AD 2000-10-13

[Federal Register Volume 65, Number 99 (Monday, May 22, 2000)]
[Rules and Regulations]
[Pages 32018-32021]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-12817]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-86-AD; Amendment 39-11737; AD 2000-10-13]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA-365N, SA-
365N1, AS-365N2 and AS-365N3 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) 
applicable to Eurocopter France Model SA-365N, SA-365N1, AS-365N2 and 
AS-365N3 helicopters. This action requires inspecting the installation 
of each window panel on the enlarged sliding door (door). If any window 
panel is installed on the outside of the door, this AD requires 
installing and sealing the window panel on the inside. This amendment 
is prompted by the loss of a window panel in flight that was 
incorrectly sealed with the window installed on the outside of the 
door. This condition, if not corrected, could result in loss of a 
window panel in flight. The actions specified in this AD are intended 
to prevent loss of a window panel, impact with a main rotor blade, and 
subsequent loss of control of the helicopter.

DATES: Effective June 6. 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before July 21, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 99-SW-86-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. You may also send comments electronically to 
the Rules Docket at the following address: <a href="/cdn-cgi/l/email-protection#467f6b2735316b272225292b2b232832350620272768212930"><span class="__cf_email__" data-cfemail="4e77632f3d39632f2a2d2123232b203a3d0e282f2f60292138">[email&#160;protected]</span></a>.

FOR FURTHER INFORMATION CONTACT: Jim Grigg, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Regulations Group, Fort Worth, Texas 
76193-0111, telephone (817) 222-5490, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: The Direction Generale De L'Aviation Civile 
(DGAC), the airworthiness authority for France, notified the FAA that 
an unsafe condition may exist on Eurocopter France Model SA-365N, SA-
365N1, AS-365N2 and AS-365N3 helicopters. The DGAC advises of the need 
to visually inspect each window for correct mounting to prevent loss of 
a window in flight, impact with a main rotor blade, and subsequent loss 
of control of the helicopter.
    Eurocopter France has issued Telex Information No. 00097, dated 
November 9, 1999 (Telex). The Telex advises of the loss of a window 
panel in flight due to the window panel being sealed and positioned on 
the outside of the door. The Telex specifies visually inspecting the 
installation of each window panel and resuming flight if the window 
panels are inside the door. If the window panels are outside the door, 
the Telex specifies repositioning and resealing the window panels 
inside the door. The DGAC classified this Telex as mandatory and issued 
AD 1999-459-049(A), dated December 1, 1999, to ensure 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 these type designs 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-365N, SA-365N1, 
AS-365N2 and AS-365N3 helicopters of the same type designs registered 
in the United States, this AD is being issued to prevent loss of a 
window panel, impact with a main rotor blade, and subsequent loss of 
control of the helicopter. This AD requires visually inspecting each 
window panel for correct installation on the door. If the window panel 
is installed properly, no further action is required by this AD. If any 
window panel is installed outside the door, this AD also requires, 
before further flight, removing, installing inside the door, and 
resealing the window panel. The short compliance time involved is 
required because the previously described critical unsafe condition can 
adversely affect the structural integrity of the helicopter. Therefore, 
visually inspecting each window panel for correct installation on the 
door is required within 10 hours time-in-service and this AD must be 
issued immediately.

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    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 60 helicopters will be affected by this AD, 
that it will take approximately 0.25 work hour to accomplish the 
inspection and that the average labor rate is $60 per work hour. Based 
on these figures and assuming 10 windows are affected at $10 each for 
the seal and 1 hour to reinstall each window, the total cost impact of 
the AD on U.S. operators is estimated to be $1,600.

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 mailed 
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. 99-SW-86-AD.'' The postcard will be date 
stamped and returned to the commenter.
    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 2000-10-13  Eurocopter France: Amendment 39-11737. Docket No. 99-
SW-86-AD.

    Applicability: Model SA-365N, SA-365N1, AS-365N2, and AS-365N3 
helicopters, with enlarged sliding doors, part number (P/N) 365A82-
1142-0051, 0054, 0153, or 0154, 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 (b) 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 within 10 hours time-in-service (TIS), 
unless accomplished previously.
    To prevent loss of a window panel, impact with a main rotor 
blade, and subsequent loss of control of the helicopter, accomplish 
the following:
    (a) Visually inspect each window panel in any enlarged sliding 
door (door) for correct positioning on the inside of the door. See 
Figure 1.
    (1) If the window panel is installed on the inside of the door, 
no further action is required by this AD.
    (2) If a window is installed on the outside, before further 
flight, remove the window and reinstall using a new seal.

    Note 2: The following optional procedure may be used to remove 
and reinstall a window, however, any procedure that results in the 
installation of a properly sealed airworthy window panel on the 
inside of the door is acceptable:

    a. From inside the door, cut the seal (see Figure 1, item 3). 
Push the window out and remove remnants of the seal from the window 
panel and door structure.
    b. Remove all traces of the sealing compound (see Figure 1, item 
4) with methyl ethyl ketone (MEK), acetone, or equivalent.
    c. Thoroughly dust the grooves of a new seal with talcum powder.
    d. Fit the new seal to the window panel. The joint will be 
located in the lower center of the window panel. The clearance 
between the seal and the window panel should not exceed 0.04 inch.
    e. Insert a 0.01-inch diameter cord (ripcord works well) into 
the seal slot. Position the cord such that the cord ends are on the 
top center of the panel).
    f. Press the window panel and seal assembly against the door 
from the inside.
    g. Gently pull outward on the cord ends, allowing the outer edge 
of the seal to pull over the door structure. Continue pulling cord 
around the window panel until complete.
    h. Apply PR1222 sealant between the seal and the door structure. 
Wipe off any excess sealant.

    Note 3: Eurocopter Telex No. 00097, dated November 9, 1999, 
pertains to this AD.

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    (b) 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 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (c) 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.
    (d) This amendment becomes effective on June 6, 2000.

    Note 5: The subject of this AD is addressed in The Direction 
Generale De L'Aviation Civile (France) AD 1999-459-049(A), dated 
December 1, 1999.


    Issued in Fort Worth, Texas, on May 15, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-12817 Filed 5-19-00; 8:45 am]
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