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Federal Register / Vol. 86, No. 236 / Monday, December 13, 2021 / Rules and Regulations
Canada Limited, 12,800 Rue de lAvenir, Mirabel, Quebec J7J 1R4, Canada;
telephone 14504372862 or 1800
3638023; fax 14504330272; email productsupport@bellflight.com; or at https www.bellflight.com/support/
contact-support. For STEC Corporation service information identified in this final rule, contact STEC Corporation, One STEC Way, Mineral Wells Municipal Airport, Mineral Wells, TX
76067; telephone 817 2157600. You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N321, Fort Worth, TX
76177. For information on the availability of this material at the FAA, call 812 2225110. Service information that is incorporated by reference is also available at https www.regulations.gov by searching for and locating Docket No.
FAA20211066.
Examining the AD Docket You may examine the AD docket at https www.regulations.gov by searching for and locating Docket No.
FAA20211066; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, any comments received, and other information. The street address for the Docket Operations is listed above.
Hye Yoon Jang, Aerospace Engineer, Delegation Oversight Section, DSCO
Branch, Compliance & Airworthiness Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817
2225190; email hye.yoon.jang@faa.gov.

FOR FURTHER INFORMATION CONTACT:

SUPPLEMENTARY INFORMATION:

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Background The FAA is adopting a new AD for certain serial-numbered Bell Textron Canada Limited Model 505 helicopters that have STEC Corporation HeliSAS
stability augmentation system and autopilot installed under Supplemental Type Certificate SR09758DS. The FAA
received a report that, during an inspection, chafing was discovered on the right forward T/R control cable due to contact with the autopilot yaw servo bracket, which is part of the HeliSAS
stability augmentation system.
Additional review revealed that the installation instructions did not include a minimum clearance limit between the right forward T/R control cable and the autopilot yaw servo bracket, which allowed the positioning of the autopilot yaw servo bracket such that it did not prevent contact and chafing. Since this discovery, STEC revised the
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installation instructions to specify a minimum cable clearance limit.
This condition, if not addressed, could result in failure of the right forward T/R control cable, loss of T/R
control, and subsequent loss of control of the helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
FAAs Determination The FAA is issuing this AD because the agency has determined the unsafe condition described previously is likely to exist or develop in other products of the same type design.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Bell Alert Service Bulletin 5052127, dated October 7, 2021 ASB. This ASB specifies inspecting the right forward T/R control cable in the area of the roller bracket assembly for any signs of contact and ensuring there is minimum clearance between the right forward T/R control cable and the roller bracket cut out.
Depending on the results, this ASB
specifies reporting information to Bell, replacing the cable assembly, and adjusting the height of the roller bracket assembly position.
This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in ADDRESSES.
Other Related Service Information The FAA reviewed STEC
Corporation Installation Instructions ST974II0001, Revision 2, dated October 6, 2021. This service information contains information necessary for installing a HeliSAS
stability augmentation system and autopilot, including information for adjusting the height of the roller bracket assembly position.
AD Requirements This AD requires inspecting the right forward T/R control cable in the area of the roller bracket assembly for any signs of chafing and, if there is any chafing, removing the cable assembly from service. This AD also requires measuring the clearance between the right forward T/R control cable and the roller bracket cut out and, depending on the results, adjusting the height of the roller bracket assembly position.
Differences Between This AD and the Service Information If there is chafing, the ASB specifies reporting certain information to Bell, whereas this AD does not.

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Justification for Immediate Adoption and Determination of the Effective Date Section 553b3B of the Administrative Procedure Act APA 5
U.S.C. 551 et seq. authorizes agencies to dispense with notice and comment procedures for rules when the agency, for good cause, finds that those procedures are impracticable, unnecessary, or contrary to the public interest. Under this section, an agency, upon finding good cause, may issue a final rule without providing notice and seeking comment prior to issuance.
Further, section 553d of the APA
authorizes agencies to make rules effective in less than thirty days, upon a finding of good cause.
An unsafe condition exists that requires the immediate adoption of this AD without providing an opportunity for public comments prior to adoption.
The FAA has found that the risk to the flying public justifies foregoing notice and comment prior to adoption of this rule because the affected components are part of an assembly that is critical to the control of a helicopter. In addition, chafing could lead to instantaneous failure before detection. As the FAA has no information pertaining to the extent of chafing of the right forward T/R
control cable that may currently exist in helicopters or how quickly the condition may propagate to failure, the actions required by this AD must be accomplished within 25 hours time-inservice or 30 days, whichever occurs first. This compliance time is shorter than the time necessary for the public to comment and for publication of the final rule. Accordingly, notice and opportunity for prior public comment are impracticable and contrary to the public interest pursuant to 5 U.S.C.
553b3B.
In addition, the FAA finds that good cause exists pursuant to 5 U.S.C. 553d for making this amendment effective in less than 30 days, for the same reasons the FAA found good cause to forego notice and comment.
Comments Invited The FAA invites you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under ADDRESSES.
Include Docket No. FAA20211066
and Project Identifier AD202101189
R at the beginning of your comments.
The most helpful comments reference a specific portion of the final rule, explain the reason for any recommended change, and include supporting data.
The FAA will consider all comments received by the closing date and may
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