N532DA

Part: BATTERY — DISCHARGED (AIRSTAIRS) · airframe 62,617 hrs · 46,606 cycles

AFT AIRSTAIR EMERGENCY LIGHT VERY DIM. REPLACED BATTERIES.

Part: RESERVOIR — LOW (HYDRAULIC SYS) · airframe 62,251 hrs · 46,360 cycles

RETURNED TO DFW FOR LOW HYDRAULICS FLUID IN SYSTEM A. SERVICED A SYSTEM TO 4.4 GALLONS. INSPECTED ACFT FOR LEAKS, NONE FOUND.

Part: FITTING — CRACKED (PYLON) · airframe 61,774 hrs · 46,039 cycles

DURING INSPECTIONS PER AD 97-05-08, CRACKS WERE FOUND IN THE#1 FORWARD ENGINE MOUNT AT HOLES C AND D. THE HOLES WERE OVERSIZED, INSPECTED AND NEW FASTENERS INSTALLED PER ERA 397735-14AD AT HMV.

Part: SKIN — CRACKED (SKIN) · airframe 61,760 hrs · 46,028 cycles

DURING AN INSPECTION REQUIRED BY AD 99-04-22 CRACKS WERE FOUND IN THE STR 4R LAP JOINT BETWEEN FS 660 AND 680. THE CRACKS WERE CUT OUT AND AN EXTERNAL REPAIR INSTALLED. THE DAMAGE WAS FOUND AT HMV.

Part: FRAME — CRACKED (CABIN) · airframe 61,760 hrs · 46,028 cycles

DURING HMV A CRACK WAS FOUND IN THE FS 344 FRAME DIRECTLY ABOVE THE L1 DOOR. THE CRACK WAS .5". THE CRACK WAS CUT OUT AND A DOUBLER WAS INSTALLED. THE DAMAGE WAS FOUND AT HMV.

Part: SKIN — CRACKED (SKIN) · airframe 61,760 hrs · 46,028 cycles

DURING THE ACCOMPLISHMENT OF THE INSPECTIONS REQUIRED BY AD 99-04-22, TWO CRACKS WERE FOUND IN THE STR 4L LAP JOINT BETWEEN FS 380 AND 400. THE CRACKS WERE CUT OUT AND REPAIRED PER B727 SRM 53-30-3, FIGURE 5. THE CRACKS WERE FOUND AT HMV.

Part: SKIN — CORRODED (SKIN) · airframe 61,756 hrs · 46,025 cycles

THE FUSELAGE SKIN AND STRINGER WERE FOUND CORRODED AT FS 950E AND STR 29R. THE STRINGER WAS CUT AT FS 950D +10 AND REMOVED TO THE AFT END OF THE PART. A NEW SECTION WAS SPLICED IN. AN EXTERNAL DOUBLER AND TRIPLE WERE USED TO REPAIR THE SKIN. THE DAMAGE WAS FOUND AT HMV.

Part: SKIN — CORRODED (SKIN) · airframe 61,756 hrs · 46,025 cycles

THE FUSELAGE SKIN WAS FOUND TO BE CORRODED AT FS1009 BETWEENSTR 29L AND 28R. THE SKIN WAS REPAIRED SIMILIAR TO THAT OF SRM 53-30-3, FIGURE 3A. THE DAMAGE WAS FOUND AT HMV.

Part: SKIN — CRACKED (FUSELAGE) · airframe 61,756 hrs · 46,025 cycles

A CRACK WAS FOUND IN THE STR 26L LAP JOINT BETWEEN FS 620 AND 640. THE CRACK WAS REMOVED AND REPIARED PER SRM 53-30-3, FIGURE 5. THE DAMAGE WAS FOUND AT HMV.

Part: FLAP TRACK — CORRODED (T/E FLAP) · airframe 61,756 hrs · 46,025 cycles

DURING OVERHAUL THE INBD FLAP, INBD TRACK WAS FOUND WITH CORROSION AND WEAR EXCEEDING THE ALLOWABLE LIMITS. REPAIRED PER ER/A 401900-14AD AND BF GOODRICH DOCUMENT 23-0682.

