36638 Federal Register / Vol. 86, No. 131 / Tuesday, July 13, 2021 / Rules and Regulations 

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

2018–0172 does not apply to this AD. 

(4) Where paragraph (1) of EASA AD 2018– 

0172 specifies to inspect each affected part, 

for this AD, prior to the inspection for 

corrosion, inspect the protective coating on 

the inside of the attachment pin for scratches 

and missing protective coating. If there is any 

scratch or any missing protective coating, 

prior to the inspection for corrosion, sand the 

attachment pin to remove the varnish in the 

area depicted as ‘‘Area A’’ in Figure 1 of the 

‘‘applicable ASB’’ as defined in EASA AD 

2018–0172. 

(5) Where paragraph (3) of EASA AD 2018– 

0172 requires removing corrosion, for this 

AD, if there is any corrosion pitting, before 

further flight, replace the affected attachment 

pin. Do not sand the attachment pin to 

remove a corrosion pit. 

(6) Although the service information 

referenced in EASA AD 2018–0172 specifies 

to do a non-destructive inspection if in doubt 

about whether there is a crack, that action is 

not required by this AD. 

(7) Although the service information 

referenced in EASA AD 2018–0172 specifies 

contacting Airbus Helicopters if any 

attachment pin with a crack is found and 

returning that part to Airbus Helicopters, 

those actions are not required by this AD. 

(8) Although the service information 

referenced in EASA AD 2018–0172 specifies 

discarding certain parts, that action is not 

required by this AD. 

(9) Where EASA AD 2018–0172 refers to 

flight hours (FH), this AD requires using 

hours time-in-service. 

(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 Katherine Venegas, Aviation Safety 

Engineer, Cabin Safety, Mechanical and 

Environmental Systems Section, Los Angeles 

ACO Branch, FAA, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5353; email: 

katherine.venegas@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 Aviation Safety Agency 

(EASA) AD 2018–0172, dated August 7, 

2018. 

(ii) [Reserved] 

(3) For EASA AD 2018–0172, contact the 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; phone: +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) 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–2020–1033. 

(5) 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 June 17, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–14775 Filed 7–12–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0195; Project 

Identifier MCAI–2020–00262–R; Amendment 

39–21624; AD 2021–13–19] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2014–11– 

02 for Airbus Helicopters Model SA– 

365N, SA–365N1, AS–365N2, and AS 

365 N3 helicopters. AD 2014–11–02 

required repetitively inspecting frame 

number (No.) 9 for a crack. This AD was 

prompted by Airbus Helicopters 

developing a modification that provides 

an optional terminating action for the 

repetitive inspections required by AD 

2014–11–02. This AD retains the 

requirements of AD 2014–11–02, 

provides an optional terminating action 

for the repetitive inspections, and 

reduces the applicability by excluding 

certain post-modified helicopters. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective August 17, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 17, 2021. 

ADDRESSES: For service information 

identified in this final rule, 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. 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. Service information 

that is incorporated by reference is also 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0195. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.govby 

searching for and locating Docket No. 

FAA–2021–0195; 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 European Union Aviation 

Safety Agency (EASA) AD, 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: Matt 

Fuller, AD Program Manager, General 

Aviation & Rotorcraft Unit, 

Airworthiness Products Section, 

Operational Safety Branch, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

matthew.fuller@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2014–11–02, 

Amendment 39–17852 (79 FR 33050, 

June 10, 2014) (AD 2014–11–02). AD 

2014–11–02 applied to Airbus 

Helicopters (previously Eurocopter 


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Federal Register / Vol. 86, No. 131 / Tuesday, July 13, 2021 / Rules and Regulations 36639 

France) Model SA–365N, SA–365N1, 

AS–365N2, and AS 365 N3 helicopters. 

The NPRM published in the Federal 

Register on April 22, 2021 (86 FR 

21231). The NPRM proposed to 

continue to require, for helicopters that 

have a No. 9 frame that has had any 

repair or alteration made, within 10 

hours time-in-service (TIS) after the 

effective date of the AD and at intervals 

not to exceed 110 hours TIS thereafter, 

inspecting the LH and RH frame No. 9 

for a crack in the areas of the latch 

support and stretcher support with a 

10X or higher power magnifying glass. 

