N920DE

Part: BATTERY — MISSING (SMOKE DETECTOR) · airframe 65,150 hrs · 47,726 cycles

LAVATORY SMOKE DETECTOR BATTERY MISSING. REPLACED THE BATTERY, OP CKS NML.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 64,214 hrs · 46,871 cycles

EMERGENCY LIGHT OVER DOOR AT 24A INOP. RELAMPED SAME OPS NML REF AMM 33-52. (LP4751576)

Part: RELAY — DEFECTIVE · airframe 63,857 hrs · 46,564 cycles

AFTER TAKE OFF SMELL OF BURNT RUBBER IN COCKPIT AND CABIN. DISSIPATED QUICKLY. GONE BY APPROXIMATELY 10,000 FEET. R/R RECIRC FAN. NO HELP. REPLACED RELAY R2-278. (LP5733780)

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHTS) · airframe 63,676 hrs · 46,415 cycles

EMERGENCY PATH LIGHT INOP @ PX 19&22. R/R SEAT WIRING HARNESS AT PAX 19&22 CKS GOOD PER AMM MD88 33-53. (LP5277974)

Part: NOSE COWL — DENTED (NR 1 ENGINE) · airframe 62,811 hrs · 45,688 cycles

DURING INSP. FOUND DENT ON NR 1 ENG INLET NOSE COWL AT 10 O'CLOCK POSITION. DENT MEASURES 2.25" X 1.25" & 0.344 DEEP & APPROX 10 O'CLOCK POSITION. PEFORMED TIME LIMITED REPAIR PER ERA 572070-14 SECTION I. NO CRACKS NOTED. REPLACED NR 1 ENGINE NOSE COWL PER RI 572070-14 03-OCT-2018 0645E SECTION III PERMANENT REPAIR INSTRUCTIONS. (LP4490184)

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 61,794 hrs · 44,814 cycles

DURING EMERGENCY LIGHT TEST DO NOT TURN ON, EXTERNAL LIGHTS ON FUSELAGE. REPLACED BATTERY PACK P/N60-1177-9IN AFT CARGO. OPS CHECKS OK.

Part: SLIDE — MALFUNCTIONED (L2 DOOR) · airframe 61,790 hrs · 44,812 cycles

DURING INITIAL INSPECTION, FOUND THAT THE FIRING LANYARD TO CONNECT MANUAL INFLATION HANDLE WAS MISSING ON THE L2 DOOR SLIDE, THE SAME SLIDE WAS FOUND WRAPPED AROUND WITH A NYLON CORD. L2 DOOR SLIDE WAS REMOVED AND REPLACED IAW AMM 25-62-00.

Part: FRAME — WORN (FUSELAGE) · airframe 61,790 hrs · 44,812 cycles

WORN FRAME ON STA Y=1510 CANT BTW 4-8 HRS POSITION AT AFT ACCESSORIES COMPARTMENT. FRAME WAS BLENDED OUT PER SRM 53-01 FIG. 1, FRAME BTW 6 AND 8 POSITION FOUND WITHIN LIMITS. FRAME AT 4 HRS POSITION MINIMUM REMAINING THICKNESS IS 0.027" THEREFORE IT IS OUT OF LIMITS PER SRM 53-01 FIG 1 SHEET 3 AND WAS REPLACED PER SRM 51-30-2, 51-30-5.

Part: SPAR CAP — CRACKED (RT HORIZ STAB) · airframe 61,790 hrs · 44,812 cycles

DUE A CRACK ON RT HORIZONTAL STABILIZER REAR SPAR CAP, REMOVE AND INSTALL RUDDER. RUDDER WAS REMOVED AND INSTALLED UNDER AMDS 2720-4421 JOB 000-0030.

Part: RIB — CRACKED (RT WING) · airframe 61,790 hrs · 44,812 cycles

CRACKED RIB, XRS 214, RT WING LEADING EDGE INNER STRUCTURE. THE RIB WAS REPLACED IAW SRM 51-30-2.

Part: CUSP WEB — CORRODED (BS 484-503) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

CORROSION FOUND ON THE RT CUSP WEB, UPPER & LOWER SURFACES, RBL 54 TO 60 BETWEEN BS 484 TO 503. THE CUSP WEB WAS REPLACED IAW SRM 5130-2, 51-30-1, AND 51-30-5.

Part: SPAR CAP — CRACKED (HORIZONTAL STAB) · airframe 61,790 hrs · 44,812 cycles

CRACK FOUND ON THE RT HORIZONTAL STABILIZER REAR SPAR CAP. THE SPAR CAP WAS REPLACED IAW 5510-4135.

Part: FRAME — WORN (BS 1485) · airframe 61,790 hrs · 44,812 cycles

FRAME FOUND WORN OUT OF LIMITS, BS 1485, BETWEEN THE 9 AND 10 HRS POSITION. THE FRAME WAS REPAIRED IAW ER/A 567923-14, REV ORIGINAL, AND ETI-88-18-039, REV 2.

Part: FRAME — CRACKED (BS 1474) · airframe 61,790 hrs · 44,812 cycles

CRACK FOUND ON THE FRAME AT BS 1474, AT THE 8 HRS POSITION IN THE AFT ACCESORY BAY. THE FRAME WAS REPAIRED IAW ER/A 567630-14, REV ORIGINAL, & ETI-88-18-033, REV ORIGINAL.

Part: FRAME — CRACKED (BS 1437) · airframe 61,790 hrs · 44,812 cycles

A CRACK WAS FOUND ON THE FRAME WEB BS 1437, LONGERON 8L. REPAIRED IAW ERA 567707-14, REV ORIGINAL, AND ETI-88-18-021, R3.

Part: PAN — CORRODED (BS 370-427) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

CORROSION FOUND ON THE LOWER PAN, BS 370 TO 427, LONGERONS 23R TO 28R AT THE CARGO DOOR FRAME. THE PAN WAS REPAIRED IAW ETI-88-18-025, REV 1, AND ER/A 567912-14, REV ORIGINAL.

Part: SKIN — DAMAGED (RUDDER) · airframe 61,790 hrs · 44,812 cycles

FOUND DAMAGED ALUMINUM FLAME SPRAY, LT & RT SIDES, SEVERAL AREAS. ON THE RUDDER. THE FRAME SPRAY WAS REPARIED IAW ERA.092613-14MA, REV C.

Part: FINGER DOUBLER — CORRODED (BS 1210-1215) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

CORROSION ON THE FINGER DOUBLER BETWEEN BS 1210 AND 1215, LONGERON 26L. FOUND TO BE OUT OF LIMITS. THE FINGER DOUBLER WAS REPLACED IAW SRM 53-04, FIG 12E, & SRM 51-30-2.

Part: SKIN — DAMAGED (RT WING) · airframe 61,790 hrs · 44,812 cycles

CRACKS, PUNCTURES AND WEAR FOUND ON THE FIXED LEADING EDGE SKIN BETWEEN XFS 60 - 70, RT WING. REPAIRED IAW ERA 567673-14, REV B, AND ETI -88-18-031, REV 6.

Part: FLOOR PANEL — CORRODED · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

CORRODED FLOOR PANEL. THE FLOOR PANEL WAS REPLACED IAW AMM 53-20-01.

Part: FLOOR PANEL — DAMAGED · airframe 61,790 hrs · 44,812 cycles

DELAMINATED COMPOSITE MATERIAL, PUNCTURES ON CHANNELS AND CORROSION ON STRAP AT FLOOR PANEL 200A. THE FLOOR PANEL AND CHANNELS WERE REPAIRED IAW SRM 51-70-1D, PAR. 10. AND DWG 9952523, REV Y.

Part: FRAME — CRACKED (BS 1474) · airframe 61,790 hrs · 44,812 cycles

CRACKED FRAME BS 1474, LONGERON 18R IN THE AFT ACCESORIES BAY. THE FRAME WAS REPAIRED IAW ER/A 567556-14, REV ORIGINAL, & ETI-88-18-023 R1.

Part: CUSP WEB — CORRODED (BS 1155-1212) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

CORROSION ON CUSP WEB LOWER SURFACE BS 1155 TO 1212, RBL 54 TO 60 IN THE AFT CARGO BAY. REPLACED IAW SRM 53-05, FIG 131A-24, SRM 51-30-2, & 51-30-5.

Part: SHEAR TIE — CRACKED (BS 1380) · airframe 61,790 hrs · 44,812 cycles

CRACK ON THE SHEAR TIE BS 1380, LONGERON 15R IN THE AFT ACCESORIES COMPARTMENT. THE SHEAR TIE WAS REPLACED IAW SRM 51-30-5, & DWG 9912246, REV CY.

Part: SKIN — CORRODED (BS 769-776) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

CORROSION FOUND ON THE FUSELAGE SKIN BETWEEN BS 769 - 776, LONGERONS 27R - 28R. THE SKIN WAS REPAIRED IAW SRM 53-04, FIG 57.

