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Page 1 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
BMAA FLIGHT TEST PLAN BMAA/AW/051a issue 1
Reg: Type: TADS or MAAN
applying:
Title:
Expanded series test schedule for 3-axis microlight aeroplanes
Limitations & Units: ASI Units: Vmin: Vmax: Va: Vf1: Vf2:
ALT Units: Min: Max:
RPM: Limit: Coolant Temp: Limit:
CHT Limit: EGT Limit:
Pitch: Limits: Bank: Limits:
Crew : Safety Equipment:
Other limitations:
(Abandonment criteria?)
1. Introduction
First flight of a new aircraft.
The first flight of a prototype or a newly built kit aircraft should normally be flown by the test pilot alone.
This flight should be a “shakedown” flight, ideally flown solo and confined to general handling only to
establish the correct functioning of the engine and systems, and basic FCMC checks. CG should be at mid
position and the take off weight should be less than MAUW. This flight should be followed by a detailed
inspection of the engine and airframe.
Subsequent flights.
The second flight should establish ASI calibration data, if required, and should be flown at similar CG
and weight to the first flight. Basic stability and control should be examined.
When the test pilot is satisfied that the aircraft is ready, he will proceed to the airworthiness test schedule.
The following details what the requirements are, and describes the test conditions required, the test points
and leaves space for the results.
Notes
(a) Issue of this test schedule alone does not give authority to fly. This must be given separately on a form
BMAA/AW/029, a CAA Permit to Fly for Test Purposes, or aircraft manufacturer’s B-conditions certificate of release
for flight.
(b) The order of tests may be re-arranged at the discretion of the project test pilot, whilst maintaining the requirement for
less hazardous tests to be carried out first. Intermediate tests may also be required at the project TP’s discretion.
(c) Please carefully read the authorising document(s) which will show the reasons for issue of this schedule, and which
parts of the schedule are required.
(d) It is anticipated that about 3 sorties will be required, all going well – but recording space is available for tasks which
extend beyond that.
(e) S251 Vibration and Buffeting During all flight testing record any undue vibration, aerodynamic buffet, control cable
instability etc that could potentially cause a problem to safe flight, fatigue life of the structure/ controls etc.
Page 2 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
2. General Please detail conditions for each sortie (If necessary, please attach a continuation sheet):
Sortie No. 1 2 3 4 5 6 7
Date:
Airfield:
Elevation:
Pilot:
FTO:
Start time:
Shutdown time:
Duration:
Wind:
OAT:
QFE:
QNH:
Weather:
Other relevant
conditions (e.g.
ballast, special
equipment,
configuration changes):
Weight:
CG:
3. Authorisation
Confirm all authorising documents checked and current prior to trial:
Please list authorising document references:
Page 3 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
4. Pre-Flight & Ground Test
Authority to proceed/ Permit to Test:
POH (S1581): Present and complete? Y / N
(4a) Controls (S777):
Flying Controls: Engine Controls:
Elevator/Stabilator: SAT/UNSAT
Ailerons: SAT/UNSAT
Rudder: SAT/UNSAT
Flaps: SAT/UNSAT / NP
Pitch Trim: SAT/UNSAT / NP
Throttle: SAT/UNSAT
Mixture/Choke: SAT/UNSAT
Fuel Cock: SAT/UNSAT
Fuel Booster Pump: SAT/UNSAT / NP
(NP = Not Present)
(4b) Cockpit View (S773): Comment upon field of View:
(4c) Equipment:
Safety Harness/Straps (S785): SAT/UNSAT
Canopy/Door Fastening/Locking (S807): SAT/UNSAT (if applicable)
Seat/ Rudder Pedal Adjustment: (S777): SAT/UNSAT (if applicable)
Note any changes from standard cockpit arrangement:
Comment upon acceptability of changes:
(4d) Instruments (S1321):
List Instruments fitted with comment upon range of operation (if different from MAAN)
Comment upon usability and visibility of each instrument
Start date:
Expiry date:
Page 4 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
(4e) Switches (S777; S1541):
Correctly Placarded: SAT/UNSAT (list unsat placards in defect log)
Correct and appropriate functioning: SAT/UNSAT
(4f) Start and Static Engine Run:
Idle RPM:
Record max static engine parameters:
RPM………….. CHT……………
EGT…………… Fuel Press………
Magneto/CDI check RPM……….. Mag drop L…………..R…………..
