82 FR 10267 - Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 27 (February 10, 2017)

We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 C-2 and MBB-BK 117 D-2 helicopters. This AD requires inspections and a torque of certain attachment points. This AD was prompted by a design reassessment. These actions are intended to prevent an unsafe condition on these products.

[Federal Register Volume 82, Number 27 (Friday, February 10, 2017)]
[Rules and Regulations]
[Pages 10267-10269]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2017-01772]



[[Page 10267]]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7415; Directorate Identifier 2015-SW-076-AD; 
Amendment 39-18786; AD 2017-02-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus 
Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 C-2 
and MBB-BK 117 D-2 helicopters. This AD requires inspections and a 
torque of certain attachment points. This AD was prompted by a design 
reassessment. These actions are intended to prevent an unsafe condition 
on these products.

DATES: This AD is effective March 17, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of March 17, 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/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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7415.

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-2016-
7415; 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; telephone (817) 222-5110; email 
[email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    On June 21, 2016, at 81 FR 40203, 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 and MBB-BK 117 D-2 helicopters with a hydraulic 
module plate assembly part number B291M0003103 with a single locking 
attachment point (attachment point) installed. The NPRM proposed to 
require performing repetitive visual inspections of each attachment 
point of the hydraulic module plate assembly for a crack and proper 
installation and a one-time torque of the nuts of each attachment 
point. The proposed requirements were intended to prevent failure of an 
attachment point, which could result in loss of the hydraulic module 
plate and subsequent loss of control of the helicopter.
    The NPRM was prompted by AD No. 2015-0210R1, Revision 1, dated 
October 28, 2015, issued by EASA, which is the Technical Agent for the 
Member States of the European Union, to correct an unsafe condition for 
the Airbus Helicopters Model MBB-BK117 C-2, MBB-BK117 C-2e, MBB-BK117 
D-2, and MBB-BK117 D-2m helicopters. EASA advises that the hydraulic 
plate assembly on certain MBB-BK117 models has four attachment points 
on the fuselage secured by a single locking mechanism. According to 
EASA, a design reassessment revealed stiffness of the hydraulic plate 
may be insufficient to withstand the in-service loads in the event one 
of the four single locking attachment points fails. EASA states that if 
this condition is not detected and corrected, it may lead to loss of 
the hydraulic module plate and possible loss of control of the 
helicopter. Therefore, the EASA AD requires a repetitive inspection and 
one-time torque tightening of the attachment points in accordance with 
Airbus Helicopters' service information. EASA considers its AD an 
interim action and states further AD action may follow.
    After we issued the NPRM, EASA revised its AD and issued EASA AD 
No. 2015-0210R2, Revision 2, dated December 2, 2016. AD 2015-0210R2 
reduces the applicability by serial number to exclude helicopters with 
an improved hydraulic module plate installation that is not subject to 
the unsafe condition.

Comments

    After our NPRM was published, we received comments from one 
commenter.

Request

    Airbus Helicopters requested revising the statements regarding what 
prompted this AD action and the intended effects of this AD action to 
more accurately describe the unsafe condition. Specifically, the 
commenter requested we state the design assessment showed that in case 
of a failure of a single attachment point, the stiffness of the 
hydraulic plate installation may be insufficient to withstand the in-
service loads.
    We agree. We have revised this statement in the Discussion 
paragraph of this Final Rule.
    The commenter also requested that in our statement of what the 
proposed actions are intended to prevent, we change ``subsequent loss 
of control of the helicopter'' to ``possible loss of control of the 
helicopter.''
    We disagree. This AD states the unsafe condition ``could result'' 
in loss of the hydraulic module plate and subsequent loss of control of 
the helicopter. This language indicates that loss of control of the 
helicopter is a possibility. Thus, the requested change is unnecessary.

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 except for the change to the 
Applicability section previously described. This change is consistent 
with the intent of the proposals in the NPRM and will not increase the 
economic burden on any operator nor increase the scope of this AD.

[[Page 10268]]

Differences Between This AD and the EASA AD

    The EASA AD requires contacting Airbus Helicopters customer support 
when replacing affected parts, and this AD does not.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Helicopters Alert Service Bulletin (ASB) No. ASB 
MBB-BK117 C-2-29A-003 for Model MBB-BK 117 C-2 helicopters and Airbus 
Helicopters ASB No. ASB MBB-BK117 D-2-29A-001 for Model MBB-BK 117 D-2 
helicopters, both Revision 0, and both dated October 12, 2015. This 
service information specifies a repetitive visual inspection for 
condition and correct installation of the attachment points, and if 
there is a crack, replacing the affected parts and contacting Airbus 
Helicopters customer support. This service information also specifies a 
tightening torque check after the initial inspection and, if torque 
cannot be applied, replacing the affected parts and contacting Airbus 
Helicopters customer support.
    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.

