# TCDS A1NM: The Boeing Company - Type: Type certificate data sheet - Status: Current - Holder: The Boeing Company - Revision: 41 - Revised: August 21, 2024 - Product: Aircraft, Large Airplane - Certification basis: Part 25 - Registered aircraft: 446, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/de/9f/de9f3ff486d82c406039cc8d9e1be7efa522c9f8858a50e5e06c08c2050f06f2 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID150834703020240822132731.0001 - Page: https://openairdocs.org/tcds/A1NM ## Models (5) As the data sheet lists them. - 767-300 Series - 767-200 Series - 767-400ER Series - 767-300F Series - 767-2C Series ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET A1NM This data sheet, which is part of Type Certificate No. A1NM, 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: The Boeing Company 737 Logan Ave N Renton, WA 98057-0000 I - Model 767-200 (Approved July 30, 1982) Engines: 2 Pratt and Whitney JT9D-7R4D, JT9D-7R4E, JT9D-7R4E4, PW4052, PW4056, PW4060A, or 2 General Electric CF6-80A, CF6-80A2, CF6-80C2-B2, -B4, -B6 or CF6-80C2B4F, -B6F, -B7F, CF6-80C2B2F. WARNING: To prevent unsafe airplane handling characteristics, PW4000 series engines with electronic engine control (EEC) part number 791100-14-102 (Pratt & Whitney part number 54D043) must not be installed on the same airplane as PW4000 series engines that have the ring case compressor configuration. This combination of engine configurations is not approved because of a significant difference in engine acceleration rates and the effect of that difference on airplane handling characteristics. Ring case compressor equipped engines were approved with the same engine model number as previously approved PW4000 configurations, and must be identified by the presence of a “/A5” marked at the end of the “INSTL ARR” block on the engine data plate. The General Electric CF6-80A engines may be intermixed with CF6-8 0A2 engines with appropriate limitations as noted in the FAA-Approved Airplane Flight Manual. Fuel: Pratt and Whitney Engines: Fuels conforming to the latest version of Pratt & Whitney Service Bulletin 2016 General Electric Engines: Fuel conforming to GE Specification D50TF2. (See Note 14) All Engines: ASTM D-1655 grades Jet A or Jet A1. (See Note 14) ASTM D 6615 grades Jet B (see Note 14) MIL-T-5624 grades JP-4 or JP-5. (See Note 14) MIL-T-83133 grades JP-8. Refer to the FAA approved Airplane Flight Manual listed in Note 2 for fuel limitations Engine Ratings & For engine ratings and operating limits see engine TC Data Sheet No. E3NE for the P&W JT9D-7R4D, -7R4E, or - Operating Limits: 7R4E4; TC Data Sheet E13NE for the GE CF6-80A, CF6-80A2, or CF6-80C2; TC Data Sheet E24NE for the PW4000, or the FAA-Approved Airplane Flight Manual. Airspeed Limits: VD = 420 KCAS to 17,854 ft/.91M above 23,000 ft, linear variation between these points. VFC = 390 KCAS to 17,600 ft/382 KCAS at 23,000 ft/.87M above 26,000 ft, linear variation between these points. VMO = 360 KCAS/.86M VLE = 270 KCAS/.82M VLO = 270 KCAS/.82M For other airspeed limits, see the appropriate FAA-Approved Airplane Flight Manual. CG Range: See the appropriate FAA-Approved Flight Manual. Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 Rev. No. 41 36 37 39 37 36 39 36 37 39 36 41 41 36 41 36 Page No. 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 Rev. No. 36 36 41 37 36 37 36 41 38 37 39 37 39 38 38 40 A1NM Revision 41 BOEING 767-200 Series 767-300 Series 767-300F Series 767-400ER Series 767-2C Series August 21, 2024 2 A1NM I. Model 767-200 (cont’d): Maximum Weights: See the appropriate FAA-Approved Flight Manual. Maximum 255 with 2 pairs of Type A plus 1 pair of Type III exits. Passengers: 290 with 2 pairs of Type A plus 2 pairs of Type III exits. Model Eligible Serial Numbers 767-201 23897-23902 767-204 22980, 22981, 23072, 23250, 23807, 24013, 24239, 24457, 24736, 24757, 25058, 25139 767-205 23057, 23058 767-209 22681, 22682 767-212 28525 767-216 23623, 23624, 24973 767-219 23326-23328, 24150 767-222 21862-21880 767-223 22307-22336, 30256 767-224 30430-30439 767-231 22564-22573 767-232 22213-22227 767-233 22517-22528, 24142-24145, 24323-24325 767-238 23304-23306, 23309, 23402, 23403, 23896 767-241 23801-23806 767-246 23212-23214 767-258 22972-22975 767-259 24618, 24835 767-260 23106, 23107, 23916 767-266 23178-23180 767-269 23280-23282 767-275 22683, 22684 767-277 22692-22696 767-281 22785-22790, 23016-23022, 23140-23147, 23431-23434 767-283 24727, 24728 767-284 24716, 24742, 24762 767-23B 23973, 23974 767-24Q 28270 767-25D 24733, 24734 767-25E 27192-27195 767-27C 27385, 27391, 28016, 28017 767-27E 24832, 24854 767-27G 25537, 27048, 27049 767-2B1 25421, 26471 767-2B7 24764, 24765, 24894, 25225, 25257, 26847 767-2AX 33685 767-2DX 32954 767-2EY 33686-33689 767-2FK 33844, 33958, 34433, 35498 767-2J6 23307, 23308, 23744, 23745, 24007, 24157 767-2N0 24713, 24867 767-2Q4 22921-22923 767-2Q8 24448 767-2S1 23494 Certification Basis: Part 25 of the Federal Aviation Regulations as amended by Amendments 25-1 through 25-37, except where superseded by the following sections of Part 25 as amended by Amendments 25-1 through: Amendment Sections 25-38 25.101, 25.161, 25.397, 25.603, 25.675, 25.685, 25.775, 25.787, 25.815, 25.841, 25.941, 25.951, 25.979(a), (b), (c), 25.999, 25.1027, 25.1041, 25.1093(b), 25.1125, 25.1143(a), (b), (c), (d), 25.1167, 25.1303, 25.1305, 25.1322, 25.1355, 25.1385, 25.1403, 25.1439, 25.1515, 25.1533, 25.1557 25-39 25.807 25-40 25.901(a), (b)(1)(ii), (b)(2), (b)(3), (b)(4), (c), 25.903, 25.933, 25.939, 25.943, 25.945, 25.952, 25.959, 25.963, 25.965, 25.973, 25.995, 25.1091(a), (b), (c), (d), 25.1093(a), (c), 25.1121, 25.1123, 25.1141, 25.1145, 25.1197, 25.1199, 25.1207, 25.1337, 25.1549 25-41 25.831, 25.1309, 25.1321, 25.1325, 25.1331, 25.1333, 25.1335, 25.1351, 25.1401, 25.1421, 25.1435, 25.1447, 25.1450, 25.1457, 25.1459, 25.1461 25-42 25.21, 25.29, 25.107, 25.111, 25.143, 25.147, 25.149, 25.177, 25.181, 25.201, 25.207, 25.233, 25.237, 25.255, 25.703, 25.729, 25.1043, 25.1353, 25.1501, 25.1521, 25.1581, 25.1583, 25.1585, 25.1587 3 A1NM I. Model 767-200 (cont’d): Certification Basis (cont’d): Amendment Sections 25-43 25.1326 25-44 25.1413 25-45 25.571, and 25.573 25-46 25.345, 25.351(a), 25.629, 25.697, 25.803, 25.901(d), 25.1103(a), (b)(2), (d), (e), (f), 25.1142, and 25.1522 25-49 25.733 25-54 25.365 (e)(1), (2) Compliance with the following optional requirements has been established with respect to the following sections of 14 CFR Part 25: §25.801 - Ditching Provisions (Over- water operation can be approved when the aircraft has been equipped and installation has been approved according to 14 CFR 25.801) §25.1419 - Ice Protection Provisions 14 CFR §26: (Based on 14 CFR §21.101(g) for changes made to TCs applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections). Compliance has been found for the following regulations at Amendment 26-0: 26.11 and Amendment 26-1: 26.43, 26.45, 26.47, and 26.49 14 CFR part 36 of the Federal Aviation Regulations with Amendments 36-1 through 36-12, effective August 1, 1981. See the appropriate FAA Approved Airplane Flight Manual listed in Note (2) for applicability of Stage 4 Noise Recertification through Amendment 36-28. Special Federal Aviation Regulation 27 Exemption from Part 25: Exemption Title Issued Date Expiration Date 4725 Exemption from 25.785(h) -Allows one seat for a required flight attendant to be located near the overwing Type III exits. 3 November, 1986 Permanent 8119 Partial Exemption from §25.901(c), Single Failures resulting in Uncontrollable High Thrust Conditions 11 June, 2003 Permanent 9749A Exemption from 14 CFR 25.785(j), 25.807(d), 25.807(g)(1), 25.807(i)(1), 25.810(a)(1), 25.812(e), 25.813(b), 25.857(e), and 25.1447(c)(1) for 767- 200 series airplanes converted from passenger to freighter with provisions for the carriage of mixed cargo/live animal operation 24 July, 2009 Permanent 9791C Partial Time-Limited Exemption from 14 CFR §25.853(a), appendix F, paragraph (a)(1)(i), Testing on Large Interior Panels (Expired Exemption No. 9791, November 28, 2010, Exemption No. 9791B, 28 February, 2011) 28 November, 2008 28 November, 2011 10767C Time-limited exemption from 14 CFR 25.901(c) and 25.981(a)(3), fuel tank ignition prevention associated with the FQIS is limited to the replacement of the ARINC 429 chip within the fuel quantity processer unit’s IOC cards and the BITE card (Expired Exemption No. 10767, 17 May, 2016, Exemption No. 10767A, 17 May, 2016) 17 December, 2015 17 May, 2016 14593 Exemption from SFAR 88, and §§ 25.901(c) and 25.981(a)(3), as they pertain to fuel-tank-ignition prevention associated with the fuel-quantity indication system and fuel-overfill-shutoff surge tank wiring installation, limited to in-service 767-200 (freighter only) 25 January, 2016 Permanent Equivalent Safety Findings (ESF’s) exist with respect to the following sections of 14 CFR Part 25: ELOS IP Title 14 CFR ANM-100S-0811-CI-2 Pressurized Cabin Loads (Crew Rest) 25.365(e)(2) ANM-100S-1727-CI-1 Cross Aisle Between Type III Exits 25.807, 25.813 ANM-100S-2332-CI-1 Pressurized Cabin Loads (Crew Rest) 25.365(e)(2) ANW-212:8110-5 Test Subjects for Emergency Evacuation Demonstration 25.803(c)(8) AT0328ST-T-C-5 "No Smoking" limitation in the passenger compartment 25.791,25.853, CAR 4b.3 81 AT1736SE-T-C-14 Door Sill Reflectance 25.811 4 A1NM I. Model 767-200 (cont’d): Certification Basis (cont’d): Equivalent Safety Findings (Cont’d) ELOS IP Title 14 CFR AT2251SE-T-F-1 Use of the 1-g Stall Speed Instead of Minimum Speed in the Stall as a Basis for Determining Compliance (Non-Structural Sections) 1.2, 25.21(b), 25.103(a),(a)(1),(a)(3- 6),(b)(c), 25.107(b)(1),(b)(2),(c)(3),(g), 25.111(a), 25.119(b), 25.121(c),(d),(d)(3), 25.125(a)(2), 25.143(g), 25.145(a),(a)(1),(b)(1- 4),(b)(6),(c), 25.147 (a),(a)(2),(c),(d), 25.149 (c), 25.161(b),(c)(1),(c)(2),(c)(3)(d),(e)(3), 25.175(a)(2),(b)(1),(b)(2),(b)(2)(ii),(b) (3),(c),(c)(4),(d),(d)(5), 25.177(c), 25.181(a),(b), 25.201(a)(2),(b)(4), 25.207(b),(c),(d),(e),(f), 25.231(a)(2), 25.233(a), 25.237(a),(b)(1),(b)(2), 25.735(f)(2),(g), 25.773(b)(1)(i), 25.1001(c)(1),(c)(3), 25.1323(c)(1),(c)(2), 25.1325(e), 25.1587(b)(2) AT6937SE-T-S-1 Hydraulic System Proof Pressure Test 25.1435 (25-45) CT1180NW-D-A-5 Emergency Exit Arrangement 25.807, 25.809, 25.813 CT1180NW-D-A-7 Type A Exit Passageway Dimensions 25.807, 25.811 CT1180NW-D-P-10 Engine Fan Cowl Compartment Fire Zone 25.1181(a)(6), 25.1182 CT1180NW-D-P-9 Induction System Deicing and Anti-icing Protection 25.1093(b)(1) CT1180NW-D-S-20 Forward Position Light Intensity in the Vertical Plane and Overlap 25.1393, 25.1395 PS05-0123-P-1 Ground Fault Interrupter Relays 25.981(a)(3) PS05-0177-P-2 Fuel Tank Flammability Rule (see Note 17) 25.981 (25-125) PS06-0496-F-18 Engine and Auxiliary Power Unit (APU) Fire Switch Handle Design 25.1555(d)(1) PS08-0670-C-1 Adhesives Used in Interior Panel Bent Joint Potting Applications 25.853(a) PS13-0901-ES-1 Oxygen Quantity Indication of the Lavatory Supplemental Oxygen System 25.1441(c) PS13-1000-C-5 Flammability Testing Hierarchy 25.853(a)(d), part 25 appendix F parts I and IV SA06091WI-T-P-1 Powerplant Instrumentation for RCI LDS-2100 installation on Boeing 767-200 series aircraft equipped with General Electric CF6-80A2 engines 25.1305 & 25.1549 TC6918SE-T- G-8 Formatting of Boeing Instructions for Continued Airworthiness Manuals - Airworthiness Limitations 25.1529 (25-54), 25.1729(25-123), H25(25-132) TD1990SE-T-C-1 Emergency Locator Transmitter (ELT) 25.1415(d) TD2695SE-T-C-1 Exterior Exit Markings 25.811(f) TD7075SE-T-C-1 Type III Exit Accessibility 25.803, 25.807(c), 25.813(c) TS13-0005-S-1 Determination of Minimum Oxygen Flow for the Lavatory Oxygen System 25.1443(c) Special Conditions with respect to the following subjects apply: Special Condition Title Effective Date 25-ANM-18 Lightning Protection, Protection from Unwanted Effects of Radio Frequency (RF) Energy and Propulsion Control System for Pratt and Whitney PW4000 series engines, General Electric CF6-80C2 FADEC engine, and Rolls Royce RB211-524H-36 engine installations 29 April, 1988 25-ANM-20 Installation of a longitudinal partition in the cabins 23 August, 1988 25-369-SC Seats with Non-Traditional, Large, Non-Metallic Panels 17 March, 2008 25-630-SC Non-Rechargeable Lithium Batteries 22 April, 2017 5 A1NM II - 767-200SF Major Design Change A 767-200SF (Special Freighter) is a 767-200 series passenger airplane that has been modified in accordance with FAA-approved Boeing Service Bulletin(s) 767-00-0038 to operate in a freighter configuration. These aircraft remain 767-200 series aircraft for documentation purposes on this TCDS and with regard to the applicability of airworthiness directives. Because of the magnitude of this design change, the certification basis for the changed aspects was required to be established and documented in accordance with section 21.101 (Changed Product Rule) All general information in TCDS A1NM for the 767-200 Series remains applicable to an airplane operating in the 767- 200SF configuration, with the following exceptions: Maximum Passengers: There are no provisions for the carriage of passengers. A maximum of four supernumeraries can occupy the flight deck as given in Exemption 9749A. The 767-200SF certification basis was established according to the requirements given in § 21.101 and AC 21.101-1, and was determined in accordance with FAA Order 8110.48. The 767-200SF consists of the following product level change which is considered significant per AC 21.101-1: Significant Product Level Change: Passenger to Freighter Conversion Certification basis: Part 36: Unchanged under the “No Acoustical Change” Provisions of § 21.93(b) SFAR 27: Unchanged from 767-200 Series Part 26, Amendments 26-0 through 26-1 Part 25 of the FAR, effective February 1, 1965, as amended by Amendments 25-1 through 25-115 with the following exceptions per section 21.101(b): SECTION NO. TITLE AT AMDT. 25- 25.365(e)(2) Pressurized Compartment Loads 25-54 (for compartments outside of the pressurized area) 25.561(c)(2) General 25-64 25.571 Damage-tolerance and fatigue evaluation of structure 25-54 25.831(g) Ventilation 25-41 25.841(a) Pressurized cabins 25-38 Changed Areas: The following is a high level description of the listing of changes incorporated as part of the passenger to SF conversion: • Installed strengthened floor beams and fuselage frames • Installed main deck cargo door • Installed rigid cargo barrier/smoke barrier • Revised cargo ventilation system • Removal of passenger windows and installation of window plugs • Installed main deck cargo fire protection system and smoke detection system • Installed aural and visual alerts in the main deck Class E cargo compartment • Installation of seats and provisions to the flight deck for four supernumeraries The certification basis for the following changes incorporated as part of the passenger to SF conversion remains at the original certification basis for the Model 767-200 shown on TCDS A1NM: • Rerouting and some minor changes to hardware associated with flight controls, landing gear, and wheel brake cables • Rerouting of air data tubing, hydraulic tubing, certain electrical wiring • Changes to performance characteristics associated with static and dynamic loads • Forward lavatory with recirculating waste system, including flush motor and related timer and circuit breaker • Re-use of passenger airplane interior mounting hardware and attach points to accommodate cargo compartment equipment like sidewall panels and ceilings. • Installation of a floor-mounted first observer seat • Revision