Crew Checklist & Quick Reference Handbook

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CL-126C

CREW CHECKLIST & QUICK REFERENCE HANDBOOK

Subject: Learjet 45 Checklist (U.S. Units) — Change 2

The following summary describes the changes that are incorporated with this change.

NORMAL PROCEDURES After Landing/Clearing Relocated “Standby Attitude Indicator — Cage”” step to Shut- Runway down procedure. Even though the gyro is caged, it is still functioning and normal taxiing procedures and tarmac irregularities may contribute to excess wear and tear on the unit.

Shutdown Added step to cage the standby attitude indicator after the aircraft has been parked.

PERFORMANCE DATA TAKEOFF Added shading and the statement that shaded areas are for interpolation only. This statement was erroneously left out on some tables.

EMERGENCY PROCEDURES General Changes Updated Tab references. Miscellaneous formatting changes throughout section. No change to content.

Cabin/Cockpit Fire, Revised step to use Clearance Delivery Radio to tune COM 1. Smoke or Funes

LR GEN FAIL Deleted reference to the 38 amp-hr Ni-Cad battery, as the duration time of 1.0 hr is the same for Lead-Acid or Ni-Cad batteries. Revised step to clarify the conditions that will exist with emergency battery until main batteries have been depleted..

Loss of Both Genera- Deleted reference to using RMU 1 to tune COM 1 as RMU 1 is tors and Both Main not available if main battery is not on-line. Batteries Moved RMU 1 from operative to inoperative column.

L REV UNSAFE R REV UNSAFE Clarified procedure by adding step to reduce speed to 160 UNL or DEP KIAS or below as required to maintain level flight. During Takeoff Above V1 Speed

In flight Added the work “level” to clarify the procedure step.

CL-126C Highlights-1 Change 2 ABNORMAL PROCEDURES General Changes Miscellaneous formatting changes throughout section.

L CHK IC SW Added amber CAS messages to indicate that there is a mis- R CHK IC SW match between the loaded IC-600 software and the approved LR CHK IC SW configuration software ID file, or that the program enable discrete is active. These CAS messages will appear in ground mode, and are inhibited on takeoff.

Landing Gear Free Fall Revised procedure to clarify action after GEAR FREEFALL lever step has been initiated.

Normal Electrical Added footnotes to Operative/Inoperative Table to clarify what System Failure Land- instruments are operative with main batteries not depleted. ing

Main Hydraulic Sys- Separated step “3a” into two separate steps to clarify the ver- tem Failure Landing biage to check that brake accumulator reservoir pressure is adequate before activating the HYD XFLOW switch for flap extension.

ADVISORY/STATUS General Changes Miscellaneous formatting changes throughout section. No change to content.

SUPPLEMENTAL DATA General Changes Miscellaneous formatting changes throughout section. No change to content.

DC Power Distribution Deleted reference to 10 Amp-Hr as it is no longer available. (Dual Generator Regardless of which battery is installed, the duration is 1 hour. Failure)

Master EICAS Index Updated Tab references. Added reference to L CHK IC SW, R CHK IC SW, and LR CHK IC SW CAS message.

APU Amps High Changed to N/A as it indicates a normal system response for excessive electrical loads being placed on the APU generator.

APU FAIL Revised NO GO or MEL RELIEF column to harmonize with DDG and MMEL.

Highlights-2 CL-126C Change 2

LIST OF EFFECTIVE PAGES

Use this List of Effective Pages to determine the current status of the Crew Checklist and Quick Reference Handbook. Pages affected by the current change are indicated by an asterisk (*) immediately preceding the page number. Dates of issue for original and changed pages are: Original ...... O ...... April 1998 Reissue...... A ...... December 1999 Reissue...... B ...... October 2004 Reissue...... C ...... October 2008 Change ...... 1 ...... June 2009 Change ...... 2 ...... March 2010

Page Change Aircraft Affected/Effectivity Code

Title ...... C All *LOEP-1 thru LOEP-7...... 2 All *LOEP-8 (Added)...... 2 All *LOR ...... 2 All *TCL-1 ...... 2 All i ...... C All ii...... 1 All iii and iv ...... C All Normal Procedures N-1 thru N-13...... C All N-14 ...... 1 Aircraft 45-002 & on not modified by SB 45-11-4 N-14.1...... 1 Aircraft 45-002 & on modified by SB 45-11-4 N-15...... C All *N-16 thru N-18...... 2 All N-19 and N-20...... 1 All Performance Data *P-1...... 2 All *P-2...... 2 D P-2.1 ...... 1 E P-2.2...... 1 F P-3...... 1 D P-3.1...... 1 E P-3.2...... 1 F P-4...... 1 D P-4.1...... 1 E P-4.2...... 1 F P-5...... 1 D P-5.1 ...... 1 E P-5.2...... 1 F Denotes pages presented in either U.S. or metric units. CL-126C Change 2 LOEP-1 Change 2 Page Change Aircraft Affected/Effectivity Code P-6 ...... 1 D *P-6.1 ...... 2 E P-6.2 ...... 1 F *P-7 ...... 2 D *P-7.1 ...... 2 E P-7.2 ...... 1 F *P-8 ...... 2 D *P-8.1 ...... 2 E P-8.2 ...... 1 F *P-9 ...... 2 D *P-9.1 ...... 2 E *P-9.2 ...... 2 F *P-10 ...... 2 D *P-10.1 ...... 2 E P-10.2 ...... 1 F *P-11...... 2 D *P-11.1 ...... 2 E *P-11.2...... 2 F *P-12 ...... 2 D *P-12.1 ...... 2 E *P-12.2 ...... 2 F *P-13 ...... 2 D *P-13.1 ...... 2 E *P-13.2 ...... 2 F P-14 ...... 1 D P-14.1 ...... 1 E P-14.2 ...... 1 F P-15 ...... 1 D *P-15.1 ...... 2 E P-15.2 ...... 1 F *P-16 ...... 2 D *P-16.1 ...... 2 E P-16.2 ...... 1 F *P-17 ...... 2 D *P-17.1 ...... 2 E *P-17.2 ...... 2 F *P-18 ...... 2 D *P-18.1 ...... 2 E *P-18.2 ...... 2 F *P-19 ...... 2 D *P-19.1 ...... 2 E *P-19.2 ...... 2 F *P-20 ...... 2 D *P-20.1 ...... 2 E *P-20.2 ...... 2 F *P-21 ...... 2 D *P-21.1 ...... 2 E *P-21.2 ...... 2 F Denotes pages presented in either U.S. or metric units. CL-126C Change 2 LOEP-2

Page Change Aircraft Affected/Effectivity Code P-22...... 1 All P-23...... 1 D and E P-23.2...... 1 F P-24...... 1 D and E P-24.2...... 1 F P-25...... 1 D and E P-25.2...... 1 F P-26...... 1 D and E P-26.2...... 1 F P-27...... 1 D and E P-27.2...... 1 F P-28...... 1 D and E P-28.2...... 1 F P-29...... 1 D and E P-29.2...... 1 F P-30...... 1 D and E P-30.2...... 1 F P-31...... 1 D and E P-31.2...... 1 F P-32...... C All P-33...... 1 D and E P-33.2...... 1 F P-34...... 1 D and E P-34.2...... 1 F P-35...... 1 D and E P-35.2...... 1 F P-36...... 1 D and E P-36.2...... 1 F P-37...... 1 D and E P-37.2...... 1 F P-38...... 1 D and E P-38.2...... 1 F P-39...... 1 D and E P-39.2...... 1 F P-40...... C All P-41...... 1 D and E P-41.2...... 1 F P-42...... 1 D and E P-42.2...... 1 F P-43...... 1 D and E P-43.2...... 1 F P-44...... 1 D and E P-44.2...... 1 F P-45...... 1 D and E P-45.2...... 1 F P-46...... 1 D and E P-46.2...... 1 F

Denotes pages presented in either U.S. or metric units. CL-126C LOEP-3 Change 2 Page Change Aircraft Affected/Effectivity Code P-47 ...... 1 D and E P-47.2 ...... 1 F P-48 ...... C All P-49 ...... 1 D and E P-49.2 ...... 1 F P-50 ...... 1 D and E P-50.2 ...... 1 F P-51 ...... 1 D and E P-51.2 ...... 1 F P-52 ...... 1 D and E P-52.2 ...... 1 F P-53 ...... 1 D and E P-53.2 ...... 1 F P-54 ...... 1 D and E P-54.2 ...... 1 F P-55 ...... 1 D and E P-55.2 ...... 1 F P-56 ...... 1 All P-57 ...... 1 All *P-58 ...... 2 All P-59 ...... 1 All P-60 ...... 1 D and E P-60.2 ...... 1 F P-61 thru P-71 ...... 1 All Emergency Procedures E-i ...... C All *E-ii...... 2 All E-1 ...... 1 All E-2 ...... C All E-3 and E-4...... 1 All E-5 thru E-7 ...... C All *E-8 and E-9...... 2 All E-10 and E-11...... C All *E-12 thru E-15 ...... 2 All E-16 and E-17...... 1 All E-18 ...... C All E-19 thru E-21 ...... 1 All E-22 and E-23...... C All E-24 ...... 1 All E-25 ...... C Aircraft 45-002 thru 45-225 not modified by SB 45-55-6 E-25.1 ...... C Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6

Denotes pages presented in either U.S. or metric units. CL-126C Change 2 LOEP-4

Page Change Aircraft Affected E-26...... C Aircraft 45-002 thru 45-225 not modified by SB 45-55-6 E-26.1...... C Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 E-27...... 1 Aircraft 45-002 thru 45-225 not modified by SB 45-55-6 E-27.1...... 1 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 E-28 and E-29 ...... C All E-30...... 1 Aircraft 45-002 thru 45-225 not modified by SB 45-55-6 E-30.1...... 1 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 E-31...... C All *E-32...... 2 All E-33...... 1 All E-34...... C All E-35...... 1 All E-36 and E-37 ...... C All E-38...... 1 All E-39...... C All *E-40 and E-41 ...... 2 All Abnormal Procedures A-i ...... C All *A-ii thru A-iv...... 2 All A-1 thru A-5 ...... C All A-6 thru A-8 ...... 1 All A-9...... C All A-10...... 1 All *A-11 and A-12 ...... 2 All A-13 ...... 1 All *A-14...... 2 All A-15 thru A-18...... 1 All *A-19...... 2 All A-20 thru A-22...... 1 All *A-23...... 2 All A-24...... 1 All *A-25...... 2 All A-26...... 1 All *A-27...... 2 All A-28 and A-29 ...... 1 All *A-30...... 2 Aircraft 45-002 & on not modified by SB 45-72-1 *A-30.1...... 2 Aircraft 45-002 & on modified by SB 45-72-1SB 45-72-1

CL-126C LOEP-5 Change 2 Page Change Aircraft Affected *A-31 ...... 2 Aircraft 45-002 & on not modified by SB 45-72-1 *A-31.1 ...... 2 Aircraft 45-002 & on modified by SB 45-72-1 A-32 ...... 1 All *A-33 ...... 2 All A-34 ...... 1 All *A-35 ...... 2 All A-36 thru A-41 ...... 1 All *A-42 and A-43 ...... 2 All A-44 ...... 1 All *A-45 ...... 2 All A-46 thru A-49 ...... 1 All *A-50 thru A-53 ...... 2 All A-54 ...... 1 All *A-55 ...... 2 All *A-56 ...... 2 Aircraft 45-002 thru 45-225 not modified by SB 45-55-6 *A-56.1 ...... 2 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 *A-56A (Added)...... 2 Aircraft 45-002 thru 45-225 not modified by SB 45-55-6 *A-56A.1 (Added)...... 2 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 *A-57 ...... 2 All *A-57.1 (Deleted) ...... 2 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 A-58 thru A-60 ...... 1 All A-61 ...... C All A-62 ...... 1 Aircraft 45-002 thru 45-225 not modified by SB 45-55-6 *A-62.1 ...... 2 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 *A-63 ...... 2 Aircraft 45-002 thru 45-225 not modified by SB 45-55-6 *A-63.1 ...... 2 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 A-64 thru A-66 ...... 1 All *A-67 ...... 2 Aircraft 45-002 thru 45-225 not modified by SB 45-55-6 A-67.1 ...... 1 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 A-68 ...... 1 Aircraft 45-002 thru 45-225 not modified by SB 45-55-6 *A-68.1 ...... 2 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 A-69 and A-70 ...... 1 All *A-71 ...... 2 All

CL-126C Change 2 LOEP-6

Page Change Aircraft Affected A-72 and A-73 ...... 1 All *A-74...... 2 Aircraft 45-002 thru 45-225 not modified by SB 45-55-6 *A-74.1...... 2 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 A-75...... 1 All *A-76...... 2 Aircraft 45-002 thru 45-225 not modified by SB 45-55-6 *A-76.1...... 2 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 *A-77...... 2 Aircraft 45-002 thru 45-225 not modified by SB 45-55-6 *A-77.1...... 2 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 A-78...... 1 All A-79...... 1 Aircraft 45-002 thru 45-225 not modified by SB 45-55-6 A-79.1...... 1 Aircraft 45-226 & on, and prior aircraft modified by SB 45-55-6 A-80 thru A-84...... 1 All *A-85...... 2 All A-86...... 1 All A-87...... 1 All A-88...... 1 All *A-89...... 2 All A-90...... 1 All A-91...... 1 All *A-92...... 2 All A-93...... 1 All *A-94...... 2 All A-95 and A-96 ...... 1 All *A-97...... 2 All A-98...... 1 All A-99 and A-100 ...... 1 All A-101...... 1 All *A-102...... 2 All *A-103...... 2 All A-104 thru A-106...... 1 All *A-107...... 2 All

Advisory/Status

A/S-i and A/S-ii ...... 1 All A/S-1 and A/S-2 ...... C All A/S-3 and A/S-4 ...... 1 All *A/S-5 and A/S-6 ...... 2 All A/S-7 ...... C All *A/S-8 ...... 2 All Denotes pages presented in either U.S. or metric units. CL-126C LOEP-7 Change 2 Page Change Aircraft Affected A/S-9 and A/S-10...... 1 All A/S-11 and A/S-12...... C All A/S-13 and A/S-14...... 1 All *A/S-15...... 2 All A/S-16 thru A/S-22 ...... 1 All *A/S-23...... 2 All A/S-24 thru A/S-27 ...... 1 All

Supplemental Data *S-1 ...... 2 All S-2 thru S-5 ...... 1 All S-6 ...... 1 Aircraft 45-002 thru 45-169 without Altitude Compensated Oxygen Sys- tem S-6.1 ...... 1 Aircraft 45-170 & on, and prior aircraft with Altitude Compensated Oxygen System S-7 ...... 1 Aircraft 45-002 thru 45-169 without Altitude Compensated Oxygen Sys- tem S-7.1 ...... 1 Aircraft 45-170 & on, and prior aircraft with Altitude Compensated Oxygen System S-8 ...... C All *S-9 and S-10 ...... 2 All S-11 ...... 1 All *S-12 ...... 2 All S-13 ...... 1 All *S-14 ...... 2 All S-15 ...... 1 All *S-16 ...... 2 All S-17 ...... 1 All *S-18 ...... 2 All S-19 ...... 1 All *S-20 ...... 2 All S-21 ...... 1 All *S-22 ...... 2 All S-23 ...... 1 All *S-24 thru S-32 ...... 2 All *S-33 (Added) ...... 2 All

CL-126C Change 2 LOEP-8 LOG OF REVISIONS

REVISION INCORPORATED DESCRIPTION DATE NO. BY

Reissue C Harmonizes with October 2008 Reissue of the AFM dated 10-9-2008.

Change 1 Harmonizes with June 2009 Change 1 of the AFM dated 6-11-2009.

Change 2 Harmonizes with March 2010 Change 2 of the AFM dated 3-4-2010.

CL-126C Change 2 LOR LOG OF TEMPORARY CHECKLIST CHANGES

This list is intended to assist the flight crew in determining the applicable temporary checklist changes for Learjet 45 aircraft. It is the responsibility of the aircraft owner and operator to maintain their CREW CHECKLIST & QUICK REFERENCE HANDBOOK with the temporary changes applicable to their aircraft. Insert this list after the LOG OF REVISIONS page.

TCL # Section Dated or Page Description Status

2009-05 E-20 Engine Failure During Approach Removed by 3-6-2009 Chg 1.

CL-126C Change 2 TCL-1 IMPORTANT TO THE OWNER OF THIS CHECKLIST

A yearly checklist revision service is available. The cost of revision service will be billed at current pricing levels. If you wish to receive the checklist revision service, please fill in the blanks below and mail to the address at the bottom of the page.

Aircraft Serial Number 45-

Mailing Address for Revision Service:

Name

Address

Business Phone No

Fax No

E-Mail Address

Mail To: Learjet Inc. P.O. Box 7707 Wichita, Kansas 67277-7707 Attn: Document Control Center (MS#71)

CL-126C TECHNICAL PUBLICATION USER COMMENT SHEET We welcome your comments, criticism, and suggestions concerning any Bombardier-Learjet publication. The action taken, as the result of your comments, will be noted below and a copy returned to you. This form may be returned in any of the following formats: - E-mailed to [email protected] (preferred) - Mailed to Bombardier-Learjet Technical Publications - Faxed to (316) 946-2002

Today’s Date Aircraft Model 45 S/N

Checklist Procedure

Page Number

Comment/Suggestion

Name

Address

Business Phone FAX

E-Mail

Action Taken

Mail To: Learjet Inc. P.O. Box 7707 Wichita, Kansas 67277-7707 Attn: Manager Technical Publications (MS#53)

CL-126C IMPORTANT NOTICE

Applicability: This checklist is applicable to Learjet 45 aircraft serial number 45-002 thru 45-2000.

Use of Checklist: These are suggested procedures only and in no way su- persede current procedures outlined in the FAA Approved Airplane Flight Manual and any revisions thereto. In the event of conflict, the FAA Approved Airplane Flight Manual takes precedence.

This checklist has been designed so that pages not applicable to a particular aircraft may be removed from the checklist. Removing such pages allows the operator to construct a checklist applicable to a particular aircraft.

Each text page of this checklist contains an effectivity block with serializations or effectivity codes located at the bottom of the page. To remove pages not applicable to your aircraft, examine the effectivity block to determine if the page is applicable to your aircraft. If the page is not applicable, remove the page from the checklist and discard. If the page is applicable, retain the page.

The performance effectivity codes used in this checklist are identical to the effectivity codes used in the basic airplane flight manual. For an explanation of the effectivity codes, refer to FLIGHT MANUAL PERFORMANCE DATA in the AFM introduction. NOTE Be sure to examine each page of the checklist to ensure that all pages not applicable to your aircraft are removed.

CL-126C i

CHECKLIST CONVENTIONS

EICAS (Engine Indicating/Crew Alerting System)

EICAS indications will be presented by all capital letters within their appropriate display fields.

EI CAS

System Page

System Page Menu

EICAS Display

Switch Indications

Normal switch condition will be assumed not illuminated on the “quiet-dark- normal” instrument panel and pedestal. “Quiet-dark-normal” is defined as day, VMC normal system operation in cruise flight. Switch legends will be presented in all capital letters (e.g. PACK Switch). Illuminated switch indications will also be noted in all capital letters (e.g. PACK ... OFF). Switch conditions that are not illuminated will be lead capped (e.g. PACK ... On), unless they are part of a longer description.

Voice and Crew Warning Panel (CWP) Annunciations

Voice annunciations will be preceded by an audio symbol (headings only) and in all capital letters within quotes. CWP annunciations will be presented by all capital letters and are usually accompanied by a CAS.

Symbols and “If” Statements

Checklist items marked with this symbol (◆) may be used for preflight during intermediate stops where both engines are shut down provided certain criteria are met. The symbol applies thru the Before Starting En- gines checklist. Refer to Section II Introduction in the FAA Approved Air- plane Flight Manual for list of criteria.

CL-126C hange 1 ii Change 1 Symbols and “If” Statements (Cont) NOTE

Because this checklist is abbreviated from the AFM, some items marked as through flight appear to entail more than the AFM itself. Only those items marked as through flight in the AFM need be accomplished.

Certain procedures are dependent on prescribed conditions. These conditions are presented in bold as independent “If” statements. “If” statements preceded by a symbol (e.g. ●, ■ or S) indicate more than one condition for that step. Other conditions for that step will be indicated by repeating that step and symbol.

Steps beginning with an “If” statement not preceded by a special symbol are accomplished only if the statement is true. There is no alternate condition(s) to be addressed at this level of the procedure. These statements are often italicized or boldfaced to distinguish them from the required action. If the statement is false, proceed to the next step in the sequence.Procedures completed at any substep level will be noted. (e.g. This checklist is complete.)

Procedures not completed at a substep level will direct the user to the next applicable step. (e.g. Go to step 3.) The last procedure of any substep will either state “This checklist is complete.” or “Go to step #.”, or refer the user to another appropriate procedure.

Cross References

References to data are made to the title (boldface) and page number (or Tab number) where the data can be found. Tab number references that exist in the Emergency and Abnormal Procedures sections will be presented on a red and amber background respectively (e.g., . . .refer to Emergency Evacuation, Tab 7 ). In this example, the red background indicates the Emergency Evacuation procedure can be found in the Emergency Proce- dures.

CL-126C iii

Circuit Breakers

Many procedures involve manipulating circuit breakers. The following criteria should be followed during “Circuit Breaker” steps.

- Circuit breakers that are “Set” should be checked for that normal condition. If the circuit breaker is not “Set”, it may be reset only once. If the circuit breaker opens again, do not reset. - Circuit breakers that “Pull” should only be pulled and not reset. - Circuit breakers that “Pull and Reset” should be pulled, delayed for several seconds, and reset only once.

Allow sufficient cooling time for circuit breakers that are “Reset” or cycled through a “Pull and Reset.”

CL-126C iv NORMAL PROCEDURES CONTENTS

Exterior Preflight...... N-2 Cabin Preflight...... N-5 Before Starting Engines ...... N-6 Starting Engines...... N-9 Before Taxi ...... N-10 Taxi & Before Takeoff ...... N-11 Runway Lineup...... N-12 After Takeoff ...... N-12 Climb ...... N-13 Cruise...... N-13 Descent ...... N-13 Approach...... N-14 Before Landing...... N-15 Go Around...... N-15 Landing ...... N-15 After Landing/Clearing Runway...... N-16 Shutdown ...... N-16 Quick Turn-Around ...... N-17 One Engine Taxi...... N-19

EFFECTIVITY CL-126C All N-1 Exterior Preflight

1 4 6 2

22 7

21 8

20 19 9 18 11 10 16

17 13

16 14

EFFECTIVITY CL-126C N-2 All ◆ During Exterior Preflight, check all vents clear, check access doors for security, & all aircraft surfaces for condition.

1 Left Pitot-Static Probe, Stall Vane & Ice Detect Probe . . . . Check 2 Right & Standby Pitot-Static Probes, Stall Vane, & Static Air Temperature Probe ...... Check

3 ◆ Controls Lock...... Remove & Stow Gear ...... DN L & R BATT ...... On EMER BATT ...... EMER APU MASTER (if installed) ...... ON Fuel Quantities ...... Check AUX HYD...... ON SUMRY Page B-ACUM Pressure ...... 2610-3600 psi AUX HYD...... Off EMERGENCY/PARKING BRAKE ...... Set SUMRY Page B-ACUM Pressure ...... ≥ 1200 psi AUX HYD...... ON AUX HYD...... Off Exterior Lights ...... Check

12 FILTER & RESERVOIR Lights (MAIN, AUX, ADD or OVER) (Hyd Service Pnl)...... Not Illuminated & Secure

14 APU (if installed) ...... Check Oil Level 3 APU MASTER (if installed) ...... Off EMER BATT ...... OFF L & R BATT ...... OFF

4 Windshield ...... Check Nose Gear Strut. . Extended a minimum of one-half inch (13mm) Rotating Disc and Linkage...... Condition & Lubrication ◆ Gear & Wheel Well, Nose Compartment Doors, Wheel & Tire ...... Check

EFFECTIVITY CL-126C All N-3 Ground Wire ...... Disconnected 5 Radome & Radome Erosion Shoe ...... Condition 6 Windshield, Oxygen Discharge Disc & Service Door, Nose Compartment Doors, Wing Inspection Light & Lens, Standby Pitot & Static Drains . . . . Check & Secure

7 ◆ Emergency Exit, Upper Antennas & Dorsal Inlets, Upper Gravity Fueling Door, Right Engine Inlet & Fan, Right Generator & Alternator Scoops, Lower Antennas, Landing Light Fairing & Lens Condition, Fuel Drains & Access Door, Toilet Servicing Door, Right Main Gear ...... Check Oxygen Servicing Door (if applicable) ...... Secure 8 Right Wing ...... Check 9 Right Nav Light/Lens & Static Wicks...... Condition Ground Wire ...... Disconnected

10 Right Aileron, Spoiler & Flap...... Condition 11 Right Brakes & Brake Wear Indicators ...... Condition Right Engine Oil ...... Check Level

12 ◆ Single-Point Fueling & Fuel Quantity Panel Access Doors ...... Secure

13 ◆ Right Engine Exhaust ...... Clear ◆ Right Thrust Reverser...... Condition & Completely Stowed

14 Tailcone Interior, Engine Fire Extinguisher Discs, Right VOR/LOC Antenna, APU Exhaust (if installed) . . . . . Check

15 ◆ Vertical Stabilizer, Rudder, Horizontal Stabilizer, Elevator, Delta Fins & Logo Lights (if installed), Static Wicks, Beacon/Strobe Light & Lens ...... Check ◆ Tailstand ...... Removed

16 Battery Vents, APU Inlet (if installed) ...... Clear Left VOR/LOC Antenna ...... Condition ◆ Baggage Heat, Baggage Door ...... On (if applicable) & Closed

17 ◆ Left Engine Exhaust ...... Clear ◆ Left Thrust Reverser ...... Condition & Completely Stowed EFFECTIVITY CL-126C N-4 All Left Engine Oil ...... Check Level 18 Left Brakes & Brake Wear Indicators...... Condition

19 Left Spoiler, Flap & Aileron ...... Condition 20 Left Nav Light/Lens & Static Wicks ...... Condition Ground Wire ...... Disconnected

21 Left Wing ...... Check 22 ◆ Fuel Drains & Access Door, Left Main Gear, Left Engine Inlet & Fan, Left Generator & Alternator Scoops, Upper Fuselage, Fuel Vent Inlet ...... Check Oxygen System Discharge Indicator (if applicable)...... Check

Cabin Preflight ◆ 1. Cabin Furnishings ...... Secure ◆ 2. Emergency Exit ...... Aisle Clear/Security Pin Removed ◆ 3. Lavatory Door ...... Open & Access Unobstructed

EFFECTIVITY CL-126C All N-5 Before Starting Engines All switches not illuminated, except as noted. ◆ 1. Seats, Safety Belts, & Shoulder Harnesses...... Secure & Adjust 2. Crew Oxygen Masks (including hoses & MIC cords) & Smoke Goggles ...... Check 3. L & R Circuit Breakers ...... Set ◆ 4. Gear...... DN ◆ 5. Electrical System: a. L & R BATT...... On, Simultaneously b. EMER BATT ...... EMER c. L & R AV MSTR...... On (OFF for BATT starts) d. L & R NON-ESS...... As Desired (OFF for BATT starts) e. L & R GEN...... OFF f. EXT PWR (if desired)...... Connect, AVAIL, then EXT PWR g. APU (if installed)...... As Desired (1) BCN/STROBE ...... BCN (2) APU MASTER ...... ON (3) FIRE DET ...... Check (4) APU START/STOP ...... START (5) EXT PWR (if applicable)...... AVAIL and Disconnect (6) APU GEN ...... ON (7) APU BLEED ...... ON (8) PACK ...... On h. BUS-TIE ...... Closed for EXT PWR or APU Starts (Open for BATT starts) 6. L & R CREW LIGHTS...... Set 7. L & R Audio Panels...... Set 8. L & R Rudder Pedals ...... Adjust

EFFECTIVITY CL-126C N-6 All 9. ELEV DISC Handle & ROLL DISC Lever ...... Check Stowed 10. Flight Controls ...... Check 11. LTS ...... Test 12. DU & REVERSION Panels ...... NORM ◆ 13. EICAS...... Check a. Engine Instruments ...... Check b. Fuel Quantity...... Check c. Fuel TOTALIZER RESET (FUEL Page) ...... Zero d. CAS Indications...... Check e. SUMRY Page ...... Select 14. L & R PROBES, L & R WSHLD (ANTI-ICE panel) ...... OFF 15. Aircraft Lighting...... Off ◆ 16. GEAR/HYD Panel: a. AUX HYD ...... ON b. SUMRY Page B-ACUM Pressure...... 2610-3600 psi c. EMERGENCY/PARKING BRAKE...... Set d. AUX HYD ...... Off 17. PAX OXYGEN/PRESSURIZATION Panels...... Checked a. PACK...... OFF (On, if APU BLEED — ON) ◆ b. LDG ALT ...... Set Destination 18. ENVIRONMENTAL CONTROL Panel...... Checked & Set ◆ 19. RUD BOOST ...... On 20. SYSTEM TEST Panel...... Test ◆ a. FIRE DET...... Check, Unless Accomplished During APU Start If EXT PWR or APU is not used, start one engine & continue checks with the following switches On: • L or R GEN ...... On • L & R AV MSTR...... On b. GEAR, FLAPS, ADC, STALL, ANTI-ICE, GPWS ...... Check

EFFECTIVITY CL-126C All N-7 21. Master CAUT ...... Inhibit ◆ 22. Trim System ...... Check ◆ 23. FUEL Panel...... Check 24. L & R ENGINE Panels: a. L & R ENG CMPTR...... ON b. ENG SYNC...... OFF ◆ 25. Altimeters...... Set Pilot, Copilot & Standby ◆ 26. Standby Instruments...... Uncaged & Checked ◆ 27. FMS ...... Set

◆ 28. Takeoff Data (V1, VR, V2, TO Pitch, Distance) ...... Computed & Speeds Set ◆ 29. Avionics...... Set

EFFECTIVITY CL-126C N-8 All Starting Engines 1. Cabin Door ...... Closed & Latched 2. SUMRY Page ELEC VOLTS...... Check - Ni-Cad — 23 VDC or Lead Acid — 24 VDC Minimum 3. BCN/STROBE ...... BCN 4. EMERGENCY/PARKING BRAKE...... Set 5. Thrust Lever(s) ...... IDLE 6. Engine ...... Start 7. Engine Instruments...... Check 8. SUMRY Page HYD - MAIN Pressure ...... 2210-3600 psi 9. Other Engine ...... Start 10. EMER LIGHTS ..... ON, Check EMER Lights Illuminated, then ARM 11. EXT PWR (if applicable)...... AVAIL & Disconnect 12. PACK ...... OFF (On, if APU BLEED — ON) 13. Anti-Ice System ...... Check & As Required 14. APU BLEED (if installed) ...... Off 15. PACK ...... On 16. Bleed Air System (first flight of day)...... Check 17. APU BLEED (if installed) ...... As Required 18. EMER PRESS ...... Check

EFFECTIVITY CL-126C All N-9 Before Taxi 1. Circuit Breakers ...... Set 2. VOLTS & AMPS ...... Check 3. Manual Mode Governor ...... Checked 4. L & R WSHLD...... On 5. Spoilers...... Check a. SPOILER...... EXT, Check Equal Rate & Extension b. SPOILER...... ARM, Check Retracted 6. FLAPS ...... Set 8° or 20° 7. Flight Controls...... Check a. Rudder Boost ...... Verify Green RB 8. EICAS ...... Check 9. Passengers Briefed/Cabin Check ...... Complete 10. Aircraft Lighting...... On, As Required 11. NO SMOKING BELTS ...... On 12. NOSE STEER...... ON 13. SUMRY Page B-ACUM Pressure ...... 2610-3600 psi 14. EMERGENCY/PARKING BRAKE...... Release

EFFECTIVITY CL-126C N-10 All Taxi & Before Takeoff 1. Brakes & Nose Wheel Steering ...... Check 2. Flight Instruments ...... Checked 3. Thrust Reversers ...... Check

4. Engine Instruments & N1 Bugs...... Check

5. Takeoff Data (V1, VR, V2, TO Pitch, Distance)...... Check 6. Nav Equipment ...... Check 7. FLAPS ...... 8° or 20°, Check Indication 8. Trims ...... Set PIT, AIL, & RUD for Takeoff 9. Crew Takeoff Briefing...... Complete 10. HI FLOW...... Off 11. Radar...... As Required 12. WING/STAB, L & R NAC (ANTI-ICE panel)...... As Required 13. APU (if installed)...... Shut Down a. APU BLEED...... Off b. APU START/STOP...... Off c. APU MASTER (after 30-second delay)...... Off d. FMS Fuel Quantity ...... Update

Takeoff Pitch Trim Setting CENTER-OF-GRAVITY — % MAC 1 to 10 12 14 16 18 20 22 to aft limit 8.7 8.1 7.6 7.0 6.4 5.9 5.3

EFFECTIVITY CL-126C All N-11 Runway Lineup 1. Transponder ...... TA/RA 2. L & R PROBES...... On 3. RECOG, L & R LDG-TAXI Lights...... On 4. BCN/STROBE...... STROBE 5. AUX HYD ...... ON 6. APR ...... ARM 7. EICAS/SUMRY or FLT Page...... Check

After Takeoff 1. Gear ...... UP

2. FLAPS ...... UP at V2 + 25 3. Yaw Damper...... As Required 4. SPOILER ...... RET 5. Anti-Ice Systems...... As Required a. Thrust Levers ...... ≤ MCT b. WING/STAB ...... ON c. L & R NAC ...... ON 6. L & R LDG-TAXI Lights ...... OFF 7. L & R IGN ...... Off 8. APR ...... Off

EFFECTIVITY CL-126C N-12 All Climb 10,000 Ft Checks: 1. NO SMOKING BELTS ...... As Required 2. Pressurization...... Check & Normal Transition Altitude (or 18,000 Ft) Checks: 3. Altimeters (x3) ...... Set to 29.92" Hg (1013 hPa) 4. RECOG Light...... OFF 5. Oxygen System ...... Checked

Cruise (As Required By Regulation) 1. Pressurization...... Check & Normal 2. Fuel Management...... As Required 3. Engine Instruments...... Check 4. Other Systems...... Monitor

Descent 1. Pressurization...... LDG ALT Set 2. Anti-Ice Systems...... As Required a. Thrust Levers ...... ≤ MCT b. WING/STAB ...... ON c. L & R NAC...... ON Transition Level (or FL 180) Checks: 3. Altimeters (x3) ...... Set 4. RECOG Light...... On 5. Passengers Briefed/Cabin Check...... Complete 6. NO SMOKING BELTS ...... On 7. Fuel Quantities & Balance ...... Check

EFFECTIVITY CL-126C All N-13 Approach 1. Landing Data (VREF, VAPP, Distance)...... Computed & Speeds Set 2. Approach Setup & Crew Briefing ...... Complete 3. HI FLOW ...... Off 4. ENG SYNC ...... OFF Landing Speeds Below 4000 Feet WEIGHT — 1000 LB SPEED 14 15 16 17 18 19 19.2 20 20.5

VREF 106 110 113 116 119 122 123 125 126

VAPP 115 119 122 125 129 132 132 134 136

Landing Distances °F -4 14 32 50 68 86 104 TEMP °C-20-100 10203040 WT — LB LANDING DISTANCE — FEET 19,200 2410 2480 2550 2620 2700 2770 2840 19,000 2390 2460 2530 2600 2680 2750 2820 18,000 2310 2380 2440 2510 2580 2650 2710 17,000 2230 2290 2350 2410 2470 2540 2600 16,000 2160 2220 2270 2320 2380 2430 2490

SEA LEVEL SEA 15,000 2080 2140 2190 2240 2290 2340 2400 14,000 2000 2050 2100 2150 2200 2240 2290 19,200 2550 2630 2710 2790 2870 2950 3030 19,000 2530 2610 2690 2760 2840 2920 3000 18,000 2440 2520 2590 2660 2730 2810 2880 17,000 2350 2420 2480 2550 2620 2690 2760

2000 ft 16,000 2270 2330 2390 2450 2510 2570 2640 15,000 2190 2250 2300 2360 2410 2470 2520 14,000 2100 2150 2200 2260 2310 2360 2410 19,200 2710 2800 2880 2970 3060 3150 3240 19,000 2690 2770 2860 2950 3030 3120 3210 18,000 2590 2670 2750 2830 2910 2990 3080 17,000 2490 2560 2640 2710 2790 2860 2940 2460 2520 4000 ft 16,000 2390 2590 2660 2730 2800 15,000 2310 2370 2430 2490 2550 2610 2670 14,000 2210 2270 2320 2380 2440 2490 2550

These speeds & distances were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed.

Change 1 EFFECTIVITYEFFECTIVITY 45-002All & on CL-126C N-14 not modified by SB 45-11-4 Change 1 Approach 1. Landing Data (VREF, VAPP, Distance)...... Computed & Speeds Set 2. Approach Setup & Crew Briefing ...... Complete 3. HI FLOW ...... Off 4. ENG SYNC ...... OFF

Landing Speeds Below 4000 Feet WEIGHT — 1000 LB SPEED 14 15 16 17 18 19 19.2 20 21 21.5

VREF 106 110 113 116 119 122 123 125 127 128

VAPP 115 119 122 125 129 132 132 134 137 138

4000 ft 16,000 2390 2460 2520 2590 2660 2730 2800 15,000 2310 2370 2430 2490 2550 2610 2670 14,000 2210 2270 2320 2380 2440 2490 2550

These speeds & distances were determined for dry runway, zero wind, zero runway gradient, anti-ice off, anti-skid on, & autospoilers deployed.

EFFECTIVITYEFFECTIVITY 45-002All & on CL-126C N-14.1 modified by SB 45-11-4 Change 1 Before Landing 1. SPOILER ...... ARM 2. FLAPS ...... 8° or 20° 3. AUX HYD...... ON 4. Gear ...... DN 5. L & R LDG-TAXI Lights...... On As Required 6. FLAPS ...... DN, Check Indication 7. EICAS/SUMRY or FLT Page...... Check

Go Around 1. Autopilot...... Disengaged 2. Thrust Lever(s) ...... T/O or As Required 3. FLAPS ...... 8° 4. Gear...... UP

5. Climb at VAPP.

6. When clear of obstacles, accelerate to VAPP + 20 & retract flaps. 7. Spoilers...... RET

Landing 1. Brakes...... As Required 2. Spoilers...... Verify Extended 3. If spoilers are not extended automatically, SPOILER ...... EXT 4. Thrust Reversers ...... As Desired

EFFECTIVITY CL-126C All N-15 After Landing/Clearing Runway 1. Transponder ...... STANDBY 2. L & R PROBES ...... OFF 3. WING/STAB, L & R NAC...... As Required 4. Lights ...... As Desired 5. SPOILER ...... RET 6. FLAPS ...... UP or Set for Next Takeoff 7. Radar ...... Off 8. APU (if installed) ...... As Desired a. APU MASTER ...... ON b. APU START/STOP ...... START c. APU GEN ...... ON d. APU BLEED ...... ON 9. SUMRY Page B-ACUM Pressure ...... 2610-3600 psi 10. AUX HYD ...... Off 11. Thrust Lever...... CUTOFF (Optional)

Shutdown 1. EMERGENCY/PARKING BRAKE and/or Chocks...... Set 2. Standby Attitude Indicator...... Cage 3. L & R AV MSTR ...... OFF 4. L & R WSHLD ...... OFF 5. Anti-Ice Systems ...... Off 6. EMER LIGHTS...... OFF 7. NOSE STEER ...... Off 8. Thrust Lever(s)...... CUTOFF 9. PACK...... OFF 10. FMS ...... OFF 11. Instrument Lights ...... As Desired

Change 2 EFFECTIVITY N-16 All CL-126C Change 2 12. APU (if installed)...... Shut Down a. APU BLEED...... Off b. APU START/STOP...... Off c. APU MASTER (after 30-second delay)...... Off 13. BCN/STROBE ...... OFF 14. EMER BATT ...... OFF 15. L & R BATT...... OFF 16. Controls Lock...... Install

Quick Turn-Around (One or No Engine Shutdown) Before Taxi 1. LDG ALT...... Set Destination 2. Fuel Quantities ...... Checked & Balanced 3. FMS ...... Set

4. Takeoff Data (V1, VR, V2, TO Pitch, Distance)...... Computed & Speeds Set 5. Avionics ...... Set 6. Cabin Door ...... Closed & Latched 7. Engine ...... Start (Both Engines Running)

8. Engine Instruments & N1 Bugs...... Check 9. PACK ...... On 10. Circuit Breakers ...... Set 11. L & R AV MSTR...... On 12. L & R WSHLD...... On 13. SPOILER ...... ARM 14. FLAPS ...... Set 8° or 20°, Check Indication 15. RUD BOOST ...... On 16. Flight Controls ...... Check 17. Passengers Briefed/Cabin Check...... Complete 18. NO SMOKING BELTS ...... On EFFECTIVITY CL-126C All N-17 Change 2 Taxi 1. Flight Instruments ...... Check 2. FLAPS ...... Set 8° or 20°, Check Indication 3. Trims ...... Set PIT, AIL & RUD for Takeoff 4. Crew Takeoff Briefing...... Complete 5. HI FLOW ...... Off 6. Radar ...... As Required 7. WING/STAB, L & R NAC (ANTI-ICE panel) ...... As Required 8. APU (if installed) ...... Shut Down a. APU BLEED ...... Off b. APU START/STOP ...... Off c. APU MASTER (after 30-second delay) ...... Off d. FMS Fuel Quantity ...... Update 9. Go to Runway Lineup checklist, page N-12.

EFFECTIVITY N-18 All CL-126C Change 2 One Engine Taxi 1. Accomplish steps 1 thru 8 of the Starting Engines checklist, Page N-9. 2. PACK ...... On 3. Circuit Breakers ...... Set 4. VOLTS & AMPS...... Check 5. Spoilers...... Check a. SPOILER...... EXT, Check Equal Rate & Extension b. SPOILER...... ARM, Check Retracted 6. FLAPS ...... Set 8° or 20° 7. Flight Controls ...... Check a. Rudder Boost ...... Verify Green RB 8. EICAS...... Check 9. Passengers Briefed/Cabin Check...... Complete 10. Aircraft Lighting...... On, As Required 11. NO SMOKING BELTS ...... On 12. NOSE STEER ...... ON 13. SUMRY Page B-ACUM Pressure ...... 2610-3600 psi 14. EMER LIGHTS ..... ON, Check EMER Lights Illuminated, then ARM 15. EXT PWR (if applicable)...... AVAIL & Disconnect When Ready to Taxi: 16. EMERGENCY/PARKING BRAKE...... Release 17. Brakes & Nose Wheel Steering ...... Check

18. Flight Instruments ...... Checked TAXI ONE ENGINE

19. Takeoff Data (V1, VR, V2, TO Pitch, Distance)...... Check 20. Nav Equipment ...... Check 21. FLAPS ...... 8° or 20°, Check Indication

EFFECTIVITY CL-126C All N-19 22. Trims ...... Set PIT, AIL, & RUD for Takeoff Takeoff Pitch Trim Setting CENTER-OF-GRAVITY — % MAC 1 to 10 12 14 16 18 20 22 to aft limit 8.7 8.1 7.6 7.0 6.4 5.9 5.3 23. HI FLOW ...... Off 24. PACK...... OFF When Ready to Start 2nd Engine: 25. SUMRY Page ELEC VOLTS ...... Check 26. Thrust Lever...... IDLE 27. Engine...... Start 28. VOLTS & AMPS ...... Check 29. Manual Mode Governor ...... Checked 30. L & R WSHLD...... On 31. Anti-Ice System...... Check & As Required 32. APU (if installed) ...... Shut Down a. APU BLEED ...... Off b. APU START/STOP ...... Off c. APU MASTER (after 30-second delay) ...... Off d. FMS Fuel Quantity ...... Update 33. PACK...... On 34. Bleed Air System (first flight of day)...... Check 35. EMER PRESS ...... Check 36. Thrust Reversers ...... Check

37. Engine Instruments & N1 Bugs ...... Check 38. Radar ...... As Required 39. Crew Takeoff Briefing...... Complete 40. WING/STAB, L & R NAC (ANTI-ICE panel) ...... As Required 41. Go to Runway Lineup checklist, Page N-12.

