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
Appendix 7 Appendix 7. Useful Information A7-1
11/16/2011 Geopotential Temp. Press. Press. Density Density Speed of Altitude Ratio Ratio Ratio Sound h P ft psi slug/ft ft/sec 1000 2.3081 2.3768x10-3 .. . . . . 1112.6 1116.4 Figure A7-1 2000 2.2409 1108.7 3000 2.1751 1104.9 4000 2.1109 1101.0 5000 2.0481 1097.1 6000 1093.2 7000 1089.2 U.S. Standard Atmosphere (1962) 8000 9000 10.50 10000 10.11 1.7553 1077.4 11000 9.720 1073.4 12000 9.346 13000 8.984 14000 8.633 15000 8.294 16000 7.965 17000 7.647 18000 19000 20000 21000 440:2 6.475 22000 6.207 23000 5.947 24000 5.696 25000 5.454 Appendix 7 AC 23-8C
0eopoteotia l Te-.p. Tea,.p. P~fl••· Pre.••• t>ensic:, Denai.t:7 Spud of Altitude a..cio R.atio letio Sound h T 8 p 0 p " V • ft OF oa oc 2ai aluf&ft 3 ft/eec 26000 - 33. 7 426.0 -36.6 .821 3 5.220 . )552 l.0 2 . 43250 1011. 7 27000 -37.) 422 .4 -38.5 . 8144 4. 994 .3398 .99 19 .41730 1007.5 28000 -40.9 418.8 --40 . 5 .8075 4 . 77 7 .)250 .9567 .40251 100).2 29000 -44 .4 415.) -42.5 .8006 4.S67 . 3107 .922S .38812 999.0 30000 -48.0 411. 7 -44.4 .7938 •. ,64 .2970 . 8893 .37413 994. 7 31000 -51.6 408.J --46.4 .7869 4.169 .2837 .8S69 .)6053 990.3 32000 -S5.1 404.6 -48.4 . 7800 3.981 .2709 .8255 . 34731 986.0 33000 -58 .7 401.0 -5o.4 • 7731 3.800 .2S86 .79S0 .33447 981.6 34000 -62 . 2 397 ·' -52.4 . 7663 3 . 626 .2467 . 7653 . 32199 977.3 3S000 -65 .8 393 .9 -S4.3 . 7594 3.458 .23S3 • 7365 .30987 972.9 36<>'.J() -69.4 390 .3 -56.4 . 752S 3.297 .2243 • 7086 .29811 968.5 37000 -0.7 390.0 -S6.S • 7519 3.142 .2138 . &759 .28435 968.1 38000 -69. 7 390.0 -56.5 .7S19 2. 994 .2038 .6442 . 27101 968.1 39000 -(,9.' HO.O -56.S . 7519 2.854 .1942 .6U9 .25829 968.1 40000 -69.1 390.0 -56 . 5 . 7S19 2. 720 .lBSl .5851 • 24617 968.1 41000 -69. 7 390.0 -56.5 . 7519 2.592 . 1764 .5577 . 23462 968. 1 42000 -69. 7 390.0 -56.5 .7S19 2.471 . 1681 . S31S . 22361 968.1 43000 -69. 7 390.0 -S6. 5 • 7519 2.3S5 . 1602 .50 65 .21 311 968. 1 44000 -69. 7 390.0 -56 .5 . 7519 2 .244 • 1527 .4828 • 20311 968. I 4S000 -69. 7 390.0 -S6.5 .7519 2.139 . 1455 .4601 . 19358 968.1 46000 -69. 7 390.0 -56.5 .7519 2.039 • 1387 .4385 .18450 968.1 47000 -69. 7 390 . 0 -56.5 . 7S19 1.943 .1322 .4180 .17S84 968.1 48000 -69 . 1 390.0 -56.S • 7519 1.852 .1260 .3983 .167S9 968.1 49000 -69. 7 390 .0 -56.S .7S19 I. 76S .1201 .3196 .1S972 968.1 S0000 -69 . , 390.0 -S6.S . 1S19 l.682 .1145 .3618 .15223 968.1 0a.ao.kine • °r + 459. 7° 01e1Yin • 0 c + i73.2° 11/16/2011 AC 23-8C Appendix 7 Figure A7-1 – U.S. Standard Atmosphere (1962) (Continued) A7-3
Appendix 7 Figure A7-2 - Temperature Conversion Chart ₴O- -230 -220 -30 -DO
- 1O 180 -150 —130