N310DA

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 58,235 hrs · 44,250 cycles

INSPECTION OF THE FS 1016 P-DOME BULKHEAD WEB PER AD 99-08- 23 REVEALED 3 CRACKED CHORD ATTACH FASTENER HOLES BETWEEN STRINGERS 5L & 7L. THE CRACKS WERE REMOVED BY TRIMMING THE WEB. THE WEB WAS REPAIRED WITH AN ALUMINUM REPAIR DOUBLER PER ER/A 095482-14AD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 58,235 hrs · 44,250 cycles

INSPECTION OF THE STRINGER 10R SKIN LAP JOINT PER AD 2003- 08-15 REVEALED A CRACK AT FS 380. THE CRACK WAS REMOVED WITH A 4 INCH CUTOUT. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER B737 SRM AND ER/A 095527-14AD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 58,235 hrs · 44,250 cycles

INSPECTION OF THE STRINGER 4R SKIN LAP JOINT PER AD 2003- 08-15 REVEALED CRACKS AT FS 470. THE CRACKS WERE REMOVED WITH A 17 INCH LONG SKIN CUTOUT. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER THE B737 SRM AND PER ER/A 095528-14AD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 58,235 hrs · 44,250 cycles

INSPECTION OF THE STRINGER 4L SKIN LAP JOINT PER AD 2003 -08-15 REVEALED A CRACK AT FS 512. THE CRACK WAS REMOVED WITH A 14 INCH LONG CUTOUT. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER B737 SRM AND ER/A 095529-14AD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 58,235 hrs · 44,250 cycles

INSPECTION OF THE STRINGER 4L SKIN LAP JOINT PER AD 2003 -08-15 REVEALED A CRACK AT FS 432. THE CRACK WAS REMOVED WITH A SKIN CUTOUT. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER B737 SRM AND ER/A 095531-14AD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 58,235 hrs · 44,250 cycles

NUMEROUS SKIN CRACKS FOUND ALONG STRINGER 4L BETWEEN STATION 540 AND 727. REPAIRED IAW ERA 095481-14AD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 58,235 hrs · 44,250 cycles

INSPECTION OF THE STRINGER 4L SKIN LAP JOINT REVEALED A CRACK AT FS 411. THE CRACK WAS REMOVED WITH A 7 INCH CUTOUT IN THE SKIN. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER THE B737 SRM AND PER ER/A 095530-14AD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 58,235 hrs · 44,250 cycles

FUSELAGE SKIN CRACKED AT MULTIPLE LOCATIONS ALONG STRINGER 4R BETWEEN STA 540 AND 727. REPAIR IAW ER/A 095480-14AD.

Part: ENGINE — MALFUNCTIONED (NR 2) · airframe 56,157 hrs · 42,645 cycles

AFTER T/O, NR 2 ENGINE WENT TO FULL THEN DROVE TO IDLE. ENGINE DATA READ ON FDR. REPLACED NR 2 ENGINE.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 54,762 hrs · 41,507 cycles

THE 'H' DOUBLER AROUND THE LOWER HINGE CUTOUT FOR THE L1 DOOR CUTOUT FWD FRAME WAS FOUND WITH A 3/8 INCH CRACK IN THE CORNER RADIUS. THE CRACK WAS STOP DRILLED AND REPAIRED WITH A TITANIUM REPAIR DOUBLER PER ER/A 384891-14, REV B.

Part: SKIN — CRACKED (FUSELAGE) · airframe 49,350 hrs · 38,969 cycles

FUSELAGE SKIN AFT GALLEY DOOR CUTOUT AT LOWER HINGE CUTOUT: THE LOWER HINGE CUTOUT OF THE AFT GALLEY DOOR (R2) CUTOUT WAS FOUND WITH A 1 IN CRACK IN THE SKIN AND UNDERLYING BEAR STRAP. THE CRACK WAS ROUTED OUT OF ALL LAYERS OF THE SKIN ASSY AND REPAIRED WITH THREE EXTERNAL ALUMINUM DOUBLERS. THE REPAIR WAS ACCOMPLISHED PER ER/A 380675-14, REV B.

Part: SKIN — CRACKED (FUSELAGE) · airframe 49,350 hrs · 38,969 cycles

FUSELAGE SKIN AFT GALLEY DOOR CUTOUT AT UPPER HINGE CUTOUT. THE UPPER HINGE CUTOUT OF THE AFT GALLEY DOOR CUTOUT (R2) WAS FOUND WITH A .25 CRACK IN THE SKIN. THE CRACK WAS ROUTED OUT AND REPAIRED WITH AN EXTERNAL STEEL DOUBLER. THE REPAIR WAS ACCOMPLISHED PER ER/A 380674-14, REV A.