EFFECTIVITY CL-126C N-20 All CHECKLIST (US) 45

AIRCRAFT 45-002 THRU 45-2000

EFFECTIVITY SB NUMBER EQUIPPED WITH CODE & UNITS

CHECKLIST ✔ SB 45-72- 1 YES TFE731-20BR-1B Upgrade F ✔ Increased MTOW to 21500 LB

CHECKLIST TFE731-20BR-1B Upgrade SB 45-11- 4 YES E ✔ Increased MTOW to 21,500 LB

CHECKLIST NO TFE731-20BR-1B Upgrade D Increased MTOW to 21,500 LB

Use the flowchart above to determine which performance code applies to a specific aircraft. Click in the effectivity code box to open the desired manual. FlightSafety EMERGENCY PROCEDURES

This section contains those operating procedures requiring the use of special systems and/or regular systems in order to protect the occupants

and the aircraft from harm during a critical situation requiring immediate EMERGENCY response. The procedures located in this section supplement normal procedures when an emergency condition exists. Use of normal procedures should be continued when applicable. Sound judgement as well as thorough knowledge of the aircraft, its characteristics, and the flight manual procedures are essential in the handling of any emergency situation. In addition to the outlined items in the emergency procedure, the following steps are considered part of all emergency situations: • Maintain Airplane Control • Analyze the Situation • Take Proper Action Memory Items Procedures in this checklist emphasized by enclosure in a box such as this should be memorized for crew accomplishment without reference to the procedure.

EFFECTIVITY CL-126C All E-i Emergency EICAS Index

CAS or (EI) Message Tab APU FIRE 1 EMERGENCY L BATT OVHT 4 R BATT OVHT 4 L BLEED AIR LEAK 10 R BLEED AIR LEAK 10 LR BLEED AIR LEAK 10 CABIN ALTITUDE 7 DEP (EI) 19 EMER/PARK BRK 18 L ENG PYLON OVHT 10 R ENG PYLON OVHT 10 LR ENG PYLON OVHT 10 ENTRY DOOR 4 FIRE (EI) 7 L FUEL PRESS LOW 13 R FUEL PRESS LOW 13 LR FUEL PRESS LOW 13 GEAR 16 LR GEN FAIL 4 NORM BRK FAIL 16 L OIL PRESS LOW 8 R OIL PRESS LOW 8 PIT TRIM BIAS 18 PIT TRIM MSCMP 18 L REV UNSAFE (CWP) 19 R REV UNSAFE (CWP) 19 SPOILERS EXT 18 STAB OVHT 1 TAKEOFF TRIM 18 UNL (EI) 19 WING OVHT 1 WING/STAB LEAK 1

EFFECTIVITY All CL-126C E-ii Change 2

Change 2 EMERGENCY PROCEDURES TAB

ANTI-ICING 1 STAB OVHT 2 WING OVHT 1 WING/STAB LEAK 3 AUXILIARY POWER UNIT (APU) APU FIRE 4 CABIN/COCKPIT FIRE & SMOKE 2 5 DOOR 6 ENTRY DOOR ELECTRICAL 4 7 BATT OVHT 8 LR GEN FAIL Loss of Both Generators and Both Main Batteries 6 9 EMERGENCY DESCENT “CABIN ALTITUDE” Voice Activates 10 CABIN ALTITUDE 11 EMERGENCY EVACUATION 7 ENGINE 12 “ENGINE FIRE” Voice Activates 13 Engine FIRE OIL PRESS LOW 14 8 Engine Failure 15 Immediate Engine Airstart 9 ENVIRONMENTAL/PRESSURIZATION 16 10 BLEED AIR LEAK 17 ENG PYLON OVHT TAB EFFECTIVITY Change 1 CL-126C E-1 Change 1 All TAB FLIGHT CONTROLS PIT TRIM BIAS 2 PIT TRIM MSCMP 10 3 SPOILERS EXT TAKEOFF TRIM 4 Aileron Control Jam 11 5 Elevator Control Jam Pitch Axis Uncommanded Motion 6 “OVERSPEED” Voice Activates Recovery from Inadvertent Overspeed 7 12 Roll or Yaw Axis Uncommanded Motion 8 Rudder Control Jam FUEL 9 FUEL PRESS LOW 10 INSTRUMENTS/AVIONICS Multi-Function Display (MFD) Annunciations 11 13 HDG FAIL 12 HDG TEST RA NO BRG 13 TERR TEST 14 Primary Flight Display (PFD) Annunciations AP 15 ATT FAIL 14 16 HDG FAIL WIND SHR 17 PULL UP 15 RA FAIL

TAB EFFECTIVITY CL-126C E-2 All LANDING GEAR/BRAKES TAB EMER/PARK BRK “GEAR” Voice Activates 1 GEAR 2 “BRAKES FAIL” Voice Activates NORM BRK FAIL16 3 Emergency Braking 4 Nose Wheel Steering Malfunction LANDINGS 5 Ditching 6 Forced Landing — Both Engines Inoperative 17 STALL 7 “STALL” Voice Activates 8 TAKEOFFS Aborted Takeoff 9 Takeoff “CONFIGURATION” Voice Activates 18 10 EMER/PARK BRK PIT TRIM BIAS 11 PIT TRIM MSCMP 12 SPOILERS EXT TAKEOFF TRIM 13 UNL or DEP (EI) THRUST REVERSER 14

“LEFT” or “RIGHT REVERSER UNSAFE” Voice Activates 15 L REV UNSAFE (CWP) 19 R REV UNSAFE (CWP) 16 UNL or DEP (EI) 17 1 TAB EFFECTIVITY Change 1 CL-126C E-3 Change 1 All STAB OVHT STAB STAB OVHT OVHT 2 1. WING/STAB ...... Off 2. Fly out of icing conditions. 3 3. L & R WING/STAB HT Circuit Breakers (respective ANTI-ICE group)...... Pull 4 If approach & landing must be made with any ice or suspected ice: 5 4. Refer to Wing and Stabilizer Heat Failure Landing, Tab 40 .

6 WING OVHT WING WING OVHT OVHT 7 1. WING/STAB ...... Off 2. Fly out of icing conditions. 8 3. L & R WING/STAB HT Circuit Breakers (respective ANTI-ICE group)...... Pull 9 If approach & landing must be made with any ice or suspected ice: 10 4. Refer to Wing and Stabilizer Heat Failure Landing, Tab 40 .

11 WING/ WING/STABWING/STAB LEAK LEAK STAB LEAK 12 1. WING/STAB ...... Off 2. Fly out of icing conditions. 13 3. L & R WING/STAB HT Circuit Breakers (respective ANTI-ICE group)...... Pull 14 If approach & landing must be made with any ice or suspected ice: 15 4. Refer to Wing and Stabilizer Heat Failure Landing, Tab 40 .

EFFECTIVITY Change 1 CL-126C E-4 All Change 1 APUAPU FIREFIRE FIRE PUSH On the ground: 1

1. APU FIRE ...... FIRE PUSH 2 2. APU MASTER ...... Off 3 3. Stop the aircraft. 4. EMERGENCY/PARKING BRAKE...... Set 4 5. Thrust Levers ...... CUTOFF 5 6. EMER LIGHTS ...... ON 7. EMER BATT, L & R BATT ...... OFF 6 8. Evacuate the aircraft: 7 a. Cabin Entry Door ...... Open & Exit b. Aft Emergency Exit...... Open & Exit 8

In flight: 9

1. APU FIRE ...... FIRE PUSH 10 2. R STBY (Fuel) ...... Off, Unless Required 3. Land as soon as possible. 11

2 EFFECTIVITY CL-126C All E-5 Cabin/Cockpit Fire, Smoke or Fumes

2 1. Crew Oxygen Masks ...... Don & 100%

3 2. Smoke Goggles...... Don 3. EMER DEPRESS ...... ON 4 4. Pilot & Copilot MIC/MASK...... MASK 5. Pilot & Copilot INPH...... INPH 5 Whether or not smoke has dissipated, if it cannot be visibly verified that the fire has been extinguished: 6 6. Cockpit Door/Curtain ...... Open 7 7. Land as soon as possible. 8. ●Source is not known: 8 a. Isolate source of smoke or fumes, and go to one of the following procedures: 9 - Bleed Air System, page E-6 - Normal Electrical System, page E-7 10 - Emergency Electrical System, page E-9 8. ●Source is known: 11 a. Extinguish fire using hand-held extinguisher or eliminate the source of smoke or fumes. 12 b. ■If fire is not extinguished: 13 (1) Land as soon as possible. (2) This checklist is complete. 14 b. ■If fire is extinguished and can visibly be verified: 15 (1) Land as soon as practical. (2) This checklist is complete. 16 Bleed Air System Is Suspected Source 17 1. R BLEED...... OFF 2. ●If smoke or fumes continue: a. R BLEED...... On b. L BLEED...... OFF

EFFECTIVITY CL-126C E-6 All c. ■If smoke or fumes continue: (1) L BLEED ...... On (2) Refer to one of the following procedures: 1 - Normal Electrical System, page E-7 2 - Emergency Electrical System, page E-9 c. ■If smoke or fumes are eliminated: 3 (1) Maintain 41,000 feet or below. Avoid flight in icing conditions. 4

(2) Land as soon as practical. 5 (3) This checklist is complete. 2. ●If smoke or fumes are eliminated: 6 a. Maintain 41,000 feet or below. Avoid flight in icing conditions. 7 b. Land as soon as practical. c. This checklist is complete. 8 Normal Electrical System Is Suspected Source 1. L & R NON-ESS ...... OFF 9 2. FLOOD Light ...... On for Night Operation 10 3. L & R MAIN...... OFF 4. ●If smoke or fumes continue, operate on EMER BATT as follows: 11 a. On aircraft 45-002 thru 45-225 not modified by SB 45-55-6, maintain 33,000 ft or below. 12

b. Airspeed...... ≤ 200 KIAS or 0.7 MI Slower If Necessary 13 c. If conditions permit, select flaps 20° (maximum) and retrim as necessary for landing. 14 d. L & R ENG CMPTR...... MAN 15 e. L & R GEN ...... OFF f. L & R BATT ...... OFF 16

3 17

EFFECTIVITY CL-126C All E-7 g. ■If smoke or fumes continue: The malfunctioning system is connected to the EMER BATT 2 bus. (1) L & R BATT...... On 3 (2) L & R GEN ...... On (3) L & R MAIN ...... On 4 (4) L & R ENG CMPTR ...... ON 5 (5) Allow attitude & air data display flags to clear. (6) Refer to Emergency Electrical System, page E-9. 6 g. ■If smoke or fumes dissipate: 7 (1) Emergency battery duration when both generators and both batteries are OFF is 1.0 hour. 8 (2) RADIO CTL HOT BUS ...... ON (3) Tune COM 1 using Clearance Delivery Radio. 9 (4) RMU 1 ...... Select PGE, ENGINE PAGE for Engine Indications 10 (5) Avoid flight in icing conditions, and land as soon as possible. 11 (6) The following conditions will exist with operative equip- 12 ment: 4 Operative Equipment Inoperative Equipment 13 Instruments/Avionics Standby Instruments Display Units 14 COM 1, L Audio Panel ➀ AHRS 1 & 2, ADC 1 & 2 RMU 1: Engine Pages ➀ RMU 2, NAV 2, COM 2 ➀ 15 RMU 1: ILS 1 Tuning FMS(es) — ATC 1 & 2 (transponder) Flight Controls 16 — L & R Stall Warning Systems — Spoilers/Spoilerons/Flaps 17 — Mach Trim & Autopilot — Pitch, Aileron & Rudder Trims — Pitch Trim Bias Anti-Icing Nacelle Heat (defaults ON) Pitot Heat, Wing/Stab & Wshld

EFFECTIVITY CL-126C E-8 All Change 2 Operative Equipment Inoperative Equipment Engines — L & R Engine Computers 1 (reverts to OFF mode) Environmental/Pressurization CABIN PRESSURE CONTROL Display Environmental Control (defaults to cold) 2 R Cabin Pressure; L Cabin Pressure Use MANUAL rate control 3 Landing Gear/Brakes Landing Gear (Control & Indication) — Inboard Brakes with Anti-Skid Outboard Brakes 4 Emergency Brakes — ➀ One or both main batteries not depleted. 5 (7) Refer to Normal Electrical System Failure Landing, Tab41 . 6 4. ●If smoke or fumes dissipate: 7 a. Land as soon as possible. b. This checklist is complete. 8 Emergency Electrical System Is Suspected Source 9 1. EMER BATT...... OFF 2. BUS Circuit Breaker (pilot’s ELECTRICAL group 10 [EMER BUS])...... Pull 11 3. Standby Instruments...... Cage Attitude Indicator Use Primary Instruments 12 4. DAU [REVERSION] ...... Channel B 5. Yaw Damper ...... As Required 13 6. Land as soon as practical. 14 7. Refer to Landing Gear Free Fall, Tab 39 , to extend landing gear prior to landing. 15 8. Refer to Emergency Brake Landing, Tab 42 . 16

4 EFFECTIVITY CL-126C E-9 Change 2 All ENTRY DOOR ENTRY ENTRY DOOR DOOR 2 ENTRY DOOR Accompanied by Evidence of Door Failure 1. NO SMOKING BELTS...... On 3 2. EMER DEPRESS ...... ON 4 3. Airspeed...... ≤ 250 KIAS or 0.7 MI Slower If Necessary 5 4. Establish descent to reduce cabin delta pressure, but not lower than the minimum safe altitude. 6 5. Land as soon as practical.

7 ENTRY DOOR Not Accompanied by Evidence of Door Failure 1. NO SMOKING BELTS...... On 8 2. Continue flight. The most probable cause is a latch pin switch malfunction. 9 L BATT OVHT L BATT R BATT L BATT OVHT OVHT OVHT 10 RR BATT BATT OVHT OVHT 11 (Nickel-Cadmium Batteries Only)

12 1. EICAS ...... Select ELEC or SUMRY Monitor Battery Temperature 13 2. Respective L or R BATT...... Verify OFF If battery temperature does not decrease: 14 3. Land as soon as possible.

EFFECTIVITY CL-126C E-10 All LR GEN FAIL GEN LR GEN FAIL FAIL 1. L & R GEN Circuit Breakers 1 (respective ELECTRICAL group) ...... Set 2. Electrical Load ...... Reduce 2 3. Engine N2 ...... 80% or Above 3 4. L & R GEN...... One at a Time, Depress (Approx 1 Sec) If a generator does not come on-line: 4 5. FLOOD Light ...... On for Night Operations 6. Use standby attitude indicator for attitude & magnetic compass for 5 directional reference. Use standby airspeed/Mach indicator & altimeter. 6 7. RMU 1 ...... Select PGE, ENGINE pages for Engine Indications 7 8. RMU 2: a. Select [1/2] for side 1 radios (COM 2, NAV 2, ADF 2, ATC 2 8 inoperative). b. Select PGE, NAVIGATION for NAV 1 course indication & 9 tuning. 10 9. Tune COM 1 as required using clearance delivery radio. Clearance delivery radio tuning may be achieved by selecting: 11 RADIO CTL HOT BUS — ON 10. L & R AV MSTR...... OFF 12 11. L & R ENG CMPTR ...... MAN 13 12. DU 2 ...... OFF 13. L & R WSHLD...... OFF 14 On Prior to Landing (Max 5 Minutes) 14. EMER LIGHTS ...... OFF 15 ON Prior to Landing (Max 10 Minutes) 15. Standby Pitot Heat...... Use As Required 16

17 5

EFFECTIVITY CL-126C All E-11 16. The following conditions will exist (L & R MAIN — OFF): - L & R pitot heat inoperative (avoid visible moisture); standby 2 pitot heat operative. - Recognition & landing/taxi lights inoperative. 3 - COM 2, NAV 2, ATC 2 inoperative. 4 - Automatic temperature control inoperative. Use MANUAL TEMP — ON. 5 Battery duration with the generators off is as follows: MAIN EMERGENCY 6 Amp-hr Time12 Time1 7 27 (Ni-Cad) 30 minutes 28 (Lead-Acid) 8 1.0 hour 38 1.0 hour

9 1 Time durations predicated upon operation on batteries only.

10 2 Time duration predicated upon the following conditions: -DU 2 — OFF. 11 - Standby Pitot Heat (R PROBES Switch) — ON for no more than 30 minutes. 12 - L & R AV MSTR — OFF.

13 - EMER LIGHTS — ON for no more than 10 minutes. - L & R MAIN — Remain OFF. 14 - L & R ENG CMPTR — MAN. 17. On aircraft 45-002 thru 45-225 not modified by SB 45-55-6, 15 maintain 33,000 feet or below. 18. ●If time to the landing airport will NOT exceed main battery 16 duration, this checklist is complete. ● 17 18. If time to the landing airport will exceed main battery duration: a. Airspeed ...... ≤ 200 KIAS or 0.7 MI Slower if Necessary

EFFECTIVITY CL-126C E-12 All Change 2 b. Provided adequate fuel is available, prior to depleting the main batteries; select flaps 20° (maximum) & trim as desired for landing. 1 c. Once the main batteries are depleted, the emergency battery will provide power to emergency bus servises. The following 2 conditions will exist with emergency battery until main batteries have been depleted: 3 Operative Equipment Inoperative Equipment Instruments/Avionics Standby Instruments Display Units 4 COM 1, L Audio Panel ➀ AHRS 1 & 2, ADC 1 & 2 RMU 1: Engine Pages ➀ RMU 2, NAV 2, COM 2 5 RMU 1: ILS 1 Tuning ➀ FMS(es) — ATC 1 & 2 (transponder) 6 Flight Controls — L & R Stall Warning Systems — Spoilers/Spoilerons/Flaps 7 — Mach Trim & Autopilot — Pitch, Aileron & Rudder Trims 8 — Pitch Trim Bias Anti-Icing 9 Nacelle Heat (defaults ON) Pitot Heat, Wing/Stab & Wshld Engines — L & R Engine Computers 10 (reverts to OFF mode) Environmental/Pressurization 11 CABIN PRESSURE CONTROL Display Environmental Control (defaults to cold) R Cabin Pressure; L Cabin Pressure Use MANUAL rate control 12 Landing Gear/Brakes Landing Gear (Control & Indication) — 13 Inboard Brakes with Anti-Skid Outboard Brakes Emergency Brakes — ➀ One or both main batteries not depleted. 14

d. Land as soon as possible. 15 e. Refer to Normal Electrical System Failure Landing, Tab41 . 16

6 EFFECTIVITY CL-126C E-13 Change 2 All Loss of Both Generators and Both Main Batteries

2 1. L & R BATT ...... On, One at a Time 2. L & R GEN Circuit Breakers 3 (respective ELECTRICAL group)...... Set

4 3. Engine N2...... 80% or Above 4. L & R GEN...... One at a Time, Depress (Approx 1 Sec) 5 5. MANUAL Rate Control (PRESSURIZATION) ...... As Required 6 6. zIf none of the main batteries or generators is restored: a. R INSTR Lights ...... As Desired 7 b. Use standby attitude indicator for attitude & magnetic compass for directional reference. Use standby airspeed/Mach indicator 8 & altimeter. c. RADIO CTL HOT BUS ...... ON 9 d. Tune COM 1 using Clearance Delivery Radio. 10 e. On aircraft 45-002 thru 45-225 not modified by SB 45-55-6, maintain 33,000 feet or below. 11 f. Fly out of icing conditions as soon as possible. All anti-icing systems except nacelle heat will be inoperative. 12 g. Emergency battery duration when both generators and both batteries fail is 1.0 hour. The following operative equipment will 13 exist with emergency battery: Operative Equipment Inoperative Equipment 14 Instruments/Avionics Standby Instruments Display Units COM 1, L Audio Panel ➀ AHRS 1 & 2, ADC 1 & 2 15 — RMU 1 & 2, NAV 2, COM 2 — FMS(es) 16 Flight Controls — L & R Stall Warning Systems 17 — Spoilers/Spoilerons/Flaps — Mach Trim & Autopilot — Pitch, Aileron & Rudder Trims — Pitch Trim Bias

EFFECTIVITY CL-126C E-14 All Change 2 Operative Equipment Inoperative Equipment Anti-Icing — Pitot Heat, Wing/Stab & Wshld 1 Engines — L & R Engine Computers (reverts to OFF mode) 2 Environmental/Pressurization CABIN PRESSURE CONTROL Display Environmental Control (defaults to cold) 3 R Cabin Pressure: L Cabin Pressure Use MANUAL rate control Landing Gear/Brakes 4 Landing Gear (Control & Indication) — Inboard Brakes with Anti-Skid Outboard Brakes 5 Emergency Brakes — ➀ One or both main batteries not depleted. 6 h. Primary and secondary pitch trim will be inoperative. ■If Elevator Pull Force is Encountered: 7 (1) Move C.G. aft if possible. 8 (2) Land as soon as possible to minimize forward C.G. movement. 9 ■If Elevator Push Force is Encountered: (1) Do not increase airspeed to minimize the time out of trim. 10 (2) Move C.G. forward if possible. 11 i. Refer to Normal Electrical System Failure Landing, Tab41 . 12 6. zIf L or R BATT is regained, but neither generator is regained: a. Land as soon as possible. 13 b. Refer to LR GEN FAIL, Tab 4 . 6. zIf one generator is regained: 14 a. Land as soon as practical. 15 b. Refer to (L or R) GEN FAIL, Tab 7 . 6. zIf both generators are regained: 16 a. Resume normal flight. 17 b. Land as soon as practical. 7

EFFECTIVITY CL-126C E-15 Change 2 All Emergency Descent 2 “CABIN ALTITUDE” CABIN CABIN ALTITUDE ALT Cabin Altitude Exceeds 10,000 Feet 3 1. Crew Oxygen Masks ...... Don & 100% 4 2. Thrust Levers ...... IDLE 5 3. Autopilot ...... Disengage 4. SPOILER ...... EXT

6 5. Descend at MMO/VMO, but not below minimum safe altitude. 6. DEPLOY (PAX OXYGEN) ...... ON 7 7. Pilot & Copilot MIC/MASK...... MASK 8 8. Pilot & Copilot INPH...... INPH 9. Yaw Damper ...... As Required 9 If time & conditions permit: 10 10. Transponder...... 7700 11. Notify controlling agency. 11 12. Check condition of passengers & provide assistance if conditions permit. 12

13 Emergency Evacuation

14 1. EMERGENCY/PARKING BRAKE...... Set 2. Thrust Levers ...... CUTOFF 15 3. EMER LIGHTS ...... ON 16 4. EMER BATT, L & R BATT ...... OFF 5. Evacuate the aircraft: 17 a. Cabin Entry Door...... Open & Exit b. Aft Emergency Exit...... Open & Exit

EFFECTIVITY CL-126C All Change 1 E-16 Change 1 FIRE (E Engine FIRE “RIGHT ENGINE FIRE FIRE LEFT ENGINE FIRE” PUSH 1

Affected engine: 2 1. Thrust Lever ...... IDLE Unless a Critical Thrust Situation Exists 3 2. ●If fire continues more than 15 seconds or there are other indications of fire: 4 a. Thrust Lever ...... CUTOFF b. Applicable FIRE (ENGINE)...... FIRE PUSH 5

c. EXTINGUISHER #1 (ENGINE)...... ARMED Push 6 d. ■If fire continues: (1) EXTINGUISHER #2 (ENGINE) ...... ARMED Push 7 (2) Land as soon as possible. 8 (3) Go to step e. d. ■If fire extinguishes: 9 (1) Land as soon as practical. 10 (2) Go to step e. e. ENG SYNC ...... OFF 11 f. Rudder Trim ...... As Required g. Yaw Damper...... As Required 12

h. Autopilot ...... As Desired 13 i. Applicable STBY (FUEL)...... Off j. Refer to Engine Shutdown in Flight, Tab 11 . 14

17 8

EFFECTIVITY CL-126C E-17 Change 1 All 2. ●If fire extinguishes in less than 15 seconds: a. Leave thrust lever at IDLE, unless a critical thrust situation 2 exists. b. ENG SYNC...... OFF 3 c. Rudder Trim...... As Required 4 d. Yaw Damper ...... As Required e. Autopilot ...... As Desired 5 f. Monitor fuel balance. Crossflow as required. STBY (FUEL) pump may be used. 6 g. Land as soon as practical. 7 h. Refer to Single-Engine Landing, Tab 43 .

L OIL R OIL 8 LL OIL OIL PRESS PRESS LOW LOW PRESS PRESS RR OIL OIL PRESS PRESS LOW LOW LOW LOW 9 1. Respective Engine OIL PSI & OIL °C ...... Check 10 2. ●If OIL PSI is below 50 PSI and/or OIL °C is high: 11 a. Reduce affected engine to idle. - If flight conditions permit: 12 A precautionary engine shutdown is advised. Refer to Engine Shutdown in Flight, Tab 11 . 13 b. Land as soon as practical. c. Refer to Single-Engine Landing, Tab 43 . 14 2. ●If OIL PSI is between 50 & 65 PSI & OIL °C is normal: 15 a. Reduce affected engine to idle. 16 b. Land as soon as practical. c. Refer to Single-Engine Landing, Tab 43 . 17 2. ●If OIL PSI & OIL °C are normal, continue to monitor OIL PSI & OIL °C.

EFFECTIVITY CL-126C E-18 All Engine Failure During takeoff: 1

Below V1 Speed 2 1. Brakes...... Apply 2. Thrust Levers ...... IDLE 3 3. Spoilers...... Verify Extended 4 4. If spoilers are not extended automatically, SPOILER...... EXT 5. Thrust Reversers ...... Deploy, if Necessary 5

Above V1 Speed 6

1. Rotate at VR to target takeoff pitch attitude; Climb at V2. 7 2. Gear ...... UP 3. Climb to 1500 feet AGL or Obstacle Clearance Altitude (as 8 appropriate), accelerate to V2 + 25, retract flaps, then accelerate to 200 KIAS en route climb speed. 9 4. Refer to Engine Shutdown in Flight, Tab 11 . 10 In flight:

1. Control Wheel Master (MSW)...... Depress & Release 11 Yaw damper & autopilot will disengage. On aircraft 45-002 thru 45-294 not modified by SB 45-27-20, the spoilers will blow down 12 while the MSW is depressed. 2. Thrust Lever (operative engine)...... Increase as Required 13 3. ENG SYNC...... OFF 14 4. Rudder Trim ...... As Required 5. Yaw Damper ...... As Required 15 6. Autopilot...... As Desired 7. Refer to Engine Shutdown in Flight, Tab 11 . 16

Change 1 9 17

EFFECTIVITY CL-126C E-19 Change 1 All During approach:

2 1. Control Wheel Master (MSW)...... Depress & Release Yaw damper & autopilot will disengage. On aircraft 45-002 thru 45-294 not modified by SB 45-27-20, the spoilers will blow down 3 while the MSW is depressed. 2. Thrust Lever (Operative Engine) ...... Increase as Required 4 3. Flaps ...... 20°

5 4. Airspeed...... VREF + 5 5. Rudder Trim ...... As Required 6 6. Yaw Damper...... As Required 7 7. Autopilot ...... As Desired 8. Refer to either of the following procedures as applicable: 8 - Single-Engine Landing, Tab 43 . 9 - Go Around, Page N-15, & Engine Shutdown in Flight, Tab11 . 10

Change 1 EFFECTIVITY CL-126C E-20 All Change 1 Immediate Engine Airstart

Affected engine: 1

1. Thrust Lever ...... IDLE 2 IGN will automatically activate. 2. STBY (FUEL) ...... ON 3 3. ●If ITT is approaching the limit & rising rapidly: 4 a. Thrust Lever ...... CUTOFF b. Perform Engine Shutdown in Flight, Tab 11 . 5 c. This checklist is complete. 6 3. ●If no indication of light-off is obtained within 20 seconds: a. Thrust Lever ...... CUTOFF 7 b. Perform Engine Shutdown in Flight, Tab 11 . c. This checklist is complete. 8 3. ●If airstart is complete: 9 a. Thrust Lever ...... Advance b. This checklist is complete. 10

10 17

EFFECTIVITY Change 1 CL-126C E-21 Change 1 All L BLEED R BLEED LL BLEED BLEED AIR AIR LEAK LEAK AIR AIR RR BLEED BLEED AIR AIR LEAK LEAK LEAK LEAK 2 LRLR BLEED BLEED AIR AIR LEAK LEAK 3 On the ground:

4 L or R BLEED AIR LEAK, or LR BLEED AIR LEAK Illuminated 1. APU START/STOP (if installed) ...... Off 5 2. Respective L or R BLEED...... OFF

6 If BLEED AIR LEAK remains illuminated: 3. Shut down respective engine. 7 In flight: 8 L or R BLEED AIR LEAK Illuminated 9 1. Respective L or R BLEED...... OFF 2. Maintain 41,000 feet or below. Avoid flight in icing conditions. 10 If BLEED AIR LEAK remains illuminated: 11 3. Reduce engine N1 on respective engine. 4. Land as soon as possible. 12 LR BLEED AIR LEAK Illuminated 13 1. EMER PRESS ...... ON 2. One L or R BLEED...... OFF 14 3. Adjust engine N1 on engine supplying EMER air to modulate cabin temperature. 15 4. Maintain 41,000 feet or below. Avoid flight in icing conditions. 16 5. Land as soon as possible.

EFFECTIVITY CL-126C E-22 All L ENG R ENG LL ENG ENG PYLON PYLON OVHT OVHT PYLON PYLON R ENG PYLON OVHT OVHT OVHT R ENG PYLON OVHT 1 LRLR ENG ENG PYLON PYLON OVHT OVHT

L or R ENG PYLON OVHT 2 1. Respective L or R NAC...... Off 3 2. Reduce engine N1 on respective engine. 3. Fly out of icing conditions. 4 If L or R ENG PYLON OVHT remains illuminated: 4. Shut down respective engine. Refer to Engine Shutdown in Flight, 5 Ta b 11 . 6 LR ENG PYLON OVHT 1. L & R NAC ...... Off 7

2. Reduce engine N1 on both engines as low as possible, unless a critical thrust situation exists. 8 3. Fly out of icing conditions. 9 If LR ENG PYLON OVHT remains illuminated: 4. Land as soon as possible. 10

PIT TRIM BIAS 11

PIT TRIM MSCMP 12

SPOILERS EXT 13 TAKEOFF TRIM 14 1. Refer to Takeoff “CONFIGURATION”, Tab 18 . 15

11 17

EFFECTIVITY CL-126C All E-23 Aileron Control Jam

2 1. Attitude Control...... As Required Use Rudder & Thrust as Necessary 3 2. ROLL DISC...... Pull 4 a. Pilot — Control aircraft with the spoilerons. b. Do Not use the copilot control. 5 c. Do Not use AIL TRIM. d. Do not reconnect. The most likely occurrence of a jam would 6 be expected in the aileron control system (copilot’s control wheel). 7 3. Airspeed...... Reduce as Necessary 8 4. Land as soon as possible. 5. Refer to Aileron Jammed Landing, Tab 43 . 9 Elevator Control Jam 10 1. Attitude Control...... As Required 11 Use Pitch Trim & Thrust as Necessary 2. ELEV DISC...... Pull & Rotate 12 3. Determine elevator without the jam & transition flight control to that pilot. 13 a. Do Not apply additional control force to the jammed control. 14 b. Do Not use PIT TRIM BIAS. 15 c. Do not reconnect. 4. Land as soon as possible. 16 5. Refer to Elevator Jammed Landing, Tab 44 . 17

Change 1

EFFECTIVITY CL-126C E-24 All Change 1 Pitch Axis Uncommanded Motion

1. Control Wheel Master (MSW)...... Depress & Hold 1

2. Attitude Control ...... As Required 2 3. Thrust Levers ...... As Required

4. Airspeed ...... ≤ Mach Trim Off MMO, but not less than 0.65 MI 3 5. zIf control force continues with the MSW depressed: 4 a. PITCH TRIM...... OFF b. Malfunctioning PRI PITCH or 5 SEC PITCH Circuit Breaker (respective pilot’s or copilot’s FLIGHT group [TRIM]) ...... Pull 6 c. Control Wheel Master (MSW) ...... Release d. Yaw Damper...... Engage 7 e. If the malfunction occurred in the Primary trim: 8 (1) PITCH TRIM...... SEC (2) SEC (pedestal [PITCH TRIM]) ...... As Required 9 (3) Refer to PRI TRIM FAIL, Tab 17 . 10 (4) This checklist is complete. e. If the malfunction occurred in the Secondary trim: 11 (1) PITCH TRIM...... PRI (2) Control Wheel Trim...... As Required 12

(3) Refer to SEC TRIM FAIL, Tab 18 . 13 (4) This checklist is complete. 5. zIf control force relieves with MSW depressed: 14 a. AFCS SERVOS Circuit Breaker (pilot’s FLIGHT group)...... Pull 15 b. Control Wheel Master (MSW) ...... Release 16 c. Control Wheel Trim ...... As Required d. Maintain 33,000 feet or below. 17 12

EFFECTIVITY CL-126C 45-002 thruAll 45-225 not modified by SB 45-55-6 E-25 Pitch Axis Uncommanded Motion

1. Control Wheel Master (MSW)...... Depress & Hold 1 2. Attitude Control ...... As Required 2 3. Thrust Levers ...... As Required 4. Airspeed ...... ≤ Mach Trim Off MMO 3 5. zIf control force continues with the MSW depressed: a. PITCH TRIM...... OFF 4 b. Malfunctioning PRI PITCH or 5 SEC PITCH Circuit Breaker (respective pilot’s or copilot’s FLIGHT group [TRIM]) ...... Pull 6 c. Control Wheel Master (MSW) ...... Release d. Yaw Damper...... As Desired 7 e. If the malfunction occurred in the Primary trim: 8 (1) PITCH TRIM...... SEC (2) SEC (pedestal [PITCH TRIM]) ...... As Required 9 (3) Refer to PRI TRIM FAIL, Tab 17 . (4) This checklist is complete. 10 e. If the malfunction occurred in the Secondary trim: 11 (1) PITCH TRIM...... PRI (2) Control Wheel Trim...... As Required 12 (3) Refer to SEC TRIM FAIL, Tab 18 . 13 (4) This checklist is complete. 5. zIf control force relieves with MSW depressed: 14 a. AFCS SERVOS Circuit Breaker (pilot’s FLIGHT group)...... Pull 15 b. Control Wheel Master (MSW) ...... Release 16 c. Control Wheel Trim ...... As Required d. Refer to AP Tab 14 or AP (steady), Tab 30 , as 17 appropriate. e. This checklist is complete. 12 EFFECTIVITY CL-126C 45-226 & on, andAll prior aircraft modified by SB 45-55-6 E-25.1E-29 e. 11Airspeed ...... ≥ 0.65 MI Until Below 33,000 Feet f. Land as soon as practical. 2 g. This checklist is complete. 3 Recovery from Inadvertent Overspeed 4 “OVERSPEED” 5 1. Thrust Levers ...... IDLE 6 2. Autopilot ...... Disengage 3. SPOILER ...... EXT 7 4. Identify aircraft pitch & roll attitude. 8 5. Level wings. 6. Elevator & Pitch Trim ...... As Required 9 7. Yaw Damper...... As Desired

10 Roll or Yaw Axis Uncommanded Motion

11 1. Control Wheel Master (MSW)...... Depress & Hold 12 2. Attitude Control...... As Required 3. Airspeed...... ≤ Mach Trim Off MMO, but not less than 0.65 MI 13 4. ●If accompanied by SPOILERS FAIL amber CAS or SPOILER JAM amber CAS: 14 a. Control Wheel Master (MSW) ...... Release 15 b. Yaw Damper ...... Engage c. Refer to SPOILERS FAIL, Tab 18 or SPOILER JAM, 16 Tab19 . d. This checklist is complete. 17 4. ●If control force continues with MSW depressed: a. EICAS/SUMRY or FLT Page ...... Select, Check Trims b. AIL or RUD Circuit Breaker (respective copilot’s or pilot’s FLIGHT group [TRIM]) ...... Pull Affected Axis

EFFECTIVITY CL-126C 45-002 thruAll 45-225 E-26 not modified by SB 45-55-6 Recovery from Inadvertent Overspeed 2 “OVERSPEED”

3 1. Thrust Levers ...... IDLE

4 2. Autopilot ...... Disengage 3. SPOILER ...... EXT 5 4. Identify aircraft pitch & roll attitude. 5. Level wings. 6 6. Elevator & Pitch Trim ...... As Required 7 7. Yaw Damper...... As Desired

8 Roll or Yaw Axis Uncommanded Motion

9 1. Control Wheel Master (MSW)...... Depress & Hold 2. Attitude Control...... As Required 10 3. Airspeed...... ≤ Mach Trim Off MMO 11 4. ●If accompanied by SPOILERS FAIL amber CAS or SPOILER JAM amber CAS: 12 a. Control Wheel Master (MSW) ...... Release b. Yaw Damper ...... As Desired 13 c. Refer to SPOILERS FAIL, Tab 18 or SPOILER JAM, Tab19 . 14 d. This checklist is complete. 15 4. ●If control force continues with MSW depressed: a. EICAS/SUMRY or FLT Page ...... Select, Check Trims 16 b. AIL or RUD Circuit Breaker (respective copilot’s or pilot’s FLIGHT group [TRIM]) ...... Pull Affected Axis 17 c. Control Wheel Master (MSW) ...... Release d. Use asymmetric thrust & decrease airspeed as required to minimize mistrim. e. Autopilot ...... As Desired

EFFECTIVITY CL-126C E-26.1 45-226 & on, andAll prior aircraft E-30 modified by SB 45-55-6 c. Control Wheel Master (MSW) ...... Release d. Use asymmetric thrust & decrease airspeed as required to minimize mistrim. 1 e. Autopilot ...... As Desired 2 f. Yaw Damper...... As Desired g. Refer to Rudder Trim Tab Jammed Landing, Tab 46 or 3 Aileron Trim Tab Jammed Landing, Tab 44 . h. This checklist is complete. 4 4. If control force relieves with MSW depressed: 5 a. AFCS SERVOS Circuit Breaker (pilot’s FLIGHT group)...... Pull 6 b. RUD BOOST...... OFF c. Control Wheel Master (MSW) ...... Release 7 d. Maintain 33,000 feet or below. 8 e. Airspeed...... ≥ 0.65 MI Until Below 33,000 Feet f. Land as soon as practical. 9 g. This checklist is complete. 10 Rudder Control Jam 11 1. Attitude Control ...... As Required Use Roll Control & Thrust as Necessary 12 2. Yaw Damper ...... Off (Use Glareshield Button) 13 3. RUD BOOST ...... OFF 4. Do not use RUDDER TRIM. 14 5. Use asymmetric thrust if required to minimize sideslip. 6. Airspeed ...... Reduce as Necessary 15 7. Land as soon as possible. 16 8. Refer to Rudder Jammed Landing, Tab 45 . 13 17

EFFECTIVITY Change 1 CL-126C E-27 45-002 thruAll 45-225 Change 1 not modified by SB 45-55-6 f. Yaw Damper...... As Desired g. Refer to Rudder Trim Tab Jammed Landing, Tab 46 or Aileron Trim Tab Jammed Landing, Tab 44 . 1 h. This checklist is complete. 2 4. If control force relieves with MSW depressed: a. AFCS SERVOS Circuit Breaker 3 (pilot’s FLIGHT group)...... Pull b. RUD BOOST...... OFF 4 c. Control Wheel Master (MSW) ...... Release 5 d. Refer to AP, Tab 14 or AP (steady), Tab 30 as appropriate. 6 e. This checklist is complete. 7 Rudder Control Jam 8 1. Attitude Control ...... As Required Use Roll Control & Thrust as Necessary 9 2. Yaw Damper ...... Off (Use Glareshield Button) 3. RUD BOOST ...... OFF 10 4. Do not use RUDDER TRIM. 11 5. Use asymmetric thrust if required to minimize sideslip. 6. Airspeed ...... Reduce as Necessary 12 7. Land as soon as possible. 13 8. Refer to Rudder Jammed Landing, Tab 45 . 14

13 17 Change 1

EFFECTIVITY CL-126C E-31E-27.1 45-226 & on, andAll prior aircraft Change 1 modified by SB 45-55-6 L FUEL R FUEL LL FUEL FUEL PRESS PRESS LOW LOW PRESS PRESS LOW LOW 2 RR FUEL FUEL PRESS PRESS LOW LOW LRLR FUEL FUEL PRESS PRESS LOW LOW

3 Affected engine: 1. STBY (FUEL)...... ON 4 2. IGN ...... ON 5 3. XFLOW (FUEL)...... Closed If FUEL PRESS LOW remains illuminated: 6 4. A descent to a lower altitude, but not below the minimum safe altitude, is recommended. This will improve the suction feed capability 7 of the engine driven fuel pump. 5. Flight can be continued at altitude if engines are operating properly. 8 Make thrust lever movements slow & cautious at high altitudes.

EFFECTIVITY CL-126C E-28 All Multi-Function Display (MFD) Annunciations 1

TERR TEST 2

HDG FAIL 3 HDG TEST 4 RA NO BRG 5

7 HDG FAIL 1. Refer to Loss of PFD Attitude or Heading Displays, Tab 28 . 8 HDG TEST Indicates the AHRS is in the power-up alignment mode and illuminates in 9 the center of the heading display. Alignment requires approximately 2 minutes on the ground or 20 seconds in flight. 10

RA NO BRG 11 Located in upper right corner of TCAS zoom window and indicates that an RA has been encountered, but no bearing to that RA is available for display. 12 1. Attempt to visually acquire intruder aircraft.

2. Request assistance from air traffic control in acquiring the intruder 13 aircraft. 14 TERR TEST Located in the upper left corner of the MFD and indicates the EGPWS self 15 test is in progress. 16

17 14

CL-126C EFFECTIVITY All E-29E-27 Primary Flight Display (PFD) Annunciations 2 AP 3 ATT FAIL 4 WIND SHR 5 HDG FAIL 6

7 AP 1. Control Wheel Master (MSW)...... Depress & Hold Until WHEEL MSTR white CAS 8 is Illuminated, then Release The red AP will either disappear or turn steady amber. 9 2. ●If the amber AP remains illuminated & is accompanied by an amber YD: 10 a. Maintain 33,000 feet or below...... ≥ 11 b. Airspeed 0.65 MI Until Below 33,000 Feet c. Land as soon as practical. 12 d. This checklist is complete. 2. ●If the amber AP remains illuminated & is not accompanied by 13 an amber YD: a. Yaw Damper ...... Engage 14 b. This checklist is complete. ● 15 2. If the amber AP extinguishes: a. Yaw Damper ...... Engage 16 b. Autopilot ...... Engage, as Desired c. This checklist is complete. 17 ATT FAIL 1. Refer to Loss of PFD Attitude or Heading Displays, Tab 28 . 18 HDG FAIL 1. Refer to Loss of PFD Attitude or Heading Displays, Tab 28 .

Change 1 EFFECTIVITY CL-126C E-30 45-002 thruAll 45-225 Change 1 E-28 not modified by SB 45-55-6 Primary Flight Display (PFD) Annunciations 2

AP 3 ATT 4 FAIL WIND SHR 5 HDG FAIL 6

7 AP 1. Control Wheel Master (MSW)...... Depress & Hold 8 Until WHEEL MSTR white CAS is Illuminated, then Release 9 The red AP will either disappear or turn steady amber. 2. ●If the amber AP remains illuminated & is accompanied by an 10 amber YD, this checklist is complete. 2. ●If the amber AP remains illuminated & is not accompanied by 11 an amber YD: a. Yaw Damper ...... As Desired 12 b. This checklist is complete. 13 2. ●If the amber AP extinguishes: a. Yaw Damper ...... As Desired 14 b. Autopilot ...... As Desired

15 c. This checklist is complete. ATT FAIL 16 1. Refer to Loss of PFD Attitude or Heading Displays, Tab 28 .

