by Damien Burke
Ram air temp. reading
RAM T. warning on
Select 2, Record
Main altimeter reading
RAM T. warning out
Return to NORM, check main altimeter returns to zero +- 50 feet.
FIRE TEST switch (Navigator)
For each position, check fire warning, check/cancel attention-getter
1 – No. 1 ENG
2 – No. 1 RHT
3 – No. 1 ENG
4 – No. 2 ENG
5 – No. 2 RHT
6 – No. 2 ENG
Return to OFF
C.W.P.
Check warnings :-
Red :- OIL 1 & 2, CONT 1 & 2, CANPY.
Amber :- GEN 1 & 2, SERV 1 & 2, CAV 1 & 2, PUMP 1, 2, 3, 4, FIN
Remove remaining escape system safety pins (4)
STARTING / FAIL TO START
STARTING
Confirm or set :-
Cockpit checks
Complete
Palouste trolley
Connected and started
Start No. 1 engine first
STARTING DRILL:-
Throttle
(Max permissible temperature at any time 550°C)
‘Start’ mark
Ground running doors open (crew chief)
FLIGHT/MOTOR OVER switch
FLIGHT
Start/relight button
Press firmly for 5 seconds (Check ignition interference on I/C)
Throttle to IDLE as temperature stabilizes, falls slightly. Temperature again rises, then falls as RPM rises.
Call ‘30% RPM’ to ground crew
‘Air valve closed’ from crew chief.
NO HANDLING TILL STEADY AT IDLING
IDLING CHECK :-
RPM
60% approx.
Turbine temperature
400°C maximum
Warnings remaining
Red: OIL 2, CONT 2, CANPY
Amber: GEN.1, SERV. 2, CAV. 2, GEN. 2, PUMP 2, PUMP 4.
Both GEN CONTROL switches
RESET and normal / guarded.
GEN 1 light out
TRU TEST switch
Hold at 1 till amber
DC warning lights; release, check instrumentation master warning light on, reselect tape and trace if necessary
If THROT warnings light, select EMERG throttle for 3 seconds; return to normal and check warnings out.
Starting No. 2 engine :-
Fueldraulic PUMP switch
X-OVER
No. 1 engine
70% RPM
Carry out STARTING DRILL for No. 2 engine.
With both engines at IDLE :-
Air conditioning (Hampson) trolley disconnected.
External electrics
Disconnected
Both RPM
Approx 60%
Both turbine temperature
400°C maximum
Warnings
All out except CANPY
Undercarriage indicator
All reds out
Brake cooling fans on
(crew chief)
Controls hydraulic pressures
(crew chief)
ENGINE DOES NOT ROTATE :-
ENGINE MASTER switch
Make one further attempt.
OFF and ON again
ENGINE ROTATES BUT FAILS TO LIGHT by 12 % RPM
Throttle
COCK OFF
Allow engine to stop completely
ENGINE MASTER switch
OFF and ON again
FLIGHT/MOTOR OVER switch
MOTOR OVER
Start/relight button
Press for 45 seconds
FLIGHT/MOTOR OVER switch
FLIGHT
Throttle
At ‘start’ mark
Carry out STARTING DRILL once more.
AFTER-STARTING / PRE TAKE-OFF
AFTER-STARTING CHECKS :-
Hydraulic pressures :-
Brake accumulators
4,000 +/- 200lb/in2
Systems (navigator)
4,000 +/- 200lb/in2
Air brakes
Check operation, leave fully in
D.C. throttle control
Select EMERG for each engine
(Throttles at red marks)
Check THROT warning and response on d.c. throttle switch
Return to normal
Fueldraulic PUMP switch
NORM
CABIN S/O VALVE
NORM
GEN. CONTROL 1 switch
Select OFF, check GEN 1 warning, select RESET and return to centre, check warning out.
GEN. CONTROL 2 switch
Check GEN 2 warnings as above
W/S DISP switch
½ to disperse accumulated water then as required.
AFCS :-
FIN and TAILN switches on (down), cover closed. All modes disengaged.
