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-26-AD; Amendment 39-10077; AD 97-15-04]

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 mandatory

retirement life of 60,000 high-power events for the main transmission

upper planetary carrier (carrier). This amendment requires 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 amendment 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 this

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.

EFFECTIVE DATE: August 19, 1997.

ADDRESSES: The service information referenced in Note 2 of this AD 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: A proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) by superseding AD 94-02-05,

Amendment 39-8803 (59 FR 32325, June 23, 1994), which is applicable to

BHTI Model 214B, 214B-1, and 214ST helicopters, was published in the

Federal Register on January 14, 1997 (62 FR 1864). That action proposed

to require creation of a component history card or equivalent record

using the RIN system and a system for tracking increases to the

accumulated RIN, and proposed to establish a retirement life of a

maximum of 120,000 accumulated RIN for the carrier.

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 one editorial change. The

ADDRESSES paragraph in the preamble has been changed to clarify that

the service bulletin is not incorporated into the AD, but is mentioned

in Note 2 for information only. 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 11 helicopters of U.S. registry will be

affected by this AD, that it will 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 will cost approximately $29,516 per helicopter. Based on

these figures, the total cost impact of the 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 by the carrier of 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 39-8803 (59 FR

32325, June 23, 1994), and by adding a new airworthiness directive

(AD), Amendment 39-10077, to read as follows:

AD 97-15-04 Bell Helicopter Textron, Inc. (BHTI): Amendment 39-

10077 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

[[Page 37711]]

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

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

------------------------------------------------------------------\1\---

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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\1\ 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 (b)(1)(ii)(B) 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.

(g) This amendment becomes effective on August 19, 1997.

Issued in Fort Worth, Texas, on July 8, 1997.

Larry M. Kelly,

Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 97-18499 Filed 7-14-97; 8:45 am]

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