# N169FE: 1966 Boeing 727-22, registration cancelled 2004-06-07 - Type: Cancelled registration (FAA registry, deregistered aircraft) - Cancelled: June 7, 2004 - Status when cancelled: Triennial form not returned - Airframe: [Boeing 727-22](https://openairdocs.org/model/boeing-727-22) (registry code 1384002) - Engine: [Pratt & Whitney JT8D-1](https://openairdocs.org/engine/pratt-whitney-jt8d-1) (registry code 52044) - Data sheets: [TCDS E2EA](https://openairdocs.org/tcds/E2EA) (OpenAirDocs) - Serial number: 18866 - Year built: 1966 - Type of aircraft: Fixed wing multi engine - Engine type: Turbo-jet - Airworthiness: Standard, transport - Airworthiness date: March 11, 1966 - Certificate issued: August 19, 1988 - Last registry action: January 20, 2004 - Mode S code: A1139F - Owner when cancelled: [Federal Express Corporation](https://openairdocs.org/faa-owner/FEDERAL%20EXPRESS%20CORPORATION) - Location: [Memphis, TN](https://openairdocs.org/faa-place/TN/Memphis) - Owner type: Corporation - Owner's area on the map: 35.0351° N, 89.9272° W: Placed by OpenAirDocs at the center of ZIP code 38118, within about 3 miles (OpenAirDocs). The owner's mailing address, not where the aircraft was based - The mark today: https://openairdocs.org/aircraft/N169FE - FAA registry: https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=169FE - Page: https://openairdocs.org/deregistered/N169FE-2004-06-07 From the FAA registry file of October 28, 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 727-22: https://openairdocs.org/model/boeing-727-22.md ## Service difficulty reports (42) Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. - [SDR 02FDEA00290](https://openairdocs.org/sdr/02FDEA00290), Apr 25, 2002: HYDRAULIC LINE. LEAKING. HYDRAULIC A-QTY TO ZERO IN FLT. REMOVED AND REPLACED NR 1 ENG A-SYSTEM HYDRAULIC PRESS LINE. REMOVED AND REPLACED 1 & 2 ENGINE HYD PUMP CASE DRAIN FILTERS PER M - [SDR 00FDEA00887](https://openairdocs.org/sdr/00FDEA00887), Dec 19, 2000: SENSOR. FAILED. 00-366 AFT T/O STICK SHAKER ACTIVATED. PULLED AC STALL WARN NR 1 CIRCUIT BREAKER & RETURN FOR LAND. R&R RIGHT ANGLE OF ATTACK SENSOR IAW 727 MM 34-18-51, NR 1 S - [SDR 98FDEA00612](https://openairdocs.org/sdr/98FDEA00612), Sep 25, 1998: FLOORBEAM. CORRODED. BS 680 CORROSION ON BOTTOM SIDE OF FLOORBEAM LWR FLANGE AT SEV AREAS. BLENDED OUT CORROSION PER EA 7-5310-29662 DATED 9-14-98. INSTALLED .071 7075-T6 ANGLES ON - [SDR 98FDEA00611](https://openairdocs.org/sdr/98FDEA00611), Sep 25, 1998: FRAME. CRACKED. AFT CARGO FWD DOOR PORTAL FRAME CRACKED AT LOWER FWD DOOR STOP, OUTBD LWR FAST. REMOVED AND REPLACED AFT CARGO FWD DOOR PORTAL FRAME PER SRM 51-10-1. - [SDR 98FDEA00610](https://openairdocs.org/sdr/98FDEA00610), Sep 25, 1998: SKIN. CORRODED. CORROSION ON FUSELAGE SKIN 25 PERCENT LOBE OF MATERIAL BETWEEN STR 25R-26R, BS 360. CUT OUT CORROSION, INSTALLED DOUBLER AND FILLER ON OUTSIDE OF SKIN EXTENDING - [SDR 98FDEA00609](https://openairdocs.org/sdr/98FDEA00609), Sep 25, 1998: FLOORBEAM. DAMAGED. UPPER LOBE