N2816W

Part: ENGINE — LEAKING (NR 3) · airframe 78,851 hrs · 53,226 cycles

OIL QUANTITY ON NB 3 ENGINE DECREASING AT A RATE OF APPROX 1 QUART EVERY 15 MINUTES. ADDED 18 PINTS OF OIL TO NR 3 ENGINE. FOUND OIL LINE LEAKING. REPLACED BOTH O-RINGS, ITEM 75 AND 40 IPC 79-20-00-20 NR 4, 5 AND 6 BREATHER LINE.

Part: BATTERY — INOPERATIVE (CABIN) · airframe 78,204 hrs · 52,788 cycles

AFT RIGHT SERVICE DOOR OVERHEAD EMERGENCY LIGHT INOP. REPLACED BATTERIES, NOW CKS NORMAL.

Part: VALVE — MALFUNCTIONED (NR 1 ENGINE) · airframe 78,146 hrs · 52,748 cycles

NR 1 ENGINE COWL ANTI-ICE VALVE WON''T INDICATE OPEN IN FLT. GOOD EPR DROP WHEN SWITCHED OPEN. REPLACED NR 1 ENGINE COWL ANTI-ICE VALVE. NO HELP. FOUND BAD GROUND TO PIN B OF VALVE CANNON PLUG. INSTALLED NEW TERMINAL TO GROUND. OPERATION CHECKS GOOD WITH ENGINE RUNNING AND WITH ENGINE OFF.

Part: SKIN — DELAMINATED (SPOILER)

LTR CHK C-1 12/6/99, NR 3 SPOILER DELAMINATED UPPER O/B SIDE. REPAIRED PER SRM 57-50-6.

Part: ANGLE — CRACKED (NR 8 LE SLAT)

COVE SKIN ATTACH ANGLE CRACKED BELOW I/B STOP PAD NR 8 SLAT. REPAIRED PER MM 57-54-0 FIG 812.

Part: ANGLE — CRACKED (NR 8 SPOILER)

A 1.5 INCH CRACK IN SUPPORT ANGLE FWD OF NR 8 SPOILER. REPAIRED PER MM 57-20-22 FIG 806.

Part: SKIN — CRACKED (BS 680-740)

LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 680 AND 740 INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN. INTERNAL HFEC INSPECTION CONFIRMED 8 CRACKS IN CONSECUTIVE FRAME BAYS. THE SKIN LAP SPLICE WAS CUT OUT ALONG THE ENTIRE PANEL LENGTH AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 367192-14AD.

Part: SKIN — CRACKED (BS 481-681)

LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 481 AND 681 INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN PANEL. INTERNAL HFEC INSPECTION CONFIRMED 24 CRACKS ALONG THE PANEL LENGTH. THE ENTIRE SKIN LAP SPLICE WAS CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 367191-14AD.

Part: SKIN — CRACKED (BS 360-480)

LFEC INSPECTION OF THE STRINGER 4R SKIN LAP SPLICE BETWEEN FS 360 AND 480 INDICATED CRACKS IN THE LOWER FASTENER ROW OF THE LOWER SKIN. INTERNAL HFEC INSPECTION CONFIRMED 7 CRACKS IN CONSECUTIVE FRAME BAYS. THE SKIN LAP SPLICE WAS CUT OUT ALONG THE ENTIRE PANEL LENGTH AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 367190-14AD.

Part: SIGN — MISSING (RT EMER EXIT)

RT FWD OVERWING EXIT SIGN MISSING. REPLACED RT FWD OVERWING EXIT SIGN, OP CKS OK.

Part: BATTERY PACK — DISCHARGED (RT WING)

RT WING FWD EMERGENCY SLIDE LIGHT INOP. REPLACED BATTERY PACK.

Part: WEB — CORRODED (BS 300)

CORROSION WAS FOUND ON THE UPPER HORIZ PRESSURE WEB DOUBLER OF THE NLG W/W FWD OF BS 315. THE DAMAGE NECESSITATED A NEW SECTION BE SPLICED IN. REPAIRED PER ERA 332271-14.

Part: FRAME — CRACKED (PAX DOORWAY)

CRACK WAS FOUND IN THE AFT ENTRY DOORWAY LT FRAME AT WL 276.6. THE CRACK WAS 4.5 INCH LENGTH AND TYPICAL OF THAT FOUND IN SB 727-53-0055 REV 9. REPAIRED PER ERA 332362-14AD.

Part: SKIN — CRACKED (BS 687)

A FAILED FASTENER WAS FOUND IN THE UPPER ROW OF THE S26R SKIN LAP JOINT AT BS 684. CRACKS WERE FOUND EMANATING FROM THIS FASTENER HOLE IN THE OUTER SKIN ONLY. THE CRACKS WERE .125 AND .0937 LONG. REPAIRED PER ERA 332342-14.

Part: STRINGER — CORRODED (BS 371)

CORROSION WAS FOUND ON THE I/B FLANGE OF S3R AT FS 371 REQUIRING A SECTION OF STRINGER TO BE CUT OUT. REPAIRED PER ERA 332244-14.