Other Related Service Information

    We also reviewed Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-
003 for Model MBB-BK 117 C-2 helicopters and Airbus Helicopters ASB No. 
ASB MBB-BK117 D-2-29A-001 for Model MBB-BK 117 D-2 helicopters, both 
Revision 1 and both dated October 14, 2016. This service information 
specifies the same repetitive visual inspection for condition and 
correct installation of the attachment points except it reduces the 
applicability by serial number due to the introduction of a new locking 
design.

Costs of Compliance

    We estimate that this AD affects 134 helicopters of U.S. Registry. 
We estimate that operators may incur the following costs in order to 
comply with this AD. We estimate the cost of labor at $85 per work-
hour. Visually inspecting the four attachment points will take about 
0.75 work-hour for an estimated cost of $64 per helicopter and $8,576 
for the U.S. fleet per inspection cycle. Inspecting the torque of the 
four attachment points will take about 0.25 work-hour for an estimated 
cost of $21 per helicopter and $2,814 for the U.S. fleet. Replacing any 
of the attachment point parts will take a minimal amount of time and 
parts will cost about $48 per attachment point.

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 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):

2017-02-07 Airbus Helicopters Deutschland GmbH: Amendment 39-18786; 
Docket No. FAA-2016-7415; Directorate Identifier 2015-SW-076-AD.

(a) Applicability

    This AD applies to Model MBB-BK 117 C-2 helicopters, serial 
numbers up to and including 9750, and Model MBB-BK 117 D-2 
helicopters, serial numbers up to and including 20110, with a 
hydraulic module plate assembly part number B291M0003103 with a 
single locking attachment point installed, certificated in any 
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of a hydraulic 
module plate assembly attachment point (attachment point). This 
condition could result in loss of the hydraulic module plate and 
subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective March 17, 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 100 hours time-in-service (TIS):
    (i) Visually inspect the split pins, castellated nuts, plugs, 
nuts, and hexagon bolts of each attachment point for a crack and for 
proper installation by following the Accomplishment Instructions, 
paragraphs 3.B.1.2.a. through 3.B.1.2.e., of Airbus Helicopters 
Alert Service Bulletin (ASB) No. ASB MBB-BK117 C-2-29A-003, Revision 
0, dated October 12, 2015 (ASB MBB-BK117 C-2-29A-003), or Airbus 
Helicopters ASB No. ASB MBB-BK117 D-2-29A-001, Revision 0, dated 
October 12, 2015 (ASB MBB-BK117 D-2-29A-001), as applicable to your 
model helicopter. Replace any part that has a crack before further 
flight. If the split pins, castellated nuts, or hexagon bolts are 
not as depicted in Figure 2 of ASB MBB-BK117 C-2-29A-003 or ASB MBB-
BK117 D-2-29A-001, before further flight, properly install them.
    (ii) Apply a torque of 9 to 10 Nm to the left-hand and right-
hand nuts of each attachment point. If a torque of 9 to 10 Nm cannot 
be applied, replace the affected nut before further flight.
    (2) Thereafter, at intervals not to exceed 400 hours TIS, 
perform the inspection in paragraph (e)(1)(i) 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,

[[Page 10269]]

FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; 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) Airbus Helicopters Alert Service Bulletin (ASB) No. ASB MBB-
BK117 C-2-29A-003 and Airbus Helicopters ASB No. ASB MBB-BK117 D-2-
29A-001, both Revision 1, and both dated October 14, 2016, which are 
not incorporated by reference, contain additional information about 
the subject of this final rule. 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/techpub. 
You may review a copy of the service information at the FAA, Office 
of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 
6N-321, Fort Worth, TX 76177.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2015-0210R1, Revision 1, dated October 
28, 2015, and EASA AD No. 2015-0210R2, Revision 2, dated December 2, 
2016. You may view the EASA ADs on the Internet at http://www.regulations.gov in Docket No. FAA-2016-7415.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 2900, Hydraulic 
Power 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 No. ASB MBB-BK117 
C-2-29A-003, Revision 0, dated October 12, 2015.
    (ii) Airbus Helicopters Alert Service Bulletin No. ASB MBB-BK117 
D-2-29A-001, Revision 0, dated October 12, 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/techpub.
    (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 January 18, 2017.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2017-01772 Filed 2-9-17; 8:45 am]
 BILLING CODE 4910-13-P