N322DL

Part: FRAME — CRACKED (FUSELAGE) · airframe 76,217 hrs · 59,787 cycles

A PARTIALLY SEVERED FRAME WAS DISCOVERED AT BS 328, S20R-S21R, DURING THE ACCOMPLISHMENT OF AD2015-28-03. THE REPAIR/PREVENTIVE MODIFICATION ON THE BS 328 FRAME WAS ACCOMPLISHED IAW SB 737-53A1323.

Part: FRAME — CRACKED (FUSELAGE) · airframe 76,217 hrs · 59,787 cycles

THE BS 360 FRAME INSULATION BLANKET HOLE WAS DISCOVERED CRACKED AT S20R, DURING ACCOMPLISHMENT OF AD2015-28-03. FRAME REPAIR INSTALLED IAW MFG SERVICE REQUEST MESSAGE: NAC-NAC-16-0016-04B.

Part: FRAME — DAMAGED (BS 500) · airframe 74,727 hrs · 58,399 cycles

FRAME DAMAGED AT BS 500 BETWEEN STRINGERS 13-14R. INSTALLED REPAIR TO FRAME IAW SRM 51-40-3, FIG 1.

Part: WEB — CORRODED (BS 887-907) · corrosion level 2 · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE BS 887 TO BS 907, RBL 65 CORRODED ON FLOOR STRESS WEB. CORROSION WAS NOTED ON THE CREASE BEAM WEB AT FLOOR LEVEL DURING INSPECTION. CORROSION WAS VISIBLY BEYOND LIMITS. FABRICATED AND INSTALLED REPLACEMENT WEB, REF KFC MCO 3218, WO 1364309.

Part: KEELBEAM — CORRODED (BS 812) · airframe 73,465 hrs · 57,254 cycles

AFT CARGO PIT BS 812, STR 27 KEEL BEAM CORRODED. REPAIRED KEEL BEAM CHORD IN AFT CARGO PIT BS812, STR27L IAW REPAIR DWG R23094.1-053-008-001.

Part: KEELBEAM — CORRODED (BS 707-727) · airframe 73,465 hrs · 57,254 cycles

LEFT KEEL BEAM FLANGE AT BS707 TO 727, LBL8 CORRODED.

Part: INTERCOSTAL — CRACKED (BS 294) · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE DOOR FRAME SUPPORT INTERCOSTAL AT BS 294 BETWEEN STR 12R AND STR 13R CRACKED. DURING INSPECTION OF THE SURROUND STRUCTURE OF THE R1 ORIFICE, A CRACK WAS NOTED ON AN ANGLE THAT ATTACHES AN INTERCOSTAL BETWEEN S12 AND S13, RIGHT TO THE AIRCRAFT SKIN. THE ANGLE WAS REPLACED AS ALLOWED BY SB 53A1241. REF KFC MCO 3218, WO 1365645.

Part: SHEAR TIE — CORRODED (BS 986) · airframe 73,465 hrs · 57,254 cycles

CORROSION FOUND AT BS 986.5 ON SHEAR TIE BETWEEN STR 19R AND STR 20R. REPLACED SHEAR TIE IAW DWG 65-46564, REV D. INSTALLED IAW 51-30-02, REV 108 SRM.

Part: WEB — CRACKED (BS 1016) · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE AT BS 1016, LBL40 FLOOR WEB CRACKED. CRACK IN THE AFT CABIN STRESS WEB. FABRICATED AND INSTALLED REPLACEMENT WEB IAW DWG 65-46812 AND SRM R108.

Part: WEB — CORRODED (BS 907) · airframe 73,465 hrs · 57,254 cycles

AFT CARGO BAY BS 907 STRINGER 17R WEB CORROSION FOUND AT RBL65. FABRICATED AND INSTALLED REPLACEMENT WEB IAW SRM 53-10-2, FIG 13, PG 97, REV 108, DWG 65-47976, REV T.

Part: INTERCOSTAL — CORRODED (BS 789) · corrosion level 2 · airframe 73,465 hrs · 57,254 cycles

AFT CARGO BAY BS 789, RBL 23 INTERCOSTAL CORRODED. BLENDED, MEASURED AND FOUND TO BE BEYOND THE LIMITS OF SRM R108, 53-10-1. FABRICATED AND INSTALLED REPLACEMENT PART IAW DWG 65-47959, SHEET 2, REV J.

Part: FLOOR SUPPORT — CRACKED (BS 787) · airframe 73,465 hrs · 57,254 cycles

AFT CARGO BAY BS 787, RBL 25, FLOOR SUPPORT CRACKED AND CORRODED. REPLACED FLOOR SUPPORT IAW 65-47957, 0002, REV D.

Part: FRAME — CRACKED (BS 277) · airframe 73,465 hrs · 57,254 cycles

FRAME AT BS 277, S16L CRACKED IN UPPER FUSELAGE. REPAIRED FRAME AT BS 277, STR 16L IN UPPER FUSELAGE IAW SRM 53-10-04 FIG 7, REPAIR 2, R108. REF KFC MCO 3218, WO 1367632.

Part: SKIN — CORRODED (BS 620) · corrosion level 2 · airframe 73,465 hrs · 57,254 cycles

LOWER LOBE SKIN CORROSION UNDER MARKER BEACON ANTENNA BS 620. REPLACED IAW BAC DWG 65-45866, REV G.

Part: DOOR FRAME — CORRODED (BS 797) · airframe 73,465 hrs · 57,254 cycles

AFT CARGO BAY BS 797, RBL 26, LWR CARGO ENTRY WAY SKIN CORRODED. OUT OF LIMITS CORROSION NOTED ON THE STRUCTURAL SILL WEB AND THE C2 THRESHOLD. REPLACED WITH NEW WEB, DWG 65-47957 AND SRM R108.

Part: BELTFRAME — CRACKED (BS 847) · airframe 73,465 hrs · 57,254 cycles

AFT CARGO PIT, BS 847 BELTFRAME CRACKED INBD OF STR 25L. CRACK FRAME AT BS 847 AT S25L +5, REPAIRED IAW SRM R108 53-10-4, FIG 7.

Part: FLOORBEAM — CORRODED (BS 867) · corrosion level 2 · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE BS 867, LBL 25 TO LBL 45 CORRODED ON LWR FLANGE OF FLOORBEAM. CORROSION BEYOND LIMITS WAS NOTED ON THE LOWER FLANGE OF THE MAIN DECK FLOORBEAM AT BS 867 FROM LBL 25-LBL 45. REPAIRED IAW SRM R108, 53-10-9, FIG 7, REF KFC MCO3218, W/O 1364373.

Part: SKIN — DAMAGED (AIRSTAIR DOOR) · airframe 73,465 hrs · 57,254 cycles

FWD AIR STAIR DOOR INNER SKIN DAMAGE IN UPPER FWD CORNER. DURING INSPECTION, SIGNIFICANT DAMAGE WAS NOTED ON THE INNER SKIN OF THE FORWARD AIRSTAIR DOOR. FABRICATED AND INSTALLED REPLACEMENT SKIN IAW DWG 65-27942 AN, REF KFC MCO 3218, WO 1365636.

Part: FAILSAFE — MISINSTALLED (BS 420) · airframe 73,465 hrs · 57,254 cycles

DURING REPAIR OF A CRACKED FRAME FAIL SAFE ANGLE IN THE AREA, IT WAS NOTED THAT THE FRAME SPLICES DID NOT CONFORM TO AEI DRAWINGS. AT REQUEST, NON-CONFORMING FRAMES IN THE AREA WERE INSPECTED AND ADDRESSED. THIS FRAME WAS REPAIRED IAW DWG R23094.1-053-016-001, REV NC AND EO1847. REF KF MCO 3218, WO 1374702.

Part: FLOOR SUPPORT — CORRODED (BS 639-673) · corrosion level 2 · airframe 73,465 hrs · 57,254 cycles

UPPER FLOOR BS 673 TO BS 639, LBL 65 HAS CORROSION ON TOP & BOTTOM OF SILL. DURING INSPECTION, CORROSION WHICH WAS VISUALLY BEYOND LIMITS WAS NOTED ON THE CREASE BEAM INNER CHORD IN THIS AREA. CHORD REPLACED IAW BAC DWG 65-47943 AND SRM R108, REF KFC MCO 3218, WO 1364928.

Part: FRAME — DAMAGED (BS 380) · airframe 73,465 hrs · 57,254 cycles

DAMAGE ON FRAME, BS 380, S15-16R. DURING INSPECTION, DAMAGE WAS NOTED ON THE INNER CHORD OF THE FRAME AT THIS LOCATION. REPAIRED IAW DWG R23094.1-053-012-001, REV NC.

