23.1561(b) 11/16/2011
23.1563(a) Placard of VA close to ASI
23.1563(b)
23.1563(c) 23.1525 Ib and turbines
23.1567(a) r normal category airplanes
23.1567(b)(1) gory airplanes es that do not meet the
23.1567(b)(2) aerobatic spin requirements ded entry airspeed; also stating
23.1567(c)
23.1567(đ) om a spin ntain information required by
23.1581(a) 23.1583- 23.1589 ration and information
23.1583- and segregated from
23.1581(b)(1) 23.1589 unapproved information
23.1581(b)(s)(i) 23.1583 shed from other parts of the
23.1581(b)(2)(ii) 23.1589 23.1585- resented in a manner to 6000 1b) acceptable
23.1581 (c) ppropriate instruments and placards
23.1581(d) fied, presented as indicated airspeeds fixed container readily
23.1581 (€) accessible to the pilot tion of revisions and/or
23.1583 23.1581 (f) amendments following: Appêndix 4
23.1583(a)(1) 23.1545 equired in $23.1545
23.1583(a)(2)
VMO/MMO and a statement that this speed must not be deliberately exceeded without 11/16/2011
23.1583(a)(3)(1) authorization (for turbine powered commuters) If an airspeed limitation is based on compressibility effects, a statement to this effect,
23.1583(a)(3)(i) further information and the recommended recovery procedure (for further powered commuters) The airspeed limits must be shown in terms of VMO/MMO for (turbine powered
23.1583(a)(3)(i1) commuters)
23.1583(b)(1),(2) 23.1521 Powerplant limitations required by § 23.1521 and explanations, when appropriate X
23.1549- Information necessary for marking powerplant instruments required in §23.1549 to
23.1583(b)(3)
23.1553 §23.1553
23.1583(c)(1) Maximum weight
23.1583(c)(2) Maximum landing weight (if less than maximum weight)
23.1583(c)(3) 23.63(c)(1) MTOW for each airdrome altitude and temperature selected by the applicant at which the airplane complies with §23.63(c)(1) (not for pistons less than 6000 Ib and commuters) For commuter airplanes, the MTOW for each airdrome altitude and temperature selected by
23.63(d)(1), the applicant at which the airplane complies with the climb requirements of §23.63(d)(1),
23.1583(c)(4) 23.55,23.59(a) the accelerate-stop distance determined in §23.55 is acceptable, the take-off distance
23.59(b) determined in §23.59(a) is acceptable and, optionally, the take-off run determined in §23.59(b) is acceptable For commuter airplanes, the maximum landing weight for each airdrome altitude selected
23.1583(c)(5) 23.63(d)(2), by the applicant at which the airplane complies with the climb requirements of
23.75,23.343 §23.63(d)(2), the landing distance determined in §23.75 is acceptable and the maximum zero wing fuel weight established in §23.343
23.1583(d) The established center of gravity limits
23.1583(€) 23.221(c) Authorized maneuvers, appropriate airspeed limitations, recommended entry speeds, spin recovery procedures and unauthorized maneuvers according to category
23.1583(f) Positive limit load factors and, for aerobatic airplanes, the negative limit load factors
23.1583(g) 23.1523 Number and functions of the minimum flight crew
23.1583(h) 23.1525 Lists of kinds of operation according to §23.1525, installed equipment affecting any operating limitation and identification as to equipment's required operational status
23.1583(I) 23.1527 Maximum operating altitude
23.1583(j) Maximum passenger seating configuration
23.1583(k) 23.1583(1) Maximum allowable lateral fuel loading differential, if less than the maximum possible Maximum allowable load and maximum intensity of loading for baggage and cargo Appêndix 4 compartments or zones
23.1583(m) Any limitations on the use of airplane systems and equipment
23.1583(n) Where appropriate, maximum and minimum ambient temperatures for operation
23.1583(o) Any restrictions on smoking in the airplane 11/16/2011
23.1583(p) 23.1587(a)(5) 23.45(g); Types of surface on which operation may be conducted (see §34.45(g) and §23.1587(a)(5) Information concerning normal, abnormal and emergency procedures and other information
23.1585(a) necessary for safe operation and achievement of scheduled performance, including
23.1585(a)(1) Explanation of significant or unusual flight or ground handling characteristics X
23.1585(a)(2) procedures Maximum demonstrated values of crosswind for take-off and landing and associated
23.1585(a)(3) A recommended speed for flight in rough air
