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83-03-05: 83-03-05 BRITTEN-NORMAN LTD: Amendment 39-4565. Applies to Model BN-2A MK III Trislander (all serial numbers) airplanes certificated in any category. COMPLIANCE: Required as indicated, unless already accomplished. To prevent the main undercarriage shock absorber support ring from separating from the inside of the undercarriage extension tube, accomplish the following: a) Within the next 50 landings on airplanes which have accumulated 3,000 landings or more on the effective date of this AD, or prior to the accumulation of 3,050 landings on airplanes that have less than 3,000 landings on the effective date of this AD, and thereafter at intervals not to exceed 1,000 landings: 1) Visually inspect the rivets retaining the main undercarriage shock absorber internal support ring to the main undercarriage leg extension tube in accordance with Steps 1 through 4 of the "Inspection" Section of Britten-Norman Service Bulletin BN-2/SB.139, Issue 1, dated January 29, 1980 (hereinafter referred to as the Service Bulletin). 2) If one or more loose rivets are found during the above inspection, before further flight, replace all three rivets in accordance with Steps 1 through 3 of the "Rectification" Section of the Service Bulletin. b) Within the next 50 landings on airplanes which have accumulated 15,000 landings or more on the effective date of this AD or prior to the accumulation of 15,050 landings on airplanes which have less than 15,000 landings on the effective date of this AD, replace all three rivets in accordance with Steps 1 through 3 of the "Rectification" Section of the Service Bulletin. c) In the event that landings have not been recorded, 1,000 hours time-in-service may be used in place of 3,000 landings for purposes of complying with this AD. d) The airplane may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. e) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. This amendment becomes effective on February 22, 1983.
2003-19-12: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B helicopters. This action requires, before further flight, determining whether the engine "GOV" warning light caution advisory display (display) panel illuminates the "GOV" warning lights when appropriate. If not, this AD requires replacing the front panel of the display panel with an airworthy display panel before further flight. This amendment is prompted by the discovery of some operating anomalies affecting the red "GOV" warning light due to wiring errors that occurred after modifying the electrical power systems. The actions specified in this AD are intended to prevent failure of the display to warn of an engine governor failure, resulting in an engine over speed, loss of an engine, and subsequent loss of control of the helicopter.
74-24-12: 74-24-12 PIPER: Amendment 39-2023. Applies to Model PA-28-151 airplanes serial numbers 28-7415001 through 28-7515228 certificated in all categories. Compliance required before further flight, unless already accomplished, and thereafter at intervals not to exceed ten hours time in service from the last inspection until the aileron centering assembly is rebuilt in accordance with Piper Kit 760847V or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. To detect possible problems with the aileron centering assembly accomplish the following: a. Gain visible access to right hand control wheel sprocket assembly area and check the aileron centering system for the following: 1. Cable fraying. 2. Spring integrity (Piper P/N 587340V). 3. Set screw security (Piper P/N 419974V). (The set screw should not allow any relative cable movement.) b. If the checks in a. reveal any of the unsatisfactory conditions noted, replace cable and/or spring as necessary and adjust set screw as required before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed provided the spring and/or cable is secured or removed so as not to interfere with the aileron system. c. If the checks in a. do not reveal noted unsatisfactory conditions, no further action is necessary until next required inspection. The pilot may perform only the checks required by paragraph a. Note: For the requirements regarding the listing of compliance and method of compliance with this AD in the airplane's permanent record, see FAR 91.173. Piper Service Bulletin No. 435 pertains to this subject. This amendment becomes effective December 2, 1974.
80-11-10: 80-11-10 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-3781. Applies to Models N22B and N24A airplanes, certificated in all categories. Unless already accomplished, compliance is required within 25 hours time in service after the effective date of this AD. However, airplanes may be flown in accordance with FAR 21.197 and 21.199 to a base where the work can be performed. (1) Applies to all Model N22B airplanes S/N 5 and up and all Model N24A airplanes S/N 42 and up, delivered or in operation prior to, or on, June 22, 1978. To prevent leakage of hot air check valve, P/N I/N-74-334, which could damage surrounding components, inspect, and repair as necessary, hot air check valve P/N I/N-74-334, in accordance with Accomplishment Instructions of GAF Alert Service Bulletin AN 22-74-1, Revision 1, dated June 30, 1978, or an FAA-approved equivalent. (2) Applies to all Model N22B airplanes S/N 5 and up, and all Model N24A airplanes, S/N 42 and up, which have not incorporated Nomad modification N301. To prevent possible disconnection or jamming of pilots' or copilots' control wheel assembly, which could result in loss of control of the airplane, remove control wheel retaining pin and replace with a new bolt in accordance with the Accomplishment Instructions of GAF Alert Service Bulletin AN 22-27-8, Revision 1, dated June 30, 1978, or an FAA-approved equivalent. (3) Applies to all Model N22B airplanes S/N 5 and up, and Model N24A airplanes S/N 42 and up, delivered from the factory prior to July 4, 1978. To prevent possible dislodging of structural bolts securing the wing center section spar support brackets to the fuselage, which could result in loss of structural integrity of the airplane, inspect wing center section spar support bracket for loose attachments, and replace loose nuts, in accordance with the Accomplishment Instructions of GAF Alert Service Bulletin ANMD-53-2, Revision 1, dated July 5, 1978, or an FAA-approved equivalent. (4)Applies to all Model N22B airplanes S/N 5 and up, and all Model N24A airplanes S/N 42 and up, which have not incorporated Nomad modification N290. To prevent possible interference and jamming of the rudder pedals with the pedal guards, which could impair control of the airplane, remove and repair rudder pedal guards in accordance with the Accomplishment Instructions of GAF Alert Service Bulletin ANMD-53-3, dated July 10, 1978, or an FAA- approved equivalent. (5) Applies to Model N22B airplanes S/N 6, 7, 11, 12, 13, 15, and 16. To prevent reduction of the flutter speed reserves as a result of excessive wear and backlash in the rudder tab operating system, which could result in loss of control of the airplane, remove rudder assembly, install steel mass balance arm and rework rudder and trim tab in accordance with the Accomplishment Instructions of GAF Alert Service Bulletin NMD-27-3, Revision 1, dated June 8, 1979, or an FAA-approved equivalent. (6) Applies to all Model N22B airplanes S/N 5 and up, and all Model N24A airplanes S/N 42 and up. To prevent excessive vibration of the horizontal stabilizer trim tab and prevent subsequent structural damage to the empennage, which could result in loss of control of the airplane, inspect the horizontal stabilizer trim tab, and empennage, and modify stub fin in accordance with the Accomplishment Instructions of GAF Alert Service Bulletin ANMD-55-5, Revision 2, dated September 3, 1979, or an FAA-approved equivalent. (7) Applies to all Model N22B airplanes S/N 5 and up, and all Model N24A airplanes, S/N 42 and up. To detect possible damage to the horizontal stabilizer control rod, visually inspect components in the horizontal stabilizer control system for wind gust damage, and replace as necessary, in accordance with the Accomplishment Instructions of GAF Alert Service Bulletin ANMD-27-12, Revision 1, dated October 30, 1979, or an FAA-approved equivalent. For the purposes of this amendment, the FAA-approvedequivalent specified in paragraphs (1) through (7) of this AD must be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii. All persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to the Government Aircraft Factories, 226 Lorimer Street, Port Melbourne 3207 vic., Australia. These documents may also be examined at the FAA, Pacific-Asia Region, 300 Ala Moana Blvd., Room 7321, Honolulu, Hawaii 96850, and at FAA Headquarters, 800 Independence Ave., S.W.., Washington, D.C. 20591. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C., and at the Pacific-Asia Region in Honolulu, Hawaii. This amendment becomes effective June 5, 1980.
