N181AW

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 59,491 hrs · 49,232 cycles

MCN - C21 CK - C - BS 178 PRESS BULKHEAD CENTER WEB, LBL 4.8, WL 187.2 TO 188 HAS A .8 INCH CRACK CONFIRMED WITH HFEC. MAINTENANCE CUT OUT DAMAGED AREA, FABRICATED REPAIR DOUBLER AND FILLERS AND INSTALLED IAW B737 SRM 53-10-11 AND TEMP REV 53-52.

Part: STRINGER — CRACKED · airframe 59,491 hrs · 49,232 cycles

MCN - C21 CK - "C" - WHILE INVESTIGATING POSSIBLE CORROSION AROUND FASTENERS AT BS 727 + 17, STR 27L TO 27R, FOUND A 3" CRACK IN STR 27R. NOTE; NO CORROSION WAS FOUND. MAINTENANCE REMOVED CRACKED SECTION OF STR 27R AND INSTALLED REPAIR IAW B737 SRM 53-10-6.

Part: FRAME — CRACKED (FUSELAGE) · airframe 59,491 hrs · 49,232 cycles

MCN - C21 CK - C - MAIN CABIN SUB FLOOR PRESSURE DECK FWD CHORD BS 663.75, LBL 24, WL 202 CRACKED 3.5 INCH. MAINTENANCE CUT OUT DAMAGED AREA, FABRICATED REPAIR PARTS AND INSTALLED IAW AWA ER 15-5312-01238-GF1.

Part: WEB — CRACKED (CENTER FUSE)

D: Frame web cracked 3 ea places at fastener holes, BS 639, RBL 65, WL 206C: Removed cracked web, drilled and installed new web IAW B737 200 SRM 51-40-2 at BS 639, RBL 65, wl 206

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 59,491 hrs · 49,232 cycles

C21 CK - C - AFT SIDE OF BS 178 PRESS BULKHEAD CENTER WEB HAS A .5 INCH CRACK AT LBL .7, WL 203 TO 203.5, CONFIRMED WITH HFEC. MAINTENANCE CUT OUT DAMAGED AREA, FABRICATED REPAIR DOUBLER AND FILLERS AND INSTALLED REPAIR IAW B737 SRM 53-10-11, PG 83 & 84 AND TEMP REV 53-52.

Part: SKIN — CHAFED (T/E FLAP) · airframe 59,491 hrs · 49,232 cycles

MCN - C21 CK - C - LT WING, I/B FLIPPER FLAP LOWER O/B SKIN CHAFED BEYOND LIMITS. MAINTENANCE REMOVED THE LOWER SKIN PANEL, FABRICATED AND INSTALLED NEW LOWER SKIN PANEL IAW AWA ER 15-5752-01249-DL4.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 59,491 hrs · 49,232 cycles

MCN - C21 - C - BS 178 PRESS BULKHEAD WEB, AFT SIDE, VERT TEE CRACKED 1 INCH ON I/B SIDE, WL 184 TO 185, LBL 5.7, FOUND VISUALLY AND CONFIRMED BY HFEC. MAINTENANCE CUT OUT DAMAGED AREA OF VERT TEE AND FORMED REPAIR ANGLES, STRAPS AND FILLERS AND INSTALLED REPAIR PARTS IAW B737 SRM 53-10-11 PG 57 & 58.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,491 hrs · 49,232 cycles

MCN - C21 CK - C - BS 967 FLOORBEAM UPPER FLANGE CORRODED IN 4 PLACES BETWEEN LBL 22 AND RBL 49, BEYOND SRM LIMITS. MAINTENANCE REMOVED THE FLOORBEAM UPPER CAP AND FABRICATED AND INSTALLED NEW UPPER CAP IAW B737 SRM 53-10-9, FIG 2, PG 7 - 11.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,491 hrs · 49,232 cycles

MCN - C21 CK - C - FLOORBEAM BS 986.5, LBL 44 TO RBL 49 HAS CORROSION IN SEVERAL PLACES ON UPPER FLANGE. MAINTENANCE REMOVED THE FLOORBEAM UPPER CAP FROM LBL 44 TO RBL 49 AND FABRICATED NEW UPPER CAP SECTION AND INSTALLED IAW B737 SRM 53-10-9 FIG 2 PG 7 - 11.

Part: WEB — CRACKED (FUSELAGE) · airframe 59,491 hrs · 49,232 cycles

MCN - C21 CK - C - RT COCKPIT FLOOR WEB CRACKED 1 INCH AT CUTOUT, BS 180, WL 207, RBL 24. MAINTENANCE REMOVED THE FLOOR WEB, FABRICATED AND INSTALLED NEW FLOOR WEB IAW AWA ER 15-5311-01234-TR1.

Part: FRAME — CRACKED (FUSELAGE) · airframe 59,491 hrs · 49,232 cycles

MCN - C21 CK - C - BS 178 PRESS BULKHEAD 1.7 INCH CRACK CENTER OF RADIUS, RT CHORD, WL 207, RBL 24. MAINTENANCE REMOVED AND REPLACED THE RT SIDE CHORD IAW AWA ER 15-5311-01242-TB2.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 59,491 hrs · 49,232 cycles

MCN - C21 CK - C - BS 178 PRESS BULKHEAD CENTER WEB .7 INCH CRACK, WL 218, RBL 11.7 TO RBL 12.7, BELOW REINFORCEMENT DETECTED BY ULTRASONIC INSPECTION. MAINTENANCE CUT OUT DAMAGED AREA OF WEB AND FABRICATED REPAIR DOUBLER AND FILLER AND INSTALLED IAW B737 SRM 53-10-11 FIG 1 PG 1 - 8.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 59,491 hrs · 49,232 cycles

MCN - C21 CK - C - BS 178 PRESS BULKHEAD CENTER WEB HAS A 1 INCH CRACK AT LBL 6.6, WL 221.5 TO WL 222.5 BELOW REINFORCEMENT AS DETERMINED WITH ULTRASONIC INSPECTION. MAINTENANCE CUT OUT DAMAGED AREA, FABRICATED REPAIR DOUBLER AND FILLERS AND INSTALLED REPAIR IAW AWA ER 15-5312-01249-DL3.

