Airworthiness Compliance Checklists for Common Part 23 Supplemental Type Certificate (STC) Projects

8/24/05 AC 23- 24T AIRWORTHINESS COMPLIANCE CHECKLISTS FOR COMMON PART 23 SUPPLEMENTAL TYPE CERTIFICATE (STC) PROJECTS 1. What is the purpose of this Advisory Circular (AC)?

This AC provides information to create compliance checklists for some common Title 14 of the Code of Federal Regulations (14 CFR) part 23 Supplemental Type Certificate (STC) projects.

These checklists may be used to fulfill some of the requirements for a Certification Plan for STC projects. The standard compliance checklist provided with this AC shows typical methods of compliance with the regulations and provides a cross-reference to other related guidance material. Guidance specific to STCs for autopilot, engine, propeller, auxiliary fuel tank, and gross weight changes is included in sections 12 through 19 of this AC. The checklists created using the information in this AC complement the guidance in the Guides for Certification of Part 23 Airplanes (ACs 23-8B, 23-16A, 23-17B, and 23-19) and other more project-specific guidance. The certification requirements listed in sections 12 through 19 of this AC may be complete for certain STC projects or may be used as a starting place when applying for an STC that may be beyond the scope of the common STCs in this AC. This AC describes an acceptable means, but not the only means, of compliance with 14 CFR part 23. The material in this AC is neither mandatory nor regulatory in nature and does not constitute a regulation.

2. Who is affected by this AC?

a. Anyone applying for an STC for the common changes covered in this AC may create a project-specific compliance checklist as a starting point for discussions with their geographical Aircraft Certification Office (ACO). The list of ACOs with their addresses and phone numbers may be found on the Internet at www.faa.gov/certification/aircraft/acochart.htm .

b. Federal Aviation Administration (FAA) engineers working on STC projects for the common changes covered in this AC may also use the compliance checklists created using this AC as a basis for discussions with anyone applying for an STC.

3. What documents does this AC supersede?

This AC does not supersede any existing documents.

4. What other publications are related to this AC?

The publications listed in these paragraphs are a representative selection of documents that are relevant to part 23 airplane certification. The compliance checklist in Appendix 1 references many of these publications as guidance applicable to individual regulations. Depending on the details of a particular certification project, other guidance material may apply, and the project specific checklist should include all guidance material used. A complete list of documents is available at the Internet addresses listed below.

a. Regulations: In general, this AC covers 14 CFR part 23 regulations in their entirety. Specific regulations that are applicable to the common STC projects covered in this AC are listed in paragraphs 12 AC 23-24T 8/24/05 through 19. In addition, the following regulations are available on the Internet at www.airweb.faa.gov/far .

14 CFR part 21, subpart E Supplemental Type Certificates 14 CFR part 33 Airworthiness Standards: Aircraft Engines 14 CFR part 34 Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered Airplanes 14 CFR part 35 Airworthiness Standards: Propellers 14 CFR part 36 Noise Standards: Aircraft Type and Airworthiness Certification Many small airplanes certificated before the Civil Air Regulations (CARs) recodification to the Federal Aviation Regulations in 1964 list the CARs in their original certification basis. The checklist in Appendix 1 lists the CAR 3 cross-reference to the 14 CFR part 23 regulations at the recodification. These historic references are on the Internet at http://dotlibrary.specialcollection.net/ .

b. FAA Orders and ACs available at no charge: Copies of the current FAA orders and ACs listed below may be obtained at no charge from: U.S. Department of Transportation Subsequent Distribution Office, M-30 Ardmore East Business Center th 3341Q 75 Avenue Landover, MD 20795 Telephone: 301-322-4779 Facsimile: 301-386-5394 These documents are also available on the Internet at www.airweb.faa.gov/orders and www.airweb.faa.gov/ac respectively.

FAA Order 8110.4B Type Certification FAA Order 8110.48 How to Establish a Certification Basis for Changed Aeronautical Products AC 20-53A Protection of Aircraft Fuel Systems Against Fuel Vapor Ignition Due to Lightning AC 20-66A Vibration and Fatigue Evaluation of Airplane Propellers AC 20-73 Aircraft Ice Protection AC 20-74 Aircraft Position and Anticollision Light Measurements AC 20-88A Guidelines on the Marking of Aircraft AC 20-119 Fuel Drain Valves 8/24/05 AC 23- 24T AC 20-122A Anti-misfueling Devices: Their Availability and Use AC 20-124 Water Ingestion Testing for Turbine Powered Airplanes AC 20-128A Design Consideration for Minimizing Hazards Caused by Uncontained Turbine Engine and Auxiliary Power Unit Rotor Failure AC 20-130A Airworthiness Approval of Navigation or Flight Management Systems Integrating Multiple Navigation Sensors AC 20-135 Powerplant Installation and Propulsion System Component Fire Protection Test Methods, Standards, and Criteria AC 20-136 Protection of Aircraft Electrical/Electronic Systems against the Indirect Effects of Lightning AC 20-138A Airworthiness Approval of Global Navigation Satellite System (GNSS) Equipment AC 20-146 Methodology for Dynamic Seat Certification by Analysis for Use in Part 23, 25, 27, and 29 Airplanes and Rotorcraft AC 20-147 Turbojet, Turboprop, and Turbofan Engine Induction System Icing and Ice Ingestion AC 21-40 Application Guide for Obtaining a Supplemental Type Certificate AC 21.101-1 CHG 1 Establishing the Certification Basis of Changed Aeronautical Products AC 23-2 Flammability Tests AC 23-9 [Large AC] Evaluation of Flight Loads on Small Airplanes with T, V, +, or Y Empennage Configurations AC 23-10 Auxiliary Systems for Reciprocating and Turbine Powered part 23 Airplanes AC 23-13 Fatigue and Fail-Safe Evaluation of Flight Structure and Pressurized Cabin for Part 23 Airplanes AC 23-14 Type Certification Basis for Conversion from Reciprocating Engine to Turbine Engine-Powered Part 23 Airplanes AC 23-15A Small Airplane Certification Compliance Program AC 23-15A CHG 1 Small Airplane Certification Compliance Program AC 23-19 Airframe Guide for Certification of Part 23 Airplanes AC 23-21 Airworthiness Compliance Checklists Used to Substantiate Major Alterations for Small Airplanes AC 23-21 CHG 1 Airworthiness Compliance Checklists Used to Substantiate Major Alterations for Small Airplanes AC 23-24T 8/24/05 AC 23-23 Standardization Guide for Integrated Cockpits in Part 23 Airplanes AC 23.143-1 Ice Contaminated Tailplane Stall (ICTS) AC 23.562-1 Dynamic Testing of Part 23 Airplane Seat/Restraint Systems and Occupant Protection AC 23.607-1 Self-Locking Nuts on Bolts Subject to Rotation AC 23.629-1B Means of Compliance with Section 23.629 “Flutter” AC 23.1309-1C Equipment, Systems, and Installations in Part 23 Airplanes AC 23-1311-1A Installation of Electronic Displays in Part 23 Airplanes AC 23.1419-2C Certification of Part 23 Airplanes for Flight in Icing Conditions AC 23-1523 Minimum Flight Crew AC 33-2B Aircraft Engine Type Certification Handbook AC 33.28-1 Compliance Criteria for 14 CFR § 33.28, Aircraft Engines, Electrical and Electronic Engine Control Systems AC 33.28-2 Guidance Material for 14 CFR § 33.28, Reciprocating Engines, Electrical and Electronic Engine Control Systems AC 35.37-1A Composite Propeller Blade Fatigue Substantiation AC 36-1H Noise Levels for U.S. Certificated and Foreign Aircraft AC 36-2C Measured or Estimated (Uncertificated) Airplane Noise Levels AC 36-3H Estimated Airplane Noise Levels in A-Weighted Decibels AC 36-4C Noise Standards: Aircraft Type and Airworthiness Certification AC 183.29-1HH Designated Engineering Representatives c. ACs available for purchase: Copies of the current ACs listed below are available to buy from: Superintendent of Documents P.O. Box 371954 Pittsburgh, PA 15250-7954 These documents are also available on the Internet at www.airweb.faa.gov/ac .

AC 23-8B Flight Test Guide for Certification of Part 23 Airplanes AC 23-16A Powerplant Guide for Certification of Part 23 Airplanes and Airships

8/24/05 AC 23- 24T AC 23-17B Systems and Equipment Guide for Certification of Part 23 Airplanes and Airships AC 23-19 Airframe Guide for Certification of Part 23 Airplanes d. Policy Statements: Copies of the current Policy Statements listed below may be obtained at no charge from: Small Airplane Directorate Regulations and Policy Branch 901 Locust St., Room 301 Kansas City, MO 64106 These documents are also available on the Internet at www.airweb.faa.gov/policy .

PS-ACE100-2001-004 Guidance for Reviewing Certification Plans to Address Human Factors for Certification of Part 23 Small Airplanes PS-ACE100-2001-006 Static Strength Substantiation of Composite Airplane Structure PS-ACE100-2002-002 Installation Approval of Multi-Function Displays Using the AML STC Process PS-ACE100-2002-004 Diesel Engine Installations PS-ACE100-2002-006 Material Qualification and Equivalency for Polymer Matrix Composite material Systems PS-ACE100-2002-007 Final Policy for Pitot Heat Indication Systems for 14 CFR, Part 23, § 23.1326(b)(1) PS-ACE100-2002-008 Propeller Testing V Versus V d NE PS-ACE100-2004-10023 Final Policy Statement for Flammability of Electrical Wiring Used in Part 23 Aircraft per 14 CFR, part 23, §§ 23.853 and 23.1359 PS-ACE100-2004-10024 Installation of Electronic Engine Control for Reciprocating Engine PS-ACE100-2004-10030 Substantiation of Secondary Composite Structures 5. How is this Advisory Circular (AC) related to other Federal Aviation Administration (FAA) ACs and Policy Statements?

a. This AC provides guidance on the applicable sets of regulations for some common STC projects and a standard checklist to use in creating a project-specific checklist. The standard checklist shows the typical methods of compliance with the regulations and cross-references other related guidance material. This AC is organized by topic to address some common STC projects and is to be used with other published guidance described in b and c below.

AC 23-24T 8/24/05 b. The Small Airplane Directorate has published Guides for Certification of Part 23 Airplanes covering broad sections of Title 14 of the Code of Federal Regulations (14 CFR) part 23 regulations (that is: Flight Test, Powerplant, Systems, and Structures). These Guides for Certification of Part 23 Airplanes (that is: ACs 23-8B, 23-16A, 23-17B, and 23-19) provide guidance for showing compliance with individual regulations.

c. The Small Airplane Directorate has published ACs and Policy Statements that address specific airplane installations (for example: AC 23-10, AC 23-14, and AC 23-1419-2C). These documents provide guidance for showing compliance with the sets of regulations applicable to specific airplane design changes and installations.

6. What common STC projects does this AC address?

a. Review of databases for STCs and Certification Project Notices (CPNs) initiated since 2002 shows the five most common categories of changes over this time period are: (1) Automatic Flight Control Systems installations, including autopilot installations with electric trim; (2) Engine installations, including total engine replacements, horsepower (hp) increases, using different engine mounts, adding Full Authority Digital Engine Controls (FADEC), cowling modifications, and adding turbochargers; (3) Propeller installations, including spinner changes and new propellers with different diameters, different number of blades, and variable pitch; (4) Fuel systems installations, including the addition of auxiliary fuel tanks/cells, fuel filters and flow transducers, annunciators, indicators and pumps, and adding tip tanks; and (5) Airplane gross weight increases.

b. These categories encompass many different potential airplane changes. This AC covers the following specific STC projects. In the future, checklists may be added to this AC to cover other specific STC projects.

(1) Installation of an autopilot system; (2) Installation of a reciprocating engine with increased horsepower; (3) Installation of a turbine engine with increased horsepower; (4) Installation of turbine engines to replace reciprocating engines; (5) Installation of a different propeller (simple); (6) Installation of a different propeller (complex); (7) Installation of auxiliary fuel tanks; and (8) Increase in the airplane gross weight.

8/24/05 AC 23- 24T 7. Where can the common STC project checklists be found?

