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90-15-13: 90-15-13 MITSUBISHI HEAVY INDUSTRIES, LTD (formerly Nihon Aeroplane Manufacturing Company, NAMC): Amendment 39-6657. Docket No. 90-NM-29-AD. Applicability: Model YS-11 and YS-11A series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent incidents of propellers failing to withdraw, accomplish the following: A. Within 1,000 flight hours after the effective date of this AD: 1. Inspect the propeller high stop withdrawal relay in accordance with the accomplishment instructions of Mitsubishi NAMC YS-11 Service Bulletin 61-5, dated December 20, 1988. If any abnormality is detected, replace the relay prior to further flight. 2. Install Decal 01-81717-27 in accordance with Mitsubishi NAMC YS-11 Service Bulletin 15-27, dated December 20. 1988. B. Repeat the inspection of the propeller high stop withdrawal relay at intervals not to exceed 3,000 flight hours after the initial inspection orafter replacement, in accordance with Mitsubishi NAMC YS-11 Service Bulletin 61-5, dated December 20, 1988. If any abnormality is detected, replace the relay prior to further flight. C. Special 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. D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used if approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Los Angeles ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Los Angeles ACO. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to NagoyaAircraft Works Mitsubishi Heavy Industries, Ltd., 10 Oye-cho, Minato-Ku, Nagoya 455, Japan; Attention: K. Saitoh, Manager, YS- 11 Group, Service Department. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. This amendment (39-6657, AD 90-15-13) becomes effective on August 20, 1990.
69-24-03: 69-24-03 MARVEL-SCHEBLER: Amdt. 39-881. Applies to Marvel Schebler Models MA-3-A, MA-3-PA, MA-3-SPA, MA-4-SPA, MA-4-5, MA-5, MA-4-5-AA, MA-6AA, and HA-6 carburetors of the following listed part numbers and serial numbers installed on the Continental, Franklin and Lycoming model engines as specified below, to wit: ENGINE MANUFACTURER & MODEL CARBURETOR MODEL CARBURETOR PART NUMBER CARBURETOR SERIAL NUMBERS CONTINENTAL A-65 & A-75 Series MA-3-PA A-10-4233 P-22-460 thru P-22-464 O-200 Series MA-3-SPA A10-4115-1 AV-4-4094 O-200 Series MA-3-SPA A10-4894 BE-14-10218 thru BE-15-11672 C-85 Series MA-3-SPA A10-4240 AU-15-235 thru AU-15-244 C-90 Series MA-3-SPA A10-4252 Q-23-2422 thru Q-23-2436 C-145 Series MA-3-SPA A10-4895 BF-14-3598 thru BF-15-3655 O-470-K MA-4-5 A10-3965-12 H-3-6894 thru H-3-6896 O-470-R MA-4-5 A10-4893 BD-13-3946 thru BD-15-4660 FRANKLIN 4A-235 Series MA-3-SPA A10-4654 BN-3-112 thru BN-3-130 GA-335 Series MA-5 A10-4865 BC-14-530 thru BC-16-706 6V-350 Series MA-5 A10-4809 BA-14-203 thru BA-14-207 6A-350 Series MA-5 A10-4865 BC-14-530 thru BC-16-706 LYCOMING O-235 Series MA-3-A A10-3103-1 Y-30-3132 thru Y-30-3275 O-235 Series MA-3-A A10-4953 BV-0-268 thru BV-0-538 O-235 Series MA-3-PA A10-4978-1 BQ-3-252 thru BQ-3-276 O-235 Series MA-3-PA A10-5050 BY-0-100 thru BY-1-291 O-290 Series MA-3-SPA A10-3346-1 B-35-342 thru B-36-359 O-320 Series MA-4-SPA A10-3678-32 A-25-14781 thru A-26-16246 O-320 Series MA-4-SPA A10-5009 BL-5-2632 thru BL-5-3435 O-360 Series MA-4-5 A10-3878 G-34-4651 thru G-36-5362 O-360 Series MA-4-5 A10-4164-1 K-27-6460 thru K-27-6602 O-360 Series MA-4-5 A10-5034 BU-0-283 thru BU-0-383 O-360 Series HA-6 A10-5045 BW-0-198 thru BW-4-550 VO-435 Series MA-4-5-AA A10-4025-12 Z-16-2304 thru Z-18-2434 TVO-435 Series MA-6-AA A10-4438-1 AH-19-3676 thru AH-21-4067 O-540 Series MA-4-5 A10-4404 R-24-6530 thru R-26-6916 O-540 Series MA-4-5 A10-4404-1 AO-20-3571 thru AO-23-3829 O-540 Series MA-4-5 A10-5042 BS-1-427 thru BS-1-588 O-540 Series MA-4-5 A10-5054 BZ-0-100 thru BZ-0-209 VO-540 Series MA-6-AA A10-4218-1 AK-17-1274 thru AK-19-1478 VO-540 Series MA-6-AA A10-4975 BK-2-125 thru BK-3-148 NOTE: The affected carburetors listed above were manufactured between December 5, 