# TCDS E2EU: Rolls-Royce Deutschland Ltd & Co KG - Type: Type certificate data sheet - Status: Current - Holder: Rolls-Royce Deutschland Ltd & Co KG - Revision: 16 - Revised: March 23, 2007 - Product: Engine - Certification basis: Part 13, Part 21, CAR 10 - Registered aircraft: 16, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/a5/05/a505f29703a5c5a1b386ab843db15d2ac7bab3281f3ed853c963a22b9643d34e - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/76B5A23371F5FD4C862572A500732805.0001 - Page: https://openairdocs.org/tcds/E2EU ## Models (11) As the data sheet lists them. - Spey 506-14A - Spey 511-14 - Spey 511-8/Mod 2970 - Spey 506-14D - Spey 555-15N - Spey 511-8 - Spey 555-15 - Spey 506-14 - Spey 555-15H - Spey 555-15P - Spey 511-14W ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text * PAGE 1 2 3 4 5 6 REV. 16 16 14 14 14 16 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTICE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES, IF ANY, ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E2EU TCDS NUMBER E2EU REVISION: 16* DATE: March 23, 2007 ROLLS-ROYCE Deutschland Ltd & Co KG MODELS: SPEY 506-14 511-14W 555-15H 506-14A 511-8 555-15N 506-14D 511-8/Mod 2970 555-15P 511-14 555-15 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E2EU) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations, provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. TYPE CERTIFICATE (TC) HOLDER: Rolls-Royce Deutschland Ltd & Co KG Postfach 1536 D-15827 Dahlewitz Germany (formerly known as Rolls-Royce plc, Derby England I. MODELS (SPEY) 506-14 / 506-14A / 506-14D 555-15N/ 555-15 555-15P / 555-15H 511-14 / 511-14W / 511-8/ 511-8/Mod 2970 TYPE Turbojet (by pass) Twin spool, 16 stage axial compressor 4 stage turbine, tube-annular combustor with 10 flame tubes - - - - - - - - Twin spool, 17 stage axial compressor - - RATINGS (See Notes 1, 2 and 4) Max. cont. static thrust at sea level, (lbs) Takeoff static thrust at sea level, (5 min, See Note 15) (lbs) 9,990 10,410 for 506-14, 506-14A and 506-14D 9,470 9,850 9,520 9,900 10,940 11,400 FUEL CONTROL (See NOTE 10) Fuel Oil Capacity Oil Types Lucas CASC 105 Lucas CASC 167 for 506-14A See NOTE 9 14.4 US pints Integral Tank 10.8 US pints usable Refer to RR Operating Instructions for model. CASC 133 - - - - - - CASC 211 - - - - - - CASC 112 for 511-14 CASC 145 for 511-14W CASC 116 or 146 for 511-8 - - - - - - PRINCIPAL DIMENTIONS Length (in) (From front of nose cone to rear of exhaust cone bullet) Max. diameter (in) (Encircling dia. Excluding accessories) 109.988 39.700 102.32 (-15) 105.34 (-15N) - - - - (-15H) - - (-15P) - - 114.565 - - TCDS E2EU PAGE 2 I. MODELS (CONT.) (SPEY) 506-14, 506-14A, 506-14D 555-15 555- 15N 555-15H 555-15P 511-14, 511-14W, 511-8, 511-8 Mod 2970 WEIGHT, dry (lbs) – including fuel system, oil system, oil tank and filters, anti-icing system, accessory drives, igniter plugs and EGT thermocouples and harness 2,297 2,222 2,238 2,247 2,257 2,483 for 511-8 2,487 for 511-14 2,506 for 511-14W CENTER OF GRAVITY, IN. Rearward of front suspension Centerline 20.2 18.2 18.4 17.9 18.1 19.3 for 511-14 19.1 for 511-14W 19.2 for 511-8 IGNITION SYSTEM (See NOTE 10) Igniters Lodge LF 114-2 or AC AR 114 Igniter Boxes Rotax NB 38 or AEI C34/TS.2 - - Igniter Boxes AEI C120TS/1 or 119TS/1 - - - - - - - - - - - - Igniter Boxes NB 38 or AEI C83/TS/1 for 511-14 & - 14W Rotax NB 34 for 511- 8 - - NOTES 1 thru 16 - - - - - - - - - - CERTIFICATION