to the Ditching and Flotation analysis document as affected by the SF modification • Revision of the EICAS to the 767-200SF configuration • Revision of Door 1L counterbalance associated with the slide removal The certification basis for areas not affected by the change will remain at the original certification basis for the Model 767-200. . Special Conditions: Special conditions that are part of the certification basis for the 767-200 Series apply to the airplane operating in the 767-200SF configuration 6 A1NM II - 767-200SF Major Design Change (cont’d) Exemptions: All exemptions from 14 CFR Part 25 listed in TCDS A1NM for the 767-200 Series apply to the 767-200SF configuration, except those listed below: Exemption No. 4725 - Exemption from 25.785(h) -Allows one seat for a required flight attendant to be located near the overwing Type III exits. Does not apply. Exemption 9749A, dated 07/24/09, provides relief from the requirements of Sections 25.785(j); 25.807(d), (g)(1), (i)(1); 25.810(a)(1); 25.812(e); 25.813(b); 25.857(e); and 25.1447(c)(1) to allow for the carriage of supernumeraries on the 767-200SF. Equivalent Safety Findings: All existing Equivalent Safety Findings listed in TCDS A1NM for the 767-200 Series apply to the 767-200 operated in the 767-200SF configuration, except those listed below: • Test Subjects for Emergency Evacuation Demonstration, Section 25.803(c)(8). Does not apply. • Passenger Emergency Exits, Section 25.807(a)(7)(iv) and (c). Does not apply. • Type III Exit Access, 25.803, 25,807(c) and 25.813(c). Does not apply. • Emergency Exit Access, 25.807, 25.809 and 25.813. Does not apply. • Exterior Exit Markings, 25.811(f)(2). Does not apply. • “No Smoking” limitation in passenger compartment, 25.791 and 25.853(c). Does not apply. • Type A Exit Passageway Dimensions, 25.807 and 25.811. Does not apply. • Cross-Aisle between Type III Exits, 25.807 and 25.813. Does not apply TCDS Notes: All Notes in TCDS A1NM that apply to the 767-200 Series also apply to an airplane operated in the 767- 200SF configuration Optional All optional requirements applicable to 767-200 Series also apply to aircraft operated in the 767-200SF Requirements: configuration. III - Model 767-300 (Approved September 22, 1986) Engines: 2 Pratt and Whitney JT9D-7R4D, JT9D-7R4E, JT9D-7R4E4, PW4056, PW4060, PW4060C, or PW4062; or 2 General Electric CF6-80A2, or CF6-80C2-B2, -B4, or -B6, or CF6-80C2-B2F, B4F, B6F, or -B7F; or 2 Rolls Royce RB211- 524H-36, or RB211-524H-T-36. WARNING: To prevent unsafe airplane handling characteristics, PW4000 series engines with electronic engine control (EEC) part number 791100-14-102 (Pratt & Whitney part number 54D043) must not be installed on the same airplane as PW4000 series engines that have the ring case compressor configuration. This combination of engine configurations is not approved because of a significant difference in engine acceleration rates and the effect of that difference on airplane handling characteristics. Ring case compressor equipped engines were approved with the same engine model number as previously approved PW4000 configurations, and must be identified by the presence of a “/A5 marked at the end of the “INSTL ARR” block on the engine data plate. Fuel: Pratt and Whitney Engines: Fuels conforming to the latest version of P&W Service Bulletin 2016 General Electric Engines: Fuel conforming to GE Specification D50TF2. (See Note 14) Rolls Royce Engines: See Rolls Royce "Operating Instructions RB211-524H on the Boeing 767-300. (See Note 15) All Engines: ASTM D-1655 grades Jet A or Jet A1. (See Note 14, 15) ASTM D 6615 grades Jet B (see Note 14) MIL-T-5624 grades JP-4 or JP-5. (See Note 14, 15) MIL-T-83133 grades JP-8. Refer to the FAA approved Airplane Flight Manual listed in Note 2 for fuel limitations Engine Ratings & Operating Limits: For engine ratings and operating limits see engine TC Data Sheet No. E3NE for the P&W JT9D- 7R4D, - 7R4E, or - 7R4E4; TC Data Sheet E13NE for the GE CF6-80A2, or CF6-80C2; TC Data Sheet E24NE for the PW4000, TC Data Sheet E30NE for the Rolls Royce RB211-524H-36, or RB211-524H-T-36; or the FAA-Approved Airplane Flight Manual. Airspeed Limits: VD = 420 KCAS to 17,854 ft/.91M above 23,000 ft, linear variation between these points. VFC = 390 KCAS to 17,600 ft/382 KCAS at 23,000 ft/.87M above 26,000 ft, linear variation between these points. VMO = 360 KCAS/.86M VLE = 270 KCAS/.82M VLO = 270 KCAS/.82M For other airspeed limits, see the appropriate FAA-Approved Airplane Flight Manual. CG Range: See the appropriate FAA-Approved Flight Manual. Maximum Weights: See the appropriate FAA-Approved Flight Manual. 7 A1NM III - Model 767-300 (Cont’d) Maximum 290 with 2 pairs of Type A plus 2 pairs of Type III exits Passengers: 290 with 3 pairs of Type A plus 1 pair of Type III exits. (See Note 6 for Type III Exit requirements.) 351 with 3 pairs of Type A plus 1 pair of Type I exits. Model Eligible Serial Numbers 767-304 28039-28042, 28208, 28883, 28979, 29137, 29138, 29384 767-306 26263, 27610-27612, 27614, 27957-27960, 28098, 28884, 30393 767-316 26327, 26329, 27597, 27613, 27615, 29227-29229, 34626, 34628, 34629, 35229-35231, 35696-35698, 36710-36712, 37800-37802, 40590-40593,40798, 40799, 41746-41748, 41993-41997, 42213, 42214 767-319 24875, 24876, 26264, 26912, 26913, 26915, 26971, 28745, 29388, 30586 767-322 25091-25094, 25280, 25283-25287, 25389-25394, 27112-27115, 27158-27160, 29236-29243, 30024-30029 767-323 24032-24046, 25193-25202, 25445-25451, 26995, 26996, 27059, 27060, 27184, 27448-27451, 29429-29432, 29603- 29606, 33081-33089 767-324 27392-27394, 27568, 27569 767-328 27135, 27136, 27212, 27427, 27428 767-330 25137, 25208, 25209, 26983-26988, 26991, 26992 767-332 23275-23279, 23435-23438, 24075-24080, 24759, 24775, 24800, 24802, 24803, 24852, 24981, 24982, 25061, 25122, 25123, 25143-25146, 25306, 25409, 25984-25991, 27110, 27111, 27582-27584, 27961, 27962, 28447-28458, 29689- 29698, 30180, 30198, 30199, 30388, 30573-30575, 30594-30597, 32776 767-333 25583-25588, 30846, 30850-30852 767-336 24333-24343, 25203, 25204, 25442-25444, 25732, 25733, 25826, 25828, 25829, 25831, 25832, 25834, 27140, 29230- 29232 767-338 24146, 24316, 24317, 24407, 24531, 24853, 24929, 24930, 25246, 25274, 25316, 25363, 25575-25577, 28153, 28154, 28724, 28725, 29117, 29118, 30186 767-341 24752, 24753, 24843, 24844, 30341, 30342 767-343 30008, 30009 767-346 23215-23217, 23645, 23961-23966, 24498, 24782, 24783, 27311-27313, 27658, 27659, 28553, 28837, 28838, 29863, 32886-32888, 33493-33497, 33845-33851, 35813-35815, 36131, 37547-37550, 40363-40569 767-352 26261, 26262 767-360 33767-33769 767-366 24541, 24542 767-375 24082-24087, 24306, 24307, 24574, 24575, 25120, 25121, 25864, 25865, 30108, 30112 767-381 23756-23759, 24002-24006, 24350, 24351, 24400, 24415-24417, 24632, 24755, 24756, 24880, 25055, 25136, 25293, 25616-25619, 25654-25662, 27050, 27339, 27444, 27445, 27942, 27943, 27944, 32972-32980, 33506-33508, 35876, 35877, 37719, 37720, 37872, 40564-40567, 40894-40898 767-383 24318, 24357, 24358, 24475-24477, 24729, 24846-24849, 25088, 25365, 26544 767-31A 24428, 24429, 25273, 25312, 26469, 26470, 27619 767-31B 25170, 26259, 26265 767-31K 27205, 27206, 28865 767-32K 33968 767-32L 40342, 40343, 41063 767-33A 25346, 25403, 25530-25536, 27189, 27310, 27376, 27377, 27468, 27476, 27477, 27908, 27909, 27918, 28043, 28138-28141, 28147, 28159, 28495, 33421-33425 767-34G 41519 767-33P 28370, 28392, 33078, 35796, 40533, 40534-40536 767-34P 33047-33049 767-35D 24865, 27902, 28656 767-35E 26063, 26064 767-35H 26387-26389 767-36D 27309, 27684, 27685, 27941, 35155, 35156 767-36N 29898, 30107, 30109-30111, 30115, 30841, 30843, 30847, 30853, 30854 767-37D 26328 767-37E 25077 767-38A 29617, 29618 767-38E 24797, 24798, 25132, 25347, 25404, 25757-25760, 25762, 25763, 29129, 30840 767-39H 26256, 26257 767-3BG 30564-30566 767-3D6 24766-24768 767-3G5 24257-24259, 28111, 29435 767-3J6 25875-25878 767-3KY 42220, 42221, 42223 767-3P6 23764, 24349, 24484, 24485, 24495, 24496, 24983-24985, 25241, 25269, 25354, 26233-26238, 27254, 27255 767-3Q8 24745, 24746, 27600, 27616-27618, 27686, 27993, 28132, 28206, 28207, 29390, 29383, 29386, 29387, 30048, 30301 767-3S1 25221, 26608 767-3T7 25076, 25117 767-3W0 28148, 28149, 28264 767-3X2 26260 767-3Y0 24947, 24948, 24952, 24953, 24999, 25000, 25411, 26200, 26204-26208 767-3Z9 23765, 24628, 26417, 27095, 29867, 30331, 30383 8 A1NM III - Model 767-300 (Cont’d) 767-3BG 30563 767-3CB 33466-33469 Certification Basis: Part 25 of the Federal Aviation Regulations as amended by Amendments 25-1 through 25-37, except where superseded by the following sections of Part 25 as amended by Amendments 25-1 through: Amendment Sections 25-38 25.101, 25.161, 25.397, 25.603, 25.675, 25.685, 25.775, 25.787, 25.815, 25.841, 25.941, 25.951, 25.979(a), (b), (c), 25.999, 25.1027, 25.1041, 25.1093(b), 25.1125, 25.1143(a), (b), (c), (d), 25.1167, 25.1303, 25.1305, 25.1322, 25.1355, 25.1385, 25.1403, 25.1439, 25.1515, 25.1533, 25.1557 25-39 25.807 25-40 25.901(a), (b)(1)(ii), (b)(2), (b)(3), (b)(4), (c), 25.903, 25.933, 25.939, 25.943, 25.945, 25.952, 25.959, 25.963, 25.965, 25.973, 25.995, 25.1091(a), (b), (c), (d), 25.1093(a), (c), 25.1121, 25.1123, 25.1141, 25.1145, 25.1197, 25.1199, 25.1207, 25.1337, 25.1549 25-41 25.831, 25.1309, 25.1321, 25.1325, 25.1331, 25.1333, 25.1335, 25.1351, 25.1401, 25.1421, 25.1435, 25.1447, 25.1450, 25.1457, 25.1459, 25.1461 25-42 25.21, 25.29, 25.107, 25.111, 25.143, 25.147, 25.149, 25.177, 25.181, 25.201, 25.207, 25.233, 25.237, 25.255, 25.703, 25.729, 25.1043, 25.1353, 25.1501, 25.1521, 25.1581, 25.1583, 25.1585, 25.1587 25-43 25.1326 25-44 25.1413 25-45 25.571, and 25.573 25-46 25.345, 25.351(a), 25.629, 25.697, 25.803, 25.901(d), 25.1103(a), (b)(2), (d), (e), (f), 25.1142, and 25.1522 25-49 25.733 25-54 25.365 (e)(1), (2) Compliance with the following optional requirements has been established with respect to the following sections of 14 CFR Part 25: §25.801 - Ditching Provisions (Over- water operation can be approved when the aircraft has been equipped and installation has been approved according to 14 CFR 25.801) §25.1419 - Ice Protection Provisions 14 CFR §26: (Based on 14 CFR §21.101(g) for changes made to TCs applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections). Compliance has been found for the following regulations at Amendment 26-0: 26.11 and Amendment 26-1: 26.43, 26.45, 26.47, 26.49 and Amendment 26-3: 26.39 14 CFR part 36 of the Federal Aviation Regulations with Amendments 36-1 through 36-12, effective August 1, 1981. See the appropriate FAA Approved Airplane Flight Manual listed in Note (2) for applicability of Stage 4 Noise Recertification through Amendment 36-28. Special Federal Aviation Regulation 27 Exemption from Part 25: Exemption Title Issued Date Expiration Date 4725 Exemption from 25.785(h) -Allows one seat for a required flight attendant to be located near the overwing Type III exits. 3 November, 1986 Permanent 8119 Partial Exemption from §25.901(c), Single Failures resulting in Uncontrollable High Thrust Conditions 11 June, 2003 Permanent 9791C Partial Time-Limited Exemption from 14 CFR §25.853(a), appendix F, paragraph (a)(1)(i), Testing on Large Interior Panels (Expired Exemption No. 9791, November 28, 2010, Exemption No. 9791B, 28 February, 2011) 28 November, 2008 28 November, 2011 10069 Exemption from 14 CFR 25.779(b)(1), 25.1301(d), and 25.1309(a), 767-300 with Rolls Royce RB211- 524G/H engines installed with Full Authority Fuel Control Software “Issue 17” software. 25 May, 2010 Permanent 10767C Time-limited exemption from 14 CFR 25.901(c) and 25.981(a)(3), fuel tank ignition prevention associated with the FQIS is limited to the replacement of the ARINC 429 chip within the fuel quantity processer unit’s IOC cards and the BITE card (Expired Exemption No. 10767, 17 May, 2016, Exemption No. 10767A, 17 May, 2016) 17 December, 2015 17 May, 2016 14593 Exemption from SFAR 88, and §§ 25.901(c) and 25.981(a)(3), as they pertain to fuel-tank-ignition prevention associated with the fuel-quantity indication system and fuel-overfill-shutoff surge tank wiring installation, limited to in-service 767-300 (freighter only) 25 January, 2016 Permanent 9 A1NM III - Model 767-300 (Cont’d) Certification Basis (Cont’d): Equivalent Safety Findings (ESF’s) exist with respect to the following sections of 14 CFR Part 25: ELOS IP Title 14 CFR AT00010BA-T-S-1 Powerplant And Auxiliary Power Unit Instruments 25.1549(b) AT0328ST-T-C-5 "No Smoking" limitation in the passenger compartment 25.791,25.853, CAR 4b.3 81 AT1736SE-T-C-14 Door Sill Reflectance 25.811 AT2251SE-T-F-1 Use of the 1-g Stall Speed Instead of Minimum Speed in the Stall as a Basis for Determining Compliance (Non-Structural Sections) 1.2, 25.21(b), 25.103(a),(a)(1),(a)(3- 6),(b)(c), 25.107(b)(1),(b)(2),(c)(3),(g), 25.111(a), 25.119(b), 25.121(c),(d),(d)(3), 25.125(a)(2), 25.143(g), 25.145(a),(a)(1),(b)(1- 4),(b)(6),(c), 25.147 (a),(a)(2),(c),(d), 25.149 (c), 25.161(b),(c)(1),(c)(2),(c)(3)(d),(e)(3), 25.175(a)(2),(b)(1),(b)(2),(b)(2)(ii),(b) (3),(c),(c)(4),(d),(d)(5), 25.177(c), 25.181(a),(b), 25.201(a)(2),(b)(4), 25.207(b),(c),(d),(e),(f), 25.231(a)(2), 25.233(a), 25.237(a),(b)(1),(b)(2), 25.735(f)(2),(g), 25.773(b)(1)(i), 25.1001(c)(1),(c)(3), 25.1323(c)(1),(c)(2), 25.1325(e), 25.1587(b)(2) AT4965SE-T-P-1 RB211-524H-T Engine Fire Detection Provisions 25.1203 AT4965SE-T-P-2 RB211-524H-T Engine Zone 2 Pressure Relief Provisions 25.1103(d) PS05-0177-P-2 Fuel Tank Flammability Rule (see Note 17) 25.981 (25-125) PS05-0123-P-1 Ground Fault Interrupter Relays 25.981(a)(3) PS06-0496-F-18 Engine and Auxiliary Power Unit (APU) Fire Switch Handle Design 25.1555(d)(1) PS08-0670-C-1 Adhesives Used in Interior Panel Bent Joint Potting Applications 25.853(a) PS13-0901-ES-1 Oxygen Quantity Indication of the Lavatory Supplemental Oxygen System 25.1441(c) PS13-1000-C-5 Flammability Testing Hierarchy 25.853(a)(d), part 25 appendix F parts I and IV SA06091WI-T-P-1 Power plant and Auxiliary Power Unit Instruments 25.1549(b), (c) T4173NM-DS-C-1 Emergency Exit Arrangement and Cross Aisle Proximity 25.813 T4173NM-DS-CI-1 Emergency Exit Arrangement 25.807, 25.809 and 25.813 T4173NM-DS-CI-2 Emergency Exit Access 25.813(c) TC6918SE-T- G-8 Formatting of Boeing Instructions for Continued Airworthiness Manuals - Airworthiness Limitations 25.1529 (25-54) 25.1729(25-123) Appendix H (25-132) TC6918SE-T-F-6 Minimum Unstick Speed (VMU) 25.107(e)(1)(iv) TD1637SE-T-C-1 Folding Waste Trolley 25.853(d) TD1990SE-T-C-1 Emergency Locator Transmitter (ELT) 25.1415(d) TD2695SE-T-C-1 Exterior Exit Markings 25.811(f) TD7075SE-T-C-1 Type III Exit Accessibility 25.803, 25.807(c), 25.813(c) TS13-0005-S-1 Determination of Minimum Oxygen Flow for the Lavatory Oxygen System 25.1443(c) 10 A1NM III - Model 767-300 (Cont’d) Certification Basis (Cont’d): Special Conditions with respect to the following subjects apply: Special Condition Title Effective Date 25-ANM-18 Lightning Protection, Protection from Unwanted Effects of Radio Frequency (RF) Energy and Propulsion Control System for Pratt and Whitney PW4000 series engines, General Electric CF6-80C2 FADEC engine, and Rolls Royce RB211-524H-36 engine installations 29 April, 1988 25-ANM-20 Installation of a longitudinal partition in the cabins 23 August, 1988 25-369-SC Seats with Non-Traditional, Large, Non-Metallic Panels 17 March, 2008 25-454-SC Seats with Inflatable Lapbelts 5 January, 2012 25-630-SC Non-Rechargeable Lithium Batteries 22 April, 2017 IV - 767-300BCF Major Design Change The 767-300BCF (Boeing Converted Freighter) is a 767-300 series passenger airplane that has