UH-1H Helicopter CBT Installation Manual

CBT INSTALLATION MANUAL
FOR UH-1H HELICOPTER
DOCUMENT NUMBER A726-005, REV. 0
Prepared by:
W.R. DAVIS ENGINEERING LIMITED
Ottawa, Ontario, Canada
DAVIS File No. A726
DECEMBER 2008
The copyright in this document, which contains information of a proprietary nature, is vested in
W.R. Davis Engineering Limited. The content of this document may not be used for purposes other than
that for which it has been supplied and may not be reproduced, either wholly or in part, in any way
whatsoever, nor may it be used by, or its content divulged to any other person whatsoever without the
prior written permission of W.R. Davis Engineering Limited.
A726-005, Rev 0.doc
Document Number A726-005, Rev 0, December 2008
AMENDMENT RECORD
ISSUE
0
DESCRIPTION
CBT Installation Manual For UH-1H
Helicopter
Q-5 F Amendment Record (01/03/03)
Document Number A726-005, Rev 0, December 2008
DATE
December 2008
Davis
REPORT DATA SHEET
DAVIS NUMBER:
SPONSOR'S NUMBER:
A726
TITLE:
CBT INSTALLATION MANUAL FOR UH-1H HELICOPTER
DOCUMENT NUMBER A726-005, REV. 0
AUTHORS:
SPONSOR'S REPRESENTATIVE:
B. Brooking, P.Eng
ORIGINAL SUBMISSION DATE:
ORIGINAL APPROVED BY:
December 2008
D. VanDam, P.Eng
REVISIONS APPROVED BY:
REVISIONS:
Please ensure all previous revisions are marked obsolete.
ABSTRACT:
This document details the installation of the CBT IRSS device aboard the UH-1H
helicopter including required cowling modifications.
ISSUE DATE:
COPY NUMBER:
SECURITY CLASSIFICATION:
December 5, 2008
UNCLASSIFIED
DISTRIBUTION:
DAVIS
:
File
Q-5 D Report Data Sheet (15/05/00)
Document Number A726-005, Rev 0, December 2008
NUMBER OF PAGES:
27
TABLE OF CONTENTS
1.0
INTRODUCTION .............................................................................................................. 1
1.1
1.2
1.3
2.0
PAGE
PARTS DESCRIPTION ......................................................................................... 1
REFERENCES ....................................................................................................... 1
DEFINITIONS AND ABBREVIATIONS............................................................. 1
INSTALLATION PROCEDURES .................................................................................... 4
2.1
2.2
COWLING MODIFICATION KIT........................................................................ 4
CBT IRSS DEVICE.............................................................................................. 13
LIST OF FIGURES
Figure 1
UH-1H OEM COWLING....................................................................................... 2
Figure 2
COWLING MODIFICATION KIT INSTALLED WITH CBT IRSS DEVICE ... 3
Figure 3
UPPER LOUVER TEMPLATE A02-02-001 ........................................................ 9
Figure 4
LOWER LOUVER TEMPLATE A02-02-002....................................................... 9
Figure 5
CUTTING TOP 3 AND TOP 4 LOUVER CUTOUTS........................................ 10
Figure 6
SAMPLE LOUVER-DOUBLER RIVET PATTERN.......................................... 10
Figure 7
COWLING LOUVER AND DOUBLER INSTALLATION............................... 11
Figure 8
TOP 4 LOUVER + TOP BACK DOUBLER INSTALLATION......................... 11
Figure 9
COWLING REINFORCING BAND AND CLOSURE SECTION..................... 12
LIST OF APPENDICES
APPENDIX A
APPENDIX B
APPENDIX C
ILLUSTRATED PARTS BREAKDOWN
SCOPE OF SUPPLY
INSTALLATION DRAWINGS
Document Number A726-005, Rev 0, December 2008
1.0
INTRODUCTION
This document describes the procedures for the installation of the DAVIS Centre
Body Tailpipe (CBT) aboard the UH-1H helicopter. In order to retrofit the UH-1H for
the CBT, the helicopter cowling must be modified to accommodate the new tailpipe.
The installation personnel must be fully aware of the procedures described in this
document prior to undertaking any of the installation procedures. Personnel must be
fully qualified to work on this aircraft.
1.1
PARTS DESCRIPTION
A complete description of the CBT and the cowling modification is given in Ref. 1).
Figure 1 shows the OEM tailpipe and cowling as installed aboard the UH-1H
helicopter.
Figure 2 shows the CBT installed within the modified cowling. For further details, see
the Illustrated Parts Breakdown document (APPENDIX A).
