N17025

Part: POWER SUPPLY — INOPERATIVE (CABIN)

INSPECTION FOUND AIRCRAFT LEFT EXTERIOR OVERWING EMERGENCY EXIT LIGHT INOPERATIVE. THE POWER SUPPLY AT L-3 DOOR WAS REMOVED AND REPLACED.

Part: WEB — CRACKED (RT TE FOREFLAP)

INSPECTION FOUND A .5 INCH CRACK IN THREE LOCATIONS OF MOST INBOARD WEB OF RT WING INBOARD FOREFLAP. THE WEB WAS REPLACED IAW SRM 51-10-01, PAGE 18.

Part: STIFFENER — CRACKED (WS 636.72)

INSPECTION FOUND A 1.5 INCH CRACK IN FORWARD VERTICAL STIFFENER AT LT WING LEADING EDGE RIB, INBOARD LEADING EDGE STA 636.72. THE STIFFENER WAS REPLACED IAW SRM 51-10-01.

Part: CHORD — CRACKED (LT TE MID FLAP)

INSPECTION FOUND AN 8 INCH CRACK IN UPPER CHORD OF LT WING OUTBOARD MID FLAP OUTBOARD REAR SPAR. THE CHORD WAS REPAIRED IAW SRM 51-40-02.

Part: WEB — CRACKED (WS 780)

INSPECTION FOUND A 2 INCH CRACK IN FORWARD SPAR WEB OF LT WING AT WS 780. THE WEB WAS REPAIRED IAW SRM 51-40-02, FIGURE 1.

Part: CHORD — CRACKED (RT TE MID FLAP)

INSPECTION FOUND A 6 INCH CRACK IN UPPER CHORD OF RT WING OUTBOARD MID FLAP OUTBOARD REAR SPAR. THE CHORD WAS REPAIRED IAW SRM 51-40-02.

Part: CHANNEL — CRACKED (NR 4 LE FLAP)

INSPECTION FOUND A .125 INCH CRACK IN AFT SUPPORT CHANNEL AT LT WING NR 4 LEADING EDGE FLAP. THE CHANNEL WAS REPAIRED IAW SRM 51-40-03, FIGURE 2.

Part: RIB — CORRODED (WS 614)

INSPECTION FOUND TOP RIB CHORD CORRODED AT LT WING LEADING EDGE, WS 614. THE RIB CHORD WAS REPAIRED IAW SRM 51-40-02, FIGURE 1.

Part: ANGLE — CRACKED (WS 631)

INSPECTION FOUND A .5 INCH CRACK IN VERTICAL SUPPORT ANGLE OF RT WING LEADING EDGE NOSE STRUCTURE BACKING WEB AT INBOARD LEADING EDGE STA 631. THE ANGLE WAS REPLACED IAW SRM 51-10-01.

Part: DOOR FRAME — CRACKED (BS 440)

INSPECTION FOUND A 1 INCH CRACK IN DOOR FRAME AT BS 440, STRINGER 26R. THE DOOR FRAME WAS REPAIRED IAW SRM 52-10-02, FIGURE 2.

Part: FRAME — CRACKED (BS 800)

INSPECTION FOUND A .75 INCH CRACK IN FRAME WEB AT STRINGER 24R AND A .75 INCH CRACK WAS FOUND IN FRAME WEB AT STRINGER 24L, BS 800. THE WEBS WERE REPAIRED IAW SRM 53-10-04, FIGURE 84.

Part: RIB — CRACKED (WS 670)

INSPECTION FOUND A 1.5 INCH CRACK IN RIB CHORD AT RT WING NR 3 MAIN TANK, WS 670. THE RIB CHORD WAS REPAIRED IAW SB 57-2273.

Part: WEB — CRACKED (BS 1650)

INSPECTION FOUND A .75 INCH CRACK IN WEB AT BS 1650, STRINGER 24L. THE WEB WAS REPAIRED IAW SRM 53-10-04, FIGURE 84.

Part: RIB — CRACKED (WS 628)

INSPECTION FOUND A .5 INCH CRACK IN RIB TOP AREA OF LT WING INBOARD LEADING EDGE STA 628. THE RIB WAS REPAIRED IAW SRM 51-40-02.

Part: DOUBLER — CRACKED (BS 400)

INSPECTION FOUND A .25 INCH CRACK IN DOUBLER AT BS 400 BULKHEAD AFT FACE, WL 120, RBL 40. A REPAIR WAS ACCOMPLISHED IAW SRM 53-10-04, FIGURE 37.

Part: WEB — CRACKED (BS 980)

INSPECTION FOUND A 3.5 INCH CRACK IN BEAM WEB AT BS 980, STRINGER 5R. THE WEB WAS REPLACED IAW SRM 51-10-01.

Part: ANGLE — CORRODED (BS 480)

INSPECTION FOUND ANGLE CORRODED AT BS 480, LBL 89. THE ANGLE WAS REPLACED IAW SRM 51-10-01.

Part: SUPPORT — CORRODED (BS 1300)

INSPECTION FOUND LATERAL FLOOR SUPPORT CORRODED AT BS 1300, RBL 11 TO 33. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-10-01.

Part: SUPPORT — CORRODED (BS 1367)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT BS 1367, RBL 11 TO RBL 33. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-10-01.

Part: SUPPORT — CORRODED (BS 1280)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT BS 1280, LBL 11 TO RBL 11. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-10-01.

Part: FITTINGS — CORRODED (BS 2360)

INSPECTION FOUND STRINGER END FITTINGS CORRODED AT BS 2360, S49L, S50L, S51L, S48R AND S51R. THE STRINGER END FITTINGS WERE REPLACED IAW SRM 51-10-01.

Part: SUPPORT PLATE — CORRODED (BS 1259)

INSPECTION FOUND FLOOR SUPPORT PLATE CORRODED AT BS 1259, RBL 11 TO 33. THE FLOOR SUPPORT PLATE WAS REPLACED IAW SRM 51-10-01.

Part: SUPPORT — CORRODED (BS 1259)

INSPECTION FOUND TWO FLOOR SUPPORTS CORRODED AT BS 1259, LBL 33 TO RBL 11. THE FLOOR SUPPORTS WERE REPLACED IAW SRM 51-10-01.

Part: SUPPORT — CORRODED (BS 765-880)

INSPECTION FOUND TWO FLOOR SUPPORTS CORRODED AT BS 765 TO 880, LBL 36. THE CORROSION WAS REMOVED AND TREATED, THE FLOOR SUPPORTS WERE REPLACED IAW SRM 51-10-01 AND 51-10-02.

Part: STRINGER — CRACKED (BS 741)

INSPECTION FOUND CRACKS IN STRINGER 2R AND 2AR AT BS 741. THERE WERE A TOTAL OF FOUR CRACKS MEASURING 2.5, 1.18, 1.38, AND 0.62 LONG. THE STRINGERS WERE REPAIRED IAW ECRA 5310-03383.

Part: SKIN — CORRODED (BS 520-741)

INSPECTION FOUND CORROSION IN SKIN LAP SPLICE AT SEVERAL LOCATIONS FROM BS 520 TO 741, STRINGER 6L. THE SKIN WAS REPAIRED IAW ECRA 5330-02472.

Part: DOUBLER — CORRODED (LT TE MID FLAP)

INSPECTION FOUND CORROSION ON LT WING OUTBOARD TRAILING EDGE MID FLAP OUTBOARD DOUBLER. THE DOUBLER WAS REPAIRED IAW ECRA 5750-02581.

Part: LUG — WORN (NR 4 TE FLAP)

INSPECTION FOUND LT WING NR 4 MOVEABLE FLAP TRACK FAIRING DRIVE ARM LOWER OUTBOARD HINGE OUTBOARD LUG WORN. THE WORN AREA WAS REPAIRED IAW ECRA 5750-02580.

Part: FITTING — CRACKED (LT REAR SPAR)

INSPECTION FOUND SPLICE FITTING AND UPPER SPLICE PLATE CRACKED AT LT WING REAR SPAR. THE CRACKS WERE 0.040 AND .25 INCH LONG. THE SPLICE PLATE AND SPLICE FITTING WERE REPLACED IAW EA 5710-01199 AND BOEING SB 57-2110.

Part: FRAME — CRACKED (BS 220)

INSPECTION FOUND A 1.75 INCH CRACK IN RT FRAME AT BS 220, STRINGER 32A. THE FRAME WAS REPAIRED IAW ECRA 5310-03374.

Part: STRINGER — CRACKED (BS 990)

INSPECTION FOUND A 1 INCH CRACK IN STRINGER 9R AT BS 990 MANUFACTURING SPLICE LOCATION. THE STRINGER WAS REPAIRED IAW ECRA 5310-03384.

Part: STRINGER — CRACKED (BS 1740)

INSPECTION FOUND A 0.87 INCH CRACK AT INBOARD VERTICAL FLANGE FASTENER HOLE OF STRINGER 9R AT THE MANUFACTURING SPLICE LOCATION, BS 1740. THE STRINGER WAS REPAIRED IAW ECRA 5310-03373.

Part: SKIN — CRACKED (WING CTR SEC)

INSPECTION FOUND A 0.040 CRACK AT THE RT WING EXTERNAL SPLICE FITTING AND A .1875 INCH CRACK AT THE MATING STRUCTURE WING CENTER SECTION UPPER SKIN PANEL. THE SPLICE FITTING WAS REPLACED IAW EA 5710-01199. THE SKIN PANEL WAS REPAIRED IAW ECRA 5710-01769.

