Federal Register / Vol. 86, No. 119 / Thursday, June 24, 2021 / Rules and Regulations 33103 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2021–10–11 The Boeing Company: 

Amendment 39–21544; Docket No. 

FAA–2021–0026 Project Identifier AD– 

2020–01164–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 29, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE does not affect 

the ability to accomplish the actions required 

by this AD. Therefore, for airplanes on which 

STC ST01219SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a report 

indicating that a crack was found on the 

splice angle flange that is attached to the 

station (STA) 540 bulkhead in the area 

between stringer 21 to stringer 22. The FAA 

is issuing this AD to address any cracking in 

the splice angle, which could result in the 

inability of a principal structural element to 

sustain limit load and could adversely affect 

the structural integrity of the airplane; in 

addition, such cracking could lead to 

adjoining parts cracking and a potential fuel 

leak and consequent fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For airplanes identified as Group 1 in 

Boeing Alert Requirements Bulletin 737– 

57A1347 RB, dated July 29, 2020: Within 120 

days after the effective date of this AD, 

inspect the airplane and do all applicable oncondition actions using a method approved 

in accordance with the procedures specified 

in paragraph (i) of this AD. 

(2) For airplanes identified as Group 2 in 

Boeing Alert Requirements Bulletin 737– 

57A1347 RB, dated July 29, 2020: Except as 

specified by paragraph (h) of this AD, at the 

applicable times specified in the 

‘‘Compliance’’ paragraph of Boeing Alert 

Requirements Bulletin 737–57A1347 RB, 

dated July 29, 2020, do all applicable actions 

identified in, and in accordance with, the 

Accomplishment Instructions of Boeing Alert 

Requirements Bulletin 737–57A1347 RB, 

dated July 29, 2020. 

Note 1 to paragraph (g): Guidance for 

accomplishing the actions required by this 

AD can be found in Boeing Alert Service 

Bulletin 737–57A1347, dated July 29, 2020, 

which is referred to in Boeing Alert 

Requirements Bulletin 737–57A1347 RB, 

dated July 29, 2020. 

(h) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Requirements 

Bulletin 737–57A1347 RB, dated July 29, 

2020, uses the phrase ‘‘the original issue date 

of Requirements Bulletin 737–57A1347 RB,’’ 

this AD requires using ‘‘the effective date of 

this AD.’’ 

(2) Where Boeing Alert Requirements 

Bulletin 737–57A1347 RB, dated July 29, 

2020, specifies contacting Boeing for repair 

instructions: This AD requires doing the 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO 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 responsible Flight 

Standards Office, as appropriate. If sending 

information directly to the manager of the 

certification office, send it to the attention of 

the person identified in paragraph (j)(1) of 

this AD. Information may be emailed to: 9- 

ANM-LAACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by The Boeing Company 

Organization Designation Authorization 

(ODA) that has been authorized by the 

Manager, Los Angeles ACO Branch, FAA, to 

make those findings. To be approved, the 

repair method, modification deviation, or 

alteration deviation must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(j) Related Information 

(1) For more information about this AD, 

contact Wayne Ha, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5238; fax: 562–627–5210; email: Wayne.Ha@

faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (k)(3) and (4) of this AD. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) 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) Boeing Alert Requirements Bulletin 

737–57A1347 RB, dated July 29, 2020. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; internet https://

www.myboeingfleet.com. 

(4) You may view this 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. 

(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/ibrlocations.html. 

Issued on April 30, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–13122 Filed 6–23–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0254; Project 

Identifier MCAI–2020–00481–R; Amendment 

39–21595; AD 2021–12–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH (AHD) 

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 

(AHD) Model MBB–BK 117 D–2 

helicopters. This AD was prompted by 

reports of chafing marks on the wiring 

harness behind the middle side panels 

in the area of the front passenger (PAX) 

panels. This AD requires inspecting, 

modifying, and rerouting the wiring 

harness, as specified in a European 

Union Aviation Safety Agency (EASA) 

AD, which is incorporated by reference. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective July 29, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 29, 2021. 


khammond on DSKJM1Z7X2PROD with RULES
33104 Federal Register / Vol. 86, No. 119 / Thursday, June 24, 2021 / Rules and Regulations 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, contact 

the EASA, Konrad-Adenauer-Ufer 3, 

50668 Cologne, Germany; telephone +49 

221 8999 000; email ADs@

easa.europa.eu; internet 

www.easa.europa.eu. You may find this 

IBR information on the EASA website at 

https://ad.easa.europa.eu. For service 

information identified in this final 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 http://

www.airbushelicopters.com/techpub. 