Part: ANGLE — CRACKED (RT TE MIDFLAP)

DURING SHOP INSPECTION, THE AFT LOWER CLOSEOUT ANGLE WAS FOUND CRACKED 33 FROM THE IB END OF FLAP. THE ANGLE WAS REPAIRED PER 727 MM 57-52-0,FIG. 802 BY INSTALLING A DOUBLER AND STOP DRILLING THE CRACK.

Part: STRINGER — CORRODED (BS 375)

CORROSION DAMAGE FOUND THAT EXCEEDED ALLOWABLE LIMITS, ON THE S1L, AT BS 375. REPAIRED PER ERA 332246-14.

Part: SPAR — CRACKED (LE FLAP)

SPAR CRACKED AT ANTI-ICE DUCT CUTOUT. REPAIRED PER MM 57-54-0.

Part: S-DUCT — CRACKED (NR 2 ENGINE)

AT HMV FOUND SKIN - BENT/CRACKED INSIDE S-DUCT APPROX 4FT FROM L/E OF INLET AT 12 O-CLOCK POSITION. CORR: MANUFACTURED REPAIR DBLR AND FILLER PER SRM 54-10-3 P.63 INSTLD PER SAME.

Part: STRINGER — CRACKED (WS 656.5)

ON HMV, RT WING OUTER UPPER STRINGER 2 RIB AT WS 656.5 STR 12 IS CRACKD AT FASTENER HOLE. CUT OUT VENT STRINGER, DRILLED UP REPAIR ANGLES RADUIS FILLERS CVR ASSY PER MM 57-13-00. INSTALLED REPAIR ANGLES.

Part: STRINGER — CRACKED (WS 656.5)

AT HMV, FOUND RT WING OUTER W/UPR STRINGER 2 RIB AT WS 656.5 STRINGER 13 IS CRACKED AT FASTENER HOLE. REPAIR INFO IS REF ON OPN 8602AD ITEM 5. CUT OUT VENT STRINGER, DRILLED UP REPAIR ANGLES RADIUS FILLER COVER ASSY PER M/M 57-13-00. INSTALLED PER SAME.

Part: ANGLE — CRACKED (LT TE MIDFLAP)

DURING SHOP INSPECTION, THE AFT LOWER SPAR ANGLE WAS FOUND CRACKED 32 INCHES FROM I/B END OF FLAP. THE ANGLE WAS REPAIRED PER MM 57-52-0 FIG 802, BY STOP DRILLING THE CRACK AND INSTALLING A DOUBLER.

Part: ANGLE — CRACKED (NR 5 LE SLAT)

AT HMV, FOUND NR 5 SLAT ANGLES - ACTUATOR ATTACH POINT BOTH I/B AND O/B ANGLES CRACKED. STOP DRILLED CRACK PER M/M, FABD REPAIR DOUBLERS, INSTALLED PER MM 57-54-00 FIG 809.

Part: GUIDE — WORN (NR 5 LE SLAT)

AT HMV, FOUND GUIDE ON NR 5 SLAT TRAILING EDGE O/B OF ACTUATOR WORN. WEAR LIMITS OK, REPAIRED PER M/M 27-81-11.

Part: RIB — CRACKED (RT TE FLAP)

I/B AFT RIB IS CRACKED AT AFT LWR CORNER. REPAIRED PER MM 57-52-0 FIG 808.

Part: SKIN — CRACKED (DORSAL FIN)

.25 INCH CRACK DORSAL FIN SKIN LEFT SIDE BELOW PANEL 9523. REPAIRED PER M/M 54-30-0 PG 804.

Part: BATTERY PACK — DISCHARGED (CABIN)

WORKING L/O, NR 2 FOUND AIRSTAIR UPPER EMERGENCY EXIT LIGHT INOP. REPLACED BATTERY PACK PER M/M OP CK GOOD.

Part: LIGHT ASSY — INOPERATIVE (CABIN)

RIGHT EMERGENCY OVERWING EXIT LIGHT INOP ON EMERGENCY PWR. OP NORMAL ON AC PWR. REPLACED LIGHT ASSY AT OVERWING EXIT.

Part: BRACKET — CRACKED (NR 1 LE SLAT)

FOUND ON A1 LETTER CK, NR 1 SLAT ACTUATOR I/B ATTACH BRACKET CRACKED. REPAIRED PER MM 57-20-21.

Part: BRACKET — CRACKED (NR 1 LE SLAT ACT)

NR 1 SLAT ACTUATOR I/B ATTACH BRACKET CRACKED. OPENED PANELS FOR ACCESS, REMOVED RIB WEB, STOP DRILLED CRACK, DRILLED UP DOUBLER. INSTALLED DOUBLER AND CLOSED UP.

Part: SKIN — CRACKED (FUSELAGE)

FOUND ON A1 LETTER CK, .1562 AND .125 INCH CRACKS IN FUSELAGE SKIN COMING OUT OF RIVET HOLE JUST AFT OF L3 WINDOW LOWER END. REPAIRED PER SRM 53-30-3.

