N529DA

Part: BATTERY — DISCHARGED (FLASHLIGHT) · airframe 58,396 hrs · 44,788 cycles

AFT FLT ATTENDANT FLASHLIGHT BLINKS EVERY 12 SECONDS. REPLACED BATTERIES.

Part: SKIN — CRACKED (VERTICAL STAB) · airframe 58,050 hrs · 44,518 cycles

A CRACK WAS FOUND IN THE VERTICAL STABILIZER SKIN AT FS 1210 AND STRINGER 3A ON THE LEFT HAND SIDE. THE CRACK WAS REMOVED WITH A 1.4 X 2.7 CUTOUT AND AN EXTERNAL DOUBLER WAS INSTALLED PER ERA 334389-14 AT HMV.

Part: HINGE FITTING — CORRODED (HORIZONTAL STAB) · airframe 58,016 hrs · 44,495 cycles

THE HORIZONTAL STABILIZER REAR SPAR HINGE FITTING LUGS WERE FOUND WORN ON THE LT AND RT I/B LUG FACES. THE LT I/B LUG FACE WAS SPOTFACED 0.010 AND THE RT I/B LUG FACE WAS SPOTFACED 0.015 TO REMOVE THE WEAR. THE LT I/B LUG BORE WAS REAMED TO 2.2345 DIA AND THE RT I/B LUG BORE WAS REAMED TO 2.2455 TO REMOVE CORROSION. ER/A 334373-14 REV A.

Part: SKIN — CRACKED (FUSELAGE) · airframe 58,016 hrs · 44,495 cycles

THE FUSELAGE SKIN WAS FOUND CRACKED AT THE STR 4L LAP JOINT BETWEEN FS 360 AND FS 481. THE LAP JOINT WAS REMOVED AND REPLACED PER ERA 334350-14AD AT HMV.

Part: SKIN — CRACKED (FUSELAGE) · airframe 58,016 hrs · 44,495 cycles

THE FUSELAGE SKIN WAS FOUND CRACKED AT THE STR 4R LAP JOINT BETWEEN FS 400 AND FS 420. ERA 334362-14AD AUTHORIZES THE REMOVAL OF THE DAMAGE AND REPAIRS THE DAMAGE PER SRM 53-30-3 FIGURE 5. THE DAMAGE WAS FOUND AT HMV.

Part: SKIN — CRACKED (FUSELAGE) · airframe 58,016 hrs · 44,495 cycles

CRACKS WERE FOUND IN THE STR 4R LAP JOINT BETWEEN FS 480 AND FS 500. ERA 334363-14 AUTHORIZES THE DAMAGE TO BE CUT OUT AND REPAIRED PER SRM 53-30-3, FIGURE 5. THE DAMAGE WAS FOUND AT HMV.

Part: SPAR — CRACKED (VERTICAL STAB) · airframe 58,016 hrs · 44,495 cycles

AT HMV2 FROM N/R 794 - FABBED PER PRI 334389-14 4-27-00/1900, INSTALLED, FABBED ACCESS DOUBLER AND PANEL PER OPN 7951, R/C 994. REMOVED FASTENERS ON STRINGER 6 BELOW ACCESS HOLE TO FOM, FABBED ACCESS PANEL/DOUBLER PER OPN 7951/R/C994.

Part: WEB — CRACKED (TAIL) · airframe 58,016 hrs · 44,495 cycles

VERTICAL WEB----CRACKED RIB CUTOUT-FS 1303 VERT WEB CRACKED AT RT RIB CUTOUT. LT RIB CUTOUT SAME CONDITION. REMOVED SUPPORT BRACKET ABOVE S-DUCT AND BEGAN REMOVING FASTENERS FROM REPAIR AREA. DYE PENNED AREA AND STOP DRILLED CRACKS. CHEMICAL TREATED PER PS 900-2-4-1 NR 2. OK TO INSTALL. INSTALLED DOUBLERS BOTH SIDE PER SRM 53-10-1D AND INSTALLED SUPPORT BRACKET.

Part: MOUNT — CORRODED (TENSION PLATE) · airframe 58,016 hrs · 44,495 cycles

FACE-CORRODED CENTER AFT MOUNT PAD FOR TENSION TIE PLATE CORRODED ON TOP SURFACE. REMOVED DAMAGE WITHIN LIMITS AS PER SRM 55-30-50 FIG 801D. ROTO PEENED PER PS 900-4- NR 5. OK TO TREAT. REPAIRED PER SRM 55-30-50 FIG 801D.

