N921R

Part: SKIN — CORRODED (FUSELAGE) · airframe 68,425 hrs · 23,168 cycles

TOP OF LT MAIN LANDING GEAR TOP SURFACE CORRODED APPROXIMATELY 1 X 4 INCHES AT STATION 860, LBL 40 TO LBL 44.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 68,425 hrs · 23,168 cycles

FUSELAGE FRAME DAMAGED AT STATION 1560, L21L.

Part: SKIN — CRACKED (FUSELAGE) · airframe 68,425 hrs · 23,168 cycles

R2 DOOR HAS CRACK INDICATION AT UPPER AFT CORNER FS 1660, L11R.

Part: STRINGER — CRACKED (RT WING) · airframe 68,425 hrs · 23,168 cycles

RIGHT WING LOWER INNER STRINGER CRACKED AT WING STATION X624.

Part: FINGER DOUBLER — CORRODED (FUSELAGE) · airframe 68,425 hrs · 23,168 cycles

RIVET HEAD POPPED FS 200, RT SIDE OF THE AIRCRAFT BELOW THE AUX STATIC PORT IDENTIFIED AS LEVEL 2 CORROSION.

Part: SKIN — CORRODED (FUSELAGE) · airframe 68,425 hrs · 23,168 cycles

FS 12 IN NOSE WHEEL WELL CEILING SKIN BULGING WITH 3 POPPED RIVETS, IDENTIFIED AS LEVEL 2 CORROSION.

Part: FITTING — CRACKED (FUSELAGE) · airframe 68,425 hrs · 23,168 cycles

LONGERON 24 LT AFT BATHTUB FITTING CRACKED AT FS 1690.

Part: FITTING — CRACKED (FUSELAGE) · airframe 68,425 hrs · 23,168 cycles

FITTING CRACKED AFT OF CARGO DOOR AT FS 300 AT CUSP LT SIDE.

Part: PRESSURE PANEL — CORRODED (MLG WW) · airframe 68,425 hrs · 23,168 cycles

FS 980 TO FS 970 TOP SURFACE OF THE RIGHT MAIN LANDING GEAR WELL HAS POPPED RIVETS/BULGING AT ATTACH ANGLE, IDENTIFIED AS LEVEL 2 CORROSION.

Part: FRAME — CORRODED (FUSELAGE) · airframe 68,425 hrs · 23,168 cycles

SEVERAL SMALL AREAS OF CORROSION IN FWD ACCESSORY COMPARTMENT AT AFT BULKHEAD CIRCUMFERENTIAL FS 80 L32L TO L32R. IDENTIFIED AS LEVEL 2 CORROSION.

Part: SKIN PANEL — CRACKED (FUSELAGE) · airframe 67,711 hrs · 22,829 cycles

DURING REPETITIVE INSPECTION OF A/D 2000-20-08 ON LEFT FRONT PAX ENTRANCE DOOR LOWER FORWARD CORNER, VISUALLY DETECTED FUSELAGE SKIN CRACK EXTENDING OUTWARD FROM DOOR RADIUS 1.5 INCH.

Part: OIL FILTER — LEAKING (NR 2 ENGINE) · airframe 67,666 hrs · 22,800 cycles

SHUTDOWN NR 2 ENGINE CLIMBING OUT OF ILG AT FL240 AT 1220Z OIL QUANTITY DROPPED TO 1 GALLON, WINDMILLING OIL PRESSURE 20 PSI.

Part: TRACK — DAMAGED (THRUST REVERSER) · airframe 67,620 hrs · 22,761 cycles

POST FLIGHT INSPECTION NR 2 THRUST REVERSER AND TRANSLATING RING DAMAGED.LOWER T/R TRACK STOP AND ATTACHING HARDWARE MISSING. DOUGLAS SERVICE BULLETIN 78-100 IDENTIFIES THIS PROBLEM.