17 HDG FAIL 1. Refer to Loss of PFD Attitude or Heading Displays, Tab 28 . 18

Change 1

EFFECTIVITY CL-126C E-30.1 45-226 & on, andAll prior aircraft E-30 modified by SB 45-55-6 Change 1 Primary Flight Display (PFD) Annunciations (Cont) WIND SHR 1 “WINDSHEAR, WINDSHEAR, WINDSHEAR” 2 During takeoff:

1. Thrust Lever(s) ...... Select T/O or APR, As Required 3 2. Maintain takeoff target pitch attitude and wings level, allowing air- 4 speed to decrease if necessary. Do not retract flaps or gear. 3. If the aircraft continues to descend, increase pitch target attitude 5 smoothly and in small increments, bleeding airspeed as necessary to stop the descent. Use stall warning onset (stick shaker) as the 6 upper limit of pitch attitude. 4. Maintain escape attitude and thrust and delay retracting flaps or 7 landing gear until safe climb-out is assured. 8 During final approach:

1. Immediately initiate go-around procedure except do not retract 9 flaps or landing gear. 10 2. Thrust Lever(s) ...... Select T/O or APR, As Required

3. Rotate smoothly to the go-around/takeoff pitch attitude, allowing air- 11 speed to decrease if necessary. Maintain wings level. 12 4. If the aircraft continues to descend, increase pitch target attitude smoothly and in small increments, bleeding airspeed as necessary 13 to stop the descent. Use stall warning onset (stick shaker) as the upper limit of pitch attitude. 14 5. Maintain escape attitude and thrust and delay retracting flaps or landing gear until safe climb-out is assured. 15

15 16

CL-126C EFFECTIVITY All E-31E-29 Primary Flight Display (PFD) Annunciations (Cont)

3 PULL UP 4

5 RA FAIL 6

7 PULL UP

8 “PULL UP” “TERRAIN, TERRAIN, PULL UP” 9 “OBSTACLE, OBSTACLE, PULL UP”

10 1. Autopilot ...... Disengage 2. Thrust Lever(s)...... Select T/O or APR, As Required 11 3. Increase pitch attitude and climb as required to avoid terrain. 12 4. SPOILER ...... RET 5. Flaps ...... Retract (8° or UP), As Required 13 6. Gear...... UP 14 7. Flaps ...... UP 8. EGPWS Terrain Awareness Display ...... Monitor 15 9. Maintain climb attitude until the warning ceases.

16 10. Notify the controlling agency.

Change 2 18

E-32 EFFECTIVITY CL-126C All Change 2 RA FAIL

Located below the VSI display and indicates resolution advisory information from the TCAS computer is corrupt. This can occur with or without an 1 actual intruder aircraft being present. 2 1. Attempt to visually acquire possible intruder aircraft. 2. RMU (ATC/TCAS)...... Select TA ONLY Mode 3

4 16 5

Change 1 EFFECTIVITY CL-126C All E-33 Change 1 1EMER/PARKEMER/PARK BRK 2 1. Refer to Takeoff “CONFIGURATION”, Tab 18 . 3 GEARGEAR “GEAR” GEAR 4 1. ●If adequate time is available to extend gear: 5 a. AUX HYD...... ON 6 b. Gear ...... DN c. This checklist is complete. 7 1. ●If adequate time is not available to extend gear: 8 a. Execute a go-around.

b. This checklist is complete. 9

10 NORMAL NORMNORM BRK BRK FAIL FAIL “BRAKES FAIL” BRAKES FAIL 11 1. ●If failure occurs just after gear extension and conditions permit: 12 a. Gear ...... UP 13 b. INBD BRAKES (pilot’s GEAR/HYDRAULICS group) & OUTBD BRAKES (copilot’s GEAR/HYD group) 14 Circuit Breakers...... Set or Pull & Reset c. AUX HYD...... ON 15 d. Gear ...... DN 16

EFFECTIVITY CL-126C E-34 All e. ■If NORM BRK FAIL red CAS & NORMAL BRAKES FAIL red CWP extinguish, this checklist is complete. e. ■If NORM BRK FAIL red CAS & NORMAL BRAKES FAIL red 1 CWP remain illuminated, go to step 2. 1. ●If failure is not associated with gear extension, go to step 2. 2 2. Refer to one of the following: 3 - Emergency Braking, this page. - Emergency Brake Landing, Tab 42 . 4

Emergency Braking 5 14Emergency Braking 1. EMERGENCY/PARKING BRAKE ...... Pull Smoothly 6

7 Nose Wheel Steering Malfunction

1. Control Wheel Master (MSW)...... Depress & Release 8

2. Thrust Levers ...... IDLE 9 3. Brake to a stop. Use differential brakes as necessary. 4. Taxi using differential brakes & thrust. 10

11 Ditching 1. If time & conditions permit: 12 a. Head toward nearest land or vessel. b. Notify controlling agency. 13

c. Transponder ...... 7700 14 d. ELT...... ON e. Crew Life Vests ...... On 15 f. Shoulder Harnesses ...... Locked 17 16

Change 1 EFFECTIVITY CL-126C All E-35 Change 1 g. Brief passengers as required. (1) Use of available flotation equipment. Inform passengers 2 not to inflate life vests (if applicable) while inside aircraft. (2) Location & operation of emergency exits. Do not open 3 lower half of cabin door. (3) Secure all loose items. 4 (4) Emergency landing brace position. 5 (5) Several impacts may be felt, depending on the sea conditions. Do not release seat belts after first impact is felt. 6 h. NO SMOKING BELTS...... On i. Seat belts ...... On Until Aircraft Stops 7 2. Gear ...... UP 8 3. FLAPS ...... DN 4. PACK...... OFF 9 5. Perform normal approach at VREF.

10 6. Thrust Levers ...... CUTOFF at Touchdown

11 7. L & R FIRE (ENGINE)...... FIRE PUSH 8. EMER BATT, L & R BATT ...... OFF 12 9. Emergency Exit(s)...... Open After Airplane Stops Do Not Open Lower Half of Cabin Door 13 15

EFFECTIVITY CL-126C E-36 All Forced Landing — Both Engines Inoperative

Airplane Best Glide Speed (Gear — UP, FLAPS — UP) is 160 KIAS 1 (approximately 2 nm per 1000 feet of altitude) 2 1. If time & conditions permit: a. Transponder ...... 7700 3

b. Advise controlling agency. 4 c. Prepare passengers for emergency landing. 5 d. NO SMOKING BELTS...... On 2. GEAR FREEFALL...... PUSH DOWN & Lock Forward 6 3. AUX HYD...... ON 7 4. Gear ...... DN

5. HYD XFLOW ...... ON 8

6. FLAPS ...... DN 9 7. HYD XFLOW ...... Off

8. Shoulder Harnesses ...... Locked 10

9. L & R FIRE (ENGINE) ...... FIRE PUSH 11 10. Touch down in normal landing attitude. 12 After airplane comes to a complete stop: 11. EMERGENCY/PARKING BRAKE...... Set 13 12. Thrust Levers...... CUTOFF 14 13. EMER LIGHTS ...... ON

14. EMER BATT, L & R BATT ...... OFF 15

15. Evacuate the aircraft: 16 a. Cabin Entry Door ...... Open & Exit

b. Aft Emergency Exit...... Open & Exit 17

CL-126C EFFECTIVITY All E-37 “STALL”“STALL” Voice Activates

2 1. Lower the pitch attitude to reduce angle of attack.

3 2. Thrust Levers ...... T/O (Manual APR if Required) 3. Level the wings. 4 4. Accelerate out of stall condition.

5 Aborted Takeoff 6 1. Brakes...... Apply 7 2. Thrust Levers ...... IDLE

8 3. Spoilers...... Verify Extended 4. If spoilers are not extended automatically, SPOILER ...... EXT 9 5. Thrust Reversers ...... Deploy, if Necessary 6. Refer to the AFM for further disposition. 10

17 18 18

Change 1 EFFECTIVITY CL-126C E-38 All Change 1 TakeoffTakeoff “CONFIGURATION” “CONFIGURATION” 18 EMER/PARK BRK 20 PIT TRIM BIAS 21 PIT TRIM MSCMP 22 SPOILERS EXT

TAKEOFF TRIM 23

UNL OR DEP (EI) 24 25 1. Brakes...... Apply

2. Thrust Levers...... IDLE 26

3. After stopping, check takeoff configuration. 27 19 28

CL-126C EFFECTIVITY All E-39 L REV R REV LUNL REV OR UNSAFE DEP (EI) “LEFT” or UNSAFE UNSAFE R REV UNSAFE “RIGHT 19 REVERSER UNSAFE” 20 During takeoff: Below V1 Speed 21 1. Brakes...... Apply 22 2. Thrust Levers ...... IDLE 3. Spoilers...... Verify Extended 23 4. If spoilers are not extended automatically, SPOILER ...... EXT 24 Above V1 Speed:

1. Rotate at VR to target takeoff pitch attitude; Climb at V2. 25 2. Gear...... UP 26 3. Climb to 1500 feet AGL or Obstacle Clearance Altitude (as appropriate), accelerate to V2 + 25, retract flaps, then accelerate 27 to 200 KIAS en route climb speed. 4. Respective Engine Thrust Lever...... IDLE 28 5. Airspeed ...... ≤ 160 KIAS As Required to Maintain Level Flight 29 6. Respective DEPLOY Circuit Breaker (ENGINE group [L or R REVERSER]) ...... Pull 30 7. Respective ANN & STOW Circuit Breakers (ENGINE group [L or R REVERSER]) ...... Set 31 8. ●If REV UNSAFE red CWP, & UNL or DEP red EI remain illuminated: 32 a. Respective Thrust Lever...... CUTOFF 33 Refer to Engine Shutdown in Flight, Tab 11 , and Thrust Reverser Deployed Landing, Tab 50 . 34 b. This checklist is complete. 7. ●If REV UNSAFE red CWP, & UNL or DEP red EI extinguish: 35 a. Respective Thrust Lever...... As Required b. This checklist is complete.

E-40 EFFECTIVITY CL-126C Change 2 All Change 2 In flight:

1. Control Wheel Master (MSW)...... Depress & Release Yaw damper & autopilot will disengage. On aircraft 45-002 thru 18 45-294 not modified by SB 45-27-20, spoilers will blow down while the MSW is depressed. 19 2. Attitude Control...... As Required 20 3. Thrust Lever (operative engine)...... Increase as Required 4. Thrust Lever (deployed engine) ...... IDLE 21 5. Airspeed ...... ≤ 160 KIAS As Required to Maintain Level Flight 22 6. Maintain 30,000 feet or below, or minimum safe altitude. 23 7. Respective DEPLOY Circuit Breaker (ENGINE group [L or R REVERSER])...... Pull 24 8. Respective ANN & STOW Circuit Breakers (ENGINE group [L or R REVERSER])...... Set 25 9. Respective Thrust Reverser Lever...... Stow 10. ●If REV UNSAFE red CWP, & UNL or DEP red EI remain 26 illuminated: a. Thrust Lever (deployed engine) ...... CUTOFF 27 b. ENG SYNC ...... OFF 28 c. Rudder Trim ...... As Required d. Yaw Damper...... As Required 29 e. Refer to Engine Shutdown in Flight, Tab 11 , and Thrust Reverser Deployed Landing, Tab 50 . 30 f. This checklist is complete. 31 10. ●If REV UNSAFE red CWP, & UNL or DEP red EI extinguish: a. Thrust Levers ...... As Required 32 b. Yaw Damper...... As Required 33 c. This checklist is complete.

20 34

EFFECTIVITY CL-126C Change 2 All E-41 ABNORMAL PROCEDURES

This section contains those operating procedures requiring the use of special systems and/or alternate use of regular systems which, if followed, will maintain an acceptable level of airworthiness or reduce operational risk re- sulting from a failure condition. The procedures located in this section supplement normal procedures when a failure condition exists. Use of normal procedures should be continued when applicable. Sound judgement as well as thorough knowledge of the aircraft, its characteristics, and the flight manual procedures are essential in the handling of any failure condition. In addition to the outlined items in the abnormal procedure, the following steps are considered part of all abnormal situations: • Maintain Airplane Control • Analyze the Situation • Take Proper Action

EFFECTIVITY CL-126C All A-i ABNORMAL

CAS or (EI) Message Tab Abnormal EICAS Index

CAS or (EI) Message Tab CAS or (EI) Message Tab AHRS 1 OVHT 22 R DAU ENG MISCMP 23 AHRS 2 OVHT 22 L DAU SYS MISCMP 23 AHRS 1-2 OVHT 22 R DAU SYS MISCMP 23 ANTI-SKID FAIL 37 DEFUEL OPEN 19 L AOA HT FAIL 1 DU 1 OVHT 24 R AOA HT FAIL 1 DU 2 OVHT 24 LR AOA HT FAIL 1 DU 3 OVHT 24 AP AIL MISTRIM 4 DU 4 OVHT 24 AP ELEV MISTRIM 4 LR ECS FAIL 14 APU AMPS HIGH 4 L ECS FAULT 15 APU FAIL 4 R ECS FAULT 15 AUX HYD PMP LO 21 EICAS CHK (MFD) 29 AUX HYD QTY LO 21 ELEVATOR DISC 17 L BATT OVHT 5 EMER BATT LOW 5 R BATT OVHT 5 EMER BUS VOLTS 5 LR BATT OVHT 5 EMER LIGHTS 7 L BLEED OVHT 12 L EMER PRESS ON 15 R BLEED OVHT 12 R EMER PRESS ON 15 LR BLEED OVHT 12 LR EMER PRESS ON 15 BRK ACUM PRESS 21 EMERGENCY EXIT 5 CAB DELTA P 13 L ENG FIRE FAIL 7 CAB DUCT OVHT 13 R ENG FIRE FAIL 7 LR CAB PRESS FAIL 14 LR ENG FIRE FAIL 7 CAB PRESS MAN 14 L ENGCMPTR FAULT 7 CABIN ALTITUDE 14 R ENGCMPTR FAULT 7 L CHK IC SW 25 LR ENGCMPTR FAULT 7 R CHK IC SW 25 L ENGINE CHIP 7 LR CHK IC SW 25 R ENGINE CHIP 7 CKPT DUCT OVHT 14 LR ENGINE CHIP 7 CNFG MISMATCH 22 L ESS BUS FAULT 6 CPLT BRK FAULT 37 R ESS BUS FAULT 6 DAU 1A FAIL 22 LR ESS BUS FAULT 6 DAU 1B FAIL 22 L ESS BUS VOLTS 6 DAU 1A-1B FAIL 22 R ESS BUS VOLTS 6 DAU 2A FAIL 23 LR ESS BUS VOLTS 6 DAU 2B FAIL 23 EXTERNAL DOORS 5 DAU 2A-2B FAIL 23 FLAPS FAIL 17 L DAU ENG MISCMP 23 FLAPS FAULT 17

EFFECTIVITY CL-126C ABNORMAL All A-ii Change 2 Change 2 Abnormal EICAS Index (Cont)

CAS or (EI) Message Tab CAS or (EI) Message Tab L FUEL FILTER 20 LR NAC HT 2 R FUEL FILTER 20 L NAC HT FAIL ON 2 LR FUEL FILTER 20 R NAC HT FAIL ON 2 L FUEL HEATER 20 LR NAC HT FAIL ON 2 R FUEL HEATER 20 NWS FAIL 38 LR FUEL HEATER 20 L OIL FILTER 7 FUEL IMBALANCE 20 R OIL FILTER 7 L FUEL QTY LOW 20 LR OIL FILTER 7 R FUEL QTY LOW 20 L OUTBD BRK FAIL 38 LR FUEL QTY LOW 20 R OUTBD BRK FAIL 38 FUEL XFLO 20 LR OUTBD BRK FAIL 38 L FWSOV FAULT 20 OXYGEN OFF 15 R FWSOV FAULT 20 OXYGEN QTY LOW 15 LR FWSOV FAULT 20 OXY PRESS HI 16 GEAR 37 PACK OVHT 16 L GEN AMPS HIGH 7 PAX OXY FAIL 16 R GEN AMPS HIGH 7 L PFD CHECK 25 LR GEN AMPS HIGH 7 R PFD CHECK 25 L GEN FAIL 7 LR PFD CHECK 25 R GEN FAIL 7 L PITOT HT 2 IC 1 OVHT 24 R PITOT HT 2 IC 2 OVHT 24 LR PITOT HT 2 IC BUS FAIL 25 PLT BRK FAULT 38 ICE DET FAIL 1 PRI TRIM FAIL 17 ICE DETECTED 1 REV (EI) 11 IGN (EI) 10 ROLL DISC 17 L INBD BRK FAIL 37 RUD BOOST INOP 18 R INBD BRK FAIL 37 SAT HT FAIL 2 LR INBD BRK FAIL 37 SEC TRIM FAIL 18 LBS/KGS CONFIG 25 L SPOILER JAM 19 MACH TRIM FAIL 17 R SPOILER JAM 19 MAIN HYD PRESS 22 LR SPOILER JAM 19 MAN (EI) 10 SPOILERS EXT 18 NAC (EI) 10 SPOILERS FAIL 18 L NAC HT 2 STAB TEMP LOW 2 R NAC HT 2 L STALLWARN FAIL 19

EFFECTIVITY A-iii CL-126C Change 2 All Abnormal EICAS Index (Cont)

CAS or (EI) Message Tab CAS or (EI) Message Tab R STALLWARN FAIL 19 WING TEMP LOW 3 LR STALLWARN FAIL 19 L WSHLD HT FAIL 3 START (EI) 11 R WSHLD HT FAIL 3 STBY PITOT HT 2 LR WSHLD HT FAIL 3 SYNC (EI) 11 L WSHLD OVHT 3 UNL (EI) 11 R WSHLD OVHT 3 WARN AUDIO 25 LR WSHLD OVHT 3 LR WARN PWR FAIL 25

EFFECTIVITY All CL-126C A-iv Change 2 ABNORMAL PROCEDURES TAB

ANTI-ICING 1 AOA HT FAIL 1 2 ICE DET FAIL ICE DETECTED 3 NAC HT 4 NAC HT FAIL ON PITOT HT 5 2 SAT HT FAIL 6 STAB TEMP LOW STBY PITOT HT 7 WING TEMP LOW WSHLD HT FAIL 8 3 WSHLD OVHT 9 Windshield Outer Ply Shattered or Cracked Engine Ice Ingestion 10 Inadvertent Icing Encounter 11 AUTOPILOT AP AIL MISTRIM 4 12 AP ELEV MISTRIM 13 AUXILIARY POWER UNIT (APU) APU AMPS HIGH 14 APU FAIL 15 DOOR EMERGENCY EXIT 5 16 EXTERNAL DOORS 17

TAB EFFECTIVITY CL-126C All A-1 ELECTRICAL TAB BATT OVHT 2 EMER BATT LOW 5 3 EMER BUS VOLTS ESS BUS FAULT 6 4 ESS BUS VOLTS 5 GEN AMPS HIGH GEN FAIL 6 EMERGENCY LIGHTS

7 EMER LIGHTS ENGINE 7 8 ENG FIRE FAIL ENGCMPTR FAULT 9 ENGINE CHIP 10 OIL FILTER Abnormal Engine Operation 11 Engine Airstart 8 12 ENG CMPTR ON (Auto Mode) ENG CMPTR - MAN or OFF 9 13 Engine Indications (EIs) 14 IGN 10 MAN 15 NAC REV 16 START 17 SYNC 11 UNL 18 Engine Overspeed Engine Shutdown in Flight TAB EFFECTIVITY CL-126C A-2 All TAB ENVIRONMENTAL/PRESSURIZATION BLEED OVHT 12 1 CAB DELTA P 13 2 CAB DUCT OVHT CAB PRESS FAIL 3 CAB PRESS MAN CABIN ALTITUDE 14 4

CKPT DUCT OVHT 5 ECS FAIL ECS FAULT 6 EMER PRESS ON 7 Inadvertent Activation of Emergency Airflow 15 OXYGEN OFF 8 OXYGEN QTY LOW 9 OXY PRESS HI PACK OVHT 16 10 PAX OXY FAIL 11 FLIGHT CONTROLS ELEVATOR DISC 12 FLAPS FAIL FLAPS FAULT 17 13 MACH TRIM FAIL 14 PRI TRIM FAIL ROLL DISC 15 RUD BOOST INOP 16 SEC TRIM FAIL 18 SPOILERS EXT 17 SPOILERS FAIL TAB EFFECTIVITY CL-126C All A-3 TAB SPOILER JAM STALLWARN FAIL 2 Jammed Stabilizer — Both PRI and SEC Trim Inoperative 19 3 FUEL DEFUEL OPEN 4 FUEL FILTER 5 FUEL HEATER FUEL IMBALANCE 6 FUEL QTY LOW 20 FUEL XFLO 7 FWSOV FAULT 8 STBY PUMP Fails ON HYDRAULICS 9 AUX HYD PMP LO 21 10 AUX HYD QTY LO BRK ACUM PRESS 11 MAIN HYD PRESS

12 INSTRUMENTS/AVIONICS AHRS OVHT 22 13 CNFG MISMATCH DAU 1 FAIL 14 DAU 2 FAIL 15 DAU ENG MISCMP 23 DAU SYS MISCMP 16 DU OVHT 24 17 IC OVHT IC 1 or 2 Failure 25 18 IC BUS FAIL LBS/KGS CONFIG TAB EFFECTIVITY CL-126C A-4 All INSTRUMENTS/AVIONICS (Cont) TAB PFD CHECK WARN AUDIO 1 25 WARN PWR FAIL 2 Air Data Computer (ADC) Failure — Single Air Data Computer (ADC) Failure — Dual 26 3 Display Unit Failure 4 Erroneous Pitot-Static Indications 27 Loss of PFD Attitude or Heading Displays 5 28 Loss of Standby Attitude Indicator Multi-Function Display (MFD) Annunciations 6 EICAS CHK 7 DGX

MAGX 8 MENU INOP 9 STAB TA NO BRG 29 10 TCAS FAIL 11 TERR FAIL TERR N/A 12 TGT WX 13

Primary Flight Display (PFD) Annunciations 14 ADCX ALT 15 30 AOA 16 AP (flash) AP (steady) 17 AP FAIL AP TEST TAB EFFECTIVITY CL-126C All A-5 TAB INSTRUMENTS/AVIONICS (Cont) ATT 2 CAS MSG 31 3 DGX FD FAIL 4 GS 5 HDG IAS 32 6 ILS LOC 7 MACH 8 GND PROX 33

MAGX 9 MAXSPD MIN 10 34 PIT 11 RA 12 —RA— RA FAIL 13 RB ROL 14 35 SGX 15 TCAS FAIL TGT 16 WIND SHR 17 WX 36 YD (flash) 18 YD (steady)

Change 1 EFFECTIVITY TAB CL-126C All A-6 Change 1 INSTRUMENTS/AVIONICS (Cont) TAB Radio Management Unit (RMU) Failure 1 LANDING GEAR/BRAKES ANTI-SKID FAIL 2 CPLT BRK FAULT 37 3 GEAR INBD BRK FAIL 4 NWS FAIL OUTBD BRK FAIL 38 5 PLT BRK FAULT 6 Landing Gear AUX HYD Extension Landing Gear Free Fall 39 7 Unsafe Gear Indication — DN Position 8 LANDINGS ANTI-ICING 9 Stabilizer Heat Failure Landing 40 (STAB TEMP LOW) 10 Wing & Stabilizer Heat Failure Landing (STAB & WING TEMP LOW) 11

Wing Heat Failure Landing 12 (WING TEMP LOW) 41 ELECTRICAL 13 Normal Electrical System Failure Landing EMERGENCY BRAKE 14 Emergency Brake Landing (NORM BRK FAIL red CAS) 42 15 (INBD BRK FAIL amber CAS) (OUTBD BRK FAIL amber CAS) 16 ENGINE 43 Single-Engine Landing 17 1

EFFECTIVITY TAB CL-126C All Change 1 A-7 LANDINGS (Cont) TAB FLIGHT CONTROLS 19 Aileron Jammed Landing 43 (ROLL DISC white CAS) 20 Aileron Trim Tab Jammed Landing 21 Elevator Jammed Landing 44 (ELEVATOR DISC white CAS) 22 Partial Flap Landing (FLAPS FAIL) 45 23 Rudder Jammed Landing Rudder Trim Tab Jammed Landing 24 Spoilers Extended Landing 46 25 (SPOILER EXT or SPOILER FAIL) Spoiler Jammed Landing 26 (L SPOILER JAM) (R SPOILER JAM) 47 27 Stabilizer Jammed Landing HYDRAULIC FAILURE 28 Main Hydraulic System Failure Landing 48 (MAIN HYD PRESS) 29 GEAR UP 49 30 Gear Up Landing THRUST REVERSER 50 31 Thrust Reverser Deployed Landing

34 1

18 3

EFFECTIVITY TAB All CL-126C A-8 Change 1 1LL AOA HT FAIL R AOA HT FAIL R AOA HT FAIL 1 LRLR AOA AOA HT HT FAIL FAIL

1. Respective AOA Circuit Breaker 2 (ANTI-ICE group [L or R PROBES HT])...... Set, or Pull & Reset 3 If AOA HT FAIL remains illuminated: 2. Fly out of icing conditions as soon as practical. 4

ICEICE DET DET FAIL FAIL 5

1. ICE DETECT Circuit Breaker 6 (copilot’s ANTI-ICE group) ...... Set, or Pull & Reset If SAT is between +10° C & -40° C, & visible moisture or night: 7 2. Thrust Levers ...... ≤ MCT 8 3. WING/STAB...... ON 4. L & R NAC ...... ON 9

ICEICE DETECTED DETECTED 10 ...... ≤ 1. Thrust Levers MCT 11 2. WING/STAB ...... ON 12 3. L & R NAC ...... ON 4. L & R WSHLD ...... Check On 13 5. HI FLOW ...... Off 14

17 2

EFFECTIVITY CL-126C All A-9 NACL NAC HT HT R NAC HT 2 R NAC HT LRLR NAC NAC HT HT 3 Affected engine: 1. IGN ...... ON 4 2. Engine N1 ...... Increase to Improve Airflow 5 3. NAC Circuit Breaker (ANTI-ICE group [L or R HEAT])...... Set, or Pull & Reset 6 If NAC HT remains illuminated: 4. Fly out of icing conditions as soon as possible. 7

8 NACL NAC HT HTFAIL FAIL ON ON RR NAC NAC HT HT FAIL FAIL ON ON LR NAC HT FAIL ON 9 LR NAC HT FAIL ON Affected engine: 10 1. NAC Circuit Breaker (ANTI-ICE group [L or R HEAT]) ...... Set, or Pull & Reset 11 LL PITOT PITOT HT HT 12 RR PITOT PITOT HT HT LRLR PITOT PITOT HT HT 13 1. Respective L or R PROBES ...... Check On 14 2. Respective PITOT Circuit Breaker (ANTI-ICE group [L or R PROBES HT]) ...... Set, or Pull & Reset 15 If PITOT HT remains illuminated: 3. Fly out of icing conditions as soon as possible. 16 4. Cross-check the three pitot-static systems. 17 If PITOT HT is accompanied by erroneous pitot-static indications: 5. Refer to Erroneous Pitot-Static Indications, Tab 27 . 18

EFFECTIVITY CL-126C All Change 1 A-10 Change 1 SATSAT HT HT FAIL FAIL

1. SAT Circuit Breaker (copilot’s ANTI-ICE group 1 [R PROBES HT])...... Set, or Pull & Reset 2 If SAT HT FAIL remains illuminated: 2. Fly out of icing conditions as soon as practical. 3

STABSTAB TEMP TEMP LOW LOW 4

1. Engine N1 ...... Increase 5 2. L & R WING/STAB HT Circuit Breaker (ANTI-ICE group)...... Set, or Pull & Reset 6 If STAB TEMP LOW remains illuminated: 7 3. Fly out of icing conditions as soon as possible. 4. Do not extend flaps beyond 8°. 8 5. Refer to Stabilizer Heat Failure Landing, Tab 40 . 9 STBY PITOT HT STBY PITOT HT 10 1. R PROBES ...... Check On 11 2. STBY PITOT Circuit Breaker (copilot’s ANTI-ICE group [R PROBES HT])...... Set, or Pull & Reset 12 If STBY PITOT HT remains illuminated: 3. Fly out of icing conditions as soon as practical. 13 4. Cross-check the three pitot-static systems. 14 If STBY PITOT HT is accompanied by erroneous pitot-static indications: 15 5. Refer to Erroneous Pitot-Static Indications, Tab 27 . 16 3 17 Change 2

EFFECTIVITY CL-126C All Change 2 A-11 WINGWING TEMP TEMP LOW LOW

2 1. L & R IGN...... ON

2. Engine N1 ...... Increase 3 3. L & R WING/STAB HT Circuit Breaker (ANTI-ICE group) ...... Set, or Pull & Reset 4 If WING TEMP LOW remains illuminated: 5 4. Fly out of icing conditions as soon as possible. 5. Do not extend flaps beyond 8°. 6 6. Refer to Wing Heat Failure Landing, Tab 41 . 7 7. Visually inspect wing for ice accumulation if possible. Use WING INSP light at night. 8 LL WSHLD WSHLD HT HT FAIL FAIL 9 RR WSHLD WSHLD HT HT FAIL FAIL LRLR WSHLD WSHLD HT HT FAIL FAIL 10 Respective windshield system or engine driven alternator has failed. 11 1. Respective L or R IGN...... ON, if in Icing Conditions 2. Respective WSHLD Circuit Breaker 12 (ANTI-ICE group [L or R HEAT]) ...... Set, or Pull & Reset 3. Respective L or R WSHLD ...... OFF, then On 13 4. ●If WSHLD HT FAIL remains illuminated: 14 a. Fly out of icing conditions as soon as possible. b. Moving the COCKPIT & CABIN TEMPERATURE knobs to HOT 15 will help reduce fogging. c. This checklist is complete. 16 4. ●If respective L or R WSHLD OVHT amber CAS is also illuminated, refer to WSHLD OVHT, Tab 3 . 17 3 18

EFFECTIVITY CL-126C Change 2 All A-12 Change 2 WSHLDL WSHLD OVHT OVHT R WSHLD OVHT R WSHLD OVHT 1 LRLR WSHLD WSHLD OVHT OVHT

1. Respective L or R WSHLD ...... OFF 2 2. Fly out of icing conditions as soon as practical. 3 3. Moving the COCKPIT & CABIN TEMPERATURE knobs to HOT will help reduce fogging. 4

Windshield Outer Ply Shattered or Cracked 5 Windshield structural integrity is maintained (outer ply is not structural). 1. Respective L or R WSHLD ...... OFF 6

2. Respective L or R IGN...... ON, if in Icing Conditions 7 3. Fly out of icing conditions as soon as practical. 8 4. Maintain 25,000 feet or below or minimum safe altitude. 5. MANUAL PRESS...... ON 9 6. MANUAL Rate Control...... UP, to Reduce Delta P ≤ 6.5 Maintain Cabin Altitude ≤ 8000 Feet 10 7. Moving the COCKPIT & CABIN TEMPERATURE knobs to HOT will help reduce fogging. 11 8. Land as soon as practical. 12

4 17

EFFECTIVITY CL-126C All Change 1 A-13 Engine Ice Ingestion 2 1. L & R IGN...... ON for Duration of Flight 2. Avoid any abrupt changes in pitch, yaw, or roll. 3 3. Fly out of icing conditions as soon as possible. 4 4. To determine extent of engine damage due to ice ingestion, proceed as follows: 5 a. Thrust Levers (one at a time): Slowly & cautiously retard to IDLE, then slowly & cautiously 6 advance & check for vibration/abnormal noise on each engine. b. If either engine flames out: Airstart in accordance with 7 Engine Airstart, Tab 8 . After restart, repeat step 4, but stay below engine speed at which engine flamed out. 8 If ice damage has been experienced: c. Engine N1 ...... Low as Possible 9 Sufficient for Anti-icing & Cabin Pressure 5. Land as soon as practical. 10

11 Inadvertent Icing Encounter 1. Thrust Levers ...... ≤ MCT 12 2. WING/STAB ...... ON 13 3. L & R NAC ...... ON 4. L & R WSHLD ...... Check On 14 5. HI FLOW ...... Off 15 6. Do not extend flaps beyond 8° until the wing/stab anti-ice system has been on for 2 minutes. 16 APAP AIL AIL MISTRIM MISTRIM 17 If condition persists: 18 1. Flight Controls...... Hold Firmly 2. Airspeed ...... ≤ 0.78 MI 3. Autopilot ...... Use Control Wheel Trim Switch to Disengage Change 2 EFFECTIVITY CL-126C All A-14 Change 2 4. Fuel Balance...... Check & Correct 5. Retrim aircraft if necessary. 1 6. Autopilot...... As Desired 7. Airspeed ...... As Desired 2 If AP AIL MISTRIM recurs and condition persists:

8. Airspeed ...... ≤ 0.78 MI 3 9. Obtain maintenance before next flight. 4

APAP ELEV ELEV MISTRIM MISTRIM 5

If condition persists: 6 1. Flight Controls ...... Hold Firmly 2. Autopilot...... Use Control Wheel Trim Switch to Disengage 7 3. Retrim aircraft if necessary. 8

APUAPU AMPS AMPS HIGH HIGH 9

1. Electrical Load ...... Reduce As Required 10

APUAPU FAILFAIL APU 11 FAIL 12 1. APU MASTER ...... Off 2. ●If APU FAIL indication extinguishes: 13 a. Inspect APU and aircraft tailcone area prior to flight to ensure airworthiness. 14 b. APU Fire Bottle ...... Proper Pressure 15 2. ●If APU FAIL indication remains illuminated: a. Do not take off. 16

5 17

EFFECTIVITY CL-126C All Change 1 Change 1 A-15 EMERGENCYEMERGENCY EXIT EXIT

2 DO NOT APPROACH HATCH 3 1. NO SMOKING BELTS...... BELTS

4 EXTERNALEXTERNAL DOORS DOORS

5 In flight: 1. Avoid slips or skids that could open doors. 6 LL BATT BATT OVHT OVHT 7 RR BATT BATT OVHT OVHT LRLR BATT BATT OVHT OVHT 8 (Nickel-Cadmium Batteries Only) 9 1. Respective L or R BATT...... OFF 10 2. EICAS ...... Select ELEC or SUMRY Monitor Battery Temperature 11 If the respective battery temperature continues to increase: 3. Land as soon as practical. 12

13 EMEREMER BATT BATT LOW LOW On the ground: 14 1. EICAS ...... Select ELEC or SUMRY 15 2. In order to ensure adequate emergency power endurance in the event of a dual generator failure, allow time for battery to charge & 16 EMER BATT LOW illumination to extinguish prior to flight. 3. This checklist is complete. 17 In flight: 1. EICAS ...... Select ELEC or SUMRY 18 2. Land as soon as practical.

EFFECTIVITY CL-126C All Change 1 A-16 Change 1 If conditions permit: 3. Pull circuit breakers, pilot’s & copilot’s circuit breaker panels, with red rings (EMER BATT bus) one at a time to isolate a possible 1 faulted component. Allow time after pulling each circuit breaker for battery to recharge. 2 4. This checklist is complete. 3 EMEREMER BUS BUS VOLTS VOLTS 4 1. EICAS...... Select ELEC or SUMRY 2. ●If EMER-V bus voltage is greater than 29.6 VDC: 5 ■ a. On the ground: 6 (1) Respective L or R, or APU (if installed) GEN ...... OFF or 7 EXT PWR...... AVAIL 8 or EXT PWR Source ...... Adjust 9 (2) This checklist is complete. a. ■In flight: 10 (1) Respective L or R GEN ...... OFF 11 (2) Land as soon as practical. (3) This checklist is complete. 12 2. ●If EMER-V bus voltage is less than 22 VDC: 13 a. ■On the ground: (1) Allow time for EMER BATT to recharge prior to flight. 14 (2) This checklist is complete. 15 a. ■In flight: (1) BUS Circuit Breaker 16 (pilot’s ELECTRICAL group [EMER BUS])...... Set (2) EMER BATT ...... On 17 (EMER illuminated) (3) 6Land as soon as practical. 6 EFFECTIVITY CL-126C All Change 1 A-17 If flight time will exceed 1.0 hour (EMER BATT duration): (4) Notify passengers of oxygen mask deployment. Instruct 2 passengers — “Do not pull lanyard. Do not use the masks unless instructed otherwise”. 3 (5) DEPLOY (PAX OXYGEN)...... ON (6) DAU (REVERSION)...... Select B 4 (7) Standby Attitude ...... Pull & Cage 5 Standby Attitude will be Inoperative (8) Standby altimeter vibrator will be inoperative. Do not refer- 6 ence this instrument for primary altitude. (9) Refer to Landing Gear Free Fall, Tab 39 . Normal 7 landing gear control will be inoperative. (10) Refer to Emergency Braking, Tab 16 . Inboard brakes 8 are inoperative. (11) This checklist is complete. 9 L ESS BUS FAULT 10 L ESS BUS FAULT R ESS BUS FAULT LR ESS BUS FAULT 11 LR ESS BUS FAULT The respective essential bus contactor has failed open on the ground. 12 L ESS BUS VOLTS 13 L ESS BUS VOLTS RR ESS ESS BUS BUS VOLTS VOLTS LRLR ESS ESS BUS BUS VOLTS VOLTS 14 1. EICAS ...... Select ELEC or SUMRY 15 2. ●If respective L or R ESS bus voltage is greater than 29.6 VDC: ■ 16 a. On the ground: (1) Respective L or R, or APU (if installed) GEN ...... OFF 17 or EXT PWR ...... AVAIL 18 or EXT PWR Source...... Adjust (2) This checklist is complete. 7 EFFECTIVITY CL-126C All A-18 Change 1 a. ■In flight: (1) Respective L or R GEN ...... OFF 1 (2) Refer to LR GEN FAIL, Tab 4 , or single (L or R) GEN FAIL, Tab 7 . 2 (3) Land as soon as practical. (4) This checklist is complete. 3 2. ●If respective L or R ESS bus voltage is less than 22 VDC: a. ■On the ground: 4 (1) Connect an EXT PWR source or switch on a generator to 5 charge the batteries. Allow time for batteries to recharge prior to flight. 6 (2) This checklist is complete. a. ■In flight: 7 (1) BUS Circuit Breaker (pilot’s or copilot’s ELECTRICAL group [L or R ESS BUS]) ...... Set 8 (2) Respective L or R GEN ...... Check On 9 (3) Land as soon as practical. (4) This checklist is complete. 10

EFFECTIVITY CL-126C All Change 2 Change 2 A-19 LL GEN GEN AMPS AMPS HIGH HIGH R GEN AMPS HIGH 2 R GEN AMPS HIGH LRLR GEN GEN AMPS AMPS HIGH HIGH

3 1. EICAS ...... Select ELEC or SUMRY 2. Respective L or R NON-ESS ...... OFF 4 3. Respective Electrical Load...... Reduce 5 If GEN AMPS HIGH remains illuminated & AMPS are greater than 350 & aircraft load has been reduced: 6 4. Respective L or R BATT...... OFF If GEN AMPS HIGH remains illuminated & AMPS are greater than 7 350: 5. Respective L or R GEN...... OFF 8 6. BUS-TIE...... Open 9 The respective main and main avionics buses will not be powered.

