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Federal Register / Vol. 86, No. 164 / Friday, August 27, 2021 / Proposed Rules
Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under ADDRESSES. Include Docket No.
FAA20210712; Project Identifier 2019CE018AD at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, 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 the proposal 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 proposed AD.
Confidential Business Information
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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 NPRM
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 NPRM, 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 NPRM. Submissions containing CBI
should be sent to Gregory Johnson, Aviation Safety Engineer, FAA, General Aviation & Rotorcraft Section, International Validation Branch, 901
Locust, Room 301, Kansas City, MO
64106. Any commentary that the FAA
receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking.
Background The FAA issued AD 20151607 R1, Amendment 3918328 80 FR 72563, November 20, 2015 AD 20151607
R1, for certain serial-numbered Reims Aviation S.A. type certificate now held by ASI Aviation Model F406 airplanes.
AD 20151607 R1 was prompted by
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MCAI originated by EASA, which is the Technical Agent for the Member States of the European Union. EASA issued EASA AD 20150159R1, dated August 24, 2015, to identify and correct an unsafe condition identified as detachment of the pilots rudder control pedal in flight.
AD 20151607 R1 requires inspecting the left-hand and right-hand rudder control pedal torque tubes and replacing with a serviceable part as necessary. The FAA issued AD 2015
1607 R1 to detect and correct cracking of the pilot rudder control pedal which, if not corrected, could result in detachment of the pedal with possible loss of airplane directional control. AD
20151607 R1 revised AD 20151607, Amendment 3918232 80 FR 49127, August 17, 2015 AD 20151607, by adding an option for acceptable serviceable replacement parts. AD
20151607 R1 retained the compliance times required by AD 20151607.
Actions Since AD 20151607 R1 Was Issued Since the FAA issued AD 20151607
R1, EASA superseded EASA AD 2015
0159R1, dated August 24, 2015, and issued EASA AD 20190016, dated January 29, 2019 referred to after this as the MCAI. The MCAI states:
An occurrence was reported where one pilot rudder control pedal of an F 406
aeroplane detached in flight. No change in aeroplane attitude occurred. The rudder was controlled using the co-pilot rudder pedals, and an uneventful landing was made.
Investigation results determined that the affected rudder pedal torque tube had failed due to a crack.
This condition, if not detected and corrected, could lead to further cases of rudder pedal torque tube failure, possibly resulting in reduced control of the aeroplane.
To address this potential unsafe condition, ASI Aviation issued SB service bulletin F406104 to provide inspection instructions.
Consequently, EASA issued Emergency AD
20150159E later revised to require a onetime inspection of the rudder control pedal torque tubes, both left-hand LH and righthand RH, and, depending on findings, replacement with a serviceable part. That EASA AD also required inspection of replacement rudder control pedal torque tubes before installation.
Since EASA AD 20150159R1 was issued, further occurrences were reported of finding cracks on rudder pedal torque tubes.
Consequently, ASI Aviation issued the SB as defined in this EASA AD to provide instructions for repetitive visual, dyeor fluorescent-penetrant, and magnetic particle inspections.
For the reason described above, this EASA AD retains the requirements of EASA
AD 20150159R1, which is superseded, and requires implementation of repetitive inspections of the affected parts and, depending on findings, replacement.

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You may examine the MCAI in the AD docket at https
www.regulations.gov by searching for and locating Docket No. FAA2021
0712.
Related Service Information Under 1
CFR Part 51
The FAA reviewed ASI Aviation Service Bulletin No. F406104, Revision 1, dated December 14, 2018. The service information specifies procedures for repetitively inspecting the left-hand and right-hand rudder control pedal torque tubes for cracks and replacing with a serviceable part.
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.
FAAs Determination This product has been approved by the aviation authority of another country and is approved for operation in the United States. Pursuant to the FAAs bilateral agreement with this State of Design Authority, it has notified the FAA of the unsafe condition described in the MCAI and service information referenced above. The FAA is issuing this NPRM after determining the unsafe condition described previously is likely to exist or develop on other products of the same type design.
Proposed AD Requirements in This NPRM
This proposed AD would retain the requirements of AD 20151607 R1, expand the applicability, and require repetitive inspections using improved procedures of the left-hand and righthand rudder control pedal torque tubes, and, depending on findings, replacement with a serviceable part.
Differences Between This Proposed AD
and the MCAI
The MCAI specifies an initial compliance time of during the next 600
flight hour FH maintenance check for a visual and a dye or fluorescent penetrant inspection. This proposed AD
would require those initial inspections before further flight.
The MCAI specifies an initial compliance time of during the next 2,400 FH maintenance check for a magnetic particle inspection. This proposed AD would require that initial inspection within 100 hours time-inservice after the effective date of this AD.
If a crack is detected during any inspection, the MCAI specifies contacting ASI Aviation for further information. This proposed AD would
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