AIRWORTHINESS DIRECTIVE
CAA-AD-T-032/1999R3
Nahrazuje CAA-AD-T-032/1999R2
Date of issue: March 01, 2002
HELICOPTER – TAIL ROTOR
HUB PITCH-CHANGE PLATE BEARING (ATA 05, 65) –
INSPECTION/REPLACEMENT
Applicability: AS 355 helicopters, versions E, F, F1,
F2 and N, fitted with tail rotor hub pitch-change plate, P/Nos. 350A33-2004-00/-01/-02/-03/-05
and which do not incorporate MOD 076551 (new generation bearing P/No.
6010F234M16 (704A33.651.190) introduced by EUROCOPTER AS 355 Service Bulletin
No. 65.00.15 R1).
Effective date: March 02, 2002
Compliance : Required as indicated in DGAC
AD 1999-084-057(A)R3.
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
DGAC ref: No. 1999-084-057(A)R3
EUROCOPTER
AS
355 Helicopters
Tail
rotor hub pitch-change plate bearing (ATA 05, 65)
1. EFFECTIVITY:
AS 355 helicopters, versions E, F, F1, F2
and N, fitted with tail rotor hub pitch-change plate, P/Nos.
350A33-2004-00/-01/-02/-03/-05 and which do not incorporate MOD 076551 (new
generation bearing P/No. 6010F234M16 (704A33.651.190) introduced by EUROCOPTER
AS 355 Service Bulletin No. 65.00.15 R1).
2. REASONS:
This
Airworthiness Directive (AD) is issued subsequent to some cases of
deterioration of the tail rotor hub pitch-change plate bearing, which can lead
to seizure of the bearing and loss of control of the aircraft.
Revisions 1 and 2 of this AD covered
Revisions 1 and 2 of EUROCOPTER Service Bulletin No. 05.00.30.
Revision 3 of this AD covers the
replacement of Service Bulletin No. 05.00.30 R2 with referenced Alert Service
Bulletin (ASB) No. 05.00.30, with no change to the technical content.
3. MANDATORY ACTIONS AND COMPLIANCE TIME:
3.1. Within 10 flying hours following the
effective date of Revision 1 of this Airworthiness Directive, check the
rotation torque of the bearing, in accordance with the instructions described
in paragraph 2.B 1) of the referenced ASB unless already carried out.
3.2. Check the bearing for axial play,
friction points and brinelling in accordance with the instructions described in
paragraph 2.B 2) of the referenced ASB.
3.2.1. within 10 flying hours (without
exceeding 2 weeks).following the effective date of Revision 1 of this
Airworthiness Directive, except for bearings which underwent this check less
than 40 flying hours ago or less than 6 months ago.
3.2.2.
every 50 flying hours (without exceeding 6 months between two checks).
3.3. Before installing a pitch-change
plate assembly or a tail rotor gear box assembly, held as spare, on an
aircraft, check the rotation torque and carry out the axial play, friction
point and brinelling check in accordance with the instructions described in
paragraphs 2.B 1) b) and 2.B 2) of the referenced ASB.
3.4.
Interpretation of results:
3.4.1.
If the measured rotational load is greater than 300 grams, remove the
pitch-change plate assembly from the aircraft, or do not install the
pitch-change plate assembly or tail rotor gear box assembly, held as spare, on
the aircraft.
3.4.2.
If the rotational load is less than 300 grams, and if the measured axial play
is greater than or equal to 0.4 mm, and/or friction points or brinelling are
detected :
- Check the condition of the parts
(excluding the pitch-change plate bearing) and replace them according to the
criteria defined in paragraph 2.B 3) b) of the referenced ASB.
-
Replace the pitch-change plate bearing with a bearing in airworthy condition.
REF. :
EUROCOPTER AS 355 Alert Service Bulletin No. 05.00.30.
This Revision 3 replaces AD
1999-084-057(A) R2 dated October 20,1999.
EFFECTIVES DATES :
Original
AD : MARCH 06,1999
Revision
1 : On receipt of the Telegraphic AD issued on MAY 14,1999
Revision
2 : OCTOBER 30, 1999
Revision 3 : MARCH 02, 200