N17402

Part: CONTROL UNIT — FAULTED (ANTI-SKID SYS) · airframe 1,250 hrs · 427 cycles

ANTI-SKID INOPERATIVE PILOT STATES AUTO BRAKE LIGHT & ANTI-SKID LIGHT CAME ON DURING TAKEOFF ROLL, PILOT ALSO STATES THAT LIGHT STAYED ON DURING THE WHOLE FLIGHT UNTIL PARKING BRAKE WAS SET AUTO BRAKE LIGHT AND ANTI-SKID LIGHT STAYED ON DURING WHOLE FLIGHT. NORMAL LANDING WAS ACOMPLISHED. PERFORMED BITE CHECK AMM 32-42-00-740-801 FOUND THR SW, ADIRU L ADIRU R & BOX 4. PERFORMED TEST & NO FAULTS, REPEATED TEST 4 TIMES WITH NO FAULTS. SUSPECT CREW CONFIG OR BOX ISSUE. CREW DECLARED EMERGENCY INTO DEN. REMOVED AND REPLACED (AACU) AUTOBRAKE, ANTI-SKID CONTROL UNIT AMM 32-42-21 OPS CHECK OK

Part: LAMP — INOPERATIVE (ZONE 200) · airframe 651 hrs · 232 cycles

EMERGENCY LIGHTS OPERATIONAL CHECK EMERGENCY LIGHTS OPERATIONAL CHECK - LEFT AFT OVERWING EMERGENCY EXIT DOOR EXTERIOR LIGHT INOP. RE-LAMPED REF MM 33-51-04-960-801. OPS CK OK.

Part: OVEN — CONTAMINATED (ZONE 900) · airframe 273 hrs · 99 cycles

OVEN 204 CREATED SMOKE I N THE GALLEY. SMOKE ALAR M BRIEFLY WENT OFF. FOUND BURNT FOOD AND DEBRIS AT THE BOTTOM OF THE OVEN. ACPED MEL. PLACED OM DF 2500BI. PLACED ON MEL. CLEAN OIL RESIDUE INSIDE OVEN #204, SMOKE STILL VISIBLE AFTER OPS CHECKING. PARTS NOT AVAILABLE AND CB PULLED AND COLLAR.

Part: BATTERY PACK — DISCHARGED (CABIN)

INSPECTION FOUND SEVERAL EMERGENCY LIGHTS INOPERATIVE IN CABIN AND AT OVERWING EXITS, BOTH SIDES. MAINTENANCE REPLACED A BAD FUSE. THE BATTERY PACKS WERE REMOVED, RECHARGED, AND REINSTALLED. OPERATIONAL CHECKS WERE GOOD IAW MM 33-50-01, PAGE 201.

Part: SKIN — CORRODED (LAV SERVICE PNL)

INSPECTION FOUND AFT LAV SERVICE PANEL AFT LOWER SKIN CORRODED. THE PANEL WAS REMOVED AND THE CORRODED INNER SKIN WAS REMOVED. A NEW SKIN AND INTERNAL AND OUTER DOUBLER WERE INSTALLED AND THE PANEL WAS REINSTALLED IAW SRM 51-10-2, PAGE 1, 51-30-2, PAGE 1 AND ECRA 5330-02799.

Part: STRINGER — CRACKED (BS 1183-1161)

INSPECTION FOUND A 4 INCH CRACK IN STRINGER 23L BETWEEN STA 1183 AND 1161, JUST BELOW LAV SERVICE PANEL INSIDE AFT CARGO COMPARTMENT. THE CRACKED SECTION OF STRINGER WAS CUT OUT, A NEW STRINGER, DOUBLER AND FILLER COVER PLATE WERE INSTALLED IAW SRM 51-10-2 AND ECRA 5330-02798.

Part: SKIN — CRACKED (LT AILERON)

INSPECTION FOUND A .5 AND .375 INCH CRACK IN LT O/B AILERON LOWER SKIN WITH A BEND AT I/B EDGE. THE AILERON WAS REMOVED AND REPLACED IAW MM 27-10-31.

Part: SKIN — DEBONDED (LT TE MIDFLAP)

INSPECTION FOUND LT WING I/B MIDFLAP I/B END OF TRAILING EDGE SKIN DEBONDED. THE DEBONDED AREA WAS CUT OUT, A SKIN AND DOUBLER HOT BOND REPAIR WAS PERFORMED IAW SRM 51-40-6.