5. Taxying S233 General
Adequate control whilst taxying SAT/UNSAT
Tendency to ground loop? Yes/No
Braking normal and satisfactory? Yes / No
6. Take-off S51/143
Flap Setting: (if applicable)
Trim Position:
Handling technique:
Rotate speed:
Speed at 50’:
Comment on Behaviour:
Assessed during
sortie No.s:
Assessed during
sortie No.s:
Page 5 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
7. Upper Air
(7a) Climb
S65/143
Timed Climb through minimum 2,000 ft at POH best climb speed,
Altimeter set to 1013hPa, recording time and height at intervals of no
greater than 500ft, test to be carried out in still air at weights not less
than 95% MTOW.
Where best climb speed is not known or in question, sawtooth climbs
should be carried out to identify this speed, which should be reported
separately using appendix B.
Climb speed used:
Aircraft mean weight through test:
kgf.
Height Time VSI Height Time VSI
Maximum engine temperatures and pressures during climb
Unit Maximum value Unit Maximum value
Assessed during
sortie No.s:
Page 6 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
(7b) Handling
a) Check ability to make smooth transitions to turns, level, pitch up and down at all powers and engine idle/off. Assess pilot
input forces required, skill levels and comment on safety when using non standard control combinations.
b) Fly in the rain, test all engine powers and engine at idle.
c) If control forces are high, measure loads to check compliance with temporary and prolonged load applications. (i.e. 20
daN temporary and 2daN prolonged for pitch etc)
Test Condition Required Test Points Results
Demonstrate safe control
Manoeuvrability
Climb Yes/No
Ability to make smooth
transitions.
Turns
Level
Pitch up and down
All powers inc idle.
Yes/No
Yes/No
Yes/No
Yes/No
Control forces Typical of type? Pitch?
Roll?
Yaw?
Wing flaps?
8. Glide performance
S 71 Descent rate power off in en-route trim condition at maximum weight. VSI indication is not an
accurate method for determination of descent rate – but should be recorded if one is fitted to check the
instrument. Difference between test heights should be at-least 500ft, test to be carried out in still air,
using POH best glide speed unless found unsatisfactory (see note below).
First height:
ft
Glide speed used:
IAS
Second height:
ft
Time between:
seconds
Average VSI reading (if fitted):
fpm
Where best glide speed is not known or in question, sawtooth glides should be carried out to identify this
speed, which should be reported separately using appendix B.
Assessed during
sortie No.s:
Assessed during
sortie No.s:
Page 7 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
9. Stalls
S201 Wings level stall Stalling will be investigated at minimum and maximum AUW over the declared CG range for the weight
conditions. Maximum weight FWD Cg and light weight AFT should suffice.
a) Straight and level trimmed to 1.4Vs (trimmer to remain at this position during testing), reduce speed
1kt/s; record speed when a/c pitches down (or pitches and rolls). If no pitch break occurs pull to
control stops, hold for 2 seconds then record speed. Check roll and yaw correct sense up to the point
of stall. Repeat this test for engine idle and maximum continuous power and at all mass & CG
combinations.
b) Record any tendency to roll during the stall; must be possible to limit roll to 20 degrees using
controls.
c) Record altitude loss for stall recovery
And for Recovery
S207 Recovery from the stall
a) Record the nature of the stall warning; if no perceivable warning (i.e. buffet, exceptionally high nose
attitude etc) then: 1) Check roll can be corrected at stall speed with yaw control neutral; 2) Check no
appreciable (<20 degrees) of wing drop occurs with roll and yaw controls neutral.
b) If the wing drop criteria of (a) above was not met then test for: 1) Distinctive stall warning in level
and turning flight; 2) Onset speed of warning; must be high enough to maintain control prior to stall.
3) Report the nature of the warning.
c) N/A ; 3 Axis a/c
Max Weight/ Forward CG
Test Condition Required Test Points Results
Sortie
No.
Engine idle
Config CR
Trim at ~1.4Vs
Decel 1kt per sec
Trimmed speed:
Weight:
Stall Warn
Stall
Height Loss
Wing drop:
Severity of pitch break:
Roll greater than 20°?
Recovery control
Comment (stall
symptoms?):
IAS
kg
IAS
IAS
ft………….
° L/R
Yes/No
Sat/Unsat
Page 8 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
Test Condition Required Test Points Results
Sortie
No.
