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) 593. 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)

1/3 No.

CF-2009-24

Issue Date 

 19 May 2009 

Number: CF-2009-24 

Subject: Air Driven Generator (ADG) – Strut Cracking

Effective: 08 June 2009 

Applicability: Bombardier Inc. Model CL-600-2B16 (CL-604), Serial Numbers 5408 through 5665 

Compliance: As indicated below. 

Background: Two cases of a crack on a "dry" ADG (Hamilton Sundstrand part number in the 761339 series), in the aft area of the strut and generator housing assembly, have been reported on CL-600-2B19 aircraft. The same part number is also installed on CL-600-2B16 (CL-604) aircraft. Investigation determined that the crack was in an area of the strut where the wall thickness of the casting was below specification, due to a manufacturing anomaly in a specific batch of ADGs. Structural failure 

and departure of the ADG during deployment could possibly result in damage to the aircraft structure. If deployment were activated by a dual engine shutdown, ADG structural failure would also result in loss of hydraulics for the flight controls. 

This directive gives instructions to check the part number of the installed ADG and, for ADGs with a 

part number in the 761339 series, the serial numbers of the ADG and the strut and generator housing assembly are also to be checked. If these serial numbers are within specified ranges [see Part I, paragraph B.(3).(a) below], initial and subsequent repeat fluorescent penetrant inspections of the ADG strut are required. 

This directive also gives instructions to perform a fluorescent penetrant inspection after each unscheduled in-flight ADG deployment and a visual inspection after each unscheduled on-ground ADG deployment. Instructions regarding re-identification (where applicable) and replacement parts are also included. 

Corrective 

Actions: 

Part I - Identification Check 

Within 400 hours air time or before the next scheduled ADG operational test, whichever comes first, after the effective date of this directive, unless already accomplished and the ADG has not subsequently been replaced: 

Check the part number of the installed ADG: 

A. If the part number of the ADG is 604-90800-23 (Hamilton Sundstrand part number 1711405), the strut wall thickness is within specification. No further action is required and compliance with this directive is complete. 

B. If the part number of the ADG is 604-90800-1, -17 or –19 (Hamilton Sundstrand part number in the 761339 series), check the ADG serial number and proceed as follows: 

1) If the serial number of the ADG is 2000 or higher, the strut wall thickness is within specification and only re-identification is required. Proceed to Part VI of this directive. 

2) If the serial number of the ADG is in the range 0101 through 1999 and the symbol 24-3 is marked in the Serial Number block of the identification plate, the strut wall thickness is 

within specification and only re-identification is required. Proceed to Part VI of this 

directive. 

3) If the serial number of the ADG is in the range 0101 through 1999 and the symbol 24-3 is not marked in the Serial Number block of the identification plate, check the serial 

number of the strut and generator housing assembly (for location, see Figure 1, Sheet 1 of Hamilton Sundstrand Service Bulletin (SB) ERPS10AG-24-3) and proceed as follows: 

a) If the serial number of the strut and generator housing assembly is in the range 0001 through 2503, a fluorescent penetrant inspection is required. Proceed to Part II of this directive. 

b) If the serial number of the strut and generator housing assembly is 2504 or higher, the strut wall thickness is within specification and only re-identification is required. Proceed to Part VI of this directive. 
No.

 N° CF-2009-24 2/3 

Note: Part I may be conducted visually, which requires the ADG to be lowered, or by checking the maintenance records. 

Part II - Initial Fluorescent Penetrant Inspection

Within 400 hours air time or before the next scheduled ADG operational test, whichever comes first, after the effective date of this directive, unless already accomplished: 

Inspect the ADG strut and replace the ADG, as necessary, in accordance with paragraphs 2.A., 2.C. and 2.D. of the Accomplishment Instructions in Bombardier Alert SB 604-24-017, Revision 1, 

dated 15 January 2007, or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada. 

Prior accomplishment of the fluorescent penetrant inspection, conducted in accordance with either 

the above referenced SB or one of the following SBs, also meets the intent of Part II of this 

directive: 

 Bombardier Alert SB 604-24-017 Original issue Dated 6 May 2005 

Hamilton Sundstrand SB ERPS10AG-24-3 Original issue Dated 14 April 2005 

Hamilton Sundstrand SB ERPS10AG-24-3 Revision 1 Dated 19 April 2005 

Hamilton Sundstrand SB ERPS10AG-24-3 Revision 2 Dated 14 November 2006 

Hamilton Sundstrand SB ERPS10AG-24-3 Revision 3 Dated 12 March 2009 

If the ADG is replaced by an ADG with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required and compliance with this directive is complete. 

