NATIONAL AIR CARGO GROUP, INC.
Also recorded as: NATIONAL AIR CARGO GROUP, INC., NATIONAL AIRLINES
Accident & enforcement record
Events that happened, regardless of the operator's own reporting. Each links to its public source.
NTSB accidents & incidents
No NTSB accidents or incidents linked to this operator.
FAA enforcement actions
FAA enforcement records haven't been loaded into GroundCheck yet, so none can be shown — a gap in our data, not evidence of a clean enforcement history.
Maintenance disclosure history
Service Difficulty Reports are self-reported maintenance findings. The NUMBER of reports is not a measure of reliability — diligent operators file more, not fewer. These are shown for transparency, not as a negative signal.
1,140 reports on file — showing most recent 50.
SMOKE IN COCKPIT FOR A MOMENT AT 2320Z ASSOCIATED BURNING SMELL (ELECTRICAL) INTERMITTENT FOR REMAINDER OF FLT IN ALL GALLEYS AND COCKPIT.ACCOMPLISHED SDCU (1)(2) BITE TEST REF A330 AMM 26-16-00 AND LOWER DECK COMPARTMENT AVC/COMP REF AMM 26-16-00. FOUND BULK CARGO FAN (282HN) FAULT. OK TO DEFER PER MEL 21-28-08A, DISCREPANCY TRANSFERRED TO DMI 250236942 MAINT ACTION C/W, M4 PLACARD INSTALLED Â CAT-C, DUE 07/1/2026
LEFT UPPER DECK DOOR SLIDE DID NOT FULLY DEPLOY WHEN INADVERTANTLY ACTIVATED. REPLACED DOOR SLIDE ASSEMBLY PER AIRCRAFT MAINTENANCE MANUAL 25-68-01.
L/H WING, L/G, W/W, KEEL BEAM AREA CENTER WEB CHORD CORROSION. (STA1276-1287) REPAIR ACCOMPLISHED IAW SRM AND FAA FORM 8100-9 CASE #06342669 CATEGORY A REPAIR 02JUN2026
EMERGENCY BATTERY PACK INOPERATIVE.
RIGHT BODY LANDING GEAR FORWARD CONDUIT DAMAGED. PERFORMED TIME LIMITED REPAIR PER FLIGHT VEHICLES CONSULTING ENGINEERING ORDER 26068-1.
PUNCTURED FUSELAGE SKIN BETWEEN BS 2742.64 AND BS 2753.10 AND BETWEEN BL0 AND RBL15.0 - ACCOMPLISHED MAJOR REPAIR.
PUNCTURED FUSELAGE SKIN BETWEEN BS 2742.64 AND BS 2753.10 AND BETWEEN LBL 1.57 AND LBL 10.0. ACCOMPLISHED MAJOR REPAIR.
2EA CRACK INDICATON FOUND AT BS2598 BULKHEAD R/H S-11R LONGERON P/N 65B02522-4 PER BOEING SR MUA-MUA-26-0026-22B REPAIR CARRIED OUT PER BOEING 8100-9 DATED MAY 12-2026 AND PER BCS 202603210023-0016
1EA CRACK FOUND AT BS2598 BULK HEAD RHS FRAME SUPPORT HOLE D AS PER BOEING SR MUA-MUA-26-0022-07B REPAIRED CARRIED OUT PER BOEING 8100-9 DATED MAY 12 2026 AND PER BOEING BCS 202603210023-0016
UPPER DECK CEILING LIGHT ASSY INOPERATIVE. REPLACED THE LIGHT ASSY AND OPS CHECKED IAW AMM 33-28-05, FOUND ABNORMAL. REPLACED THE CEILING BATTERY ASSY AND OPS CHECKED IAW AMM 33-51-04 FOUND NORMAL.