23.1585(a)(4) 23.903(f) Procedures for restarting any engine in flight, including the effects of altitude
23.1585(a)(5) 23.73, 23.75 accordance with §23.73 and §23.75 and transition to the balked landing condition Procedures, speeds and configurations for making a normal approach and landing in
23.1585(b) 23.71 For all single-engine airplanes, procedures, speeds and configurations for a glide following engine failure and the subsequent forced landing
23.1585(c)(1) For all twin-engine airplanes, procedures, speeds and configurations for making an approach and landing with one engine inoperative For all twin-engine airplanes, procedures, speeds and configurations for making a go-
23.1585(c)(2) around with one engine inoperative, the conditions under which it can be performed safely or a warning against attempting a go-around
23.51(a),(b) For all normal, utility and aerobatic airplanes, procedures, speeds and configurations for
23.1585(d)(1) 23.53(a), (b) making a normal take-off (§§23.51(a), (b) 23.53(a), (b)) and subsequent climb (§§23.65,
23.65,23.69(a) 23.69(a))
23.1585(d)(2) For all normal, utility and aerobatic airplanes, procedures for abandoning a take-off For all normal, utility and aerobatic twin-engine airplanes, procedures and speeds for
23.1585(€)(1) continuing a take-off following engine failure, the conditions under which it can be performed safely or a warning against continuing the take-off
23.1585(€)(2) 23.67,23.69(a) For all normal, utility and aerobatic twin-engine airplanes, procedures and speeds for continuing a climb following engine failure after take-off (§23.67) or en-route (§23.69(b))
23.1585(f)(1) For commuter category airplanes, procedures, speeds and configurations for making a normal take-off
23.1585(f)(2) 23.55 For commuter category airplanes, procedures and speeds for carrying out an accelerate-stop
23.57, For commuter category airplanes, procedures and speeds for continuing a take-off following Appêndix 4
23.1585(F)(3) 23.59(a)(1), engine failure (§23.59(a)(1) and for following the flight path (§$23.57, 23.61(a))
23.61(a)
23.1585(g) 23.953 For twin-engine airplanes, information and instructions regarding fuel supply independence
23.1353(g)(2), For cach airplane showing compliance with §23.1353(g)(2) or (g)(3), the procedures for 11/16/2011
23.1585(h)
23.1353(g)(3) disconnecting the battery from its charging source
23.1585(i) Information on the total quantity of usable fuel for each tank and the effect pump failure
23.1585(j) Procedures for the safe operation of the airplane's systems and equipment, in normal use and in the event of malfunction
23.1587 23.45(b) Unless other wise presented, performance information must be provided over the altitude and temperature ranges required by §23.45(b)
23.1587(a)(1) and the effect on these stalling speeds of bank angles up to 60° Stalling speeds Vso and Vsi at maximum weight with landing gear and wing flaps retracted
23.1587(a)(2) Steady rate and gradient of climb with all engines operating The landing distance for each airdrome altitude and standard temperature and the type of
23.1587(a)(3) surface for which it is valid The effect on landing distance of operation on other than smooth hard surfaces, when dry X The effect on landing distance of runway slope, 50% of the headwind component and 150% X of the tailwind component
23.1587(b) 23.77(a) climb/descent For normal, utility and aerobatic piston airplanes of 6000 Ib or less, the steady angle of
23.1587(c)(1) 23.53 which it is valid For normal, utility and aerobatic airplanes, the take-off distance and the type of surface for
23.1587(c)(2) 23.45(g) The effect on take-off distance of operation on other than smooth hard surfaces, when dry
23.1587(c)(3) of the tailwind component The effect on take-off distance of runway slope, 50% of the headwind component and 150%
23.1587(c)(4) 23.66 For twin piston airplanes of more than 6000 Ib MTOW and turbine airplanes, the oneengine inoperative take-off climb/descent gradient
23.1587(c)(5) 23.69(b) For twin-engine airplanes, the en-route rate and gradient of climb/descent with one-engine inoperative
23.1587(c)(6) 23.71 For single-engine airplanes, the glide performance
23.1587(d)(1) 23.55 For commuter airplanes, the accelerate-stop distance
