N908DL

Part: BATTERY — DISCHARGED (CABIN) · airframe 81,580 hrs · 62,737 cycles

MULTIPLE EMERGENCY LIGHTS INOP IN CEILING. R/R EMERGENCY BATTERIES IN OVERHEAD BIN AT SEATS 4DC, 17ED, AND 24ED PER AMM 33-53 OPS CK NORMAL OK FOR SVC. (LP5351209)

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 81,318 hrs · 62,509 cycles

OVERHEAD EMERGENCY LIGHT WAS OUT ROWS 1 - 4 & 16 - 20. REPLACED BATTERY PACKS B5-100 AND B5-102 IAW AMM 44-53. OPS CHECKED GOOD. AC OK FOR SERVICE.

Part: UNKNOWN — ODOR (COCKPIT) · airframe 80,874 hrs · 62,137 cycles

ON SHORT APPROACH AT 800 AGL, A VERY STRONG, ACRID, ELECTRICAL SMELL IN COCKPIT. NO VISIBLE SMOKE. FLIGHT ATTENDANTS SMELLED NOTHING. VERY SLOW TO DISSIPATE AT GATE. PERFORMED PNEUMATIC DIST CABIN SMOKE/ODOR TROUBLESHOOTING W/C 2120-2367 PER NO-DO ODI PROCEDURES. COULD NOT FIND SOURCE OF SMELL. PERFORMED DUCT BURN PROCEDURES IAW AMM 21-20-02 SECTION C. NO TROUBLE FOUND. A/C OK FOR SERVICE.

Part: SLIDE — DAMAGED (L1 DOOR) · airframe 80,607 hrs · 61,920 cycles

L1 DOOR SLIDE HAS COME APART. REMOVED AND REPLACED L1 DOOR SLIDE PER WORKCARD 2561-4964 SLIDE, PN OFF 09-2561-9-0011 01159 ON 88-2560-9-0003 03247.

Part: CONTROLLER — MALFUNCTIONED (WINDOW HEAT) · airframe 80,253 hrs · 61,628 cycles

CENTER WINDSHIELD ANTI FOG SENSOR UNIT OVERHEATED WITH CORRESPONDING ODOR/FUMES. REPLACED CENTER WINDSHIELD & CONTROLLER. REPLACED BURNT SCREW ON WINDOW HEAT TERMINAL. OPERATION CHECKS NORMAL.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHTS) · airframe 80,110 hrs · 61,513 cycles

DURING A SERVICE CHECK, EMERGENCY OVERHEAD LIGHTS OUT AT ROWS 17 - 21. REPLACED THE LAMPS.

Part: LIGHT — INOPERATIVE (SEAT 14D) · airframe 79,255 hrs · 60,844 cycles

SEAT 14D EMERGENCY LIGHT INOPERATIVE. REPAIRED THE LIGHT IAW AMM 33-53.

Part: BATTERY PACK — DISCHARGED (COCKPIT) · airframe 79,255 hrs · 60,843 cycles

COCKPIT OVERHEAD DOME/PEANUT LIGHTS INOP. RMVD/RPLD EMERGENCY BATTERY PACK B5-23. OPS CK GOOD. OK FOR SVC PER WDM 33-51.

Part: BATTERY — DISCHARGED (CABIN) · airframe 78,721 hrs · 60,429 cycles

OVERWING EXIT FWD POSITION EMERGENCY LIGHTS INOP. REPLACED BATTERYS IN OVERWING BATTERY PACK AS PER AMM 33-53-00 CKS GOOD.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 78,673 hrs · 60,391 cycles

EMER CEILING LIGHTS INOP FROM ROW 16-20. REPLACED BATTERY PACK AT B5-102 REF AMM 33-53. OPS CHECK GOOD.

Part: FRAME — CRACKED (BS 1463) · airframe 77,461 hrs · 59,471 cycles

CRACK FOUND IN WEB OF CANTED FRAME BS 1463. REPAIRED IAW PRI 554532-14 REV 0, PRI 554532-14 REV 1, PRI 554532-14 REV 2.

Part: STRUCTURE — CRACKED (TAILCONE) · airframe 77,461 hrs · 59,471 cycles

TAIL CONE INTERIOR CRACKED BOTTOM AFT LEFT SIDE. INSTALLED SERVICEABLE TAIL CONE IAW AMDS TASK CARD 5350-4287. (LP2852835)

Part: GUIDE — MISSING (TAILCON) · airframe 77,461 hrs · 59,471 cycles

TAIL CONE RELEASE CABLE PULLEY MISSING CABLE GUIDE AT 9 O'CLOCK. INSTALLED PULLEY CABLE GUIDE AT 9 O'CLOCK POSITION, O.K. FOR SERVICE.

Part: LATCH — DAMAGED (TAILCONE) · airframe 77,461 hrs · 59,471 cycles

TAIL CONE LATCH AT 4 O'CLOCK POSITION MISSING HARDWARE AND LOOSE. INSTALLED MISSING HARDWARE AND TIGHTENED, OK FOR SERVICE.

Part: PUMP — FAILED (FUEL BOOST) · airframe 77,404 hrs · 59,416 cycles

DIVERTED DUE TO THE CIRCUIT BREAKER FOR THE RIGHT WING FORWARD FUEL BOOST PUMP TRIPPED AT FL 330. CREW RECEIVED EOAP MESSAGE RT FUEL INLET PRESSURE LOW AND THE RIGHT WING AFT FUEL BOOST PUMP WAS ON MEL. CREW WAS ABLE TO CROSSFEED FUEL FROM THE LEFT WING TANK. REMOVED AND REPLACED THE RIGHT FORWARD FUEL BOOST PUMP.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 77,404 hrs · 59,416 cycles

MULTIPLE CEILING EMERGENCY LIGHTS INOPERATIVE. REMOVED & REPLACED THE BATTERIES. OPS CHECKED GOOD.

Part: BLADE — DAMAGED (NR 1 ENGINE) · airframe 76,900 hrs · 59,080 cycles

RETURNED TO SGF DUE TO NR 1 ENGINE COMPRESSOR STALL WITH A REDUCED THRUST. CABIN CREW VERIFIED COMPRESSOR STALL AND CABIN ODOR. MTC FOUND FAN BLADE TIPS BENT FORWARD INDICATING ENGINE INGESTED SOFT FOD. MTC FOUND 2ND STAGE VANES PULLING FROM CASE. ENGINE WAS NOT SHUT DOWN. ENGINE REPLACED AND COALESCER BAGS REPLACED.

Part: WIRE — OUT OF POSITION (CABIN) · airframe 76,673 hrs · 58,899 cycles

1R GALLEY OVERHEAD EMERGENCY LIGHTS INOPERATIVE. FOUND WIRES CROSSED BETWEEN 1R DOOR OVERHEAD EMERGENCY LIGHT SOCKET AND SWITCH FOR OVERHEAD WORK LIGHTS. RECONFIGURED WIRING IAW WDM 33-51-12. OPS CHECK GOOD.

Part: SLIDE — MISINSTALLED (TAILCONE) · airframe 74,074 hrs · 57,044 cycles

MAINTENANCE FOUND TAIL CONE SLIDE NOT PROPERLY INSTALLED. SLIDE WAS PROPERLY INSTALLED.

Part: RELEASE CABLE — BROKEN (TAILCONE) · airframe 74,072 hrs · 57,043 cycles

MAINTENANCE FOUND BROKEN STRANDS ON TAILCONE RELEASE CONTROL CABLE SEGMENT. TAIL CONE RELEASE CONTROL CABLE SEGMENT WAS R & R.

Part: FRAME SPLICE — NOT REPORTED (BULKHEAD) · airframe 74,072 hrs · 57,043 cycles

AFT PRESSURE BULKHEAD LOWER FRAME SPLICES WERE FOUND BETWEEN LONGERON 26R-27R AND BETWEEN LONGERON 26-27L. AREA WAS REPAIRED IAW ER/A 537817-14, REV ORIG.

Part: SKIN — DAMAGED (BS 1079-1098) · airframe 74,072 hrs · 57,043 cycles

HAD LIGHTNING STRIKE ON FUSELAGE SKIN ABOVE LONGERGON 3R BETWEEN BS 1079-1098. REPAIRED IAW ER/A 537810-14, REV ORIGINAL.

Part: STRUCTURE — BROKEN (RT MLG) · airframe 74,072 hrs · 57,043 cycles

DURING MAINTENANCE, FOUND BROKEN EDGES AT RT MLG BEARING BORE. REPAIRED IAW ER/A 537816-14AD, REV ORIGINAL.

Part: SKIN — CRACKED (BS 1418) · airframe 74,072 hrs · 57,043 cycles

ONE CRACK 2.937 INCHES IN LENGTH WAS FOUND ON FUSELAGE SKIN AT BS 1418 AND BETWEEN LONGERONS 1 AND 2R. REPAIRED IAW ER/A 537780-14, REV A.

Part: SKIN — DAMAGED (BS 125-133) · airframe 74,072 hrs · 57,043 cycles

DURING VISUAL INSPECTION IAW ETI-88-15-326, STEP 3, ELONGATED HOLES ON FS=125-133 Z=22 AT LT FUSELAGE SKIN EXISTING REPAIR AREA. AREA WAS REPAIRED IAW ER/A 234659-14, REV E.

Part: CARGO TRACK — DAMAGED (BS 427-522) · airframe 74,072 hrs · 57,043 cycles

ELONGATED HOLES ON LT CARGO TRACK FROM BS 427 - 522. THE CARGO TRACK WAS REPAIRED IAW SRM 51-30-2, 51-30-5, 51-10-3, PAR 21,14 AND ER/A 537819-14, REV ORIGINAL AND 53-05, FIG 49.

Part: SKIN — DEFORMED (R1 DOOR) · airframe 74,072 hrs · 57,043 cycles

DEFORMED EXTERNAL SKIN ON R1 DOOR LOWER EDGE. R1 DOOR LOWER EDGE WAS REPAIRED IAW ER/A 537815-14, REV. ORIGINAL.

Part: CARGO TRACK — DAMAGED (BS 427-522) · airframe 74,072 hrs · 57,043 cycles

ELONGATED HOLES ON RT CARGO TRACK BS 427 - 522. THE CARGO TRACK WAS REPLACED WITH SRM 51-30-1, 01-30-2, 51-10-4, AN D51-10-3 PAR 14, 21.

Part: TEE FITTING — CORRODED (BS 1361-1410) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION FOUND ON TEE BETWEEN BS 1361 - 1410, LONGERON 24 - 25L IN THE AFT ACCESSORY COMPARTMENT. FOUND TO BE OUT OF LIMITS. THE TEE WAS REMOVED, REPAIRED AND INSTALLED IAW SRM 53-01, FIG 2, SH 4, SRM 51-10-3, PAR 14-21, 51-30-2 AND 51-30-5.

Part: FRAME — CRACKED (BS 1418) · airframe 74,072 hrs · 57,043 cycles

CRACKED FRAME CAP ON BS Y=1418 BETWEEN LONG 1 RT AND 2 RT AT AFT ACCESSORY COMPARTMENT, CAT, SM, IN REF CARD 06, ZONE 65, ZONE 65, CARD 27. FRAME CAP WAS REPLACED IAW SRM 51-30-5, 51-10-3, CRACK 0.800".

