N14347

Part: STRINGER — CORRODED (BS 897) · airframe 55,982 hrs · 29,173 cycles

INSPECTION FOUND AFT CARGO COMPARTMENT STRINGER 21L CORRODED ON UPPER FLANGE AT STA 897. A STRINGER REPAIR WAS INSTALLED IAW SRM 53-00-03, FIGURE 201.

Part: WEB — CORRODED (FUSELAGE) · airframe 55,982 hrs · 29,173 cycles

INSPECTION FOUND WEB AT L-1 DOOR CORRODED FROM STA 312-350, LBL 62. THE WEB WAS REMOVED AND A NEW WEB WAS INSTALLED IAW SRM 53-10-15 AND 51-10-15.

Part: SKIN PANEL — CRACKED (FUSELAGE) · airframe 55,982 hrs · 29,173 cycles

INSPECTION FOUND A 2" CRACK IN BOTTOM SKIN PANEL BETWEEN KEEL BEAMS AT STA 685, S29L TO S29R. THE CRACK WAS STOP DRILLED AND A DOUBLER WAS INSTALLED IAW SRM 53-60-12, REPAIR NR 2.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 55,982 hrs · 29,173 cycles

INSPECTION FOUND RT I/B CABIN SEAT TRACK CORRODED AT STA 847, RBL 24. A REPAIR WAS INSTALLED IAW SRM 53-60-52.

Part: SKIN — DENTED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND FUSELAGE SKIN DENTED AT BS 400 BETWEEN S17L AND S18L. REPAIRED IAW ECRA 5331-01139.

Part: SKIN — CRACKED (NR 3 SLAT) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND 0.2 INCH CRACKS AT THREE FASTENERS IN NR 3 SLAT LOWER SKIN. A REPAIR DOUBLER WAS INSTALLED IAW SRM 57-43-01, FIGURE 206.

Part: SUPPORT FITTING — CRACKED (NR 2 PYLON) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND NR 2 ENGINE PYLON O/B MID SPAR FITTING PANEL AFT RETAINER (SUPPORT FITTING) CRACKED AT UPPER AREA, PYLON STA 279.5. THE SUPPORT FITTING WAS REMOVED AND REPLACED IAW SRM 51-40-02.

Part: SKIN — GOUGED (NR 3 MID FLAP) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND NR 3 MID FLAP OUTBOARD L/E SKIN GOUGED JUST FORWARD OF EXHAUST GATE. FILLER AND DOUBLER WERE INSTALLED IAW ECRA 5752-01144.

Part: STIFFENER — CORRODED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND AFT PRESSURE BULKHEAD LOWER WEB AND STIFFENER CORRODED JUST AFT OF FS 1016, S23L. REPAIRED IAW ECRA 5311-01186.

Part: ATTACH FITTING — CRACKED (NR 2 PYLON) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND A .25 INCH CRACK IN NR 2 PYLON PANEL 5842 FORWARD ATTACH RAIL. THE ATTACH RAIL WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: ATTACH ANGLE — CRACKED (T/E FLAP) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND A 1.2 INCH CRACK IN NR 2 FLAP TRACK FAIRING ATTACH ANGLE. AN ANGLE REPAIR WAS INSTALLED IAW SRM 51-70-13.

Part: SKIN — DENTED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND THE RT FUSELAGE SKIN DENTED AT STA 875 BELOW S19R AFT OF C-2 DOOR. A DOUBLER REPAIR WAS INSTALLED IAW SRM 53-00-01 FIGURE 210.

Part: ATTACH ANGLE — CORRODED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND ATTACH ANGLE FOR FLOOR PANEL AROUND GEAR DOWNLOCK VIEWER CORRODED AT AFT ATTACH ANGLE, BS 270, BL 0. A REPAIR WAS INSTALLED IAW ECRA 5321-01172.

