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### CF-2009·27 TP 7245E 

### 1/4 

# AIRWORTHINESS Issue Dale 

### 08June 

### 2009 

# DIRECTIVE

Number: Subject: Effective: Applicability:

Compliance: Background:

Corrective Actions: CF-2009-27

Air Driven Generator (ADG)
- Strut Cracking 29 June 2009 Bombardier Inc. Models: CL,600-2B19, Serial Numbers 7305 through 8051. CL-600-2C10, Serial Numbers 10003 through 10260. CL-500-2D15 and CL-600-2D24. Serial Numbers 15001 through 15106. As indicated below, unless already accomplished. Two cases of a crack on a~dry"ADG (Hamilton Sundslrand part number inthe 761339 series), in the aft area of the strut and generator housing assembly, have been reported on CL-600-2819 aircraft. The same part isalso installed on CL-6OQ-2C10.-2015 and -2D24 aircraft Investigation determined that the crack was in an area of the strut where the wall thickness of the casting was below specification, due toamanufacturing anomaly in aspecific batch ofADGs, Structural failure and departure of the ADG during deployment could possibly resuit in damage to the aircraft structure. If deployment was activated by a dual engine shutdown, ADG structural failure would also result inloss ofhydraulics fortheflight controls. This directive gives instructions to check the part number ofthe installed ADG and, forADGs with a part number in the 761339 series, the serial numbers of the ADG and strut and generator housing assembly are also to be checked_Ifthese serial numbers arewithin specified ranges [see Part I, paragraph R(3).(a) below], a one-time fluorescent penetrant inspection of the ADG strut is required. Note: For ADGs with serial numbers in the above-referenced specified ranges, subsequent fluorescent penetrant inspections are required after each scheduled in-night or on-ground functional check of the ADG and also after each unscheduled in-flight ADG deployment. These inspection requirements are not mandated in this directive but are specified in the approved maintenance program,
Part I - Identification Check Within 1000 hours air lime or before the nextscheduled ADG funclional check. whichever comes first, after the effective date of Ihisdirective: Checkthe part number ofthe installed ADG: A. Ifthe ADG has Hamilton Sundstrand part number 1711405, the strut wall thickness is within specification. Nofurther action is required and compliance with thisdirective iscompiete_ B_ Ifthe ADG hasaHamilton Sundstrand part number inthe 761339 series, check theADG serial number and proceed asfoliows: 1) If the serial number of the ADG is 2000 or higher, the strut wall thickness is within specification, Nofurther action is required and compliance with this directive iscomplete_

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### CF·2009-27 N' 2) Ifthe serial number of the ADG is in the range 0101 through 1999 and symbol 24-3 is marked in the Serial Number block of the identification plale, the strut walilhickness is within specification. No further action is required and compliance with this directive is complete. 3) Ifthe serial number ofthe ADG is inthe range 0101 through 1999and symbol 24-3 is not marked in the Serial Number block of the identification plate, check the serial number of thestrut and generator housing assembly (for location, see Figure 1,Sheet 1 of Hamilton Sundstrand Service Bulletin (58) ERP510AG-24-3) and proceed asfollows: (a) Ifthe serial number of the strut and generator housing assembly is inthe range 0001 through 2503, afluorescent penetrant inspection is required_Proceed to Part IIofthis directive. (b) Iftheserial number ofthe strut and generator housing assembly is2504 orhigher, the strut wall thickness is within specification. No further actlon is required and compliance with thisdirective iscomplete. 

# I 4) If the serial number of the strut and generator housing assembly is not checked, fluorescent penetrant inspection is required. Proceed to Part IIofthis directive NOle: Part I may be conducted visually, which requires the ADG to be lowered, or bychecking the maintenance records. Part It- Fluorescent Penetrant Inspection A. Applicable toCL-600-2B19 Aircraft, Serial Numbers 7305 through 8051: Within 1000 hours air time or before the next scheduled ADG functional check, whichever comes first. afterthe effective date ofthisdirective: Inspect the ADG strut, and replace the ADG as necessary, in accordance with the Accomplishment Instructions in Bombardier Alert Service Bulletin (ASB) A601R-24-120, Revision C, dated 20 April 2009, 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 S8 orone of thefollowing SBs, also meets the intent of Part II01 thisdirective: Bombardier Alert SB Original issue Dated 20April 2005 A601 R·24·120 Bombardier Alert SB Revision A Dated 1 December 2005 A601 R-24·120 Bombardier Alert SB Revision 8 Dated 7 December 2006 A601R·24·120 Hamilton Sundslrand 58 Original issue Dated 14April 2005 ERPS10AG-24-3 Hamilton Sundslrand 58 Revision 1 Dated 19April 2005 ERPS10AG·24-3 Hamilton Sundstrand 58 Revision 2 Dated 14November 2006 ERPS10AG·24-3 Hamilton Sundstrand SB Revision 3 Dated 12 March 2009 ERPS10AG-24-3 Following completion of Part II, nofurther action is required and compliance with this directive iscomplete. Notes: 1. Part II is only applicable If required by Part I, Paragraph B.(3).(a}, or by Part I,

