TEMPORARY REVISION. AMM-TR-OÄM f. Auxiliary Fuel Tanks

Transcription

1 TEMPORARY REVISION % AMM-TR-OÄM f % % This AMM-TR-OÄM f is approved in conjunction with the Optional Design Change Advisory OÄM g and is valid in conjunction with the Airplane Maintenance Manual (AMM) until this has been incorporated into the AMM. The limitations and information contained herein either supplement or, in the case of conflict, override those in the AMM. The technical information contained in this document has been approved under the authority of DOA No. EASA.21J.052. Doc. No. Section Affected Pages a, 64a, 68a, 69a a a a a, 2a, 3a, 3b a, 3a, 3b, 4a, 5a a, 5 thru 8, 201a, 205a, 211 thru a, 3a, 3b, 4a, 216 thru a a Instruction ) Print this document on yellow paper (single-sided). ) Insert this cover page as the first page of the AMM. ) Insert the other pages of this in front of the corresponding AMM pages. AMM-TR-OÄM f COVER Page 1

2 CHAPTER 05 TIME LIMITS AND MAINTENANCE CHECKS Section Scheduled Maintenance Checks Maintenance Practices Maintenance Checklist DA Engine Ground Test The following table is amended to read. Do an engine ground test as follows (complete a copy of the Engine Ground Test Record as part of the engine ground test (Refer to Paragraph 8)): WARNING: Inspection Items Time Initials DO NOT LET PERSONS GO INTO THE DANGER AREA OF THE PROPELLER. PROPELLERS CAN CAUSE INJURY OR DEATH. WARNING: SET THE PARKING BRAKE TO ON. IF YOU DO NOT DO THIS, THE AIRPLANE CAN MOVE. THIS CAN CAUSE INJURY OR DEATH. 1. Set the parking brake to ON. X X X X 2. Put the chocks against the airplane main wheels. X X X X 3. Do an engine run. (Refer to the AFM). X X X X 4. Check engine instruments. X X X X 5. Do a test of the cross-feed system. (Refer to Section X X X X 28-20). 6. Do a test of the fuel shut-off system. (Refer to Section X X 28-20). 7. If auxiliary tanks are installed (OÄM ) do test of X X X the auxiliary fuel transfer system. (Refer to Section 28-20) 8. Do a test of the feathering & unfeathering system X X X X (Refer to Section 61-20). 9. Shut engines down. X X X X 10. Read FADEC values. (Refer to Section 72-00). X X X X AMM-TR-OÄM f Page 5a

3 4. Maintenance Checklist Zones G. Wings (1) Wings, General Item 2 in the checklist is amended to read: 100 hr items marked X* apply to US registered airplanes only Inspection Items, Wings, General Time Initials 2. Remove the fuel tanks from the wings. (Refer to Chapter 28). S Remove the main fuel tanks from the wings. S If installed, remove the auxiliary fuel tanks (OÄM ) from the engine nacelles. X X AMM-TR-OÄM f Page 64a

4 (4) Fuel Tanks % The following Item is inserted into the table: 100 hr items marked X* apply to US registered airplanes only Inspection Items, Fuel Tanks Time Initials Note: If the auxiliary fuel tanks (OÄM ) are installed, then the inspection items shown in this table must also be applied to the auxiliary fuel tanks. % 3a. Examine auxiliary fuel tank vents for blockage (if X X X X % installed, OÄM carried out) % % % S open fuel filler cap and blow through the vent line from outside into the tank with compressed air S check vent hole in the fuel filler fitting for blockage % AMM-TR-OÄM f Page 68a

5 (5) Wings, Miscellaneous Item 3 in the checklist is amended to read: 100 hr items marked X* apply to US registered airplanes only Inspection Items, Wings, Miscellaneous Time Initials 3. Install the fuel tanks to the wings. (Refer to Chapter 28). S If furnished (OÄM ), install the auxiliary fuel tanks into the engine nacelles. S Install the main fuel tanks into the wings. X X AMM-TR-OÄM f Page 69a