23.1587(d)(2) 23.1587(d)(3) 23.59(a) 23.59(b) For commuter airplanes, the take-off distance For commuter airplanes, the take-off run at the applicant's option Appendix 4 AC 23-8C
23.1587(d)(4) 23.45(g) For commuter airplanes, the effect on accelerate-stop distance, take-off distance and, if determined, take-off run of operation on other than smooth hard surfaces, when dry
For commuter airplanes, the effect on accelerate-stop distance, take-off distance and, if 11/16/2011
23.1587(d)(5) determined, take-off run of runway slope, 50% of the headwind component and 150% of the tailwind component
23.1587(d)(6) 23.61(b) For commuter airplanes, the net take-off path X
23.1587(dy(7) 23.69(b) For commuter airplanes, the en-route gradient of climb/descent with one engine inoperative For commuter airplanes, the effect on the net take-off path and the en-route gradient of
23.1587(d)(8) climb/descent with one engine inoperative, of 50% of the headwind component and 150% of the tailwind component
23.1587(d)(9) 23.63(d)(2), 75 For commuter airplanes, overweight landing performance information (the maximum X weight at which the airplane complies with $23.63(d)(2) and the landing distance in §23.75)
23.1587(d)(10) 23.1323(b).(c) For commuter airplanes, the relationship between IAS and CAS
23.1587(d)(11) 23.1325(€) For commuter airplanes, the altimeter system calibration X
23.1587(d)(7) 23.69(b) For commuter airplanes, the en-route gradient of climb/descent with one engine inoperative
23.1589(a) 23.25 The weight and location of each item of equipment that can be easily removed and was installed when the airplane was weighed
23.1589(b) 23.23, 23.25 Appropriate loading instructions for each permissible loading condition of weight and og App. G23-2,3,4 23.1529 Instructions for continued airworthiness 00 Appendix 4
Appendix 5 Appendix 5 –Guide for Preparing Airplane Flight Manual and Pilots’s Operating Handbook Supplements
1. Introduction. An applicant is responsible for prep aring an Airplane Flight Manual (AFM) supplement when the airplane has been modified in such a manner that limitation, procedures, performance, or loading information have changed. The supplement should be prepared to reflect this supplemental information. If there is no change in one of the sections, it should so state.
a. Pilot's Operating Handbook Supplements. Refer to GAMA Specification No. 1, Revision No. 1.
b. AFM Supplements. Refer to paragraph 2 below and sample AFM.
2. General.
a. Enter name and address of applicant and document number (if used).
b. Enter make and model of the airplane. Multiple models may be used.
c. Enter registration number. Note: If more than one airplane is to be approved under this supplemental type certificate, leave this space blank on the master copy of the supplement so it can be filled in for each airplane as the modification is accomplished.
d. Enter airplane serial number. This number is on the airplane data plate. Note: If more than one airplane is to be approved under this supplemental type certificate, leave this space blank on the master copy of the supplement so it can be filled in for each airplane as the modification is accomplished. If only one airplane is to be approved, add "only" after the serial number.
e. Enter original AFM date or reissue date (if applicable).
f. Enter the type of modification or equipment installed.
g. Enter approval basis such as: Form 337, specification item number, Supplemental type Certificate Number, and so forth.
h. Enter any changed or additional limitations as a result of the modification. Follow the format of the basic AFM. If no change, state "NO CHANGE".
i. Enter any change in or additional procedures as a result of the modification. Follow the format of the basic AFM. This section may be divided into Normal and Emergency Procedures, if necessary. If no change, state "NO CHANGE".
j. Enter any change in performance as a result of the modification. If no change, state "NO CHANGE". In some cases, it is possible to show a statement similar to the following. "The performance of this airplane equipped with the Continental E-225-8 engine and Beech Model 215 propeller is equal to or better than the performance as listed in the original FAA-approved AFM."
k. Enter any change in the loading instructions, if necessitated by the change.
