Aircraft record

N355PH1997 Dehavilland DHC-8-202

DeregisteredUnclaimedSource: FAA, updated Oct 20, 2026

This N-number isn't registered right now. Below is its last known registration, canceled Jan 24, 2013.

Safety record in brief:No NTSB accidents or incidents since 19823 ADs may apply223 service difficulty reports

Registration: Deregistered
Last based in: Wilmington, DE; owner city / state
Engine: PW123 · 2142 hp; P&W Canada
Owners: 1; since 2008
NTSB events: None; since 1982
ADs may apply: 3; confirm with A&P
Service reports: 223; since 1995

Registration

FAA Aircraft Registry · Oct 20, 2026

Last registered owner: Win Win Services LLC
Owner type: Corporation
City, state: Wilmington, DE
Certificate issued: Nov 3, 2008
Canceled: Jan 24, 2013
Airworthiness: Standard · Transport
Airworthiness date: Oct 31, 1997

We never show street addresses, even though they appear in the public FAA file. Individual owners are shown by city and state only.

Airframe & engine

FAA Registry + type data

Airframe

Manufacturer: Dehavilland
Model: DHC-8-202
Year: 1997
Serial number: 500
Aircraft type: Fixed wing multi engine
Category: Land
Certification: Type Certificated
Seats: 40
Engines: 2
Max takeoff weight: 20,000 and over lb
Mode S code: A3F8AD

Engine

Make and model: P&W Canada Pw123
Type: Turbo-prop
Power: 2142 hp

Total time and engine hours aren't public. They appear here once the owner adds logbooks.

Ownership history

Ownership history from FAA records

2008 – 2013Win Win Services LLCWilmington, DE

Individual owners are shown by city and state only.

Safety record

NTSB · Oct 15, 2026 · FAA ADs · Oct 20, 2026 · SDRs · Oct 16, 2026

NTSB events (0)

No NTSB accidents or incidents found for this airframe since 1982.

Accident history for this model

ADs published since 1998 that may apply (3)

These match the airframe or engine model. Whether each one applies, and whether it's been complied with, depends on serial numbers, equipment and logbook entries. Applicability must be confirmed by a mechanic against the aircraft's records.

AD	Subject	Effective	Applies to
2013-15-08	Pratt & Whitney Canada Corp. Turboprop Engines	Sep 17, 2013	Engine (PW123)Serial numbers per Table 1 of the Appendix of P&WC Service Bulletin No. PW100-72-21823, Revision 3. Only with: First-stage power turbine blade P/N 3120973-01, 3120983-01, or 3054053-01 installed with a serial number listed in the referenced SB table.
2012-26-08	Pratt & Whitney Canada Corp. Turboprop Engines	Feb 15, 2013	Engine (PW123)Serial numbers per P&WC ASB No. PW100-72-A21813 Rev 3, PW100-72-A21802 Rev 4, and PW100-72-A21798 Rev 5. Only with: Engines with propeller shafts having serial numbers listed in the referenced P&WC ASBs.
2004-20-01	Pratt & Whitney Canada Models PW123, PW123B, PW123C, PW123D, PW123E, PW123AF, PW124B…	Nov 5, 2004	Engine (PW123)Only with: Mechanical fuel controls (MFCs) P/Ns 3244841-21, 3244853-17, 3244855-15, 3244857-14, 3244858-23, 3244871-5, 3244873-4, and 3244874-4 installed.

AI-extracted — verify against original. Matched from each AD's applicability section; ADs replaced by a later AD are left out.

Service Difficulty Reports (223)

Reports of failures and defects that operators and repair stations sent to the FAA since 1995. A report describes one finding; it is not an accident.

Engine · oil system · overservicedJun 28, 2008
PDX - CREW REPORTS OIL ODOR IN CABIN. FOUND ENGINE OIL FOR NR 1 OVER SERVICED. ADJUSTED LEVEL. GROUND RUN CHECKS OK. RETURNED TO SERVICE. NO PARTS REPLACED. (A)
From FAA Service Difficulty Reports; matched by N-number and serial number.
Fuselage · floorbeam · corrodedApr 18, 2008
PDX C4 CHECK ZONE 144 AFT FLOOR SUPPORT ANGLE AT STA X600 IS CORRODED AT Y29.5R. REMOVED CORROSION IAW CPM CHAP 4. UT THICKNESS IAW -8 200 PT 1, 51-00-04, HI .083 LOW .077. HFEC INSP. IAW -8 200 NDTM PT 6, 51-00-01 NO CRACKS NOTED. REMOVED .006" MATERIAL FOUND WITHIN LIMITS PER -8 200 SRM 51-20-11…
From FAA Service Difficulty Reports; matched by N-number and serial number.
Fuselage · floorbeam · corrodedApr 18, 2008
PDX C4 CHECK ZONE 144 AFT FLOOR SUPPORT ANGLE AT STA X600 IS CORRODED AT Y20L AND Y24L. REMOVED CORROSION IAW CPM CHAP 4. UT THICKNESS IAW -8 200 PT 1, 51-00-04, HI .083 LOW .061. HFEC INSP. IAW -8 200 NDTM PT 6, 51-00-01 NO CRACKS NOTED. REMOVED .022" MATERIAL FOUND OUT OF LIMITS PER -8 200 SRM…
From FAA Service Difficulty Reports; matched by N-number and serial number.

