37228 Federal Register / Vol. 87, No. 119 / Wednesday, June 22, 2022 / Rules and Regulations 

compliance times specified in, and in 

accordance with, EASA AD 2021–0259. 

(h) Exceptions to EASA AD 2021–0259 

(1) Where EASA AD 2021–0259 requires 

compliance in terms of flight hours (FH), this 

AD requires using hours time-in-service. 

(2) Where EASA AD 2021–0259 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(3) Where paragraph (1) of EASA AD 2021– 

0259 specifies ‘‘inspect, using a borescope, 

the affected part in accordance with the 

instructions of Section 3 Part I of the ASB,’’ 

for this AD replace ‘‘in accordance with the 

instructions of Section 3 Part I of the ASB’’ 

with ‘‘in accordance with the 

Accomplishment Instructions, Section 3 Part 

I, paragraphs 5. through 5.5 of the ASB.’’ 

(4) Where paragraph (2) of EASA AD 2021– 

0259 specifies ‘‘if, during the inspection as 

required by paragraph (1) this AD, a crack or 

any discrepancy is detected, replace the 

affected part in accordance with the 

instructions of Section 3 Part II of the ASB,’’ 

this AD requires before further flight, 

removing the TGB fitting from service and 

replacing with an airworthy part, if any crack 

or discrepancy is detected. For this AD, 

discrepancies include damage, which 

includes scratches and dents on the outer 

surfaces of the forward and right-hand sides 

of the TGB fitting above the horizontal row 

of fastener holes. The instructions specified 

in paragraph (2) of EASA AD 2021–0259 are 

for reference only and are not required for the 

replacement required by this paragraph. 

(5) Where paragraph (4) of EASA AD 2021– 

0259 allows (re)installing an affected part 

provided it is inspected as required by 

paragraph (1) of EASA AD 2021–0259, for 

this AD, the inspected part cannot be 

(re)installed if any crack or discrepancy is 

detected. 

(6) This AD does not mandate compliance 

with paragraph (3) of EASA AD 2021–0259. 

(7) This AD does not mandate compliance 

with the ‘‘Remarks’’ section of EASA AD 

2021–0259. 

(i) Special Flight Permit 

Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199, 

provided no passengers are onboard. 

(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)(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. 

(k) Related Information 

(1) For more information about this AD, 

contact Andrea Jimenez, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 1600 Stewart 

Ave., Suite 410, Westbury, NY 11590; 

telephone (516) 228–7330; email 

andrea.jimenez@faa.gov. 

(2) For service information identified in 

this AD, contact EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; telephone 

+49 221 8999 000; email ADs@

easa.europa.eu; internet 

www.easa.europa.eu. 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. 

This material may be found in the AD docket 

at https://www.regulations.gov by searching 

for and locating Docket No. FAA–2022–0283. 

(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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2021–0259, dated November 17, 

2021, and corrected November 22, 2021. 

(ii) [Reserved] 

(3) 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 

at https://www.regulations.gov by searching 

for and locating FAA–2022–0283. 

(4) 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 

fr.inspection@nara.gov, or go to: https://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on May 25, 2022. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–13267 Filed 6–21–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0685; Project 

Identifier MCAI–2022–00243–R; Amendment 

39–22093; AD 2022–13–07] 

RIN 2120–AA64 

Airworthiness Directives; AutoGyro 

Certification Limited (Type Certificate 

Previously Held by RotorSport UK Ltd) 

Gyroplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

AutoGyro Certification Limited (type 

certificate previously held by 

RotorSport UK Ltd) Model Calidus, 

Cavalon, and MTOsport 2017 

gyroplanes. This AD was prompted by 

reports of rotor blade longitudinal 

cracking and rotor blade attachment bolt 

hole fretting corrosion and cracking. 

This AD requires reducing the life limits 

for the rotor systems, repetitively 

inspecting each rotor blade, and 

depending on the outcome, removing 

parts from service. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD becomes effective July 

7, 2022. 

The FAA must receive comments on 

this AD by August 8, 2022. 

