dfs346
Pre-Flight
For the first time in the public domain, the FBI has released one of the technical reports on the Boeing Company’s tests of the Boeing 727 with the air stairs down in flight. The report in question is numbered and titled D6-7771: “Flight Characteristics with Aft Airstair Down – B”. The airplane used was the second prototype, tail number N72700. The tests described were conducted on March 13 and 19, 1964.
For anyone interested, the FBI release is at https://vault.fbi.gov/D-B-Cooper /d.-b.-cooper-part-71-of-71/view. The Boeing report is on pages 333-356.
I extracted the following key passages: “Purpose of Conditions Performed: Simulate a failure of the aft airstair up-latch in flight, evaluating the characteristics of the extended airstair and the effect on airplane performance and handling. The airstair was extended both by allowing it to freefall and by utilizing normal hydraulic power. These extensions were made with the airplane trimmed for level flight at 125 knots and flaps at 25 degrees. The airstair extended a nominal 8.5 degrees when allowed to free-fall and it required only approximately one-tenth unit of nose-down trim to compensate for the stair. The stair extended a nominal 13.5 degrees with hydraulic power and this caused approximately a three-tenths unit nose-down trim change."
On November 24, 1971, the hijacker of Flight 305 departed the airplane via the aft airstair, at an indicated air speed of between 160 and 170 knots. Would it be reasonable to conclude that via the control lever, with or without hydraulic power, he would have been unable to lower the stairs by more than 13.5 degrees?
Alternatively, did the Flight 305 airplane (model 727-51, tail number N467US) have a different control system for the aft airstair, or a more powerful hydraulic system than the prototype N72700, such that the airstair could be fully extended in flight? Documents in the public domain indicate that the 727 hydraulic system generally had an operating pressure range of 2800-3100 psi, but I have not found documents specific to the prototypes or the 727-51 model.
For anyone interested, the FBI release is at https://vault.fbi.gov/D-B-Cooper /d.-b.-cooper-part-71-of-71/view. The Boeing report is on pages 333-356.
I extracted the following key passages: “Purpose of Conditions Performed: Simulate a failure of the aft airstair up-latch in flight, evaluating the characteristics of the extended airstair and the effect on airplane performance and handling. The airstair was extended both by allowing it to freefall and by utilizing normal hydraulic power. These extensions were made with the airplane trimmed for level flight at 125 knots and flaps at 25 degrees. The airstair extended a nominal 8.5 degrees when allowed to free-fall and it required only approximately one-tenth unit of nose-down trim to compensate for the stair. The stair extended a nominal 13.5 degrees with hydraulic power and this caused approximately a three-tenths unit nose-down trim change."
On November 24, 1971, the hijacker of Flight 305 departed the airplane via the aft airstair, at an indicated air speed of between 160 and 170 knots. Would it be reasonable to conclude that via the control lever, with or without hydraulic power, he would have been unable to lower the stairs by more than 13.5 degrees?
Alternatively, did the Flight 305 airplane (model 727-51, tail number N467US) have a different control system for the aft airstair, or a more powerful hydraulic system than the prototype N72700, such that the airstair could be fully extended in flight? Documents in the public domain indicate that the 727 hydraulic system generally had an operating pressure range of 2800-3100 psi, but I have not found documents specific to the prototypes or the 727-51 model.
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