N841AX

Part: SEAT — WORN (COCKPIT)

DURING TAKEOFF, FIRST OFFICER'S SEAT CAME UNLOCKED AND MOVED AFT. OCCURED AGAIN DURING FLIGHT. REPLACED FIRST OFFICER'S SEAT IAW DC8 MM.

Part: SPAR CAP — CORRODED (HORIZ STAB)

LEFT HORIZONTAL STABILIZER HAS CORROSION ON AFT FLANGE, FORWARD LOWER SPAR CAP. REPAIRED IAW ABX REA D855-24384MR.

Part: SPAR CAP — CORRODED (HORIZ STAB)

LEFT HORIZONTAL STABILIZER HAS CORROSION DAMAGE IN BARREL NUT HOLES IN UPPER FORWARD SPAR CAP. REPAIRED IAW ABX REA D855-24382MR, REV A.

Part: SPAR CAP — CRACKED (WS 26)

NR 3 MAIN TANK ACCESS PANEL NR 506A, LOWER CENTER SPAR IS CRACKED BETWEEN FUEL TRANSFER SLOTS AND FASTENERS AT STATION XRS 26. REPAIRED IAW ABX REA D857-24357MR, REV F.

Part: KEEL BEAM — CORRODED (BS 980)

CORROSION UNDER BEAM, PANEL LKB11 IN LEFT WHEEL WELL, STATION 980. REPAIRED IAW ABX REA D853-24306, REV A.

Part: ANGLE — CRACKED (NR 3 PYLON)

NR 3 ENGINE PYLON SUPPORT ANGLE CRACKED AT AFT OUTBOARD END. REPAIRED PYLON RIB, LOWER SECTION IAW ABX REA-D854-24337MR.

Part: BEAM — CRACKED (FUSELAGE)

AT C-CHECK, CRACKS WERE FOUND IN THE J-BEAM WHICH IS ATTACHED ON THE AFT FACE OF THE AFT PRESSURE BULKHEAD. THE CRACKS ORIGINATE IN THE RADII ADJACENT TO ATTACH BOLTS APPROXIMATELY 1 INCH EACH SIDE OF THE AIRCRAFT CENTERLINE. THE CRACKS APPEAR TO OCCUR UNDER NORMAL OPERATING CONDITIONS AND ARE POSSIBLY CAUSED BY THE COMBINED FORCES OF CABIN PRESSURE AGAINST THE FRONT FACE OF THE BULKHEAD AND TENSION FROM THE 13 FLIGHT CONTROL CABLES WHICH ARE ROUTED THROUGH PULLEYS ATTACHED TO THE J-BEAM. SUBMITTER RECOMMENDS THE FOLLOWING: PERFORM PERIODIC INSPECTIONS OF ALL DC-8 ACFT WITH FLAT AFT PRESSURE BULKHEADS, AND, REPAIR CRACKS PER DC-8 SRM 53-2-5 FIG 26.

Part: BEAM — CRACKED (FUSELAGE)

AT C-CHECK, CRACKS WERE FOUND IN THE J-BEAM WHICH IS ATTACHED TO THE AFT FACE OF THE AFT PRESSURE BULKHEAD. THE CRACKS ORIGINATE IN THE RADII ADJACENT TO ATTACH BOLTS APPROXIMATELY 1 INCH EACH SIDE OF THE ACFT CENTERLINE. OPERATING CONDITIONS ARE POSSIBLY CAUSED BY THE COMBINED FORCES OF CABIN PRESSURE AGAINST THE 13 FLIGHT CONTROL CABLES WHICH ARE ROUTED THROUGH PULLEYS ATTACHED TO THE J-BEAM. SUBMITTER RECOMMENDED THE FOLLOWING: PERFORM PERIODIC INSPECTIONS OF ALL DC-8 ACFT WITH FLAT AFT PRESSURE BULKHEADS, AND, REPAIR CRACKS PER DC-8 SRM 53-2-5 FIG 26.