Part: FRAME — CORRODED (BS 1463) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

ACFT HAS CORROSION ON PREVIOUS REPAIR TRIPLER ON FRAME ANGLE AT BS 1463 FROM LONGERONS 6 - 18L AT AFT ACCESSORY COMPARTMENT. REPAIR TRIPLER WAS REPLACED IAW SR J060287. REV AND SRM 51-30-5, 51-10-2 AND 53-03D, FIG 27, 51-10-3, PAR 21,14.

Part: FLOOR PANEL — DELAMINATED (NOT REPORTED) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS DELAMINATED FLOOR PANE. FLOOR PANEL FABRICATED IAW AMM 53-20-01-201.

Part: FLOOR PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORRODED FLOOR PANEL. FLOOR PANEL FABRICATED AND REPLACED IAW AMM 53-20-01-201.

Part: CARGO TRACK — CORRODED (BS 1008-1322) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

ACFT HAS CORROSION ON RT CARGO TRACK BS 1008-1322. THE CARGO TRACK WAS REPLACED IAW SRM 53-05, FIG 4C AND 51-30-2 AND 51-30-1, 51-10-4, 51-10-3 PAR 14 AND 21.

Part: RETAINER — CRACKED (EMERGENCY EXIT) · airframe 74,072 hrs · 57,043 cycles

CRACKED SEAL RETAINER AT RT FWD EMERGENCY DOOR LOWER AREA, REF NRC CARD 92, ZONE 201. SEAL RETAINER AT RT FWD EMERGENCY DOOR LOWER AREA, REF NRC CARD 92, ZONE 201 WAS REPLACED IAW SRM 51-30-2. CRACK LENGTH 0.437".

Part: FINGER DOUBLER — CRACKED (BS 1251-1260) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION AND CRACK ON SPLICE FINGER DOUBLER AT LONGERON 26, LT FROM BS 1251 - 1260 C3. CRACK DIMENTION IS 1.00" THE SECTION FINGER DOUBLER DAMAGE WAS REMOVED AND NEW SECTION WAS FABRICATED AND WAS TREATED AND PAINTED AND WAS INSTALLED IAW SRM 51-10-1, FIG 36 AND DWG 5936667, REV CD.

Part: CARGO TRACK — CORRODED (BS 1156-1322) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION ON LT CARGO TRACK BS 1156 - 1322 AT AFT CARGO COMPARTMENT C3. TIE TRACK WAS REPLACED IAW SRM 51-30-1, 51-30-2, 51-30-5, 51-10-4, 51-10-3 PAR 21 AND 14, AND DOUGLAS DWG NR 5956705.

Part: CHANNEL — CRACKED (BS 994) · airframe 74,072 hrs · 57,043 cycles

CRACKED AFT CHANNEL BS 994 X-53 AT RT WHEEL WELL. TEE WAS REPLACED IAW SRM 51-10-4 AND DWG 5936395, REV BF AND SRM 51-10-3, PAR 14, 21 ALSO SRM 51-30-2, 51-30-5A.

Part: BEAM — CORRODED (BS 639-691) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

ACFT HAS CPCP CORROSION ON BEAM FROM BS 639 - 691 AT CENTER LOWER CARGO COMP DOOR JAMB. SPACER WAS REPLACED IAW SRM 51-30-5 AND 53-05, FIG 123-A 51-10-3, PAR 14 AND 21, 38.

Part: FLOOR PANEL — PUNCTURED (NOT REPORTED) · airframe 74,072 hrs · 57,043 cycles

PUNCTURED FLOOR PANEL. FLOOR PANEL FABRICATED IAW AMM 53-20-01-201.

Part: FRAME — CRACKED (BS 1464) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS A CRACK ON PREVIOUS TRIPLER REPAIR ON FRAME ANGLE AT BS 1464 ON LONG 18R AT AFT ACCESSORY COMPARTMENT. TRIPLER REPAIR ON FRAME CLIP WAS REPLACED IAW SRM 51-10-4; 51-30-5 AND SR J060287-12, REV.

Part: CUSP WEB — CORRODED (BS 670-710) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

ACFT HAS CORROSION ON LT CUSP WEB BS Y= 670 TO 672 AND 696 TO 710 BETWEEN X=54 TO 60 AT PASSENGER CABIN FLOOR STRUCTURE. CORROSION WAS ATTENDED WITH SRM 51-30-2, 53-05 FIG. 131A-13, 51-10-3, PARA 14, 21, 38.

Part: SKIN — DAMAGED (RUDDER) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS DAMAGED METALLIZED BOTH FACES ON RUDDER. METALIZED BOTH FACES ON RUDDER WERE REPAIRED IAW SRM 51-70-1A PAR 23A.

Part: CUSP WEB — CORRODED (BS 555-559) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

ACFT HAS CORROSION ON PREVIOUS REPAIR DOUBLER ON LT CUSP WEB BETWEEN BS X=54 TO 60 AND Y=555-559, Y=644-647. REASON FOR RE-WRITE: MISSING "OK TO INSTALL" OF SEAT TRACK FROM BS Y=522 TO 674 AND ALSO FRAME FITTING ON BS Y=541, MISSING INSTALL FASTENERS ON CUSP WEB REPAIR FROM STA Y=533 TO Y=560 X=54. FITTING STA Y= 541 WAS INSTALLED IAW SRM 51-30-1 AND 51-30-5. SEAT TRACK FROM BS Y=522 TO 674 WAS INTALLED IAW SRM 51-30-1 AND MISSING FASTENERS WILL BE INSTALLED WITH NR 78, ZONE 201.

Part: VANE — PUNCTURED (RT WING TE FLAP) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS A PUNCTURE ON LOWER SURFACE RT INBD FLAP INBD VANE. SURFACE RT INBD FLAP, INBD VANE WAS REPAIRED IAW SRM 57-03D, PAR II AND ACFT 2000-8149-06.

Part: FLOOR PANEL — DAMAGED (BS 1003-1361) · airframe 74,072 hrs · 57,043 cycles

FLOOR PANEL BS 1003 - 1361 IN PAX CABIN DAMAGED. REPAIRED IAW AMM 53-20-01-201, PAR 7.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS DELAMINATED FLOOR PANEL IN PASSENGER CABIN. FLOOR PANEL FABRICATED IAW AMM 53-20-01-201, PAR 7.

Part: SEAT TRACK — CORRODED (BS 378-528) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

HAS CORROSION ON RT SEAT TRACK BS X=-54 AND Y=378-384, Y=394-418, Y=422-424, Y=435-452, Y=462 -487, Y=491-520, Y=524-528. SEAT TRACK WAS REPLACED FROM STA Y=218 TO STA Y= 798 WITH SPLICING REPAIRS ON STA Y=474, ON STA Y=550, ON STA Y=627 AND STA Y=740 IAW SRM 53-05, FIG 4F. REPLACED 4 SECTION BS Y= 218 TO BS= 798.

Part: SKIN — DAMAGED (BS 515-549) · airframe 74,072 hrs · 57,043 cycles

SEVERAL LIGHTNING STRIKES, 6 EA, ON EXTERIOR FUSELAGE SKIN FROM BS Y=515 TO 549 BETWEEN LONGERONS 2 RT TO 6 RT ON LIGHTNING STRIKES, REMOVED AREA PAINTED/TREATED IAW SRM 51-10-3 PAR. 14, 15, 21, 4 EA BUT ON BS Y=537.500, 1EA. IT WAS REPAIRED WITH PLUG REPAIR IAW SRM 53-04-2, PAR 3C, 2, A, 1, A, FIG 1 AND ON BS Y= 539.125, 1EA. IT WAS REPAIRED BY BLENDED OUT WITH DIMENTIONS AS FOLLOW, UT WAS ACCOMPLISHED IAW NDT SPM 04-00-07, PAR 5, FIG 3.

Part: FLOOR SUPPORT — WORN (BS 1309-1342) · airframe 74,072 hrs · 57,043 cycles

WEAR FOUND ON FLOOR SUPPORT FROM BS 1309 TO 1342 AND X=17, LT SIDE AT PASSENGER CABIN. FLOOR SUPPORT WAS REMOVED AND AREAS WAS BLENDED OUT, FLOOR SUPPORT WAS MEASURE AND ITS OUT OF LIMITS, REPAIR PARTS WERE FABRICATED, TREATED AND PAINTED AND INSTALLED. FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-1, 53-01, FJJIG 1, 53-01, FIG 2, 51-10-3, PAR 21 AND 14 AND ER/A 511165-14 MA, REV-C.

Part: STIFFENER — CRACKED · airframe 74,072 hrs · 57,043 cycles

ACFT HAS CRACKED STIFFENER, 11 O`CLOCK POSITION, CRACKED CLIP, 8 O`CLOCK POSITION. SHEARED FASTENERS, 2 O`CLOCK POSITION AND MISSING FASTENER AT 7 O`CLOCK POSITION AT RT ENGINE NOSECOWL. FWD BULKHEAD AFT FACE. CRACKED STIFFENER 11 O`CLOCK, CRACKED CLIP 8 O`CLOCK AND FASTENERS SHEARED 2 O`CLOCK, MISSING FASTENER 7 O`CLOCK WERE REPLACED IAW ER/A 451282-14MA.

Part: SKIN — DAMAGED (BS 807-826) · airframe 74,072 hrs · 57,043 cycles

ACFT LIGHTNING STRIKE ON FUSELAGE SKIN BETWEEN LONGERON 1 AND LONGERON 2 RT BETWEEN BS 807 AND 826. LIGHTNING STRIKE WAS REPAIRED IAW SRM 53-04-2, PAR 3, FIG 2. SHEET 6.

Part: CUSP WEB — CORRODED (BS 1224-1241) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

DURING CORROSION REMOVAL PROCEDURE ON CUSP WEB FROM BS 1224, X58 AND BS 1231 TO BS 1241 X 50-X56 AREAS WERE FOUND OUT OF LIMITS IN REF CARD N109, ZONE 201. REASON FOR RE-WRITE: MISSING "OK TO INSTALL" OF SEAT TRACK, FITTING AND ALSO MISSING PERFORMED THE OTHER REPAIR ON CUSP WEB. CUSP WEB FROM BS Y=1231-1271 WAS REPAIRED IAW SRM 53-05 FIG 131-A, 51-10-3 PAR 14/21, 51-30-2 AND 51-30-5. FITTING AND SEAT TRACK WERE INSTALLED IAW SRM 51-30-1 AND 51-30-5.

Part: FLOOR PANEL — DELAMINATED (PAX CABIN) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS DELAMINATED PAX CABIN FLOOR PANEL. FLOOR PANEL FABRICATED IAW AMM 53-20-01-201.

Part: FLOOR SUPPORT — BROKEN (NOT REPORTED) · airframe 74,072 hrs · 57,043 cycles

BROKEN CHANNEL FOUND ON FLOOR PANEL NR 617A. CRACK DIMENTION 2.00" WAS STOP DRILL WITH 0.250" DIAMETER. REPAIR DOUBLER WAS FABRICATED, TREATED AND PAINTED IAW SRM 53-05 PAR 145 AND 51-10-3 PAR 14 AND 21. REPAIR PARTS WERE INSTALLED IAW SRM 51-30-2.

