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82-26-04: 82-26-04 DORNIER: Amendment 39-4518. Applies to Model DO28D-1 (Serial Nos. 4036, 4037, 4050, 4055 through 4058, 4303, 4308 through 4318, 4321 through 4325, 4331 and 4332) airplanes, certificated in any category, when equipped with ARC PA-500A autopilot actuators. COMPLIANCE: Required as indicated, unless already accomplished. To prevent restriction of control movement due to jamming of the ARC PA-500A actuator gear train, accomplish the following: (a) Within the next 100 hours time-in-service after the effective date of this AD and thereafter at intervals not to exceed 100 hours time-in-service, inspect the ARC PA-500A actuator in accordance with Dornier Service Bulletin No. 1069-2820, dated May 27, 1980, which incorporates ARC Field Engineering Service Bulletin No. 181. Prior to further flight correct any unsafe condition noted by adjustment or replacement of parts as necessary. (b) Within 12 months after the effective date of this AD, modify the ARC Model PA-500A actuator(s) in accordance with Dornier Service Bulletin No. 1069-2820, dated May 27, 1980, which incorporates ARC Field Engineering Service Bulletin No. 181. (c) The inspections required by paragraph (a) of this AD may be discontinued when the modifications required in paragraph (b) of this AD have been accomplished. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) The intervals between repetitive inspections required by this AD may be adjusted up to 10 hours time-in-service to allow them to be accomplished concurrent with other scheduled maintenance on the airplane. (f) An equivalent method 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 December 27, 1982.
97-15-13: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes (formerly referred to as Beech Models 1900, 1900C, and 1900D airplanes). This action requires installing lubrication fittings in the airstair door handle and latch housing mechanisms. The AD results from reports of the airstair door not opening because the door was frozen shut. The actions specified by this AD are intended to prevent moisture from accumulating and freezing in the airstair door handle and latch housing, which could result in the door freezing shut and passengers not being able to evacuate the airplane in an emergency situation.
2007-01-09: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100B SUD, 747-200B, 747-300, 747-400, 747- 400D, and 747SP series airplanes. This AD requires repetitive inspections for cracking of the crease beam and adjacent intercostals, stringers, frames, and skin panels; and related investigative and corrective actions if cracking is found. This AD results from a report indicating that an operator discovered crease beam cracking on two Model 747 airplanes. We are issuing this AD to detect and correct cracking of the crease beam and adjacent structure, which could become large and result in in-flight depressurization and inability of the airframe structure to sustain flight loads.
2007-02-11: We are adopting a new airworthiness directive (AD) to supersede AD 2002-21-11, which applies to certain EXTRA Flugzeugbau GmbH (EXTRA) Model EA-300S airplanes. AD 2002-21-11 currently requires you to inspect, using a fluorescent dye check penetrant method, the upper longeron at the horizontal stabilizer attachment for cracks, repair any cracks found, and modify the horizontal stabilizer. That AD also requires a limit on operation to the Normal category until the initial inspection and modification on airplanes with less than 200 hours time-in-service is done. Since we issued AD 2002-21-11, cracks have been found on Models EA-300L and EA-300/200 airplanes. Consequently, this AD adds airplanes to the Applicability section and requires you to inspect and modify the upper longeron at the horizontal stabilizer attachment. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect, correct, and prevent cracks in the upper longeron at the horizontal stabilizer attachment, which could result in structural failure of the aft fuselage. This failure could lead to loss of control.
84-08-05 R1: 84-08-05 R1 BOEING: Amendment 39-4852 as amended by Amendment 39-4889. Applies to Boeing Model 727-100 airplanes modified to install a Performance Data Computer under STC SA1602NM. To preclude the loss of airspeed information due to conditions related to the pitot- static system, accomplish the following no later than November 5, 1984, unless already accomplished. \n\n\tA)\tConnect the first and second pilots' flight instruments to the appropriate pitot-static systems to conform with Civil Air Regulations (CAR) 4b.612 using a means approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB)\tPerform a leak check of the pitot-static system in accordance with Federal Aviation Regulations (FAR) Part 91.170. \n\n\tC)\tPerform a functional test of the air data system. \n\n\tD)\tPerform a functional check of the pitot heat system. \n\n\tE)\tAlternate 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.\n \n\tAmendment 39-4852 became effective May 7, 1984. \n\tThis Amendment 39-4889 becomes effective August 1, 1984.
2019-14-01: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) TAY 650-15 and TAY 651-54 turbofan engines with low-pressure compressor (LPC) fan blade module M01300AA or M01300AB, installed. This AD was prompted by reports of LPC fan blade retention lug fractures on engines with a high number of dry- film lubrication (DFL) treatments. This AD requires determining the number of DFL treatments applied on each LPC fan blade, and removing from service and replacing the affected LPC fan blades if the DFL treatment limit is exceeded. The FAA is issuing this AD to address the unsafe condition on these products.
46-38-03: 46-38-03 ERCO: (Was Mandatory Note 7 of AD-718-6.) Applies to 415-C, -CD and -D Aircraft Serial Numbers 345 to 2134, Inclusive. To be accomplished prior to November 15, 1946. In order to prevent possible fuel system failures, the dural elbow fitting AN 914-2D between the fuel filter and the carburetor should be replaced with elbow fitting AN 914-2. (Erco Service Bulletin No. 12 dated July 11, 1946, covers this same subject.)