BASIS CAR 10/FAR 21.29 and British Civil Airworthiness Requirements, Section C, Issue 5 except for Spey 555-15, 555-15H, 555-15N, and 555-15P which comply with Issue 6 of BCAR. (The BCAR Section C is equivalent to US CAR Part 13 effective June 15, 1956, as amended by 13-1 through 13-5, Section C, Issue 6 is equivalent to FAR 33-1). Type Certificate No. E2EU date of application February 21, 1964, issued March 6, 1964. Amended to include 506-14 and 506-14AW on February 26, 1965; 506-14B, 510-14 and 510-14 and delete 505-5 and 506-14AW October 15, 1965; to include 511-14 on August 30, 1966, 511-8 and delete 506-14B on June 1, 1967; to include 506-14C on March 11, 1968, 555-15 on December 20, 1968, 506-14A on June 24, 1969, 506-14D on April 19, 1971, 511-14W on May 11, 1973, and delete 510-14 on December 17, 1974; to include 511-8/Mod 2970 on December 17, 1974; to include 555-15H on March 3, 1980; to include 555-15N and 555-15P on October 26, 1981; to delete 506-14C on June 10, 1985. The aviation authority for Germany, Luftfahrt-Bundesamt, type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E2EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Germany. IMPORT REQUIREMENTS To be considered eligible for installation on U.S. registered aircraft, each new engine to be exported to the United States with Luftfahrt-Bundesamt (Germany) or EASA airworthiness approval shall have a Joint Aviation Authorities (JAA) or EASA Form 1, Authorized Release Certificate. The JAA or EASA Form 1 should state that the engine conforms to the type design approved under the U.S. Type Certificate E2EU, is in a condition for safe operation and has undergone a final operational check. Additional guidance is contained in FAA Advisory Circular 21-23, “Airworthiness Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States.” TCDS E2EU PAGE 3 NOTES I. MODELS (SPEY) 506-14, 506- 14D 506-14A 555-15N, 555-15 555-15P, 555-15H 511-8, 511-8/ Mod 2970, 511-14 511-14W NOTE 1. Rotor Speed Limitations Low Pressure (LP) Rotor, % rpm Takeoff , dry (5 min.**) Takeoff, wet (5 min.) Maximum continuous Reverse thrust (30 sec.) *Overspeed (20 sec. Max.) 107.2/9,000 --- 107.2/9,000 105.5/8,855 110.2/9,250 107.8/9,050 - - 107.8/9,050 106.0/8,900 113.5/9,528 108.5/9,106 - - 108.5/9,106 (See Note 4) 115.5/9,694 109.5/9,190 - - - - - - - - 106.6/8,950 - - 106.6/8,950 106.6/8,950 110.0/9,230 - - 106.6/8,950 - - - - - - High Pressure (HP) Rotor, % rpm Takeoff , dry (5 min.**) Takeoff, wet (5 min.) Maximum continuous Reverse thrust (30 sec.) *Overspeed (20 sec. Max.) 99.7/12,450 --- 97.3/12,150 94.5/11,800 102.7/12,820 98.9/12,350 - - 97.0/12,109 94.5/11,800 103.2/12,880 101.0/12,257 - - 98.5/11,954 (See Note 4) 104.5/12,682 102.5/12,439 - - - - - - 105.5/12,803 100.1/12,500 - - 98.1/12,250 100.1/12,500 103.1/12,870 - - 101.0/12,600 - - - - 104.0/12,983 (Maximum permissible engine operating speeds for the engine rotors are as above, in which 100% HP = 12,136 rpm, and 100% LP = 8,393 rpm for Spey 555-15, -15N, =15H, and –15P; for all other models, 100% HP = 12,484 rpm and 100% LP = 8,393 rpm). *If these limits are exceeded the engine requires inspection in accordance with the Rolls-Royce Maintenance Manual. **See NOTE 15. NOTE 2. Temperature Limitations ( oC) Turbine gas temperature (mean of 10 thermocouples in exhaust cone with automatic compensation for intake temperature) (All 506-14A, 506-14D, 511-14W, 511-14, 511-8, 555-15, 555-15N, 555- 15H, and 555-15P engines incorporate approved trimmer resistors). 