# N355MC: 1985 Boeing 747-341, registration cancelled 2018-03-22

- Type: Cancelled registration (FAA registry, deregistered aircraft)
- Cancelled: March 22, 2018
- Status when cancelled: Registration expired, pending cancellation
- Airframe: [Boeing 747-341](https://openairdocs.org/model/boeing-747-341) (registry code 13848AM)
- Engine: [Amateur-built UNKNOWN ENG](https://openairdocs.org/engine/amateur-built-unknown-eng) (registry code 99999)
- Data sheets: [TCDS A20WE](https://openairdocs.org/tcds/A20WE) (OpenAirDocs)
- Serial number: 23395
- Year built: 1985
- Type of aircraft: Fixed wing multi engine
- Airworthiness: Standard, transport
- Airworthiness date: February 21, 2011
- Certificate issued: May 25, 2000
- Last registry action: April 25, 2014
- Mode S code: A3F876
- Owner when cancelled: [Atlas Air Inc](https://openairdocs.org/faa-owner/ATLAS%20AIR%20INC)
- Location: [Purchase, NY](https://openairdocs.org/faa-place/NY/Purchase)
- Owner type: Corporation
- Owner's area on the map: 41.0382° N, 73.7107° W: Placed by OpenAirDocs at the center of ZIP code 10577, within about a mile (OpenAirDocs). The owner's mailing address, not where the aircraft was based
- The mark today: https://openairdocs.org/aircraft/N355MC
- FAA registry: https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=355MC
- Page: https://openairdocs.org/deregistered/N355MC-2018-03-22

From the FAA registry file of October 29, 2026, cancelled registrations. Owners' street addresses are left out. The Mode S code belongs to the N-number, not the airframe.

ADs and bulletins for the Boeing 747-341: https://openairdocs.org/model/boeing-747-341.md

## Service difficulty reports (158, newest 50)

Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model.

- [SDR UIEA2011122300728](https://openairdocs.org/sdr/UIEA2011122300728), Dec 21, 2011: SKIN. DAMAGED. THE ACFT WAS STRUCK BY GROUND EQUIPMENT AND SUSTAINED DAMAGE TO THE FUSELAGE SKIN, BEAR STRAP AND BS-670 FRAME JUST ABOVE THE THE LOWER AFT CORNER OF THE FWD CA
- [SDR UIEA2011102000603](https://openairdocs.org/sdr/UIEA2011102000603), Oct 16, 2011: RELAY. MALFUNCTIONED. AIR TURN BACK, AUTO PRESSURIZATION INOPERATIVE ON CLIMBOUT. IN AUTO, BOTH VALVES INDICATED 90 PERCENT CLOSED AT FL 100. ATC REPORTS TRANSPONDER INOPERATIVE. CYC
- [SDR UIEA2011102000602](https://openairdocs.org/sdr/UIEA2011102000602), Oct 15, 2011: LOGIC CARD. INOPERATIVE. AIRTURN BACK DUE UPPER DECK FLIGHT LOCK LIGHT ILLUMINATED AFTER TAKE OFF. CABIN WOULD NOT PRESSURIZE. EXTINGUISHED ON LANDING. ATC COULD NOT RECEIVE SQUAK CODE 
- [SDR UIEA2011081000452](https://openairdocs.org/sdr/UIEA2011081000452), Aug 10, 2011: FAIRING. CRACKED. DURING WALK-AROUND INSP, MX REPORTED LT INBD WING TO FUSELAGE PANEL 293AL - WBL 128.46 CRACK/DAMAGE (REF FIG 1). PERFORMED A TIME LIMITED REPAIR.