Part: SKIN — CRACKED (FUSELAGE) · airframe 59,491 hrs · 49,232 cycles

C-21 CK - C - L-1 DOOR CUTOUT FUSELAGE SKIN LOWER EDGE BS 338.5 CRACKED .0625 INCH AT SILL PLATE ATTACH HOLE. MAINTENANCE REAMED CRACKED FASTENER HOLE, DRILLED AND INSTALLED REPAIR DOUBLER AT L-1 DOOR CUTOUT LOWER EDGE, BS 338.5 PER AWA ER 15-5300-01234-DD1.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 59,491 hrs · 49,232 cycles

MCN - C21 CK - C - BS 178 PRESS BULKHEAD CENTER WEB HAS A 1 INCH CRACK, WL 227.7 TO 228.7, RBL 6.4, BELOW REINFORCEMENT, FOUND WHILE PERFORMING ULTRASONIC INSPECTION. MAINTENANCE CUT OUT DAMAGED AREA, FABRICATED REPAIR DOUBLER AND FILLER AND INSTALLED REPAIR PARTS IAW B737 SRM 53-10-11 PG 1 - 8.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 59,491 hrs · 49,232 cycles

MCN - C21 CK - C - BS 178 PRESS BULKHEAD CENTER WEB HAS A .8 INCH CRACK AT LBL 9.2 TO LBL 10, WL 218, UNDER REINFORCEMENT AS DETERMINED WITH ULTRASONIC INSPECTION. MAINTENANCE CUT OUT DAMAGED AREA, FABRICATED REPAIR DOUBLER AND FILLERS AND INSTALLED REPAIR IAW AWA ER 15-5312-01249-DL3.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 59,491 hrs · 49,232 cycles

MCN - C21 CK - C - BS 178 PRESS BULKHEAD CENTER WEB HAS A .75 INCH CRACK, WL 234, RBL 10, FWD SIDE AT A FASTENER HOLE, AS DETERMINED WITH HFEC. MAINTENANCE CUT OUT DAMAGED AREA AND FABRICATED REPAIR DOUBLER AND FILLER AND INSTALLED IAW B737 SRM 53-10-11, PG 1 - 8.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 59,491 hrs · 49,232 cycles

MCN - C21 CK - C - BS 178 PRESS BULKHEAD CENTER WEB HAS A .5 INCH CRACK, WL 234, LBL 10 AT A FASTENER HOLE AS DETERMINED WITH HFEC. MAINTENANCE CUT OUT DAMAGED AREA AND FABRICATED REPAIR DOUBLER AND FILLER AND INSTALLED REPAIR PARTS IAW AWA ER 15-5312-01249-DL3.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 59,491 hrs · 49,232 cycles

MCN - C21 CK - C - BS 178 PRESS BULKHEAD CENTER WEB, AFT SIDE HAS A 1 INCH CRACK, LBL .7, WL 185 FOUND VISUALLY AND CONFIRMED WITH HFEC. MAINTENANCE CUT OUT DAMAGED AREA AND FABRICATED REPAIR DOUBLER AND FILLER AND INSTALLED REPAIR PARTS IAW B737 SRM 53-10-11 PG 83 & 84 AND TEMP REV 53-52.

Part: SHEAR TIE — CORRODED (BS 965, RBL 20) · airframe 59,491 hrs · 49,232 cycles

MCN - C-21 CK - "C" - FUSELAGE SKIN BULGE AND CUPPED FASTENERS IN SKIN AT BS 977, BETWEEN STR 23R TO 24R. MAINTENANCE REMOVER FASTENERS IN SKIN, NO CORROSION FOUND ON FUSELAGE SKIN, HOWEVER FOUND SHEAR TIE CORRODED BS 965, RBL 20. REMOVED AND REPLACED SHEAR TIE BS 965, RBL 20 IAW B737 SRM 51-30-2.

Part: PACKING — BROKEN (NR 2 ENGINE) · airframe 58,058 hrs · 48,149 cycles

INFLIGHT NR 2 ENGINE OIL PRESSURE DROPPED BELOW THE RED RADIAL; THE CREW ACCOMPLISHED ENGINE SHUTDOWN PER THE ORH, RETURNED TO OAK. THE ENGINE WAS SHUTDOWN FOR 25 MIN WITH WINDMILLING OIL PRESSURE OF 20 PS. IN OAK THE OIL PRESSURE TRANSMITTER AND OIL PRESSURE INDICATOR WERE REPLACED AND TESTED GOOD; THE ENGINE WINDMILLING INSPECTION WAS PERFORMED AND THE MAIN OIL FILTER WAS REPLACED (NO DEBRIS IN FILTER); ON THE NEXT FLIGHT THE OIL QUANTITY WAS FOUND TO FOLLOW THE POWER LEVER AT ALL SETTINGS; TAKEOFF 2.0-2.5 GALS, IDLE 3.0-3.5 GALS AND AFTER SHUTDOWN IN PHX 4.0 GALS. IN PHX OIL PUMP WAS REPLACED. UPON REMOVAL TE CENTER O-RING WAS FOUND TO BE BROKEN, THE OTHER 2 WERE OK. PUMP WAS REPLACED THOUGH NORMAL.

Part: PACKING — BROKEN (OIL PUMP) · airframe 58,058 hrs · 48,149 cycles

IN PHX OIL PUMP WAS REPLACED. UPON REMOVAL THE CENTER O-RING WAS FOUND TO BE BROKEN. THE OTHER 2 WERE OK. PUMP WAS REPLACED THOUGH IT APPEARED TO BE NORMAL.

Part: WEB — CRACKED (FUSELAGE) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, WEB AT STA 351.2 STR 20L CRACKED IN TWO PLACES AT E & E BAY. REMOVED DAMAGED WEB IAW 737 SRM 51-30-2, FAB''''D REPLACEMENT WEB IAW DWG 65-458-92, INSTALLED REPLACEMENT WEB IAW 737 SRM 51-30-2.

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, SIDE CHORD CRACKED AT FS 178, WL 195 AND WL 207. CUT OUT DAMAGED AREA, FABRICATED REPAIR PARTS, AND INSTALLED SIDE CHORD, SPLICE ANGLE AND STRAPS IAW SB 737-53A-1028 AND ER 15-5310-00274-JS5.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, FWD PRESSURE BULKHEAD CENTER WEB HAS 7 INCH CRACK BEHIND I/B FLANGE OF ANGLE STIFFENER AT FS 178, LBL 5 - 7, WL 226. REMOVED DAMAGE IAW 737 SRM 53-10-11 FIG 1, FAB''D REPAIR PARTS IAW 737 SRM 53-10-11 FIG 1, AND INSTALLED PARTS IAW 737 SRM 53-10-11.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, CABIN SUB FLOOR PRESSURE DECK STIFFENER IS CRACKED AT FS 727, RBL 18. REMOVED AND REPLACED STIFFENER (NEW) IAW 737 SRM 51-30-2.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, BULKHEAD CENTER WEB CRACKED AT FS 178, LBL 5.5, WL 200. CUT OUT DAMAGED AREA IAW 737 SRM 53-10-11, FAB''D REPAIR PARTS IAW SRM 53-10-11 FIG 1, INSTALLED REPAIR PARTS IAW SRM 51-30-2.

Part: WEB — CRACKED (AIRSTAIR DOOR) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, AIRSTAIR DOOR INSIDE WEB CRACKED AT AFT UPPER CORNER. REMOVED WEB, CUT OUT DAMAGE, FABRICATED REPAIR WEB, DOUBLER, AND SPLICE, INSTALLED REPAIR PARTS IAW 737 SRM 51-30-2, 51-40-3 FIG 3, AND 51-40-2.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, CABIN SUB FLOOR PRESSURE DECK STIFFENER IS CRACKED AT FS 727, RBL 9. REMOVED AND REPLACED STIFFENER (NEW) AT FS 727, RBL 9.

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, FWD CABIN FS 303, STR 17R FRAME IS CRACKED AT LOWER INBD FLANGE. REMOVED DAMAGED AREA, FABED REPAIR PARTS, AND INSTALLED REPAIR PARTS IAW 737 SRM 51-30-2.

Part: SKIN — DENTED (TE FLAP) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, LEFT INBD MID FLAP L/E HAS DENT THAT IS OUT OF LIMITS. REMOVED DAMAGE IAW 737 SRM 57-50-4 FIG 3, FABED REPAIR PARTS IAW SRM 57-50-4, AND INSTALLED REPAIR IAW SRM 57-50-4 AND 51-30-2.

Part: SKIN — CRACKED (FUSELAGE) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, .5 INCH CRACK IN FUSELAGE SKIN AT TOP OF CAPTAINS NR 1 WINDOW OUTBOARD UPPER CORNER CUTOUT. REMOVED DAMAGE IAW 737 SRM 53-10-01 FIG 210, FABRICATED AND INSTALLED REPAIR FILLER AND DOUBLER IAW 737 SRM 53-10-1 FIG 210 AND ER 15-5330-00272-JS1.

Part: WEB — CRACKED (FUSELAGE) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, CABIN SUB FLOOR STA 664 LBL 35 PRESSURE DECK HAS CRACK. REMOVED DAMAGED AREA, FABRICATED REPAIR PARTS (FILLER AND DOUBLER), AND INSTALLED REPAIR IAW ER 15-5710-00273-SSI, 737 SRM 51-30-2, AND 51-30-0.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, AFT CARGO DOOR HAS TEMP REPAIR, REFER TO AWA ER 15-5361-00210-JS2A, ALLOY STEEL FASTENERS TO BE REPLACED WITH A286 CRES FASTENERS. REMOVED DOOR WEB AND BRACKET IAW 737 SRM 51-30-2, REMOVED AND REPLACED FASTENERS IAW AWA ER 15-5361-00210-JS2A, REINSTALLED WEB AND BRACKET IAW SRM 51-30-2.

Part: FLOOR SUPPORT — CRACKED (CABIN) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, THREE CRACKS IN LEFT SIDE VERTICAL WEB OF FLOOR SUPPORT AT STA 717, 724, AND 725, BL 0. REMOVED DAMAGE SECTION OF WEB IAW ER 15-B700-00274-JS4, FAB''D AND INSTALLED REPAIR PARTS IAW ER 15-5700-0027.

Part: SKIN — CRACKED (FUSELAGE) · airframe 57,137 hrs · 447,448 cycles

C-CHECK, FUSELAGE SKIN BETWEEN BS 727 AND 767, STR 14R TO 20R HAS SEVERAL EXISTING REPAIRS WITH NEW CRACKS IN 3 PLACES. REMOVED DAMAGED AREA, FABRICATED REPAIR PARTS AND SKIN SECTION, INSTALLED SKIN AND SPLICE REPAIR IAW AWA ER 15-5331-00256-DL2.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, SHEAR TIE CRACKED AT FS 400 STR 14R. REMOVED DAMAGED SECTION IAW 737 SRM 51-10-1, FABED SHEAR TIE IAW 737 SRM 53-10-4, INSTALLED REPAIR PARTS IAW 737 SRM 53-10-4.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 57,137 hrs · 47,488 cycles

C-CHECK, SEALANT BLOWN OUT OF EXISTING REPAIR AT FS 907 APPROX STR 22R. REMOVED OLD REPAIR IAW 737 SRM 51-40-02, FAB''D REPAIR PARTS IAW 53-30-3 FIG 28, INSTALLED REPAIR PARTS IAW 51-40-8 AND 53-30-3 FIG 28.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 57,137 hrs · 47,488 cycles

C-CHECK, INTERCOSTAL CRACKED AT FS 180, LBL 26, WL 195. REMOVED DAMAGED INTERCOSTAL IAW 737 SRM 53-10-11, FABED REPAIR PARTS PARTS IAW 737 SRM 53-10-16, INSTALLED REPAIR PARTS IAW 737 SRM 51-30-0.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, FUSLAGE HAS CREASE THAT IS OUT OF LIMITS AT FS 1110, STR 14R. CUT OUT DAMAGED AREA IAW 737 SRM 51-30-2, FABED REPAIR DOUBLER AND PARTS IAW 737 SRM 51-30-3, INSTALLED REPAIR PARTS IAW 737 SRM 51-30-2.

