N8882Z

Part: RIB — CRACKED (VERTICLE FIN) · airframe 59,227 hrs · 39,418 cycles

VERT. STAB RIB L/H ATTACH ANGLE CRACKED AT FIN STA 133.800 AND STR 9LEFT REPAIR PER M/M 55-30-000-8

Part: WARNING SYSTEM — ACTIVATED (COCKPIT) · airframe 58,130 hrs · 38,614 cycles

CREW REPORTS NOSE GEAR UNSAFE INDICATION AND VIBRATION ON GEAR RETRACTION. JACKED NOSE AND SWUNG GEAR, ALL OPS NORMAL.

Part: SKIN — CRACKED (FUSELAGE) · airframe 57,962 hrs · 38,500 cycles

THE UPPER HINGE CUTOUT OF THE L1 DOOR CUTOUT WAS FOUND WITH A .5 INCH CRACK IN THE SKIN AND A CRACK INDICATION AT A FASTENER HOLE IN THE BEAR STRAP. THE CRACKS WERE REMOVED AND REPAIRED WITH DOUBLERS PER ER/A 383169-14, REV B.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 57,960 hrs · 38,499 cycles

FOUND ON D1 LETTER CK, CORROSION AT STR 28 RT AT STA 620. REPAIRED PER SRM 53-10-3.

Part: SKIN — CRACKED (R1 DOOR) · airframe 56,616 hrs · 37,645 cycles

FUSELAGE / SKIN / FWD GALLEY DOOR CUTOUT / LWR AFT CORNER : CRACK REPAIR THE LOWER AFT CORNER OF THE FWD GALLEY DOOR CUTOUT WAS FOUNDWITH A CRACK EMANATING FROM A FASTENER HOLE. THE CRACK IS TYPICAL OF BAC S/B 727-53-0188. THE CRACK WAS IN THE SKIN ONLY AND WAS REMOVED WITH A CUTOUT IN THE SKIN. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL REPAIR DOUBLER PER THE S/B AND PER ER/A 381969-14.

Part: SKIN — CRACKED (R1 DOOR CUTOUT) · airframe 56,616 hrs · 37,645 cycles

FOUND ON C2 LETTER CK 5/16 IN CRACK FUSELAGE SKIN R-1 DOOR LOWER AFT CUTOUT. REPAIRED PER ERA 381969-14 AND EO 4-58974-3AD.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 56,336 hrs · 37,467 cycles

L-1 WING EMERGENCY EXIT LIGHT INOP, REPLACED CHARGER.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 54,880 hrs · 36,474 cycles

ON L/O CHECK, FOUND R-2 OVERHEAD EMERGENCY EXIT DOOR LIGHT INOP. REPLACED R-2 OVERHEAD EMERGENCY EXIT DOOR BATTERY PACK, OPS NOW NORMAL.

Part: FRAME — CRACKED (FUSELAGE) · airframe 54,553 hrs · 36,247 cycles

FUSELAGE / OVERWING EXIT / LT / FRAME / FS 783.95 : CRACK REPAIR. INSPECTIONS OF THE LH OVERWING EMERGENCY EXIT OPENING FRAMESREVEALED CRACKING IN THE FS 783.95 FRAME. THE CRACKING IS TYPICAL OF BAC S/B 727-53-0197 AND AD 94-02-04. THE FRAME WAS REPAIRED AND MODIFIED IN ACCORDANCE WITH THE S/B TO ELIMINATE THE PROBLEM AND DOCUMENTED PER ER/A 379595-14AD.

Part: START VALVE — FAILED (NR 2 ENGINE) · airframe 54,031 hrs · 35,875 cycles

NR 2 ENGINE START VALVE CAME AT CLIMBOUT POWER 1.96 EPR WITH THE AIRCRAFT PASSING 5000 FT MSL. AFTER ENGINE NR 2 WAS RETARDEDTHE START VALVE OPEN LIGHT EXTINGUISHED. NR 2 ENG SHUTDOWN. REPLACED START VALVE AND PRESS SW; CKD CHIP DETECTOR AND STRAINER, CKS OK. REPLACED OIL FILTER. PERF WINDMILL INSPECTION PER MM. PERF HIGH PWR RUN, CKS GOOD.