Part: CUSP WEB — CORRODED (BS 218-220) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION ON CUSP WEB BETWEEN X -50 AND X -60, BS 218-220. REPAIRED IAW SRM 53-05, 51-30-2, AND 51-10-3, PAR G14, 21, 26, 38, 51, 308.

Part: LONGERON — CORRODED (BS 1287-1309) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION FOUND ON LONGERON 28L BETWEEN BS 1287 - 1309. REPAIRED IAW SRM 51-30-2, 51-30-5, 53-02 FIG 18, 51-10-4, AND 51-10-3 PAR 14,21.

Part: CUSP WEB — CRACKED (BS 807) · airframe 74,072 hrs · 57,043 cycles

CRACKED CUSP WEB X=-55, BS 807. CUSP WEB WAS REPLACED IAW SRM 53-05, FIG 131A-24.

Part: STRUCTURE — CORRODED (BS 1401-1423) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION ON TEE BETWEEN BS 1401 - 1423 AT AFT ACCY COMPARTMENT LT CUT OUT VENTRAL STAIR. A/A, SM, ZONE 100, CARD 188. DUE TO EXESIVE CORROSION WILL BE REPLACE CAP ANGLE IAW SRM 51-10-2, 51-30-2 AND 51-30-5.

Part: STOP FITTING — CRACKED (R1 DOOR) · airframe 74,072 hrs · 57,043 cycles

CRACK FOUND ON INTERIOR FITTING OF DOOR STOP AT R1, DOOR NR 1 BEAM FWD EDGE, INTERNAL STRUCTURE. DAMAGE FITTING WAS REPLACED IAW SRM 51-30-5.

Part: BEAM — CRACKED (R1 DOOR) · airframe 74,072 hrs · 57,043 cycles

CRACK FOUND ON R1 DOOR BEAM 4 FWD EDGE. DAMAGE BEAM NR 4 WAS REPLACED IAW SRM 51-30-2 AND 51-30-5, DWG 9911582, REV. T.

Part: DOOR FRAME — CRACKED (R1 DOORWAY) · airframe 74,072 hrs · 57,043 cycles

A CRACK WAS FOUND ON CORNER RADIUS OF R1 DOOR UPPER FRAME BEAM, FWD AND AFT EDGES INTERNAL STRUCTURE. CRACK ON CORNER RADIUS OF R1 DOOR UPPER FRAME BEAM WAS REPLACED IAW 52-40-0, FIG 1, SHEET 1-2 AND DWG 9911579, REV. L.

Part: INTERCOSTAL — CRACKED (BS 978) · airframe 74,072 hrs · 57,043 cycles

CRACKED INTERCOSTAL ON KEEL BEAM, BS 978. INTERCOSTAL WAS REPAIRED IAW SRM 53-01, FIG 2, SHEET 3.

Part: STRUCTURE — CORRODED (HORIZONAL STAB) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION FOUND IN HORIZONTAL STAB BARREL NUTS BORES 19, 16 RT AT XH=27. BARREL NUT BORES WERE REPAIRED IAW ERA 537792-14, REV ORIGINAL AND ERA 537783-14, REV ORIGINAL.

Part: STIFFENER — CRACKED (BS 1339 BULKHEAD) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS A CRACKED STIFFENER BS 1339 BETWEEN PROYECTION LONGERONS 3-4L AT AFT BULKHEAD. STIFFENER WAS REPLACED IAW SRM 51-30-2, 51-30-5, 51-10-4, 51-10-3 PAR 21 AND 14 AND DWG 99155625, REV P.

Part: INTERCOSTAL — CRACKED (BS 1416) · airframe 74,072 hrs · 57,043 cycles

CRACKED INTERCOSTAL BS 1416 CANT BETWEEN LONGERONS 11 - 12 LTT. REMOVED AND REPLACED IAW SRM 51-30-2, 51-30-5, 53-01, 51-01, PAR 21, 53-01 FIG 2.

Part: SKIN — DAMAGED (LT ELEVATOR) · airframe 74,072 hrs · 57,043 cycles

ACFT DELAMINATED AREA CAUSED BY DENT ON LT ELEVATOR CONTROL TAB 17" FROM INBD EDGE, ALSO PUNCTURE ON ELEVATOR CONTROL TAB 28" FROM OTBD EDGE, BOTH AT LOWER SKIN. DENT ON LT ELEVATOR CONTROL TAB 17" FROM INBD EDGE, ALSO PUNCTURE ON ELEVATOR CONTROL TAB 28" FROM OTBD EDGE BOTH AT LOWER SKIN WERE REPAIRED IAW SRM 55-04, PAR 2A.

Part: CUSP WEB — CORRODED (BS 322-540) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION FOUND ON LT CUSP WEB BETWEEN X 54 TO X 60 AND BS 322 - 540. REPAIRED IAW SRM 53-05, FIG. 131A.

Part: FRAME — CRACKED (BS 1451) · airframe 74,072 hrs · 57,043 cycles

CRACKED FRAME ANGLE BS 1451 BETWEEN LONGERON 2 - 3L. REMOVED AND REPLACED IAW SRM 51-30-2 AND 51-30-5.

Part: VANE — WORN (LT WING TE FLAP) · airframe 74,072 hrs · 57,043 cycles

WEAR ON REPAIR DOUBLER OF LT OTBD FLAP INBD VANE. LT OTBD FLAP INBD VANE WAS REPAIRED IAW SRM 57-03D, PAR. II.

Part: SKIN — WORN (CARGO DOOR) · airframe 74,072 hrs · 57,043 cycles

WEAR FOUND ON EXTERNAL SKIN OF CARGO DOOR BARRIER. REPAIRED IAW ER/A 096425-14 MA, REV. "D".

Part: PAN — DENTED (EMERGENCY EXIT) · airframe 74,072 hrs · 57,043 cycles

A DENT WAS FOUND ON THE RT AFT OVERWING EMERGENCY DOOR PAN. REPAIRED IAW ERA 537798-14, REV ORIGINAL.

Part: CUSP WEB — CORRODED (BS 629-712) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

ACFT HAS CORROSION ON RT CUSP WEB BS 629 - 712. CUSP WEB WAS REPLACED IAW SRM 53-05, FIG 131A-24, SHEET 1.

Part: FRAME — CRACKED (BS 1437) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS A CRACKED FRAME WEB BS 1437, LONGERON 10R. FRAME WEB WAS REPAIRED IAW SRM 53-01, FIG. 2.

Part: PAN — DENTED (EMERGENCY EXIT) · airframe 74,072 hrs · 57,043 cycles

A DENT WAS FOUND ON THE RT FWD OVERWING EMERGENCY DOOR PAN. REPAIRED IAW ERA 537797-14, REV ORIGINAL.

Part: WEB — CRACKED (BS 1386) · airframe 74,072 hrs · 57,043 cycles

CRACKED WEB ON LT INTERNAL PYLON STRUCTURE BS 1386 AND X 68. THE WEB WAS REPAIRED IAW SRM 54-01, FIG 2.

Part: VANE — WORN (RT WING TE FLAP) · airframe 74,072 hrs · 57,043 cycles

THE RIGHT WING TE FLAP VANE HAS WEAR ON THE REPAIR DOUBLER. REPAIRED IAW SRM 57-03D, PAR II.

Part: DOOR — CRACKED (SLAT TRACK) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS CRACKED SLAT TRACK DOOR NR 13 AND NR 14 AT LT WING. SLAT TRACK DOOR NR 13 AND 14 WERE FABRICATED IAW ER/A 512356-14MA REV. ORIGINAL.

Part: LONGERON — CRACKED (BS 1437) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS A CRACK ON LONGERON 16R, BS 1437 AT AFT ACCESSORY COMPARTMENT. LONGERON WAS REPLACED IAW 53-14-4, 51-30-2, 51-30-5.

Part: FLOOR PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

ACFT HAS EXCESSIVE CORROSION ON FLOOR PANEL 160G. FLOOR PANEL 160G WAS REPLACED IAW SRM 51-10-2, 51-10-4, DWG 9957828, REV AB.

Part: BUSHING — CORRODED (MLG FITTING) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

ACFT HAS CORROSION ON RT MLG SUPPORT FITTING BUSHING BORE. DAMAGE ON BUSHING BORE WAS REPAIRED IAW DWG SR09570087, NOTE 11, REV. B.

Part: FITTING — CORRODED (LT MLG) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

ACFT HAS CORROSION ON LT MLG SUPPORT FITTING BUSHING BORE. DAMAGE ON BUSHING BORE WAS REPAIRED IAW DWG SR09570087, NOTE 11, REV. B.

Part: FLOOR PANEL — CORRODED (PAX CABIN) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

ACFT HAS CORRODED FERRULES ON PAX CABIN FLOOR PANEL. FABRICATED IAW AMM 53-20-01-201. REPLACED IAW AMM 53-20-01-201.

Part: PAN — CRACKED (R1 DOOR) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS CRACK ON PAN OF R1 DOOR LOCATION. LOWER HINGE AREA APPROXIMATELY. INTERNAL STRUCTURE. PERFORMED REPAIR ON PAN OF R1 DOOR LOCATION. LOWER HINGE INTERNAL STRUCTURE IAW SRM 51-30-2, SRM 51-10-2, SRM 52-03, D FIGURE 3, SRM 51-10-3 PAR 14 AND 21.

Part: SEAT TRACK — CORRODED (BS 199-227) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION FOUND ON SEAT TRACK X 22, BS 199 - 227. SECTION OF THE SEAT TRACK WAS REPLACED IAW SRM 53-05, FIG 4F.

Part: LONGERON — CRACKED (BS 200) · airframe 74,072 hrs · 57,043 cycles

CRACKED LONGERON 4L, BS 200 AT CABIN PAX. THE LONGERON WAS REPLACED IAW SRM 53-02, FIG 18, 51-30-2 AND 51-30-5.

Part: LONGERON — CRACKED (BS 1437) · airframe 74,072 hrs · 57,043 cycles

HAS CRACKED LONGERON 16L, BS 1437 AT AFT ACCESORY COMPARTMENT. LONGERON WAS REPLACED IAW SRM 53-14-4 AND 51-30-2, 51-30-5.

Part: CUSP WEB — DAMAGED (BS 1136-1155) · airframe 74,072 hrs · 57,043 cycles

ACFT DUE TO EXCESSIVE BLENDING, WORN OUT ON CUSP WEB, UNDER SEAT TRACK X=-54 BETWEEN BS 1136 - 1155. CUSP WEB WAS REPAIRED IAW SRM 53-05, 51-30-1, 51-30-2, 51-30-5, AND 51-10-3.

Part: CUSP WEB — CORRODED (BS 903-916) · airframe 74,072 hrs · 57,043 cycles

CRACK FOUND ON CUSP WEB BETWEEN BS 903 - 916, BETWEEN X -50 AND X -60. WEB WAS REMOVED. CRACK WAS STOPPED, REPAIR IN CUSP WEB WITH DOUBLER AND FILLER WERE FABRICATED, TREATED, PAINTED AND INSTALLED IAW SRM 51-30-5, 53-01 FIG 2, 53-05, FIG 131A, 51-10-3 FOR 14 AND 21 AND 51-30-2 LONGERON CRACK 2.500". REPAIR CUSP WEB BS=Y903 TO Y= 904 WILL BE ATTENDED NRCS 20000077571 AND CARD 291, ZONE 201 AND REPAIR WAS ACCOMPLISHED FROM STA Y=905 TO Y=916. BETWEEN X=-50 AND X=-60.

