[Federal Register Volume 61, Number 67 (Friday, April 5, 1996)]
[Rules and Regulations]
[Pages 15184-15185]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-8384]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-SW-26-AD; Amendment 39-9561; AD 96-07-12]
Airworthiness Directives; Bell Helicopter Textron, Inc., Model
214ST Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to Bell Helicopter Textron, Inc. (BHTI) Model 214ST
helicopters with certain tailboom assemblies and a certain emergency
float kit installed, that requires initial and repetitive inspections
of the tailboom for cracks until modifications of the tailboom are
accomplished. This amendment is prompted by several reports of cracks
in the lower aft skin of the tailboom assembly. The actions specified
by this 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: Effective May 10, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 10, 1996.
ADDRESSES: The service information referenced in this AD 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; or at the Office of the
Federal Register, 800 North Capitol Street NW., suite 700, Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Mr. Charles Harrison, Aerospace
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5447,
fax (817) 222-5959.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to BHTI Model 214ST helicopters,
serial numbers (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, was published in the
Federal Register on November 1, 1995 (60 FR 55495). That action
proposed to require 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.
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 six helicopters of U.S. registry will be
affected by this AD, that it will take approximately 20 work 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 will cost
approximately $1,100 per helicopter. Based on these figures, the total
cost impact of the AD on U.S. operators is estimated to be $14,880.
The regulations adopted herein will not have substantial direct
effects on the
[[Page 15185]]
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 final rule does not have
sufficient federalism implications to warrant the preparation of a
Federalism Assessment.
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:
AD 96-07-12 Bell Helicopter Textron, Inc. (BHTI): Amendment 39-
9561. 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 methods 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.
(f) The inspections and modifications shall be done in
accordance with Bell Helicopter Textron, Inc. Alert Service Bulletin
214ST-95-72, dated July 24, 1995. 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., Attention: Customer Support, P.O. Box
482, Fort Worth, Texas 76101. Copies may be inspected at the FAA,
Office of the Assistant Chief Counsel, 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 May 10, 1996.
Issued in Fort Worth, Texas, on March 26, 1996.
Larry M. Kelly,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 96-8384 Filed 4-4-96; 8:45 am]
BILLING CODE 4910-13-M
