STC SA2252CE

141002 05.-'01/07 11:20 '5'3169464164 ACE-115W ~- 'l:lnittd ~tatrJ ·Of 91Jme -.. • .,r. - :Btpmment of 1'.ran.sporr11tton-f roaal 2ll1iotion 2tdminiBtr11tion i,upplrmcntal 1t~pt ~crtificatt Shi Mar·chetti S.p.A.

2, Iridipendenza 21018 Sesto Calende (Varese) Italy -.E,Jk,,./h.a/-.a.-.~, .. ..,./kr~_,t .. Lk~y/u-";,..t.,,,,-,d.Lk,.ku:tau:,,,,,,,.,.;,u.1=,.&~ .d,,,,,,./f,-,-.aa,.a/>,u~.k-.nudJ,Jk~.,;,"'4d-,,.,f'u:acm,,MJ-~@.,0 3 .,yf.db Ci Vil Air ."~..,.kk,,,..,.

~,uu{&f~----:ftYfa'~.../it,,,/_., A 10EU .,/t,.k . .- SIAI Marchetti S. p .A ~: F260C &F260D ~PeAIU.?1"'~' Installation of Allison. 250B17D engine and H,'lrtzell HG-B3!'F-7A/T10173-25ll Propeller. Data Required: Gates Learjet Corporation Master Ora~ing List !100051, Original Release, Dsted May 20, 1987, Re•tised October 9, 1987, or later nFAA Approved" revision. Gates Lear jet FM Approved Airplane Flight ~anual for SIAI Marchetti F260C aod D, Original Release, Dated t1ay 20, 19871 Revised October 14, 1987, or later "FM Approved" revision.

~ .... ...d~~; This approval should not be extended to other specifio airplanes of these models on which other previously apprcwed modifications are incorporated, unless it is determined that the interi"elationship between this change and any of those otl1er previously approv,,d modifieations Will introduae no adverse effeot •.IPOn the airworthiness. or· thi airplane, (See Continuation Sheets 2 through 6.)

,53[.,;,,.,.,.,,,.r,r"«:«l'b..a,nd'..a..,1~,:,,?.,£,.t:,.~ ...... /k../.,,;,J.fo--#-"<=/..,,A,,//..~~-,,~·-··':,,,"'lfir/..,,,,,/.,:/__,...

,,,.,,d,,-4.,;.~4,~,.,,,._,,,.&,;,.,..,;,,..,~...,,{.t,..,a...otk,.,,,~atd/,M,u,f../y,.db..r>U,,~:r,:.ii4-«4-,..,f'd.

~.~~.~.w,u May 20, 1987 October 14, 1937 3'.?y . ..1.i,,,;i;.,, ,,,: ~. rM,,,:,,.,;;,t,,,,4.,..

Orig!ne~ Sl~r.c.d Bi' r;c)b~rt ,A .. !~P.imhll"HL . g~ · {SfgrralJlr~). ·· Robert A·. Gambri 1, .ir. , Manager Wiob.ita Aircraft Certification Office (Tit/,!

AT!)' altur(ltz'an oJ this catlf,cr,.le U pu1rl$fu1..6le ~Ya.fine ofnal aceedi'ng IJ .000, or fmprisonment not exceedihg 3 years, or both.

FAAfOf.M 8l 10-:1(10-6SJ

141003 -v.i.v~":tV-,1..l.U'i ACE-115\V 'tinitt!l Sr:amr Df 9mm :Bi:pattmOit c;..-.uansportation-1,tilttal 2lniiltion runJill:5tranon ~upplemental ~HPt <iertificatc (cr:ontinnstion tShtet) ._,/~ SA2252CE Limitations and Conditions; (Continued) Propeller and Propeller Limits: Model Hartzell HC-B3T Hub HC-B3TF-7A Blade T10173-25R Diameter 76 inches (no cutoff approved) Flight Idle 10°+.5° Measured at 30 in. span Low Pitch Stop - Airspeed Limits; IAS (knots) Maximum Operating Speed 229 V (Decrease 4 Knots per 1000 ft.

a~8ve 12,.000 feet to 196 KIAS at 20,000 feet Maneuvering 174 v_ "' Maximum flap Extended V fe Flaps 20° 125 Flaps 50° (Full Down) 108 Maximum Landing Gear 108 Operating Speed, v10 Maximum Outside Air Temperature Limits: 110°F (43,3°c) at sea0 level, with a reduction of 3,6°F (2 C) per 1000 feet altitude, for all operations.