FLOORBEAM HAS DOUBLER DRILL HOLE BS 990. CUT OUT DAMAGE, INSTALLED DOUBLER PER AARD 53-10-07-02 AND EA 7-5310-29648. - [SDR 98FDEA00608](https://openairdocs.org/sdr/98FDEA00608), Sep 25, 1998: FLOORBEAM. DAMAGED. CABIN FLOORBEAM HAS ONE DOUBLE DRILL HOLE BS 1010, RBL 63. CUT OUT DAMAGE AND INSTALLED DOUBLER PER AARD 53-10-07-02 FIG 3 AND EA 7-5310-29648. - [SDR 98FDEA00607](https://openairdocs.org/sdr/98FDEA00607), Sep 25, 1998: FLOORBEAM. DAMAGE. FLOORBEAM CUT ACROSS TOP FLANGE BS 1130, RBL 63. BLENDED OUT DAMAGE AND INSTALLED .080 STRAP OF 7075-T6 ALUM PER AARD 53-10-07-01 AND 7-5310-29698. - [SDR 98FDEA00606](https://openairdocs.org/sdr/98FDEA00606), Sep 25, 1998: FLOORBEAM. DAMAGED. CABIN FLOORBEAM CUT ACROSS TOP FLANGE BS 1050, RBL 63. CUT OUT DAMAGE, INSTALLED DOUBLER PER AARD 53-10-07-02 AND EA 7-5310-29648. - [SDR 98FDEA00605](https://openairdocs.org/sdr/98FDEA00605), Sep 25, 1998: FLOORBEAM. DAMAGED. CABIN FLOORBEAM CUT ACROSS TOP FLANGE AT STR 970, RBL 63. CUT OUT DAMAGE AND INSTALLED DOUBLER PER AARD 53-10-07-02 AND EA 7-5310-29648. - [SDR 98FDEA00603](https://openairdocs.org/sdr/98FDEA00603), Sep 25, 1998: FLOORBEAM. CORRODED. UPPER LOBE, BS 1050 HEAVY CORROSION ON LWR FWD LEG OF FLOORBEAM AT LBL 29. BLENDED OUT CORROSION IN AREA NOTED PER SRM 51-10-6. BLENDED AREA OUT OF LIMITS. CUT - [SDR 98FDEA00613](https://openairdocs.org/sdr/98FDEA00613), Sep 16, 1998: FLOORBEAM. CORRODED. AFT CARGO FLOORBEAM BS 1050, LWR CHORD HAS CORROSION FROM RBL 24- RBL 43. INSTALLED FLOORBEAM REPAIR LWR CHORD PER SRM 53-10-8 PG 11-17. - [SDR 98FDEA00602](https://openairdocs.org/sdr/98FDEA00602), Sep 16, 1998: FLOORBEAM. CORRODED. UPPER LOBE HEAVY CORROSION ON UPPER SURFACE OF LWR FLANGE OF FLOORBEAM BS 1050, RBL 39. INSTALLED FLOORBEAM LWR CHORD REPAIR PER SRM 53-10 8 PG 11-17. - [SDR 98FDEA00601](https://openairdocs.org/sdr/98FDEA00601), Sep 14, 1998: FLOORBEAM. MISDRILLED. UPPER LOBE FLOORBEAM BS 1070, RBL 625 HAS DOUBLE DRILL HOLE IN FLOORBEAM. CUT OUT AREA OF DAMAGE AND REPAIR PER AARD 53-10-07. - [SDR 98FDEA00559](https://openairdocs.org/sdr/98FDEA00559), Sep 9, 1998: FLOORBEAM. CORRODED. NR 0936 - UPPER LOBE, FLOORBEAM BS 680 CORROSION ON UPPER FLANGE LBL 10- RBL 6. CORROSION REMOVAL OUT OF LIMITS AT LBL 5 FWD SIDE OF FLANGE. INSTALLED ANGLE DOU - [SDR 98FDEA00557](https://openairdocs.org/sdr/98FDEA00557), Sep 9, 1998: SKIN. DAMAGED. NR 0698 - LFEC IND 10 PERCENT MATERIAL LOSS JUST ABOVE STR 23 LT, 2 AFT OF BS 360 FRAME. DAMAGED AREA, REMOVED AND REPLACED DOUBLER INSTALLED PER SRM 53-30-3 PG - [SDR 98FDEA00556](https://openairdocs.org/sdr/98FDEA00556), Sep 9, 1998: SKIN. CORRODED. NR 0342 - UPPER LOBE BS 886 HEAVY CORROSION AT WINDOW BELT AND ON SKIN 8 ABOVE STR 14L. REMOVED CORROSION FRAME WAS TAKEN OUT OF LIMITS. WINDOW FRAME REPLACED F - [SDR 98FDEA00549](https://openairdocs.org/sdr/98FDEA00549), Aug 26, 1998: SKIN. DAMAGED. LOW FREQ EDDY CURRENT IND 15 PERCENT MATERIAL LOSS BS 360 AFT FASTENER ROW STR 4 RT BOTTOM OF SKIN LAP TO ONE INCH BELOW. REMOVED DAMAGE AND INSTALLED