A5-1
___________________________________________________________________________________ Appendix 5
l. Copy this item, as shown on the sample AFM Supplement, leaving a blank space for typing of the ACO Manager's name below the signature line. This item needs to be coordinated with the ACO prior to submitting because in some ACO's the manager does not sign the AFM.
m. Type as shown on sample AFM Supplement, leaving a blank space so date of approval can be added.
n. If the supplement requires more than one page, a cover page should be prepared in accordance with page 3 of this appendix, except that items (h), (u), (j), and (k) should be on page 2 or subsequent. Each page should have: (1) the name and address of applicant and document number; (2) AFM supplement for Make and Model; (3) "FAA-approved" and "date" of approval; and (4) page number as (Page 1 of 3).
o. For those airplanes without flight manuals, and placards are not appropriate, the document should be labeled a Supplemental Airplane Flight Manual and arranged and worded as necessary with reference to the appropriate markings and placards. Identification of the material as Limitations, Procedures, or Performance should be clearly presented.
p. If applicant revises the AFM supplements, pertaining to one airplane model, a log of revisions may be added, as follows: (This revision log also needs a signature block.)
LOG OF REVISIONS Revision No. Pages Affected Description FAA-Approved Date Note: The revision page should immediately follow the cover page.
q. Vertical bars should be placed in the margin of the revised pages to indicate changed material.
A5-2
Appendix 5 Name _______________________________________ ( a ) Address _______________________________________ Supplement No._______________________________________
FAA-APPROVED
AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR
(b) _______ Make and Model Airplane R e g . N o . ( c ) Ser. No. (d) This supplement must be attached to the FAA- approved Airplane Flight Manual dated (e) when
(f) is installed in accordance with (g) . The information contained in this document supplements or supersedes the basic manual only in those areas listed. For limitations, procedures, performance, and loading information not contained in this supplement, consult the basic Airplane Flight Manual.
I. LIMITATION: (h) II. PROCEDURES: (i) III. PERFORMANCE: (j) IV. LOADING INFORMATION: (k) FAA-Approved (1) Manager, Aircraft Certification Office Federal Aviation Administration City, State DATE (m) Revised
(If applicable) P a g e 1 o f ( n ) A5-3
Appendix 6 Appendix 6. Sample Kinds of Operating Equipment List This airplane may be operated in day or night VFR, day or night IFR, and known or forecast icing conditions when the appropriate equipment is installed and operable.
The following equipment list identifies the systems and equipment upon which type certification for each kind of operation was predicated. The following systems and items of equipment must be installed and operable for the particular kind of operation indicated.
The ATA numbers refer to equipment classifications of Air Transport Association Specification Code
100.
VFR Day VFR Night IFR Day IFR Night I c i n g Condition s Communications (ATA-23)
1. Communication Radio (VHF) 0 0 1 1 1 Electrical Power (ATA-24)
1. Battery 1 1 1 1 1
2. D.C. Generator 2 2 2 2 2
3. D.C. Loadmeter 2 2 2 2 2
4. D.C. Generator Warning Light 2 2 2 2 2
5. Inverter 2 2 2 2 2
6. Inverter Warning Light 1 1 1 1 1
7. Feeder Limiter Warning Light 1 1 1 1 1
8. Battery Monitor system 1 1 1 1 1
9. AC Volt Meter 1 1 1 1 1 Equipment/Furnishings (ATA-25)
1. Exit Signs - Self-Illuminated 4 4 4 4 4 Fire Protection (ATA-26)
