N69803

Part: SKIN — CRACKED (STA 1401) · airframe 55,949 hrs · 26,235 cycles

INSPECTION FOUND A 1/2" CRACK IN R/H FUSELAGE SKIN JUST ABOVE ENGINE PYLON AT STA 1401. A DOUBLER WAS INSTALLED IAW SRM 53-04.

Part: THRESHOLD — DENTED (CARGO BAY)

INSPECTION FOUND FORWARD CARGO DOOR THRESHOLD DENTED. REPAIRED IAW ECRA 5310-03953.

Part: SCUFF PLATE — TORN (BS 1133 - 1191)

INSPECTION FOUND AFT PIT DOOR SCUFF PLATE TORN AT ONE CORNER AND EDGES DAMAGED AT FS 1133-1192, LONGERON 27R. THE DAMAGED AREA WAS TRIMMED OUT IAW SRM 51-10-4. A REPAIR DOUBLER WAS INSTALLED IAW SRM 52-01, FIGURE 2, 51-30-2, AND ECRA 5310-03947.

Part: PAN — GOUGED (CARGO DOOR)

INSPECTION FOUND AFT CARGO DOOR SEAL FLANGE GOUGED AND BENT AT STOPS. AN ANGLE REPAIR WAS INSTALLED ON AFT CARGO DOOR AFT EDGE OF PAN IAW ECRA 5230-01494.

Part: SKIN — GOUGED (RT LE FLAP)

INSPECTION FOUND RT WING NR 3 FLAP LEADING EDGE BULL NOSE GOUGED. REPAIRED IAW ECRA 5750-03318 AND INSTALLED NEW CHAFE STRIP IAW SRM 51-30-2.

Part: SKIN — CORRODED (BS 1155)

INSPECTION FOUND AFT FUSELAGE LOWER SKIN CORRODED AT AREA UNDER LOWER ANTENNA, FS 1155. THE AREA WAS REPAIRED IAW SRM 51-10-3 AND 53-04, FIGURE 38A.

Part: SKIN — CRACKED (APU DOOR)

INSPECTION FOUND A 2 INCH CRACK WITH GOUGE IN APU DOOR OUTER SKIN. A DOUBLER WAS INSTALLED IAW SRM 52-01, FIGURE 2, 51-10-3, AND 52-10, FIGURE 2.

Part: SLAT — DENTED (RT LE FLAP)

INSPECTION FOUND RT WING NR 0 SLAT END LEADING EDGE DENTED AT STA XFS 55. THE DENT WAS BLENDED OUT AND REPAIRED WITH FILLER IAW SRM 57-03, FIGURE 14B.

Part: SKIN — GOUGED (LT WING)

INSPECTION FOUND THE LT WING LOWER SKIN SURFACE ADJACENT TO FUEL PANEL 1373C GOUGED. THE SKIN WAS REPAIRED IAW EA 9-5731-2-A0530 AND ECRA 5730-01669.

Part: COWL — CORRODED (NR 2 ENGINE)

INSPECTION FOUND CORROSION ON INLET SKIN OF NR 2 NOSE COWL INSIDE FRONT ACCESS. THE NOSE COWL WAS REMOVED AND REPLACED IAW MM 71-10-01.

Part: SKIN — DENTED (CARGO DOOR)

INSPECTION FOUND AFT CARGO DOOR OUTER SKIN AFT EDGE DENTED. A REPAIR DOUBLER WAS INSTALLED IAW SRM 52-05, FIGURE 1, 52-32-0, AND 51-10-3.

Part: BRACKET — CRACKED (CARGO DOOR)

INSPECTION FOUND A 1 INCH CRACK IN INTERNAL SUPPORT BRACKET AT FORWARD CARGO DOOR LOWER FORWARD DOOR STOP. THE SUPPORT BRACKET WAS REMOVED AND A NEW BRACKET WAS INSTALLED IAW SRM 51-30-2 AND 51-30-5.

Part: FITTING — CORRODED (BS 218)

INSPECTION FOUND G-2 GALLEY FITTING CORRODED AFTER REMOVAL OF RT O/B SEAT TRACK AT STA 218. THE FITTING WAS REMOVED AND REPLACED IAW SRM 51-10-2.

Part: SEAT TRACK — CORRODED (BS 218)

INSPECTION FOUND CABIN RT CENTER SEAT TRACK CORRODED AT STA 218, RBL 24. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-1 AND 53-05, FIGURE 4F.