A standard checklist is in Appendix 1. Sections 12 through 19 of this AC list the basic regulations applicable to each of the different common STC projects. This information may be used to create a checklist for the project as described in sections 9, 10, and 11. The checklists created using this AC are also available on the Internet at http://www.faa.gov/other_visit/aviation_industry/designees_delegations/tools/forms/checklists in a format that allows the user to fill the forms in on their computer.

8. How were the standard compliance checklist and the lists of applicable regulations for these common STC projects developed?

Checklists used by various ACOs on past and present certification projects and current guidance material were used to develop the standard compliance checklist and the lists of applicable regulations for each of the common STC projects.

9. How should the compliance checklists in this AC be used in certification projects?

Order 8110.4B and AC 21-40 describe the STC application process that begins with the applicant submitting a completed FAA Form 8110-12 with a Certification Plan. A compliance checklist may fulfill some of the requirements for the Certification Plan. The information in this AC is a starting point to create a project-specific compliance checklist for some common STC projects that tells how the applicant intends to show compliance with the regulations. This checklist submitted as part of the Certification Plan provides applicants and ACO engineers a communication tool to begin the project.

10. Should these checklists be combined into one for projects that cover more than one of these changes?

Yes, the requirements for each of the changes should be combined into a single checklist if the project includes more than one of the changes listed in this AC. For example, adding auxiliary fuel tanks could involve a gross weight increase. In such cases, it is prudent to plan the certification program to show compliance to the applicable rules for these changes at the same time.

AC 23-24T 8/24/05 11. How should the standard checklist be filled in to generate a checklist specific to a project?

Figures 1 and 2 show the first and second pages of the standard compliance checklist from appendix 1 of this AC. The following paragraphs describe the checklist entries with the letters of the paragraphs below matching the circled letters in the figures. A template checklist for each of the common STC projects listed in sections 12 through 19 of this document is available at http://www.faa.gov/other_visit/aviation_industry/designees_delegations/tools/forms/checklists .

The regulations shown in the standard and template checklists do not show all subparagraphs.

Where the method of compliance differs between subparagraphs of the same regulation, you should expand the checklist to show the subparagraphs and the methods of compliance for each.

Figure 3 shows an example of an expanded checklist entry.

a. When you initially use the checklist, this field will be blank. The ACO assigns a project number when accepting the project application.

b. Enter the name of the originator of the completed checklist.

c. Enter the date of the latest checklist revision.

d. Enter the latest checklist revision. The applicant may choose any method to track this, provided it can distinguish different versions. For example, use sequential numbering or lettering for each new version of the checklist.

e. Enter the make of the airplane to receive this STC, as shown on the Type Certificate Data Sheet (TCDS) (for example: Cessna, Piper).

f. Enter the complete model number of the airplane to receive this STC, as shown on the TCDS (for example: 150C, PA-32-260).

g. Enter the number of the TCDS for the airplane make and model listed in e and f. The TCDS information is on the Internet at www.airweb.faa.gov/TCDS .

h. Enter the original certification basis of the airplane as listed on the airplane TCDS. It is acceptable to reference the airplane TCDS.

i. Enter the proposed certification basis for this STC project. Refer to AC 21.101-1 CHG 1 and FAA Order 8110.4B for guidance on choosing the proposed certification basis.

j. Check the box to indicate whether the proposed STC is for one serial number only or if it will be for duplication on other aircraft.

k. Enter a brief description of the modification similar to that stated on FAA Form 8110-12 (found in FAA Order 8110.4B). A complete description of the change will appear in the certification plan provided to the ACO as described in FAA Order 8110.4B.

l. Enter the page number and the number of pages.

m. Enter the applicable regulation amendment level used as the Certification Basis for the STC.

n. Enter the method or combination of methods used to show compliance with the regulations. Make an entry for each regulation (or sub-paragraph as explained in paragraph 11 above) in the checklist. The regulations listed in sections 12 through 19 are considered the 8/24/05 AC 23- 24T minimum required for showing compliance. Other regulations may be applicable depending on the specific changes proposed for the STC. Determine the applicability to the project for all the regulations. The standard checklist in appendix 1 lists typical methods of compliance that have been acceptable for other STC projects in the past. The unique features of the project may require other combinations of methods. Check whether the methods listed are appropriate and change them to reflect the certification plan for the specific STC project. When choosing the applicable regulations, make sure to consider the impact of the airplane changes on areas such as structural integrity, performance, controllability, and human factors. See FAA Policy Statement PS-ACE100-2001-004 for guidance that addresses human factors considerations. Use the following definitions when filling in this column. A more detailed description of the method of compliance (for example: component testing, hand calculations, validated finite element model analysis, or a combination of methods) should be included in any compliance plans referenced in the checklist plan column and remarks column described in sections 11.o and 11.q respectively.

(1) Flight Test (FT) – This method of compliance is a test of the airplane in the air or on the ground when the nature of the test requires a flight test pilot.

(2) Ground Test (GT) – This method of compliance includes component bench testing, testing of simulated airplane systems, and ground testing of the airplane. These tests may be precursors to a flight test or may be used to show compliance when appropriate, and judged to be conservative.

(3) Analysis (AN) – This method of compliance includes a quantitative or qualitative assessment, as appropriate, of structures, systems, components, or the entire airplane. An analysis may be a precursor to ground and flight tests and a validation of the design. An analysis must be validated using published previous experience or appropriate testing to be accepted for showing compliance to the regulations.

(4) Design (DE) – This method of compliance encompasses the inherent features of structures, systems, or components. Inspection of airplane hardware, the drawings, the bill of materials, or other documentation, such as material specifications shows compliance with the applicable regulations.

(5) Similarity (SI) – This method of compliance is a comparison between a previously certificated design and the proposed design. The intent is to show that these designs are the same in all ways relative to showing compliance with the applicable regulation, so the proposed design will perform the same or better than the previously certificated design. The applicant must account for any differences in the regulations if the amendment levels of the regulations are not the same for the two designs. Refer to the other guidance applicable to the different regulations to determine if similarity is proper.

(6) Equivalent Level of Safety Finding (ELOS) – Title 14 CFR part 21, § 21.21(b)(1) and FAA Order 8110.4B paragraph 2-10g describe this method of compliance. An ELOS is issued when the applicant cannot show literal compliance with a regulation, and the applicant shows to the FAAs satisfaction that compensating factors achieve a safety level equal to that of the applicable regulation. The applicant may propose the use of an ELOS by submitting a letter to the ACO for consideration. The FAA is responsible for making the finding of equivalency and AC 23-24T 8/24/05 issuing the ELOS memo if satisfied. If proposing an ELOS for a given regulation, enter the reference for the proposal letter into the checklist under the “Plan, Drawing, Report Number” column for the regulation (see section 11.o.) and on the last page of the checklist under the “EQUIVALENT LEVELS OF SAFETY (ELOS):” heading. Make all proposals for ELOSs to the ACO early in the project to allow time for processing.

(7) Petition for Exemption (PExmpt) – Title 14 CFR part 11, § 11.15 defines a petition for exemption as, “… a request to the FAA by an individual or entity asking for relief from the requirements of a current regulation. ” Petitions for exemptions are rulemaking as described in 14 CFR part 11 and are subject to a public review process that is outside the scope of this AC. If petitioning for exemption from a given regulation, enter the reference for the petition letter into the “Plan, Drawing, Report Number” column for the regulation (see section 11.o.) and on the last page of the checklist under the “EXEMPTIONS:” heading. Make all petitions for exemption to the ACO early in the project to allow time for processing.

(8) Not Applicable (N/A) – This means the specific regulation does not apply to the design or modification for this STC; therefore, a showing of compliance is not necessary. Enter the reason the rule is not applicable in the “Applicable Guidance, References, and Remarks” column of the checklist described in section 11.q. below.

o. Enter the plan, drawing, and report numbers used to document the showing of compliance with the regulation. The items referenced here should contain sufficient detail to show compliance to the regulation.

p. Enter the name and designee number (as applicable) of the Person or Entity that will find or recommend compliance with each of the applicable regulations. This could be a Designee (Designated Engineering Representatives (DER), Designated Alteration Stations (DAS), Delegated Option Authorization) or the FAA. The FAA encourages applicants to use Designees in their projects. More information on designees is on the Internet at www.faa.gov/other_visit/aviation_industry/designees_delegations . Consultant DERs typically provide their services to applicants for a fee. A directory of DERs is available in AC 183.29-1HH. An updated electronic directory and more information on DERs may is on the Internet at www.faa.gov/certification/aircraft/av-info/dst/DER_content.htm . Get Designees concurrence before submitting the checklist to the ACO.

q. Enter the applicable guidance followed as well as other references and remarks clarifying how you are showing compliance with the applicable regulations. If entering N/A for Method of Compliance, enter the reason the rule is not applicable in this column. The checklist in this AC lists the latest revisions of other ACs with applicable guidance in this column. These revisions are current as of the release date of AC 23-24. When creating a project-specific checklist, enter the latest revisions of these documents in this column as found on the Internet at www.airweb.faa.gov/AC . Reference other applicable guidance as appropriate.

8/24/05 AC 23- 24T a c b d e j f g k h i l Figure 1 – First page of the compliance checklist AC 23-24T 8/24/05 a c b d q n o p m l Figure 2 – Second page of the compliance checklist 8/24/05 AC 23- 24T Figure 3 – Example of an expanded checklist entry

AC 23-24T 8/24/05 12. What are the applicable regulations and guidance for the installation of an autopilot system?

a. This change covers the installation of components associated with an autopilot system including the autopilot mode control and annunciation panel, the autopilot computer, the servos and actuators that drive control surfaces, and the data sources (pressure sensors, attitude data sources, navigation sources, other system interfaces) needed for proper functioning. The certification requirements for these installations are dependent on the type of autopilot system being implemented. AC 23-17B provides additional guidance regarding autopilot installations.

b. There are common certification issues that are related to autopilot installation approvals that need to be addressed, but are not covered in AC 23-17B and other existing guidance. Most of these issues can be related to specific installation aspects and complexity of a particular installation, the interface with existing systems on a particular airplane, and maintenance related issues. These items are dependent on the autopilot design. The following are examples of items that should be considered: (1) Certification Basis: Advisory Circular 21.101-1 CHG 1 generally classifies autopilot installations as non-significant. Digital autopilot systems frequently are complex enough that this may not be the case. These systems may require additional effort to assure the proper interactions of the software and hardware. Hardware design assurance should also include RTCA/DO-160 testing to make sure the sensors and components being used meet appropriate airworthiness requirements. Other regulations in addition to those listed in section 12.c. below may need to be considered in this case.

(2) System Integration: Current guidance in AC 20-130A and AC 20-138A requires the source of navigation information be annunciated on or near the affected display. For an autopilot installation, the source of navigation data must be clearly annunciated to indicate to the pilot which source is driving the autopilot. This could include a Global Positioning System (GPS) roll steering source, an Instrument Landing System course deviation source, or some other navigation source. The lack of clear annunciation and the subsequent potential for confusion has been a contributing factor to several small airplane accidents. Any new autopilot installation must be integrated with existing navigation systems in a way that is clear to the pilot. The autopilot should be designed to avoid inadvertent mode changes. Also, if a Control Wheel Steering (CWS) function is implemented to allow temporary interrupt of the autopilot for the pilot to reposition the airplane, the CWS switch should not cause inadvertent mode changes.

(3) AFM Limitations on the Autopilot Envelope: Many autopilots are not capable of acceptable control of the airplane in all flight conditions. Frequently, flight manual limitations are used to restrict the use of the autopilot above or below a given airspeed, in certain turbulence conditions, or in certain airplane configurations. Title 14 CFR part 23, § 23.1329 clearly states that the autopilot cannot cause deviations in flight path. This includes the requirement that the autopilot should not be able to drive the airplane into a stalled condition, particularly in icing conditions.

