# N1373A: 1994 Boeing 767-31K - Status: Valid registration - Airframe: [Boeing 767-31K](https://openairdocs.org/model/boeing-767-31k) (registry code 1385192, 261 seats) - Engine: [GE CF6-80C2B2](https://openairdocs.org/engine/ge-cf6-80c2b2) (registry code 30102) - Data sheets: [TCDS E13NE](https://openairdocs.org/tcds/E13NE) (General Electric Company GE Aerospace) (OpenAirDocs) - Serial number: 27205 - Year built: 1994 - Type: Fixed wing multi engine - Engine type: Turbo-fan - Airworthiness: Standard, transport - Airworthiness date: October 24, 2017 - Certificate issued: December 15, 2017 - Expires: December 31, 2027 - Mode S code: A097F4 - Registered owner: [Msn 27205 LLC](https://openairdocs.org/faa-owner/MSN%2027205%20LLC) - Location: [Purchase, NY](https://openairdocs.org/faa-place/NY/Purchase) - Owner type: LLC - 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 is based - FAA registry: https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=1373A - Page: https://openairdocs.org/aircraft/N1373A From the FAA registry file of October 24, 2026. ADs below are matched by the registry's airframe and engine model codes. They may apply; each AD's applicability can narrow it by serial number, part number or installed equipment. This is not a compliance determination. ## ADs that may apply (OpenAirDocs): 30 in force ### Matched by airframe (Boeing 767-31K) None in force. ### Matched by engine (GE CF6-80C2B2) - [AD 2021-26-22](https://openairdocs.org/ad/2021-26-22): Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Mar 14, 2022 - [AD 2021-14-11](https://openairdocs.org/ad/2021-14-11): Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 25 more. Effective Aug 27, 2021 - [AD 2021-03-02](https://openairdocs.org/ad/2021-03-02): Fuel Control/Turbine Engines · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Mar 31, 2021 - [AD 2016-08-10](https://openairdocs.org/ad/2016-08-10): Accessory heat shield · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 26 more. Effective Jun 1, 2016 - [AD 2014-21-01](https://openairdocs.org/ad/2014-21-01): Fuel manifold · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 26 more. Effective Nov 28, 2014 - [AD 2013-08-20](https://openairdocs.org/ad/2013-08-20): Fuel tube · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 14 more. Effective May 31, 2013 - [AD 2012-03-12](https://openairdocs.org/ad/2012-03-12): No. 3 bearing packing · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 21 more. Effective Apr 5, 2012 - [AD 2009-21-07](https://openairdocs.org/ad/2009-21-07): Thrust and thrust control · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 21 more. Effective Dec 1, 2009 - [AD 2009-07-03](https://openairdocs.org/ad/2009-07-03): Eddy current inspection (ECI) · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 26 more. Effective Apr 30, 2009 - [AD 2009-04-10](https://openairdocs.org/ad/2009-04-10): Critical life-limited parts · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 30 more. Effective Mar 30, 2009 - [AD 2008-21-11](https://openairdocs.org/ad/2008-21-11): Low-pressure turbine (LPT) cases · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 25 more. Effective Nov 28, 2008 - [AD 2007-11-20](https://openairdocs.org/ad/2007-11-20): Fuel shroud retaining rings · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 22 more. Effective Jul 10, 2007 - [AD 2007-05-14](https://openairdocs.org/ad/2007-05-14): Cast titanium weld- repaired forward engine mount platforms · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Apr 9, 2007 - [AD 2006-16-06](https://openairdocs.org/ad/2006-16-06): Certain stage 1 high- pressure turbine (HPT) rotor disks · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Sep 5, 2006 - [AD 2005-17-05](https://openairdocs.org/ad/2005-17-05): High pressure compressor rotor (HPCR) · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 25 more. Effective Sep 27, 2005 - [AD 2004-22-07](https://openairdocs.org/ad/2004-22-07): Stage 2 nozzle guide vanes (HPT S2 NGVs) · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Dec 1, 2004 - [AD 2003-02-07](https://openairdocs.org/ad/2003-02-07): Low pressure turbine (LPT) shrouds · General Electric CF6-50A, CF6-50C, CF6-50C1 and 30 more. Effective Mar 3, 2003 - [AD 2002-25-08](https://openairdocs.org/ad/2002-25-08): High pressure compressor rotor · General Electric CF6-45A, CF6-45A2, CF6-50A and 40 more. Effective Jan 23, 2003 - [AD 2002-22-12](https://openairdocs.org/ad/2002-22-12): Titeflex hoses · BAE Systems ATP, Avro 146-RJ100A, Avro 146-RJ70A and 122 more. Effective Dec 13, 2002 - [AD 2000-03-04](https://openairdocs.org/ad/2000-03-04): General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 19 more. Effective Apr 10, 2000 - [AD 99-01-01](https://openairdocs.org/ad/99-01-01): Accessory Gearbox (AGB) idler adapters · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 19 more. Effective Jan 21, 1999 - [AD 98-22-06](https://openairdocs.org/ad/98-22-06): Fan Disks · General Electric CF6-45A, CF6-45A2, CF6-50A and 41 more. Effective Nov 23, 1998 - [AD 97-22-14](https://openairdocs.org/ad/97-22-14): (HPCR) 3-9 Spool · General Electric CF6-50A, CF6-50C, CF6-50C1 