506-14 506-14A 506-14D 555-15N 555-15 555-15P 555-15H 511-14 511-14W 511-8 511-8/ Mod 2970** Takeoff, dry (5 min.***) *Max. for acceleration (2 min.) Takeoff, wet (5 min.) Max. continuous Max. for reverse thrust on ground (30 sec. Limit) Max. for ground idling Max. for starting & relights T.G.T. Overtemp (20 sec. Limit) Oil inlet (cont.) (15 min. operation) Fuel at HP pump inlet (cont.) (15 min. operation) 615 --- --- 575 615 575 615 630 100 120 90 110 600 --- --- 560 600 560 590 620 - - - - - - - - 570 - - --- 550 570 - - 570 585 - - - - - - - - 520 --- --- 490 --- 490 540 540 - - - - - - - - 565 --- --- 520 --- 520 570 585 - - - - - - - - 580 --- --- 540 580 540 570 595 - - - - - - - - - - --- 590 - - - - - - - - - - - - - - - - - - 585 --- --- - - - - - - - - 610 - - - - - - - - - - 595** --- - - - - - - - - 615** - - - - - - - - *Total combined time must not exceed 5 minutes ** See NOTE 12 *** See NOTE 15 NOTE 3. Fuel and Oil Pressure Limits Fuel Pressure: Measured at inlet to engine main pump. Minimum for operation: 12 p.s.i.a. or 6 p.s.i. above fuel tank pressure, whichever is lower, but not less than 2 p.s.i.g. Minimum for starting, Ground: 10 p.s.i.a. (Refer to RR HK31257, Issue 4). Oil Pressure: Normal 30 to 55 p.s.i.g. with minimum in flight of 25 p.s.i.g. at appropriate maximum continuous r.p.m. for 506 and 555 series, and 35 to 55 p.s.i.g. with minimum in flight of 30 p.s.i.g. for the 511-14 and –14W, 40 to 55 p.s.i.g. with a minimum in flight of 35 for the 511-8. TCDS E2EU PAGE 4 NOTE 4. The ratings are based on standard conditions 59 oF and 29.92” Hg Barometer, with no air bleed or power offtake, pw/po = .01 with turbine gas temperature within limits. Engine to be fitted with jet piper Part No. J88926 (or approved equivalent). Final nozzle J88931, test bed intake flare REP 23224. Test results are corrected to a fuel calorific value of 18550 BTU/lb. Thrust reverser unit Spey TR 504-14B for 506 series and TR 504-14C for 511-14 series. The 511-8 is fitted with a thrust reverser manufactured by ROHR. No thrust reverser is fitted to the Spey 555- 15 series. NOTE 5. ACCESSORY DRIVE PROVISIONS DRIVE Rotation Speed Ratio To Turbine TORQUE (lb - in) Max. Cont. Instantaneous Maximum Overhang (lb - in) Fuel Pump: Type GD: 111 (506-14 series) 119 (511-14, -14W; 511-8) 114 (555-15 series) Fuel Control: Type CASC: 105 (506-14 series) 112 (511-14) 116 or 146 (511-8) 133 (555-15, -15N) 211 (555-15H, 15P) Backing Pump: Type BP 230/6 H..P. Tacho KGA 2302 L.P. Tacho KGA 2302 CSD Plessey Type 220 (including starter) Sundstrand Type 20-AG-DO-2 for 555-15 series Starter AiResearch ATSV 100-1 for 555-15 series; 100-3 for 511-8 Alternator 976J-118-6 or 976J-119-6 Bendix 28B 153-76 for 511-8 Westinghouse 6QM 20D for 555-15 series Generator Bendix 30E 20-41A for 511-8 Hydraulic Pump: 61698-L8 61699-R8 Kellog AP-10V-60 for 511-8 Kellop AP-6V-35 & AP-1V-19 for 555-15 series CC CC CC CC CC CW CW CW CC CC CC CW CW CC CC CC CW 0.2504 .4780 .4263 .3364 .5004 XLP .3727 .5088 1.0398 6000 rpm constant .8005 8000 rpm constant .6707 .2639 .2639 .2614 .2615 .2445 500 10 30 7 7 1270 659 - 380 500 248 250 730 730 732 461 176 760 260 568 50.0 50.0 7200 5620 2981 6000 2310 2000 2310 3170 3170 3000 1400 500 132 120 30.6 3.2 3.2 1300 283.5 153.4 488 250 262.7 220 115.0 115.0 140 36.4 11.5 NOTES: CW = clockwise CC = counter-clockwise