Part: BRACKET — CRACKED (NR 5 LE FLAP ACT)

INSPECTION FOUND A .125 INCH CRACK AT UPPER END OF OUTBOARD BRACKET AT RT WING LEADING EDGE WHERE NR 5 L/E FLAP ACTUATOR MOUNTS. THE FASTENERS AND SUPPORT BRACKET WERE REMOVED IAW SRM 51-20-2. A NEW SUPPORT BRACKET WAS INSTALLED IAW SRM 51-10-1, PARAGRAPH 4 AND 51-10-2.

Part: WIRE — BROKEN (CABIN)

THE RT FORWARD EMERGENCY EXIT LIGHT WAS FOUND INOPERATIVE. MAINTENANCE FOUND A BROKEN WIRE. THE WIRE WAS REPAIRED IAW WPM 20-10-13, PAGE 1. OPERATION OF THE EXIT LIGHT CHECKED GOOD.

Part: CONTROL TAB — DENTED (RIGHT ELEVATOR)

INSPECTION FOUND THE RT ELEVATOR CONTROL TAB UPPER O/B TRAILING EDGE SKIN DENTED. THE ELEVATOR TAB WAS REMOVED AND REPLACED IAW MM 27-30-11.

Part: ANGLE — CRACKED (LT WING)

INSPECTION FOUND A 2.75 INCH CRACK IN LT WING REAR SPAR O/B SUPPORT ANGLE WHERE NR 2 SPOILER ACTUATOR AND FLAP DRIVE CASTING MOUNTS. THE SUPPORT ANGLE WAS REMOVED AND REPLACED IAW SRM 51-10-1 AND 51-30-2.

Part: SKIN — DEBONDED (LT TE FOREFLAP)

INSPECTION FOUND LT I/B FOREFLAP UPPER SURFACE DEBONDED. THE FOREFLAP WAS REMOVED AND REPLACED IAW MM 27-51-14.

Part: SKIN — CRACKED (LT TE FOREFLAP)

INSPECTION FOUND A .5 INCH CRACK IN LT O/B FOREFLAP I/B END CASTING AT LEADING EDGE AND TRAILING EDGE. THE FOREFLAP WAS REMOVED AND REPLACED IAW MM 27-51-11.

Part: SKIN — DEBONDED (RIGHT WING)

INSPECTION FOUND RT WING UPPER AND LOWER SKIN DEBONDED O/B AND AFT OF APU EXHAUST AREA. THE SKIN PANEL WAS REPAIRED IAW SRM 51-30-08 PAGE 1.

Part: SKIN — CRACKED (RT TE FLAP)

INSPECTION FOUND A .3125 INCH CRACK IN RT INBOARD AFT FLAP LOWER LEADING EDGE. THE FLAP WAS REMOVED AND REPLACED IAW MM 27-51-02.

Part: PRESSURE DECK — CRACKED (BS 270)

INSPECTION FOUND A 3.5 INCH CRACK IN NOSE WHEEL WELL PRESSURE DECK AT FS 270, LBL 14. THE CRACKED AREA WAS CUT OUT, A DOUBLER REPAIR WAS INSTALLED IAW SRM 51-40-2.

Part: CHORD — CRACKED (NR 2 LE SLAT)

INSPECTION FOUND A .375 INCH AND .125 INCH CRACK AT LT WING NR 2 SLAT LOWER CHORD BELOW TELESCOPING ANT-ICE TUBE. THREE ACCESS PANELS WERE REMOVED PER SRM 51-30-2 AND THE CRACKS WERE STOP DRILLED IAW SRM 51-10-1, PAGE 6B. AN ANGLE REPAIR DOUBLER WAS INSTALLED IAW SRM 51-10-2 AND 51-40-1. THE THREE ACCESS PANELS WERE REINSTALLED IAW SRM 51-30-2.

Part: CHORD — CRACKED (NR 1 LE SLAT)

INSPECTION FOUND A .3125 INCH CRACK AT LT WING NR 1 SLAT LOWER CHORD AT CUTOUT BELOW TELESCOPING ANTI-ICE TUBE. THE CRACK WAS STOP DRILLED AND AN ANGLE REPAIR WAS INSTALLED IAW SRM 57-30-2.

