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99-25-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model 382 series airplanes, that requires a one time visual inspection of the under floor to ring fittings at fuselage station 817E to verify installation of the correct sized fasteners; and follow on corrective actions, if necessary. This amendment is prompted by notification from the manufacturer indicating that during production incorrect sized fasteners were installed on the under floor to ring fittings at fuselage station 817E. The actions specified by this AD are intended to prevent fatigue cracking of the fastener holes and adjacent fuselage structure due to installation of the incorrect sized fasteners, which could result in reduced structural integrity of the airplane.
80-19-12 R1: 80-19-12 R1 BEECH: Amendment 39-3916 as amended by Amendment 39-4404. Applies to Model 76 (Serial Numbers ME-1 through ME-415) airplanes certificated in any category, that have 100 hours or more time-in-service. COMPLIANCE: Required as indicated unless already accomplished. To ensure the integrity of the engine mount structure, accomplish the following: A) Within the next 50 hours time-in-service after the effective date of this AD and thereafter at intervals not to exceed 100 hours time-in-service, accomplish the following: 1. Remove the engine cowlings in accordance with instructions in the Aircraft Manufacturer's Maintenance Manual. 2. Perform a dye penetrant inspection of the two lower tubes of each engine mount assembly which extend from the firewall to the lower engine-mounting pads in accordance with FAA Advisory Circular AC 43.13-1A, paying particular attention to the area just aft of the gusset on the forward end of the tubes. NOTE: Thoroughly clean and degrease the area to be inspected; however, it is not necessary to remove the paint. B) Each 50 hours time-in-service after the dye penetrant inspections required by Paragraph A), visually inspect the same areas of the lower engine mount tubes. C) Prior to further flight, repair any cracks detected in the engine mount lower tubes as a result of any inspection required by this AD. Contact the Sales and Service Department, Beech Aircraft Corporation, Liberal, Kansas 67901, telephone (316) 624-1613, for repair instructions. D) The time-in-service for the inspections required herein may be adjusted up to 10 hours to facilitate accomplishing the inspections concurrent with other scheduled maintenance on the airplane. E) The repetitive inspections required by paragraphs A) and B) of this AD may be discontinued when engine mount assemblies are replaced with P/N 105-910019-1 engine mount assemblies in accordance with Beechcraft Service Instructions No. 1147, Revision 1. F) Any equivalent means of compliance with this AD must be approved by the Chief, Aircraft Certification Program, Federal Aviation Administration, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209, telephone (316) 942-4285. Amendment 39-3916 became effective September 25, 1980. This Amendment 39-4404 becomes effective on June 14, 1982.
78-26-08: 78-26-08 GENERAL ELECTRIC COMPANY: Amendment 39-3376. Applies to all model CT58-100-2, CT58-110-1, CT58-110-2, CT58-140-1 series A&L, CT58-140-1 and CT58-140-2 turboshaft engines. Compliance required as indicated, unless already accomplished. To prevent failure of the lube pump drive shaft and resultant loss of oil pressure, perform the following in accordance with General Electric Alert Service Bulletin CEB-253 ((CT58) A72-157) dated October 6, 1978, or later FAA approved revision. 1. Engines with new lube and scavenge pumps P/N 4000T98P02, Serial Number NMA-05635, 5724, 5729, 5736, and 5938 through 06151, or with any lube and scavenge pump P/Ns 37D400035P101, 4000T98P01, or 4000T98P02 overhauled after March 1976. (A) Remove from service pumps with 50 hours or less time in service since new or since overhaul within 4 hours operating time after the effective date of this AD. Replace with serviceable pump. (B) Remove from service pumps with over 50 but less than 500hours time in service since new or since overhaul within 50 hours operating time after the effective date of this AD. Replace with serviceable pump. 2. Inspect removed pumps, spare pumps overhauled after March 1976 and new spare pumps in the above serial number range, prior to installation on an engine, in accordance with Section 2B of the bulletin. Remove lip seals marked Viton and replace with new unmarked Sirvene seals and inspect adjacent parts for damage in accordance with the instructions in Section 2B(7) of the bulletin. NOTE: New pumps in the affected serial number range were shipped on new production CT58-140-1 engines, S/Ns 295218 through 295233, 295235 through 295241, 295243 through 295249, and 295255. The manufacturer's service bulletin identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer mayobtain copies upon request to Customer Service and Support Manager, General Electric Company, 1000 Western Avenue, Lynn, Massachusetts 01910. This document may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. This amendment becomes effective December 19, 1978.
