N787NC

Part: SHEAR TIE — CRACKED (BS 332 L17R) · airframe 70,496 hrs · 64,310 cycles

CRACK IN FRAME SHEAR TIE AT RT BS 332 JUST BELOW LONGERON 17 (204-01) OUT SIDE AD INSPECTION AREA, DISCOVERED WHILE PERFORMING AD INSPECTION. REMOVED DAMAGE SHEAR TIE IAW SRM 51-30-2, FABRICATED NEW SHEAR TIE IAW SRM 53-13-2, PG 2, FIG 1, ITEM 9. HEAT TREATED SHEAR TIE TO T6 ON TRAVEL 70002389430001, LOCATED AND DRILLED SHEAR TIE IAW SRM 51-30-4 TREATED AND PRIMED SHEAR TIE IAW SRM 51-10-3, INSTALLED SHEAR TIE IAW SRM 51-30-2 AND 51-305.

Part: SKIN — DENTED (FUSELAGE) · airframe 70,546 hrs · 64,370 cycles

RT FUSELAGE DENTED AT BS 83.5 BETWEEN L26-27R. WITHIN LIMITS IAW SRM 53-04-1 PARA 7(E) PG.30. NO CRACKS NOTED IAW NDT SPM 06-10-01.001.

Part: LONGERON — CRACKED (BS 1240 L12R) · airframe 70,496 hrs · 64,310 cycles

LONGERON 12R IS CRACKED AT STA 1240, AT AFT ACCESSORY COMPARTMENT ABOVE APU EXHAUST DUCT. R & R LONGERON SEGMENT AT L12R, BS 1219 TO BS 1250 IAW SRM'S 53-02, 51-30-2 (FIG 18), 51-30-05.

Part: BATTERY PACK — DISCHARGED (EMERGENCY LIGHTS) · airframe 3,459 hrs · 3,112 cycles

DURING TEST, EMERGENCY EGRESS AISLE LIGHTS BETWEEN ROWS 16-20 ILLUMINATED FOR ONLY 15 SECONDS. PLUGGED IN EXTERNAL POWER AND LET BATTERIES CHARGE, OPS CHECKED OK PER MM 33-53-00.

Part: WIRE — DAMAGED (CATWALK) · airframe 68,100 hrs · 61,834 cycles

MAINTENANCE FOUND TAIL CONE WALKWAY EMERGENCY EXIT LIGHT INOPERATIVE IN AFT POSITION. MAINTENANCE REPAIRED WIRING INSIDE CATWALK. OPERATIONAL CHECK WAS GOOD.

Part: SKIN — CRACKED (FLOOR PANEL) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN METAL SKIN FLOOR PANEL NR 64 HAS CORROSION AROUND EDGES AND HAS 3EA CRACKS ON SKIN. MAIN CABIN METAL SKIN FLOOR PANEL 64 WAS BLENDED OUT OF LIMITS AROUND I/B FASTENER HOLES ON W/O 2451NO0803 (6C/141) IAW DC-9 SRM 53-01 FIG 1 SH 3. RECEIVED NEW PANEL P/N 9957921-17. LOCATED, DRILLED AND DEBURRED IAW DC-9 SRM 51-10-4.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

FUSELAGE STA 37 BLKHD LT CRACKED AT LOWER GUIDE PIN. FAB FILLER DOUBLER USING A2469 ZETEC PER NDT SPM 06-10-01 FOUND NO CRACKS NOTED HEAT TREATED NEW DOUBLER ON PEMCO TRAVELER 2451N01760 FAB TAPERED SHIMS IAW DC9 SRM 51-10-4 SHIM IAW DC9 RECEIVED SPLICE ON PEMCO TRAVELER 2451N01734 INSTALLED NEW DOUBLER, SHIMS FILLER & SPLICE IAW ER/A 490994-14MA.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN PAX CABIN FLOOR PNL 64 FWD END HAS 2EA BLOWN OUT FASTENERS HOLES AND CORROSION ON I/B CORNER HOLE BS 674. REMOVED CORROSION FROM 2EA I/B BLOWN OUT FASTENER HOLES AND FOUND MATERIAL TO BE OUT OF LIMITS IAW DC-9 SRM 53-01 FIG 1 SH 3. RECEIVED NEW PANEL 64 PN 9957921-17. LOCATED, DRILLED & DEBURRED IAW DC9 SRM 51-10-4.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 712 LEFT SIDE CUSP WEB CRACKED APPROX 3 INCHES UNDER HORSE SHOE COLLAR 2EA PLACES. REMOVED DAMAGED WEB (20"X 15") BETWEEN STA 712 TO 692. FABRICATED WEB FROM .020 7075-T6. FABRICATED 4 EA DOUBLER RINGS FROM .050 7075-T6, 4 EACH RINGS FROM .063 7075-T6. INSTALLED WEB, 8 EARINGS. RESTORED AREA IAW DC-9 SRM 51-30-2, SRM 51-30-5, SRM 51-10-2 SRM 51-10-4 AND DWG SG 09530019.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN METAL SKIN FLOOR PANEL NR 65 HAS CORROSION AROUND EDGES. REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS IAW DC-9 SRM 53-01 FIG 1 SH 3. REMOVED DAMAGE 8.5 X 21 INCHES. FABRICATED AND INSTALLED DOUBLER IAW DC-9 SRM 53-01 FIG 4 AND ER/A 489369-14. APPLIED PERMANENT REPAIR ID TAG PER PS900-5-1 N 4. DOUBLER MAT .032 7075-T6.

Part: ANGLE — CHAFED (VERTICAL STAB) · airframe 67,736 hrs · 61,525 cycles

VERTICAL STABILIZER REAR SPAR Z-ANGLE FOR ACCESS PANEL 6404A IS CHAFED THROUGH AT FASTENER HOLE. REMOVED DAMAGED ANGLE. RECEIVED REPAIR MATERIAL. FABRICATED, DRILLED, FITTED, TREAT & PRIME & INSTALLED IAW DC-9 SRM 51-70-5, 51-10-3, 51-30-5 & 51-31-0.

Part: FLOOR PANEL — CHAFED (CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN FLOOR PNL 90 CHAFED AT FASTENER HOLES ON FWD END OF PNL. BLENDED CHAFED AREA AND FOUND MAT TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1 SH 3. REMOVED FL/PNL 90 IAW DC-9 SRM 51-30-01. REMOVED DAMAGED AREA APPROX 8" X 21". FABBED NEW DOUBLER FROM .032 7075T6 IAW DC-9 SRM 51-70-4 AND ERA 490834-14. INSTALLED ID TAG PER PS 900-5-1 NR 4.

Part: SKIN — CRACKED (WING) · airframe 67,736 hrs · 61,525 cycles

DURING MCK AT DHN, THE WING LEADING EDGE SKIN AT STA 481 WAS FOUND CRACKED IN TWO PLACES UNDER AN EXISTING REPAIR WHICH HAD NOT BEEN STOP DRILLED. SECTION II - ON OR BEFORE 5,000 FLIGHT HRS AFTER SECTION I ASSOCIATED ER/A 13-490105. REMOVED PREVIOUSLY INSTALLED DOUBLER IAW ERA 490105-14 AND DC9 SRM 51-30-5, FABRICATED AND INSTALLED NEW REPAIR DOUBLER IAW ERA 490105-14 AND DC9 SRM 51-30-5.

Part: SKIN — CORRODED (FLOOR PANEL) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN METAL SKIN FLOOR PANEL 26 HAS CORROSION ON PREVIOUS REPAIR. REMOVED CORROSION AND FOUND MAT TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1 SHT 3. FABRICATED REPAIR DOUBLER FROM .032 7075T6 IAW DC-9 SRM 51-70-4 FIG 1 ERA 490-100-14. INSTALLED PERMANENT REPAIR ID TAG PER PS 900-5-1NO 4.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

MAIN PASSENGER CABIN STA 851 BL 0 L ANGLE ON TOP OF PRESSURE DECK WHEEL WELL HAS CORROSION, REMOVED CORROSION IAW DC9 SRM 53-01 FIG 1 SHT 1. ORIG MAT .125.REMOVED.045, .080 REMAINING OUT OF LIMITS. CUT OUT DAMAGED AREA 2.35 X 1. 8. FABRICATED REPAIR FILLER AND STEEL ANGLE IAW DC9 ERA 490828-14, INSTALLED REPAIR ANGLE AND FILLER IAW DC9 SRM 51-30-5 AND ERA 480828-14.

Part: FITTING — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN BETWEEN STA 693 AND 713 LONG 19 RIGHT SIDE BATH TUB FITTING HAS CORROSION. FITTING FOUND TO BE OUT OF LIMITS. GAINED ACCESS TO FITTING. REMOVED FITTING. RECEIVED, FIT, DRILLED AND INSTALLED NEW FITTING PART NUMBER 5913055-508. RESTORED ACCESS IAW DC9 SRM 53-01 FIG 1, 51-10-4, 51-10-3, 51-30-1 51-30-5, 51-10-7.P-174 26.

Part: FITTING — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN BETWEEN STA 693 AND 712 LONG 19 LEFT SIDE BATH TUB FITTING HAS CORROSION. FITTING FOUND TO BE OUT OF LIMITS. GAINED ACCESS TO FITTING. REMOVED CORRODED FITTING. RECEIVED, LOCATED, DRILLED AND INSTALLED NEW FITTING P/N 3913055-507 RESTORED ACCESS IAW DC9 SRM 53-01 FIG 1, 51-10-4, 51-30-1, 51-30-5, 51-10-3, 51-10-9. P-174.

