[Federal Register Volume 67, Number 86 (Friday, May 3, 2002)]
[Rules and Regulations]
[Pages 22349-22350]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-10650]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-37-AD; Amendment 39-12737; AD 2002-09-04]
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: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
Bell Helicopter Textron, Inc. (BHTI) Model 205A, 205A-1, 205B, 212, 
412, 412EP, and 412CF helicopters, that requires 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. 
This AD also requires modifying certain tail rotor blades by installing 
shear pins and tip closure rivets. This amendment is prompted by five 
occurrences of missing tip blocks or tip closures resulting in minor to 
substantial damage. The actions specified by this 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: Effective June 7, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 7, 2002.

ADDRESSES: The service information referenced in this AD may be 
obtained from Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, 
Texas 76101, telephone (817) 280-3391, fax (817) 280-6466. This 
information may be examined at the FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or 
at the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

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: A proposal to amend 14 CFR part 39 to 
include an AD for BHTI Model 205A, 205A-1, 205B, 212, 412, 412EP, and 
412CF helicopters was published in the Federal Register on November 28, 
2001 (66 FR 59374). That action proposed to 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. It also proposed 
to require modifying certain tail rotor blades by installing shear pins 
and tip closure rivets in the tip area of affected tail rotor blades.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.
    The FAA estimates that 281 helicopters of U.S. registry will be 
affected by this AD, that it will 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 will cost approximately $25 per 
helicopter. Based on these figures, the total cost impact of the AD on 
U.S. operators is estimated to be $57,605.
    The regulations adopted herein will 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 final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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:

2002-09-04  Bell Helicopter Textron, Inc.: Amendment 39-12737. 
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.


[[Page 22350]]


    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 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 
(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.
    (f) The inspection, removal, and modification shall be done in 
accordance with Bell Helicopter Textron, Inc. Alert 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. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Bell Helicopter Textron, Inc., P.O. 
Box 482, Fort Worth, Texas 76101, telephone (817) 280-3391, fax 
(817) 280-6466. Copies may be inspected at the FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.
    (g) This amendment becomes effective on June 7, 2002.

    Issued in Fort Worth, Texas, on April 22, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-10650 Filed 5-2-02; 8:45 am]
BILLING CODE 4910-13-P