N503DA

Part: BEAM — CRACKED (TORQUE BOX) · airframe 73,460 hrs · 49,705 cycles

THE RT TORQUE BOX OF THE VENTRAL STAIRWAY WAS FOUND WITH A TYPICAL CRACK IN THE FS 1263 UPPER HORIZONTAL BEAM. THE CRACK IS TYPICAL OF BAC S/B 727-53-0129. THE CRACKED PIECE OF STRUCTURE WAS REMOVED AND REPLACED WITH A NEW MEMBER PER THE REQUIREMENTS OF THE S/B AND ER/A 378287-14AD.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 73,213 hrs · 49,542 cycles

WHILE ACCOMPLISHING INSPECTIONS OF THE AFT ENTRY DOOR FRAMES ON THE FS 1183 BULKHEAD, AN ELONGATED FASTENER HOLE WAS FOUND IN THE RBL 17.8 FRAME CAP COMMON TO AN INTERCOSTAL AT WL 263. THE HOLE WAS REAMED TO A CLEAN AND ROUND CONDITION AND AN OVERSIZE FASTENER INSTALLED PER ER/A 377967-14AD.

Part: BALLAST — SMOKE (CABIN) · airframe 72,815 hrs · 49,274 cycles

WHILE BOARDING A/C NOTICIED WHITE SMOKE FROM OVER CEILING PANEL AT L-1 DOOR. C/MTC FOUND ENTRY BRIGHT C/B POPPED. INSPECTED LIGHT ASSEMBLY, FOUND BAD BALLAST. REPLACED SAME.

Part: SKIN — GOUGED (BS 990)

THIS AIRCRAFT RECEIVED GROUND DAMAGE TO THE FUSELAGE SKIN AT FS 990 AND STR 24R. THE DAMAGE WAS FOUND AT HMV AND REPAIRED PER ERA 334013-14.

Part: GIMBAL FITTING — GOUGED (HORIZ STAB)

LT AND RT GIMBAL ATTACH FITTINGS WERE FOUND GOUGED IN THE FILLET RADIUS OF THE UPPER LUGS. ER/A 333979-14 REV A.

Part: SPAR — CRACKED (TE FLAP)

LWR AFT SPAR CRACKED 19, 32 & 37 FROM I/B END. ALSO, CRACKED 37 & 43 FROM O/B END. THIS DAMAGE REPAIRED PER M/M 57-52-0 FIG 802.

Part: SKIN — CRACKED (TE FLAP)

APPROX .75 INCH LONG CRACK IN COVE SKIN, 32 FROM I/B END OF FLAP. REPAIRED PER MM 57-52-0 FIG 809.

Part: SKIN — CRACKED (LE FLAP)

COVE SKIN CRACKED 32 INCHES FROM I/B END. REPAIRED PER M/M 57-52-0.

Part: SPAR — CRACKED (TE FLAP)

AFT SPAR DOUBLER CRACKED 21, 34 & 57S FROM I/B END DAMAGE LISTED ON N/R'S 016162, 016079 & 016080. REPAIRED PER CMM 57-52-0 FIG 802.

Part: SLAT — WORN (L/H WING)

SKIN CRACKED AT FENCE ATTACH HOLES. REPAIRED PER M/M 57-54-0.

Part: SKIN — CRACKED (BS 500-520)

LFEC INSPECTIONS OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 480 & 680 INDICATED A CRACK. INTERNAL HFEC INSPECTION CONFIRMED A SINGLE CRACK IN THE LOWER FASTENER ROW OF THE LOWER SKIN BETWEEN FS 500 & 520. THE CRACK WAS ROUTED OUT AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER B727 SRM 53-30-3, FIG 5 AND ER/A 368077-14AD.

Part: BRACKET — CRACKED (NR 2 SLAT ACT)

FOUND ON A1 LETTER CK, NR 2 SLAT ACTUATOR O/B ATTACH BRACKET CRACKED. REPAIRED PER MM 57-42-0.

Part: SKIN — CRACKED (BS 481-681)

FUSELAGE SKIN FS 481-681, STRINGER 26L SKIN LAP SPLICE, CRACK REPAIR. LFEC INSPECTION OF THE STRINGER 26L SKIN LAP SPLICE BETWEEN FS 481 AND 681 INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN. INTERNAL HFEC INSPECTION CONFIRMED MULTIPLE CRACKS ALONG THE PANEL LENGTH. THE ENTIRE SKIN LAP SPLICE WAS CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 367232-14AD, REV A.

