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Federal Register / Vol. 86, No. 132 / Wednesday, July 14, 2021 / Rules and Regulations ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Cost per product
Cost on U.S.
operators
3 work-hours $85 per hour = $255

$0

$255

$11,220

The FAA estimates the following costs to do any necessary on-condition replacements that would be required
based on the results of any required actions. The FAA has no way of determining the number of helicopters
that might need these on-condition replacements:

ESTIMATED COSTS OF ON-CONDITION ACTIONS
Labor cost
Parts cost
Cost per product
Up to 20 work-hours $85 per hour = $1,700 per blade up to 4
blades.

Up to $23,100 per blade up to 4
blades.

Up to $24,800 per blade up to 4
blades.

Authority for This Rulemaking Title 49 of the United States Code specifies the FAAs 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 Agencys 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 helicopters identified in this rulemaking action.

lotter on DSK11XQN23PROD with RULES1

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 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.

VerDate Sep<11>2014

16:14 Jul 13, 2021

Jkt 253001

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

address bolted lead inner weights of the main rotor blade, which could loosen and cause cracking of the open blade trailing edge. The unsafe condition, if not addressed, could result in loss of control of the helicopter.

The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:

f Compliance
PART 39AIRWORTHINESS
DIRECTIVES

Within 30 days after the effective date of this AD, review the log card or equivalent record and visually inspect each main rotor blade to determine if any bolted main rotor blades i.e., main rotor blade with bolted lead inner weight are installed in accordance with paragraphs 2.A.1., 2.B.1., 2.B.2., and 2.B.3. of the Accomplishment Instructions of Eurocopter Alert Service Bulletin No. ASB
MBBBK11710125, dated February 14, 2005. If during the review, the total hours time-in-service TIS cannot be positively determined, this AD requires treating that part as having accumulated more than 3,000
total hours TIS. If any bolted main rotor blade i.e., main rotor blade with bolted lead inner weight is installed, replace the main rotor blade in accordance with paragraph 2.B.4. of the Accomplishment Instructions of Eurocopter Alert Service Bulletin ASB
MBBBK11710125, dated February 14, 2005, as follows:
1 For a bolted main rotor blade that has accumulated less than 2,300 total hours TIS
on the blade since bolting of the lead inner weight as of the effective date of this AD:
Before accumulating 2,500 total hours TIS on the blade since bolting of the lead inner weights.
2 For a bolted main rotor blade that has accumulated 2,300 total hours TIS up to 3,000 total hours TIS inclusive, on the blade since bolting of the lead inner weight as of the effective date of this AD: Within 200
hours TIS after the effective date of this AD.
3 For a bolted main rotor blade that has accumulated more than 3,000 total hours TIS
on the blade since bolting of the lead inner weight as of the effective date of this AD:
Within 50 hours TIS after the effective date of this AD.

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 adding the following new airworthiness directive:

20211405 Airbus Helicopters Deutschland GmbH: Amendment 39
21632; Docket No. FAA20210335;
Project Identifier MCAI202001665R.
a Effective Date This airworthiness directive AD is effective August 18, 2021.
b Affected ADs None.
c Applicability This AD applies to all Airbus Helicopters Deutschland GmbH Model MBBBK 117 A
1, MBBBK 117 A3, MBBBK 117 A4, MBBBK 117 B1, MBBBK 117 B2, and MBBBK 117 C1 helicopters, certificated in any category.
d Subject Joint Aircraft Service Component JASC
Code: 6210, Main Rotor Blades.
e Unsafe Condition This AD was prompted by a report of sudden severe vibrations and a cracked open blade trailing edge caused by a loosened lead inner weight. The FAA is issuing this AD to
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Comply with this AD within the compliance times specified, unless already done.
g Required Actions
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