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79-25-07: 79-25-07 CESSNA: Amendment 39-3633. Applies to: \n\t180 Series (Serial Numbers 18051762 thru 18052981, except 18052975) airplanes; \n\t182/F182 Series (Serial Numbers 18257446 thru 18266590, F18200001 thru F18200094) airplanes; \n\t185 and A185 Series (Serial Numbers 18501096 thru 18503619) airplanes; \n\t188 and A188 Series (Serial Numbers 18800050 thru 18803240) airplanes; \n\tP206 Series (Serial Numbers P20600280 thru P20600647) airplanes; \n\tU206 and TU206 Series (Serial Numbers 20600634 thru 20604649) airplanes; \n\t207 and T207 Series (Serial Numbers 20700001 thru 20700451) airplanes; \n\t210 and T210 Series (Serial Numbers 21058783 thru 21062649, 21062651 thru 21062661, 21062663 thru 21062666, T210-0001 thru T210-0454) airplanes; \n\tModel P210N (Serial Numbers P21000001 thru P21000026) airplanes. \n\n\tCOMPLIANCE: Required within the next 50 hours' time-in-service after the effective date of this AD unless previously accomplished. \n\n\tTo preclude the possibility of electrical orelectronic component damage or an in-flight fire due to a short between an ungrounded alternator and flammable fluid carrying lines, accomplish the following: \n\n\tA)\tPerform either 1 or 2 below: \n\n\t\t1)\tInstall an additional ground strap, Cessna P/N 1570102-22, between the ground stud on the alternator and the lower left hand mounting stud on the engine auxiliary drive pad in accordance with Cessna Single Engine Service Information Letter SE79-59. An equivalent ground strap fabricated per FAA Advisory Circular 43.13-1A appropriate for the alternator rating is also acceptable. \n\n\t\t2)\tModify the alternator installation by installing a different engine mount leg per Cessna Service Kit SK210-84 (Reference Cessna Single Engine Customer Care Service Information Letter SE79-5, dated February 26, 1979) or for the 182 Series, Cessna Service Kit SK182-55A (Reference Cessna Single Engine Customer Care Service Information Letter SE79-58 dated November 23, 1979). \n\n\t\tNOTE: When accomplishing Paragraph 1) or 2), assure all contact areas are clean and provide good electrical continuity. \n\n\tB)\tVisually inspect the alternator installation for, and if necessary, provide at least 1/2 inch clearance between the alternator installation and adjacent flammable fluid carrying lines, powerplant controls and electrical wiring in accordance with FAA Advisory Circular 43.13-1A. \n\n\tC)\tVisually inspect the existing alternator to airframe ground for proper installation (Reference View A-A of SE79-59), evidence of looseness at the terminal and adequate length to allow for relative motion between the alternator and airframe. Also, visually verify that the ground straps between the engine and airframe mount are installed and provide continuity between the engine and mount. Correct any unsatisfactory conditions noted per FAA Advisory Circular 43.13-1A. \n\n\tD)\tAirplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. \n\n\tE)\tAny equivalent method of compliance with this Airworthiness Directive must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region, 601 E. 12th Street, Kansas City, Missouri 64106. \n\n\tCessna Single Engine Customer Care Service Information Letters SE79-5 dated February 26, 1979, SE79-58 dated November 23, 1979, and SE79-59 dated November 23, 1979, pertain to the subject matter of this AD. \n\n\tThis amendment becomes effective December 13, 1979.
2017-15-06: We are adopting a new airworthiness directive (AD) for British Aerospace Regional Aircraft Model HP.137 Jetstream Mk.1, Jetstream Series 200 and 3101, and Jetstream Model 3201 airplanes that would supersede AD 97-10-05. 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 cracks in the main landing gear (MLG) fitting at the pintle to cylinder interface, which could cause failure of the MLG during takeoff and landing. We are issuing this AD to require actions to address the unsafe condition on these products.
2017-15-05: We are superseding Airworthiness Directive (AD) 69-13-03 for all Piper Aircraft, Inc. Models PA-23, PA-23-160, PA-23-235, PA-23-250, PA-E23-250, and PA-30 airplanes. AD 69-13-03 required inspection of the heater exhaust extension, replacement of the extension as necessary, and overhaul of the combustion heater assembly. This AD retains the inspection of the heater exhaust extension with replacement of the extension as necessary and removes the overhaul requirement of the combustion heater assembly. This AD was prompted by a recently issued AD that applies to the Meggitt (Troy), Inc. combustion heaters, and the combustion heater AD incorporates corrective actions for the heater that contradict the overhaul requirement of AD 69-13-03. We are issuing this AD to continue to address the unsafe condition on these products and avoid potential contradiction of actions.