Part: FRAME — GOUGED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

AFT ACCESSORY RT SIDE CANTED FRAME STA 1339 GOUGED AT LOWER AFT SIDE. EVALUATED GOUGE RT CANTED FRAME. FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 PG 8. GAINED ACCESS. REMOVED AND REPLACED RT CANTED FRAME IAW DC9 SRM 51-30-02, 51-30-5. NEW FRAME PT 9911843-5. RESTORED ACCESS .

Part: FRAME — GOUGED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

AFT ACCESSORY CANTED FRAME STA 1339 LOWER AFT SIDE GOUGED. EVALUATED GOUGE ON LT CANTED FRAME. FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 PG 8. GAINED ACCESS, REMOVED & REPLACED LT CANTED FRAME IAW DC9 SRM 51-30-2 & 51-30-05. NEW FRAME PT 9911843-6.

Part: FLOORBOARD — CORRODED (COCKPIT) · airframe 67,736 hrs · 61,525 cycles

COCKPIT, FLOORBOARD 14B CORRODED AND SOFT. FABRICATED 1EA FLOOR PANEL 14B PN 9957826-39 OF .025" 7075T6 P/N 1120200 & 3EA HAT SECTIONS S2912282 CUST FURN PER ER/A 490099-14. P174 REQUIRED INSPECTION COMPLETED BY Q919.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

F/O'S SLIDING WINDOW OPENING TOP AFT DOUBLER CRACKED. TRIMMED SEAL DOUBLER IAW ER/A 490826-14 STEP 1. HFEC INSPECTION VERIFIED NO CRACKS IAW ER/A 490826-14 STEP 2. SEALED DOUBLER IAW DC9 51-20-0 AND ER/A 490826-14. APPLIED TAG 4. 174 REQUIRED INSPECTION COMPLETED.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN PAX CABIN PNL 46 O/B SIDE FWD HAS CORROSION AROUND FASTENER HOLES BETWEEN BS 465 AND BS 484. REMOVED CORR AROUND HOLES NR 1, 2, 3, 5, 6, 7, 9 PER SRM 53-01 FIG 1 ORIG MAT .025" PER SRM 53-23-0 FIG 4 REMAIN MAT. 021. REMOVED .004 OUT OF LIMIT. REMAINING .018 LOST .007 TRIMMED AREA 1.5 X 1/1.25 PER SRM 53-05 FIG 1. PERFORMED NDT NO DAMAGE NOTED PER NDT SPM 06-10-01.001 A2700 FABBED DOUBLER INST DOUBLER & FILLER PER DC9 SRM 53-05 FIG 1.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN COMPOSITE FLOOR PANEL 69 CRACKED 5EA PLACES AT FASTENER HOLES ON METAL EXPANSION JOINT. REMOVED AND REPLACED CRACKED METAL EXPANSION JOINT ON MAIN CABIN. COMPOSITE FLOOR PANEL 69 IAW DC-9 SRM 51-30-2. P/N 9957925-109.

Part: DOUBLER — DAMAGED (FLOOR PANEL) · airframe 67,736 hrs · 61,525 cycles

MAIN PAX CABIN RT FLOOR PNL 57 IS MISSING OLD BONDED REPAIR DOUBLER BETWEEN BS 541 AND BS 560. REMOVED PNL FOR DAMAGE. NDT PERFORMED. NO CRACKS NOTED. RECEIVED DOUBLER AND FILLER .032 AND .020 7075 T6 FILLER. FABBED, LOCATED, DRILLED AND DEBURRED IAW DC9 SRM 51-10-2, 4. INSTALLED IAW DC9 SRM 51-10-4. RE-INSTALLED PANEL ON CARD 0590-4020-8M.

Part: ATTACH ANGLE — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

AFT CARGO STATION 1167 BETWEEN L28L-L30 AFT SIDE OF FRAME ATTACH ANGLE HAS CORROSION. ATTACH ANGLE FOUND TO BE OUT OF LIMITS. REMOVED CORRODED ANGLE. NEW ATTACH ANGLE LOCATED DRILLED, TREATED, PRIMED AND INSTALLED. RESTORED ACCESS IAW DC9 SRM 51-30-2, 51-30-5, 51-30-1, 51-10-3, 51-10-4, 53-01 FIG 1.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN PAX CABIN FLOOR PNL 63 FWD END HAS CORROSION AT FASTENER HOLE BS 598. REMOVED CABIN FL/PNL IAW DC-9 SRM 51-30-01. REMOVED CORROSION AND FOUND MATERIAL TO BE OUT OF LIMITS IAW DC-9 SRM 53-01 FIG 1 SH 3. REMOVED DAMAGE 1.125"X 1". FABRICATED AND INSTALLED DOUBLER AND FILLER FROM .020 7075T6. HFEC ISP PER NDT SPM 06-10-01. VERIFIED DAMAGE REMOVED PANEL RE-INSTALLED ON CARD 0590-4020-8M.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN METAL SKIN FLOOR PANEL 99 HAS CORROSION AROUND EDGES, CRACKED AT FASTENER HOLE AND END BROKEN. REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1 SHT 3. FABRICATED AND ASSEMBLED SKIN .025 7075T6 AND HAT CHANNELS S2912282 IAW ER/A 490096-14.

Part: CARGO TRACK — CORRODED (CARGO BAY) · airframe 67,736 hrs · 61,525 cycles

FWD CARGO COMPARTMENT STA 398 TO 598 LT CARGO TRACK TIE DOWN CORRODED. REMOVED TIE DOWN TRACK AND SPLICE FROM FWD CARGO STA 398-598 LT IAW DC9 SRM 51-30-5. RECEIVED NEW TRACK P/N S2922535730 IAW DWG S29225357 FABRICATED LOCATED AND DRILLED IAW DC9 SRM 51-10-2 & 51-10-4. INSTALLED NEW TRACK AND RE-INSTALLED SPLICE IAW DC9 SRM 51-30-1 & 51-30-5.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN METAL SKIN FLOOR PANEL 53 HAS CORROSION AROUND EDGES. REMOVED CORROSION FOUND TO BE OUT LIMIT WITH .025 ORG .010 LOSS AND .015 REMAINING. FABRICATED REPAIR PER SRM 53-01 FIG 4 SHEET 4. MATERIAL.0327075T6 TREATED PRIMED PER SRM 51-10-3. INSTALLED PER SRM 53-01 FIG 4 SHEET 4.

Part: TRACK — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

AFT CARGO STATION 1167 RT TIE DOWN TRACK ATTACH FITTING TO FRAME CRACKED. REMOVED AND REPLACED FITTING IN AFT CARGO COMP AT STA 1167 RT TIE DOWN TRACK IAW DC9 SRM 51-30-5 & 51-20-0. PART NUMBER 5956034-524.

Part: PAN — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

AFT CARGO STATION 1068-1100 DOOR CUTOUT LOWER PAN CORROSION REMOVED AND REPLACED DOOR CUTOUT PAN IAW DC9 SRM 51-30-5, 51-30-2, 51-10-4, 51-20-0. PART NUMBER J0602289 IAW DC9 SRM 53-05 FIG 44 DOOR PAN IN AFT CARGO HAS LOSS OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN METAL SKIN FLOOR PANEL 79 HAS CORROSION AROUND EDGES AND 4EA CRACKS ON SKIN. REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1 SHT 3, FABRICATED AND ASSEMBLED NEW PANEL SKIN .025 7075T 6, 2EA HAT CHANNEL S2912282 AND 1EA STRAP.071 7075T6 IAW ER/A490097-14. APPLIED STENCIL AND PERMANENT REPAIR ID TAG IAW ER/A 490097-14.

Part: STATIC WICK — DAMAGED (ELEVATOR) · airframe 67,736 hrs · 61,525 cycles

LT ELEVATOR OUTBOARD T/E AT STATIC WICK HAS STATIC DISCHARGE DAMAGE IN SEVERAL PLACES TOP AND BOTTOM. CUT OUT DAMAGED AREA UPPER AND LOWER SURFACES .80"X 2.3" IAW SRM 55-01 FIG 4. NDT VERIFIED DAMAGE REMOVED BOTH UPPER AND LOWER SURFACES IAW NDT SPM 06-10-01. FABBED DOUBLERS AND FILLERS FROM .040 7075-T6. AND FABBED STATIC WICK DOUBLER FROM.020" 2024-T3. INSTALLED FILLERS AND DOUBLERS IAW SRM 55-01 FIG 4.

Part: SKIN — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

BETWEEN GEAR DOORS THRU ACCESS PANEL 5501NW LOWER SKIN UPPER SURFACE HAS CORROSION. REMOVED CORROSION ORIGINAL MAT. .060" IAW DWG 9923459. UT INSP IAW NDT SPM 04-00-07 FOUND CORR STILL PRESENT WITH .040" REMAINING. FOUND TO BE OUT OF LIMITS IAW SRM 53-01 FIG 1 AND DWG 9923459. RECEIVED NEW WEB SKIN P/N 9923459-35, INSTALLED NEW SKIN IAW SRM 51-30-2.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 708 RBL-47 RT SIDE CUSP WEB CRACKED. GAINED ACCESS, REMOVED CUSP WEB MULTIPLE FS 693 -753 RBS 44-60 IAW SRM 51-10-4 AND 51-10-2. INSTALLED NEW CUSP WEB P/N 9910151-6 IAW SRM 51-10-4 AND 51-30-5. RESTORED AREA.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 693 RBL 50 RIGHT SIDE CUSP WEB CRACKED 2EA PLACES. REMOVED CUSP WEB AND ATTACHING CLIPS AND SPLICES IAW SRM 51-10-4 REPAIRED CRACKED WEB USING .020 7075-T6 AND .025 7075-T6 IAW DC-9 SRM DC9A-53-010-16-801-663A-A PGS 1-7. RE-INSTALLED REPAIRED CUSP WEB, ATTACHING CLIPS AND SPLICES IAW SRM 51-30-5 AND 51-30-1 P245.

