FAA orders · airworthiness directive · current

2006-13-14: Tail rotor counterweight bellcrank (bellcrank)

FAA order 2006-13-14 is an airworthiness directive in force since July 11, 2006. The FAA's subject line: Tail rotor counterweight bellcrank (bellcrank). It names Bell 222, Bell 230, Bell 430: about 64 aircraft on the U.S. register today across them, though an order usually covers particular versions or serial numbers rather than every one. System: rotorcraft systems.

What it applies to as the FAA lists it

Kind of product: Aircraft
Makes: Bell Helicopter Textron, A Division of Textron Canada
Models: 222, 222B, 222U, 230, 430
On this site: Bell 222 21 registered
Bell 230 13 registered
Bell 430 30 registered

Dates and paperwork

In force since: July 11, 2006
Published: June 26, 2006 (signed June 16, 2006)
Docket: FAA-2006-25098
Status: Current
The FAA's document: Read the order on the FAA's site

The FAA's summary their words, unchanged

This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (BHTC) model helicopters. This action requires initial and repetitive inspections of each tail rotor counterweight bellcrank (bellcrank) with a specified part number and serial number. If external damage, a crack, roughness, or looseness between the bearing set and bellcrank is found or if bearing set axial play exceeds 0.015 inch, this action requires replacing the bellcrank with an airworthy bellcrank with two prefix letters in the serial number. This amendment is prompted by reports of failure and subsequent loss of a weighted portion of the bellcrank and reports of certain replacement bellcranks having design flaws. The actions specified in this AD are intended to prevent bellcrank failure, loss of a weighted portion of the bellcrank, and subsequent loss of control of the helicopter.

The order itself the regulatory text, as published

Show the full text (2,512 characters)

2006-13-14 Bell Helicopter Textron Canada: Amendment 39-14667. Docket No. FAA-2006-25098; Directorate Identifier 2006-SW-12-AD. 

Applicability 

	Models 222, serial number (S/N) 47006 through 47089; 222B, S/N 47131 through 47156; 222U, S/N 47501 through 47574; 230, S/N 23001 through 23038; and 430, S/N 49001 through 49105, with tail rotor counterweight bellcrank (bellcrank), part number (P/N) 222-012-727- 003 or 222-012-727-105, without two prefix letters in the serial number, installed, certificated in any category. 

Compliance 

	Required as indicated. 

	To prevent bellcrank failure, loss of a weighted portion of the bellcrank, and subsequent loss of control of the helicopter, accomplish the following: 

	(a) Within the next 10 hours time-in-service (TIS), unless done previously, and at intervals not to exceed 50 hours TIS: 
	(1) Inspect each bellcrank for external damage, cracking, looseness, or bearing set roughness by rotating the bellcrank while applying a loadto the bearing set in both axial and radial directions. 

	(2) If a bellcrank has external damage, cracking, roughness, looseness between the bearing set and bellcrank or bearing set axial play exceeding 0.015 inch, before further flight, replace it with bellcrank, P/N 222-012-727-105, with two prefix letters in the part serial number. 

	Note 1: The following Bell Helicopter Textron Canada Alert Service Bulletins pertain to the subject of this AD: Nos. 222-04-99, 222U-04-70, 230-04-30, and 430-04-30, all Revision C, all dated February 16, 2006; and Nos. 222-04-101, 222U-04-72, 230-04-32, and 430-04-32, all Revision B, all dated March 15, 2006. 

	(b) Replacing each bellcrank, P/N 222-012-727-003 and P/N 222- 012-727-105, without two prefix letters in the part serial number, with a bellcrank, P/N 222-012-727-105, with two prefix letters in the part serial number, is terminating action for the inspection requirements of this AD. 

	(c) To request a different method of complianceor a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Rotorcraft Directorate, Regulations and Guidance Group, FAA, ATTN: Sharon Miles, Aviation Safety Engineer, Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-5961, for information about previously approved alternative methods of compliance. 

	(d) This amendment becomes effective on July 11, 2006. 

	Note 2: The subject of this AD is addressed in Transport Canada (Canada) AD CF-2005-27R1, dated March 15, 2006.

Related safety bulletins advice on the same designs, not orders

2003-03-20SW-03-32 ·

Source: FAA Dynamic Regulatory System, airworthiness directives. The FAA's document is the authority; the register counts are this site's, from the FAA register of October 27, 2026. Connections as data: /graph/directive/2006-13-14.json · aircraft systems.