X-15 FLIGHT REQUEST

Flight No.: 3-50-74 Scheduled Date: October 8, 1965

Pilot: Capt. W. Knight

Purpose: Pilot checkout

Launch: Hidden Hills on a magnetic heading of 212°, MH-96 Adaptive, R.C. "OFF," BCS "OFF," heading vernier to "Standby," ventral off.

Launch point coordinates: 36° 20' N, 115° 59' W.

No. Time Alt V a q Event

1. 0 45 790 2 145 Launch, light engine at 75%T. (Chamber pressure = 480 psi). Rotate at 11° a until q = 30°.

2. 27 48 1600 11 500 q = 30°, maintain q = 30°.

3. 41 58 1950 5 480 Pushover to zero g.

4. 80 80 3900 0 660 Increase a to maintain H dot = 0.

5. 88 80 4500 4 870 Shutdown, maintain H dot = 0.

6. 97 80 4400 4 830 Yaw damper to "Fixed Gain." Increase a to 10°, maintain a = 10° until H dot = +600 fps.

7. 120 86 3800 10 460 H dot = 600 fps - pushover to » 5° a, roll into a 90° left bank, increase a to » 15° and perform several rudder step inputs.

8. 143 94 3400 15 250 Peak altitude - decrease a to » 5°, roll to a 60° right bank, (maintain H dot » -600 fps), increase a to » 15° and perform several rudder step inputs.

9. 178 80 3200 15 450 Vector to High Key. Maintain H dot » -400 fps.

10. 200 65 3000 5 800 Cuddeback, speed brakes as required. Yaw damper "OFF" at pilot's discretion. Perform moderate rudder pulses. Yaw Damper "Adaptive."

11. High Key - check flap and "Squat" circuit breakers in. Engine Master "OFF."

Before APU shutdown, cycle flaps, set stabilizer trim to zero, data "Off."

Notes:

1. q vernier will be set at 30°, a cross-pointer null at 0°.

2. Emergency lake: Cuddeback.

3. Flight duration: Approximately 9 minutes.

4. Flight plan based on 47,000lb thrust at 73%. Engine #109.

Total burn time at 73% = 103 sec.

Launch Wt. = 33,350lb Burnout Wt. = 15,500lb.

Inflight jettison check.

Ground Rules For No Launch:
1. Radio, radar or T.M. malfunction.

2. FCS malfunction as indicated on Analyzer check list.

3. Malfunction of inertial platform.

4. Malfunction of ball nose.

Alternate Situations After Launch:

	Failure	Action

1.	Radio or Radar	Proceed as planned.

2.	Total Yaw Damper	Proceed, pushover to 2° a at 41 sec. Vector to High Key after shutdown, do not perform pullup and roll maneuvers.

3.	Total Pitch/Roll Damper	Same as 2, except turn Yaw Damper "OFF."

4.	Fixed Gain in any axis	Proceed as planned. (Turn Yaw Damper to correspond to Roll Damper).

5.	Attitude Failure	Use 6° a in place of 30° q at 27 sec. Perform roll maneuvers at pilot's discretion.

6.	Ball Nose	Proceed as planned. Rotate at 1.5g instead of 11° a. Heading vernier to "^·Y." Do not perform pullup and roll maneuvers.

7.	Delayed engine light	Pushover to zero g at H = 56,000 ft.

8. Inadvertent engine shutdown:

0 - 58 sec Hidden Hills

58 - 68 sec Cuddeback (2700 fps)

68 - Up sec Edwards (3200 fps)


1.	0	45	790	2	145	Launch, light engine at 75%T. (Chamber pressure = 480 psi). Rotate at 11° a until q = 30°.

2.	27	48	1600	11	500	q = 30°, maintain q = 30°.

3.	41	58	1950	5	480	Pushover to zero g.

4.	80	80	3900	0	660	Increase a to maintain H dot = 0.

5.	88	80	4500	4	870	Shutdown, maintain H dot = 0.

6.	97	80	4400	4	830	Yaw damper to "Fixed Gain." Increase a to 10°, maintain a = 10° until H dot = +600 fps.

7.	120	86	3800	10	460	H dot = 600 fps - pushover to » 5° a, roll into a 90° left bank, increase a to » 15° and perform several rudder step inputs.

8.	143	94	3400	15	250	Peak altitude - decrease a to » 5°, roll to a 60° right bank, (maintain H dot » -600 fps), increase a to » 15° and perform several rudder step inputs.

9.	178	80	3200	15	450	Vector to High Key. Maintain H dot » -400 fps.

10.	200	65	3000	5	800	Cuddeback, speed brakes as required. Yaw damper "OFF" at pilot's discretion. Perform moderate rudder pulses. Yaw Damper "Adaptive."

11.						High Key - check flap and "Squat" circuit breakers in. Engine Master "OFF."

						Before APU shutdown, cycle flaps, set stabilizer trim to zero, data "Off."