[Federal Register: June 14, 2004 (Volume 69, Number 113)]
[Rules and Regulations]
[Page 32857-32859]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14jn04-7]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2004-SW-05-AD; Amendment 39-13665; AD 2004-12-06]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model EC 155 B and B1
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 (Eurocopter) Model EC 155 B and B1 helicopters. This
action requires inspecting each main
[[Page 32858]]
rotor blade (blade) for a crack in the blade tip cap mounting bracket
(tenon), measuring the vertical clearance between each blade assembly
and a straight edge at the blade-to-tip cap junction, and replacing the
blade if a crack is found or if the measured distance is not within
certain specifications. This amendment is prompted by the discovery of
a crack in a tenon. This condition, if not detected, could result in
loss of the tip cap, which could lead to severe vibration and loss of
control of the helicopter.
DATES: Effective June 29, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 29, 2004.
Comments for inclusion in the Rules Docket must be received on or
before August 13, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 2004-SW-05-AD, 2601 Meacham Blvd., Room
663, Fort Worth, Texas 76137. You may also send comments electronically
to the Rules Docket at the following address: 9-asw-adcomments@faa.gov.
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 National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-741-
6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
FOR FURTHER INFORMATION CONTACT: Charles Harrison, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Safety Management Group, Fort
Worth, Texas 76193-0111, telephone (817) 222-5128, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for the
Eurocopter Model EC 155 B and B1 helicopters. This action requires:
For blades with 100 or less hours time-in-service (TIS),
prior to reaching 110 hours TIS, inspecting the tenon for a crack, and
replacing the blade if a crack is found in the tenon;
For blades with more than 100 hours TIS, within the next
10 hours TIS, inspecting the tenon for a crack, and replacing the blade
if a crack is found in the tenon;
After accomplishing the initial inspection for a crack as
described above, before further flight, establishing the baseline
clearance (``DO'') between a straight edge and the upper surface of the
blade assembly at the blade-to-tip cap junction; and
Thereafter, before the first flight of each day and on or
before reaching each 10 hours TIS interval during the day, measuring
the clearance between the straight edge and the upper surface of the
blade assembly of the blade-to-tip cap junction. If the measured
distance is equal to or greater than ``DO'' + 2mm, replacing the blade
is required.
This amendment is prompted by a report of a crack that was
discovered on a tenon. This condition, if not detected, could result in
loss of the blade tip cap, which could lead to severe vibration and
loss of control of the helicopter.
The Direction Generale De L'Aviation Civile (DGAC), the
airworthiness authority for France, notified the FAA that an unsafe
condition may exist on Eurocopter EC 155 B and B1 helicopters. The DGAC
advises of the discovery of a crack in a blade tenon, the growth of
which could lead to the loss of the tip cap and make the helicopter
impossible to control.
Eurocopter has issued Alert Telex No. 05A004, dated November 3,
2003, which specifies checks on each blade to ensure that there is no
crack in the tenon to which the blade tip is attached. The DGAC
classified this alert telex as mandatory and issued AD No. F-2003-418,
dated December 24, 2003, adopting the actions contained in the
manufacturer's alert telex 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
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the
applicable bilateral 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.
This unsafe condition is likely to exist or develop on other
helicopters of the same type design registered in the United States.
Therefore, this AD is being issued to detect a crack in a tenon, which
could result in loss of the tip cap, causing severe vibration and loss
of control of the helicopter. This AD requires, for Eurocopter Model EC
155 B and B1 helicopters:
For blades with 100 or less hours TIS, prior to reaching
110 hours TIS, an initial inspection of each tenon for a crack;
For blades with more than 100 hours TIS, within the next
10 hours TIS, an initial inspection of the tenon for a crack;
Replacing any blade if a crack is found in the tenon; and
After accomplishing the initial inspection for a crack as
described above, before further flight, measuring the clearance between
the lower edge of the straight edge to the upper surface of the blade
assembly at the blade-to-tip cap junction (``DO'') to establish the
baseline clearance and then, before the first flight of each day (not
to exceed 10 hours TIS), measuring the clearance between the lower edge
of the straight edge and the upper surface of the blade assembly at the
blade-to-tip cap junction for each blade, and if the distance is equal
to or greater than ``DO'' + 2mm, replacing the blade with an airworthy
blade.
