Caterpillar cat 349 e l excavator (prefix mpz) service repair manual (mpz0000...
C206 Camera Portal Modification
1. CIVIL AIR PATROLCIVIL AIR PATROL
L3 COMMUNICATIONSL3 COMMUNICATIONS
CDRCDR
T206H AFT BAGGAGE CAMERA PORTAL MODIFICATIONT206H AFT BAGGAGE CAMERA PORTAL MODIFICATION
11/3/201111/3/2011
Prepared by Jason LabontePrepared by Jason Labonte
Project Manager: Ernie SmithProject Manager: Ernie Smith
Designer/Draftsman: Jason LabonteDesigner/Draftsman: Jason Labonte
Structural DER: Venkat RamachandranStructural DER: Venkat Ramachandran
Structural Engineer: Eric LewisStructural Engineer: Eric Lewis
2. MODIFICATION
PROGRAM
1. Aft baggage area camera portal Design
-Flight control cable dwgs
-Structure design (Eric Lewis) Analysis
-Equipment shelf relocation dwgs
2. Belly Door dwgs
3. Electrical Modifications
-Power Outlet at portal design
-Belly Door controls/ indication in cockpit panel design
Slide 1
11-3-2011
4. Master Drawing List (MDL)
5. Certification
3. STCSTC
CERTIFICATION PATHCERTIFICATION PATH
Straight Flight has engaged support from the ARINC ODA to assist in
the issuance of a new FAA STC for the FAA Part 23 Cessna Aircraft
single engine T206H/206H to prevent delay in FAA ACO processing.
Straight Flight has assigned a Managing DER responsible for all
coordination of DER subsets and report generation.
The ARINC ODA shall assist in the following specific areas related to
obtaining STC:
Act as the interface to the FAA in conjunction with SF's Managing DER
Provide guidance, when requested for showing compliance with the
applicable regulatory requirements
Provide guidance, when requested for test plans, test reports, and
analysis reports in order to show compliance to federal regulations
Collaborate with SF's Managing DER to create relevant certification
documentation
Slide 2
11-3-2011
4. DESCRIPTION OF WORKDESCRIPTION OF WORK
The new Camera Portal STC will encompass the following items:
Actual one 18" wide x 19.8” long rectangular camera portal
open to the atmosphere in the fuselage belly centerline at
station FS 130.00 or centered in the aft baggage area.
28VDC power port near new portal rated for 30 Amps.
Electrically driven belly door with controls and indication in
cockpit. Dwg provided.
New cable routing. Dwg provided.
Aft equipment shelf. Dwg provided.
Slide 3
11-3-2011
5. Major Drawing Tree DivisionsMajor Drawing Tree Divisions
Aft Camera Portal ModificationAft Camera Portal Modification
(Cessna Aircraft,(Cessna Aircraft, StationairStationair Model T206H, N176CP)Model T206H, N176CP)
Slide 4
Top level install drawings
• Removal of structure, OEM Flight control cables and wiring. M
• Installation of camera portal assembly structure. M
• Installation of Motor driven sliding Belly Door. D
• Installation of 28 VDC power port. P
• Installation of cockpit controls for Power/ Belly Door and lights. D
• Installation of equipment shelf. D
• Installation of cables. D
D = DWG CREATED
M = MODEL DEFINED
P = IN PROTOTYPE STAGE
NOTE: many of the assemblies called out in drawings are created.
11-3-2011
6. Slide 5
First Look At The Aircraft Modification
Side Profile View
First Discussion of the Modification
DETAIL
11-3-2011
7. Slide 6
First Look At The Aircraft
Aircraft Pre Modification
(Model Created using AUTOCAD Inventor 2012)
Power outlet
Camera Hole
Cable
Routing
Belly Door
Equipment
Shelf
DETAIL VIEW
11-3-2011
8. AFT BAGGAGE CAMERA PORTALAFT BAGGAGE CAMERA PORTAL
PRE MODIFICATION
POST CAMERA HOLE
MODIFICATION
Slide 7
Structure Modification
Removable front plate
& Mount plate to allow installation
Of G3’s RCM P/N# TBA
11-3-2011
9. Slide 8
EXPLODED CAMERA PORTAL INSTALLATION
Structure
Fwd Doubler
Fwd Plate
Intercostal
Doubler
Top Plate
Mount Plate
Aft Doubler
Cut Out OEM Frames
11-3-2011
10. Slide 9
EQUIPMENT SHELF
All equipment
under the aft
baggage area
and empennage
equipment
interfering with
new cable
routing will be
relocated to the
new shelf. The
shelf transitions
across the
empennage and
between frame
145 to 165
Larger view next slide
11-3-2011
30. FEMFEM
Software used: FEMAP & NX NASTRANSoftware used: FEMAP & NX NASTRAN
22”” elements used except at new cutoutelements used except at new cutout
Shell and beam elements usedShell and beam elements used
Compare original and modified fuselage designsCompare original and modified fuselage designs
Constraints
applied at
forward edgeLoad applied
near horizontal
tail
30
Slide 30
11-3-2011
34. Modified DesignModified Design
34
0.040” skin doubler
0.040” side wall
1.5” x 0.75”x 0.09” c‐channel
Skin cutout is 19” x 18” with a 5” radius
Slide 33
11-3-2011
35. Stiffness/Stress ComparisonStiffness/Stress Comparison
Three individual load cases:Three individual load cases:
•• 2,500 lb down load2,500 lb down load
•• 2,500 lb lateral load2,500 lb lateral load
•• 80,000 in80,000 in--lb torsion moment (2500 lb x 36 in.)lb torsion moment (2500 lb x 36 in.)
