N27783

Part: SKIN — DENTED (LT TE FOREFLAP)

INSPECTION FOUND LT I/B TE FOREFLAP DENTED AND A 1 X 1 AREA OF DEBONDING JUST OUTBOARD OF NR 3 FLAP TRACK AREA AT LOWER SURFACE. THE LT I/B TE FOREFLAP WAS REMOVED AND REPLACED IAW MM 27-51-1.

Part: COVER — CRACKED (NR 2 SPOILER)

INSPECTION FOUND A .1875 AND .125 CRACK IN LT WING UPPER T/E HINGE COVER OF NR 2 SPOILER HINGE. THE T/E HINGE COVER WAS REMOVED AND A NEW T/E HINGE COVER WAS INSTALLED IAW SRM 51-30-2, PARAGRAPH 7.

Part: SKIN — CRACKED (NR 2 LE SLAT)

INSPECTION FOUND TWO 1 INCH CRACKS AT SCREW HOLE TO RIVET HOLES OF NR 2 SLAT UPPER TRAILING EDGE WHERE I/B HOOK MOUNTS. THE FASTENERS WERE REMOVED AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 51-10-2, PAGE 3 AND 57-50-3, PAGES 27-28.

Part: PLATE — CRACKED (RT TE MIDFLAP)

INSPECTION FOUND A 1 INCH CRACK IN PLATE AT RT INBOARD MIDFLAP ABOVE AFT END OF NR 5 SPINDLE. THE PLATE WAS REMOVED IAW SRM 51-30-2, PAGE 4. A NEW PLATE WAS INSTALLED IAW SRM 51-10-1 AND 51-10-2, PAGE 1.

Part: COVER — CRACKED (NR 3 SPOILER)

INSPECTION FOUND A .25 INCH CRACK IN LT WING UPPER T/E HINGE COVER OF NR 3 SPOILER HINGE. THE T/E HINGE COVER WAS REMOVED AND A NEW T/E HINGE COVER WAS INSTALLED IAW SRM 51-20-1 AND 51-30-2, PARAGRAPH 7.

Part: ANGLE — CRACKED (NR 2 LE SLAT)

INSPECTION FOUND A .375 INCH CRACK IN LT WING NR 2 SLAT LOWER CHORD ANGLE BELOW TELESCOPING ANTI-ICE DUCT AREA. THE CRACK WAS STOP DRILLED AND A REPAIR ANGLE WAS INSTALLED IAW SRM 51-40-4, PAGE 16.

Part: SKIN — CRACKED (NR 1 LE SLAT)

INSPECTION FOUND A 4 INCH CRACK IN SKIN AT AFT FACE OF LT WING NR 1 SLAT, INBOARD OF INBOARD TRACK AREA. THE NR 1 LE SLAT WAS REMOVED AND REPLACED IAW MM 27-81-11.

Part: BRACKET — CRACKED (NR 6 LE SLAT ACT)

INSPECTION FOUND TWO .5 INCH CRACKS IN NR 6 LE FLAP O/B ACTUATOR MOUNT BRACKET. THE BRACKET WAS REMOVED AND A NEW BRACKET WAS INSTALLED IAW SRM 51-20-1, FIGURE 18.

Part: WEB — PUNCTURED (CARGO COMPT)

INSPECTION FOUND A PUNCTURE IN FORWARD CARGO AREA WEB JUST FORWARD OF UPPER AFT DOOR STOP. THE PUNCTURED AREA WAS ROUTED OUT IAW SRM 51-10-1, PAGE 6B. A WEB REPAIR DOUBLER WAS INSTALLED IAW SRM 51-40-2, FIGURE 1 AND 51-10-2, PAGE 4.

Part: ACCESSORY UNIT — INOPERATIVE (E/E COMPT)

THE LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED THE LANDING GEAR ACCESSORY UNIT IAW MM 32-09-121. OPERATION OF THE GEAR CHECKED GOOD.

Part: LIGHT — INOPERATIVE (CABIN)

AFT AIRSTAIR OVERHEAD EMERGENCY LIGHTS INOP. REPLACED LIGHT ASSEMBLY.