83-13-06: 83-13-06 McCAULEY ACCESSORY DIVISION: Amendment 39-4667. Applies to McCauley Model 3AF32C504, 3AF32C505, 3AF32C506, 3AF32C507, 3AF32C508, and 3AF32C509 full feathering propellers with specific serial numbers listed in McCauley Service Bulletin No. 147 installed on, but not limited to, Piper PA-34-220T, Cessna T303, T310P, T310Q, T310R, 320D, 320E, 320F, 335, 340Z 340A, 401, 401A, 401B, 402, 402A, 402B, 402C, 414, and 414A type aircraft certificated in all categories. Compliance required within the next 30 days after the effective date of this AD, unless already accomplished A. To prevent possible failures of the counterweight bolts, accomplish the following: 1. Remove propeller spinner (shell). 2. Remove propeller counterweight bolt, P/N A-1635-125, from each blade, and install new P/N A-1635-125 bolt(s), identified with the letter "M" stamped on the head, torqued to 65-60 lb.-ft. in accordance with paragraphs 3 and 4 of McCauley Service Bulletin 147 dated March 4, 1983, or FAA approved equivalent. 3. Reinstall propeller spinner (shell). B. A special flight permit may be used in accordance with Federal Aviation Regulations 21.197 and 21.199 to operate the aircraft to a base where the AD can be accomplished. Upon request of the operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018. Portions of the McCauley Service Bulletin No. 147 identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain a copy upon request to McCauley Accessory Division, Cessna Aircraft Company, 3535 McCauley Drive, P.O. Box 430, Vandalia, Ohio 45377. This document also may be examined at Rules Docket, Office of Regional Counsel,FAA, Attn: Rules Docket No. 83-ANE-17, 12 New England Executive Park, Burlington, Massachusetts 01803, and may be examined weekdays, except Federal holidays, between 8:00 am and 4:30 pm. This amendment becomes effective July 5, 1983.
2014-12-04: We are superseding Airworthiness Directive (AD) 2003-01-04 for BHTI Model 204B, 205A, 205A-1, 205B, and 212 helicopters. AD 2003-01-04 required inspecting the main rotor grip (grip) and reporting certain inspection results to the FAA. AD 2003-01-04 also required performing additional inspections, repair, or replacement depending on whether a crack or delamination was found, and determining and recording the hours time-in-service (TIS) and the engine start/stop cycles for each grip on a component history card or equivalent record. This new AD requires the same actions as AD 2003-01-04 but adds a retirement life to certain grips and expands the applicability to include the Model 210 helicopter and additional part-numbered grips. This AD was prompted by the discovery of additional cracked grips. We are issuing this AD to prevent failure of a grip, separation of a main rotor blade, and subsequent loss of control of the helicopter.
2014-12-08: We are superseding Airworthiness Directive (AD) 2004-11-10 for Przedsiebiorstwo Doswiadczalno-Produkcyjne Szybownictwa ``PZL-Bielsko'' Model SZD-50-3 ``Puchacz'' sailplanes. 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 fatigue damage of the welded joint between the airbrake torque tube and the airbrake control system lever located inside the fuselage. We are issuing this AD to require actions to address the unsafe condition on these products.
99-25-05: This amendment adopts a new airworthiness directive (AD) that is applicable to Hartzell Propeller, Inc., Model HD-E6C-3( ) series propellers, installed on Fairchild Dornier 328-110 series and 328-120 series airplanes. This action supersedes telegraphic AD T99-06-51 that currently requires initial and repetitive inspections of the propeller hub for cracks or grease leaks, and replacement of the hub if any cracks are found. This amendment requires an initial and repetitive inspections of Hartzell propeller hub, part number (P/N) D-5108-1, for cracks or grease leaks, replacement of the hub if any cracks are found, and allows the installation of propeller hub, P/N D-5108-5, as a terminating action for the inspection requirements. This amendment is prompted by the addition of propeller hub P/N D-5108-5 as a terminating action for the inspection requirements and by the removal of the inspection requirements for Hartzell propeller hub, P/N D-5108-5. The actions specified by this AD are intended to prevent severe vibration due to cracks in the propeller hub that could result in propeller blade loss, loss of control, and possible damage to the airplane.