and 29 more. Effective Nov 17, 1997 - [AD 96-16-07](https://openairdocs.org/ad/96-16-07): Rear Right Hand Mount Link · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 17 more. Effective Aug 28, 1996 - [AD 95-10-11](https://openairdocs.org/ad/95-10-11): Fan Reversers · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 17 more. Effective May 31, 1995 - [AD 94-20-06](https://openairdocs.org/ad/94-20-06): Oil System · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Dec 27, 1994 - [AD 94-06-03](https://openairdocs.org/ad/94-06-03): High Pressure Turbine Disk · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Apr 29, 1994 - [AD 93-14-18](https://openairdocs.org/ad/93-14-18): High pressure turbine (HPT) thermal shields · General Electric CF6-45A, CF6-45A2, CF6-50A and 40 more. Effective Oct 4, 1993 - [AD 91-15-25](https://openairdocs.org/ad/91-15-25): High Pressure Compressor Rotor · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 16 more. Effective Sep 6, 1991 - [AD 91-11-05](https://openairdocs.org/ad/91-11-05): High Pressure Compressor Rotor · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 16 more. Effective Jul 5, 1991 ### Historical (superseded or no longer in force) - [AD 2020-20-13](https://openairdocs.org/ad/2020-20-13) (historical): Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Nov 12, 2020 - [AD 2018-15-04](https://openairdocs.org/ad/2018-15-04) (historical): Turbine/Turboprop Engine--Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Oct 2, 2018 - [AD 2009-05-02](https://openairdocs.org/ad/2009-05-02) (historical): Drainless fuel manifold assemblies · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 26 more. Effective Mar 31, 2009 - [AD 2004-04-07](https://openairdocs.org/ad/2004-04-07) (historical): Stage 1 HPT rotor disks · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Mar 12, 2004 - [AD 2002-07-12](https://openairdocs.org/ad/2002-07-12) (historical): Life Limits Section of Continued Airworthiness (ICA) - Selected Critical Life-limited Parts · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 27 more. Effective May 15, 2002 - [AD 2001-10-07](https://openairdocs.org/ad/2001-10-07) (historical): High Pressure Turbine Rotor Disks · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 19 more. Effective Jun 18, 2001 - [AD 2000-16-12](https://openairdocs.org/ad/2000-16-12) (historical): High Pressure Compressor Rotor Stage 3-9 Spools · General Electric CF6-45A, CF6-45A2, CF6-50A and 39 more. Effective Sep 5, 2000 - [AD 99-24-15](https://openairdocs.org/ad/99-24-15) (historical): High Pressure Compressor Rotor (HPCR) Stage 3-9 Spools · General Electric CF6-45A, CF6-45A2, CF6-50A and 39 more. Effective Jan 28, 2000 - [AD 99-08-13](https://openairdocs.org/ad/99-08-13) (historical): General Electric CF6-80A, CF6-80A1, CF6-80A2 and 26 more. Effective May 13, 1999 - [AD 91-20-02](https://openairdocs.org/ad/91-20-02) (historical): Fuel Manifolds · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 12 more. Effective Nov 25, 1991 - [AD 90-26-01](https://openairdocs.org/ad/90-26-01) (historical): Fuel Manifold Systems · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 11 more. Effective Dec 20, 1990 ## Information bulletins (advisory) (5 in force) - [SAIB 2023-15](https://openairdocs.org/saib/2023-15): Falsified Forms from AOG Technics. Issued Dec 19, 2023 - [SAIB NE-11-27](https://openairdocs.org/saib/NE-11-27): Fuel Injector Nozzle - CF6-80 Improperly Welded Fuel Nozzles. Issued Apr 5, 2011 - [SAIB NE-10-37](https://openairdocs.org/saib/NE-10-37): Engine Fuel and Control: FADEC Fuel Metering Valve Resolver Feedback Faults. Issued Jul 12, 2010 - [SAIB NE-08-44](https://openairdocs.org/saib/NE-08-44): Engine Thrust Reverser Transcowl Clevis Pin. Issued Sep 3, 2008 - [SAIB NE-07-01](https://openairdocs.org/saib/NE-07-01): Dual engine flameouts on twin engine airplanes. Issued Oct 12, 2006 ## NTSB investigations None matched to N1373A. ## FAA accident and incident reports None matched to N1373A. ## Service difficulty reports (479, newest 50) As reported by operators and repair stations. Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. - [SDR ABXR2026082800015](https://openairdocs.org/sdr/ABXR2026082800015), Aug 28, 2026: SUPPORT. CORRODED. CORROSION ON THE CUTOUT/ SUPPORT STRUCTURE FOR PANEL 195ML, AT THE LEFT UPPER FILLET AREA, AS VIEWED WITH DOOR OPEN. REMOVED CORROSION FROM PNL 195ML'S SUPPORT - [SDR ABXR082800014](https://openairdocs.org/sdr/ABXR082800014), Aug 28, 2026: STIFFENER. CRACKED. STA. 246 FLOORBEAM HAS CRACKED VERTICAL STIFFENER AT LBL 43 IN LEFT TUNNEL OF MEC .REPAIRED VERTICAL STIFFENER AT STA 246 FLOORBEAM LBL 43 IN LEFT TUNNEL OF MEC - [SDR ABXR082800013](https://openairdocs.org/sdr/ABXR082800013), Aug 28, 2026: STIFFENER. CRACKED. STA. 246 FLOORBEAM HAS A CRACKED VERTICAL STIFFENER ON FWD SIDE AT LBL 28 IN LEFT TUNNEL OF MEC . REPAIRED VERTICAL STIFFENER ON FWD SIDE FLOORBEAM OF STA 246 L - [SDR UIEA2025031900344](https://openairdocs.org/sdr/UIEA2025031900344), Mar 15, 2025: FITTING. CORRODED. HORIZONTAL STABILIZER PIVOT FITTING RH UPPER ATTACHMENTS, TWO HOLES WITH CORROSION. SEE NDT INSPECTION REPORT.(