Part: VALVE — INOP (LEFT)

AT FL250 ALTITUDE WARNING HORN WENT OFF WITH CABIN ALT AT 12,000 FT. CREW WENT ON 02, OUTFLOW VALVE SHOWED CLOSED. CARGO VALVE CLOSED, LT PACK OFF, DUE TO PREVIOUS WRITE UP. FOUND LT PACK VALVE INOP AND LT ACM NOT TURNING. REPLACED LT PACK VALVE AND ACM CKS OK.

Part: PANEL — HOLE (LT HORIZ STAB)

FOUND ON F1 LETTER CHECK, HOLE .25 IN LOWER LT HORIZONTAL STAB ACCESS PANEL INBD OF ELEV PWR PACK. INSTALLED DOUBLER PER SRM 55-20-3.

Part: SILL — CORRODED (BS 950)

THE OUTBOARD CAP (EXTRUDED TEE) OF THE C2 DOOR SURROUND LOWER SILL WAS FOUND BADLY CORRODED ON THE OUTBD FLANGE. THE FLANGE WAS CUT AWAY TO REMOVE THE CORROSION. THE CUT FLANGE WAS REPAIRED WITH A SHEET METAL ANGLE REPAIR PER ER/A 363872-14, REV A.

Part: STRINGER — CORRODED (BS 950)

STRINGER 29R WAS FOUND CORRODED NEAR FS 950E+10. THE STRINGER WAS CUT AT FS 950D+10 AND THE AFT SECTION REMOVED. A NEW SECTION OF STRINGER WAS SPLICED IN PER ER/A 363710-14, REV B.

Part: SKIN — CORRODED (BS 715)

CORROSION WAS FOUND IN THE SKIN AT FS 705, BL 0. BECAUSE OF THE CORROSION AND THE PRESENSE OF EXISTING REPAIRS IN THE AREA THE SKIN WAS SPLICED AT APPROX FS 715 FROM STR 26L TO 26R. THE NEW SECTION OF SKIN WAS SPLICED PER B727 SRM 53-30-3, EXCEPT THE SPLICE ENDS WERE MODIFIED TO ACCOMODATE THE S-26 LAP SPLICES. THE REPAIR WAS ACCOMPLISHED PER ER/A 363516-14, REV C.

Part: SKIN — CRACKED (RT LE FLAP)

CRACK IN LWR T/E SKIN AT ACTUATOR FITTING. REPAIRED SKIN PER SRM 57-50-3.

Part: SPAR — CRACKED (RT LE FLAP)

FRONT SPAR CRACKED. REPAIRED SPAR PER SRM 51-40-3 (REF 57-50-2) ENG SIG.

Part: SKIN — CORRODED (BS 700)

THE FUSELAGE SKIN A FS 705, BL 0 WAS FOUND WITH A SMALL AREA OF CORROSION. THE DAMAGE WAS REMOVED WITH A 1 DIA HOLE. THREE OTHER REPAIRS WERE IN THE GENERAL AREA OF THE CUTOUT. THEREFORE, THE SKIN WAS CUT AT FS 710 FROM S-26L TO S-26R AND A NEW SECTION OF SKIN WAS SPLICED IN PER ER/A 363516-14.

Part: BLKHD STIFFENER — CRACKED (FS 1183)

A 2 INCH CRACK WAS FOUND IN THE RBL 36.83 STIFFENER AND A 1 INCH CRACK WAS FOUND IN THE LBL 36.83 STIFFENER AT WL 238 ON THE FS 1183 BULKHEAD. THE STIFFENERS WERE REPAIRED PER BOEING S/B 727-53-0192 AS DOCUMENTED IN ER/A 363498-14.

Part: WEB — CRACKED (BS 870)

AT MV-2/DFW, FOUND A CRACK AT A LIGHTENING HOLE AT FS 870 IN WEB AND DBLR. REPAIRS WHERE COMPLETED PER SRM 53-10-9 FIG 5. CRACK WAS LOCATED AT THE 5 O'CLOCK POSITION.

