[Federal Register Volume 66, Number 229 (Wednesday, November 28, 2001)]
[Proposed Rules]
[Pages 59374-59375]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-29593]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 66, No. 229 / Wednesday, November 28, 2001 / 
Proposed Rules  

[[Page 59374]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-37-AD]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron, Inc. Model 
205A, 205A-1, 205B, 212, 412, 412EP, and 412CF Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 205A, 
205A-1, 205B, 212, 412, 412EP, and 412CF helicopters. The AD would 
require inspecting each affected tail rotor blade forward tip weight 
retention block (tip block) and the aft tip closure (tip closure) for 
adhesive bond voids and removing any tail rotor blade with an excessive 
void from service. The AD would also require modifying certain tail 
rotor blades by installing shear pins and tip closure rivets. This 
proposal is prompted by five occurrences of missing tip blocks or tip 
closures resulting in minor to substantial damage. The actions 
specified by the proposed AD are intended to prevent loss of a tip 
block or tip closure, loss of a tail rotor blade, and subsequent loss 
of control of the helicopter.

DATES: Comments must be received on or before January 28, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-37-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: [email protected]. 
Comments may be inspected at the Office of the Regional Counsel between 
9 a.m. and 3 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office, 
Fort Worth, Texas 76193-0170, telephone (817) 222-5447, fax (817) 222-
5783.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments will 
be considered before taking action on the proposed rule. The proposals 
contained in this document may be changed in light of the comments 
received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this proposal must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2001-SW-37-AD.'' The postcard will be date 
stamped and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-37-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.

Discussion

    This document proposes the adoption of a new AD for BHTI Model 
205A, 205A-1, 205B, 212, 412, 412EP, and 412CF helicopters, with a tail 
rotor blade, part number (P/N) 212-010-750-009, -011, -105, -107, -109, 
or -111, having a serial number (S/N) prefix ATR or A3, or a S/N with a 
prefix A and a number less than or equal to 11529. The AD would require 
inspecting the tip block and the tip closure for adhesive bonding voids 
and removing any tail rotor blade with an excessive void from service. 
The AD would also require modifying certain tail rotor blades by 
installing shear pins and tip closure rivets in the tip area of 
affected tail rotor blades. This proposal is prompted by five 
occurrences of missing tip blocks and tip closures resulting in minor 
to substantial damage. This condition, if not corrected, could result 
in loss of the tip block or tip closure, loss of the tail rotor blade, 
and subsequent loss of control of the helicopter.
    The FAA has reviewed BHTI Service Bulletins 205-00-80, 205B-00-34, 
212-00-111, 412-00-106, and 412CF-00-13, all Revision A, all dated 
December 20, 2000. The service bulletins describe procedures for 
inspecting and modifying certain tail rotor blades and were issued as a 
result of an investigation of an in-flight loss of a tail rotor blade 
tip block, P/N 212-010-750-105. The investigation revealed that the 
countersunk screws retaining the tip block were installed incorrectly, 
resulting in inadequate tip block retention. Also, reports have been 
submitted about loss of the tail rotor tip closures possibly due to an 
inadequate adhesive bond in this area.
    We have identified an unsafe condition that is likely to exist or 
develop on other BHTI Model 205A, 205A-1, 205B, 212, 412, 412EP, and 
412CF helicopters of the same type design. Therefore, the proposed AD 
would require the following:
     Inspecting certain tail rotor blades' tip block and tip 
closure for voids.
     Removing any tail rotor blade that has a void in excess of 
specified limitations.
     Modifying certain tail rotor blades by installing shear 
pins.
     Modifying all affected S/N tail rotor blades by installing 
aft tip closure rivets.
    The actions would be required to be accomplished in accordance with 
the service bulletins described previously.
    The FAA estimates that 281 helicopters of U.S. registry would be 
affected by this proposed AD, that it

[[Page 59375]]

would take approximately 3 work hours per helicopter to inspect certain 
tail rotor blades and to install the shear pins and tip closure rivets, 
and that the average labor rate is $60 per work hour. Required parts 
would cost approximately $25 per helicopter. Based on these figures, 
the total cost impact of the proposed AD on U.S. operators is estimated 
to be $57,605.
    The regulations proposed herein would not have a substantial direct 
effect on the States, on the relationship between the national 
Government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, will not have a significant economic impact, 
positive or negative, on a substantial number of small entities under 
the criteria of the Regulatory Flexibility Act. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 14 
CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

Bell Helicopter Textron, Inc.: Docket No. 2001-SW-37-AD.

    Applicability: Model 205A, 205A-1, 205B, 212, 412, 412EP, and 
412CF helicopters with a tail rotor blade, part number 212-010-750-
009, -011, -105, -107, -109, or -111, having a serial number (S/N) 
prefix ATR or A3, or a S/N with a prefix A and a number less than or 
equal to 11529, installed, certificated in any category.

    Note 1: This AD applies to each helicopter identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. For helicopters that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (d) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Within 100 hours time-in-service, unless 
accomplished previously.
    To prevent loss of the forward tip weight retention block (tip 
block) or aft tip closure (tip closure), loss of the tail rotor 
blade, and subsequent loss of control of the helicopter, accomplish 
the following:
    (a) Inspect the tip block and tip closure for voids. Remove from 
service any tail rotor blade with a void in excess of that allowed 
by the Component Repair and Overhaul Manual limitations.
    (b) Inspect the tip block attachment countersink screws in four 
locations to determine if the head of each countersunk screw is 
flush with the surface of the abrasion strip. The locations of these 
four screws are depicted on Figure 1 of Bell Helicopter Textron, 
Inc. Alert Service Bulletin 205-00-80, 205B-00-34, 212-00-111, 412-
00-106, and 412CF-00-13, all Revision A, all dated December 20, 2000 
(ASB). If any of these screws are set below the surface of the 
abrasion strip or are covered with filler material, install shear 
pins in accordance with the Accomplishment Instructions, Shear Pin 
Installation paragraphs, of the applicable ASB.
    (c) Install the aft tip closure rivets on all affected tail 
rotor blades in accordance with the Accomplishment Instructions, Aft 
Tip Closure Rivet Installation paragraphs, of the applicable ASB.
    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Rotorcraft Certification Office, 
Rotorcraft Directorate, FAA. Operators shall submit their requests 
through an FAA Principal Maintenance Inspector, who may concur or 
comment and then send it to the Manager, Rotorcraft Certification 
Office.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Certification Office.

    (e) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the requirements of this AD can be accomplished.

    Issued in Fort Worth, Texas, on November 20, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-29593 Filed 11-27-01; 8:45 am]
BILLING CODE 4910-13-P