N8889Z

Part: SPAR — WORN (LT WING) · airframe 48,841 hrs · 32,098 cycles

RUB MARKS ON FWD I/B LWR END OF AUX SPAR NEAR MLG W/W. REPAIR PER M/M 57-43-0.

Part: BATTERY PACK — DISCHARGED (RT OVERWING) · airframe 47,337 hrs · 31,057 cycles

RT OVERWING EXIT SIGN 2 EACH INOP. REPLACED BATTERY PACK.

Part: CLAMP — LEAKING (NR 3 ENGINE) · airframe 47,240 hrs · 30,984 cycles

NR 3 ENG STRUT OVERHEAT LIGHT ILLUM AFTER T/O. LIGHT WENT OUT WITH THROTTLE AT IDLE. FOUND NR 3 ENG PRECOOLER INLET VALVE CLAMP LEAKING BADLY. REPLACED CLAMP, RAN ENG, NO PNEU LEAKS PER MM.

Part: SKIN — WORN (LE FLAP)

INSTALLED REPAIR PER B727 MM 57-54-0, FIG 813. SLAT WORN.

Part: BRACKET — CRACKED (NR 8 SLAT ACT)

THREE INCH CRACK IN NR 8 SLAT ACTUATOR I/B SUPPORT BRACKET. REPAIRED PER MM 51-20-21.

Part: LIGHT — INOP (L 2 DOOR)

L-2 DOOR EMERGENCY EXIT LIGHT INOP. REPLACED L-2 EMERGENCY EXIT LIGHT ASSY CHECKS OK.

Part: BATTERY PACK — DISCHARGED (CABIN)

RIGHT CENTER OVERWING EMERGENCY LIGHT INOP. REPLACED BATTERY PACK. OP CKS GOOD.

Part: B-NUT — LOOSE (COCKPIT)

CREW 02 WENT TO ZERO IN FLIGHT. TIGHTENED LOOSE B-NUT ON REGULATOR 3RD OFFICERS POSITION AND REPLACED O2 BOTTLE, LEAK CHECKS OK.

Part: BATTERY PACK — DISCHARGED (R 2 DOOR)

R2 DOOR EMER EXIT LIGHT INOP. REPLACED BATTERY PACK.

Part: BATTERY PACK — DISCHARGED (RT EXTERIOR)

RT EXTERIOR AND INTERIOR OVERWING EMER LIGHTS INOP. REPLACED BATTERY PACK.

Part: BATTERY PACK — DISCHARGED (RT OVERWING)

RT OVERWING EMEG EXIT SIGN INOP. REPLACED BATTERY PACK.

Part: WEB — CRACKED (BS 1230)

A .25 INCH CRACK LIGHTENING HOLE STA 1230 LT ON AFT AIRSTAIR CUTOUT VERT WEB. REPAIRED PER M/M 53-11-0 PG 828.

Part: BATTERY PACK — DISCHARGED (CABIN)

RT AFT OVERWING EMERG LIGHT OUT. REPLACED BATTERY IN M956 LOCATION OPN GD.

Part: BATTERY PACK — DISCHARGED (CABIN)

RIGHT AFT OVERWING EMERGENCY LIGHT INOP. REPLACED BATTERY PACK, CK'S GOOD.

Part: WIRE — LOOSE (BS 950)

LOOSE FLOORBOARD BY SEAT 27A WITH EXPOSED WIRES. SPARKS REPORTED BY PAX. FOUND VACUUM CLEANER RECP WITH WIRE PULLED LOOSE. INSTALLED TERMINAL ON RECP AND CK OK REF WDM25-11-01 PG 2 STA 950A +10.

Part: GUSSET — CRACKED (BS 1273)

FS 1273 TORQUE BOX STRUCTURE FOUND WITH A CRACK IN A GUSSET AND BEAM CHORD. THE CRACKED STRUCTURE WAS REPLACED PER THE GUIDELINES OF S/B 53-0129 TO COMPLY WITH AD 94-07-08. ER/A 363305-14AD WAS ISSUED TO DOCUMENT THE DAMAGE AND CONTROL THE REPAIR PROCESS.

Part: SKIN — CRACKED (FUSELAGE)

FOUND AT D-2 LETTER CHECK, .5 INCH CRACK I/B AFT CORNER OF PNEUMATIC GROUND CONNECTION DOOR. INSTALLED TIME LIMITED REPAIR DOUBLER PER M/M 53-30-0 AND ERA 363309-14.

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

NR 8 SLAT O/B ACTUATOR ATTACH BRACKET I/B WEB CRACKED. REPAIRED PER M/M 57-20-21 P 812.

Part: BATTERY PACK — DISCHARGED (CABIN)

EMERGENCY EGRESS LIGHTS EXTERIOR AFT WING AND AFT CARGO DOOR RT SIDE INOP. REPLACED BATTERY PACK.

