N26SW
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
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.
18 reports on file, 1995-06-24 – 1997-09-08.
Part: FLOOR BEAM — CRACKED (BS 685)
FLOOR BEAM CRACKED, STA 685, STR 62R. REPAIRED PER DALFORT AVIATION XEA NR X2-53-180 REV 1 DATED 7-18-97. APPROVAL DATA: FAA FORM 8110-3 DATED 7-29-97.
Part: STRINGER — CRACKED (BS 344)
ONE EACH ATTACHMENT HOLE CRACKED BEYOND ALLOWABLE LIMITS, LOWER ROW SKIN LAP. LOCATED AT STA 344, STR 14R. LIMITS BASED ON AD 95-25-05. REPAIRED PER DALFORT AVIATION XEA NR X2-53-177 REV 1 DATED 7-17-97 AND XEA NR X2-53-17 REV 3 DATED 7-1-97. APPROVAL DATA: FAA FORM 8110-3 DATED 7-17-97.
Part: STRINGER — DOUBLER CRACKED (BS 380)
PREVIOUS REPAIR IS NOT IN C/W SB 737-53-A 1177 AND THE INNER DOUBLER IS CRACKED AT STA 380, STR 19R. REPAIRED PER DALFORD AVIATION XEA NR X2-53-182 REV 1 DATED 7-31-97. APPROVAL DATA: FAA 8110-3 DATED 8-18-97.
Part: STRINGER — OUT OF LIMITS (BS 393)
ONE EACH 0.233 INCH DIAMETER HOLE OUT OF ALLOWABLE LIMITS PER DALFORT AVIATION XEA NR X2-53-168. LOCATED AT STR 10L, STA 393. REPAIRED PER DALFORT AVIATION XEA NR X2-53-168, REV 3 DATED 6-30-97. APPROVAL DATA: FAA FORM 8110-3 DATED 6-27-97.
Part: STRINGER — CRACKED (BS 498 - BS 887)
ONE EACH ATTACHMENT HOLE CRACKED BEYOND LIMITS, STR 14R, STA 734 AND STR 10L, STA'S 498 AND 500. ONE EACH ATTACHMENT HOLE CRACKED BEYOND LIMITS, STR 14L, STA 416 AND STA 443, AND, STR 20L, STA 827 AND STA 887. ABOVE MENTIONED LIMITS BASED ON AD 94-25-05. REPAIRED PER DALFORT AVIATION XEA NR X2-53-173, REV 3, DATED 7-1-97. APPROVAL DATA: FAA FORM 8110-3, DATED 6-26-97.
Part: STRINGER — CRACKED (BS 269 - BS 285)
THREE ATTACHMENT HOLES CRACKED BEYOND LIMITS, LOWER SKIN LAP ROW AT STA 269 THROUGH STA 285, STR 19L. LIMITS BASED ON AD 64-25-05. REPAIRED PER DALFORT AVIATION XEA NR X2-53-176 DATED 7-1-97 AND XEA NR X2-53-173 REV 3 DATED 7-1-97. APPROVAL DATA: FAA FORM 8110-3 DATED 7-17-97.
Part: STRINGER — CRACKED (BS 360 - BS 908)
NUMEROUS FASTENER HOLES CRACKED BEYOND LIMITS, STR 4L, STA 360 TO STA 908, AND STR 4R, STA 360 TO STA 908. NUMEROUS FASTENER HOLES CRACKED BEYOND LIMITS, STR 10R, STA 727 TO STA 908, AND STR 10L, STA 360 TO STA 540, AND STA 727 TO STA 908. ABOVE MENTIONED LIMITS BASED ON AD 94-25-05. REPAIRED PER DALFORT AVIATION XEA NR X2-53-171, REV 5, DATED 8-5-97. APPROVAL DATA: FAA FORM 8110-3, DATED 7-9-97.
