APPROVED BY: TESTED BY:

R.A. Hills Christopher Bennetts Technical Manager Senior Project Engineer

10 VANADIUM PLACE, PO BOX 9194, ADDINGTON 8243, CHRISTCHURCH, NEW ZEALAND Page 1 of 19

TEL: +64 3 940 4400 FAX: +64 3 940 4411 EMAIL: enquiries@nz.ul.com INTERNET: www.nz.ul.com

Laboratory Test Report Report No.: 08CA65949-01 This report may not be reproduced except in full. Date Issued: 22 January 2009 It contains no corrections or erasures.

SUBJECT:

Iridium 9505/A Mount

REQUESTED BY: Flightcell International Ltd 98 Vickerman Street PO Box 1481 Nelson New Zealand

INSTRUCTIONS: Vibration testing based on Method 514.5 – Vibration of Mil-Std-810F “Department of Defence Test Method Standard for Environmental Engineering Considerations and Laboratory Tests”. Shock testing to customer’s specification.

CONTENTS: General Date of test Description Results A: Mil-Std 810F – Method 514.5 Vibration Results B: Shock Testing Appendix A: Representative Vibration Test Results Appendix B: Representative Shock Test Results

SUMMARY: Test results in this report confirm that the Iridium 9505/A Mount was tested according to Method 514.5 – Vibration of Mil-Std-810F and according to the customer’s shock test specification. The ball-joint slipped under shock loading but no damage was observed on the mount or the 9505 telephone.

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

GENERAL

a) As detailed in this report, one specimen of the Iridium 9505/A Mount was received for testing.

b) The results detailed in this report relate only to the specimen submitted by the customer.

c) The Iridium 9505/A Mount was tested based on Method 514.5 – Vibration of Mil-Std-810F and according to a customer-specified shock test.

d) All testing was carried out under the following environmental conditions, unless otherwise noted:

Ambient temperature 15°C to 25°C Relative humidity 30 % to 60 % Atmospheric pressure 86 kPa to 106 kPa

e) Note: N/R = Not Relevant to design assessed, N/T = Not Tested at manufacturer’s request, EUT = Equipment Under Test, DNC = Did Not Comply.

f) The reported expanded uncertainties (U ) listed below are based on standard uncertainties multiplied by a coverage factor k = 2, and define an interval ±U providing a level of confidence of approximately 95%.

i. acceleration 0.05 m/s2 – 500 m/s2 ± 5 %

DATE OF TEST

Testing was completed on 17 December 2008.

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

DESCRIPTION

The Iridium 9505/A Mount was a lightweight anodized aluminium cradle for a satellite telephone. It was designed to hold a 9505 or 9505A phone in a vehicle environment at an angle determined by the adjustable base. The two ball-joints on the base were tightened via a single handle. For the purpose of this test a telephone was placed in the cradle and the circular base was clamped rigidly to the shock-test surface. Approximate dimensions [mm]: Cradle: L 220 x W 70 x H 70 Ball-joint base: H 90 x Diameter 60

Iridium 9505/A Mount: Overall View Showing Adjustable Base

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

Iridium 9505/A Mount: Overall View Showing Placement of 9505 Satellite Telephone

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

RESULTS A: Method 514.5 – Vibration from Mil-Std-810F “Department of Defence Test Method Standard for Environmental Engineering Considerations and Laboratory Tests”.

CLAUSE 1 SCOPE Applied

CLAUSE 2 TAILORING GUIDANCE Noted

CLAUSE 3 INFORMATION REQUIRED Noted

Clause 3.1 Pre-test Noted

(1) Test fixture requirements: The base of the Iridium 9505/A Mount was clamped to the vibration generator using bolts and washers.

(2) Test fixture modal survey was not performed for this test. (3) Test item / fixture modal survey was not performed for this test. (4) Vibration exciter control strategy: Single point control. (5) Test tolerances: ±3 dB over the frequency range. Out of tolerance

bandwidths <5 % of total test control bandwidth. (6) Combined Environments were not required for this test. (7) Test schedule and duration of exposure: Procedure I – General

Vibration. Category 14. Duration = 1 hour per axis (8) Axes of exposure: The samples were exposed to vibration in each of

the three axes defined in the following photograph. Measurement instrumentation configuration: Current feedback of piezoelectric acceleration signals via LDS controller and associated software.

(9) Test shutdown procedures: Test shuts down if control signal acceleration departs from the desired profile by ± 6 dB.