been modified in accordance with FAA- approved Boeing Service Bulletin(s) 767-00-0039 to operate in a freighter configuration. These aircraft remain 767-300 series aircraft for documentation purposes on this TCDS and with regard to the applicability of airworthiness directives. Because of the magnitude of this design change, the certification basis for the changed aspects was required to be established and documented in accordance with section 21.101 (Changed Product Rule). All general information in TCDS A1NM for the 767-300 Series remains applicable to an airplane operating in the 767-300BCF configuration, with the following exceptions: Maximum Passengers: There are no provisions for the carriage of passengers. A maximum of four supernumeraries can occupy the flight deck as given in Exemption 9696A A 767-300BCF certification basis was established according to the requirements given in § 21.101 and AC 21.101-1, and was determined in accordance with FAA Order 8110.48. The 767-300BCF consists of the following product level change which is considered significant per AC 21.101-1: Significant Product Level Change - Passenger to Freighter Conversion: Certification basis: Part 36: Unchanged under the “No Acoustical Change” Provisions of § 21.93(b) SFAR 27: Unchanged from 767-300 Series Part 26, Amendments 26-0 through 26-1 Part 25 of the FAR, effective February 1, 1965, as amended by Amendments 25-1 through 25-117 with the following exceptions per section 21.101(b): SECTION NO. TITLE AT AMDT. 25- 25.365(e)(2) Pressurized Compartment Loads 25-54 (for compartments outside of the pressurized area) 25.561(c)(2) General 25-64 25.571 Damage-tolerance and fatigue evaluation of structure 25-54 25.831(g) Ventilation 25-41 25.841(a) Pressurized cabins 25-38 Changed Areas: The following is a high level description of the listing of changes incorporated as part of the passenger to BCF conversion: • Installed strengthened floor beams and fuselage frames • Installed main deck cargo door • Installed rigid cargo/smoke barrier • Revised cargo ventilation system • Removal of passenger windows and installation of window plugs • Installed main deck cargo fire protection system and smoke detection system • Installed aural and visual alerts in the main deck Class E cargo compartment • Installation of seats and provisions to the flight deck for four supernumeraries 11 A1NM IV - 767-300BCF (cont’d) Changed Areas (cont’d) The certification basis for the following changes incorporated as part of the passenger to BCF conversion remains at the original certification basis for the Model 767-300 shown on TCDS A1NM: • Rerouting and some minor changes to hardware associated with flight controls, landing gear, and wheel brake cables • Rerouting of air data tubing, hydraulic tubing, certain electrical wiring • Changes to performance characteristics associated with static and dynamic loads • Forward lavatory with recirculating waste system, including flush motor and related timer and circuit breaker • Re-use of passenger airplane interior mounting hardware and attach points to accommodate cargo compartment equipment like sidewall panels and ceilings. • Installation of a floor-mounted first observer seat • Revision to the Ditching and Flotation analysis document as affected by the BCF modification • Revision of the EICAS to the 767-300BCF configuration • Incorporation of the 767-300 production stabilizer electric alternate trim control system • Optional installation of English and foreign language placards in appropriate exterior and interior locations • Optional modification of lower lobe air conditioning • Strengthening of landing gear to accommodate differences in weight and CG • Revision of Door 1L counterbalance associated with slide removal The certification basis for areas not affected by the change will remain at the original certification basis for the Model 767-300 shown on TCDS A1NM. Special Conditions: Special conditions that are part of the certification basis for the 767-300 Series apply to the airplane operating in the 767-300BCF configuration. Exemptions: All exemptions from 14 CFR Part 25 listed in TCDS A1NM for the 767-300 Series apply to the 767- 300BCF configuration, except those listed below: Exemption No. 4725 - Exemption from 25.785(h) -Allows one seat for a required flight attendant to be located near the over wing Type III exits. Does not apply. Exemption 9696, dated May 14, 2008 and corrected on May 22, 2008 provides relief from the requirements of Sections 25.785(j), 25.807(d), 25.807(g)(1), 25.807(i)(1), 25.809(a), 25.810(a)(1), 25.812(e), 25.813(b), 25.857(e), and 25.1447(c)(1) to allow for the carriage of supernumeraries on the 767- 300BCF. Exemption 9696A, dated November 14, 2008 provides relief from the requirements of Sections 25.785(j); 25.807(d), (g)(1), (i)(1); 25.809(a); 25.810(a)(1); 25.812(e); 25.813(b); 25.857(e); and 25.1447(c)(1) to allow for the carriage of supernumeraries on the 767-300BCF. Equivalent Safety Findings: All existing Equivalent Safety Findings listed in TCDS A1NM for the 767-300 Series apply to the 767- 300 operated in the 767-300BCF configuration, except those listed below: • Test Subjects for Emergency Evacuation Demonstration, Section 25.803(c)(8). Does not apply • Passenger Emergency Exits, Section 25.807(a)(7)(iv) and (c). Does not apply • Type III Exit Access, 25.803, 25,807(c) and 25.813(c). Does not apply • Emergency Exit Access, 25.807, 25.809 and 25.813. Does not apply • Exterior + Markings, 25.811(f)(2). Does not apply • “No Smoking” limitation in passenger compartment, 25.791 and 25.853(c). Does not apply • Type A Exit Passageway Dimensions, 25.807 and 25.811. Does not apply • Cross-Aisle between Type III Exits, 25.807 and 25.813. Does not apply • Oxygen Quantity Indication of the Lavatory Supplemental Oxygen System, 25.1441(c). Does not apply Equivalent Safety Findings (ESF’s) exist with respect to the following sections of 14 CFR Part 25: § 25.855(e) - Cargo Compartment Smoke Detection TCDS Notes: All Notes in TCDS A1NM that apply to the 767-300 Series also apply to an airplane operated in the 767- 300BCF configuration. Optional All optional requirements in TCDS A1NM that apply to the 767-300 Series also apply to an airplane operated in the Requirements: 767-300BCF configuration. 12 A1NM V - Model 767-300F (Freighter) (Approved October 12, 1995) Engines: 2 General Electric CF6-80C2B6F or B7F Fuel: General Electric Engines: Fuel conforming to GE Specification D50TF2 All Engines: ASTM D-1655 grades Jet A or Jet A1, or Jet B ASTM D 6615 grades Jet B MIL-T-5624 grades JP-4 or JP-5 MIL-T-83133 grades JP-8 Refer to the FAA approved Airplane Flight Manual listed in Note 2 for fuel limitations. Engine Ratings & Operating Limits: For engine ratings and operating limits see engine TC Data Sheet E13NE for the GE CF6-80C2. Airspeed Limits: VD = 420 KCAS to 17,854 ft/.91M above 23,000 ft, linear variation between these points VFC = 390 KCAS to 17,600 ft/.382 KCAS at 23,000 ft/.87M above 26,000 ft, linear variation between these points VMO = 360 KCAS/.86M VLE = 270 KCAS/.82M VLO = 270 KCAS/.82M For other airspeed limits, see the appropriate FAA-Approved Airplane Flight Manual. CG Range: See the appropriate FAA-Approved Airplane Flight Manual. Maximum Weights: See the appropriate FAA-Approved Airplane Flight Manual. Maximum 0 passengers (767-300F) 2 crew, 4 persons with one floor level exit equipped with inertia reels and right hand Passengers flight crew exit operable from outside. (Exemption No. 5993A) Model Eligible Serial Numbers 767-300F 63110-63129, 63130, 63131, 63132, 63133, 63134-63141, 63142, 63143, 64058-64060, 65791, 65907- 65909, 66240-66247, 66249-66254, 66809-66812, 66864, 66865, 66866, 66867-66869, 67023-67027, 67530, 67531, 67532, 67533, 67534, 67535, 67536, 67537, 67788, 67920, 67968, 67969, 67970, 67971, 67972, 67973, 67974, 67975 767-32LF 41063, 41068, 41069 767-34AF 27239-27243, 27740-27764, 32843, 32844, 37856-37865, 37866-37878, 37944-37947, 65788-65790 767-38EF 25756, 25761, 29129 767-316F 29881, 30780, 30842, 32572, 32573, 34245, 34246, 34627 767-346F 35816, 35817, 35818 767-381F 33404, 33509, 33510, 35709 767-3JHF 37805-37810 767-3S2F 42706-42732, 43538, 43541-43554, 43630-43633, 44377-44380, 61205, 61206, 62497-62500, 63094- 63109, 64055-64057 Certification Basis: Part 25 of the Federal Aviation Regulations as amended by Amendments 25-1 through 25-37, except where superseded by the following sections of Part 25 as amended by Amendments 25-1 through: Amendment Sections 25-38 25.101, 25.161, 25.397, 25.603, 25.675, 25.685, 25.775, 25.787, 25.815, 25.841, 25.941, 25.951, 25.979(a), (b), (c), 25.999, 25.1027, 25.1041, 25.1093(b), 25.1125, 25.1143(a), (b), (c), (d), 25.1167, 25.1303, 25.1305, 25.1322, 25.1355, 25.1385, 25.1403, 25.1439, 25.1515, 25.1533, 25.1557 25-39 25.807 25-40 25.901(a), (b)(1)(ii), (b)(2), (b)(3), (b)(4), (c), 25.903, 25.933, 25.939, 25.943, 25.945, 25.952, 25.959, 25.963, 25.965, 25.973, 25.995, 25.1091(a), (b), (c), (d), 25.1093(a), (c), 25.1121, 25.1123, 25.1141, 25.1145, 25.1197, 25.1199, 25.1207, 25.1337, 25.1549 25-41 25.831, 25.1309, 25.1321, 25.1325, 25.1331, 25.1333, 25.1335, 25.1351, 25.1401, 25.1421, 25.1435, 25.1447, 25.1450, 25.1457, 25.1459, 25.1461 25-42 25.21, 25.29, 25.107, 25.111, 25.143, 25.147, 25.149, 25.177, 25.181, 25.201, 25.207, 25.233, 25.237, 25.255, 25.703, 25.729, 25.1043, 25.1353, 25.1501, 25.1521, 25.1581, 25.1583, 25.1585, 25.1587 25-43 25.1326 25-44 25.1413 25-45 25.571, and 25.573 25-46 25.345, 25.351(a), 25.629, 25.697, 25.803, 25.901(d), 25.1103(a), (b)(2), (d), (e), (f), 25.1142, and 25.1522 25-49 25.733 25-54 25.365 (e)(1), (2) 25-64 25.561 Applies to seats for supernumeraries, galley and rigid barrier 25-72 25.783 Applies to main deck cargo door 13 A1NM V - Model 767-300F (Freighter) (cont’d) Certification Basis (Cont’d) Compliance with the following optional requirements has been established with respect to the following sections of 14 CFR Part 25: §25.801 - Ditching Provisions (Over- water operation can be approved when the aircraft has been equipped and installation has been approved according to 14 CFR 25.801) §25.1419 - Ice Protection Provisions 14 CFR §26: (Based on 14 CFR §21.101(g) for changes made to TCs applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections). Compliance has been found for the following regulations at Amendment 26-0: 26.11 and Amendment 26-1: 26.43, 26.45, 26.47, 26.49 and Amendment 26-3: 26.39 14 CFR part 34 as amended by Amendments 34-1 through 34-7A 14 CFR part 36 of the Federal Aviation Regulations with Amendments 36-1 through 36-12, effective August 1, 1981. See the appropriate FAA Approved Airplane Flight Manual listed in Note (2) for applicability of Stage 4 Noise Recertification through Amendment 36-28. Special Federal Aviation Regulation 27 Exemption from Part 25: Exemption Title Issued Date Expiration Date 5993 Partial Exemption from 25.807(c)(1) and 25.857(e) - Allows for the carriage of up to seven persons including the flight crew members, when the airplane is equipped with a floor level exit with escape slide, and a right hand flight crew window emergency exit that is operable from the outside 23 November 1994 Permanent 5993A Partial Exemption from 25.809(f)(1) - Allows for the carriage of persons other than flight crew members. In lieu of an escape slide, the emergency evacuation assist means at the entry door shall be an inertial reel descent device and harness provided for each occupant. See Note 12 9 August 1995 Permanent 8119 Partial Exemption from §25.901(c), Single Failures resulting in Uncontrollable High Thrust Conditions 11 June, 2003 Permanent 9791C Partial Time-Limited Exemption from 14 CFR §25.853(a), appendix F, paragraph (a)(1)(i), Testing on Large Interior Panels (Expired Exemption No. 9791, November 28, 2010, Exemption No. 9791B, 28 February, 2011) 28 November, 2008 28 November, 2011 10767D Time-limited exemption from 14 CFR 25.901(c) and 25.981(a)(3), fuel tank ignition prevention associated with to the latent-plus-single failures for the FQIS processor, and fuel-quantity-system wiring that is co-routed with airplane wiring carrying electrical power exceeding intrinsically safe levels. (Expired Exemption No. 10767, 17 May, 2016, Exemption No. 10767A, 17 May, 2016, Exemption 10767C, 31 December, 2019) 17 December, 2015 31 December, 2027 14593 Exemption from SFAR 88, and §§ 25.901(c) and 25.981(a)(3), as they pertain to fuel-tank-ignition prevention associated with the fuel-quantity indication system and fuel-overfill-shutoff surge tank wiring installation, limited to in-service 767-300 (freighter only) 25 January, 2016 Permanent Equivalent Safety Findings (ESF’s) exist with respect to the following sections of 14 CFR Part 25: ELOS IP Title 14 CFR AT00010BA-T-S-1 Powerplant And Auxiliary Power Unit Instruments 25.1549(b) AT0141SE-T-S-1 Supplemental Oxygen Equipment 25.1447(c)(1) and (3) AT0328ST-T-C-5 "No Smoking" limitation in the passenger compartment 25.791,25.853, CAR 4b.3 81 AT1736SE-T-C-14 Door Sill Reflectance 25.811 PS05-0123-P-1 Ground Fault Interrupter Relays 25.981(a)(3) PS05-0177-P-2 Fuel Tank Flammability Rule (see Note 17) 25.981 (25-125) PS06-0496-F-18 Engine and Auxiliary Power Unit (APU) Fire Switch Handle Design 25.1555(d)(1) PS08-0670-C-1 Adhesives Used in Interior Panel Bent Joint Potting Applications 25.853(a) 14 A1NM V - Model 767-300F (Freighter) (cont’d) Certification Basis (Cont’d) Equivalent Safety Findings (cont’d) ELOS IP Title 14 CFR PS13-1000-C-5 Flammability Testing Hierarchy 25.853(a)(d), part 25 appendix F parts I and IV ST06344WI-T_P-1 Powerplant Instrumentation for RCI LDS-2100 Installation on Boeing 767- 300F Series Aircraft 25.1549(b), (c) TC6918SE-T- G-8 Formatting of Boeing Instructions for Continued Airworthiness Manuals - Airworthiness Limitations 25.1529 (25-54) 25.1729(25-123) Appendix H (25-132) TD1990SE-T-C-1 Emergency Locator Transmitter (ELT) 25.1415(d) TD2695SE-T-C-1 Exterior Exit Markings 25.811(f) TS13-0005-S-1 Determination of Minimum Oxygen Flow for the Lavatory Oxygen System 25.1443(c) Special Conditions with respect to the following subjects apply: Special Condition Title Effective Date 25-ANM-18 Lightning Protection, Protection from Unwanted Effects of Radio Frequency (RF) Energy and Propulsion Control System for Pratt and Whitney PW4000 series engines, General Electric CF6-80C2 FADEC engine, and Rolls Royce RB211-524H-36 engine installations 29 April, 1988 25-630-SC Non-Rechargeable Lithium Batteries 22 April, 2017 VI - 767-300F Major Design Change – Large Format Display System The aircraft listed below were produced with a Rockwell Collins, Inc. STC number ST01750WI installed in production. As a result, the certification basis for these aircraft has been advanced for the areas associated with the STC as identified below. Section V (767-300F) of this TCDS remains applicable for all regulatory aspects not discussed below. Certification Basis: The certification basis is advanced for the following regulations for the areas listed below: SECTION NO. TITLE AT AMDT. 25- 25.143(b) General – Controllability and Maneuverability 129 25.305(a)(b)(c) Strength and Deformation 86 25.307(a) Proof of Structure 72 25.561 General – Emergency Landing Conditions 91 25.603 Materials 46 25.605(a) Fabrication Methods 46 25.611 Accessibility Provisions 123 25.613(a)(b)(c) Material Strength Properties and Material Design Values 112 25.625(a)(b)(c) Fitting Factors 72 25.773(a) Pilot Compartment View 136 25.777(a)(b)(c) Cockpit controls 46 25.831(d) Ventilation 89 25.853(a) Compartment Interiors 116 25.869(a) Fire