1.2
REFERENCES
1) A726-002, CBT Structural Design Report
2) A726-004, Instructions For Continued Airworthiness (ICA) CBT IRSS Device
3) TM55-1520-210-23-1, Aviation Unit And Intermediate Maintenance
Instructions Army Model UH-1H/V/EH-1H/X Utility Helicopters
1.3
DEFINITIONS AND ABBREVIATIONS
CBT
Centre Body Tailpipe
CRES
Corrosion-Resistant Steel
DAVIS
W.R. Davis Engineering Limited
ICA
Instructions for Continued Airworthiness
IPB
Illustrated Parts Breakdown
IR
Infrared
IRSS
Infrared Signature Suppressor
LHS
Left Hand Side
OEM
Original Equipment Manufacturer
RHS
Right Hand Side
Document Number A726-005, Rev 0, December 2008
1
Figure 1 UH-1H OEM COWLING
Document Number A726-005, Rev 0, December 2008
2
Figure 2 COWLING MODIFICATION KIT INSTALLED WITH CBT IRSS DEVICE
Document Number A726-005, Rev 0, December 2008
3
2.0
INSTALLATION PROCEDURES
Section 2.1 details the preparation and modification of the OEM UH-1H helicopter
exhaust cowling to accommodate the CBT IRSS device. Section 2.2 details the
installation of the CBT itself.
Appendix B provides a list of parts supplied by DAVIS for the CBT IRSS installation
and cowling modification.
Note that rivets and tooling (with the exception of the louver templates) are not
included. The cowling modifications use 1/8” solid aluminum 2117-T4 rivets. It is
the responsibility of the installer to select the appropriate rivet grip length at
installation. Installation drawings are provided in Appendix C.
2.1
COWLING MODIFICATION KIT
The following instructions detail the steps required to modify the OEM cowling for
adaption for use with the CBT IRSS device.
1. Unbolt and remove the OEM cowling from the helicopter.
2. De-rivet all eight (8) louvers on each side of the OEM cowling according to
standard aerospace practices.
3. De-rivet the reinforcing ring that encircles the exit of the cowling.
4. Beginning with the upper louvers on either the RHS or LHS, locate the flexible
Upper Louver Template (see Figure 3). Place the template on the outside of
the cowling ensuring the template is oriented with the word ‘TOP’ toward the
top of the cowling.
5. Align the forward two cutouts of the template with the existing forward two
louver holes on the cowling. Trace the aft two cutouts onto the outside of the
cowling with a non-scoring marking tool and remove the template.
6. Take the Top Front Doubler [18] and hand work the part to match the
curvature of the cowling when the doubler is aligned with the existing forward
two louver cutouts. Ensure the contoured edge of the doubler is oriented
toward the top of the cowling.
7. When the doubler adequately conforms to the curvature of the cowling, align
the forward two cutouts of the doubler with the existing forward two louver
holes on the outside of the cowling and confirm that the third louver cutout
aligns with that marked in step 5. Remove the doubler. Confirm that the Top
3 Louver ([5] on left side, [12] on right side) can be installed at this location.
Trim louver flanges if necessary to accommodate equipment installed on top of
the cowling.
Document Number A726-005, Rev 0, December 2008
4
8. Take the Top 4 Louver ([6] on left side, [13] on right side) and fit it up against
the cowling such that the louver flange aligns with the markings from step 5.
Make any small adjustments in location that allow the louver to best fit the
curvature of the cowling without deviating more than ¼” from the marked
outline. Mark the new outline of the louver flange if necessary.
9. Locate and mark an offset inside the louver flange outline equal to the width of
the louver flange (i.e. the theoretical profile of the louver flange).
10. Take the Top Back Doubler [20] and hand work the part to match the curvature
of the cowling when the doubler is aligned with the inside profile of the louver
flange. Trim the top and bottom of the doubler where necessary to
accommodate the stiffening ribs on the inside of the cowling. Note the overlap
with the existing rivet holes for the reinforcing band on the doubler. See
Figure 8 to see the typical overlap between the doubler and the reinforcing
band. If the edge of the doubler prevents rivets from being successfully
installed, that region of the doubler may be trimmed away.
11. Using a step drill, drill out the radius corners of the two new louver cutouts
marked in step 5. See Figure 5.
12. Cut the remainder of the louver cutouts using standard aerospace practices.
The use of a reciprocating saw is recommended for cutting the cowling skin.
