N402DA

Part: SKIN — CRACKED (L1 DOOR)

REF NRC 53 TPA LETTER CHECK C-1, .5 INCH CRACK IN R-1 DOOR SKIN AT LWR AFT CORNER. INSTALLED DOUBLER PER M/M 52-11-01, NR 8.

Part: SKIN — CRACKED (R1 DOOR)

REF NRC 52 - TPA LETTER CHECK C-1, .5 INCH CRACK IN DOOR SKIN, R-1 DOOR LOWER FWD CORNER. INSTALLED DOUBLER PER M/M 52-11-01, NR 8.

Part: SKIN — CRACKED (BS 360-480)

LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 360 AND 480 REVEALED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN. INTERNAL HFEC INSPECTION CONFIRMED SEVERAL CRACKS ALONG THE PANEL LENGTH. THE ENTIRE SKIN LAP WAS CUT OUT AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 366782-14, REV B.

Part: SKIN — CRACKED (BS 681-740)

LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN PANEL BETWEEN FS 681 AND 740. INTERNAL HFEC INSPECTION CONFIRMED 35 CRACKS. THE SKIN LAP SPLICE WAS CUT OUT ALONG THE ENTIRE PANEL LENGTH AND REPAIR WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 366784-14, REV A.

Part: FRAME — CRACKED (PAX DOORWAY)

FOUND AT LETTER CK B-2, AFT ENTRY DOOR CUTOUT LT FRAME HAS .3125 INCH VISIBLE CRACK 6 INCHES BELOW UPPER STOP CASTING. REPAIRED PER SRM 53-10-8.

Part: WIRE — DAMAGED (CABIN)

FIRST CLASS EMER ESCAPE PATH LIGHTING INOP. FOUND BLOWN POWER SUPPLY FUSE AND MELTED WIRING AT C/P. REPLACED POWER SUPPLY AND BATTERY, REPAIRED DAMAGED WIRING. OPN TEST OK.

Part: SPAR — MISDRILLED (NR 3 TE MIDFLAP)

NR 3 MIDFLAP/ REAR SPAR/WBL 124/AD 94-07-08 - OS HOLE: OVERSIZED HOLE IN REAR SPAR UPR CHORD AND UPPER SKIN IN AD INSPECTION AREA. FOUND DURING ACCOMPLISHMENT OF EO, 4-58705-3AD MODIFICATION. FAA AMOC REC'D TO INSTALL OS HI-LOK IN HOLE.

Part: BLKHD STIFFENER — CRACKED (BS 1183)

CRACKS WERE FOUND IN THE LBL AND RBL 36.83 VERT STIFFENER ON THE FWD SIDE OF THE FS 1183 BLKHD. THE CRACKS WERE LOCATED AT APPROX WL 238 AND WERE NO MORE THAN 2 IN LENGTH. REPAIRED PER ERA 331543-14.

Part: ANGLE — CRACKED (NR 3 TE MIDFLAP)

DURING SHOP INSPECTION, A DOUBLER ON THE AFT LOWER SPAR ANGLE WAS FOUND CRACKED ANGLE, 32 FROM I/B END. THE ANGLE WAS REPAIRED PER 727 MM 57-52-0 FIG 802 BY INSTALLING/REPLACING THE REPAIR DOUBLER.

Part: ANGLE — CRACKED (NR 3 TE MIDFLAP)

DURING SHOP INSPECTION, THE NR 3 MIDFLAP WAS FOUND WITH A CRACK IN THE AFT LOWER CLOSEOUT ANGLE, 18 FROM I/B END. THE ANGLE WAS REPAIRED PER 727 MM 57-52-0, FIG 802 BY STOP DRILLING THE CRACK AND INSTALLING A DOUBLER.

Part: RIB — CRACKED (NR 1 TE MIDFLAP)

DURING SHOP VISIT, THE NR 1 MIDFLAP WAS FOUND WITH IB AFT CLOSEOUT RIB CRACKED AT LOWER AFT CORNER. THE RIB WAS REPAIRED BY STOP DRILLING THE CRACK AND INSTALLING A DOUBLER PER 727 MM 57-52-0,FIG. 808.

Part: DOUBLER — CRACKED (NR 2 TE MIDFLAP)

REPAIR DOULBERS CRACKED IN THREE PLACES 19, 32 AND 37 FROM I/B END OF LOWER AFT CHORD ANGLE NR 2 MIDFLAP. REPAIRED BY REPLACING DOUBLERS PER BOEING M/M 57-52-0 FIG 802. ON NON-ROUTINE CARDS NR 005932 AND 005933.