Part: WIRE — SHORTED (NR 1 ENG DIFF SW) · airframe 67,514 hrs · 22,708 cycles

NR 1 ENGINE OIL PRESSURE WARNING LIGHT ILLUMINATED. PERFORMED PRECAUTIONARY SHUTDOWN NR 1 ENGINE AT 2245Z, OIL PRESSURE 45PSI,OIL TEMP 95 DEGREES C, WINDMILLING OIL PRESSURE 32 PSI.

Part: CRANK ASSY — FRACTURED (LE FLAPS) · airframe 67,473 hrs · 22,678 cycles

FLIGHT CREW REPORTED WING SLOT LIGHT ON WITH FLAPS EXTENDED. FOUND RIGHT AHND EXTENDED LEADING OOUTBOARD SLOT DOOR INOPERATIVE DUE TO FRACTURED AND BROKEN CRANK ASSEMBLY AT STA.XS476

Part: SPAR CAP — CRACKED (RT WING) · airframe 67,301 hrs · 22,571 cycles

DURING REPETITIVE COMPLIANCE WITH A/D 2001-06-02 & S/B 57-90 R5 DETECTED 2 EACH CRACK INDICATIONS IN NON ADJACENT ATTACHMENT HOLES OF THE FORWARD LEG OF THE RIGHT WING FRONT SPAR LOWER CAP. REPAIRED 2 EACH CRACKED HOLES IAW DC-8 S/B 57-90 R5 TABLE 4, CONDITION NR 2 AND STRESS COINED REMAINING HOLES TO CONDITION NR 1,OPTION 2.

Part: SPAR CAP — CRACKED (RT WING)

DURING REPETIVE COMPLIANCE WITH AD AND SB, DETECTED 2 CRACKS AT RT WING FRONT SPAR LOWER CAP, REPAIRED IAW SB. REMAINING HOLES STRESS COINED TO CONDITION 1, OPTION 2.

Part: FASTENER — MISMANUFACTURED (L2 DOOR)

REPAIRED L2 DOOR AT LOWER FORWARD CORNER FS1620 IAW MM.

Part: COMPRESSOR — OVERSERVICED (NR 2 AND 3)

ON TEST FLIGHT, SMOKE IN COCKPIT. FOUND NR 2 AND NR 3 TURBO COMPRESSORS OVERSERVICED. SERVICED PROPERLY IAW MM 21-10-01. (M)

Part: CONTROL CABLE — UNSECURE (LANDING GEAR)

LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF. NO ATTEMPT AT HANDLE LATCH FLIGHT RELEASE. FOUND LANDING GEAR ANTI RETRACTION CABLE NOT SECURE, SECURED SAME LDG GEAR HANDLE AND GEAR OPS NORMAL ON GRD CK.

Part: WHEEL — BROKE OFF (MLG)

ON LANDING, THE NR 1 MLG WHEEL AND TIRE ASSEMBLY BROKE FROM AXLE. TIRE ASSEMBLY ROLLED INTO PARKED EQUIPMENT. AIRCRACFT WAS TOWED TO RAMP FOR INSPECTION. *S/D* REMOVED AND REPLACED NR 1 MAIN WHEEL AND TIRE ASSEMBLY, REPLACED NR 1 MAIN BRAKE ASSEMBLY, REPLACED MLG ANTI-SKID TRANSDUCER AND REPLACED LT MAIN BOGIE ASSEMBLY.

Part: FLOORBEAM — CORROSION (BS 920)

DURING A MAINTENANCE VISIT, FOUND FLOORBEAM CORRODED BEYOND LIMITATIONS IAW DC-8 SRM AT STA 920.57 LEFT. FABRICATED AND INSTALLED REPAIR ANGLE IAW FAA APPROVED COTNEY ENGINEERING SKETCH D02-R04. TREATED AREA IAW DC-8 SRM 51-1-8.

Part: LONGERON — CORRODED (BS 163)

DURING A MAINTENANCE VISIT, FOUND CORROSION DAMAGE ON LONGERON 31 LEFT AT, STA 163 TO STA 170. *S/D* REMOVED CORROSION DAMAGE, FABRICATED AND INSTALLED REPAIR ANGLES IAW FAA APPROVED DER COTNEY ENGINEERING SKETCH D02-R17 AND DC-8 SRM 51-1-8, 51-1-21 AND 53-2-0.