Compare deflection of loaded nodeCompare deflection of loaded node
•• Down and lateral deflection is lower => stiffness isDown and lateral deflection is lower => stiffness is
higherhigher
•• Torsion deflection is higher => stiffness is lowerTorsion deflection is higher => stiffness is lower
35
Slide 34
11-3-2011
37. Stress ComparisonStress Comparison
Modified Design : down loadModified Design : down load
37
Majority of
region has
stresses in
the 1‐3 ksi
range, with
peak at
cutout of 9
ksi
Slide 36
11-3-2011
38. Stress ComparisonStress Comparison
Original Design : lateral loadOriginal Design : lateral load
38
Majority of
region has
stresses in
the 2‐5 ksi
range, red
region 9‐10
ksi
Slide 37
11-3-2011
39. Stress ComparisonStress Comparison
Modified Design: lateral loadModified Design: lateral load
39
Majority of
region has
stresses in
the 1‐4 ksi
range, with
peak at
cutout of
10 ksi
Slide 38
11-3-2011
40. Stress ComparisonStress Comparison
Original Design: torsion loadOriginal Design: torsion load
40
Majority of
region has
stresses in
the 4‐5 ksi
range, with
peak of 9
ksi
Slide 39
11-3-2011
41. Stress ComparisonStress Comparison
Modified Design : torsion loadModified Design : torsion load
41
Majority of
region has
stresses in
the 1‐4 ksi
range, with
peak at
cutout of
12 ksi
Slide 40
11-3-2011
42. ConclusionConclusion
The modified design is:The modified design is:
•• A stiffer fuselage in down/lateralA stiffer fuselage in down/lateral
bending (4% stiffer)bending (4% stiffer)
•• A softer fuselage in torsion (2% softer)A softer fuselage in torsion (2% softer)
•• The peak stresses at the 5The peak stresses at the 5”” radiusradius
cutout are slightly higher than thecutout are slightly higher than the
original stressesoriginal stresses
42
Slide 41
11-3-2011
43. Future WorkFuture Work
Future Analysis WorkFuture Analysis Work
•• Modify FEM per actual aircraftModify FEM per actual aircraft
installationinstallation
•• Look at going to 0.032 inchLook at going to 0.032 inch doublerdoubler
•• Cable Routing AnalysisCable Routing Analysis
•• Structural Analysis ReportStructural Analysis Report
43
Slide 42
11-3-2011
44. Certification StatusCertification Status
Original Certification Plan Submitted July 2011Original Certification Plan Submitted July 2011
•• Approximately 50 comments receivedApproximately 50 comments received
•• All comments workedAll comments worked
Rev A of Certification Plan Submitted Oct 2011Rev A of Certification Plan Submitted Oct 2011
•• Three Additional Unit Members AddedThree Additional Unit Members Added
AcousticsAcoustics
FlutterFlutter
LightningLightning
Awaiting Approval of Certification PlanAwaiting Approval of Certification Plan
44
Slide 43
11-3-2011
45. Engineers / Managers:Engineers / Managers:
•John May - ARINC ODA, Administrator - 719.574.9001
•Ernest Smith - Straight Flight, Project Manager – 303.867.9777
•Jason Labonte - Straight Flight, Designer / CAD Draftsman - 303.867.9775
•Venkat Ramachandran - Structures DER / Managing DER - 303.514.1882
•Mike Gukich - Flight Test DER - 303.752.0468
•David Barnes - Flight Analyst DER - 303.666.8266
•Karl Jones - Electrical DER - 303.404.3856
•Chuck Goodard - Mechanical Systems DER - 336.602.2159
•Robert Husted - Program DAR - 303.550.6507
•Ralph Rissmiller – Flight Test Pilot DER – 316.253.6182
•Brian Gothan – Sheet Metal Lead – 303-799-8906
Slide 44
11-3-2011
