N14233

Part: HYD LINE — CHAFED (LT MLG WW)

THE A-HYDRAULIC SYSTEM BEGAN TO LEAK SLOWLY WHILE EN ROUTE. THE HYDRAULIC PUMPS WERE TURNED OFF BEFORE LOW PRESSURE LIGHTS ILLUMINATED. THE AIRCRAFT WAS DIVERTED TO MCO WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND A-SYSTEM HYDRAULIC PRESSURE LINE IN LT WING UPPER GEAR WELL CHAFED. THE HYDRAULIC LINE WAS REMOVED AND REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED TO FULL. LEAK AND OPERATIONAL CHECKS WERE GOOD.

Part: SKIN — CRACKED (WS 190)

INSPECTION FOUND A 4.5 INCH CRACK IN RT WING LEADING EDGE SKIN AT WS 190. THE CRACKED AREA WAS REMOVED, REPAIR PARTS WERE FABRICATED AND INSTALLED IAW SRM 57-30-2, FIGURE 2.

Part: STRINGER — CRACKED (BS 907)

INSPECTION FOUND A 2 INCH CRACK IN STRINGER AT STA 907. THE CRACKED SECTION OF STRINGER WAS REMOVED IAW SRM 53-10-3, STRINGER SPLICES WERE FABRICATED AND INSTALLED IAW SRM 53-10-2, 53-10-3 AND 51-30-2.

Part: ANGLE — CRACKED (BS 540)

INSPECTION FOUND STA 540 WING TO BODY FRAME CRACKED LOWER AREA LBL 31, T-ANGLE WAS CRACKED INTO TWO PIECES. THE CRACKED SECTION WAS REMOVED, ANGLES AND T-CHORD WERE FABRICATED AND INSTALLED IAW SRM 51-30-2.

Part: FITTING — CRACKED (VERT STAB)

INSPECTION FOUND A 1 INCH CRACK AT BOTTOM AFT FACE OF VERTICAL STABILIZER LT AFT OUTBOARD FITTING TO LUG. THE CRACKED FITTING WAS REMOVED, A NEW FITTING WAS DRILLED AND INSTALLED IAW SRM 51-10-7 AND 51-30-2.

Part: BULKHEAD WEB — PUNCTURED (AFT PRESS BLKHD)

INSPECTION FOUND A .25 INCH DIAMETER PUNCTURE IN AFT PRESSURE BULKHEAD WEB AT 8:30 POSITION, TWO FEET FROM CENTER. THE DAMAGED AREA WAS REMOVED, A DOUBLER AND FASTENERS WERE FABRICATED AND INSTALLED IAW SRM 53-10-4 AND 51-30-0.

Part: WEB — CRACKED (BS 715)

INSPECTION FOUND THREE EACH CRACKS AT RIVETS OF WEB UNDER NR 3 SEAT TRACK AT BS 715. THE CRACKS WERE APPROXIMATELY 2 INCHES LONG. THE CRACKED AREAS WERE REMOVED, REPAIR SHIMS AND DOUBLER WERE FABRICATED AND INSTALLED IAW SRM 51-40-2.

Part: STRINGER — CRACKED (BS 787)

INSPECTION FOUND A .5 INCH CRACK IN RADIUS OF STRINGER 6L AT STA 787. THE CRACKED SECTION OF STRINGER WAS REMOVED, A STRINGER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-3, 51-30-2, AND 51-20-4.

Part: ANGLE — CRACKED (LT WING)

INSPECTION FOUND A 2.5 INCH CRACK IN RIB LOWER CHORD ANGLE AT S3 IN FUEL ACCESS PANEL 7202 AT LT WING FUEL TANK, WBL 135.5. THE CRACKED AREA WAS REMOVED, A REPAIR TEE WAS INSTALLED IAW BOEING SERVICE BULLETIN 737-57-1186 AND REPAIR ENGINEERING ORDER NUMBER 02665. LEAK CHECK WAS GOOD IAW MM 28-11-00.

