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47-02-03: 47-02-03 MCDONNELL DOUGLAS: Amendment 39-3720. (Was Mandatory Note 11 of AD-762-7.) Applies to C-54 and DC-4 Aircraft. \n\n\tTo be accomplished not later than August 1, 1947. \n\n\tBecause of failures in service of the main 9" Douglas aluminum accumulator, it is necessary to replace it with at least one 7 1/2" steel accumulator, Bendix P/N 406920 or Vickers P/N AA14308B, or Vickers 10" accumulator Model AA-14310. \n\n\t(Douglas Service Bulletin DC-4 No. 9 and Addendum dated January 6, 1956 cover the same subject.) \n\n\tThis Amendment 39-3720 becomes effective March 27, 1980.
2009-26-04: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires repetitive lubrication of the left and right main landing gear (MLG) forward trunnion pins; and an inspection for discrepancies of the transition radius, lead-in chamfer, and cross- bolt bore of the MLG forward trunnion pins, and repair or replacement if necessary. Doing the applicable inspections and repairs/ replacements, or overhauling the trunnion pins ends the repetitive lubrication requirements of this AD. For airplanes on which a certain repair is done, this AD requires repetitive inspections for discrepancies of the transition radius. This AD results from a report that the protective finishes on the forward trunnion pins for the left and right MLG might have been damaged during final assembly. We are issuing this AD to prevent cracking of the forward trunnion pin, which could result in fracture of the pin and consequentcollapse of the MLG.
80-22-05: 80-22-05 TELEDYNE CONTINENTAL MOTORS: Amendment 39-3948. Applies to engine models as follows: TSIO-520-M, serial numbers 511000 through 520187, 230126R through 230129R, 230131R through 230142R, and 230144R through 230146R, installed in, but not limited to, certain Cessna Models TU206G and T207A airplanes certificated in all categories; TSIO-520-P, serial numbers 513000 through 513620, and 236401R, installed in, but not limited to, certain Cessna Model P210N airplanes certificated in all categories; TSIO-520-R, serial numbers 512000 through 517961, 230226R, 230228R, 230230R through 230233R, 230235R through 230246R, and 230248R, installed in, but not limited to, certain Cessna Models T210M and T210N airplanes certificated in all categories. Compliance is required within the next 25 hours time in service after effective date of this AD, unless already accomplished. To prevent the crankshaft front oil seal being dislodged from the engine crankcase, accomplish the following: (a) Remove engine top cowl panel and left and right nose cowl sections. (b) Inspect the crankshaft front oil seal which is located on the crankshaft where it passes through the front engine case. If the seal is displaced or there is evidence of oil leakage, replace the oil seal in accordance with the appropriate maintenance manual. (c) Install two (2) seal half plates, TCM Part No. 641361, on the forward face of the crankcase with four (4) TCM Part No. 628321-.38 bolts. Torque bolts to 21-25 in-lbs. (d) Reinstall left and right nose cowl sections and engine top cowl panel, ensuring that baffle seals are fitted and turned in the correct direction. (e) Run the engine until normal operating temperature is reached and inspect crankshaft front oil seal for leaks. (f) Make an appropriate maintenance record entry. NOTE: Teledyne Continental Service Bulletin No. M80-20, dated September 12, 1980, pertains to this subject. An equivalent method of compliance may be approvedby the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. This amendment is effective October 24, 1980.
