N44214

Part: HYDRAULIC LINE — LEAKING (RT ENG PYLON)

THE A-SYSTEM HYDRAULIC QUANTITY BEGAN TO DROP DURING CLIMBOUT. THE AIRCRAFT WAS RETURNED TO CLE WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND HYDRAULIC SUPPLY FLEX LINE IN RIGHT ENGINE PYLON AREA LEAKING. THE LINE WAS REMOVED AND REPLACED AND LEAK CHECKS WERE GOOD.

Part: HYD LINE — LEAKING (NR 2 ENGINE)

THE A HYDRAULIC SYSTEM QUANTITY AND PRESSURE DROPPED TO ZERO ON DESCENT INTO EWR. THE A SYSTEM PUMPS WERE TURNED OFF AND THE HYDRAULIC LOSS CHECKLIST WAS ACCOMPLISHED. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE RT ENGINE A SYSTEM PRESSURE LINE LEAKING. THE LINE WAS REPLACED USING FLEX LINE. A DIP WAS ISSUED TO REPLACE THE FLEX LINE WITHIN 500 FLIGHTS OR 1200 FLIGHT HOURS, WHICHEVER COMES FIRST.

Part: SKIN — CRACKED (C2 DOOR CUTOUT)

INSPECTION FOUND A 1 INCH CRACK AT AFT LOWER CORNER OF C-2 DOOR AFT CUTOUT. THE CRACKED AREA WAS CUT OUT AND FILLER AND DOUBLERS WERE INSTALLED IAW ECRA 5330-02460.

Part: BULKHEAD SKIN — CRACKED (BS 178)

INSPECTION FOUND A 6 INCH AND 7 INCH CRACK IN SKIN AT B.S. 178 BULKHEAD. THE CRACKED AREA WAS CUT OUT. DOUBLER AND FILLERS WERE FABRICATED AND INSTALLED IAW SRM 51-30-2 AND SRM 53-10-11.

Part: SHEAR WEB — CRACKED (BS 664)

INSPECTION FOUND A 1 INCH CRACK IN INBOARD RADIUS OF SHEAR WEB AT S18A, LT B.S. 664. NEW REPAIR ANGLES WERE INSTALLED IAW BOEING DRAWING NR 65C29228 AND SRM 51-30-2.

Part: BULKHEAD SKIN — CRACKED (BS 178)

INSPECTION FOUND A .50 INCH CRACK IN STA 178 BULKHEAD SKIN AT WL 233.5 AND A 6 INCH CRACK WAS FOUND AT HORIZONTAL STIFFENER AT WL 218, RT SIDE. THE CRACKED AREAS WERE CUT OUT. FILLERS AND DOUBLERS WERE FABRICATED AND INSTALLED IAW SRM 53-10-11 AND SRM 51-10-2.

Part: SKIN — CRACKED (C2 DR CUTOUT)

INSPECTION FOUND A 1 INCH CRACK IN INBOARD SKIN AT LOWER AFT CORNER OF C-2 DOOR CUTOUT. THE CRACKED SECTION OF SKIN WAS REMOVED. A DOUBLER AND TRIPLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-10-2, 51-30-2, AND ENGINEERING ORDER REO-02348.

Part: BULKHEAD SKIN — CRACKED (BS 178)

INSPECTION FOUND A 6.5 INCH CRACK IN STA 178 BULKHEAD SKIN PANEL ALONG HORIZONTAL STIFFENER AT WL 218, ON LT SIDE. THE CRACKED AREA WAS CUT OUT. A FILLER AND DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-10-11 AND SRM 51-10-2.

Part: FRAME — CRACKED (BS 520)

INSPECTION FOUND A 1 INCH CRACK THROUGH NUTPLATE HOLE AT LOWER AFT CORNER OF LT STA 520 WING TO BODY ATTACH FRAME. THE FASTENERS AND EXISTING ANGLE WERE REMOVED. AN ATTACH ANGLE, REPAIR ANGLE, AND CLIPS WERE FABRICATED AND INSTALLED IAW ECRA 5350-01227, SRM 51-10-2, AND SRM 51-30-2.

