[Federal Register Volume 86, Number 45 (Wednesday, March 10, 2021)]
[Proposed Rules]
[Pages 13665-13667]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-04804]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 86, No. 45 / Wednesday, March 10, 2021 / 
Proposed Rules

[[Page 13665]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0135; Project Identifier MCAI-2020-01044-R]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2019-07-07 for various Airbus Helicopters Deutschland GmbH (Airbus 
Helicopters) Model MBB-BK117 and Model BO-105 helicopters. AD 2019-07-
07 requires removing certain part numbered swashplate bellows (bellows) 
from service, cleaning and inspecting certain parts, and depending on 
the inspection results removing certain parts from service, applying 
torque, and repetitively inspecting the swashplate assembly 
(swashplate). AD 2019-07-07 also prohibits the installation of certain 
part-numbered bellows. This proposed AD would retain certain 
requirements of AD 2019-07-07, expand the installation prohibition, add 
additional inspections, and update the applicable service information. 
The actions of this proposed AD are intended to address an unsafe 
condition on these products.

DATES: The FAA must receive comments on this proposed AD by April 26, 
2021.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0135; 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 (now European 
Union Aviation Safety Aviation) (EASA) AD, any comments received and 
other information. The street address for Docket Operations is listed 
above. 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 https://www.airbus.com/helicopters/services/technical-support.html. You may 
view this 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, AD Program Manager, 
Operational Safety Branch, Airworthiness Products Section, General 
Aviation & Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 
76177; telephone 817-222-5110; email <a href="/cdn-cgi/l/email-protection#75381401011d10025b330019191007351314145b121a03"><span class="__cf_email__" data-cfemail="6e230f1a1a060b1940281b02020b1c2e080f0f40090118">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2021-0135; Project Identifier 
MCAI-2020-01044-R'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
this proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this proposal.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to Matt 
Fuller, AD Program Manager, Operational Safety Branch, Airworthiness 
Products Section, General Aviation & Rotorcraft Unit, FAA, 10101 
Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; email 
<a href="/cdn-cgi/l/email-protection#6c210d181804091b422a190000091e2c0a0d0d420b031a"><span class="__cf_email__" data-cfemail="54193520203c31237a122138383126143235357a333b22">[email protected]</span></a>. Any commentary that the FAA receives which is 
not specifically designated as CBI will be placed in the public docket 
for this rulemaking.

Discussion

    The FAA issued AD 2019-07-07, Amendment 39-19618 (84 FR 16394, 
April 19, 2019) (AD 2019-07-07) for Airbus Helicopters Model BO-105A, 
BO-105C, BO-105S, BO-105LS 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. AD 2019-07-07 requires a one-time inspection 
of the swashplate with the bellows removed and thereafter, a repetitive 
inspection of the swashplate. AD 2019-07-07 also prohibits the 
installation of certain part-

[[Page 13666]]

numbered bellows and gearboxes with certain part-numbered bellows.
    AD 2019-07-07 was prompted by EASA AD No. 2016-0142, dated July 19, 
2016, which was revised to EASA AD No. 2016-0142R1, dated April 12, 
2018, issued by EASA, which is the Technical Agent for the Member 
States of the European Union. 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, and a detached clamp could damage the swashplate and 
pitch link or strike the tail rotor, resulting in loss of control of 
the helicopter.

Actions Since AD 2019-07-07 Was Issued

    Since the FAA issued AD 2019-07-07, it was identified that bellows 
(part number) P/N B623M20X220 was inadvertently omitted from the 
prohibition in the Required Actions paragraph. It was also identified 
that Airbus Helicopters updated its service information by issuing 
several alert service bulletins which specified removing the bellows 
and repetitively inspecting the swashplate. Accordingly, this proposed 
AD would update the service information and any incorporated by 
reference information, add to the inspection requirements of AD 2019-
07-07, and prohibit installation of bellows P/N B623M20X220.

FAA's Determination

    These helicopters have been approved by EASA and are approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Union, EASA has notified the FAA about the 
unsafe condition described in its AD. The FAA is proposing this AD 
after evaluating all known relevant information and determining that an 
unsafe condition is likely to exist or develop on other helicopters of 
the same type designs.

