N14209

Part: SKIN — DENTED (BS 178)

INSPECTION FOUND FUSELAGE SKIN DENTED AT UPPER EDGE OF BULKHEAD STA 178. THE DENTED AREA WAS REMOVED, A REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-10-6.

Part: SKIN — LIGHTNING STRIKE (FUSELAGE)

INSPECTION FOUND A LIGHTNING BURN AT FASTENER HEAD FOURTEEN INCHES AFT OF R-1 DOOR, STRINGER 9L. THE DAMAGED AREA WAS CUT OUT, A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3.

Part: SKIN — CRACK (BS 312)

INSPECTION FOUND A .0937 INCH CRACK AND CORROSION IN FUSELAGE SKIN AT STA 312, STRINGER 26L. THE CORRODED AREA WAS CUT OUT, A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3.

Part: SKIN — CRACKED (WS 219.67)

INSPECTION FOUND A .125 INCH CRACK IN LT WING LEADING EDGE SKIN AT LE STA 219.67. THE CRACKED AREA WAS CUT OUT, A DOUBLER WAS FABRICATED AND INSTALLED IAW ECRA 5720-01569 AND 5720-01570.

Part: BRACKET — CRACKED (R1 DOOR)

INSPECTION FOUND A 1 INCH CRACK AT UPPER ATTACH BRACKET OF R-1 DOOR WEB. THE BRACKET WAS REMOVED AND A NEW BRACKET WAS FABRICATED AND INSTALLED IAW SRM 51-40-3.

Part: CLIP — CRACKED (BS 300)

INSPECTION FOUND A 1 INCH CRACK IN FUSELAGE CLIP TIE AT STA 300, STRINGER 29L. THE CLIP WAS REMOVED, A NEW CLIP WAS FABRICATED AND INSTALLED IAW SRM 51-10-1.

Part: STRINGER — CRACKED (BS 727)

INSPECTION FOUND A 1 INCH CRACK AT FORWARD FASTENER HOLE OF STRINGER 23L AND FAIL SAFE CHORD WAS BULGED AT BS 727. A STRINGER CLIP WAS FABRICATED AND INSTALLED IAW SRM 51-30-2.

Part: HINGE — CRACKED (NR 3 SPOILER)

INSPECTION FOUND A 1.5 INCH CRACK IN LT WING NR 3 SPOILER INBOARD HINGE. THE HINGE WAS REMOVED, A NEW HINGE WAS FABRICATED AND INSTALLED IAW SRM 51-30-2.

Part: LIGHT — INOPERATIVE (LT OVERWING)

GSO - INSPECTION FOUND LT OVERWING EMERGENCY LIGHT INOPERATIVE. THE LT OVERWING EMERGENCY LIGHT ASSY REMOVED AND REPLACED. (X)

Part: ANGLE — CORRODED (LT SLIDING WNDW)

GSO - INSPECTION FOUND SUPPORT ANGLE CORRODED AT LT SLIDING WINDOW, STA 248.7. THE CORRODED SECTION OF ANGLE WAS CUT OUT IAW SRM 51-40-4. REPAIR ANGLES WERE FABRICATED AND INSTALLED IAW SRM 51-40-4, AND SRM 51-30-2. (X)

Part: TAB HINGE FTG — CRACKED (NR 3 AILERON)

GSO - INSPECTION FOUND LT WING NR 3 AILERON HINGE FITTING CRACKED AT TAB ATTACH POINT. THE CRACK LENGTH WAS NOT IDENTIFIED. THE HINGE ASSY WAS REMOVED AND REPLACED IAW SRM 51-30-2. (X)

Part: SKIN — BUCKLED (BS 767-804)

GSO - INSPECTION FOUND FUSELAGE SKIN LAP BUCKLED AND A .25 INCH CRACK IN STR 20L, STA 767 TO STA 804. THE EFFECTED SECTION OF SKIN AND STRINGER WERE REMOVED. A SKIN AND STRINGER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3, FIGURE 13, SRM 53-10-3, FIGURE 1, AND SRM 51-30-2. (X)

Part: SLAT — DELAMINATED (NR 5 POSITION)