(10) Test interruption recovery procedure: Test stopped in the event of a test item failure.

(11) Test completion procedure: Test is complete when all elements of the test item have successfully passed a complete test.

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

Iridium 9505/A Mount Set Up For X-Axis Vibration And Showing Other Axis Definitions For The Purposes Of This Testing

Clause 3.2 During Test Noted

An Iridium 9505 satellite phone was installed in the Mount to determine whether the vibration would cause loosening.

Clause 3.3 Post-test Noted

Visual checks of the Mount and phone were conducted following testing.

CLAUSE 4 TEST PROCESS Applied

Clause 4.1 Test Facility Applied

Clause 4.1.1 Procedure I – General Vibration Applied

Vibration testing was conducted using Underwriters Laboratories’ electrodynamic shaker.

Clause 4.1.2 Procedure II – Loose Cargo Transportation N/R

X-AXIS Y-AXIS

Z-AXIS

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

Clause 4.1.3 Procedure III – Large Assembly Transportation N/R

Clause 4.1.4 Procedure IV – Assembled Aircraft Store Captive Carriage and Free Flight N/R

Clause 4.2 Controls Applied

Clause 4.2.1 Control Strategy Applied

Clause 4.2.1.1 Acceleration input control strategy Applied

Clause 4.2.1.2 Force control strategy N/R

Clause 4.2.1.3 Acceleration limit strategy N/R

Clause 4.2.1.4 Acceleration response control strategy N/R

Clause 4.2.1.5 Open loop waveform control strategy N/R

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

Clause 4.2.2 Tolerances Applied

The following tolerances were applied:

Clause 4.2.2.1 Acceleration Spectral Density: Applied

a. Vibration environment: Acceleration spectral density was within ±3 dB over the specified frequency range

b. Vibration measurement: The system provided acceleration spectral density measurements within ±0.5 dB of the vibration level of the transducer mounting surface over the required frequency range. The control system utilised 4096 frequency lines, with 250 degrees of freedom.

Clause 4.2.2.2 Peak Sinusoidal Acceleration Noted

Clause 4.2.2.3 Frequency Measurement Applied

The vibration measurement system provided frequency measurements within ±1.25 % at the transducer mounting surface over the required frequency range.

Clause 4.2.2.4 Cross axis accelerations Noted

Clause 4.3 Test Interruption N/R

Clause 4.4 Test Setup Applied

Mounting method as per Clause 3.1. Gravitational orientation with respect to gravity was maintained as shown in the photograph on page 6.

Clause 4.5 Test Execution Applied

Clause 4.5.1 Preparation for test Applied

A visual examination was carried out before the commencement of the test and no existing damage was observed.

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

Clause 4.5.2 Procedure I – General vibration Applied

Category 14: “Rotary wing aircraft – Helicopter” was chosen as helicopter transportation was thought to be the worst in-service condition for this item. No specific helicopter model was provided, so an average value was chosen using the blade frequencies in Table 514.5C-IV of Mil-Std 810F. Four blades and a frequency of 4.35 Hz were selected. “General” location within the vehicle. Four blade-passing harmonics were superimposed upon a random vibration spectrum between 10 Hz and 500 Hz as shown below:

Random Vibration Frequency [Hz] Acceleration [g2/Hz]

10 0.001

100 0.01

300 0.01

500 0.001

Sinusoidal Tone Frequency [Hz] Amplitude [gn]

1 4.35 0.11

2 17.4 1.74

3 34.8 2.5

4 52.2 1.5 Further test details and a representative graphical output are included in Appendix A.

Clause 4.5.3 Procedure II – Loose cargo transportation N/R

Clause 4.5.4 Procedure III – Large assembly transportation N/R

Clause 4.5.5 Procedure IV – Assembled Aircraft Store Captive Carriage and Free Flight N/R

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

CLAUSE 5 ANALYSIS OF RESULTS Complied

The sample was subjected to visual checks following testing. No physical damage was observed. The satellite phone was held satisfactorily in the Iridium 9505/A Mount and the base joint angles were maintained.

CLAUSE 6 REFERENCE/RELATED DOCUMENTS Noted

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

RESULTS B: Shock Testing

This testing was performed to the customer specification, which was not known to relate directly to any published standard.

