N410DA

Part: WARNING LIGHT — FALSE INDICATION (COCKPIT) · airframe 62,611 hrs · 51,398 cycles

R-2 DOOR IND ILLUM ON T/O ROLL. ABORTED T/O BELOW 100 KTS. INSPECTED DOOR, NO PROBLEM NOTED. DOOR OPS NORM. CYCLED NUMEROUS TIMES, UNABLE TO DUPLICATE.

Part: ANGLE — CRACKED (NR 8 SLAT) · airframe 61,943 hrs · 50,961 cycles

1/2 INCH CRACK IN NR 8 L/E SLAT COVE SKIN ANGLE AT ANTI-ICE DUCT CUTOUT REPAIRED PER MM 57-54-000-8

Part: SIGN — INOPERATIVE (CABIN) · airframe 60,865 hrs · 50,163 cycles

FOUND AFT SERVICE DOORS OVERHEAD EXIT SIGN IN AFT GALLEY. REINSTALLED EXIT SIGN. LIGHTS DID NOT ILLUMINATE. REPLACED BATTERY PACK AND BASE, NO HELP. FOUND WIRE BROKEN ON EXIT SIGN. REPAIRED WIRE. SIGN OPS NORMAL NOW.

Part: RELAY — FAILED (PACK VALVE) · airframe 60,594 hrs · 49,941 cycles

AFTER TAKEOFF PRESSURIZATION AUTO FAILED TO STBY. ATTEMPTED OPERATION IN STBY AND MANUAL. CABIN DIDN''T PRESSURIZE. FOUND PACK VALVE C/B POPPED. LEVELED AT 8,000 FT, CABIN ALT 8,000. PSI DIF. ISOLATED POPPING C/B TO R23 RELAY. REPLACED BOTH R23 AND R22 RELAYS. RESET C/B, RAN LT AND RT PACKS IN AUTO AND MANUAL. OPS OK.

Part: PUMP — DAMAGED (NR 1 ENGINE) · airframe 60,351 hrs · 49,714 cycles

AS ENG POWER WAS ADVANCED FOR TAKEOFF NR 1 ENG FLAMED OUT. EPR ON NR 1 ENG REACHED 1.3 BEFORE ENGINE INST. ROLLED BACK, NO TAKEOFF WAS INITIATED. FOUND ENG FUEL PUMP SHEARED. REPLACED SAME AND ENG FUEL CONTROL.

Part: SIGN — INOPERATIVE (CABIN) · airframe 60,259 hrs · 49,650 cycles

AFT EMERGENCY EXIT SIGN INOP AT CENTER AISLE STA 1046. REPLACED BATTERY RACK, CKS NORMAL.

Part: FRAME — CORRODED (FUSELAGE) · airframe 60,244 hrs · 49,632 cycles

CORROSION WAS FOUND ON THE FS 1142.7 CARGO DOOR OPENING FRAME ON THE FORWARD SIDE OF THE WEB. THE CORROSION WAS BLENDED AND A DOUBLER INSTALLED PER ERA 334273-14 AT HMV.

Part: SKIN — GOUGED (FUSELAGE) · airframe 60,244 hrs · 49,632 cycles

A GOUGE WAS FOUND IN THE FUSELAGE SKIN AT THE AFT EDGE OF THE C-2 DOOR AT FS 990. THE DAMAGE WAS LOCATED APPROX 1 INCH ABOVE STRINGER 24R. THE SKIN, DOUBLER AND TRIPLER WERE TRIMMED, INSPECTED AND TREATED PER ERA 334268-14. THE DAMAGE WAS FOUND AT HMV.

Part: FRAME — CRACKED (FUSELAGE) · airframe 60,244 hrs · 49,632 cycles

A PREVIOUS REPAIR WAS FOUND ON THE FS 910 FRAME AT STR 18A ON THE RIGHT SIDE OF THE AIRCRAFT. THE REPAIR WAS REMOVED, INSPECTED AND A NEW REPAIR INSTALLED PER ERA 334253-14. THE DAMAGE WAS FOUND AT HMV.

Part: FRAME — WORN (FUSELAGE) · airframe 60,214 hrs · 49,611 cycles

THE FS 1148 FRAME INNER CHORD WAS WORN AT STRINGER 5R. THE DAMAGE WAS BLENDED SMOOTH AND A REPAIR WAS INSTALLED PER ERA334258-14. THE DAMAGE WAS FOUND AT HMV.

