[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:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
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.
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]
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