list of effective pages · 2011. 4. 7. · doors list of effective pages chapter section subject...

52 − EffectivePages

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CSTRUCTURAL REPAIR MANUAL

DOORSLIST OF EFFECTIVE PAGES

ChapterSectionSubject Config Page Date


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Pages

Apr 10/2011

THIS PAGE INTENTIONALLY LEFT BLANK

52−00−00 52−00−00

DOORS − GENERAL 1 ALL

General

Structural Classification

Stations

Structural Identification

DOOR INTERNAL STRUCTURE − ALLOWABLE

DAMAGE

101 ALL

General

52−00−27 52−00−27

DOOR FITTINGS − STRUCTURAL IDENTIFICATION 1 ALL

General

DOOR FITTINGS − ALLOWABLE DAMAGE 101 ALL

General

DOOR FITTINGS − REPAIRS 201 ALL

General

52−00−31 52−00−31

DOOR SKIN AND PLATING − STRUCTURAL

IDENTIFICATION

1 ALL

General

DOOR SKIN AND PLATING − ALLOWABLE DAMAGE 101 ALL

General

Allowable Damage

DOOR SKIN AND PLATING − REPAIRS 201 ALL

General


DOORSTABLE OF CONTENTS

Subject

ChapterSectionSubject Page Effectivity

MasterEFFECTIVITY: ALL 52−Contents Page 1

Jun 10/2007

52−01−00 52−01−00

DOOR SEALS 1 ALL

General

DOOR SEALS — REPAIRS 201 ALL

General

Equipment and Materials

Repair

52−10−00 52−10−00

PASSENGER−DOOR MAIN STRUCTURE − GENERAL 1 ALL

General


Allowable Damage

52−10−14 52−10−14

PASSENGER−DOOR FRAME STRUCTURE −

STRUCTURAL IDENTIFICATION

1 ALL

General

PASSENGER−DOOR FRAME STRUCTURE − REPAIRS 201 ALL

General

52−10−27 52−10−27

PASSENGER−DOOR FITTINGS − ALLOWABLE

DAMAGE

101 ALL

General

PASSENGER−DOOR FITTINGS − REPAIRS 201 ALL

General

52−10−31 52−10−31

PASSENGER DOOR SKIN AND PLATING −


1 ALL

General


Subject



Jun 10/2007

PASSENGER DOOR SKIN AND PLATING −

ALLOWABLE DAMAGE

101 ALL

General

PASSENGER DOOR SKIN AND PLATING − REPAIRS 201 ALL

General

Replacement of Passenger Door Hinge (door section).

52−12−00 52−12−00

PASSENGER−DOOR AUXILIARY STRUCTURE −

GENERAL

1 ALL

General


Allowable Damage

52−12−55 52−12−55

PASSENGER DOOR STAIRS − STRUCTURAL

IDENTIFICATION

1 ALL

General

PASSENGER DOOR STAIRS − ALLOWABLE DAMAGE 101 ALL

General

PASSENGER−DOOR STAIRS − REPAIRS 201 ALL

General

52−12−57 52−12−57

PASSENGER DOOR HANDRAIL − STRUCTURAL

IDENTIFICATION

1 ALL

General

PASSENGER DOOR HANDRAIL − ALLOWABLE

DAMAGE

101 ALL

General

Passenger−Door Handrail − Repairs 201 ALL

General


Subject



Jun 10/2007

52−20−00 52−20−00

EMERGENCY EXITS − GENERAL 1 ALL

General


Allowable Damage

52−21−00 52−21−00

EMERGENCY EXIT DOOR − STRUCTURAL

IDENTIFICATION

1 ALL

General

OVERWING EMERGENCY EXIT DOORS −

ALLOWABLE DAMAGE

101 ALL

General

Specific

Emergency Exit Door − Repairs 201 ALL

General

52−22−00 52−22−00

CREW ESCAPE HATCH − STRUCTURAL

IDENTIFICATION

1 ALL

General

CREW ESCAPE HATCH − ALLOWABLE DAMAGE 101 ALL

General

52−30−00 52−30−00

CARGO DOOR − STRUCTURAL IDENTIFICATION 1 ALL

General

CARGO DOOR − ALLOWABLE DAMAGE 101 ALL

General

CARGO DOOR − REPAIRS 201 ALL

General


Subject



Jun 10/2007

52−30−55 52−30−55

CARGO DOOR STEP PLATE − STRUCTURAL

IDENTIFICATION

1 ALL

General

CARGO DOOR STEP PLATE − ALLOWABLE DAMAGE 101 ALL

General

CARGO DOOR STEP PLATE − REPAIRS 201 ALL

General

52−40−00 52−40−00

SERVICE DOORS − GENERAL 1 ALL

General


Allowable Damage

52−41−00 52−41−00

SERVICE DOOR − GENERAL 1 ALL

General


Allowable Damage

52−41−14 52−41−14

SERVICE DOOR SKIN AND FRAME STRUCTURE −


1 ALL

General


ALLOWABLE DAMAGE

101 ALL

General


REPAIRS

201 ALL

General


Subject



Jun 10/2007

52−41−27 52−41−27

SERVICE DOOR FITTINGS − STRUCTURAL

IDENTIFICATION

1 ALL

General

SERVICE DOOR FITTINGS − ALLOWABLE DAMAGE 101 ALL

General

52−42−00 52−42−00

MAIN AVIONICS DOOR − STRUCTURAL

IDENTIFICATION

1 ALL

General

MAIN AVIONICS COMPARTMENT DOOR −

ALLOWABLE DAMAGE

101 ALL

General

MAIN AVIONICS DOOR − REPAIRS 201 ALL

General

52−43−00 52−43−00

AFT EQUIPMENT BAY DOOR − STRUCTURAL

IDENTIFICATION

1 ALL

General

AFT EQUIPMENT COMPARTMENT DOOR −

ALLOWABLE DAMAGE

101 ALL

General

52−44−00 52−44−00

FORWARD EQUIPMENT−COMPARTMENT ACCESS

AND AIR−DRIVEN GENERATOR (ADG) DOORS −

GENERAL

1 ALL

General


Allowable Damage


Subject



Jun 10/2007

52−44−32 52−44−32


DOORS − STRUCTURAL IDENTIFICATION

ALL

General


DOORS − ALLOWABLE DAMAGE

101 ALL

General


DOORS − REPAIRS

201 ALL

General

52−44−37 52−44−37

AIR DRIVEN GENERATOR (ADG) DOOR −


1 ALL

General

AIR−DRIVEN GENERATOR (ADG) DOOR −

ALLOWABLE DAMAGE

101 ALL

General

General Limitations

Specific Limitations

AIR DRIVEN GENERATOR (ADG) DOOR − REPAIRS 201 ALL

General

52−45−00 52−45−00

SERVICING DOORS − GENERAL 1 ALL

General

SERVICING DOORS − ALLOWABLE DAMAGE 101 ALL

General

SERVICING DOORS − REPAIRS 201 ALL

General


Subject



Jun 10/2007

52−45−01 52−45−01

APU FAULT AND GROUND AIR CONNECTION DOOR −


1 ALL

General

APU FAULT AND GROUND AIR CONNECTION DOOR −

ALLOWABLE DAMAGE

101 ALL

General

52−45−02 52−45−02

REFUELING ACCESS DOOR − STRUCTURAL

IDENTIFICATION

1 ALL

General

REFUELING ACCESS DOOR − ALLOWABLE DAMAGE 101 ALL

General

52−45−03 52−45−03

OXYGEN REFILLING DOOR − STRUCTURAL

IDENTIFICATION

1 ALL

General

52−45−04 52−45−04

AC ELECTRICAL GROUND POWER DOOR −


1 ALL

General

AC ELECTRICAL GROUND POWER DOOR −

ALLOWABLE DAMAGE

101 ALL

General

52−45−05 52−45−05

EXTERNAL SERVICE PANEL DOOR − STRUCTURAL

IDENTIFICATION

1 ALL

General


Subject



Jun 10/2007

EXTERNAL SERVICE PANEL DOOR − ALLOWABLE

DAMAGE

101 ALL

General

52−45−06 52−45−06

DC ELECTRICAL GROUND POWER DOOR −


1 ALL

General

DC ELECTRICAL GROUND POWER DOOR −

ALLOWABLE DAMAGE

101 ALL

General

52−45−07 52−45−07

LAVATORY SERVICE DOORS − STRUCTURAL

IDENTIFICATION

1 ALL

General

52−45−08 52−45−08

REFUEL / DEFUEL CONTROL PANEL DOOR −


1 ALL

General

REFUEL/DEFUEL CONTROL PANEL DOOR −

ALLOWABLE DAMAGE

101 ALL

General

52−45−09 52−45−09

POTABLE WATER SERVICE DOOR − STRUCTURAL

IDENTIFICATION

1 ALL

General


Subject



Jul 10/2008

52−51−00 52−51−00

FLIGHT COMPARTMENT DOOR − ALLOWABLE

DAMAGE

101 ALL

General

FLIGHT COMPARTMENT DOOR − REPAIRS 201 ALL

General

52−80−00 52−80−00

LANDING GEAR DOORS − GENERAL 1 ALL

General


Allowable Damage

52−81−00 52−81−00

NOSE LANDING GEAR DOORS − STRUCTURAL

IDENTIFICATION

1 ALL

General

NOSE LANDING−GEAR DOORS − ALLOWABLE

DAMAGE

101 ALL

General

General Limitations

Specific Limitations

NOSE LANDING−GEAR DOORS − REPAIRS 201 ALL

General

52−82−00 52−82−00

MAIN LANDING GEAR DOOR − STRUCTURAL

IDENTIFICATION

1 ALL

General

MAIN LANDING GEAR DOOR − ALLOWABLE DAMAGE 101 ALL

General

Specific


Subject



Jun 10/2007

MAIN LANDING GEAR DOOR − REPAIRS 201 ALL

General


Subject



Jun 10/2007

DOORS − GENERAL

1. General

A. Chapter 52 contains structural identification data, allowable damage limits and repairs for theaircraft doors.

B. Section 52−00 contains data that is applicable to doors in general such as general allowabledamage limits.

2. Structural Classification

A. Most doors are primary structure. For the structural classification of the different doors, refer toSRM 51−00−00.

3. Stations

Refer to Chapter 53.

4. Structural Identification

For the structural identification locator of the different doors refer to Figure 1.


MasterEFFECTIVITY: ALL 52−00−00 Page 1

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52−45−09

52−45−06

52−21−00

52−45−02

52−45−08

52−45−09

52−45−07

52−41−00 52−44−32

52−45−03

52−44−37

52−44−32

52−22−00

52−10−14

52−21−00

52−30−00

52−45−01


Door Structural Identification LocatorFigure 1 (Sheet 1)


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52−82−00

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52−45−04


Door Structural Identification LocatorFigure 1 (Sheet 2)


Feb 18/2003

DOOR INTERNAL STRUCTURE − ALLOWABLE DAMAGE

1. General

CAUTION: ALWAYS REFER TO PAGE BLOCK 101−199 APPLICABLE TO A GIVENSTRUCTURAL ELEMENT FOR SPECIFIC ALLOWABLE DAMAGE LIMITS. IF THIS ISNOT DONE, IT IS POSSIBLE THAT YOU WILL USE THE INCORRECT DATA.

A. Use the general allowable damage limits given in this subject when specific damage limits are notsupplied in the subject for a given structural element.

B. For allowable damage to the extruded, machined parts (other than fittings) and formed sheetmetal parts of the doors, refer to Figure 101 and Figure 102. For allowable damage of the doorskins, refer to SRM 52−00−31. For allowable damage of fittings, refer to the applicable subject inthis chapter.



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RUN−OUT20XMIN

THE BOTTOM OF THE REMOVEDDAMAGE MUST HAVE A RADIUS

OF 1.0 in. (25.4 mm) MINIMUM

T X = DEPTH OF MATERIALREMOVAL = 10% THICKNESS

(T) MAXIMUM

TWO WEBELEMENTSAT A HOLE

FLANGE

CORNER

WEB

FREEFLANGE

BULB(EXTRUSIONS

ONLY)

AREA OF MATERIALREMOVAL MUST NOTBE MORE THAN 10%OF ELEMENT WIDTH

THE DISTANCE OF THEDAMAGE FROM A HOLE,FASTENERS OR EDGE

MUST NOT BE LESSTHAN 20X

REMOVALLIMIT

DAMAGEAREA

THE DISTANCE OF THEDAMAGE FROM A HOLE,FASTENERS OR EDGE

MUST NOT BE LESSTHAN 20X

T

T1

2

T3

REMOVEDDAMAGE

Remove damage as shown for small edgedamage, detail A. T must be larger than Tafter damage removal.

2 For added data, refer to Sheet 3.

NOTES

3 2

MATERIAL

SKIN ELEMENT

15T 15T

T = SKIN THICKNESS

EXTRUDED SECTION

EXTRUDED AND MACHINEDSECTION ELEMENTS−EXAMPLE

SMALLEDGE DAMAGE

SURFACE DAMAGE

CORNER DAMAGE

X

TOTAL CROSS−SECTION(INCLUDES SKIN)


Extruded and Machined Parts (Other than Fittings) – Allowable Damage – GeneralFigure 101 (Sheet 1)


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RADIUS OFREMOVED DAMAGEIS FOUND BY THE

DAMAGE DEPTH (X).R = 1.0 in. (25.4 mm)

MINIMUM

FASTENER EDGEDISTANCE LIMIT

(EXAMPLE)

DEPTH X − MUSTNOT BE MORE THAN

FASTENER DIAMETEROR 10% OF ELEMENT

WIDTH

MATERIAL REMOVEDTO REMOVE DAMAGE

DAMAGE REMOVALWHERE THE FASTENER EDGE DISTANCES

DO NOT HAVE OVERLAPS

DEPTH X − MUSTNOT BE MORE THAN

FASTENER DIAMETEROR 10% OF ELEMENT

WIDTH


HAVE OVERLAPS

EDGE DAMAGE

FASTENEREDGE DISTANCELIMIT (EXAMPLE)

LIMIT OF DAMAGEREMOVAL. RADIUS OFREMOVED DAMAGE IS

FOUND BY THEDAMAGE DEPTH (X).R = 1.0 in. (25.4 mm)

MINIMUM

For added data, refer to sheet 3.

NOTE




Feb 18/2003

DAMAGE REMARKS

Cracks

Cracks are not permitted in webs.

Cracks are permitted in flange edges if they are in material removal limits shown foredge damage.

Scratches,nicks, gougesand corrosion

Removed damage must not decrease the thickness (or the cross−section area) of agiven element by more than 10 percent (an extruded bulb is an element).

Dents Dents are not permitted.

Holes andpunctures

Holes and punctures are not permitted in attachment flanges.

You can plug holes thru 0.25 inch (6.35 mm) in diameter (refer to the Notes that follow)if they are not nearer than 4 X the repaired hole diameter to:

− Adjacent holes

− Part edges

− Corner radii

− Other damage.

NOTE: The hole must not decrease the cross−section area of a given element by morethan 10 percent.

NOTE: If the adjacent fasteners are rivets or clearance−fit fasteners, use an AD rivet toplug the hole. If the adjacent fasteners are interference−fit fasteners (e.g. Hi−Lok pins),contact Bombardier Aerospace Regional Aircraft, Customer Support (refer to SRM51−13−01).

General

Damage is permitted in only one element at a given cross−section. Removed damage atone element must not have an overlap on removed damage at another element (refer tothe data given for formed parts in Figure 102, (Sheet 1).

NOTE: Attached skins for a distance of 15 X the local skin thickness from theattachment row of fasteners are an element of the cross−section (refer to Sheet 1 of thisFigure).

If the part was shot peened when it was made, it must be shot peened again (refer toSRM 51−24−11) after damage removal.

NOTE: Approved repair or replacement of a member is necessary when more than 30 percent of its lengthis damaged.

NOTE: For full instructions on the treatment of allowable damage, refer to SRM 51−12−00. Use anapproved repair (refer to SRM 51−13−00) to repair damage that does not agree with the allowabledamage limits.

NOTE: Remove damage as shown in Sheets 1 and 2 of this Figure.




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ATTACHMENTFLANGE

LIP

WEB

FORMED SECTIONELEMENTS EXAMPLE

FLANGE

15T 15T

T = SKIN THICKNESS

SKIN ELEMENT

FORMEDSECTION

FREEFLANGE

Repaired areas must nothave an overlap.

2 For added data,

NOTES

refer to Sheet 3.

DENTS MUST BESMOOTH AND NOT

HAVE SHARP CREASES,GOUGES, OR CRACKS.

FOR DEPTH LIMITCALCULATION, REFER

TO SHEET 2

D(DEPTH OF DENT)

W(WIDTH OF MINOR

AXIS OF DENT)

INITIALCONTOUR

AREA REPAIREDBEFORE

THE BOTTOM OF THEREMOVED DAMAGE MUSTHAVE A RADIUS OF 1.0 in.

(25.4 mm) MINIMUM

X = DEPTH OFDAMAGE REMOVAL

= 10% FLANGEWIDTH MAXIMUM

20XMINIMUMRUN−OUT

TOTAL CROSS−SECTION(INCLUDES SKIN)

DENTS

REMOVAL OF NICK OR CRACKDAMAGE ON AN EDGE


Formed Parts – Allowable Damage – GeneralFigure 102 (Sheet 1)


Feb 18/2003

DAMAGE REMARKS

Cracks

Edge cracks are permitted only in free flanges. Cracks are not permitted in lippedflanges or in webs.

Remove damage as shown in Sheet 1 of this Figure.

Scratches,nicks, gougesand corrosion

Removed damage must not decrease the thickness or the cross−section area of a givenelement by more than 10 percent.

Dents

Dents are permitted in webs only.

Dents must be smooth and not have sharp creases, gouges, cracks, or signs ofdamaged or loose rivets.

W/D must not be less than 20 where: W = Width of the minor axis of the dent D = Depthof the dent from the initial contour.

Holes andpunctures

Holes and punctures are not permitted in attachment flanges.

You can plug holes thru 0.25 inch (6.35 mm) in diameter (refer to the Note that follows)if they are not nearer than 4 X the repaired hole diameter to:

− Adjacent holes

− Part edges

− Corner radii

− Other damage.

NOTE: The hole must not decrease the cross−section area of a given element by morethan 10 percent.

NOTE: If the adjacent fasteners are rivets or clearance−fit fasteners, use an AD rivet toplug the hole. If the adjacent fasteners are interference−fit fasteners (e.g. Hi−Lok pins),contact Bombardier Aerospace Regional Aircraft, Customer Support (refer to SRM51−13−01).

General

Damage is permitted in only one element at a given cross−section. Removed damage atone element must not have an overlap on removed damage at another element (refer toSheet 1 of this Figure).

NOTEs: Attached skins for a distance of 15 X the local skin thickness from theattachment row of fasteners are an element of the cross−sec tion (refer to Sheet 1 ofthis Figure).

NOTE: Approved repair or replacement of a member is necessary when more than 30 percent of its lengthis damaged.

NOTE: For full instructions on the treatment of allowable damage, refer to SRM 51−12−00. Use anapproved repair (refer to SRM 51−13−00) to repair damage that does not agree with the allowabledamage limits.


Formed Parts – Allowable Damage – GeneralFigure 102 (Sheet 2)


Feb 18/2003

DOOR FITTINGS − STRUCTURAL IDENTIFICATION

1. General

A. Passenger Door Main Structure

Refer to SRM 52–10–27

B. Passenger Door Auxiliary Structure

(1) Passenger Door Stairs


(2) Passenger Door Handrail


C. Emergency Exits

(1) Overwing Emergency Exit Doors


D. Service Doors

(1) Service Door


(2) Main Avionic Compartment Door


(3) Aft Equipment Compartment Door


(4) Forward Equipment Compartment Door


E. Landing Gear Doors

(1) Nose Landing Gear Door


(2) Main Landing Gear Doors




Feb 18/2003

DOOR FITTINGS − ALLOWABLE DAMAGE

1. General

A. General allowable damage limits for fittings are not available. Canadair will supply damage limitsas necessary.



Feb 18/2003

DOOR FITTINGS − REPAIRS

1. General

A. For repairs to the door fittings, contact Bombardier Aerospace Regional Aircraft, CustomerSupport (refer to SRM 51−13−01).



Feb 18/2003

DOOR SKIN AND PLATING − STRUCTURAL IDENTIFICATION

1. General

A. Passenger Door Main Structure

Refer to SRM 52−10−31

B. Passenger Door Auxiliary Structure

(1) Passenger Door Stairs


C. Emergency Exits

(1) Overwing Emergency Exit Doors


(2) Crew Escape Hatch


D. Cargo Door


E. Service Doors

(1) Service Door


(2) Main Avionic Compartment Door


(3) Aft Equipment Compartment Door


(4) Forward Equipment Compartment Door


(5) Air−Driven Generator (ADG) Door


(6) Servicing Doors

(a) APU Fault and Ground Air Connection Door


(b) Refueling Access Door


(c) Oxygen Re−Filling Door


(d) AC Electrical Ground Power Door


(e) External Service Panel Door


(f) DC Electrical Ground Power Door


(g) Lavatory Services Door




Feb 18/2003

(h) Refuel/Defuel Control Panel Door


(i) Potable Water Service Door


F. Landing Gear Doors

(1) Nose Landing Gear Door


(2) Main Landing Gear Doors




Feb 18/2003

DOOR SKIN AND PLATING − ALLOWABLE DAMAGE

1. General

CAUTION: ALWAYS REFER TO PAGE BLOCK 101−199 APPLICABLE TO A GIVENSTRUCTURAL ELEMENT FOR SPECIFIC ALLOWABLE DAMAGE LIMITS. IF THIS ISNOT DONE, IT IS POSSIBLE THAT YOU WILL USE THE INCORRECT DATA.

A. Use the allowable damage limits given in this subject when specific damage limits are notsupplied in the subject for a given structural element.

B. The door skin panels are of two general types: sheet metal and honeycomb composite structures.The honeycomb composite structures are made of Kevlar/epoxy and graphite/epoxy laminatedfacing skins on nylon honeycomb cores. To provide lightning protection, these panels havealuminum wire screen mesh bonded to the external facing skin surfaces.

2. Allowable Damage

A. Composite Honeycomb Panels

(1) Scratched paint or primer is the only allowable damage permitted for honeycomb compositepanels. If the damage has not gone through the paint or primer, there is no limit on theamount of scratch damage. You must use approved typical, generic or specific repairs for allother damage (refer to SRM 51−13−00 and the applicable 201−299 page block).

B. Sheet Metal Panels

(1) For flight operation limits of scratch damage, refer to Figure 101. For general damage limits,refer to Figure 102.



Feb 18/2003

DOOR LOCATION (PRESSUR-IZED FUSELAGE AREAS) SKIN THICKNESS IN. (MM)

MAXIMUM SCRATCH DEPTHIN. (MM)

Passenger 0.045 (1.14)

0.063 (1.6) and thicker

0.015 (0.38)

0.025 (0.635)

Service 0.040 (1.2)

0.058 (1.47) and thicker

0.015 (0.38)

0.025 (0.635)

Cargo compartment 0.050 (1.27) and thicker 0.025 (0.635)

Avionics compartment 0.060 (1.52) and thicker0.020 (0.51)

Overwing emergency exit 0.050 (1.27) and thicker

CAUTION:

THE FLIGHT OPERATION LIMITS APPLY TO SKIN DAMAGE THAT IS CONTAINED IN SINGLE LOCALAREAS (BAYS) THAT HAVE AN ATTACHED SUPPORT STRUCTURE ON ALL SIDES. WHERE ASCRATCH GOES ACROSS SUPPORT MEMBERS SUCH AS STRINGERS, INTERCOSTALS, ORFRAMES, THE SKIN DAMAGE DEPTH MUST NOT BE MORE THAN 10 PERCENT OF THE LOCALSKIN AND DOUBLER THICKNESS. IF YOU DO NOT OBEY THESE LIMITS, YOU WILL USEINCORRECT ALLOWABLE DAMAGE LIMITS.