Part: ANGLE — CRACKED (EMERGENCY DOOR) · airframe 74,072 hrs · 57,043 cycles

CRACKED ANGLE ON INTERNAL STRUCTURE OF RT AFT OVERWING EMERGENCY DOOR NR 10 STOP FITTING. A NEW ANGLE WAS INSTALLED IAW DWG 9957735, REV G, SRM 51-10-2, 51-10-4, 51-10-2, PARA 14 & 21, 51-30-2 AND 51-30-5.

Part: FRAME — CRACKED (BS 1322) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS A CRACKED FRAME BS 1322 AND LONGERON 17L. DAMAGE WAS REMOVED, REPAIR PARTS WERE FABRICATED, TREATED, PAINTED AND INSTALLED IAW ER/A 493697-14MA, REV B.

Part: HINGE BRACKET — CRACKED (RT ELEVATOR) · airframe 74,072 hrs · 57,043 cycles

RT ELEVATOR NR 6 HINGE BRACKET CRACKED. REPLACED IAW DWG SR09550030 REV C.

Part: CUSP WEB — CORRODED (BS 826-845) · airframe 74,072 hrs · 57,043 cycles

CUSP WEB HAS A CRACK UNDER SEAT TRACK AT LBL 54 BETWEEN BS 826 & 845. A NEW CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-18, 51-30-5, 51-300-2, 53-01 FIG 2, 51-01, PAR 21, INS 1 AND 51-10-3, PAR 14/21.

Part: CUSP WEB — NOT REPORTED (BS 984-1003) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CUSP WEB HAS OUT OF LIMITS AREA BS 984 - 1003. DOUBLER WAS FABRICATED, TREATED AND PAINTED. REPAIR INSTALLED. CIC WAS APPLIED IAW SRM 51-10-3 PAR 14, 21 AND 38, 53-05, FIG 131A-1, SHEET 9, 51-30-2.

Part: SKIN — WORN (BS 1380) · airframe 74,072 hrs · 57,043 cycles

WEAR WAS FOUND ON A REPAIR DOUBLER BS 1380 BTW LONGERONS 4 - 5L. THE DOUBLER REPAIR WAS REMOVED AND A NEW REPAIR WAS FABRICATED, TREATED, PAINTED, AND INSTALLED IAW SRM 51-30-2, SRM 53-01 AND 51-10-3. PAR 21 & 14.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

ACCESS PANEL CORRODED. ACCESS PANEL REPLACED.

Part: ANGLE — CRACKED (BS 965) · airframe 74,072 hrs · 57,043 cycles

A CRACK WAS FOUND ON AN ANGLE AT RT SIDE WINDOW BELT AFT, UPPER BS 965. ANGLE WAS REPLACED IAW DWG 3920346, ITEM 501, REV ORG, SRM 51-30-2 AND 51-30-5.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

ACCESS PANEL CORRODED IN THE SETTLEMENT AND COUNTERSINK. ACCESS PANEL REPLACED.

Part: CUSP WEB — CORRODED (BS 503-522) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CUSP WEB HAS CORROSION ON REPAIR DOUBLER BS 503 - 522 BETWEEN X 54 TO X 60. REPAIR WAS REMOVED, FABRICATED, TREATED, PAINTED AND INSTALLED AND CIC WAS APPLIED IAW SRM 51-30-2, 53-05 FIG 131A, 51-10-3, PAR 21, 14 AND 38 AND 51-30-5.

Part: SUPPORT — CORRODED · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION WAS FOUND ON CEILING SUPPORTS BELOW FLOOR PANEL 1250C AT PAX CABIN FLOOR STRUCTURE. CORROSION WAS REMOVED, AREAS MEASURED WITHIN LIMITS WAS TREATED AND PAINTED, CIC WAS APPLIED IAW SRM 51-10-3, PAR 26, 21, 14, 38 AND ER/A 511165-14MA, REV B AND SUPPORT ON BS Y=1297 WAS REMOVED, NEW SUPPORT WAS FABRICATED, TREATED AND PAINTED, NEW SUPPORT WAS INSTALLED IAW SRM 51-30-2, 53-24-0, FIG 11, SHEET 2, 51-10-2, 51-10-3 PAR 21, 4.

Part: LONGERON — CORRODED (BS 503-522) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

ACFT HAS CORROSION ON ANGLE DOUBLER ON LONGERON 18R BETWEEN BS 503 AND 522. ANGLE WAS REMOVED IAW SRM 51-30-5, DUE TO EXCCESIVE CORROSION WILL BE REPLACED, NEW ANGLE WAS FABRICATED IAW SRM 53-14-2 AND BWG 9930538. NEW ANGLE WAS TREATED AND PAINTED IAW SRM 51-10-3 PAR 14 AND 21. REPAIR PARTS WAS INSTALLED IAW SRM 51-30-5.

Part: CUSP WEB — CORRODED (BS 256-261) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CUSP WEB FOUND CORRODED BETWEEN X 54 TO X 60, BS 256 - 261. REPAIRED IAW SRM 53-05, FIG 131A-10, SHEET 1 AND TREATED AND PAINTED IAW SRM 51-10-3 PAR 14 AND 21.

Part: CUSP WEB — CRACKED (BS 1231-1250) · airframe 74,072 hrs · 57,043 cycles

HAS A CRACK ON RT CUSP WEB BETWEEN BS 1231 AND 1250 X -54 AND X -60. CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-6, SHEET 1.

Part: CUSP WEB — CORRODED (BS 620-624) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CUSP WEB HAS CORROSION BS 620 - 624, X 54 - 60. CUSP WEB WAS REPAIRED IAW SRM 53-02, FIG 131A-13, 51-30-2 AND 51-10-3, PAR 14, 21 AND 38.

Part: LONGERON — CRACKED (BS 1380) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS A CRACK ON LONGERON 11L BS 1380 AT AFT ACCESORY COMPARTMENT. LONGERON 11L BETWEEN BS 1368 TO 1406 WAS REPAIRED IAW SRM 53-02, FIG 18.

Part: CUSP WEB — CRACKED (BS 886-905) · airframe 74,072 hrs · 57,043 cycles

DURING CUSP WEB INSPECTION FOUND A CRACK UNDER SEAT TRACK LBL 54 BETWEEN BS 886 AND 905. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A, 51-10-3, PARR 14 AND 21, 51-30-2 AND 51-10-3 PAR 38.

Part: BEAM — CORRODED (BS 1158-1210) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION FOUND ON BEAM FROM BS 1158 - 1210 AT AFT LOWER CARGO COMP DOOR JAMB. REPAIR SPACER AND NUT STRIPS WERE REPLACED IAW SRM 53-05, FIG 123.

Part: CUSP WEB — CORRODED (BS 606-613) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

ACFT HAS CORROSION ON REPAIR OF CUSP WEB X 54 - 60 BS 606-613. REPAIR WAS REMOVED AND A NEW REPAIR WAS FABRICATED TREAT AND PAINT AND INSTALLED IAW SRM 51-30-5, 53-05, FIG 131A-14, AND 51-10-3, PAR 14, 21, 26.

Part: BEARING — STUCK (AILERON) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS A STUCK BEARING ON AILERON CONTROL TAB SECTOR LINK AT LT WING T/E. STUCK BEARING ON LT AILERON CONTROL TAB SECTOR LINK WAS REPLACED IAW CMM 27-11-17.

Part: CUSP WEB — CORRODED (BS 889-908) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

FOUND CORROSION OUT LIMITS ON CUSP WEB, BS 889 - 908 BETWEEN RBL 54 - 60. REPAIRED IAW SRM 53-05, FIG 131A, 51-10-3, PAR 14 AND 21-38 AND 51-30-2.

Part: SKIN — WORN (CARGO DOOR) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS WEAR ON FWD/AFT CORNERS DOUBLERS OF OTBD SKIN OF C1 DOOR LOWER AREA. DOUBLERS WERE FABRICATED, TREATED, PAINTED, AND INSTALLED IAW ER/A 486624-14MA, REV ORIGINAL.

Part: DOUBLER — CRACKED (BS 977-995) · airframe 74,072 hrs · 57,043 cycles

FOUND A CRACKED PRODUCTION DOUBLER BETWEEN BS 995 - 977. REPLACED THE DOUBLER IAW AND 51-30-2, CMM 32-17-05.

Part: CUSP WEB — CORRODED (BS 882-889) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

FOUND CORRODED REPAIR DOUBLER ON CUSP WEB AT BS 882-889 X 53-57. THE DOUBLER WAS REMOVED, FABRICATED, TREATED AND PAINTED IAW SRM 53-05, FIG 131A-1, 51-10-3, PAR 21, 14 AND IAW SRM 51-30-2. THE DOUBLER WAS INSTALLED IAW SRM 51-30-2, 51-30-5.

Part: PIN — MISSING (L1 DOOR SLIDE) · airframe 74,072 hrs · 57,043 cycles

MAINTENANCE FOUND RELEASE PIN ON L1 SLIDE FOLDING FLAP COVER LEFT OUT. SLIDE WAS REPLACED.

Part: FLOOR PANEL — DAMAGED (CABIN) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

HAS CORROSION AND CRACKS FOUND ON RT FLOOR PANEL 120E, FOUND OUT OF LIMITS IAW ER/A 511165-14MA, REV LP2119851.

Part: STOP FITTING — CRACKED · airframe 74,072 hrs · 57,043 cycles

HAS CRACKED FWD STOP FITTING OF BEAM 3 ACTUATOR 1 DOOR. STOP FITTING WAS REPLACED IAW SRM 51-30-5, AND 51-10-4.

Part: SKIN — DAMAGED (BS 989) · airframe 74,072 hrs · 57,043 cycles

ACFT HAS A LIGHTNING STRIKE ON FWD, UPPER CORNER WINDOW BELT RT SIDE BS 989. LIGHTNING STRIKE WAS ATTENDED WITH SRM 53-05, FIG 111.

Part: CUSP WEB — CRACKED (BS 1228) · airframe 74,072 hrs · 57,043 cycles

A CRACK WAS FOUND ON CUSP WEB AT BS 1228, LBL 49. A REPAIR WAS FABRICATED IAW SRM 53-05, FIG 131A-13 AND INSTALLED IAW SRM 53-05, FIG 131A-13.

Part: PAN — CRACKED (BS 237) · airframe 74,072 hrs · 57,043 cycles

CRACKED AFT UPPER CORNER OF WINDOW RING PAN BS 237. REPAIRED IAW SRM 53-05, FIG 122, ER/A 493648-14MA, REV A, ER/A 487747-14MA, REV A.

Part: PAN — CRACKED (BS 845) · airframe 74,072 hrs · 57,043 cycles

CRACKED FWD UPPER CORNER OF WINDOW PAN, BS 845. REPAIRED IAW SRM 53-05, FIG 122; ER/A 493648-14MA, REV A, AND ER/A 487747-14MA, REV A.