Part: SKIN — DENTED (FUSELAGE) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, FUSLAGE SKIN DENTED BEYOND LIMITS ABOVE DOOR L-1 (A=.7, Y=.05, AY=14). CUT OUT DAMAGED AREA IAW 737 SRM 53-30-5 FIG 3. REWORKED AREA AND INSTALLED DOUBLER IAW 737 SRM 51-30-1, 51-30-2, AND 53-30-3 FIG 1.

Part: SEAT TRACK — GOUGED (CABIN) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, SEAT TRACK GOUGED AT FS 340, RBL 25. REMOVED, FAB''D REPLACEMENT TRACK AND INSTALLED SEAT TRACK IAW 737 SRM 53-10-5 FIG 2.

Part: SKIN — GOUGED (FUSELAGE) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, FUSELAGE SKIN GOUGED OUT OF LIMITS AT AC GROUND SERVICE DOOR LT SIDE. CUT OUT DAMAGE IAW AWA ER 15-5243-00256-DL1, TREATED IAW 737 SRM 51-10-02.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 57,137 hrs · 47,448 cycles

C-CHECK, CRACKED STRINGER AT 500B, STR 16L, FORWARD OF WING ANTI ICE. REMOVED DAMAGED AREA, FABED REPAIR PARTS, AND INSTALLED REPAIR PARTS IAW AWA ER 15-5314-00255-DL1.

Part: SKIN — CRACKED (FUSELAGE) · airframe 56,904 hrs · 47,256 cycles

CARGO LOADER STRUCK AIRCRAFT AT AFT CARGO DOOR SURROUND STRUCTURE. TEMP REPAIRED IAW ER 15-5361-00210-JS2A, INSPECTION REQUIRED AT EVERY C-CHECK, NOT TO EXCEED 4,500 FLT CYCLES.

Part: SIGN — INOPERATIVE (CABIN) · airframe 56,189 hrs · 46,705 cycles

NON ROUTINE, R-2 EXIT SIGN WILL NOT ILLUMINATE. REMOVED AND REPLACED EMERGENCY EXIT SIGN ASSEMBLY, OPS CK GOOD.

Part: BATTERY PACK — INOPERATIVE (ROW 17) · airframe 54,124 hrs · 44,554 cycles

NON ROUTINE, EMERGENCY LIGHTS INOP ON LAST SIX LT SEAT ROWS. REMOVED AND REPLACED BATTERY PACK AT ROW 17 ABC, OP CK GOOD. RECOMMENDATION: REMAIN OPEN, MONITOR -- AIRCRAFT HAS SEVERAL DISCREPANCIES IN THIS AREA FOR WIRE REPAIRS AND BATTERY REPLACEMENTS.

Part: WIRE — BROKEN (ROW 17)

SEAT EMERGENCY EXIT LIGHT INOP AT ROW 17 LT. REPAIRED BROKEN WIRE UNDER SEAT, OPS CK NORMAL.

Part: FLOORBEAM — CRACKED (BS 578)

C-CHECK, MAIN CABIN FLOORBEAM FS 578 RBL 65 CRACKED WEB AT WL 207. REMOVED, FABRICATED AND REPAIRED PER ER 2-53-15-86A.

Part: STRINGER — CRACKED (BS 515)

C-CHECK, STRINGER 16 LT CRACKED AT STA 515. REMOVED DAMAGED SECTION, FABRICATED REPAIR PART AND INSTALLED IAW SRM 51-10-2 AND SRM 53-10-2 FIG 9, BS 515-540.

Part: BULKHEAD WEB — CRACKED (BS 727)

C-CHECK, TWO CRACKS ON RT O/B BULKHEAD SHEAR WEB AT BS 727 STR 18A SHEAR BEAM. REMOVED WEB AND ATTCH PARTS IAW SRM 51-30-2. INSTALLED NEW WEB AND ATTACH PARTS. REMOVED AND REINSTALLED 3 STIFFENERS FROM 18A WEB.

Part: SKIN — CHAFFED (RT TE MID FLAP)

C-CHECK, RT I/B MID FLAP REPAIR ON I/B SIDE IS CHAFED OUT OF LIMITS. REMOVED DAMAGED SECTION AND FABRICATED REPLACEMENT SKIN SECTION OF 2024T3,QQA 250/5 0.080 DOUBLER AND 2 CORNER TRIPLERS WITH ONE FILLER OF 2024 T-3 .040 IAW 737 SRM 57-50-4 FIG 4, INSTALLED IAW SRM 51-30-2 AND SEALED.

Part: SKIN — CRACKED (BS 312)

C-CHECK, EXTERNAL SKIN AROUND L1 DOOR, AT UPPER DOOR HINGE CUTOUT, 1 CRACK EXTENDING FWD FROM FWD EDGE OF CUTOUT. FABRICATED AND INSTALLED REPAIR PARTS PER SRM 53-30-3 FIG 21.

Part: CLIP — CRACKED (BS 7273)

SHEAR TIE CRACKED AT STA 727B, STR 4L DOT NR 087-199. REMOVED AND REPLACED DAMAGED SHEAR TIE CLIP IAW 537 SRM 51-40-2.

