Results
78-16-08: 78-16-08 PIPER AIRCRAFT CORPORATION: Amendment 39-3223 as amended by amendment 39-3497. Applies to Model PA-32R-300 serial numbers 32R-7680001 through 32R- 7880068 inclusive; Model PA-32RT-300 serial numbers 32R-7885001 through 32R-7885207 inclusive, airplanes, certificated in all categories. Compliance is required as indicated. To prevent engine failure due to engine oil loss, accomplish the following: (a) On or before September 30, 1979, unless already accomplished, accomplish either (1) or (2): (1) Replace both engine oil coolers, Piper Part Number 16599-00 (Harrison Part number AP09AU06-01), if installed, with Piper Oil Cooler replacement kit 763-859V. (2) Modify the oil cooler system in accordance with Aircraft Metal Products STC SA3736WE dated September 27, 1978. (b) Prior to the first flight of each day and immediately after the last flight of each day, unless (a) has been accomplished: (1) Check below the nose gear wheel well for signsof fresh engine oil deposits. (2) Check the following areas of the airplane for engine oil deposits. (i) Inside surface on nose gear doors. (ii) Inside lower edge of lower cowl. (iii) Lower forward face of firewall. (iv) Aft face of nose gear strut, linkage, and tire. (v) Forward belly of fuselage. (3) If no oil leakage is evident, make appropriate maintenance record entry. (4) If oil leakage is evident and an oil cooler is determined to be leaking or contains a crack, have it replaced with a serviceable oil cooler. Refer to the appropriate Piper Service Manual for replacement instructions. Special caution is necessary during installation of the oil hoses to prevent damage to the replacement oil cooler. (c) Within the next 10 hours time in service after the effective date of this A.D. and thereafter at intervals not to exceed 10 hours time in service from the last check, unless (a) has been accomplished: (1) Insure thatthe engine oil is at normal operating temperature by conducting this check immediately after a flight or a ground run. (2) Gain access to the engine by removing the top engine cowl. (3) Check both the right and left engine oil coolers in the area of the oil hose assembly end fittings and in the area of the fluted portion at the oil cooler end tanks for cracks and oil leakage. (i) If no oil leakage or cracks are found, make appropriate maintenance record entry. (ii) If an oil cooler is determined to be leaking or contains a crack, have it replaced with a serviceable oil cooler. Refer to the appropriate Piper Service Manual for replacement instructions. Special caution is necessary during installation of the oil hoses to prevent damage to the replacement oil cooler. (d) An alternate method of compliance must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. The checks in this A.D. may be accomplished by the pilot and appropriate maintenance record entries made in accordance with FAR 91.173. Inspections and component replacements must be accomplished by a person authorized by FAR 43.3. Piper Service Bulletin 586B, dated July 24, 1978, pertains to this same subject. Amendment 39-3223 superseded Amendment 39-3106, 43 FR 4, A.D. 78-01-03. Amendment 39-3223 became effective August 11, 1978. This amendment 39-3497 becomes effective June 25, 1979.
50-52-01: 50-52-01\tHAMILTON STANDARD: Applies to All Convair Model 240 Series, Douglas DC-6 and Martin Models 202 and 202A Aircraft Equipped With Hamilton Standard 2H17 Series Blades.\n \n\tCompliance required daily until further notice.\n \n\tThere have been several cases in which a crack has been detected in Hamilton Standard 2H17 blades during routine ground inspections and recently there was a case in which a section of the blade tip shell was lost in flight requiring an unscheduled landing. In order to eliminate the possibility of other blade failures, the following precautionary measures must be taken:\n \n\t(1)\tThoroughly clean the entire surface of each blade to remove oil, grease, dirt, etc., so that an adequate inspection of the entire blade surface can be made.\n \n\t(2)\tCarefully examine visually at close range (12 inches-14 inches) and in detail, the entire surface of each blade for cracks and surface defects in accordance with Hamilton Standard Service Bulletins Nos. 177 and 193. Any suspected areas should then be more closely examined by using a suitable magnifying glass, permanent magnet or any other suitable means as required.\n \n\t(3)\tIf any cracks are found in the blade surface, it must be retired immediately from service. All doubtful cases should be referred to the propeller manufacturer.\n \n\tThis directive supplements previous Hamilton Standard information on the same subject to all affected operators.
80-13-05 R1: 80-13-05 R1 ROLLS-ROYCE, LTD: Amendment 39-3804 as amended by Amendment 39-4742. Applies to Rolls-Royce RB211-22B turbofan engines. Compliance required as indicated, unless already accomplished. To preclude possible high pressure compressor (HPC) rotor stage 1 and 2 disk assembly failure, remove from service all HPC rotor stage 1 and 2 disk assemblies, listed by part number and serial number in Appendices 1 and 2 of Rolls-Royce Alert Service Bulletin No. RB211-72-A5722, Revision 3, dated April 17, 1981, in accordance with the following compliance schedule: 1. For disk assemblies listed in Appendix 1: a. After July 31, 1980, no disk assemblies may exceed 7,000 flight cycles. b. After December 31, 1980, no disk assemblies may exceed 6,000 flight cycles. c. All remaining disk assemblies by April 30, 1981. 2. For disk assemblies listed in Appendix 2: a. After the effective date of this amendment, no disk assemblies may exceed 9,000 flight cycles. NOTE: For the purpose of this AD, a flight cycle is considered to be an engine operating sequence from takeoff to landing. Replace with an FAA-approved, serviceable HPC rotor stage 1 and 2 disk assembly. The manufacturer's Alert Service Bulletin identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a). All persons affected by this directive who have not already received the service bulletin from the manufacturer may obtain copies upon request to Technical Publications Department, Rolls-Royce, Ltd., Derby, England DE2 8BJ. The service bulletin may also be examined at Federal Aviation Administration, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, Massachusetts. Amendment 39-3804 became effective upon publication in the Federal Register. This Amendment 39-4742 becomes effective November 28, 1983.
