AD 97-06-02

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 transmissionand subsequent loss of control of the helicopter.

Final rule

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.

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 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 ofit 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 USC 106(g), 40113, 44701.

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: