Source: https://ja.scribd.com/document/136797766/GE-Engines
Timestamp: 2019-07-16 14:08:35
Document Index: 513598649

Matched Legal Cases: ['art 33', 'art 34', 'art 33', 'art 34', 'art 33', 'art 34']

GE Engines | Horsepower | Engines
DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00049EN
TCDS NUMBER E00049EN REVISION 15 DATE: February 24, 2010 GENERAL ELECTRIC COMPANY MODELS: GE90-76B GE90-77B GE90-85B GE90-90B GE90-94B GE90-110B1 GE90-113B GE90-115B
Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00049EN) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations, provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. TYPE CERTIFICATE (TC) HOLDER: General Electric Company GE Aircraft Engines 1 Neumann Way Cincinnati, OH 45215-6310 I. MODELS TYPE RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb Takeoff (5 min. see NOTE 16) at sea level, static thrust, lb Flat rating ambient temperature Takeoff Maximum continuous GE90-76B GE90-77B GE90-85B GE90-90B
Dual rotor, axial flow, high bypass ratio turbofan. The 10-stage high pressure compressor is driven by a 2-stage high pressure turbine. The single stage fan and 3-stage low pressure compressor are driven by a 6-stage low pressure turbine.
75,430 81,070
75,430 81,700
81,230 88,870 86oF/30oC --
90,580 94,000
91F/32.8C 77F/25C
COMPONENTS (GE P/Ns) Hydromechanical Control Unit
1693M75 1851M65
Full Authority Digital Engine Control (FADEC) Hardware (H/W) & Software (S/W) HW (See NOTE 21)
1838M16 1959M87 1838M16 1853M99
SW (See NOTE 21)
PAGE REV. 1 15 2 9 3 9 4 15 5 15 6 11 7 11 8 9 9 15 10 15
"- - -" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL"
TCDS E00049EN
I. MODELS (cont.) Configuration Type Box (See NOTE 10)
GE90-76B 320-837-701-0 320-839-501-0 320-892-101-0 320-892-201-0 320-846-701-0 320-892-601-0 320-915-201-0 320-921-501-0 320-833-701-0
GE90-77B ----------320-833-901-0
GE90-85B ----------320-833-801-0 320-834-201-0 --
GE90-90B ----------320-834-001-0
FADEC Rating Plug
Main Fuel Pump IGNITION SYSTEM Two ignition units GE P/N Two ignitor plugs GE P/N
1689M10
9238M66 1754M84
PRINCIPAL DIMENSIONS (in) Length (Fan spinner to nozzle centerbody) Width (maximum envelope) Height (maximum envelope) WEIGHT (DRY) Includes basic engine, basic engine accessories, and optional equipment as listed in the manufacturer's engine specifications. CENTER OF GRAVITY LOCATIONS (in) (Engine only) Station (axial) Waterline Buttline 227.5+1.5 99.9+0.5 100.4+0.5 ----------
286.9 152.4 155.6 17,400
II. MODELS TYPE
GE90-94B Dual rotor, axial flow, high bypass ratio turbofan. The 10-stage high pressure compressor is driven by a 2-stage high pressure turbine. The single stage fan and 3-stage low pressure compressor are driven by a 6-stage low pressure turbine.
RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb Takeoff (5 min. see NOTE 16) at sea level, static thrust, lb Flat rating ambient temperature Takeoff Maximum continuous COMPONENTS (GE P/Ns) Hydro-mechanical Control Unit
90,580 97,300 86oF/30oC 77oF/25oC
1851M65
Full Authority Digital Engine Control (FADEC) Hardware (H/W) & Software (S/W) Hardware (H/W) (See NOTE 21) Software (S/W) (See NOTE 21) Configuration Type Box (See NOTE 10) FADEC Rating Plug Main Fuel Pump IGNITION SYSTEM Two ignition units GE P/N Two ignitor plugs GE P/N PRINCIPAL DIMENSIONS (in) Length (Fan spinner to nozzle centerbody) Width (maximum envelope) Height (maximum envelope) WEIGHT (DRY) Includes basic engine, basic engine accessories, and optional equipment as listed in the manufacturer's engine specifications. CENTER OF GRAVITY LOCATIONS (in) (Engine only) Station (axial) Waterline Buttline
1959M87 1838M16 1853M99 320-921-501-0 320-834-301-0 1689M10
286.9 152.4 155.6
227.5+1.5 99.9+0.5 100.4+0.5
III MODELS TYPE RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb Takeoff (5 min. see NOTE 16) at sea level, static thrust, lb Flat rating ambient temperature Takeoff Maximum continuous COMPONENTS (GE P/Ns) Hydro-mechanical Control Unit Full Authority Digital Engine Control (FADEC) Hardware (H/W) (See NOTE 21) Software (S/W) (See NOTE 21 Configuration Type Box
110,000 110,760
110,000 113,530
110,000 115,540
92F/33C 77F/25C
86F/30C 77F/25C
1962M80
1962M67 2041M27 390-850-001-0 390-851-001-0
----390-802-001-0 390-804-001-0 ----
----390-800-001-0 390-805-001-0 390-805-011-0 390-805-021-0 --
390-801-011-0 390-803-001-0 390-803-011-0 390-803-021-0 2042M69
PRINCIPAL DIMENSION (in) 286.67 Length (Fan spinner to nozzle centerbody) Width (maximum envelope) Height (maximum envelope) WEIGHT (DRY) Includes basic engine, basic engine accessories, and optional equipment as listed in the manufacturers engine specifications. CENTER OF GRAVITY LOCATIONS (in) (Engine only) Station (axial) Waterline Buttline 148.38 154.56 -------
219.2+1.5 100.14+0.5 100.28+0.5
IV. MODELS FUEL OIL
ALL See NOTE 7 for approved fuels. Type 2 oils conforming to GE90 Specification D50TF1 or the latest revisions are authorized. For approved brand of oils refer to GE90 Service Bulletin 79-001.
CERTIFICATION BASIS (-76B/-77B/-85B/-90B)
14 Code of Federal Regulations (CFR), Part 33, effective February 1, 1965, Amendments 33-1 through 33-15, inclusive; Part 34, effective September 10, 1990, including Amendments 34-1 through 34-3; and Special Condition Number SC-33-ANE-08-NE. 14 Code of Federal Regulations (CFR), Part 33, effective February 1, 1965, including Amendments 33-1 through 33-15, and Amendment 19; Part 34, effective September 10, 1990, including Amendments 34-1 through 34-3; Special Condition SC-33-ANE-08-NE, and Equivalent Level of Safety Finding for 33.68(b) Number 8040-ELOS-00-NE-01. 14 Code of Federal Regulations (CFR), Part 33, effective February 1, 1965, including Amendments 33-1 through 33-20; Part 34, effective September 10, 1990, including Amendments 34-1 through 34-3; Special Condition SC-33-ANE08-NE, and Exemption to 33.73(b), No. 7953 dated January 15, 2003
CERTIFICATION BASIS (-94B)
CERTIFICATION BASIS (-110B1, -113B, -115B)
TYPE CERTIFICATE E00049EN MODELS GE90-76B GE90-85B GE90-90B GE90-77B GE90-94B GE90-113B GE90-115B GE90-110B1 GE90-75B GE90-92B APPLICATION DATE DEC 16, 1991 DEC 16, 1991 AUG 10, 1994 NOV 20, 1995 MAR 5, 1999 JUN 27, 2000 JUN 27, 2000 JAN 9, 2002 DEC 16, 1991 AUG 10, 1994 ISSUED/AMENDED FEB 2, 1995 FEB 2, 1995 JUL 2, 1996 JUL 2, 1996 JUN 9, 2000 JUL 30, 2003 JUL 30, 2003 JUL 30, 2003 FEB 2, 1995 (Deleted JUL 24, 1995) JUL 2, 1996 (Deleted June 26, 2000)
GE90-76B/-77B/-85B/-90B/-94B/-110B1/-113B/-115B Production Certificate No. 108
NOTE 1. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS GE90-76B Low pressure rotor (N1) High pressure rotor (N2) * 100 percent N1 is 2261.5 RPM ** 100 percent N2 is 9332.0 RPM *** 100 percent N1 is 2355.0 RPM GE90-77B/-85B/-90B/-94B GE90-110B1/-113B/-115B 2602 RPM (110.5 percent)*** 11292 RPM (121 percent)**
2,465 RPM 2,465 RPM (109.0 percent)* (109.0 percent)* 10,705 RPM 10,918 RPM (114.7 percent)** (117 percent)**
MAXIMUM PERMISSIBLE TEMPERATURES Indicated turbine exhaust gas temperature (T49) GE90-76B (see NOTE 10) Takeoff (5 minute see NOTE 16) 1787oF (975oC)* Maximum Continuous 1697oF (925oC) Ground starts (manual or auto) 1382oF (750oC) Inflight starts (manual or auto) 1517oF (825oC) * 60 seconds maximum transient * 40 seconds start EGT exceedance limit for 94B only Oil temperature limits Continuous Transient 1796oF (980oC)
GE90-77B/-85B/ -90B/-94B 1885oF (1030oC) 1859oF (1015oC) 1382oF (750oC)** ---1517oF (825oC)
255oF (124oC) 275oF (135oC)
Indicated turbine exhaust gas temperature (T49) Takeoff (5 minute see NOTE 16) Maximum Continuous Ground starts (manual or auto) Inflight starts (manual or auto) ***30 seconds maximum transient Oil temperature limits Continuous Transient
GE90-110B1/ -113B/ -115B 1994oF (1090oC)*** 1922oF (1050oC) 1382oF (750oC) 1517oF (825oC) 2003oF (1095oC)
270oF (132oC) 290oF (143oC)
FUEL AND OIL PRESSURE LIMITS FUEL PRESSURE LIMITS AT THE ENGINE PUMP INLET The limit is from minimum fuel pressures of not less than the greater of true vapor pressure plus 7.0 psi or ambient plus 7.0 psi to a maximum of 70 psig. OIL PRESSURE LIMITS LOW PRESSURE The limit is 10.0 psid (69 kPa diff.). (See NOTE 14)
ACCESSORY DRIVE PROVISIONS
GE90-76B/-77B/-85B/-90B/-94B
Rotation Facing Gearbox Pad CCW (*) CCW CCW Gear Ratio To Core Speed 0.7947 0.3783 2.4126 Horsepower Continuous Pad Rating HP (KW) 243 (181.3) 85 (63.5) 58 (43.3) Shear Torque in-lb (N-m) 10000 - 10500 (1130 - 1187) 4250 - 4850 (480 - 548) 3500, 4500** (395, 508)** Maximum Overhung Moment in-lb (N-m) 2000 (226.0) 230 (26.0) 400 (45.2)
DRIVE PAD IDG (120 KVA) Hydraulic Pump VSCF/PMG Generator (20/30 KVA) IDG Overload Limits
304 HP (226.8 KVA) for 5 minutes per 1000 hours of operation 406 HP (302.9 KVA) for 5 seconds per 1000 hours of operation 500 HP (373.0 KVA) electrical fault 87 HP (64.9 KVA) for 5 minutes per 1000 hours of operation 116 HP (86.5 KVA) for 5 seconds per 1000 hours of operation 128 HP (95.5 KVA) electrical fault 100 percent core speed is 9,332 RPM (*) Counter Clockwise (**) Shear torque capability is a function of operator requirements. Consult GE Aircraft Engines for installed capability.
VSCF/PMG Overload limits
GE90-110B1/-113B/-115B
Rotation Facing Gearbox Pad CCW (*) CCW CCW Gear Ratio To Core Speed 0.7947 0.3783 2.4126 Horsepower Continuous Pad Rating HP (KW) 243 (181.3) 85 (63.5) 58 (43.3) Shear Torque in-lb (N-m) 10500 max (1187 max) 4250 - 4850 (480 - 548) 1250 max (141.2 max) Maximum Overhung Moment in-lb (N-m) 2000 (226.0) 230 (26.0) 400 (45.2)
DRIVE PAD IDG (120 KVA) Hydraulic Pump VSCF/PMG Generator (20/30 KVA) IDG Overload Limits VSCF/PMG Overload limits
304 HP (226.8 KVA) for 5 minutes per 1000 hours of operation 406 HP (302.9 KVA) for 5 seconds per 1000 hours of operation 500 HP (373.0 KVA) electrical fault 87 HP (64.9 KVA) for 5 minutes per 1000 hours of operation 116 HP (86.5 KVA) for 5 seconds per 1000 hours of operation 128 HP (95.5 KVA) electrical fault 100 percent core speed is 9,332 RPM (*) Counter Clockwise
Engine ratings are based on calibrated test stand performance under the following conditions: 1. Sea level static, standard pressure (14.696 psia), 59F 2. No customer bleed or customer horsepower extraction 3. Ideal inlet, 100% ram recovery 4. Production aircraft flight cowling 5. Production instrumentation 6. Fuel lower heating value of 18400 BTU#
MAXIMUM PERMISSIBLE AIR BLEED EXTRACTION Allowable Bleed Limits (Percent) GE90-76B/-77B/-85B/-90B/-94B Stage 4 Stage 7 Stage 10 Below 23 Percent N1K 23 to 31 Percent N1K 31 to 57.4 Percent N1K 57.4 to 80 Percent N1K 80 to 96.8 Percent N1K Above 96.8 Percent N1K GE90-110B1/-113B/-115B Below 27 Percent N1K At 51 Percent N1K At 80 Percent N1K At 88 Percent N1K At 93 Percent N1K today Above 93 Percent N1K 7.8 7.6 7.4 7.2 7.0 6.5 Stage 4 7.6 7.6 7.6 7.6 7.6 7.6 1.8 1.6 1.3 1.3 1.3 1.3 Stage 7 1.5 1.5 1.5 1.5 1.5 1.5 13.6 12.8 12.6 12.6 6.5 6.5 Stage 9 11.2 11.5 12.0 11.0 8.0 7.3
Maximum Allowable 15.4 14.4 13.9 13.9 8.3 7.8 Maximum Allowable 12.7 13.0 13.5 12.5 9.1 9.1
Fuel Approved fuels must conform to GE Specification D50TF2. Certain fuels such as those produced to PRC Specification RP3 meet the requirements of D50TF2 by means of the Specification. The engine will operate with a mixture of fuels or additives conforming to GE Specification D50TF2. Life limits established for critical rotating components for: GE90-76B/-77B/-85B/-90B/094B are published in Chapter 5 of the GE90 Engine Manual, GEK 100700 GE90-110B1/-113B/-115B are published in Chapter 5 of the GE90-100 Engine Manual, GEK 109993 Power setting, power checks, and control of engine thrust output in all operations are based on Fan Speed (N1). Speed sensors are included in the engine assembly for this purpose. GE90-76B engines with configuration type box number 320-839-501-0 must incorporate the HP/LP turbine hardware and associated changes per General Electric GE90 Service Bulletin 72-169. The FADEC incorporates a 30oC shunt. The corresponding indicated EGT limits are 975oC (take-off), 980oC (take-off with 60 second max. transient), and 965oC (max. continuous).
For ground operation in icing conditions the following procedures must be observed: GE90-76B/-77B/-85B/-90B/-94B During ground operations (including taxi-in and taxi-out) in icing conditions, the pilot must perform one of the following shed procedures: (a) Run up the engines momentarily to a minimum of 50 percent N1 at intervals not to exceed 15 minutes, or (b) For operation at ambient conditions of -6 degrees C (23 degrees F) and above, and at airport altitudes up to 3048 meters (10,000 ft), perform the following at intervals not to exceed 60 minutes:
Increase throttle to a minimum of 55 percent N1 Dwell at the specified N1 for 20 seconds minimum Decelerate to idle or proceed with normal takeoff procedure.
See GE90 Operating Instructions Manual GEK 100703. GE90-110B1/-113B/-115B During ground operations (including taxi-in and taxi-out) in icing conditions, the engine must be run up momentarily to a minimum of 50 percent N1 at intervals not to exceed 60 minutes. See GE90-100 Operating Instructions Manual GEK109994. Note: For possible variations in engine acceleration times in icing conditions see the GE90-100 Installation Manual GEK 109995. NOTE 12. All GE90 engines with configuration type box part numbers 320-892-101-0 or 320-892-201-0 must incorporate the PT25 extended wedge ice shield per GE90 Service Bulletin 77-008 and must incorporate FADEC software P/N 1853M99P06 (version 9.1.9.7 or later) per GE90 Service Bulletin 73-040. All GE90 engines with configuration type box part numbers 320-837-701-0, 320-839-501-0, 320-892-101-0, 320-892201-0, 320-846-701-0, 320-892-601-0 and 320-915-201-0, have a minimum permissible N2 of 6066 RPM for in-flight operation during icing conditions. All GE90 engines with configuration type box part numbers 320-921-501-0 have a minimum permissible N2 of 6310 RPM for in-flight operation during icing conditions. All GE90 engines with configuration type box part numbers 390-850-001-0 and 390-851-001-0 have a minimum permissible N1 of 730 RPM for in-flight operation during icing conditions. NOTE 13. Demonstration of compliance to 33.68, Induction System Icing is installation specific to the B777-200LR/300ER and B777 Freighter airplanes for the GE90-110B1/-113B/-115B model engines. Installation of these model engines on different airplane models or types will require a separate evaluation and finding of compliance to 33.68. During "negative-G" operation only, it is permissible to operate below minimum oil pressure of 10 psid (69.0 kPa diff) for a maximum of 15 seconds. See GE90 Operating Instructions Manual, GEK 100703 for GE90-76B/-77B/-85B/-90B/-94B See GE90-100 Operating Instructions Manual GEK 109994 for GE90-110B1/-113B/-115B.
