[Federal Register Volume 60, Number 211 (Wednesday, November 1, 1995)]
[Proposed Rules]
[Pages 55495-55496]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-27000]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-SW-26-AD]
Airworthiness Directives; Bell Helicopter Textron, Inc. Model
214ST 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) that is applicable to Bell Helicopter Textron, Inc.
(BHTI) Model 214ST helicopters with certain tailboom assemblies and a
certain emergency float kit installed. This proposal would require
initial and repetitive inspections of the tailboom for cracks until
modifications of the tailboom are accomplished. This proposal is
prompted by several reports of cracks in the lower aft skin of the
tailboom assembly. The actions specified by the proposed AD are
intended to prevent cracks in the tailboom assembly, which could result
in structural failure of the tailboom and subsequent loss of control of
the helicopter.
DATES: Comments must be received by January 2, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Assistant Chief Counsel, Attention:
Rules Docket No. 95-SW-26-AD, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137. Comments may be inspected at this location between 9:00
a.m. and 3:00 p.m., Monday through Friday, except Federal holidays.
The service information referenced in the proposed rule may be
obtained from Bell Helicopter Textron, Inc., Attention: Customer
Support, P.O. Box 482, Fort Worth, Texas 76101. This information may be
examined at the FAA, Office of the Assistant Chief Counsel, 2601
Meacham Blvd., Room 663, Fort Worth, Texas.
FOR FURTHER INFORMATION CONTACT: Mr. Tom Henry, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Certification Office, 2601
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5158, fax
(817) 222-5959.
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,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice 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 comments
submitted in response to this notice must submit a self addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 95-SW-26-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 Assistant Chief Counsel, Attention: Rules
Docket No. 95-SW-26-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.
Discussion
This document proposes to adopt a new AD that is applicable to BHTI
Model 214ST helicopters, serial number (S/N) 28101 through 28132, with
a tailboom assembly, part number (P/N) 214-031-003-111 or 214-031-003-
277, and with an emergency float kit, P/N 214-706-120, installed. There
have been reports of cracks found in five Model 214ST helicopter
tailbooms with the emergency float kit installed. The cracks were found
in the lower aft skin between boom stations 243.76 and 284.38. This
condition, if not corrected, could result in structural failure of the
tailboom and subsequent loss of control of the aircraft.
The FAA has reviewed Bell Helicopter Textron, Inc. Alert Service
Bulletin 214ST-95-72 (ASB), dated July 24, 1995, which describes
procedures for a visual inspection of the affected tailboom area of
Model 214ST helicopters with emergency float kits installed. The ASB
also describes a modification to the helicopters that adds internal
stiffeners and doublers to the tailboom, and replaces the existing
access door frame, P/N 214-030-325, with a redesigned frame of
increased thickness.
Since an unsafe condition has been identified that is likely to
exist or develop on certain other BHTI Model 214ST helicopters of the
same type design, the proposed AD would require, for Model 214ST
helicopters, S/N 28101 through 28132, with a tailboom assembly, P/N
214-031-003-111 or 214-031-003-277, and with an emergency float kit, P/
N 214-706-120, installed, inspections of the tailboom assembly for
cracks within 250 hours time-in-service (TIS) or at the next 180-day
float inspection, and thereafter, at each 180-day float inspection
until certain modifications of the tailboom are accomplished. The
modifications, which are to be accomplished if any crack is found in
the tailboom or on or before accumulating an additional 500 hours TIS
after the effective date of this AD, whichever occurs first, include
installing stiffeners and doublers in the tailboom, and replacing the
access door frame with a thicker access door frame. The actions would
be required to be accomplished in accordance with the procedures
contained in BHTI Alert Service Bulletin (ASB) 214ST-95-72, dated July
24, 1995.
The FAA estimates that six helicopters of U.S. registry would be
affected by this proposed AD, that it would take approximately 20 work
[[Page 55496]]
hours per helicopter to accomplish the modifications, approximately 3
work hours per helicopter to accomplish the 250 hours TIS inspection,
and that the average labor rate is $60 per work hour. Required parts
would cost approximately $1,100 per helicopter. Based on these figures,
the total cost impact of the proposed AD on U.S. operators is estimated
to be $14,880.
The regulations proposed herein would not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
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
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 USC 106(g), 40101, 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. (BHTI): Docket No. 95-SW-26-AD.
Applicability: Model 214ST helicopters, serial number (S/N)
28101 through 28132, with a tailboom assembly, part number (P/N)
214-031-003-111 or 214-031-003-277 and with an emergency float kit,
P/N 214-706-120, 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
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 use the authority
provided in paragraph (d) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition, or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any helicopter from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent cracks in the tailboom assembly, structural failure
of the tailboom and subsequent loss of control of the helicopter,
accomplish the following:
(a) Within the next 250 hours time-in-service (TIS) or at the
next 180-day float inspection, whichever occurs first, and
thereafter at intervals not to exceed each 180-day float inspection,
visually inspect the tailboom assembly for cracks in accordance with
the maintenance procedures contained in Part 1 of the Accomplishment
Instructions of BHTI Alert Service Bulletin 214ST-95-72, dated July
24, 1995.
(b) Upon discovery of a crack or on or before accumulating an
additional 500 hours TIS after the effective date of this AD,
whichever occurs first, modify the tailboom assembly in accordance
with Part 2 of the Accomplishment Instructions of BHTI Alert Service
Bulletin No. 214ST-95-72, dated July 24, 1995.
(c) Modification of the tailboom assembly in accordance with
paragraph (b) constitutes terminating action for the requirements of
this AD.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used when approved by the Manager, Rotorcraft Certification Office.
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
sections 21.197 and 21.199 of the Federal Aviation Regulations (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 October 23, 1995.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 95-27000 Filed 10-31-95; 8:45 am]
BILLING CODE 4910-13-U
