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, 24
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)
24T Appendix 1T APPENDIX 1 – STANDARD COMPLIANCE CHECKLIST A1T-1 (and A1-2)
Supplemental Type Certificate Compliance Checklist Project Number: Date:
Originator: Revision:
*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 8/24/05 AC 23-24 Appendix 1 dix 1 Make: Make:
Model:
Description of Change: One-only STC Multiple STC TCDS #:
Original Certification Basis:
Proposed Certification Basis:
A1-1 A1-1 Page ___ of ___
Supplemental Type Certificate Compliance Checklist Project Number: Date:
Originator: Revision:
*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 A1-2 AC 23-24 8/24/05 Appendix 1 ndix 1
Regulation Regulation Title 14 CFR (1964 CAR 3) Title 14 CFR (1964 CAR 3) Applicable Amendment Applicable Amendment Method of Compliance* Method of Compliance* Plan, Drawing, Report Number Plan, Drawing, Report Number Person or Entity Finding Compliance Person or Entity Finding Compliance Applicable Guidance, References, & Remarks Applicable Guidance, References, & Remarks
Title 14 CFR part 23: (CAR 3)
Subpart A -- General
Section
23.1 Applicability. (3.0) DE AC 23-8B
23.2 Special retroactive requirements. AN, GT
23.3 Airplane categories. (3.20 (less 2nd sent. of (a)(2) and 2nd and 3rd sent. of (b)), 3.20-1, 3.20-2 (1st sent.)
DE AC 23-8B
Subpart B -- Flight
GENERAL
23.21 Proof of compliance. (3.61,
3.71-1) AN, GT, FT AC 23-8B
23.23 Load distribution limits. (3.71) DE, AN, FT AC 23-8B
23.25 Weight limits. (3.74, 3.75) AN, FT AC 23-8B Page ___ of ___
Supplemental Type Certificate Compliance Checklist Project Number: Date:
Originator: Revision:
*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 Regulation Title 14 CFR (1964 CAR 3) Applicable Amendment Method of Compliance* Plan, Drawing, Report Number Person or Entity Finding Compliance Applicable Guidance, References, & Remarks Regulation Title 14 CFR (1964 CAR 3) Applicable Amendment Method of Compliance* Plan, Drawing, Report Number Person or Entity Finding Compliance Applicable Guidance, References, & Remarks 8/24/05 AC 23-24 AC 23-24 Appendix 1Appendix 1 A1-3 A1-3
23.29 Empty weight and corresponding center of gravity. (3.73 (1st sent.),
3.73-3(b)) AN, GT AC 23-8B
23.31 Removable ballast. (3.72) DE, AN AC 23-8B
23.33 Propeller speed and pitch limits.
(3.418, 3.419, 3.420, 3.421) AN, FT AC 23-8B
PERFORMANCE
23.45 General. (3.81) AN, GT, FT AC 23-8B
23.49 Stalling period. (3.82, 3.81-1,
3.83) AN, FT AC 23-8B
23.51 Takeoff speeds. (3.84 (less (c)),
3.84-2, 3.84a, 3.780(a) (1st sent.)) AN, FT AC 23-8B
23.53 Takeoff performance. AN, FT AC 23-8B
23.55 Accelerate-stop distance. GT, FT AC 23-8B
23.57 Takeoff path. FT AC 23-8B
23.59 Takeoff distance and takeoff run.
FT AC 23-8B
23.61 Takeoff flight path. FT AC 23-8B
23.63 Climb: General. FT AC 23-8B
23.65 Climb: All engines operating.
(3.85(a),3.85-5(b) (less (1) and (2)),
3.85a(a), 3.419-1 (a) (2nd sent.)) FT AC 23-8B Page ___ of ___
Supplemental Type Certificate Compliance Checklist Project Number: Date:
Originator: Revision:
*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 Regulation Title 14 CFR (1964 CAR 3) Applicable Amendment Method of Compliance* Plan, Drawing, Report Number Person or Entity Finding Compliance Applicable Guidance, References, & Remarks Regulation Title 14 CFR (1964 CAR 3) Applicable Amendment Method of Compliance* Plan, Drawing, Report Number Person or Entity Finding Compliance Applicable Guidance, References, & Remarks AC 23-24 8/24/05 Appendix 1
