N10791
Registered owner: GLOBAL MEDIA BOX, NM (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
78 reports on file, 1995-05-24 – 1999-11-08.
Part: LIGHT — INOP (ROW 22)
INSPECTION FOUND INTERIOR OVERHEAD EMERGENCY EXIT LIGHT INOPERATIVE AT ROW 22. THE LIGHT ASSEMBLY WAS REMOVED AND REPLACED AND OPERATION CHECKED GOOD.
Part: FLOORBEAM — CORRODED (BS 1130)
INSPECTION FOUND MAIN DECK FLOORBEAM IN AFT CARGO COMPARTMENT CORRODED AT STA 1130 FROM BL 0 TO RBL 30. REPAIRED IAW SRM 53-10-8 AND ECRA 5310-03898.
Part: ACCESSORY UNIT — INOPERATIVE (LANDING GEAR)
WHEN GEAR WAS RETRACTED AFTER DEPARTURE A LOUD THUMP WAS HEARD WHEN NOSE GEAR RETRACTED. A LIGHT TEST WAS DONE AND THE NOSE GEAR GREEN LIGHT DID NOT COME ON. PRESS TO TEST AND NEW BULBS HAD NO EFFECT. FLIGHT MANUAL PROCEDURE WAS ACCOMPLISHED. THE LIGHT TEST WAS CHECKED AGAIN AND NEITHER THE NOSE GEAR GREEN OR RT MAIN GEAR GREEN LIGHTS WOULD TEST. WHEN GEAR WAS EXTENDED FOR LANDING AT IAH 3 GREEN GEAR LIGHTS WERE INDICATED. WHEN FLAPS WERE PUT TO 30 DEGREES THE GEAR WARNING HORN SOUNDED AND STAYED ON. THE AIRCRAFT LANDED AT IAH WITHOUT INCIDENT. THE LANDING GEAR ACCESSORY UNIT WAS REPLACED. A LANDING GEAR AND FLIGHT CONTROL POSITION AND WARNING CHECK WAS PERFORMED AND SYSTEM CHECKS WERE GOOD.
Part: STATOR — MIGRATED (NR 3 ENGINE)
ENGINE NUMBER THREE FAILED ON CLIMB-OUT. CONSTANT VIBRATION, OVER TEMP, ENGINE SHUT DOWN IN FLIGHT. AIRCRAFT RETURNED TO LAS. ENGINE AND DAMAGED COWLING REPLACED AND AIRCRAFT RETURNED TO SERVICE. PRELIMINARY ENGINE INSPECTION REVEALED A FAILURE IN THE HIGH PRESSURE COMPRESSOR SECTION AND AN UNCONTAINED CASE PENETRATION IN THE PRBC AREA CAUSING COWL DAMAGE. SDR TO REMAIN OPEN PENDING ENGINEERING INVESTIGATION AND ENGINE TEARDOWN. TEARDOWN FINDINGS REVEALED C12 STATOR MIGRATION AS THE PRIMARY CAUSE OF ENGINE FAILURE.
Earlier reports · 1995–1998 · 74 reports
1998
Part: BATTERY — DISCHARGED (CABIN)
MAIN CABIN O/H EMERGENCY LIGHT FLICKERING. RECHARGED BATTERY PACK PER MM 33-50-0.
Part: OXY CONTL UNIT — FAILED (PAX COMPT)
FWD OXYGEN PASSENGER DROP FAILED FUNCTIONAL TEST. REPLACED OXYGEN CONTROL UNIT AND PERFORMED PNEUMATIC OXYGEN DROP PER MM 35-21-00.
Part: WIRE — BROKEN (CABIN)
LT EXIT LIGHT INOP OVER EXIT IN CABIN. REPAIRED BROKEN WIRE AT EXIT IDENTIFIER, OPS CHECK PER 33-50-00.
