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80-20-02: 80-20-02 BOEING: Amendment 39-3928. Applies to all Boeing Model 747 airplanes which are equipped with B.F. Goodrich slides or turbofans identified in B.F. Goodrich Service Bulletin 25-060 dated July 14, 1980. \n\n\tNOTE: Boeing Service Bulletin 747-25-2543 dated September 5, 1980, lists the airplanes originally delivered with the affected slides. These slides may be on airplanes not listed in this service bulletin.\n \n\tCompliance is required as indicated. Accomplish the following: \n\n\tA.\tWithin 30 days from the effective date of this AD, unless already accomplished, replace the flapper valves in affected B.F. Goodrich slides installed on the upper deck of any Model 747-200F and 747-200C airplanes carrying passengers on the upper deck only. Install flapper valves in accordance with B.F. Goodrich Service Bulletin 25-060 dated July 14, 1980, or later FAA approved revisions or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\n\tB.\tPrior to January 1, 1981, replace the flapper valves in all remaining B.F. Goodrich slides and turbofans in accordance with B.F. Goodrich Service Bulletin 25-060 dated July 14, 1980, or later FAA approved revisions or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.\n \n\tC.\tUpon request of the operator, an FAA Maintenance Inspector, subject to prior approval by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region may adjust the compliance times if the request contains substantiating data to justify the changes. \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 Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents mayalso be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective October 7, 1980.
2005-18-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100& 440) airplanes, that requires performing an inspection of the electrical harnesses of the spoiler and the brake pressure sensor unit on both sides of the wing root to detect any chafing or wire damage, and repairing or replacing any damaged or chafed harness or wire with a new harness, as applicable. This action also provides/requires a terminating modification for the one-time inspection. The actions specified by this AD are intended to detect and correct chafing of the electrical cables of the spoiler and brake pressure sensor unit on both sides of the wing root, which could result in loss of the flight control system and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
97-25-02: This amendment adopts a new airworthiness directive (AD) that applies to all Mitsubishi Heavy Industry (Mitsubishi) MU-2B series airplanes. This AD requires amending the Limitations Section of the airplane flight manual (AFM) to prohibit the positioning of the power levers below the flight idle stop while the airplane is in flight. This AFM amendment will include a statement of consequences if the limitation is not followed. This AD results from numerous incidents and five documented accidents involving airplanes equipped with turboprop engines where the propeller beta was improperly utilized during flight. The actions specified by this AD are intended to prevent loss of airplane control or engine overspeed with consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
97-25-03: This amendment adopts a new airworthiness directive (AD) that applies to all Raytheon Aircraft Company (Raytheon) 65, 90, 99, 100, 200, 300, 1900, and 2000 series airplanes. This AD requires amending the Limitations Section of the airplane flight manual (AFM) to prohibit lifting or positioning the power levers below the flight idle stop while the airplane is in flight. This AFM amendment will include a statement of consequences if the limitation is not followed. This AD results from numerous incidents and five documented accidents involving airplanes equipped with turboprop engines where the propeller beta was improperly utilized during flight. The actions specified by this AD are intended to prevent nose down pitch and a descent rate leading to aircraft damage and injury to personnel caused by the power levers being positioned below the flight idle stop or the power levers being lifted while the airplane is in flight.
60-13-03: 60-13-03 LOCKHEED: Amdt. 176 Part 507 Federal Register June 24, 1960. Applies to All 188 Airplanes Not Equipped With Fuel Tank Pressure Relief Overflow Valves. Compliance required as indicated. Service experience indicates that a check of the fueling system valves at a high fuel level point should be made when filling tanks to capacity. This check is necessary to determine that the system is functioning properly since failure of a fueling valve to close fully may subject the tank to high fuel pressure which could cause not only tank rupture but structural damage. To prevent possible fuel tank overpressurizing, the following actions are required commencing not later than 10 days after publication of this airworthiness directive in the Federal Register. (a) Conduct a check of the fueling system at the start of each fueling operation in accordance with the placard located on the fueling panel. (b) (1) On all outboard tanks and on extended inboard tanks, when installed,conduct a second check of the primary and secondary controls between 8,000 and 10,000 pounds fuel per item 2 on the placard. (2) When standard inboard tanks are installed, conduct a second check of the primary and secondary controls between 4,500 and 6,500 pounds fuel. (c) Any malfunctions indicated by the checks required by items (a) and (b) of this airworthiness directive must be corrected prior to continuance of pressure fueling to that tank. (d) The fueling panel will be monitored during the entire fueling operation. This supersedes paragraph (d) of AD 60-09-03.