Protection System 72 25.899 Electrical Bonding and Protection Against Static Electricity 123 25.1301(a) Function and Installation 123 25.1303 Flight and Navigation Instruments 90 25.1305(a)(3-6),(c)(1-3),(d)(1)(3) Powerplant Instruments 115 25.1307(e) Miscellaneous Equipment 72 25.1309(a)(b)(c)(d)(e) Equipment Systems and Installations 123 25.1310(a)(1)(2)(3)(i) Power Source Capacity and Distribution 123 15 A1NM VI - 767-300F Major Design Change – Large Format Display System (Cont’d) Certification Basis (Cont’d) SECTION NO. TITLE AT AMDT. 25- 25.1316 System lightning protection 134 134 25.1317(a)(b)(c) High-intensity Radiated Fields (HIRF) Protection 122 25.1322 Warning, Caution, and Advisory Lights 131 25.1323(a)(f)(g) Airspeed Indicating System 109 25.1329(i)(j)(k) Flight Guidance System 119 25.1351(a) General - Electrical Systems and Equipment 72 25.1353(a)(c) Electrical Equipment and Installations 123 25.1360(b) Precautions Against Injury 123 25.1381(a)(b) Instrument Systems 72 25.1431 Electronic Equipment 113 25.1438(b) Pressurization and Pneumatic Systems 41 25.1459(c) Flight Recorders 124 25.1535 Appx. K25.1.1 ETOPS Approval 120 25.1535 Appx. K25.1.2 ETOPS Approval 120 25.1551 Oil Quantity Indicator 72 25.1581(a)(2) Airplane Flight Manual 72 25.1583(c)(1) Operating Limitations 130 25.1585(a)(b) Operating Procedures 105 Changed Areas: The following is a high level description of the listing of changes incorporated as part of the installation of the Rockwell Collins LDS Amended STC ST01750WI: • Installed new forward instrument panel to accept new line-replaceable units (LRU) • Installed graphics generator units (3 GGUs) • Installed adaptive flight displays (3 AFDs) • Installed display control panels (2 DCPs) • Installed display dimming panels (2 DDPs) • Installed operational software for the GGU Equivalent Safety Findings which apply only to the Model 767-300F series with incorporation of STC exist with respect to the following sections of 14 CFR Part 25: §25.1549(b) & (c) - Powerplant [and auxiliary power unit instruments] (ELOS Memo SA06180WI-T-P-1). Model Eligible Serial Numbers 767-300F 63110-63129, 63130, 63131, 63132, 63133, 63134- 63141, 63142, 63143, 64058-64060, 65791, 65907- 65909, 66240-66247, 66249-66254, 66809-66812, 66864, 66865, 66866, 66867- 66869, 67023- 67027, 67530, 67531, 67532, 67533, 67534, 67535, 67536, 67537, 67788, 67920, 67968, 67969, 67970, 67971, 67972, 67973, 67974, 67975 767-34AF 65788-65790 767-3S2F 42720-42732, 43538, 43541, 43547-43554, 43630-43633, 61205, 61206, 62497-62500, 63094-63109, 64055- 64057 VII – Model 767-400ER (Approved July 20, 2000) Engines: 2 General Electric CF6-80C2B8F Fuel: General Electric Engines: Fuel conforming to GE Specification D50TF2 ASTM-D-1655 grades Jet A or Jet A1 ASTM D6615 grades Jet B MIL-T-5624 grades JP-4 or JP-5 MIL-T-83133 grades JP-8 Refer to the FAA approved Airplane Flight Manual listed in Note 2 for fuel limitations Engine Ratings & Operating Limits: For engine ratings and operating limits see engine TC Data Sheet E13NE for the GE CF6-80C2. Airspeed Limits: VD = 420 KCAS to 17,854 ft/. 91M above 23,000 ft., linear variation between these points VFC = 390 KCAS to 17,600 ft/. 382 KCAS at 23,000 ft/. 87M above 26,000 ft, linear variation between these points VMO = 360 KCAS/. 86M VLE = 270 KCAS/. 82M VLO = 270 KCAS/. 82M For other airspeed limits, see the appropriate FAA-Approved Airplane Flight Manual. 16 A1NM VII – Model 767-400ER (cont’d) Certification Basis (Cont’d) CG Range: See the appropriate FAA-Approved Airplane Flight Manual. Maximum Weights: See the appropriate FAA-Approved Airplane Flight Manual. Maximum 375 with the as designed exit configuration Passengers: Model Eligible Serial Numbers 767-424ER 29446-29461 767-432ER 29699-29719 767-4FSER 34205 Certification Basis: Title 14 Code of Federal Regulations (CFR) Part 25 as amended by Amendments 25-1 through 25-89 for the complete airplane with the exceptions listed below: SECTION NO. TITLE AT AMDT. 25- 25.101 Performance - General 92 25.105 Takeoff 92 25.107 Takeoff Speeds 92 25.109 Accelerate-Stop Distance 92 25.113 Takeoff Distance and Takeoff run 92 25.115 Takeoff Flight Path 92 25.341 Gust Loads 861 25.365(d) Pressurized Compartment Loads 71 25.365(e)(2) Pressurized Compartment Loads 546 25.499(e) Nose Wheel Yaw 91 25.519(b)(2) Jacking and Tie-down Provisions not part of the TC basis 25.562 Emergency Landing Dynamic Conditions 643 25.571 Damage - Tolerance and Fatigue Evaluation of Structure 45 25.703 Takeoff Warning System 424 25.735 Brakes 92 25.783(e), (g) Doors 235 25.783(f) Doors not part of the TC basis 25.831(a) Ventilation 41 25.831 (b)(2) Ventilation 41 25.831(g) Ventilation not part of the TC basis 25.841 Pressurization 38 25.853(d)(3) Compartment Interiors 72 25.855 Cargo or Baggage Compartments 722, 32 25.858(a) Cargo Compartment Fire Detection Systems not part of the TC basis 25.903(d) Engines 40 25.903(e) Engines 734 25.1316 System Lightning Protection 807 25.1419(c) Ice Protection 23 25.1517 (2) Rough Air Speed for Turbulence Penetration Speed not part of the TC basis 25.1533 Additional Operating Limitations 92 767-400ER Exception Notes: 1. For damage tolerance analysis, to be compatible with the requested reversion to Amendment 25-45 for §25.571, Boeing proposes to comply with Amendment 25-0 for static strength (fail-safe) analysis resulting from single element failures of the strut towing attachment interfaces. 2. Applicable to systems, equipment installations, and structures that are new and significantly modified, or significantly affected by other changes. Where two amendment levels are shown for the same paragraph, the amendment level without the superscript (2) applies to structures, systems and portions of the airplane, which are not new or significantly modified. 3. Pilot/Co-Pilot Seats: Pilot/co-pilot seats will comply with Amendment 25-64 except paragraph (c)(5), (c)(6). Passenger Seats: Passenger seats will comply with Amendment 25-64 except for Front Row Head Impact Criteria (HIC) per paragraph (c)(5). Stretchers for transporting non-ambulatory occupants are not required to comply with §25.562. Flight Deck Observer Seats: Flight Deck Observer seats will comply with Amendment 25-64 except paragraph (c)(6). Flight Attendant seats: Flight Attendant seats will comply with Amendment 25-64. 17 A1NM VII – Model 767-400ER (cont’d) Certification Basis (Cont’d) 767-400ER Exception Notes (Cont’d): 4. Boeing intends to comply with the amendment level indicated for this rule, however, Boeing requests an exception to the latest policy and prefers to revert to the earlier policy. 5. The equivalent regulation to §25.783(g) at Amendment 25-88 is §25.783(f) at Amendment 25-23. The equivalent regulation to §25.783(g) at Amendment 25-23 is §25.783(h) and (i) at Amendment 25-88. Unchanged doors will comply with §25.783(e) and (f) at Amendment 25-23. Any new doors will comply with §25.783(e)-(g) at Amendment 25-88. 6. Reversion is requested for sub-paragraph (2) only. That is, Boeing will comply with paragraph (e) at Amendment 25-87, combined with (2) at Amendment 25-54. 7. For §25.1316, Applicable to new and significantly modified structure and systems and portions of the airplane affected by these changes. 14 CFR §26: Based on 14 CFR §21.101(g) for changes made to TCs applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Compliance has been found for the following regulations at Amendment 26-0: 26.11 Compliance has been found for the following regulations at Amendment 26-1: 26.43, 26.45, 26.47, and 26.49 Part 34 as amended at the time of certification. Part 36, as amended at the time of certification. Part 121 is sometimes amended to require compliance with newly adopted standards of Part 25 on retroactive basis. If not already included in the above type-certification basis, Boeing will be requested to voluntarily accept the corresponding Part 25 standards as part of the type-certification basis for these derivative airplanes in order to facilitate operators' compliance with any such newly adopted Part 121 requirements. Exemption from Part 25: Exemption Title Issued Date Expiration Date 6886 Exemption from §25.1435(b)(1), Hydraulic Proof Pressure Test 8 April, 1999 Permanent 6935 Exemption from §25.562(b)(2), Floor Warpage for Flight Deck Seats 4 August, 1999 Permanent 8119 Partial Exemption from §25.901(c), Single Failures resulting in Uncontrollable High Thrust Conditions 11 June, 2003 Permanent 9791C Partial Time-Limited Exemption from 14 CFR §25.853(a), appendix F, paragraph (a)(1)(i), Testing on Large Interior Panels (Expired Exemption No. 9791, November 28, 2010, Exemption No. 9791B, 28 February, 2011) 28 November, 2008 28 November, 2011 10767C Time-limited exemption from 14 CFR 25.901(c) and 25.981(a)(3), fuel tank ignition prevention associated with the FQIS is limited to the replacement of the ARINC 429 chip within the fuel quantity processer unit’s IOC cards and the BITE card (Expired Exemption No. 10767, 17 May, 2016, Exemption No. 10767A, 17 May, 2016) 17 December, 2015 17 May, 2016 Equivalent Safety Findings (ESF’s) exist with respect to the following sections of 14 CFR Part 25: ELOS IP Title 14 CFR AT00010BA-T-S-1 Powerplant And Auxiliary Power Unit Instruments 25.1549(b) AT0328ST-T-C-5 "No Smoking" limitation in the passenger compartment 25.791,25.853, CAR 4b.3 81 AT1736SE-T-C-14 Door Sill Reflectance 25.811 AT2251SE-T-A-2 Material Design Values 25.613 AT2251SE-T-C-2 Escape Slide Inflation Times 25.809(b)(2), 25.810(a)(1) 18 A1NM VII – Model 767-400ER (cont’d) Certification Basis (Cont’d) Equivalent Safety Findings (Cont’d) ELOS IP Title 14 CFR AT2251SE-T-F-1 Use of the 1-g Stall Speed Instead of Minimum Speed in the Stall as a Basis for Determining Compliance (Non-Structural Sections) 1.2, 25.21(b), 25.103(a),(a)(1),(a)(3- 6),(b)(c), 25.107(b)(1),(b)(2),(c)(3),(g), 25.111(a), 25.119(b), 25.121(c),(d),(d)(3), 25.125(a)(2), 25.143(g), 25.145(a),(a)(1),(b)(1- 4),(b)(6),(c), 25.147 (a),(a)(2),(c),(d), 25.149 (c), 25.161(b),(c)(1),(c)(2),(c)(3)(d),(e)(3), 25.175(a)(2),(b)(1),(b)(2),(b)(2)(ii),(b) (3),(c),(c)(4),(d),(d)(5), 25.177(c), 25.181(a),(b), 25.201(a)(2),(b)(4), 25.207(b),(c),(d),(e),(f), 25.231(a)(2), 25.233(a), 25.237(a),(b)(1),(b)(2), 25.735(f)(2),(g), 25.773(b)(1)(i), 25.1001(c)(1),(c)(3), 25.1323(c)(1),(c)(2), 25.1325(e), 25.1587(b)(2) AT2251SE-T-P-3 Flight Critical Thrust Reversers 25.933(a)(1)(ii) AT2251SE-T-P-4 Auxiliary Power Unit Induction System 25.1103(e) AT2251SE-T-P-5 Auxiliary Power Unit (APU) Instrumentation and Monitoring Requirements and Operation as an Alternate Electrical Power Source 25.1305(a)(3-6), (c)(l), (c)(3), (c)(4) and (c)(6) AT2251SE-T-P-6 Auxiliary Power Unit (APU) Operating Limitations 25.1522 and 25.1549 AT2251SE-T-S-1 Overspeed Aural Warning 25.1303(c)(1) AT2251SE-T-S-4 Airplane Operation with Air Conditioning Packs Off During Takeoff 25.831(a) AT4965SE-T-A-2 Material Design Values 25.613 PS05-0123-P-1 Ground Fault Interrupter Relays 25.981(a)(3) PS05-0177-P-2 Fuel Tank Flammability Rule (see Note 17) 25.981 (25-125) PS06-0496-F-18 Engine and Auxiliary Power Unit (APU) Fire Switch Handle Design 25.1555(d)(1) PS08-0670-C-1 Adhesives Used in Interior Panel Bent Joint Potting Applications 25.853(a) PS13-0901-ES-1 Oxygen Quantity Indication of the Lavatory Supplemental Oxygen System 25.1441(c) PS13-1000-C-5 Flammability Testing Hierarchy 25.853(a)(d), part 25 appendix F parts I and IV TC6918SE-T- G-8 Formatting of Boeing Instructions for Continued Airworthiness Manuals - Airworthiness Limitations 25.1529 (25-54) 25.1729(25-123) Appendix H (25-132) TD2695SE-T-C-1 Exterior Exit Markings 25.811(f) TD7075SE-T-C-1 Type III Exit Accessibility 25.803, 25.807(c), 25.813(c) TS13-0005-S-1 Determination of Minimum Oxygen Flow for the Lavatory Oxygen System 25.1443(c) 19 A1NM VII – Model 767-400ER (cont’d) Certification Basis (Cont’d) Special Conditions with respect to the following subjects apply: Special Condition Title Effective Date 25-149-SC Sudden Engine Stoppage 16 September, 1999 25-152-SC High Intensity Radiated Fields (HIRF) 3 January, 2000 25-369-SC Seats with Non-Traditional, Large, Non-Metallic Panels 17 March, 2008 25-448-SC Seats with Inflatable Lapbelts 6 October, 2011 25-630-SC Non-Rechargeable Lithium Batteries 22 April, 2017 VIII - Model 767-2C (Approved December 21, 2017) Engines: Two Pratt and Whitney PW4062, Reference Engine Type Certificate No. E24NE Refer to the FAA approved Airplane Flight Manual identified in Note 2 for engine limitations. Fuel: Jet A and Jet A-1 as specified in ASTM D1655 JP-5 as specified in MIL-DTL-5624 JP-8 as specified in MIL-DTL-83133 Any other fuel specified in Pratt and Whitney Service Bulletin 2016 Refer to the FAA approved Airplane Flight Manual listed in Note 2 for fuel limitations Engine Ratings & Operating Limits: For engine ratings and operating limits see engine TC Data Sheet E24NE or the FAA Approved Airplane Flight Manual Airspeed Limits: VD = 420 KCAS to 17,854 ft/.91M above 23,000 ft, linear variation between these points. VFC = 390 KCAS to 17,600 ft/382 KCAS at 23,000 ft/.87M above 26,000 ft, linear variation between these points. VMO = 360 KCAS / .86M VLE = 270 KCAS / .82M VLO = 270 KCAS / .82M For other airspeed limits, see the appropriate FAA-Approved Airplane Flight Manual C. G. Range: See appropriate FAA approved Airplane Flight Manual. Maximum Weights: See appropriate FAA approved Airplane Flight Manual. Pilot Type Rating: The Boeing 767-2C has not been evaluated by the Flight Standards Board. No pilot type rating or training, checking and currency requirement determinations have been made. Maximum 14 (767-2C) 4 flight crew members in the flight deck and 10 supernumeraries in the aircrew member compartment Passengers: Model Eligible Serial Numbers (See Note 19) 767-2C 34052, 34061, 34075, 34076, 34077, 34078, 34079, 34080, 34086-34092, 34105-34115, 34121, 34124, 34126, 34127, 34134-34141, 41855, 41858, 41859, 41860, 41861, 41863-41868, 41870, 41873, 41874, 41878, 41879, 41881, 41883-41886, 41888, 41889, 41890, 41891, 41892, 41893, 41894, 41895, 41896, 41897, 41898, 41899, 41901, 41902, 41903, 41904, 41905, 41906, 41907, 41908, 41909, 41910, 41911, 41912, 41913, 41915, 41920, 41925, 41984, 41985, 41986, 66585, 66622, 67061, 67062 Certification Basis: Title 14, Code of Federal Regulations (14 CFR) part 25 as amended by Amendments 25-0 through 25-136 with exceptions permitted by 14 CFR 21.101 SECTION No. TITLE AT AMDT 25- EXCEPTION APPLIES TO: 25.21 Proof of compliance. 72 Entire Airplane 25.103 Stall speed. 108 Entire Airplane 25.105 Takeoff. 92 Entire Airplane 25.107 Takeoff speeds. 108 Entire Airplane 25.111 Takeoff path. 115 Entire Airplane 25.119 Landing climb: All-engines- operating. 108.94 Entire Airplane 20 A1NM VIII - Model 767-2C (Cont’d) Certification Basis (Cont’d) SECTION No. TITLE AT AMDT 25- EXCEPTION APPLIES TO: 25.121 Climb: One-engine-inoperative. 108 Entire Airplane 25.123 En route flight paths. 0 Entire Airplane 25.125 Landing. 108 Entire Airplane 25.143 General. 108 Entire Airplane 25.207 Stall warning. 108 Entire Airplane 25.237 Wind velocities. 108 Entire Airplane 25.253(c) High-speed characteristics. N/A Entire Airplane 25.335(b)(2) Design airspeeds. 23 Loads: Design Dive Speeds 25.365(e)(2) Pressurized cabin loads. 54* Section 41 and Underwing Structures * See paragraph below, “Additional Design Requirements and Conditions,” for information on required design features. 25.519(b)(2) Jacking & tie-down provisions. N/A* Primary Jacking Points * See paragraph below, “Additional Design Requirements and Conditions,” for information on required design features. 