81-12-51: 81-12-51 FLUG UND FAHRZEUGWERKE AG: Amendment 39-4239. Applies to AG Model Diamant HBV and 16.5 gliders, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent loss of the rudder lower close tolerance bolt, which could result in loss of the rudder, accomplish the following: (a) Before further flight, unless already accomplished within the last 25 flight hours, and thereafter at intervals not to exceed 25 flight hours until replacement per paragraph (b) is accomplished, inspect the rudder close tolerance bolt for tightness in accordance with Flug Und Fahrzeugwerke AG Service Bulletin Number 10, dated April 1981, or in accordance with applicable criteria of FAA Advisory Circular 43.13-1A. If the bolt is loose (free to rotate), before further flight, replace the bolt in accordance with the above noted Service Bulletin, or an FAA- approved equivalent. (b) Unless already accomplished, prior to January 1, 1982, replace the rudder close tolerance bolt in accordance with Flug Und Fahrzeugwerke AG Service Bulletin Number 10, dated April 1981, or an FAA-approved equivalent, as follows: (1) Remove rudder as follows: (i) Push rudder to the right deflection limit so that the bolt is visible through the opening on the left side of the rudder. (ii) Remove connecting bolt at the end of the push rod. (iii) Remove close tolerance bolt. (iv) Remove rudder from the bearing block by pulling the rudder backwards. As soon as the rudder is off the bearing block, pull the rudder downwards to remove it from the upper bearing. (2) Modification procedure: (i) On the lower bearing block, remove both rivets from the anchor nut. Then rivet bracket and sheet together again (without anchor nut). (ii) Mount rudder in reverse order to Item 1. (iii) Check deflections according to the flight manual, Item 5.2. (plus or minus 30 degrees, +3 degrees, -0 degrees).(iv) Check rudder and elevator controls for free movement. (3) Material: Materials Part Number 1 connecting bolt D1.206-0303 1 spacer R20002 AN 960-C10L 2 castle nuts M6 VSM 13780 2 cotter pins 1.6 x 16 VSM 12760 1 close tolerance bolt D1.201-1228.1 2 rivets MS 20470-AD2-10 (c) For the purpose of compliance with this AD, an equivalent procedure may be approved by the Chief of the FAA Engineering and Manufacturing Branch of any FAA region. 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 Flug Und Fahrzeugwerke AG, CH-9422 Staad SG, Switzerland. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, D.C. 20591. This amendment becomes effective October 22, 1981, as to all persons except those persons to whom it was made immediately effective by telegraphic AD T81-12-51, issued June 10, 1981, which contained this amendment.
2009-25-09: We are adopting a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) helicopters. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI Emergency AD states that there has been a report of the failure of a flexible coupling on one of the main gearbox (MGB) inputs, which may be the result of loss of the tightening torque load, or insufficient tightening of the nuts on the bolts fixing the discs of the flexible coupling to its sliding and fixed hinges. This condition, if not corrected, could result in failure of the coupling discs, and if this condition develops on both the left-hand (LH) and right-hand (RH) MGB inputs, a complete loss of power to the transmission and subsequent loss of control of the helicopter.
80-13-09: 80-13-09 MCDONNELL DOUGLAS: Amendment 39-3811. Applies to McDonnell Douglas Model DC-10-10, -10F, -30, -30F and -40 Series Airplanes certificated in all categories utilizing Air Cruisers Part No. 24D30051 series passenger evacuation systems with the following serial numbers: \n\n\tLeft Hand Door: Air Cruisers Company P/N 24D30051 series, all serial numbers prior to S/N 1531, except 1508, 1510, 1511, 1515, 1519, 1521, 1523 and 1525. \n\n\tRight Hand Door: Air Cruisers Company P/N 24D30051 series, all serial numbers prior to S/N 1630, except 1605, 1611, 1613, 1615, 1619, 1621 and 1623. \n\n\tCompliance required within next eighteen (18) calendar months after the effective date of this AD, unless already accomplished. \n\n\tTo prevent improper deployment of the Air Cruisers Company emergency evacuation system due to delay in separation of the velcro tracking restraint device, accomplish the following: \n\n\ta.\tModify the affected evacuation system assemblies in accordance with Part 2, Accomplishment Instructions, of Air Cruisers Company Service Bulletin No. 25-75 dated January 24, 1980. \n\n\tb.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of modifications required by this AD. \n\n\tc.\tAlternative modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective August 30, 1980.
