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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.
72-04-02: 72-04-02 BENDIX: Amdt. 39-1393 as amended by Amendment 39-1398. Applies to P/N 2601901 (inboard wheel halves prior to Serial Number B5312 (Production) and Serial Number H204 (Service)) and to P/N 2603561 (inboard wheel halves prior to Serial Number B1996 (Production) and Serial Number H78 (Service)) wheel assemblies (TSO C26B). Compliance: Required as indicated, unless already accomplished. To prevent wheel failure accomplish the following: A) At the next tire change after the effective date of this AD, and thereafter at every other tire change until five (5) additional inspections have been accomplished (except as noted in Paragraph B below), inspect the subject wheel assemblies for cracks. This inspection requires use of the dye penetrant method or an FAA-approved equivalent on the hubs of wheel halves, P/Ns 2602118 and 2603745, with particular attention to the area in or near the radius in the hub I.D. behind the inboard bearing cup. One such FAA-approved equivalent is an eddy current inspection conducted in accordance with Bendix Service Information Letter No. 319, dated September 16, 1971, and Supplement No. 1, dated February 11, 1972, which reduces the number of inspections required herein to one inspection. B) On wheels that have had a minimum of twelve (12) tire changes, a one time only inspection in accordance with Paragraph A is required. C) If cracks are found during any inspection required by Paragraphs A or B, prior to further flight, replace all defective parts with airworthy parts. The replacement of defective parts will not relieve the requirement for accomplishing the repetitive inspections specified in Paragraph A. Bendix Service Information Letter No. 319, dated September 16, 1971, and Supplement No. 1, dated February 11, 1972, pertains to this subject. Amendment 39-1393 became effective February 17, 1972. This Amendment 39-1398 becomes effective March 4, 1972.
2016-11-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes equipped with Pratt and Whitney engines. This AD was prompted by reports of blocked drain lines at the engine forward strut that caused flammable fluid to accumulate in a flammable leakage zone. This AD requires doing the following actions on the left strut and right strut: A one-time cleaning of certain forward strut drain lines; installing new forward strut drain lines and insulation blankets; a leak check of the forward strut drain lines; and repair if any leak is found. This AD also requires revising the maintenance or inspection program, as applicable, to incorporate a certain airworthiness limitation. We are issuing this AD to prevent blockage of forward strut drain lines. This condition could cause flammable fluids to collect in the forward strut area and potentially cause an uncontrolled fire or cause failure of engine attachment structure and consequent airplane loss.
67-12-02: 67-12-02 FAIRCHILD-HILLER: Amdt. 39-384 Part 39 Federal Register April 5, 1967. Applies to Models F-27 Series and FH-227 Series Airplanes. Compliance required as indicated. Due to several instances of failure of the nose landing gear to extend to full down and locked position, accomplish the following: (a) For Model F-27 Series airplanes, Serial Numbers 108 through 122 inclusive, and Model FH-227 Series airplanes, Serial Numbers 501 through 539 inclusive, incorporating Walter Kidde nose gear steer system, P/N 891800 or P/N 893364 (spur gear system), comply with (e) within the next 100 hours' time in service after the effective date of this AD unless already accomplished. (b) For Model F-27 Series airplanes, Serial Numbers 1 through 107 inclusive, incorporating Walter Kidde nose gear steer system, P/N 891800 or P/N 893364 (spur gear system,) comply with (e) within the next 600 hours' time in service after the effective date of this AD unless already accomplished. (c) For Model F-27 Series airplanes, Serial Numbers 1 through 107 inclusive, incorporating Walter Kidde nose gear steer system, P/N 890373 (pneumatic gear system), comply with (f) within the next 1000 hours' time in service after the effective date of this AD unless already accomplished. (d) For Model F-27 Series airplanes, Serial Numbers 1 through 107 inclusive, incorporating Fairchild nose gear steer system (hydraulic gear system), comply with (g) within the next 1000 hours' time in service after the effective date of this AD unless already accomplished. (e) Install nose landing gear fork, P/N 27-423031-17, and slide, P/N 27-423006-37, in accordance with Fairchild-Hiller Service Bulletin No. 32-62 (F-27 Series), dated February 3, 1967, or Fairchild-Hiller Service Bulletin No. 32-4 (FH-227 Series), dated February 2, 1967, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or install an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (f) Install nose landing gear fork, P/N 27-423031-17, and slide, P/N 27-423006-37, in accordance with Fairchild-Hiller Service Bulletin No. 32-63, dated March 3, 1967, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or install an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (g) Install nose landing gear fork, P/N 27-423031-17, and slide, P/N 27-423006-39, in accordance with Fairchild-Hiller Service Bulletin No. 32-63, dated March 3, 1967, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or install an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (h) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region may adjust the initial compliance times specified in this AD if the request contains substantiating data to justify the increase for that operator. (Fairchild-Hiller Alert Service Letters No. 383(F-27), and 32-5 (FH-227), dated January 13, 1967 pertains to this subject.) This directive effective April 5, 1967.