Part: GENERATOR — FAILED (NR 3 ENGINE)

LOST ALL AIRCRAFT PWR AFTER T/O. DID NOT GET PWR BACK UNTIL ON THE GROUND WHEN NR 3 GEN TURNED OFF. FOUND 1 AND 2 GENERATORS OPERATING NORMALLY. WHEN NR 3 USED THE PWR STARTED TO FLUX. REPLACED NR 3 GEN, CSD, GCU, AND BPP.

Part: SUPPORT — CORRODED (FUSELAGE)

CORROSION INSIDE HINGE SUPPORT STRUCTURE FOR PANEL 3448R. REMOVED CORROSION PER SRM 51-10-6. FOWARD CORROSION WITHIN SRM LIMITS 53-10-1 FIG 1. CUTOUT REAR CORROSION. CUTOUT ANGLE PER M/M 53-30-1 FIG 804, MADE NEW ANGLE, SPLICES AND DRILLED. REPAIRED ANGLE PER M/M 53-30-1 FIG 804. FINISHED INSTALLING ANGLE PER M/M 53-30-1 FIG 804.

Part: ANGLE — CORRODED (FUSELAGE)

SUPPORT ANGLE FOR PANEL 3348L IS CORRODED. CUT OUT CORRODED T, CLEANED OTHER CORROSION PER SRM 51-10-6 WITHIN LIMITS SRM 51-10-1 FIG 1, MADE REPLACEMENT ANGLE REF M/M 53-30-1 FIG 804. REPAIRED PER DAL M/M 53-30-1, FIG 804.

Part: STRINGER — DAMAGED (FUSELAGE)

TIME LIMITED REPAIR ON STR 18A RT ABOVE UPLOCK ASSY. REMOVED TIME LIMITED REPAIR, CUT AND REMOVED SECTION OF STR 18A PER M/M 53-12-0 PG 819. FABRICATED REPAIR PER M/M 53-12-0 PG 819. INSTALLED REPAIR PER M/M 53-12-0 PG 819.

Part: RIB — CRACKED (NR 3 LE SLAT)

NR 3 SLAT RIB NR 3 IS CRACKED IN 2 PLACES LWR FLANGE AT NUTPLATE AND UPPER FLANGE IN RADIUS. REPAIRED AND INSTALLED DOUBLER PER M/M 57-54-00, PG 813A AND SRM 57-50-3 PG 26.

Part: FRAME — DAMAGED (FS 913)

DURING ACCOMPLISHMENT OF M/M53-11-0 NR 12 PERMANENT REPAIR (REPAIR/MOD TO STA 910 AND 913 FRAME STUB BEAMS) MAINTENANCE DISCOVERED THAT INSTALLATION OF THE TIME LIMITED REPAIR DAMAGED THE EXISTING STUB FRAME. REPAIRED FRAME STUB PER M/M 53-11-00, FIG 813. REPLACED STA 913.5 FRAME STUB PER M/M 53-11-00, FIG 814.

Part: BLKHD STIFFENER — CRACKED (BS 1183)

CRACKS WERE FOUND IN THE VERT STIFF AT RBL 36.83 AND LBL 36.83 ON THE FWD SIDES OF THE BS 1183 BLKHD. THE CRACKS ARE APPROX 1.5 LONG AND ARE LOCATED AT APPROX WL 238 IN THE O/B RADIUS OF THE AFT CHORD. THIS AREA IS ADDRESSED BY S/B 727-53-0192 (EO 4-59821-3). ACCOMPLISH EO 4-59821-3, ME-02, OPN 0250 AND OPN 0255; OPTIONAL FABRICATE REPAIR PARTS PER BACO DWG 65C34406-12 (LT) AND 65C34406-13 (RT) BEAM INST.

Part: ANGLE — CRACKED (TE FLAP)

LOWER CHORD ANGLE CRACKED AT 55 FROM I/B END OF FLAP. REPAIRED PER M/M 57-52-0 FIGURE 802.

Part: LIGHT — INOPERATIVE (CABIN)

EPL LIGHT AT SEAT 5C IS LOOSE FROM MOUNTING AND LIGHT INOP. REPLACED LIGHT ASSY AND CHECKS OK.

Part: BULKHEAD WEB — CRACKED (BS 1183)

THE FS 1183 BULKHEAD WEB WAS FOUND CRACKED AT RBL 27. THERE IS A .125 VERTICAL CRACK AND A .5 HORIZONTAL CRACK AT WL 170. THE WEB IS A BONDED ASSEMBLY OF CLAD 2024-T3 WITH A LOCAL THICKNESS OF 0.050. THE CRACK LOCATION IS OUTSIDE OF THE INSPECTION AREA SPECIFIED BY BOEING S/B 727-53-171. THE CRACKS WILL BE CUTOUT AND A REPAIR DOUBLER INSTALLED.