97-25-01: This amendment adopts a new airworthiness directive (AD) that applies to all Raytheon Aircraft Company (Raytheon) 58, 60, 90, 100, 200, and 300 series and Model 2000 airplanes (formerly referred to as Beech 58, 60, 90, 100, 200, and 300 series and Beech Models 65-90 and 2000 airplanes). This AD requires replacing certain AlliedSignal Aerospace outflow/safety valves in the pressurization system with new or serviceable valves. The AD results from a report of cracking and consequent failure of the affected outflow safety valves in the pressurization system. Investigation has revealed problems during the manufacturing process of certain Allied Signal outflow/safety valves. The actions specified by this AD are intended to prevent outflow/safety valve cracking and consequent failure, which could result in rapid decompression of the airplane.
64-20-02: 64-20-02 SUD AVIATION: Amdt. 800 Part 507 Federal Register August 22, 1964. Applies to Caravelle Models III and VIR Aircraft. Compliance required as indicated. As a result of a landing gear malfunction which resulted in landing gear interference with the aluminum fuel lines and electric wiring in the wheel wells, accomplish the following modifications: (a) Within 300 hours' time in service after the effective date of this AD, install 3 fusible plugs in each main landing gear wheel hub on all Model III aircraft except aircraft with Serial Numbers 170, 177, and higher as provided for in Hispano Suiza Aero Service Bulletin 111, Section 1, No. 46, dated December 2, 1963. (b) Within 6,000 hours' time in service after the effective date of this AD, remove existing aluminum alloy fuel lines in the main landing gear wheel well and replace them with stainless steel tubing in all Models III and VIR aircraft except aircraft with Serial Numbers 136, 160, 171, and higher, as provided for in Sud Service Bulletin 28-31 dated February 12, 1964, or FAA approved equivalent. (c) Within 6,000 hours' time in service after the effective date of this AD, install protective shrouds over electric wiring and fuel lines in the main landing gear wheel wells on all Model III aircraft except aircraft with Serial Numbers 172 and higher as provided for in Sud Service Bulletin 53-35 dated May 4, 1964, or FAA approved equivalent. (Sud Service Bulletins 28-31 dated February 12, 1964, 53-35 Revision 1 dated May 4, 1964, and Hispano Suiza Service Bulletin 111, Sections 1, No. 46 dated December 2, 1963, pertain to this same subject.) This directive effective September 21, 1964.
61-08-03: 61-08-03 VICKERS: Amdt. 274 Part 507 Federal Register April 8, 1961. Applies to Viscount Models 744 and 745D Series Airplanes. Compliance required as indicated, unless already accomplished. As a result of reported failures of the bolt, P/N 80216-627, forming the forward attachment of the outboard diagonal strut on the inboard engine nacelle structure the following must be accomplished on the structure of both inboard engine nacelles. (a) Bolts P/N 80216-627 or bolts P/N 70116-9*, as applicable, having 4,000 or more hours' time in service must be removed not later than the next 600 landings and inspected for cracks by magnetic particle inspection or FAA approved equivalent method. Particular attention should be given to the area at the junction of the head and shank and also to the thread undercut. (b) Bolts found cracked must be replaced prior to further flight. (c) Compliance with "The Action" paragraphs of British Aircraft Corporation (Operating) Limited, Preliminary Technical Leaflet (PTL 228), Issue 2 (700 Series) is required when accomplishing the inspection of paragraph (a). (d) After compliance with (a), (b), and (c) no further inspection is necessary. (e) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each aircraft's hours' time in service by the operator's fleet average time from takeoff to landing for the aircraft type. Model 745D operators who have kept a record of flights prior to the effective date of this AD may account for them in complying with this AD by counting each flight as one landing. (British Aircraft Corporation (Operating) Limited, PTL No.228, Issue 2, (700 Series) covers this subject. This directive effective May 9, 1961. Revised September 28, 1965. *Bolts P/N 80216-627 were incorporated by Mod. 1306 and on later production aircraft. Pre-mod. standard bolts P/N70116-9 are identical except 1/32-inch less in diameter.
64-03-04: 64-03-04 PIAGGIO: Amdt. 675 Part 507 Federal Register January 21, 1964. Applies to All Model P.166 Aircraft Equipped With Magnaghi Modification 22027 or Modification 2-22027 Shock Absorbers. Compliance required within the next 50 hours' time in service after the effective date of this AD. Fatigue cracks have developed inservice on nose landing gear steering control unit P/N's 4105.26 and 4105.31. To correct this condition, replace flanges in nose undercarriage unit as follows: (a) On aircraft equipped with Modification 2-22027 shock absorber, replace old flange P/N 4105.26 with new flange P/N 4105.26A. (b) On aircraft equipped with Modification 22027 shock absorber, replace old flange P/N 4105.31 with new flange P/N 4105.31A. (c) Accomplish replacement as provided for in Piaggio Service Bulletin No. 166-35 dated July 8, 1963. (Piaggio Service Bulletin No. 166-35 dated July 8, 1963, covers the same subject.) This directive effective February 20,1964.
