Federal Register / Vol. 86, No. 132 / Wednesday, July 14, 2021 / Rules and Regulations 37017 

Issued in Des Moines, Washington, on July 

7, 2021. 

Mary A. Schooley, 

Acting Manager, Technical Innovation Policy 

Branch, Policy and Innovation Division, 

Aircraft Certification Service. 

[FR Doc. 2021–14975 Filed 7–13–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0335; Project 

Identifier MCAI–2020–01665–R; Amendment 

39–21632; AD 2021–14–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus Helicopters Deutschland GmbH 

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. 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. This AD requires 

inspections to determine if any bolted 

main rotor blades are installed, and 

replacement of the affected main rotor 

blades. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective August 18, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of August 18, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, 2701 N Forum 

Drive, Grand Prairie, TX 75052; phone: 

972–641–0000 or 800–232–0323; fax: 

972–641–3775; or at https://

www.airbus.com/helicopters/services/- 

support.html. You may view the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. Service information that is 

incorporated by reference is also 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0335. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0335; 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 

final rule, the Luftfahrt-Bundesamt AD, 

any comments received, and other 

information. The street address for 

Docket Operations is U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Kathleen Arrigotti, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

phone and fax: 206–231–3218; email: 

kathleen.arrigotti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Airbus Helicopters 

Deutschland GmbH 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. 

The NPRM published in the Federal 

Register on April 26, 2021 (86 FR 

21965). In the NPRM, the FAA proposed 

to require inspections to determine if 

any bolted main rotor blades are 

installed, and replacement of the 

affected main rotor blades. The NPRM 

was prompted by a report of sudden 

severe vibrations and a cracked open 

blade trailing edge caused by a loosened 

lead inner weight. 

German AD D–2005–115, effective 

March 15, 2005 (German AD D–2005– 

115), issued by Luftfahrt-Bundesamt, 

which is the aviation authority for 

Germany, was issued to correct an 

unsafe condition for Eurocopter 

Deutschland (now Airbus Helicopters 

Deutschland GmbH) 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. Luftfahrt-Bundesamt 

advises that during the flight of a BK117 

severe vibrations suddenly occurred, 

stemming from a cracked open blade 

trailing edge, which was traced to a 

loosened lead inner weight bolt. 

Additional inspection revealed extreme 

cavities of the lead weight resulting 

from the bolting process, which was 

performed as a repair for main rotor 

blades with bulging in the area of the 

lead inner weights. This condition, if 

not addressed, could result in loss of 

control of the helicopter. 

Accordingly, German AD D–2005–115 

requires an inspection and log card 

review to determine if any bolted main 

rotor blades are installed, and 

replacement of the affected main rotor 

blades. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 

Conclusion 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to the FAA’s 

bilateral agreement with Germany (now 

a member of the European Union), 

Luftfahrt-Bundesamt, its technical 

representative, has notified the FAA of 

the unsafe condition described in its 

AD. The FAA reviewed the relevant 

data and determined that air safety 

requires adopting this AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

helicopters. Except for minor editorial 

changes, this AD is adopted as proposed 

in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Eurocopter Alert 

Service Bulletin No. ASB–MBB–BK117– 

10–125, dated February 14, 2005. This 

service information specifies procedures 

for an inspection (for cracking of the 

paint) and log card review (for a certain 

entry or equivalent) to determine if any 

bolted main rotor blades (i.e., main rotor 

blades with bolted lead inner weights) 

are installed, and replacement of the 

affected main rotor blades. 

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. 

Costs of Compliance 

The FAA estimates that this AD 

affects 44 helicopters of U.S. Registry. 

Labor rates are estimated at $85 per 

work-hour. Based on these numbers, the 

FAA estimates the following costs to 

comply with this AD. 


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37018 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 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 helicopters identified in this 

rulemaking action. 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 adding 

the following new airworthiness 

directive: 

2021–14–05 Airbus Helicopters 

Deutschland GmbH: Amendment 39– 

21632; Docket No. FAA–2021–0335; 

Project Identifier MCAI–2020–01665–R. 