Part: STOP FITTING — CRACKED (CARGO DOOR) · airframe 74,072 hrs · 57,043 cycles

CRACKED STOP FITTING ON UPPER FWD AREA OF CARGO DOOR. THE STOP FITTING WAS REPLACED IAW SRM 51-30-5 AND 51-30-1.

Part: ACCESS PANEL — DAMAGED (NOT REPORTED) · airframe 74,072 hrs · 57,043 cycles

AIRCRAFT HAS INADEQUATE DRILL HOLES AND SCRATCHES ON FUEL ACCESS PLATE 2301C. ACCESS PLATE 2301C WAS REPLACED IAW TABLE 1, SRM 51-22-2A.

Part: SEAT TRACK — CORRODED (BS 728-729) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

HAS CORROSION ON REPAIR PLUG PM SEAT TRACK X-22 AND BS 728 - 729. PLUG WAS REMOVED AND REPLACED IAW SRM 51-30-1, 53-05 FIG 4B-1, 51-10-3, PAR 14, 21 AND 38.

Part: SEAT TRACK — CORRODED (BS 427-429) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION FOUND ON LEFT SEAT TRACK PLUG BS 427 - 429. THE PLUG WAS REMOVED AND REPLACED IAW SRM 51-30-1, 53-05, FIG 1A, 51-10-3 PAR 14 AND 21, 38.

Part: SEAT TRACK — CORRODED (BS 858-862) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION FOUND ON REPAIR PLUG ON SEAT TRACK LBL 22 FROM BS 858-862. THE REPAIR WAS REMOVED AND REPLACED IAW SRM 51-30-1, 53-05, FIG 4A, AND51-10-3, PAR 14, 21 - 38.

Part: CUSP WEB — CORRODED (BS 1060-1066) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION FOUND ON CUSP WEB BETWEEN BS 1060 - 1066 AND X-44 TO X-60. DAMAGE WAS REMOVED, REPAIR FABRICATED AND TREATED AND PAINTED, AND INSTALLED IAW SRM 51-30-1, 53-05 FIG 131A-7, 51-10-3 PAR 14, 21, 38, AND 51-30-5.

Part: SEAT TRACK — CORRODED (BS 486-489) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION WAS FOUND ON THE SEAT TRACK REPAIR PLUG LBL 54, BS 486 - 489 . THE REPAIR WAS REMOVED AND REPLACED IAW SRM 51-30-1, 53-05, FIG 1A, 51-10-3, PAR 14 AND 21.

Part: SEAT TRACK — CORRODED (BS 454-457) · corrosion level 2 · airframe 74,072 hrs · 57,043 cycles

CORROSION WAS FOUND ON THE SEAT TRACK REPAIR PLUG LBL 54, BS 454 - 457 . THE REPAIR WAS REMOVED, ADJUSTED, TREATED, PAINTED AND INSTALLED IAW SRM 51-30-1, 53-05, FIG 1A, AND 51-10-3 PAR 21 - 14.

Part: CUSP WEB — PUNCTURED (BS 788-807) · airframe 74,072 hrs · 57,043 cycles

PERFORATION ON THE RT CUSP WEB BS 788 - 807. DAMAGE WAS REMOVED, DOUBLER WAS FABRICATED, TREATED, PAINTED AND INSTALLED IAW SRM 53-01, FIG 4, 51-10-3 PAR 14 AND 21 AND 51-30-2.

Part: LONGERON — CRACKED (BS 1338) · airframe 74,072 hrs · 57,043 cycles

CRACKED LONGERON 13L, BS 1338, LONGERON REPLACED IAW SRM 53-14-3, 51-30-5 AND 51-10-3 PAR. 21 AND 14.

Part: CUSP WEB — PUNCTURED (BS 1199) · airframe 74,072 hrs · 57,043 cycles

PUNCTURED CUSP WEB BS 1199 LBL 52. REPAIRED IAW SRM 53-05, FIG 134A-17.

Part: SKIN — CRACKED (FUSELAGE) · airframe 74,072 hrs · 57,043 cycles

INSPECTION OF LOWER SKIN FOUND CRACKED AT S17. REPAIRED IAW SECTION I OF ER/A 536836-14 .

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 72,192 hrs · 55,766 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY EXIT SIGNS AT BOTH OF THE OVERWING HATCHES WERE INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES IN THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: DOOR — OBSTRUCTED · airframe 71,292 hrs · 55,099 cycles

THE AFT EXIT PATH WAS BLOCKED DUE TO THE DOOR BEING JAMMED BY THE AFT F/A SEAT HARNESS BUCKLES. MAINTENANCE SECURED THE HARNESS REEL CORRECTLY. OPS THEN CHECKED NORMALLY AND THE DOOR WAS ABLE TO BE OPERATED.

Part: WIRE — PULLED (EMERGENCY LIGHT) · airframe 70,959 hrs · 54,847 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING AT SEAT 27DE IN THE CABIN WAS INOPERATIVE. MAINTENANCE FOUND WIRES PULLED OUT OF THE CONNECTOR. THE LIGHT ASSEMBLY WAS REPLACED AND THE SYSTEM RETURNED TO NORMAL OPERATION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 70,737 hrs · 54,693 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE OVERHEAD EMERGENCY LIGHTING IN THE COCKPIT WAS INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES. OPS CHECKED GOOD.

Part: HANDLE — OUT OF POSITION (TAILCONE) · airframe 69,832 hrs · 54,130 cycles

DURING MAINTENANCE WALK-AROUND, NOTED THE TAIL CONE EXTERIOR JETTISON HANDLE WAS NOT FLUSH. FOUND INTERIOR HANDLE CLIP NOT SEATED ON HANDLE. REPOSITIONED CLIPS ON INTERIOR HANDLE, NO RIG OR CABLES AFFECTED. EXTERIOR HANDLE WITHIN LIMITS REF AMM 53-53.

Part: SLEEVE — MISSING (TAILCONE CABLE) · airframe 69,286 hrs · 53,764 cycles

MX FOUND THE TAILCONE RELEASE CABLE SLEEVE WAS MISSING AND THE CABLE WAS OUT OF ALLOWABLE RIG LIMITS. THIS DISCREPANCY WAS LOCATED NEAR THE AFT ACCESSORY COMPARTMENT ON THE LEFT SIDE AT STA 1480 TO AFT ENTRY DOOR. THE CABLE WAS REPLACED, ADJUSTED, AND RIGGED BACK INTO SPECIFICATIONS. THE RII STEPS WERE COMPLETED AND THE FOLLOW-UP CHECK WAS SUCCESSFUL.

Part: FRAME — CRACKED (BS 1497) · airframe 69,286 hrs · 53,764 cycles

CRACKED FRAME BS 1497 OTBD OF INTERIOR TAILCONE RELEASE HANDLE. COMPLIED WITH PRI 591345-14, REV 0, ER/A 591345-14, REV ORIG.

Part: SKIN — DAMAGED (BS 838-850) · airframe 69,286 hrs · 53,764 cycles

FUSELAGE CROWN DAMAGED. DOUBLER INSTALLED IN INSPECTED AREA BS 838-850 BETWEEN L1-2R & L2-L3R.

Part: SKIN — DAMAGED (BS 915-927) · airframe 69,286 hrs · 53,764 cycles

FUSELAGE CROWN DAMAGED. DOUBLER INSTALLED IN INSPECTED AREA BS 927-915 L2-3R.

Part: DOOR — NOT REPORTED (CARGO) · airframe 69,278 hrs · 53,760 cycles

CARGO DOOR REPAIRED IAW AA 5230-01159.

Part: RELEASE MECH — CRACKED (TAILCONE) · airframe 69,278 hrs · 53,760 cycles

MX DISCOVERED THAT THE TAILCONE RELEASE TRIGGER ASSY IN THE AFT CABIN WAS CRACKED. THE ASSY WAS REPLACED.

Part: SKIN — CRACKED (BS 1437) · airframe 69,278 hrs · 53,760 cycles

FUSELAGE CROWN SKIN IS CRACKED AT FASTENER JUST ABOVE PREVIOUS REPAIR BS 1437. REPAIRED IAW PRI 519308-14, REV 2.

Part: DUCT — CRACKED (RAM AIR) · airframe 69,278 hrs · 53,760 cycles

CRACKED RAM AIR DUCT LT SIDE BS 1429. WELDED IAW ER/A 382101-14MA.

Part: DUCT — CRACKED (RAM AIR) · airframe 69,278 hrs · 53,760 cycles

RAM AIR DUCT CRACKED ON LT SIDE BS 1437. WELDED CRACK IAW ER/A 382101-14MA, 030469, VERIFIED WELD WITH FPI IAW MOD NDT SPM 900-6-3.

Part: CAM — WORN (TAILCONE RELEASE) · airframe 69,278 hrs · 53,760 cycles

MX DISCOVERED THAT THE TAILCONE RELEASE MECHANISM CAM BASE WAS WORN OUT OF ALLOWABLE LIMITS. CAM BASE WAS REPLACED AND THE SYS WAS RIGGED TO SPECIFICATIONS.

Part: TEE FITTING — CORRODED (BULKHEAD) · corrosion level 2 · airframe 69,278 hrs · 53,760 cycles

AFT PRESSURE BULKHEAD TEE ANGLE CORRODED ON LOWER FWD FLANGE, LEFT OF LONGERON 30. REMOVED CORRODED FRAME DOUBLER, DAMAGE CONTAINED. CORROSION CONTAINED IN AREA WITH REMOVAL OF FRAME DOUBLER. REAMED ALL FASTENER HOLES COMMON TO DOUBLER, TO JACK FITTING, AND TO DIVERTER. INSTALLED DOUBLER, WEB, CENTER POST, AND ALL RELATED PARTS.

Part: STRAP — MISROUTED (ESCAPE SLIDE) · airframe 69,278 hrs · 53,760 cycles

INSPECTION DISCOVERED THAT THE EMERGENCY ESCAPE SLIDE IN THE TAILCONE WAS NO LONGER IN AN ACCEPTABLE CONFIGURATION. THE SLIDE PULL STRAP WAS NOT PROPERLY ROUTED OR RIGGED. A MISRIGGED OR ILL-ARRANGED SLIDE ASSY WOULD PREVENT PROPER DEPLOYMENT OF THE ESCAPE SYS AND IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. THE TAILCONE SLIDE PULL STRAP WAS REROUTED PROPERLY AND AN RII WAS COMPLETED SATISFACTORILY.

Part: COVER — DAMAGED (TAILCONE SLIDE) · airframe 69,278 hrs · 53,760 cycles

INSPECTION DISCOVERED THAT THE EMERGENCY ESCAPE SLIDE IN THE TAILCONE HAD A COVER THAT WAS MISSING CRITICAL MATERIALS AND WAS NO LONGER IN AN ACCEPTABLE CONFIGURATION. THE ABSENCE OF THIS VELCRO ASSY COULD PREVENT PROPER DEPLOYMENT OF THE ESCAPE SYS AND IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. THE TAILCONE SLIDE COVER WAS REPLACED AND AN RII WAS COMPLETED SATISFACTORILY.

Part: COVER — DETERIORATED (TAILCONE SLIDE) · airframe 69,278 hrs · 53,760 cycles

INSPECTION DISCOVERED THAT THE EMERGENCY ESCAPE SLIDE COVER IN THE TAILCONE HAD CRITICAL MATERIALS IN A DETERIORATED CONDITION. TAILCONE SLIDE COVER WAS REPLACED.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 69,257 hrs · 53,744 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY ESCAPE LIGHT ABOVE AFT OVERWING EXIT WAS INOPERATIVE. MX REPLACED BATTERIES. OPS CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 68,132 hrs · 52,904 cycles

DURING LINE CHECK, MX FOUND THAT THE OVERWING EMERGENCY EXIT SIGNS AT THE AFT HATCH WERE INOPERATIVE. MX REPLACED THE BATTERIES. OPS CHECK WAS GOOD.

Part: BATTERY PACK — FAILED (EMERGENCY LIGHT) · airframe 68,011 hrs · 52,827 cycles

DURING LINE CHECK, MX FOUND THAT THE EMERGENCY PATHWAY LIGHTING IN THE AFT SECTION OF THE CABIN HAD FAILED. MX REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 67,189 hrs · 52,280 cycles

DURING LINE CHECK, MX FOUND THAT THE OVERHEAD EMERGENCY PATHWAY LIGHTING IN THE FIRST CLASS SECTION OF THE CABIN WERE INOPERATIVE. MX REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPS CONDITION.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 67,189 hrs · 52,280 cycles

DURING LINE CHECK, MX FOUND THAT THE OVERHEAD EMERGENCY PATHWAY LIGHTING AT SEAT ROWS 27-30 WAS INOPERATIVE. MX REPLACED THE BATTERY PACK AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: BATTERY — LOOSE (EMERGENCY LIGHTS) · airframe 66,261 hrs · 51,601 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT BOTH OF THE FORWARD OVERWING EMERGENCY EXIT SIGNS INOPERATIVE. MAINTENANCE FOUND THAT THE BATTERY WAS LOOSE IN ITS CRADLE. THE BATTERY WAS RE-SECURED AND THE LIGHTS RETURNED TO AN OPERATIONAL CONDITION.

Part: FRAME — CORRODED (FUSELAGE) · airframe 65,725 hrs · 51,223 cycles

AFTER REMOVAL L22 STA 1307 AND STA 1322 WAS FOUND CORROSION ON FRAMES ATTACHED TO L22. REMOVED CORROSION, FOUND FRAMES OUT OF LIMITS. REMOVED DAMAGE, FABRICATED REPAIR AND INSTALLED IAW DC9/MD80 SRM 53-03. DURING PSV AT ST AEROSPACE SAN ANTONIO.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 65,725 hrs · 51,223 cycles

AFT FUSELAGE AFTER REMOVED SKIN ASSY FOUND CORROSION IN THE INTERNAL DOUBLER STA 1202 TO STA 1338 BETWEEN LONGERON 18L TO 23L. REMOVED DOUBLER, FOUND TO BE OUT OF LIMITS, FABRICATION AND INSTALLATION ACCOMPLISHED ON NRC 88 IAW DC9/MD80 SRM 51-10-3. DURING HMV.

Part: PLATE — CORRODED (FUSELAGE) · airframe 65,725 hrs · 51,223 cycles

AFT FUSELAGE - AFTER REMOVED SKIN ASSY FOUND CORROSION IN THE PLATE OF THE OUT FLOW VALVE STA 1287 TO 1307 BETWEEN LONGERON 20L TO 23L / VENT SUPPORT PLATE OUT OF LIMITS. REMOVED PLATE, COMPLETED STEPS 3 THROUGH 6 ON ERA 501667-14 REV A FOR FABRICATION, ACCOMPLISHED ERA 501667-14 REV A, DURING PSV.

Part: LONGERON — CORRODED (BS 1309-1322) · airframe 65,725 hrs · 51,223 cycles

AFT FUSELAGE AFTER SKIN FOUND CORROSION IN THE LONGERON 19L STA 1309 TO 1322. REMOVED CORROSION ON L19L STA 1309 TO STA 1322 AFT FUSE IAW DC9/MD80 SRM 53-01 FIG 1 SH 2 PG 8. FOUND OUT OF LIMITS IAW SRM 53-14-3 FIG 4 SH 2 PG 30-31 ITEM 21 AND SRM 51-10-1 FIG 15 PG 69. REMOVED L19L STA 1212 TO 1388 IAW SRM 51-30-05 PG 1. INSTALLED L19L FROM STA 1202 TO 1338 IAW SRM 51-30-05 PG 12.

Part: LONGERON — CORRODED (BS 1211-1328) · airframe 65,725 hrs · 51,223 cycles

AFT FUSELAGE CORROSION IN THE LONGERON 25L STA 1211, STA 1231 STA 1325-1328 AS 603. CORROSION OUT OF LIMITS 25L SAT 1211 AND 1231 PER SRM 53-01 FIG 1 SHEET 3. INSTALLED NEW LONGERON 25L AT STA 1202-1294.5 PER SRM 51-30-05 PG 20.

Part: LONGERON — CORRODED (BS 1202-1281) · airframe 65,725 hrs · 51,223 cycles

AFT FUSELAGE FOUND CORROSION IN THE LONGERON 24L STA 1231 - 1250. CORROSION OUT OF LIMITS. FABRICATED AND INSTALLED NEW LONGERON 24L BS 1202-1281 IAW SRM 51-10-4 PG 1,51-30-5 PG 12 AND DWG 5936021.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 65,725 hrs · 51,223 cycles

FOUND CORROSION IN LONGERON AT AFT FUSELAGE. REMOVED CORROSION AT L23L STA 1287, 1211, 1271 IAW SRM MD-88 53-01 FIG 1 SH 3 PG 8. FOUND OUT OF LIMITS IAW MD-88 SRM 53-14-3 FIG 4 SH 2 PG 30-31. INSTALLED NEW LONGERON AT L23L FROM STA 1202 TO 1338 IAW MD-88 SRM 51-30-5 PG 1. AT SAA/SAT DURING HMV. (REPAIR ACCOMPLISHED ON 04APR12. NOT REPORTED UNTIL 17APR)

Part: LONGERON — CORRODED (BS 1211-1309) · airframe 65,725 hrs · 51,223 cycles

AFT FUSELAGE FOUND CORROSION IN LONGERON 22L BS 1211-1309. FOUND OUT OF LIMITS. FABRICATED AND REPLACED LONGERON 22L STA 1202-1338 IAW 51-10-01 FIG 15 PG 69 AND DWG 5936021 AND 51-30-05 PG 12.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 65,725 hrs · 51,223 cycles

AFT FUSELAGE AFTER REMOVING SKIN, FOUND CORROSION IN THE LONGERON 23L STA 1211 STA 1271 STA 1287. REMOVED CORROSION ON LONGERON, FOUND TO BE OUT OF LIMITS, REMOVED, FABRICATED AND INSTALLED NEW SECTION OF LONGERON AND SPLICES IAW DC9/MD80 SRM 51-30-5 DURING HMV.

Part: SEAT TRACK — CORRODED (BS 1112 LBL 22) · airframe 65,725 hrs · 51,223 cycles

BS 1112 LBL 22 SEAT TRACK HAS CORROSION. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS. REMOVED AND REPLACED SEAT TRACK FROM STA 1088 TO 1202 IAW SRM 53-05.

Part: FLOORBEAM — CORRODED (BS 200 LBL 2-4) · airframe 65,725 hrs · 51,223 cycles

MAIN ENTRY AREA, BS 200 LBL 2 AND LBL 4 FLOORBEAM CORRODED. REMOVED, FABRICATED AND INSTALLED NEW FLOORBEAM IAW SRM 51-30-5.

Part: FLOOR PANEL — CORRODED (AFT CARGO BAY) · airframe 65,725 hrs · 51,223 cycles

AFT CARGO COMPARTMENT FLOOR PANEL CORRODED. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS. FABRICATED NEW FLOOR PANEL IAW AMM 25-52-01.

Part: FLOOR PANEL — CRACKED (AFT CARGO BAY) · airframe 65,725 hrs · 51,223 cycles

AFT CARGO COMPARTMENT FLOOR PANEL CRACKED, FOUND ADDITIONAL FOUR CRACKS AND CORROSION DURING EVALUATION, OUT OF LIMITS. FABRICATED NEW FLOOR PANEL IAW AMM 25-52-01.

Part: SEAT TRACK — CORRODED (STA 1211-1251) · airframe 65,725 hrs · 51,223 cycles

LBL 22 SEAT TRACK CORRODED BS 1211, 1231 TO 1233 BS 1250 TO 1251. REMOVED CORROSION FROM SEAT TRACK, FOUND TO BE OUT OF LIMITS. REMOVED AND REPLACED SEAT TRACK IAW SRM 53-05.

Part: SKIN — CORRODED (BS 229 L23R) · airframe 65,725 hrs · 51,223 cycles

TWO RIVETS DAMAGE, LOCATED ON FUSELAGE EXTERIOR SKIN BS 229 LONGERON 23 RIGHT. REMOVED RIVETS, FOUND CORROSION ON SPLICE AND LONGERON, CORROSION FOUND TO BE OUT OF LIMITS, REMOVED DAMAGED SECTION AND SPLICE, FABRICATED AND INSTALLED NEW LONGERON AND SPLICE IAW SRM, 51-10-3.

Part: THRESHOLD — CORRODED (BS 636-693) · airframe 65,725 hrs · 51,223 cycles

CORROSION ON THRESHOLD MID CARGO COMPARTMENT AT STA 636-693 BETWEEN LONGERON 28R AND 29R. CORROSION OUT OF LIMITS PER SRM 53-01 PG 8 FIG 1 SHEET 3. FABRICATED AND INSTALLED REPAIR IAW SRM 51-30-05 PG 3.

Part: LONGERON — CORRODED (BS 1287-1295) · airframe 65,725 hrs · 51,223 cycles

HEAD RIVET MISSING ON FUSELAGE SKIN AT STA 1287 27R. ONCE REMOVED FOUND CORROSION ON LONGERON 27R AT 1287-1295. OUT OF LIMITS. FABRICATED AND INSTALLED NEW LONGERON AT STA 1279-1338 PER SRM 51-10-04 PG 1. INSTALLED SPLICE STA 1271-1287 IAW SRM 53-02 PG 53 FIG 16. INSTALLED LONGERON 27R STA 1279-1338 IAW SRM 51-30-02 PG 24 AND 51-30-05. INSTALLED SPLICE 27R STA 1271-1287 IAW SRM 53-02 PG 53 FIG 18 AND 51-30-5. INSTALLED ID TAG ON REPAIR IAW PS 900-5-1 NR 4 PG 3.

Part: WEB — CORRODED (FUSELAGE) · airframe 65,725 hrs · 51,223 cycles

CORROSION AROUND OF AFT LAVATORY SERVICE DOOR BETWEEN STA 1309 AND STA1322 LONGERON 19-22L. REMOVED CORROSION FROM AREA SEVERAL AREAS OUT OF LIMITS. ACCOMPLISHED ERA 501668-14 REV ORIGINAL DURING PSV.