10 GENL GEN FAIL FAIL R GEN FAIL 11 1. Respective L or R GEN Circuit Breaker 12 (ELECTRICAL group)...... Set, or Pull & Reset 2. Engine N2 ...... ≥ 80% 13 3. Respective L or R GEN...... Depress (Approx 1 Sec) If GEN FAIL remains illuminated: 14 4. L & R NON-ESS...... As Desired 15 5. Remaining (non-affected) GEN AMPS ...... Monitor

16 EMEREMER LIGHTS LIGHTS

17 1. EMER LIGHTS...... ARM

EFFECTIVITY CL-126C All A-20 Change 1 LL ENG ENG FIRE FIRE FAIL FAIL R ENG FIRE FAIL RLR ENG ENG FIRE FIRE FAIL FAIL 1 LR ENG FIRE FAIL 2 The engine fire detection system has detected a fault on the ground that may not allow the detection system to indicate a fire. 3

ENGCMPTRL ENGCMPTR FAULT FAULT 4 RR ENGCMPTR ENGCMPTR FAULT FAULT LR ENGCMPTR FAULT LR ENGCMPTR FAULT 5 1. Engine Instruments...... Monitor 2. ENG SYNC...... OFF 6 3. Respective Thrust Lever...... ≤ MCR 7 4. Respective L or R ENG CMPTR...... OFF, then ON If ENGCMPTR FAULT remains illuminated: 8 5. Respective L or R ENG CMPTR...... MAN & Continue Flight 9 Engine acceleration & deceleration in MAN mode will be slower than normal. The slower response should be considered in a go-around condition. Refer to applicable thrust setting performance data, Perfor- 10 mance Checklist, to obtain rated thrust. The thrust lever detents do not automatically set thrust in MAN mode. 11

LL ENGINE ENGINE CHIP CHIP 12 RR ENGINE ENGINE CHIP CHIP LR ENGINE CHIP 13 LR ENGINE CHIP Metal particles have been detected in the oil while on the ground. 14

15 LL OIL OIL FILTER FILTER RR OIL OIL FILTER FILTER LR OIL FILTER 16 LR OIL FILTER The engine oil filter has an impending bypass while on the ground. 17 8

EFFECTIVITY CL-126C All Change 1 A-21 Abnormal Engine Operation 2 Fan speed (N1) or turbine speed (N2) is decreasing or inappropriate for thrust lever position with no ENGCMPTR FAULT amber CAS. 3 1. Engine Instruments...... Monitor 4 2. ENG SYNC ...... OFF 3. Respective Thrust Lever ...... IDLE 5 4. Respective L or R ENG CMPTR ...... MAN 5. Land as soon as practical. 6

7 Engine Airstart ENG CMPTR ON (Auto Mode) 8 Auto Mode Airstart Envelope

45-178 9 35000

10 30000 11 25000

12 WINDMILL OR STARTER 20000 ASSISTED 13

15000 STARTER 14 ASSISTED

15 PRESSURE ALTITUDE — FEET 10000

16 5000 17 0

18 50 100 150 200 250 300 350 AIRSPEED — KIAS

EFFECTIVITY CL-126C All A-22 Change 1 ENG CMPTR ON (Auto Mode) (Cont) Before Start Affected engine: 1 1. Complete Engine Shutdown in Flight, Tab11 . 2 2. Assure that aircraft is within appropriate Airstart Envelope. 3. ENG CMPTR ...... ON 3 4. Fuel Supply...... Check Available from Wing Tank 5. FUEL Panel as Follows: 4 a. XFLOW (FUEL)...... Closed 5 b. STBY (FUEL) ...... ON 6. FIRE (ENGINE) ...... Check Open 6 7. WSHLD...... OFF 8. Electrical Load ...... Reduce 7 9. WING/STAB...... Off 8 10. NAC ...... Off 11. BLEED...... OFF 9 12. Conduct the following windmill or starter assisted airstart. Start 10 Windmill Airstart Affected engine: 11

1. Thrust Lever (at minimum 10% N2) ...... IDLE 12 2. IGN & FUEL FLOW ...... Check 3. ITT ...... Check Rise 13 If no indication of light-off is obtained within 20 seconds of achieving thrust lever movement to idle: 14 a. Thrust Lever ...... CUTOFF b. Repeat airstart or refer to Engine Shutdown in Flight, 15 Tab11 . 4. Engine Instruments...... Normal 16 9 17

EFFECTIVITY CL-126C All Change 2 Change 2 A-23 ENG CMPTR ON (Auto Mode) (Cont) Starter Assisted Airstart 2 Affected engine: 1. START...... ON 3 2. Thrust Lever (at minimum 10% N2)...... IDLE 4 3. IGN & FUEL FLOW...... Check 4. ITT ...... Check Rise 5 If no indication of light-off is obtained within 20 seconds of achieving thrust lever movement to idle: 6 a. Thrust Lever ...... CUTOFF 7 b. Repeat airstart or refer to Engine Shutdown in Flight, Tab11 . 8 5. Engine Instruments...... Normal

After Start 9 Affected engine: 10 1. FUEL Panel as Follows: a. STBY (FUEL) ...... Off, as Desired 11 b. XFLOW (FUEL) ...... As Desired

12 2. GEN ...... On 3. WSHLD...... On 13 4. WING/STAB ...... As Required 5. NAC ...... As Required 14 6. BLEED ...... On 15 7. RMU (ATC/TCAS)...... As Desired

EFFECTIVITY Change 1 CL-126C All A-24 Change 1 ENG CMPTR - MAN or OFF Manual Mode Airstart Envelope 45-179 35000 1

2 30000 3 25000 4

20000 5

15000 6

PRESSURE ALTITUDE — FEET WINDMILL OR 7 10000 STARTER STARTER ASSISTED ASSISTED 8 5000 9

0 10 50 100 150 200 250 300 350 AIRSPEED — KIAS 11 Before Start Affected engine: 12 1. Complete Engine Shutdown in Flight, Tab11 . 2. Assure that aircraft is within appropriate Airstart Envelope. 13 3. ENG CMPTR ...... MAN or OFF (MAN recommended) 14 4. Fuel Supply...... Check Available from Wing Tank 5. FUEL Panel as Follows: 15

a. XFLOW (FUEL)...... Closed 16 b. STBY (FUEL) ...... ON 6. FIRE (ENGINE) ...... Check Open 17 10

EFFECTIVITY CL-126C All Change 2 Change 2 A-25 7. WSHLD...... OFF 8. Electrical Load ...... Reduce 2 9. WING/STAB ...... Off 3 10. NAC ...... Off 11. BLEED ...... OFF 4 12. Conduct the following windmill or starter assisted airstart. Start 5 Windmill Airstart 6 Affected engine: 1. IGN ...... ON

7 2. Thrust Lever (at minimum 10% N2)...... IDLE 3. IGN & FUEL FLOW...... Check 8 4. ITT ...... Check Rise 9 If no indication of light-off is obtained within 20 seconds of achieving thrust lever movement to idle: 10 a. Thrust Lever ...... CUTOFF b. IGN ...... Off 11 c. Repeat airstart or refer to Engine Shutdown in Flight, Tab11 . 12 5. Engine Instruments...... Normal 13 Starter Assisted Airstarts Affected engine: 14 1. IGN ...... ON 2. START...... ON 15 3. Thrust Lever (at minimum 10% N2)...... IDLE 16 4. IGN & FUEL FLOW...... Check 5. ITT ...... Check Rise 17 If no indication of light-off is obtained within 20 seconds of achieving thrust lever movement to idle: 18 a. Thrust Lever ...... CUTOFF b. START ...... Off

EFFECTIVITY CL-126C All A-26 Change 1 c. IGN...... Off d. Repeat airstart or refer to Engine Shutdown in Flight, Tab11 . 1 6. Engine Instruments...... Normal After Start 2 Affected engine: 1. IGN ...... Off 3 2. FUEL Panel as Follows: 4 a. STBY (FUEL) ...... Off, as Desired b. XFLOW (FUEL)...... As Desired 5 3. GEN...... On 6 4. WSHLD...... On 5. WING/STAB...... As Required 7 6. NAC ...... As Required 8 7. BLEED...... On 8. RMU (ATC/TCAS)...... As Desired 9

10 Engine Indications (EIs) IGNIGN 11 1. CH A & CH B Circuit Breakers (respective L or R IGN group [ENGINE]) ...... Set, or Pull & Reset 12 If IGN remains illuminated: 13 2. Airstarts will not be possible. 14 MANMAN Refer to L or R ENGCMPTR FAULT, Tab7 . 15

NACNAC 16 Refer to L or R NAC HT, Tab2 or L or R NAC HT FAIL ON, Tab2 . 17

11 EFFECTIVITY Change 2 CL-126C All Change 2 A-27 REVREV Thrust reverser is armed in flight OR on the ground with a TLA (thrust lever 2 angle) greater than MCR. 3 In flight: 1. Respective Thrust Reverser Lever...... Stow 4 2. Respective DEPLOY Circuit Breaker (ENGINE group)...... Pull 3. Continue flight. 5 STARTSTART 6 Ground Start Affected engine: 7 1. START...... Off 8 If START remains illuminated, the starter is still engaged: 2. Thrust Lever ...... CUTOFF 9 3. Turn off all electrical power. 10 Starter-Assisted Airstart 1. Complete airstart procedure. 11 2. Continue flight. If START remains illuminated, the starter is still engaged: 12 3. At shutdown, L & R BATT ...... OFF 13 SYNCSYNC 14 1. ENG SYNC ...... OFF

15 UNLUNL On the ground, the thrust reverser is in transition between stow and deploy. 16 It will temporarily illuminate during normal thrust reverser deployment. If illumination continues for more than 3 seconds, an abnormal condition exists & the master caution is tripped. 17

Change 1 EFFECTIVITY CL-126C All A-28 Change 1 Engine Overspeed

Affected engine: 1 1. Thrust Lever...... Retard 2 If engine does not respond: 2. Thrust Lever...... CUTOFF 3 If engine does not respond: 3. FIRE (ENGINE) ...... FIRE PUSH 4 4. After engine has shut down, ENG CMPTR...... MAN 5 5. Refer to Engine Shutdown in Flight, Tab 11 . 6 Engine Shutdown in Flight 7 Affected engine: 1. ENG SYNC...... OFF 8 2. Thrust Lever...... CUTOFF 3. Rudder Trim ...... As Required 9 4. Yaw Damper ...... As Required 10 5. Autopilot...... As Desired 6. Electrical Load ...... Reduce, Within Generator Limits 11 7. WSHLD ...... OFF Avoid flight in icing conditions 12 8. BLEED...... OFF 13 9. RMU (ATC/TCAS)...... TA ONLY 10. Monitor fuel balance. Crossflow as required. 14 11. Land as soon as practical. 15 12. Refer to En Route Climb Gradient — Single Engine chart, Section V of the AFM. 16 13. Refer to Engine Airstart Tab 8 , if applicable, or Single- Engine Landing, Tab 43 , or Thrust Reverser Deployed Land- ing, Tab 50 , as appropriate. 17

12 EFFECTIVITY CL-126C All Change 1 A-29 LL BLEED BLEED OVHT OVHT R BLEED OVHT LRR BLEEDBLEED OVHTOVHT 2 LR BLEED OVHT

3 L or R BLEED OVHT Illuminates 1. Respective BLEED ...... OFF 4 Allow Time for System to Cool 2. ●If BLEED OVHT continues: 5 a. Reduce N1 on respective engine. 6 b. Maintain 41,000 feet or below. Avoid flight in icing conditions. c. Land as soon as practical. 7 d. This checklist is complete. ● 8 2. If BLEED OVHT extinguishes, respective BLEED may be selected On. 9 If BLEED OVHT recurs: 3. Respective BLEED ...... OFF 10 4. Maintain 41,000 feet or below. Avoid flight in icing conditions. 5. This checklist is complete. 11 LR BLEED OVHT Illuminates 12 1. L BLEED ...... OFF 2. Reduce N1 on right engine. Allow time for system to cool. 13 3. ●If LR BLEED OVHT continues: 14 a. L BLEED...... On b. Right Engine N1...... As Required 15 c. R BLEED...... OFF

d. Reduce N1 on left engine. Allow time for system to cool. 16 If LR BLEED OVHT continues: 17 e. Maintain 41,000 feet or below. Avoid flight in icing conditions. f. Land as soon as practical. 18 g. This checklist is complete.

Change 2 12 EFFECTIVITY CL-126C 45-002All & on A-30 not modified by SB 45-72-1 Change 2 LL BLEED BLEED OVHT OVHT R BLEED OVHT 2 R BLEED OVHT LRLR BLEED BLEED OVHT OVHT

3 L or R BLEED OVHT Illuminates 1. Affected Thrust Lever...... Advance or Retard 4 If BLEED OVHT continues: 5 2. Respective BLEED ...... OFF Allow time for system to cool 6 3. ●If BLEED OVHT continues: a. Reduce N1 on respective engine. 7 b. Maintain 41,000 feet or below. Avoid flight in icing conditions. 8 c. Land as soon as practical. d. This checklist is complete. 9 3. ●If BLEED OVHT extinguishes, respective BLEED may be selected On. 10 If BLEED OVHT recurs:

11 4. Respective BLEED ...... OFF 5. Maintain 41,000 feet or below. Avoid flight in icing conditions. 12 6. This checklist is complete. LR BLEED OVHT Illuminates 13 1. Thrust Levers ...... Advance or Retard 14 If BLEED OVHT continues: 2. L BLEED ...... OFF 15 3. Reduce N1 on right engine. Allow time for system to cool. 12 16

EFFECTIVITY CL-126C 45-002All & on A-30.1 modified by SB 45-72-1 Change 2 If either L or R BLEED OVHT extinguishes: h. BLEED (on side that caution extinguished)...... On i. Refer to the L or R BLEED OVHT procedure above. 1 ● 3. If either L or R BLEED OVHT extinguishes: 2 a. BLEED (on side that caution extinguished)...... On b. Refer to the L or R BLEED OVHT procedure above. 3

13 6 7 13 8

EFFECTIVITY CL-126C 45-002All & on Change 2 not modified by SB 45-72-1 A-31 4. ●If LR BLEED OVHT continues: a. L BLEED ...... On 1 b. Right Engine N1 ...... As Required c. R BLEED...... OFF 2 d. Reduce N1 on left engine. Allow time for system to cool. If LR BLEED OVHT continues: 3 e. Maintain 41,000 feet or below. Avoid flight in icing conditions. 4 f. Land as soon as practical. g. This checklist is complete. 5 If either L or R BLEED OVHT extinguishes: 6 h. BLEED (on side that caution extinguished)...... On i. Refer to the L or R BLEED OVHT procedure above. 7 4. ●If either L or R BLEED OVHT extinguishes: 8 a. BLEED (on side that caution extinguished)...... On b. Refer to the L or R BLEED OVHT procedure above. 9

13 10

EFFECTIVITY CL-126C 45-002All & on Change 2 modified by SB 45-72-1 A-31.1 CABCAB DELTA DELTA P P

2 1. EICAS ...... Select ECS & Check DELTA P

3 2. L & R PRESS Circuit Breakers (pilot’s & copilot’s ENVIRONMENTAL & ENVIR group)...... Pull & Reset ● 4 3. If DELTA P is greater than 9.5 psid: a. MANUAL PRESS ...... ON 5 b. MANUAL Rate Control ...... UP, to Reduce Delta P If CAB DELTA P remains illuminated: 6 c. One L or R BLEED...... OFF

7 d. Adjust N1 on opposite engine to control cabin pressurization. e. Maintain 41,000 feet or below. Avoid flight in icing conditions. 8 If still unable to regulate the overpressurization: 9 f. EMER DEPRESS...... ON g. Descend to reduce differential pressure, but not below mini- 10 mum safe altitude. h. This checklist is complete. 11 3. ●If DELTA P is less than -0.5 psid: 12 a. MANUAL PRESS ...... ON b. MANUAL Rate Control ...... DN, to increase Delta P 13 If CAB DELTA P remains illuminated:

14 c. Decrease aircraft descent rate. d. This checklist is complete. 15

EFFECTIVITY CL-126C All A-32 Change 1 CABCAB DUCT DUCT OVHT OVHT

1. EICAS...... Select ECS 1

2. MANUAL TEMP...... ON 2 3. CABIN TEMPERATURE COLD-HOT Knob...... Full COLD 4. TEMP CONT (ECS Page) ...... Verify CAB Moving to 3 or at C (cold) Position If CAB DUCT OVHT remains illuminated: 4 5. L BLEED Circuit Breaker (pilot’s ENVIRONMENTAL group)...... Pull 5 Allow time for air to cool 6 6. Maintain 41,000 feet or below. With L BLEED — On, anti-ice airflow is available to the respective anti-ice valves. 7 If CAB DUCT OVHT remains illuminated: 7. R BLEED Circuit Breaker (copilot’s ENVIR group) ...... Pull 8 Allow time for air to cool. Avoid flight in icing conditions.

8. Adjust N1 to control cabin pressurization. Spoilers may be required 9 for descent. If CAB DUCT OVHT remains illuminated or icing conditions can 10 not be avoided: 9. L & R BLEED Circuit Breakers (pilot’s & copilot’s 11 ENVIRONMENTAL & ENVIR group) ...... Set 10. EMER PRESS ...... ON 12

11. One L or R BLEED ...... OFF 13 12. Reduce N1 on engine with bleed air on. 14

16 14 17 Change 2

EFFECTIVITY CL-126C All Change 2 A-33 LRLR CAB CAB PRESS PRESS FAIL FAIL

2 1. L & R PRESS Circuit Breakers (pilot’s & copilot’s ENVIRONMENTAL & ENVIR group) ...... Pull & Reset 3 If LR CAB PRESS FAIL remains illuminated: 4 2. Maintain below 8000 feet or minimum safe altitude. Land below 8000 feet field elevation, if possible. 5 When below 8000 feet: 3. PACK...... OFF 6 CAB PRESS MAN 7 CAB PRESS MAN 1. MANUAL Rate Control ...... As Required 8 CABIN ALTITUDE 9 CABIN ALTITUDE Cabin Altitude Exceeds 8500 Feet 10 1. Crew Oxygen Masks...... Don &100% 11 2. If aircraft is climbing, stop climbing and level off at (or descend to) the nearest appropriate altitude. 12 3. Pilot & Copilot MIC/MASK...... MASK 4. Pilot & Copilot INPH...... INPH 13 5. PACK...... Check On 14 6. L & R BLEED ...... Check On 7. EICAS ...... Select ECS & Check CABIN ALT 15 8. ●If cabin altitude continues to climb: 16 a. MANUAL PRESS ...... ON b. MANUAL Rate Control Knob...... DN As Required 17 If cabin altitude continues to climb:

18 c. EMER PRESS...... ON 8. ●If cabin altitude stabilizes at a safe altitude, continue flight. Con- tinued use of the oxygen system is at the crew’s discretion.

EFFECTIVITY CL-126C All A-34 Change 1 CKPTCKPT DUCT DUCT OVHT OVHT 1. EICAS...... Select ECS 1 2. MANUAL TEMP...... ON 2 3. COCKPIT TEMPERATURE COLD-HOT Knob...... Full COLD 4. TEMP CONT (ECS Page) ...... Verify CKPT Moving to 3 or at C (cold) Position If CKPT DUCT OVHT remains illuminated: 4 5. L BLEED Circuit Breaker (pilot’s ENVIRONMENTAL group)...... Pull 5 Allow time for air to cool 6. Maintain 41,000 feet or below. With L BLEED — On, anti-ice airflow 6 is available to the respective anti-ice valves. If CKPT DUCT OVHT remains illuminated: 7 7. R BLEED Circuit Breaker (copilot’s ENVIR group) ...... Pull 8 Allow time for air to cool. Avoid flight in icing conditions. 8. Adjust N1 to control cabin pressurization. Spoilers may be required 9 for descent. If CKPT DUCT OVHT remains illuminated or icing conditions 10 cannot be avoided: 9. L & R BLEED Circuit Breakers (pilot’s & copilot’s 11 ENVIRONMENTAL & ENVIR group) ...... Set 10. EMER PRESS ...... ON 12 11. One L or R BLEED ...... OFF 13 12. Reduce N1 on engine with bleed air on. 14 LRLR ECS ECS FAIL FAIL 15 1. L & R BLEED Circuit Breakers (pilot’s & copilot’s ENVIRONMENTAL & ENVIR group)...... Set, or Pull & Reset 16 If LR ECS FAIL remains illuminated: 2. Maintain 41,000 feet or below. 17 15

Change 2 EFFECTIVITY CL-126C All Change 2 A-35 LL ECS ECS FAULT FAULT R ECS FAULT 2 R ECS FAULT 1. Respective L or R BLEED Circuit Breaker (respective 3 ENVIRONMENTAL or ENVIR group)...... Set, or Pull & Reset

4 LL EMER EMER PRESS PRESS ON ON RR EMER EMER PRESS PRESS ON ON 5 LRLR EMER EMER PRESS PRESS ON ON Inadvertent Activation of Emergency Airflow 6 If cabin altitude is below 9500 feet: 7 1. EMER PRESS ...... Off 2. ●If L or R EMER PRESS ON remains illuminated: 8 a. Respective L or R BLEED ...... OFF If Emergency Flow Stops, 9 Leave Switch OFF b. Maintain 41,000 feet or below. Avoid flight in icing conditions. 10 c. This checklist is complete. 11 2. ●If LR EMER PRESS ON remains illuminated: a. One (L or R) BLEED...... OFF 12 b. Adjust N1 on engine supplying EMER air to modulate cabin temperature. 13 c. Maintain 41,000 feet or below. Avoid flight in icing conditions. 14 d. Land as soon as practical. If emergency airflow continues: 15 e. Reduce N1 on respective engine as low as practical. 16 f. Respective L or R BLEED Circuit Breaker (respective ENVIRONMENTAL or ENVIR group)...... Pull 17 Emergency pressurization may not be available through the affected side. The corresponding EMER PRESS ON amber 18 CAS will extinguish, however, the emergency valve may not close.

EFFECTIVITY CL-126C All A-36 Change 1 g. Respective L or R BLEED ...... On Allows anti-ice airflow to the respective anti-ice valves. h. Land as soon as possible. 1 i. This checklist is complete. 2

OXYGENOXYGEN OFF OFF 3 On the ground: 4 1. Select Oxygen Bottle Pressure Regulator ON prior to flight or service oxygen bottle. 5 2. This checklist is complete. In flight: 6 1. EICAS...... Select ECS 2. OXY QTY...... Check 7 3. Crew Masks ...... Test 8 4. ●If oxygen quantity is satisfactory: a. Continue flight. 9 b. This checklist is complete. 10 4. ●If oxygen quantity is not satisfactory: a. Maintain below 25,000 feet or minimum safe altitude. 11 b. Replan flight as necessary. c. This checklist is complete. 12

13 OXYGENOXYGEN QUANTITY QTY LOW LOW

On the ground: 14 1. EICAS...... Select ECS 15 2. OXY QTY...... Check 3. Using the oxygen quantity mission planning table on page S-7, 16 determine if the oxygen quantity is sufficient for the planned mission. 17 16

EFFECTIVITY CL-126C All Change 1 A-37 If oxygen quantity is not satisfactory: 4. Refer the problem to maintenance personnel for correction. 2 In flight: 3 1. EICAS ...... Select ECS 2. OXY QTY ...... Check 4 3. Using the oxygen duration chart on page S-6, determine if the oxygen quantity is sufficient based on the cabin altitude and the number 5 of passengers. If oxygen quantity is not satisfactory: 6 4. Maintain below 25,000 feet or minimum safe altitude.

7 5. Replan flight as necessary.

8 OXYOXY PRESS PRESS HI HI

9 Oxygen bottle is over serviced. Oxygen quantity digits will be amber dashed. 10 On the ground: 1. Refer problem to maintenance personnel for correction. 11 In flight: 1. Continue flight. 12

13 PACKPACK OVHT OVHT 1. HI FLOW ...... Off 14 2. APU BLEED (if installed) ...... Off 15 If PACK OVHT remains illuminated: 3. L or R BLEED ...... Select one OFF 16 4. Reduce N1 on opposite engine as low as practical. 17 5. Maintain 41,000 feet or below. Avoid flight in icing conditions.

EFFECTIVITY CL-126C All A-38 Change 1 If PACK OVHT remains illuminated: 6. EMER PRESS ...... ON 1 7. PACK ...... OFF 8. Adjust thrust lever on engine supplying EMER PRESS air to modu- 2 late cabin temperature. 3 PAXPAX OXY OXY FAIL FAIL 4 1. Notify passengers of mask deployment and mask use if necessary. 2. DEPLOY (PAX OXYGEN) ...... ON 5 3. ●If passenger oxygen masks deploy: a. Continue flight. 6 b. This checklist is complete. 7 3. ●If passenger oxygen masks do not deploy: a. Maintain below 25,000 feet or minimum safe altitude. 8 b. Replan flight as necessary. 9 c. This checklist is complete. 17 10

EFFECTIVITY CL-126C All Change 1 A-39 ELEVATORELEVATOR DISC DISC 2 1. Obtain maintenance prior to flight.

3 FLAPSFLAPS FAIL FAIL 4 1. EICAS ...... Select FLT 2. FLAP CTRL Circuit Breaker (copilot’s FLIGHT group)...... Set 5 3. FLAPS ...... Detent Closest to Actual Flap Position 6 4. SYS TEST/RESET (FLAP RESET) ...... Press 5. SYS TEST/RESET (FLAPS)...... Press 7 6. SYS TEST/RESET (FLAP RESET) ...... Press If FLAPS FAIL remains illuminated: 8 7. Refer to Partial Flap Landing, Tab 45 . 9 FLAPSFLAPS FAULT FAULT 10 1. EICAS ...... Select FLT 11 2. FLAP CTRL Circuit Breaker (copilot’s FLIGHT group) ...... Set 3. FLAPS ...... Select New Detent, 12 Then Detent Closest to Actual Flap Position 4. ●If FLAPS FAULT extinguishes: 13 a. Select flaps as desired. 14 b. This checklist is complete. 4. ●If FLAPS FAULT remains illuminated: 15 a. SYS TEST/RESET (FLAP RESET)...... Press 16 b. This checklist is complete.

EFFECTIVITY CL-126C All A-40 Change 1 MACHMACH TRIM TRIM FAIL FAIL 1. PITCH TRIM ...... PRI 1 2. PRI PITCH Circuit Breaker (pilot’s FLIGHT group [TRIM])...... Set 2 If MACH TRIM FAIL remains illuminated: 3 3. ●If autopilot is disengaged:

a. Airspeed...... ≤ Mach trim off MMO 4 b. This checklist is complete. 5 3. ●If autopilot disengagement is desired: a. Airspeed...... ≤ Mach trim off MMO 6 b. Autopilot ...... Disengage Engage yaw damper as required. 7 c. This checklist is complete. 8

PRIPRI TRIM TRIM FAIL FAIL 9 1. PITCH TRIM ...... SEC 10 2. SEC NDN-NUP...... As Required to Maintain Trim 3. PRI PITCH Circuit Breaker (pilot’s FLIGHT group [TRIM]) ...... Pull 11 If neither PRI nor SEC pitch trim is available: 12 4. Refer to Jammed Stabilizer — Both PRI and SEC Trim Inopera- tive, Tab 19 . 13

ROLLROLL DISC DISC 14 1. Align control wheels. 15 2. Push the small roll disconnect lever forward. 3. Verify ROLL DISC CAS extinguishes. 16

17 18

EFFECTIVITY CL-126C All Change 1 A-41 RUDRUD BOOST BOOST INOP INOP 2 On the ground: 1. AFCS SERVOS Circuit Breaker 3 (pilot’s FLIGHT group) ...... Set, or Pull & Reset 2. Control Wheel Master (MSW)...... Depress & Release 4 3. NOSE STEER...... ON If RUD BOOST INOP remains illuminated: 5 4. RUD BOOST Switch ...... OFF 6 Refer to RUD BOOST INOP, page A/S-8. In flight: 7 1. AFCS SERVOS Circuit Breaker (pilot’s FLIGHT group) ...... Set, or Pull & Reset 8 2. Control Wheel Master (MSW)...... Depress & Release

9 3. Yaw Damper...... As Required

10 SECSEC TRIM TRIM FAIL FAIL

11 1. PITCH TRIM ...... PRI 2. Control Wheel Trim Switch...... As Required to Maintain Trim 12 3. SEC PITCH Circuit Breaker (copilot’s FLIGHT group [TRIM])...... Pull 13 4. Do not engage autopilot. If neither PRI nor SEC pitch trim is available: 14 5. Refer to Jammed Stabilizer — Both PRI and SEC Trim Inopera- 15 tive, Tab 19 .

16 SPOILERSSPOILERS EXT EXT 17 Depending on conditions: 1. Perform one of the following: 18 - SPOILER...... RET - FLAPS ...... UP Change 2 EFFECTIVITY CL-126C All A-42 Change 2 SPOILERSSPOILERS FAIL FAIL On the ground: 18 1. Complete Starting Engines, page N-9. 19 2. SPOILER ...... RET 3. SPLR CTRL and SPLR IND Circuit 20 Breakers (respective pilot’s and copilot’s FLIGHT group) ...... Pull, Wait 5 Seconds and Reset 21 Allow 20 seconds for the system to restart. 4. EICAS...... Select FLT 22 5. SPOILER ...... EXT Check for equal extension rate and position. 23 6. SPOILER ...... ARM Check for spoilers retracted. (AUTOSPLR ARM white CAS) 24 If SPOILERS FAIL remains illuminated: 25 7. Do not take off. Refer the problem to maintenance personnel for correction. 26 In flight: 1. SPOILER ...... RET 27 2. SPLR CTRL & SPLR IND Circuit Breakers (respective pilot’s & copilot’s FLIGHT group)...... Set 28 3. EICAS...... Select FLT & Check Spoiler Positions 29 4. SYS TEST/RESET (SPLRN RESET)...... Depress & Release If SPOILERS FAIL remains illuminated: 30 5. Spoilers & spoilerons will be inoperative in flight. Maintain 35,000 feet or below. 31 6. Refer to Spoilers Extended Landing, Tab 46 . 19 32

EFFECTIVITY CL-126C All A-43 Change 2 Change 2 SPOILERL SPOILER JAM JAM R SPOILER JAM 19 SPOILER JAM SPOILERLR SPOILER JAM JAM 20 L or R SPOILER JAM Illuminated 21 1. Control aircraft with roll control. 2. Autopilot ...... Disengage (Do not use MSW) 22 3. SPOILER ...... Deploy as Required to Minimize Roll 4. EICAS ...... Select FLT & Check Spoiler Positions 23 5. Slow aircraft as necessary to reduce roll control forces. Do not reset spoiler system with SYS TEST/RESET (SPLRN RESET). 24 6. Land as soon as possible. 25 7. Refer to Spoiler Jammed Landing, Tab 47 . LR SPOILER JAM Illuminated 26 1. Refer to SPOILERS FAIL, Tab 18 . 27 LRL STALLWARN STALLWARN FAIL FAIL 28 RR STALLWARN STALLWARN FAIL FAIL LLR STALLWARN STALLWARN FAIL FAIL 29 1. Respective L or R STALL WARN Circuit 30 Breaker (FLIGHT group)...... Set, or Pull & Reset 2. Maintain airspeed at least 25 knots above stall speeds shown in 31 Section V of the AFM. VREF may be maintained on final approach in the landing configuration. 32 3. Limit bank angles to 30° maximum.

EFFECTIVITY All CL-126C A-44 Change 1 Jammed Stabilizer — Both PRI and SEC Trim Inoperative Elevator Pull Force Is Encountered 18 If the stabilizer jams during a high-speed condition: 19 1. Delay reducing airspeed as long as possible to minimize the time out of trim. Do not re-engage autopilot. 20 2. Move C.G. aft if possible. 3. Land as soon as possible to minimize forward C.G. movement. 21 4. PIT TRIM BIAS ...... NUP Hold switch to trim out and reduce elevator force. 22 5. Refer to Stabilizer Jammed Landing, Tab 47 . 23 Elevator Push Force Is Encountered If the stabilizer jams during a low-speed condition: 24 1. Do not increase airspeed to minimize the time out of trim. Do not re- engage autopilot. 25 2. Move C.G. forward if possible. 3. Land as soon as possible. 26 4. Refer to Stabilizer Jammed Landing, Tab 47 . 27

DEFUELDEFUEL OPEN OPEN 28

On the ground: 29 1. DEFUEL on Refueling Panel ...... OFF If DEFUEL OPEN remains illuminated: 30 2. Close defuel valve (tailcone) prior to takeoff. 31 3. This checklist is complete. In flight: 32 1. Check EICAS or select FUEL page. 2. Monitor fuel quantities. 33

3. This checklist is complete. 34 20 Change 2

EFFECTIVITY CL-126C All A-45 Change 2 LL FUEL FUEL FILTER FILTER R FUEL FILTER 19 R FUEL FILTER LRLR FUEL FUEL FILTER FILTER 20 Either the respective engine or aircraft fuel filter has an impending bypass on the ground. 21 LL FUEL FUEL HEATER HEATER 22 RR FUEL FUEL HEATER HEATER LRLR FUEL FUEL HEATER HEATER 23 1. Fly to warmer conditions if possible. 24 2. Respective L or R STBY (FUEL) ...... ON

25 FUELFUEL IMBALANCE IMBALANCE

26 1. Check EICAS or select FUEL page. 2. Check trim. 27 3. Fuel Quantities...... Check 28 Correct fuel distribution, if required: a. XFLOW (FUEL) ...... Open 29 b. L or R STBY (FUEL) (Heavy Wing)...... ON 30 c. Monitor wing fuel quantity. When fuel balance is achieved: 31 d. L or R STBY (FUEL)...... Off

32 e. XFLOW (FUEL) ...... Close

21 18

EFFECTIVITY All CL-126C A-46 Change 1 LL FUEL FUEL QTY QTY LOW LOW R FUEL QTY LOW R FUEL QTY LOW 18 LRLR FUEL FUEL QTY QTY LOW LOW

1. Check EICAS or select FUEL page. 19 2. Fuel Quantities ...... Check 20 3. Respective L or R STBY (FUEL) ...... ON 4. Replan flight if necessary. 21

FUELFUEL XFLO XFLO 22

1. Check EICAS or select FUEL page. 23 2. Fuel Quantities ...... Check 3. XFLO (FUEL)...... Cycle 24 4. ●If XFLO valve fails to open: 25 a. Maintain wing fuel balance by adjusting power setting. b. This checklist is complete. 26 4. ●If XFLO valve fails to close: 27 a. Appropriate L or R STBY (FUEL)...... ON to Maintain Wing Fuel Balance 28 b. This checklist is complete. 29 18LL FWSOVFWSOV FAULT FAULT RR FWSOV FWSOV FAULT FAULT 30 LRLR FWSOV FWSOV FAULT FAULT 31 1. Respective L or R STBY (FUEL) ...... Off 32 STBY PUMP Fails ON 33 Fuel will normally remain balanced without opening the FUEL XFLO valve. Fuel balance can be maintained by use of the FUEL XFLO and the PWR and CTRL circuit breakers [respective L or R STBY PUMP group] on the 34 “failed ON” pump. 21 EFFECTIVITY CL-126C All A-47 Change 1 AUXAUX HYD HYD PMP PMP LO LO

19 1. EICAS ...... Select HYD or SUMRY

20 2. HYD XFLOW...... Off 3. PWR Circuit Breaker 21 (pilot’s GEAR/HYDRAULICS group [AUX HYD PUMP])...... Set 4. Check B-ACUM pressure. 22 5. ●If B-ACUM pressure is normal: a. Emergency/parking brakes will operate normally. 23 b. This checklist is complete. 24 5. ●If B-ACUM pressure is low (BRK ACUM PRESS amber CAS): a. Emergency/parking brakes may not be operational. 25 b. This checklist is complete. 26 AUXAUX HYD HYD QTY QTY LO LO 27 1. HYD XFLOW...... Off 28 2. EICAS ...... Select HYD or SUMRY 3. Check B-ACUM pressure. 29 4. ●If B-ACUM pressure is normal: 30 a. Emergency/parking brakes will operate normally. b. This checklist is complete. 31 4. ●If B-ACUM pressure is low (BRK ACUM PRESS amber CAS):

32 a. Emergency/parking brakes may not be operational. b. AUX HYD ...... ON to Charge B-ACUM Pressure 33 c. This checklist is complete.

18 22

EFFECTIVITY All CL-126C A-48 Change 1 BRKBRK ACUM ACUM PRESS PRESS

1. EICAS...... Select HYD or SUMRY 18

2. Check B-ACUM pressure. 19 3. ●If B-ACUM pressure is accompanied with an AUX HYD QTY LO amber CAS: 20 a. Landing gear extension will turn the AUX HYD pump ON. b. HYD XFLOW ...... Off 21 c. AUX HYD ...... Off 22 d. AUX HYD ...... ON, Just Before Landing e. This checklist is complete. 23 3. ●If B-ACUM pressure is high: 24 a. AUX HYD ...... Off b. Cycle EMERGENCY/PARKING BRAKE handle to reduce 25 pressure. c. This checklist is complete. 26 3. ●If B-ACUM pressure is low: 27 a. AUX HYD ...... ON If B-ACUM pressure remains low: 28 b. Reduced emergency/parking brake capability will exist. c. This checklist is complete. 29

22 32

EFFECTIVITY CL-126C All A-49 Change 1 MAINMAIN HYD HYD PRESS PRESS

19 1. EICAS ...... Select HYD or SUMRY

20 2. Check MAIN & B-ACUM hydraulic pressures. 3. ●If MAIN pressure is high: 21 a. Obtain maintenance prior to next flight. b. This checklist is complete. 22 3. ●If MAIN pressure is low: 23 a. Do not use HYD XFLOW system to retract gear or flaps. b. Maintain 35,000 feet or below. 24 c. Refer to Main Hydraulic System Failure Landing, Tab48 . 25

26 AHRSAHRS 1 1 OVHT OVHT AHRSAHRS 2 2 OVHT OVHT AHRS 1-2 OVHT 27 AHRS 1-2 OVHT 1. AHRS NORM (REVERSION) ...... Select Operative AHRS 28 2. Monitor standby attitude & heading indicator. 29 3. ●AHRS 1 OVHT a. # 1 PRI & # 1 SEC Circuit Breaker 30 (respective pilot’s & copilot’s INSTRUMENTS group [AHRS PWR])...... Pull 31 b. Refer to Loss of PFD Attitude or Heading Displays, Tab28 . 32 3. ●AHRS 2 OVHT a. # 2 SEC & # 2 PRI Circuit Breaker 33 (respective pilot’s & copilot’s INSTRUMENTS group [AHRS PWR])...... Pull 34 b. Refer to Loss of PFD Attitude or Heading Displays, Tab28 . 18

Change 2 EFFECTIVITY All CL-126C A-50 Change 2 3. ●AHRS 1-2 OVHT a. # 2 SEC & # 2 PRI Circuit Breaker (respective pilot’s & copilot’s 18 INSTRUMENTS group [AHRS PWR])...... Pull b. # 1 PRI & # 1 SEC Circuit Breaker 19 (respective pilot’s & copilot’s INSTRUMENTS group [AHRS PWR])...... Pull 20 c. Refer to Loss of PFD Attitude or Heading Displays, Tab28 . 21

CNFGCNFG MISMATCH MISMATCH 22 The configuration, between the IM-600s (Integrated Computer Configura- 23 tion Modules), does not agree. Obtain maintenance. 24 DAUDAU 1A 1A FAIL FAIL DAUDAU 1B 1B FAIL FAIL 25 DAUDAU 1A-1B 1A-1B FAIL FAIL 26 1. Respective CH A and/or CH B Circuit Breaker(s) (pilot’s INSTRUMENTS/INDICATIONS group [DAU 1])...... Set 27 2. ●DAU 1A FAIL a. DAU NORM (REVERSION) ...... Select Channel B 28 b. This checklist is complete. 29 2. ●DAU 1B FAIL a. Do not revert to DAU B. 30 b. This checklist is complete. 31 2. ●DAU 1A-1B FAIL a. Match left thrust lever to the right. 32 b. Monitor right engine displays. c. Land as soon as practical. 33

d. This checklist is complete. 34 23

Change 2 EFFECTIVITY CL-126C All A-51 Change 2 DAUDAU 2A 2A FAIL FAIL DAU 2B FAIL 19 DAU 2B FAIL DAUDAU 2A-2B 2A-2B FAIL FAIL

20 1. Respective CH A and/or CH B Circuit Breaker(s) (copilot’s INSTRUMENTS/INDICATIONS group [DAU 2]) ...... Set 21 2. ●DAU 2A FAIL a. Do not revert to DAU B (DAU 2A not normally displayed). 22 b. This checklist is complete. 23 2. ●DAU 2B FAIL a. DAU NORM (REVERSION) ...... Select Channel A 24 b. This checklist is complete. 25 2. ●DAU 2A-2B FAIL a. Match right thrust lever to the left. 26 b. Monitor left engine displays. 27 c. Land as soon as practical. d. This checklist is complete. 28 LL DAU DAU ENG ENG MISCMP MISCMP 29 RR DAU DAU ENG ENG MISCMP MISCMP 30 1. DAU NORM (REVERSION) ...... Select Channel A, then B Compare engine data between left & right N1, ITT, & N2 indications 31 to determine which channel is presenting good data. 2. ●If valid channel is known: 32 a. DAU NORM (REVERSION) ...... Select Valid Channel 33 b. This checklist is complete. 2. ●If valid channel is not known: 34 a. DAU NORM (REVERSION) ...... NORM 18 b. This checklist is complete.

EFFECTIVITY All CL-126C A-52 Change 2 LL DAU DAU SYS SYS MISCMP MISCMP R DAU SYS MISCMP R DAU SYS MISCMP 18 1. EICAS...... Select SUMRY 19 2. DAU NORM (REVERSION)...... Select Channel A, then B Evaluate system parameters to determine which channel is presenting valid data. 20 3. ●If valid channel is known: 21 a. DAU NORM (REVERSION) ...... Select Valid Channel b. This checklist is complete. 22 3. ●If valid channel is not known: 23 a. DAU NORM (REVERSION) ...... NORM b. This checklist is complete. 24

24 33

EFFECTIVITY CL-126C All A-53 Change 2 DUDU 1 1 OVHT OVHT DU 2 OVHT 19 DU 2 OVHT DUDU 3 3 OVHT OVHT DUDU 4 4 OVHT OVHT 20 1. INSTR FAN Circuit Breaker 21 (pilot’s ENVIRONMENTAL group) ...... Set, or Pull & Reset If the temperature continues to increase, the display will blank. It is recom- 22 mended to perform the following procedure, conditions permitting, prior to the display blanking. 23 2. ●DU 1 OVHT a. DU 2 Reversion ...... PFD 24 EICAS will automatically revert to DU 3. b. DU 1 Circuit Breaker (pilot’s 25 INSTRUMENTS group [DISPLAY]) ...... Pull c. This checklist is complete. 26 2. ●DU 2 OVHT 27 a. DU 2 Reversion ...... OFF EICAS will automatically revert to DU 3. 28 b. DU 2 Circuit Breaker (pilot’s INSTRUMENTS group [DISPLAY]) ...... Pull 29 c. This checklist is complete. 2. ●DU 1-2 OVHT 30 a. DU 2 Reversion ...... OFF EICAS will automatically revert to DU 3. 31 b. DU 1 & DU 2 Circuit Breakers (pilot’s INSTRUMENTS group [DISPLAY]) ...... Pull 32 Rely on the copilot’s flight displays & standby instruments. 33 c. This checklist is complete.

18 25

EFFECTIVITY All CL-126C A-54 Change 1 2. ●DU 3 OVHT a. DU 3 Reversion...... Push (if DU 3 is presently in EICAS format) 18 b. DU 3 Circuit Breaker (copilot’s INSTRUMENTS group [DISPLAY]) ...... Pull 19 c. This checklist is complete. 20 2. ●DU 4 OVHT a. DU 3 Reversion...... PFD 21 EICAS will automatically revert to DU 2. b. DU 4 Circuit Breaker (copilot’s 22 INSTRUMENTS group [DISPLAY]) ...... Pull c. This checklist is complete. 23 2. ●DU 3-4 OVHT 24 a. DU 3 Reversion...... Push as Required to get EICAS on DU 2 b. DU 3 & DU 4 Circuit Breakers (copilot’s 25 INSTRUMENTS group [DISPLAY]) ...... Pull Rely on the pilot’s flight displays & standby instruments. 26 c. This checklist is complete. 27 ICIC 1 1 OVHT OVHT ICIC 2 2 OVHT OVHT 28

If conditions permit (before IC shutdown, or after IC shutdown has 29 occurred): 1. Autopilot...... Disengage 30 Engage yaw damper as required. 2. Monitor standby instruments. 31 3. IC/SG NORM (REVERSION) ...... Select Other (unaffected) IC/SG 32 4. Respective IC/SG 1 or 2 Circuit Breaker (INSTRUMENTS/INDICATIONS group)...... Pull 33 5. Refer to IC 1 or 2 Failure Procedure, Tab25 . 34 25

Change 2 EFFECTIVITY CL-126C All A-55 Change 2 IC 1 or 2 Failure Procedure 19 IC 1 Failure 1. Control Wheel Master (MSW)...... Depress & Release 20 2. Monitor standby instruments. 3. Yaw Damper...... As Required 21 4. Airspeed...... ≤ Mach trim off MMO 22 5. IC/SG 1 Circuit Breaker (INSTRUMENTS/INDICATIONS group)...... Set, or Pull & Reset 23 If IC 1 remains failed: 6. IC/SG NORM (REVERSION)...... Select 2 24 Use copilot’s PFD/EICAS bezel controls. MFD display and functions will not be available. 25 7. Airspeed...... ≤ Mach trim off MMO 26 IC 2 Failure 1. Control Wheel Master (MSW)...... Depress & Release 27 2. Monitor standby instruments. 3. IC/SG 2 Circuit Breaker 28 (INSTRUMENTS/INDICATIONS group)...... Set, or Pull & Reset 4. Yaw Damper...... As Required 29 5. Do not re-engage autopilot, even if IC 2 is restored. 30 If IC 2 remains failed: 6. IC/SG NORM (REVERSION)...... Select 1 31 Use pilot’s PFD/EICAS bezel controls. MFD display and functions will not be available. 32 7. Maintain 33,000 feet or below.

8. Airspeed...... ≥ 0.65 MI Until Below 33,000 Feet 33 9. Land as soon as practical. 34

Change 2 EFFECTIVITY 45-002 thruAll 45-225 not modified by SB 45-55-6 CL-126C A-56 Change 2 IC 1 or 2 Failure Procedure 19 IC 1 Failure 1. Control Wheel Master (MSW)...... Depress & Release 20 2. Monitor standby instruments. 3. Yaw Damper...... As Required 21 4. Airspeed...... ≤ Mach trim off MMO 22 5. IC/SG 1 Circuit Breaker (INSTRUMENTS/INDICATIONS group)...... Set, or Pull & Reset 23 If IC 1 remains failed: 6. IC/SG NORM (REVERSION)...... Select 2 24 Use copilot’s PFD/EICAS bezel controls. MFD display and functions will not be available. 25 7. Airspeed...... ≤ Mach trim off MMO 26 IC 2 Failure 1. Control Wheel Master (MSW)...... Depress & Release 27 2. Monitor standby instruments. 3. IC/SG 2 Circuit Breaker 28 (INSTRUMENTS/INDICATIONS group)...... Set, or Pull & Reset 4. Yaw Damper...... As Required 29 5. Do not re-engage autopilot, even if IC 2 is restored. 30 If IC 2 remains failed: 6. IC/SG NORM (REVERSION)...... Select 1 31 Use pilot’s PFD/EICAS bezel controls. MFD display and functions will not be available. 32

Change 2 EFFECTIVITY 45-226 & on, andAll prior aircraft modified by SB 45-55-6 CL-126C A-56.1 Change 2 ICIC BUS BUS FAIL FAIL 1. Yaw Damper ...... Engage 18 2. IC/SG NORM (REVERSION) ...... Select to Pilot Flying Side Use pilot flying side PFD/EICAS bezel controls. 19

20 LL CHK CHK IC IC SW SW RR CHK CHK IC IC SW SW LRLR CHK CHK IC IC SW SW 21 This indicates a mismatch has occurred between the approved software ID 22 file and the loaded software configuration, or the program enable discrete is active. These messages will only appear on the ground and are inhibited on takeoff. Obtain maintenance prior to flight. 23 24

Change 2 34

EFFECTIVITY CL-126C 45-002 thruAll 45-225 A-56AA-56.2 Change 2 not modified by SB 45-55-6 ICIC BUS BUS FAIL FAIL 1. Yaw Damper ...... As Desired 18 2. IC/SG NORM (REVERSION) ...... Select to Pilot Flying Side Use pilot flying side PFD/EICAS bezel controls. 19

LL CHK CHK IC IC SW SW 20 RR CHK CHK IC IC SW SW LRLR CHK CHK IC IC SW SW 21

This indicates a mismatch has occurred between the approved software ID 22 file and the loaded software configuration, or the program enable discrete is active. These messages will only appear on the ground and are inhibited on takeoff. Obtain maintenance prior to flight. 23

EFFECTIVITY CL-126C 45-226 & on andAll prior aircraft A-56A.1A-56.3 Change 2 modified by SB 45-55-6 LBS/KGSLBS/KGS CONFIG CONFIG The pounds/kilograms configuration of the IC-600 (Integrated Computer) 18 disagrees with the configuration of the DAU 1 or DAU 2 on the ground. 19 LRL PFDPFD CHECKCHECK R PFD CHECK 20 LR PFD CHECK 21 1. DU 2 (or DU 3 for R PFD CHECK) Reversion ...... PFD EICAS will be displayed on the opposite inboard DU. 22 If condition remains: 2. DU 2 (or DU 3 for R PFD CHECK) Reversion ...... NORM 23 3. Monitor opposite PFD & standby instruments. 24 4. AP XFR...... Select to Functioning PFD Side 5. Autopilot...... As Desired 25 6. Land as soon as practical. 26 WARN AUDIO WARN AUDIO 27 1. Monitor EFIS/CAS displays for related visual warning indications. 28 LR WARN PWR FAIL LR WARN PWR FAIL 29 1. L & R WARN PANEL Circuit Breakers (pilot’s and copilot’s INSTRUMENTS/INDICATIONS group) ...... Set 30 If LR WARN PWR FAIL remains illuminated: 31 2. Monitor EFIS/CAS displays & pressurization controller for related visual warning indications. 32 3. Land as soon as practical.

