ASI f1 f2 ALT RPM: Coolant Temp: CHT Bank: Crew : Safety ... · a) Straight and level trimmed to 1.4Vs (trimmer to remain at this position during testing), reduce speed 1kt/s; record

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


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


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


(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


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


(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


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


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



Sortie

No.

Engine idle

Config LAND

Trim at 1.4Vs

Decel 1kt per sec

Trimmed speed:

Weight:

Stall Warn

Stall

Height Loss

Wing drop:



Recovery control

Comment (stall

symptoms?):

IAS

kg

IAS

IAS

ft………….

° L/R

Yes/No

Sat/Unsat

Page 9 of 30



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:



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:



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


Light Weight/ Aft CG


Sortie

No.

Engine idle

Config CR

Trim at ~1.4Vs

Decel 1kt per sec

Trimmed speed:

Weight:

Stall Warn

Stall

Height Loss

Wing drop:



Recovery control

Comment (stall

symptoms?):

IAS

kg

IAS

IAS

ft………….

° L/R

Yes/No

Sat/Unsat

Page 11 of 30



Sortie

No.

Engine idle

Config LAND

Trim at 1.4Vs

Decel 1kt per sec

Trimmed speed:

Weight:

Stall Warn

Stall

Height Loss

Wing drop:



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:



Recovery control

Comment (stall

symptoms?):

IAS

kg

IAS

IAS

ft………….

° L/R

Yes/No

Sat/Unsat



Page 12 of 30



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:



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


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:



Page 13 of 30



LEFT RIGHT

Config LAND Warning

Stall:

Altitude Loss

Wing drop?:





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?:





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?:





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 14 of 30


Light/Aft CG


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?:





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?:





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?:





IAS

IAS

ft

° L / R

Y/N

Y/N

IAS

IAS

ft

° L / R

Y/N

Y/N



Page 15 of 30



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?:





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


10. Control

(10a) Simulated Sudden Engine Failure


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


(10b) High speed flight


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


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


Must be less than 5 secs

Yes/No

Yes/No

Page 18 of 30



Sortie

No.

Roll control

1.3Vso

Config LAND









Yes/No

Yes/No

Sortie

No.

Roll control

VNE

Config CR

Speed used:






IAS




Yes/No

Yes/No

Sortie

No.

Roll control

VFE

Config LAND





Roll control adequate?:




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


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



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


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:


IAS

Yes/No

Sortie

No.

Config LAND, Throttle

closed

Speed used:


IAS

Yes/No

Sortie

No.


full

Speed used:


IAS

Yes/No

Page 20 of 30


(11b) Light Weight/ Aft CG


Sortie

No.

Config CR, Throttle closed Speed used:


IAS

Yes/No

Sortie

No.

Config CR, Throttle full Speed used:


IAS

Yes/No

Sortie

No.


closed

Speed used:


IAS

Yes/No

Sortie

No.


full

Speed used:


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;


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



Sortie

No.


config LAND,

MTOW/fwd,

evaluate trim speed

band.

Trimmed speed:

RPM:

Altitude:



IAS

IAS

ft

Sortie

No.


config CR,

Lightweight/aft,

evaluate trim speed

band.

Trimmed speed:

RPM:

Altitude:



IAS

IAS

ft

Sortie

No.


config LAND,

Lightweight/aft,

evaluate trim speed

band.

Trimmed speed:

RPM:

Altitude:



IAS

IAS

ft

Page 22 of 30


(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.


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



IAS

Yes/No

Yes/No

Sortie

No.

VREF (approach

speed), IDLE pwr

Config PA (approach

configuration)

RPM:

Speeds used (trim, min, max)



IAS

Yes/No

Yes/No

Sortie

No.

VNE Max speed used:

Force increasing to VNE?

IAS

Yes/No

Page 23 of 30


(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.



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


(12d) Dynamic Stability (S181)



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


time to damp

Sortie

No.

Trim at ~1.1Vs Induce

yaw /roll oscillations

(rudder doublet)

Pedals free.

Pedals fixed


time to damp

Ratio:


time to damp

Ratio:

Sortie

No.

Trim at VH


(pitch doublet)

Speed achieved:

Stick free.

Stick fixed.

IAS


time to damp


time to damp

Sortie

No.

Trim at VH Induce yaw

/roll oscillations (rudder

doublet)

Pedals free.

Pedals fixed


time to damp

Ratio:


time to damp

Ratio:

Sortie

No.

VNE


(pitch doublet)

Speed used:

Stick free (only

required if VNE

trimmable)

Stick fixed.

IAS


time to damp


time to damp

Page 25 of 30



Sortie

No.

VNE Induce yaw /roll

oscillations (rudder

doublet)

Pedals free.

Pedals fixed


time to damp

Ratio:


time to damp

Ratio:

13. Landing

S171 Stability and Control during landing


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


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


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


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


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


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:


Basic aircraft

Pilot


Fuel


Total

Sortie No:


Basic aircraft

Pilot


Fuel


Total

Sortie No:


Basic aircraft

Pilot


Fuel


Total

Sortie No:


Basic aircraft

Pilot


Fuel


Total

Documents

ASI f1 f2 ALT RPM: Coolant Temp: CHT Bank: Crew : Safety ... · a) Straight and level trimmed to 1.4Vs (trimmer to remain at this position during testing), reduce speed 1kt/s; record