Tag Archives: Eddy Current

FAA AD 2017-13-07 Airbus Model A319, A320, and A321 series airplanes

SUMMARY: We are adopting a new airworthiness directive (AD) for all Airbus Model A319, A320, and A321 series airplanes. This AD was prompted by a report that a main landing gear (MLG) door could not be closed due to rupture of the actuator fitting. This AD requires repetitive inspections for cracking of the MLG door actuator fitting and its components, and corrective actions if necessary. This AD also requires eventual replacement of all affected MLG door actuator fittings with new monoblock fittings, which would terminate the repetitive inspections. We are issuing this AD to address the unsafe condition on these products. HFEC and LFEC NDT inspections

Link to FAA.gov

http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgad.nsf/0/bbaed0d56e8330798625815400541180/$FILE/2017-13-07.pdf

FAA AD 2015-25-08

SUMMARY: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 777 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the lap splices of the aft pressure bulkhead webs are subject to widespread fatigue damage (WFD) on aging Model 777 airplanes that have accumulated at least 38,000 total flight cycles. This AD requires repetitive inspections for any crack in the aft webs of the radial lap splices of the aft pressure bulkhead, and, if necessary, corrective actions.


FAA AD2015-25-08

 

 

Eddyfi Expands its Family of DefHi® Array Probe

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Québec, November 3, 2015 — Eddyfi is proud to announce the expansion of its family of DefHi array probes for tubing inspection. Eddyfi improved and expanded the selection of heavy wall (HW) DefHi probes to offer superior coverage and penetration in very-low-frequency applications (4 kHz to 60 kHz) such as brass and cupronickel tubing.

Additionally, Eddyfi introduces the all new high frequency (HF) series of DefHi probes. The HF DefHi furthers the already highly versatile reach of the DefHi array probes for tubing. If you need to perform a high-speed, high-resolution, multiple axis inspection of thin-walled titanium (including circumferential cracking at top of tubesheets), 300-series stainless steel, or other high-resistivity materials, Eddyfi now delivers the array solution you need.

Eddyfi DefHi Array Probe

FAA AD 2015-21-08 (Boeing 737 upper wing skin) Eddy Current inspection

This AD requires repetitive eddy current inspections for any cracking in the inspar upper skin, and related investigative and corrective actions if necessary. This AD was prompted by a report that an operator discovered a crack in a certain section of the inspar upper skin, just forward of the rear spar on the right wing. We are issuing this AD to detect and correct any cracking in the inspar upper skin and rear spar upper chord, which could result in the inability of the structure to carry limit load, or result in a fuel leak, which could prevent continued safe flight and landing.

FAA AD2015-21-08

FAA AD 2015-15-06 / Boeing 767

SUMMARY: We are superseding Airworthiness Directive (AD) 2003-13-01 for certain The Boeing Company Model 767 airplanes. AD 2003-13-01 required an inspection to detect cracks and fractures of the outboard hinge fitting assemblies on the trailing edge of the inboard main flap, and follow-on and corrective actions if necessary. For certain airplanes, AD 2003-13-01 required an inspection to determine if a tool runout option has been performed in the area. This new AD reduces certain compliance times, adds airplanes to the applicability, and provides optional terminating action for certain inspections. This AD was prompted by reports of hinge assembly fractures found before certain required compliance times in AD 2003-13-01. We are issuing this AD to prevent the inboard aft flap from separating from the wing and potentially striking the airplane, which could result in damage to the surrounding structure and potential personal injury.

Apex Inspections NDT Seal

Apex Inspections NDT

FAA AD 2015-15-06

FAA AD 2015-20-05 – Lockheed Martin – L188 (Electra)

SUMMARY: We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 188 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the upper and lower wing skin planks at the attachment of the main landing gear (MLG) ribs at certain wing-stations are subject to widespread fatigue damage (WFD). This AD requires an inspection (for cracking) and modification of the chordwise fastener rows of the upper and lower wing planks at the attachments to the MLG ribs at certain wing-stations. We are issuing this AD to prevent fatigue cracking of the upper and lower wing skin planks at the attachment of the MLG ribs, which could result in failure of the wing.

(g) Inspection, Modification, and Corrective Action At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Remove the chord-wise fastener rows of the upper and lower wing planks at the attachments to the MLG ribs at wing-station (WS) 167 and WS 209; do a bolt-hole eddy current (BHEC) inspection to detect cracking of the fastener rows; and replace the original fasteners with new, first oversize fasteners; in accordance with the Accomplishment Instructions of Lockheed Martin Electra Service Bulletin 88/SB-721, dated April 30, 2014. If any cracking is found during any inspection required by this paragraph: Before further flight, repair the cracking, in accordance with the Accomplishment Instructions of Lockheed Martin Electra Service Bulletin 88/SB-721, dated April 30, 2014.

FAA AD2015-20-05

Youtube Link

YouTube link of Electra

FAA AD 2015-19-12 Boeing 767 – Fuselage Skin

This AD was prompted by reports that six fasteners may not have been installed in the left and right stringer 37 (S-37) between body stations (BS) 428 and 431 lap splices on certain airplanes. We are issuing this AD to detect and correct missing fasteners, which could result in cracks in the fuselage skin that could adversely affect the structural integrity of the airplane. Open Hole Eddy Current of 6 fasteners

FAA AD 2015-19-12