DOUBLER P - [SDR 98FDEA00550](https://openairdocs.org/sdr/98FDEA00550), Aug 18, 1998: FLOORBEAM. CORRODED. UPPER LOBE BS 380 HEAVY CORROSION ON FLOORBEAM AT LBL 34. REMOVED CORROSION PER SRM 51-10-6. CORROSION REMOVAL OUT OF LIMITS. INSTALLED REPAIR PER AARD 53-10-07 - [SDR 97FDEA00299](https://openairdocs.org/sdr/97FDEA00299), May 21, 1997: ENGINE. FAILED. PASSING 16,000 FEET ON DESCENT POWER AT IDLE, NR 2 ENGINE FLAMED OUT. ONLY ABNORMAL INDICATION WAS ZERO OIL PRESSURE. QUANTITY OK WITH N1 ROTATION. NO N2 WAS OB - [SDR 96FDEA00194](https://openairdocs.org/sdr/96FDEA00194), Feb 7, 1996: FITTING. CRACKED. CRACK IN HOLES NR 2 AND NR 4 OF ROW 2, FWD O/B FLANGE, AT BS 870 JUST BELOW STR 9R. REPAIRED CRACK IN HOLES NR 2 AND NR 4 OF ROW 2 FWD O/B FLANGE, AT BS 870 JUS - [SDR 96FDEA00193](https://openairdocs.org/sdr/96FDEA00193), Feb 6, 1996: SKIN. CORRODED. CORROSION ON SKIN INTERIOR AT BS 875 TO 878 BELOW STR 9R. REPAIRED CORROSION ON INTERIOR SKIN AT BS 875 TO 878 BELOW STR 9R PER FEDEX EA 7-5310-26957. - [SDR 96FDEA00192](https://openairdocs.org/sdr/96FDEA00192), Feb 6, 1996: FITTING. CRACKED. DURING UT INSPECTION, CRACK INDICATION FOUND AT FUSE BS 870 TERMINAL FITTING RT AFT OF ROW 2, BELOW FASTENER 6. REPAIRED CRACK AT BS 870 TERMINAL FITTING RT AFT - [SDR 96FDEA00183](https://openairdocs.org/sdr/96FDEA00183), Feb 2, 1996: STIFFENER. CORRODED. CORROSION (C53-224-03-1/2), ON VERTICAL STIFFENER BS 336 WL 181 RBL 15. REMOVED CORROSION AND INSTALLED REPAIR IAW FEDEX SRM 51-40-4. - [SDR 96FDEA00182](https://openairdocs.org/sdr/96FDEA00182), Feb 2, 1996: STIFFENER. CORRODED. CORROSION (C53-111-03-1/2), ON VERTICAL STIFFENER BS 319 WL 181 RBL 15. REMOVED CORROSION AND INSTALLED REPAIR IAW FEDEX SRM 51-40-4. - [SDR 96FDEA00167](https://openairdocs.org/sdr/96FDEA00167), Feb 1, 1996: FITTING. CRACKED. CRACK IN AFT FLANGE OF TERMINAL FITTING AT BS 870 STR 13R. HFEC DAMAGE FABRICATED REPAIR PARTS AND INSTALLED PER EWO NR 96-2-43. - [SDR 96FDEA00157](https://openairdocs.org/sdr/96FDEA00157), Jan 31, 1996: RIB. CORRODED. CORROSION ON NR 6 K-FLAP MOST OUTBOARD RIB WHERE LANDING LIGHT CONDUIT ATTACHES TO RIB UPPER BOLT HOLE. REMOVED CORROSION, REPAIRED PER EWO NR 96-2025. - [SDR 96FDEA00156](https://openairdocs.org/sdr/96FDEA00156), Jan 31, 1996: HINGE. CORRODED. RIGHT WING OUTBOARD AILERON INBOARD HINGE FITTING IS CORRODED (NR 2 HINGE FITTING). REMOVED CORROSION, FABRICATED REPAIR ANGLE ON FLANGE ON RIGHT WING OUTBOARD - [SDR 96FDEA00155](https://openairdocs.org/sdr/96FDEA00155), Jan 31, 1996: SKIN. DENTED. DENT TO SKIN DUE TO TOOL BOX AT STA 1083 AND BETWEEN STR 28 - 29L. REPAIRED DAMAGED SKIN AT BS 1083, BETWEEN STR 28 - 29L PER FEDEX SRM 53-30-3 PER ENGINE REPAI - [SDR 96FDEA00137](https://openairdocs.org/sdr/96FDEA00137), Jan 26, 1996: FITTING. CORROSION. CORROSION ON STR TO FRAME TIE AT BS 360 STR 20L. REMOVED AND REPLACED STR TIE AT BS 360 20L, DUE TO CORROSION OUT OF LIMITS. - [SDR 96FDEA00136](https://openairdocs.org/sdr/96FDEA00136), Jan 26, 1996: FITTING. CRACKED. LT