Part: SKIN — CRACKED (FUSELAGE) · airframe 60,214 hrs · 49,611 cycles

A CRACK WAS FOUND IN THE LOWER AFT CORNER OF THE L1 DOOR CUTOUT. THE CRACK IS THROUGH THE SKIN, DOUBLER AND BEARSTRAP AND IS APPROXIMATELY 2 INCHES LONG. THE CRACK WAS CUT OUT AND REPAIRED PER ERA 334242-14 WITH AND EXTERNAL REPAIR DOUBLER AND TRIPLER. THE DAMAGE WAS FOUND AT HMV.

Part: SKIN — GOUGED (FUSELAGE) · airframe 60,214 hrs · 49,611 cycles

A GOUGE WAS FOUND IN THE FUSELAGE SKIN AT FS 360 BETWEEN STRINGER 17L AND 18L JUST BELOW AND AFT OF THE L1 DOOR CUTOUT. AN EXTERNAL REPAIR DOUBLER WAS INSTALLED AT HMV PER ERA 334256-14.

Part: STIFFENER — CRACKED (BULKHEAD) · airframe 60,214 hrs · 49,611 cycles

CRACKS WERE FOUND ON BOTH THE LBL 8 AND RBL 8 STIFFENERS OF THE 1183 BULKHEAD AT WL 182. THE CRACKS ARE IN THE TYPICAL LOCATIONS AS THOSE DESCRIBED IN S/B 727-53-0175. THE S/B REPAIR WAS INSTALLED PER ERA 334276-14AD AT HMV.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 60,214 hrs · 49,611 cycles

THE RT FRAME OF THE AFT ENTRY DOOR WAS FOUND CRACKED IN THE FORWARD FLANGE AT WL 276. THE BEAM WAS CUT AND A NEW SECTION SPLICED IN PER ERA 334236-14. THE DAMAGE WAS FOUND AT HMV.

Part: SKIN — CRACKED (FUSELAGE) · airframe 60,214 hrs · 49,611 cycles

SEVERAL CRACKS WERE FOUND IN THE LAP JOINT OF THE FUSELAGE SKIN AT STRINGER 4L BETWEEN FS 360 AND FS 481. THE LAP JOINT WAS REPLACED PER ERA 334230-14AD AT HMV.

Part: BEAM — CORRODED (MLG) · airframe 60,214 hrs · 49,611 cycles

DURING OVERHAUL THE I/B FLAP, I/B TRACK ASSY TYPICAL CORROSION WAS FOUND AT THE MLG AND SPOILER BEAM ATTACH PADS AREAS AND WEAR AT THE FWD ATTACH LUGS AND TOGGLE DETENT HOLE. REPAIR PER ER/A 387256-14AD AND BF GOODRICH REPAIR NR 23-0592.

Part: RIB — CRACKED (NR 5 SLAT) · airframe 60,214 hrs · 49,611 cycles

NR 5 SLAT I/B RIB CRACKED. INSTALLED REPAIR DOUBLER PER B727 MM 57-54-0, FIG 814.

Part: ANGLE — CRACKED (TE FLAP) · airframe 60,214 hrs · 49,611 cycles

DURING SHOP VISIT THE AFT LOWER CHORD ANGLE WAS FOUND CRACKED IN 3 PLACES. A SECTION OF THE ANGLE WAS REPLACED AND NEW SECTION SPLICED IN PER MM 5752-01, FIG 802.

Part: SKIN — WORN (NR 5 SLAT) · airframe 60,214 hrs · 49,611 cycles

AT HMV THE 5 SLAT LEADING EDGE WAS FOUND WORN AT FENCE. DRILLED REPAIR DOUBLER PER MM 57-54-0. DYE PEN INSP AREA UNDER FENCE FOUND 2 CRACKS STOP DRILLED. INSTALLED DOUBLER PER MM 57-54-0 FIG 817.

Part: RIB — CRACKED (NR 4 SLAT) · airframe 60,214 hrs · 49,611 cycles

AT HMV A RIB WAS FOUND CRACKED ON 4 L/E SLAT I/B END. REPAIRED PER 57-54-0 FIG 814.

Part: SKIN — WORN (NR 4 LE SLAT) · airframe 60,214 hrs · 49,611 cycles

AT HMV THE SKIN ON 4 L/E SLAT WAS WORN ON UPPER AND LWR SURFACES I/B TRACK. AREA BURNISHED REPAIR DOUBLER MANUF INSTALLED DOUBLER PER MM 57-54-0 FIG 813.

Part: SKIN — DAMAGED (TE FLAPS) · airframe 60,214 hrs · 49,611 cycles

DURING SHOP VISIT THE LEADING EDGE SKIN WAS FOUND WORN AT THE I/B LOWER CORNER. THE SKIN WAS REPAIRED PER 727 M/M 57-52-0 FIG 803, BY REMOVING THE DAMAGE AND INSTALLING A DOUBLER AND SKIN FILLER.