You may view this material 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. It is also available 

in the AD docket on the internet at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0254. 

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– 

0254; 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, 

any comments received, and other 

information. The 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: 

Blaine Williams, Aerospace Engineer, 

Los Angeles ACO Branch, Compliance & 

Airworthiness Division, 3960 

Paramount Blvd., Lakewood, CA 90712; 

telephone 562–627–5371; email 

blaine.williams@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The EASA, which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2019–0305, dated December 17, 2019 

(EASA AD 2019–0305), to correct an 

unsafe condition for all Airbus 

Helicopters Deutschland GmbH Model 

MBB–BK117 D–2 helicopters. 

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–BK117 

D–2 helicopters. The NPRM published 

in the Federal Register on April 2, 2021 

(86 FR 17330). The NPRM was 

prompted by reports of chafing marks 

on the wiring harness behind the 

middle side panels in the area of the 

front PAX panels. The NPRM proposed 

to require inspecting, modifying, and 

rerouting the wiring harness, as 

specified in the EASA AD. 

The FAA is issuing this AD to prevent 

electrical failure of the helicopter wiring 

harness. See the EASA AD for 

additional background information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The FAA received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Conclusion 

The FAA reviewed the relevant data 

and determined that air safety and the 

public interest require adopting this 

final rule as proposed. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2019–0305 specifies 

inspecting the wiring harness installed 

behind the front PAX panel of the left 

and right hand middle side panels and 

depending on the results, repairing or 

modifying the wiring harness. For a 

modified wiring harness, EASA AD 

2019–0305 specifies repetitively 

inspecting for damage. 

The FAA also reviewed Airbus 

Helicopters Alert Service Bulletin (ASB) 

MBB–BK117 D–2–88A–003, Revision 1 

and dated December 9, 2019 (ASB 

MBB–BK117 D–2–88A–003). ASB 

MBB–BK117 D–2–88A–003 applies to 

Model MBB–BK–117 D–2 and D–2m 

helicopters. This service information 

specifies inspecting, repairing, and 

modifying the wiring harness installed 

behind the front PAX panel of the left 

and right hand middle side panels. This 

material 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. 

Differences Between This AD and the 

EASA AD 

Where the EASA AD refers to flight 

hours, this AD uses hours time-inservice (TIS) instead. Where the EASA 

AD allows a tolerance to the compliance 

time of certain initial and repetitive 

inspections, this AD requires a 

compliance time of within 440 hours 

TIS after modification of an affected part 

for a certain initial inspection and 

thereafter at intervals within 440 hours 

TIS for certain repetitive inspections 

instead. Where the EASA AD requires 

repetitive inspections in accordance 

with paragraph 3.B.8. of ASB MBB– 

BK117 D–2–88A–003, this AD requires 

repetitive inspections in accordance 

with paragraph 3.B.9. of ASB MBB– 

BK117 D–2–88A–003. 

Costs of Compliance 

The FAA estimates that this AD 

affects 60 helicopters of U.S. Registry. 

Labor rates are estimated at $85 per 

work-hour. Based on these numbers, the 

FAA estimates that operators may incur 

the following costs in order to comply 

with this AD. Inspecting the wiring 

harness takes about 6 work-hours for an 

estimated cost of $510 per helicopter 

and $30,600 for the U.S. fleet, per 

inspection cycle. Modification during 

the inspection of the wiring harness 

takes about 6 work-hours for an 

estimated cost of $510 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 

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 


khammond on DSKJM1Z7X2PROD with RULES
Federal Register / Vol. 86, No. 119 / Thursday, June 24, 2021 / Rules and Regulations 33105 

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: 

2021–12–08 Airbus Helicopters 

Deutschland GmbH (AHD): Amendment 

39–21595; Docket No. FAA–2021–0254; 

Project Identifier MCAI–2020–00481–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 29, 2021. 

