N126AM

Part: CONTROL PANEL — STUCK (WEATHER RADAR) · airframe 44,474 hrs · 20,789 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO DURING TAXING, THE EICAS MSG RADAR FAIL WAS SHOWN. DURING MX REVISION, THE TEST SWITCH OF THE WEATHER RADAR CONTROL PANEL WAS DETECTED STUCK. THE WEATHER RADAR CONTROL PANEL WAS REPLACED IAW AMM 34-43-91, TESTED CORRECT.

Part: CHARGER — FAILED (MAIN BATTERY) · airframe 43,628 hrs · 20,435 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO DURING TAXING, THE ELEC LIGHT TURNED ON. PERFORMED ELEC SYS AUTO TEST IAW FIM 24-31 TASK 825, DETECTING THE RT AUXILIARY BATTERY CHARGER WITH FAILURE. THE RT AUXILIARY BATTERY CHARGER & AUXILIARY BATTERY WERE REPLACED IAW AMM 24-31-31 & AMM 24-31-11, TESTED CORRECT.

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 42,204 hrs · 19,859 cycles

AIRCRAFT RETURNED TO PLATFORM DUE TO AFTER FLIGHT CONTROLS TEST, THE AUTO SLAT FAIL LIGHT TURNED ON. PERFORMED THE FIM 27-32 TASK 801 PROCEDURE, SHOWING FAILURE CODE 27-31031 & THE FIM 27-32 TASK 809 WAS PERFORMED, NO CONFIRMING THE FAILURE. AS A PRECAUTIONARY ACTION, PERSONNEL PERFORMED A FUNCTIONAL TEST IAW AMM 27-83-00, ALL CORRECT.

Part: SKIN — DAMAGED (TE FLAP) · airframe 41,493 hrs · 19,567 cycles

DURING TRANSIT CHECK, IT WAS DETECTED A PERFORATION IN LOWER SKIN OF RT INTERIOR FLAP & INSPECTION PERSONNEL EVALUATED THE DAMAGE & FOUND A PERFORATION OUT OF LIMITS OF 0.437 INCHES IN DIAMETER AT STATION 57 WBL 85.74 IAW SRM 27-51-00. ACFT WAS SENT TO THE HANGAR & NRC A0222819 WAS ISSUED TO CORRECT THE REPORT. RT WING INBD FLAP WAS REPAIRED IAW SRM 57-53-01 ALLOWABLE DAMAGE 2 PARAGRAPH 4 4 5 B & SRM 51-70-10 REPAIR 2, ALL CORRECT.

Part: CONTROLLER — DAMAGED (AC BAY) · airframe 40,196 hrs · 18,980 cycles

DURING TRANSIT CHECK, IT WAS DETECTED EICAS MSG L TEMP CONTROL INOPERATIVE. PERFORMED REVISION DETECTING THE CB P6-4 POS A1 WAS POPPED SO THE LT TEMPERATURE CONTROL WAS DEFERRED IAW MEL 21-19 CAT C. THE LT PACK CONTROLLER WAS REPLACED IAW AMM 21-51-31, TESTED CORRECT.

Part: LUBRICATION UNIT — DAMAGED (LT ENGINE) · airframe 38,472 hrs · 18,167 cycles

CAPTAIN REPORTED THAT DURING CRUISE, THE LT ENG VIBRATION REACHED 2.1 & THE RT ENG VIBRATION REACHED 0.16. ACFT WAS SENT TO THE HANGAR & MX REPLACED THE LT LUBRICATION UNIT, THE ENG FIRE DETECTOR HARNESS IAW AMM 79-21-01, AMM 26-11-02 & CONDITIONAL INSPECTION TO ACFT IAW AMM 05-51-67 FIGURE 201. CHECK NR 6 & VIBRATION TEST NR 7 WAS PERFORMED IAW MM 72-00-00, BEING WITHIN LIMITS.

Part: LUBRICATION UNIT — LEAKING (LT ENGINE) · airframe 37,867 hrs · 17,886 cycles

DURING 500 HOURS CHECK, DETECTED AN OIL LEAK ON BOTH ENGS. MX PERSONNEL PERFORMED ENG LEAKING INSPECTION IAW AMM 73-21-00 DETECTING OIL LEAK IN THE LUBRICATION UNIT OF BOTH ENGS. THE LT LUBRICATION UNIT WAS REPLACED & THE RT LUBRICATION UNIT SEAL WAS REPLACED IAW AMM 79-21-01 & BOTH ENGS WERE RUN IAW AMM 71-00-00, TEST 3A, ALL CORRECT.