25.571(a) and (b), except (b)(1) through (b)(6) Damage-tolerance and fatigue evaluation of structure. 86* Structures1 * See paragraph below, “Additional Design Requirements and Conditions,” for information on required design features. 25.603 Materials. 38 Empennage: ▪ Fin and Rudder (except wire brackets/installation on rear spar and fixed trailing edge panels between Rudder Sta. 230.97 and 305.87) ▪ Horizontal Stabilizer Elevators and Fix Engine Nacelle: ▪ Engine Nacelle Fan Cowl Panel Engine Pylon: Pylon Forward, Underwing, and Nacelle Fairings and all related fairing support structure 21 A1NM VIII - Model 767-2C (Cont’d) Certification Basis (Cont’d) SECTION No. TITLE AT AMDT 25- EXCEPTION APPLIES TO: 25.613 Material strength properties and design values. 0 Fuselage: ▪ Nose Landing Gear Doors and support structure Empennage: ▪ Fin and Rudder (except wire brackets/installation on rear spar and fixed trailing edge panels between Rudder Sta. 230.97 and 305.87) ▪ Horizontal Stabilizer Elevators and Fixed TE Engine Nacelle: ▪ Engine Nacelle Fan Cowl Panel Engine Pylon: ▪ Pylon Forward, Underwing, and Nacelle Fairings and all related fairing support structure Flight Control Systems: ▪ Primary Flight Control hydraulic equipment (except Elevator Feel Computer, and Elevator Feel Shift Module) Landing Gear Systems: ▪ Landing Gear Actuation System (except for gear extension/retraction command, alternate extend cable load limiter, and flight deck indication) ▪ Brake Control System (except for right brake control cable and antiskid light and brake temperature indication) Nose Wheel Steering System 25.615 Design properties. 23 Fuselage: ▪ Nose Landing Gear Doors and support structure Empennage: ▪ Fin and Rudder (except wire brackets/installation on rear spar and fixed trailing edge panels between Rudder Sta. 230.97 and 305.87) ▪ Horizontal Stabilizer Elevators and Fixed TE Engine Nacelle: ▪ Engine Nacelle Fan Cowl Panel Engine Pylon: ▪ Pylon Forward, Underwing, and Nacelle Fairings and all related fairing support structure Flight Control Systems: ▪ Primary Flight Control hydraulic equipment (except Elevator Feel Computer, and Elevator Feel Shift Module) Landing Gear Systems: ▪ Landing Gear Actuation System (except for gear extension/retraction command, alternate extend cable load limiter, and flight deck indication) ▪ Brake Control System (except for right brake control cable and antiskid light and brake temperature indication) Nose Wheel Steering System 25.729 Retracting mechanism. 42 Landing Gear Systems: Electrical Subsystems Landing Gear Position Indication 25.735 Brakes. 23 Landing Gear Systems: Brake Control System (except for right brake control cable and antiskid light and brake temperature indication) 22 A1NM VIII - Model 767-2C (Cont’d) Certification Basis (Cont’d) SECTION No. TITLE AT AMDT 25- EXCEPTION APPLIES TO: 25.735(a), (f)(1), (f)(2), (g), (h)(1) and (h)(2) Brakes. 92 Landing Gear Systems: Tires, Wheels, and Brakes 25.773(b)(2) Pilot compartment view. 23 Flight Crew Operations: Pilot Compartment View 25.777 Cockpit controls. 0 Landing Gear Systems: Brake Control System (except for right brake control cable and antiskid light and brake temperature indication) 25.783 Doors. 23 Fuselage: ▪ Wing-to-Body Fairing Access Door Assy - ADP, Aft Fairing3 ▪ Wing-to-Body Fairing Access Door Assy - Hydraulic Reservoir Fill, Aft Fairing3 ▪ Wing-to-Body Fairing Access Door Assy - Pressure Bottle, Aft Fairing3 ▪ Wing-to-Body Fairing Panel Assy - Pressure Relief Door, Aft Fairing3 ▪ Wing-to-Body Fairing Door Assy - RAT, Aft Fairing3 ▪ Wing-to-Body Fairing Underwing Fairing Access Panels/Doors3 Fuselage Doors: ▪ Fwd Access Door ▪ EE Access Door ▪ Lower Fwd Small Cargo Door ▪ Lower Aft Small Cargo Door ▪ Aft Entry and Service Doors ▪ Overwing Exit Doors ▪ Electrical Subsystems Door Control and Indication Flight Deck Windows: Flight Deck No. 2 Openable Window3 25.783(c)(2) Doors. N/A* Fuselage Doors: ▪ Fwd Entry and Service Doors2 * See paragraph below, “Additional Design Requirements and Conditions,” for information on required design features. 25.795(b)(1) Security considerations 106 Entire Airplane 25.795(c)(2) Security considerations. 106* Entire Airplane4 25.809(a) Emergency Exit Arrangement. 34 Escape Systems: ▪ Flight Deck Window Egress Viewing Means Overwing Exit and Aft Exit Windows Viewing Means 25.863 Flammable fluid fire protection. 23 Landing Gear Systems: ▪ Landing Gear Actuation System (except for gear extension/retraction command, alternate extend cable load limiter, and flight deck indication) Brake Control System (except for right brake control cable and antiskid light and brake temperature indication) 25.869 Fire protection: Systems. N/A Landing Gear Systems: ▪ Landing Gear Actuation System (except for gear extension/retraction command, alternate extend cable load limiter, and flight deck indication) Brake Control System (except for right brake control cable and antiskid light and brake temperature indication) 25.1021 Oil drains. 0 Engine Systems: Engine Oil System (drainage hardware) 23 A1NM VIII - Model 767-2C (Cont’d) Certification Basis (Cont’d) SECTION No. TITLE AT AMDT 25- EXCEPTION APPLIES TO: 25.1091(e) Air induction. N/A Engine Systems: Engine Inlet Probe 25.1093(b) Induction system deicing and anti-icing provisions. 38 Engine Systems: Engine Operability 25.1163(a) Powerplant accessories. 0 Engine Systems: Engine Air Turbine Starter Oil System 25.1183 Flammable fluid-carrying components. 57 Engine Systems: Engine Air/Vent System (hardware) 25.1301 Function and installation. 0 Entire Airplane 25.1309 Equipment systems and installations. 41 Entire Airplane 25.1310 Power source capacity and distribution. N/A Entire Airplane 25.1316 System lightning protection. N/A* Avionics: ▪ Thrust Management Computer Flight Control Systems: ▪ Spoiler Control System Electronics Unit ▪ Spoiler Control Module ▪ High Lift System Landing Gear Systems: ▪ Brake Control System (except for right brake control cable and antiskid light and brake temperature indication) Environmental Control Systems: ▪ Ice and Rain Protection Systems (Window Heat System only) * See paragraph below, “Additional Design Requirements and Conditions,” for information on required design features. 25.1317 High-intensity radiated fields (HIRF) protection. N/A* Avionics: ▪ Thrust Management Computer Flight Control Systems: ▪ Spoiler Control System Electronics Unit ▪ Spoiler Control Module ▪ High Lift System Landing Gear Systems: ▪ Brake Control System (except for right brake control cable and antiskid light and brake temperature indication) Environmental Control Systems: ▪ Ice and Rain Protection Systems (Window Heat System only) Engine Systems: ▪ Engine Control System *See paragraph below, “Additional Design Requirements and Conditions,” for information on required design features. 25.1353. Electrical equipment and installations. 42 Landing Gear Systems: ▪ Landing Gear Actuation System (except for gear extension/retraction command, alternate extend cable load limiter, and flight deck indication) Brake Control System (except for right brake control cable and antiskid light and brake temperature indication) 25.1360 Precautions against injury. N/A Landing Gear Systems: ▪ Landing Gear Actuation System (except for gear extension/retraction command, alternate extend cable load limiter, and flight deck indication) Brake Control System (except for right brake control cable and antiskid light and brake temperature indication) 24 A1NM VIII - Model 767-2C (Cont’d) Certification Basis (Cont’d) SECTION No. TITLE AT AMDT 25- EXCEPTION APPLIES TO: 25.1365(d) Electrical appliances, motors and transformers N/A Primary Flight Controls ▪ Aileron lockout actuator ▪ Lateral trim actuator ▪ Rudder trim actuator ▪ Autospeed brake actuator ▪ Stabilizer trim control module motor motor-operated valve Avionics High frequency transceiver equipment 25.1419 Ice protection. 23 Entire Airplane5 25.1431 Electronic equipment. 0 Landing Gear Systems: Brake Control System (except for right brake control cable and antiskid light and brake temperature indication) 25.1435 Hydraulic systems. 41 Flight Control Systems: ▪ Primary Flight Control hydraulic equipment (except Elevator Feel Computer, and Elevator Feel Shift Module) ▪ High Lift System Landing Gear Systems: ▪ Landing Gear Actuation System (except for gear extension/retraction command, alternate extend cable load limiter, and flight deck indication) ▪ Brake Control System (except for right brake control cable and antiskid light and brake temperature indication) Nose Wheel Steering System 25.1435 Hydraulic systems. 72 Flight Control Systems: ▪ Elevator Control System Feel Shift Module Elevator Control System Feel Computer Exception Notes: 1. The certification requirement for § 25.571(a) and (b) is Amendment 25-86. The certification requirement for §§ 25.571(b)(1), (b)(2), (b)(3), (b)(4), (b)(5) and (b)(6) is Amendment 25-132. 2. The certification requirement for the Forward Entry and Service Doors is § 25.783 Amendment 25-114, except that the self-latching requirement of § 25.783(c)(2) does not apply; the self-latching requirement of subparagraph (c)(2) did not exist prior to Amendment 25-114. 3. Section 25.783 is not applicable to this area at Amendment 25-23. 4. Compliance is not required (for the entire airplane) for the following regulations: §§ 25.795(c)(2), (c)(2)(i), and (c)(2)(ii) 5. Compliance with the ice protection requirements of § 25.1419 at Amendment 25-23 includes compliance with part 25 appendix C at Amendment 25-0. Optional Design Requirements: Ditching: §§ 25.801; 25.1411(d), (e), (f), and (g); and 25.1415 Ice Protection: § 25.1419 14 CFR §26: 14 CFR part 26 as amended by Amendment 26-1 through 26-6. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Compliance has been found for the following regulations: §26.11 at Amendment 26-0 §26.49 at Amendment 26-1 §§26.33 and 26.39 at Amendment 26-3 §§26.43 and 26.45 at Amendment 26-4 §26.21 at Amendment 26-6 14 CFR part 34 as amended by Amendments 34-1 through 34-7A. 14 CFR part 36 as amended by Amendments 36-1 through 36-30 25 A1NM VIII - Model 767-2C (Cont’d) Certification Basis (Cont’d) Additional Design Requirements and Conditions (ADRC) for 767-2C: 14 CFR 21.35(a), (b)(2) and (f)(2) – All model 767-2C aircraft must be flown with a Boeing pilot in command prior to the completion of that aircraft model’s F&R testing. 14 CFR 25.365(e)(2) – Pressurized Compartment Loads for the Flight Deck Compartment, E/E Bay and Nose Wheel Well volumes of Section 41 and the Underwing Keel Beam Cavity. When evaluating these compartments for compliance with §25.365(e)(2) Amendment 25-54, the compartments must be analyzed in accordance with the conditions identified below. In lieu of the following, compliance with §25.365 at Amendment 25-87, may be shown: 1. Flight deck compartment - 840 in2 hole in the fuselage. 2. E/E Bay / Nose Wheel Well Compartment - 415 in2 hole in the fuselage. 3. Underwing Keel Beam Cavity - 115 in2 hole in the front spar bulkhead. 14 CFR 25.519(b)(2) – Jacking and tie-down provisions The following design features must be incorporated in the type design (reference § 25.519, Amendment N/A). In lieu of incorporating the following design features, compliance with § 25.519 at Amendment 25-81, may be shown: The primary jacking points on the body and wing shall be designed for the following ultimate conditions with the maximum jacking loads prescribed in the Maintenance Manual: a) Vertical 2.5 factor b) Vertical 2.0 factor and side 0.50 factor (acting singularly) c) Vertical 2.0 factor and longitudinal 0.50 factor (acting singularly) 14 CFR 25.571(a) and (b) [excluding (b)(1) through (b)(6)] – Damage-tolerance and fatigue evaluation of structure, Model 767-2C Airplane Structures. The following design features must be incorporated in the type design (reference §25.571(a) and (b), Amendment 25-86). In lieu of incorporating the following design features, compliance with §25.571(a) and (b), Amendment 25-132, may be shown: 1. For the Model 767-2C structure, an evaluation of the existing damage tolerance analysis (DTA) maintenance actions must be performed to determine if any changes are required due to changes in loads, geometry, material, etc. New or changed maintenance actions for the 767-2C must be included in the Airworthiness Limitations Document D011T030-01-01 in accordance with §25.571(a)(3) at Amendment 25-86. 2. The above evaluation must include loading magnitudes and loading spectra which are developed in accordance with § 25.571 at Amendment 25-96. This includes usage of the 1.15 factor for pressure acting alone in accordance with § 25.571(b)(5) at Amendment 25-96. 3. Maintenance instructions must be based on in-service data and fatigue testing to ensure freedom from widespread fatigue damage. 14 CFR 25.783(c)(2) – Doors. Forward Entry and Service Doors The following design features must be incorporated in the type design (reference § 25.783(c)(2), Amendment N/A). In lieu of incorporating the following design features, compliance with § 25.783(c)(2) at Amendment 25-114, may be shown: These doors must remain open to the extent necessary to prevent pressurization or safely close (but not latch) as pressurization takes place. 14 CFR 25.1316 – System Lightning Protection The following design features must be incorporated in the type design (reference § 25.1316, Amendment N/A). In lieu of incorporating the following design features, compliance with § 25.1316 at Amendment 25-134, may be shown: 1. Thrust Management Computer (TMC). The following design features are required to minimize exposure of the TMC to coupled lightning transients: a. TMC wiring routed to the Electronic Engine Control (inside the pressure vessel) must incorporate enhanced shielding, i.e. have a single, braided shield, grounded at every break. b. TMC wiring routed to the Electronic Engine Control (outside the pressure vessel) must incorporate enhanced shielding, i.e., have a second layer of shielding (typically overbraid) applied to it, and the majority of this shielding must be terminated peripherally at pressure hull, at outboard equipment, and all disconnects between the outboard equipment and pressure hull. 2. Window Heat System. The following design features are required to minimize exposure of the Window Heat System to coupled lightning transients: a. The power and sensor wiring between the Window Heat Control Unit and the No. 1 flight deck window must be shielded. 14 CFR 25.1317 High-intensity Radiated Fields (HIRF) Protection The following design features must be incorporated in the type design (reference § 25.1317, Amendment N/A). In lieu of the following, compliance with § 25.1317 at Amendment 25-122, may be shown: 1. Electronic Engine Control System (EECS). The following design features are required to minimize exposure of the EECS to internal HIRF fields. a. The EECS must comply with Special Condition 25-ANM-18, dated April 29, 1988. 26 A1NM VIII - Model 767-2C (Cont’d) Certification Basis (Cont’d) Additional Design Requirements and Conditions (Cont’d) b. All on-engine EECs wiring must incorporate enhanced shielding, i.e., have a second layer of shielding (typically overbraid) applied to it, and the majority of this shielding must be terminated peripherally, rather than with multi-inch long jumper wires. c. RF shielding of the EECS is required as part of the engine nacelle type design as follows: i. The fan cowl shall have a ply of BMS8-336 expanded aluminum foil or equivalent on the OML surfaces. ii. The fan cowl and its access doors shall have a ply of BMS8-289 aluminum foil or equivalent on their IML which shall be in electrical physical contact with the adjacent nacelle components when closed. iii. An aluminum foil layer must be incorporated on the forward strut fairing panels. 