Part: SKIN — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

FUSELAGE EXTERIOR STA 1136 BETWEEN LONGERONS 13-14R SKIN CRACKED. CUT OUT DAMAGE AREA PER DWG SGO9530001. FAB EXTERNAL DOUBLER AND INTERNAL FINGER DOUBLER AND FILLER FROM .025 2024-T3.040 7075-T6.050 SPLICE 2024-T3 .071 707 5-T6 FILLER. INSTALLED EXTERNAL AND INTERNAL DOUBLERS AND FILLERS IAW DWG SG09530001.

Part: SKIN — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

STA 237 1 INCH ABOVE LONG 25L RIVET HOLE CRACKED AT OLD LIGHTNING STRIKE. REMOVED DAMAGE AREA IAW DWG SG09530001. FABRICATED TITANIUM FINGER DOUBLER AND FILLER IAW SRM 51-10-2 AND 51-10-4. INSTALLED DOUBLER AND FILLER IAW DWG SG09530001.

Part: STRUCTURE — CRACKED (ELEVATOR) · airframe 67,736 hrs · 61,525 cycles

HORIZONTAL STAB LT ELEVATOR O/B TIP IS CRACKED. REMOVED LT O/B ELEVATOR TIP END IAW SRM 51-30-2. FABRICATED NEW TIP END FROM .020 7075-T6 PO 1120495 IAW SRM 55-21-0 AND 51-60-0 FIG 1. INSTALLED TIP END IAW SRM 51-30-2.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

FWD SERVICE DOOR JAMB FWD UPPER CORNER HAS CRACK AT FASTENER REPAIR PER 5330-01134-02B. FABRICATED AND INSTALLED 1EA TITANIUM DOUBLER DMS1592 .025", 1EA -9 DOUBLER .090" 2024-T31EA -11 DOUBLE R .063" 2024-T3 AND 1EA FILLER .050" 2024-T3 IAW SRO 9530172. CUT OUT SIZE 3"X2.4", HFEC INSP IAW NDT SPM 06-10-01 VERIFIED DAMAGE REMOVED.

Part: WEB — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

AFT CARGO STA 1060-1108, DOOR CUTOUT LOWER PAN WEB HAS CORROSION. REMOVED CORR ON WEB IAW SRM 53-01 FIG 1. FOUND TO BE OUT OF LIMITS IAW SRM 53-01 FIG 1. REMOVED AND REPLACED WEB P/N 5910158491 IAW SRM 51-30-2,-4, AND -5.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 1136 L8R CRACKED AT FASTENER. REMOVED DAMAGED SECTION OF LONG 8R IAW SRM 53-02 FIG 18. REPLACED SECTION OF LONG AND SPLICES P/N 2777922-4, 7637813-3 IAW SRM 51-30-2 AND 53-02 FIG 18 P106. REQUIRED INSP. COMPLETED PEMCO Q925.

Part: FRAME — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 522 L17L FRAME CRACKED AT FASTENER. CUT OUT DAMAGE 1.5"X 3" AREA. FABBED -32 ANGLE DRILLED AND DEBURRED. REPAIR FROM SR09530095-5. DRILLED AND DEBURRED NEW FILLER PN SR09530095-29. DRILLED AND DEBURRED IAW DC9 SRM 53-01 FIGURE 32 SHEET 4. ALODINED AND PRIMED AND INSTALLED IAW DC-9 SRM 51-30-2 & 51-30-5. INSTALLED ID TAG IAW 900-5-1 NR 4.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

AFT CARGO, STA 1098 BETWEEN L28R-29R INTERCOSTAL HAS CORROSION. REMOVED CORROSION ON INTERCOSTAL IAW SRM 53-01 FIG 1. FOUND TO BE OUT OF LIMITS IAW SRM 53-01 FIG 1. REMOVED AND REPLACED INTERCOSTAL IAW SRM 53-30-2 AND 51-30-5.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

AFT CARGO STA 1088 BETWEEN L28R-29R INTERCOSTAL HAS CORROSION. REMOVED CORR ON INTERCOSTAL IAW SRM 53-01 FIG 1. FOUND TO BE OUT OF LIMITS IAW SRM 53-01 FIG 1. REMOVED AND REPLACED INTERCOSTAL IAW SRM 51-30-2 AND 51-30-5.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

E & E COMPARTMENT STA 200 LEFT LONG 24 LONGERON CRACKED. REMOVED DAMAGED LONGERON AND SPLICE. HFEC INSP AREA WITH NO INDICATIONS NOTED IAW NDT SPM06-10-01. INSTALLED NEW LONGERON AND SPLICE P/N S2777922-3 AND 7637813-3. IAW SRM 51-10-4, 51-30-2 AND 51-30-5. P245. REQUIRED INSP. COMPLETED PEMCO Q910.

Part: SUPPORT ANGLE — CHAFED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

FWD ACC COMPT STA110 RBL 20 LOWER WEB SUPPORT ANGLE CHAFED. BLENDED DAMAGED AREA FROM SUPPORT ANGLE 1 X1 INCH IAW DC9 SRM 53-01 FIG 1 ORIGINAL MAT .093 BLENDED .050 .43 REMAINING FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1 FABRICATED REPAIR DOUBLERS AND INSTALLED IAW DC9 SRM 53-01 FIG 2.

Part: STRAP — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

AFT CARGO LOWER PAN FORWARD O/B STRAP HAS CORROSION. REMOVED CORROSION ON STRAP IAW DC9 SRM 53-01 FIG 1 FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1. REMOVED STRAP IAW DC9 SRM 51-30-5. LOCATED DRILLED & INSTALLED NEW STRAP IAW DC9 SRM 51-30-2 & 51-30-5.

Part: ATTACH FITTING — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

AFT CARGO COMPT AFTER MOVING DOOR PAN WEB FOUND DOOR STOP ATTACH FITTING AT STA 1088 HAS CORROSION. REMOVED CORROSION ON ATTACH FITTING IAW DC9 SRM 53-01 FIG 1 FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1. REMOVED DAMAGED ATTACH FITTING IAW DC9 SRM 51-30-5. LOCATED, DRILLED & INSTALLED NEW ATTACH FITTING IAW DC9 SRM 51-30-5 P245.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 1,849 hrs · 1,625 cycles

MAIN CABIN RT CUSP WEB AT STATION 1060 IS CRACKED. REMOVED DAMAGED AND REPAIRED CRACKED RT CUSP WEB AT STA 1060 IAW DRAWING SG09530019 FABRICATED LOCATED & DRILLED REPAIR DOUBLER & FILLER IAW 51-10-4 REPAIR FABRICATED OUT OF .020 7075T6 IAW SRM 53-13-3. INSTALLED REPAIR & FILLER IAW 51-30-2 TAGGED REPAIR IAW PROCESS STANDARD 900-5-1 NR 4.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

FWD WET AREA STA 200-285 RBL 22 SEAT TRACK HAS CORROSION. REMOVED CORR 1" X 2" AREA ON RBL 22 SEAT TRACK STA 200-285 IAW DC9 SRM 51-10-3 AND ORIG MAT THICKNESS .070 IAW DC9 SRM 51-10-1 FIG 26 SHEET 1 AND 53-23-0 FIG 4 MATL LOSS .020 REMAINING .050 OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1. REMOVE SEAT TRACK IAW DC9 SRM 51-30-1 REC NEW SEAT TRACK FIT. TRIMMED, LOCATED, DRILLED IAW 51-10-4. TREAT & PRIME IAW 51-10-3. INSTALL IAW SRM 51-30-1, 51-30-5.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN METAL SKIN FLOOR PANEL NR 20 HAS CORROSION. REMOVED CORROSION ORIG MATL THICKNESS .025 LOST .007 REMAINING .019 FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1 SHEET 3. ORDERED & RECEIVED NEW FLOOR PNL LOCATED DRILLED NEW PNL IAWDC9 SRM 51-10-4. TREATED & PRIMED NEW PNL IAW DC9 SRM 51-10-3 INSTALLED 2EA NUTPLATES IAW DC9 SRM 51-30-2.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

FWD WET AREA STA 200-265 RBL 44 SEAT TRACK HAS CORROSION. REMOVED CORROSION IAW DC9 SRM 51-10-3, ORG MATL WAS .115 IAW DC9 SRM 53-23-0 REMAINING IS .065 FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1. REMOVED AND REPLACED NEW SEAT TRACK FROM STA 200-265 RBL 44 IAW DC9 SRM 51-30-1 & SRM 51-30-5 P106.