Part: FRAME ANGLE — CRACKED (BS 1401-1405) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

AFTER REMOVING CORROSION, A CRACK WAS FOUND ON THE CAP ANGLE ATTACHED TO STAIRWAY FRAME, BETWEEN BS 1401 - 1405, LT SIDE. THE CAP ANGLE WAS REPLACED IAW SRM 51-30-2.

Part: TEE FITTING — CORRODED (BS 1380) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

CORROSION ON THE TEE FITTING, BS 1380 BETWEEN LONGERONS 25L & 25R. THE TEE FITTING WAS REPLACED IAW SRM 51-30-2, AND 51-30-5.

Part: FLOOR SUPPORT — DAMAGED (BS 826) · airframe 61,790 hrs · 44,812 cycles

ELONGATED HOLE ON THE FLOOR SUPPORT BS 826, RBL 22. REPAIRED IAW ERA 567554-14, REV ORIG, AND ETI-88-18-022, REV ORIG.

Part: FRAME — CRACKED (BS 1510) · airframe 61,790 hrs · 44,812 cycles

A CRACK WAS FOUND ON THE FRAME, BS 1510. THE FRAME WAS REPLACED IAW SRM 51-30-1, 51-30-2, AND 51-30-5.

Part: TAB — DENTED (ELEVATOR) · airframe 61,790 hrs · 44,812 cycles

DURING INSPECTION, FOUND SEVERAL DENTS ON UPPER SKIN AT THE RT CONTROL TAB. THE RT CONTROL TAB WAS REPLACED IAW 55-04 PAR 2.

Part: VANE — DELAMINATED (LT WING TE FLAP) · airframe 61,790 hrs · 44,812 cycles

DURING INSPECTION, DELAMINATED WAS FOUND ON THE PREVIOUS DOUBLER REPAIR ON OTBD FLAP VANE OF OTBD FLAP, LT WING. THE FLAP VANE WAS REPLACED IAW SRM 57-04, PAR. 5

Part: FITTING — CRACKED (DOOR FRAME) · airframe 61,790 hrs · 44,812 cycles

CRACKED FITTINGS AT THE RT AND LT SIDES AT AFT CABIN BULKHEAD DOOR FRAME. FITTINGS REPLACED IAW SRM 51-30-2, 51-30-5, AND 51-30-1.

Part: TAB — DEBONDED (ELEVATOR) · airframe 61,790 hrs · 44,812 cycles

DISBONDED UPPER AND LOWER SKIN AT LT ANTI FLOAT TAB, XEFT 160. THE LT ANTI-FLOAT TAB WAS REPLACED IAW 55-04, PAR 2.

Part: TAB — DENTED (ELEVATOR) · airframe 61,790 hrs · 44,812 cycles

SEVERAL DENTS ON UPPER SKIN AT THE LT GEARED TAB. THE TAB WAS REPLACED IAW 55-04, PAR 2.

Part: CHANNEL — CRACKED (CABIN) · airframe 61,790 hrs · 44,812 cycles

CRACK CHANNEL ON GENERATION FLOOR NBR 313A, 313E, 389G, 541F, 617G, 927A AND 927E. CHANNEL ON GENERATION FLOOR NBR 313A, 313E, 389G, 541F, 617G AND 927E WERE REPAIR PER DC-9/MD-80 SRM 53-05 FIG.131B AND 131C (SHEET 1 ), AND FLOOR PANEL NBR. 927A WAS REPLACED PER DWG 9952521 REV BB. (ET) HFEC INSPECTION WAS ACCOMPLISHED PER DC-MD NDT SPM 06-10-01.001, NO CRACKS WERE FOUND AFTER STOP DRILL AT ALL FLOOR PANELS. (LP0508980)

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 61,790 hrs · 44,812 cycles

CORROSION ON RH FUEL ACCESS PLATES NBR 1436C, 1454C, 1414C, 1478C AND 1470C. FUEL ACCES PLATE 1454C, 1436C, 1414C, 1478C AND 1470C WERE REPLACED PER DC9/MD-80 SRM 51-22-2A. (LP0507595)

Part: ACCESS PANEL — CORRODED (LT WING) · airframe 61,790 hrs · 44,812 cycles

CORROSION ON LH FUEL ACCESS PLATES NBR 1311C, 1335C AND 1363C. ACCESS PLATE NBR 1311C, 1335C AND 1363C WERE REPLACED PER DC-9/MD-80 SRM 51-22-2A PAR 6 (LP0507458)

Part: FLOOR PANEL — CRACKED (COCKPIT) · airframe 61,790 hrs · 44,812 cycles

CRACK COCKPIT RT FLOOR PANEL NR 120D. FLOOR PANEL WAS REPAIRED (PERMANENT REPAIR) PER SRM 53-01 FIG 2 (SHEET3).

Part: FLOOR PANEL — DAMAGED (COCKPIT) · airframe 61,790 hrs · 44,812 cycles

ELONGATED HOLES ON COCKPIT FLOOR PANEL NR 120B LT SIDE. FLOOR WAS REPAIRED (PERMANENT REPAIR) PER DC-9/MD-80 SRM 53-01 FIG 4 (SHEET4).

Part: FLOOR PANEL — CRACKED · airframe 61,790 hrs · 44,812 cycles

CRACK UPPER SKIN ON GENERATION FLOOR NR 465E AND 826G. FLOOR NR 465E AND 826G WERE REPAIRED (AS A PERMANENT REPAIR) PER SRM 53-01 FIG.2 (SHEET3) AND FIG 4 (SHEET4).

Part: FITTING — CRACKED (FUSELAGE) · airframe 61,790 hrs · 44,812 cycles

CRACK ON SHEAR CLIP STA Y= 1380 LONG 15L AT AFT ACCESSORIES COMPARTMENT. FRAME CLIP WAS REPLACED PER SRM 53-14-4 & DWG 9912246 REV CY.

Part: ACCESS PANEL — CORRODED (WING) · airframe 61,790 hrs · 44,812 cycles

CORROSION ON LH/RH FUEL ACCESS PLATES NBR 1303C AND 1409C IN REF AMDS 2000-2636. DUE TO BLEND OUT REPAIR IS NOT PERMITTED ON THE UPPER WING ACCESS DOOR (P/N 3912757) DUE TO THE REDUCED AREA OF THE CONDUCTIVE INTERFACE. FUEL ACCESS DOOR 1409C AND 1303C WERE REPLACED DC9/MD88 SRM: 51-22-2A. (LP0505957)

Part: FLOOR SUPPORT — CRACKED (BS 1271-1287) · airframe 61,790 hrs · 44,812 cycles

CRACKED FLOOR SUPPORT, BS 1271 TO 1287, LBL 2. REPAIRED IAW SRM 53-01, PAR. 4 FIG.2, SHEET 4.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

CORROSION ON RT CUSP WEB STA Y =1072 AT CPAX. CORROSION 2: REPAIR WAS ACCOMPLISHED (PERMANENT REPAIR) PER SRM53-05 FIG 131-A-13.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 61,790 hrs · 44,812 cycles

INITIAL INSPECTION DELAMINATION ON FLOOR PANELS NBRS 160D, 120C, 160C, 160E, 200D, 200B, 1174E, 160F, 617D, 617E, 617F, 769E, 769F, AND 826E. FLOOR PANELS NBRS 160D, 120C, 160C, 160E, 200D, 200B, 1174E, 160F, 617D, 617E 617F, 769E, 769F, AND 826E WERE FABRICATE REPLACED AND IDENTIFIED PER MD88 A.M.M. 53-20-01-201 AND WERE INSTALLED PER ROUTINE TARK CARD 001-0071:2500-0539. (LP0503680)

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 61,790 hrs · 44,812 cycles

INITIAL INSPECTION CRACKS ON FLOOR PANELS NBRS 168B, 200C, 160A, 389F AND 1003B AT PAX CAB. FLOOR PANELS NBRS 168B, 200C, 160A ,389F AND 1003B WERE FABRICATED REPLACED AND IDENTIFIED PER MD88 A.M.M. 53-20-01-201 AND WERE INSTALLED PER ROUTINE TASK CARD 001-0071:2500-0539. (LP0503686)

Part: CUSP WEB — CORRODED (BS 1049) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

CORROSION ON THE RT CUSP WEB BS 1049. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

CORROSION ON LT CUSP WEB STA X=54 TO X=60 BTW STA Y=674 AND Y=693. CORROSION 2; LT CUSP WEB STA X=54 TO X=60 BTW STA Y=674 AND Y=693 WAS REPAIRED (PERMANENT REPAIR) PER SRM 53-05 FIG 131A-9.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 61,790 hrs · 44,812 cycles

CRACK LONG 12L STA Y=1437 AT AFT ACCESSORIES COMPARTMENT. LONG 12L STA Y=1437 AT AFT ACCESSORIES WAS REPAIR ( AS A PERMANENT REPAIR )PER SRM 53-02-FIG.18, SRM 51-30-5 AND SRM 51-30-2.