Part: WEB — CRACKED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND A .25 INCH CRACK IN C-2 DOOR OPENING LOWER FORWARD SILL WEB AT STA 787. THE WEB WAS REMOVED AND REPLACED IAW SRM 51-40-02.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND AFT BAGGAGE BIN TIE DOWN RAIL CORRODED AT FASTENER HOLES FROM STA 787-847. THE TIE DOWN RAIL WAS REMOVED AND REPLACED IAW SRM 51-40-02 AND 53-00-53.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND ANGLE ATTACHED TO FORWARD WALL OF NOSE WHEEL WELL CORRODED AT STA 227, RBL 14. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND AFT CARGO FLOORBEAMS UNDER CROSS STRAP CORRODED AT STA 767 + 6, RBL 8, RBL 3, AND LBL 3. REPAIRS WERE INSTALLED IAW ECRA 5320-01603.

Part: SKIN — DENTED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND FUSELAGE SKIN DENTED AT BS 324 JUST BENEATH S20R. THE DENTED AREA WAS CUT OUT AND A DOUBLER WAS INSTALLED IAW SRM 53-00-01, FIGURE 202.

Part: HINGE — CRACKED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND A 1 INCH CRACK IN R-2 DOOR HINGE HOUSING AT LOWER SURFACE, STA 954, RBL 55, WL 230. THE HOUSING WAS REMOVED AND REPLACED IAW SRM 51-40-02.

Part: WEB — CORRODED (FUSLAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND AFT WEB RT SIDE ADJACENT TO RUBBER MEMBRANE AT APB, STA 1016, RBL 0 TO RBL 48, CORRODED. A NEW WEB WAS INSTALLED IAW SRM 51-40-02.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND A 4 INCH CRACK IN AFT BAGGAGE BIN INTERCOSTAL UNDER TRANSITION PANEL AT STA 928, RBL 26. THE INTERCOSTAL WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND FORWARD SIDE OF AFT PRESSURE BULKHEAD LEFT AND RIGHT OF CENTER STIFFENER (APB DOME WEB) CORRODED AT STA 1016, BL 0. A REPAIR DOUBLER WAS INSTALLED IAW BOEING DRAWING 65C28106.

Part: WEB — CRACKED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND A 2 INCH CRACK IN SHEAR WEB PANEL FORWARD OF STA 578, S17L. THE WEB WAS REMOVED AND A REPAIR WAS INSTALLED IAW SRM 51-70-13. THE WEB WAS REINSTALLED IAW SRM 51-41-02.

Part: STIFFENER — CORRODED (PRESS BULKHEAD) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND FORWARD SIDE LOWER AFT PRESSURE BULKHEAD CENTER CHANNEL STIFFENER CORRODED AT BS 1016-1025, BL 0. STIFFENERS AND SPLICES WERE INSTALLED IAW BOEING DRAWING 65C28106.

Part: WEB — CORRODED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND SHEAR WEB IN RT AFT LAV AREA CORRODED AT FS 1019, RBL 28. THE SHEAR WEB WAS REMOVED AND REPLACED IAW SRM 51-40-02.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND STRINGER 25L CORRODED BETWEEN STRINGER END FITTING FORWARD OF STA 1016. A REPAIR WAS INSTALLED IAW SRM 53-00-03, FIGURE 201, PAGE 206.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND STRINGER 8R CRACKED AT FIVE ADJACENT FASTENERS AT FRAME BS 380. THE CRACKS WERE .75 INCH LONG. A STRINGER PLATE WAS INSTALLED WITH LOCK FASTENERS IAW SRM 51-40-02.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND R-1 DOOR CUTOUT ZEE ANGLE CORRODED FROM STA 290-360. THE ZEE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-40-02.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND A 6 INCH CRACK IN INTERCOSTAL BETWEEN STA 344 AND 360, BL 0. THE INTERCOSTAL WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND STRINGER 26R CORRODED BETWEEN STA 1006-1016. REPAIRED IAW BOEING DRAWING 65-45776.