Part: SKIN — CRACKED (VERT STAB)

SKIN CRACKED, PREVIOUSLY STOP DRILLED CRACK AT BASE OF VERTICAL STAB FRONT SPAR, RT SIDE. REMOVED FASTENERS. CUT OUT DAMAGED SECTION OF SKIN. E/C INSP OK. FABRICATED FILLER AND BEGAN FABRICATION OF DOUBLER PER SRM 55-30-3. OK TO INSTALL DOUBLER. STARTED INSTALLING DOUBLER PER SRM 55-30-3. COMPLETED INSTALLATION OF DOUBLER PER SRM 55-30-3.

Part: WEB — CRACKED (VERT STAB)

WEB CRACKED VERT STAB INTERIOR, VERTICAL WEB OVER S-DUCT IS CRACKED AT BOTH LOWER CORNERS (2 PLACES). REMOVED FASTENERS DYE PEN'D STOP DRILL, NO CRACK NOTED AFTER STOP DRILL HOLES ON BOTH SIDES, FABRICATED NEW DOUBLERS AS PER SRM 53-10-4 FIG 17. INSTALLED DOUBLER AND SHIM ON LT SIDE OF WEB. INSTALLED RT SIDE DOUBLER AS PER SRM 53-10-4 FIG 17.

Part: SKIN — CORRODED (BS 680)

FUSELAGE SKIN FS 680, STRINGER 26L-28L, REPAIR FOR CORROSION CUTOUTS. TWO AREAS OF CORROSION WERE CUTOUT OF THE FUSELAGE SKIN AT FS 680 BETWEEN STRINGERS 26L AND 28L. THE CUTOUTS WERE REPAIRED WITH AND EXTERNAL ALUMINUM DOUBLER PER ER/A 363860-14, REV A.

Part: PRESSURE DECK — CRACKED (BS 950)

FOUND ON A2 LETTER CK, 1 INCH CRACK AT LEFT MLG W/W PRESSURE DECK BEAD STA 950 AT LBL 63. STOP DRILLED CRACK PER MM 53-14-0.

Part: WEB — CRACKED (BS 1223/1243)

FOUND ON A2 LETTER CK, TORQUE BOX WEB CRACKED .5 INCH AT DOUBLER UPPER LIGHTNING HOLE STA 1223 AND .25 INCH CRACK AT LIGHTNING HOLE FWD STA 1243. REPAIR PER ERA 363858-14 AND M/M 53-11-0.

Part: ANGLE — CRACKED (NR 3 LE FLAP ACT)

FOUND 0N A2 LETTER CK, NR 3 L/E FLAP ACTUATOR BOX CRACKED AT OUTBOARD LOWER CORNER. REPAIRED PER MM 57-20-21 AND ERA.

Part: BULB — FAILED (CABIN)

AFT MOST RED BULB INOP ON FLOOR PROX LIGHT STRIP. REPLACED BULB SOCKET.

Part: RIB — CRACKED (NR 6 LE FLAP)

FOUND ON A1 LETTER CK, .75 IN CRACK IN RADIUS OF NR 6 SLAT RIBS I/B AND O/B SIDES OF ACTUATOR AT COVE SKIN ATTACH. REPAIRED PER MM 57-54-0.

Part: ACTUATOR — FAILED (NR 5 LE FLAP)

SYSTEM-A QTY WENT TO 0, SYS-A HYD PUMPS WERE TURNED OFF PRIOR TO LOSING PRESS. TOWED FROM TAXIWAY. NR 5 LE FLAP ACT FAILED. REPLACED LE ACT, CHECK CASE DRAIN FILTERS OK.

Part: SKIN — CRACKED (LT ELEVATOR)

FOUND A .5 INCH CRACK IN LT ELEVATOR TOP SKIN, FWD OF OUTBD END OF TAB CUTOUT. REPAIRED PER SRM 55-20-3.

Part: POST — CRACKED (COCKPIT WINDOW)

FOUND CRACK AT THE INBOARD LOWER CORNER OF THE L4 COCKPIT WINDOW. REPAIRED IN ACCORDANCE WITH DER FORM 8110-3, DER DESIGNATIONSO-831, DATED 9/12/96.

Part: DOOR FRAME — CRACKED (BS 761)

A CRACK WAS FOUND IN THE FOURTH FASTENER HOLE LOCATED ABOVE THE CABIN FLOOR LINE ON THE LT STA 761 OVERWING EXIT FRAME. THE HOLE WAS OVERSIZED TO 0.340 AND A HIGH FREQUENCY EDDY CURRENT INSPECTION SHOWED THAT THE CRACK NO LONGER EXISTED IN THE FASTENER HOLE. REPAIRED PER ERA 304129-14AD.

