[Federal Register Volume 82, Number 32 (Friday, February 17, 2017)]
[Proposed Rules]
[Pages 10978-10980]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-02859]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0061; Directorate Identifier 2016-SW-005-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
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 Deutschland GmbH (Airbus Helicopters) Model MBB-BK 
117 C-2 (including configuration C-2e) and MBB-BK 117 D-2 helicopters. 
This proposed AD would require replacing the main rotor (M/R) blade 
vibration absorbers. This proposed AD is prompted by a report of strong 
M/R blade vibrations on a Model MBB-BK 117 C-2 helicopter. The proposed 
actions are intended to prevent an unsafe condition on these products.

DATES: We must receive comments on this proposed AD by April 18, 2017.

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 by searching for and locating Docket No. FAA-2017-
0061 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) 
ADs, 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, 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, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX 
76177.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 
Hillwood Pkwy, Fort Worth, TX 76177; 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. 2016-0002, dated January 4, 
2016, to correct an unsafe condition for Airbus Helicopters Model MBB-
BK 117 C-2, MBB-BK 117 C-2e, MBB-BK 117 D-2, and Model MBB-BK 117 D-2m 
helicopters. EASA AD No. 2016-0002 supersedes EASA AD No. 2015-0045, 
dated March 13, 2015. EASA advises that the M/R blade of a Model MBB-BK 
117 C-2 helicopter was vibrating heavily while in service, and that 
bearing damage was discovered after the vibration absorber was 
disassembled. The bearings were damaged because of a loss of 
lubrication and were not freely spinning. The manufacturer reports two 
known cases of cracked bearings.
    EASA states that bearing damage, if not corrected, could lead to 
the loss of balls from the ball bearing while the M/R blade is turning, 
possibly resulting in damage to the helicopter and injury to persons on 
the ground. According to EASA, this same condition may affect Model 
MBB-BK 117 D-2 helicopters because they have a similar design. To 
address this unsafe condition, EASA requires replacing the spacers with 
flanged spacers in the main rotor blade vibration absorber and re-
identifying the vibration absorber and M/R blade. The manufacturer, 
meanwhile, reports that it is considering using a new boot to keep the 
bearings from becoming contaminated with dirt and water.
    EASA advises that since AD No. 2015-0045 was issued, it was 
determined that re-identification of the parts as the AD instructs 
leads to using the same new part number (P/N) for M/R blades of 
different structural design. This could lead to erroneous part 
management and maintenance.
    As a result, EASA superseded its AD with AD No. 2016-0002 to 
correct the part-identification instructions and expand the 
applicability to include Model MBB-BK 117 C-2e and Model MBB-BK117 D-2m 
helicopters.

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 Under 1 CFR Part 51

    We reviewed Airbus Helicopters Alert Service Bulletin (ASB) MBB-
BK117 C-

[[Page 10979]]

2-62A-009 for Model MBB-BK 117 C-2 and C-2e helicopters and ASB MBB-
BK117 D-2-62A-001 for Model MBB-BK 117 D-2 and D-2m helicopters. The 
ASBs, both Revision 1 and both dated October 28, 2015, specify 
replacing the vibration absorber spacers with flanged spacers to 
prevent the balls from escaping from the ball bearings. The ASBs also 
provide procedures for re-identifying the M/R blade and vibration 
absorber.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Proposed AD Requirements

    Within 200 hours time-in-service (TIS), this proposed AD would 
require replacing the spacers in each M/R blade vibration absorber with 
flanged spacers and re-identifying the vibration absorber and M/R 
blades. After replacing the spacers, this proposed AD would prohibit 
installing M/R blade P/N B621M1002103 or P/N D621M1002101, vibration 
absorber P/N B621M3001101, or spacer P/N 117-801841.11 on that 
helicopter. This proposed AD would allow you to install M/R blade P/N 
B621M1002101 or P/N B621M1002102 if you first comply with the 
requirements of this proposed AD.

Differences Between This Proposed AD and the EASA AD

    The EASA AD requires replacing the M/R blade vibration absorber 
spacers within 12 months after the effective date of the EASA AD. The 
proposed AD would require the replacement within 200 hours TIS. The 
EASA AD applies to Airbus Helicopters Model MBB-BK 117 D-2m 
helicopters. This AD would not because Model MBB-BK 117 D-2m 
helicopters have no FAA type certificate.

Interim Action

    We consider this proposed AD to be an interim action. The design 
approval holder 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 136 helicopters of 
U.S. Registry and that labor costs average $85 per work-hour. Based on 
these estimates, we expect that modifying the main rotor blade 
vibration absorber spacers and re-identifying the parts would require 4 
work-hours and parts would cost about $1,439, for a total cost of 
$1,779 per helicopter and $241,944 for the U.S. fleet. The cost of 
recording the new part numbers would be minimal.

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.

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 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 (Airbus Helicopters): Docket No. 
FAA-2017-0061; Directorate Identifier 2016-SW-0005-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model MBB-BK 117 C-2 
(including configuration C-2e) and Model MBB-BK 117 D-2 helicopters 
with a main rotor (M/R) blade vibration absorber spacer P/N 117-
801841.11 installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as damage to a bearing in 
an M/R blade vibration absorber. This condition could result in 
failure of the bearing, possibly resulting in the loss of the balls 
and damage to the helicopter and injury to persons on the ground.

(c) Comments Due Date

    We must receive comments by April 18, 2017.

(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 200 hours time-in-service:
    (i) Replace each spacer on the vibration absorber with a flanged 
spacer.
    (ii) Re-identify each vibration absorber and M/R blade in 
accordance with paragraphs 3.B.2.3. or 3.B.2.4, as applicable, of 
Airbus Helicopters Alert Service Bulletin (ASB) MBB-BK117 C-2-62A-
009, Revision 1, dated October 28, 2015, or ASB MBB-BK117 D-2-62A-
001, Revision 1, dated October 28, 2015, whichever applies to your 
model helicopter. Record the new part numbers and serial numbers for 
each M/R blade on the component history card or equivalent record.
    (2) After replacing the spacer in accordance with paragraph 
(e)(1) of this AD, do not install M/R blade P/N B621M1002103 or P/N 
D621M1002101, vibration absorber P/N B621M3001101, or spacer P/N 
117-801841.11 on that helicopter. You may install M/R blade P/N 
B621M1002101 or P/N B621M1002102 provided you have complied with the 
requirements of paragraph (e)(1) of this AD.

[[Page 10980]]

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Matt Fuller, Senior Aviation 
Safety Engineer, Safety Management 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

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2015-0045, dated March 13, 2015, and corrected 
April 2, 2015, and in EASA AD No. 2016-0002, dated January 4, 2016. 
You may view the EASA ADs on the Internet at http://www.regulations.gov in the AD Docket.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor 
System.

    Issued in Fort Worth, Texas, on January 30, 2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2017-02859 Filed 2-16-17; 8:45 am]
 BILLING CODE 4910-13-P