For all other helicopters, the NPRM 

proposed to require the inspection 

within 110 hours TIS after the effective 

date of the AD and thereafter at intervals 

not to exceed 110 hours TIS. If there is 

a crack, the NPRM proposed to continue 

to require, before further flight, 

repairing the crack. The NPRM also 

proposed to provide an optional 

terminating action for the repetitive 

inspections that would consist of 

installing Eurocopter modification 

(MOD) 53C17 or MOD 53D02, or Airbus 

Helicopters MOD 07 53D21 or MOD 07 

53D22, as applicable to your helicopter. 

The NPRM was prompted by EASA 

AD 2012–0108R1, dated September 19, 

2019 (EASA AD 2012–0108R1), issued 

by EASA, which is the Technical Agent 

for the Member States of the European 

Union, to correct an unsafe condition 

for certain Airbus Model helicopters 

except those that have been modified by 

Eurocopter MOD 53C17 or MOD 53D02, 

or Airbus Helicopters (AH) MOD 07 

53D21 or MOD 07 53D22. EASA AD 

2012–0108R1 revises EASA AD 2012– 

0108–E, dated June 15, 2012 (EASA AD 

2012–0108–E), which was issued after a 

crack was discovered during the ‘‘T’’ 

inspection of an AS365 helicopter. The 

crack started at a rivet hole of a doubler 

that was installed on the frame No. 9 in 

accordance with Eurocopter Alert 

Service Bulletin No. 53.00.42, dated 

January 31, 2001. EASA stated in EASA 

AD 2012–0108–E that structural 

alteration of frame No. 9 by 

modifications or repairs can result in 

fatigue crack initiation under normal 

operational loads. According to EASA, 

this condition, if not corrected, could 

lead to crack propagation and failure of 

frame No. 9, which would adversely 

affect the structural integrity of the 

helicopter. For these reasons, EASA AD 

2012–0108–E required repetitive 

inspections of frame No. 9 for a crack in 

the area of the doubler or any repair 

performed in the area of the latch 

support and stretcher support. EASA 

advises in EASA AD 2012–0108R1 that 

Airbus Helicopters developed MOD 07 

53D21 and MOD 07 53D22. 

Consequently, EASA AD 2012–0108R1 

was issued to introduce the MODs as 

optional terminating action for the 

repetitive inspections, reduce the 

applicability by excluding certain postMOD helicopters, and make some 

editorial changes that do not affect the 

required actions. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM nor on the determination of 

the costs. 

Conclusion 

These helicopters have been approved 

by EASA and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the 

European Union, EASA has notified the 

FAA about 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. 

Related Service Information Under 1 

CFR Part 51 

Airbus Helicopters has co-published 

as one document Emergency Alert 

Service Bulletin EASB No. 05.00.63, 

Revision 2, dated December 20, 2018 

(EASB 05.00.63 Rev 2), for Model 

AS365-series helicopters and EASB No. 

05.00.30, Revision 2, dated December 

20, 2018 (EASB 05.00.30 Rev 2), for 

non-FAA type certificated Model 

AS565-series helicopters. EASB 

05.00.63 Rev 2 is incorporated by 

reference in this AD; EASB 05.00.30 Rev 

2 is not. 

EASB 05.00.63 Rev 2 applies to 

helicopters with a frame No. 9 that has 

not been modified by MOD 07 53C17, 

07 53D21, 07 53D22, or 07 53D02, and 

that has had doublers installed or 

repairs performed in accordance with 

certain service instructions. EASB 

05.00.63 Rev 2 describes procedures for 

inspecting the frame No. 9 for a crack 

and specifies contacting Airbus 

Helicopters for further procedures if 

there is a crack. 

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. 

Other Related Service Information 

The FAA reviewed Airbus Helicopters 

Service Bulletin SB No. AS365– 

53.00.57, Revision 0, dated December 

20, 2018 (SB AS365–53.00.57), for 

Model AS365-series helicopters. SB 

AS365–53.00.57 specifies replacing the 

upper section of the No. 9 frame with a 

reinforced version as an option to 

terminate the visual inspections 

specified in EASB 05.00.63 Rev 2. 

