[Federal Register Volume 62, Number 48 (Wednesday, March 12, 1997)]
[Rules and Regulations]
[Pages 11318-11319]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-6090]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-SW-24-AD; Amendment 39-9959; AD 97-06-02]
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 40,000 high-power events for the lower planetary spider
(spider). This amendment changes the method of calculating the
retirement life for the spider from high-power events to a maximum
accumulated Retirement Index Number (RIN) of 80,000, and makes this RIN
applicable to an additional part-numbered spider. This amendment is
prompted by fatigue analyses and tests that show certain spiders fail
sooner than originally anticipated because of the unanticipated higher
number of external load lifts and takeoffs (torque events) performed
with those spiders, 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 spider, which could result
in failure of the main transmission and subsequent loss of control of
the helicopter.
EFFECTIVE DATE: April 16, 1997.
ADDRESSES: The service information referenced in this AD may be
obtained from Bell Helicopter Textron, Inc., P.O. Box 482, Ft. Worth,
Texas 76101.
FOR FURTHER INFORMATION CONTACT: Mr. Uday Garadi, Aerospace Engineer,
FAA, Rotorcraft Certification Office, Rotorcraft Directorate, 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 93-05-02,
Amendment 39-8608 (58 FR 45833, August 31, 1993), which is applicable
to BHTI Model 214B, 214B-1, and 214ST helicopters, was published in the
Federal Register on November 14, 1996 (61 FR 58353). That action
proposed changing the method of calculating the retirement life for the
spider from high-power events to a maximum accumulated RIN of 80,000,
and proposed making this RIN applicable to an additional part-numbered
spider.
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 some editorial changes. The FAA
has determined that these changes will neither increase the economic
burden on any operator nor expand 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
to replace a spider affected by 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 $10,920 per helicopter. Based on these figures, the
[[Page 11319]]
total cost impact of the AD on U.S. operators is estimated to be
$28,220 for the first year and $27,120 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 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 39-8608 (58 FR
45833, August 31, 1993), and by adding a new airworthiness directive
(AD), Amendment 39-9959, to read as follows:
AD 97-06-02 Bell Helicopter Textron, Inc.: Amendment 39-9959.
Docket No. 94-SW-24-AD. Supersedes AD 93-05-02, Amendment 39-8608.
Applicability: Model 214B and 214B-1 helicopters, with lower
planetary spider (spider), part number (P/N) 214-040-080-001 or -
101, and Model 214ST helicopters, with spider, P/N 214-040-080-101,
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 (f) 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 spider, 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 for the spider, P/N 214-040-
080-001 or -101.
(b) For Model 214B and 214B-1 helicopters with spider, P/N 214-
040-080-001, determine and record the accumulated Retirement Index
Number (RIN) as follows:
(1) If the number of takeoffs and the number of external load
lifts conducted with this spider are known, record one (1) RIN for
each takeoff and one (1) RIN for each external load lift.
(2) If either the number of takeoffs or the number of external
load lifts conducted with this spider are unknown, record twenty-
four (24) RIN for each hour TIS.
(3) If either the number of takeoffs or the number of external
load lifts conducted with this spider are unknown, or the hours TIS
are unknown, record twenty-one thousand, six hundred (21,600) RIN
for each calendar year TIS. Prorate the number of RIN, based on the
number of calendar days, for a portion of a year.
(c) For Model 214B, 214B-1, and 214ST helicopters with spider,
P/N 214-040-080-101, determine and record the accumulated RIN by
multiplying the high-power events by two (2).
Note 2: BHTI Alert Service Bulletin (ASB) No. 214-94-53, which
is applicable to Model 214B and 214B-1 helicopters, and ASB No.
214ST-94-68, which is applicable to Model 214ST helicopters, both
dated November 7, 1994, pertain to this subject.
(d) After complying with paragraphs (a) and (b) or (c) 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, or
increase the RIN by 2 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 pickup point
and the release point is 200 feet or greater.
(2) For the Model 214ST helicopter:
(i) Increase the RIN by 2 for each takeoff.
(ii) Increase the RIN by 2 for each external load lift, 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 pickup point
and the release point is 200 feet or greater.
(e) Remove the spider, P/N 214-040-080-001 or -101, from service
on or before attaining an accumulated RIN of 80,000. The spider 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 spider of 80,000 RIN.
(f) 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.
(g) 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.
(h) This amendment becomes effective on April 16, 1997.
Issued in Fort Worth, Texas, on February 26, 1997.
Larry M. Kelly,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 97-6090 Filed 3-11-97; 8:45 am]
BILLING CODE 4910-13-U
