STC ST09559AC

FAA Form 8110-2 (5/14) Page 1 of 10

Reissued on July 14, 2017 to supersede the original STC, which has been lost or misplaced.

Number: ST09559AC

Parts 23 and 25 of the Federal Aviation Regulations.

Original Product – Type Certificate Number: A27CE and A22CE Make: Cessna Model: See Approved Model List Description of Type Design Change:

Installation of Williams International Company, L.L.C. FJ44-2A engines in Cessna 501/500 aircraft or Williams International Company, L.L.C. FJ44-3A engines in Cessna Model 550/S550 aircraft in accordance with Sierra Industries Drawing shown in AML or later FAA approved revision. Sierra Industries, LTD. Airplane Flight Manual Supplements for Cessna Model 501, 500, 550, and S550 is required. (See AML for installation kit no. and AFMS number.)

Compatibility of this design change with previously approved modifications must be determined by the installer. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission.

(See continuation sheet 3 of 10)

Date of Application: June 12, 1998 Date Reissued: 11/24/03; 3/10/06; 3/24/06; 7/14/17 Date of Issuance: March 14, 2002 Date Amended: November 13, 2008; July 8, 2009

Signature

Title James A. Grigg Manager, Fort Worth Aircraft Certification Office , Southwest Region Sierra Industries, Ltd.

122 Howard Langford Drive Uvalde, TX 78801

FAA Form 8110-2 (5/14) Page 2 of 10

Transfer the ownership of Supplemental Type Certificate Number: ST09559AC

To (Name and address of transferee)

From (Name and address of grantor)

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST09559AC

FAA Form 8110-2 (5/14) Page 3 of 10

Date of Issuance: March 14, 2002 Date Amended: July 8, 2009 Date of Reissuance: July 14, 2017

Model 501, Citation (Normal Category)

Engines Two Williams International Co. L.L.C. FJ44-2A turbofans used in combination.

Fuel Commercial kerosene Jet A, Jet A-1 and JP-8. These fuels, except JP-8 require the addition of anti-ice additive (MIL-I-27686 or MIL-I-85470); and must be blended into the aircraft fuel in concentrations not less than 0.060 percent or more than 0.15 percent by volume.

Engine Limits Static thrust standard day, sea level:

Takeoff (5 min.) 2300 lb.

Max. continuous 2300 lb.

Max. permissible engine rotor speeds:

N1 (Fan) 105.2 percent 18,150 r.p.m.

N2 (Gas Gen.) 98.8 percent 40,700 r.p.m.

Max. permissible interturbine gas temperatures:

Takeoff 820°C.

Max. continuous 805°C.

Transient (10 Sec.) 835°C.

Airspeed Limits: When incorporating configuration SI360-001-1 (AFMS SRW137) VA (Sea Level) 185 knots

When incorporating configuration SI360-001-3 (AFMS 170-104) VMO (Maximum operating) (Below 30,900 feet) 259 kias MMO (Above 30,900 feet) 0.705 Mach (indicated) VA (Sea Level) See AFMS for variations with weight and altitude VFE (Flaps extended) 40° (Landing) 176 kias 15° (Takeoff and approach) 202 kias VLO (Landing gear operating) 176 kias

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST09559AC

FAA Form 8110-2 (5/14) Page 4 of 10

Date of Issuance: March 14, 2002 Date Amended: July 8, 2009 Date of Reissuance: July 14, 2017

Model 501, Citation (Normal Category) Cont’d:

Maximum Weight When incorporating configuration SI360-001-1 (AFMS SRW137) Takeoff 12,500 lb.

Landing 11,350 lb.

Zero Fuel 9,500 lb.

Ramp 12,500 lb.

When incorporating configuration SI360-001-3 (AFMS 170-104) Takeoff 12,500 lb.

Landing 11,350 lb.

Zero Fuel 8,600 lb.

Ramp 12,650 lb.