TWO HOLES WITH CORROSION AT HORIZONTAL STABILI - [SDR UIEA2025031900343](https://openairdocs.org/sdr/UIEA2025031900343), Mar 15, 2025: SKIN. PUNCTURED. PUNCTURE DAMAGE TO UPPER SPOILER SKIN 6, REPAIR AS REQUIRED.(

UPPER SPOILER SKIN 6 WAS REPAIRED I.A.W B767 SRM 57-70-01-2R-1 AND SRM 51-70-04-0G-0 PAR 5 B AND - [SDR UIEA2025031900342](https://openairdocs.org/sdr/UIEA2025031900342), Mar 15, 2025: SUPPORT. CORRODED. LH WING INBOARD FLAP TRACK #3 SUPPORT AFT ATTACHMENT HOLES, BORE WITH CORROSION (4EA).(

LH WING INBOARD FLAP TRACK #3 SUPPORT AFT ATTACHMENT HOLES WERE REPAIR - [SDR UIEA2025031900341](https://openairdocs.org/sdr/UIEA2025031900341), Mar 15, 2025: FITTING. CORRODED. HORIZONTAL STABILIZER PIVOT FITTING RH LOWER ATTACHMENTS, HOLE WITH CORROSION. SEE NDT INSPECTION REPORT.(

