[Federal Register Volume 63, Number 164 (Tuesday, August 25, 1998)]
[Rules and Regulations]
[Pages 45169-45170]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-22698]



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 Rules and Regulations
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  Federal Register / Vol. 63, No. 164 / Tuesday, August 25, 1998 / 
Rules and Regulations  

[[Page 45169]]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-SW-29-AD; Amendment 39-10717; AD 98-18-01]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron, Inc. Model 
214B, 214B-1, and 214ST Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 214B, 
214B-1, and 214ST helicopters, that currently establishes a retirement 
life of 60,000 high-power events for the main rotor trunnion 
(trunnion). This amendment requires changing the method of calculating 
the retirement life for the trunnion from high-power events to a 
maximum accumulated Retirement Index Number (RIN). This amendment is 
prompted by fatigue analyses and tests that show certain trunnions fail 
sooner than originally anticipated because of the unanticipated higher 
number of lifts or takeoffs (torque events) performed with those 
trunnions. The actions specified by this AD are intended to prevent 
fatigue failure of the trunnion, which could result in loss of the main 
rotor and subsequent loss of control of the helicopter.

EFFECTIVE DATE: September 29, 1998.

FOR FURTHER INFORMATION CONTACT: Mr. Harry Edmiston, Aerospace 
Engineer, FAA, Rotorcraft Certification Office, Rotorcraft Directorate, 
Fort Worth, Texas 76193-0170, telephone (817) 222-5158, fax (817) 222-
5959.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 94-15-14, 
Amendment 39-8985 (59 FR 40798, August 10, 1994), which is applicable 
to BHTI Model 214B, 214B-1, and 214ST helicopters, was published in the 
Federal Register on December 12, 1996 (61 FR 65367). That action 
proposed to require creation of a component history card using the RIN 
system; a system for tracking increases to the accumulated RIN; and 
proposed to establish a maximum accumulated RIN for the trunnion of 
120,000 at which time the trunnion must be removed from service.
    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 one non-substantive change. The model 214B-1 
has been added to paragraph (b)(1) of the AD to explicitly state that 
the accumulated RIN is calculated the same for both Model 214B and 
214B-1 helicopters. The FAA has determined that this change will 
neither increase the economic burden on any operator nor increase the 
scope of the AD.
    The FAA estimates that 8 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately (1) 10 work hours 
to replace the affected trunnion 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); and (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 $11,000 per helicopter. Based on 
these figures, the total cost impact of the AD on U.S. operators is 
estimated to be $17,360 for the first year and $16,520 for each 
subsequent year. These costs assume replacement of the trunnion in one 
helicopter each year, creation and maintenance of the records for all 
the fleet the first year, and creation of one helicopter'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 FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

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 removing Amendment 39-8985 (59 FR 
40798, August 10, 1994), and by adding a new airworthiness directive 
(AD), Amendment 39-10717 to read as follows:
AD 98-18-01  Bell Helicopter Textron, Inc. (BHTI): Amendment 39-
10717. Docket No. 94-SW-29-AD. Supersedes AD 94-15-14, Amendment 39-
8985, Docket No. 93-SW-20-AD.

    Applicability: Model 214B, 214B-1, and 214ST helicopters, with 
main rotor trunnion (trunnion), part number (P/N) 214-010-230-101, 
installed, certificated in any category.


[[Page 45170]]


    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 trunnion, which could result 
in loss of the main rotor and subsequent loss of control of the 
helicopter, accomplish the following:
    (a) Create a component history card or an equivalent record for 
the trunnion, P/N 214-040-230-101.
    (b) Determine and record on a component history card or 
equivalent record the accumulated Retirement Index Number (RIN) to-
date on the trunnion by multiplying the accumulated high-power event 
total to-date by 2 or as follows:
    (1) For Model 214B and 214B-1, multiply the flight hour total 
to-date by 24 (round-up any resulting fraction to the next higher 
whole number); or
    (2) For Model 214ST, multiply the factored flight hour total to-
date by 24 (round-up any resulting fraction to the next higher whole 
number).

    Note 2: BHTI Alert Service Bulletin (ASB) No. 214-94-55, which 
is applicable to Model 214B and 214 B-1 helicopters, and ASB No. 
214ST-94-70, which is applicable to Model 214ST helicopters, both 
dated November 7, 1994, pertain to this AD.

    (c) After complying with paragraphs (a) and (b) of this AD, 
during each operation thereafter, maintain a count of the number and 
type of external load lifts and the number of takeoffs performed 
and, at the end of each day's operations, increase the accumulated 
RIN on the component history card as follows:
    (1) For the Model 214B and 214B-1 helicopters,
    (i) Increase the RIN by 1 for each takeoff.
    (ii) Increase the RIN by 1 for each external load lift 
operation, or increase the RIN by 2 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.
    (2) For the Model 214ST helicopters,
    (i) Increase the RIN by 2 for each takeoff.
    (ii) Increase the RIN by 2 for each external load lift 
operation, 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 trunnion, P/N 214-010-230-101, from service on or 
before attaining an accumulated RIN of 120,000. The trunnion is no 
longer retired based upon flight hours. This AD revises the 
Airworthiness Limitation section of the maintenance manual by 
establishing a new retirement life for the trunnion of 120,000 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 September 29, 1998.

    Issued in Fort Worth, Texas on August 17, 1998.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-22698 Filed 8-24-98; 8:45 am]
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