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Federal Register / Vol. 86, No. 104 / Wednesday, June 2, 2021 / Rules and Regulations 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 has determined that 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 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.
Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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:

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20211021 Airbus Helicopters Deutschland GmbH: Amendment 39
21554; Docket No. FAA20210135;
Project Identifier MCAI202001044R.
a Effective Date This airworthiness directive AD is effective July 7, 2021.
b Affected ADs This AD replaces AD 20190707, Amendment 3919618 84 FR 16394, April 19, 2019 20190707.

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c Applicability This AD applies to Airbus Helicopters Deutschland GmbH Model BO105A, BO
105C, BO105S, BO105LS A3, MBBBK
117A1, MBBBK 117A3, MBBBK 117A
4, MBBBK 117B1, MBBBK 117B2, MBB
BK 117C1, MBBBK 117C2, and MBBBK
117D2 helicopters, certificated in any category.
d Subject Joint Aircraft Service Component JASC
Code: 6200, Main Rotor System.
e Unsafe Condition This AD was prompted by a lower clamp found missing from the swashplate bellows bellows and damaging the swashplate bearing ring before becoming detached. The FAA is issuing this AD to prevent a loose bellows clamp. The unsafe condition, if not addressed, could result in 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.
f Compliance Comply with this AD within the compliance times specified, unless already done.
g 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 ASB BO10540A107 ASB BO105
40A107; or Detail 11, Figure 5 of ASB
BO105 LS40A12 ASB BO105 LS 40A12;
or Detail 11, Figure 5 of ASB MBBBK117
40A115, ASB MBBBK11740A115; or Detail 11, Figure 5 of ASB MBBBK117 C
262A007 ASB MBBBK117 C262A
007, each Revision 5 and dated July 25, 2017; or Detail 11, Figure 5 of ASB MBB
BK117 D262A003, 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 g1iii: A figure of the clamp is depicted in Detail 9, Figure 6
of ASB BO10540A107; or Detail 9, Figure 5 of ASB BO105 LS40A12, 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.

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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 LS40A
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
LS40A12, 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 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 g1 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 LS40A12, 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.
h Alternative Methods of Compliance AMOCs 1 The Manager, International Validation Branch, 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 the person identified in paragraph i1 of this AD.
Information may be emailed to: 9-AVS-AIR730-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.
i Related Information 1 For more information about this AD, 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 9-AVS-AIR-730-AMOC@faa.gov.

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