47-10-29: 47-10-29 LOCKHEED: (Was Mandatory Note 32 of AD-763-3.) Applies to All Model 49 Serials Prior to 2080 on Which Metal Ailerons Are Installed. Compliance required prior to April 1, 1947. Between aileron Stations 69.5 and 99.7, install drain holes in the lower aileron surface outboard of each rib and forward of each stringer (17 holes total). (LAC Service Bulletin 49/SB-214 covers this same subject.)
80-18-03: 80-18-03 PIPER (Ted Smith): Amendment 39-3900. Applies to Aerostar Model 601 and 601P series airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent possible engine failure due to excessive lean fuel/air mixture, accomplish the following: (a) Within 30 days from the effective date of this AD, index and mark the left hand and right hand engine fuel pressure gauges with a yellow arc between the 12 psi and 18 psi range, and incorporate provisions in the Airplane Flight Manual Operations Limitations Section as follows: 1. In the Power Plant Instruments paragraph and under the Yellow ARC Caution column of the fuel pressure data add "12 -18 psi" 2. In the Fuel System Limitations paragraph add the statement "Fuel boost pump must be "ON" when fuel pressure indication is less than 18 psi and engine is operating above idle power." (b) 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 the modifications required by this AD. (c) Alternative modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective October 6, 1980.
80-19-10: 80-19-10 CESSNA: Amendment 39-3922. Applies to Model 335 (Serial Numbers 335-0001 thru 335-0054 and 335-0056) and Model 340A (Serial Numbers 340A0901 thru 340A0994 and 340A1002) airplanes certified in all categories. COMPLIANCE: Required as indicated unless the requirements of Paragraph B) have been previously accomplished. To prevent flight in adverse weather conditions with no means to supply electrical power to the deicer systems: A) Prior to further flight: 1. Install, and operate the airplane in accordance with, a temporary placard on the instrument panel just below the glareshield in the pilot's line of forward vision when seated in the left control seat which states, "Not Approved For Flight In Icing Conditions." 2. Install black electrician's tape or equivalent over the bottom portion of the airplane Operational Limits placard, which is located on the pilot's sun visor, to cover the wording "AND FLIGHTS INTO ICING CONDITIONS IF THE PROPER OPTIONAL EQUIPMENT IS INSTALLED AND OPERATIONAL." 3. Pull the propeller deice and optional heated windshield circuit breakers, if installed, and install a band around each breaker to prevent activating those circuits. B) Within 25 hours time-in-service after the effective date of the AD, perform the wiring inspection and accomplish the wiring change, if required, in accordance with Cessna Multi-engine Customer Care Service Information Letter ME80-31 dated July 18,1980. Make the prescribed entry in the airplane maintenance records. C) Remove the temporary placard, cover tape and circuit breaker bands specified in Paragraphs A)1., 2., and 3. when Paragraph B has been accomplished. D) Within seven days notify, in writing, the Chief, Aircraft Certification Program, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209 of any incorrect wiring of the deicer buss found when complying with Paragraph B). One acceptable means of making these reports is Malfunction or Defect Report (FAA Form 8010-4). (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) Failure to comply with this paragraph subjects owners/operators to agency enforcement action. E) The airplane may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. F) Any equivalent method of compliance with this Airworthiness Directive must be approved by the Chief, Aircraft Certification Program, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209. This amendment becomes effective on September 29, 1980, to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated September 4, 1980, and is identified as AD 80-19-10.
2009-24-22: We are adopting a new airworthiness directive (AD) for certain Learjet Model 45 airplanes. This AD requires inspecting the baggage bay door fire barrier seal for inconel mesh in the fire barrier seal material; for certain airplanes, inspecting the fiberglass doublers for presence of red Room Temperature Vulcanizing (RTV) sealant; and doing related investigative and corrective actions if necessary. This AD results from reports of incorrect external baggage door seal material and door seal sealant, as well as incorrect sealant on interior baggage panels used during manufacture of the airplane. We are issuing this AD to prevent the use of door seals and sealant that do not meet flammability requirements, which could result in an uncontrollable and undetected fire within the baggage compartment.