1EA CRACK FOUND AT BS2598 BULKHEAD RHS OUTER CHORD HOLE C PER BOEING SR MUA-MUA-26-0022-07B REPAIR CARRIED OUT PER BOEING 8100-9 DATEED MAY, 12,2026.REFF BOEING BCS 202603210023-0016
FCD 744-53-0025 OPEN HOLE NDI INSPECTION FOUND CRACK SIGNALS WHILE PERFORMING STA R/H 1160 AND STRINGER 10R REPAIR CARRIED OUT PER 8100-9 DATED 04/28/2026 REF BOEING COMMUNICATION SYSTEM MESSAGE NUMBERS FOR CASE # 06320986
ONE CRACK FOUND AT FRAME SUPPORT OF 747 SSID REV. H ITEMS FÂ49G ON THE RHS AREA OF THE HINGE FITTING. PER BOEING SR MUAÂMUAÂ26Â0026Â03B. REPAIR CARRIED OUT PER BOEING 8100Â9 DATED MAY 13 2026 AND REF BCS 202603130057Â009
U/D EMEGENCY LIGHT NO ON QTY 3 EA. REPLACED THE LAMP AND OPERATION CHECK PER AMM 33-51-07 FOUND NORMAL
FCD 744-53-0025 OPEN HOLE NDI INSPECTION FOUND CRACK SIGNALS WHILE PERFORMING STA L/H 1160 AND STRINGER 10L REPAIR CARRIED OUT PER BOEING 8100-9 DATED MAY 12, 2026 REF BCS 0632095
OPEN HOLE NDI INSPECTION FOUND CRACK SIGNALS AT 1120 R/H TENSION TIE. REPAIR CARRIED OUT PER 8100=9 DATED 05/08/2026 REFF BOEING COMMUNICATION CASE 063200880
LOCK FASTENER HEAD BROKEN AT TENSION TIE ATTACH FRAME LOCATED AT BS 1220 RT AND STRINGER 10R
0.7" CRACK HAS EXTENDED FROM THE STOP HOLE OF THE PREVIOUS CRACK AT R/H STABILIZER UPPER LOBE DOUBLER. REPAIR COMPLETED PER :CASTLE ID: 202603060065: BOEING 8100-9 ISSUED DATED 04/21/2026. REF ID 202603060065-0011
FINDING 002002 DOCUMENT FCD 744-53-0057-DURING C-CHECK 0.7" CRACK HAS EXTENDED FROM THE STOP HOLE OF THE PREVIOUS CRACK AT R/H STABILIZER UPPER LOBE DOUBLER. REPAIR WAS COMPLTED PER FAA 8100-9 DATED 0/21/2006 ON BOEING SERVICE REQUEST 202603060065-0011.
APPROXIMATELY 30 MINUTES AFTER TOP OF CLIMB, CRUSING AT FLIGHT LEVEL 34,000, EICAS MESSAGE "HYD QTY LOW 1" QUANTITY OBSERVED DECREASING REPIDLY ON HYD SYNOPTIC PAGE. SHORTLY AFTER, QUANTITY AT 0.00. EICAS "HYD PRESS SYS 1". NON NORMAL CHECKLIST ACTIONED. - REPAIRED HYDRAULIC TUBE IN NUMBER 1 ENGINE PYLON.
AFT CARGO INTERCOSTAL CRACK AT STA 1940 TO STA 1960, LBL77 PERFORMED REPAIR IAW SRM 51-70-13 R1
CRACK FOUND ON FORWARD FUSELAGE WEB OF THE NOSE GEAR WELL AT STRINGER 26, BS 160-180 CORRECTIVE ACTION: CAT B. REPAIR PER SRM. REINSPECT DUE AT 33,018 CYCLES
CRACK FOUND ON FORWARD FUSELAGE WEB OF NOSE GEAR WELL AT STRINGER S-26 STA 140-160 WL 205 R&R WEB PART NUMBER 65B01870U243 IAW SRM 51-40-02
OPEN-HOLE NDI INSPECTION FOUND DEFECT SIGNALS WHILE PERFORMING BS 1180LT - 1140 RT.
OPEN-HOLE NDI INSPECTION FOUND DEFECT SIGNALS WHILE PERFORMING STA 1180 L/H STA 1140 R/H. REPAIR COMPLETED PER BCS MESSAGE NUMBER 06316150 INSPECTION THRESHOLD 21,108 TOTAL FLIGHT CYCLES
WHILE IN C CHECK - PERFORMED SURFACE HFEC INSPECTION OF FCD 744-53-0017 R2 A 1 INCH CRACK WAS FOUND ON CHORD BETWEEN S-37R AND S-38R. REPAIR PERFORMED PER BOEING BCS MUA N952CA / 25238 FRAME CRACK BS 1140 RH, RBL 80 / WL 330.
DURING TAXI, EICAS MESSAGE FIRE APU - APU FIRE BOTTLE DISCHARGED. - UPON INSPECTION, NO EVIDENCE OF FIRE. APU PLACED ON A DEFERRED MAINTENANCE ITEM PER MINIMUM EQUIPMENT LIST 49-11-01-01.
DURING A-CHECK AT RKSI, WHILE ACCOMPLISHING T/C 33-050-01-01, FOUND 11 EACH EMERGENCY LIGHT INOPERATIVE. BATTERY ASSY P/N: 2013-1A WAS REPLACED AND DOCUMENTED ON SHARP TECHNICS K W.O. MNT004216 / NR-0013. OPERATIONAL CHECK SATISFACTORY.
