[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]
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