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 Gerry Speich; 

Poplar Farm, Wentnor, Bishops Castle, 

South Shropshire, United Kingdom, 

SY9 5EJ; telephone +44–1588–505060; 

or at http://www.auto-gyro.co.uk/. 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 


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Federal Register / Vol. 87, No. 119 / Wednesday, June 22, 2022 / Rules and Regulations 37229 

76177. For information on the 

availability of this material at the FAA, 

call (817) 222–5110. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0685; 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 United Kingdom (UK) 

Civil Aviation Authority (CAA) 

Mandatory Permit Directive (MPD), any 

comments received, and other 

information. The street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Chirayu Gupta, Aerospace Engineer, 

Mechanical Systems & Administrative 

Services Section, New York ACO 

Branch, Compliance & Airworthiness 

Division, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; 

telephone (516) 228–7300; email 9-avsnyaco-cos@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

UK CAA, which is the aviation 

authority for the United Kingdom, has 

issued UK CAA MPD 2022–002, dated 

January 24, 2022 (UK CAA MPD 2022– 

002), to correct an unsafe condition for 

Autogyro Certification Limited 

(formerly Rotorsport Uk Limited) Model 

MT–03, MTOsport, MTOsport 2017, 

Calidus, and Cavalon gyroplanes. UK 

CAA advises of rotor blade longitudinal 

cracking and rotor blade attachment bolt 

hole fretting corrosion and cracking on 

gyroplanes with a Rotor System II 

installed. According to the UK CAA, 

due to design similarity, this condition 

may also affect gyroplanes with a Rotor 

System I installed. This condition, if not 

addressed, could result in loss of a rotor 

blade and subsequent loss of control of 

the gyroplane. 

Accordingly, UK CAA MPD 2022–002 

requires determining the accumulated 

flight hours on the rotor system, 

complying with new life limits for the 

rotor systems, and repetitively 

inspecting each rotor blade to hub bar 

attachment fastenings and blade holes. 

Depending on the outcome of the 

inspections, UK CAA MPD 2022–002 

requires replacing and returning parts, 

and reporting certain information to 

Autogyro Certification Limited and the 

UK CAA. 

FAA’s Determination 

These gyroplanes have been approved 

by the aviation authority of the UK and 

are approved for operation in the United 

States. Pursuant to the FAA’s bilateral 

agreement with the UK, the UK CAA, its 

technical representative, has notified 

the FAA of the unsafe condition 

described in its MPD. The FAA is 

issuing this AD after evaluating all 

known relevant information and 

determining that the unsafe condition 

described previously is likely to exist or 

develop on other gyroplanes of these 

same type designs. 

Related Service Information 

The FAA reviewed RotorSport UK Ltd 

Service Bulletin SB–144 Issue 1, dated, 

August 19, 2021. This service 

information specifies new Rotor System 

I and II life limits and new rotor blade 

to hub bar attachment fastenings and 

blade hole inspection compliance times. 

This service information also specifies a 

recurring inspection of the rotor system 

hub bar assembly bolts. 

The FAA also reviewed RotorSport 

UK Ltd Service Information Letter SIL– 

028, Issue 1, dated June 17, 2019. This 

service information provides 

construction and general information 

regarding the different versions of Rotor 

System I and II and the rotor blades, and 

highlights particular areas of importance 

of the rotor blades. This service 

information specifies procedures for 

inspecting the blade to hub bar joints, 

rotor blade surfaces and planes, and 

rotor blade attachment bolt holes. This 

service information also specifies 

information regarding and provides 

photos of trailing edge damage, leading 

edge damage, and a longitudinal blade 

root crack that is adjacent to the bolted 

area. Lastly, this service information 

provides information regarding if there 

is substantial damage of a rotor blade or 

rotor system. 

AD Requirements 

This AD requires reducing the life 

limits for Rotor Systems I and II. This 

AD also requires repetitively removing, 

cleaning, and inspecting certain areas of 

each rotor blade and each rotor blade 

bolt hole, and depending on the 

outcome, removing parts from service 

and installing airworthy parts. 