- [SDR UIEA2011080700423](https://openairdocs.org/sdr/UIEA2011080700423), Aug 7, 2011: SPOILER SYS. MALFUNCTIONED. WHEN TAKEOFF POWER APPLIED, AUTO SPOILERS DEPLOYED AND WARNING HORN SOUNDED. RETURNED TO BLOCKS. APPLIED MEL 27-9 FOR AUTO SPOILERS INOP, COMPLIED WITH MX ACTIO
- [SDR UIEA2011080600429](https://openairdocs.org/sdr/UIEA2011080600429), Aug 6, 2011: SKIN. DAMAGED. DURING INSP, MX FOUND THE NR1 ENGINE LT THRUST REVERSER CORE COWL INNER SKIN DAMAGED/DELAMINATED. REF FIG 1. DISPOSITION IS TO REPAIR THE SIDEWALL DAMAGE ON THE
- [SDR UIEA2011052700267](https://openairdocs.org/sdr/UIEA2011052700267), May 27, 2011: RELIEF VALVE. DEFECTIVE. DURING CLIMBOUT, NR 2 ENGINE FIRE WARNING SOUNDED WITH BOTH FIRE LOOP INDICATORS AT 9. RAN ENGINE FIRE CHECKLIST. NR 2 ENGINE FIRE LIGHT WENT OUT WHEN THROTTLE 
- [SDR UIEA2011032800163](https://openairdocs.org/sdr/UIEA2011032800163), Mar 28, 2011: PANEL. GOUGED. DURING ROUTINE CHECK, GOUGE DAMAGE TO THE RT INBD ELEVATOR LOWER PANEL WAS FOUND. THE DAMAGE OCCUPIES AN AREA OF APPROX 4.5-IN BY 3-IN AND LOCATED AT 23-IN FROM
- [SDR UIEA2011032000157](https://openairdocs.org/sdr/UIEA2011032000157), Mar 20, 2011: ACCESS PANEL. MISSING. DURING WALKAROUND INSP, MX FOUND THE RT BODY GEAR DOOR WITH ACCESS PANELS (2 EA) MISSING (REF FIG 1). (DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS 
- [SDR UIEA2011030100135](https://openairdocs.org/sdr/UIEA2011030100135), Mar 1, 2011: RUB STRIP. DAMAGED. ACFT AT SIN D CHECK. THE NR 1 LT FAN COWL WAS ROUTED TO THE COMPOSITE SHOP FOR REPAIRS. DURING INSTALLATION ON THE ACFT THE L/E RUB STRIP MISMATCH (6 O'CLOCK) W
- [SDR UIEA2011022000124](https://openairdocs.org/sdr/UIEA2011022000124), Feb 20, 2011: FLOORBEAM. CORRODED. DURING D CHECK OF DATUM AIRCRAFT, CORROSION FOUND ON LOWER LOBE CAP AFT FLANGE LOWER SURFACE OF THE SECTION 46- STA 1680 AFT CARGO FLOOR BEAM BETWEEN LBL 30 AND
- [SDR UIEA2011021900129](https://openairdocs.org/sdr/UIEA2011021900129), Feb 19, 2011: SKIN. CORRODED. DURING A D-CHECK. SIAE REPORTED CORROSION IN FUSELAGE SKIN ADJACENT TO AND BELOW THE LAP JOINTS AT MULTIPLE LOCATIONS. NO ACTION REQUIRED - THIS PART WAS PREVIO
- [SDR UIEA2011021900120](https://openairdocs.org/sdr/UIEA2011021900120), Feb 19, 2011: SKIN. CRACKED. DURING A D-CHECK. REPORTED A CRACK IN THE NR 4 STRUT RIGHT SIDE SKIN ASSEMBLY INTERNAL BONDED DOUBLER AT THE 482AR ACCESS PANEL CUTOUT, LOCATED BETWEEN N.S.211.
- [SDR UIEA2011021100062](https://openairdocs.org/sdr/UIEA2011021100062), Feb 11, 2011: BULKHEAD. CRACKED. THE PURPOSE OF THIS EO IS TO DOCUMENT A REPAIR PERFORMED ON THE DATUM ACFT AT SIAE DURING A D-CHECK. SIAE REPORTED A CRACK IN THE BS 400 BULKHEAD LOWER WEB ASSY
- [SDR UIEA2011020800058](https://openairdocs.org/sdr/UIEA2011020800058), Feb 8, 2011: STRINGER. CRACKED. DURING D-CHECK OF DATUM ACFT, FOUND A 0.75 INCH LONG CRACK EMANIATING FROM THE CUT OUT EDGE OF S-10AR ON FRAME AT STA 440 WITH PN 65B01715-1022. FIG 1 FOR DAMAG