1968, and June 23, 1969. Approximately 25% of these carburetors have been inspected and cleaned by Marvel Schebler or the manufacturers of the engines or aircraft on which the carburetors are installed. Marvel Schebler Service Bulletin A1-69 lists the carburetors remaining to be inspected and covers the same subject matter as this AD. Any carburetor serial numbers included in this AD but not listed on Marvel Schebler Service Bulletin A1-69 comply with this AD, and require no further inspection or cleaning. A logbook entry of compliance and nameplate marking must be made on these unlisted carburetors. The "A" prefix to the part numbers listed above does not appear on the carburetor nameplate. Compliance: Required within the next 25 hours' time in service after the effective date of this AD, unless previously accomplished. To prevent possible power losses due to blockage of carburetor metering passeges by thread lubricant or other foreign material, accomplish the following or an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, or Chief, Engineering and Manufacturing Branch, FAA, Eastern Region: Remove the carburetor bowl drain plug with the aircraft fuel valve in the "ON" position and allow the carburetor to flush for 20 to 30 seconds. The auxiliary pump, if installed, should be operating. After flushing, inspect the drain plug cavity and drain plug for thread lubricant or other foreign material and remove any such material noted. After cleaning, reflush 20 to 30 seconds, reinstall plug approximately one thread into cavity, apply Parker Seal Lube or equivalent on exposed threads and tighten. NOTE: If practical, aircraft should be positioned so that bottom of bowl slopes toward drain opening during flushing and cleaning. Recommended torque for 1/8" pipe plug is 50-60 in. lbs., for 1/4" pipe plug is 120-144 in. lbs. After completion of the above, impression stamp or engrave "A1" on a nameplate or apply approximately 1/4-inch diameter dot of yellow enamel or similar permanent material to nameplate. This amendment becomes effective November 29, 1969.
2009-21-07: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-80C2 series turbofan engines with certain thrust reverser ballscrew gearbox assembly adjustable-length end actuators installed. This AD requires initial visual inspections and repetitive replacements of the 3/8-inch rod-ends installed on the thrust reverser ballscrew gearbox assembly adjustable-length end actuators. This AD also allows an optional terminating action to those repetitive replacements. This AD also requires initial visual inspections and replacements, if necessary, of the other hardware connecting the thrust reverser transcowls to the engine. This AD results from reports of four failures of rod-ends on certain thrust reverser ballscrew gearbox assembly adjustable-length end actuators, leading to partial or complete separation of the transcowl from the engine and airplane during thrust reversal. We are issuing this AD to prevent asymmetric thrust and loss of thrust control.
97-15-04: This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 214B, 214B-1, and 214ST helicopters, that currently establishes a mandatory retirement life of 60,000 high-power events for the main transmission upper planetary carrier (carrier). This amendment requires changing the method of calculating retirement life for the carrier from high-power events to a maximum accumulated Retirement Index Number (RIN) of 120,000. This amendment is prompted by fatigue analyses and tests that show certain carriers fail sooner than originally anticipated because of the unanticipated high number of lifts or takeoffs (torque events) performed with those carriers in addition to the time-in-service (TIS) accrued under other operating conditions. The actions specified by this AD are intended to prevent fatigue failure of the carrier, which could result in failure of the main transmission and subsequent loss of control of the helicopter.
