Transport Transports 

Canada Canada

 TP 7245E

 

AIRWORTHINESS DIRECTIVE

The following airworthiness directive (AD) may be applicable to an aircraft which our records indicate is registered in your name. ADs are issued pursuant to Canadian 

Aviation Regulation (CAR) 521 Division X. Pursuant to CAR 605.84 and the further details of CAR Standard 625, Appendix H, the continuing airworthiness of a Canadian registered aircraft is contingent upon compliance with all applicable ADs. Failure to comply with the requirements of an AD may invalidate the flight authorization of the aircraft. Alternative means of compliance shall be applied for in accordance with CAR 605.84 and the above-referenced Standard. 

This AD has been issued by the Continuing Airworthiness Division (AARDG), National Aircraft Certification Branch, Transport Canada, Ottawa, telephone 613 952-4357.

Pursuant to CAR 202.51 the registered owner of a Canadian aircraft shall, within seven days, notify the Minister in writing of any change of his or her name or address. 

To request a change of address, contact the Civil Aviation Communications Centre (AARC) at Place de Ville, Ottawa, Ontario K1A 0N8, or 1-800-305-2059, or www.tc.gc.ca/civilaviation/communications/centre/ address.asp 

24-0022 (01-2005)

1/2 No.

CF-2014-02

Issue Date 

 8 January 2014 

Number: CF-2014-02 

Subject: Rudder Control System – Cracking of the Pilot-Side Rudder Pedal Tubes 

Effective: 22 January 2014 

Applicability: Bombardier Inc.: 

Model CL-600-2C10 aeroplanes, serial numbers 10002 through 10342; 

Model CL-600-2D15 & CL-600-2D24 aeroplanes, serial numbers 15001 through 

15337; 

Model CL-600-2E25 aeroplanes, serial numbers 19001 through 19040. 

Compliance: As indicated below, unless already accomplished. 

Background: There have been two in-service reports of fracture of the rudder pedal tubes installed on 

the pilot-side rudder bar assembly on CL-600-2B19 model aeroplanes. 

Laboratory examination of the fractured rudder pedal tubes found that in both cases, the 

fatigue cracks initiated at the aft taper pin holes where the connecting rod fitting is 

attached. Fatigue testing of the rudder pedal tubes confirmed that the fatigue cracking is 

due to loads induced during parking brake application. Therefore, only the rudder pedal 

tubes on the pilot’s side are vulnerable to fatigue cracking as the parking brake is

primarily applied by the pilot. 

Loss of pilot rudder pedal input during flight would result in reduced yaw controllability of 

the aeroplane. Loss of pilot rudder pedal input during takeoff or landing may lead to a

runway excursion. 

Although there have been no reported failures to date on any CL-600-2C10, -2D15,

-2D24 and -2E25 model aeroplanes, the same torque tubes part number (P/N) 

600-90204-3 are installed which may be prone to premature fatigue cracking. 

This AD mandates initial and repetitive inspections of the pilot-side rudder pedal tubes, 

P/N 600-90204-3, until the terminating action is accomplished. 

Corrective 

Actions: 

Part I – Initial Inspection

A. Prior to accumulating 26 000 total flight cycles, perform a Detailed Visual 

Inspection (DVI) or eddy current inspection of both pilot-side rudder pedal tubes in 

accordance with the Accomplishment Instructions in Part A of the Bombardier Service 

Bulletin (SB) 670BA-27-065, Initial Issue, dated 15 November 2013, or later revisions 

approved by the Chief, Continuing Airworthiness, Transport Canada. 

B. If a crack is found around the aft tapered holes, before further flight, replace the 

rudder bar assembly in accordance with the Accomplishment Instructions in Part B of 

the above-mentioned SB. 
No.

N° CF-2014-02 2/2 

C. If any other damage is found, contact the Bombardier Technical Help Desk for a 

Transport Canada approved repair and incorporate the repair before further flight. 

The approved repair must specifically reference this AD. 

D. If no cracks or damage are found, repeat the inspection of the pilot-side rudder pedal 

tubes in accordance with Part II of this AD until the terminating action in Part III of this 

AD is accomplished. 

Part II – Repetitive Inspections 

A. Perform a DVI or eddy current inspection of the pilot-side rudder pedal tubes in 

accordance with the Accomplishment Instructions in Part A of SB 670BA-27-065, 

Initial Issue, dated 15 November 2013 or later revisions approved by the Chief, 

Continuing Airworthiness, Transport Canada, in accordance with the 

following schedule: 

1. Within 750 flight cycles from the previous DVI inspection; or 

2. Within 1250 flight cycles from the previous eddy current inspection. 

B. If a crack is found around the aft tapered holes, before further flight, replace the 

rudder bar assembly in accordance with the Accomplishment Instructions in Part B of 

the above-mentioned SB. 

C. If any other damage is found, contact the Bombardier Technical Help Desk for a 

Transport Canada approved repair and incorporate the repair before further flight. 

The approved repair must specifically reference this AD. 

D. If no cracks or damage are found, repeat the inspections of the pilot-side rudder 

pedal tubes in accordance with Part II of this AD until the terminating action in Part III 

of this AD is accomplished. 

Part III – Terminating Action 

Replacement of both pilot-side rudder bar assemblies in accordance with the 

Accomplishment Instructions in Part B of the above-mentioned SB constitutes terminating 

action for the inspections in Part I & II of this AD. 

Authorization: For the Minister of Transport, 

ORIGINAL SIGNED BY 

Derek Ferguson 

Chief, Continuing Airworthiness 

Contact: Robert Farinas, Continuing Airworthiness, Ottawa, telephone 613-952-4357, facsimile 

613-996-9178 or e-mail AD-CN@tc.gc.ca or any Transport Canada Centre.