[Federal Register Volume 64, Number 222 (Thursday, November 18, 1999)]
[Proposed Rules]
[Pages 62988-62990]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-30147]


 ========================================================================
 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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 

  Federal Register / Vol. 64, No. 222 / Thursday, November 18, 1999 / 
Proposed Rules  

[[Page 62988]]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-65-AD]


Airworthiness Directives; Eurocopter France Model SE 3130, SA 
3180, SE 313B, SA 318B, and SA 318C Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to Eurocopter France Model SE 
3130, SA 3180, SE 313B, SA 318B, and SA 318C helicopters. The existing 
AD currently requires visual inspections and modification, if 
necessary, of the horizontal stabilizer spar tube (spar tube). This 
action would require the same corrective actions as the existing AD but 
would also require visually inspecting the four half-shell attachment 
clamps for cracks and fitting a safety wire around the attachment 
clamps. 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 of the horizontal stabilizer and impact with the main or 
tail rotor, and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before January 18, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 98-SW-65-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; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: 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-65-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-65-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

Discussion

    On June 2, 1998, the FAA issued AD 98-12-20, Amendment 39-10574 (63 
FR 31350, June 9, 1998), to require initial and repetitive visual 
inspections and modification, if necessary, of the spar tube. That 
action was prompted by an in-service report of fatigue cracks that 
initiated from corrosion pits. The requirements of that 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.
    Since the issuance of that AD, Eurocopter France has issued 
Eurocopter France SA3130/3180 Service Bulletin No. 55.10, Revision 3, 
dated May 4, 1998, which specifies a visual inspection of the spar 
tube, inspection and modification of the stabilizer supports, 
modification of the stabilizer, visually inspecting the four attachment 
clamps for cracking, and fitting a lockwire around the four attachment 
clamps.
    The Direction Generale De L'Aviation Civile (DGAC), which is the 
airworthiness authority for France, has notified the FAA that an unsafe 
condition may exist on Eurocopter France Model SE 3130, SA 3180, SE 
313B, SA 318B, and SA 318C helicopters. The DGAC advises that improving 
the horizontal stabilizer fatigue strength is necessary in these model 
helicopters and has issued AD 96-278-054(A)R2, dated July 29, 1998.
    These helicopter models are manufactured in France and are 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.

[[Page 62989]]

    Since an unsafe condition has been identified that is likely to 
exist or develop on other Eurocopter France Model SE 3130, SA 3180, SE 
313B, SA 318B, and SA 318C helicopters of the same type design, this 
proposed AD would supersede AD 98-12-20 to require the same actions 
required by that AD but would also require visually inspecting the four 
half-shell attachment clamps for cracks, replacing any cracked 
attachment clamp, and fitting a safety wire around the attachment 
clamps.

Cost Impact

    The FAA estimates that 14 helicopters of U.S. registry would be 
affected by this proposed AD. It would take approximately 0.5 work hour 
per helicopter to accomplish the inspection, 3 work hours per 
helicopter to accomplish the modification, and 1 work hour to 
accomplish the attachment clamp inspection and to install the safety 
wire. The average labor rate is $60 per work hour. Required parts would 
cost approximately $1,100 per helicopter. Based on these figures, the 
total cost impact of the proposed AD on U.S. operators is estimated to 
be $19,180.

Regulatory Impact

    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 removing Amendment 39-10574 (63 FR 
31350, June 9, 1998), and by adding a new airworthiness directive (AD), 
to read as follows:

Eurocopter France: Docket No. 98-SW-65-AD. Supersedes AD 98-12-20, 
Amendment 39-10574, Docket No. 98-SW-03-AD.

    Applicability: Model SE 3130, SA 3180, SE 313B, SA 318B, and SA 
318C helicopters with horizontal stabilizer, part number (P/N) 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 (g) 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), separation of the horizontal stabilizer and impact 
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 
to determine whether Modification 072214 (installing 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 SA3130/3180 Service 
Bulletin No. 55.10, Revision 3, dated May 4, 1998 (SB). 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 SB.

    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 SB. 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 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 SB.
    (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 SB.
    (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, 3,200 hours total 
TIS, or 144 calendar months 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 SB.
    (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 SB.
    (f) Within 30 calendar days, visually inspect the four 
attachment clamps of the half-shells and install a safety wire 
around the four attachment clamps in accordance with paragraph 
2.B.2)d) of the SB. If any attachment clamp is found cracked, 
replace it with an airworthy attachment clamp and

[[Page 62990]]

install a safety wire around the replacement attachment clamp before 
further flight.
    (g) 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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (h) 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 4: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 96-278-054(A)R2, dated 
July 29, 1998.

    Issued in Fort Worth, Texas, on November 10, 1999.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-30147 Filed 11-17-99; 8:45 am]
BILLING CODE 4910-13-P