The Iridium 9505/A Mount was subjected to the following test parameters:

SHOCK PULSE PARAMETERS

Peak acceleration [g] 20

Effective pulse length [ms] 25

Pulse shape half sine

Tolerances on pulse shape according to ISO

Shocks pulses in each axis 3 positive, 3 negative

Total number of shocks 18

Refer to Appendix B for further test details and representative software outputs. An Iridium 9505 phone was installed in the Mount to determine whether the shocks would result in loosening. Gravitational orientation of the EUT was maintained as per the operational setup (see photograph on page 6). The base of the Iridium 9505/A Mount was clamped to the vibration generator using bolts and washers.

TEST PROCESS

Instrumentation

Shock test control was by means of a single piezoelectric accelerometer (PCB type 353B03).

Visual and Functional Checks

Visual checks were carried out on the Iridium 9505/A Mount before and after testing. The ball-joint fastener was screwed in as tight as was practical with one hand.

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

RESULTS During the repeated shocks the angle of the ball joints changed (<30°). In some cases this slippage resulted in the cradle contacting the mounting surface during subsequent shocks. The sample and satellite phone were subjected to a visual check following testing and no detrimental effects were observed.

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

APPENDIX A: Representative Vibration Test Results

Project File Name: General Helicopter Mil-Std Cat14.prj Profile Name: Iridium Mount vertical axis Test Type: Sine on Random Run Folder: .\RunDefault Oct 31,2008 14-39-09

profile(f)

high-abort(f)

low-abort(f)

high-alarm(f)

low-alarm(f)

control(f)

552.962.56 10.00 100.00

67.5274

0.0001

0.0010

0.0100

0.1000

1.0000

10.0000

Frequency (Hz)

(gn)²/Hz

Level: 100 % Control RMS: 2.975885 gn Full Level Elapsed Time: 01:00:00 Lines: 1600 Frame Time: 3.200000 Seconds Demand RMS: 2.996112 gn Remaining Time: 00:00:00 DOF: 250 dF: 0.312500 Hz Data saved at 02:51:34 PM, Friday, October 31, 2008 Report created at 02:51:36 P.M., Friday, October 31, 2008

Shaker Parameters Shaker Name: LDS - V830-335 Positive Displacement Limit Peak: 1.00 in Negative Displacement Limit Peak: 1.00 in Maximum Velocity Peak: 78.70 in/s Maximum Acceleration Peak: 180.00 gn Minimum Drive Frequency: 5.00 Hz Maximum Drive Frequency: 3000.00 Hz Maximum Drive Peak: 10.00 Volts Orientation: Vertical Assume Noisy Measurement?: Yes

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

Channel Parameters

Input Channel Parameter

Input Type Max. Volts mv/(gn) Weighting Coupling 3 Control 1.00 10.05 1.00 AC

Output Channel Parameter Output Type Max. Volts 1 Output 10.00

Control Parameters

Test Parameters Number of Spectral Lines: 1600 Max. Test Frequency: 500.00 Hz Measurement Strategy: Single Channel Line Abort Ratio: 0.30 Line Abort Number: 480 Averaging Number: 125 Drive Limit: 10.00 Volts Sigma Clip: Disable Data Points/Frame: 4096 Frame Time: 3.200000 Seconds Sampling Rate: 1280 Hz DOF: 250 dT: 0.000781 Seconds dF: 0.312500 Hz

Pre-test parameters Method of Acquiring the Loop Frequency Response Function:

Measure During Pre-Test

Initial Peak Drive: 0.005000 Volts Ramp-Up Rate: Fast Response Level Goal: 10.00 % Maximum Peak Drive: 1.000000 Volts

Profile Parameters

profile 1 Profile name: Iridium Mount vertical axis Broadband Acceleration RMS: 1.790427 gn Broadband Velocity RMS: 1.068702 in/s Broadband Displacement RMS: 0.006902 in Narrowband Acceleration RMS: 2.402051 gn Narrowband Velocity RMS: 5.602560 in/s Narrowband Displacement RMS: 0.058428 in Overall Acceleration RMS: 2.995910 gn

