[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:
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Average number of external load lift operations per hour Factor *
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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