Part: SKIN — CRACKED (BS 520)

C-CHECK, CRACK IN FUSELAGE LT SIDE APPROX 9 AFT AND PARALLEL TO WING SCAN LIGHT (TEMP REPAIR INSTALLED) BS 520 BETWEEN STR 16 & 17 LT. REMOVED EXISTING REPAIR DOUBLER, FABRICATED AND INSTALLED PERMANENT REPAIR IAW SRM 53-30-3 FIG 1.

Part: SEAT TRACK — CORRODED (BS 872-877)

SEAT TRACK HAS CORROSION STA 872-877, RBL 45. REMOVED AND FABRICATED REPLACEMENT PART BAC1520-792 FROM R659935 AND SPLICE FROM .030 301 1/2 HARD R679407, TREATED, PRIMED AND INSTALLED IAW SRM 53-00-52, 53-10-5, AND 53-10-2.

Part: TIE CLIP — CRACKED (BS 520)

C-CHECK, STRINGER TIE CLIP CRACKED STA 520 STR 16 LT. REMOVED, FABRICATED, AND INSTALLED IAW 51-10-3 FIG 2 & SRM 51-30-2.

Part: SHEAR TIE — CRACKED (BS 967)

FRAME TO FUSELAGE CLIP CRACKED, LT SIDE FS 967 STR 8L. REMOVED, FABRICATED, TREATED, PRIMED, AND INSTALLED CLIP IAW SRM 53-10-4, 51-30-2, AND 51-30-2, 7075-T6 .050.

Part: TIE CLIP — CRACKED (BS 344)

C-CHECK, TIE CLIP CRACKED RT SIDE FUSELAGE STA 344 STR 11R. REMOVED, FABRICATED REPLACEMENT PART, AND INSTALLED IAW SRM 51-30-2, SRM 51-10-3 FIG 2.

Part: ANGLE — CRACKED (BS 598)

C-CHECK, FLOORBEAM ATTACH ANGLE TO FUSELAGE AT STA 598 WL 208 LT CUSP LINE CRACK STR 17L. REMOVED, FABRICATED, AND INSTALLED REPAIR PARTS PER AWA ER 2-53-15-86 + SB 737-53-1061.

Part: FRAME — CRACKED (BS 907)

CORROSION AFT PIT STA 907 BETW STR 25L AND 26L, FRAME HAS CORROSION ON AFT SIDE WITH CRACKS AT FWD SKIN ATTACH AREA, REF X2D53002. REMOVED DAMAGED AREA, FABRICATED, TREATED, PRIMED AND INSTALLED REPAIR ANGLE AND FILLER IAW 737SRM 53-10-4, 51-10-2, AND 52-30-2. MAT'L .063 SHT 7075-0 QQA 250/13, HEAT TREATED 7075T6 FOR REPAIR ANGLE .050 SHT.

Part: FLOORBEAM — CRACKED (BS 685)

C-CHECK, CABIN FLOORBEAM RBL 27, STA 685 DOUBLER REPAIR IS CRACKED AT UPPER RADIUS. REMOVED, FABRICATED REPLACEMENT PART, AND INSTALLED IAW SRM 51-30-2.

Part: SKIN — CRACKED (BS 727-760)

DURING ROUTINE MAINTENANCE CHECK, FOUND FUSELAGE SKIN CRACKED BETWEEN STA 727A AND 760 APPROX ABOVE STRINGER 17 RT FUSELAGE. TEMP REPAIR PER SRM. REINSPECT AT 3,000 FLIGHT CYCLES AND EVERY 2500 FLIGHT CYCLES THEREAFTER. PERMANENT REPAIR MUST BE C/W WITHIN 10,000 FLIGHT CYCLES PER SRM 53-30-3, FIG 1 PG 2C.

Part: SKIN — CRACKED (BS 760)

FOUND CRACK AT STA 760 STR 17 RT. CRACK WAS VERIFIED WITH HFEC. COMPLIED WITH REPAIR PER SRM 53-30-03. INSTALLED DOUBLER OUT OF 2024 T3 .063.

Part: ENGINE — FAILED (NR 2)

NR 2 ENGINE LOST OIL PRESS AND NR 2 LOW OIL PRESS LIGHT ILLUMINATED. OIL TEMP ROSE TO 135 DEGREES. SHUT NR 2 ENG DOWN WHEN PRESS REACHED 20 PSI, WINDMILLED APPROXIMATELY 18 MINUTES. AIR RETURN, RNR NR 2 ENGINE IAW TASK CARDS F5M71002 F5M76001 R5M71002 R5M71002 F5M78002 R5M71003.

Part: SKIN — CRACKED (FUSELAGE)

LEFT FUSELAGE IS CRACKED APPROX 9 INCHES AFT OF WING SCAN LIGHT, CRACK WAS VARIFIED 1.4 INCHES. REPAIRED PER 53-30-03 FIG 1.

Part: CHORD — CRACKED (BS 639)

CABIN STA 639 LT CHORD AND OUTER WEB CRACKED. REMOVED AND REPLACED PER SRM 53-10-03, REPAIRED PER SB53-1061.

Part: STRINGER — CORRODED (BS 344-360)

STR 23L STA 344-360 IN E AND E COMPARTMENT HAD SEVERE CORROSION. REMOVED AND REPLACED STR PER SRM 53-10-03 FIG 1.

Part: FLOORBEAM — CORRODED (BS 967)

CORROSION IN FLOORBEAM TOP FLANGE STA 967 BL-0 TO RBL-30. REPAIRED PER SRM 53-10-09.

Part: FLOORBEAM — CORRODED (BS 986)

CORROSION FLOORBEAM TOP FLANGE STA 986 RBL-15. REPAIR PER SRM 53-10-09.

