, LBL 2.5. MAINTENANCE REMOVED THE NUTPLATE AND CLEANED CORROSION ON FLOOR SUPPORT BEAM AT FS 860, LBL 2.5 IAW 51-40-02 PG 1, 53-60-53, PG 108, .047 MATERIAL REMAING. FABRICATED 2 EACH REPAIR ANGLES, TREATED AND PRIMED ANGLES, AND INSTALLED REPAIR PARTS IAW B737-300 SRM 53-00-53, PG. 201, MM 51-21-21 PG. 705-705.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 44,192 hrs · 31,365 cycles

MAJOR REPAIR - DURING C-15 CHECK CORROSION WAS FOUND ON THE TOP OF FLOORBEAM AT BS 986.5, LBL 58. MAINTENANCE CLEANED CORROSION OFF FLOORBEAM AND FOUND MATERIAL LOSS EXCEEDING ALLOWABLE LIMITS. FABRICATED FLOORBEAM REPAIR STRAP AND INSTALLED REPAIR PART AT BS 986.5, LBL 58.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 44,192 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK CORROSION WAS FOUND ON FLOOR SUPPORT BEAM AND NUTPLATES IN THE AFT CARGO COMPARTMENT AT BS 727D+6, LBL 7.5. MAINTENANCE REMOVED CORROSION IAW B737-300 SRM 51-10-2, PG. 24, FABRICATED 2 EACH REPAIR ANGLES FROM 7075-0-.071, 7075-0-.080, HEAT TREATED TO 7075-T6, PRIMED, AND INSTALLED REPAIR PARTS AT BS 727D+6, LBL 7.5 IAW B737-300 SRM 53-00-53, FIG. 201, PG. 203.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 44,192 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK EXFOLIATED CORROSION WAS FOUND ON AFT PIT FLOOR SUPPORT AT BS 860, LBL 12.5. MAINTENANCE CLEANED CORROSION AND FOUND MATERAIL LOSS OUT OF LIMITS. FABRICATED AND INSTALLED 2 EACH REPAIR ANGLES IAW B737-300 SRM 53-00-53, PG. 203, FIG. 201.

Part: STRAP — CORRODED (FUSELAGE) · airframe 44,192 hrs · 31,365 cycles

MAJOR REPAIR - DURING C-15 CHECK CORROSION WAS FOUND ON THE RT FLOOR SUPPORT LOWER STRAP IN THE AFT CARGO COMPARTMENT AT BS 849, RBL 19. MAINTENANCE REMOVED CORROSION AND FOUND MATERIAL LOSS OUT OF LIMITS. REMOVED CORRODED STRAP AT RBL 19, BS 849, FABRICATED AND INSTALLED A NEW STRAP.