50-05-01: 50-05-01 PIPER: Applies to All J3C, PA-11, PA-12 Aircraft Manufactured Between November 1945 and November 1946 Inclusive. Compliance required at next periodic inspection but not later than March 1, 1950. In order to minimize the possibility of understrength Nicopress sleeves in the control system, check the major dimension of the pressed portions of all sleeves. If this dimension exceeds 0.353 inch, the sleeve should be repressed to this dimension by two presses with National Telephone Supply Co.'s hand tool 51-M-850. The go-gage furnished with the tool may be used to check the 0.353-inch dimension. In repressing the sleeves, the hand tool used should be carefully adjusted in accordance with the manufacturer's instructions and the sleeves should be recompressed with the larger axis in the same plane as during the original press. If new Nicopress sleeves are installed, three presses with the hand tool should be used as recommended by the sleeve manufacturer.
88-11-07: 88-11-07 CESSNA: Amendment 39-5971. Final copy of priority letter AD. Applicable to Model S550 and 552 airplanes, Serial Numbers S550-0001 through S550-0153, and 552-0001 through 552-0017, certificated in any category. Compliance is required prior to further flight after the effective date of this amendment, unless already accomplished. To prevent loss of a flap panel, accomplish the following: A. Visually inspect the inboard lower surface of each of the four flap panels to verify that each panel has the three required drain/vent holes, and verify that these holes are unobstructed. If all required holes are installed and unobstructed, no further action is required. NOTE: The drain holes are 3/16-inch diameter and are located approximately one inch outboard of the inboard end of the lower surface of each flap panel. (Reference: Maintenance Manual, Section 5-10-01, "Hour and Calendar Inspection Requirements," Item Z(6), "Flaps;" or Cessna Service Letter SLAS550-57-01, dated May 20, 1988.) B. If any drain/vent hole in any flap panel is not present or is found to be obstructed, repair or replace prior to further flight, in accordance with Cessna Service Bulletin SBS550-57-5 (for Model S550 series airplanes), dated May 24, 1988; Cessna Service Bulletin 552-57-5 (for Model 552 series airplanes), dated May 24, 1988; or an FAA-approved method. C. 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, Wichita Aircraft Certification Office, FAA, Central Region. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer, may obtain copies upon request to Cessna Aircraft Company, Citation Jet Marketing Division, Technical Services Department, Attention: Roger Hatfield, P.O. Box 7706, Wichita, Kansas 67277. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas. Amendment 39-5971 was effective earlier to all recipients of Priority Letter AD 88-11-07, issued May 24, 1988. This amendment, 39-5971, becomes effective July 21, 1988.
80-21-52: 80-21-52 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 4380. Applies to Model SA-360C series helicopter, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent loss of main rotor speed due to a failure in the engine to main transmission connection, within 10 hours time in service after the effective date of this AD, accomplish the following: (a) Visually inspect for cracks and other defects in the two half housings and the gimbal ring attachment flange. NOTE: During the inspection required by paragraph (a) of this AD, particular attention should be directed to the attachment points/areas. (b) Remove the upper housing half and visually inspect the flexible couplings on the clutch and main transmission sides at the attachment points for cracks, breaks, distortion, and fretting corrosion. (c) Remove the nut from one of the bolts attaching the flexible coupling and check for correct positioning of the flectors. NOTE: 1. The press-fit area of the flector bushings should be located on the flange side. 2. Upon re-installation of the nut, dry torque the nut to 4 to 5 mdaN. (30-35 ft lbs). (d) Check the condition of the main transmission input coupling flange for marks, scores, and impacts. (e) If during the inspections and checks required by paragraphs (a), (b), (c), and (d) of this AD, a crack is found, inspect the main transmission flange for cracks using the dye penetrant method. (f) If cracks are found during the inspections and checks required by paragraphs (a), (b), or (e) of this AD, before further flight, except as provided by paragraph (h) of this AD, replace the main transmission housing and gimbal ring attachment flange with a serviceable part. (g) If no cracks are found during the inspections and checks required by paragraphs (a), (b), (c), (d), or (e) of this AD, repair other defects as necessary. (h) The helicopter may be flown in accordance with FAR 21.197 and FAR 21.199 to a base where the inspections and repairs required by this AD can be accomplished provided paragraph (a) of this AD has been accomplished. (i) Report defects found to the Chief, Aircraft Certification Staff, Europe, Africa and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. Reporting approved by the Office of Management and Budget OMB No. 04-R0174. NOTE: Aerospatiale Work Cards No. 65-31-601, dated November 1976, and No. 65-31- 401, dated June 1975, and Section 02.80 of the Aerospatiale Standard Practices Manual, refer to the inspections and checks required by this AD. This amendment becomes effective May 6, 1981, as to all persons except those persons to whom it was made immediately effective by telegraphic AD T80-21-52, issued October 8, 1980, which contained this amendment.
2017-15-04: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 and 787-9 airplanes. This AD was prompted by wire harness chafing on the electro-mechanical actuators (EMAs) for certain spoilers due to insufficient separation with adjacent structure. This AD requires replacement of affected EMAs. We are issuing this AD to address the unsafe condition on these products.
84-03-03: 84-03-03 BRITISH AEROSPACE: Amendment 39-4812. Applies to Model HS 125 airplanes series 1A with modifications 251867 and 252605, series 400A with modification 252550, series 600A with modification 252468, and series 700A, certificated in all categories. The serial numbers of the affected airplanes are listed in the Planning Information section of British Aerospace 125 series Service Bulletin 24-225-(2747), dated October 17, 1980. Compliance is required as indicated, unless already accomplished. To prevent loss of power to both engine fuel computers by a single fuse failure, accomplish the following: A. Modify the engine fuel computers' direct current power supply electrical circuits within the next 500 hours time in service or one year, whichever occurs first after the effective date of this AD, in accordance with paragraph 2, Accomplishment Instructions, of British Aerospace, HS 125 series Service Bulletin 24-225-(2747), dated October 17, 1980. B. Alternate means ofcompliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 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. This amendment becomes effective March 22, 1984.
81-21-05: 81-21-05 ARTEX AIRCRAFT SUPPLIES, INC.: Amendment 39-4231. Applies to Artex replacement battery packs, P/N 00-21-006, which are designed for use in the Emergency Beacon Corporation Emergency Locator Transmitter. Within 30 calendar days after the effective date of this AD, inspect the ELT and if the battery is an Artex Battery Pack, P/N 00-21-006, replace it with a battery pack with a different part number which is approved under TSO-C91 for use in this ELT. Note: If no replacement battery pack is immediately available, placard the ELT "Not to be used in salt water." The airplane may be operated for up to 90 days with a placarded ELT. Alternative means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. This amendment becomes effective October 19, 1981.
82-09-51 R1: 82-09-51 R1 CANADAIR: Amendment 39-4452. Applies to all Canadair CL-600 airplanes certificated in all categories. Because of the possible loss of normal braking, accomplish the following unless already accomplished. 1. Revise flight manual operating procedures as follows before further flight: A. The critical engine failure recognition speed V1 shown in Section 4, page 4-39; Supplement 2, page S2-69; or Supplement 6, page S6-74 of the airplane flight manual shall be reduced by 10 KIAS but shall not be lower than 105 KIAS (VMCG). B. The takeoff distances derived from Section 4, page 4-44; Supplement 2, page S2-73; or Supplement 6, page S6-80 of the airplane flight manual shall be increased by a factor of 1.2 (20 percent). C. The landing distances derived from Section 4, page 4-63; Supplement 2, page S2-94; or Supplement 6, page S6-101 of the airplane flight manual shall be increased by a factor of 1.65 (65 percent). 2. If any suspected braking deficiencyoccurs during the brake operation, immediately release brakes, switch off the anti-skid system, and control the brakes manually as described in paragraph 35.3 of Section 2 of the airplane flight manual. 3. Within the next 50 flights after the effective date of this AD, modify the anti-skid system in accordance with Canadair Service Bulletin A600-0212 dated May 1, 1982. Accomplishment of this modification constitutes terminating action for this AD and authorizes removal of the airplane Flight Manual revisions imposed by item 1. above. 4. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 5. 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. 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). This amendment becomes effective September 9, 1982, and was effective earlier to all recipients of telegraphic AD T82-09-51 dated April 14, 1982.