Part: FRAME — DAMAGED (BS 360) · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE BS 360, FRAME S17-16R DAMAGED.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 73,465 hrs · 57,254 cycles

FWD CARGO BAY DOOR INNER SKIN LIGHTING HOLE CRACKED AT BS 450 AND RBL 34. REPAIRED CRACKED LIGHTNING HOLE WITH DOUBLER INSTALLED IAW 52-30-1, FIG 1, REV 108, AND SRM 51-40-02, FIG 1, REV 108.

Part: WEB — CORRODED (BS 616-639) · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE FLOOR CORRODED SHEAR WEB BS 616 TO BS 639, RBL 65, STR 17R. DURING INSPECTION, OUT OF LIMITS, CORROSION WAS NOTED ON THE CREASEBEAM WEB BETWEEN BS 616 AND BS 639, RT. FABRICATED AND INSTALLED REPLACEMENT WEB.

Part: FLOORBEAM — CORRODED (BS 480) · corrosion level 2 · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE FLOOR BS 480, RBL 65-45 HAS CORROSION ON FLOORBEAM. UPPER FUSELAGE BS 480 RBL 65-45 HAD CORROSION ON FLOORBEAM BEYOND LIMITS. REPAIRED FLOORBEAM IAW SRM 53-10-01, FIG 7, REV 108.

Part: KEELBEAM — DETERIORATED (BS 700-727) · airframe 73,465 hrs · 57,254 cycles

RT KEEL BEAM FLANGE AT BS 700-727, RBL 8. HAS DETERIORATED TEFLON PAINT. REPAIRED RT KEELBEAM FLANGE IAW DWG R23094 1-053-013-001.

Part: FITTING — CORRODED (VERTICAL STAB) · airframe 73,465 hrs · 57,254 cycles

CORROSION ON VERTICAL STABILIZER ON RT AFT FITTING FWD SIDE. DURING THIS INSPECTION, CORROSION WAS NOTED IN THIS FITTING AND FOUND TO BE BEYOND LIMITS. FITTING WAS REPLACED WITH NEW IAW BAC DWG 65-53744, REV C AND SRM R108, REF KFC MCO 3218, WO 1367614.

Part: FRAME — DAMAGED (BS 787) · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE, BS 787 BETWEEN S17R-16R DAMAGED FRAME. REPAIRED IAW KF DWG R23094.1-053-007-001, REV NC.

Part: SUPPORT — CRACKED (BS 775) · airframe 73,465 hrs · 57,254 cycles

AFT CARGO BAY BS 775, RBL 2 ANTENNA SUPPORT STRUCTURE HAS 2 CRACKS. THE INTERIOR STRUCTURE WAS REPLACED AND AN EXTERNAL DOUBLER WAS INSTALLED. DOUBLER IS IN PROXIMITY TO A DER INSTALLED EXTERNAL DOUBLER USED ON TI: VRX4. DUE TO THE NATURE OF THIS REPAIR, 1 TI WILL COVER BOTH THE CHANNEL REPLACEMENT AND THE SKIN DOUBLER. IAW SR 4-2852566977, KFC-NAC-15-0009-07B. INSTALLED IAW SRM 51-30-02, REV 108.

Part: ANGLE — CRACKED (BS 727) · airframe 73,465 hrs · 57,254 cycles

AFT CARGO BAY BS 727, RBL 18, WL 200 CRACKED CLIP. DURING INSPECTION, A CRACKED CLIP WHICH SERVES TO SECURE THE UPPER END OF THE RBL 18 VERTICAL BEAM OF THE BS 727 BULKHEAD WAS NOTED. FABRICATED AND INSTALLED A REPLACEMENT CLIP IAW DWG 65-46547, REV DK AND SRM R108. THIS AREA IS NOT PART OF THE BS 727 BULKHEAD, LONGITUDUNAL FLOORBEAM AD AREA, REF KFC MCO 3218, WO 1365527.

Part: FLOOR SUPPORT — CRACKED (BS 616-639) · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE FLOOR BS 616 & BS 639 AT RBL 65 SIDE RAIL CRACKED. DURING INSPECTION, CRACKS WERE NOTED AT THE CREASE BEAM INNER CHORD. THIS CHORD ALSO SUPPORTS THE FLOORBOARD EDGES. THE 62" SECTION OF CHORD WAS REPLACED IAW DWG 65-48973 AND SRM R108.

Part: STRINGER — CORRODED (BS 904) · corrosion level 2 · airframe 73,465 hrs · 57,254 cycles

AFT CARGO BAY BS 904, STRINGER 26R CORRODED OUT OF LIMITS. . FABRICATED AND INSTALLED REPLACEMENT STRINGER SECTION AND ASSOCIATED SPLICES.

Part: FLOOR SUPPORT — CRACKED (BS 380-400) · airframe 73,465 hrs · 57,254 cycles

FWD CARGO BAY MAIN DECK INTERCOSTAL BETWEEN FLOORBEAMS CRACKED AT BS 380 TO 400 & BL 0. FABRICATED AND INSTALLED REPLACEMENT INTERCOSTAL IAW DWG 69-35365.

Part: WEB — CORRODED (BS 927-947) · airframe 73,465 hrs · 57,254 cycles

AFT CARGO BAY WEB FROM BS 927 TO BS 947, RBL65 CORROSION FOUND. FABRICATED AND INSTALLED REPLACEMENT WEB IAW DWG 65-45855, REV CV.

Part: FLOORBEAM — CORRODED (BS 807) · corrosion level 2 · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE BS 807, LBL 65 TO RNL 65 HAS CORROSION ON LWR FLANGE OF FLOORBEAM & LWR STRAP. DURING INSPECTION, CORROSION WAS NOTED ON THE LOWER FLANGE OF THE BS 807 FLOORBEAM AND ON THE AEI STRAP ON THE UNDERSIDE OF THE BEAM. THE STRAP WAS BLENDED, MEASURED AND FOUND TO BE WITHIN LIMITS. THE FLOORBEAM FLANGE WAS REPAIRED IAW SRM R108, 53-10-9, FIG 7. FLOORBEAMS ARE FLAGNOTE B FCBS SO DTA IS NOT REQUIRED, REF KFC MCO 3218, WO 1364375.

Part: FLOOR SUPPORT — CORRODED (BS 540-727B) · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE FLOOR HAS CORROSION ON FLOORBEAM FLANGE STRUCTURE AT BS 727B TO BS 540, RBL45. OUT OF LIMITS CORROSION WAS NOTED ON THE UPPER CAP OF THE LONGITUDINAL FLOORBEAM LOCATED AT RBL45. IT WAS NOTED THAT THERE WAS PREVIOUS BLEND ACTIVITY ON THIS CAP. THE PREVIOUS BLEND ACTIVITY IS DETAILED IN TI: WS5G WHICH HAS NOW BEEN SUPERSEDED BY THIS TI. THE SUCCESSIVE BLENDS, BY DEFINITION, REDUCE THE CORROSION LEVEL OF THIS REPLACEMENT TO A LEVEL 1, REF KF MCO 3218, WO 1364378.

Part: FRAME — DAMAGED (BS 360) · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE FRAME BS 360 S16L DAMAGE ON FRAME.

Part: FLOORBEAM — CORRODED (BS 867) · corrosion level 2 · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE BS 867, LBL 25 TO LBL 45 CORRODED ON LWR FLANGE OF FLOORBEAM. CORROSION BEYOND LIMITS WAS NOTED ON THE LOWER FLANGE OF THE MAIN DECK FLOORBEAM AT BS 867 FROM LBL 25-LBL 45. REPAIRED IAW SRM R108, 53-10-9, FIG 7. REF KFC MCO3218, W/O 1364373.

Part: FLOOR SUPPORT — CORRODED (BS 540-727B) · corrosion level 2 · airframe 73,465 hrs · 57,254 cycles

FLOORBEAM CHORD AT RBL24 FROM BS 540 TO BS 727B HAS CORROSION AROUND CLIPNUT HOLES. OUT OF LIMITS CORROSION NOTED IN SEVERAL PLACES DURING INSPECTION NECESSITATING REPLACEMENT OF THE ENTIRE UPPER CAP. REF DWG 65-45410, REV P AND SRM R108 AND SB 57-1139 R4, FIG 13.

Part: SUPPORT ANGLE — CRACKED (BS 440) · airframe 73,465 hrs · 57,254 cycles

FWD CARGO BAY STRINGER SUPPORT ANGLE CRACKED AT BS 440 AT STR 24R. REPLACED WITH MADE PART IAW DWG 65-20722, REV K. FASTENERS INSTALLED IAW -200, SRM 51-30-2.

