TCDS A13NM

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Rev. No. 24 15 18 18 13 22 15 13 18 19 23 21 20 23 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A13NM Revision 24 De Havilland Aircraft of Canada Limited DHC-8-100 Series DHC-8-200 Series DHC-8-300 Series DHC-8-400 Series October 19, 2026 TYPE CERTIFICATE DATA SHEET NO. A13NM This data sheet, which is a part of Type Certificate No. A13NM, 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 De Havilland Aircraft of Canada Limited 4100 Westwinds Drive NE Calgary, Alberta Canada T3J 4L2 Type Certificate Holder Record Bombardier Inc. 123 Garratt Boulevard Downsview, Ontario Canada M3K 1Y5 1. DHC-8-100 Series (see Note 5) Model -101 - Approved Dec. 11, 1984, by the FAA and Sept . 28, 1984, by the Canadian Department of Transport Model -102 - Approved Aug. 7, 1986, by the FAA and June . 12, 1986, by the Canadian Department of Transport Model -103 - Approved Nov. 30, 1988, by the FAA and July . 20, 1987, by the Canadian Department of Transport Model -106 - Approved Dec. 10, 1993, by the FAA and Nov. 20, 1992, by the Canadian Department of Transport Data Pertinent to all Models Except as Indicated Engines 2-Pratt & Whitney Canada, Inc., PW120 or PW120A (-101) 2-Pratt & Whitney Canada, Inc., PW120A or PW121 (-102) 2-Pratt & Whitney Canada, Inc., PW121 (-103) 2-Pratt & Whitney Canada, Inc., PW121 (-106) (See Data Pertinent to All Models Except as Indicated) Fuel ASTM D1655 Jet A, Jet A1, Jet B, MIL-DTL-5624 JP-4 & JP-5, and MIL-DTL-83133 JP- 8 conforming to Pratt and Whitney Canada, Inc. Specification No. CPW 204 Oil Oils conforming to Pratt and Whitney Canada, Inc. Specification No. PWA 521 Type II (MIL-L-23699). Engine Limits See AFM as listed under Approved Publications A13NM Page 2 of 14 Propeller and Propeller Limits 2-Hamilton Standard Model 14SF-7 Blade SFA13( )-0A Diameter 3.96M (13 Ft) Pitch settings at 0.75 radius: Feather 77.5 o Flight fine 10.5 o Ground fine -5.5 o Full reverse -18.5 o Propeller (Np) - Takeoff 1212 r.p.m. Max Continuous 1212 r.p.m. (See Data Pertinent to All Models Except as Indicated) Knots m.p.h. Airspeed Limits V MO(Maximum operating) 0 to 14000 ft 242 279 (IAS) 15000 ft 239 275 20000 ft 223 257 25000 ft 207 238 V FE (Flaps extended) Flaps 5 o 148 170 Flaps 15 o 148 170 Flaps 35 o 130 150 V A (Maneuvering) (-101, -102, -103) 163 188 V A (Maneuvering)(-106) 164 189 V LO (Landing gear operation) 158 182 V LE (Landing gear extended) 172 198 V B (Rough Air) 180 207 Landing Gear Doors Open Operative 140 161 Speed (Max. speed for operation following an alternate landing gear extension) V MCA (Minimum control speed) Flaps 5 o 79 91 15 o 75 86 Maximum Weight DHC-8-101 Take-off weight 14,970 kg (33,000 lb) (Mass) DHC-8-102 Take-off weight 15,649 kg (34,500 lb) DHC-8-103 Take-off weight 15,649 kg (34,500 lb) 15,966 kg (35,200 lb) (With MODSUM 8Q420649 incorporated) DHC-8-106 Take-off weight 16,466 kg (36,300 lb) (For other weights see AFM as listed under Approved Publications) CG Limits See AFM as listed under Approved Publications Maximum Baggage 454 kg (1000 lb) (See Weight and Balance Manual for mixed passenger cargo configuration) 907 kg (2000 lb) with Mod 8/0063 or 8/0083 Page 3 of 14 A13NM 2. DHC-8-200 Series Model -201 - Approved January 4, 1996, by the FAA and A ugust_24, 1995, by the Canadian Department of Transport Model -202 - Approved April 19, 1995, by the FAA and Marc h 9, 1995, by the Canadian Department of Transport Engines 2-Pratt & Whitney Canada, Inc., PW123C (201) 2-Pratt & Whitney Canada, Inc., PW123D (202) (See Data Pertinent to All Models Except as Indicated) Fuel ASTM D1655 Jet A, Jet A1, Jet B, MIL-DTL-5624 JP-4 & JP-5, and MIL-DTL-83133 JP-8 conforming to Pratt and Whitney