Results
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.
2020-11-10: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report of an in-flight event where a flightcrew observed a SPOILER FAIL message and had difficulty maintaining roll control of the airplane. This AD requires revising the existing airplane flight manual (AFM) to provide the flightcrew with procedures related to roll spoiler failures that reduce the flightcrew workload during this type of failure scenario. The FAA is issuing this AD to address the unsafe condition on these products.
83-21-03: 83-21-03 DEHAVILLAND AIRCRAFT OF CANADA, LTD.: Amendment 39-4753. Applies to DeHavilland model DHC-7 airplanes, certificated in all categories, which are equipped with ground spoiler valves installed in accordance with DeHavilland modification No. 7/1732. To detect failures of the pilot valve of the ground spoiler valve No. 2, accomplish the following, unless previously accomplished: A. Within 25 flight hours from the effective date of this AD, perform an operational check of the ground spoiler system, and take appropriate corrective action, if necessary, in accordance with the Accomplishment Instructions of DeHavilland Aircraft of Canada, Ltd., Alert Service Bulletin A7-27-56, dated June 28, 1983. B. Repeat the functional checks of paragraph A. at intervals not to exceed 800 flight hours. C. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest MountainRegion. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective November 2, 1983.
2020-11-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC120B helicopters. This AD was prompted by a report of recurrent loss of tightening torque on several attachment bolts of the tail rotor hub body. This AD requires repetitive inspections of the tail rotor hub body for cracks and applicable corrective actions if necessary, and repetitive replacement of the attachment bolts, washers, and nuts of the tail rotor hub body. The FAA is issuing this AD to address the unsafe condition on these products.
65-07-01: 65-07-01\tBOEING: Amdt. 39-51 Part 39 Federal Register April 1, 1965. Applies to Models 707 and 720 Series Aircraft. \n\n\tCompliance required as indicated. \n\n\tTo reduce the possibility of further fires in the cabin lower sidewall panels in the return air system, accomplish the following: \n\n\t(a)\tWithin 5,000 hours' time in service after March 20, 1964, install lower sidewall modifications, including flame-resistant insulation, fire-stop air baffles, and metal grills, in areas other than behind galleys and other equipment located flush against the cabin sidewall, in accordance with Boeing Service Bulletins Nos. 1807(R-1), 1807(R-1)A, 1861, and 1868, as applicable, or an FAA-approved equivalent.\n \n\t(b)\tWithin 6,000 hours' time in service after March 20, 1964, install lower sidewall modifications, including flame-resistant insulation, fire-stop air baffles, and metal grills, behind galleys and other equipment located flush against the cabin sidewall in accordance with Boeing Service Bulletins Nos. 1807(R-1), 1807(R-1)A, 1861, and 1868, as applicable, or an FAA- approved equivalent.\n \n\tThis supersedes AD 64-04-01. \n\n\tThis directive effective April 1, 1965.
2020-10-03: The FAA is adopting a new airworthiness directive (AD) for all Weatherly Aircraft Company (Weatherly) Models 201, 201A, 201B, 201C, 620, 620A, 620B, 620B-TG, and 620TP airplanes. This AD was prompted by reports of fatigue cracking of the center wing and outer wing spar hinge brackets due to corrosion pitting. This AD requires repetitive inspections of the wing hinge brackets, pins, and wing spar structure with repair or replacement of parts as necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2020-09-01: The FAA is superseding Airworthiness Directive (AD) 2008-24-04 for Eurocopter France (now Airbus Helicopters) Model AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters. AD 2008-24-04 required repetitively inspecting the lubricating pump and checking the magnetic chip detector plug (chip detector) and the main gearbox (MGB) oil-sight glass. This new AD retains the requirements of AD 2008-24-04 and allows the option of altering the MGB oil flow distribution as a terminating action for the inspections. This AD was prompted by an alteration developed by Airbus Helicopters of the MGB oil flow distribution that corrects the unsafe condition. The actions of this AD are intended to address an unsafe condition on these products.
81-04-09: 81-04-09 SHORT BROTHERS LIMITED: Amendment 39-4047. Applies to Model SD3-30 airplanes, certificated in all categories, which have Menasco nose landing gear steering actuator, P/N 18002, serial numbers MMC-003 through MMC-048, and/or nose landing gear beam assembly, P/N 18004, serial numbers MMC-001 through MMC-041, installed. Compliance is required as indicated unless already accomplished. To prevent failure of the end cap sub-assembly of the nose wheel steering actuator, or of the link sub-assembly of the nose landing gear beam, accomplish the following: (a) Within the next 25 landings after the effective date of this AD, or prior to accumulation of 10,500 landings, whichever occurs later, replace the end cap sub-assembly, P/N 18382-7A or P/N 18391-7A, of nose landing gear steering actuator assembly, P/N 18002, with end cap, P/N 18382-9 or P/N 18391-9, in accordance with Menasco Manufacturing Service Bulletin 32-21, Revision 3, dated August 7, 1979, or an FAA-approved equivalent. (b) Within the next 25 landings after the effective date of this AD, or prior to the accumulation of 10,000 landings, whichever occurs later, replace in accordance with Menasco Manufacturing Service Bulletin 32-30, dated February 9, 1979, or an FAA-approved equivalent, the link sub-assembly, P/N 18053-1 or P/N 18053-3 as appropriate, with a link sub-assembly of the same part number, and continue replacement at intervals not to exceed 10,000 landings; or replace with link sub-assembly P/N 18293-1, in which case no further replacement is required and reidentify the nose landing gear beam assembly, P/N 18004, in accordance with paragraph 10D of Menasco Service Bulletin 32-30, dated February 9, 1979, or an FAA-approved equivalent. (c) If an equivalent means of compliance is used in complying with this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, AEU-100, Federal Aviation Administration, Europe, Africa, and Middle East Office, Brussels, Belgium. This amendment becomes effective March 3, 1981.
2020-08-13: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, Model CL-600-2C10 (Regional Jet Series 700, 701 & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, and Model CL-600-2D24 (Regional Jet Series 900) airplanes; and all Bombardier, Inc., Model CL-600-2C11 (Regional Jet Series 550) airplanes. This AD was prompted by reports of fractured rudder primary feel unit shafts; a subsequent investigation determined that the fractures in the shafts are consistent with fatigue damage. This AD requires replacement of the rudder primary feel unit shaft. The FAA is issuing this AD to address the unsafe condition on these products.
79-25-06: 79-25-06 LOCKHEED: Amendment 39-3631. Models 382 series, Serial Numbers 3946 through 4832, certificated in all categories. Compliance is required within the next 50 hours time in service, unless already accomplished. a. To prevent the clear vision windows from opening in flight, inspect the window latch catches, part numbers 385057-1 and -2, and 393433-1 and -2, which are mounted on the windshield post at each window, in accordance with Lockheed-Georgia Company Service Bulletin A382-56-1, dated October 17, 1979. b. If discrepant catches are found, before further flight, replace the catches in accordance with Lockheed-Georgia Company Service Bulletin A382-56-1, dated October 17, 1979. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. This amendment is effective December 19, 1979.
80-22-06: 80-22-06 UNIVERSAL OIL PRODUCTS, INC.: Amendment 39-3953. Applies to Model 900 series aircraft seats. Compliance is required as indicated, unless already accomplished. To prevent the possible failure of a passenger seat caused by a crack in the rear stretcher tube, accomplish the following: 1. Within the next 90 days after the effective date of this AD, visually inspect all UOP, Inc., Model 900 series aircraft seats for cracks in the rear stretcher tube. Note. - Direct particular attention to the aisle end of the tube at the side arm attaching bolt hole. 2. Except as provided in Paragraph 3 below, replace all cracked tubes with serviceable units. Until cracked tubes are replaced, placard or otherwise mark the seat position adjacent to the cracked stretcher tube end as unusable and not to be occupied. 3. Stretcher tubes with cracks less than 1.19 inches, measured along the longitudinal axis from the centerline of the attach hole, may be repaired withclamp P/N 81672-1, in accordance with installation instructions in UOP, Inc., Service Bulletin 25-634, dated April 3, 1980. This repair is not authorized for Model 900-200B-2L seats. An equivalent method may be approved by the Chief, Engineering and Manufacturing Branch. If after installation of the clamp, the crack extends beyond the end of the clamp, the stretcher tube must be replaced. This amendment becomes effective November 25, 1980.