Part: FRAME — CRACKED (FUSELAGE) · airframe 44,192 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK A 1.5 INCH CRACK WAS FOUND ON CABIN SIDE WALL FRAME ATTACHED TO FLOORBEAM AT BS 616, LBL 66, WL 208, LOCATED JUST BELOW FLOOR LINE UNDER THE OVERWING EMERGENCY EXIT. MAINTENANCE REMOVED INNER CHORD, FABRICATED NEW INNER CHORD AND INSTALLED REPAIR IAW B737-300, SRM 53-00-07 PG 101-104, AND DWG 65-46539.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 44,192 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK EXFOLIATION CORROSION WAS FOUND ON FLOOR SUPPORT BEAM AND NUTPLATES IN THE AFT ACRGO COMPARTMENT AT BS 860, LBL 7.5. MAINTENANCE FABRICATED 3 EACH REPAIR ANGLES, TREATED AND PRIMED, AND INSTALLED REPAIRS IAW B737-300 SRM 53-00-53, FIG 201, SHT 1-3.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 44,192 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK EXFOLIATION CORROSION WAS FOUND ON FLOOR SUPPORT BEAM IN THE AFT CARGO COMPARTMENT AT BS 860, RBL 7.5. MAINTENANCE FABRICATED 2 EACH REPAIR ANGLES, TREATED AND PRIMED ANGLES, AND INSTALLED REPAIR PARTS IAW B737-300 SRM 53-00-53, FIG 201, PG. 201-203.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 441,923 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK CORROSION WAS FOUND ON AFT CARGO PIT RT FLOOR SUPPORT BEAM BS 727D+6, RBL 7.5. MAINTENANCE REMOVED CORROSION AND MATERAIL REMAINING .039, FABRICATED 2 EACH REPAIR ANGLES FROM 7075-0.071, 7075-0-.081, HEAT TREATED IAW B737-300 SRM 53-00 FIG 201 SHT 1-3 & TPS-1003, TRIMMED, DRILLED, DEBURRED, TREATED, PRIMED, INSTALLED ANGLES AT BS 727D+6, RBL 7.5 IAW B737-300 SRM 53-00-53 FIG 201, SHT 1-3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 44,192 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK CORROSION WAS FOUND ON AFT CARGO PIT FLOOR SUPPORT NUT PLATE BS 860, RBL 2.5. MAINTENANCE REMOVED NUT PLATE AND CORROSION AT BS 860, RBL 2.5. MATERAIL REMAINING .031, FABRICATED 2 EACH REPAIR ANGLES, HEAT TREATED, TRIMMED, DRILLED, DEBURRED, TREATED, PRIMED, AND INSTALLED ANGLES IAW B737-300 SRM 51-40-02, PG 1, 53-60-53, PG 108, ASTM E797-95, 53-00-53, PG 201 AND 51-21-21, PG 703-705.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 44,192 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK A CRACK WAS FOUND RUNNING FROM SEAT TRACK FLOORBEAM TEE CAP LOWER EDGE TO A FASTENER HOLE ON INBOARD SIDE, BS 663.75, RBL 26. FABRICATED A REPAIR STRAP, SHIMS AND INSTALLED REPAIR PARTS IAW B737-300 SRM 51-40-02 PG 10 AND CP2-LCQ-02-00007H, PG 1 & 2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 44,192 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK GALVANIC CORROSION WAS FOUND ON FLOOR SUPPORT AND NUTPLATES IN THE AFT CARGO PIT AT BS 773, LBL 2.5. MAINTENANCE REMOVED NUTPLATES AND CLEANED CORROSION, FABRICATED 2 EACH REPAIR ANGLES AND INSTALLED REPAIR PARTS IAW B737-300 SRM 53-00-58, FIG. 201, PG. 203.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 44,192 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK CORROSION WAS FOUND ON FLOOR SUPPORT BEAM IN THE AFT CARGO COMPARTMENT AT BS 773, RBL 2.5. MAINTENANCE CLEANED CORROSION ON FLOOR SUPPORT BEAM AT FS 773, RBL 2.5 AND FOUND MATERIAL LOSS TO BE OUT OF LIMITS. FABRICATED 2 EACH REPAIR ANGLES, TREATED AND PRIMED ANGLES, AND INSTALLED REPAIR PARTS IAW B737-300 SRM 53-00-53, FIG 201, SHT 201-203.

Part: SKIN — CRACKED (FUSELAGE) · airframe 44,192 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK A .250 INCH CRACK WAS FOUND ON THE SKIN OF THE L2 DOOR CUTOUT AT BS 986.5, STR 8 LT. FABRICATED REPAIR DOUBLERS AND INSTALLED IAW B737-300 SRM.

Part: STRINGER — CORRODED · corrosion level 0 · airframe 44,192 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK EXFOLIATION CORROSION WAS FOUND ON STRINGER IN THE AFT CARGO COMPARTMENT BS 1010, STR 27 R/H. MAINTENANCE REMOVED CORRODED STRINGER 27 R/H AT STA 1010, FABRICATED AND INSTALLED A NEW STRINGER IAW B737-300 SRM 51-10-2, PG. 12, SRM 51-40-2, PG. 1, AND BMM 20-50-11, PG. 204.

Part: SKIN — CRACKED · corrosion level 0 · airframe 44,192 hrs · 31,365 cycles

LCQ - MAJOR REPAIR - DURING C-15 CHECK 3 EACH .300" CRACKS WERE FOUND ON LOWER AFT RADIUS RIVET PATTERN OF R1 DOOR CUTOUT. MAINTENANCE CUTOUT CRACKED AREA OF SKIN, PERFORMED HFEC INSPECTION TO VERIFY CRACKS WERE CONTAINED, FABRICATED 2 EACH REPAIR DOUBLERS AND INSTALLED REPAIR PARTS AT R1 DOOR LOWER AFT CORNER IAW B737-300 SRM 53-10-01, FIG. 202, PG. 204-208.

