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~--IP I PRDNCI~ I QACln¥7 {Q~

Date Serial No. S.0 .WCmt..l Tr~dc AT~ Work Order,/ 04/10/20 I 5 554 R18 80285

Task Card I Check# RD 8-53-2959

Required Action

COMPLY WITH RD 8-53-2959 - INSPECT CLOSING ANGLES BETWEEN 3LH AND 3RH

Parts Rcqui,tion Numhcrs:

I Continuation Sheet Control Numbers:

Rectification: CD (1' p L,\ ED

fi~6,tcS

Tools Used:

Tool Description:

Qty Description

Parts C0ntirmation Sheets

Ops Cheek Transferred Tc Work Card 1'0.

Date:

Number of Discrepancies:

Form 408 Orieinal: I March 2006

c, ID Numher:

Cal Due:

I

Tool Description: ID Numher:

Cal Due:

PARTS USED Po; P,1' Off: PiN On:

Leak Check Tran,ferrcd To Work Card No.

Date:

Work Card Numbers:

Tool Description:

SIN Off

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2149

I Budget

I RII Required: Write Yes or No No

ID Numbc,r:

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SIN On Batch No

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· ... . r--------.--...-------------------..--~....,,,,.,--~--RD 8-53-2959 PREPARED G.G.

CHECKED

DATE Jul-99

BOMBARDIER ~ AEROSPACE ,._,-

SECT 1

PAGE 1 . . ., . . .... :tJlJ\ -; . .

. I : :

ISSUE .f' ~ $~ (} 7

. ? ; The following RD allows continued operation with cracks detected on the wing spar to fuselage roof skin angles 85300011-111/112, and 85300016-117/121 LH and RH sides. Cracks must be outboard of stringer 3. Cracks are allowed on any or all of the four angles (FIS Stbd, Port, R/S Stbd, and Port). Seal as required with PR1422-B2 or equivalent in accordance with the instructions of the DASH 8 structural repair manual PSM 1-83-3 chaprer 51-30-26.

•M.,, ~- "'tll

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For continued flight with cracked closing angles, the front and rear spar angles between stringers 3 LH and 3 RH mu.st be inspected and be era.ck free using a detailed visual inspection. Tbe center angles must be ~ inspected at every "C" Check or every 10000 Fligb~ which ever-1 is less. No Cncb Pennltted on center anglest~ll-113, and 8530001~119). @

Vfo..._.r_l'(.er-top~l"f 1'~1011g7 For oontiaued 1, tbe RH and LIi dished akin to~g lower skin fastenen must be replaced, and additional straps installed as per pages ~. and 6. The fastenen and straps may be imtaOed bdore crw:lo are detected to avoid unacheduled down 1ime. The fastener replacement and additional straps SE E do not end the requirement for the above center ncle impectious. P1 1l3 r-o 2 AJI outb'd an mcludin uncracked an es must be laced on er before 40000 flights.

Pt1..-TG "'~ After the outb'd angles are replaced, all angles must be inspected as per maintenance task 5310/3 lA SC-l+E ULE. If further cracks are found on the outb'd angles, continued opention is allowed for an additional 40000

flights from the time of angle replacement The front and rear spar angles between stringers 3 U{ and 3 RH must be inspected and be crack free using detailed visual inspection. Hthe outb'd angles are cracked, the center andes must be ~pected at every "C" Check or every 10000 ftlgha which ever is lea. No Cracks Permitted on center angles (M.100011-113, and 85300016-119).

The details of this poredure are covered by RD 8-53-29S9 section 1. page 1 issue%jL,)'l(f-'t>1ge 4 issue l P•Je I" ,.s~'-'£

, ~ page 2 issue 1 page 5 issue...Y~ r·~ e I l\ 's.JtJE{ 't ,<', ~ AT issuf z : ,.~ I, s- ~A 1sEb ,o ,ssvE 2.. page 3 issue 1 page 6 issue.r.t JJ cl g ~ Sf~IIP 1'10T)1,:'/tl> i::o~ C..LE ,ll#-1 ANC£ A-r ,ssvE ! : r.! I il:A1SO ro IU\JE 3, f'j ,. • e ~ ""' TO avf:~\-\~D 61N 8~ETS, CLEt•cAL CHA..,,e · TO 1....>JPa..,.., ,..., pr;1t.1oD <t _j i't'A:l €RRd loRRfG1'EC . ...L IIJ " ~ ... RD __ 1ss_u_E ____ 1 _____ 2... _____ I--->, __ ~..._ Title: Temporary Continued Operation ~ -~ . ~ DA TE 26-Jul-99 with Cracks on the Wing Spar ~, N DRAWN to Fmelage Roof Angles ~ -~ APPROVED Series 300 Model 311/314/315 .....