Part: WEB — CORRODED (BS 616-639) · corrosion level 2 · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE FLOOR CORRODED SHEAR WEB BS 616 TO BS 639, LBL 65, STR 17L. FABRICATED AND INSTALLED REPLACEMENT WEB IAW SRM 53-10-02, FIG 1, ITEM 3, REV 108, REF KFC MCO 3218, WO 1367615.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 73,465 hrs · 57,254 cycles

FWD CARGO BAY DOOR INNER SKIN LIGHTING HOLE CRACKED AT BS 480, RBL 44. REPAIRED CRACKED LIGHTNING HOLE WITH DOUBLER INSTALLED AT BS 480, RBL 44 WITH FABRICATED PART IAW 52-30-1, FIG 1, REV 108, SRM 51-40-02, FIG 1, REV 108, SRM, REF KFC MCO3218, W/O 1365812.

Part: FAILSAFE — CRACKED (FRAME) · airframe 73,465 hrs · 57,254 cycles

DURING REPAIR OF A CRACKED FRAME FAIL SAFE ANGLE IN THE AREA, IT WAS NOTED THAT THE FRAME SPLICES DID NOT CONFORM TO AEI DRAWINGS. NON-CONFORMING FRAMES IN THE AREA WERE ADDRESSED. THIS FRAME WAS REPAIRED IAW DWG R23094.1-053-016-001, REV NC AND EO1847, REF KF MCO 3218, WO 1374715.

Part: FLOOR SUPPORT — CORRODED (BS 540-727B) · corrosion level 2 · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE FLOOR BS727B TO 540 LBL25 CORROSION ON FLOORBOARD FLANGE STRUCTURE. AWAITING PAPERWORK FROM C-CHECK.

Part: FLOORBEAM — CRACKED (BS 328) · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE FLOORBEAM SUPPORT ANGLE AT BS 328, RBL 34 HAS CRACK. REPLACED CRACKED ANGLE WITH FABRICATED NEW PART IAW 51-20-01, FIG 7, REV 108, SRM, REF KFC MCO3218, W/O 1365671.

Part: SHEAR WEB — CORRODED (BS 639-663) · corrosion level 2 · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE FLOOR CORRODED SHEAR WEB BS 639 TO BS 663, LBL 65, STR 17R. DURING INSPECTION, CORROSION THAT WAS VISIBLY BEYOND LIMITS WAS NOTED ON THE CREASE BEAM WEB AT S17L THAT RUNS BETWEEN BS639 AND BS663. FABRICATED AND INSTALLED REPLACEMENT WEB IAW SRM R108 53-10-2, FIG 1, MAT ID, BACD2000 AND 51-30-02.

Part: WEB — CRACKED (BS 450) · airframe 73,465 hrs · 57,254 cycles

CRACKED LIGHTNING HOLE AT BS 450, RBL 44. REPAIRED CRACKED LIGHTNING HOLE WITH DOUBLER INSTALLED AT BS450, RBL 44 WITH FABRICATED PART IAW 52-30-1, FIG 1, REV 108, SRM 51-40-02, FIG 1, REV 108, SRM, REF KFC MCO3218, W/O 1364044.

Part: FRAME — CRACKED (BS 380) · airframe 73,465 hrs · 57,254 cycles

FRAME CRACKED IN MAIN CABIN FRAME BS 380, STRINGER 17L. REPAIRED THE FRAME IAW 51-20-01, REV 108 SRM.

Part: SUPPORT FITTING — CRACKED (MLG) · airframe 73,465 hrs · 57,254 cycles

OTBD MLG SUPPORT BEAM FITTING CRACKED. THE FITTING WAS REPLACED WITH THE NEWER STYLE AS SHOWN SB 57-1216R2, REF KFC MCO 3218, WO 1367210.

Part: FAILSAFE — CRACKED (FRAME) · airframe 73,465 hrs · 57,254 cycles

DURING REPAIR OF A CRACKED FRAME FAIL SAFE ANGLE IN THE AREA, IT WAS NOTED THAT THE FRAME SPLICES DID NOT CONFORM TO AEI DRAWINGS. NON-CONFORMING FRAMES IN THE AREA WERE ADDRESSED. THIS FRAME WAS REPAIRED IAW DWG R23094.1-053-017-001, REV NC AND EO1847, KF MCO 3218, WO 1374700.

Part: FAILSAFE — CRACKED (FRAME) · airframe 73,465 hrs · 57,254 cycles

DURING REPAIR OF A CRACKED FRAME FAIL SAFE ANGLE IN THE AREA, IT WAS NOTED THAT THE FRAME SPLICES DID NOT CONFORM TO AEI DRAWINGS. NON-CONFORMING FRAMES IN THE AREA WERE ADDRESSED. THIS FRAME WAS REPAIRED IAW DWG R23094.1-053-016-001, REV NC AND EO1847. REF KF MCO 3218, WO 1374705.

Part: STRINGER CLIP — CRACKED (BS 663) · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE BS 663, STRINGER 10L CLIP CRACKED. REPLACED WITH NEW STRINGER CLIP IAW SB 53-1268R00.

Part: FLOOR SUPPORT — CRACKED (BS 683-722) · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE MAIN CABIN BL0 BS719 LONGITUDINAL FLOOR BEAM WEB CRACKED 3 PLACES. REPLACED UPPER FUSELAGE MAIN CABIN BL0 BS719 LONGITUDINAL FLOOR BEAM WEB WITH MADE REPAIR PART IAW SB 737-57-1210, REV 4. REPLACED LOWER CHORD UPPER FUSELAGE MAIN CABIN BL0 BS683 TO BS722 WITH MADE REPAIR PART IAW DWG 65-45410, REV H.

Part: ATTACH FITTING — CORRODED (VERTICAL STAB) · airframe 73,465 hrs · 57,254 cycles

CORROSION ON VERTICAL STABILIZER ATTACH FITTING LT AFT FWD FACE. DURING INSPECTION CORROSION WAS NOTED ON THE VERTICAL STABILIZER ATTACH FITTING, LT SIDE, AFT. FITTING WAS REPLACED WITH NEW. STABILIZER REMOVAL WAS NOT NECESSARY.

Part: STRINGER CLIP — CRACKED (BS 663) · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE BS 663, STRINGER 10R CLIP CRACKED. REPLACED WITH NEW STRINGER CLIP IAW SB53-1268R00.

Part: SKIN — CRACKED (BS 747-767) · airframe 73,465 hrs · 57,254 cycles

CRACKED EXTERIOR FUSELAGE BETWEEN BS 747 & BS 767 AT STR 18L. REPAIRED CRACK WITH EXTERNAL DOUBLER AT BS 747-BS 767 IAW SB 737-53-1065, REV 2, APRIL 19, 2001, REPAIR FIGURE 54.

Part: FAILSAFE — CRACKED (FRAME) · airframe 73,465 hrs · 57,254 cycles

DURING REPAIR OF A CRACKED FRAME FAIL SAFE ANGLE IN THE AREA, IT WAS NOTED THAT THE FRAME SPLICES DID NOT CONFORM TO AEI DRAWINGS. NON-CONFORMING FRAMES IN THE AREA WERE ADDRESSED. THIS FRAME WAS REPAIRED IAW DWG R23094.1-053-016-001 REV NC AND EO1847, REF KF MCO 3218, WO 1374703.

Part: FAILSAFE — CRACKED (BS 520) · airframe 73,465 hrs · 57,254 cycles

FORWARD CARGO PIT AT BS 520, LBL 30, FAILSAFE CRACKED.

Part: FLOORBEAM — CORRODED (BS 887) · corrosion level 2 · airframe 73,465 hrs · 57,254 cycles

UPPER FUSELAGE FLOOR BS 887, RBL 25 TO LBL 12.5 HAS CORROSION ON LOWER FLANGE OF FLOORBEAM. REPAIRED FLOOR BEAM IAW SRM R108, 53010-9, FIG 7. REF KFC MCO 3218, WO 1364162.

Part: FAILSAFE — CRACKED (FRAME) · airframe 73,465 hrs · 57,254 cycles

DURING REPAIR OF A CRACKED FRAME FAIL SAFE ANGLE IN THE AREA, IT WAS NOTED THAT THE FRAME SPLICES DID NOT CONFORM TO AEI DRAWINGS. NON-CONFORMING FRAMES IN THE AREA WERE ADDRESSED. THIS FRAME WAS REPAIRED IAW DWG R23094.1-053-016-001, REV NC AND EO1847, REF KF MCO 3218, WO 1374719.

