[Federal Register Volume 64, Number 215 (Monday, November 8, 1999)]
[Proposed Rules]
[Pages 60743-60744]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-29174]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-63-AD]


Airworthiness Directives; Eurocopter France Model SA. 315B 
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 SA. 
315B helicopters, that currently requires an initial and repetitive 
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, and would require an additional 
dye-penetrant inspection of the half-shell attachment clamps (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 7, 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-63-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: 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-63-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, 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, notified the FAA that an unsafe 
condition may exist on Eurocopter France Model SA. 315B helicopters. 
The DGAC advises that fatigue failure of the spar tube can result in 
separation of the horizontal stabilizer and impact with the main or 
tail rotor, and subsequent loss of control of the helicopter.
    Eurocopter France has issued Eurocopter France Service Bulletin No. 
55.01, Revision 4, dated May 4, 1998, which specifies initial and 
repetitive visual inspections, modification of the horizontal 
stabilizer spar tube if necessary, and a one-time dye penetrant 
inspection of the half shell attachment clamps with repetitive visual 
inspections of those clamps. The DGAC classified this service bulletin 
as mandatory and issued DGAC AD 96-277-037(A)R2, dated July 29, 1998, 
in order to assure the continued airworthiness of these helicopters in 
France.
    On June 2, 1998, the FAA issued AD 98-12-21, Amendment 39-10575 (63 
FR 31610), to require an initial and repetitive visual inspections and 
modification, if necessary, of the horizontal stabilizer 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 of the 
horizontal stabilizer and impact with the main or tail rotor, and 
subsequent loss of control of the helicopter.
    Since the issuance of that AD, the DGAC has advised that the clamps 
should be inspected for cracks and replaced if a crack is found. If no 
crack is found, a safety wire should be wrapped around each clamp so 
that the clamp is held together in the event of clamp failure.
    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 SA. 315B helicopters 
of the same type design, the proposed AD would supersede AD 98-12-21 to 
require an initial and repetitive visual inspections and modification, 
if necessary, of the spar tube, as well as installing safety wire 
around each attachment clamp.
    The FAA estimates that 28 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 
inspections;

[[Page 60744]]

     3 work hours per helicopter to accomplish the 
modification; and
     0.5 work hour per helicopter to inspect and fit the safety 
wire;
and that 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 $37,520.
    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 39-10575 (63 FR 
31610, June 10, 1998), and by adding a new airworthiness directive 
(AD), to read as follows:

Eurocopter France: Docket No. 98-SW-63-AD. Supersedes AD 98-12-21, 
Amendment 39-10575, Docket No. 98-SW-02-AD.

    Applicability: Model SA. 315B helicopters with horizontal 
stabilizers, part number (P/N) 315A35-10-000-1, 315A35-10-000-2, 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 
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 (f) 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, unless accomplished 
previously.
    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, 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. 55.01, Revision 4, 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 
Accomplishment Instructions 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) Within 90 calendar days and thereafter at intervals not to 
exceed 24 calendar months, visually inspect the inside of the 
horizontal spar tube in accordance with paragraph 2.A. and 2.B.1) of 
the Accomplishment Instructions 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 18 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 Accomplishment Instructions of the SB.
    (e) Within 30 calendar days, perform a one-time dye-penetrant 
inspection for cracking on the 4 attachment clamps (See No. 11 on 
Figure 3 of the SB) of the half-shells as shown in Figure 3 of the 
SB. If a crack is found in any clamp, replace the cracked clamp with 
an airworthy clamp. If no crack is found, safety wire the clamp as 
shown in Detail C in the SB using two wraps of 0.6-mm or 0.8 mm 
(.023 or .032 inch) diameter lockwire (See No. 21 on Figure 3 of the 
SB) around the clamp so that the clamp is held together in the event 
of clamp failure. After installing the safety wire, inspect the 
clamps before the first flight of each day in accordance with 
paragraph (b)(1) of this AD.
    (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 
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 96-277-037(A)R2, dated 
July 29, 1998.

    Issued in Fort Worth, Texas, on November 1, 1999.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-29174 Filed 11-5-99; 8:45 am]
BILLING CODE 4910-13-P