Figure 2-15. Sample excerpt from TCDS A00009CH (continued).
Figure 2-15. Sample excerpt from TCDS A00009CH (continued).
-3- A00009CH
Minimum Crew One (1) Pilot
Number of Seats 4 (2 at 143.5 inches aft of datum, 2 at 180 inches aft of datum)
Maximum Baggage 130 Lbs. at 208 inches
Fuel Capacity Total: S/N 1005 thru 1877, 1879 thru 1885
60.5 gal at 153.75 inches
Usable: 56 gal (See Note 1)
S/N 1878, 1886 and subsequent:
58.5 gal at 154.9 inches
Usable: 56 gal (See Note 1)
Oil Capacity 8 quarts at 76.2 inches
Maximum Operating
Altitude With a portable oxygen system, the aircraft is limited to 17,500 ft MSL.
Oxygen must be provided as required by the operating rules. Only portable oxygen systems listed
in the FAA Approved Airplane Flight Manual, document number 11934-002, or later FAA
approved revisions, are allowed.
Control Surface
Movements Wing Flaps: Up 0°± 0.5° Down 50% 16°± 0.5° Down 100% 32°± 0.5°
Aileron: Up 12.5° ± 1.0° Down 12.5° ±1.0°
Elevator: Up 25.0° +0°/-1.0° Down 15° ± 1.0°
Elevator Trim: Up 17.0° Minimum Down 10.5° ± 1.0°
Rudder: Right 20.0° ± 1.0° Left 20.0° ± 1.0°
Additional Limitations: Airframe life limit: 12,000 flight hours
Design Data: The airplane shall be manufactured in accordance with the latest FAA approved revision of
“Master Drawing List”, Document No. 13750, or other FAA approved data. NOTE: Document
No. 12609 is the predecessor document to Document No. 13750.
Serial Nos. Eligible 1005 and on
II - Model SR22, Normal Category, Approved November 30, 2000
Engine Teledyne Continental IO-550-N, Type Certificate Data Sheet E3SO
Engine Limits Maximum Take-off 2700 RPM (310 hp)
Maximum Continuous Power 2700 RPM (310 hp)
Propeller and
Propeller limits 1. Hartzell Propeller Inc. P/N PHC-J3YF-1RF/F7694 or F7694B
TCDS P36EA Hartzell
Maximum Diameter: 78 inches
Minimum Diameter: 76 inches
Number of Blades: 3
Low Pitch: 14.1°+/-0.5°
High Pitch: 35.0°+/-1.0°
No operating limitations to 2700 RPM
Spinner: Hartzell P/N A-2295-1(P) NOTE: Spinner may be painted or polished.
2. McCauley Propeller Systems P/N D3A34C443/78CYA-0
TCDS P47GL McCauley
Maximum Diameter: 78 inches
Minimum Diameter: 76 inches
Number of Blades: 3
-5- A00009CH
Minimum Crew One (1) Pilot
Number of Seats 4 (2 at 143.5 inches aft of datum, 2 at 180 inches aft of datum)
Maximum Baggage 130 Lbs. at 208 inches
Fuel Capacity Total: S/N 0002 thru 2333, 2335 thru 2419, and 2421 thru 2437
84 gallon at 154.9 inches
Usable: 81 gallon (See Note 1)
S/N 2334, 2420, 2438 and subsequent
94.5 gallon at 154.9 inches
Usable: 92.0 gallon (See Note 1)
or
58.5 gal at 154.9 inches
Usable: 56 gal (See Note 1)
Oil Capacity 8 quarts at 77.1 inches
Maximum Operating
Altitude With a portable oxygen system, the aircraft is limited to 17,500 ft MSL.
Oxygen must be provided as required by the operating rules. Only portable oxygen systems listed
in the FAA Approved Airplane Flight Manual, document number 13772-001, or later FAA
approved revisions, are allowed.
