N519DA

Part: DOOR — MISSING (NR 3 ENGINE) · airframe 66,362 hrs · 50,580 cycles

PANEL NR 3 ENGINE OIL SERVICE DOOR MISSING. REPLACED NR 3 OIL SERVICE DOOR.

Part: ATTACH ANGLE — CRACKED (L/E SLAT) · airframe 66,242 hrs · 50,505 cycles

A 1 INCH CRACK COVE SKIN ATTACH ANGLE AT O/B STOP PAD. REPAIR PER M/M 57-54-000-8.

Part: STIFFENER — CRACKED (WING) · airframe 66,242 hrs · 50,505 cycles

A 2 INCH CRACK WING L/E SPAR STIFFENER I/B TRACK NR 2 SLAT I/B STIFFENER. REPLACED ANGLE PER M/M 57-200021-8.

Part: ACTUATOR — FAILED (NOSE GEAR) · airframe 64,220 hrs · 49,120 cycles

WITH GEAR HANDLE DOWN AND MAIN GEAR LOCKED DOWN (GREEN LIGHTS) - EXCESSIVE TIME DELAY BEFORE NOSE GEAR SHOWED LOCKED DOWN AND GREEN LIGHT. NOTE: RED DOOR LIGHT STAYED ILLUM UNTIL NOSE GEAR GREEN LIGHT ILLUMINATED. THROTTLES WERE NOT AT IDLE AND FLAPS WERE NOT MOVING. INSPECTED NOSE GEAR DOORS. NO DEFECTS NOTED. REPLACED NOSE GEAR ACTUATOR FOR BYPASSING. OPS CKS NORMAL.

Part: BEAM — MISINSTALLED (FUSELAGE) · airframe 64,096 hrs · 49,034 cycles

LBL AND RBL 17.8 VERTICAL BEAMS OF THE STA 1183 BULKHEAD HAVE SEVERAL FASTENERS INSTALLED FLUSH IN LIEU OF THE DRAWING REQUIRED BUTTON HEAD. ER/A 334720-14AD.

Part: STRAP — TOOL DAMAGE (FUSELAGE) · airframe 64,096 hrs · 49,034 cycles

TOOLING DAMAGE FOUND ON THE STA 784 LT FRAME REINFORCING STRAP. THE DAMAGE IS AT THE FOURTH FASTENER HOLE ABOVE THE FLOOR LINE. NO DAMAGE TO THE FRAME ITSELF. ER/A 334717-14AD REV A.

Part: STRAP — CORRODED (FUSELAGE) · airframe 64,096 hrs · 49,034 cycles

THE BEAR STRAP AT THE C-3 DOORWAY WAS FOUND CORRODED ON THE INTERIOR SURFACE AT THE LOWER FWD CORNER OF THE DOORWAY CUTOUT. ER/A 334752-14AD REV A.

Part: FRAME — TOOL DAMAGE (FUSELAGE) · airframe 64,096 hrs · 49,034 cycles

TOOLING DAMAGE IN THE LT AND RT OVERWING EXIT FRAMES AT FS 761, DAMAGE FOUND IN BOTH THE I/B AND O/B CHORDS. THE LT FRAME DAMAGE AT THE 4TH FASTENER ABOVE THE FLOOR LINE. THE RT FRAME DAMAGE AT THE THIRD FASTENER ABOVE THE FLOOR LINE. ER/A 334726-14AD REV A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 64,096 hrs · 49,034 cycles

STA 1142.7 RT FRAME CRACKED/CORRODED JUST ABOVE C3 DOOR LOWER SILL. ER/A 334693-14AD REV A.

Part: FLAP TRACK — CORRODED (LT WING) · airframe 64,097 hrs · 49,034 cycles

NUMBER 1 FLAP TRACK LT WING WAS CORRODED IN THE BARREL NUT HOLE. TRACK CLEANED UP AND REPAIRED PER MM 57-52-0.

Part: CHANNEL — WORN (FUSELAGE) · airframe 64,096 hrs · 49,034 cycles

FIREWALL CHANNEL WORN AT 5:30 POSITION FS 1343 AT MATING SURFACE FOR NR 2 ENG COWLING. REPAIRED PER 53-11-0.

Part: FLAP TRACK — CORRODED (LT WING) · airframe 64,097 hrs · 49,034 cycles

NUMBER 2 FLAP TRACK LT WING WAS CORRODED IN THE BARREL NUT HOLE. TRACK CLEANED UP AND REPAIRED PER MM 57-52-0.