Part: SKIN — GOUGED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

FUSELAGE EXTERIOR STA 908 BETWEEN L20L AND L21L SKIN GOUGED. FABRICATED INTERNAL DOUBLER LOCATED, DRILLED DEBURRED. TREATED & PRIMED IAW DC9 SRM 51-10-3 INSTALLED INTERNAL DOUBLER & REPAIR IAW DC9 DWG SG09530001 & INSTALLED ID REPAIR TAG IAW DELTA PS 900-5-1 NR 4.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

FORWARD WET AREA STA 200-285 LBL 44 SEAT TRACK HAS CORROSION. REMOVED CORROSION FROM SEAT TRACK IAW DC9 SRM 51-10-3 ORG MAT .070 LOSS .021 REMAINING .059 FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1. REMOVED AND REPLACED SEAT TRACK AND SPLICE IAW DC9 SRM 51-30-1, 51-30-5 AND 53-05 FIG 4F SHEET 1. REQUIRED INSPECTION COMPLETED.

Part: CHANNEL — CRACKED (FLOOR PANEL) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN METAL CABIN FLOOR PANEL NR 61, 1 EA HAT CHANNEL CRACKED ON END. CUT OUT CRACKED AREA OF HAT CHANNEL PER DC 9 SRM 53-05 FIG 1. HFEC CHECK COMPLETED DAMAGE REMOVED PER NDT SPM 06-10-01. FABBED LOCATED, DRILLED TREATED & PRIMED NEW HAT SECTION AND SPLICE PER DC 9 SRM 51-10-2, 51-10-4, 51-10-3, AND 53-05 FIG 1. REPAIR WEIGHT 22G PER SCALE H9573 INSTALLED REPAIR & REPAIR TAG PER DC9 SRM 53-05 FIG 1 & 51-30-2 AND DPS 900-5-1.

Part: FRAME — CRACKED (BS 1245) · airframe 67,736 hrs · 61,525 cycles

AFT ACCESSORY CANTED FRAME, STA 1245, STIFFENER CRACKED AT L6R. REMOVED FASTENERS TO GET ACCESS AT CRACKED STIFFENER IAW SRM 51-30-2 STOP DRILLED ENDS OF CRACK IAW SRM 53-01, FIG 2. FABRICATED 2EA REPAIR ANGLES IAW SRM 53-01, FIG 2. INSTALLED REPAIR ANGLES AT STA 1245 AND FASTENERS REMOVED TO HAVE ACCESS IAW SRM 53-01, FIG 2 & 51-30-2. REQUIRED INSPECTION COMPLETED.

Part: SKIN — GOUGED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

FUSELAGE EXTERIOR STA 908 BETWEEN L20R AND L21R SKIN GOUGED. FABRICATED AN INTERNAL REPAIR DOUBLER IAW DC9 DWG SG09530001 TREATED AND PRIMED IAW DC9 SRM 51-10-3 6AL-4V TITANIUM .032. INSTALLED DOUBLER REPAIR IAW DC9 SRM 51-30-2 & DWG SG0953 0001. REQUIRED INSPECTION COMPLETED.

Part: STRUT — CRACKED (CARGO BAY) · airframe 67,736 hrs · 61,525 cycles

FORWARD CARGO COMPARTMENT, STA 226 LT SIDE WALL STRUT CRACK AT LWR END. CUT OUT CRACK AREA. CONTAINED CRACK. HFEC CRACK REMOVED PER NDT SPM 06-10-01. FABRICATED 2EA REPAIR ANGLES 7075T6 .063 7075T6 .050 DRILLED, DEBURRED, ALODINED, PRIMED AND INSTALLED IAW DC9 SRM 53-01 FIGURE 2 SHEET 4.

Part: SHEAR TIE — CRACKED (STA 1151 L14L) · airframe 67,736 hrs · 61,525 cycles

CRACKED SHEAR TIE, STA 1151, L14L. REMOVED CRACKED SHEAR-TIE IAW SRM 51-30-02. RECIEVED NEW SHEAR-TIE. INSTALLED IAW SRM 51-30-05. REQUIRED INSP COMPLETED.

Part: FLOORBEAM — CORRODED (BS 160 LBL 49-52) · airframe 67,736 hrs · 61,525 cycles

FORWARD WET AREA STA 160 LBL 49-52, FLOOR SUPPORT HAS CORROSION. BLENDED CORROSION MATERIAL LOSS OUT OF LIMITS IAW SRM 53-01. REMOVED FLOOR SUPPORT IAW SRM 51-30-02. FABBED NEW SUPPORT IAW SRM 51-10-04. INSTALLED NEW FLOOR SUPPORT IAW SRM 51-30-02. P180.

Part: CARGO TRACK — CRACKED (BS 1088) · airframe 67,736 hrs · 61,525 cycles

AFT CARGO STA 1088 LT TIE DOWN TRACK ATTACH FITTING TO FRAME CRACKED. CUSTOMER FURNISHED PART. LOCATED, DRILLED, DEBURRED IAW SRM 51-10-4. INSTALLED IAW SRM 51-30-5. P106.

Part: FLOORBEAM — CRACKED (BS 636 BL 0-22L) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 636 BETWEEN BL-0 AND LBL-22 FLOOR SUPPORT CRACKED AND HAS CORROSION. REMOVED CRACKED FLOOR SUPPORT AND FABRICATED NEW FROM IAW SRM 53-13-2, FIG 4 LOCATED AND DRILLED IAW SRM 51-10-4. TREATED AND PRIMED IAW SRM 51-10-3 INSTALLED IAW SRM 51-30-5. P180 REQUIRED INSP COMPLETED.

Part: LONGERON — CRACKED (BS 332 L16R) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN, STA 332, L16R, LONGERON CRACKED. R & R L16R IN MAIN CABIN AREA AT STA 229 TO STA 370 IAW SRM 51-30-2 51-30-5 51-20-0 53-02 FIG 18 SHT 1, LONGERON PN S2777922-3-25000, SPLICE CAP PN 7637813-3. REQUIRED INSP COMPLETED.

Part: FLOORBEAM — CHAFED (BS 636 BL 0-22L) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 636 BETWEEN BL-0 AND LBL-22 TOP FLOORBEAM CHAFED. CORRECTED, REMOVED PREVIOUS REPAIR, STAINLESS STEEL STRIP AND FABRICATED NEW IAW SRM 53-05 FIG 20. LOCATED AND DRILLED IAW SRM 51-10-4. TREATED AND PRIMED IAW SRM 51-10-3. INSTALLED IAW SRM 53-05, FIG 20 RII COMPLETED.

Part: CARGO TRACK — CRACKED (BS 1167) · airframe 67,736 hrs · 61,525 cycles

AFT CARGO STA 1167 LT TIE DOWN TRACK ATTACH FITTING TO FRAME CRACKED. REMOVED AFT CARGOSTA 1167 LT TIEDOWN TRACK FITTING RECIEVED CUSTOMER FURN PART, LOCATED, DRILLED, DEBURRED IAW SRM 51-10-4, INSTALLED IAW SRM 51-30-5. P106.

Part: WEB — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

AFT ACCESSORY LT SIDE WEB ABOVE RAIN BOX AFT END CRACKED. CORRECTED, STOP DRILLED CRACK IAW SRM 53-01, FIG 2, SHT 3 FABRICATED AND DRILLED REPAIR DOUBLER IAW SRM 51-10-2 AND 51-10-4 AND 53-01 FIG 2, SHT.3. INSTALLED REPAIR DOUBLER IAW SRM 53-01 FIG 2, SHT.3 P106 REQUIRED INSP COMPLETED.

Part: LONGERON — CRACKED (BS 313 L17L) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 313, L17L CRACKED AT FASTENERS R & R L16L IN MAIN CABIN AREA AT STA 229 TO STA 313 IAW SRM 51-30-2 51-30-5 51-20-0 53-02 FIG 18, SHT 1. LONGERON PN S2777922-3-25000, SPLICE CAP PN 7637813-3. REQUIRED INSP COMPLETED.

Part: FLOOR SUPPORT — DAMAGED (BS 636 LBL 7) · airframe 67,736 hrs · 61,525 cycles

UPON REMOVAL OF FLOOR SUPPORT FOUND A DOUBLE DRILLED HOLE IN FLOOR BEAM AT STA 636, LBL-7, CORRECTED. REMOVED DOUBLER, DRILLED HOLE BY CUTOUT STA 636, LBL-7. FABRICATED ANGLE FROM AND FILLER FROM IAW SRM 53-05, FIG 79A LOCATED AND DRILLED IAW SRM 51-10-4. TREATED AND PRIMED IAW SRM 51-10-3 INSTALLED IAW SRM 53-05, FIG 79A. P180 REQUIRED INSP, COMPLETED.

Part: CUSP WEB — CRACKED (BS 754 RBL 52) · airframe 67,736 hrs · 61,525 cycles

MAIN PASSENGER CABIN STA 754, RBL 52, CUSP WEB IS CRACKED. R & R CUSP WEB, STA 754 TO 794 IAW SRM 51-30-2 AND 51-30-5 AND DWG 9910151 & SG09530019. P106 REQUIRED INSPECTION COMPLETED.

Part: LONGERON — CRACKED (BS 313 L17R) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 313, RT LONG 17 CRACKED. R & R L17R IN MAIN CABIN AREA AT STA 307 TO STA 340 IAW SRM 51-30-2 51-30-5 51-20-0 53-02 FIG 18 SHT, 1 LONGERON PN S2777922-3-25000, SPLICE CAP PN 7637813-3. REQUIRED INSP COMPLETED.