Part: FRAME — PART (BS 1352)

FS FRAME 1352 FRAME WORN AT THE 6 O'CLOCK POSITION. FRAME WAS REPAIRED PER MM 53-11-0.

Part: BRACKET — CRACKED (NR 8 SPOILER ACT)

FOUND DURING E-2 LETTER CHECK - NBR 8 SPOILER ACTUTOR MOUNT CASTING LWR ATTACH BRKT CRACKED REPAIRED PER M/M 57-20-22

Part: COWL — CRACKED (NR 2 ENGINE)

1 1/2 CRACK EXTENDING FROM LOWER AFT CORNER OF EXISTING REPAIR DOUBLER RT SIDE OF #2 ENG NOSE COWL AFT OF NOSE RING REPLACED DOUBLER PER M/M 54-30-0

Part: BATTERY PACK — DISCHARGED (CABIN)

OVERWING EMERGENCY LIGHT FAILS TO TEST. REPLACED BATTERY PACK RACK, CHECKS NORMAL.

Part: SKIN — DAMAGED (BS 340-400)

LAX REPORTED DAMAGE TO THE SKIN, STRINGERS AND FRAMES BETWEEN STA 340 TO STA 400 AND STR 22R TO S-24R. SEVERAL REPAIRS HAVE BEEN INSTALLED PER THE B727 SRM. DUE TO LIMITED ACCESS BLIND FASTENERS WILL BE INSTALLED IN SEVERAL LOCATIONS ON A TIME LIMITED BASIS, REPAIR APPROVAL PER DL ERA 303310-14.

Part: MOUNT BRACKET — CRACKED (RT WING)

FOUND DURING D-1 LETTER CHECK, .375 INCH CRACK AT NR 6 L/E FLAP ACTUATOR MOUNT BOX UPPER O/B CORNER. REPAIRED PER M/M 57-20-21 PG 811.

Part: SKIN — CORRODED (BS 870)

DURING INSPECTION, CORROSION WAS FOUND ON THE FUSELAGE SKIN AT STA 870 AND STR 9R. THE CUT OUT MEASURES 5 INCHES BY 3 INCHES, IN ACCORDANCE WITH B727 SRM 53-30-3 FIG 3A, A DOUBLER AND TRIPLER WERE INSTALLED.

Part: SLIDE — LOW PRESSURE (R1 DOOR)

DURING INSPECTION, R-1 DOOR SLIDE PRESSURE FOUND LOW 500 LBS. REPLACED SLIDE.

Part: ANGLE — CRACKED (NR 6 LE FLAPS)

UPON INSPECTION A CRACK WAS FOUND ON THE LOWER ANGLE BETWEEN THE ACTUATOR RIBS. REPAIRED PER MM 57-54-0 FIG 812. FOUND DURING SHOP INSPECTION FOR NR 6 L/E SLAT.

Part: SKIN — CRACKED (NR 6 LE FLAPS)

UPON INSPECTION A CRACK WAS FOUND IN THE THERMAL ANTI-ICE SKIN BETWEEN THE RIBS O/B FROM THE ACTUATOR RIBS. REPAIRED PER M/M 57-54-0 FIG 803. FOUND DURING SHOP INSPECTION FOR NR 6 L/E SLAT.

Part: RIB — CRACKED (NR 6 LE FLAP)

DURING SHOP INSPECTION, NR 6 L/E SLAT WAS FOUND CRACKED AT THE INBD RIB, INBD TRACK ARM IN RADIUS. ALSO, I/B ACTUATOR RIB CRACKED TOP FWD CORNER. REPAIRED PER MM 57-54-0 FIG 805 AND FIG 804.

Part: SKIN — CORRODED (FS 700)

DURING CV-2 INSPECTION, CORROSION WAS FOUND IN THE FUSELAGE SKIN JUST AFT OF STA 700 AND OUTBD OF STRINGER 28L. DAMAGE REMOVAL RESULTED IN A 2 BY 2 CUTOUT. DUE TO THE PROXIMITY TO AN EXISTING REPAIR, THE FACT THAT THE SKIN IS A SSI ITEM AND THE PROXIMITY TO THE INSPECTION AREA OF BACO S/B 727-53-A0203, THE DAMAGE REMOVAL WAS IN ACCORDANCE WITH B727 SRM 53-30-3, FIG 1. ACCOMPLISHED REPAIRS PER DL ERA 302177-14.