A1-4 A1-4
23.66 Takeoff climb: One-engine inoperative.
FT AC 23-8B
23.67 Climb: One engine inoperative.
(3.85(b), 3.85-3, 3.85a(b)) FT AC 23-8B
23.69 Enroute climb/descent. FT AC 23-8B
23.71 Glide: Single-engine airplanes. FT AC 23-8B
23.73 Reference landing approach speed.
FT AC 23-8B
23.75 Landing distance. (3.86(a),
3.87, 3.780(a) (1st sent.)) FT AC 23-8B
23.77 Balked landing. (3.85 (less (a) and (b)),3.85a (less (a) and (b))) FT AC 23-8B
FLIGHT CHARACTERISTICS
23.141 General. (3.105) FT AC 23-8B
CONTROLLABILITY AND
MANEUVERABILITY
23.143 General. (3.106) FT AC 23-8B, AC 23.143-1
23.145 Longitudinal control. (3.109) FT AC 23-8B
23.147 Directional and lateral control.
(3.110) FT AC 23-8B Page ___ of ___
Supplemental Type Certificate Compliance Checklist Project Number: Date:
Originator: Revision:
*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 Regulation Title 14 CFR (1964 CAR 3) Applicable Amendment Method of Compliance* Plan, Drawing, Report Number Person or Entity Finding Compliance Applicable Guidance, References, & Remarks Regulation Title 14 CFR (1964 CAR 3) Applicable Amendment Method of Compliance* Plan, Drawing, Report Number Person or Entity Finding Compliance Applicable Guidance, References, & Remarks 8/24/05 AC 23-24 AC 23-24 Appendix 1Appendix 1 A1-5 A1-5
23.149 Minimum control speed.
(3.111) FT AC 23-8B
23.151 Acrobatic maneuvers. (3.107,
3.108) FT AC 23-8B
23.153 Control during landings. FT AC 23-8B
23.155 Elevator control force in maneuvers.
FT AC 23-8B
23.157 Rate of roll. FT AC 23-8B
TRIM
23.161 Trim. (3.112) FT AC 23-8B
STABILITY
23.171 General. (3.113) FT AC 23-8B
23.173 Static longitudinal stability.
(3.114, 3.115 (less (a)-(c))) FT AC 23-8B
23.175 Demonstration of static longitudinal stability. (3.115 (a)-(c)) FT AC 23-8B
23.177 Static directional and lateral stability. (3.118) FT AC 23-8B
23.181 Dynamic stability. (3.117) FT AC 23-8B
Page ___ of ___
Supplemental Type Certificate Compliance Checklist Project Number: Date:
Originator: Revision:
pliance:
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 Page ___ of ___
Regulation Title 14 CFR (1964 CAR 3) Applicable Amendment Method of Compliance* Plan, Drawing, Report Number Person or Entity Finding Compliance Applicable Guidance, References, & Remarks Regulation Title 14 CFR (1964 CAR 3) Applicable Amendment Method of Compliance* Plan, Drawing, Report Number Person or Entity Finding Compliance Applicable Guidance, References, & Remarks AC 23-24 8/24/05 Appendix 1
A1-6 A1-6 STALLS
23.201 Wings level stall. (3.120(a),
3.120(b), 3.120 (less (a)-(f)), 3.120-1,
3.122 (2nd sent.)) FT AC 23-8B
23.203 Turning flight and accelerated turning stalls. (3.120(c), 3.120(d),
3.120(e) (1st through 26th words),
3.121, 3.122 (less 2nd sent.)) FT AC 23-8B
23.207 Stall warning. (3.120(f)) FT AC 23-8B
SPINNING
23.221 Spinning. (3.124(a) (less last sent.), 3.124(b), 3.124(c) (less (4)),
3.124(d)) FT AC 23-8B
GROUND AND WATER
HANDLING CHARACTERISTICS
*Methods of Com
23.231 Longitudinal stability and control. (3.144) FT AC 23-8B
23.233 Directional stability and control. (3.145) FT AC 23-8B
23.235 Operation on unpaved surfaces. (3.146) FT AC 23-8B
Supplemental Type Certificate Compliance Checklist Project Number: Date:
Originator: Revision:
*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 Regulation Title 14 CFR (1964 CAR 3) Applicable Amendment Method of Compliance* Plan, Drawing, Report Number Person or Entity Finding Compliance Applicable Guidance, References, & Remarks Regulation Title 14 CFR (1964 CAR 3) Applicable Amendment Method of Compliance* Plan, Drawing, Report Number Person or Entity Finding Compliance Applicable Guidance, References, & Remarks 8/24/05 AC 23-24 AC 23-24 Appendix 1Appendix 1 A1-7 A1-7