Part: FLOOR PANEL — PUNCTURED (MAIN CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN METAL SKIN FLOOR PANEL NR 73 HAS 1EA PUNCTURED HOLE. CUTOUT PUNCTURED AREA (2.0625" X 1.0625") IAW SRM 53-01, FIG 4 HFEC VERIFIED DAMAGE. REMOVED IAW NDT SPM 06-10-01.001 ORIG MAT .020, 7075T6 IAW SRM 53-23- FIG 5 FABRICATED & LOCATED & DRILLED IAW SRM 53-01, FIG 4 AND 51-10-4. TREATED & PRIMED IAW SRM 51-10-3 INSTALLED IAW SRM 53-01, FIG 4 AND SRM 51-30-2. REQUIRED INSP COMPLETED.

Part: WEB — CRACKED (BS 1209) · airframe 67,736 hrs · 61,525 cycles

AFT ACCESSORY T/H SIDE STA 1209 WEB CRACKED AT LIGHTNING HOLE. STOP DRILLED END OF CRACK IAW SRM 53-01, FIG 2. FABRICATED DOUBLER IAW SRM 53-01, FIG 2. TREATED & PRIMED REP DOUBLER IAW SRM 51-10-3 AND INSTALLED REPAIR DOUBLER AT AFT ACCESSORY T/H SIDE STA 1209 WEB AT LIGHTNING HOLE IAW SRM 51-30-5 AND 53-01, FIG 2. REQUIRED INSP COMPLETED.

Part: FLOOR PANEL — DAMAGED (MAI CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN PAX CABIN FLOOR PANEL NR 61 FWD FASTENERS HOLES ARE CHAFED. BLENDED AREA 6 EA FASTENER HOLES FOUND 5 EA TO BE IN LIMITS & 1 EA TO BE OUT. ORIGINAL MATERIAL .032, REMOVED .015 WITH .017 REMAINING. REMOVED DAMAGE AREA 1.1250 X 2.2500" NDT HFEC VERIFY DAMAGE REMOVED FABBED REPAIR & FILLER TREATED PRIMED INSTALLED IAW SRM 53-01, FIG 1, SHEET 3, 53-01 FIG 4, SHEET 4, 51-10-4, 51-10-3, 51-30-2, & DPS 900-5-1 NO. CORRECTED, REQUIRED INSP COMPLETED.

Part: VANE — DELAMINATED (TE FLAP) · airframe 67,736 hrs · 61,525 cycles

LEFT WING O/B FIXED FLAP VANE LOWER CENTER SURFACE DELAMINATED. REMOVED AND REPLACED LT WING OUTBD FLAP VANE TO BE INSTALLED ON WORKCARD 2750-9807M-LT VANE, FLAP, LT.

Part: PANEL — DAMAGED (BS 970) · airframe 67,736 hrs · 61,525 cycles

MAIN PAX CABIN PANEL NR 91 OTBD SIDE HAS 1EA HOLE APPROX .2500 IN DIA AT DIA AT BS 970. REMOVED DAMAGE AREA .5" X .5" IAW SRM 53-01, FIG 4 FABRICATED FILLER AND DOUBLER IAW SRM 53-01, FIG 4 LOCATED AND DRILLED HOLES ON FILLER AND DOUBLER IAW SRM 51-10-4 TREATED AND PRIMED IAW 51-10-3 INSTALLED FILLER AND DOUBLER IAW SRM 53-01 FIG 4, SHT 4, 51-30-2 DOUBLER WEIGHT IS 8 GRAMS, H9523 DUE 30SEP11. REQUIRED INSPECTION COMPLETED..

Part: STOP FITTING — CRACKED (BS 1187) · airframe 67,736 hrs · 61,525 cycles

STA 1187 LT LOWER STOP FITTING CRACKED. REMOVED LT LOWER STOP FITTING IAW SRM 51-30-5. RECEIVED CUST FURNISHED PART. LOCATED, DRILLED, DEBURRED AND INSTALLED IAW SRM 51-10-4 AND 51-30-5, PN 3917624-517.

Part: FLOOR PANEL — CORRODED (MAIN CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN METAL SKIN FLOOR PANEL NR 70 HAS CORROSION AROUND EDGES. REMOVED CORROSION FROM EDGES. FOUND TO BE WITHIN LIMITS. OUT OF LIMITS AT FWD INBD CORNER IAW SRM 53-01 FIG 1, 53-23-01. DAMAGE REMOVED IAW SRM 53-05 FIG 1. HFEC INSP IAW DC9 NDT SPM 06-10-01. REPAIRED PANELS IAW NDT SPM 06-10-01.001. REMOVED, REPAIRED PANELS IAW SRM 53-05 FIG 1. INSTALLED ID TAG PER DSP 900-5-1 NR 4.

Part: PAN — CORRODED (CARGO DOORWAY) · airframe 67,736 hrs · 61,525 cycles

FORWARD CARGO COMPARTMENT CARGO DOOR CUT OUT LOWER PAN HAS CORROSION. REMOVED FORWARD AND AFT SPLICES AND PAN. TRIMMED, FITTED DRILLED AND DEBURRED NEW PAN PN J060228-3PO 1140346 AND INSTALLED NEW PAN, FWD AND AFT SPLICES IAW SRM 53-05 FIGURE 44 AND 51-30-3 AND 51-30-2.

Part: CUSP WEB — CRACKED (BS 693) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 693 LEFT SIDE CUSP WEB CRACKED APPROX 1 INCH UNDER HORSE SHOE COLLAR. REMOVED DAMAGE SECTION OF CUSP WEB IAW DOCUMENT SG09530019, REPAIR 7007. FABRICATED REPAIR DOUBLER AND REPAIR RING AND INSTALLED IAW DOCUMENT SG09530019 REPAIR 7007 AND SRM 51-30-2.

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN PAX CABIN PANEL NR 91 INBOARD SIDE HAS 1 CRACK APPROX 1/2 INCH LONG AT BS 981. REMOVED DAMAGE 1 1/2 INCH BY 2 INCH IAW SRM 53-01 FIG 4. DAMAGE CONTAINED IAW NDT SPM 06-10-01.001. RECEIVED MAT FOR REPAIR DOUBLER AND FILLER .0207075T6 IAW SRM 53-23-0. LOCATED, DRILLED, DEBURRED AND INSTALLED DOUBLER AND FILLER IAW SRM 53-01 FIG 4, 53-23-0, 51, 30-2 AND INSTALL ID TAG IAW DPS 900-5-1 NR 4.

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN PASSENGER CABIN FLOOR NR 75 CRACKED ON INBD SIDE AROUND FASTENER HOLE. REMOVED DAMAGED AREA IAW SRM 53-01 FIG 4. HFEC INSPECTION IAW NDT SPM 06-10-01. FOUND DAMAGE REMOVED AND REPAIRED PANEL IAW SRM 53-01 FIG 4. INSTALLED ID TAG PER DPS 900-5-1 NR 4.

Part: FLOORBEAM — CRACKED (BS 775 BL 0-22R) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 775 BETWEEN BL-0 AND RBL-22 FLOOR SUPPORT CRACKED AND HAS CORROSION. REMOVED CORROSION FROM FLOOR SUPPORT IAW SRM 51-10-3.ORG MAT THICKNESS .050 IAW SRM 53-13-3. REMOVED.003 REMAINING .047 IN LIMITS IAW SRM 53-01. REMOVED CRACKED FLOOR SUPPORT IAW SRM 51-30-2. FABRICATED SUPPORT IAW SRM 51-10-2. LOCATED AND DRILLED IAW SRM 51-10-4. INSTALLED IAW SRM 51-30-2.

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN METAL SKIN FLOOR PANEL NR 75 CRACKED ON END REMOVED DAMAGE IAW SRM 53-01 FIG 4. HFEC INSPECTION FOUND DAMAGE. REMOVED IAW NDT SPM 06-10-01.001. REPAIRED PANEL IAW SRM 53-01 FIG 4. INSTALLED ID TAG PER DPS 900-5-1 NR 4.

Part: FLOORBEAM — CORRODED (BS 674 BL 0-22R) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 674 BETWEEN BL-0 AND RBL-22 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-3, SUPPORT OUT OF LIMITS. MATERIAL ID .050 2024T3 IAW SRM 53-18-2 SHEET 2 FIG 4. REMOVED .015 REMAINING .035 IAW SRM 53-01 FIG 1 AND 51-10-3. REMOVED SUPPORT AND FABRICATED NEW SUPPORT IAW SRM 51-10-2 TREATED AND INSTALLED IAW SRM 51-30-5.

Part: FLOOR SUPPORT — CORRODED (BS 160-200 RBL44) · airframe 67,736 hrs · 61,525 cycles

FORWARD WET AREA STA 160-200 RBL 44 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION FROM AREA IAW SRM 51-10-3, MATL THICKNESS IS .060 IAW 53-13-1 REMAINING IS .040 FOUND TO BE OUT OF LIMITS IAW SRM 53-01 FIG 1 MATERIAL ID EXTRUSION NR 265479 RECEIVED MATERIAL PO NR 1021992 IAW SRM 53-13-1. FABRICATED LOCATED DRILLED IAW SRM 51-10-4. TREATED AND PRIMED IAW SRM 51-10-3. INSTALLED IAW SRM 51-30-5.

Part: FLOORBEAM — CORRODED (BS 712 RBL 22-44) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 712 BETWEEN RBL-22 AND RBL-44 FLOOR SUPPORT HAS CORROSION AND GOUGED. REMOVED CORROSION AND GOUGES FROM FLOOR SUPPORT STA 712 RBL-22 AND RBL-44 ORG MAT .050 MAT. REMOVED .020 MAT. REMAINING .030 FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1 AND 53-13-3 FIG 11 ITEM 6. FABRICATED NEW FLOOR SUPPORT IAW DC9 SRM 51-10-2, 51 -10-4. INSTALLED FLOOR SUPPORT IAW DC9 SRM 51-30-2. P245.

