N33202

Part: FITTING — CRACKED (BS 685)

INSPECTION FOUND A 1.5 INCH CRACK IN FRAME FITTING AT BS 685, WL 208, LBL 62. THE FASTENER HOLE WAS COLD WORKED, A REPAIR ANGLE WAS FABRICATED AND INSTALLED IAW ECRA 5310-03346.

Part: FRAME — CRACKED (BS 727)

INSPECTION FOUND A 2 INCH CRACK EXTENDING AFT OF SECOND FASTENER HOLE IN LT BS 727 FRAME CHORD. THE LOWER CHORD SEGMENT WAS REMOVED AND REPLACED IAW CAL WORK CARD JA5310-0163802001.

Part: SKIN — CRACKED (BS 188-251.6)

INSPECTION FOUND CRACKS IN SECTION 41 RT FUSELAGE EXTERNAL SKIN FROM BS 188 TO 251.6, WL 207 TO 234. THE CRACK LENGTHS WERE NOT IDENTIFIED. THE SKIN WAS REPAIRED IAW EA 5310-01188.

Part: FLOORBEAM — CRACKED (BS 675)

INSPECTION FOUND A 1.5 INCH CRACK IN LOWER RADIUS OF FLOORBEAM AT STA 675, BBL 0. THE LOWER T-CHORD WAS REMOVED, A NEW CHORD WAS FABRICATED AND INSTALLED IAW SRM 51-20-2, 51-30-2 AND BOEING DRAWING NR 65-45410.

Part: SKIN — CRACKED (BS 747-727)

INSPECTION FOUND A 1 INCH CRACK IN RT FUSELAGE SKIN AT BS 747 AND AT BS 727A. BOTH CRACKED AREAS WERE CUT OUT, A DOUBLER REPAIR WAS FABRICATED AND INSTALLED OVER EACH CRACK FROM STA 725 TO 790 IAW SRM 53-30-3.

Part: BULKHEAD — CRACKED (BS 178)

INSPECTION FOUND A 6 INCH CRACK IN BULKHEAD BEHIND STIFFENER ON RT SIDE AT STA 178, WL 218. ALSO, A 1 INCH CRACK WAS FOUND AT WL 230.5, RT SIDE. THE CRACKED AREA AT WL 218 WAS REMOVED AND THE CRACK AT WL 230.5 WAS STOP DRILLED IAW SRM 53-10-11. REPAIR DOUBLER, FILLER AND SHIMS WERE FABRICATED AND INSTALLED IAW SRM 53-10-11, 51-10-2 AND 51-30-2.

Part: WIRE — BURNED (ENG ANTI ICE)

SMOKE DEVELOPED FROM BEHIND COCKPIT OVERHEAD PANEL AFTER TURNING ON ENGINE ANTI-ICE WHILE CRUISING AT FL 240 EN ROUTE FROM EWR TO CAE. THE SMOKE CEASED WHEN ANTI-ICE WAS TURNED OFF. THE FLIGHT WAS CONTINUED TO CAE WHERE IT LANDED WITHOUT FURTHER PROBLEMS. MAINTENANCE FOUND BURNT WIRING TO ANTI-ICE MODULE AND AFT OF ANTI-ICE MODULE IN THE COCKPIT OVERHEAD PANEL. THE BURNT WIRING WAS REPLACED. IN ADDITION, THE C146 CIRCUIT BREAKER AND ANTI-ICE VALVE WERE REPLACED. OPERATIONAL CHECKS OF THE SYSTEM WERE GOOD WITH NO OTHER DEFECTS FOUND.

Part: TIRE — FAILED (RT MLG)

A LOUD BANG WAS HEARD AFTER TAKEOFF, WHILE CLIMBING THROUGH 3,000 FEET. THE FLIGHT CONTINUED TO BOS WHERE IT LANDED SAFELY. MAINTENANCE FOUND THAT THE NR 3 TIRE HAD BLOWN RESULTING IN DAMAGE TO RT OUTBOARD SIDE OF WHEEL WELL. THE RT I/B FLAP TRACK FAIRING AND THREE HYDRAULIC LINES WERE ALSO DAMAGED. THE RT O/B SIDE OF WHEEL WELL WAS REPAIRED IAW ECRA 5350-01273. THE RT I/B FLAP TRACK FAIRING WAS REPLACED IAW MM 27-51-141, FIGURE 401. THE THREE DENTED HYDRAULIC LINES WERE REMOVED AND REPLACED. IN ADDITION, THE NR 3 MAIN TIRE ASSEMBLY WAS REPLACED. THE NR 3 BRAKE AND NR 4 MAIN TIRE ASSEMBLY WERE REMOVED AND REPLACED AS A PRECAUTION.

Part: LAMP — INOPERATIVE (RT MLG)

FLT NR 591 - MSP - THE RIGHT MLG GREEN LIGHT DID NOT ILLUMINATED WHEN GEAR WAS EXTENDED FOR LANDING ON APPROACH TO MSP, AND IT WOULD NOT TEST. CHANGING BULBS DID NOT HELP. THE GEAR WAS VISUALLY INSPECTED AND CONFIRMED DOWN AND LOCKED. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE RIGHT MLG DOWN INDICATION LIGHT BURNED OUT. THE INDICATOR LIGHT WAS RELAMPED AND OPERATION CHECKED NORMAL. (M)

Part: STRINGER — CRACKED (RT WING)

GSO - INSPECTION FOUND A 2 INCH CRACK IN RT WING STR 13 AT WBL 92.5 AND A 1.5 INCH CRACK IN SAME STRINGER AT WBL 114. THE STRINGER WAS REPAIRED IAW BOEING DWG 65C34533. (X)

Part: CHORD — CRACKED (BS 727)

GSO - INSPECTION FOUND STA 727 RT CHORD CRACKED AT STR 18A. THE CRACK WAS LOCATED AT BOTH FORWARD AND AFT FASTENERS AND TOTALED 1 INCH IN LENGTH. THE CRACKED CHORD SEGMENT WAS REMOVED AND REPLACED IAW EA 5310-01638 AND BOEING DWG 65C33722. (X)

Part: FRAME — CRACKED (BS 440)

GSO - INSPECTION FOUND A .75 INCH CRACK IN FRAME AT STA 440. THE FRAME WAS REMOVED AND REPLACED IAW SRM 53-10-04 AND SRM 51-30-0. (X)

Part: PCU — LEAKING (AILERON)

FLT NR 1790 - THE B-HYDRAULIC SYSTEM HAD A PARTIAL DROP IN QUANTITY WHILE EN ROUTE TO GSO. THE AIRCRAFT LANDED AT GSO WITHOUT INCIDENT. MAINTENANCE FOUND THE B-SYSTEM AILERON PCU LEAKING. THE AILERON PCU WAS REMOVED AND REPLACED IAW MM 27-11-71 AND OPERATION CHECKED GOOD. (M)

Part: HYD LINE — LEAKING (A-HYD SYST)

EWR - FLT 1477 - THE A-SYSTEM HYDRAULIC QUANTITY DROPPED TO ZERO WHILE ON DESCENT INTO EWR. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND NR 1 ENGINE A-SYSTEM HYDRAULIC PRESSURE LINE IN LEFT WING ABOVE LEFT GEAR LEAKING. THE LINE WAS REPLACED USING FLEX LINE AND A DIP WAS ISSUED TO REPLACE THE FLEX LINE WITH RIGID LINE WITHIN 500 FLIGHTS OR 1200 HOURS, WHICHEVER COMES FIRST. (X)