Part: WEB — CRACKED (TORQUE BOX) · airframe 53,553 hrs · 35,544 cycles

A 1.5 INCH CRACK IN VERTICAL TORQUE BOX WEB RT FS 121, 3 INCHES JUST ABOVE THIRD STEP FROM TOP (48 SEC). REPAIRED PER M/M.

Part: SKIN — CORRODED (FUSELAGE) · airframe 53,499 hrs · 35,509 cycles

THE FUSELAGE SKIN AND UNDERLYING STRINGER WERE FOUND CORRODED BETWEEN FS 680 & 700 AT STRINGER 27R. THE DAMAGED SECTION OF SKIN AND STRINGER WERE CUTOUT AND REMOVED. A NEW SECTION OF STRINGER WAS SPLICED IN PER THE B727 SRM AND THE SKIN CUTOUT WAS REPAIRED WITH AND EXTERNAL ALUMINUM DOUBLER PER ER/A 378032-14, REV B.

Part: BEAM — TOOL DAMAGE (FUSELAGE) · airframe 53,499 hrs · 35,509 cycles

WHILE ACCOMPLISHING INSPECTIONS OF THE LBL 17.8 VERTICAL BEAM ON THE FS 1183 BULKHEAD PER BAC S/B 727-53-0210 AND AD 99-18-05, AN ELONGATED HOLE WAS FOUND COMMON TO THE WL 273 DOOR STOP INTERCOSTAL. THE HOLE WAS REAMED TO A CLEAN AND ROUND CONDITION, HFEC INSPECTED, AND AN OVERSIZE FASTENER INSTALLED PER ER/A 377987-14AD.

Part: VALVE — INOPERATIVE (RT PACK) · airframe 53,156 hrs · 35,276 cycles

LEFT PACK WILL NOT HOLD CABIN PRESS ABOVE 10,000 FEET. CARGO HEAT OUTFLOW VALVE CLOSED AND PACK ON PRESSURE IN MANUAL OUTFLOW VALVE FULL CLOSED. DUCT PRESSURE WAS NORMAL. REPLACED RT PACK VALVE.

Part: BATTERY PACK — INOPERATIVE (CABIN) · airframe 53,015 hrs · 35,182 cycles

OVERWING EMERG LIGHT INOP. REPLACED BATTERY PACK.

Part: STRINGER — CRACKED (VERT STAB)

VERTICAL STAB INTERIOR, STRINGER CRACKED AT TIE TO RIB LEFT SIDE AT FIN STA 1338. INSTALLED REPAIR PER SRM 55-30-0 FIG 803.

Part: WEB — CRACKED (BS 1243)

FOUND ON A-2 LETTER CK, .5 INCH CRACK AT LT TORQUE BOX VERTICAL WEB AT THE UPPER LIGHTENING HOLE STA 1243. REPAIRED PER MM 53-11-0.

Part: FRAME — CRACKED (CARGO DOORWAY)

LTR CHECK A2, 1 INCH CRACK AT C-2 DOOR CUTOUT FWD FRAME WEB AT LOWER END. REPAIRED PER SRM 53-10-4.

Part: WEB — CRACKED (BS 1243)

FOUND ON A2 LETTER CK. .25 INCH CRACK AT RT TORQUE BOX VERT WEB LOWER LIGHTENING HOLE STA 1243. REPAIRED PER MM 53-11-0.

Part: ANGLE — CRACKED (BS 913)

MLG W/W STA 913 ANGLE CRACKED AT UPPER RADIUS BLOCK ABOVE UPLOCK. REPAIRED PER DAL M/M 53-11-0 PGS 834-837 AND ERA 367582-14 ALLOWING USE OF DAL M/M REPAIR ON EX - EAL AIRCRAFT.

Part: SIGN — INOPERATIVE (2R DOOR)

EMERGENCY EXIT SIGN OVER 2R SERVICE DOOR FLICKERS FROM DIM TO BRIGHT WITH EMERGENCY LIGHT SYSTEM OFF.

Part: VALVE — LEAKING (B HYD SYST)

LOSS OF B HYD IN FLT. REPLACED LEAKING CHECK VALVE IN LEFT WHEEL WELL.

