# Aircraft Acceptance Test Procedure Folder

# Aircraft Acceptance Test ProcedureTest Objective

The successful completion of this test in its entirety; establishes that the aircraft applicable to this test

be dee med airworthy and ready for flight. If there are any portions of this test that cannot be completed

due to design constraints, applicability or any other reason; the notes section must be updated with the

associated section, step and what is done to mitiga te any potential risk. Consult management/

engineering as required.

Aircraft

Model: Serial

Number: Date:

Section Documentation Acquisition Tech

Initials

1 Acquire most recent Surface Calibration Procedure Documentation (DCN: BT_300_66)

2 Acquire most recent Range Check Procedure Documentation (DCN: BT_300_110)

3 Acquire most recent Supplemental ATP Procedures Documentation (as required)

Section Airframe Checks Tech

Initials

1 Review Production plan accompanying aircraft and verifying all prod uction steps and QA checks have

been completed.

If checks or signatures are missing do not continue.

2 Check aircraft ICD for proper antenna length.

3 Inspect all aircraft avionics, payload, power sources and any other internal component for secure,

proper mounting. Ensure that the autopilot is mounted appropriately to be isolated from power plant

vibrations.

4 Ensure that all wiring harnesses are connected and strain

- relieved properly.

5 Connect power to avionics/ payload/ engine as necessary if access is not granted after aircraft

assembly.

6 Assemble aircraft completely. Ensure that the proper hardware is utilized and the entire airframe is

structurally sound.

7 Connect servos as necessary. Ensure that all extensions are secured properly.

8 Ensure deployable surfaces are of the correct length (wings and tail surfaces)

9 Check control surfaces are 90 degrees from fuselage

10 Check the control surfaces for smooth transition to extremities without binding.

11 Check that the control sur faces do not have excessive play due to poor linkage connections.

12 Ensure that all servo arms and control linkages are secured with proper screws, securing compound

and restraints.

13 Check landing gear/ wheels for wear and mounting integrity.

14 I nstall and secure the correct propeller for the power plant/ application. Clock appropriately for a level

with the horizon stopping point on compression stroke (where applicable). Inspect propeller for nick

and cracks. DO NOT USE A COMPROMISED PROPELLER.

15 Record propeller type and size and engine type in Aircraft Configuration Worksheet.

16 Inspect pitot and static tubes for FOD and trueness. DO NOT USE air data tubes that are compromised.

Install pitot and static tubes if applicable.

17 Ensure p roper routing of pitot and static lines. Be careful to not have pinched air data tubes when

assembling aircraft.Aircraft

Model: Serial

Number: Date:

Section Weight and Balance Checks Tech

Initials

1 Conduct center of gravity checks appropriately for the aircraft. Seek assistance from management for

proper CG procedures. Verify proper center of gravity for all intended flight configurations. (e.g. with

and without captive carry aircraft)

2 Record CG locations in Aircraft Configuration Worksheet.

3 Record empty mass (less fuel) for all intended flight configurations in the Aircraft Configuration

Worksheet.

4 Fuel aircraft completely and verify that there are no leaks present during fueling procedure.

5 Weigh aircraft and record Gross Mass pr operties in the Aircraft Configuration Worksheet.

6 Verify proper CG with full fuel for all intended flight configurations. Record CG in Aircraft Configuration

Worksheet.

QA Quickly look over aircraft for any issue

QA Ensure servo linkages have no e xcess play

QA Verify appropriate weight and CG are applicable for asset

QA Ensure weight, CG, propeller size and engine type are recorded in configuration sheet

QA Verify there are no open discrepancies in the discrepancy log

WARNING:

The follow ing steps require a Ground Control Station (GCS) to communicate with the aircraft through a RF link. RF

antennas emit radio frequencies that can cause acute and chronic health problems. Seek the advice of the management

team for procedures on how to operat e the GCS safely. Improper set

- up of the GCS and aircraft antennas can cause

damage to GCS and aircraft components.

Section Autopilot Systems Checks Tech

Initials

1 Set up the aircraft and GCS outside ensuring that electronic line of sight (ELOS) is not blocked for

command and control (C2) and GPS reception.

2 Verify that the C2 antenna is connected properly to autopilot and airframe.

3 Establish communications between the aircraft and GCS. Verify that the proper power settings are

used for the radio s. 1.0 watt settings will be used initially.

4 Check for software and firmware compatibility between PCC and GCS.

Section Piccolo Command Center> Window Menu> Preflight Windows> Preflight Tech

Initials

5 Upload the correct/last known good .xml confi guration for the aircraft. DO NOT CONTINUE if the

proper configuration file cannot be uploaded!!!!