Part: STRINGER — CRACKS (BS 485 - BS 957)
THREE EACH ATTACHMENT HOLES OUT OF ALLOWABLE LIMITS. LOCATED AT STR 10L AT STATIONS 445, 485, AND 507. LIMITS BASED ON DALFORT AVIATION XEA NR X2-53-168, REV 2, DATED 6-30-97. TWO ATTACHMENT HOLES CRACKED BEYOND ALLOWABLE LIMITS. LOCATED ON LOWER ROW SKIN LAP ON STR 10R AT STA 957.25. LIMITS BASED ON AD 94-25-05. REPAIRED PER DALFORT AVIATION XEA NR X2-53-167, REV 1 DATED 6-4-97. BOEING SB 53A117 REV 1 AND FAA AD 94-25-05.
Part: STRINGER — HOLES WORN (STA 540)
TWO EACH ATTTACHMENT HOLES CRACKED BEYOND ALLOWABLE LIMITS. LOCATED IN LOWER ROW SKIN LAP ON STR 14L, STA 540. LIMITS BASED ON AD 94-25-05. REPAIRED PER DALFORT AVIATION XEA NR X2-53-184 REV 1 DATED 8-20-97. APPROVAL DATA: FAA FORM 8110-3 DATED 8-19-97.
Earlier reports · 1995–1996 · 9 reports
1996
Part: BULKHEAD — CRACKED (BS 727)
DURING SCHEDULED SERVICE VISIT CHECK, FOUND BS 727 BULKHEAD CRACKED. REPAIRED PER BOEING SRM.
Part: SKIN — CRACKED (NLG WW)
DURING SCHEDULED C1 CHECK, FOUND NOSE W/W CEILING SKIN CRACKED AFT OF MANUAL EXTENSION RETURN SPRING BRACKET. REPAIRED PER BOEING SRM.
Part: BATTERY — DISCHARGED (CABIN)
DURING SCHEDULED SERVICE CHECK, FOUND FWD EMERGENCY EXIT LIGHTS INOP. REPLACED BATTERY PACK PER BOEING M/M.
Part: WEB — CRACKED (CARGO DOOR)
DURING SCHEDULED B2 CHECK, FOUND FWD CARGO DOOR LOWER WEB CRACKED ORIGINATING FROM RIVET HOLE, ADJACENT TO AFT/LOWER STOP FITTING. REPAIRED PER BOEING SRM.
Part: RETRACT MECH — MALFUNCTIONED (LANDING GEAR)
AFTER TAKEOFF, CREW WAS UNABLE TO RAISE GEAR WITHOUT USING OVERRIDE TRIGGER. AIRCRAFT RETURNED TO DAL AND MADE AN UNEVENTFUL LANDING. CYCLED GEAR SEVERAL TIMES, NO DEFECTS NOTED. RESET LANDING GEAR POSITION LIGHTS C/B.
1995
Part: WEB — CRACKED (NLG WW)
DURING SCHEDULED CHECK, FOUND NOSE WHEELWELL LEFT VERTICAL WEB CRACKED 3.1 INCHES, BELOW FWD LEFT ACCESS PANEL. REPAIRED PER BOEING STRUCTURAL REPAIR MANUAL.
Part: SKIN — CRACKED (FUSELAGE)
DURING SCHEDULED MAINT VISIT, FOUND FUSELAGE SKIN CRACKED AT AFT LOWER CORNER OF FORWARD AIRSTAIRS DOORWAY CUTOUT AT DOUBLER. REPAIRED PER DALFORT XEA X2-53-153.
Part: SKIN — CRACKED (BS 227.8)
DURING SCHEDULED MAINT VISIT, FOUND FUSELAGE SKIN CRACKED THREE PLACES AT BS 227.8, BETWEEN S13 AND 16L. REPAIRED PER DALFORT XEA X2-53-154.
Part: SKIN — CRACKED (BS 227.8)
DURING SCHEDULED MAINT VISIT, FOUND FUSELAGE SKIN CRACKED AT AFT LOWER CORNER OF FORWARD AIRSTAIRS DOORWAY CUTOUT AT THREE PLACES AT BS 227.8, BETWEEN S13 AND 16L. REPAIRED PER DALFORT XEA X2-53-154.