[Federal Register Volume 63, Number 212 (Tuesday, November 3, 1998)]
[Proposed Rules]
[Pages 59252-59255]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-29378]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-SW-14-AD]


Airworthiness Directives; Eurocopter France Model SA. 315B, SA. 
316B, SA. 316C, SA. 319B, and SE. 3160 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 SA. 315B, 
SA. 316B, SA. 316C, SA. 319B, and SE. 3160 helicopters. This proposal 
would require inspecting the main rotor blade cuff attachment fitting 
in the area of the main rotor blade (blade) attachment bolts for 
cracks, and removing and replacing the blade if a crack is found. This 
proposal is prompted by a report of a crack in a main rotor blade cuff 
attachment fitting/spar assembly that was discovered during fatigue 
testing by the manufacturer. The actions specified by the proposed AD 
are intended to prevent failure of a main rotor blade cuff attachment 
fitting at a bolt hole location, loss of a main rotor blade, and 
subsequent loss of control of the helicopter.

DATES: Comments must be received on or before January 4, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 97-SW-14-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.

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. 97-SW-14-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. 97-SW-14-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 SA. 315B, SA. 
316B, SA. 316C, SA. 319B, and SE. 3160 helicopters. The DGAC advises 
that, within 400 operating hours, and thereafter at every 400 operating 
hours, a crack detection inspection of the main rotor blade cuff 
attachment fitting in the area of the main rotor blade attachment bolt 
holes must be performed. The DGAC issued AD 96-081-036(B)R1, applicable 
to Eurocopter France Model SA. 315B helicopters, and AD 96-082-54(B)R1 
applicable to Eurocopter France Model SA. 316B, SA. 316C, SA. 319B, and 
SE. 3160 helicopters, both dated April 24, 1996, in order to assure the 
continued airworthiness of these helicopters in France.
    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.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Eurocopter France Model SA. 315B, SA. 316B, 
SA. 316C, SA. 319B, and SE. 3160 helicopters of the same type design 
registered in the United States, the proposed AD would require 
inspecting the attachment fitting in the area of the blade attachment 
bolt holes for cracks, and removing and replacing any blade in which a 
crack is found.
    The FAA estimates that 83 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 2 work 
hours per helicopter to accomplish the proposed initial inspection and 
2 work hours per helicopter for each repetitive inspection, and that 
the average labor rate is $60 per work hour. Required parts would cost 
$40,000 per blade, if needed. Based on these figures, the total cost 
impact of the proposed AD on U.S. operators is

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estimated to be $49,960 for one inspection and one blade replacement 
for each helicopter per year.
    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. 97-SW-14-AD.

    Applicability: Model SA. 315B, SA. 316B, SA. 316C, SA. 319B, and 
SE. 3160 helicopters, with a main rotor blade, part number (P/N) 
316OS.11.10.000, 316OS.11.30.000, 316OS.11.35.000, 316OS.11.40.000, 
316OS.11.45.000, 316OS.11.50.000, or 316OS.11.55.000, 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 (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: (1) For blades with less than 400 hours time-in-
service (TIS), required prior to the accumulation of 400 hours TIS, 
unless accomplished previously, and thereafter at intervals not to 
exceed 400 hours TIS; or (2) for blades with 400 hours or more TIS, 
required within 50 hours TIS or 30 calendar days, whichever occurs 
first, unless accomplished previously, and thereafter at intervals 
not to exceed 400 hours TIS:
    To prevent failure of a main rotor blade (blade) cuff attachment 
fitting at a bolt hole location, loss of a blade, and subsequent 
loss of control of the helicopter, accomplish the following:
    (a) Inspect both upper and lower blade surfaces of each blade 
cuff for cracks (see Figure 1) as follows:
    (1) Use a mild liquid detergent or equivalent to remove all dirt 
from the blade cuff.
    (2) Inspect the blade cuff for cracks, paying particular 
attention to the area around the attaching bolts, using a 10-power 
or higher magnifying glass.
    (3) If a crack is suspected, remove any paint and clean the area 
under inspection using a Naptha-type solvent or equivalent, and 
conduct a dye penetrant inspection. Completely isolate the area 
under inspection with self-adhesive aluminum tape to prevent solvent 
or penetrating dye seepage into the other areas of the blade.
    (b) If a crack is detected, remove the blade and replace it with 
an airworthy blade.

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    (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, Rotorcraft Standards Staff, 
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, 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 (France) AD 96-081-036(B)R1 and AD 96-
082-054(B)R1, both dated April 24, 1996.

    Issued in Fort Worth, Texas, on October 27, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-29378 Filed 11-2-98; 8:45 am]
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