N73243

Part: WEB — CRACKED (BS 664)

INSPECTION FOUND A CRACK IN LT MLG WHEEL WELL UPPER PRESSURE WEB AT LT FORWARD CORNER JUST AFT OF STA 664. LENGTH OF CRACK NOT IDENTIFIED. THE WEB WAS REMOVED AND A NEW PART WAS FABRICATED AND INSTALLED IAW SRM 51-30-2, 51-10-2, AND 53-10-2, FIGURE 3.

Part: SKIN — CREASED (CARGO DOOR)

INSPECTION FOUND AFT CARGO DOOR EXTERNAL SKIN CREASED AND OIL CANNED. THE DAMAGED AREA WAS REMOVED, A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 52-00-3 FIGURE 6, 52-30-3 AND 51-10-6.

Part: SUPPORT — CORRODED (BS 887)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT FS 887, RBL 60. THE CORRODED AREA WAS REMOVED, REPAIR PARTS WERE FABRICATED AND INSTALLED IAW SRM 51-40-3, 51-30-2, 51-10-2 AND 53-10-2.

Part: AIR DATA COMP — CONTAMINATED (E/E COMPT)

THE ACFT EXPERIENCED INTERMITTENT ROLL OF NO MORE THAN 10 DEGREES UNCOMMANDED WITH BOTH AUTOPILOT A ANDB SELECTED WHILE EN ROUTE. PITCH MODE FUNCTIONED NORMALLY. MAINTENANCE PERFORMED A GROUND TEST OF BOTH AUTOPILOT SYSTEMS. THE A-SYSTEM WAS TOTALLY INOPERATIVE IN ROLL. INSPECTION FOUND LOOSE PINS ON SOME PITCH AND ROLL COMPUTER CONNECTORS. THE ROLL COMPUTER WAS REMOVED AND REPLACED DUE TO FAILURE OF SELF TEST. THE AIRCRAFT HAS CONTINUED TO HAVE ROLL RELATED PROBLEMS ON SUBSEQUENT FLIGHTS. *S/D* IN A SUBSEQUENT PROBLEM THE AIR DATA COMPUTER WAS REPLACED. SHOP FINDINGS REVEALED LIQUID CONTAMINATION IN THE ADC. AN INSPECTION OF THE E AND E COMPARTMENT DRIP PAN AND SHROUDS INSTALLATION, REVEALED THAT THE

Part: ENGINE — OIL LEAK (NR 2)

THE NR 2 ENGINE OIL PRESSURE AND QUANTITY DROPPED ON TAKEOFF. THE DROP IN PRESSURE AND QUANTITY WAS ACCOMPANIED BY ILLUMINATION OF THE LOW OIL PRESSURE LIGHT. THE AIRCRAFT WAS RETURNED TO CLE WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 2 ENGINE COWLING COVERED WITH OIL AND THE OIL STRAINER COVER WAS CRACKED. THE NR 2 ENGINE WAS REMOVED AND REPLACED. THE SDR WILL REMAIN OPEN FOR PART INFORMATION PENDING INVESTIGATION. *S/D* SHOP FINDINGS REPORTED THAT THE OIL FILTER HOUSING, WHICH HAD BEEN SUSPECT, HAD NO CRACK. THE ENGINE TESTED GOOD AND A BEARING INSPECTION WAS PERFORMED WITH NO DISCREPANCIES NOTED. THE SOURCE OF OIL LEAKAGE WAS NOT CONFIRMED.

Part: BATTERY PACK — DISCHARGED (CABIN)

FLT NR 1626 - CLE - INSPECTION FOUND BOTH THE INTERIOR AND EXTERIOR EMERGENCY LIGHTS AT RIGHT WING EMERGENCY EXIT INOPERATIVE. THE CHARGER AND BATTERY PACK WERE REMOVED AND THE CONNECTIONS TO BOTH WERE CLEANED. EXTERIOR SOCKET WAS RELAMPED AND OPERATION OF THE LIGHTS WAS GOOD. (M)

Part: FIREWALL — CRACKED (NR 2 ENGINE)

IAH - INSPECTION FOUND THE NR 2 ENGINE PYLON FIREWALL PAN HAD A 2.5 INCH CRACK THROUGH FOUR FASTENERS AT NAC STATION 144. A DOUBLER WAS INSTALLED IAW ECRA 5450-01139. A DIP WAS ISSUED TO REINSPECT THE AREA AT LPV CHECKS AND PERMANENTLY REPAIR PAN AT NEXT 1/4D-CHECK. (M)

