Frangibility Test Data
The frangibility tests on the Pollite approach pole were conducted as per the above test plan on 11th March and 24th April 2008 in the presence of Intertek Etl Semko.
Impact tests were conducted on three 5m frangible approach poles manufactured to identical specifications.
The purpose of these tests was to ensure the Pollite approach pole design fulfilled the test requirements laid out in ICAO Doc 9/57 AN/901 Aerodrome Design Manual Pt 6 Chpt 4, 4.9 19 - 4.9.23 & US Dept of Transportation FAA Advisory Circular No. 150/5345-45C 3.9 a-e.
As per 4.9.20 of the above ICAO documents: 'The support structure should not impose a force on the aircraft in excess of 45 kN. The maximum energy imparted to the aircraft as a result of the collision should not exceed 55kJ over the contact period'
Result:
Recorded Impact Contact Period recorded at 90 milliseconds
Maximum impact force measured: 39.28 kN (8660lbs)
Energy Imparted: 30.33kJ (22375.2 ft lbs)
Impact Force kN graph over 90 milliseconds contact period.
As per 4.9.21 of the above ICAO documents: 'The impacted structure should give way to passage of the aircraft in a manner such that the latter may still achieve a successful landing..'
Result: During the test as visible on the film the pole gave way to the vehicle and impactor without obstructing it's passage.
As per 5.2.19 a & b of the above ICAO documents: 'The portion of the tower above the point of impact should not grasp the aircraft wing while the lower portion remains attached to the foundation thus inordinately altering the direction of aircraft' & 'upon impact, the tower may fragment into several components. The mass of these components and their manner of release should not cause a secondary hazard to the aircraft.'
Result: During the test as visible on the attached DVD (attachment 1) the portion of pole above impact did not grasp the aircraft wing nor was their any visual indication of an obvious potential for secondary hazard to the aircraft.
As per 4.9.23 of the above ICAO documents: 'With regard to cabling, the designer should ensure that there are points of disconnection so that segmentation is not hindered'
Result: During the test, as visible on the film, segmentation of cabling is clearly visible at impact.
Conclusion
Following the three tests undertaken and the collection of data from load cells and camera footage the Pollite designed approach pole fulfills the frangibility requirements laid out in ICAO Doc 9/57 AN/901 Aerodrome Design Manual Pt 6 Chpt 4, 4.9 19 - 4.9.23 & US Dept of Transportation FAA Advisory Circular No. 150/5345-45C 3.9 a-e.
Certification available upon request.
