N70330

Part: SKIN — CRACKED (RT WING LE) · airframe 62,277 hrs · 32,200 cycles

INSPECTION FOUND A .75 INCH CRACK IN RIGHT WING LEADING EDGE SKIN AT NR 5 SLAT ACTUATOR. THE SKIN WAS REPAIRED IAW SRM 57-41-01, PAGE 202, FIGURE 201.

Part: BRACKET — CRACKED (BS 500A) · airframe 62,277 hrs · 32,200 cycles

INSPECTION FOUND A 1 INCH CRACK IN FORWARD BAGGAGE BIN STA 500A VHF ANTENNA MOUNTING BRACKET. A NEW ANTENNA MOUNTING BRACKET WAS INSTALLED IAW SRM 51-40-02.

Part: STRINGER — CORRODED (BS 540 S26L) · airframe 62,277 hrs · 32,200 cycles

INSPECTION FOUND STRINGER 26L CORRODED AT STA 540. A REPAIR WAS INSTALLED IAW SRM 53-00-03.

Part: STRINGER CLIP — CORRODED (BS 540 S26L) · airframe 62,277 hrs · 32,200 cycles

INSPECTION FOUND STRINGER TIE IN FORWARD BAGGAGE BIN CORRODED AT STA 540, S26L. THE STRINGER TIE WAS REPAIRED IAW SRM 51-40-02 AND GMM 10-900-01.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 62,277 hrs · 32,200 cycles

INSPECTION FOUND A .5 INCH CRACK AT LOWER STOP PAD HOLES OF FORWARD BAG BIN DOOR CUTOUT AFT FRAME. THE FRAME WAS REMOVED AND REPLACED IAW SRM 51-40-02 AND BOEING DRAWING 65-20723.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,277 hrs · 32,200 cycles

INSPECTION FOUND A .25 INCH CRACK IN FORWARD BAGGAGE BIN FRAME WEB AT STA 500, BL 0. THE CRACKED AREA WAS REMOVED AND A REPAIR DOUBLER AND FILLER WERE INSTALLED IAW SRM 51-70-11.

Part: SKIN — CRACKED (FUSELAGE) · airframe 62,277 hrs · 32,200 cycles

INSPECTION FOUND A 1.5 INCH CRACK IN RIGHT FUSELAGE SKIN LAP AT STA 880, S25R. THE SKIN WAS REPAIRED IAW SRM 53-00-01, REPAIR 31.

Part: SKIN — CRACKED (FUSELAGE) · airframe 62,277 hrs · 32,200 cycles

INSPECTION FOUND A 1 INCH CRACK IN LEFT FUSELAGE SKIN AT STA 727E, S22L. THE SKIN WAS REPAIRED IAW SRM 53-00-01, FIGURE 201.

Part: SKIN — CRACKED (FUSELAGE) · airframe 59,447 hrs · 30,911 cycles

FUSELAGE CRACK R/S AFT OF WING, 12 INCHES AFT OF EMERGENCY LIGHT. REPAIRED IAW SRM 53-00-01, REPAIR 31, FIG 201.

Part: SKIN — CRACKED (FUSELAGE) · airframe 59,447 hrs · 30,911 cycles

FUSELAGE CRACK RT SIDE AFT OF WING, 12 INCHES AFT OF EMERGENCY LIGHT. REPAIRED IAW SRM 53-00-01, REPAIR 31, FIG 201.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 58,569 hrs · 30,508 cycles

THE EMERGENCY EXIT LIGHTS AT AFT DOORS WERE FOUND INOPERATIVE. THE BATTERY PACK WAS REPLACED.

Part: STIFFENER — CRACKED (BS 663.75) · airframe 57,459 hrs · 29,970 cycles

INSPECTION FOUND A TWO INCH CRACK IN WING CENTER SECTION VERTICAL STIFFENER AT STA 663.75, RBL 6.15. THE STIFFENER WAS REPAIRED IAW EA 5714-01002. A DIP WAS ISSUED TO ACCOMPLISH A VISUAL INSPECTION OF THE STIFFENER FOR CRACKS EVERY 4500 FLIGHT CYCLES AND TO REPLACE BOTH STIFFENERS IAW EA 5714-01002 OP 02-05 PRIOR TO THE ACCUMULATION OF 15,000 FLIGHT CYCLES FROM REPAIR INSTALLATION.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 55,784 hrs · 29,162 cycles

MAINTENANCE FOUND A CRACK AT LIGHTENING HOLE IN THE LOWER INNER SKIN OF THE FORWARD CARGO DOOR WHILE THE DOOR WAS IN SHOP FOR MAINTENANCE. THE DOOR HAD BEEN REMOVED PREVIOUSLY AT HOU DURING A 4C MAINTENANCE CHECK IN MAY OF 2005. THE DOOR WAS REPAIRED IAW ECRA 5232-01069.