Part: FLAP TRACK — CORRODED (T/E FLAP) · airframe 61,756 hrs · 46,025 cycles

DURING OVERHAUL THE INBD FLAP, INBD TRACK ASSY WAS FOUND WITH CORROSION AND WEAR. DAMAGE EXCEEDED ALLOWABLE LIMITS AT THE MLG BEAM ATTACH BOLT HOLES AND SPOTFACES, SPOILER BEAM ATTACH HOLES, MLG DOOR FWD AND AFT HINGE FITTING ATTACH HOLES, HINGE SUPPORT FITTING HOLES, FWD ATTACH LUG BORES AND GAPS, AND THE TOGGLE DETENT HOLE. REPAIR PER ER/A 401901-14AD AND BF GOODRICH DOCUMENT 23-0859.

Part: FASTENER — LOOSE (L/E SLAT) · airframe 61,756 hrs · 46,025 cycles

NR 2 SLAT I/B ACTUATOR RIB FASTENERS LOOSE. REQUIRING A SKIN SPLICE PER 727 SRM CH 57-54-000-8 FIG 801. ACTUAL DAMAGE NOT RELATED TO METHOD USED TO GAIN ACCESS. REASON FOR MAJOR REPAIR CLASSIFICATION UNKNOWN.

Part: FRAME — WORN (#2 ENG COWL) · airframe 61,756 hrs · 46,025 cycles

AT HMV FOUND FRAME WORN STA.1342 6,O-CLOCK POSITION FRAME FOR FWD END OF #2 ENG COWL'S. CORR: REMVD DAMAGE PER MM 53-11-000-8,FABD REPAIR ANGLE PER MM 53-11-000-8,2054-0-.071,DRILLED DOUBLER PER MM 53-11-000-8,FABD FILLER,OK INSTL REPAIR,T/P PER PS 2-4-1 #2,INSTLD DBLER PER MM 53-11-000-8.

Part: ANGLE — CRACKED (T/E FLAP) · airframe 61,756 hrs · 46,025 cycles

AFT CHORD ANGLE CRACKED 22 INCHES AND 37 INCHES FROM THE I/B END. REPAIRED NR 3 FLAP CHORD ANGLE.

Part: SPAR — CRACKED (WING) · airframe 61,756 hrs · 46,025 cycles

AT HMV FOUND FAST SPAR LWR CHORD - CRACK, REPAIR LOOSE LOC AT LWR END OF NR 7 SPOILER ACT FITTING. REMOVED NR 6/7 SPOILER MOUNT ARM, REMOVED DAMAGED SECTION OF BEAM PER MM 57-55-00-08 FIG 805, FABD AND DRILLED UP PARTS PER MM 57-55-00-08 FIG 805, OK TO INSTALL, INSTALLED REPAIR PER MM 57-55-00-08 AND REINSTALLED SUPPORT ARM.

Part: LIGHT — INOPERATIVE (R1 DOOR) · airframe 61,468 hrs · 45,818 cycles

1R DOOR EMERGENCY LIGHT WOULD NOT COME ON WITH TEST. REPLACED EMER LIGHT ASSY.

Part: BATTERY — INOPERATIVE (CABIN) · airframe 60,089 hrs · 44,862 cycles

EMERGENCY EXIT LIGHT NOT HOLDING CHARGE. REPLACED BATTERY.

Part: BEAM — CRACKED (FUSELAGE) · airframe 59,199 hrs · 44,262 cycles

HFEC BOLT HOLE INSPECTION OF TWO FASTENERS COMMON TO AN INTERCOSTAL AND THE FWD CAP OF THE FS 1183 BULKHEAD VERTICAL BEAM AT RBL 17.8 AND WL 273.25 REVEALED CRACK INDICATIONS. THE HOLES WERE OVERSIZED TO REMOVE THE CRACK INDICATIONS WITH AN ADDITIONAL INSURANCE CUT. OVERSIZE FASTENER WERE INSTALLED IN THE HOLES. THE REPAIR WAS ACCOMPLISHED PER ER/A 377542-14AD.

