[Federal Register Volume 67, Number 251 (Tuesday, December 31, 2002)]
[Proposed Rules]
[Pages 79893-79894]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-32889]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-SW-45-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS332C, C1, L, 
and L1 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 (Eurocopter) Model AS332C, C1, L, and L1 
helicopters. This proposal would require inspecting the main gearbox 
bevel gear (bevel gear) for a crack using a borescope. This proposal is 
prompted by a crack that was detected on a bevel gear during a main 
gearbox teardown inspection. The actions specified by this proposed AD 
are intended to detect a bevel gear crack and prevent failure of the 
bevel gear, loss of torque to the main rotor system, and subsequent 
loss of control of the helicopter.

DATES: Comments must be received on or before March 3, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2002-SW-45-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. 2002-SW-45-AD.'' The postcard will be date 
stamped and returned to the commenter.

Discussion

    The Direction Generale De L'Aviation Civile (DGAC), the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on Eurocopter Model AS332C, C1, L, and L1 
helicopters, equipped with main gearbox main reduction gear modules, 
part numbers (P/N) 332A32-2027-00 or 332A32-2026-00, containing bevel 
gears, P/N 332A-2181-00, -02, -03, or -04, or 331A32-3110-07, -09, or -
19. The DGAC advises that borescope inspections of the bevel gear are 
necessary to detect cracks.
    Eurocopter has issued Alert Telex No. 05.00.58, dated August 6, 
2002, which indicates that as a result of metal particles found on the 
chip detector of the main gearbox sump on a helicopter,

[[Page 79894]]

further investigation has revealed a longitudinal crack that grows 
lengthwise in the tube in the bevel gear where the ring retains the 
pinion toe bearing. The alert telex specifies inspecting the bevel gear 
for cracks using a borescope. Pending the result of the investigation 
into the cause of the fatigue crack initiation currently being 
conducted in France, Eurocopter specifies inspecting the bevel gear for 
a crack using a borescope. The DGAC classified this alert telex as 
mandatory and issued AD No. T2002-424-081(A), dated August 8, 2002, to 
ensure the continued airworthiness of these 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 this 
interim AD action is necessary for products of these type designs that 
are certificated for operation in the United States until the cause of 
these fatigue cracks in the bevel gear are discovered.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design registered in the United States. 
Therefore, the proposed AD would require, for bevel gears with more 
than 6,600 hours time-in-service (TIS), inspecting the bevel gear for 
cracks using a borescope within 50 hours TIS, and thereafter at 
intervals not to exceed 150 hours TIS. If a crack were found in the 
bevel gear, replacing the bevel gear would be required. The actions 
would be required to be accomplished in accordance with the alert telex 
described previously.
    The FAA estimates that 4 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 4 work 
hours per helicopter to accomplish the inspections and 16 work hours 
per helicopter to replace the bevel gear. The average labor rate is $60 
per work hour. Required parts would cost approximately $31,372. Based 
on these figures, the total cost impact of the proposed AD on U.S. 
operators is estimated to be $130,288, assuming that upon the first 
inspection a crack is detected and the bevel gear will 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 adding a new airworthiness directive 
to read as follows:

Eurocopter France: Docket No. 2002-SW-45-AD.

    Applicability: Model AS332C, C1, L, and L1 helicopters, with 
main gearbox bevel gear (bevel gear), part numbers (P/N) 332A32-
2027-00 or 332A32-2026-00, containing bevel gears, P/N 332A-2181-00, 
-02, -03, or -04, or 331A32-3110-07, -09, or -19, 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 (c) 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.
    To detect a bevel gear crack and prevent failure of the bevel 
gear, loss of torque to the main rotor system, and subsequent loss 
of control of the helicopter, accomplish the following:
    (a) For bevel gears that have more than 6,600 hours time-in-
service (TIS), within 50 hours TIS, unless accomplished previously, 
and thereafter at intervals not to exceed 150 hours TIS, inspect for 
a crack using a borescope in accordance with the Operational 
Procedure, paragraph 2.B.1. and 2.B.2., of Eurocopter Telex No. 
05.00.58, dated August 6, 2002.
    (b) If a crack is found in the bevel gear, before further 
flight, replace the bevel gear with an airworthy bevel gear.
    (c) 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.


    (d) 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.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD T2002-424-081(A), dated 
August 8, 2002.


    Issued in Fort Worth, Texas, on December 20, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-32889 Filed 12-30-02; 8:45 am]
BILLING CODE 4910-13-P