Differences Between This AD and the 

UK CAA MPD 

UK CAA MPD 2022–002 applies to 

Model MT–03 and MTOsport 

gyroplanes, whereas this AD does not 

because those models are not FAA typecertificated. UK CAA MPD 2022–002 

requires accomplishing the initial 

instance of the inspections within 100 

hours or 12 months for Rotor System I, 

and within 100 or 500 hours depending 

on accumulated usage or 2 years or 1 

year (recommended) depending on 

operational or storage usage for Rotor 

System II; whereas this AD requires 

accomplishing the initial inspections 

within 10 hours time-in-service (TIS) or 

3 months, whichever occurs first, for a 

gyroplane with a Rotor System I or II, 

all part numbers and serial numbers, 

installed. For certain Rotor System II 

units, UK CAA MPD 2022–002 

recommends a shorter recurring 

inspection time; whereas this AD does 

not. This AD requires wiping the 

inspection areas of the rotor blades 

clean before accomplishing the 

inspections; whereas UK CAA MPD 

2022–002 does not. UK CAA MPD 

2022–002 refers to service information 

that states that ‘‘means of inspection can 

be dye penetrant or visual high 

magnification or as determined 

appropriate by the inspector;’’ whereas 

this AD mandates what types of 

inspections must be accomplished. UK 

CAA MPD 2022–002 requires returning 

parts to the manufacturer, whereas this 

AD does not. UK CAA MPD 2022–002 

requires reporting certain information; 

whereas this AD does not. 

Justification for Immediate Adoption 

and Determination of the Effective Date 

Section 553(b)(3)(B) of the 

Administrative Procedure Act (APA) (5 

U.S.C. 551 et seq.) authorizes agencies 

to dispense with notice and comment 

procedures for rules when the agency, 

for ‘‘good cause,’’ finds that those 

procedures are ‘‘impracticable, 

unnecessary, or contrary to the public 

interest.’’ Under this section, an agency, 

upon finding good cause, may issue a 

final rule without providing notice and 

seeking comment prior to issuance. 

Further, section 553(d) of the APA 

authorizes agencies to make rules 

effective in less than thirty days, upon 

a finding of good cause. 

An unsafe condition exists that 

requires the immediate adoption of this 

AD without providing an opportunity 

for public comments prior to adoption. 

The FAA has found that the risk to the 

flying public justifies foregoing notice 

and comment prior to adoption of this 

rule because cracking and fretting on the 

surfaces of the rotor blades can lead to 

degradation or structural failure of the 

rotor system and subsequent loss of 

control of the gyroplane. Loss of 

aerodynamic control due to the 

mentioned unsafe condition could 

ultimately be categorized as a 

catastrophic failure. In addition, the 

FAA has no information regarding the 

number of rotor blades that are in 

service beyond their fatigue life or 

pertaining to the extent of cracking or 

corrosion of rotor blades that may 

currently exist in gyroplanes or how 

quickly the condition may propagate to 


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failure. In light of this, this AD reduces 

the life limit threshold of the rotor 

systems and the initial instance of the 

rotor blade inspections required by this 

AD must be accomplished within 10 

hours TIS or 3 months, whichever 

occurs first. This compliance time is 

shorter than the time necessary for the 

public to comment and for publication 

of the final rule. Accordingly, notice 

and opportunity for prior public 

comment are impracticable and contrary 

to the public interest pursuant to 5 

U.S.C. 553(b)(3)(B). 

In addition, the FAA finds that good 

cause exists pursuant to 5 U.S.C. 553(d) 

for making this amendment effective in 

less than 30 days, for the same reasons 

the FAA found good cause to forego 

notice and comment. 

Comments Invited 

The FAA invites you to send any 

written data, views, or arguments about 

this final rule. Send your comments to 

an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2022–0685; 

Project Identifier MCAI–2022–00243–R’’ 

at the beginning of your comments. The 

most helpful comments reference a 

specific portion of the final rule, explain 

the reason for any recommended 

change, and include supporting data. 

The FAA will consider all comments 

received by the closing date and may 

amend this final rule because of those 

comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to https://

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this final rule. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this AD contain 

commercial or financial information 

that is customarily treated as private, 

that you actually treat as private, and 

that is relevant or responsive to this AD, 

it is important that you clearly designate 

the submitted comments as CBI. Please 

mark each page of your submission 

containing CBI as ‘‘PROPIN.’’ The FAA 

will treat such marked submissions as 

confidential under the FOIA, and they 

will not be placed in the public docket 

of this AD. Submissions containing CBI 

should be sent to Chirayu Gupta, 

Aerospace Engineer, Mechanical 

Systems & Administrative Services 

Section, New York ACO Branch, 

Compliance & Airworthiness Division, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone (516) 

228–7300; email 9-avs-nyaco-cos@

faa.gov. Any commentary that the FAA 

receives which is not specifically 

designated as CBI will be placed in the 

public docket for this rulemaking. 

Regulatory Flexibility Act 

The requirements of the Regulatory 

Flexibility Act (RFA) do not apply when 

an agency finds good cause pursuant to 

5 U.S.C. 553 to adopt a rule without 

prior notice and comment. Because the 

FAA has determined that it has good 

cause to adopt this rule without prior 

notice and comment, RFA analysis is 

not required. 