THREE INCH CRACK WAS IDENTIFIED IN THE LEFT WING LEADING EDGE UPPER SPLICE PLATE. ACCOMPLISHED MAJOR REPAIR IAW FLIGHT VEHICLES CONSULTING INC. ENGINEERING ORDER CONTROL 25197-3.
DURING SHEDULED C-CHECK VISIT, FOUND LT WINGLET T/E WEDGE LIGHTNING STRIKE DAMAGE. REPAIR HAS BEEN C/W IAW EO 25197-2.
APU GENERATOR #2 HAS SPARKS COMING OUT OF CASE - APU AFTER FIRE INSPECTION IN ACCORDANCE WITH AIRCRAFT MAINTENANCE MANUAL 49-11-00. APU COOLING AIR INTAKE DAMAGED. APU DEFERRED PER MINIMUM EQUIPMENT LIST AND GENERATOR WILL BE REPLACED AT A LATER DATE.
DURING CREW PREFLIGHT CHECKS (AIRCRAFT DOORS OPEN), APU FIRE AND APU AUTOSHUTDOWN DISPLAYED. - FOUND #1 APU GENERATOR MECHANICAL FAILURE CAUSING FIRE IN APU COMPARTMENT. FIRE CONTAINED TO APU COMPARTMENT AND WAS EXTINGUISHED BY CREW PERFORMING APU FIRE EXTINGUISHING PROCEDURE. ALL FIRE AND SMOKE DAMAGE REPAIRED AND APU WAS REPLACED, INCLUDING #1 GENERATOR.
LH EMERGENCY SLIDE RESERVOIR PRESSURE IS BELOW GREEN BAND.
DURING A-CHECK INSPECTION AT SHARP TK LOCATED IN RKSI, A CRACK INDICATION WAS DETECTED AT THE INBOARD UPPER HOLE OF THE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD AT RBL 43.5 BY OPEN-HOLE HFEC. OVERSIZED HOLE AND FREEZE PLUG INSTALLATION PERFORMED IAW BOEING COMMUNICATION SYSTEM MUA-MUA-25-0076-06B.
AIRCRAFT SUSTAINED GROUND DAMAGE TO THE LOWER FUSELAGE SKIN, FORWARD OF THE FORWARD LOWER CARGO DOOR, STA 539.125, BETWEEN STRINGERS S-33R AND S-34R, MEASURING 3.875" LONG AND STA 574.750 BETWEEN STRINGERS S-33R AND S-34R MEASURING 4.875" LONG - ACCOMPLISHED CAT B PERMANENT REPAIR IN ACCORDANCE WITH FLIGHT VEHICLES CONSULTING, INC. ENGINEERING ORDER 25198-1 REVISION IR DATED 10/09/2025. DATA APPROVED ON FAA FORM 8110-3 DATED 10/12/2025 BY R. MANASHI.
DURING A CHECK, UPPER DECK DOOR LT EMERGENCY POWER SYSTEM BATTERY FOUND INOPERATIVE DURING TEST. CARTRIDGE ASSY WAS REPLACED. OPERATIONAL CHECK WAS SATISFACTORY.
DURING A CHECK AT RKSI, WHILE PERFORMING FCD 744-53-0076 R2, 250 FLIGHT CYCLE (FC) REPETITIVE INSPECTIONS FOR SCRIBE LINE FINDINGS ON SB 747-53A2563 LIMITED RETURN TO SERVICE (LRTS) PROGRAM, IT WAS DISCOVERED THAT SKIN PANEL 33L WITH P/N: 65B04135-343 HAVE 02 EACH 0.5 INCH CRACKS. PERMANENT REPAIR WAS ACCOMPLISHED IAW MSG MUA-MUA-25-0057-15B AND BOEINGREPAIRSKETCH_MUA-MUA-25-0057-12C REFERENCE COMMUNICATION SYSTEM MESSAGE NUMBERS FOR CASE #06216788, AND APPROVED ON 8100-9
DURING HEAVY CHECK C AT KSAT FOUND ON UPPER DECK RH DOOR EMERGENCY TEST FAIL (EMERGENCY S W 51541) ,LOW BATTERY VOLTAGE.
DURING PERFORMANCE OF TASK CARD 527100-04-1 (6) / FNC DOOR AND ESCAPE SLIDE CONTROL, REMOVE BATTERY OF AUTONOMOUS STANDBY POWER SUPPLY UNIT (ASPSU) FOR IN-SHOP BATTERY CAPACITY CHECK, ASPSU #2 BATTERY P/N 3214-31 S/N 899440 FOUND FAULTY DURING BITE TEST. REPLACED BATTERY IAW AIRBUS AMM 52-71-36-04 REV 20 PERFORMED, SATIS.