Fuel Capacity (Gal.) Configuration SI360-001-1 Two wing tanks: Total 339 each; usable 334 Configuration SI360-001-3 Two wing tanks: Total 287 each; usable 282

Oil Capacity (Qts.) Two engine mounted tanks: Total 3.60 each; usable 2.73

Maximum Operating Altitude 43,000 Feet

Model 500, Citation (Normal Category)

Engines Two Williams International Co. L.L.C. FJ44-2A turbofans used in combination.

Fuel Commercial kerosene Jet A, Jet A-1 and JP-8. These fuels, except JP-8 require the addition of anti-ice additive (MIL-I-27686 or MIL-I-85470); and must be blended into the aircraft fuel in concentrations not less than 0.060 percent or more than 0.15 percent by volume.

Engine Limits Static thrust standard day, sea level:

Takeoff (5 min.) 2300 lb.

Max. continuous 2300 lb.

Max. permissible engine rotor speeds:

N1 (Fan) 105.2 percent 18,150 r.p.m.

N2 (Gas Gen.) 98.8 percent 40,700 r.p.m.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST09559AC

FAA Form 8110-2 (5/14) Page 5 of 10

Date of Issuance: March 14, 2002 Date Amended: July 8, 2009 Date of Reissuance: July 14, 2017

Model 500, Citation (Normal Category) Cont’d:

Max. permissible interturbine gas temperatures:

Takeoff 820°C.

Max. continuous 805°C.

Transient (10 Sec.) 835°C.

Airspeed Limits: When incorporating configuration SI360-001-1 (AFMS SRW135) VA (Sea Level) 185 kcas

When incorporating configuration SI360-001-3 (AFMS 170-104) VMO (Maximum operating) (Below 30,900 feet) 259 kias MMO (Above 30,900 feet) 0.705 Mach (indicated) VA (Sea Level) See AFMS for variations with weight and altitude VFE (Flaps extended) 40° (Landing) 176 kias 15° (Takeoff and approach) 202 kias VLO (Landing gear operating) 176 kias

Maximum Weight When incorporating configuration SI360-001-1 (AFMS SRW135) Takeoff 12,500 lb.

Landing 11,350 lb.

Zero Fuel 9,500 lb.

Ramp 12,650 lb.

When incorporating configuration SI360-001-3 (AFMS 170-104) Takeoff 12,500 lb.

Landing 11,350 lb.

Zero Fuel 8,600 lb.

Ramp 12,650 lb.

Fuel Capacity (Gal.) Configuration SI360-001-1 Two wing tanks: Total 339 each; usable 334 Configuration SI360-001-3 Two wing tanks: Total 287 each; usable 282

Oil Capacity (Qts.) Two engine mounted tanks: Total 3.60 each; usable 2.73

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST09559AC

FAA Form 8110-2 (5/14) Page 6 of 10

Date of Issuance: March 14, 2002 Date Amended: July 8, 2009 Date of Reissuance: July 14, 2017

Model 500, Citation (Normal Category) Cont’d:

Maximum Operating Altitude 43,000 Feet A/C 500 – 0001 thru – 0213 not incorporating SB21-9 35,000 Feet

Model 550, Citation (Normal Category):

Engines Two Williams International Co. L.L.C. FJ44-3A turbofans used in combination.

Fuel Commercial kerosene Jet A, Jet A-1, Jet B, JP-4, JP-5 or JP-8. These fuels, except JP-5 require the addition of anti-ice additive (MIL-I-27686 or MIL-I-85470); and must be blended into the aircraft fuel in concentrations not less than 0.10 percent or more than 0.15 percent by volume. JP-5 require the addition of anti-ice additive (MIL-I-27686 or MIL-I-85470); and must be blended into the aircraft fuel in concentrations not less than 0.10 percent or more than 0.20 percent by volume.

Engine Limits Static thrust standard day, sea level:

Takeoff (5 min.) 2820 lb.

Max. continuous 2820 lb.