GSO - INSPECTION FOUND THE OUTBOARD END OF NR 5 SLAT TOP SURFACE DELAMINATED IN AN AREA APPROXIMATELY 10 INCHES SQUARE. THE DELAMINATED SKIN AND CORE WERE REMOVED. THE AREA WAS REPAIRED BY REPLACING CORE AND APPLYING WET FIBERGLASS OVERLAYS IAW SRM 51-40-6. (X)

Part: SKIN — DENTED (CARGO DOOR)

GSO - THE FORWARD LOWER CORNER OF FORWARD CARGO DOOR SKIN FOUND DENTED AND SCRATCHED. THE DAMAGED SKIN REMOVED OVER AN AREA OF APPROXIMATELY 6 INCHES IN DIAMETER IAW SRM 52-00-3, FIGURE 3. REPAIR PARTS WERE FABRICATED AND INSTALLED IAW SRM 52-00-3, FIGURE 3, SRM 51-10-2, AND SRM 51-30-2. (X)

Part: SPOILER — BULGED (NR 3 POSITION)

GSO - INSPECTION FOUND THE NR 3 SPOILER UPPER SURFACE BULGED. THE SPOILER SKIN WAS RETURNED TO ORIGINAL CONTOUR BY FORMING IAW SRM 51-40-1. (X)

Part: SKIN — CRACKED (R-2 DOORWAY)

GSO - INSPECTION FOUND A 1 INCH CRACK IN SKIN AT FORWARD LOWER CORNER OF R-2 DOORWAY CUT-OUT. THE CRACK WAS CUT OUT. A DOUBLER, TRIPLER, AND FILLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3. (X)

Part: SKIN — CORRODED (E/E DOOR CUTOUT)

GSO - INSPECTION FOUND SKIN AND CHORD CORROSION AT FORWARD RT CORNER OF E AND E BAY DOORWAY CUT-OUT. THE CORRODED SECTION OF SKIN AND CHORD WERE REMOVED IAW SRM 51-30-2 AND SRM 53-30-3. NEW SKIN AND TEE SECTIONS WERE FABRICATED AND INSTALLED IAW SRM 53-30-3 AND ECRA 53-10-01233. (X)

Part: DOOR FRAME — CRACKED (R2 DOORWAY)

GSO - INSPECTION FOUND A 1.25 INCH CRACK IN UPPER SECTION OF FORWARD R-2 DOORWAY FRAME AT STR 10R. THE FRAME SEGMENT WAS REMOVED AND REPLACED IAW SRM 51-30-2 AND BOEING DRAWING 65-46561. (X)

Part: WEB — CRACKED (FWD TORQUE BOX)

GSO - INSPECTION FOUND A 1 INCH CRACK IN WEB SECTION AT FORWARD R-2 TORQUE BOX UPPER HINGE ARM. THE CRACK WAS CUT OUT IAW SRM 51-40-2. A NEW WEB WAS FABRICATED AND INSTALLED IAW SRM 51-40-2 AND BOEING DRAWING 65-46561. (X)

Part: SKIN — GOUGED (LT TE FOREFLAP)

GSO - INSPECTION FOUND A GOUGE APPROXIMATELY 10 INCHES SQUARE IN TOP SURFACE OF LT WING INBOARD FOREFLAP. REMOVED GOUGED AREA AND POTTED CORE. REPAIRED WITH FIBERGLASS OVERLAYS IAW SRM 51-40-9. (X)

Part: SKIN — DELAMINATED (NR 2 SPOILER)

GSO - INSPECTION FOUND NR 2 SPOILER SKIN INBOARD LOWER SURFACE DELAMINATED OVER AN AREA OF APPROXIMATELY 10 INCHES BY 8 INCHES. THE DELAMINATED AREA WAS REMOVED AND FIBERGLASS OVERLAYS WERE APPLIED IAW SRM 57-50-5. (X)

Part: WEB — GOUGED (E/E COMPARTMENT)

GSO - INSPECTION FOUND A 1 INCH LONG GOUGE IN WEB OF E AND E COMPARTMENT AT LT SIDE OF DOORWAY CUT-OUT. THE WEB WAS REMOVED. A NEW WEB WAS FABRICATED AND INSTALLED IAW SRM 53-10-2 AND SRM 51-30-2. (X)