Part: UNKNOWN — ODOR (CABIN) · airframe 37,539 hrs · 17,724 cycles

DURING TRANSIT CHECK, BURNING ODOR WITH NO EVIDENCE OF SMOKE WAS DETECTED IN PAX CABIN. PERFORMED SMOKE OR FUMES IN CABIN CONDITIONAL INSPECTION IAW MM 05-51-56 & FIM 21-00 TASK 806 PROCEDURE, NO ODOR OR SMOKE EVIDENCES WERE FOUND. THE AIR CONDITIONING SYSTEM TEST WAS PERFORMED IAW MM 21-00-05, ALL CORRECT.

Part: BLADES — DAMAGED (LT ENGINE FAN) · airframe 37,118 hrs · 17,506 cycles

ACFT RETURNED DUE TO THE LT ENGINE VIBRATION REACHING 6.0 UNITS. FLIGHT CREW ACCOMPLISHED QRH 7.24 PROCEDURE AND VIBRATION WAS STABILIZED IN 4.0 UNITS. MAINTENANCE DETECTED A CRACK ON FOUR FAN BLADES 1 INCH LONG AND 0.750 INCHES IN DEPTH, CRACKS OUT OF LIMITS IAW AMM 72-00-00. LT ENGINE REPLACED IAW AMM 71-00-02, TESTED CORRECT.

Part: ACTUATOR — LEAKING (TRUST REVERSER) · airframe 34,329 hrs · 16,082 cycles

DURING TRANSIT CHECK, MX DETECTED A HYD LEAK IN THE LOWER HYD ACTUATOR OF THE RT ENGINE REVERSER. MX REPLACED THE LOWER HYD ACTUATOR OF THE RT ENGINE REVERSER IAW MM 78-31-03, TESTED CORRECT.

Part: SKIN — DENTED (FUSELAGE) · airframe 33,647 hrs · 15,744 cycles

DURING TRANSIT CHECK, THE RT SIDE FUSELAGE SKIN WAS DETECTED A HOLE OF 1.125" DIAMETER AND 0.750" DEPTH FROM STA 391 BETWEEN S-23R AND S-24R; THE RT SIDE FUSELAGE SKIN WAS REPAIRED IAW SRM 53-00-01, REPAIR 12, FIGURE 201 AND NDT INSPECTION WERE PERFORMED, NO CRACKS WERE FOUND IAW NDTM PART 6 51-00-00, FIG 23, ALL CORRECT. LIKEWISE, THE SLAT NR 6 L/E WAS DETECTED A DENT OF 16.0" LONG, 8.0"WIDE AND 0.150" DEPTH BETWEEN STATIONS 176 AND 192; THIS DENT WAS FOUND OUT OF LIMITS IAW SRM 57-42-01; SO, THE SLAT NR 6 L/E WAS REPLACED IAW MM 27-81-21, ALL CORRECT.

Part: PANEL — LOOSE (MLG WW) · airframe 36,978 hrs · 12,876 cycles

DURING TRANSIT CHECK, IT WAS DETECTED LACKING THE AFT OTBD WHEEL WELL PANEL 193CL. MX PERSONNEL INSTALLED THE PANEL 193CL IAW SRM 53-51-21, THE GENERAL DIMENSIONS ABOUT SIZE AND WEIGHT OF THE PARTS DEPARTING AIRPLANES IS: SIZE.20.4 X 55.4 (IN) AND WEIGH 1.0 (LB.); LIKEWISE, A DENT WAS DETECTED IN THE LT INBD T/E MAIN FLAP LOWER SKIN ON STA WBL 110 WITH 7.750" LONG, 2.50" WIDTH AND 0.075" DEPTH, IT WAS WITHIN LIMITS IAW SRM 57-53-01 ALLOWABLE DAMAGE PARAGRAPH 4.(3) FIG 103 DETAIL F AND GROUND HANDLING EQUIPMENT HITS AIRPLANE OR PART DEPARTS AIRPLANE CONDITIONAL INSP IAW MM 05-51-59, NO DAMAGES WERE DETECTED.

Part: SWITCH — DAMAGED (MLG) · airframe 30,403 hrs · 14,068 cycles

DURING CLIMB, MAIN LANDING GEAR DID NOT RETRACT. AIR RETURN. CREW ACCOMPLISHED QRH 14.16 PROCEDURE, CONFIRMING FAILURE. DURING MX REVISION, MANUAL EXTENSION ACCESS DOOR SWITCH AND ACTUATOR DETECTED DAMAGED. MANUAL EXTENSION ACCESS DOOR SWITCH AND ACTUATOR REPLACED IAW MM 32-34-11, TESTED CORRECT.