Part: FIREWALL PANEL — CRACKED (NR 2 ENGINE)

FOUND ON CV2 CK, NR 2 ENG FIREWALL, NR 1 PANEL CRACKED .75 INCH, LT SIDE OF INLET, AND .50 INCH, RT SIDE OF INLET. REPAIR: REPAIRED PER SRM 54-10-3, FIG. 1.

Part: SKIN — CORRODED (BS 720)

FOUND ON CV2 CK. CORROSION ON SKIN LAP JOINT OUTBOARD OF STR 26R FROM STA 720C-STA 720F. REPAIR: REPAIRED PER ERA 302175-14.

Part: ANGLE — CRACKED (NR 5 LE SLAT)

FOUND ON CV2 CK, CRACK INBD OF ACTUATOR NR 5 SLAT. REPAIR: REMOVED SLAT PER OPN 7005, PEPAIRED PER MM 57-54-0, FIG 804.

Part: TURB SHEAR PIN — FAILED (NR 1 ENGINE)

THIS ENGINE WAS EXHIBITING HIGH EGT INDICATIONS AND SENT TO ATL FOR ENGINE TEST RUN ON WING. A NORMAL START WAS PERFORMED WITH START VALVE LIGHT EXTINGUISHING. THEN, 15 MINUTES AFTER START AND IDLE THE ENGINE FIRE WARNING LIGHT ILLUMINATED, JUST PRIOR TO REACHING TAKEOFF POWER. LIGHT EXTINGUISHED AS ENGINE WAS SHUTDOWN. THE STARTER WAS FOUND TO HAVE HAD A TURBINE BEARING FAILURE FOLLOWED BY THE SHEARING OF THE EXDUCER ROLL PIN WHICH ALLOWED THE EXDUCER TO EXIT THE REAR OF THE CONTAINMENT BASKET. THE REMAINDER OF THE TURBINE WHEEL WAS CONTAINED IN THE STARTER SCROLL EXHAUST DUCT.

Part: EEL BATTERY PACK — DISCHARGED (CABIN)

RIGHT OVERWING EMERGENCY EXIT SIGN LIGHTS INOP. REPLACED BATTERY, CHECKS GOOD.

Part: STIFFINERS — CRACKED (FS 1263)

DURING INSPECTION (L/C), THE RT TORQUE BOX WAS FOUND TO HAVE CRACKED STIFFENERS AT FS 1263. THE DAMAGED PART WILL BE REPLACED IN ACCORDANCE WITH B727 S/B 53-0129, REV 4.

Part: SKIN — CRACKED (NR 4 SLAT)

DURING SHOP ISNPECTION, LEFT WING NR 4 SLAT UPPER SKIN WAS WORN AT FENCE. ALSO, A TIME LIMITED REPAIR WAS FOUND ON LOWER SKIN AT FENCE AREA. REPAIRED PER MM 57-54-0 FIG 813 AND SRM 57-50-3 FIG 1.

Part: RIB — CRACKED (NR 4 SLAT)

DURING SHOP INSPECTION, FOUND LEFT WING NR 4 SLAT WITH RIB NR 12 AND NR 18 CRACKED. REPAIRED PER MM 57-54-0.

Part: RIB — CRACKED (NR 4 SLAT)

DURING SHOP INSPECTION, FOUND LEFT WING NR 4 SLAT WITH THE RIB CHORD CRACKED AT THE O/B END, AND WORN AT THE I/B TRACK. REPAIRED PER MM 57-54-0 FIG 812.

Part: SKIN — CRACKED (NR 4 SLAT)

DURING SHOP INSPECTION, LEFT WING NR 4 SLAT WAS FOUND WITH CRACKED LOWER SKIN AT INBD TRACK FAIRING. REPAIRED PER MM 57-54-0 FIG 15.

Part: RIB — CRACKED (NR 4 SLAT)

DURING SHOP INSPECTION, LEFT WING NR 4 SLAT WAS FOUND WITH RIB NR 11 CRACKED. REPAIRED PER SRM 57-54-0.