[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