Part: ACTUATOR — LEAKING (NR 7 SLAT) · airframe 59,169 hrs · 44,240 cycles

ON T/O ROLL IN MSO, BOTH SYS A HYDRAULIC LOW PRESSURE LIGHTS CAME ON AT APROX 100 KIAS, SYS A QTY RAPIDLY WENT TO ZERO. T/O CONTINUED CHECKLIST C/W, UNEVENTFUL LANDING IN MSO. MTC FOUND NR 7 SLAT ACTUATOR LEAKING. REPLACED SAME.

Part: ACM — MALFUNCTIONED (LEFT PACK) · airframe 58,712 hrs · 43,920 cycles

LEFT PACK ON DESCENT INCREASED TO 90 DEGREES AND SMOKE WAS EXHAUSTING BRIEFLY INTO THE CABIN WITH A SMELL. REDUCING MANUALLY TO 50 DEGREES STOPPED SMOKE. MTC ATL NOTIFIED IN FLIGHT. REMAINDER OF FLIGHT NORMAL. RAN LEFT PACK IN AUTO AND MANUAL THROUGH FULL TEMP RANGES. ALL INDICATIONS NORMAL. NO SMELL OR SMOKE IN CABIN. REPLACED CABIN TEMP CONTOLLER AS PRECAUTION. OPS CKS GOOD.

Part: BRAKE — FAILED (MLG)

ON LANDING, NR2 BRAKE LOCKED AND BLEW NR 2 MAIN TIRE. REPLACED NR 2 BRAKE, NR 1 AND NR 2 WHEEL ASSY. T/S NR 2 WHEEL ANTI-SKID SYSTEM. OPERATION NORMAL.

Part: BATTERY — DISCHARGED (L2 DOOR)

L-2 DOOR OVERHEAD EMERGENCY LT WOULD NOT TEST REPLACED BATTERY PACK.

Part: SKIN — CRACKED (BS 360-481)

FUSELAGE SKIN FS 360-481 STRINGER 4R SKIN LAP SPLICE, CRACK REPAIR. LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 360 AND 481 INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN. INTERNAL HFEC INSPECTION CONFIRMED 5 CRACKS IN 3 CONSECUTIVE FRAME BAYS. THE SKIN LAP WAS CUTOUT ALONG THE PANEL LENGTH AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 367160-14AD.

Part: WEB — CRACK (BS 1303)

FOUND ON MV2 CK, .5 INCH CRACK STA 1303 WEB RT AT LOWER RT CORNER. REF NR 143. FOUND ON MV2 CK, .5 INCH CRACK STA 1303 WEB RT AT THE CUTOUT FOR THE STRINGER. REF NR 142. BOTH CRACKS REPAIRED WITH THE SAME DOUBLER PER SRM 53-10-4.

Part: WEB — CRACKED (BS 1303)

FOUND ON MV2 CK, .5 INCH CRACK IN STA 1303 WEB LT LOWER CORNER. REPAIRED PER SRM 53-10-4.

Part: FRAME — CRACKED (PAX DOORWAY)

FOUND DURING MV2 CORROSION VISIT NRC 134, .375 INCH VISIBLE CRACK LT CUTOUT FRAME, AFT ENTRY DOORWAY AT SECOND FROM UPPER STOP CASTING. REPAIRED PER SRM 53-10-9.

Part: STRINGER — CRACKED (WS 656.5)

REPAIRED CRACK AT UPPER STRINGER TO RIB FASTENER HOLE AT RT WING STA 656.50 STR 14 PER M/M 57-13-0.

Part: DOUBLER — CRACKED (NR 8 LE SLAT ACT)

WING FIXED LEADING EDGE, NR 8 SLAT ACTUTOR SUPPORT BRACKET REPAIR FOR CRACKED DOUBLER. THE OUTBD SUPPORT BRACKET DOUBLER FOR THE NR 8 SLAT WAS FOUND CRACKED. THE INBD AND OUTBD ACTUATOR BRACKETS FOR THE NR 8 SLAT WERE REPAIRED/MODIFIED PER THE REQUIREMENTS OF B727 S/B727-57-0130. THE REPAIR/MODIFICATION WAS DOCUMENTED PER ER/A 366349-14AD.