Part: FRAME — CRACKED (FUSELAGE) · airframe 55,784 hrs · 29,162 cycles

MAIN CABIN STA 616L FRAME INNER CHORD CRACKED. INSTALLED FRAME PER ECRA 5311-01158.

Part: FLOORBEAM — CORRODED (FUSLEAGE) · airframe 55,784 hrs · 29,162 cycles

CABIN FLOORBEAM CORRODED AT STA 328, LBL 29. INSTALLED NEW ANGLE PER SRM 53-10-51.

Part: FLOORBEAM — CORRODED (FUSLEAGE) · airframe 55,784 hrs · 29,162 cycles

CABIN FLOORBEAM CORRODED AT STA 328, LBL 29. INSTALLED NEW ANGLE PER SRM 53-10-51.

Part: SKIN — CRACKED (HORIZ STAB) · airframe 51,868 hrs · 27,055 cycles

MAINTENANCE FOUND A SMALL CRACK IN THE LT HORIZONTAL STABILIZER LOWER SKIN JUST FORWARD OF THE REAR SPAR FORWARD FLANGE, STAB STA 152. AN INTERIM REPAIR WAS PERFORMED IAW ECRA 5510-01692. A DIP WAS ISSUED TO PERFORM A DETAILED VISUAL INSPECTION OF THE INTERIM REPAIR AT INTERVALS NOT TO EXCEED 3,000 FLIGHT HOURS AND TO PERFORM A PERMANENT REPAIR PRIOR TO THE ACCUMULATION OF 15,000 FLIGHT HOURS.

Part: PANEL — DELAMINATED (RT WING) · airframe 51,868 hrs · 27,055 cycles

INSPECTION FOUND RT WING PANEL UPPER SURFACE DELAMINATED O/B OF MLG. THE PANEL WAS REPAIRED IAW BOEING DRAWING 65-50820-188.

Part: PANEL — GOUGED (RUDDER) · airframe 51,868 hrs · 27,055 cycles

INSPECTION FOUND RUDDER HINGE COVER PANELS NR 9559 AND 9555 GOUGED. NEW PANELS WERE INSTALLED IAW SRM 51-10-02 AND BOEING DRAWING 65C25973.

Part: SKIN — CRACKED (L/E SLAT) · airframe 51,868 hrs · 27,055 cycles

INSPECTION FOUND NR 1 SLAT LOWER L/E SKIN CRACKED AT O/B TRACK. THERE WERE FOUR CRACKS MEASURING FROM .125 TO .25 INCH IN LENGTH. A REPAIR DOUBLER WAS INSTALLED IAW SRM 57-43-01.

Part: CHANNEL — CORRODED (FUSELAGE) · airframe 51,868 hrs · 27,055 cycles

INSPECTION FOUND LT CHANNEL CORRODED ON FORWARD SIDE OF AFT PRESSURE BULKHEAD AT LOWER END, STA 1016, BL 0. THE CHANNEL WAS REPAIRED IAW EA 5310-04045 AND DRAWING 65C28106-1.

Part: SKIN — CRACKED (RT WING) · airframe 51,868 hrs · 27,055 cycles

INSPECTION FOUND A 1 INCH CRACK IN RT WING LEADING EDGE SKIN AT NR 4 SLAT ACTUATOR. A REPAIR DOUBLER WAS INSTALLED IAW SRM 57-41-01.

Part: SKIN — CRACKED (NR 1 PYLON) · airframe 51,868 hrs · 27,055 cycles

INSPECTION FOUND A 0.40 INCH CRACK IN PYLON CUTOUT FOR PANEL NR 5727, NR 1 ENGINE. THE CRACK WAS STOP DRILLED AND A REPAIR WAS INSTALLED IAW ECRA 5430-01230.

Part: ATTACH ANGLE — CRACKED (HORIZ STAB) · airframe 51,868 hrs · 27,055 cycles

INSPECTION FOUND A 6 INCH CRACK IN ATTACH ANGLE ON HORIZONTAL STABILIZER CENTER SECTION AT UPPER BEAM. THE ATTACH ANGLE WAS REMOVED AND REPLACED IAW SRM 51-40-02.