Part: FLOORBEAM — CORRODED (BS 480)

INSPECTION FOUND FLOORBEAM CORRODED AT STA 480 FROM RBL 46 TO SIDEWALL. THE CORRODED AREA WAS CUT OUT. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-8, FIGURE 3.

Part: SUPPORT — CRACKED (BS 720)

INSPECTION FOUND A 1 INCH CRACK IN FLOOR SUPPORT AT STA 720F, BL 0. A NEW SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 51-10-1.

Part: WEB — CRACKED (BS 885)

INSPECTION FOUND A 1.5 INCH CRACK IN WEB BELOW CABIN FLOOR TRACK AREA AT BS 885, RBL 45. THE WEB WAS REMOVED AND A NEW WEB WAS FABRICATED AND INSTALLED IAW SRM 51-10-1.

Part: FLOORBEAM — CORRODED (BS 277)

INSPECTION FOUND FLOORBEAM CORRODED AT STA 277, RBL 12. A REPAIR WAS INSTALLED IAW SRM 51-10-1.

Part: FLOOR TRACK — CORRODED (BS 1110)

INSPECTION FOUND FLOOR TRACK CORRODED AT STA 1110 RBL 25. THE TRACK WAS REMOVED AND A REPLACEMENT TRACK WAS FABRICATED AND INSTALLED IAW SRM 53-10-5.

Part: SKIN — CRACKED (VERT STAB)

INSPECTION FOUND A 1 INCH CRACK IN RT SIDE OF VERTICAL STABILIZER INNER COMPARTMENT AT RIB NR 8 AND STRINGER 7. THE CRACKED AREA WAS CUT OUT, A REPAIR WAS INSTALLED IAW SRM 55-30-05.

Part: FLOOR TRACK — CORRODED (BS 400-440)

INSPECTION FOUND FLOOR TRACK CORRODED AT BS 400 TO 440, RBL 46. THE FLOOR TRACK WAS REMOVED, A NEW TRACK WAS FABRICATED AND INSTALLED IAW SRM 53-10-5.

Part: FLOORBEAM — CORRODED (BS 1110)

INSPECTION FOUND FLOORBEAM CORRODED AT STA 1110 BETWEEN RBL 25 AND RBL 46. THE CORROSION WAS REMOVED. FILLER AND DOUBLER WERE FABRICATED AND INSTALLED IAW SRM 53-10-8.

Part: FLOORBEAM — CORRODED (BS 344)

INSPECTION FOUND CORROSION ON UPPER SURFACE OF FLOORBEAM AT STA 344, LBL 30. THE CORRODED SECTION WAS CUT OUT. A BEAM REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-8.

Part: SKIN — CRACKED (VERT STAB)

INSPECTION FOUND A 1 INCH CRACK IN LT SIDE OF VERTICAL STABILIZER INNER COMPARTMENT AT RIB NR 2 AND STRINGER NR 7. THE CRACKED AREA WAS CUT OUT, A REPAIR WAS INSTALLED IAW SRM 55-30-05.

Part: SKIN — CRACKED (BS 870)

INSPECTION FOUND THREE 1 CRACKS AT LT WHEEL WELL KEEL BEAM SKIN AT FORWARD END OF APU CUTOUT, JUST AFT OF BS 870. THE CRACKED AREA WAS CUT OUT. DOUBLERS WERE FABRICATED AND INSTALLED IAW SRM 51-40-2 AND ECRA 5310-03522.

Part: STRINGER — CORRODED (BS 720)

INSPECTION FOUND STRINGER 28R IN FORWARD CARGO COMPARTMENT CORRODED AT STA 720E. THE CORRODED SECTION OF STRINGER WAS CUT OUT, A STRINGER AND SPLICE REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-3.

Part: FLOORBEAM — CRACKED (BS 825)

INSPECTION FOUND A .5 INCH CRACK COMING FROM LIGHTENING HOLE IN FLOORBEAM AT BS 825, LBL 54. A REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-40-2.