Part: SKIN — CRACKED (TE FLAPS) · airframe 58,016 hrs · 44,495 cycles

DURING SHOP VISIT, THE COVE SKIN WAS FOUND CRACKED AT I/B AFT FLAP DRIVE ROD CUTOUT. THE DAMAGE WAS REPAIRED PER 727 M/M 57-52-0, FIG 809 BY REMOVING THE CRACK AND INSTALLING A DOUBLER AND SKIN FILLER.

Part: SKIN — DAMAGED (LE SLAT) · airframe 58,016 hrs · 44,495 cycles

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

Part: SKIN — DAMAGED (TE FLAP) · airframe 58,016 hrs · 44,495 cycles

DURING SHOP VISIT, THE LEADING EDGE SKIN WAS FOUND WORN AT THE I/B END OF THE MIDFLAP. THE SKIN WAS REPAIRED BY REMOVING THE DAMAGE AND INSTALLING A DOUBLER AND FLUSH FILLER PER MM 57-52-0, FIG 803.

Part: ANGLE — CRACKED (TE FLAP) · airframe 58,016 hrs · 44,495 cycles

DURING SHOP VISIT, THE AFT SPAR LOWER ANGLE WAS FOUND CRACKED 20, 37, AND 55 INCHES FROM I/B END OF FLAP. A SECTION OF ANGLE WAS REPLACED AND SPLICED IN PER 727 M/M 57-52-0, FIG 802.

Part: FLAP TRACK — CORRODED (TE FLAP) · airframe 58,016 hrs · 44,495 cycles

DURING OVERHAUL OF THE I/B FLAP, I/B TRACK, SEVERAL AREAS EXCEEDED APPROVED LIMITS FOR WEAR. AREAS INCLUDED MLG BEAM ATTACH BOLT HOLES, NOTCHES, AND SPOTFACES, THE SPOILER BEAM ATTACH BOLT HOLES, THE MLG DOOR FWD AND AFT HINGE FITTING HOLES, THE SPLICE PLATE ATTACH HOLES, THE FWD ATTACH LUG BORES AND FACES, THE TOGGLE DETENT HOLE, THE CLIP ASSEMBLY ATTACH HOLES, AND THE SPACER BAR ATTACH BOLT HOLES REPAIR PER ER/A 387544-14AD AND BF GOODRICH ENGINEERING REPORT 23-0684.

Part: SKIN — CRACKED (FUSELAGE) · airframe 58,016 hrs · 44,495 cycles

THREE CRACKS WERE FOUND IN THE STR 4L LAP JOINT IN THE LOWER SKIN BETWEEN FS 380 AND FS 480. THE LAP JOINT WAS REPLACED FROM FS 360 TO FS 480 PER ERA 334350-14AD AT HMV.

Part: FLAP TRACK — CORRODED (TE FLAP) · airframe 58,016 hrs · 44,495 cycles

DURING OVERHAUL OF THE I/B FLAP, I/B TRACK ASSY AT BF GOODRICH, TYPICAL CORROSION WAS FOUND AT THE MLG AND SPOILER BEAM ATTACH PAD AREAS, AND TYPICAL WEAR WAS FOUND AT THE FWD ATTACH LUGS, MLG DOOR HINGE FITTING ATTACH HOLES, AND THE TOGGLE DETENT HOLE. DIMENSIONS WERE OUTSIDE LIMITS AT THE MLG BEAM ATTACH BOLT HOLES AND SPOT FACES, SPOILER BEAM ATTACH HOLES, MLG DOOR FWD AND AFT HINGE FITTING ATTACH HOLES, FWD ATTACH LUGS AND THE DETENT HOLE. REPAIR PER ER/A 387543-14AD AND BF GOODRICH ENGINEERING REPAIR NR 23-0709.

Part: SKIN — CRACKED (VERTICAL STAB) · airframe 58,016 hrs · 44,495 cycles

AT HMV2 FOUND SKIN CRACKED, LT SIDE VERT STAB AT FRONT SPAR. SKIN HAS TWO CRACKS ABOVE FS 1210, W/W N/R 1080. REMOVED DAMAGE PER DRD 55-30-3D, HFEC INSP PER DRD 55-30-3D NO DISCREPANCIES FOUND IN THIS AREA, REMOVED DAMAGE PER PRI 334389-14 DATED 4-27-00/1900, DRILLED ADD FASTENER HOLES ON A/C PER PRI 334389-14 4-27-00/1900, DRILLED DOUBLER PER PRI 334399-14 4-27-00/1900, CONTNUED ON N/R 1178.

