Service difficulty reports · 8
Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model.
SDR MK1Y20201029015Skin · dentedFUSELAGE SKIN, STA 1898, 10 O'CLOCK APPROXIMATELY. DURING MAINTENANCE INSPECTION AT IAI, A DENT WAS FOUND ON THE FUSELAGE SKIN ON THE UPPER TAIL SIDE. THE DENT WAS MEASURED OUT AND IT WAS FOUND THAT THE WIDTH OF THE MINOR AXIS OF THE DENT WAS A=1.23" AND THESDR MK1Y20201029014Skin · damagedFUSELAGE SKIN STA 1266 2.5 BELOW STR-24R. FOUND EXISTING BLEND OUT ON FUSELAGE EXTERNAL SKIN THAT NOT PERMITTED, IAW SRM 53-00-01, FIG 101, ADL1, TABLE I, DETAIL II. PERFORMED NDT INSPECTION FOUND ORIGINAL THICKNESS SKIN 0.209 AND NOMINAL 0.205.SDR MK1Y20201029010Exhaust Cone · dentedENG NR 1 EXHAUST OUTBOARD SIDE BETWEEN NAC STA 317.94-349.236 DENT HAS BEEN CAUSED DURING INSTALLATION OF PRIMARY EXHAUST P/N 015U1547-271, S/N: 0475A, LOCATION OF DENT: B/T 8-9 O`CLOCK. DIMENSIONS: L=11.5" W=1.53" Y=0.07" A/Y=21.
THE DENT IS NOT WITHIN ALLSDR MK1Y20201029007Skin · dentedDURING MAINTENANCE INSPECTION AT IAI FOUND DENT ON THE FUSELAGE SKIN ON THE UPPER TAIL SIDE.SDR MK1Y20201029004Skin · damagedFUSELAGE SKIN, STA 1197+132, STR 39L TO STR 39R. DURING MAINTENANCE INSPECTION AT IAI, AN EXISTING BLEND OUT WAS FOUND. PER NDT REPORT NO U-20-029 THE TOTAL LOSS IN SKIN THICKNESS IS ABOUT 9.8% 9 FROM 0.071 TO 0.064, 0.007 LOSS, WHITHIN SRM LIMITS. HOWEVER,SDR MK1Y20201029003Skin · damagedFUSELAGE SKIN STA 1547 STR-23L. DURING MAINTENANCE INSPECTION AT IAI AN EXISTING BLEND OUT WAS FOUND. PER NDT REPORT NR U-20-030 THE TOTAL LOSS IN SKIN THICKNESS IS ABOUT 11.1% (FROM 0.072” TO 0.064” 0.008 LOSS) WITHIN SRM LIMITS. HOWEVER, THERE ARE SEVERALSDR MK1Y20201029002Door Sill · corrodedFWD CARGO DOOR, LOWER MAIN SILL, OUTER CHORD, STA 500, RBL 44.0. DURING INSPECTION AT IAI, THE CORROSION WAS FOUND ON OUTER CHORD P/N 143T8205-3. THE CORROSION WAS REMOVED, PER SRM 53-00-15, ALLOWABLE DAMAGE. AFTER THE REMOVAL THE MINIMUM THICKNESS IS 0.150SDR MK1Y20201029001Frame · crackedDURING PERFORMANCE OF AD 2012-22-17 AND SB 767-53A0209, FOUND CRACK BY LENGTH OF 0.430" AT FRAME INNER CHORD TRANSITION RADIUS LT STA.903.5 LBL 89.
Other aircraft with N544LA · 1
The FAA can assign a mark to another aircraft once a registration is cancelled. N544LA is registered now to the first aircraft listed.