DURING PERFORMANCE OF TASK CARD 527100-04-1 (6) / FNC DOOR AND ESCAPE SLIDE CONTROL, REMOVE BATTERY OF AUTONOMOUS STANDBY POWER SUPPLY UNIT (ASPSU) FOR IN-SHOP BATTERY CAPACITY CHECK, ASPSU #1 BATTERY P/N 3214-31 S/N 862710 FOUND FAULTY DURING BITE TEST. REPLACED BATTERY IAW AIRBUS AMM 52-71-36-04 REV 20 PERFORMED, SATIS.
IN CRUISE, FIRE MN DK AFT EICAS MESSAGE DISPLAYED INTERMITTANTLY - TROUBLESHOOTING IN PROGRESS
FIRE MAIN DECK AFT EICAS MESSAGE DISPLAYED AT THE GATE - REPLACED MULTIPLE MAIN DECK CARGO COMPARTMENT AFT SMOKE DETECTORS.
DURING ACCOMPLISHMENT OF TC 256241-03-1 OPERATION CHECK OF SLIDE-ESCAPE DOOR 3R, ESCAPE SLIDE P/N 7A1509-125 S/N BD0822 FAILED TO DEPLOY WITHOUT INTERVENTION. THE DOOR DAMPER ID CORRECTLY ADJUSTED BUT DAMPENING EFFECT DOES NOT OCCUR. REMOVED AND REPLACED DOOR DAMPER, DAMPENING EFFECT OCCURS. ALL WORK PERFORMED IAW AIRBUS AMM 52-22-14-000-801-A REV 20 AND AIRBUS AMM 52-22-14-400-801-A REV 20.
L/H U/D EMERGENCY DOOR ASSIST BOTTLE PRESSURE ZERO.
ON DESCENT ELECTRICAL BURNING SMELL. STATUS: EE CLNG EXH FAN. PERFORMED EE CLNG EXT FAN GROUND TEST PER AMM 21-58-00, TEST OF. INSPECTED ELECTRONIC EQUIPMENT COMPARTMENT FOR SUSPECTED BURNING AND CHECKED FOR ALL CBS, ALL OK. NO VISIBLE BURNS OR BURNING SMELL NOTICED UPON INSPECT. AIRCRAFT OK FOR SERVICE.
DURING INSPECTION OF DATUM AIRCRAFT PER TASK CARD 57-934-01-01 (NOT AD INSPECTION), CRACKS WERE FOUND ON THE REF. /B/ RIB WEB, REF. /CL RIB UPPER CHORD AND REF. !DI RIB LOWER CHORD OF REF/A/ RHW FIXED TRAILING EDGE RIB INSTL AT WBL 255.692. PLEASE REFER TO FIGURE 1 FOR DETAILS.
DURING AIRCRAFT HEAVY CHECK IN XMV, HAECO MAINTENANCE DISCOVERED 1EA EXISTING REPAIR DOUBLER WAS INSTALLED ON REF. /A/ L1 MED FWD FRAME WEB. THE EXISTING DOUBLER WAS FOUND WORN DAMAGE DUE TO INTERFERENCE WITH THE REF. /C/ DOOR CUTOUT FWD FRAME SUPPORT BRACKET. AFTER REMOVING THE REPAIR DOUBLER, 1EA CRACK WITH 2EA STOP DRILL HOLES WERE FOUND ON DOOR FWD FRAME WEB. SEE FIGURE 1 FOR DETAILS. TO AVOID INTERFERENCE WITH THE SUPPORT BRACKET IN FUTURE. THIS EO PROVIDES INSTRUCTIONS TO TRIM REF/B/ SUPPORT BRACKET LOWER FLANGE AS REQUIRED.
FUEL PANEL WAS INCORRECTLY SET AND CAUSED FUEL TO OVERBOARD THROUGH THE FUEL TANK VENT R/H. PANEL TESTED AND NO DEFECTS NOTED.
DURNING C CHECK IN HAECO SECTION 41 FUSELAGE SKIN, BETWEEN STA 488 AND STA 520 AND BETWEEN 22L AND STR -257 WAS FOUND WITH BLENDOUT DENT DAMAGE
DURING INSPECTION OF DATUM AIRCRAFT, ON SECTION 41 FUSELAGE SKIN, BETWEEN STA 488 AND STA 520 AND BETWEEN STR-22L AND STR-25L, WAS FOUND WITH BLEND OUT AND DENT DAMAGE.
Linked aircraft
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