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2020-16-10: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Inc. (Bell) Model 204B, 205A, 205A-1, 205B, 212, 214B, 214B-1, 412, 412CF, and 412EP helicopters. This AD was prompted by a report of a shoulder harness seat belt comfort clip (comfort clip) interfering with the seat belt inertia reel. This AD requires removing comfort clips from service and inspecting the seat belt shoulder harness (harness) for a rip or an abrasion. The actions of this AD are intended to address an unsafe condition on these products.
79-16-02: 79-16-02 INDIANA MILLS AND MANUFACTURING, INC.: Amendment 39-3519. Applies to Model IMM 111040-1, -2, -3, -4 and -8 safety belt assemblies marked as meeting the standards of FAA TSO-C22f. These safety belts are installed in, but not limited to, Gulfstream American Corp. (formerly Grumman American Aviation Corp.) AA-1B, AA-1C, AA-5, AA-5A, AA-5B model airplanes. These safety belts can no longer be considered to meet the standards prescribed by FAA TSO-C22f and the approved special criteria for push-button release mechanisms which requires the push-button release force to be between 2.5 and 8 pounds when using the loading conditions specified in FAA TSO-C22f (Section 4.3.2.2 of NAS 802). Within 120 days from the effective date of the AD, these safety belts shall not be used in type certificated aircraft. NOTE - Information regarding replacement safety belts for Gulfstream American airplanes can be obtained from: Gulfstream Light Aircraft Customer Service P.O. Box 2206 Savannah, Georgia 31410 Telephone (912) 964-3000 Telex 54-6470 This amendment becomes effective August 2, 1979.
2020-16-03: The FAA is adopting a new airworthiness directive (AD) for PZL Swidnik S.A. (PZL) Model PZL W-3A helicopters. This AD requires establishing a life limit for certain horizontal stabilizers and removing from service any affected horizontal stabilizer in accordance with that life limit. This AD was prompted by the discovery of an error in the Airworthiness Limitations for PZL Model PZL W-3A helicopters. The actions of this AD are intended to address an unsafe condition on these products.
80-08-04: 80-08-04 CHADWICK, INC.: Amendment 39-3736. Applies to all Hughes model 369 helicopters equipped with Chadwick model C-20 Auxiliary Fuel System installed as per STC SH129WE and Bell model 206 helicopters equipped with Chadwick, Inc. model C-22 Auxiliary Fuel System installed per STC SH139WE. Compliance is required as indicated. To prevent a static discharge type of source ignition, accomplish the following: A. Within 120 days after the effective date of this Airworthiness Directive, unless already accomplished, install the Chadwick, Inc. supplied appropriate bonding and grounding harness kit in accordance with Chadwick, Inc., Installation Instructions dated January 2, 1980, (for the C-20 installation) or December 27, 1979, (for the C-22 installation), or an equivalent modification approved by the Chief, B. Conduct a continuity check every 100 hours time in service while equipped with the Chadwick, Inc. auxiliary fuel system, to assure proper grounding between attach points of bonding and grounding kits. Reference: AC 43.13.1A, Chapter 11, Section 3, Paragraph 452, Page 188. 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 Chadwick, Inc., 11969 Southwest Herman Road, Sherwood, Oregon 97140. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective April 17, 1980.
2020-12-15: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a report that certain safety valves at the left- and right-hand sides of the cabin pressure control system were not installed correctly and that the trunnion nuts used to fasten the V-band clamp were over torqued. This AD requires a measurement of the trunnion nut torque of the V-band clamp, an inspection of the safety valve and airplane bulkhead flange area for any cracking and deformations, and corrective actions, if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
61-04-01: 61-04-01 BRANTLY: Amdt. 252 Part 507 Federal Register February 10, 1961. Applies to All B-2 Helicopters. Compliance required as indicated. Instances have occurred wherein the centrifugal clutch has failed to release at engine shutdown and subsequent restarting has sheared the bolts which transmit torque from the B2-8-14 clutch disc assembly into the fabric coupling and from the fabric coupling into the lugs of the free-wheeling clutch housing. To preclude recurrence of this condition the following must be accomplished: (a) Within the next 10 hours of flight time after the effective date of this directive, inspect all 6 of the AN 4-10A bolts which secure the fabric coupling to the B2-8-14 clutch disc assembly and to the free-wheeling clutch housing for shear failure. This inspection is to be accomplished by inserting an appropriately sized wrench through the lubrication access hole in the B2-7-17 clutch dust cover and checking each bolt for snugness. Any sheared bolts must be replaced prior to further operation. (b) Within the next 10 hours of flight time after the effective date of this directive a placard shall be installed immediately aft or incorporated with the operating limitations placard located between the fuel mixture control and the carburetor heat control levers to read: "PRIOR TO EACH ENGINE START, TURN ROTOR BACKWARD BY HAND THROUGH 30 DEGREES MINIMUM TO CHECK CLUTCH FREEDOM." The purpose of this placard is to insure that these coupling bolts are not subjected to damage resulting from failure of the clutch to release. (Brantly Service Bulletin No. 6 covers this same subject.) This directive effective February 22, 1961.
2020-11-01: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation (Gulfstream) Model GVI airplanes. This AD was prompted by a report that the primary flight control actuation system (PFCAS) linear variable displacement transducer (LVDT) mechanical disconnect monitor may not trigger the disconnect of the affected control surfaces as required in the event of a control surface failure. This AD requires updating the software of each PFCAS remote electronics unit (REU), which includes an improvement to the LVDT. The FAA is issuing this AD to address the unsafe condition on these products.