Part: WIRE — CRACKED (NR 3 ENGINE)

ON HUSH-KIT MOD FOUND NUMEROUS LONGITUDINAL CRACKS ON INSULATION ON ALL 3 GEN FEED CABLES IN MID PYLON AREA. REPLACED CABLES FROM SPLICES IN RT 48SEC TO FIREWALL DISCONNECT WITH NEW TYPE CABLES BMS13-58 DL (P/N 012210733).

Part: SKIN — DAMAGED (BS 1230)

INCORPORATION OF SKIN DAMAGE INTO MODIFICATION DOUBLER WHILE ACCOMPLISHING A MODIFICATION TO THE AIRCRAFT. INSTALLED FED-EX HUSHKITS AND EXISTING SKIN REPAIR WAS FOUND TO INTERFER WITH THE INSTALLATION OF A TITANIUM MODIFICATION DOUBLER ON THE SKIN. THE EXISTING REPAIR WAS REMOVED REVEALING A 2 INCH DIA SKIN CUTOUT BETWEEN FS 1223 AND 1243 S-15L & 16L. THE MOD DOUBLER WAS ENLARGED TO ENCOMPASS AND REPAIR THE DAMAGE PER ER/A 366686-14.

Part: ANGLE — CORRODED (NR2 ENGINE)

ON HUSH-KIT MOD, FOUND NR 2 ENG AFT MOUNT CHORD ANGLE CORRODED BEYOUND MFG SPECS. REPLACED CHORD ANGLE WITH NEW MFG RT SIDE.

Part: CORD ANGLE — NEW (NBR2 ENG AFT)

ON HUSH-KIT MOD, FOUND LT NR 2 ENG MOUNT CHORD ANGLE CORRODED BEYOUND MFG SPECS. REPLACED CHORD ANGLE WITH ANGLE OF NEW MFG.

Part: VALVE — FAILED (LT PACK)

LEFT PACK ON, CAUSED SMOKE IN CABIN. REPLACED FWD PACK VALVE AND MIX VALVE. CK OK.

Part: WEB — CRACKED (BS 1223)

FOUND ON A1 LETTER CK, 1 INCH CRACK LT TORQUE BOX VERTICAL WEB FWD OF STA 1223. REPAIRED PER MM 53-11-0 AND ERA 366033-14.

Part: WEB — CRACKED (BS 1283)

FOUND ON A1 LETTER CK, .5 INCH CRACK LT LOWER TORQUE BOX VERTICAL WEB STA 1283. REPAIRED PER MM 53-11-0 AND ERA 366033-14.

Part: RIB — CRACKED (NR 4 LE SLAT)

FOUND ON A1 LETTER CK, 1 INCH CRACK L/E RIB O/B OF ACTUATOR ON NR 4 SLAT. REPAIRED PER MM 57-54-0 AND ERA 366036-14.

Part: BATTERY PACK — DISCHARGED (CABIN)

EXTERIOR EMERGENCY LIGHT INOP RT SIDE 2ND LIGHT AFT OF OVERWING ESCAPE HATCHES. REPLACED BULBS, BATTERY PACK, CLEANED SOCKETS AND CHECKS OK.

Part: LIGHT — INOPERATIVE (CABIN)

EMERGENCY LIGHT INOP ABOVE AFT AIRSTAIR BOTTOM STEP IN CEILING. RELAMPED AND CLEANED SOCKET, CHECKS OK.

Part: OUTFLOW VALVE — STUCK (CABIN)

AFTER TAKEOFF, AIRCRAFT WOULD NOT PRESSURIZE. ALL MODES TRIED, PULLED AND RESET C/B, NO HELP. REPLACED OUTFLOW VALVE AND PRESSURE CONTROLLER AND CONTROL PANEL.

Part: BATTERY PACK — DISCHARGED (CABIN)

EMERGENCY EXIT LIGHT M1088 FAIL TEST. REPLACED BATTERY PACK, CHECKS OK.

Part: FRAME — CORRODED (BS 620)

INBD CHORD OF THE FS 620 FRAME WAS FOUND CORRODED APPROX 2 INCHES OUTBD OF S26R. CORROSION WAS ON THE INBD CHORD ONLY. REPAIRED PER ERA 331533-14.