The FAA also reviewed Eurocopter 

Emergency Alert Service Bulletin EASB 

No. 05.00.63, Revision 1, dated June 18, 

2012 (EASB 05.00.63 Rev 1). EASB 

05.00.63 Rev 1 specifies the same 

procedures as EASB 05.00.63 Rev 2; 

however, EASB 05.00.63 Rev 2 excludes 

helicopters with certain MODs installed 

from its effectivity. 

Differences Between This AD and the 

EASA AD 

EASA AD 2012–0108R1 requires 

contacting Airbus Helicopters for repair 

instructions if there is a crack; this AD 

does not. EASA AD 2012–0108R1 

applies to Airbus Helicopters Model 

365-series helicopters with a frame No. 

9 on which certain doublers or repairs 

have been accomplished; this AD 

applies to those model helicopters 

regardless of if those doublers or repairs 

have been accomplished. 

Costs of Compliance 

The FAA estimates that this AD 

affects 33 helicopters of U.S. Registry. 

The FAA estimates that operators may 

incur the following costs in order to 

comply with this AD. At an average 

labor rate of $85 per hour, inspecting 

the LH and RH frame No. 9 takes about 

3 work-hours, for a cost per helicopter 

of $255 and a total cost to U.S. operators 

of $8,415 per inspection cycle. 

Repairing a cracked frame No. 9 takes 

about 20 work-hours, and required parts 

cost about $15,000, for a cost per 

helicopter of $16,700. 

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 


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36640 Federal Register / Vol. 86, No. 131 / Tuesday, July 13, 2021 / Rules and Regulations 

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 

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: 

■ a. Removing Airworthiness Directive 

(AD) 2014–11–02, Amendment 39– 

17852 (79 FR 33050, June 10, 2014); and 

■ b. Adding the following new AD: 

2021–13–19 Airbus Helicopters: 

Amendment 39–21624; Docket No. 

FAA–2021–0195; Project Identifier 

MCAI–2020–00262–R. 

(a) Applicability 

This airworthiness directive (AD) applies 

to Airbus Helicopters Model SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters, certificated in any category, 

except helicopters with Eurocopter 

modification (MOD) 53C17 or MOD 53D02, 

or Airbus Helicopters MOD 07 53D21 or 

MOD 07 53D22, installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in frame number (No.) 9, which if not 

detected and corrected, could result in failure 

of frame No. 9, loss of structural integrity, 

and subsequent loss of control of the 

helicopter. 

(c) Affected ADs 

This AD replaces AD 2014–11–02, 

Amendment 39–17852 (79 FR 33050, June 

10, 2014). 

(d) Effective Date 

This AD is effective August 17, 2021. 

(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) For helicopters that have any repair or 

alteration to the frame No. 9, within 10 hours 

time-in-service (TIS) after the effective date 

of this AD and thereafter at intervals not to 

exceed 110 hours TIS, using a 10X or higher 

power magnifying glass, inspect the left-hand 

(LH) and right-hand (RH) frame No. 9 for a 

crack in the area of the latch support and 

stretcher support, as depicted in Figure 1 of 

Airbus Helicopters Emergency Alert Service 

Bulletin EASB No. 05.00.63, Revision 2, 

dated December 20, 2018 (EASB 05.00.63). 

(2) For all other helicopters, within 110 

hours TIS after the effective date of this AD 

and thereafter at intervals not to exceed 110 

hours TIS, perform the inspection in 

paragraph (f)(1) of this AD. 

(3) If there is a crack, before further flight, 

repair the frame No. 9. Repairing a frame is 

not terminating action for the repetitive 

inspections required by paragraphs (f)(1) and 

(2) of this AD. 

(4) As an optional terminating action for 

the repetitive inspections required by 

paragraphs (f)(1) and (2) of this AD, replace 

the upper section of frame No. 9 with a 

reinforced frame, Eurocopter MOD 53C17 or 

MOD 53D02, or Airbus Helicopters MOD 07 

53D21 or MOD 07 53D22. 