Part: SUPPORT — BROKEN (BS 490)

INSPECTION FOUND FORWARD CARGO PIT FLOOR SUPPORT BROKEN AT STA 490 ABOVE STRINGER 28L. THE BROKEN SECTION WAS REMOVED IAW SRM 53-10-1 AND 51-30-2, A NEW SECTION OF SUPPORT WAS TRIMMED, FITTED AND SPLICED IAW SRM 53-10-5. THE NEW SECTION AND SPLICES WERE INSTALLED IAW SRM 51-30-2.

Part: SKIN — CRACKED (WS 213)

INSPECTION FOUND A 1.5 INCH CRACK IN SKIN PANEL AT LEADING EDGE STA 213 OF LT WING LOWER SURFACE. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-40-0 AND 51-30-2.

Part: FRAME — CORRODED (BS 270/277)

INSPECTION FOUND STA 270 LT FRAME, STA 277 LT CAP ANGLE, FRAME WEB, STIFFENER CHANNELS AT STA 270 AND 277, AND BEAR STRAP AT STA 277 LT CORRODED. FRAME ANGLES, WEB, REPAIR DOUBLER, STIFFENER CHANNELS, BEAR STRAP, FILLER AND DOUBLERS WERE FABRICATED AND INSTALLED IAW ECRA 5100-01788, SRM 53-10-2 AND 51-40-2.

Part: BULKHEAD — CRACKED (BS 294.5)

INSPECTION FOUND A 8.25 INCH CRACK AT RBL 7.5 AND A 5.25 INCH CRACK AT LBL 6.12 IN BULKHEAD, STA 294.5. THE CRACKED AREAS WERE CUT OUT, DOUBLERS AND FILLERS WERE FABRICATED AND INSTALLED IAW ECRA 5310-03410.

Part: FRAME — CORRODED (BS 250-277)

INSPECTION FOUND STA 250 RT VERTICAL STIFFENER, STA 277 RT FRAME WEB, STA 270 RT SHEAR TIE ANGLE CHORD IN RT NOSE WHEEL WELL CORRODED. A VERTICAL BEAM, FRAME WEB REPAIR ANGLES, AND SHEAR TIE REPAIR ANGLES WERE FABRICATED AND INSTALLED IAW SRM 53-10-2, 51-10-2, AND 53-10-4.

Part: FLOORBEAM — CORRODED (BS 360)

INSPECTION FOUND FLOORBEAM CORRODED BETWEEN SEAT TRACKS 2-13 AT STA 360. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-9.

Part: FRAME — CRACKED (BS 987)

INSPECTION FOUND FRAME CRACKED AND BENT AT STA 987, BL ZERO - RBL 10. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-4 AND 51-30-2.

Part: FLOORBEAM — CORRODED (BS 980)

INSPECTION FOUND UPPER FLANGE OF FLOORBEAM CORRODED AT STA 980. THE UPPER FLANGE WAS REMOVED. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-9 AND 51-30-2.

Part: FLOORBEAM — CORRODED (BS 744)

INSPECTION FOUND FLOORBEAM CORRODED AT STA 744, RBL 15 TO LBL 15. THE CORRODED SECTION OF FLOORBEAM WAS REMOVED. A FLOORBEAM REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-9 AND 51-30-2.

Part: ANGLE — CORRODED (BS 947-970)

INSPECTION FOUND FLOOR SUPPORT ANGLE CORRODED AT STA 947 TO 970, ON RT SIDE. THE CORRODED SECTION OF FLOOR SUPPORT WAS REMOVED, A REPAIR SECTION AND SPLICES WERE FABRICATED AND INSTALLED IAW SRM 51-40-3 AND 51-30-2.

