[Federal Register Volume 69, Number 113 (Monday, June 14, 2004)]
[Rules and Regulations]
[Pages 32857-32859]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-12905]


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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: [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, 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]
BILLING CODE 4910-13-P