HOLE WITH CORROSION AT HORIZONTAL STABILIZER PIVOT - [SDR UIEA2025031900340](https://openairdocs.org/sdr/UIEA2025031900340), Mar 15, 2025: PACKING. LEAKING. RH WING, PDU SLATS, HYDRAULIC MOTOR WITH EVIDENCE OF HYD LEAK.(

RH WING PDU HYD MOTOR PACKING WAS REPLACED AND LINES WERE TIGHTEN I.A.W AMM 27-81-11-424-029 R - [SDR UIEA2025031900339](https://openairdocs.org/sdr/UIEA2025031900339), Mar 15, 2025: BUSHING. CORRODED. HORIZONTAL STAB, RH PIVOT PIN, SLEEVE WITH CORROSION.(

HORIZONTAL STAB RH PIVOT PIN SLEEVE WAS REPLACED WITH NR00439 IAW SRM 51-10-02-0G-0 REV 12 - [SDR UIEA2025031900338](https://openairdocs.org/sdr/UIEA2025031900338), Mar 15, 2025: LONGERON. CORRODED. AFT CARGO COMPARTMENT, BTW STA 1065 AND 1087, STRG 23L AND 24L, LONGERON WITH CORROSION, L=4" W=1.580".(

AFT CARGO COMPARTMENT, BTW STA 1065 AND 1087, STRG 23 - [SDR UIEA2025031900337](https://openairdocs.org/sdr/UIEA2025031900337), Mar 15, 2025: SUPPORT. CORRODED. RIGHT WING TRAILING EDGE OUTBOARD FLAP SUPPORT #7, SUPPORT ACTUATOR HOLE WITH CRACK INDICATION AT 6 O´CLOCK APPROX.(

RIGHT WING TRAILING EDGE OUTBOARD FLAP S - [SDR UIEA2025031940336](https://openairdocs.org/sdr/UIEA2025031940336), Mar 15, 2025: SUPPORT. CORRODED. RIGHT WING TRAILING EDGE OUTBOARD FLAP SUPPORT #8, SUPPORT ACTUATOR HOLE WITH CORROSION INDICATION.(

RIGHT WING TRAILING EDGE OUT BOARD FLAP SUPPORT #8, SUPPO - [SDR UIEA2025031200280](https://openairdocs.org/sdr/UIEA2025031200280), Mar 15, 2025: SKIN. DAMAGED. DURING THE REMOVAL OF SLAT #6 FOR REPAIR (NR 00005), HIDDEN DAMAGE WAS FOUND ON LH WING FIXED LEADING EDGE AT RIB LES 351.10, WITH EXCESSIVE WEAR AND HOLE.(

O - [SDR UIEA2025031200279](https://openairdocs.org/sdr/UIEA2025031200279), Mar 15, 2025: CASE. CORRODED. ENG 2, FAN CASE, AT 6' O CLOCK, UNDER STRUT AREA, BASE WITH CORROSION L=2.100" W=1"(

ENG 2, FAN CASE, AT 6' O CLOCK, UNDER STRUT AREA, BASE, CORROSION LEVEL 1 - [SDR UIEA2025031200278](https://openairdocs.org/sdr/UIEA2025031200278), Mar 15, 2025: CASE. CORRODED. ENG 1, AFT FAN CASE, AT 5 TO 6 O'CLOCK APROX, WITH SEVERAL POINTS OF CORROSION (3EA).(

ENG 1, AFT FAN CASE, AT 5 TO 6 O'CLOCK APROX, CORROSIONS LEVEL 1 WAS RE - [SDR UIEA2025031900255](https://openairdocs.org/sdr/UIEA2025031900255), Mar 15, 2025: SKIN. DENTED. LH WING INBOARD TRAILING EDGE FLAP, LOWER AREA UPPER SKIN WITH SEVERAL DENTS.(

ONE DENT WAS REPAIRED IAW SRM 57-53-01-2R-1 PAG.1-7 FIG. 201 SHEET 4 AND SRM 51 - [SDR UIEA2025031900254](https://openairdocs.org/sdr/UIEA2025031900254), Mar 15, 2025: SKIN. PUNCTURED. RH OUTBOARD ELEVATOR, LOWER AND UPPER SKIN WITH A PUNCTURE BTW ELEV STA 200 AND 176, AT 2" FROM TRAILING EDGE.(

