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.

Proposed Rules Federal Register

13665 

Vol. 86, No. 45 

Wednesday, March 10, 2021 

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: 

• Federal eRulemaking Docket: Go to 

https://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 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 Matthew.Fuller@faa.gov. 

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 Matthew.Fuller@faa.gov. 

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 partVerDate Sep<11>2014 17:00 Mar 09, 2021 Jkt 253001 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 E:\FR\FM\10MRP1.SGM 10MRP1
13666 Federal Register / Vol. 86, No. 45 / Wednesday, March 10, 2021 / Proposed Rules 

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 overtorqueing 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, Dseries 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 timein-service (TIS): 

• 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; 

• 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; 

• Inspecting each ball bearing for 

corrosion, and depending on the 

inspection results, removing each ball 

bearing from service; and 

• 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 

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

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by, 

■ a. Removing Airworthiness Directive 

(AD) 2019–07–07, Amendment 39– 

19618 (84 FR 16394, April 19, 2019) 

and, 

■ 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 

cm2 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 9- 

AVS-AIR-730-AMOC@faa.gov. 

(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