6 The Weighing Report is amended to read: WEIGHING REPORT Model: DA 42 Serial Number: Registration: Data with reference to the Type Certificate Data Sheet and the Airplane Flight Manual. Reference Plane: Vertical plane 2196 mm (86.46 in) in front of the leading edge of wing at the root rib. Horizontal reference line: Front baggage compartment floor, left side. Equipment Inventory - dated: Cause for Weighing: Weight and Balance Calculations (Weighing at the wheels) Weight Condition: Include brake fluid, hydraulic fluid, coolant, engine oil, unusable fuel main tanks (7.57 liters/2 US gal) and unusable fuel auxiliary tanks (if installed; 5.0 liters / 1.32 US gal). Support Gross Tare Net Lever Arm MAIN G 1LH X 1LH = MAIN G 1RH X 1RH = NOSE G 2 X 2 = Empty Weight % Calculate the Empty Weight, G = MAIN G 1LH + MAIN G 1RH + NOSE G 2. G = % Calculate the Empty Weight Moment, M = (G 1LH * X 1LH )+( G 1RH * X 1RH ) + (G 2 * X 2 ). M = % % % Calculate the Empty Weight Center-of-Gravity position, X CG = M/G. X CG = Maximum permitted all-up-weight: Max AUW. Maximum useful load = Max AUW - G. Record the Empty Weight (G) and the Empty-Weight Moment (M) in the Airplane Flight Manual. Place/Date Authorizing Stamp Authorizing Signature Figure 4: Weighing Report for Mechanical Scales Under the Wheels AMM-TR-OÄM f Page 7a

7 DA DA DA 42 AMM CHAPTER 11 PLACARDS AND MARKINGS 1. General Section Exterior Placards and Markings Figure 1 is amended as follows: WARNING APPROVED FUEL: JET-A1 or see Airplane Flight Manual LH & RH LH & RH Coolant EMERGENCY EXIT: The keylock must be unlocked during flight! LH & RH LH & RH If de-icing system is installed Gearbox Oil Shell EP 75W90 API GL-4 or see AFM OIL Shell Helix Ultra 5W/30 synth. API SJ/CF or see Airplane Flight Manual DE-ICING FLUID Refer to AFM for approved fluids. WARNING APPROVED FUEL: JET-A1 or see Airplane Flight Manual LH & RH, optional (OÄM ) LH & RH 4.5 bar / 65 psi 3 Off Between the Blades 6.0 bar / 87 psi External Power Connection CAUTION: 28 V DC WARNING APPROVED FUEL: JET-A1 or see Airplane Flight Manual Figure 1: Exterior Placards AMM-TR-OÄM f Page 1a

8 2. Description Section Internal Placards and Markings Figure 2 is amended as follows: Figure 2: Interior Placards - Instrument and Control Panels AMM-TR-OÄM f Page 3a

9 CHAPTER 12 SERVICING Section Replenishment 2. Fuel System The following headline is added before text: A. Main Fuel Tanks The following paragraphs are added before the CAUTIONS: B. Auxiliary fuel tanks (OÄM ) are optional equipment. The auxiliary fuel tanks consist of a single fuel chamber in each engine nacelle. The auxiliary fuel tanks are installed in the rear section of the engine nacelles, above the wing main spars. The additional fuel capacity is 13.7 US gallons (52 liters) per side. The total fuel capacity (main fuel tanks and auxiliary fuel tanks) is 39.6 US gallons (150 liters) per side. Each auxiliary fuel tank has a filler cap located on the top surface of the nacelle. The filler cap connects to the forward end of auxiliary tanks. A fuel tank drain is located at the rear of each auxiliary tank. AMM-TR-OÄM f Page 1a

10 Figure 1 is amended as follows: Fuel Fuel (optional, OÄM ) Hydraulic Fluid Brake Fluid (on Co-Pilot's Brake Pedals) Engine Oil Engine Oil Fuel (optional, OÄM ) Coolant Fuel Nitrogen & Oil Tire Air Coolant Nitrogen & Oil Tire Air (LH & RH) Figure 1: Replenishment Points AMM-TR-OÄM f Page 2a

11 A. Refueling The procedure is amended as follows: Detail Steps/Work Items 1. Shut down the engines. 2. Engine MASTER OFF. 3. All occupants leave the airplane. Key Items/References 4. Ground the airplane electrically. At the refueling connection. 5. Ground the refueling vehicle electrically. 6. Remove the fuel filler cap. On the upper surface of the wing. 7. Refuel the airplane. 8. Install the fuel filler cap. Make sure that the filler cap is locked. 9. Do items 6 thru 8 for the other wing. 10. Do items 6 thru 8 for the auxiliary tanks, if installed (OÄM ). Filler caps located on the outboard side of the engine nacelles. 11. Remove the ground cable from the airplane. 12. Remove the ground cable from the refueling vehicle. AMM-TR-OÄM f Page 3a