Part: WIRE — BROKEN (CABIN)

EMERGENCY TRACK LIGHTING SECTION IN FWD COACH AREA DOES NOT ILLUMINATE. REPAIRED SECTION OF WIRE.

Part: COWL — CRACKED (NR 2 ENGINE)

FOUND .75 INCH CRACK NR 2 ENG NOSE COWL 10 INCH AFT OF NOSE RING 3.00 POS. REPAIRED PER MM 54-30-0 P 801.

Part: INDICATOR — FAILED (NR 3 ENGINE)

SMOKE IN THE COCKPIT, FLT DIVERTED TO BHM. MTC FOUND NR 3 ENG OIL QTY IND TO BE SOURCE OF SMOKE. REPLACED INDICATOR.

Part: TORQUE BOX — CRACKED (BS 1263)

THE TORQUE BOX WAS FOUND WITH A CRACKED UPPER CHORD AND A CRACKED FS 1263 UPPER BEAM ANGLE AND CHANNEL. THE CRACKED MEMBERS WERE REPLACED OR REPAIRED PER S/B 53-0129. ER/A 363340-14AD WAS ISSUED TO DOCUMENT THE DAMAGE AND CONTROL THE REPAIR METHOD.

Part: SKIN — CRACKED (NR 6 LE FLAP)

FOUND ON D1 LETTER CK, ONE 3 AND ONE 3.5 INCH CRACK IN SLAT LOWER SKIN OF NR 6 L/E SLAT AT O/B T/E. REPAIRED PER MM 57-54-0.

Part: BATTERY — DISCHARGED (CABIN)

AT LAYOVER, FOUND L2 DOOR EMERGENCY EXIT POWER PACK INOP. REPLACED BATTERIES.

Part: OVEN — FAILED (GALLEY)

FWD GALLEY OVEN FIRE IN FLT AFTER DEPARTURE. PERFORMED SMOKE/ID, RMVAL AND CLEAN UP CHECKLIST. RETURNED TO LAND AT PHX. REMOVED OVEN, INSPECTED WIRING AND COMPARTMENT, ALL CKD OK. REPLACED OVEN AS PRECAUTIONARY.

Part: SKIN — EROSION (RT ELEVATOR)

THE RT LOWER ELEVATOR SKIN HAS A 6 SPAN X 7 CHORD HOLE 12 O/B OF THE FUSELAGE. THE HOLE WAS CAUSED WHEN A DOUBLER PEELED BACK INTO THE AIRSTREAM. THE DEPARTING PIECE PUNTURED THE SKIN APPROXIMATELY 8 INCHES AFT OF THE HOLE. THE PUNCTURE IS 1.0 DIA, THE SKIN IS .025 2024-T3 CLAD SHEET. REPAIRED PER ERA 362664-14.

Part: SKIN — CORRODED (RAM AIR DOOR)

CORROSION WAS FOUND IN THREE AREAS AROUND THE RAM AIR ACTUATOR ACCESS DOOR. THE DAMAGED AREAS MEASURE 3.5 BY 4.375 IN THE AFT RT CORNER, 7.375 BY 3.625 ON THE FWD LT SIDE AND 3.5 BY 4.75 ON THE AFT LT SIDE. THE DAMAGE WAS REPAIRED WITH TITANIUM DOUBLERS AND APPROVED BY FAA FORM 8110-3 DER DESIGNATION SO-831, DTD 19, DEC 1996.

Part: LIGHT PANEL — SMOKING (FE PANEL)

PRIOR TO DEPARTURE WITH PSGRS ON BOARD, B-SYS STBY HYD PANEL WAS SMOKING. PSGRS WERE DEPLANED IN A NORMAL MANNER. FOUND BACKGROUND LIGHTING PANEL DAMAGED. REPLACED PANEL ASSEMBLY.