Part: PRESSURE WEB — CORRODED (BS 974)

DURING A MAINTENANCE VISIT, FOUND CORROSION DAMAGE UNDER FINGER DOUBLER ATTACH TO PRESSURE WEB AT, STA 974 AND BL 65 RIGHT SIDE. *S/D* REMOVED CORROSION DAMAGE, FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER COTNEY ENGINEERING SKETCH D02-R16 AND DC-8 SRM 51-1-8, 51-1-20D AND 51-1-21.

Part: BEAM — CORRODED (STA 1754 R/T)

DURING A MAINTENANCE VISIT, FOUND CORROSION DAMAGE TO AFT PRESSURE BULKHEAD VERTICAL BEAM AT STA 1754 RIGHT SIDE, LOWER AFT FACE. *S/D* REMOVED CORROSION DAMAGE, FABRICATED AND INSTALLED REPAIR ANGLES IAW FAA APPROVED DER COTNEY ENGINEERING SKETCH D02-R18. TREATED AREA IAW DC-8 SRM 51-1-8.

Part: SUPPORT — CORRODED (BS 1660)

DURING A MAINTENANCE VISIT, FOUND CORROSION DAMAGE PAST LIMITATIONS ON FLOOR SUPPORT AT, STA 1660 AND BL 33 RIGHT. *S/D* REMOVED DAMAGED SECTION, FABRICATED AND INSTALLED (2 EACH) FILLERS AND DOUBLERS IAW FAA DER APPROVED ENGINEERING SKETCH D02-R15 AND DC-8 SRM 51-1-8 AND 51-1-21.

Part: LONGERON — CRACKED (BS 1270)

DURING A MAINTENANCE VISIT, FOUND CRACK ON LONGERON 34 RIGHT AT, STA 1270. *S/D* REMOVED LONGERON 34R, FABRICATED AND INSTALLED REPAIR SPLICE IAW FAA DER APPROVED COTNEY ENGINEERING SKETCH D02-R09.

Part: SKIN — DAMAGED (BS 296-302)

DURING A MAINTENANCE VISIT, FOUND FUSELAGE OUTER SKIN BENT AND DAMAGED BELOW A PIT DOOR BETWEEN STA 296 TO STA 302. REMOVED DAMAGED SKIN SECTION, FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED DER COTNEY ENGINEERING SKETCH D02-R01.

Part: SKIN — CORRODED (BS 1655-1660)

DURING C-CHECK INSPECTION, FOUND BULGE IN FUSELAGE SKIN LONGERON 28 LT FS 1655 TO 1660.

Part: PRESSURE WEB — CORRODED (BS 923)

DURING C-CHECK INSPECTION, FOUND PRESSURE WEB UPPER SURFACE CORRODED FS 923 BL 0.

Part: ANGLE — CORROSION (BS 857)

DURING C-CHECK INSPECTION, FOUND LT WHEEL WELL UPPER PRESSURE WEB ATTACH ANGLE CORRODED FS 857 BL 41 TO 46 LT. *S/D* REMOVED ATTACHMENT ANGLE, REMOVED CORROSION, FABRICATED AND INSTALLED REPAIR DOUBLER IAW DC-8 SRM 53-2-5 FIGURE 16 SHEET 2. TREATED AREA IAW DC-8 SRM 51-1-8.

Part: ANGLE — CORROSION (WS 41-55)

DURING C-CHECK INSPECTION, FOUND LT WING INBD L/E UPPER SCREW ATTACH HOLES CORRODED AT ATA XFS 41 TO 55. *S/D* REMOVED CORROSION AND FOUND LEADING EDGE UPPER SPAR ATTACHMENT ANGLE DAMAGED BEYOND LIMITATIONS IAW DC-8 SRM. REMOVED ATTACHMENT ANGLE, FABRICATED AND INSTALLED NEW ATTACHMENT ANGLE IAW DC-8 SRM 57-1-0. TREATED AREA IAW DC-8 SRM 51-1-8.