Engine idle
Config LAND
Trim at 1.4Vs
Decel 1kt per sec
Trimmed speed:
Weight:
Stall Warn
Stall
Height Loss
Wing drop:
Severity of pitch break:
Roll greater than 20°?
Recovery control
Comment (stall
symptoms?):
IAS
kg
IAS
IAS
ft………….
° L/R
Yes/No
Sat/Unsat
Page 9 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
Test Condition Required Test Points Results
Sortie
No.
Max continuous
power
Config CR
Trim at 1.4Vs
Decel 1kt per sec
Trimmed speed:
Weight:
RPM used:
Stall Warn
Stall
Height Loss
Wing drop:
Severity of pitch break:
Roll greater than 20°?
Recovery control
Comment (stall
symptoms?):
IAS
kg
IAS
IAS
ft………….
° L/R
Yes/No
Sat/Unsat
Sortie
No.
Max continuous
power1
Config LAND
Trim at 1.4Vs
Decel 1kt per sec
Trimmed speed:
Weight:
Stall Warn
Stall
Height Loss
Wing drop:
Severity of pitch break:
Roll greater than 20°?
Recovery control
Comment (stall
symptoms?):
IAS
kg
IAS
IAS
ft………….
° L/R
Yes/No
Sat/Unsat
1 Note: If the use of maximum continuous power results in extreme pitch attitudes, consult the technical
office who will advise what power settings should be used.
Page 10 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
Light Weight/ Aft CG
Test Condition Required Test Points Results
Sortie
No.
Engine idle
Config CR
Trim at ~1.4Vs
Decel 1kt per sec
Trimmed speed:
Weight:
Stall Warn
Stall
Height Loss
Wing drop:
Severity of pitch break:
Roll greater than 20°?
Recovery control
Comment (stall
symptoms?):
IAS
kg
IAS
IAS
ft………….
° L/R
Yes/No
Sat/Unsat
Page 11 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
Test Condition Required Test Points Results
Sortie
No.
Engine idle
Config LAND
Trim at 1.4Vs
Decel 1kt per sec
Trimmed speed:
Weight:
Stall Warn
Stall
Height Loss
Wing drop:
Severity of pitch break:
Roll greater than 20°?
Recovery control
Comment (stall
symptoms?):
IAS
kg
IAS
IAS
ft………….
° L/R
Yes/No
Sat/Unsat
Sortie
No.
Max continuous
power2
Config CR
Trim at 1.4Vs
Decel 1kt per sec
Trimmed speed:
Weight:
RPM used:
Stall Warn
Stall
Height Loss
Wing drop:
Severity of pitch break:
Roll greater than 20°?
Recovery control
Comment (stall
symptoms?):
IAS
kg
IAS
IAS
ft………….
° L/R
Yes/No
Sat/Unsat
2 Note: If the use of maximum continuous power results in extreme pitch attitudes, consult the technical
office who will advise what power settings should be used.
Page 12 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
Test Condition Required Test Points Results
Sortie
No.
Max continuous
power3
Config LAND
Trim at 1.4Vs
Decel 1kt per sec
Trimmed speed:
Weight:
Stall Warn
Stall
Height Loss
Wing drop:
Severity of pitch break:
Roll greater than 20°?
Recovery control
Comment (stall
symptoms?):
IAS
kg
IAS
IAS
ft………….
° L/R
Yes/No
Sat/Unsat
S203 Turning Flight Stalls a) Stall in 30 degree bank turn, record nature of recovery; must not roll more than 30 degrees into turn,
60 degrees out, check for spinning tendencies. Test full power and engine idle across mass/CG range
b) Record the altitude loss for turning stall recovery
Heavy/Fwd CG
Test Condition Required Test Points Results
LEFT RIGHT
Trimmed speed:
Weight:
Sortie
No.
Stall in 30°
banked turn,
left and right.
Engine at idle.
Config CR Warning
Stall:
Altitude Loss
Wing drop?:
Not more that 30° into
Or 60° out of turn?:
Uncontrollable roll or
spinning tendencies?
IAS
IAS
ft
° L / R
Y/N
Y/N
IAS
IAS
ft
° L / R
Y/N
Y/N
Sortie
No.
Stall in 30°
banked turn,
left and right.
Engine at idle.
Trimmed speed:
Weight:
3 Note: If the use of maximum continuous power results in extreme pitch attitudes, consult the technical
office who will advise what power settings should be used.