- [SDR UIEA2011020700043](https://openairdocs.org/sdr/UIEA2011020700043), Feb 7, 2011: STRUCTURE. DAMAGED. VERTICAL STABILIZER L/E CAP AT L/E STA 133.581 RT SIDE DAMAGED OUT OF LIMIT IAW SRM 55-30-01 DEPTH FOUND TO BE 0.018". TRIMMING OUT OF DAMAGED LEADING EDGE ASSY
- [SDR UIEA2011020700042](https://openairdocs.org/sdr/UIEA2011020700042), Feb 7, 2011: SKIN. CORRODED. FUSELAGE STA 2195, ON S30L, FOUND CORROSION 2" BY 1" AND SKIN CRACKED ACROSS FASTERNER 1.5". TO PROVIDE ACCESS TO DETERMINE EXTEND OF DAMAGED AND CARRY OUT REPA
- [SDR UIEA2011012400123](https://openairdocs.org/sdr/UIEA2011012400123), Jan 24, 2011: SKIN. CRACKED. DURING D-CHECK, BS 2184 FUSELAGE SKIN AT STRINGER 39R, FOUND CRACKED DURING INSPECTION. REPAIRED USING GAUGE 0.071" DOUBLER 10.5 X 7.3". HOLES PICKED UP AND PRO
- [SDR UIEA2011012400119](https://openairdocs.org/sdr/UIEA2011012400119), Jan 24, 2011: BULKHEAD. CRACKED. DURING D CHECK OF DATUM AIRCRAFT, ONE CRACK OF 1.75 INCH LONG FOUND ON OUTER RING CHORD AFT SIDE ON FWD PRESSURE BULKHEAD IN NOSE SECTION AT STA 140, S-19R, WL2
- [SDR UIEA2011011700127](https://openairdocs.org/sdr/UIEA2011011700127), Jan 17, 2011: SKIN. SCRATCHED. FOUND SCRATCH MARK (APPROX 1.5") ON VERTICAL STABILIZER LEADING EDGE CAP AT LE STA 135.581, BLENDING CARRIED OUT ON SCRATCH MARKS ON ABOVE SAID LOCATION. FOUND 
- [SDR UIEA2011011500130](https://openairdocs.org/sdr/UIEA2011011500130), Jan 15, 2011: DOOR. DENTED. DURING D-CHECK OF THE DATUM AIRCRAFT, FOUND THE APU DOOR DENTED AND BENT AT LOWER FOWARD CORNER. THE DAMAGE COVERS AN AREA OF APPROXIMATELY 4.5-IN BY 5.25-IN. S
- [SDR UIEA2011011400126](https://openairdocs.org/sdr/UIEA2011011400126), Jan 14, 2011: STRINGER. CRACKED. DURING D-CHECK, FUSELAGE BS 2090 STRINGER 29R WAS FOUND CRACKED DURING INSPECTION. THE CRACKED STRINGER WAS REPAIRED PER SRM 53-10-03 FIGURE 1, BY SPLICING THE 
- [SDR UIEA2011011400098](https://openairdocs.org/sdr/UIEA2011011400098), Jan 14, 2011: INTERCOSTAL. CORRODED. BULK CARGO STA 2000 - 1920, ANCHOR NUTS UNDER SKIN CORRODED AT RBL 50 INTERCOSTAL. TO REMOVE NUT FOR DAMAGE REMOVAL DETERMINES LIMITS.(NUTS REMOVED AND BLENDOUT
- [SDR UIEA2011011400099](https://openairdocs.org/sdr/UIEA2011011400099), Jan 14, 2011: INTERCOSTAL. CORRODED. BULK CARGO INTERCOSTAL AT RBL 45. SKIN CORRODED UNDER ANCHOR NUT AT STA 1935. TO REMOVE NUT AND REMOVE DAMAGE FOR ASSESSMENTS. (BLENDING DONE. MATERIAL THICKNES
- [SDR UIEA2011011400100](https://openairdocs.org/sdr/UIEA2011011400100), Jan 14, 2011: INTERCOSTAL. CORRODED. BULK CARGO INTERCOSTAL AT RBL 45 STA 2040-2060. SKIN UNDER ANCHOR NUTS CORRODED. TO REMOVE ANCHOR NUTS FOR DAMAGE REMOVAL AND TO DETERMINE LIMITS.(BLENDING DONE
- [SDR UIEA2011011400107](https://openairdocs.org/sdr/UIEA2011011400107), Jan 14, 2011: INTERCOSTAL. CORRODED. BULK CARGO STA 1940 - 1945 RBL 22.5. ANCHOR NUT UNDER SKIN CORRODED ON INTERCOSTAL. TO REMOVE NUT. REMOVE DAMAGE AND FIND LIMITS.(NUTS REMOVED. BLEND OUT DONE P
- [SDR UIEA2011011400112](https://openairdocs.org/sdr/UIEA2011011400112), Jan 14, 2011: INTERCOSTAL. CORRODED. BULK CARGO INTERCOSTAL AT STA 2040 -0 2100 RBL 22.5, ANCHOR NUTS UNDER SKIN CORRODED. TO REMOVE NUTS AND REMOVE CORROSION AND DETERMINE LIMITS.(NUTS REMVOED, BL
- [SDR UIEA2011011400113](https://openairdocs.org/sdr/UIEA2011011400113), Jan 14, 2011: INTERCOSTAL. CORRODED. BULK CARGO INTERCOSTAL AT STA 1920 - 1940 RBL 45 ANCHOR NUT UNDER SKIN CORRODED OFF. TO DO REPAIR.(INTERCOSTAL REMOVED PER SRM 51-30-02. REPLACEMENT DONE PER SR
- [SDR UIEA2011011400114](https://openairdocs.org/sdr/UIEA2011011400114), Jan 14, 2011: INTERCOSTAL. CORRODED. BULK CARGO INTERCOSTAL AT STA 1955 RBL 50 ANCHOR NUT UNDER SKIN CORRODED. TO REMVOE NUT, REMOVE DAMAGE AND DETERMINE LIMITS(NUTS REMVOED AND BLENDOUT PER SRM 51
- [SDR UIEA2011011400115](https://openairdocs.org/sdr/UIEA2011011400115), Jan 14, 2011: INTERCOSTAL. CORRODED. BULK CARGO INTERCOSTAL STA 2070. 2025 1965 - 1940 LBL 37.5 ANCHOR NUT UNDER SKIN CORRODED. TO REMOVE NUT, REMOVE DAMAGE AND DETERMINE LIMITS.(INTERCOSTAL REMOVE
- [SDR UIEA2011011400116](https://openairdocs.org/sdr/UIEA2011011400116), Jan 14, 2011: INTERCOSTAL. CORRODED. BULK CARGO INTERCOSTAL STA 1920- 2160. LBL 22.5. ANCHOR NUT UNDER SKIN CORRODED OFF. TO DO REPLACEMENT(ANCHOR NUTS REMOVED AND BLENDOUT DONE PER SRM 51-10-01. M
- [SDR UIEA2011011400117](https://openairdocs.org/sdr/UIEA2011011400117), Jan 14, 2011: INTERCOSTAL. CORRODED. BULK CARGO INTERCOSTAL STA 1920 - 1945 LBL 15. ANCHOR NUT UNDER SKIN CORRODED OFF. TO DO REPAIR.(INTERCOSTAL REMOVED AND REPLACED PER SRM 51-30-02. NUTS REPLACE
- [SDR UIEA2011011200125](https://openairdocs.org/sdr/UIEA2011011200125), Jan 12, 2011: SKIN. CRACKED. DURING D-CHECK, FUSELAGE BS 2170, STRINGER 39R WAS FOUND CRACKED DURING INSPECTION. THE CRACKED STRINGER WAS REPAIRED PER SRM 53-10-03 FIGURE 1, BY SPLICING THE
- [SDR UIEA2011011100094](https://openairdocs.org/sdr/UIEA2011011100094), Jan 11, 2011: STRINGER. CORRODED. AFT CARGO STA 1700 S40L. STRINGER TOP FLANGE CORRODED 1/2" X 1/4". STRINGER REMOVED FOR REPAIR. REPAIR PARTS FABRICATED PER SRM 53-10-03. WEB, STIFFENERS AND CL
- [SDR UIEA2011011100095](https://openairdocs.org/sdr/UIEA2011011100095), Jan 11, 2011: STRINGER. CORRODED. AFT CARGO STA 1725 - 1733 S36L CORROSION FOUND AT BASE OF STRINGER. BLENDED PER SRM 51-10-01. MATERIAL THICKNESS = 0.063. REMAINING THICKNESS = 0.04. OUT OF SRM
- [SDR UIEA2011011100096](https://openairdocs.org/sdr/UIEA2011011100096), Jan 11, 2011: STRINGER. CORRODED. AFT CARGO BS 1721 S40L, STRINGER BASE CORRODED. TO REMOVE FASTENERS AND FREE STRINGER FOR CORROSION REMOVAL.(FASTENERS REMOVED, TO DETERMINE EXTENT OF DAMAGE. B
- [SDR UIEA2011010600128](https://openairdocs.org/sdr/UIEA2011010600128), Jan 6, 2011: SKIN. CORRODED. FOUND PITTING CORROSION AT MULTIPLE LOCATIONS FROM STA 1383.0 TO STA 1480. BELOW STR 19L LAP JOINT. BLENDOUT CARRIED OUT AS PER SRM 53-30-01 AND SRM 51-10-01. T