Part: FLOOR PANEL — CRACKED (FUSELAGE) · airframe 51,868 hrs · 27,055 cycles

INSPECTION FOUND A 4 INCH CRACK IN PILOT'S LT SIDE FLOOR PANEL. THE FLOOR PANEL WAS REMOVED AND A NEW PANEL WAS INSTALLED IAW SRM 51-10-02.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 51,868 hrs · 27,055 cycles

INSPECTION FOUND A .5000 INCH CRACK IN CABIN FLOOR SUPPORT BETWEEN BS 380-400, BL 0. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-40-02.

Part: SKIN — NICKED (STA 235.8) · airframe 50,834 hrs · 26,476 cycles

INSPECTION FOUND A NICK IN L/H FUSELAGE SKIN AT STA 235.8, 17.7 INCHES BELOW WL 207.5. A REPAIR DOUBLER AND FILLER WERE INSTALLED IAW ECRA 5330-03218.

Part: KEELBEAM — CRACKED (FUSELAGE) · airframe 46,516 hrs · 24,202 cycles

INSPECTION FOUND A 0.045 INCH CRACK AT HOLE OF KEEL BEAM RT LOWER CHORD, STA 682, RBL 8 (WHEEL WELL AREA). THE CRACKED AREA WAS REMOVED, A FREEZE PLUG AND REPAIR STRAP WAS INSTALLED IAW ECRA 5310-04144.

Part: WEB — CRACKED (CARGO DOOR) · airframe 46,516 hrs · 24,202 cycles

INSPECTION FOUND A 0.3 INCH CRACK IN C-2 DOOR AT LIGHTENING HOLE LOCATED AT ACCESS TO SPRING SUPPORT FITTING. THE CRACKED AREA WAS TRIMMED AND DRESSED UP AND A DOUBLER WEB REPAIR WAS INSTALLED IAW SRM 51-70-13.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 46,516 hrs · 24,202 cycles

INSPECTION FOUND A SMALL CREASE IN FUSELAGE SKIN AT STA 1042, S13L. A DOUBLER WAS INSTALLED IAW SRM 53-00-01, FIGURE 202 AND 51-70.

Part: SKIN — CRACKED (FUSELAGE) · airframe 46,516 hrs · 24,202 cycles

INSPECTION FOUND A 2 INCH CRACK IN FUSELAGE SKIN AND INTERIOR SUPPORT FOR NR 3 VHF ANTENNA BETWEEN STA 727D AND 727E, BL 0. REPAIRED IAW SRM 53-00-01.

Part: SKIN — DENTED (FUSELAGE) · airframe 46,516 hrs · 24,202 cycles

INSPECTION FOUND FUSELAGE SKIN DENTED AT STA 1008, S16L. THE DENTED AREA WAS CUT OUT AND A DOUBLER WAS INSTALLED IAW SRM 53-00-01, FIGURE 202.

Part: SPAR — CRACKED (RT WING) · airframe 46,516 hrs · 24,202 cycles

INSPECTION FOUND A 0.1 INCH CRACK IN RT REAR SPAR UPPER CHORD AT RT MLG BEAM O/B END AFT SPAR FITTING ATTACH AREA. THE CRACK WAS REPAIRED IAW ECRA 5743-01033. A DIP WAS ISSUED TO REINSPECT THE AREA AT 3,000 FLIGHT CYCLE INTERVALS.

Part: STRINGER — GOUGED (FUSELAGE) · airframe 46,516 hrs · 24,202 cycles

INSPECTION FOUND STRINGER 14R GOUGED AT STA 600. A NEW STRINGER SECTION WAS INSTALLED IAW SRM 53-00-03, PAGE 201.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 46,516 hrs · 24,202 cycles

INSPECTION FOUND LEFT O/B SEAT TRACK CORRODED AT STA 887-947.5. A SEAT TRACK REPAIR WAS INSTALLED IAW SRM 53-00-52, FIGURE 204.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 46,516 hrs · 24,202 cycles

INSPECTION FOUND R-1 DOOR ENTRYWAY Z-ANGLE CORRODED. THE Z-ANGLE WAS REMOVED AND REPLACED IAW SRM 51-40-2.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 46,516 hrs · 24,202 cycles