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REPORT NUMBER APPLICABil)TY

DHC-8 SERIES300 .

RD8-S3-29S9 Model 311/314/315

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RD 8-53-2959 SECT

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BOMBARDIER SECT 1 CHECKED PAGE 18 DATE Apr '05 ISSUE 2

Alternate Procedure For Cracked Angle Replacement Schedule

As detailed on Page 1, the requirement for continued flight with known cracking in the outer closing angles, is that after 40,000 flights ALL outer angles (including any remaining uncracked angles) are to be replaced. The aircraft may then return to service with no added inspection requirements or restrictions. If further cracking is found, RDS-53-2959 may be invoked again on the "new" angles to continue flight with up to all 4 new outer angles cracked for 40,000 flights.

An alternate procedure may also be followed, as given below:

.Alternate Procedure

A) At time of detected cracking in the outer angle (or angles) RDS-53-2959 is invoked to permit continued operation. After a maximum of 40,000 flights of continued operation, only the cracked angles are replaced. Any remaining uncracked outer angles may be left in place.

B) However, at return to service for this aircraft, the outer angles must now be subjected to a continued repetitive detailed visual inspection for cracks. This inspection interval is 10,035 Flights or at next 'C' check, whichever comes first.

0 C) An aircraft in operation in accordance with this alternate procedure may subsequently have new cracking found in any one of the 4 outer angles (but not the centre angles) and continue in operation for a maximum of 40,000 flights with the angle cracked (from the time of the detection of this new cracking). The repetitive flight inspection as noted in B) must be continued. However, if cracking occurs in more than one outer angle, then all cracked angles must be replaced within 5,500 flight hours (of discovery of multi angle cracking) or at next "C" check, whichever comes first.

D) At replacement of angles per C), the procedure starts over at B) again.

NOTE: No cracking of centre angles is permitted.

0 At issue 2: changed inspection intervals in note B) to 10,o35 Flights, (was 5'.500 flight hours)

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AEROSPACE W PAGE 6 DATEJul-99

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Fastener Codes. HST12-8 HiLite fasteners at existing locations. Hole Dia . . 2455"/.2475" HST1087-8 collars -preferred fastener or HL12V-8 Hi-Lok fasteners at existing locations. Hole Dia .. 2460"/.2480" HL86-8 collars + Reference only.

General notes:

1. Fabricate the repair strap from 0.190" 7075 clad T6 (QQ-A-250/13) material. c:.. Machine outside profile to match existing strap. Form to required contour. '6,'0~ 1.Jn-~ r..-L ~TltAPS P,rJ "'S?IU,{.gO . 2. All new parts arc to be finished with alodine and epoxy primer.

3. Maintain a minimum of two times the fastener diameter edge distance, unless otherwise specified. The edge distance is measured from the center of the fastener hole to the edge of the material and must be maintained on all material through which the fastener passes.

4. Fayseal all mating surfaces with Pro-Seal 870C sealant or equivalent in accordance with DASH-8 structural repair manual PSM 1-83-3 chapter 51-30-26. This sealant is procured to OHMS S3 .06 Type 1 Class C-80.

5. If the aircraft is equipped with long range fuel tanks, install all fasteners wet with Pro­Seal 870C sealant or equivalent in accordance with DASH-8 structural repair manual PSM 1-83-3 chapter 51-30-26. Dome seal the internal collars with PR1422-B2 or equivalent in accordance with the instructions of the DASH 8 structural repair manual PSM 1-83-3 chapter 51-30-26.

I • I•

... ....,. _ , ......... -·- -- -·· .. .. . - ·-·-·· .. · ···--·-- .... -­.-----······----- ------·

AVMAX NON-ROUTil\E WORK CARD l)atc : Serial No.

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Parts Requisition Numbers:

commended Action:

Continuation Sheet Numbers:

Rectification:

Par,s Continuntion Sheets

Ops Check Transfe rred To Work Card No.

FORM ,1119 l 1S l{F \ '_ t

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s/-,v, Estimntcd Hrs & Customer Approval

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Po; PIN Off:

Leak Check Transferrc~I To Work Card No.

Date:

((\!' \' (WHITE) - CUSTOM El{ COl' Y

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PIN On:

Budget I lrs & Customer Approval

To.11 Description:

SIN Off

Panel Closure Transferred To Work Canl No.

Rll Sign Off

Date:

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Work Card II

ID !\umber

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S/N On Batch l'<o.

SDR Required YesO

l

.A-WofltCard ro.tatg1w~ OASHS 200/300 SERIES MPM - Appendix A

MAINTENANCE TASK WORK CARD 9

04/01/11 TA/1.f

N

General

FM regulations require aircraft damage, repairs, alterations and/or modifications have Damage Tolerance Evaluations (DTE). DTE may result in Damage Tolerance Instructions (DTI) with Instructions for Continued Airworthiness (ICA). Procedures given here ensure that DTE is/has been performed and DTI for ICA, if required, be performed when required. DTE must be by an FM acceptable source (i.e. DAH (Design Approval Holder), DER (Designated Engineering Representatives), etc.). DTI for ICA is normally found in but not limited to DAH RO's (Repair Drawing), OAH SDIR's (In-Service Deviation Inspection Requirements), DAH PDIR's (Production Deviation Inspection Requirements), DER EA's (Engineering Authorization), STC's (Supplemental Type Certificate) and/or CA-72 FCD's (Fleet Campaign Directive).

Reference Material: Bombardier Service Letters DHB-SL-51-008 and DHS-SL-51-007 A

FAR parts 121.1109 and 129.109 (c) (2)

Instructions

Individual damage, repairs, alterations and/or modification must have the following instructions completed each time to ensure continuing compliance with the Aging Aircraft Safety Rule (AASR) (FAR parts 121 .1109 and 129.109 (c) (2)).

PROCEDURE$ FOR ENSURING DTE IS Pl:RFORMEO

1. Record damage, alteration, modification or existing repair, alteration or modification to have DTE in Figure 1 at the end of this work card. Provide as much of the information requested as possible, if this document goes to an FM accepted source for DTE it will be needed. Special attention should be given describing any damage, alteration, modification or existing repair, alteration or modification that may affect the following :

A. Any aspect of the Electrical Wiring Interconnection System.

B. Introduce additional potential hazards in the form of design features that could favor electrical arcing when a lightning strike is experienced, attention should be paid to proper fit and sealing of parts and fasteners that are within or penetrate any fuel tank.

NOTE: Any removable component with damage, alteration, modification or existing repair, alterstlon or modification that result in DTI with /CA Is to be tracked against the component

PAGE 1 OF 8

DASH8 200/300 SERIES MPM - Appendix A

MAINTENANCE TASK WORK CARD

PROCEDURES FO . ENS RING DTE IS PERFORMED

2. Review currently published repairs (SRM and RD's), SB's, AD's, STC's and/or company generated modifications (FCD's) in an attempt to obtain an FAA acceptable publication. A. If no existing publication(s) can be obtained proceed to Step 3.

-OR-If existing publication(s) is obtained reference shall be made in corresponding CA-49 corrective action to the publication obtained.

1) If existing publication(s) is obtained check for DTI with ICA. -OR-If existing publication is obtained and no documentation of DTE for DTI with ICA exists;

a. Obtain proof from publication holder DTE was performed and no DTI with ICA is required. - OR-

If publication holder cannot provide DTE for DTI with ICA, provide proof DTE was performed resulting in no DTI with ICA or cannot be contacted, proceed to step 3.

2) Document ICA if given in "Follow Up Maintenance Required" space provided on CA-49. 3) DTE is complete

a. If damage is found acceptable or after damage is repaired or alteration/modification is complete discrepancy generated on CA-49 shall be signed off. -OR-

For MPM TASKs 0500/Q02 or 0500/003 return to MTC050002 listing being wori<ed, initial DTE column and record reference number (i.e. RD/EA number, SRM chapter, SB, AD, STC. etc.). CA-49 discrepancy may be signed off.