Part: LUG — NOT REPORTED (HORIZONTAL STAB) · airframe 65,719 hrs · 51,219 cycles

HORIZONTAL STABILIZER HINGE RIB PIVOT BEARING LUG REPAIRED IAW AA 5500-01011.

Part: SKIN — NOT REPORTED (HORIZONTAL STAB) · airframe 65,719 hrs · 51,219 cycles

HORIZONTAL STABILIZER UPPER CENTER SKIN PANEL REPAIRED IAW AA 5510-01086.

Part: SPAR — CRACKED (WING) · airframe 64,903 hrs · 50,668 cycles

WING REAR SPAR CRACKING AT XRS 164. REPAIRED IAW AA 5710-01110.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 64,028 hrs · 50,080 cycles

DURING LINE CHECK MAINTENANCE FOUND EMERGENCY LIGHTS BATTERY PACK B5-27 INOPERATIVE. MAINTENANCE REPLACED BATTERY PACK B5-27. BATTERY AND LIGHTS NOW CHECK OK.

Part: HEATER — NOT REPORTED (STATIC PORT) · airframe 63,781 hrs · 49,916 cycles

STATIC PORT HEATER REPAIRED IAW EA 09-465286-03.

Part: HEATER — NOT REPORTED (STATIC PORT) · airframe 63,781 hrs · 49,916 cycles

STATIC PORT HEATER REPAIRED IAW AA 3030-01027.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 63,456 hrs · 49,695 cycles

DURING LINE CHECK, MX FOUND THE COCKPIT OVERHEAD EMERGENCY LIGHT INOPERATIVE. MX R & R POWER SUPPLY AND BATTERIES. OPERATION CHECKS GOOD. ACFT OK FOR SERVICE.

Part: SPAR — CRACKED (VERTICAL STAB) · airframe 62,158 hrs · 48,843 cycles

VERT STAB FRONT SPAR CHORD BHEC REVEALED CRACK INDICATION AT RT SIDE VERT STAB FRONT SPAR CHORD FORWARD FLANGE AT FIRST FASTENER HOLE BELOW ZFS 52. REPAIRED PER ERA 486620-14 REV ORIG ON N/R 103. (DLM88102844)

Part: FUSE — BLOWN (CABIN) · airframe 61,858 hrs · 48,652 cycles

MX FOUND THE EMERGENCY TRACK LIGHTING AT ROWS 24-30 TO BE INOPERATIVE. MX REPLACED THE FUSES ON THE BATTERY PACK. ALL LIGHTS WERE THEN GOOD EXCEPT 27DE WHICH WAS FORWARDED TO MCO. MX FOUND BLOWN FUSES ON THE AFT BATTERY PACK AND REPLACED THE FUSES. AN OPS CHECK WAS PERFORMED AND THE ACFT WAS RETURNED TO SERVICE.

Part: TRANSMITTER — MALFUNCTIONED (OIL PRESSURE) · airframe 59,677 hrs · 47,218 cycles

LT ENG OIL PRESS PEAKED HIGH AT CRUISE TO 70 PSI, THROTTLES MOVED BACK TO IDLE AND PRESSURE DOWN TO 45 PSI. OIL PRESS FOLLOWING THROTTLES, ALL OTHER INDICATIONS NORMAL. REMOVED AND REPLACED NR 1 ENG OIL PRESS RELIEF VALVE AND OIL PRESSURE TXMTR PER AMM. ALSO PERFORMED TEST C PER AMM, NO LEAKS NOTED. OK FOR SERVICE.

Part: STRUCTURE — UNKNOWN (CABIN) · airframe 59,572 hrs · 47,127 cycles

REMOVED AND INSTALLED AFT ACCESSORY EMERGENCY ESCAPE SLIDE PLATFORM TO FACILITATE INSPECTION ON THAT AREA. REMOVED AND INSTALLED PLATFORM IAW AMM 20-30-01-201.

Part: SPAR CAP — DAMAGED (HORIZ STAB) · airframe 59,572 hrs · 47,127 cycles

DURING HMV WHILE PERFORMING REPAIR ON RT HORZ STAB UPPER SPAR CAP A DRILLED HOLE WAS FOUND OUT OF LIMITS ED PER SR09550027 DWG. ERA 461318-14AD WAS ISSUED FOR ED OF DRILLED HOLE.

Part: FRAME — CRACKED (FUSELAGE) · airframe 59,572 hrs · 47,127 cycles

DURING HMV A CRACK WAS FOUND ON FRAME 1510 BELOW PLATE ON LEFT LOWER TAIL CONE LATCH PLATE. FRAME WAS REPAIRED IAW SRM 51-70-5 FIG 1.

Part: SPAR CAP — CRACKED (HORIZ STAB) · airframe 59,572 hrs · 47,127 cycles

C/W VA 71043 AD HORZ STAB REAR SPAR UPPER CAP REF EA 09-460214-12AD ME 16. C/W VA 71043AD.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 59,572 hrs · 47,127 cycles

DURING HMV EXCESSIVE CORROSION WAS FOUND ON LONGERON 24 LT BETWEEN STA Y=1287-1309. LONGERON WAS REPLACED IAW SRM 53-02 FIG 18.

Part: SKIN — CRACKED (FUSELAGE) · airframe 59,572 hrs · 47,127 cycles

DURING HMV A CRACK WAS FOUND ON AFT FUSELAGE SKIN STA Y=1437 BETWEEN LONGERON 3 RT AND 4 RT. CRACK WAS REPAIRED IAW SRM 53-04D0 FIG 27.

Part: BEAM — CRACKED (R1 DOOR) · airframe 59,572 hrs · 47,127 cycles

DURING HMV A CRACK WAS FOUND ON NR 1 BEAM AFT EDGE AT R1 DOOR STRUCTURE. BEAM WAS REPLACED IAW SRM 51-30-2 AND 51-30-5.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 59,572 hrs · 47,127 cycles

DURING HMV CORROSION WAS FOUND ON LOWER C1 DOOR JAMB FROM STA Y=370-427. DOOR JAMB WAS REPLACED IAW SRM 53-05D FIG 804D.

Part: SKIN — CRACKED (FUSELAGE) · airframe 59,572 hrs · 47,127 cycles

DURING HMV THREE CRACKS WAS FOUND ON FUSELAGE SKIN OF .500 INCH, .340 INCH AND .200 INCH OF FWD UPPER CORNER AT FWD SERVICE DOOR JAMB. AREA WAS REPAIRED IAW SRM 53-05 FIG 112.

Part: ANGLE — MISSING (R1 DOOR) · airframe 59,572 hrs · 47,127 cycles

RE-WRITE CRACKED BEAM 4 FWD SECTION ON R1 DOOR REASON FOR RE-WRITE MISSING -15 ANGLE ON R1 DOOR REPAIR IN ACCORDANCE WITH SRM 52-05 FIG 25. INSTALLED ANGLE IAW SRM 52-05D FIG 25.

Part: FITTING — CORRODED (LT MLG) · airframe 59,572 hrs · 47,127 cycles

DURING HMV PITTING CORROSION WAS FOUND ON LT MLG FITTING BUSHING BORE. BORE WAS REPAIRED IAW EA 09-093855-03AD.

Part: BEAM — CRACKED (R1 DOOR) · airframe 59,572 hrs · 47,127 cycles

DURING HMV A CRACK WAS FOUND IN NUMBER 4 BEAM FWD SECTION AND CLIP AFT SECTION SAME BEAM ON R1 DOOR. BEAM AND CLIP WAS REPAIRED IAW SRM 52-05D FIG 25.

Part: BELT — DAMAGED (FUSELAGE) · airframe 59,572 hrs · 47,127 cycles

DURING HMV LIGHTNING STRIKE WAS FOUND ON AFT LWR FRAME WINDOW NR 45 BETWEEN STA Y=636 AND 655 LT. WINDOW BELT WAS REPAIRED IAW SRM 53-05 FIG 111 AND ERA 471664-14 REV A.

Part: SKIN — CRACKED (FUSELAGE) · airframe 59,572 hrs · 47,127 cycles

DUE SRM 53-04D FIG 12B PERMANENT REPAIR OF CRACK FUSELAGE SKIN AT STA Y=1435 12 INCHES BELOW LT LWR ATTACH ANGLE VERT STAB. REPAIR CRACK IAW SRM 53-04D FIG 12B.

Part: HINGE FITTING — CORRODED (HORIZ STAB) · airframe 59,572 hrs · 47,127 cycles

DURING HMV FRETTING CORROSION WAS FOUND ON INNER SURFACE OF RIGHT OUTBOARD BUSHING OF RIGHT HORZ STAB ATTACHMENT. RIGHT HORZ STAB ATTACHMENT REPAIRED IAW SRM 55-02 PARA 24.

Part: SUPPORT — DAMAGED (RT MLG) · airframe 59,572 hrs · 47,127 cycles

DURING HMV PER EA 09-093855-03 OVERSIZED BUSHING ON RH MLG SUPPORT BUSHING BORE. NEW OVERSIZED BUSHING INSTALLED IAW EA 09-093855AD

Part: SKIN — CRACKED (FUSELAGE) · airframe 59,572 hrs · 47,127 cycles

DUE SRM 53-04D FIG 12B SHEET 51 PERMANENT REPAIR FOR CRACK FUSELAGE SKIN AT STA Y=1435 12 INCHES BELOW LT LOWER ATTACH ANGLE VERTICAL STAB. PERMANENT REPAIR C/W IAW SRM 53-04D FIG 12B.

Part: BEAM — CORRODED (FUSELAGE) · airframe 59,572 hrs · 47,127 cycles

DURING HMV EXFOLIATION CORROSION WAS FOUND ON DOOR JAMB LOWER BEAM STA 636 TO 693 AT C2. BEAM WAS REPAIRED IAW SRM 53-05 FIG 123.

Part: WINDOW FRAME — DAMAGED (FUSELAGE) · airframe 59,572 hrs · 47,127 cycles

DURING HMV LIGHTNING STRIKE WAS FOUND ON FWD LWR FRAME WINDOW NR 43 BTW STA Y=617 AND 636.

Part: BELT — DAMAGED (FUSELAGE) · airframe 59,572 hrs · 47,127 cycles

DURING HMV LIGHTNING STRIKE WAS FOUND ON AFT LWR WINDOW NR 71 BETWEEN STA Y= 886-905. WINDOW BELT WAS REPAIRED IAW SRM 53-05 FIG 111 AND ERA 471664-14 REV A.

Part: HINGE FITTING — WORN (HORIZ STAB) · airframe 59,572 hrs · 47,127 cycles

DURING HMV WEAR WAS FOUND ON EDGE OF LT INBOARD BUSHING OF LT HORZ STAB ATTACHMENT. HORZ STAB ATTACHMENT WAS REPAIRED IAW SRM 55-02 PARA 24.

Part: SPAR CAP — CRACKED (HORIZ STAB) · airframe 59,572 hrs · 47,127 cycles

DURING HMV A CRACK WAS FOUND AT UPPER INBOARD EXTERNAL HOLE SINCE EDGE HOLE AND DOWN (RT) MATCH WITH NRC T0147748. AREA REPAIRED IAW EA 09-460214-12AD ME 16.