12 B. Defueling The procedure is amended as follows: Detail Steps/Work Items Key Items/References 1. Ground the airplane electrically. At the refueling connection. 2. Put a suitable container below the drain valve for the wing that you will defuel. Make sure that you have enough containers to hold all the fuel. Each wing can hold approximately 26 US gallons (100 liters) fuel. 3. Open the drain valve. 4. When the fuel stops draining, close the drain valve. 5. Do items 2 thru 4 for the auxiliary fuel tank, if installed (OÄM ). Make sure that the drain valve is seated correctly. Each auxiliary fuel tank can hold approximately 14 US gallons (52 liters) fuel. 6. If necessary, do items 2 thru 5 for the other wing. 7. Remove the ground cable from the airplane. At the refueling ground connection. AMM-TR-OÄM f Page 3b

13 CHAPTER 28 FUEL 1. General The following paragraph is inserted between the 2 nd and 3 rd paragraph: Auxiliary fuel tanks are optional equipment (OÄM ). The auxiliary fuel tanks consist of a single fuel chamber in each engine nacelle. The additional fuel capacity is 13.7 US gallons (52 liters) per side. The total fuel capacity (main fuel tanks and auxiliary fuel tanks) is 39.6 US gallons (150 liters) per side. Each auxiliary tank has its own fuel tank filler and a fuel transfer pump which pumps fuel into the main fuel tank. AMM-TR-OÄM f Page 1a

14 2. Description The following sentence is added to the end of the first paragraph: Figure 2 shows the auxiliary fuel tank system schematic diagram for the DA 42 airplane. The auxiliary fuel tank system is optional equipment (OÄM ). It has a fuel chamber in each engine nacelle. Paragraph 'A' is amended to read: A. Main Fuel Tanks Each wing tank assembly has 3 separate chambers. The chambers are connected by large diameter flexible hoses. Smaller hoses inter-connect the chambers at the top to provide a vent system for the fuel tank assembly. The inboard chamber has a fuel contents probe, fuel temperature sensor, low fuel level switch, and the fuel supply and return connections. Some (low) serial numbers have a high level fuel switch installed which is unused. The rest of the serial numbers have a plug in this place. The fuel supply connection attaches to a finger filter mounted on the fuel chamber. A fuel drain valve is located at the lowest part of the inboard fuel chamber. The middle fuel chamber is a plain chamber and has no installed components. The outboard fuel chamber has a fuel quantity probe, high fuel level switch, and the fuel filler assembly. The high fuel level switch is only used when the optional auxiliary fuel tanks (OÄM ) are installed. In this case, it switches off the fuel transfer pump as soon as the main fuel tank is full. The outboard chamber also has the check valve, vent valve and pressure relief valve for the fuel tank assembly vent system. The fuel quantity probes go from the bottom inboard corner to the top outboard corner of the fuel chambers. The probes sense the level of fuel in the fuel tank assemblies and displays the information on the display screen of the integrated cockpit system. The following paragraph is inserted after paragraph 'A': B. The auxiliary fuel tank system is optional equipment (OÄM ). The auxiliary fuel tanks consist of a single fuel chamber in each engine nacelle. Each auxiliary fuel tank has a fuel transfer pump which pumps fuel into the main fuel tank on the same side of the airplane. Each auxiliary fuel tank has a shut-off switch which switches off the fuel transfer pump when the level in the auxiliary fuel tank is low. The fuel supply connection attaches to a finger filter mounted at the rear of the auxiliary fuel tank. A fuel drain valve is located at the lowest part of the auxiliary fuel tank. A vent line with check valve and capillary is connected at the forward wall of the auxiliary fuel tank. A drain line is connected to the filler drip tray. AMM-TR-OÄM f Page 3a

15 A page with the following figure is inserted between pages 3 and 4 of Section : Fuselage TAE Diesel Filter Fuel Selector/ Shut Off Valve Check Valve Inc. Capillare Fire wall Sediment Bowl Shut-off Switch Drain Fuel Supply Auxiliary Tank LH Fuel Cooler Drain Fuel-Filler Check Valve Finger Filter TAE 125 Engine Return Pipe Auxilliary Fuel Pump Inline Filter Temperature Sensor Low Fuel Sensor Finger Filter Wing Tank LH Drain Pressure Check Valve Figure 2: Auxiliary Fuel System Schematic Diagram AMM-TR-OÄM f Page 3b