PAGE 20F 8

9

OASH8 200/300 SERIES MPM - Appendix A

MAINTENANCE TASK WORK CARD

3. If existing publication DTE was not established Q[ there is no existing publication(s) ~ further fllaht submit a copy of Figure 1 of this MTC for damage, alteration, modification or existing repair, alteration or modification to an FAA acceptable source (i.e. DAH, DER, etc.). SRM chapter 51-13-01 gives definitive procedures to follow for damaae reporting. Pictures with markings to indicate location and dimensions of damage or existing repair, alteration or modification are also highly recommended as they are normally requested. NOTE: Review paperworlc provided from source for proof required below, It must be provided

In order for repair to be considered airworthy and damage tolerant. These documents are but not limited to a DAH RD or DER EA.

A. Obtain repair that is airworthy and damage tolerant. -OR-Obtain proof that damage or existing repair, alteration or modification is airworthy and damage tolerant. -OR-If existing repair, alteration or modification is determined not to be airworthy and/or damage tolerant request one that is and rework as required. NOTE: Only an FAA acceptable source (I.e. DAH, DER, etc.) may determine ff a repair Is

airworthy and damage tolerant or H repair Is not and must be reworlced. 1) Obtain proof DTE is complete and DTI with ICA was provided.

-OR-Obtain proof DTE is deferred (1 yr max) and DTI are to be determined. -OR-Obtain proof DTE is complete and there is no DTI with ICA. NOTE: Bombardier provided RD's the DAH for the DHC-8 Serles 200 airers~ wfll specify

DTf with #CA and provide an SDIR document. If !H21 s~fflfd/provlded there Is no DTI with ICA.

4. After proof has been obtained that damage, repair, alteration, modification or existing repair, alteration or modification is airworthy and damage tolerant and DTE is complete or deferred document in corresponding CA-49 corrective action. A. Document ICA if given in "Follow Up Maintenance Required" space provided on CA-49. B. DTE is complete

1) If damage is found acceptable or after damage is repaired or alteration/modification is complete discrepancy generated on CA-49 shall be signed off. -OR-For MPM TASKs 0500/002 or 0500/003 return to MTC050002 listing being worked, initial DTE column and record reference number (i.e. RD/EA number, SRM chapter, SB, AD, STC. etc.). CA-49 discrepancy may be signed off.

5. Generate Form CA-1 indicating that a Revision to the maintenance program may be required for tracking and performing of ICA if ICA was determined, otherwise mark NIA.

PAGE 3OF 8

9

I

I

DASH8 200/300 SERIES MPM -Appendix A

MAINTENANCE TASK WORK CARD

5. For records use only - Verify damage/repair/alteration/modification is added to records for aircraft.

6. For records use only - Verify damage is reported as required by Section 1 and Section 9 of the MPM. Check applicable box and forward copies of all relevant information to Quality Assurance Department for reporting as instructed. Review damage reporting checklist to obtain necessary information.

0 Fatigue damage classified as a major repair per GMM Section 3 paragraph H (repair, alteration, modification) - BARA quarterly.

0 Level 1 Corrosion - BARA quarterly- FAA not required

D Level 2 Corrosion - BARA within 30 days - FAA not required (must implement FAA acceptable means to reduce to Level 1 or better 'Mthin 60 days)

D Level 3 Corrosion - BARA within 14 days - FAA within 3 days (Within 10 day submit plan to check remainder of fleet for similar corrosion or substantiating data it is isolated caae. Must implement FAA acceptable means to reduce to Level 1 or better within 60 da )

7. For records use only -Assign SDIR number if required, use following example to format. Use RD number for Bombardier generated repairs.

8-53-XXXX

8 - is to indicate Dash 8 aircraft

53 - is to indicate associated ATA

XXXX - are numbers referencing back to EA or equivalent.