Part: O-RING — DETERIORATED (HYD SYSTEM) · airframe 72,308 hrs · 56,361 cycles

NR 2 HYDRAULIC LOW PRESSURE LIGHT FLICKERED ON & OFF ALONG WITH MASTER CAUTION LIGHT DURING DEPARTURE. SYSTEM "A" INDICATED .5 GALLONS DURING CLIMB AND VISUAL APPROACH. FOUND O-RINGS ON ELEVATOR FEEL COMPUTER FILTER CAPS DETERIORATED. REPLACED O-RINGS ON BOTH INPUT & OUTPUT, LEAK CHECKED GOOD IAW CMM 27-09-31. SERVICED HYDRAULIC SYSTEM TO FULL IAW AMM 12-12-0, PG 201, PARA C.

Part: INDICATOR — SPLIT (FLAPS) · airframe 71,865 hrs · 55,944 cycles

PILOT REPORTED NO FLAPS EXTENSION ON DESCENT. ACFT RETURNED TO HOME BASE. PERFOMED DETAILED INSPECTION OF FLAP SYSTEM COMPONENTS. REPLACED HYD FLAP DRIVE MOTOR AND FLAP POSITION INDICATOR. TEST PERFORMED IAW MM 27-51-01, AND SYSTEM CHECKED OK.

Part: SKIN — CRACKED (BS 940) · airframe 71,683 hrs · 55,769 cycles

FUSELAGE SKIN CRACKED AT BS 940, JUST BELOW STRINGER 24R, VERIFIED WITH HFEC. INSTALLED REPAIR IAW DWG 5330D1816, SHEET 1-2 AND SRM 53-30-3.

Part: SKIN — CRACKED (BS 934) · airframe 70,923 hrs · 55,058 cycles

FUSELAGE SKIN CRACKED AT BS 934, JUST ABOVE S24R. REPAIRED IAW ASI DWG 5330D1744, SHEET 1-2 & SRM 53-30-3 FIG 48, DETAIL XXXVI.

Part: TRANSMITTER — FAULTY (NR 2 ENGINE) · airframe 69,454 hrs · 53,651 cycles

TAKEOFF WAS ABORTED AT 90KTS DUE TO EXCESSIVE FUEL FLOW INDICATION ON NR 2 ENGINE. REPLACED NR 2 ENGINE FUEL FLOW TRANSMITTER, REF: B737-200MM 73-31-11.

Part: SHEAR WEB — CRACKED (FUSELAGE) · airframe 69,425 hrs · 53,625 cycles

INNER SKIN SHEAR WEB IS CRACKED (2) PLACES & HAD CORROSION STA 348.2 - 351.2 LT STR 15-17. REPLACEMENT OF INNER SKIN SHEAR WEB STA 348.2-351.2 LT STR 15-17 IAW B737-200 DWG 65-17685 REV N.

Part: SKIN — DENTED (FUSELAGE) · airframe 69,424 hrs · 53,625 cycles

DENT FOUND ON SKIN AT STATION 914, STRINGER 24 R. PERFORMED HFEC ON EXISTING HOLES COMMON TO REPAIR AND FUSELAGE SKIN, NO CRACKS FOUND. INSTALLED PERMANENT REPAIR FOR DENT IAW B737 SRM 53-30-3 FIGURE 48 REVISION 105.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 69,425 hrs · 53,625 cycles

CORROSION ON SEAT TRACK STA 380-460 CORROSION ON SEAT TRACK STA 380-460 RBL 45 BEYOND ALLOWABLE LIMITS. SEAT TRACK REPAIRED IAW B737-200 SRM 53-10-5 FIG 2 REV 105.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 69,425 hrs · 53,625 cycles

CRACK IN INTERCOSTAL ANGLE STA 278 STR 9R-18R BETWEEN. REPLACED CRACKED INTERCOSTAL ANGLE STA 278 STR 9R-18R BETWEEN IAW B737 SRM 51-10-01 PARA 7 REV 105 AND B737 SRM 51-30-02 REV 105.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 69,425 hrs · 53,625 cycles

CORROSION ON SEAT TRACK BS 400 - 470 LBL 25.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 69,425 hrs · 53,625 cycles

CORROSION ON SEAT TRACK BS 360 - BS 470, LBL 45. CORROSION ON SEAT TRACK REPAIRED BY REPLACEMENT IAW B737-200 SRM 51-10-5 FIG 2 REV 105.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 69,425 hrs · 53,625 cycles

CORROSION ON FLOOR SUPPORT ANGLE BS 346 LBL 61 AT L1 DOOR ORIFICE.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 69,425 hrs · 53,625 cycles

FOUR CRACKS FOUND IN WEB OF LONGITUDINAL FLOORBEAM BS 706 - BS 716 RBL 24. REPAIRED WEB OF LONGITUDINAL FLOORBEAM STA 706-716 RBL 24 IAW B737 SB 737-57-1296 FIG 22 REV 1.

Part: SKIN — CRACKED (FUSELAGE) · airframe 69,425 hrs · 53,625 cycles

CRACK IN FUSELAGE SKIN BS 788 S17L - S16L IN BETWEEN STRINGERS. REPAIRED CRACK IN FUSEALGE SKIN STA 788 STR 17L-16L IN BETWEEN STRINGERS IAW BOEING SB737-53-1065 FIG 54 REV 2.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 69,425 hrs · 53,625 cycles

SEVEN CRACKS FOUND IN WEB OF LONGITUDINAL FLOORBEAM BS 706-716 LBL 24. REPAIRED WEB OF LONGITUDINAL FLOORBEAM STA 706-716 LBL 24 IAW B737 SB 737-57-1296 FIG 21 REV 1.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 69,425 hrs · 53,625 cycles

NDT DETECTED CRACK DURING OPEN HOLE PROBE AS PER SB737-57- 1296, LONGITUDINAL FLOORBEAM LOWER CHORD BS 663 RBL 24, AFT HOLE.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 69,425 hrs · 53,625 cycles

CRACK IN INTERCOSTAL BS 329 LBL 47. REPLACE CRACKED INTERCOSTAL STA 329 LBL 47 IAW BOEING DRAWING 65-45834 REV F AND B737 SRM 51-30-2 REV 105.

Part: SKIN — CRACKED (FUSELAGE) · airframe 69,425 hrs · 53,625 cycles

CRACK ON FUSELAGE SKIN S16R BS 520. REPAIRED CRACK ON FUSELAGE SKIN STR 16R STA 520 IAW B737-200 SRM 53-30-3 FIG 48 DETAIL VII SHT 29 REV 105.

Part: DOOR FRAME — DAMAGED (FUSELAGE) · airframe 69,425 hrs · 53,625 cycles

HOLE DAMAGE TO BS 248.2 FRAME INNER CHORD & INTERCOSTALS & DOORSTOPS FROM S14 TO S7 L1 DOOR ORIFICE.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 69,425 hrs · 53,625 cycles

CORROSION ON FLOORBEAM UPPER "T" BS 328 BS 12-35. CORROSION ON FLOORBEAM UPPER "T" STA 328 RBL 12-35 BEYOND LIMITS IAW B737 SRM 53-10-1 FIG 1 REV 105. UPPER "T" REPLACED IAW BOEING DWG 65-45812 REV L AND B737 SRM 53-10-9 FIG 5 REV 105.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 69,425 hrs · 53,625 cycles

CRACK IN INTERCOSTAL BS 327 LBL 47. REPLACED CRACKED INTERCOSTAL STA 327 LBL 47 IAW BOEING DRAWING 65-45834 REV F AND BOEING 737 SRM 51-30-2 REV 105.

Part: FLOORBEAM — GOUGED (FUSELAGE) · airframe 69,425 hrs · 53,625 cycles

GOUGE IN LOWER FLANGE FLOORBEAM BS 294.5 LBL 50 WL 203.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 69,425 hrs · 53,625 cycles

NDT DETECTED CRACK DURING OPEN HOLE PROBE AS PER SB737-57-1296, LONGITUDINAL FLOORBEAM LOWER CHORD BS 663 LBL 24, AFT HOLE.

Part: STRUCTURE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 69,425 hrs · 53,625 cycles

CORROSION AROUND L1 ENTRY AFT DRAIN LINE UNDERSIDE.

Part: SHEAR TIE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 69,425 hrs · 53,625 cycles

CORROSION ON FITTING THAT ATTACHES BELT FRAME TO THE SKIN AT BS 986.5 BETWEEN S24R AND S25R. REPLACED CORRODED SHEAR TIE THAT ATTACHES BELTFRAME TO THE SKIN AT STA 986.5 BETWEEN STRINGERS 24R AND 25R IAW BOEING DWG 65-46564 REV AB.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 69,425 hrs · 53,625 cycles

CORROSION ON S27R IN AFT CARGO PIT EQUIPMENT BAY BS 947.5. STRINGER 27R IN AFT CARGO PIT EQUIPMENT BAY STA 947.5 REPAIRED IAW BOEING 737-200 SRM 53-10-3 FIG1 REV 105.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 69,424 hrs · 53,625 cycles

CORROSION ON FLOOR SUPPORT STA 535 WL 208 HAVE BEEN BLENDED OUT IAW B737-200 SRM 53-10-01. MTL THICKNESS 0.040" MTL REMOVED 0.010" MTL REMAIN 0.030" AND FOUND BEYOND LIMITS. REPLACED FLOOR SUPPORT STA 535 LBL 45-LBL IAW B737-200 SRM 51-10-1 PAGE 9 & IAW B737-200 SRM 51-30-02 REV 105.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 69,425 hrs · 53,625 cycles

CORROSION ON FLOORBEAM CAP UNDER CLIP NUTS BS 480 LBL 47 - LBL 62.

Part: SKIN — CRACKED (FUSELAGE) · airframe 69,161 hrs · 53,379 cycles

CRACK IN L2 DOOR LOWER FORWARD CUTOUT AT STA 965, STR 19L. REPAIRED CRACK IN FUSELAGE SKIN AT L2 DOOR, LOWER FORWARD CUTOUT BY REMOVING DAMAGED AREA OF SKIN, DOUBLER & BEARSTRAP AND INSTALLING REPAIR PER BOEING SRM 53-30-3, FIG 46, DETAIL IV.

Part: INDICATOR — DEFECTIVE (COCKPIT) · airframe 67,216 hrs · 51,695 cycles

ABORTED TAKEOFF DUE TO FAULTY N1 GUAGE READING NO HIGHER THAN 50 PERCENT. REPLACED NR 1 ENGINE N1 GAUGE.

Part: DOOR FRAME — CRACKED (CARGO BAY) · airframe 67,080 hrs · 51,627 cycles

FWD BAGGAGE PIT DOORWAY AFT FRAME STA 492.4 HAS CRACK IN FRAME RADIUS, UPPER FLANGE FWD (FLANGE TOWER) ABOVE STRINGER 24R. DISCOVERED WHILE ACCOMPLISING MAIN CARGO DOOR SSID INSPECTION F-10-3 REF: AD 2005-07-19 SB B737-53A1228. REPLACED FRAME. REF: B737-200 SRM 51-30-2 AND BOEING DRAWING NUMBER 65-20723.

Part: TURBINE BLADES — DISINTEGRATED (NR 2 ENGINE) · airframe 66,218 hrs · 50,813 cycles

NR 2 ENGINE FAILURE ON TAKEOFF ROLL (TURBINE SHELLED). REPLACEMENT OF ENGINE IN PROGRESS. TURBINE BLADES DISINTEGRATED. UNCLEAR WHY AT THIS TIME. DAMAGE CONTAINED WITHIN ENGINE COMPARTMENT.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

CORROSION ON END OF STRINGER 26R STA 530 FWD CARGO PIT. REMOVED CORROSION AT END OF STRINGER 26R AT BS 530 FWD CARGO PIT IAW B737 SRM 51-10-6 REMAINING MATERIAL FOUND TO BE BEYOND LIMITS PER 53-10-1 FIG 1 DETAIL VI. REPAIRED STRINGER AT STA 530 STR 26R FWD CARGO PIT IAW B737 SRM 53-10-2 FIG 1 SHEETS 1 TO 9.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

CORROSION ON AFT BULKHEAD STA 1016 STR 24L TO STR 24R BOTTOM. CORROSION ON AFT BULKHEAD AT STA 1016 STR 24L TO 24R REMOVED IAW B737 SRM 51-10-6, REMAINING MATERIAL IS BEYOND LIMITS PER 53-10-1 FIG 1 SHEET 11-12. REPAIRED AFT PRESSURE BULKHEAD AT STA 1016 STR 24L TO STR 24R IAW B737 SB 53A-1075 DATED 8 JUNE 2000 REV 3 & SB737 - DRW 65C28106.

Part: STRUCTURE — CRACKED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

CRACKED INNER CHORD AT BS 639L AT FASTENER JUST BELOW STR 15L. CRACKED INNER CHORD AT BS 639 AT FASTENER JUST BELOW STR 15L REPAIRED IAW BOEING SB; SB737-53A1254, PART 4 FIG 14, DWG 65C38795 SB REV 1 DATED 9 JULY 2009.

Part: STRINGER — DAMAGED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

HOLE DAMAGE ON STR 7R AT STA 1085. FABRICATED NEW STRINGER PIECE IAW B737 SRM 53-10-03 PG 3 TO PG 10. REPAIRED HOLE DAMAGE ON STR 7R AT STA 1085 IAW B737 SRM 53-10-03 PG 3 TO 10, AND B737 SRM 51-30-02 PG 5 PARA 7 TO PG 6.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

CRACKED INTERCOSTAL IN FWD CARGO COMPARTMENT STA 500B BL 0. FABRICATED AND INSTALLED REPLACEMENT INTERCOSTAL IN FWD CARGO PIT, STA 500B BL 0 IAW BSRM 51-10-01 PG 9 PARA 7 AND 51-30-02 AND BOEING 737 DWG 69-41680 SHEET 2 ITEM 2.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

CORROSION ON KEEL BEAM ANGLE RBL 6 STA 520 FWD CARGO PIT. REMOVED CORROSION ON KEEL BEAM ANGLE RBL 6, STA 520 FWD CARGO PIT IAW BOEING 737-200 SRM 51-10-6. BLEND OUT FOUND TO BE BEYOND LIMITS IAW B737-200 SRM 53-10-1, FIG. 7. REPAIRED KEEL BEAM ANGLE RBL 6, STA 520 FWD CARGO PIT IAW FAA FORM 8110-3, NR 066-1026-11-1044/SUBJECT: RT KEEL BEAM LOWER CHORD BLEND REPAIR.

Part: RIB — GOUGED (HORIZ STAB) · airframe 65,596 hrs · 50,230 cycles

RIGHT ELEVATOR NR 2 BALANCE PANEL BAY HAS WEAR GOUGE ON HORIZONTAL STABILIZER RIB, O/B SIDE, ELEVATOR STN 94-07. REPAIRED HORIZONTAL STAB RIB ALONG O/B SKIN SURFACE AT ELEVATOR STA 94-07 IN NR 2 BALANCE PANEL BAY IAW B737-200 SRM 51-40-24 PG 2, FIG 1. RIGHT ELEVATOR NR 2 BALANCE BAY PANEL REFINISHED IAW MM 51-21-81 PG 701.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

CRACKED ANGLE AT STA 1088 AFT SIDE STR 25R TO STR 25L. CRACKED ANGLE AT STA 1088 AFT SIDE STR 25R TO STR 25L. FABRICATED & INSTALLED IAW B737 DRW 65-54837 SHEET 1 REV E PART 65-54837-2.

Part: PAN — CRACKED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

CRACKED AND GOUGED LAN PAN AT STA 1016 BL 0 ON BOTTOM OF FLOOR. CRACKED AND GOUGED LAN PAN AT STA 1016 AT BL 0 ON BOTTOM OF PAN REPAIRED IAW B737 SRM 51-40-2 FIG 1 SHEET 1-4.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

CRACKED SILL SUPPORT INTERCOSTAL FWD CARGO PIT STA 50A TO 500B AT STR 26L. REPLACED CRACKED SILL SUPPORT INTERCOSTAL IN FWD CARGO PIT STA 500A TO 500B AT STR 26L IAW B737-200 DRW 69-41473.

Part: FITTING — GOUGED (HORIZ STAB) · airframe 65,596 hrs · 50,230 cycles

WEAR MARK ON FITTING ON LEFT HORIZONTAL STABILIZER UPPER AFT FITTING. WEAR MARK ON FITTING ON LEFT HORIZONTAL STABILIZER UPPER AFT FITTING REPAIRED IAW FAA FORM 8100-9. REF: ID 201102210081-0003D1, SUBJECT HORIZONTAL STABILIZER CENTER SECTION REAR SPAR UPPER FITTING LEFT CLEVIS FWD LUG GOUGE DAMAGE FROM GAP COVER SCREWS. SCREW IN STAB CLOSE OUT PANEL ADJUSTED IAW B737 DWG 65-53746, CLEARANCE CHECKED.

Part: INTERCOSTAL — DAMAGED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

DOUBLE DRILLED HOLES ON INTERCOSTAL & CLIP STA 520 STR 26L FWD CARGO PIT. REPLACED DAMAGED INTERCOSTAL IN FWD PIT STA 500B TO STA 520 IAW B737-200 DRW 69-18388 AND REPLACED CLIP IAW DRW 69-38780.

Part: INTERCOSTAL — DAMAGED (FUSELAGE) · airframe 65,596 hrs · 502,320 cycles

DAMAGED HOLES IN UPPER FLANGE OF INTERCOSTAL FROM STA 440 TO STA 460 AND STR 26L CRACKED. REPLACED INTERCOSTAL AT STA 440 TO STA 460 STR 26L IAW B737-200 DWR 69-41473 REV D.