Part: TAB — DENTED (LEFT ELEVATOR)

INSPECTION FOUND LEFT ELEVATOR CONTROL TAB LOWER O/B LEADING EDGE SKIN DENTED. THE LEFT ELEVATOR CONTROL TAB WAS REMOVED AND REPLACED IAW MM 27-30-11.

Part: SKIN — DEBONDED (LT TE FLAP)

INSPECTION FOUND LT INBOARD AFT FLAP LOWER SURFACE DEBONDED. THE FLAP WAS REMOVED AND REPLACED IAW MM 27-51-2.

Part: CHORD — CRACKED (NR 7 LE SLAT)

INSPECTION FOUND A 3 INCH AND .375 INCH CRACK AT RT WING NR 7 SLAT LOWER CHORD. THE LOWER SLAT PANEL WAS REMOVED FOR ACCESS AND REMOVED ANGLE IAW SRM 51-30-2, PAGE 1. A NEW ANGLE WAS INSTALLED IAW SRM 51-10-20 AND 51-30-2. REINSTALLED ACCESS PANEL IAW SRM 51-30-2.

Part: SKIN — DEBONDED (RT TE FLAP)

INSPECTION FOUND RT O/B FLAP AFT SEGMENT DEBONDED AT TRAILING EDGE. THE FLAP WAS REMOVED AND REPLACED IAW MM 27-51-11.

Part: SKIN — DENTED (LT TE FLAP)

INSPECTION FOUND LT O/B FLAP AFT SEGMENT UPPER SURFACE DENTED AND DEBONDED. THE FLAP WAS REPAIRED IAW SRM 51-40-6.

Part: WEDGE — DEBONDED (RT TE MID FLAP)

INSPECTION FOUND RT WING O/B MID FLAP T/E WEDGE DEBONDED. THE TRAILING WAS REMOVED AND REPLACED IAW SRM 51-30-2, PAGE 1.

Part: BULKHEAD ANGLE — CRACKED (BS 870)

INSPECTION FOUND A .75 INCH CRACK IN FWD BULK VERT ANGLE AT RT WHEEL WELL BS 870 KEEL BEAM. THE FWD BULK VERT ANGLE WAS REPLACED IAW SRM 51-10-1, PAGE 4 AND 51-30-5, PAGE 1.

Part: FLOORBEAM WEB — CRACKED (BS 294)

INSPECTION FOUND A 3 INCH CRACK IN FLOORBEAM WEB AT FS 294, RBL 48. THE CRACK WAS STOP DRILLED AND A DOUBLER WAS INSTALLED IAW SRM 51-40-2 FIGURE 1, SHEET 6.

Part: BATTERY — DISCHARGED (CARGO DOOR)

INSPECTION FOUND RT AFT CARGO DOOR EMERGENCY EXIT LIGHT INOPERATIVE. THE BATTERY PACK WAS REPLACED AND LIGHT WAS RELAMPED.

Part: GEAR HANDLE — LACK OF LUBE (COCKPIT)

WHEN GEAR WAS EXTENDED ON APPROACH, CREW RECEIVED THREE GREEN AND THREE RED GEAR INDICATION LIGHTS. THE GEAR WAS CYCLED AND CREW GOT THREE GREEN. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE LANDING GEAR HANDLE STICKING WHEN PULLED OUT. THE GEAR HANDLE WAS LUBRICATED AND CHECKED SEVERAL TIMES WHILE ON GROUND. THE GROUND CHECKS WERE GOOD WITH NO STICKING NOTED AND GEAR WARNING LIGHTS ALL CHECKED GOOD.

Part: DOOR FRAME — CRACKED (BS 410)

INSPECTION FOUND A 5 INCH CRACK IN UPPER AFT SECTION OF R-1 DOOR FRAME AT BS 410. THE CRACKED SECTION OF DOOR FRAME WAS CUTOUT IAW BOEING DRAWING 69-69978. A NEW SECTION OF FRAME WAS FABRICATED AND INSTALLED IAW SRM 51-30-2, 51-10-2, AND MM 51-20-11.

Part: WEB — CRACKED (BS 872.5)

INSPECTION FOUND A .125 CRACK IN RT MLG WHEEL WELL PRESSURE WEB AT BS 872.5, RBL 52.25. A PRESSURE WEB REPAIR WAS FABRICATED AND INSTALLED IAW ECRA 5310-03671.