Notes: 

1. Part II is only applicable if required by Part I, Paragraph B.(3).(a) of this directive. 

2. For aircraft with serial numbers 5611 through 5665, Bombardier conducted the initial 

fluorescent penetrant inspection prior to aircraft delivery. As long as the ADG has not been replaced since aircraft delivery, this meets the intent of Part II of this directive. 

3. In Hamilton Sundstrand SB ERPS10AG-24-3, the fluorescent penetrant inspection is referred to as “Penetrant Check”. 

Part III - Repeat Fluorescent Penetrant Inspections 

Before further flight after each scheduled ADG operational test: 

Inspect the ADG strut and replace the ADG, as necessary, in accordance with paragraphs 2.A., 2.C. and 2.D. of the Accomplishment Instructions in Bombardier Alert SB 604-24-017, Revision 1, 

dated 15 January 2007, or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada. 

If the ADG is replaced by an ADG with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required and compliance with this directive is complete. 

Note: Part III is required for each ADG that has been inspected in accordance with Part II of this directive. 

Part IV - Inspection after an Unscheduled In-Flight ADG Deployment 

A. Before further flight after each unscheduled in-flight ADG deployment: 

 Visually inspect the ADG strut and replace the ADG, as necessary, in accordance with paragraphs 2.A., 2.B. and 2.D. of the Accomplishment Instructions in Bombardier Alert SB-604-

24-017, Revision 1, dated 15 January 2007, or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada. 

 If the ADG is replaced by an ADG with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required and compliance with this directive is complete. 

B. Within 72 hours or 10 hours air-time, whichever comes first, after each unscheduled in-flight ADG deployment: 

 Perform a fluorescent penetrant inspection of the ADG strut and replace the ADG, as necessary, in accordance with paragraphs 2.A., 2.C. and 2.D. of the Accomplishment Instructions in Bombardier Alert SB 604-24-017, Revision 1, dated 15 January 2007, or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada. 

 If the ADG is replaced by an ADG with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required and compliance with this directive is complete.

Notes: 

1. Part IV is required, after an unscheduled in-flight ADG deployment, for each ADG that is specified in Part I, Paragraph B.(3).(a) of this directive. 
No.

 N° CF-2009-24 3/3 

2. The visual inspection specified in Part IV, Paragraph A above is not required if the fluorescent penetrant inspection, specified in Paragraph B, is performed before further flight. Part V - Inspection after an Unscheduled On-Ground ADG Deployment 

Before further flight following each unscheduled on-ground ADG deployment task: 

Visually inspect the ADG strut and replace the ADG, as necessary, in accordance with paragraphs 2.A., 2.B. and 2.D. of the Accomplishment Instructions in Bombardier Alert SB 604-24-017, 

Revision 1, dated 15 January 2007, or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada. 

If the ADG is replaced by an ADG with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required and compliance with this directive is complete. 

Note: Part V is required, after an unscheduled on-ground ADG deployment, for each ADG that is specified in Part I, Paragraph B.(3).(a) of this directive. 

Part VI - Re-Identification 

Within 400 hours air time or before the next scheduled operational test, whichever comes first, after the effective date of this directive: 

Re-identify the ADG in accordance with the Accomplishment Instructions in Bombardier SB-604-24-019, dated 1 October 2007, or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada. 

Re-identification, conducted in accordance with Revision 2, dated 14 September 2007, Revision 3, 

dated 12 February 2008 or Revision 4, dated 30 April 2009 of Hamilton Sundstrand SB-ERPS10AG-24-4, also meets the intent of Part VI of this directive. 

Following re-identification, no further action is required and compliance with this directive is complete. 

Note: Part VI is only applicable if required by Part I, Paragraph B.(1), B.(2) or B.(3).(b) of this directive. The strut wall thickness of the ADGs specified in these paragraphs is not below specification. 

Part VII - Replacement Parts 

As of the effective date of this directive: 

It is not permitted to install a replacement ADG with part number 604-90800-1, -17 or –19 (Hamilton Sundstrand part number in the 761339 series) on any aircraft if the serial number of the 

ADG is in the range 0101 through 1999 strut and the serial number of the generator housing assembly is in the range 0001 through 2503. 

However, it is permitted to install one of the above-specified ADGs back onto the same aircraft if it 

has been removed for non-related purposes, such as for maintenance or to gain access to other 

components, etc. 

Note: The CL-604 Illustrated Parts Catalog also specifies that, for an ADG with a Hamilton Sundstrand part number in the 761339 series, future procurement is to be an ADG with Hamilton Sundstrand part number 1711405. 

Authorization: For Minister of Transport, Infrastructure and Communities 

Derek Ferguson 

Acting Chief, Continuing Airworthiness 

Contact: 

Mr. Richard Topham, Continuing Airworthiness, Ottawa, telephone 613-952-4428, facsimile 613-996-9178 or e-mail richard.topham@tc.gc.ca or any Transport Canada Centre.