Part: FLOORBEAM — CRACKED (BS 659)

UPON CLEANING AND OK TO CLOSE FLOOR PANELS, FOUND CRACKS NOTED FLOORBEAM AT STA 659, BLO. REMOVED DAMAGED SECTION NDT EXISTING HOLES, NO CRACKS NOTED. FABRICATED REPAIR PARTS INSTALLED PER SB737-57-1210.

Part: FUSELAGE — CRACKED (BS 727)

D-CRACK IN FUSELAGE 1 AT STA 727 STR 16R. C/W REPAIR PER 53-30-03 PAGE11.

Part: SKIN — CRACKED (R2 DOORWAY)

R2 DOOR CUTOUT HAS CRACK AT LOWER HINGE IN FUSELAGE, APPROXIMATELY 1.75 INCHES LONG/CRACK IN FUSELAGE SKIN RT WING TO BODY AREA (2 CRACKS). REPAIRED PER PRELIMINARY CIR 3-53-35-AB AND SRM 53-30-31 PAGE 28 RESPECTIVELY.

Part: WIRE — DISCONNECTED (CABIN)

DURING ROUTINE MAINTENANCE CHECK, FOUND EMERGENCY LIGHTS INOP AT ROW 1 AB. RECONNECTED AND SECURED HARNESS. OPS CHECK GOOD.

Part: CONNECTOR — LOOSE (CABIN)

DURING ROUTINE MAINTENANCE CHECK, FOUND EMERGENCY LIGHTS ROW 1 LEFT INOP. RESECURED LOOSE CONNECTOR. OPS CHECK GOOD.

Part: CONNECTOR — BAD (CABIN)

DURING ROUTINE MAINTENANCE CHECK, FOUND EMERGENCY PATH LIGHTING INOP FROM ROW 15 TO 20. REPLACED SOLDER SPLICE BETWEEN PIN 7 OF D9022 AND REST OF SEAT LIGHTS, OPS TEST GOOD. STC - SA3432NM

Part: STRINGER — CRACKED (BS 500)

16R STA 500B CRACKED AT AFT END NEXT TO WING ILLUMINATION LIGHT COVER. REMOVED AND REPLACED LONGERON AT STA 500B IAW SRM 53-10-03.

Part: STRINGER — CORRODED (BS 980)

DURING ROUTINE MAINTENANCE CHECK, FOUND CORROSION AT STR 25 L, BS 980. REMOVED STRINGER 25L, BS 967 TO 990. FABRICATED STRINGER AND STALLED PER SRM 53-10-03.

Part: STRINGER — CORRODED (BS 907)

DURING ROUTINE MAINTENANCE CHECK, FOUND CORROSION ON STRINGER SPLICE STR 27R, BS 907. REMOVED STRINGER. FABRICATED STRINGER AT BS 875 TO 925, STR 27 R. INSTALLED STRINGER PER SRM 53-10-03.

Part: STRINGER — CORRODED (BS 907-1016)

DURING ROUTINE MAINTENANCE CHECK, FOUND CORROSION ON STR 27L AT BS 907 TO 1016. FABRICATED STRINGER SEGMENT BA 967 TO 1016, STR 17 L. REPLACED STRINGER PER SRM 53-10-03.

Part: STRINGER — CORRODED (BS 729-735)

DURING ROUTINE MAINTENANCE CHECK, FOUND CORROSION AT BS 729 TO 735, STRINGER 25L. REMOVED CORRODED SECTION. FABRICATED AND INSTALLED REPAIR PARST PER SRM 53-10-03.

Part: CONTROLS — VIBRATION (TE FLAPS)

DURING LANDING APPROACH, WHEN FLAPS MOVED FROM 1 DEGREE TOWARD 5 DEGREES, FLIGHT CONTROL VIBRATION AND ROLL-OFF TOWARD THE LEFT WAS NOTED. APPEARED NORMAL BEYOND 5 DEGREE SETTING. LOWERED FLAPS, INSPECTED FLAP SYSTEM INCLUDING CARRIAGES, SPINDLES, PANELS, BEARINGS, TRACKS FOR CONDITION AND OPERATION. CHECKED SPOILER SYSTEM FOR PROPER FAIR, FLOAT, DELAM AND INTEGRITY. ALL SYSTEMS OPERATED NORMAL WITH NO DEFECTS FOUND.

Part: LIGHT — BROKEN (CABIN)

DURING ROUTINE MAINTENANCE CHECK, FOUND EMERGENCY EXIT LIGHT AT SEAT 9C BROKEN OFF. REPLACED EMERGENCY LIGHT ASSEMBLY AT 9C. OPS NORMAL. STC - SA3432NM.

Part: LIGHT — INOPERATIVE (CABIN)

DURING ROUTINE MAINTENANCE CHECK, FOUND R-2 DOOR EMERGENCY EXIT LIGHT INOP. REMOVED AND REPLACED LIGHT ASSEMBLY EMERGENCY EXIT BATTERY, OPS CHECK GOOD STC - SA3432NM.

Part: LIGHT — INOPERATIVE (CABIN)

DURING ROUTINE MAINTENANCE CHECK, FOUND R-2 DOOR EMERGENCY EXIT LIGHT INTERIOR ABOVE DOOR INOP. REPLACED LIGHT ASSEMBLY, OPS CHECK GOOD STC - SA3432NM.