Page 13 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
Test Condition Required Test Points Results
LEFT RIGHT
Config LAND Warning
Stall:
Altitude Loss
Wing drop?:
Not more that 30° into
Or 60° out of turn?:
Uncontrollable roll or
spinning tendencies?
IAS
IAS
ft
° L / R
Y/N
Y/N
IAS
IAS
ft
° L / R
Y/N
Y/N
Trimmed speed:
Weight:
RPM:
Sortie
No.
Stall in 30°
banked turn,
left and right.
Max
continuous
power4
Config CR Warning
Stall:
Altitude Loss
Wing drop?:
Not more that 30° into
Or 60° out of turn?:
Uncontrollable roll or
spinning tendencies?
IAS
IAS
ft
° L / R
Y/N
Y/N
IAS
IAS
ft
° L / R
Y/N
Y/N
Trimmed speed:
Weight:
RPM:
Sortie
No.
Stall in 30°
banked turn,
left and right.
Max
continuous
power
Config LAND Warning
Stall:
Altitude Loss
Wing drop?:
Not more that 30° into
Or 60° out of turn?:
Uncontrollable roll or
spinning tendencies?
IAS
IAS
ft
° L / R
Y/N
Y/N
IAS
IAS
ft
° L / R
Y/N
Y/N
Ensure recovery satisfactory and typical of type- comment separately on any unsatisfactory or
atypical tendencies.
4 Note: If the use of maximum continuous power results in extreme pitch attitudes, consult the technical
office who will advise what power settings should be used.
Page 14 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
Light/Aft CG
Test Condition Required Test Points Results
LEFT RIGHT
Trimmed speed:
Weight:
Sortie
No.
Stall in 30°
banked turn,
left and right.
Engine at idle.
Config CR Warning
Stall:
Altitude Loss
Wing drop?:
Not more that 30° into
Or 60° out of turn?:
Uncontrollable roll or
spinning tendencies?
IAS
IAS
ft
° L / R
Y/N
Y/N
IAS
IAS
ft
° L / R
Y/N
Y/N
Trimmed speed:
Weight:
Sortie
No.
Stall in 30°
banked turn,
left and right.
Engine at idle.
Config LAND Warning
Stall:
Altitude Loss
Wing drop?:
Not more that 30° into
Or 60° out of turn?:
Uncontrollable roll or
spinning tendencies?
IAS
IAS
ft
° L / R
Y/N
Y/N
IAS
IAS
ft
° L / R
Y/N
Y/N
Trimmed speed:
Weight:
RPM:
Sortie
No.
Stall in 30°
banked turn,
left and right.
Max
continuous
power5
Config CR Warning
Stall:
Altitude Loss
Wing drop?:
Not more that 30° into
Or 60° out of turn?:
Uncontrollable roll or
spinning tendencies?
IAS
IAS
ft
° L / R
Y/N
Y/N
IAS
IAS
ft
° L / R
Y/N
Y/N
5 Note: If the use of maximum continuous power results in extreme pitch attitudes, consult the technical
office who will advise what power settings should be used.
Page 15 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
Test Condition Required Test Points Results
LEFT RIGHT
Trimmed speed:
Weight:
RPM:
Sortie
No.
Stall in 30°
banked turn,
left and right.
Max
continuous
power
Config LAND Warning
Stall:
Altitude Loss
Wing drop?:
Not more that 30° into
Or 60° out of turn?:
Uncontrollable roll or
spinning tendencies?
IAS
IAS
ft
° L / R
Y/N
Y/N
IAS
IAS
ft
° L / R
Y/N
Y/N
Ensure recovery satisfactory and typical of type- comment separately on any unsatisfactory or
atypical tendencies.
Page 16 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
10. Control
(10a) Simulated Sudden Engine Failure
Test Condition Required Test Points Results
Sortie
No.
Height sufficient for
safe recovery, take-
off configuration,
lightweight/aft,
trimmed at ~1.3Vs,
initially full throttle..
Simulated sudden engine
failure (close throttle),
pause 2 seconds with stick
held still, attempt to
recover to approach speed.
Trim speed used:
IAS
Lowest speed seen:
IAS
Flap setting:
Did aircraft stall? Yes / No
(If yes) what were stall
characteristics?
Any tendency to spin? Yes / No
Height lost in recovering to
approach speed:
ft
Any concerns over handling or
attitude changes?
Sortie
No.
Height sufficient for
safe recovery, take-
off configuration,
MTOW/fwd,
trimmed at ~1.3Vs,
initially full throttle,
POH recommended
initial (after take-off)
climb speed.