Part: DUCT — BLOWN (FWD B/B-AFT AREA) · airframe 48,320 hrs · 38,538 cycles

SMOKE IN CABIN, RETURN TO BOSTON. REPLACED LT MIXING CHAMBER AND SUPPLY DUCT, LEAK CHECKED. NEEDS ENGINE RUN AND DUCT BURNOUT. PERFORMED SAME, CHECKS GOOD.

Part: FITTING — CORRODED (STABILIZER) · airframe 47,940 hrs · 38,378 cycles

CORROSION WAS REMOVED FROM THE HORIZONTAL STABILIZER ATTACH LUGS FROM THE BORE AND FACE. ERA 396375-14 REPAIRED THE AREA AT HMV.

Part: DOOR FRAME — CORRODED (CARGO DOOR) · airframe 47,940 hrs · 38,378 cycles

THE FORWARD FRAME OF THE C2 DOOR OPENING WAS FOUND CORRODED ON THE AFT SURFACE UNDERNEATH THE DOOR LATCH FITTING. THE CORROSION WAS CUT OUT AND REPAIRED PER ERA 396463-14AD AT HMV.

Part: FITTING — CORRODED (FUSELAGE) · airframe 47,940 hrs · 38,378 cycles

CORROSION WAS FOUND ON THE HORIZONTAL STABILIZER CLEVIS LUGS IN THE BORES AND FACES. THE DAMAGE WAS REMOVED AND REPAIRED PER ERA 396374-14 AT HMV.

Part: FITTING — CORRODED (STABILIZER) · airframe 47,940 hrs · 38,378 cycles

THE VERTICAL STABILIZER ATTACHMENT LUGS WERE FOUND CORRODED AT HMV. ERA 396368-14 REMOVES CORROSION FROM THE BORES AND FACES OF THE LUGS AND REINSTALLS THE BUSHING AND SLEEVES.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 47,940 hrs · 38,378 cycles

DURING SHOP VISIT THE C-2 DOOR OUTER SKIN WAS FOUND DAMAGED. A CRACK WAS FOUND IN THE UPPER AFT CORNER OF THE DOOR HANDLE LATCH CUTOUT. REPAIRED PER ER/A 396879-14.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 47,940 hrs · 38,378 cycles

CRACKS WERE FOUND IN THE BL 0 FLOORBEAM WEB AND CHORD BETWEEN FS 650 AND FS 675. THE DAMAGE WAS REMOVED AND REPAIRED SIMILIARL TO THAT OF S/B 737-57-1210 PER ERA 396377-14 AT HMV.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 47,940 hrs · 38,378 cycles

THE BL 0.07 FLOORBEAM WAS FOUND CRACKED FROM FS 700 TO FS 717 IN THE WEB. THE DAMAGE WAS REMOVED AND REPAIRED PER B737 S/B 57-1210 AT HMV.

Part: FRAME — CRACKED (FUSELAGE) · airframe 47,940 hrs · 38,378 cycles

A CRACK WAS FOUND AT THE LOWER FASTENER ON THE INNER CHORD OF THE LEFT AND RIGHT FS 616 FRAMES AT THE OVERWING FRAME TO BEAM JOINT STUB. ERA 396361-14 AUTHORIZES A REPAIR SIMILIAR TO THAT OF SB 737-53-1182 AT HMV.

Part: TRANSMITTER — INACCURATE (NR 2 ENGINE) · airframe 47,319 hrs · 38,101 cycles

RTO AT EWR DUE TO RIGHT ENGINE DID NOT REACH T/O EPR SETTING. REPLACED RIGHT ENGINE EPR TRANSMITTER. OPERATED RIGHT ENGINE AT T/O POWER PER PFHB AND ALL ENGINE PARAMETERS NORMAL.

Part: GENERATOR — INOPERATIVE (NR 1 ENGINE) · airframe 47,250 hrs · 38,072 cycles

LT ENGINE GENERATOR FAILED DURING TAKEOFF ROLL AT APPROX 80 KTS. CHECKED NR 1 CSD OIL LEVEL AND FILTER BYPASS, CKS GOOD. REPLACED GCU, RAN ENG FOUND GEN FOLLOWING THROTTLE. REPLACED GENERATOR AND CSD.

Part: COFFEEMAKER — MALFUNCTIONED (GALLEY)

DURING TAXI IN, NOTICED ELECTRICAL FUMES. FUMES SEEMED TO BE COMING FROM CB PANEL BEHIND F/O SEAT. ALSO, NOTICED BT LEAD. FLIGHT ATTENDANT FOUND R1 GALLEY COFFEEMAKER OVERHEATING. REPLACED SAME, PERFORMED OPS AND CHECK ALL OK. INSPECTED ALL CB PANELS AND OVERHEAD AREA, ALL CHECK OK.

