[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
