TCDS A21EU

A21EU Page 1 of 12 Page No. 1 2 3 4 5 6 7 8 9 10 11 12 Rev. No. 21 8 9 13 13 12 15 20 18 18 16 17 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A21EU Revision 21 British Aerospace (Operations) Limited HP.137 Jetstream Mk.1 Jetstream Series 200 Jetstream Series 3101 October 13, 2021 TYPE CERTIFICATE DATA SHEET No. A21EU This data sheet, which is a part of Type Certificate No. A21EU prescribes conditions and limitations under which the product for which the type certificate was issued, meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder. British Aerospace (Operations) Limited (trading as) British Aerospace Regional Aircraft Prestwick International Airport Ayrshire KA9 2RW Scotland I. Model HP.137 Jetstream Mk.1 (Normal Category), approved April 25, 1969. (See NOTE 7). Type Certificate Ownership Record (1) The EASA TC for this model was surrendered to the state of design on January 24, 2008 and is no longer valid. Only standard airworthiness certificates issued prior to January 1, 2014 are valid. (2) Future unsafe conditions existing in the aircraft may result in the revocation of the airworthiness certificates of the aircraft if there is no entity to comply with 14 CFR § 21.99(a), “Required design changes.” (3) Replacement parts may not be available in the future. Engine. 2 Turbomeca Astazou XIVC or XIVC1 (Propeller Turbine) or 2 Turbomeca Astazou XVIF1 (Propeller Turbine) (ADA MOD. 040/137) (See NOTE 5). Fuel. American British French NATO ASTM Jet A or A1 or D.Eng.RD 2453 or 2494 or AIR 3405 or F34 or F35 *ASTM Jet B or JP-4 *or D.Eng.RD 2454 or 2486 or AIR 3407 *or F40 or F45 (MIL-T-5624) JP-5 (MIL-T-5624) or D.Eng.RD.2498 or AIR 3404 or F42 or F44 * Not usable for airplanes with MOD.NO.5168 (Specifications as revised) Oil. American British French NATO (Engine & Gearbox) MIL-L-7808 - or AIR 3513 or 3514 or 0-148 or 0-150 - D.Eng.RD 2487 or AIR 3517 or 0-149 or 0-159 - D.Eng.RD 2490 or AIR 3515 or 0-135 MIL-L-23699 - - or 0-156 Specifications as revised) Engine Limits. Static Ratings The static ratings for the Astazou engines are specified under the following test conditions. A21EU Page 2 of 12 Page No. 1 2 3 4 5 6 7 8 9 10 11 12 Rev. No. 21 8 9 13 13 12 15 20 18 18 16 17 International Standard Atmospheric Conditions at Sea Level. Calibrated slave air intake duct (TURBOMECA 6 103 43 905 0) Short and straight slave exhaust diffuser, outlet diameter 8.98 in. (228 mm) All optional air bleeds closed. Aircraft Service accessory drive unloaded. 43089 engine RPM. Astazou XIVC and XIVCI Shaft Horse Power Jet Thrust (lb) Torquemeter Reading (%) Indicated RPM (%) Specific Fuel Consumption (lb/shp/hr) Jet Pipe Temp.(EGT) °C Conditions Takeoff Max. Cont. 776 699 123.5 121.0 98.5 88.5 98.7 98.7 0.562 0.582 500 480 Astazou XIVC and XIVCI Shaft Horse Power Jet Thrust (lb) Torquemeter Reading (%) Indicated RPM (%) Specific Fule Consumption (lb/shp/hr) Jet Pipe Temp.(EGT) °C Conditions Takeoff Max. Cont. 839 786 137.5 136.5 103.6 97.0 98.7 98.7 0.558 0.569 585 540 Engine Limits. All new and overhauled engines must meet the above acceptance limits. See ARB Approved Flight Manual, DOC. HP.4.3 for additional engine operating Limitations. (See NOTE 5). Propeller and Propeller Limits. 