1. Engine Fire Detector System 2 2 2 2 2
2. Firewall Fuel Shutoff System 2 2 2 2 2 A6-1
Appendix 6 VFR Day VFR Night IFR Day IFR Night Icing Condition Flight Controls (ATA-27) . Flap System 1 1 1 1 1
2. Flap Position Indicator 1 1 1 1 1
3. Horizontal Stabilizer Trim System – Main 1 1 1 1 1
4. Horizontal Stabilizer Trim System – Standby 1 1 1 1 1
5. Stabilizer out-of-trim Aural Warning Indicator 1 1 1 1 1
6. Trim-in-Motion Aural Indicator 1 1 1 1 1
7. Horizontal Stabilizer Position Indicator 1 1 1 1 1
8. Stall Warning Horn 1 1 1 1 1
9. Trim Tab Indicator – Rudder 1 1 1 1 1
10.Trim Tab Indicator Aileron 1 1 1 1 1 Fuel (ATA-28)
1. Fuel Boost Pumps (4 are installed) PER AFM Limitations
2. Fuel Quantity Indicator 2 2 2 2 2
3. Fuel Quantity Gauge Selector Switch 1 1 1 1 1
4. Nacelle Not-Full Warning Light 2 2 2 2 2
5. Crossfeed Light 1 1 1 1 1
6. Fuel Boost Pump Low Pressure Warning Light 2 2 2 2 2
7. Fuel Flow Indicator 2 2 2 2 2
8. Jet Transfer Pump 2 2 2 2 2 Ice and Rain Protection (ATA-30)
1. Engine Inlet Scoop Deicer Boot 2 2 2 2 2
2. Indicator – Propeller/Inlet Deicer 1 1 1 1 1
3. Engine Inertial Anti-Icing System 2 2 2 2 2
4. Pitot Heat 0 0 2 2 2
5. Alternate Static Air Source 0 0 1 1 1
6. Engine Auto-Ignition System (if installed) 2 2 2 2 2
7. Propeller Deicer System 0 0 0 0 1
8. Windshield Heat (Left) 0 0 0 0 1
9. Surface Deicer System 0 0 0 0 1
10. Stall Warning Mounting Plate Heater 0 0 0 0 1
11. Wing Ice Light (Left) 0 0 0 0 1
12. Windshield Wiper (Left) 1 1 1 1 1 A6-2
Appendix 6 VFR Day VFR Night IFR Day IFR Night Icing Condition Instruments (ATA-31)
1. Clock 0 0 1 1 1 Landing Gear (ATA-32)
1. Landing Gear Position Indicator Lights 3 3 3 3 3
2. Flap-Controlled Landing Gear Aural Warning 1 1 1 1 1
3. Nose Steering Disconnect Actuator 1 1 1 1 1
4. Landing Gear Hydraulic Pump 1 1 1 1 1 Lights (ATA-33)
1. Cockpit and Instrument (Required Illumination) 0 1 0 1 0
2. Anti-Collision 0 2 0 2 0
3. Landing Light 0 2 0 2 0
4. Position Lights 0 3 0 3 0
5. Cabin Door Warning Light (Note) 1 1 1 1 1
6. Baggage Door Warning Light (Note) 1 1 1 1 1 Note: Where combined into one cabin/baggage annunciator – one (1) is required for all conditions.
Navigation (ATA-34)
1. Altimeter 1 1 1 1 1
2. Airspeed 1 1 1 1 1
3. Magnetic Compass 1 1 1 1 1
4. Outside Air Temperature 1 1 1 1 1
5. Attitude Indicator (Gyro stabilized) 0 0 1 1 1
6. Directional Indicator (Gyro stabilized) 0 0 1 1 1
7. Sensitive Altimeter 0 0 1 1 1
8. Turn and Bank Indicator or Turn Coordinator 0 0 1 1 1
9. Vertical Speed Indicator 0 0 1 1 1
10. Navigation Radio (VHF) 0 0 1 1 1 Vacuum System
1. Suction or Pressure Gauge 1 1 1 1 1
2. Instrument Air System 1 1 1 1 1 A6-3
Appendix 6 VFR Day VFR Night IFR Day IFR Night Icing Conditions Propeller (ATA-61)
1. Autofeather System 2 2 2 2 2
2. Low Pitch Light 2 2 2 2 2
3. Do Not Reverse Warning Light 1 1 1 1 1 . Propeller Reversing 2 2 2 2 2 Engine Indicating (ATA-77)
1. Tachometer Indicator (Propeller) 2 2 2 2 2
2. Tachometer Indicator (Gas Generator) 2 2 2 2 2
3. ITT Indicator 2 2 2 2 2
4. Torque Indicator 2 2 2 2 2 Engine Oil (ATA-79)
1. Oil Temperature Indicator 2 2 2 2 2
2. Oil Pressure Indicator 2 2 2 2 2
3. Low Oil Pressure Light 2 2 2 2 2
4. Engine Chip Detector System 2 2 2 2 2 Note 1: The zeros (0) used in the above list mean that either the equipment or system, or both were not required for type certification for that kind of operation.
Note 2: The above system and equipment list is predicated on a crew of one pilot.
Note 3: Either equipment or systems in addition to those listed above may be required by the operating regulations.
Note 4: Further information may be drawn from an approved Minimum Equipment List (MEL), if applicable.
A6-4