Part: FLOORBEAM — CRACKED (BS 667)

INSPECTION FOUND A 2 INCH CRACK ON UPPER FLANGE OF FLOORBEAM AT BS 667, BL 0. A REPAIR WAS FABRICATED AND INSTALLED IAW ECRA 5710-01779.

Part: FLOORBEAM — CRACKED (BS 675/685)

INSPECTION FOUND A 1 INCH CRACK IN LOWER RADIUS OF FLOORBEAM AT STA 685, BL 0. A 1 INCH CRACK WAS FOUND IN TRANSVERSE BEAM AT STA 675, BL 0. THE FLOORBEAM WAS REPAIRED IAW BAC DRAWING 65C19643. THE TRANSVERSE BEAM WAS REPAIRED IAW BAC DRAWING 65C17103.

Part: SKIN — GOUGED (CARGO DOORWAY)

INSPECTION FOUND AFT CARGO DOOR CUTOUT FORWARD LOWER CORNER SKIN GOUGED. THE GOUGED SKIN WAS CUT OUT, REPAIR FILLERS AND DOUBLER WERE FABRICATED AND INSTALLED IAW SRM 51-30-2 AND ECRA 5330-02484.

Part: FLOORBEAM — CORRODED (BS 328)

INSPECTION FOUND UPPER FLANGE OF FLOORBEAM CORRODED AT STA 328, RBL 24 TO RBL 50. THE UPPER CHORD OF BEAM WAS REMOVED. REPAIRS WERE FABRICATED AND INSTALLED IAW SRM 53-10-9 AND 51-30-2.

Part: SUPPORT — CRACKED (BS 460)

INSPECTION FOUND TWO 8 INCH CRACKS IN FORWARD CARGO PIT FLOOR SUPPORT AT STA 460, RBL 14. THE FLOOR SUPPORT WAS REMOVED AND A NEW SUPPORT WAS INSTALLED IAW SRM 51-30-2 AND 51-40-4.

Part: STRINGER — CRACKED (FS 465)

INSPECTION FOUND A .25 INCH CRACK IN STRINGER AT RT WING FS 465 LEADING EDGE SLAT WELL. THE STRINGER WAS REMOVED AND A NEW STRINGER WAS FABRICATED AND INSTALLED IAW SRM 51-20-1 AND 51-30-2.

Part: BULKHEAD — CRACKED (BS 178)

INSPECTION FOUND AN 8 INCH CRACK IN BULKHEAD AT STA 178, RBL 29 AND A 10 INCH CRACK WAS FOUND IN BULKHEAD AT STA 178, LBL 29. THE CRACKED AREAS WERE CUT OUT, FILLER AND DOUBLER REPAIRS WERE FABRICATED AND INSTALLED IAW SRM 51-10-2 AND 53-10-11.

Part: FLOORBEAM — CRACKED (BS 459)

GSO - INSPECTION FOUND A .50 INCH CRACK AND CORROSION ON COCKPIT AFT FLOORBEAM AT STA 459. THE CORRODED AREAS WERE REMOVED. NEW ANGLES WERE FABRICATED AND INSTALLED IAW SRM 51-40-3. (X)

Part: FRAME — CRACKED (CARGO DOOR)

GSO - INSPECTION FOUND A 3 INCH CRACK IN LOWER FORWARD FRAME OF C-1 DOOR. THE FRAME SECTION WAS REMOVED AND REPLACED IAW SRM 51-30-2. (X)

Part: SKIN — CORRODED (NR 2 ENGINE)

GSO - INSPECTION FOUND THE NR 2 ENGINE FORWARD OUTBOARD COWL OUTER SKIN CORRODED AROUND ENGINE RADIUS WARNING PLACARD. THE CORRODED SECTION OF SKIN WAS CUT OUT. A DOUBLER AND FILLERS WERE FABRICATED AND INSTALLED IAW SRM 54-30-2. (X)

Part: LINE — CHAFED (NR 2 ENGINE)

