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81-07-10 R1: This amendment amends an existing Airworthiness Directive (AD) applicable to Hughes Helicopters Model 369 series helicopters equipped with any cargo hook by clarifying cargo hook operating time recordation. This amendment is needed to relieve an undue burden on operations.
76-09-02: 76-09-02 BEECH: Amendment 39-2592. Applies to Models 200 and Military A100-1 (Serial Numbers BB-3 thru BB-19, BB-21 thru BB-38, BB-40, BB-41, BB-43 thru BB-75 and BB-78) and Model C-12A (Serial Numbers BC-1, BC-2, BC-3, BD-2 and BD-3) airplanes. \n\n\tCompliance: Required as indicated, unless already accomplished. \n\n\tTo detect inadequate edge distance on the bolt holes in the wing center section lower forward spar cap for attachment of the outer wing panel lower forward spar cap, within the next 100 hours' time in service after the effective date of this AD, accomplish the following: \n\n\tA)\tInspect for proper fit between the wings and center section at the lower forward spar attachment as follows: \n\n\t\t1.\tUsing a vernier caliper or a suitable depth gage, graduated in increments of .01-inch, measure the protrusion of the wing spar cap below the center section spar cap at the lower forward wing spar cap below the center section spar cap at the lower forward wing attachment on both the LH and RH sides. \n\n\t\t2.\tIf the protrusion does not exceed .10-inch, no further action is necessary. \n\n\t\t3.\tIf the protrusion exceeds .10-inch, remove the wing and measure the edge distance of the wing attachment hole in the center section lower spar in accordance with Figure 1. Provide this information to the manufacturer and thereafter operate or modify the airplane in accordance with FAA-approved limitations or instructions provided by the manufacturer. \n\n\tB)\tAny equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. \n\n\tNOTE: The manufacturer's address is Beech Aircraft Corporation, Commercial Service Operations, Wichita, Kansas 67201. \n\n\tBeechcraft Service Instruction No. 0775-062 or later approved revisions cover the subject matter of this AD. \n\n\tThis amendment becomes effective May 3, 1976. \n\nFIGURE 1 \nAD 76-09-02
93-17-13: 93-17-13 SCHWEIZER AIRCRAFT CORPORATION and HUGHES HELICOPTERS, INC.: Amendment 39-8684. Docket Number 93-SW-11-AD. Applicability: Model 269A, 269A-1, 269B, 269C, and TH55A helicopters, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the lower coupling drive shaft (shaft), loss of power to the rotor system, and subsequent loss of control of the helicopter, accomplish the following: (a) Within the next 30 days or 100 hours' time-in-service after the effective date of this AD, whichever occurs first-- (1) Install engine and rotor tachometer markings in accordance with Part II of Schweizer Aircraft Corporation Service Bulletin B-257.1, dated May 21, 1993 (SB). NOTE: Figure B-257.1-2 indicates the position of the white slippage mark on the lens and lens frame. (2) Visually inspect the shaft for cracks, machining steps, manufacturing tool marks, surface defects, and lack of cleanup during the production grinding operation in accordance with Part I of the SB. NOTE: Failure to accomplish proper cleanup of the shaft surface is evidenced by a non-uniform surface smoothness. The actual surface finish value may vary from shaft to shaft. (b) Repeat the visual inspection for cracks as described in paragraph (a)(2) of this AD at intervals not to exceed 300 hours' time-in-service from the last inspection. (c) Replace any shaft found to be unairworthy during the inspection required by this AD with an airworthy shaft, before further flight. (d) 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, New York Aircraft Certification Office, FAA, New England Region, 181 South Franklin Avenue, Valley Stream, New York 11581. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, New York Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York Aircraft Certification Office. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished. (f) The modification and inspections shall be done in accordance with Part I and II of Schweizer Aircraft Corporation Service Bulletin B-257.1, dated May 21, 1993. 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 Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New York 14902. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 4400 Blue Mound Road, bldg. 3B, room 158, Fort Worth, Texas 76106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on October 20, 1993.
81-24-07: 81-24-07 PIPER AIRCRAFT CORPORATION: Amendment 39-4255. Applies to: Models Affected: Serial Numbers Affected: PA-32R-300 Lance 32R-7680001 through 32R-7880068 PA-32RT-300 Lance II 32R-7885001 through 32R-7985105 PA-32RT-300T Turbo Lance II 32R-778700I, 32R-7887002 through 32R-7987126 PA-32R-301 Saratoga S.P. 32R-8013001 through 32R-8113112 PA-32R-301T Turbo Saratoga S.P. 32R-8029001 through 32R-8129104 Applies to airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent a potentially hazardous condition during landing and ground operation due to the failure of landing gear down lock, accomplish the following: a. Within the next 50 hours time in service after the effective date of this AD, modify the nose landing gear in accordance with Piper Service Letter No. 927, dated October 2, 1981, and Piper Kit, P/N 764135V. b. Make an appropriate maintenance record entry. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. This amendment becomes effective November 20, 1981.
