Results
58-20-02: 58-20-02 de HAVILLAND: Applies to All Model 104 "Dove" Aircraft. Compliance required by January 1, 1959. In an emergency such as a wheels up landing, the placing of the ground/flight switch on the "Ground" position to minimize fire risk would isolate the fire extinguisher system. Dove Modification 655 has therefore been introduced which provides an electrical supply to the fire extinguisher circuit from the battery side of the ground/flight switch, even when the switch is in the "Ground" position, thus ensuring that the fire extinguisher system is operative at all times. The British Air Registration Board considers this mandatory. The FAA concurs with this action and considers compliance therewith mandatory. (de Havilland TNS CT (104) No. 153 covers the same subject.)
2003-22-14: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly Rolls- Royce plc) models Tay 650-15 and 651-54 turbofan engines with certain part numbered fan blades and fan discs. That AD currently requires initial and repetitive visual and ultrasonic inspections of fan blades for cracks, and, if necessary, replacement with serviceable parts. In addition, that AD requires recording instances when engines are operated in a stabilized manner in newly prohibited ranges. This ad has the same requirements. In addition, this AD requires recording instances when engines are operated inadvertently in reverse thrust in prohibited ranges, and requires before further flight, initial and repetitive ultrasonic inspections of fan blades for cracks and if necessary, dispositioning of fan blades and fan discs, if certain reverse thrust events occurred. This AD is prompted by updated prohibited ranges of engine operation and the introduction of an N1 Alert System in Fokker Model F.28 Mark 0100 airplanes with Tay 650-15 engines installed. We are issuing this AD to prevent fan blade failures, which can result in an uncontained engine failure, engine fire, and damage to the airplane.
72-13-08: 72-13-08 FAIRCHILD-HILLER: Amendment 39-1471 as amended by Amendment 39-1539. Applies to Fairchild Hiller UH-12L, UH-12L4, and UH-12E-L helicopters certificated in all categories. 1. Within 10 hours in service after effective date of this airworthiness directive remove from service P/N 53100-01 main rotor blades S/N's 5, 21, 29, 66, 71, 74, 88, 125, 129, 130, 132, 142, 143, 158, 159, 160, 161, 162, 171, and 176, and replace with blades P/N 53100-01 with S/N's other than those listed. 2. Within 30 hours time in service after the effective date of this airworthiness directive, inspect and alter all other main rotor blades in accordance with Fairchild Hiller Service Bulletin SBUH12L-51-1, 7/31/72, Para. 2A thru 2K, or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Amendment 39-1539 was effective June 27, 1972, and was effective for all recipients of the air mail notice dated May 11, 1972 which contained this airworthiness directive. This amendment 39-1539 is effective October 19, 1972.
2016-11-01: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes, Model A330-200 Freighter series airplanes, and Model A340-541 and A340-642 airplanes. This AD was prompted by a report of an under-torqued forward engine mount bolt. This AD requires a one-time torque check of the forward and aft engine mount bolts and corrective actions if necessary. We are issuing this AD to detect and correct improperly torqued engine mount bolts, which could lead to detachment of the engine from the airplane during flight and consequent damage to the airplane and injury to persons on the ground.
71-15-02: 71-15-02 BRITISH AIRCRAFT CORPORATION: Amendment 39-1248 as amended by Amendment 39-1361. Applies to Model BAC 1-11 200 and 400 series airplanes. Compliance is required within the next 2,300 hours' time in service after the effective date of this AD, unless already accomplished. To reduce the possibility of fire which could result from overheating of the materials in and around the flight deck center roof panel "E" area, accomplish the following: (a) For Model BAC 1-11 200 series airplanes, modify the flight deck roof panel "E" installation and the flight deck panel lighting electrical system in accordance with parts (b), (c), and (d) of British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 33-PM-4477, dated March 30, 1970, or later ARB-approved issue or an FAA-approved equivalent. (b) For Model BAC 1-11 400 series airplanes, modify the flight deck roof panel "E" installation and the flight deck panel lighting electrical system in accordance with parts (a), (b), (c), (d), and (e) of British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 33-PM-4477, dated March 30, 1970, or later ARB-approved issue or an FAA-approved equivalent. (British Aircraft Corporation Model BAC 1-11 Alert Service Bulletin No. 33-A-PM-4169, Issue 4, dated June 7, 1970, refers to this subject.) Amendment 39-1248 became effective 26 July 1971. This Amendment 39-1361 becomes effective December 21, 1971.
2024-19-04: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports that engine nacelle anti-icing (NAI) forward bulkheads have been found with elongated locating holes. This AD requires a one-time detailed inspection of the engine NAI forward bulkhead locating holes for elongation and loose fasteners and applicable corrective actions, and prohibits the installation of affected parts under certain conditions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
72-21-04: 72-21-04 AVCO LYCOMING: Amdt. 39-1532. Applies to HIO-360-D1A model engines installed on Hughes Model 269C and 300C helicopters. Compliance required as indicated after effective date of this AD. To prevent possible failures of the Bendix S4LN-1208 magnetos, P/N 10-349285-5, accomplish the following: 1. Within the next 50 hours time in service and at each 50 hours time in service thereafter, inspect and lubricate the magneto distributor bushing of both magnetos in accordance with Lycoming Service Bulletin No. 336B or later revision or equivalent procedure approved by Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 2. Within the next 100 hours time in service and at each 100 hours time in service thereafter, replace those parts in the left magneto with the parts contained in Bendix Kit No. 10-391320 or equivalent FAA-approved parts. 3. Upon request, with substantiating data submitted through an FAA maintenance inspector, the compliance time may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective October 13, 1972.
2003-22-05: The FAA is adopting a new airworthiness directive (AD) for Hartzell Propeller Inc. model HC-A6A-3 series propellers with A10460 series composite blades. This AD requires initial and repetitive visual inspections of A10460 series composite blades for cracks. This AD is prompted by reports of cracks in propeller blades, including an in- flight separation of a blade that caused damage to the airplane. We are issuing this AD to prevent separation of the propeller blade due to possible fatigue failure, which could result in damage to the airplane and possible loss of control of the airplane.
86-11-03: 86-11-03 ROLLS-ROYCE LIMITED: Amendment 39-5301. Applies to Rolls-Royce Spey 555-15, -15H, - 15N, and -15P turbofan engines. Compliance is required as indicated unless already accomplished. To prevent possible failure of the stage 12 high pressure compressor (HPC) disk, stage 12 HPC rotor seal, and low pressure compressor (LPC) drive shaft (Pre-Mod. 4927), accomplish the following in accordance with Rolls-Royce Service Bulletin (SB) Sp 72-969, dated May 1984, or FAA approved equivalent: Remove stage 12 HPC disks and rotor seals, and LPC drive shafts (Pre-Mod. 4927) from service on or before accumulating the cyclic lives (flights) specified below. Parts which have accumulated more cycles in service than those specified below on the effective date of this AD, must be removed prior to further flight. CYCLIC LIVES PART DESCRIPTION MODIFICATION A* NUMBER OF FLIGHTS B* NUMBER OF FLIGHTS C* NUMBER OF FLIGHTS D* NUMBER OF FLIGHTS E* NUMBEROF FLIGHTS F* NUMBER OF FLIGHTS High Pressure Compressor Stage 12 Rotor Disks and Seals 13,800 15,600 17,600 19,700 22,100 17,300 Low Pressure Compressor Rotor Drive Shaft Pre-Mod 4927 10,800 10,800 11,500 12,600 14,400 11,200 *NOTE: Cyclic lives for each component are for flight profiles as denoted by A through F and defined below: For engines with no N2 monitoring: A. Spey 555-15 and 555-15N full throttle Spey 555-15H and 555-15P rated takeoff For engines with N2 monitoring: B. Where 85 percent of takeoffs do not exceed 100 percent N2 C. Where 85 percent of takeoffs do not exceed 99 percent N2 D. Where 85 percent of takeoffs do not exceed 98 percent N2 E. Where 85 percent of takeoffs do not exceed 97 percent N2 F. Datum profile, average 99.5 percent N2 Aircraft may be ferried in accordance with the provisions of FAR Sections 21.197 and 21.199 to a base where the AD can be accomplished.Rolls-Royce SB Sp 72-969, dated May 1984, identified and described in part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to the Service Manager, Spey Engine, Rolls-Royce Limited, East Kilbride, Glasgow G74-4PY, Scotland. This document also may be examined at the Office of the Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, Room Number 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday except Federal holidays. This amendment becomes effective on June 20, 1986.
2016-11-15: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by the need for more restrictive fuel system airworthiness limitations. This AD requires revising the maintenance program or inspection program, as applicable, to incorporate certain fuel system airworthiness limitations. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.