Federal Aviation Administration July 7, 2016 – Federal Register Recent Federal Regulation Documents
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Airworthiness Directives; Airbus Airplanes
We are revising an earlier proposed airworthiness directive (AD) for all Airbus Model A300 B4-603, B4-620, B4-622, B4-605R, B4- 622R, F4-605R, F4-622R, and C4-605R variant F airplanes. The NPRM proposed to require repetitive detailed inspections of the lower frame fittings, related investigative actions, and corrective actions if necessary. The NPRM was prompted by reports of cracks in the frame base fittings connecting the frame lower positions to the center wing box. This action revises the NPRM by replacing the proposed requirements with new repetitive detailed inspections for cracking of the lower frame fittings of the frame foot, and replacement with a new frame foot if cracking is found. This action also provides optional terminating action for the repetitive inspections. We are proposing this supplemental NPRM (SNPRM) to detect and correct cracking of the lower frame fittings, which could result in reduced structural integrity of the airplane. Since these actions impose an additional burden over those proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on these proposed changes.
Airworthiness Directives; The Boeing Company Airplanes
We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 767-200, and -300 series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the frame-to-floor-beam joints and frames common to shear ties at certain locations of fuselage structure are subject to widespread fatigue damage (WFD). This proposed AD would require repetitive inspections for cracking of the frame inner chords and webs common to the floor beam joint and at frames common to the shear ties at certain sections on the left and right fuselage sides, and corrective action if necessary. We are proposing this AD to detect and correct cracking of the frame inner chords and webs common to the floor beam joint and at frames common to the shear ties at certain sections on the left and right fuselage sides, which could result in reduced structural integrity of the airplane.
Airworthiness Directives; Airbus Airplanes
We propose to supersede Airworthiness Directive (AD) 2011-17- 05, for certain Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C airplanes. AD 2011-17-05 currently requires repetitive inspections in sections 13 through 18 of the fuselage between rivets of the longitudinal lap joints between frames (FR) 18 and 80 for cracking, and repair or modification if necessary. Since we issued AD 2011-17-05, we have determined that a revised inspection program is necessary. This proposed AD would include a revised repetitive inspection program of all longitudinal lap joints and repairs between frames 18 and 80 to address this widespread fatigue damage (WFD). We are proposing this AD to detect and correct fatigue cracking of the longitudinal lap joints of the fuselage, which could result in reduced structural integrity of the airplane.
Airworthiness Directives; Airbus Airplanes
We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This proposed AD was prompted by a determination that, due to significant differences among all airspeed sources, the flight controls will revert to alternate law, the autopilot (AP) and the auto-thrust (A/THR) will automatically disconnect, and the flight director (FD) bars will be automatically removed. Then, if two airspeed sources become similar while still erroneous, the flight guidance computers will display the FD bars again, and enable the re-engagement of the AP and A/THR. In some cases, however, the AP orders may be inappropriate, such as possible abrupt pitch command. This proposed AD would require a software standard upgrade (modification or replacement) of the three flight control primary computers (FCPCs). We are proposing this AD to prevent autopilot engagement under unreliable airspeed conditions, which could result in reduced controllability of the airplane.
Airworthiness Directives; Embraer S.A. Airplanes
We propose to adopt a new airworthiness directive (AD) for Embraer S.A. Models EMB-500 and EMB-505 airplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as incorrect installation of passenger seat attachment fittings. We are issuing this proposed AD to require actions to address the unsafe condition on these products.
Airworthiness Directives; Textron Aviation Inc. Airplanes
We are superseding Airworthiness Directive (AD) 2008-15-06 for certain Textron Aviation Inc. Models 175 and 175A airplanes (type certificate previously held by Cessna Aircraft Company). AD 2008-15-06 required checking the airplane logbook to determine if the original engine mounting brackets had been replaced. If the original engine mounting brackets were still installed, the AD required repetitively inspecting those brackets for cracks and replacing any cracked engine mounting bracket until all four original engine mounting brackets were replaced. Replacing all four original engine mounting brackets terminated the actions required in AD 2008-15-06. Since we issued AD 2008-15-06, we have determined that the applicability needs to be changed to add one serial number and remove another. This new AD retains the actions required in AD 2008-15-06 and changes the Applicability section. We are issuing this AD to correct the unsafe condition on these products.
Airworthiness Directives; REIMS AVIATION S.A. Airplanes
We propose to adopt a new airworthiness directive (AD) for certain REIMS AVIATION S.A. Model F406 airplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracks found in the horizontal stabilizer rear attach structure and the vertical fin rear spar attach structure. We are issuing this proposed AD to require actions to address the unsafe condition on these products.
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