Simulated sudden engine
failure (close throttle),
pause 2 seconds with stick
held still, attempt to
recover to best glide
speed.
Trim speed used:
IAS
Lowest speed seen:
IAS
Did aircraft stall? Yes / No
(If yes) what were stall
characteristics?
Any tendency to spin? Yes / No
Height lost in recovering to best
glide speed:
ft
Any concerns over handling or
attitude changes?
Page 17 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
(10b) High speed flight
Test Condition Required Test Points Results
Sortie
No. Nil turbulence, power as required, to recover above 1500ft agl,
lightweight/aft,
CR
Dive to speed exceeding VNE but not beyond VDF, increasing speed slowly, small stick and rudder “raps” at each speed increase. If VNE cannot reasonably be achieved, note maximum speed achievable and reasons for limitation.
Stick force always increasing
adequately?:
Response to small control inputs?:
Any tendency to flutter?:
Any DR or SPO excited?:
Max. speed seen?:
IAS
Handling OK on recovery?:
Sortie
No. Nil turbulence, power as required, to recover above 1500ft agl,
MTOW/fwd,
CR
Dive to speed exceeding VNE but not beyond VDF, increasing speed slowly, small stick and rudder “raps” at each speed increase If VNE cannot reasonably be achieved, note maximum speed achievable and reasons for limitation.
Stick force always increasing
adequately?:
Response to small control inputs?:
Any tendency to flutter?:
Any DR or SPO excited?:
Max. speed seen?:
IAS
Handling OK on recovery?:
(10c) Lateral and Directional Control (S147)
All tests in this section at MTOW/Fwd
Test Condition Required Test Points Results
Sortie
No.
Roll control
1.3Vs
Config CR
Speed used:
Roll from 30° to 30° Right
Roll from 30° to 30° Left
Amount of roll control used:
Any undemanded motion?
Roll control adequate?
IAS
Time: ………………secs
Time: ………………secs
Must be less than 5 secs
Yes/No
Yes/No
Page 18 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
Test Condition Required Test Points Results
Sortie
No.
Roll control
1.3Vso
Config LAND
Roll from 30° to 30° Right
Roll from 30° to 30° Left
Amount of roll control used:
Any undemanded motion?
Roll control adequate?
Time: ………………secs
Time: ………………secs
Must be less than 5 secs
Yes/No
Yes/No
Sortie
No.
Roll control
VNE
Config CR
Speed used:
Roll from 30° to 30° Right
Roll from 30° to 30° Left
Amount of roll control used:
Any undemanded motion?
Roll control adequate?
IAS
Time: ………………secs
Time: ………………secs
Must be less than 5 secs
Yes/No
Yes/No
Sortie
No.
Roll control
VFE
Config LAND
Roll from 30° to 30° Right
Roll from 30° to 30° Left
Amount of roll control used:
Any undemanded motion?
Roll control adequate?:
Time: ………………secs
Time: ………………secs
Must be less than 5 secs
Yes/No
Yes/No
(10d) Pitch Control Force in Manoeuvres (S155) Check control forces increase with a/c acceleration (g) whilst recovering from manoeuvres.
a) Accelerate to VH, descend in wind up turn, increase pitch force whilst increasing bank angle; maintain
speed. (USE INCREMENTAL BUILD-UP TECHNIQUE!)
b) N/A; 3-axis control
Test Condition Required Test Points Results
Sortie
No.
Config CR. Descend in
wind up turn, VH (trimmed
to VH6 or fastest trimmable
speed below that)
Trim speed:
Test Airspeed used:
Pitch force continuously
increasing
Maximum g achieved:
Back-stick force at max g
achieved
IAS
IAS
YES/NO
Pitch force:
daN
6 VH is maximum achievable speed in level flight
Page 19 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
Test Condition Required Test Points Results
Sortie
No.
As above, with Config
LAND, trimmed to VFE–5
kn (or nearest achievable)
CAUTION: check g-limits
with flaps, may be
reduced.
Trim speed:
Test Airspeed used:
Pitch force continuously
increasing
Maximum g achieved:
Back-stick force at max g
achieved
IAS
IAS
YES/NO
Pitch force:
daN
11. Trim S161. Demonstrate ability to trim a/c in pitch, roll and yaw at a speed between 1.3Vs to 2Vs in each
configuration.
(11a) Max Weight/Fwd CG
Test Condition Required Test Points Results
Sortie
No.
Config CR, Throttle closed Speed used:
Will a/c trim hands off ?
IAS
Yes/No
Sortie
No.
Config CR, Throttle full Speed used:
Will a/c trim hands off ?
IAS
Yes/No
Sortie
No.
Config LAND, Throttle
closed
Speed used:
Will a/c trim hands off ?
IAS
Yes/No
Sortie
No.
Config LAND, Throttle
full
Speed used:
Will a/c trim hands off ?
IAS
Yes/No
Page 20 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
(11b) Light Weight/ Aft CG
Test Condition Required Test Points Results
Sortie
No.
Config CR, Throttle closed Speed used:
Will a/c trim hands off ?
IAS
Yes/No
Sortie
No.
Config CR, Throttle full Speed used:
Will a/c trim hands off ?
IAS
Yes/No
Sortie
No.
Config LAND, Throttle
closed
Speed used:
Will a/c trim hands off ?
IAS
Yes/No
Sortie
No.
Config LAND, Throttle
full
Speed used:
Will a/c trim hands off ?
IAS
Yes/No
12. Stability
S171 General The aircraft must demonstrate suitable control feel and stability during manoeuvre; this test may be co-
ordinated with S143 above. Any adverse feel or stability must be commented upon separately.
(12a) Trim Speed Band (S173) Test trim speed band to ensure a/c returns to within 10% of trim speed when disturbed;
Test Condition Required Test Points Results
Sortie
No.
Trim for level flight,
config CR,
MTOW/fwd,
evaluate trim speed
band.
Trimmed speed:
RPM:
Altitude:
Minimum of speed band:
Maximum of speed band:
IAS
IAS
ft
Page 21 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
Test Condition Required Test Points Results
Sortie
No.
Trim for level flight,
config LAND,
MTOW/fwd,
evaluate trim speed
band.
Trimmed speed:
RPM:
Altitude:
Minimum of speed band:
Maximum of speed band:
IAS
IAS
ft
Sortie
No.
Trim for level flight,
config CR,
Lightweight/aft,
evaluate trim speed
band.
Trimmed speed:
RPM:
Altitude:
Minimum of speed band:
Maximum of speed band:
IAS
IAS
ft
Sortie
No.
Trim for level flight,
config LAND,
Lightweight/aft,
evaluate trim speed
band.
Trimmed speed:
RPM:
Altitude:
Minimum of speed band:
Maximum of speed band:
IAS
IAS
ft
Page 22 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
(12b) Demonstration of static longitudinal Stability (S175 )
a) Record the force vs speed curve for the following flight conditions: For first example of type (or if
requested), attach graphs of apparent LSS at Fwd and Aft CG conditions, otherwise test at furthest aft
readily attainable CG. Otherwise, the table below is sufficient information.
1) Climb at 1.4Vs at maximum power
2) Cruise at maximum level flight
3) Cruise at Vne
4) Approach at 1.3Vs (or established approach speed), engine running
5) Approach at 1.3Vs engine off
All tests at lightweight-aft in this section.
Test Condition Required Test Points Results
Sortie
No.
General data Weight:
CG:
Altitude:
Sortie
No.
Climb at 1.4Vs1, max
power.
Speed used
+15%, Perceptible Push Force?
-15%, Perceptible Pull Force?
IAS
Yes/No
Yes/No
Sortie
No.
VH (or maximum
trimmable speed
below this)
Speed achieved
+15%, Perceptible Push Force?
-15%, Perceptible Pull Force?
IAS
Yes/No
Yes/No
Sortie
No.
VREF (approach
speed), IDLE pwr
Config PA (approach
configuration)
RPM:
Speeds used (trim, min, max)
+15%, Perceptible Push Force?
-15%, Perceptible Pull Force?
IAS
Yes/No
Yes/No
Sortie
No.
VNE Max speed used:
Force increasing to VNE?
IAS
Yes/No
Page 23 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
(12c) Lateral and Directional Stability (S177)
a) A/C Straight and level apply opposite roll yaw and check side slip angle proportional to control
forces. (this does not have to be linear)
b) Fly a/c in side slip and check any further changes to a/c orientation is progressive (i.e. higher forces
to increase; reduce force to recover to straight and level); it need not be linear but must not reverse.
All tests at lightweight-aft in this section.
Test Condition Required Test Points Results
Sortie
No.
