Special Conditions: DAHER Aerospace Model TBM700 Airplanes; Autothrust System, 45649-45651 [2019-18814]

Download as PDF Federal Register / Vol. 84, No. 169 / Friday, August 30, 2019 / Rules and Regulations public inspection, as second copy for use in AMS, and a third copy for use in the Office of the General Counsel, USDA). All three copies must be received in the headquarters of the Packers and Stockyards Division, Agricultural Marketing Service (AMS), USDA, Washington, DC 20250. * * * * * PART 206—SWINE CONTRACT LIBRARY 52. The authority citation for part 206 continues to read: ■ Authority: 7 U.S.C. 198–198b; 7 U.S.C. 222. 53. In part 206, wherever it occurs: a. Remove the term ‘‘GIPSA’’ and add in its place ‘‘PSD’’; ■ b. Remove the words ‘‘GIPSA website (https://gipsa.usda.gov)’’ and add in their place ‘‘AMS website (https:// ams.usda.gov)’’; and ■ c. Remove the term ‘‘USDA GIPSA,’’ and add in its place ‘‘USDA, AMS, PSD’’. ■ ■ § 206.2 [Amended] 54. Amend § 206.2, in paragraph (b), by removing the words ‘‘Grain Inspection, Packers and Stockyards Administration (GIPSA)’’ and adding in their place ‘‘Packers and Stockyards Division (PSD)’’. ■ Dated: August 20, 2019. Greg Ibach, Under Secretary, Marketing and Regulatory Programs. [FR Doc. 2019–18201 Filed 8–29–19; 8:45 am] BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 23 [Docket No. FAA–2019–0649; Special Conditions No. 23–296–SC] Special Conditions: DAHER Aerospace Model TBM700 Airplanes; Autothrust System Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions; request for comments. AGENCY: These special conditions are issued for the DAHER Aerospace Model TBM700 airplane. This airplane will have a novel or unusual design feature associated with the use of an autothrust system. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this jspears on DSK3GMQ082PROD with RULES SUMMARY: VerDate Sep<11>2014 15:51 Aug 29, 2019 Jkt 247001 design feature. These special conditions contain the additional safety standards the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards. DATES: The effective date of these special conditions is August 30, 2019. The FAA must receive your comments by September 30, 2019. ADDRESSES: Send comments identified by docket number FAA–2019–0649 using any of the following methods: b Federal eRegulations Portal: Go to https://www.regulations.gov and follow the online instructions for sending your comments electronically. b Mail: Send comments to Docket Operations, M–30, U.S. Department of Transportation (DOT), 1200 New Jersey Avenue SE, Room W12–140, West Building Ground Floor, Washington, DC 20590–0001. b Hand Delivery of Courier: Take comments to Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue SE, Washington, DC, between 9 a.m., and 5 p.m., Monday through Friday, except Federal holidays. b Fax: Fax comments to Docket Operations at 202–493–2251. Privacy: The FAA will post all comments it receives, without change, to https://regulations.gov, including any personal information the commenter provides. Using the search function of the docket website, anyone can find and read the electronic form of all comments received into any FAA docket, including the name of the individual sending the comment (or signing the comment for an association, business, labor union, etc.). DOT’s complete Privacy Act Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477–19478), as well as at https://DocketsInfo.dot.gov. Docket: Background documents or comments received may be read at https://www.regulations.gov at any time. Follow the online instructions for accessing the docket or go to the Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue SE, Washington, DC, between 9 a.m., and 5 p.m., Monday through Friday, except Federal holidays. FOR FURTHER INFORMATION CONTACT: Jeff Pretz, AIR–691, Small Airplane Standards Branch, Policy and Innovation Division, Aircraft Certification Service, Federal Aviation Administration, 901 Locust, Room 301, Kansas City, MO 64106; telephone (816) 329–3239; facsimile (816) 329–4090. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 45649 Reason for No Prior Notice and Comment Before Adoption The FAA has determined, in accordance with 5 U.S. Code §§ 553(b)(3)(B) and 553(d)(3), that notice and opportunity for prior public comment hereon are unnecessary because substantially identical special conditions have been subject to the public comment process in several prior instances such that the FAA is satisfied that new comments are unlikely. For the same reason, the FAA finds that good cause exists for making these special conditions effective upon issuance. The FAA is requesting comments to allow interested persons to submit views that may not have been submitted in response to the prior opportunities for comment. Special conditions No. Company/airplane model 23–291–SC 1 .. Innovation Solutions & Support, Inc.; Textron Aviation, Inc./Model B200. Pilatus Aircraft Ltd./Model PC–24. Cirrus Aircraft Corporation/ Model SF–50. 