8/24/05 AC 23- 24T (4) Maintenance Related Issues: The applicant should provide a means to insure proper autopilot rigging with the existing controls system. This would include checking primary and bridal cable tensions to make sure the airplane is rigged properly before and after the installation, and at regular maintenance intervals.

c. The applicable regulations for the installation of an autopilot system should include but are not limited to the following: (1) Title 14 CFR part 23, subpart B, §§ 23.143, 23.253; (2) Title 14 CFR part 23, subpart C, §§ 23.301, 23.303, 23.305, 23.307, 23.391, 23.395, 23.397, 23.561; (3) Title 14 CFR part 23, subpart D, §§ 23.603, 23.605, 23.607, 23.609, 23.611, 23.613, 23.619, 23.625, 23.627, 23.671, 23.672, 23.677, 23.685, 23.689, 23.693, 23.771, 23.777, 23.779, 23.853, 23.867; (4) Title 14 CFR part 23, subpart F, §§ 23.1301, 23.1307, 23.1309, 23.1311, 23.1321, 23.1322, 23.1325, 23.1329, 23.1335, 23.1351, 23.1357, 23.1359, 23.1365, 23.1367, 23.1381, 23.1431; and (5) Title 14 CFR part 23, subpart G, §§ 23.1501, 23.1529, 23.1541, 23.1555, 23.1581, 23.1583, 23.1585.

13. What are the applicable regulations and guidance for the installation of a reciprocating engine with increased horsepower?

a. This change covers the replacement of a spark ignition reciprocating engine with a different spark ignition reciprocating engine that is able to supply more horsepower. This type of change is done mostly to increase the performance of the airplane in take-off and climb and maintains the airspeed limits of the airplane. These installations may increase the gross weight of the airplane in which case the applicant should refer to the gross weight increase compliance checklist for additional requirements. The impact of the increased horsepower on the noise level should be considered and accounted for per Title 14 CFR part 36. AC 23-19 provides additional guidance regarding modifications involving increased engine power.

b. The need for a limited spin matrix on an STC program is a subjective decision based on the service history of the specific airplane being modified. It is not possible to offer a comprehensive list of when to re-test the spin matrix because of the number of variables to consider. There are instances of airplanes with significant modifications that had little effect on spin recovery, and airplanes with subtle modifications that changed the spin recovery dramatically. If it is determined that the airplane does need to be re-evaluated for spin recovery, then a limited matrix using the middle and edges of the envelope is normally all that is needed to verify the airplane recovers.

c. The following key airplane characteristics and features seem to relate directly to the “stall/spin” or departure accidents, and should indicate the need for more evaluation of the spin characteristics.

AC 23-24T 8/24/05 (1) Stall characteristics - Does the airplane just buffet at full aft control or does it roll off dramatically with no aerodynamic warning? Does the airplane require talented footwork to keep the wings level or could the pilot put their feet on the floor during the stall with little roll- off? An airplane that is resistant to stalling and easy to keep the wings level may not need a spin recovery re-evaluation, but an airplane with poor stall handling qualities and a poor “stall/spin” accident history will need a spin recovery re-evaluation.

(2) Stick force gradient - Airplanes with steep stick force gradients are involved in fewer “stall/spin” accidents than airplanes with light force gradients.

(3) Stall warning - A stall warning system can reduce the number of “stall/spin” accidents depending on the effectiveness of the system. There are numerous stall warning schemes ranging from the ineffective lights to the very effective stick shakers with warning horns.

d. The following rules-of-thumb have been used with reasonable success since 1972 for airplane changes that increase the power and should be considered when addressing the spin recovery.

(1) Spin tests that are required because of mass distribution changes will require the use of power (75% Maximum Continuous Power (MCP) / thrust or full throttle, whichever is less) for one full turn into the spin.

(2) Airplanes modified by increasing the installed horsepower (maximum takeoff power) by more than 10% or 25 horsepower, whichever is less, over the original type certificated airplane installed horsepower rating, will require spin testing.

(3) Turbocharged engine installations will be evaluated as follows: (a) Determine the maximum power available on the original engine at 10,000 feet pressure altitude.

(b) Determine the value of 75% MCP on the new engine.

(c) If the difference between (a) and (b) exceeds either 10% of the original installed horsepower (maximum takeoff power) or 25 horsepower, spin tests will be conducted.

(4) Airplanes modified as described in paragraph 9.d.(2) may accept a de-rated power schedule in lieu of spin testing. The maximum horsepower difference criteria, 10% or 25 horsepower, whichever is less, applies from sea level to the airplane service ceiling. This requires a placard of manifold pressure versus pressure altitude (at rated Revolutions Per Minute (RPM)) corresponding to the maximum allowable horsepower differential between the de-rated engine and the original type certificated engine.

8/24/05 AC 23- 24T e. Using a limited spin matrix should be considered if the change to the airplane causes a weight and/or a rotational inertia increase of greater than 10%.

f. The applicable regulations for the installation of a reciprocating engine with increased horsepower should include, but are not limited to, the following: (1) Title 14 CFR part 23, subpart B, §§ 23.25, 23.33, 23.45, 23.49, 23.65, 23.66, 23.67, 23.75, 23.77, 23.143, 23.145, 23.147, 23.149, 23.155, 23.161, 23.171, 23.175, 23.177, 23.201, 23.203, 23.207, 23.221 (except agricultural and twin engine airplanes), 23.231, 23.233, 23.235, 23.237, 23.239, 23.251, 23.253; (2) Title 14 CFR part 23, subpart C, §§ 23.301, 23.303, 23.305, 23.307, 23.331, 23.333, 23.335, 23.337, 23.341, 23.361, 23.363, 23.371, 23.479, 23.499, (23.572, 23.573, 23.574, 23.575 as required or if part of original certification basis); (3) Title 14 CFR part 23, subpart D, §§ 23.601, 23.603, 23.607, 23.609, 23.611, 23.613, 23.619, 23.627, 23.629, 23.735, 23.777, 23.779, 23.781, 23.831, 23.841, 23.863, 23.865, 23.867; (4) Title 14 CFR part 23, subpart E, §§ 23.901, 23.903, 23.905, 23.907, 23.925, 23.929, 23.933, 23.939, 23.943, 23.951, 23.953, 23.954, 23.955, 23.959, 23.961, 23.991, 23.993, 23.994, 23.995, 23.997, 23.1105, 23.1107, 23.1011, 23.1013, 23.1015, 23.1017, 23.1019, 23.1021, 23.1023, 23.1027, 23.1041, 23.1043, 23.1047, 23.1091, 23.1093, 23.1101, 23.1103, 23.1105, 23.1107, 23.1121, 23.1123, 23.1141, 23.1143, 23.1145, 23.1147, 23.1149, 23.1153, 23.1163, 23.1165, 23.1181, 23.1182, 23.1183, 23.1189, 23.1191, 23.1193, 23.1195, 23.1197, 23.1199, 23.1201, 23.1203; (5) Title 14 CFR part 23, subpart F, §§ 23.1301, 23.1303, 23.1305, 23.1309, 23.1311, 23.1321, 23.1322, 23.1329, 23.1337, 23.1351, 23.1353, 23.1357, 23.1359, 23.1416, 23.1437, 23.1435, 23.1438; (6) Title 14 CFR part 23, subpart G, §§ 23.1501, 23.1505, 23.1513, 23.1521, 23.1527, 23.1529, 23.1541, 23.1543, 23.1545, 23.1549, 23.1551, 23.1555, 23.1557, 23.1581, 23.1583, 23.1585, 23.1587; and (7) Title 14 CFR part 36.

14. What are the applicable regulations and guidance for the installation of a turbo-prop engine with increased horsepower?

a. This change covers the replacement of a turbo-prop engine with a different turbo-prop engine that is able to supply more horsepower. This type of change is done mostly to increase the performance of the airplane in take-off, climb, and cruise at altitude. These installations may increase the gross weight of the airplane, in which case, the applicant should refer to the gross weight increase compliance checklist for additional requirements. The impact of the increased horsepower on the noise level should be considered and accounted for per Title 14 CFR part 36.

AC 23-19 provides additional guidance regarding modifications involving increased engine power.

AC 23-24T 8/24/05 b. The need for a limited spin matrix on an STC program is a subjective decision based on the service history of the specific airplane being modified. It is not possible to offer a comprehensive list of when to re-test the spin matrix because of the number of variables to consider. There are instances of airplanes with significant modifications that had little effect on spin recovery, and airplanes with subtle modifications that changed the spin recovery dramatically. If it is determined that the airplane does need to be re-evaluated for spin recovery, then a limited matrix using the middle and edges of the envelope is normally all that is needed to verify the airplane recovers.

c. The following key airplane characteristics and features seem to relate directly to the “stall/spin” or departure accidents, and should indicate the need for more evaluation of the spin characteristics.

(1) Stall characteristics - Does the airplane just buffet at full aft control or does it roll off dramatically with no aerodynamic warning? Does the airplane require talented footwork to keep the wings level or could the pilot put their feet on the floor during the stall with little roll- off? An airplane that is resistant to stalling and easy to keep the wings level may not need a spin recovery re-evaluation, but an airplane with poor stall handling qualities and a poor “stall/spin” accident history will need a spin recovery re-evaluation.

(2) Stick force gradient - Airplanes with steep stick force gradients are involved in fewer “stall/spin” accidents than airplanes with light force gradients.

(3) Stall warning - A stall warning system can reduce the number of “stall/spin” accidents depending on the effectiveness of the system. There are numerous stall warning schemes ranging from the ineffective lights to the very effective stick shakers with warning horns.

d. The following rules-of-thumb have been used with reasonable success since 1972 for airplane changes that increase the power and should be considered when addressing the spin recovery.

(1) Spin tests that are required because of mass distribution changes will require the use of power (75% MCP or full throttle, whichever is less) for one full turn into the spin.

(2) Airplanes modified by increasing the installed horsepower (maximum takeoff power) by more than 10% or 25 horsepower, whichever is less, over the original type certificated airplane installed horsepower rating, will require spin testing.

(3) Turboprop engine installations will be evaluated as follows: (a) Determine the maximum power available on the original engine at 10,000 feet pressure altitude.

(b) Determine the value of 75% MCP on the new engine.

(c) If the difference between (a) and (b) exceeds either 10% of the original installed horsepower (maximum takeoff power) or 25 horsepower, spin tests will be conducted.

(4) Airplanes modified as described in paragraph 10.d.(2) may accept a de-rated power schedule in lieu of spin testing. The maximum horsepower difference criteria, 10% or 25 8/24/05 AC 23- 24T horsepower whichever is less, applies from sea level to the airplane service ceiling. This requires a placard of manifold pressure versus pressure altitude (at rated RPM) corresponding to the maximum allowable horsepower differential between the de-rated engine and the original type certificated engine.

e. Using a limited spin matrix should be considered if the change to the airplane causes a weight and/or a rotational inertia increase of greater than 10%.

f. The applicable regulations for the installation of a turbo-prop engine with increased horsepower should include, but are not limited to, the following: (1) Title 14 CFR part 23, subpart B, §§ 23.25, 23.33, 23.45, 23.49, 23.65, 23.66, 23.67, 23.75, 23.77, 23.143, 23.145, 23.147, 23.149, 23.155, 23.161, 23.175, 23.171, 23.177, 23.201, 23.203, 23.207, 23.221 (except agricultural and twin engine airplanes), 23.231, 23.233, 23.235, 23.237, 23.239, 23.251, 23.253; (2) Title 14 CFR part 23, subpart C, §§ 23.301, 23.303, 23.305, 23.307, 23.331, 23.333, 23.335, 23.337, 23.341, 23.361, 23.363, 23.367, 23.371, 23.479, 23.499, (23.572, 23.573, 23.574, 23.575 as required or if part of original certification basis); (3) Title 14 CFR part 23, subpart D, §§ 23.601, 23.603, 23.607, 23.609, 23.611, 23.613, 23.619, 23.627, 23.629, 23.735, 23.777, 23.779, 23.781, 23.831, 23.841, 23.863, 23.865, 23.867; (4) Title 14 CFR part 23, subpart E, §§ 23.901, 23.903, 23.904, 23.905, 23.907, 23.925, 23.929, 23.933, 23.937, 23.939, 23.943, 23.951, 23.953, 23.954, 23.955, 23.959, 23.961, 23.965, 23.973, 23.977, 23.991, 23.993, 23.994, 23.995, 23.997, 23.1011, 23.1013, 23.1015, 23.1017, 23.1019, 23.1021, 23.1023, 23.1027, 23.1041, 23.1043, 23.1045, 23.1091, 23.1093, 23.1103, 23.1105, 23.1107, 23.1111, 23.1121, 23.1123, 23.1141, 23.1143, 23.1145, 23.1149, 23.1153, 23.1155, 23.1163, 23.1165, 23.1181, 23.1182, 23.1183, 23.1189, 23.1191, 23.1193, 23.1195, 223.1197, 23.1199, 23.1201, 23.1203; (5) Title 14 CFR part 23, subpart F, §§ 23.1301, 23.1303, 23.1305, (23.1307 if necessary to maintain original operating envelope and conditions), 23.1309, 23.1311, 23.1321, 23.1322, 23.1329, 23.1337, 23.1351, 23.1353, 23.1357, 23.1359, 23.1416, 23.1435, 23.1437, 23.1438; (6) Title 14 CFR part 23, subpart G, §§ 23.1501, 23.1505, 23.1513, 23.1521, 23.1527, 23.1529, 23.1541, 23.1543, 23.1545, 23.1549, 23.1551, 23.1555, 23.1557, 23.1581, 23.1583, 23.1585, 23.1587; (7) Title 14 CFR part 34; and (8) Title 14 CFR part 36.