Part: INTERCOSTAL — DAMAGED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

DAMAGED HOLES IN UPPER FLANGE OF INTERCOSTAL FROM STA 460 TO STA 480, STR 26L ALSO CRACKED. REPLACED INTERCOSTAL IN FWD CARGO PIT STA 460 TO STA 480 AND STR 26L IAW B737-200 DRW 69-41473 REV D.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

CORROSION AROUND LIGHTING HOLES AND ANCHOR NUTS ON INTERCOSTAL STA 520 TP 500B STR 26R FWD CARGO COMPARTMENT. CORROSION AROUND LIGHTING HOLES AND ANCHOR NUTS ON INTERCOSTAL AT STA 500B TO 520 STR 26R FWD CARGO COMPARTMENT WAS FOUND BEYOND LIMITS IAW B737-200 SRM 53-10-01 PG 1 & PG 4 DETAIL 1. NEW PARTS FABRICATED AND INSTALLED IAW B737-200 DRW 69-18388 REV D AND AFT CLIP WAS FABRICATED AND INSTALLED IAW B737-200 DRW 69-38780.

Part: FITTING — DAMAGED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

ELONGATED HOLE AROUND HI-LOK IN FWD LOWER CARGO COMPARTMENT STA 460L STR 26L. FABRICATED NEW INTERCOSTAL CLIP IN FWD LOWER CARGO COMPARTMENT STA 460L STR 26L IAW DWG 69-51411 AND INSTALLED IAW BOEING DWG 69-41473.

Part: SKIN — CRACKED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

SKIN CRACKED AT STA 727B STR 18R UNDER AFT WING/BODY FAIRING. ZONE 1 PER B SB 737-53-1065 FIG 3 P 44. REPAIRED SKIN AT STA 727B STR 18R UNDER AFT WING/BODY FAIRING IAW B737-200 SRM 53-30-3 FIG 48 DET X.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

CRACKED INTERCOSTAL AT STA 1040 BETWEEN STR 3L & 4L. CRACKED INTERCOSTAL AT STA 1040 BETWEEN STR 3L & 4L, REMOVED AND REPLACED WITH FABRICATED PART AS PER B737-200 SRM 51-30-2 FIG 7, 3 AND 11 AND B737-200 SRM 51-20-1 FIG 7 AND BOEING DRW 65-46569.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 65,596 hrs · 50,230 cycles

CRACKED STRINGER FWD CARGO PIT STR 24L STA 430. CRACKED STRINGER IN FWD CARGO PIT STR 24L STA 430 REPAIRED IAW BOEING SRM 53-10-3 PG 1-8, INSTALLED IAW BOEING SRM 51-30-02 PG 2 PARA 4.

Part: LINE — LEAKING (NR 2 ENGINE) · airframe 64,618 hrs · 49,607 cycles

NR 2 ENGINE POWER LOSS, ENGINE SHUT DOWN. REMOVED PRESSURIZING & DUMP VALVE, REPLACED LEAKING LINE AND RE-INSTALLED P&D VALVE. OP & LEAK CHECK GOOD. REF: P&W MM 73-12-01.

Part: SKIN — CRACKED (FUSELAGE) · airframe 63,587 hrs · 48,658 cycles

FUSELAGE BELLY SKIN AT STA 520, BETWEEN STRINGERS 28L & 28R HAS A CRACK WHICH COMES OUT OF THE FORWARD L CORNER OF THE EXTERNAL AIR CONDITION ACCESS DOOR CUTOUT. PERFORMED HFEC AND SURFACE CONTOUR. CUT OUT, FABRICATED AND INSTALLED REPAIR DOUBLER .080 2024-T3 IN REFERENCE TO ASI SOLUTIONS DRAWING 5330840-1 REV IR.

Part: WINDOW — CRACKED (COCKPIT) · airframe 63,417 hrs · 48,502 cycles

CAPTAINS SIDE WINDOW MULTIPLE CRACKS & FIRE (SPARKS). REPLACED L2 WINDOW. REF: B737-200 MM 56-12-11. CHECKED GOOD.

Part: FILTER — UNKNOWN (HYD SYSTEM) · airframe 62,925 hrs · 48,019 cycles

NUBMER 1 "A" SYSTEM HYDRAULIC LOW PRESSURE LIGHT ILLUMINATED. NR 2 "A" SYSTEM LOW PRESSURE LIGHT ON/OFF INTERMITTENTLY. REMOVED NR 1 & 2 SYSTEM CASE DRAIN FILTERS, INSPECTED, NO CONTAMINATION NOTED. REPLACED WITH NEW FILTERS. OP & LEAK CHECK GOOD. PURGED HYDRAULIC RESERVOIR HEAD PRESSURE SYSTEM FROM THE NR 1 & 2 ENGINE TO MANFOLD IN WHEEL WELL. ALL MOISTURE REMOVED. SECURED LINE AND SECURED SYSTEM. LEAK CHECKED LINE, NO LEAKS NOTED. REF: MM 29-11-41 ALL SYSTEMS OP CHECK NORMAL.

Part: SKIN — CRACKED (FUSELAGE) · airframe 60,202 hrs · 45,318 cycles

FUSELAGE SKIN CRACK AT STRINGER 23R STA 950 APPROXIMATELY 2 3/8" LONG. CRACK HAS BEEN TRIMMED OUT PER BOEING 737 SRM 53-30-03, FIG 48 TO 2,9375 INCH LONG AND .5625 INCH WIDE. LOCATED AT STR 23R, BS 950.75 - BS 953.6875. INSTALLED REPAIR DOUBLER, TRIPLER, TEAR STRAP REPAIR PER BOEING SERVICE REQUEST MESSAGES 1-793858201-1 THRU -14, AND 8100-9, DATED 26 MARCH 2008. THIS INTERIM REPAIR DOES ENCOMPASS THE PREVIOUS REPAIR.

Part: SKIN — CRACKED (FUSELAGE) · airframe 60,202 hrs · 45,318 cycles

FUSELAGE SKIN CRACK AT STRINGER 24R STA 953 APPROXIMATELY 2 1/2" LONG. CRACK HAS BEEN TRIMMED OUT PER BOEING 737 SRM 53-30-03, FIG 48 TO 2,9375 INCH LONG AND .5625 INCH WIDE. LOCATED AT STR 24R, BS 953.125-BS 956.0625. INSTALLED REPAIR DOUBLER, TRIPLER, TEAR STRAP REPAIR PER BOEING SERVICE REQUEST MESSAGES 1-793858201-1 THRU -14, AND 8100-9, DATED 26 MARCH 2008. THIS INTERIM REPAIR DOES ENCOMPASS THE PREVIOUS REPAIR.

Part: CONTROL UNIT — MALFUNCTIONED (LE FLAPS) · airframe 56,669 hrs · 42,475 cycles

UPON FLAP RETRACTION AFTER TAKEOFF L/E FLAPS TRANSIT LIGHT FLICKERED, NR 1 L/E SLAT ANNUNCIATOR INDICATED FULL EXT, L/E FLAPS TRANSIT LIGHT EVENTUALLY REMAINED ILLUMINATED. REPLACED FLAP/SLAT POSITION SWITCH UNIT MODULE AND PERFORMED A TEST WITH L/E FLAP/SLAT BREAK OUT BOX -10M8546. OPS CHECKED OK PER MM27-88-000-101.

Part: SKIN — CRACKED (FUSELAGE) · airframe 56,166 hrs · 42,094 cycles

THE FUSELAGE SKIN WAS FOUND WITH A TYPICAL 3.5 INCH LONG CRACK ALONG THE BONDED DOUBLER MILL LINE AT STRINGER 18L NEAR FS 727B. THE CRACK WAS REMOVED WITH A CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 091605-14.

Part: PROXIMITY SWITCH — FAILED (LT MLG) · airframe 54,465 hrs · 40,784 cycles

ATB LANDING MAIN RED LIGHT ON WITH GEAR RETRACTED. FOUND LEFT MAIN GEAR UPLOCK PROX SWITCH BAD S-72. REMOVED SAME, INSTALLED NEW PROX SENSOR AND ADJUSTED. CHECK GOOD ON GEAR SWING.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 54,063 hrs · 40,440 cycles

WEB CORROSION REPAIR INSPECTION OF THE FS 1016 BULKHEAD WEB REVEALED CORROSION AT THE BL 0 STIFFENER NEAR THE BOTTOM OF BULKHEAD AT WL 190-200. AN OIL CAN CONDITION WAS DISCOVERED JUST OUTBOARD OF THE CORROSION AREA. BOTH DAMAGES WERE REMOVED WITH A WEB CUTOUT AND REPAIRED WITH ALUMINUM REPAIR DOUBLERS IAW BAC S/B 737-53A1075 AND IAW ER/A 385542-14AD, REV A.