Part: STRINGER — CRACKED (BS 2180-2190)

INSPECTION FOUND A .125 INCH CRACK IN STRINGER 3R AT MAIN DECK BS 2180 TO 2190. THE STRINGER WAS REPAIRED IAW SRM 53-10-03, FIGURE 6.

Part: SKIN — DELAMINATED (LT TE MID FLAP)

INSPECTION FOUND LT WING INBOARD MID FLAP PANEL NR 577KT SKIN DELAMINATED. A HOT BOND REPAIR WAS ACCOMPLISHED IAW SRM 51-40-06, FIGURE 15.

Part: FRAME — CRACKED (BS 360)

INSPECTION FOUND A .5 INCH CRACK IN FRAME AT MAIN DECK BS 360, LT SIDE, BETWEEN STRINGER 15 AND 16. THE FRAME WAS REPAIRED IAW ECRA 5310-03376.

Part: FRAME — CRACKED (BS 360)

INSPECTION FOUND A .75 INCH CRACK IN FRAME AT BS 360 ON RT SIDE, STRINGER 14E. THE FRAME WAS REPAIRED IAW ECRA 5310-03375.

Part: SPAR WEB — CRACKED (WS 688)

INSPECTION FOUND A .1875 INCH CRACK AT FASTENER HOLE OF NR 2 PYLON WING FRONT SPAR VERTICAL WEB AT INBOARD NACELLE RIB POST ATTACH AREA, WS 688. THE FRONT SPAR VERTICAL WEB WAS REPAIRED PER BOEING DRAWING 112U8040, FCD 5710-01758 AND SRM 51-10-01.

Part: SPLICE — CRACKED (BS 1480)

INSPECTION FOUND STRINGER SPLICE CORRODED WITH A 1.8 INCH CRACK ALONG FLANGE AT BS 1480, STRINGER 1L. THE STRINGER SPLICE WAS REPLACED IAW ECRA 5310-03380.

Part: FITTING — CORRODED (LT/RT WING)

INSPECTION FOUND LT AND RT WING TO BODY KICK FITTINGS CORRODED. THE BODY KICK FITTINGS WERE REPAIRED IAW ECRA 5340-01283.

Part: SKIN — CORRODED (WS 1454-1548)

INSPECTION FOUND CORROSION AT RT WING LOWER SKIN FORWARD OF FRONT SPAR LOWER CHORD AND EXTENDING AFT OF FRONT SPAR BETWEEN WS 1454 AND WS 1548. THE AREA WAS REPAIRED IAW ECRA 5710-01766.

Part: FRAME — CRACKED (BS 280)

INSPECTION FOUND A 2 INCH CRACK IN FRAME AT THE OUTBOARD FRAME WEB BETWEEN STRINGER 26R AND 27AR, BS 280. THE FRAME WAS REPAIRED IAW ECRA 5310-03370.

Part: FRAME — CRACKED (BS 380)

INSPECTION FOUND A .75 INCH CRACK IN FRAME AT BS 380, STRINGER 23R. THE FRAME WAS REPAIRED IAW ECRA 5310-03367.

Part: RIB — CRACKED (WS 670)

INSPECTION FOUND A 1 INCH CRACK IN FORWARD SHEAR TIE AT LT WING NR 2 MAIN TANK WS 670, UPPER STRINGER 27 AND A .5 INCH CRACK WAS FOUND AT SHEAR TIE OF RIB CHORD, LOWER STRINGER 19. THE RIB CHORD AT UPPER STRINGER 27 WAS REPAIRED IAW SB 57-2273. THE RIB CHORD AT LOWER STRINGER 19 WAS REPLACED IAW SRM 51-10-01.

Part: BULKHEAD — CRACKED (NR 3 PYLON)

INSPECTION FOUND A .125 INCH CRACK AT NR 3 PYLON FASTENER HOLE COMMON TO THE AFT BULKHEAD VERTICAL CHORD LT FITTING. THE NR 3 PYLON LT BULKHEAD ASSEMBLY WAS REPLACED IAW SRM 51-10-01 AND BOEING DRAWING 65B90413.

Part: BULKHEAD — CRACKED (NR 4 PYLON)

INSPECTION FOUND A 2 INCH CRACK AT UPPER POSITION OF NR 4 PYLON AFT BULKHEAD INBOARD CHORD. THE CHORD AND AFT BULKHEAD ASSEMBLY WERE REPLACED IAW SRM 57-10-01 AND SB 747-54A2159.

Part: BULKHEAD CHORD — CRACKED (NR 2 PYLON)

INSPECTION FOUND A .125 INCH CRACK AT FASTENER HOLE COMMON TO THE AFT BULKHEAD VERTICAL CHORD LT FITTING OF NR 2 PYLON. THE CHORD ASSEMBLY WAS REPLACED IAW BOEING DRAWING 65B90413 AND SRM 51-10-01.