AC 23-24T 8/24/05 15. What are the applicable regulations and guidance for the installation of turbine engines to replace reciprocating engines?

a. This change covers the replacement of reciprocating engines with gas turbine engines (turbopropeller, turbojet, or turbofan). Additional guidance for this may be found in AC 23-14.

The impact on the noise levels should be considered and accounted for per Title 14 CFR part 36.

Installations that involve the following changes may require additional substantiation and/or additional certification basis requirements that could exceed the scope of this AC.

(1) primary structure; (2) aerodynamics; (3) airspeeds; (4) mass distribution (may induce whirl mode, flutter, and fatigue life changes); (5) maximum weight; (6) system changes; (7) changes in center of gravity (c.g.) limits; or (8) power increases affecting high speed characteristics or airplane handling qualities.

b. Projects such as commuter category or restricted category airplanes will require a more detailed analysis to establish the appropriate certification basis. Installations that increase the gross weight of the airplane should refer to the gross weight increase compliance checklist for additional requirements.

c. The applicable regulations for the installation of a turbine engine to replace a reciprocating engine should include, but are not limited to, the following: (1) Title 14 CFR part 23, subpart B, §§ 23.25, 23.33, 23.45, 23.49, 23.65, 23.67, 23.77, 23.145, 23.149, 23.155, 23.161, 23.175, 23.177, 23.201, 23.203, 23.221 (except agricultural and twin engine airplanes), 23.231, 23.233, 23.239, 23.251, 23.253; (2) Title 14 CFR part 23, subpart C, §§ 23.301, 23.303, 23.305, 23.307, 23.331, 23.333, 23.337, 23.341, 23.335, 23.361, 23.363, 23.367, 23.371, 23.479, (23.572, 23.573, 23.574, 23.575 as required or if part of original certification basis); (3) Title 14 CFR part 23, subpart D, §§ 23.603, 23.627, 23.629, 23.735, 23.777, 23.781, 23.831, 23.863, 23.865; (4) Title 14 CFR part 23, subpart E, §§ 23.901, 23.903, 23.904, 23.905, 23.907, 23.925, 23.929, 23.933, 23.937, 23.939, 23.943, 23.951, 23.953, 23.955, 23.959, 23.961, 23.965, 23.973, 23.977, 23.991, 23.993, 23.994, 23.995, 23.997, 23.1011, 23.1013, 23.1015, 23.1017, 23.1019, 23.1021, 23.1023, 23.1027, 23.1041, 23.1043, 23.1045, 23.1091, 23.1093, 23.1103, 23.1111, 23.1121, 23.1123, 23.1141, 23.1143, 23.1145, 23.1149, 23.1153, 23.1155, 23.1163, 23.1165, 23.1181, 23.1182, 23.1183, 23.1189, 23.1191, 23.1193, 23.1203;

8/24/05 AC 23- 24T (5) Title 14 CFR part 23, subpart F, §§ 23.1301, 23.1303, 23.1305, 23.1307, 23.1309, 23.1321, 23.1322, 23.1329, 23.1337, 23.1351, 23.1353, 23.1357, 23.1359, 23.1435, 23.1438; (6) Title 14 CFR part 23, subpart G, §§ 23.1501, 23.1505, 23.1513, 23.1521, 23.1527, 23.1529, 23.1545, 23.1549, 23.1551, 23.1555, 23.1557, 23.1583, 23.1585, 23.1587; (7) Title 14 CFR part 34; and (8) Title 14 CFR part 36.

16. What are the applicable regulations and guidance for the installation of a different propeller (simple)?

a. A simple propeller change consists of replacing an originally certificated propeller with a different propeller that has the same diameter and number of blades as the original propeller.

The regulations listed in section 16.b. apply to single engine tractor configuration (Normal Category) airplanes only. The impact on the noise levels should be considered and accounted for per Title 14 CFR part 36. AC 20-66A provides additional guidance regarding propeller installation.

b. The applicable regulations for the installation of a different propeller (simple) should include, but are not limited to, the following: (1) Title 14 CFR part 23, subpart B, §§ 23.33, 23.53, 23.65, 23.71, 23.75, 23.77, 23.201, 23.251; (2) Title 14 CFR part 23, subpart C, §§ 23.301, 23.303, 23.305, 23.307, 23.361, 23.363, 23.371, (23.573, 23.574, 23.575 as required or if part of original certification basis); (3) Title 14 CFR part 23, subpart E, §§ 23.901, 23.905, 23.907, 23.925, 23.1041, 23.1043, 23.1045, 23.1047; (4) Title 14 CFR part 23, subpart G, §§ 23.1501, 23.1521, 23.1529, 23.1541, 23.1549, 23.1559, 23.1581, 23.1583, 23.1585, 23.1587; and (5) Title 14 CFR part 36.

AC 23-24T 8/24/05 17. What are the applicable regulations and guidance for the installation of a different propeller (complex)?

a. A complex propeller change consists of replacing an originally certificated propeller with a different propeller that has a different diameter and/or a different number of blades than the original propeller. The regulations listed in section 17.b. apply to single engine (Utility, Acrobatic, or Commuter Category) and twin-engine reciprocating and turbine airplanes only.

The impact on the noise levels should be considered and accounted for per Title 14 CFR part 36.

AC 20-66A provides additional guidance regarding propeller installation.

b. The applicable regulations for the installation of a different propeller (complex) should include, but are not limited to, the following: (1) Title 14 CFR part 23, subpart B, §§ 23.33, 23.45, 23.49, 23.51, 23.53, 23.55, 23.57, 23.59, 23.61, 23.63, 23.65, 23.66, 23.67, 23.69, 23.71, 23.73, 23.75, 23.77, 23.141, 23.143, 23.145, 23.147, 23.149, 23.151, 23.153, 23.155, 23.157, 23.161, 23.171, 23.173, 23.175, 23.177, 23.181, 23.201, 23.203, 23.207, 23.221 (except agricultural and twin engine airplanes), 23.231, 23.233, 23.235, 23.237, 23.239, 23.251, 23.253; (2) Title 14 CFR part 23, subpart C, §§ 23.301, 23.303, 23.305, 23.307, 23.321, 23.331, 23.333, 23.335, 23.337, 23.341, 23.347, 23.349, 23.351, 23.361, 23.363, 23.367, 23.371, 23.391, 23.393, 23.395, 23.397, 23.399, 23.405, 23.407, 23.409, 23.415, 23.421, 23.423, 23.425, 23.427, 23.441, 23.443, 23.445, 23.455, 23.459, 23.571, (23.573, 23.574, 23.575 as required or if part of original certification basis); (3) Title 14 CFR part 23, subpart D, §§ 23.629, 23.671, 23.672, 23.673, 23.675, 23.677, 23.679, 23.681, 23.683, 23.685, 23.687, 23.689, 23.691, 23.693, 23.697, 23.699, 23.701, 23.703, 23.721, 23.723, 23.725, 23.726, 23.727, 23.729, 23.731, 23.733, 23.735, 23.737, 23.745, 23.751, 23.753, 23.755, 23.757, 23.771, 23.773, 23.775, 23.777, 23.779, 23.781, 23.783, 23.785, 23.787, 23.791, 23.803, 23.805, 23.807, 23.811, 23.812, 23.813, 23.815, 23.831, 23.841, 23.843, 23.851, 23.853, 23.855, 23.859, 23.863, 23.865, 23.867, 23.871; (4) Title 14 CFR part 23, subpart E, §§ 23.901, 23.905, 23.907, 23.925, 23.929, 23.933, 23.934, 23.937, 23.939, 23.943, 23.1027, 23.1041, 23.1043, 23.1045, 23.1047, 23.1091, 23.1093, 23.1121, 23.1149, 23.1153, 23.1155; (5) Title 14 CFR part 23, subpart G, §§ 23.1501, 23.1505, 23.1507, 23.1511, 23.1513, 23.1519, 23.1521, 23.1529, 23.1541, 23.1543, 23.1545, 23.1549, 23.1555, 23.1559, 23.1583, 23.1585, 23.1587; and (6) Title 14 CFR part 36.

8/24/05 AC 23- 24T 18. What are the applicable regulations and guidance for the installation of auxiliary fuel tanks?

a. AC 23-10 provides additional guidance and criteria for the installation of auxiliary fuel tanks. These installations may increase the gross weight of the airplane in which case the applicant should refer to the gross weight increase compliance checklist for additional requirements.

b. Performing spin recovery tests with a limited spin matrix should be considered if the change to the airplane causes a weight and/or a rotational inertia increase of greater than 10%.

c. The applicable regulations for the installation of auxiliary fuel tanks should include, but are not limited to, the following: (1) Title 14 CFR part 23, subpart B, §§ 23.23, 23.25, 23.29, 23.147, 23.251, 23.157, 23.177, 23.181, 23.201, 23.203, 23.221 (except agricultural and twin engine airplanes); (2) Title 14 CFR part 23, subpart C, §§ 23.301, 23.303, 23.305, 23.307, 23.321, 23.331, 23.333, 23.335, 23.337, 23.341, 23.343, 23.471, 23.473, 23.479, 23.485, 23.561, 23.571, 23.572, (23.573, 23.574, 23.575 as required or if part of original certification basis); (3) Title 14 CFR part 23, subpart D, §§ 23.601, 23.603, 23.605, 23.607, 23.609, 23.611, 23.613, 23.619, 23.623, 23.625, 23.627, 23.629, 23.777, 23.787, 23.843, 23.853, 23.863, 23.867; (4) Title 14 CFR part 23, subpart E, §§ 23.901, 23.903, 23.951, 23.953, 23.954, 23.955, 23.957, 23.959, 23.961, 23.963, 23.965, 23.967, 23.969, 23.971, 23.973, 23.975, 23.977, 23.991, 23.993, 23.994, 23.995, 23.997, 23.999, 23.1001, 23.1011, 23.1183, 23.1189; (5) Title 14 CFR part 23, subpart F, §§ 23.1301, 23.1305, 23.1309, 23.1337, 23.1351, 23.1357; (6) Title 14 CFR part 23, subpart G, §§ 23.1501, 23.1505, 23.1507, 23.1511, 23.1513, 23.1519, 23.1521, 23.1522, 23.1523, 23.1524, 23.1525, 23.1527, 23.1529, 23.1541, 23.1543, 23.1549, 23.1553, 23.1555, 23.1557, 23.1581, 23.1583, 23.1585, 23.1589; and (7) Title 14 CFR part 36 if the auxiliary tanks are externally mounted or there is a change to the airplane performance.