Part: ANGLE — BENT (NR 2 NACELLE) · airframe 58,016 hrs · 44,495 cycles

AT HMV THE NBR 2 ENG FWD RT COWL CONTACT ANGLE WAS BENT AT THE 5 O''CLOCK POS AT STA 1351. TRIMMED WORN CAP FLANGE, FABRICATED REPAIR ANGLE PER 53-11-0, VERIFIED 2024-T4 HARDNESS TEST, INSTALLED REPAIR PER 53-11-0.

Part: RIB — CRACKED (NR 2 SLAT) · airframe 58,016 hrs · 44,495 cycles

AT HMV, THE RIB OF THE NR 2 SLAT WAS FOUND CRACKED JUST O/B OF ANTI-ICE DUCT. REMOVED DAMAGE AND MADE DOUBLER AND FILLER. INSTALLED DOUBLER AND FILLER PER MM 57-54-0 FIG 814.

Part: SPLICE — CORRODED (FUSELAGE) · airframe 58,016 hrs · 44,495 cycles

AT HMV2, FOUND SPLICE STRAP CORRODED FS 970 - 990 STR 29R. REMOVED CORR PER SRM 51-10-6 & COMMON FASTENERS THRU SKIN FOR FURTHER EVAL, REMOVED RT SIDE OF REPAIR ANGLE, CLEANED/REMOVED ALL CORROSION PER SRM 51-10-6, WITHIN LIMITS PER 53-10-110, ROTO PEENED ARE PER SRM 53-10-11D, OK T&P, RE-INSTALLED ANGLE PER 53-10-11D.

Part: BATTERY — DISCHARGED (CABIN)

RIGHT OVERWING EMERGENCY LIGHT FLASHING. REPLACED BATTERY PACK.

Part: LATCH ROLLER — OUT OF ADJUST (PAX DOOR)

ON TAKEOFF ROLL, L-1 DOOR LIGHT ILLUMINATED AND F/A NOTICED DOOR HANDLE MOVED AND GAP WAS SEEN UNDER DOOR. REPLACED GUIDE ARMS, FOUND DOOR LATCH ROLLER OVER CENTER RIGGING OUT OF ADJUSTMENT. ADJUSTED SAME AND RIGGED DOOR. OP CHECKS GOOD.

Part: SKIN — DENTED (BS 1166-1183)

THE FUSELAGE SKIN WAS FOUND DENTED JUST ABOVE STRINGER 21R BETWEEN FS 1166 AND 1183. THE DENT WAS CUT OUT 2 X 7.25, REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 366004-14, REV B.

Part: FITTING — CRACKED (NR 7 SLAT ACT)

O/B SUPPORT FOR ACTUATOR FITTING LOBE CRACKED AT NR 7 SLAT. REPAIRED PER MM 57-42-0.

Part: SKIN — CORRODED (BS 1080)

FUSELAGE SKIN FS 1070-109, STRG 28R, SKIN CORROSION CUTOUT REPAIR. THE FUSELAGE SKIN WAS FOUND CORRODED IN TWO AREAS NEAR S-28R BETWEEN FS 1070 AND 1091. THE CORRODED AREAS WERE CUTOUT WITH A 14.25 BY 3.25 CUTUOUT AND A .75 BY 1.5 CUTOUT. BOTH CUTOUTS WERE REPAIRED WITH A SINGLE EXTERNAL ALUMINUM DOUBLER, INSTALLED PER B727 SRM 53-30-3, FIG 3 AND DOCUMENTED PER ER/A 365930-14.

Part: SKIN — CRACKED (L1 DOORWAY)

A 1 INCH CRACK WAS FOUND IN THE SKIN AT THE UPPER HINGE CUTOUT OF THE FWD ENTRY DOOR CUTOUT. AN EXISTING EXTERNAL DOUBLER REPAIR WAS LOCATED MIDWAY BETWEEN THE UPPER HINGE CUTOUT ANDTHE LOWER HINGE CUTOUT. THE UPPER HINGE CRACK WAS REPAIRED PER SRM 53-30-3, FIG 29 & 31 (BASED ON S/B REPAIR) AND THE EXISTING DOUBLER WAS REMOVED AND REPLACED WITH AN INTERNAL DOUBLER INSTALLED PER SRM 53-30-3 FIG 13.

Part: BLKHD STIFFENER — CRACKED (BS 1183)

THE FS 1183 BULKHEAD VERTICAL STIFFENER AT RBL 36.83 WAS FOUND WITH TYPICAL CRACKING AT WL 240. THE CRACKED STIFFENER WAS REPAIRED PER BAC S/B 727-53-0192 AND DOCUMENTED PER ER/A 365894-14.

