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AD/S-92/5 - Tail Rotor Pitch Change Bearing Assembly
Sikorsky S-92 Series HelicoptersSikorsky S-92 Series Helicopters
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Sikorsky S-92 Series Helicopters
| AD/S-92/5 | Tail Rotor Pitch Change Bearing Assembly | 11/2007 TX |
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| Applicability: | Model S-92A helicopter, with a tail rotor pitch change shaft and bearing assembly (shaft and bearing assembly) part number 92358- 06303-041, installed. |
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| Requirement: | 1. Borescope inspect as follows:a) Inspect each affected shaft and bearing assembly at tail rotor side by following the Accomplishment Instructions, paragraphs 3.A.(1) through (7) and Figure 4 of Sikorsky Aircraft Corporation Alert Service Bulletin (ASB) No. 92-64-002, dated 3 August 2007.b) Inspect each shaft and bearing assembly on the servo side through the oil filler cap by following the Accomplishment Instructions, paragraphs B.(1) through (9) and Figures 2 and 3, of the ASB.Note 1: Maintenance Manual SA S92A-ANM-000 pertains to the subject of this AD.2. Carry out the inspections detailed in Requirement 1 of this AD.3. If the shaft bearing fails the inspection, as detailed in Requirement 1 of this AD, replace the shaft and bearing assembly.Note 2: FAA AD 2007-17-05 Amdt 39-15163 dated 9 August 2007 refers. |
| Compliance: | 1. Within 20 hours time-in-service (TIS) after the effective date of this AD, unless previously accomplished.2. Between 10 and 15 hours TIS after installing a shaft and bearing assembly.3. Before further flight after the effective date of this AD. |
| This Airworthiness Directive becomes effective on 30 August 2007. |
| Background: | This AD requires, within a specified time, borescope inspecting a certain part-numbered tail rotor pitch change shaft and bearing assembly (shaft and bearing assembly) and also inspecting after any installation. This AD is prompted by an incident involving failure of a shaft and bearing assembly and servo clevis shaft resulting in loss of tail rotor control. The actions specified in this AD are intended to prevent failure of a shaft and bearing assembly, loss of tail rotor pitch and yaw control, and subsequent loss of control of a helicopter. |
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Charles Lenarcic
Delegate of the Civil Aviation Safety Authority
27 August 2007