RH OUTBOARD ELEVATOR, LOWER AND UPPER SKIN WAS - [SDR UIEA2025031900253](https://openairdocs.org/sdr/UIEA2025031900253), Mar 15, 2025: BEAM. CORRODED. AFT CARGO DOOR, BEAM INNER CHORD, BTW STA 1285 AND STA 1329 STRG 23 WITH CORROSION AROUND FASTENER HOLES (L= 1.250" W=1 ").(

REPAIRED IN ACCORDANCE WITH TRE67 - [SDR UIEA2025031000252](https://openairdocs.org/sdr/UIEA2025031000252), Mar 15, 2025: SKIN. DENTED. LEFT WING, SLAT 6 INBOARD FACE WITH DENT APRX 10€Œ OF OUTBOARD EDGE.(

LEFT WING, SLAT 6 INBOARD FACE WITH DENT APRX 10€Œ OF OUTBOARD EDGE WAS REPAIRED IAW S - [SDR UIEA2025031000251](https://openairdocs.org/sdr/UIEA2025031000251), Mar 15, 2025: SUPPORT. CORRODED. RIGHT WING TRAILING EDGE INBOARD FLAP #5 SUPPORT MECHANISM 6-6 OUTER PIN WITH SEVERAL CORROSION IN THE INNER BORE.(

RIGHT WING TRAILING EDGE INBOARD FLAP #5 S - [SDR UIEA2025031900250](https://openairdocs.org/sdr/UIEA2025031900250), Mar 15, 2025: SKIN. CORRODED. CORROSION ON THE UPPER SKIN OF THE HORIZONTAL STABILIZER CENTER SECTION, RH SIDE.(

THE UPPER SKIN OF THE HORIZONTAL STABILIZER CENTER SECTION, RH SIDE MWAS RE - [SDR UIEA2025031900247](https://openairdocs.org/sdr/UIEA2025031900247), Mar 15, 2025: SKIN. DENTED. SLAT #5, LEADING EDGE EXTERNAL SKIN, LOWER INBOARD EDGE WITH A DENT.(

SLAT #5, LEADING EDGE EXTERNAL SKIN, LOWER INBOARD EDGE DAMAGE WAS REPAIRED IAW. TRE6757 - [SDR UIEA2025031900246](https://openairdocs.org/sdr/UIEA2025031900246), Mar 15, 2025: SKIN. CORRODED. FUSELAGE SECTION 48, APU INTAKE DOOR CUTOUT, UPPER STRIP BROKEN AND WITH CORROSION.(

FUSELAGE SECTION 48, APU INTAKE DOOR CUTOUT, UPPER STRIP WAS REPLACED IAW - [SDR UIEA2025031900244](https://openairdocs.org/sdr/UIEA2025031900244), Mar 15, 2025: SKIN. DAMAGED. RH WING, FIXED LEADING EDGE, BETWEEN WS 538.2 AND WS 564.2 (SLAT # 9, INBOARD MAIN TRACK, CUT OUT) WITH EDGE BROKEN.(

RH WING, FIXED LEADING EDGE, BETWEEN WS - [SDR UIEA2025031900243](https://openairdocs.org/sdr/UIEA2025031900243), Mar 15, 2025: SPACER. CORRODED. HORIZONTAL STABILIZER RH PIVOT PIN, OUTER SPACER WITH CORROSION.(

HORIZONTALSTABILIZER RH PIVOT PIN, OUTER SPACER WAS REPLACED I.A.W AMM 55-17-51-404-013 REV - [SDR UIEA2025031900241](https://openairdocs.org/sdr/UIEA2025031900241), Mar 15, 2025: STRINGER. BROKEN. BULK CARGO COMPARTMENT, BTW STA 1480 AND STA 1502, STRINGER 30L BROKEN.(

BULK CARGO COMPARTMENT, BTW STA 1480 AND STA 1502, STRINGER 30L WAS REPAIRED IAW. TRE - [SDR UIEA2025030800240](https://openairdocs.org/sdr/UIEA2025030800240), Mar 15, 2025: CONTROL MODULE. LEAKING. HORIZONTAL STABILIZER WITH EVIDENCE OF HYDRAULIC LEAKAGE STAB TRIM CONTROL MODULE RH.(

