SOLICITATION NOTICE
15 -- AH-1 Main Rotor Blade Static Testing and Expanded Repairs - J&A
- Notice Date
- 11/1/2012
- Notice Type
- Presolicitation
- NAICS
- 336411
— Aircraft Manufacturing
- Contracting Office
- Department of the Navy, Naval Air Systems Command, NAVAIR HQ, Building 2272, 47123 Buse Road Unit IPT, Patuxent River, Maryland, 20670, United States
- ZIP Code
- 20670
- Solicitation Number
- N0001913P2PY037
- Archive Date
- 11/30/2012
- Point of Contact
- Audra J Jones, Phone: 301-757-5251, Andrew H Warner, Phone: (301) 757-5250
- E-Mail Address
-
Audra.Jones@navy.mil, andrew.warner@navy.mil
(Audra.Jones@navy.mil, andrew.warner@navy.mil)
- Small Business Set-Aside
- N/A
- Description
- J&A The Naval Air Systems Command intends to award a sole source delivery order under BOA N00019-11-G-0003 to Bell Helicopter Textron Inc, 600 Hurst Blvd, Hurst, TX 76053, for AH-1 Main Rotor Blade Static Tesing and Expanded Repairs. Due to recently found cracks at the AH-1 Main Rotor Blade tip weight retention the following efforts are required: 1. Define requirements for blade tip static test and generate test request. 2. Design test fixture and generate test plan. 3. Design tip splice joint. 4. Design and procure alternate fasteners. 5. Fabricate and install tip splice joint (2 test parts and 1 DT for verification). 6. Modify tip weight support to accommodate test fixture (10 total parts). 7. Fabricate and set up test fixture. 8. Conduct static test of up to 10 test specimens. 9. Summarize test data and write test report. Options are requested for the following: The Contractor shall perform the non-recurring Engineering tasks required for expanded repair limits. The scope includes: • Creating a finite element model of the critical AH-1 blade section • Evaluating the state of stress at the apex of the spar • Evaluating the effect of a Kt caused by pitting at the apex of the spar (modeled by FEM) • If the stress at the apex of the spar with the Kt for pitting is sufficiently low, then the slick bond allowable will be increased. • As a result of this effort, the Contractor shall create graphics to support the incorporation of the repair allowance information into the aircraft manuals by the Government FST. Option 2- Expanded trim and/or rebond limitiations on doubler stack • Reviewing results of 212 blade doubler disbond evaluation and growth analysis • Comparing the 209 and 212 doubler geometry and loading for similarities/comparability • Building finite element model of the 209 inboard geometry to evaluate impact of doubler trim/rebond if similarity is insufficient. • FE Analysis • As a result of this effort, the Contractor shall create graphics to support the incorporation of the repair allowance information into the aircraft manuals by the Government FST. Option 3 - Zoning the allowable proximity and size of repairs near the spar & Non-flush skin patch over spar • Rotor Stress analysis will evaluate the impact of this repair by o Using FEM of critical blade section modified to include an overlap patch of the skin, evaluating the stress in the spar to ensure that the patch does not significantly affect the stress in the spar. o Recommend size limitations on overlap patch based on similar blade field experience. o Model stresses at the bond line of the overlap patch and compare to adhesive allowable. • Aerodynamics will evaluate the performance impact of the overlap patch in the recommended zones as developed by rotor stress • Rotor design will o Evaluate the effect of the proposed overlap patch zones on the weight and balance requirements of the blade to insure proper coverage for weight adjustments. o Provide a historical overview of the successful use of overlap patch on similar metallic blades as applicable. • As a result of this effort, the Contractor shall create graphics to support the incorporation of the repair allowance information into the aircraft manuals by the Government FST. Option 4 - Expanded Spar Thickness Limits at outboard end • Demonstrate that a splice over tip weight joint so that the loading is sufficiently carried through the bond and overlap material which will allow for thinner spar material. • As a result of this effort, the Contractor shall create graphics to support the incorporation of the repair allowance information into the aircraft manuals by the Government FST. Option 5 - Repairs over the tip doubler • Rotor Stress analysis will evaluate the impact of this repair by method similar to that described for Option 3. This will include a finite element model of the outboard tip doubler and proposed repair to evaluate post-repair stress state. • As a result of this effort, the Contractor shall create graphics to support the incorporation of the repair allowance information into the aircraft manuals by the Government FST. Option 6 - Full chord skin replacement outboard end of blade, approx 36" • Destructive testing of a repaired asset to verify manufacturing quality • Analysis (static) • As a result of this effort, the Contractor shall create graphics to support the incorporation of the repair allowance information into the aircraft manuals by the Government FST. Option 7 - Zoning the allowable proximity and size of repairs near the doubler stack • Reviewing results of 212 blade doubler disbond evaluation for stress concentrations near the doubler stack to determine acceptable proximity of repairs. • Comparing the 209 and 212 doubler geometry and loading for similarities/comparability • Building a finite element model of the 209 inboard geometry to evaluate stresses in the proximity of the doubler if similarity is insufficient. This analysis will consider smooth dents that could potentially be left unrepaired. • As a result of this effort, the Contractor shall create graphics to support the incorporation of the repair allowance information into the aircraft manuals by the Government FST. Ms Barbara Russell, 817-280-2011 is the point of contact at Bell Helicopter Textron Inc for any subcontracting opportunities. Numbered Note 22 applies.
- Web Link
-
FBO.gov Permalink
(https://www.fbo.gov/spg/DON/NAVAIR/N00019/N0001913P2PY037/listing.html)
- Place of Performance
- Address: 600 E Hurst Blvd, Hurst, Texas, 76053, United States
- Zip Code: 76053
- Zip Code: 76053
- Record
- SN02923312-W 20121103/121101234956-528767984eaba26d0146c0b186e7cd5f (fbodaily.com)
- Source
-
FedBizOpps Link to This Notice
(may not be valid after Archive Date)
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