NOTE:

Continued flight operations are permitted without limits if the scratch depth (after blending) is not morethan shown and the scratch is correctly blended (refer to SRM 51−12−00).


Scratch Damage in Metallic Door Skin Plating − Flight Operation LimitsFigure 101


Feb 18/2003

rsr5

2007, yf

r, 1

5/0

7/9

9

For added data, refer to sheet 3.NOTE

X DEPTH = 0.15 in.(3.81 mm) MAX

MATERIAL REMOVEDTO REMOVE DAMAGE RADIUS OF

REMOVED DAMAGEIS FOUND BY THE

DAMAGE DEPTH (X).


(EXEMPLE)

LIMIT OF DAMAGEREMOVAL. RADIUS OFREMOVED DAMAGE IS

FOUND BY THEDAMAGE DEPTH (X).




HAVE OVERLAPS

EDGE DAMAGE

X DEPTH = 0.15 in.(3.81 mm) MAX


(EXEMPLE)


Metallic Door Skin and Plating − Allowable Damage − GeneralFigure 102 (Sheet 1)


Feb 18/2003

rsr5

2008, yf

r, 1

6/0

7/9

9

D(DEPTH OF DENT)

W(WIDTH OF MINOR

AXIS OF DENT)

INITIALCONTOUR

DENTS

0.100 in. (2.54 mm) MAX

RUN−OUT20XMIN

THE BOTTOM OF THE REMOVEDDAMAGE MUST HAVE A RADIUS

OF 1.0 in. (25.4 mm) MINIMUM

X = DEPTH OFDAMAGE REMOVAL

THE DISTANCE OF THEEDGE OF THE REMOVED

DAMAGE FROM THE HOLES,FASTENERS OR SKIN EDGE

MUST NOT BE LESS THAN 20X

T = THICKNESSOF THE MATERIAL

SCRATCHES, NICKS, GOUGES AND CORROSION

(MAJOR AXIS OF THEREMOVED MATERIAL)

DAMAGEAREA

DAMAGEREMOVAL

LIMIT

Refer to sheet 3, for added data.NOTE




Feb 18/2003

DAMAGE REMARKS

CracksCracks are permitted only at the edges of the skins.


Scratches, nicks,gouges and

corrosion


For the depth limits of scratches and nicks, Figure 101.

Removed corrosion damage must not be more than 10 percent of the local skinthickness. For the removal of corrosion damage, refer to SRM 51−21−06.

Dents

Dents must be separated by one−half (1/2) the width of the largest adjacent dent.

Dents must be smooth and not have sharp creases, cracks, or signs of damaged orloose rivets. W/D must not be less than 25 where:

W = Width of the minor axis of the dent

D = Depth of the dent from the initial contour.

Holes andpunctures/

Holes thru 0.25 inch (6.35 mm) in diameter can be plugged with AD type rivets if theyare not nearer than 4 X the repaired hole diameter to:

− Adjacent holes

− Skin edges

− Chem−milled pocket radii

− Other damage.

General edgedamage

There are no limits for the linear dimension of the removed damage if standard edgedistances are maintained (refer to SRM 51−40−06). A decreased edge distance of 1.5X fastener diameter is permitted for 10 percent of the linear dimension.

NOTE: Approved repair or replacement is necessary when more than 30 percent of the area of a panel isdamaged.

NOTE: For full instructions on the treatment of allowable damage, refer to SRM 51−12−00. Use anapproved repair (refer to SRM 51−13−00) for repair damage that does not agree with the allowabledamage limits




Jul 10/2008

DOOR SKIN AND PLATING − REPAIRS

1. General

A. For repairs to the door skin and plating, contact Bombardier Aerospace Regional Aircraft,Customer Support (refer to SRM 51−13−01).



Feb 18/2003

DOOR SEALS

1. General

A. Structural Identification

(1) The structural identification for the door seals is given in the applicable 1−101 page block foreach door.

B. Repairs

(1) For repairs to the door seals, refer to page block 201−299 in this subject.

C. Sealing Pads

(1) Most access panels and some access doors are sealed with sealing pads. The sealing padsare also used to make the panels/doors level (aerodynamically smooth) with the adjacentexternal skin panels. The pads are made from sealing compounds. For removal ofunserviceable sealant, refer to SRM 51−23−00. For installation of new sealing pads, referto SRM 51−23−16.



Feb 18/2003

DOOR SEALS — REPAIRS

1. General

Refer to Figure 201.

This procedure covers the repairs to small rips or punctures of the passenger door and service doorseals.

2. Equipment and Materials

A. Consumable Materials

Reference Designation

— DAPCO 3302, Silicone adhesive − D AircraftProducts, Anaheim, CA (USA)

— Silicone rubber compound #AR395A−NPC (0.060inch (1.52 mm) thick reinforced with 0.008 inch(0.203 mm) Dacron polyester fabric), FreudenbergNOK Inc., Ont., CAN.

Specification ASTM D740 Type V MEK (Methyl Ethyl Ketone)

Commercial Aluminum−oxide abrasive paper, 180−grit

3. Repair

A. Procedure

(1) Cut away small rips or punctures, to a regular profile as shown in Repair A or Repair C,otherwise cut and splice seal as required, as shown in Repair B.

(2) Using repair material, prepare repair patches to suit as shown in Repair A, B, or C. Do notcover vent holes.

(3) Use 180 grit paper or fine paper, and lightly rub the seal and repair material to make repairarea rough.

(4) Solvent clean the repair area with MEK (refer to SRM 51−26−00).

(5) Mix adhesive according to the manufacturer’s instructions.

(6) Apply adhesive to both surfaces and air dry for 30 minutes at room temperature until tackfree prior to bonding.

NOTE: Great care must be taken when bonding repair items. The adhesive does notallow adjustment after contact.

.

(7) Assemble substrates and apply moderate pressure to achieve intimate contact.

.

(8) Optimum adhesion is achieved after a seven day cure at room temperature 70 °F (21 °C ).



Feb 18/2003

rsr5

20

78

, sb

, 0

5/0

6/0

1

0.25 in.(6.35 mm)

(TYP)

TYPICAL SECTIONTHROUGH REPAIR A

All dimensions are given ininches followed by millimetersin parentheses.

0.50 in.(12.7 mm)

CUT LINE

0.40 in.(10.16 mm)

R FULL

0.50 in.(12.7 mm)

(TYP)

1.0 in.(25.4 mm)

MAX

REPAIR A

CUT LINE

1.0 in.(25.4 mm)

(TYP)

REPAIR B

MAX

NOTE

TYPICAL SECTIONTHROUGH REPAIR B

SERVICE EFFECTIVITY

REPAIR

REPAIR A

REPAIR B

REPAIR C

SERVICE EFFECTIVITY

A/C 7003−7174PRE SB 601R−52−067A/C 7003−7174

A/C 7003−7174 POST SB 601R−52−067PRE SB 601R−52−067

A/C 7175 SUBSEQUENT

1

1

1


Repair of Door SealsFigure 201 (Sheet 1)


Feb 18/2003

rsr5

2077, ic

, 03/1

2/0

1

All dimensions are given ininches followed by millimetersin parentheses.

REPAIR C

NOTE

SERVICE EFFECTIVITY

REPAIR

REPAIR A

REPAIR B

REPAIR C

SERVICE EFFECTIVITY

A/C 7003−7174

A/C 7003−7174

A/C 7003−7174 POST SB 601R−52−067

PRE SB 601R−52−067

PRE SB 601R−52−067

A/C 7175 SUBSEQUENT

1

1

0.25 in.(6.35 mm)

(TYP)CUT LINE

TYPICAL SECTIONTHROUGH REPAIR C

SEAL RETAINERREF

0.30 in.(7.62 mm)

1.00 in.(25.40 mm)

0.50 in.(12.70 mm)

(TYP)

CUT LINER FULL

MAX MAX


Repair of Door SealsFigure 201 (Sheet 2)


Feb 18/2003

PASSENGER−DOOR MAIN STRUCTURE − GENERAL

1. General

A. This section contains structural identification data and allowable damage limits for thepassenger−door main structure.


A. Framing Structure

Refer to SRM 52−10−14, Page Block 1−99.

B. Fittings


C. Skin and Plating


3. Allowable Damage


A. Fittings


B. Skin and Plating




Feb 18/2003

PASSENGER−DOOR FRAME STRUCTURE − STRUCTURAL IDENTIFICATION

1. General

Refer to Figure 1 for the structural identification of the passenger−door frame structure.

Refer to Figure 2 for the structural identification of the Phase IV passenger−door frame structure.



Jun 10/2007

rsr5

2011

.dg,

ng/

rm, 0

5/04

/06

FS311.75

FS320.10

FS329.50

FS338.00 FS

347.25

1

2

3

4

5

6

7

8

9

10

1112

13

14

15

1617

1819

20

21

22

23

24

25

26

27

28

29

30

33

34

35

36

37

38

39

4041

42

43

44

4546

4748

50

51

52

53

55

56

57

32

31

55

54

54

54

54

54

54

56

55

5638

4948 49

4546


Passenger−Door Frame Structure − Structural IdentificationFigure 1


Jul 10/2006

ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISH

CODE ♦ EFFECTIVITY

Assembly −Structure,PassengerDoor

601R31902 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

1 Former Inner,FS320.10

601R31902−99,−411, −455

0.063 (1.60) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

2 Channel 601R31902−93,−449

0.063 (1.60) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

3 Former Inner,FS338.90

601R31902−5 0.063 (1.60) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


Key to Figure 1 (Sheet 1)


Jun 10/2007



4 Channel 601R31902−7 0.063 (1.60) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

5 Former Outer,FS347.25

601R31902−3 0.063 (1.60) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

6 Former Outer,FS311.75

601R31902−101 0.063 (1.60) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

7 Former 601R31902−25 0.063 (1.60) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456




Jun 10/2007




QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

9 Intercostal

DD 1

601R31902−23 0.050 (1.27) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

10 Intercostal

DD 1A

601R31902−21 0.050 (1.27) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

11 Intercostal

DD 2

600−31902−263 0.050 (1.27) Al Alloy 7075−T62

QQ−A−250/13

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456




Jun 10/2007



12 Intercostal

DD 3

601R31902−33 0.050 (1.27) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

13 Intercostal

DD 4

601R31902−337 0.050 (1.27) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

14 Intercostal

DD 5

601R31902−415 0.050 (1.27) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

15 Intercostal

DD 6

601R31902−413 0.050 (1.27) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456




Jun 10/2007



16 Intercostal

DD 7

600−31902−279 0.063 (1.60) Al Alloy 7075−T62

QQ−A−250/13

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

17 Former 600−31902−251 0.063 (1.60) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456




Jun 10/2007



20 Former 600−31902−255 0.063 (1.60) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456




Jun 10/2007




QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

25 Intercostal 601R31902−318 0.050 (1.27) Al Alloy 7075−T62

QQ−A−250/13

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/13

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/13

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456




Jun 10/2007




QQ−A−250/13

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/13

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/13

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456




Jun 10/2007




QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/5

A023 7002−7054

34A Intercostal 601R31902−485 0.050 (1.27) Al Alloy 2024−T42

QQ−A−250/5

A023 7055−7389

7391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456




Jun 10/2007



36 Intercostal 600−31902−311 0.050 (1.27) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456


QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456




Jun 10/2007



40 Channel 601R31902−87 0.050 (1.27) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

41 Bottom Corner,Forward

600−31998−10 0.063 (1.60) Al Alloy 7075−T62

QQ−A−250/13

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

42 Bottom Corner,Aft

600−31998−9 0.063 (1.60) Al Alloy 7075−T62

QQ−A−250/13

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

43 Cover, UpperCorner −Forward

600−31902−288 0.050 (1.27) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456




Jun 10/2007



44 Cover, UpperCorner − Aft

600−31902−287 0.050 (1.27) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

45 Diaphragm 600−31902−283 0.050 (1.27) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

46 Diaphragm 600−31902−284 0.050 (1.27) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

47 Upper Channel 600−31902−285 0.063 (1.60) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456




Jun 10/2007



48 Diaphragm 601R31902−145 0.050 (1.27) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

49 Diaphragm 601R31902−146 0.050 (1.27) Al Alloy 2024−T42

QQ−A−250/5

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

50 Back−up Fitting 600−31922−3 0.125 / 0.210 (3.18 / 5.33 )7050−T73651 Al Alloy

CMS 516−03 (BAMS516−003)

A024 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

51 Back−up Fitting 600−31922−4 0.125 / 0.210 (3.18 / 5.33 )7050−T73651 Al Alloy

CMS 516−03 (BAMS516−003)

A024 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456




Jun 10/2007



52 Back−upFitting, Tee

600−31986−3 0.250 / 0.375 (6.35 / 9.52)7050−T73651 Al Alloy

CMS 516−03 (BAMS516−003)

A024 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

53 Back−upFitting, Tee

600−31986−4 0.250 / 0.375 (6.35 / 9.52)7050−T73651 Al Alloy

CMS 516−03 (BAMS516−003)

A024 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

54 Cleat 600−31902−269 0.050 (1.27) Al Alloy 7075−T62

QQ−A−250/13

A023 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

55 Support Angle 601R31902−35 3.00 (76.2) 7075 Al Alloy ExtdBar & Shapes ♣QQ−A−200/11

A024 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456




Jun 10/2007



56 Support Angle 601R31902−71 2.50 (63.5) M/F S−2199 ♦♦ A024 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

57 Support Angle 601R31902−73 2.25 (57.15) M/F S−2236 ♦♦ A024 7002−73897391−73957397−74087410−74117413−74157417−74227424−74317433−74437445−74517453−74547456−7456

♦ Refer to SRM 51−21−16

♦♦ Refer to SRM 51−31−59

♣ Make from Tiernay Extrusion No. 60−17077

NOTE: All dimensions are in inches followed by millimeters in parenthesis.




Jun 10/2007

rsr5

2106

.dg,

rm

, 03/

04/0

6

8780

22

74

73

46

32

45

63

73

46

50

46

31

2124

5

8023

20

39

1980

5

48

6466

267

35

4468

1110

1

6

6

5

45

57

46

73

64

65

45

82

81

62

81

4630

46

45

60

37

61

27

56

FS311.75

FS347.25

1011

9

9

9

9

9

9

38

58

45

9


Passenger−Door Frame Structure − Structural IdentificationFigure 2 (Sheet 1)


Jun 10/2007

57

52

36

8990

9255

78

16

14

13 79 14 72

83

91

86

8371

54

78

59

29

53

51

26

4140

1843

3

424

75

33

77

FS311.75

FS347.25

34 25

28

15

84

8415

88

70

49

76

85

17

12

9

69

9

9

9

9

9

9

47

rsr5

2107

.dg,

rm

, 04/

04/0

6




Jun 10/2007

rsr5

2108

.dg,

rm

, 04/

04/0

6

93

94

95

96

97

98

99

100




Jun 10/2007

rsr5

2109

.dg,

rm

, 04/

04/0

6

102

103

104

105

106

107

108

109

110111 (OPP.)




Jun 10/2007



Assembly −Structure,Passenger Door

Phase IV − Door

601R31702 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

1

Corner, Bottom −Forward

601R319983−1 4.00 (101.6) Al Alloy7475−T7351

CMS 516−02 (BAMS516−002)

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8029

1A

Corner, Bottom −Fwd

601R319983−3 4.00 (101.6) Al Alloy7475−T7351

CMS 516−02 (BAMS516−002)

A025 8030−8400

2

Corner, Bottom −Aft

601R319983−2 4.00 (101.6) Al Alloy7475−T7351

CMS 516−02 (BAMS516−002)

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8029

2A

Corner, Bottom −Aft

601R319983−4 4.00 (101.6) Al Alloy7475−T7351

CMS 516−02 (BAMS516−002)

A025 8030−8400




Jun 10/2007



3

Intercostal, DD5 601R318075−3 Al Alloy 7475−T7351

CMS 516−02 (BAMS516−002)

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−7879

3AIntercostal, DD5 601R318075−5 Al Alloy 7475−T7351

CMS 516−02 (BAMS516−002)

A025 7880−8400

4

Bracket Assy 601R38921−13 M/F S3975T ♦♦ A024 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−79477949−7950

4A Bracket Assy 601R319076−1 M/F B0510038BA ♦♦ A024 7948−79487951−8400

5

Riser 600−31022−111 M/F S4897 ♦♦ A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



6

Intercostal 600−31902−257 0.050 (1.27) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

7

Intercostal DD1 600−31902−259 0.050 (1.27) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

8

Intercostal DD1A 600−31902−260 0.050 (1.27) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

9

Cleat 600−31902−269 0.050 (1.27) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



10

Clip 600−31902−275 0.063 (1.60) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8089

10A Clip 601R319034−1 M/F B0501140BD ♦♦ A025 8090−8400

11

Clip 600−31902−276 0.063 (1.60) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8089

11A Clip 601R319034−2 M/F B0501140BD ♦♦ A025 8090−8400

12

Cleat 600−31902−277 0.040 (1.02) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8029

12ACleat 601R38121−1 0.040 (1.02) Al Alloy

7075−T62

QQ−A−250/13

A023 8030−8074

12BCleat 601R38121−3 0.040 (1.02) Al Alloy

7075−T62

QQ−A−250/13

A023 8076−8400




May 10/2010



13

Cleat 600−31902−278 0.040 (1.02) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8029

13ACleat 601R38121−2 0.040 (1.02) Al Alloy

7075−T62 clad

QQ−A−250/13

A023 8030−8074

13BCleat 601R38123−1 0.040 (1.02) Al Alloy

7075−T62 clad

QQ−A−250/13

A023 8076−8400

14

Diaphragm 600−31902−283 0.050 (1.27) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8029

14ADiaphragm 601R38122−1 0.050 (1.27) Al Alloy

2024−T42

QQ−A−250/5

A023 8030−8400

15

Diaphragm 600−31902−284 0.050 (1.27) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8029

15ADiaphragm 601R38122−2 0.050 (1.27) Al Alloy

2024−T42

QQ−A−250/5

A023 8030−8400




Jun 10/2007



16

Bracket 600−31981−3 Al Alloy 7050−T73651

CMS 516−03 (BAMS516−003)

A024 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8074

16ABracket 600−38124−1 Al Alloy 7475−T7351

CMS 516−02 (BAMS516−002)

A024 8076−8400

17

Bracket 600−31981−4 Al Alloy 7050−T73651

CMS 516−03 (BAMS516−003)

A024 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8074

17ABracket 600−38124−2 Al Alloy 7475−T7351

CMS 516−02 (BAMS516−002)

A024 8076−8400

18

Bracket,Mounting Pulley

601R317106−1 Al Alloy 7475−T7351

CMS 516−02 (BAMS516−002)

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



19

Former,FS311.75

601R318031−1 0.063 (1.60) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−7894

19AFormer,FS311.75

601R318031−3 0.063 (1.60) Al Alloy7075−T62

QQ−A−250/13

A023 7895−8029

19BFormer,FS311.75

601R318031−5 0.063 (1.60) Al Alloy7075−T62

QQ−A−250/13

A023 8030−8400

20

Frame, FS320.00 601R318032−3 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−7879

20AFrame, FS320.00 601R318032−5 0.063 (1.60) Al Alloy

2024−T42

QQ−A−250/5

A023 7880−8400

21

Frame,FS338.963

601R318033−3 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8029

21AFrame,FS338.963

601R318033−5 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 8030−8400




Jun 10/2007



22

Former,FS347.27

601R318034−1 0.063 (1.60) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−7894

22AFormer,FS347.27

601R318034−3 0.063 (1.60) Al Alloy7075−T62

QQ−A−250/13

A023 7895−8029

22BFormer,FS347.27

601R318034−5 0.063 (1.60) Al Alloy7075−T62

QQ−A−250/13

A023 8030−8400

23

Former,FS323.363

601R318035−5 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

24

Former,FS335.763

601R318036−7 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



25

Former,FS338.963

601R318037−3 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

26

Former,FS320.163

601R318038−3 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

27

Intercostal DD2 601R318051−1 0.050 (1.27) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

28


QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



29


QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

30


QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

31


QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

32


QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



33


QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

34

Clip 601R318058−1 0.050 (1.27) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

35

Frame,FS327.763

601R318062−3 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

36

Former,FS329.50

601R318065−3 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



37

Intercostal DD1A 601R318066−1 0.050 (1.27) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

38


QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

39

Channel, Upper 601R318071−3 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

40

Hinge, Half 601R318073−5 Al Alloy 7475−T7351

CMS 516−02 (BAMS516−002)

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



41

Channel, Lower 601R318074−5 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

42

Former,FS329.41

601R318078−3 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

43

Intercostal, DD4 601R318081−1 0.050 (1.27) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

44

Intercostal DD7A 601R318083−1 0.050 (1.27) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



45

Bracket 601R318084−1 0.050 (1.27) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

46


QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

47

Plate, DoorCentering

601R318085−1 Al Alloy 7075−T651

QQ−A−250/12

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

48

Plate, DoorCentering

601R318085−2 Al Alloy 7075−T651

QQ−A−250/12

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



49

Frame, FS313.56 601R318086−1 0.050 (1.27) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

50

Former,FS329.41

601R318088−1 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−7859

50AFormer,FS329.41

601R318088−3 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7860−8400

51


QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−7879

51AIntercostal, DD5 601R318091−3 0.050 (1.27) Al Alloy

2024−T42

QQ−A−250/5

A023 7880−8029

51BIntercostal, DD5 601R318091−5 0.050 (1.27) Al Alloy

2024−T42

QQ−A−250/5

A023 8030−8400




Jun 10/2007



52

Former,FS329.50, DD2

601R318092−1 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

53


QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

54

Doubler, Pull inCam

601R318094−1 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

55

Doubler, Pull inCam

601R318094−2 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



56

Plate, Mounting 601R318129−3 Al Alloy 7475−T7351

CMS 516−02 (BAMS516−002)

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

56A

Plate, Mounting 601R318129−5 Al Alloy 7475−T7351

CMS 516−02 (BAMS516−002)

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

57

Angle 601R318231−1 Al Alloy 7475−T7351

CMS 516−03 (BAMS516−003)

A024 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−7939

57AAngle 601R318231−5 Al Alloy 7475−T7351

CMS 516−03 (BAMS516−003)

A024 7940−8400

58

Channel 601R318232−3 Al Alloy 7075−T7351

QQ−A−250/12

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−7939




Jun 10/2007



58AChannel 601R318232−5 Al Alloy 7075−T7351

QQ−A−250/12

A025 7940−8400

59


QQ−A−250/12

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−7939


QQ−A−250/12

A025 7940−8400

60


QQ−A−250/12

A024 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−7939


QQ−A−250/12

A024 7940−8400

61

Clip, DD1A 601R318277−1 0.050 (1.27) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