Part: ACCESS PANEL — CRACKED (LT ELEVATOR)

TWO INCH CRACK IN NR 2 LT BALANCE BOARD ACCESS PANEL AT O/B EDGE (MARKED). INSTALLED REPAIR DOUBLER PER SRM 55-20-3 FIG 5.

Part: PANEL — CRACKED (RT HORIZ STAB)

A 1.25 INCH CRACK AT NR 1 RT BALANCE BOARD ACCESS PANEL O/B EDGE (MARKED).

Part: SKIN — CRACKED (LT ELEVATOR)

1 INCH HOLE WITH CRACKS AT LT ELEVATOR UPPER SKIN AT INBD END. REPAIRED PER 727 SRM 55-20-3 FIG 4.

Part: BATTERY PACK — DISCHARGED (CABIN)

ALL 1ST CABIN SEAT MOUNTED EMERGENCY EXIT LIGHT AND ROWS 10 AND 11 EMERGENCY EXIT PATH LIGHTS INOP DURING STBY POWER CHECK. REPLACED BATTERY PACK AND BATTERY RACK OPS CKS OK.

Part: RIB — CRACKED (NR 7 LE SLAT)

FOUND ON E2 LETTER CK, 2 CRACKS IN NR 7 SLAT NOSE RIB AT THE OUTBD SIDE OF THE ACTUATOR. REPAIRED PER MM 57-54-0.

Part: LIGHT — INOPERATIVE (CABIN)

AFT OUTBOARD EMERGENCY FLASHLIGHT IS NOT FLASHING. REPLACED FLASHLIGHT ASSY AND BREAKAWAY BAND.

Part: SKIN — CRACKED (FUSELAGE)

FOUND .25 INCH CRACK IN A/C SKIN LEFT FWD OF A/C JUST AFT OF THE DOOR. REPAIRED PER SRM 53-30-03.

Part: BATTERY PACK — DISCHARGED (CABIN)

AFT TWO EXTERNAL EMERGENCY LIGHTS INOP. REPLACED BATTERY PACK.

Part: RIB — CRACKED (NR 4 LE SLAT)

FOUND DURING E 1 LETTER CHECK .0625 INCH CRACK PAST STOP DRILL AT NR 4 SLAT O/B ACTUATOR MOUNT RIB. REPAIR PER MM 57-54-0.

Part: FIRE LOOP — MALFUNCTIONED (NR 3 ENGINE)

ON CLIMBOUT, NR 3 ENGINE FIRE LIGHT ILLUMINATED. FIRE DETECTOR SWITCH IN A-MODE AS PER MCO. ALL OTHER ENGINE INDICATIONS NORMAL. SHUTDOWN ENGINE AS PER POM, FIRED BOTH BOTTLES AS PER POM AND FIRE LIGHT REMAINED ON UNTIL LANDING. TESTED FIRE LIGHT AFTER IT WENT OUT AFTER LANDING AND IT RE-ILLUMINATED AND STAYED ILLUMINATED AFTER TEST. REPLACED NR 3 ENG FIRE WARNING LOOP, CKS GOOD NO FIRE IND.

Part: FAN — SHORTED (CABIN)

STRONG ELECTRICAL FUMES IN ACFT, COINCIDING WITH GASPER FAN C/B POPPED. REPLACED GASPER FAN, CKS OK.

Part: WIRE HARNESS — CHAFED (FUSELAGE)

DURING PREFLIGHT CK, STANDBY HYD PUMP WAS INOPERATIVE WITH THE ASSOCIATED CIRCUIT BREAKER POPPED. FOUND THE WIRE HARNESS TO THE PUMP HAD CHAFED ON A STRINGER IN THE LT 48 SECT BEHIND THE PUMP, ALSO CAUSING DAMAGE TO THE STRINGER. THE PUMP WAS REPLACED, THE WIRE HARNESS REPAIRED AND STRINGER NR 15 REPAIRED PER SRM 53-10-03 FIG 1.

Part: STRINGER — CRACKED (VERT STAB)

FOUND THREE VERTICAL STABILIZER STRINGERS CRACKED AT STR 9 LEFT STA 157.200, STR 9 LEFT STA 110.400 AND STR 6 LEFT STA 6.372. REPAIRED PER M/M 55-30-0.

Part: SKIN — CRACKED (VERT STAB)

FOUND A 1 INCH CRACK ON THE VERTICAL STAB SKIN LT SIDE BELOW LOWER VORTEX GENERATOR. REPAIRED PER MM 55-30-0.