23.237 Operation on water. FT AC 23-8B
23.239 Spray characteristics. (3.147) FT AC 23-8B
MISCELLANEOUS FLIGHT
REQUIREMENTS
23.251 Vibration and buffeting.
(3.159) FT AC 23-8B, PS-ACE100-2001-004, PS-ACE100-2002-008
23.253 High speed characteristics. FT AC 23-8B
Subpart C -- Structure
GENERAL
23.301 Loads. (3.171,3.171-1) AN, GT, FT AC 23-19
23.302 Canard or tandem wing configurations.
AN, GT, FT AC 23-19
23.303 Factor of safety. (3.172) AN, GT AC 23-19
23.305 Strength and deformation.
(3.173) AN, GT AC 23-19, PS-ACE100-2001-006, PS-ACE100-2004-10030
23.307 Proof of structure. (3.174) AN, GT AC 23-19, PS-ACE100-2001-006, PS-ACE100-2004-10030
Page ___ of ___
Supplemental Type Certificate Compliance Checklist Project Number: Date:
Originator: Revision:
*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
Regulation Title 14 CFR (1964 CAR 3) Applicable Amendment Method of Compliance* Plan, Drawing, Report Number Person or Entity Finding Compliance Applicable Guidance, References, & Remarks
A1-8 AC 23-24 8/24/05 Appendix 1
FLIGHT LOADS
23.321 General. (3.181, 3.182) AN, GT, FT AC 23-19
23.331 Symmetrical flight conditions.
(3.183, 3.189) AN AC 23-19
23.333 Flight envelope. (3.185,
3.187, Figure 3-1) AN, GT AC 23-19
23.335 Design airspeeds. (3.184) AN AC 23-19
23.337 Limit maneuvering load factors. (3.186) AN AC 23-19
23.341 Gust loads factors. (3.188,
3.188-1) AN AC 23-19
23.343 Design fuel loads. AN, GT AC 23-19
23.345 High lift devices. (3.190 and note, 3.190-1)
AN, GT AC 23-19
23.347 Unsymmetrical flight conditions. (3.191 (less (a) and (b))) AN AC 23-19
23.349 Rolling conditions. (3.191(a) and note) AN, GT AC 23-19
23.351 Yawing conditions. (3.191(b)) AN, GT AC 23-19
23.361 Engine torque. (3.195) AN, GT AC 23-19
23.363 Side load on engine mount.
(3.196) AN, GT AC 23-19 Page ___ of ___
Supplemental Type Certificate Compliance Checklist Project Number: Date:
Originator: Revision:
*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 Regulation Title 14 CFR (1964 CAR 3) Applicable Amendment Method of Compliance* Plan, Drawing, Report Number Person or Entity Finding Compliance Applicable Guidance, References, & Remarks Regulation Title 14 CFR (1964 CAR 3) Applicable Amendment Method of Compliance* Plan, Drawing, Report Number Person or Entity Finding Compliance Applicable Guidance, References, & Remarks 8/24/05 AC 23-24 AC 23-24 Appendix 1Appendix 1 A1-9 A1-9
23.365 Pressurized cabin loads.
(3.197) AN, GT AC 23-19
23.367 Unsymmetrical loads due to engine failure.
AN, GT AC 23-19
23.369 Rear lift truss. (3.194 and note) AN AC 23-19
23.371 Gyroscopic and aerodynamic loads.
AN AC 23-19
23.373 Speed control devices. AN, GT AC 23-19
CONTROL SURFACE AND
SYSTEM LOADS
23.391 Control surface loads. (3.211) AN, GT AC 23-19
23.393 Loads parallel to hinge line. AN AC 23-19
23.395 Control system loads. (3.231,
3.231-1 (1st and 4th sent.), 3.231-2) AN, GT AC 23-19
23.397 Limit control forces and torques. (3.212, 3.212-1, Figure 3-11) AN, GT AC 23-19
23.399 Dual control system. (3.232) AN, GT AC 23-19
23.405 Secondary control system.
(3.234) AN AC 23-19
23.407 Trim tab effects. (3.213) AN AC 23-19
23.409 Tabs. (3.224) AN AC 23-19 Page ___ of ___