[Federal Register Volume 79, Number 159 (Monday, August 18, 2014)]
[Proposed Rules]
[Pages 48696-48698]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-19506]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0578; Directorate Identifier 2013-SW-048-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
(Previously Eurocopter Deutschland GmbH) (Airbus Helicopters) 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Airbus Helicopters Model MBB-BK 117 C-2 helicopters with certain duplex 
trim actuators installed. This proposed AD would require repetitively 
inspecting the lateral and longitudinal trim actuator output levers for 
correct torque of the nuts. This proposed AD is prompted by a design 
review that the attachment screws can become lost under certain 
circumstances. The proposed actions are intended to prevent the loss of 
an attachment screw, which could result in movement of the output lever 
in an axial direction, contact of a bolt connecting the control rod to 
an output lever with the actuator housing, and subsequent loss of 
helicopter control.

DATES: We must receive comments on this proposed AD by October 17, 
2014.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket 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 AD docket contains this proposed AD, the European 
Aviation Safety Agency (EASA) AD, the economic evaluation, any comments 
received, and other information. The street address for the Docket 
Operations Office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.
    For service information identified in this proposed AD, contact 
Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at 
http://www.airbushelicopters.com/techpub. You may review the referenced 
service information at the FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety 
Engineer,

[[Page 48697]]

Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham 
Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email 
[email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to participate in this rulemaking by submitting 
written comments, data, or views. We also invite comments relating to 
the economic, environmental, energy, or federalism impacts that might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. To 
ensure the docket does not contain duplicate comments, commenters 
should send only one copy of written comments, or if comments are filed 
electronically, commenters should submit only one time.
    We will file in the docket all comments that we receive, as well as 
a report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD No. 2013-0182, dated August 12, 
2013, to correct an unsafe condition for Airbus Helicopters Model MBB-
BK 117 C-2 helicopters with a lateral duplex trim actuator, part number 
(P/N) 418-00878-050 or P/N 418-00878-051, or with a longitudinal duplex 
trim actuator, P/N 418-00878-000 or P/N 418-00878-001. EASA advises 
that recent analysis has shown that under unfavorable circumstances, a 
total loss of the trim actuator output lever attachment screw could 
lead to a restriction of the lateral and longitudinal control range. 
According to EASA, without the attachment screw, the output lever can 
move in the axial direction. This condition, if not detected, could 
cause the bolt that connects the control rod to the output lever to 
make contact with actuator housing, possibly resulting in reduced 
control of the helicopter. To prevent this condition, EASA requires an 
initial torque check of the lateral and longitudinal trim actuator 
output level attachment screws, the application of a torque marking, 
and repetitive inspections for correct torque thereafter. The AD's 
requirements are considered an interim solution, pending a terminating 
modification.
    Since the issuance of EASA AD No. 2013-0182, Eurocopter Deutschland 
GmbH has changed its name to Airbus Helicopters Deutschland GmbH.

 FAA's Determination

    These helicopters have been approved by the aviation authority of 
Germany and are approved for operation in the United States. Pursuant 
to our bilateral agreement with Germany, EASA, its technical 
representative, has notified us of the unsafe condition described in 
its AD. We are proposing this AD because we evaluated all known 
relevant information and determined that an unsafe condition is likely 
to exist or develop on other products of the same type design.

Related Service Information

    We reviewed Eurocopter (now Airbus Helicopters) Alert Service 
Bulletin MBB-BK117 C-2-67A-020, Revision 0, dated June 18, 2013 (ASB), 
which advises of a design review that showed that a loss of the 
attachment screw of the trim actuator output lever could restrict the 
lateral and longitudinal control range. The ASB consequently calls for 
an initial torque check and application of torque markings of the self-
locking nuts, and subsequent repetitive inspections to maintain the 
proper torque.