85-04-02: 85-04-02 BOEING: Amendment 39-5007. Applies to the Model 767-200 series airplanes certificated in all categories. Compliance is required as indicated unless previously accomplished. To prevent fuel boost pump seizures in flight, as a result of operation with cold fuel, accomplish the following: \n\n\tA.\tWithin 30 days after the effective date of this AD, install a cockpit placard which limits fuel tank temperature to -37 degrees C (-35 degrees F), in accordance with Boeing Service Bulletin 767-28-14 dated June 20, 1984, or later FAA approved revision. \n\n\tB.\tWithin one year after the effective date of this AD, replace at least one fuel boost pump in each main fuel tank and at least one fuel boost pump in each center auxiliary fuel tank (if activated) with an improved boost pump, in accordance with Boeing Service Bulletin 767-28-14 dated June 20, 1984, or later FAA approved revision. \n\n\tC.\tWithin two years after the effective date of this AD, replace all unimproved fuel boost pumps in each main tank and all unimproved fuel boost pumps in each center auxiliary tank (if activated) with improved fuel boost pumps, in accordance with Boeing Service Bulletin 767- 28-14 dated June 20, 1984, or later FAA approved revision. \n\n\tD.\tThe fuel temperature limitation and cockpit placard required by paragraph A., above, may be removed after at least one improved fuel boost pump is installed in each tank location required by paragraph B., above. \n\n\tNOTE: The center auxiliary fuel tank boost pumps need not be replaced on airplanes with deactivated center auxiliary fuel tanks (i.e., those not able to be fueled); however, this deviation must be recorded in the permanent aircraft records. All center auxiliary fuel tank boost pumps must be replaced with the improved boost pumps identified in Boeing Service Bulletin 767-28-14 prior to activation of the center auxiliary fuel tank. \n\n\tE.\tAlternate means of compliance which provide an equivalent level of safety may be used whenapproved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \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 inspections and/or modifications required by this AD. \n\n\tThis amendment becomes effective March 28, 1985.
63-13-03: 63-13-03 HARTZELL: Amdt. 577 Part 507 Federal Register June 22, 1963. Applies to Models HC-93Z30-2/10152-5 1/2, HC-B3Z30-2/ 10152-5 1/2, and HC-B3Z30-2/10160-6 Propellers Installed on Pratt and Whitney R-985 Engines. Compliance Required as indicated. To preclude propeller blade slippage and blade shank failures, accomplish the following: (a) Within 25 hours' time in service after the effective date of this AD, on blades with less than 1,975 hours' total time in service that have not been previously indexed in the manner described in (e)(4), accomplish the following: (1) By means of a portable propeller blade protractor, measure the angle of each blade on the propeller at the 30-inch radius station, when each is set in a true horizontal position. (2) Should the relative blade angle between each blade of a given propeller differ by more than 1 degree ( a tolerance of + 1/2 degree is permissible) from each of the other blades, inspections in accordance with(e) shall be accomplished before further flight, regardless of propeller total time in service. However, if the blades are set within acceptable limits, they shall be indexed in accordance with (e) (4), and shall be inspected and reworked in accordance with (e) before the accumulation of 2,000 hours' total time in service. (b) Blades with less than 1,975 hours' total time in service that have been previously indexed in the manner described in (e)(4) shall be inspected and reworked in accordance with (e) before the accumulation of 2,000 hours' time in service. (c) Blades with 1,975 hours' or more total time in service on the effective date of this AD, shall be inspected and reworked within 25 hours' time in service after the effective date of this AD in accordance with (e). (d) Blades for which the total time in service cannot be determined shall be inspected and reworked in accordance with (e) within 25 hours' time in service after the effective date of this AD. (e)The inspection and rework shall be accomplished as follows: (1) Inspect for cracks, the blade and blade shank by a dye penetrant method, and the hub by a magnetic particle process, in accordance with instructions outlined in Hartzell Overhaul Manual No. 114, and Hartzell Service Bulletin No. 83. Remove cracked blades from service before further flight. (2) Shot peen the blade shank and hub per instructions and specifications in Hartzell Service Bulletin No. 83. (Not applicable to the HC-93Z30 hub.) (3) The blades of the propellers shall be checked for proper blade clamp clearances, and the blade angles set up as outlined in Hartzell Service Bulletin No. 69 and Overhaul Manual No. 114. (4) The blades and clamps shall be indexed with red plastic tape as indicated in Hartzell Service Bulletin No. 69, Supplement No. 1. During the routine preflight inspections this provides a method for visual inspection of any blade slippage in the blade clamps. (Hartzell Service Bulletins Nos. 69 dated September 16, 1959, Supplement No. 1 dated September 19, 1962, 83 dated October 18, 1962, cover this subject, and Hartzell Manuals Nos. 104A and 114 also apply, including all supplements thereto of the preceding releases.) This directive effective July 23, 1963.
98-22-04: This amendment supersedes an existing airworthiness directive (AD), applicable to all CASA Model C-212 series airplanes, that currently requires replacement of the cover of the power control quadrant pedestal with a cover that incorporates slot protection. This amendment requires repetitive inspections for deterioration or damage of the slot protection installed in the cover of the power control quadrant pedestal. This amendment also requires eventual modification of the cover, which constitutes terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent deterioration of the slot protection installed in the cover of the power control quadrant pedestal, which could allow foreign objects to jam or interfere with the power or trim control system and result in reduced controllability of the airplane.