Icing: Restricted frofu flight in known icing conditions.

' Weight Limits:

Maximum Takeoff Weight :: 2558 lb.

Maximum Landing Weight 2558 lb.

Minimum Gross Weight 1958 lb.

Maximum Baggage 44 lb, Any d/l;ration of this c,rt[ficalt fr punishf!ble by afim q/ not exmding 11,000, or im}msonmenl not exce,ding 3 y,ar,, or both.

FAA FORM BJ 10.2-1 (lo-69) 74i,t ea<tifaitk ffuDl be tran:iferrtd i'n ~,ordanu with FAR 21,i'J.

PAGE 3 OF 6 PAGES March 3, 1988 C FAA AC: 73-2651

141004 05/01/97 11: 21 '5'3169~64164 ACE-115\V i - · ilnitd ~tw of l!lmcricn " Bqi9l'onmcii of'--iiransportatlon-,:11'tdfral 5!\l!ation Sdmitn:eil'ation ~upp(cmmtal 1tnpe [crtifirate Straight line variation between points (itonttnnation ~hcct) A;~ SA2252CE Limitations and Conditions: (Continued) C.G. Range:

(Landing Gear Extended) (+90,6) (+86.8) to to (+91,3) (+91,3) at 2558 lb.

at 1984 lbs. or less given.

Reference Datum: 59,05 inches forward of firewall bulkhead with aircraft leveled.

Fuel Capacity: Total Fuel System 64 U.S. Gal.

Usable 58.14 U.S. Gal.

Oil Capacity: Total Capacity 2, 3 U, S, Gal.

Usable Capacity 1.8 U.S. Gal.

Maximum Operating Altitude: 20,000 ft.

Ii I Control Surface Movements:

Wing Flaps ]):)wn 50° -1- 1 Aileron Servotab Up 23°±_1 D::iwn 14° + 1 Aileron Up 21\0 -i-1 Down 13° +1 Rudder Left 30°+1 Right 30°+1 Elevator Tab Up 20°+1 Down 25°+1 Elevator Up 21\o:!:1 lx>wn 16°+1 Serial Numbers Eligible: See Type Certificate A10EU.

Required Equipment: Equipment described in Type Certificate Data Sheet A10EU for the F260C and F260D are required. to be on the aircraft except as modified by this STC.

Any alteration ef thi.t certijiaatt is Ptmi!hf:hle by a.fine qf not e:cc«ding IJ,000, ot imprisonm,nt not exceeding 3 years, or both.

FAA FORM 811~1 (t~t.S) Thi.I C'1tifem,t ~ he trurufrrud µI. at~C1rd&tnt1! wifh FAil 21.47.

PA<:lE 4 OF 6 Pi'IGES March 3, 1986 C FAA AC 7$-2GS1

Lg] uuo 05/01/97 11: 22 '5'3169464164 ACE-115\V ~nittil iitatu of 9mcrlcrr Bcpartmrot or-i'.ransportetion-jftdtral Slliation S:ldm!Tlm'tration ~upplrntcnral 1t~pr: <t:ertificatc ('1:ontinustion ;eheet) SA2252CE .At~ Limitations and Conditions: (Continued) Required Equipment: (Continued) In addition, the following must be in the airplane for airworthiness certifioation:

(a) Airplane Flight Manual FM-111,

(b) Current weight and balanoe report inoluding a list of equipment included in the certifioated empty weight (see note 1).

Certification Basis:

Part 3 of the Civil Air Regulations as amended to May 15, 1956, and Amendments 3-1 through :3-8. The following speaifia sections of FAR 23 are required to maintain the airplane's existing level of airworthiness with the turboprop engine insta:Uled.

FAR 23 dated February 1', 1965, sections 23.251, 23,907, 23.1105 as adopted;

23.937, 23.955, 23.1041,, 23.1045, 23.1091, 23.1103, 23.1155, 23.1505,

23.1527, 23.1583(a) as 'amended through 23-7; 23. 173, 23.201, 23,929, 23.1017,

23.1027, as amended thrpugh 23-11!; 23.951, 23,1013, 23,1015 as amended through 23-15; 23.335 a·s amended through 23-16; 23,933, 23,977, 23.1111,

23.1165, 23.1303 as amended through 23-17; 23,939, 23,943, 23.959, 23.1121,

23.1141, 23.1145, 23.1337 as amended through 23-18; 23,45, 23.49, 23.65,

23.75Cd), 23,77, 23.175, 23.1043, 23, 1521 as amended through 23-21; 23,863, 23,1545, 23.1557 as amended through 23-23; 23.253, 23,361, 23.371, 23.991,

23.1305, 23.1529 as amended through 23-26; 23.1549 as amended through 23-28;

23.901, 23,903, 23,905 exoept para (d), 23.997, 23.1019, 23.1093, 23,11~3,

23.1183 as amended throµgh 23-29; and 23.629(e) and (f) as amended through

23-31. Part 36 of the Federal Aviation Regulations.

Speoial Federal Aviation Regulation 27, as amended by 27-1 and 27-2.

Note 1: The Empty Weigbt and Center of Gravity of the airplane shall be determined by actual weighing after modification in aooordance with this STC and prior to return to servioe. This weight and center of gravity shall be recorded in the appropriate place in the airplane weight and balance report.

The certificated empty weight and oorresponding center of gravity locations must include full system engine oil of 16,5 lbs. at 48.7 inches aft of datum and unusable fuel of 3914 lbs. at 102.7 inches aft of datum.

------- ---- •it·-----~-~----------------A'!J' alteration of tkis certiJi<au is pr,nilJuibl, by ajin, of not ,xmrfing $1,000, or imprisonment not cxc«ding 3 y,ars, or both. - · - 11· 'ft"AA ~ORM 1!1110.Z.1 (t0.G9) if Thl.s. &trJifo:flk.111/J.,) ht 11'd1Ujr:n"cd itt attr:zrdmu;& wUh FAR 21.4?, PAGE 50F 6 PAGES March 3, 1988 C FAA AC 13-255'1

Ii:!:! vvu 'Bnlttd ,l:,tlll.?/; of ~G Bcparnnrot of ""•ansporration-jedcral .2Uliation S!dmilll.5'tration ~up~aLidtntal 1ijCHPf [ertifirate (trontinttation iShtet) Jfl~~ SA2252CE Lirr:.~ations and Conditions: (Continued) Note 2: Refer to the FAA Approved Airplane Flight Manual for required marking:s and placards.

Note 3: The engine ice protectkn system consists of an electrically heated inlet, engine bleed air heate( ;:;ornp-essor front bearing support hub and inlet guide vanes, c<ill£c~nt.iri.uo..,~ ignition. The engine ioe protection system giu:st be on for ground anaflight· operat.i · ;, i.n vi:sible moisture at an OAT of 5 C (41°F) and below, or while operating in falling and blowing snow regardless of ambient temperature.

Tne engine ice protection system must not be deactivated until the above ioing conditions have been departed and all aoournulated airframe ioe has dissipated.

The engine ignition system must be orf,.for all operations in heavy rain or snow.

Note 4: The fuel used in thL 0 i.rplane must have an anti-icing additive that conforms to MIL-I-27686D or i, ~. Phillips PF A55MB, incorporated or added into the fuel during refuel1n~ in accordance with the additive manufaoturer's instruC'tions.

Any alt,ration qf thi, ct:ttifo:at, is punir¥hl, by a fin, ef not ,xce,ding Sl,000, or imprisonm,n/ not e:weding 3 years, or both.

PAA FORM IJUQ-2-.t (10..69) This ctriificak may /Je tr(mJft:ft~ in. a&cordaru, with FAR 21.47, PAGE 6 Or' 6 PAGES March 3, 1988 C FAA AC 73-1:!651