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 na me. 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 ma y 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 b y the Continuin g Airworthiness Division ( AARDG ) , National Aircraft Certification Branch, Trans p ort Canada, Ottawa, tele p hone 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 Communicat ions 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

2 4-0022 ( 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 frac ture 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 pi n holes where the connecting rod fitting is attached. Fatigue testing of the rudder pedal t ubes confirmed that the fatigue cracking is due to loads induced during parking brake applic ation. 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 w ould 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 failure s 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 ins pections 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 inspecti on of both pilot-side rudder pedal tubes in accordance with the Accomplishment Instructi ons 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 t he Bombardier Technical Help Desk for a Transport Canada approved repair and incorporat e the repair before further flight. The approved repair must specif ically 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 inspecti on of the pilot-side rudder pedal tubes in accordance with the Accomplishment Inst ructions 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 t he 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 t he Bombardier Technical Help Desk for a Transport Canada approved repair and incorporat e the repair before further flight. The approved repair must specif ically reference this AD. D. If no cracks or damage are found, repeat t he 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 Airworthine ss, Ottawa, telephone 613-952-4357, facsimile 613-996-9178 or e-mail AD-CN@tc.gc.ca or any Transport Canada Centre.