Part: INTERCOSTAL — CORRODED (FS 870-887)

GSO - INSPECTION FOUND INTERCOSTAL CORRODED IN AFT CARGO COMPARTMENT AT FS 870 - FS 887, STR 20R TO STR 21R. THE INTERCOSTAL WAS REMOVED IAW SRM 51-30-2, A NEW INTERCOSTAL WAS FABRICATED AND INSTALLED IAW SRM 53-10-2. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-40-2. (X)

Part: FRAME — CRACKED (BS 440)

GSO - INSPECTION FOUND A 1 INCH CRACK IN FRAME AT STA 440 ABOVE STR 21L. A NEW FRAME AND CLIP WERE FABRICATED AND INSTALLED IAW BOEING DRAWING 65C25113 AND SRM 51-10-2. (X)

Part: SHEAR TIE — CRACKED (BS 440)

GSO - INSPECTION FOUND A .50 INCH CRACK IN SHEAR TIE AT STA 440, BL ZERO. THE CRACKED SECTION SHEAR TIE WAS CUT OFF IAW SRM 53-10-4. AN ANGLE AND FILLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-4 AND SRM 51-30-2. (X)

Part: SKIN — CORRODED (E/E DOOR CUTOUT)

GSO - INSPECTION FOUND SKIN CORROSION AT FORWARD LT CORNER OF E AND E BAY DOORWAY CUT-OUT. THE CORROSION WAS REMOVED AND A T-CHORD SECTION WAS CUT OUT IAW SRM 51-10-6. A REPAIR STRAP AND NEW T-CHORD WERE FABRICATED AND INSTALLED IAW ECRA 5310-01233. (X)

Part: DOUBLER — CRACKED (EXT PWR RECEPT)

GSO - INSPECTION FOUND .25 INCH CRACKS IN SEVERAL AREAS OF DOUBLER FOR EXTERNAL POWER RECEPTACLE. THE DOUBLER WAS REMOVED IAW SRM 51-30-2. THE CORROSION WAS REMOVED IAW SRM 51-10-6. A NEW DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-30-2 AND SRM 51-30-2. (X)

Part: FLOOR BEAM — CORRODED (BS 328)

GSO - INSPECTION FOUND FLOOR BEAM UPPER CAP CORRODED AT STA 328, RBL 45 TO RBL 65. THE FLOOR BEAM UPPER CAP WAS REMOVED IAW SRM 53-10-9. A NEW CAP AND SPLICE ANGLES WERE FABRICATED AND INSTALLED IAW SRM 53-10-9 AND SRM 51-30-0. (X)

Part: PANEL — CORRODED (NLG WW)

GSO - INSPECTION FOUND NOSE WHEELWELL UPPER FORWARD PANEL CORRODED. THE PANEL WAS REPAIRED IAW E.A. 5310-02452. (X)

Part: FRAME — CRACKED (BS 460)

GSO - INSPECTION FOUND LEFT LOWER FRAME IN FORWARD PIT, STA 460, CRACKED AT NUTPLATES FOR CARGO LINER. THE CRACK LENGTHS WERE NOT IDENTIFIED. THE FRAME WAS REPAIRED IAW E.A. 5310-01211. (X)

Part: FLOOR BEAM — CORRODED (COCKPIT)

GSO - INSPECTION FOUND FLOOR BEAM AND WEB CORRODED IN COCKPIT UNDER CAPTAIN'S SEAT. THE AREA WAS REPAIRED IAW SRM 51-40-2 AND ECRA 5310-03239. (X)

Part: FRAME — CRACKED (BS 480)

GSO - INSPECTION FOUND THE LT LOWER FRAME IN FORWARD PIT STA 480 CRACKED TWO PLACES AT NUTPLATE LOCATIONS FOR CARGO LINER. THE CRACK LENGTHS WERE NOT IDENTIFIED. THE FRAME WAS REPAIRED IAW E.A. 5310-01211. (X)

Part: STRINGER — CRACKED (BS 360-440)