AFCS Confidence testing: (all off at even positions)
1) (resetting)
13) TNR.CD, TAILN., FIN
3) TRN.CD, TAILN.
15) TNR.CD, TAILN., FIN
5) TRN.CD, TAILN.
17) TNR.CD, TAILN., FIN
7) TRN.CD, TAILN.
19) TNR.CD, FIN
9) TRN.CD, TAILN.
21) TNR.CD, FIN
11) TRN.CD, TAILN.
23) TNR.CD, FIN
FLAP BLOWING CHECK :-
Set for take-off :-
Flaps 20°
FLAP BLOW ON
NOZZLE OV/RIDE switches
Select MAX DRY at 90% RPM.
Check nozzles close: return to NORMAL
TAKE-OFF CHECKS :-
TRIM
YAW : 0
ROLL : 0
PITCH : 1 divn. nose-up
ROLL/YAW : 0
AIR BRAKES
Fully in
FUEL
CROSSFEED cock SHUT
Manual transfer off
With navigator:
Contents
CG (at G and FL); leave at G.
INSTRUMENTS
Attitude indicator erected
Stand-by horizon erected
Nav. display FG
Check with navigator
OXYGEN
Contents
Pressure
Flow
Check with navigator
HOOD
Closed and locked
Shoot bolts home
Selector OPEN
Check with navigator
HARNESS
Tight and locked
Check with navigator
HYDRAULICS
Flying controls check
Brake accumulator pressures
Systems pressures with navigator
WARNINGS
All out
TAKE-OFF :-
MAX. DRY power, brakes holding on a dry surface
Nozzles at ‘max dry’ marks
Stabilized limits (NORMAL DOUBLE DATUM) :-
No. 1 engine 99.5% / 775°C
No. 2 engine 100% / 774°C
Release brakes and apply MAX. REHT.
Check nozzles open
Temperatures and RPM still within limits
CHECKS AFTER TAKE-OFF :-
Nosewheel steering
Disengage
Undercarriage
Select UP before 240knots
Lights out by 315kt
Flaps
Select 0°
0° by 300kt
DOUBLE DATUM switches
Cancel reheat
INTERMEDIATE
DESCENT AND APPROACH :
DESCENT PROCEDURES (Throttles at IDLE)
Normal descent (airbrakes OUT)
0.9M / 350knots
Slow descent (airbrakes IN)
0.9M / 320knots
Single engine descents identical
CIRCUIT
APPROACH SETTINGS (FLAP BLOW ON)
LANDING AND OVERSHOOTING CHECKS BEFORE LANDING :-
DO
UBLE DATUM switches
NORMAL
FLAP BLOW
ON
Flaps
20° below 250knots
Undercarriage
DOWN below 240knots : 3 greens
Flaps
35° below 225knots
Blowing gauge
In 20° double band (approx.)
Fuel
Contents
Harness
Tight and locked
Check with navigator
Brakes
Accumulator pressure
4000 +/- 200lb/in2
Apply brakes:
4 line pressures 1,750lb/in2 max.
Release brakes, pressures zero
Nosewheel steering
Disengaged
Parachute
MAX.
Trim
ROLL/YAW : 0 (or optimum)
APPROACH AND TOUCHDOWN
Speeds
Approach 180knots
Touchdown 170knots
After touchdown :-
Throttles
IDLE
Aerodynamic braking down to 155knots
Nosewheel
Lower, engage steering
Parachute
PULL ONCE to stream at 150knots
Brakes
As required
CABIN S/O VALVE
SHUT
RAM AIR VALVE
OPEN before unlocking canopy.
TWO-ENGINE OVERSHOOT
MAX DRY power, air brakes IN, maintain configuration, accelerate to 220knots and climb into circuit.
BRITISH AIRCRAFT CORPORATION
(PRESTON DIVISION)
T.S.R. 2
(XR219)
FLIGHT REFERENCE CARDS (2)
NAVIGATOR’S
NORMAL OPERATING DRILLS
ISSUE 1, AUGUST 1964
INCORPORATING AMENDMENT LIST 2, AUGUST 1964
Issued by - Technical Publications Dept.,
WARTON AERODROME, LANCS.