13. Apply a chromate primer to the cut edges before continuing.
14. Align the Top Front Doubler [18] as in step 7 to the inside of the cowling.
Mark the locations of the existing cowling rivet holes around the front two
louvers onto the doubler. Remove the doubler from the cowling.
15. Continue to mark the rivet pattern on the doubler, as started in step 14, around
the louver cut outs (See Figure 6) with a pitch of approximately 1 inch while
maintaining standard edge clearances (twice rivet diameter + 1/16”). Also mark
a similar rivet pattern around the third (aft) louver cut out. Ensure all new rivet
holes will not violate edge clearances with stiffening ribs or other assembly
members.
16. Drill the marked rivet holes using standard aerospace practices. Be sure to deburr all drilled holes.
17. Align the doubler into place on the inside of the cowling and clamp into place.
Match drill the rivet holes from step 16 through the cowling skin.
18. Align the Top 1, Top 2 and Top 3 Louvers ([3], [4], [5] on the left side; [10],
[11], [12] on the right side) into place on the outside of the cowling. Ensure
that the rivet holes will not violate edge clearance limits on the louver flanges
by marking the locations onto the louver flanges and removing for inspection.
Clamp the parts back in place when completed. Match drill all the doubler
rivet holes through the louver flanges. Remove doubler and louvers. De-burr
all rivet holes. Apply sealant (PR1422 or equivalent) to all faying surfaces,
refit and Cleco in place.
Document Number A726-005, Rev 0, December 2008
5
19. Complete the riveting of the Top 1, Top 2 and Top 3 Louvers into place along
with the Top Front Doubler using standard aerospace practices in place as
indicated by Figure 7 assembly. Do not rivet the Top 4 Louver and Top Back
Doubler [20] at this time.
20. Repeat steps 4-19 for the top louvers on the other side of the cowling. When
these steps have been completed, all Top 1, 2 and 3 Louvers and Top Front
Doublers will have been riveted in place and the cutout for the Top 4 Louver
will have been created.
21. Continue with the lower louvers on either the RHS or LHS. Locate the flexible
Lower Louver Template (see Figure 4). Place the template on the outside of
the cowling ensuring the template is oriented with the word ‘TOP’ toward the
top of the cowling.
22. Align the forward two cutouts of the template with the existing forward two
louver cutouts in the OEM cowling. Trace the aft two cutouts onto the outside
of the cowling with a non-scoring marking tool and remove the template.
23. Take the Bottom Front Doubler [19] and hand work the part to match the
curvature of the cowling when the doubler is aligned with the existing forward
two louver cutouts.
24. When the doubler adequately conforms to the curvature of the cowling, mark
the existing rivet hole locations onto the doubler and remove from the cowling.
25. Continue to mark the rivet pattern on the doubler, as started in step 24, around
the louver cut out (See Figure 6) with a pitch of approximately 1 inch while
maintaining standard edge clearances (twice rivet diameter + 1/16”). Ensure all
new rivet holes will not violate edge clearances with stiffening ribs or other
assembly members.
26. Drill the marked rivet holes into the doubler. De-burr all holes.
27. Align the doubler into place on the inside of the cowling and clamp into place.
Match drill the rivet holes from step 26 through the cowling skin.
28. Align the Bottom Front Louvers [7] at these two locations. Mark the rivet
holes onto the louver flanges and inspect rivet edge clearances. Trim the
louver flanges if necessary to clear items such as the reinforcing rib on side of
the cowling.
29. Clamp the louvers into place and match drill all rivet holes through the louver
flanges. Remove parts and de-burr all drilled holes. Apply sealant to faying
surfaces, reinstall and Cleco into place.
30. Take the Bottom 3 Louver ([8] on left side, [14] on right side) and fit it up
against the cowling such that the outside of the louver flange aligns with the
markings from step 22. Make any small adjustments in location that allow the
louver to best fit the curvature of the cowling without deviating more than ¼”
from the marked outline. Trim louver flanges if necessary to accommodate the
stiffening rib on the side of the cowling. Mark the new outline of the louver
flange if necessary.
Document Number A726-005, Rev 0, December 2008
6
31. Locate and mark an offset inside the Bottom 3 Louver flange outline equal to
the width of the louver flange (i.e. the theoretical profile of the louver flange)
32. Repeat steps 30 and 31 for the Bottom 4 Louver ([9] on left side, [15] on right
side).
33. Take the Bottom Back Doubler [21] and hand work the part to match the
curvature of the cowling when the doubler is aligned with the inside outline of
the louver flanges as marked in step 31. Trim the top and bottom of the
doubler where necessary to accommodate the stiffening ribs in this area.