General data Weight:
CG:
Altitude:
Sortie
No.
Cruise configuration,
PLF
apply roll
oppose with yaw.
(Steady heading
sideslip)
Maximum speed VA
Airspeed:
RPM:
Sideslip angle proportional to
control forces?
Control force increases
progressively with sideslip?
Tendency to reverse /
overbalance?
IAS
Left: Yes/No
Right Yes/No
Yes/No
Yes/No
Sortie
No.
Configuration
LAND, PLF
apply roll
oppose with yaw.
(Steady heading
sideslip)
Maximum speed,
lower of VA and
VFE.
Airspeed:
RPM:
Sideslip angle proportional to
control forces?
Control force increases
progressively with sideslip?
Tendency to reverse /
overbalance?
IAS
Left: Yes/No
Right Yes/No
Yes/No
Yes/No
Additional checks during Steady heading sideslips:
Sortie
No.
Any significant pitch motion?
Any significant ASI, VSI or
altimeter errors appearing?
Yes / No
Yes / No
Page 24 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
(12d) Dynamic Stability (S181)
All tests at lightweight-aft in this section.
Test Condition Required Test Points Results
Sortie
No.
Trim at ~1.1Vs
Induce pitch oscillation
(pitch doublet)
Speed used:
Stick free.
Stick fixed.
IAS
Undamped / ___ cycles to damp / ____
time to damp
Undamped / ___ cycles to damp / ____
time to damp
Sortie
No.
Trim at ~1.1Vs Induce
yaw /roll oscillations
(rudder doublet)
Pedals free.
Pedals fixed
Undamped / ___ cycles to damp / ____
time to damp
Ratio:
Undamped / ___ cycles to damp / ____
time to damp
Ratio:
Sortie
No.
Trim at VH
Induce pitch oscillation
(pitch doublet)
Speed achieved:
Stick free.
Stick fixed.
IAS
Undamped / ___ cycles to damp / ____
time to damp
Undamped / ___ cycles to damp / ____
time to damp
Sortie
No.
Trim at VH Induce yaw
/roll oscillations (rudder
doublet)
Pedals free.
Pedals fixed
Undamped / ___ cycles to damp / ____
time to damp
Ratio:
Undamped / ___ cycles to damp / ____
time to damp
Ratio:
Sortie
No.
VNE
Induce pitch oscillation
(pitch doublet)
Speed used:
Stick free (only
required if VNE
trimmable)
Stick fixed.
IAS
Undamped / ___ cycles to damp / ____
time to damp
Undamped / ___ cycles to damp / ____
time to damp
Page 25 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
Test Condition Required Test Points Results
Sortie
No.
VNE Induce yaw /roll
oscillations (rudder
doublet)
Pedals free.
Pedals fixed
Undamped / ___ cycles to damp / ____
time to damp
Ratio:
Undamped / ___ cycles to damp / ____
time to damp
Ratio:
13. Landing
S171 Stability and Control during landing
Test Condition Required Test Points Results
Sortie
No.
Demonstrate safe stability
and control during
landing using techniques
and speeds recommended
by POH.
Descent
Landing power on
Landing power off
Yes/No
Yes/No
Yes/No
14. Take-off and landing in crosswind (Should opportunity arise, S235)
Investigate ability to control cross-wind landings.
Flap Setting: (if applicable)
Trim Position:
Runway Alignment: ………………
Wind:………./…………kn
Comment on Behaviour:
Assessed during
sortie No.s:
Page 26 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
FLIGHT TEST COMPLETION CERTIFICATE
I have carried out the flight testing required by the attached schedule and also carried out an in-flight ASI
calibration in smooth air which is attached on a form BMAA/AW/043 (note: AW/043a is also available
for convenience when calibrating aircraft with a wider speed range).
Copies of my test cards are / are-not attached. (Copies are to be retained by the pilot if they were not
submitted to the BMAA).
Provisional operating limitations have been entered in the aircraft logbook and placarded. Record of all
test flying has been made in the aircraft logbook(s).
For initial certification a comprehensive Post Flight Report (PFR)will be required.
For routine testing this may not be necessary
Additional PFR Attached YES/NO (_____ pages)
Additionally, a report will be required documenting any of the following:
- Failures to comply
- Changes to design
- Classified**
recommendations for improvement
- Other design comment
- Recommendations/advice for inclusion in POH/AFM
Additional report attached YES/NO (_______ pages)
I certify that the Schedule has been completed and that the aircraft complies with the approval basis and,
subject to completion of any endurance and noise testing requirements, is fit for the award of a Permit to
Fly.
