[Federal Register Volume 76, Number 55 (Tuesday, March 22, 2011)]
[Rules and Regulations]
[Pages 15802-15805]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-6212]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0212; Directorate Identifier 2010-SW-055-AD; 
Amendment 39-16632; AD 2011-06-07]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France (Eurocopter) Model 
EC130 B4 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 Model EC130 B4 helicopters. This action requires identifying 
and inspecting a certain emergency flotation gear unit ``1G'' (1G 
unit). This action also requires modification of certain affected 1G 
units. This amendment is prompted by an uncommanded in-flight 
deployment of the emergency flotation gear when it was not armed by the 
crew. The actions specified in this AD are intended to prevent an 
uncommanded in-flight deployment of the emergency flotation gear, 
unexpected deceleration and pitch down movement of the helicopter, and 
subsequent loss of control of the helicopter.

DATES: Effective April 6, 2011.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 6, 2011.
    Comments for inclusion in the Rules Docket must be received on or 
before May 23, 2011.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
    <bullet> Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-

[[Page 15803]]

30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, 
SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays.
    You may get the service information identified in this AD from 
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 
75053-4005, telephone (800) 232-0323, fax (972) 641-3710, or at http://www.eurocopter.com.

Examining the Docket

    You may examine the docket that contains the AD, any comments, and 
other information on the Internet at http://www.regulations.gov, or in 
person at the Docket Operations office between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The Docket Operations 
office (telephone (800) 647-5527) is located in Room W12-140 on the 
ground floor of the West Building at the street address stated in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: George Schwab, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Safety Management Group, 2601 
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5114, fax 
(817) 222-5961.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD No. 2010-0088-E, dated May 6, 2010, to correct an unsafe condition 
for the Model EC130 B4 helicopters. EASA advises that an uncontrolled 
in-flight deployment of the emergency flotation gear (not armed) on an 
EC130 B4 helicopter has been reported. The flight crew heard a 
detonation followed by heavy vibrations and noticed the emergency 
flotation gear floats were inflating. Investigations on the emergency 
flotation gear control system revealed that a wire was damaged inside 
the 1G unit. This wire was damaged, due to interference with the screw 
securing cable 1GR19E lug to the bus bar, causing a short circuit in 
the emergency flotation gear deployment activation circuit and the 
consequent deployment of the emergency flotation gear. EASA further 
states the possibility of interference of the 1G unit's internal wire 
harnesses with a fuselage metal structure member (stringer) has been 
identified, which could have the same consequences.

Related Service Information

    Eurocopter has issued Emergency Alert Service Bulletin No. 25A037, 
dated April 27, 2010, for the Model EC130 B4 helicopters, which 
specifies inspecting 1G units without an ``*'' displayed on the 1G unit 
panel after the part number (P/N) and taking various corrective actions 
at various times pending installation of a conforming 1G unit. EASA 
classified this EASB as mandatory and issued AD No. 2010-0088-E, dated 
May 6, 2010, to ensure the continued airworthiness of these 
helicopters.

FAA's Evaluation and Unsafe Condition Determination

    This helicopter has been approved by the aviation authority of 
France and is approved for operation in the United States. Pursuant to 
our bilateral agreement with France, EASA, their technical 
representative, has notified us of the unsafe condition described in 
the MCAI AD. We are issuing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition exists 
and is likely to exist or develop on other helicopters of this same 
type design.

Differences Between This AD and the EASA AD

    This AD does not require the actions to be completed at the 
compliance times of 3 months and 8 months, nor does it require the 
repetitive actions specified in the EASA AD. This AD requires the 
actions to be done within 15 hours time-in-service (TIS). Also, this AD 
refers to flight hours as hours TIS.