Part: CUSP WEB — CORRODED (BS 727-739) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

CORROSION ON CUSP WEB WAS FOUND WITHOUT LIMITS, BS 727 TO 739 BETWEEN LBL 54 TO 60. THE CUSP WEB WAS REPAIRED IAW SRM 53-05, FIG 131A-9.

Part: LONGERON — CRACKED (BS 1437) · airframe 61,790 hrs · 44,812 cycles

A CRACK WAS FOUND ON LONGERON 3R, BS 1437. THE LONGERON WAS REPAIRED IAW SRM 53-02, FIG 18, SRM 51-30-5, AND SRM 51-30-2.

Part: CUSP WEB — DAMAGED (BS 1006-1072) · airframe 61,790 hrs · 44,812 cycles

A PUNCTURE AND A BEND ON THE LT CUSP WEBS LBL 44 TO 54, BS 1006 AND 1072. LT CUSP WEB REPAIRED IAW SRM 53-05, FIGURE 131A-17.

Part: WEB — CRACKED (BS 361-389) · airframe 61,790 hrs · 44,812 cycles

CRACKED WEB, BS 361 TO 389, BETWEEN RBL 54 AND 60. REPAIRED IAW SRM 51-02, FIG 1.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

CORROSION ON LT CUSP WEBS UPPER AND LWR SIDE IN STA X=54 TO X=60 BTW Y= 294 TO Y= 313 AT PAX CABIN. LEVEL CORROSION 2, CUSP MEMBRANE WAS REPAIRED PER SRM 53-05 FIG, 131A-14. PERMANENT REPAIR.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

OUT OF LIMITS IN REF CORROSION ON PAX CABIN LT CUSP WEB BTW X=54 AND X=60 STA Y=1088 TO Y=1089. CORROSION LEVEL 2: CUSP WEB WAS REPAIRED PER SRM 53-05 FIG 131A-13.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 61,790 hrs · 44,812 cycles

CRACK ON L=2R STA Y=965 AT PAX CABIN. LONGERON 2 RT STA Y=965 AT PAX CABIN WAS REPAIRED (PERMANENT REPAIR) PER SRM 53-02 FIG 18.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 61,790 hrs · 44,812 cycles

HIDDEN CRACK; DURING REMOTION OF RING DOUBLER RELATED WITH NRC 00370 A CRACK WAS FOUND: CRACK ON LT CUSP WEBS IN STA Y= 888 BTW X=54 TO X=60 AT PAX CABIN. CUSP WEB WAS REPAIRED (PERMANENT REPAIR) PER SRM 53-01 FIG 2 (SHEET 3).

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

OUT OF LIMITS; LEVEL CORROSION 2; DURING REMOTION OF CORROSION AN AREA WAS FOUND WITHOUT LIMITS: CORROSION ON RT SEAT TRACKS X= -44 FROM STA Y= 246 TO Y=256 AT CABIN PAX. SEAT TRACK ON STA Y:200 TO Y:264 WAS REPAIRED PER SRM 53-05 FIG 4F.

Part: PAN — CRACKED (FUSELAGE) · airframe 61,790 hrs · 44,812 cycles

INITIAL INSPECTION: CRACKED LT UPPER/FWD CORNER WINDOW RING PAN IN STA Y= 886 AT CPAX. LT UPPER/FWD CORNER WINDOW RING PAN IN STA Y= 886 AT CPAX WAS REPAIRED (PERMANENT REPAIR) PER SRM 53-05 FIG 122, SRM 51-30-2, SRM 51-30-5, ER/A 487747-14MA REV A AND ER/A 493648-14MA REV A.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

OUT OF LIMITS CORROSION ON LT SEAT TRACK X=22 Y=795-797 AT CPAX. LEVEL CORROSION 2; LT SEAT TRACK X=22 Y= 795-797 AT CPAX WAS REPAIRED (PERMANENT REPAIR) PER SRM 53-05 FIGURE 4F.

Part: DIAPHRAGM — CRACKED (FUSELAGE) · airframe 61,790 hrs · 44,812 cycles

INITIAL INSPECTION. CRACKED DIAPHRAGM Y=123 X=-47 AT COCKPIT. DAMAGE WAS REPAIRED PER SRM 53-01,(ET) HFEC INSPECTION WAS ACCOMPLISHED ON DIAPHRAGM Y=123 X=-47 AT COCKPIT.

Part: CUSP WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

OUT OF LIMITS CORROSION ON LT CUSP WEB BTW STA Y=546-547 ALSO Y=556-557 AT CPAX. CUSP WEB WAS REPAIRED (REPAIR PERMANENT) CORROSION LEVEL 2 PER SRM 53-05 FIG 131A-14.

Part: BEAM — CRACKED (NR 4 DOOR) · airframe 61,790 hrs · 44,812 cycles

INITIAL INSPECTION: CRACKED BEAM NR 4 ON FWD CORNER OF FWD SERVICE DOOR R1. BEAM NR 4 WAS REPLACED PER SRM 51-30-2, 51-30-5 AND DWG 9911582 REV T.

Part: FLOOR SUPPORT — CORRODED (BS 160-168) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

DURING REMOVAL OF CORROSION, A FLOOR SUPPORT BS 160-168, LBL 54 WAS FOUND OUT OF LIMITS. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-30-2, 51-30-5, AND 51-10-4.

Part: SUPPORT — CRACKED (BS 182-198) · airframe 61,790 hrs · 44,812 cycles

CRACKED SUPPORT IN RBL 29 BETWEEN BS 182 - 198. THE SUPPORT WAS REPLACED IAW SRM 51-30-2, SRM 51-10-2, AND DWG 9936535-67, REV CS.

Part: WEB — CORRODED (BS 282-284) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

CORROSION FOUND ON THE LT CUSP WEB UPPER AND LWR SURFACES LBL 54 TO 60, BETWEEN BS 282 TO 284. REPAIRED THE WEB IAW SRM 53-05, FIG 131, A-5.

Part: FLOOR SUPPORT — CORRODED (BS 210) · corrosion level 2 · airframe 61,790 hrs · 44,812 cycles

CORROSION ON THE FLOOR SUPPORT BS 210, RLB 10. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-30-2, AND 51-10-4.

Part: DOOR — DAMAGED (FWD CARGO) · airframe 61,790 hrs · 44,812 cycles

CRACK BELOW FWD STOP FITTING 3, ON OUTER PAN AT THE FWD CARGO DOOR. FWD CARGO DOOR WAS REPAIRED IAW SRM 52-05, FIGURE 50, SRM 51-30-1, AND 51-30-2.

Part: TAB — DAMAGED (RIGHT) · airframe 61,790 hrs · 44,812 cycles

DEBONDED UPPER AND LOWER SKIN AT RT ANTI-FLOAT TAB BETWEEN XEFT 154 AND 173. RT ANTI-FLOAT TAB WAS REPLACED IAW SRM 55-04, PAR 2, AND WAS INSTALLED WITH AMDS 2730-4334.

Part: CONTROL VALVE — LEAKING (THRUST REVERSER) · airframe 59,761 hrs · 43,206 cycles

ON ENTERING THE ACFT, FOUND A STRONG BURNING ELECTRICAL ODOR THROUGHOUT CABIN. FOUND THE LEFTT THRUST REVERSER CONTROL VALVE LEAKING AND APU INTAKE CONTAMINATED. REPLACED THE LEFT SIDE THRUST REVERSER CONTROL VALVE IAW MM 78-31-04. LEAK AND OPS CHECKED OK. PERFORMED APU INLET CLEANING, ALT DUCT BURN AND COALESCE BAG R & R IAW 4900-1184/ 4950-2215, AND 2170-4139. ACFT OK FOR SERVICE.

Part: CONNECTOR — LOOSE (EMERGENCY LIGHTS) · airframe 59,528 hrs · 43,032 cycles

EMERGENCY LIGHTS 26D AND 28D INOPERATIVE. SECURED LOOSE CONNECTORS AT 26 AND 28D. CHECKED GOOD.

Part: LIGHT — DAMAGED (SEAT 11D) · airframe 59,499 hrs · 43,005 cycles

SEAT 11 D EMERGENCY EXIT LIGHT DAMAGED. REPLACED EMERGENCY PATH LIGHT ASSY SEAT 11D.

Part: DOOR FRAME — CORRODED (BS 1155-1211) · corrosion level 2 · airframe 59,276 hrs · 42,832 cycles

CORROSION ON LOWER CARGO DOOR FRAME FROM BS 1155 - 1211. THE DOOR FRAME WAS REPAIRED IAW SRM 53-05, PARAGRAPH 140, FIGURE 123.