- [SDR UIEA2011010600093](https://openairdocs.org/sdr/UIEA2011010600093), Jan 6, 2011: STRINGER. CORRODED. CARGO AFT COMPARTMENT STA 1743 S42R. STRINGER CORRODED BELOW TOP HAT 3" CORROSION REMOVED PER SRM 53-30-01. DAMAGED SKIN TRIMMED OUT. STRINGER REPLACED PER SRM 
- [SDR UIEA2010073100133](https://openairdocs.org/sdr/UIEA2010073100133), Jul 31, 2010: ROD END. BROKEN. AFTER LANDING PERFORMED, 180 DEGREE TURN AND THE RT BODY UNLOCK LIGHT ILLUMINATED AND ACFT WOULD NOT MOVE. WENT OUT FOR VISUAL INSP AND FOUND 1 ALT ROD END BROK
- [SDR UIEA201000188](https://openairdocs.org/sdr/UIEA201000188), May 20, 2010: FRAME. CRACKED. EO 4753A448, A CRACK WAS FOUND IN THE BS 420, S-10R FRAME WEB . THE DAMAGE WAS TRIMMED OUT AND REPAIRED IAW NRC 500789 AND SRM 53-10-04, FIGURE 11. PART 1 OF TH
- [SDR UIEA201000067](https://openairdocs.org/sdr/UIEA201000067), Mar 29, 2010: TIRE. DAMAGED. AFTER LANDING DISCOVERED NR 14 TIRE FLAT SPOTTED. REPLACED NR 14 TIRE AND REPLACED NR 13 TIRE PRECAUTIONARY DUE OVERLOAD AND REPLACED NR 14 WHEEL TRANSDUCER. PR
- [SDR UIEA201000051](https://openairdocs.org/sdr/UIEA201000051), Feb 22, 2010: FAILSAFE. CRACKED. FUSELAGE - BS 860, S6-7R FRAME FAIL-SAFE CHORD CRACK REPAIR SRM 53-30-1 FIGURE 1, DETAILS I AND II. REPEAT REQ: PERMANENT.
- [SDR UIEA201000057](https://openairdocs.org/sdr/UIEA201000057), Feb 17, 2010: FLOORBEAM. CRACKED. FUSELAGE: BS 680, BL28-30 FLOORBEAM WEB CRACK REPAIR SRM 53-10-07, FIG 11, COMPLETED.
- [SDR UIEA201000041](https://openairdocs.org/sdr/UIEA201000041), Feb 17, 2010: DOOR. DAMAGED. DOOR - RT BODY GEAR DOOR DAMAGE. REPAIRED PER SRM 52-80-01, FIG 3, SH 6 ITEM 3, SRM 51-40-02, SRM 51-40-03. REPEAT REQUIREMENT: PERMANENT.
- [SDR UIEA201000056](https://openairdocs.org/sdr/UIEA201000056), Feb 16, 2010: STRAP. CRACKED. FUSELAGE - BS 1241, LT BULKHEAD - SPLICE STRAP AND FORGING CRACK - REPAIR 747-53-2283, REV 4.
- [SDR UIEA201000055](https://openairdocs.org/sdr/UIEA201000055), Feb 15, 2010: SKIN. DENTED. FUSELAGE - BS 1520 - 1540, S43L-44L SKIN DENT REPAIR SRM 53-30-03, FIG 1. REPEAT REQ: PERMANENT.
- [SDR UIEA201000054](https://openairdocs.org/sdr/UIEA201000054), Feb 14, 2010: SKIN. DENTED. FUSELAGE - BS 2060-2080, S39L-40L SKIN DENT REPAIR SRM 53-30-03, FIG 1. REPEAT REQ: PERMANENT.
- [SDR UIEA201000049](https://openairdocs.org/sdr/UIEA201000049), Feb 14, 2010: BEAM. CRACKED. FUSELAGE - BS 540-560, RBL 45 LONGITUDINAL BEAM CRACK REPAIR SRM 53-10-05 FIG 5. REPEAT REQ: PERMANENT.
- [SDR UIEA201000053](https://openairdocs.org/sdr/UIEA201000053), Feb 13, 2010: SKIN. DENTED. FUSELAGE - BS 740-755, S46L; 46R SKIN DENT REPAIR SRM 53-30-03, FIG 1. REPEAT REQ: I-15,000 FC. R-6,000 FC.
- [SDR UIEA201000048](https://openairdocs.org/sdr/UIEA201000048), Feb 13, 2010: BEAM. CRACKED. FUSELAGE - BS 570-580, RBL 25 LONGITUDINAL BEAM CRACK REPAIR SRM 53-10-05 FIG 5. REPEAT REQ: PERMANENT.

All 158: https://openairdocs.org/deregistered/N355MC-2018-03-22/reports.md

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