FAA's Determination and Requirements of This AD

    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, this AD is being issued 
to prevent an uncommanded in-flight deployment of the emergency 
flotation gear, unexpected deceleration and pitch down movement of the 
helicopter, and subsequent loss of control of the helicopter.
    This AD requires determining if the 1G unit has an asterisk after 
the P/N displayed on the 1G unit panel. If an asterisk follows the P/N, 
the AD requires inspecting for a rubber extrusion installed on the 
stringer. If no rubber extrusion is installed on the stringer, the AD 
requires removing the 1G unit, bonding a rubber extrusion on the 
stringer, reinstalling the 1G unit, and functionally testing the 
emergency flotation gear control system. If no asterisk follows the P/
N, the AD requires removing the 1G unit and inspecting the 1G unit for 
interference between the harness wires and the stringer and between 
internal parts. Also, the AD requires if no rubber extrusion is 
installed on the stringer, protecting the stringer by bonding a rubber 
extrusion on the stringer. The AD also requires inspecting for 
interference between the attachment screw and the wires of the nearby 
harness and for damage to the wires of the harness. The AD also 
requires modifying the 1G unit as necessary to protect the 1G unit from 
interference. Also, the AD requires identifying the modified 1G unit by 
marking an asterisk after the P/N. The AD also requires reinstalling 
and functionally testing the 1G unit. Installing a conforming 1G unit 
is terminating action for the requirements of this AD. Do the actions 
by following specified portions of the service bulletin described 
previously.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability of the helicopter. This AD requires, within 15 hours 
TIS, determining whether a conforming 1G unit is installed, and if not, 
modifying the 1G unit within 15 hours TIS. Fifteen hours TIS is a very 
short compliance time; therefore, 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.

Costs of Compliance

    We estimate that this AD will affect about 119 helicopters of U.S. 
registry. Determining whether an asterisk is present on the 1G unit 
panel will require a minimal amount of time. We estimate that it will 
take about 8 work-hours per helicopter to remove, modify, and replace a 
1G unit. The average labor rate is $85 per work-hour. Required parts 
will cost about $25 per helicopter. Based on these figures, we estimate 
the cost of this AD on U.S. operators is $8,460, assuming 12 
helicopters will require modification of the 1G unit per this AD.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES. Include ``Docket No. FAA-2011-0212;

[[Page 15804]]

Directorate Identifier 2010-SW-055-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this AD. Using the search function of the 
docket Web site, you can find and read the comments to any of our 
dockets, including the name of the individual who sent the comment. You 
may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78).

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 AD docket 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 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

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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:

2011-06-07 Eurocopter France: Amendment 39-16632; Docket No. FAA-
2011-0212; Directorate Identifier 2010-SW-055-AD.