34. Using a step drill, drill out the radius corners of the two new louver cutouts
(per side). See Figure 5.
35. Cut the remainder of the louver cutouts using standard aerospace practices.
The use of a reciprocating saw is recommended for cutting the cowling skin.
36. Apply a chromate primer to the cut edges before continuing.
37. Mark a rivet hole pattern on the doubler [21] around the louver cutouts using
an approximate pitch of 1 inch, maintaining standard edge clearances (twice
rivet diameter + 1/16”). Figure 6 illustrates what the doubler rivet pattern
should look like. Move holes if edge clearances will be interfered with by
stiffening ribs or other assembly members. Drill and de-burr the marked rivet
holes.
38. Fit the doubler [21] to the inside of the cowling. Match drill the doubler rivet
holes including those through the cowling skin, maintaining standard edge
clearances (twice rivet diameter + 1/16”).
39. Align the Bottom 3 and Bottom 4 Louvers to the outside of the cowling. Mark
the rivet holes from step 38 onto the louver flanges. Remove and inspect for
edge clearance violations. Clamp back into place. Match drill through the
louver flanges. Remove parts, de-burr all rivet holes and apply sealant to all
faying surfaces. Cleco the louvers and doubler into place.
40. Complete the riveting of the Bottom 3 and Bottom 4 Louvers into place along
with the Bottom Back Doubler [21] using standard aerospace practices in the
locations indicated in Figure 7 assembly.
41. Repeat steps 21-40 for the louvers on the other side of the cowling.
42. At this point all louvers have been installed except for the Top 4 Louvers ([6]
on left side, [13] on right side)
43. Test fit the cowling over the CBT device to ensure clearance at the cowling
exit. Ensure there will be sufficient space for the largest diameter portion of
the CBT to pass through the cowling exit with the reinforcing ring installed.
When the cowling is installed, the gap between the cowling and the tailpipe
should be consistent around the entire circumference. The cowling may be
trimmed if necessary to allow for installation over the CBT. Remove the
cowling and continue modifications.
Document Number A726-005, Rev 0, December 2008
7
44. Locate the new Cowling Reinforcing Band [16] and fit it into place on the
inside of the cowling. The band must be flexed slightly in a spring type action
to allow it to fit into place. The band must fit between the reinforcing ribs and
the cowling skin with the gap in the band located toward the bottom.
45. Fit the Cowling Closure Section [17] into place at the bottom of the cowling to
complete the reinforcing band. See Figure 9. The cowling closure section
ends are joggled to allow the cowling reinforcing band to sit underneath it
when the band is installed Measure how much of the band must be trimmed to
fully accommodate the closure section. Remove the reinforcing band and trim.
46. Fit the band back into place along with closure section. Locate the closure
section toward the bottom of the cowling. Drill the rivet holes in the overlap
section through the band and Cleco into place. See Figure 9.
47. Align the Top Back Doublers [20] on each side of the cowling. These doublers
were trimmed to fit in step 10. The reinforcing band should lie between the
doubler and the cowling skin.
48. Joggle the doublers [20] as necessary where they overlap the reinforcing band
to ensure best fit up. Clamp into place.
49. Match drill the reinforcing band [16] and doublers [20] through the existing
reinforcing band rivet holes. Remove the doublers.
50. Continue the rivet pattern on the doublers [20], as started in step 49, around the
louver cut out with a pitch of approximately 1 inch while maintaining standard
edge clearances (twice rivet diameter + 1/16”). Figure 6 illustrates what the
doubler rivet pattern should look like. Move holes if edge clearances are
interfered with by other assembly members.
51. Fit doublers [20] back into place and align the Top 4 Louvers [6] and [13] and
clamp into place, trimming the louver flanges as necessary.
52. Match drill louvers and cowling skin to the holes drilled in the doubler in step
50.
53. Remove the louvers, doublers and reinforcing band. De-burr all drilled holes.
Apply sealant to all faying surfaces, reinstall and Cleco into place.
54. Complete the riveting of [6] ([13]), [20], [16] and [17] using standard
aerospace practices.