23–283–SC 2 .. 23–272–SC 3 .. Comments Invited The FAA invites interested people to take part in this rulemaking by sending written comments, data, or views. The most helpful comments reference a specific portion of the special conditions, explain the reason for any recommended change, and include supporting data. The FAA asks that you send two copies of written comments. The FAA will consider all comments received on or before the closing date for comments. The FAA will consider comments filed late if it is possible to do so without incurring expense or delay. The FAA may change these special conditions based on the comments received. Background On March 28th, 2018, DAHER Aerospace (DAHER) applied for FAA validation of its change to Type Certificate No. A60EU 4 for installation of an autothrust system (ATS), also known as an autothrottle system, in the Model TBM700 airplane. The Model TBM700 is a normal category, metallic, pressurized, low-wing, monoplane that seats up to 5 passengers and two flightcrew. A single Pratt & Whitney 1 https://www.federalregister.gov/d/2018-28116. 2 https://www.federalregister.gov/d/2017-14938. 3 https://federalregister.gov/a/2015-31058. 4 https://rgl.faa.gov/Regulatory_and_Guidance_ Library/rgMakeModel.nsf/0/B777E11E03DD396 C862583AE006215E4?OpenDocument. E:\FR\FM\30AUR1.SGM 30AUR1 45650 Federal Register / Vol. 84, No. 169 / Friday, August 30, 2019 / Rules and Regulations PT6A turboprop engine driving a five bladed variable pitch constant speed Hartzell propeller powers the airplane. The airplane has retractable tricycle landing gear, a Garmin G3000 avionics suite, and a maximum takeoff weight of 7,394 pounds. The installation of an ATS in the Model TBM700 is intended to reduce pilot workload. The ATS is useable in all phases from takeoff to approach. The system includes torque and airspeed management capability along with monitors to prevent the system from exceeding critical engine or airspeed limits. Throttle movement is provided by a servo, which moves the throttle lever. The servo can be overridden by pilot movement of the throttle and disengages upon selection of the A/T disconnect switch on the throttle. Section 23.1329, amendment 23–49, only contained requirements for automatic pilot systems that act on the airplane flight controls. Autothrust systems are automatic systems that act on the thrust controls. These systems provide enhanced automation and safety, but may also introduce pilot confusion, countering the safety benefit. 14 CFR 25.1329, amendment 25–119, addresses these concerns for transport airplanes. Therefore, these special conditions are based on § 25.1329 and provide additional requirements to standardize the pilot interface and system behavior and enhance pilot awareness of system active and armed modes. jspears on DSK3GMQ082PROD with RULES Type Certification Basis Under the provisions of 14 CFR 21.101, DAHER must show that the Model TBM700 airplane, as changed, continues to meet the applicable provisions of the regulations incorporated by reference in Type Certificate No. A60EU or the applicable regulations in effect on the date of application for the change. The regulations incorporated by reference in the type certificate are commonly referred to as the ‘‘original type certification basis.’’ Refer to Type Certificate Data Sheet No. A60EU for the complete certification basis. If the Administrator finds that the applicable airworthiness regulations in part 23 do not contain adequate or appropriate safety standards for the Model TBM700 airplane because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 21.16. The FAA issues special conditions, as defined in § 11.19, under § 11.38 and they become part of the type certification basis under § 21.101. VerDate Sep<11>2014 15:51 Aug 29, 2019 Jkt 247001 Special conditions are initially applicable to the model for which they are issued. Should the type certificate for that model be amended later to include any other model that incorporates the same novel or unusual design feature, or should any other model already included on the same type certificate be modified to incorporate the same novel or unusual design feature, the FAA would apply these special conditions to the other model. In addition to the applicable airworthiness regulations and special conditions, the Model TBM700 must comply with the fuel vent and exhaust emission requirements of 14 CFR part 34 and the noise certification requirements of 14 CFR part 36; and the FAA must issue a finding of regulatory adequacy under § 611 of Public Law 92– 574, the ‘‘Noise Control Act of 1972.’’ Novel or Unusual Design Features The Model TBM700 airplane will incorporate the following novel or unusual design features: An ATS, which provides commands to a servo attached to the throttle lever that automatically controls engine thrust. The ATS can be operated to control torque or airspeed. Discussion The part 23 airworthiness regulations in the type certification basis do not contain appropriate safety standards for this design feature. However, part 25 regulations contain appropriate airworthiness standards; therefore, these special conditions are derived from 14 CFR 25.1329, ‘‘Flight guidance system,’’ applicable to autothrust systems. Applicability These special conditions are applicable to the Model TBM700 airplane. Should DAHER apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, the FAA would apply these special conditions to that model as well. Conclusion This action affects only a certain novel or unusual design feature on the Model TBM700 airplane. It is not a rule of general applicability. List of Subjects in 14 CFR Part 23 Aircraft, Aviation safety, Signs and symbols. Citation The authority citation for these special conditions is as follows: PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 Authority: 49 U.S.C. 106(f), 106(g), 40113, 44701–44702; Pub. L. 113–53, 127 Stat 584 (49 U.S.C. 44704) note. The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for DAHER Aerospace Model TBM700 airplanes. Autothrust System In addition to the requirements of §§ 23.143, 23.1309, and 23.1329, the following apply: (a) Quick disengagement controls for the autothrust function must be provided for each pilot. The autothrust quick disengagement controls must be located on the thrust control levers. Quick disengagement controls must be readily accessible to each pilot while operating the thrust control levers. (b) The effects of a failure of the system to disengage the autothrust function when manually commanded by the pilot must be assessed in accordance with the requirements of § 23.1309. (c) Engagement or switching of the flight guidance system, a mode, or a sensor may not cause the autothrust system to affect a transient response that alters the airplane’s flight path any greater than a minor transient, as defined in paragraph (l)(1) of these special conditions. (d) Under normal conditions, the disengagement of any automatic control function of a flight guidance system may not cause a transient response of the airplane’s flight path any greater than a minor transient. (e) Under rare normal and non-normal conditions, disengagement of any automatic control function of a flight guidance system may not result in a transient any greater than a significant transient, as defined in paragraph (l)(2) of these special conditions. (f) The function and direction of motion of each command reference control, such as heading select or vertical speed, must be plainly indicated on—or adjacent to—each control if necessary to prevent inappropriate use or confusion. (g) Under any condition of flight appropriate to its use, the flight guidance system may not produce hazardous loads on the airplane, nor create hazardous deviations in the flight path. This applies to both fault-free operation and in the event of a malfunction, and assumes that the pilot begins corrective action within a reasonable period of time. (h) When the flight guidance system is in use, a means must be provided to E:\FR\FM\30AUR1.SGM 30AUR1 jspears on DSK3GMQ082PROD with RULES Federal Register / Vol. 84, No. 169 / Friday, August 30, 2019 / Rules and Regulations avoid excursions beyond an acceptable margin from the speed range of the normal flight envelope. If the airplane experiences an excursion outside this range, a means must be provided to prevent the flight guidance system from providing guidance or control to an unsafe speed. (i) The flight guidance system functions, controls, indications, and alerts must be designed to minimize flightcrew errors and confusion concerning the behavior and operation of the flight guidance system. Means must be provided to indicate the current mode of operation, including any armed modes, transitions, and reversions. Selector switch position is not an acceptable means of indication. The controls and indications must be grouped and presented in a logical and consistent manner. The indications must be visible to each pilot under all expected lighting conditions. (j) Following disengagement of the autothrust function, a caution must be provided to each pilot. (k) During autothrust operation, it must be possible for the flightcrew to move the thrust levers without requiring excessive force. The autothrust may not create a potential hazard when the flightcrew applies an override force to the thrust levers. (l) For purposes of these special conditions, a transient is a disturbance in the control or flight path of the airplane that is not consistent with response to flightcrew inputs or environmental conditions. (1) A minor transient would not significantly reduce safety margins and would involve flightcrew actions that are well within their capabilities. A minor transient may involve a slight increase in flightcrew workload or some physical discomfort to passengers or cabin crew. (2) A significant