Part: SWITCH — FAILED (NR 2 ENGINE) · airframe 53,070 hrs · 39,687 cycles

ON CLIMBOUT 20 MIN AFTER T/O NR 2 OIL FILTER BYPASS LIGHT ILLUMINATED. RETARDED THROTTLE, LIGHT ON, SHUTDOWN ENG AND RETURNED TO MCO. REMOVED AND INSP OIL FILTER/MCD. NO EVIDENCE OF CARBON OR DEBRIS, REPLACED FILTER AND OIL PRESS SWITCH. CLEARED OIL PRESS LINES. NO BLOCKAGE DETECTED. RAN ENG, LK CK GOOD. OPN/PARAMETERS CK GOOD. INLET AND EXHAUST CK NORMAL.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 52,524 hrs · 39,449 cycles

EMERGENCY LIGHTS WOULD NOT TURN OFF - REPLACED BATTERY PACK

Part: WINDOW — CRACKED (RT_NO.2) · airframe 50,473 hrs · 38,596 cycles

R2 WINDOW OUTER PANE CRACKED DURING FLT. DIVERTED TO MCO_C/ARPLD R2 WINDOW AND HEAT CONTROLLER PER M.M. OPN NORMAL

Part: WEB — CRACKED (CABIN) · airframe 50,284 hrs · 38,516 cycles

CRACKS WERE FOUND IN THE WEBS OF THE RBL AND LBL 24 FLOOR BEAMS AT F.S. 680. THE CRACKS WERE CUT OUT AND A DOUBLER INSTALLED PER ERA 398177-14AD. THE DAMAGE WAS FOUND AT HMV.

Part: FRAME — CRACKED (CABIN) · airframe 50,234 hrs · 38,494 cycles

CRACKS WERE FOUND IN THE FS 663.75 FRAME AT STR 3L, 2L, AND 2R. THE CRACKS WERE REMOVED AND REPAIRED PER SRM 53-10-4, FIG 14. DUE TO ED PROBLEMS HOLES WERE CUT IN THE FUSELAGE SKIN AT EACH LOCATION AND REPAIRED BY INSTALLING A EXTERNAL DOUBLER AND TRIPLER. THE DAMAGE WAS FOUND AT HMV.

Part: ATTACH FITTING — CORRODED (HORIZ STAB) · airframe 50,234 hrs · 38,494 cycles

THE REAR SPAR UPPER CLEVIS FITTING OF THE HORIZONTAL STAB WAS FOUND CORRODED. THE DAMAGE WAS REMOVED AND OVERSIZED BUSHINGS WERE INSTALLED. THE DAMAGE WAS FOUND AT HMV.

Part: ATTACH FITTING — CORRODED (HORIZ STAB) · airframe 50,234 hrs · 38,494 cycles

SEVERAL OF THE BORES AND FACES OF THE LT AND RT ATTACH LUGS ON THE HORIZONTAL STABILIZER WERE FOUND CORRODED. THE DAMAGE WAS CLEANED UP AND OVERSIZED BUSHINGS WERE INSTALLED. THE DAMAGE WAS FOUND AT HMV.

Part: ATTACH FITTING — CORRODED (HORIZ STAB) · airframe 50,234 hrs · 38,494 cycles

THE HORIZONTAL STABILIZER CLEVIS ATTACH LUGS WERE FOUND CORRODED ON THE FACES AND BORES. THE DAMAGE WAS CLEANED UP AND OVERSIZED BUSHINGS WERE INSTALLED. THE DAMAGE WAS FOUND AT HMV.

Part: FRAME — CRACKED (FUSELAGE) · airframe 50,234 hrs · 38,494 cycles

A CRACK WAS FOUND IN THE FS 807 FRAME AT THE STR 13L SHEAR TIE. THE CRACK WAS CUT OUT AND A DOUBLER INSTALLED. THE DAMAGE WAS FOUND AT HMV.

Part: FRAME — CRACKED (FUSELAGE) · airframe 50,234 hrs · 38,494 cycles

A CRACK WAS FOUND IN THE FS 787 FRAME AT THE STR 13L SHEAR TIE. THE DAMAGE WAS CUT OUT AND A DOUBLER INSTALLED. THE DAMAGE WAS FOUND AT HMV.

Part: BEAM — CRACKED (CABIN) · airframe 50,234 hrs · 38,494 cycles

A CRACK WAS FOUND IN THE RADIUS OF THE UPPER CAP OF THE FS 520 FLOOR BEAM. IT WAS LOCATED AT LBL 24.75. THE CRACK WASREPAIRED PER S/B 737-53-1120 AT HMV.

Part: FRAME — CORRODED (CABIN) · airframe 50,234 hrs · 38,494 cycles

CORROSION WAS FOUND ON THE FS 947 FRAME AT STR 17R. THE DAMAGE WAS REMOVED BY TRIMMING OFF THE INBOARD FLANGE. THE FRAME WAS REPAIRED PER B737-200 SRM 51-40-3, FIG. 1 AT HMV.

Part: SKIN — CRACKED (FS 951) · airframe 49,729 hrs · 38,269 cycles

FUSELAGE / SKIN / AFT GALLEY DOOR (R2) OPENING / UPPER HINGECUTOUT : CRACK REPAIR A TYPICAL CRACK WAS FOUND IN THE SKIN AT THE UPPER HINGE CUTOUT OF THE AFT GALLEY DOOR OPENING. THE CRACK WAS ROUTED OUT AND REPAIRED WITH AN EXTERNAL STEEL DOUBLER PER B737 SRM 53-30-3, FIG 21A AND ER/A 381595-14, REV A.

Part: SKIN — CRACKED (FUSELAGE) · airframe 48,394 hrs · 37,690 cycles

A SMALL CRACK WAS FOUND IN THE UPPER AFT CORNER OF THE L2 DOOR CUTOUT SKIN. THE CRACK WAS REMOVED WITH .25 INCH X .8 INCH TRIMOUT IN THE OUTER LAYER OF SKIN ONLY. THE TRIMOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 380477-14, REV A.

Part: STALL WARNING — MALFUNCTIONED (COCKPIT) · airframe 47,596 hrs · 37,340 cycles

PASSING THROUGH FL260 STICK SHAKER WENT OFF. ALL FLT LEVELS, AIRSPEED, MACH, FUEL FLOW AND RPM READINGS WERE NORMAL. DIVERTED TO MCO. REPLACED STALL WARNING MODULE. OPN TEST GOOD. A/C DIVERTED FROM TPA.

Part: SKIN — CRACKED (FUSELAGE) · airframe 45,681 hrs · 36,504 cycles

THE SKIN AROUND THE AFT GALLEY DOOR (R2) CUTOUT WAS FOUND WITH A TYPICAL CRACK IN THE LOWER DOOR HINGE CUTOUT. THE CRACK WAS REMOVED WITH A 1 INCH X 1 INCH CUT OUT THROUGH THE SKIN AND BONDED SURROUND DOUBLER. THE DAMAGE WAS REPAIRED WITH AN EXTERNAL STEEL DOUBLER INSTALLED PER B737-200 SRM 53-30-3FIG. 35 AND ER/A 377632-14, REV A.

Part: SKIN — CRACKED (BS 951)

A TYPICAL CRACK WAS FOUND IN THE SKIN AND BONDED DOUBLER OF THE LOWER HINGE CUTOUT OF THE AFT ENTRY DOOR (L2) CUTOUT. THE CRACK WAS ROUTED OUT WITH A .75 INCH CUTOUT. THE UNDERLYING BEARSTRAP WAS INSPECTED AND FOUND UNDAMAGED. THE SKIN ASSY WAS REPAIRED WITH AN EXTERNAL DOUBLER AND TRIPLER PER B737 SRM 53-30-3, FIG 36 AND ER/A 369231-14, REV A.

Part: BEAM — CRACK (CARGO DOOR)

AFT CARGO DOOR / NR 2 STOP BEAM / OUTER CHORD: AD 98-11-04, R1 CRACK FOUND IN TYPICAL POSITION ON NR 2 STOP BEAM OUTER CHORD AS ADDRESSED IN SUBJECT AD (I.E. LOCATED AT FWD END OF BEAM ADJACENT TO STOP FITTING). AUTHORIZED ANGLE REPAIR.

Part: STRINGER — CRACKED (BS 727)

THE STRINGER 18A WEB WAS FOUND WITH A CRACKED FASTENER HOLE AT FS 727 ON THE LT AND RT SIDES OF THE AIRCRAFT. THE CRACKS ARE TYPICAL OF THOSE NOTED IN BAC S/B 737-53-1066. THE CRACKS WERE REPAIRED WITH A NEW GUSSET CHANNEL SIMILAR TO THE S/B AND INSTALLED PER ER/A 368583-14.

