[Federal Register Volume 62, Number 9 (Tuesday, January 14, 1997)]
[Proposed Rules]
[Pages 1864-1866]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-879]



[[Page 1864]]

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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-SW-26-AD]


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of 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 action 
would require 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 proposal 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 the proposed 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.

DATES: Comments must be received by March 17, 1997.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Assistant Chief Counsel, Attention: 
Rules Docket No. 94-SW-26-AD, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137. Comments may be inspected at this location between 9:00 
a.m. and 3:00 p.m., Monday through Friday, except Federal holidays.
    The service information referenced in the proposed rule 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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 94-SW-26-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Office of the Assistant Chief Counsel, Attention: Rules 
Docket No. 94-SW-26-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

Discussion

    On June 6, 1994, the FAA issued AD 94-02-05, Amendment 39-8803, (59 
FR 32325, June 23, 1994), to require changing the method of calculating 
the retirement life for the carrier, part number (P/N) 214-040-077-007 
and -101, from flight hours to high-power events calculated using the 
number of takeoffs and external load lifts, removing the 2,500 hours 
TIS magnetic particle inspection for the carrier, and making the 
requirements applicable to the Model 214ST as well as the Model 214B 
and 214B-1 helicopters. That action was prompted by fatigue analyses 
and tests that show certain carriers fail sooner than originally 
anticipated because of the unanticipated high number of lifts and 
takeoffs (torque events) performed with those carriers in addition to 
the TIS accrued under other operating conditions. The requirements of 
that 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.
    Since the issuance of that AD, BHTI has issued BHTI Information 
Letter GEN-94-54, dated April 15, 1994, Subject: Retirement Index 
Number (RIN) For Cycle Lifed Components, which introduces a different 
method of accounting for fatigue damage on components that have 
shortened service lives as a result of frequent torque events. 
Additionally, BHTI has issued 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, and describe procedures for converting flight hours 
and total number of torque events into a RIN for the carrier, P/N214-
040-077-007 and -101. Although ASB 214-94-52 does not state that it 
applies to Model 214B-1 helicopters, this was an oversight by the 
manufacturer. That ASB was intended to apply to both Model 214B and 
214B-1 helicopters.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other BHTI Model 214B, 214B-1, and 214ST 
helicopters of the same type design, the proposed AD would supersede AD 
94-02-05 to require creation of a component history card using the RIN 
system and a system for tracking increases to the accumulated RIN, and 
establish a maximum accumulated RIN for the carrier of 120,000 at which 
it must be retired.
    The FAA estimates that 11 helicopters of U.S. registry would be 
affected by this proposed AD, that it would 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 would cost approximately $29,516 per 
helicopter. Based on these figures, the total cost impact of the 
proposed 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 of the spider 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 proposed herein would not have substantial direct 
effects on the States, on the relationship between the national 
government and

[[Page 1865]]

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 proposal would not 
have sufficient federalism implications to warrant the preparation of a 
Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) Is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting 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.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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), to read as follows:

Bell Helicopter Textron, Inc. (BHTI): 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 
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 
upper planetary carrier (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 *
------------------------------------------------------------------------
0-2.00.......................................................          7
2.01-5.00....................................................          7
5.01-16.00...................................................         14
16.01-27.00..................................................         21
Above 27.00..................................................        28 
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* 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 (ii)(B) above 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.


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    Issued in Fort Worth, Texas, on January 7, 1997.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 97-879 Filed 1-13-97; 8:45 am]
BILLING CODE 4910-13-U