62

Angle, Support,Forward

601R318731−3 0.063 (1.60) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

63

Angle, Support,Aft

601R318732−3 0.063 (1.60) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

64

Wedge, Lower 601R318737−1 Al Alloy 2024−T351

QQ−A−250/4

A024 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−7509

64AWedge, Lower 601R318737−3 Al Alloy 2024−T351

QQ−A−250/4

A024 7510−7796

64BWedge, Lower 601R318738−1/

−2Al Alloy 2024−T351

QQ−A−250/4

A024 7797−7935

64CWedge, Lower 601R318738−3/

−4Al Alloy 2024−T351

QQ−A−250/4

A024 7936−8400




Jun 10/2007



65

Clip, Intercostal,DD7

601R318824−1 0.050 (1.27) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

66

Clip, Intercostal,DD7

601R318824−2 0.050 (1.27) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

67


QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

68


QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



69

Former,FS335.163

601R31902−15 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

70

Former,FS323.963

601R31902−16 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

71


QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

72


QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



73

Intercostal 601R31902−317 0.050 (1.27) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

74


QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

75


QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

76


QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



77

Target 601R31902−349 4130 Sheet Steel Cond. N

MIL−S−18729

D015 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

78

Deflector 601R31902−375 L−P−410 6/6 Nylon N/A 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

79

Deflector 601R31902−376 L−P−410 6/6 Nylon N/A 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

80

Strip 601R31902−383 0.050 (1.27) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



81


QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

82


QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

83

Diaphragm 601R31902−541 0.050 (1.27) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

84

Diaphragm 601R31902−542 0.050 (1.27) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



85


QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−7592

85ABracket 601R31902−555 0.050 (1.27) Al Alloy

2024−T42

QQ−A−250/5

A023 7593−8400

86


QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−7592

86ABracket 601R31902−556 0.050 (1.27) Al Alloy

2024−T42

QQ−A−250/5

A023 7593−8400

87

Member, Edge,Upper

601R31920−5 Al Alloy 7050−T7451

CMS 516−03 (BAMS)516−003

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−75307532−75347561−7561

87AMember, Edge,Upper

601R31920−7 Al Alloy 7050−T7451

CMS 516−03 (BAMS)516−003

A023 7531−75317535−75607562−8400




Jun 10/2007



88

Former,FS329.50

601R318065−4 0.063 (1.60) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

89

Gusset 601R318927−3 0.063 (1.60) Al Alloy7075−T62

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

90

Plate, CornerSupport

601R318928−1 0.080 (2.03) Al Alloy 7075−T6

QQ−A−250/13

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

91

Plate, Protector 601R318929−1 0.063 (1.60) Steel Sheet AMS5862

Cond. H−1000 15−5ph

S010 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



92

Bracket Assy 601R38921−13 Al Alloy 7075−T73511

QQ−A−200/111

M/F S3975T ♦♦

A024 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−79477949−7950

92A

Bracket Assy 601R319076−1 Al Alloy 7075−T73511

QQ−A−200/111

M/F S3975T ♦♦

A024 7948−79487951−8400

C

Handle, MountingAssembly

601R31708 N/A N/A 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−79477949−79557957−79577967−7967

93


QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



94


QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

95

Cover 601R317083−3 0.050 (1.27) Al Alloy 2024−T3

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

96

Angle, Inner 601R318072−1 0.050 (1.27) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

97

Angle 601R31908−9 0.050 (1.27) Al Alloy2024−T42

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



98


QQ−A−250/13

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

99


QQ−A−250/13

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

100


QQ−A−250/13

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

101 Not Used − − − −

DHandle, MountingAssembly

601R319050 N/A N/A 7956−79567958−79667968−8400

102

Cover, Handle 601R319051−1 Al Alloy 7475−T7351

CMS 516−02 (BAMS516−002)

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



103

Cover, Handle 601R319052−3 Al Alloy 7475−T7351

CMS 516−02 (BAMS516−002)

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

104

Panel, HandleMounting

601R319053−1 Al Alloy 7475−T7351

CMS 516−02 (BAMS516−002)

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

105

Panel, HandleMounting

601R319054−1 Al Alloy 7475−T7351

CMS 516−02 (BAMS516−002)

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

106

Angle, InnerHandle

601R319055−1 M/F B0501025AA ♦♦ A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



107

Angle, InnerHandle

601R319056−1 M/F B0501025AA ♦♦ A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

108

Bracket, InnerHandle

601R319057−1 0.050 (1.27) Al Alloy 2024−T3

QQ−A−250/5

A023 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

109

Bracket, InnerHandle

601R319058−3 M/F AMS−3301 ♦♦ E002 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400

110

Angle, Aft 601R319063−1 Al Alloy 7475−T7351

CMS 516−02 (BAMS516−002)

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400




Jun 10/2007



111

Angle, Forward 601R319069−1 Al Alloy 7475−T7351

CMS 516−02 (BAMS516−002)

A025 7390−73907396−73967409−74097412−74127416−74167423−74237432−74327444−74447452−74527455−74557457−8400


♦♦ Refer to SRM 51−31−59





Jun 10/2007

PASSENGER−DOOR FRAME STRUCTURE − REPAIRS

1. General

For repairs to the passenger−door frame structure, contact Bombardier Aerospace Regional Aircraft,Customer Support (refer to SRM51−13−01), except for the REOs listed below.

A. List of REOs

The repairs listed below are only applicable to this subject. Details of these repairs are found inappropriate chapters of the Structural Generic Repair Engineering Order (SGREO) Manual,CSP−A−092.

The SGREO Manual contains the latest issue of each repair. Repairs to an earlier issue remainvalid unless otherwise indicated on the current issue of the REO. Make sure that you record theissue of the REO that was used.

REO TITLE/DESCRIPTION EFFECTIVITY

601R−52−11−014 Plugging of tooling holes,passenger door sealing anddrainage.

601R−52−11−088 Repair to passenger door innerskin.

601R−52−11−090 Repair to passenger door,forward outer former.

601R−52−11−101 Temporary repair to passengerdoor, inner skin.

601R−52−11−102 Passenger door inner skinpuncture near FS 349.00.

601R−52−11−402 Repair to passenger doorforward/aft frame members,FS320.10 and FS338.90

601R−52−11−408 General repair to inner passengerdoor

601R−52−11−806 Deviation to REO601R−52−11−402



Mar 10/2006

PASSENGER−DOOR FITTINGS − ALLOWABLE DAMAGE

1. General

A. For the allowable damage limits for the passenger door fittings, contact Bombardier AerospaceRegional Aircraft, Customer Support (refer to SRM 51−13−01).



Feb 18/2003

PASSENGER−DOOR FITTINGS − REPAIRS

1. General

For repairs to the passenger door fittings, contact Bombardier Aerospace Regional Aircraft, CustomerSupport (refer to SRM 51−13−01), except for the REO’s listed below.

A. List of REO’s

The repairs listed below are only applicable to this subject. Details of these repairs are found inappropriate chapters of the Generic Repairs Engineering Orders (GREO) Manual, CSP−A−092.

REO ISSUE TITLE/DESCRIPTION EFFECTIVITY

601R−52−11−034 A Pivot fitting supportpassenger door.



Feb 18/2003

PASSENGER DOOR SKIN AND PLATING − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the passenger door skin and plating, refer to Figure 1.



Feb 18/2003

rsr5

2068

.dg,

pl/l

r, a

pr19

/200

7

FS310.00 FS349.00FS329.50

DATUM #1

DATUM #4

DATUM #7

FS310.00 FS349.00FS329.50

DATUM #1

DATUM #4

DATUM #7

VIEW LOOKING INBOARDON OUTER SKIN

2 1

3

4 5

3

LEGEND

1t = 0.040 in. (1.016 mm)

1t

1t 1t 1t 1t

1t

1t 1t 1t 1t

1t 1t

1t

1t 1t 1t 1t

1t

1t 1t 1t 1t

1t 1t

A

A

B

BVIEW LOOKING INBOARD

ON OUTER SKINB


Passenger Door Skin and Plating − Structural IdentificationFigure 1 (Sheet 1)


Jun 10/2007

rsr5

2073

.dg,

pl/l

r, a

pr19

/200

7

LEGEND

12

t = 0.040 in. (1.016 mm)t = 0.058 in. (1.473 mm)3t = 0.108 in. (2.743 mm)4t = 0.158 in. (4.013 mm)

FS310.00 FS349.00FS329.50

DATUM #1

DATUM #4

DATUM #7

FS310.00 FS349.00FS329.50

DATUM #1

DATUM #4

DATUM #7

VIEW LOOKING INBOARDON OUTER SKIN

876

1t 1t

1t 1t 1t 1t

1t

1t 1t 1t 1t

1t 1t

3

1t

3t

1t

1t 1t

2t

2t 1t 1t

1t 1t 1t 1t

4t

3t 3t

2t

A

B

A

B

BVIEW LOOKING INBOARD

ON OUTER SKINB




Jun 10/2007

rsr5

2074

.dg,

pl/l

r, a

pr19

/200

7

11

13

14

16

14

19

10

12

14

15

17

1418

920

20

21

22

C

C

D

D

11

13

14

16

14

10

12

14

15

17

14

9

TOOL FACE

25

21 20

20

22

23

D

E

E

2426

24

2426

F

FF

2525252525

252525

F

24

24




Jun 10/2007



— PassengerDoor StructureAssembly

601R31902

−351

7003−7038


601R31902

−427

7002−7002,7039−7050


601R31902

−441

7051−7055


601R31902

−469

7056−7209


601R31902

−515

7210−7228


601R31902

−519

7229−7323


601R31902

−545

7324−7389,7391−7395,7397−7408,7410−7411,7413−7415,7417−7422,7424−7431,7433−7443,7445−7451,7453−7454,7456−7456


Phase IV Door

601R31702

−5

7390−7390,7396−7396,7409−7409,7412−7412,7416−7416,7423−7423,7432−7432,7444−7444,7452−7452,7455−7455,7457−7530,7532−7534,7561−7561


Phase IV Door

601R31702

−9

7531−7531,7535−7560,7562−7659




Jun 10/2007




Phase IV Door

601R31702

−13

7660−8029


Phase IV Door

601R31702

−15

8030−8400

1 Outer Skin 601R31902

−331

0.063 (1.60) clad 2024−T3QQ−A−250/5 †

A110 7003−7038

2 Doubler 601R31902

−315

0.050 (1.27) clad 2024−T42QQ−A−250/5 †

A040 7003−7038

3 Doubler 601R31902

−95

0.050 (1.27) clad 2024−T42QQ−A−250/5 †

A048 7002−7389,7391−7395,7397−7408,7410−7411,7413−7415,7417−7422,7424−7431,7433−7443,7445−7451,7453−7454,7456−7456

4 Doubler 601R31902

−433

0.050 (1.27) clad 2024−T3QQ−A−250/5 †

A040 7002−7002,7039−7050


−431

0.063 (1.60) clad 2024−T3QQ−A−250/5 †

A110 7002−7002,7039−7050

6 Doubler 601R31902

−447

0.050 (1.27) clad 2024−T3QQ−A−250/5 †

A048 7051−7389,7391−7395,7397−7408,7410−7411,7413−7415,7417−7422,7424−7431,7433−7443,7445−7451,7453−7454,7456−7456




Jun 10/2007




−445

0.063 (1.60) clad 2024−T3QQ−A−250/5 †

A110 7051−7389,7391−7395,7397−7408,7410−7411,7413−7415,7417−7422,7424−7431,7433−7443,7445−7451,7453−7454,7456−7456


−5

0.160 (4.06) clad 2024−T3QQ−A−250/5 †♠

A116 7390−7390,7396−7396,7409−7409,7412−7412,7416−7416,7423−7423,7432−7432,7444−7444,7452−7452,7455−7455,7457−7680,7684−7689,7692−7823,7825−7826,7835−7838,7841−7841,7845−7845,7849−7849,7852−7852

8A Outer Skin 601R319066

−1

0.160 (4.06) clad 2024−T3QQ−A−250/5 †

A116 7681−7683,7690−7691,7824−7824,7827−7834,7839−7840,7842−7844,7846−7848,7850−7851,7853−8029

8B Outer Skin 601R319066

−5

0.160 (4.06) clad 2024−T3QQ−A−250/5 †

A116 8030−8064

8C Outer Skin 601R319066

−7

0.160 (4.06) clad 2024−T3QQ−A−250/5 †

A116 8065−8400

9 Inner Skin 601R31902

−319

0.040 (1.02) clad 7075−T6QQ−A−250/13 †

A023 7003−7038




Jun 10/2007



9A Inner Skin 601R31902

−407

0.040 (1.02) clad 7075−T6QQ−A−250/13 †

A023 7002−7002,7039−7050

9B Inner Skin 601R31902

−451

0.040 (1.02) clad 7075−T6QQ−A−250/13 †

A023 7051−7055

9C Inner Skin 601R31902

−481

0.040 (1.02) clad 7075−T6QQ−A−250/13 †

A023 7056−7228

9D Inner Skin 601R31902

−537

0.040 (1.02) clad 7075−T6QQ−A−250/13 †

A023 7229−7323

9E Inner Skin 601R31902

−547

0.040 (1.02) clad 7075−T6QQ−A−250/13 †

A023 7324−7389,7391−7395,7397−7408,7410−7411,7413−7415,7417−7422,7424−7431,7433−7443,7445−7451,7453−7454,7456−7456

9F Inner Skin 601R318024

−5

0.040 (1.02) clad 7075−T6QQ−A−250/13 †

A023 7390−7390,7396−7396,7409−7409,7412−7412,7416−7416,7423−7423,7432−7432,7444−7444,7452−7452,7455−7455,7457−7659

9G Inner Skin 601R318024

−7

0.040 (1.02) clad 7075−T6QQ−A−250/13 †

A023 7660−7859

9H Inner Skin 601R318024

−11

0.040 (1.02) clad 7075−T6QQ−A−250/13 †

A023 7860−8029

9J Inner Skin 601R318024

−13

0.040 (1.02) clad 7075−T6QQ−A−250/13 †

A023 8030−8400

10 Access Door 600−31902

−335

0.050 (1.27) clad 7075−T6QQ−A−250/13 †

A023 7002−8400

11 Access Door 601R31902

−217

0.050 (1.27) clad 7075−T62QQ−A−250/13 †

A023 7002−8400




Jun 10/2007




−77

0.050 (1.27) clad 7075−T62QQ−A−250/13 †

A023 7002−7055

12A Access Door 601R31902

−471

0.050 (1.27) clad 7075−T62QQ−A−250/13 †

A023 7056−7389,7391−7395,7397−7408,7410−7411,7413−7415,7417−7422,7424−7431,7433−7443,7445−7451,7453−7454,7456−7456

12B Access Door 601R318954

−1

0.050 (1.27) clad 2024−T42QQ−A−250/5 †

A023 7390−7390,7396−7396,7409−7409,7412−7412,7416−7416,7423−7423,7432−7432,7444−7444,7452−7452,7455−7455,7457−7859

12C Access Door 601R318954

−3

0.050 (1.27) clad 2024−T42QQ−A−250/5 †

A023 7860−8400


−327

0.050 (1.27) clad 7075−T62QQ−A−250/13 †

A023 7002−7055


−473

0.050 (1.27) clad 7075−T62QQ−A−250/13 †

A023 7056−7389,7391−7395,7397−7408,7410−7411,7413−7415,7417−7422,7424−7431,7433−7443,7445−7451,7453−7454,7456−7456




Jun 10/2007




−3

0.050 (1.27) clad 2024−T42QQ−A−250/5 †

A023 7390−7390,7396−7396,7409−7409,7412−7412,7416−7416,7423−7423,7432−7432,7444−7444,7452−7452,7455−7455,7457−8400


−295

0.050 (1.27) clad 7075−T6QQ−A−250/13 †

A023 7002−8400


−79

0.050 (1.27) clad 7075−T62QQ−A−250/13 †

A023 7002−7055


−475

0.050 (1.27) clad 7075−T62QQ−A−250/13 †

A023 7056−7389,7391−7395,7397−7408,7410−7411,7413−7415,7417−7422,7424−7431,7433−7443,7445−7451,7453−7454,7456−7456


−1

0.050 (1.27) clad 2024−T42QQ−A−250/5 †

A023 7390−7390,7396−7396,7409−7409,7412−7412,7416−7416,7423−7423,7432−7432,7444−7444,7452−7452,7455−7455,7457−8400


−80

0.050 (1.27) clad 7075−T62QQ−A−250/13 †

A023 7002−7055




Jun 10/2007




−476

0.050 (1.27) clad 7075−T62QQ−A−250/13 †

A023 7056−7389,7391−7395,7397−7408,7410−7411,7413−7415,7417−7422,7424−7431,7433−7443,7445−7451,7453−7454,7456−7456


−3

0.050 (1.27) clad 2024−T42QQ−A−250/5 †

A023 7390−7390,7396−7396,7409−7409,7412−7412,7416−7416,7423−7423,7432−7432,7444−7444,7452−7452,7455−7455,7457−8400


−327

0.050 (1.27) clad 7075−T6QQ−A−250/13 †

A023 7002−7055


−463

0.050 (1.27) clad 2024−T42QQ−A−250/5 †

A023 7056−8400


−83

0.050 (1.27) clad 7075−T62QQ−A−250/13 †

A023 7002−7055


−477

0.050 (1.27) clad 7075−T62QQ−A−250/13 †

A023 7056−7389,7391−7395,7397−7408,7410−7411,7413−7415,7417−7422,7424−7431,7433−7443,7445−7451,7453−7454,7456−7456


−81

0.050 (1.27) clad 7075−T62QQ−A−250/13 †

A023 7002−7055




Jun 10/2007




−479

0.050 (1.27) clad 7075−T62QQ−A−250/13 †

A023 7056−7389,7391−7395,7397−7408,7410−7411,7413−7415,7417−7422,7424−7431,7433−7443,7445−7451,7453−7454,7456−7456

20 Deflector 601R31902

−375, −376

0.375 (9.53) Nylon †† NA 7002−7002,7039−8400

21 Bracket 601R38921

−3

2.5 (63.50) ♠♠† A024 7002−7389,7391−7395,7397−7408,7410−7411,7413−7415,7417−7422,7424−7431,7433−7443,7445−7451,7453−7454,7456−7456

21A Bracket 601R38921

−15

2.5 (63.50) ♠♠† A024 7390−7390,7396−7396,7409−7409,7412−7412,7416−7416,7423−7423,7432−7432,7444−7444,7452−7452,7455−7455,7457−7947,7949−7950

21B Bracket 601R319076

−3

2.25 (57.15) ♠♠♠† A024 7948−7948,7951−8400

22 Bracket 601R38921

−11

2.5 (63.50) ♠♠† A024 7002−7002,7039−8400




Jun 10/2007



23 Plate 601R318928

−1

0.080 (2.03) clad 7075−T6QQ−A−250/13 †

A023 7390−7390,7396−7396,7409−7409,7412−7412,7416−7416,7423−7423,7432−7432,7444−7444,7452−7452,7455−7455,7457−8400

24 Cup Assembly 601R319023

−1, −4

† E212 7324−7389,7391−7395,7397−7408,7410−7411,7413−7415,7417−7422,7424−7431,7433−7443,7445−7451,7453−7454,7456−7456

24A Cup Assembly 601R319023

−3, −2

† E212 7390−7390,7396−7396,7409−7409,7412−7412,7416−7416,7423−7423,7432−7432,7444−7444,7452−7452,7455−7455,7457−7659

24B Cup Assembly 601R318972

−3, −4

Polyamide Nylon 6/6 perL−P−410

E002 7660−8400

25 Glass Fabric 601R319023 BAMS 18 Type II 7324−7659

26 Doubler 601R318972

−5, −6

0.032 (0.81) clad 2024−T3QQ−A−250/5 †

A023 7660−7859

♦ Refer to SRM 51−21−16.

— Item not shown

† Polyurethane topcoat color white number 17875 per Federal Standard 595.

†† Specification ASTM 5989−96.

♠ Chem−mill per MPS 186.




Jun 10/2007



♠♠ Make from S3975−T.

♠♠♠ Make from B0510038BA.

NOTE: All dimensions are given in inches followed by millimeters in parentheses.




Jun 10/2007

PASSENGER DOOR SKIN AND PLATING − ALLOWABLE DAMAGE

1. General

A. For the allowable damage limits for the passenger door skin and plating, refer to SRM 52−00−31.



Feb 18/2003

PASSENGER DOOR SKIN AND PLATING − REPAIRS

1. General

For repairs to the passenger door skin and plating, contact Bombardier Aerospace Regional Aircraft,Customer Support (refer to SRM 51−13−01), except for the REOs and repairs listed below.

A. List of REOs

The repairs listed below are applicable to this subject. Details of these repairs are found inappropriate chapters of the Structural Generic Repair Engineering Order (SGREO) Manual,CSP−A−092.



601R−52−11−024 Passenger door handle cutoutchamfer.

2. Replacement of Passenger Door Hinge (door section).

NOTE: Bombardier Aerospace recommends that all work be carried out by a well trained andexperience crew.

A. Consumable Materials

Reference Designation

liquid shim EA 934, Moldable CL 1, Grade 1 and 2

B. Job Set−up

(1) Remove the passenger door (refer to AMM 52−11−00).

(2) Place the door on a secure workbench.

(3) Get access to the hinge underside area inside the door as follows:

(a) Remove the handrails (refer to AMM 52−11−05).

(b) Remove all the steps (refer to AMM 52−11−04) .

(c) Remove or disconnect the passenger door handle and mechanism as necessary foraccess (refer to AMM 52−11−21).

(d) Remove the stair structure from the door (refer to SRM 52−12−55).

(e) Remove the fasteners as necessary and carefully release the inner door skin from thedoor structure.

(4) Inspect the area for possible damage or corrosion.

(5) Protect door from contamination.

(6) Remove FWD and AFT hinge fairings from the door.

(7) Manufacture Jig locator blocks as shown in Figure 201, sheet 1.

NOTE: Jig alignment block can be fabricated on site, using any metallic material, in orderto locate the new hinge from the removed hinge reference location points.

(8) Apply protective tape at the mating point of the jig locator blocks and the door outer skin toprotect the surface.



Jul 10/2006

(9) Mark off hinge location on the outer skin.

(10) Install the tooling pin using washers between the locator block and the hinge ends asfollows :

– Make sure the pin is protruding at least 9 in. (22.86 cm) into the lugs on both side of thehinge.

– Make sure there is no free play between the pin, hinge holes and locator holes.

(11) Hold the jig alignment block with quick cure epoxy (or equivalent) and clamps.

NOTE: Do not use excessive force on clamps in order to keep alignment.

(12) Cure with tooling pin installed.

(13) Back drill 2 holes in the jig locator blocks from existing fairing holes.

(14) Secure locator blocks with bolts, washers and nuts (any type).

(15) Remove the clamps

(16) Make sure that the tooling pin moves freely

(17) Remove the tooling pin.

C. Procedure

(1) Remove all fasteners common to the hinge.

(2) Carefully remove the hinge from the door.

(3) Remove and clean (refer to SRM 51−26−00) the liquid shim from the old hinge and retainfor future reference.

(4) Inspect the fastener holes.

(5) Position and secure the new hinge on the door.

(6) Re−install tooling pins.

(7) Make sure that the pin moves freely.