Document Number A726-005, Rev 0, December 2008
8
Figure 3 UPPER LOUVER TEMPLATE A02-02-001
Figure 4 LOWER LOUVER TEMPLATE A02-02-002
Document Number A726-005, Rev 0, December 2008
9
Figure 5 CUTTING TOP 3 AND TOP 4 LOUVER CUTOUTS
Figure 6 SAMPLE LOUVER-DOUBLER RIVET PATTERN
Document Number A726-005, Rev 0, December 2008
10
Figure 7 COWLING LOUVER AND DOUBLER INSTALLATION
Figure 8 TOP 4 LOUVER + TOP BACK DOUBLER INSTALLATION
Document Number A726-005, Rev 0, December 2008
11
Figure 9 COWLING REINFORCING BAND AND CLOSURE SECTION
Document Number A726-005, Rev 0, December 2008
12
2.2
CBT IRSS DEVICE
Install the CBT IRSS device [2] according to the following procedure:
1. If in place, unfasten and remove the cowling.
2. Remove the OEM tailpipe starting with disconnecting the fuel drain from the
OEM tailpipe.
3. Support the tailpipe and loosen the bolt on the existing v-band clamp until the
clamp may be removed.
4. Lift the OEM tailpipe off of the engine flange and remove.
5. Lift the CBT into place, locating the alignment pins and aligning with the holes
on the engine mounting flange. The CBT should angle upwards when located
correctly.
6. Seat the CBT mounting flange against the engine flange securely.
7. Install the band clamp around both flanges and hand-tighten the bolt. Lightly
tap around the clamp (while still supporting the tailpipe) with a wooden or
rubber mallet to ensure the tailpipe is seated. Torque to the installation value
indicated in the UH-1H manual.
8. Connect the fuel drain to the fitting on the bottom of the CBT.
9. Replace the cowling, sliding the exit over the CBT, and bolt into place.
Document Number A726-005, Rev 0, December 2008
13
APPENDIX A
ILLUSTRATED PARTS BREAKDOWN
Document Number A726-005, Rev 0, December 2008
ITEM
1
PART NO.
A02-E0-900-0
2
A02-F0-900-0
DESCRIPTION
COWLING MODIFICATION KIT
CENTRE BODY TAILPIPE; IRSS
ASSEMBLY
ITEM
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
PART NO.
A02-E0-001-0
A02-E0-002-0
A02-E0-003-0
A02-E0-004-0
A02-E0-005-0
A02-E0-006-0
A02-E0-007-0
A02-E0-008-0
A02-E0-009-0
A02-E0-010-0
A02-E0-011-0
A02-E0-012-0
A02-E0-013-0
A02-E0-017-0
A02-E0-018-0
A02-E0-019-0
A02-E0-020-0
A02-E0-021-0
A02-E0-022-0
DESCRIPTION
LOUVER; CBT COWLING; LEFT TOP 1
LOUVER; CBT COWLING LEFT TOP 2
LOUVER; CBT COWLING LEFT TOP 3
LOUVER; CBT COWLING LEFT TOP 4
LOUVER; CBT COWLING BOTTOM FRONT
LOUVER; CBT COWLING LEFT BOTTOM 3
LOUVER; CBT COWLING LEFT BOTTOM 4
LOUVER; CBT COWLING RIGHT TOP 1
LOUVER; CBT COWLING RIGHT TOP 2
LOUVER; CBT COWLING RIGHT TOP 3
LOUVER; CBT COWLING RIGHT TOP 4
LOUVER; CBT COWLING RIGHT BOTTOM 3
LOUVER; CBT COWLING RIGHT BOTTOM 4
REINFORCING BAND; COWLING
CLOSURE SECTION; COWLING
TOP FRONT DOUBLER
BOTTOM FRONT DOUBLER
TOP BACK DOUBLER
BOTTOM BACK DOUBLER
ITEM
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
54
55
56
57
PART NO.
