N58545

Part: APU — FAILED (AFT FUSELAGE)

THE APU FIRE DETECTION LOOP LIGHT ILLUMINATED AFTER TAKEOFF. THE FIRE BOTTLE WAS DISCHARGED AND THE LIGHT EXTINGUISHED. THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. THE APU COMPARTMENT WAS INSPECTED AND THERE WAS NO EVIDENCE OF FIRE FOUND. THE APU AUTO SHUTDOWN WITH A FAINT B-LOOP DETECTION LIGHT DURING TROUBLESHOOTING RUN. THE APU WAS REMOVED AND REPLACED DUE TO A SUSPECT AIR LEAK. A LEAK CHECK WAS DONE WITH NO LEAKS NOTED.

Part: ACTUATOR — OUT OF ADJUST (RT MLG)

RIGHT MAIN LANDING GEAR FAILED TO RETRACT ON TAKEOFF. FOUND MAIN LANDING GEAR ACTUATOR OUT OF ADJUSTMENT. ADJUSTED MAIN LANDING GEAR ACTUATOR IN ACCORDANCE WITH MAINTENANCE MANUAL.

Part: FRAME — CRACKED (BS 897)

INSPECTION FOUND A 1 INCH CRACK IN BELTFRAME WITH CORROSION AT STA 897, LONGERON 23L. THE CORRODED AREA WAS REMOVED, A REPAIR WAS SPLICED IN IAW SRM 53-03, FIGURE 2A.

Part: LONGERON — CRACKED (BS 756)

INSPECTION FOUND A 1 INCH CRACK IN AFT CARGO LONGERON 30 AT FORWARD BULKHEAD STA 756. REPAIRED IAW SRM 53-02, FIGURE 12.

Part: STIFFENER — CRACKED (BS 996)

INSPECTION FOUND A .25 INCH CRACK IN STIFFENER BETWEEN LONGERON 2L AND 3L AT STA 996. THE CRACK WAS STOP DRILLED AND DOUBLERS WERE INSTALLED IAW SRM 53-01, FIGURE 2.

Part: ANGLE — CRACKED (BS 680)

INSPECTION FOUND A 2.5 INCH CRACK IN FLOOR ATTACH ANGLE AT STA 680. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-30-5.

Part: LONGERON — CRACKED (BS 256)

INSPECTION FOUND A .5 INCH CRACK IN LONGERON 17R AT STA 256. REPAIR SPLICES WERE INSTALLED IAW SRM 53-02, FIGURE 2.

Part: LONGERON — CRACKED (BS 960)

INSPECTION FOUND A 1 INCH CRACK IN LONGERON 17R AT STA 960. A NEW LONGERON SECTION WAS SPLICED IN IAW SRM 53-02, FIGURE 2.

Part: SUPPORT — CRACKED (BS 680)

INSPECTION FOUND A .25 INCH CRACK IN FLOOR SUPPORT FOR LEFT INBOARD FLOOR AT STA 680. THE FLOOR SUPPORT WAS REPLACED IAW SRM 53-11-3.

Part: LONGERON — CRACKED (BS 237)

INSPECTION FOUND A .25 INCH CRACK IN LONGERON 17L AT STA 237. A NEW LONGERON SECTION AND SPLICE SECTION WERE INSTALLED IAW SRM 53-02, FIGURE 2.

Part: ANGLE — CRACKED (BS 756)

INSPECTION FOUND A .5 INCH CRACK IN AFT CARGO L-ANGLE AT STA 756 LONGERON 28L AND A .5 INCH CRACK IN L-ANGLE AT STA 756 LONGERON 26L. THE ANGLES WERE REPLACED IAW SRM 51-30-0.

Part: SPLICE — CRACKED (BS 416-418)

INSPECTION FOUND A .5 INCH CRACK IN LONGERON 29L SPLICE BETWEEN STA 416 AND 418. A NEW SPLICE WAS INSTALLED IAW SRM 51-30-5.

Part: LONGERON — CORRODED (BS 230-235)

INSPECTION FOUND LONGERON 28L CORRODED BETWEEN STA 230 TO 235. A NEW LONGERON SECTION WAS SPLICED IN IAW SRM 53-02, FIGURE 2.

Part: ANGLE — CRACKED (BS 658)

INSPECTION FOUND A .25 AND 1.5 INCH CRACK IN FLOOR SUPPORT ANGLE UNDER SEAT TRACK AT STA 658. THE FLOOR SUPPORT ANGLE WAS REPLACED IAW SRM 51-30-5.

Part: SKIN — DAMAGED (BS 69)

THE AIRCRAFT STRUCK A FLOCK OF BIRDS DURING CLIMBOUT BETWEEN 2,500 TO 3,000 FEET. THE AIRCRAFT WAS RETURNED TO CLE. MAINTENANCE DISCOVERED IMPACT DAMAGE TO FUSELAGE SKIN, APPROXIMATELY 2 FEET BY 2 INCHES IN AREA, TWO FEET AFT OF RADOME ON LT FORWARD LOWER SKIN PANEL AT STA 69. THE AREA WAS REPAIRED IAW ECRA 5330-02468 AND A DIP WAS ISSUED FOR ONE YEAR EVALUATION BY DACO ENGINEERING. IN ADDITION, CABIN WINDOWS NR 1, NR 2 AND NR 3 ON LT SIDE WERE REPLACED DUE TO DAMAGE CAUSED BY THE BIRD STRIKE. LEAK CHECK WAS GOOD IAW MM 56-20-00. THE NR 1 ENGINE WAS BORESCOPED AND NO DAMAGE WAS FOUND.

Part: UPLOCK SPRING — BROKEN (RT MLG DOOR)

IAH - FLT 1453 - THE GEAR DOOR OPEN LIGHT ILLUMINATED IN-FLIGHT WITH HYDRAULIC SYSTEM ON LOW. A GEAR UPLATCH CHECK WAS PERFORMED AND THE LIGHT EXTINGUISHED AND REMAINED OUT. MAINTENANCE FOUND RT MLG DOOR UPLATCH MECHANISM SPRING BROKEN. THE MECHANISM WAS REMOVED AND THE SPRING WAS REPLACED. THE MECHANISM WAS REINSTALLED IAW MM 32-31-4. AN EXTENSION AND RETRACTION FOR THE LANDING GEAR WAS PERFORMED IAW MM 32-30-0, CODE 1 AND OPERATION CHECKED GOOD. (X)

Part: SKIN — CRACKED (BS 996)

IAH - INSPECTION FOUND A .1250 INCH CRACK IN SKIN AT STATION 996 BETWEEN LONGERONS 9 AND 10R. A REPAIR WAS FABRICATED AND INSTALLED IN REFERENCE TO DAC DRAWING J060138 AND EA 5361-01001. (M)