19. What are the applicable regulations and guidance to increase the airplane gross weight?

a. Many changes may cause an increase in the airplane gross weight. In many cases, due to changes in the operational requirements of an owner/operator, the need arises to modify and

AC 23-24T 8/24/05 substantiate the structure for an increase in maximum takeoff weight, in maximum landing weight, or in maximum zero fuel weight.

b. An increase in maximum gross weight is in general a large effort, as it requires a complete review of all aspects of the aircraft design. When an airplane is initially designed, the manufacturer determines the gross weight through a process of compromise with the desired performance features. Once the gross weight is fixed, the details of the aircraft are designed around that weight. This means that the basic loads for the aircraft are determined using that weight, then the control surfaces and wing area are sized for those loads, and the size of the primary structure is determined using the same loads. Most manufacturers over estimate the weight by a small percentage to allow for future growth and unforeseen weight increases. This margin may be used in some cases to allow a small gross weight increase without changing the primary structure, but the applicant must be familiar with all the analysis to determine how much margin exists in the design. It must be kept in mind that this margin may exist to mitigate fatigue and airframe longevity. Gross weight changes that do not involve using this margin in the airframe will require a complete re-analysis of the airplane to determine the effect on basic loads, performance, and primary structural strength.

c. A common misconception is that since an airplane has operated over gross weight and seems to fly fine, the airplane is good for that weight, and should be granted an approval for increased gross weight. The nature of aircraft design is that many airplanes have the capability to takeoff and fly well in excess of their allowable gross weight under the right conditions.

However, the airplane will no longer be able to perform in its entire certificated performance envelope. This results in a lower service ceiling, decreased takeoff and climb performance, increased landing distance, a decreased ability to withstand the design g-loads without deformation, and a decrease in fatigue life of the airframe that could result in early structural cracking and possible failure. In the end, this airplane no longer meets the requirements of 14 CFR part 23, and is less safe than the original design even though it seems to fly fine.

d. The need for a limited spin matrix on an STC program is a subjective decision based on the service history of the specific airplane being modified. It is not possible to offer a comprehensive list of when to re-test the spin matrix because of the number of variables to consider. There are instances of airplanes with significant modifications that had little effect on spin recovery, and airplanes with subtle modifications that changed the spin recovery dramatically. If it is determined that the airplane does need to be re-evaluated for spin recovery, then a limited matrix using the middle and edges of the envelope is normally all that is needed to verify the airplane recovers. Using a limited spin matrix should be considered if the change to the airplane causes a weight and/or a rotational inertia increase of greater than 10%.

e. The applicable regulations to increase the airplane gross weight should include, but are not limited to, the following: (1) Title 14 CFR part 23, subpart B, §§ 23.21, 23.23, 23.25, 23.29, 23.45, 23.49, 23.51, 23.53, 23.55, 23.59, 23.63, 23.65, 23.66, 23.67, 23.69, 23.71, 23.73, 23.75, 23.77, 23.141, 23.143, 23.145, 23.147, 23.149, 23.151, 23.153, 23.155, 23.157, 23.161, 23.171, 23.173, 23.175, 8/24/05 AC 23- 24T (2) 23.177, 23.181, 23.201, 23.203, 23.207, 23.221 (except agricultural and twin engine airplanes), 23.231, 23.233, 23.235, 23.237, 23.239, 23.251, 23.253; (3) Title 14 CFR part 23, subpart C, §§ 23.301, 23.302, 23.303, 23.305, 23.307, 23.321, 23.331, 23.333, 23.335, 23.337, 23.341, 23.343, 23.345, 23.347, 23.349, 23.351, 23.369, 23.373, 23.391, 23.395, 23.397, 23.399, 23.405, 23.407, 23.409, 23.415, 23.421, 23.423, 23.425, 23.427, 23.441, 23.443, 23.445, 23.455, 23.459, 23.471, 23.473, 23.479, 23.481, 23.483, 23.485, 23.493, 23.497, 23.499, 23.505, 23.507, 23.509, 23.511, 23.521, 23.523, 23.525, 23.527, 23.529, 23.531, 23.533, 23.535, 23.537, 23.561, 23.562, 23.571, 23.572, 23.573, 23.574, 23.575; (4) Title 14 CFR part 23, subpart D, §§ 23.601, 23.603, 23.605, 23.607, 23.609, 23.611, 23.613, 23.619, 23.621, 23.623, 23.625, 23.627, 23.629, 23.641, 23.651, 23.657, 23.671, 23.672, 23.673, 23.677, 23.681, 23.683, 23.687, 23.689, 23.691, 23.693, 23.721, 23.723, 23.725, 23.726, 23.727, 23.731, 23.733, 23.735, (23.737 if part of type design), 23.751, 23.753, 23.755, 23.757; (5) Title 14 CFR part 23, subpart G, §§ 23.1501, 23.1505, 23.1507, 23.1511, 23.1513, 23.1519, 23.1521, 23.1527, 23.1529, 23.1541, 23.1557, 23.1563, 23.1567, 23.1581, 23.1583, 23.1585, 23.1587, 23.1589; and (6) Title 14 CFR part 36.

25 (and 26) 8/24/05 AC 23- 24T Appendix 1T APPENDIX 1 – STANDARD COMPLIANCE CHECKLIST A1T-1 (and A1-2) 8/24/05 AC 23-24 A p p endix 1 dix 1 Date: Multiple STC One-only STC Revision: Description of Change: Page ___ of ___

Supplemental Type Certificate Compliance Checklist

Originator: Make: Make: Model: TCDS #: Original Certification Basis: Proposed Certification Basis: Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable A1-1 A1-1 AC 23-24 8/24/05 A p p endix 1 ndix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & Date: AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ DE DE AN, FT AN, GT Method of Method of AN, GT, FT DE, AN, FT Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.71) (3.61, (CAR 3) (3.20 (less (3.74, 3.75) (3.0) (1964 CAR 3) (1964 CAR 3) Regulation Regulation GENERAL Subpart B -- Flight Subpart A -- General Originator: Proof of compliance. Load distribution limits. Weight limits.

Applicability. Special retroactive requirements. Airplane categories.

Title 14 CFR Title 14 CFR Title 14 CFR part 23: Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable Section 23.1 23.2 23.3 2nd sent. of (a)(2) and 2nd and 3rd sent. of (b)), 3.20-1, 3.20-2 (1st sent.) 23.21 3.71-1) 23.23 23.25 A1-2 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B AC 23-8B AC 23-8B AC 23-8B Date: AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT FT FT FT FT AN, FT AN, FT AN, FT AN, FT GT, FT AN, GT DE, AN Method of Method of AN, GT, FT Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.73 (3.72) (3.84 (less (c)), (3.82, 3.81-1, (1964 CAR 3) (1964 CAR 3) (3.81) Regulation Regulation PERFORMANCE Originator: Empty weight and Removable ballast. Propeller speed and pitch limits. General. Stalling period. Takeoff speeds. Takeoff performance. Accelerate-stop distance. Takeoff path. Takeoff distance and takeoff Takeoff flight path. Climb: General. Climb: All engines operating.

Title 14 CFR Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.29 corresponding center of gravity. (1st sent.), 3.73-3(b)) 23.31 23.33 (3.418, 3.419, 3.420, 3.421) 23.45 23.49 3.83) 23.51 3.84-2, 3.84a, 3.780(a) (1st sent.)) 23.53 23.55 23.57 23.59 run. 23.61 23.63 23.65 (3.85(a),3.85-5(b) (less (1) and (2)), 3.85a(a), 3.419-1 (a) (2nd sent.)) A1-3 A1-3 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B AC 23-8B Date: AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B, AC 23.143-1 AC 23-8B AC 23-8B Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT FT FT FT FT FT FT FT FT FT FT Method of Method of Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.109) (3.86(a), (3.85 (less (a) (1964 CAR 3) (1964 CAR 3) (3.105) (3.106) Regulation Regulation General. General. Longitudinal control. Directional and lateral control.

Originator: Takeoff climb: One-engine Climb: One engine inoperative. Enroute climb/descent. Glide: Single-engine airplanes. Reference landing approach Landing distance. Balked landing. MANEUVERABILITY Title 14 CFR Title 14 CFR CONTROLLABILITY AND FLIGHT CHARACTERISTICS Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.66 inoperative. 23.67 (3.85(b), 3.85-3, 3.85a(b)) 23.69 23.71 23.73 speed. 23.75 3.87, 3.780(a) (1st sent.)) 23.77 and (b)),3.85a (less (a) and (b))) 23.141 23.143 23.145 23.147 (3.110) A1-4 A1-4 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B AC 23-8B Date: AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT FT FT FT FT FT FT FT FT FT FT Method of Method of Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.107, (3.117) (3.115 (a)-(c)) (1964 CAR 3) (1964 CAR 3) (3.113) TRIM (3.112) Regulation Regulation STABILITY (3.118) Minimum control speed. Acrobatic maneuvers. Control during landings. Elevator control force in Rate of roll. Trim. General. Static longitudinal stability. Demonstration of static Static directional and lateral Dynamic stability.

Originator: Title 14 CFR Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.149 (3.111) 23.151 3.108) 23.153 23.155 maneuvers. 23.157 23.161 23.171 23.173 (3.114, 3.115 (less (a)-(c))) 23.175 longitudinal stability. 23.177 stability. 23.181 A1-5 A1-5 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & Date: AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT FT FT FT FT FT FT Method of Method of Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.120(a), (3.120(f)) pliance: (1964 CAR 3) (1964 CAR 3) (3.124(a) (less last STALLS (3.120(c), 3.120(d), Regulation Regulation SPINNING (3.146) (3.144) (3.145) Wings level stall. Turning flight and accelerated Stall warning. Spinning. Longitudinal stability and Directional stability and Operation on unpaved Originator: GROUND AND WATER Title 14 CFR Title 14 CFR HANDLING CHARACTERISTICS Project Number: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.201 3.120(b), 3.120 (less (a)-(f)), 3.120-1, 3.122 (2nd sent.)) 23.203 turning stalls. 3.120(e) (1st through 26th words), 3.121, 3.122 (less 2nd sent.)) 23.207 23.221 sent.), 3.124(b), 3.124(c) (less (4)), 3.124(d)) *Methods of Com 23.231 control. 23.233 control. 23.235 surfaces.

A1-6 A1-6 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B PS-ACE100-2002-008 AC 23-8B PS-ACE100-2004-10030 PS-ACE100-2004-10030 Date: AC 23-8B AC 23-8B, PS-ACE100-2001-004, AC 23-19 AC 23-19 AC 23-19 AC 23-19, PS-ACE100-2001-006, AC 23-19, PS-ACE100-2001-006, Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT FT FT FT AN, GT AN, GT AN, GT Method of Method of AN, GT, FT AN, GT, FT Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.147) (3.174) (3.172) (1964 CAR 3) (1964 CAR 3) (3.171,3.171-1) Regulation Regulation GENERAL REQUIREMENTS Operation on water. Spray characteristics. Vibration and buffeting. High speed characteristics. Loads. Canard or tandem wing Factor of safety. Strength and deformation. Proof of structure.

Originator: Subpart C -- Structure Title 14 CFR Title 14 CFR MISCELLANEOUS FLIGHT Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.237 23.239 23.251 (3.159) 23.253 23.301 23.302 configurations. 23.303 23.305 (3.173) 23.307 A1-7 A1-7 AC 23-24 8/24/05 Appendix 1 Remarks Applicable Guidance, References, & Date: AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 Revision: Person or Entity Finding Compliance Plan, Drawing, Report Number Page ___ of ___ AN AN AN AN AN AN, GT AN, GT AN, GT AN, GT AN, GT AN, GT AN, GT Method of AN, GT, FT Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Amendment (3.191(b)) (3.191(a) (3.188, (3.184) (3.190 and (3.185, (3.195) (1964 CAR 3) (3.181, 3.182) Regulation (3.191 (less (a) and (b))) FLIGHT LOADS General. Symmetrical flight conditions. Flight envelope. Design airspeeds. Limit maneuvering load (3.186) Gust loads factors. Design fuel loads. High lift devices. Unsymmetrical flight Rolling conditions. Yawing conditions. Engine torque. Side load on engine mount.