(8) Back drill five holes, equally spaced from the skin on the new hinge for each row as shownin Figure 201, sheet 2.

NOTE: Do not back drill any holes in the lower flange of the hinge at this stage.

(9) Remove and deburr the hinge as required.

(10) Apply release agent on the door outer skin surface and let dry.

(11) Apply liquid shim at mating surfaces as shown in Figure 201, sheet 3.

(12) Reinstall the hinge with tooling pin.

NOTE: Do not apply excessive pressure on the hinge, or the liquid shim will squeeze outtoo much.

(13) Install, finger tight only, five wing nuts, twist Clecos, or similar in the upper row of hinge.

(14) Let the liquid shim cure.

NOTE: If authorized, use a heat gun to accelerate cure time.

(15) Use a drill bushing to back drill all fastener holes from existing holes on to the outer flangeof hinge.

(16) If required, cut the flange of the old hinge and use as template for holes that are too difficultto reach from the inside of the door structure as follows:

– Secure template on the hinge with wing nuts.

– Use the drill bushing to spot drill on the new hinge.

NOTE: Do not drill through, the template is tapered and may cause misalignment ofholes.



Jul 10/2006

– Progressively open the holes to the final size.

– Periodically verify the alignment, hole roundness and tooling pin (freedom ofmovement).

(17) Countersink holes (refer to SRM 51−40−11) for installation of Hi−Lites.

(18) Wet install the Hi−Lites (refer to SRM 51−23−00 and SRM 51−42−21) .

(19) Back drill the solid rivet row through lower flange of hinge, if necessary use the template anddrill bushing to spot drill holes that are to difficult to reach from the underside of door.

(20) Wet install the solid rivets (refer to SRM 51−23−00 and SRM 51−42−06).

(21) Install the FWD and AFT hinge fairings on the door.

(22) Touch up as required (refer to SRM 51−25−00).

D. Close out

(1) Remove all tools, and unwanted materials from the work area.

(2) Attach the inner skin to the door structure.

(3) Install the stair structure on the door (refer to SRM 52−12−55).

(4) Install or connect the passenger door handle and mechanism as applicable (refer to AMM52−11−21).

(5) Install the steps (refer to AMM 52−11−04) .

(6) Install the passenger door (refer to AMM 52−11−00) .



Jul 10/2006

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JIGLOCATOR

BLOCKAFT

JIGLOCATOR

BLOCKFORWARD

TOOLING PIN

VIEW LOOKING INBOARD AT HINGE

WASHERSWASHER

AFT


Passenger Door Skin and Plating − RepairsFigure 201 (Sheet 1)


Jul 10/2006

rsr5

2104

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cc,

06/

01/0

6




Jul 10/2006

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ay24

/200

6

VIEW LOOKING AT CROSS SECTION OF PAX DOOR AND HINGE

DOORSTRUCTURE

LIQUIDSHIM

HINGE

OUTERFLANGE

LOWERFLANGE




Jul 10/2006

PASSENGER−DOOR AUXILIARY STRUCTURE − GENERAL

1. General

A. This section contains structural identification data and allowable damage limits for thepassenger−door auxiliary structure.


A. Stair Structure


B. Handrails


3. Allowable Damage

A. Stair Structure


B. Handrails




Feb 18/2003

PASSENGER DOOR STAIRS − STRUCTURAL IDENTIFICATION

1. General

A. For the structural identification of the passenger door stairs, refer as follows:

(1) Fixed Stair Assembly

Refer to Figure 1.

(2) Hinged Stair Panels

Refer to Figure 2.



Feb 18/2003

14

2419

228

8 22

223

3013

25

527

20

14

5

29

18

28

12

16

10

16

4

1

4

2532

34

33

16

14

114

12

3

2

10

419

21

14

2

15

2(TYPICAL)

26

13

31

rsr5

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.dg,

ss,

mar

23/2

01036


Fixed Stair Assembly−Structural IdentificationFigure 1 (Sheet 1)


Apr 10/2011

rsr5

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ps/

ss, j

an20

/201

1

3

5

6

7

8

10

11

12

13

14

1718

19

2021

25

28

2

2

3

3

3

5

7

8

8

12

13

13

14

28

25

29

30

2 (5 PLACES)

(2 PLACES) 2

2 (4 PLACES)

2 (5 PLACES)31

2 (4 PLACES)

2 (5 PLACES)

2 (5 PLACES)

(DOOR REF)

3 (4 PLACES)

2 (5 PLACES)

FWD

35


Fixed Stair Assembly−Structural IdentificationFigure 1 (Sheet 2)


Apr 10/2011

ITEM DESCRIPTION DRAWING MATERIAL REFERENCE

FINISHCODE

♦EFFECT−

IVITY

Stair Structure 601R31907

1 Tread 0.063 (1.60) clad 2024−T42 A023

2 Stiffener S−6665 extruded2024−T3511

A024

3 Support angle S−2175 extruded 2024−T42 A024

4 Anti−skid tread V−2500−GD plastic sheet ¶

5 Cleat 0.040 (1.02) clad 2024−T42 A023

— Packer 0.032 (0.81) clad 2024−T42 A023

— Packer 0.050 (1.27) clad 2024−T42 A023

6 Support Zee 0.050 (1.27) clad 2024−T4 A023

7 Shear clip 0.050 (1.27) clad 2024−T42 A023

8 Support angle S−2201 extruded2024−T3511

A024

9 Doubler 0.250 (6.35) nylon 6/6 sheet¶¶

E002

10 Doubler 0.050 (1.27) clad 2024−T42 A023

11 Support Tee 60−1900 extruded2024−T3511 ♠

A024

12 Attach angle 600−31907 60−10229 extruded2024−T3511 ♠

A024

13 Stiffener S−4883 formed 2024−T3 A023

14 Stiffener 0.040 (1.02) clad 2024−T42 A023

15 Stiffener Machined 2024 −T4 rolledbar

A024

16 Door 0.032 (0.81) clad 2024−T42 A023

17 Support angle 0.040 (1.02) clad 2024−T42 A023

18 Edge member 600−31907−225 0.040 (1.02) clad 2024−T42 A023 7003−7067,7069−7355,7357−7368

18A Edge member 600−31907−389 0.040 (1.02) clad 2024−T42 A023 7002,7356,7369−8990

19 Support 0.063 (1.60) clad 2024−T42 A023




Apr 10/2011


FINISHCODE

♦EFFECT−

IVITY

20 Cleat 0.040 (1.02) clad 2024−T42 A023

21 Shroud Organic fiber (Kevlar − 2plies) ♠♠

E102 •

22 Cover 0.050 (1.27) clad 2024−T42 A023

23 Retainer 0.050 (1.27) clad 2024−T42 A023

— Packer 0.100 (25.4) clad 2024−T42 A023

24 Base plate 0.050 (1.27) clad 2024−T42 A023

— Washer 0.080 Teflon ♠♠♠

25 Panel 0.032 (0.81) clad 2024−T42 A023

26 Support Zee 0.040 (1.02) clad 2024−T42 A023

— Packer 0.032 (0.81) clad 2024−T42 A023

27 Stiffener 0.050 (1.27) clad 2024−T42 A023

28 Angle 0.063 (1.60) clad 2024−T42 A023

29 Cleat 0.040 (1.02) clad 2024−T42 A023

30 Hand−rail support fitting 600−31955 Machined 2024−T3511extrusion (60−6480 ♠)

A024

31 Hand−rail support fitting 601R31954 Machined 2024−T3511extrusion (60−6480 ♠)

A024

32 Bracket 601R38629 S−2091 extruded 7075−T6 A024

33 Window 601R38630 0.063 (1.60) acrylic plastic † E002

34 Plate 601R38632 0.050 (1.27) clad 2024−T3 A023

— Lever 601R38646 Refer to the CMM (CSPA−033)

— Structure Assy, Stair 601R31707

35 Beam, Gas shock 601R318011− 1 3.00 (76.20) Al Alloy 7475−T7351 Plate ††

A025 †††

36 Beam, Gas shock 601R318011− 2 3.00 (76.20) Al Alloy 7475−T7351 Plate ††

A025 †††

— Item not shown

¶ Flexcon Co. Inc., Spencer, MA, U.S.A.

♦ Refer to 51−21−16.

¶¶ Specification L−P−410




Apr 10/2011


FINISHCODE

♦EFFECT−

IVITY

♠ Tiernay Metals

♠♠ Canadair Specification CMS 532−01, Type I.

• External surface only. Finish code on internal surface is E002.

♠♠♠ Specification AMS 3651

† Specification MIL−P−5425, Finish A

†† Specification CMS 516−02 (BAMS 516−002)

††† Effectivity: 7390, 7396, 7409, 7412, 7416, 7423, 7432, 7444, 7452, 7455, 7457−7999, 8000−8400


NOTE: A gloss−white (Federal Standard 595 color number 17875) polyurethane topcoat is applied on allinternal areas of the doors forward of FS621.00.

NOTE: Corrosion−inhibiting compound (Type I, Level 1 − refer to SRM 51−21−11) is applied over theprimer/paint finishes on the internal areas of the fixed stair assembly.




Apr 10/2011

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03/

10/0

0

4

12

112

8

15

5

2

1

1

10

9

13

7

5

6

4

142

1

11

1

12

8

3

−


Hinged Stair Panels – Structural IdentificationFigure 2


Feb 18/2003


FINISHCODE

♦

EF-FECT−IVITY

Hinged Stair Panels 600−31980

1 Facings 0.020 (0.51) clad 2024−T3 A110

2 Core 5052 aluminum honeycomb ¶ A002

3 Support 0.063 (1.60) clad 2024−T42 A023

4 Hinge MS20001P10 stock material X055

5 Hinge MS20001P5 stock material X055

6 Packer 0.032 (0.81) clad 2024−T3 A023

7 Packer 0.050 (1.27) clad 2024−T3 A023

8 Edge member S−6130 extruded 2024−T8311 A048

9 Edge member 0.063 (1.60) clad 2024−T42 A048

10 Zee member 0.020 (0.51) clad 2024−T3 A110

11 Bumper 0.125 (3.18) synthetic rubbersheet ¶¶

12 Anti−skid tread V−2500 plastic sheet ♠

13 Chamfered washer 0.063 (1.60) clad 2024−T3 (11places)

A023

14 Rod attachment fitting 600−31956 S−2270 extruded 2024−T4 ♠♠♠ A024

— Countersink inserts 402CA3−08 Potted insert ♠♠

— Flat−head inserts 404HA3−08 Potted insert ♠♠

¶ Specification MIL−C−7438, cell size = 3/16 inch (1.59 mm), density = 3.1 lbs/cubic foot (PCF), foilthickness = 0.001 inch (0.025 mm)

¶¶ Specification AMS 3209, Shore hardness 65 to 75

♠ Flexcon Co. Inc., Spencer MA, U.S.A.

♠♠ Delron Co.

♠♠♠ Refer to the Component Maintenance Manual (CMM) for fits, clearances and wear limits.

♦ Refer to 51−21−16.

— Item not shown.

NOTE: All dimensions are shown in inches followed by millimeters in parentheses.


Key to Figure 2


Feb 18/2003

PASSENGER DOOR STAIRS − ALLOWABLE DAMAGE

1. General

A. Find the allowable damage limits for the passenger door stairs as follows:

(1) Skin Panels

Refer to Figure 102, SRM 52−00−31.

(2) Formed, Extruded and Machined Parts


(3) Metal Honeycomb Panels

Allowable damage limits for the door stair honeycomb−panels are not available. Canadairwill supply damage limits as necessary.



Feb 18/2003

PASSENGER−DOOR STAIRS − REPAIRS

1. General

For repairs to the passenger door stairs, contact Bombardier Aerospace Regional Aircraft, CustomerSupport (refer to SRM 51−13−01), except for the REOs listed below.

A. List of REOs


The SGREO Manual contains the latest issue of each repair. Repairs to an earlier issue remainsvalid unless otherwise indicated on the current issue of the REO. Make sure that you record theissue of the REO that was used.


601R−52−11−022 Repair to passenger dooranti−slip walkway.

601R−52−11−082 Repair to passenger door stairangle.

601R−52−11−279 Repair to passenger door edgemember

601R−52−11−503 Temporary repair to passengerdoor stair aft drag angle

601R−52−11−513 Repair to passenger door stair aftdrag angle

601R−52−11−652 Repair to passenger door top,mid(s), lower mid, and bottomsteps

601R−52−11−665 Temporary repair to passengerdoor steps

601R−52−11−702 Repair to passenger door forwardand aft side panel



Mar 10/2006

PASSENGER DOOR HANDRAIL − STRUCTURAL IDENTIFICATION

1. General

Refer to Figure 1 for the structural identification of the passenger door handrail.



Feb 18/2003

rsr5

2021

, ja,

05/

09/0

0

3

14

15

12

4

5

4 58

79

10

5

13

4

6

10

2

51 2

6

11

10

13

10

97

8

12

15

2

14

3

4

11


Passenger Door Handrail – Structural IdentificationFigure 1


Feb 18/2003


FINISHCODE

♦EFFEC-TIVITY

Handrail Installation 600R31909

1 Cross tube 600−31967 7075−T6 tube, 1.5 (38.1) OD X0.095 (2.41) wall thickness ¶

A023

2 Bearing housing 600−31968 Machined 2024−T351 plate ¶¶ A024

3 Fitting 600−31927 Machined 2024−T351 plate A024

— Packer 600−31909 0.160 (4.06) clad 7075−T6 A023

4 Handrail tube 601R38580 6061−T62 tube, 1.62 (41.1) OD X0.058 (1.47) wall thickness ¶¶¶

♠

5 Fitting 601R38581 Machined 6061−T351 bar ♠♠

6 Tube 601R38583 7075−T6 tube, 1.62 (41.1) OD X0.083 (2.11) wall thickness ¶

A010

7 Fitting 601R38584 17−4PH CRES, Cond H1025 ‡ S021

8 Fitting 601R38585 Machined 7475−T7351 plate ‡‡¶¶

A012

9 Tube 601R38586 Machined 2024−T351 rod ♠♠ A010

— Link lever 601R38588 Refer to the CMM (CSP A−033)

10 Fitting 600−31826 Machined 7475−T7351 plate ‡‡ A024

11 Fitting 601R38593 Machined 7475−T7351 plate ‡‡¶¶

A012

12 Cover 601R38589 Fiberglass prepreg (5 plies) ‡‡‡ E100

13 Bracket 601R38591 Machined 2024−T351 rolled bar♠♠

A024

— Pad 0.063 (1.60) silicone rubber † E002

14 Actuating rod 601R38578 Machined 7475−T7351 plate ‡‡¶¶ ♠♠

A024

15 Clevis 601R38577 17−4PH CRES, Cond H1025 { S011

♦ Refer to 51−21−16.

— Item not shown.

¶ Specification WW−T−700/7.

¶¶ Refer to the Component Maintenance Manual (CMM) for fits, clearances and wear limits.

¶¶¶ Specification WW−T−700/6.




Jun 17/2003


FINISHCODE

♦EFFEC-TIVITY

♠ Nickel−plated 0.001 inch (0.025 mm) thick and then chromium−plated 0.002 inch (0.051 mm)thick on the outside surface (commercial quality plating).

♠♠ Shot peened.

‡ Specification AMS−5643.

‡‡ Specification CMS 516−02.

‡‡‡ Specification CMS 532−18, Style 181.

† Specification AMS−3302.

NOTES: All dimensions are in inches (millimeters) unless otherwise specified.

The cross tube is installed in the post assemblies with a retaining compound, SpecificationMIL−R−46082, Type I.




Jun 17/2003

PASSENGER DOOR HANDRAIL − ALLOWABLE DAMAGE

1. General

A. Find the allowable damage limits for the passenger−door handrail installation as follows:

(1) Machined Parts


(2) Fiberglass Laminate

Scratched paint or primer is the only allowable damage permitted on fiberglass laminateparts. If the damage has not gone through the paint or primer, there is no limit on theamount of scratch damage.

(3) Tubes

For allowable damage limits for the side post and handrail tubes, refer to Figure 101.



Feb 18/2003

DAMAGEDEPTH IN.

(MM)QUANTITY

OF DAMAGE REMARKS

Dents Thru 0.25(6.35)

No limit

Examine tube hinges for damage.

Make sure there is no effect on function.

Scratches

0.050 (1.27)max

Blend out scratches (refer to SRM 51−12−00).


Corrosion Remove corrosion (refer to SRM 51−21−06).


Cracks — — Contact Bombardier Aerospace Regional Aircraft,Customer Support (refer to SRM 51−13−01) .


Passenger Door Handrail Tubes – Allowable DamageFigure 101


Feb 18/2003

Passenger−Door Handrail − Repairs

1. General

A. For repairs to the passenger door handrail, contact Bombardier Aerospace Regional Aircraft,Customer Support (refer to SRM 51−13−01).



Feb 18/2003

EMERGENCY EXITS − GENERAL

1. General

A. This section contains structural identification data and allowable damage limits for the emergencyexits.


A. Overwing Emergency−Exit Doors


B. Crew Escape Hatch


3. Allowable Damage

A. Overwing Emergency−Exit Doors


B. Crew Escape Hatch




Feb 18/2003

EMERGENCY EXIT DOOR − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the emergency exit doors, refer to Figure 1.



Feb 18/2003

rsr5

2024

, lc/

ds, 0

4/08

/04

4

10 919

14 (12 PLACES)

13 (20 PLACES)

31

28

6

5

7

11 (2 PLACES)

15 (4 PLACES)

4

17 (2 PLACES)

20 (2 PLACES)9

4

16(6 PLACES)

12

18

A

A


Emergency Exit Door – Structural IdentificationFigure 1


Sep 28/2004

ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISHCODE

EFFEC-TIVITY

1 Skin, outer (chem−milled)

601R31123 0.050 / 0.100 (1.27 / 2.54) clad2024−T3

A115

2 Doubler, lipped 601R31123 0.040 (1.02) clad 2024−T42 A023 7003−7815

3 Skin, inner 601R31123 0.063 (1.60) clad 7075−T62 A023 7003−7815

4 Frame, door, outer 601R31123 0.050 (1.27) clad 7075−T62 A023 7003−7815

5 Former 601R31123 0.040 (1.02) clad 7075−T62 A023 7003−7815

6 Plate, end 601R31123 0.040 (1.02) clad 7075−T62 A023 7003−7815

7 Web 601R31123 0.040 (1.02) clad 7075−T62 A023 7003−7815

8 Surround 601R31123 0.050 (1.27) clad 7075−T62 A023 7003−7815

9 Retainer, Seal 601R31123 0.040 (1.02) clad 7075−T62 A023 7003−7815

10 Seal 601R31406 7003−7815

11 Gusset 601R31123 0.050 (1.27) clad 7075−T62 A023 7003−7815

12 Plate gusset 601R31123 0.040 (1.02) clad 7075−T62 A023 7003−7815

13 Cleats 601R31123 0.040 (1.02) clad 7075−T62 A023 7003−7815

14 Diaphragm 601R31123 0.040 (1.02) clad 7075−T62 A023 7003−7815

15 Bracket, attachment 601R31123 0.040 (1.02) clad 7075−T62 A023 7003−7815

16 Fitting, support 601R31123 2024−T4 QQ−A−225/6 A023 7003−7815

17 Panel, access 601R31123 0.040 (1.02) clad 7075−T62 A023 7003−7815

18 Packer 601R31123 0.063 (1.60) clad 7075−T62 A023 7003−7815

19 Splice 601R31123 0.050 (1.27) clad 7075−T62 A023 7003−7815

20 Angle, splice 601R31123 0.050 (1.27) clad 7075−T62 A023 7003−7815

— Shims 601R31123 0.050 (1.27) clad 7075−T62 A023 7003−7815

— Shim, peelable 601R38685 0.032 (0.81) Max MIL−S−22499COMP 3 Type 1 Class 1

S002 7816−8300

NOTE: All dimensions are in inches followed by millimetres in parenthesis.


Key to Figure 1


Sep 28/2004

OVERWING EMERGENCY EXIT DOORS − ALLOWABLE DAMAGE

CAUTION: ALWAYS REFER TO THE SUBJECT PAGE BLOCK 101−199 APPLICABLE TO A GIVENSTRUCTURAL ELEMENT FOR SPECIFIC ALLOWABLE DAMAGE LIMITS. IF THIS ISNOT DONE, IT IS POSSIBLE THAT YOU WILL USE INCORRECT DATA.

YOU MUST REFER TO THE CONTINUING AIRWORTHINESS INSPECTIONREQUIREMENTS TO DETERMINE IF ADDITIONAL DAMAGE TOLERANCEINSPECTIONS APPLY (REF. SRM 51−13−00).

1. General

The general allowable damage limits of 10% given in SRM 52−00−00 may not apply to this section.You must replace the general limits of 10% with the limits specified for each item identified in section 2below. For the allowable damage limits for any item not specified in section 2 below, contactBombardier Aerospace Regional Aircraft, Customer Support (refer to SRM 51−13−01).

CAUTION: MAKE SURE THAT THE REMOVED DAMAGE, INCLUDING ANY PREVIOUS DAMAGEREMOVAL, IS WITHIN ALLOWABLE LIMITS AT ANY SPECIFIC LOCATION. RECORDDAMAGE REMOVAL LOCATION.

2. Specific

A. Find the allowable damage limits for the overwing emergency exit doors as follows:

(1) Skin and Plating

Refer to SRM 52−00−31.

(2) Internal Structure


(3) For the allowable damage limits for the emergency exit door fittings and latch bolt, refer toFigure 101. These limits comply with the wear limits specified in Repair Engineering Order(REO) 601R−52−21−006 Revision NC and 601R−52−21−009 Revisison NC.



May 10/2010

rsr5

2003

.dg,

yf,

14/0

2/05

.

12

HINGE FITTING

0.020 in. (0.508 mm)

DEPTH DUE TO WEAR.

(REF)

FS449.85 FS461.50 FS473.15

WL88.733

D

D

B B

C

C

STOP FITTING(TYPICAL6 PLACES)

DOOR

FRAME STATION STOP FITTING PIN (REF)

A

A

VIEW LOOKING INBOARD

B B−

0.040 in.(1.02 mm)

C C− TYPICAL 2 PLACES

WL88.733

BL50.351

STGR8

5

4

3

D D− TYPICAL 2 PLACES

2

NOTES

Maximum permissible depth due to wear.

Touch up/finish damaged area AO23

1However, door must be rigged to achieveproper seating in fuselage.

per SRM 51−21−16.

2

1

ASSEMBLY

DOORASSEMBLY

DOORASSEMBLY

(REF)

(REF)

MAXIMUM PERMISSIBLE


Overwing Emergency Exit Door (Fittings and Latch Bolt) − Allowable DamageFigure 101 (Sheet 1)


Jul 10/2006

LIN

EIT

EM

RE

FE

RE

NC

E O

RIG

INA

L M

AN

UF

AC

TU

RE

S L

IMIT

S IN

INC

HE

S (

mm

)IN

−SE

RV

ICE

WE

AR

LIM

ITS

IN IN

CH

ES

(m

m)

DE

SC

RIP

-T

ION

PA

RT

NO

.

DIM

EN

SIO

NS

CL

EA

RA

NC

ED

IME

N−

SIO

NS

LIM

ITS

MA

XIM

UM

AL

LO

WA

BL

EC

LE

AR

AN

CE

—M

INM

AX

MIN

MA

X

1P

inM

S

2039

24C

19

O/D

0.30

90(7

.85)

0.31

10(7

.90)

0.00

15(0

.04)

0.00

40(0

.10)

No

wea

ral

low

ed

0.00

60 (

0.15

)2

Hin

gesu

ppor

tfit

ting

600−

3139

1

−1/

−2

I/D0.