Part: FLAP TRACK — CORRODED (LT WING) · airframe 64,096 hrs · 49,034 cycles

NR 2 FLAP TRACK CORRODED CARD NR 115. REPAIRED PER M/M.

Part: FLAP TRACK — CORRODED (LT WING) · airframe 64,096 hrs · 49,034 cycles

NR 3 FLAP TRACK CORRODED NR 116. REPAIRED PER M/M.

Part: SWITCH — FAILED (NR 2 ENGINE) · airframe 63,602 hrs · 48,689 cycles

INFLIGHT SHUTDOWN DUE TO NR 2 ENG FILTER BYPASS LIGHT ON. REMOVED AND INSPECTED MAIN OIL FILTER. NO CONTAMINENTS FOUND. CHIP DET CHECKS CLEAN. REPLACED FILTER BYPASS SWITCH.

Part: PCU — MALFUNCTIONED (RUDDER) · airframe 63,405 hrs · 48,537 cycles

RUDDER LOAD LIMITER FOLLOWING MEL PROCEDURES WHEN REENGAGED SYSTEM A RUDDER BEFORE FLAP EXTENSION RECEIVED UNCOMMANDED LOWER RUDDER YAW 1 INDICE RT SYS A RUDDER THEN TURNED OFF AGAIN. STBY ON AND LOWER RUDDER RETURNED TO NORMAL. CENTERED POSITION. LANDING MADE WITH SYSTEM A OFF STBY ON. REPLACED RUDDER A SYS PCA. RUDDER LOAD LIMITER ON MCO PER MEL.

Part: SKIN — CRACKED (TE FLAP) · airframe 63,273 hrs · 48,442 cycles

A .5 INCH CRACK ON NR 2 MIDFLAP LOWER COVE SKIN AT THE I/B ROD CUTOUT.

Part: SKIN — CRACKED (NR 5 SLAT) · airframe 63,273 hrs · 48,442 cycles

NR 5 SLAT LOWER SKIN WORN O/B OF O/B ALIGNMENT SPADE. CUT INNER SKIN MADE NEW SKIN DOUBLERS. REPAIRED PER MM 57-54-0 FIG 801.

Part: BATTERY — DISCHARGED (CABIN)

R1 DOOR EMERGENCY EXIT LIGHT INOP. REPLACED BATTERY, OPS NOW OK.

Part: BATTERY PACK — DISCHARGED (CABIN)

FOUND ON LAYOVER AFT EMERGENCY CEILING LIGHT STROBING. REPLACED BATTERY CHARGER AND BATTERY.

Part: BRAKE — FAILED (NR 1 BRAKE)

AFTER TAXI TO RUNWAY, A/C REQUIRED APPROX 1.4 EPR TO INITIATE TAXI. WHEN A/C MOVED A VERY LOUD SHUDDER WAS FELT ON LT SIDE OF A/C. MAINT TOW BACK TO GATE. REPLACED NR 1 BRAKE AND TIRE ASSY DUE NR 1 BRAKE FAILUR.

Part: BULB — FAILED (CABIN)

ON L/O 2 CK, FOUND NO SMOKING LIGHTS INOP AT 4CD, 14DEF, 19DEF, 23DEF. ALSO, FOUND FASTEN SEAT BELT LIGHTS AT 4CD, 2AB, 20DEF INOP. RELAMPED, ALL CHECK GOOD.

Part: POWER SUPPLY — INOPERATIVE (ROW 20-26)

ON S/C FOUND E PATH LIGHTING AT SECTION 20 TO 26 INOP. FOUND BAD FUSE ON AFT PWR SUPPLY. REPLACED AFT PWR SUPPLY, OPS NORMAL NOW.

Part: BATTERY PACK — DISCHARGED (CABIN)

MID CABIN SEAT EMERGENCY LIGHTS INOP. REPLACED BATTERY RACK AND BATTERY PACK, ALL OPS NORMAL.

Part: LIGHT — INOP (PAX DOOR)

LEFT AFT ENTRY DOOR OVERHEAD EMERGENCY LIGHT INOP. REPLACED RACK, NOW CKS NORMAL.

Part: SKIN — CRACKED (BS 360-481)

FUSELAGE SKIN FS 360-481, STRG 4L, SKIN LAP SPLICE, REPAIR FOR CRACKS. EXTERNAL LFEC INSPECTION REVEALED CRACK INDICATIONS IN THE LOWER SKIN OF THE STRINGER 4L LAP SPLICE BETWEEN FS 360-481. INTERNAL HFEC INSPECTION CONFIRMED 10 CRACKS ALONG THE LOWER ROW OF FASTENERS IN THE LAP. THE SKIN LAP WAS CUTOUT ALONG THE ENTIRE PANEL LENGTH AND REPAIRED WITH AND EXTERNAL ALUMINUM DOUBLER PER ER/A 366641-14, REV B.