Part: SKIN — CORRODED (BS 83-96)

DURING C-CHECK, INSPECTION FOUND RT FWD WASTE SERVICE DOOR HINGE ATTACH AREA IS CORRODED FS 83 TO 96, LONGERON 27 RT AND 28. *S/D* REMOVED DAMAGED SECTION, FABRICATED AND INSTALLED REPAIR DOUBLER AND FILLER IAW FAA DER COTNEY ENGINEERING SKETCH D02-R10. TREATED AREA IAW DC-8 SRM 51-1-8.

Part: LONGERON — CRACKED (BS 1270)

DURING C-CHECK INSPECTION, FOUND LONGERON 35 RT CRACKED ON SIDE AT FS 1270. *S/D* REMOVED LONGERON 35R, FABRICATED AND INSTALLED NEW LONGERON IAW FAA DER APPROVED COTNEY ENGINEERING SKETCH D02-R09.

Part: RIB — CRACKED (LT TE FLAP)

DURING C-CHECK INSPECTION, FOUND OTBD RIB ON INBD LT FLAP CRACKED IN RADIUS.

Part: SKIN — CORRODED (BS 1060)

DURING C-CHECK, INSPECTION FOUND SKIN UNDER LONGERON 35 RT BETWEEN FRAMES 1060 AND 1080 TO BE CORRODED.

Part: FRAME — CORRODED (BS 1020)

DURING C-CHECK INSPECTION, FOUND FS 1020 FRAME HAS CORROSION ON UPPER FWD FLANGE ABOVE LONGERON 33 AND 34 LT.

Part: SKIN — CRACKED (WS 520)

DURING C-CHECK INSPECTION, FOUND LT WING CENTER OF LEADING EDGE CRACKED AT SCREW HOLE (LOWER SURFACE) STA XFS 520. *S/D* REMOVED DAMAGED AREA, FABRICATED AND INSTALLED REPAIR DOUBLER AND FILLER, IAW FAA DER APPROVED ENGINEERING SKETCH D02-R12, AND TREATED AREA IAW DC-8 SRM 51-1-8.

Part: FLOORBEAM — CORRODED (BS 920)

DURING A MAINTENANCE VISIT, FOUND CORROSION DAMAGE TO FLOORBEAM AT, STA 920 RT. *S/D* REMOVED CORROSION DAMAGE FROM FLOORBEAM, FABRICATED AND INSTALLED REPAIR ANGLES IAW FAA APPROVED COTNEY ENGINEERING SKETCH D02-R04 AND DC-8 SRM 51-1-8, 51-1-20D AND 51-1-21.

Part: SKIN — CRACKED (WS 520)

DURING A MAINTENANCE VISIT, FOUND CRACK ON RIGHT WING UPPER SKIN AT XFS= 520. *S/D* REMOVED DAMAGED SECTION, FABRICATED AND INSTALLED REPAIR DOUBLER AND FILLER IAW FAA DER COTNEY ENGINEERING SKETCH D02-R06, DC-8 SRM 51-1-21 AND 51-3-0.

Part: RIB — CRACKED (RT TE FLAP)

DURING A MAINTENANCE VISIT, FOUND CRACK DAMAGE RIGHT FLAP RIB AT, XFS= 38.

Part: PRESSURE PANEL — CORRODED (BS 920)

DURING A MAINTENANCE VISIT, FOUND CORROSION/CRACKED ON PRESSURE PANEL WEB AT, STA 920, BL 62 LEFT. *S/D* REMOVED CORROSION DAMAGE, FABRICATED AND INSTALLED REPAIR DOUBLERS AND FILLERS IAW FAA APPROVED DER COTNEY ENGINEERING SKETCHES D02-R04 AND D02-R07 AND DC-8 SRM 51-1-8, 51-1-20D AND 51-1-21.

