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62-05-02: 62-05-02 BRANTLY: Amdt. 402 Part 507 Federal Register February 28, 1962. Applies to All Model B-2 Helicopters With Serial Numbers Prior to 180. Compliance required within the next 25 hours' time in service after the effective date of this directive. To preclude failure of the seals in the engine driven fuel pump due to excessively high temperature conditions in the engine compartment, modify the engine driven fuel pump, Lear- Romec Model RD7790D3, to incorporate high temperature seals in accordance with Brantly Service Bulletin No. 16 and Lear-Romec Service Bulletin No. 3. Reidentify modified units by revising the pump nameplate as follows: (a) Add suffix "-3" to the pump serial number. (b) Change pump model number to "RG7790G". (Brantly Service Bulletin No. 16 and Lear-Romec Service Bulletin No. 3 both cover this same subject.) This directive effective February 28, 1962.
77-14-03: 77-14-03 SOCIETE NATIONAL INDUSTRIELLE AEROSPATIALE (formerly SUD AVIATION): Amendment 39-295l. Applies to Alouette III Helicopter Model SE 3160 and SA 316B, certificated in all categories. Compliance is required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished in accordance with Alouette Service Bulletin No. 05.38, as revised June 14, 1971. To prevent possible binding of the tail rotor directional control, either replace the Houdaille type AV4S2 hydraulic damper with type AV4S3, or modify the type AV4S2 hydraulic damper by incorporating Houdaille Kit 10.338, in accordance with subparagraph 1C(2)(b) of Alouette Service Bulletin 05.38 as revised June 14, 1971, or equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, A.P.O. New York, N.Y. 09667. This amendment becomes effective August 1, 1977.
87-12-09 R1: 87-12-09 R1 SOCATA GROUPE AEROSPATIALE: Amendment 39-5650 as revised by Amendment 39-6224. Applicability: Models TB 20 and TB 21 (Serial Numbers 275 through 700) airplanes certificated in any category. Compliance: Required within the next 50 hours time-in-service (TIS) after the effective date of this AD, and each 100 hours TIS thereafter, unless already accomplished in accordance with the original issuance of AD 87-12-09. To prevent structural failure of the aileron, possible flutter, and loss of control, accomplish the following: (a) Visually inspect the five aileron balance weight attachment rivets for any detectable looseness, and the aileron skin for cracks using the procedures described in paragraph A, SOCATA TB Service Bulletin (S/B) No. 28, dated December 1986. (1) If one or more loose rivets, or cracks extending less than 9/16 inch (15 mm) from the center of the rivet is found, prior to further flight, repair as described in paragraph B of SOCATA TB AircraftS/B No. 28, dated December 1986. (2) If a crack 9/16 inch or longer from the center of the rivet is found, prior to further flight, replace the P/N TB 20.15.001.000 aileron with P/N TB 20.15.001.001 or P/N TB 20.15.001.002 aileron as applicable. (b) The repetitive inspections specified in this AD are no longer required when the ailerons have been repaired or replaced per the actions specified in either paragraph (a)(1), or (a)(2) above. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Brussels Aircraft Certification Office, FAA, AEU-100, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium; Telephone (322) 513.38.30. All persons affected by this directive may obtain copies of document(s) referred to herein upon request to SOCATA Groupe AEROSPATIALE, B.P. 38, 65001 Tarbes, France; Telephone 62.51.73.00 or 62.93.99.45 (for recorder); or the Product Support Manager, U.S., AEROSPATIALE, 2701 Forum Drive, Grand Prairie, Texas, 75053; Telephone (214) 641-3614; or may examine these documents referred to herein at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This AD revises AD 87-12-09, Amendment 39-5650, which became effective on June 26, 1987. This amendment (39-6224, AD 87-12-09 R1) becomes effective on June 25, 1989.
