AIRWORTHINESS DIRECTIVE
CAA-AD-T-054/2000
Date of issue: June 6, 2000
HELICOPTER - TAIL ROTOR HEAD - INSPECTION
Applicability:
AS 350 helicopters, versions: B, B1, B2, B3, BA, BB and D [TAD no T2000-222-079(A)] AS 355 helicopters, versions: E, F, F1, F2 and N [TAD no T2000-223-059(A)] fitted with tail rotor pitch change rotating plates, all part numbers, on which MOD 07 6554 has not been embodied.Effective date: Upon receipt.
Compliance : Required as indicated in DGAC AD T2000-223-059(A).
Remarks:. The compliance of this AD must be recorded in Aircraft Logbook, where applicable the requirements of this AD must be integrated into Aircraft Technical Documentation. Address inquiries concerning this AD to: Civil Aviation Authority, Airworthiness Division, Ruzyne Airport, 160 08 Prague 6, Czech Republic, tel: 420 2 33320922, fax: 420 2 20562270
Ing. Pavel MATOUŠEK
Director of Airworthiness Division
CAA CZ
TELEGRAPHIC AIRWORTHINESS DIRECTIVES RELEASED BY THE DIRECTION
GENERALE DE L'AVIATION CIVILE (France).
THIS TEXT IS NOT SENT TO FOREIGN OPERATORS OF AICRAFT NON
REGISTERED IN FRANCE. IT IS UP TO THE NATIONAL AUTHORITIES TO FORWARD
IT TO THEM ON RECEIPT.
No. T2000-222-079(A]-EUROCOPTER-AS 350 Helicopters
No. T2000-223-059/A] - EUROCOPTER -AS 355 Helicopters
SUBJECT : Bearing Spacer of the Tail Rotor Head Pitch Change Plate (ATA 05, 64).
1. EFFECTIVITY:
AS 350 helicopters, versions: B, B1, B2, B3, BA, BB and D [TAD no T2000-222-079(A)]
AS 355 helicopters, versions: E, F, F1, F2 and N [TAD no T2000-223-059(A)]
fitted with tail rotor pitch change rotating plates, all part numbers, on which MOD 07 6554 has not been embodied.
2. REASON:
These Telegraphic Airworthiness Directives are issued to prevent deterioration and loss of the tail rotor head (TRH) pitch change control.
3. MANDATORY ACTIONS AND COMPLIANCE TIME:
The following measures are rendered mandatory from the effective date of this Telegraphic Airworthiness Directive.
3.1. At the latest within 10 flying hours, identify the position of the tail rotor pitch change rotating plate and of the spacer in compliance with the instructions given in paragraph 2B1 of referenced EUROCOPTER AS 350 No. 05.00.33 and AS 355 Service Bulletins No. 05.00.33
referenced below.
3.2. At check after the last flight of the day, check in compliance with the instructions given in paragraph 2B2 of referenced Service Bulletins that the pain index marks on the tail rotor pitch change rotating plate and on the spacer are aligned.
If the paint index marks are aligned: comply with the instructions described in paragraph 2B3 of referenced Service Bulletins (embodiment of MOD 07 6554) at the latest during the next "T" basic inspection.
If the paint index marks are not aligned: comply with the instructions described in paragraph 2B4 of referenced Service Bulletins (embodiment of MOD 07 6554) at the latest within 25 flying hours from detection of the misalignment.
3.3. Before installing a pitch change plate assembly or a tail rotor gear box assembly, held as spares, on an aircraft, comply with the instructions described in paragraph 2B3 of referenced Service Bulletins (embodiment of MOD 07 6554).
REF. : EUROCOPTER AS 350 Service Bulletin No. 05.00.33
EUROCOPTER AS 355 Service Bulletin No. 05.00.33.
EFFECTIVE DATE: UPON RECEIPT