transient may lead to a significant reduction in safety margins, an increase in flightcrew workload, discomfort to the flightcrew, or physical distress to the passengers or cabin crew, possibly including non-fatal injuries. Significant transients do not require, in order to remain within or recover to the normal flight envelope, any of the following: (i) Exceptional piloting skill, alertness, or strength. (ii) Forces applied by the pilot which are greater than those specified in § 23.143(c). (iii) Accelerations or attitudes in the airplane that might result in further hazard to secured or non-secured occupants. VerDate Sep<11>2014 15:51 Aug 29, 2019 Jkt 247001 Issued in Kansas City, Missouri, on August 21, 2019. Pat Mullen, Manager, Small Airplane Standards Branch, Policy and Innovation Division, Aircraft Certification Service. [FR Doc. 2019–18814 Filed 8–29–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2019–0627; Amendment No. 71–51] RIN 2120–AA66 Airspace Designations; Incorporation by Reference Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This action amends Title 14 Code of Federal Regulations (14 CFR) part 71 relating to airspace designations to reflect the approval by the Director of the Federal Register of the incorporation by reference of FAA Order 7400.11D, Airspace Designations and Reporting Points. This action also explains the procedures the FAA will use to amend the listings of Class A, B, C, D, and E airspace areas; air traffic service routes; and reporting points incorporated by reference. DATES: These regulations are effective September 15, 2019, through September 15, 2020. The incorporation by reference of FAA Order 7400.11D is approved by the Director of the Federal Register as of September 15, 2019, through September 15, 2020. ADDRESSES: FAA Order 7400.11D, Airspace Designations and Reporting Points, and subsequent amendments can be viewed on line at https:// www.faa.gov/air_traffic/publications/. For further information, you can contact the Airspace Policy Group, Federal Aviation Administration, 800 Independence Avenue SW, Washington, DC 20591; telephone: (202) 267–8783. The Order is also available for inspection at the National Archives and Records Administration (NARA). For information on the availability of FAA Order 7400.11D at NARA, email fedreg.legal@nara.gov or go to https:// www.archives.gov/federal-register/cfr/ ibr-locations.html. FOR FURTHER INFORMATION CONTACT: Sarah A. Combs, Airspace Policy Group, Office of Airspace Services, Federal Aviation Administration, 800 SUMMARY: PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 45651 Independence Avenue SW, Washington, DC 20591; telephone: (202) 267–8783. SUPPLEMENTARY INFORMATION: History FAA Order 7400.11C, Airspace Designations and Reporting Points, effective September 15, 2018, listed Class A, B, C, D and E airspace areas; air traffic service routes; and reporting points. Due to the length of these descriptions, the FAA requested approval from the Office of the Federal Register to incorporate the material by reference in the Federal Aviation Regulations section 71.1, effective September 15, 2018, through September 15, 2019. During the incorporation by reference period, the FAA processed all proposed changes of the airspace listings in FAA Order 7400.11C in full text as proposed rule documents in the Federal Register. Likewise, all amendments of these listings were published in full text as final rules in the Federal Register. This rule reflects the periodic integration of these final rule amendments into a revised edition of Order 7400.11D, Airspace Designations and Reporting Points. The Director of the Federal Register has approved the incorporation by reference of FAA Order 7400.11D in section 71.1, as of September 15, 2019, through September 15, 2020. This rule also explains the procedures the FAA will use to amend the airspace designations incorporated by reference in part 71. Sections 71.5, 71.15, 71.31, 71.33, 71.41, 71.51, 71.61, 71.71, and 71.901 are also updated to reflect the incorporation by reference of FAA Order 7400.11D. Availability and Summary of Documents for Incorporation by Reference This document incorporates by reference FAA Order 7400.11D, Airspace Designations and Reporting Points, dated August 8, 2019, and effective September 15, 2019, in section 71.1. FAA Order 7400.11D is publicly available as listed in the ADDRESSES section of this final rule. FAA Order 7400.11D lists Class A, B, C, D, and E airspace areas, air traffic service routes, and reporting points. The Rule This action amends Title 14 Code of Federal Regulations (14 CFR) part 71 to reflect the approval by the Director of the Federal Register of the incorporation by reference of FAA Order 7400.11D, effective September 15, 2019, through September 15, 2020. During the incorporation by reference period, the FAA will continue to process all proposed changes of the airspace E:\FR\FM\30AUR1.SGM 30AUR1

