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2018-10-10: We are superseding Airworthiness Directive (AD) 2017-01-12, AD 2017-11-08, and AD 2017-15-09 for certain Diamond Aircraft Industries GmbH Model DA 42 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and address an unsafe condition on an aviation product. The MCAI describes the unsafe condition as uncommanded engine shutdown during flight due to failure of the propeller-regulating valve caused by hot exhaust gases coming from fractured engine exhaust pipes. We are issuing this AD to require actions to address the unsafe condition on these products.
46-50-01: 46-50-01 WACO: (Was Special Note 2 of AM-166.) Applies to Models INF, KNF, MNF, RNF Aircraft. Inspection required before next flight - rework (if needed) not later than April 1, 1946. Inspect the fuel line (or lines) connecting the fuel strainer and the carburetor to determine that this line is made up of either: (a) Rigid metal tubing with flexible hose connections at each end, or (b) Approved type flexible hose assembly. Aircraft found to have fuel line installations not conforming to either (a) or (b) shall be altered to conform as soon as possible. (Waco Service Bulletin No. 154 also covers this subject.)
91-06-17: 91-06-17 BOEING: Amendment 39-6931. Docket No. 90-NM-164-AD. \n\n\tApplicability: Model 747-400 series airplanes through line number 791, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent the failure of either pilot's electronic flight instrument system (EFIS) control panel, with resultant smoke in the flight deck, accomplish the following: \n\n\tA.\tWithin 90 days after the effective date of this AD, inspect both EFIS control panels installed on the airplane and record the serial number and modification status. Control Panels with serial numbers identified in Collins Service Bulletin DCP-7000-31-04, dated December 1, 1989, and which do not have Modification 4 implemented, must be removed and modified in accordance with the service bulletin before further flight. \n\n\tB.\tAny EFIS control panel with a serial number identified in Collins Service Bulletin DCP- 7000-31-04, dated December 1, 1989, and which does not have Modification 4 implemented, must be modified in accordance with the service bulletin before installation on an airplane. \n\n\tC.\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 (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124; and Collins Air Transport Division/Rockwell International, 400 Collins Road N.E., Cedar Rapids, Iowa 52406. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tThis amendment (39-6931, AD 91-06-17) becomes effective on April 15, 1991.
2018-09-51: We are adopting a new airworthiness directive (AD) for CFM International, S.A., (CFM) CFM56-7B model engines. This emergency AD was sent previously to all known U.S. owners and operators of CFM CFM56-7B model engines. This AD requires a one-time ultrasonic inspection (USI) of the concave and convex sides of the fan blade dovetail. This AD was prompted by a recent engine failure due to a fractured fan blade, which resulted in the engine inlet cowl disintegrating and debris penetrating the fuselage, causing a loss of pressurization, and prompting an emergency descent. We are issuing this AD to address the unsafe condition on these products.
86-22-03: 86-22-03 BOEING: Amendment 39-5443. Applies to the Model 737-300 series airplanes specified in Boeing Alert Service Bulletin 737-28A1062, Revision 1, dated April 11, 1986, certificated in any category. \n\n\tTo minimize the fire hazard associated with a fuel leak, due to the fuel feed tube assembly chafing against strut fasteners, accomplish the following within 3 months after the effective date of this AD, unless previously accomplished: \n\n\tA.\tInspect and, if necessary, adjust fuel feed tube assembly clearance and replace chafed tubes in accordance with Boeing Service Bulletin 737-28A1062, Revision 1, dated April 11, 1986, or later FAA-approved revision. \n\n\tB.\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\tC.\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 inspections and/or modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received copies of the manufacturer's Service Bulletin may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective November 24, 1986.
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.