Part: LIGHT — INOPERATIVE (CABIN)

LAS - FLT 2157 - DURING ROUTINE MAINTENANCE CHECK, FOUND L-2 DOOR EMERGENCY EXIT LIGHT INOP. REPLACED EMERGENCY EXIT LIGHT ASSEMBLY AS REQUIRED. OPS NORMAL AT THIS TIME. (M)

Part: CONNECTOR — LOOSE (CABIN)

PHX - FLT 7803 - DURING ROUTINE MAINTENANCE CHECK, FOUND EMERGENCY EXIT LIGHTS OVER EXIT WINDOWS INOP. REINSTALLED CANNON PLUG ABOVE CEILING PANEL PAX ROW 9. FUNCTIONAL CHECK GOOD. (M)

Part: SILL — CORRODED (BS 270-360)

PAE - FLT 7848 - DURING ROUTINE SCHEDULED C-16 MAINTENANCE CHECK, FOUND RIGHT FWD THRESHOLD CORRODED BS 270-360, WL 208, RBL 60. REMOVED AND REPLACED MOPSILL PER SRM 51-30-2, SRM 51-10-1. (M)

Part: SKIN — CRACKED (BS 727)

PAE - FLT 7848 - DURING ROUTINE SCHEDULED C-16 MAINTENANCE CHECK, FOUND 2 HOLES THROUGH SKIN AT BS 727B, STRINGER 16L (CRACK IN SKIN). REMOVED DAMAGE, FABRICATED REPAIR PARTS AND INSTALLED PER SRM 53-30-3. (M)

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

PAE - FLT 7848 - DURING ROUTINE SCHEDULED C-16 MAINTENANCE CHECK, FOUND CORROSION ON SEAT TRACK AT STATION 328-344, RBL 45, WL 208. REMOVED, FABRICATED AND INSTALLED PER SRM 51-10-1, 51-21-41. (M)

Part: SILL — CORRODED (BS 344)

PAE - FLT 7848 - DURING ROUTINE SCHEDULED C-16 MAINTENANCE CHECK, FOUND CORROSION ON FWD MOPSILL AT BS 344, LBL 65, WL 208. REPLACED FWD MOPSILL AT BS 294 TO 360, LBL 65, WL 208. (M)

Part: FLOOR BEAM — CORRODED (BS 294)

PAE - FLT 7848 - DURING ROUTINE SCHEDULED C-16 MAINTENANCE CHECK, FOUND CORROSION ON FLOOR BEAM AT STATION 294, LBL 15 TO RBL 45, WL 208. REPLACED UPPER T-CHORD WITH FABRICATED PART BS 294, LBL 60 TO RBL 60, WL 208. (M)

Part: CONNECTOR — MISSING (CABIN)

PAE - FLT 7848 - DURING ROUTINE MAINTENANCE CHECK, FOUND ROW 6 LT PROX WIRING CONNECTOR MISSING. REPLACED PER STANDARD WIRE MANUAL. (X)

Part: WIRE — DISCONNECTED (CABIN)

PHX - FLT 2081 - DURING ROUTINE MAINTENANCE CHECK, FOUND SEAT 3C FLOOR PROX LIGHT OUT. RESECURED WIRE CONNECTOR. OPERATIONS CHECK GOOD. (X)

Part: PT7 JAM NUT — LOOSE (NR 2 ENGINE)

MDW/CMH - FLT 0282 - NR 2 EPR INDICATION WAS LOW AND FLUCTUATING. MAINTENANCE INSPECTED AND FOUND P2 TEST CAP AT EPR TRANSMITTER LOOSE AND THE JAM NUT AT PT7 TEE FITTING TO TRANSMITTER LOOSE. RESECURED. RAN ENGINES TO TAKEOFF POWER. EPR MADE ALL PARAMETERS PER MM 71-11-01 AND MM 71-09-236. REFERENCE: OPERATOR CONTROL NR AWXA960035. (X)

Part: P2 CAP — LOOSE (NR 2 ENG)

FLT NR 282 - MDW-CMH - ABORTED TAKEOFF, NR 2 EPR INDICATION WAS LOW AND FLUCTUATING. MAINTENANCE INSPECTION AND FOUND THE P2 TEST CAP AT EPR TRANSMITTER LOOSE AND THE JAM NUT AT PT7 TEE FITTING TO TRANMITTER LOOSE, RESECURED. RAN ENGINES TO TAKEOFF POWER. EPR MADE ALL PARAMETERS PER MM 71-11-01 AND 71-09-236. (M)

Part: PT7 JAM NUT — LOOSE (NR 2 ENG)

FLT NR 282 - MDW-CMH - ABORTED TAKEOFF, NR 2 EPR INDICATION WAS LOW AND FLUCTUATING. MAINTENANCE INSPECTION AND FOUND THE P2 TEST CAP AT EPR TRANSMITTER LOOSE AND THE JAM NUT AT PT7 TEE FITTING TO TRANMITTER LOOSE, RESECURED. RAN ENGINES TO TAKEOFF POWER. EPR MADE ALL PARAMETERS PER MM 71-11-01 AND 71-09-236. REFERENCE AWXA960035.

Part: LINE — RUPTURED ('A' HYD SYSTEM)

LAS/PDX - FLT NR 671 - TWENTY MILES FROM PDX, CREW REPORTED LOSS OF 'A' SYSTEM HYDRAULIC FLUID. AIRCRAFT LANDED WITHOUT FURTHER INCIDENT AFTER DECLARING AN EMERGENCY LANDING. MAINTENANCE FOUND RUPTURED LINE AT THE 'A' SYSTEM HYDRAULIC MODULE. REPLACED LINE, INSPECTED PRESSURE AND CASE DRAIN FILTERS, NO CONTAMINATION NOTED. AIRCRAFT RETURNED TO SERVICE. (M)

Part: ANTI-ICE DUCT — BROKEN (NR 2 ENGINE)

PHX - DURING ROUTINE MAINTENANCE CHECK FOLLOWING A HIGH EGT EXCURSION, FOUND NR 2 ENGINE 8TH STAGE ANTI-ICE DUCT RUPTURED 1 INCH FORWARD OF AFT MOUNT POINT. ENGINE REMOVED AND REPLACED WITH SERVICEABLE UNIT. (M)

Part: EEL ASSY — INOPERATIVE (CABIN)

PHX - DURING ROUTINE MAINTENANCE CHECK, FOUND EMERGENCY EXIT LIGHTS INOPERATIVE. REMOVED AND REPLACED SEAT LIGHT ASSEMBLY AT ROW 5, OPS CHECK GOOD. (M)