A02-00-001-0
A02-CA-800-0
A02-C0-001-0
A02-C0-002-0
A02-CB-800-0
A02-CC-800-0
A02-CD-800-0
A02-CE-800-0
A02-C0-003-0
A02-C0-004-0
A02-C0-005-0
A02-C0-006-1
A02-C0-006-2
A02-DE-800-0
A02-D0-002-0
A02-D0-003-0
A02-D0-004-0
A02-DA-800-0
A02-DB-800-0
A02-DC-800-0
A02-DD-800-0
A02-D0-006-1
A02-D0-006-2
A02-D0-006-3
A02-D0-008-0
A02-AA-800-0
A02-AB-800-0
A02-AA-006-L
A02-AA-006-R
A02-B0-001-0
A02-BB-800-0
A02-BA-800-0
A02-B0-003-1
A02-B0-003-2
A02-B0-003-3
DE5340-1
DESCRIPTION
LABEL - CBT IDENTIFIER
OUTER BODY RING 2
OUTER BODY RING 3
OUTER BODY RING 4
OUTER BODY RING 5
OUTER BODY RING 3 DOUBLER
OUTER BODY RING 4 DOUBLER
OUTER BODY RING 5 DOUBLER
R1 - R2 STANDOFF
R1-R2 STANDOFF DOUBLER
R2 - R3 STANDOFF
R3 - R4 STANDOFF
R4 - R5 STANDOFF
OUTER BODY RING 6
OUTER BODY RING 7
OUTER BODY RING 8
OUTER BODY RING 9
OUTER BODY RING 7 DOUBLER
OUTER BODY RING 8 DOUBLER
OUTER BODY RING 9 DOUBLER
OUTER BODY RING 9 DOUBLER
STANDOFF; OUTER BODY; R6-R7
STANDOFF; OUTER BODY; R7-R8
STANDOFF; OUTER BODY; R8-R9
STANDOFF; OUTER BODY; R5-R6
OUTER BODY RING1
INNER BODY RING1
STRUT COLLAR; SLIDING - LEFT
STRUT COLLAR; SLIDING - RIGHT
INNER BODY RING 2
INNER BODY RING 3
INNER BODY RING 4
STANDOFF; INNER BODY; R1-R2
STANDOFF; INNER BODY; R2-R3
STANDOFF; INNER BODY; R3-R4
INSTALLATION KIT; FUEL DRAIN
APPENDIX B
SCOPE OF SUPPLY
Document Number A726-005, Rev 0, December 2008
No.
QTY./SHIP SET CUSTOMER PART #
DAVIS PART #
PART DESCRIPTION
DRAWING NO.
SERIAL NO.
CRATE#
PACKED BY
CHECKED BY
COWLING MODIFICATION KIT
1
1
A02-E0-001-0
LOUVER, CBT COWLING, LEFT TOP 1
A02-E0-001
2
1
A02-E0-002-0
LOUVER, CBT COWLING, LEFT TOP 2
A02-E0-002
3
1
A02-E0-003-0
LOUVER, CBT COWLING, LEFT TOP 3
A02-E0-003
4
1
A02-E0-004-0
LOUVER, CBT COWLING, LEFT TOP 4
A02-E0-004
5
4
A02-E0-005-0
LOUVER, CBT COWLING, BOTTOM FRONT
A02-E0-005
6
1
A02-E0-006-0
LOUVER, CBT COWLING, LEFT BOTTOM 3
A02-E0-006
7
1
A02-E0-007-0
LOUVER, CBT COWLING, LEFT BOTTOM 4
A02-E0-007
8
1
A02-E0-008-0
LOUVER, CBT COWLING, RIGHT TOP 1
A02-E0-008
9
1
A02-E0-009-0
LOUVER, CBT COWLING, RIGHT TOP 2
A02-E0-009
10
1
A02-E0-010-0
LOUVER, CBT COWLING, RIGHT TOP 3
A02-E0-010
11
1
A02-E0-011-0
LOUVER, CBT COWLING, RIGHT TOP 4
A02-E0-011
12
1
A02-E0-012-0
LOUVER, CBT COWLING, RIGHT BOTTOM 3
A02-E0-012
13
1
A02-E0-013-0
LOUVER, CBT COWLING, RIGHT BOTTOM 4
A02-E0-013
14
1
A02-E0-017-0
REINFORCING BAND, COWLING
A02-E0-017
15
1
A02-E0-018-0
CLOSURE SECTION, COWLING
A02-E0-018
16
2
A02-E0-019-0
TOP FRONT DOUBLER
A02-E0-019
17
2
A02-E0-020-0
BOTTOM FRONT DOUBLER
A02-E0-020
18
2
A02-E0-021-0
TOP BACK DOUBLER
A02-E0-021
19
2
A02-E0-022-0
BOTTOM BACK DOUBLER
A02-E0-022
20
1
A02-02-001-0
UPPER LOUVER TEMPLATE
A02-002-001
21
1
A02-02-002-0
LOWER LOUVER TEMPLATE
A02-002-002
IRSS ASSEMBLY
20
1
A02-F0-900-0
SUPPRESSOR ASSEMBLY
A02-F0-900
B
UPDATED AS PER DAVIS ECC #08-213; ADDED LOUVER INSTALLATION TEMPLATES
T.PREM
26/11/2008
A
INITIAL RELEASE
T.PREM
05/11/2008
B.CHANTER
11/07/2008
W.HUMPHRIES
11/06/2008
DATE
CHECKED
APPROVED
DESCRIPTION
REV.