Part: RIB — CRACKED (NR 4 SLAT) · airframe 60,214 hrs · 49,611 cycles

AT HMV 4 L/E SLAT RIB WAS FOUND CRACKED ON O/B END. REPLACED PER MM 57-54-0 FIG 814. DYE CHECKED, FOUND NO CRACKS.

Part: ANGLE — CRACKED (TE FLAP) · airframe 60,214 hrs · 49,611 cycles

DURING SHOP VISIT THE AFT LOWER CHORD ANGLE WAS FOUND CRACKED. THE CHORD WAS REPAIRED PER MM 57-52-0, FIG 802.

Part: ANGLE — CRACKED (NR 2 TE FLAP) · airframe 60,214 hrs · 49,611 cycles

DURING SHOP VISIT THE AFT LOWER CHORD ANGLE WAS FOUND CRACKED. A SECTION OF THE ANGLE WAS REPLACED AND SPLICED TO OLD SECTION PER MM 57-52-0, FIG 802.

Part: FLAP TRACK — CORRODED (RT WING) · airframe 60,214 hrs · 49,611 cycles

HMV- ATTACH LUG HOLE FORWARD FITTING MLG WING DOOR CORRODED. REPAIRED PER MM 57-43-01.

Part: RIB — CRACKED (TE FLAP) · airframe 60,214 hrs · 49,611 cycles

DURING SHOP VISIT THE I/B AFT RIB WAS FOUND CRACKED IN THE LOWER RADIUS AT THE AFT END. THE CRACK WAS STOP DRILLED AND A DOUBLER INSTALLED PER 727 MM 57-52-0, FIG 808.

Part: PANEL — DAMAGED (VERTICAL STAB) · airframe 60,214 hrs · 49,611 cycles

AT HMV A TEMP REPAIR WAS INSTALLED ON LT SIDE OF VERT STAB AT L/E STA 1298 JUST FWD OF L/E PNL 9525. TEMP REPAIR WAS REMOVED AND DAMAGE CUT OUT AND PERM REPAIR INSTALLED PER MM 54-30-0 FIG 802.

Part: SKIN — CRACKED (VERTICAL STAB) · airframe 60,214 hrs · 49,611 cycles

AT HMV THE VERT SKIN WAS CRACKED AT PANEL 9523 LT FWD SIDE OF VERT STAB. REPAIR WAS FABRICATED PER MM 54-30-0 FIG 903 AND REPAIR WAS INSTALLED.

Part: SKIN — CRACKED (BS 480-500)

FUSELAGE SKIN FS 480-500, STRG 4L, SKIN LAP SPLICE, CRACK REPAIR. HFEC INSPECTION OF THE LOWER FASTENER ROW OF THE LOWER SKIN OF THE STRINGER 4L LAP SPLICE BETWEEN FS 480 AND 680 INDICATED A SINGLE CRACK BETWEEN FS 480 AND 500. THE CRACK WAS CUTOUT OF THE SKIN LAP AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER B727 SRM 53-30-3, FIG 5 AND ER/A 367765-14AD.

Part: SKIN — CRACKED (BS 700-720)

FUSELAGE SKIN FS 700-720, STRG 4R, SKIN LAP SPLICE : CRACK REPAIR. LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 680 AND 740 INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN. INTERNAL HFEC INSPECTION CONFIRMED A SINGLE CRACK BETWEEN FS 700 AND 720. THE CRACK WAS CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER B727 SRM 53-30-3, FIG 5 AND ER/A 367766-14AD.

Part: SKIN — CRACKED (BS 481-681)

FUSELAGE SKIN FS 481-681, STRG 4R, SKIN LAP SPLICE, CRACK REPAIR. LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 481 AND 681 INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN. INTERNAL HFEC INSPECTION CONFIRMED 29 CRACKS ALONG THE PANEL LENGTH. THE SKIN LAP WAS CUTOUT ALONG THE ENTIRE PANEL AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 367768-14AD.

Part: SKIN — CRACKED (BS 720)

FUSELAGE SKIN FS 720A-720B, STRG 4R SKIN LAP SPLICE CRACK REPAIR. LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 680 AND 740 INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN. INTERNAL HFEC INSPECTION CONFIRMED 3 CRACKS BETWEEN FS 720A AND 720B. THE CRACKS WERE CUTOUT OF THE SKIN LAP AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER B727 SRM 53-30-3, FIG. 5 AND ER/A 367767-14AD.