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. 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. The EASA AD requires reporting corrosion to 
Airbus Helicopters while this proposed AD would not.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) 
BO105-40A-107 for Model BO105C-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 117 A-1, MBB-BK 117 A-3, MBB-BK 
117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 
helicopters; and ASB MBB-BK117 C-2-62A-007 for Model MBB-BK 117 C-2 
helicopters, each Revision 5 and dated July 25, 2017. The FAA also 
reviewed Airbus Helicopters ASB MBB-BK117 D-2-62A-003, Revision 3, 
dated July 25, 2017, for Model MBB-BK 117 D-2 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 the following within 50 hours hours 
time-in-service (TIS):
    <bullet> Removing the affected bellows from the swashplate, 
cleaning and inspecting the support tube for scratches, and depending 
on the inspection results reworking the cylindrical area;
    <bullet> Inspecting the clamp for corrosion, damage and incorrect 
installation, and, depending on the inspection results, removing the 
clamp from service, reinstalling the clamp correctly and applying a 
torque;
    <bullet> Inspecting each ball bearing for corrosion, and depending 
on the inspection results, removing each ball bearing from service; and
    <bullet> Inspecting the deflection ring for foreign objects by 
removing the lockwire, screws, and the outer deflection ring and 
removing any foreign objects;
    The proposed AD would also require, within 400 hours TIS, 
inspecting the swashplate for foreign objects and excessive bearing 
rolling friction. Finally, this proposed AD would prohibit installing a 
bellows P/N 105-10113.05, P/N 4619305044, P/N 4638305043, or P/N 
B623M20X2240, or a gearbox with a bellows P/N 105-10113.05, P/N 
4619305044, or P/N 4638305043 on any helicopter.

Costs of Compliance

    The FAA estimates that this proposed AD would affect 211 
helicopters of U.S. Registry. The FAA estimates that operators may 
incur the following costs in order to comply with this proposed AD. 
Labor costs are estimated at $85 per work-hour.
    Inspecting the swashplate assembly would take about 3 work-hours 
for an estimated cost of $255 per helicopter and $53,805 for the U.S. 
fleet per inspection cycle.
    Repairing a scratched support tube would take about 3 work-hours 
for an estimated cost of $255 per helicopter.
    Replacing a corroded or damaged clamp would take about 2 work-hours 
and parts would cost about $8 for a cost of $178 per helicopter.
    Replacing corroded ball bearings would take about 4 work-hours and 
parts would cost about $3,000 for a cost of $3,340 per helicopter.
    Removing foreign objects from the outer deflection ring would take 
about 2 work-hours for an estimated 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.
    The FAA is 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

    The FAA 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

[[Page 13667]]

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. Will not affect intrastate aviation in Alaska, and
    3. 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.

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,
0
a. Removing Airworthiness Directive (AD) 2019-07-07, Amendment 39-19618 
(84 FR 16394, April 19, 2019) and,
0
b. Adding the following new AD:

Airbus Helicopters Deutschland GmbH: Docket No. FAA-2021-0135; 
Project Identifier MCAI-2020-01044-R.

(a) Applicability

    This airworthiness directive (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 swashplate 
bellows (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) Affected ADs

    This AD replaces AD 2019-07-07, Amendment 39-19618 (84 FR 16394, 
April 19, 2019) (2019-07-07).

(d) Comments Due Date

    The FAA must receive comments by April 26, 2021.

(e) 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.

