NO. ••• Transport

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TP 7245E

I

1/3

CF-2009-42R1 L.._-j

Issue Date

14 May 2010

AIRWORTHINESS, DIRECTIVE

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",glSrar~o ."craft ,s conbngent upon COmplla<'lC€w~h all applicable ADs, Failure 10compJy W1!~me requirements 01an Kg" may Invalidate 1M TI;~\ authori,aMn 01the a,rcrafl.

Alf.mau ••••m~.n, oJ "ompl,ance snail !J.e applied for in accoo;lan"" with CAR 605.84 aCId the above".!.",nc""; Standard.

This AD has teen i••,,~d by the Continuing AirwO<1hinessDivision(AAROG),NafionalAircraft ce~c.a~on 8ranch. T,.o'pon Canada. Ortawa, '~Iephon. 613 952-4357.

Number:

Subject:

Effective;

Revision:

Applicability:

Compliance:

Background:

Corrective

Actions:

CF-2009-42R1 I

Hydraulic Accumulators - Screw Cap/End Cap Failure

,

3 June 2010

,

Supersedes Airworthiness Directive (AD) CF-2009-42, dated 16 November 2009.

Bombardier Inc. Models:

Cl-215-1A10 (Cl-215) -Serial Numbers 10011throU9h 1990

Cl-215-6811 (Cl-215T)- Serial Numbers 1056 through 1125

Cl-215-6811 (CL-415) - Serial Numbers 2001 through 2990

As indicated below, unless already aceomplishe,d.

Seven cases of ,on-ground hydraulic accumulator screw cap or end cap failure have been

experienced on Cl-600-2B 19 (CRJ) aircraft, resulting in loss of the associated hydraulic system and

high-energy impact damage to adjacent systemls and structure. To date, the lowest number of flight

cycles accumulated at the time of failure has bebn 6991.

Although there have been no failures to date on any CL-215-1A10 (CL-215) or CL-215"6B11

(CL-215T and CL-415) aircraft, similar accumulators, Part Number (PIN) 08-8423-010 (MS28700-

3), to those installed on the CL-600-2819, arh installed on the aircraft listed in the Applicability

section of this directive.

A detailed analysis of the systems and structure in the potential line of trajectory of a failed screw

caplend cap for each accumulator has bee~ conducted. It has identified that the worst-case

scenarios would be impact damage to various components, potentially resulting in fuel spillage,

uncommanded flap movement, or loss of aileron control.

This directive mandates repetitive inspections :of the accumulators for cracks and replacement of

any accumulator in which a crack is detected.

This revision clarifies the text of the directive, iny1uding the PIN of the affected accumulators,

Part I: Records Check

Within 50 hours air time after the effectiye date of the original issue of this directive

(26 November 2009):

Determine and record the number of flight cycles accumulated by each of the accumulators, PIN

08-8423-010 (MS28700-3). installed on the airCraft [i.e. accumulators for the brake (CL-215-1A10

and CL-215-6811), aileron (CL215-6B11). elevator (CL215-6811) and rudder (CL215--6811)j.

Proceed to Part II of this directive.

Part II: Initial Ultrasonic Inspection

A. Inspection Schedule: CL·215-1A 10 (CL-215) and CL-215--68 11 (CL-215T)

Canada

1) For each accumulator, PIN 08-8423-010 (MS28700-3), with more than 875 flight cycles,

inspect the accumulator within 125 f1jg~tcycles after the effective date of the original issue

of this directive (26 November 2009)i, in accordance with Part II. Paragraph C of this

,

PufSuonlto CAR 202,~' the registered owner 01a Canadian airmfi shall. within so""o da~, notjli ithe Mini.tor

In writing 01MycMnge of his or hor name c>raddress I

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I

No. ~.CF·2009-42R1

2)

3)

directive.

