[Federal Register: April 7, 1998 (Volume 63, Number 66)]
[Proposed Rules]               
[Page 16916-16918]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07ap98-24]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-07-AD]

 
Airworthiness Directives; Eurocopter France Model AS 332C, L, L1, 
and L2 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to Eurocopter France Model AS 332C, 
L, L1, and L2 helicopters. This proposal would require visually 
inspecting the intermediate gearbox-to-structure attachment stirrup 
(stirrup) front tabs for cracks, and if a crack is discovered, removing 
the intermediate gearbox and replacing it with an airworthy 
intermediate gearbox; and inspecting for the conformity of the 
attachment parts. This proposal is prompted by five reports of failure 
of the two stirrup tabs. The actions specified by the proposed AD are 
intended to prevent failure of the intermediate gearbox stirrup front 
tabs, loss of anti-torque drive, and subsequent loss of control of the 
helicopter.

DATES: Comments must be received on or before May 7, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 98-SW-07-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. Comments may be inspected at this location 
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal 
holidays.
    The service information referenced in the proposed rule may be 
obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand 
Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-
3527. This information may be examined at the FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort 
Worth, Texas.

FOR FURTHER INFORMATION CONTACT: Mr. Scott Horn, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5125, 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, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice 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 comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 98-SW-07-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. 98-SW-07-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

Discussion

    The Direction Generale De L'Aviation Civile (DGAC), which is the 
airworthiness authority for France, recently notified the FAA that an 
unsafe condition may exist on Eurocopter France Model AS 332C, L, L1, 
and L2 helicopters with intermediate gearboxes, part number 332A35-0002 
all dash numbers, 332A35-0010 all dash numbers, and 332A35-0011-01, 
that have not been modified in accordance with MOD 0761049 or MOD 
0761050. The DGAC advises that cracks have

[[Page 16917]]

been discovered on the stirrup, and mandates visually inspecting the 
stirrup front tabs for cracks. If a crack is discovered, the DGAC 
mandates removing the intermediate gearbox and replacing it with an 
airworthy intermediate gearbox; and inspecting for the conformity of 
the attachment parts.
    Eurocopter France has issued Eurocopter France AS 332 Service 
Bulletin No. 01.00.47 Revision No. 1, dated September 10, 1997. The 
DGAC classified this service bulletin as mandatory and issued AD 96-
263-060(AB)R1 for Model AS 332C, L, and L1 helicopters, and AD 96-262-
004(AB)R1 for Model AS 332L2 helicopters, both dated November 5, 1997, 
in order to assure the continued airworthiness of these helicopters in 
France.
    This helicopter model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness 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 this type design that are 
certificated for operation in the United States.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Eurocopter France Model AS 332C, L, L1, and 
L2 helicopters of the same type design registered in the United States, 
the proposed AD would require visually inspecting the stirrup front 
tabs for cracks, and if a crack is discovered, removing the 
intermediate gearbox and replacing it with an airworthy intermediate 
gearbox; and inspecting for the conformity of the attachment parts. The 
actions would be required to be accomplished in accordance with the 
service bulletin described previously.
    The FAA estimates that 4 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 0.25 
work hours to inspect the tabs, and 3 work hours to inspect for 
conformity, and that the average labor rate is $60 per work hour. Based 
on these figures, the total cost impact of the proposed AD on U.S. 
operators is estimated to be $780.
    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    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. 98-SW-07-AD.

    Applicability: Model AS 332C, L, L1, and L2 helicopters, with 
intermediate gearboxes (IGB), part numbers (P/N) 332A35-0002 all 
dash numbers, 332A35-0010 all dash numbers, and 332A35-0011-01, 
installed, except those IGBs modified in accordance with MOD 0761049 
or MOD 0761050, 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 (c) 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 as indicated, unless accomplished 
previously.
    To prevent failure of the IGB-to-structure attachment stirrup 
(stirrup) front tabs, loss of anti-torque drive, and subsequent loss 
of control of the helicopter, accomplish the following:
    (a) Before the first flight of each day, perform a visual 
inspection of the stirrup front tabs for cracks in accordance with 
paragraph 2.B1) of the Accomplishment Instructions in Eurocopter 
France AS 332 Service Bulletin 01.00.47, Revision No. 1, dated 
September 10, 1997 (SB). If a crack is found, remove the IGB and 
replace it with an airworthy IGB before further flight. Completion 
of the conformity procedure contained in paragraph 2.B.2.1.3) of the 
SB is terminating action for the requirement of this AD to inspect 
for cracks prior to the first flight of each day.
    (b) Within 100 hours time-in-service (TIS), inspect the two 
front attaching assemblies securing the stirrup of the IGB to the 
angle bracket of the structure (attachment assembly) for thickness 
of the stirrup front tabs in accordance with paragraph 2.B.2) of the 
SB.
    (1) If the attachment assembly meets the conformity requirements 
of either paragraph 2.B.2.1.1) or 2.B.2.1.2) of the SB, reassemble 
the attachment assembly in accordance with paragraph 2.B.2.1.3) of 
the SB.
    (2) If the attachment assembly does not meet the conformity 
requirements of either paragraph 2.B.2.1.1) or 2.B.2.1.2) of the SB, 
replace it with an attachment assembly which does meet the 
conformity requirements of either of those paragraphs. Install the 
attachment assembly hardware in accordance with 2.B.2.1.3) of the 
SB.
    (3) If a crack is discovered in the stirrup front tabs as a 
result of the conformity inspection, remove the IGB and replace it 
with an airworthy IGB before further flight.
    (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, FAA, Rotorcraft Directorate, 
Rotorcraft Standards Staff. Operators shall submit their requests 
through an FAA Principal Maintenance Inspector, who may concur or 
comment and then send it to the Manager, Rotorcraft Standards Staff.

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

    (d) 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.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile

[[Page 16918]]

(France) AD 96-263-060(AB)R1 for Eurocopter France (ECF) Model AS 
332C, L, and L1 helicopters, and AD 96-262-004(AB)R1 for ECF Model 
AS 332L2 helicopters, both dated November 5, 1997.

    Issued in Fort Worth, Texas, on March 30, 1998.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-8989 Filed 4-6-98; 8:45 am]
BILLING CODE 4910-13-P