(f) Required Actions

    (1) Within 50 hours time-in-service (TIS) after the effective 
date of this AD:
    (i) Remove from service bellows part number (P/N) 105-10113.05, 
P/N 4638305043, P/N 4619305044, or P/N B623M20X2240 from the 
swashplate assembly (swashplate).
    (ii) Clean and inspect the support tube for scratches as 
depicted in Detail 11, Figure 6 of Airbus Helicopters Alert Service 
Bulletin (ASB) BO105-40A-107 (ASB BO105-40A-107); or Detail 11, 
Figure 5 of ASB BO105 LS 40A-12 (ASB BO105 LS 40A-12); or Detail 11, 
Figure 5 of ASB MBB-BK117-40A-115, (ASB MBB-BK117-40A-115); or 
Detail 11, Figure 5 of ASB MBB-BK117 C-2-62A-007 (ASB MBB-BK117 C-2-
62A-007), each Revision 5 and dated July 25, 2017; or Detail 11, 
Figure 5 of ASB MBB-BK117 D-2-62A-003, Revision 3, dated July 25, 
2017 (ASB MBB-BK117 D-2-62A-003); as applicable to your model 
helicopter. If there are scratches on the support tube, before 
further flight, rework the cylindrical area to a max depth of 0.1 mm 
with a polishing cloth #400 or equivalent polishing cloth. The 
reworked area must not exceed 10 mm in width or 3 cm\2\ in area, the 
minimum separation between any adjacent reworked areas must be 30 
mm, and total reworked areas must not exceed 10 percent of the 
cylindrical area.
    (iii) Inspect the clamp for corrosion and correct installation.

    Note 1 to paragraph (f)(1)(iii): A figure of the clamp is 
depicted in Detail 9, Figure 6 of ASB BO105-40A-107; or Detail 9, 
Figure 5 of ASB BO105 LS 40A-12, ASB MBB-BK117-40A-115, or ASB MBB-
BK117 C-2-62A-007; or Detail 9, Figure 5 of ASB MBB-BK117 D-2-62A-
003; as applicable to your model helicopter.
    (A) If there is corrosion on the clamp, before further flight 
remove the clamp from service.
    (B) If the clamp is incorrectly installed, before further flight 
install the clamp correctly on the shield as depicted in Detail 10, 
Figure 6 of ASB BO105-40A-107; or Detail 10, Figure 5 of ASB BO105 
LS 40A-12, ASB MBB-BK117-40A-115, or ASB MBB-BK117 C-2-62A-007; or 
Detail 10, Figure 5 of ASB MBB-BK117 D-2-62A-003; as applicable to 
your model helicopter.
    (C) Apply a torque between 0.5 Nm and 0.7 Nm to the screw and 
install lockwire as depicted in Detail 8, Figure 6 of ASB BO105-40A-
107; or Detail 8, Figure 5 of ASB BO105 LS 40A-12, ASB MBB-BK117-
40A-115, or ASB MBB-BK117 C-2-62A-007; or Detail 8, Figure 5 of ASB 
MBB-BK117 D-2-62A-003; as applicable to your model helicopter.
    (iv) Inspect each ball bearing for corrosion. If there is 
corrosion on any ball bearing, before further flight, remove the 
ball bearing from service.
    (v) Inspect the area under the deflection ring for foreign 
objects by removing the lock wire, removing the screws, and removing 
the outer deflection ring. If there are any foreign objects, remove 
the foreign objects with a lint-free cloth.
    (2) Within 400 hours TIS after the effective date of this AD, 
after complying with the actions in paragraph (f)(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.4 of ASB BO105-40A-107; or paragraph 3.B.3 of 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; as applicable to your model helicopter.
    (3) After May 24, 2019 (the effective date of AD 2019-07-07), 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.
    (4) As of the effective date of this AD, do not install a 
bellows P/N B623M20X2240 on any helicopter.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Strategic Policy Rotorcraft Section, FAA, has 
the authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Validation Branch, send 
it to the attention of: Matt Fuller, AD Program Manager, Operational 
Safety Branch, Airworthiness Products Section, General Aviation & 
Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; 
telephone 817-222-5110; email <a href="/cdn-cgi/l/email-protection#caf3e78b9c99e78b8398e7fdf9fae78b8785898aacababe4ada5bc"><span class="__cf_email__" data-cfemail="c6ffeb879095eb878f94ebf1f5f6eb878b898586a0a7a7e8a1a9b0">[email protected]</span></a>.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(h) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (now European Union Aviation Safety Agency) (EASA) AD No. 
2016-0142R1, dated April 12, 2018. You may view the EASA AD on the 
internet at https://www.regulations.gov in the AD Docket.

(i) Subject

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

    Issued on March 2, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.

[FR Doc. 2021-04804 Filed 3-9-21; 8:45 am]
BILLING CODE 4910-13-P


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