Part: SKIN — CRACKED (WS 461)

DURING A MAINTENANCE VISIT, FOUND LEFT WING LEADING EDGE OF STUB WING UPPER SURFACE SKIN CRACKED AT SCREW HOLE XFS=461. *S/D* REMOVED DAMAGED SECTION, FABRICATED AND INSTALLED REPAIR DOUBLER AND FILLER IAW FAA DER APPROVED ENGINEERING SKETCH D02-R02, AND DC-8 SRM 51-1-21 AND 51-1-8.

Part: SKIN — CORRODED (BS 380)

DURING A MAINTENANCE VISIT, FOUND CORROSION DAMAGE AND CRACK ON INNER SKIN AT, STA 380 TO STA 400 AND BETWEEN LONGERONS 31 RIGHT AND 34 RIGHT. *S/D* REMOVED DAMAGED SECTION, FABRICATED AND INSTALLED REPAIR DOUBLER AND FINGER DOUBLER IAW FAA DER APPROVED ENGINEERING SKETCH D02-R05, AND DC-8 SRM 51-1-21, 51-1-20D AND 51-3-0.

Part: OIL TEMP IND — MALFUNCTIONED (NR 2 ENGINE)

NR 2 ENGINE SHUTDOWN DURING FLIGHT AT 0414Z FOR HIGH OIL TEMP. WINDMILL OIL PRESSURE .23 PSI. ADJUST ACCORDING TO SPEED AS EXPECTED. FUEL TO ENGINE WINDMILLED FROM 0457 - 0500Z. INSPECTED ENGINE IAW EWA JRH PAGE 69-70 OIL TEMP WAS WITHIN LIMITS, NO DEFECTS NOTED. ALSO, INSPECTED NR 2 ENGINE DUE TO WINDMILLING IAW EWA JRH, PG 79. NO DEFECTS NOTED. ENGINE OIL TEMP WAS WITHIN LIMITS.

Part: OIL PRESS IND — MALFUNCTIONED (NR 3 ENGINE)

NR 3 ENGINE OIL PRESSURE INDICATOR READS 100 PSI. PRECAUTIONARY ENGINE SHUT DOWN AND RESTART IN FLIGHT.

Part: ELEVATOR CONTROL — FLUTTER (EMPENNAGE)

ELEVATOR HAS AREO DYNAMIC FLUTTER AS THE AIRSPEED INCREASES, THE FLUTTER RATE INCREASES. AT 300 KTS IAS THE FLUTTER IS FAST ENOUGH THAT IT FEELS LIKE A BUZZ. INSPECTED ELEVATOR SYSTEM IAW MM CHAPTER 27-40-0, NO DEFECTS NOTED, ELEVATOR SYSTEM OPS CHECK GOOD.

Part: DAMPER UNIT — MALFUNCTIONED (LT/RT ELEVATOR)

ELEVATOR HAS BUFFETING AS AIRSPEED INCREASES. WHEN THE AIRPLANE IS BANKED AND ELEVATOR BACK PRESSURE IS APPLIED, BUFFET INCREASES, ON FINAL APPROACH FOR LANDING, FULL FLAPS, SPEED 160KTS BUFFETING IS ALSO FELT IF ELEVATOR BACK PRESSURE IS APPLIED. NOTE: PTC ON OR OFF HAS NO EFFECT. WITH THE BUFFET THERE IS AN UNEXPLAINED HARD INPUT TO THE ELEVATOR, USUALLY NOSE DOWN. CONTROL YOKE USUALLY MOVES 3 TO 5 FORWARD. REMOVED AND REPLACED BOTH LEFT AND RIGHT HAND ELEVATOR DAMPER UNITS. LEAK AND OPS CHECK GOOD IAW MM 27-30-5.

Part: FITTING — PULLED LOOSE (NR 2 ENGINE)

SHUTDOWN NR 2 ENGINE DUE TO LOSS OF OIL QUANTITY AND PRESSURE. WINDMILLED FOR 62 MIN WITH ZERO OIL PRESSURE. MAINTENANCE PREPPED AIRCRAFT FOR THREE ENGINE FERRY TO BDL FOR ENGINE REMOVAL. FOUND OIL FILTER HOUSING FITTING PULLED OUT OF HOUSING.