DFW - FLT 1648 - LOSS OF A-SYSTEM HYD QUANTITY. REQUIRED BRAKE REPLACEMENT TO REMOVE FROM RUNWAY DUE TO OVERTEMP ON LANDING. FOUND LINE ON NR 2 ENGINE DRIVEN PUMP CHAFED. REPLACED LINE, FLUSHED, OPERATION AND LEAK CHECKED SYSTEM. REMOVED AND REPLACED NR 1, 2, 3, AND 4 BRAKES DUE TO OVERTEMP ON LANDING. (X)

Part: CARGO DOOR — CRACKED (CARGO COMPT)

CLE - FLT 1639 - MAINTENANCE FOUND TWO CRACKS IN THE FORWARD CARGO DOOR AT THE SEAL RETAINER WHILE UNDERGOING A DECAY CHECK FOR PRESSURIZATION PROBLEMS. THE CRACKS WERE 8 INCHES AND 4.5 INCHES LONG. THE FORWARD CARGO DOOR WAS REMOVED AND REPLACED IAW MM 52-31-0. A SUBSEQUENT DECAY CHECK WAS GOOD. (X)

Part: FAN BLADE — BENT (NR 2 ENGINE)

FLT NR 1464 - IAH - ON MAINTENANCE WALKAROUND, FOUND NR 2 ENGINE FAN BLADE BENT OUT OF LIMITS. AIRCRAFT REMOVED FROM SERVICE ENGINE C1 DISK FAN ASSY. CHANGE COMPLETED, OPS CHECK GOOD. (W)

Part: HYD MODULE — FAILED (A-HYD)

GSO - FLT 1735 - THE A-HYDRAULIC SYSTEM PRESSURE DROPPED TO ZERO DURING CLIMB OUT OF GSO. CHECK LIST PROCEDURES WERE COMPLIED WITH AND THE AIRCRAFT WAS RETURNED TO GSO WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND A CHECK VALVE FAILURE OF THE A-HYDRAULIC SYSTEM MODULE. THE A-SYSTEM MODULE WAS REMOVED AND REPLACED. LEAK AND OPERATIONAL CHECKS WERE GOOD. THE HYDRUALIC WAS SERVICED IAW MM 29-11-61. (X)

Part: CHORD — CRACKED (FS 727)

GSO - INSPECTION FOUND A .50 INCH CRACK IN RT STA 727 OUTBOARD CHORD AT STR 18A. THE CRACKED CHORD WAS REMOVED AND A NEW CHORD WAS FABRICATED AND INSTALLED IAW BOEING DRAWING 65C33722. (X)

Part: FLOOR PANEL — CORRODED (FS 312)

GSO - INSPECTION FOUND THE NR 6 FLOOR PANEL SUPPORT CORRODED AT STA 312. THE PANEL SUPPORT WAS REPAIRED IAW SRM 51-30-2. (X)

Part: FRAME — CRACKED (BS 500)

GSO - INSPECTION FOUND A 1 INCH CRACK IN BELT FRAME AT BS 500 BETWEEN STR 21L AND STR 20L. THE CRACKED BELT FRAME WAS REMOVED AND A REPAIR WAS INSTALLED IAW SRM 51-30-2. (X)

Part: INTERCOSTAL — CRACKED (E & E BAY)

GSO - INSPECTION FOUND A 1 INCH CRACK IN INTERCOSTAL BEHIND AFT FORMER IN E AND E BAY. THE INTERCOSTAL WAS REMOVED AND A NEW INTERCOSTAL WAS FABRICATED AND INSTALLED IAW SRM 53-30-2. (X)

Part: SKIN — CORRODED (FS 727)

GSO - INSPECTION FOUND CORROSION ON RT EXTERNAL SKIN AND DOUBLER AT STA 727 BETWEEN STR 17R AND STR 18R. THE CORROSION WAS REMOVED AND A DOUBLER IN INSTALLED IAW EC 5330-02227. (X)