80-15-08: 80-15-08 SLINGSBY: Amendment 39-3849. Applies to Model T65A Vega gliders, all serial numbers up to and including 1913, certificated in all categories. Compliance required as indicated. To prevent main wing failure due to possible inadequate bonding of the main wing shear web to the wing spar cap, accomplish and operate the glider in accordance with the following: (a) Prior to further flight: (1) Install a placard in full view of and legible to the pilot which reads: Both VNE and rough air airspeed are restricted to 95 kts. maximum. Maximum gross weight is limited to 775 lbs. (2) Install a red radial line on the airspeed indicator dial face at 95 kts., VNE, indicated airspeed. Check the airspeed indicator dial face to determine if it is free to turn. The red radial line may be installed on the airspeed indicator face glass, if the face glass is firmly fixed and not free to turn. If the face glass is free to turn, install the red radial line on the airspeed instrument face. (b) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished, replace the main wing with a Slingsby certified serviceable wing which is identified with "Mod. 27 embodied" adjacent to the wing serial number or with a serviceable wing approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, Brussels, Belgium, at which time the limitations imposed by paragraph (a) of this AD no longer apply. NOTE: Slingsby Technical Instruction No. 38 pertains to this AD and provides guidance to glider owners affected by this AD on obtaining serviceable replacement wings from Slingsby or through Slingsby authorized representatives. This amendment becomes effective July 17, 1980, as to all persons except to those persons to whom it was made immediately effective by telegraphic AD T79EU-12, issued September 12, 1979, which contained this amendment.
81-10-06: 81-10-06 McDONNELL DOUGLAS: Amendment 39-4109. Applies to McDonnell Douglas Model DC-10-10, -10F, -30, -30F, and -40 series airplanes certificated in all categories utilizing the following slide or slide/raft assemblies at the No. 3 door: \n\n\nManufacturer\nPart No. \nLeft-Hand Door \nSargent Industries, Pico Division\n5LD230500-112 \n\n5LD230500-114 \n\n5WD230500-101 \n\n5WD230500-101 (DAW95) \n\n5WD230500-201\n\n5WD230500-201 (DAW95) \n\n5WD230500-401 \n\n5WD230500-401 (DAW95)\nAir Cruisers Company\n24D29220-3 \n\n24D30051-11 \n\n24D30051-11 (DAW98) \n\n24D30051-13 (DAW98) \n\n24D30051-51 \n\n24D30051-53 (DAW98) \n\n24D30051-91 \n\nRight-Hand Door \nSargent Industries, Pico Division\t\n5LD230600-112 \n\n5LD230600-114 \n\n5WD230600-101 \n\n5WD230600-101 (DAW95) \n\n5WD230600-201 \n\n5WD230600-201 (DAW95) \n\n5WD230600-401 \n\n5WD230600-401 (DAW95) \nAir Cruisers Company\n24D29220-4 \n\n24D30051-21 \n\n24D30051-21 (DAW98) \n\n24D30051-23 (DAW98)\n\n24D30051-61 \n\n24D30051-63 (DAW98) \n\n24D30051-101\n\t\t\t\n\tCompliance is required as indicated unless already accomplished. \n\n\tTo prevent improper deployment of No. 3 door slide or slide/raft, accomplish the following: \n\n\tAt the next slide or slide/raft assembly overhaul after the effective date of this AD, but in no case exceeding three years from the effective date of this AD, unless already accomplished, modify the affected evacuation system assemblies and container assembly, Douglas P/N AWD7446-503, in accordance with Part 2 of Douglas Service Bulletin No. 25-278 dated March 7, 1980. \n\n\tAlternate methods of compliance may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, Northwest Region. \n\n\tThe 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). \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). \n\n\tThese documents also may be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108, or 15000 Aviation Boulevard, Hawthorne, California 90261, Room 6W14. \n\n\tThis amendment becomes effective June 12, 1981.
63-25-02: 63-25-02 LOCKHEED: Amdt. 651 Part 507 Federal Register November 30, 1963. Applies to All Models 49, 149, 649, 649A, 749, 749A, 1049-54, 1049C, 1049D, 1049E, 1049G, and 1049H Series Aircraft. Compliance required as indicated. As a result of several fatigue failures of the nose landing gear actuating cylinder attach bolts, accomplish the following: (a) For operators maintaining records of landings, within the next 1,000 landings after the effective date of this AD, unless already accomplished within the last 5,000 landings, and thereafter within each 6,000 landings from the last replacement, comply with (c). Where past records of landings are unavailable the number of landings prior to the effective date of this AD may be obtained by substituting one landing for each hour of time in service prior to the effective date of this AD. (b) For operators not maintaining records of landings, within the next 1,000 hours' time in service after the effective date of this AD, unless already accomplished within the last 5,000 hours' time in service, and thereafter within each 6,000 hours' time in service from the last replacement, comply with (c). (c) Replace the nose landing gear actuating cylinder bolts as follows: (1) Replace the two forward bolts, P/N 307403 and P/N 307404, which attach the forward end of the actuating cylinder to the fuselage structure via a universal joint, with new bolts of the same part numbers. (2) Replace the aft bolt, P/N 307402, which attaches the actuating cylinder rod to the drag strut pivot, with a new bolt of the same part number. (3) For those aircraft which use P/N 272216-3 and P/N 272238 in lieu of P/N 307402 and P/N 307403, replace these bolts with new bolts of the same part numbers or replace P/N 272216-3 with P/N 307402 and replace P/N 272238 with P/N 307403 in accordance with items 1, 2, 3, 5, 6, and 7 of the section entitled "Description of Change B" of Lockheed Service Bulletin 49/SB-616. (4) Forthose aircraft which use P/N 272216-2 in lieu of P/N 307404 replace this bolt with P/N 307404 and accomplish the rework of the section entitled "Description of Change A", Lockheed Service Bulletin 49/SB-616. This supersedes AD 63-01-02. This directive effective December 30, 1963.