...... 26 33

EFFECTIVITY CL-126C All A-57 Change 2 Air Data Computer (ADC) Failure — Single

19 1. ADC NORM (REVERSION)...... Select Operational ADC

20 If time & conditions permit: 2. Respective ADC Circuit Breaker 21 (INSTRUMENTS group)...... Set, or Pull & Reset 3. ADC NORM (REVERSION)...... NORM 22 4. Cross-check airspeed & altitude indications with the standby instruments. Refer to Airspeed/Mach Calibrations — Standby System or 23 Altitude Position Corrections — Standby System charts, Section V in the AFM. 24 If air data computer is not recovered: 5. ADC NORM (REVERSION)...... Select Operational ADC 25 6. Airspeed...... ≤ Mach Trim Off MMO, Prior to Disengaging the Autopilot 26

27 Air Data Computer (ADC) Failure — Dual 1. Maintain aircraft control by reference to the standby airspeed/Mach 28 indicator & altimeter. Roll control authority may be less than normal. 2. Pilot’s & copilot’s ADC 1 & 2 Circuit Breakers 29 (respective INSTRUMENTS/INDICATIONS group)...... Set, or Pull & Reset 30 If neither ADC operation is restored: 3. Monitor the standby attitude indicator. 31 4. Airspeed...... ≤ Mach Trim Off MMO, Prior to Disengaging the Autopilot 32 5. Autopilot ...... As Desired 33 PIT, ROL, HDG, NAV & APP Only 6. MANUAL Rate Control (PRESSURIZATION) ...... As Required 34 7. Land as soon as possible.

EFFECTIVITY All CL-126C A-58 Change 1 Display Unit Failure 18

●DU 1 Failure 24

1. DU 2 Reversion ...... PFD The pilot’s PFD will be displayed on DU 2, the EICAS will be dis- 25 played on DU 3 and the MFD will not be available. 26 ●DU 2 Failure 1. DU 2 Reversion ...... OFF 27 The EICAS will be displayed on DU 3 and the MFD will not be available. 28 ●DU 3 Failure 1. ■If DU 2 is displaying MFD, DU 2 or DU 3 Reversion ...... Push 29 The EICAS will be displayed on DU 2 and the MFD will not be available. 30 1. ■If DU 2 is displaying EICAS, no further action is required. The MFD will not be available. 31 ●DU 4 Failure 1. DU 3 Reversion ...... PFD 32 The copilot’s PFD will be displayed on DU 3, the EICAS will be displayed on DU 2 and the MFD will not be available. 33 27 34

EFFECTIVITY CL-126C All A-59 Change 1 Change 1 Erroneous Pitot-Static Indications

19 1. Maintain safe aircraft attitude & thrust setting. Using the autopilot in PIT, ROL, HDG, NAV or APP modes will help reduce work load. Do 20 not use ALT, SPD, FLC, VS or VNAV modes. Minimize large changes in thrust setting unless they are necessary to control the 21 aircraft. If an L or R PITOT HT or STBY PITOT HT amber CAS is illuminat- 22 ed, that system should be the suspected system: a. L & R PROBES ...... On 23 b. PITOT & STBY PITOT Circuit Breakers (respective ANTI-ICE group [L & R PROBES HT]) ...... Set 24 c. Fly out of icing conditions as soon as possible.

25 2. Compare pilot’s, copilot’s, & standby airspeed, Mach & altitude. 3. ●If the malfunction is known or suspected in the pilot’s or 26 copilot’s pitot-static system: a. ADC NORM (REVERSION) ...... Select Valid ADC 27 b. Autopilot ...... As Desired c. Land as soon as practical. 28 d. This checklist is complete. 29 3. ●If the malfunction is known or suspected in both the pilot’s & copilot’s pitot-static systems: 30 a. Refer to the standby system. The standby system indications must be corrected before comparison to the ADC indications. 31 Refer to Airspeed/Mach Calibrations & Altitude Position Correc- tions — Standby System charts, Section V in the AFM. 32 b. Autopilot ...... As Desired Use PIT, ROL, HDG, NAV or APP modes. 33 Do not use ALT, SPD, FLC, VS or VNAV modes. c. Land as soon as possible. 34 d. This checklist is complete.

EFFECTIVITY A-60 CL-126C All Change 1 3. ●If the malfunction is known or suspected in the standby pitot- static system: a. Refer to the normal ADC displays. 18 b. Autopilot ...... As Desired 19 c. Land as soon as practical. d. This checklist is complete. 20 28 21

CL-126C EFFECTIVITY All A-61 Loss of PFD Attitude or Heading Displays

19 1. ●If the attitude or attitude and heading display is affected, go to step 2. 20 1. ●If only one heading display is affected: 21 a. Establish aircraft in straight and level, unaccelerated flight. b. Associated HEADING Switch...... FREE, then Slave 22 c. ■If red HDG FAIL remains illuminated, go to step 2. c. ■If red HDG FAIL extinguishes, this checklist is complete. 23 1. ●If both heading displays are affected: 24 a. Both HEADING Switches ...... FREE b. Conduct flight operations in DG mode. 25 c. This checklist is complete. 26 2. AHRS NORM (REVERSION) ...... Select Operative AHRS 3. Monitor standby attitude & heading indicator. 27 4. Maintain 33,000 feet or below. ≥ 28 5. Airspeed...... 0.65 MI Until Below 33,000 Feet 6. Land as soon as practical. 29 If time & conditions permit: 7. Establish aircraft in straight & level, unaccelerated flight. 30 8. ●If the loss is associated with the pilot’s PFD: 31 a. Pilot’s #1 PRI & Copilot’s #1 SEC Circuit Breakers (respective INSTRUMENTS/ 32 INDICATIONS group [AHRS PWR])...... Pull Both b. Pilot’s #1 PRI & Copilot’s #1 SEC Circuit Breakers ...... Set 33 c. Go to step 9.

EFFECTIVITY CL-126C A-62 45-002 thru 45-225All not modified by Change 1 SB 45-55-6 Change 1 Loss of PFD Attitude or Heading Displays

19 1. ●If the attitude or attitude and heading display is affected, go to step 2. 20 1. ●If only one heading display is affected: 21 a. Establish aircraft in straight and level, unaccelerated flight. b. Associated HEADING Switch...... FREE, then Slave 22 c. ■If red HDG FAIL remains illuminated, go to step 2. c. ■If red HDG FAIL extinguishes, this checklist is complete. 23 1. ●If both heading displays are affected: 24 a. Both HEADING Switches ...... FREE b. Conduct flight operations in DG mode. 25 c. This checklist is complete. 26 2. AHRS NORM (REVERSION) ...... Select Operative AHRS 3. Monitor standby attitude & heading indicator. 27 4. Land as soon as practical. 28 If time & conditions permit: 5. Establish aircraft in straight & level, unaccelerated flight. 29 6. ●If the loss is associated with the pilot’s PFD: a. Pilot’s #1 PRI & Copilot’s #1 SEC Circuit 30 Breakers (respective INSTRUMENTS/ INDICATIONS group [AHRS PWR])...... Pull Both 31 b. Pilot’s #1 PRI & Copilot’s #1 SEC Circuit Breakers ...... Set 32 c. Go to step 7. 6. ●If the loss is associated with the copilot’s PFD: 33 a. Pilot’s #2 SEC & Copilot’s #2 PRI Circuit Breakers (respective INSTRUMENTS/ 34 INDICATIONS group [AHRS PWR])...... Pull Both

35 b. Pilot’s #2 SEC & Copilot’s #2 PRI Circuit Breakers ...... Set c. Go to step 7. EFFECTIVITY CL-126C A-62.1 45-226 & on, and priorAll aircraft modified by Change 2 SB 45-55-6 Change 2 8. ●If the loss is associated with the copilot’s PFD: a. Pilot’s #2 SEC & Copilot’s #2 PRI Circuit Breakers (respective INSTRUMENTS/ 18 INDICATIONS group [AHRS PWR])...... Pull Both b. Pilot’s #2 SEC & Copilot’s #2 PRI Circuit Breakers...... Set 19 c. Go to step 9. 20 9. AHRS NORM (REVERSION) ...... NORM Maintain aircraft attitude by monitoring the operating side flight display & the standby attitude indicator. Initialization should occur 21 within approximately 20 seconds. Successful initialization is indicated by attitude & heading displays. 22 If initialization does not occur within approximately 20 seconds: 23 10. AHRS NORM (REVERSION) ...... Select Operative AHRS 24 Loss of Standby Attitude Indicator 25 If EMER BUS VOLTS amber CAS is illuminated, refer to EMER BUS VOLTS, Tab 5 . 26 1. EMER BATT...... On 2. BUS Circuit Breaker (pilot’s 27 ELECTRICAL group [EMER BUS]) ...... Set 3. Establish aircraft in straight & level, unaccelerated flight. 28 4. Standby Attitude Indicator...... Cage, then Uncage 29 If standby attitude is not recovered: 5. Standby Attitude Indicator ...... Cage 30 6. Land as soon practical. 29 31

EFFECTIVITY CL-126C 45-002 thru 45-225All not modified by A-63 Change 2 Change 2 SB 45-55-6 7. AHRS NORM (REVERSION) ...... NORM Maintain aircraft attitude by monitoring the operating side flight display & the standby attitude indicator. Initialization should occur 18 within approximately 20 seconds. Successful initialization is indicated by attitude & heading displays. 19 If initialization does not occur within approximately 20 seconds: 8. AHRS NORM (REVERSION) ...... Select Operative AHRS 20

Loss of Standby Attitude Indicator 21 If EMER BUS VOLTS amber CAS is illuminated, refer to EMER BUS 22 VOLTS, Tab 5 . 1. EMER BATT...... On 23 2. BUS Circuit Breaker (pilot’s ELECTRICAL group [EMER BUS]) ...... Set 24 3. Establish aircraft in straight & level, unaccelerated flight. 25 4. Standby Attitude Indicator...... Cage, then Uncage If standby attitude is not recovered: 26 5. Standby Attitude Indicator ...... Cage 27 6. Land as soon practical. 29 28

EFFECTIVITY CL-126C 45-226 & on, and priorAll aircraft modified by A-63.1 Change 2 Change 2 SB 45-55-6 Multi-Function Display (MFD) Annunciations MAGx DGx 19 EICAS CHK 20 TERR FAIL TERR N/A 21 TGT 22 WX STAB 23 TCAS FAIL TA NO BRG 24 MENU INOP EICAS CHK 25 1. DU 2 or DU 3 Reversion ...... Push 26 2. ●If EICAS CHK extinguishes: a. Leave EICAS display on current DU until landing. 27 b. This checklist is complete. 28 2. ●If EICAS CHK remains illuminated: a. Monitor engine instruments (N1, ITT or N2) for abnormal 29 indications. b. This checklist is complete. 30 DGx Indicates AHRS or IC/SG reversion has been selected & the respective 31 HEADING switch is in the unslaved (FREE) mode.

32 MAGx Indicates AHRS or IC/SG reversion has been selected & the respective 33 HEADING switch is in the slaved mode. MENU INOP 34 Indicates the MFD bezel menu is inoperative. 35 1. L & R CTRL Circuit Breaker (pilot’s & copilot’s INSTRUMENTS/INDICATIONS group [DISPLAY])...... Set

EFFECTIVITY A-64 CL-126C All Change 1 Multi-Function Display (MFD) Annunciations (Cont) If condition persists: 18 2. DU 2 or DU 3 Reversion ...... Push if MFD Functionality Required The EICAS will now have the MENU INOP condition. 19 STAB 20 Indicates weather radar stabilization is off.

TA NO BRG 21 Indicates that a TA has been encountered, but no bearing to that TA is available for display. 22

TCAS FAIL 23 Indicates that TCAS is failed. 1. TCAS Circuit Breaker (copilot’s 24 INSTRUMENTS/INDICATIONS group) ...... Pull & Reset 2. Verify correct transponder operation. Select opposite transponder. 25 3. Select ATC ALT mode on the RMU (ATC/TCAS) until the failed condition is resolved. 26

TERR FAIL 27 Indicates the Terrain Mode is inoperative. 1. FMS 1 and FMS 2 (if installed) ...... Check ON 28 2. GPWS Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group)...... Pull & Reset 29 TERR N/A 30 Indicates that terrain information cannot be displayed because of an uncer- tain FMS position or loss of inputs required for terrain awareness alerting and display functions. 31

TGT 32 Indicates a weather radar target alert is activated. Take appropriate action to verify the weather radar alert. 33 WX Indicates an invalid weather radar. 34

30 EFFECTIVITY CL-126C All A-65 Change 1 Primary Flight Display (PFD) Annunciations 19 AP AP TEST 20 AP FAIL ADCx 21 A L 22 T

23 A O A 24

25 ADCx 26 Indicates both pilot & copilot displayed air data sources are the same.

27 ALT 1. Check that both pilot’s altimeters are set to the same value. 28 If mismatch persists: 2. Refer to Erroneous Pitot-Static Indications, Tab 27 . 29 AOA 30 Indicates invalid angle-of-attack data. The Low Speed Awareness (LSA) cue will not be displayed. Cross reference the other PFD LSA cue. May be 31 accompanied by an L (R) STALLWARN FAIL amber CAS. Refer to STALLWARN FAIL, Tab 19 . 32 AP (flash) 33 Flashes for 5 seconds & clears. Indicates the autopilot has disengaged & is accompanied by the aural “cavalry charge” alert. 34

EFFECTIVITY A-66 CL-126C Change 1 All Change 1 Primary Flight Display (PFD) Annunciations (Cont) AP (steady) 1. ●If accompanied by an amber YD: 18 a. Maintain 33,000 feet or below 19 b. Airspeed ...... ≥ 0.65 MI Until Below 33,000 Feet If conditions permit: 20 c. IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ...... Pull & Reset to 21 Regain Autopilot d. ■If amber YD remains illuminated: 22 (1) Land as soon as practical. 23 (2) This checklist is complete. d. ■If amber YD extinguishes: 24 (1) Yaw Damper ...... Engage 25 (2) This checklist is complete. 1. ●If not accompanied by an amber YD: 26 a. Yaw Damper...... Engage b. This checklist is complete. 27

AP FAIL 28 1. AFCS SERVOS Circuit Breaker (pilot’s FLIGHT group) ...... Set 29 2. IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group)...... Pull & Reset 30 AP TEST 31 Indicates test mode for the AP during ground power-up of the AHRS. 32 31 33

34 Change 2 EFFECTIVITY CL-126C 45-002 thru 45-225All not modified by A-67 Change 2 SB 45-55-6 Primary Flight Display (PFD) Annunciations (Cont) AP (steady) 18 1. ●If accompanied by an amber YD and conditions permit: a. Respective IC/SG 2 Circuit Breaker (copilot’s 19 INSTRUMENTS/INDICATIONS group) ...... Pull & Reset to Regain Autopilot 20 b. ■If amber YD remains illuminated, this checklist is complete. b. ■ If amber YD extinguishes: 21 (1) Yaw Damper ...... As Desired 22 (2) This checklist is complete. 1. ●If not accompanied by an amber YD: 23 a. Yaw Damper...... As Desired 24 b. This checklist is complete.

AP FAIL 25 1. AFCS SERVOS Circuit Breaker (pilot’s FLIGHT group) ...... Set 26 2. IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group)...... Pull & Reset 27 AP TEST Indicates test mode for the AP during ground power-up of the AHRS. 28

30 31 31

EFFECTIVITY CL-126C 45-226 & on, and priorAll aircraft modified by A-67.1 Change 1 SB 45-55-6 Primary Flight Display (PFD) Annunciations (Cont)

19 FD FAIL

20 ATT

21 CAS MSG

22 DGx 23

24 ATT 25 1. Compare indications with standby attitude indicator to determine faulty system. 26 2. Autopilot & Yaw Damper ...... Disengage 3. AHRS NORM (REVERSION) ...... Select Operative AHRS 27 4. Do not re-engage autopilot or yaw damper. 28 5. Maintain 33,000 feet or below. 6. Airspeed ...... ≥ 0.65 MI Until Below 33,000 Feet 29 7. Land as soon as practical.

30 CAS MSG 1. Note existing CAS messages. 31 2. DU 2 or DU 3 Reversion ...... Push & Compare the CAS Messages on the Reverted EICAS 32 3. Take the appropriate CAS message action for any new messages.

33 DGx Indicates AHRS or IC/SG reversion has been selected & the respective 34 HEADING switch is in the unslaved (FREE) mode.

EFFECTIVITY CL-126C A-68 45-002 thru 45-225All not modified by SB 45-55-6 Change 1 Primary Flight Display (PFD) Annunciations (Cont)

19 FD FAIL

20 ATT

21 CAS MSG

22 DGx 23

25 ATT 1. Compare indications with standby attitude indicator to determine 26 faulty system.

27 2. Autopilot & Yaw Damper ...... Disengage 3. AHRS NORM (REVERSION) ...... Select Operative AHRS 28 4. Do not re-engage autopilot or yaw damper.

29 CAS MSG 1. Note existing CAS messages. 30 2. DU 2 or DU 3 Reversion ...... Push & Compare the CAS Messages on the Reverted EICAS 31 3. Take the appropriate CAS message action for any new messages.

32 DGx Indicates AHRS or IC/SG reversion has been selected & the respective 33 HEADING switch is in the unslaved (FREE) mode.

Change 2 EFFECTIVITY CL-126C A-68.1 45-226 & on, and priorAll aircraft modified by SB 45-55-6 Change 2 Primary Flight Display (PFD) Annunciations (Cont) FD FAIL Display of the FD FAIL & removal of the flight director steering commands 18 indicate a failure in the flight director system or loss of sensor data required for the active modes on that side. 19 If FD FAIL appears because of internal failure, loss of AHRS data, or selec- tion of AHRS reversion, the autopilot will disconnect. If FD FAIL appears be- 20 cause of invalid sensor data, the autopilot will not disconnect. If the autopilot remains engaged to the failed flight director, operation will 21 be in basic PIT & ROL mode. 1. Monitor aircraft attitude. 22 2. XFR (guidance controller)...... Selecte Opposite Side If conditions permit: 23 3. Respective IC/SG 1 or 2 Circuit Breaker (INSTRUMENTS/INDICATIONS group)...... Pull & Reset to 24 Regain Autopilot 25 4. Yaw Damper ...... As Required 26

32 32

EFFECTIVITY CL-126C All A-69 Change 1 Primary Flight Display (PFD) Annunciations (Cont)

19 I A S 20 M A 21 C H 22 GS ILS 23 LOC 24 HDG GS 25 Indicates a comparator mismatch of the pilot’s & copilot’s glideslope data. 1. NAV Source ...... Determine Correct NAV Source & Select 26 If unable to determine correct source: 27 2. Use localizer approach minimums. HDG 28 1. Establish aircraft in straight & level, unaccelerated flight. 29 2. Compare indications with magnetic compass. 3. ●If single system is in error: 30 a. Autopilot ...... Disengage 31 b. Associated HEADING ...... FREE, then Slave c. If heading split cannot be corrected, 32 AHRS NORM (REVERSION)...... Select AHRS with Correct Heading 33 d. This checklist is complete. 3. ●If heading cannot be determined: 34 a. Autopilot ...... Disengage 35 b. Both HEADING...... FREE, then Slave c. This checklist is complete.

EFFECTIVITY A-70 CL-126C All Change 1 Primary Flight Display (PFD) Annunciations (Cont) IAS Indicates a mismatch of the pilot’s & copilot’s airspeed data. Refer 18 to Erroneous Pitot-Static Indications, Tab 27 . 19 ILS Indicates a comparator mismatch of the pilot’s & copilot’s localizer & glides- 20 lope data. 1. NAV Source ...... Determine Correct NAV Source & Select 21 If unable to determine correct source: 22 2. Execute missed approach. 23 LOC Indicates a comparator mismatch of the pilot’s & copilot’s localizer data. 24 1. NAV Source ...... Determine Correct NAV Source & Select If unable to determine correct source: 25 2. Execute missed approach. 26 MACH Indicates a mismatch of the pilot’s & copilot’s Mach number data. Refer to 27 Erroneous Pitot-Static Indications,Tab 27 . 33 28 29

34 Change 2

EFFECTIVITY CL-126C All A-71 Change 2 Primary Flight Display (PFD) Annunciations (Cont) GND PROX Alert 19

22 GND PROX

“CAUTION OBSTACLE, CAUTION OBSTACLE” or 26 “OBSTACLE AHEAD, OBSTACLE AHEAD” 27 1. EGPWS Terrain Awareness Display ...... Monitor 2. Stop any descent and climb as required. 28 “CAUTION TERRAIN, CAUTION TERRAIN” or 29 “TERRAIN AHEAD, TERRAIN AHEAD”

30 1. EGPWS Terrain Awareness Display ...... Monitor 2. Stop any descent and climb as required. 31 “DON’T SINK” 32 1. Arrest sink rate as required. 33 “GLIDESLOPE” 34 1. Fly aircraft to glideslope. Once triggered, alerts may be cancelled by selecting G/S Switch OFF. 35

EFFECTIVITY A-72 CL-126C All Change 1 Primary Flight Display (PFD) Annunciations (Cont)

18 “SINK RATE” 19 1. Arrest sink rate as required. 20 “TERRAIN, TERRAIN” 1. EGPWS Terrain Awareness Display ...... Monitor 21 2. Stop any descent and climb as required. 22

“TOO LOW, FLAPS” 23 1. FLAPS ...... DN, Check Indication 24 “TOO LOW, GEAR” 25 1. ●If adequate time is available to extend gear: a. GEAR...... DN 26 b. This checklist is complete. 27 1. ●If adequate time is not available to extend gear: a. Execute go-around. 28 b. This checklist is complete. 29 “TOO LOW, TERRAIN” 30 1. Fly out of the warning envelope or reconfigure as required. 31 34 32

EFFECTIVITY CL-126C All A-73 Change 1 Primary Flight Display (PFD) Annunciations (Cont)

19 PIT

20 M A X 21 S P 22 D RA

23 RA

24 MIN MAGx RA FAIL MAGx 25 Indicates AHRS or IC/SG reversion has been selected & the respective HEADING switch is in the slaved mode. 26 MAXSPD 27 Indicates the autopilot overspeed mode is active. MIN 28 Indicates capture of the BARO or RA minimums when the barometric altitude is equal to or less than the BARO minimums readout, or the radio al- 29 titude is equal to or less than the RA minimums readout (whichever one, BARO or RA, is displayed on the PFD). 30 PIT 31 1. Compare indications with standby attitude indicator to determine faulty system. 32 2. Autopilot & Yaw Damper ...... Disengage 3. AHRS NORM (REVERSION) ...... Select Operative AHRS 33 4. Do not re-engage autopilot or yaw damper. 34 5. Maintain 33,000 feet or below. 6. Airspeed ...... ≥ 0.65 MI Until Below 33,000 Feet 35 7. Land as soon as practical.

Change 2 EFFECTIVITY CL-126C A-74 45-002 thru 45-225All not modified by SB 45-55-6 Change 2 Primary Flight Display (PFD) Annunciations (Cont)

19 PIT 20 M A X 21 S P 22 D RA 23 RA

EFFECTIVITY CL-126C A-74.1 45-226 & on, and priorAll aircraft modified by SB 45-55-6 Change 2 Primary Flight Display (PFD) Annunciations (Cont) RA Indicates a comparator mismatch of the displayed pilot’s & copilot’s radio al- 18 titude. 19 1. Use BARO minimums for approach.

—RA— 20 Indicates invalid radio altitude. RA minimums, & TCAS (if installed), and EGPWS (if installed) are inoperative. The radio altitude function of the gear 21 warning system is inoperative. 1. RAD ALT 1 or 2 (If Installed) Circuit Breaker 22 (pilot’s or copilot’s INSTRUMENTS/INDICATIONS group) ...... Set 23 2. Refer to GEAR, Tab 37 . The takeoff & landing CAS inhibit function is disabled. 24 RA FAIL Indicates resolution advisory information from the TCAS computer is invalid 25 or not received. This can occur with or without an actual intruder aircraft being present. 26 1. Attempt to visually acquire possible intruder aircraft. 27 If annunciation persists: 2. RMU (ATC/TCAS)...... TA ONLY 28

220 33 35 34

EFFECTIVITY CL-126C All A-75 Change 1 Primary Flight Display (PFD) Annunciations (Cont)

19 RB

20 SGx 21 ROL 22

23 TCAS FAIL 24 RB 25 Indicates the rudder boost system has disengaged due to a monitor. Do not takeoff. 26 1. RUD BOOST ...... OFF 2. Control Wheel Master (MSW)...... Depress & Release 27 3. ●If RB extinguishes: 28 a. Yaw Damper ...... Engage b. This checklist is complete. 29 3. ●If RB remains illuminated: a. Maintain 33,000 Feet or below. Yaw damper is not operative. 30 b. Airspeed...... ≥ 0.65 MI Until Below 33,000 Feet 31 c. If conditions permit, IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ...... Pull & Reset to 32 Regain Autopilot d. ■If RB remains illuminated: 33 (1) Land as soon as practical. (2) This checklist is complete. 34 d. ■If RB extinguishes: 35 (1) Yaw Damper...... Engage Change 2 (2) This checklist is complete.

EFFECTIVITY CL-126C A-76 45-002 thru 45-225All not modified by SB 45-55-6 Change 2 Primary Flight Display (PFD) Annunciations (Cont)

19 RB

20 SGx 21 ROL 22

23 TCAS FAIL 24 RB 25 Indicates the rudder boost system has disengaged due to a monitor. Do not takeoff. 26 1. RUD BOOST...... OFF 2. Control Wheel Master (MSW)...... Depress & Release 27 3. ●If RB extinguishes: 28 a. Yaw Damper ...... As Desired b. This checklist is complete. 29 3. ●If RB remains illuminated and conditions permit: a. IC/SG 2 Circuit Breaker (copilot’s 30 INSTRUMENTS/INDICATIONS group)...... Pull & Reset to Regain Autopilot 31 b. ■If RB remains illuminated, this checklist is complete. 32 b. ■If RB extinguishes: (1) Yaw Damper ...... As Desired 33 (2) This checklist is complete.

EFFECTIVITY CL-126C A-76.1 45-226 & on, and priorAll aircraft modified by SB 45-55-6 Change 2 Primary Flight Display (PFD) Annunciations (Cont)

ROL 35 1. Compare indications with standby attitude indicator to determine faulty system. 36 2. Autopilot & Yaw Damper ...... Disengage 3. AHRS NORM (REVERSION) ...... Select Operative AHRS 37 4. Do not re-engage autopilot or yaw damper. 38 5. Maintain 33,000 feet or below.

6. Airspeed...... ≥ 0.65 MI Until Below 33,000 Feet 39 7. Land as soon as practical. 40 SGx Indicates both pilot & copilot are displaying the same AHRS, air data, & nav- 41 igation sources from one IC/SG. Accompanied by the ADCX & ATTX annunciators. 42 TCAS FAIL 43 Indicates that TCAS is failed. 1. TCAS Circuit Breaker (copilot’s 44 INSTRUMENTS/INDICATIONS group) ...... Pull & Reset 2. Verify correct transponder operation. Select opposite transponder. 45 3. Select ATC ALT mode on the RMU (ATC/TCAS) until the failed condition is resolved. 46

36 CL-126C EFFECTIVITY A-77 Change 2 45-002 thru 45-225All not modified by SB 45-55-6 Primary Flight Display (PFD) Annunciations (Cont) ROL 35 1. Compare indications with standby attitude indicator to determine faulty system. 36 2. Autopilot & Yaw Damper ...... Disengage 3. AHRS NORM (REVERSION) ...... Select Operative AHRS 37 4. Do not re-engage autopilot or yaw damper. 38 SGx Indicates both pilot & copilot are displaying the same AHRS, air data, & nav- 39 igation sources from one IC/SG. Accompanied by the ADCX & ATTX annunciators. 40 TCAS FAIL 41 Indicates that TCAS is failed. 1. TCAS Circuit Breaker (copilot’s 42 INSTRUMENTS/INDICATIONS group) ...... Pull & Reset 2. Verify correct transponder operation. Select opposite transponder. 43 3. Select ATC ALT mode on the RMU (ATC/TCAS) until the failed condition is resolved. 44

CL-126C EFFECTIVITY A-77.1 Change 2 45-226 & on, and priorAll aircraft modified by SB 45-55-6 Primary Flight Display (PFD) Annunciations (Cont)

36 YD (flash) YD (steady) 37 WIND SHR 38 TGT 39 WX 40

41 TGT Indicates a weather radar target alert is activated. Take appropriate action 42 to verify the weather radar alert.

43 WIND SHR Indicates increasing head wind (or decreasing tail wind) and vertical up 44 drafts typically associated with the leading edge of microburst windshears. During takeoff: 45 1. Thrust Lever(s)...... Select T/O Detent or APR As Required 2. Takeoff/go-around target pitch attitude should be maintained until 46 safe climb-out is assured. During approach: 47 1. Add wind and gust allowances to the approach speed. Increase thrust if necessary. 48 2. Avoid getting low on the approach glide path or letting the thrust levers remain at flight idle for extended periods of time. 49 WX 50 Indicates an invalid weather radar.

51 YD (flash) Flashes for 5 seconds & clears. Indicates the yaw damper has been disen- 52 gaged by the pilot.

EFFECTIVITY All CL-126C Change 1 A-78 Primary Flight Display (PFD) Annunciations (Cont) YD (steady) 35 Indicates the yaw damper has failed and is disengaged. Autopilot and rudder boost are inoperative. 36 On the ground: 1. Control Wheel Master (MSW)...... Depress & Release 37 2. IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group)...... Pull & Reset 38 3. NOSE STEER ...... ON 4. ●If amber YD extinguishes, this checklist is complete. 39 ● 4. If amber YD remains illuminated, do not take off. The yaw 40 damper and rudder boost are inoperative. In flight: 41 1. Control Wheel Master (MSW)...... Depress & Release 2. ●If amber YD extinguishes: 42 a. Yaw Damper...... Engage 43 b. This checklist is complete. 2. ●If amber YD remains illuminated: 44 a. Maintain 33,000 feet or below. 45 b. Airspeed ...... ≥ 0.65 MI Until Below 33,000 Feet If conditions permit: 46 c. IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ...... Pull & Reset 47 d. ■If amber YD remains illuminated: (1) Land as soon as practical. 48 (2) This checklist is complete. 49 d. ■If amber YD extinguishes: (1) Yaw Damper ...... Engage 50 (2) This checklist is complete. 51 37

CL-126C EFFECTIVITY A-79 Change 1 45-002 thru 45-225All not modified by SB 45-55-6 Primary Flight Display (PFD) Annunciations (Cont) YD (steady) Indicates the yaw damper has failed & is disengaged. Autopilot and rudder 35 boost are inoperative. On the ground: 36 1. Control Wheel Master (MSW)...... Depress & Release 37 2. IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group)...... Pull & Reset 38 3. NOSE STEER ...... ON 4. ●If amber YD extinguishes, this checklist is complete. 39 4. ●If amber YD remains illuminated, do not take off. The yaw damper and rudder boost are inoperative. 40

In flight: 41 1. Control Wheel Master (MSW)...... Depress & Release 2. ●If amber YD extinguishes: 42 a. Yaw Damper...... As Desired 43 b. This checklist is complete. 2. ●If amber YD remains illuminated and conditions permit: 44 a. IC/SG 2 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ...... Pull & Reset 45 to Regain Autopilot b. ■If amber YD remains illuminated, this checklist is complete. 46 b. ■ If amber YD extinguishes: 47 (1) Yaw Damper ...... As Desired (2) This checklist is complete. 48

CL-126C EFFECTIVITY A-79.1 Change 1 45-226 & on, and priorAll aircraft modified by SB 45-55-6 Radio Management Unit (RMU) Failure

36 1. Respective PRI & SEC Circuit Breakers (AVIONICS group [COMMUNICATIONS - 37 RMU 1 or 2 PWR]) ...... Pull & Reset If RMU failure remains: 38 2. Tune radios using the cross-side RMU’s 1/2 function or through the FMS CDU, or use the Clearance Delivery Radio (Com 1 & Nav 1 39 only, no DME is available with Clearance Delivery Radio in EMRG).

40 ANTI-SKIDANTI-SKID FAIL FAIL 41 1. ANTI-SKID ...... OFF, then On 2. Refer to Section V in the AFM for increased stopping distances for 42 anti-skid OFF landing. 3. Cautiously apply brakes as required. 43

44 CPLTCPLT BRK BRK FAULT FAULT 1. Use pilot’s brakes. 45

46 GEARGEAR “GEAR” ● 47 1. If the gear is in transit & airspeed is greater than 210 KIAS: a. Slow to below 200 KIAS. 48 b. This checklist is complete. 1. ●If the Radio Altimeter is inoperative, airspeed is less than 170 49 KIAS, altitude is below 14,500 feet, thrust levers are less than MCR, & the landing gear is not down & locked: 50 a. RAD ALT 1 Circuit Breaker (pilot’s INSTRUMENTS/INDICATIONS group) ...... Set 51 b. Extend gear prior to landing. 52 c. This checklist is complete.

38 EFFECTIVITY All CL-126C Change 1 A-80 LL INBD INBD BRK BRK FAIL FAIL R INBD BRK FAIL R INBD BRK FAIL 35 LRLR INBD INBD BRK BRK FAIL FAIL

1. ●If failure occurs just after gear extension and conditions 36 permit: a. Gear ...... UP 37 b. INBD BRAKES Circuit Breaker (pilot’s GEAR/HYDRAULICS group)...... Set, or Pull & Reset 38 c. AUX HYD ...... ON 39 d. Gear ...... DN e. ■If INBD BRK FAIL remains illuminated, go to step 2. 40 e. ■If INBD BRK FAIL extinguishes, this checklist is complete. 41 1. ●If failure is not associated with gear extension, go to step 2. 2. Refer to Emergency Braking, Tab 16 , or Emergency Brake 42 Landing, Tab 42 . Emergency brakes should be available on ALL brakes. 43 38 44

CL-126C EFFECTIVITY A-81 Change 1 Change 1 All NWSNWS FAIL FAIL

36 During taxi: 1. Maintain directional control using differential braking. 37 2. Nose Wheel Steering...... Disengage (use MSW) 38 3. Thrust Levers ...... IDLE 4. Brake to a stop. 39 5. NOSE STEER ...... ON 40 Taxi is possible using differential braking & thrust. Avoid sharp turns. If a sharp turn is made, it may not be possible to straighten the nose wheel by differential braking. 41 During takeoff or landing: 42 1. Maintain directional control using differential braking. 2. Nose Wheel Steering...... Disengage (use MSW) 43 In flight: 1. After gear is down, NOSE STEER ...... ON 44 If NWS FAIL remains illuminated: 45 2. Maintain directional control using rudder and differential braking on landing. 46

A-82 EFFECTIVITY CL-126C All Change 1 DL BRK OUTBD FAIL BRK FAIL LRR OUTBDOUTBD BRKBRK FAILFAIL LR OUTBD BRK FAIL 35

1. ●If failure occurs just after gear extension and conditions 36 permit: a. Gear ...... UP 37 b. OUTBD BRAKES Circuit Breaker (copilot’s GEAR/HYD group)...... Set, or Pull & Reset 38 c. AUX HYD ...... ON 39 d. Gear ...... DN e. ■If OUTBD BRK FAIL remains illuminated, go to step 2. 40 e. ■If OUTBD BRK FAIL extinguishes, this checklist is complete. 41 1. ●If failure is not associated with gear extension, go to step 2. 2. Refer to Emergency Braking, Tab 16 , or Emergency Brake 42 Landing, Tab 42 . Emergency brakes should be available on ALL brakes. 43

PLTPLT BRK BRK FAULT FAULT 44

Use copilot’s brakes. 45

CL-126C EFFECTIVITY A-83 Change 1 All Landing Gear AUX HYD Extension 36 The landing gear free fall procedure should be used to extend the landing gear in case of electrical or hydraulic problems. Use of landing 37 gear free fall is recommended to reserve hydraulic pressure for flaps and brakes. The AUX HYD pump and HYD XFLOW valve can also operate the landing gear system. If main hydraulic system has failed, do not use the 38 AUX HYD system to retract landing gear, unless a critical performance situation exists. 39 To use AUX HYD system to extend landing gear: 40 1. Airspeed...... 180 KIAS Recommended 2. GEAR FREEFALL Lever (copilot’s side pedestal)...... UP 41 3. HYD XFLOW...... ON 4. AUX HYD ...... ON 42 5. Gear ...... DN 43 After gear has extended: 6. HYD XFLOW...... Off 44 7. AUX HYD ...... Off 45 Landing Gear Free Fall 46 1. Airspeed...... 180 KIAS Recommended 2. Gear ...... DN 47 3. AUX HYD ...... Off 48 4. ●If Landing Gear Free Fall is conducted because of an electrical problem: 49 a. GEAR Circuit Breaker (pilot’s GEAR/ HYDRAULICS group) ...... Pull 50 b. Go to step 5. 4. ●If Landing Gear Free Fall is conducted because of a hydraulic 51 system problem: a. GEAR Circuit Breaker (pilot’s GEAR/ 52 HYDRAULICS group) ...... Set b. Go to step 5. Change 1 EFFECTIVITY All CL-126C A-84 Change 1 5. GEAR FREEFALL Lever (copilot’s side pedestal) ...... Push Full Down & Latch Forward 6. Gear...... Check Three Green DOWN 35 The two white (main gear) in-transit lights may also be illuminated. 7. ●If any of the three green DOWN lights fail to illuminate: 36 a. ■If there is no indication of a hydraulic system fluid loss, the Landing Gear AUX HYD Extension procedure, Tab 39 , 37 may be attempted. a. ■If there is indication of a hydraulic system fluid loss, the 38 Landing Gear AUX HYD Extension procedure, Tab 39 , may still be attempted. However, depending on where the 39 hydraulic fluid loss occurred, may result in loss of auxiliary hydraulic fluid. In this case, normal braking may not be available upon landing. Refer to Emergency Braking, Tab 16 . 40 b. Refer to Gear Up Landing, Tab 49 if three green DOWN lights fail to illuminate. 41 ● 7. If three green DOWN and two white in-transit lights are indi- 42 cated: a. This checklist is complete. 43

Unsafe Gear Indication — DN Position 44

45 ILLUMINATED ADVISORY INDICATION (white hash) GEAR/HYD N - CORRESPONDING GEAR POSITION NOSE STEE R

DOWN DOES NOT AGREE WITH LANDING GEAR L DOWN R 46 CONTROL SWITCH POSITION. ANTI-SKID DOWNDOWN - CORRESPONDING MAIN GEAR INBOARD OFF

UP DOOR IS NOT UP AND LOCKED. AUX HYD 47

VL O 200 ON ILLUMINATED DOWN INDICATION (GREEN) VL E 260 - CORRESPONDING GEAR IS DOWN AND HYDX FLOW 48 ON LOCKED. DN 49 1. ●If alternate extension is possible, attempt either Landing Gear Free Fall, Tab 39 , or Landing Gear AUX HYD Extension, Tab 50 39 as appropriate. 1. ●If alternate extension is not advised due to known or sus- 51 Change 2 pected mechanical binding, refer to Gear Up Landing, Tab49 . 40 EFFECTIVITY CL-126C Change 2 All A-85 Stabilizer Heat Failure Landing 36 (STAB TEMP LOW) If approach & landing must be made with any ice (or suspected ice) on the 37 horizontal stabilizer: 1. Complete Descent procedure, Normal Checklist. 38 2. Final Approach Speed ...... VLND8 + 30, Computed & Set 39 Refer to Approach Speeds — Abnormal Landings, this page. 3. Normal Landing Distance ...... Multiply by 2.2 40 4. Approach Setup & Crew Briefing ...... Complete 41 5. ENG SYNC ...... OFF 6. HI FLOW ...... Off 42 7. FLAPS ...... 8°, Check Indication

43 8. SPOILER ...... ARM 9. AUX HYD ...... ON 44 10. Gear ...... DN Three Green DOWN 45 11. L & R LDG/TAXI Lights ...... On as Required 12. L & R IGN...... ON 46 13. FLAP (EGPWS) ...... OFF 47 14. EICAS/SUMRY Page ...... Check Approach Speeds — Abnormal Landings (Gear Down) 48 VLNDX (X = FLAPS) — KIAS ALT WEIGHT FLAPS 49 FEET LB UP (0°) 8° 20° 14,000 117 115 110 15,000 121 119 114 50 16,000 125 122 118 17,000 128 125 121 4000 18,000 132 129 124 and 19,000 135 132 127 51 BELOW 19,200 135 132 127 20,000 138 134 130 21,000 140 137 132 52 21,500 142 138 133 For altitudes above 4000 feet, refer to the AFM, Section V. Figures in shaded area are above maximum certified landing weight. EFFECTIVITY Change 1 All CL-126C A-86 Change 1 Wing and Stabilizer Heat Failure Landing (STAB and WING TEMP LOW) 35 If approach and landing must be made with any ice on the wing leading edge and any ice on the horizontal stabilizer: 36 1. Complete Descent procedure, Normal Checklist. 37 2. Final Approach Speed ...... VLND8 + 30, Computed & Set Refer to Approach Speeds — Abnormal Landings, previous page. 38 3. Normal Landing Distance ...... Multiply by 2.2 39 4. Approach Setup & Crew Briefing...... Complete 5. ENG SYNC...... OFF 40 6. HI FLOW...... Off 41 7. FLAPS ...... 8°, Check Indication 8. SPOILER ...... ARM 42 9. AUX HYD...... ON 10. Gear ...... DN 43 Three Green DOWN 11. L & R LDG/TAXI Lights ...... On as Required 44 12. L & R IGN ...... ON 45 13. FLAP (EGPWS)...... OFF 14. EICAS/SUMRY Page...... Check 46

41 47

EFFECTIVITY CL-126C Change 1 All A-87 Wing Heat Failure Landing 36 (WING TEMP LOW) If approach and landing must be made with any ice (or suspected ice) on 37 the wing leading edge: 1. Complete Descent procedure, Normal Checklist. 38 2. Final Approach Speed ...... VLND8 + 30, Computed & Set 39 Refer to Approach Speeds — Abnormal Landings, this page. 3. Normal Landing Distance ...... Multiply by 2.2 40 4. Approach Setup & Crew Briefing ...... Complete

41 5. ENG SYNC ...... OFF 6. HI FLOW ...... Off 42 7. FLAPS ...... 8°, Check Indication 8. SPOILER ...... ARM 43 9. AUX HYD ...... ON 44 10. Gear ...... DN Three Green DOWN 45 11. L & R LDG/TAXI Lights ...... On as Required 12. L & R IGN...... ON 46 13. FLAP (EGPWS) ...... OFF 47 14. EICAS/SUMRY Page ...... Check

48 Approach Speeds — Abnormal Landings (Gear Down) VLNDX (X = FLAPS) — KIAS 49 ALT WEIGHT FLAPS FEET LB UP (0°) 8° 20° 14,000 117 115 110 15,000 121 119 114 50 16,000 125 122 118 17,000 128 125 121 4000 18,000 132 129 124 and 19,000 135 132 127 51 BELOW 19,200 135 132 127 20,000 138 134 130 21,000 140 137 132 52 21,500 142 138 133 For altitudes above 4000 feet, refer to the AFM, Section V. Figures in shaded area are above maximum certified landing weight. 42 EFFECTIVITY All CL-126C A-88 Change 1 Normal Electrical System Failure Landing

This procedure would be used for landing with a normal electrical system 35 failure & operation with emergency battery. Operative Equipment Inoperative Equipment 36 Instruments/Avionics Standby Instruments Display Units 37 COM 1 & L Audio Panel ➀ AHRS 1 & 2, ADC 1 & 2 RMU 1: Engine Pages ➀ RMU 2, NAV 2, COM 2 38 RMU 1: ILS 1 Tuning ➀ FMS(es) — ATC 1 & 2 (transponder) Flight Controls 39 — L & R Stall Warning Systems — Spoilers/Spoilerons/Flaps 40 — Mach Trim & Autopilot — Pitch, Aileron & Rudder Trims 41 — Pitch Trim Bias Anti-Icing Nacelle Heat (defaults ON) Pitot Heat, Wing/Stab & Wshld 42 Engines — L & R Engine Computers 43 (reverts to OFF mode) — Thrust Reversers Environmental/Pressurization 44 CABIN PRESSURE CONTROL Display Environmental Control (defaults to cold) R Cabin Pressure; L Cabin Pressure 45 Use MANUAL rate control Landing Gear/Brakes 46 Landing Gear (Control & Indication) Nose Wheel Steering Inboard Brakes with Anti-Skid Outboard Brakes Emergency Brakes — 47 Lighting — External Lighats 48 ➀ One or both main batteries not depleted. 1. MANUAL Rate Control...... Depressurize Cabin Prior to Landing 49 2. Standby Altimeter ...... Set 50 3. Cabin Check ...... Complete a. Brief passengers of no smoking & seat belt requirements. 51 b. Swivel Seats...... Forward or Aft and in Outboard Position Headrests in Place for Occupied Aft Facing Seats 42 EFFECTIVITY Change 2 CL-126C Change 2 All A-89 c. Work Tables and Toilet Doors...... Check Stowed d. Emergency Exit ...... Aisle Clear 36 4. Final Approach Speed ...... VLNDX for the Flap Extension Obtained 37 Refer to Approach Speeds — Abnormal Landings, this page. 5. Normal Landing Distance ...... Multiply by 2.2 38 6. Approach Setup & Crew Briefing ...... Complete 39 7. Gear ...... DN Three Green DOWN 40 After touchdown: 8. EMERGENCY/PARKING BRAKE Handle ...... Pull Smoothly 41 Increasing Extension Increases Brake Pressure 42 Approach Speeds — Abnormal Landings (Gear Down) 43 VLNDX (X = FLAPS) — KIAS ALT WEIGHT FLAPS FEET LB UP (0°) 8° 20° 44 14,000 117 115 110 15,000 121 119 114 16,000 125 122 118 17,000 128 125 121 45 4000 18,000 132 129 124 and 19,000 135 132 127 BELOW 19,200 135 132 127 20,000 138 134 130 46 21,000 140 137 132 21,500 142 138 133

47 For altitudes above 4000 feet, refer to the AFM, Section V. Figures in shaded area are above maximum certified landing weight. 48

EFFECTIVITY All CL-126C A-90 Change 1 Emergency Brake Landing (NORM BRK FAIL red CAS) 35 (INBD BRK FAIL amber CAS) (OUTBD BRK FAIL amber CAS) 36 This procedure would be used for landing with emergency brake for stopping. All other systems (flaps, spoilers, etc.) are operational. This proce- 37 dure may be used in association with the following CAS procedures: red NORM BRK FAIL (or NORMAL BRAKES FAIL red CWP), amber INBD BRK 38 FAIL & amber OUTBD BRK FAIL. 1. Complete Descent procedure, Normal Checklist. 39

2. Final Approach Speed ...... VREF, Computed & Set 40 3. Normal Landing Distance ...... Use Anti-Skid OFF Corrections Refer to Section V in the AFM 41 4. Approach Setup & Crew Briefing...... Complete 5. ENG SYNC...... OFF 42 6. HI FLOW...... Off 43 7. FLAPS ...... 8° or 20° 8. SPOILER ...... ARM 44 9. AUX HYD...... ON 45 10. Gear ...... DN, Three Green DOWN 11. L & R LDG/TAXI Lights ...... On 46 12. L & R IGN ...... ON 13. FLAPS ...... DN, Check Indication 47 14. EICAS/SUMRY Page...... Check 48 After touchdown: 15. EMERGENCY/PARKING BRAKE Handle ...... Pull Smoothly 49 Increasing Extension Increases Brake Pressure 50 43 51

EFFECTIVITY CL-126C Change 1 All A-91 Single-Engine Landing

36 1. Complete Descent procedure, Normal Checklist.

