Results
76-11-03: 76-11-03 SCHEMPP HIRTH and BURKHART GROB: Amendment 39-2626. Applies to Standard Cirrus gliders certificated in all categories, Serial Numbers 1 through 604 for Schempp Hirth and Serial Numbers 1G through 200G for Burkhart Grob. Compliance is required as indicated, unless already accomplished. To prevent possible tow release lever jamming and consequent crashing of the glider during a winch launch, accomplish the following: (a) Within the next 10 flights after the effective date of this AD, visually inspect the clearance between the tow release lever and the occupied pilot seat by performing a functional inspection of the operation of the tow release mechanism. If the occupied seat interferes with the operation of the tow release mechanism, before further flight, comply with paragraph (c) of this AD. (b) Within the next 50 flights after the effective date of this AD, unless earlier compliance is required pursuant to paragraph (a) of this AD, comply with paragraph (c) of this AD. (c) Reinforce the pilot seat in accordance with steps 2 and 3 of the paragraph entitled "Instructions" of Schempp Hirth Technical Note 278-18, dated December 8, 1975, or an FAA-approved equivalent, except that the minimum overall depth of the stiffening material used under step 2b should be 1/3 its width. This amendment becomes effective June 10, 1976.
2020-26-15: The FAA is superseding Airworthiness Directive (AD) 2016-07- 14, which applied to certain Airbus Model A319-111, -112, -113, -114, - 115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, - 213, -231, and -232 airplanes. AD 2016-07-14 required replacing the clips, shear webs, and angles, related investigative actions, and repair if necessary. This AD retains the actions of AD 2016-07-14, and requires modifying (replacing) the clips, shear webs, and angles at a certain rear fuselage area with new parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA has also determined that additional airplanes are subject to the unsafe condition. This AD was prompted by fatigue testing that determined that fatigue damage could appear on clips, shear webs, and angles at certain rear fuselage sections and certain frames. The FAA is issuing this ADto address the unsafe condition on these products.
2010-03-02: We are adopting a new airworthiness directive (AD) for the Lifesavings Systems Corp., D-Lok Hook assembly installed on certain rescue hoist assemblies. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states that rescue hoist operators have reported surface irregularities and discontinuities on certain D-Lok Hooks because of an unapproved change in the hook design and manufacturing process from forged material to cast material that have different physical properties. The actions are intended to prevent failure of a hook during rescue hoist operations, loss of the rescued passenger, and subsequent serious injury or fatality.
2020-26-10: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. (Leonardo) Model A119 and AW119 MKII helicopters. This AD requires revising the existing Rotorcraft Flight Manual (RFM) for your helicopter and installing a placard to prohibit intentional entry into autorotation. This AD would also allow replacement of an affected fuel control unit (FCU) as an optional terminating action for the RFM revision and placard installation. This AD was prompted by reports that certain FCUs may not have been calibrated to specification during overhaul. The actions of this AD are intended to address an unsafe condition on these products.
91-14-23: 91-14-23 BOEING: Amendment 39-7063. Docket No. 91-NM-60-AD. \n\n\tApplicability: Model 747-400 series airplanes delivered with Door 5 Crew Rest Stations, certificated in any category. \n\n\tCompliance: Required within 60 days after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent the occurrence of smoke and fire in the Door 5 Crew Rest Station, accomplish the following: \n\n\tA.\tDisconnect, cap, and stow the wires connected to circuit breakers C8823 and C8824 at the P84 circuit breaker panel, which provides electrical power to the crew rest bunk reading lights, Grimes Part Number 15-0175-9. Circuit breakers C8823 and C8824 must be collared in the open position and labeled INOPERATIVE. \n\n\tB.\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\tC.\tSpecial 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. \n\n\tThis amendment (39-7063, AD 91-14-23) becomes effective on August 9, 1991.
2003-26-10: This amendment adopts a new airworthiness directive (AD) that is applicable to the Airbus airplanes listed above. This action requires a one-time inspection for cracking of the lower outboard flange of gantry No. 4 in the main landing gear bay area, and repair if necessary. This action is necessary to find and fix such cracking, which could result in reduced structural integrity of the fuselage, and consequent rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
95-02-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires modification of the fire extinguishing system in the number two engine strut. This amendment is prompted by reports of chafing of the fire extinguishing tubes in a certain inboard strut to wing area. The actions specified by this AD are intended to prevent chafing of the fire extinguishing tube; such chafing could cause cracking of the tube and consequently produce a hole in the fire extinguishing tube, which could prevent the proper distribution of the fire extinguisher agent within the nacelle in the event of a fire.
2020-26-12: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP Model Gulfstream G280 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a Civil Aviation Authority of Israel (CAAI) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
78-20-04: 78-20-04 MCDONNELL DOUGLAS: Amendment 39-3308. Applies to DC-10-10, -10F, -30, -30F and -40 airplanes certificated in all categories. \n\n\tCompliance is required as indicated unless already accomplished. \n\n\tTo prevent failure of an outboard slat drive arm or drum shaft, accomplish the following: \n\n\t(a)\tWithin the next 1500 hours' time in service after the effective date of this AD, unless the inspection and modifications specified in McDonnell Douglas DC-10 Service Bulletin 27-160, dated March 1, 1978, are already accomplished, inspect the outboard slat drive arms ultrasonically for cracks in accordance with McDonnell Douglas DC-10 Service Bulletin A27-160 Revision 2, dated March 22, 1978. \n\n\t(b)\tWithin the next 4,000 hours' time in service after the effective date of this AD, inspect by magnetic particle methods for cracks and modify or replace the outboard slat drive arms and drum shafts in accordance with McDonnell Douglas DC-10 Service Bulletin 27-160, dated March 1, 1978. \n\n\t\t(1)\tAs an alternate to applying sealant in accordance with Service Bulletin 27-160, it is permissible to install a lubrication fitting and fillet seal in accordance with McDonnell Douglas DC-10 Service Bulletin 27-161, dated March 3, 1978, and, thereafter, at intervals not to exceed 2500 hours' time in service apply MIL-G-81322 grease or equivalent to the ARH 7011-1 bolt assembly fitting. \n\n\tNOTE: Service Bulletin A27-160 Revision 2 dated March 22, 1978, Service Bulletin 27-160 dated March 1, 1978 and Service Bulletin 27-161 dated March 3, 1978 are the only versions of the service bulletins suitable for compliance with paragraphs (a) and (b) of this AD. \n\n\t(c)\tAny outboard slat drive arm or drum shaft found to be cracked must be replaced prior to further flight. \n\n\t(d)\tEquivalent inspections, modifications or parts may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(e)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for accomplishment of inspections required by this AD. \n\n\tThis amendment becomes effective November 7, 1978.
95-14-09: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 60 airplanes. This action requires inspection to detect bends in or damage to the fuel crossflow tube; inspection to determine clearance between the fuel crossflow tube and the flight control cables; and replacement or repair of the tube, if necessary. This amendment is prompted by reports of damage to the fuel crossflow tube and inadequate clearance between the fuel crossflow tube and the flight control cables due to bends in the fuel crossflow tube. The actions specified in this AD are intended to prevent chafing and eventual failure of the fuel crossflow tube due to inadequate clearance between the tube and the flight control cables; this condition could result in loss of fuel from one fuel tank during normal operating conditions or loss of fuel from both main fuel tanks during fuel cross feeding operations.