Part: STRINGER — CORRODED (BS 720)

INSPECTION FOUND STRINGER 27R CORRODED IN AFT CARGO COMPARTMENT BETWEEN STA 720 AND 720A. THE CORRODED SECTION OF STRINGER AND SKIN WERE REMOVED. A STRINGER REPAIR, REPAIR SPLICES, AND DOUBLER WERE FABRICATED AND INSTALLED IAW SRM 51-10-3, FIGURE 1, 53-30-3, FIGURE 3, 51-10-2, 53-10-3, FIGURE 1, AND MM 51-21-2.

Part: FLOORBEAM — CORRODED (BS 380)

INSPECTION FOUND FLOORBEAM CORRODED AT CLIP NUTS, STA 380 BETWEEN RBL 24 AND 45. THE FLOORBEAM WAS REPAIRED IAW SRM 53-10-8.

Part: SKIN — CORRODED (BS 68)

INSPECTION FOUND FUSELAGE SKIN TEAR STRAP CORRODED IN FORWARD CARGO COMPARTMENT AT BS 68, STRINGER 28R. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-30-4, 51-30-8, 51-30-3, FIGURE 12, AND 51-10-2.

Part: SKIN — DENTED (BS 279)

INSPECTION FOUND FUSELAGE SKIN DENTED AT STA 279, STRINGER 22L. DOUBLER AND FILLER WERE FABRICATED AND INSTALLED IAW SRM 51-30-1, FIGURE 1, 53-30-3, FIGURE 13, 51-10-2, 51-30-2, AND MM 51-20-11.

Part: SUPPORT — CRACKED (BS 303.9)

INSPECTION FOUND CABIN FLOOR SUPPORT WEB CRACKED .125 BEYOND STOP DRILL HOLE AT STA 303.9, LBL 45. THE FLOOR SUPPORT WEB WAS REMOVED. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-2, 51-10-2, AND 51-30-1.

Part: SUPPORT — CRACKED (LT/RT ELEVATOR)

INSPECTION FOUND A 1.25 INCH CRACK IN LT ELEVATOR SUPPORT AT TRAILING EDGE OF ELEVATOR OUTBOARD OF INBOARD TRIM TAB HINGE BEARING. A 1.25 INCH CRACK WAS FOUND IN RT ELEVATOR OUTBOARD SUPPORT FOR ELEVATOR TRAILING EDGE AT TRIM TAB MOUNT AREA. THE SUPPORTS WERE REMOVED, NEW SUPPORTS WERE FABRICATED AND INSTALLED IAW SRM 51-40-3, 51-30-2, AND 51-10-2.

Part: SUPPORT — CRACKED (BS 294.5)

INSPECTION FOUND A 1.5 INCH CRACK ON UPPER FLANGE OF CABIN FLOOR SUPPORT THREE INCHES AFT OF FLOORBEAM AT STA 294.5, RBL 45. THE FLOOR SUPPORT WAS REMOVED, A REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-40-3, FIGURE 1, 51-10-1, 51-40-3, FIGURE 3, AND 51-30-2.

Part: STRINGER — CORRODED (BS 680-700)

INSPECTION FOUND STRINGER 28R IN FORWARD CARGO COMPARTMENT CORRODED BETWEEN STA 680 AND 700. THE STRINGER SPLICE WAS REMOVED AND A STRINGER SPLICE WAS FABRICATED AND INSTALLED IAW SRM 53-10-3, 51-30-02, 51-10-2, AND MM 51-20-11.

Part: SKIN — CRACKED (BS 510)

INSPECTION FOUND A 5.25 INCH CRACK IN FUSELAGE SKIN AT STA 510 BETWEEN STRINGER 25 AND 26R. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-30-3. THE DOUBLER AND FILLER WERE INSTALLED IAW SRM 51-30-8 AND 51-30-3.

