[Federal Register Volume 83, Number 77 (Friday, April 20, 2018)]
[Proposed Rules]
[Pages 17510-17512]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-08097]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9395; Product Identifier 2016-SW-027-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 
various Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model 
MBB-BK117 and Model BO-105 helicopters. This proposed AD would require 
removing the swashplate bellows (bellows) and repetitively inspecting 
the swashplate assembly. This proposed AD is prompted by reports of 
loose and missing clamps installed on bellows. The proposed actions are 
intended to detect and prevent an unsafe condition on these products.

DATES: We must receive comments on this proposed AD by June 19, 2018.

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-2016-
9395; or in person at Docket Operations 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 Docket Operations (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 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.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; 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 aviation authority for Germany, has issued AD 
No. 2016-0142, dated July 19, 2016, to correct an unsafe condition for 
Airbus Helicopters Model MBB-BK 117A-1, MBB-BK 117A-3, MBB-BK 117A-4, 
MBB-BK 117B-1, MBB-BK 117B-2, MBB-BK 117C-1, MBB-BK 117C-2, MBB-BK 
117C-2e, BO-105A, BO-105C, BO-105D, BO105S, BO-105LS A-3 helicopters.
    EASA advises of several reports of a lower clamp found missing from 
the bellows and damaging the swashplate bearing ring before becoming 
detached. EASA states an investigation showed that over-torqueing can 
damage the clamp, which may have caused the clamp to become loose and 
detach. According to EASA, this condition, if not detected and 
corrected, could lead to loss of a swashplate clamp, resulting in loss 
of helicopter control. A detached clamp could damage the swashplate and 
pitch link or strike the tail rotor. EASA states that its AD is 
considered interim action and a further AD to implement a terminating 
action will follow.

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) BO105-
40A-107 for Model BO105 C-series, D-series and S-series helicopters; 
ASB BO105 LS-40A-12 for Model BO-105LS A-3 helicopters; ASB MBB-BK117-
40A-115 for Model MBB-BK 117A-1, MBB-BK 117A-3, MBB-BK 117A-4, MBB-BK 
117B-1, MBB-BK 117B-2, and MBB-BK 117C-1 helicopters; and ASB MBB-BK117 
C-2-62A-007 for Model MBB-BK 117C-2 and MBB-BK 117C-2e helicopters. 
These ASBs are all Revision 4 and all dated May 23, 2016. We also

[[Page 17511]]

reviewed Airbus Helicopters ASB MBB-BK117 D-2-62A-003, Revision 2, 
dated May 23, 2016, for Model MBB-BK117 D-2 and MBB-BK117 D-2m 
helicopters. This service information specifies removing the bellows 
and repetitively inspecting the swashplate.
    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

    This proposed AD would require a one-time inspection within 50 
hours time-in-service (TIS) and repetitive inspections every 100 hours 
TIS and every 400 hours TIS, by following the instructions in the 
manufacturer's service bulletin. This proposed AD would also prohibit 
installing on any helicopter bellows P/N 105-10113.05, P/N 4619305044, 
and P/N 4638305043 and any gearbox that has these bellows installed.

Differences Between This Proposed AD and the EASA AD

    The EASA AD requires compliance within different time intervals for 
some actions than what this proposed AD would require. The EASA AD 
allows a non-cumulative tolerance of 10 percent that may be applied to 
the compliance times, and this proposed AD would not. The EASA AD 
allows replacing the bellows clamps with cable ties before removing the 
bellows, and this proposed AD would not. This proposed AD would apply 
to Model MBB-BK 117D-2 helicopters while the EASA AD does not. The EASA 
AD applies to Model BO-105D helicopters, while this proposed AD would 
not.

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 286 helicopters of 
U.S. Registry and that labor costs would average $85 per work hour. 
Based on these estimates, we expect the following costs:
     Removing and inspecting the swashplate assembly would 
require 3 work-hours. No parts would be needed for a cost of $255 per 
helicopter and $72,930 for the U.S. fleet per inspection cycle.
     Repairing a scratched support tube would require 3 work-
hours. No parts would be needed for a cost of $255 per helicopter.
     Replacing a corroded or damaged clamp would require 2 
work-hours. Parts would cost $8 for a cost of $178 per helicopter.
     Replacing corroded ball bearings would require 4 work-
hours. Parts would cost $3,000 for a cost of $3,340 per helicopter.
     Removing foreign objects from the outer deflection ring 
would require 2 work-hours. No parts would be needed for a cost of $170 
per helicopter.