3125

(7.9

4)0.

3130

(7.9

5)I/D

0.3

150

(8.0

0) M

ax§

3La

tch

bolt

600−

3139

5

−1

O/D

0.49

93(1

2.68

)0.

4997

(12.

69)

0.00

15(0

.04)

0.00

24(0

.06)

O/D

0.4

981

(12.

65)

Min

§§0.

0036

(0.

09)

4D

oor

latc

hfit

ting

600−

3159

6

−1/

−2

I/D0.

5012

(12.

73)

0.50

17(1

2.74

)I/D

0.5

029

(12.

77)

Max

§

5D

oor

fram

e la

tch

fittin

g

600−

3139

4

−1/

−2

I/D—

——

—N

o w

ear

expe

cted

§T

ouch

up

dam

aged

are

a fin

ish

code

S01

0 pe

r S

RM

51−

21−

16.

§§T

ouch

up

dam

aged

are

a fin

ish

code

A04

4 pe

r S

RM

51−

21−

16.


Overwing Emergency Exit Door (Fittings and Latch Bolt) − Allowable DamageFigure 101 (Sheet 2)


Jul 10/2006

Emergency Exit Door − Repairs

1. General

For repairs to the emergency exit door, contact Bombardier Aerospace Regional Aircraft, CustomerSupport (refer to SRM 51−13−01), except for the REOs listed below.

A. List of REOs




601R−52−21−019 Repair to overwing Eemergencyexit door Sseal



Mar 10/2006

CREW ESCAPE HATCH − STRUCTURAL IDENTIFICATION

1. General

A. For the structural identification of the crew escape hatch refer to Figure 1 and Figure 2.



Jun 10/2007

rsr5

2110

.dg,

rm

, 02/

02/0

7

1

2

3

4

5

6

7

8

9

1011

12

13

14

16

18

19

22

27

12

12

12

16

7

6

15

15

17

1759

10

11

19

14

23

1322

EFFECTIVITY: 7003 − 7521


Crew Escape−Hatch Structure − Structural IdentificationFigure 1 (Sheet 1)


Jun 10/2007

rsr5

2111

.dg,

rm

, 02/

02/0

7

3

4

6

7

14

16

17

23

25

26

2829

30

12

12

14

20

2021

21

27

24

24

5

23

16

20

20

18

6

7





Jun 10/2007

ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISHCODE♦ EFFECTIVITY

StructuralAssembly, Pilot’sEscape Hatch

600−33046 NA NA 7003−7521

1 Frame, Hatch, Aft 600−33046−11 0.040 (1.27) clad 2024−T42 A010 7003−7039

1A Frame, Hatch, Aft 600−33046−113 0.050 (1.27) clad 2024−T42 A010 7040−7521

2 Frame, Hatch,Fwd

600−33046−105 0.040 (1.27) clad 2024−T42 A010 7003−7038

2A Frame, Hatch,Fwd

600−33046−115 0.050 (1.27) clad 2024−T42 A010 7039−7521

3 Canted Rib, Aft 600−33046−13 0.050 (1.27) clad 7075−T6 A010 7003−7521

4 Canted Rib, Fwd 600−33046−101 0.050 (1.27) clad 7075−T6 A010 7003−7521

5 Intercostal 600−33046

−17, −18

0.040 (1.02) clad 7075−T6 A010 7003−7521


−19, −20

0.040 (1.02) clad 7075−T6 A010 7003−7521


−21, −22

0.040 (1.02) clad 7075−T6 A010 7003−7521

8 Diaphragm 600−33046

−89, −90

0.032 (0.81) clad 7075−T6 A010 7003−7521

9 Diaphragm 600−33046

−91, −92

0.032 (0.81) clad 7075−T6 A010 7003−7521

10 Cleat 600−33046

−93, −94

M/F S−2400−T6 extrusion A012 7003−7259

10A Cleat 600−33046

−135, −136

M/F S−2400−T6 extrusion A012 7260−7521

11 Cleat 600−33046

−95, −96

M/F S−2400−T6 extrusion A012 7003−7259

11A Cleat 600−33046

−127, −128

M/F S−2400−T6 extrusion A012 7260−7521

12 Fitting, StopSupport

600−33243−1 M/F S−6508−T extrusion A012 7003−7521

13 Platform, PivotMount

600−33046−55 0.040 (1.02) clad 7075−T6 A010 7003−7521

14 Angle, Splice 600−33046−29 0.040 (1.02) clad 7075−T6 A010 7003−7521




Jun 10/2007


15 Angle, Splice 600−33046−109 0.040 (1.02) clad 7075−T6 A010 7003−7521

16 Fitting, HingeSupport

600−33242−1 M/F S−6508−T A012 7003−7521

17 Strap 600−33046−99 0.050 (1.27) clad 7075−T6 A010 7003−7521

18 Strap 600−33046−37 0.050 (1.27) clad 7075−T6 A010 7003−7521

19 Cleat 600−33046

−23, −24

0.040 (1.02) clad 7075−T6 A010 7003−7259

19A Cleat 600−33046

−129, −130

0.040 (1.02) clad 7075−T62 A010 7260−7521

20 Gusset 600−33046−41 0.040 (1.02) clad 7075−T6 A010 7003−7521

21 Gusset 600−33046−43 0.040 (1.02) clad 7075−T6 A010 7003−7521

22 Bracket, PivotClosing

600−33046−53 0.040 (1.02) clad 7075−T6 A010 7003−7521

23 Bracket, Indicator 600−33046

−111, −112

0.040 (1.02) clad 7075−T62 A010 7003−7521

24 Doubler 600−33046

−97, −98

0.050 (1.27) clad 7075−T62 A010 7003−7521

25 Frame, InnerAngle, Aft

600−33046−59 0.040 (1.02) clad 2024−T42 A010 7003−7259

25A Frame, InnerAngle, Aft

600−33046−133 0.040 (1.02) clad 2024−T42 A010 7260−7521

26 Frame, InnerAngle, Fwd

600−33046−103 0.040 (1.02) clad 2024−T42 A010 7003−7259

26A Frame, InnerAngle, Fwd

600−33046−131 0.040 (1.02) clad 2024−T42 A010 7260−7521

27 Handle Assembly,Crew EscapeHatch

601R33050−1 NA NA 7003−7521

28 Skin, Outer 600−33046−107 0.063 (1.60) clad 2024−T42 A010 7003−7053

28A Skin, Outer 600−33046−117 0.063 (1.60) clad 2024−T42 A109 7054−7206

28B Skin, Outer 600−33046−125 0.063 (1.60) clad 2024−T42 A109 7207−7521

29 Seal 600−33203−3 silicone rubber NA 7003−7521

30 Angle, Seal 600−33046−33

−34

0.050 (1.27) clad 7075−T6 A010 7003−7521




Jun 10/2007


♦ Refer to 51−21−16





Jun 10/2007

rsr5

2112

.dg,

rm

, 02/

02/0

7


1

2

5

6

7

8

9

10

11

12

13

14

16

15

17

18

19

20

21

22

23

24

25

26

27

28

29

30

31

36

37

38

39

40

41

42

43

44

45

46

47

48

49

50

51

56

57

58

59

61

24

27

45

67

68

69 Hatch skin, seal and retainers added for clarity.

NOTE

3

4




Jun 10/2007

rsr5

2113

.dg,

rm

, 02/

02/0

7

3

4

28

29

32

33

34

3536

37

38

39

41

42

43

4445

52

53

54

55

56

57

56

60

64

65

6667

68

7071(OPP)

40

60

33

57

68


45

32

62

63




Jun 10/2007

ITEM DESCRIPTION DRAWING

MATERIAL

REFERENCEFINISHCODE♦ EFFECTIVITY

Structural Assembly,Pilot’s Escape Hatch

CC670−38002 NA NA 7522−8400

1 Frame, Outer CC670−38025−1

NHA: CC670−38002

CMS 516−03 AL Alloy7050−T7451

A025 7522−8400

2 Frame, Fwd CC670−38027−1

NHA: CC670−38002

0.050 (1.27)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400

3 Frame, Aft CC670−38028−1

NHA: CC670−38002

0.050 (1.27)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400

4 Diaphragm CC670−38029−1

NHA: CC670−38002

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400


NHA: CC670−38002

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400


NHA: CC670−38002

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400


NHA: CC670−38002

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400


NHA: CC670−38002

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400


NHA: CC670−38002

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400

10 Diaphragm, BL 4.73 CC670−38032−1

NHA: CC670−38002

0.032 (0.81)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400

11 Diaphragm, BL 4.73 CC670−38032−2

NHA: CC670−38002

0.032 (0.81)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400


NHA: CC670−38002

0.032 (0.81)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8079

12A Diaphragm CC670−38033−3

NHA: CC670−38002

0.032 (0.81)QQ−A−250/13 AL Alloy7075−T62

A023 8080−8400




Jun 10/2007


MATERIAL



NHA: CC670−38002

0.032 (0.81)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8079

13A Diaphragm CC670−38033−4

NHA: CC670−38002

0.032 (0.81)QQ−A−250/13 AL Alloy7075−T62

A023 8080−8400

14 Angle CC670−38034−1

NHA: CC670−38002

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400

15 Angle CC670−38034−2

NHA: CC670−38002

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400

16 Angle, BL 4.73 CC670−38035−1

NHA: CC670−38002

QQ−A−200/11 AL Alloy7075−T73511

A025 7522−8400

17 Angle, BL 4.73 CC670−38035−2

NHA: CC670−38002

QQ−A−200/11 AL Alloy7075−T73511

A025 7522−8400

18 Angle, BL 2.07 CC670−38036−1

NHA: CC670−38002

QQ−A−200/11 AL Alloy7075−T73511

A025 7522−8400

19 Angle, BL 2.07 CC670−38036−2

NHA: CC670−38002

QQ−A−200/11 AL Alloy7075−T73511

A025 7522−8400

20 Fitting, Stop SupportFwd

CC670−38037−1

NHA: CC670−38002

CMS 516−02 AL Alloy7475−T7351

A025 7522−8400

21 Fitting, Stop SupportFwd

CC670−38037−2

NHA: CC670−38002

CMS 516−02 AL Alloy7475−T7351

A025 7522−8400

22 Bracket, Mechanism CC670−38039−1

NHA: CC670−38002

0.40 (1.02)QQ−A−200/13 AL Alloy7075−T62

A023 7522−8400

23 Bracket, Mechanism CC670−38039−2

NHA: CC670−38002

0.40 (1.02)QQ−A−200/13 AL Alloy7075−T62

A023 7522−8400

24 Splice, Side CC670−38040−1

NHA: CC670−38002

0.050 (1.27)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8400

25 Splice, Aft CC670−38042−1

NHA: CC670−38002

0.050 (1.27)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8400




Jun 10/2007


MATERIAL


26 Splice, Fwd CC670−38044−1

NHA: CC670−38002

0.050 (1.27)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8400

27 Fitting, HingeBackup

CC670−38046−1

NHA: CC670−38002

CMS 516−02 AL Alloy7475−T7351

A025 7522−8400

28 Strap, Fwd CC670−38048−1

NHA: CC670−38002

0.050 (1.27)QQ−A−250/13 AL Alloy7075−T6

A023 7522−8400

29 Strap, Aft CC670−38049−3

NHA: CC670−38002

0.063 (1.60)QQ−A−250/13 AL Alloy7075−T6

A023 7522−8400

30 Angle CC670−38050−1

NHA: CC670−38002

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400

31 Angle CC670−38050−2

NHA: CC670−38002

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400

32 Gusset CC670−38051−1

NHA: CC670−38002

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T6

A023 7522−8400

33 Gusset CC670−38052−1

NHA: CC670−38002

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T6

A023 7522−8079

33A Gusset CC670−38052−3

NHA: CC670−38002

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T6

A023 8080−8400

34 Strap, Int. Handle CC670−38055−3

NHA: CC670−38002

0.090 (2.29)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8079

34A Strap, Int. Handle CC670−38055−5

NHA: CC670−38002

0.090 (2.29)QQ−A−250/5 AL Alloy2024−T42

A023 8080−8400

35 Strap, Int. Handle CC670−38055−4

NHA: CC670−38002

0.090 (2.29)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8079

35A Strap, Int. Handle CC670−38055−6

NHA: CC670−38002

0.090 (2.29)QQ−A−250/5 AL Alloy2024−T42

A023 8080−8400

36 Bracket, FurnishingFwd Ctr

CC670−38057−5

NHA:CC670−38002−1

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8007,8009




Jun 10/2007


MATERIAL


36A Bracket, FurnishingFwd Ctr

601R412907−1

NHA: 601R412900

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 8008,8010−8069

36B Bracket, FurnishingFwd Ctr

601R412907−3

NHA: 601R412900

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 8070−8400

37 Bracket, FurnishingFwd Outbd

CC670−38058−5

NHA:CC670−38002−1

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8007,8009

37A Bracket, FurnishingFwd Outbd

601R412908−1

NHA: 601R412900

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 8008,8010−8400

38 Bracket, FurnishingFwd Outbd

CC670−38058−6

NHA:CC670−38002−1

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8007,8009

38A Bracket, FurnishingFwd Outbd

601R412908−2

NHA: 601R412900

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 8008,8010−8400

39 Bracket, FurnishingSide Fwd

CC670−38059−3

NHA:CC670−38002−1

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8007,8009

39A Bracket, FurnishingSide Fwd

601R412903−1

NHA: 601R412900

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 8008,8010−8400

40 Bracket, FurnishingSide Fwd

CC670−38059−4

NHA:CC670−38002−1

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8007,8009

40A Bracket, FurnishingSide Fwd

601R412903−2

NHA: 601R412900

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 8008,8010−8400

41 Bracket, FurnishingSide Aft

CC670−38095−1

NHA:CC670−38002−1

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8007,8009

41A Bracket, FurnishingSide Aft

601R412904−1

NHA: 601R412900

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 8008,8010−8400

42 Bracket, FurnishingSide Aft

CC670−38060−4

NHA:CC670−38002−1

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8007,8009




Jun 10/2007


MATERIAL


42A Bracket, FurnishingSide Aft

601R412904−2

NHA: 601R412900

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 8008,8010−8400

43 Bracket CC670−38061−5

NHA:CC670−38002−1

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8007,8009

43A Bracket 601R412905−3

NHA: 601R412900

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 8008,8010−8400

44 Bracket CC670−38061−5

NHA:CC670−38002−1

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8007,8009

44A Bracket 601R412905−4

NHA: 601R412900

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T42

A023 8008,8010−8400

45 Mount, Isolator SL2337−08

NHA: 601R2900

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400

46 Angle, Mechanism CC670−38064−1

NHA: 601R2900

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400

47 Angle, Mechanism CC670−38064−2

NHA: 601R2900

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400

48 Fitting, Stop Aft CC670−38066−1

NHA: CC670−38002

CMS 516−02 AL Alloy7475−T7351

A025 7522−8400

49 Fitting, Stop Aft CC670−38066−2

NHA: CC670−38002

CMS 516−02 AL Alloy7475−T7351

A025 7522−8400

50 Angle, MechanismBracket

CC670−38069−1

NHA: CC670−38002

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400

51 Angle, MechanismBracket

CC670−38069−2

NHA: CC670−38002

0.040 (1.02)QQ−A−250/13 AL Alloy7075−T62

A023 7522−8400

52 Bracket CC670−38070−3

NHA: CC670−38070

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T3

A023 7522−8400

53 Bracket CC670−38070−4

NHA: CC670−38070

0.040 (1.02)QQ−A−250/5 AL Alloy2024−T3

A023 7522−8400




Jun 10/2007


MATERIAL


54 Doubler CC670−38079−1

NHA: CC670−38002

0.050 (1.27)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8400

55 Doubler CC670−38079−2

NHA: CC670−38002

0.050 (1.27)QQ−A−250/5 AL Alloy2024−T42

A023 7522−8400

56 Packer, Stop Fitting CC670−38080−1

NHA: CC670−38002

0.063 (1.60)QQ−A−250/5 AL Alloy2024−T3

A023 7522−8400

57 Packer, Hinge Fitting CC670−38081−1

NHA: CC670−38002

0.063 (1.60)QQ−A−250/5 AL Alloy2024−T3

A023 7522−8400

58 Packer, Stop Fitting CC670−38082−1

NHA: CC670−38002

0.063 (1.60)QQ−A−250/5 AL Alloy2024−T3

A023 7522−8400

59 Handle Assy,Cockpit EscapeHatch

601R33050−1

NHA: CC670−38002

NA 7522−8400

60 Plate, Base 600−33272−5

NHA: 600−33272

SAE 4130 SteelMIL−S−18729 COND N

D001 7522−8400

61 Plate, Base 600−33273−5

NHA: 600−33273

SAE 4130 SteelMIL−S−18729 COND N

D001 7522−8400

62 Angle, Iml Fwd CC670−38077−1

NHA: CC670−38002

CMS 516−02 AL Alloy7475−T7351

A025 7522−8400

63 Angle, Iml Fwd CC670−38077−2

NHA: CC670−38002

CMS 516−02 AL Alloy7475−T7351

A025 7522−8400

64 Angle, Iml Aft CC670−38078−1

NHA: CC670−38002

CMS 516−02 AL Alloy7475−T7351

A025 7522−8400

65 Angle, Iml Aft CC670−38078−2

NHA: CC670−38002

CMS 516−02 AL Alloy7475−T7351

A025 7522−8400

66 Skin, Pilot EscapeHatch

CC670−38020−1 0.063 (1.60)QQ−A−250/5 AL Alloy2024−T3

A116 7522−7720,7722, 7730,7882−8007,8009

66A Skin, Pilot EscapeHatch

CC670−38020−3 0.063 (1.60)QQ−A−250/5 AL Alloy2024−T3

A116 7721,7723−7729,7731−7881,8008,8010−8400




Jun 10/2007


MATERIAL


67 Seal CC670−38022−1 AMS3345 E002 7522−8400

68 Retainer, Seal CC670−38023−3 CMS 516−02 AL Alloy7475−T7351

A025 7522−8400


A025 7522−8400


A025 7522−8400


A025 7522−8400


♦ Refer to 51−21−16




Jun 10/2007

CREW ESCAPE HATCH − ALLOWABLE DAMAGE

1. General

A. Find the allowable damage limits for the crew escape hatch as follows:





(3) Fittings




Feb 18/2003

CARGO DOOR − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the cargo door, Figure 1.



Feb 18/2003

rsr5

2028

.dg,

lc/lr

, 10/

02/0

5

1 2

3

5

7

8

9

11

12

15

18

19

22

23

24

15

2

29303132(REF)

25262728(REF)

SEAL(REF)

A

B

B

29

2631

27

SEAL(REF)

A

30

28

32

25

EFFECTIVITY:7465 − 8400


Cargo Door – Structural IdentificationFigure 1 (Sheet 1)


Apr 10/2005

rsr5

2090

.dg,

ds/

lr, 1

0/02

/05

C

D − D

CD

D

4

6

1013

1416

20

21

16

20

17

SEAL

CARGO DOOR(REF)

FILLETSEAL

SEALRETAINER

D − D

CARGO DOOR(REF)

B




Cargo Door – Structural IdentificationFigure 1 (Sheet 2)


Apr 10/2005


EFFEC-TIVITY

1 Skin, inner 601R35027 0.040 (1.02) clad 7075−T63 A023


601R35027 0.050 / 0.100 (1.27 / 2.54) clad2024−T3

A116

3 Frame, surround 601R35027 0.063 (1.60) clad 2024−T42 A023

4 Member, vertical 601R35027 0.040 (1.02) clad 2024−T42 A023

5 Intercostal 601R35027 0.063 (1.60) clad 2024−T42 A023

6 Angle 601R35027 0.050 (1.27) clad 2024−T42 A023

7 Doubler 601R35027 0.063 (1.60) clad 7075−T6 A023

8 Strap 601R35027 0.100 (2.54) clad 7075−T62 A023

9 Angle, surround 601R35027 0.063 (1.60) clad 2024−T42 A023

10 Clip 601R35027 0.050 (1.27) clad 7075−T62 A023

11 Strap 601R35027 0.100 (2.54) clad 7075−T6 A023

12 Strap 601R35027 0.125 (3.18) clad 2024−T3 A023

13 Angle 601R35027 0.050 (1.27) clad 7075−T62 A023

14 Gusset 601R35027 0.050 (1.27) clad 7075−T62 A023

15 Angle 601R35027 0.080 (2.03) clad 7075−T62 A023

16 Angle 601R35027 0.080 (2.03) clad 7075−T62 A023

17 Angle 601R35027 0.050 (1.27) clad 2024−T42 A023

18 Member, transv. lower 601R35027 0.063 (1.60) clad 2024−T42 A023

19 Member, transv. upper 601R35027 0.063 (1.60) clad 2024−T42 A023

20 Angle 601R35027 0.063 (1.60) clad 2024−T42 A023

21 Channel, support 601R35027 0.063 (1.60) clad 7075−T62 A023

22 Splice 601R35027 0.063 (1.60) clad 2024−T42 A023

23 Stiffener 601R35027 0.063 (1.60) clad 2024−T42 A023

24 Doubler 601R35027 0.063 (1.60) clad 2024−T42 A023

25 Retainer Seal, Lower CC670−38742

−1

0.050 (1.27) Al Alloy 6061−T6†

A023 7465−8400

26 Retainer Seal, Upper CC670−38741

−1

0.050 (1.27) Al Alloy 6061−T6†

A023 7465−8400




Apr 10/2005


EFFEC-TIVITY

27 Retainer Seal, Forward CC670−38739

−3

0.050 (1.27) Al Alloy 6061−T6†

A023 7465−8400

28 Retainer Seal, Aft CC670−38740

−3

0.050 (1.27) Al Alloy 6061−T6†

A023 7465−8400

29 Retainer Corner Seal,Upper Forward

CC670−38743

−1

0.050 (1.27) Al Alloy 6061−T6†

A023 7465−8400

30 Retainer Corner Seal,Lower Forward

CC670−38744

−1

0.050 (1.27) Al Alloy 6061−T6†

A023 7465−8400

31 Retainer Corner Seal,Upper Aft

CC670−38745

−1

0.050 (1.27) Al Alloy 6061−T6†

A023 7465−8400

32 Retainer Corner Seal,Lower Aft

CC670−38746

−1

0.050 (1.27) Al Alloy 6061−T6†

A023 7465−8400

† Specification AMS QQ−A−250/11.


A gloss−white (Federal Standard 595 color number 17875) polyurethane topcoat is applied to all structuralparts below WL 85.70 and between FS169.00 and FS621.00 (includes the internal surfaces of the skins).




Apr 10/2005

CARGO DOOR − ALLOWABLE DAMAGE

1. General

A. Find the allowable damage limits for the cargo door as follows:



(2) Frame Structure


(3) Fittings




Feb 18/2003

CARGO DOOR − REPAIRS

1. General

For repairs to the cargo door, contact Bombardier Aerospace Regional Aircraft, Customer Support(refer to SRM51−13−01), except for the REO’s listed below.

A. List of REO’s

The repairs listed below are only applicable to this subject. Details of these repairs are found inappropriate chapters of the Generic Repair Engineering Orders (GREO) Manual, CSP−A−092.