INSPECTION FOUND FLOORBEAM CORRODED AROUND FASTENER HOLES AT STA 312, LBL 12-RBL 12. THE MAJORITY OF CORROSION WAS BURNISHED OUT. A REPAIR STRAP WAS INSTALLED IAW SRM 53-00-1 AT ONE LOCATION FOUND OUT OF LIMITS.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 45,916 hrs · 23,899 cycles

INSPECTION FOUND TWO CRACKS ON FLOOR STRUCTURE WEB AT LT AND RT W/L 195, ONE CRACK ON CENTER WEB AT W/L 200, LBL 5.7 AND ONE CRACK ON CENTER WEB AT W/L 201, RBL 5.7 DURING 737 FUS-BS 178 BULKHEAD INSPECTION. THE CRACKS WERE .5 INCH IN LENGTH. REPAIRS WERE ACCOMPLISHED IAW EA 5310-1-0037.

Part: SKIN — CRACKED (FUSELAGE) · airframe 45,916 hrs · 23,899 cycles

INSPECTION FOUND A 1 INCH CRACK IN AFT SKIN CUTOUT FOR THE E&E COMPARTMENT COOLING EXHAUST. A REPAIR DOUBLER WAS INSTALLED IAW ECRA 5330-02894.

Part: SKIN — CRACKED (NR 2 PYLON)

INSPECTION FOUND A .5 INCH CRACK IN NR 2 ENGINE PYLON SKIN AT PANEL NR 5824 AND A .5 INCH CRACK WAS FOUND IN PANEL NR 5828. REPAIRS WERE INSTALLED IAW ECRA 5430-01230.

Part: FLOORBEAM — CORRODED (BS 986.5)

INSPECTION FOUND CORROSION ON TOP OF FLOORBEAM AT STA 986.5. THE CORRODED AREA WAS CUT OUT AND A T-SECTION WAS INSTALLED IAW ECRA 5310-03450.

Part: ANGLE — CRACKED (TE FLAP FAIRING)

INSPECTION FOUND A .75 INCH CRACK IN NR 3 FLAP FAIRING WING TRAILING EDGE ATTACH ANGLE. THE ANGLE WAS REPLACED IAW SRM 51-10-02.

Part: SUPPORT — CORRODED (BS 950)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT BS 950, LBL 11. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: STRAP — CORRODED (BS 1006-1016)

INSPECTION FOUND LT AFT LAV STRAP CORRODED AT BS 1006 TO 1016, LBL 3. A NEW STRAP WAS FABRICATED AND INSTALLED IAW SRM 51-10-2.

Part: FLOORBEAM — CORRODED (BS 344)

INSPECTION FOUND FLOORBEAM CORRODED AT STA 344 LBL 31.6 TO L-1 DOOR AND RBL 30 TO LBL 10. THE CORRODED AREAS WERE REMOVED, REPAIRS WERE INSTALLED IAW SRM 53-10-51 AND ECRA 5310-03480.

Part: SUPPORT — CORRODED (BS 294.5-312)

INSPECTION FOUND FLOOR SUPPORTS CORRODED BETWEEN STA 294.5 AND 312, RBL 15 AND RBL 30. THE FLOOR SUPPORTS WERE REMOVED AND REPLACED IAW ECRA 5310-03477 AND SRM 51-10-02.

Part: SUPPORT — CORRODED (BS 2299)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 299, RBL 20. A REPAIR WAS INSTALLED IAW ECRA 5310-03477.

Part: FLOORBEAM — CORRODED (BS 294.5)

INSPECTION FOUND FLOORBEAM CORRODED AT STA 294.5, RBL 0. A NEW FLOORBEAM SECTION WAS INSTALLED IAW SRM 53-10-51.

Part: INTERCOSTAL — CORRODED (BS 947-967)

INSPECTION FOUND FLOORBEAM INTERCOSTAL CORRODED AT BS 947 TO 967, RBL 12. THE INTERCOSTAL WAS REPLACED IAW ECRA 5310-03477.

Part: SUPPORT — CORRODED (BS 986-990)

INSPECTION FOUND RT AFT LAV FLOOR SUPPORT CORRODED AT BS 986 TO 990, RBL 10. THE FLOOR SUPPORT WAS REPAIRED IAW SRM 51-10-00.

Part: CHANNEL — CORRODED (BS 990)

INSPECTION FOUND RT AFT LAV AND LT AFT LAV U-CHANNELS CORRODED AT BS 990. THE CHANNELS WERE REMOVED AND REPLACED IAW SRM 51-10-00 AND 51-10-2.

