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2005-14-04: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 and -300 series airplanes. This AD requires replacing the existing halogen lamps in the cargo compartment light assemblies with new incandescent lamps, and installing warning and identification placards. This AD is prompted by a report of an aft cargo fire during flight. We are issuing this AD to prevent a fire in the cargo compartment.
73-12-10: 73-12-10 HANDLEY PAGE (JETSTREAM AIRCRAFT LTD): Amdt. 39-1660. Applies to Model HP-137 Mk 1 airplanes. Compliance is required within the next 50 hours' time in service after the effective date of this AD unless already accomplished. To prevent the possible unnecessary interruption of current flow to the battery bus and non-essential bus, replace the 30 amp fuse, F10 in the D.C. power control box with a 25 amp Klixon circuit breaker, P/N D6761- 1-25, in accordance with Jetstream Aircraft Limited Modification No. 5006, Parts 1 and 2, dated September 1971, or an FAA-approved equivalent. This amendment becomes effective July 6, 1973.
64-10-04: 64-10-04 PIPER: Amdt. 728 Part 507 Federal Register May 12, 1964. Applies to Model PA-24-250 Aircraft, Compliance required within 50 hours' time in service after the effective date of this AD. In order to prevent portions of the carburetor air box deflector vanes from breaking loose and lodging within the carburetor throat, remove the deflector vanes from the air box, P/N 21943- 03, in accordance with Piper Service Letter No. 420. Upon removal of these vanes, the air box P/N becomes 21943-05. (Piper Service Letter No. 420 dated March 5, 1964, covers this subject.) This directive effective May 12, 1964.
99-26-21: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-300, -400, -500, -600, -700, and -800 series airplanes. This action requires a one-time detailed visual inspection of certain wire bundles and hydraulic hoses for the electric motor driven pump (EMDP) for hydraulic system "B" located in the right main wheel well to detect discrepancies; and corrective actions, if necessary. This amendment is prompted by a report that the wire bundle to the EMDP had been chafed by the pressure hose for hydraulic system "B" on a Model 737-700 series airplane, and reports of failed or damaged case drain or pressure hoses on the EMDP for hydraulic system "B" on Model 737-400 series airplanes. The actions specified in this AD are intended to prevent electrical arcing due to chafing between certain hydraulic hoses and adjacent wire bundles, which could result in a consequent increased risk of fire.
71-15-03: 71-15-03 SOCATA MORANE SAULNIER: Amdt. 39-1247. Applies to Morane Saulnier Model MS.880B and MS.894A airplanes. Compliance is required within the next 50 hours' time in service after the effective date of this AD unless already accomplished. To prevent short circuits in the cables of the generator system, rework the cables of the generator system in accordance with paragraph 2 degrees/, SOCATA Service Bulletin No. 79 (Gr. 24-01), dated October 1970, or an FAA-approved equivalent. This amendment becomes effective 26 July 1971.
88-15-04: 88-15-04 BOEING: Amendment 39-5979. Applies to Model 767 series airplanes, as listed in Boeing Alert Service Bulletin 767-32A0071, dated June 2, 1988, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo preclude failure of the main landing gear to fully extend and lock due to faulty actuator piston seals or obsolete configuration rod seals, accomplish the following: \n\n\tA.\tWithin the next 300 hours time-in-service after the effective date of this AD, inspect the main landing gear drag brace actuators in accordance with Boeing Alert Service Bulletin 767-32A0071, dated June 2, 1988. \n\n\tB.\tIf any actuator has accumulated less than 200 hours total time-in-service at the time of inspection, repeat the inspection required by paragraph A., above, at intervals not to exceed 100 hours time-in-service until the actuator has accumulated more than 200 hours time- in-service, at which time the inspections may be terminated. \n\n\tC.\tIf anyactuator is found to have swollen seals or obsolete configuration seals, before further flight, replace or modify the actuator, in accordance with Boeing Service Bulletin 767-32A0071, dated June 2, 1988. \n\n\tD.\tAccomplishing the piston seal replacement, and the rod seal inspection and replacement, if necessary, in accordance with Boeing Service Bulletin 767-32A0071, dated June 2, 1988, constitutes terminating action for the initial and repetitive inspections required by paragraphs A. and B., above. \n\n\tE.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tF.\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 the inspections required by this AD. \n\n\tAll persons affected by this directive who have not already received copies of the appropriate service bulletin cited herein may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment, 39-5979, becomes effective August 3, 1988.
2018-10-09: We are superseding Airworthiness Directive (AD) 2017-11-03 for DG Flugzeugbau GmbH Model DG-500MB gliders that are equipped with a Solo 2625 02 engine modified with a fuel injection system following the instructions of Solo Kleinmoteren GmbH Technische Mitteilung 4600-3 and identified as Solo 2625 02i. 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 failure of the connecting rod bearing resulting from too much load on the rod bearings from the engine control unit. This AD adds a model to the applicability. We are issuing this AD to require actions to address the unsafe condition on these products.
2018-10-07: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76C helicopters. This AD requires inspecting the engine collective position transducer (CPT). This AD was prompted by reports of wear of the CPT that has resulted in several One Engine Inoperative (OEI) incidents. The actions of this AD are intended to detect and prevent an unsafe condition on these products.
2018-10-06: We are adopting a new airworthiness directive (AD) for Bell Model 407 helicopters. This AD requires repetitive inspections of the tail rotor (TR) driveshaft segment assemblies and a torque check of the TR adapter retention nuts. This AD was prompted by a report of an in- flight failure of the TR drive system. The actions of this AD are intended to detect and correct an unsafe condition on these products.
84-24-52 R1: 84-24-52 R1 SHORT BROTHERS, LTD.: Amendment 39-4992 as Amended by Amendment 39-5802. Applies to all Model SD3-60 airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To reduce the potential for engine flameouts, accomplish the following: A. Before further flight, incorporate the following information into the Airplane Flight Manual and provide this information to flight crews. This may be accomplished by including a copy of this AD in the Airplane Flight Manual and Operating Manual: "Increase the threshold temperatures from 4 degrees C to 10 degrees C on Page 37, Section 4, Systems Operation, Ice and Rain Protection Systems (as fitted)." B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Within one year after the effective date of this amendment, modify the fuel low pressurebooster pumps in accordance with Parts B and C of Short Brothers Service Bulletin SD360-28-17, dated November 1985. Accomplishment of these modifications constitute terminating action for the increased temperature threshold required by paragraph A., above. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Short Brothers Aircraft, 1725 Jefferson Davis Highway, Arlington, Virginia 22202. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. AD 84-24-52 Amendment 39-4992 became effective February 7, 1985 except to those recipients of telegraphic AD T84-24-52, dated December 7, 1984. This amendment 39-5802 becomes effective February 1, 1988.