Max. permissible engine rotor speeds:

N1 (Fan) 105.2 percent 18,500 r.p.m.

N2 (Gas Gen.) 98.8 percent 41,200 r.p.m.

Max. permissible interturbine gas temperatures:

Takeoff 877°C.

Max. continuous 840°C.

Transient (10 Sec.) 891°C.

Maximum Weight

550-0001 Through 550-0626 550-0627 Through 550-0733 Takeoff 13,300 lb 14,100 lb Landing 12,700 lb 13,500 lb Zero fuel 9,500 lb 11,000 lb Ramp 13,500 lb 14,300 lb *See NOTE 1 for optional zero fuel weight (S/N 550-0001 through 550-0549) This STC is compatible with STC SA4954NM, for S/N 550-001 through 550-0626, up to a max takeoff weight of 14,100 lbs.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST09559AC

FAA Form 8110-2 (5/14) Page 7 of 10

Date of Issuance: March 14, 2002 Date Amended: July 8, 2009 Date of Reissuance: July 14, 2017

Model 550, Citation (Normal Category) Cont’d:

Fuel Capacity (Gal.) Two wing tanks: Total 376 each; usable 371 each

Oil Capacity (Qts.) Two engine mounted tanks: Total 4.37 each; usable 3.35

Maximum Operating Altitude 43,000 Feet

Model S550, Citation (Normal Category):

Engines Two Williams International Co. L.L.C. FJ44-3A turbofans used in combination.

Fuel Commercial kerosene Jet A, Jet A-1, Jet B, JP-4, JP-5 or JP-8. These fuels, except JP-5 require the addition of anti-ice additive (MIL-I-27686 or MIL-I-85470); and must be blended into the aircraft fuel in concentrations not less than 0.10 percent or more than 0.15 percent by volume. JP-5 require the addition of anti-ice additive (MIL-I-27686 or MIL-I-85470); and must be blended into the aircraft fuel in concentrations not less than 0.10 percent or more than 0.20 percent by volume.

Engine Limits Static thrust standard day, sea level:

Takeoff (5 min.) 2820 lb.

Max. continuous 2820 lb.

Max. permissible engine rotor speeds:

N1 (Fan) 105.2 percent 18,500 r.p.m.

N2 (Gas Gen.) 98.8 percent 41,200 r.p.m.

Max. permissible interturbine gas temperatures:

Takeoff 877°C.

Max. continuous 840°C.

Transient (10 Sec.) 891°C.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST09559AC

FAA Form 8110-2 (5/14) Page 8 of 10

Date of Issuance: March 14, 2002 Date Amended: July 8, 2009 Date of Reissuance: July 14, 2017

Model S550, Citation (Normal Category) Cont’d:

Maximum Weight

*S/N S550-0001 Through S550- 0085 S/N S550-0086 Through S550-0166 Takeoff 15,100 lb 15,100 lb Landing 14,400 lb 14,400 lb Zero fuel 11,200 lb 11,200 lb Ramp 15,300 lb 15,300 lb

*S/N S550-001 through S550-0085 are eligible for this STC when Cessna SB S550-11-1 has been incorporated.

Fuel Capacity (Gal.) Two wing tanks: Total 376 each; usable 371 each

Oil Capacity (Qts.) Two engine mounted tanks: Total 4.37 each; usable 3.35

Maximum Operating Altitude 43,000 Feet

Certification Basis:

Based on 14 CFR §§21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the Cessna Model 501 is that contained in TCDS A27CE.

Based on 14 CFR §§21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the Cessna Model 500 is that contained in TCDS A22CE.

