[Federal Register Volume 67, Number 31 (Thursday, February 14, 2002)]
[Proposed Rules]
[Pages 6885-6886]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-3581]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-47-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS332C, L, L1, 
and Model SA330F, G, and J 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 (ECF) Model AS332C, L, and L1 and 
Model SA330F, G, and J helicopters. That AD currently requires an 
inspection to determine the angular play of the tail rotor gearbox 
(gearbox) at specified intervals. This action would change the 
measurement limits and the load to be applied to a tail rotor blade 
(blade) when determining the angular play. This proposal is prompted by 
a review of design data and a determination that the amount of play can 
be increased with an increase in the amount of applied load during the 
inspection. The actions specified by the proposed AD are intended to 
detect excessive angular play and to prevent failure of a gearbox, loss 
of tail rotor drive, and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before April 15, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-47-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: [email protected]. 
Comments may be inspected at the Office of the Regional Counsel between 
9 a.m. and 3 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Uday Garadi, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0110, 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, both before and after the closing 
date for comments, 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. 2001-SW-47-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. 2001-SW-47-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.

Discussion

    On June 18, 1998, the FAA issued AD 98-06-04, Amendment 39-10633 
(63 FR 34790, June 26, 1998) to require an inspection to determine the 
angular play of the gearbox at specified intervals depending on the 
amount of play detected. That AD was prompted by an accident involving 
a Model SA330 helicopter that lost tail rotor drive. An investigation 
determined that the loss of tail rotor drive was caused by excessive 
play between the gearbox bevel wheel and the tail rotor driveshaft. The 
requirements of that AD are intended to prevent failure of the gearbox, 
loss of tail rotor drive, and subsequent loss of control of the 
helicopter.
    Since the issuance of that AD, ECF has issued Alert Service 
Bulletin Nos. 05.00.44 and 05.86, both dated January 11, 2001, 
specifying a check of the angular play of certain gearboxes and to 
introduce new lower minimum and higher maximum angular play values.
    The Direction Generale De L'Aviation Civile (DGAC), which is the 
airworthiness authority for France, classified these service bulletins 
as mandatory and issued ADs 1997-332-067(A) R2 and 1997-323-079(A) R2, 
both dated February 21, 2001, to ensure the continued airworthiness of 
these helicopters in France.
    The DGAC notified the FAA that an unsafe condition may exist on 
Model AS332 and SA330 helicopters. The DGAC advises of the accident of 
a Model SA330 helicopter due to loss of the tail rotor drive due to 
worn splines on the bevel wheel and on the tail rotor drive shaft. The 
bevel wheel is the output bevel gear in the tail rotor

[[Page 6886]]

gearbox. The play is measured between the splines of the bevel gear and 
the tail rotor driveshaft.
    These helicopter models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral agreement, France has kept the FAA informed of the 
situation described above. The FAA has examined the findings of the 
DGAC, reviewed all available information, and determined that AD action 
is necessary for products of this type design that are certificated for 
operation in the United States.
    We have identified an unsafe condition that is likely to exist or 
develop on other helicopters of the same type designs. Therefore, the 
proposed AD would supersede AD 98-06-04 to change the measurement 
limits and inspection intervals.
    The FAA estimates that 4 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 3 work 
hours per helicopter to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Creating measurement tools 
would cost approximately $100 per helicopter and it would cost $45,000 
to replace a gearbox. Based on these figures, the total cost impact of 
the proposed AD on U.S. operators is estimated to be $1120, assuming no 
gearbox would need to be replaced.
    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 39-10633 (63 FR 
34790, June 26, 1998), and by adding a new airworthiness directive 
(AD), to read as follows:

Eurocopter France: Docket No. 2001-SW-47-AD. Supersedes AD 98-06-04, 
Amendment 39-10633, Docket No. 98-SW-11-AD.

    Applicability: Model AS332C, L, and L1 and Model SA330F, G, and 
J helicopters, with tail rotor gearbox (gearbox), part number (P/N) 
332A33-0001-all dash numbers, 330A33-0000-all dash numbers, 330A33-
0011-all dash numbers (for AS332 models), or 330A33-9109-all dash 
numbers (for SA330 models), 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 
otherwise 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. The 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 detect excessive angular play in the gearbox and to prevent 
failure of a gearbox, loss of tail rotor drive, and subsequent loss 
of control of the helicopter, accomplish the following:
    (a) Within 25 hours time-in-service (TIS) for any gearbox with 
495 or more hours TIS, inspect each gearbox for play between the 
splines of the gearbox bevel gear and tail rotor driveshaft in 
accordance with the Accomplishment Instructions, paragraphs 2.A. 
through 2.B.4. of Eurocopter France Alert Service Bulletin No. 
05.00.44 for the Model AS332 helicopters or No. 05.86 for the Model 
SA330 helicopters, both Revision 1 and both dated January 11, 2001.
    (1) Thereafter, reinspect the gearbox for play:
    (i) At intervals not to exceed 520 hours TIS, if the play 
measurement is 0.30 millimeter (mm) (0.0118 inch) or less for Model 
SA330 helicopters or 0.44mm (0.0173 inch) or less for Model AS332 
helicopters, or
    (ii) At intervals not to exceed 100 hours TIS, if the play 
measurement is greater than 0.30mm and less than 0.65mm (0.0255 
inch) for Model SA330 helicopters or greater than 0.44mm and less 
than 0.75mm (0.0295 inch) for the Model AS332 helicopters.
    (2) Before further flight, remove any gearbox if the play 
measurement is equal to or greater than 0.65mm for Model SA330 
helicopters or 0.75mm for Model AS332 helicopters.
    (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 will not be issued.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile, (France) ADs 1997-322-067(A) R2 and 
1997-323-079(A) R2, both dated February 21, 2001.


    Issued in Fort Worth, Texas, on February 6, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-3581 Filed 2-13-02; 8:45 am]
BILLING CODE 4910-13-P