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2017-23-02: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage crown skin panels are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections, replacement, and applicable on-condition actions for certain fuselage crown skin panels. We are issuing this AD to address the unsafe condition on these products.
61-03-01: 61-03-01 BELL: Amdt. 249 Part 507 Federal Register February 7, 1961. Applies to All Model 47J-2 Helicopters Except Those Equipped With Lycoming VO-540-B1B3 Engines (Third Order Torsional Dampers). Compliance required as indicated. To preclude failures of the pinion gear on the inboard end of the P/N 47-620-539-1 cooling fan drive assembly which are associated with a poor tooth mesh condition, the following inspections and corrective action must be accomplished no later than the next 10 hours of flight time after the effective date of this directive, and by the completion of the 25 hour, 50 hour, 100 hour, and 300 hour flight time periods subsequent to the accomplishment of the initial inspection. Inspections accomplished in accordance with Bell Mandatory Service Bulletin 130SB prior to the effective date of this directive need not be repeated and only those remaining inspections necessary to complete the series are required. (a) Remove cooling fan drive assembly, P/N 47-620-539-1, from transmission in accordance with instructions contained in Bell Model 47J-2 Maintenance and Overhaul Instructions, and inspect driven side of pinion gear teeth (P/N 47-620-530-1). (b) Replace gear if conditions defined by Figure 2 of Bell Service Bulletin 130SB are found. (c) If replacement of the pinion gear is required, further disassembly as necessary and inspection of the cooling fan driving gear (P/N 47-620-207-1) must be conducted. If conditions defined by Figure 4 of Bell Service Bulletin 130SB are found, this gear must also be replaced. (d) If replacement of either gear is required, back lash and gear pattern must be established in accordance with instructions contained in Maintenance and Overhaul Instructions. (e) Reassemble cooling fan drive assembly in accordance with Maintenance and Overhaul Instructions except that nut, P/N 47-620-565-1 shall be torqued to 960 inch-pounds and fan pulley bolt AN 6H5A shall be torqued to 300 inch-pounds. (f) If either or both gears are replaced, perform the above inspections at 10, 25, 50, 100 and 300 hours of flight time following gear replacement. This procedure must be reconducted until a satisfactory wear pattern on the pinion gear and drive gear is maintained through 300 hours of flight time, after which inspections in accordance with this directive may be discontinued. (Bell Mandatory Service Bulletin 130SB covers this same subject.) This directive effective February 22, 1961. Revised May 13, 1961. Revised November 5, 1966.
2017-22-11: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (CL-604 Variant) airplanes. This AD was prompted by reports of in-service incidents regarding the loss of all air data system information provided to the flightcrew. This AD requires revising the airplane flight manual (AFM) to provide ``Unreliable Airspeed'' procedures to the flightcrew to stabilize the airplane's airspeed and attitude for continued safe flight and landing. We are issuing this AD to address the unsafe condition on these products.
60-21-01: 60-21-01 ALLISON: Amdt. 208 Part 507 Federal Register October 8, 1960. Applies to All Model 501-D13 Series Engines. Compliance required at next overhaul of engine, power section or torquemeter, whichever occurs first, after the effective date of this AD. Several cases of rubbing of the torquemeter housing by the torquemeter reference shaft have resulted in complete separation of the housing into two sections. To preclude such failures, a mid-bearing torquemeter assembly, P/N 6823900, identified by a 1/2-inch by 2 1/2-inch blue stripe on the forward bevel of the housing shall be installed. (Allison Commercial Engine Bulletin No. 72-113 covers the same subject.) This directive effective November 9, 1960.