Part: WIRE — BROKEN (CABIN)
ESCAPE PATH LIGHTS INOP ROW 24 TO 29. REPAIRED BROKEN WIRE GOING TO SEATS PER MM 33-50-00.
Part: STRINGER — CRACKED (VERT STAB)
VERT STAB INNER COMPARTMENT NR 7 STRINGER NR 2 AND NR 3 CRACKED (2) AT ATTACH BOLT. REPAIRED NR 7 RT STRINGER NR 2 AND NR 3 ON VERTICAL STAB PER SRM 55-30-4.
Part: FLANGE — CRACKED (BS 700)
TOP FLANGE RADIUS FS 700 ABOVE 24 L HAS 1.5 INCH CRACK. STOP DRILLED, FABRICATED DOUBLER AND INSTALLED PER SRM 51-30-2 AND 51-40-3.
Part: WEB — CRACKED (VERT STAB)
VERT STAB INNER COMPARTMENT NR 1 CANTED STATION 1303 HAS CRACK (2.5) AT RT LOWER CORNER. ALSO, CRACK (1) AT RT UPPER CORNER. STOP DRILLED CRACKS, FABRICATED AND INSTALLED DOUBLERS PER SRM 51-40-2.
Part: FRAME — CRACKED (FRAME 520)
TOP FLANGE AT FRAME 520 HAS .5 INCH CRACK ABOVE STR 26R. STOP DRILLED CRACK PER SRM 51-10-1. FABRICATED AND INSTALLED REPAIR PER SRM 51-10-6. HEAT TREAT PER BAC 5602.
Part: JAMB — CRACKED (C1 DOOR)
C-1 DOOR JAMB BENT/TORN AT TWO PLACES. REMOVED AND REPLACED DOOR JAMB AS REQUIRED PER SRM 51-10-1.
Part: SKIN — CORRODED (BS 693)
FUSELAGE SKIN IN FORWARD BAG BIN FS 695.700 AT RBL HAS SURFACE CORROSION. REMOVED DAMAGED AREA AND INSTALLED DOUBLER PER SRM 53-30-03.
Part: FLANGE — CRACKED (FRAME 500)
A 1 INCH CRACK AT FRAME 500 TOP FLANGE RADIUS ABOVE 24 L. FABRICATED NEW DOUBLER AND INSTALLED IN ACCORDANCE WITH SRM 51-40-3. HEAT TREATED PER BAC 5602.
Part: STRINGER — CORRODED (BS 720)
INSPECTION FOUND STRINGER 28L CORRODED AT STA 720D. THE CORRODED AREA OF STRINGER WAS REMOVED. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-10-2 AND 53-10-3.
Part: SUPPORT — CRACKED (VERT STAB)
INSPECTION FOUND A 2.5 CRACK IN VERTICAL STABILIZER STRINGER 4L SUPPORT WEB. THE SUPPORT WEB WAS REMOVED IAW SRM 51-30-2. A NEW SUPPORT WEB WAS FABRICATED AND INSTALLED IAW SRM 51-10-1.
Part: FRAME — CRACKED (BS 560)
INSPECTION FOUND A .375 INCH CRACK WITH CORROSION IN FRAME 560 TO SKIN ATTACH FLANGE, BBL 0 TO LBL 6. THE CORRODED AREA OF FLANGE WAS CUT OFF IAW SRM 53-10-4. A NEW FLANGE WAS FABRICATED AND INSTALLED IAW SRM 53-10-4.
Part: FRAME — CRACKED (BS 640)
INSPECTION FOUND A 1 CRACK IN UPPER FLANGE RADIUS OF FRAME 640, RBL 8, FORWARD BAGGAGE BIN. THE CRACKED AREA WAS CUT OUT IAW SRM 51-40-3. A DOUBLER AND FITTING WERE FABRICATED AND INSTALLED IAW SRM 51-40-3, FIGURE 1, SHEET A, SRM 51-10-2, AND 51-30-2.