Part: SKIN — CRACKED (BS 345)

FUSELAGE, SKIN ASSY, L1 DOOR CUTOUT, CRACK REPAIR. A CRACK WAS FOUND IN THE SKIN, DOUBLER, AND BEAR STRAP AT THE LOWER AFT CORNER OF THE L1 DOOR CUTOUT. THE CRACK IS TYPICAL OF BAC S/B 737-53-1083. THE CRACK WAS REPAIRED WITHIN INTERIM STRAP REPAIR PER THE S/B AND PER ER/A 368397-14.

Part: POWER SUPPLY — INOP (FWD GALLEY)

ON TAXI OUT, UNABLE TO EXTINGUISH EMERG FLOOR PATH LIGHTING SYS RT SIDE OF A/C. REPLACED AFT RT EMERGENCY LIGHT PWR PACK AND BATTERY IN FWD GALLEY CEILING. SYS OPERATION NORMAL.

Part: SENSOR — INOP (NR 1 LE FLAP)

NR 1 LEADING EDGE DEVICE INDICATED FULL EXTENDED AFTER FLAPSWERE PUT UP. REPLACED NR 1 LEADING EDGE FLAP DOWN SENSOR.

Part: VALVE — LEAKING (POTABLE WATER)

POTABLE WATER SCV VALVE LEAKING IN THE CLOSED POSITION WHEN A/C IS PRESSURIZED. SUSPECTED OF CAUSING ICE BALL THAT DAMAGED HORZ STAB. REPLACED THE VALVE AND L/E OF THE HORIZONTAL STAB.

Part: COALESCER — CONTAMINATED (CABIN)

DIVERSION DUE TO SMOKE IN CABIN. PERFORMED LT AND RT ENG AND APU BLD COMPRESSION CONT SYS TEST WITH OPERATIONAL LT PACK ONLY. CKS GOOD. REPLACED LT PACK COALESER BAG PER MM. PERFORMED VIS INSPECTION OF BOTH AC BAYS, ALL NORMAL.

Part: SKIN — CRACKED (R2 DOORWAY)

THE LOWER FORWARD CORNER OF THE R-2 DOOR CUTOUT WAS FOUND WITH A TYPICAL CRACK IN THE SKIN AND DOUBLER. THE BEAR STRAP WAS NOT CRACKED. THE DAMAGE WAS REPAIRED PER B737 SRM53-30-3, FIG 24 EXCEPT BLIND BOLTS WERE SUBSTITUTED ON A TIME-LIMITED BASIS. THE REPAIR WAS ACCOMPLISHED PER ER/A 365253-14, REV A.

Part: DOORWAY FRAME — CRACKED (BS 334)

THE R1 DOOR FRAME INTERCOSTAL AT STRG 8A WAS FOUND CRACKED IN THE TYPICAL MANNER SHOWN IN SB 737-53A1108, R5. REPAIRED IN ACCORDANCE WITH ERA 330874-14AD AND SB 737-53A1108 (REV 5) AND AD88-03-03.

Part: FLOORBEAM — CRACKED (BS 520)

THE FLOORBEAM AT BS 520 WAS FOUND CRACKED AT RBL 25. CRACKING FOUND IS TYPICAL OF THAT DESCRIBED IN SB 737-53-1120 (R1). REPAIR PER SB 737-53-1120 AUTHORIZED BY DELTA ER/A 330883-14.

Part: ANTI ICE DUCT — CRACKED (NR 1 ENGINE)

DURING CLIMB-OUT, NR 1 ENGINE OVERHEAT LIGHT ILLUMINATED. LIGHT EXTINGUISHED AS THROTTLE REDUCED. RETURNED TO MCO. FOUND NOSE ANTI-ICE DUCT CRACKED. REPLACED SAME. FOUND BLEED DUCT ON LEFT SIDE OF ENGINE LEAKING AT FLANGE. REPLACED SAME. LEAK CHECKS NORMAL.

Part: MANIFOLD — RUPTURED (NR 2 FUEL HEAT)

RIGHT ENGINE OVERHEAT LIGHT ON T/O. FOUND RT ENGINE FUEL HEAT MANIFOLD RUPTURED. REPLACED MANIFOLD.

Part: BULKHEAD WEB — FATIGUE (BS 178)

THE STATION 178 BULKHEAD WEB WAS FOUND CRACKED IN SEVERAL LOCATIONS. DAMAGE CUTOUT DIMENSIONS ARE: 1 BY 4 FOR RBL 5.7 AT WL 198 TO 201; 1 BY 4 FOR LBL 5.7 AT WL 198 TO 201; AND 2 BY 1 FOR RBL 1 AT WL 188. DIMENSIONS ARE I/B TO O/B VERTICALLY RESPECTIVELY. THE BULKHEAD WEB IS MANUFACTURED FROM .032 CLAD 2024-T3.

Part: DOOR FRAME — CRACKED (BS 794.3)

THE AFT CARGO DOOR OPENING FORWARD FRAME STA 794.3 WAS FOUND WITH A 1 INCH CRACK AT THE NR 5 STOP FITTING. THE FRAME IS MADE FROM A 0.071 7075-T6 CLAD MATERIAL. THIS ER/A WILL ALLOW THE USE OF THE SRM TYPICAL FORMED SECTION REPAIR ON A TIME LIMITED BASIS.

Part: LIGHT — INOPERATIVE (CABIN)

CABIN RT SIDE EMERGENCY LITE INOPERATIVE AT ROW 2D. REPLACED POWER SUPPLY. OPS CHECK OK FOR SERVICE.

Part: IGNITION WIRES — FAILED (COCKPIT)

WHEN STOWING STBY COMPASS INSTRUMENT ARCED ACCOMPANIED BY A TRACE OF SMOKE AND ELECTRICAL SMELL. FOUND WIRES IN IGNITION SWITCH FOR NR 1 ENGINE BURNED AND MAKING CONTACT WITH STANDBY COMPASS. REPAIRED ALL WIRES, OPS CHECK NORMAL.

Part: FUSE — BLOWN (CABIN)

R1 AND L1 DOORS LWR EMERGENCY LIGHTS EXIT IDENT LIGHTS INOP. REPLACED FUSE ON RACK M9221, OPS CHECKS GOOD.

Part: GEARBOX STUDS — PULLED LOOSE (NR 1 ENGINE)

LOW OIL QTY LIGHT ON - THEN LOW OIL PRESS LIGHT. ENGINE SHUT-DOWN. MTC SENT FROM ATL - REPLACED 2 STUDS FOUND PULLED LOOSE ON THE GEARBOX. HAD TO INSTALL HELICOIL.

Part: RIB — CRACKED (NR 3 LE SLAT)

NR 3 L/E SLAT SUPPORT RIB IS CRACKED 8 INCHES FROM I/B END. REPAIRED PER SRM 57-54-0.

Part: FLOORBEAM — CRACKED (BS 294.5)

THE STA 294.5 FLOORBEAM UPPER T-CAP WAS FOUND CRACKED AT RBL 52, UPON INSPECTION PER SI 3-61663-12AD. THE UPPER CAP IS MANUFACTURED FROM 10136-2401 (0.094 7075-T6511 EXTRUSION). ACCOMPLISHED REPAIRS PER DL ERA 302777-14AD.

Part: SKIN — TORN (SPOILER)

DUE TO THE FATIGUE FAILURE OF THE O/B ACTUATOR FITTING, THE FRONT SPAR AND THE UPPER SKIN OF THE SUBJECT SPOILER WERE TORN. IN ACCORDANCE WITH BACO S/B 737-57-1207, THE SKIN AND SPOILER WERE REPAIRED.

Part: ADI — INOP (LT COCKPIT)

CAPT ADI INOP WITH ALT FLAG, ROLL LIGHT ILLUMINATED. TEST SWITCH RESULTED IN INDICATOR SPINNING AT HIGH SPEED IN ROLL DIRECTION, AUX GYRO NO HELP. AIR TURNBACK TO ATL AT 1420. C/A REPLACED CAPT ADI, FUNCTIONS NORMAL.

Part: FLOOR BEAM — CRACKED (FS 663)

THE BL 0.07 FLOOR BEAM OF THE WING CENTER SECTION IS CRACKED AT STATION 663. THE UPPER CAP OF THE BEAM IS CRACKED ON THE RIGHT HAND FLANGE ONLY, STARTING FROM AN EXISTING FASTENER HOLE. NO CRACKS WERE FOUND ON THE WEB. THE PANEL ATTACH HOLE WAS ALSO FOUND CRACKED AFTER HFEC INSPECTION. THE AREAWILL BE TRIMMED OUT AND REPAIRED.