Part: WEB — CRACKED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND SHEAR WEB PANEL CRACKED IN TWO PLACES AT LT FUSELAGE FORWARD OF STA 639 AT S17L. THE WEB WAS REMOVED AND A NEW WEB WAS INSTALLED IAW SRM 51-40-02.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND A 4 INCH CRACK IN ANGLE ON TOP OF INTERCOSTAL BETWEEN STA 380 AND 400, BL 0. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 53-30-51.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND A 2 INCH CRACK IN AFT CABIN L-ANGLE AT TOP OF INTERCOSTAL WEB AT FASTENER HOLES (4 EACH), STA 927-947, BL 0, WL 209. A SHEAR WEB ANGLE WAS INSTALLED IAW SRM 51-40-02 AND BOEING DRAWING 69-36656.

Part: SUPPORT — CORRODED (THRESHOLD) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND L-1 DOOR THRESHOLD SUPPORTS CORRODED. INNER AND OUTER THRESHOLD SUPPORTS WERE INSTALLED IAW SRM 51-40-02.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND FORWARD ENTRY SEAT TRACK CORRODED FROM STA 270-294.5, RBL 40. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 51-40-02.

Part: SUPPORT — CORRODED (THRESHOLD) · airframe 49,642 hrs · 26,094 cycles

INSPECTION FOUND R-1 DOOR THRESHOLD SUPPORTS CORRODED AT STA 300-326. THE SUPPORTS WERE REPLACED IAW SRM 51-10-02.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 48,591 hrs · 25,504 cycles

INSPECTION FOUND FLOORBEAM FLANGE AT NUTPLATE HOLE CORRODED, FS 947, LBL 5. A REPAIR STRAP WAS INSTALLED SRM 53-00-51, PAGE 213.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 48,591 hrs · 25,504 cycles

INSPECTION FOUND FLOORBEAM NUT PLATE HOLE CORRODED AT FS 967, LBL 28. A REPAIR STRAP WAS INSTALLED IAW SRM 51-21-3.

Part: FRAME — CORRODED (FUSELAGE) · airframe 48,591 hrs · 25,504 cycles

INSPECTION FOUND CHORD CORRODED AROUND NUTPLATE HOLE AT FS 967, LBL 42. AN UPPER CHORD REPAIR WAS INSTALLED IAW SRM 53-00-51.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 48,591 hrs · 25,504 cycles

INSPECTION FOUND FLOORBEAM CORRODED AT BS 986.5, RT SIDE. A T-CAP WAS INSTALLED IAW ECRA 5310-03851.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 48,591 hrs · 25,504 cycles

INSPECTION FOUND FLOORBEAM CORRODED AT BS 986.5 LT SIDE, AFT OF WATER TANK. A T-CAP WAS INSTALLED IAW ECRA 5310-03851.

Part: SHEAR TIE — CORRODED (STA 986.5) · airframe 45,792 hrs · 23,895 cycles

AFT BILGE AREA CORROSION WHERE ANGLE BRACKETS MEET AFT FACE OF FRAME STATION 986.5 BETTWEEN 27L AND 27R BL0. REMOVED AND REPLACED SHEAR TIE ANGLE PER SRM 51-10-02.

Part: SKIN · airframe 45,793 hrs · 23,895 cycles

FUSELAGE SKIN STA 380-400 HAS 4"X2" DENT WITH OIL CANNING BETWEEN STR 17 & 18. INSTALLED DOUBLER IAW SRM 53-00-01.

Part: FLOORBEAM — CORRODED (BS 986.5)

INSPECTION FOUND FLOORBEAM CORRODED AT AFT LAV, STA 986.5. THE FLOORBEAM UPPER CHORD WAS REPLACED IAW ECRA 5310-03851.

Part: SENSOR — OUT OF ADJUST (LANDING GEAR)

THE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF FROM EWR. THE ABNORMAL CHECKLIST WAS COMPLETED AND THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE AIR SAFETY SENSOR OUT OF ADJUSTMENT. THE SENSOR WAS ADJUSTED IAW MM 32-09-01. AN EXTENSION AND RETRACTION OF THE LANDING GEAR WAS PERFORMED IAW MM 32-32-00 AND OPERATION AND INDICATIONS CHECKED GOOD.