Part: HYDRAULIC LINE — CHAFED (LT MLG WW)

EWR - FLT 0674 - THE B-HYDRAULIC SYSTEM LOW QUANTITY ILLUMINATED ON APPROACH TO DWR. THE 'A' AND 'B' SYSTEMS REMAINED AT 3,000 PSI WITH 2 GALLONS QUANTITY. THE GEAR AND FLAPS EXTENDED NORMALLY. THE QUANTITY WENT TO 1 GALLON WITH T/R ACTIVATED AND RETURNED TO 1.8 GALLONS WHERE IT REMAINED. ACFT LANDED WITHOUT INCIDENT. B-SYSTEM PRESSURE WENT TO ZERO AT THE GATE. MAINTENANCE FOUND AN A-SYSTEM PRESSURE LINE AND A B-SYSTEM SPOILER LINE, BOTH IN THE LT MLG WHEELWELL, CHAFED. BOTH LINES WERE REPLACED. PRESSURE AND LEAK CHECKS WERE GOOD. THE HYDRAULIC SYSTEM WAS SERVICED TO FULL. (X)

Part: HYD LINE — LEAKING (A-HYD SYSTEM)

BUF - FLT 1420 - AIRCRAFT LOST A-SYSTEM HYDRAULIC QUANTITY WHILE EN ROUTE FROM EWR TO BUF. THE AIRCRAFT LANDED IN BUF WITHOUT INCIDENT. MAINTENANCE FOUND THE HYDRAULIC PRESSURE LINE AT SYSTEM 'A' MODULAR UNIT LEAKING. THE PRESSURE LINE WAS REMOVED AND REPLACED. IN ADDITION, BOTH ENGINE DRIVE HYDRAULIC PUMPS WERE REMOVED AND REPLACED AS A PRECAUTIONARY MEASURE. AN ENGINE RUN WAS PERFORMED WITH ALL FLIGHT CONTROLS OPERATED AND THE GEAR HANDLE CYCLED. LEAK AND OPERATIONAL CHECKS WERE GOOD. (X)

Part: HYD LINE — CHAFED (A HYD SYSTEM)

FLT NR 1036 - GSO - THE 'A' HYDRAULIC SYSTEM FLUID QUANTITY DROPPED TO ZERO WHILE EN ROUTE FROM BNA TO EWR. A MANUAL GEAR EXTENSION WAS PERFORMED AND THE AIRCRAFT WAS DIVERTED TO GSO WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE HYDRAULIC LINE IN LEFT WING ROOT CHAFED. THE HYDRAULIC LINE WAS REMOVED AND REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED TO FULL AND LEAK CHECK WAS GOOD. (M)

Part: HYD LINE — LEAKING ('A' HYD SYSTEM)

FLT NR 1069 - TPA - THE 'A' HYDRAULIC SYSTEM WAS LOST WHILE IN FLIGHT WITH THE QUANTITY GAUGE INDICATING ZERO. THE AIRCRAFT LANDED AT TPA WITHOUT INCIDENT. MAINTENANCE FOUND FLEX LINE TO 'A' HYDRAULIC SYSTEM PRESSURE MODULE LEAKING. THE LINE WAS REPLACED USING ORIGINAL EQUIPMENT RIGID LINE. THE HYDRAULIC SYSTEM WAS SERVICED TO FULL AND LEAK CHECKS WERE GOOD. (M)

Part: HYD LINE — CHAFED ('A' HYD SYSTEM)