Part: STRINGER — CRACKED (VERT STAB)

THE VERTICAL STABILIZER STRINGER 9L WAS FOUND CRACKED AT FIN STA 157.2, DURING EXECUTION OF EO 4-59253-12AD. THIS EO CALLS FOR A REPAIR PER B727 SRM 55-30-4, HOWEVER STR 9L CANNOT BE REPAIRED PER SRM PROCEDURE DUE TO SPACE LIMITATION ON INBOARD FLANGE. STRINGER WILL BE REPAIRED IN ACCORDANCE WITH S/B 727-55 0075R2.

Part: ACTUATOR BRACKET — CRACKED (NR 5 LE FLAP)

FOUND ON F1 LETTER CHECK, NR 5 LE FLAP ACTUATOR ATTACH ANGLE CRACKED. REPAIRED PER MM 57-20-21.

Part: STIFFENER — CRACKED (WING LE SPAR)

FOUND ON F1 LETTER CHECK, 1.25 INCH CRACK AT L/E EDGE SPAR VERTICAL STIFFENER AFT OF NR 6 SLAT OUTBOARD TRACK OUTBOARD SIDE. REPLACED STIFFENER PER MM 57-20-21.

Part: SKIN — CRACKED (MAIN ENTRY DOOR)

FOUND ON LETTER CHECK, MAIN ENTRY DOOR UPPER AFT SKIN HAS A CRACK EXTENDING FROM FASTENER. REPAIR: REPAIRED PER M/M 52-12-0, NR 10, FIG 806 10P PER PS 900-5-1, NR 04.

Part: ACTUATOR BRACKET — CRACKED (NR 1 SLAT ACT)

FOUND ON F1 LETTER CHECK, NR 1 SLAT ACTUATOR INBOARD MOUNT BRACKET CRACKED AT UPPER MOUNT BOLT. REPAIRED PER MM57-20-21.

Part: SLAT — CRACKED (NR 2 LE SLAT)

THE INNR SKIN WAS FOUND CRACKED BY THE TELESCOPING ANTI-ICE DUCT. REPAIRED INNR SKIN PER SRM 57-50-3, FOR NR 2 L/E SLAT.

Part: RIB — CRACKED (NR 2 LE SLAT)

RIB MARKED NR 14 WAS FOUND CRACKED IN THE LOWER RADIUS NEAR ATTACH ANGLE. THE NOTED RIB WAS REPAIRED IN COMPLIANCE WITH MM 57-54-0 FIGURE 805, FOR NR 2 L/E SLAT.

Part: RIB — CRACKED (NR 2 LE SLAT)

THE 3RD RIB WAS FOUND CRACKED. REPAIRED RIB PER MM 57-54-0, FOR NR 2 L/E SLAT.

Part: CADC — FAILED (E/E COMP)

AFTER TAKEOFF, TCAS DISPLAYED ALL FAILED AND MAIN TCAS SCREEN SHOWED NR 1 XPONDER DATA BUS AND ALT DATA. CENTER ADVISED THEY RECEIVED SQUAWK, BUT NO ALT READOUT. AT FL 310 LEVEL OFF AND CRUISE MACH .80, A/C BEGAN MILD DUTCH ROLL. ROLL CEASED WHEN SPEED SLOWED TO 270/260 KIAS. BOTH FLT DIR INOP, YAW DAMPER FLAGS NOT IN VIEW AND DIVERTED TO CVG PER DISPATCHER AND MAINT CONTROL. REPLACED CADC, CAPT ALT FLAG OUT, TCAS OPS OK, NORMAL NO FLAGS.

Part: SLAT — CRACK (NR 2 LE)

FOUND DURING E-1 LETTER CHECK, 2 INCH BY .25 INCH CRACKS BELOW ANTI-ICE TUBE ON NBR 2 L/E SLAT. REPAIRED PER MM 57-54-0 PG 807A.

Part: SKIN — CRACK (VERT STAB)

FOUND DURING E-1 LETTER CHECK, SKIN CRACKED .5 INCH VERTICAL STAB LT SIDE BELOW ACCESS PNL 9501. REPAIRED PER SRM 55-30-3 FIG 1.

Part: PANEL — SHORTED (FLIGHT DECK)

DURING CRUISE, HAD ELECTRICAL BURNING SMELL AND SMOKE COMING FROM FLIGHT ENGINEERS PANEL THROUGH GASPER FAN SWITCH HOLE. DEACTIVATED CIRCUITS, ODOR CEASED. FOUND P4-22 PANEL SHORTED TO GROUND. REPLACED PANEL, OPERATION NORMAL.