Part: SKIN — CRACKED (BS 360-481)

FUSELAGE SKIN FS 360-481, STRG 4R, SKIN LAP SPLICE REPAIR FOR CRACKED FASTENER HOLES. LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 360-481 REVEALED CRACK INDICATIONS. HFEC INTERNAL INSPECTION CONFIRMED A TOTAL OF 4 CRACKS IN TWO SEPERATE FRAME BAYS ALONG THE LOWER ROW OF FASTENERS. THE SKIN LAP WAS CUTOUT ALONG THE PANEL LENGTH AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER. THE REPAIR WAS ACCOMPLISHED PER ER/A 366636-14, REV B.

Part: SKIN — CRACKED (BS 528)

FUSELAGE SKIN, FS 528, STRG 4, REPAIR FOR SKIN CRACK. LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE GAVE A CRACK INDICATION. HFEC INTERNAL INSPECTION WAS THEN ACCOMPLISHED ALONG THE ENTIRE LENGTH OF THE PANEL WITH ONLY ONE CRACK FINDING. THE CRACK WAS IN THE LOWER FASTENER ROW OF THE LOWER SKIN AND WAS LOCALLY TRIMMED OUT AN REPAIRED PER B727 SRM 53-30-3, FIG 5. 10 FASTENERS FWD AND AFT OF THE CUTOUT WERE REMOVED AN HFEC INSPECTED WITH NO CRACKS.

Part: SKIN — CRACKED (NR 8 LE SLAT)

4.5 INCH CRACK IN NR 8 SLAT COVE SKIN ANGLE AT O/B UPSTOP PAD. REPAIR PER MM 57-54-0 PG 816.

Part: STOP — LOOSE (6-7 & 8 LE SLAT)

DURING INSPECTION PER REQUIREMENTS OF AD 94-07-08, LOOSE SLAT STOP ATTACH BOLTS WERE FOUND LOOSE FOR THE NR 6, 7 & 8 SLATS. EACH OF THESE SLAT LOCATIONS WERE MODIFIED PER THE REQUIREMENTS OF BAC S/B 727-57-171. THE MODIFICATION WAS DOCUMENTED PER ER/A 366092-14AD.

Part: SPAR WEB — CRACKED (CENTER SECTION)

WING CENTER SECTION REAR SPAR, WEB RBL 3 AND RBL 9 : REPAIR FOR WEB CRACKS. THE WING CENTER SECTION SPAR WEB WAS FOUND WITH TYPICAL CRACKS NEAR THE UPPER SPAR CAP. THE CRACKS WERE CUTOUT AND REPAIRED WITH AN ALUMINUM REPAIR DOUBLER. THE REPAIR WAS ACCOMPLISHED PER ER/A 365001-14AD, REV B. THE REPAIR IS TEMPORARY UNTIL HMV WHEN THE SPAR WEB WILL BE MODIFIED PER AD 97-25-15.

Part: SKIN — CRACKED (NR 4 LE FLAP)

FOUND AT B2 LETTER CHECK, 2 CRACKS .75 INCH AND 2 INCH AT NR 4 L/E FLAP O/B HINGE CUTOUT. REPAIRED PER ERA 364950-14 AND M/M 57-53-0.

Part: SKIN — HOLE (RUDDER)

HOLE IN LT L/E SKIN, 34 INCH FROM BOTTOM. INSTALLED REPAIR DOUBLER PER SRM 55-40-3 FIG. 1.

Part: SKIN — HOLE (RUDDER)

HOLE IN LEFT L/E SKIN ON LOWER RUDDER. REPAIRED PER SRM 55-40-3.

Part: SKIN — GOUGED (RUDDER)

SKIN GOUGED AT LOWER END OF LOWER RUDDER. INSTALLED DOUBLER PER SRM 55-40-3, FIG 1.

Part: ANGLE — CRACKED (NR 3 TE MIDFLAP)

THE LOWER AFT CHORD ANGLE WAS FOUND CRACKED DURING SHOP INSPECTION AT HMV VISIT. THE ANGLE WAS REPAIRED PER 727 MM 57-52-0 BY STOP DRILLING CRACK AND INSTALLING A DOUBLER.

Part: STRINGER — CRACKED (WS 686.5)

STRINGER TO RIB CRACK LEFT WING STA 686.5 AT STR 12. REPAIRED PER M/M57-13-0 FIG 804.