Costs of Compliance 

The FAA estimates that this AD 

affects 41 gyroplanes 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. 

Replacing a rotor system takes about 

1.5 hours and parts cost about $5,500 for 

an estimated cost of $5,628 per 

gyroplane and $230,748 for the U.S. 

fleet, per instance. Inspecting a rotor 

system takes about 1 work-hour for an 

estimated cost of $85 per gyroplane and 

$3,485 for the U.S. fleet, per inspection 

cycle. 

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, I certify 

that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

and 

(2) Will not affect intrastate aviation 

in Alaska. 

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: 

2022–13–07 AutoGyro Certification 

Limited (Type Certificate Previously 

Held by RotorSport UK Ltd): 

Amendment 39–22093; Docket No. 

FAA–2022–0685; Project Identifier 

MCAI–2022–00243–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 7, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to AutoGyro Certification 

Limited (type certificate previously held by 

RotorSport UK Ltd) Model Calidus, Cavalon, 

and MTOsport 2017 gyroplanes, certificated 

in any category. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6210, Main Rotor Blades. 

(e) Unsafe Condition 

This AD was prompted by reports of rotor 

blade longitudinal cracking and rotor blade 

attachment bolt hole fretting corrosion and 

cracking. The FAA is issuing this AD to 

prevent a rotor system from remaining in 

service beyond its fatigue life and detect 

fretting corrosion and cracking. The unsafe 

condition, if not addressed, could result in 

failure or loss of a rotor blade and subsequent 

loss of control of the gyroplane. 


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Federal Register / Vol. 87, No. 119 / Wednesday, June 22, 2022 / Rules and Regulations 37231 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For a gyroplane with a Rotor System I, 

all part numbers and serial numbers, 

installed: 

(i) That has accumulated 700 or more total 

hours time-in-service (TIS) on the rotor 

system, before further flight after the effective 

date of this AD, remove the rotor system, 

which includes the rotor bearing, from 

service. 

(ii) That has accumulated less than 700 

total hours TIS on the rotor system, before 

accumulating 700 total hours TIS after the 

effective date of this AD, remove the rotor 

system, which includes the rotor bearing, 

from service. 

(iii) Thereafter following paragraph (g)(1)(i) 

or (ii) of this AD, remove the rotor system, 

which includes the rotor bearing, from 

service before accumulating 700 total hours 

TIS. 

(2) For a gyroplane with a Rotor System II, 

all part numbers and serial numbers, 

installed: 

(i) That has accumulated 2,500 or more 

total hours TIS on the rotor system, before 

further flight after the effective date of this 

AD, remove the rotor system, which includes 

the rotor bearing, from service. 

(ii) That has accumulated less than 2,500 

total hours TIS on the rotor system, before 

accumulating 2,500 total hours TIS after the 

effective date of this AD, remove the rotor 

system, which includes the rotor bearing, 

from service. 

(iii) Thereafter following paragraph (g)(2)(i) 

or (ii) of this AD, remove the rotor system, 

which includes the rotor bearing, from 

service before accumulating 2,500 total hours 

TIS. 

(3) For a gyroplane with a Rotor System I 

or II, all part numbers and serial numbers, 

installed, accomplish the actions required by 

paragraph (g)(4) of this AD within 10 hours 

TIS or 3 months after the effective date of this 

AD, whichever occurs first. 

(4) For each rotor blade, starting with the 

rotor blade bolt closest to the rotor hub, 

sequentially remove each bolt and lock nut, 

remove the rotor blade, and remove the inner 

end cap. 

(i) Using a dry cloth, wipe clean the rotor 

blade upper and lower surfaces within 100 

mm of the circumference of each bolt hole. 

(A) Dye penetrant inspect, or use a 

flashlight and 10X or higher power 

magnifying glass, to inspect the cleaned rotor 

blade upper and lower surfaces within 100 

mm of the circumference of each bolt hole for 

a crack, split, dent, and fretting corrosion. If 

there is a crack, split, dent, or fretting 

corrosion at any point within 100 mm over 

the full circumference (360°) of a bolt hole, 

before further flight, remove the rotor system, 

which includes the rotor bearing, from 

service and install airworthy parts. 