NOTE 6. These engines meet FAA requirements for icing protection, for adequate turbine disc integrity, for rotor blade containment and do not require external armoring. NOTE 7. Compressor air bleed may be used in accord ance with RR instructions such that the operating limitations are not exceeded up to maximum of 3.1% of the no bleed mass flow for HP bleed and 3.5% for the LP bleed for the 506-14, and 506-14D. 2.7% HP bleed and 3.3% LP bleed for 506-14A. 2.45% HP bleed and 3.65% LP bleed for the 511 series. TCDS E2EU PAGE 5 NOTE 7. (continued) For the Spey 555-15 series, the maximu m air bleed flows are given by the following nondimensional values: M 7 T1 M 12 T1 M T T1 P 1 P 1 P 1 Takeoff 6.45 7.4 13.85 Max. Cont. and below 6.25 6.9 13.15 Where T 1 = Total temperature at engine intake –oK P 1 = Total pressure at engine intake – p.s.i.a M 7 = Stage 7 bleed mass flow – lbs./sec. M 12 = Stage 12 and anti-icing bleed mass flow – lbs./sec. M T = Stage 7, stage 12 and anti-icing bleed mass flow – lbs./sec. NOTE 8. The maximum allowable thrust for below sta ndard and/or ram conditions for 5 minutes at T0 conditions, 10,500 lbs., for 555 series; 11,200 lbs. for the 506 series; 12,100 lbs. for the 511 series. The maximum thrust for both T0 and max. continuous conditions is automatically limited by the compressor delivery pressure limiter as shown in RR Performance Brochures. NOTE 9. Approved fuels and fuel additives are given in Rolls-Royce Operating Instructions for each model: 506-14, 506-14D 506-14A 511-14 511-14W 555-15, 555-15N, 555-15H, 555-15P 511-8 F-Sp3-B F-Sp3W-B F-Sp4-Bk F-Sp4W-B F-Sp2-F F-Sp4-G NOTE 10. Type numbers quoted for fuel control, ignite rs and igniter boxes are the basic standard. Later approved type numbers are quoted in the relevant RR Maintenance and Overhaul Manuals. NOTE 11. The above models incorporate the following general characteristics: MODEL RR RATING NUMBER CHARACTERISTICS SPEY 505-5 RB 163-1 Basic model for use in Trident. Approved March 6, 1964; withdrawn October 15, 1965, owing to non-applicability for US operators. 506-14 RB 163-2 Variant for installation in BAC 1-11 aircraft with appropriate installation features, and a higher rating. Added February 26, 1965. 506-14A RB 163-2 As 506-14AW but with water in jection features deleted. Added June 24, 1969. 506-14B RB 163-2 As 506-14, but with higher T0 limitations and 3% increased hot day thrust. Added October 15, 1965, and deleted on June 1, 1967, as model withdrawn. 506-14C RB 163-2 As 506-14, but with higher TO limitations and approximately 1- 1/2% increased TO thrust. Added March 11, 1968, and deleted June 10, 1985. 506-14AW RB 163-2W Variant with water injection for BAC 1-11 200 series approved February 26, 1965, withdrawn October 15, 1965, owing to non- applicability for US operators. 510-14 RB 163-25 Variant for BAC 1-11 400 se ries aircraft. Extra stage on LP compressor and 5.5% higher ratings than 506-14 engine. Added October 15, 1965, and deleted December 17, 1974. 511-14 RB 163-25 Variant for FAC 1-11 400 series with higher TO rating. Otherwise mechanically as 510-14. Added August 30, 1966. 511-8 RB 163-25 Variant of the Spey RB 163-25 for installation in the Grumman Gulfstream II aircraft, and with installation changes to suit this aircraft. Added on June 1, 1967. 555-15 RB 183 Variant of the Spey 506-14AW, but de-rated and with various lightening features. No water injection system and with installation features to suit the Fokker F-28 aircraft. Added December 20, 1968. 