Part: FLOOR SUPPORT — CORRODED (BS 200) · corrosion level 2 · airframe 59,276 hrs · 42,832 cycles

CORROSION ON FLOOR SUPPORT BS 200 LBL 54. THE FLOOR SUPPORT WAS REMOVED IAW SRM 51-30-5. A NEW FLOOR SUPPORT WAS FABRICATED IAW DWG 9910078 REV JC AND SRM 51-10-2. THE FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-5.

Part: FLOOR SUPPORT — CORRODED (BS 200) · corrosion level 2 · airframe 59,287 hrs · 42,840 cycles

FWD WET AREA HAS CORROSION ON THE FLOOR SUPPORT BS 200 LBL 54. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-30-5, DWG 9910078, REV JC, AND SRM 51-10-2,

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,276 hrs · 42,832 cycles

CORROSION ON WEB STA Y =1212- 1218 BTW LONG 26R. WEB WAS REPAIRED PER SRM 53-01 FIG 4 SHEET 4.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 59,276 hrs · 42,832 cycles

AFT CARGO COMPARTMENT, CORROSION ON INTERCOSTAL STA=1003 TO STA=1022 BTW LONG 28L. INTERCOSTAL WAS REMOVED, FABRICATED AND INSTALLED PER DWG 9958212 ITEM 503 REV ED.

Part: BEAM — CRACKED (L1 DOOR) · airframe 59,276 hrs · 42,832 cycles

L1 DOOR NR 1 BEAM CRACKED AT FWD EDGE. THE BEAM WAS REPAIRED IAW SRM 52-05 FIG 98.

Part: TAB — DAMAGED (RUDDER) · airframe 59,276 hrs · 42,832 cycles

RUDDER CONTROL TAB, COMPOSITE MATERIAL WAS FOUND DAMAGED. DAMAGE AREA WAS REPAIRED IAW SRM 51-90-0 PARAGRAPH 8.K.

Part: LANYARD — BROKEN (R1 DOOR SLIDE) · airframe 59,276 hrs · 42,832 cycles

R1 DOOR HAD A BROKEN SLIDE LANYARD. THE SLIDE LANYARD WAS REPLACED IAW AMM 25-62-00-201.

Part: CARGO TRACK — CORRODED (BS 1220-1322) · corrosion level 2 · airframe 59,276 hrs · 42,832 cycles

LEFT CARGO TRACK IN AFT CARGO BAY, FROM BS 1220 TO 1322 CORRODED OUT OF LIMITS IAW SRM 53-05, FIG. 4C. THE CARGO TRACK WAS REPLACED IAW SRM 53-14-3.

Part: BEAM — CRACKED (L1 DOOR) · airframe 59,276 hrs · 42,832 cycles

L1 DOOR HAD A CRACKED BEAM NR 8 AND ANGLE AT AFT EDGE. THE BEAM WAS REPAIRED IAW SRM 52-05 FIG. 111 SHEET 8.

Part: FITTING — CRACKED (R1 DOOR) · airframe 59,276 hrs · 42,832 cycles

R1 DOOR CRACKED FITTING ON BEAM NR 4 AFT EDGE. THE FITTING WAS REPLACED IAW SRM 51-30-01, 51-30-05, AND DWG 9911582 REV. T.

Part: ANGLE — CRACKED (L1 DOOR) · airframe 59,276 hrs · 42,832 cycles

L1 DOOR HAD A CRACKED FWD ANGLE AT UPPER EDGE. THE ANGLE WAS REPLACED IAW SRM 51-30-2.

Part: P&D VALVE — LEAKING (LT ENGINE) · airframe 58,652 hrs · 42,398 cycles

FLT 0377 RETURNED TO ATL AFTER THE LT ENGINE FAILED AFTER TAKE-OFF. THE CREW REPORTED THAT ON CLIMB OUT THAT THE ENGINE ROLLED BACK AND SHUT DOWN. MAINTENANCE FOUND FUEL LEAKING AT THE P&D VALVE FLANGE. THE P&D VALVE WAS REPLACED. THE MAGNETIC CHIP DETECTORS WERE CHECKED AND THE FUEL FILTER AND MAIN OIL FILTER WERE REPLACED. THE INLET AND EXHAUST WERE INSPECTED WITH NO PROBLEMS NOTED. AN ENGINE RUN WAS PERFORMED PER THE AMM AND CHECKED GOOD. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 57,989 hrs · 41,902 cycles

F/C CEILING EMERGENCY LIGHTS INOPERATIVE. REPLACED THE BATTERY PACK IAW AMM 33-53. OPS CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 57,619 hrs · 41,628 cycles

EMERGENCY EXIT LIGHT INOPERATIVE ON BOTH AFT OVERWING EXIT DOORS. R & R THE BATTERY PACK IAW SSM 33-51-00, TESTED OK.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 57,551 hrs · 41,581 cycles

EMERGENCY CEILING LIGHTS IN FIRST CLASS INOPERATIVE. REPLACED BOTH BATTERIES IN BATTERY PACK ASSY.

Part: CONNECTOR — DISCONNECTED (EMERGENCY LIGHT) · airframe 56,099 hrs · 40,575 cycles

EMERGENCY LIGHT FOUND INOPERATIVE. CONNECTOR WAS FOUND DISCONNECTED. RECONNECTED, CHECKED OK.

Part: VANE — DAMAGED (LT WING TE FLAP) · airframe 54,548 hrs · 39,442 cycles

WHILE WORKING SPOILER DEPLOYED MEL, FOUND FIXED FLAP VANE DAMAGED BELOW INBD FLT SPOILER LT WING. REM AND REP VANE IAW AMM 27-51-03-201. OPS CK GOOD IAW TOPP 40-30-05 APPENDIX G.

Part: DOOR FRAME — CORRODED (BS 636-693) · corrosion level 2 · airframe 54,002 hrs · 39,071 cycles

CORROSION FOUND ON LOWER DOOR FRAME BS 636-693. REMOVED CORROSION, COMPLIED WITH NDTSPM PT4, 04-00-02. FOUND TO BE WITHIN REPAIRABLE LIMITS IAW SRM 53-05, FIG 123. INSTALLED A REPAIR IAW SRM 53-05, FIG 123.

Part: SHEAR TIE — CORRODED (BS 1212) · corrosion level 2 · airframe 53,995 hrs · 39,065 cycles

CORROSION IN AFT CARGO BILGE AREA SHEAR TIE BS 1212 BETWEEN L29 AND 30R. REMOVED THE CORROSION AND FOUND IT OUT OF LIMITS IAW SRM 53-01. REMOVED & INSTALLED NEW IAW SRM 51-30-05, 51-10-4, 51-10-3 & DWG 9919603, REV B.

Part: LANYARD — MISINSTALLED (TAILCONE SLIDE) · airframe 53,995 hrs · 39,065 cycles

TAIL SLIDE LANYARD FOUND INSTALLED INCORRECTLY . CORRECTLY INSTALLED TAIL SLIDE STRAP THROUGH RING.

Part: INTERCOSTAL — CORRODED (BS 1200) · corrosion level 2 · airframe 53,967 hrs · 39,061 cycles

CORROSION IN THE AFT CARGO LOWER DOOR FRAME INTERCOSTAL AFT FACE APPROXIMATELY AT BS 1200 BETWEEN LONGERON 28 AND 29R. REMOVED INTERCOSTAL AT AFT CARGO PIT STA 1200 IAW SRM 51-30-05. REMOVED CORROSION AT INTERCOSTAL IAW SRM 51-10-03 PART 26. FOUND OUT OF LIMITS IAW SRM. LOCATED DRILLED & DEBURRED NEW INTERCOSTAL IAW SRM 51-10- 4, PART 2. INSTALLED INTERCOSTAL IAW SRM 51-30-05 & DWG 5936026, REV A.

Part: INTERCOSTAL — CORRODED (BS 1172) · corrosion level 2 · airframe 53,967 hrs · 39,061 cycles

AFT CARGO DOOR FRAME INTERCOSTAL AT BS 1172 BETWEEN LONGERONS 28-29R IS CORRODED. REMOVED AND REPLACED THE INTERCOSTAL IAW SRM 51-30-07 & 05, SRM 51-10-3, SRM 53-01 SRM 51-10-4, PARA 2, 3, AND SRM 51-30-05.

Part: DOOR FRAME — CORRODED (CARGO BAY) · corrosion level 2 · airframe 53,967 hrs · 39,061 cycles

CORROSION ON THE SILL BEAM "INBD" OF THE AFT CARGO LOWER DOOR JAMB APPROX AT STA 1215 LONGERON 29R, MRB 53-019-02. REMOVED CORROSION ON JAMB BEAM INBD IAW SRM 51-10-3. ALODINED AREA IAW SRM 51-10-3. UT INSP AREA IAW NDT SPM PT4 04-00-07 ORIGINAL MATERIAL 0.150 REMAINING AT LOWEST POINT 0.058 HFEC INSP AREA IAW NDTSPM PT6 06-10-1 AND FOUND OUT OF LIMITS. REMOVED JAMB BEAM AT STA 1110 TO 1255 IAW SRM 51-30-02 AND 05. LOCATED AND DRILLED HOLES ON JAMB BEAM. ALODINED AND PRIMED HOLES IAW SRM 51-10-3. TOP COATED JAMB BEAM IAW SRM 51-10-3B. INSTALLED JAMB BEAM IAW SRM 51-30-5.

