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

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

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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]

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