FLT NR 1069 - TPA - AIRCRAFT LOST THE 'A' SYSTEM HYDRAULICS WHILE EN ROUTE FROM GSO TO TPA. QRH CHECKLIST PROCEDURES WERE ACCOMPLISHED AND THE AIRCRAFT LANDED AT TPA WITHOUT INCIDENT. MAINTENANCE FOUND 'A' SYSTEM HYDRAULIC PRESSURE LINE ABOVE LEFT MLG CHAFED THROUGH. A FLEX LINE WAS INSTALLED AND A DIP WAS ISSUED TO REPLACE THE FLEX LINE WITHIN 500 FLIGHTS OR 1200 HOURS, WHICHEVER COMES FIRST. LEAK CHECK OF THE HYDRAULIC SYSTEM CHECKED GOOD. (M)

Part: TEE CHORD — CRACKED (WS 685)

GSO - INSPECTION FOUND A 2 INCH CRACK IN TEE CHORD AT STA 685, BL ZERO. THE CRACK WAS STOP DRILLED. A REPAIR ANGLE WAS FABRICATED AND INSTALLED IAW ECRA 5710-01705. (X)

Part: LAP SEAM — CORRODED (BS 420)

31J - INSPECTION FOUND CORROSION IN THE LAP SEAM AT BS 420, STR 27R. THE CORRODED AREA WAS REMOVED. A DOUBLER AND FILLER REPAIR WERE FABRICATED AND INSTALLED IAW SRM 53-30-03. (X)

Part: FITTING — CRACKED (BS 695)

31J - INSPECTION FOUND A .3750 INCH CRACK IN THE RT BS 695 FRAME AFT LOWER FITTING AT THE OUTBOARD FASTENERS IN THE AFT HORIZONTAL FLANGE. THE CRACK WAS STOP DRILLED AND A REPAIR WAS INSTALLED IAW SB 737-53-1080, REV. 2 AND BOEING DRAWING 65C34490. (X)

Part: SHEAR BEAM — CRACKED (BS 664)

3LJ - A .3750 INCH CRACK WAS FOUND IN THE RADIUS OF THE INBOARD FLANGE AT THE FORWARD END OF THE LT S18A SHEAR BEAM, AFT SIDE OF BS 664 BULKHEAD. THE CRACK WAS STOP DRILLED, A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-10-1, SRM 51-40-3, SRM 51-10-2, SRM 51-30-0, AND MM 51-00. (X)

Part: FRAME — CRACKED (L2 DOOR)

31J - A 1 INCH CRACK WAS FOUND IN THE AFT LOWER CORNER OF THE L-2 DOOR FRAME. THE CRACK WAS STOP DRILLED AND A REPAIR WAS INSTALLED IAW ECRA 5210-01224. (X)

Part: BATTERY CHARGER — INOPERATIVE (E/E BAY)

TPA - FLT 1790 - THE FLIGHT ATTENDANT REPORTED A SMOKY ODOR IN CABIN DURING CLIMB-OUT. THE BATTERY CHARGER CIRCUIT BREAKER WAS PULLED AND THE ODOR SUBSIDED. THE AIRCRAFT WAS RETURNED TO TPA WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE BATTERY CHARGER AT FAULT AND THE BATTERY WAS HOT. BOTH THE CHARGER AND BATTERY WERE REMOVED AND REPLACED. ALL CIRCUIT BREAKERS WERE RESET AND THE SYSTEM TESTED GOOD PER MM 24-31-21, PAGE 501. (X)

Part: HYD LINE — CHAFED (RT MLG WW)

FLT NR 1680 - ORD - THE 'A' SYSTEM HYDRAULIC QUANTITY INDICATION SLOWLY DROPPED TO ZERO WHILE EN ROUTE FROM MCI TO MKE. THE AIRCRAFT WAS DIVERTED TO ORD. THE 'A' SYSTEM LOW PRESSURE LIGHTS BEGAN TO FLICKER ON AND OFF WHILE ON FINAL APPROACH. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND A CHAFED HYDRAULIC LINE IN THE RIGHT WHEEL WELL. THE HYDRAULIC LINE IN THE RIGHT WHEEL WELL. THE HYDRAULIC LINE WAS REMOVED AND REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED TO FULL AND LEAK CHECKS WERE GOOD. (Z)