(g) Special Flight Permits 

Special flight permits to a repair facility 

may be issued provided that the flight does 

not exceed 10 hours TIS, any crack does not 

exceed a maximum crack length of 80 mm, 

and no passengers are onboard. 

(h) Credit for Previous Actions 

You may take credit for the actions 

required by paragraphs (f)(1) and (2) of this 

AD if you performed them before the 

effective date of this AD using Eurocopter 

Emergency Alert Service Bulletin EASB No. 

05.00.63, Revision 1, dated June 18, 2012. 

(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 office, send it to the attention of the 

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

AD. Information may be emailed to: 9-AVSAIR-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. 

(j) Related Information 

(1) For more information about this AD, 

contact Matthew Fuller, AD Program 

Manager, General Aviation & Rotorcraft Unit, 

Airworthiness Products Section, Operational 

Safety Branch, FAA, 10101 Hillwood Pkwy., 

Fort Worth, TX 76177; telephone (817) 222– 

5110; email matthew.fuller@faa.gov. 

(2) Eurocopter Emergency Alert Service 

Bulletin EASB No. 05.00.63, Revision 1, 

dated June 18, 2012, which is not 

incorporated by reference, contains 

additional information about the subject of 

this AD. This service information is available 

at the contact information specified in 

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

(3) The subject of this AD is addressed in 

European Union Aviation Safety Agency 

(EASA) AD 2012–0108R1, dated September 

19, 2019. You may view the EASA AD on the 

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

Docket No. FAA–2021–0195. 

(k) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5300, Fuselage Structure. 

(l) 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) Airbus Helicopters Emergency Alert 

Service Bulletin EASB No. 05.00.63, Revision 

2, dated December 20, 2018. 

(ii) [Reserved] 

Note 1 to paragraph (l)(2)(ii): Airbus 

Helicopters Emergency Alert Service Bulletin 

EASB No. 05.00.63, Revision 2, dated 

December 20, 2018 is co-published as one 

document along with Airbus Helicopters 

Emergency Alert Service Bulletin EASB No. 

05.00.30, Revision 2, dated December 20, 

2018, which is not incorporated by reference 

in this AD. 

(3) For service information identified in 

this AD, 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. 

(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. 


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Federal Register / Vol. 86, No. 131 / Tuesday, July 13, 2021 / Rules and Regulations 36641 

Issued on June 17, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–14777 Filed 7–12–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 31377; Amdt. No. 3963] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This rule establishes, amends, 

suspends, or removes Standard 

Instrument Approach Procedures 

(SIAPS) and associated Takeoff 

Minimums and Obstacle Departure 

procedures (ODPs) for operations at 

certain airports. These regulatory 

actions are needed because of the 

adoption of new or revised criteria, or 

because of changes occurring in the 

National Airspace System, such as the 

commissioning of new navigational 

facilities, adding new obstacles, or 

changing air traffic requirements. These 

changes are designed to provide safe 

and efficient use of the navigable 

airspace and to promote safe flight 

operations under instrument flight rules 

at the affected airports. 

DATES: This rule is effective July 13, 

2021. The compliance date for each 

SIAP, associated Takeoff Minimums, 

and ODP is specified in the amendatory 

provisions. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of July 13, 

2021. 

ADDRESSES: Availability of matters 

incorporated by reference in the 

amendment is as follows: 

For Examination 

1. U.S. Department of Transportation, 

Docket Ops-M30. 1200 New Jersey 

Avenue SE, West Bldg., Ground Floor, 

Washington, DC 20590–0001. 

2. The FAA Air Traffic Organization 

Service Area in which the affected 

airport is located; 

3. The office of Aeronautical 

Information Services, 6500 South 

MacArthur Blvd., Oklahoma City, OK 

73169 or, 

4. 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. 

Availability 

All SIAPs and Takeoff Minimums and 

ODPs are available online free of charge. 

Visit the National Flight Data Center at 

nfdc.faa.gov to register. Additionally, 

individual SIAP and Takeoff Minimums 

and ODP copies may be obtained from 

the FAA Air Traffic Organization 

Service Area in which the affected 

airport is located. 