Proposed AD Requirements

    This proposed AD would require, within 300 hours time-in-service 
(TIS) and thereafter at intervals not exceeding 400 hours TIS, 
inspecting the lateral and longitudinal trim actuator output lever 
self-locking nuts for correct torque and applying torque marking. For 
each inspection where the nuts are not torqued to the correct value and 
must be adjusted, the torque marking would be removed and reapplied.

Interim Action

    We consider this AD to be an interim action because Airbus 
Helicopters is currently developing a modification that will address 
the unsafe condition identified in this AD. Once this modification is 
developed, approved and available, we might consider additional 
rulemaking.

Costs of Compliance

    We estimate that this proposed AD would affect 100 helicopters of 
U.S. Registry and that labor costs average $85 per work-hour. Based on 
these estimates, we expect the following costs:
    Applying torque and torque marking to the lateral and longitudinal 
trim actuator output levers would require 1 work-hour for a labor cost 
of $85. No parts would be needed, so the cost for the U.S. fleet would 
total $8,500.
    Visually inspecting for correct torque would require 0.5 work-hour 
for a labor cost of about $43. No parts would be needed, so the total 
cost for the U.S. fleet would be $4,300 per inspection cycle.

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 proposed 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.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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, I certify this proposed 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);
    3. Will not affect intrastate aviation in Alaska to the extent that 
it justifies making a regulatory distinction; and
    4. 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

[[Page 48698]]

this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Airbus Helicopters Deutschland GmbH (Previously Eurocopter 
Deutschland GmbH) (Airbus Helicopters) Helicopters: Docket No. FAA-
2014-0578; Directorate Identifier 2013-SW-048-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model MBB-BK 117 C-2 
helicopters with a lateral duplex trim actuator, part number (P/N) 
418-00878-050 or P/N 418-00878-051, or a longitudinal duplex trim 
actuator, P/N 418-00878-000 or P/N 418-00878-001, installed, 
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as loss of a trim actuator 
output lever attachment screw. This condition could result in 
movement of the output lever in an axial direction, contact of a 
bolt connecting the control rod to an output lever with the actuator 
housing, and subsequent loss of control of the helicopter.

(c) Comments Due Date

    We must receive comments by October 17, 2014.

(d) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(e) Required Actions

    (1) Within 300 hours time-in-service (TIS), apply a torque of 
31.0 inch-pounds (3.5 Nm) to the self-locking nut (nut) on each 
lateral and longitudinal trim actuator output lever and apply a 
torque marking between the nut and the screw.
    (2) Thereafter at intervals not to exceed 400 hours TIS, 
visually inspect each nut on each lateral and longitudinal trim 
actuator output lever to determine whether the torque is at 31.0 
inch-pounds (3.5 Nm). If the torque is not at 31.0 inch-pounds, 
apply a torque of 31.0 inch-pounds (3.5 Nm), remove the previous 
torque marking, and apply a new torque marking between the nut and 
the screw.
    (3) Do not install a lateral duplex trim actuator, part number 
(P/N) 418-00878-050 or P/N 418-00878-051, or a longitudinal duplex 
trim actuator, P/N 418-00878-000 or P/N 418-00878-001, on any 
helicopter unless each nut has been inspected for proper torque in 
accordance with the requirements of this AD.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; email [email protected].
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office before operating any aircraft 
complying with this AD through an AMOC.

(g) Additional Information

    (1) Eurocopter Alert Service Bulletin MBB-BK117 C-2-67A-020, 
Revision 0, dated June 18, 2013, which is not incorporated by 
reference, contains additional information about the subject of this 
AD. For service information identified in this AD, contact Airbus 
Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or 
at http://www.airbushelicopters.com/techpub. You may review the 
referenced service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137.
    (2) The subject of this AD is addressed in the European Aviation 
Agency (EASA) AD No. 2013-0182, dated August 12, 2013. You may view 
the EASA AD on the Internet at http://www.regulations.gov in the AD 
Docket.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: Rotorcraft Flight 
Control, 6700.

     Issued in Fort Worth, Texas, on August 8, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-19506 Filed 8-15-14; 8:45 am]
BILLING CODE 4910-13-P