REO ISSUE TITLE/DESCRIPTION EFFECTIVITY

601R−52−31−004 A Damaged stop boltbracket assembly incargo door − repair



Feb 18/2003

CARGO DOOR STEP PLATE − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the cargo door step plate, refer to Figure 1.



Feb 18/2003

rsr5

2030, lc

, 19/0

5/9

9

6

42

1

8

1

601R31668(REF)

601R35160(REF)

5

11

10

9

3(3 PLACES)


Cargo Door Step Plate – Structural IdentificationFigure 1


Feb 18/2003


EFFEC-TIVITY

1 Clip 601R35205 0.063 (1.60) clad 2024−T42 A023

2 Shim, laminated 601R35205 0.050 (1.27) MIL−S−22499 cmop1, type 1, class 1

X070

3 Clip 601R35205 0.032 (.81) clad 2024−T42 A023

4 Latch 601R35205 M / F Hartwell H1000S2B5NR X110

5 Plate, Step 601R35205 0.080 (2.03) clad 7075−T62 A023

6 Bracket 601R35205 0.050 (1.27) 304 stainless steelannealed MIL−S−4043

X110

7 Hinge assembly 601R35205

8 Support 601R35205 0.500 (12.7) M / F 6/6 nylon barfed spec L−P−410A

9 Spacer 601R35205 NAS 43HTO−31A

10 Spring 601R35205 S 1443

11 Hinge 601R35205 M / F MS 20001PH6−1439 X070

NOTE: All are dimensions in inches followed by millimetres in parenthesis.


Key to Figure 1


Feb 18/2003

CARGO DOOR STEP PLATE − ALLOWABLE DAMAGE

1. General

A. For the allowable damage limits for the cargo door step plate, refer to SRM 52−00−00, PageBlock 101−199.



Feb 18/2003

CARGO DOOR STEP PLATE − REPAIRS

1. General

A. For repairs to the cargo door step plate, contact Bombardier Aerospace Regional Aircraft,Customer Support (refer to SRM 51−13−01).



Feb 18/2003

SERVICE DOORS − GENERAL

1. General

A. This section contains structural identification data and allowable damage limits for the servicingand equipment access doors.


A. Service Door (Galley)


B. Main−Avionics Compartment Door


C. Aft Equipment−Compartment Door


D. Nose−Equipment Access Doors


E. Air−Driven Generator Door

Refer to SRM 52−44−37, Page Block 1−99

F. Servicing Doors


3. Allowable Damage

A. Service Door (Galley)


B. Main−Avionics Compartment Door


C. Aft Equipment−Compartment Door


D. Forward Equipment−Compartment Access Doors


E. Air−Driven Generator Door


F. Servicing Doors




Feb 18/2003

SERVICE DOOR − GENERAL

1. General

A. This section contains structural identification data and allowable damage limits for the servicedoor structure.


A. Skin and Frame Structure


B. Fittings


3. Allowable Damage

A. Skin and Internal Structure


B. Fittings




Feb 18/2003

SERVICE DOOR SKIN AND FRAME STRUCTURE − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the service door skin and framing, refer to Figure 1.



Feb 18/2003

rsr5

2032, lc

, 19/0

5/9

9

10

2

11

19

18

3

1

20

13

12

1415

172

5 (9 PL)

6 (5 PL)

4 (19 PL)

9 (4 PL)

8 (14 PL)

21 (4 PL)

22 (2 PL) 23 (2 PL)

12

7 (2 PL)

16


Service Door Skin and Frame Structure – Structural IdentificationFigure 1


Feb 18/2003


EFFEC-TIVITY


2 Pan 601R38304 0.063 (1.60) clad 7075−T62 A023

3 Pan 601R38304 0.063 (1.60) clad 7075−T62 A023

4 Angle 601R38304 0.063 (1.60) clad 7075−T62 A023


6 Former 601R38304 0.063 (1.60) clad 7075−T62 A023

7 Channel 601R38304 0.063 (1.60) clad 7075−T62 A023

8 Filler 601R38304 0.063 (1.60) clad 2024−T3 A023

9 Splice 601R38304 0.063 (1.60) clad 7075−T62 A023

10 Angle, seal support 601R38304 0.040 (1.02) clad 2024−T42 A023

11 Filler, radius 601R38304 0.100 (2.54) clad 2024−T3 A023

12 Panel, access 601R38304 0.063 (1.60) clad 2024−T3 A023

13 Panel, access 601R38304 0.063 (1.60) clad 2024−T42 A023

14 Doubler, inner 601R38304 0.063 (1.60) clad 7075−T6 A023

15 Window, indicator 601R38304 0.050 (1.27) clad 2024−T42 A023


17 Clip 601R38304 0.080 (2.03) clad 7075−T62 A023

18 Doubler, outer 601R38304 0.050 (1.27) clad 2024−T3 A048


601R38304 0.048 / 0.063 (1.22 / 1.60) clad2024−T3

A110

20 Zee 601R38304 0.063 (1.60) clad 7075−T62 A023 −381

20 Zee 601R38304 M /F S−6676−T A024 −1,−361−373

NOTEs: All dimensions are in inches followed by millimetres in parenthesis.


Key to Figure 1


Feb 18/2003

SERVICE DOOR SKIN AND FRAME STRUCTURE − ALLOWABLE DAMAGE

1. General

A. Find the allowable damage limits for the service door skin and frame structure as follows:



(2) Formed, Extruded and Machined Parts




Feb 18/2003

SERVICE DOOR SKIN AND FRAME STRUCTURE − REPAIRS

1. General

For repairs to the service door, contact Bombardier Aerospace Regional Aircraft, Customer Support(refer to SRM 51−13−01), except for the REOs listed below.

A. List of REOs




601R−52−41−004 Damage to Service Door Seal −Repair



Mar 10/2006

SERVICE DOOR FITTINGS − STRUCTURAL IDENTIFICATION

1. General

A. For the structural identification of the service door fittings, refer to Figure 1.



Feb 18/2003

rsr5

2035

, ng,

03/

10/0

0

6

4

3

14

15

12

2

11

10

5

8

13

10

9

7

1

The structure is symmetrical aroundthe centerline, unless shown differently.

NOTE


Service Door Fittings – Structural IdentificationFigure 1


Feb 18/2003


FINISHCODE

♦EFFEC-TIVITY

Service Door Assembly 601R38302

1 Door stabilizer fitting 601R38425 Machined 7050−T7451 plate ¶ ¶¶ A024

— Laminated shim 601R38418 0.063 (1.60) shim stock § D003

2 Support fitting 601R38571 Machined 7050−T7451 plate ¶ ¶¶ A024


3 Door stop fitting 601R38417 CRES, PH13 8Mo † ‡ SO24

4 Roller fitting 601R38420 Machined SAE 4140 steel †† D010


5 Pivot fitting 601R38423 Machined 7050−T7451 plate ¶ ¶¶‡

A025


6 Backup fitting 601R38574 Machined 7050−T7451 plate ¶ A024

— Radius filler 601R38304 0.100 (2.54) clad 2024−T3 A023

7 Back−up fitting 601R38433 Machined 7050−T7451 plate ¶ ‡ A024

— Laminated shim 601R38418 0.093 (2.36) stock § D003

8 Backup fitting 601R38422 Machined 7050−T7451 plate ¶ ‡ A024




— Laminated shim 0.080 (2.03) shim stock § D003

11 Roller fitting 601R38428 Machined SAE 4140 steel †† ¶¶ D010


12 Support fitting 601R38508 Machined 7050−T7451 plate ¶ A024


— Laminated shim 0.063 (1.60) shim stock § D003

13 Backup fitting 601R38572 Machined 7050−T7451 plate ¶ A024


14 Pin guide 601R38688 Machined 7050−T7451 plate ¶ ¶¶ A024





Feb 18/2003


FINISHCODE

♦EFFEC-TIVITY

— Handle assembly 601R38305 Refer to the CMM (CSP A−033)‡‡

— Door mechanismassembly

601R38306 Refer to the CMM (CSP A−033)

— Uplock installation 601R38721 Refer to the CMM (CSP A−033)

15 Support fitting 601R38495 Machined 7050−T7451 plate ¶ ¶¶ A024


¶ Specification CMS 516−03.

¶¶ For fits and clearances, and wear limits, refer to the Component Maintenance Manual (CMM).

‡ Shot peened.

‡‡ Hartwell Part No. H3412−1.

§ Specification MIL−S−22499, Comp. 1, Type I, Class 1.

† Specification AMS 5629, Cond. H1050.

†† Specification MIL−S −5626, HT 160−180 ksi (1103−1241 MPa).

— Not shown.


NOTES: A gloss−white (Federal Standard 595 color number 17875) polyurethane topcoat is applied on allinternal areas of the doors forward of FS 621.00.

Corrosion−inhibiting compound (Type I, Level 1 − refer to SRM 51−21−11) is applied over theprimer/paint finishes on the internal areas of the service door assembly.

All dimensions are in inches (millimeters) unless otherwise specified.

Refer to SRM 53−21−27 for the mating fitting components on the fuselage.




Jun 17/2003

SERVICE DOOR FITTINGS − ALLOWABLE DAMAGE

1. General

A. For the allowable damage limits for the service door fittings, refer to SRM 52−00−27.



Feb 18/2003

MAIN AVIONICS DOOR − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the main avionics door, refer to Figure 1.



Feb 18/2003

rsr5

2038

.dg,

lc/lr

, feb

20/2

006

A

36

5

4

1

2

3

8

10

9

9

11

10

13

13

14

15

16

17

18

19

23

22

21

20

25

24

27

28

29

30

31

32

33

3334

34

35

35

26

19

7

6

15

12

37

38

39

Outer skin omitted for clarity.

NOTE

A

B

B

40


Main Avionics Compartment Door – Structural IdentificationFigure 1 (Sheet 1)


Jul 10/2006

rsr5

2039

.dg,

lr, f

eb20

/200

6

VIEW LOOKING OUTBOARDON OUTER SKIN

t2

42

41

C

C

t2

t2

t2

t2 t2 t2 t2

t2t2t2

t2 t2 t2

t2t2t2

t1

LEGEND

t1= 0.040 in. (1.01 mm).t2= 0.060 in. (1.52 mm).


Main Avionics Compartment Door – Structural IdentificationFigure 1 (Sheet 2)


Jul 10/2006

ITEM DESCRIPTION DRAWING MATERIAL REFERENCE †

FIN-ISH

CODE(note

2)EFFEC-TIVITY

Assembly −Avionics Door

601R31050 7002−7454

Assembly −Avionics Door

CC670−38651 7455−8400

1 Angle, Aft RHS 601R31050−157 0.040 (1.02) clad 2024−t42 †† A023 7002−7454

1a Angle, Aft RHS CC670−38660−1 0.040 (1.02) clad 2024−t42 †† A023 7455−8400

2 Angle, Aft LHS 601R31050−63 0.040 (1.02) clad 2024−T42 †† A023 7002−7454

2a Angle, Aft LHS CC670−38661−1 0.040 (1.02) clad 2024−T42 †† A023 7455−8400

3 Angle, Fwd LHS 601R31050−17 0.040 (1.02) clad 2024−T42 †† A023 7002−7454

3a Angle, Fwd LHS CC670−38664−1 0.040 (1.02) clad 2024−T42 †† A023 7455−8400

4 Angle, Fwd RHS 601R31050−19 0.040 (1.02) clad 2024−T42 †† A023 7002−7454

4a Angle, Fwd RHS CC670−38665−1 0.040 (1.02) clad 2024−T42 †† A023 7455−8400

5 Coving, Outer, Fwd 601R31050−9 0.050 (1.27) clad 2024−T42 †† A023

6 Coving, Inner, Fwd 601R31050−13 0.050 (1.27) clad 2024−T42 †† A023

7 Coving, Inner, Aft 601R31050−15 0.050 (1.27) clad 2024−T42 †† A023

8 Coving, Outer, Aft 601R31050−155 0.050 (1.27) clad 2024−T42 †† A023

9 Intercostal 601R31050−33 0.063 (1.60) clad 7075−T62 ††† A023 7002−78927894−7894

9a Intercostal CC670−38680−1 0.063 (1.60) clad 7075−T62 ††† A023 7893−78937895−8400










Jul 10/2006


FIN-ISH

CODE(note

2)EFFEC-TIVITY

13 Bracket 601R31050−37 0.080 (2.03) clad 2024−T42 †† A023 7002−76807682−76857730−7730

13a Bracket CC670−38677−1 0.080 (2.03) clad 2024−T42 †† A023 7681−76817686−77297731−8400

14 Doubler 601R31050−43 0.063 (1.60) clad 7075−T62 ††† A023

15 Bracket 601R31050−45 0.050 (1.27) clad 2024−T42 †† A023

16 Bracket 601R31050−46 0.050 (1.27) clad 2024−T42 †† A023

17 Bracket 601R31050−49 0.063 (1.60) clad 7075−T62 ††† A023

18 Bracket 601R31050−50 0.063 (1.60) clad 7075−T62 ††† A023

19 Fitting, cable 601R31050−61 0.063 (1.60) clad 7075−T62 ††† A023

20 Intercostal 601R31050−141 0.063 (1.60) clad 7075−T62 ††† A023








26 Bracket 601R31050−149 0.063 (1.60) clad 7075−T62 ††† A023

27 Doubler 601R31050−150 0.063 (1.60) clad 7075−T6 ††† A023



30 Bracket 601R31050−159 0.050 (1.27) clad 7075−T62 ††† A023


32 Doubler 601R31050−203 0.063 (1.60) clad 7075−T6 ††† A023




Jul 10/2006


FIN-ISH

CODE(note

2)EFFEC-TIVITY

33 Fitting 601R38359−1 M/F S2734T (note 1) A024 7002−8066

33a Fitting 601R38359−7 3.00 (76.20) Al alloy 7475−T7351 A024 8067−8400

34 Fitting 601R38359−5 M/F S2748T (note1) A024 7002−8066


35 Fitting 601R38359−6 M/F S2748T (note1) A024 7002−8066


36 Retainer, Seal, AftLHS

CC670−38662−5 0.050 (1.27) M/F S4943 (note 1) A046&X055

7455−8400

37 Retainer, Seal, FwdLHS

CC670−38663−5 0.050 (1.27) M/F S4943 (note 1) A046&X055

7455−8400

38 Retainer, Seal, FwdRHS

CC670−38674−3 0.050 (1.27) M/F S4943 (note 1) A046&X055

7455−8400

39 Retainer, Seal, AftRHS

CC670−38675−3 0.050 (1.27) M/F S4943 (note 1) A046&X055

7455−8400

40 Skin, Inner 601R31050−191 0.050 (1.27) Al alloy 7075−T62 ††† A023

41 Skin, Outer(chem−milled)

601R31050−193 0.100 (2.54) Al alloy 2024−T3 †† A116

42 Doubler 601R31050−7 0.063 (1.60) Al alloy 7075−T62 †††

†: All dimensions are in inches followed by millimeters in parenthesis.

†† Specification QQ−A−250/5

††† Specification QQ−A−250/13

Note 1: refer to SRM51−32−59−001−001−A01

Note 2: refer to SRM51−21−16−001−001−A01




Jul 10/2006

MAIN AVIONICS COMPARTMENT DOOR − ALLOWABLE DAMAGE

1. General

A. Find the allowable damage limits for the main avionics compartment door as follows:





(3) Fittings




Feb 18/2003

MAIN AVIONICS DOOR − REPAIRS

1. General

For repairs to the main avionics door, contact Bombardier Aerospace Regional Aircraft, CustomerSupport (refer to SRM 51−13−01), except for the REOs listed below.

A. List of REOs




601R−52−42−006 Repair to Main Avionic Bay DoorSeal



Mar 10/2006

AFT EQUIPMENT BAY DOOR − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the aft equipment bay door, refer to Figure 1.



Feb 18/2003

rsr5

2040, lc

, 19/0

5/9

9

177

6

14(10 PLACES)

8(6 PLACES)

92

1

59

3

9

4

3

1610 7

15

11

1913

6

1812


Aft Equipment Bay Door – Structural IdentificationFigure 1


Feb 18/2003


EFFEC-TIVITY


600−35128 0.040 / 0.050 (1.02 / 1.27) clad2024−T3

A109

2 Vent 600−35131 0.040 (1.02) clad 2024−T42 A100

3 Frame 600−35128 0.040 (1.02) clad 2024−T42 A010

4 Angle 600−35128 0.040 (1.02) clad 2024−T42 A010

5 Angle, splice 600−35128 0.040 (1.02) clad 2024−T3 A010

6 Longeron 600−35128 0.032 (.81) clad 2024−T42 A010

7 Angle 600−35128 0,040 (1.02) clad 2024−T42 A010

8 Channel 600−35128 0.032 (.81) clad 2024−T42 A010

9 Angle 600−35128 0.040 (1.02) clad 2024−T42 A010

10 Channel 600−35128 0.032 (.81) clad 2024−T42 A010

11 Web 600−35128 0.032 (.81) clad 2024−T3 A010

12 Doubler 600−35128 0.040 (1.60) clad 2024−T42 A010

13 Cover, dished 600−35128 0.032 (.81) clad 2024−T42 A010

14 Gusset 600−35128 0.040 (1.02) clad 2024−T3 A010

15 Support 600−35029 0.050 (1.27) clad 2024−T42 A010

16 Fitting, bolt guide 600−35093 Plate 7050−T73651 CMS 516−03 A012

17 Fitting, hinge 600−35130 Plate 7050−T73651 CMS 516−03 A012

18 Doubler 600−35128 0.040 (1.02) clad 2024−T3 A010

19 Seal 600−35128 silicone rubber, Haveg #7574



Key to Figure 1


Feb 18/2003

AFT EQUIPMENT COMPARTMENT DOOR − ALLOWABLE DAMAGE

1. General

A. Find the allowable damage limits for the aft equipment compartment door as follows:





(3) Fittings




Feb 18/2003

FORWARD EQUIPMENT−COMPARTMENT ACCESS AND AIR−DRIVEN GENERATOR(ADG) DOORS − GENERAL

1. General

A. This section contains structural identification data and allowable damage limits for the forwardequipment−compartment access and ADG doors. The forward equipment−compartment accessand ADG doors are hinged advanced−composite structures.


A. Forward Equipment−Compartment Access Doors


B. ADG Door


3. Allowable Damage

A. Forward Equipment−Compartment Access Doors


B. ADG Door




Feb 18/2003

FORWARD EQUIPMENT−COMPARTMENT ACCESS DOORS − STRUCTURALIDENTIFICATION

1. General

For the structural identification of the forward equipment−compartment access doors, refer to Figure 1and 2.



Sep 28/2004

rsr5

2042

, ds/

lr, 0

3/11

/04

71

TYPICALEDGE DETAIL

A

B

E E

B

C

C C

C

C

C

A

D

D

D D E E

C C C CEFFECTIVITY: EFFECTIVITY:7003−7369 7370−7522

10

8

5

2

6

12

5

9

5

7

81

3 1

141213

112

4

13 12


Forward Equipment−Compartment Access Doors – Structural IdentificationFigure 1 (Sheet 1)


Mar 10/2006

ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISHCODE♦

EFFEC-TIVITY

Access Door, UpperElectrical Bay Assembly

600−33039

−3, −4

E104††

E112†7003−7369

Access Door, UpperElectrical Bay Assembly

600−33039

−39, 040

E104††

E112†††7370−7522

1 Kevlar (2 laminations) 600−33039

−5

CMS 532−01, Type I 7003−7369

1A Kevlar (1 lamination) 600−33039

−5

CMS 532−01, Type I 7370−7522

2 Honeycomb, Nomex 600−33039

−13, −14

0.500 (12.70) CMS 539−01,type 1

7003−7522

3 Graphite fabric (1lamination)

600−33039

−41

CMS 532−04, Type I 7370−7522

4 Packer 600−33039

−17

0.040 (1.02) 2024−T3QQ−A−250/5

7003−7522

5 Seal 600−33039

−21

Made from S4551 7003−7522

6 Seal 600−33039

23

Made from S4551 7003−7522

7 Aluminum screen 600−33039

−25

120 mesh 0.004 dia. wire5056 RR−W−360, type 1,class 2

7003−7369

7A Copper foil 600−33039

−43

CMS 553−01, Type 2 7370−7522

8 Aluminum foil 600−33039

−31

CYCOM AEL 200/1100 ♣ 7003−7522

9 Bracket 600−33291

−3, −4

0.050 (1.27) clad 2024−T42 A010 7003−7522

10 Latch handle assembly 600−33039

−35, −36

A010 7523−8400

Access door assembly,lower electronic bay

600−33040

−1

E102†

E104††

7003−8400

11 Honeycomb, Nomex 600−33040

−11

0.375 (9.53) CMS 539−01,type 1

7003−8400


Figure 1 (Sheet 2)


Mar 10/2006


EFFEC-TIVITY

12 Doubler, edge, Kevlar (2laminations)

600−33040

−5

CMS 532−01, Type I, class ll 7003−8400

13 Kevlar (2 laminations) 600−33040

−7, −9

CMS 532−01, Type I, class ll 7003−8400

14 Aluminum screen 600−33040

−25

120 mesh 0.004 dia. wire5056 RR−W−360, type 1,class 2

7003−8400


† Inside finish polyurethane topcoat color white number 17875 per FED−STD−595.

†† Outside finish polyurethane topcoat color grey number 16473 per FED−STD−595.

♣ Applied at original installation. Not required for replacement or repair on CRJ 100/200 aircraft.



Figure 1 (Sheet 3)


Mar 10/2006

A

NOTEAll dimensions are given in inches followed bymillimeters in parentheses.

rsr5

2086

.dg,

lr, 0

8/07

/04

1451961718

145196789101112131415161718

181719541

145

196

1718

B B

t=0.097 (2.46)

t=0.264(6.71)

t=0.063 (1.60)

t=0.097(2.46)

A

VIEW LOOKING OUTBOARD

B

B

C

C

D

D G

G

J

J

H

H

F

E

E

FS193.00

TRACEWL79.50

FS173.00

−45°20°

45°

0°

F

14

15

16

17

2

5

19

6

7

8

9

10

11

12

13

14

15

16

17

18

320 21

4

18

N/A

0°

45°

0° or 90°

−45°

0° or 90°

45° or −45°

0° or 90°

45° or −45°

0° or 90°

45° or −45°

0° or 90°

45° or −45°

0° or 90°

45° or −45°

90°

OPTIONAL

2

3

4

5

6

7

8

9

10

11

12

13

LAY−UP TABLEPLY SEQUENCE NUMBERED

FROM TOOL SURFACE

1 1 N/A

PLYSEQUENCE

NUMBER

PLYITEMNo.

ORIENTATIONDEGREE


Forward Equipment−Compartment Access Doors − Structural IdentificationFigure 2 (Sheet 1)


Mar 10/2006

rsr5

2087

.dg,

lr, 0

8/07

/04

1345196789101112131415161718

t=0.268 (6.81)

C C

1245196789101112131415161718

t=0.268 (6.81)

D D

1817161514131211109876

19541

t=0.264 (6.71)

1817619541

t=0.097(2.46)

E E

NOTE

All dimensions are given in inchesfollowed by millimeters in parentheses.




Mar 10/2006

rsr5

2088

.dg,

lr, 0

8/07

/04

18176

19541

t=0.097 (2.46)

F F G G

18176

19541

t=0.097 (2.46)

H H

18176

1954

201

t=0.097 (2.46)

J J

18176

1954

211

t=0.097 (2.46)

NOTE

All dimensions are given in inchesfollowed by millimeters in parentheses.




Mar 10/2006

rsr5

2089

.dg,

lr, 0

8/07

/04

K

K

VIEW LOOKING OUTBOARD

25

23

25

24

FS193.00

TRACEWL79.50

22

FS173.00

FS187.00

FS177.25

ACCESS DOOR HINGEDATUM LINE AXIS




Mar 10/2006


EFFEC-TIVITY

Access door, upperelectrical bay assembly

601R33029

−1, −2

E102†

E100††7523−8064

Access door, upperelectrical bay assembly

601R33029

−3, −4

E102†

E100††8065−8400

1 Copper foil 601R33029

−005, −006

CMS 553−01, Type II GRD 4†††

7523−8064


−051, −052


8065−8400


−007, −008


7523−8064


−009, −010


7523−8064

4 Graphite fabric 601R33029

−011, −012

CMS 532−19, Class II ††† 7523−8400


−013, −014

CMS 532−19, Class II ††† 7523−8400


−017, −018

CMS 532−19, Class II ††† 7523−8400


−019, −020

CMS 532−19, Class II ††† 7523−8400


−21, −022

CMS 532−19, Class II ††† 7523−8400


−023, −024

CMS 532−19, Class II ††† 7523−8400


−025, −026

CMS 532−19, Class II ††† 7523−8400


−027, −028

CMS 532−19, Class II ††† 7523−8400


−029, −030

CMS 532−19, Class II ††† 7523−8400


−031, −032

CMS 532−19, Class II ††† 7523−8400


Key to Figure 2Figure 2 (Sheet 5)


Mar 10/2006


EFFEC-TIVITY


−033, −034

CMS 532−19, Class II ††† 7523−8400


−035, −036

CMS 532−19, Class II ††† 7523−8400


−037, −038

CMS 532−19, Class II ††† 7523−8400


−039, −040

CMS 532−19, Class II ††† 7523−8400

18 Fiberglass fabric 601R33029

−043, −044

CMS 532−06, Style 120 ††† 7523−8064

18 Fiberglass fabric 601R33029

−053, −054

CMS 532−31, Style ll ††† 8065−8400


−045, −046

CMS 532−19, Class II††† 7523−8400


−047, −048


7523−8064


−049, 050


7523−8064

Access door assembly 601R33028

−1, −2

A145 7523−8064

Access door assembly 601R33028

−3, −4

A145 8065−8400

22 Seal CC670−33297

−1, −2

AMS 3301, Make fromS4551

E002 7523−8400

23 Seal CC670−33298

−1, −2

AMS 3301, Make fromS4551

E002 7523−8400

24 Bracket strut support CC670−33424

−1, −2

.050 (1.27) 2024−T3,QQ−A−250/5,

A023 7523−8400

25 Latch handle assembly H2438

−15K3239

−1, −2

7523−8400





Mar 10/2006


EFFEC-TIVITY

† Inside finish polyurethane topcoat color white number 17875 per FED−STD−595.

†† Outside finish polyurethane topcoat color grey number 16473 per FED−STD−595.

††† Refer to Lay−up table for ply sequence and fiber orientation.

NOTE: All dimensions are in inches followed by millimeters in parentheses.




Mar 10/2006

FORWARD EQUIPMENT−COMPARTMENT ACCESS DOORS − ALLOWABLEDAMAGE

1. General

A. General

The allowable damage limits given in this procedure are only for the forwardequipment−compartment access doors, part number 601R33029−1 and 601R33029−2. Theseallowable limits must not be used for any other part number.

B. Contact Bombardier Aerospace Regional Aircraft, Customer Support (refer to SRM 51−13−01)when:

– there is damage that is more than the limits that follow.

– the part number (or dash number) of the damaged part is not given above.

C. General Limitations

NOTE: These general limitations must be applied before the specific limitations areconsidered.

(1) All fasteners that connect the hinges and latches to the composite structure must remaineffective.

(2) No damage is allowed to the footprint area of the hinge fittings and the latches or for 1.5 in.(38.1 mm) arround the footprints.

D. Specific Limitations

Refer to Figure 101.



Apr 10/2005

rsr5

2102

.cgmVIEW LOOKING OUTBOARD ON LEFT HAND SIDE

A

LAMINATE AREA

REINFORCEDLAMINATE AREA

A

Left side shown Right side opposite.

NOTE


Upper Electrical Access Bay − Allowable DamageFigure 101 (Sheet 1)


Apr 10/2005

COMPOSITE STRUCTURE—ALLOWABLE DAMAGE LIMITS

TYPE OFDAMAGE

LOCATION OFDAMAGE LIMITS REMARKS

Cracks

Free edge The maximum acceptable cracklength is 1.00 in. (25.4 mm)provided:

− the nearest structural fasteneris 3L minimum.

− there are no more than twocracks per square foot.

Apply speed tape to thedamaged areas (Refer to SRM51−27−15).

Do a detailed visual inspection atevery subsequent ’A’ check fordamage propagation and speedtape integrity. Replace the speedtape as necessary.

Do a permanent repair no laterthan the next ’C’ check.

Laminate

(reinforced area)

The maximum crack length (L)allowed is 2.00 in. (50.8 mm)provided:

− the distance from anyunrepaired damage, hingefasteners or latch fasteners is 3Lminimum.


Laminate

(all other areas)


− the distance from anyunrepaired damage or structuralfastener is 3L minimum.


Holes andpunctures

All areas The maximum puncture diamater(D) allowed is 2.0 in. (50.8 mm)provided:

− the distance from anyunrepaired damage or structuralfastener is 3D minimum.

− there are no more than twopunctures per square foot.

− the distance from any freeedge is 3D minimum.





FORWARD EQUIPMENT−COMPARTMENT ACCESS DOORS—Allowable DamageFigure 101 (Sheet 2)


Apr 10/2005


TYPE OFDAMAGE


Dents ordepressions

All areas Dent does not penetrate skin andis less than 0.040 in. (1.02 mm)deep.

No repair necessary.

Dent is more than 0.040 in. (1.02mm) deep but is less than fullpenetration.

Treat as penetration of 0.500 in.(12.70 mm).

Do a tap test and check fordelamination and repeat at every’A’ check. If there isdelamination, refer to the limitsfor delamination.


The maximum dent diamater (D)allowed is 2.00 in (50.8 mm)provided:


− there are no more than threedents per square foot.

− there is no fiber damage.

Do a tap test around the dent. Ifthere is fiber damage, cracks,delamination or disbonding oneither surface of the structure,refer to the relevant damage typefor limits.

Repeat tap test at every ’A’check.

No temporary repair necessary.


Scratches

All areas The maximum damage length (L)is 4.00 in. (101.6 mm)

− the damage is limited to onlyone ply (0.012 in. (0.30 mm)maximum depth), otherwise referto allowable damage limits forcrack.

− the distance from anyunrepaired damage is a minimumof 3L or 4.00 in. (101.6 mm).

Do a detailed visual inspection atevery subsequent ’A’ check fordamage propagation.





Apr 10/2005


TYPE OFDAMAGE


Nicks orgouges

All areas The allowable limits given forholes and punctures must alsobe considered in addition to theallowable limits given below.

The maximum area of damageshall be 1.0 square inchprovided:

− the maximum damage length(L) is 2.00 in. (50.8 mm).





Delaminations

Free edge The maximum delaminationlength (L) allowed is 1.00 in.(25.4 mm) provided:

− the distance from anyunrepaired damage or structuralfastener is 3L minimum

− there are no more than twodelaminations per square foot.

− the delamination is not at thedoor corner

− maximum delamination area isone square inch.


Do a tap test and repeat at everysubsequent ’A’ check for damagepropagation.


All other areas The maximum delaminationlength (L) allowed is 2.00 in.(50.8 mm) provided:


− there are no more than threedelaminations per square foot.

− maximum delamination area is2 square inches.







Apr 10/2005


TYPE OFDAMAGE


Erosion

Free edge The maximum damage length inthe wind direction is 1.50 in.(38.1 mm) provided:

− the damage is limited to twoplies maximum.

− the maximum damage length inthe crosswind direction is 1.5 in.(38.1 mm)

− the damage is not adjacent toany fasteners.




All other areas Maximum erosion of one ply shallbe treated as a scratch.

More than one ply removed isassessed as a puncture hole.

Maximum area of damage is onesquare inch.





Apr 10/2005

FORWARD EQUIPMENT−COMPARTMENT ACCESS DOORS − REPAIRS

1. General

For repairs to the forward equipment−compartment access doors, contact Bombardier AerospaceRegional Aircraft, Customer Support (refer to SRM 51−13−01), except for the REOs listed below.

A. List of REOs




601R−52−44−038 Generic temporary repair toforward upper equipmentcompartment doors

601R−52−44−042 Generic temporary repair toforward lower electronics bayaccess doors



Mar 10/2006

AIR DRIVEN GENERATOR (ADG) DOOR − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the air driven generator door (ADG), refer to Figure 1.



Feb 18/2003

rsr5

2044, dd, 19/0

5/9

9

6

5

TYPICAL CENTRESTRUCTURE

1 2

14

1

2

4

11

1 3 3

2 1 3 3 4


Air Driven Generator (ADG) Door – Structural IdentificationFigure 1


Feb 18/2003


EFFEC-TIVITY

1 Kevlar 600−33253 CMS 532−01, type 1 E109

2 Honeycomb, Nomex 600−33253 CMS 539−01, type 4

3 Carbon fibre 600−33253 prepreg 12" (304.8) wide tape withT300 fibre and 5209 resin system

4 Screen, aluminum 600−33253 120 mesh 0.004 dia wire 5056RR−W−360, type 1, class 2

5 Hinge assembly, fwd. 600−33254 al alloy 2024−T351 QQ−A−250/4 A012

6 Hinge assembly, aft 600−33255 al alloy 2024−T351 QQ−A−250/4 A012



Key to Figure 1


Feb 18/2003

AIR−DRIVEN GENERATOR (ADG) DOOR − ALLOWABLE DAMAGE

1. General

A. The allowable damage limits which follow are only for the air−driven generator door, part number600−33253−31. You must not use these allowable limits for any other part number.




2. General Limitations

NOTE: These general limitations must be applied before the specific limitations are considered.

A. Refer to Figure 101. Damage is not allowed in the areas shown.

B. The fasteners attaching the attachment fittings to the air−driven generator door must remain fullyeffective. Damage is not allowed to the composite structure around the fasteners for a radius of1.00 in (25.4 mm).

3. Specific Limitations



Apr 10/2005

rsr5

2100

.cgm

FS190.00

VIEW LOOKING INBOARD ON OUTER SKIN

FS184.75 FS174.62 FS169.00

No damage permitted

OUTER SKIN

4.00 in.(101.6 mm)

3.00 in.(76.2 mm)

4.50 in.(114.3 mm)

9.00 in.(228.6 mm)

A

A

4.30 in.(109.22 mm)

4.50 in.(114.3 mm)

6.43 in.(163.32 mm)

2.50 in.(63.5 mm)


Air−Driven Generator (ADG) Door − Allowable DamageFigure 101 (Sheet 1)


Apr 10/2005

rsr5

2101

.cgm

2.50 in.(63.5 mm)

FS190.00FS184.75FS174.62FS169.00

INNER SKIN

VIEW LOOKING OUTBOARD ON INNER SKIN

FS190.00FS184.75FS174.62FS169.00

VIEW LOOKING OUTBOARD ON SANDWICH STRUCTURE CORE

HONEYCOMB CORE

3.50 in.(88.9 mm)

A

14.38 in.(365.25 mm)

No damage permitted

3.00 in.(76.2 mm)

4.50 in.(114.3 mm)

4.00 in.(101.6 mm)

8.50 in.(215.9 mm)

A

4.00 in.(101.6 mm)

1.00 in.(25.4 mm)


Air−Driven Generator (ADG) Door − Allowable DamageFigure 101 (Sheet 2)


Apr 10/2005


TYPE OFDAMAGE


Cracks

Laminate

(free edge)

The maximum crack length (L)allowed is 1.00 in. (25.4 mm)provided the distance from anystructural fastener is 3Lminimum.




Laminate

(all other areas)




Sandwich

(all areas)




Holes andpunctures

Laminate

(all areas)

The maximum puncture diamater(D) allowed is 2.0 in. (50.8 mm)provided:

− the distance from anyunrepaired damage or structuralfastener is 3D minimum

− there are no more than twopunctures per square foot





Sandwich

(all areas)

The maximum puncture diamater(D) allowed is 2.0 in (50.8 mm)provided:




Air−Driven Generator (ADG) Door—Allowable DamageFigure 101 (Sheet 3)


Apr 10/2005


TYPE OFDAMAGE


Dents





Do a tap test and check fordelamination at everysubsequent ’A’ check. If there isdelamination, refer to the limitsfor delamination.

Laminate

(all areas)

The maximum dent diamater (D)allowed is 2.00 in (50.8 mm)provided:


− there are no more than threedents per square foot

If there is fibre damage, cracks ordelamination on either surface ofthe laminate, refer to theallowable damage limits forcracks or delaminations asnecessary.




Sandwich

(all areas)

The maximum dent diamater (D)allowed is 2.0 in. (50.8 mm)provided:


− there are no more than fourdents per square foot

− the maximum depth of the dentmust not be more than 20% ofthe complete thickness of thesandwich structure, otherwisetreat as a hole.

If there is fibre damage, cracks ordelamination on either surface ofthe laminate, refer to theallowable damage limits forcracks, delaminations ordisbonds as necessary.







Apr 10/2005


TYPE OFDAMAGE


Scratches

All areas The maximum damage length (L)is 4.00 in. (101.6 mm) provided:





Nicks andgouges

All areas The maximum area of damageshall be 1.0 square inchprovided:

− the maximum damage length(L) is 2.00 in. (50.8 mm)





Delaminationsand

Disbonds

Less than 1.50 in.(38.1 mm) fromdoor corner

Not allowed Contact Bombardier AerospaceRegional Aircraft, CustomerSupport (refer to SRM51−13−01).

Free edge The maximum delaminationlength (L) allowed is 1.00 in.(25.4 mm) provided:



Where there is free edgedamage apply speed tape to thedamaged areas (Refer to SRM51−27−15).



All other areas The maximum delaminationlength (L) allowed is 2.00 in.(50.8 mm) provided:









Apr 10/2005


TYPE OFDAMAGE


Erosion

Free edge Edge erosion is acceptableprovided:

− the damage is limited to twoplies maximum

− the damage length parallel tothe free edge does not exceed1.00 in. (25.4 mm)

− the damage does not exceedmore than 2.00 in. (50.8 mm)perpendicular to the free edge..




All other areas Erosion of one ply shall betreated as a scratch provided:

− the maximum eroded area isnot more than 5.00 squareinches.

Erosion of more than one plyshall be treated as a puncturehole.




Apr 10/2005

AIR DRIVEN GENERATOR (ADG) DOOR − REPAIRS

1. General

For repairs to the air driven generator (ADG) door, contact Bombardier Aerospace Regional Aircraft,Customer Support (refer to SRM 51−13−01), except for the REOs listed below.

A. List of REOs




601R−52−44−043 Generic temporary repair to ADGdoor



Mar 10/2006

SERVICING DOORS − GENERAL

1. General

For the structural identification locator of the different servicing doors refer to Figure 1.



Feb 18/2003

rsr5

2072, m

cp, 31/1

0/0

0

52−45−09

52−45−06

52−45−02

52−45−08

52−45−09

52−45−07

52−45−03

52−45−01

52−45−07

52−45−05

52−45−04


Servicing DoorsFigure 1


Feb 18/2003

SERVICING DOORS − ALLOWABLE DAMAGE

1. General

A. Find the allowable damage limits for the servicing doors as follows:

(1) Conventional Support Structures


(2) Metal Skins and Composite Honeycomb Structures


(3) Fittings




Feb 18/2003

SERVICING DOORS − REPAIRS

1. General

A. For repairs to the servicing doors, contact Bombardier Aerospace Regional Aircraft, CustomerSupport (refer to SRM 51−13−01).



Feb 18/2003

APU FAULT AND GROUND AIR CONNECTION DOOR − STRUCTURALIDENTIFICATION

1. General

For the structural identification of the APU fault and ground air connection door, refer to Figure 1.



Feb 18/2003

rsr5

2046, dd, 19/0

5/9

9

3

1

2

4


APU Fault and Ground Connection Door – Structural IdentificationFigure 1


Feb 18/2003


EFFEC-TIVITY

1 Skin 601−35009 0.032 (0.81) clad 2024−T42 A048

2 Reinforcement 601−35009 0.032 (0.81) clad 2024−T42 A048

3 Latch 601−35009 Hartwell H5000−2−072−196

4 Hinge assembly 601−35009

Hinge flanges 0.040 (1.02) MIL−S−5059 type301, annealed

S010

Hinge pin 0.091 (2.31) DIA. X 10.5 (266.7)MS 9226−08

NOTE: All dimensions are in inches (millimeters) unless otherwise specified.


Key to Figure 1


Jun 17/2003

APU FAULT AND GROUND AIR CONNECTION DOOR − ALLOWABLE DAMAGE

1. General

A. For the allowable damage limits for the APU fault and ground air connection door, contactBombardier Aerospace Regional Aircraft, Customer Support (refer to SRM 51−13−01).



Feb 18/2003

REFUELING ACCESS DOOR − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the refueling access door, refer to Figure 1.



Feb 18/2003

rsr5

2048

.dg,

lr, j

an23

/200

7−

10 (1 PLY)9A (6 PLY)9 (5 PLY) 2

31A (6 PLY)1 (5 PLY)

4(4 PLACES)

8(4 PLACES)

3 6(2 PLACES)

57

12

9A (6 PLY)9 (5 PLY)

10 (1 PLY)

3

TYPICAL EDGE DETAIL

A

A

B

B

C

C

B B

−C C

1 (5 PLY)1A (6 PLY)

−C C

12

CORE SPLICE(REF)

11(2 PLACES)


Refueling Access Door − Structural IdentificationFigure 1


Jun 10/2007

ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISHCODE EFFECTIVITY

RefuelingAccess Door

Assembly600−31183

7003 7775

7777 7799

7801 7816

7818 7839

Access Door−Refuel FwdWing/fuse

Fairing

601R31183

7776 7776

7800 7800

7817 7817

7840 8400

1 KevlarLaminate

600−31183−41 CMS 532−01, type 1, class 2 E002 7003 7775

7777 7799

7801 7816

7818 7839

1A Graphite Cloth 601R31183−13/−15/−17/−19/−21/−23

0.0167 (0.424), CMS 532−19,class 2

7776 7776

7800 7800

7817 7817

7840 8400

2 Flex Core 600−31183−45 0.500 (12.7), CMS 539−01 type6

E002 7003 7166

2A Flex Core 600−31183−61 0.500 (12.7), CMS 539−01 type1

7167 7269

2B Flex Core 600−31183−69 0.500 (12.7), CMS 539−01 type6

7270 8400

3 Screen,Aluminum

600−31183−55 0.004 (0.102) dia wire, 5056R.R.W. 360, type 1, class 2

E002 7003 7775

7777 7799

7801 7816

7818 7839

3A Copper Foil 601R31183−11 0.004 (0.102), CMS 553−01,type 2, Grade 4

E001 7776 7776

7800 7800

7817 7817

7840 8400

4 Plate 600−31183−35 0.040 (1.02), MIL−S−5050 type301, cond. annealed

S020

5 Plate 600−31183−53 0.050 (1.27), clad 2024−T42 A010 7003 8019

5A Plate 600−31183−73 0.050 (1.27), Steel 4130 (AMS6350)

8020 8400




Jun 10/2007

ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISHCODE EFFECTIVITY

6 Latch NA 0.094 (2.39), HartwellH2561−1−145

Alternate part

Hartwell H2561−9−145

X110

7 Shim 600−31183−51 0.094 (2.39), MIL−S−22499comp 1, type 1, class 1

X110

8 Bracket, Hinge 600−31183−25/−27/−29/−31

0.063 (1.60), clad 2024−T42 A010

9 KevlarLaminate

600−31183−43 CMS 532−01, type 1, class 2 E002 7003 7775

7777 7799

7801 7816

7818 7839

9A Graphite Cloth 601R31183−13/−15/−17/−19/−21/−23

0.0167 (0.424), CMS 532−19,class 2

7776 7776

7800 7800

7817 7817

7840 8400

10 FiberglassCloth

601R31183−25 0.005 (0.127), CMS 532−06,style 120

7776 7776

7800 7800

7817 7817

7840 8400

11 FoamingAdhesive

600−31183−65 CMS 551−07, Grade 2 Class 1 7167 8400

12 HoneycombCore

600−31183−59 0.200 (5.08), CMS 539−01,Type 1

7167 7269

12A HoneycombCore

600−31183−67 0.150 (3.81), CMS 539−01,Type 6

7270 8400

Note: All dimensions are in inches followed by millimeters in parentheses.




Jun 10/2007

REFUELING ACCESS DOOR − ALLOWABLE DAMAGE

1. General

A. For the allowable damage limits for the refueling access door, contact Bombardier AerospaceRegional Aircraft, Customer Support (refer to SRM 51−13−01).



Feb 18/2003

OXYGEN REFILLING DOOR − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the oxygen refilling door, refer to Figure 1.



Feb 18/2003

rsr5

2050

, dg,

03/

10/0

0

2

6

5

3

1

4

FS201.57

FS196.40


Oxygen Refilling Door – Structural IdentificationFigure 1


Feb 18/2003


EFFEC-TIVITY

1 Latch 600−33280 Hartwell H5000−2−064−115

2 Hinge 600−33280 M / F MS 20001P4

3 Gasket 600−33280 0.063 (1.60) sponge rubberMIL−R−6130 type 2, grade cmedium

4 Panel (chem−milled) 600−33280 0.040 / 0.063 (1.02 / 1.60) clad7075−T62

A109

5 Doubler 600−33280 0.063 (1.60) clad 7075−T62 A109

6 Spring 600−33280 S1440



Key to Figure 1


Feb 18/2003

AC ELECTRICAL GROUND POWER DOOR − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the AC electrical ground power door, refer to Figure 1.



Feb 18/2003

rsr5

2052

, ps,

03/

10/0

0

14

3

2


AC Electrical Ground Power Door – Structural IdentificationFigure 1


Feb 18/2003


EFFEC-TIVITY

1 Door 600−33283 0.063 (1.60) clad 7075−T6 A116

2 Hinge 600−33283 M / F MS 20001P4 A024

3 Doubler 600−33283 0.063 (1.60) clad 7075−T6 A023

4 Latch 600−33283 Hartwell H5000−2−064−102



Key to Figure 1


Feb 18/2003

AC ELECTRICAL GROUND POWER DOOR − ALLOWABLE DAMAGE

1. General

A. For the allowable damage limits for the AC electrical ground power door, contact BombardierAerospace Regional Aircraft, Customer Support (refer to SRM 51−13−01).



Feb 18/2003

EXTERNAL SERVICE PANEL DOOR − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the external service panel door, refer to Figure 1.