Canada, Inc. Specification No. CPW 204 Oil Oils conforming to Pratt and Whitney Canada, Inc. Specification No. PWA 521 Type II (MIL-L-23699). Engine Limits See AFM as listed under Approved Publications Propeller and Propeller Limits 2-Hamilton Standard Model 14SF-23 Blade SFA13( )-0A Diameter 3.96M (13 Ft) Pitch settings at 0.75 radius: Feather 77.5 o Flight fine 10.5 o Ground fine -5.5 o Full reverse -18.5 o Propeller (Np) - Takeoff 1212 r.p.m. Max Continuous 1212 r.p.m. (See Data Pertinent to All Models Except as Indicated) Knots m.p.h. Airspeed Limits V MO(Maximum operating) 0 to 14000 ft 242 279 (IAS) 15000 ft 239 275 20000 ft 223 257 25000 ft 207 238 V FE (Flaps extended) Flaps 5 o 148 170 Flaps 15 o 148 170 Flaps 35 o 130 150 V A (Maneuvering) 164 188 V LO (Landing gear operation) 158 182 V LE (Landing gear extended) 172 198 V B (Rough Air) 180 207 Landing Gear Doors Open Operative 140 161 Speed (Max. speed for operation following an alternate landing gear extension) V MCA (Minimum control speed) Flaps 5 o 80 91 15 o 74 86 Maximum Weight (Mass) All Models, Take-off weight 16,466 kg (36,300 lb) (For other weights see AFM as listed under Approved Publications) CG Limits See AFM as listed under Approved Publications Maximum Baggage 907 kg (2000 lb) (See Weight and Balance Manual for mixed passenger cargo configuration) A13NM Page 4 of 14 3. DHC-8-300 Series Model -301- Approved June 8, 1989, by the FAA and Feb. 14, 1989, by the Canadian Department of Transport Model -311- Approved September 14, 1990, by the FAA and July 31, 1990, by the Canadian Department of Transport Model -315- Approved June 28, 1995, by the FAA and June 2, 1995, by the Canadian Department of Transport Engines 2-Pratt & Whitney Canada, Inc., PW123 (-301 and -311) 2-Pratt & Whitney Canada, Inc., PW123E (-315) (See Data Pertinent to All Models Except as Indicated) Fuel ASTM D1655 Jet A, Jet A1, Jet B, MIL-DTL-5624 JP-4 & JP-5, and MIL-DTL-83133 JP-8 conforming to Pratt and Whitney Canada, Inc. Specification No. CPW 204 Oil Oils conforming to Pratt and Whitney Canada, Inc. Specification No. PWA 521 Type II (MIL-L-23699). Engine Limits See AFM as listed under Approved Publications Propeller and 2-Hamilton Standa rd Model 14SF-15 or 14SF-23 Propeller Limits Blade SFA13 ( )-0A Diameter 3.96M (13 Ft) Pitch settings at 0.75 radius: Feather 77.5 o Flight fine 11.5 o Ground fine -7.5 o Full reverse -18.5 o Propeller (Np) - Takeoff 1212 r.p.m. Max Continuous 1212 r.p.m. (See Data Pertinent to All Models Except as Indicated) Knots m.p.h. Airspeed Limits V MO (Maximum operating) 0 to 17000 ft 243 280 (IAS) 20000 ft 232 267 25000 ft 214 246 DHC-8-301 V FE (Flaps extended) Flaps 5 o 160 184 Flaps 10 o 149 171 Flaps 15 o 149 171 Flaps 35 o 127 155 V A (Maneuvering) 176 203 V LO (Landing gear operation) 158 182 V LE (Landing gear extended) 173 199 V B (Rough Air) 188 216 Page 5 of 14 A13NM 3. DHC-8-300 Series (cont’d) Knots m.p.h. Landing Gear Doors Open Operative 140 161 Speed (Max. speed for operation following an alternate landing gear extension) V MCA (Minimum control speed) Flaps 5 o 83 96 Flaps 15 o 78 89 DHC-8-311 and 315 V FE (Flaps extended) Flaps 5 o 163 187 Flaps 10 o 154 177 Flaps 15 o 150 173 Flaps 35 o 138 159 V A (Maneuvering) 177 204 V LO (Landing gear operation) 163 187 V LE (Landing gear extended) 173 199 V B (Rough Air) 190 219 Landing Gear Doors Open Operative 140 161 Speed (Max. speed for operation following an alternate landing gear extension) V MCA (Minimum control speed) Flaps 15 o 78 90 Flaps 10 o 80 92 Flaps 5 o 83 95 Flaps 0 o 94 109 Maximum Weight DHC-8-301 Take-off weight 18,643 kg (41,100 lb) (Mass) DHC-8-311 and 315 Take-off weight 18,643 kg (41,100 lb) 18,997 kg (41,880 lb) (with CR803SO00001 incorporated) 19,505 kg (43,000 lb) (with CR803SO00002 incorporated) (For other weights see AFM as listed under Approved Publications) CG Limits See AFM as listed under Approved Publications Maximum Baggage 1,130 kg (2500 lb) for standard baggage compartment (See Weight and Balance Manual for other configurations) Cargo/Combi All cargo, 20, 40 or 48 passenger configurations with a moveable passenger/ (DHC-8-311) cargo bulkhead located at station 197.0, 354.0, 515.0 or 579.0 respectively A13NM Page 6 of 14 4. DHC-8-400 Series Model 400 Approved January 24, 2000 by the FAA and July 30, 1999 by the Canadian Department of Transport Model 401 Approved January 25, 2000 by the FAA and August 3, 1999 by the Canadian Department of Transport Model 402 Approved January 26, 2000 by the FAA and August 4, 1999 by the Canadian Department of Transport Engines 2 Pratt & Whitney Aircraft of Canada engines as follows: DHC-8-400, 401 and 402, PW150A Fuel Kerosene Type: ASTM D1655 JET A, ASTM D1655 JET A1 MIL-DTL-5624 JP-5, MIL-T-83133 JP-8 Wide Cut Type: A S T M D 1 6 5 5 J E T B , MIL-DTL-5624 JP-4 conforming to Pratt & Whitney Canada, Inc. Specification No. CPW 204 Oil Oils conforming to specification MI L-L-23699 (See AFM as listed in Approved Publications.) Engine Limits See AFM as listed in Approved Publications. Propeller and Dowty Aero space Model R408/6-123-F/17 Propeller Limits Blade 4.11 M (13.5 ft.) nominal Diameter Pitch setting at 0.70 radius: F e a t h e r 8 4 . 5 o Flight fine (Electronic) 16.5 o Flight fine (Hydraulic) 16.0 o G r o u n d f i n e - 3 . 5 o Full reverse -19.0 o Propeller (NP) - Take-off 1020 rpm M a x . c o n t i n u o u s 1 0 2 0 r p m A i r s p e e d L i m i t s K n o t s m . p . h (IAS) V MO (Maximum Operating) 0 to 8,000 ft 245 282 1 0 , 0 0 0 f t 2 8 2 3 2 5 1 8 , 0 0 0 f t 2 8 6 3 2 9 2 0 , 0 0 0 f t 2 7 5 3 1 6 2 5 , 0 0 0 f t 2 4 8 2 8 5 V FE (Flaps extended) Flap 5 o 200 230 F l a p 1 0 o 181 208 F l a p 1 5 o 172 198 F l a p 3 5 o 158 182 Page 7 of 14 A13NM V A (Maneuvering) 204 235 V LO (Landing gear operation) 200 230 V LE (Landing gear extended) 215 247 V B (Rough Air) 210 242 Landing Gear Door Open Operative Speed 185 213 (Max. Speed for operation following an alternate landing gear extension) VMCA (Minimum control speed) Flap 15 o 91 105 F l a p 1 0 o 95 109 F l a p 5 o 98 113 F l a p 0 o 113 130 (Refer to AFM for airspeed limits) Maximum Weight Take-off weight: Models 400, 401 and 402 (With Modsum 4-201539 incorporated) 27,987 Kg (61,700 lb) (With Modsum 4-308807 incorporated) 28,998 Kg (63,930 lb) (With Modsum 4-308907 incorporated) 29,257 Kg (64,500 lb) (With Modsum 4-309238 incorporated) 29,574 Kg (65,200 lb) C.G. Limits See AFM as lis ted in Approved Publications. Maximum Baggage For standard baggage compartments Aft baggage compartment: 1669 Kg (3680 lb) Fwd baggage compartment: 413 Kg (910 lb) See Weight and Balance Manual for other configurations DATA PERTINENT TO ALL MODELS EXCEPT AS INDICATED: Series 100, 200 and 300: Propeller and Propeller Limits The following Hamilton Standard Propeller combinations are approved. Basic Aircraft Model 101 Models 102, 103 & 106 Models 201 & 202 Models 301, 311, & 315 14SF-7 & -7 14SF-7 & -7 14SF-23 & -23 14SF-15 & 15 14SF-23 & -23 Modification 8/2579 allows the following additional Hamilton Standard Propeller combinations. Models 102, 103, & 106 Models 20 1 & 202 Models 301, 311, & 315 14SF-15 & 14SF-15 14SF-15 & 14SF-15 14SF-15 & 14SF-23 14SF-15 & 14SF-7 14 SF-15 & 14SF-23 14SF-15 & 14SF-23 14SF-23 & 14SF-23 14SF-23 & 14SF-7 A13NM Page 8 of 14 Engines The following Pratt & Whitney Aircraft of Canada engine combinations are approved. Any combination of original engines and/or optional engines within each aircraft model is permitted. For series 200 and 300 aircraft, optional engines must incorporate modification 8/2735 Approved Engine Combinations Aircraft Model Ori ginal Engine Optional En gine 102 PW120A PW121 201 PW123C PW123 PW123B PW123D PW123E 202 PW123D PW123 PW123B PW123E 301 and 311 PW123 PW123B PW123E The following P&WC Service Bulletin matrix lists the service bulletins which must be incorporated to change an optional engine to the rating of an original engine. The cancelling derate service bulletin is also shown. P&WC Service Bulletin Matrix Optional Engine Original Engine Rating P&WC S.B. Derate P&WC S.B. Cancel Derate PW123 PW123C PW123D 21501 21502 PW123B PW123 PW123C PW123D 21499 21500 PW123D PW123C 21503 21504 PW123E PW123 PW123C PW123D 21497 21498 Reference Datum (Series 100, 200, 300) Plate located on centerline at Station 423.0 in. (1074.4 cm) on underside of fuselage. (Series 400) Plate located on centerline at “Station 428.0 in” (1087.1 cm) on underside of fuselage. Leveling Means Plum bob and target in RH emergency exit opening. Minimum Crew 2 (Pilot and Copilot) Maximum Series 100 and 200 Occupants Not to exceed 44, including 2 p ilots, 1 attendants and 1 check pilot (40 passengers when fitted with an approved interior) Series 300 Not to exceed 61, including 2 pilo ts, 2 attendants and 1 check pilot (56 passengers when fitted with an approved interior) Page 9 of 14 A13NM Series 400 Model 400: Not to exceed 74, including 2 pilots, maximum 3 attendants, minimum 2 attendants and 1 check pilot (68 passengers when fitted with an approved interior) Model 401: Not to exceed 76, including 2 pilots, maximum 3 attendants, minimum 2 attendants and 1 check pilot (70 passengers when fitted with an approved interior) Model 402: Not to exceed 86, including 2 pilots, maximum 3 attendants, minimum 2 attendants and 1 check pilot (80 passengers when fitted with an approved interior) Flight Load Flaps Up +2.5g; -1.0g. Factors Flaps extended +2.0g; 0.0g. Fuel Capacity kg lb US Gal Imp Gal (Series 100, 200, 300) Usable 2575 5678 835 695 Unusable 40 87 13 11 Total 2615 5765 848 706 (Series 400) Usable 5318 11724 1724 1436 Unusable 73 160 24 20 Total 5391 11884 1748 1456 Oil Capacity US Gal Imp Gal Per Engine PW120/120A/121 Usable 1.0 0.83 Total 4.7 3.9 PW123/123B/123E Usable 1.9 1.6 Total 5.5 4.57 (Series 400) PW150A Usable 1.48 1.23 Total 6.58 5.48 Maximum Operating Altitude Take-off and landing 10,000 feet Enroute 25,000 feet Outside Air Temperature See AFM, as listed under Approved Publications Limits Control Surface See Maintenance Manual: Series 100 PSM 1-8-2 Series 200 PSM 1-82-2 Series 300 PSM 1-83-2 Series 400 PSM 1-84-2 Import Eligibility A U.S Airworthiness certificate may be issued on the basis of the Canadian Department of Transport "Certificate of Airworthiness for Export" signed by the Minister of Transport. This form must contain the following statement: "This certifies that the aircraft described above has been manufactured in conformity with the data forming the basis for the DOT Aircraft Type Approval No. A-142 as modified in accordance with the requirements for U.S. registered airplanes FAA Type Certificate No. A13NM defined in AEROC 8.1.AC.1." A13NM Page 10 of 14 Certification Basis Series 100, 200 and 300: FAR Part 25 dated February 1, 1965 including Amendments 25-1 through 25-51; FAR 25.832, Amendment 25-56; FAR 36 dated December 1, 1969 including Amendments 36-1 through 36-12; SFAR 27 dated December 12, 1973 including Amendments 27-1 through 27-5. Application for Type Certificate: March 31, 1980 (Series 100) Series 200 Additional Requirements: FAR Part 25, Amendments 25-52 through 25-66; FAR 25.963(e), Amendment 25-69; FAR 25.361, Amendment 25-72; FAR 25.729(e), Amendment 25-75; FAR Part 34 date d September 10, 1990 (Replaces SFAR 27); FAR Part 36, Amendments 36-1 through 36-20 With the following exceptions (See Note 6) FAR 25.365(e), Amendment 25-54; FAR 25.561, Amendment 25-64; FAR 25.562, Amendment 25-64; FAR 25.783, Amendment 25-54; FAR 25.785, Amendment 25-64; FAR 25.904, Amendment 25-62; FAR 25.1091(e), Amendment 25-57 Series 300 Additional Requirements: All Models; FAR 25.812, Amendment 25-58 DHC-8-301; FAR 25.853, Amendment 25-59 DHC-8-311 and 315; FAR 25.853, Amendment 25-66 DHC-8-315; FAR Part 34 dated September 10, 1 990 (Replaces SFAR 27); FAR Part 36, Amendments 36-1 through 36-20 Series 100, 200 and 300 Items of Equivalent Safety 1. Pilot compartment view FAR 25.773(b)(2). 2. Ditching emergency exits FAR 25.807(d)(2) Amdt. 25-55. (DHC-8-311 and 315 with CR803SO 00001 or CR803SO00002 incorporated) 3. Cargo compartment classification FAR 25.857(b)&(d) Amdt. 25-60, for the 20, 40 & 48 passenger configurations. DHC-8-311 Flight Manual Suppl. 42, Iss. 3, Cargo Loading Manual PSM 1-83-8A, Suppl. 1, Iss. 3 and Weight & Balance Manual PSM 1-83-8C are required. (S/N 230 & 242) Special Conditions 1. Automatic take-off power control system (ATPCS) (ref. FAA Special Conditions No. 25.-ANM-3). 2. Special Condition No. 25-394-SC, Passenger seats with non-traditional, large, non-metallic panels. Page 11 of 14 A13NM 3. Special Condition No. 25-660-SC, Non-Rechargeable Lithium Batteries, effective to design changes applied for after May 1, 2017. See the applicability section of this special condition for more information on which design changes must meet it. Exemptions 1. FAR 25.571(e)(2) Propeller Debris (ref. FAA exemption No. NM-102) 2. FAR 25.807(c)(1) 40 passenger configuration Series 100 and 200 (ref. FAA exemption No. 4723 dated October 24, 1986) Compliance with the following additional optional requirements has been established: Ice Protection - FAR 25.1419 Compliance with FAR 25.801 has been established when the safety equipment requirements of FAR 25.1411 and the ditching equipment requirements of FAR 25.1415 are satisfied. Part 26 – Continued Airworthiness and Safety Improvements for Transport Category Airplanes: Based on § 21.101(g) for changes to TCs, applicable provisions of Part 26 are included in th e certification basis. For any future Part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Compliance has been found for the following regulations 14 CFR § 26.11, 26.43, 26.45 and 26.49. (Amdt.No.26-0, through 26-1) Certification Basis Series 400: Federal Aviation Regulations (FAR) Part 25, Airworthiness Standards: Transport Category Airplanes, dated 01 February 1965, Amendments 25-1 through 25-83 Federal Aviation Regulations (FAR) Part 34, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered Airplanes, effective 10 September, 1990, including Amendment 34-3 effective February 3, 1999. US Code of Federal Aviation Regulation (CFR) Title 14 part 36, effective 1 December, 1969, including Amendment 36-1 through 36-21, Stage 3. US Code of Federal Aviation Regulation (CFR) Title 14 part 36, effective 1 December, 1969, including Amendment 36-1 through 36-28, Stage 4, when De Havilland Aircraft of Canada Limited AFM Revision 185, dated 24 September 2007 is installed. US Code of Federal Aviation Regulation (CFR) Title 14 part 36, effective 1 December, 1969, including Amendment 36-1 through 36-31, Stage 5, when De Havilland Aircraft of Canada Limited AFM Revision 401.1, dated 17 June 2021 is installed. Additional Requirements: Federal Aviation Regulations (FAR) Part 25, Airworthiness Standards: Transport Category Airplanes, dated 01 February 1965, Amendments 25-84 through 25-86, and 25-92. A13NM Page 12 of 14 Items of Equivalent Safety: 1. FAA Issue Paper F-1. “Use of 1-g Stall Speed Criteria Instead of Minimum Speed in the Stall” 2. Equivalent Level of Safety has been made for the following regulation: 14 CFR § 25.815, Width of Aisle, documented in ELOS Memo # AT7055NY- T-CS-1. (See Note 8) Special Conditions: 1. Special Condition No. 25-ANM-121, High Intensity Radiated Fields (HIRF) 2. Special Condition No. 25-154-SC, Automatic take-off power control system (ATPCS) 3. Special Condition No. 25-394-SC, Passenger seats with non-traditional, large, non-metallic panels. 