Part: FLOORBEAM — CRACKED (BS 825)

INSPECTION FOUND A .5 AND .3125 INCH CRACK OUT OF LIGHTENING HOLE OF FLOORBEAM AT BS 825, RBL 49. THE CRACK WAS STOP DRILLED, A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-2.

Part: STRINGER — CRACKED (BS 656.5)

INSPECTION FOUND A 1 INCH CRACK IN RT WING STRINGER JUST FORWARD OF FUEL DUMP LINE AT STA 656.50. A REPAIR WAS FABRICATED AND INSTALLED IAW BOEING SERVICE BULLETIN 727-57A159.

Part: STRINGER — CRACKED (WS 629)

INSPECTION FOUND A 1 INCH CRACK IN MID UPPER AFT LT WING STRINGER AT RIB STATION 629. THE CRACK WAS STOP DRILLED. THE STRINGER WAS REPAIRED IAW BOEING SERVICE BULLETIN 57A159.

Part: SKIN — CORRODED (BS 720)

INSPECTION FOUND FUSELAGE SKIN CORRODED AT BS 720A BETWEEN STRINGER 27R AND 28R. A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3.

Part: STRINGER — CORRODED (BS 620)

INSPECTION FOUND STRINGER S28R IN FORWARD CARGO COMPARTMENT CORRODED AT STA 620. THE CORRODED SECTION OF STRINGER WAS CUT OUT, A NEW SECTION WAS FABRICATED AND INSTALLED IAW SRM 53-10-3, FIGURE 1.

Part: SKIN — CORRODED (BS 720)

INSPECTION FOUND FORWARD CARGO COMPARTMENT SKIN BETWEEN STRINGER 27 AND 28 AT STA 720D CORRODED. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-30-3.

Part: SUPPORT — CORRODED (BS 424)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 424, RBL 45. A NEW SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 53-10-5.

Part: CLIP — CRACKED (BS 460)

INSPECTION FOUND A .5 INCH CRACK IN S28L TIE CLIP AND A .5 INCH CRACK IN S28R TIE CLIP AT STA 460. REPLACEMENT TIE CLIPS WERE FABRICATED AND INSTALLED IAW SRM 51-10-1, 51-30-2, AND 51-10-3.

Part: SPAR — CRACKED (WS 335)

INSPECTION FOUND A .75 INCH CRACK IN RT WING FRONT SPAR UPPER CHORD AT STA 335. THE CRACKED SECTION WAS CUT OUT. FILLER AND DOUBLER WERE FABRICATED AND INSTALLED IAW ECRA 5710-01819 AND SRM 57-10-6.

Part: SKIN — CRACKED (FUSELAGE)

INSPECTION FOUND A .75 INCH CRACK IN FUSELAGE SKIN AT BOTTOM OF WINDOW POST AREA BETWEEN FIRST OFFICER'S WINDSHIELD AND SLIDING WINDOW. THE CRACK WAS STOP DRILLED. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-30-3, FIGURE 8.

Part: BULKHEAD — CRACKED (BS 870)

INSPECTION FOUND A 2.5 INCH CRACK IN BULKHEAD AT APU LOAD CONTROL CUTOUT, BS 870. THE CRACK WAS STOP DRILLED AND A DOUBLER WAS FABRICATED AND INSTALLED IAW ECRA 5310-01544.

Part: SKIN — DENTED (BS 1086-1093)

INSPECTION FOUND A DENT IN RT FUSELAGE SKIN AT STA 1086 TO 1093 BETWEEN STRINGER 21R AND 22R. A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3, FIGURE 1.

Part: SKIN — CRACKED (BS 600)

INSPECTION FOUND A .1875 INCH CRACK IN FUSELAGE SKIN WITH CORROSION AT LAP SEAM BS 600, STRINGER 26L. THE CORROSION WAS REMOVED AND THE CRACKED AREA WAS CUT OUT, A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3.