91-12-06: 91-12-06 GROB LUFT UND RAUMFAHRT: Amendment 39-7017. Docket No. 91- CE-05-AD. Applicability: Model G 109B motor gliders (serial numbers 6200 through 6362), certificated in any category. Compliance: Required within the next 3 calendar months after the effective date of this AD, unless already accomplished. To prevent separation of the studs in the root rib stud plate that could result in loss of the aileron and airbrake control systems, accomplish the following: (a) Inspect the security of the studs in the root rib stud plate (part number 109B- 4108) in accordance with the instructions in GROB Service Bulletin No. TM-817-29, dated August 6, 1990. If any loose studs are found, prior to further flight, repair the stud plate in accordance with the instructions in the referenced SB. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the motor glider to a location where the requirements of this AD can be accomplished.(c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B- 1000 Brussels, Belgium; Telephone (322) 513.38.30. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (d) All persons affected by this directive may obtain copies of the document discussed in this AD upon request to GROB Luft und Raumfahrt, D-8939 Mattsies, Federal Republic of Germany; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-7017, AD 91-12-06) becomes effective on July 5, 1991.
2009-24-05: We are adopting a new airworthiness directive (AD) for the products listed above. 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: Under certain ambient conditions, ice can accumulate on the walls of the fuel pipes within the aircraft fuel system, which can then be released downstream when fuel flow demand is increased. This released ice can then collect on the fuel-to-oil heat exchanger (FOHE) front face and limit fuel flow through the FOHE. We are issuing this AD to prevent ice from blocking the FOHE, which could result in an unacceptable engine power loss, and loss of control of the airplane.
77-14-05: 77-14-05 BRITISH AIRCRAFT CORPORATION: Amendment 39-2953. Applies to BAC 1- 11 200 and 400 series airplanes, certificated in all categories, with Garrett AiResearch Models GTCP 85-115, -115C or -115CK APU's installed, that do not have British Aircraft Corporation Modification PM 5217 incorporated. Compliance is required as indicated. To prevent excessive fuel contamination of the Auxiliary Power Unit oil contents, accomplish the following: (a) Within the next 60 APU hours' time in service after the effective date of this AD, unless accomplished within the last 20 APU hours' time in service, and thereafter at intervals not to exceed 80 APU hours' time in service from the last inspection, inspect for fuel leakage in accordance with paragraph 2.1 of the Accomplishment Instructions of British Aircraft Corporation Model BAC 1-11 Service Bulletin 49-PM 5217, or an FAA-approved equivalent. (b) If the fuel leakage rate exceeds one drop per minute, prior to further use of the APU, rectify the leakage, drain and refill the oil system with fresh oil, and thereafter continue the inspections required by paragraph (a) of this AD. (c) Upon the request of an operator, the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, APO New York, N.Y. 09667, may adjust the repetitive inspection intervals specified in paragraph (a) of this AD if the request contains substantiating data to justify the change. This amendment becomes effective August 5, 1977.
98-15-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111 and -211 series airplanes. This action requires repetitive inspections to detect fatigue cracking of the frames of the sliding windows in the cockpit, and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct fatigue cracking of the frames of the sliding windows in the cockpit, which could result in reduced structural integrity of the pressure vessel of the fuselage of the airplane.
2009-26-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: It has been found the occurrence of engine anti-ice system valve failure, where the valve spring seat has broken and obstructed the anti-ice system venturi tube. * * * Therefore, should the aircraft encounter icing conditions, ice may accrete in the engine inlet lip and be ingested through the air inlet, resulting in possible engine damage and flame-out. We are issuing this AD to require actions to correct the unsafe condition on these products.
97-19-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes, that currently requires revising the Limitations Section of the Airplane Flight Manual (AFM) to provide the flight crew with procedures to check the travel range of the aileron. That AD also requires inspection for damage of the shear pins of the aileron flutter damper and aileron hinge fittings, and various follow-on actions. This amendment adds a requirement for accomplishment of an installation that eliminates the need for the AFM revision. This amendment also adds airplanes to the applicability of the existing AD. This amendment is prompted by reports of failure of shear pins in the aileron flutter damper. The actions specified by this AD are intended to prevent damage to the aileron hinge fittings due to failed shear pins, and consequent reduced controllability of the airplane.