(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 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, 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 

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. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

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– 

MBB–BK117–10–125, 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– 

MBB–BK117–10–125, 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. 


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Federal Register / Vol. 86, No. 132 / Wednesday, July 14, 2021 / Rules and Regulations 37019 

(h) Contacting the Manufacturer To 

Determine TIS 

Where Eurocopter Alert Service Bulletin 

ASB–MBB–BK117–10–125, dated February 

14, 2005, specifies to send a form to the 

manufacturer to determine TIS since bolting, 

this AD does not include that requirement. 

(i) 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 (j)(1) 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Kathleen Arrigotti, Aerospace 

Engineer, Large Aircraft Section, 

International Validation Branch, FAA, 2200 

South 216th St., Des Moines, WA 98198; 

phone and fax: 206–231–3218; email: 

kathleen.arrigotti@faa.gov. 

(2) The subject of this AD is addressed in 

Luftfahrt-Bundesamt German AD D–2005– 

115, effective March 15, 2005. You may view 

the Luftfahrt-Bundesamt German AD at 

https://www.regulations.gov in Docket No. 

FAA–2021–0335. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Eurocopter Alert Service Bulletin No. 

ASB–MBB–BK117–10–125, dated February 

14, 2005. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Airbus Helicopters, 2701 N 

Forum Drive, Grand Prairie, TX 75052; 

phone: 972–641–0000 or 800–232–0323; fax: 

972–641–3775; or at https://www.airbus.com/ 

helicopters/services/-support.html. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

email: fedreg.legal@nara.gov, or go to: 

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on July 8, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–14925 Filed 7–13–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0566; Project 

Identifier MCAI–2021–00733–T; Amendment 

39–21651; AD 2021–15–04] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 767–300 

series airplanes as modified by a certain 

supplemental type certificate (STC). 

This AD was prompted by a report that 

the electrical diagram for the C9066 

circuit breaker connection (wiring) for 

the ‘‘Main Deck Oxygen Alert Control’’ 

is erroneous and might have resulted in 

incorrect installation. This AD requires 

inspecting the wiring connection 

common to the C9066 circuit breaker 

and, if necessary, making changes to the 

wiring connection and testing the main 

deck oxygen alert system. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD becomes effective July 

14, 2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 14, 2021. 

The FAA must receive comments on 

this AD by August 30, 2021. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

https://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this final rule, contact Israel Aerospace 

Industries, Ltd., Ben Gurion Airport, 

Israel 70100; telephone 972–39359826; 

email tmazor@iai.co.il. You may view 

this referenced service information at 

the FAA, Airworthiness Products 

Section, Operational Safety Branch, 

2200 South 216th St., Des Moines, WA. 

For information on the availability of 

this material at the FAA, call 206–231– 

3195. It is also available on the internet 

at https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0566. 

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– 

0566; or in person at the Docket 

Operations office between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, any comments 

received, and other information. The 

street address for the Docket Operations 

office is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Brian Hernandez, Aerospace Engineer, 

Systems and Equipment Section, FAA, 

Seattle ACO Branch, 2200 South 216th 

St., Des Moines, WA 98198; phone and 

fax: 206–231–3535; email: 

Brian.Hernandez@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The Civil Aviation Authority of Israel 

(CAAI), which is the aviation authority 

for Israel, has issued Israeli AD ISR–I– 

24–2021–6–6R1, dated June 27, 2021 

(also referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for The Boeing 

Company Model 767–300 series 

airplanes, that have been modified to a 

Bedek Division Special Freighter 

(BDSF), designated as 767–300BDSF, in 

accordance with CAAI STC SA218/FAA 

STC ST02040SE/European Union 

Aviation Safety Agency (EASA) STC 

10028430 (as listed in the appendix of 

the MCAI). Only FAA STC ST02040SE 

is approved for U.S. operators. You may 

examine the MCAI on the internet at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0566. 

This AD was prompted by a report 

that the electrical diagram for the C9066 

circuit breaker connection (wiring) for 

the ‘‘Main Deck Oxygen Alert Control’’ 

is erroneous and might have resulted in 


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