[Federal Register Volume 62, Number 135 (Tuesday, July 15, 1997)]
[Rules and Regulations]
[Pages 37710-37711]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-18499]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-SW-26-AD; Amendment 39-10077; AD 97-15-04]
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 mandatory 
retirement life of 60,000 high-power events for the main transmission 
upper planetary carrier (carrier). This amendment requires changing the 
method of calculating retirement life for the carrier from high-power 
events to a maximum accumulated Retirement Index Number (RIN) of 
120,000. This amendment is prompted by fatigue analyses and tests that 
show certain carriers fail sooner than originally anticipated because 
of the unanticipated high number of lifts or takeoffs (torque events) 
performed with those carriers 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 carrier, which could 
result in failure of the main transmission and subsequent loss of 
control of the helicopter.

EFFECTIVE DATE: August 19, 1997.

ADDRESSES: The service information referenced in Note 2 of this AD may 
be obtained from Bell Helicopter Textron, Inc., P.O. Box 482, Fort 
Worth, Texas 76101.

FOR FURTHER INFORMATION CONTACT: Mr. Uday Garadi, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Certification Office, Fort 
Worth, Texas 76193-0170, telephone (817) 222-5157, fax (817) 222-5959.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 94-02-05, 
Amendment 39-8803 (59 FR 32325, June 23, 1994), which is applicable to 
BHTI Model 214B, 214B-1, and 214ST helicopters, was published in the 
Federal Register on January 14, 1997 (62 FR 1864). That action proposed 
to require creation of a component history card or equivalent record 
using the RIN system and a system for tracking increases to the 
accumulated RIN, and proposed to establish a retirement life of a 
maximum of 120,000 accumulated RIN for the carrier.
    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, with one editorial change. The 
ADDRESSES paragraph in the preamble has been changed to clarify that 
the service bulletin is not incorporated into the AD, but is mentioned 
in Note 2 for information only. 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 11 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately (1) 48 work hours 
per helicopter to replace the affected part 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 $29,516 per helicopter. Based on 
these figures, the total cost impact of the AD on U.S. operators is 
estimated to be $61,813 for the first year and $60,713 for each 
subsequent year. These costs assume replacement by the carrier of 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 removing Amendment 39-8803 (59 FR 
32325, June 23, 1994), and by adding a new airworthiness directive 
(AD), Amendment 39-10077, to read as follows:

AD 97-15-04  Bell Helicopter Textron, Inc. (BHTI): Amendment 39-
10077 Docket No. 94-SW-26-AD. Supersedes AD 94-02-05, Amendment 39-
8803.

    Applicability: Model 214B, 214B-1, and 214ST helicopters with 
main transmission upper planetary carrier (carrier), part number (P/
N) 214-040-077-007 or -101, 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

[[Page 37711]]

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 carrier, which could result in 
failure of the main transmission and subsequent loss of control of 
the helicopter, accomplish the following:
    (a) Create a component history card or equivalent record for the 
carrier, P/N 214-040-077-007 or -101.
    (b) Determine and record the accumulated Retirement Index Number 
(RIN) to date on the carrier as follows (if the multiplication 
results in a fraction, round the results up to the next whole 
number):
    (1) For Model 214B or B-1 helicopters:
    (i) Multiply the high-power event total to date by 2, or
    (ii) If the actual operating hours are known, and:
    (A) If the type of operation is internal load lift operations 
only, multiply each operating hour by 7;
    (B) If the type of operation involves any external load lift 
operations and the number of external load lift operations is known, 
use the table below and multiply the appropriate factor for the 
average number of external load lift operations by the number of 
actual operating hours:

------------------------------------------------------------------------
   Average number of external load lift operations per hour      Factor 
------------------------------------------------------------------\1\---
0-2.00.......................................................          7
2.01-5.00....................................................          7
5.01-16.00...................................................         14
16.01-27.00..................................................         21
above 27.00..................................................        28 
------------------------------------------------------------------------
\1\ RIN = Factor  x  Actual Operating Hours.                            

    (C) If the type of operation involves any external load lift 
operations and the number of external load lift operations is 
unknown, multiply each actual operating hour by 21; or
    (D) If the type of operation is unknown, multiply each actual 
operating hour by 21.
    (iii) If the actual operating hours are unknown, assume 900 
operating hours per calendar year. Prorate the assumed operating 
hours for partial years.
    (A) If the type of operation is internal only, multiply the 
assumed operating hours by 7.
    (B) If the type of operation involves any external load lift 
operations and the number of external load lift operations is known, 
use the table in paragraph (b)(1)(ii)(B) and multiply the 
appropriate factor for the average number of external load lift 
operations by the number of assumed operating hours.
    (C) If the type of operation involves any external load lift 
operations and the number of external load lift operations is 
unknown, multiply each assumed operating hour by 21.
    (D) If the type of operation is unknown, multiply each assumed 
operating hour by 21.
    (2) For Model 214ST helicopters:
    (i) Multiply the high-power event total to-date by 2, or
    (ii) Multiply the factored flight hour total to-date by 12.

    Note 2: BHTI Alert Service Bulletin (ASB) 214-94-52, which is 
applicable to Model 214B helicopters, and ASB 214ST-94-66, which is 
applicable to Model 214ST helicopters, both of which are dated 
November 7, 1994, pertain to this subject.

    (c) After compliance with paragraphs (a) and (b) of this AD, and 
during each operation thereafter, maintain a count of each lift or 
takeoff performed and at the end of each day's operations, increase 
the accumulated RIN on the component history card or equivalent 
record as follows:
    (1) For 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 the elevation 
between the pick up point and the release point is 200 feet or 
greater.
    (2) For 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 in 
which the load is picked up at a higher elevation and released at a 
lower elevation and the difference in elevation between the pick up 
point and the release point is 200 feet or greater.
    (d) Remove the carrier, P/N's 214-040-077-007 or -101, from 
service on or before attaining an accumulated RIN of 120,000. The 
carrier is 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 carrier 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 August 19, 1997.

    Issued in Fort Worth, Texas, on July 8, 1997.
Larry M. Kelly,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 97-18499 Filed 7-14-97; 8:45 am]
BILLING CODE 4910-13-U