COCKPIT CHECKS
PRELIMINARIES (ground power on and air supplies connected).
BEFORE ENTERING AIRCRAFT
Emergency oxygen pressure
1,800psi min.
Safety pins
Inserted in seat gun, ‘chute withdrawal guillotine, firing handle, canopy jettison handle.
Removed from head restraint guillotine.
AFTER ENTERING AIRCRAFT
Centralized warning panel
OXY, PL OX, ADC, and possibly BAL, warnings on. Check other filaments.
Inertial platform control unit :
LATITUDE control
Local latitude
N LAT-S LAT switch
N LAT
Alignment switch
STANDBY
(Proceed with alignment – separate stages or ALIGN 2 and FLIGHT – at intervals, when ‘stage complete’ lamps light during following checks)
Rapid start panel
All ganged switches ON, ADC warning out
Auto variation control unit:
DEV control
As required
AUTO-MANUAL switch
MANUAL, set variation
N-S switch
N
LAT control
Local latitude, then synchronize compass on MAG.
Safety pins
Check removed from rocket pack sear and both canopy external jettison breeches.
Strap in, connect P.E.C.
OXY warning out (PL OX out when pilot connects)
Services selector switch No. 4
I/C NORM
Instrumentation switch panel
Check time base and ident. readouts zeroed in both compartments
Instrumentation master switch
(Pilot’s compartment)
Check with pilot that switch is on
INTERNAL CHECKS
PORT CONSOLE
FUEL CONTENTS SAMPLING switch
NORMAL
Ess. a.c. busbar frequency meter
398 +/- 8 c.p.s.
Fuel panel :-
Refuel/defuel MASTER switch
OFF
Refuel level switch
FULL
RESET and trim unit
Auto and press. BAL warning out
Tank switches
FLGT
Fuel contents
Check TOTAL and 2 & 4, + O/L and WING (BAL warning at 2 & 4). Compare with pilot’s readings.
Set TOTAL and O/L
Mode selector
PRES RATE
FLIGHT TIME REMAINING
418 minutes
FUEL REMAINING
Equals total of gauges
c.g. meter
Check agreement of G and F positions. Set F then check with pilot’s G position
A.F.C.S. ‘frig’ box
Check INITIATE switch OFF – guarded – and lamp out
Brake pressure gauges
Check parking brake pressure 1 and 2 FWD-1750psi max,
min.
FORWARD PANEL – PORT
Instrumentation switch panel :
ENG and AFCS power lamps
On
Engineering tape recorder
START, recording lamp on
Crash recorder
Check running
Downward sight
ON. Function and set aft view
B.S.E. RECORDER
Check HT neon on. Select according to Flight Test Schedule.
Oxygen contents
Sufficient for flight
Oxygen pressure
70 – 85psi
Oxygen flow indicator
Operating
Intercomm CALL lamp
Press. Pilot confirms function by pressing his CALL lamp
PORT INDICATOR UNIT
V.S.I.
Zero
Altimeter
Monitor during A.D.C. test
Power failure flag clear, set 1013.2 mbs
Combined speed indicator
Monitor during A.D.C. test
All pointers zero
STARBOARD INDICATOR UNIT
Artificial horizon
Power failure flag clear, check erecting then fast erect
Compass and heading indicator
Power failure flag clear. Check DG position with pilot, set MAG.
FORWARD PANEL – STARBOARD
Tacan
Check channel with pilot and compare direct range and bearing. Set offset computer as required by pilot
Engine instrumentation panel :
No. 1 and 2 H.P. turb. air temp.
Warning lamps out. Press to test
No. 1 and 2 Rear bearing temp.
Warning lamps out. Press to test
No. 1 and 2 Oil inlet temp.
-
No. 1 and 2 Rear bearing diff. press.
Zero
No. 1 and 2 Flowmeters
Zero
No. 1 and 2 Nozzle positions
Closed
STARBOARD CONSOLE
U.H.F. - I/C control unit (H.F. not fitted):
Switch No. 1
UHF T/R
Switches No. 2, 3 and 5
Off. Pilots transmit and received heard in headphones