16 3. Operation A. Normal Operation The following text is added at the end of paragraph A: Auxiliary fuel tanks are optional equipment (OÄM ). For each auxiliary tank there is a FUEL TRANSFER switch in the cockpit, in the center console behind the elevator trim wheel. When this switch is set to ON, then fuel is pumped from the auxiliary fuel tank into the related main fuel tank. The pump is automatically switched off when the main fuel tank is full, or when the auxiliary fuel tank is empty. AMM-TR-OÄM f Page 4a

17 E. Fuel Drains The first sentence is amended to read: You can use the fuel drains in each main fuel tank, each auxiliary fuel tank and each sediment bowl to defuel the airplane. AMM-TR-OÄM f Page 5a

18 Section Fuel Storage System 1. General The text at the beginning is amended to read: This Section tells you about the fuel storage system of the DA 42 airplane. It tells you about these components: ) Main fuel tanks. ) Fuel filler assembly. ) Fuel tank vents. ) Auxiliary fuel tanks (optional equipment). Headline 2 is amended to read: 2. Main Fuel Tank Description AMM-TR-OÄM f Page 3a

19 The following paragraphs (3 and 4) are inserted after paragraph 2: 3. Auxiliary Fuel Tank Description Figure 3 shows the auxiliary fuel tank installation. The airplane has 2 auxiliary fuel tank assemblies (optional equipment, OÄM ) One in the left wing and one in the right wing. A single chamber makes the auxiliary fuel tank assembly. The chambers is located in the rear section of the engine nacelle. The chamber is a welded aluminum structure. Baffles in the chamber prevent the fuel from moving quickly from one end of the tank to the other. The chamber has bosses welded into the forward and rearward end-plates to make connections for the flexible hoses and other components that attach to the end-plates of the chamber. A tank outlet is located at the inboard rear corner of the chamber. A finger-filter at the tank outlet prevents debris from entering the main fuel tank. A drain valve is located at the lower surface at the rear end of the chamber. You can use this drain valve for doing fuel contamination tests and for draining the auxiliary fuel tank assembly. A fuel low-level sensor is also mounted on the rearward end-plate of the chamber. The forward end-plate of the fuel chamber has a fitting for the auxiliary fuel tank vent line. The top surface has the fitting for the fuel filler assembly. The auxiliary fuel tank has no fuel quantity indicating system. Two ribs in the nacelle hold the fuel chamber in position in the nacelle. The rearward rib is open on the bottom side. A stainless steel strap closes the rear rib. Rubber strips go between the tank chamber and the ribs. The filler cap assembly is attached to the upper surface of the nacelle. AMM-TR-OÄM f Page 5

20 LH Installation Shown RH Installation Similar Fuel Level Sensor Finger Filter Auxiliary Tank Fuel Filler Cap Check Valve Figure 3: Auxiliary Fuel Tank Installation AMM-TR-OÄM f Page 6

21 4. Auxiliary Fuel Tank Filler The auxiliary fuel tank filler has a flange that attaches to a drip tray in the top skin of the nacelle. It also has slots that engage the fuel filler cap. Turn the filler cap counter-clockwise to release it. Turn the cap clockwise to install it. A drain line is connected to the drip tray. Bonding strips connect the tank to the airplane bonding system. AMM-TR-OÄM f Page 7

22 Auxiliary Tank Filler Cap O-Ring Cover Plate Connecting Pipe LH shown, RH similar O-Rings Drip Tray AMM-TR-OÄM f Page 8

23 Maintenance Practices Headlines no. 2, A, and B are amended to read: 2. Remove/Disassemble a Main Fuel Tank Assembly A. Remove a Main Fuel Tank Assembly B. Disassemble a Main Fuel Tank Assembly AMM-TR-OÄM f Page 201a

24 Headlines no. 3, B, and C are amended to read: 3. Assemble/Install a Main Fuel Tank Assembly B. Assemble a Main Fuel Tank Assembly C. Install a Main Fuel Tank Assembly AMM-TR-OÄM f Page 205a