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

Overall Velocity RMS: 5.703578 in/s Overall Displacement RMS: 0.058834 in Overall Expected Acceleration (Peak): 8.987731 gn Overall Expected Velocity (Peak): 17.110733 in/s Overall Expected Displacement (Peak): 0.353007 in Shaker Acceleration (Peak): 180.0000 gn Shaker Velocity (Peak): 78.7000 in/s Shaker Displacement (Peak-Peak): 2.0000 in RMS Limits come from: Calculated based on table High Abort: 3.572382 gn (99.53 %) High Alarm: 2.529044 gn (41.25 %) Profile: 1.790427 gn Low Alarm: 1.267527 gn (-29.21 %) Low Abort: 0.897341 gn (-49.88 %) Profile Table: Frequency Left Slope Acceleration Velocity Displacement Right Slope Hz dB/Oct (gn) Peak (in/s) Peak (in) Peak dB/Oct 10.0 0.001 0.00614479 0.000195595 3.01043 100.0 3.01043 0.01 0.00614479 1.95595e-005 Const. Acce. 300.0 Const. Acce. 0.01 0.00204826 2.17328e-006 -13.5692 500.0 -13.5692 0.001 0.000122896 7.82379e-008

Sine Tone Profile Parameters Sweep in harmonic mode: No

Tone Number 1 Amplitude Peak: 0.11 gn Amplitude High Alarm: 3 dB Amplitude High Abort: 6 dB Ramping Up/Down rate: 12 dB/sec Sweep Low Frequency: 4.35 Hz Sweep Start Frequency: 4.35 Hz Sweep High Frequency: 4.35 Hz Sweep Mode: Linear Sweep Rate: 0 Hz/Sec Initial Sweep Direction: Up Enable burst this tone on and off rapidly: No

Tone Number 2 Amplitude Peak: 1.74 gn Amplitude High Alarm: 3 dB Amplitude High Abort: 6 dB Ramping Up/Down rate: 12 dB/sec Sweep Low Frequency: 17.4 Hz Sweep Start Frequency: 17.4 Hz Sweep High Frequency: 17.4 Hz Sweep Mode: Linear Sweep Rate: 0 Hz/Sec Initial Sweep Direction: Up Enable burst this tone on and off rapidly: No

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

Tone Number 3

Amplitude Peak: 2.5 gn Amplitude High Alarm: 3 dB Amplitude High Abort: 6 dB Ramping Up/Down rate: 12 dB/sec Sweep Low Frequency: 34.8 Hz Sweep Start Frequency: 34.8 Hz Sweep High Frequency: 34.8 Hz Sweep Mode: Linear Sweep Rate: 0 Hz/Sec Initial Sweep Direction: Up Enable burst this tone on and off rapidly: No

Tone Number 4 Amplitude Peak: 1.5 gn Amplitude High Alarm: 3 dB Amplitude High Abort: 6 dB Ramping Up/Down rate: 12 dB/sec Sweep Low Frequency: 52.2 Hz Sweep Start Frequency: 52.2 Hz Sweep High Frequency: 52.2 Hz Sweep Mode: Linear Sweep Rate: 0 Hz/Sec Initial Sweep Direction: Up Enable burst this tone on and off rapidly: No

Schedule Parameters

schedule 1 schedule name: Schedule1 0:0:10 at Level 50.0 % SoR On 1,2,3,4, Off 5,6,7,8,9,10,11,12, Broadband On 0:0:10 at Level 50.0 % 1:00:0 at Level 100.0 % Save All Panes Auto-Save Signals

Pre-Test Result Noise At Level 10 % Estimated at Full Level Drive 0.000000 volts 0.013413 volts 0.134128 volts input 3 0.018348 volts 0.012127 volts 0.121272 volts

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

APPENDIX B: Representative Shock Test Results

Project File Name: iDesign 20g max.prj Profile Name: Iridium Mount y-axis 20gn 25mSec Test Type: Classical Shock Run Folder: .\RunDefault Dec 17,2008 13-57-04

profile(t)

high-abort(t)

low-abort(t)

control(t)

0.05-0.03 -0.02 -0.01 0 0.01 0.02 0.03 0.04 0.05

27.5000

-30.0000

-27.0000

-24.0000

-21.0000

-18.0000

-15.0000

-12.0000

-9.0000

-6.0000

-3.0000

0

3.0000

6.0000

9.0000

12.0000

15.0000

18.0000

21.0000

24.0000

Time (Seconds)

gn

Level: 100 % Block Size: 512 Elapsed Pulses: 14 Frame Time: 0.170667 Seconds Control Peak: 20.461372 gn Control RMS: 7.429550 gn Full Level Elapsed Pulses: 6 dT: 0.000333 Seconds Demand Peak: 20.000000 gn Demand RMS: 7.253651 gn Remaining Pulses: 0 Pulse Type: Half Sine Amplitude: 20.000000 gn Data saved at 01:59:10 PM, Wednesday, December 17, 2008 Report created at 01:59:26 P.M., Wednesday, December 17, 2008