Part: STRINGER — CRACKED (WS 686.5)

HFEC INSPECTION PER OPN NO 8602 AS SHOWS CRACK ON STRINGER TO RIB AT STA 686.5 5-10. PERFORMED DYE CHECK TO IDENTIFY CRACK. NO STOP DRILL HOLE REQUIRED. DISCONNECTED FUEL DUMP LINE AT STA 686.5 - 700 FOR ACCESS TO REPAIR. DRILLED UP REPAIR DOUBLERS PER MM 57-13-0 FIG 801. OK TO INST RECONNECTED FUEL LINE. INSTALLED REPAIR ANGLE PER M/M 57-13-0.

Part: BRACKET — CRACKED (LE FLAP ACT)

THE NR 2 L/E FLAP ACTUATOR SUPPORT BRACKETS I/B AND O/B ARE CRACKED. REMOVED SUPPORT BRACKETS AND BEGAN REPAIRS PER M/M 57-20-21 FIG 807, FINISHED REPAIR PER MM 57-20-21 FIG 807.

Part: ANGLE — CRACKED (LT TE FLAP)

AFT LOWER CHORD ANGLE IS CRACKED AT I/B AFT FLAP TRACK CUTOUT I/B AND O/B CORNERS. INSTALLED DOUBLER PER M/M 57-52-0 FIG 802.

Part: SKIN — DENTED (BS 1050-1070)

DUE TO THE C2 CARGO DOOR COMING OPEN DURING FLIGHT (REF ER/A 362866-14 AND ER/A 362862-14), THE FUSELAGE SKIN IS DENTED BETWEEN FS 1050 AND FS 1070 BETWEEN S22R AND S23R. THE SKIN WILL BE CUT OUT AND AN EXTERNAL REPAIR DOUBLER WILL BE ADDED.

Part: HINGES — DAMAGED (C2 CARGO DOOR)

AFT CARGO DOOR REPORTED OPEN BY FLT ATTEND DURING CLIMB-OUT. NR 3 ENG COMPRESSOR STALLS NOTED. SHUT DOWN NR 3 ENG. NO COCKPIT IND OF OPEN DOOR. INSPECTED NR 3 ENG INLET/EXHAUST, NO FOD FOUND. INSP, REPLACED MAIN OIL SCREEN, RAN ENG PER PFHB-ALL PARAM NML. FOUND C2 CARGO DOOR OPEN AND BOTH HINGES DAMAGED. C2 CARGO DOOR SECURED CLOSED PER ERA 362866-14. PRESS A/C TO 5PSID. NO LEAKS NOTED, PREPARED A/C FOR FERRY FLT TO ATL.

Part: WEB — CRACKED (BS 1223)

FOUND DURING A-2 LETTER CHECK, .5 INCH CRACK IN TORQUE BOX VERTICAL WEB AT LIGHTENING HOLE STA 1223 RT SIDE. A 1.5 INCN CRACK IN TORQUE BOX VERTICAL WEB AT LIGHTENING HOLE STA 1243 RT SIDE. REPAIRED PER M/M 53-11-0.

Part: SKIN — OUT OF CONTOUR (BS 550)

THE FUSELAGE SKIN BETWEEN STRINGERS 9R AND 10R AT STA 550 ABOVE THE 7TH WINDOW AFT OF THE R1 DOOR WAS FOUND WITH AN UNEVEN CONTOUR EXTENDING OUTWARD UP TO .25 MAX FROM NORMAL CONTOUR, OVER A 10 BY 10 SIZE AREA. ACCOMPLISHED PERMANENT REPAIR PER ERA 361950-14.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

AFT CABIN FLOOR TRACK LIGHTING INOP. REPLACED POWER SUPPLY, CHECKS NORMAL.

Part: BATTERY PACK — DISCHARGED (CABIN)

ON LAYOVER, FOUND L1 DOOR SLIDE LIGHT INOP. REPLACED BATTERY PACK, CHECKS OK.

Part: BATTERY PACK — DISCHARGED (CABIN)

SEVERAL OUTSIDE EMERGENCY LIGHTS INOPERATIVE. C/A REPLACED BATTERY RACK M982. REPLACED BATTERY RACK M982, M955 AND BATTERY PACK M654. EMERGENCY LIGHTS OPS CHECKED GOOD.

Part: FAN — INOPERATIVE (CARGO COMPT)

AFTER TAKEOFF, FLIGHT ATTENDANT REPORTED SMOKE IN CABIN. COMPLIED WITH P.O.M. AND RETURNED TO SFO. (PACK TEMP NORMAL) REPLACED GASPER FAN. OPS CHECK NORMAL.

