[Federal Register Volume 67, Number 139 (Friday, July 19, 2002)]
[Proposed Rules]
[Pages 47488-47490]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-18196]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-35-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS332C, AS332L, 
AS332L1, SA330F, SA330G, and SA330J Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for Eurocopter France (ECF) Model AS332C, AS332L, AS332L1, SA330F, 
SA330G, and SA330J helicopters. This proposal would require inspecting 
the tail rotor pitch change rod (change rod) bearing and replacing the 
bearing if the bearing does not meet the specified tolerance. Also, 
this proposal would require inspecting the bearing for spalling, 
friction, and grinding and removing any unairworthy bearing. This 
proposal is prompted by the seizure of a bearing on an ECF Model SA330 
helicopter. The actions specified by this proposed AD are intended to 
prevent bearing wear, bearing seizure of the change rod, loss of tail 
rotor effectiveness, and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before September 17, 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-35-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: Jim Grigg, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0110, telephone (817) 222-5490, 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

[[Page 47489]]

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-35-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-35-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.

Discussion

    The Direction Generale De L'Aviation Civile (DGAC), the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on ECF Model AS332C, AS332C1, AS332L, AS332L1, 
SA330F, SA330G, and SA330J helicopters. The DGAC advises that the pitch 
change rod bearing seized on a Model SA330 helicopter.
    ECF has issued Eurocopter France Alert Service Bulletin (ASB) Nos. 
05.81, Revision 2, and 05.00.29, Revision 3, both dated January 18, 
2001, which specify modifying the operational and bearing check 
procedure for the change rod equipped with bearing, part number (P/N) 
330A33-9903-20. The DGAC classified ASB No. 05.00.29, Revision 3, dated 
January 18, 2001, as mandatory and issued AD No. 1990-230-041(A) R4, 
dated February 21, 2001, to ensure the continued airworthiness of the 
ECF Model AS332 helicopters in France.
    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, the DGAC 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 these type designs that are certificated 
for operation in the United States.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type designs registered in the United States. 
Therefore, the proposed AD would require the following inspections 
initially, repetitively, and before installing any tail rotor gearbox 
that has been previously installed on another helicopter and has not 
been inspected:
     Inspect the tail rotor spider for end play. Remove the 
change rod bearing if the tail rotor spider is not within allowable 
tolerances.
     Inspect each bearing for spalling, friction, grinding, 
damaged bearing sealing flanges, overheating at the bearing inner and 
outer races and the flanges, deposits of corrosion, and shearing or 
wear marks on the lockwasher, and remove any unairworthy bearing.
     If a bearing is removed, before replacing the bearing, 
inspect the change rod for visible wear marks or scoring on the bearing 
journal circumference. If wear marks or circular scoring is found, 
repair or replace the bearing housing.
    The actions would be required to be accomplished in accordance with 
the service bulletins described previously.
    The FAA estimates that 3 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 4 work 
hours to inspect and replace a bearing, and that the average labor rate 
is $60 per work hour. Required replacement parts would cost 
approximately $120. Based on these figures, the total cost impact of 
the proposed AD on U.S. operators is estimated to be $1080, assuming 
one bearing is replaced on each helicopter.
    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 adding a new airworthiness directive 
to read as follows:

Eurocopter France: Docket No. 2001-SW-35-AD.

    Applicability: Model AS332C, AS332L, AS332L1, SA330F, SA330G, 
and SA330J helicopters with a tail rotor pitch change rod (rod) and 
a bearing, part number 330A33-9903-20, 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 (d) 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: Within 20 hours time-in-service (TIS) or 1 month, 
whichever occurs first, or before installing any tail rotor gearbox 
previously installed on another helicopter and not inspected within 
the previous 250 hours TIS, unless accomplished previously, and 
thereafter at intervals not to exceed 250 hours TIS or 18 months, 
whichever occurs first.
    To prevent bearing wear, bearing seizure of the change rod, loss 
of tail rotor effectiveness and subsequent loss of control of the 
helicopter, accomplish the following:
    (a) Inspect the axial end play of the tail rotor pitch change 
spider assembly in accordance with the Accomplishment Instructions, 
paragraph 2.B.1. of Eurocopter France (ECF) Alert Service Bulletin 
No. 05.81, Revision 2, dated January 18, 2001 (ASB 330) for the ECF 
Model 330 helicopters or Eurocopter France Alert Service Bulletin 
No. 05.00.29, Revision 3, dated January 18, 2001 (ASB 332) for the 
Model 332 helicopters. If the axial end play is not within allowable 
tolerances, remove the rod bearing from service.

[[Page 47490]]

    (b) Inspect each bearing for spalling, friction, grinding, 
damaged bearing sealing flanges, overheating at the bearing inner 
and outer races and the flanges, deposits of corrosion, and shearing 
or wear marks on the lockwasher in accordance with the 
Accomplishment Instructions, paragraph 2.B.2., of ASB 330 or ASB332, 
as applicable. Remove from service any unairworthy bearing.
    (c) If a bearing is removed from service, before replacing the 
bearing with an airworthy bearing:
    (1) Inspect the change rod for visible wear marks or scoring on 
the bearing journal circumference. If marks or scoring is found, 
remove the change rod from service.
    (2) Inspect the bearing housing for visible wear marks or 
circular scoring. If wear marks or circular scoring is found, repair 
or replace the bearing housing in accordance with the Accomplishment 
Instructions, paragraph 2.B.3., of ASB 330 or ASB 332, as 
applicable.
    (d) 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.

    (e) Special flight permits will not be issued.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD No. 1990-230-041(A) R4, 
dated February 21, 2001.



    Issued in Fort Worth, Texas, on July 5, 2002.
Larry M. Kelly,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-18196 Filed 7-18-02; 8:45 am]
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