DESIGNED BY
T.PREM
DRAWN BY
T.PREM
CHECKED BY
B.CHANTER
APPROVED BY
W.HUMPHRIES
DESIGNED DATE
05/11/2008
DRAWN DATE
DAVIS
W.R. DAVIS ENGINEERING LTD.
OTTAWA
CANADA
TITLE
05/11/2008
CBT ASSEMBLY
SCOPE OF SUPPLY
CHECKED DATE
05/11/2008
APPROVED DATE
05/11/2008
DRAWN
CONT. NO.
A726
CONT.NAME
CAGE CODE
CBT
DRAWING NO.
3AB25 A02-06-000
REV.
B
This document unless otherwise noted, remains the property of
W.R. Davis Engineering Limited. It shall not be reproduced or
used for manufacture, design, or construction without the express
authorization of the owner. The recipient, by accepting this
document assumes the custody thereof and under the above
terms, agrees not to allow its use by unauthorized persons without
incurring liability for penalities imposed by law.
APPENDIX C
INSTALLATION DRAWINGS
Document Number A726-005, Rev 0, December 2008
1
2
3
4
5
6
7
8
9
10
11
12
13
14
A
15
16
17
18
19
20
21
ITEM
QTY
PART NUMBER
DESCRIPTION
1
1
A02-E0-900-0
COWLING MODIFICATION KIT
ALUMINUM
2
1
A02-F0-900-0
IRSS ASSEMBLY
SST / INCONEL / TITANIUM
22
23
MATERIAL DESCRIPTION
24
MANUFACTURER
A
B
B
1
C
C
D
D
E
E
2
F
F
G
G
H
H
J
J
K
K
L
L
M
M
N
N
P
P
Q
B
UPDATED AS PER DAVIS ECC #08-190;
ORIGINAL A02-00-000 RENAMED TO A02-F0-900
T.PREM
08/11/04
A
INITIAL PRODUCTION RELEASE
T.PREM
08/05/27
S.REINISCH
08/06/12
W.HUMPHRIES
08/06/12
DRAWN
DATE
CHECKED
APPROVED
REV.
DESCRIPTION
Q
REVISIONS
This drawing unless otherwise noted, remains
the property of W.R. Davis Engineering Limited.
It shall not be reproduced or used for
manufacture, design or construction without
the express authorization of the owner. The
recipient, by accepting this drawing assumes
the custody thereof and under the above
terms, agrees not to allow its use by
unauthorized persons without incurring
liability for penalties imposed by law.
R
UNLESS OTHERWISE SPECIFIED:
1. DIMENSIONS ARE IN: mm
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
DECIMALS
3. SURFACE FINISH: --
SHTA0 101606
1
5. TOLERANCES:
2. SCALE: 1:2
4. REMOVE ALL BURRS
AND SHARP EDGES
18
DESIGNED
.X
±
0.5
.XX ±
--
.XXX ±
--
A. PREM
DRAWN
08/11/04
DATE
A. PREM
08/11/04
DATE
CHECKED
S. REINISCH
WHOLE NUMBERS ±
1.0
ANGLES
±
0.5° APPROVED
HOLE SIZES
±
0.5
HOLE CENTERS
±
0.5
19
DATE
W.HUMPHRIES
20
08/11/04
CONT. NO .
A726
21
R
CBT ASSEMBLY
08/11/04
DATE
W. R. DAVIS ENGINEERING LTD.
OTTAWA
CANADA
Davis
TITLE
CONTRACT NAME
CAGE CODE
CBT
3AB25
22
USED ON
DRAWING NO.
REV.