4. Special Condition No. 25-660-SC, Non-Rechargeable Lithium Batteries, effective to design changes applied for after May 1, 2017. See the applicability section of this special condition for more information on which design changes must meet it. Exemptions: 1. Exemption No. 6790 to FAR 25.571(e)(1) “Damage Tolerance (Discrete Source) Evaluation at Amendment 25-72” 2. Exemption No. 6833 to FAR 36 Appendix C, Section C36.3c. “Definition of noise Sideline Point [compliance will be shown with ICAO Annex 16, Vol. 1, Iss. 3, Amendment 5, Chapter 3, Section 3.3.1(a)(2)] 3. Exemption No. 6864 to FAR 25.1435(b)(1) “Hydraulic System – Test and Analysis, at Amendment 25-72” Part 26 – Continued Airworthiness and Safety Improvements for Transport Category Airplanes: Based on § 21.101(g) for changes to TCs, applicable provisions of Part 26 are included in th e certification basis. For any future Part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Compliance has been found for the following regulations 14 CFR § 26.11, 26.43, 26.45 and 26.49. (Amdt.No.26-0, through 26-1) Optional Requirements: 1. Ice Protection: FAR 25.1419 2. Ditching: Compliance with FAR 25.801 has been established when the safety requirements of FAR 25.1411 and the ditching equipment requirements of FAR 25.1415 are satisfied Serial Numbers Eligible Series 100 Serial number 2 and subsequent Series 200 Serial number 391 and subsequent Series 300 Serial number 100 and subsequent Page 13 of 14 A13NM Series 400 Serial 4001 and subsequent Equipment The basic required equipment as prescribed in the applicable airworthiness requirements (See Certif ication Basis) must be installed in the aircraft. Approved Publications Flight Manual Series 100: PSM 1-81-1A (Models 101, 102, 103 and 106) Series 200: PSM 1-82-1A (Model 201, 202) Series 300: PSM 1-83-1A (Models 301, 311 and 315) Series 400: PSM 1-84-1A (Models 400, 401 and 402) Airworthiness Limitations (Part 2) an d MRB Report (Sections 2 and 3) of the Maintenance Program Series 100: PSM 1-8-7 Series 200: PSM 1-82-7 Series 300: PSM 1-83-7 Maintenance Requirements Manual, MRM (Section 1, MRB report and Section 2, Airworthiness Limitation Items Series 400: PSM 1-84-7 Definition Report AEROC 8.1.AC.1 Service Information Service Bulletins, structural re pair manuals, and aircraft flight manuals which contain a statement that the docume nt is Transport Canada approved or Transport Canada approved through the Manufacturers Design Approval Representative are accepted by the FA A and are considered FAA approved. These approvals pertain to the type design only. Life Limited Parts Components wh ich are life limited are listed in the "Airworthiness Limitations" section of the Maintenance Program. (See Note 3). Note 1. A current weight and balance report including list of equipment included in certificated empty weight, and loading instructions must be in each aircraft at the time of original certification and at all times there after except in the case of operators having an approved weight control system. The aircraft total system fuel must be included in the empty weight. System fuel is the amount of fuel required to fill the system plumbing and tanks to the undrainable level plus unusable fuel in the tanks established under FAR 25.959.