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74-05-02: 74-05-02 CANADAIR: Amdt. 39-1790. Applies to CL-44-D4 and CL-44-J airplanes certificated in all categories. Compliance required as indicated. To prevent cracks in the main landing gear uplock actuator cylinder on the Canadair Models CL-44-D4 and CL-44-J aircraft, resulting in the inability to extend the landing gear, accomplish the following: 1. Prior to accumulation of 3,500 hours time in service on the main landing gear uplock actuator cylinders, modify the aircraft in accordance with Canadair Service Bulletin No. CL-44-D4-381, revised September 28, 1968, observing the shimming requirements of Canadair Service Information Circular No. 317-CL-44-D4, dated August 28, 1964, or in accordance with an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 2. For those aircraft modified as described in paragraph 1, the following apply: a. An uplock actuator cylinder installed in a primary uplock actuator must be replaced prior to the accumulation of 8,000 hours in service in primary uplock actuators. Service time accumulated on uplock cylinders prior to accomplishment of Canadair Service Bulletin No. CL-44-D4-381, must be counted as part of the aforementioned 8,000 hours. b. Cylinders removed from primary uplock actuators including unmodified, single cylinder uplock systems, may be used in emergency uplock actuators provided that: (a) Cylinders are subjected to a dye-penetrant inspection, and are found to be free from cracks. (b) Satisfactory dye-checked cylinders are reidentified to distinguish them from new cylinders. (c) Cylinders do not exceed 16,000 hours total combined service time in primary and emergency systems. c. A new actuator cylinder installed in an emergency uplock system has an unrestricted service life. This AD supersedes AD 65-04-04. This amendment is effective February 26, 1974.
75-05-13: 75-05-13 GENERAL ELECTRIC: Amendment 39-2114 as amended by Amendment 39-2524. Applies to all General Electric CF700-2C, CF700-2D, and CF700-2D-2 turbofan engines having compound turbine and fan blade, Part Number 6002T57P01, with the following serial numbers: 001CY through 9994CY 001DN through 999DN 001CZ through 1038CZ 001DO through 999DO 001DA through 999DA 001DP through 999DP 001DB through 999DB 001DQ through 999DQ 001DC through 999DC 001DR through 999DR 001DE through 999DE 001DS through 999DS 001DF through 999DF 001DT through 999DT 001DG through 999DG 001DU through 999DU 001DH through 999DH 001DV through 999DV 001DW through 999DW 001DJ through 999DJ 001DX through 999DX 001DK through 999DK 001DY through 999DY 001DL through 999DL 001DI through 999DI 001DZ through 999DZ 001DM through 999DM Compliance required as indicated unless already accomplished. To preclude possible failures of compound turbine and fan blades, perform an eddy current inspection as specified in the Accomplishment Instructions section of General Electric Alert Service Bulletin No. (CF700) A72-124, or (CF700) A72-125 or later FAA approved revisions or a fluorescent-penetrant inspection as specified in General Electric Overhaul Manual SEI-133 Section 72-72-1, or equivalent inspection method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region, in accordance with the following schedule: a. Compound turbine and fan blades with 400 or more hours total time in service on the effective date of this AD: Inspect within the next 30 hours time in service and inspect every 400 hours time in service thereafter. b. Compound turbine and fan blades with less than 400 hours total time in service on the effective date of this AD: Inspect prior to the accumulation of 430 hours total time in service and inspect every 400 hours time in service thereafter . Replace all compound turbine and fan blades, confirmed as cracked, prior to further flight. Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the inspection interval specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. Amendment 39-2114 was effective March 12, 1975. This amendment 39-2524 becomes effective March 3, 1976.
52-01-05: 52-01-05 BELL: Applies to All Models 47B and 47B3 Helicopters and to Model 47D Helicopters Serial Numbers 1 to 110, Inclusive. Compliance required at next 300-hour overhaul, but not later than March 1, 1952. To provide a tail rotor blade grip retaining bolt of increased service life, replace each existing 47-641-026-1 bolt with the 47-641-052-1 bolt, and torque to 160-190 inch-pounds. Also, replace the 47-641-036-1 flat washer type micarta seal in the blade yoke on Models 47B and 47B3 helicopters with the 47-641-042-1 cup seal type. (Bell Service Bulletin No. 80 covers this same subject.)