37 2. Final Approach Speeds...... VLND20 & VAPP, Set Refer to Approach Speeds — Abnormal Landings, this page. 38 3. Normal Landing Distance ...... Multiply by 1.2 4. Approach Setup & Crew Briefing ...... Complete 39 5. ENG SYNC ...... OFF 40 6. HI FLOW ...... Off 7. FLAPS ...... 20° 41 8. SPOILER ...... ARM 42 9. AUX HYD ...... ON 10. Gear ...... DN 43 Three Green DOWN 11. L & R LDG/TAXI Lights ...... On as Required 44 12. Operating Engine IGN...... ON 45 13. FLAP (EGPWS) ...... OFF 14. EICAS/SUMRY Page ...... Check 46

47 Approach Speeds — Abnormal Landings (Gear Down) VLNDX (X = FLAPS) — KIAS 48 ALT WEIGHT FLAPS FEET LB UP (0°) 8° 20° 14,000 117 115 110 15,000 121 119 114 49 16,000 125 122 118 17,000 128 125 121 4000 18,000 132 129 124 and 19,000 135 132 127 50 BELOW 19,200 135 132 127 20,000 138 134 130 21,000 140 137 132 51 21,500 142 138 133 For altitudes above 4000 feet, refer to the AFM, Section V. Change 2 52 Figures in shaded area are above maximum certified landing weight.

EFFECTIVITY All CL-126C A-92 Change 2 Aileron Jammed Landing (ROLL DISC white CAS) 35

1. Complete Descent procedure, Normal Checklist. 36 2. Final Approach Speed ...... VREF, Computed & Set 3. Normal Landing Distance ...... Computed 37 4. Approach Setup & Crew Briefing...... Complete 38 5. ENG SYNC...... OFF 6. HI FLOW...... Off 39 7. FLAPS ...... 8° or 20° 40 8. SPOILER ...... ARM 9. AUX HYD...... ON 41 10. Gear ...... DN Three Green DOWN 42 11. L & R LDG/TAXI Lights ...... On 12. L & R IGN ...... ON 43 13. FLAPS ...... DN, Check Indication 44 14. EICAS/SUMRY Page...... Check 45 44 46

EFFECTIVITY CL-126C Change 1 All A-93 Aileron Trim Tab Jammed Landing

36 1. Complete Descent procedure, Normal Checklist.

37 2. Final Approach Speed ...... VREF, Computed & Set 3. Normal Landing Distance ...... Computed 38 4. Approach Setup & Crew Briefing ...... Complete 5. ENG SYNC ...... OFF 39 6. HI FLOW ...... Off 40 7. FLAPS ...... 8° or 20° 8. SPOILER ...... ARM 41 9. AUX HYD ...... ON 42 10. Gear ...... DN Three Green DOWN 43 11. L & R LDG/TAXI Lights ...... On 12. L & R IGN...... ON 44 13. FLAPS ...... DN, Check Indication 45 14. EICAS/SUMRY Page ...... Check

Change 2 EFFECTIVITY All CL-126C A-94 Change 2 Elevator Jammed Landing (ELEVATOR DISC white CAS) 35 1. Complete Descent procedure, Normal Checklist. 36 2. Final Approach Speed ...... VLND8 + 10, Computed & Set Refer to Approach Speeds — Abnormal Landings, this page. 37 3. Normal Landing Distance ...... Multiply by 1.6 4. Approach Setup & Crew Briefing...... Complete 38

5. ENG SYNC...... OFF 39 6. HI FLOW...... Off 7. FLAPS ...... 8°, Check Indication 40 8. SPOILER ...... ARM 41 9. AUX HYD...... ON 10. Gear ...... DN 42 Three Green DOWN 11. L & R LDG/TAXI Lights ...... On 43 12. L & R IGN ...... ON 44 13. FLAP (EGPWS)...... OFF 14. EICAS/SUMRY Page...... Check 45

Approach Speeds — Abnormal Landings (Gear Down) 46 VLNDX (X = FLAPS) — KIAS ALT WEIGHT FLAPS 47 FEET LB UP (0°) 8° 20° 14,000 117 115 110 15,000 121 119 114 16,000 125 122 118 48 17,000 128 125 121 4000 18,000 132 129 124 and 19,000 135 132 127 BELOW 19,200 135 132 127 49 20,000 138 134 130 21,000 140 137 132 21,500 142 138 133 50 For altitudes above 4000 feet, refer to the AFM, Section V. Figures in shaded area are above maximum certified landing weight. 51 45

EFFECTIVITY Change 1 CL-126C Change 1 All A-95 Partial Flap Landing 36 (FLAPS FAIL) 1. Complete Descent procedure, Normal Checklist.

37 2. Final Approach Speed ...... VLNDX for the Flap Deflection Obtained

38 Refer to Approach Speeds — Abnormal Landings, this page. Use the lesser flap deflection VLNDX speed for flap settings between the detent values. 39 3. Normal Landing Distance ...... Multiply by 1.3 40 4. Approach Setup & Crew Briefing ...... Complete 5. ENG SYNC ...... OFF 41 6. HI FLOW ...... Off 42 7. FLAPS ...... As Obtained 8. SPOILER ...... ARM 43 9. AUX HYD ...... ON 10. Gear ...... DN 44 Three Green DOWN

45 11. L & R LDG/TAXI Lights ...... On 12. L & R IGN...... ON 46 13. FLAP (EGPWS) ...... OFF 14. EICAS/SUMRY Page ...... Check 47 Approach Speeds — Abnormal Landings (Gear Down) 48 VLNDX (X = FLAPS) — KIAS ALT WEIGHT FLAPS 49 FEET LB UP (0°) 8° 20° 14,000 117 115 110 15,000 121 119 114 16,000 125 122 118 50 17,000 128 125 121 4000 18,000 132 129 124 and 19,000 135 132 127 BELOW 19,200 135 132 127 51 20,000 138 134 130 21,000 140 137 132 21,500 142 138 133 52 For altitudes above 4000 feet, refer to the AFM, Section V. Figures in shaded area are above maximum certified landing weight.

EFFECTIVITY All CL-126C A-96 Change 1 Rudder Jammed Landing 1. Complete Descent procedure, Normal Checklist. 35 2. Final Approach Speed ...... VREF, Computed & Set 36 3. Normal Landing Distance ...... Computed 4. Approach Setup & Crew Briefing...... Complete 37 5. ENG SYNC...... OFF 6. HI FLOW...... Off 38 7. FLAPS ...... 8° or 20° 39 8. SPOILER ...... ARM 9. AUX HYD...... ON 40 10. Gear ...... DN Three Green DOWN 41 11. NOSE STEER ...... Check Off 42 12. L & R LDG/TAXI Lights ...... On 13. L & R IGN ...... ON 43 14. FLAPS ...... DN, Check Indication 44 15. EICAS/SUMRY Page...... Check 16. Carry power down to touchdown to aid in directional control. 45 17. Yaw Damper ...... Off After landing: 46

18. Maintain directional control with differential braking. 47

46 48

Change 2 51

EFFECTIVITY CL-126C Change 2 All A-97 Rudder Trim Tab Jammed Landing

36 1. Complete Descent procedure, Normal Checklist. 37 2. Final Approach Speed ...... VREF, Computed & Set 3. Normal Landing Distance ...... Computed 38 4. Approach Setup & Crew Briefing ...... Complete 5. ENG SYNC ...... OFF 39 6. HI FLOW ...... Off 40 7. FLAPS ...... 8° or 20° 8. SPOILER ...... ARM 41 9. AUX HYD ...... ON 42 10. Gear ...... DN Three Green DOWN 43 11. L & R LDG/TAXI Lights ...... On 12. L & R IGN...... ON 44 13. FLAPS ...... DN, Check Indication 45 14. EICAS/SUMRY Page ...... Check 15. Yaw Damper...... Off 46

EFFECTIVITY All CL-126C A-98 Change 1 Spoilers Extended Landing (SPOILER EXT or SPOILER FAIL) 35 1. Complete Descent procedure, Normal Checklist. 2. SPOILER ...... RET 36

3. Final Approach Speed ...... VLND8 + 5, Computed & Set 37 Refer to Approach Speeds — Abnormal Landings, this page. 4. Normal Landing Distance ...... Multiply by 1.6 38 5. Approach Setup & Crew Briefing...... Complete 39 6. ENG SYNC...... OFF 7. HI FLOW...... Off 40 8. FLAPS ...... 8°, Check Indication 41 9. AUX HYD...... ON 10. Gear ...... DN 42 Three Green DOWN 11. L & R LDG/TAXI Lights ...... On 43 12. L & R IGN ...... ON 13. FLAP (EGPWS)...... OFF 44 14. EICAS/SUMRY Page...... Check 45 Approach Speeds — Abnormal Landings (Gear Down) 46 VLNDX (X = FLAPS) — KIAS ALT WEIGHT FLAPS FEET LB UP (0°) 8° 20° 47 14,000 117 115 110 15,000 121 119 114 16,000 125 122 118 48 17,000 128 125 121 4000 18,000 132 129 124 and 19,000 135 132 127 BELOW 19,200 135 132 127 49 20,000 138 134 130 21,000 140 137 132 21,500 142 138 133 50 For altitudes above 4000 feet, refer to the AFM, Section V. Figures in shaded area are above maximum certified landing weight. Change 1 51

EFFECTIVITY CL-126C Change 1 All A-99 Spoiler Jammed Landing 36 (L SPOILER JAM) (R SPOILER JAM) 37 1. Complete Descent procedure, Normal Checklist. 2. SPOILER ...... Deploy, as Required to Minimize Roll 38 3. Final Approach Speed ...... VLND8 + 5, Computed & Set 39 Refer to Approach Speeds — Abnormal Landings, this page. 4. Normal Landing Distance ...... Multiply by 1.6 40 5. Approach Setup & Crew Briefing ...... Complete 6. ENG SYNC ...... OFF 41 7. HI FLOW ...... Off 42 8. FLAPS ...... 8°, Check Indication 9. AUX HYD ...... ON 43 10. Gear ...... DN Three Green DOWN 44 11. L & R LDG/TAXI Lights ...... On 45 12. L & R IGN...... ON 13. FLAP (EGPWS) ...... OFF 46 14. EICAS/SUMRY Page ...... Check 47 Approach Speeds — Abnormal Landings (Gear Down) 48 VLNDX (X = FLAPS) — KIAS ALT WEIGHT FLAPS 49 FEET LB UP (0°) 8° 20° 14,000 117 115 110 15,000 121 119 114 50 16,000 125 122 118 17,000 128 125 121 4000 18,000 132 129 124 and 19,000 135 132 127 51 BELOW 19,200 135 132 127 20,000 138 134 130 21,000 140 137 132 52 21,500 142 138 133 Change 1 For altitudes above 4000 feet, refer to the AFM, Section V. Figures in shaded area are above maximum certified landing weight. EFFECTIVITY All CL-126C A-100 Change 1 Stabilizer Jammed Landing If elevator pull force is encountered — Stabilizer jammed in nose-down 35 trim position (aircraft in climb, cruise, or descent configuration): 1. Complete Jammed Stabilizer — Both PRI and SEC Trim Inopera- 36 tive procedure, Tab 19 . 2. Complete Descent procedure, Normal Checklist. 37

3. Final Approach Speed ...... VLND0, Computed & Set 38 Refer to Approach Speeds — Abnormal Landings, previous page. 4. Normal Landing Distance ...... Multiply by 1.3 39 5. Approach Setup & Crew Briefing...... Complete 40 6. ENG SYNC...... OFF 7. HI FLOW...... Off 41 8. FLAPS ...... UP (0°), Check Indication 42 9. PIT TRIM BIAS ...... NUP or NDN Hold switch to trim out and reduce elevator force. 43 10. SPOILER ...... ARM 11. AUX HYD...... ON 44 12. Gear ...... DN Three Green DOWN 45 13. L & R LDG/TAXI Lights ...... On 46 14. L & R IGN ...... ON 15. FLAP (EGPWS)...... OFF 47 16. EICAS/SUMRY Page...... Check If elevator push force is encountered — Stabilizer jammed in nose-up 48 trim position (aircraft in takeoff or landing configuration): 49 1. Move C.G. forward if possible. Conduct normal landing. 2. Complete Descent procedure, Normal Checklist. 50 3. Complete Approach procedure, Normal Checklist. 51 Change 1 4. Complete Before Landing procedure, Normal Checklist.

EFFECTIVITY CL-126C Change 1 All A-101 Main Hydraulic System Failure Landing 36 (MAIN HYD PRESS) 1. Complete Descent procedure, Normal Checklist. 37 2. Complete Landing Gear Free Fall, Tab 39 . 38 3. If AUX HYD is available: a. AUX HYD...... ON 39 b. SUMRY Page B-ACUM Pressure...... 2310-3600 psi c. HYD XFLOW ...... ON 40 d. FLAPS...... 20°, Check Indication 41 (Do not extend beyond 20°) When flaps reach their maximum extension: 42 e. HYD XFLOW ...... Off f. AUX HYD...... Off 43 4. Final Approach Speed ...... VLNDX for the Flap Extension Obtained 44 Refer to Approach Speeds — Abnormal Landings, next page. 5. Normal Landing Distances: 45 a. ●If emergency braking is used:

46 (1) Multiply by 2.2 (2) Go to step 6. 47 a. ●If normal braking is used with AUX HYD pressure available: 48 (1) Multiply by 1.4 (2) Go to step 6. 49 6. Approach Setup & Crew Briefing ...... Complete 50 7. ENG SYNC ...... OFF 8. HI FLOW ...... Off 51 9. Gear ...... DN Three Green DOWN 52 Change 2 The two white (main gear) in-transit lights may also be illuminated. 10. L & R LDG/TAXI Lights ...... On EFFECTIVITY All CL-126C A-102 Change 2 11. L & R IGN ...... ON 12. FLAP (EGPWS)...... OFF 35 13. EICAS/SUMRY Page...... Check Prior to touchdown: 36 14. AUX HYD...... ON After touchdown: 37 15. ●If AUX HYD pressure is available, normal anti-skid braking should be available from the auxiliary pump. Be prepared to use 38 EMERGENCY BRAKING. This checklist is complete. 39 15. ●If AUX HYD pressure is not available, use EMERGENCY BRAKING. 40 a. EMERGENCY/PARKING BRAKE Handle...... Pull Smoothly Increasing Extension Increases Brake Pressure 41

b. Rudder and/or Nose Wheel 42 Steering...... As Required for Directional Control c. This checklist is complete. 43 Approach Speeds — Abnormal Landings (Gear Down) 44 VLNDX (X = FLAPS) — KIAS ALT WEIGHT FLAPS FEET LB UP (0°) 8° 20° 45 14,000 117 115 110 15,000 121 119 114 16,000 125 122 118 46 17,000 128 125 121 4000 18,000 132 129 124 and 19,000 135 132 127 BELOW 19,200 135 132 127 47 20,000 138 134 130 21,000 140 137 132 21,500 142 138 133 48 For altitudes above 4000 feet, refer to the AFM, Section V. Figures in shaded area are above maximum certified landing weight. 49 49 50

51 Change 2

EFFECTIVITY CL-126C Change 2 All A-103 Gear Up Landing

36 1. Brief passengers as required.

37 a. Location & operation of emergency exits. b. Secure all loose items. 38 c. Shoulder Harness & Seat Belts...... Secure d. Emergency landing brace position. 39 2. Complete Descent procedure, Normal Checklist. 40 3. PACK...... OFF 4. FLAPS ...... DN 41 5. Perform normal power-on approach at VREF & touch down at the lowest possible airspeed with minimum sink rate. Do not decelerate 42 below shaker speed. 6. ●If no landing gear has extended: 43 a. Plan to land slightly nose high. 44 b. Go to step 7. 6. ●If the nose gear fails to extend: 45 a. Relocate passengers aft to obtain aft C.G., if possible. 46 b. SPOILER...... ARM c. AUX HYD...... ON 47 d. EICAS/SUMRY Page ...... Check

48 e. Hold the nose off the runway as long as elevator control is available. 49 f. ■If hydraulic pressure is not available: (1) Use EMERGENCY/PARKING BRAKE. 50 (2) Go to step 7. f. ■If hydraulic pressure is available: 51 (1) Normal braking may be used & spoilers deployed. Use rud- 52 der and/or brakes for directional control. Be prepared to use EMERGENCY/PARKING BRAKE. (2) Go to step 7. EFFECTIVITY All CL-126C A-104 Change 1 6. ●If a main gear fails to extend: a. Plan to land on the same side of the runway as the extended gear. 35 b. ANTI-SKID ...... OFF 36 Heavy brake pressures may skid the tires & cause tire blow-out. c. NOSE STEER...... Check ON to Assist 37 in Maintaining Directional Control d. AUX HYD ...... ON 38 e. EICAS/SUMRY Page ...... Check 39 f. Hold the applicable wing up as long as possible. Maintain directional control with rudder & nose wheel steering. 40 g. ■If hydraulic pressure is not available: (1) Use EMERGENCY/PARKING BRAKE. 41 (2) Go to step 7. 42 g. ■If hydraulic pressure is available: (1) Normal braking may be used & spoilers deployed. Use rud- 43 der and/or brakes for directional control. Be prepared to use EMERGENCY/PARKING BRAKE. 44 (2) Go to step 7. At touchdown: 45 7. Thrust Levers...... CUTOFF 46 8. FIRE (L & R ENGINE) ...... FIRE PUSH After aircraft stops: 47 9. EMER LIGHTS ...... ON 10. EMER BATT, L & R BATT ...... OFF 48

11. Evacuate the aircraft: 49 a. Cabin Entry Door ...... Open & Exit b. Aft Emergency Exit...... Open & Exit 50 50 51

EFFECTIVITY CL-126C Change 1 All A-105 36

44 INTENTIONALLY LEFT BLANK

EFFECTIVITY All CL-126C A-106 Change 1 Thrust Reverser Deployed Landing

1. Complete Descent procedure, Normal Checklist. 35

2. Final Approach Speed ...... VLND8 + 10, Computed & Set 36 Refer to Approach Speeds — Abnormal Landings, this page. 37 3. Normal Landing Distance ...... Multiply by 1.6 4. Approach Setup & Crew Briefing...... Complete 38 5. ENG SYNC...... OFF 6. HI FLOW...... Off 39

7. FLAPS ...... 8°, Check Indication 40 8. SPOILER ...... ARM 9. AUX HYD...... ON 41 10. Gear ...... DN Three Green DOWN 42 11. L & R LDG/TAXI Lights ...... On 43 12. Operating Engine IGN ...... ON 13. FLAP (EGPWS)...... OFF 44 14. EICAS/SUMRY Page...... Check 45 15. Yaw Damper ...... Off

Approach Speeds — Abnormal Landings (Gear Down) 46 VLNDX (X = FLAPS) — KIAS ALT WEIGHT FLAPS 47 FEET LB UP (0°) 8° 20° 14,000 117 115 110 15,000 121 119 114 48 16,000 125 122 118 17,000 128 125 121 4000 18,000 132 129 124 and 19,000 135 132 127 49 BELOW 19,200 135 132 127 20,000 138 134 130 21,000 140 137 132 50 21,500 142 138 133

Change 2 For altitudes above 4000 feet, refer to the AFM, Section V. 51 Figures in shaded area are above maximum certified landing weight.

EFFECTIVITY CL-126C Change 2 All A-107 Advisory/Status EICAS Index CAS or (EI) Message Page CAS or (EI) Message Page AHRS 1 BASIC A/S-18 EMER LIGHTS A/S-26 AHRS 2 BASIC A/S-18 EMER/PARK BRK A/S-25 AHRS 1-2 BASIC A/S-18 L ENG FIRE FAIL A/S-9 AP ELEV MISTRIM A/S-8 R ENG FIRE FAIL A/S-9 APR (EI) A/S-12 LR ENG FIRE FAIL A/S-9 APR (EI outbd N1s) A/S-12 L ENG SHUTDOWN A/S-10 L APR FAULT A/S-9 R ENG SHUTDOWN A/S-10 R APR FAULT A/S-9 LR ENG SHUTDOWN A/S-10 LR APR FAULT A/S-9 L ENG VIB MON A/S-10 APR ON (EI inbd N1s) A/S-12 R ENG VIB MON A/S-10 APU AVAILABLE A/S-8 LR ENG VIB MON A/S-10 AUTOSPLR ARMED A/S-13 L ENGCMPTR FAULT A/S-10 BRAKE FAULT A/S-25 R ENGCMPTR FAULT A/S-10 BUS TIE CLSD A/S-9 LR ENGCMPTR FAULT A/S-10 BUS TIE MANUAL A/S-9 L ENGINE CHIP A/S-11 L CAB PRESS FAIL A/S-13 R ENGINE CHIP A/S-11 R CAB PRESS FAIL A/S-13 LR ENGINE CHIP A/S-11 CAB PRESS MAN A/S-13 ENTRY DOOR PIN A/S-8 L CHECK EDS A/S-26 L ESS BUS FAULT A/S-9 R CHECK EDS A/S-26 R ESS BUS FAULT A/S-9 LR CHECK EDS A/S-26 LR ESS BUS FAULT A/S-9 CKLST MISMATCH A/S-19 EXTERNAL POWER A/S-9 CVR FAIL A/S-25 FDR FAIL A/S-26 DAU A REV A/S-19 L FUEL BAY LOW A/S-16 DAU B REV A/S-19 R FUEL BAY LOW A/S-16 DEP (EI) A/S-12 LR FUEL BAY LOW A/S-16

DU 1 FAN FAIL A/S-19 L FUEL FILTER A/S-17 ADVISORY/STATUS DU 2 FAN FAIL A/S-19 R FUEL FILTER A/S-17 DU 1-2 FAN FAIL A/S-19 LR FUEL FILTER A/S-17 DU 3 FAN FAIL A/S-20 L FUEL HEATER A/S-17 DU 4 FAN FAIL A/S-20 R FUEL HEATER A/S-17 DU 3-4 FAN FAIL A/S-20 LR FUEL HEATER A/S-17 L ECS FAULT A/S-13 L FUEL QTY FAULT A/S-17 R ECS FAULT A/S-13 R FUEL QTY FAULT A/S-17 ELEVATOR DISC A/S-14 FUEL QTY FAULT A/S-17 EMER DEPRESS A/S-13 FUEL XFLO OPEN A/S-16

Advisory/ Change 1 CL-126C EFFECTIVITY Change 1 All Status-i Advisory/Status EICAS Index (Cont) CAS or (EI) Message Page CAS or (EI) Message Page L FWSOV CLSD A/S-17 PAX OXY DEPLOY A/S-13 R FWSOV CLSD A/S-17 PIT TRIM BIAS A/S-14 LR FWSOV CLSD A/S-17 PIT TRIM MSCMP A/S-14 GND PROX FAIL A/S-20 PITCH TRIM OFF A/S-14 GPWS FAIL A/S-21 PRI TRIM FAULT A/S-14 GPWS FLAP OVRD A/S-20 REV (EI) A/S-12 GPWS G/S INHIB A/S-21 L REV AUTOSTOW A/S-26 GPWS SYS FAIL A/S-21 R REV AUTOSTOW A/S-26 L HYD PUMP LOW A/S-18 LR REV AUTOSTOW A/S-26 R HYD PUMP LOW A/S-18 L REV FAULT A/S-27 LR HYD PUMP LOW A/S-18 R REV FAULT A/S-27 HYD XFLOW ON A/S-18 LR REV FAULT A/S-27 IC 1 CNFG FAIL A/S-21 ROLL DISC A/S-15 IC 2 CNFG FAIL A/S-21 RUD BOOST INOP A/S-8 IC 1 FAN FAIL A/S-21 SEC PITCH TRIM A/S-15 IC 2 FAN FAIL A/S-21 SEC TRIM FAULT A/S-15 IC 1-2 FAN FAIL A/S-21 SPOILERS EXT A/S-15 IC 1 WOW INOP A/S-22 STAB TMP FAULT A/S-7 IC 2 WOW INOP A/S-22 START (EI) A/S-12 IC 1-2 WOW INOP A/S-22 L STBY PUMP ON A/S-18 ICE DETECTED A/S-7 R STBY PUMP ON A/S-18 IGN (EI) A/S-12 LR STBY PUMP ON A/S-18 IGN (EI) A/S-12 SYNC (EI) A/S-12 INSTR PNL TEMP A/S-22 T/O (EI) A/S-12 LBS/KGS CONFIG A/S-22 TAKEOFF TRIM A/S-15 MACH TRIM FAIL A/S-8 TERR FAIL A/S-22

ADVISORY/STATUS MAIN HYDQTY LO A/S-18 TERR INHIB or INHB A/S-23 MAN (EI) A/S-12 WARN AUDIO A/S-27 MCR (EI) A/S-12 L WARN PWR FAIL A/S-27 MCT (EI) A/S-12 R WARN PWR FAIL A/S-27 NAC (EI) A/S-12 WG/STAB HT OK A/S-7 NOSE BAY TEMP A/S-22 WHEEL MSTR A/S-16 NWS FAULT A/S-25 WINDSHEAR FAIL A/S-23 L OIL FILTER A/S-11 WING TMP FAULT A/S-7 R OIL FILTER A/S-11 L WSHLD HT FAULT A/S-7 LR OIL FILTER A/S-11 R WSHLD HT FAULT A/S-7 PACK HIGH FLOW A/S-13 LR WSHLD HT FAULT A/S-7

Advisory/ EFFECTIVITY CL-126C Change 1 Status-ii All Change 1 ADVISORY/STATUS ANNUNCIATIONS

All of the following CAS & EI illuminations are white unless otherwise indicated.

ANTI-ICING ...... A/S-7 ICE DETECTED...... A/S-7 L WSHLD HT FAULT R WSHLD HT FAULT LR WSHLD HT FAULT ...... A/S-7 STAB TMP FAULT ...... A/S-7 WG/STAB HT OK ...... A/S-7 WING TMP FAULT ...... A/S-7 AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS) ...... A/S-8 AP ELEV MISTRIM ...... A/S-8 MACH TRIM FAIL...... A/S-8 RUD BOOST INOP ...... A/S-8 AUXILIARY POWER UNIT (APU) ...... A/S-8 APU AVAILABLE ...... A/S-8 DOOR...... A/S-8 ENTRY DOOR PIN ...... A/S-8 ELECTRICAL...... A/S-9 BUS TIE CLSD...... A/S-9 BUS TIE MANUAL ...... A/S-9 L ESS BUS FAULT R ESS BUS FAULT LR ESS BUS FAULT...... A/S-9 EXTERNAL POWER...... A/S-9 ENGINE...... A/S-9 L APR FAULT R APR FAULT LR APR FAULT...... A/S-9

EFFECTIVITY CL-126C Advisory/ All Status-1 ENGINE (Cont) L ENG FIRE FAIL R ENG FIRE FAIL LR ENG FIRE FAIL...... A/S-9 L ENG SHUTDOWN R ENG SHUTDOWN LR ENG SHUTDOWN ...... A/S-10 L ENG VIB MON R ENG VIB MON LR ENG VIB MON...... A/S-10 L ENGCMPTR FAULT R ENGCMPTR FAULT LR ENGCMPTR FAULT...... A/S-10 L ENGINE CHIP R ENGINE CHIP LR ENGINE CHIP ...... A/S-11 L OIL FILTER R OIL FILTER LR OIL FILTER ...... A/S-11 EIs (Green)...... A/S-12 APR ...... A/S-12 MCR ...... A/S-12 MCT...... A/S-12 T/O ...... A/S-12 EIs (Green/White)...... A/S-12 APR ON...... A/S-12 APR ...... A/S-12 DEP ...... A/S-12 IGN ...... A/S-12 MAN ...... A/S-12 NAC ...... A/S-12 REV ...... A/S-12 START ...... A/S-12 SYNC ...... A/S-12 EFFECTIVITY Advisory/ CL-126C Status-2 All ENVIRONMENTAL/PRESSURIZATION L CAB PRESS FAIL R CAB PRESS FAIL...... A/S-13 CAB PRESS MAN...... A/S-13 L ECS FAULT R ECS FAULT...... A/S-13 EMER DEPRESS...... A/S-13 PACK HIGH FLOW...... A/S-13 PAX OXY DEPLOY...... A/S-13 FLIGHT CONTROLS ...... A/S-13 AUTOSPLR ARMED ...... A/S-13 ELEVATOR DISC ...... A/S-14 PIT TRIM BIAS...... A/S-14 PIT TRIM MSCMP ...... A/S-14 PITCH TRIM OFF ...... A/S-14 PRI TRIM FAULT...... A/S-14 ROLL DISC ...... A/S-15 SEC PITCH TRIM ...... A/S-15 SEC TRIM FAULT...... A/S-15 SPOILERS EXT ...... A/S-15 TAKEOFF TRIM ...... A/S-15 WHEEL MSTR ...... A/S-16 FUEL ...... A/S-16 L FUEL BAY LOW R FUEL BAY LOW LR FUEL BAY LOW...... A/S-16 FUEL XFLO OPEN ...... A/S-16 L FUEL FILTER R FUEL FILTER LR FUEL FILTER ...... A/S-17 L FUEL HEATER R FUEL HEATER LR FUEL HEATER ...... A/S-17

Change 1 EFFECTIVITY Advisory/ CL-126C All Status-3 Change 1 FUEL (Cont) L FUEL QTY FAULT R FUEL QTY FAULT...... A/S-17 FUEL QTY FAULT ...... A/S-17 L FWSOV CLSD R FWSOV CLSD LR FWSOV CLSD ...... A/S-17 L STBY PUMP ON R STBY PUMP ON LR STBY PUMP ON...... A/S-18 HYDRAULICS ...... A/S-18 HYD XFLOW ON...... A/S-18 L HYD PUMP LOW R HYD PUMP LOW LR HYD PUMP LOW...... A/S-18 MAIN HYDQTY LO...... A/S-18 INSTRUMENT/AVIONICS ...... A/S-18 AHRS 1 BASIC AHRS 2 BASIC AHRS 1-2 BASIC ...... A/S-18 CKLST MISMATCH ...... A/S-19 DAU A REV DAU B REV ...... A/S-19 DU 1 FAN FAIL DU 2 FAN FAIL DU 1-2 FAN FAIL...... A/S-19 DU 3 FAN FAIL DU 4 FAN FAIL DU 3-4 FAN FAIL...... A/S-20 GND PROX FAIL ...... A/S-20 GPWS FLAP OVRD ...... A/S-20 GPWS G/S INHB...... A/S-21

GPWS FAIL OR GPWS SYS FAIL ...... A/S-21

Advisory/ EFFECTIVITY Status-4 All CL-126C Change 1 INSTRUMENT/AVIONICS (Cont) IC 1 CNFG FAIL IC 2 CNFG FAIL ...... A/S-21 IC 1 FAN FAIL IC 2 FAN FAIL IC 1-2 FAN FAIL ...... A/S-21 IC 1 WOW INOP IC 2 WOW INOP IC 1-2 WOW INOP ...... A/S-22 INSTR PNL TEMP ...... A/S-22 LBS/KGS CONFIG...... A/S-22 NOSE BAY TEMP ...... A/S-22 TERR FAIL ...... A/S-22

TERR INHB OR TERR INHIB...... A/S-23 WINDSHEAR FAIL...... A/S-23 Multi-Function Display (MFD) ...... A/S-23 ABV ...... A/S-23 BLW...... A/S-23 DGx ...... A/S-23 FL ...... A/S-23 TA ONLY...... A/S-23 TCAS...... A/S-24 TCAS FAILURES ...... A/S-24 TCAS OFF ...... A/S-24 TCAS TEST ...... A/S-24 TERR ...... A/S-24 TERR INHIB...... A/S-24

Change 2 EFFECTIVITY Advisory/ CL-126C All Status-5 Change 2 Primary Flight Display (PFD) Annunciations ...... A/S-24 DGx ...... A/S-24 TA ONLY...... A/S-24 TCAS INOP ...... A/S-24 TCAS OFF...... A/S-25 TCAS TEST...... A/S-25 LANDING GEAR/BRAKES...... A/S-25 BRAKE FAULT...... A/S-25 EMER/PARK BRK ...... A/S-25 NWS FAULT...... A/S-25 MISCELLANEOUS...... A/S-25 CVR FAIL...... A/S-25 EMER LIGHTS ...... A/S-26 FDR FAIL (if installed) ...... A/S-26 L CHECK EDS R CHECK EDS LR CHECK EDS...... A/S-26 THRUST REVERSER...... A/S-26 L REV AUTOSTOW R REV AUTOSTOW LR REV AUTOSTOW ...... A/S-26 L REV FAULT R REV FAULT LR REV FAULT...... A/S-27 WARN...... A/S-27 L WARN PWR FAIL R WARN PWR FAIL ...... A/S-27 WARN AUDIO ...... A/S-27

Advisory/ EFFECTIVITY Status-6 All CL-126C Change 2 ANTI-ICING ICEICE DETECTED DETECTED

Ice is being detected with the WING/STAB & L & R NAC heat anti-ice systems selected ON.

LL WSHLD WSHLD HT HT FAULT FAULT RR WSHLD WSHLD HT HT FAULT FAULT LR WSHLD HT FAULT LR WSHLD HT FAULT The temperature modulating function of the windshield system is operating in a degraded mode. The system will automatically operate in a full on/off mode. The system will provide effective anti-icing.

STABSTAB TMP TMP FAULT FAULT One of the two horizontal stabilizer temperature sensors has failed. The stabilizer anti-ice system should function normally using the opposite stabilizer sensor.

WG/STABWG/STAB HT HT OK OK The wing & horizontal stabilizer anti-ice controller & sensors have been properly tested with pilot activation of the SYS TEST/RESET switch.

WINGWING TMP TMP FAULT FAULT One or more of the four wing temperature sensors have failed. The wing anti-ice system should function normally using the opposite wing sensor.

EFFECTIVITY CL-126C Advisory/ All Status-7 AUTOMATIC FLIGHT CON-APAP ELEV ELEV MISTRIM MISTRIM TROL SYSTEM The autopilot pitch servo is holding excessive torque & the pitch trim system is not operating normally. If the autopilot is to be disengaged with this CAS illuminated: 1. Flight Controls...... Hold Firmly 2. Autopilot ...... Use Control Wheel Trim Switch to Disengage 3. Retrim aircraft if necessary. 4. Autopilot ...... Engage As Desired

MACHMACH TRIM TRIM FAIL FAIL

The Mach trim function is disabled & the Mach number is less than 0.76 MI. 1. PITCH TRIM ...... PRI 2. PRI PITCH Circuit Breaker (pilot’s FLIGHT group [TRIM]) ...... Set If autopilot disengagement is desired:

3. Airspeed ...... Mach Trim Off MMO or Below 4. Autopilot ...... Disengage Engage yaw damper as required.

RUDRUD BOOST BOOST INOP INOP Rudder boost is selected OFF. Do not takeoff.

APU APU AVAILABLE

The auxiliary power unit is operating and is available for bleed air and electrical power.

ENTRYENTRY DOOR DOOR PIN PIN DOORThere is a disagreement between one or more entry door pins with the door open. This CAS will only appear while the aircraft is on the ground & will also be accompanied by an ENTRY DOOR red CAS & CWP.

Change 2 Advisory/ EFFECTIVITY Status-8 All CL-126C Change 2 ELECTRICAL BUSBUS TIE TIE CLSD CLSD BUS TIE switch is closed (either automatically or manually). The BUS TIE switch will illuminate with a white bar.

BUSBUS TIE TIE MANUAL MANUAL Pilot has manually selected the MAN position of the BUS TIE switch. The bus tie position changes & prevents automatic operation of the bus tie. MAN & a white bar (if generator buses are tied) on the switch will illuminate. Pressing the BUS TIE switch a second time restores automatic control; MAN on the switch & BUS TIE MANUAL white CAS will extinguish.

LL ESS ESS BUS BUS FAULT FAULT RR ESS ESS BUS BUS FAULT FAULT LR ESS BUS FAULT LR ESS BUS FAULT The respective essential bus contactor has failed open in flight.

EXTERNALEXTERNAL POWER POWER The external power source is connected to the aircraft (regardless of whether it is powering the aircraft). The external power source is powered if the EXT PWR switch on the ELEC panel has a green AVAIL illuminated.

ENGINE LL APR APR FAULT FAULT RR APR APR FAULT FAULT LR APR FAULT LR APR FAULT The respective DEEC has detected a fault within the APR function of the computer. Refer to APR OFF performance data, Section V in the AFM.

LL ENG ENG FIRE FIRE FAIL FAIL RR ENG ENG FIRE FIRE FAIL FAIL LR ENG FIRE FAIL LR ENG FIRE FAIL The engine fire detection system has detected a fault during flight that may not allow the detection system to indicate a fire. EFFECTIVITY Advisory/ CL-126C All Status-9 Change 1 LL ENG ENG SHUTDOWN SHUTDOWN RR ENG ENG SHUTDOWN SHUTDOWN LR ENG SHUTDOWN LR ENG SHUTDOWN This collector message indicates the engine is shutdown with the thrust lever at CUTOFF. The respective OIL PRESS LOW (red), FUEL PRESS LOW (red), GEN FAIL (amber), & HYD PUMP LO (white) CAS are inhibited. When the thrust lever is moved out of CUTOFF, the inhibited CAS will flash & may be reset with the Master WARN/CAUT switches. LR ENG SHUTDOWN LR GEN FAIL (red) CAS will be inhibited on the ground & will illuminate in flight.

LL ENG ENG VIB VIB MON MON RR ENG ENG VIB VIB MON MON LR ENG VIB MON LR ENG VIB MON A higher than normal level of vibration has been sensed in the respective engine. 1. Engine Instruments...... Monitor for Abnormal Indications If ENG VIB MON remains illuminated for more than 30 seconds and if conditions permit: 2. Respective Thrust Lever ...... Adjust 3. Refer problem to maintenance personnel for correction after landing.

LL ENGCMPTR ENGCMPTR FAULT FAULT RR ENGCMPTR ENGCMPTR FAULT FAULT LR ENGCMPTR FAULT LR ENGCMPTR FAULT The respective DEEC has detected a minor malfunction on the ground. The engine computer retains engine control & operation is not affected. This procedure may be used prior to takeoff to clear the fault. 1. Respective Thrust Lever ...... IDLE 2. Respective ENG CMPTR...... OFF, then ON

Advisory/ EFFECTIVITY Status-10 All CL-126C Change 1 LL ENGINE ENGINE CHIP CHIP RR ENGINE ENGINE CHIP CHIP LR ENGINE CHIP LR ENGINE CHIP Metal particles have been detected in the oil during flight.

LL OIL OIL FILTER FILTER RR OIL OIL FILTER FILTER LR OIL FILTER LR OIL FILTER The engine oil filter has an impending bypass during flight. 1. Monitor oil pressure & temperature.

EFFECTIVITY CL-126C Advisory/ All Status-11 ENGINE INDICATIONS (EIS)

The following illuminations appear in the EI displays outboard of the N1 digital display of the EICAS. EIs (Green) The associated thrust lever is in the Automatic Performance APR Reserve (APR) detent.

