[Federal Register Volume 64, Number 41 (Wednesday, March 3, 1999)]
[Rules and Regulations]
[Pages 10208-10209]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-5039]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-SW-23-AD; Amendment 39-11055; AD 99-05-07]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron, Inc. Model 
214B and 214B-1 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. (BHTI) Model 214B and 214B-
1 helicopters, that requires creation of a component history card or an 
equivalent record using the Retirement Index Number (RIN) system, 
establishing a system for tracking increases to the accumulated RIN, 
and establishing a maximum accumulated RIN for the pillow block bearing 
bolts (bearing bolts) of 17,000 before they must be removed from 
service. This amendment is prompted by fatigue analyses and tests that 
show certain bearing bolts fail sooner than originally anticipated 
because of the unanticipated high number of lifts and takeoffs (torque 
events) performed with those bearing bolts 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 
bearing bolts, which could result in failure of the main rotor system 
and subsequent loss of control of the helicopter.

EFFECTIVE DATE: May 3, 1999.

FOR FURTHER INFORMATION CONTACT: Harry Edmiston, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Certification Office, Fort 
Worth, Texas 76193-0170, telephone (817) 222-5158, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that is 
applicable to BHTI Model 214B and 214B-1 helicopters was published in 
the Federal Register on July 6, 1998 (63 FR 36377). That action 
proposed to require creation of a component history card or an 
equivalent record using the RIN system, establishing a system for 
tracking increases to the accumulated RIN, and establishing a maximum 
accumulated RIN for the bearing bolts of 17,000 before they must be 
removed from service.
    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.
    The FAA estimates that 54 helicopters of U.S. registry will be 
affected by this AD, that it will take, per helicopter, approximately 
(1) 24 work hours to replace the affected bearing bolts due to the new 
method of determining the retirement life; (2) 2 work hours to create 
the component history card or equivalent record (record); and (3) 10 
work hours to maintain the record each year; and that the average labor 
rate is $60 per work hour. Required parts will cost approximately 
$2,000 per helicopter. Based on these figures, the total cost impact of 
the AD on U.S. operators is estimated to be $224,640 for the first year 
and $128,520 for each subsequent year. These costs assume replacement 
of the bearing bolts in the fleet the first year, and creation and 
maintenance of the records for all the fleet; and replacement of one-
half of the fleet's bolts, creation of the records for one-half of the 
fleet, 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 Federal Aviation Administration (FAA), 
Office of the Regional Counsel, Southwest Region, Attention: Rules 
Docket No. 94-SW-23-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

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 adding a new airworthiness directive 
to read as follows:

AD 99-05-07  Bell Helicopter Textron, Inc.: Amendment 39-11055. 
Docket No. 94-SW-23-AD.

    Applicability: Model 214B and 214B-1 helicopters, 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 (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), 
unless accomplished previously.

[[Page 10209]]

    To prevent fatigue failure of the pillow block bearing bolts 
(bearing bolts), part number (P/N) 20-057-12-48D or -50D, which 
could result in failure of the main rotor system and subsequent loss 
of control of the helicopter, accomplish the following:
    (a) Create a Retirement Index Number (RIN) component history 
card or an equivalent record for the bearing bolts, P/N 20-057-12-
48D or -50D.
    (b) Calculate and record on the component history card the 
historical accumulated RIN for the bearing bolts as follows:
    (1) When the type of operation (internal or external load lift), 
actual flight hours, and number of external load lifts or takeoffs 
per hour are known, multiply the actual flight hours by the 
appropriate factor in the following table for external load lift 
operation:

------------------------------------------------------------------------
Average number of external load lift events per flight hour     Factor
------------------------------------------------------------------------
0-2.00.....................................................          6.8
2.01-5.00..................................................         13.6
5.01-16.00.................................................         27.2
16.01--27.00...............................................         40.8
Above 27.00................................................         54.4
------------------------------------------------------------------------

    When the type of operation is internal load and no external 
lifting is involved, each hour of actual operating time is equal to 
6.8 RIN.
    (2) When the actual flight hours on the bolts are known, but the 
type of operation (internal or external load lift) is unknown, 
multiply the actual flight hours by a factor of 40.8.
    (3) When the actual flight hours on the bolts are unknown, 
assume 75 flight hours per month.
    (4) When the flight hours on the bolts are assumed, but the type 
of operation (internal or external load lift) is known,
    (i) Multiply the number of flight hours assumed for internal 
load operations by a factor of 6.8.
    (ii) Multiply the number of flight hours assumed for external 
load operations by a factor of 40.8.
    (5) When the flight hours on the bolts are assumed and the type 
of operation (internal or external load lift) is unknown, multiply 
the assumed flight hours by a factor of 40.8.
    (c) After compliance with paragraphs (a) and (b) of this AD, 
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 bearing bolts component history card as 
follows:
    (1) Increase the RIN by 1 for each takeoff.
    (2) Increase the RIN by 1 for each external load lift, or 
increase the RIN by 2 for each external load operation 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.

    Note 2: Bell Helicopter Textron, Inc. Alert Service Bulletin No. 
214-94-54, dated November 7, 1994, pertains to the subject of this 
AD.

    (d) Remove the bearing bolts from service on or before attaining 
an accumulated RIN of 17,000. The bearing bolts are no longer 
retired based upon flight hours. If any of the four bolts require 
replacement for any reason, then all four bolts must be replaced at 
that time. This AD revises the Airworthiness Limitations section of 
the maintenance manual by establishing a new retirement life for the 
bearing bolts of 17,000 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, 
Rotorcraft Directorate, FAA. 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 May 3, 1999.

    Issued in Fort Worth, Texas, on February 19, 1999.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-5039 Filed 3-2-99; 8:45 am]
BILLING CODE 4910-13-U