Part: SEQUENCE VALVE — LEAKING (LT MLG)

THE SYSTEM-A HYDRAULIC FAILURE LIGHTS ILLUMINATED ON CO-PILOT PANEL AFTER GEAR RETRACTION. ALSO, THE A-SYSTEM HYDRAULIC LOW PRESSURE LIGHTS ON SECOND OFFICER'S PANEL ILLUMINATED WITH THE ELEVATOR LOW PRESSURE LIGHT ILLUMINATING MOMENTARILY. THE GEAR WAS LOWERED MANUALLY AND THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE LT MLG LOCK SEQUENCE VALVE CASE BLOWN. THE LOCK SEQUENCE VALVE WAS REMOVED AND REPLACED. IN ADDITION, BOTH THE NR 1 AND NR 2 ENGINE DRIVEN HYDRAULIC PUMPS WERE REMOVED AND REPLACED. LEAK AND OPERATIONAL CHECKS WERE GOOD.

Part: HYD MODULE — CRACKED (A-HYD SYS)

THE AIRCRAFT WAS DIVERTED TO PHX, AFTER LOSING THE A-HYDRAULIC SYSTEM FLUID QUANTITY. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE A-SYSTEM HYDRAULIC MODULE FITTING CRACKED. THE A-SYSTEM HYDRAULIC MODULE WAS REMOVED AND REPLACED. IN ADDITION, BOTH A-SYSTEM HYDRAULIC ENGINE DRIVEN PUMPS WERE REMOVED AND REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED, LEAK AND OPERATIONAL CHECKS WERE GOOD.

Part: FLEX HOSE — LEAKING ('B' HYD SYS)

FLT NR 477 - TPA - A/C LOST THE 'B' SYS HYD FLUID IN FLT. THE LOSS WAS ACCOMPANIED BY FLICKERING 'B' SYS HYD LOW PRESS LIGHTS. CHECKLIST PROCEDURES WERE COMPLIED WITH AND THE AIRCRAFT LANDED WITHOUT INCIDENT. MX FOUND THE HYD PRESS FLEX HOSE FROM THE NR 2 ELECTRIC 'B' PUMP LEAKING. THE HOSE WAS REPLACED USING 3000 PSI FLEX HOSE PER GMM 10-799-78, PAGE 14. A DIP WAS ISSUED TO REPLACED THE INTERIM FLEX HOSE WITHIN 500 FLIGHTS OR 1200 FLIGHT HOURS. THE HYD SYSTEM WAS SERVICED TO FULL. ALL CONTROL SURFACES WERE EXERCISED AND OPERATION WAS NORMAL WITH NO LEAKS NOTED. (M)

Part: ANGLE — CORRODED (BS 1168)

STATION 31J - INSPECTION FOUND CORROSION AT BOTTOM OF FLOOR BEAM AT GILL SUPPORT FRAME ANGLE IN AFT CARGO PIT AT BS 1168, RBL 55. THE CORRODED AREA OF ANGLE WAS CUT OUT. A NEW ANGLE AND DOUBLER ANGLE WERE FABRICATED AND INSTALLED IAW SRM 51-10-2, 51-20-2, AND 51-40-3. (M)

Part: FLOOR PAN — CORRODED (BS 1140-1176)

INSPECTION FOUND CENTER OF LT AFT LAV FLOOR PAN CORRODED AT BS 1140 TO BS 1176. THE CORROSION WAS REMOVED FROM THE FLOOR PAN. A REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-30-2 AND SRM 51-20-4. (X)

Part: CHANNEL SUPPORT — CORRODED (BS 803)

STATION 31J - INSPECTION FOUND CORROSION ON CHANNEL SUPPORT AT BS 803, BL 0. THE CORROSION WAS REMOVED AND A 'T' ANGLE REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-4. (M)

Part: PANEL SUPPORT — CORRODED (BS 880)

STATION 31J - INSPECTION FOUND LOWER FUSELAGE PANEL SUPPORT CORRODED AT BS 880, LBL 9 AND RBL 9. THE CORRODED AREA WAS CUT OUT. REPAIR ANGLES AND FILLERS WERE FABRICATED AND INSTALLED IAW SRM 51-40-3. (M)

Part: FLAP TRACK — CORRODED (TE FLAPS)

STATION 31J - INSPECTION FOUND CORROSION AT RIGHT MLG BEAM INBOARD FLAP INBOARD TRACK ATTACH POINT. THE AREA WAS REPAIRED IAW ECRA 5750-02438. (M)

Part: BEAM — CORRODED (LT MLG)

INSPECTION FOUND CORROSION ON LT MLG BEAM LOWER FLANGE AT INBOARD FLAP INBOARD TRACK ATTACH POINT. A REPAIR WAS PERFORMED IAW ECRA 5750-02437 AND SRM 51-10-6 AD SRM 51-10-2. (X)

Part: FLOOR BEAM — CORRODED (BS 1010)

STATION 31J - INSPECTION FOUND ELONGATED HOLES AND PITTING CORROSION IN FLOOR BEAM AND SEAT TRACK AT BS 1010, RBL 55. THE AREA OF ELONGATED HOLES WAS CUT OUT. REPAIR ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-40-3, FIGURE 1. (M)

Part: SUPPORT — CORRODED (BS 780)

STATION 31J - INSPECTION FOUND CORROSION ON INBOARD SIDE OF PANEL SUPPORT AT BS 780, LBL 9. THE CORROSION WAS MECHANICALLY REMOVED. TWO BRACKETS WERE FABRICATED AND INSTALLED IAW SRM 51-40-4, FIGURE 2. (M)

Part: FLOOR BEAM — CORRODED (BS 1110)

INSPECTION FOUND FLOOR BEAM UPPER CHORD CORRODED AT BS 1110, RBL 26 TO RBL 44. THE CORRODED SECTION OF FLOOR BEAM UPPER CHORD WAS REMOVED. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-8, SRM 51-10-2, AND MM 51-20-151. (X)

Part: SUPPORT — CORRODED (BS 813)

STATION 31J - INSPECTION FOUND FUSELAGE PANEL SUPPORT CORRODED BELOW ANCHOR NUT AT BS 813, LBL 9 BETWEEN LEFT AND RIGHT HEAT EXCHANGER. THE CORROSION WAS REMOVED IAW SRM 51-10-2, AN 'L' ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-10-2, 51-30-2, AND MM 51-20. (M)

Part: SUPPORT — CORRODED (BS 813)

STATION 31J - INSPECTION FOUND FUSELAGE PANEL SUPPORT CORRODED BELOW ANCHOR NUT AT BS 813, RBL 9 BETWEEN HEAT EXCHANGERS. THE CORRODED AREA WAS CUT OUT, TWO 'L' ANGLES AND FILLERS WERE FABRICATED AND INSTALLED IAW SRM 51-40-3, 51-10-2, 51-30-2, AND MM 51-20-0. (M)

Part: RIB — CHAFED (NR 7 LE SLAT)

INSPECTION FOUND A .3125 INCH CHAFED HOLE IN WEB AT INNER SKIN FLANGE OF RT WING L/E SLAT NR 7 OUTBOARD RIB. THE AREA WAS DRESSED OUT. A REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 57-50-3, FIGURE 9. (X)

Part: FLOOR SUPPORT — BROKEN (BS 760)

INSPECTION FOUND FLOOR SUPPORT BROKEN AT BS 760, LBL 2. THE BROKEN SUPPORT WAS REMOVED AND A NEW SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 51-40-3. (X)

Part: DOOR FRAME — CORRODED (BS 380)

INSPECTION FOUND R-1 DOOR INTERIOR LOWER FORWARD FRAME CORRODED AT BS 380, RBL 60. THE CORRODED AREA WAS CUT OUT. AN ANGLE AND DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-10-2 AND SRM 51-40-3, FIGURE 1. (X)

Part: BEAM — CRACKED (BS 803-812)

INSPECTION FOUND CORROSION ON TOP SIDE OF DELTA BEAM AT BS 803, RBL 9 AND A 1.5 INCH CRACK AT BS 812. THE CORROSION WAS REMOVED IAW SRM 51-10-2. A TEE SECTION WAS FABRICATED AND INSTALLED IAW MM 51-20. (X)

Part: THRESHOLD ANGLE — CORRODED (BS 344)

INSPECTION FOUND THRESHOLD ANGLE AT DRAIN PAN CORRODED AT BS 344. THE CORRODED AREA WAS CUT OUT. A THRESHOLD ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-40-3. (X)

Part: FLOOR BEAM — CORRODED (BS 344)

INSPECTION FOUND FLOOR BEAM UPPER CHORD CORRODED AT BS 344, RBL 20 TO LBL 20. THE CORRODED UPPER CHORD WAS REMOVED. A NEW CHORD WAS FABRICATED AND INSTALLED IAW SRM 53-10-8. FIGURE 3. (X)

Part: FLOOR BEAM — CORRODED (BS 380)

