[Federal Register Volume 59, Number 153 (Wednesday, August 10, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-19401]


[[Page Unknown]]

[Federal Register: August 10, 1994]


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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]
BILLING CODE 4910-13-P