2. Thrust Management Computer (TMC). The following design features are required to minimize exposure of the TMC to internal HIRF fields: a. TMC wiring routed to the Electronic Engine Control (inside the pressure vessel) must incorporate enhanced shielding, i.e. have a single, braided shield, grounded at every break. b. TMC wiring routed to the Electronic Engine Control (outside the pressure vessel) must incorporate enhanced shielding, i.e., have a second layer of shielding (typically overbraid) applied to it, and the majority of this shielding must be terminated peripherally at pressure hull, at outboard equipment, and all disconnects between the outboard equipment and pressure hull. 3. Window Heat System. The following design features are required to minimize exposure of the Window Heat System to internal HIRF fields: a. The power and sensor wiring between the Window Heat Control Unit and the No. 1 flight deck window must be shielded. Ignition System The engine in-flight start demonstration flight test conditions should be performed using the most critical single ignition configuration. The configuration(s) selected should be based on a consideration of the most critical igniter position, the most critical applicable ignition power configuration, and the most critical igniter plug adjustment. In-Flight All-Engines Restart A minimum restart capability after an all-engines-out scenario must be established under the following conditions using procedures provided in the airplane flight manual (AFM): a. During the take-off and the initial climb-out portion of the flight, the airplane should have the capability for the flight crew to restore engine power immediately following an all-engine-out scenario and when the fuel source to the engine is restored. b. During the high altitude portion of the flight at cruise speed and maximum altitude, the airplane should have the capability for the flight crew to restart engines from a stabilized windmill speed prior to descending below an altitude of 15,000 feet, by showing either or both: 1) All but one engine should be restarted and accelerated to produce maximum continuous thrust/power, or 2) The engine(s) should be restarted, and the necessary thrust/power achieved, to enable the airplane to maintain level flight. c. During flight at speeds greater than the minimum flaps-up “holding speed” and at altitudes below 20,000 feet, the airplane should have the capability for the flight crew to restart engines from a stabilized windmill speed prior to descending 5000 feet from the initiation of the restart procedure and prior to exceeding an airspeed of 300 knots, by showing either or both: 1) All but one engine should be restarted and accelerated to produce maximum continuous thrust/power, or 2) The engine(s) should be restarted, and the necessary thrust/power achieved, to enable the airplane to maintain level flight. Protection of Critical Systems Located in or in the Vicinity of the Main Deck Class E Cargo Compartment from the Effects of a Cargo Fire 1. Following fire/smoke detection, the crew must follow the AFM procedure to depressurize the cabin and ascend or descend the airplane to an altitude of 25,000 feet until final descent to a suitable airport is possible. 2. A main deck stationary smoke barrier must be installed between the occupied areas and the main deck cargo compartment. The barrier and associated joints will be tested to meet the requirements of 14 CFR part 25 appendix F part III (refer to Amendment 25-60). 3. Class E cargo compartment liners will be tested to meet the requirements of 14 CFR part 25 appendix F part III (refer to Amendment 25-60), except at the locations identified below: a) Dado Panels (Vented and Non-Vented) located along the sidewall at the floor of the main deck cargo compartment. b) Door Liner and Doorway Liner Materials and Joints (Main Deck Cargo Door, Aft Passenger and Service Doors, Emergency Escape Hatch), including joints covering door operating mechanisms, latches, door tracks and hinges. c) Aft Lowered Ceiling Area, STA 1459 to the Aft Pressure Dome. 4. Critical systems and wiring located behind, or in close proximity to features excluded in section 3, must be protected 27 A1NM VIII - Model 767-2C (Cont’d) Certification Basis (Cont’d) Additional Design Requirements and Conditions (Cont’d) with any one, or combination of the methods listed in section 5. 5. Protection of critical systems and the electrical interconnection wiring systems (EWIS) components required for continued safe flight and landing, located in, or in close proximity to the Class E compartment must be accomplished by any one, or combination of the following: a) Routing below the main deck floor and outside of the cargo compartment; b) Routing behind fire resistant liners that meet the requirements of 14 CFR part 25 appendix F part III (refer to Amendment 25-60); c) Use of fire hardened EWIS components or insulation where required to protect wire in locations subject to potential high temperatures on the backside of cargo liners and above ceiling panels; d) Routing redundant EWIS on opposite sides of the main deck floor and/or opposite sides of the crown area, and/or with a minimum separation of 6 feet; e) Routing redundant control cables to meet separation requirements; f) Placement of air dams or fire stops behind cargo liners as required to prevent propagation of fire behind the liner; g) Placement of special fire resistant covers behind air return grilles, decompression vents, and dados as required. Exemptions: The following Exemptions are applicable to the 767-2C: Exemption Number Applicable Section Title Date Issued Comments 12920A1 21.35(a),(b)(2) and (f)(2) Conduct Function and Reliability Testing After TC 3/9/2017 Time Limited Exemption: Termination Date April 24, 2018. 10861 25.562(b)(2) Floor Warpage - Testing Requirement for Flight Deck Seats 9/8/2013 11068 25.777(a) 25.1301(a)(b)(d) 25.1309(a)(c) Flight Deck Provisions 9/19/2014 10691 25.785(j) 25.795(b)(2), (c)(1),(c)(3) 25.809(a) 25.810(a)(1) 25.857(e) 25.1447(c)(1) Carriage of Supernumeraries with Main Deck Class E In-Flight Access and No Auto-Presenting Oxygen Dispensing Units and 10% Overage in the Aircrew and Cargo Compartments 1/28/2013 10866 25.841(a)(2)(i), (a)(2)(ii) Pressurized Cabins – Uncontained Engine Failure 9/11/2013 Partial Exemption 8119 25.901(c) No Single Failure 6/11/2003 Partial Exemption 11086A 25.961(a)(5) Fuel System Hot Weather Operations with JP-4 3/10/2016 10884A 25.981(a)(3) Fuel Tank Structural Lightning Ignition Protection 12/15/2017 17591 25.1329(j) Autopilot Disconnect 10/17/2017 Time Limited Exemption: Termination Date: December 31, 2019 17631 25.1322(d)(1) Windshear Detection and Warning System 11/2/2017 Time Limited Exemption: Termination Date: December 31, 2019 176332 25.903(d)(1) Minimization of Hazards from Engine Rotor Failure 11/3/2017 Line-Limited 176673 25.863(a) 25.1191(b)(1) APU Forward Firewall 11/28/2017 Line Limited 17651 25.959 25.1322(d)(1) Center Tank Fuel Management 11/17/2017 Time Limited Exemption: Termination Date: December 31, 2019 17658 25.1301(a), (d) Altitude Callouts 11/22/2017 Time Limited Exemption: Termination Date: December 31, 2019 17686 25.995(b) Fuel Valve Installations 12/15/2017 767-2C Exemptions Notes: 1. Function and Reliability Testing completed on 1/31/2018. 2. Exemption is limited to the first 32 767-2C model airplanes produced (through production Line Number 1145) 28 A1NM VIII - Model 767-2C (Cont’d) Certification Basis (Cont’d) Exemptions (Cont’d) 3. Exemption is limited to the first 41 767-2C model airplanes produced (through production Line Number 1164) Equivalent Safety Findings (ESF’s) exist with respect to the following sections of 14 CFR Part 25: ELOS IP Title 14 CFR PS05-0212-F-4 Longitudinal Trim 25.161(a),(c)(3), 25.1301(a), 25.1309(a) PS09-0863-A-2 Flight Flutter Test Requirement 25.629(e) PS05-0212-SF-1 Wing Flap Control Lever 25.777(e) PS09-0863-C-2 Other Exits in the Cargo Compartment 25.807(h)(2) AT2251SE-T-C-2 Escape Slide Inflation Times 25.810(a)(1)(ii) PS05-0020-ES-3 Acceptable High Temperature Physiological Environment During Failure Conditions 25.831(g) PS09-0863-P-11 Display of Powerplant Instruments 25.1549(b) PS09-0863-P-5 Flammability Exposure Evaluation Time 25.981(b) Appendix N25.3 AT2251SE-T-P-4 Auxiliary Power Unit Induction System 25.1103(e) PS09-0863-P-9 Fire Safety Requirements for PW4062 Fan Compartment 25.1181(b) 25.1182(a) PS09-0863-P-8 Engine Aft Fairing and Main Strut Fire Safety Requirements 25.1183(a) 25.1189(a),(d) PS05-0212-P-16 Fireproof Cowling and Nacelle Skin 25.1193(e)(3) PS09-0863-P-4 Auxiliary Power Unit (APU) Compartment Fireproof Skin Requirements 25.1193(e)(3) PS09-0863-P-12 Pressure Fueling System 25.979(b)(1) TC6918SE-T-SA-11 Overspeed Aural Warning 25.1303(c)(1) AT2251SE-T-P-5 Auxiliary Power Unit (APU) Instrumentation and Monitoring Requirements and Operation as an Alternate Electrical Power Source 25.1305(a)(3),(a)(4), (a)(5),(a)(6),(c)(1),(c)(3), (c) (4),(c)(6) PS09-0863-SE-1 Forward Position and Anti-Collision Lights 25.1387(b),(c) 25.1401(b) PS09-0863-SE-3 Forward and Rear Position Light Distribution and Intensities 25.1389(b)(3) PS09-0863-SE-8 Engine Electrical Wiring Interconnection System (EWIS) – Fire Protection 25.1713(c) TC6918SE-T-F-4 Rough Air Speed (VRA) 25.1517 AT2251SE-T-P-6 Auxiliary Power Unit (APU) Operating Limitations 25.1522 25.1549 TC6918SE-T-G-8 Formatting of Boeing Instructions for Continued Airworthiness Manuals - Airworthiness Limitations 25.1529 25.1729 Appendix H25.4 PS06-0496-F-18 Engine and Auxiliary Power Unit (APU) Fire Switch Handle Design 25.1555(d)(1) PS09-0863-EE-3 Early Extended Operations (ETOPS) Method Auxiliary Power Unit (APU) Validation Test 25.1535 K25.2.2((f) PS09-0863-P-19 Fuel Tank Ignition Prevention – Hot Surface Ignition Temperature 25.981(a) PS09-0863-P-37 Fuel Pump Control and Indication 25.901(c) 25.981(a)(3) PS17-0570-EE-2 Engine- Condition Monitoring, Early Extended Operations (ETOPS) Method Propulsion System Design and Validation Test Appendices K25.1.5, K25.2.2(b)(1) & (d) 29 A1NM VIII - Model 767-2C (Cont’d) Certification Basis (Cont’d) Special Conditions: The following Special Conditions are applicable to the Model 767-2C: Special Condition Title Effective Date 25-ANM-18 Boeing Model 767 Series Airplanes With Pratt & Whitney PW4000 Series Engines: Lightning Protection, Protection from Unwanted Effects of Radio Frequency (RF) Energy, and Propulsion Control System 4/29/1988 25-149-SC Sudden Engine Stoppage 9/16/1999 25-571-SC Interaction of Fuel Systems and Structures 11/24/2014 25-574-SC Isolation of Aircraft Electronic System Security Protection from Unauthorized Internal Access 2/26/2015 25-575-SC Aircraft Electronic System Security Protection from Unauthorized External Access 2/26/2015 25-630-SC Non-Rechargeable Lithium Batteries and Battery Systems 4/22/2017 Production Basis: Production Certificate No. 700 has been issued to The Boeing Company See Note 13. Required Equipment: The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed in the aircraft. Service Information: Boeing Document D634T201 (D634T245 for 767-2C) "Structural Repair Manual" is FAA-approved. Service Bulletins and other service information when FAA-approved shall carry a statement to that effect. DATA PERTINENT TO ALL MODELS Maximum Baggage/Cargo: See appropriate Weight and Balance Manual. Fuel and Oil Capacities: See appropriate Weight and Balance Manual. Minimum Crew: Two (2); pilot and copilot Minimum Required Fuel: See appropriate FAA-Approved Flight Manual. Maximum 43,100 feet Operating Altitude: 40,100 feet (767-2C) Leveling Means: Two inclinometers, plumb bob support and target (scale), left main gear well. Datum: Sta 0.0, located 92.5 in forward of airplane nose (B.S. 92.5). MAC: 237.5 inches Control Surface Control surfaces must be rigged in accordance with Boeing Drawings 251T1001, 251T2001, 251T3001, 251T4001, Movements: 254T7001, 257T4001, 256T1001, 256T2001, 256T3001. NOTES: Note 1. A current Weight & Balance Report must be in each aircraft at the time of original airworthiness certification and at all times thereafter except in the case of an operator having an FAA approved loading system for weight and balance control. Note 2. Airplane operation must be in accordance with the FAA-Approved Airplane Flight Manual. All placards required by either FAA- Approved Airplane Flight Manual, the applicable operating rules, or the Certification Basis must be installed in the airplane. Boeing Document No. D6T11320 is the basic FAA Approved Airplane Flight Manual for Pratt and Whitney powered Model 767-200/-300/-2C airplanes. Boeing Document No. D6T11321 is the basic FAA Approved Airplane Flight Manual for GE powered Model 767- 200/-300 airplanes. Boeing Document No. D631T001 is the basic FAA Approved Airplane Flight Manual for Model 767-400ER airplanes. Note 3. The FAA approved Airworthiness Limitations Section of the Instructions for Continued Airworthiness are referenced in Maintenance Planning Data Document (MPD) Section 9 - Airworthiness Limitations and Certification Maintenance Requirements; Boeing Document D622T001-9. The Airworthiness Limitations section is FAA-approved and specifies maintenance required under 14 CFR §§ 43.16 and 91.403, unless an alternative program has been FAA approved. 30 A1NM DATA PERTINENT TO ALL MODELS (Cont’d) NOTES (Cont’d) The operational limitations and maintenance tasks set forth in the following documents constitute the Airworthiness Limitations of the Boeing 767-200/300/300F/400ER model airplanes. For airplanes delivered after April 5, 2019, the applicable revision level of each of these documents is listed on the airplane-specific Revision Effectivity Report (RER) MPE- RER-767-LNXXXX letter of each airplane. Airplane operators are required to observe the limitations and perform the maintenance tasks per the specified revision level or a later FAA-approved revision of the documents. The following documents are the FAA approved requirements to comply with 14 CFR §§ 25.571, 25.981, 25.1529, 43.16 and 91.403: Boeing Document Title Description D622T001-9-01 767-200/300/300F/ 400ER Airworthiness Limitations (AWLs) Contains required structural inspections and the retirement times for structural safe-life and life-limited parts. Also contains required retirement times for systems life-limited parts and other systems limitations. D622T001-9-02 767-200/300/300F/ 400ER Airworthiness Limitations – Line Number Specific Existing structures AWLs that were impacted by airplane production non-conformances may result in airplane specific revised inspection requirements and/or inspection intervals. D622T001-9-03 767-200/300/300F/ 400ER Certification Maintenance Requirements (CMRs) Required periodic tasks to specific Systems installations. D622T001-9-04 767-200/300/300F/ 400ER Special Compliance Items/ Airworthiness Limitations This document lists and provides instructions for Airworthiness Limitation Instructions (ALIs) and Critical Design Configuration Control Limitations (CDCCLs) required to comply with 14 CFR Part 25.981 D622T001-DTR 767-200/300/300F/ 400ER Damage Tolerance Rating (DTR) Check Form Document This document contains completed (filled) DTR Check Forms. These forms were used to develop a suggested Supplemental Structural Inspection Program (SSIP) which is part of the SSIP in the Maintenance Planning Data document D622T001. These completed DTR Check Forms also serve as examples to assist operators while completing their own DTR Check Forms. 