AD/S-PUMA/26 - Single Pole Circuit Breaker
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
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Eurocopter AS 332 (Super Puma) Series Helicopters
AD/S-PUMA/26 Single Pole Circuit Breaker 12/97
Applicability: All Eurocopter AS 332 C, C1, L and L1 helicopters fitted with single pole circuit breakers manufactured by CROUZET bearing the following part numbers:
| 1 | Amp. : | 84 400 028 | 7.5 | Amp. : | 84 400 033 |
|---|---|---|---|---|---|
| 2 | Amp. : | 84 400 029 | 10 | Amp. : | 84 400 034 |
| 2.5 | Amp. : | 84 400 030 | 15 | Amp. : | 84 400 035 |
| 3 | Amp. : | 84 400 031 | 20 | Amp. : | 84 400 036 |
| 5 | Amp. : | 84 400 032 | 25 | Amp. : | 84 400 037 |
Note: The aircraft primarily affected are those delivered new between 24 April 1995 and 31 August 1996, however other aircraft are affected if the circuit breakers have been replaced since 24 April 1995.
Requirement: 1. Check all circuit breakers with part numbers 84 400 XXX that are fitted to installations listed in paragraph 1D1 of EUROCOPTER AS 332 Service Bulletin (SB) No. 01.00.49 dated 30 June 1997.
2. Apply the procedure detailed in paragraph 2B of the SB to all the circuit breakers for the remaining installations.
3. Test each circuit breaker held as a spare and bearing a part number listed in this airworthiness directive by applying a torque load and checking the circuit breaker in accordance with the directives given in paragraphs 2B(1) and 2B(2) of the SB.
4. The use of the circuit breakers bearing the part numbers listed in this Airworthiness Directive is prohibited.
Note: DGAC AD 97-202-062 (AB) refers.
Compliance: 1. Within 100 hours time in service but no later than 6 February 1998.
2. Within 500 hours time in service but no later than 6 May 1998.
3. Prior to, and after, installation.
4. From 31 December 1999.
This airworthiness directive becomes effective on 6 November 1997.
Background: This AD is issued to check for any loss of electrical continuity for single-pole circuit breakers bearing the part numbers listed. During testing by the OEM a loss of electrical continuity was discovered between the terminals of the circuit breaker in the engaged position. This loss was found to be due to deterioration of the circuit breaker operation brought about by excessive torque loading during installation.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES