Voglio sapere a riguardo di…

Federal Register / Vol. 86, No. 45 / Wednesday, March 10, 2021 / Proposed Rules 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 39AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.
39.13

Amended
2. The FAA amends 39.13 by, a. Removing Airworthiness Directive AD 20190707, Amendment 39
19618 84 FR 16394, April 19, 2019
and, b. Adding the following new AD:

Airbus Helicopters Deutschland GmbH:
Docket No. FAA20210135; Project Identifier MCAI202001044R.
a Applicability This airworthiness directive AD applies to Airbus Helicopters Deutschland GmbH
Model BO105A, BO105C, BO105S, BO105LS A3, MBBBK 117A1, MBBBK
117A3, MBBBK 117A4, MBBBK 117B1, MBBBK 117B2, MBBBK 117C1, MBB
BK 117C2, and MBBBK 117D2
helicopters, certificated in any category.
Note 1 to paragraph a of this AD:
Helicopters with an MBBBK 117C2e designation are Model MBBBK 117C2
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 20190707, Amendment 3919618 84 FR 16394, April 19, 2019 20190707.
d Comments Due Date The FAA must receive comments by April 26, 2021.

VerDate Sep<11>2014

17:00 Mar 09, 2021

Jkt 253001

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 10510113.05, 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 BO10540A107 ASB BO10540A
107; or Detail 11, Figure 5 of ASB BO105 LS
40A12 ASB BO105 LS 40A12; or Detail 11, Figure 5 of ASB MBBBK11740A115, ASB MBBBK11740A115; or Detail 11, Figure 5 of ASB MBBBK117 C262A007
ASB MBBBK117 C262A007, each Revision 5 and dated July 25, 2017; or Detail 11, Figure 5 of ASB MBBBK117 D262A
003, Revision 3, dated July 25, 2017 ASB
MBBBK117 D262A003; 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 f1iii: A figure of the clamp is depicted in Detail 9, Figure 6
of ASB BO10540A107; or Detail 9, Figure 5 of ASB BO105 LS 40A12, ASB MBB
BK11740A115, or ASB MBBBK117 C2
62A007; or Detail 9, Figure 5 of ASB MBB
BK117 D262A003; 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 BO10540A107; or Detail 10, Figure 5 of ASB BO105 LS 40A
12, ASB MBBBK11740A115, or ASB
MBBBK117 C262A007; or Detail 10, Figure 5 of ASB MBBBK117 D262A003;
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
40A107; or Detail 8, Figure 5 of ASB BO105
LS 40A12, ASB MBBBK11740A115, or ASB MBBBK117 C262A007; or Detail 8, Figure 5 of ASB MBBBK117 D262A003;
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
PO 00000

Frm 00003

Fmt 4702

Sfmt 9990

13667

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 f1 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 BO10540A107; or paragraph 3.B.3 of ASB BO105 LS 40A12, ASB MBB
BK11740A115, ASB MBBBK117 C2
62A007, or ASB MBBBK117 D262A
003; as applicable to your model helicopter.
3 After May 24, 2019 the effective date of AD 20190707, do not install a bellows P/N 10510113.05, P/N 4619305044, or P/N
4638305043, or a gearbox with a bellows P/
N 10510113.05, 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 8172225110; email 9AVS-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. 20160142R1, 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. 202104804 Filed 3921; 8:45 am BILLING CODE 491013P

E:FRFM10MRP1.SGM

10MRP1