Part: SKIN — CRACKED (NLG CUTOUT) · airframe 53,967 hrs · 39,061 cycles

REPAIR DOUBLER AT LT NLG DOOR AFT HINGE CUTOUT IS CRACKED BS 101. REMOVED AND REPLACED THE DOUBLER IAW SRM 53-05, PARA 162.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 53,863 hrs · 38,988 cycles

MAINTENCE FOUND THE CEILING EMERGENCY LIGHTS AT ROW 16 WERE INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY LIGHT BATTERY PACK AND THE LIGHTS TESTED GOOD.

Part: CONNECTOR — DISCONNECTED (EMERGENCY LIGHTS) · airframe 53,049 hrs · 38,377 cycles

DURING LINE CHECK, MAINTENANCE FOUND THAT THE SEAT MOUNTED EMERGENCY EXIT LIGHT AT THE OVERWING EXIT ROW WAS INOPERATIVE. MAINTENANCE FOUND A CONNECTOR IN THE WIRE HARNESS UNPLUGGED, RECONNECTED IT, AND FUNCTIONALLY CHECKED THE SYSTEM.

Part: STRAINER — CLOGGED (LT ENGINE) · airframe 52,700 hrs · 38,133 cycles

RETURNED TO DEPARTURE AIRPORT DUE TO A LT ENGINE STRAINER CLOG MESSAGE. LEFT ENGINE WAS AT IDLE AND WAS NOT SHUTDOWN. REPLACED LT ENGINE DUE TO CARBON BEING FOUND IN THE FILTER.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 52,536 hrs · 37,997 cycles

DURING LINE CHECK, MAINTENANCE FOUND THE EMERGENCY EXIT LIGHTS ABOVE BOTH AFT OVERWING EXIT DOORS TO BE INOPERATIVE. MAINTENANCE REPLACED THE BATTERIES AND THE LIGHTS RETURNED TO AN OPERATIONAL STATE. (LP 5435139).

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 51,251 hrs · 37,139 cycles

DURING LINE CHECK, THE EMERGENCY LIGHTS INOPERATIVE AT ROW 1 THROUGH 7. REPLACED POWER SUPPLY IAW AMM 33-53 AND OPS CHECKED GOOD.

Part: PAN — CORRODED · corrosion level 2 · airframe 50,772 hrs · 36,788 cycles

DURING SCHEDULED INSPECTION, CORROSION WAS NOTED AT THE AFT LAV PAN AREA ON THE LOWER EDGE OF THE PAN CUTOUT. REPAIRED IAW ER/A 517741-14, SECTION 1. FOLLOW-UP INSPECTION IAW SECTION 2 AND PERMANENT REPAIR IAW SECTION 3 LIMITS ESTABLISHED IAW MONITOR LOGPAGE AND ER/A 517741-14.

Part: SKIN — CRACKED (BS 1418) · airframe 50,772 hrs · 36,788 cycles

SKIN CRACK NOTED, BS 1418 AT L2R. REPAIRED IAW ER/A 517731-14AD.

Part: FRAME — CRACKED (BS 1510) · airframe 50,772 hrs · 36,788 cycles

BS 1510 FRAME CRACKED ON LT SIDE IN 3 LOCATIONS. FRAME REPLACED IAW SRM 51-01 AND DWG 9911843-698815.

Part: FRAME — CRACKED (BS 1510) · airframe 50,772 hrs · 36,788 cycles

BS 1510 FRAME RT CRACKED. FRAME REPLACED IAW SRM 51-01.

Part: SKIN — CRACKED (BS 1418) · airframe 50,772 hrs · 36,788 cycles

DURING SCHEDULED CHECK, A CRACK WAS NOTED IN SKIN AT BS 1418 BETWEEN LONGERON L2 & 3R AT THE FASTENER HOLES. REPAIR COMPLETED IAW ER/A 517731-14AD.

Part: PULLEY — WORN (TAILCONE RELEASE) · airframe 50,772 hrs · 36,788 cycles

DURING SCHEDULED INSPECTION, THE TAILCONE RELEASE CABLE PULLEY WAS NOTED TO BE WORN AT THE 11 O'CLOCK POSITION AT STATION 1510 IN THE AFT ACCESSORY COMPARTMENT. THE PULLEY WAS REPLACED AND FUNCTIONAL CHECK AND REQUIRED INSPECTIONS WERE COMPLETED REF: AMDS WC 5350-01077-0101.

Part: SLIDER — WORN (TAILCONE RELEASE) · airframe 50,772 hrs · 36,788 cycles

DURING SCHEDULED INSPECTION, THE TAILCONE RELEASE CABLE, CABLE CLAMP/SLIDER BLOCK WAS NOTED TO BE WORN AT THE UPPER RT LATCH. THE SLIDER BLOCK ASSEMBLY WAS REPLACED IAW AMM 53-53 AND THE RIG, FUNCTIONAL CHECK AND REQUIRED INSPECTIONS WERE COMPLETED.

Part: CAM — WORN (TAILCONE RELEASE) · airframe 50,772 hrs · 36,788 cycles

DURING SCHEDULED INSPECTION, THE TAILCONE RELEASE KEVLAR CABLE CAM BASE WAS FOUND TO BE WORN AT THE ROLLER GUIDES. THE CAM ASSY AND BASE WERE BOTH REPLACED IAW AMM 53-53 AND AMDS WC 5350-01077-0101. THE REQUIRED INSPECTIONS WERE COMPLETED.

Part: BUSHING — WORN (TAILCONE RELEASE) · airframe 50,772 hrs · 36,788 cycles

DURING SCHEDULED INSPECTION, TAILCONE RELEASE TEE PIN CLEVIS BUSHINGS WERE NOTED TO BE WORN ON THE LT SIDE OF THE AFT ACCESSORY COMPARTMENT. THE BUSHINGS WERE REPLACED IAW AMM 53-53 AND THE FUNCTIONAL CHECK AND REQUIRED INSPECTIONS WERE COMPLETED.

Part: THRESHOLD — CORRODED (CARGO DOOR) · airframe 50,772 hrs · 36,788 cycles

DURING ROUTINE INSPECTION, EXTENSIVE CORROSION WAS NOTED IN THE AFT CARGO BIN THRESHOLD BEAM. CORROSION WAS REMOVED AND REPAIRS COMPLETED IAW BLUEPRINT, PN 5936038-501 AND ALL REQUIRED INSPECTIONS WERE COMPLETED.

Part: INTERCOSTAL — CRACKED (BS 1497) · airframe 50,772 hrs · 36,788 cycles

DURING SCHEDULED INSPECTION, A CRACKED INTERCOSTAL WAS FOUND AFT OF THE TAIL COMPARTMENT CATWALK ON THE LT SIDE. REPAIRED IAW ER/A 517848-14.

Part: PIN — WORN (TAILCONE RELEASE) · airframe 50,772 hrs · 36,788 cycles

DURING SCHEDULED INSPECTION, THE TAIL CONE RELEASE TEE PIN CLEVIS AREA WAS NOTED TO BE WORN ON THE LT SIDE OF THE AFT ACCESSORY COMPARTMENT. THE TEE PIN WAS REPLACED IAW AMM 53-53 AND THE REQUIRED FUNCTIONAL CHECK AND REQUIRED INSPECTIONS WERE COMPLETED.

Part: FASTENER — LOOSE (VERTICAL STAB) · airframe 50,772 hrs · 36,788 cycles

DURING SCHEDULED INSPECTION, ONE FASTENER WAS FOUND TO BE LOOSE ON THE LT VERTICAL STABILIZER L/E JUST ABOVE ZFS 52-267 AND FWD OF THE VERTICAL STABILIZER FRONT SPAR. REPAIRED IAW SRM 53-03D AND AMDS 5530-01045-0801.

Part: LENS — BROKEN (EMERGENCY LIGHT) · airframe 50,729 hrs · 36,759 cycles

DURING ROUTINE LINE INSPECTION, THE FORWARD GALLEY EMERGENCY LIGHT LENS WAS FOUND TO BE BROKEN. THE EMERGENCY LIGHT ASSY WAS REPLACED IAW AMM 33-50 AND OPS CHECKED GOOD.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 50,135 hrs · 36,342 cycles

DURING A ROUTINE EMERGENCY LIGHT TEST BY LINE MX, THE WING DOOR EMERGENCY EXIT SIGN AT ROW 24A & 24E WAS FOUND INOPERATIVE. THE POWER SUPPLY WAS REPLACED IAW AMM 33-53 AND GROUND CHECKED GOOD.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN FLOOR STRUCTURE SUPPORT CORRODED STA 200 RBL 45 TO RBL 55 HAS CORROSION. MECHANICALLY REMOVED CORROSION AT MAIN CABIN FLOOR SUPPORT AT STA 200 RBL45 - 55. FOUND OUT OF LIMITS PER MD80 SRM 53-01PG 8 FIG 1 SHEET 3. REPLACED FLOOR SUPPORT PER MD88 SRM 51-30-5 PG 12 DURING HMV.