Part: LIGHT — INOPERATIVE (L2 DOOR)

L2 DOOR OVERHEAD EMERGENCY LIGHT INOP. REPLACED LIGHT ASSY, OPS CHKS GOOD.

Part: ANGLE — CORRODED (NR 2 ENGINE)

WHILE PERFORMING HUSH-KIT MOD, FOUND NR 2 ENG AFT MOUNT CHORD ANGLES CORRODED BEYOUND MFG SPECS. REPLACED CHORD ANGLES WITH ANGLES OF NEW MFG.

Part: ANGLE — CRACKED (BS 910)

A .25 INCH CRACK ON ANGLE FWD SIDE OF FS 910 RT ABOVE AND FWD OF H BRACKET. REPAIRED PER MM 53-11-0, TIME LIMITED REPAIR.

Part: ACTUATOR — LEAKING (NR 14 SPOILER)

ON WALKAROUND INSPECTION, FOUND NR 14 SPOILER ACTUATOR LEAKING.

Part: SKIN — DAMAGED (RT ELEVATOR)

DURING BUYBACK OF N/R 218, FOUND NUT PLATE EMBEDDED AT RT ELEVATOR LOWER SKIN. SKIN HAS .3125 INCH IN HOLE REPAIRED PER SRM 55-20-3.

Part: STRINGER — CRACKED (BS 848.95)

THE OUTER CHORD OF THE STRINGER 17L CREASE BEAM WAS FOUND WITH A .5 CRACK AT STA 848.95. THE CRACK WAS IN THE HORIZONTAL FLANGE OF THE TEE WHERE THE FLANGE WAS MILLED AWAY TO PASS UNDER THE FRAME. THE CRACK WAS ROUTED OUT OF THE HORIZONTAL FLANGE AND STOP DRILLED IN THE BASE FLANGE. TWO REPAIR ANGLES AND A STRAP WERE INSTALLED PER ER/A 364638-14, REV A.

Part: REAR SPAR — CRACKED (RT ELEVATOR)

AN .375 INCH CRACK RT ELEVATOR REAR SPAR AT 2ND FROM O/B TAB, HINGE. REPLACED REAR SPAR UNDER EO 4-70183-3AD ME 02 AND ME 03.

Part: BEAR STRAP — CRACKED (R1 DOOR)

FUSELAGE/SKIN ASSY, R1 DOOR SURROUND DOUBLER, UPPER HINGE CUTOU. REPAIR FOR CRACK IN REINFORCING DOUBLER. THE R1 DOOR SURROUND REINFORCING DOUBLER (BEAR STRAP) WAS FOUND WITH A TYPICAL CRACK IN THE UPPER HINGE CUTOUT. THE CRACK WAS IDENTIFIED AS BEING IN REGION 'E' PER BAC S/B 727-53-0136. THE CRACK WAS ROUTED OUT AND REPAIRED WITH A DOUBLER PER S/B 727-53-0136 AND ER/A 364614-14, REV A.

Part: SKIN — CRACKED (VERT STAB)

THREE EACH .125 IN CRACKS IN VERTICAL STABILIZER OUTER SKIN RT SIDE FWD OF PANEL 9501 (MARKED). INSTALLED REPAIR PER MM 54-30-0.

Part: BEAR STRAP — CRACKED (R1 DOOR CUTOUT)

FOUND ON MV2 CORROSION VISIT, CRACK IN EDGE OF BEARSTRAP AT RT FWD SERVICE DOOR UPPER HINGE CUTOUT UPPER FWD CORNER. REFERENCE SUPPLEMENTAL CARD FOR SI 4-72762-12 ME-02. REPAIRED PER ERA 364614-14 REV A.

Part: FLOORBEAM — CORROSION (BS 1030)

CORROSION FLOORBEAM STA 1030 BL 0. REMOVED CORROSION, FOUND OUT OF LIMITS PER SRM 53-10-1. REPAIRED PER SRM 53-20-11.

Part: BRACKET — CRACKED (NR 8 SLAT)

NR 8 SLAT ACT ATTACH BRACKET CRACKED AT WEB. REPAIRED PER MM 57-20-21 P 812.

Part: BRACKET — CRACKED (NR 2 LE FLAP ACT)

FOUND ON MV2 CORROSION VISIT, NR 2 L/E FLAP ACTUATOR O/B ATTACH BRACKET CRACKED, LOWER END. REPAIRED PER 57-20-21.

Part: BRACKET — CRACKED (NR 1 LE FLAP ACT)

FOUND ON MV2 CORROSION VISIT, NR 1 L/E FLAP ACTUATOR INBD ATTACH BRACKET CRACKED, UPPER AND LOWER CORNERS. REPAIRED PER M/M 57-20-21.