767-2C The FAA approved Airworthiness Limitations Section of the Instructions for Continued Airworthiness are referenced in Maintenance Planning Data Document (MPD) Section 9 - Airworthiness Limitations and Certification Maintenance Requirements; Boeing Document D011T030-01. The Airworthiness Limitations section is FAA-approved and specifies maintenance required under 14 CFR 43.16 and 91.403 of the Federal Aviation Regulations, unless an alternative program has been FAA approved. The operational limitations and maintenance tasks set forth in the following documents constitute the Airworthiness Limitations of the Boeing 767-2C model airplanes. For airplanes delivered after December 2, 2019, the applicable revision level of each of the MPD Section 9 sub-tier documents (D011T030-01-01, D011T030-01-02, D011T030-01-03, D011T030- 01-04) and the 767-2C Damage Tolerance Rating (DTR) Check Form Document (D011T030–04) is listed on the airplane- specific Revision Effectivity Report (RER) MPE-RER-7672C-LNXXXX letter of each airplane. Airplane operators are required to observe the limitations and perform the maintenance tasks per the specified revision level or a later FAA- approved revision of the documents. The following documents are the FAA approved requirements to comply with 14 CFR 25.571, 25.981, 25.1529, 25.1729, 43.16 and 91.403: Boeing Document Title Description D011T030-01-01 767-2C Airworthiness Limitations (AWLs) Contains required structural inspections and the retirement times for structural safe-life and life-limited parts. Also contains required retirement times for systems life-limited parts and other systems limitations. D011T030-01-02 767-2C Airworthiness Limitations (AWLs) – Line Number Specific Existing structures AWLs that were impacted by airplane production non-conformances may result in airplane specific revised inspection requirements and/or inspection intervals. D011T030-01-03 767-2C Certification Maintenance Requirements (CMRs) Required periodic tasks to specific Systems installations. 31 A1NM DATA PERTINENT TO ALL MODELS (Cont’d) NOTES (Cont’d) Boeing Document Title Description D011T030-01-04 767-2C Special Compliance Items (SCIs) /Airworthiness Limitations This document lists and provides instructions for Airworthiness Limitation Instructions (ALIs) and Critical Design Configuration Control Limitations (CDCCLs) required to comply with 14 CFR Part 25.981 D011T030-01-05 767-2C Electrical Wiring Interconnection Systems (EWIS) Document This document contains the EWIS Instructions for Continued Airworthiness tasks and procedures in compliance with Title 14 CFR 25.1729 that must be incorporated into the operator’s EWIS maintenance program. D011T030–04 767-2C Damage Tolerance Rating (DTR) Check Form Document This document contains completed (filled) DTR Check Forms. These forms were used to develop a suggested Supplemental Structural Inspection Program (SSIP) which is part of the SSIP in the Maintenance Planning Data document D011T030. These completed DTR Check Forms also serve as examples to assist operators while completing their own DTR Check Forms. Note 4. Systems and Powerplant Certification Maintenance Requirements (CMR): The CMRs are listed in either the FAA- approved Certification Maintenance Requirements (CMRs) Document D622T001-9-03 (D011T013-01-03 for 767-2C) or the applicable engine Type Certificate Data Sheet. The more restrictive requirement from these two documents shall be in force. Note 5. Crew procedures identified as required by engineering failure analyses in Boeing Document D230T405 must not be changed unless approved by FAA Seattle Aircraft Certification Office. Note 6. The following requirements apply to the design features at the required Type III overwing emergency exits: 1. With one pair of Type III exits there must be an unobstructed cross-aisle at least 20 inches wide between main aisles in close proximity to the overwing exit pair. With two pair of Type III exits, the cross-aisle must be in close proximity to both exit pairs. 2. Emergency lighting for the cross aisle must be provided in accordance with FAR 25.812. 3. The seat pitch at the seat row that provides access to each overwing exit from the main-aisle must be not less than 36 Inches. 4. A maximum of two inches of seat cushion may encroach into the actual projected opening of the exit, provided that the cushion can be readily compressed Note 7. The type design reliability and performance of this airplane has been evaluated in accordance with FAA Advisory Circular 120- 42A and found suitable for extended operations when configured in accordance with Boeing Document D6T11604 "CONFIGURATION, MAINTENANCE AND PROCEDURES FOR EXTENDED RANGE(ER) OPERATION". This finding does not constitute approval to conduct extended operations. The type-design reliability and performance of the Models 767-300BCF and 767-200SF have been evaluated under 14 CFR§25.1535 and found suitable for up to 180 minutes extended operations (ETOPS) when the configuration, maintenance, and procedures standard contained in Boeing Document D6T11604 "CONFIGURATION, MAINTENANCE AND PROCEDURES FOR EXTENDED RANGE (ER) OPERATION" are met. The actual maximum approved diversion time for this airplane may be less based on its most limiting system time capability. This finding does not constitute operational approval to conduct ETOPS. The type-design reliability and performance of the Model 767-2C have been evaluated under 14 CFR 25.3(b)(1) and 25.1535 and found suitable for up to 180 minutes extended operations (ETOPS) when the configuration, maintenance, and procedures standard contained in Boeing Document D922T010-01 "767-2C Configuration, Maintenance and Procedures" are met. The actual maximum approved diversion time for this airplane may be less based on its most limiting system time capability. This finding does not constitute operational approval to conduct ETOPS. Note 8. There are service bulletins which call for modifications which do not comply with the Type Certification Basis. These service bulletins are listed in Boeing Document D624T001 "Service Bulletin 767". The records of airplanes imported into the USA should be reviewed to be sure that further modifications are accomplished to ensure compliance, if the non FAA- approved service bulletins modifications have been installed. Note 9. The Engine Indication and Crew Alerting System (EICAS) provides displays of engine parameters, crew messages of non- normal conditions, system status maintenance data. EICAS messages are divided into the following categories: 32 A1NM DATA PERTINENT TO ALL MODELS (Cont’d) NOTES (Cont’d) WARNING - Red message, immediate crew action required. CAUTION - Amber message, subsequent crew action required. ADVISORY - Indented amber message, possible subsequent crew action required. STATUS - White message appears on EICAS Status page, provides readiness for dispatch information which require crew awareness prior to dispatch. MAINTENANCE - White message appears on ECS/MSG page of EICAS, for use of maintenance personnel only. Note 10. Airplane line numbers 231 and subsequent were manufactured after August 20, 1988, and Airplane line numbers 322 and subsequent were manufactured after August 20, 1990 (Reference FAR 121.312(a)(1) and (2), Amendment 121-198). Airplanes 322 through 326 are exempt (Exemption No. 5176A). See Boeing Service Bulletin Index, D6-30300, for cross reference of line number to serial number to block number. Note 11. The Pratt and Whitney PW4000 series, General Electric CF6-80C2 FADEC series, and Rolls Royce RB211-524H-36 or RB211- 524H-T-36 series engine type certificate data sheets define allowable dispatch criteria with certain faults present in the engine control system. The three fault categories defined in the engine type data sheets correspond to the following Boeing EICAS messages. Engine Fault Level RB-211-524H, T PW4000 CF6-80C2 FADEC EICAS Boeing Message Category C A C ENG CONTROL-ADVISORY C1 B C1 ENG EEC C1 – STATUS C2 C C2 ENG EEC C2 - MAINTENANCE Note 12. Exemption 5993A for the 767-300F requires that the procedures found to be acceptable during the emergency evacuation demonstration be incorporated into the approved operator's procedures. Any deviation requires coordination with FAA Seattle Aircraft Certification Office. Note 13. The following Serial Number was produced under Type Certificate only: 27240 Note 14. CF6-80C2 series engines incorporating Dribble Flow Fuel Nozzles PN 9331M72P33, P34 and P41 are prohibited from the use of JP-4 and Jet B (wide cut) fuel. Note 15. Use of JP-4 and Jet B (wide cut) fuel is prohibited when one or two Rolls-Royce RB211-524H-T-36 series engines are installed. Note 16. Mandatory replacement times, inspection intervals, related inspection procedures and all critical design configuration control limitation for the fuel tank system determined during the Special Federal Aviation Regulation No. 88 program and for compliance with 14 CFR 25.981 are listed in the FAA-approved Special Compliance Items (SCls)/Airworthiness Limitations Document D622T001-9-04 (D011T030-01-04 for 767-2C). Note 17. An Equivalent Safety Finding for the Flammability Reduction System (FRS), 14 CFR 25.981 at Amendment 25-125 is applied if fuel tank inerting is installed in new airplane production (starting with line # 993) or as a modification on existing in service aircraft per Boeing Service Bulletin 767-47-0001. Airworthiness Limitations for the FRS are contained in Section 9 of the applicable Maintenance Planning Document. Note 18. The FAA has concluded that the occurrence of any uncontrollable high thrust failure condition, or any of the associated causal failures listed within Boeing Document D332N402, “may endanger the safe operation of an airplane” and hence are reportable under §§ 121.703 (c), 125.409 (c), and 135.415(c). Note 19. KC-46A airplanes are tanker/cargo versions of the Model 767-2C. Prior to operation as a commercial aircraft, the following must be accomplished: a) The maintenance, overhaul and modification records of each aircraft must be reviewed for changes made by the military services that may affect the airworthiness of the aircraft. Modifications, changes of equipment and repairs, which affect the safety or performance of the aircraft, must be approved by the FAA b) All aircraft returned to civil operations must comply with all applicable Airworthiness Directives c) All items that are not FAA approved must be removed from the aircraft if they affect the safety or performance of the aircraft. d) Each deviation from the FAA approved type design as listed on FAA Form 8130-31 “Conformity Certificate – Military Aircraft” that is required for civil certification must be corrected per FAA approved data. The following serial numbers were produced as part of the ATC project and have not been reworked to the type design configuration to be eligible for a Standard Airworthiness Certificate: 34054, 41273-41275, 41852, 41856, 41983. .....END..... ``` ## ADs (454, first 50, in force first) - [AD 2026-18-08](https://openairdocs.org/ad/2026-18-08): Fuselage · Boeing 767-300F Series. Effective Oct 22, 2026 - [AD 2026-16-06](https://openairdocs.org/ad/2026-16-06): Wings · Boeing 767-300 Series and 767-300F Series with STC ST01920SE. Effective Sep 17, 2026 - [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026 - [AD 2026-13-16](https://openairdocs.org/ad/2026-13-16): Navigation · Boeing 757-200 Series, 757-200PF Series, 757-200CB Series and 6 more. Effective Jul 1, 2026 - [AD 2026-05-03](https://openairdocs.org/ad/2026-05-03): Fuselage · Boeing 767-200 Series and 767-300 Series. Effective Apr 16, 2026 - [AD 2026-05-07](https://openairdocs.org/ad/2026-05-07): Wings · Boeing 767-200 Series, 767-300 Series, 767-300F Series and 1 more. Effective Apr 16, 2026 - [AD 2026-04-10](https://openairdocs.org/ad/2026-04-10): Communications · Boeing 767-200 Series, 767-300 Series, 767-300F Series and 1 more. Effective Apr 10, 2026 - [AD 2025-18-05](https://openairdocs.org/ad/2025-18-05): Navigation · Boeing 767-300 Series with STC ST02040SE. Effective Oct 23, 2025 - [AD 2025-15-08](https://openairdocs.org/ad/2025-15-08): Equipment/furnishings · Boeing 767-200 Series, 767-300 Series, 767-300F Series and 1 more. Effective Aug 21, 2025 - [AD 2025-02-07](https://openairdocs.org/ad/2025-02-07): Navigation · Modification of Rockwell Collins, Inc. Multi-Mode Receiver (STC ST01883WI or 4 others). Effective Mar 17, 2025 - [AD 2024-26-03](https://openairdocs.org/ad/2024-26-03): Water/waste · Boeing 767-200 Series, 767-300 Series and 767-400ER Series. Effective Mar 7, 2025 - [AD 2024-25-08](https://openairdocs.org/ad/2024-25-08): Landing Gear · Boeing 767-200 Series, 767-300 Series and 767-300F Series. Effective Feb 12, 2025 - [AD 2024-24-05](https://openairdocs.org/ad/2024-24-05): Equipment/Furnishings · Boeing 767-300F Series. Effective Jan 13, 2025 - [AD 2024-15-05](https://openairdocs.org/ad/2024-15-05): Electrical Power · Boeing 767-300 Series. Effective Oct 15, 2024 - [AD 2024-05-03](https://openairdocs.org/ad/2024-05-03): Fuselage · Boeing 767-200 Series, 767-300 Series, 767-300F Series and 2 more. Effective May 8, 2024 - [AD 2023-13-12](https://openairdocs.org/ad/2023-13-12): Oxygen · Boeing 737-100 Series, 737-200 Series, 737-200C Series and 17 more. Effective Sep 5, 2023 - [AD 2023-13-09](https://openairdocs.org/ad/2023-13-09): Flight controls · Boeing 767-2C Series, 767-200 Series, 767-300 Series and 2 more. Effective Aug 24, 2023 - [AD 2023-12-23](https://openairdocs.org/ad/2023-12-23): Placards and markings · Boeing 767-300F Series. Effective Aug 15, 2023 - [AD 2023-12-12](https://openairdocs.org/ad/2023-12-12): Navigation · Boeing 757-200 Series, 757-200PF Series, 757-200CB Series and 6 more. Effective Jun 21, 2023 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2023-05-12](https://openairdocs.org/ad/2023-05-12): Electrical Power · Boeing 767-2C Series. Effective Apr 20, 2023 - [AD 2022-19-04](https://openairdocs.org/ad/2022-19-04): Electrical power · Boeing 767-2C Series. Effective Oct 11, 2022 - [AD 2022-13-10](https://openairdocs.org/ad/2022-13-10): Equipment/furnishings · Boeing 767-200 Series, 767-300 Series, 767-300F Series and 1 more. Effective Sep 20, 2022 - [AD 2022-13-18](https://openairdocs.org/ad/2022-13-18): Oxygen · Boeing 737-700 Series, 737-800 Series, 747-8 Series and 3 more. Effective Sep 15, 2022 - [AD 2022-15-08](https://openairdocs.org/ad/2022-15-08): Information systems · Airbus A318-111, A318-112, A319-111 and 49 more. Effective Aug 12, 2022 - [AD 2022-06-18](https://openairdocs.org/ad/2022-06-18): Air conditioning · Boeing 767-2C Series. Effective Apr 18, 2022 - [AD 2021-20-19](https://openairdocs.org/ad/2021-20-19): Fuel · Boeing 767-200 Series, 767-300 Series, 767-300F Series and 1 more. Effective Nov 30, 2021 - [AD 2021-12-11](https://openairdocs.org/ad/2021-12-11): Equipment/furnishings · Boeing 767-200 Series, 767-300 Series, 767-300F Series and 1 more. Effective Jul 29, 2021 - [AD 2021-15-04](https://openairdocs.org/ad/2021-15-04): Electrical Power · Boeing 767-300 Series with STC ST02040SE. Effective Jul 14, 2021 - [AD 2021-10-19](https://openairdocs.org/ad/2021-10-19): Flight Controls, Doors, Fuselage, Nacelles/pylons, Stabilizers, Wings · Winglets, wing structural reinforcement (Aviation Partners Boeing STC ST01920SE). Effective Jul 1, 2021 - [AD 2021-08-04](https://openairdocs.org/ad/2021-08-04): Oxygen · Boeing 737-200 Series, 737-300 Series, 737-400 Series