Airworthiness Directives; Eurocopter Canada Limited Model BO 105 LS A-3 Helicopters

[Federal Register Volume 71, Number 144 (Thursday, July 27, 2006)]
[Rules and Regulations]
[Pages 42576-42577]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-11909]



[[Page 42576]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24632; Directorate Identifier 2005-SW-31-AD; 
Amendment 39-14695; AD 2006-15-14]
RIN 2120-AA64


Airworthiness Directives; Eurocopter Canada Limited Model BO 105 
LS A-3 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
Eurocopter Canada Limited (Eurocopter) Model BO 105 LS A-3 helicopters 
that requires replacing certain fixed bolts and nuts, re-identifying 
certain main rotor nuts, and revising the Airworthiness Limitations--
Time Change Items (TCI) list to reflect the new life limits and new 
part numbers. This amendment is prompted by a re-evaluation of certain 
fatigue-critical parts, which resulted in establishing new life limits 
for certain like-numbered parts and re-identifying a certain existing 
part with a different part number, or in some cases, replacing them 
with new parts. The actions specified by this AD are intended to 
prevent fatigue failure of the fixed bolts and nuts, and subsequent 
loss of control of the helicopter.

DATES: Effective August 31, 2006.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 31, 2006.

ADDRESSES: You may get the service information identified in this AD 
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, 
Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527.

Examining the Docket

    You may examine the docket that contains this AD, any comments, and 
other information on the Internet at http://dms.dot.gov, or at the 
Docket Management System (DMS), U.S. Department of Transportation, 400 
Seventh Street, SW., Room PL-401, on the plaza level of the Nassif 
Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, 
Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-
5961.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to 
include an AD for the specified model helicopters was published in the 
Federal Register on May 2, 2006 (71 FR 25787). That action proposed to 
require, within 30 days, incorporating revised life limits and part 
numbers into the list of life-limited parts, or TCI list, which is 
contained in the helicopter delivery file, and within 150 hours time-
in-service (TIS), replacing 4 fixed bolts, part number (P/N) LN 9038 
K08018, with fixed bolts, P/N 105-101021.17. It also proposed to 
require replacing 4 main rotor nuts, P/N 105-142241.01, within 30 days 
if they have less than 150 hours TIS remaining, or re-identifying those 
main rotor nuts within 150 hours TIS if they have 150 or more hours TIS 
remaining.
    Transport Canada, the airworthiness authority for Canada, notified 
the FAA that an unsafe condition may exist on Eurocopter Model BO 105 
LS A-3 helicopters. Transport Canada advises that changes to the TCI 
list must be incorporated, and affected parts must be replaced and re-
identified in accordance with the manufacturer's service information.
    Eurocopter has issued Alert Service Bulletin No. ASB BO 105 LS 10-
11, dated May 11, 2005, which specifies changes to and introduction of 
life limits, and re-identification of certain life-limited parts. 
Transport Canada classified this alert service bulletin as mandatory 
and issued AD No. CF-2005-17, dated June 6, 2005, to ensure the 
continued airworthiness of these helicopters in Canada.
    This helicopter model is manufactured in Canada and is 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, Transport Canada has kept the FAA 
informed of the situation described above. The FAA has examined the 
findings of Transport Canada, 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.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.
    The FAA estimates that this AD will affect 7 helicopters of U.S. 
registry, and the required actions will take approximately:
    <bullet> 1 work hour per helicopter to remove and replace 4 fixed 
bolts;
    <bullet> 16 work hours per helicopter to remove, replace, and re-
identify four nuts; and
    <bullet> 1 work hour per helicopter to create component history 
cards at an average labor rate of $65 per work hour. Required parts 
will cost approximately $3.80 for each fixed bolt, P/N 105-101021.17, 
and $882.67 for each nut, P/N 105-142241.01. Based on these figures, we 
estimate the total cost impact of the AD on U.S. operators to be 
$33,011, assuming all nuts and bolts on the entire fleet are replaced.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD. See the DMS to examine the economic evaluation.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on

[[Page 42577]]

products identified in this rulemaking action.

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:

2006-15-14 Eurocopter Canada Limited: Amendment 39-14695. Docket No. 
FAA-2006-24632; Directorate Identifier 2005-SW-31-AD.

    Applicability: Model BO 105 LS A-3 helicopters certificated in 
any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fatigue failure of a fixed bolt and main rotor nut, 
and subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Within 30 days:
    (1) Modify the Airworthiness Limitation section, Time Change 
Items (TCI) list, or table of life-limited components, with their 
revised life limits by adding part number (P/N) 105-142241.01 and by 
changing P/N LN 9038 K08018 to P/N 105-101021.17, as shown in the 
following table.

----------------------------------------------------------------------------------------------------------------
              Part name                           P/N                               Life limit
----------------------------------------------------------------------------------------------------------------
Fixed Bolt (Bolt)....................  105-101021.17 (Formerly   6,000 hours time-in-service (TIS).
                                        P/N LN 9038-K08018).
----------------------------------------------------------------------------------------------------------------
Main Rotor Nut (Nut).................  105-142241.01...........  122,850 flights or 18,900 hours TIS, whichever
                                                                  occurs first.
----------------------------------------------------------------------------------------------------------------
The number of flights equals the number of landings (i.e., ground contacts).

    (2) Create a historical or equivalent record for each of the 
parts listed in the preceding table.
    (3) Review the aircraft records and determine the TIS and 
landings on each nut, P/N 105-142241.01. If the number of flights 
(i.e., landings) is unknown, the initial life limit is 18,900 hours 
TIS. Thereafter, record the number of flights for use when 
determining the retirement life.
    (b) Before further flight, replace any nut that has less than 
150 hours TIS remaining before reaching its life limit. Unless 
accomplished previously, prior to replacing a nut, re-identify the 
nut in accordance with paragraph (c)(2) of this AD.
    (c) Within 150 hours TIS:
    (1) Replace the 4 bolts, P/N LN 9038 K08018, with bolts, P/N 
105-101021.17, as shown in Figure 1 of Eurocopter Alert Service 
Bulletin No. ASB BO 105 LS 10-11, dated May 11, 2005 (ASB).
    (2) For those nuts with 150 or more hours TIS remaining on their 
life, remove and re-identify those nuts, P/N 105-142241.01, by 
adding the serial number of the main rotor head, followed by a dash 
and a consecutive number, in accordance with the procedures stated 
in Figure 2 of the ASB.
    (d) Before further flight, remove any life-limited part on which 
the life limit has been equaled or exceeded.
    (e) 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 Manager, Regulations and Policy Group, Rotorcraft 
Directorate, FAA, ATTN: Sharon Miles, Aviation Safety Engineer, FAA, 
Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, 
Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-5961, for 
information about previously approved alternative methods of 
compliance.
    (f) The replacements shall be done in accordance with the 
specified portion of Eurocopter Alert Service Bulletin No. ASB BO 
105 LS 10-11, dated May 11, 2005. The Director of the Federal 
Register approved this incorporation by reference 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 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.
    (g) This amendment becomes effective on August 31, 2006.

    Note: The subject of this AD is addressed in Transport Canada 
(Canada) AD No. CF-2005-17, dated June 6, 2005.



    Issued in Fort Worth, Texas, on July 18, 2006.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E6-11909 Filed 7-26-06; 8:45 am]
BILLING CODE 4910-13-P

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