2 Hamilton Standard reversible propellers Type 23LF-335, 23LF-373, or 23LF-371 for ADA MOD 040/137 only. Blades : 3 Type 1017 Diameter : 8 ft. 6 in. (No reduction permitted) Pitch settings at 42 in. station: Ground - 5.5 Flight Fine + 7 ± ½ Feathered + 80 Full Reverse - 14 (with Modification 1331 embodied -10) Airspeed Limits. (Maximum Operating Speed) W/O MOD.NO.5168 With MOD.NO.5168 embodied See NOTE 7 VMO up to 18000 ft. 215 knots up to 19000 ft 220 knots at 20000 ft. 205 knots at 25000 ft. 180 knots at 25000 ft 190 knots VA (Maneuvering Speed) 170 knots 174 knots VFE (Flaps Extended Speed) Takeoff 156 knots 162 knots Landing 50° Down 120 knots 120 knots VLE (Landing Gear Extended Speed) 156 knots 162 knots VLO (Landing Gear Operating Speed) 156 knots 162 knots VMC (Minimum Control Speed) 88 knots 88 knots C.G. Limits. (+ 213.5 in.) to (+ 228 in.) at 11,000 lb, or less (Landing Gear Extended) (+ 215.0 in.) to (+ 228 in.) at 12,500 lb. (+ 215.0 in.) to (+ 228.0 in.) at 13,230 lbs. Straight line variation between points given. Moment change (Landing Gear Retraction) -4550 lb. in. (moves C of G forward) A21EU Page 3 of 12 Page No. 1 2 3 4 5 6 7 8 9 10 11 12 Rev. No. 21 8 9 13 13 12 15 20 18 18 16 17 Datum. Fuselage station “0” (140 inches fwd of marked “cowling type” screw on fuselage bottom). Leveling Means. Leveling Marks provided on fuselage seat rails. At station 225.5 left and right At station 252.5 right only. Maximum Weight. W/O MOD. NO. 5168 WITH MOD.NO.5168 Takeoff 12,500 lb. 13,230 lbs. Zero Fuel 12,500 lb. 12,500 lbs. Minimum Crew. 1 pilot 1 pilot Maximum Passengers. 18 19 Maximum Baggage. 550 lb. (+ 391.3 in.) Fuel Capacity. 461 U.S. Gals. in 2 tanks (+ 226.2 in.) 459 U.S. Gals. usable. (See NOTE 1 for data on system fuel). Oil Capacity. 2.1 U.S. Gals./tank on each engine (+ 167 in.) 1.3 U.S. Gals./tank usable. (See NOTE 1 for data on system oil). Max. Operating Altitude. 25,000 ft. Control Surface Movements. Elevator 28° Up 22° Down Elevator Trim Tab 5° Up 13° Down Rudder 25° Right 25° Left) Measure relative Rudder Trim Tab 20° Right 20° Left) to aircraft datum Aileron 25° Up 15° Down Aileron Trim Tab 8.5° Up 8.5° Left side only Flaps Landing 50° Down Takeoff 20° Down Lift Dump 70° Down II. Jetstream Series 200 (Normal Category), approved May 17, 1977. Engine. 2 Turbomeca Astazou XVICI or XVIF (Propeller turbine). These engines are not interchangeable. Fuel. American British French NATO ASTM Jet A or A1 or D.Eng.RD 2453 or 2494 or AIR 3405 or F34 or F35 ASTM Jet B or JP-4 or D.Eng.RD 2454 or 2486 or AIR 3407 *or F40 or F45 (MIL-T-5624) JP-5 (MIL-T-5624) or D.Eng.RD.2498 or AIR 3404 or F42 or F44 (Specifications as revised) Oil. American British French NATO (Engine & Gearbox) MIL-L-7808 - or AIR 3513 or 3514 or 0-148 or 0-150 - D.Eng.RD 2487 or AIR 3517 or 0-149 or 0-159 - D.Eng.RD 2490 or AIR 3515 or 0-135 MIL-L-23699 - - or 0-136 (Specifications as revised) Page 4 of 12 A21EU Engine Limits. Static Ratings The static ratings for the Astazou engines are specified under the following test conditions. International Standard Atmospheric Conditions at Sea Level. Calibrated slave air intake duct (TURBOMECA 6 103 43 905 0) Short and straight slave exhaust diffuser, outlet diameter 8.98 in. (228mm) All optional air bleeds closed. Aircraft service accessory drives unloaded. 43089 engine RPM. Engine Limits. Astazou XVIC1C and XVIF (Continued) Shaft Horse Power Jet Thrust (lb) Torquemeter Reading (%) Indicated RPM (%) Specific Fuel Consumption (lb/shp/hr) Jet Pipe Temp.(EGT) °C Conditions Takeoff Max. Cont. 912 785 141.6 139.4 97.3 83.7 98.7 98.7 0.558 0.579 585 540 All new and overhauled engines must meet the above acceptance limits. See CAA Approved Flight Manual, Doc. HP.4.8 for additional engine Operating Limitations. Propeller and Propeller Limits. 