[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
Federal Register
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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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