Name:………………………… Signature:………………………………..
BMAA No: ……………….. Date: …………………………
**
Classify deficiencies Unsatisfactory or Unacceptable, and recommendations as desirable, highly
desirable or essential.
Page 27 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
Appendix A to form BMAA/AW/051 Takeoff & Landing Performance
S 51; The takeoff distance at 95% MTOW or above from rest to attaining 15m (50ft) at a speed of not
less than1.3Vs or Vs1+10 kn must be determined when taking off from dry, level, short grass. The
speeds given in the POH should be used, or if they are found incorrect, a report attached recommending
alterations.
Take Off
1 2 3 4 5 6 (Spare1) (Spare2)
W/V
Time to
unstick IAS at
unstick
Time to 15m
IAS at 15m
S 75; The landing on a dry, level, short grass surface at maximum weight in zero wind from a height of
15m (50ft) must be determined for the recommended approach speed. The data used below is based upon
the “timed segment” method, other methods may be used by prior agreement with the technical office.
Landing
1 2 3 4 5 6 (Spare1) (Spare2)
W/V
Approach
IAS Time 15m
to T/D
IAS at T/D Time T/D
to stop
Common data
(Runway) Surface
conditions:
Aircraft Weight:
Runway in use: QFE:
Slope:
OAT:
Page 28 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
Appendix B to form BMAA/AW/051
B1 Sawtooth climbs – this appendix need only be used if best climb speed is in question.
Sortie No. Mean test
weight:
Lower test
height:
Upper test
height:
Height
difference:
ISA ± Mean
σ7
kgf
ft
ft
ft
°C
Test No → 1 2 3 4 5 6 7 8 9 10
Time, s →
IAS →
CAS(kn)→
TAS(kn)→
=CAS * σ
Climb rate, fpm8 →
= 60 * height difference / time
Climb angle →
=
°
−
686.1*sin 1
TAS
RoC
0
200
400
600
800
1000
1200
1400
1600
1800
2000
0 10 20 30 40 50 60 70 80 90knots CAS
Ra
te o
f clim
b,
fpm
0
5
10
15
20
25
Clim
b a
ng
le,
de
gre
es
Best rate climb speed = _____ kn CAS = _____IAS Best angle climb speed = ____ kn CAS = ____ IAS
7 Calculate from form AW/043
8 DO NOT use VSI reading.
Page 29 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
B2 Sawtooth glides - this appendix need only be used if best glide speed is in question.
Sortie No. Mean test
weight:
Upper test
height:
Lower test
height:
Height
difference:
ISA ± Mean
σ9
kgf
ft
ft
ft
°C
Test No → 1 2 3 4 5 6 7 8 9 10
Time, s →
IAS →
CAS(kn)→
TAS(kn)→
=CAS * σ
Sink rate, fpm10
→ = 60 * height difference / time
glide angle →
=
°
−
686.1*sin 1
TAS
RoD
0
100
200
300
400
500
600
700
800
900
1000
0 10 20 30 40 50 60 70 80 90knots CAS
Rate
of
descent,
fpm
0
2
4
6
8
10
12
14
16
18
20
Glid
e a
ngle
, degre
es
Minimum sink speed = _____ kn CAS = _____IAS Best glide angle speed = ____ kn CAS = ____ IAS
9 Calculate from form AW/043
10 DO NOT use VSI reading.
Page 30 of 30
Form BMAA/AW/051a issue 1(Nov 2005)
B3 Pro-forma for calculating weight and balance, to be used at Test Pilot’s discretion
Sortie No:
Mass Moment Arm Moment
Basic aircraft
Pilot
Observer (if carried)
Fuel
Ballast (if carried)
Total
Sortie No:
Mass Moment Arm Moment
Basic aircraft
Pilot
Observer (if carried)
Fuel
Ballast (if carried)
Total
Sortie No:
Mass Moment Arm Moment
Basic aircraft
Pilot
Observer (if carried)
Fuel
Ballast (if carried)
Total
Sortie No:
Mass Moment Arm Moment
Basic aircraft
Pilot
Observer (if carried)
Fuel
Ballast (if carried)
Total
Sortie No:
Mass Moment Arm Moment
Basic aircraft
Pilot
Observer (if carried)
Fuel
Ballast (if carried)
Total