require to join 4130 rod into a 18-8 fitting. Basic strength requirement - like to avoid cracking.
Any comments & / or suggestions for filler rod. Looking at TIG process. Not a critical application - short term / corrosion susceptibility not a factor here..
.. I am listening to the potential issues .. better to be prepared ahead of time.
Small antenna .. even with abuse loads - load transfer into the frames should be minor.
Should this become a repeat job - will attempt to provide a test coupon for the bonding next time so i could get some credit...
I feel good about this ..
Planning an internal stiffener/channel that will pick up at frames either end and only have the 2X antenna mounting screws pass through the skin into the channel. channel will be spaced with a Teflon gasket to prevent chaffing. Channel will support support antenna aero...
Dont want to drag this topic away ..
- Back in my apprentice days ..
Great Firewall Design! Great Engine Design !
but has anyone looked into how we gonna replace the magneto ????
U guys are a great wealth of knowledge .. I do appreciate the input.
an Old goat like me - who once knew it all acknowledges your contribution.
- I stopped the Dimple install.
but I do like the isolated-Channel method.
- One only has to accept an reinforced hole (BNX connector .7 Dia.) thru the...
It seems you guys are have little life outside aviation - like me ..
No replies to this question at 9PM & by 4AM - 4X replies .. Haha
Aircraft is a turboprop - 6 passenger - pressurized.
Skin panel is .050 / .032 chem milled with .050 thickness over frames & stringers.
Total thickness .. .032...
Lately projects keep getting more difficult with a new twist each time.
I am required to install an antenna Reinforcement to a .032 Thick crown skin. Customer insists on having no external Doubler.
Since aircraft is CAR 23.573b regulated (DTA Analysis requirement)- the following options are...
I usually have dealt with or seen most hardware issues. Here im helping someone & am frustrated that i know almost nothing about this item.
Latest i hear its from an Elevator on a McDonnell-Douglas A-4.
attached is a 'quasi' data sheet - but it does not tell me much.
Is the pin knocked in /...
specifically
PN 6952-x-xx-x / CSK Head
PN 6953-x-xx-x / Prot Head
Encountered these type on an aileron repair. Have no data & have not been able to locate any pertinent info.
Has anybody in our collective fields of experience dealt with these fasteners?
I have never installed one nor seen one...
RB1957 .. to simplify the story even more ..
Cabin is non-pressurized & antenna is a 17" slim line COM-DAT
- will add couple plies & a .050 alum plate so satisfy any 'non-believers' & provide addition stiffness internally.
Antenna (CI-2580-200) just happens to have an additional BNC connector...
Happy to see that lots of useful information has been provided here.
But can we restrict this to FAR23 aircraft (unpressurized) & keep it moderated.
.. unlikely that someone who just wants to install his GPS antenna will want to dish out for a fuselage mockup & a full series of cyclic testing...
Appreciate the replies. RB1957 input about employing Max Alt press load would be a conservative hoop stress value at 1 cycle/ Flight.
This is for a Cirrus SR20 where its required to add a second .75" dia hole 1.5" away from an existing .75" dia. hole. The location - cabin upper crown is defined...
Neglected to add that this was an pressurized aircraft and additional plies or Doubler would be added to compensate for the .75" Dia hole.
.. also since this is non-pressurized; what is a comparable cyclic loading to calculate the crack growth?
PITA ???
Lately I have several FAR23 aircraft (Composite construction) (Post Amdt. 45/48) certification that I have to demonstrate compliance with FAR23.571 & FAR23.573 ..
We are not dealing with complicated situations - just a few holes to allow the mounting of Antennas - never the less the analysis has...
I understood that he NAPA # does not constitute an approval.
So general consensus is that Test Data approved under a 8110-3 or STC is 'approved data' irrelevant of the ODA# or originating ODA/DER. It can be used to any project given same material /adhesive and specified process is being used ...
In the Canadian system the DAO (ODA) or DAR (DER) opens up a NAPA# which ties in the project to a Federal Transport Canada Registry. I was under the assumption that this ODA file number is a registry to the a FAA system. Any internal ODA reference# is of limited use & only useful dealing with...
This is why im attempting to glean the fine details here ..
In my Master Drawing Document List for Job B .. can I can attach the Allowables Test Report previously done for Job A ??
.. noting that the original test report specifically lists the ODA project # for Job A ..
& the customer for Job B...
This is fun part of this business ..
Test House did not admit it can issue a 8110-3 without ODA project #.
- Outside DER believed it could be done ...
considering amount of $$ we paying .. why would the Test house shoot themselves in the foot ..