Part: SUPPORT — CRACKED (VERT STAB)
INSPECTION FOUND A 1 CRACK IN VERTICAL STABILIZER SUPPORT WEB AT STRINGER 3L AND STRINGER 3R. THE LT AND RT SUPPORT WEB WAS REMOVED. A NEW SUPPORT WEB WAS FABRICATED AND INSTALLED IAW SRM 51-10-1.
Part: HYD PUMP — LEAKING (NR 2 ENGINE)
THE 'A' SYSTEM HYDRAULIC RESERVOIR QUANTITY WENT TO ZERO AND LOW PRESSURE LIGHTS ILLUMINATED WHILE EN ROUTE FROM MSY TO IAH. THE HYDRAULIC QUANTITY LOSS AND HYDRAULIC SYSTEM FAILURE CHECKLISTS WERE COMPLETED. THE LANDING GEAR WAS CRANKED DOWN AND THE FLAPS WERE LOWERED ELECTRICALLY. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 2 ENGINE DRIVEN HYDRAULIC PUMP CASE LEAKING. BOTH THE NR 1 AND NR 2 HYDRAULIC PUMPS WERE REMOVED AND REPLACED. THE HYDRAULIC SYSTEMS WERE SERVICED. LEAK AND OPERATIONAL CHECKS WERE GOOD.
1997
Part: BEAM — CRACKED (WS 232)
INSPECTION FOUND A .365 INCH AND .625 INCH CRACK IN RT WING UPPER TRAILING EDGE AFT OF MLG SUPPORT BEAM AT UPPER INBOARD CORNER OF NR 8 SPOILER ACTUATOR LINKAGE CASTING, WS 232. THE CRACKS WERE ROUTED OUT. REPAIR STRAPS WERE FABRICATED AND INSTALLED IAW ECRA 5750-02772 AND BOEING DRAWING 26425-6114.
Part: DOUBLER — CORRODED (BS 680)
INSPECTION FOUND CORROSION AND POPPED RIVETS IN REPAIR DOUBLER AT FS 680, STRINGER 28R - 28L. THE EXISTING DOUBLER WAS REMOVED AND THE CORRODED AREA WAS CUT OUT. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-30-3.
Part: BRACKET — CRACKED (NR 5 LE FLAP)
INSPECTION FOUND A .5 CRACK IN UPPER AND LOWER RADIUS OF NR 5 KRUGER FLAP ACTUATOR SUPPORT BRACKET. A REPLACEMENT BRACKET WAS FABRICATED AND INSTALLED IAW SRM 51-10-1.
Part: SKIN — PUNCTURED (NR 7 LE SLAT)
INSPECTION FOUND A .25 INCH DIAMETER HOLE IN SKIN AT UPPER LEADING EDGE OF NR 7 SLAT. A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 57-50-3.
Part: SKIN — CRACKED (LT WING)
INSPECTION FOUND A .375 INCH CRACK AT LEFT WING FIXED LEADING EDGE CUTOUT ABOVE NR 3 SLAT INBOARD TRACK. THE CRACK WAS STOP DRILLED. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-10-1, 51-30-2, AND 51-40-2.
Part: SKIN — DENTED (BS 380)
INSPECTION FOUND TWO DENTS IN RT FUSELAGE SKIN AT STA 380. THE DENTED AREA WAS CUT OUT. FILLER AND DOUBLER WERE FABRICATED AND INSTALLED IAW SRM 53-30-3.
Part: BRACKET — CRACKED (NR 1 LE FLAP)
INSPECTION FOUND A .75 CRACK IN BRACKET AT INBOARD AND OUTBOARD SIDE WHERE LEFT WING NR 1 L/E FLAP ACTUATOR MOUNTS (I/B LOWER AND O/B UPPER). REPLACEMENT BRACKETS WERE FABRICATED AND INSTALLED IAW SRM 51-10-1 AND 51-10-2.