Part: SKIN — CORRODED (BS 700-715)

INSPECTION FOUND FUSELAGE SKIN BULGING WITH TWO FASTENERS POPPED AT LEFT LAP SEAM 26L BETWEEN BS 700 TO 715. THE CORRODED AREA WAS CUT OUT, A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3.

Part: SKIN — CRACKED (BS 575-588)

INSPECTION FOUND .0625 INCH CRACKS AROUND RIVET HEADS OF FUSELAGE SKIN AT LAP SEAM 26L BETWEEN BS 575 TO 588. THE CRACKED AREA OF SKIN WAS CUT OUT, A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3.

Part: LG ACCY UNIT — INOPERATIVE (E/E COMPT)

THE RT MLG RED UNSAFE LIGHT REMAINED ILLUMINATED WHEN LANDING GEAR WAS EXTENDED ON APPROACH. THE GEAR WAS CYCLED AND THE RED LIGHT EXTINGUISHED. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED THE LANDING GEAR ACCESSORY UNIT AND OPERATIONAL CHECKS WERE GOOD.

Part: DUCT — BROKEN (NR 3 ENGINE)

THE NR 3 FIRE LIGHT AND BELL ACTIVATED IN FLIGHT. THE ENGINE THROTTLE WAS REDUCED TO IDLE AND THE WARNING CEASED. WHEN THE THROTTLE WAS INCREASED THE LIGHT CAME ON AGAIN. THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE DUCT FROM 13TH STAGE BLEED TO COWL ANTI-ICE BROKEN. THE DUCT WAS REPLACED AND OPERATIONAL CHECKS WERE GOOD.

Part: DUCT — RUPTURED (NR 3 ENGINE)

THE BLOW OUT PANEL ON NR 3 ENGINE UPPER OUTBOARD COWLING WAS FOUND MISSING WHEN AIRCRAFT ARRIVED. THE COWLS WERE OPENED AND THE DUCTING WAS INSPECTED. THE 13TH STAGE DUCT WAS FOUND RUPTURED. THE DUCT WAS REMOVED AND REPLACED AND A NEW BLOW OUT PANEL WAS INSTALLED. THE COWL SKIN ADJACENT TO THE SEVENTH RIB WAS FOUND HEAT DAMAGED. THE RIB WAS STRAIGHTENED AND DAMAGED RIVETS WERE REPLACED, NO CRACKS WERE FOUND. ECRA 7110-01170 WAS ISSUED FOR PERMANENT REPAIR. A DIP WAS ISSUED TO REINSPECT THE AREA EVERY 7 DAYS AND TO PERFORM A PERMANENT REPAIR WITHIN 30 DAYS. THE ENGINE WAS RUN AND DUCTS WERE LEAK CHECKED WITH NO LEAKS NOTED.

Part: BULKHEAD WEB — CRACKED (BS 1183)

INSPECTION FOUND A 1 INCH CRACK IN STA 1183 PRESSURE BULKHEAD AT LBL 8, W.L. 162. THE BULKHEAD WEB WAS REPAIRED IAW ECRA 5310-01473 AND BOEING DRAWING 65C33041.

Part: ACTUATOR — LEAKING (NR 6 TE SLAT)

FLT NR 0209 - CUN - THE 'A' HYDRAULIC SYSTEM WAS LOST WHILE EN ROUTE FROM IAH TO SAL. 'ABNORMAL' PROCEDURES WERE COMPLIED WITH AND THE AIRCRAFT WAS DIVERTED TO CUN. WHILE ON APPROACH TO CUN, THE NR 6 SLAT WOULD NOT COME DOWN AND LOCK USING THE ALTERNATE FLAP SYSTEM. THE SLAT WAS VISUALLY CONFIRMED TO BE IN THE 'UP' POSITION. THE AIRCRAFT LANDED WITHOUT INCIDENT. THE NR 6 LE SLAT ACTUATOR WAS FOUND LEAKING. THE ACTUATOR WAS REMOVED AND REPLACED. LEAK AND OPERATIONAL CHECKS WERE GOOD. (M)

Part: SKIN — CORRODED (BS 500)