    Applicability: Model EC130 B4 helicopters with a flotation gear 
unit ``1G'' (1G unit), part number (P/N) 350A63256300, installed, 
certificated in any category.
    Compliance: Within 15 hours time-in-service, unless accomplished 
previously.
    To prevent an uncommanded in-flight deployment of the emergency 
flotation gear, unexpected deceleration and pitch down movement of 
the helicopter, and subsequent loss of control of the helicopter, do 
the following:
    (a) Determine whether the 1G unit has an asterisk (*) after the 
P/N displayed on the 1G unit panel as shown in Figure 4 of 
Eurocopter Emergency Alert Service Bulletin No. 25A037, dated April 
27, 2010 (EASB).
    (b) If there is an asterisk after the P/N displayed on the 1G 
unit panel, determine if there is a rubber extrusion installed on 
the stringer as shown in Figure 6 of the EASB.
    (1) If no rubber extrusion is installed on the stringer, remove 
the 1G unit by following the Accomplishment Instructions, paragraph 
2.B.2.a. of the EASB.
    (2) Bond a rubber extrusion onto the stringer using Bostik 1400 
or an equivalent adhesive. Bostik 1400 is ready for use; if using an 
equivalent adhesive, follow the manufacturer's directions for 
preparation and application.
    (i) Thoroughly clean the bonding surfaces of the stringer; 
remove all traces of grease.
    (ii) Apply a uniform adhesive film on the bonding surfaces.
    (A) For Bostik 1400, allow to dry until tack free (about 15 
minutes).
    (B) For equivalent adhesive, follow the manufacturer's 
procedures.
    (iii) After adhesive application, assemble the bonding faces and 
press firmly to eliminate air bubbles. Maintain the pressure 
throughout the hardening period as described for the adhesive being 
used. For Bostik 1400, the adhesive hardens in about 48 hours at 
room temperature.
    (3) Reinstall the 1G unit by following the Accomplishment 
Instructions, paragraph 2.B.2.b., of the EASB. Functionally test the 
emergency flotation gear control system.
    (c) If there is no asterisk displayed after the P/N on the 1G 
unit panel, remove the 1G unit by following the Accomplishment 
Instructions, paragraph 2.B.2.a., of the EASB.
    (1) Inspect the 1G unit for interference:
    (i) If you find interference between the harness wires and the 
stringer, install a sheath, P/N EN6049-006-08-5, on all the 
harnesses in the area of the interference, and secure the sheath 
with cable ties as depicted in Figure 5 of the EASB.
    (ii) If you find interference between the harness wires and the 
inside surface of the 1G unit or with any of the 1G unit's internal 
components, remove the installed cable ties, P/N E0043-1A0P, and 
spacer(s), P/N E0688-01, as required, to allow repositioning or 
routing of the harness to eliminate interference. Secure 
repositioned harnesses using new cable ties, P/N E0043-1A0P, and new 
spacers, P/N E0688-01.
    (iii) If you find interference between the harness and the 
helicopter structural stringer, install a sheath, P/N EN6049-006-08-
5, on all the harnesses located at the stringer as depicted in 
Figures 5 and 6 of the EASB. Secure the sheath with cable ties, P/N 
E0043-1A0P, so that no interference between the sheathed harness and 
the structural stringer exists.
    (iv) Bond a black rubber extrusion, P/N BT4, on the stringer as 
shown in Figure 6 by following the requirements of paragraph (b)(2) 
of this AD.
    (2) Inspect the attachment screw of cable 1GR19E for orientation 
and arrangement that matches the Post EASB detail, as shown in 
insert D of Figure 5 of the EASB, and determine if it is covered 
with heat shrink, P/N VG95343T05E004A, or equivalent. If orientation 
and arrangement of the attachment screw cable 1GR19E are not as 
shown in insert D of Figure 5 or the attachment screw is not covered 
with heat shrink, modify the attachment screw by following the 
Accomplishment Instructions, paragraph 2.B.5.b., of the EASB.

    Note 1. Figure 5 of the EASB does not show the heat shrink 
installed for clarity of screw head and lug detail.

    (3) Inspect for damage to a wire of the harness inside the 1G 
unit as depicted in Figure 7 of the EASB. Replace any damaged wire 
using the correct wire and contact information listed in the 
Appendix, paragraph 4, of the EASB.
    (4) Mark an asterisk ``*'' after P/N 350A63256300 on the 1G unit 
panel using indelible ink to indicate compliance with this AD.
    (5) Reinstall the 1G unit by following the Accomplishment 
Instructions, paragraph 2.B.2.b., of the EASB, and functionally test 
the emergency flotation gear control system.
    (d) Installing an airworthy 1G unit that has been modified and 
identified as required by

[[Page 15805]]

this AD is terminating action for the requirements of this AD.
    (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, Safety Management Group, FAA, Attn: George 
Schwab, Aviation Safety Engineer, Rotorcraft Directorate, 2601 
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5114, 
fax (817) 222-5961, for information about previously approved 
alternative methods of compliance.
    (f) The Joint Aircraft System/Component (JASC) Code is 2497: 
Electrical Power System Wiring.
    (g) Remove and install the 1G unit, determine the correct wire 
and contact information, and do the inspections by following the 
specified portions of Eurocopter Emergency Alert Service Bulletin 
No. 25A037, dated April 27, 2010. 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, TX 
75053-4005, telephone (800) 232-0323, fax (972) 641-3710, or at 
http://www.eurocopter.com. 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.
    (h) This amendment becomes effective on April 6, 2011.

    Note 2: The subject of this AD is addressed in European Aviation 
Safety Agency No. 2010-0088-E, dated May 6, 2010.


    Issued in Fort Worth, Texas, March 7, 2011.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-6212 Filed 3-21-11; 8:45 am]
BILLING CODE 4910-13-P