N2817W

Part: BULKHEAD BEAM — CRACKED (BS 1183)

FUSELAGE BULKHEAD FS 1183, RBL 26.83, VERTICAL BEAM, CRACK REPAIR. THE RBL 26.83 VERTICAL BEAM ON THE FS 1183 BULKHEAD WAS FOUND WITH A TYPICAL CRACK. THE BEAM WAS REPAIRED PER BOEING S/B 727-53-0182, REV 1 AND DOCUMENTED PER ER/A 367994-14AD.

Part: FRAME — CRACKED (PAX DOORWAY)

FOUND AT B-2 LETTER CHECK, .5 INCH CRACK ON LT AFT ENTRY DOOR FRAME. REPAIRED PER SRM 53-10-9.

Part: FRAME — CRACKED (PAX DOORWAY)

FOUND AT B-2 LETTER CHECK, .5 INCH CRACK ON RT AFT ENTRY DOOR FRAME. REPAIRED PER SRM 53-10-9.

Part: SKIN — CRACKED (RT ELEVATOR)

A 2.5 INCH CRACK IN RT ELEVATOR LOWER SKIN AFT OF NR 4 BALANCE BOARD. REPAIRED PER SRM 55-20-3.

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 PANEL. INTERNAL HFEC INSPECTION CONFIRMED 9 CRACKS IN THE PANEL. THE SKIN LAP WAS CUT OUT ALONG THE LENGTH OF THE PANEL AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 367124-14AD.

Part: SKIN — CRACKED (BS 360-481)

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 PANEL. INTERNAL HFEC INSPECTION CONFIRMED 5 CRACKS IN TWO CONSECUTIVE FRAME BAYS. THE SKIN LAP WAS CUT OUT ALONG THE ENTIRE PANEL LENGTH AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 367122-14AD.

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. INTERNAL HFEC INSPECTION CONFIRMED 41 CRACKS ALONG THE PANEL. THE LAP SPLICE WAS CUT OUT ALONG THE PANEL LENGTH AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 367123-14AD.

Part: COALESCER — DIRTY (CABIN)

STRONG BURNING SMELL IN CABIN NEAR OVERWING EXITS WHEN MAIN SUPPLY TEMP EXCEEDS 80 DEGREES F. ISOLATED PACKS WITH APU AND ALL ENG BLEED SOURCES. RAN SUPPLY TEMP TO 130 DEGREES F WITH EVERY COMBINATION POSSIBLE. NO SMELLS OF ANY KIND. REPLACED BOTH WATER SEPARATOR BAGS AS PRECAUTIONARY.

Part: AIR DISTRIBUTION — ODOR (CABIN)

STRONG BURNING SMELL IN MID CABIN NEAR OVERWING EXITS. CKD APU FOR SIGNS OF OIL LEAKS, NONE FOUND. CHECKED OPR OF PACKS AND PACK FANS, NORMAL. RAN PACKS NO ABNORMAL ODORS NOTED IN CABIN.

Part: SKIN — DAMAGE (BS 620)

DURING REPLACEMENT OF BELLY SKIN, A FASTENER HOLE SUSTAINED TOOLING DAMAGE NEAR THE C-1 DOOR CUTOUT. REPAIR PER ERA 332149-14.

Part: SPAR — CRACKED (RT TE MIDFLAP)

AFT SPAR RAIL CRACKED 2 PLACES, 21 INCHES FROM I/B END OF FLAP. REPAIRED PER MM 57-52-0 FIG 802.

Part: SKIN — CRACKED (LT TE FLAP)

CRACK IN COVE SKIN 31 INCHES FROM I/B END OF FLAP. DAMAGE REPAIRED PER MM 57-52-0 FIG 809.

Part: SPAR — CRACKED (LT TE FLAP)

AFT SPAR RAIL CRACKED TWO PLACES 35 INCHES FROM I/B END OF FLAP. DAMAGE WAS REPAIRED PER MM 57-52-0 FIG 802.

Part: RIB — CRACKED (NR 4 TE MIDFLAP)

DURING SHOP VISIT, THE I/B AFT CLOSEOUT RIB WAS FOUND CRACKED. THE RIB WAS REPAIRED BY INSTALLING A DOUBLER PER 727 MM 57-52-0, FIG 808.

Part: HEAT SHIELD — CRACKED (NR 6 LE SLAT)

CRACKS IN HEAT SHIELD, NR 6 LE SLAT, ONE IS JUST OUTBOARD OF ACTUATOR ATTACH RIB, THE OTHER IS JUST OUTBOARD OF OUTBOARD TRACK. MANUFACTURED AND INSTALLED DOUBLERS ON HEAT SHIELD SKIN PER MM 57-54-0 FIG 803A. MANUFACTURED AND INSTALLED DOUBLER ON HEAT SHIELD SKIN PER MM 57-54-0 FIG 803A. STOP DRILLED AREAS. OK TO INSTALL DOUBLERS.

