Endeavor Air Bombardier Inc CL 600 2B19 100 incident
Bombardier Inc CL 600 2B19 100 · Incident: powerplant system/component malfunction/failure en route
From Baltimore/Washington International Thurgood Marshall Airport (BWI) to Cincinnati Northern Kentucky International Airport (CVG)
Event
- NTSB case
- ENG17IA008
- Event typeAccident: someone killed or seriously injured, or the aircraft substantially damaged (NTSB definition). Incident: an occurrence that affected or could have affected safety, short of that. Glossary
- Incident
- InvestigationHow far the investigation had got when the record was published: preliminary, ongoing, final or completed. Unknown where the source does not say. Glossary
- Completed
- API-reported fatalities
- 0 · all aircraft and ground
- Ground fatalities
- Unknown
- OperationWhat kind of flying it was, grouped by the rules it flew under: airline (US Part 121), air taxi and commuter (Part 135), general aviation (Part 91 and similar), military or government. Glossary
- Airline
- WeatherVisual meteorological conditions (VMC): good enough to fly by looking outside. Instrument conditions (IMC): cloud or low visibility, flying by instruments. Glossary
- Unknown
Bombardier Inc CL 600 2B19 100
- Aircraft type
- Bombardier CL-600
- Category
- Airplane
- RegistrationThe aircraft's tail number, such as N12345 or G-ABCD. Registrations are reissued, so the same one years apart can be a different aircraft. Glossary
- N8986B
- Operator
- Endeavor Air
- Onboard fatalities
- Unknown
- Route
- From Baltimore/Washington International Thurgood Marshall Airport (BWI), Baltimore, MDTo Cincinnati Northern Kentucky International Airport (CVG), Covington, KY
- Aircraft age
- About 13 years (built 2004)
- Flight rulesThe regulations the flight operated under: in the US, Part 91 (general aviation), Part 121 (airlines), Part 135 (air taxi and commuter) and others; for flights abroad, the NTSB's coarser commercial or non-commercial code. Glossary
- Part 121: Air Carrier
- Phase of flightThe stage of the flight when things started to go wrong: standing, taxi, takeoff, initial climb, en route, maneuvering, approach or landing. Glossary
- En route · climb to cruise
- Defining eventThe single coded event the NTSB judges best describes what happened (records from 2008 on). Older records name the first occurrence in the sequence instead. Glossary
- Powerplant system/component malfunction/failure
- DamageDestroyed: beyond practical repair. Substantial: damage that affects the structure, performance or handling and normally needs major repair. Minor: less than that. Glossary
- None
Cause areas
- Aircraft › Aircraft power plant
Approximate · Coordinates from the NTSB case API, which marks them as estimated or does not say; no uncertainty radius is established.
NTSB narrative
The No. 2 engine fan blade airfoil separation was caused by a low cycle fatigue crack that originated at the forward blade pin hole attachment tang due to insufficient residual stress (hoop stress) levels in the Ti-8-1-1 blade material. The fan blade had undergone a hot form repair following a bird strike incident in December 2007 to restore the blade profile. During the hot form repair process the blade was placed in a ceramic die and heated to 1150-1200oF to restore the blade geometry. The hot form process relieved the compressive residual stress layer in the fan blade and the layer was not properly restored with a lance peen/shot peen step as called out in the GE Standard Repair Manual. There was visual evidence of 100% lance peen/shot peen coverage on the fan blade attachment pin holes surfaces that was identified during the materials lab examination, but the peen marks were most likely formed during the original fan blade manufacturing process.
When the fan blade airfoil separated during the incident it was contained by the engine fan case containment system. The fan blade impact with the fan case containment system resulted in a bulge in the Kevlar wrap that damaged the attaching hardware at the fan cowl flanges, and the cowl subsequently separated when exposed to the jet stream. When the fan cowls separated from the engine they impacted the thrust reverser translating cowl and core cowl and resulted in gouging and surface buckling.
The fan blade airfoil separation caused a fan imbalance that led to high No. 2 engine vibration levels. The high vibration levels caused the engine transition case to LPT flange separation, AGB housing fracture, and starter damage.
Probable cause
A Bombardier CRJ200 No. 2 engine failure due to the separation of a fan blade airfoil at a low cycle fatigue crack that originated at the forward fan blade pin hole attachment. The separated fan blade had previously undergone a hot form repair and both metallurgical analysis and repair records indicated that the lance/shot peen step required to restore sufficient residual stress levels to the blade material was not completed.
Verbatim NTSB analysis and probable cause from the NTSB dataset
Sources
NTSB record ENG17IA008
- Event ID
- 20170124X45041
- Case number
- ENG17IA008
- Dataset
- full-current
- Source SHA-256
- 5cf380f0061817c0331a6b2d8cc7e0ee3a79bea469a1001dc5c10e56f35f5ab3
Source notes (4)
- Unreviewed is an editorial label, not an investigation status. API-sourced is not report-checked or human-reviewed. Explicit event totals are used without summing aircraft injury tables; onboard allocation is withheld. Unknown values remain unknown. The operation category is mapped from the NTSB-reported FAR part and has not been reviewed.
- Filled from the NTSB case API where the bulk record had no value: investigation status, coordinates, damage. Values present in the bulk record are kept.
- The date is the local date, which is the same as the UTC date the NTSB stores.
- API snapshot SHA-256: 6e764555fed85f405b03c4bfe8c446b4fcac57486583d9999c886ed7450371d4; retrieved 2026-09-16T04:58:04.249Z.