Airworthiness Directives; Eurocopter France Model AS332L2 Helicopters

[Federal Register Volume 66, Number 124 (Wednesday, June 27, 2001)]
[Rules and Regulations]
[Pages 34106-34108]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-15792]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-04-AD; Amendment 39-12271; AD 2001-12-16]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS332L2 
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 AS332L2 helicopters. This AD requires, at 
specified time intervals, visually inspecting the main rotor blade 
sleeve yoke (sleeve) for cracks, corrosion, fretting, or bonding 
separation; the bearing surface of the metal bushing (bushing) for 
fretting or cracks; and the sleeve-to-damper attachment bolt (bolt) for 
corrosion and deterioration of the fluorimid varnish coating. Replacing 
any cracked or nonairworthy sleeve, bushing, or bolt is also required 
before further flight. This AD is prompted by the discovery of 
extensive deterioration of the fluorimid varnish coating on the bolt; 
cracks in the bushing; and fretting and corrosion of the sleeve. The 
actions specified in this AD are intended to detect corrosion and 
cracks in the yoke, which could result in separation of the blade 
damper assembly and subsequent loss of control of the helicopter.

DATES: Effective July 12, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 12, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before August 27, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-04-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: [email protected].
    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, Room 663, Fort Worth, Texas; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, Washington, 
DC.

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), which is the airworthiness authority for France, notified the 
FAA that an unsafe condition may exist on Eurocopter France Model 
AS332L2 helicopters. The DGAC advises that cracks in the yokes of the 
damper attachment sleeves may result in loss of the damper attachment 
and the occurrence of vibrations, leading to loss of control of the 
helicopter.
    Eurocopter issued Eurocopter Service Bulletin No. 05.00.53, 
Revision 1, dated July 6, 1999, which specifies checking the sleeve 
yoke for cracks and the damper attachment for damage. The DGAC 
classified this service bulletin as mandatory and issued AD No. 1999-
260-014(A) R1, dated July 13, 1999, 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 
section 21.29 of the Federal Aviation

[[Page 34107]]

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.
    None of the Eurocopter France Model AS332L2 helicopters affected by 
this AD are on the U.S. Register. All helicopters included in the 
applicability of this AD are currently operated by non-U.S. operators 
under foreign registry; therefore, they are not directly affected by 
this AD action. However, the FAA considers that this rule is necessary 
to ensure that the unsafe condition is addressed in the event that any 
of these subject helicopters are imported and placed on the U.S. 
Register in the future.
    Should an affected helicopter be imported and placed on the U.S. 
Register in the future, it will require approximately 1 work hour per 
helicopter to inspect the sleeve, and either 10 work hours per 
helicopter to remove, inspect, and reinstall the current damper 
attachment bolt and bushing or 10 work hours to remove, inspect, and 
install a replacement damper attachment bolt and bushing or the sleeve 
if the current parts are damaged. The average labor rate is $60 per 
work hour. Required parts will cost approximately $54,549 per blade 
($54,305 for a sleeve and $244 for a bolt). Based on these figures, the 
total cost impact of the AD on U.S. operators is estimated to be 
$55,209 for each helicopter, assuming each imported helicopter would 
require one new sleeve and one new bolt and bushing.
    The FAA has identified an unsafe condition that is likely to exist 
or develop on other Eurocopter France Model AS332L2 helicopters of the 
same type design, which may become registered in the United States. 
This AD is being issued to detect corrosion and cracks in the sleeve, 
which could result in separation of the blade damper assembly and 
subsequent loss of control of the helicopter. This AD requires, at 
specified time intervals, visually inspecting the sleeve for cracks, 
corrosion, fretting, or bonding separation; the bearing surface of the 
bushing for fretting or cracks; and the bolt for corrosion and 
deterioration of the fluorimid varnish coating. Replacing any cracked 
or non-airworthy sleeve, bushing, or bolt would also be required before 
further flight. The actions must be accomplished in accordance with the 
service bulletin described previously.
    Since this AD action does not affect any helicopter that is 
currently on the U.S. register, it has no adverse economic impact and 
imposes no additional burden on any person. Therefore, notice and 
public procedures hereon are unnecessary, and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

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 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. 2001-SW-04-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 notice and prior public comment are 
unnecessary in promulgating this regulation; therefore, it can be 
issued immediately to correct an unsafe condition in aircraft since 
none of these model helicopters are registered in the United States. 
The FAA has also determined that this regulation 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:

2001-12-16  Eurocopter France: Amendment 39-12271. Docket No. 2001-
SW-04-AD.

    Applicability: Model AS332L2 helicopters, with main rotor hub 
sleeve, part number (P/N) 332A31-1860-03 or -04, and sleeve-to-drag 
damper attachment bolt, P/N 332A31-1961-20, 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 (c) of 
this AD. The request should include an assessment of

[[Page 34108]]

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 as indicated, unless accomplished 
previously.
    To detect corrosion on a sleeve-to-blade damper attachment bolt 
(bolt) or a crack on the main rotor blade sleeve yoke (sleeve) and 
to prevent failure of the damper attachment and subsequent loss of 
control of the helicopter, accomplish the following:
    (a) For sleeves with 175 or less hours time-in-service (TIS), 
before accumulating 275 hours TIS, and thereafter at intervals not 
to exceed 275 hours TIS, remove the sleeve-to-blade-damper assembly 
in accordance with paragraph 2.B.2 of the Accomplishment 
Instructions in Eurocopter Service Bulletin No. 05.00.53, Revision 
1, dated July 6, 1999 (SB), and inspect in accordance with 
paragraphs 2.B.2.1, 2.B.2.2, and 2.B.2.3 of the SB. Returning a 
sleeve to the manufacturer is not required by this AD. Replace any 
unairworthy part before further flight.
    (b) For sleeves with more than 175 hours TIS that have not 
complied with paragraph (a) of this AD, before the first flight of 
each day, visually inspect the sleeve for a crack in accordance with 
paragraph 2.B.1 of the SB. Replace any cracked sleeve with an 
airworthy sleeve before further flight. Within the next 100 hours 
TIS and thereafter at intervals not to exceed 275 hours TIS, remove 
the sleeve-to-blade-damper assembly in accordance with paragraph 
2.B.2 of the SB, and inspect in accordance with paragraphs 2.B.2.1, 
2.B.2.2, and 2.B.2.3 of the SB. Returning a sleeve to the 
manufacturer is not required by this AD. Replace any unairworthy 
part before further flight.
    (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, 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.

    (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.
    (e) Removing the sleeve-to-blade damper assembly and inspecting 
the sleeve shall be done in accordance with the Accomplishment 
Instructions, paragraphs 2.B.1, 2.B.2, 2.B.2.1, 2.B.2.2, and 
2.B.2.3, of Eurocopter Mandatory Service bulletin No. 05.00.53, 
Revision 1, dated July 6, 1999. 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. This 
information may be examined at the FAA, Office of the Regional 
Counsel, Southwest Region, Room 663, Fort Worth, Texas; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC. Copies may be inspected 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.
    (f) This amendment becomes effective on July 12, 2001.

    Note 3: The subject of this AD is addressed in Direction 
Generale de L'Aviation Civile (France) AD No. 1999-260-014(A) R1, 
dated July 13, 1999.


    Issued in Fort Worth, Texas, on June 8, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-15792 Filed 6-26-01; 8:45 am]
BILLING CODE 4910-13-U

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