
[Federal Register Volume 82, Number 119 (Thursday, June 22, 2017)]
[Rules and Regulations]
[Pages 28399-28401]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-12800]


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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; 
Amendment 39-18934; AD 2017-13-04]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting 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 AD 
requires replacing the main rotor (M/R) blade vibration absorbers. This 
AD was prompted by a report of strong M/R blade vibrations on a Model 
MBB-BK 117 C-2 helicopter. The actions of this AD are intended to 
prevent an unsafe condition on these products.

DATES: This AD is effective July 27, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of July 27, 2017.

ADDRESSES: For service information identified in this final rule, 
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/website/en/ref/Technical-Support_73.html. You may review the referenced service information at 
the FAA, Office of the Regional Counsel, Southwest Region, 10101 
Hillwood Pkwy., Room 6N-321,

[[Page 28400]]

Fort Worth, TX 76177. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0061.

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 AD, the European Aviation Safety Agency (EASA) ADs, any 
incorporated-by-reference service information, the economic evaluation, 
any comments received, and other information. The street address for 
the Docket Operations Office (phone: 800-647-5527) is U.S. Department 
of Transportation, Docket Operations Office, M-30, West Building Ground 
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 
Hillwood Pkwy., Fort Worth, TX 76177; email matthew.fuller@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    On February 17, 2017, at 82 FR 10978, the Federal Register 
published our notice of proposed rulemaking (NPRM), which proposed to 
amend 14 CFR part 39 by adding an AD that would apply to Airbus 
Helicopters Model MBB-BK 117 C-2 (including configuration C-2e) and 
Model MBB-BK 117 D-2 helicopters with an M/R blade vibration absorber 
spacer part number (P/N) 117-801841.11 installed. The NPRM proposed to 
require replacing the M/R blade vibration absorbers. The proposed 
requirements were intended to prevent damage to a bearing in an M/R 
blade vibration absorber. Such damage could result in failure of the 
bearing, possibly resulting in the loss of balls and damage to the 
helicopter and injury to persons on the ground.
    The NPRM was prompted by AD No. 2016-0002, dated January 4, 2016, 
issued by EASA, which is the Technical Agent for the Member States of 
the European Union, 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 advises of damaged bearings 
that 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. To address this 
unsafe condition, EASA requires replacing the spacers with flanged 
spacers in the M/R blade vibration absorber and re-identifying the 
vibration absorber and M/R blade.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we received no comments on the NPRM.

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 
the EASA 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 these same 
type designs and that air safety and the public interest require 
adopting the AD requirements as proposed.

Interim Action

    We consider this 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.

Differences Between This 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. This 
AD requires the replacement within 200 hours TIS. The EASA AD applies 
to Airbus Helicopters Model MBB-BK 117 D-2m helicopters. This AD does 
not because Model MBB-BK 117 D-2m helicopters have no FAA type 
certificate.

Related Service Information Under 1 CFR Part 51

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

Costs of Compliance

    We estimate that this AD affects 136 helicopters of U.S. Registry 
and that labor costs average $85 per work-hour. Based on these 
estimates, we expect that modifying the M/R blade vibration absorber 
spacers and re-identifying the parts require 4 work-hours and parts 
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 P/N is 
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 helicopters identified in this 
rulemaking action.

Regulatory Findings

    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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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

[[Page 28401]]

under the criteria of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this 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.

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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2017-13-04 Airbus Helicopters Deutschland GmbH (Airbus Helicopters): 
Amendment 39-18934; Docket No. FAA-2017-0061; Directorate Identifier 
2016-SW-005-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 part number 
(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) Effective Date

    This AD becomes effective July 27, 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 P/Ns 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.

(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, 10101 Hillwood Pkwy., Fort Worth, Texas 76177; telephone (817) 
222-5110; email 9-ASW-FTW-AMOC-Requests@faa.gov.
    (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 Docket No. FAA-2017-0061.

(h) Subject

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

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus Helicopters Alert Service Bulletin MBB-BK117 C-2-62A-
009, Revision 1, dated October 28, 2015.
    (ii) Airbus Helicopters Alert Service Bulletin MBB-BK117 D-2-
62A-001, Revision 1, dated October 28, 2015.
    (3) For Airbus Helicopters service information identified in 
this 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/website/en/ref/Technical-Support_73.html.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177. For information on the availability of 
this material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference 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/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on June 6, 2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2017-12800 Filed 6-21-17; 8:45 am]
BILLING CODE 4910-13-P