Control Surface
Movements Wing Flaps: Up 0°±0.5° Down 50% 16° ± 0.5° Down 100% 32° ±0.5°
Aileron: Up 12.5° ± 1.0° Down 12.5° ± 1.0°
Aileron Trim: Up 6 ± 1.0° Down 6 ± 1.0°
Elevator: Up 25.0° +0°/-1.0° Down 15° ± 1.0°
Elevator Trim: Up 17.0° Minimum Down 10.5° ± 1.0°
Rudder: Right 20.0° ± 1.0° Left 20.0° ± 1.0°
Additional Limitations: Airframe life limit: 12,000 flight hours
Design Data: The airplane shall be manufactured in accordance with the latest FAA approved revision of
“Master Drawing List”, Document No. 13750, or other FAA approved data.
Serial Nos. Eligible 0001 and on.
Data Pertinent to All Models
Reference Datum 100 inches in front of the forward face of firewall bulkhead
Leveling Means Door sill and leve ling points as defined in AFM
Certification Basis Model SR20 : 14 CFR Part 23 of the Federal Aviation Regulations effective February 1, 1965, as
amended by 23-1 through 23-47, except as follows:
14 CFR 23.573, 23.575, 23.611, 23.657, 23.673 through Amendment 23-48;
14 CFR 23.783, 23.785, 23.867, 23.1303, 23.1307, 23.1309, 23.1311, 23.1321, 23.1323,
23.1329, 23,1361, 23.1383, 23.1401, 23.1431, 23.1435 through Amendment 23-49;
14 CFR 23.3, 23.25, 23.143, 23.145, 23.155, 23.1325, 23.1521, 23.1543, 23.1555, 23.1559,
23.1567, 23.1583, 23.1585, 23.1589 through Amendment 23-50;
14 CFR 23.777, 23.779, 23.901, 23.907, 23.955, 23.959, 23.963, 23.965, 23.973, 23.975,
23.1041, 23.1091, 23.1093, 23.1107, 23.1121, 23.1141, 23.1143, 23.1181, 23.1191, 23.1337
through Amendment 23-51;
14 CFR 23.1305 through Amendment 23-52
Noise: 14 CFR Part 36 dated December 1, 1969 as amended by 36-1 through 36-21.
Figure 2-16. Weight and balance report.
Item C.G. Arm (in) Moment (lb-in/1,000)
Standard empty weight
Optional equipment
Special installation
Paint
Unusable fuel
Basic empty weight
1,876.0
1.2
6.2
—
30.0
1,913.4
67,798.6
16.7
257.3
—
1,380.0
69,452.6
36.1
13.9
41.5
—
46.0
Aircraft Serial No. 18259080 FAA Registration No. N42565 Date: 4-22-09
Weight (lb) ×
Figure 2-15. Sample excerpt from TCDS A00009CH (continued).
-7- A00009CH
Special Conditions 23-ACE-88 for ballistic parachute, for models SR20, SR22.
23-134-SC for protection of systems for High Intensity Radiated Fields (HIRF), for models SR20,
SR22.
23-163-SC for inflatable restraint system. Addition to the certification basis model SR20 effective
S/N 1541 and subsequent; model SR22 S/N 1500, 1520 and subsequent.
Exemptions Exemption No. 9849 to regulation 23.1419(a) for Flight Into Known Icing operations only on
model SR22 (Effective S/N 3003, 3310, 3326, 3403 and subsequent). Exemption allows for a
higher stall speed than that required by 23.49(c) & (d) when operating in icing conditions.
Production Basis Production Certificate 338CE issued June 12, 2000
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (See
Certification Basis) must be installed in the airplane for certification.
In addition to the above required equipment, the following equipment are also required:
• The latest FAA approved Revision of the “PILOT’S OPERATING HANDBOOK AND FAA
APPROVED AIRPLANE FLIGHT MANUAL for the CIRRUS DESIGN SR20”, Document No.
11934-001 for aircraft serials 1005 through 1147 with 2900 pound TOGW, Document No. 11934-
002 for aircraft serials 1005 through 1147 with 3000 pound TOGW and for aircraft serials 1148
through 1267, Document No. 11934-003 for aircraft serials 1268 and subsequent, or Document No.
11934-004 for aircraft serials 2016 and subsequent.
• The latest FAA approved Revision of the “PILOT’S OPERATING HANDBOOK AND FAA
APPROVED AIRPLANE FLIGHT MANUAL for the CIRRUS DESIGN SR22”, Document No.