Paragraph 8.(4) ofthisdirective. 2. For ADGs specified in Part I, Paragraph 8.(3).(a), repeat lIuorescent penetrant inspections (per Hamilton Sundstrand S8 ERPS1OAG-24-3) are required as part of the periodic AOG Functional Check procedure. RefertoAirworthiness Requirements, Part 2 of Maintenance Requirements Manual, Appendix A - Certification Maintenance Requirements (CMR) and theAircraft Maintenance

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### CF·2009·27 N°
Manual (AMM), asfollows: CMR Task No. C24-20-129-01. AMM Task No: 24-23-01-720-803. 3. For ADGs specified in Part I, Paragraph B.(3}.(a), fluorescenl penetrant inspectionj (per Hamilton Sundslrand 58 ERPS10AG-24-3) is required following each future unscheduled in-flight ADG deployment, as specified in the following task: AMM Task No: 05-51-19-210-801. 4, In Hamilton Sundslrand 58 ERPS10AG-24-3, the fluorescent penetrant inspection is referred 10as a ~Penetrant Check",
B. Applicable to CL-60Q.-2Cl0 Aircraft, Serial Numbers 10003lhrough 10260, and CL-600-2D15 and Cl-600-2D24 Aircraft, Serial Numbers 15001 through 15106: Within 1000 hours air time or before the next scheduled ADG functional check, whidlever comes first, afterthe effeclive dale ofthisdirective: Inspect the ADG strut, and replace the AOG as necessary. in accordance with the Accomplishment Instructions in Bombardier ASS A670SA-24-020, Revision C, dated 20 April 2009, orlater revisions approved bythe Chief, Continuing Airworthiness, Transport Canada. Prioraccomplishment ofthe fluorescent penetrant inspection, conducted inaccordance with either the above referenced S8 or one of the following SSs, also meets the intent of Part II of this directive: Bombardier Alert 5B Original issue 

# I Dated 20April 2005 A670BA-24-o20 Bombardier Alert SB Revision A Dated 17 May 2005 A670BA-24.(J20 Bombardier Alert SB Revision B Dated 7 December 2006 A670BA-24-o20 Hamilton Sundstrand Original issue Dated 14April 2005 58 ERPS10AG·24·3 Hamilton Sundstrand Revision 1 Dated 19April 2005 58 ERPS10AG·24-3 Hamilton Sundstrand Revision 2 Dated 14November 2006 58 ERPS10AG·24-3 Hamilton Sundstrand Revision 3 Dated 12March 2009 S6 ERPS10AG·24·3 Following completion of Part II, 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 8.(3).(a), and Part I,

Paragraph 8.(4) ofthisdirective. 2_ For ADGs specified in Part J, Paragraph 8.(3)_(a), repeat fluorescent penetrant inspections (per Hamilton Sundstrand 58 ERPS10AG-24-3) are required as part of the periodic ADG Functional Check procedure. RefertoAirworthiness Requirements, Part 2 of Maintenance Requirements Manual, Appendix A - Certification Maintenance Requirements (CMR) and the Aircraft Maintenance Manual (AMM), as follows:

-CMR Task No. 24-23-00-102.

-AMM Task No: 24-23-01-720-802. 3. For ADGs specified in Part I, Paragraph 8.(3).(a), fluorescent penetrant inspection (per Hamilton Sundslrand SB ERPS10AG-24-3) is required following each future unscheduled in-flight ADG deployment, as specified in

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### CF·2009·27 

# ,. thefollowing task:

-AMM Task No: 05-51-19-210-801.

Authorization: 4. In Hamilton Sundstrand S8 ERPStOAG-24-3, the fluorescent penetrant inspection is referred toas a"Penetrant Check".
ForMinister ofTransport, Infrastructure and Communities

Derek Ferguson Acting Chief, Continuing Airworthiness Contact: Mr. Richard Topham, Continuing Airworthiness, Ottawa, telephone 613-952-4428,

613-996-9178 ore-mail richard.lopham@tc.gc.caoranyTransport Canada Centre. 

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