Agencies

[Federal Register Volume 84, Number 169 (Friday, August 30, 2019)]
[Rules and Regulations]
[Pages 45649-45651]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-18814]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. FAA-2019-0649; Special Conditions No. 23-296-SC]


Special Conditions: DAHER Aerospace Model TBM700 Airplanes; 
Autothrust System

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

-----------------------------------------------------------------------

SUMMARY: These special conditions are issued for the DAHER Aerospace 
Model TBM700 airplane. This airplane will have a novel or unusual 
design feature associated with the use of an autothrust system. The 
applicable airworthiness regulations do not contain adequate or 
appropriate safety standards for this design feature. These special 
conditions contain the additional safety standards the Administrator 
considers necessary to establish a level of safety equivalent to that 
established by the existing airworthiness standards.

DATES: The effective date of these special conditions is August 30, 
2019.
    The FAA must receive your comments by September 30, 2019.

ADDRESSES: Send comments identified by docket number FAA-2019-0649 
using any of the following methods:
    [squ] Federal eRegulations Portal: Go to https://www.regulations.gov 
and follow the online instructions for sending your comments 
electronically.
    [squ] Mail: Send comments to Docket Operations, M-30, U.S. 
Department of Transportation (DOT), 1200 New Jersey Avenue SE, Room 
W12-140, West Building Ground Floor, Washington, DC 20590-0001.
    [squ] Hand Delivery of Courier: Take comments to Docket Operations 
in Room W12-140 of the West Building Ground Floor at 1200 New Jersey 
Avenue SE, Washington, DC, between 9 a.m., and 5 p.m., Monday through 
Friday, except Federal holidays.
    [squ] Fax: Fax comments to Docket Operations at 202-493-2251.
    Privacy: The FAA will post all comments it receives, without 
change, to https://regulations.gov, including any personal information 
the commenter provides. Using the search function of the docket 
website, anyone can find and read the electronic form of all comments 
received into any FAA docket, including the name of the individual 
sending the comment (or signing the comment for an association, 
business, labor union, etc.). DOT's complete Privacy Act Statement can 
be found in the Federal Register published on April 11, 2000 (65 FR 
19477-19478), as well as at https://DocketsInfo.dot.gov.
    Docket: Background documents or comments received may be read at 
https://www.regulations.gov at any time. Follow the online instructions 
for accessing the docket or go to the Docket Operations in Room W12-140 
of the West Building Ground Floor at 1200 New Jersey Avenue SE, 
Washington, DC, between 9 a.m., and 5 p.m., Monday through Friday, 
except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Jeff Pretz, AIR-691, Small Airplane 
Standards Branch, Policy and Innovation Division, Aircraft 
Certification Service, Federal Aviation Administration, 901 Locust, 
Room 301, Kansas City, MO 64106; telephone (816) 329-3239; facsimile 
(816) 329-4090.

SUPPLEMENTARY INFORMATION:

Reason for No Prior Notice and Comment Before Adoption

    The FAA has determined, in accordance with 5 U.S. Code Sec. Sec.  
553(b)(3)(B) and 553(d)(3), that notice and opportunity for prior 
public comment hereon are unnecessary because substantially identical 
special conditions have been subject to the public comment process in 
several prior instances such that the FAA is satisfied that new 
comments are unlikely. For the same reason, the FAA finds that good 
cause exists for making these special conditions effective upon 
issuance. The FAA is requesting comments to allow interested persons to 
submit views that may not have been submitted in response to the prior 
opportunities for comment.

------------------------------------------------------------------------
      Special conditions No.               Company/airplane model
------------------------------------------------------------------------
23-291-SC \1\.....................  Innovation Solutions & Support,
                                     Inc.; Textron Aviation, Inc./Model
                                     B200.
23-283-SC \2\.....................  Pilatus Aircraft Ltd./Model PC-24.
23-272-SC \3\.....................  Cirrus Aircraft Corporation/Model SF-
                                     50.
------------------------------------------------------------------------

Comments Invited

    The FAA invites interested people to take part in this rulemaking 
by sending written comments, data, or views. The most helpful comments 
reference a specific portion of the special conditions, explain the 
reason for any recommended change, and include supporting data. The FAA 
asks that you send two copies of written comments.
---------------------------------------------------------------------------

    \1\ https://www.federalregister.gov/d/2018-28116.
    \2\ https://www.federalregister.gov/d/2017-14938.
    \3\ https://federalregister.gov/a/2015-31058.
---------------------------------------------------------------------------

    The FAA will consider all comments received on or before the 
closing date for comments. The FAA will consider comments filed late if 
it is possible to do so without incurring expense or delay. The FAA may 
change these special conditions based on the comments received.

