AD 2000-17-07

[Federal Register Volume 65, Number 167 (Monday, August 28, 2000)]
[Rules and Regulations]
[Pages 52012-52015]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-21870]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-33-AD; Amendment 39-11881; AD 2000-17-07]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model EC120B 
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) for 
Eurocopter France Model EC120B helicopters. This action requires 
adjusting the clearance of the cabin sliding door if necessary. This 
amendment is prompted by an in-flight loss of a cabin sliding door, 
which had been locked in the fully opened position. The actions 
specified in this AD are intended to prevent in-flight loss of a cabin 
sliding door, impact with the horizontal stabilizer, main rotor, or 
fenestron tail rotor, and subsequent loss of control of the helicopter.

DATES: Effective September 12, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before October 27, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-33-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#1d24307c6e6a307c797e7270707873696e5d7b7c7c337a726b"><span class="__cf_email__" data-cfemail="675e4a0614104a060304080a0a020913142701060649000811">[email&#160;protected]</span></a>. 
Comments may be inspected at the Office of the Regional Counsel between 
9 a.m. and 3 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Richard Monschke, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort 
Worth, Texas 76193-0110, telephone (817) 222-5116, 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 EC120B 
helicopters. The DGAC advises that the cabin sliding door must be 
adjusted, if necessary, to prevent in-flight loss of the cabin sliding 
door.
    Eurocopter France has issued Service Telex No. 05-005, dated June 
30, 2000, which specifies adjusting any cabin sliding door if a roller 
is not completely inside its rail with a minimum clearance of 3 mm. 
Eurocopter France received a report of an in-flight loss of the cabin 
sliding door. An investigation shows that the loss of the door was due 
to the forward upper roller being out of its guide rail. The door edge 
thus exposed to the slipstream caused the forward lower roller train to 
be driven out of the guide rail due to the aerodynamic loads. The door 
aft hinges failed, and the door departed from the aircraft. The DGAC 
classified this service telex as mandatory and issued AD T2000-285-
005(A), dated June 30, 2000, to ensure the continued airworthiness of 
these helicopters in France.
    This helicopter model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
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.
    We have identified an unsafe condition that is likely to exist or 
develop on other Eurocopter France Model EC120B helicopters of the same 
type design registered in the United States. This AD is being issued to 
prevent in-flight loss of a cabin sliding door, impact with the 
horizontal stabilizer, main rotor, or fenestron tail rotor, and 
subsequent loss of control of the helicopter. This AD requires 
adjusting the clearance of any cabin sliding door to a minimum of 3 mm 
from the aft end of the rail. The short compliance time involved is 
required because the previously described critical unsafe condition can 
adversely affect the structural integrity and controllability of the 
helicopter. Therefore, adjusting the clearance of the cabin sliding 
door to a minimum of 3 mm from the aft end of the rail is required 
before further flight with the door in the open position 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 24 helicopters will be affected by this AD, 
that it will take approximately 0.25 work hours to adjust the cabin 
sliding door, and that the average labor rate is $60 per work hour. 
Based on these figures, the total cost impact of the AD on U.S. 
operators is estimated to be $360.

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. 2000-SW-

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33-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:

2000-17-07  Eurocopter France: Amendment 39-11881. Docket No. 2000-
SW-33-AD.

    Applicability: Model EC120B helicopters, 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 before further flight with the cabin 
sliding door in the open position or within 60 days, whichever 
occurs first, unless accomplished previously, and prior to further 
flight after installing a cabin sliding door.
    To prevent in-flight loss of a cabin sliding door, impact with 
the horizontal stabilizer, main rotor, or fenestron tail rotor, and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Adjust the cabin sliding door (23) (see Figure 1) in 
accordance with the following:
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    (1) Loosen the screws (19) and the stop (15).
    (2) Open and push the cabin sliding door aft until the roller 
goes past the locking pin (13) while keeping the roller (21) inside 
the rail (12).
    (3) Move the cabin sliding door forward to bring the roller (21) 
into contact with the locking pin (13).
    (4) Move the stop (15) as far forward as possible toward the 
nose of the aircraft.
    (5) Mark the location of the stop (15) with respect to the rail 
(14).
    (6) Unlock the cabin sliding door and move it forward to gain 
access to the screws (19).
    (7) Hold the stop (15) aligned with the rail (14), and secure 
the stop (15) and the screws (19) at the location previously marked.
    (8) Ensure that the pin (13) locking mechanism (pin) locks the 
cabin sliding door in the open position. If the pin does not lock 
the door in the open position, before further flight, repair or 
replace the pin with an airworthy pin.
    (9) Bring the roller (22) into contact with the stop (15) of the 
rail (14).
    (10) If the roller (21) is completely inside the rail (12) with 
a minimum clearance of 3 mm from the aft end of the rail (12), the 
cabin door is properly adjusted and no further action is required by 
this AD.
    (11) If the roller (21) is less than 3 mm from the aft end of 
the rail (12), before further flight, repeat steps (1) through (10) 
until a minimum clearance of 3 mm is obtained.
    (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 2: 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 14 
CFR 21.197 and 21.199 to operate the helicopter with the sliding 
cabin door closed or removed to a location where the requirements of 
this AD can be accomplished.
    (d) This amendment becomes effective on September 12, 2000.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD T2000-285-005(A), dated 
June 30, 2000.


    Issued in Fort Worth, Texas, on August 21, 2000.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-21870 Filed 8-25-00; 8:45 am]
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