2010-23-11: 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: The manufacturer has informed Transport Canada that a certain number of the resolver stators, which were installed in the angle of attack (AOA) transducers, were not cleaned correctly. This condition can degrade the AOA transducer performance at low temperatures resulting in freezing of the AOA transducer resolver, which may provide inaccurate AOA data to the Stall Protection System (SPS). If not corrected, this condition can result in early or late activation of the stick shaker and/or stick pusher. These conditions could result in reduced ability of the flight crew to maintain a safe flight and landing of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
93-16-12: 93-16-12 BEECH AIRCRAFT CORPORATION: Amendment 39-8670. Docket 92-NM-248-AD. Applicability: Model 400A airplanes, serial numbers RK-1 through RK-41 inclusive; and Model 400T airplanes, serial numbers TT-3 through TT-20 inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent structural failure of the emergency door frame support, which could lead to decompression of the cabin, accomplish the following: (a) Within 200 hours time-in-service after the effective date of this AD, perform an inspection to verify the installation of all rivets in the area adjacent to the upper edge of the emergency exit door, in accordance with Beechcraft Service Bulletin 2482, dated December 1992. (1) If no rivet is missing, no further action is required by this AD. (2) If any rivet is missing, prior to further flight, install a rivet in accordance with the service bulletin. (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, Wichita Aircraft Certification Office (ACO), FAA, Small 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, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (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 inspection and installation shall be done in accordance with Beechcraft Service Bulletin 2482, dated December 1992. 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 Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on October 13, 1993.
2001-12-12: This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model CN-235 series airplanes, that requires installation of fuselage skin reinforcements in the right and left zones of the fuselage between stations 11232 and 11740 and stringers P7 and P9. The actions specified by this AD are intended to prevent premature fatigue cracking of the fuselage, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
92-11-05: 92-11-05 BRITISH AEROSPACE: Amendment 39-8255. Docket No. 91-NM-281-AD. Applicability: Viscount Model 744 and 745D series airplanes, post-mod D3070 and D3292; and Viscount Model 810 series airplanes, post-mod FG1925 and FG2172, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the engine mount attachment to the wing and wing structure, accomplish the following: (a) Within 100 landings or within 4 months after the effective date of this AD, whichever occurs earlier, visually inspect the upper boom of the wing rib at wing station 257, left and right, for proper fastener edge distance, in accordance with British Aerospace Viscount Alert Preliminary Technical Leaflet (PTL) 192 or PTL 323, both dated January 31, 1990, as applicable. (b) If any discrepancies are detected in the fastener edge distance, prior to further flight, replace the rib boom with a new part, or repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (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 inspection and replacement shall be done in accordance with British Aerospace Viscount Alert PTL 192, Issue 1, dated January 31, 1990; or British Aerospace Viscount Alert PTL 323, Issue 1, dated January 31, 1990; as applicable. (NOTE: The issue date of PTL 192 and PTL 323 is indicated only on "page 3 of 5" of each document; no other page of these documents is dated.) 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, D.C. 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 July 9, 1992.
99-19-15: This amendment adopts a new airworthiness directive (AD), applicable to certain CASA C-212 and CN-235 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
2001-12-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-300 series airplanes, that requires replacement of the hydraulic line between the main hydraulic pump and the pulsation damper in hydraulic system "B" with a new hydraulic flex hose. This action is necessary to prevent cracking in the hydraulic line (due to a production defect), leading to heavy leakage in hydraulic system "B," which could impair the functioning of the airplane's flaps, roll spoilers, inner ground spoilers, and nose wheel steering. This action is intended to address the identified unsafe condition.
2016-18-11: We are adopting a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation Model G-1159, G-1159A, G-1159B, G-IV, and GV airplanes; and certain Model GIV-X and GV-SP airplanes. This AD requires a one-time replacement of the actuator end cap fitting of the main landing gear (MLG) door, and revision of the maintenance or inspection program to establish the life limit of the end cap fitting. This AD was prompted by a report of the failure of the right MLG to extend due to fatigue cracking of the end cap fitting. We are issuing this AD to prevent such cracking, which could result in depletion of the combined (left) and utility hydraulic system fluid and the nitrogen emergency blowdown system, failure of the combined (left) hydraulic system (all phases) to provide adequate hydraulic pressure, and failure of the MLG to extend when commanded.