Part: POWER SUPPLY — FAILED (CABIN) · airframe 43,867 hrs · 31,152 cycles

AFT EMERGENCY EXIT LIGHTS FROM ROW 18 LT, ALL THE WAY AFT WILL NOT ILLUMINATE DURING TEST. MAINTENANCE TROUBLESHOT AND FOUND THE AFT POWER SUPPLY INOPERATIVE AT BS 947, REPLACED POWER SUPPLY IAW BMM 33-51-51, EMERGENCY EXIT LIGHTS OPERATIONALLY CHECKED GOOD.

Part: CREASE BEAM — CORRODED (FUSELAGE)

BS 767-787 LT CREASE BEAM PANEL IS CORRODED. SHEAR WEB MADE AND INSTALLED AS PER DWG 65-55885-3, PART PAINTED AS PER MM 51-21-10 PG 701.

Part: WEB — CRACKED (STA 178)

D: Web Crack on Floor Level (WL 207) At STA .178 on R/H Side RBL 28C: Removed Cracked Web, Fabricated New Web P/N 65-45833-40 Per REF DWG 65-45833, install Web Per 45-45833

Part: BULKHEAD — CRACKED (FUSELAGE)

WEB CRACKS AT STA 178 LBL 5.7. REMOVED FASTENERS PER SRM 51-40-2 AT REPAIR AREA. REPAIRED CRACKS PER SRM 53-10-08 FIG 209. NDT CHECKED CRACKS CONTAINMENT. FABRICATED REPAIR PARTS PER SRM 53-10-08 FIG 209 SH-3. PROTECTIVE TREATMENT FOR REPAIR PARTS PER SRM 51-20-01 FR PRIMED REPAIR PARTS PER SOPM 20-41-02. INSTALLED REPAIR PARTS PER SRM 53-10-08 FIG 209. PAINTED AREA WHITE PER SRM 51-21-99.

Part: STRINGER — CRACKED (STA 178, WL 207,)

D: Stringer crack at STA 178. WL 207. RBL 28C: fabricated repair parts per SRM 51-70-12 Fig 1 detail 7. Installed repair parts per SRM 51-70-12 Fig 1

Part: FRAME — CRACKED (FUSELAGE)

FUSELAGE LT SIDE CHORD AT WL 207 STA 178 CRACKED. INSTALLED NEW 65-16300-86 SIDE CHORD AS PER DWG 65-16300 SHEET 4 FRAME 1 TO 8.

Part: FRAME — CRACKED (FUSELAGE)

FUSELAGE RT SIDE CHORD AT WL 207, STA 178 CRACKED. INSTALLED NEW SIDE CHORD P/N 65-16300-87 AS PER DWG 65-16300 SHEET 4 FRAME 1-8.

Part: WEB — CRACKED (STA 178)

D: Center Bulkhead Web Crack At Body STA .178 . WL 187. BLO.C: Remove Crack Per SRM 53-10-08 Fig 203. NDT Checked For Crack Containment. Frabricate Repair Parts and installed Per SRM 53-10-08 Fig 203

Part: SKIN — DAMAGED (FUSELAGE)

FUSELAGE SKIN HAS A NON STANDARD REPAIR AT RIVET LOCATION BS 727C AND 2 INCHES BELOW STRINGER 17L. FUSELAGE SKIN REPAIRED AT BS 727C AND 2 INCHES BELOW STR 17L PER SRM 53-00-01 FIG 203 PAGE 207.

Part: TEE CHORD — CRACKED (CARGO DOOR)

CRACK INDICATION ON AFT CARGO DOOR LOWER AFT CORNER, LOWER WEB TO SKIN ATTACH ANGLE, CRACK, LOCATED BETWEEN TWO AFT RIVETS WEB. AFT LOWER WEB T-CHORD REPAIRED PER SB 737-52A1079/DRW 65 C25 180 + SRM 51-40-02 PG 4.

Part: BLEED VALVE — FAILED (NR 1 ENGINE) · airframe 34,292 hrs · 24,343 cycles

AIR TURNBACK, NR 1 ENGINE BLEED AIR VALVE W/N CLOSE, CURCUIT BREAKER POPPED. REMOVED AND REPLACED NR 1 ENGINE BLEED AIR REGULATOR. TT 0049297 M+E=03-3611-9-0001. RECOMMENDATION: REMAIN OPEN PENDING REVIEW OF TEARDOWN REPORT.