Part: STIFFENER — CRACKED (WING LE SPAR)

A 1.5 INCH CRACK_IN SPAR STIFFENER LOCATED OUTBD SIDE OF NR 6 SLAT INBD TRACK. REPAIRED PER MM 57-20-21.

Part: BULKHEAD — CRACKED (BS 1183)

A 2 INCH CRACK WAS FOUND IN THE 1183 BULKHEAD AT RBL 8.0 AND WL 180. THIS ER/A WILL GIVE INSTRUCTIONS TO ACCOMPLISH A REPAIR UNTIL THE FULL MODIFICATION REQUIRED BY AIRWORTHINESS DIRECTIVE 90-06-09 IS ACCOMPLISHED. THE REPAIR WILL BE INSTALLED ON THE FWD SIDE OF THE BULKHEAD. THE CRACK WILL BE CUT OUT.

Part: STRINGER — CRACKED (VERT STAB)

STRINGER 8 CRACKED INSIDE VERT STAB RT SIDE FIN STA 133.800. REPAIRED PER M/M 55-30-0.

Part: FRAME — CRACKED (RT SERVICE DOOR)

RT AFT SERVICE DOOR FWD FRAME CRACKED .5 INCH AT LOWER I/B CORNER OF UPPER HINGE CUTOUT. REPAIRED PER SRM 52-40-2 FIG 4.

Part: STIFFENER — CRACKED (RT WING LE)

A 1 INCH CRACK IN WING L/E VERTICAL STIFFENER AT NR 5 SLAT I/B TRACK O/B POSITION. REPLACED STIFFENER PER M/M.

Part: FRAME — CRACKED (RT SERVICE DOOR)

RT AFT SERVICE DOOR FWD FRAME CRACKED .5 INCH AT LWR I/B CORNER OF UPPER HINGE CUTOUT. REPAIRED PER SRM 52-40-2 FIG 4.

Part: WEB — CRACKED (LWR TORQUE BOX)

FOUND DURING E-2 LETTER CHECK - .50 INCH CRACK, LT FWD TORQUE BOX LIGHTENING HOLE. REPAIRED PER M/M 53-11-0.

Part: ANGLE — CORRODED (LWR FUS FAIRING)

FOUND DURING E-2 LETTER CHECK - CORROSION AT HINGE ON LOWER FUSELAGE FAIRING PANEL FWD OF LOWER BEACON. REPAIRED PER M/M 53-30-1.

Part: SKIN — CRACKED (VERT STAB)

FOUND DURING E-2 LETTER CHECK - 2 EA, .25 INCH CRACKS EXTENDING FROM RIVET HOLES, RT VERTICAL STAB SKIN, JUST BELOW SADDLE PLATE 9501. REPAIRED PER M/M 54-30-0.

Part: SKIN — GOUGES (FS 1070)

MTC REPORTS, 3 GOUGES IN THE FUSELAGE SKIN BELOW AND JUST AFT OF THE L2 DOOR LWR AFT CORNER. THE FIRST GOUGE IS LOCATED JUST AFT OF FS 1070, IT IS 7 INCHES LENGTH, HAS A MAX DEPTH OF 0.010, AND RUNS PERPENDICULAR TO S-18L. IT WILL BE BLENDED AND TREATED PER B727 SRM 53-30-1 FIG 1 DETAIL 1. THE OTHER TWO GOUGES ARE LOCATED AT FS 1070, BETWEEN S-17L AND S-18L. THE FWD GOUGE IS 4 INCHES IN LENGTH AND HAS A MAX DEPTH OF 0.014. THE AFT GOUGE HAS A MAX DEPTH OF 0.028 AND IS 5 INCHES IN LENGTH. REPAIRED PER DL ERA 302623-14.

Part: VENTRAL WEB — CRACKED (BS 1245/1225)

FOUND DURING E-1 LETTER CHECK - LIGHTNING HOLE HAS CRACK LT VENTRAL WEB STA 1245 - LT VENTRAL WEB HAS CRACK AT TOP OF WEB AT STA 1225. REPAIRED PER MMM 53-11-0 PG 828 - 832.

Part: SKIN — DAMAGED (RT ELEVATOR)

FOUND DURING E-1 LETTER CHECK - 1 INCH HOLE ON BOTTOM SKIN OF RT ELEVATOR. REPAIRED PER MM 55-20-3.

Part: PANEL — DELAMINATED (RT SPOILER)

DURING LETTER CHECK, FOUND RT WING SPOILER PANEL WITH DELAMINATION DAMAGE, REPAIRED PER SRM 57-50-6.

Part: ANGLE — CRACKED (NR 6 SLAT)

FOUND DURING D-2 LETTER CHECK, COVE SKIN ATTACH ANGLE CRACKED 2 INCH AT O/B STOP FITTING NR 6 SLAT. REPAIRED PER MM 57-54-0 PG 816.

Part: ANGLE — CRACKED (FS 1273)

DURING INSPECTION, THE RT TORQUE BOX UPPER TRANSVERSE BEAM GUSSET ANGLE AT FS 1273 WAS FOUND CRACKED. THE ANGLE WILL BE REPLACED IN ACCORDANCE WITH B727 SB 53-0129 REV 4.