2 Hamilton Standard Type 23LF-371 reversible propellers. (Clarification) Blades : 3 Type 1017 Diameter : 8 ft. 6 in. (No reduction permitted) Pitch settings at 42 in. station: Ground - 5.5° Flight Fine + 7° ± 0.5° Feathered + 80° Full Reverse - 14° Airspeed Limits. (Maximum Operating Speed) VMO up to 18,000 ft. 215 knots at 25,000 ft. 180 knots VA (Maneuvering Speed) 170 knots VFE (Flaps Extended Speed) Takeoff 156 knots Landing 50° Down 120 knots VLE (Landing Gear Extended Speed) 156 knots VLO (Landing Gear Operating Speed) 156 knots VMC (Minimum Control Speed) 89.5 knots C.G. Limits. (+ 213.5 in.) to (+ 228 in.) at 11,000 lb, or less (Landing Gear Extended) (+ 215.0 in.) to (+ 228 in.) at 12,500 lb. Straight line variation between points given. Moment change (Landing Gear Retraction) -4550 lb. in. (moves C of G forward) Datum. Fuselage station “0” (140 inches fwd of marked “cowling type” screw on fuselage bottom). Page 5 of 12 A21EU Leveling Means. Leveling Marks provided on fuselage seat rails. At station 225.5 left and right At station 252.5 right only. Maximum Weight. Takeoff 12,500 lb. Zero Fuel 12,250 lb. Minimum Crew. 1 pilot Maximum Passengers. 18 Maximum Baggage. 550 lb. (+ 391.3 in.) Fuel Capacity. 461 U.S. Gals. in 2 tanks (+ 226.2 in.) 459 U.S. Gals. usable. (See NOTE 1 for data on system fuel). Oil Capacity. 2.1 U.S. Gals./tank on each engine (+ 167 in.) 1.3 U.S. Gals./tank usable. (See NOTE 1 for data on system oil). Max. Operating Altitude. 25,000 ft. Control Surface Movements. Elevator 28° Up 22° Down Elevator Trim Tab 5° Up 12° Down Rudder 25° Right 25° Left (Measure relative) Rudder Trim Tab 25° Right 25° Left (to aircraft datum) Aileron 24° Up 15° Down Aileron Trim Tab 8.5° Up 8.5° Down (Both sides) Flaps Landing 50° Down Takeoff 20° Down Lift Dump 70° Down III. Jetstream Model 3101 (Normal Category), approved November 30, 1982. The Jetstream Model 3101 is same as Jetstream Series 200 except for: 1) turbopropeller engines; 2) propeller; 3) powerplant control and indications; 4) electrical generation and distribution; 5) air conditioning; 6) passenger cabin; 7) increased overall structural strength; 8) increased design weights and speeds; 9) certification basis Engine. 2 Airesearch TPE 331-10UF-501H turbopropeller or TPE 331-10UF-511H (BAe Mod 7300) or TPE 331-10UF-512H (BAe Mod 7356) or TPE 331-10UF-513H (BAe Mod 7357) or TPE 331-10UR-513H (BAe Mod 7379) or TPE 331-10UG-513H (BAe Mod 7432) (See Note 9) or TPE 331-10UGR-513H (BAe Mod 7434) (See Note 9) or TPE 331-10UGR-514H (BAe Mod 7547) (See Note 9) or TPE 331-10UG-514H (BAe Mod 7548) (See Note 9) Both engines must have same model number (See Note 10) Page 6 of 12 A21EU Fuel. American British NATO ASTM Jet A - - ASTM Jet A1 or D.Eng.RD 2494 or F35 MIL-T-83133,JP8* or D.Eng.RD 2453* or F34* Fuel marked thus * contain fuel system icing inhibitor (FSII) and no further additions shall be made. (Specifications as revised) Oil. MIL-L-23699B (Engine and Gearbox) (Specifications as revised) Engine Limits. Static Ratings The static ratings for the Airesearch engines are based on the conditions specified on TCDS E4WE. Engine Limits. Shaft Horse Prop Shaft Exhaust Gas Power (SHP) Speed (RPM) Temp. (EGT) Single Red Line (°C) Conditions Takeoff 940* 1591 650 Maximum Cont. 900 1591 650 Starting - - 770 * For airplane incorporating BAe MOD 7340, otherwise 900 SHP. All new and overhauled engines must meet the above acceptable limits. See CAA Approved Flight Manual, Doc. HP.4.10 for additional engine Operating Limitations. Propeller and Propeller Limits. 