Based on 14 CFR §§21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the Cessna Model 550 is as follows:

a. The type certification basis for Cessna Model 550/S550 series airplanes is shown on TCDS A22CE for parts not changed or not affected by the change.

b. The certification basis for parts changed or affected by the change since the reference date of application, July 13, 2006, is based upon part 25 as amended by Amendment 25-123. Based on 14 CFR §§21.101 and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for this modification was determined to be:

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST09559AC

FAA Form 8110-2 (5/14) Page 9 of 10

Date of Issuance: March 14, 2002 Date Amended: July 8, 2009 Date of Reissuance: July 14, 2017

Certification Basis (Continued):

Regulations at the latest amendment 25-0 through 25-123

25.1 - 25.3, 25.23 – 25.33, 25.117, 25.171, 25.173, 25.235, 25.239, 25.301, 25.303, 25.305(c) - 25.333, 25.337, 25.561,

25.581, 25.601 – 25.623, 25.863, 25.899, 25.901, 25.903, 25.939, 25.943, 25.951, 25.952, 25.954, 25.955, 25.961, 25.975,

25.977, 25.991 – 25.999, 25.1011 – 25.1025, 25.1041 – 25.1093, 25.1103, 25.1107 – 25.1123, 25.1141, 25.1143, 25.1145,

25.1163, 25.1165, 25.1181 – 25.1191, 25.1193 – 25.1201, 25.1207, 25.1305, 25.1316 – 25.1322, 25.1351(a)(c)(d),

25.1355, 25.1357, 25.1363, 25.1381, 24.1383, 25.1387 – 25.1397, 25.1399, 25.1411 – 25.1423, 25.1431,

25.1441 – 25.1445, 25.1449, 25.1453, 25.1503, 25.1507 – 25.1513, 25.1519 – 25.1531, 25.1541 – 25.1563, 25.1581,

25.1583(b), 25.1585

Regulations at an intermediate amendment

25.113, 25.335, 25.1305(d)(3) as amended by Amendment 25-23;

25.119, 25.121, 25.125, 25.145, 25.149 as amended by Amendment 25-84;

25.161, 25.1303 as amended by Amendment 25-38;

25.21, 25.521 as amended by Amendment 25-72;

25.105 – 15.111, 25.115, 25.123, 25.341, 25.343, 25.349, 25.363, 25.367, 25.371, 25.625, 25.1419, 25.1435, 25.1438,

25.1533, 25.1587 as amended by Amendment 25-17;

25.345, 25.351, 25.361, 25.473 as amended by Amendment 25-37;

25.571, 25.629 as amended by Amendment 25-45;

25.869(a), 25.1353(a)(b)(d) as amended by Amendment 25-113;

25.1203 as amended by Amendment 25-26;

25.1301 as amended by Amendment 25-20;

25.1309 amended by Amendment 25-41

c. Aircraft fuel venting as shown on TCDS A22CE. Engine fuel venting and exhaust emissions as shown on TCDS E3GL.

d. The modified aircraft meets 14 CFR Part 36 as amended by Amendment 36-28.

NOTE 1: Model 550 S/N 550-0001 through 550-0549 conforming to ECR EC04574 or SB550-34-4 are eligible for 11,000 lb.

zero fuel weight with VMO reduced to 260 KCAS from 14,000 ft. to 30,500 ft. 11,000 lb. zero fuel weight provision is standard at S/N 550-0550 through 550-0733.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST09559AC

FAA Form 8110-2 (5/14) Page 10 of 10

Date of Issuance: March 14, 2002 Date Amended: July 8, 2009 Date of Reissuance: July 14, 2017

Certification Basis (Continued):

NOTE 2: Model 550 S/N 550-0001 through 550-0505, and S/N 550-0550 through 550-0626 when modified in accordance with Cessna Service Bulletin SB550-32-14 are eligible to operate at the following VLO and VLE:

Model 550 SB550-32-14 11,000 lb. ZFW 9,500 lb. ZFW VLO (Landing gear operating extend) 248 KCAS 248 KCAS VLO (Landing gear operating retract) 198 KCAS 198 KCAS VLE (Landing gear extended) 260 KCAS 275 KCAS

-END-

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: ST09559AC

FAA Form 8110-2 (5/14) Page 11 of 10