Part: SHIM — MIGRATED (TE FLAP TRACK)

DURING ROUTINE INSPECTIONS PER SI 4-58662-12AD, LAMINATED SHIMS WERE FOUND MIGRATED GREATER THAN THE .25 LIMIT ALLOWED PER BAC S/B 727-57-0178 AND AD 90-07-05. THE SHIMS WERE REPLACED PER THE REQUIREMENTS OF THE S/B AND THE AD. THE INSPECTIONS PER SI 4-58662-12AD WILL CONTINUE. THE REPAIR WAS DOCUMENTED PER ER/A 364927-14AD, REV A.

Part: LIGHT — INOPERATIVE (CABIN)

ON LAYOVER 2 CHECK, FOUND AFT CABIN OVERHEAD EMERGENCY LIGHT INOP. RELAMPED, NO HELP. REPLACED BATTERIES, NO HELP. REPLACED LIGHT ASSEMBLY AND INSTALLED NEW BATTERIES, OPERATIONAL CHECKS NORMAL.

Part: FUEL CONTROL — FAILED (NR 1 ENGINE)

ENGINE NUMBER ONE FAILURE IMMEDIATELY AFTER T/O. FLAMEOUT/ LOSS OF THRUST REPORT FILLED OUT. REMOVED AND REPLACED NR ONE ENGINE FUEL BOOST PUMP AND FUEL CONTROL. RAN AND TRIMMED ENGINE PER PRHB.

Part: BULKHEAD WEB — CRACKED (BS 1183)

DURING INPSECTION OF STA 1183 BULKHEAD PER SPECIAL INSPECTION 4-69150-12, A CRACK WAS DISCOVERED JUST BELOW A STIFFENER AT LBL 30, WL 188 IN THE WEB. THE CRACK MEASURED 2.5 INCHES. THE WEB MATERIAL IS .050 2024-T3 CLAD. THE -12 SPECIAL INSPECTION CALLS FOR THE ACCOMPLISHMENT OF EO 4-69150-3 IF A CRACK IS FOUND. HOWEVER, IN TPA'S CASE, THE A/C IS A LAYOVER A/C ONLY WITH INSUFFICIENT TIME TO FULLY ACCOMPLISH THE PERMANENT REPAIR. THEREFORE, A TEMPORARY REPAIR WILL BE INSTALLED UNTIL SUCH TIME THAT THE PERMANENT REPAIR CAN BE ACCOMPLIHSHED.

Part: STIFFENER — CRACKED (LT WING)

FOUND DURING A-1 LETTER CHECK, 1.5 INCH CRACK L/E SPAR STIFFENER AT NR 2 SLAT I/B TRACK ROLLER BOX I/B SIDE. REPAIRED PER M/M 57-20-21.

Part: BRACKET — CRACKED (NR 6 LE FLAP)

NR 6 L/E FLAP ACTUATOR MOUNT BRACKET CRACKED I/B SIDE AT MOUNT BOLT HOLES. REPAIRED PER MM 57-20-21.

Part: FITTING — CRACKED (RT HORIZ STAB)

FOUND A 1 INCH CRACK IN RT ELEVATOR HINGE SUPPORT CASTING 4TH HINGE FROM O/B END. REPAIRED PER M/M 55-10-31.

Part: STRINGER — CRACKED (VERT STAB)

FOUND DURING MV2, JUST INSIDE ACCESS 9504 ON RT SIDE 2ND FROM TOP STRINGER, CRACK AT RIB ATTACH BOLT. FABRICATED AND DRILLED REPAIR PARTS PER M/M 55-30-0 PG. 803. INSTALLED REPAIR PER M/M 55-30-0.

Part: BLKHD STIFFENER — CRACKED (BS 1183)

A CRACK WAS FOUND IN THE VERTICAL STIFFENER AT LBL 36.83 ON THE FWD SIDE OF THE BS 1183 BULKHEAD. THE CRACK WAS APPROX 1.75 LONG AT WL 237. THE STIFFENER WAS REPAIRED PER BOEING S/B 727-53-0192.

Part: SKIN — BENT (L1 DOOR)

L-1 DOOR EXT SKIN UPPER AFT CORNER BENT. STRAIGHTENED METAL, DYE-CHECKED FOR CRACKS PER PS 400-6-3. REPAIRED PER M/M 52-10-01 FIGURE 804, PG 806.

Part: BATTERY PACK — DISCHARGED (CABIN)

FWD OVERWING EXIT LIGHT ON RIGHT SIDE OF FUSELAGE INOP. REPLACED BATTERY PACK, OVERWING EXIT LIGHT CHECKED GOOD.

Part: RIB — CRACKED (NR 5 LE FLAP)

DURING INITIAL INSPECTION, RIB NR 4 AND RIB NR 5 WERE FOUND CRACKED. THEY WERE REPAIRED PER SRM 57-50-3.

Part: FUEL PUMP — FAILED (NR 1 ENGINE)

NUMBER 1 ENGINE SHUTDOWN 30 SECONDS AFTER LIFT OFF. FOUND SHAFT SHEARED ON FUEL PUMP. REPLACED PUMP AND CONTROL.

Part: COOLING VALVE — FAILED (EE COMP)

DISPATCHED WITH ONE PACK, MIX VLV INOP. ACFT WOULD NOT HOLD THE CABIN WITH CARGO HEAT OUTFLOW CLOSED AND OUTFLOW VLV FULL CLOSED. REPLACED EQUIP COOLING VLV IN E/E COMP, PRESS ACFT TO 3 PSI AND OPERATION CKS OK.

Part: SKIN — DENTED (FS 660-680)

THE FUSELAGE SKIN WAS OIL CANNED BETWEEN FS 660 TO 680 STR 23R AND STR 26R. THE DAMAGED AREA OF THE SKIN WAS TRIMMED OUT FROM FS 680 BUTT JOINT FORWARD FOR 19.75 AND FROM THE SKIN LAP JOINT AT STR 26R UP 25.75. A REPAIR DOUBLER WAS INSTALLED PER 8110-3 12-28-95, DL ERA 302929-14.

Part: BEADED DOUBLER — CRACKED (RT HORZ STAB)

DURING C/V, FOUND RT HORIZONTAL STABILIZER UPPER TRAILING EDGE PANEL BEADED DOUBLER LOWER PANEL CRACKED. REPAIRED PER SRM 55-20-3 FIG 3.

Part: SKIN — CORROSION (BS 690)

THE SKIN AT FS 680 CL AND FS 690 STR 26R WAS FOUND TO HAVE CORROSION DAMAGE. THE DAMAGE CUTOUT AT STA 680 CL IS APPROXIMATELY 2 BY 3, LOCAL SKIN THICKNESS IS 0.050. THE DAMAGE CUTOUT AT FS 690 IS APPROXIMATELY 2 BY 2, WITH A LOCAL SKIN THICKNESS OF 0.050. THERE IS A PREVIOUS INTERNAL REPAIR AT FS 680 TO 710, STR 26R TO STR 27R REFERENCE ER/A 232661-14 AND A PREVIOUS EXTERNAL REPAIR AT FS 703 STR 28L AND STR 28R, REFERENCE ER/A 216859-14. THIS ER/A IS CLASSIFIED AS AN RII DUE TO THE SIZE OF THE REPAIR AT STATION 690.

Part: SKIN — CORROSION (BS 500-570)

THE SUBJECT FUSELAGE SKIN WAS FOUND WITH CORROSION DAMAGE AT STR 26L LAP JOINT, FS 500, 520 TO 540 AND 560 TO 570. AT FS 500, THE DAMAGE CUTOUT IS APPROXIMATELY 8 BY 2 IN THE LOWER SKIN. AT FS 520 TO 540, THE DAMAGE CUTOUT IS APPROXIMATELY 7.75 BY 2 IN THE UPPER SKIN AND 14.5 BY 2.75 IN THE LOWER SKIN. AT STA 560 TO 570, THE DAMAGE CUTOUT IS APPROXIMATELY 9 BY 2.5 IN THE UPPER SKIN.

Part: SEAT TRACK — CORRODED (G-3 GALLEY)

SEAT TRACK AT G-3 GALLEY INBOARD AFT MOUNT IS CORRODED. REPAIR PER M/M 53-20-11, PAGE 805.

Part: WINDOW — CRACKED (COCKPIT)

R2 WINDOW OUTER PANE CRACKED PASSING THROUGH 23,000 ON CLIMBOUT. REPLACED R2 WINDOW AND HEAT CONTROLLER.

Part: BATTERY — OUT OF POSITION (CABIN)

OVERHEAD EMERGENCY LIGHT AT ROW 29 INOP. FOUND BATTERY CASE OUT OF POSITION. REPLACED BATTERY AS PRECATIONARY, OPN NORMAL.

Part: BULB — FAILED (CABIN)

RT AFT OVERWING EMERGENCY LIGHT INOP. RELAMPED, OPERATION NORMAL.

Part: BATTERY PACK — DISCHARGED (CABIN)

LT AFT OVERWING EMERGENCY LIGHT INOP. FOUND DEFECTIVE BATTERY PACK, REPLACED PACK, OPERATION NORMAL.

Part: SLAT — CRACKED (NR 2 LE FLAP)

FOUND DURING E-1 LETTER CHECK - .50 INCH CRACK AT I/B STOP PAD ON NR 2 SLAT. REPAIRED PER MM 57-54-0.

Part: RIB — CRACKED (NR 4 LE FLAP)

FOUND DURING E-1 LETTER CHECK - .1875 INCH CRACK BOTTOM OF NOSE RIB JUST LEFT OF SLAT ACTUATOR ROD END ON NR 4 SLAT. ONE INCH CRACK ON NR 4 SLAT I/B TRACK LOWER FAIRING RADIUS. BOTH REPAIRED PER MM 57-54-0.

Part: SLAT — CRACKED (NR 7 LE FLAP)

FOUND DURING E-1 LETTER CHECK - .25 INCH CRACK AT NR 7 SLAT O/B STOP PAD BELOW COVE PNL. REPAIRED PER MM 57-54-0.