2005-17-19: The FAA adopts a new airworthiness directive (AD) for certain Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. This AD requires you to measure and adjust the crew seat break-over bolts and to replace the crew seat recline locks on both crew seats. This AD results from CDC discovering that the crew seats, under emergency landing dynamic loads, may fold forward at less than the 26 g required by the regulations. We are issuing this AD to prevent the crew seats from folding forward during emergency landing dynamic loads with consequent occupant injury.
2016-25-04: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by a report of cracking in a certain section of the secondary structure of the wing. This AD requires a one-time inspection of the trailing edge rib, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products.
2016-24-09: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8 and 787-9 airplanes. This AD requires repetitive cycling of either the airplane electrical power or the power to the three flight control modules (FCMs). This AD was prompted by a report indicating that all three FCMs might simultaneously reset if continuously powered on for 22 days. We are issuing this AD to address the unsafe condition on these products.
55-09-03: 55-09-03 DOUGLAS: Applies to All DC-6 Series Aircraft Incorporating Hamilton Standard Propellers Prior to Serial No. 473. \n\n\tTo be accomplished as soon as practicable but not later than August 1, 1955. \n\n\tLoss of manual r.p.m. control can occur as a result of tripping of the fast-acting magnetic circuit breaker before the slow-acting fuse is blown on a faulted branch. Improved circuit protective coordination and resultant reliability in the manual control function should be provided by replacing the "Manual" 10-ampere magnetic circuit breaker with a 5-ampere thermal type breaker, and replacing the four 5-ampere fuses in the synchronizer unit with 2-ampere Slo-Blo fuses. \n\n\t(Douglas Service Letter DC-6 No. 171 dated November 17, 1953, and Hamilton Standard Service Bulletin No. 283 dated December 21, 1953, covers this same subject.)
77-14-12: 77-14-12 BRITISH AIRCRAFT CORPORATION: Amendment 39-2967. Applies to Model BAC 1-11, 200 and 400 series airplanes, certificated in all categories. Compliance is required within the next 500 hours time in service after the effective date of this AD, unless already accomplished. To prevent possible leaks in the ring main ducts of the passenger oxygen system, accomplish the following: (a) Gain access to and conduct a one-time inspection of the passenger oxygen ring main ducts in accordance with paragraph 2.1.1. of the "Accomplishment Instructions" of British Aircraft Corporation Alert Service Bulletin 35-A-PM 5124, Issue No. 1, dated February 12, 1973, or an FAA-approved equivalent. (b) If during the inspection required by paragraph (a) of this AD, chafing of any of the oxygen ducts is found or the clearance with adjacent structure is less than 0.050 inches, comply with the applicable provisions specified in paragraph 2.1.2, 2.1.3, 2.1.4, or 2.1.5 of BAC Alert Service Bulletin 35-A-PM 5124, dated February 12, 1973, or an FAA-approved equivalent. (c) If, as a result of any of the actions required by paragraph (b) of this AD, the use of the passenger oxygen system is restricted, install an FAA-approved placard in full view of the pilot which defines the restriction and states that flight operations must be limited to those allowed by the applicable operating rules for the particular airplane. This amendment becomes effective August 15, 1977.
2016-24-03: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of cracked and corroded barrel nuts found at the mid-spar location of the horizontal-stabilizer-to-vertical-stabilizer attachment joint. This AD requires repetitive detailed [[Page 88624]] inspections of each barrel nut and cradle, a check of the bolt torque of the preload indicating (PLI) washers, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products.
2016-24-06: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, and -106 airplanes, Model DHC- 8-200 series airplanes, and Model DHC-8-300 series airplanes. This AD was prompted by several occurrences of loss of airspeed data on both pilot and co-pilot air speed indicators due to the accumulation of ice on the pitot probes caused by inoperative pitot probe heaters. This AD requires replacing the existing circuit breakers in the pitot heater system. We are issuing this AD to address the unsafe condition on these products.
2010-12-05: We are superseding an existing 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: Following in-flight test deployments on CL-600-2B19 aircraft, several Air-Driven generators (ADGs) failed to come online. Investigation revealed that, as a result of a wiring anomaly that had not been detected during ADG manufacture, a short circuit was possible between certain internal wires and their metallic over- braided shields, which could result in the ADG not providing power when deployed. * * * The unsafe condition is failure of the ADG, which could lead to loss of several functions essential for safe flight. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective July 12, 2010. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of April 30, 2009 (74 FR 13094, March 26, 2009).
