[Federal Register Volume 66, Number 68 (Monday, April 9, 2001)]
[Proposed Rules]
[Pages 18416-18419]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-8620]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-12-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS350B, B1, B2, 
B3, BA, C, D, D1, and AS355E, F, F1, F2, and N Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes superseding an existing airworthiness 
directive (AD) for Eurocopter France Model AS350B, B1, B2, BA, C, D, 
D1, and AS355E, F, F1, F2, and N helicopters. That AD currently 
requires measuring the tail rotor pitch control rod (control rod) 
outboard spherical bearing (bearing) for radial and axial play and 
replacing the control rod with an airworthy control rod if the play 
exceeds 0.008-inch. This action would retain those requirements but 
would add the Eurocopter France Model AS350B3 helicopter and an 
additional control rod to the applicability. This action would also add 
a daily inspection of the control rod and an axial play limit of 0.016-
inch and would revise the AD compliance interval from 50 hours time-in-
service (TIS) to 30 hours TIS. This proposal is prompted by two 
comments received on AD 98-24-35 and the determination that the AD 
inspection interval should coincide with the normal maintenance 
interval and the AD should apply to the Eurocopter France Model AS350B3 
helicopter. The actions specified by the proposed AD are intended to 
prevent separation of the bearing ball from its outer race, rubbing of 
the body of the control rod against the tail rotor blade pitch horn 
clevis, failure of the control rod, and loss of control of the 
helicopter.

DATES: Comments must be received on or before June 8, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-12-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. You may also email comments to the Rules Docket at [email protected].

FOR FURTHER INFORMATION CONTACT: Uday Garadi, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Regulations Group, Fort Worth, Texas 
76193-0111, telephone (817) 222-5123, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments will 
be considered before taking action on the proposed rule. The proposals 
contained in this document may be changed in light of the comments 
received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available in the Rules Docket for 
examination by interested persons. A report summarizing each FAA-public 
contact concerned with the substance of this proposal will be filed in 
the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this proposal must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2000-SW-12-AD.'' The postcard will be date 
stamped and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-12-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.

Discussion

    On November 19, 1998, the FAA issued AD 98-24-35, Amendment 39-
10921 (63 FR 66418, December 2, 1998), to require measuring the control 
rod bearing radial and axial play within 50 hours TIS and thereafter at 
intervals not to exceed 50 hours TIS. That action was prompted by an 
accident and an incident involving Eurocopter France Model AS350B2 
helicopters offshore over the Gulf of Mexico. There were two other 
unconfirmed incidents cited by the National Transportation Safety Board 
(based on manufacturer's reports) involving the same control rod, part

[[Page 18417]]

number (P/N) 350A33-2145-01. The requirements of that AD are intended 
to prevent separation of the bearing ball from its outer race, rubbing 
of the body of the control rod against the tail rotor blade pitch horn 
clevis, failure of the control rod, and loss of control of the 
helicopter.
    Since the issuance of that AD, Eurocopter France has issued Service 
Letter No. 1367-64-98, dated January 12, 1999. The service letter 
provides operators with a more accurate way to determine the looseness 
of the bearing by adding an axial play limit of 0.016 inch and a daily 
inspection. Also, the FAA received comments to AD 98-24-35 from two 
commenters, the manufacturer and an operator. The commenters state that 
a larger axial play limit and a 30-hour visual check would provide a 
satisfactory degree of safety for this control rod and an adequate 
inspection interval. The FAA agrees, and this action would add a daily 
inspection of the control rod and an axial play limit of 0.016-inch and 
would revise the AD compliance interval from 50 hours TIS to 30 hours 
TIS.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other helicopters of these same type designs, the 
proposed AD would supersede AD 98-24-35 to retain the same requirements 
and would add the following requirements:
     Add the Eurocopter France Model AS350B3 helicopter to the 
applicability.
     Add control rod, P/N 350A33-3145-00, to the applicability.
     Revise the AD inspection interval so that it does not 
exceed 30 hours TIS to coincide with the normal maintenance interval.
     Establish a daily inspection of the tail rotor pitch 
control rod bearing for axial play.
     Establish an axial play limit of 0.016-inch.
    The FAA estimates that 610 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 1 work 
hour per helicopter to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts would cost 
approximately $1,224 for two control rods per helicopter. Based on 
these figures, the total cost impact of the proposed AD on U.S. 
operators is estimated to be $783,240.
    The regulations proposed herein would not have a substantial direct 
effect 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, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting 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.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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 removing Amendment 39-10921 (63 FR 
66418, December 2, 1998), and by adding a new airworthiness directive 
(AD), to read as follows:

Eurocopter France: Docket No. 2000-SW-12-AD. Supersedes AD 98-24-35 
Amendment 39-10921, Docket No. 98-SW-41-AD.

    Applicability: Eurocopter France Model AS350B, B1, B2, B3, BA, 
C, D, D1, and AS355E, F, F1, F2, and N helicopters, with tail rotor 
pitch control rod (control rod), part number (P/N) 350A33-2145-01 or 
P/N 350A33-3145-00, 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 request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. This request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent separation of the outboard spherical bearing 
(bearing) ball from its outer race, rubbing of the body of the 
control rod against the tail rotor blade pitch horn clevis, failure 
of the control rod, and loss of control of the helicopter, 
accomplish the following:
    (a) Before the first flight of each day, configure the 
helicopter by ensuring the tail rotor pedals are in neutral 
position. If the helicopter is fitted with a tail rotor load 
compensator, discharge the accumulator as described in the flight 
manual. Inspect the bearing for play (Figure 1) on the helicopter, 
by observation and feel, by slightly moving the tail rotor blade in 
the flapping axis while monitoring the bearing for movement.
    (1) If the Teflon cloth is found to be coming out of its normal 
position within the bearing, totally or partially, replace the 
control rod with an airworthy control rod before further flight.
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    (2) If play is detected, measure the bearing wear using a dial 
indicator as shown in Figure 2. Perform the following steps (Figure 
2) unless they were accomplished within the last 30 hours TIS.
    (i) Remove the control rod.
    (ii) Install a bolt, washers, and a nut to secure the bearing.
    (iii) Mount the bearing in a vise as shown in Figure 2.
    (iv) Using a dial indicator, take two radial measurements in the 
areas shown by the two arrows.
    (v) Take axial measurements in the area shown by an arrow.
    (vi) Record the hours of operation on each control rod.
    (vii) If the radial play exceeds 0.008 inch or axial play 
exceeds 0.016 inch, replace the control rod with an airworthy 
control rod before further flight.
    (3) If the radial and axial play are within limits, reinstall 
the control rod.
    (4) At intervals not to exceed 30 hours TIS, remove the control 
rod and measure the bearing wear with a dial indicator (Figure 2) 
using steps (a)(2)(i) through (a)(2)(vii).

[[Page 18419]]

[GRAPHIC] [TIFF OMITTED] TP09AP01.001

    (b) 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, Regulations Group, 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, Regulations Group.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (c) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the requirements of this AD can be accomplished.

    Issued in Fort Worth, Texas, on April 2, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-8620 Filed 4-6-01; 8:45 am]
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