Results
2024-05-09: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. This AD was prompted by a report of a crack at fuselage station (STA) 1640 frame web common to the lower hinge intercostal tee clip center hole of the upper fastener row. This AD requires a maintenance records check for existing repairs at STA 1640, repetitive ultrasonic (UT) inspections for cracking of the frame web, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
95-26-14: This amendment adopts a new airworthiness directive (AD) that applies to Beech Aircraft Corporation (Beech) Model 1900D airplanes. This action will require inspecting the cabin partition to ensure that a right-hand forward partition bracket exists on certain airplanes, installing this bracket if it does not exist, and improving the right-hand forward partition installation on all affected airplanes. The actions specified by this AD are intended to prevent cabin partition failure because of a structural deficiency in the bracket or if the bracket is not installed, which, if not detected and corrected, could cause passenger injury if the partition could not withstand the load incurred with the baggage compartment loaded to its 250-pound limit.
96-01-02: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires a visual inspection to detect cracks or discrepancies in the aft mount beam assembly of the engines; and replacement of the cracked or discrepant aft mount beam assembly with a new assembly, or a previously inspected and re-identified assembly. That amendment was prompted by reports of cracking in a certain aft mount beam assembly. This new amendment requires additional inspections to detect cracks or discrepancies in the subject area, and various follow-on actions. The actions specified by this amendment are intended to prevent cracks in the aft mount beam assembly of the engines, which could result in loss of the capability of the aft mount beam assembly to support engine loads, and possible separation of the engine from the airplane.
2002-20-07 R1: This amendment revises an existing airworthiness directive (AD), applicable to all Boeing Model 737 series airplanes, that currently requires installation of a new rudder control system and changes to the adjacent systems to accommodate that new rudder control system. That amendment would have superseded seven existing ADs; however, this new amendment removes any reference to superseding four of those seven ADs. This new amendment is prompted by an FAA determination that the requirements of those four ADs must remain in effect until installation of the new rudder control system and corresponding changes to the adjacent systems. The actions specified in this AD are intended to prevent an uncommanded rudder hardover event and consequent loss of control of the airplane due to inherent failure modes, including single-jam modes, and certain latent failures or jams combined with a second failure or jam.
2024-03-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports that some overheat detection sensing elements of the bleed air leak detection system were manufactured with insufficient salt fill, which can result in an inability to detect hot bleed air leaks. This AD requires maintenance records verification, and if an affected part is installed, would prohibit the use of certain Master Minimum Equipment List (MMEL) items under certain conditions by requiring revising the operator's existing Minimum Equipment List (MEL). This AD also requires testing the overheat detection sensing elements, marking each serviceable sensing element with a witness mark, and replacing each nonserviceable part with a serviceable part. This AD also prohibits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
95-26-11: This amendment supersedes an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that currently requires visual inspections to detect cracking of the fittings that attach the aft pressure bulkhead to the fuselage stringers. That AD also currently requires replacement of cracked fittings, and repair of adjacent structure if found to be cracked. This amendment requires new repetitive inspections to detect cracking of the fittings and of the splice tab of the aft pressure bulkhead, and corrective actions, if necessary. This amendment is prompted by the results of the visual inspections performed in accordance with the existing AD, which indicate that the visual inspection is inadequate to detect fatigue cracking. The actions specified in this AD are intended to prevent fatigue cracking of the aft pressure bulkhead, which could lead to failure of the end fittings and splice tabs, and subsequent rapid decompression of the airplane during flight.
2018-02-10: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engines. This AD was prompted by the discovery of multiple cracked outer diffuser cases. This AD requires initial and repetitive inspections to detect cracks in the outer diffuser case and removal from service of cases that fail inspection. We are issuing this AD to address the unsafe condition on these products.
95-26-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that currently requires repetitive purging of the hydraulic system and installation of a spoiler actuator that has been previously certified. That AD was prompted by a report of damage to the locking mechanisms on some pistons of the spoiler actuators. The actions specified by the AD are intended to prevent uncommanded extension of the lift spoiler in the event of loss of hydraulic pressure in the spoiler actuator. This amendment establishes an increased life limit for certain spoiler actuators, and provides an optional terminating action for the requirements of that AD. This amendment also limits the applicability of the rule to fewer airplanes.
2018-02-09: We are superseding Airworthiness Directive (AD) 2008-06-20 R1, which applied to all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes, and certain Model F28 Mark 1000, 2000, 3000, and 4000 airplanes. AD 2008-06-20 R1 required revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness for certain airplanes, and the maintenance or inspection program, as applicable, for certain other airplanes, to incorporate new limitations for fuel tank systems. AD 2008-06-20 R1 also clarified the intended effect on spare and on-airplane fuel tank system components, regarding the use of maintenance manuals and instructions for continued airworthiness. This new AD was prompted by revised fuel airworthiness limitation items (ALI) tasks, and critical design configuration control limitations (CDCCL) items, and associated [[Page 2900]] thresholds, intervals, and instructions. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. We are issuing this AD to address the unsafe condition on these products.
91-04-04: 91-04-04 AIRBUS INDUSTRIE: Amendment 39-6895. Docket No. 90-NM-224-AD. Applicability: Model A320-111, A320-211, and A320-231 series airplanes, equipped with twin wheel axles; Serial Numbers 002 through 044, 052 through 055, 059 through 073, 076 through 078, and 081; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect defects in the main landing gear (MLG) sliding tube assemblies, accomplish the following: A. Prior to the accumulation of 6,600 landings, or within 30 days after the effective date of this AD, whichever occurs later, accomplish the following in accordance with Airbus Industrie Service Bulletin A320-32-1031, Revision 1, dated March 19, 1990: 1. Perform an inspection of the MLG wheel axles, using "Stresscan 500C" test equipment. 2. Identify the part number of the MLG sliding tube assemblies. 3. Replace all sliding tube assemblies identified as suspect. NOTE: The Airbus Industrie service bulletin references Dowty Rotol Service Bulletin 200-32-70, Appendix A, dated December 7, 1989, for additional instructions. B. If defects are found as a result of the inspection required by paragraph A. of this AD, prior to further flight, replace all sliding tube assemblies, in accordance with Airbus Industrie Service Bulletin A320-32-1031, Revision 1, dated March 19, 1990. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6895, AD 91-04-04) becomes effective on March 19, 1991.