1、CEN PREN13773- 001 94 3404587 00b4452 169 AECMA STANDARD NORME AECMA AECMA NORM prEN 3773-00 1 Edition P 1 June 1994 DIT PAR LASSOCIATION EUROPEENNE DES CONSTRUCTEURS DE MATRIEL AROSPATIAL Technopolis - 175, rue Jean-Jacques Rousseau - F-92138 Issy-les-Moulineaux Cedex - Tl. (1) 47.36.98.76 UDC : 62
2、1.316.57:629.7 Descriptors : Aircraft industry, aircraft equipment, circuit breaker, manufacturing requirements, designation, marking ENGLISH VERSION Aerospace series Circuit breakers, single-pole, temperature compensated, rated currents 1 A to 25 A, switching capacity 65 Znll O00 A max. Part O01 :
3、Technical specification Srie arospatiale Disjoncteurs unipolaires compenss en temprature, intensits nominales 1 A 25 A, pouvoir de coupure 65 Inll O00 A max. Partie 001 : Spcification technique Luft- und Raumfahrt Temperaturkompensierte einpolige Schutzschalter, Nennstrme von 1 A bis 25 . Schaltverm
4、gen 65 In11 O00 A max. Teil 001 : Technische Lieferbedingungen This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA (Association Europenne des Constructeurs de Matriel Arospatial). It is published on green paper for the needs of AECMA-Members. It has been technical
5、ly approved by the experts of the concerned Technical Committee following comment by the Member countries. Subsequent to the publication of this prestandard, the technical content shall not be changed to an extent that interchangeability is affected, physically or functionally, without re-identifica
6、tion of the standard. After examination and signature of the AECMA Standard Checking Centre (NPS) and formal agreement of the Official Services of the Member countries it will be submitted as a draft European Standard to CEN (European Committee for Standardization) for formal vote. Nota - Extra copi
7、es can be supplied by B.N.A.E. - Technopolis 54 - 199, rue Jean-Jacques Rousseau - 921 38 ISSY-LES-MOULINEAUX CEDEX Comments should be sent within six months after the date of publication to I Edition approved for publication AECMA 1994-06-30 I Technooolis - 175. rue Jean-Jacaues Rousseau I 921 38 I
8、ssy-les-Moulineaux Cedex - FRANCE C2 Chairman M. Le Cunff aecma 1994 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PREN*3773- 001 94 M 3404589 00
9、64453 OT5 Page 3 prEN 3773-001 : 1994 Rated currents (In) A 1 2 2,5 3 5 7,5 10 15 20 Code 01A 02A 2A5 03A 05A 7A5 10A 15A 20A 1 Scope 25 25A This standard specifies the required characteristics for single-pole temperature compensated circuit breakers with rated currents from 1 A to 25 A for use in a
10、ircraft electrical systems, at a temperature between - 55 OC and 125 OC and at a maximum altitude of 2 = 22 O00 rn. It shall be used together with EN 2350. These circuit breakers are for use in aircraft with power supplies in accordance with EN 2282. Range 1) Low Medium 2 Normative references High I
11、S0 71 37 : 1987 Aircraft - Environmental conditions and test procedures for airborne equipment (Endorsement of EUROCAE/EDI 4B and RTCA/DO-l60B) EN 2282 Aerospace series - Characteristics of aircraft electrical supplies EN 2350 Aerospace series - Circuit breakers - Technical specification EN 3042 Aer
12、ospace series - Quality assurance - EN aerospace products - Qualification procedure - Button marking 3 Definitions 1 2 2- 1 3 5 71 10 15 20 25 2 2 See EN 2350. 4 Description These circuit breakers are operated by a push-pull control button with trip free release, and delayed tripping ; they are expl
13、osion-proof. Their function is assured up to the short-circuit current. 5 Required characteristics 1) Range in accordance with 6.1 .I of EN 2350 Table 2 r- I 28 V d.c. 26 V a.c., frequency 400 Hz, single phase 115 V a.c., frequency 400 Hz, Voltage of aircraft electrical system single phase Previous
14、page is blank Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PRENs3773- O01 94 3404589 0064454 T3L Characteristics Closing force Opening force Ope
15、rating force Page 4 prEN 3773-001 : 1994 Requirements 3,5 N to 45 N 5 N to 30 N If an aircraft electrical power supply of variable frequency is used, the limit values (voltage and frequency) shall be specified, in accordance with EN 2282. Actuation component 6 Tests 6.1 Mechanical tests See table 3
16、and 5.2 of EN 2350 I Push direction 110 N minimum Longitudinal Table 3 load 6.2 Pull direction 110 N minimum Tightening torque Rotational torque Attachment Mechanical strength 5 Nm minimum 3 Nm minimum I Transverse load I 1 IO N minimum Tightening torque 1,7 Nm minimum Tensile strength Main 110 N mi