Part: BEAM — CRACKED (FUSELAGE)

THE C-CHECK, CrACKS WERE FOUND IN THE J-BEAM WHICH IS ATTACHED TO THE AFT FACE OF THE AFT PRESSURE BULKHEAD. THE CRACKS ORIGINATE IN THE RADII ADJACENT TO ATTACH BOLTS APPROXIMATELY 1 INCH EACH SIDE OF THE ACFT CENTERLINE. THE CRACKS APPEAR TO OCCUR UNDER NORMAL OPERATING CONDITIONS AND ARE POSSIBLE CAUSED BY THE COMBINED FORCES OF CABIN PRESSURE AGAINST THE FRONT FACE OF THE BULKHEAD AND TENSION FROM THE 13 FLIGHT CONTROL CABLES WHICH ARE ROUTED THROUGH PULLEYS ATTACHED TO THE J-BEAM. SUBMITTER RECOMMENDED THE FOLLOWING: PERFORM PERIODIC INSPECTION OF ALL DC-8 ACFT WITH FLAT AFT PRESSURE BULKHEADS, AND, REPAIR CRACKS PER DC-8 SRM 53-2-5 FIG 26.

Part: CABLE — OUT OF ADJ (LT COCKPIT)

CAPTAIN'S SEAT DID NOT LOCK IN PLACE AND SLID BACK INADVERTENTLY, DURING CRUISE. ADJUSTED AND LUBRICATED LOCK PIN CABLE.

Part: AIR DISTRIBUTION — ODOR (COCKPIT)

BEFORE PUSH BACK, AFTER DEPARTURE AND IN CRUISE, NOTED STRONG SMELL OF EXHAUST FUMES. ISOLATED CTCS, PULLED AFT CARGO BLOWER C/B'S AND PERFORMED COCKPIT SMOKE REMOVAL PROCEDURES. FUMES SUBSIDED TO MINIMAL. AIRCRAFT LANDED AT FLL WITHOUT FURTHER PROBLEMS. PURGED AIRCRAFT, OPERATED AFT CARGO BLOWER, RECIRCULATING FAN AND SUPPLY HEATING. ALL CHECKED GOOD. NO UNUSUAL ODORS NOTED. SUSPECT AIRCRAFT WAS CONTAMINATED BY EXTERNAL EXHAUST FUMES PRIOR TO TAKEOFF.

Part: TAB — DELAMINATED (LT AILERON)

LEFT INBOARD AILERON TAB FOUND TO BE DELAMINATED. REPLACED HONEYCOMB CORE, SKIN AND INTERNAL DOUBLERS.

Part: TAB — DELAMINATED (ELEVATOR)

ELEVATOR TAB DENTED AND DELAMINATED. REPLACED ALL HONEYCOMB CORE, DOUBLERS AND SKIN.

Part: TAB — DELAMINATED (AILERON)

AILERON TAB DELAMINATED. REPLACED ALL HONEYCOMB CORE, DOUBLERS AND SKIN.

Part: DOOR PAN — CORROSION (C2 DOOR)

DURING C - CHECK INSPECTION, FOUND CORROSION ON THE C-2 DOOR PAN. REPAIRED IAW ABX REA D852-11915-MR.

Part: DOUBLER — CORRODED (BS 852)

DURING C - CHECK INSPECTION FOUND CORROSION ON DOUBLER AT STATION 852 AT XCW 4L AND XCW 6R ON CENTER WING SECTION. REPAIRED IAW ABX REA D857-11890-MR.

Part: ANGLE — CORRODED (BS 810)

DURING C - CHECK INSPECTION DISCOVERED CORROSION ON UPPER WEB ATTACH ANGLE AT STATION 810. REPAIRED IAW ABX REA D853-11911-MR.

Part: DOUBLER — CORRODED (WS 0.00)

DURING C - CHECK INSPECTION, FOUND CORROSION ON UPPER JOINT DOUBLER AT XWC-0.00, STRINGER 4L. REPAIRED IAW ABX REA D857-11900-MR.

Part: ANGLE — CORRODED (BS 857)

DURING C - CHECK INSPECTION FOUND CORROSION ON FLANGE SHEAR WEB ATTACH ANGLE AT STATION 857, LBL 28 AND RBL 28. REPAIRED IAW ABX REA D853-11888-MR.

Part: HYD HOSE — RUPTURED (RT MLG)

ON SHORT FINAL, THE HYDRAULIC FLUID QUANTITY LEVEL DROPPED TO THE STANDPIPE LEVEL AFTER GEAR AND FLAP EXTENSION. LEVEL REMAINED THERE AFTER LANDING. FOUND THE RIGHT GEAR UNLOCK BOGIE TRIM LINE RUPTURED. REMOVED AND REPLACED THE HYDRAULIC LINE IAW DC 8 MM CHAPTER 32. SYSTEM LEAK AND OPS CHECKED GOOD.