Part: OVERHEAT SENSOR — OUT OF POSITION (AFT FUSELAGE)

LOWER AFT BODY OVERHEAT LIGHT ILLUM. C/W PROM LIGHT WENT OUT WHEN LT PACK AND BLEED TURNED OFF. REPOS OVERHEAT SENSOR IN 48 SECTION. RAN ENGINE WITH NO OVERHEAT IND.

Part: WEB — CRACKED (BS 1243)

FOUND ON B2 LETTER CHECK, LOWER RT TORQUE BOX LIGHTENING HOLE WEB CRACKED FS 1243. REPAIRED PER MM 53-11-0.

Part: ANGLE — CRACKED (NR 8 LE SLAT)

A CRACK WAS FOUND 32.5 FROM I/B END ON LOWER AFT COVE SKIN ATTACH ANGLE BELOW ANTI-ICE DUCT. REPAIRED AS PER MM 57-54-0 FIG 805A, FOR NR 8 L/E SLAT.

Part: LIGHT — INOPERATIVE (CABIN)

FOUND EMERGENCY EXIT LIGHT INOP AT AFT LT DOOR IN EMERGENCY. REPLACED LIGHT ASSY.

Part: GEARBOX — FAILED (NR 2 ENGINE)

NR 2 ENG FAILED ON TAKEOFF. AFTER RETURNING TO YVR, CNTR MAINT FOUND THE NR 2 ENGINE GEARBOX HAD COME APART. REPLACED ENGINE AND ROUTED TO SHOP.

Part: SHIM — MISALIGNMENT (RT TE FLAP)

DURING ROUTINE INSECTION, THE LAMINATED SHIM INSTALLED ON THE RIGHT WING I/B FLAP TRACK WAS FOUND TO HAVE MIGRATED FROM LEFT TO RIGHT. COMPLYING WITH AD 90-07-05, THE MIGRATED SHIM WILL BE RELOCATED, REINSTALLED AND THE ATTACHMENTS WILL BE RETORQUED. INSPECTIONS PER SI 4-58662-12AD WILL BE CONTINUED.

Part: EEL SIGN — BROKEN (CABIN)

EMERGENCY EXIT LIGHT FOUND BROKEN AND HANGING ON SIDEWALL PANEL SEAT ROW 20ABC. REPLACED LIGHT ASSEMBLY, OPERATION NORMAL.

Part: EEL BATTERY PACK — DISCHARGED (AFT AIRSTAIR)

DURING LAYOVER, FOUND THE AFT AIRSTAIR OVERHEAD EMERGENCY LIGHT INOP. RELAMPED, CLEANED CONNECTIONS AND REPLACED BATTERY PACK. OPERATION NORMAL.

Part: ANGLE — CRACKED (NR 6 LE SLAT)

FOUND DURING B-1 LETTER CHECK, NR 6 L/E SLAT O/B STOP PAD ANGLE CRACKED O/B END. REPAIRED PER MM 57-54-0.

Part: WEB — CRACKED (NR 7 LE SLAT)

FOUND DURING B-1 LETTER CHECK, NR 7 SLAT ACT ROD END WEB CRACKED .5 INCH I/B WEB. REPAIRED PER MM 57-54-0 PG 803.

Part: ANGLE — CRACKED (NR 3 LE SLAT)

FOUND DURING B-1 LETTER CHECK, .5 INCH CRACK NR 3 SLAT COVE ANGLE BELOW ANTI-ICE DUCT. REPAIRED PER MM 57-54-0 PG 807A.

Part: FLAP — CRACKED (NR 5 LE FLAP)

PREVIOUS REPAIR CRACKED AT CENTER ATTACH POINT FOR BULLNOSE, 36 INCHES FROM INBD END, OF NR 5 L/E KRUGER FLAP. REPAIRED PER SRM 57-50-3, FIG. 11 REFERENCE ERA NR 270969-14.

