Airworthiness Directive · Amendment 39-19651 · Tail rotor control system
Bell Helicopter Textron Canada Limited Helicopters
Superseded. A later AD replaced this one: AD 2022-09-07. Comply with the one in force.
This AD applies to Bell Helicopter Textron Canada Limited Model 429 helicopters, certificated in any category, with a pitch link assembly part number (P/N) 429-012-112-101, 429-012-112-103, 429-012-112-101FM, or 429-012-112-103FM installed.
We are superseding Airworthiness Directive (AD) 2015-22-02 for certain Bell Helicopter Textron Canada Limited (Bell) Model 429 helicopters. AD 2015-22-02 required inspecting the tail rotor (TR) pitch link assemblies. This AD retains the inspections of AD 2015-22-02 and requires replacing certain pitch link bearings. This AD was prompted by a new design bearing introduced by Bell. We are issuing this AD to address the unsafe condition on these products.
You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(1) Within 50 hours time-in-service (TIS) and thereafter at intervals not to exceed 50 hours TIS:
(i) Perform a dimensional inspection of each inboard and outboard pitch link assembly for axial and radial bearing play. With a 10X or higher power magnifying glass, inspect the bearing liner for a crack, deterioration of the liner, and extrusion of the liner from the plane. If there is axial or radial play that exceeds allowable limits, or if there is a crack, deterioration of the liner, or extrusion of the liner, before further flight, replace the bearing.
(ii) Inspect the pitch link assembly sealant for pin holes and voids and to determine if the sealant thickness is 0.025 inch (0.64 mm) or less, extends over the roll staked lip by 0.030 inch (0.76 mm) or more, and is clear of the bearing ball. If there is a pin hole or void, or if the sealant exceeds 0.026 inch (0.66 mm), does not extend over the roll staked lip by 0.030 inch (0.76 mm) or more, or is not clear of the bearing ball, before further flight, replace the bearing.
(2) For pitch link assembly part number (P/N) 429-012-112-101, 429-012-112-103, 429-012-112-101FM, and 429-012-112-103FM, within 200 hours TIS following the initial inspection required by paragraph (f)(1) of this AD, or if the hours TIS of a pitch link assembly exceed 250 hours TIS or are unknown, at the next 50-hour-TIS inspection required by paragraph (f)(1) of this AD:
(i) Replace each bearing P/N 429-312-107-103 with a date of manufacture before January 13, 2015, with a bearing P/N 429-312-107-103 that was manufactured on or after January 13, 2015.
(ii) Using a white permanent fine point marker or equivalent, re-identify the pitch link assembly:
(A) Re-identify P/N 429-012-112-101 and 429-012-112-101FM as 429-012-112-111FM.
(B) Re-identify P/N 429-012-112-103 and 429-012-112-103FM as 429-012-112-113FM.
(iii) Apply a coating of DEVCON 2-TON (C-298) or equivalent over the new P/N.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