6 Record configuration file uploaded:Aircraft

Model: Serial

Number: Date:

Section Piccolo Command Center> Window Menu> Status Windows> System T ech

Initials

9 Temp (C ° )

- 40 to 80

10 Uplink & Downlink = 100 if using Piccolo 2.2.1B or newer ( If using 2.1.4G or older, link = 100 )

11 Power = < 5.0

12 Voltage = > 12.0 (verify proper charged voltage for aircraft/ avionics battery)

13 Inter nal = OK

14 IMU= Internal

15 CPU = < 75%

16 Pilot Sample = 100% (Pilot Console needs to be connected)

17 Pilot Uplink [Hz] = 16

- 17 (Pilot Console needs to be connected)

18 System Version: Verify current version

- Record aircraft firmware level i n the Aircraft Configuration

Worksheet.

19 Radio Settings > Press Request. N/A

20 Channel = As required

21 Power = 1.0

22 RSSI =

- 39 to

- 71

23 VSWR = 1.0 to 2.0 or N/AAircraft

Model: Serial

Number: Date:

Section Piccolo Comm and Center> Window Menu> Status Windows> Telemetry Tech

Initials

Aircraft must be outside with a clear view of sky for the following steps. N/A

24 Verify SBAS, ANT, 3D are green.

25 Nav filter => Mode = GPSINS, all other = OK. (Pos flashing red is ok)

26 Satellites = > 5 used / XX visible. Ensure that the difference between used and visible is not > 4.

27 PDOP ≤ 4

28 Solution = Internal, Aided by SBAS

Section Piccolo Command Center> Window Menu> Status Windows> Sensor Telemetry Tech

Initials

Aircraft must be level and stable for the following steps. N/A

29 Gyros (all) = ± 1.0 (No motor on)

30 From zero, increasing incrementally by .1 to full throttle (1.0). Verify gyro changes are less than ±10®

31 Gyro Bias Estimate (all) = ( if < Piccolo 2.1.2, ± 2.0 deg/sec) (if ≥ Piccolo 2.1.2, ± 3.0 deg/sec)

32 Accelerometers = X = 0.0 ± 1.0, Y = 0.0 ± 1.0, Z =

- 32.00 ± 1.0

33 Accelerometer Bias Estimate (all) = 0.0 ± 2.0

Aircraft must be clear of obstacles for the following steps for free range of slow movements. N/A

34IMUCheck Roll aircraft right = Positive value

35 Pitch aircraft up = Positive Va lue

36 Yaw aircraft right = Positive Value

Section Piccolo Command Center> Window Menu> Preflight Windows> Preflight Tech

Initials

Ensure that the autopilot temperature has reached > 40C ° before the next steps.

37 Enter 29.92 in the Altimeter Setti ng Window. Press Send.

38 Enter 2400 in Actual Altitude window > Shield Pitot/ Static Tubes > Press Zero Air Data.

39 In the Primary Flight Display, verify ALT = 2400 ± 10.0 ft. and IAS = 0.0 ± 2.0 kts.

40 Verify operation of the airspeed sensors by b lowing into the pitot tube

Note : If using Piccolo 2.2.1B or newer firmware, the firmware automatically detects and corrects for

reversed pitot and static lines. To determine whether they are truly reversed, watch the system

telemetry page. Watch Internal. If Internal = OK briefly switches to Internal = Fail and then back to

Internal = OK during the test, then the lines are reversed.

QA Verify previous two steps after 5 minutes have passed.

QA Perform IMU check.

QA Validate file and confirm no signific ant differences. Verify file is recorded.

QA Verify autopilot and FW version are recorded in configuration sheet.Aircraft

Model: Serial

Number: Date:

WARNING:

The proper Remote Video Terminal (RVT) and associated computer/ software will be set

- up for the following checks. Seek

the advice of the management team for procedures on how to operate the payload systems. Improper setup and use can

cause damage to payload components.

Section Payload Systems Checks Tech

Initials

1 Verify that the payloa d(s) antennas are connected to the RVT and aircraft Tx properly.

2 Power on the RVT and aircraft payload(s)/ Tx. Change the frequency as necessary to match the RVT

and aircraft Tx.

3 Verify that the reception of video data is acceptable and payload(s) function properly.

1 Ensure limits match maximum deflections of surfaces CAUTION:

The aircraft will need to be level and stable for the following steps. Refer to the Piccolo Surface Calibration Procedure for

instructions on how to conduct a surface calibration. Each aircraft type will have different values for desired maximum

deflection on different control surfaces. Seek the advice of the management team for aircraft specific values.