2020-07-15: The FAA is adopting a new airworthiness directive (AD) for all PZL (Sacute)widnik S.A. Model PZL W-3A helicopters. This AD was prompted by a report of a cracked nose landing gear (NLG) bellcrank assembly. This AD requires a one-time inspection of the NLG bellcrank assembly for discrepancies and replacement if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2020-07-51: The FAA is adopting a new airworthiness directive (AD) for certain International Aero Engines AG (IAE) V2522-A5, V2524-A5, V2525- D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 model turbofan engines. This emergency AD was sent previously to all known U.S. owners and operators of these engines. This AD requires removal of affected high-pressure turbine (HPT) 1st-stage disks from service. This AD was prompted by investigative findings from an event involving an uncontained failure of a HPT 1st-stage disk that resulted in high-energy debris penetrating the engine cowling. The FAA is issuing this AD to address the unsafe condition on these products.
2020-06-17: The FAA is superseding Airworthiness Directive (AD) 2011-09- 06, which applied to all Airbus SAS Model A330-200 Freighter series airplanes; Model A330-200 and -300 series airplanes; and Model A340-200 and -300 series airplanes. AD 2011-09-06 required repetitive inspections and operational checks of the spring function of the emergency exit door slider mechanism, application of corrosion inhibitor, and corrective actions. This AD retains those requirements, with extended repetitive intervals for certain actions, and also requires those actions on additional airplanes; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by report that an escape slide deployment test found a girt bar that was not in a locked position and was detached from the airplane. The FAA is issuing this AD to address the unsafe condition on these products.
2020-04-15: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes and Model 767-200, -300, and - 300F series airplanes. This AD was prompted by reports of excessively high flight deck or cabin temperatures. This AD requires revising certificate limitations and operating procedures of the existing airplane flight manual (AFM), to provide the flightcrew with procedures for hot flight deck or cabin temperatures to follow under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
64-22-01: 64-22-01\tBOEING: Amdt. 815 Part 507 Federal Register September 19, 1964. Applies to Models 707 and 720 Series Aircraft. \n\n\tCompliance required as indicated. \n\n\tThere have been failures of the fuel tank vent float valve arms causing the float to break loose from the main valve assembly. This permits the vent valve (which is normally float actuated to the closed position by a high fuel level) to remain open and allow (under some flight conditions) fuel to fill the surge tank and spill out the wing tip vent scoop. To correct this condition, accomplish the following: \n\n\t(a)\tWithin 500 hours' time in service after the effective date of this directive, unless already accomplished in the previous 500 hours' time in service and within every 1,000 hours time in service thereafter until compliance with (b) has been accomplished, visually inspect the reserve fuel tank vent valve assemblies in each wing for cracks or deformation. If the valve assembly is in a failed condition, or if cracks or deformed parts are found, replace the parts before further flight. \n\n\t(b)\tWithin 6,000 hours' time in service after the effective date of this directive modify all fuel tank vent valve assemblies in each tank by installing a float stop bracket assembly, Boeing P/N 69-31399-1, in accordance with Boeing Service Bulletin No. 1958 or an equivalent method processed through the Aircraft Engineering Division, FAA Western Region, Los Angeles, California. When this modification has been accomplished the repetitive inspection of (a) may be discontinued. \n\n\t(c)\tUpon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. \n\n\t(Boeing Service Bulletin No. 1958 covers thissubject.) \n\n\tThis directive effective October 22, 1964.
2020-04-17: 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 of passenger door girt bar fitting assembly safety hooks being stuck in the upward position. This AD requires repetitive detailed inspections of girt bar fitting assemblies, repetitive greasing of girt bar fitting assembly bushes, and, depending on findings, accomplishment of applicable corrective actions, 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.