Results
96-18-21: This amendment supersedes Airworthiness Directive (AD) 75-26-15, which currently requires repetitively inspecting the aileron mass balance clamp unit attachment for looseness on Pilatus Britten-Norman Ltd. (Pilatus Britten-Norman) BN-2A and BN2A MK. 111 series airplanes, and modifying the aileron and mass balance clamp unit if any looseness is found. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. This action retains the repetitive inspections required by AD 75-26-15, and requires modifying the aileron and mass balance unit (at a certain time) as terminating action for the repetitive inspection requirement. The actions specified in this AD are intended to prevent failure of the aileron mass balance attachment, which could result in loss of control of the airplane.
77-07-07: 77-07-07\tAVCO LYCOMING: Amendment 39-2864 as amended by Amendment 39-3415. Applies to the O-320-H2AD series Lycoming engines Serial Numbers L-101-76 thru L-1049-76. \n\tCompliance required within 50 hours in service after the effective date of this AD, unless previously accomplished. \n\tTo prevent the incorrect installation of the P/N LW-14784 or the P/N LW-15481 oil level gage modify the P/N 75675 oil filler extension by installing a P/N LW-15498 perforated sleeve as follows: \n\t(a)\tRemove the P/N 75675 oil filler extension from the engine. \n\t(b)\tInsert the P/N LW-15498 perforated sleeve in the oil filler extension. Make certain that the flanged end rest evenly against the recessed surface below the threads inside of the oil filler extension. Locate and mark the perforated sleeve where it protrudes through the base of the oil filler extension. \n\t(c)\tAfter locating this position, remove the perforated sleeve from the oil filler extension and insert a length of 3/4 inch diameter steel rod into the sleeve. Place the steel rod and sleeve in a vise or other suitable holding device and with a narrow chisel cut the perforated sleeve as shown in figure 1 at the location marked per instructions of item (b) of this AD. \n\t(d)\tRemove the 3/4 inch diameter steel rod and install the perforated sleeve in the oil filler extension. Bend the chiseled section of the perforated sleeve at the seam to form a tab as shown in figure 2. \n\n\n\n\t(e)\tInstall the reworked oil filler extension and perforated sleeve in the engine, making certain that the P/N 70457 gasket is properly in place between the oil filler extension and the engine crankcase. Install either P/N LW-14784 or P/N LW-15481 oil level gage. Apply lockwire as required. \n\t(f)\tUpon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the compliance time. \n\t(Note: AVCO Lycoming Service Bulletin No. 407A covers this subject). \n\tAmendment 39-2864 became effective April 11, 1977. \n\tThis amendment 39-3415 is effective February 20, 1979
78-12-10: 78-12-10 SHORT BROTHERS LIMITED: Amendment 39-3236. Applies to Model SD3-30 airplanes certificated in all categories. Compliance is required prior to the accumulation of 4000 landings or prior to accumulating 25 landings after the effective date of this AD, whichever occurs later, unless already accomplished, and thereafter at intervals not to exceed 4000 landings. To prevent failure of the rod end bearing of the nose wheel steering actuator, replace the rod end bearing, P/N MS 21242S8K, with a new part of the same part number in accordance with Section 10, "Accomplishment Instructions" of Menasco Manufacturing Service Bulletin 32-21, dated January 11, 1978, or an FAA approved equivalent. NOTE: Short Brothers Limited Service Bulletin SD3-32-37 covers this same subject. This amendment becomes effective June 26, 1978.
96-18-04: This amendment supersedes two existing airworthiness directives (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that currently require modification of the packing and slide containers of the escape slide, and repetitive inspections of the velcro girt retaining straps of the escape slides at the forward door. The existing AD's were prompted by reports of slide girt material interfering with the girt bar stowage brackets during door opening. This new amendment requires the installation of a new modification, which constitutes terminating action for the repetitive inspection requirements. The actions specified by this amendment are intended to prevent failure or interference of opening of the forward doors, which could delay or impede the evacuation of passengers during an emergency.
2021-04-21: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model EC120B helicopters. This AD was prompted by a report of broken and bent attachment bolts of the main rotor (MR) hub scissors assembly. This AD requires an inspection of the attachment bolts of the MR hub scissors assembly for discrepancies and repair if necessary; part marking of the attachment bolts of the MR hub scissors assembly; and repetitive inspections of the part marking of the attachment bolts, and repair if necessary; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2021-05-15: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD was prompted by a report that the cabin lateral sliding plug door failed its emergency jettisoning test; subsequent investigation revealed that the jettison handle cable interfered with the cable clamps. This AD requires modifying the release system of each cabin lateral sliding plug door, or modifying the design of the jettison system of each cabin lateral sliding plug door, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
91-21-12: 91-21-12 BOEING: Amendment 39-8059. Docket No. 91-NM-86-AD. \n\n\tApplicability: Model 737, 757, and 747-400 series airplanes, equipped with Boeing part number (P/N) 285U0037-104, -105, -201, -202, or -203 series radio control panels, certificated in any category. \n\n\tCompliance: Required within 12 months of the effective date of this AD unless previously accomplished. \n\n\tTo prevent uncommanded frequency changes of the high frequency (HF) and very high frequency (VHF) radios, accomplish the following: \n\n\t(a)\tRemove the P/N 285U0037-104, -105, -201, -202, or -203 series radio control panels and replace them with panels approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\t(b)\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.NOTE: 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\t(c)\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 (39-8059, AD 91-21-12) becomes effective on November 12, 1991.
96-16-07: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-80C2 series turbofan engines. This action supersedes priority letter AD 96-09-01 that currently requires borescope inspections of the rear right hand mount link to determine if the serial number matches those listed in applicable service bulletins as improperly manufactured, and replacement, if necessary, with a serviceable part. This action references a newly revised service bulletin and bases the compliance time on the effective date of this superseding AD for engines installed on McDonnell Douglas MD-11 series aircraft. This amendment is prompted by the availability of the newly revised service bulletin. The actions specified by this AD are intended to prevent rear right hand mount link failure, which could result in engine separation from the aircraft.
96-08-01 R1: This amendment revises airworthiness directive (AD) 96-08-01, that is applicable to Hamilton Standard Model 14RF-9 propellers. The current AD superseded priority letter AD 95-24- 09, and requires an ultrasonic shear wave inspection, adds a one-time visual and fluorescent penetrant inspection, and repair of the propeller blade shank. This revision will add a new shank eddy current inspection and will allow repair of certain blade shanks removed from service under the current AD. The actions specified by this AD are intended to prevent propeller blade separation due to propeller blade shank cracking that can result in loss of control of the aircraft.
74-24-13: 74-24-13 UNITED INSTRUMENTS, INC.: Amendment 39-2028. Applies to P/N 5932 ( ) (Serial Numbers 47851 thru 69000) and P/N 5934 ( ) (Serial Numbers 70,000 thru 102,000, A1 thru A9999, B1 thru B9999, and C1 thru C2860) altimeters installed on various aircraft, such as Piper, Beech, Cessna, Bell, Aero Commander, Schweizer, Enstrom, Helio, American Aviation, Bellanca, et al. Note 1: United Instruments P/N 5932 ( ) altimeters may be additionally identified as TKK Model LA 4 TSO C-10b. United Instrument P/N 5934 ( ) altimeters may be additionally identified as TKK Model LA 7 TSO C-10b. Note 2: These altimeters may also be identified by various aircraft manufacturer's part numbers. Some but not all are: Beech: P/N 50-380094-( ), 50-384119-( ), 58-380011-( ), 58-380012-( ), 58-380041-( ), 100-324056-( ), 169-380073-( ) Cessna: P/N C661011-( ), C661071-( ), C661025-( ), C661014-( ) Piper: P/N 99009-( ), 450-611-( ), 450-694-( ), PS50008-( )-( ), 550-488-( ), 550-489-( ), 550-490-( ), 550-491-( ), 550-492-( ), 550-493-( ), 322-81-03, 322-81-04 Bell: P/N 206-070-263-( ), 47-711-303-( ) Compliance: Required as indicated, unless already accomplished. To prevent being deprived of altimeter readings during certain aircraft operating conditions, accomplish the following: A) Within the next 10 hours' time in service after the effective date of this AD, check each altimeter installed in all aircraft or check the aircraft's permanent maintenance record to determine if the altimeter falls within the Part Number and Serial Number designations set forth in the applicability statement. The owner/operator of the aircraft may make these checks. B) If, as a result of the determinations required by Paragraph A, an altimeter falls within the Part Number and Serial Number designations in the applicability statement, prior to further flight, either comply with Paragraph C or install a placard on the instrument panel in clear view of the pilot which states: "AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY" and operate the aircraft in accordance with this limitation. C) On or before November 30, 1976, on any altimeter which falls within the Part Number and Serial Number designations set forth in the applicability statement, either replace the altimeter with an approved replacement part, an altimeter from outside the applicable Serial Numbers, or modify the existing altimeter in accordance with the United Instruments, Inc., Service Bulletin No. 1, dated September 19, 1974, or subsequent approved revisions. A modified altimeter will be identified by a 1/4-inch white dot painted alongside the nameplate on the back of the case. Upon compliance with this paragraph, the requirements of Paragraph B are no longer applicable. D) Any alternate means of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. E) Compliance with Paragraph B of this AD is notrequired if the aircraft has two sensitive altimeters installed. In the event of failure of one of the altimeters, where both altimeters are noted in the applicability statement, compliance with Paragraph B and/or C is required. This amendment becomes effective December 5, 1974.