Part: ACTUATOR — LEAKING (NR 2 LE FLAP)
AIRCRAFT LOST A-HYDRAULIC SYSTEM FLUID AFTER TAKEOFF. THE LOSS WAS ACCOMPANIED BY ILLUMINATION OF RUDDER SYSTEM A CAUTION LIGHT. THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 2 KREUGER FLAP ACTUATOR LEAKING. THE ACTUATOR WAS REMOVED AND REPLACED. ALSO, THE BRAKE METERING VALVE IN MAIN WHEEL WHEEL WAS FOUND LEAKING DURING TROUBLESHOOTING. THE BRAKE METERING VALVE WAS REMOVED AND REPLACED. IN ADDITION, BOTH THE NR 1 AND NR 2 ENGINE DRIVEN HYDRAULIC PUMPS WERE REMOVED AND REPLACED AS A PRECAUTIONARY MEASURE. THE HYDRAULIC SYSTEM WAS SERVICED, AN ENGINE RUN WAS PERFORMED AND THE FLIGHT CONTROLS WERE CYCLED WITH OPERATION CHECKING GOOD AND NO LEAKS DETECTED.
Part: HYD PUMP — LEAKING (NR 2 ENGINE)
ACFT LOST THE A-HYDRAULIC SYSTEM FLUID QUANTITY ON APPROACH. THE FLUID LOSS WAS ACCOMPANIED BY THE PUMP LIGHT GOING ON AND OFF INTERMITTENTLY. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 2 ENGINE DRIVEN HYDRAULIC PUMP LEAKING AT PUMP CASE. THE NR 2 ENGINE DRIVEN HYDRAULIC PUMP WAS REMOVED AND REPLACED. IN ADDITION, THE STANDBY HYDRAULIC MODULE WAS REPLACED DUE TO LEAKAGE, LEAK AND OPERATIONAL CHECKS WERE GOOD. THE A-HYDRAULIC SYSTEM WAS SERVICED TO FULL. *S/D* INVESTIGATION REVEALED THAT THE STANDBY HYDRAULIC SYSTEM MODULE PACKAGE ASSEMBLY HAD THREE VALVE ATTACHMENT SCREWS OF IMPROPER LENGTH INSTALLED WHICH EVENTUALLY RESULTED IN LEAKAGE. THE UNIT HAD BEEN INSTALLED ON THIS AIRCRAFT
1996
Part: SKIN — DAMAGED (TE MIDFLAP)
THE RT INBOARD TRAILING EDGE MID FLAP LOWER SKIN SUSTAINED DAMAGE WHEN THE RT MLG TIRE BLEW. THE MID FLAP WAS REPAIRED IAW ECRA 5750-02565.
Part: GEARBOX — LEAKING (NR 3 ENGINE)
THE NR 3 ENGINE LOST OIL QUANTITY AFTER TAKEOFF. THE LOSS OF OIL WAS ACCOMPANIED BY LOSS OF OIL PRESSURE AND ILLUMINATION OF FORWARD PANEL LIGHT. FUEL WAS DUMPED AND THE AIRCRAFT WAS RETURNED TO SJU WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 3 ENGINE GEARBOX LEAKING. THE NR 3 ENGINE GEARBOX WAS REMOVED AND REPLACED, LEAK AND OPERATIONAL CHECKS WERE GOOD.
Part: DUCT — BLOWN (NR 2 ENGINE)
THE NR 2 ENGINE FAILED AFTER TAKEOFF. THE AIRCRAFT WAS RETURNED TO SJU WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 2 ENGINE 13TH STAGE DUCT BLOWN. THE NR 2 ENGINE WILL BE REMOVED AND REPLACED.
Part: AIRSTAIRS — OUT OF ADJUST (TAIL SECTION)
THE AFT AIRSTAIRS FELL DOWN WHILE TAXIING TO GATE AFTER LANDING AT IAH. THE AIRCRAFT WAS STOPPED AND THE STAIRS WERE SECURED. WHEN THE AIRSTAIRS WAS EXAMINED FOR DAMAGE ONLY A SKID MARK WAS FOUND ON THE SKID PLATE. THE AIRSTAIR WAS OPERATED SEVERAL TIMES. MAINTENANCE FOUND THAT THE STAIR HANDLE WAS NOT GOING OVERCENTER EVERY TIME. TROUBLESHOOTING FOUND STOPS ADJUSTED TOO LOW CAUSING CAM ROLLER TO NOT ENGAGE. THE STOPS WERE ADJUSTED AND TESTED PER MM 52-62-01 AND OPERATION OF THE STAIRS CHECKED GOOD.
Part: ACTUATOR — LEAKING (NR 2 LE FLAP)
THE A-SYSTEM HYDRAULIC QUANTITY WAS LOST DURING CLIMBOUT. FUEL WAS DUMPED AND THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 2 LEADING EDGE FLAP ACTUATOR LEAKING. THE ACTUATOR WAS REMOVED AND REPLACED. IN ADDITION, BOTH ENGINE DRIVEN HYDRAULIC PUMPS WERE REMOVED AND REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED, LEAK AND OPERATIONAL CHECKS WERE GOOD.
Part: FLOORBEAM — CORRODED (BS 1130)
INSPECTION FOUND THE FLOORBEAM CORRODED AT STA 1130, RBL 34 DURING FLIGHT PHONE INSTALLATION. THE FLOORBEAM WAS REPAIRED IAW SRM 5310-03300.
Part: SHEAR TIE — CORRODED (BS 580)
INSPECTION FOUND SHEAR TIE CORRODED AT STA 580 BETWEEN STRINGER 27R AND 28R. THE SHEAR TIE WAS REMOVED AND A NEW SHEAR TIE WAS FABRICATED AND INSTALLED IAW SRM 51-30-2, 53-10-4, FIG 15 AND MM 51-20-2, 51-20-15.
Part: STRINGER — CORRODED (BS 685)
INSPECTION FOUND STRINGER 28R FLANGE CORRODED AT F.S. 685. THE CORRODED SECTION OF STRINGER WAS REMOVED. A NEW STRINGER AND SPLICE WERE FABRICATED AND INSTALLED IAW SRM 53-10-3.
Part: STRINGER — CORRODED (BS 520-540)
INSPECTION FOUND STRINGER 28R CORRODED AT STA 520 T0 540. THE CORRODED STRINGER SECTION WAS REMOVED. A NEW STRINGER AND SPLICE WERE FABRICATED AND INSTALLED IAW SRM 53-10-3 AND 51-30-2.
Part: ANGLE — CORRODED (BS 580)
INSPECTION FOUND CORROSION ON SKIN ATTACH ANGLE AT STA 580, STRINGER 27L. A NEW ANGLE WAS FABRICATED AND INSTALLED IAW SRM 53-10-4, 51-30-2 AND MM 51-20-11.
Part: SUPPORT — CORRODED (BS 535)
INSPECTION FOUND THE FORWARD CARGO COMPARTMENT FLOOR SUPPORT CORRODED AT STA 535, S28L TO S29L. A REPAIR ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-10-6, 51-40-4, 51-10-2, 53-10-1 AND 51-30-2.
Part: SKIN — CORRODED (BS 720)
INSPECTION FOUND SKIN LAP CORRODED AT STA 720D TO 720E, STRINGER 27R. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3 AND 51-30-2.
Part: SHEAR TIE — CORRODED (BS 265)
INSPECTION FOUND SHEAR TIE CORRODED AT STA 265, S25R. A REPAIR WAS PERFORMED IAW SRM 53-10-4, 51-10-2, 51-30-2 AND MM 51-20-21.
Part: ANGLE — CORRODED (BS 540)
INSPECTION FOUND ATTACH ANGLE CORRODED AT STA 540, S29R. THE ATTACH ANGLE WAS REMOVED. A REPAIR PART WAS FABRICATED IAW SRM 53-10-4, 53-10-1 AND 51-20-4.
Part: FRAME — CORRODED (BS 540)
INSPECTION FOUND STA 540 FRAME ASSEMBLY CORRODED. A REPAIR ANGLE WAS FABRICATED AND INSTALLED IAW SRM 53-10-4, PAGE 43.
Part: ANGLES — CORRODED (BS 580)
INSPECTION FOUND SKIN ATTACH ANGLES(2) AT BILGE, STA 580, BL ZERO CORRODED. ANGLE DOUBLERS WERE FABRICATED AND INSTALLED IAW SRM 51-40-3, 51-10-2, 51-30-2, AND MM 51-20-0.
Part: FLOOR BEAM — CORRODED (BS 1130)
INSPECTION FOUND FLOORBEAM CORRODED AT B.S. 1130, LBL 25. NEW PARTS WERE FABRICATED AND INSTALLED IAW SRM 53-10-1, 53-10-8, AND MM 51-20-11.
Part: SUPPORT — CORRODED (BS 1010-1030)
INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 1010-1030, RBL 65. A REPAIR WAS FABRICATED AND INSTALLED IAW 51-30-2, 51-10-2, AND 51-40-3.
Part: FLOOR BEAM — CORRODED (BS 380)
INSPECTION FOUND CABIN FLOORBEAM CORRODED AT STA 380, RBL 28 TO 59. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-8.
Part: WEB — CRACKED (BS 1348)
INSPECTION FOUND A FOUR INCH CRACK IN STIFFENER WEB INSIDE VERTICAL FIN ABOVE S-DUCT AT STA 1348. THE CRACK WAS STOPPED DRILLED, A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-40-2, 51-30-2 AND MM 51-20-11.
Part: SKIN — CRACKED (RT WING)
INSPECTION FOUND A .5 INCH CRACK IN RT WING LEADING EDGE SKIN FORWARD OF OUTBOARD SLAT CARRIAGE, NR 5 SLAT. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-10-2, 57-30-4, FIG 4 AND 9, MM 51-20-11.
Part: FLOOR BEAM — CORRODED (BS 312)
INSPECTION FOUND FLOORBEAM CORRODED AT STA 312, LBL 30. REPAIR PARTS WERE FABRICATED AND INSTALLED IAW SRM 53-10-8, 51-10-2, 51-30-4 AND MM 51-20-11.
Part: FLOOR BEAM — CORRODED (BS 1110)
INSPECTION FOUND FLOORBEAM CORRODED AT STA 1110, BL ZERO TO RBL 66. ANGLES, STRAPS, AND CORDS WERE FABRICATED AND INSTALLED IAW SRM 53-10-8, 51-30-2, AND 51-10-2.
Part: SUPPORT — CORRODED (BS 308-312)
INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 308 TO 312, LBL 30. A NEW FLOOR SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 51-40-3, 51-30-2 AND MM 51-20-151.
Part: FLOOR BEAM — CORRODED (BS 328)
INSPECTION FOUND CABIN FLOORBEAM CORRODED AT STA 328, LBL 30. THE CORRODED AREA WAS CUT OUT, A REPAIR ANGLE WAS FABRICATED AND INSTALLED IAW SRM 53-10-8, FIGURE 9.
Part: FLOOR BEAM — CRACKED (BS 335)
INSPECTION FOUND A .3750 INCH CRACK AND A .50 INCH CRACK IN FLOORBEAM U-CHANNEL AT B.S. 335, LBL 25, WL 200. THE CHANNEL WAS REMOVED. A NEW CHANNEL WAS FABRICATED AND INSTALLED IAW SRM 51-30-2, 53-40-3, AND MM 51-20-11.