Part: FLOORBEAM — CRACKED (BS 655 BL 0-22L) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA.655 BETWEEN BL-0 AND LBL-22 FLOOR SUPPORT CRACKED AND HAS CORROSION. REMOVED FLOOR SUPPORT DUE TO CRACK IAW SRM 51-30-2. REMOVED CORROSION IAW SRM 51-10-3, FOUND TO BE WITHIN LIMITS MATERIAL ID .050 2024T3 IAW SRM 53-13-02. REMOVED .002 MATERIAL REMAINING. 48. FABRICATED NEW FLOOR SUPPORT IAW SRM 51-10-2. TREATED IAW SRM 51-10-3. INSTALLED IAW SRM 51-30-5. P202.

Part: INTERCOSTAL — GOUGED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

AFT ACCY COMP - UPON REMOVAL OF TIE DOWN TRACK ATTACH FITTING FOUND INTERCOSTAL ST L28R GOUGED T STA 1166. REMOVED INTERCOSTAL AFT CARGO IAW SRM 51-30-2 & 51-30-05 FABRICATED NEW INTERCOSTAL IAW DWG 5922349. HEAT TREATED INTERCOSTAL ON PEMCO TRAVELER 2431NO1650 LOCATED DRILLED IAW DC9 SRM 51-10-4.

Part: FLOOR SUPPORT — CORRODED (BS 160-200 LBL44) · airframe 67,736 hrs · 61,525 cycles

FORWARD WET AREA STA 160-200 LBL 44 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION FROM FLOOR SUPPORT IAW SRM 51-10-3 ORG MAT .060 IAW DC9 SRM 53-13-1 FIG 11. REMOVED .020 REMAINING .040 FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1. REMOVED OLD FLOOR SUPPORT IAW SRM 51-30-2. FABRICATED NEW FLOOR SUPPORT LOCATED AND DRILLED IAW SRM51-10-2 AND 51-10-4. TREATED AND PRIMED IAW DC9 SRM 51-10-3. INSTALLED NEW FLOOR SUPPORT IAW SRM 51-30-5.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 598 BETWEEN BL-0 AND LBL-22 FLOOR SUPPORT CRACKED. REMOVED FLOOR SUPPORT AT STA 598 BL-0-LBL-22 IAW DC-9 SRM 51-30-2. FABRICATED FLOOR SUPPORT FROM .050 2024-T3 IAW DC-9 SRM 51-10-2 AND 51-10-4 AND 51-10-3 AND INSTALLED FLOOR SUPPORT IAW DC-9 SRM 51-30-2.

Part: ATTACH ANGLE — CRACKED (PYLON) · airframe 1,849 hrs · 1,625 cycles

MAIN CABIN STA 1136 PYLON BULKHEAD AFT SIDE ATTACH ANGLE AT L17L CRACKED. REMOVED ANGLE IAW DC-9 SRM 51-3 AND P IAW DC-9 SRM 51-10-3. INSTALLED ANGLE IAW DC-9 SRM 51-30-5. REQUIRED INSPECTION COMPLETED.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

FORWARD WET AREA STA 200 LBL 1-20 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION FROM FLOOR SUPPORT STA 200 LBL-1-20 IAW DC-9 SRM 51-10-3 ORG MAT .060 IAW DC9 SRM 53-13-1 FIG 11. REMOVED.025 REMAINING .035 FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG 1. REMOVED FLOOR SUPPORT AND FABRICATED FLOOR SUPPORT LOCATED AND DRILLED IAW DC9 SRM 51-10-4 AND 51-10-2. INSTALLED FLOOR SUPPORT IAW DC9 SRM 51-30-2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

FORWARD WET AREA STA 218-294 BL-0 FLOOR SUPPORT HAS CORROSION. REMOVED FLOOR SUPPORT IAW DC-9 SRM 51-30-5. REMOVED CORROSION ORIG MAT .060 REMOVED .020 FROM FLOOR SUPPORT .040 REMAINING. OUT OF LIMITS DC9 SRM 53-01 H337 DEPTH GAUGE CAL NR 03 MAR 11. REMOVED AND INSTALLED SUPPORT IAW DC9 SRM 51-30-5.

Part: FLOOR PANEL — CORRODED (CARGO BAY) · airframe 67,736 hrs · 61,525 cycles

FORWARD CARGO COMPARTMENT FLOOR PANEL NR 3 RIBS HAVE SEVERAL SPOTS OF CORROSION PARTS RACK NR 91C. BLENDED CORROSION ON PANEL NR 3 ORG MAT .063 MEASURED BT TOOL NR L1-117093. FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG 2. RECEIVED PART, DRILLED AND INSTALLED IAW DC9 SRM 51-10-4, 51-30- 01.

Part: SKIN — CRACKED (FLOOR PANEL) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN METAL SKIN FLOOR PANEL NR 59 CRACKED AT FASTENER. REMOVED DAMAGE IAW DC9 SRM 53-05 FIG 1. HFEC INSPECTION FOUND DAMAGE TO BE REMOVED IAW DC9 NDT SPM 06-10-01.001. REPAIRED PANEL IAW DC9 SRM 53-05 FIG 1. INSTALLED ID TAG PER DPS 900-5-1 NR 4 O.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

FORWARD WET AREA STA. 200 LBL 22-44 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION AT FLOOR SUPPORT STA 200 LBL 22-44 IAW DC9 SRM 51-10-3. ORIG MAT .060 IAW DC9 SRM 53-13-1FIG 11. REMOVED .020 REMAINING .040 OUT OF LIMITS IAW DC9 SRM 53-01. REMOVED FLOOR SUPPORT IAW DC9 SRM 51-30-2. FABRICATED NEW FLOOR SUPPORT TREATED AND PRIMED. INSTALLED FLOOR SUPPORT IAW DC9 SRM 51-30-2.

Part: FLOOR SUPPORT — CHAFED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 1136, LBL 3 TO LBL 11 FLOOR SUPPORT CHAFFED 3EA PLACES AT AFT SIDE. REMOVED CHAFE MARKS FROM FLOOR SUPPORT ORIGINAL MAT .050 IAW DC9 SRM 53-01 FIG 1 REMOVED FLOOR SUPPORT AND FABRICATED NEW LOCATED AND DRILLED IAW DC9SRM 51-10-4 AND DC9 SRM 51-10-2 INSTALLED IAW DC9 SRM 51-30-5.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 617 BETWEEN BL-0 AND LBL-22 FLOOR SUPPORT CRACKED AND HAS CORROSION. REMOVED CORROSION FROM FLOOR SUPPORT IAW DC9 SRM 51-10-3 ORIGINAL MAT L .050. REMOVED .006 REMAINING .044 FOUND TO BE IN LIMITS IAW DC9 SRM 53-01 FIG1. REMOVED CRACKED SUPPORT IAW DC9 SRM 51-30-2. RECEIVED MATL FOR NEW FLOOR SUPPORT. LOCATED DRILLED AND TRIMMED NEW SUPPORT IAW DC9 SRM 51-10-2 51-10-4. INSTALLED NEW SUPPORT IAW DC9 SRM 51-32-2, 51-30-5.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 674 BETWEEN BL-0 AND LBL-22 FLOOR SUPPORT CRACKED AND HAS CORROSION. REMOVED AND FABRICATED SUPPORT AT MAIN CABIN STA 674 BETWEEN BL-0 AND LBL-22 IAW 51-10-4. REMOVED CORROSION IAW 51-10-3 ORG MAT.050 IAW DC9 SRM 53-13-2. REMOVED .004 AREA BLENDED 18 BY 1 FOUND TO BE IN LIMITS.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 712 BETWEEN LBL-22 AND LBL-44 FLOOR SUPPORT HAS CORROSION. REMOVED CORROSION FROM FLOOR SUPPORT STA 712 LBL22 ORIGINAL MAT 2024T3 .050 IAW DC9 SRM 53-13-3 FIG 11. REMOVED .021 REMAINING .029 OUT OF LIMITS IAW DC9 SRM 53-01 FIG1. REMOVED FLOOR SUPPORT AND FABRICATED NEW IAW DC9 SRM 51-10-2 LOCATED AND DRILLED IAW DC9 SRM 51-10-4. TREATED AND PRIMED IAW DC9 SRM 51-10-3. INSTALLED FLOOR SUPPORT IAW DC9 SRM 51-30-2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

FORWARD WET AREA STA 237 RBL 1-20 FLOOR SUPPORT HAS CORROSION. EXFOLIATED FOUND TO BE OUT OF LIMITS 100 PERCENT. RECEIVED MAT .050 2024 T3 FABRICATED LOCATED DRILLED DEBURRED IAW DC9 SRM 51-10-2 51-10-4. TREATED AND PRIMED IAW DC9 SRM 51-10-3. INSTALLED IAW DC9 SRM 51-30-5.