IAH - INSPECTION FOUND CORROSION ON FUSELAGE SKIN LAP JOINT AT STATION 500, STRINGER 26R. THE AREA WAS REPAIRED IAW SRM 53-30-3, FIGURE 5. (M)

Part: REGULATOR — INOPERATIVE (NR 3 ENGINE)

LAX - FLT 0418 - AIRCRAFT LOST CABIN PRESSURE WHILE AT 33,000 FEET EN ROUTE FROM SFO TO LAX. CABIN PRESSURE COULD NOT BE CONTROLLED IN STAND-BY A.C. OR D.C. MODES AND RT PACK COULD NOT BE RESET. OXY MASKS DEPLOYED AND AIRCRAFT WAS DIVERTED TO LAX WHERE IT LANDED WITHOUT INCIDENT. BOTH THE HIGH PRESSURE REGULATOR AND HIGH PRESSURE MODULATING VALVE WERE REMOVED AND REPLACED AND OPERATIONAL CHECKS WERE GOOD. OPERATION OF THE RT PACK AND MIX VALVE CHECKED GOOD. DECAY CHECK WAS PERFORMED IAW MM 5-12-71 AND PRESSURE WAS WITHIN LIMITS. THE OUTFLOW VALVE WAS REPLACED AS A PRECAUTIONARY MEASURE. ALSO NOTED BY MAINTENANCE ALL OXY MASKS HAD DEPLOYED. OXY MASKS WERE STOWED AND OXY BOTTLES SERVICED TO FULL. (X)

Part: STRINGER — CORRODED (BS 720)

GSO - INSPECTION FOUND CORROSION ON STRINGER LOWER SURFACE AFT SIDE OF STA 720 FRAME IN FORWARD LOWER CARGO AREA. THE CORRODED SECTION WAS REMOVED AND A STRINGER AND STRINGER SPLICE WERE INSTALLED IAW SRM 53-10-3 AND SRM 51-30-2. (X)

Part: SKIN — CRACKED (SECTION 41)

GSO - INSPECTION FOUND 3 CRACKS RUNNING FROM FASTENER HOLES IN SECTION 41 SKIN PANEL ON RT SIDE OF FUSELAGE. THE CRACKS WERE APPROXIMATELY .25 INCH LONG. THE EXISTING DOUBLER WAS REMOVED AND THE DAMAGED SKIN WAS CUT OUT. FILLERS AND DOUBLERS WERE INSTALLED IAW SRM 53-30-2 AND SRM 51-30-2. (X)

Part: SKIN — CRACKED (BS 720)

GSO - INSPECTION FOUND FUSELAGE SKIN CRACKED THROUGH RIVET HOLES BETWEEN STA 720 AND STA 720A AT CENTERLINE ON LOWER FUSELAGE. THE CRACK WAS 2.5 INCHES LONG. THE DAMAGED AREA WAS REMOVED AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-30-3. (X)

Part: STRINGER — CORRODED (BS 720)

GSO - INSPECTION FOUND CORROSION ON STR 28R IN FORWARD BAG PIT AT STA 720. A REPAIR SPLICE WAS FABRICATED AND INSTALLED IAW SRM 51-10-6, SRM 51-30-2, AND SRM 51-20-4. (X)

Part: STRINGER — CORRODED (BS 675)

GSO - INSPECTION FOUND CORROSION ON LOWER SURFACE OF STRINGER 28L IN FORWARD BAG PIT AT STA 675. THE DAMAGED SECTION OF STRINGER WAS REMOVED AND A REPAIR WAS INSTALLED IAW SRM 53-10-3 AND SRM 51-30-2. (X)

Part: RIB — CRACKED (NR 3 LE SLAT)

GSO - INSPECTION FOUND A 2.25 INCH CRACK IN RADIUS OF NR 3 SLAT INBOARD TRACK INBOARD RIB. THE CRACK WAS STOP DRILLED AND A REPAIR WAS INSTALLED IAW SRM 57-30-2 AND SRM 51-30-2. (X)

Part: FLOOR — CORRODED (BS 620)