Part: FRAME — CRACKED (LT NACELLE)

FLUORESCENT PENETRANT INSPECTION INDICATED CRACKS IN LEFT FORWARD NACELLE NR 1 FRAME. REPETITIVE DISCREPANCY AS PREVIOUSLY DETAILED AND REPORTED. SUBMITTER STATED POSSIBLE CAUSE REMAINS UNDETERMINED, WOULD SUSPECT ENGINE TORQUE AND VIBRATION AS CONTRIBUTING FACTORS. SUGGESTED TIMED INTERVAL REPETITIVE INSPECTION OF AREA.

Part: FRAME — CRACKED (RT NACELLE)

FLUORESCENT PENETRANT INSPECTION INDICATED CRACKS IN RIGHT FORWARD NACELLE NR 1 FRAME. REPETITIVE DISCREPANCY AS PREVIOUSLY DETAILED AND REPORTED. SUBMITTER STATED POSSIBLE CAUSE REMAINS UNKNOWN, WOULD SUSPECT ENGINE TORQUE AND VIBRATION AS CONTRIBUTING FACTORS. SUGGESTED TIMED INTERVAL REPETITIVE INSPECTION OF AREA.

Part: FRAME — CRACKED (RT/LT NACELLE)

DURING ROUTINE MAINTENANCE CHECKS, CRACKS WERE FOUND ON BOTH ENGINE NACELLE NR 1 FRAMES. ON THE LT FRAME, THE CRACK IS LOCATED ON THE LOWER SIDE OF THE STIFFENING WEB BETWEEN THE TOP OUTBOARD MOUNTING BOLT HOLE AND THE OUTBOARD EDGE OF THE FRAME. THE CRACK IS .45 INCH FROM THE CENTER OF THE BOLT HOLE, AND .225 INCH IN LENGTH. ON THE RT FRAME, THE CRACK IS LOCATED ON THE LOWER SIDE OF THE STIFFENEING WEB BETWEEN THE TOP OUTBOARD MOUNTING BOLT HOLE AND THE OUTBOARD EDGE OF THE FRAME. THE CRACK IS .52 INCH FROM THE CENTER OF THE BOLT HOLE, AND .250 INCH IN LENGTH. SUBMITTER RECOMMMENDED REPLACING BOTH FRAMES AND CONTINUE MONITORING IAW EXISTING MAINTENANCE CHECKS.

Part: START/GENERATOR — FAILED (RT ENGINE)

ON CLIMB-OUT DFW-TUL, RIGHT MAIN GENERATOR FAILED AND CREW NOTICED ELECTRICAL BURNING SMELL IN COCKPIT. CREW ELECTED TO RETURN TO DFW WHERE LANDING WAS MADE SAFELY AND WITHOUT FURTHER INCIDENT. DFW MAINTENANCE REMOVED AND REPLACED THE RIGHT MAIN GENERATOR AND GENERATOR CONTROL UNIT. GROUND CHECKS WERE GOOD AND THE AIRCRAFT WAS RELEASED FOR FURTHER SERVICE. (M)

Part: HYDRAULIC PUMP — FAILED (LT ENGINE)

ATL/MEI - FLT 7768 - EN ROUTE, LOST GREEN HYDRAULICS. CREW DECLARED AN EMERGENCY AND RETURNED TO ATL WITHOUT FURTHER INCIDENT. ATL MAINTENANCE REMOVED AND REPLACED THE LEFT ENGINE DRIVEN HYDRAULIC PUMP. OPERATIONAL AND LEAK CHECKS WERE GOOD, AIRCRAFT RELEASED FOR FURTHER SERVICE. (X)

Part: EEL BATTERY — DISCHARGED (CABIN)

STL - AFT EMERGENCY FLOOR LIGHTING IS INOPERATIVE. MAINTENANCE REPLACED AFT EMERGENCY LIGHTING BATTERY. (Z)

Part: FILTER — DIRTY (LT HYD BAY)

STL - FLT 7478 - LT HYDRAULIC FILTER LIGHT ILLUMINATED. MAINTENACE REPLACED LEFT HYDRAULIC FILTER. GROUND RUN REVEALED NORMAL OPERATION AND LEAK CHECK GOOD. (X)

Part: COMPUTER — MALFUNCTIONED (AVIONICS BAY)

BHM - FLT 7461 - BOTH CAPTAINS AND FIRST OFFICERS EFIS SCREENS WENT BLANK. MAINTENANCE RE-INITIALIZED AHRS COMPUTER. SYSTEM TEST REVEALED NORMAL OPERATION. (Z)

Part: EJECTOR VALVE — FAULTY (LT AFT)

ALO - FLT 7455 - BOTH OUTBOARD HORIZONTAL AND VERTICAL STABILIZER DE-ICE BOOTS FAILED. MAINTENANCE REPLACED DE-ICE EJECTOR VALVE FOR HORIZONTAL AND VERTICAL STABILIZER DE-ICE BOOT, GROUND CHECK OKAY. (X)`