Part: TURB BLADE — BROKE (NR 2 ENGINE)

FLT NR 1930 - IAH - THE NR 2 ENGINE SHUDDERED AND THEN BEGAN TO LOSE POWER DURING CLIMB-OUT OF IAH. THE NR 2 ENGINE WAS SHUT DOWN AND THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. THE NR 2 ENGINE WAS REMOVED AND REPLACED. INVESTIGATION REVEALED A FIRST STAGE TURBINE BROKEN ABOOUT .5 INCH FROM THE TIP. (M)

Part: ANGLE — CORRODED (BS 323-328)

GSO - INSPECTION FOUND T-ANGLE CORRODED AT STA 323 - STA 328, RT SIDE. A NEW T-ANGLE, SPLICES, AND DOUBLER WERE INSTALLED IAW ECRA 5330-02337. (X)

Part: ANGLE — CORRODED (BS 323)

GSO - INSPECTION FOUND T-ANGLE CORRODED AT STA 323, S27L TO S27R. A NEW T-ANGLE WAS INSTALLED IAW SRM 51-30-2. (X)

Part: DOUBLER — CORRODED (BS 323)

GSO - INSPECTION FOUND DOUBLER CORRODED AT STA 323, STR 27L. A REPAIR DOUBLER WAS INSTALLED IAW ECRA 5330-02337. (X)

Part: SKIN — CORRODED (BS 290)

GSO - INSPECTION FOUND RT FUSELAGE SKIN PANEL CORRODED AT STA 290. THE SKIN PANEL WAS REMOVED AND REPLACED IAW SRM 51-30-2. (X)

Part: PANEL — CRACKED (STA 277)

GSO - INSPECTION FOUND A 4 INCH CRACK IN NOSE WHEELWELL CEILING PRESSURE PANEL AT STA 277, RT SIDE. THE CRACK WAS STOP DRILLED. A REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW EC 5310-03186. (X)

Part: HYD PUMP — INOPERATIVE (NR 2 ENGINE)

FLT NR 1746 - GSO - THE HYDRAULIC QUANTITY INDICATOR GAUGE DECREASED SLOWLY TO ZERO WITH NO OTHER INDICATIONS WHILE ON APPROACH TO GSO. THE AIRCRAFT LANDED AT GSO WITHOUT INCIDENT. THE NR 2 ENGINE DRIVEN HYDRAULIC PUMP WAS REMOVED AND REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED AND THE ENGINE WAS RUN WITH NO LEAKS NOTED. (M)

Part: HYD PUMP — LEAKING (NR 2 ENGINE)

GSO - FLT 1275 - THE A-SYSTEM HYDRAULIC QUANTITY DECREASED TO ZERO DURING CLIMB-OUT OF GSO. THE FLUID LOSS WAS ACCOMPANIED BY ILLUMINATION OF THE A-HYDRAULIC SYSTEM LOW PRESSURE LIGHTS. A MANUAL GEAR AND FLAP EXTENSION WAS PERFORMED AND THE AIRCRAFT WAS RETURNED TO GSO WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 2 ENGINE DRIVEN HYDRAULIC PUMP LEAKING. THE NR 2 PUMP WAS REMOVED AND REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED TO FULL. LEAK AND OPERATIONAL CHECKS WERE GOOD. (X)

Part: FIRE WARNING — ACTIVATED (APU)

EWR - FLT 1452 - WHEN THE APU WAS STARTED ON APPROACH, THE APU FIRE WARNING LIGHT AND BELL ACTIVATED. THE APU WAS SHUTDOWN, THE APU FIRE BOTTLE WAS DISCHARGED AND THE FIRE WARNING CEASED. THE ACFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND NO EVIDENCE OF FIRE. THE APU AND APU FIRE DETECTION SYSTEM WERE PLACARDED INOPERATIVE. THE SDR WILL REMAIN OPEN FOR PART INFORMATION PENDING CORRECTIVE ACTION. THE WIRING AND CONNECTORS ON APU FIRE DETECTION SYSTEM CHECKED GOOD. NO DEFECTS WERE FOUND. OPERATION OF THE FIRE DETECTION SYSTEM AND APU CHECKED GOOD. THE APU FIRE BOTTLE WAS REPLACED AND THE PLACARD WAS REMOVED. (W)