60-02-04: 60-02-04\tBOEING: Amdt. 86 Part 507 Federal Register January 21, 1960. Applies to the following Model 707 Series aircraft only: Serial Numbers 17586 through 17591, 17609 through 17612, 17628 through 17652, 17658 through 17672, 17691, 17696 through 17702, 17925 through 17927. \n\n\tTo increase the capabilities and reliability of the Mach trim warning lights and the Mach warning and fire warning bell systems the following modification(s) shall be accomplished as indicated: \n\n\tUnless already completed, the following shall be accomplished by April 30, 1960. \n\n\t(a)\tRemove Mach and fire warning bell support bracket, Boeing P/N 69-1640, from below flight engineer's table and rework to accept redesigned warning bell assembly Boeing P/N 69-50013 or equivalent. Install reworked bracket and redesigned components as shown in Boeing Drawing 65-2801. (Boeing Service Bulletin No. 444 pertains to this same subject.) \n\n\t(b)\tInstall two diodes, Boeing assembly 69-43070-6, in the Mach trim systemresistor box and revise the indicating light circuitry such that this light will indicate when the system is not turned on as well as indicating Mach trim system malfunctions. (Boeing Service Bulletin No. 474 (R-1) describes a satisfactory modification.)
99-11-01: This amendment adopts a new airworthiness directive (AD) that is applicable to all EMBRAER Model EMB-145 series airplanes. This action requires repetitive replacement of the bleed-air check valve and associated gaskets on the bleed low-pressure line of the engine, with new parts. 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 prevent failure of the bleed-air check valve on the bleed low-pressure line of the engine. Such failure could result in engine compressor stall and consequent flameout of the affected engine.
2008-06-16: 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: DCA/750XL/3A is prompted by a report from the manufacturer of the possibility that wiring loom protective sleeving is not fitted to aircraft S/N 107 through to 134. AD applicability revised to include aircraft up to S/N 134. To prevent fretting damage to the wiring loom that may lead to arcing in proximity to the fuel vent lines and the possibility of fire * * *. We are issuing this AD to require actions to correct the unsafe condition on these products.
92-06-10: 92-06-10 SOCATA GROUPE AEROSPATIALE: Amendment 39-8190; Docket No. 91-CE-81-AD. Applicability: Morane Saulnier Models MS892A150, MS892E150, MS893A, MS893E, MS894A, and MS894E airplanes (all serial numbers); and Rallye Models 235C and 235E airplanes (all serial numbers), certificated in any category. Compliance: Required initially upon the accumulation of 500 hours time-in-service (TIS) or within the next 50 hours TIS after the effective date of this AD, whichever occurs later, and thereafter as indicated, unless already accomplished. To prevent nose wheel axle fatigue failure, accomplish the following: (a) Dye penetrant inspect the nose wheel axle assembly for cracks in accordance with the instructions in DESCRIPTION: 1) of SOCATA Groupe AEROSPATIALE Service Bulletin No. 150, dated June 1991. (1) If cracks are found, prior to further flight, replace the nose wheel axle assembly in accordance with the applicable maintenance manual, and reinspect thereafterat intervals not to exceed 500 hours TIS. (2) If no cracks are found, reinspect thereafter at intervals not to exceed 500 hours TIS. (b) At every 4th repetitive inspection interval (2,000 hours TIS) mandated in paragraphs (a)(1) and (a)(2) of this AD, replace the nose wheel axle attaching screws instead of reinstalling the existing screws as specified in the instructions of DESCRIPTION: 2) of SOCATA Groupe AEROSPATIALE SB No. 150, dated June 1991. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety, may be approved by the Manager, Brussels Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. 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. (e) The inspections and replacements required by this AD shall be done in accordance with SOCATA Groupe AEROSPATIALE Service Bulletin No. 150, dated June 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from SOCATA Groupe AEROSPATIALE, Socata Product Support, Aeroport Tarbes-Ossun-Lourdes, B P 930, 65009 Tarbes Cedex, France. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (f) This amendment (39-8190) becomes effective on April 17, 1992.
2020-06-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, - 113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, - 131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a report of cracking found on the frame of the right-hand side sliding window in the flight deck. This AD requires repetitive inspections for cracking of the vertical stiffeners of the left- and right-hand sides of the window frames and corrective actions if necessary, 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.
2020-06-11: The FAA is adopting a new airworthiness directive (AD) for MD Helicopters Inc. (MDHI) Model 600N helicopters. This AD requires establishing a life limit for the main rotor (M/R) blade upper control collective/longitudinal link assembly (link assembly). This AD was prompted by the discovery that the life limit was omitted from the maintenance manual. The actions of this AD are intended to prevent an unsafe condition on these products.
82-10-03: 82-10-03 BOEING: Amendment 39-4375. Applies to Boeing Model 727 airplanes, line number 1 through 1612, certificated in all categories. Compliance is required within the next 2500 hours time-in-service from the effective date of this AD, unless already accomplished. To minimize the possibility of cross-connecting the ground spoiler hydraulic tube assemblies, accomplish either one of the following, unless already accomplished: \n\n\tA.\tReplace the ground spoiler hydraulic tube assemblies per figure 1 of Boeing Service Bulletin 727-27-202, Revision 1, dated December 18, 1981, or later revisions approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. \n\n\tB.\tColor code the ground spoiler hydraulic tube assemblies per figure 2 of the same bulletin. \n\n\tAlternate means of compliance with the AD which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. \n\n\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 June 11, 1982.