The actions must be done in accordance with the alert telex
described previously. The short compliance time involved is required
because the previously described critical unsafe condition can
adversely affect the controllability and structural integrity of the
helicopter. Therefore, inspecting each blade for a crack in the tenon
within the short compliance time is required, 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 this AD will affect 6 helicopters. The
initial inspection will take approximately 1.5 work hours, and the
repetitive inspections will take 0.5 work hours to accomplish. It will
take approximately 1 work hour to replace all 5 blades. The average
labor rate is $65 per work hour. Required parts will cost approximately
$97,000 per blade. Based on these figures, the total estimated cost
impact of the AD on U.S. operators is $586,563, assuming one blade per
helicopter will need to be replaced each year and that 20 repetitive
inspections will be needed per helicopter each year.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not
[[Page 32859]]
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. 2004-SW-05-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, Incorporation by
reference, Safety.
Adoption of the Amendment
0
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
0
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]
0
2. Section 39.13 is amended by adding a new airworthiness directive to
read as follows:
2004-12-06 Eurocopter France: Amendment 39-13665. Docket No. 2004-
SW-05-AD.
Applicability: Model EC 155 B and B1 helicopters, with main
rotor blade (blade), part number (P/N) 365A11-0080-00, installed,
certificated in any category.
Compliance: Required as indicated.
To detect a crack in a blade tip cap mounting bracket (tenon),
which could result in loss of the tip cap, severe vibration, and
loss of control of the helicopter, accomplish the following:
(a) Unless accomplished previously, remove each blade and each
tip cap, and inspect both the upper and lower side of the tenon for
a crack using a 10x or higher magnifying glass while applying light
manual upward and then downward pressure on the tenon as depicted in
Figure 3 of Eurocopter Alert Telex No. 05A004, dated November 3,
2003 (Alert Telex) as follows:
(1) For blades with more than 100 hours time-in-service (TIS),
inspect each blade within the next 10 hours TIS.
(2) For blades with 100 or less hours TIS, inspect each blade
before it reaches 110 hours TIS.
(3) If a crack is found, replace the blade with an airworthy
blade before further flight.
(b) After inspecting each blade as required by paragraph (a) of
this AD:
(1) Unless accomplished previously, before further flight, using
a 24'' (500mm) straight edge, measure the clearance between the
lower edge of the straight edge and the upper surface of the blade
assembly at the blade-to-tip cap junction by following the
Accomplishment Instructions, paragraph 2.B.2. of the Alert Telex,
except contacting the manufacturer is not required. This initial
clearance distance is called ``DO''.
(2) Thereafter, before the first flight of each day and on or
before reaching each 10-hour TIS interval during the day, measure
the clearance between the lower edge of the straight edge and the
upper surface of the blade assembly at the blade-to-tip cap junction
for each blade as required by paragraph (b)(1) of this AD. If the
measured clearance is equal to or greater than ``DO'' + 2mm, replace
the blade with an airworthy blade before further flight.
(c) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Safety Management Group, Rotorcraft Directorate, FAA,
for information about previously approved alternative methods of
compliance.
(d) Special flight permits will not be issued.
(e) The inspections and measurement shall be done in accordance
with Eurocopter Alert Telex No. 05A004, dated November 3, 2003. 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 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; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
(f) This amendment becomes effective on June 29, 2004.
Note: The subject of this AD is addressed in Direction Generale
De L'Aviation Civile (France) AD No. F-2003-418, dated December 24,
2003.
Issued in Fort Worth, Texas, on June 1, 2004.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-12905 Filed 6-10-04; 8:45 am]
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