Part: YAW DAMPER — MALFUNCTIONED (E&E COMP)

UNCOMMANDED ROLL/YAW AT 31000 FT, 77 MACH AUTOPILOT ENGAGED, A/C ROLLED HARD LEFT. REQUIRED 40-50 DEGREE AILERON TO TO RIGHT TO COUNTER COMMAND ROLL. POM COMPLIED WITH YAW DAMPER DISENGAGED. A/C RETURNED TO NORMAL FLIGHT. REPLACED YAW DAMPER COUPLER AND RUDDER PCU PER M/M. REMOVED AND REPLACED FLIGHT DATA RECORDER FOR INVESTIGATION.

Part: VALVE — STUCK OPEN (NR 1 PACK)

F/A REPORTED, DENSE ACRID SMOKE IN CAB AFTER T/O. SMOKE CONCENTRATED FROM ROWS 4 TO 10. DENSE FROM 4 FT ABOVE FLOOR TO CEILING CAB LIGHTS WERE LOW. SMOKE APPEARED TO BE GREY OR WHITE. CHANGED LT 35 DEGREE VLV AND SENSOR. RUN UP BOTH PACKS WITH ENGINE. FOUND SYSTEM NORMAL.

Part: SKIN — CRACKED (L2 DOORWAY)

DUE TO FATIGUE, THE L-2 DOOR LOWER CUTOUT HAS BEEN FOUND TO HAVE A 1.5 TYPICAL CRACK IN THE BEAR STRAP, OUTER SKIN AND THE DOUBLER. THE CRACK CAN BE REPAIRED PER THE B737-200 SRM 53-30-3, FIGURE 24. A TIME LIMITED REPAIR WILL BE INSTALLED WITH BLIND FASTENERS DUE TO TIME CONSTRAINTS AND ACCESS. REPAIRED PER ERA 362539-14

Part: BEARINGS — WORN (COCKPIT)

ON TAKEOFF/CLIMBOUT, STAB TRIM NOISY MAKING CLICKING NOISE. FLIGHT DIVERTED TO BOS. FOUND STAB TRIM WHEEL BEARING WORN ON RT SIDE OF PEDESTAL. REPLACED BEARINGS AND CROSS SHAFT, CHECKED NORMAL.

Part: FIRE DETECTOR — MALFUNCTIONED (APU)

APU FIRE AURAL WARNING AND FIRE HANDLE LIGHT ABOUT 2-3 MINS AFTER START ATTEMPT ON FINAL TO 17 AT MCO. DECLARED EMERGENCY, PULLED AND ROTATED FIRE HANDLE AND WARNING WENT OUT. CKD APU EXHAUST INLET AND OPENED BATHTUB, NO EVIDENCE OF FIRE ALL CKS NML. REPLACED BOTTLES AND FIRE WARNING MODULE TEST GOOD.

Part: BULKHEAD — CRACKED (BS 178)

STATION 178 BULKHEAD WAS FOUND CRACKED IN SEVERAL LOCATIONS. DAMAGE CUTOUTS ARE: 1INCH BY 2.5 INCH FOR RBL 5, WL 194, AND 1INCH BY 2.0 INCH FOR LBL 5, WL 194. REPAIRED PER ERA 304373-14 REV A.

Part: MOUNT — CORRODED (ENGINE)

THE FWD ENGINE MOUNT HAS TWELVE BOLT HOLES THAT ARE USED TO ATTACH TWO COVER PLATES TO EITHER END OF THE MOUNT, SIZE HOLES PER COVER PLATE. THE TWELVE BOLT HOLES WERE FOUND WITH CORROSION IN THEM. THE BOLT HOLES WERE OVERSIZED TO .400/.407 TO REMOVE THE CORROSION. THE ENGINE MOUNT IS MADE FROM 4340 STEEL HEAT TREATED TO 270-300 KSI. THIS ER/A AUTHORIZES THE REPAIR OF THE BOLT HOLES.

Part: PRESS LINE — LEAKING (LT MLG)

HYD SYS-A LOST QTY AND INDICATES ZERO. REPLACED LEFT MLG UPLOCK PRESS LINE.

Part: EEL BULB — FAILED (CABIN)

EXTERIOR EMERGENCY LIGHT INOP AT L2 DOOR. RELAMPED, OPERATION NORMAL.

Part: SKIN — CORRODED (FS 480,STR 26R)

DURING HMV INSPECTION, THE SKIN AT STA 480 WAS FOUND CORRODED IN TWO LOCATIONS BETWEEN STR 26R-28R. THE DAMAGE CONSISTED OF A 1.125 INCH CUTOUT NEAR STR 27R AND A 3.25 INCH BY 2.5 INCH CUTOUT AT THE STA 480 BUTT SPLICE. IN ACCORDANCE WITH B727 SRM 53-30-3, FIG 3A AND DER APPROVAL, AN EXTERNAL DOUBLER AND TRIPLER WERE INSTALLED.

Part: VALVE — LEAKING (LT MLG WW)

ON TAXI OUT LOST ALL HYDRAULIC FLUID. FOUND BRAKE SHUTTLE VALVE LEAKING. REPLACED VALVE, OPERATION NORMAL.