2020-17-08: The FAA is adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model 750XL airplanes with wing lightning protection panels installed. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as insufficient electrical bonding of the wing lightning protection panels. The FAA is issuing this AD to address the unsafe condition on these products.
74-18-13: 74-18-13 PIPER: Amendment 39-1939. Applies to Model PA-32-260 Serial Numbers 32-7400001 through 32-7400050 and Model PA-32-300 Serial Numbers 32-7440001 through 32- 7440086 and 32-7440088 through 32-7440160, certificated in all categories. Compliance required within the next 50 hours time in service from the effective date of this AD unless already accomplished. To prevent excessive nose gear vibration install Piper Kit No. 760885V in accordance with Piper Service Bulletin No. 428 or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, Federal Aviation, Southern Region, may adjust the compliance time specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiation to justify theincrease for that operator. This amendment becomes effective September 3, 1974.
2009-01-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Some operators have reported occurrences of loss of the AC BUS 1 with subsequent loss of the AC ESS BUS and DC ESS BUS, resulting in the loss of 5 upper Display Units and the loss of integral lighting. In this situation, flight crew[s] have reported concerns in reading the standby instruments when the DOME lights were selected to OFF. This situation, if not corrected, could increase the workload of the flight crew * * *. * * * * * The unsafe condition is reduced ability of the flightcrew to maintain the safe flight and landing of the airplane in adverse operating conditions. We are issuing this AD to require actions to correct the unsafe condition on those products.
2020-16-20: The FAA is superseding Airworthiness Directive (AD) AD 2018- 04-09 for Pacific Aerospace Limited Model 750XL airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as incorrectly marked and annunciated low oil- pressure indication warnings. The FAA is issuing this AD to address the unsafe condition on these products.
83-10-05: 83-10-05 CANADAIR: Amendment 39-4654. Applies to all Canadair Model CL-44D4 and CL-44J airplanes. Compliance required as indicated unless previously accomplished. To detect cracks in the horizontal stabilizer rear attachment fittings, accomplish the following: 1. Within the next 200 hours time in service and thereafter at intervals not to exceed 2000 hours time in service, inspect the horizontal stabilizer rear spar attachment fittings, Part Numbers 44-A45022A and 44-A45022B, for cracks in accordance with Paragraph 3.5 and 3.6 of Canadair Service Information Circular No. 379-CL44, Issue 3, dated February 23, 1982. Ensure that the lugs are properly shimmed in accordance with paragraph 4.1 of the circular. If a crack is found the length of which is less than half the width of the lug, repeat the inspection every 100 hours time in service and replace the fitting within the next 500 hours time in service. When a crack is found the length of which extends to or beyond half thewidth of the lug, replace the fitting prior to further flight in accordance with the circular. 2. Within the next 200 hours time in service and thereafter at intervals not to exceed 2000 hours time in service, inspect the reinforcing channels, Part Numbers 28-A24559A and 22- A24559B, for cracks in accordance with paragraph 3-11 of Canadair Service Information Circular No. 379-CL44, Issue 3, dated February 23, 1982. If a crack is found in the reinforcing channel, replace the part prior to further flight in accordance with the circular. Terminating action for this inspection consists of replacement of the reinforcing channels with steel reinforcements, Parts Numbers 28-21312-2, -3, -4, and -5 in accordance with paragraphs 3.13 and 3.14 of the Service Information Circular. 3. 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 Mountain Region. 4. 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 June 6, 1983.
2020-17-11: The FAA is superseding Airworthiness Directive (AD) 2017-14-05 for Airbus Helicopters Model SA330J helicopters. AD 2017-14-05 required replacing certain right-hand (RH) hydraulic pumps and was prompted by reports of broken screws that attach the cover of the hydraulic pump. This new AD requires replacing certain left-hand (LH) and RH hydraulic pumps. This AD was prompted by reports of broken bolts that attach the cover of the hydraulic pump. The actions of this AD are intended to address an unsafe condition on these products.