2 Dowty Rotol (c) R.333/4-82-F/12 Blades : 4 Diameter : 106 inches (No reduction permitted) Pitch angles at Section J-J setting line: Start Locks - 1° 45’ + 0° 30’ Flight Idle + 9° + 0° 30’ Feathered + 82° 20’ ± 0° 20’ Reverse - 13° + 0° 30’ Airspeed Limits. VMO (Maximum Operating Speed) Without MOD 7380 With MOD 7380 up to 16,750 ft. 230 knots up to 18,300 ft. 223 knots at 25,000 ft. 194 knots 194 knots VA (Maneuvering Speed) 180 knots 176 knots VFE (Flaps Extended Speed) Takeoff 10° Down 177 knots 172 knots Approach 20° Down 168 knots 164 knots Landing (pre Mod 7760) 50° Down 130 knots 130 knots Landing (post Mod 7760) 35° Down 149 knots 153 knots Lift Dump 70° Down 100 knots 100 knots VLE (Landing Gear Extended Speed) 168 knots 164 knots VLO (Landing Gear Operating Speed) 168 knots 164 knots VMC (Minimum Control Speed) Takeoff (Flaps 10°) 92 knots 92 knots Approach (Flaps 20°) 90 knots 90 knots For airplane with Mod 7340: Approach (Flaps 20°) 94 knots 94 knots Page 7 of 12 A21EU C.G. Limits. (+ 213.5 in.) to (+ 226 in.) at 11,000 lb, or less (Landing Gear Extended) (+ 217.2 in.) to (+ 226 in.) at 14,550 lb. for airplanes without BAe MOD 7380 (+ 217.8 in.) to (+ 226 in.) at 15,212 lb. for airplanes with BAe MOD 7380 Aft C.G. limit is 227.5 in. at all weights for airplanes with BAe MOD 7362. Straight line variation between points given. Moment change (Landing Gear Retraction) -4450 lb. in. (moves C of G forward) Datum. Fuselage station “0” (140 inches fwd of marked “cowling type” screw on the bottom surface of fuselage). Leveling Means. Leveling marks provided on fuselage seat rails. At station 225.5 left and right At station 252.5 right only. Maximum Weight. Without MOD 7380 With MOD 7380 Ramp 14,660 lb. (6650 Kg) 15,322 lb. (6950 kg) Takeoff 14,550 lb. (6600 Kg) 15,212 lb. (6900 kg) Zero Fuel 13,228 lb. (6000 Kg) 13,668 lb. (6200 kg) (Pre-Mod 7456) Zero Fuel - 13,889 lb. (6300 kg) (Pre-Mod 7456) Zero Fuel - 14,300 lb. (6486 kg) (Post-Mod 7846) Landing 14,550 lb. (6600 Kg) 14,550 lb. (6600 kg) (Pre-Mod 7713) Landing - 14,900 lb. (6759 kg) (Pre-Mod 7713) Minimum Crew. 2 pilots Maximum Crew. 2 (See NOTE 4) Maximum Passengers. 19 (See NOTE 4) Maximum Baggage. 661 lb. (+ 380.0 in.) Fuel Capacity. 461 U.S. Gals. in 2 tanks (+ 226.2 in.) 451 U.S. Gals. usable. (See NOTE 1 for data on system fuel). Oil Capacity. 1.56 U.S. Gals./tank in each engine compartment (+ 179.8 in.) 1.50 U.S. Gals./tank usable. (See NOTE 1 for data on system oil). Max. Operating Altitude. 25,000 ft. Control Surface Movements. Elevator 28° Up 22° Down Elevator Trim Tab 5° Up 7.5° Down (For airplane without BAe MOD 7362) 8.5° Down (For airplane wit BAe MOD 7362) Rudder 25° Right 25° Left Rudder Trim Tab 25° Right 25° Left Aileron 25° Up 15° Down Aileron Trim Tab 8.5° Up 8.5° Down Flaps Takeoff 10° Down Approach 20° Down Landing 50° Down (Pre Mod 7760) Landing 35° Down (Post Mod 7760) Lift Dump 70° Down Page 8 of 12 A21EU DATA PERTINENT TO ALL MODELS Serial Nos. Eligible. The United Kingdom Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft for which application for certification is made. Model HP.137 Jetstream Mk.1: Only those aircraft serials holding a standard airworthiness certificate issued prior to January 1, 2013 are eligible. Import Requirements. A United States Airworthiness Certificate may be issued on the basis of a United Kingdom Certificate of Airworthiness for Export signed by a representative of the United Kingdom Civil Aviation Authority containing the following statement: “The airplane covered by this certificate has been examined, tested and found to conform to the 14 CFR Part 23 design approved under US Type Certificate A21EU and is in a condition for safe operation.” (See NOTE 6). Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft Model HP.137 Jetstream Mk.1:None eligible after January 1, 2013. Certification Basis. For Models HP.137 Jetstream Mk 1 and Jetstream Series 200 (See NOTE 7). FAR 21.29 and FAR 23, effective February 1, 1965, including Amendments 23-1 through 23-3, plus Special Conditions notified by the U.S. Government to the Government of the United Kingdom in FAA letter of October 30, 1967. Compliance has been demonstrated with the requirements of 14 CFR Section 25.1419: Ice Protection. Date of Application for original Type Certificate: February 15, 1966. Request for extension granted in accordance with FAR 21.17(b)(2). Date of application for amended Type Certificate Jetstream Series 200: November 22, 1973. Compliance has been demonstrated with the Special Federal Aviation requirements SFAR-41C effective September 13, 1982 (See NOTE 7). Date of application for amended Type Certificate Model HP.137 Jetstream MK1 Mod 5168-SFAR-41C: May 11, 1981. The United Kingdom CAA originally type certificated this aircraft under is type certificate Number BA15. The FAA validated this product under U.S. Type Certificate number A21EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the United Kingdom CAA. For Jetstream Model 3101: FAR 21.29 and FAR 23, effective February 1, 1965 including Amendments 23-1 through 23-3. Special Conditions notified by the U.S. Government to the Government of the United Kingdom in FAA letter of October 30, 1967. Special Federal Aviation Regulation No. 41, effective October 17, 1979 including Amendments 41-A and 41-C. Federal Aviation Administration Exemption No. 3548, issued on June 10, 1982. Page 9 of 12 A21EU Special Federal Aviation Regulation No. 27, effective February 1, 1974, including Amendments 27-1 through 27-4 (Fuel Venting). - The Airesearch TPE 331 approved engines comply with the fuel venting emission requirements of SFAR 27 with the installation of Garrett Fuel Manifold Purge System Kit No. 3101458-1. FAR 36, effective December 1, 1969, including Amendments 36-1 through 36-12. Compliance was demonstrated to the following FAR 25 requirements in effect of 8 May 1970, in lieu of the FAR 23 ground load and landing gear requirements. FAR Sections 25.471, 25.473, 25.477, 25.479, 25.481, 25.483, 25.485, 25.487, 25.489, 25.491, 25.493, 25.495, 25.499, 25.503, 25.507, 25.509, 25.511, 25.573, 25.723, 25.725, 25.727, 25.729 (in effect on 7 May 1970), 25.731, 25.733 and 25.735. Compliance has been demonstrated with the requirements of 14 CFR Section 25.1419: Ice Protection. Compliance has been demonstrated with the requirements of FAR Sections 23.253, 23.335(b)(4), 23.1505(c) and 23.1545(d), as amended by Amendment 23-7. Compliance has been demonstrated with the requirements of Special Federal Aviation Regulations SFAR-41c when supplements are incorporated into the Flight Manual Document No. HP.4.10 (See NOTE 6). Compliance has been demonstrated with FAA Special Conditions Reference 23/ACE/9 effective 1 February 1985, when BAe MOD Kit 3299, Automatic Performance Reserve (with BAe MOD. No. 7376), or BAe MOD KIT 3359/1: Automatic Performance Reserve (with BAe MODS No. 7376 and 7472) have been embodied and when Supplement No. 4 is incorporated into Flight Manual Doc. No. HP.4.10. Date of Application for amended Type Certificate Jetstream Model 3101: February 21, 1980. Type Certificate No. A21EU issued April 25, 1969 for the HP.137 Jetstream Mk 1, amended May 17, 1977 for the Jetstream Series 200, and amended November 30, 1982 for the Jetstream Model 3101, and amended April 19, 1985 for Mod. No. 5168. Certification basis for the water-methanol systems BAe MOD KIT 3147/2 and BAe MOD KIT 3358 is as follows (See NOTE 8). 