25 The following paragraphs (4. and 5. are included): 4. Remove/Install an Auxiliary Fuel Tank A. Remove an Auxiliary Fuel Tank Detail Steps/Work Items Key Items/References 1. Make sure that the auxiliary fuel tank that you will remove is empty. Defuel and drain the auxiliary fuel tank. 2. Remove the auxiliary fuel tank access panel from the engine nacelle: S Remove the 8 screws that attach the access panel to the nacelle. S Disconnect the vent line and the drain line (coming from the drip tray) from the connectors on the access panel. S Move the access panel clear of the nacelle. 3. Disconnect the electrical connector for the fuel level switch at the rearward end of the fuel chamber. 4. Disconnect the fuel line from the tank outlet. 5. Disconnect the bonding strip from the cooler bracket. 6. Remove the fuel filler assembly: S Open the access door to the fuel filler cap. S Remove the fuel filler cap. S Remove the 3 screws that attach the cover plate to the drip tray. S Remove the cover plate with the connection pipe. 7. Remove the bolt, washer and nut which closes the metal strap on the rear attachment rib. 8. Disconnect the front bonding cable at the connection point, in the chamber below the tank compartment. Hold the tank. Accessible through the inspection cover below the tank filler. AMM-TR-OÄM f Page 211

26 Detail Steps/Work Items Key Items/References 9. Disconnect the 2 vent hoses at the front wall of the auxiliary fuel tank: S Gently move the tank rearward a small distance. S Pull the vent lines off the connectors on the tank. Through the hole for the drip tray. 10. Remove the fuel tank assembly: S Gently pull the auxiliary fuel tank assembly out of the nacelle in a rearward and downward direction. S Move the tank clear of the nacelle and support it on a clean workbench. AMM-TR-OÄM f Page 212

27 B. Install an Auxiliary Fuel Tank Detail Steps/Work Items 1. Install the fuel tank assembly: Key Items/References S Gently move the auxiliary fuel tank assembly into the nacelle in an upward and forward direction. Do not move the tank fully forward (see next item). 2. Connect the 2 vent hoses at the front wall of the auxiliary fuel tank: S Connect the vent lines to the connectors on the tank. S Gently move the tank fully forward. 3. Connect the front bonding cable at the connection point, in the chamber below the tank compartment. Through the hole for the drip tray. Accessible through the inspection cover below the tank filler. 4. Install the bolt, washer and nut which closes the metal strap on the rear attachment rib. 5. Install the fuel filler assembly: S Install the cover plate with the connection pipe. S Install the 3 screws that attach the cover plate to the drip tray. S Install the fuel filler cap. S Close the access door to the fuel filler cap. 6. Connect the bonding strip to the cooler bracket. 7. Connect the fuel line to the tank outlet. 8. Connect the electrical connector for the fuel level switch at the rearward end of the fuel chamber. AMM-TR-OÄM f Page 213

28 Detail Steps/Work Items Key Items/References 9. Install the auxiliary fuel tank access panel to the engine nacelle: S Move the access panel in place on the nacelle. S Connect the vent line and the drain line (coming from the drip tray) to the connectors on the access panel. S Install the 8 screws that attach the access panel to the nacelle. 10. Refuel the auxiliary fuel tank. 11. Check auxiliary fuel tank assembly for leakage. AMM-TR-OÄM f Page 214

29 Section Fuel Distribution The caption of figure 1 is amended to read: Figure 1: Fuel Distribution System Schematic without Auxiliary Tanks AMM-TR-OÄM f Page 2a

30 2. Description A. Normal Operation The first sentence is replaced by the following text: Figure 1 shows the schematic diagram for the fuel distribution system for the DA 42 airplane when the auxiliary fuel tanks are not installed. Figure 1A shows the schematic diagram when the auxiliary fuel tanks are installed. Figure 1B shows the items of the auxiliary fuel supply to the main fuel tank. The following text is added at the end of paragraph A: If the optional auxiliary fuel tank is installed (OÄM ), a flexible hose runs from the outlet of the auxiliary tank to the fuel transfer pump. Another flexible hose runs from the outlet of the fuel transfer pump via the relief valve to a T-piece which feeds the auxiliary fuel into the return fuel circuit. The relief valve prevents a backflow of the cooled return fuel from the engine into the auxiliary fuel tank. To protect the relief valve from contamination an inline filter is installed in the fuel transfer line direct at the outlet of the fuel transfer pump. A check valve prevents the auxiliary fuel from being pumped into the fuel cooler. AMM-TR-OÄM f Page 3a