Part: FIRE WARNING — DEFECTIVE (NR 2 ENGINE)

EINN/KORD - FLT 9123 - HAD INTERMITTENT FIRE WARNING ON NR 2 ENGINE DURING CRUISE. KORD MAINTENANCE REMOVED AND REPLACED NR 2 ENGINE FIRE WARNING AMPLIFIER, REPLACED WIRES FROM AMPLIFIER TO NR 2 ENGINE PYLON BOX. SYSTEM OPS CHECKED GOOD. (X)

Part: FIRE LOOPS — DEFECTIVE (NR 2 ENGINE)

KDFW/KDAY - FLT 021 - HAD A FIRE WARNING ON NR 2 ENGINE AT TOP OF CLIMB WHEN REDUCING POWER TO CRUISE. WARNING WAS INTERMITTENT AND SHORT. KDAY MAINTEANNCE REPLACED UPPER FORWARD AND AFT FIRE LOOPS. REPAIRED TWO WIRES AND REPLACED CANNON PLUG ON AFT LOOP. SYSTEM OPS CHECKED GOOD.

Part: FIRE LOOP — DEFECTIVE (NR 2 ENGINE)

KDAY/KDFW - FLT 022 - ON DESCENT INTO KDFW, GIT A FIRE WARNING ON NR 2 ENGINE. PULLED THROTTLE BACK TO FLIGHT IDLE, LIGHT WENT OUT, BUT BELL WOULD NOT TEST. SHUT ENGINE DOWN ON DESCENT. KDFW MAINTENANCE REPLACED NR 2 LOWER FIRE LOOP. LEAK CHECKED ALL PNEUMATIC DUCTS AND LINES FOR LEAKS. CHECKED ENGINE FOR CRACKS. FOUND LOWER LOOP DAMAGED BY ENGINE COWL-LOOP WOULD SHORT WHEN FLEXED. SYSTEM OPS CHECKED GOOD.

Part: CONNECTOR — LOOSE (NR 2 ENGINE)

MOMENTARY FIRE WARNING ON NR 2 ENGINE. PULLED THROTTLE BACK. TESTED FIRE WARNING. NO TEST. SHUT NR 2 ENGINE DOWN. MAINTENANCE RE-SECURED NR 2 ENGINE FIRE WARNING LOOP CANNON PLUG. SYSTEM OPERATIONAL CHECKED GOOD.

Part: FIRE LOOP — GROUNDED (NR 2 ENGINE)

ON CLIMBOUT, THE NR 2 ENGINE GOT A FIRE WARNING. REDUCED POWER AND FIRE WENT OUT, FIRE WARNING DID RESET. MAINTENANCE AT CYYZ FOUND NR 2 FIRE LOOP GROUNDED OUT. REMOVED AND REPLACED LOWER FIRE WARNING HARNESS. SYSTEM OPS CHECKED GOOD. (W)

Part: LONGERON — CORRODED (FS 680)

DURING C-CHECK, FOUND CORROSION ON LONGERON 31 LEFT FS 680 IN MID-SHIP ACCESSORY COMPT. REMOVED DAMAGED AREA OF LONGERON, FABRICATED REPAIR AND SPLICES. INSTALLED IAW DER APPROVED COTNEY ENGINEERING SKETCH SKA 94190-5.

Part: FRAME — MISDRILLED (FS 540)

DURING C-CHECK, FOUND A HOLE DRILLED IN FRAME RADIUS AT CUSP ATTACH FITTING FS 540 RT. FABRICATED AND INSTALLED REPAIR IAW DER APPROVED COTNEY ENGINEERING SKETCH SKA 94190-4.