LEAKAGE CHECK IN STAB TRIM CONTROL MODULE RH WAS PERFORMED IAW AMM 29-1 - [SDR UIEA2025031900237](https://openairdocs.org/sdr/UIEA2025031900237), Mar 15, 2025: DOOR FRAME. CORRODED. AFT CARGO COMPARTMENT, CUT OUT LOWER DOOR, BETWEEN STA 1263 AND STA 1285, FRAME WITH CORROSION, L=2", W=1.5".(

AFT CARGO COMPARTMENT, CUT OUT LOWER DOOR, BETW - [SDR UIEA2025031900235](https://openairdocs.org/sdr/UIEA2025031900235), Mar 15, 2025: LENS. BROKEN. SWITCH "MAIN DECK CARGO", LENS BROKEN.(

MAIN DECK CARGO LIGHTS SWITCH LENS WAS REPLACED IAW AMM 33-34-00-900-801 REV 144 22DEC24 MAIN DECK CAR GO LIGHTS SWITC - [SDR UIEA2025031900234](https://openairdocs.org/sdr/UIEA2025031900234), Mar 15, 2025: SKIN. GOUGED. ENG 1, LH SIDE, SKIN ON AFT TORQUE BOX WITH A GOUGE.(

ENG 1, LH SIDE, SKIN ON AFT TORQUE BOX DAMAGE WAS REPAIRED IAW TRE6754205 ISSUED DATE 01MAR25. RDR NUMBE - [SDR UIEA2025031980233](https://openairdocs.org/sdr/UIEA2025031980233), Mar 15, 2025: BRACKET. CORRODED. CORROSION ON PROXIMITY SENSORS BASE SUPPORT (S234, S235) AT FWD BULKHEAD OF NLG WHEEL WELL. (L= 1 IN, W= 2 IN).(

PROXIMITY SENSORS BASE SUPPORT (S234, S235) A - [SDR UIEA2025030800232](https://openairdocs.org/sdr/UIEA2025030800232), Mar 15, 2025: ELEC CONNECTOR. CORRODED. CORROSION ON UPPER CONNECTOR OF PROXIMITY SENSOR S234 AT FWD BULKHEAD OF NLG WHEEL WELL.(

CONNECTOR S234 WAS REPLACED IAW SWPM 20-61-00 REV 88, TEST SATISFACT - [SDR UIEA2025030800230](https://openairdocs.org/sdr/UIEA2025030800230), Mar 15, 2025: LAMP. INOPERATIVE. REF DMI 225254 PARKING BRAKE LIGHT INOP, PARKING BRAKE LIGHTS, PARK BRAKE LIGHT 300 ANTISKID LIGHT VERIFIED OPERATIVE.(

PARK BRAKE LIGHT 300 ANTISKID LIGHT VE - [SDR UIEA2025031980228](https://openairdocs.org/sdr/UIEA2025031980228), Mar 15, 2025: SKIN. DENTED. LEFT WING, OUTBOARD SLAT #1 IN REAR SKIN WITH DENT.(

LEFT WING, SLAT 1 T/E WEDGE, LOWER SURFACE WAS REPAIRED IAW SRM 57- 43-02-2R-1 FIG.201 PAG.2-3 AND SRM 51 - [SDR UIEA2025031960223](https://openairdocs.org/sdr/UIEA2025031960223), Mar 15, 2025: SUPPORT. CRACKED. LEFT WING TRAILING EDGE INBOARD FLAP 4 SUPPORT MECHANISM 6-6 OUTER PIN WITH CRACK INDICATION.(

THE 6-6 OUTER PIN OF THE LH WING INB FLAP SUPPORT #4 WAS REPLAC - [SDR UIEA2025031900218](https://openairdocs.org/sdr/UIEA2025031900218), Mar 15, 2025: WEB. CORRODED. BULK CARGO COMPARTMENT, CUT OUT DOOR, BETWEEN STA 1480 AND STA 1502, INTERCOSTAL SKIN WITH CORROSION, L=2", W=1".(

BULK CARGO COMPARTMENT, CUT OUT DOOR, BETWE - [SDR UIEA2025030190216](https://openairdocs.org/sdr/UIEA2025030190216), Mar 15, 2025: ANTENNA. CORRODED. CORROSION ON BOTTOM TCAS ANTENNA.(

