Bombardier CL-600-2B19 CFCRJ

Summary

On 26 July 1993 at about 18:52 local time, a Bombardier CL-600-2B19 registered CFCRJ was involved in an accident near Byers, Kansas, United States. 3 people were on board and 3 died. The aircraft was destroyed. The NTSB has published a probable cause for this accident; it is quoted in full below.

Date

26 July 1993 at 18:52

Classification

Accident

Location

Byers, Kansas, United States

Coordinates

37.7809, -98.8596

Aircraft

Bombardier CL-600-2B19

Registration

CFCRJ

Category

Airplane

Engines

2

Operator

Not recorded

Operating rule

Part 91: General Aviation

Purpose of flight

Flight Test

Phase of flight

Not recorded

Route

Wichita → Wichita

Aircraft damage

Destroyed

Weather

VMC

Light

Day

NTSB number

CHI93MA276

3 people died.

THE CAPTAIN'S FAILURE TO ADHERE TO THE AGREED UPON FLIGHT TEST PLAN FOR ENDING THE TEST MANEUVER AT THE ONSET OF PRESTALL STICK SHAKER, AND THE FLIGHTCREW'S FAILURE TO ASSURE THAT ALL REQUIRED SWITCHES WERE PROPERLY POSITIONED FOR ANTI-SPIN CHUTE DEPLOYMENT. A FACTOR WHICH CONTRIBUTED TO THE ACCIDENT WAS THE INADEQUATE DESIGN OF THE ANTI-SPIN CHUTE SYSTEM WHICH ALLOWED DEPLOYMENT OF THE CHUTE WITH THE HYDRAULIC LOCK SWITCH IN THE UNLOCKED POSITION. (WHEN IN THE UNLOCKED POSITION, THE HOOKS CLASPING THE CHUTE SHACKLE TO THE AIRFRAME ARE OPEN.)

Quoted verbatim from the NTSB record. This site does not paraphrase or interpret it.

Read the full NTSB narrative

THE CREW WAS PERFORMING A LATERAL & DIRECTIONAL STABILITY TEST. CHANGES FROM EARLIER TESTS COMBINED NEW LEADING EDGE FAIRING, NEW FLAP SETTING, LOWER REFERENCE AIRSPEED, AND TRIAL SETTINGS FOR THE STALL PROTECTION SYSTEM (SHAKER & PUSHER). ENGINEERS HAD BRIEFED THE CREW DATA WOULD BE SUFFICIENT IF THE STEADY HEADING SIDESLIP (SHSS) MANEUVER ENDED AT A 15 DEG SIDESLIP, OR AT ONSET OF STALL WARNING; CREW AGREED TO END AT STALL WARNING. DURING THE TEST THE CAPT CONTINUED PAST STALL WARNING TO 21 DEG SIDESLIP AT FULL RUDDER. THE AIRPLANE ROLLED RAPIDLY THROUGH 360 DEG & ENTERED A DEEP STALL. THE COPILOT ATTEMPTED TO DEPLOY THE ANTI-SPIN CHUTE. HOWEVER, ALL THE CHUTE SYSTEM COCKPIT SWITCHES WERE NOT PROPERLY PRESET; INSTEAD OF ASSISTING RECOVERY, THE CHUTE PARTED FROM THE AIRPLANE. FULL CONTROL WAS NOT REGAINED BEFORE IMPACT. THE CHUTE SYSTEM DESIGN ALLOWED DEPLOYMENT OF THE CHUTE EVEN WHEN THE HYD LOCK SWITCH WAS IN THE UNLOCKED POSITION & THE HOOKS CLASPING THE CHUTE SHACKLE TO THE AIRFRAME WERE OPEN. SYSTEM TESTED OK BEFORE FLIGHT.

Quoted verbatim from the NTSB record.