Part: TR DOOR — OUT OF ADJUST (NR 2 ENG)

PHX - DURING SCHEDULED C-15 INSPECTION, FOUND NR 2 ENGINE UPPER T/R BUCKET DOOR BUMPERS DO NOT HAVE FULL CONTACT. WELDED PER ER 2-78-32-02. (M)

Part: SKIN — CRACKED (R2 DOOR CUTOUT)

PHX - DURING SCHEDULED C-15 INSPECTION, FOUND FUSELAGE SKIN CRACKED AT R2 DOOR CUTOUT, UPPER FORWARD CORNER UPPER HINGE CUTOUT. FABRICATED REPAIR DOUBLER AND INSTALLED REPAIR PER SRM 53-30-3, FIGURE 21A. (M)

Part: FAN INLET CASE — CRACKED (NR 1 ENG)

PHX - DURING SCHEDULED C-15 INSPECTION, FOUND NR 1 ENGINE IGV CASE CRACKED AT WELD AT 10:00 POSITION. WELDED CRACK PER ER 2-72-23-02B. (M)

Part: FLAP TRACK — CORRODED (NR 2 TE FLAP)

PHX - DURING SCHEDULED C-15 INSPECTION,FOUND NR 2 FLAP TRACK CORRODED AT AFT SPAR PARTING SURFACE. REMOVED AND REPLACED FLAP TRACK ASSY PER BMM 27-51-151, PAGE 406. (M)

Part: STRINGER — CORRODED (BS 945)

PHX - DURING SCHEDULED C-15 INSPECTION, FOUND STRINGER 27R BS 947 CORRODED. REMOVED AND REPLACED STRINGER 27R SECTION FROM BS 945 TO 957 PER SRM 53-10-3, FIG 1. (M)

Part: DRAG BRACE — CRACKED (NLG)

DURING SCHEDULED C-15 INSPECTION, FOUND NOSE GEAR 'A' FRAME CRACKED BY DOOR CRANK ARMS. REMOVED AND REPLACED NLG 'A' FRAME (DRAG BRACE) PER AWA TASK CARD R4N32003. (M)

Part: SEAT TRACK — CORRODED (BS 986.5)

PHX - DURING SCHEDULED C-15 INSPECTION, FOUND AFT GALLEY SEAT TRACK ATTACH POINTS CORRODED ON UNDER SIDE OF FLOOR BOARD AT ATTACH HOLES, BS 986.5 TO 1016, WL 208.1. REMOVED AND REPLACED SEAT TRACK EXTRUSION AT RBL 30 PER SRM 51-30-2. (M)

Part: FAN INLET CASE — CRACKED (NR 2 ENG)

PHX - DURING SCHEDULED C-15 INSPECTION, FOUND NR 2 ENGINE IGV CASE CRACKED AT WELD AT 1:00 TO 3:00 POSITION AND 11:00 POSITION. WELDED CRACK PER ER 2-72-23-02B. (M)

Part: EXHAUST STRUTS — CRACKED (NR 1 ENGINE)

PXH - DURING SCHEDULED C-15 INSPECTION, FOUND NR 1 ENGINE EXHAUST STRUTS (4 EACH) CRACKED AT LEADING EDGES. WELDED CRACKS PER PWA ENGINE MANUAL 72-54-02, REPAIR NR 03. (M)

Part: DOOR FRAME — CRACKED (CARGO COMPT)

PHX - DURING SCHEDULED C-15 INSPECTION, FOUND FORWARD CARGO DOOR CUTOUT FRAME CRACKED AT STATION 440 STOP 5. REMOVED AND REPLACED FRAME PER BOEING DRAWING 65C35244 AND SRM 51-10-1. (M)

Part: EEL WIRE — LOOSE (CABIN)

PHX - DURING ROUTINE MAINTENANCE CHECK, FOUND SEAT MOUNTED EMERGENCY EXIT LIGHTS INOPERATIVE AT ROWS 16 AND 17. RESECURED WIRE, OPS CHECK GOOD. (M)

Part: EEL BATT PACK — INOPERATIVE (CABIN)

DURING ROUTINE MAINTENANCE CHECK, FOUND LT OVERWING EMERGENCY EXIT LIGHT INOPERATIVE. REMOVED AND REPLACED BATTERY PACK, OPS CHECK GOOD. (Z)

Part: ANTI-ICE VALVE — FAILED (NR 2 ENGINE)

OMA/LAS - FLT 780 - AIRCRAFT DIVERTED TO ICT. DURING PREVIOUS FLIGHT TO OMA, NR 2 ENGINE RT ANTI-ICE VALVE BECAME INOPERATIVE. CONTRACT MX WAS INSTRUCTED TO LOCK THE VALVE IN THE OPEN POSITION AND MX CONTROL ISSUED AN UNMANNED STATION RELEASE. SHORTLY AFTER TAKEOFF FROM OMA, NR 2 ENGINE FUEL HEAT VALVE WOULD NOT CLOSE AND OIL TEMPERATURE ROSE TO 140 DEGREES. CREW SHUT NR 2 ENGINE DOWN AND DIVERTED AIRCRAFT TO ICT. CONTRACT MX FOUND FUEL HEAT VALVE LOCKED IN OPEN POSITION. MAINTENANCE UNLOCKED FUEL HEAT AND LOCKED RT ANTI-ICE VALVE OPEN. ALSO, PERFORMED WINDMILL INSPECTION PROCEDURE WITH NO DEFECTS NOTED. ACFT RELEASED FOR FURTHER SERVICE. (X)

Part: EEL POWER SUPPLY — INOPERATIVE (CABIN)

PHX - DURING ROUTINE MAINTENANCE CHECK, FOUND ROW 16 AND 17 SEAT MOUNTED EMERGENCY EXIT LIGHTS INOPERATIVE. REMOVED AND REPLACED POWER SUPPLY AT 18 LT, OPS CHECK GOOD. (Z)