Part: FRAME — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

AFT CARGO STA 1287 FROM R24 TO L24 FRAME STRUCTURE CORROSION. REMOVED CORROSION ON AFT CARGO FRAME STA 1287 PER MD80 SRM 51-10-3 PG 46, FOUND FRAME TO BE OUT OF LIMITS FROM L28 TO R28 PER MD80 SRM 53-01 PG 8. WORK TO BE PERFORMED ON NRC 197587 DURING HMV.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

AFT CARGO COMPARTMENT L-26L HAS CORROSION FROM STA 1041 TO STA 1201. REMOVED CORROSION IAW MD80 SRM 51-10-3 PG 46. FOUND TO BE OUT OF LIMITS IAW MD80 SRM 53-01 PG 8. FABBED 4EA CHANNELS IAW MD80 SRM 53-02 PG 57. INSTALLED CHANNELS AT STA 1041,1079, 1111 AND 1195 IAW MD80 53-02 PG 54.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN CUSP WEB HAS CORROSION AT STA 812 LBL 59. REMOVED CORROSION ON CUSP WEB STA 812 LBL 59 IAW MD80 SRM 51-10-3 PG 46. FOUND TO BE OUT OF LIMITS IAW MD80 SRM 53-01 PG 8. CUT OUT DAMAGED AREA IAW DWG SG09530019. HFEC C/W IAW MD80 NDTSPM 06-10-01.001 NO DEFECTS FOUND. FABBED REPAIR DOUBLER AND FILLER IAW DWG SG09530019. INSTALLED SAME IAW MD80 SRM 51-30-5 PG 22 FIG 10 AND DWG SG09530019. ID TAG INSTALLED VIEW PS900-5-1 NR 4 PG 3, 4 AND 6.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN FLOOR STRUCTURE SUPPORT STA 1155 LBL 23 TO LBL 44 HAS CORROSION. REMOVED CORROSION IAW MD80 SRM 51-10-3 PG 46. FOUND TO OUT OF LIMITS IAW MD80 SRM 53-01 PG 8. REMOVED FLOOR SUPPORT AT STA 1155 LBL 23 TO LBL 44 IAW MD80 SRM 51-30-5 PG 29. FABBED FLOOR SUPPORT IAW MD80 SRM 53-13-3 PG 29. INSTALLED SAME AT STA 1155 LBL 23 TO LBL 44 IAW MD80 SRM 51-30-5 PG 12.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN CUSP WEB STA 1060 TO 1077 HAS CORROSION MULTIPLE PLACES LBL 55. REMOVED CORROSION AT CUSP WEB STA 1060 TO LBL 55. FOUND AREA 100 PERCENT EXFOLIATED. FABBED DOUBLER AND FILLER. INSTALLED SAME AT STA 1058-1062 IAW BOEING DWG SG09530019 AND MD80 SRM 51-30-05 PG 12-28 DURING HMV.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN FLOOR STRUCTURE SUPPORT STA 1155 LBL12 HAS CORROSION AROUND SCREW HOLE ON LOWER SURFACE. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS PER MD80 SRM 53-01 PG 8. FABRICATED EXTRUSION IAW MD80 SRM 51-10-4 AND 53-14-3 PGS 47 AND 48. INSTALLED FABRICATED FLOOR STRUCTURE SUPPORT AT MAIN CABIN STA 1155 LBL 12 IAW MD80 SRM 51-30-5 PG 1 THRU 14.

Part: SUPPORT FITTING — CORRODED (R1 DOOR) · airframe 47,219 hrs · 34,300 cycles

R1 DOOR GIRT BAR SUPPORT FITTINGS 2 EA ARE CORRODED. REMOVED CORROSION ON SUPPORT FITTINGS PER MD80 SRM 52-01 PG 3 PARA 3 AND FOUND TO BE OUT OF LIMITS. REPLACED SUPPORT FITTINGS PER 51-10-4 AT SAA DURING HMV ON N/R CARD 199306.

Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN FLOOR STRUCTURE ANGLE SUPPORT EXFOLIATED STA 200 BL 0. REMOVED MAIN CABIN FLOOR STRUCTURE ANGLE SUPPORT AT STA 200 BL 0 IAW MD80 SRM 51-30-2 PG 26A. 100 PERCENT MATERIAL LOSS. FABBED NEW SUPPORT ANGLE IAW MD80 SRM 51-10-4. INSTALLED SAME IAW MD80 SRM 51-30-5 AND MD80 SRM 51-20-00.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN CUSP WEB HAS CORROSION AT STA 503 RBL 59. REMOVED FITTING AT WEB STA 503 RBL 59 PER DC9-MD80 SRM 51-30-3 PARA 8 PAGE 19. FABRICATED DOUBLER W/OUT RETORN LIP FROM CLAD 7075-T6, RING DOUBLER FROM 7075-T6 AND FILLER FROM CLAD 7075-T6 PER GENERAL REPAIR DRAWING SG09530019. INSTALLED REPAIR PER GENERAL REPAIR DRAWING SG09530019.AT SAA/SAT DURING HMV ON N/R 186536 W/O 89712840001.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN CUSP WEB HAS CORROSION AT STA 622 LBL 59. CUT OUT DAMAGED SECTION AT CUSP WEB FROM STA 598 TO 625 LBL 55 IAW DWG SG09530019 CONFIG -7021. NDT HFEC INSP IAW NDTSPM 06-10-01.001 NO DEFECTS FOUND. FABBED DOUBLERS IAW DWG SG09530019 CONFIG -7021. INSTALLED NEW DOUBLERS IAW MD80 SRM 51-30-05.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN CUSP WEB HAS CORROSION AT STA 607 TO 617 LBL 59 ON UPPER AND LOWER SURFACES, AREA WAS PREVIOUSLY BLENDED AND HAS A PREVIOUS REPAIR. REMOVED EXISTING REPAIR AT STA 612. CUT OUT DAMAGED SECTION AT CUSP WEB FROM STA 598 TO 625 LBL 55 REF DWG SG09530019 CONFIG -7021. FABBED DOUBLER AND RING DOUBLER PER DWG SG09530019 CONFIG -7021. NDT HFEC C/W IAW NDTSPM 06-10-01.001 NO DEFECTS FOUND. INSTALLED NEW DOUBLERS IAW MD80 SRM 51-30-05 PG 29 DURING HMV.

Part: DOOR — CORRODED (APU) · airframe 47,219 hrs · 34,300 cycles

CORROSION ON OUTER FLANGE INNER SURFACE OF APU LT DOOR. REMOVED CORROSION ON OUTER FLANGE, FOUND TO BE OUT OF LIMITS IAW DC-9/MD80 SRM 52-42-0.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

CENTER CARGO ANTENNA CUTOUT HAS CORROSION AT STA 681 BETWEEN L-30 AND L-29L AROUND FASTENER HOLES (INTERNAL) AND EXTERNAL ON RING. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS IAW MD80 SRM 53-01. REMOVED ANTENNA DOUBLER AT STA 681 BETWEEN L-30 AND L-39, INSTALLED NEW ANTENNA MOUNT DOUBLER IAW DC9/MD80 SRM 51-30-2 DURING HMV.

Part: SKIN — DENTED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

THREE DENTS ON FUSELAGE SKIN AT STA 222, BELOW LONGERON 18L. CUT OUT DAMAGE AREA AT FUSELAGE SKIN AT STA 222, BELOW LONGERON 18L IAW DC9-MD80 SRM 53-04DPG 60BV FIG 12B. FABRICATED DOUBLER, FILLER FINGER DOUBLER AND STRAP IAW DCP/MD80 SRM 53-04D FIG 12B PAGE 60G AND 60BV AND SRM DC9/MD80 53-34-0 FIG 1 PAGES 3, 4 ITEM 27. INSTALLED REPAIR IAW DC9/MD80 SRM 53-34-0 FIG 1 PG 3.4 AT SAA/SAT DURING HMV ON W/O 89708600001.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

AFT CARGO LONG 28L CORROSION FROM STA 1193 TO 1322.

Part: FRAME — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

AFT CARGO FRAME STA 1287 FRAME DOUBLER FROM 26R TO 26L CORROSION.