Part: WEB — CRACKED (BS 218)

INSPECTION FOUND A .5 INCH CRACK IN CUSP WEB AT STA 218. THE CRACK WAS STOP DRILLED IAW SRM 53-10, FIGURE 2. A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-01, FIGURE 2 AND 51-10-4.

Part: SUPPORT — CRACKED (BS 200)

INSPECTION FOUND A 3 CRACK AND CORROSION ON FORWARD CARGO FLOOR SUPPORT AT FORWARD BULKHEAD, STA 200. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-30-1.

Part: BRACKET — CRACKED (CARGO DOOR)

INSPECTION FOUND A 1 CRACK IN MID CARGO DOOR BRACKET AT LOWER END OF FORWARD STIFFENER. THE BRACKET WAS REMOVED AND A NEW BRACKET WAS INSTALLED IAW SRM 51-30-2 AND 52-33-0, FIGURE 1.

Part: ANGLE — CRACKED (VERT STAB)

INSPECTION FOUND A 1 CRACK IN ANGLE AT BASE OF LT LOWER AFT SIDE VERTICAL STABILIZER. FILLER AND DOUBLER WERE INSTALLED IAW SRM 53-05, FIGURE 23A.

Part: LONGERON — CORRODED (BS 110)

INSPECTION FOUND LONGERON 30 AT FS 110 CORRODED. THE LONGERON WAS REMOVED AND REPLACED IAW SRM 51-10-01.

Part: SUBFLOOR — CORRODED (BS 148-158)

INSPECTION FOUND SUBFLOOR CORRODED AT STA 148-158, RBL 44 TO RBL 54. THE CORRODED AREA WAS REMOVED IAW SRM 51-10-3, SHEET 3. A DOUBLER REPAIR WAS INSTALLED IAW SRM 53-01, FIGURE 4, 53-14-1, FIGURE 11, 51-30-5, AND 51-30-8.

Part: ANGLE — CORRODED (BS160)

INSPECTION FOUND FORWARD SERVICE DOOR CLOSEOUT PANEL LOWER ATTACH ANGLES CORRODED AT STA 160, RBL 52. THE ANGLES WERE REMOVED AND REPLACED IAW SRM 51-10-4 AND 53-14-1, FIGURE 11.

Part: SEAT TRACK — CORRODED (BS 1136-1240)

INSPECTION FOUND LT CENTER SEAT TRACK CORRODED FROM STA 1136-1240, LBL 12. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 53-05, FIGURE 4F, 51-10-3, 51-30-1, AND 51-30-5.

Part: SKIN — DENTED (RUDDER)

INSPECTION FOUND LT UPPER RUDDER SKIN DENTED. THE DENTED AREA WAS CUT OUT IAW SRM 53-03. A DOUBLER REPAIR WAS INSTALLED IAW SRM 55-03, FIGURE 11.

Part: SKIN — BROKEN (HORIZ STAB)

INSPECTION FOUND UPPER LT HORIZONTAL STABILIZER BANANA PANEL SKIN AND DOUBLER BROKEN. THE DAMAGED AREA WAS REMOVED. A DOUBLER AND FILLER WERE INSTALLED IAW SRM 55-03, FIGURE 17, 51-10-3, AND 51-10-4.

Part: ANGLE — CORRODED (BS 160-200)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 160-200, LBL 54. THE ANGLE WAS REMOVED AND A NEW ANGLE WAS INSTALLED IAW SRM 51-10-4, 51-10-2, 51-30-2, AND 51-30-5.

Part: STRINGER — CRACKED (BS 500)

INSPECTION FOUND A 1 INCH CRACK IN STRINGER 16L AT BS 500C. A STRINGER SPLICE REPAIR WAS INSTALLED IAW SRM 53-00-03, FIGURE 201.

Part: ANGLE — CRACKED (VERT STAB)

INSPECTION FOUND A .625 INCH CRACK IN LT VERTICAL STABILIZER ANGLE 37.5 INCHES AFT OF STA 1089.5. REPAIRED IAW SRM 55-02, FIGURE 26.

Part: SKIN — CRACKED (RT WING)

INSPECTION FOUND A 1.9 CRACK IN RT WING LEADING EDGE SKIN AT ACCESS PLATE FOR NR 8 SLAT TRACK. A REPAIR WAS INSTALLED IAW ECRA 5720-01616.