(B) Using a flashlight and 10X or higher 

power magnifying glass, inspect each plane 

on the cleaned upper and lower surfaces for 

bending within 100 mm of the circumference 

of the bolt hole. If there is any bending in any 

plane within 100 mm over the full 

circumference (360°) of a bolt hole, before 

further flight, remove the rotor system, which 

includes the rotor bearing, from service and 

install airworthy parts. 

(ii) Dye penetrant inspect, or use a 

flashlight and 10X or higher power 

magnifying glass to inspect the rotor blade 

upper and lower inside surfaces at the rotor 

blade extrusion end (where the inner end cap 

was removed) for a crack, paying particular 

attention for a longitudinal crack adjacent to 

the bolted area. If there is a crack, before 

further flight, remove the rotor system, which 

includes the rotor bearing, from service and 

install airworthy parts. 

Note 1 to paragraph (g)(4)(ii): Page 5 of 

RotorSport UK Ltd Service Information Letter 

SIL–028, Issue 1, dated June 17, 2019, 

includes a photo of a longitudinal blade root 

crack. 

(iii) Using a flashlight and 10X or higher 

power magnifying glass, inspect each bolt 

hole in the rotor blade upper and lower 

surfaces for any burrs and fretting corrosion. 

If there is a burr or fretting corrosion, before 

further flight, remove the rotor system, which 

includes the rotor bearing, from service and 

install airworthy parts. 

(iv) Using a dry cloth, wipe clean and dye 

penetrant inspect, or use a flashlight and 10X 

or higher power magnifying glass to inspect 

each bolt hole in the rotor blade upper and 

lower surfaces for a crack. If there is a crack, 

before further flight, remove the rotor system, 

which includes the rotor bearing, from 

service and install airworthy parts. 

(5) Thereafter following paragraph (g)(3) of 

this AD, repeat the actions required by 

paragraph (g)(4) of this AD at intervals not to 

exceed the compliance time specified in 

paragraphs (g)(5)(i) through (iii) of this AD, 

as applicable to your rotor system. 

(i) For a gyroplane with a Rotor System I, 

all part numbers and serial numbers, 

installed, at intervals not to exceed 100 hours 

TIS or 12 months, whichever occurs first. 

(ii) For a gyroplane with a Rotor System II, 

all part numbers and serial numbers, 

installed, that has accumulated more than 

1,500 total hours TIS on the rotor system, at 

intervals not to exceed 100 hours TIS or 24 

months, whichever occurs first. 

(iii) For a gyroplane with a Rotor System 

II, all part numbers and serial numbers, 

installed, that has accumulated 1,500 or less 

total hours TIS on the rotor system, at 

intervals not to exceed 500 hours TIS or 24 

months, whichever occurs first. 

(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 (i)(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. 

(i) Related Information 

(1) For more information about this AD, 

contact Chirayu Gupta, Aerospace Engineer, 

Mechanical Systems & Administrative 

Services Section, New York ACO Branch, 

Compliance & Airworthiness Division, FAA, 

1600 Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone (516) 228–7300; email 

9-avs-nyaco-cos@faa.gov. 

(2) RotorSport UK Ltd Service Information 

Letter SIL–028, Issue 1, dated June 17, 2019, 

which is not incorporated by reference, 

contains additional information about the 

subject of this AD. For service information 

identified in this AD, contact Gerry Speich; 

Poplar Farm, Wentnor, Bishops Castle, South 

Shropshire, United Kingdom, SY9 5EJ; 

telephone +44–1588–505060; or at http://

www.auto-gyro.co.uk/. You may view this 

referenced 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. 

(3) The subject of this AD is addressed in 

United Kingdom (UK) Civil Aviation 

Authority (CAA) Mandatory Permit Directive 

(MPD) 2022–002, dated January 24, 2022. 

You may view the UK CAA MPD at https:// 

www.regulations.gov in Docket No. FAA– 

2022–0685. 

(j) Material Incorporated by Reference 

None. 

Issued on June 13, 2022. 

Christina Underwood, 

Acting Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–13362 Filed 6–16–22; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2021–0465; Airspace 

Docket No. 20–ANM–59] 

RIN 2120–AA66 

Modification of Class E Airspace; Rifle 

Garfield County Airport, CO 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: This action modifies the Class 

E airspace extending upward from 700 

feet above the surface at Rifle Garfield 

County Airport, Rifle, CO, and supports 

modifications to the RNAV (GPS) Y 

RWY 8 approach at the airport. This 

action will ensure the safety and 

management of instrument flight rules 

(IFR) operations at the airport. 


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