Part: FRAME — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

AFT CARGO AREA STA 1271 R24 TO L24 FRAME STRUCTURE CORRODED.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN CUSP WEB HAS CORROSION AT STA 598 LBL 59. FABRICATED REPAIR DOUBLER FROM SHT 7075-T6 .032 BATCH #0002108938 ND FAB RING DOUBLER FROM SHT 7075-T6 0.050 BATCH # 002108938 EF DRAWING SG09530019 CONFIGURTION-7021. INSTALLED REPAIR PER DRAWING SG09530012. AT SAA/SAT DURING HMV ON W/O W/O 89712900001.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN FLOOR SEAT TRACK LBL 54 STA 1174 TO 1309 HAS CORROSION AND GOUGES MULTIPLE AREAS. REMOVED CORROSION AND BLENDED GOUGES, SEAT TRACK UPPER LOBE OUT OF LIMITS IAW DC9/MD80 SRM 51-10.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN FLOOR STRUCTURE SUPPORT STA 148 BETWEEN RBL 35 TO RBL 45 HAS CORROSION RUNNING UNDER FLOORBOARD, REMOVED CORROSION. FOUND TO BE OUT OF LIMITS. REMOVED, FABRICATED, AND INSTALLED FLOOR SUPPORT IAW MD-88 SRM 51-30-5 DURING HMV.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN FLOOR STRUCTURE SUPPORT STA 200 RBL 9 TO RBL 46 HAS CORROSION ON MULTIPLE PLACES. FLOOR STRUCTURE STA 200 RBL 9 HAS 100 PERCENT MATERIAL LOSS.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN FLOOR STRUCTURE SEAT TRACK AT STA 148 TO 200 LBL 7 HAS CORROSION. REMOVED CORROSION. FOUND TO BE OUT OF LIMITS. REMOVED, FABRICATED, AND INSTALLED REPLACEMENT SEAT TRACK AT STA 148-200 LBL 7 IAW DC9/MD80 SRM 51-30-1 DURING HMV.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN FLOOR STRUCTURE SUPPORT STA 160 TO 200 RBL 54 HAS CORROSION UPPER AND LOWER SURFACE / FOUND FLOOR STRUCTURE SUPPORT HEAVILY CORRODED AND CRACKED. REMOVED AND REPLACED FLOOR SUPPORT IAW MD80 SRM 53-14-1.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN FLOOR STRUCTURE SUPPORT STA 160 TO 198 RBL 44 HAS CORROSION. REMOVED CORROSION ON MAIN CABIN FLOOR STRUCTURE FOUND TO BE OUT OF LIMITS. REMOVED SUPPORT , ADDITIONAL CORROSION ON WEB SURFACE, FABRICATED AND INSTALLED SUPPORT IAW MD88 SRM 51-10-03 DURING HMV.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN FLOOR STRUCTURE SEAT TRACK HAS CORROSION LBL 54 STA 217-484. REMOVED CORROSION. FOUND TO BE OUT OF LIMITS. REMOVED SEAT TRACK LBL 54 FROM 217 TO 248, FABRICATED SEAT TRACK, REPAIR STRAPS, AND INSTALLED IAW MD-88 SRM 53-05. DURING HMV.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN FLOOR STRUCTURE SUPPORT AND FILLER ARE CORRODED LBL 55 STA 160 TO 200. REMOVED CORROSION. FOUND TO BE OUT OF LIMITS. REMOVED FLOOR SUPPORT AND REPLACED ON NRC 162925. DURING HMV.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN FLOOR STRUCTURE SUPPORT STA 1079 RBL 24 TO RBL 45 HAS CORROSION AND CHAFED WEAR ON LOWER SIDE. REMOVED CORROSION. FOUND TO BE OUT OF LIMITS. REMOVED AND FABRICATED NEW SUPPORT. INSTALLED SUPPORT IAW MD-88 SRM 51-30-5 DURING HMV.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN CUSP WEB HAS CORROSION AT STA 799 LBL 59. REMOVED CORROSION ON CUSP WEB. FOUND TO BE OUT OF LIMITS. CUT OUT DAMAGED AREA, FABRICATED FILLER AND DOUBLERS IAW MD-88 SRM 53-05 AND INSTALLED DURING HMV.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN CUSP WEB HAS CORROSION AT STA 477 RBL 60. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS. REMOVED DAMAGED AREA OF CUSP WEB, FABRICATED DOUBLER, AND INSTALLED IAW MD-88 SRM 53-05 DURING HMV.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN SEAT TRACK HAS CORROSION AND GOUGES FROM STA 417 TO STA 899 RBL 54. REMOVED CORROSION AND BLENDED GOUGES, FOUND TO BE OUT OF LIMITS IAW DC-9/MD80 SRM 53-05.

Part: CUSP WEB — CORRODED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN AREA STA 446-465 L18 CUSP AREA CORROSION & CRACKED SURFACE. REMOVED DAMAGED AREA, FABRICATED AND INSTALLED REPAIR FILLER, DOUBLER AND DOUBLER RING IAW SRM MD80 51-10-3.

Part: CUSP WEB — DAMAGED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

MAIN CABIN AREA STA 446-465 L18 CUSP AREA CORROSION AND CRACKED SURFACE. CUT OUT DAMAGE AERA AT MAIN CABIN STA 446-465 CUSP IAW SG09530019. FABRICATED FILLER, DOUBLER, AND DOUBLER RING IAW SRM MD80 51-10-3 PG 31-40. INSTALLED FILLER , DOUBLER AND DOUBLER RING IAW SG09530019. DURING HMV AT SAA/SAT ON N/R 196294 W/O 89712190001.

Part: DOUBLER — GOUGED (FUSELAGE) · airframe 47,219 hrs · 34,300 cycles

GOUGE ON REPAIR DOUBLER AT FUSELAGE SKIN AT STA 234 BETWEEN LONGERON 18L AND 21L. REMOVED DOUBLER, FABRICATED NEW DOUBLER AND INSTALLED PER ERA 334645-14 DURING HMV.

Part: SKIN — DENTED (ELEVATOR TAB) · airframe 46,551 hrs · 33,820 cycles

DENTS ON RT ELEVATOR CONTROL TAB UPPER AND LOWER SKIN. THIS N/R WAS ACCOMPLISHED IAW JIC OPN 1031 CARDS 1760 TO 1768 AND SRM 55-04 PARA 2A AND 3A.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 45,034 hrs · 32,744 cycles

DURING LINE CHECK, MAINTENANCE FOUND OVERHEAD EMERGENCY LIGHTS INOPERATIVE IN CABIN. MAINTENANCE REPLACED BULBS. OPERATIONAL CHECK WAS GOOD.

Part: WIRE — DAMAGED (EMERGENCY LIGHTS) · airframe 44,268 hrs · 32,248 cycles

DURING MX CHECK, FOUND EMERGENCY LIGHTING IN CEILING ABOVE ROW 11 SEATS NON-OPERATIONAL. MX REWIRED LIGHTING. OPS OF LIGHTS CHECKS GOOD.

Part: OIL SYSTEM — LEAKING (APU) · airframe 44,174 hrs · 32,161 cycles

DURING CLIMBOUT THE AFT SMOKE DETECTOR ALARM SOUNDED AND PASSENGERS SMELLED ODD ODOR IN REAR OF ACFT. FLIGHT CREW RETURNED ACFT TO DEPARTURE AIRPORT. MX FOUND OIL LEAKING FROM THE APU AREA AND REPLACED THE APU IAW AMM. PERFORMED OPN 5089 DUCT BURNOUT AND REPLACED COALESCER BAGS.

Part: PAN — CRACKED (CARGO DOOR) · airframe 43,711 hrs · 31,824 cycles

AFT CARGO DOOR LOWER OUTER PAN CRACKED. ALL FITTINGS CRACKED PROBABLY DUE TO IMPROPER RIGGING OF DOOR. MUST FOLLOW PROPER AMM RIGGING INSTRUSTIONS, MANY DOORS ARE RECEIVED CRACKED DUE TO IMPROPER RIGGING. C/A IS TO REPLACE ALL BROKEN PARTS AND O/H DOORS ON CK3993 NRC 674.

Part: ENGINE — FAILED (NR 2) · airframe 42,580 hrs · 31,080 cycles

RT ENG PWR LOSS AFTER TAKEOFF. FOUND METAL IN TAIL PIPE, REQUIRES ENGINE CHANGE. REPLACED RT ENG.

Part: BULB — BURNED OUT (MLG INDICATOR) · airframe 41,512 hrs · 30,299 cycles

NO GEAR DOWN INDICATION ON LEFT MAIN. RELAMPED LIGHT BULB AND CYCLED GEAR. THREE GREEN. CREW RELAMPED LEFT MAIN DOWNLOCK INDICATION PERFORMAED OPS. CHK PER M/M. ALL CHKS NML.