Aircraft Surface Calibration Checks

Left Aileron (elevon/ canarderon)

Pulse [us]

Deflection

Right Ai leron (elevon/ canarderon)

Pulse [us]

Deflection

Elevator

Pulse [us]

Deflection

Rudder

Pulse [us]

Deflection

Left Throttle

– IF USING TURBINE: Use Turbine Throttle Calibration and Learn RC Guide

Pulse [us]

Position

Surface ___________

Pulse [us]

Deflection

Surface ___________

Pulse [us]

DeflectionAircraft

Model: Serial

Number: Date:

Section Power Plant Checks Tech

Initials

1 (GAS/ELEC) Confirm that there are no signs of leaks, excessive wear, exposed wires, bad

bearings, etc

...

2 (GAS/ELEC) Prime engine/ connect power plant batteries as requ ired. 

### !Important! In an

Electric motor configuration with a motor that does not go through an “ arming ” process, if

pitot tube lines are pinched internally and/or the pitot tube cover is on, it is likely that the

autopilot will think that the plane is flyi ng, thus turning on the motor as soon as batteries

are plugged in. Prevent this by watching pitot tubes and pitot covers and disabling the

engine as soon as communications are established with the aircraft. 

### !Important!

Section Piccolo Command Center> Aircraft Actions Toolbar Tech

Initials

The following steps will be conducted in manual flight mode (AP off) using the Flight

Control Box. N/A

3 (GAS/ELEC) Enable Engine

4 (GAS) Start engine, allow for engine warm up and establish a proper i dle.

(note throttle idle setting in: PPC> Window Menu> Status Windows> Surface

Telemetry )

5 (GAS/ELEC) Command full throttle noting engine/ motor transition.

6 (GAS) Adjust fuel/ air mixture if necessary.

7 (GAS/ELEC) Perform throttle response chec ks by commanding:

idle

– wide open throttle

– idle x3

8 (ELEC) Connect watt/ amp meter or a calibrated Current Shunt to ensure

proper amp draw

9 (GAS/ELEC) Ensure a smooth transition and adequate wide open throttle

RPM. Record wide open throttle RPM in the Aircraft Configuration

Worksheet.

10 (ELEC) Ensure that the motor/ prop combination does not over draw power

plant batteries. See management for correct hardware combinations.

Section Piccolo Command Center> Window Menu> Preflight Windows> Prefl ight Tech

Initials QA

Initials

The following steps will be conducted in autonomous flight mode (AP On) for the next

steps. N/A N/A

10 (GAS) Throttle > Enter .15 > Press Hold.

11 (GAS) Start engine and establish a proper idle by entering in the previou sly

recorded throttle setting for idle.

12 (GAS) Verify that the engine has a smooth idle and does not stall.

13 (GAS/ ELEC) Command throttle setting of 1.0 (100%). Ensure that the engine

has a smooth transition.

14 (GAS/ ELEC) Ensure that the wide open throttle RPM matches that of the

manual throttle checks.Aircraft Model: Serial Number: Date:

Section Piccolo Command Center> Window Menu> Status Windows> Sensor Telemetry Tech

Initials

WARNING:

It is required to perform three throttle re sponse checks while monitoring the AP sensors to ensure that the isolation

mounts for the autopilot are sufficient in removing vibrations that can cause navigational problems. Failure to complete

this section can cause loss of aircraft in autonomous flight . The user must also monitor the Primary Flight Display during

throttle response checks to ensure that the aircraft attitude does not change from actual attitude.

15 Throttle Response Checks > Perform under Manual and or Auto (Piccolo Command Center>

Win dow Menu> Preflight Windows> Preflight)

16 Gyro Bias Estimate (all) = +/

- 2.0

17 Accelerometers = Z = Negative number throughout the throttle range

18 Accelerometer Bias Estimate (all) = 0.0 +/

- 2.0

Section Piccolo Command Center> Aircraft Actions Toolbar Tech

Initials

19 (GAS/ELEC) Disable Engine

Range Check

NOTES:

Refer to the Universal Range Check Procedure Guide for detailed instructions on manning and procedural steps while

conducting the range procedure. Record data from the range check in the fields provided. When complete with the range

check, ensure the engine is disabled, if equipped.

If the servos must be powered to safely operate the power plant, remember to verify they are operational before

operating the power plant.

Section Nom inal power (1.0 watt) Radio System Performance Checks Tech

Initials

1 North Link RSSI VSWR GPS PDOP

2 East Link RSSI VSWR GPS PDOP

3 South Link RSSI VSWR GPS PDOP

4 West Link RSSI VSWR GPS PDOP

Alternate Configuration (if applicabl e)____________ Radio System Performance Checks Initials

5 North Link RSSI VSWR GPS PDOP

6 East Link RSSI VSWR GPS PDOP

7 South Link RSSI VSWR GPS PDOP

8 West Link RSSI VSWR GPS PDOP

Amplified Power (if applicable) Radio System Perf ormance Checks Initials

9 North Link RSSI VSWR GPS PDOP

10 East Link RSSI VSWR GPS PDOP

11 South Link RSSI VSWR GPS PDOP

12 West Link RSSI VSWR GPS PDOPAircraft

Model: Serial

Number: Date:

Section Test Completion Steps Tec h

Initials QA

Initials

1 Verify Supplemental ATP steps have been completed

2 Upload and save applicable flight boundaries and send to aircraft

3 Upload and save applicable flight plans and send to aircraft

4 Configuration Management> Save All. Use the correct naming convention and save the

configuration file (.XML) onto a media and transfer to the shared drive in the appropriate

folder.