Part: BLEED LINES — LOOSE (RIGHT)

CABIN PRESSURE WAS LOST WHILE EN ROUTE FROM IAH TO CZM. THE RIGHT PACK OUTPUT WENT TO ZERO. AN EMERGENCY DESCENT WAS PERFORMED AND THE O2 MASKS WERE DEPLOYED. THE AIRCRAFT LANDED AT CZM WITHOUT FURTHER EVENT. MAINTENANCE FOUND HIGH BLEED REGULATOR LINES LOOSE. THE LINES WERE REPOSITIONED AND TIGHTENED AND OPERATIONAL CHECKS WERE GOOD. IN ADDITION, THE O2 GENERATORS WERE REMOVED AND REPLACED. THE O2 MASKS WERE REPACKED AND LATCH SYSTEMS CHECKED IAW MM 35-22-11.

Part: SLAT — DAMAGED (NR 6 LE FLAP)

A CATERING TRUCK STRUCK THE RT OUTBOARD NR 6 SLAT. A REPAIR WAS COMPLETED IAW SRM 57-43-01.

Part: FITTING — GOUGED (LT HORIZ STAB)

INSPECTION FOUND THE LT HORIZONTAL STABILIZER AFT LOWER ATTACH FITTING GOUGED IN THREE AREAS ON LOWER SIDE. THE GOUGES WERE BURNISHED, SHOT PEENED, TREATED, AND PRIMED IAW ECRA 5550-01035.

Part: FITTING — GOUGED (RT HORIZ STAB)

INSPECTION FOUND RT HORIZONTAL STABILIZER AFT LOWER FITTING OF AFT SPAR GOUGED. THE GOUGE WAS BURNISHED, AND THE AREA WAS SHOT PEENED, TREATED, AND PRIMED IAW ECRA 5550-01035.

Part: HYD PUMP — LEAKING (NR 1 ENG)

FLT NR 784 - IAH - THE 'A HYDRAULIC SYSTEM QUANTITY DROPPED TO ONE FOURTH AFTER DEPARTING ATL. THE NR 1 ENGINE LOW PRESSURE LIGHT FLICKERED ON AND OFF WHILE AT CRUISE. CHECKLIST PROCEDURES WERE COMPLIED WITH AND THE 'A' SYSTEM ENGINE PUMP WAS TURNED OFF. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 1 ENGINE DRIVEN HYDRAULIC PUMP LEAKING. THE PUMP WAS REMOVED AND REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED AND NO LEAKS WERE NOTED DURING ENGINE RUN. (M)

Part: HYD LINE — RUPTURED (B-HYD SYSTEM)

FLT NR 778 - IAH - THE 'B' SYSTEM HYDRAULIC QUANTITY DROPPED TO ZERO WHILE IN CRUISE FLIGHT. ALTERNATE FLAPS WERE USED AND THE GROUND PROXIMITY FLAP INHIBIT SWITCH WAS ACTIVATED IAW THE AIRCRAFT FLIGHT MANUAL. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE HYDRAULIC FLEX LINE TO THE HYDRAULIC MODULE RUPTURED. THE HYDRAULIC FLEX LINE WAS REMOVED AND REPLACED. LEAK CHECK WAS GOOD. (M)

Part: HINGE CUT OUT — CRACKED (GALLEY DOOR)

IAH - INSPECTION FOUND A .1250 INCH CRACK IN UPPER CORNER OF FORWARD GALLEY DOOR HINGE LOWER CUT OUT. THE CUT OUT WAS REPAIRED IAW EA 5210-01055. (X)

Part: HINGE CUT OUT — CRACKED (ENTRY DOOR)

IAH - INSPECTION FOUND A .25 INCH CRACK IN LOWER CORNER OF FORWARD ENTRY DOOR HINGE LOWER CUT OUT. THE CUT OUT WAS REPAIRED IAW EA 5210-01055. (X)