Part: BULKHEAD WEB — CRACKED (BS 1183)

THE BS 1183 BULKHEAD WEB WAS FOUND CRACKED AT RBL 27. THERE IS A .125 VERTICAL CRACK AND A .5 HORIZONTAL CRACK AT WL 170. THE WEB IS A BONDED ASSEMBLY OF 2024-T3 CLAD WITH A LOCAL THICKNESS OF 0.050. THE CRACK LOCATION IS OUTSIDE OF THE INSPECTION AREA SPECIFIED BY BOEING SERVICE BULLETIN 727-53-171. THE CRACKS WILL BE CUT OUT AND A REPAIR DOUBLER INSTALLED.

Part: BRACKET — CRACKED (NR 1 SLAT ACT)

APPROX 2 INCH CRACK IN NR 1 SLAT I/B AND O/B ACTUATOR MOUNT BRACKET'S. REPAIRED PER M/M 57-20-21 AND ERA DUE TO A/C EFFECTIVITY.

Part: ANGLE — CRACKED (NR 1 LE FLAP)

FOUND DURING C-CHECK, .5 INCH CRACK IN NR 1 SLAT SKIN ATTACH ANGLE BELOW TAI DUCT. REPAIRED PER M/M 51-54-0 AND ERA DUE TO EFFECTIVITY.

Part: AUX SPAR — CHAFED (LT WING)

FOUND DURING C-CHECK, LT MLG STRUT DOOR CHAFING AUX SPAR I/B END MARKED, FWD OF NR 4 SCREWJACK. REPAIRED PER M/M 57-43-0 PG 802.

Part: WEB — CRACKED (BS 1237)

A .625 INCH CRACK IN LT LOWER TORQUE BOX VERTICAL WEB AT LOWER LIGHTENING HOLE STA 1237. REPAIRED PER M/M 53-11-0 AND ERA DUE TO EFFECTIVITY.

Part: STRINGER — CRACKED (BS 940)

STRINGER 18A RT CRACKED AT STA 940 SUPPORT FITTING AFT BOLT. REPAIRED PER MM 53-12-0.

Part: BRACKET — CRACKED (LE FLAP ACT)

NR 1 L/E FLAP ACTUATOR MOUNT BRACKET CRACKED AT LOWER I/B CORNER. REPAIRED PER M/M 57-20-21 AND ERA DUE TO A/C EFFECTIVITY.

Part: FRAME — CRACKED (RT SVC DOOR)

FOUND DURING C-CHECK, AFT RT SVC DOOR FWD FRAME CRACKED AT LWR I/B END OF UPPER HINGE CUTOUT. REPAIRED PER SRM 52-40-2.

Part: SHIM — MISALIGNMENT (RT TE FLAP TRACK)

THE LAMINATED SHIM INSTALLED ON THE RIGHT WING INBOARD TRAILING EDGE FLAP INBOARD TRACK WAS FOUND TO HAVE MIGRATED GREATER THAN THE .25 LIMIT SPECIFIED IN THE INSPECTION. IN COMPLIANCE WITH AD 90-07-05, THE MIGRATED SHIM WILL BE RELOCATED AND ATTACHMENTS RETORQUED. INSPECTIONS PER SI 4-58662-12AD WILL BE CONTINUED. ACCOMPLISHED REPAIRS PER DL ERA 303342-14AD.

Part: EEL RACK — FAULTY (CABIN)

DURING INSPECTION, ALL 3 RT WING EMERGENCY LIGHTS, AND CENTER CABIN OVERWING EMERGENCY EXIT LIGHT WERE INOP. REPLACED POWER SUPPLY, OPERATION NORMAL.

Part: EEL PACK — DISCHARGED (CABIN)

DURING INSPECTION, RIGHT SIDE EMERGENCEY EXIT LIGHTS FAILED TO TEST. REPLACED BATTERY ASSEMBLY OPERATION NORMAL.

Part: SKIN — CORRODED (FS 680)

DURING INSPECTION, THE FUSELAGE SKIN AT F.S. 680-686 WAS FOUND CORRODED AT STR. 28L AND WAS CUT OUT. A PRE-EXISTING REPAIR DOUBLER SPANNING THE AREA FROM F.S. 688-720A AND STR. 28L-28R WAS REMOVED AND EXTENDED TO INCLUDE THE NEW CUTOUT NOTED ABOVE. BOTH OF THESE REPAIRS WERE REPAIRED IN ACCORDANCE WITH THE SRM SKIN SPLICE FROM B727 SRM 53-30-3, FIG. 12.