Part: SKIN — DAMAGED (BS 1207)

AN EXISTING REPAIR WAS REMOVED FROM THE LOWER SKIN PANEL NEAR THE STRINGER 20R LAP SPLICE. THE UNDERLYING SKIN CUTOUT WAS 3.5 X 4. THE SKIN CUTOUT AND SURROUNDING AREA WAS DYE PENETRANT INSPECTED TO ENSURE NO CRACKS AND AN EXTERNAL ALUMINUM DOUBLER INSTALLED PER ER/A 364319-14, REV B.

Part: FLOORBEAM — CORRODED (BS 1110)

THE UPPER CAP OF THE FS 1110 PASSENGER FLOORBEAM WAS FOUND CORRODED. A SECTION OF THE CAP WAS CUT OUT BETWEEN RBL 12 AND LBL 12. THE CAP WAS REPAIRED WITH A FILLER SECTION AND FOUR SPLICE ANGLES PER ER/A 364205-14, REV A.

Part: SKIN — WORN (NR 1 TE MIDFLAP)

DURING SHOP VISIT THE LEADING EDGE SKIN WAS FOUND WORN BEYOND LIMITS AT THE I/B END OF FLAP. THE SKIN WAS REPAIRED PER 727 MM 57-52-0, FIG 803 BY REMOVING THE DAMAGE AND INSTALLING A DOUBLER.

Part: SPAR — CRACKED (WING)

AFT SPAR LWR RAIL GOUGED 57 FROM I/B END N/R 004267. AFT SPAR LWR RAIL, CRACKED FROM I/B END. N/R 004268, BOTH AREAS REPAIRED PER M/M 57-52-0 FIG 802. AFT SPAR BOTTOM FLANGE, 15 TR O/B END 5 ELONGATED HOLES N/R 004292, AFT SPAR LWR RAIL CRACKED 19 FROM I/B N/R 004274 AFT SPAR LWR RAIL HOLE ELONGATED 39 FROM I/B END N/R004271AFT SPAR BOTTOM FLANGE 5 HOLES ELONGATED 15 FROM O/B END N/R 004292, ALL DAMAGED REPAIRED PER M/ 57-52-0 FIG 802.

Part: ANGLE — CRACKED (NR 2 TE MIDFLAP)

THE MIDFLAP WAS FOUND WITH A CRACKED REAR SPAR ANGLE DURING SHOP VISIT. THE ANGLE WAS REPAIRED PER 727 MM 57-52-0 BY INSTALLING A DOUBLER.

Part: COVE SKIN — CRACKED (NR 2 TE FLAP)

DURING SHOP VISIT/INSPECTION, THE NR 2 MIDFLAP COVESKIN WAS FOUND CRACKED 31 INCHES FROM I/B END AT DRIVE ROD CUTOUT. THE COVESKIN WAS REPAIRED PER 727 MM 57-52-0 BY REMOVING THE CRACK AND INSTALLING A DOUBLER.

Part: ANGLE — CRACKED (NR 2 TE MIDFLAP)

DURING SHOP VISIT/INSPECTION, THE NR 2 MIDFLAP AFT SPAR ANGLE WAS FOUND CRACKED 32 FROM THE I/B END OF FLAP. THE DAMAGE WAS REPAIRED PER 727 MM 57-52-0 BY INSTALLING A DOUBLER.

Part: ANGLE — CRACKED (NR 2 TE MIDFLAP)

THE MIDFLAP WAS FOUND TO HAVE A CRACKED REAR SPAR ANGLE DURING SHOP VISIT. THE ANGLE WAS REPAIRED PER 727 MM 57-52-0 BY INSTALLING A DOUBLER.

Part: RIB — CRACKED (NR 1 TE MIDFLAP)

DURING SHOP VISIT, THE AFT RIB WAS FOUND CRACKED AT AFT SPAR I/B END OF FLAP. THE RIB WAS REPAIRED PER 727 MM 57-52-0 FIG 808 BY STOP DRILLING THE CRACK AND INSTALLING A DOUBLER.