VERTICAL FIN FRONT SPAR TERMINAL FITTING FWD O/B FLANGE IS CRACKED. REPAIRED LT VERTICAL FIN FRONT SPAR TERMINAL FITTING FWD O/B FLANGE IAW FEDEX EA 7-5510-2 - [SDR 96FDEA00135](https://openairdocs.org/sdr/96FDEA00135), Jan 26, 1996: STRINGER. DELAMINATION. DELAMINATION OF SKIN LAP STRINGER 19L BS 360 TO 368. REMOVED FASTENERS IN SKIN LAP AT STR 19L. UPON REMOVAL OF FASTENERS FOUND NO FURTHER INDICATIONS OF DELAMIN - [SDR 96FDEA00077](https://openairdocs.org/sdr/96FDEA00077), Jan 19, 1996: FITTING. CRACKED. DURING UT INSP, CRACK IND FOUND AT FUSE BS 870 TERMINAL FITTING RT AFT OF ROW 2, BELOW FASTENER 6. REPAIRED CRACK AT BS 870 TERMINAL FITTING RT AFT OF ROW 2, BE - [SDR 96FDEA00076](https://openairdocs.org/sdr/96FDEA00076), Jan 19, 1996: FITTING. CRACKED. CRACK IN AFT FLANGE OF TERMINAL FITTING AT BS 870 STR 13R. HFEC DAMAGE, FABRICATED REPAIR PARTS AND INSTALLED PER EWO NR 96-2043. - [SDR 96FDEA00075](https://openairdocs.org/sdr/96FDEA00075), Jan 19, 1996: SKIN. LIGHTNING STRIKE. LIGHTNING STRIKES AT BS 706, 793, 824 AND 888 BETWEEN STR 4 AND 5. REPAIRED LIGHTNING STRIKES AT BS 750, 793, 824 BY INSTALLING NEW FASTENERS. REPAIRED BS 888 B - [SDR 96FDEA00074](https://openairdocs.org/sdr/96FDEA00074), Jan 19, 1996: SKIN. CHAFING. RT WING I/B FOREFLAP IS CHAFING APPROX 24 INCHES O/B FROM I/B LEADING EDGE. REPAIRED DAMAGE AREA ON RT WING I/B FOREFLAP APPROX 24 INCHES O/B FROM I/B LEADING E - [SDR 96FDEA00078](https://openairdocs.org/sdr/96FDEA00078), Jan 18, 1996: SKIN. CORRODED. CORROSION ON SKIN INTERIOR AT BS 875 TO 878 BELOW STR 9R. REPAIRED CORROSION ON INTERIOR SKIN AT BS 875 TO 878 BELOW STR 9R PER FEDEX EA 7-5310-26957. - [SDR 96FDEA00067](https://openairdocs.org/sdr/96FDEA00067), Jan 18, 1996: TE SKIN. DISBONDED. RIGHT WING INBD FORE FLAP UPPER SURFACE HAS DISBOND ON T/E AREA MARKED. REPAIRED RT WING INBOARD FORE FLAP IAW SRM 51-40-6. - [SDR 96FDEA00066](https://openairdocs.org/sdr/96FDEA00066), Jan 18, 1996: STRINGER. CORRODED. CORROSION (C53-224-03-1/2) ON STR 22R, BS 396. REMOVED CORROSION AT BS 396, STR 22R. REMOVED IN A 1 INCH BY 2 INCH AREA. ORIGINAL METAL THICKNESS IS .040 INCH. - [SDR 96FDEA00065](https://openairdocs.org/sdr/96FDEA00065), Jan 17, 1996: STIFFENER. CORRODED. CORROSION (C53-111-03-1/2), ON VERTICAL STIFFENER BS 319 WL 181 RBL 15. REMOVED CORROSION AND INSTALLED REPAIR IAW FEDEX SRM 51-40-4. - [SDR 96FDEA00060](https://openairdocs.org/sdr/96FDEA00060), Jan 17, 1996: SKIN. GOUGED. THERE'S A GOUGE ON THE RT WING FOREFLAP UPPER SURFACE ABOVE THE NR 8 FLAP TRACK. REMOVED AND REPLACED DAMAGE ON O/B RT WING FOREFLAP IAW FEDEX SRM 51-40-6. - [SDR 96FDEA00064](https://openairdocs.org/sdr/96FDEA00064), Jan 15, 1996: STIFFENER. CORRODED. CORROSION (C53-224-03-1/2), ON VERTICAL STIFFENER, BS 336 WL 181 RBL 15. REMOVED CORROSION AND INSTALLED REPAIR IAW FEDEX SRM 51-40-4. ## Other aircraft with N169FE - [Registered now](https://openairdocs.org/aircraft/N169FE): Boeing 767-300F, S/N 63101, built 2018 --- 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.