Equipment list operational and

REMARKS OR EXCEPTIONS

10. Cabin Altimeter

16. Baggage Door Seal

17. APU Bleed Air Max Cool Valve

(O) May be inoperative provided:

a) Cabin Altimeter is operative, and

b) A Chart is provided to convert Altitude Pressure to Differential Pressure.

OPERATIONAL PROCEDURES

1. Refer to Standard Atmosphere Chart Appendix Page

2. Place placard adjacent to Cabin Differential Pressure Gauge stating, “CABIN DIFFERENTIAL GAUGE INOPERATIVE.”

3. Make appropriate discrepancy report entry.
(O) May be inoperative provided:

a) Cabin Differential Pressure Gauge is operative,

b) A Chart is provided to convert Differential Pressure

OPERATIONAL PROCEDURES

1. Refer to Standard Atmosphere Chart Appendix Page A-2 to convert cabin differential pressure to altitude.

2. Place placard adjacent to Cabin Differential Pressure Gauge stating, “CABIN ALTIMETER INOPERATIVE.”

3. Make appropriate discrepancy report entry.

a) The aircraft is operated below 41,000 feet,

b) The number of flights with the baggage compartment not pressurized is logged, and

c) AFM and Maintenance Manual limitations are complied with.

OPERATIONAL PROCEDURES

1. Record number of flights made with the baggage compartment unpressurized.

2. Make appropriate discrepancy report entry.
(M) May be inoperative provided a blocking plate is
installed to block APU cooling bleed airflow.

MAINTENANCE PROCEDURE

1. Using a stainless steel sheet at least .025 inches, up

2. With the V-band clamp removed, slide the disk in

(Continued Next Page)

REMARKS OR EXCEPTIONS

3. Hold the lower half of the clamp in place to prevent the disk from slipping out.

4. Reinstall the V-band clamp.

5. Do a functional check to detect any escaping air from capped line or valve.

(a) Start the APU.

(b) Turn the bleed air and at least one of the ECU's

(c) A technician should carefully check for leaks.

6. Place a maintenance tag on the assembly after

7. Make appropriate discrepancy report entry.

8. Placard the Max Cool Valve switch on the APU control panel stating "Bleed Air Max Cool Valve INOP."
NOTE The above procedure requires the installation of a blocking plate. In the absence of a blocking plate installation, with an "OPEN" failed valve, it will not be possible to start the engines using the APU. Aircraft must be started with an air supply cart. Refer to MMEL for APU INOP relief.

REMARKS OR EXCEPTIONS

1. Autopilot Systems (Flight Guidance Computers)

2. Lower Rudder Yaw Damper

(O) May be inoperative except where RVSM or approach minimums require use of an autopilot provided both Flight Guidance Computers are verified to be operative.

OPERATIONAL PROCEDURES (for both Autopilot relief items)

1. Place placard adjacent to Flight Guidance Controller, “Autopilot (A/B/Both) INOPERATIVE.”

2. Make appropriate discrepancy report entry.

3. Refer to AFM Normal Procedures for Cockpit Preparation and Flight Guidance power up. When the flight guidance is powered-up it accomplishes a system self-test, which takes approximately 30 seconds to complete. When the test is completed, the white FGC A-B MASTER status message will be displayed for five seconds. If failure is detected in either FGC, the blue advisory message FGC A-B FAIL will be displayed.

4. Verify that the white FGC A-B MASTER CAS message is displayed, and FGC A-B FAIL is not displayed.

------------------------ or ---------------------------------------

3. 
   With electrical power and avionics on, from MFD Main page 2/2, select FGC Source from A to B, and from B to A.
   
4. 
   Verify that the FGC A-B FAIL CAS message is not displayed.
   

(O) May be inoperative provided:

a) AFM limitations applicable to dual rudder YD failure (see YD FAIL LOWER A-B amber abnormal procedure) are complied with, and

b) Both Flight Guidance Computers (FGC's) are verified operative.

OPERATIONAL PROCEDURES

1. Place placard adjacent to EICAS Display stating, “Lower Rudder Yaw Damper (A or B) INOPERATIVE.”

2. Make appropriate discrepancy report entry.

3. With electrical power and avionics on, from MFD Main page 2/2, select FGC Source to the side that has the OPERATIVE Lower Rudder Yaw Damper.

4. Verify that EICAS does NOT display an FGC FAIL CAS message.

5. Verify that EICAS does NOT display an YD FAIL LOWER A-B amber message. (Cyan message may be displayed.)

NOTE: If FGC Source is selected to the side with the inoperative Yaw Damper, crew should observe a momentary FGC FAIL CAS message, followed by an uncommanded FGC source swap to the "good" side.

6. Flight should be dispatched with the FGC selected to the "good" side. FGC comparator monitoring will still be available, though the autopilot on the "bad" side will not engage because of the failed Yaw Damper.