Background

    On March 28th, 2018, DAHER Aerospace (DAHER) applied for FAA 
validation of its change to Type Certificate No. A60EU \4\ for 
installation of an autothrust system (ATS), also known as an 
autothrottle system, in the Model TBM700 airplane. The Model TBM700 is 
a normal category, metallic, pressurized, low-wing, monoplane that 
seats up to 5 passengers and two flightcrew. A single Pratt & Whitney

[[Page 45650]]

PT6A turboprop engine driving a five bladed variable pitch constant 
speed Hartzell propeller powers the airplane. The airplane has 
retractable tricycle landing gear, a Garmin G3000 avionics suite, and a 
maximum takeoff weight of 7,394 pounds.
---------------------------------------------------------------------------

    \4\ https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/0/B777E11E03DD396C862583AE006215E4?OpenDocument.
---------------------------------------------------------------------------

    The installation of an ATS in the Model TBM700 is intended to 
reduce pilot workload. The ATS is useable in all phases from takeoff to 
approach. The system includes torque and airspeed management capability 
along with monitors to prevent the system from exceeding critical 
engine or airspeed limits. Throttle movement is provided by a servo, 
which moves the throttle lever. The servo can be overridden by pilot 
movement of the throttle and disengages upon selection of the A/T 
disconnect switch on the throttle.
    Section 23.1329, amendment 23-49, only contained requirements for 
automatic pilot systems that act on the airplane flight controls. 
Autothrust systems are automatic systems that act on the thrust 
controls. These systems provide enhanced automation and safety, but may 
also introduce pilot confusion, countering the safety benefit. 14 CFR 
25.1329, amendment 25-119, addresses these concerns for transport 
airplanes. Therefore, these special conditions are based on Sec.  
25.1329 and provide additional requirements to standardize the pilot 
interface and system behavior and enhance pilot awareness of system 
active and armed modes.

Type Certification Basis

    Under the provisions of 14 CFR 21.101, DAHER must show that the 
Model TBM700 airplane, as changed, continues to meet the applicable 
provisions of the regulations incorporated by reference in Type 
Certificate No. A60EU or the applicable regulations in effect on the 
date of application for the change. The regulations incorporated by 
reference in the type certificate are commonly referred to as the 
``original type certification basis.'' Refer to Type Certificate Data 
Sheet No. A60EU for the complete certification basis.
    If the Administrator finds that the applicable airworthiness 
regulations in part 23 do not contain adequate or appropriate safety 
standards for the Model TBM700 airplane because of a novel or unusual 
design feature, special conditions are prescribed under the provisions 
of Sec.  21.16.
    The FAA issues special conditions, as defined in Sec.  11.19, under 
Sec.  11.38 and they become part of the type certification basis under 
Sec.  21.101.
    Special conditions are initially applicable to the model for which 
they are issued. Should the type certificate for that model be amended 
later to include any other model that incorporates the same novel or 
unusual design feature, or should any other model already included on 
the same type certificate be modified to incorporate the same novel or 
unusual design feature, the FAA would apply these special conditions to 
the other model.
    In addition to the applicable airworthiness regulations and special 
conditions, the Model TBM700 must comply with the fuel vent and exhaust 
emission requirements of 14 CFR part 34 and the noise certification 
requirements of 14 CFR part 36; and the FAA must issue a finding of 
regulatory adequacy under Sec.  611 of Public Law 92-574, the ``Noise 
Control Act of 1972.''

Novel or Unusual Design Features

    The Model TBM700 airplane will incorporate the following novel or 
unusual design features:
    An ATS, which provides commands to a servo attached to the throttle 
lever that automatically controls engine thrust. The ATS can be 
operated to control torque or airspeed.

Discussion

    The part 23 airworthiness regulations in the type certification 
basis do not contain appropriate safety standards for this design 
feature. However, part 25 regulations contain appropriate airworthiness 
standards; therefore, these special conditions are derived from 14 CFR 
25.1329, ``Flight guidance system,'' applicable to autothrust systems.

Applicability

    These special conditions are applicable to the Model TBM700 
airplane. Should DAHER apply at a later date for a change to the type 
certificate to include another model incorporating the same novel or 
unusual design feature, the FAA would apply these special conditions to 
that model as well.

Conclusion

    This action affects only a certain novel or unusual design feature 
on the Model TBM700 airplane. It is not a rule of general 
applicability.

List of Subjects in 14 CFR Part 23

    Aircraft, Aviation safety, Signs and symbols.

