JIG Inspectors Workshop. Teddington September

Transcription

1 JIG Inspectors Workshop Teddington September

2 Title of Presentation Here Nic Mason Technical Services Manager Q8 Aviation 2

3 Equipment Qualification Aircraft fuelling nozzles and hose end regulators to SAE AS Aircraft fuelling hose to EI

4 Aircraft Fuelling Nozzles and Hose End Regulators to SAE AS

5 Aircraft Fuelling Nozzles and Hose End Regulators to SAE AS SAE Aerospace Standard 5877 prescribes requirements for the various types of nozzles that are used for the refuelling of aircraft fitted with pressure fuel servicing systems. The standard includes requirements for hose end pressure control valves (regulators), strainers and swivels. 5

6 SAE AS Qualification Tests & Sequence TEST PARAGRAPH TEST UNIT (SAMPLE) Proof Pressure & 2 Functional - Static & 2 Pressure Loss & 2 Leakage & 2 Swivel Endurance Endurance Electrical Conductivity Fuel Resistance / Extreme Temperature Accelerated Corrosion Strength Drop Test Worn Adaptor Burst Pressure

7 SAE AS 5877 Tests Proof pressure closed to 180 psig. Open to 300 psig. Functional static open & close poppet 5 times at 60 psig with no binding. Pressure loss nozzle & HER pressure loss not to exceed 35 psig at 600 usgpm. Electrical continuity across nozzle and adaptor when connected, resistance not exceeding 10 Ω. 7

8 SAE AS 5877 Tests Leakage no leakage over a range of closed vacuum and pressure and open pressures. Swivel endurance 2000 cycles with a 100 ft-lb bending load no leakage. Endurance 2000 poppet open-close cycles against a force of 25 lb 50 lb. No leakage poppet open close cycles at 400 usgpm flow at 55 psig pressure. No leakage. 4 x the above tests (2 x 8000 cycles) for Extended Operation. 8

9 SAE AS 5877 Tests Fuel Resistance & extreme temperature - 9

10 SAE AS 5877 Tests Accelerated corrosion -nozzle assembly immersed in salt water then placed in an oven at 54 C for 1 hour. Repeat cycle 50 times then wash and carry out 3 endurance cycle tests. Strength bending and axial loads of up to 600 ft lbs applied to connected and pressurised nozzle with no leakage, damage or deformation. Drop - With nozzle assembly connected to hose, dropped onto a concrete floor from a height of 6 feet ten times and then still be functional. Repeat drop test forty times during which one change of poppet lever and operating handles is permitted. 10

11 SAE AS 5877 Tests Worn adaptor - nozzle shall be attached to a badly worn adaptor and opened. It shall not be able to be disconnected while poppet is open. Burst pressure - unit will withstand a closed pressure of 240 psig and open pressure of 450 psig with no visual evidence of structural rupture. 11

12 SAE AS 5877 Tests 13.Strainer Strength 14.Hose end regulator performance and endurance 12

13 Drop Test 13

14 Strength Test & Leakage Test 14

15 Aircraft Fuelling Hose to EI

16 Typical Type C hose construction Tube (liner) Carcass Cover 16

17 EI 1529 Tests 17

18 Aircraft Fuelling Hose to EI 1529 Tolerance on inside diameter - +/-1.2 mm for 2 & 3 hoses. +/- 1.6 mm for greater than 3 and +/- 0.8 mm for less than 2 hoses. Hose Length - Length to be specified by purchaser. All hoses shall be one continuous length. 18

19 Aircraft Fuelling Hose to EI 1529 Proof pressure 600 psi Minimum burst pressure psi Adhesion after contact with fuel lbsf/ Dry adhesion lbsf/ Vacuum resistance - Type C -2.5 psi Type E & F -10 psi 19

20 Aircraft Fuelling Hose to EI 1529 Flexibility - hose shall be flexible and maintain pressure rating to -30 C.t all be Kink resistance cycle kink test with no permanent deformation. Electrical resistance 1 x 10 3 to 1 x 10 6 ohms/metre. Fuel contamination - 72 hour synthetic fuel soak test followed by an existent gum test. Gum not to exceed 10mg/100ml of test fluid. Kink resistance

21 Aircraft Fuelling Hose to EI 1529 Fuel discolouration - colour of the test fluid following the fuel contamination test shall not be less than +15 Saybolt. Ozone resistance - No cracking of cover material after 72 hours in an ozone enriched atmosphere. Cocentricity - Shall not be more than 1 mm. 21

22 Aircraft Fuelling Hose to EI 1529 Thickness of tube and cover - Tube not less than 1.6 mm. Cover 1.6 mm for hoses < 2 and 2.0mm for 2 and larger hoses. Security of coupling attachment - pressure tested to 600 psi Reattachable coupling approval cyclic surge pressures. 22

23 Aircraft Fuelling Hose Hose application Type B (conductive) not commonly used for fuelling commercial aircraft. Type C (semi-conductive) delivery hoses, hydrant inlet hoses. Type E (conductive) and F (semi-conductive) riser hoses and trailer connection hoses. Type F (semi conductive) regular high flow rate defuelling. 23

24 Aircraft Fuelling Hose to EI 1529 Type B and Type E hoses should not be used for into-plane delivery or hydrant servicer inlet hoses. Connections to aircraft or hydrant systems should only be made with Type C or Type F hoses. Type B and 24

25 Qualification and Approval Qualification is the process of demonstrating that equipment successfully meets or exceeds all of the mandatory test requirements of the relevant specification. Approval. It is only user companies that finally decide if a specific item of equipment is acceptable for their use. Neither the JIG or EI issue approvals.

26 Qualification and Approval Example individual company manual. Type B and Type E hoses should not be used for into-plane delivery or hydrant servicer inlet hoses. Connections to aircraft or hydrant system 26

27 Aircraft Fuelling Hose - New requirement In JIG Issue 11,if an aircraft fuelling hose is run over then it has to be replaced. 27