Part: INTERCOSTAL — CORRODED (BS 312-340)
INSPECTION FOUND INTERCOSTAL CORRODED AT STA 312 TO 340, RBL 55. AN INTERCOSTAL WAS FABRICATED AND INSTALLED IAW SRM 51-20-1, 51-10-2 AND 51-30-2.
Part: FLOOR BEAM — CORRODED (BS 1070)
INSPECTION FOUND UPPER FLANGES OF FLOORBEAM CORRODED AT BS 1070, RBL 9 TO 12. THE CORRODED AREA WAS REMOVED. AN UPPER CHORD, SUPPORT ANGLES, FILLER AND STRAPS WERE FABRICATED AND INSTALLED IAW 53-10-8, FIGURE 1.
Part: FLOOR BEAM — CORRODED (BS 1070)
INSPECTION FOUND UPPER FORWARD FLANGE OF FLOORBEAM CORRODED AT BS 1070, RBL 47.25 TO 50.25. THE UPPER CHORD WAS REMOVED AND REPLACED IAW SRM 53-10-8. AN UPPER CHORD, SUPPORT ANGLES, FILLERS, STRAPS AND WEB DOUBLERS WERE FABRICATED AND INSTALLED IAW SRM 53-10-8.
Part: SKIN — CRACKED (WS 555)
INSPECTION FOUND A 1.5 INCH CRACK IN LEADING EDGE SKIN ABOVE NR 6 SLAT OUTBOARD TRACK OF RT WING, WS 555. THE CRACK WAS STOPPED DRILLED, A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-10-2, 51-30 AND MM 51-20-2.
Part: SKIN — CRACKED (WS WING)
INSPECTION FOUND TWO .5 INCH CRACKS IN SKIN OF RT WING TIP LOWER LEADING EDGE. THE CRACKS WERE STOP DRILLED, A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-10-1, 57-30-4 AND 51-10-2.
Part: STRINGER SPLICE — CORRODED (BS 740)
INSPECTION FOUND CORROSION ON STRINGER 27R SPLICE AT BS 740. A NEW STRINGER SPLICE WAS FABRICATED AND INSTALLED IAW SRM 53-10-3 AND 51-30-2.
Part: SHEAR TIE — CORRODED (BS 720)
INSPECTION FOUND SHEAR TIE CORRODED AT BS 720A, STRINGER 29R. A NEW SHEAR TIE WAS FABRICATED AND INSTALLED IAW SRM 51-30-2, 51-10-2 AND MM 51-20-11.
Part: SKIN — CRACKED (LT ELEVATOR)
INSPECTION FOUND FOUR CRACKS IN THE LT ELEVATOR LOWER SKIN BETWEEN STA 17.2 AND 37. THE CRACKS RANGED IN LENGTH FROM 1.12 FT TO 6. THE CRACKED SKIN WAS REMOVED AND A Z-ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-20-1 AND 51-10-2.
Part: FLOOR BEAM — CORRODED (BS 400)
INSPECTION FOUND FLOORBEAM CORRODED AT STA 400, RBL 10. A NEW FLOORBEAM WAS FABRICATED AND INSTALLED IAW SRM 53-10-8.
Part: GUSSET — CORRODED (BS 950)
INSPECTION FOUND CORRODED GUSSET AT ATTACH STRINGER 30 TO CIRCUMFERENTIAL AT CENTERLINE, STA 950B. A NEW GUSSET WAS FABRICATED AND INSTALLED IAW SRM 51-10-6, 51-10-3, 51-40-3, 51-30-2, AND 53-10-1.
Part: SUPPORT — CORRODED (BS 950)
INSPECTION FOUND FLOORBOARD SUPPORT CORRODED AT CENTERLINE ABOVE STRINGER 30, STA 950F AND STA 950E. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-40-3, 51-30-2, 51-10-2, AND 51-20-2.