Part: SKIN — CORRODED (BS 696)

A PUNCTURE REPAIR WAS FOUND CORRODED. THE CORROSION LED TO A 1 BY 2 CUT OUT AT STA 695 OUTBOARD OF STRINGER 28R. DAMAGE WAS REPAIRED PER B727 SRM 53-30-3, FIGURE 1.

Part: STIFFENER — CRACKED (NR 2 LE SLAT ACT)

THE OUTBOARD ACTUATOR ATTACH RIB STIFFENER ON THE NR 2 SLAT ACTUATOR WAS FOUND CRACKED. THE DAL MFG PART NUMBER FOR THE INBOARD AND OUTBOARD STIFFENERS IS (57-0367-002). THE ERA REPLACED BOTH THE INBOARD AND OUTBOARD ATTACH RIB STIFFENERS PER EO 4-59271-3AD.

Part: WEB — CRACKED (BS 1323)

WEB IS CRACKED AT LIGHTENING HOLE LT SIDE STA 1323. REPAIRED PER M/M 53-11-0 PG 828 NR 15.

Part: BLKHD WEB — CRACKED (FS 1183)

THE BS 1183 BULKHEAD WEB WAS FOUND CRACKED IN TWO LOCATIONS AT RBL 18. THERE IS A 1 INCH CRACK AT WL 166.3 TO WL 167.5 AND A .1875 INCH CRACK AT WL 169. THE WEB IS A BONDED ASSEMBLY OF 2024-T3 CLAD WITH A LOCAL THICKNESS OF 0.050 INCH. THE CRACK LOCATIONS ARE OUTSIDE OF THE INSPECTION AREA SPECIFIED BY BOEING SERVICE BULLETIN 727-53-171. MTC REPORTS THAT THE VERTICAL STIFFENER AT RBL 18, THE TOPIC OF BOEING SB 727-53-0202, IS NOT DAMAGED. THE CRACKS WILL BE STOP DRILLED AND A REPAIR DOUBLER INSTALLED PER DL ERA 302880-14.

Part: WEB — CRACKED (BS 1223)

A .25 INCH CRACK LT LWR TORQUE BOX VERTICAL WEB STA 1223 AT TOP ROW OF RIVETS. ALSO, .25 INCH CRACK IN LIGHTENING HOLE BELOW THE TOP ROW OF RIVETS. REPAIRED PER MM 53-11-0.

Part: STRINGER — CORRODED (FS 1176)

DURING INSPECTION, FOUND MISSING AND SHEARED RIVETS AT STRINGER NR 29R AT FS 1176. ALSO, FOUND STRINGER CORRODED. REPAIRED BY REPLACING SECTION OF STRINGER PER SRM 53-10-03 PG 3.

Part: EEL — INOPERATIVE (AFT STAIRWELL)

DURING INSPECTION, FOUND AFT STAIRWELL EMERGENCY LIGHT INOP. REPLACED LIGHT ASSEMBLY OPERATION NORMAL.

Part: EEL BATTERY PACK — DISCHARGED (CABIN)

DURING LAYOVER, RIGHT AFT OVERWING EMERGENCY EXIT LIGHT INOP. REPLACED BATTERY PACK, OPS CKS NORMAL.

Part: TRUNNION — CORRODED (NLG)

DURING LTR CHECK, FOUND NOSE GEAR LEFT AFT TRUNNION BOLT BORE CORRODED. OPENED HOLE TO .9385, HFEC CK OK. REAMED HOLE PER M/M 53-40-0, MACHINED BUSHINGS TO SIZE AND TREATED. TREATED, PAINTED BOLT BORES AND INSTALLED BUSHINGS PER M/M 53-40-0.

Part: ANGLE — CRACKED (NR 3 SPOILER)

OUTBD ATTACH CASTING CRACKED 1.75 INCH NR 3 SPOILER AT ACTUATOR. CRACK REPAIR TO BE ACCOMPLISHED WITHIN 30 DAYS PER SRM 57-50-6.

Part: ANGLE — CRACKED (NR 4 SLAT)

COVE SKIN ATTACH ANGLE CRACKED NR 4 SLAT OUTBRD TRACK .25 INCH, FOUND DURING E-2 LTR CK TPAMM. REPAIRED PER MM 57-54-0.

Part: ANGLE — CRACKED (NR 2 SLAT)

DOUBLER CRACKED COVE SKIN ATTACH ANGLE NR 2 SLAT INBD STOP PAD, FOUND DURING E-2 LTR CK TPAMM. REPAIRED PER M/M 57-54-0.