THESE MODELS INCORPORATE THE FOLLOWING GENERAL CHARACTERISTICS ENGINE MODEL GE90-76B GE90-77B GE90-85B GE90-90B GE90-94B GE90-110B1 CHARACTERISTICS Basic Model Same as GE90-76B except improved HPT/LPT flowpath and higher thrust ratings. Corresponding Rating Plug changes. Same as GE90-76B except higher thrust ratings. Corresponding Rating Plug changes. Same as GE90-77B except higher thrust ratings. Corresponding Rating Plug changes. Same as GE90-90B except 3D aero HPC and higher thrust ratings. Corresponding rating plug changes. Differs primarily from basic model in FAN, LPC, HPC, HPT and LPT hardware, higher takeoff thrust rating with increased speed, and temperature limitations. Corresponding rating plug changes. See Note 22. Same as GE90-110B1 except higher thrust ratings. Corresponding Rating Plug changes. Same as GE90-113B except higher thrust ratings. Corresponding Rating Plug changes.
GE90-113B GE90-115B
NOTE 16. NOTE 17.
The normal 5 minute takeoff time limit may be extended to 10 minutes for engine out contingency. TIME LIMITED DISPATCH CRITERIA Criteria pertaining to the dispatch and maintenance requirements for the engine control systems are specified in: For the GE90-76B/-77B/-85B/-90B/-94B see General Electric Document GEK 103084 and the Airworthiness Limitations Section of the GE90 Engine Manual GEK 100700, which defines the various configurations and maximum operating intervals. For the GE90-110B1/-113B/-115B the requirements are defined in the Airworthiness Limitations section of the GE90100 Engine Manual GEK 109993
For approval of repairs of fan blade composite material in the root section of the fan blade up to the inner annulus flow path line see the Airworthiness Limitations Section of GE90 Engine Manual GEK 100700 for the GE90-76B/-77B/85B/-90B/-94B and GE90-100 Engine Manual GEK 109993 for the GE90-110B1/-113B/-115B. Note deleted
NOTE 20. NOTE 21.
Reserved The FADEC unit P/N originally defined both hardware and software. The hardware and software are now defined by separate P/Ns. The engine should be equipped with a FADEC defined either by the combined P/N or by the hardware and the software P/Ns. An exemption to 21.19(a) was granted and issued in Washington, DC, on August 26, 2002, for the GE90-110B1/113B/-115B engine models. This exemption allowed GEAE to amend Type Certificate No. E00049EN to add these models rather than apply for a new type certificate for those engines, subject to the following conditions and limitations: 1. GEAE must comply with 21.17 as if it was a new type certificate. 2. GEAE must conduct a large flocking bird test as part of compliance with 33.76, Bird Ingestion. 3. GEAE must include an engine test to demonstrate compliance to 33.90 Initial Maintenance Inspection. 4. An applicant installing the GE90-110B1/-113B/-115B engine models into an aircraft must comply with all of the applicable airworthiness standards for a new type certificated engine, including applicable aircraft special conditions. Demonstration of compliance to 33.73(b) Power or Thrust Response is installation specific to the B777200LR/300ER and B777 Freighter airplanes for the GE90-110B1/-113B/-115B model engines. Installation of these model engines on different airplane models or types will require a separate evaluation and finding of compliance to 33.73(b).
- - ---END- - ---
Magtrol Load ISP521
capitulo 17 ventiladores
Nuclear Posture Review FactSheet 20100406
Popular in Type Certificate
Magentos Series s20-200
Procedures Pt
Rule: Special Conditions: Boeing Model 747 Series Airplanes&#8212; Boeing Model 767 Series Airplanes; Seats with Non-Traditional, Large, Non-Metallic Panels
Christos Stefoulis