Part: STRINGER — CORRODED (BS 540)
INSPECTION FOUND FORWARD CARGO STRINGER 28R AT STA 540 CORRODED. A STRINGER WAS FABRICATED AND INSTALLED IAW SRM 53-10-3.
Part: SHEAR TIE — CORRODED (BS 680)
INSPECTION FOUND CORROSION ON FRAME SHEAR TIE AT STA 680, STRINGER 28L. A NEW SHEAR TIE WAS FABRICATED AND INSTALLED IAW SRM 51-30-2.
Part: STRINGER — CORRODED (BS 480)
INSPECTION FOUND STRINGER 27R CORRODED AT STA 480. THE CORROSION WAS REMOVED AND A NEW STRINGER WAS FABRICATED AND INSTALLED IAW SRM 51-10-2, 53-10-1 AND MM 51-20-11.
Part: STRINGER — CORRODED (BS 700)
INSPECTION FOUND CORROSION ON STRINGER 27R AT STA 700. A NEW STRINGER AND ANGLE WERE FABRICATED AND INSTALLED IAW SRM 53-10-3, 51-10-2 AND 51-20-11.
Part: PANEL — CRACKED (BS 273.5)
INSPECTION FOUND A .375 INCH CRACK AT FASTENER HOLE IN TOP LEFT PANEL AT BS 273.5, LBL 14.5. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-10-2, 51-40-2, 51-20-4 AND MM 51-20-11.
Part: STRINGER — CORRODED (BS 480)
INSPECTION FOUND STRINGER 21L CORRODED AT STA 480. NEW PARTS WERE FABRICATED AND INSTALLED IAW SRM 53-10-3, FIGURE 3 AND 51-30-2.
1995
Part: SPLICE — CORRODED (BS 965)
INSPECTION FOUND STRINGER SPLICE CORRODED AT BS 965 IN AFT BAGGAGE BIN. THE CORRODED SECTION OF STRINGER WAS REMOVED. A NEW STRINGER SPLICE WAS FABRICATED AND INSTALLED IAW SRM 53-10-3. (X)
Part: LAP SEAM — CORRODED (BS 660)
INSPECTION FOUND CORROSION ON SKIN AT LAP SEAM AT BS 660 AND STR 30. THE CORROSION WAS REMOVED AND A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-30-3. (X)
Part: SKIN — CORRODED (BS 540)
INSPECTION FOUND CORROSION ON SKIN AT LAP SEAM FORWARD OF CARGO DOOR, STA 540. THE CORRODED SECTION WAS CUT OUT. A FILLER AND DOUBLER REPAIR WERE FABRICATED AND INSTALLED IAW SRM 53-30-3. (X)
Part: ACTUATOR FTG — CRACKED (NR 2 LE FLAP)
FLT NR 0219 - EWR - THE 'A' SYSTEM HYDRAULIC QUANTITY DROPPED TO ZERO ACCOMPANIED BY ILLUMINATION OF THE LOW PRESSURE LIGHTS DURING CLIMB-OUT OF EWR. 'ABNORMAL' PROCEDURES WERE COMPLIED WITH, FUEL WAS DUMPED, AND THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 2 LEADING EDGE FLAP ACUTATOR WAS REPLACED. ALL FLIGHT CONTROLS WERE CYCLED AND LEAK AND OPERATIONAL CHECKS WERE GOOD. (M)
Part: HYD PUMP — INOPERATIVE ('A' HYD SYSTEM)
FLT NR 0774 - IAH - THE 'A' SYSTEM HYDRAULIC QUANTITY WENT TO ZERO AND WAS ACCOMPANIED BY LOSS OF 'A' SYSTEM PRESSURE WHLE IN FLIGHT. THE LANDING GEAR WAS MANUALLY EXTENDED AND THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED BOTH THE NR 1 AND NR 2 ENGINE DRIVEN HYDRAULIC PUMPS. THE ENGINES WERE RUN AND LEAK AND OPERATIONAL CHECKS WERE GOOD. (W)