((b) Affected Airworthiness Directives 

None. 

(c) Applicability 

This AD applies to all Airbus Helicopters 

Deutschland GmbH (AHD) Model MBB–BK 

117 D–2 helicopters, certificated in any 

category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code: 1497, Miscellaneous Wiring. 

(e) Reason 

This AD was prompted by reports of 

chafing marks found on the wiring harness 

behind the middle side panels, in the area of 

the front passenger panels. Further 

investigations identified low clearance 

between the harness and the surrounding 

structure. Airbus Helicopters identified the 

cause of the chafing marks as contact of the 

harness with the front passenger panel 

screws. The FAA is issuing this AD to 

prevent electrical failure of the helicopter 

wiring harness. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

((g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, European Union Aviation 

Safety Agency (EASA) AD 2019–0305, dated 

December 17, 2019 (EASA AD 2019–0305). 

(h) Exceptions to EASA AD 2019–0305 

(1) Where EASA AD 2019–0305 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where EASA AD 2019–0305 refers to 

flight hours (FH), this AD requires using 

hours time-in-service (TIS). 

(3) Where paragraph (6) of EASA AD 2019– 

0305 specifies a compliance time for the 

initial inspection of within 400 flight hours 

after the modification of an affected part and 

thereafter at intervals not exceeding 400 

flight hours, plus a non-cumulative tolerance 

of 40 flight hours, this AD requires a 

compliance time of within 440 hours TIS 

after the modification of an affected part for 

the initial inspection and thereafter at 

intervals not exceeding 440 hours TIS. 

(4) Where paragraph (6) of EASA AD 

specifies repetitive inspections in accordance 

with paragraph 3.B.8. of the referenced Alert 

Service Bulletin (ASB), this AD requires 

repetitive inspections in accordance with 

paragraph 3.B.9. of ASB MBB–BK117 D–2– 

88A–003, Revision 1 and dated December 9, 

2019. 

(5) Where the service information 

referenced in EASA AD 2019–0305 specifies 

to use tooling, equivalent tooling may be 

used. 

(6) The ‘‘Remarks’’ section of EASA AD 

2019–0305 does not apply to this AD. 

(i) Special Flight Permit 

Special flight permits, as described in 14 

CFR 21.197 and 21.199, are not allowed. 

(j) 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 (k) 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. 

(k) Related Information 

For more information about this AD, 

contact Blaine Williams, Aerospace Engineer, 

Los Angeles ACO Branch, Compliance & 

Airworthiness Division, 3960 Paramount 

Blvd., Lakewood, CA 90712; telephone 562– 

627–5371; email blaine.williams@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) 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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2019–0305, dated December 17, 

2019. 

(ii) Airbus Helicopters Alert Service 

Bulletin ASB MBB–BK117 D–2–88A–003, 

Revision 1, dated December 9, 2019. 

(3) For EASA AD 2019–0305, contact the 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email ADs@easa.europa.eu; internet 

www.easa.europa.eu. You may find this 

EASA AD on the EASA website at https://

ad.easa.europa.eu. 

(4) For Airbus Helicopters Alert Service 

Bulletin ASB MBB–BK117 D–2–88A–003, 

Revision 1, contact Airbus Helicopters, 2701 

North 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. 

(5) 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. This 

material may be found in the AD docket on 

the internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0254. 

(6) You may view this material 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 May 28, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–13128 Filed 6–23–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0448; Project 

Identifier MCAI–2021–00044–T; Amendment 

39–21591; AD 2021–12–04] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Fokker Services B.V. Model F28 Mark 

0070 and 0100 airplanes. This AD was 

prompted by a report that corrosion was 

found on the horizontal flange on the 

front spar lower boom, between the 

rebate strap and the lower boom, and 


khammond on DSKJM1Z7X2PROD with RULES