TCAS ANTENNA BOTTOM WAS REPLACED, ON P/N 071-50001-8102 S/N 582-34534, OFF P/N 071-50001-8102 S/N TLS33506. TEST SATISFACTO - [SDR UIEA2025030600215](https://openairdocs.org/sdr/UIEA2025030600215), Mar 15, 2025: BOLT. CORRODED. ENG 2, FAN CASE, OGVS BOLTS AREA, 113 BOLTS, BETWEEN 7 - 11 WITH CORROSION.(

ENG 2, FAN CASE, OGVS BOLTS AREA, 113 BOLTS, BETWEEN 7 - 11, CORROSION WAS EVALUA - [SDR UIEA2025030190204](https://openairdocs.org/sdr/UIEA2025030190204), Mar 15, 2025: RETAINER. CORRODED. CORROSION ON FWD SEAL RETAINER AT FWD BULKHEAD AT NLG WHEEL WELL. (BELOW TO PROXIMITY SENSORS S234, S235) (L= 4 IN, W= 0.5 IN).(

FWD SEAL RETAINER AT FWD BULK - [SDR UIEA2025030400203](https://openairdocs.org/sdr/UIEA2025030400203), Mar 15, 2025: RETAINER. CORRODED. CORROSION ON LH SEAL RETAINER AT FWD BULKHEAD AT NLG WHEEL WELL. (NEXT TO PROXIMITY SENSOR S256) (L= 4 IN, W= 0.5 IN).(

LH AT FWD BULKHEAD AT NLG WHEEL WELL S - [SDR UIEA2025030194202](https://openairdocs.org/sdr/UIEA2025030194202), Mar 15, 2025: CASE. CORRODED. ENG 1, FWD FAN CASE, AT 6 O'CLOCK APPROX, FWD MATING FLANGE WITH SEVERAL POINTS OF CORROSION (2EA).(

ENG 1, FWD FAN CASE, AT 6 O'CLOCK APPROX, FWD MATING FLAN - [SDR UIEA2025030194201](https://openairdocs.org/sdr/UIEA2025030194201), Mar 15, 2025: SKIN. CRACKED. FWD ENTRY DOOR, AFT LOWER CORNER, CRACK INDICATION AT HOLE 3 ON SKIN AT APPROX 10 O´CLOCK. AND CRACK INDICATION AT HOLE 4, THROUGH THE HOLE (SKIN AND BEAR STRA - [SDR UIEA2025030400200](https://openairdocs.org/sdr/UIEA2025030400200), Mar 15, 2025: WEDGE. DENTED. LEFT WING, SLAT 6 INBOARD FACE, TRAILING EDGE WEDGE WITH DENT APRX 42€Œ OF OUTBOARD EDGE.(

LEFT WING, SLAT 6 INBOARD FACE, T/E WEDGE AT APRX 42" OF OUTBOARD - [SDR UIEA2025030400199](https://openairdocs.org/sdr/UIEA2025030400199), Mar 15, 2025: WEDGE. BENT. LEFT WING, SLAT 6 INBOARD FACE WITH BENT APRX 50€Œ OF INBOARD EDGE.(

LEFT WING, SLAT 6 T/E WEDGE INBOARD FACE AT APRX 50" OF INBOARD EDGE WAS REPAIRED IAW SR - [SDR UIEA2025030400198](https://openairdocs.org/sdr/UIEA2025030400198), Mar 15, 2025: SKIN. CRACKED. FWD SERVICE DOOR, AFT LOWER CORNER, CRACK INDICATION AT HOLE 3 ON SKIN AT APPROX 2 O´CLOCK AND CRACK INDICATION AT HOLE 4, THROUGH THE HOLE (SKIN AND BEAR STRA - [SDR UIEA2025022500165](https://openairdocs.org/sdr/UIEA2025022500165), Mar 15, 2025: BRACKET. CORRODED. HORIZONTAL STABILIZER ENTER SECTION, UPPER SURFACE, LBL 41.5 AND BETWEEN REAR SPAR AND S-1, BRACKET WITH CORROSION.
(

HORIZONTAL STABILIZER ENTER SECTION, - [SDR UIEA2025022500164](https://openairdocs.org/sdr/UIEA2025022500164), Mar 15, 2025: FRAME. CORRODED. BULK CARGO COMPARTMENT, AT STA 1518, BTW STRG 28L AND 29L FRAME WITH CORROSION (L=2" W=1.5").(