STATION 31J - INSPECTION FOUND FLOOR BEAM CORRODED AT BS 380, RBL 40 TO RBL 60. A NEW FLOOR BEAM WAS FABRICATED AND INSTALLED IAW SRM 53-10-8, FIGURE 3, 51-10-2, AND 51-20-0. (M)

Part: DOOR FRAME — CRACKED (BS 620)

INSPECTION FOUND A 1.5 INCH CRACK IN INBOARD UPPER SURFACE OF BS 620 FORWARD CARGO COMPARTMENT DOOR CUT OUT AFT FRAME COVER WEB. THE CRACKED AREA WAS REMOVED FROM THE WEB. A DOUBLER AND FILLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-2, 51-30-2, AND 51-40-2, FIGURE 1. (X)

Part: SKIN — CRACKED (WS 304)

STATION 31J - INSPECTION FOUND A .5 INCH CRACK IN LOWER SKIN PANEL OUTBOARD OF PANEL 8505R AT RIGHT WING STATION 304. THE CRACKED AREA WAS REMOVED. A NEW ATTACH ANGLE PLATE WAS FABRICATED AND INSTALLED IAW SRM 51-30-3, FIGURE 4. (M)

Part: FORMER — CORRODED (BS 774)

STATION 31J - INSPECTION FOUND CORROSION ON HORIZONTAL FORMER AT BS 774, RBL 9-35. THE CORRODED AREA WAS CUT OUT. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-3. (M)

Part: SUPPORT — CORRODED (BS 850)

STATION 31J - INSPECTION FOUND KEEL BEAM PANEL SUPPORT AT BS 850 LBL 10 CORRODED THROUGH AND BOTTOM OF SUPPORT HAS SURFACE CORROSION FROM RBL 10 TO LBL 10. A NEW SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 51-40-3. (M)

Part: BEAM — CRACKED (BS 870)

STATION 31J - INSPECTION FOUND A .75 INCH CRACK AT TERMINAL FITTING ATTACH POINT OF BS 870 HORIZONTAL BEAM IN FORWARD UPPER OUTBOARD CORNER OF LEFT WHEEL AT STRINGER 18A. THE CRACKED SECTION OF BEAM WAS REMOVED. AN ANGLE AND DOUBLER WERE FABRICATED AND INSTALLED IAW SRM 51-40-3, FIGURE 1. (M)

Part: RIB WEB — CRACKED (LT WING LE)

STATION 31J - INSPECTION FOUND A 1.5 INCH CRACK IN LEFT WING LEADING EDGE RIB WEB. THE CRACK WAS STOP DRILLED. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-40-2. (M)

Part: FITTING RIB — CRACKED (LT ELEVATOR)

STATION 31J - INSPECTION FOUND A 1.75 INCH CRACK IN LEFT ELEVATOR FITTING RIB BETWEEN BAYS 3 AND 4. THE LEFT ELEVATOR FITTING RIB WAS REMOVED AND REPLACED IAW MM 55-20-0 AND SRM 51-30-2. (M)

Part: LEVER ASSY — LACK OF LUBE (GEAR HANDLE)

FLT NR 0618 - FLL - WHEN GEAR WAS EXTENDED FOR LANDING AT FLL ALL THREE GREEN AND ALL THREE RED GEAR LIGHTS WERE ILLUMINATED AND THE TAIL SKID LIGHT WAS ON. THE RED DOOR LIGHT AND DOORS LIGHT ON SECOND OFFICERS PANEL WERE OUT. THE GEAR WAS CYCLED AND ALL INDICATIONS WERE NORMAL. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THAT THE GEAR LEVER WAS NOT FULLY RETRACTING. THE GEAR HANDLE/LEVER ASSY WAS CLEANED AND LUBRICATED. ALL POSITION SWITCHES WERE CHECKED AND FOUND TO BE OPERATING NORMALLY. AN OPERATIONAL CHECK OF THE GEAR SYSTEM WAS GOOD. (M)

Part: ACTUATOR — LEAKING (LT MLG DOOR)

FLT NR 0748 - IAH - THE AIRCRAFT LOST 'A' SYSTEM HYDRAULICS AFTER TAKEOFF FROM IAH. THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE LEFT MLG DOOR ACTUATOR LEAKING. THE ACTUATOR WAS REMOVED AND REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED TO FULL AND LEAK CHECKS WERE GOOD. (Z)