[Federal Register Volume 63, Number 228 (Friday, November 27, 1998)]
[Rules and Regulations]
[Pages 65548-65552]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-31589]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-05-AD; Amendment 39-10918; AD 98-24-32]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS-365N2, SA-
360C, SA-365C, C1, C2, N, N1, and SA-366G1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Eurocopter France Model AS-365N2, SA-360C, SA-365C, 
C1, C2, N, N1, and SA-366G1 helicopters. This action requires 
inspecting for broken or out-of-tolerance attachment springs on the 
tail rotor hub fairing (fairing), replacing broken attachment springs 
and attachment springs that are out-of-tolerance, and marking the 
fairing to indicate compliance with this AD. This amendment is prompted 
by three in-service reports of failed attachment springs. The actions 
specified in this AD are intended to prevent failure of an attachment 
spring, which could cause loss of the fairing, damage to the tail 
rotor, and subsequent loss of control of the helicopter.

DATES: Effective December 14, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before January 26, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 98-SW-05-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

FOR FURTHER INFORMATION CONTACT: Mr. Shep Blackman, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817) 
222-5961.

SUPPLEMENTARY INFORMATION: 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 AS-365N2, SA-360C, SA-365C, C1, C2, N, N1, and SA-366G1 
helicopters. The DGAC advises that inspecting for broken or out-of-
tolerance attachment springs on the fairing, replacing broken 
attachment springs and attachment

[[Page 65549]]

springs that are out-of-tolerance, and marking the fairing are 
necessary due to reports of broken attachment springs.
    Eurocopter France has issued SA-360C, SA-365C, C1, C2 Service 
Bulletin No. 01.34, dated 96-14(N); SA-365N Service Bulletin No. 
01.00.43, dated 96-14(N); SA-365N1, AS-365N2 Service Bulletin No. 
01.00.42, dated 96-14(N), and SA-366G1 Service Bulletin No. 01.22, 
dated 96-14(N). These service bulletins specify several actions 
regarding the fairing and attachment springs. The DGAC classified these 
service bulletins as mandatory and issued AD 95-107-039(B)R1 and AD 95-
112-040(B), both dated June 7, 1995, and AD 95-108-018(B), dated May 
24, 1995, 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 previously described. 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 Model AS-365N2, SA-360C, SA-365C, C1, C2, N, 
N1, and SA-366G1 helicopters of the same type design registered in the 
United States, this AD is being issued to prevent failure of the 
attachment springs which could cause loss of the tail rotor hub 
fairing, damage to the tail rotor, and subsequent loss of control of 
the helicopter. This AD requires inspecting for broken or out-of-
tolerance attachment springs on the fairing, replacing broken 
attachment springs and those that are out-of-tolerance, and marking the 
fairing with an ``X'' by the fairing part number to indicate 
compliance.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability of the helicopter. Therefore, the inspections, 
replacement, and marking are required prior to further flight, and this 
AD must be issued immediately.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.
    The FAA estimates that 135 helicopters of U.S. registry will be 
affected by this AD, that it will take 1.5 work hours per helicopter to 
accomplish the actions, and that the average labor rate is $60 per work 
hour. Required parts will cost approximately $988 per helicopter. Based 
on these figures, the total cost impact of this AD on U.S. operators is 
estimated to be $145,530.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 98-SW-05-AD.'' The postcard will be date stamped and 
returned to the commenter.
    The regulations adopted herein will 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, may be obtained from 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.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 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:

AD 98-24-32 Eurocopter France: Amendment 39-10918. Docket No. 98-SW-
05-AD.

    Applicability: Model AS-365N2, SA-360C, SA-365C, C1, C2, N, N1, 
and SA-366G1, 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

[[Page 65550]]

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 failure of an attachment spring (spring), which could 
cause loss of the tail rotor hub fairing (fairing), damage to the 
tail rotor, and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Before further flight with fairing, part number (P/N) 
360A33-1079-01, installed, that has modification 365A07-64B20 
incorporated but is not marked with an ``X'' after the part number:
    (1) Remove the six fairing attachment bolts (bolts), then remove 
the fairing from the helicopter.
    (2) Inspect for broken springs, especially in the rounded 
sections at the rotor hub groove (Point A, Figure 1).

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    (3) If any broken springs are discovered, replace them with 
airworthy springs using the procedure specified in paragraph (b) of 
this AD.
    (4) Lubricate the threads with NATO 156 oil, then reinstall the 
six bolts, torqued to 0.4-0.5 m.daN (35.3-44.2 in.-lbs.).
    (5) Inspect for interference between the spring and the fairing 
(Point B, Figure 2), and replace any spring that exhibits such 
interference in accordance with the procedure specified in paragraph 
(b) of this AD.
    (6) Measure the outward axial protrusion (Dimension e, Figure 
1), for each spring. If the protrusion dimension obtained from the 
measurement required by paragraph (a)(6) of this AD is less than 1mm 
(0.039-inches), or greater than 2.7mm (0.106 inches), either
    (i) replace the spring with an airworthy spring before further 
flight or,
    (ii) Inspect the out-of-tolerance spring(s) in accordance with 
paragraph (a)(2) before the first flight of each day until each 
spring is replaced with an airworthy spring. Any out-of-tolerance 
spring must be replaced with an airworthy spring within 25 hours 
time-in-service (TIS).
    (b) Replace a broken or out-of-tolerance spring as follows:
    (1) Remove the spring attachment rivet.
    (2) Temporarily install an airworthy spring, P/N 360A33-1078-01, 
and verify that the axial protrusion (Dimension e, Figure 1) is 
within tolerance and that no interference (see Figure 2) exists.
    (3) Permanently secure the new spring to the fairing with one 
ASN-A0078B402 rivet, coated with Mastinox 6856KD150-2, and installed 
with the rivet head on the outside of the fairing (see Figure 1).
    (4) Mark an ``X'' after the fairing part number using indelible 
ink after completing all inspections and spring replacements, as 
required.
    (c) Reinstall the fairing.
    (d) If one or more springs are replaced, rebalance the tail 
rotor head.
    (e) 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.

    (f) Special flight permits will not be issued.
    (g) This amendment becomes effective on December 14, 1998.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 95-107-039(B)R1 and AD 95-
112-040(B), both dated June 7, 1995, and AD 95-108-018(B), dated May 
24, 1995.

    Issued in Fort Worth, Texas, on November 19, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-31589 Filed 11-25-98; 8:45 am]
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