BULK CARGO COMPARTMENT, AT STA 1518, BTW STRG 28L AND 29L FRAME - [SDR UIEA2025022500163](https://openairdocs.org/sdr/UIEA2025022500163), Mar 15, 2025: SUPPORT. CORRODED. CORROSION ON LH ANGLE STRAP SUPPORT (NEXT TO PROXIMITY SENSOR S256 CONNECTOR BOX) AT LH MID SIDE AREA OF FWD BULKHEAD AT NLG WHEEL WELL. (L= 0.260 IN, W= 0.1 IN - [SDR UIEA2025022500162](https://openairdocs.org/sdr/UIEA2025022500162), Mar 15, 2025: CASE. CORRODED. ENG 2, FAN CASE AREA AT 6 O´CLOCK POSITION, AROUND THE ANCHORED NUT WITH CORROSION.(

ENG 2, FAN CASE AREA AT 6 O´CLOCK POSITION, AROUND THE ANCHORED NUT WAS - [SDR UIEA2025022500161](https://openairdocs.org/sdr/UIEA2025022500161), Mar 15, 2025: FITTING. CORRODED. CORROSION AT LH LOWER FITTING ON FWD BULKHEAD OF NLG WHEEL WELL. (L= 0.1 IN, W= 0.2 IN)(

CORROSION LEVEL 1 WERE REMOVED, EVALUATED, INSPECTED AND FOUND TO BE All 479: https://openairdocs.org/aircraft/N1373A/reports.md ## STCs that may be installed (OpenAirDocs) (6) Approved for this aircraft's airframe or engine model, in force first, then newest. The registry doesn't record which STCs an aircraft has; its records do. ### Approved for the engine (GE CF6-80C2B2) - [STC SE01543CH](https://openairdocs.org/stc/SE01543CH): Replace Hamilton Sundstrand P/N 778839-13, 778839-14, 778839-19, 778839-20, 778839-37, 778839-38, 816682-1, 840618-2, 880724 carbon bushings with Cook Airtomic P/N AIR22947 Slotted Entry Busing in the High Pressure Shutoff Valve. Cook Airtomic - [STC SE01478CH](https://openairdocs.org/stc/SE01478CH): Installation of Cook Airtomic alignment joint p/n AIR 22912. Cook Airtomic - [STC SE00969CH](https://openairdocs.org/stc/SE00969CH): Install AeroControlex P/N 2605290-001 variable stator feedback control cable. AeroControlex Group TransDigm Inc - [STC SE01471AT](https://openairdocs.org/stc/SE01471AT): Replace right and left side Rohr, Inc. fire detection harness on GE CF6-80C2 engine. Unison Industries. Lists CF6-80C2 Series - [STC SE00463LA](https://openairdocs.org/stc/SE00463LA): Install fireproof blankets on the engine fan reverser intermediate fireseal, in lieu of fireproof intumescent coating. This STC is jointly by owned by Hi Temp Insulation and MRA Systems acting through Middle River Aircraft Systems, 103 Chesapeake Park Plaza, Baltimore, MD 21220. Hi Temp Insulation Inc - [STC SA2227SO](https://openairdocs.org/stc/SA2227SO): Installation of wiring and associated components for utilization of the Rolls Royce, Inc., ARINC, interface/readers UT1317 or UT1317/1, for the purpose of acquisition, recording, and analysis in real time of engine/aircraft/ systems. (767 SERIES POWERED BY RR RB-11-524 SERIES. Rolls Royce, Inc. Lists CF6-80 Series ## Earlier aircraft with N1373A The FAA can reassign an N-number once a registration is cancelled. These aircraft carried N1373A before. - [Cancelled 1982-11-04](https://openairdocs.org/deregistered/N1373A-1982-11-04): Piper PA-18-125, S/N 18-1202. Administratively canceled. Owner: [Hannon Harry R](https://openairdocs.org/faa-owner/HANNON%20HARRY%20R), [Anchorage, AK](https://openairdocs.org/faa-place/AK/Anchorage) ## Related - Other Boeing 767-31K aircraft: https://openairdocs.org/model/boeing-767-31k/aircraft.md - The GE CF6-80C2B2 engine: https://openairdocs.org/engine/ge-cf6-80c2b2.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.