17、nimum along FI Compression strength 55 N minimum along F2 Environmental tests See table 4 as well as 5.3 and 5.4 of EN 2350 Table 4 Characteristics Vibration : curve R, IS0 7137 Mechanical shock 1) Centrifugai acceleration 1) Sand and dust Corrosion Humidity Explosion-proof ness Contamination by liq
18、uids Requirements 5 Hz to 57 Hz, constant amplitude 2 a = 0,76 mm 57 Hz to 350 Hz, constant acceleration 49 m/s2 (= 5 g) 350 Hz to 500 Hz, constant amplitude 2 a = 0,02 mm 500 Hz to 2 O00 Hz, constant acceleration 98,l m/s2 (= 1 O g) 245,25 m/s2 (= 25 g), 11 ms 166,8 m/s2 (= 17 g) See EN 2350 See EN
19、 2350 See EN 2350 Category B : 10 cycles Short-circuit current See EN 2350 1 ) The tightening torques shall be those specified in the product standard. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or n
20、etworking permitted without license from IHS-,-,- - CEN PRENx3773- 001 74 3404587 0064455 978 Voltage drop at rated current Insulation resistance Page 5 prEN 3773-001 : 1994 See table 6 Minimum 100 MR 6.3 Electrical tests See tables 5 to 12 and 5.5 of EN 2350 Table 5 - Electrical characteristics Upp
21、er and lower trip limits Overload tripping I Characteristics I Requirements I See table 7 See table 8 Short-circuit performance Service life at no load and with load Service life under overload trip conditions Dielectric strength See table 9 See table 10 See table 11 1 500 V on ground t = (23 f 5) O
22、C t = (- 55 * 5) oc t = (125 * 5) OC 400 V at 22 O00 m t = (23 * 5) OC Overload test with mechanism locked Leakage current Il mA No flashover, no damage See table 12 1 2 2,5 3 5 7,5 10 Rated current A Maximum voltage drop v Maximum voltage drop V 100 mA at rated current 1,lO 0,80 0,75 0,55 0,35 0,30
23、 0,30 at minimum current 100 40 30 18 8 4 2,5 Trip free operation Lower trip thresholds at maximum altitude of 22 O00 rn = 40 hPa 15 20 25 0,25 0,25 0,20 2,5 2,5 2,5 105 % of In 105 % of In OC 80 % of In Ambient temperature Temperature * 5 oc 23 See table 8, at 23 OC only Load as % of In Minimum 1 h
24、 Maximum Il h 115 140 No tripping 70 _ 105 140 Table 7 - Tripping thresholds Rated current A 1 to 25 - 55 I 115 I 160 125 I 1 O0 I 140 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitt
25、ed without license from IHS-,-,-Page 6 prEN 3773-001 : 1994 Temperature f 5 oc Table 8 - Overload tripping times Overload as % of In 200 500 1 O00 1,5 to 20 2 to 30 1,5 to 20 I Tripping times in s I 0,035 to 0,6 Open circuit voltage Table 9 - Short-circuit performance (30 & 2) V (120 f 5) v Rated vo
26、ltage Fault current establishment time Prospective current and circuit Product standard Product standard 2 ms to 10 ms 2 ms to 5 ms In of circuit breaker 1 Ato25A 1 Ato25A calibration 1) Test altitude Ground 22 O00 m Ground 22 O00 m L/R 10A 5 O00 5 O00 1) See product standard I 2) For CO and OCO, se
27、e EN 2350 2 500 up to In I 3 A - Table 10 - Service life at no load and with load 5 O00 2 500 Number of operations to be performed I Supply voltage Open circuit Close Circuit characteristics Test conditions z=o E = 22 O00 m Overload t = (23 f 5) OC t = (23 f 5) OC 15 cycles CO 15 cycles OCO 1) I= 5I
28、n L/R = 5 ms (28 k 1,4) V d.c. 28 V d.c. 20 cycles CO 1) (1 15 f 5,751 V a.c., frequency 400 Hz I= 51n 15 cycles CO 1) 20 cycles CO 1) 0,6 I cos cp I 0,7 15 cycles OCO 1) 115 V a.c. to 200 V a.c., frequency 400 Hz At In inductive 0,6 2 cos cp 5 0,7 (MI 1) 5 O00 2 500 1) Tests marked (M) shall be pre
29、ceded by a no-load mechanical endurance test. NOTE : Tolerance for voltage, current and frequency values : f 5 %. I 1) For CO and OCO, see EN 2350. I Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or net
30、working permitted without license from IHS-,-,-CEN PREN*3773- 001 94 = 3404589 O064457 740 Opening time Requirement Page 7 prEN 3773-001 : 1994 10 x In 30 s 20 s 10s 8s ISC 1s Opening of circuit by destruction of circuit breaker without production of flames or excessive smoking Table 12 - Overload t
31、est with mechanism locked The circuit breaker shall be connected to cable with section to EN 2350 with length of 0,5 m without strains Loads 10 x In and short-circuit current (Isc) V = 115 V a.c. 7 Quality assurance See EN 3042 Sampling plan : see EN 2350 8 Designation See product standard 9 Marking See EN 2350. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
