Results
2017-23-07: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracks found in the lower chord of the left wing rear spar. This AD requires repetitive inspections for cracking of the lower chord of the rear spar and lower aft skin and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
2001-02-11: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 204B helicopters that requires replacing any main rotor mast assembly (mast), part number (P/N) 204-011-450-001, within 25 hours time-in-service (TIS). This amendment is prompted by the crash of a restricted category Model UH-1B helicopter due to failure of a mast, P/N 204-011-450-001. The same mast P/N is used on the Model 204B helicopters. The actions specified by this AD are intended to prevent failure of the mast and subsequent loss of control of the helicopter.
2018-04-05: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319-112, A319-115, A320-214, A320-232, and A321-211 airplanes. This AD was prompted by in-service experience and further analysis, which showed that the galley 5 without kick-load retainers, was unable to withstand the expected loading during several flight phases or in case of emergency landing. This AD requires modification of galley 5 trolley compartments by adding kick-load retainers. We are issuing this AD to address the unsafe condition on these products.
72-21-07: 72-21-07 PIPER AIRCRAFT CORP: Amendment 39-1540 as amended by Amendment 39-2586. Applies to PA23-250 airplanes, S/Ns 27-4575 to 27-4587 inclusive, 27-4589 to 27- 4620 inclusive, 27-4622 to 27-4672 inclusive, 27-4674 to 27-4682 inclusive, and 27-4684 to 27- 4694 inclusive, and PA-23-250 airplanes which have been altered by substitution of Piper P/N 32958-00, Section Assembly - Fuselage, Nose, 34552-00, Section Assembly - Fuselage, Nose, or 33346-05, Radome Assembly for Piper P/N 30517-00, Section Assembly - Fuselage, Nose, or 30517-06, Section Assembly - Fuselage, Nose, certificated in all categories. Compliance required within 30 days after the effective date of this AD, unless already accomplished. To improve the longitudinal stability characteristics and to prevent longitudinal stick force reversal during certain flight conditions, accomplish the alteration contained in Piper Service Bulletin No. 345, dated 7 Oct. 1971; or an equivalent method approved by the Chief,Engineering and Manufacturing Branch, FAA Eastern Region. Upon request through a maintenance inspector, accompanied by substantiating data, the compliance time specified in the AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Amendment 39-1540 was effective October 19, 1972. This amendment 39-2586 is effective April 29, 1976.
2007-13-14: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: Two cases of rudder lower support with cracks have been reported, waiting for a technical solution, inspections are required. We are issuing this AD to require actions to correct the unsafe condition on these products.
2001-03-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B19 series airplanes. This action requires repetitive ultrasonic inspection to detect damage of the actuator lugs of the flight spoiler center hinge; corrective action, if necessary; and eventual replacement of the flight spoilers with new, improved spoilers. This action is necessary to prevent uncommanded deployment of a flight spoiler, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2018-04-08: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the gore web lap splices of the aft pressure bulkhead are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections of the gore webs, gore web lap splices, and repair webs, as applicable, of the aft pressure bulkhead, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products. \n\n((Page 8326))
76-04-10: 76-04-10 PIPER AIRCRAFT: Amendment 39-2531. Applies to Model PA-31-350, S/Ns 31-5001 to 31-7552073 inclusive. Compliance required within the next 100 hours' time in service after the effective date of this AD unless already accomplished. To prevent the hazards associated with toxic fumes from the battery being drawn into the cabin, accomplish the following: (a) Relocate and modify the battery drain and vent system in accordance with Piper Service Bulletin No. 460A, dated January 23, 1976, or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be increased by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region. This amendment is effective March 5, 1976.
2007-13-12: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: EASA EAD 2006-0072-E was issued on 31st March 2006 following a further failure of the forward support of the Main Wing Outboard Flap (MWOF), caused by corrosion. This condition, if not corrected, may cause surface twisting during deployment at landing. The analysis of that event highlighted the need for the reduction of the previous inspection interval which was mandated by ENAC through AD 2004-523, approved by EASA with reference 2004-12521. We are issuing this AD to require actions to correct the unsafe condition on these products.
2000-25-54: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2000-25-54, which was sent previously to all known U.S. owners and operators of Agusta (Agusta) S.p.A. Model A109E helicopters by individual letters. This AD requires, before each start of the engines, visually checking both sides of each tail rotor blade (blade) for a crack and, at specified intervals, inspecting each blade for a crack using a 5-power or higher magnifying glass. Dye-penetrant inspecting each blade for a crack is also required at specified time intervals. If a crack is found, replacing the blade with an airworthy blade is required before further flight. This amendment is prompted by five reports of cracked tail rotor blades. The actions specified by this AD are intended to prevent failure of a blade and subsequent loss of control of the helicopter.