Kirby,
2001 ARAC Committee discussion of origin and possible meaning of 'improperly done' and 'appreciably affect'. See link.
Aviation Rulemaking Advisory Committee, Air Carrier/General Aviation Maintenance Issue Area Clarification of Major/Minor Repairs or Alteration Working Group Task 1 –...
Ed,
Document, DOT/FAA/AR-98/33 - Uniaxial and Biaxial Tests on Riveted Fuselage Lap Joint Specimens, contains fatigue data on riveted dimpled, csk, and csk/bonded joints. A good read.
Regards
ed,
As SW stated, the SR20 fuselage is made from two halves bonded at top and bottom with paste adhesive. Depiction in this article. 99% positive original material is 3M SP381 resin with 7781 glass weave fabric and S2 glass tape. 'B' basis properties for these two were part of AGATE and...
Caution:
The PMA part may be acceptable and approved by the FAA for installation on a specific model but that does not authorize the MRO to install it on an aircraft they do not own and operate. The customer may have a policy that restricts PMA parts on their aircraft for various reasons. You...
The structure you refer to mates up with the Fan Case and as you described rests in a "V" groove. It is my understanding this is the main load path for any axial loads (mostly aft) from the reverser to the engine, which then gets transferred to the pylon. Critical load case for this joint is...
The URL below is to a paper that I found a few years ago and thought it may be useful in the MRB / Liaison role. Seems very relevant to your discrepancy.
http://espace.library.uq.edu.au/view/UQ:131820/A1.3.pdf
Regards
I do not have a copy of PSS-03-1202 but reviewing the ECSS Insert Design Handbook, alpha is defined as the ratio of stiffness between core and face sheets. The alpha equation [Equation # 12.2-4] further states that Gc = shear modulus of the core.
It appears that Gc as defined on page 373 of...
Boeing and Airbus's lists of FCBS do not include safe life certified parts such as landing gear. Airbus specifically identifies the safe life certified parts seperate from the FCBS structure in their Structural Repair Manual.
Kontiki99,
Came across FAA policy PS-ANM-25-05, Risk Assessment Methodology for Transport Category Airplanes, and the associated Transport Airplane Risk Assessment
Methodology (TARAM) Handbook that may provide the information you seek. From the handbook scope;
"This handbook describes the...
Linked is a great paper on the MIL-HDBK-5 conversion to MMPDS. On page 8 they specifically talk about the S basis history, how it was linked to A-basis and what its use will be going forward. It should shed a lot of light on the subject...
AiBBoe,
Not exactly correct. The FAA form 8100-9 is issued under Organization Designation Authorization (ODA) which is issued to a company (in this case Boeing). The company then decides who to appoint as the individual members. A DER cannot sign the 8100-9 form unless they are also an ODA...
The L164 specification is a British Standards Aerospace call out with the full specification being BS L 164 and is titled;
"Sheet and Strip of Aluminium-Coated Aluminium- Copper- Magnesium-Silicon- Manganese Alloy (Solution Treated and Aged at Room Temperature) (Cu 4.4, Mg 0.5, Si 0.8, Mn...
Curled blind rivet heads due to use of single action rivet gun for double action rivets.
Carbon fiber repairs installed over painted surface.
Aircraft slipping off jacks and receiving punctures in the wings / fuselage due to faulty jacking equipment and inattentive operators.
Double drilled...
If it's used for one off repairs on secondary structure with follow on testing I don't see too much of a problem if there is more strain energy available then what the stress strain curves show in the document.
Anyone have the shear stress-strain curve of AF163 film adhesive mfg by 3M? Publicly available?
I'm looking for the data generated following ASTM D 5656 "KGR" extensometer test.
I'm looking to develop an elastic-perfectly plastic idealization of the adhesive for bonded joint analysis.
Values for csk fasteners in the MMPDS are from testing while those for protruding head fasteners are typically a calculated value using Fbru.
I personally would bond a doubler on using EA9394 in lieu of riveting if I had to fix the damage. Holes are always the enemy in composites and bonding...
