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82-09-01: 82-09-01 TELEDYNE CONTINENTAL MOTORS: Amendment 39-4412. Applies to the following engines installed in, but not limited to, Cessna Models 340 and 414 series airplanes: NEW ENGINES: TSIO-520-NB serial numbers 519735 thru 519738, 519781 thru 519785, 519885 thru 519890, 519893 thru 519897, 519899 through 519915, 519929 thru 519933, 519935 thru 519937, 519939 thru 519962, 521026 thru 521045, 521049 thru 521074, 521085 thru 521088, 521097, 521141 thru 521168, 521170 thru 521183, 521187 thru 521237, 521239 thru 521247, 521249 thru 521255, 521257, 521258, 521260 thru 521281, 521284 thru 521305, 521307 thru 521335, 521339, 521340, 521342 thru 521345, 521347, 521349, 521351, 521353, 521354, 521357, 521358, 521362, 521365, 521366, 521371, 521378, 521384, 521385, 521393, 521395, 521398, 521413 thru 521418, 521441, 521442, 521455, 521461. REBUILT ENGINES: TSIO-520-J serial numbers 218830, 218831, 218836, 218838 thru 218873; TSIO- 520-K serial numbers 224563, 224565 thru 224573; TSIO-520-N serial numbers 228231, 228243, 228248 thru 228250, 228255, 228262 thru 228363, 228365 thru 228368, 228373; TSIO-520-NB serial numbers 233976, 233982, 233986, 233987, 233989 thru 234058, 234060 thru 234069, 234071 thru 234074, 234077, 234078. Compliance is required as indicated unless already accomplished. To prevent the possibility of a fuel leak which could result in an engine compartment fire, accomplish the following: A. Prior to next flight, activate the boost pump to static check the fuel pressure regulator inlet and outlet for leaks. Visually inspect in the area of the fuel pressure regulator for the presence of fuel stains. If either inspection indicates a leak or stains, comply with Paragraph B before further flight. If no leak or stain is evident, comply with Paragraph B within the next 10 hours of operation. B. Remove the fuel fittings from the regulator and inspect the thread bores in the regulator and the threads of the fittings. If the threads in the regulator appear damaged, cut, or chipped (when compared to a normal pipe thread), replace the fuel pressure regulator with a serviceable regulator of a like part number. Replace any damaged fittings. Prior to installing the fittings, clean the threads with clean degreaser, Loctite "LOQUIC PRIMER T" or equivalent, to be sure all oil and dirt is removed. Blow dry with dry compressed air. Apply Loctite Hydraulic Sealant 69 or 569 or equivalent sparingly 3/4 of the way around on the fitting threads only. To avoid contamination of the fuel cavity, do not apply sealant to the first thread. Install the fittings until tight (at least 3-5 threads engagement). Allow sealant to cure for 30 minutes before pressure testing. NOTE: Teledyne Continental Motors Service Bulletin No. M82-5, dated April 26, 1982, pertains to this subject. An equivalent method of compliance may be approved by the Chief, Atlanta Aircraft Certification Office, Federal Aviation Administration, ACE-115A, P.O. Box 20636, Atlanta, Georgia 30320. This amendment becomes effective July 8, 1982, as to all persons except those to whom it was made immediately effective by priority mail, issued April 16, 1982.
65-12-03: 65-12-03 MOONEY: Amdt. 39-74 Part 39 Federal Register May 28, 1965. Applies to Model M20E Aircraft, Serial Numbers 101 through 722 Equipped with Hartzell Propeller, HC-C2YK/7666-2 or CHC-C2YK/7666-2. Compliance required within the next 25 hours' time in service after the effective date of this AD unless already accomplished. To avoid continuous propeller operation in the speed range where vibration stresses are high, accomplish the following: (a) Add the following operating limitation to the Airplane Flight Manual: "Avoid continuous operation between 2,100 and 2,350 r.p.m." (b) Mark engine tachometer with a red arc from 2,100 to 2,350 r.p.m., install Mooney decal P/N 150010-65, on tachometer bezel glass in accordance with Mooney Service Letter No. 21-127, dated April 15, 1965. This directive effective May 28, 1965.
2016-14-02: We are superseding Airworthiness Directive (AD) 2012-18-12 for certain Airbus Model A318, A319, and A320 series airplanes. AD 2012-18- 12 required modifying the off-wing escape slide (OWS) enclosures on the left-hand (LH) side and right-hand (RH) side of the fuselage. This new AD retains the requirements of AD 2012-18-12 and expands the applicability to all Airbus Model A318, A319, and A320 series airplanes. This AD was prompted by reports that additional OWS part numbers have been affected. We are issuing this AD to prevent off-wing exits on the LH and RH sides of the fuselage from becoming inoperative. During an emergency, inoperative off-wing exits could impair the safe evacuation of occupants, possibly resulting in personal injuries.