Part: STRINGER — CRACKED (BS 940)

FOUND ON MV2 CORROSION VISIT, 1 VISABLE CRACK STR 18A RT, AFT OF STA 940 FITTING UPPER AFT ATTACH BOLT. REPAIRED PER M/M 53-12-0.

Part: BRACKET — CRACKED (LT LE FLAP ACT)

FOUND ON MV2 CORROSION VISIT, NR 2 L/E FLAP I/B ACTUATOR ATTACH BRACKET CRACKED. REPAIRED PER M/M 57-20-21.

Part: CHARGER — INOPERATIVE (CABIN)

ON L/O, FOUND FWD O/H EMERGENCY AISLE AND EXIT LIGHT INOP. FOUND CHARGER BAD. REPLACED CHARGER, CKS OK.

Part: NUT — MISSING (NR 1 ENGINE)

FOUND DURING C-1 CHECK, UPPER ENGINE MOUNT CONE BOLT NUT MISSING AND BOLT BACKED OUT ABOUT .25 INCH. LOWER ENGINE MOUNT CONE BOLT NUT LOOSE, NO TORQUE STRIPS. DROPPED ENGINE AND REPLACED CONE BOLTS REF TRANS 4T216, OPN 5130, ERA 279520-14, SI 4-72242-12.

Part: SKIN — INOPERATIVE (CABIN)

FOUND EXIT SIGN ABOVE SEAT ROW 3 NOT ILLUMINATED DURING TEST. REPLACED BATTERY PACK, OPS CKS OK.

Part: SKIN — CRACKED (R-4 WINDOW CTOUT)

A .3750 INCH CRACK WAS FOUND IN THE R-4 WINDOW CUTOUT AT THE FWD, LWR EDGE OF THE CUTOUT. REPAIRED PER SRM 53-30-3, FIG 8, REPAIR V.

Part: SKIN — CORRODED (BS 720)

THE SKIN BETWEEN S-28 LT AND S-28 RT AT STA 720 WAS FOUND TO BE CORRODED. THE DAMAGE WAS REMOVED AND A DOUBLER WAS INSTALLED PER DL ERA 302443-14AD.

Part: VERT STIFFENER — CRACKED (BS 1263)

DURING CV-2 IN TPA, THE RT TORQUE BOX VERTICAL STIFFENER ANGLE AT STA 1263 WAS FOUND CRACKED. THE VERTICAL STIFFENER ANGLE WAS REPLACED IN ACCORDANCE WITH S/B 727-53-0129 REV 4.

Part: SKIN — DENTED (RT ELEVATOR)

FOUND ON CV2 CHECK, SEVERAL DENTS AND GOUGES AT TOP SIDE OF RT ELEVATOR O/B END. REPAIRED PER SRM 55-20-3 FIG 4, O/B DENT ONLY. THE I/B DENTS WITHIN LIMITS PER SRM 55-20-1.

Part: ANGLE — CRACKED (NR 7/8 SLAT)

CRACK ON ANGLE NR 7 LE SLAT BELOW ANTI-ICE TUBE. CRACK ON ANGLE BELOW INBD STOP PAD NR 8 SLAT. FOUND AT B-1 LETTER CK, REPAIRED PER MM 57-54-0.

Part: ANGLES — CRACKED (NR 2/3 SLAT)

CRACK ON SUPPORT ANGLE ON NR 3 SLAT BELOW TAI DUCT. CRACK BELOW I/B STOP PAD ON NR 2 SLAT. FOUND AT B-1 LTR CHECK, REPAIRED PER MMM 57-54-0.

Part: EEL BATTERY — DISCHARGED (RT OVERWING)

ON LAYOVER HAD RIGHT OVERWING EMERGENCY LIGHT INOP. REPLACED BATTERY, OPERATION NORMAL.

Part: EEL BATTERY — DISCHARGED (CABIN)

DURING LAY OVER, R2 OVERWING EMERGENCY EXIT LIGHT FAILED TO TEST. REPLACED BATTERY PACK, OPERATION NORMAL.

Part: EEL BATTERY — DISCHARGED (CABIN)

ON PRE-FLIGHT CHECK, FOUND RIGHT OVERWING EMERGENCY EXIT LIGHT INOP. REPLACED BATTERY PACK OPERATION NORMAL.

Part: NOSE COWL — WORN (NR 1 ENGINE)

DURING ROUTINE SHOP INSPECTION THE AFT LANDING STRIP BETWEEN 8-9 0'CLOCK POSITION WAS FOUND TO BE WORN. ON NR 1 ENGINE NOSE COWL, REPAIRED PER SRM 54-10-3 FIG 3.