Part: FRAME — CORRODED (FS 1240)

DURING C-CHECK, FOUND FRAME CORRODED FS 1240 LONGERON 34 LEFT TO 31 RIGHT. CUT OUT DAMAGED AREA. FABRICATED AND INSTALLED REPAIR IAW DER APRROVED ENGINEERING SKETCH SKA 94190-3. (X)

Part: PLATING — CORRODED (FS 1220-1240)

DURING C-CHECK, FOUND INNER SKIN CORRODED IN C-PIT, FS 1220 TO FS 1240 AT LONGERONS 31 RIGHT TO 35 LEFT. OUTER FUSELAGE SKIN HAD TO BE CUT FOR ACCESS TO CORROSION. REMOVED CORROSION. FABRICATED STRAPS, FILLERS, AND DOUBLERS. INSTALLED IAW DER APPROVED COTNEY ENGINEERING SKETCH SKA 94190-9.

Part: NOSE COWL — CRACKED (STA YN86.9)

DURING C-CHECK, FOUND TRAILING EDGE OF NR 1 ENGINE COWL CRACKED AT 2 O'CLOCK POSITION BY ANTI-ICE TUBE. FABRICATED AND INSTALLED REPAIR IAW SRM 71-5-2 PG 314 AND DER APPROVED COTNEY ENGINEERING SKETCH SKA 94190-1.

Part: FLOOR TRACK — WORN (CARGO COMPT)

DURING C-CHECK, FOUND FLOOR TRACK WORN AFT COMP 3 BL 45.500 RIGHT 2 EA PLACES. CUT OUT DAMAGED TRACK. FABRICATED NEW TRACK SECTION IAW DER APPROVED COTNEY ENGINEERING SKETCH SKA 94190-10 AND INSTALLED IAW SRM 53-2-3.

Part: FRAME — MISDRILLED (FS 1560)

DURING C-CHECK, FOUND FRAME FITTING SHIM AT CUSP HAD COROSION. FRAME HAD SURFACE CORROSION AND HOLE DRILLED IN RADIUS FS 1560 RIGHT. REMOVED CORROSION. REMOVED AND REPLACED FITTING. FABRICATED AND INSTALLED FRAME REPAIR IAW DER APPROVED COTNEY ENGINEERING SKETCH SKA 94190-4.

Part: CUSP — CORRODED (FS 1365)

DURING C-CHECK, FOUND CORROSION BETWEEN RT LOWER CUSP AND WEB F/S 1365 RT. CUT OUT DAMAGED AREA. FABRICATED AND INSTALLED REPAIR IAW DER APPROVED COTNEY ENGINEERING SKETCH SKA 94190-8.

Part: DOUBLER — CUT (BS 80-95)

DURING C-CHECK, FOUND CORROSION UNDER FINGER DOUBLER FS 80 TO FS 95 AT LONGERON 31 RIGHT. EXISTING REPAIR STRAP HAD TO BE CUT FOR ACCESS. CUT STRAP AND PEELED BACK FUSELAGE SKIN. REMOVED CORROSION UNDER FINGER DOUBLER. TREATED AND PRIMED AREA. REINSTALLED SKIN AND STRAP WITH SPLICE DOUBLER IAW DER APPROVED COTNEY ENGINEERING SKETCH SKA 94190-6.

Part: DOUBLERS — CORRODED (FS 380-400)

DURING C-CHECK, FOUND CORROSION ON AND UNDER INTERNAL DOUBLER AT FS 380 TO FS 400 AT LONGERONS 35 LEFT TO 36. CUT AND REMOVED SECTION OF INTERNAL DOUBLER. REMOVED CORROSION AND TREATED AREA. FABRICATED NEW SECTION OF INTERNAL DOUBLERS AND EXTERNAL DOUBLER. INSTALLED IAW DER APPROVED COTNEY ENGINEERING SKETCH SKA 94190-7.

Part: FLOOR BEAM — CORRODED (FS 1702)

DURING C-CHECK, FOUND FLOOR BEAM SUPPORT CORRODED BEYOND LIMITS, COMPARTMENT 18 BL 24.750 RIGHT FS 1702. CUT OUT DAMAGED AREA. FABRICATED AND INSTALLED REPAIR IAW DER APPROVED COTNEY ENGINEERING SKETCH SKA 94190-2.