8. For records use only - Generate Form CA-9 if needed to add tracking of any ICA to work due listing for aircraft.

PAGE 4 OF 8

DASHS 200/300 SERIES MPM - Appendix A

MAINTENANCE TASK WORK CARD 9

DAMAGE REPORTING CHECKLIST

REFERENCE NO. (PO•)

TYPE OF REPAIR REQUESTED: PERMANENT 0 TEMPORARY ~ IF TEMPORARY, MNIMUM TIME DATE REQUIRED BY: {l), 601> ~L "'{ t\\2->

I REQUESTED: (i,o, Next L Ched<, A""'C.,+:,'-f,f~;a:-;-J.a..~--. etc.)

N 'l/b7C(} DATE: y;~~j I AIRCRAFT TYPE: Q!:i.i. SERIES: D 200 N· 300 (ReglstratlOn runDor) e,,: I j e;j ; 7 ~ OPERATOR: CommutAir AJC SIN: ->..n T.A.T.: Z8l/Dl, , (HRS) T.A.C.: 3)1 (CYC)

CONTACT PERSON(S) (give cell phone number u direct contact below or extension): a~ ::"J7 5 ~ 4 Sica • )p1g19commut.alr.com; rradllwlec9Commutalr.com; mpeck9Commutalr.com to receive • nal drafta.

TELEPHONE NUMBERS REGULAR HOURS:

AFTER HOURS:

216-898-0909 press 9 for Hangar

216-898-0909 press 9 for Hangar

FAX NUMBER: 216-898--0966

Direct contact: ff\\ L \\~)\{; £~

Evaluatlon Is for: D Damage• ~epair D Alteration D Modification D associated with AASR ins.:f.ion 0500/Q02 or 0500/Q03 • Corroeion Is conlidered -,v1ronmeo111 damage Pre-Exl1tlng: D Yes /\ No

MAJOR ASSEMBLY: JlFuselage D Wing/Flaps D Nacelles D Empennage MAJOR SUB-ZONE: 2,00 stat1orJ, 387, 3 S-: Stringers: cJn 1,L. ~/'and OIB 31\ other. ___________________ ________________ _ (Othef is provided to document part numbers or assemblies such as but not Hmited to ailerons, elevators, stabMizers, etc. indicate positions i.e. left or right. Provide SIN if data plate has one.)

Damage la con1ldered: 0 Environmental O Accidental 11\._Fatigve Provide pictures of damage, repair, alteration or modification whenever practical, if plcturn are utilized they shall be Included with CA-49 that documents the damage. Label fulelage/1tructure1 with Information below In greaae pencil !2! provide Information In apacn below 2! UH any other mNM acceptable to an FAA accepted aource perfonnlng DTE. Reference GMM Section 3 paragraph H (repair, alteration and modification) to determine If 1ource performing DTE la FAA acceptable.

Give dl11anc:e to a,ry other damage, repelr, alteration or modification and brief description If found ~• mark NIA:

AJ )'1

FIGURE 1 (sheet 1 of 2)

PAGE 5 OF 8

I

..

DASH8 200/300 SERIES MPM - Appendix A

MAINTENANCE TASK WORK CARD Revision: 9

DAMAGE REPORTING CHECKLIST

•r~" ,mUkDl~~ Damage qpe: ~Crack D Crease D Dent D Scratch D Corrosion• D Chafe D Contamination . ¥ ·---~--, ... - .LU¥ Length: ,, , . Width: 7,o I Max Depth: N \~ Remaining original material thicknna: Original ma al type (If known): 70 7~ Tb .J qji f• Edge distance to fastaners, wlndowa, door frame, skin joint, ate.: Al-6tJ ~ ~tvrr l, 1.,)t

Damage to undertying structure: iloNB (Lill if it.911 ~le~.- . bon<*! alruaur•. dlobondino, • le. p~ pict.,,-90 when•-~I)

Other damaga/repalr/alteratlonlmodlficatlon In area: >Jotd.i (PIO\lldt pielul'9s ~ piadical)

N)~ Matartale available for repair: t:>~f 10 ~~ S~Clt(:1.-et:> ~~

Check box if applicable: D Fatigue damage dassified major repair per GMM Section 3 paragraph H (repair, alteration, modification)

~J2BBOSION Classification: D Level 1 0 Le11el2 0 Level 3 (reference MPM section 1 for definitions and detennination)

Extent of Corr09ion: Indicate length, width and max depth under space provided in METAL STRUCTURES above

Further explanation of Corrosion If nNdad:

'-OIIIPOS(~ l,TRUCTUREI, ' Damage type: D Scratch/Chafe D Crack D Tear D Puncture D Delaminating D 0t11er:

Extent of damage: Dimensions Depth Plies damaged: (19nglh and 'Mdttl)

For Scratch/Chafe: Material lost Damage to honeycomb core: (gi.,. leoglll and gr-It depth) ~-· · O'U!lled, punc:11.ftd)

Contamination type: 0 Moisture D Skydrol D Chemical Solvents D Other:

Edge distance to fasteners, windows, door frame, skin Joint, etc.: ...

