AD Amdt-39-10108

[Federal Register Volume 62, Number 161 (Wednesday, August 20, 1997)]
[Rules and Regulations]
[Pages 44207-44208]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 97-22044]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-SW-27-AD; Amendment 39-10108; AD 97-17-06]
RIN 2120-AA64


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, that requires replacement of each emergency float 
inflation solenoid valve (valve). This amendment is prompted by two 
inadvertent inflations of emergency float systems that resulted from 
self-

[[Page 44208]]

 activations of the valves. The actions specified by this AD are 
intended to prevent self-activation of the valves, and subsequent 
inadvertent inflation of the emergency float system, which could lead 
to loss of control of the helicopter.

EFFECTIVE DATE: September 24, 1997.

FOR FURTHER INFORMATION CONTACT: Mr. Uday Garadi, Aerospace Engineer, 
FAA, Rotorcraft Certification Office, 2601 Meacham Blvd., Fort Worth, 
Texas 76137, telephone (817) 222-5157; fax (817) 222-5960.

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 Model 214ST helicopters, equipped 
with an emergency float kit, part number (P/N) 214-706-120, containing 
valves, P/N 214-073-929-103 or -105, in solenoid valve assemblies 
(valve assemblies), P/N 214-073-940-101 or -103, was published in the 
Federal Register on November 20, 1996 (61 FR 59033). That action 
proposed to require replacement of all existing valves, P/N 214-073-
929-103 and -105, in valve assemblies, P/N 214-073-940-101 and -103.
    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 9 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 2 work hours per 
helicopter to accomplish the required actions, and that the average 
labor rate is $60 per work hour. Required parts will cost approximately 
$2,100 per helicopter. Based on these figures, the total cost impact of 
the AD on U.S. operators is estimated to be $19,980.
    The regulations adopted herein will 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 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, 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 97-17-06  Bell Helicopter Textron, Inc.: Amendment 39-10108. 
Docket No. 96-SW-27-AD.

    Applicability: Model 214ST helicopters, equipped with an 
emergency float kit, part number (P/N) 214-706-120, containing 
emergency float inflation solenoid valves,
P/N 214-073-929-103 or -105, in solenoid valve assemblies, P/N 214-
073-940-101 or -103, 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 (c) 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 self-activation of the valves, and subsequent 
inadvertent inflation of the emergency float system, which could 
lead to loss of control of the helicopter, accomplish the following:
    (a) At the next scheduled ``B'' (250 hour) inspection, or 180-
day float inspection, or 3-year float system operational inspection, 
whichever occurs first, remove solenoid valves, P/N 214-073-929-103 
or -105, from solenoid valve assemblies, P/N 214-073-940-101 or -
103, and replace with solenoid valves, P/N 214-073-929-107.

    Note 2: Solenoid valve assemblies, P/N 214-073-940, consist of a 
valve, P/N 214-073-929 and a decal, P/N 31-023-8B. Solenoid valve 
assembly, P/N 214-073-940-105, contains solenoid valve, P/N 214-073-
929-107.

    (b) Installation of solenoid valves, P/N 214-073-929-107, or 
solenoid valve assemblies, P/N 214-073-940-105, constitutes 
terminating action for the requirements of this AD.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Certification Office.

    (c) 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.
    (d) 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.
    (e) This amendment becomes effective on September 24, 1997.

    Issued in Fort Worth, Texas, on August 13, 1997.
Larry M. Kelly,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 97-22044 Filed 8-19-97; 8:45 am]
BILLING CODE 4910-13-U