Part: STRUCTURE — CRACKED (VERTICAL STAB) · airframe 39,407 hrs · 28,166 cycles

C-CHECK, VERT STAB UPPER RUDDER HINGE POINT RT STRUCTURE HAS CRACK AT CORNER. REMOVED DAMAGED CORNER COVER, FABRICATED REPAIR COVER IAW 737 SRM 51-30-30, 51-20-02, AND 51-40-02, TREATED AND PRIMED IAW 737 SRM 51-20-06, INSTALLED IAW 737 SRM 51-40-02.

Part: SKIN — CRACKED (LE SLATS) · airframe 39,407 hrs · 28,166 cycles

C-CHECK, CRACKS IN LOWER SKIN OF THE LEADING EDGE OF NR 2 AND NR 3 SLATS. REMOVED DAMAGED AREA IAW ER NR 3-57-55-17E, FABRICATED FILLERS FROM MAT SHT 77075 T6 X .063 QQA 250, 2 DOUBLERS FROM 2024T3 QQA 250/5, INSTALLED FILLER AND DOUBLER IAW 737 SRM 51-40-02.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 39,407 hrs · 28,166 cycles

C-CHECK, CORROSION OUT OF LIMITS ON T-CAP AT FS 986.5 RBL 18. REMOVED DAMAGED T CAP IAW 737 SRM 51-40-02, FABRICATED T CAP FROM BAC 1505 100617/7077, IAW 737 SRM 53-00-51, TREATED AND PRIMED IAW 737 SRM 51-20-01, INSTALLED REPAIR PARTS IAW 737 SRM 53-00-51 AND 51-40-02.

Part: MODULE — INOP (COCKPIT WINDOW)

NML OPS, ELECTRICAL SMELL IN COCKPIT. UNKNOWN ELECTRICAL SMELL IN COCKPIT. INSPECTED COCKPIT, RAN ENGINES ISOLATED ODOR TO P5-9 WINDOW, PITOT HEAT MODULE. REPLACED PER MM 30-09-11. ACFT OK FOR SERVICE (TAG 014234).

Part: FLOORBEAM — CORRODED (BS 328)

CORROSION AROUND SCREW HOLES TOP AND BOTTOM OF UPPER TEE CHORD RBL 21-56, FRAME STA 328 RT. FABRICATED T-CHORD AND REPAIR AS PER AWA ER 3-53-1529 INSTRUCTIONS.

Part: FLOORBEAM — CORRODED (BS 294.5)

FLOORBEAM UPPER CHORD CORRODED RBL 6 TO RBL 52 AT STA 294.5. FABRICATED T-CHORDS AND REPAIRED AS PER AWA ER 3-53-1529 INSTRUCTIONS.

Part: FLOORBEAM — CORRODED (BS 986.5)

FLOORBEAM 986.5 REQUIRES REPAIR SPLICES IAW AWA ER 3-53-1529 DUE TO CORROSION ON T-CAP. FABRICATED T-CHORDS AND REPAIRED ANGLES PER AWA ER 3-53-1529 INSTRUCTIONS, 986.5 FLOORBEAM T-CAP REPLACED RT BL TO LT BL ALL INCLUSIVE SPLICE.

Part: CONTROLLER — FAILED (LT COCKPIT)

SMOKE CAME OUT OF THE AFT PORTION OF THE COPILOTS FORWARD WINDOW, NEAR THE DRAIN HOSE. THE WINDOW HEAT WAS TURNED OFF AND THE SMOKE WENT AWAY. REMOVED AND REPLACED THE COPILOTS NR 1 WINDOW HEAT CONTROLLER.

Part: SKIN — DENTED (CARGO DOOR)

DURING ROUTINE MAINTENANCE CHECK, FOUND C-2 DOOR AFT CARGO OUTER SKIN DENTED AND CREASED IN SEVERAL PLACES. REMOVED AND REPLACED C-2 DOOR OUTER SKIN IAW B737, SRM 52-30-01 AND 51-40-02. MAT ID 2024-T3 .071. FABRICATED NEW DOOR SKIN IAW B737 SRM 52-30-01.

Part: SKIN — DENTED (FUSELAGE)

PHX - FLT NR 842 - DURING ROUTINE MAINTENANCE CHECK, FOUND FUSELAGE SKIN DENTED ACROSS STRINGER 25R, 4 FEET FORWARD OF AFT CARGO DOOR CUTOUT. OPENED UP INTERIOR FOR INSPECTION AND NO DAMAGE NOTED. FUSELAGE SKIN WITHIN LIMITS PER SRM 53-00-01, FIGURE 101. NDT INSPECTION COMPLIED WITH ON W/O NR 7516-01-A336. (M)

Part: OUTFLOW VALVE — FAILED (CABIN)

PHX/BUR - FLT 0484 - AUTOPRESSURE INOPERATIVE AT 280 FEET CABIN ALTITUDE AT 3,000 FEET, DIFFERENTIAL PRESSURE 8.4. REMOVED AND REPLACED REAR OUTFLOW VALVE. OPS CHECKED GOOD. REMOVED AND REPLACED CABIN PRESSURE CONTROLLER. OPS CHECKED GOOD. REFERENCE CONTROL NR 96ZZZX565. (X)

Part: CONTROLLER — FAILED (CABIN)

PHX/BUR - FLT 0484 - AUTOPRESSURE INOPERATIVE AT 280 FEET CABIN ALTITUDE AT 3,000 FEET, DIFFERENTIAL PRESSURE 8.4. REMOVED AND REPLACED REAR OUTFLOW VALVE. OPS CHECKED GOOD. REMOVED AND REPLACED CABIN PRESSURE CONTROLLER. OPS CHECKED GOOD. REFERENCE CONTROL NR AWXA960011.

Part: COVER — LOOSE (GALLEY)

LAS - FLT 1512 - DURING ROUTINE MAINTENANCE CHECK, FOUND EMERGENCY EXIT LIGHT COVER IN FORWARD GALLEY LOOSE. REPLACED EMERGENCY LIGHT ASSEMBLY. OPS CHECK GOOD. (X)

Part: BATTERY PACK — INOPERATIVE (CABIN)

PHX - FLT NR 1258 - DURING ROUTINE MAINTENANCE CHECK, FOUND CENTER CABIN BULL NOSE EMERGENCY LIGHTS INOP. REMOVED AND REPLACED RIGHT MID BATTERY PACK. OPS CHECKED GOOD ON GROUND. (M)

Part: CONNECTOR — LOOSE (CABIN)

PHX - DURING ROUTINE MAINTENANCE CHECK, FOUND FLOOR PROXIMITY EMERGENCY EXIT LIGHTS INOPERATIVE FROM ROW 6 THROUGH ROW 10. RECONNECTED LOOSE CONNECTOR AT ROW 10, OPS CHECK GOOD. (M)

Part: EEL WIRE — DISCONNECTED (CABIN)

PHX - DURING ROUTINE MAINTENANCE CHECK, FOUND EMERGENCY EXIT LIGHTS INOPERATIVE FROM ROW 17 THROUGH ROW 19. REPINNED WIRE AT ROW 19, OPS CHECK GOOD. (M)

Part: FUEL SYSTEM — MALFUNCTIONED (CTR TANK)

PHX - FLT 2172 - LAS-IAH - DURING CRUISE, THE CENTER FUEL TANK SEEMED TO CONSUME FUEL AT AN EXCESSIVE RATE, 3600 LBS TO LESS THAN 900 LBS IN APPROXIMATELY 20 MINUTES. DUE TO A POSSIBLE FUEL LEAK, CREW DIVERTED AIRCRAFT TO PHX AND LANDED WITHOUT FURTHER PROBLEMS. MAINTENANCE INSPECTED FUEL QUANTITY SYSTEM AND CHECKED FOR LEAKS ON CENTER TANK AND VENTS. NO DEFECTS WERE NOTED. COMPLIED WITH OVERWEIGHT INSPECTION. NO DISCREPANCIES NOTED. AIRCRAFT RETURNED TO SERVICE. (W)

Part: EEL WIRE — LOOSE (CABIN)

PHX - DURING ROUTINE MAINTENANCE CHECK, FOUND FLOOR MOUNTED MID CABIN EMERGENCY EXIT LIGHTS INOPERATIVE. RECONNECTED WIRES, OPS CHECK GOOD. (Z)