A02-00-000 B
--
A0
23
SHT
1
OF
1
24
1
2
3
4
5
6
7
8
9
10
12
11
13
14
MS20470AD | 4N
21
A
15
16
17
18
19
20
21
DESCRIPTION
22
23
ITEM
QTY
PART NUMBER
MATERIAL DESCRIPTION
1
1
A02-E0-001-0
LOUVER, CBT COWLING, LEFT TOP 1
ALUMINUM ALLOY, TYPE 2024
2
1
A02-E0-002-0
LOUVER, CBT COWLING, LEFT TOP 2
ALUMINUM ALLOY, TYPE 2024
3
1
A02-E0-003-0
LOUVER, CBT COWLING, LEFT TOP 3
ALUMINUM ALLOY, TYPE 2024
4
1
A02-E0-004-0
LOUVER, CBT COWLING, LEFT TOP 4
ALUMINUM ALLOY, TYPE 2024
5
4
A02-E0-005-0
LOUVER, CBT COWLING, BOTTOM FRONT
ALUMINUM ALLOY, TYPE 2024
6
1
A02-E0-006-0
LOUVER, CBT COWLING, LEFT BOTTOM 3
ALUMINUM ALLOY, TYPE 2024
7
1
A02-E0-007-0
LOUVER, CBT COWLING, LEFT BOTTOM 4
ALUMINUM ALLOY, TYPE 2024
8
1
A02-E0-008-0
LOUVER, CBT COWLING, RIGHT TOP 1
ALUMINUM ALLOY, TYPE 2024
9
1
A02-E0-009-0
LOUVER, CBT COWLING, RIGHT TOP 2
ALUMINUM ALLOY, TYPE 2024
10
1
A02-E0-010-0
LOUVER, CBT COWLING, RIGHT TOP 3
ALUMINUM ALLOY, TYPE 2024
11
1
A02-E0-011-0
LOUVER, CBT COWLING, RIGHT TOP 4
ALUMINUM ALLOY, TYPE 2024
12
1
A02-E0-012-0
LOUVER, CBT COWLING, RIGHT BOTTOM 3
ALUMINUM ALLOY, TYPE 2024
13
1
A02-E0-013-0
LOUVER, CBT COWLING, RIGHT BOTTOM 4
ALUMINUM ALLOY, TYPE 2024
ALUMINUM, 2024-0
24
MANUFACTURER
A
B
B
C
C
D
D
E
F
14
1
A02-E0-017-0
REINFORCING BAND, COWLING
15
1
A02-E0-018-0
CLOSURE SECTION, COWLING
ALUMINUM, 2024-0
16
2
A02-E0-019-0
TOP FRONT DOUBLER
ALUMINUM ALLOY, TYPE 2024
ALUMINUM ALLOY, TYPE 2024
17
2
A02-E0-020-0
BOTTOM FRONT DOUBLER
18
2
A02-E0-021-0
TOP BACK DOUBLER
ALUMINUM ALLOY, TYPE 2024
19
2
A02-E0-022-0
BOTTOM BACK DOUBLER
ALUMINUM ALLOY, TYPE 2024
20
A/R
MS20426AD4
RIVET, 0.125" DIA. COUNTERSUNK HEAD, SOLID
ALUMINUM 2117-T4
21
A/R
MS20470AD4
RIVET, 0.125" DIA. UNIVERSAL HEAD, SOLID
ALUMINUM 2117-T4
E
F
G
G
16
16
8
9
1
2
3
H
10
11
4
H
J
J
14
K
K
18
18
L
L
19
19
M
M
N
N
15
REF
17
17
P
P
5
5
5
5
12
13
6
7
Q
Q
A
INTIAL PRODUCTION RELEASE
K.WONG
08/09/12
REV.
DESCRIPTION
DRAWN
DATE
CHECKED
APPROVED
REVISIONS
This drawing unless otherwise noted, remains
the property of W.R. Davis Engineering Limited.
It shall not be reproduced or used for
manufacture, design or construction without
the express authorization of the owner. The
recipient, by accepting this drawing assumes
the custody thereof and under the above
terms, agrees not to allow its use by
unauthorized persons without incurring
liability for penalties imposed by law.
R
NOTES:
1) FOR INSTALLATION PROCEDURE, REFER TO A726-005 - "CBT INSTALLATION MANUAL".
1
2
3
4
5
6
UNLESS OTHERWISE SPECIFIED:
1. DIMENSIONS ARE IN: mm
8
9
10
11
12
13
14
15
16
17
DECIMALS
3. SURFACE FINISH: --
SHTA0 101606
7
5. TOLERANCES:
2. SCALE: 1:2.5
4. REMOVE ALL BURRS
AND SHARP EDGES
18
DESIGNED
.X
±
T.PREM
0.75 DRAWN
.XX ±
--
.XXX ±
--
WHOLE NUMBERS ±
1.5
ANGLES
±
1.0
HOLE SIZES
±
--
HOLE CENTERS
±
--
19
DATE
08/09/12
DATE
K.WONG
08/09/12
CHECKED
DATE
APPROVED
DATE
T.PREM
W.HUMPHRIES
Q.A. APPROVED
--
20
08/09/12
08/09/12
DATE
--
W. R. DAVIS ENGINEERING LTD.
OTTAWA
CANADA
Davis
TITLE
CONT. NO .
A726
21
R
COWLING MODIFICATION KIT
CONTRACT NAME
CAGE CODE
USED ON
DRAWING NO.
3AB25 A02-00-000
CBT
22
23
REV.
A02-E0-900 A
A0
SHT
1
OF
1
24