13772-001 for aircraft serials 0002 and subsequent, or Document No. 13772-002 for aircraft serials
2979, 2992, 3002 and subsequent.
Note 1. A current weight and balance report including list of equipment included in the certificated empty weight, and
loading instructions when necessary must be provided for each aircraft at the time of original certification. The
certificated empty weight and loading corresponding center of gravity location must include unusable fuel of 27
lb. at (+153.8 inches) for model SR20 S/N 1005 thru 1877, 1879 thru 1885; unusable fuel of 18 lb at (+154.9
inches) for model SR22 S/N 0002 thru 2333, 2335 thru 2419, and 2421 thru 2437; and unusable fuel of 15 lb at
(+154.9 inches) for models SR22 S/N 2334, 2420, 2438 and subsequent, and SR20 S/N 1878, 1886 and
subsequent.
Note 2. All placards specified in the latest FAA approved revisions of the "PILOT'S OPERATING HANDBOOK AND
FAA APPROVED AIRPLANE FLIGHT MANUAL FOR THE CIRRUS SR20", document numbers 11934-001,
11934-002, 11934-003 or 11934-004 and the latest FAA approved revisions of the "PILOT'S OPERATING
HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL FOR THE CIRRUS SR22" document
numbers 13772-001 or 13772-002 must be displayed in the airplane in the appropriate locations.
Note 3. FAA approved Airworthiness Lim itations are included in Section 4 of the Airplane Maintenance Manual (AMM)
Document No. 12137-001 for model SR20, and 13773-001 for model SR22.
Note 4. Exterior colors are limited to those specified in the latest FAA accepted revision of the Airplane Maintenance
Manual (AMM) Document No. 12137-001 for model SR20, and 13773-001 for model SR22.
Note 5. Major structural repairs must be accomplished in accordance with FAA approved Cirrus
Design repair methods or other methods approved by the FAA.
Note 6. For Model SR22 S/N 0002 thru 2333, 2335 thru 2419, and 2421 thru 2437 a maximum landing weight exists
along the line between 141.4 inches at 3210 lbs and 142.7 inches at 3400 lbs.
-- END --
Data Pertinent to all Models
The location of the datum is specified and is described, for
example, as: 100 inches in front of the forward face of the
firewall bulkhead.
Manufacturer-Furnished Information
When an aircraft is initially certificated, its empty weight and
EWCG are determined and recorded in the weight and balance
record, such as the one in Figure 2-16. Notice in this figur
that the moment is expressed as “Moment (lb-in/1,000).” This
is a moment index, which means that the moment, a very
large number, has been divided by 1,000 to make it more
manageable. Chapter 4, Light Sport Aircraft—Weight and
Balance Control, discusses moment indices in more detail.
The aircraft is furnished with an equipment list, specifies
all the required equipment and all equipment approved for
installation in the aircraft. The weight and arm of all installed
equipment are included on the list and checked prior to the
aircraft leaving the factory.
When an aircraft mechanic or repairman adds or removes
any item on the equipment list, he or she must change the
weight and balance record to indicate the new empty weight
and EWCG, and the equipment list is revised to show
which equipment is actually installed. Figure 2-17 is from a
comprehensive equipment list that includes all of the items
of equipment approved for this particular model of aircraft.
The pilot’s operating handbook (POH) for each individual
aircraft includes an aircraft-s pecific equipment list of the
items from this master list. When any item is added to or
removed from the aircraft, its weight and arm are determined
in the equipment list and used to update the weight and
balance record. The POH and airplane flight manual (AFM)
also contain CG moment envelopes and loading graphs.
Examples of the use of these helpful graphs are given in
Chapter 5, Single-Engine Aircraft Weight and Balance
Computations.
In addition to the weight and balance report and equipment
list, the manufacturer also provides a CG range chart. The
CG range can be found in text form in the TCDS. The CG
range chart is furnished in the POH.
Figure 2-17. Excerpt from a typical comprehensive equipment list.
Figure 2-17. Excerpt from a typical comprehensive equipment list (continued).