[Federal Register Volume 62, Number 176 (Thursday, September 11, 1997)]
[Rules and Regulations]
[Pages 47754-47755]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-24117]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-SW-28-AD; Amendment 39-10129; AD 97-19-09]
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 creation of a component history card or 
equivalent record using a Retirement Index Number (RIN) system; 
establishes a system for tracking increases to the accumulated RIN; and 
establishes a maximum accumulated RIN for the pillow block bearing 
bolts (bearing bolts). This amendment is prompted by fatigue analyses 
and tests that show certain bearing bolts fail sooner than originally 
anticipated because of the unanticipated high number of takeoffs and 
external load lifts utilizing high-power settings in addition to the 
time-in-service (TIS) accrued under other operating conditions. The 
actions specified by this AD are intended to prevent fatigue failure of 
the bearing bolts, which could result in failure of the main rotor 
system and subsequent loss of control of the helicopter.

EFFECTIVE DATE: October 16, 1997.

FOR FURTHER INFORMATION CONTACT: Mr. Charles Harrison, Aerospace 
Engineer, FAA, Rotorcraft Certification Office, Rotorcraft Directorate, 
Fort Worth, Texas 76193-0170, 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 was 
published in the Federal Register on December 23, 1996 (61 FR 67503). 
That action proposed to require creation of a component history

[[Page 47755]]

card using a RIN system; establishing a system for tracking increases 
to the accumulated RIN; and establishing a maximum accumulated RIN for 
the bearing bolts.
    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 with three non-substantive changes. The words 
``based on condition'' were deleted from paragraph (d) of the AD. If 
any of the four bearing bolts are replaced for any reason, all four 
bearing bolts must be replaced. The words ``or equivalent record'' are 
added to paragraphs (b) and (c). The FAA has determined that these 
changes will neither increase the economic burden on any operator nor 
increase the scope of the AD.
    The FAA estimates that 6 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately (1) 24 work hours 
per helicopter to replace the affected bearing bolts due to the new 
method of determining the retirement life required by this AD; (2) 2 
work hours per helicopter to create the component history card or 
equivalent record (record); (3) 10 work hours per helicopter to 
maintain the record each year, and that the average labor rate is $60 
per work hour. Required parts will cost approximately $2,000 per 
helicopter. Based on these figures, the total cost impact of the AD on 
U.S. operators for the first year is estimated to be $7,760 and each 
subsequent year to be $7,160. These costs assume replacement of the 
bearing bolts in one-sixth of the fleet each year, creation and 
maintenance of the records for all the fleet the first year, and 
creation of one-sixth of the fleet's records and maintenance of the 
records for all the fleet each subsequent year.
    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:

97-19-09 Bell Helicopter Textron Inc.: Amendment 39-10129. Docket 
No. 94-SW-28-AD.

    Applicability: All Model 214ST helicopters with pillow block 
bearing bolts (bearing bolts), part number (P/N) 20-057-12-48D or -
50D, 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 (e) 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 within 25 hours time-in-service (TIS) after 
the effective date of this AD, unless accomplished previously.
    To prevent fatigue failure of the bearing bolts, which could 
result in failure of the main rotor system and subsequent loss of 
control of the helicopter, accomplish the following:
    (a) Create a component history card or an equivalent record for 
the bearing bolts, P/N 20-057-12-48D or -50D.
    (b) To determine the accumulated Retirement Index Number (RIN) 
to date on parts in service, multiply the factored flight hour total 
to date by 13.6 (round-off the result to the next higher whole 
number). Record on the component history card or equivalent record 
the accumulated RIN.

    Note 2: Bell Helicopter Textron, Inc. Alert Service Bulletin 
214ST-94-69, dated November 7, 1994, pertains to this AD.

    (c) After compliance with paragraphs (a) and (b) of this AD, 
during each operation thereafter, maintain a count of each takeoff 
and external load lift performed, and at the end of each day's 
operations, increase the accumulated RIN on the component history 
cards or equivalent record as follows:
    (1) Increase the RIN by 2 for each takeoff.
    (2) Increase the RIN by 2 for each external load lift, or 
increase the RIN by 4 for each external load lift operation in which 
the load is picked up at a higher elevation and released at a lower 
elevation, and the difference in elevation between the pickup point 
and the release point is 200 feet or greater.
    (d) Remove the bearing bolts from service on or before attaining 
an accumulated RIN of 17,000. If any of the four bearing bolts are 
replaced, then all four bolts must be replaced at that time. The 
bolts are no longer retired based upon flight hours. This AD revises 
the Airworthiness Limitations section of the maintenance manual by 
establishing a new retirement life for the bearing bolts of 17,000 
RIN.
    (e) 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, 
FAA, Rotorcraft Directorate. 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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Certification Office.

    (f) 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.
    (g) This amendment becomes effective on October 16, 1997.

    Issued in Fort Worth, Texas, on September 5, 1997.
Larry M. Kelly,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 97-24117 Filed 9-10-97; 8:45 am]
BILLING CODE 4910-13-P