[Federal Register Volume 86, Number 231 (Monday, December 6, 2021)]
[Rules and Regulations]
[Pages 68897-68899]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-26329]



[[Page 68897]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0712; Project Identifier 2019-CE-018-AD; Amendment 
39-21807; AD 2021-23-09]
RIN 2120-AA64


Airworthiness Directives; ASI Aviation (Type Certificate 
Previously Held by Reims Aviation S.A.) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2015-16-07 
R1, which applied to certain Reims Aviation S.A. (type certificate now 
held by ASI Aviation) Model F406 airplanes. AD 2015-16-07 R1 required 
inspecting the left-hand and right-hand rudder control pedal torque 
tubes and replacing with a serviceable part as necessary. Since the FAA 
issued AD 2015-16-07 R1, the European Aviation Safety Agency (EASA) 
superseded its mandatory continuing airworthiness information (MCAI) to 
correct an unsafe condition on these products. This AD retains the 
requirements of AD 2015-16-07 R1, expands the applicability, and 
requires repeating the inspections using updated procedures. The FAA is 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective January 10, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 10, 
2022.

ADDRESSES: For service information identified in this final rule, 
contact ASI Aviation, A[eacute]rodrome de Reims Prunay, 51360 Prunay, 
France; telephone: +33 3 26 48 46 84; fax: +33 3 26 49 18 57; email: 
[email protected]; website: https://asi-aviation.fr/page-Accueil.html. You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 901 Locust, 
Kansas City, MO 64106. For information on the availability of this 
material at the FAA, call (816) 329-4148. It is also available at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2021-0712.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0712; 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 
MCAI, 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: Gregory Johnson, Aviation Safety 
Engineer, International Validation Section, FAA, 901 Locust, Room 301, 
Kansas City, MO 64106-2641; phone: (720) 626-5462; email: 
[email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2015-16-07 R1, Amendment 39-18328 (80 FR 
72563, November 20, 2015) (AD 2015-16-07 R1). AD 2015-16-07 R1 applied 
to certain Reims Aviation S.A. (type certificate now held by ASI 
Aviation) Model F406 airplanes and required inspecting the left-hand 
and right-hand rudder control pedal torque tubes and replacing with a 
serviceable part as necessary. The NPRM published in the Federal 
Register on August 27, 2021 (86 FR 48083).
    The NPRM was prompted by AD 2019-0016, dated January 29, 2019 
(referred to after this as ``the MCAI''), issued by EASA, which is the 
Technical Agent for the Member States of the European Union. 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] F406-104 to provide inspection instructions. 
Consequently, EASA issued Emergency AD 2015-0159-E (later revised) 
to require a one-time inspection of the rudder control pedal torque 
tubes, both left-hand (LH) and right-hand (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 2015-0159R1 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, dye- or 
fluorescent-penetrant, and magnetic particle inspections.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2015-0159R1, which is superseded, and 
requires implementation of repetitive inspections of the affected 
parts and, depending on findings, replacement.

    You may examine the MCAI in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0712.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of 
the costs.

Conclusion

    This product has been approved by the aviation authority of another 
country and is approved for operation in the United States. Pursuant to 
the FAA's 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 determined that air 
safety requires adopting this AD as proposed. Accordingly, the FAA is 
issuing this AD to address the unsafe condition on these products. This 
AD is adopted as proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed ASI Aviation Service Bulletin No. F406-104, 
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 ADDRESSES.

Differences Between This 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 AD requires 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 AD 
requires that initial inspection within

[[Page 68898]]

100 hours time-in-service 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 AD requires 
replacing the rudder control pedal torque tube with a serviceable part.

Costs of Compliance

    The FAA estimates that this AD affects 4 airplanes of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD:

                                                                     Estimated Costs
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              Action                    Labor cost        Parts cost              Cost per airplane                      Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections......................  5 work-hours x $85             $0  $425 per inspection cycle...............  $1,700 per inspection cycle.
                                    per hour = $425 per
                                    inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to replace a rudder control 
pedal torque tube if required by the results of the inspections. The 
FAA has no way of determining the number of airplanes that might need 
these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        airplane
----------------------------------------------------------------------------------------------------------------
Replacement..................................  20 work-hours x $85 per hour =           $9,100          $10,800
                                                $1,700.
----------------------------------------------------------------------------------------------------------------

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 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

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by
0
a. Removing Airworthiness Directive 2015-16-07 R1, Amendment 39-18328 
(80 FR 72563, November 20, 2015); and
0
b. Adding the following new airworthiness directive:

2021-23-09 ASI Aviation (Type Certificate Previously Held by Reims 
Aviation S.A.): Amendment 39-21807; Docket No. FAA-2021-0712; 
Project Identifier 2019-CE-018-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective January 10, 2022.