For each accumulator, PIN 08-8423l010 (MS28700-3), with 875 or less flight cycles,

Inspect the accumulator before it has ,accumulated 1000 night cycles, in accordance wilh

Part II, Paragraph C of this directive. I

If it is nol possible to determine the flight cycles accumulated for an accumulator, PIN 08-

8423-010 (MS28700-3), inspect the adcumulator within 125 flight cycles after the effective

of the original issue of this directive (26 November 2009). in accordance with Part II,

Paragraph C of this directive.

S, Inspection Schedule: CL-215-6B11 (CL-415)

I

1) For each accumulator, PIN 08-8423-0~O (MS28700-3), with more than 750 flight cycles,

inspect the accumulator within 250 flight cycles after the effective date of the original issue

of this directive (26 November 2009)! in accordance with Part 11,Paragraph C of this

directive. I

2) For each accumulator, PIN 08-8423-910 (MS28700-3), with 750 or less flight cycles,

inspect the accumulator before it has accumulated 1000 flight cycles, in accordance with

Part II, Paragraph C of this directive. I

3) If it is not possible to detennine thle Might cycles accumulated for an accumulator,

PIN 08-8423-010 (MS28700-3), inspect the accumulator within 250 flight cycles after the

effective date of the original issue of this directive (26 November 2009), in accordance with

Part II, Paragraph C of this directive. I

C, Inspection Procedure

Inspect each accumulator, PIN 08-8423-010 I(MS28700-3), in accordance with Part B of the

Accomplishment Instructions in the applicable S6 listed below, or later revisions approved by the

Chief, Continuing Airworthiness, Transport Can~da.

Model Service Bulletin Date

CL-21S-1A10 (CL-215) S!3 215 541, Revision 1 12 March 2010

CL-215-6611 (CL-215T) S!3 215-3155, Revision 1 12 March 2010

CL-21S-6611 (CL-415) S8 215--4414, Revision 1 12 March 2010

Note: Inspection in accordance with Part B of t~e Accomplishment Instructions in the original issue

of S8 215-541, SB 215-3155 or S8 215- 4414 (all dated 9 July 2009), as applicable, also

meets the intent of Part II of this directivej

1)

2)

If there is no indication of a crack, proci:ed to Part III of this directive for subsequent repeat

ultrasonic inspection requirements. I

If there is an indication of a crack, repla'ce the accumulator before further flight. Inspect the

replacement accumulator in accorda~ce with Part n and Part III of this directive, as

applicable. I

Part III: Repeat Ultrasonic Inspections

For each accumulator, PIN 08-8423-010 (MS'2870D-3), in which no crack has been previously

detected, ultrasonically re-inspect the accum~lator within 750 flight cycles after each previous

ultrasonic inspection, in accordance with Part 8 of the Accomplishment Instructions in the

applicable S8 listed below, or later revisions I approved by the Chief, Continuing Airworthiness,

Transport Canada.

Model I Service Bulletin Date

CL-215-1A 10 (CL-215) S~ 215541, Revision 1 12 March 2010

CL-215-6B11 (CL-215T) S!3 215-3155, Revision 1 12 March 2010

CL-215-fiB11 (CL-415) S8 215-1414, Revision 1 12 March 2010 ,

I

Note: Inspection in accordance with Part B of the Accomplishment Instructions in the original issue

of 58 215-541, S8 215-3155 or S8 215- 4414 (all dated 9 July 2009), as applicable, also
I ~~. CF·2009·42R1

Authorization:

Contact:

meets the intent of Part III of this directive.

1) If there is no indication of a crack, proq:!ed to Part III of this directive for subsequent repeat

ultrasonic inspection requirements.

2) If there is an indication of a crack, replace the accumulator before further flight. Inspect the

replacement accumulator in accordante with Part II and Part III of this directive, as

appiicable I

For Minister of Transport, Infrastructure and Coh,munities

I

OR1GIN;\L STGNED BY

Derek Ferguson

Chief, Continuing Airworthiness

Mr. Richard Topham, Continuing Ailworthin1ess, Ottawa, telephone 613-952-4357, facsimile

613-996-9178 or e-mail CA\lVlJVEBFeedback@tt.9C.ca or any Transport Canada Centre

I