GSO - INSPECTION FOUND THE FORWARD BAG PIT CENTER FLOOR CORRODED AT STA 620. THE DAMAGED AREA WAS TRIMMED OUT AND REPAIR DOUBLER AND FILLER WERE INSTALLED IAW SRM 51-40-3 AND SRM 51-30-2. (X)

Part: STRINGER — CORRODED (BS 740)

GSO - INSPECTION FOUND STRINGER 27R CORRODED IN FORWARD BAG PIT AT STA 740. THE STRINGER WAS REPAIRED IAW SRM 51-10-6, SRM 51-10-3, AND SRM 51-20-4. (X)

Part: RIBS — CRACKED (LE FLAP)

GSO - INSPECTION FOUND 2 LOWER LEADING EDGE INBOARD SLAT RIBS CRACKED AT ACTUATOR. THE CRACKS WERE APPROXIMATELY .75 INCH LONG. THE CRACKS WERE STOP DRILLED AND DOUBLERS WERE INSTALLED IAW SRM 57-30-3 AND SRM 51-30-2. (X)

Part: SUPPORT — CORRODED (FS 540)

GSO - THE FORWARD BAG PIT FLOOR SUPPORT JUST FORWARD OF STA 540 AND ABOVE STR 29L HAD CORROSION ON UPPER AND LOWER SURFACE. A REPAIR DOUBLER WAS INSTALLED IAW SRM 51-10-6, SRM 51-40-3, AND SRM 51-30-2. (X)

Part: RIB — CRACKED (NR 3 LE SLAT)

GSO - INSPECTION FOUND A 1 INCH CRACK IN RADIUS OF THE NR 3 SLAT OUTBOARD TRACK OUTBOARD RIB. THE CRACK WAS STOP DRILLED AND A REPAIR WAS INSTALLED IAW SRM 57-50-3, SRM 51-40-3, AND SRM 51-30-2. (X)

Part: SKIN — CRACKED (FUSELAGE)

GSO - INSPECTION FOUND 13 CRACKS RUNNING FROM FASTENER HOLES IN LEFT SECTION 41 SKIN PANEL. THE CRACKS RANGED IN LENGTH FROM 0.25 INCH TO 0.009 INCH. THE EXISTING DOUBLER WAS REMOVED AND THE DAMAGED AREAS WERE CUT OUT. FILLERS AND DOUBLERS WERE INSTALLED IAW SRM 51-30-2 AND SRM 51-30-3. (X)E

Part: SKIN — CRACKED (BS 580)

GSO - INSPECTION FOUND A .25 INCH CRACK IN SKIN AT FASTENER HOLE, BS 580, LAP SEAM 26L. THE DAMAGED AREA WAS REMOVED AND REPAIRED. DOUBLER, FILLER, AND SHIM WERE INSTALLED IAW SRM 53-30-3 AND SRM 51-30-2. (X)

Part: ACCESSORY UNIT — INOPERATIVE (LANDING GEAR)

DEN - FLT 0759 - THE LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF FROM DEN. 'ABNORMAL' PROCEDURES WERE COMPLIED WITH AND THE AIRCRAFT WAS RETURNED TO DEN WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE SWUNG THE GEAR SEVERAL TIMES, BUT WERE UNABLE TO DUPLICATE THE FAILURE. THE LANDING GEAR ACCESSORY UNIT WAS REMOVED AND REPLACED AS A PRECAUTIONARY MEASURE. (X)

Part: HYD LINE — LEAKING (NR 1 ENG)

MIA - FLT 334 - THE 'A' SYSTEM HYDRAULIC QUANTITY DECREASED TO .1250 GALLON WHILE IN FLIGHT. 'ABNORMAL' PROCEDURES WERE COMPLIED WITH AND THE ACFT WAS DIVERTED TO MIA WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 1 ENGINE DRIVEN HYDRAULIC PUMP PRESSURE LINE LEAKING. THE LINE WAS REMOVED AND REPLACED. LEAK AND PRESSURE CHECKS AFTER HYDRAULIC SYSTEM SERVICING WERE GOOD. (W)