### 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) 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 invalidat e 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 Can ada, 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 Communica tions Centre (AARC)

at Place de Ville, Ottawa, Ontario K1A 0N8 , or 1-800-305-2059

, or www.tc.gc.ca/civilaviation/communications/centre/ addr ess.asp

24-0022 (01-2005) 

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### 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 install ed on CL-600-2B16 (CL-604) aircraft. Investigation

determined that the crack was in an area of the strut where the wa ll thickness of the casting was below specification, due to a manuf acturing anomaly in a specific batch of ADGs. Structural failure and departure of the ADG during deployment coul d 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 hydrau lics for the flight controls.

This directive gives instructions to check the par t 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 penet rant inspections of the ADG strut are required.

This directive also gives instructions to per form a fluorescent penetrant inspection after each unscheduled in-flight ADG deployment and a vis ual inspection after each unscheduled on-ground ADG deployment. Instructions regarding re-identif ication (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 directiv e, 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 Sunds trand part number 1711405), the strut wall thickness is within specificati on. 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 (Hamilt on 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-i dentification 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 i dentification plat e, the strut wall thickness is within specification and only re -identification is required. Pr oceed 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 plat e, check the serial number of the strut and generator housing assembly (for loca tion, 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 specific ation and only re-identific ation is required.

Proceed to Part VI of this directive.No.

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### CF-2009-24 2/3

Note: Part I may be conducted visually, which r equires 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 A ccomplishment Instructions in Bombar dier 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 fluor escent penetrant inspec tion, 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 Or iginal 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 (H amilton Sundstrand part number 1711405), no further action is required and comp liance with this directive is complete.

Notes:

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

2. For aircraft with serial numbers 5611 th rough 5665, Bombardier conducted the initial fluorescent penetrant inspection prior to airc raft delivery. As long as the ADG has not been replaced since aircraft delivery, this meets t he intent of Part II of this directive.

3. In Hamilton Sundstrand SB ERPS10AG-24-3, the fluoresc ent 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 A ccomplishment Instructions in Bombar dier 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 (H amilton Sundstrand part number 1711405), no further action is required and comp liance 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 Unsch eduled In-Flight ADG Deployment

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

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

24-017, Revision 1, dated 15 J anuary 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 (H amilton Sundstrand part

number 1711405), no further action is required and comp liance with this directive is complete.

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

Perform a fluorescent penetrant ins pection 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, Conti nuing Airworthiness, Transport Canada.

If the ADG is replaced by an AD G with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required and comp liance 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.

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### CF-2009-24 3/3

2. The visual inspection specified in Part IV, Paragraph A above is not required if the fluorescent penetrant inspec tion, specified in Paragr aph 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 A ccomplishment Instructions in Bombardier Alert SB 604-24-017, Revision 1, dated 15 January 2007, or later re visions approved by the Chief, Continuing Airworthiness, Transport Canada.

If the ADG is replaced by an ADG with part number 604-90800-23 (H amilton Sundstrand part number 1711405), no further action is required and comp liance 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 schedul ed operational test, whichever comes first, after

the effective date of this directive:

Re-identify the ADG in accordance with the A ccomplishment Instructions in Bombardier SB-604-24-019, dated 1 Oct ober 2007, or later revisions appr oved by the Chief, Continuing Airworthiness, Transport Canada.

Re-identification, conduct ed in accordance with Revision 2, dated 14 September 2007, Revision 3, dated 12 February 2008 or Revision 4, dat ed 30 April 2009 of Hamilton Sundstrand SB-ERPS10AG-24-4, also meets the intent of Part VI of this directive.

Following re-identification, no furt her 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 AD Gs specified in these paragraphs is not below specification.

Part VII - Replacement Parts

As of the effective dat e 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 t he serial number of the generator housing assembly is in the range 0001 through 2503.

However, it is permitted to inst all 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, futu re 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 Airworthi ness, Ottawa, telephone 613-952-4428, facsimile

613-996-9178 or e-mail richar d.topham@tc.gc.ca or any Transport Canada Centre.