93-11-04: 93-11-04 FOKKER: Amendment 39-8595. Docket 92-NM-195-AD. Applicability: Model F27 series airplanes (except Model F27 Mark 050 series airplanes); serial numbers 10102 and 10105 through 10240, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent premature failure of the outer flap center hinge due to fatigue, which could result in reduced structural integrity of the outer flap, accomplish the following: (a) For airplanes on which Fokker Service Bulletin SBF27/57-22 has not been accomplished and that have accumulated 72,000 or more total landings as of the effective date of this AD: Within 1,000 landings or 6 months after the effective date of this AD, whichever occurs first, perform a high frequency eddy current inspection of the outer flap center hinges to detect cracks, in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin F27/57-66, dated October 11, 1991.(1) If no crack is found, repair the outer flap center hinge within 2,800 landings or 2 calendar years following the inspection required by paragraph (a) of this AD, whichever occurs first, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin F27/57-66, dated October 11, 1991. (2) If any crack is found, repair the outer flap center hinge, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin F27/57-66, dated October 11, 1991, at the times specified in paragraph (a)(2)(i) or (a)(2)(ii) of this AD. (i) If the crack length inside the bore is less than 5 mm, and if no crack is found on any of the faces around the bore: Repair within 300 landings following the inspection required by paragraph (a) of this AD. (ii) If the crack length inside the bore is equal to or more than 5 mm; or if the crack length inside the bore is less than 5 mm, and the crack is also present in one of the faces around the bore: Repair prior to further flight. (b) For airplanes on which Fokker Service Bulletin SBF27/57-22 has been accomplished and that have accumulated 55,000 or more total landings as of the effective date of this AD: Within 1,000 landings or 6 months after the effective date of this AD, whichever occurs first, perform a high frequency eddy current inspection of the outer flap center hinges to detect cracks, in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin F27/57-66, dated October 11, 1991. (1) If no crack is found, repair the outer flap center hinge within 2,800 landings or 2 calendar years following the inspection required by paragraph (b) of this AD, whichever occurs first, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin F27/57-66, dated October 11, 1991. (2) If any crack is found, repair the outer flap center hinge in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin F27/57-66, dated October 11, 1991, at the times specified in paragraph (b)(2)(i) or (b)(2)(ii) of this AD. (i) If the crack length inside the bore is less than 5 mm, and if no crack is found on any of the faces around the bore: Repair within 300 landings following the inspection required by paragraph (b) of this AD. (ii) If a crack inside the bore is located on the grease nipple bore half of the hinge; or if the crack length inside the bore is equal to or more than 5 mm; or if the crack length inside the bore is less than 5 mm and the crack is also present in one of the faces around the bore: Repair prior to further flight. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the 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 inspections and repairs shall be done in accordance with Fokker Service Bulletin F27/57-66, dated October 11, 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW.,suite 700, Washington, DC. (f) This amendment becomes effective on July 22, 1993.
99-22-01: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-22-01, which was sent previously to all known U.S. owners and operators of Eurocopter Deutschland GmbH (ECD) Model EC135 P1 and T1 helicopters by individual letters. This AD requires, before further flight and at specified time intervals until a modified tail boom connecting frame flange (frame flange) is installed, inspecting and replacing, if necessary, the frame flange. This AD also requires, within 7 days, installing an additional bearing support on the frame flange. Thereafter, this AD requires visually inspecting the frame flange for cracks or misalignment of the slippage marks at specified time intervals. This amendment is prompted by the discovery of a crack in the frame flange at the attachment points of the tail rotor drive shaft bearing support. The actions specified by this AD are intended to prevent a fracture of the bearing frame flange, failure of the tailrotor drive shaft, and subsequent loss of control of the helicopter.
2014-12-03: We are adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-725A1-12 turbofan engines. This AD requires removal of affected fuel metering units (FMUs) on RRD BR700-725A1-12 engines. This AD was prompted by reports of wear on the receptors of the double-ended unions in the FMU housing on BR700-725A1-12 engines causing fuel leakage. We are issuing this AD to prevent failure of the FMU, which could lead to damage to one or more engines and damage to the airplane.