2023-05-10: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200, A330-200 Freighter, A330-300, A330-800, A330-900, A340-200, A340-300, A340-500, and A340-600 series airplanes. This AD was prompted by a report that an A319 airplane lost the right- hand front windshield in flight. Due to the design similarity, this condition can also exist or develop on Model A330 and A340 airplanes. This AD requires repetitive detailed inspections (DET) and electrical test measurements (ETM) of the affected parts and applicable corrective action, 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. The FAA is issuing this AD to address the unsafe condition on these products.
48-48-02: 48-48-02 DOUGLAS: Applies to All DC-6 Aircraft Not Equipped With Steel Vacuum Pump Discharge Lines Aft of the Firewall and Chicago Metal Hose Assemblies From the Oil Separator to the Pesco Pump. \n\n\tTo be accomplished as soon as practicable, but not later than May 1, 1949. \n\n\tIn cases of malfunctioning of vacuum pumps or other vacuum pump system components, fire can occur within the lines and burn through the hose connection into the engine compartment. To prevent such occurrences, replace the present Aeroquip Hose P/N 260-10WD-15 1/2, existing between oil separator and Pesco vacuum pump, with a new Chicago Metal Hose Assembly No. 9273-1. \n\n\t(Douglas Service Bulletin No. 383 covers this same subject.) Also, to prevent fire from entering the zone behind the firewall, replace the dural vacuum pump discharge line, aft of the firewall, with a steel line. \n\n\t(Douglas Service Bulletin DC-6 No. 401 covers this same subject.)
70-15-07: 70-15-07 HAWKER SIDDELEY: Amdt. 39-1034. Applies to de Havilland Model DH.104 "Dove" airplanes. Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, accomplish the following: (a) Inspect the right wing and left wing flap datum hinge links for drilled holes around the circumference of the bearing housing recess. If one or more drilled holes or attempted drilled holes (for cotter pin installation) are found located outside the limits given in Hawker Siddeley Aviation, Ltd., Technical News Sheet CT (104) No. 216, Issue 1, dated June 8, 1970, or later ARB-approved issue or an FAA-approved equivalent, before further flight, replace the flap datum hinge link with a serviceable link of either pre-modification 982 or post-modification 982 standards. The complete flap datum hinge assembly must conform to the modification standard of the flap datum hinge link installed. (b) Install special washers P/N 4WF 465 or an FAA-approved equivalent between the nut on the flap datum hinge bolt and the hinge lever assembly at both the right wing and left wing datum hinge locations. A special washer equivalent to P/N 4WF 465 may be manufactured from 0.028 inch, minimum thickness mild steel sheet material. The special washer must have an outside diameter of at least 0.87 inches, a hole diameter of 0.323 inches, and a flat cut across a sector of the outer circumference producing a straight edge located no closed than 0.35 inches from the center of the hole. (c) Inspect the flange of the ball race housing on both the right wing and left wing flap datum hinge assemblies to determine that it is secured to the wing flap datum hinge link with a 1/16 inch diameter cotter pin for pre-modification 982 flap datum hinge assemblies or a 1/8 inch diameter cotter pin for post-modification 982 datum hinge assemblies. This amendment is effective upon publication in the Federal Register as to all persons except thosepersons to whom it was made immediately effective by the telegram dated June 20, 1970, which contained the amendment.