Part: FLOORBOARD — CRACKED (FUSELAGE) · airframe 68,643 hrs · 62,328 cycles

FLOOR BOARD PANEL NR 60B HAS BOTTOM GUIDE SUPPORTS WITH SEVERAL CRACKS. REMOVED 10 AREAS DAMAGE AND PREPARED DAMAGE AREA ON PANEL 60B IAW DC-9 MM 53-22-01801-603A-A, IAWDC-9 SRM 51-90-0 PARA 5E. APPLIED REPAIR PLIES AND HOT BONDED AT 250* TO 270* F FOR 90 MIN, USING HEATCON ID NR 03-1062 DUE DATE 09-23-11 IAW DC-9 SRM 51-90-0 PARA 6.0.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

FORWARD WET AREA STA 200 RBL 22-44 FLOOR SUPPORT HAS CORROSION. INTERGRANULAR CORROSION 100 PERCENT MAT LOSS FOUND TO BE OUT OF LIMITS IAW DC9 SRM 53-01 FIG1. REMOVED FLOOR SUPPORT RECIEVED MAT .050 2024T3. FABRICATED LOCATED DRILLED DEBURRED IAW DC9 SRM 51-30-5 51-10-2 51-10-4. TREATED AND PRIMED IAW DC9 SRM 51-10-3. INSTALLED IAW DC9 SRM 51-30-5.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 67,736 hrs · 61,525 cycles

MAIN CABIN STA 775 BETWEEN BL-0 AND LBL-22 FLOOR SUPPORT CRACKED. REMOVED BROKEN FLOOR SUPPORT IAW DC9 SRM 51-30-2. RECEIVED .050 2024T3 PO 1120351 FABRICATED DRILLED DEBURRED NEW FLOOR SUPPORT IAW DC9 SRM 51-10-4 AND 53-13-3 FIG 11. INSTALLED IAW DC9 SRM 51-30-2.

Part: SEAT TRACK — CORRODED (BS 200-285) · airframe 67,736 hrs · 61,525 cycles

FORWARD WET AREA STA 200-285 LBL-22 SEAT TRACK HAS CORROSION. REMOVED CORROSION FROM SEAT TRACK, ORIGINAL MAT. .090, REMOVED.090, 100 PERCENT MAT. LOST, OUT OF LIMITS IAW SRM 53-01 FIG 1. REMOVED SEAT TRACK AND FABRICATED NEW LOCATED AND DRILLED IAW SRM 51-10-4. INSTALLED IAW SRM 51-30-5 AND SRM 53-05 FIG 4.

Part: ANGLE — CRACKED (NR 1 PYLON) · airframe 67,736 hrs · 61,525 cycles

NR 1 PYLON LE PANEL UPPER ATTACH ANGLE REPAIR CRACKED REMOVED CRACKED ANGLE REPAIR IAW SRM 51-30-2. FABRICATED NEW ANGLE REPAIR IAW SRM 54-04 FIGURE 10. LOCATED AND DRILLED IAW SRM 51-10-4. PRIMED IAW SRM 51-10-3. INSTALLED NEW REPAIR ANGLE IAW SRM 51-30-2.

Part: UNKNOWN — ODOR (GALLEY) · airframe 66,039 hrs · 60,028 cycles

CABIN CREW REPORTED A STRONG BURNING SMELL THROUGHOUT CABIN AND DESCRIBED IT AS POSSIBLY ELECTRICAL IN NATURE. CREW SECURED THE GALLEY POWER AND THE FUMES DISSIPATED. FLIGHT CONTINUED TO SCHEDULED DESTINATION WITH GALLEY POWER DEACTIVATED. MX COULD NOT FIND ANY EVIDENCE FOR SOURCE OF FUMES, SMELL, OR SMOKE.

Part: DUCT — CRACKED (RT A/C SYSTEM) · airframe 58,063 hrs · 53,084 cycles

WHILE IN CRUISE FLIGHT AT FL340, AUTOMATIC TEMPERATURE CONTROL WAS LOST AND THE CABIN STARTED CLIMBING AT 700-800 FPM. AN EMERGENCY DESCENT WAS INITIATED WHEN THE CABIN REACHED 10,000 FT. CABIN ALTITUDE MAXED OUT AT 11,500 FT AND THEN BEGAN TO DESCEND. FLIGHT CONTINUED TO DESTINATION AT 10,000 FT MSL AND LANDED WITHOUT ANY OTHER COMPLICATIONS. MAINTENANCE AT DTW FOUND A DUCT CRACKED & OPENED AND REPLACED IT. ALSO REPLACED TEMPERATURE CONTROLLER. LEAK CHECK WAS GOOD AND THE AIRCRAFT HAS RETURNED TO SERVICE.

Part: BRACKET — CRACKED · airframe 50,741 hrs · 46,372 cycles

During M-ck in Atl, while working in the area of sta 69, the right and left brackets were found cracked. Repaired per EA 98-185475.

Part: LIGHT — INOPERATIVE (TAILCONE) · airframe 48,011 hrs · 43,992 cycles

DURING LINE CHECK, FOUND EMERGENCY LIGHTS FOR AFT EVACUATION SLIDE INOPERATIVE. MAINTENANCE CLEANED THE LAMP SOCKETS AND REPLACED THE LAMP IN THE TAIL CONE LIGHT ASSEMBLIES. OPERATIONAL CHECK NORMAL.

Part: AIR DIST — SMOKE (LAVATORY)

DURING CLIMBOUT, FLIGHT ATTENDANTS REPORTED SMOKE IN CABIN ALONG WITH AFT LAVATORY SMOKE DETECTOR ACTIVATED. CREW DECLARED A RED EMERGENCY AND FLIGHT WAS RETURNED TO BUF. AIRCRAFT LANDED WITHOUT INCIDENT. FIRE EXTINGUISHERS IN AFT LAVATORY WERE UTILIZED TO DAMPEN SMOKE. MAINTENANCE INSPECTED AFT LAVATORIES FOR EVIDENCE OF SMOKE, OVERHEATING, AND/OR ELECTRICAL DAMAGE. NO PROBLEMS WERE FOUND.

Part: RESTRICTORS — FAILED (LANDING GEAR)

APPROACHING TO LAND AT MSP, THE NOSE LANDING GEAR DID NOT EXTEND. FLIGHT CREW FOLLOWED COM PROCEDURES AND ACTIVATED THE EMERGENCY LANDING GEAR EXTENSION LEVER, LANDING GEAR EXTENDED SUCCESSFULLY. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED 2 HYDRAULIC RESTRICTORS IN THE NOSE LANDING GEAR WHEEL WELL, OPERATIONAL CHECK NORMAL.

Part: BATTERY PACK — DISCHARGED (COCKPIT)

DURING LINE MAINTENANCE INSPECTION, FOUND COCKPIT EMERGENCY LIGHTS INOPERATIVE. REPLACED BATTERY PACK. OPERATIONAL CHECK NORMAL.

Part: RETRACT MECH — MALFUNCTIONED (NLG)

DURING APPROACH INTO ATL, NOSE LANDING GEAR GREEN LIGHT DID NOT ILLUMINATE AFTER GEAR EXTENSION. CREW RECYCLED GEAR WITH SAME RESULTS. EMERGENCY GEAR EXTENSION PROCEDURES WERE UTILIZED AND AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE PERFORMED FUNCTIONAL CHECK OF NOSE GEAR, NO PROBLEMS WERE FOUND. REPLACED NOSE GEAR RETRACT ACTUATOR AND BUNGEE CYLINDER AS A PRECAUTION. ALSO, RERIGGED CONTROL VALVE AND ALTERNATE GEAR EXTENSION. REPLACED THE LEFT INBOARD GEAR DOOR DUE TO DAMAGE INCURRED ON LANDING.

Part: SPAR — WORN (RT PYLON)

DURING PERIODIC CHECK, RIGHT UPPER AFT PYLON SPAR HOLES 1-22 EXCEED MAXIMUM DIAMETER PER WORK CARD NR 5440-01042. REPAIRED PER EA 99-163231.

Part: LATCH — INOPERATIVE (LT MLG DOOR)

DURING APPROACH, THE LANDING GEAR DOOR OPEN LIGHT ILLUMINATED WITH LANDING GEAR EXTENDED. THE FLIGHT CREW PERFORMED COM REFERENCE 2.32.3, INITIATED A GO-AROUND PROCEDURE, RECYCLED THE LANDING GEAR SYSTEM, AND LANDED AT DTW WITHOUT INCIDENT. NORMAL LANDING GEAR POSITION INDICATIONS WERE ACHIEVED WITH THE LANDING GEAR DOOR LIGHT ILLUMINATED. MAINTENANCE REPLACED THE LEFT MAIN LANDING GEAR UPLOCK ROLLER SPRING ASSEMBLY, THE LEFT AND RIGHT MAIN LANDING GEAR DOOR SKID PADS, AND REPAIRED THE LEFT AND RIGHT MAIN LANDING GEAR DOOR ASSEMBLIES. OPERATIONAL CHECK NORMAL.

Part: BATTERY PACK — DISCHARGED (CABIN)

DURING LINE MAINTENANCE INSPECTION, FOUND SEVERAL OVERHEAD EMERGENCY LIGHTS IN MAIN CABIN INOPERATIVE. REPLACED BATTERY PACK, OPERATIONAL CHECK NORMAL.

Part: BATTERY — DISCHARGED (CABIN)

DURING LINE CHECK, FOUND OVERHEAD EMERGENCY LIGHTS INOPERATIVE AT SEAT ROWS 5 THROUGH 9. MAINTENANCE REPLACED BATTERIES IN BATTERY PACK B5-40. OPERATIONAL CHECK NORMAL.

Part: BATTERIES — DISCHARGED (TAIL COMPT)

DURING LINE MAINTENANCE INSPECTION, FOUND TAIL COMPARTMENT EMERGENCY LIGHTS INOPERATIVE. REPLACED BATTERIES. OPERATIONAL CHECK NORMAL.