Part: BELTFRAME — CORRODED (BS 1322)

INSPECTION FOUND BELTFRAME LOWER FLANGE CORRODED AT STA 1322, L27L TO L27R. BELTFRAME AND DOUBLERS WERE FABRICATED AND INSTALLED IAW SRM 53-03 AND ECRA 5310-03607.

Part: FITTING — CORRODED (RT MLG)

INSPECTION FOUND RT MLG RETRACT ACTUATOR UPPER ATTACH FITTING (COKE BOTTLE FITTING) CORRODED WITH .125 PLAY. THE COKE BOTTLE FITTING AND BUSHINGS WERE REMOVED AND THE LIGHT CORROSION WAS REAMED OUT PER OHM 57-40-01. A DYE CHECK WAS PERFORMED AND FOUND OK. BUSHINGS AND A RETRACT FITTING WERE FABRICATED AND INSTALLED PER OHM 57-40-01, PAGE 508.

Part: CABLE — FRAYED (TAIL CONE)

THE FORCE REQUIRED TO DROP TAIL CONE USING THE INTERIOR RELEASE HANDLE EXCEEDED 40 POUNDS. THE TAIL CONE FAILED TO DISENGAGE USING THE PASSENGER AFT ENTRANCE DOOR RELEASE MECHANISM. INSPECTION FOUND LT UPPER SECTION OF TAIL CONE RELEASE CABLE WORN AND FRAYED. THE CABLE WAS REPLACED, TAILCONE CABLES WERE ADJUSTED IAW MM 53-53-00 AND OPERATIONAL CHECK WAS GOOD.

Part: DOOR JAMB — CORRODED (CARGO COMPT)

INSPECTION FOUND MAIN BAGGAGE BIN LOWER DOOR JAMB CORRODED. THE LOWER DOOR JAMB BEAM WAS REMOVED AND REPLACED IAW SRM 53-05, FIGURE 63, SHEETS 1-4.

Part: FRAME — CORRODED (BS 1309)

INSPECTION FOUND LOWER FLANGE OF BELTFRAME CORRODED AT STA 1309, L28L TO L28R. THE FRAME WAS REPAIRED IAW SRM 53-03, FIGURE 2A, PAGE 4A.

Part: DOOR PAN — CORRODED (FWD BAGG BIN)

INSPECTION FOUND FORWARD BAGGAGE BIN DOOR FRAME PAN CORRODED. THE CORRODED SECTION OF PAN WAS REMOVED. A NEW SECTION OF PAN WAS INSTALLED IAW SRM 53-05, FIGURE 44.

Part: BATTERIES — DISCHARGED (CABIN)

INSPECTION FOUND EMERGENCY OVERHEAD AISLE LIGHT AT ROW 26 AND 28 INOPERATIVE. THE BATTERIES IN BATTERY PACK WERE REMOVED AND REPLACED.

Part: BRAKE LIMITER — LEAKING (LEFT)

THE LT HYDRAULIC SYSTEM QUANTITY DEPLETED DURING CLIMBOUT. THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE LT HYDRAULIC SYSTEM BRAKE FLUID QUANTITY LIMITER FAILED. THE BRAKE FLUID QUANTITY LIMITER WAS REMOVED AND REPLACED. THE LEFT HYDRAULIC SYSTEM WAS SERVICED TO FULL AND LEAK CHECK WAS GOOD. THE NR 1 AND NR 2 BRAKES WERE BLED, SYSTEM PRESSURE CHECKED NORMAL.

Part: COALESCER BAG — DIRTY (LT/RT PACKS)

A STRONG ODOR WAS OBSERVED TEMPORARILY IN THE CABIN DURING TAKEOFF AND CLIMB. THE ODOR DISAPPEARED AFTER SEVERAL MINUTES. THE FLIGHT WAS CONTINUED WITHOUT FURTHER PROBLEM. MAINTENANCE REMOVED AND REPLACED BOTH WATER SEPARATOR BAGS. THE ENGINES WERE RUN WITH ALL BLEED SOURCES USED AND NO ODOR WAS DETECTED.

Part: PRESS LINE — CRACKED (RT TR UNIT)

THE RT HYDRAULIC SYSTEM PRESSURE TEMPORARILY WENT TO ZERO UPON GEAR EXTENSION FOR LANDING AT IAH. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE HYDRAULIC QUANTITY AT ZERO. THE RT THRUST REVERSER CONTROL VALVE HYDRAULIC PRESSURE LINE WAS FOUND CRACKED. AN INTERIM FLEX LINE WAS INSTALLED AND A DIP WAS ISSUED TO REPLACE THE FLEX LINE WITH A PERMANENT LINE WITHIN 1200 HOURS OR 500 FLIGHTS, WHICHEVER OCCURS FIRST. LEAK CHECKS WERE GOOD.