GSO - INSPECTION FOUND TWO EACH .25 INCH CRACKS AT FASTENER HOLES OF STR 23R, STA 360 TO STA 440. THE STRINGER WAS REMOVED AND REPLACED IAW SRM 51-30-2. (X)

Part: ACT FITTING — CRACKED (NR 5 SPOILER)

GSO - INSPECTION FOUND A 1 INCH CRACK AT ROD ATTACH POINT OF NR 5 SPOILER INBOARD ACTUATOR FITTING. THE FITTING WAS REMOVED AND REPLACED IAW SRM 51-30-2. (X)

Part: STRINGER — CORRODED (BS 478)

GSO - INSPECTION FOUND STR 24R IN FORWARD PIT CORRODED AT STA 478. THE STRINGER WAS REMOVED AND REPLACED IAW SRM 51-30-2 AND BOEING DRAWING 65-45768. (X)

Part: SKIN — CRACKED (BS 188-251)

GSO - INSPECTION FOUND CRACKS AROUND FASTENERS IN LT EXTERNAL SKIN AT BS 188 TO BS 251, WL 207 THROUGH WL 234. THE CRACK LENGTHS WERE NOT IDENTIFIED, BUT THE REPAIRED AREAS WERE LESS THAN 6 INCHES IN DIAMETER. THE CRACKS WERE CUT OUT. REPAIR DOUBLERS AND FILLERS WERE FABRICATED AND INSTALLED IAW E.A. 53-10-01188. (X)

Part: FRAME — CRACKED (BS 400)

GSO - INSPECTION FOUND A DENT AND .50 INCH CRACK IN FORWARD PIT BELT FRAME AT STA 400, STR 23L TO STR 25L. THE FRAME WAS REPAIRED BY FABRICATING AND INSTALLING ANGLE, DOUBLER, AND FILLER IAW SRM 51-40-3. (X)

Part: STRINGER — CRACKED (RT WING)

GSO - INSPECTION FOUND A .50 INCH CRACK IN RT WING STR 13 AT WBL 92.5. REPAIR ANGLES AND SPLICES WERE FABRICATED AND INSTALLED IAW BOEING DRAWING 65C34533 AFTER STOP DRILLING CRACK. (X)

Part: SKIN — CORRODED (BS 295-340)

GSO - INSPECTION FOUND SKIN CORRODED AT STA 295 TO STA 340, STR 18R TO STR 19R. THE CORRODED SKIN WAS REMOVED. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-30-3. (X)

Part: BEAR STRAP — CRACKED (C1 DOOR CUTOUT)

GSO - INSPECTION FOUND A .3750 INCH CRACK IN BEAR STRAP AT C-1 DOOR CUT-OUT, LOWER AFT CORNER. THE SKIN WAS REPLACED AND A DOUBLER INSTALLED IAW ECRA 5330-02366. (X)

Part: CHORD — CRACKED (LT MLG WW)

STA 31J - INSPECTION FOUND A 14 INCH CRACK IN THE LEFT MLG WHEEL WELL AFT BULKHEAD LOWER CIRCUMFERENTIAL ANGLE (PREVIOUSLY STOP DRILLED). THE CHORD WAS REPLACED IAW SERVICE BULLETIN 737-53-1088 AND ECRA 5310-03133. (M)

Part: CARRIAGE SPINDLE — SHEARED (RT O/B FLAP)

IAH - INSPECTION FOUND THE RIGHT OUTBOARD FLAP OUTBOARD CARRIAGE SPINDLE SHEARED AT FORWARD RETAINING NUT. THE CARRIAGE ASSEMBLY WAS REMOVED AND REPLACED AND OPERATION CHECKED GOOD. (M)

Part: HYD LINE — LEAKING (A-HYD SYST)

CLE - FLT 1475 - THE A-SYSTEM HYDRAULIC FLUID QUANTITY BEGAN TO DECREASE AFTER TAKEOFF FROM CLE. THE AIRCRAFT WAS RETURNED TO CLE WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND NR 2 ENGINE A-HYDRAULIC SYSTEM PRESSURE LINE UNION IN THE RT WHEELWELL LEAKING. THE UNION WAS TIGHTENED AND LEAK CHECK WAS GOOD DURING AN ENGINE RUN. (X)