Part: SKIN — DAMAGED (BS 1022-1041) · airframe 57,505 hrs · 45,701 cycles

FUSELAGE WINDOW BELT HAD LIGHTNING DAMAGE AT STA 1022-1041 ON THE RT SIDE OF THE AIRCRAFT. REMOVED DAMAGE PER MD88 SRM 53-05, FIGURE 111 AND SUBMITTED FINAL DIMENSIONS TO BOEING FOR APPROVAL. 8100-9 APPROVAL WAS RECEIVED FROM BOEING FOR THE REWORK AS TIME LIMITED UNTIL THE PANEL IS REPLACED.

Part: OIL CAP — DAMAGED (APU) · airframe 50,571 hrs · 40,986 cycles

ODOR FROM A/C SYSTEM CAUSED AFT SMOKE DETECTOR IN LAV TO GO OFF DURING TAKEOFF. SOME HAZE IN AFT CABIN. REPLACED SEAL UNDER APU OIL CAP. CLEANED OIL FROM APU INLET, PERFORMED DUCT BURNOUT.

Part: PUMP — FAILED (NR 2 ENGINE FUEL) · airframe 46,609 hrs · 38,129 cycles

ON TAKEOFF ROLL AT 50 KTS RT ENGINE ROLLED BACK AND SHUTDOWN. REPLACED FUEL PUMP AND FUEL CONTROL UNIT PER MM. RAN ENGINE PER PFHB.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 44,746 hrs · 36,903 cycles

THE FUSELAGE SKIN AND UNDERLYING DOUBLER WERE FOUND CRACKED AT THE FWD EDGE OF THE C1 DOOR CUTOUT BETWEEN LONGERON 24 & 25. THE CRACK WAS CUT OUT OF THE SKIN AND DOUBLER. THE CUTOUT WAS REPAIRED WITH 2 EXTERNAL ALUMINUM REPAIR DOUBLERS PER ER/A 385745-14.

Part: HYDRAULIC LINE — CHAFED (HYD SYSTEM) · airframe 44,697 hrs · 36,865 cycles

RT HYD SYS FAIL RT HYD SYS PRESS LOW ON AOP WITH HYD PRESS AND QTY DECREASING. REPLACED CHAFED LINE IN AFT CARGO COMPT.

Part: LINE — CHAFED (NR 1 ENGINE) · airframe 44,351 hrs · 36,619 cycles

DURING CLIMBOUT PASSING FL250. THE LT HYD PRESS LOW MSG ILLUMINATED ON OAP. LT HYD QTY DROPPED TO 3 QTS, ACCOMPLIHED POM PROCEDURE FOR HYD PRESS LOW,HYD QTY LOW OR DECREASING AND FINALLY LT HYD SYS FAILURE. PRIOR TO ENG START THE HYD QTY READ L-16..RT-14. FOUND LT ENG CENTER HYD FLEX LINE FROM PYLON TO ENG BADREPLACED HYD LINE LEAK CHECKS GOOD

Part: DOOR — MISSING (AFT LAV SERVICE) · airframe 42,803 hrs · 35,544 cycles

AFT LAV SERVICE DOOR NOT ON A/C UPON ARRIVAL DFW. INSPECTED A/C. NO DAMAGE NOTED OTHER THAN DOOR. REPLACE AFT LAV SERVICE DOOR.

Part: PROXIMITY SENSOR — OUT OF ADJUST (NLG) · airframe 40,783 hrs · 34,072 cycles

NOSE GEAR UNSAFE LIGHT AFTER RETRACTION. CYCLED GEAR GOT THREE GREEN IN DOWN POSITION. RETRACTED AGAIN AND NOSE GEAR WOULD NOT RETRACT. SERVICED NOSE STRUT AND ADJUSTED PROX SENSOR.

Part: TANK — LEAKING (APU) · airframe 39,830 hrs · 33,390 cycles

AFT LAV SMOKE DETECTORS ACTIVATED DURING CLIMB AND SMOKE WAS APPARENT. NATURE OF PROBLEM, SMOKE IN CABIN. CAUSE OF SMOKE DETERMINED TO BE OIL LEAKING FROM APU OIL TANK AND INGESTED IN APU INLET. RENDERED APU INOP AND PERFORMED OPER 5088 FOR DUCT BURN OUT PROCEDURE. APU WILL NEED REPLACEMENT DUE TO LOCATION OF OIL LEAK.

Part: LINK — BROKEN (MLG BRAKE LINE) · airframe 37,229 hrs · 31,505 cycles

RIGHT SYSTEM HYDRAULIC QUANTITY DECREASING EN ROUTE TO PBI. DIVERTED TO ATL. FOUND LEFT GEAR UPPER BRAKE HOSE SUPPORT LINK BROKEN WITH RUPTURED BRAKE LINE.

Part: SLIDE — DEPLOYED (PAX DOOR) · airframe 36,626 hrs · 31,064 cycles

R1 DOOR SLIDE BLEW WHEN OPENING DOOR. SLIDE WAS LEFT ARMED. REPLACED SLIDE.

Part: HYDRAULIC SYSTEM — OVERSERVICED (AFT) · airframe 36,475 hrs · 30,956 cycles

AFTER TURNING ON PACKS HAD SMOKE IN CABIN, SEEMED TO COME OUT OF BOTH PACKS. MAINT FERRY A/C TO PHX. FOUND LEFT HYD SYS OVERSERVICED AND DRAIN BOTTLE FULL, FLUID INGESTED BY APU. PERFORMED DUCT BURN OUT PER MM AND REPLACED WATER SEPARATOR BAGS.

Part: BEARING — WORN (RECIRC FAN) · airframe 36,178 hrs · 30,725 cycles

DURING CLIMB HAD VISABLE SMOKE IN CABIN. REPLACED RECIRC FAN DUE WORN BEARINGS.

Part: SKIN — DAMAGED (CARGO DOORWAY)

A 1 X 1 SECTION OF FUSELAGE SKIN TORN FROM THE FWD EDGE OF THE C-2 CARGO DOOR OPENING. ACTION TAKEN, ERA 266915-14.

Part: SKIN — DAMAGED (BS 226)

GROUND DAMAGE INCURRED AT FS 226 BETWEEN S17L AND S18L, THE TIME LIMITED REPAIR WAS REMOVED AT THE CURRENT VISIT. CUTOUT WAS MADE LARGER TO REMOVE ALL FASTENER HOLES FROM T/L REPAIR. REPAIRED PER ERA 271221-14, REV B.

Part: POWER SUPPLY — INOP (CABIN)

ON INSPECTION, FOUND APPROX ONE THIRD OF EMERGENCY PATH LIGHTS INOP IN CENTER PORTION OF CABIN. REPLACED AFT POWER SUPPLY FOR EMERGENCY PATH LIGHTS, OPN NORMAL.

Part: TARGET — OUT OF POSITION (LT MLG)

AFTER GEAR RETRACTION LEFT MAIN GEAR DID NOT INDICATE UP AND LOCKED. FOUND LT MLG RETRACTED POSTION TARGET OUT OF POSITION REPOSITIONED AND INSTALLED HARDWARE CKS OK. REF MD 88 IPC 32-30-00-12A ITEM 445, 450 AND 470.

Part: JAMB — CORRODED (C1 DOOR)

FWD CARGO DOOR OPENING LWR JAMB PAN HAD EXTENSIVE CORROSION. REPAIRED PER ERA 331138-14.

Part: BULB — FAILED (FLT DECK)

AFTER INITIAL GEAR EXTENTION, DID NOT HAVE CENTER GEAR LIGHT (GREEN) FOR CONFIRMED EXTENSION. AFTER GO-AROUND AND RESEATING NOSE GEAR LIGHT ASSY, LIGHTS WORKED AND SHOWED SAFE GEAR EXTENSION. RELAMPED NOSE GEAR INDICATOR.

Part: BATTERY PACK — DISCHARGED (CABIN)

EMERGENCY TRACK LITE SYS INOP IN FIRST CLASS AND IN 3 ROWS OF TOURIST CLASS. FOUND BATTERY PACK DEAD, REPL. BATTERY PACK, CK'S OK.

Part: OIL SEAL — LEAKING (APU)

ON CLIMB-OUT ABOUT 4,000 FEET, BOTH SMOKE ALARMS IN REAR OF A/C SOUNDED AND THERE WAS A LIGHT MIST/SMOKE VISIBLE IN THE A/C. THE SMOKE ALARMS COULD NOT BE SILENCED BY FANNING TO VENTILATE BOTH HPS BLEEDS ON A/C. PACKS TURNED OFF. NO HELP. CORRECTIVE ACTION FOUND APU LEAKING OIL IN EXHAUST AND BACK INTO A/C SYSTEM. REPLACED OIL SEAL AND BURNED OUT DUCT. OPS CHECK OK.

Part: THROTTLE SWITCH — FAILED (CENTER PEDESTAL)

ON TAKEOFF, HAD LANDING GEAR WARNING WITH GEAR RAISED. REPLACED RIGHT THROTTLE SWITCH PACK DUE TO SWITCH 320 FAILED. SYSTEM CHECKS GOOD PER M/M.

Part: SWITCH — FAILED (FLT DECK)

RETRACTED THE LANDING GEAR AFTER TAKEOFF, RECEIVED LANDING GEAR WARNING AND ALL 3 RED UNSAFE LIGHTS WITH GEAR HANDLE UP. POM PROCEDURES CYCLED GEAR, NO HELP. GEAR HANDLE UP, 3 RED WARNING LIGHTS, GEAR DETERMINED TO BE UP. INSPECTED GEAR SYSTEMS, NO TROUBLE FOUND. ON SUBSEQUENT OCCURENCE INSPECTION, FOUND S1-320 SWITCH BAD IN RT THROTTLE SWITCH PACK R AND R RT SWITCH PACK AND ADJ PER MM, GEAR SWING NORMAL.

Part: PIGTAIL — BROKEN (CABIN)

EMERGENCY TRACK LIGHTS BROKEN AT ROWS 1 AND 2 C/D. REPLACED PIGTAILS AND LIGHT COVERS.

Part: WIRE — BROKEN (CABIN)

PN PREFLIGHT, L-1 AND R-1 DOOR EMERGENCY EXIT IDENTIFIER LIGHTS FOUND INOP. MTC REPAIRED BROKEN WIRE IN THE RT SIDE F/C FLOOR TRACK AND OPERATION NORMAL.

Part: TAB — DAMAGED (ELEVATOR)

DURING SHOP INSPECTION, ELEVATOR TAB WAS RESTORED PER DRAWING 5930497 AND REPAIRED PER SRM 55-04 AND 51-70-2.

Part: ELEV TAB — CRACKED (LT ELEV)

THREE INCH CRACK FOUND IN TRAILING EDGE SIX INCHES IBD FROM OUTBOARD, TRAILING EDGE AND LARGE AREA OF DELAMINATION, ON LEFT ELEVATOR GEAR TAB. REPAIRED PER SRM-55-04.

Part: HYD HOSE — LEAKING (TAIL COMP)

DURING CLIMBOUT, ON FLAP SLAT RETRACTION HAD TOTAL LOSS OF RIGHT SYSTEM HYDRAULIC PRESSURE AND FLUID. RETURNED TO DFW. FOUND LEAKING LINE AT RIGHT FWD FILTER MODULE IN TAIL COMAPARTMENT. REPLACED LINE OPERATION NORMAL.