Part: LIGHT — INOPERATIVE (CABIN)

DURING FLIGHT, FOUND SEAT 6D PROXIMITY LIGHT INOPERATIVE. MAINTENANCE REPLACED THE LIGHT ASSEMBLY. OPERATIONAL CHECK OK.

Part: BATTERY PACK — DISCHARGED (CABIN)

DURING INSPECTION, THE FORWARD OVERHEAD EMERGENCY LIGHTS WERE FOUND TO BE INOPERATIVE. MAINTENANCE REPLACED THE EMERGENCY LIGHTS BATTERY PACK, OPERATIONAL CHECK OK.

Part: FITTING — CRACKED (RT TE FLAP)

DURING POST FLIGHT INSPECTION, FOUND CRACK IN THE RIGHT OUTBAORD FLAP HINGE RESULTING IN DAMAGE TO THE FLAP, FLAP COVE, FLAP HINGE FITTING FAIRING, AND THE BUTTE DOOR. REPLACED THE FLAP HINGE FITTING PER AMM.

Part: FUSE — BLOWN (CABIN)

DURING LINE MAINTENANCE INSPECTION, FOUND RIGHT FORWARD OVERWING EMERGENCY EXIT AND SEAT MOUNTED LIGHTS BETWEEN ROWS 5 THROUGH 12 INOPERATIVE. REPLACED FUSE. OPERATIONAL CHECK NORMAL.

Part: BATTERIES — DISCHARGED (CABIN)

DURING LINE MAINTENANCE INSPECTION, FOUND RIGHT FORWARD OVERWING EXIT EMERGENCY LIGHT INOPERATIVE. REPLACED BATTERIES IN POWER SUPPLY, OPERATIONAL CHECK NORMAL.

Part: BATTERIES — DISCHARGED (CABIN)

DURING LINE MAINTENANCE INSPECTION, FOUND EMERGENCY LIGHTS BETWEEN ROWS 5 THRU 8 INOPERATIVE. REPLACED BATTERIES, OPERATIONAL CHECK OK.

Part: FUSE — INOPERATIVE (CABIN)

DURING LINE CHECK, FOUND EMERGENCY EXIT LIGHTS INOPERATIVE AT SEAT ROWS 5 THRU 8. MAINTENANCE REPLACED FUSE IN POWER SUPPLY, OPERATIONAL CHECK OK.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

PILOT REPORTED EMERGENCY LIGHTS AT SEAT ROWS 5 THROUGH 8 ILLUMINATED DURING FLIGHT AND WILL NOT TEST PROPERLY. MAINTENANCE REPLACED POWER SUPPLY AND BATTERY PACK AT STATION 711, OPERATIONAL CHECK OK.

Part: FUSE — FAILED (CABIN)

DURING LINE CHECK, FOUND SEAT MOUNTED EMERGENCY EXIT LIGHTS AT SEAT ROWS 5 THROUGH 8 AND AT FORWARD RIGHT OVERWING EXIT INOPERATIVE. MAINTENANCE REPLACED FUSE. OPERATIONAL CHECK OK.

Part: FUSE — BLOWN (CABIN)

DURING LINE CHECK, FOUND SEAT MOUNTED EMERGENCY EXIT LIGHTS AT SEAT ROWS 5 THROUGH 8 AND AT FORWARD RIGHT OVERWING EXIT INOPERATIVE. MAINTENANCE REPLACED FUSE. OPERATIONAL CHECK OK.

Part: FUSE — FAILED (POWER SUPPLY)

DURING LINE CHECK, FOUND EMERGENCY EXIT LIGHTS INOPERATIVE AT SEAT ROWS 5 THROUGH 8. MAINTENANCE REPLACED FUSE IN RIGHT BATTERY PACK POWER SUPPLY. OPERATIONAL CHECK OK.

Part: FUSE — FAILED (CABIN)

DURING LINE CHECK, FOUND FORWARD RIGHT OVERWING EMERGENCY EXIT SIGN INOPERATIVE. MAINTENANCE REPLACED FUSE IN BATTERY CHARGER, OPERATIONAL CHECK OK.

Part: MOTOR — INOPERATIVE (SPOILER ACTUATOR)

DURING CLIMBOUT, FLIGHT CREW NOTICED SMOKE IN THE CENTER PEDESTAL, RIGHT SIDE AREA. FLIGHT CREW FOLLOWED FIRE/SMOKE CHECKLIST. DIVERTED TO MSN AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND SPOILER ACTUATOR MOTOR FAULT. PULLED AND COLLARED SPOILER CONTROL CIRCUIT BREAKERS. PERFORMED PREFLIGHT CHECK OF ALL SYSTEMS, CHECKED OK.

Part: POWER SUPPLY — INOPERATIVE (TAIL CONE)

DURING LINE CHECK, FOUND FLOODLIGHTS IN TAIL CONE FOR HANDLE AND TAIL CONE LIGHT INOPERATIVE. REPLACED POWER SUPPLY, OPERATIONAL CHECK OK.

Part: EVAC SLIDE — LOW PRESSURE (TAIL CONE)

DURING LINE MAINTENANCE INSPECTION, FOUND TAIL EVACUATION SLIDE BOTTLE PRESSURE LOW. REPLACED SLIDE.

Part: LIGHT — INOPERATIVE (TAILCONE)

DURING LINE CHECK, FOUND TAILCONE SPOT LIGHTS INOPERATIVE. REPLACED BULBS AND BATTERIES, OPERATIONAL CHECK OK.

Part: LIGHT — INOPERATIVE (TAILCONE)

DURING LINE CHECK, FOUND TAILCONE EMERGENCY LIGHTS AND EXTERIOR EMERGENCY LIGHTS INOPERATIVE. REPLACED BATTERIES, BULBS AND POWER SUPPLY, OPERATIONAL CHECK GOOD.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

DURING LINE CHECK, FOUND CEILING EMERGENCY LIGHTS OUT AT ROW 20 TO 24. REPLACED POWER SUPPLY AND BATTERIES, OPERATIONAL CHECK OK.

Part: BATTERIES — DISCHARGED (CABIN)

DURING LINE CHECK, FOUND CEILING EMERGENCY LIGHTS INOPERATIVE BETWEEN ROWS 20 TO 24. REPLACED BATTERIES IN POWER SUPPLY, OPERATIONAL CHECK OK.

Part: BATTERIES — DISCHARGED (CABIN)

DURING LINE CHECK, FOUND EMERGENCY EXIT LIGHTS IN AFT STAIRS INOPERATIVE. REPLACED BATTERIES. OPERATIONAL CHECK OK.

Part: FUEL CONTL SYST — OUT OF ADJUST (NR 1 ENGINE)

NR 1 ENGINE WOULD NOT DEVELOP TARGET EPR FOR TAKEOFF. THE TAKEOFF WAS ABORTED AND THE AIRCRAFT RETURNED TO THE GATE. MAINTENANCE TRIMMED THE ENGINE AND SUBSEQUENT RUNUP WAS SATISFACTORY.

Part: EEL WIRE — LOOSE (CABIN)

DURING LINE MAINTENANCE INSPECTION, FOUND OVERHEAD EMERGENCY LIGHTS AT STA 828 INOPERATIVE. FOUND WIRE L1233K18N DISCONNECTED AT GROUND STUD, RECONNECTED WIRE AND OPERATIONAL CHECK OK.

Part: EEL WIRE — LOOSE (CABIN)

DURING LINE MAINTENANCE INSPECTION, FOUND OVERHEAD EMERGENCY LIGHTS AT VENTRAL STAIR DOOR INOPERATIVE. REPLACED BATTERIES IN BATTERY PACK B5-27, NO HELP. FOUND WIRE L800A18N LOOSE AT GROUND STUD 415, SECURED WIRE AND OPERATIONAL CHECK OK.

Part: FLOORBEAM — CORRODED (FS 1136)

DURING H-CHECK, FOUND CORROSION ON THE FS 1136 FLOORBEAM CHORD AT RBL 25. REPAIRED FLOORBEAM (P/N 9912243-55), PER EA 98-103308.

Part: BLKHD WEB — OIL CANNED (LT/RT PYLON)

DURING H-CHECK, FOUND OIL CANNING IN THE PYLON BULKHEAD WEB, LEFT AND RIGHT SIDES. REPAIRED WEB (P/N 9912243), PER EA 98-102600.

Part: CONTROL UNIT — MALFUNCTIONED (NR 2 ENGINE)

ON TAKEOFF ROLL, THE NR 2 ENGINE 'A' LOOP FIRE WARNING ILLUMINATED. THE TAKEOFF WAS ABORTED BELOW 30 KNOTS. THE AIRCRAFT RETURNED TO THE GATE. MAINTENANCE REPLACED THE NR 2 FIRE DETECTION CONTROL UNIT. THE SYSTEM TESTED OK. THE AIRCRAFT RETURNED TO SERVICE.

Part: FUEL CONTROL — FAILED (NR 1 ENGINE)

ON TAKEOFF, THE NR 1 ENGINE EPR AND N1 ROLLED BACK TO IDLE. THE TAKEOFF WAS ABORTED AND THE AIRCRAFT RETURNED TO THE GATE. MAINTENANCE REPLACED THE FUEL CONTROL UNIT AND THE ENGINE WAS RUNUP AND CHECKED OK. AIRCRAFT RETURNED TO SERVICE.