File Name:

5 De

- fuel aircraft/ remove power plant batteries for charging. (If applicable)

6 Remove autopilot p ower, disassemble aircraft and place aircraft in quarantine zone or

charging station

7 Charge batteries in preparations for flight.

Section Administrative Tech

Initials QA

Initials

1 Label aircraft components properly with correct serial numbers.

2 Verify that all supporting documentation is filled out and placed into the Aircraft Log Book.

Technician name: Completion Date:

Quality Assurance: Completion Date:

## Aircraft Flight Log worksheetAircraft Data

A/C

Model Serial

Number Autopilot S/N

- Mx

Propulsion

Unit Fuel

Source Firmware / Date

Flight Data

Flight

# Date Eng. Time (hrs) Flight Time (hrs) Takeoff Cycles Touchdown Cycles

Engine Time Page

Total: Flight Time Page

Total:

Notes

Page of

## Aircraft Discrepancy Log

- sheetAircraft Status Symbol Legend

X = Not Serviceable / =Known Issue, Serviceable √ = Serviceable

Symbol Discr epancy Symb ol Corrective Action

Date: Employee: Date: Employee:

Symbol Discr epancy Symbol Corrective Action

Date: Employee: Date: Employee:

Symbol Discr epancy Symbol Corrective Action

Date: Employee: Da te: Employee:

Symbol Discr epancy Symbol Corrective Action

Date: Employee: Date: Employee:

Symbol Discr epancy Symbol Corrective Action

Date: Employee: Date: Employee:

Aircraft Model,

S/N: Page: Of

## Ai rcraft Maintenance LogDate Record

Hobbs

Meter Total

time in

service Description of Inspections, Tests, Repairs and Alterations Tech

initials

## Aircraft Configuration WorksheetAvionics

Autopilot

S/N: Initial/

Date: Autopilot

S/N: Initial/

Date: Autopilot

S/N: Initial/

Date:

Autopilot

FW Version:

Initial/ Date: Autopilot

FW Version:

Initial/ Date: Autopilot

FW Version:

Initial/ Date:

Initial/ Date: Initial/ Date: Initial/ Date:

Payload

Payload / type:

Initial/ Date: Payload / type:

Initial/ Date: Payload / type:

Initial/ Date:

Initial/ Date: Initial/ Date : Initial/ Date:

Power Plant

Motor Type:

Prop type/

size:

Max RPM:

Max Amp :

Initial/Date: Motor Type:

Prop type/ size:

Max RPM:

Max Amp:

Initial/Date: Motor Type:

Prop type/

size:

Max RPM:

Max Amp:

Initial/Date:

Weight and Balance

CG / location:

Empty Mass:

Gross Mass:

Initial/ Date: CG / location:

Empty Mass:

Gross Mass:

Initial/ Date: CG / location:

Empty Mass:

Gross Mass:

Initial/ Date:

Aircraft Trim Settings

Trims Settings for Level Flight PCB Trim Values

Ail eron Elevator Rudder Throttle

Communications

Date C2 freq./ Ch. # Video freq. Notes

## UAV F l ight RecordDate A ircraft / UAV # A uto p ilot # Test/ M is s io n#

Internal Pilot / GCS Oper. External Pilot / Safety Pilot Test Director Crew Chief

Safety Officer Videographer Still Photographer Launcher Operator

Gross Weight CG Payload Video Tx/ Frequency

Engine / Motor Prop Onboard Computer C2 Frequency

Range Check Distance:

North East South West

Link

RSSI

Video Receiver Level

GPS Sat. (Used /

Available)

GPS PDOP

Location Wind (kts) Direction Visibility (SM) Weather

Temperature (F) Dew Point (F) Altimeter (Hg) Elevation (ft) (Kestrel)

Elevation (ft) (GPS) Density Altitude (ft) Humidity % ATIS (number)

Range Call In at Operations Start: Range Call in at Operations End:

Pre

- Flight Assembly Complete Signatures

Internal / External Pilot Acceptance Signatures

Reset

Log Battery /

Fuel level

Preflight Launch

Time Launch

Type Landing

Time Landing

Type Battery /

Fuel level

Post Flight Flight Time

Notes: