N115AM
Registered owner: ALC B379 122019 LLC, DE (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| AEROVIAS DE MEXICO S.A DE C.V - "AEROMEXICO" | Operator | on 2024-12-03 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
7 reports on file, 2021-09-10 – 2022-01-31.
Part: NONE — NONE · airframe 1,457 hrs · 826 cycles
AIRCRAFT RETURNED OF FLIGHT DUE TO DURING CLIMB, THE RED LIGHT OF NOSE LANDING GEAR TURNED ON, WITH THE LANDING GEAR LEVER IN UP POSITION. MAINTENANCE PERSONNEL PERFORMED REVISION, DETECTING THE NLG LOCK PIN WAS FOUND INSTALLED; SO NLG LOCK PIN WAS REMOVED IAW AMM 32-30-00, ALL CORRECT. THE OVERWEIGHT INSPECTION WAS NOT NECESSARY DUE TO THE AIRCRAFT LANDED WITHIN THE MAXIMUM ALLOWABLE LANDING WEIGHT.
Part: NONE — NONE · airframe 1,548 hrs · 882 cycles
DURING PUSH BACK, THE TRACTOR EXCEEDING MAXIMUM TOWING ANGLE WITH BEND OF TOW BAR. MAINTENANCE PERSONNEL PERFORMED REVISION TO NOSE LANDING GEAR IAW 32-33-00-710-802, DETECTING NOSE LANDING GEAR TOW FITTING AND BOLTS BENT AND WARPED; SO THE NOSE LANDING GEAR TOW FITTING AND BOLTS WERE REPLACED IAW AMM 32-21-14; THE NOSE LANDING GEAR SHOCK STRUT PRESSURE WAS VERIFIED IAW AMM 12-15-41-610-802, ALL CORRECT.
Part: FITTING — DAMAGED (ZONE 700) · airframe 1,548 hrs · 882 cycles
DURING PUSH BACK, THE TRACTOR EXCEEDING MAXIMUM TOWING ANGLE WITH BEND OF TOW BAR, MAITENANCE PERSSONNEL PERFORMED REVISION TO NOSE LANDING GEAR, DETECTING NOSE LANDING GEAR TOW FITTING AND BOLTS BENT AND WARPED, THE NOSE LANDING GEAR TOW FITTING AND BOLTS WERE REPLACED, THE NOSE LANDING GEAR SHOCK STRUT PESSURE WAS VERIFIED, ALL CORRECT.
Part: LANDING GEAR — MECHANIC ERROR (ZONE 700) · airframe 1,459 hrs · 827 cycles
THE LIGHTS OF NOSE LANDING GEAR TURNED ON, AIRCRAFT RETURNED OF FLIGHT DUE TO DURING CLIMB, THE RED LIGHT OF NOSE LANDING GEAR TURNED ON, WITH THE LANDING GEAR LEVER IN UP POSITION. MAINTENANCE PERSONNEL PERFORMED REVISION, DETECTING THE NLG LOCK PIN WAS FOUND INSTALLED; SO NLG LOCK PIN WAS REMOVED IAW AMM, 32-30-00, ALL CORRECT. THE OVERWEIGHT INSPECTION WAS NOT NECESSARY DUE TO THE AIRCRAFT LANDED WITHIN THE MAXIMUM ALLOWABLE LANDING WEIGHT.
Part: LANDING GEAR — MECHANIC ERROR (ZONE 700) · airframe 1,459 hrs · 827 cycles
THE LIGHTS OF NOSE LANDING GEAR TURNED ON, AIRCRAFT RETURNED OF FLIGHT DUE TO DURING CLIMB, THE RED LIGHT OF NOSE LANDING GEAR TURNED ON, WITH THE LANDING GEAR LEVER IN UP POSITION. MAINTENANCE PERSONNEL PERFORMED REVISION, DETECTING THE NLG LOCK PIN WAS FOUND INSTALLED; SO NLG LOCK PIN WAS REMOVED IAW AMM, 32-30-00, ALL CORRECT. THE OVERWEIGHT INSPECTION WAS NOT NECESSARY DUE TO THE AIRCRAFT LANDED WITHIN THE MAXIMUM ALLOWABLE LANDING WEIGHT.
Part: NONE — NONE · airframe 920 hrs · 523 cycles
DURING TRANSIT CHECK, IT WAS DETECTED A LIGHTNING STRIKE ON RUDDER SKIN. MAINTENANCE PERSONNEL PERFORMED A LIGHTNING STRIKE CONDITIONAL INSPECTION PHASE 1A, LEVEL EXAMINATION AND PHASE 1B AND II, GENERAL VISUAL INSPECTION AND SYSTEM COMPONENTS IAW AMM 05-51-19-710-801, DETECTING A LIGHTNING STRIKE ON RUDDER SKIN WITH DAMAGES; SO THE RUDDER SKIN WAS PERMANENT REPAIR PERFORMED IAW STRUCTURAL REPAIR DRAWING MEXMR -AMXTR-126-21, MESSAGE BOEING NUMBERS AMX-21-0397-17B, 21B, 22B, 24B AND SRM 51-70-05, PARAGRAPH 4, IF, ALL CORRECT.
Part: NONE — NONE · airframe 615 hrs · 343 cycles
DURING OVERNIGHT CHECK AT MEX STATION, IT WAS DETECTED SEVERAL LIGHTNING STRIKES ON RUDDER SKIN TRAILING EDGE. MAINTENANCE PERSONNEL PERFORMED A LIGHTNING STRIKE CONDITIONAL INSPECTION PHASE 1A, LEVEL EXAMINATION AND PHASE 1B AND II, GENERAL VISUAL INSPECTION AND SYSTEM COMPONENTS IAW AMM 05-51-19-710-801, DETECTING LIGHTNING STRIKE DAMAGES ON RUDDER SKIN TRAILING EDGE FASTENERS AT STA 217 TO 223; ON RH RUDDER SKIN LEADING EDGE FASTENER STA 172; ON VERTICAL STABILIZER LEADING EDGE STA 238 AND STA 223 TO 226; ON RH VERTICAL STABILIZER TRAILING EDGE FIXED PANEL FASTENER STA 178. THE WO´S 7756542, 7756544, 7756548, 7756558, 7756560 AND 7756568 WERE ISSUED TO REPAIR THE DAMAGES DETECTED; SO TIME LIMITED REPAIRS WERE PERFORMED IAW MESSAGE BOEING NUMBER AMX-AMX-21-0397-03B; BALANCE PROCEDURES WERE PERFORMED IAW SRM 51-60-07, PARAGRAPH 5; REPAIR AREAS WERE PAINTED IAW AMM 51-21-00/701; FASTENERS WERE REWORKED IAW SRM55-40-01, ALLOWABLE DAMAGE 1, PARAGRAPH 4G(1); DAMAGES WERE REMOVED IAW SRM 55-30-01, ALLOWABLE DAMAGE 1, PARAGRAPH 2A; HFEC INSPECTION AND UT-PE THICKNESS MEASUREMENT WERE PERFORMED IAW MESSAGE MEXMR-AMXTR-127-21 AND B737 NDTM PART 6, 51-00-00, PROCEDURE 23 AND NDTM PART 4, 51-00-00 PROCEDURE 2; RESISTANCE CHECKS BETWEEN THE FASTENER HEAD AND THE INITIAL STRUCTURE WERE PERFORMED IAW MESSAGE BOEING NUMBER AMX-AMX-21-0399-02B(R1); HEAT DAMAGE EVALUATIONS WERE PERFORMED IAW MESSAGE BOEING NUMBER AMX-AMX-21-0399-02B AND B737 NDTM PART 6, 51-00-00, PROCEDURE 3; DAMAGES WERE REPAIRED AND SEALED IAW MESSAGE BOEING NUMBER AMX-AMX-21-0399-04B; FASTENERS WERE REPLACED IAW SRM 51-40-02, PARAGRAPH 9, ALL CORRECT.