Originator: Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.321 23.331 (3.183, 3.189) 23.333 3.187, Figure 3-1) 23.335 23.337 factors. 23.341 3.188-1) 23.343 23.345 note, 3.190-1) 23.347 conditions. 23.349 and note) 23.351 23.361 23.363 (3.196) A1-8 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-19 AC 23-19 Date: AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ AN AN AN AN AN AN AN, GT AN, GT AN, GT AN, GT AN, GT AN, GT AN, GT Method of Method of Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.211) (3.231, (3.232) (3.213) (3.194 and (1964 CAR 3) (1964 CAR 3) (3.224) Regulation Regulation SYSTEM LOADS (3.212, 3.212-1, Figure 3-11) Pressurized cabin loads. Unsymmetrical loads due to Rear lift truss. Gyroscopic and aerodynamic Speed control devices. Control surface loads. Loads parallel to hinge line. Control system loads. Limit control forces and Dual control system. Secondary control system. Trim tab effects. Tabs.

Originator: Title 14 CFR Title 14 CFR CONTROL SURFACE AND Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.365 (3.197) 23.367 engine failure. 23.369 note) 23.371 loads. 23.373 23.391 23.393 23.395 3.231-1 (1st and 4th sent.), 3.231-2) 23.397 torques. 23.399 23.405 (3.234) 23.407 23.409 A1-9 A1-9 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & Date: AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ AN AN AN AN AN AN AN AN, GT Method of Method of Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.218) (3.216 (3.219 (3.215 and (3.217 and notes) (3.220) (1964 CAR 3) (1964 CAR 3) Regulation Regulation Ground gust conditions. Balancing loads. Maneuvering loads. Gust loads. Unsymmetrical loads. Maneuvering loads. Gust loads. Outboard fins or winglets.

Originator: VERTICAL SURFACES Title 14 CFR Title 14 CFR HORIZONTAL STABILIZING AND BALANCING SURFACES Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.415 (3.233, 3.233-1) 23.421 note) 23.423 and notes, 3.216-4 (a) and (b)) 23.425 23.427 23.441 and notes) 23.443 23.445 (3.221) A1-10 A1-10 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & Date: AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ AN AN AN, GT AN, GT AN, GT AN, GT AN, GT AN, GT AN, GT AN, GT Method of Method of Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.249) (3.225) (1964 CAR 3) (1964 CAR 3) (3.222(a), (b), and (3.241) DEVICES Regulation Regulation (3.85-4 (last sent.), GROUND LOADS Ailerons. Special devices. General. Ground load conditions and Landing gear arrangement. Level landing conditions. Tail down landing conditions. One-wheel landing conditions. Side load conditions. Braked roll conditions.

Originator: Title 14 CFR Title 14 CFR AILERONS AND SPECIAL Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.455 (e)) 23.459 23.471 23.473 assumptions. 3.242, 3.243) 23.477 (3.244) 23.479 (3.245, 3.245-1(b)) 23.481 (3.246) 23.483 (3.247) 23.485 23.493 (3.248) A1-11 A1-11 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-19 AC 23-19 AC 23-19 Date: AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-19 Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ AN AN AN AN AN AN AN AN AN AN AN, GT AN, GT Method of Method of Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.265, (1964 CAR 3) (1964 CAR 3) Regulation Regulation (3.253, 3.254, 3.255, (3.250, 3.251, 3.252) (3.257) WATER LOADS Supplementary conditions for Supplementary conditions for Supplementary conditions for Jacking loads. Towing loads. Ground load; unsymmetrical Water load conditions. Design weights and center of Application of loads. Hull and main float load Hull and main float landing Hull and main float takeoff Originator: Title 14 CFR Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.497 tail wheels. 23.499 nose wheels. 3.256) 23.505 skiplanes. 23.507 23.509 23.511 loads on multiple-wheel units. 23.521 3.265-1(a), 3.265-2) 23.523 gravity positions. 23.525 23.527 factors. 23.529 conditions. 23.531 condition.

A1-12 A1-12 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-19 AC 23-19 Date: AC 23-19 AC 23-19 AC 23-19, AC 23.562-1 AC 23-19 AC 23-19 AC 23-19, PS-ACE100-2001-006 AC 23-19 Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ DE AN AN AN, GT AN, GT AN, GT AN, GT AN, GT AN, GT AN, GT Method of Method of Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (1964 CAR 3) (1964 CAR 3) Regulation Regulation CONDITIONS (3.270) Hull and main float bottom Auxiliary float loads. Seawing loads. General. Emergency landing dynamic Metallic pressurized cabin Metallic wing, empennage, Damage tolerance and fatigue Metallic damage tolerance and Inspections and other Originator: Title 14 CFR Title 14 CFR EMERGENCY LANDING FATIGUE EVALUATION Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.533 pressures. 23.535 23.537 23.561 23.562 conditions. 23.571 structures. 23.572 and associated structures. 23.573 evaluation of structure. 23.574 fatigue evaluation of commuter category airplanes. 23.575 procedures.

A1-13 A1-13 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & PS-ACE100-2001-006, PS-ACE100-2004-10039 PS-ACE100-2001-006, PS-ACE100-2004-10039 AC 23-19, PS-ACE100-2002-006, PS-ACE100-2001-006, PS-ACE100-2004-100399 PS-ACE100-2004-10030 PS-ACE100-2001-006, PS-ACE100-2004-10030 Date: AC 23-19, PS-ACE100-2002-006, AC 23-19, PS-ACE100-2002-006, AC 23-19, AC 23.607-1 AC 23-19. PS-ACE100-2001-006, AC 23-19 AC 23-19, PS-ACE100-2002-006, AC 23-19 AC 23-19 AC 23-19 AC 23-19 Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ DE DE DE DE AN AN AN, GT AN, GT Method of Method of DE, AN, GT DE, AN, GT DE, AN, GT Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.293) (3.305) (3.304) (3.302, 3.303) (3.306) (1964 CAR 3) (1964 CAR 3) (3.294 (last sent.)) (3.301 and note) (3.291) Regulation Regulation Construction General. Materials and workmanship. Fabrication methods. Fasteners. Protection of structure. Accessibility provisions. Material strength properties Special factors. Casting factors. Bearing factors. Fitting factors.

Originator: Subpart D -- Design and Title 14 CFR Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.601 23.603 (3.292) 23.605 23.607 23.609 (3.295) 23.611 (3.296) 23.613 and design values. 23.619 23.621 23.623 23.625 A1-14 A1-14 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & PS-ACE100-2002-008 AC 23-19 AC 23-8B, AC 23-17B, PS-ACE100-2001-004 AC 23-8B, AC 23-17B, PS-ACE100-2001-004 Date: AC 23-19 AC 23-19, AC 23.629-1B, AC 23-19 AC 23-19 AC 23-19 AC 23-19 AC 23-17B AC 23-17B Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT FT DE AN AN AN AN AN, GT DE, AN Method of Method of AN, GT, FT DE, AN, FT DE, AN, GT, DE, AN, GT, Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.317) (3.327) (3.307) (3.330) (3.328) (1964 CAR 3) (1964 CAR 3) (3.335) (3.329) (3.311, 3.11-1, 3.311- WINGS Regulation Regulation Fatigue strength. Flutter. Proof of strength. Proof of strength. Installation. Hinges. Mass balance. General. Stability augmentation and Primary flight controls. Stops.

Originator: CONTROL SYSTEMS CONTROL SURFACES Title 14 CFR Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.627 23.629 2(a)) 23.641 23.651 23.655 23.657 23.659 23.671 23.672 automatic and power-operated systems. 23.673 (3.336) 23.675 A1-15 A1-15 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B, AC 23-17B, PS-ACE100-2001-004 PS-ACE100-2001-004 AC 23-8B, AC 23-17B AC 23-17B AC 23-8B, AC 23-17B AC 23-8B, AC 23-17B AC 23-8B, AC 23-17B AC 23-17B Date: AC 23-8B, AC 23-17B, AC 23-17B AC 23-17B AC 23-17B AC 23-17B AC 23-17B AC 23-17B AC 23-17B AC 23-17B AC 23-17B AC 23-17B Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ DE DE GT GT AN DE, GT GT, FT AN, FT DE, FT GT, FT DE, FT AN or FT AN or GT AN or GT AN or GT Method of Method of DE, AN, FT AN, GT, FT DE, AN, FT Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.337) (1964 CAR 3) (1964 CAR 3) Regulation Regulation LANDING GEAR Trim systems. Control system locks. Limit load static tests. Operation tests. Control system details. Spring devices. Cable systems. Artificial stall barrier system. Joints. Wing flap controls. Wing flap position indicator. Flap interconnection. Takeoff warning system. General. Shock absorption tests. Limit drop tests. Ground load dynamic tests. Reserve energy absorption Originator: Title 14 CFR Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.677 23.679 23.681 23.683 23.685 23.687 23.689 23.691 23.693 23.697 23.699 23.701 23.703 23.721 23.723 23.725 23.726 23.727 drop test.

A1-16 A1-16 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B, AC 23-17B AC 23-17B AC 23-8B, AC 23-17B AC 23-17B AC 23-17B AC 23-17B AC 23-8B, AC 23-17B, AC 23-1311-1A, PS-ACE100-2001-004 AC 23-8B, AC 23-17B, AC 23-1311-1A, PS-ACE100-2001-004 AC 23-8B, AC 23-17B Date: AC 23-17B AC 23-17B AC 23-17B AC 23-17B Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT AN AN DE, FT GT, FT DE, GT DE, AN DE, AN DE, AN AN, GT DE, AN Method of Method of DE, AN, FT AN, GT, FT Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (1964 CAR 3) (1964 CAR 3) Regulation Regulation Landing gear extension and Wheels. Tires. Brakes. Skis. Nose/tail wheel steering. Main float buoyancy. Main float design. Hulls. Auxiliary floats. Pilot compartment. Pilot compartment view. Windshields and windows.

Originator: FLOATS AND HULLS ACCOMMODATIONS Title 14 CFR Title 14 CFR PERSONNEL AND CARGO Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.729 retraction system. 23.731 23.733 23.735 23.737 23.745 23.751 23.753 23.755 23.757 23.771 23.773 23.775 A1-17 A1-17 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B, AC 23-17B, AC 23-1311-1A, PS-ACE100-2001-004 PS-ACE100-2001-004 AC 23-8B, AC 23-17B AC 23-8B, AC 23-17B AC 23-17B AC 23-17B AC 23-8B, AC 23-17B Date: AC 23-17B AC 23-17B AC 23-17B AC 23-8B, AC 23-17B, AC 23-17B AC 23-17B AC 23-17B AC 23-17B AC 23-17B Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ DE GT DE DE, FT DE, FT DE, GT DE, GT DE, AN DE, AN DE, AN Method of Method of AN, GT, FT DE, AN, GT DE, AN, GT DE, AN, GT DE, AN, GT Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.390, (3.393) (1964 CAR 3) (1964 CAR 3) (3.389) (3.392) Regulation Regulation (Figure 3-14) Cockpit controls. Motion and effect of cockpit Cockpit control knob shape. Doors. Seats, berths, litters, safety Baggage and cargo Passenger information signs. Emergency evacuation. Flightcrew emergency exits. Emergency exits. Emergency exit marking. Emergency lighting. Emergency exit access. Width of aisle. Ventilation.

Originator: Title 14 CFR Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.777 23.779 controls. 23.781 (Figure 3-13) 23.783 23.785 belts, and shoulder harnesses. 3.390-2) 23.787 compartments. 23.791 23.803 23.805 23.807 23.811 23.812 23.813 23.815 23.831 A1-18 A1-18 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B, AC 23-17B AC 23-8B, AC 23-17B AC 23-17B PS-ACE100-2004-10023, PS-ACE100-2004-10030 AC 23-17B Date: AC 23-2, AC 23-17B, AC 23-2, AC 23-17B AC 23-17B AC 23-17B Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ DE GT GT, FT DE, GT AN, GT Method of Method of DE, AN, GT DE, AN, GT DE, AN, GT Compliance* Compliance* DE and AN or

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.396) (3.395) (1964 CAR 3) (1964 CAR 3) Regulation Regulation PRESSURIZATION Pressurized cabins. Pressurization tests. Fire extinguishers. Passenger and crew Cargo and baggage Combustion heater fire Flammable fluid fire Fire protection of flight FIRE PROTECTION Originator: Title 14 CFR Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.841 23.843 23.851 23.853 compartment interiors. 23.855 compartment fire protection. 23.859 protection. 23.863 protection. 23.865 controls, engine mounts, and other flight structure.