Part: FRAME — CRACKED (PAX DR CUTOUT)

GSO - INSPECTION FOUND A .25 INCH CRACK IN FORWARD ENTRY DOOR FORWARD FRAME CUT OUT AT UPPER HINGE ARM. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-2, SRM 51-10-2, AND SRM 51-30-2. (X)

Part: FRAME — CRACKED (BS 480)

GSO - INSPECTION FOUND A .50 INCH CRACK IN BELT FRAME AT BS 480 BETWEEN STR 21L AND STR 20L. THE CRACK WAS STOP DRILLED AND A REPAIR WAS INSTALLED IAW SRM 51-30-0. (X)

Part: FRAME — CRACKED (FS 578)

GSO - INSPECTION FOUND A .50 INCH CRACK IN STA 578 MAIN CABIN FRAME AT STR 16 - STR 17L. THE FRAME WAS REPAIRED IAW SRM 51-40-3 AND SRM 51-30-2. (X)

Part: SKIN — CRACKED (LT HORIZ STAB)

GSO - INSPECTION FOUND A .50 INCH CRACK IN THE LT HORIZONTAL STABILIZER TRAILING EDGE LOWER SKIN AT STA 66. THE CRACK WAS STOP DRILLED AND REPAIR DOUBLERS WERE INSTALLED IAW SRM 55-10-3 AND SRM 51-30-2. (X)

Part: SKIN — CRACKED (BS 188-251.6)

GSO - INSPECTION FOUND SKIN CRACKED AT SEVERAL FASTENER HOLES BETWEEN BS 188 AND BS 251.6 ON THE LT SIDE OF FUSELAGE. ALL CRACKS WERE APPROXIMTELY .25 INCH LONG. THE CRACKS WERE REPAIRED IAW EA 5310-01188, PART 3. (X)

Part: FLOORBEAM — CRACKED (FS 639)

GSO - INSPECTION FOUND A 1 INCH CRACK IN STA 639 LT SIDE FLOORBEAM WEB CABLE CUTOUT. THE FLOORBEAM WEB WAS REPAIRED IAW BOEING DRAWING 65C25211. (X)

Part: INTERCOSTAL — CRACKED (BS 508)

GSO - INSPECTION FOUND A 1 INCH CRACK IN INTERCOSTAL AT BS 508 BETWEEN STR 28L AND STR 28R. THE INTERCOSTAL WAS REMOVED AND REPLACED IAW SRM 51-30-2. (X)

Part: FRAME — CRACKED (BS 500A)

GSO - INSPECTION FOUND A 1 INCH CRACK IN BELT FRAME AT BS 500A BETWEEN STR 21L AND STR 20L. THE CRACKED FRAME WAS CUT OUT IAW BOEING DRAWING 65C225113 AND A REPAIR WAS INSTALLED IAW SRM 51-30-0. (X)

Part: BELT FRAME — CRACKED (BS 420)

GSO - INSPECTION FOUND A 2 INCH CRACK IN BELT FRAME AT BS 420, STR 22L. THE CRACK WAS REPAIRED IAW BOEING DRAWING 65C25113. (X)

Part: SKIN — CRACKED (BS 188-251.6)

GSO - INSPECTION FOUND SKIN CRACKED AT SEVERAL FASTENER HOLES ON RT SIDE OF FUSELAGE BETWEEN BS 188 AND BS 251.6. ALL CRACKS WERE APPROXIMATELY 1 INCH LONG. THE CRACKS WERE REPAIRED IAW EA 5310-01188, PART 3. (X)

Part: STRINGER — CRACKED (FS 685)

GSO - INSPECTION FOUND A 1 INCH CRACK IN STR 5R AT STA 685. THE CRACK WAS STOP DRILLED AND A REPAIR CHANNEL WAS INSTALLED IAW SRM 53-10-3. (X)