506-14D RB 163-2 As 506-14 but featuring trimmed TGT limitations. Added April 19, 1971. 511-14W RB 163-25W As 511-14 with water in jection features. Added May 11, 1973. 511-8/Mod 2970 RB 163-25 Same as 511-8 except fo r higher temp turbine blades (Mod 2970). Added December 17, 1974. TCDS E2EU PAGE 6 NOTE 11. (continued) 555-15H RB 183 Variant of Spey 555-15. Higher takeoff and maximum continuous limitations. Added March 3, 1980. 555-15N RB183 As 555-15 but with redesigned exhaust mixer for improved silencing. Added October 26, 1981. 555-15P RB 183 As 555-15H but with redesigned exhaust mixer for improved silencing. Added October 26, 1981. NOTE 12. T.G.T. limits of 595 oC for 2 minutes acceleration and 615oC for 20 second overtemperature apply only to Spey Mk.511-8 engines of Modification No. 2970 standard or approved equivalent. For Spey Mk.511-8 engines incorporating Modification No. 2970 or the approved equivalent, the engine Data Plate shall be marked in accordance with Rolls-Royce Service Bulletin Sp. 77-43. NOTE 13. Life-limited parts are identified in the Spey Overhaul Manual, Section 5-10. NOTE 14. The following engines comply with the applicab le exhaust emission and fuel venting requirements of SFAR 27-5 and 40 CFR 87: a. MK555/mod 6122, mod 6123 b. MK 511-8/mod 6121 c. Certain Spey engines are exempted form 40 CFR 87.21 by exemption number 4040A, dated February 7, 1985. d. Certain model MK555-15 engines are exempted from 40 CFR 87.21 by exemption number 3913, dated January 25, 1984. NOTE 15. For the Spey 555 series engines only, the ta ke-off rating and its associated operating limitations may be used for up to 10 minutes in the event of engine out contingency, but their use is otherwise limited to not more than 5 minutes. NOTE 16. Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or, for approvals made before September 28, 2003 by Luftfahrt-Bundesamt (Germany) or CAA (UK). Any such documents including those approved under a delegated authority, are accepted by the FAA and are considered FAA approved. • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. • Technical Variances These approvals pertain to the type design only. ----END---- ``` ## ADs (14, in force first) - [AD 2017-10-25](https://openairdocs.org/ad/2017-10-25): Turbine Engine Compressor · Rolls-Royce Deutschland Spey 506-14A, Spey 555-15, Spey 555-15H and 2 more. Effective Jun 12, 2017 - [AD 2013-05-20](https://openairdocs.org/ad/2013-05-20): Bolts · Rolls-Royce Deutschland Spey 511-8. Effective Apr 24, 2013 - [AD 2004-24-05](https://openairdocs.org/ad/2004-24-05): Split low pressure (LP) compressor case · Rolls-Royce Deutschland Spey 555-15, Spey 555-15H, Spey 555-15N and 1 more. Effective Dec 29, 2004 - [AD 2002-18-03](https://openairdocs.org/ad/2002-18-03): Stage 2 LPT Blades · Rolls-Royce Deutschland Spey 506-14A, Spey 555-15, Spey 555-15H and 2 more. Effective Oct 16, 2002 - [AD 2000-23-11](https://openairdocs.org/ad/2000-23-11): Disk Drive Arm · Rolls-Royce Deutschland Spey 555-15, Spey 555-15H, Spey 555-15N and 1 more. Effective Dec 20, 2000 - [AD 94-25-09](https://openairdocs.org/ad/94-25-09): High Pressure Compressor Disk · Rolls-Royce Deutschland Spey 506-14, Spey 506-14A, Spey 506-14D and 6 more. Effective Feb 17, 1995 - [AD 94-23-09](https://openairdocs.org/ad/94-23-09): High Pressure Compressor Disks · Rolls-Royce