AD/Bell 222/24 Amdt 1 Main Rotor Hydraulic Actuator Support (Cth)

AIRWORTHINESS DIRECTIVE

On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/BELL 222/24 and issues the following AD under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Bell Helicopter Textron Canada (BHTC) 222 Series Helicopters

AD/BELL 222/24 Amdt 1 Main Rotor Hydraulic Actuator Support 9/2007

Applicability:

Model 222, 222B, 222U, and 230 helicopters, with a main rotor hydraulic actuator support part number 222-040-125-001 installed.

Requirement:

1.    a.     Visually inspect the main rotor hydraulic actuator support for the presence of all dowel pins and for sealant between the support and the transmission.  If any pin is missing, or if no sealant is visible, before further flight, remove the support and further inspect the support, transmission case, studs, and dowel pins in accordance with the Accomplishment Instructions paragraphs 5 through 7 of BHTC Alert Service Bulletin (ASB) 222-00-86, 222U-00-57 or 230-00-18, as applicable.  Repair or replace any unserviceable support, transmission case, stud, or dowel pin before further flight.

b.    Verify the torque of the support attaching nuts.  Upper nuts must not rotate at a torque less than 40 inch-pounds.  Lower nuts must not rotate at a torque less than 90 inch-pounds

(i)    If two or more upper nuts rotate at a torque less than 40 inch-pounds or two or more lower nuts rotate at a torque less than 90 inch-pounds, before further flight, remove the support and further inspect the support, transmission case, studs, and dowel pins in accordance with the Accomplishment Instructions paragraph 5 through 7 of the applicable ASB.  Repair or replace any unserviceable support, transmission case, stud, or dowel pin before further flight.

(ii)   If less than two upper nuts rotate at a torque less than 40 inch-pounds or less than two lower nuts rotate at a torque of less than 90 inch pounds, before further flight, re-torque the upper nut to 50 to 70 inch-pounds plus tare and the lower nut to 100 to 140 inch-pounds plus tare.

2.    After re-installing a support for any reason, verify the torque of the nuts in accordance with Requirement 1.

Note:  Transport Canada ADCF-2000-29 and FAA AD 2001-01-51 refer.

Compliance:

1.    Unless the initial inspection is already accomplished, within 25 hours time in service after 30 August 2007.  Thereafter at intervals not to exceed 600 hours time in service or 12 months, whichever occurs first.

2.    At not less than 20 hours time in service, nor more than 30 hours time in service.

The compliance time for Requirement 2 remains unchanged by this issue of the Directive.

This Amendment becomes effective on 30 August 2007.

Background:

The FAA received a report of the failure of a main rotor hydraulic actuator support, resulting in an accident of a Model 222U helicopter.

Amendment 1 is issued to include the Model 230 helicopter in applicability.

David Villiers
Delegate of the Civil Aviation Safety Authority

11 July 2007