Feb 18/2003

rsr5

2054

, ps,

03/

10/0

0

FS202.75FS193.004

1

3

2


External Service Panel Door – Structural IdentificationFigure 1


Feb 18/2003


EFFEC-TIVITY

1 Door 601R33003 0.063 (1.60) clad 7075−T6 A116

2 Hinge 601R33003 M / F MS 20001P4 A023

3 Doubler 601R33003 0.063 (1.60) clad 7075−T6 A023

4 Latch 601R33003 Hartwell H5000−2−064−115



Key to Figure 1


Feb 18/2003

EXTERNAL SERVICE PANEL DOOR − ALLOWABLE DAMAGE

1. General

A. For the allowable damage limits for the external service panel door, contact BombardierAerospace Regional Aircraft, Customer Support (refer to SRM 51−13−01).



Feb 18/2003

DC ELECTRICAL GROUND POWER DOOR − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the DC electrical ground power door, refer to Figure 1.



Feb 18/2003

rsr5

2056

, ps,

03/

10/0

0

FS661.30

FS654.50

2

4

31


DC Electrical Ground Power Door – Structural IdentificationFigure 1


Feb 18/2003


EFFEC-TIVITY

1 Door 601R35119 0.063 (1.60) clad 2024−T42 A109

2 Latch 601R35119 Hartwell H5000−2−064−132

3 Flange, hinge 601R35119 0.040 (1.02) S5059 comp 301,annealed

S010

4 Pin, hinge 601R35119 0.091 (2.31) dia X 4.00 (101.6) M /F MS 9226−08



Key to Figure 1


Feb 18/2003

DC ELECTRICAL GROUND POWER DOOR − ALLOWABLE DAMAGE

1. General

A. For the allowable damage limits for the DC electrical ground power door, contact BombardierAerospace Regional Aircraft, Customer Support (refer to SRM 51−13−01).



Feb 18/2003

LAVATORY SERVICE DOORS − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the lavatory service doors, refer to Figure 1.



Jul 10/2008

rsr5

2058

, lc,

04/

10/0

0

−

3

2

1

4(2 PLACES)

9

8(9 PLY)

8(11 PLY)

7

68

(9 PLY)7

8(7 PLY)

8(9 PLY)

8(7 PLY)9

8

8(7 PLY)

5(2 PLACES)

9


Lavatory Service Doors – Structural IdentificationFigure 1


Feb 18/2003


EFFEC-TIVITY

1 Hinge 601R38329 0.080 (2.03) MS28257C5−1100 X055

2 Door panel (chem−milled)

601R38329 0.080 (2.03) clad 2024−T3 A116

3 Trigger lock 601R38329 Hartwell H 2757−1−080 3

3 Trigger lock 601R38329 Hartwell H5100−2−081−218 73

4 Doubler 601R35232 0.050 (1.27) clad 2024−T42 A023

5 Hinge arm 601R35232 0.050 (1.27) clad 2024−T42 A023

6 Latch 601R35232 Hartwell H2561−11−088

7 Honeycomb (Nomex) 601R35232 0.750 (19.05) CMS 539−01 type 7

8 Kevlar laminate 601R35232 CMS 532−01 type 1, class 1 E109

9 Screen, aluminum 601R35232 0.004 (0.102) dia. wire 5056RR−W−360, type 1, class 2

NOTE: All dimensions are in inches (millimetres) unless otherwise specified.


Key to Figure 1


Jul 10/2008

REFUEL / DEFUEL CONTROL PANEL DOOR − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the refuel / defuel control panel door, refer to Figure 1.



Feb 18/2003

rsr5

2060

, cr,

04/

10/0

0

1

5

2

3

4


Refuel/Defuel Control Panel Door – Structural IdentificationFigure 1


Feb 18/2003

ITEM DESCRIPTIONDRAW-

ING MATERIAL REFERENCEFINISHCODE

EFFEC-TIVITY

1 Door (chem−milled) 601R38321 0.066 / 0.090 (1.68 / 2.29) clad2024−T3

A116

2 Latch 601R38321 Hartwell H5100−091−115

3 Hinge, upper 601R38321 Hartwell H 795−1

4 Hinge, lower 601R38321 Hartwell H 971−1

5 Doubler 601R38321 0.050 (1.27) clad 2024−T3 A048



Key to Figure 1


Feb 18/2003

REFUEL/DEFUEL CONTROL PANEL DOOR − ALLOWABLE DAMAGE

1. General

A. For the allowable damage limits for the refuel/defuel control panel door, contact BombardierAerospace Regional Aircraft, Customer Support (refer to SRM 51−13−01).



Feb 18/2003

POTABLE WATER SERVICE DOOR − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the potable water service door, refer toFigure 1.



Feb 18/2003

−3 and −153INSTALLATION

−113 and −151INSTALLATION

t1= 0.058 in. (1.473 mm).t2= 0.108 in. (2.743 mm).

LEGEND

1

5

6

7

t1

t2

2

34

34

1

t1

t2

rsr5

2062

.dg,

lc/r

m, 2

3/05

/06


Potable Water Service Door – Structural IdentificationFigure 1


Jul 10/2006


EFFEC-TIVITY

Potable Water SystemAft Service Door −Installation

601R35014−3 7003−7076

7082−7091

7136

7140

7152

7176


601R35014−113 7077

7092−7135

7137−7139

7153−7175

7177−7196


601R35014−151,−153

7197−8400

1 Skin, door(chem−milled)

601R35014−47 0.125 (3.18) clad 2024−T42 A116

2 Stiffener 601R38316−69 0.050 (0.127) clad 2024−T42 A023 7003−7076

7078−7091

7136

7140

7152

7176

3 Spacer 601R35014−21 0.125 (3.18) clad 2024−T3 A023 7003−7196

4 Spacer 601R35014−155 0.125 (3.18) clad 2024−T3 A023 7197−8400

5 Bracket 601R35014−109 0.050 (0.127) clad 2024−T42 A023 7077

7092−7135

7137−7139

7141−7151

7153−7175

7177−8400




Jul 10/2006


EFFEC-TIVITY

6 Stiffener 601R35014−85 0.050 (0.127) clad 2024−T42 A023 7077

7092−7135

7137−7139

7141−7151

7153−7175

7177−8400

7 Bracket 601R35014−93 0.050 (0.127) clad 2024−T42 A023 7077

7092−7135

7137−7139

7141−7151

7153−7175

7177−8400

NOTE: All dimensions are in inches followed by millimeters in parentheses.





Jul 10/2006

FLIGHT COMPARTMENT DOOR − ALLOWABLE DAMAGE

1. General

A. For the allowable damage limits for the flight compartment door, contact Bombardier AerospaceRegional Aircraft, Customer Support (refer to SRM 51−13−01).



Feb 18/2003

FLIGHT COMPARTMENT DOOR − REPAIRS

1. General

A. For repairs to the flight compartment door, contact Bombardier Aerospace Regional Aircraft,Customer Support (refer to SRM 51−13−01).



Feb 18/2003

LANDING GEAR DOORS − GENERAL

1. General

A. This section contains structural identification data and allowable damage limits for the landinggear doors.


A. Nose Landing−Gear Doors


B. Main Landing−Gear Doors


3. Allowable Damage

A. Nose Landing−Gear Doors


B. Main Landing−Gear Doors




Feb 18/2003

NOSE LANDING GEAR DOORS − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the nose landing gear doors, refer to Figure 1.



Feb 18/2003

rsr5

20

64

, n

g,

12

/08

/99

NOTE

Structure symetricalabout centerline,except as shown.

8109

18 13 19

1 2

17 3

12 11

6

167

4

5

1416

15

TYP. CROSS SECTIONTYP. CROSS SECTION


Nose Landing−Gear Doors – Structural IdentificationFigure 1


Feb 18/2003


EFFEC-TIVITY

1 Skin, inner (Kevlar, 2lams. with 2 lam.doubler)

600−33043 CMS 532−01, Type I E102

2 Core, honeycomb(Nomex)

600−33043 1.50 (38.1) CMS 539−01 type 4

3 Screen, aluminum 120mesh

600−33043 0.004 (.102) dia. wire 5056RR−W−360 type I, class 2

4 Edge member 600−33043 0.040 (1.02) sheet 6061−T4 A010

5 Retainer, seal 600−33043 0.040 (1.02) sheet 6061−T4 A010

Packer 600−33043 0.18 (4.57) Phenolic MIL−P−15035type FBI

Seal 600−33043 0.060 (1.52) AMS 3302 C10

6 Fitting, hinge 600−33210 extruded bar 2024−T3511 A023

Packer 600−33043 0.020 (.51) − 0.100 (2.54) (asrequired) clad 2024−T3

A010

7 Fitting, actuator 600−86105 extruded bar 2024−T3511 A024

8 Skin, inner (Kevlar, 2lams.)

600−33044 CMS 532−01, Type I E102


600−33044 0.410 (10.41) CMS 539−01, Type 1


600−33044 0.660 (16.76) CMS 539−01 type 1

11 Fitting, actuator 600−33213 extruded bar 2024−T3511 A012

12 Fitting, hinge 600−33212 extruded bar 2024−T3511 A012

13 Screen, aluminum 120mesh

600−33044 0.004 (.102) dia. wire 5056RR−W−360 Type I, class 2

14 Channel 600−33043 0.032 (.81) clad 2024−T3 A010

15 Target 600−33043 0.062 (1.57) SAE 1020MIL−S−7952

D010

16 Plate, bearing 600−33043 0.100 (2.54) clad 2024−T42 A048

17 Skin, outer (Kevlar, 4lams.)

600−33043 CMS 532−01, Type I E109

18 Skin, outer (Kevlar, 2lams.)

600−33044 CMS 532−01, Type I E109

19 Edge doubler (Kevlar, 1lam.)

600−33044 CMS 532−01, Type I




Feb 18/2003


EFFEC-TIVITY





Feb 18/2003

NOSE LANDING−GEAR DOORS − ALLOWABLE DAMAGE

1. General

A. The allowable damage limits given in this procedure are only for the components that follow.These allowable limits must not be used for any other part number:

– forward nose−landing−gear (NLG) door, part numbers 600−33043−1007 and600−33043−1008.

– aft nose−landing−gear (NLG) door, part number 600−33044−1001.




2. General Limitations

NOTE: These general limitations must be applied before the specific limitations are considered.

A. Damage is not allowed to either the skins or the honeycomb core of the forward NLG doors at theattachment fiitings, and for 1.00 in. (25.4 mm) around the attachment fittings.

B. Damage is not allowed to either the skins or the honeycomb core of the aft NLG door at theattachment fittings, and for 2.00 in (50.8 mm) around the attachment fittings.

C. All fasteners that connect the attachment fittings to the composite must remain fully effective.

3. Specific Limitations



Apr 10/2005


TYPE OFDAMAGE


Cracks

Laminate The maximum crack length (L)allowed is 1.00 in. (25.4 mm)provided:



− the crack does not open on afree edge.

Apply speed tape to thedamaged areas (Refer to ).



Sandwich The maximum crack length (L)allowed is 1.25 in. (31.75 mm)provided:



Holes andpunctures

Laminate The maximum puncture diamater(D) allowed is 1.00 in. (25.4 mm)provided:


− there are no more than twopunctures per square foot





Sandwich The maximum puncture diamater(D) allowed is 1.00 in. (25.4 mm)provided:




NOSE LANDING−GEAR DOORS—Allowable DamageFigure 101 (Sheet 1)


Apr 10/2005


TYPE OFDAMAGE


Dents ordepressions





Do a tap test and check fordelamination. Repeat tap test atevery ’A’ check. If there isdelamination, refer to the limitsfor delamination.

Laminate The maximum dent diamater (D)allowed is 1.00 in (25.4 mm)provided:


− there are no more than threedents per square foot.




Sandwich The maximum dent diamater (D)allowed is 2.00 in (50.8 mm)provided:


− there are no more than fourdents per square foot.

Do a tap test and check fordelamination. Repeat tap test atevery ’A’ check. If there isdelamination, refer to the limitsfor delamination.

If there is disbonding, thedamage must be repairedimmediately.





Apr 10/2005


TYPE OFDAMAGE


Scratches

Laminate The maximum length (L) ofdamage shall be 2.00 in. (50.8mm) provided:





Sandwich The maximum length (L) ofdamage shall be 4.00 in. (101.6mm) provided:



Nicks orgouges

Laminate The maximum area of damageshall be 1.00 square inchprovided:

− the distance from any structuralfastener is 3L minimum

− the maximum damage length is1.00 in. (25.4 mm)

− the minimum distance from anyunrepaired damage is 4.00 in.(101.6 mm).




Sandwich The maximum area of damageshall be 1.00 square inchprovided:

− the distance from any structuralfastener is 3L minimum

− the maximum damage length is1.00 in. (25.4 mm)

− the minimum distance from anyunrepaired damage is 4.00 in.(101.6 mm).




Apr 10/2005


TYPE OFDAMAGE


Delaminations

Door Corner Not allowed Contact Bombardier AerospaceRegional Aircraft, CustomerSupport (refer to SRM 51−13−01.

Free edge The maximum area of damageshall be 2.00 square inchprovided:

− the maximum delaminationlength is 1.00 in. (25.4 mm)


− there are no more than fourdelaminations per square foot


Do a tap test at everysubsequent ’A’ check for damagepropagation.


All areas The maximum area of damageshall be 2.00 square inchprovided:


− there are no more than fourdelaminations per square foot


Do a tap test at everysubsequent ’A’ check for damagepropagation.


Erosion

Laminate

(free edge)

Edge erosion is acceptableprovided:

− the damage is limited to twoplies maximum

− the damage length in the winddirection does not exceed 1.50in. (38.1 mm)

− the damage does not exceedmore than two attachments in thecrosswind direction.


Laminate

(all other areas)

Maximum erosion of one ply shallbe treated as a scratch.

More than one ply removed isassessed as a puncture hole.

Maximum erosion area shall be1.0 square inch.

Sandwich

(all areas)

Treat as a gouge.




Apr 10/2005

NOSE LANDING−GEAR DOORS − REPAIRS

1. General

For the repairs to the nose landing−gear doors, contact Bombardier Aerospace Regional Aircraft,Customer Support (refer to SRM51−13−01), except for the REOs listed below.

A. List of REOs




601R−52−81−020 Repair to NLG door leading edgedelamination/erosion.

601R−52−81−079 Temporary Repair to Aft NLGDoor, Forward Edge



Mar 10/2006

MAIN LANDING GEAR DOOR − STRUCTURAL IDENTIFICATION

1. General

For structural identification of the main landing gear door, refer to Figure 1.



Feb 18/2003

rsr5

20

66

, n

g,

13

/08

/99

18

1910 11

89

5

6

4

234

420

21

217

13

15

22

1217

6

16

6

5

14

1

13

18

3


Main Landing Gear Door – Structural IdentificationFigure 1


Feb 18/2003


EFFEC-TIVITY


2 Skin, outer 601R31178 0.063 (1.60) clad 2024−T42 A109

3 Clip 601R31178 0.050 (1.27) clad 2024−T42 A010

4 Brace, channel 601R31178 0.050 (1.27) clad 2024−T42 A010

5 Brace, hinge 601R31178 0.050 (1.27) clad 2024−T42 A010

6 Clip 601R31178 0.063 (1.60) clad 2024−T42 A010

7 Gusset 601R31178 0.050 (1.27) clad 2024−T42 A010

8 Shim, hinge 601R31178 0.063 (1.60) MIL−S−22499 comp 1,type 1, class 1

X110

9 Doubler, hinge 601R31178 0.063 (1.60) clad 2024−T42 A010

10 Shim, hinge 601R31178 0,050 (1.27) clad 2024−T42 A010

11 Shim 601R31178 0.063 (1.60) MIL−S−22499 comp 1,type 1, class 1

X110

12 Support, brush 601R31178 0.063 (1.60) clad 2024−T42 A010

13 Shim 601R31178 0.040 (1.02) MIL−S−22499 comp 1,type 1, class 1

X110

14 Roller assembly 601R38119 2.50 (63.50) 7075−T7351QQ−A−250/12

15 Fitting, door attach 601R38119 0.500 (12.7) 7050−T7451 al alloyCMS 516−03

A023

16 Dish 601R38537 0.040 (1.02) clad 2024−T42 A023

17 Brush 601R31180 Fuller Brush Company

18 Tee 601R38531 1.25 (31.75) 7050−T7451 al alloyCMS 516−03

A024

19 Fitting, hinge support 601R31519 1.75 (44.45) 7050−T7451 al alloyCMS 516−03

A024

20 Doubler 601R31178 0.050 (1.27) clad 2024−T42 A010

21 Channel 601R31178 0.050 (1.27) clad 2024−T42 A010

22 Zee 601R31178 0.050 (1.27) clad 2024−T42 A010



Key to Figure 1


Feb 18/2003

MAIN LANDING GEAR DOOR − ALLOWABLE DAMAGE

CAUTION: ALWAYS REFER TO THE SUBJECT PAGE BLOCK 101−199 APPLICABLE TO A GIVENSTRUCTURAL ELEMENT FOR SPECIFIC ALLOWABLE DAMAGE LIMITS. IF THIS ISNOT DONE, IT IS POSSIBLE THAT YOU WILL USE INCORRECT DATA.

YOU MUST REFER TO THE CONTINUING AIRWORTHINESS INSPECTIONREQUIREMENTS TO DETERMINE IF ADDITIONAL DAMAGE TOLERANCEINSPECTIONS APPLY (REF. SRM 51−13−00).

1. General

The general allowable damage limits given at the beginning of this chapter (ref. SRM 52−00−00, PageBlock 101−199) do not apply to this section. You must replace the general limits with the limitsspecified for each item identified in section 2 below. For the allowable damage limits for any item notspecified in section 2 below, contact Bombardier Aerospace Regional Aircraft, Customer Support (refertoSRM 51−13−01.

CAUTION: MAKE SURE THAT THE REMOVED DAMAGE, INCLUDING ANY PREVIOUS DAMAGEREMOVAL, IS WITHIN ALLOWABLE LIMITS AT ANY SPECIFIC LOCATION. RECORDDAMAGE REMOVAL LOCATION.

2. Specific

For the allowable damage limits for the Main Landing−Gear−Doors, refer to Figure 101.



May 10/2010

0.032(0.81)

0.048(1.22)

rsr5

2079

, ds,

05/

09/0

3

BL47.90

FS525.69

5

6

10

9

7

8

4

2

1 3

BL56.06

MAXIMUM TRIMMING2D EDGE DISTANCEFROM CENTER OFFASTENER HOLES

(REFER TO DETAIL C)

MAXIMUMBLEND

THICKNESS0.0275 (0.70)

FS526.00 FS531.67

A

A

All dimensions arein inches (millimeters).

NOTE

0.048(1.22) 0.048 (1.22)

0.048(1.22)

0.048(1.22)

0.048(1.22)

0.032(0.81)

0.032(0.81)

0.032(0.81)

OUTER SKIN


Main Landing Gear Doors − Allowable DamageFigure 101 (Sheet 1)


Jun 22/2004

rsr5

2080

.dg,

ds/

lr, 1

6/02

/04

FS525.69

56

10

9

7

8

4

2

13

MAXIMUM TRIMMING2D EDGE DISTANCEFROM CENTER OFFASTENER HOLES

(REFER TO DETAIL C)

FS526.00FS531.67

B

MAXIMUM BLENDTHICKNESS0.020 (0.51)

13

12

11

B

0.040(1.02)

0.040(1.02)0.040 (1.02)

0.040(1.02)

0.040(1.02)

0.040(1.02)

0.040 (1.02)

0.040(1.02)

0.040 (1.02)

0.040(1.02)

0.040(1.02)

0.040(1.02)

0.040(1.02)

All dimensions arein inches (millimeters).

NOTE

INNER SKIN




Jun 22/2004

rsr5

2081

, ds,

05/

09/0

3

W(WIDTH OF MINOR

AXIS OF DENT)

INITIALCONTOUR

DENTS

X DEPTH = 0.15 in.(3.81 mm) MAXIMUM

MATERIAL THAT CANBE REMOVED

TO REMOVE DAMAGE

SKINEDGE

2D FASTENER EDGEDISTANCE LIMIT



D(DEPTH OF DENT)

0.075 in. (1.91 mm) MAXIMUM

C

2D MINIMUM

RADIUS OF REMOVEDDAMAGE IS FOUND

BY THE DAMAGEDEPTH (X).

R=1.0 in. (25.4 mm).

Dent ratio W/D must not be less than 2D.

11.500 in. (38.10 mm) maximummust not exceed 1/3 of pocketwidth or 1/3 of pocket heightwhichever is smaller.(Pocket dimension measuredfrom rivet line to next rivet line).

NOTES

1

2

2




Jun 22/2004

MAXIMUM1.500 in.

(38.10 mm)

rsr5

2082

.dg,

ds/

lr, 1

6/02

/04

0.750 in.(19.05 mm)

0.750 in.(19.05 mm)

0.750 in.(19.05 mm)

MAXIMUM DENTDEPTH0.075 in.

(1.91 mm)

FASTENERHOLE

(TYPICAL)

DETAIL OF THE MAXIMUM DENT SIZE ALLOWED AND WHERE DENTSCAN BE LOCATED FROM FASTENER HOLE PATTERNS IN THE

INNER OR OUTER SKIN POCKETS

NO DENTS ALLOWED

REFER TODETAIL "C"




Jun 22/2004

OUTER SKIN INNER SKIN

Area

OriginalThickness(in, mm)

Max BlendDepth

(in, mm)

DentLimit(qty) Area

OriginalThickness(in, mm)

Max BlendDepth

(in, mm)

DentLimit(qty)

1 0.048 (1.22) 0.010 (0.25) 0 1 0.040 (1.02) 0.008 (0.21) 0

2 0.048 (1.22) 0.009 (0.23) 1 2 0.040 (1.02) 0.008 (0.21) 1

3 0.048 (1.22) 0.010 (0.25) 0 3 0.040 (1.02) 0.008 (0.21) 0

4 0.048 (1.22) 0.010 (0.25) 2 4 0.040 (1.02) 0.008 (0.21) 2

5 0.048 (1.22) 0.010 (0.25) 2 5 0.040 (1.02) 0.008 (0.21) 2

6 0.048 (1.22) 0.010 (0.25) 2 6 0.040 (1.02) 0.008 (0.21) 2

7 0.032 (0.81) 0.003 (0.08) 2 7 0.040 (1.02) 0.008 (0.21) 2

8 0.032 (0.81) 0.005 (0.13) 1 8 0.040 (1.02) 0.008 (0.21) 2

9 0.032 (0.81) 0.005 (0.13) 2 9 0.040 (1.02) 0.008 (0.21) 2

10 0.032 (0.81) 0.005 (0.13) 2 10 0.040 (1.02) 0.008 (0.21) 2

− − − − 11 0.040 (1.02) 0.008 (0.21) 0

− − − − 12 0.040 (1.02) 0.008 (0.21) 0

− − − − 13 0.040 (1.02) 0.008 (0.21) 0





Jun 22/2004

MAIN LANDING GEAR DOOR − REPAIRS

1. General

For repairs to the main landing gear door, contact Bombardier Aerospace Regional Aircraft, CustomerSupport (refer to SRM 51−13−01), except for the REOs listed below.

A. List of REOs




601R−52−82−016 Repair to MLG door inner andouter skin chafing

601R−52−82−033 Allowable damage limits forchafing on left and right MLGdoors forward zee member

601R−52−82−034 Repair to MLG door inner skinchafing

601R−52−82−102 Repair to MLG door forwardcorner and outer skin, left sideand right side



Mar 10/2006

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