Part: PAN — CRACKED (BAGG DOOR)

HOU - INSPECTION FOUND A 1.75 INCH CRACK IN UPPER PAN OF MAIN BAGGAGE BIN DOOR. THE CRACK WAS STOP DRILLED AND A DOUBLER WAS INSTALLED IAW SRM 52-03, FIGURE 1, AND ECRA 5230-01291. (X)

Part: INTERCOSTAL — CRACKED (BS 1271-1287)

HOU - INSPECTION FOUND A .75 INCH CRACK IN INTERCOSTAL AT NUTPLATE IN AFT BAGGAGE BIN CEILING, STA 1271 TO STA 1287. A REPAIR WAS INSTALLED PER SRM 53-01. (X)

Part: SUPPORT — CRACKED (WING)

HOU - INSPECTION FOUND UPPER WING PANEL T-SUPPORT CRACKED IN HALF. THE T-SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-30-5. (X)

Part: PAN — CRACKED (BAGG DOOR)

HOU - INSPECTION FOUND A 2.5 INCH CRACK IN PAN OF FORWARD BAGGAGE BIN DOOR ON AFT SIDE AT LATCH. THE PAN WAS REPAIRED PER ECRA 5261-01000. (X)

Part: ANGLE — CRACKED (FWD SERVICE DR)

HOU - INSPECTION FOUND THE FORWARD SERVICE DOOR UPPER FORWARD CORNER INTERNALLY CRACKED THROUGH ACROSS RADIUS OF ANGLE. THE CRACK WAS 1.5 INCHES LONG. A NEW ANGLE WAS INSTALLED IAW SRM 51-30-5. (X)

Part: ACTUATOR — INOPERATIVE (APU)

FLT NR 0594 - EWR - THE APU AUTO SHUT DOWN IN FLIGHT AND CONTINUED TO WINDMILL 8-10 PERCENT AFTER MASTER SWITCH WAS TURNED OFF. MAINTENANCE REMOVED AND REPLACED BENT NON-RAM DOOR ACTUATOR PER MM 49-10-00. AN OPERATIONAL CHECK WAS PERFORMED AND NO DEFECTS WERE NOTED. (M)

Part: OIL PRESS LIGHT — MALFUNCTIONED (APU)

FLT NR 0200 - IAH - WHILE OPERATING THE APU IN FLIGHT, WITH THE LEFT GENERATOR PLACARDED INOPERATIVE, THE APU LOW OIL PRESSURE LIGHT ILLUMINATED. THE APU WAS SHUT DOWN AND THE FLIGHT WAS COMPLETED WITHOUT ANY FURTHER PROBLEM. MAINTENANCE CHECKED THE APU OIL LEVEL AND FOUND IT TO BE FULL. THE APU WAS STARTED AND RAN WITHOUT FAULT. THE FAILURE COULD NOT BE DUPLICATED. (M)

Part: EEL BATTERIES — DISCHARGED (CABIN)

IAH - FLT 0138 - INSPECTION FOUND EMERGENCY EXIT LIGHTS SWITCH ON, RESULTING IN DEAD BATTERIES. THE BATTERIES FOR ALL INTERIOR EMERGENCY LIGHTS WERE REPLACED AND OPERATION CHECKED GOOD. (X)

Part: PROX SENSORS — INOPERATIVE (MLG DOORS)

CLE - FLT 1718 - MAIN LANDING GEAR DOORS WOULD NOT RETRACT AFTER GEAR EXTENDED FOR LANDING AT CLE. THE LANDING GEAR DOOR OPEN LIGHT ILLUMINATED AND CREW CONFIRMED THE DOORS WERE DOWN BY A VISUAL CHECK THROUGH THE VIEW PORTS. 'ABNORMAL' PROCEDURES WERE FOLLOWED AND THE AIRCRAFT LANDED WITH GEAR DOORS DOWN. MAINTENANCE FOUND LT MLG DOOR DAMAGED. THE LT MLG DOOR WAS REMOVED AND REPLACED. BOTH MLG DOOR PROXIMITY SENSORS WERE REMOVED AND REPLACED. GEAR INDICATIONS AND OPERATION CHECKED GOOD. (X)