Part: RELAY — STUCK (APU) · airframe 38,363 hrs · 28,278 cycles

OUTBOUND CREW OF FLT 782 CALLED MTC TO REPORT CLOCKS INOP. MX FOUND THE MAIN BATTERY CHARGER INOP AND BATTERIES LOW. REPLACED CHARGER AND BATTERIES AND CLEARED ITEM. WHEN CREW NEXT ATTEMPTED TO START APU THEY HAD A FAULT LIGHT AND ECU FAULTED THE STARTER MOTOR. MTC INVESTIGATED AND FOUND STARTER MOTOR SHOWED SIGNS OF ELECTRICAL OVERHEAT AND DAMAGED. ELECTRICAL HARNESS FOR STARTER AND APU GEN ALSO DAMAGED. REPLACED APU ASSY PER M/M. REPLACED R2-63 RELAY PER M/M MCO/PLAC REMOVED.

Part: DUCT — CRACKED · airframe 31,831 hrs · 23,893 cycles

TAIL COMPARTMENT TEMP HI MSG PASSING THROUGH FL 250 AT CLIMB POWER. REPLACED CRACKED SPYDER DUCT.

Part: LIGHT — ODOR (GALLEY) · airframe 28,185 hrs · 21,346 cycles

APPROACHING CRUISE ALTITUDE OF 330 CABIN CREW AS WELL AS FLIGHT CREW SMELLED ELECTRICAL ODOR, NO SMOKE. REPLACED FIRST CLASS GALLEY OVER LIGHT ASSY 339101074.

Part: COFFEEMAKER — DIRTY (AFT GALLEY) · airframe 26,865 hrs · 20,439 cycles

ON TAKEOFF FROM ATLANTA THERE WAS AN ODOR OF BURNED RUBBER IN CABIN. NO SMOKE DETECTORS NOR ALARMS WENT OFF NOR ANY SMOKE OR HEAT NOTICED BY CREW OR PASSENGERS. ODOR DISSIPATED DURING CLIMBOUT AND WAS GONE AT LEVEL OFF. MTC PERFORMED OPN 5088 DUCT BURNOUT. DURING INSPECTION FOUND BURNT DEBRIS ON AFT GALLEY COFFEEMAKER HOT PLATE. CLEANED HOT PLATE AND ODOR WENT AWAY.

Part: BRACKET — FAILED (W/W) · airframe 25,036 hrs · 19,240 cycles

AFTER T/O L/R MAIN GEAR WARNING LTS REMAINED ILLUM W/ AMBER GEAR DOOR CAUTION LT. NOTED THE EMERGENCY LNDG GEAR EXTENSION HANDLE DOOR COVER PARTIALLY RAISED AND HANDLE OUT OF DETENT. PUSHED HANDLE DOWN TO NRML POSITION RESULTING IN NORMAL INDICATION FOUND BRACKET BENT ON LEFT STRUT THAT SUPPORTS THE NUMBER 2 BRAKE HYDRAULIC LINE. OUT OF POSITION LINE CONTACTED ALT GEAR EXTEND MECH AT LEFT GEAR DOOR UPLOCK. REPLACED BRACKET,LINES, CLAMPS AND HARDWARE ON LEFT SHOCK STRUT. GEAR CYCLED NUMEROUS TIMES AND CHECKS NORMAL.

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 23,672 hrs · 18,296 cycles

AFT CABIN EMERGENCY LIGHTS INOP. REPLACED PWR SUPPLY, OPS NORMAL.

Part: COALESCER BAG — DIRTY (A/C BAY) · airframe 23,577 hrs · 18,214 cycles

SMELLED SMOKE AT 28K CRZ FOLLOWED BY AFT LAV SMOKE DETECTORS AND VISIBLE SMOKE AROUND CEILING OF CABIN. WITHIN 3 MINUTES SMOKE HAD DISSIPATED. INSP ACM AND ENG, NTF. PERFORMED DUCT BURNOUT AND REPLACED COALESCOR BAGS. RAN ENGINES, CKS GOOD.

Part: ENGINE — SMOKE (NR 1) · airframe 22,563 hrs · 17,455 cycles

ON T/O CREW OF ANOTHER AIRCRAFT OBSERVED SMOKE (WHITE AT RST CHANGING TO DARK SMOKE) COMING OUT OF TAIL ON LEFT ENGINE DURING T/O ROLL AND CLIMBOUT. ALL COCKPIT INDICATIONS INDICATE NORMAL. PERFORMED VISUAL INSP OF INLET/ EXHAUST AND ENGINE EXTERIOR COMPONENTS. NO FOD, INSPECTED, RAN BOTH ENGINES TO T/O PWR, NO VIBS FELT AND ALL ENGINE PARAMETERS EVENLY MATCHED. RAN TO T/O PWR 5 TIMES, NO SMOKE NOTED. CONFERENCE CALL WITH ENG ANALYST AND SR COORDINATOR. OK FOR SERVICE.

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 21,831 hrs · 16,864 cycles

SEAT ROW 31-38 EMERGENCY TRACK LIGHTING INOP. REPLACED POWER SUPPLY.

Part: OVEN — ODOR (GALLEY) · airframe 19,074 hrs · 14,838 cycles

DURING CLIMB, A BURNING SMELL APPEARED APPROX 5 MIN AFTER FIRST CLASS OVENS TURNED ON. TURNED OFF OVENS AND PULLED C/BS AND SMELL WENT AWAY. MTC FOUND BURNED PIECE OF PAPER ON OVEN LOWER HEATING ELEMENT. REMOVED PAPER AND CHECKED OVENS. OVENS TEST OK.

Part: WARNING UNIT — FAILED (E/E COMP)

F/W WILL NOT TEST WHEN BUTTONS ARE PUSHED NO AURAL SOUND NO LIGHTS IN MASTER WARNING MASTER CAUTION. NO LOOP LIGHTS, NO ENGINE FIRE LIGHTS. REPLACED CENTRAL AURAL WARNING UNIT. RAN FIRE WARNING TEST FIRE WARNING TEST OK.

Part: POWER SUPPLY — INOPERATIVE (COCKPIT)

COCKPIT OVERHEAD EMERGENCY LIGHTS INOP. FOUND POWER SUPPLY INOP. REPLACED SUPPLY AND BATTERIES CKS OK.

Part: WIRE — CHAFED (CABIN)

AFT SECTION OF FLOOR TRACK EMERGENCY LIGHTS FROM SEAT 30 TO 38 INOP. FOUND WHEN REPLACING MISSING TRACK LIGHT SOCKET AT ROW 28. FOUND WIRE CHAFED AT LIGHT ASSEMBLY L2-848. REPAIRED WIRE, CK OK.

Part: FLASHLIGHT — BROKEN (CABIN)

EMERGENCY FLASHLIGHT AT MID JUMPSEAT DOES NOT BLINK. FOUND STRAP BROKEN AND FLASHLIGHT TAMPERED WITH. REPLACED LIGHT ASSY, CKS OK.

Part: BULB — FAILED (RT MLG)

ON APPROACH TO CVG, RIGHT MLG DOWNLOCK IND GREEN LIGHT FAILED TO ILLUMINATE. ALL OTHER IND WERE NORMAL, NO HORN AND NO RED LIGHT. CHECKED SENSORS RT GEAR AND PERFORMED BITE CHECK OF PSEV, NO FAULTS. RELAMPED RT GEAR POS IND AND CHECKS GOOD.

Part: ENGINE — OIL LEAK (NR 2)

ATB/MCO - SMOKE IN CABIN OIL SMELL. UNABLE TO ISOLATE DUE TO TIME AVAILABLE BEFORE LANDING. FOUND RT AIR CYCLE MACHINE SYSTEM FILLED WITH OIL. FORWARD RT PACK TO MCO AND PLA. DISC SENSE LINE TO FLOW CONTROL VALVE. ALSO, FORWARD RT CROSS-FEED VALVE CLOSED TO MCO AND PLA. REPLACED NR 2 ENGINE DUE TO OIL LEAK IN COMPRESSOR SECTION.

Part: GENERATOR — MALFUNCTIONED (NR 1 ENGINE)

WHEN STARTING RT ENGINE, LT GENERATOR CYCLED ON AND OFF. FREQS WERE 380 CPS THEN CAME BACK TO 400. AFTER TAKEOFF, LT GENERATOR CYCLED ON AND OFF AT 380 CPS. RETURNED TO ATL DUE TO APU INOP. FOUND NR 1 ENG CSD FILTER INDICATOR PIN POPPED. REMOVED CSD, GENERATOR, AND COOLER. INSTALLED SERVICEABLE CSD, GENERAT0R, AND COOLER. LEAK AND OPERATION CHECK OK.

Part: AIR COND — ODOR (CABIN)

DURING TAKEOFF, HAD SMOKE ODOR IN CABIN. RETURNED TO MCI AND PERFORMED VISUAL ACFT INSP, NO LEAKS NOTED. RAN PACKS AND COULD NOT DUPLICATE. RETURNED A\C TO SERVICE.