71-05-01: 71-05-01 SIKORSKY: Amdt. 39-1157. Applies to S-61 Type Helicopters Certified in all Categories. Compliance required as follows: To preclude the possibility of failure of the S-61 Main Landing Gear Axle, P/N 6125-50115-0, unless already accomplished, inspect and replace the axle in accordance with paragraph 2, Accomplishment Instructions of Sikorsky Service Bulletin 61B25-3 dated 15 January 1971 or later FAA-approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Report results of above inspection in compliance with this AD to Chief, Engineering and Manufacturing Branch, FAA, Eastern Region (Reporting Approved by Bureau of the Budget under BOB No. 04-R0174.) Replacement axle P/N S6125-50115-2 has a service life of 242,550 landings. This amendment is effective February 23, 1971.
2004-02-03: This amendment adopts a new airworthiness directive (AD) for the specified Agusta S.p.A. (Agusta) model helicopters that requires modifying each passenger compartment sliding door (door) by applying a kit to replace the levers and links. This amendment is prompted by instances of a door inadvertently opening during flight due to the unstable configuration of the door. The actions specified by this AD are intended to prevent the inadvertent opening of a door during flight and loss of a passenger or other objects from the cabin.
2016-14-06: We are superseding Airworthiness Directive (AD) 2006-13-05 for certain Pacific Aerospace Limited Model 750XL (type certificate previously held by Pacific Aerospace Corporation Ltd.) airplanes. 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 some critical rivets on the wing not being fully age-hardened and being installed in specific locations where reduction in rivet strength reduces wing strength. We are issuing this AD to require actions to address the unsafe condition on these products.
56-26-01: 56-26-01 LOCKHEED: Applies to Super Constellation 1049 Series Aircraft, LAC Serial Numbers 4501 Through 4565, 4572 Through 4647 and 4163 Through 4166. Compliance required as soon as possible but not later than the next block overhaul or major inspection period after parts become available. The relays housed within the generator feeder protection main relay box have been found capable of overheating at high generator output. This could become excessive when one or more generators become inoperative. This box contains the main DC bus, which is the tie-point of all primary electric power for the airplane. To minimize the probability of complete electrical outage in this vital area, greater heat transfer capability shall be provided either by installing a blower and replacing the existing interconnecting bus bars with new bus bars having increased cooling areas, or by an equivalent means approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. (Lockheed 1049 Service Bulletin No. 2838, dated August 20, 1956, contains FAA- approved rework information for compliance with this AD.) This airworthiness directive does not apply to aircraft equipped with two 11 KVA alternators. Revised July 25, 1962.
82-06-09: 82-06-09 CANADAIR: Amendment 39-4347. Applies to Canadair CL-600-1A11 airplanes, Serial Numbers 1002 and on, certificated in all categories. To prevent collapse of the landing gear caused by loss of the side stay strut reaction point, accomplish the following: 1. Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, visually inspect the right and left hand main landing gear side stay attachment pins for cracked or missing locking pins Dowty Rotol part number 200809689. Cracked or missing locking pins must be replaced with MS20392-1C41 Pin, Straight, Headed- Drilled Shank; MS24665-132 Pin, Cotter (Split); and AN960-6L Washer, prior to further flight. 2. Within the next 50 hours time in service after the effective date of this AD, Dowty Rotol part number 20080689 locking pins in the right and left hand main landing gear side stay attachment must be replaced with MS20392-1C41 Pin, Straight, Headed-Drilled Shank; MS24655-132 Pin, Cotter (Split); and AN960-6L Washer. After replacement, these locking pins must be visually inspected for cracks at intervals not to exceed 150 hours time in service. 3. The repetitive inspections of paragraph 2 may be discontinued upon the incorporation of an installation approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 4. Equivalent inspections and parts must be approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 5. Airplanes may be flown in accordance with FAR 21.197 to a maintenance base for the accomplishment of the inspections required by this AD. 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 the addresses listed above. These documents may also be examined at the FAA Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective March 22, 1982.
2024-10-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-800 and A330-900 series airplanes. This AD was prompted by a report of a protective cap found still in place on the drain hole of a fire extinguishing pipe, and by further investigations indicating these caps may have remained on other airplanes. This AD requires a one-time general visual inspection (GVI) of the engine fire extinguishing pipe drain hole and, depending on findings, removal of the protective cap, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2016-14-05: We are superseding Airworthiness Directive (AD) 2008-15-06 for certain Textron Aviation Inc. Models 175 and 175A airplanes (type certificate previously held by Cessna Aircraft Company). AD 2008-15-06 required checking the airplane logbook to determine if the original engine mounting brackets had been replaced. If the original engine mounting brackets were still installed, the AD required repetitively inspecting those brackets for cracks and replacing any cracked engine mounting bracket until all four original engine mounting brackets were replaced. Replacing all four original engine mounting brackets terminated the actions required in AD 2008-15-06. Since we issued AD 2008-15-06, we have determined that the applicability needs to be changed to add one serial number and remove another. This new AD retains the actions required in AD 2008-15-06 and changes the Applicability section. We are issuing this AD to correct the unsafe condition on these products.