A1-19 A1-19 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-17B, PS-ACE100-2004-10030 AC 23-8B, AC 23-16A, AC 20-136 AC 23-8B, AC 23-16A AC 23-8B, AC 23-16A Date: AC 23-17B AC 23-8B, AC 23-16A, AC 20-136, AC 23-1311-1A AC 23-16A AC 23-16A Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT FT FT DE DE, GT Method of Method of AN, GT, FT AN, GT, FT AN, GT, FT DE, AN, GT, DE, AN, GT, DE, AN, GT, Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.417) (3.401) (3.411) (3.416) (1964 CAR 3) (1964 CAR 3) (3.415) Regulation Regulation GENERAL MISCELLANEOUS Electrical bonding and Leveling means. Installation. Engines. Automatic power reserve Propellers. Propeller vibration. Turbocharger systems.

Originator: Subpart E -- Powerplant Title 14 CFR Title 14 CFR LIGHTNING PROTECTION ELECTRICAL BONDING AND Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.867 protection against lightning and static electricity. 23.871 23.901 23.903 23.904 system. 23.905 23.907 23.909 A1-20 A1-20 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B, AC 23-16A AC 23-8B, AC 23-16A AC 23-8B, AC 23-16A AC 23-8B, AC 23-16A AC 23-8B, AC 23-16A AC 23-16A, AC 20-53A, AC 20-136 Date: AC 23-16A AC 23-16A AC 23-16A AC 23-16A AC 23-16A AC 23-16A Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT AN AN, GT DE, AN Method of Method of AN, GT, FT AN, GT, FT AN, GT, FT AN, GT, FT AN, GT, FT AN, GT, FT DE, AN, GT DE, AN, GT Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.422, (1964 CAR 3) (1964 CAR 3) (3.433, 3.434, (3.429, 3.430) Regulation Regulation FUEL SYSTEM Propeller clearance. Engine installation ice Reversing systems. Turbojet and turbofan engine Turbopropeller-drag limiting Powerplant operating Negative acceleration. General. Fuel system independence. Fuel system lightning Fuel flow. Flow between interconnected Originator: (3.439) Title 14 CFR Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.925 3.422-2) 23.929 protection. 23.933 23.934 thrust reverser systems tests. 23.937 systems. 23.939 characteristics. 23.943 23.951 23.953 (3.431) 23.954 protection. 23.955 3.435, 3.436) 23.957 tanks.

A1-21 A1-21 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B, AC 23-16A AC 23-8B, AC 23-16A AC 23-16A AC 23-16A AC 23-16A AC 23-16A AC 23-16A Date: AC 23-16A AC 23-16A AC 23-16A AC 23-16A AC 23-16A Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT FT FT DE, GT AN, GT DE, AN DE, AN DE, AN DE, AN DE, AN Method of Method of AN, GT, FT DE, AN, GT DE, AN, GT, DE, AN, GT, DE, AN, GT, Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.442, (3.440 (3.448) (3.444) (3.441) (3.449, 3.449-1) (1964 CAR 3) (1964 CAR 3) Regulation Regulation (3.446, 3.447A) (3.438) Unusable fuel supply. Fuel system hot weather Fuel tanks: General. Fuel tank tests. Fuel tank installation. Fuel tank expansion space. Fuel tank sump. Fuel tank filler connection. Fuel tank vents and carburetor Fuel tank outlet. Pressure fueling systems. Fuel pumps.

Originator: Title 14 CFR Title 14 CFR FUEL SYSTEM COMPONENTS Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.959 (3.437(a) (less last sent.), 3.437 (less (a))) 23.961 operation. 23.963 (less last two sent.)) 23.965 23.967 3.442-1) 23.969 (3.443) 23.971 23.973 (3.445) 23.975 vapor vents. 23.977 23.979 23.991 A1-22 A1-22 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-16A AC 23-8B, AC 23-16A AC 23-16A AC 23-16A AC 23-8B, AC 23-16A Date: AC 23-16A AC 23-16A AC 23-16A AC 23-16A AC 23-2, AC 23-16A AC 23-16A AC 23-16A AC 23-16A AC 23-16A Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT FT GT DE, GT DE, AN AN, GT AN, GT AN, GT Method of Method of DE, AN, FT AN, GT, FT DE, AN, GT DE, AN, GT DE, AN, GT DE, AN, GT DE, AN, GT, DE, AN, GT, Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.570, (3.552) (3.573) (3.553) (3.574) (3.564) (3.572) (3.563, 3.565, (1964 CAR 3) (1964 CAR 3) (3.561, 3.561-1(b)) Regulation Regulation OIL SYSTEM Fuel jettisoning system. General. Oil tanks. Oil tank tests. Oil lines and fittings. Oil strainer or filter. Oil system drains. Oil radiators. Propeller feathering system.

Fuel system lines and fittings. Fuel system components. Fuel valves and controls. Fuel strainer or filter. Fuel system drains.

Originator: Title 14 CFR Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.993 (3.550) 23.994 23.995 (3.551, 3.633) 23.997 23.999 23.1001 23.1011 23.1013 3.566, 3.567, 3.568, 3.569) 23.1015 23.1017 3.575) 23.1019 23.1021 23.1023 23.1027 (3.577) A1-23 A1-23 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B, AC 23-16A AC 23-8B, AC 23-16A AC 23-8B, AC 23-16A AC 23-8B, AC 23-16A AC 23-16A AC 23-2, AC 23-8B, AC 23-16A Date: AC 23-16A Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT DE, AN AN, GT Method of Method of AN, GT, FT AN, GT, FT AN, GT, FT AN, GT, FT DE, AN, GT, Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.590) (3.582, 3.582- (3.588. 3.589, (1964 CAR 3) (1964 CAR 3) (3.581) Regulation Regulation COOLING General. Cooling tests. Cooling test procedures for Cooling test procedures for Installation. Coolant tank tests. Air induction system.

LIQUID COOLING Originator: INDUCTION SYSTEM Title 14 CFR Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.1041 23.1043 1, 3.583, 3.583-1 (1st sent.), 3.584, 3.585) 23.1045 turbine engine powered airplanes. (3.586) 23.1047 reciprocating engine powered airplanes. (3.587) 23.1061 3.591, 3.592, 3.593, 3.594, 3.595) 23.1063 23.1091 (3.605) A1-24 A1-24 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B, AC 23-16A AC 23-16A AC 23-16A AC 23-16A AC 23-16A AC 23-16A AC 23-16A AC 23-16A Date: AC 23-16A AC 23-16A AC 23-16A Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT FT GT, FT AN, GT DE, AN DE, AN DE, AN DE, AN DE, AN Method of Method of DE, SI, AN, DE, AN, GT DE, AN, GT DE, AN, GT, DE, AN, GT, Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.609) (1964 CAR 3) (1964 CAR 3) (3.615) (3.608) Regulation Regulation (3.606) Induction system icing Carburetor deicing fluid flow Carburetor deicing fluid Carburetor deicing fluid Induction air preheater Induction system ducts. Induction system screens. Induction system filters. Turbocharger bleed air Turbine engine bleed air General.

(3.610) EXHAUST SYSTEM Originator: Title 14 CFR Title 14 CFR (3.607) Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.1093 protection. 23.1095 rate. 23.1097 system capacity. 23.1099 system detail design. 23.1101 design. 23.1103 (3.611) 23.1105 (3.612) 23.1107 23.1109 system. 23.1111 system. 23.1121 A1-25 A1-25 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-16A AC 23-8B, AC 23-16A AC 23-16A AC 23-8B, AC 23-16A AC 23-16A AC 23-8B, AC 23-16A AC 23-16A Date: AC 23-16A AC 23-16A AC 23-16A AC 23-16A Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT FT FT FT FT FT FT DE, AN AN, GT Method of Method of DE, AN, FT DE, AN, FT DE, AN, GT, DE, AN, GT, DE, AN, GT, DE, AN, GT, DE, AN, GT, DE, AN, GT, DE, AN, GT, Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.629) (3.630) (3.628) (3.616) pliance: (1964 CAR 3) (1964 CAR 3) Regulation Regulation ACCESSORIES Exhaust system. Exhaust heat exchangers. Powerplant controls: General. Auxiliary power unit Engine controls. Ignition switches. Mixture controls. Propeller speed and pitch (3.631) Propeller feathering controls. Turbine engine reverse thrust Carburetor air temperature (3.634) Originator: Title 14 CFR Title 14 CFR POWERPLANT CONTROLS AND Project Number: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.1123 23.1125 (3.617, 3.618) *Methods of Com 23.1141 (3.627) 23.1142 controls. 23.1143 23.1145 23.1147 23.1149 controls. 23.1153 (3.632) 23.1155 and propeller pitch settings below the flight regime. 23.1157 controls.

A1-26 A1-26 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-16A AC 23-16A AC 23-16A AC 23-16A Date: AC 23-16A AC 23-16A AC 23-2, AC 23-16A AC 23-2, AC 23-8B, AC 23-16A AC 23-2, AC 23-16A AC 23-2, AC 23-16A AC 23-2, AC 23-16A Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT DE DE, AN Method of Method of AN, GT, FT DE, AN, GT DE, AN, GT DE, AN, GT DE, AN, GT DE, AN, GT DE, AN, GT DE, AN, GT DE, AN, GT, Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.625) (3.637) (3.623, 3.623-1, (1964 CAR 3) (1964 CAR 3) Regulation Regulation (3.638) PROTECTION Powerplant accessories. Engine ignition systems. Designated fire zones; Nacelle areas behind Lines, fittings, and Shutoff means. Firewalls. Engine accessory Cowling and nacelle. Fire extinguishing systems. Fire extinguishing agents.

Originator: POWERPLANT FIRE Title 14 CFR Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.1163 (3.635) 23.1165 (3.636) 23.1181 regions included. 23.1182 firewalls. 23.1183 components. 23.1189 23.1191 3.624) 23.1192 compartment diaphragm. 23.1193 23.1195 23.1197 A1-27 A1-27 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-16A AC 23-8B, AC 23-17B, AC 23.1311-1A, PS-ACE100-2001-004 AC 23-8B, AC 23-17B, AC 23.1311-1A AC 23-8B, AC 23-17B AC 23.1309-1C, AC 23.1311-1A, AC 20-136, PS-ACE100-2001-004 Date: AC 23-16A AC 23-16A AC 23-8B, AC 23-17B AC 23-8B, AC 23-17B, Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT FT DE DE, AN Method of Method of DE, GT, FT AN, GT, FT DE, AN, GT DE, AN, GT DE, AN, GT, DE, AN, GT, Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (1964 CAR 3) (1964 CAR 3) Regulation Regulation GENERAL (3.655(a)) Extinguishing agent Fire extinguishing systems Fire detector system. Function and installation. Flight and navigation Powerplant instruments. Miscellaneous equipment. Equipment, systems, and Originator: Subpart F -- Equipment Title 14 CFR Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.1199 containers. 23.1201 materials. 23.1203 23.1301 (3.651 (less 1st sent.), 3.652, 3.652-1) 23.1303 instruments. 23.1305 (3.655(b)) 23.1307 (3.655(d)(1), 3.655 (less (a), (b), and (d))) 23.1309 installations.

A1-28 A1-28 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B, AC 23-17B, AC 23.1311-1A, PS-ACE100-2001-004 AC 23.1311-1A, PS-ACE100-2001-004 AC 23.1311-1A, PS-ACE100-2001-004 AC 23.1311-1A AC 23-8B, AC 23-17B, PS-ACE100-2002-007 AC 23-8B, AC 23-17B AC 23-8B, AC 23-17B, AC 23.1311-1A AC 23.1311-1A Date: AC 23-8B, AC 23-17B, AC 23-8B, AC 23-17B, AC 23-8B, AC 23-17B, AC 23-8B, AC 23-17B AC 23-8B, AC 23-17B AC 23-8B, AC 23-17B, Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT FT GT, FT Method of Method of DE, GT, FT DE, GT, FT DE, GT, FT DE, GT, FT DE, GT, FT DE, GT, FT DE, GT, FT DE, AN, GT, DE, AN, GT, Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (1964 CAR 3) (1964 CAR 3) Regulation Regulation Electronic display instrument Arrangement and visibility. Warning, caution, and Airspeed indicating system. Static pressure system. Pitot heat indication systems. Magnetic direction indicator. Automatic pilot system. Instruments using a power Flight director systems.

