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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.
60-20-01: 60-20-01 AERO COMMANDER: Amdt. 204 Part 507 Federal Register September 28, 1960. Applies to Models 680-E and 720, Serial Numbers 501, 623 Through 873 Except 820, 850, 860, 867 and 872. Compliance required within the next 100 hours' time in service after the effective date of this amendment. The manufacturer's inspection has determined a nonconformity with the approved design data and it is possible that aircraft in service may have the following nonconformity: AN 426AD-5 rivets have been installed instead of 3/16-inch huckbolts in the lower surface of the wing at the rear spar between wing station 54 and the inboard nacelle attach angle on both the left and right wings. (a) Inspection. Inspect the lower wing at rear spar between wing station 54 and the inboard nacelle attach angles on both the left and right wings to determine whether 3/16-inch huckbolts or AN 426AD-5 rivets have been installed. If the AN 426AD-5 rivets are installed, the wing shall be reworked as outlined in paragraph (b). (b) Rework. Remove flaps and wing trailing edge closeout skins on both left and right wings. Drill out the AN 426AD-5 rivets and replace with AN 426AD-6 rivets. These rivet heads will protrude below the wing surface by approximately 0.030 inch. Do not overdrive the rivets in an attempt to sink them completely. Measure the distance between the rivet which passes through the wing skin and rear spar cap at wing station 54 and the screw which passes through the inboard nacelle attach angle. This distance should be approximately 4.5 inches and should contain six rivets (0.75 inch on center) and the screw. If only five rivets exists in this area, a brazier head rivet (AN 456AD-6) must be added between the nacelle attach angle screw and the next rivet inboard. If sufficient space does not exist to permit minimum rivet to rivet spacing of three rivet diameters, contact the Service Department, Aero Design & Engineering Company for approved repairinstructions. Replace flaps and left and right wing trailing edge skins. (Aero Design Service Bulletin No. 62 covers this same subject.) This directive effective October 28, 1960.
63-15-06: 63-15-06 PIAGGIO: Amdt. 591 Part 507 Federal Register July 24, 1963. Applies to Model P.166 Aircraft, Serial Numbers 1, through 403. Compliance required within 25 hours' time in service after the effective date of this AD. To preclude failure of the elevator trim tab control system and lever, P/N 5069, because of unsound welding seams, accomplish the following: (a) Inspect right and left levers, P/N's 5069.03 and 5069.02, respectively, for cracks or unsatisfactory machining in accordance with Piaggio Service Bulletin No. 166-30 dated February 1, 1963. (b) If any defects specified in the service bulletin are found, before further flight replace the lever with a lever inspected and found to have no defects. This directive effective August 23, 1963.
2017-21-08: We are adopting a new airworthiness directive (AD) for all Airbus Model A310 series airplanes. This AD was prompted by a revision of certain airworthiness limitation items (ALI) documents, which require more restrictive maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program to incorporate the maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2017-21-04: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP Model Gulfstream G150 airplanes. This AD was prompted by a report indicating that the main entrance door (MED) opened during flight, and by the determination that the ``CABIN DOOR UNLOCK'' crew alerting system (CAS) message may extinguish before the handle latch pin is fully engaged. This AD requires accomplishing an updated rigging procedure for the adjustment of the MED microswitch. We are issuing this AD to address the unsafe condition on these products.