Part: WEB — CRACKED (BS 1226)

FOUND LOWER TORQUE BOX VERTICAL WEB CRACKED IN TWO PLACES STA 1236 AND STA 1226 RIGHT SIDE. REPAIRED PER M/M 53-11-0.

Part: CHORD — CRACKED (VERT STAB)

FOUND THE VERTICAL STAB BULKHEAD CHORD CRACKED AT STA 157.200, STR 10 LEFT. REPAIRED PER M/M 55-30-0.

Part: SKIN — CORROSION (BS 1058)

CORROSION WAS DISCOVERED IN THE FUSELAGE SKIN AT STA 1050, STR 28L. THE RESULTING DAMAGE CUTOUT IS 10 INCH FWD/AFT, BY 4.75 INCH I/B AND O/B AND IS CENTRALLY LOCATED AT THE INTERSECTION OF THE FRAME AT STA 1050 AND STR 28L. ALSO, STR 28L IS CORRODED AND WILL BE SPLICED FWD AND AFT OF THE DAMAGE CUTOUT. THE SKIN AT THIS LOCATION IS MANUFACTURED FROM 0.140 2024-T3 CLAD, MACHINED LOCALLY TO 0.070 AND 0.050. THE STRINGER IS MANUFACTURED FROM BAC1498-145, 7075-T6 EXTRUSION.

Part: SKIN — CRACKED (L1 DOOR)

FOUND ON C2 LETTER CHECK, MAIN ENTRY DOOR OUTER SKIN CRACKED .75 INCH LOWER AFT CORNER. REPAIRED PER MM 52-11-01.

Part: SKIN — CORROSION (BS 720)

CORROSION WAS FOUND ON THE RAM AIR ACTUATOR ACCESS DOOR CUT-OUT AT THE FWD LT CORNER AND LT SIDE OF THE AFT EDGE. THE SKIN IS 0.168 INCH (MEASURED) CLAD 2024-T3 AND IS CHEM MILLED AROUND THE DOOR TO 0.085 INCH (MEASURED). ACCOMPLISHED REPAIRS PER DL ERA 302626-14.

Part: ANGLE — CRACKED (NR 7 LE SLAT)

FOUND ON CV2 CHECK, COVE SKIN SUPPORT ANGLE CRACKED AT INBD STOP PAD NR 7 SLAT. FASTENERS LOOSE OUTBD SLAT TRACK FAIRING NR 7 SLAT. REPAIRED PER M/M 57-54-0 2. REPLACED FASTENER.

Part: ANGLE — CORRODED (BS 740)

FOUND ON CV2 CHECK, CORROSION ON SKIN SUPPORT ANGLE STA 740 AND RBL 10. REPAIRED PER M/M 53-11-0 PG 858, REPLACED SKIN SUPPORT ANGLE.

Part: ANGLE — CRACKED (NR 6 LE SLAT)

FOUND ON CV2 CHECK, COVE SKIN SUPPORT ANGLE CRACKED AT INBD STOP PAD NR 6 SLAT. REPAIRED PER M/M 57-54-0 FIG 816.

Part: FLOOR BEAM — CORRODED (BS 400)

FOUND ON CV2 CHECK, CORROSION ON FLOOR BEAM CORRODED AT STA 400 BETWEEN BL ZERO AND RBL 44. REPAIR: REPAIRED PER MM 53-20-11, FIG 804 A.

Part: RIB — CRACKED (NR 7 LE FLAP)

1) NR 7 SLAT ACT ROD END WEB CRACKED I/B AFT SIDE. 2) NR 7 SLAT ACT ROD END WEB CRACKED O/B AFT SIDE. FOUND DURING C-1 LTR CK. REPAIRED BOTH ITEMS PER MM 57-54-0 PAR 3B.

Part: ANGLE — CRACKED (NR 3 LE FLAP)

ANGLE CRACKED .50 INCH BELOW TAI DUCT ON NR 3 SLAT. FOUND AT C-1 LTR CK. REPAIRED PER MM 57-54-0 PG 807.

Part: FAIRING — CRACKED (NR 5 LE FLAP)

NR 5 SLAT I/B TRACK FAIRING CRACKED. FOUND AT C-1 LTR CK. REPAIRED PER MM 57-54-0 PG 820.

Part: ANGLE — CRACKED (NR 7 LE FLAP)

1.25 INCH CRACK IN NR 7 SLAT ACT I/B ATTACH FITTING, AFT OF UPPER MOUNT BOLT ON WING FRONT SPAR. FOUND AT C-1 LTR CK. REPAIRED PER MM 57-42-0.