Part: LE SKIN — DAMAGE (NR 4 FORE FLAP)

RT WING NR 4 FORE FLAP FLAP L/E DAMAGE DUE TO HITTING T/E BRACKETS IN UP POSITION. REPAIRED PER SRM 57-50-4 FIG 1.

Part: SKIN — DAMAGED (RT TE FLAP)

TOP SKIN DENTED 19 INCHES FROM I/B, BOTTOM SKIN DENTED AND TORN AWAY FROM SPAR 19 INCHES FROM I/B, BOTTOM SKIN DENTED 30 INCHES FROM I/B. THESE WERE ALL REPAIRED PER SRM 51-40-6. DEEP GOUGE IN L/E FWD OF I/B ARM, CHAFING MARKS AT 62 INCHES FROM I/B, CHAFING MARKS AT 68 AND 72 INCHES ON L/E. THESE WERE ALL REPAIRED PER SRM 57-50-4 FOR RIGHT WING FLAP PANEL, DURING SHOP INSPECTION.

Part: SPAR — CRACKED (NR 3 TE FLAP)

THE NR 3 MID FLAP DAMAGED FROM BLOWN TIRE. AFT SPAR RAIL CRACKED IN TWO PLACES AT I/B QUADRANT CUTOUT. REPAIRED PER MM 57520 FIG 802. SPLICED IN NEW RAIL SECTION.

Part: ENGINE — FLAMED OUT (NR 3)

DURING DESCENT, NR 3 ENGINE FLAMED OUT UPON RETARD OF THROTTLES AT FL370. FUEL HEAT AND IGNITION ON AT THE TIME. HAD SUCCESSFUL AIR RESTART. INSPECTED AND REPLACED FUEL AND OIL FILTERS FOUND OK, RAN ENGINE PER PFHB, NO PROBLEMS FOUND, RETURNED TO SERVICE.

Part: RIB — CRACKED (NR 4 LE SLAT)

DURING INSPECTION OF THE NR 4 LEADING EDGE SLAT, RIB MARKED NR 18 WAS FOUND TO HAVE A CRACK. THE RIB WAS REPAIRED PER MM 57-54-0 FIG 805.

Part: REAR SPAR — CRACKED (RT ELEVATOR)

DURING INSPECTION, THE RT ELEVATOR REAR SPAR WAS FOUND TO HAVE A CRACK EMANATING .25 INCH FROM INBD SIDE OF THE SHEAR PLATE AT THE SECOND FROM OUTBD TAB HINGE FITTING-TO-REAR SPAR ATTACHMENT. IN ACCORDANCE WITH B727 S/B 55-0087, THE CRACK WAS STOP DRILLED AND SET UP FOR REPETITIVE INSPECTION UNTIL PERMANENT REPAIR.

Part: COVER — CRACKED (LE SLAT TRACK)

FOUND ON LETTER CK -1. .5 IN CRACK ON NR 5 L/E SLAT I/B TRACK COVER SKIN - 2. .5 IN CRACK ON NR 6 L/E SLAT I/B TRACK COVER SKIN - 1. AND 2. REPAIRED PER M/M 57-54-0 PG 820.

Part: FLAP — CRACKED (NR 6 LE FLAP)

FOUND ON LETTER CHECK, 1 IN CRACK I/B END OF NR 6 L/E FLAP, REPAIR. INSTALLED DOUBLER PER M/M 57-53-0 PG 804.

Part: WEB — CRACKED (FS 1290-1330)

FOUND ON LETTER CHECK, LIGHTNING HOLES DAMAGED LEFT AT STA 1290 1330 IN STAIR WELL VERTICAL WEB, REPAIR. INSTALLED DOUBLER AT STA 1330 PER M/M 53-11-0.

Part: FUEL PUMP — SHEARED SHAFT (NR 3 ENGINE)

DURING DESCENT, NR 3 ENGINE FLAMED OUT. UNABLE TO RESTART, LANDED ORD WITHOUT INCIDENT. REPLACED FUEL PUMP AND FUEL CONTROL, OPERATION NORMAL. SHOP INSPECTION FOUND FUEL PUMP SHAFT WAS SHEARED.