Citation

    The authority citation for these special conditions is as follows:

    Authority: 49 U.S.C. 106(f), 106(g), 40113, 44701-44702; Pub. L. 
113-53, 127 Stat 584 (49 U.S.C. 44704) note.

The Special Conditions

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the following special conditions are issued as part of 
the type certification basis for DAHER Aerospace Model TBM700 
airplanes.

Autothrust System

    In addition to the requirements of Sec. Sec.  23.143, 23.1309, and 
23.1329, the following apply:
    (a) Quick disengagement controls for the autothrust function must 
be provided for each pilot. The autothrust quick disengagement controls 
must be located on the thrust control levers. Quick disengagement 
controls must be readily accessible to each pilot while operating the 
thrust control levers.
    (b) The effects of a failure of the system to disengage the 
autothrust function when manually commanded by the pilot must be 
assessed in accordance with the requirements of Sec.  23.1309.
    (c) Engagement or switching of the flight guidance system, a mode, 
or a sensor may not cause the autothrust system to affect a transient 
response that alters the airplane's flight path any greater than a 
minor transient, as defined in paragraph (l)(1) of these special 
conditions.
    (d) Under normal conditions, the disengagement of any automatic 
control function of a flight guidance system may not cause a transient 
response of the airplane's flight path any greater than a minor 
transient.
    (e) Under rare normal and non-normal conditions, disengagement of 
any automatic control function of a flight guidance system may not 
result in a transient any greater than a significant transient, as 
defined in paragraph (l)(2) of these special conditions.
    (f) The function and direction of motion of each command reference 
control, such as heading select or vertical speed, must be plainly 
indicated on--or adjacent to--each control if necessary to prevent 
inappropriate use or confusion.
    (g) Under any condition of flight appropriate to its use, the 
flight guidance system may not produce hazardous loads on the airplane, 
nor create hazardous deviations in the flight path. This applies to 
both fault-free operation and in the event of a malfunction, and 
assumes that the pilot begins corrective action within a reasonable 
period of time.
    (h) When the flight guidance system is in use, a means must be 
provided to

[[Page 45651]]

avoid excursions beyond an acceptable margin from the speed range of 
the normal flight envelope. If the airplane experiences an excursion 
outside this range, a means must be provided to prevent the flight 
guidance system from providing guidance or control to an unsafe speed.
    (i) The flight guidance system functions, controls, indications, 
and alerts must be designed to minimize flightcrew errors and confusion 
concerning the behavior and operation of the flight guidance system. 
Means must be provided to indicate the current mode of operation, 
including any armed modes, transitions, and reversions. Selector switch 
position is not an acceptable means of indication. The controls and 
indications must be grouped and presented in a logical and consistent 
manner. The indications must be visible to each pilot under all 
expected lighting conditions.
    (j) Following disengagement of the autothrust function, a caution 
must be provided to each pilot.
    (k) During autothrust operation, it must be possible for the 
flightcrew to move the thrust levers without requiring excessive force. 
The autothrust may not create a potential hazard when the flightcrew 
applies an override force to the thrust levers.
    (l) For purposes of these special conditions, a transient is a 
disturbance in the control or flight path of the airplane that is not 
consistent with response to flightcrew inputs or environmental 
conditions.
    (1) A minor transient would not significantly reduce safety margins 
and would involve flightcrew actions that are well within their 
capabilities. A minor transient may involve a slight increase in 
flightcrew workload or some physical discomfort to passengers or cabin 
crew.
    (2) A significant transient may lead to a significant reduction in 
safety margins, an increase in flightcrew workload, discomfort to the 
flightcrew, or physical distress to the passengers or cabin crew, 
possibly including non-fatal injuries. Significant transients do not 
require, in order to remain within or recover to the normal flight 
envelope, any of the following:
    (i) Exceptional piloting skill, alertness, or strength.
    (ii) Forces applied by the pilot which are greater than those 
specified in Sec.  23.143(c).
    (iii) Accelerations or attitudes in the airplane that might result 
in further hazard to secured or non-secured occupants.

    Issued in Kansas City, Missouri, on August 21, 2019.
Pat Mullen,
Manager, Small Airplane Standards Branch, Policy and Innovation 
Division, Aircraft Certification Service.
[FR Doc. 2019-18814 Filed 8-29-19; 8:45 am]
BILLING CODE 4910-13-P
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