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: Docket No. FAA-2016-9395; 
Product Identifier 2016-SW-027-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Deutschland GmbH Model BO-
105A, BO-105C, BO-105S, BO105LS A-3, MBB-BK 117A-1, MBB-BK 117A-3, 
MBB-BK 117A-4, MBB-BK 117B-1, MBB-BK 117B-2, MBB-BK 117C-1, MBB-BK 
117C-2, and MBB-BK 117D-2 helicopters, certificated in any category.

    Note 1 to paragraph (a) of this AD:  Helicopters with an MBB-BK 
117C-2e designation are Model MBB-BK 117C-2 helicopters.

(b) Unsafe Condition

    This AD defines the unsafe condition as a loose bellows clamp. 
This condition can cause loss of the bellows, contact of the bellows 
with the main rotor blades, main rotor mast, and tail rotor, and 
subsequent loss of helicopter control.

(c) Comments Due Date

    We must receive comments by June 19, 2018.

(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 50 hours time-in-service (TIS):
    (i) Remove the swashplate bellows (bellows) part number (P/N) 
105-10113.05, P/N 4638305043, P/N 4619305044, or B623M20X2240 from 
the swashplate.
    (ii) Inspect the swashplate by following the Accomplishment 
Instructions, paragraph 3.B.1.(h) through 3.B.1.(k) of Airbus 
Helicopters Alert Service Bulletin (ASB)

[[Page 17512]]

BO105-40A-107, Revision 4, dated May 23, 2016 (ASB BO105-40A-107); 
ASB BO105 LS 40A-12, Revision 4, dated May 23, 2016 (ASB BO105 LS 
40A-12); ASB MBB-BK117-40A-115, Revision 4, dated May 23, 2016 (ASB 
MBB-BK117-40A-115); or ASB MBB-BK117 C-2-62A-007, Revision 4, dated 
May 23, 2016 (ASB MBB-BK117 C-2-62A-007); or paragraph 3.B.1.5 
through 3.B.1.8 of Airbus Helicopters ASB MBB-BK117 D-2-62A-003, 
Revision 2, dated May 23, 2016 (ASB MBB-BK117 D-2-62A-003); 
whichever is applicable to your helicopter. If there is corrosion on 
a ball bearing, you are not required to contact Airbus Helicopters 
customer support; instead, before further flight, replace the ball 
bearing.
    (2) Within 100 hours TIS after complying with the actions in 
paragraph (1) of this AD, and thereafter at intervals not to exceed 
100 hours TIS, inspect the swashplate by following the 
Accomplishment Instructions, paragraph 3.B.2 of ASB BO105-40A-107, 
ASB BO105 LS 40A-12, ASB MBB-BK117-40A-115, ASB MBB-BK117 C-2-62A-
007, or ASB MBB-BK117 D-2-62A-003, except you are not required to 
contact Airbus Helicopters customer support. If there is corrosion 
on a ball bearing, before further flight, replace the ball bearing.
    (3) Within 400 hours TIS after complying with the actions in 
paragraph (1) of this AD, and thereafter at intervals not to exceed 
400 hours TIS, inspect the swashplate by following the 
Accomplishment Instructions, paragraph 3.B.3 of ASB BO105-40A-107, 
ASB BO105 LS 40A-12, ASB MBB-BK117-40A-115, ASB MBB-BK117 C-2-62A-
007, or ASB MBB-BK117 D-2-62A-003.
    (4) Do not install a bellows P/N 105-10113.05, P/N 4619305044, 
or P/N 4638305043 or a gearbox with a bellows P/N 105-10113.05, P/N 
4619305044, or P/N 4638305043 on any helicopter.

(f) Alternative Methods of Compliance (AMOCs)

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

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2016-0142, dated July 19, 2016. 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: 6200, Main Rotor 
System.

    Issued in Fort Worth, Texas, on April 11, 2018.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2018-08097 Filed 4-19-18; 8:45 am]
 BILLING CODE 4910-13-P