FOR FURTHER INFORMATION CONTACT: 

Thomas J. Nichols, Flight Procedures 

and Airspace Group, Flight 

Technologies and Procedures Division, 

Flight Standards Service, Federal 

Aviation Administration. Mailing 

Address: FAA Mike Monroney 

Aeronautical Center, Flight Procedures 

and Airspace Group, 6500 South 

MacArthur Blvd., Registry Bldg. 29, 

Room 104, Oklahoma City, OK 73169. 

Telephone (405) 954–4164. 

SUPPLEMENTARY INFORMATION: This rule 

amends 14 CFR part 97 by establishing, 

amending, suspending, or removes 

SIAPS, Takeoff Minimums and/or 

ODPS. The complete regulatory 

description of each SIAP and its 

associated Takeoff Minimums or ODP 

for an identified airport is listed on FAA 

form documents which are incorporated 

by reference in this amendment under 5 

U.S.C. 552(a), 1 CFR part 51, and 14 

CFR part 97.20. The applicable FAA 

Forms 8260–3, 8260–4, 8260–5, 8260– 

15A, 8260–15B, when required by an 

entry on 8260–15A, and 8260–15C. 

The large number of SIAPs, Takeoff 

Minimums and ODPs, their complex 

nature, and the need for a special format 

make publication in the Federal 

Register expensive and impractical. 

Further, airmen do not use the 

regulatory text of the SIAPs, Takeoff 

Minimums or ODPs, but instead refer to 

their graphic depiction on charts 

printed by publishers or aeronautical 

materials. Thus, the advantages of 

incorporation by reference are realized 

and publication of the complete 

description of each SIAP, Takeoff 

Minimums and ODP listed on FAA form 

documents is unnecessary. This 

amendment provides the affected CFR 

sections and specifies the typed of 

SIAPS, Takeoff Minimums and ODPs 

with their applicable effective dates. 

This amendment also identifies the 

airport and its location, the procedure, 

and the amendment number. 

Availability and Summary of Material 

Incorporated by Reference 

The material incorporated by 

reference is publicly available as listed 

in the ADDRESSES section. 

The material incorporated by 

reference describes SIAPS, Takeoff 

Minimums and/or ODPs as identified in 

the amendatory language for part 97 of 

this final rule. 

The Rule 

This amendment to 14 CFR part 97 is 

effective upon publication of each 

separate SIAP, Takeoff Minimums and 

ODP as amended in the transmittal. 

Some SIAP and Takeoff Minimums and 

textual ODP amendments may have 

been issued previously by the FAA in a 

Flight Data Center (FDC) Notice to 

Airmen (NOTAM) as an emergency 

action of immediate flights safety 

relating directly to published 

aeronautical charts. 

The circumstances that created the 

need for some SIAP and Takeoff 

Minimums and ODP amendments may 

require making them effective in less 

than 30 days. For the remaining SIAPs 

and Takeoff Minimums and ODPs, an 

effective date at least 30 days after 

publication is provided. 

Further, the SIAPs and Takeoff 

Minimums and ODPs contained in this 

amendment are based on the criteria 

contained in the U.S. Standard for 

Terminal Instrument Procedures 

(TERPS). In developing these SIAPs and 

Takeoff Minimums and ODPs, the 

TERPS criteria were applied to the 

conditions existing or anticipated at the 

affected airports. Because of the close 

and immediate relationship between 

these SIAPs, Takeoff Minimums and 

ODPs, and safety in air commerce, I find 

that notice and public procedure under 

5 U.S.C. 553(b) are impracticable and 

contrary to the public interest and, 

where applicable, under 5 U.S.C. 553(d), 

good cause exists for making some 

SIAPs effective in less than 30 days. 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current. It, therefore—(1) is not a 

‘‘significant regulatory action’’ under 

Executive Order 12866; (2) is not a 

‘‘significant rule’’ under DOT 

Regulatory Policies and Procedures (44 

FR 11034; February 26, 1979); and (3) 

does not warrant preparation of a 

regulatory evaluation as the anticipated 

impact is so minimal. For the same 

reason, the FAA certifies that this 

amendment will not have a significant 

economic impact on a substantial 


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