78-07-04: 78-07-04 AVCO LYCOMING: Amendment 39-3166. Applies to Avco Lycoming T5508D model turboshaft engines. Compliance is required by May 1, 1978. To prevent fatigue failure of the engine accessory inner bevel gear leading to engine stoppage, remove inner bevel gear P/N 2-070-005-02 and replace with inner bevel gear assembly P/N 2-070-030-01, in accordance with Avco Lycoming Service Bulletin No. 5508-0013, dated March 15, 1978, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. 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 these documents from the manufacturer may obtain copies upon request to Avco Lycoming Division, 550 South Main Street, Stratford, Connecticut 06497. These documents 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 March 30, 1978.
76-12-10: 76-12-10 BEECH: Amendment 39-2644. Applies to Model 200 (Serial Numbers BB-3 thru BB-41) airplanes. Compliance: Required as indicated, unless already accomplished. To prevent flight into icing conditions with inoperative wing de-ice boots, accomplish the following: A) Within 50 hours' time in service after the effective date of this AD: 1. Remove the access plates on the outboard side of the nacelles, forward of the main spar, and visually inspect the wing de-ice tubes to determine if they are high temperature supply tubes which are identified by their black color. 2. If they are black high temperature supply tubes no further action is required. 3. If they are not black high temperature supply tubes, either install a placard on the instrument panel in full view of the pilot which reads: "DO NOT OPERATE IN ICING CONDITIONS" and operate the aircraft in accordance with this limitation or comply with Paragraph B. B) On or before October 1, 1976,install new P/N 130936N8D1200 black high temperature supply tubes in the right and left hand wings outboard of the engine nacelles. When this has been accomplished the placard and operating instructions required in Paragraph A are no longer applicable. C) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Procedures for inspecting and replacing the wing de-ice boot supply tubes are provided in Beechcraft Service Instructions 0822-193 or later approved revisions. This amendment becomes effective June 23, 1976.
76-12-11: 76-12-11 LAKE AIRCRAFT, DIVISION of CONSOLIDATED AERONAUTICS, INC: Amendment 39-2646. Applies to all Model LA-4-200 airplanes equipped with the AC GF- 416 fuel filter. Compliance required as specified below unless already accomplished. 1. To prevent engine power loss resulting from fuel injector contamination caused by filter housing corrosion, remove the AC GF-416 fuel filter from aircraft, cut open the housing and inspect the inside for corrosion in accordance with the following schedule: a. Inspect the AC GF-416 filters installed in aircraft 60 or more days, within the next 30 days. b. Inspect AC GF-416 filters installed in aircraft less than 60 days, prior to the accumulation of 90 days on aircraft. Thereafter, c. Inspect AC GF-416 replacement filters prior to the accumulation of 90 days on aircraft. If corrosion is observed, inspect the Bendix Fuel Injection Unit in accordance with Paragraphs 2 a, b, and c, prior to further flight. 2. If the aircraft has had at least one fuel filter changed since the installation of a new or overhauled fuel injection unit before the effective date of this AD, perform the following inspection of the Model RSA-5AD1 Bendix Fuel Injection Unit, P/N 252054-4, within the next 30 calendar days: a. Remove and inspect fuel inlet strainer. b. Inspect housing area enclosing strainer. c. Remove and inspect each of the four injector nozzles P/N 2524107, including the shield P/N 2520418 and screen P/N 367687. If corrosion contamination is found in the fuel injector nozzle assembly, strainer or housing area, replace or overhaul the fuel injection unit and the flow divider P/N 2524057-2 prior to further flight. Reference: Lake Aircraft Division Service Bulletin B-57. Equivalent methods of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803.This amendment becomes effective June 29, 1976.