Shaker Parameters Shaker Name: LDS - V830-335 Positive Displacement Limit Peak: 0.08 ft Negative Displacement Limit Peak: 0.08 ft Maximum Velocity Peak: 1998.98 mm/s Maximum Acceleration Peak: 75.00 gn Minimum Drive Frequency: 5.00 Hz Maximum Drive Frequency: 3000.00 Hz Maximum Drive Peak: 10.00 Volts Orientation: Vertical Assume Noisy Measurement?: No

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

Channel Parameters

Input Channel Parameter

Input Type Max. Volts mv/(gn) Weighting Coupling 3 Control 1.00 10.53 1.00 AC

Output Channel Parameter Output Type Max. Volts 1 Output 10.00

Control Parameters

Test Parameters Block Size: Auto Averaging Number: 4 Drive Limit: 10.00 Volts Pulse Interval: 3.000 seconds Point Abort Ratio: 0.10 Low-Pass Filter Type: Do not apply filter Data Points/Frame: 512 Frame Time: 0.170667 Seconds Sampling Rate: 3000 Hz dT: 0.000333333 Seconds Maximum Analysis Frequency: 1318.36 Hz SRS Analysis: Disable

Pre-test parameters Method of Acquiring the Loop Frequency Response Function:

Measure during close-loop pre-test

Initial Peak Drive: 0.001000 Volts Ramp-Up Rate: Fast Response Level Goal: 10.00 % Maximum Peak Drive: 1.000000 Volts

Profile Parameters

profile 1 Profile name: Iridium Mount y-axis 20gn 25mSec Pulse Type: half sine Amplitude: 20.00 gn Pulse Width: 25.00 ms Main Pulse Tails: ISO Standard Compensation Template: Pre-Post half sine Pre-Pulse Height: 80.00 % Post Pulse Height: 80.00 % Abort Setting: ISO Standard

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Report No.: 08CA65949-01 Date Issued: 22 January 2009

Schedule Parameters

schedule 1

schedule name: Schedule1 1 Pulses at Level 50.00 % 3 Pulses at Level 100.00 % Inverse Pulse 3 Pulses at Level 100.00 % Save All Panes Auto-Save Signals

Pre-Test Result Noise At Level 10 % Estimated at Full Level Drive 0.000000 volts 0.108850 volts 1.088501 volts input 3 0.000276 volts 0.019852 volts 0.198517 volts

Run log Dactron Dual DSP Shaker Control System

Classical Shock Test Run Log 13:57:05, Wednesday, December 17, 2008 ENTRY TIME LEVEL CTL/DEMAND SOURCE DESCRIPTION /ELAPSED (Peak) 00:00:00/ 0 0.00 % User Command Start the Test 00:00:02/ 1 Open 0.036/ 2.000 gn Controller Running in pre-test 00:00:04/ 2 0.53 % 0.106/ 2.000 gn Controller 00:00:07/ 3 2.12 % 0.378/ 2.000 gn Controller 00:00:11/ 4 8.46 % 1.664/ 2.000 gn Controller 00:00:14/ 5 10.00 % 1.980/ 2.000 gn Controller 00:00:16/ 6 10.00 % 1.999/ 2.000 gn Controller 00:00:20/ 7 10.00 % 1.962/ 2.000 gn Controller System paused after pre-test 00:00:22/ 7 10.00 % User Command Run Scheduled Test 00:00:22/ 8 50.00 % 9.977/10.000 gn Controller Running in scheduled test 00:00:26/ 9 100.00 % 19.076/20.000 gn Controller 00:00:28/ 10 100.00 % 19.403/20.000 gn Controller 00:00:31/ 11 100.00 % 19.519/20.000 gn Controller 00:00:35/ 12 100.00 % 20.737/20.000 gn Controller 00:00:37/ 13 100.00 % 20.540/20.000 gn Controller 00:00:40/ 14 100.00 % 20.461/20.000 gn Controller 00:00:45/ 14 100.00 % Controller All Panes saved to the disk. 00:00:45 100.00 % Controller 'control(t),' Saved Signals 00:00:45/ 14 100.00 % 20.461/20.000 gn Controller End of Test 00:00:45/ 14 100.00 % Full level elapsed 6 00:00:45/ 14 100.00 % Total elapsed 14

END OF REPORT