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69-15-03: 69-15-03 CESSNA: Amendment 39-798. Applies to all Cessna Model 170, 172, and 175 series airplanes modified in accordance with Supplemental Type Certificates SA3-13, SA3-126, SA3-571, SA3-672, SA3-674, SA135CE, SA420CE, SA421CE, or SA424CE, incorporating a Piper Muffler Assembly, P/N 10308-00, with the installation of a Lycoming engine. Compliance required as indicated. To detect cracks in the muffler assembly, accomplish the following: (a) Inspect muffler assemblies with less than 950 hours' time in service on the effective date of this AD, in accordance with paragraph (c) below within the next 50 hours' time in service and thereafter at intervals not to exceed 100 hours' time in service from the last inspection until accumulating 950 hours' time in service, then comply with paragraph (b) below. (b) Inspect muffler assemblies with more than 950 hours' time in service on the effective date of this AD, in accordance with paragraph (c) below within the next 50 hours' time in service and thereafter at intervals not to exceed 50 hours' time in service from the last inspection. (c) Inspect the engine exhaust muffler and shroud assembly (including the internal baffle tube and tail pipe), carburetor heat shroud and air duct, support braces, clamps and brackets, exhaust stacks and manifolds. Remove muffler assembly, disconnect air ducts, stacks, and shrouds as necessary, and visually inspect exterior and interior surfaces with a probe light and mirror for signs of cracks, corrosion, burn-throughs, heat damage, collapsed stack, or weld separations. Special attention should be given to the exhaust stack under the carburetor heat shroud. Except for the initial inspection, the muffler assembly need not be removed from the airplane if the shroud is opened for inspection of external portions of the muffler and the internal portions are inspected through the muffler tail pipe outlet and one end of the muffler at the stack connection. CAUTION:Do not alter these mufflers to remove the internal baffle tube without prior FAA approval. (Piper Service Letter No. 324B describes the critical areas.) (d) Replace or repair parts having any of the defects listed in paragraph (c) before further flight, and thereafter comply with the inspection requirements of paragraph (a) or (b), whichever is applicable. Make welding repairs and pressure test in accordance with Advisory Circular AC 43.13-1 or an FAA approved equivalent. Care should be exercised when reinstalling the exhaust system components to prevent distortion or preloading of parts. This amendment becomes effective August 20, 1969.
47-51-13: 47-51-13 BELLANCA: Applies to Model 14-13 Serial Numbers 1060 Through 1513, 1545, 1548, 1551 Through 1560. Compliance required not later than May 1, 1948. To eliminate the possibility of an engine compartment fire entering the fuselage through the firewall cabin heater opening, remove the aluminum cabin heat control valve and replace with a steel valve of new design Bellanca Drawing No. 15067-40. (Bellanca Service Bulletin No. 11 dated June 20, 1947, covers this same subject.)
77-07-01: 77-07-01 HUGHES HELICOPTERS: Amendment 39-2859. Applies to Hughes Model 269 series helicopters certificated in all categories, incorporating belt drive clutch linear actuator assemblies (hereinafter referred to as the "clutch actuator") P/N's DL1020-M81C (12V), DL1020-MS82C (24V), DL1020M48, and 269A4564. Compliance required as indicated, unless already accomplished. To detect possible cracks in belt drive clutch aluminum actuating shaft and actuator attachment fixed end fittings which can cause separation of the actuator attachment resulting in declutching of the main rotor, accomplish the following: (a) Within 10 days after the effective date of this AD, prior to the first flight each day, conduct a visual check of the clutch actuator in accordance with the procedures described in Part II of Hughes Service Information Notice N-141.1 dated March 8, 1977, or later FAA approved revision. If any indication of cracks, corrosion or deformation is observed, perform a dyepenetrant inspection of the suspect areas per Part III of above referenced service notice. Before further flight, replace any defective clutch actuator with a serviceable unit. (b) The daily visual check required by paragraph (a) of this AD may be performed by the pilot. (c) Within the next 100 hours time in service after the effective date of this AD, and at intervals not to exceed 100 hours time in service thereafter, perform a dye penetrant inspection of the clutch actuator per Part III of Hughes Service Information Notice N-141.1 dated March 8, 1977, or later FAA-approved revision. Before further flight, replace any defective clutch actuator with a serviceable part. (d) When the clutch actuator is modified to, or replaced with, an actuator incorporating the stainless steel parts as described in Part I of Hughes Service Information Notice N-141.1, dated March 8, 1977, or later FAA approved revision, the visual checks required by paragraph (a) and the dye penetrant inspection required by paragraph (c) may be discontinued. (e) Equivalent checks, inspections and modification procedures for the clutch actuator may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. (f) Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate helicopters to a base for accomplishment of the 100 hour inspections required by paragraph (c) of this AD. (g) Record the daily visual check required by this AD in the rotorcraft maintenance record in accordance with FAR 91.173. This amendment becomes effective April 4, 1977.
98-01-01: 98-01-01 CESSNA AIRCRAFT COMPANY: Priority Letter issued on December 22, 1997. Docket No. 97-CE-150-AD. Applicability: The following airplane models and serial numbers, certificated in any category: Model 172R Airplanes: serial numbers 17280003 through 17280171, 17280173 through 17280175, 17280177 through 17280179, 17280182 through 17280184, 17280186, 17280189, 17280190, 17280192 through 17280212, 17280214, 17280216 through 17280221, 17280223 through 17280236, 17280239 through 17280251, 17280253 through 17280263, 17280265, 17280268, 17280270 through 17280272, 17280283, 17280297, and 17280301; and Model 182S Airplanes: serial numbers 18280001, 1820002, 18280004 through 18280045, 18280048 through 18280060, 1820062 through 18280064, 18280067, and 18280070. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (h) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated in the body of this priority letter AD, unless already accomplished. To prevent erroneous indications from the altimeter, airspeed, and vertical speed indicators, which could cause the pilot to react to incorrect flight information and possibly result in loss of control of the airplane, accomplish the following: (a) Prior to further flight after receipt of this priority letter AD, fabricate placards with the following words, using letters at least 1/8-inch in height, and install these placards in the cockpit within the pilot s clear view: (1) "IFR operation is prohibited." (2) "Use of the alternate static air source is prohibited." (b) Within the next 100 hours time-in-service (TIS) after receipt of this priority letter AD or within the next 4 calendar months after receipt of this priority letter AD, whichever occurs first, inspect the alternate static air source valve to assure that the alternate static air source valve is not restricted by the identification placard and to assure that the valve body does not separate from the valve flange in accordance with Cessna Service Bulletin No. SB97-34-02, Revision 1, dated December 22, 1997. (1) If the alternate static air source valve is restricted, prior to further flight after the inspection required by paragraph (b) of this AD, rework the alternate static air source assembly in accordance with Cessna Service Bulletin No. SB97-34-02, Revision 1,dated December 22, 1997. (2) If the valve body separates from the valve flange, replace the alternate static air source assembly in accordance with the maintenance manual at one of the compliance times presented below (paragraph (b)(2)(i) or (b)(2)(ii) of this AD): (i) Prior to further flight to eliminate the operating limitations required by the placards in paragraphs (a), (a)(1), and (a)(2) of this AD; or (ii) Within the next 25 hours TIS after the inspection provided the operating limitations required by the placards in paragraphs (a), (a)(1), and (a)(2) of this AD are adhered to. (c) The placard requirements of paragraphs (a), (a)(1), and (a)(2) of this AD may be eliminated when the inspection, rework, and replacement requirements are accomplished as specified in paragraphs (b), (b)(1), and (b)(2) of this AD. (d) The inspection, rework, and replacement requirements specified in paragraphs (b), (b)(1), and (b)(2) of this AD may be accomplished at any time prior to "within the next 100 hours TIS after receipt of this priority letter AD or within the next 4 calendar months after receipt of this priority letter AD, whichever occurs first." (e) Within 10 days after the inspection required by paragraph (b) of this AD, send the results of the inspection in writing to the FAA at the address specified in paragraph (h) of this. Include the serial number of the airplane and state whether the alternate static air source assembly needed to be reworked or replaced. (Reporting approved by the Office of Management and Budget under OMB No. 2120-0056). (f) Fabricating and installing the placards as required by paragraph (a) of this AD may be performed by the owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7), and must be entered into the aircraft records showing compliance with this AD in accordance with section 43.9 of the Federal Aviation Regulations (14CFR 43.9). (g) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (h) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (i) Copies of the applicable service information may be obtained from the Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 941-5800; facsimile: (316) 942-9006. This information may also be examined at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (j) Priority Letter AD 98-01-01, issued December 22, 1997, becomes effective immediately upon receipt.
48-12-05: 48-12-05 BELL: Applies to Models 47B Series and 47D. Compliance required at next 100-hour teardown inspection if less than 600 hours have been accumulated. (If over 600 hours have been accumulated, this change must be accomplished immediately.) Replace the dural shear screws in the transmission spider assembly with steel shear screws (P/N 47-620-485-1). (Bell Service Bulletin No. 47C66, revised February 10, 1948, also covers this same subject.)
2012-07-08: We are superseding an existing airworthiness directive (AD) for all EMBRAER Model ERJ 170 airplanes. That AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) to incorporate new structural inspection requirements. Since we issued that AD, during full scale fatigue testing, cracks were found in certain structural components of the airplane. Analysis of these cracks resulted in the manufacturer modifying the ALS of EMBRAER 170 Maintenance Review Board Report (MRBR), to include new inspections tasks, or modifying the current tasks and their respective thresholds and intervals. This new AD requires revising the maintenance program to incorporate new or revised structural inspection requirements. We are issuing this AD to detect and correct fatigue cracking which could result in the loss of structural integrity of the airplane.
78-07-08: 78-07-08 ROLLS ROYCE, LTD.: Amendment 39-3171. Applies to Dart engines Series 542-4, 542-10, 543-10, and variants, featuring any of the following, Modifications 1243, 1244, 1432, 1448, or 1607, used on, but not limited to Convair 600 and 640 aircraft, and Nihon YS-11 and YS-11A series aircraft. Compliance is required as indicated. To prevent excessive wear in flame tube liners and suspension pins that may result in loss of flame tube support causing overheating and failure of the turbine rotors, accomplish the following: (a) Within the next 500 hours engine time in service after the effective date of this AD, unless already accomplished, inspect the flame tube liners and suspension pins for wear in accordance with the instructions contained in paragraph 4A of Rolls Royce Dart Service Bulletin Da 72-431, dated July 1, 1977 (hereafter RR SB 72-431), or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, APO New York, New York 09667 (hereafter FAA-approved equivalent). (b) If, during an inspection required by this AD, flame tube liner or suspension pin wear is found to exceed the limits given in paragraph 4A(1) of RR SB 72-431, or an FAA-approved equivalent, before further flight, except that the aircraft may be flown in accordance with FAR Sections 21.197 and 21.199 to a base where the work can be performed, replace the affected part with a serviceable part and reinspect in accordance with either paragraph (c) or (d) of this AD, as applicable. (c) If, during an inspection required by this AD, flame tube liner wear is 0.030 or greater inches on any one flame tube of any engine in the operator's fleet, determine the flame tube time in service since new or overhauled, and establish a fleet repetitive inspection time interval in accordance with paragraph 4.A(1)(c)(ii) or 4.A(2) as applicable, of RR SB 72-431 or an FAA-approved equivalent. (d) If, during an inspection required by this AD, flame tube liner wear is less than 0.030 inches on any one flame tube of any engine in the operator's fleet, replace, if necessary, the affected parts according to paragraph (b) of this AD and reinspect in accordance with paragraph 4.A(4) of RR SB 72-431, or an FAA- approved equivalent, at intervals not to exceed 2000 hours engine time in service from the last inspection. (e) If, during a repetitive inspection required by paragraph (c) or (d) of this AD, flame tube liner wear is 0.030 or greater inches on any one flame tube of an engine in the operator's fleet, reduce the Repetitive Inspection Interval for all engines in the fleet in accordance with paragraph 4.A(2) of RR SB 72-431, or an FAA-approved equivalent. (f) Record the repetitive inspection time intervals established pursuant to paragraphs (c), (d), and (e) in the aircraft maintenance records. This amendment becomes effective May 3, 1978.
2012-08-10: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes. This AD was prompted by reports of the air driven generator (ADG) failing to power essential buses during functional tests, due to the low threshold setting of the circuit protection on the ADG's generator control unit (GCU) preventing the ADG from supplying power to the essential buses. This AD requires installing a new or serviceable ADG GCU. We are issuing this AD to prevent loss of power from the ADG to the essential buses which, in the event of an emergency, could prevent continued safe flight.
98-02-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 and Mark 0070 series airplanes, that requires modification of the hook and latch engagement assemblies of the engine cowl doors, measurement of the aerodynamic mismatch between the fixed cowl and lower cowl door, and repair, if necessary. This amendment is prompted by reports of operational experience that indicate that an aerodynamic mismatch may exist between the fixed engine cowl and the lower cowl door, and may be the result of one or more hooks of the engagement assemblies not engaging adequately. This condition may cause the other hooks to carry loads higher than they were originally designed to carry, and could result in the failure of those hooks that are engaged. The actions specified by this AD are intended to prevent possible separation of the lower cowling from the airplane due to failure of the hooks of the engagement assemblies.
92-07-03: 92-07-03 BRITISH AEROSPACE: Amendment 39-8199. Docket No. 91-NM-208-AD. Applicability: Model BAe 125-800A series airplanes, as listed in British Aerospace Service Bulletin 25-67-25A013A, Revision 2, dated October 18, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced controllability of the airplane, accomplish the following: (a) Within 30 days after the effective date of this AD, drain the water from the wash basin water tank; and fabricate and install a placard to indicate that the wash basin is "inoperative." (b) Within 3 months after the effective date of this AD, install a new collector/outlet and drain pipe below the wash basin water tank outlet in accordance with British Aerospace Service Bulletin 25-67- 25A013A, Revision 2, dated October 18, 1991. After installing the new collector/outlet and drain pipe, remove the placard required by paragraph (a) of this AD. (c) An alternative method 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, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (d) 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. (e) The installation shall be done in accordance with British Aerospace Service Bulletin 25-67-25A013A, Revision 2, dated October 18, 1991, which includes the following list of effective pages: NOTE: The individual pages of this service bulletin are marked only with a "revision level." No dates appear on the pages, except for page 1, which references July 18, 1991, as the issue date of the original version of the service bulletin, and October 18, 1991, as the issue date of Revision 2. Page Number Revision Level 1, 7-8, 9-10, 2 2, 3, 4, 5-6, 11-12, 13, 14 Original 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (f) This amendment becomes effective on May 4, 1992.