Show all 10 reports

Fuselage · structure · corrodedApr 18, 2008
PDX C4 CHECK ZONE 144 SUBFLOOR TOP SURFACE IS CORRODED AT Y580-X581 AND Y24L-Y26L. REMOVED CORROSION IAW CPM CHAP 4. REMOVED .002 MATERIAL FROM ORIGINAL THICKNESS. .043 MATERIAL REMAINING WITHIN LIMITS IAW -8 200 SRM 51-20-11 STEP 3. HFEC INSP. IAW -8 200 NDTM PT 6, 51-00-01 NO CRACKS NOTED. C/W…
From FAA Service Difficulty Reports; matched by N-number and serial number.
Fuselage · structure · corrodedApr 18, 2008
PDX C4 CHECK ZONE 144 SUBFLOOR IS CORRODED AT Y565 AND Y25L-Y27L. REMOVED CORROSION IAW CPM CHAP 4. REMOVED .002 MATERIAL FROM ORIGINAL THICKNESS, .043 MATERIAL REMAINING WITHIN LIMITS IAW -8 200 SRM 51-20-11 STEP 3. HFEC INSP. IAW -8 200 NDTM PT 6, 51-00-01 NO CRACKS NOTED. ALODINED PRIMED…
From FAA Service Difficulty Reports; matched by N-number and serial number.
Fuselage · structure · corrodedApr 18, 2008
PDX C4 CHECK ZONE 144 SUBFLOOR IS CORRODED AT Y546 AND Y35.5L. REMOVED CORROSION IAW CPM CHAP 4. REMOVED .003 MATERIAL FROM .045 ORIGINAL THICKNESS, .042 MATERIAL REMAINING WITHIN LIMITS IAW -8 200 SRM 51-20-11 STEP 3. HFEC INSP. IAW -8 200 NDTM PT 6, 51-00-01 NO CRACKS NOTED. ALODINED PRIMED…
From FAA Service Difficulty Reports; matched by N-number and serial number.
Fuselage · frame · corrodedApr 18, 2008
PDX C4 CHECK SUSPECT CORROSION OF FRA X201 AT STR 31S. REMOVED CORROSION IAW CPM CHAP 4 PARA 9A-B(1-6(A)). UT THICKNESS CHECK IAW -8 200 NDTM PT 1, 51-00-04 HI .032 LOW .029. HFEC INSP. IAW -8 200 NDTM PT 6, 51-00-01 NO CRACKS NOTED. ALODINED PRIMED IAW -8 200 SRM 51-20-16, 51-20-36.
From FAA Service Difficulty Reports; matched by N-number and serial number.
Fuselage · structure · damagedApr 18, 2008
PDX C4 CHECK CORROSION ON FORE AND AFT LOWER CORNER COMBING PIECES, I/B FLANGE, ON PAX DOOR APERTURE LOWER EDGE. REMOVED NUTPLATE FROM CASTING AND REMOVED CORROSION. REMOVED .002" MATERIAL REF CPM SECT 4. WITH IN LIMITS PER -8 200 SRM 51-20-11. REINSTALLED NUT PLATE ON CASTING.
From FAA Service Difficulty Reports; matched by N-number and serial number.
Fuselage · keelbeam · corrodedApr 18, 2008
PDX C4 CHECK SUSPECT CORROSION AT I/B BOTTOM OF VERTICAL KEELBEAM AT STA X370 AND STR 31P. REMOVED CORROSION AT BOTTOM OF VERTICAL KEEL BEAM STA 370.8. REF CPM CHAP 4 PG 4-25 PARA 9. ORIGINAL THICKNESS .050" REMAINING THICKNESS .046". MAX MATERIAL REMOVED .004 WITHIN LIMITS REF -8 200 SRM 51-20-11…
From FAA Service Difficulty Reports; matched by N-number and serial number.
Fuselage · stringer · corrodedApr 18, 2008
PDX C4 CHECK CORROSION ON STR 23S (X387 TO X392) AND CONNECTING CLIP TO FRONT SPAR MAIN FRAME ON AFT SIDE AT X387.35. REMOVED LIGHT SURFACE FROM STRINGER AND CONNECTING CLIP USING SCOTCH BRITE PAD. ALODINED EXPOSED ALUM. IAW -8 200 CPM CHAP 4 AND 5. NEGLIGIBLE MATERIAL REMOVED. PRIMED IAW…
From FAA Service Difficulty Reports; matched by N-number and serial number.

Showing the 10 most recent of 223 reports.

Sources

FAA Aircraft RegistryRegistration, owner city and state, airframe, engineupdated Oct 20, 2026
NTSB accident and incident databaseAccidents and incidents since 1982updated Oct 15, 2026
FAA Airworthiness Directives (Federal Register)ADs published since 1998updated Oct 20, 2026
FAA Service Difficulty ReportsReports since 1995updated Oct 16, 2026

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