[Federal Register Volume 63, Number 76 (Tuesday, April 21, 1998)]
[Proposed Rules]
[Pages 19668-19670]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-10460]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-03-AD]


Airworthiness Directives; Eurocopter France Model SE3130, SA3180, 
SE313B, SA318B, and SA318C 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 SE3130, 
SA3180, SE313B, SA318B, and SA318C helicopters. This proposal would 
require initial and repetitive visual inspections and modification, if 
necessary, of the horizontal stabilizer spar tube (spar tube). This 
proposal is prompted by an in-service report of fatigue cracks that 
initiated from corrosion pits. The actions specified by the proposed AD 
are intended to prevent fatigue failure of the spar tube, separation 
and impact of the horizontal stabilizer with the main or tail rotor, 
and subsequent loss of control of the helicopter.


[[Page 19669]]


DATES: Comments must be received on or before May 21, 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-03-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. Richard Monschke, Aerospace 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5116, 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-03-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-03-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 SE3130, SA3180, 
SE313B, SA318B, and SA318C helicopters. The DGAC advises that fatigue 
failure of the spar tube can result in separation and impact of the 
horizontal stabilizer with the main or tail rotor and subsequent loss 
of control of the helicopter.
    Eurocopter France has issued Eurocopter France Service Bulletin No. 
55.10, Revision 2, dated April 25, 1997, which specifies visual 
inspections of the spar tube for corrosion until a modified spar tube 
is installed, and visual inspections of the spar tube at specified time 
intervals. The DGAC classified this service bulletin as mandatory and 
issued DGAC AD 96-278-054(B)R1, dated May 21, 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 
Sec. 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 SE3130, SA3180, 
SE313B, SA318B, and SA318C helicopters of the same type design 
registered in the United States, the proposed AD would require an 
initial and repetitive inspections and modification, if necessary, of 
the spar tube. The actions would be required to be accomplished in 
accordance with the service bulletin described previously.
    The FAA estimates that 14 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 0.5 work 
hour per helicopter to accomplish the inspection and 3 work hours per 
helicopter to accomplish the modification, and that the average labor 
rate is $60 per work hour. Required parts would cost approximately 
$1100 per helicopter. Based on these figures, the total cost impact of 
the proposed AD on U.S. operators is estimated to be $1310 per 
helicopter.
    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-03-AD.

    Applicability: SE3130, SA3180, SE313B, SA318B, and SA318C 
helicopters with horizontal stabilizer, part number (P/N)

[[Page 19670]]

3130-35-60-000, 3130-35-60-000-1, 3130-35-60-000-2, 3130-35-60-000-
3, 3130-35-60-000-4 or higher dash numbers, 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 use the authority 
provided in paragraph (e) 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 fatigue failure of the horizontal stabilizer spar 
tube (spar tube), impact of the horizontal stabilizer with the main 
or tail rotor and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Before further flight:
    (1) Inspect the aircraft records and the horizontal stabilizer 
installation to determine whether Modification 072214 (installation 
of the spar tube without play) or Modification 072215 (adding two 
half-shells on the spar) has been accomplished.
    (2) If Modification 072214 has not been installed, comply with 
paragraphs 2.A., 2.B.1), 2.B.2)a), and 2.B.2)b) of the 
Accomplishment Instructions of Eurocopter France Service Bulletin 
No. 55.10, Revision 2, dated April 25, 1997 (service bulletin). If 
the fit and dimensions of the components specified in paragraph 
2.B.2)a) exceed the tolerances in the applicable structural repair 
manual, replace with airworthy parts.
    (3) If Modification 072215 has not been installed, first comply 
with paragraphs 2.A., 2.B.1), and 2.B.3), and then comply with 
paragraph 2.B.2)c) of the Accomplishment Instructions of the service 
bulletin.

    Note 2: Modification kit P/N 315A-07-0221571 contains the 
necessary materials to accomplish this modification.

    (b) Before the first flight of each day:
    (1) Visually inspect the installation of the half-shells, the 
horizontal stabilizer supports, and the horizontal stabilizer for 
corrosion or cracks. Repair any corroded parts in accordance with 
the applicable maintenance manual. Replace any cracked components 
with airworthy parts before further flight.
    (2) Confirm that there is no play in the horizontal stabilizer 
supports by lightly shaking the horizontal stabilizer. If play is 
detected, comply with paragraphs 2.A. and 2.B.2)a) of the service 
bulletin. If the fit and dimensions of the components specified in 
paragraph 2.B.2)a) exceed the tolerances in the applicable 
structural repair manual, replace with airworthy parts before 
further flight.
    (c) At intervals not to exceed 400 hours time-in-service (TIS) 
or four calendar months, whichever occurs first, inspect and 
lubricate the spar tube attachment bolts.
    (d) For stabilizers, P/N 3130-35-60-000, 3130-35-60-000-1, 3130-
35-60-000-2, or 3130-35-60-000-3, within 90 calendar days and 
thereafter at intervals not to exceed 18 calendar months, visually 
inspect the inside of the horizontal spar tube in accordance with 
paragraph 2.A. and 2.B.)1) of the service bulletin.
    (1) If corrosion is found inside the tube, other than in the 
half-shell area, replace the tube with an airworthy tube within the 
next 500 hours TIS or 24 calendar months, whichever occurs first.
    (2) If corrosion is found inside the tube in the half-shell 
area, apply a protective treatment as described in paragraph 
2.B.1)b) of the service bulletin.
    (e) For stabilizers, P/N 3130-35-60-000-4 or higher dash 
numbers, accomplish the following:
    (1) At or before the next major inspection, 3200 hours total 
TIS, or 12 calendar years total TIS, whichever occurs first, and 
thereafter at each major inspection, visually inspect the inside of 
the horizontal spar tube in accordance with paragraph 2.A. and 
2.B.1) of the service bulletin.
    (2) If corrosion is found inside the tube, other than in the 
half-shell area, replace the tube with an airworthy tube within the 
next 500 hours TIS or 18 calendar months, whichever occurs first. If 
corrosion is found inside the tube in the half-shell area, apply a 
protective treatment as described in paragraph 2.B.1)b) of the 
service bulletin.
    (f) 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, Rotorcraft Standards Staff, FAA, 
Rotorcraft Directorate. 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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Standards Staff.

    (g) Special flight permits may be issued in accordance with 
Secs. 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 4: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 96-278-054(B)R1, dated May 
21, 1997.

    Issued in Fort Worth, Texas, on April 14, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-10460 Filed 4-20-98; 8:45 am]
BILLING CODE 4910-13-U