23.901(a) and (d); 23.903 (a)(1) and (c); 23.1041; 23.1141(a); 23.1143(a),(b),(c),(d), and (e); 23.1182; 23.1183(a); 23.1189(a)(1),(a)(4),(a)(5),(a)(6), and (c); 23.1301; 23.1309 (a) and (b) effective March 26, 1984, and 25.945 effective May 2, 1977. FAR Part 135 Appendix A Sections 4(e) and (g); 5; 6(b) and (c); 18, 19(b); 20(a)(b), (d)(e), and (f); 35(a), (c), (d) and (h); 38(a)(1) and (a)(3); 46; 59; 60; 63(b) and 64. SFAR 41C section 5(h). The United Kingdom CAA originally type certificated this aircraft under is type certificate Number BA6. The FAA validated this product under U.S. Type Certificate number A29EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the United Kingdom CAA. Service Information. Service Information. The Type Certificate for HP.137 Jetstream Mk.1, Jetstream Series 200 and Jetstream Model 3101 (Series 3100) is held by BAE SYSTEMS (Operations) Ltd. of PrestwickInternational Airport. Flight Manuals, Overhaul and Maintenance Manuals, Pilot’s or Crew or Manufacturer’s Operating Manuals, Structural Repair Manuals, Service Bulletins, Vendor Manuals, including amendments thereto, and related documents, issued in respect of HP.137 Jetstream Mk.1 and/or Jetstream Series 200 Page 10 of 12 A21EU and/or Jetstream Model 3101 (Series 3100) by either Handley Page Limited, or Handley Page Aircraft Limited, or Scottish Aviation Limited, or British Aerospace - Aircraft Group - Scottish Division, or British Aerospace PLC -Aircraft Group - Scottish Division, or British Aerospace PLC - Aircraft Group – Civil Division - Prestwick, or British Aerospace PLC - Civil Division - Prestwick, or British Aerospace PLC - Civil Aircraft Division - Prestwick, or British Aerospace (Commercial Aircraft) Limited - Airlines Division - Prestwick, or British Aerospace Regional Aircraft Limited - Prestwick, or Jetstream Aircraft Limited or BAE SYSTEMS (Operations) Ltd., which contain a statement that the document is ARB or CAA approved, or ARB or CAA approved through the Manufacturer’s ARB or CAA Approval Ref. AD/1039/39 or DAI/8208/71 or AD/1051/44 or DAI/1743/44 or DAI/1011/55 or DAI/9386/92 or JAA JAR 21 Approval Ref. CAA.JA02034, are accepted by the FAA and are considered FAA approved. These approvals pertain to the type design only. 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 the United Kingdom CAA. • Service bulletins, • Structural repair manuals, • Vender manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. The FAA accepts such documents and considers the FAA -approved unless on of the following conditions exits: • The documents change the limi tations, performance, or procedures of the FAA approved manuals: or • The documents make an acoustical or emissions change to this product’s U. S. type certificate as defined in 14 CFR 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case-by -case to EASEA to approve on Behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. Design changes that are contained in BAE SYSTEMS Service Bulletins and that are classified as Level 1 Major in accordance with either the US/UK or US/EASA Bilateral Aviation Safety Agreement Implementation Procedures for Airworthiness must be approved by the FAA. Airframe mandatory inspections and component life limits resulting from investigations