The associated thrust lever is in the Maximum Cruise (MCR) MCR detent.

The associated thrust lever is in the Maximum Continuous MCT Thrust (MCT) detent.

T/O The associated thrust lever is in the Takeoff (TO) detent. EIs (Green/ White) The following illuminations appear in the EI displays of the EICAS.

APR ON The Automatic Performance Reserve (APR) has activated.

APR The APR is armed in both DEECs. DEP The thrust reverser is deployed with aircraft on the ground.

IGN The ignition is ON (either manually or automatically). The ignition is ON, either manually or automatically, & one IGN ignitor plug has failed. The other plug is functioning normally. The DEEC is in the MANual mode or OFF mode as selected MAN by the pilot.

The NAC anti-ice switch is ON & the system is functioning NAC normally.

The thrust reverser hydraulic control unit is receiving hydrau- REV lic pressure & the thrust reversers are armed with aircraft on the ground.

A vertical START illumination indicates that the engine START starter is engaged.

SYNC The ENG SYNC is ON (adjacent to either N1 or N2).

EFFECTIVITY Advisory/ CL-126C Status-12 All NVIRONMEN AL/PRESSUR-LL CAB CAB PRESS PRESS FAIL FAIL IZATIONRR CAB CAB PRESS PRESS FAIL FAIL The left or right pressurization control has failed & will automatically switch operation to the opposite control. 1. Respective L or R PRESS Circuit Breaker (respective ENVIRONMENTAL group) ...... Set, or Pull & Reset

CABCAB PRESS PRESS MAN MAN The crew has selected manual rate control of the pressurization system.

LL ECS ECS FAULT FAULT RR ECS ECS FAULT FAULT A fault has been detected in the respective channel of the ECS controller during flight. 1. Respective L or R BLEED Circuit Breaker (respective ENVIRONMENTAL group) ...... Set, or Pull & Reset 2. Monitor cabin altitude.

EMEREMER DEPRESS DEPRESS Emergency depressurization has been selected by the crew. Emergency depressurization commands both outflow valves full open, but will attempt to limit the cabin altitude to approximately 13,700 ft.

PACKPACK HIGH HIGH FLOW FLOW HI FLOW has been selected ON.

PAXPAX OXY OXY DEPLOY DEPLOY An electrical command (automatic or manual) has been provided to the passenger oxygen deploy valve to deploy the masks.

AUTOSPLR ARMED Autospoilers have been armed. Change 1 EFFECTIVITY Advisory/ CL-126C All Status-13 Change 1 ELEVATORELEVATOR DISC DISC The elevator disconnect has split the elevator controls during flight. Do not reconnect. The pilot’s control column moves the left elevator. The copilot’s control column moves the right elevator. Autopilot will disengage & not re- engage.

PITPIT TRIM TRIM BIAS BIAS The pitch trim bias system is moved from the normal position. PIT TRIM BIAS should only be used for jammed stabilizer conditions in flight. If the pitch trim bias system has moved from the normal position without pilot action, a normal landing may be accomplished.

PITPIT TRIM TRIM MSCMP MSCMP The stabilizer pitch trim indications between IC-600s (Integrated Comput- ers) do not agree while on the ground.

PITCHPITCH TRIM TRIM OFF OFF PITCH TRIM selector switch is OFF. Autopilot, configuration trim & Mach trim will be inoperative.

PRIPRI TRIM TRIM FAULT FAULT An IC-600 (Integrated Computer) trim fault has been detected. Primary trim may be available, however, operation may be at a lower trim rate. The configuration & Mach trim will be inoperative. 1. ●If primary trim is available: a. PRI PITCH Circuit Breaker (pilot’s FLIGHT group [TRIM]) ...... Pull & Reset b. Control Wheel Master (MSW) ...... Depress & Release to Attempt to Clear Fault 1.●If PRI pitch trim is not available, refer to PRI TRIM FAIL, Tab 17 . 1.●If neither PRI nor SEC pitch trim is available, refer to Jammed Stabilizer — Both PRI and SEC Trim Inoperative, Tab 19 .

Change 1 Advisory/ EFFECTIVITY Status-14 All CL-126C Change 1 ROLLROLL DISC DISC Roll disconnect has occurred during flight. The pilot’s control wheel controls the spoilerons & the copilot’s control wheel controls the ailerons. Autopilot will disengage & not re-engage.

SECSEC PITCH PITCH TRIM TRIM Secondary pitch trim has been selected. Autopilot is available.

FLIGHT CON TROL SECSEC TRIM TRIM FAULT FAULT A power-up stabilizer actuator fault has been detected. Pitch trim may be- come inoperative without an associated FAULT or FAIL message. If conditions permit: 1. SEC PITCH Circuit Breaker (copilot’s FLIGHT group [TRIM])...... Pull & Reset 2. Control Wheel Master (MSW)...... Depress & Release to Attempt to Clear Fault 3. SEC TRIM ...... As Desired Trim will operate normally even if CAS remains illuminated.

SPOILERSSPOILERS EXT EXT Spoilers are not fully retracted. Spoileron extension will not activate this CAS.

TAKEOFFTAKEOFF TRIM TRIM Pitch, aileron, or rudder trim is not set for takeoff while the aircraft is on the ground & thrust levers are less than MCR.

Change 2 EFFECTIVITY Advisory/ CL-126C All Status-15 Change 2 WHEELWHEEL MSTR MSTR The Control Wheel Master (MSW) has been depressed or power to one of the MSWs has been lost. This CAS will be accompanied by the PRI TRIM FAULT white CAS. The MSW will interrupt the pitch, aileron, rudder trims, configuration trim, Mach trim, PIT TRIM BIAS, & rudder boost systems. The autopilot, yaw damper & nose wheel steering (on the ground) will disconnect. On aircraft 45-002 thru 45-294 not modified by SB 45-27-20, the spoiler control valve will close which causes the spoiler & spoilerons to retract to the float position. The MACH TRIM FAIL white & amber CAS messages will not illuminate, & the MMO overspeed red limit bar on the PFD will not reduce to the Mach trim off MMO. 1. Respective L or R WHL MSTR Circuit Breaker (respective FLIGHT group) ...... Set If either WHL MSTR circuit breaker remains pulled: 2. The following systems are inoperative: autopilot, yaw damper, rudder boost, Mach trim & configuration trim. Refer to the appropriate system failed procedures. The primary manual trim will be in the slow mode. The respective MSW will be inoperative.

FUEL LL FUEL FUEL BAY BAY LOW LOW RR FUEL FUEL BAY BAY LOW LOW LR FUEL BAY LOW LR FUEL BAY LOW A float switch has detected low fuel in the collector bay. This may be an indication of a scavenge pump (motive flow) system failure or sideslip. The CAS will be displayed with the respective engine shut down. 1. Minimize sideslips & uncoordinated maneuvering.

FUELFUEL XFLO XFLO OPEN OPEN The wing fuel crossflow valve is open.

Advisory/ EFFECTIVITY Status-16 All CL-126C Change 1 LL FUEL FUEL FILTER FILTER RR FUEL FUEL FILTER FILTER LR FUEL FILTER LR FUEL FILTER Either the respective engine or aircraft fuel filter has an impending bypass during flight. 1. Respective L or R STBY ...... ON

LL FUEL FUEL HEATER HEATER RR FUEL FUEL HEATER HEATER LR FUEL HEATER LR FUEL HEATER The respective fuel heater/oil cooler has failed to the hot condition.

LL FUEL FUEL QTY QTY FAULT FAULT RR FUEL FUEL QTY QTY FAULT FAULT Indicates the left or right channel has detected a fault or a loss of compensation.

FUELFUEL QTY QTY FAULT FAULT The FUEL QTY FAULT indicates that the attitude input from the AHRS is inoperative & the quantity may not be as accurate as normal, or that a fuselage probe is inoperative or invalid. This CAS will also illuminate during AHRS alignment. A probe failure may result in a FUEL IMBALANCE amber CAS due to cal- culation in the fuel quantity indicating conditioner.

LL FWSOV FWSOV CLSD CLSD RR FWSOV FWSOV CLSD CLSD LR FWSOV CLSD LR FWSOV CLSD The respective fuel firewall shutoff valve is closed.

EFFECTIVITY Advisory/ CL-126C All Status-17 Change 1 LL STBY STBY PUMP PUMP ON ON RR STBY STBY PUMP PUMP ON ON LR STBY PUMP ON LR STBY PUMP ON Electrical power has been provided to the respective standby pump. The pumps may be turned on manually, & will automatically turn on during starter-assisted engine starts. The right standby pump will automatically turn on during APU starts (if installed) and will remain on during APU operation.

HYDRAULICS HYDHYD XFLOW XFLOW ON ON Hydraulic crossflow valve is open.

LL HYD HYD PUMP PUMP LOW LOW RR HYD HYD PUMP PUMP LOW LOW LR HYD PUMP LOW LR HYD PUMP LOW The left or right engine hydraulic pressure is less than 1900 psi. The hydraulic pump symbol on the HYD page will be amber with this CAS message displayed. 1. EICAS ...... Select HYD or SUMRY Page 2. Monitor MAIN hydraulic pressure.

MAINMAIN HYDQTY HYDQTY LO LO Main hydraulic quantity is low.

INSTRUMENT/ AVIONICSAHRSAHRS 1 1 BASIC BASIC AHRSAHRS 2 2 BASIC BASIC AHRS 1-2 BASIC AHRS 1-2 BASIC The Attitude Heading Reference System, AHRS 1 or 2, has reverted to basic mode due to a loss of true airspeed from both air data computers. The attitude displays, autopilot, FMS, & radar stabilization will operate normally. Minimize sustained shallow bank turns (less than 6° bank) to minimize small AHRS errors.

Advisory/ EFFECTIVITY Status-18 All CL-126C Change 1 CKLSTCKLST MISMATCH MISMATCH Indicates that the checklists loaded in IC 1 & IC 2 do not match.

DAUDAU A A REV REV DAUDAU B B REV REV Pilot has selected DAU Reversion to Channel A or B. In reversion, both ICs use the same channel (A or B) of both DAUs. Some loss of redundancy & comparison monitoring occurs during reversion, & DAU REV should not be selected unless a DAU fault or failure is detected.

DUDU 1 1 FAN FAN FAIL FAIL DUDU 2 2 FAN FAN FAIL FAIL DU 1-2 FAN FAIL DU 1-2 FAN FAIL Indicates that the respective Display Unit (DU) cooling fan has failed. If conditions permit: DU 1 FAN FAIL 1. DU 2 Reversion...... PFD EICAS will automatically revert to DU 3. 2. DU 1 Circuit Breaker (pilot’s INSTRUMENTS/INDICATIONS group [DISPLAY]) ...... Pull DU 2 FAN FAIL 1. DU 2 Reversion...... OFF EICAS will automatically revert to DU 3. 2. DU 2 Circuit Breaker (pilot’s INSTRUMENTS/INDICATIONS group [DISPLAY]) ...... Pull DU 1-2 FAN FAIL 1. DU 2 Reversion...... OFF EICAS will automatically revert to DU 3. 2. DU 1 & DU 2 Circuit Breakers (pilot’s INSTRUMENTS/INDICATIONS group [DISPLAY]) ...... Pull Rely on the copilot’s flight displays & standby instruments.

EFFECTIVITY Advisory/ CL-126C All Status-19 Change 1 DUDU 3 3 FAN FAN FAIL FAIL DUDU 4 4 FAN FAN FAIL FAIL DU 3-4 FAN FAIL DU 3-4 FAN FAIL Indicates that the respective Display Unit (DU) cooling fan has failed. DU 3 FAN FAIL 1. DU 3 Reversion...... Push if DU 3 is Presently in EICAS Format 2. DU 3 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group [DISPLAY]) ...... Pull

DU 4 FAN FAIL 1. DU 3 Reversion...... PFD EICAS will automatically revert to DU 2. 2. DU 4 Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group [DISPLAY]) ...... Pull

DU 3-4 FAN FAIL 1. DU 3 Reversion...... Push As Required to get EICAS on DU 2 2. DU 3 & DU 4 Circuit Breakers (copilot’s INSTRUMENTS/INDICATIONS group [DISPLAY]) ...... Pull Rely on the pilot’s flight displays & standby instruments.

GND PROX FAIL

One or more of the GPWS modes 1 - 5 are inoperative. 1. GPWS Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ...... Pull & Reset

GPWS FLAP OVRD

FLAP switch has been selected OFF. Flap input is forced to 40° flaps into the EGPWS computer.

Advisory/ EFFECTIVITY Status-20 All CL-126C Change 1 GPWS G/S INHB

G/S switch has been selected OFF.

GPWSGPWS FAILFAIL OR GPWS SYS FAIL All modes of the GPWS system have failed. 1. GPWS Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group)...... Pull & Reset

ICIC 1 1 CNFG CNFG FAIL FAIL ICIC 2 2CNFG CNFG FAIL FAIL A communication failure has occurred between the IC-600 (Integrated Computer) and IM-600 (Integrated Computer Configuration Module). The IC-600 will continue to function properly, and will power up with the configuration stored at the last power-down.

ICIC 1 1 FAN FAN FAIL FAIL ICIC 2 2 FAN FAN FAIL FAIL IC 1-2 FAN FAIL IC 1-2 FAN FAIL The respective IC (Integrated Computer) 1 or 2 cooling fan has failed. Mon- itor for deteriorating IC functionality & select IC/SG REVERSION as necessary.

EFFECTIVITY Advisory/ CL-126C All Status-21 Change 1 ICIC 1 1 WOW WOW INOP INOP ICIC 2 2 WOW WOW INOP INOP IC 1-2 WOW INOP IC 1-2 WOW INOP The respective IC (Integrated Computer) has tripped the Weight-On-Wheel monitor by a detected mismatch between the Weight-On-Wheel inputs & airspeed logic. Weight-On-Wheel logic is used by the IC for internal logic tests & external tests. The monitor check is performed once after takeoff, & once after landing. On the ground: 1. Respective IC/SG 1 or 2 Circuit Breaker (pilot’s or copilot’s INSTRUMENTS/INDICATIONS group) ...... Pull & Reset In flight: 1. Continue flight.

INSTRINSTR PNL PNL TEMP TEMP An instrument panel thermal switch has tripped. 1. INSTR FAN Circuit Breaker (pilot’s ENVIRONMENTAL group) ...... Set, or Pull & Reset

LBS/KGSLBS/KGS CONFIG CONFIG The pounds/kilograms configuration of the IC-600 (Integrated Computer) disagrees with the configuration of DAU 1 & 2 during flight.

NOSENOSE BAY BAY TEMP TEMP A nose bay thermal switch has tripped.

TERR FAIL

The Terrain Mode is inoperative. 1. FMS 1 and FMS 2 (if installed) ...... Check ON 2. GPWS Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ...... Pull & Reset

Advisory/ EFFECTIVITY Status-22 All CL-126C Change 1 TERRTERR INHB INHB OR TERR INHIB

TERR switch has been selected OFF. Terrain display, annunciations of alerts and warnings, and TCFs are all disabled.

WINDSHEARWINDSHEAR FAIL FAIL The windshear monitor detects loss of power or loss of inputs required for windshear monitoring functions. 1. GPWS Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group)...... Pull & Reset

Multi-Function Display (MFD) ABV Located in the upper left corner of the TCAS zoom window, this annunciation indicates traffic will be displayed at relative altitudes of -2,700 feet to +7,000 feet.

BLW Located in the upper left corner of the TCAS zoom window, this annunciation indicates traffic will be displayed at relative altitudes of -7,000 feet to +2,700 feet.

DGx Located to the right of the MFD heading readout and indicates the respective HEADING switch is in the unslaved (FREE) mode.

FL Located in the upper left corner of the TCAS zoom window, this annunciation indicates that Flight Level mode has been selected by the pilot. All traffic altitudes will be displayed in 3-digit flight level format (e.g., 19,000 feet will be displayed as 190).

TA ONLY Located in the upper left corner of the TCAS zoom window, this annunciation indicates no resolution advisory information or guidance will be provided. Change 2 EFFECTIVITY Advisory/ CL-126C All Status-23 Change 2 TCAS Located in the upper left corner of the TCAS zoom window, this annunciation indicates normal TCAS system operation. It is the default TCAS message.

TCAS FAILURES Displayed in the upper right corner of the TCAS zoom window at the end of each self test. This annunciation is just a header. If any part of the self test fails, a description of the failure will be displayed below this header.

TCAS OFF Located in the upper left corner of the TCAS zoom window, this annunciation indicates that the system is functional but in standby mode, or non- functional due to incorrect or failed ADC operation.

TCAS TEST Located in the upper left corner of the TCAS zoom window, this annunciation indicates that the TCAS system self test is in progress.

TERR Located in the upper left corner of the MFD and indicates Terrain is selected for display.

TERR INHIB Located in the upper left corner of the MFD and indicates the TERR switch has been selected OFF.

Primary Flight Display (PFD) Annunciations DGx Located to the right of the PFD heading readout and indicates the respective HEADING switch is in the unslaved (FREE) mode.

TA ONLY Located below the VSI display, this annunciation indicates no resolution advisory information or guidance will be provided.

TCAS INOP Located below the VSI display, this annunciation indicates that TCAS is not enabled, but the system has been strapped to accept it. Advisory/ EFFECTIVITY Status-24 All CL-126C Change 1 TCAS OFF Located below the VSI display, this annunciation indicates that the system is functional but in standby mode, or non-functional due to incorrect or failed ADC operation.

TCAS TEST Located below the VSI display, this annunciation indicates that the TCAS system self test is in progress.

BRAKEBRAKE FAULT FAULT A brake system fault has been sensed that results in minor system degra- dation. Increase the takeoff & landing distances as follows: - Dry Runway Aircraft not modified by SB 45-11-4 — Add 300 feet (91 meters). Aircraft modified by SB 45-11-4 — Add 500 feet (153 meters). - Wet Runway — Add 600 feet (183 meters).

EMER/PARKEMER/PARK BRK BRK The emergency brake is being used or the parking brake valve is not fully released, & thrust levers are less than MCR.

NWSNWS FAULT FAULT

NWS FAULT may indicate a loss of pedal force steering. 1. NOSE STEER ...... Off, then ON

CVRCVR FAIL FAIL

The cockpit voice recorder has failed. 1. CVR Circuit Breaker (pilot’s INSTRUMENTS/INDICATIONS group)...... Set If circuit breaker remains pulled: 2. The CWP tone/voice volume will be at a fixed (high) level. EFFECTIVITY Advisory/ CL-126C All Status-25 Change 1 EMEREMER LIGHTS LIGHTS The emergency lights are on.

FDRFDR FAIL FAIL (IF INSTALLED) The flight data recorder has failed. 1. FDR Circuit Breaker (copilot’s INSTRUMENTS/INDICATIONS group) ...... Set If DAU 1A amber CAS is also illuminated, the FDR may still operate.

LL CHECK CHECK EDS EDS RR CHECK CHECK EDS EDS LR CHECK EDS LR CHECK EDS One of the following conditions of the applicable Engine Diagnostic System (EDS) (part of the Engine Condition Trend Monitor (ECTM) system) has occurred. - The EDS has lost power. - The EDS built-in test equipment (BITE) has detected a system failure. - The EDS memory is 85% full. - The system has detected an engine condition which was out of acceptable parameters.

LL REV REV AUTOSTOW AUTOSTOW RR REV REV AUTOSTOW AUTOSTOW LR REV AUTOSTOW LR REV AUTOSTOW The respective thrust reverser autostow function has activated & applied hydraulic pressure to the stow side of the actuator.

Advisory/ EFFECTIVITY Status-26 All CL-126C Change 1 LL REV REV FAULT FAULT RR REV REV FAULT FAULT LR REV FAULT LR REV FAULT A fault has been detected in the respective thrust reverser system.

On the ground: 1. Respective DEPLOY, ANN and STOW Circuit Breakers (ENGINE group [L or R REVERSER])...... Pull & Reset 2.●If respective REV FAULT remains illuminated: a. Do not take off. b. Refer the problem to maintenance personnel for correction. 2.●If respective REV FAULT extinguishes, this checklist is complete.

In flight: 1. Land as soon as practical.

WARN LL WARN WARN PWR PWR FAIL FAIL RR WARN WARN PWR PWR FAIL FAIL The respective Crew Warning Panel (CWP) power supply has failed or lost power. The CWP is still operational from the opposite power supply; however, the CWP annunciators may look dim. 1. Respective L or R WARN PANEL Circuit Breaker (respective INSTRUMENTS/INDICATIONS group) ...... Set

WARNWARN AUDIO AUDIO The Crew Warning Panel (CWP) has detected a fault in either one of the output audio channels, or in the Automatic Gain Control (AGC) input. The CWP is still operational, & the tone/voice volume will be at a fixed (high) level.

EFFECTIVITY Advisory/ CL-126C All Status-27 Change 1 SUPPLEMENTAL DATA

Conversions Temperature Conversion ...... S-2 Linear Conversion...... S-3 Volume Conversion...... S-4 Weight Conversion ...... S-5 Environmental Oxygen Duration...... S-6 Oxygen Quantity Mission planning ...... S-7 Electrical DC Power Distribution (Dual Generator Failure)...... S-9 Schematics Electrical System (Dual Generator Failure) ...... S-10 SUPPLEMENTAL DATA SUPPLEMENTAL Electrical System (Normal)...... S-11 Engine Fire Extinguishing System...... S-12 Bleed Air System ...... S-13 Temperature Control System...... S-14 Pressurization System...... S-15 Fuel System...... S-16 Hydraulic System ...... S-17 Hydraulic System (HYD XFLOW ON)...... S-18 Landing Gear Extended...... S-19 Landing Gear Retracted ...... S-20 Brake System ...... S-21 APU Operating Procedures ...... S-22 Master EICAS Index...... S-24

CL-126C EFFECTIVITY Change 2 Change 2 All S-1 Temperature Conversion • To convert from Celsius to Fahrenheit, find, in bold face columns, the number representing the Celsius temperature to be converted. The equivalent Fahren- heit temperature is read in the adjacent column headed °F. • To convert from Fahrenheit to Celsius, find, in bold face columns, the number representing the Fahrenheit temperature to be converted. The equivalent Cel- sius temperature is read in the adjacent column headed °C.

°F °C °F °C °F °C °F °C °F °C -148.0 -100 -73.3 -58.0 -50 -45.6 32.0 0 -17.8 122.0 50 10.0 212.0 100 37.8 -146.2 -99 -72.8 -56.2 -49 -45.0 33.8 1 -17.2 123.8 51 10.6 213.8 101 38.3 -144.4 -98 -72.2 -54.4 -48 -44.4 35.6 2 -16.7 125.6 52 11.1 215.6 102 38.9 -142.6 -97 -71.7 -52.6 -47 -43.9 37.4 3 -16.1 127.4 53 11.7 217.4 103 39.4 -140.8 -96 -71.1 -50.8 -46 -43.3 39.2 4 -15.6 129.2 54 12.2 219.2 104 40.0 -139.0 -95 -70.6 -49.0 -45 -42.8 41.0 5 -15.0 131.0 55 12.8 221.0 105 40.6 -137.2 -94 -70.0 -47.2 -44 -42.2 42.8 6 -14.4 132.8 56 13.3 222.8 106 41.1 -135.4 -93 -69.4 -45.4 -43 -41.7 44.6 7 -13.9 134.6 57 13.9 224.6 107 41.7 -133.6 -92 -68.9 -43.6 -42 -41.1 46.4 8 -13.3 136.4 58 14.4 226.4 108 42.2 -131.8 -91 -68.3 -41.8 -41 -40.6 48.2 9 -12.8 138.2 59 15.0 228.2 109 42.8 -130.0 -90 -67.8 -40.0 -40 -40.0 50.0 10 -12.2 140.0 60 15.6 230.0 110 43.3 -128.2 -89 -67.2 -38.2 -39 -39.4 51.8 11 -11.7 141.8 61 16.1 231.8 111 43.9 -126.4 -88 -66.7 -36.4 -38 -38.9 53.6 12 -11.1 143.6 62 16.7 233.6 112 44.4 -124.6 -87 -66.1 -34.6 -37 -38.3 55.4 13 -10.6 145.4 63 17.2 235.4 113 45.0 -122.8 -86 -65.6 -32.8 -36 -37.8 57.2 14 -10.0 147.2 64 17.8 237.2 114 45.6 -121.0 -85 -65.0 -31.0 -35 -37.2 59.0 15 -9.4 149.0 65 18.3 239.0 115 46.1

SUPPLEMENTAL DATA SUPPLEMENTAL -119.2 -84 -64.4 -29.2 -34 -36.7 60.8 16 -8.9 150.8 66 18.9 240.8 116 46.7 -117.4 -83 -63.9 -27.4 -33 -36.1 62.6 17 -8.3 152.6 67 19.4 242.6 117 47.2 -115.6 -82 -63.3 -25.6 -32 -35.6 64.4 18 -7.8 154.4 68 20.0 244.4 118 47.8 -113.8 -81 -62.8 -23.8 -31 -35.0 66.2 19 -7.2 156.2 69 20.6 246.2 119 48.3 -112.0 -80 -62.2 -22.0 -30 -34.4 68.0 20 -6.7 158.0 70 21.1 248.0 120 48.9 -110.2 -79 -61.7 -20.2 -29 -33.9 69.8 21 -6.1 159.8 71 21.7 249.8 121 49.4 -108.4 -78 -61.1 -18.4 -28 -33.3 71.6 22 -5.6 161.6 72 22.2 251.6 122 50.0 -106.6 -77 -60.6 -16.6 -27 -32.8 73.4 23 -5.0 163.4 73 22.8 253.4 123 50.6 -104.8 -76 -60.0 -14.8 -26 -32.2 75.2 24 -4.4 165.2 74 23.3 255.2 124 51.1 -103.0 -75 -59.4 -13.0 -25 -31.7 77.0 25 -3.9 167.0 75 23.9 257.0 125 51.7 -101.2 -74 -58.9 -11.2 -24 -31.1 78.8 26 -3.3 168.8 76 24.4 258.8 126 52.2 -99.4 -73 -58.3 -9.4 -23 -30.6 80.6 27 -2.8 170.6 77 25.0 260.6 127 52.8 -97.6 -72 -57.8 -7.6 -22 -30.0 82.4 28 -2.2 172.4 78 25.6 262.4 128 53.3 -95.8 -71 -57.2 -5.8 -21 -29.4 84.2 29 -1.7 174.2 79 26.1 264.2 129 53.9 -94.0 -70 -56.7 -4.0 -20 -28.9 86.0 30 -1.1 176.0 80 26.7 266.0 130 54.4 -92.2 -69 -56.1 -2.2 -19 -28.3 87.8 31 -0.6 177.8 81 27.2 267.8 131 55.0 -90.4 -68 -55.6 -0.4 -18 -27.8 89.6 32 0.0 179.6 82 27.8 269.6 132 55.6 -88.6 -67 -55.0 1.4 -17 -27.2 91.4 33 0.6 181.4 83 28.3 271.4 133 56.1 -86.8 -66 -54.4 3.2 -16 -26.7 93.2 34 1.1 183.2 84 28.9 273.2 134 56.7 -85.0 -65 -53.9 5.0 -15 -26.1 95.0 35 1.7 185.0 85 29.4 275.0 135 57.2 -83.2 -64 -53.3 6.8 -14 -25.6 96.8 36 2.2 186.8 86 30.0 276.8 136 57.8 -81.4 -63 -52.8 8.6 -13 -25.0 98.6 37 2.8 188.6 87 30.6 278.6 137 58.3 -79.6 -62 -52.2 10.4 -12 -24.4 100.4 38 3.3 190.4 88 31.1 280.4 138 58.9 -77.8 -61 -51.7 12.2 -11 -23.9 102.2 39 3.9 192.2 89 31.7 282.2 139 59.4 -76.0 -60 -51.1 14.0 -10 -23.3 104.0 40 4.4 194.0 90 32.2 284.0 140 60.0 -74.2 -59 -50.6 15.8 -9 -22.8 105.8 41 5.0 195.8 91 32.8 285.8 141 60.6 -72.4 -58 -50.0 17.6 -8 -22.2 107.6 42 5.6 197.6 92 33.3 287.6 142 61.1 -70.6 -57 -49.4 19.4 -7 -21.7 109.4 43 6.1 199.4 93 33.9 289.4 143 61.7 -68.8 -56 -48.9 21.2 -6 -21.1 111.2 44 6.7 201.2 94 34.4 291.2 144 62.2 -67.0 -55 -48.3 23.0 -5 -20.6 113.0 45 7.2 203.0 95 35.0 293.0 145 62.8 -65.2 -54 -47.8 24.8 -4 -20.0 114.8 46 7.8 204.8 96 35.6 294.8 146 63.3 -63.4 -53 -47.2 26.6 -3 -19.4 116.6 47 8.3 206.6 97 36.1 296.6 147 63.9 -61.6 -52 -46.7 28.4 -2 -18.9 118.4 48 8.9 208.4 98 36.7 298.4 148 64.4 -59.8 -51 -46.1 30.2 -1 -18.3 120.2 49 9.4 210.2 99 37.2 300.2 149 65.0 EFFECTIVITY CL-126C S-2 All Change 1 Linear Conversion • To convert from meters to feet, find, in the bold face columns, the number of meters to be converted. The equivalent number of feet is read in the adjacent column headed FEET. • To convert from feet to meters, find, in the bold face columns, the number of feet to be converted. The equivalent number of meters is read in the adjacent column headed METERS.

METERS FEET METERS FEET METERS FEET 304.8 1000 3280.8 1341.1 4400 14435.5 2377.5 7800 25590.2 335.3 1100 3608.9 1371.6 4500 14763.6 2407.9 7900 25918.3 365.8 1200 3937.0 1402.1 4600 15091.7 2438.4 8000 26246.4 396.2 1300 4265.0 1432.6 4700 15419.8 2468.9 8100 26574.5 426.7 1400 4593.1 1463.1 4800 15747.8 2499.4 8200 26902.6 457.2 1500 4921.2 1493.5 4900 16075.9 2529.9 8300 27230.6 487.7 1600 5249.3 1524.0 5000 16404.0 2560.4 8400 27558.7 518.2 1700 5577.4 1554.5 5100 16732.1 2590.8 8500 27886.8 548.6 1800 5905.4 1585.0 5200 17060.2 2621.3 8600 28214.9 579.1 1900 6233.5 1615.5 5300 17388.2 2651.8 8700 28543.0 609.6 2000 6561.6 1645.9 5400 17716.3 2682.3 8800 28871.0 640.1 2100 6889.7 1676.4 5500 18044.4 2712.8 8900 29199.1 670.6 2200 7217.8 1706.9 5600 18372.5 2743.2 9000 29527.2 701.0 2300 7545.8 1737.4 5700 18700.6 2773.7 9100 29855.3 731.5 2400 7873.9 1767.9 5800 19028.6 2804.2 9200 30183.4 762.0 2500 8202.0 1798.3 5900 19356.7 2834.7 9300 30511.4 792.5 2600 8530.1 1828.8 6000 19684.8 2865.2 9400 30839.5 823.0 2700 8858.2 1859.3 6100 20012.9 2895.6 9500 31167.6 853.5 2800 9186.2 1889.8 6200 20341.0 2926.1 9600 31495.7 883.9 2900 9514.3 1920.3 6300 20669.0 2956.6 9700 31823.8 914.4 3000 9842.4 1950.7 6400 20997.1 2987.1 9800 32151.8 944.9 3100 10170.5 1981.2 6500 21325.2 3017.6 9900 32479.9 975.4 3200 10498.6 2011.7 6600 21653.3 3048.0 10000 32808.0 1005.9 3300 10826.6 2042.2 6700 21981.4 3352.8 11000 36088.8 1036.3 3400 11154.7 2072.7 6800 22309.4 3657.6 12000 39369.6 1066.8 3500 11482.8 2103.1 6900 22637.5 3962.4 13000 42650.4 1097.3 3600 11810.9 2133.6 7000 22965.6 4267.3 14000 45931.2 1127.8 3700 12139.0 2164.1 7100 23293.7 4572.1 15000 49212.0 1158.3 3800 12467.0 2194.6 7200 23621.8 4876.9 16000 52492.8 1188.7 3900 12795.1 2225.1 7300 23949.8 5181.7 17000 55773.6 1219.2 4000 13123.2 2255.5 7400 24277.9 5486.5 18000 59054.4 1249.7 4100 13451.3 2286.0 7500 24606.0 5791.3 19000 62335.2 1280.2 4200 13779.4 2316.5 7600 24934.1 6096.1 20000 65616.0 1310.7 4300 14107.4 2347.0 7700 25262.2 6400.9 21000 68896.8

CL-126C EFFECTIVITY Change 1 All S-3 Volume Conversion • To convert from liters to gallons, find, in the bold face columns, the number of liters to be converted. The equivalent number of gallons is read in the adjacent column headed GALLONS. • To convert from gallons to liters, find, in the bold face columns, the number of gallons to be converted. The equivalent number of liters is read in the adjacent column headed LITERS.

LITERS GALLONS LITERS GALLONS LITERS GALLONS 18.9 5 1.3 1476.2 390 103.0 2952.3 780 206.1 37.9 10 2.6 1514.0 400 105.7 2990.2 790 208.7 75.7 20 5.3 1551.9 410 108.3 3028.0 800 211.4 113.6 30 7.9 1589.7 420 111.0 3065.9 810 214.0 151.4 40 10.6 1627.6 430 113.6 3103.7 820 216.6 189.3 50 13.2 1665.4 440 116.2 3141.6 830 219.3 227.1 60 15.9 1703.3 450 118.9 3179.4 840 221.9 265.0 70 18.5 1741.1 460 121.5 3217.3 850 224.6 302.8 80 21.1 1779.0 470 124.2 3255.1 860 227.2 340.7 90 23.8 1816.8 480 126.8 3293.0 870 229.9 378.5 100 26.4 1854.7 490 129.5 3330.8 880 232.5 416.4 110 29.1 1892.5 500 132.1 3368.7 890 235.1 454.2 120 31.7 1930.4 510 134.7 3406.5 900 237.8 492.1 130 34.3 1968.2 520 137.4 3444.4 910 240.4 529.9 140 37.0 2006.1 530 140.0 3482.2 920 243.1 567.8 150 39.6 2043.9 540 142.7 3520.1 930 245.7 605.6 160 42.3 2081.8 550 145.3 3557.9 940 248.3 643.5 170 44.9 2119.6 560 148.0 3595.8 950 251.0 681.3 180 47.6 2157.5 570 150.6 3633.6 960 253.6 719.2 190 50.2 2195.3 580 153.2 3671.5 970 256.3 757.0 200 52.8 2233.2 590 155.9 3709.3 980 258.9 794.9 210 55.5 2271.0 600 158.5 3747.2 990 261.6 832.7 220 58.1 2308.9 610 161.2 3785.0 1000 264.2 870.6 230 60.8 2346.7 620 163.8 4163.5 1100 290.6 908.4 240 63.4 2384.6 630 166.4 4542.0 1200 317.0 946.3 250 66.1 2422.4 640 169.1 4920.5 1300 343.5 984.1 260 68.7 2460.3 650 171.7 5299.0 1400 369.9 1022.0 270 71.3 2498.1 660 174.4 5677.5 1500 396.3 1059.8 280 74.0 2536.0 670 177.0 6056.0 1600 422.7 1097.7 290 76.6 2573.8 680 179.7 6434.5 1700 449.1 1135.5 300 79.3 2611.7 690 182.3 6813.0 1800 475.6 1173.4 310 81.9 2649.5 700 184.9 7191.5 1900 502.0 1211.2 320 84.5 2687.4 710 187.6 7570.0 2000 528.4 1249.1 330 87.2 2725.2 720 190.2 7948.5 2100 554.8 1286.9 340 89.8 2763.1 730 192.9 8327.0 2200 581.2 1324.8 350 92.5 2800.9 740 195.5 8705.5 2300 607.7 1362.6 360 95.1 2838.8 750 198.2 9084.0 2400 634.1 1400.5 370 97.8 2876.6 760 200.8 9462.5 2500 660.5 1438.3 380 100.4 2914.5 770 203.4 9841.0 2600 686.9

EFFECTIVITY CL-126C S-4 All Change 1 Weight Conversion • To convert from kilograms to pounds, find, in the bold face columns, the number of kilograms to be converted. The equivalent number of pounds is read in the adjacent column headed POUNDS. • To convert from pounds to kilograms, find, in the bold face columns, the number of pounds to be converted. The equivalent number of kilograms is read in the adjacent column headed KILOGRAMS.

KILOGRAMS POUNDS KILOGRAMS POUNDS KILOGRAMS POUNDS 4.5 10 22.0 208.7 460 1014.1 412.8 910 2006.2 9.1 20 44.1 213.2 470 1036.2 417.3 920 2028.2 13.6 30 66.1 217.7 480 1058.2 421.8 930 2050.3 18.1 40 88.2 222.3 490 1080.3 426.4 940 2072.3 22.7 50 110.2 226.8 500 1102.3 430.9 950 2094.4 27.2 60 132.3 231.3 510 1124.3 435.5 960 2116.4 31.8 70 154.3 235.9 520 1146.4 440.0 970 2138.5 36.3 80 176.4 240.4 530 1168.4 444.5 980 2160.5 40.8 90 198.4 244.9 540 1190.5 449.1 990 2182.6 45.4 100 220.5 249.5 550 1212.5 453.6 1000 2204.6 49.9 110 242.5 254.0 560 1234.6 499.0 1100 2425.1 54.4 120 264.6 258.6 570 1256.6 544.3 1200 2645.5 59.0 130 286.6 263.1 580 1278.7 589.7 1300 2866.0 63.5 140 308.6 267.6 590 1300.7 635.0 1400 3086.4 68.0 150 330.7 272.2 600 1322.8 680.4 1500 3306.9 72.6 160 352.7 276.7 610 1344.8 907.2 2000 4409.2 77.1 170 374.8 281.2 620 1366.9 1134.0 2500 5511.5 81.6 180 396.8 285.8 630 1388.9 1360.8 3000 6613.8 86.2 190 418.9 290.3 640 1410.9 1587.6 3500 7716.1 90.7 200 440.9 294.8 650 1433.0 1814.4 4000 8818.4 95.3 210 463.0 299.4 660 1455.0 2041.2 4500 9920.7 99.8 220 485.0 303.9 670 1477.1 2268.0 5000 11023.0 104.3 230 507.1 308.4 680 1499.1 2494.8 5500 12125.3 108.9 240 529.1 313.0 690 1521.2 2721.6 6000 13227.6 113.4 250 551.1 317.5 700 1543.2 2948.4 6500 14329.9 117.9 260 573.2 322.1 710 1565.3 3175.2 7000 15432.2 122.5 270 595.2 326.6 720 1587.3 3402.0 7500 16534.5 127.0 280 617.3 331.1 730 1609.4 3628.8 8000 17636.8 131.5 290 639.3 335.7 740 1631.4 3855.6 8500 18739.1 136.1 300 661.4 340.2 750 1653.4 4082.4 9000 19841.4 140.6 310 683.4 344.7 760 1675.5 4309.2 9500 20943.7 145.2 320 705.5 349.3 770 1697.5 4536.0 10000 22046.0 149.7 330 727.5 353.8 780 1719.6 4989.6 11000 24250.6 154.2 340 749.6 358.3 790 1741.6 5443.2 12000 26455.2 158.8 350 771.6 362.9 800 1763.7 5896.8 13000 28659.8 163.3 360 793.7 367.4 810 1785.7 6350.4 14000 30864.4 167.8 370 815.7 371.9 820 1807.8 6804.0 15000 33069.0 172.4 380 837.7 376.5 830 1829.8 7257.6 16000 35273.6 176.9 390 859.8 381.0 840 1851.9 7711.1 17000 37478.2 181.4 400 881.8 385.6 850 1873.9 8164.7 18000 39682.8 186.0 410 903.9 390.1 860 1896.0 8618.3 19000 41887.4 190.5 420 925.9 394.6 870 1918.0 9071.9 20000 44092.0 195.0 430 948.0 399.2 880 1940.0 9525.5 21000 46296.6 199.6 440 970.0 403.7 890 1962.1 9979.1 22000 48501.2 204.1 450 992.1 408.2 900 1984.1 10432.7 23000 50705.8

CL-126C EFFECTIVITY Change 1 All S-5 Oxygen Duration

CREW MASKS set to NORM CREW MASKS set to 100% Cabin Altitude — 1000 FT Cabin Altitude — 1000 FT

10 15 20 25 45-136C 25 20 15 10 0 0 0 0 0 0 0 0

5 5 5 5 5 5 5 NUMBER OF 10 10 10 10 PASSENGERS 10 10 10 15 15 10 15 15 9 8 15 20 20 15 20 20 6 20 15 5 25 25 20 25 25 0 0 0 0 0 0 0 0

10 10 10 10 10 5 NUMBER OF 10 10 20 20 20 20 PASSENGERS 20 10 30 30 4 30 30 20 30 15 40 40 40 20 40 2 30 20 50 50 50 40 50 60 60 1 30 25 60 50 40 60 70 70 30 70 60 70 80 50 40 80 80 35 80 0 70 90 90 90 Example 60 40 90 80 50 DURATION — MINUTES 200 300 400 500 600 700 DURATION — MINUTES OXYGEN — LTR

Example: OXY QTY...... 500 LTR Cabin Altitude ...... 25,000 feet

Passengers...... 6 Duration ...... 13.5 min. @ 100% 14 min. @ NORM

EFFECTIVITY EFFECTIVITY CL-126C Aircraft 45-002 thru 45-169 without Altitude Change 1 S-6 Compensated AllOxygen System Oxygen Duration

CREW MASKS set to NORM CREW MASKS set to 100% Cabin Altitude — 1000 FT Cabin Altitude — 1000 FT

10 15 20 25 45-137B 25 20 15 10 0 0 0 0 0 0 0 0 5 5 5 10 5 5 5 10 5 5 15 10 15 20 10 10 10 20 15 10 25 10 20 15 30 25 NUMBER OF 15 15 PASSENGERS 15 35 30 25 20 15 40 35 20 20 30 9 20 45 40 25 35 8 20 50 45 25 25 55 25 50 40 30 6 60 30 30 25 55 45 5 65 35 30

10 10 10 10 5 5 20 10 20 20 10 10 30 30 20 10 40 40 30 NUMBER OF 20 15 PASSENGERS 20 15 50 50 40 30 20 60 60 30 20 50 40 30 25 70 70 4 60 30 25 80 80 50 40 70 40 35 30 90 90 2 100 100 80 60 50

10 10 10 10 20 20 20 10 5 30 30 20 10 40 40 30 10 50 50 40 30 20 10 60 60 50 20 70 70 40 NUMBER OF 30 15 60 20 80 80 50 PASSENGERS 90 90 70 40 30 20 100 100 80 60 110 110 90 50 30 25 120 120 70 1 40 130 100 130 80 140 140 110 60 30 150 150 120 Example 50 40 90 0 160 160 130 70 35 200 300 400 500 600 700 DURATION — MINUTES DURATION — MINUTES OXYGEN — LTR

Example:

OXY QTY...... 500 LTR Cabin Altitude ...... 25,000 feet Passengers...... 6 Duration ...... 20 min. @ 100% 22 min. @ NORM

EFFECTIVITYEFFECTIVITY Aircraft 45-170 & on, and prior CL-126C Change 1 S-6.1 aircraft with AltitudeAll Compensated Oxygen System Oxygen Quantity Mission Planning

MINIMUM OXYGEN QUANTITY — LITERS (as required by regulations) Number of Passengers 0123456789 228 269 311 353 395 437 479 520 562 604 TIME (hours:minutes) Light face numbers indicate one crew member using oxygen above FL410 Bold face numbers indicate one crew member using oxygen above FL350 OXY QTY Number of Passengers LTR 0123456789 8:11 7:25 6:38 5:52 5:05 4:19 3:32 2:46 1:59 1:13 670 6:42 6:03 5:26 4:48 4:10 3:32 2:54 2:16 1:38 1:00 7:19 6:33 5:46 5:00 4:13 3:27 2:40 1:54 1:07 0:21 623 6:00 5:22 4:44 4:05 3:28 2:50 2:12 1:34 0:56 0:17 6:58 6:12 5:25 4:39 3:52 3:06 2:19 1:33 0:46 0:00 604 5:42 5:03 4:26 3:48 3:09 2:32 1:54 1:16 0:38 0:00 6:12 5:25 4:39 3:52 3:06 2:19 1:33 0:46 0:00 562 5:03 4:26 3:48 3:09 2:32 1:54 1:16 0:38 0:00 5:25 4:39 3:52 3:06 2:19 1:33 0:46 0:00 520 4:26 3:48 3:09 2:32 1:54 1:16 0:38 0:00 4:39 3:52 3:06 2:19 1:33 0:46 0:00 479 3:48 3:09 2:32 1:54 1:16 0:38 0:00 3:52 3:06 2:19 1:33 0:46 0:00 437 3:09 2:32 1:54 1:16 0:38 0:00 3:06 2:19 1:33 0:46 0:00 395 2:32 1:54 1:16 0:38 0:00 2:19 1:33 0:46 0:00 353 1:54 1:16 0:38 0:00 1:33 0:46 0:00 311 1:16 0:38 0:00 0:46 0:00 269 0:38 0:00 0:00 228 0:00

NOTE: The time obtained from this table may exceed the fuel endurance available.

