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. 93-SW-20-AD; Amendment 39-8985; AD 94-15-14]

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 adopts a new airworthiness directive (AD),

applicable to Bell Helicopter Textron, Inc. Model 214B, 214B-1, and

214ST helicopters, that establishes a mandatory retirement life of

60,000 high-power events for the main rotor trunnion (trunnion), which

is currently not a life-limited part. This amendment is prompted by the

manufacturer's analysis and retesting that has shown that frequent

takeoffs and external load lifts (high-power events) shorten the life

of the trunnion. The actions specified by this AD are intended to

prevent fatigue failure of the trunnion, loss of the main rotor, and

subsequent loss of control of the helicopter.

EFFECTIVE DATE: September 14, 1994.

FOR FURTHER INFORMATION CONTACT: Mr. Lance Gant, Aerospace Engineer,

Rotorcraft Certification Office, FAA, Rotorcraft Directorate, ASW-170,

Fort Worth, Texas 76137, telephone (817) 222-5141, fax (817) 222-5959.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to include an airworthiness

directive (AD) that is applicable to Bell Helicopter Textron, Inc.

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

Register on January 5, 1994 (59 FR 556). That action proposed to

establish a mandatory retirement life of 60,000 high-power events for

the main rotor trunnion (trunnion), part number (P/N) 214-010-230-101,

which is currently not a life-limited part. High-power events are

takeoffs and external load lifts.

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. However,

the FAA has added a sentence to paragraph (d) of this AD dealing with

the retirement life of this part to make it clear that the retirement

life established is 60,000 high-power events; but, since this AD

establishes a new method of determining the retirement life, those

trunnions that have 59,400 or more high-power events need not be

retired until on or before the accumulation of an additional 600 high-

power events. The FAA has determined that air safety and the public

interest require the adoption of the rule as proposed with this change.

The FAA has determined that this change will not increase the scope

of the AD. However, the FAA has performed a more detailed cost analysis

and has determined that, when factoring in the creation and maintenance

of the component history card or equivalent record, the anticipated

costs are $9,900 higher than the proposed amount for the first year and

$8,525 higher than the proposed amount for each subsequent year. In the

proposal, the cost of this AD was estimated to be $29,523 each year.

The FAA estimates that 15 helicopters of U.S. registry will be

affected by this AD, and that (1) it will take approximately 16 work

hours per helicopter to replace the affected part due to the new method

of determining the retirement life required by this AD; (2) it will

take approximately 2 work hours per helicopter to create the component

history card or equivalent record (record); (3) it will take

approximately 10 work hours per helicopter to maintain the record each

year; and (4) the average labor rate is $55 per work hour. Required

parts will cost approximately $10,929 per helicopter. Based on these

figures, the total cost impact of the AD on U.S. operators for the

first year is estimated to be $39,423 and each subsequent year to be

$38,048, assuming replacement of the trunnion in one-sixth of the fleet

each year, and creation and maintenance of the records for all the

fleet the first year and creation of one-sixth of the 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. This AD and any related

information may be examined in the Rules Docket at the Federal Aviation

Administration (FAA), Office of the Assistant Chief Counsel, 2601

Meacham Blvd., Room 663, Fort Worth, Texas.

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. App. 1354(a), 1421 and 1423; 49 U.S.C.

106(g); and 14 CFR 11.89.

Sec. 39.13 [Amended]

2. Section 39.13 is amended by adding a new airworthiness directive

to read as follows:

AD 94-15-14 Bell Helicopter Textron, Inc.: Amendment 39-8985.

Docket Number 93-SW-20-AD.

Applicability: Model 214B, 214B-1, and 214ST helicopters,

equipped with main rotor trunnion (trunnion), part number (P/N) 214-

010-230-101, certificated in any category.

Compliance: Required as indicated, unless accomplished

previously.

To prevent fatigue failure of the trunnion as a result of

takeoffs and external load lifts (high-power events), that could

result in loss of the main rotor and subsequent loss of the

helicopter, accomplish the following:

(a) Within the next 25 hours' time-in-service (TIS) after the

effective date of this airworthiness directive (AD), accomplish the

following:

(1) Create a component history card or an equivalent record for

the affected trunnion.

(2) Determine the actual TIS of the trunnion from maintenance

records, if possible. If the actual TIS cannot be determined, use a

TIS of 900 hours per year. Prorate the hours for a partial year.

(3) For Model 214B and 214B-1 helicopters, determine and record

the accumulated high-power events on the trunnion as follows:

(i) If the number of high-power events is unknown, assign 12

high-power events for each hour TIS obtained in accordance with

paragraph (a)(2).

(ii) If the number of high-power events is known, divide that

number by 2 and record the resulting number as the total accumulated

high-power events.

(4) For Model 214ST helicopters, determine and record the

accumulated high-power events on the trunnion as follows:

(i) If the number of high-power events is unknown, assign 11

high-power events for each hour TIS obtained in accordance with

paragraph (a)(2).

(ii) If the number of high-power events is known, record that

number as the total accumulated high-power events.

(b) After the effective date of this AD, continue to record

high-power events. For Model 214B and 214B-1 helicopters, divide the

number of high-power events as they occur by 2 and add the resulting

number to the previously recorded sum. For Model 214ST helicopters,

add the high-power events as they occur to the previously recorded

sum.

(c) Remove the trunnion and replace it with an airworthy

trunnion in accordance with the following:

(1) For each trunnion with 59,400 or more high-power events,

replace with an airworthy trunnion on or before the accumulation of

an additional 600 high-power events.

(2) For each trunnion with less than 59,400 high-power events,

replace the trunnion with an airworthy trunnion on or before

attaining 60,000 high-power events.

(d) This AD revises the helicopter Airworthiness Limitations

Section of the maintenance manual by establishing a new retirement

life for the trunnion of 60,000 high-power events. However,

trunnions with 59,400 or more high-power events need not be retired

until on or before the accumulation of an additional 600 high-power

events.

(e) An alternative method of compliance or adjustment of the

compliance time that provides an acceptable level of safety may be

used when 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: 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

Sec. Sec. 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 14, 1994.

Issued in Fort Worth, Texas, on July 20, 1994.

James D. Erickson,

Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 94-19401 Filed 8-9-94; 8:45 am]

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