31 A page with the following figure is added between the existing pages 3 and 4: Fuselage TAE Diesel Filter Fuel Selector/ Shut Off Valve Check Valve Inc. Capillare Fire wall Sediment Bowl Shut-off Switch Drain Fuel Supply Auxiliary Tank LH Fuel Cooler Drain Fuel-Filler Check Valve Finger Filter TAE 125 Engine Return Pipe Auxilliary Fuel Pump Inline Filter Temperature Sensor Low Fuel Sensor Finger Filter Wing Tank LH Drain Pressure Check Valve Figure 1A: Fuel Distribution System Schematic with Auxiliary Tanks (OÄM ) AMM-TR-OÄM f Page 3b

32 A page with the following figure is added between the existing pages 4 and 5: LH Installation Shown RH Installation Similar Check Valve Relief Valve Fuel Cooler Auxiliary Tank Return Fuel Line from Engine Inline Filter Fuel Pump To Exterior Drain Line Vent Line Fuel Feed Line to Main Fuel Tank Figure 1B: Auxiliary Fuel Supply to the Main Fuel Tank AMM-TR-OÄM f Page 4a

33 The following maintenance practices are added behind page 215: 10. Remove/Install an inline filter Obey the safety precautions for fuel at all times. A. Remove an inline filter Detail Steps/Work Items Key Items/References 1. Make sure that the auxiliary fuel tank is empty. Defuel and drain the auxiliary fuel tank. 2. Remove the auxiliary fuel tank access panel from the engine nacelle: S Remove the 8 screws that attach the access panel to the nacelle. S Disconnect the vent line and the drain line (coming from the drip tray) from the connectors on the access panel. S Move the access panel clear of the nacelle. 3. Disconnect the fuel transfer line from the auxiliary fuel pump outlet. 4. Remove the inline filter. Filter is inserted in the fuel transfer line. B. Install an inline filter Detail Steps/Work Items Key Items/References 1. Insert the inline filter into the fuel transfer line. Directly at the auxiliary tank outlet connection fitting. 2. Connect the fuel transfer line to the auxiliary fuel pump outlet. 3. Refuel the auxiliary fuel tank. Fill more than 2 US gal of fuel into the auxiliary tank. 4. Perform a test of the auxiliary fuel transfer system Refer to Paragraph Check auxiliary fuel tank assembly for leakage. AMM-TR-OÄM f Page 216

34 Detail Steps/Work Items Key Items/References 6. Install the auxiliary fuel tank access panel to the engine nacelle: S Move the access panel in place on the nacelle. S Connect the vent line and the drain line (coming from the drip tray) to the connectors on the access panel. S Install the 8 screws that attach the access panel to the nacelle. AMM-TR-OÄM f Page 217

35 11. Test the auxiliary fuel transfer system A. Equipment Item Quantity Part Number Ground power supply 1 - Stopwatch 1 Commercial B. Procedure Obey the safety precautions for fuel at all times. CAUTION: YOU MUST REPLACE THE INLINE FILTER IF THE TEST FAILS. Detail Steps/Work Items Key Items/References 1. Connect the aircraft to ground power. 2. Defuel the auxiliary tank using the auxiliary fuel transfer pump. On the side of the auxiliary fuel system that you want to test. Make sure that the corresponding main tank is empty enough to hold the auxiliary fuel. The auxiliary fuel pump must stop due to the auxiliary tank empty switch. 3. Fill 2 US gal of fuel into the auxiliary fuel tank. 4. Measure transfer time for transferring the 2 US gal of fuel from the auxiliary tank into the main tank. The auxiliary fuel pump must stop due to the auxiliary tank empty switch. Measure time from switching on the fuel pump until the fuel transfer stops due to the auxiliary tank empty switch. The transfer time must not be more than 4 min. Check if the corresponding main tank fuel quantity indication increases. 5. Repeat items 2 thru 4 for the other auxiliary fuel transfer system. AMM-TR-OÄM f Page 218

36 Section Fuel Indicating 2. Description The following text is added at the end of Paragraph 2: The fuel quantity in the auxiliary fuel tanks (optional equipment, OÄM ) is not indicated. AMM-TR-OÄM f Page 1a

37 CHAPTER 92 WIRING DIAGRAMS 1. General The following lines are added to the table: Title Drawing No. Rev. No. No. of Sheets LH Aux Fuel Wiring D "b" 1 RH Aux Fuel Wiring D "b" 1 The following line is amended in the table: Title Drawing No. Rev. No. No. of Sheets G1000 D "e" 6 AMM-TR-OÄM f Page 1a