(b) Affected ADs

    This AD replaces AD 2015-16-07 R1, Amendment 39-18328 (80 FR 
72563, November 20, 2015) (AD 2015-16-07 R1).

(c) Applicability

    This AD applies to ASI Aviation (type certificate previously 
held by Reims Aviation S.A.) Model F406 airplanes, all serial 
numbers, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC) Code 2700, Flight Control 
System.

(e) Unsafe Condition

    This AD was prompted by reports of detachment of the pilot's 
rudder control pedal in flight. The FAA is issuing this AD to detect 
and correct cracking of the pilot's rudder control pedal. The unsafe 
condition, if not addressed, could result in detachment of the pedal 
with possible loss of airplane directional control.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Definition

    For the purpose of this AD, a serviceable part is:
    (1) A rudder control pedal torque tube (left-hand (LH) part 
number (P/N) 5115260-1 or right-hand (RH) P/N 5115260-2) that has 
had a magnetic particle inspection by following the instructions of 
Part B of ASI Aviation Service Bulletin No. F406-104, Revision 1, 
dated December 14, 2018, and no cracks were found; or
    (2) A new rudder control pedal torque tube (LH P/N 5115260-1 or 
RH P/N 5115260-2) that has never been installed on an airplane.

(h) Repetitive Inspections and Corrective Actions

    (1) Before further flight after the effective date of this AD, 
and thereafter at intervals not to exceed 600 hours time-in-service 
(TIS), do a visual inspection and a dye or fluorescent penetrant 
inspection for cracks of the LH and RH rudder control pedal torque 
tubes by

[[Page 68899]]

following the Accomplishment Instructions, Part A or Part AA, in ASI 
Aviation Service Bulletin No. F406-104, Revision 1, dated December 
14, 2018.
    (2) Within 100 hours TIS after the effective date of this AD, 
and thereafter at intervals not to exceed 2,400 hours TIS, do a 
magnetic particle inspection for cracks of the LH and RH rudder 
control pedal torque tubes by following the Accomplishment 
Instructions, Part B, in ASI Aviation Service Bulletin No. F406-104, 
Revision 1, dated December 14, 2018.
    (3) If, during any inspection required by paragraph (h)(1) or 
(2) of this AD, any crack is detected on a rudder control pedal 
torque tube, you are not required to contact ASI Aviation as 
specified in steps A.16, AA.5, and B.4 of ASI Aviation Service 
Bulletin No. F406-104, Revision 1, dated December 14, 2018. Instead, 
before further flight, replace the rudder control pedal torque tube 
with a serviceable part as defined by this AD.

(i) Installation Limitation

    As of the effective date of this AD, do not install a rudder 
control pedal torque tube P/N 5115260-1 (LH) or P/N 5115260-2 (RH) 
on any airplane unless it is a serviceable part as defined by this 
AD.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation Branch, 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 certification office, send it to the 
attention of the person identified in paragraph (k)(1) of this AD or 
email: [email protected].
    (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 Gregory Johnson, 
Aviation Safety Engineer, International Validation Section, FAA, 901 
Locust, Room 301, Kansas City, MO 64106-2641; phone: (720) 626-5462; 
email: [email protected].
    (2) Refer to European Aviation Safety Agency (EASA) AD 2019-
0016, dated January 29, 2019, for more information. You may examine 
the EASA AD in the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0712.

(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) ASI Aviation Service Bulletin No. F406-104, Revision 1, 
dated December 14, 2018.
    (ii) [Reserved].
    (3) For service information identified in this AD, contact ASI 
Aviation, A[eacute]rodrome de Reims Prunay, 51360 Prunay, France; 
telephone: +33 3 26 48 46 84; fax: +33 3 26 49 18 57; email: 
[email protected]; website: https://asi-aviation.fr/page-Accueil.html.
    (4) You may view this service information at FAA, Airworthiness 
Products Section, Operational Safety Branch, 901 Locust, Kansas 
City, MO 64106. For information on the availability of this material 
at the FAA, call (816) 329-4148.
    (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: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on October 27, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-26329 Filed 12-3-21; 8:45 am]
BILLING CODE 4910-13-P


