[Federal Register Volume 63, Number 54 (Friday, March 20, 1998)]
[Rules and Regulations]
[Pages 13510-13512]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-7230]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-SW-66-AD; Amendment 39-10418; AD 98-06-39]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS 332C, L, L1, 
and L2 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Eurocopter France Model AS 332C, L, L1, and L2 
helicopters. This action requires determining the thickness of the shim 
washers, inspecting certain cockpit door hinge tenons (hinge tenons) 
for cracks, and if a crack is found, replacing the hinge tenon with an 
airworthy hinge tenon. This amendment is prompted by several reports of 
cracked hinge tenons due to improper shimming. The actions specified in 
this AD are intended to detect cracks in the hinge tenons due to 
unintended loading of the improperly shimmed tenons caused by closing 
the door, which may lead to separation of the door from the helicopter, 
impact with the main rotor or tail rotor system, and subsequent loss of 
control of the helicopter.

DATES: Effective April 6, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 6, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before May 19, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 97-SW-66-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.
    The service information referenced in this AD 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; or 
at the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.


[[Page 13511]]


FOR FURTHER INFORMATION CONTACT: Mr. Mike Mathias, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5123, 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 332C, L, L1, and L2 helicopters. The DGAC advises that 
an inspection of the hinge tenons for cracks must be performed on 
helicopters that have washers of a certain thickness installed.
    Eurocopter France has issued Eurocopter AS 332 Service Bulletin No. 
01.00.50, dated August 5, 1997, which specifies an inspection of the 
hinge tenons for cracks on helicopters that have washers of a certain 
thickness installed. The DGAC classified this service bulletin as 
mandatory and issued AD 97-108-006(AB)R1 and AD 97-109-061(AB)R1, both 
dated April 23, 1997, in order to assure 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 
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 AS 332C, L, L1, and 
L2 helicopters of the same type design registered in the United States, 
this AD is being issued to detect cracks in the hinge tenons due to 
unintended loading caused by improper shimming of the tenons upon 
closing the door, which may lead to separation of the door from the 
helicopter, impact with the main rotor or tail rotor system, and 
subsequent loss of control of the helicopter. The actions are required 
to be accomplished in accordance with the service bulletin described 
previously.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability of the helicopter. Therefore, since the hinge tenons 
must be inspected and replaced prior to further flight if a crack is 
found, 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 4 helicopters of U.S. registry will be 
affected by this proposed AD, that it will take approximately 4 work 
hours to accomplish the inspection and installation (if needed), and 
that the average labor rate is $60 per work hour. Required parts will 
cost approximately $1,000 per helicopter. Based on these figures, the 
total cost impact of the proposed AD on U.S. operators is estimated to 
be $4,960.

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. 97-SW-66-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, Incorporation by 
reference, 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 98-06-39  Eurocopter France: Amendment 39-10418. Docket No. 97-
SW-66-AD.

    Applicability: Model AS 332C, L, L1, and L2 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 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For helicopters that have been modified, 
altered,

[[Page 13512]]

or repaired so that the performance of the requirements of this AD 
is affected, the owner/operator must use the authority provided in 
paragraph (b) 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: Required as indicated, unless accomplished 
previously.
    To detect cracks in the cockpit door hinge tenons (hinge tenons) 
due to unintended loading of the improperly shimmed tenons caused by 
closing the door, which may lead to separation of the door from the 
helicopter, impact with the main rotor or tail rotor system, and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Within 50 hours time-in-service (TIS), inspect the thickness 
of the shim washers and perform the following in accordance with 
Eurocopter Service Bulletin No. 01.00.50, dated August 5, 1997:
    (1) If the washers are equal to or less than 3 mm thick, perform 
the requirements of paragraph 2.B.1.1. and 2.B.2.
    (2) If the washers are more than 3 mm thick and equal to or less 
than 3.5 mm thick, perform the requirement of paragraph 2.B.1.2. and 
2.B.2.
    (3) If the washers are more than 3.5 mm thick, perform a dye 
penetrant inspection for cracks on the hinge tenon as specified in 
paragraph 2.B.1.3.
    (i) If a crack is found, before further flight, install an 
airworthy, zero hours TIS hinge tenon in accordance with the 
requirements of paragraph 2.B.1.3. and 2.B.2.
    (ii) If the hinge tenon is determined to be airworthy and is 
reinstalled, remove and replace the reinstalled hinge tenon with an 
airworthy, zero hours TIS hinge tenon within 500 hours TIS, in 
accordance with paragraph 2.B.1.3. and 2.B.2.
    (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, 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.

    (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) The inspections and replacement shall be done in accordance 
with Eurocopter Service Bulletin No. 01.00.50, dated August 5, 1997. 
This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from American Eurocopter Corporation, 
2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 
641-3460, fax (972) 641-3527. Copies may be inspected at the FAA, 
Office of the Regional Counsel, Southwest Region, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas 76137; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.
    (e) This amendment becomes effective on April 6, 1998.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 97-108-006(AB)R1 and AD 
97-109-061(AB)R1, both dated August 27, 1997.

    Issued in Fort Worth, Texas, on March 12, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-7230 Filed 3-19-98; 8:45 am]
BILLING CODE 4910-13-U