and 23 more. Effective May 26, 2021 - [AD 2021-06-10](https://openairdocs.org/ad/2021-06-10): Fuel · Boeing 747-100 Series, 747-100B Series, 747-100B SUD Series and 16 more. Effective Apr 28, 2021 - [AD 2020-18-16](https://openairdocs.org/ad/2020-18-16): Fuel · Boeing 767-200 Series, 767-300 Series, 767-300F Series and 1 more. Effective Nov 10, 2020 - [AD 2020-04-15](https://openairdocs.org/ad/2020-04-15): Air conditioning · Boeing 757-200 Series, 757-200CB Series, 757-200PF Series and 4 more. Effective May 8, 2020 - [AD 2019-24-18](https://openairdocs.org/ad/2019-24-18): Navigation · Boeing 727-100 Series, 727-100C Series, 727-200 Series and 11 more. Effective Feb 3, 2020 - [AD 2019-19-10](https://openairdocs.org/ad/2019-19-10): Fuel · Boeing 737-300 Series, 737-400 Series, 737-500 Series and 21 more. Effective Jan 16, 2020 - [AD 2018-23-12](https://openairdocs.org/ad/2018-23-12): Equipment/furnishings · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 180 more. Effective Dec 28, 2018 - [AD 93-14-19 R1](https://openairdocs.org/ad/93-14-19-R1): Wings · Boeing 767-200 Series, 767-2C Series, 767-300 Series and 2 more. Effective Nov 26, 2018 - [AD 2018-20-13](https://openairdocs.org/ad/2018-20-13): Fuel · Boeing 757-200 Series, 757-200CB Series, 757-200PF Series and 13 more. Effective Nov 15, 2018 - [AD 2018-13-06](https://openairdocs.org/ad/2018-13-06): Wings · Boeing 767-300 Series and 767-300F Series. Effective Aug 22, 2018 - [AD 2018-11-08](https://openairdocs.org/ad/2018-11-08): Fuselage · Boeing 767-200 Series and 767-300 Series. Effective Jul 10, 2018 - [AD 2018-07-18](https://openairdocs.org/ad/2018-07-18): Fuselage · Boeing 767-200 Series, 767-300 Series, 767-300F Series and 1 more. Effective May 21, 2018 - [AD 2018-01-02](https://openairdocs.org/ad/2018-01-02): Water/waste · Boeing 767-200 Series, 767-300 Series and 767-400ER Series. Effective Feb 7, 2018 - [AD 2017-19-05](https://openairdocs.org/ad/2017-19-05): Smoke Detection · Airbus A330-201, A330-202, A330-203 and 30 more. Effective Oct 31, 2017 - [AD 2017-17-16](https://openairdocs.org/ad/2017-17-16): Fuselage · Boeing 767-200 Series, 767-300 Series, 767-300F Series and 1 more. Effective Oct 2, 2017 - [AD 2017-11-04](https://openairdocs.org/ad/2017-11-04): Fuselage · Boeing 767-200 Series, 767-300 Series and 767-400ER Series. Effective Jul 13, 2017 - [AD 2017-12-01](https://openairdocs.org/ad/2017-12-01): Wings · Boeing 767-200 Series with STC ST01329WI-D. Effective Jun 23, 2017 - [AD 2017-05-06](https://openairdocs.org/ad/2017-05-06): Fuselage · Boeing 767-200 Series and 767-300 Series. Effective Apr 7, 2017 - [AD 2017-01-09](https://openairdocs.org/ad/2017-01-09): Air Conditioning · Boeing 767-300 Series and 767-300F Series. Effective Feb 21, 2017 - [AD 2016-25-07](https://openairdocs.org/ad/2016-25-07): Fuselage · Boeing 767-200 Series and 767-300 Series. Effective Feb 7, 2017 All 454: https://openairdocs.org/tcds/A1NM/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Boeing 767-300F](https://openairdocs.org/model/boeing-767-300f): 169 aircraft (registry codes 138513G, 138513H) - [Boeing 767-332](https://openairdocs.org/model/boeing-767-332): 46 aircraft (registry code 1385101) - [Boeing 767-322](https://openairdocs.org/model/boeing-767-322): 36 aircraft (registry code 1385200) - [Boeing 767-323](https://openairdocs.org/model/boeing-767-323): 27 aircraft (registry code 1385205) - [Boeing 767-432ER](https://openairdocs.org/model/boeing-767-432er): 21 aircraft (registry code 1385134) - [Boeing 767-424ER](https://openairdocs.org/model/boeing-767-424er): 16 aircraft (registry code 1385270) - [Boeing 767-338](https://openairdocs.org/model/boeing-767-338): 13 aircraft (registry code 1385151) - [Boeing 767-316](https://openairdocs.org/model/boeing-767-316): 12 aircraft (registry code 1385150) - [Boeing 767-346](https://openairdocs.org/model/boeing-767-346): 11 aircraft (registry code 1385210) - [Boeing 767-281](https://openairdocs.org/model/boeing-767-281): 9 aircraft (registry code 1385129) - [Boeing 767-381](https://openairdocs.org/model/boeing-767-381): 8 aircraft (registry code 1385130) - [Boeing Company The 767-2C](https://openairdocs.org/model/boeing-company-the-767-2c): 7 aircraft (registry code 138510K) - [Boeing 767-232](https://openairdocs.org/model/boeing-767-232): 6 aircraft (registry code 1385132) - [Boeing 767-319](https://openairdocs.org/model/boeing-767-319): 6 aircraft (registry code 138526G) - [Boeing 767-224](https://openairdocs.org/model/boeing-767-224): 5 aircraft (registry code 1385170) - [Boeing 767-300](https://openairdocs.org/model/boeing-767-300): 5 aircraft (registry code 1385204) - [Boeing 767-306](https://openairdocs.org/model/boeing-767-306): 5 aircraft (registry code 1385148) - [Boeing 767-316F](https://openairdocs.org/model/boeing-767-316f): 5 aircraft (registry code 138526F) - [Boeing 767-336](https://openairdocs.org/model/boeing-767-336): 4 aircraft (registry code 1385399) - [Boeing 767-223](https://openairdocs.org/model/boeing-767-223): 3 aircraft (registry code 1385123) - [Boeing 767-231](https://openairdocs.org/model/boeing-767-231): 3 aircraft (registry code 1385131) - [Boeing 767-304](https://openairdocs.org/model/boeing-767-304): 3 aircraft (registry code 1385135) - [Boeing 767-324](https://openairdocs.org/model/boeing-767-324): 3 aircraft (registry code 1385203) - [Boeing 767-200](https://openairdocs.org/model/boeing-767-200): 2 aircraft (registry code 1385120) - [Boeing 767-233](https://openairdocs.org/model/boeing-767-233): 2 aircraft (registry code 1385113) - [Boeing 767-238](https://openairdocs.org/model/boeing-767-238): 2 aircraft (registry code 1385114) - [Boeing 767-330](https://openairdocs.org/model/boeing-767-330): 2 aircraft (registry code 1385304) - [Boeing 767-333](https://openairdocs.org/model/boeing-767-333): 2 aircraft (registry code 1385301) - [Boeing 767-341](https://openairdocs.org/model/boeing-767-341): 2 aircraft (registry code 1385250) - [Boeing 767-375](https://openairdocs.org/model/boeing-767-375): 2 aircraft (registry code 1385217) - [Boeing 767-383](https://openairdocs.org/model/boeing-767-383): 2 aircraft (registry code 1385214) - [Boeing 767-222](https://openairdocs.org/model/boeing-767-222): 1 aircraft (registry code 1385122) - [Boeing 767-241](https://openairdocs.org/model/boeing-767-241): 1 aircraft (registry code 1385115) - [Boeing 767-246](https://openairdocs.org/model/boeing-767-246): 1 aircraft (registry code 1385116) - [Boeing 767-266](https://openairdocs.org/model/boeing-767-266): 1 aircraft (registry code 1385137) - [Boeing 767-277](https://openairdocs.org/model/boeing-767-277): 1 aircraft (registry code 1385128) - [Boeing 767-328](https://openairdocs.org/model/boeing-767-328): 1 aircraft (registry code 1385290) - [Boeing 767-360](https://openairdocs.org/model/boeing-767-360): 1 aircraft (registry code 1385165) - [Boeing 767-201](https://openairdocs.org/model/boeing-767-201): 0 aircraft (registry code 1385125) - [Boeing 767-204](https://openairdocs.org/model/boeing-767-204): 0 aircraft (registry code 1385110) - [Boeing 767-205](https://openairdocs.org/model/boeing-767-205): 0 aircraft (registry code 1385121) - [Boeing 767-209](https://openairdocs.org/model/boeing-767-209): 0 aircraft (registry code 1385127) - [Boeing 767-216](https://openairdocs.org/model/boeing-767-216): 0 aircraft (registry code 1385124) - [Boeing 767-219](https://openairdocs.org/model/boeing-767-219): 0 aircraft (registry code 1385111) - [Boeing 767-258](https://openairdocs.org/model/boeing-767-258): 0 aircraft (registry code 1385117) - [Boeing 767-259](https://openairdocs.org/model/boeing-767-259): 0 aircraft (registry code 1385136) - [Boeing 767-260](https://openairdocs.org/model/boeing-767-260): 0 aircraft (registry code 1385118) - [Boeing 767-269](https://openairdocs.org/model/boeing-767-269): 0 aircraft (registry code 1385103) - [Boeing 767-275](https://openairdocs.org/model/boeing-767-275): 0 aircraft (registry code 1385119) - [Boeing 767-284](https://openairdocs.org/model/boeing-767-284): 0 aircraft (registry code 1385184) All 57: https://openairdocs.org/tcds/A1NM/aircraft.md ## STCs approved under this data sheet (970, first 50) - [STC ST11152SC](https://openairdocs.org/stc/ST11152SC): Installation of the Iridium Communications System. L2 Aviation - [STC ST09889AC](https://openairdocs.org/stc/ST09889AC): Installation of Rockwell Collins LDS-2100 large display systems (LDS). L2 Aviation - [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center - [STC ST00885LA](https://openairdocs.org/stc/ST00885LA): Installation of fire extinguisher cartridges as replacements for Pacific Scientific fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON, LLC d/b/a MASS Systems - [STC SA4187NM-D](https://openairdocs.org/stc/SA4187NM-D): Installation of one (1) coat closet, one (1) centerline class divider and two (2) outboard class dividers.. Safran Cabin Inc. - [STC ST04254NY](https://openairdocs.org/stc/ST04254NY): Installation of Viasat Satcom Software. ALOFT AeroArchitects - [STC ST00197IB](https://openairdocs.org/stc/ST00197IB): Installation of the Universal Quick Access Recorder (uQAR). Flight Data Technologies Inc. - [STC ST02040SE](https://openairdocs.org/stc/ST02040SE): Conversion of a Boeing 767-300 passenger configuration airplane to a special freighter (SF) configuration. Israel Aerospace Industries LTD - [STC ST03205NY](https://openairdocs.org/stc/ST03205NY): Installation of a Panasonic Avionics Corporation Global Communications Suite Antenna. Delta Engineering Corporation - [STC ST00428AT](https://openairdocs.org/stc/ST00428AT): Installation of Canadian-Marconi Satcom Antenna Provisions only.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST00431AT](https://openairdocs.org/stc/ST00431AT): Installation of Collins SAT-906 SATCOM System.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST01783AT-D](https://openairdocs.org/stc/ST01783AT-D): Interior reconfiguration from Three Class to Two Class.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST01808AT-D](https://openairdocs.org/stc/ST01808AT-D): Installation of a Collins VHF-900B Transceivers and Boeing Radio Control Panels with 8.33 KHz spacing.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST01868AT-D](https://openairdocs.org/stc/ST01868AT-D): Interior reconfiguration from Three Class to Two Class. For model 767-300ER. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST01869AT-D](https://openairdocs.org/stc/ST01869AT-D): Interior reconfiguration.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST02086AT-D](https://openairdocs.org/stc/ST02086AT-D): Aft lavatory relocation.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST02159AT-D](https://openairdocs.org/stc/ST02159AT-D): Interior Reconfiguration - Crew Rest Installation/Fleet Standardization.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST02219AT-D](https://openairdocs.org/stc/ST02219AT-D): Interior reconfiguration.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST02497AT-D](https://openairdocs.org/stc/ST02497AT-D): Interior reconfiguration, 325 seats eight abreast, with in-seat audio provisions. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST02666AT-D](https://openairdocs.org/stc/ST02666AT-D): Interior reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST02753AT-D](https://openairdocs.org/stc/ST02753AT-D): Interior Reconfiguration.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST02769AT-D](https://openairdocs.org/stc/ST02769AT-D): Upgrade Modifications and Installation of an A-3 Lavatory for Disabled Passengers.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03067AT-D](https://openairdocs.org/stc/ST03067AT-D): Interior Reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03068AT-D](https://openairdocs.org/stc/ST03068AT-D): Cabin Standardization. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03107AT-D](https://openairdocs.org/stc/ST03107AT-D): Interior reconfiguration.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03135AT-D](https://openairdocs.org/stc/ST03135AT-D): Installation of Rockwell Collins ACARS CMU-900. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03222AT-D](https://openairdocs.org/stc/ST03222AT-D): 767-300 B Zone Elimination. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03366AT-D](https://openairdocs.org/stc/ST03366AT-D): Cabin Re-configuration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03372AT](https://openairdocs.org/stc/ST03372AT): Installation of a Lower Lobe Crew Rest Module (CRM) and Main Deck Vestibule.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03435AT-D](https://openairdocs.org/stc/ST03435AT-D): Interior reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03468AT-D](https://openairdocs.org/stc/ST03468AT-D): Installation of a Rockwell Collins SRT-2100 SATCOM system. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03492AT-D](https://openairdocs.org/stc/ST03492AT-D): Interior reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03515AT-D](https://openairdocs.org/stc/ST03515AT-D): Interior reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03552AT-D](https://openairdocs.org/stc/ST03552AT-D): Installation of Aircraft Cabin Systems (ACS) 32 inch LCD Monitors. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03578AT-D](https://openairdocs.org/stc/ST03578AT-D): Cell Modem Installation. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03582AT-D](https://openairdocs.org/stc/ST03582AT-D): Installation of a F1 Lavatory Bi-fold Door in United Airlines Boeing 767-300 aircraft.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03596AT-D](https://openairdocs.org/stc/ST03596AT-D): Installation of an Interior Reconfiguration on Japan Airlines Boeing 767-300 aircraft. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03604AT-D](https://openairdocs.org/stc/ST03604AT-D): Cell Modem Installation.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03665AT-D](https://openairdocs.org/stc/ST03665AT-D): Installation of seven (7) Upgraded Lavatories. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03706AT-D](https://openairdocs.org/stc/ST03706AT-D): Installation of an Interior Reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03811AT-D](https://openairdocs.org/stc/ST03811AT-D): Installation of an Interior Reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03820AT-D](https://openairdocs.org/stc/ST03820AT-D): Installation of an Interior Reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03884AT-D](https://openairdocs.org/stc/ST03884AT-D): LCD Monitor Upgrade. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST03977AT](https://openairdocs.org/stc/ST03977AT): Lavatory Installation Program. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04132AT](https://openairdocs.org/stc/ST04132AT): Floor structure reinforcement installation. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04138AT](https://openairdocs.org/stc/ST04138AT): Crew Rest Curtain Installation. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04196AT](https://openairdocs.org/stc/ST04196AT): Installation of an Interior Reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04217AT](https://openairdocs.org/stc/ST04217AT): Interior Reconfiguration. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04259AT](https://openairdocs.org/stc/ST04259AT): Installation of a HAECO Cabin Solutions Lavatory. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST04264AT](https://openairdocs.org/stc/ST04264AT): Interior reconfiguration installation. AIRCRAFT RECONFIG TECHNOLOGIES, LLC All 970: https://openairdocs.org/tcds/A1NM/stcs.md --- 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.