Conditions: • Cabin Pressure — Normal • One crew member using oxygen (crew mask in normal mode)

CL-126C EFFECTIVITYEFFECTIVITY Change 1 Aircraft 45-002 thru 45-169All without Altitude Compensated Oxygen System S-7 Oxygen Quantity Mission Planning

MINIMUM OXYGEN QUANTITY — LITERS (as required by regulations) Number of Passengers 0123456789 228 248 267 287 307 327 347 367 387 407 TIME (hours:minutes) Light face numbers indicate one crew member using oxygen above FL410 Bold face numbers indicate one crew member using oxygen above FL350 OXY QTY Number of Passengers LTR 0123456789 8:11 7:49 7:27 7:05 6:42 6:20 5:58 5:36 5:14 4:51 670 6:42 6:24 6:05 5:48 5:30 5:11 4:53 4:35 4:17 3:59 7:19 6:57 6:34 6:12 5:50 5:28 5:06 4:43 4:21 4:00 623 5:59 5:41 5:23 5:04 4:47 4:29 4:10 3:52 3:34 3:16 6:19 5:57 5:34 5:12 4:50 4:28 4:06 3:43 3:21 3:00 569 5:10 4:52 4:34 4:16 3:58 3:40 3:21 3:02 2:45 2:27 5:19 4:57 4:34 4:12 3:50 3:28 3:06 2:43 2:21 2:00 515 4:21 4:02 3:45 3:27 3:08 2:50 2:32 2:14 1:56 1:38 3:19 2:57 2:35 2:13 1:50 1:28 1:06 0:44 0:22 0:00 407 2:43 2:25 2:07 1:49 1:31 1:13 0:54 0:36 0:18 0:00 2:57 2:35 2:13 1:50 1:28 1:06 0:44 0:22 0:00 387 2:25 2:07 1:49 1:31 1:13 0:54 0:36 0:18 0:00 2:35 2:13 1:50 1:28 1:06 0:44 0:22 0:00 367 2:07 1:49 1:31 1:13 0:54 0:36 0:18 0:00 2:13 1:50 1:28 1:06 0:44 0:22 0:00 347 1:49 1:31 1:13 0:54 0:36 0:18 0:00 1:50 1:28 1:06 0:44 0:22 0:00 327 1:31 1:13 0:54 0:36 0:18 0:00 1:28 1:06 0:44 0:22 0:00 307 1:13 0:54 0:36 0:18 0:00 1:06 0:44 0:22 0:00 287 0:54 0:36 0:18 0:00 0:44 0:22 0:00 267 0:36 0:18 0:00 0:22 0:00 248 0:18 0:00 0:00 228 0:00

NOTE: The time obtained from this table may exceed the fuel endurance available.

Conditions: • Cabin Pressure — Normal • One crew member using oxygen (crew mask in normal mode)

CL-126C EFFECTIVITYEFFECTIVITY Change 1 Aircraft 45-170All & on, and prior aircraft with Altitude Compensated S-7.1 Oxygen System CREW NOTES

EFFECTIVITY CL-126C S-8 All DC Power Distribution (Dual Generator Failure) EMER BATT BUS [EMER BUS] BUS, VOLTS [DAU 1] CH A [DAU 2] CH A [STBY] GYRO, ALT VIB GEAR Control Indicator PAX OXY [RMU 1 PWR] SEC INBD BRAKES/Anti-Skid [CKPT INSTRS] EMER PWR (Lights) R PRESS L EMER HOT BUS [L FIRE] EXT, FWSOV R EMER HOT BUS [R FIRE] EXT, FWSOV ***Emergency Battery Duration: 1 Hr * * L ESS AV R HOT BUS CLR DEL RAD OVRHD Cockpit Lights ENTRY Lights L GEN BUS L TAXI/LDG CTRL Light R GEN BUS R TAXI/LDG CTRL Light NAV LIGHT-FWD NAV LIGHTS-AFT R ESS AV [DISPLAY] DU 1 [DISPLAY] DU 3 [DISPLAY] DU 4 REAR HOT BUS SPPR Baggage Lights Tailcone Utility Light TOILET Service Emergency Lighting ***Main Battery Duration: 27 Size & 28 30 Amp-Hr: Min. 38 Size 1 Amp-Hr: Hr R ESS BUS AUDIO 2 [RMU 2 PWR] SEC R WARN PANEL (CWP), FDR [DISPLAY] R CTRL IC/SG 2, ADC 2 [DAU 2] CH B [AHRS PWR] #1 SEC [AHRS PWR] #2 PRI R SQUAT Switch OUTBD BRAKES/Anti-Skid BRAKE ACCUM PRESS R STALL WARN SPLR IND (Spoiler Indicator) R FLAP POS, CTRL [TRIM] PIT TRIM BIAS, SEC PITCH, RUD RUD FORCE R WHL MSTR [R ESS BUS] BUS, VOLTS/START R FUEL FLOW [R IGN] CH A/B R CMPTR ** [R FIRE] DET [R REVERSER] DEPLOY, ANN, STOW R OIL PRESS/Temperature R QTY (Fuel) [R STBY PUMP] PWR/CTRL (Fuel) XFLOW VALVE CTRL (Fuel) R BLEED, [TEMP CTRL] MAN R EMER PRESS [R HEAT] WSHLD ** ICE DETECT [R PROBES HT] STBY PITOT ** L ESS BUS Instrument/Avionics COMM 1, AUDIO 1/CLR DLY, CABIN PA, ADF 1, DME NAV FMS 1, ATC [RMU 1 PWR] PRI [DISPLAY] L CTRL, DU 2 IC/SG 1, ADC 1 [DAU 1] CH B [AHRS PWR] #1 PRI, [AHRS PWR] #2 SEC CVR, L WARN PANEL (CWP) Landing Gear/Brakes L SQUAT Switch MAIN HYD PRESS Indicator [AUX HYD PUMP] PWR, CTRL [NOSE STEER] MOTOR, CMPTR Flight Controls L STALL WARN SPLR CTRL (Spoiler Control) L FLAP POS [TRIM] AIL, PRI PITCH ELEV DISC (Disconnect) L WHL MSTR Electrical [L ESS BUS] BUS, VOLTS/START Engine L FUEL FLOW [L IGN] CH A/B L CMPTR ** [L FIRE] DET [L REVERSER] DEPLOY, ANN, STOW L OIL PRESS/Temperature L QTY (Fuel) [L STBY PUMP] PWR/CTRL (Fuel) Environmental/Pressurizatiom L BLEED, LEAK DETECT, PACK L EMER PRESS Anti-Icing [L HEAT] WSHLD ** Lights [COCKPIT] FLOOD, MAP [CKPT INSTRS] L ESS PWR DOOR * NOTE 1: L and R Essential Avionics Buses will also remain powered until AV MSTR switches are selected OFF, as pe r AFM procedure. ** NOTE 2: AFM procedure calls for turning L & R WSHLD - OFF (until 5 min. before landing), ENG CMPTR MAN, and DU 2 OFF. *** NOTE 3: Battery duration from time both generators are off.

CL-126C EFFECTIVITY Change 2 Change 2 All S-9 Electrical System (Dual Generator Failure) R OFF OFF GCU R GEN NON-ESS OFF R AV MSTR GEN R MAIN AV BUS R START R NON-ESS BUS OFF R MAIN R ESS AV BUS R MAIN BUS R MAIN BATT R GEN BUS 80A R ESS BUS R ESS BUS (copilot's ELECTRICAL) DIODE CONTACTOR CIRCUIT BREAKER R HOT BUS (copilot's ELECTRICAL) 15A EMER BATT R HOT BUS R EMER HOT BUS EMER BUS (pilot's ELECTRICAL) 15A 15A (Nose Compartment) (SHUNT) FUSE CURRENT SENSOR LEGEND REAR HOT BUS EMER BATT BUS OFF EMER EMER BATT L HOT BUS 15A L EMER HOT BUS 20A L HOT BUS (Tailcone) BATTERY POWER EMER BATTERY POWER (pilot's ELECTRICAL) L ESS BUS (pilot's ELECTRICAL) 80A L ESS BUS L MAIN BATT L GEN BUS L MAIN BUS OFF L MAIN L ESS AV BUS GEN L START OFF L AV MSTR L NON-ESS BUS L L MAIN AV BUS OFF OFF OFF L GEN GCU NON-ESS

Change 2 EFFECTIVITY CL-126C Change 2 S-10 All Electrical System (Normal) R ON GCU OFF OFF R GEN R START NON-ESS OFF R AV MSTR GEN R MAIN AV BUS R START R NON-ESS BUS OFF R MAIN OFF 35A R ESS AV BUS R BATT * R MAIN BUS 35A R MAIN BATT R GEN BUS 80A R ESS BUS R ESSENTIAL CONTACTOR ON RUN GEN APU AVAIL START START APU GEN START/STOP * DIODE CONTACTOR CIRCUIT BREAKER 15A (COCKPIT) EMER BATT R ISOLATION CONTACTOR R HOT BUS R EMER HOT BUS 15A 15A (SHUNT) FUSE AUTO OPN ONLY CURRENT SENSOR LEGEND REAR HOT BUS EMER BATT BUS * OFF EMER EMER BATT MAN BUS-TIE * L HOT BUS 15A L EMER HOT BUS 20A (COCKPIT) CONTACTOR L ISOLATION BATTERY POWER GEN/GPU/APU POWER ON GPU AVAIL EXT PWR ANTIÐFLASH CONTACTOR * 80A L ESSENTIAL CONTACTOR L ESS BUS 35A L MAIN BATT L GEN BUS L MAIN BUS OFF 35A L BATT OFF L MAIN L ESS AV BUS GEN L START OFF L AV MSTR L NON-ESS BUS L L MAIN AV BUS OFF ON OFF OFF GCU L GEN L START NON-ESS

CL-126C EFFECTIVITY Change 1 All S-11 Engine Fire Extinguishing System

L ENGINE R ENGINE EXTINGUISHER FIRE FIRE EXTINGUISHER #1 #2 #2 #1

CLOSED CLOSED

ARMED ARMED FIRE FIRE ARMED ARMED PUSH PUSH

BLEED AIR BLEED AIR SHUTOFF PRESSURE SHUTOFF VALVE PRESSURE GAGE GAGE VALVE

TWO-WAY CONTAINER CONTAINER CHECK FUEL #1 #2 FUEL SHUTOFF VALVE VALVES SHUTOFF VALVE

RELIEF VALVE RELIEF VALVE

HYDRAULIC HYDRAULIC SHUTOFF VALVE SHUTOFF VALVE LH RH NACELLE NACELLE

TR ISOLATION TR ISOLATION VALVE VALVE

LEGEND ENGINE DISCHARGE MANUAL DISCHARGE THERMAL DISCHARGE THERMAL MANUAL DISCHARGE DISCHARGE INDICATOR INDICATOR

Change 2 EFFECTIVITY CL-126C Change 2 S-12 All Bleed Air System

LEGEND RIGHT ENGINE

HP BLEED AIR HP BLEED PORTS LP BLEED AIR

HP/LP BLEED AIR HP PRESS SW (130 PSI) LP BLEED PORT CONDITIONED AIR

VALVE NAC A/I CHECK VALVE VALVE TEMP/PRESS SENSOR A/I PRSOV PYLON TEMP SENSOR ON ELECTRICAL R NAC HP SOV R BLEED ECS 3 EMER PRESS 28 VDC CONTROLLER VALVE 1 680 F ECS PRSOV WING STAB CPCS LOAD COCKPIT EXHAUST PACK ANTI-ICE ANTI-ICE BI-LEVEL CONTROL VALVE 4 5 PRSOV RH CABIN RIGHT APU BLEED CH PACK ON LEFT PACK OFF CH WING/STAB LH CABIN 4 5 HI FLOW APU A/I ON CONTROL COCKPIT/ 2 ON CIRCUIT CABIN RAM AIR GASPERS ECS PRSOV

EMER PRESS 1 680 F 28 VDC 3 L BLEED VALVE HP SOV EMER ON L NAC PRESS ON

OFF OFF A/I PRSOV NAC A/I L BLEED R BLEED VALVE

HP PRESS SW (130 PSI) CAS MESSAGES LP BLEED PORT

1 "LR BLEED OVHT" > 680û F

2 "PACK HIGH FLOW" HP BLEED PORTS 3 "LR EMER PRESS" ON

4 "LR ECS FAIL" LEFT ENGINE 5 "LR ECS FAULT" "LR ENG PYLON OVHT" > 250û F

CL-126C EFFECTIVITY Change 1 All S-13 Temperature Control System HP SOV HP SOV FROM APU HP HP PACK PRSOV BI-LEVEL ECS PRSOV ECS PRSOV ENGINE BLEED-AIR ENGINE BLEED-AIR PACK RAM AIR LP LP CAB TEMP CONT VALVE EXHAUST CKPT TEMP CONT VALVE RAM AIR EMER PRESS VALVE EMER PRESS VALVE AFT PRESSURE BULKHEAD (REF) 2 LH SIDE CABIN COCKPIT GASPERS CKPT & CABIN RH SIDE CABIN 2 1 CABIN TEMP SENSOR/FAN CAS MESSAGES INTEGRATED ECS TEMP CONTROLLER Honeywell 315 47.0 OVER TEMP LIMITER TEMP SENSOR M/P RNG GEN

6 "CKPT DUCT OVHT" > 300 ° F "CAB DUCT OVHT" > 300 ° F 300 TAS +15 SAT 245 GSPD R 200 28.0 R ESS VOLT FUEL 50 3 AMPS AMPS 38 0 A FLT APU #TOC FL300 LL01 KDVT 1 2 ECS N C 360 28.0 BATT TEMPS *PBD01 HYD

35 33 PLAB1 50 MFD CHK EICAS MAG2 RTN ELEC

PLAB2

AMPS 30 L 28.2 200 L ESS VOLT EMER BUS VOLTS 25 SUMRY GEN STAB TGT WX -16 FMS1 KDVT 12.5 NM 12 MIN Honeywell CABIN COCKPIT LEGEND 00 9.4 000 CAS 22 8750 1 20 6.5 10 000 -15 END FUEL FLAPS SAT C CABIN RATE DELTA P CABIN ALT MANUAL RATE LDG ALT L R BLEED AIR LEAK L R ENG PYLON OVHT L R BLEED OVHT L R CAB DUCT OVHT L R CKPT DUCT OVHT L R EMER PRESS ON FLT PITCH TRIM +10 1800 ECS 80 60 50.0 LBS 75.0 550 1002 1750 R HYD OXY C OXY PSI TEMPERATURE N1 ITT N2 TEMPERATURE 1000 OIL C 4450 F FF PPH OIL PSI ELEC EICAS H C COLD HOT COLD HOT 76 60 984 550 50.0 75.0 1700 FUEL LF SUMRY CAB TEMP 78 TEMP CONT CABN CKPT COCKPIT TEMP SENSOR HP BLEED-AIR LP BLEED-AIR HP/LP BLEED-AIR CONDITIONED AIR (COLD) CONDITIONED AIR (HEAT) ON MANUAL TEMP

Change 2 EFFECTIVITY CL-126C Change 2 S-14 All Pressurization System L MAIN BUS EMER BATT BUS CABIN PRESSURE ADC1/ADC2 ADC1/ADC2 ACM BYPASS RELAY (40,000 FT.) THROTTLE SW (82% N1) THROTTLE SW (82% N1) R PRESS LDG GEAR SW L PRESS CABIN PRESSURE LDG GEAR SW UP PSID FPM FT ON PRESS MANUAL MANUAL DN ON EMER DEPRESS UP PRESSURIZATION CABIN PRESSURE CONTROL (LEFT) LDG ALT ON (RIGHT) PRIMARY CHANNEL CHANNEL DN APU BLEED SECONDARY CAB ALT CABIN PRESSURE CONTROLLER DELTA P CAB RATE ON OFF OFF PACK ON R BLEED HI FLOW DEPLOY PAX OXYGEN OFF ON PAX OFF L BLEED (CAS) OXY/AUTO EMER PRESS (CWP) OR OR EICAS CABIN 9,500 FT. 10,000 FT. 14,500 FT. 14,500 FT. 14,500 FT. OXYGEN ON "CABIN ALTITUDE" CABIN ALT EMER PRESSURE CABIN ALTITUDE ENGINE SERVO BLEED-AIR JET PUMP TORQUE MOTOR TORQUE MOTOR CABIN ALT LIMITER (13,700 FT.) CABIN ALT LIMITER (13,700 FT.) DELTA P LIMITERS (9.7 PSID)

DISCHARGE SEC PRI AIR

VALVE VALVE CABIN

OUTFLOW OUTFLOW OWR RSUEBULKHEAD PRESSURE FORWARD

CL-126C EFFECTIVITY Change 1 All S-15 Fuel System

FUEL L STBY XFLOW R STBY ON ON COLLECTOR TANK COLLECTOR TANK

CROSSFLOW VALVE

LEFT WING FUEL TANK SHUTOFF RIGHT WING FUEL TANK VALVES

FILLER PORT

FUSELAGE FUEL TANK LEFT RIGHT

ENGINE ENGINE SPPR ADAPTER

LEGEND

ENGINE DRIVEN FUEL PUMP FUEL FILTER MOTOR DRIVEN VALVE PRESSURE SWITCH STANDBY PUMP CHECK VALVE

FLOAT SWITCH JET PUMP LOW FUEL SENSOR

HIGH PRESSURE LOW PRESSURE STORAGE TRANSFER

FUEL LBS FUEL 4250 FIRE L STBY XFLOW R STBY FIRE LF1600 1000 R 1650 CLOSED ON ON CLOSED

FIRE FIRE FUEL QUANTITY INDICATION ON EICAS PUSH TOTALIZER RESET PUSH

TOTAL LBS 4250 L ENG CMPTR R ENG CMPTR ENG SYNC APR L WING R WING ON EDS RECORD ON N1 1600 1650 M M A N2 ARM A N N FUSELAGE OFF 1000 OFF OFF L ENG 495 USED R ENG

FUEL SYSTEM SCHEMATIC ON EICAS/MFD DISPLAY ENGINE/FUEL CONTROL PANEL

Change 2 EFFECTIVITY CL-126C Change 2 S-16 All Hydraulic System RESERVOIR FULL (GSP INDICATOR) HYD FLUID LEVEL SENSOR OVERFULL (GSP INDICATOR) 5 4 SUPPLY MAIN PRESSURE MAIN RETURN AUX PRESSURE AUX RETURN BLEED AIR FIRE PUSH CLOSED DC MOTOR DRIVEN AUX PUMP SHUTOFF VALVES PASS THROUGH FIRE PUSH PRESS MODULE CLOSED ON AUX HYD ENGINE PUMPS LEGEND PRESSURE TRANSDUCER ELECTRICAL MECHANICAL 3 1 2 GROUND SERVICING VALVE TR'S ENGINE BLEED AIR MAIN FILTER MANIFOLD AUX FILTER MANIFOLD EMERGENCY/ PARKING BRAKE 6 MAIN SYSTEM ACCUM 7 EMER/PARK BRAKE VALVE SPOILERS/ SPOILERONS BRAKE ACCUM

SOL AUX MAIN BRAKE FLAP DRIVE MAIN/AUX BRAKES PRESSURE EMER/PARK HYD XFLOW DOOR CONTROL VALVE LANDING GEAR CONTROL VALVE MODULE LDG GEAR CONTROL VALVE AUX HYD QTY LOW MAIN HYD PRESS B-ACUM R HYD PUMP LOW L HYD PUMP LOW AUX HYD PUMP LO AUX HYD QTY LO MAIN HYD PRESS BRK ACUM PRESS MAIN HYDQTY LO CAS MESSAGES EICAS/MFD SUMRY HYD INDICATIONS 4 6 7 1 2 3 4 5 6 7 LDG GEAR FREE-FALL LEVER

CL-126C EFFECTIVITY Change 1 All S-17 Hydraulic System (HYD XFLOW ON) RESERVOIR FULL (GSP INDICATOR) HYD FLUID LEVEL SENSOR OVERFULL (GSP INDICATOR) 5 4 SUPPLY MAIN PRESSURE MAIN RETURN AUX PRESSURE AUX RETURN BLEED AIR FIRE PUSH CLOSED DC MOTOR DRIVEN AUX PUMP SHUTOFF VALVES FIRE PUSH PRESS MODULE CLOSED ON AUX HYD ENGINE PUMPS LEGEND PRESSURE TRANSDUCER ELECTRICAL MECHANICAL 3 1 2 GROUND SERVICING VALVE TR'S ENGINE BLEED AIR MAIN FILTER MANIFOLD AUX FILTER MANIFOLD EMERGENCY/ PARKING BRAKE 6 MAIN SYSTEM ACCUM SHUTTLE VALVE 7 EMER/PARK BRAKE VALVE SPOILERS/ SPOILERONS BRAKE ACCUM

SOL AUX MAIN BRAKE ON FLAP DRIVE MAIN/AUX BRAKES PRESSURE EMER/PARK HYD XFLOW DOOR CONTROL VALVE LANDING GEAR CONTROL VALVE MODULE LDG GEAR CONTROL VALVE AUX HYD QTY LOW MAIN HYD PRESS B-ACUM R HYD PUMP LOW L HYD PUMP LOW AUX HYD PUMP LO AUX HYD QTY LO MAIN HYD PRESS BRK ACUM PRESS MAIN HYDQTY LO CAS MESSAGES EICAS/MFD SUMRY HYD INDICATIONS 4 6 7 1 2 3 4 5 6 7 LDG GEAR FREE-FALL LEVER

Change 2 EFFECTIVITY CL-126C Change 2 S-18 All Landing Gear (Extended) ON ON ANTI-SKID AUX HYD LANDING GEAR FREE-FALL LEVER HYD XFLOW NOSE STEER DOWN GEAR / HYD N DOWN UP DN LR DOWN CENTER PEDESTAL VLO 200 VLE 260

SOL HYD XFLOW VALVE FLAP DRIVE SOL SOL RETRACT FREE-FALL VALVE LDG GEAR CONTROL VALVE EXTEND EXTEND RETRACT SOL DOOR CONTROL VALVE SOL LANDING GEAR CONTROL VALVE MODULE MAIN HYD PRESS MAIN RETURN HYD AUX HYD PRESS AUX RETURN HYD ELECTRICAL MECHANICAL LEGEND

CL-126C EFFECTIVITY Change 1 All S-19 Landing Gear (Retracted) ANTI-SKID AUX HYD LANDING GEAR FREE-FALL LEVER HYD XFLOW NOSE STEER DOWN GEAR / HYD N DOWN UP DN LR CENTER PEDESTAL VLO 200 VLE 260

SOL HYD XFLOW VALVE FLAP DRIVE SOL SOL FREE-FALL VALVE LDG GEAR CONTROL VALVE EXTEND RETRACT EXTEND RETRACT DOOR CONTROL VALVE SOL SOL LANDING GEAR CONTROL VALVE MODULE MAIN HYD PRESS MAIN RETURN HYD AUX HYD PRESS AUX RETURN HYD ELECTRICAL MECHANICAL LEGEND

Change 2 EFFECTIVITY CL-126C Change 2 S-20 All Brake System

EICAS/CWP

PILOT COPILOT

PEDAL TRANSDUCERS (4) SQUAT SWITCH BRAKE SQUAT SWITCH CONTROL OFF LEGEND UNIT (BCU) ANTI-SKID MAIN HYD SYSTEM PRESS MAIN METERED PRESSURE PRESSURE PRESSURE BRAKE PRESS XDUCER XDUCER

RETURN

AUX HYD RETURN SYSTEM PRESS

ELECTRICAL BRAKE MECHANICAL SHUTOFF VALVES CHECK VALVE AUX INBOARD OUTBOARD PRESSURE BRAKE ACCUM BRAKE BRAKE TRANSDUCER CONTROL CONTROL VALVES VALVES BRAKE FUSE BRAKE (2) (3) (1) (4) ACCUMULATOR

EMERGENCY/ PARKING BRAKE

EMERGENCY/ PARKING BRAKE VALVE

PRESSURE TRANSDUCERS (4)

BRAKE FUSES (5)

WHEEL SPEED TRANSDUCERS (4)

CL-126C EFFECTIVITY Change 1 All S-21 APU Operating Procedures These procedures are intended for start-up and shutdown of the APU separate from the airplane normal checklist. If the APU is operated in line with the airplane normal checklist, refer to the Normal Procedures Checklist for the appropriate procedures. APU PRE-START CHECK 1. L & R BATT...... On, Simultaneously 2. EMER BATT...... EMER 3. APU MASTER...... ON 4. Tailcone Interior Check: a. OIL TEST ...... Select & Check Indicator b. APU FAN FAIL...... Check c. APU Fire Bottle...... Check 5. APU Exhaust...... Clear 6. APU Inlet...... Clear 7. APU Firebox Drains ...... Check 8. Fuel Quantity (right wing)...... Check 9. PACK Circuit Breaker (pilot’s ENVIRONMENTAL group)...... Set 10. APU Circuit Breakers (copilot’s APU group) ...... Set 11. L & R BLEED Circuit Breakers (pilot’s and copilot’s ENVIRONMENTAL & ENVIR group)...... Set 12. MAN & AUTO Circuit Breakers (copilot’s ENVIR group) ...... Set 13. L & R BLEED ...... OFF 14. PACK...... OFF 15. HI FLOW ...... Off 16. MANUAL TEMP ...... Off 17. COCKPIT & CABIN TEMPERATURE COLD-HOT ...... Mid (12 o’clock) Position

Change 2 EFFECTIVITY CL-126C Change 2 S-22 All APU START UP 1. L INSTR Lights ...... On 2. BCN/STROBE ...... BCN 3. APU Fire Detection System...... Test a. SYSTEM TEST ...... FIRE DET, Press & Hold b. Verify: - APU FIRE red CAS activates. - Master WARN tone & lights activate. - APU FIRE switch/indicator illuminates. - APU fire warning horn will sound after 13 to 18 seconds. c. SYSTEM TEST ...... Release 4. APU START/STOP ...... Press & Release 5. APU GEN ...... ON 6. APU BLEED ...... ON 7. PACK ...... On

APU SHUTDOWN 1. APU START/STOP ...... Press & Release 2. APU MASTER (after 30-second delay) ...... Off 3. BCN/STROBE ...... OFF 4. EMER BATT...... OFF 5. L & R BATT...... OFF

CL-126C EFFECTIVITY Change 1 All S-23 Master EICAS Index This GO/NO GO guide contains data for quick reference. This guide in no way supersedes data outlined in the current Minimum Equipment List. In case of conflict, the MEL takes precedence. After performing the applicable checklist procedure and the message persists, check dispatchability as follows:

NO GO or CAS or (EI) Message Tab MEL RELIEF AHRS 1 BASIC A/S-18 N/A AHRS 2 BASIC A/S-18 N/A AHRS 1-2 BASIC A/S-18 N/A AHRS 1 OVHT 22 NO GO AHRS 2 OVHT 22 NO GO AHRS 1-2 OVHT 22 NO GO ANTI-SKID FAIL 37 32-1 L AOA HT FAIL 1 30-1 R AOA HT FAIL 1 30-1 LR AOA HT FAIL 1 30-1 AP AIL MISTRIM 4 NO GO AP ELEV MISTRIM 4 NO GO AP ELEV MISTRIM A/S-8 NO GO APR (EI) A/S-12 N/A APR (EI outbd N1s) A/S-12 N/A L APR FAULT A/S-9 76-3 R APR FAULT A/S-9 76-3 LR APR FAULT A/S-9 76-3 APR ON (EI inbd N1s) A/S-12 N/A APU AVAILABLE A/S-8 N/A APU AMPS HIGH 4N/A APU FAIL 4 49-1 APU FIRE 1 NO GO AUTOSPLR ARMED A/S-13 N/A AUX HYD PMP LO 21 NO GO AUX HYD QTY LO 21 NO GO L BATT OVHT 4 NO GO R BATT OVHT 4 NO GO L BATT OVHT 5 NO GO R BATT OVHT 5 NO GO Change 2 LR BATT OVHT 5 NO GO

EFFECTIVITY CL-126C S-24 All Change 2 Master EICAS Index (Cont) NO GO or CAS or (EI) Message Tab MEL RELIEF L BLEED AIR LEAK 10 NO GO R BLEED AIR LEAK 10 NO GO LR BLEED AIR LEAK 10 NO GO L BLEED OVHT 12 NO GO R BLEED OVHT 12 NO GO LR BLEED OVHT 12 NO GO BRAKE FAULT A/S-25 32-3 BRK ACUM PRESS 21 NO GO BUS TIE CLSD A/S-9 N/A BUS TIE MANUAL A/S-9 N/A CAB DELTA P 13 NO GO CAB DUCT OVHT 13 NO GO LR CAB PRESS FAIL 14 NO GO L CAB PRESS FAIL A/S-13 21-1 R CAB PRESS FAIL A/S-13 21-1 CAB PRESS MAN 14 NO GO CAB PRESS MAN A/S-13 N/A CABIN ALTITUDE 7 NO GO CABIN ALTITUDE 14 NO GO L CHK IC SW 25 NO GO R CHK IC SW 25 NO GO LR CHK IC SW 25 NO GO L CHECK EDS A/S-26 N/A R CHECK EDS A/S-26 N/A LR CHECK EDS A/S-26 N/A CKLST MISMATCH A/S-19 N/A CKPT DUCT OVHT 14 NO GO CNFG MISMATCH 22 NO GO CPLT BRK FAULT 37 NO GO CVR FAIL A/S-25 23-16 DAU 1A FAIL 22 NO GO DAU 1B FAIL 22 NO GO DAU 1A-1B FAIL 22 NO GO DAU 2A FAIL 23 NO GO DAU 2B FAIL 23 NO GO DAU 2A-2B FAIL 23 NO GO DAU A REV A/S-19 N/A DAU B REV A/S-19 N/A Change 2

CL-126C EFFECTIVITY Change 2 All S-25 Master EICAS Index (Cont) NO GO or CAS or (EI) Message Tab MEL RELIEF L DAU ENG MISCMP 23 NO GO R DAU ENG MISCMP 23 NO GO L DAU SYS MISCMP 23 NO GO R DAU SYS MISCMP 23 NO GO DEFUEL OPEN 19 NO GO DEP (EI) 19 NO GO DEP (EI) A/S-12 N/A DU 1 OVHT 24 NO GO DU 2 OVHT 24 NO GO DU 3 OVHT 24 NO GO DU 4 OVHT 24 NO GO DU 1 FAN FAIL A/S-19 NO GO DU 2 FAN FAIL A/S-19 NO GO DU 1-2 FAN FAIL A/S-19 NO GO DU 3 FAN FAIL A/S-20 NO GO DU 4 FAN FAIL A/S-20 NO GO DU 3-4 FAN FAIL A/S-20 NO GO LR ECS FAIL 14 NO GO L ECS FAULT 15 NO GO R ECS FAULT 15 NO GO L ECS FAULT A/S-13 N/A R ECS FAULT A/S-13 N/A EICAS CHK (MFD) 29 NO GO ELEVATOR DISC 17 NO GO ELEVATOR DISC A/S-14 N/A EMER BATT LOW 5 NO GO EMER BUS VOLTS 5 NO GO EMER DEPRESS A/S-13 N/A EMER LIGHTS 7N/A EMER LIGHTS A/S-26 N/A L EMER PRESS ON 15 N/A R EMER PRESS ON 15 N/A LR EMER PRESS ON 15 N/A EMER/PARK BRK 18 N/A EMER/PARK BRK A/S-25 N/A EMERGENCY EXIT 5 52-1 L ENG FIRE FAIL 7 NO GO R ENG FIRE FAIL 7 NO GO LR ENG FIRE FAIL 7 NO GO

EFFECTIVITY CL-126C S-26 All Change 2 Master EICAS Index (Cont) NO GO or CAS or (EI) Message Tab MEL RELIEF L ENG FIRE FAIL A/S-9 N/A R ENG FIRE FAIL A/S-9 N/A LR ENG FIRE FAIL A/S-9 N/A L ENG PYLON OVHT 10 NO GO R ENG PYLON OVHT 10 NO GO LR ENG PYLON OVHT 10 NO GO L ENG SHUTDOWN A/S-10 N/A R ENG SHUTDOWN A/S-10 N/A LR ENG SHUTDOWN A/S-10 N/A L ENG VIB MON A/S-10 N/A R ENG VIB MON A/S-10 N/A LR ENG VIB MON A/S-10 N/A L ENGCMPTR FAULT 7 NO GO R ENGCMPTR FAULT 7 NO GO LR ENGCMPTR FAULT 7 NO GO L ENGCMPTR FAULT A/S-10 N/A R ENGCMPTR FAULT A/S-10 N/A LR ENGCMPTR FAULT A/S-10 N/A L ENGINE CHIP 7 NO GO R ENGINE CHIP 7 NO GO LR ENGINE CHIP 7 NO GO L ENGINE CHIP A/S-11 N/A R ENGINE CHIP A/S-11 N/A LR ENGINE CHIP A/S-11 N/A ENTRY DOOR 452-1 ENTRY DOOR PIN A/S-8 52-1 L ESS BUS FAULT 6 NO GO R ESS BUS FAULT 6 NO GO LR ESS BUS FAULT 6 NO GO L ESS BUS FAULT A/S-9 N/A R ESS BUS FAULT A/S-9 N/A LR ESS BUS FAULT A/S-9 N/A L ESS BUS VOLTS 6 NO GO R ESS BUS VOLTS 6 NO GO LR ESS BUS VOLTS 6 NO GO EXTERNAL DOORS 552-1 EXTERNAL POWER A/S-9 N/A FDR FAIL A/S-26 31-4

CL-126C EFFECTIVITY Change 2 All S-27 Master EICAS Index (Cont) NO GO or CAS or (EI) Message Tab MEL RELIEF FIRE (EI) 7N/A FLAPS FAIL 17 NO GO FLAPS FAULT 17 NO GO L FUEL BAY LOW A/S-16 N/A R FUEL BAY LOW A/S-16 N/A LR FUEL BAY LOW A/S-16 N/A L FUEL FILTER 20 NO GO R FUEL FILTER 20 NO GO LR FUEL FILTER 20 NO GO L FUEL FILTER A/S-17 N/A R FUEL FILTER A/S-17 N/A LR FUEL FILTER A/S-17 N/A L FUEL HEATER 20 NO GO R FUEL HEATER 20 NO GO LR FUEL HEATER 20 NO GO L FUEL HEATER A/S-17 NO GO R FUEL HEATER A/S-17 NO GO LR FUEL HEATER A/S-17 NO GO FUEL IMBALANCE 20 N/A L FUEL PRESS LOW 13 NO GO R FUEL PRESS LOW 13 NO GO LR FUEL PRESS LOW 13 NO GO L FUEL QTY FAULT A/S-17 28-4 R FUEL QTY FAULT A/S-17 28-3 FUEL QTY FAULT A/S-17 NO GO L FUEL QTY LOW 20 N/A R FUEL QTY LOW 20 N/A LR FUEL QTY LOW 20 N/A FUEL XFLO 20 NO GO FUEL XFLO OPEN A/S-16 N/A L FWSOV CLSD A/S-17 N/A R FWSOV CLSD A/S-17 N/A LR FWSOV CLSD A/S-17 N/A L FWSOV FAULT 20 NO GO R FWSOV FAULT 20 NO GO LR FWSOV FAULT 20 NO GO GEAR 16 N/A GEAR 37 N/A

EFFECTIVITY CL-126C S-28 All Change 2 Master EICAS Index (Cont) NO GO or CAS or (EI) Message Tab MEL RELIEF L GEN AMPS HIGH 7N/A R GEN AMPS HIGH 7N/A LR GEN AMPS HIGH 7N/A LR GEN FAIL 4 NO GO L GEN FAIL 7 NO GO R GEN FAIL 7 NO GO GND PROX FAIL A/S-20 34-15 GPWS FAIL A/S-21 34-15 GPWS FLAP OVRD A/S-20 N/A GPWS G/S INHB A/S-21 N/A GPWS SYS FAIL A/S-21 34-15 L HYD PUMP LOW A/S-18 NO GO R HYD PUMP LOW A/S-18 NO GO LR HYD PUMP LOW A/S-18 NO GO HYD XFLOW ON A/S-18 N/A IC 1 OVHT 24 NO GO IC 2 OVHT 24 NO GO IC BUS FAIL 25 NO GO IC 1 CNFG FAIL A/S-21 N/A IC 2 CNFG FAIL A/S-21 N/A IC 1 FAN FAIL A/S-21 NO GO IC 2 FAN FAIL A/S-21 NO GO IC 1-2 FAN FAIL A/S-21 NO GO IC 1 WOW INOP A/S-22 NO GO IC 2 WOW INOP A/S-22 NO GO IC 1-2 WOW INOP A/S-22 NO GO ICE DET FAIL 1 30-12 ICE DETECTED 1N/A ICE DETECTED A/S-7 N/A IGN (EI) 10 NO GO IGN (EI) A/S-12 74-1 IGN (EI) A/S-12 N/A L INBD BRK FAIL 37 NO GO R INBD BRK FAIL 37 NO GO LR INBD BRK FAIL 37 NO GO INSTR PNL TEMP A/S-22 N/A LBS/KGS CONFIG 25 NO GO LBS/KGS CONFIG A/S-22 N/A

CL-126C EFFECTIVITY Change 2 All S-29 Master EICAS Index (Cont) NO GO or CAS or (EI) Message Tab MEL RELIEF MACH TRIM FAIL 17 22-2 MACH TRIM FAIL A/S-8 22-2 MAIN HYD PRESS 22 NO GO MAIN HYDQTY LO A/S-18 NO GO MAN (EI) 10 NO GO MAN (EI) A/S-12 NO GO MCR (EI) A/S-12 N/A MCT (EI) A/S-12 N/A NAC (EI) 10 30-7 NAC (EI) A/S-12 N/A L NAC HT 230-7 R NAC HT 230-7 LR NAC HT 230-7 L NAC HT FAIL ON 2N/A R NAC HT FAIL ON 2N/A LR NAC HT FAIL ON 2N/A NORM BRK FAIL 16 NO GO NOSE BAY TEMP A/S-22 N/A NWS FAIL 38 32-2 NWS FAULT A/S-25 32-2 L OIL FILTER 7 NO GO R OIL FILTER 7 NO GO LR OIL FILTER 7 NO GO L OIL FILTER A/S-11 N/A R OIL FILTER A/S-11 N/A LR OIL FILTER A/S-11 N/A L OIL PRESS LOW 8 NO GO R OIL PRESS LOW 8 NO GO L OUTBD BRK FAIL 38 NO GO R OUTBD BRK FAIL 38 NO GO LR OUTBD BRK FAIL 38 NO GO OXYGEN OFF 15 NO GO OXYGEN QTY LOW 15 N/A OXY PRESS HI 16 NO GO PACK HIGH FLOW A/S-13 N/A PACK OVHT 16 21-6 PAX OXY DEPLOY A/S-13 N/A PAX OXY FAIL 16 35-3

EFFECTIVITY CL-126C S-30 All Change 2 Master EICAS Index (Cont) NO GO or CAS or (EI) Message Tab MEL RELIEF L PFD CHECK 25 NO GO R PFD CHECK 25 NO GO LR PFD CHECK 25 NO GO PIT TRIM BIAS 18 NO GO PIT TRIM BIAS A/S-14 NO GO PIT TRIM MISCMP 18 NO GO PIT TRIM MSCMP A/S-14 NO GO PITCH TRIM OFF A/S-14 N/A L PITOT HT 230-9 R PITOT HT 230-9 LR PITOT HT 230-9 PLT BRK FAULT 38 NO GO PRI TRIM FAIL 17 NO GO PRI TRIM FAULT A/S-14 NO GO REV (EI) 11 NO GO REV (EI) A/S-12 N/A L REV AUTOSTOW A/S-26 N/A R REV AUTOSTOW A/S-26 N/A LR REV AUTOSTOW A/S-26 N/A L REV FAULT A/S-27 78-1 R REV FAULT A/S-27 78-1 LR REV FAULT A/S-27 78-1 L REV UNSAFE (CWP) 19 78-1 R REV UNSAFE (CWP) 19 78-1 ROLL DISC 17 NO GO ROLL DISC A/S-15 N/A RUD BOOST INOP 18 NO GO RUD BOOST INOP A/S-8 N/A SAT HT FAIL 230-2 SEC PITCH TRIM A/S-15 N/A SEC TRIM FAIL 18 NO GO SEC TRIM FAULT A/S-15 NO GO L SPOILER JAM 19 NO GO R SPOILER JAM 19 NO GO LR SPOILER JAM 19 NO GO SPOILERS EXT 18 N/A SPOILERS EXT 18 N/A SPOILERS EXT A/S-15 N/A SPOILERS FAIL 18 NO GO

CL-126C EFFECTIVITY Change 2 All S-31 Master EICAS Index (Cont) NO GO or CAS or (EI) Message Tab MEL RELIEF STAB OVHT 1 NO GO STAB TEMP LOW 2 30-4 STAB TMP FAULT A/S-7 30-4 L STALLWARN FAIL 19 NO GO R STALLWARN FAIL 19 NO GO LR STALLWARN FAIL 19 NO GO START (EI) 11 NO GO START (EI) A/S-12 N/A STBY PITOT HT 2 30-9 L STBY PUMP ON A/S-18 N/A R STBY PUMP ON A/S-18 N/A LR STBY PUMP ON A/S-18 N/A SYNC (EI) 11 N/A SYNC (EI) A/S-12 N/A T/O (EI) A/S-12 N/A TAKEOFF TRIM 18 N/A TAKEOFF TRIM A/S-15 N/A TERR FAIL A/S-22 34-15 TERR INHB A/S-23 N/A TERR INHIB A/S-23 N/A UNL (EI) 19 78-1 UNL (EI) 11 N/A WARN AUDIO 25 NO GO WARN AUDIO A/S-27 NO GO LR WARN PWR FAIL 25 NO GO L WARN PWR FAIL A/S-27 NO GO R WARN PWR FAIL A/S-27 NO GO WG/STAB HT OK A/S-7 N/A WHEEL MSTR A/S-16 N/A WINDSHEAR FAIL A/S-23 34-15 WING OVHT 1 NO GO WING TEMP LOW 3 30-4 WING TMP FAULT A/S-7 30-4 WING/STAB LEAK 1 NO GO L WSHLD HT FAIL 3 30-10 R WSHLD HT FAIL 3 30-10 LR WSHLD HT FAIL 3 30-10

EFFECTIVITY CL-126C S-32 All Change 2 NO GO or CAS or (EI) Message Tab MEL RELIEF L WSHLD HT FAULT A/S-7 30-10 R WSHLD HT FAULT A/S-7 30-10 LR WSHLD HT FAULT A/S-7 30-10 L WSHLD OVHT 3 NO GO R WSHLD OVHT 3 NO GO LR WSHLD OVHT 3 NO GO

CL-126C EFFECTIVITY Change 2 All S-33