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ADs updated daily at www.Tdata.com
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| 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.
(f) COMPLIANCE
Comply with this AD within the compliance times specified, unless al-
ready 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 sys-
tem, 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 be-
fore 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 sys-
tem, 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 be-
fore 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 para-
graph (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 in-
stall 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 in-
cludes 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 longitu-
dinal 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 Infor-
mation 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 corro-
sion, 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-AIR-730-AMOC@faa.gov.
(2) Before using any approved AMOC, notify your appropriate principal in-
spector, 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 infor
-mation 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 Avia-
tion 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.
FOR FURTHER INFORMATION CONTACT: Chirayu Gupta, Aerospace Engineer, Mechan
-ical Systems & Administrative Services Section, New York ACO Branch, Com-
pliance & Airworthiness Division, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone (516) 228-7300; email 9-avs-nyaco-cos@faa.
gov.
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DEPARTMENT OF TRANSPORTATION |