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2018-12-04: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-300ER series airplanes. This AD requires replacing the water filter assembly in certain steam ovens. This AD was prompted by a report that water can enter the steam oven cavity and become heated and then released when the oven door is opened. We are issuing this AD to address the unsafe condition on these products.
47-32-18: 47-32-18 BELLANCA: (Was Service Note 1 of AD-773-5.) Applies to Models 14-13, 14-13-2 Serial Numbers 1075, and Up. Compliance required prior to October 15, 1947, and after each 25 hours of operation. Remove the washer and cotter pin from the clevis bolt which holds on the aileron idler sprocket located at the top center of the control yoke and back off the sprocket. Lubricate the entire bearing surface of the clevis pin with oil. Reinstall sprocket and washer, and safety with new cotter pin of same type (AN 380-3-3). (Bellanca Service Bulletin No. 9 covers the same subject, and the installation of a grease fitting to avoid removing the sprocket.)
2005-18-22: The FAA adopts a new airworthiness directive (AD) for certain Raytheon Aircraft Company (Raytheon) Premier 1 390 airplanes. This AD requires you to verify minimum clearances to correct chafing conditions in the powerplant left-hand and right-hand engine installations. This AD results from reports of inadequate left-hand and right-hand engine assembly cable, wire, and hose routing clearance. We are issuing this AD to detect and correct chafing conditions in the engine installation, which could result in leaking flammable fluids near an ignition source. This failure could lead to fire damage or loss of airplane control.
76-02-08: 76-02-08 UNITED AIRCRAFT OF CANADA LIMITED: Amendment 39-2503. Applies to all PT6T-3 and PT6T-6 series turboshaft engines. Compliance required as indicated unless previously accomplished. To preclude leakage of the Sundstrand Aviation 025277 series fuel pump without the part number 5002557 injector cap and screen assembly, accomplish the following: (a) Within the next 25 hours in service after the effective date of this A.D., unless previously accomplished, inspect the fuel pump in accordance with paragraph 2 Accomplishment Instructions detailed in Pratt & Whitney Aircraft of Canada Limited Special Instruction No. 5-75 dated August 12, 1975, or approved equivalent inspection. (b) Within the next 250 hours in service after the effective date of this A.D., unless previously accomplished, install part number 5002557, injector cap and screen assembly, in accordance with paragraph 2 Accomplishment Instructions, Pratt & Whitney Aircraft of Canada Limited Engine Service BulletinNo. 5111 dated September 4, 1975 or approved equivalent alteration. The aircraft may be flown in accordance with FAR 21.197 and 21.199 to a base where the inspection or alteration can be accomplished. Upon submission of substantiating data, through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection times specified in this A.D. An equivalent alteration or inspection must be approved by the Chief, Engineering and Manufacturing Branch of the Eastern Region of the FAA. This amendment is effective February 5, 1976.
2018-12-02: We are adopting a new airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, - 114, and -115 airplanes; Model A320-211, -212, -214, and -216 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. This AD was prompted by a review of maintenance instructions for a blend repair of the snout diameter of the main beam assembly of the forward engine mount that would create an excessive gap between the bearing mono-ball and the snout. This AD requires modifying the main beam assembly of the forward engine mount. We are issuing this AD to address the unsafe condition on these products.
88-01-10 R1: 88-01-10 R1 SHORT BROTHERS: Amendment 39-5819 as amended by amendment 39-6011. Applies to Model SD3-60 series airplanes, Serial Numbers SH3601 through SH3667, certificated in any category. Compliance required as indicated, unless previously accomplished. To preclude failure of the horizontal stabilizer attach fittings, accomplish the following: A. Within the next 3 months after the effective date of this AD, inspect the interference fit bushings in each of the four horizontal stabilizer attach fittings in accordance with Shorts Service Bulletin Number SD360-55-10, dated November 1985. B. If the bushing is found to be loose in its fitting and the movement exceeds 0.005 inch, replace the fitting before further flight. C. If the bushing is found to be loose in its fitting and the movement does not exceed 0.005 inch, replace the fitting within the next 60 days. D. An 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. E. 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. 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, PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. 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. This Amendment, 39-6011, amends AD 88-01-10, Amendment 39-5819. This Amendment, 39-6011, becomes effective October 10, 1988.
64-27-04: 64-27-04 VERTOL: Amdt. 39-9 Part 39 (New) Federal Register December 5, 1964. Applies to Models H-21 and 42 Series Helicopters. Compliance required as indicated. As a result of a fatigue failure of a wood rotor blade root socket, P/N 22R1364-1, accomplish the following: (a) Conduct a daily visual inspection, using a magnifying glass of at least 8-power, of wood rotor blade root sockets, P/N 22R1364-1, with 750 or more hours' time in service as of the effective date of this AD, for cracks in the slot area between the inboard clamp bolt and the relief hole at the inboard end of the slot while supporting the rotor blade tip so that the blade does not rest on the droop stop. (b) Replace any cracked socket before further flight. (c) Within 25 hours' time in service after the effective date of this AD retire from service all wood rotor blade root sockets, P/N 22R1364-1, having 725 or more hours' time in service on the effective date of this AD. (d) Upon theaccumulation of 750 hours' time in service, retire from service all wood rotor blade root sockets, P/N 22R1364-1, having less than 725 hours' time in service on the effective date of this AD. This directive effective December 10, 1964.
64-24-05: 64-24-05 PIPER: Amdt. 826 Part 507 Federal Register October 24, 1964. Applies to Model PA-25-235 Aircraft, Serial Numbers 25-02, 25-2000 through 25-2931. Compliance required within 50 hours' time in service after the effective date of this AD unless already accomplished. Air leaks, which permit entrance of engine fumes into the cockpit, exist in the area of the fuselage right main landing gear fittings. To correct this condition, accomplish the following: Install seals, Piper Kit Number 756824 or FAA approved equivalent, at the front and rear right main landing gear fittings as indicated on the sketch on the reverse side of Piper Service Bulletin No. 221 dated August 27, 1964. (Piper Service Bulletin No. 221 dated August 27, 1964, pertains to this same subject.) This directive effective October 24, 1964.
2018-12-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracks found in the rear spar web and lower chord on the left and right wings. This AD requires repetitive detailed inspections for cracking of the rear spar web and lower chord, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
88-18-05: 88-18-05 SHORT BROTHERS, PLC: Amendment 39-5993. Applies to Model SD3-60 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent pitot tubes from becoming inoperative due to icing, which could result in erroneous airspeed and altitude indication, accomplish the following: A. Within the next 180 days after the effective date of this AD, replace pitot tubes having the code letter "Z" adjacent to the serial number with one containing a code letter other than "Z," in accordance with accomplishment instructions in Service Bulletin SD360-34-09, dated March 1984. B. An 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to Manager, Standardization Branch, ANM-113. C. 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 inspections and/or modifications required by this AD. 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, PLC, Service Representative, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. 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. This amendment, 39-5993, becomes effective September 7, 1988.