Damage to u~rtylng atructura: (Lill~.,.,_ la dll~ to stringn, trwnes, bonded,~. Oiobonding , etc. plOllicle p1cturea--practical)

Other damage/repalr/11teration/modl1lcation In araa: (Pnwid• piaurea w!l-- p<actlcal)

CommutAlt has trained end qualified personnel to perform repairs and currently hH capabfflty to do vacuum begging.

Other capabllltlaa/materlals available:

FIGURE 1 (sheet 2 of 2)

PAGE60F 8

DASH8 200/300 SERIES MPM - Appendix A

MAINTENANCE TASK WORK CARD 9

DASH 8 STRUCTURAL REPAIR This page is to be completed aQd added to Section 2.1, Table 2,1 of the Structural Deviation Inspection Requirements (SOIA) document when a repair from this SAM (53-30-21) has been done on the aircraft, (Reference Document $DIR a-Aircraft Serial Number), Record an Information In the spaces provided below.

1 A/C Serial Number : s~ q AIC Model Number = 31, Repair Number : it>g-53-ptst'-, (This number Is to be incremented sequentially every

time the same repair has been used on the Aircraft but In different areas)

Date of Repair Incorporation : r, I frJ @~ ) 11) ~ r~ I (Day/Month/Year)

Number of Aircraft Cycles at repair Incorporation date : _j)_)_)_7_l _____ _ Aircraft repaired per PSM 1-83-3 SAM 53-30-21 Figure. ___ ,Page __ _

SSI II. ,Table#._. __ _

Location of Repair : Between Station X~....__and X --=-...--Stringers #~nd # 3 fi ~

INSPECTION REQUIREMENTS. This repair affects the airworthiness limitations document and requires an additional task. The inspection requirement for this task, which are shown below, are Transport Canada ap­proved. The operator must incorporate this additional task in the SDIR document for the af. fected aircraft serial number. It is the operator's responsibility to incorporate the added in­spection in the maintenance program for the affected aircraft. The time for threshold insp~ tion is measured from the time of repair incorporation.

Threshold : _f.f_.D,...~Q .... Dt> _____ lt ___ S __ (Flights) Repeat: IP,6QD tiiv~ (Flights)

The above inspection times were determined in report AEROC B.4.AC.11 , Section 53-0037-1 using the Transport Canada accepted damage tolerance evaluation procedure documented in AEROC 8.4.AC.5, Section 19.1

Inspection Method : Standard low frequency eddy current for basic aircraft structure (subsurface) and standard high frequency eddy current for repair patch (surface).

Inspection Procedure: Refer to Dash 8 NDT Manual PSM 1-83-7A, PART 1. Section 51-00-06

Operator's Entry Signature ::?f?t~ /O~t?-10 Date:~ - Jj-/S-A copy of this page must be inserted Into the SDIR Document SDIR 8-____ _

PAGE 7 OF 8

.. . . ...

DASH8 200/300 SERIES MPM - Appendix A

MAINTENANCE TASK WORK CARD Revision: 9 Effective: 04/01/11

Intentionally left blank

PAGE 8 OF 8

1 . I I •

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DATEJul-99

BOMBARDIER ~ AEROSPACE 'W"

SECT I

PAGE 1

ISSUE ¥/f$}rrt7

The following RD aJlows continued operation with cracks detected on the wing spar to fuselage roof skin angles 85300011-l l l/112, and 85300016-117/121 LH and RH sides. Cracks must be outboard of stringer-3. Cracks are aJlowed on any or all of the four angles (FIS Stbd, Port, R/S Stbd, and Port). Seal as required with PR1422-B2 or equivalent in acrordance with the instructions of the DASH 8 structural repair manual PSM 1-83-3 c~ 51-30-26. For continued flight with cracked closing angles, the front and rear spar angles between stringers 3 LH and 3 RH must be inspected and be crack free using a detailed visual inspection. The center angles molt be re­impeded at every "C" Check or every 10000 FUgb~ which ever:1 is lea. No Cracks Permitted on center angleaGll-113, and 85300016-119). @

Vfo{_~Er-foP~t"f t'<il10llg7 For continued t, tbe RH ud Lil dished akin to iring lower skin futeoen mmt be replaced, and additional stnps Installed as per pages 5, and 6. Tbe fastenen and strape may be iutaDed before cracka are detKted to avoid IIDICbeduled down time. 1be fastener replacement and additional straps do not end the requirement for the above center 8Dgle impediom. All outb'd an includin uncracked es must be laced on or before 40000 flights. N~ Afu:r the outb' dangles are replaced, all angles must be inspected as per maintenance tBsk 5310/'3 lA.

SC-H-E IJLE. If further cracks are found on the outb'd angles, continued operation is allowed for an additional 40000 flights froot the time of angle replacement The front and rear spar angles between stringers 3 LH and 3 RH must be inspected and be crack tree using detailed visual inspection. Jfthe outb'd angles are cracked, the center angles molt be re-Inspected at every "C" Check or every 10000 ftights which ever is le&1. No .t Craclm Permitted on cuter angles (SS.300011-113, and 8530001~119). ; The details of this {X'OCOOUre are covered by RD 8-53-2959 section 1.

page 2 issue 1 page 5 issue -1" ~ r•-1 e I & '>.s u E { '1 !'1 page 1 issue..f;L.;YA,..lif>'?ige 4 issue 1 f'•Je '" ,,~oJ£

' -<'I ~ AT issuE z. : ,.3 I, s- RA 1sEb r o ,uue 1.. page 3 issue 1 page 6 issue.t2. JJ d .0 t S'T"VIP t101)1f"tfD i:o~ CLE~~ A.NC£- A,- ,ssvE 5: P,1 I 1i:,,,1,.so "r1> 1S..S"E J, Pj 1•"' e ""i, ..- TQ ov~~a:,o 6'1N a~~E~. CLE~_'ftlL CHA"''-£: · TO t..J.SPec.:n N PG1t.1oi> ~ .:; T'iFb ~RRo GoR~e'C,i~ • 1ot------,------,.------------:1rp-__,;;....;;;;..:..;.:.;._;~=.:.,.:.;..;,..:.....;...;:~----1 -.!c ~ RD ISSUE 2._ Title: Temporary Continued Operation ~ ~1----------------------- --+---1 ~ . ~ DA TE 26-Jul-99 with Cracks on the Wing Spar

l/l "-N DRAWN to Fuelage Roof Angles ~ -~ APPROVED Series 300 Model 311/314/315

STRESS

REPORT NUMBER D.

A. RD8-S3-2959

R.

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BOMBARDIER SECT 1

CHECKED PAGE 18

DATE Apr '05 ISSUE 2

Alternate Procedure For Cracked Anste Replacement Schedule

As detailed on Page 1, the requirement for continued flight with known cracking in the outer closing angles, is that after 40,000 flights ALL outer angles (including any remaining uncracked angles) are to be replaced. The aircraft may then return to service with no added inspection requirements or restrictions. If further cracking is found, R0S-53-2959 may be invoked again on the "new" angles to continue flight with up to all 4 new outer angles cracked for 40,000 flights.

An alternate procedure may also be followed, as given below:

Alternate Procedure

A) At time of detected cracking in the outer angle (or angles) R0S-53-2959 is invoked to permit continued operation. After a maximum of 40,000 flights of continued operation, only the cracked angles are replaced. Any remaining uncracked outer angles may be left in place.

' B) However, at return to service for this aircraft, the outer angles must now be subjected to a continued repetitive detailed visual inspection for cracks. This inspection interval is 10,035 Flights or at next 'C' check, whichever comes first.

0 C) An aircraft in operation in accordance with this alternate procedure may subsequently have new cracking found in any one of the 4 outer angles (but not the centre angles) and continue in operation for a maximum of 40,000 flights with the angle cracked (from the time of the detection of this new cracking). The repetitive flight inspection as noted in B) must be continued. However, if cracking occurs in more than one outer angle, then all cracked angles must be replaced within 5,500 flight hours (of discovery of multi angle cracking) or at next "C" check, whichever comes first.

D) At replacement of angles per C), the procedure starts over at 8) again.

NOTE: Ho cracking of centre angles is permitted.

0 At issue 2: changed inspection intervals in note B) to l0,Q35 Flights, (was 5'.500 flight hours)

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AEROSPACE ~ PAGE 6 DATE Jul-99 ISSUE.¥"~

Fastener Codes. -$- HST12-8 HiLite fasteners at existing locations. Hole Dia .. 2455"/.2475"

HST1087-8 collars - preferred fastener or HL12V-8 Hi-Lok fasteners at existing locations. Hole Dia .. 2460"/.2480" HL86-8 collars + Reference only.

General notes:

I. Fabricate the repair strap from 0.190" 7075 clad T6 (QQ-A-250/13) material. ,.::;,. Machine outside profile to match existing strap. Form to required contour. \6,10~ J,..)STA-1.-t.. ~'-'A's Pi,-,.) ,:s71~t,O . 2. All new parts arc to be finished with alodinc and epoxy primer.

3. Maintain a minimum of two times the fastener diameter edge distance, unless otherwise specified. The edge distance is measured from the center of the fastener hole to the edge of the material and must be maintained on all material through which the fastener passes.

4. Fayseal all mating surfaces with Pro-Seal 870C sealant or equivalent in accordance with DASH-8 structural repair manual PSM 1-83-3 chapter 51-30-26. This sealant is procured to OHMS S3.06 Type 1 Class C-80.

5. If the aircraft is equipped with long range fuel tanks, install all fasteners wet with Pro­Seal 870C sealant or equivalent in accordance with DASH-8 structural repair manual PSM 1-83-3 chapter 51-30-26. Dome seal the internal collars with PR1422-B2 or equivalent in accordance with the instructions of the DASH 8 structural repair manual PSM 1-83-3 chapter 51-30-26.

I

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Date tJ ~/tJ5/1 S • 4

Maint Performed

Release Signature

Certificate Number Date ____ _

Sia

Item No.

I

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Sta

WO No.

COMMUTAIR AIRCRAFT LOG/ FLIGHT WORKSHEET

Maintenance Release:

Time Station ------ ----

Oil Added (Qts)

No. 2 Eng

Discrepancy

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PIC Sig. (If Req)

Dailv Checks

Check Name

System Check/Run-up

Full Pwr Takeoff

Engine Trend

VOR Check

Location ________ Circle Type of Check: voi: Bearing Error I Difference'-----------Narne Signature

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Corrective Action Part/ Serial No. Sta

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Discrepancy/Purpose, See Item Number __ _____ _ _ above

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Flight Crew - See ferry permit (attached) ___________ ______ __ Pilot Signature Maintenance Actions (if required) ____________________________ ______ _

lnsp.

Mecl1anic - This aircraft has been inspected and is determined safe for ferry flight from _ _ _ to ___ _ _ ___________ Mechanics Signature

Wllite - Mainlenance Yellow - Duplicate Blue - Aircraft Form 222

•

Date

Main! Performed

Release Signature

Certificate Number

Date

Sta No. 1 Eng.

CoPy COMMUTAIR AIRCRAFT LOG I FLIGHT WORKSHEET

Maintenance Release: ally ec s D 'I Ch k

Check Name

System Check/Run-up

Full Pwr Takeoff

Time ______ Station ___ _ Engine Trend

Oil Added (Qts) VORCheck

No. 2 Eng Signature/Cert# Location _______ Circle Type of Check: VOT Bearing Error/ Difference _________ _

0019195

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Signature

Dual Ground Dual Air

Name Signature

ircra 1screpanc1es A' tto· Item

Sta Discrepancy Item

Corrective Action Part/ Serial No. Sta Sign and No. No. No. Date

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Mechanic - This aircrart has been inspected and is determined safe for ferry night from ___ to __ _ -----------··--·---· .. ·-·_Mechanics Signature

White - Maintenance Yellow - Duplicate Blue - Aircraft Form 222