(3.668) Originator: Title 14 CFR Title 14 CFR INSTRUMENTS: INSTALLATION Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.1311 systems. 23.1321 (3.661, 3.662) 23.1322 advisory lights. 23.1323 (3.663) 23.1325 (3.665) 23.1326 23.1327 (3.666) 23.1329 (3.667) 23.1331 source. 23.1335 (3.669) A1-29 A1-29 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23.1311-1A AC 23-8B, AC 23-17B, AC 23.1311-1A AC 23.1311-1A AC 23-8B, AC 23-17B, AC 23.1311-1A, PS-ACE100-2001-004 AC 23.1311-1A, PS-ACE100-2004-10023 AC 23.1311-1A AC 23.1311-1A AC 23.1311-1A, PS-ACE100-2001-004 Date: AC 23-8B, AC 23-17B, AC 23-8B, AC 23-17B, AC 23-8B, AC 23-17B, AC 23-8B, AC 23-17B, AC 23-8B, AC 23-17B, AC 23-8B, AC 23-17B, Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ DE, GT DE, GT AN, GT or GT, FT Method of Method of DE, GT, FT AN, GT, FT DE, AN, FT DE, AN, GT (DE and AN) Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.694, 3.695) (1964 CAR 3) (1964 CAR 3) (3.681, 3.682, Regulation Regulation (3.671, 3.672, 3.672-1, (3.683) (3.693) EQUIPMENT Powerplant instruments General. Storage battery design and Circuit protective devices. Electrical system fire Master switch arrangement. Electric cables and Switches.

Originator: Title 14 CFR Title 14 CFR ELECTRICAL SYSTEMS AND Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.1337 installation. 3.673, 3.674, 3.675) 23.1351 3.685, 3.686, 3.687) 23.1353 installation. 23.1357 (3.690, 3.691, 3.692) 23.1359 protection. 23.1361 (3.688, 3.689) 23.1365 equipment. 23.1367 A1-30 A1-30 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23.1311-1A, PS-ACE100-2001-004 AC 23-8B, AC 23-17B AC 23-17B, AC 20-74 Date: AC 23-8B, AC 23-17B, AC 23-17B, AC 20-74 AC 23-17B, AC 20-7 AC 23-17B AC 23-17B AC 23-17B AC 23-17B AC 23-17B AC 23-17B Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT GT GT DE, FT DE, GT DE, GT DE, GT Method of Method of DE, GT, FT DE, AN, GT DE, AN, GT DE, AN, GT DE, AN, GT, Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.703) (3.696, (3.704) (1964 CAR 3) (1964 CAR 3) LIGHTS Regulation Regulation (3.700) (3.702, 3.702-1, 3.702-2) Instrument lights. Taxi and landing lights. Position light system Position light system dihedral Position light distribution and Minimum intensities in the Minimum intensities in any Maximum intensities in Color specifications. Riding light. Anticollision light system.

(3.701) Originator: Title 14 CFR Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.1381 3.696-1, 3.697) 23.1383 (3.698, 3.699) 23.1385 installation. 23.1387 angles. 23.1389 intensities. 23.1391 horizontal plane of position lights. (Figure 3-15) 23.1393 vertical plane of position lights. (Figure 3-16) 23.1395 overlapping beams of position lights. (Figure 3-17) 23.1397 23.1399 23.1401 (3.705, 3.705-1 (1st sent.), Figure 3-18) A1-31 A1-31 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B, AC 23-17B AC 23-8B, AC 23-17B AC 23.1419-2C, AC 20-73, AC 23.143-1 AC 23-8B, AC 23-17B, AC 23.1419-2C, AC 20-73, AC 23.143-1 The analysis and tests to be conducted must be specified. An exemption ma y be required for stall speed in icing. AC 23.1311-1A, AC 20-136, PS-ACE100-2001-004 Date: AC 23-8B, AC 23-17B, AC 23-8B, AC 23-17B, AC 23-8B, AC 23-17B AC 23-17B Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ DE DE DE, GT DE, GT GT, FT, PExmpt AN, GT Method of Method of DE, SI, AN, AN, GT, FT Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.716, (3.726, (3.712) pliance: (1964 CAR 3) (1964 CAR 3) (3.711 (1st through Regulation Regulation (3.725) General. Ditching equipment. Pneumatic de-icer boot Ice protection. Electronic equipment. Hydraulic systems. Accessories for multiengine Originator: SAFETY EQUIPMENT Title 14 CFR Title 14 CFR MISCELLANEOUS EQUIPMENT Project Number: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable *Methods of Com 23.1411 27th words)) 23.1415 3.717, 3.718) 23.1416 system. 23.1419 23.1431 (3.721) 23.1435 3.727, 3.728) 23.1437 airplanes.

A1-32 A1-32 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-17B AC 23-8B, AC 23-17B AC 23-8B, AC 23-17B AC 23-17B AC 23-8B, AC 23-17B AC 23-8B, AC 23-17B Date: AC 23-17B AC 23-17B AC 23-8B, AC 23-17B AC 23-17B AC 23-17B AC 23-17B AC 23-8B, AC 23.1311-1A Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ DE DE DE DE DE AN DE, GT DE, FT AN, GT AN or GT Method of Method of DE, GT, FT DE, GT, FT DE, GT, FT Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (1964 CAR 3) (1964 CAR 3) (3.735, 3.737) Regulation Regulation and Information Pressurization and pneumatic Oxygen equipment and Minimum mass flow of Oxygen distribution system. Equipment standards for Means for determining use of Chemical oxygen generators. Fire protection for oxygen Protection of oxygen Cockpit voice recorders. Flight recorders. Equipment containing high General.

Originator: Title 14 CFR Title 14 CFR Subpart G -- Operating Limitations Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.1438 systems. 23.1441 supply. 23.1443 supplemental oxygen. 23.1445 23.1447 oxygen dispensing units. 23.1449 oxygen. 23.1450 23.1451 equipment. 23.1453 equipment from rupture. 23.1457 23.1459 23.1461 energy rotors. 23.1501 A1-33 A1-33 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B, AC 23.1523, PS-ACE100-2001-004 AC 23-8B AC 23.1311-1A Date: AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B AC 23-8B Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ FT DE, FT DE, FT DE, FT DE, FT DE, FT DE, FT DE, FT DE, FT DE, FT DE, FT DE, FT Method of Method of DE, AN, GT, Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.738, (3.742) (3.750) (1964 CAR 3) (1964 CAR 3) Regulation Regulation Airspeed limitations. Operating maneuvering Flap extended speed. Minimum control speed. Weight and center of gravity. Powerplant limitations. Auxiliary power unit Minimum flight crew. Maximum passenger seating Kinds of operation. Maximum operating altitude. Instructions for Continued Originator: (3.741) Title 14 CFR Title 14 CFR Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.1505 3.739, 3.740) 23.1507 speed. 23.1511 23.1513 (3.743) 23.1519 (3.748) 23.1521 (3.744) 23.1522 limitations. 23.1523 (3.749) 23.1524 configuration. 23.1525 23.1527 23.1529 Airworthiness.

A1-34 A1-34 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & AC 23-8B, AC 23.1311-1A, AC 20-88A AC 23-8B, AC 23.1311-1A, AC 20-88A AC 23-8B, AC 23.1311-1A, AC 20-88A AC 23-8B, AC 23.1311-1A, PS-ACE100-2001-004 AC 23-8B Date: AC 23-8B, AC 23.1311-1A AC 23-8B AC 23-8B, AC 23.1311-1A AC 23-8B, AC 23.1311-1A AC 23-8B AC 23-8B, AC 23.1311-1A AC 23-8B AC 23-8B Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ DE, FT DE, FT DE, FT DE, FT DE, FT DE, FT DE, FT DE, FT DE, FT DE, FT DE, FT DE, FT DE, FT Method of Method of Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.757) (3.771) (3.762, (3.759) (1964 CAR 3) (1964 CAR 3) (3.755) Regulation Regulation (3.766, 3.767, 3.768, 3.769) General. Instrument markings: Airspeed indicator. Magnetic direction indicator. Powerplant and auxiliary Oil quantity indicator. Fuel quantity indicator. Control markings. Miscellaneous markings and Operating limitations placard. Safety equipment. Airspeed placards. Flight maneuver placard.

(3.756) Originator: Title 14 CFR Title 14 CFR MARKINGS AND PLACARDS Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.1541 23.1543 General. 23.1545 23.1547 (3.758) 23.1549 power unit instruments. 23.1551 (3.760) 23.1553 (3.761 (less 49th through 85th words)) 23.1555 3.762-1, 3.763, 3.764, 3.765) 23.1557 placards. 23.1559 (3.770, 3.772) 23.1561 23.1563 23.1567 A1-35 A1-35 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & Date: AC 23-8B, AC 23.1311-1A AC 23-8B, AC 23.1311-1A AC 23-8B AC 23-8B AC 23-8B Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ DE, FT DE, FT DE, FT DE, FT DE, FT Method of Method of Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.73-3 (1964 CAR 3) (1964 CAR 3) (3.777) Regulation Regulation MATERIAL General. Operating limitations. Operating procedures. Performance information. Loading information.

Originator: Title 14 CFR Title 14 CFR AND APPROVED MANUAL AIRPLANE FLIGHT MANUAL Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable 23.1581 23.1583 (3.124(a) (last sentence), 3.124(c)(4), 3.761 (49th through 85th words), 3.778) 23.1585 (3.779) 23.1587 (3.84(c), 3.86(b), 3.120(e) (less 1st through 26th words), 3.123(b) (less (1) and (2)), 3.437(a) (last sent.), 3.440 (next to last sent.), 3.780, 3.780(b) (1st sent.)) 23.1589 (less (a) and (b)), 3.76) Appendix A to Part 23 -- Simplified Design Load Criteria A1-36 A1-36 8/24/05 AC 23-24 AC 23-24 Appendix 1 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & Date: Revision: Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ Method of Method of Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (3.245-1(b) (1964 CAR 3) (1964 CAR 3) Regulation Regulation (Figures 3-12(a), 3-12(b)) SAFETY (ELOS): Originator: Title 14 CFR Title 14 CFR EQUIVALENT LEVELS OF Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable Appendix B to Part 23 [Reserved] (note following 3.211, Figures 3-3(a), 3-3(b), 3-4, 3-5(a), 3-5(b), 3-6, 3-7, 3- 8, 3-9, 3-10) Appendix C to Part 23 -- Basic Landing Conditions Appendix D to Part 23 -- Wheel Spin- Up and Spring-Back Loads (equation and following)) Appendix E to Part 23 [Reserved] Appendix F to Part 23 -- Test Procedure Appendix G to Part 23 -- Instructions for Continued Airworthiness Appendix H to Part 23 -- Installation of An Automatic Power Reserve (APR) System Appendix I to Part 23 -- Seaplane Loads ELOS for 23.xxx ELOS for 23.xxx A1-37 A1-37 AC 23-24 8/24/05 Appendix 1 Remarks Remarks Applicable Guidance, References, & Applicable Guidance, References, & Date: AC 36-4C AC 36-4C Revision: FAA only FAA only FAA only Person or Entity Person or Entity Finding Compliance Finding Compliance Plan, Drawing, Plan, Drawing, Report Number Report Number Page ___ of ___ N/A AN, FT AN, FT Method of Method of Compliance* Compliance*

Supplemental Type Certificate Compliance Checklist

Applicable Applicable Amendment Amendment (1964 CAR 3) (1964 CAR 3) Change] Regulation Regulation Originator: Title 14 CFR Title 14 CFR Piston Engine Turbine Engine (Reference 34.11) Title 14 CFR part 36: [No Acoustical Project Number: *Methods of Compliance: FT = Flight Test, GT = Ground Test, AN = Analysis, DE = Design, SI = Similarity, ELOS = Equivalent Level of Safety Finding, PExmpt = Petition for Exemption, N/A = Not Applicable EXEMPTIONS: Exemption to 23.xxx Exemption to 23.xxx SPECIAL CONDITIONS: Special Condition 1 Special Condition 2 Title 14 CFR part 34: Title 14 CFR part 36: [Acoustical Change] A1-38 A1-38