81-14-05: 81-14-05 KAWASAKI HEAVY INDUSTRIES, LTD.: Amendment 39-4149. Applies to Model KV 107-II and KV 107-IIA helicopters, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent fatigue failure of the rotor pitch housing, accomplish the following: (a) For aft rotor pitch bearing housings, P/N's 107R2553-8, -10, -14, and -16: (1) Prior to the accumulation of 1,000 hours time in service, or within the next 50 hours time in service after the effective date of this AD, whichever occurs later, install crack detector wires on pitch bearing housings in accordance with Part I, "Installation Procedure," of Kawasaki Service Bulletin No. KSB-V107-615, dated September 10, 1980 (hereinafter referred to as the Service Bulletin), or an FAA-approved equivalent. (2) Within the next 50 hours time in service after the effective date of this AD, inspect the lug area of the pitch bearing housings for cracks in accordance with PartII, "Inspection Procedure," of the Service Bulletin, or an FAA-approved equivalent, and continue to inspect at intervals not to exceed 25 hours time in service. (b) For forward rotor pitch bearing housings, P/N's 107R2553-7, -9, -13, and -15: (1) Prior to the accumulation of 2,000 hours time in service, or within the next 100 hours time in service after the effective date of this AD, whichever occurs later, install crack detector wires on pitch bearing housings in accordance with Part I, "Installation Procedure," of the Service Bulletin, or an FAA-approved equivalent. (2) Within the next 100 hours time in service after the effective date of this AD, inspect the lug area of the pitch bearing housings for cracks in accordance with Part II, "Inspection Procedure," of the Service Bulletin, or an FAA-approved equivalent, and continue to inspect at intervals not to exceed 50 hours time in service. (c) Conduct a visual inspection for cracks in the lug area of blade sockets, P/N's 42R1043-11, -12, -13, and -14, at intervals not to exceed 50 hours time in service. This may be accomplished without disassembly from the helicopter. (d) If any cracks are found as a result of the inspections required by paragraphs (a), (b), and (c) of this AD, before further flight, replace with a serviceable part of the same part number, or an FAA-approved equivalent, and continue to inspect in accordance with this AD. (e) Retire from service all rotor pitch bearing housings, P/Ns 107R2553-7, -8, -9, -10, -13, -14, -15, and -16, prior to the accumulation of 5,000 hours time in service. (f) If an equivalent means of compliance is used in complying with this AD, that equivalent means must be approved by the Chief, Airworthiness District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii. (g) Upon request of an operator and submission of substantiating data, the Chief, Airworthiness District Office, Pacific-Asia Region, may upon recommendation of the cognizant FAA aviation safety inspector adjust the compliance time specified in this AD. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Kawasaki Heavy Industries, Ltd., Aircraft Division, Kawasakicho, Kakamigahara, Gifu Prefecture, Japan. The documents may also be examined at the FAA, Pacific-Asia Region, Airworthiness District Office, 300 Ala Moana Blvd., Room 7321, Honolulu, Hawaii 96850, and Rules Docket, Room 916, 800 Independence Avenue, SW., Washington, DC 20591. This amendment becomes effective July 9, 1981.
60-05-03: 60-05-03 PIPER: Amdt. 108 Part 507 Federal Register March 2, 1960. Applies to PA-22 "150" and PA-22 "160" Aircraft Serial Numbers 22-3218, 22-3387, 22-3388 to 22-7049 Inclusive, and 22-7054. Compliance required by April 1, 1960. Install safety belt extension, P/N 14920-02 or equivalent, on the front seat belt in order to eliminate deterioration due to heat from the rear seat heater outlet and chafing where the web attaches to the attaching lug. P/N 14920-02 has the same geometric design as P/N 14920-0 being replaced, except that P/N 14920-02 is one inch longer measuring 3.5 inches between bolt centerlines. (Piper Service Bulletin No. 184 covers this same subject.) This supersedes AD 57-17-02. Revised November 2, 1960.
2017-22-02: We are adopting a new airworthiness directive (AD) for certain Ipeco Holdings Ltd. (Ipeco) pilot and co-pilot seats. This AD requires modification and reidentification of the affected seats. This AD was prompted by reports of unexpected movement of pilot and co-pilot seats on takeoff and landing. We are issuing this AD to address the unsafe condition on these products.
85-11-03: 85-11-03 BOEING: Amendment 39-5067. Applies to all Model 757 series airplanes equipped with Air Cruisers evacuation slides, part numbers (P/N) as specified in Boeing Service Bulletin 757-25-0040 dated December 21, 1984. To assure slides do not become unsafe due to porosity, accomplish the following, unless already accomplished. \n\n\tA.\tAccomplish inspection procedures in accordance with the service bulletin or later FAA-approved revisions, as follows: \n\n\t\t1.\tFor slides manufactured prior to six months before the effective date of this AD, accomplish the inspection within the next 12 months. \n\n\t\t2.\tFor all other slides, accomplish the inspection within 18 months after the date of manufacture.\n \n\t\t3.\tSlides which do not meet the limitations set forth in the service bulletin must be replaced with a serviceable slide prior to further flight. \n\n\tB.\tRepeat the inspection procedures of paragraph A., above, within 18 months after the last leak check inspection performed in accordance with the service bulletin, or later FAA- approved revisions. \n\n\tC.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office. \n\n\tD.\tUpon request of an operator, an FAA Principal Maintenance Inspector, subject to prior approval by the Manager, Seattle Aircraft Certification Office, may adjust the compliance times if the request contains substantiating data to justify the request. \n\n\tE.\tAircraft may be ferried to a base for maintenance in accordance with Sections 21.197 and 21.199 of the Federal Aviation Regulations. \n\n\tThis amendment becomes effective June 28, 1985.
2017-22-05: We are superseding Airworthiness Directive (AD) 2013-15-03 for Eurocopter France Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, and AS350D1 helicopters. AD 2013-15-03 required inspecting the hydraulic pump drive pulley bearing (bearing) for leaks, rust, overheating, and condition. This new AD adds a requirement to grease the bearing and inspect for bronze particles in the grease, and changes the inspection and inspection intervals of the bearing until it is replaced with an improved bearing. This AD was prompted by additional reports of hydraulic pump drive belt failure caused by bearing seizures. The actions of this AD are intended to prevent an unsafe condition on these products.
2017-22-04: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of skin doublers that disbonded from their skin panels. This AD requires repetitive inspections of fuselage skin panels, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.