90-02-04: 90-02-04 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6467. Docket No. 89-NM-207-AD. Applicability: Model DHC-8 series airplanes, serial numbers 3 through 144 inclusive; certificated in any category; equipped with main landing gear uplock actuator, Part Numbers 10800-103, -105, -107, -109, -111; and which do not have Modification 8/1098 incorporated. Compliance: Required as indicated, unless previously accomplished. To prevent failure of the main landing gear (MLG) to extend, accomplish the following: A. Within 50 hours time-in-service after the effective date of this AD, inspect the MLG uplock installation in accordance with the compliance section of de Havilland Service Bulletin No. 8-32-79, Revision A, dated February 3, 1989. If the sensor bracket is under flush, and there are no spacers fitted, prior to further flight, rework the actuator in accordance with the service bulletin. B. Whenever the proximity sensor and/or the proximity sensor mounting bracket on an uplock actuator has been reset or replaced, prior to further flight, perform the inspection and any necessary repair as required by paragraph A., above. C. Within one year after the effective date of this AD, rework and reidentify all uplock actuators in accordance with DOWTY Alert Service Bulletin (part of de Havilland Service Bulletin No. 8-32-79) paragraph 2.E., "Rework" instructions. After rework is accomplished, the inspections required in paragraphs A. and B., above, may be terminated. D. 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, New York Aircraft Certification Office, FAA, New England Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, New York Aircraft Certification Office. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing of Canada, Ltd., de Havilland Division, Garrett Boulevard, Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment (39-6467, AD 90-02-04) becomes effective on February 12, 1990.
92-15-08: 92-15-08 FOKKER: Amendment 39-8302. Docket No. 92-NM-47-AD. Applicability: Model F28 Mark 0100 series airplanes; serial numbers 11244 through 11308, inclusive; 11310, and 11312 through 11314, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue damage and subsequent reduced structural capability of the horizontal stabilizer attachment, accomplish the following: (a) Within 7 months after the effective date of this AD, remove the normal maximum (second) detent for the reverse thrust control and install a modified detent, in accordance with Fokker Service Bulletin SBF100-76-008, dated May 8, 1991. (b) 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, 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. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (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) The removal and installment shall be done in accordance with Fokker Service Bulletin SBF100-76-008, dated May 8, 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, 1100 L Street NW.,Room 8401, Washington, DC. (e) This amendment becomes effective on September 8, 1992.
77-09-07: 77-09-07 DOWTY ROTOL: Amendment 39-2890. Applies to Dowty Rotol Type (c)R175/4-30-4/13E and (c)R212/4-30-4/22 propellers having hub and driving center, P/N 601023166, 601023223, or 601023227 modified to Dowty Rotol Mod. No. (c)VP2381 standard. These propellers are installed on, but not necessarily limited to, Fokker Model F-27 Mks. 100, 300, and 700 Series and Hawker Siddeley Model 748 Series 2A airplanes. Compliance is required at the next propeller overhaul or within the next 4700 hours propeller time in service after the effective date of this AD, whichever occurs first, unless already accomplished. To prevent cracking and possible failure of the hub driving center due to improper machining, accomplish the following: (a) For Type (c)R175/4-30-4/13E propellers, that incorporate the following hub and driving center assemblies, rework the hub driving center to salvage scheme No. 640144020 in accordance with Paragraph 2A of Dowty Rotol Service Bulletin 61-857, datedFebruary 3, 1975, or an equivalent approved in accordance with Paragraph (c) of this AD: Hub and Driving Center Assembly Serial Numbers 175/58/67 175/58/72 175/58/91 175/58/146 175/59/184 (b) For Type (c)R175/4-30-4/13E propellers that incorporate hub and driving center assemblies having serial numbers not listed in paragraph (a) of this AD and Type (c)R212/4-30- 4/22 propellers - (1) Inspect the hub driving center to verify correct machining in accordance with Paragraph 2B of Dowty Rotol Service Bulletin 61-857 dated February 3, 1975, or an equivalent approved in accordance with paragraph (c) of this AD; and (2) If the hub driving center is found to have been incorrectly machined, rework it to salvage scheme No. 640144020 in accordance with Paragraph 2A of Dowty Rotol Service Bulletin 61-857, dated February 3, 1975, or an equivalent approved in accordance with paragraph (c) of this AD. (c) The equivalent means of compliance specified inparagraphs (a) and (b) of this AD must be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region c/o American Embassy, APO New York, N.Y. 09667. This amendment becomes effective May 19, 1977.
99-06-14: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that requires one-time visual inspections of the elevator trim system for paint contamination on the actuator pistons and to determine the moisture level of the moisture indicator; verification of the installation and condition of the gasket of the flex drive; and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the elevator trim system due to paint/moisture contamination, and consequent reduced controllability of the airplane.