2016-19-16: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 707-300, 707-300B, and 707-300C series airplanes; and certain Model 727C, 727-100C, and 727-200F series airplanes. This AD was prompted by a report indicating that a cam latch on the main cargo door (MCD) broke during flight. This AD requires various inspections and related investigative and corrective actions, if necessary. We are issuing this AD to address the unsafe condition on these products.
2005-18-03: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney (PW) PW2000 series turbofan engines. That AD currently requires revisions to the engine manufacturer's time limits section (TLS) to include enhanced inspection of selected critical life- limited parts at each piece-part opportunity. This AD requires modifying the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. This AD results from an FAA study of in-service events involving uncontained failures of critical rotating engine parts that indicates the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. We are issuing this AD to prevent critical life-limited rotating engine part failure, which could result inan uncontained engine failure and damage to the airplane.
80-20-01: 80-20-01 BOEING: Amendment 39-3927. Applies to those Model 747 series airplanes listed under Groups I and II in Boeing Service Bulletin 747-53-2114, Revision 3, dated September 3, 1980, or later FAA approved revisions. Prior to January 31, 1981, unless already accomplished: \n\n\tA.\tModify stringers 18 and 19, left and right side, between fuselage stations 2360 and 2412, in accordance with Boeing Service Bulletin 747-53-2114, Revision 3, dated September 3, 1980, or later FAA approved revisions; or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.\n \n\tB.\tUpon request of the operator, an FAA Principal Maintenance Inspector, subject to prior approval by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, may adjust the compliance times if the request contains substantiating data to justify the increase for that operator. \n\n\tC.\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 \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 Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective October 7, 1980.
2016-24-05: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by heavy corrosion found on the wing rear spar lower girder. This AD requires inspections of the affected areas, modification of the wing trailing edge lower skin panels, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
61-10-02: 61-10-02 CONVAIR: Amdt. 283 Part 507 Federal Register May 11, 1961. Applies to All Model 22 (880) Aircraft. Compliance required as indicated. Two cases of failure of the forward engine mount support fitting P/N 22-02593-1, have been reported. Failure of this part permits the engine to rotate with the forward end coming to rest on the bottom of the engine pod structure. (a) Unless P/N 22-02593-3 or an FAA approved equivalent has already been installed, within the next 250 hours' time in service and at intervals of 250 hours' time in service thereafter, remove and inspect by means of dye penetrant or magnetic particle inspection, or equivalent, P/N 22-02593-1 for cracks and/or material defects. If cracks and/or material defects are found, the part must be replaced prior to further flight. (b) When P/N 22-02593-1 has been replaced with P/N 22-02593-3 or FAA approved equivalent, the inspection required above may be discontinued. (Convair Service Bulletin No. A71-2 covers this same subject.) This directive effective May 11, 1961.
81-15-07: 81-15-07 KAWASAKI HEAVY INDUSTRIES, LTD. (KHI): Amendment 39-4164. Applies to Models KV107-II and KV107-IIA helicopters equipped with main rotor tension-torsion strap assemblies, P/N 107R2003-1, certificated in all categories (Airworthiness Docket No. 81-ASW-11). Compliance required as indicated. To prevent fatigue failure of the main rotor tension-torsion strap assemblies, remove from service tension-torsion strap assemblies, P/N 107R2003-1, on or before the accumulation of 27,800 hours' time in service and replace with a serviceable part that has less than 27,800 hours' total time in service. This amendment becomes effective August 25, 1981.
2005-17-18: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes; and Model A340-541 and -642 airplanes. This AD requires repetitively resetting the display units (DUs) for the electronic instrument system (EIS) either by switching them off and back on again or by performing a complete electrical shutdown of the airplane. This AD results from an incident in which all of the DUs for the EIS went blank simultaneously during flight. We are issuing this AD to prevent automatic reset of the DUs for the EIS during flight and consequent loss of data from the DUs, which could reduce the ability of the flightcrew to control the airplane during adverse flight conditions.
97-12-02: This amendment supersedes an existing priority letter airworthiness directive (AD), applicable to McDonnell Douglas Helicopter Systems (MDHS) Model MD900 helicopters, which prohibits flight or ground operations of helicopters with a certain adjustable collective drive link assembly (link assembly) installed. This amendment requires installation of a redesigned airworthy link assembly after which further operations are permitted. This amendment is prompted by recent incidents in which the link assembly failed during flight. The actions specified by this AD are intended to prevent failure of the link assembly, which could result in loss of control of the helicopter.