[Federal Register Volume 84, Number 76 (Friday, April 19, 2019)]
[Rules and Regulations]
[Pages 16394-16396]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-07562]



[[Page 16394]]

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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; Amendment 
39-19618; AD 2019-07-07]
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 various 
Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-
BK117 and Model BO-105 helicopters. This AD requires removing the 
swashplate bellows (bellows) and repetitively inspecting the swashplate 
assembly. This AD was prompted by reports of loose and missing clamps 
installed on bellows. The actions of this AD are intended to detect and 
prevent an unsafe condition on these products.

DATES: This AD is effective May 24, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of May 24, 2019.

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-2016-9395.

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 AD, the European Aviation Safety Agency (EASA) AD, any 
incorporated-by-reference service information, the economic evaluation, 
any comments received, and other information. The street address for 
Docket Operations (phone: 800-647-5527) is U.S. Department of 
Transportation, Docket Operations, 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 Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; 
email [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    On April 20, 2018, at 83 FR 17510, 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 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. The NPRM proposed to 
require removing the bellows and repetitively inspecting the swashplate 
assembly. The proposed requirements were intended to detect and prevent 
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.
    The NPRM was prompted by AD No. 2016-0142, dated July 19, 2016, 
issued by EASA (EASA AD 2016-0142), which is the Technical Agent for 
the Member States of the European Union, 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.

Changes to the Final Rule

    On April 12, 2018, EASA revised its AD and issued AD No. 2016-
0142R1 (``EASA AD 2016-0142R1''). EASA AD 2016-0142R1 removed the 
repetitive 100-hour and 400-hour inspections contained in EASA AD 2016-
0142. EASA determined that the repetitive inspections were no longer 
required to address the unsafe condition. EASA states the 400-hour 
inspections will be included in the airworthiness limitations section 
of the aircraft maintenance manual, and the 100-hour inspections will 
be deleted.
    We have made the same determination because of the lack of 
corrosion found on the parts since the bellows were removed. The 100-
hour repetitive inspections contained in the NPRM have been removed in 
this Final rule.

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 EASA and are approved for 
operation in the United States. Pursuant to our bilateral agreement 
with the European Union, EASA 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 
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.

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

    EASA AD 2016-0142R1 has a different compliance time for helicopters 
with new bellows, while this AD does not. This AD applies to Model MBB-
BK 117D-2 helicopters while EASA AD 2016-0142R1 does not. EASA AD 2016-
0142R1 applies to

[[Page 16395]]

Model BO-105D helicopters, while this AD does not. This AD requires 
repetitively inspecting the swashplate every 400 hours time-in-service, 
while EASA AD 2016-0142R1 does not.

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 
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.

Costs of Compliance

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

2019-07-07 Airbus Helicopters Deutschland GmbH: Amendment 39-19618; 
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) Effective Date

    This AD becomes effective May 24, 2019.

(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) 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 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.
    (3) 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.

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(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, and EASA AD No. 
2016-0142R1, dated April 12, 2018. You may view the EASA ADs on the 
internet at http://www.regulations.gov in Docket No. FAA-2016-9395.

(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 BO105-40A-107, 
Revision 4, dated May 23, 2016.
    (ii) Airbus Helicopters Alert Service Bulletin BO105 LS-40A-12, 
Revision 4, dated May 23, 2016.
    (iii) Airbus Helicopters Alert Service Bulletin MBB-BK117-40A-
115, Revision 4, dated May 23, 2016.
    (iv) Airbus Helicopters Alert Service Bulletin MBB-BK117 C-2-
62A-007, Revision 4, dated May 23, 2016.
    (v) Airbus Helicopters Alert Service Bulletin MBB-BK117 D-2-62A-
003, Revision 2, dated May 23, 2016.
    (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 March 21, 2019.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2019-07562 Filed 4-18-19; 8:45 am]
BILLING CODE 4910-13-P