Part: INTERCOSTAL — CORRODED (BS 967-986)

INSPECTION FOUND FLOORBEAM INTERCOSTAL CORRODED AT BS 967 TO 986, RBL 12. A REPAIR WAS PERFORMED IAW ECRA 5310-03477.

Part: SUPPORT — CORRODED (BS 950)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT BS 950 FROM RBL 12 TO RBL 40. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW ECRA 5310-03477.

Part: COUPLER — INOPERATIVE (E/E COMPT)

A/C YAWED LT ON CLIMBOUT. UNCOMMANDED YAW OR ROLL CHECKLIST WAS RUN. AUTOPILOT WAS TURNED BACK ON AND NO MORE INPUTS NOTED WITH YAW DAMPER SWITCH OFF. A/C RETURNED IAH. YAW DAMP COUPLER REPLACED AND TESTED PER MM 22-12-31, PAGES 501-505. ALL TEST STEPS GOOD. A RUDDER PCU DUAL SERVO SLIDE CHK PERFORMED IAW ECRA 2721-01012, ALL CHKS OK. AUTOPILOT ACCY UNIT WAS R/R'D IAW ECRA 2720-01162. TEARDOWN OF YAW DAMP COUPLER REVEALED RATE GYRO AT FAULT. VENDOR TEARDOWN OF AUTOPILOT ACCY UNIT REVEALED FAILURE OF DIODES CR1-CR4.

Part: STRUT — LEAKING (NLG)

FLT NR 0295 - IAH - THE LANDING GEAR LEVER WOULD NOT RAISE BEYOND THE OFF POSITION AFTER TAKEOFF FROM ORD. THE LOCK OVERRIDE WAS USED TO RETRACT THE GEAR. THE FLIGHT WAS CONTINUED TO IAH WHERE IT LANDED WITHOUT INCIDENT. THE CONTROL LEVER LOCK SYSTEM WAS TROUBLESHOT PER MM 32-31-21 AND NO FAULTS WERE NOTED. MAINTENANCE FOUND THE NLG STRUT LEAKING. THE NLG STRUT WAS REPACKED IAW MM 32-21-11 AND SERVICED PER MM 12-15-41. A DIP WAS ISSUED TO CHECK STRUT PRESSURE AND X-DIMENSION AFTER 4, BUT PRIOR TO 20 LANDINGS. (M)

Part: UPLOCK ACTUATOR — INOPERATIVE (RT MLG)

FLT NR 1525 - CLE - THE RIGHT MLG RED LIGHT REMAINED ILLUMINATED AFTER TAKEOFF WITH THE GEAR HANDLE IN THE UP POSITION. WHEN HANDLE WAS SELECTED TO OFF THE RED LIGHT REMAINED ON AND THE RIGHT GEAR GREEN LIGHT CAME ON AFTER A FEW SECONDS. THE GEAR HANDLE WAS CYCLED UP AND THE GREEN LIGHT WENT OUT AND THE GEAR COULD BE FELT COMING UP. THE GEAR WAS CYCLED DOWN WITH SAFE INDICATIONS AND THE AIRCRAFT WAS RETURNED TO CLE WHERE IT LANDED WITHOUT INCIDENT. THE RIGHT MLG UPLOCK ACTUATOR WAS REMOVED AND REPLACED. IN ADDITION, THE RIGHT MLG UPLOCK SENSOR WAS ALSO REPLACED. GEAR OPERATION AND INDICATIONS CHECKED GOOD. (M)

Part: TOGGLES — WORN (RT TE FOREFLAP)

CLE - INSPECTION FOUND THE RIGHT INBOARD FOREFLAP GOUGED CAUSED BY THE FOREFLAP TOGGLE WHICH HAD WORN BEARINGS AND BUSHINGS. THE RIGHT INBOARD TRAILING EDGE FOREFLAP AND TOGGLE WERE REMOVED AND REPLACED IAW MM 27-51-07. (M)

Part: SKIN — GOUGED (LT HORIZ STAB)

FLT NR 0225 - FLL - ON OVERNIGHT INSPECTION, FOUND 5 INCH .125 INCH DEEP GOUGE WITH SMALL HOLE ON THE MOST INBOARD LEFT HORIZ STABILIZER, REQUIRED PER ECRA 55-10-01299 AND SETUP REPETIVE INSPECTION. (W)