Deutschland Spey 506-14, Spey 506-14A, Spey 506-14D and 6 more. Effective Jan 6, 1995 - [AD 87-18-07](https://openairdocs.org/ad/87-18-07): Primary Airscoop · Rolls-Royce Deutschland Spey 506-14, Spey 506-14A, Spey 506-14D and 8 more. Effective Sep 28, 1987 - [AD 86-11-03](https://openairdocs.org/ad/86-11-03): Stage 12 HPC Disks And Rotor Seals, And LPC Drive Shafts · Rolls-Royce Deutschland Spey 555-15, Spey 555-15H, Spey 555-15N and 1 more. Effective Jun 20, 1986 - [AD 78-16-07](https://openairdocs.org/ad/78-16-07): High Pressure Fuel shutoff Valves · Rolls-Royce Deutschland Spey 511-8. Effective Aug 21, 1978 - [AD 72-20-07](https://openairdocs.org/ad/72-20-07): Fuel Tubes · Rolls-Royce Deutschland Spey 555-15, Spey 555-15H, Spey 555-15N and 1 more. Effective Oct 2, 1972 - [AD 68-17-05](https://openairdocs.org/ad/68-17-05): Air System Center Section Duct · Rolls-Royce Deutschland Spey 506-14, Spey 511-14 and Spey 511-8. Effective Jun 28, 1972 - [AD 67-22-08](https://openairdocs.org/ad/67-22-08): Fuel Flow Controls · Rolls-Royce Deutschland Spey 506-14. Effective Aug 25, 1967 - [AD 67-08-06](https://openairdocs.org/ad/67-08-06): Fuel Tube Clamps · Rolls-Royce Deutschland Spey 506-14 and Spey 511-14. Effective Aug 1, 1967 ## Registered aircraft by registry model (OpenAirDocs) - [Rolls-Royce SPEY-511-8](https://openairdocs.org/engine/rolls-royce-spey-511-8): 15 aircraft (registry code 54069) - [Rolls-Royce SPEY-506-14](https://openairdocs.org/engine/rolls-royce-spey-506-14): 1 aircraft (registry code 54519) - [Rolls-Royce SPEY-506-14A](https://openairdocs.org/engine/rolls-royce-spey-506-14a): 0 aircraft (registry code 54062) - [Rolls-Royce SPEY-506-14D](https://openairdocs.org/engine/rolls-royce-spey-506-14d): 0 aircraft (registry code 54063) - [Rolls-Royce SPEY-511-14](https://openairdocs.org/engine/rolls-royce-spey-511-14): 0 aircraft (registry code 54067) - [Rolls-Royce SPEY-511-14W](https://openairdocs.org/engine/rolls-royce-spey-511-14w): 0 aircraft (registry code 54068) - [Rolls-Royce SPEY-511-8MOD](https://openairdocs.org/engine/rolls-royce-spey-511-8mod-series): 0 aircraft (registry code 54070) - [Rolls-Royce SPEY-555-15](https://openairdocs.org/engine/rolls-royce-spey-555-15): 0 aircraft (registry code 54521) - [Rolls-Royce SPEY-555-15H](https://openairdocs.org/engine/rolls-royce-spey-555-15h): 0 aircraft (registry code 54066) - [Rolls-Royce SPEY-555-15N](https://openairdocs.org/engine/rolls-royce-spey-555-15n): 0 aircraft (registry code 54064) - [Rolls-Royce SPEY-555-15P](https://openairdocs.org/engine/rolls-royce-spey-555-15p): 0 aircraft (registry code 54065) ## STCs approved under this data sheet (3) - [STC SE01291LA](https://openairdocs.org/stc/SE01291LA): Installation of a Really Quiet LLC Internal Mixer Part Number RQ720100T, Revision B, dated January 25, 2000, or later FAA approved revisions, in accordance with Installation Instructions RQ73-3000-401/-402, Revision C, dated January 9, 2002, or later FAA approved revisions. This installation must be done concurrently with STC No. ST01292LA which modifies the airplane engine installation.. Global United Capital LLC - [STC SE994EA](https://openairdocs.org/stc/SE994EA): Manufacture of oil tank sight gage float.. Airwork Service Division - [STC SE748EA](https://openairdocs.org/stc/SE748EA): Installation of GLA ignition exciter.. General Laboratory Association Inc. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.