2020-09-04: The FAA is adopting a new airworthiness directive (AD) for AERMACCHI S.p.A. Models F.260, F.260B, F.260C, F.260D, F.260E, and F.260F airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracks on the body of the flap actuators. The FAA is issuing this AD to require actions to address the unsafe condition on these products.
97-20-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 series airplanes, that requires repetitive inspections to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar; and repair or modification of this area, if necessary. This amendment is prompted by a report from the manufacturer indicating that, during full-scale fatigue testing of the airframe, fatigue cracking was detected in this area. The actions specified by this AD are intended to detect and correct this cracking, which could reduce the residual strength of the top skin of the wings, and consequently affect the structural integrity of the airframe.
78-05-02: 78-05-02 AIRESEARCH MANUFACTURING COMPANY OF ARIZONA: Amendment 39-3145 as amended by amendment 39-3445. Applies to AiResearch Model TPE331-1, -2, -3, -5, and -6 Series engines. Compliance required as indicated. To prevent failure of the propeller pitch control cam follower pin accomplish the following: (1) Within the next 500 hours time in service after April 1, 1978 or prior to September 30, 1979, or at next engine overhaul, whichever comes first, unless already accomplished, remove propeller pitch control sleeve assembly Part Number 869647-1, -2, or -3 from the engine and replace it with a serviceable propeller pitch control sleeve assembly Part Number 869647-4 or other later FAA approved sleeve assembly in accordance with AiResearch Service Bulletin TPE331-72-0115, Revision 1, dated September 26, 1977, or later FAA approved revisions, or by equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. (2) Special flight permits may be issued per FAR 21.197 and 21.199 to authorize operation of aircraft to a base where this modification required by this AD may be performed. Amendment 39-3145 became effective April 1, 1978. This amendment 39-3445 becomes effective April 5, 1979.
2008-10-14: 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: Strip results from some of the engines listed in the applicability section of this directive revealed excessively corroded low pressure turbine disks stage 2 and stage 3. The corrosion is considered to be caused by the environment in which these engines are operated. Following a life assessment based on the strip findings it is concluded that inspections for corrosion attack are required. The action specified by this AD is intended to avoid a failure of a low pressure turbine disk stage 2 or stage 3 due to potential corrosion problems which could result in uncontained engine failure and damage to the airplane. We are issuing this AD to detect corrosion that could cause stage 2 or stage 3 disk of the low pressure turbine to fail and result in an uncontained failure of the engine.
81-06-08: 81-06-08 PIPER: Amendment 39-4264. Applies to Piper PA-18-150 Airplanes, S/N 18- 8602 thru 18-8109013, certificated in all categories. Compliance required as indicated. To prevent failure of the lower fuselage attachment tab which connects the lower horizontal stabilizer brace wire to the fuselage, accomplish the following: (a) Within the next 10 hours in service after the effective date of this AD, unless already accomplished, conduct a visual inspection of the lower fuselage attachment tab, Piper P/N 80292-15, in the area of the welds for cracks. If cracks are found, install the tail brace wire support in accordance with the Instructions Section of Piper Service Bulletin 706 dated February 23, 1981, or approved alternate method, prior to further flight. If no cracks are found, install the tail brace wire support in accordance with (b) or (c), as appropriate. (b) For airplanes with less than 500 hours in service on the effective date of this AD, within the next 10 hours in service, unless already accomplished, install the tail brace wire support in accordance with the Instructions Section of Piper Service Bulletin 706 dated February 23, 1981. (c) For airplanes with 500 hours or more time in service on the effective date of this AD, within the next 100 hours in service, unless already accomplished, install the tail brace wire support in accordance with the Instructions Section of Piper Service Bulletin 706 dated February 23, 1981. (d) Report findings of cracked parts to the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, within five days of the inspection; include the time on the part and aircraft serial number. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) (e) Alternative inspections, alterations, or repairs which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (f) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the compliance times specified in this AD. NOTE: Retention of original tab fitting P/N 80292-15 on the airplane is optional. This amendment is effective November 19, 1981, for all persons except those to whom it was made effective immediately by airmail letter dated March 13, 1981.
2008-06-20: 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: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, * * * Special Federal Aviation Regulation 88 (SFAR88) * * * required a safety review of the aircraft Fuel Tank System * * *. * * * * * Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an `unsafe condition' * * *. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers' requirements. We are issuing this AD to require actions to correct the unsafe condition on these products.