Part: SKIN — WORN (RT TE MIDFLAP)

DURING SHOP INSPECTION, THE FLAP WAS FOUND WITH LEADING EDGE SKIN WORN BEYOND ALLOWABLE DAMAGE LIMITS AT O/B END. THE SKIN WAS REPAIRED BY REMOVING THE DAMAGED SKIN AND INSTALLING A FILLER AND DOUBLER PER 727 MM 57-52-0, FIG 803.

Part: ANGLE — CRACKED (NR 1 TE MID FLAP)

AFT LOWER SPAR CHORD ANGLE IS CRACKED 22 FROM O/B END OF FLAP. REPAIRED PER M/M 57-52-0.

Part: BATTERY PACK — DISCHARGED (CABIN)

AFT AIRSTAIR EMERGENCY EXIT LIGHT INOP. REMOVED AND REPLACED EMERGENCY BATTERY PACK. OPS CHECK OK PER MM 33-50-23. (M)

Part: LIGHT — BROKEN (CABIN)

EMERGENCY LIGHT AT L1 DOOR BROKEN. REMOVED AND REPLACED EMERGENCY LIGHT ASSEMBLY AND OPS CHECKED OK AS PER MM 33-50-01. (M)

Part: ACTUATOR SWITCH — STUCK (NR 8 L/E FLAP)

EWR/BDA - FLT 2 - AFTER TAKEOFF DURING FLAP RETRACTION, THE L/E FLAPS LIGHT ON FORWARD PANEL REMAINED ON (AMBER). AS FLAP RETRACTED TO ZERO DEGREES ON SECOND OFFICER'S SLAT POSITION INDICATOR, NR 8 WAS ILLUMINATED AMBER. A/C RETURNED TO EWR. REMOVED AND REPLACED NR 8 L/E SLAT ACTUATOR. OPS CHECK OK PER MM 27-81-32. (X)

Part: PBE — PIN PROTUDING (COCKPIT)

INDICATOR ON COCKPIT BEYOND LIMITS. REMOVED AND REPLACED COCKPIT PBE PER MM 25-60-00. (M)

Part: HEAT BLANKET — BURNT HOLE (AFT BAG FS 950C)

DURING A C-5 CHECK, NOTED THAT AFT BAG PIT HEAT BLANKET, P/N 10-60911-20; (COX P/N 2137-29), HAD A 2 INCH BY .50 INCH BURN THROUGH THE BLANKET. THE INSULATION BEHIND IT ALSO SHOWED SIGNS OF BURNING.

Part: LAMP — INOP (CABIN)

EMERGENCY LIGHT INOP AT ROW 20. REMOVED AND REPLACED EMERGENCY LIGHT BULB AND LENSE. OPS CHECK OK. (M)

Part: CONNECTOR — DIRTY (CABIN)

ON POST FLIGHT CHECK, FOUND LEFT AND RIGHT FORWARD OVERWING EMERGENCY LIGHTS INOP. CLEANED CONTACTS TO BOTH LEFT AND RIGHT FORWARD OVERWING LIGHTS. OPS CHECK OK. (M)

Part: POWER PACK — INOPERATIVE (CABIN)

EWR - POST-FLIGHT INSPECTION - EMERGENCY EXIT SIGN AT ROW 17 CEILING INOPERATIVE. REMOVED AND REPLACED POWER PACK. (X)

Part: TIRE — FLAT (NR 3)

NEWARK TO TAMPA - FLT 25 - NR 3 TIRE FLAT AFTER LANDING. ALSO, APPARENT DAMAGE TO WHEEL AND BRAKE. REMOVED AND REPLACED TIRE, BRAKE, AND AXLE SLEEVE. (X)

Part: CONNECTOR — DEFECTIVE (RT MLG DOOR)

INBOUND TO ATL, FLT NR 47, RIGHT GEAR DOOR WARNING LIGHT DID NOT COME ON WHEN GEAR WAS PUT UP OR DOWN AT FE PANEL. REMOVED AND REPLACED DEFECTIVE CANNON PLUG ON RIGHT DOOR WARNING SWITCH, PER MM 32-62-0, OPS CHECKED OK. (M)