Results
2005-13-37: The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0070 and 0100 airplanes. This AD requires repetitive inspections for damage of the drive rod assembly of the aileron tab on each aileron actuator; repetitive measurements of the clearance between the aileron hydraulic lines and the drive rod; and related investigative and corrective actions if necessary. This AD is prompted by a report of an aileron 2 fault caused by severe wear of the polyamide washer that is part of an anti-rotation bush assembly in the aileron attachment lug. We are issuing this AD to prevent excessive wear of the polyamide washer of the aileron actuator bush assembly, which could result in aileron flutter and loss of control of the airplane.
2010-23-12: 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: * * * * * Investigation conducted by Thales on * * * probes revealed oil residue between the stator and the rotor parts of the AoA [angle of attack] vane position resolvers. This oil residue was due to incorrect cleaning of the machining oil during the manufacturing process of the AoA resolvers. At low temperatures, this oil residue becomes viscous (typically in cruise) causing lag of AoA vane movement. Such condition could lead to discrepant AoA measurement. If not corrected, and if two or three AoA probes were simultaneously affected and provided wrong indications of the AoA to a similar extent, it could lead to a late activation of the angle ofattack protection, which in combination with flight at high angle of attack would constitute an unsafe condition. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
70-14-05: 70-14-05 BELL: Amendment 39-1025. Applies to all Model 206A helicopters certificated in all categories equipped with voltage regulator P/N 206-075-027-3. Compliance is required within 300 hours time in service after the effective date of this airworthiness directive, unless already accomplished. Replace the voltage regulator, Bell Part No. 206-075-027-3, in accordance with the instructions in paragraphs 1 through 11, as applicable, of Bell Helicopter Company Service Letter No. 206A-139, Revision "A", dated October 14, 1969, or later FAA approved revision. Alternate means of compliance or equivalent replacement parts may be acceptable if approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. This amendment becomes effective August 15, 1970.
2005-13-38: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-100, DHC-8-200, and DHC-8-300 series airplanes. This AD requires revising the airworthiness limitations section of the Instructions for Continued Airworthiness by incorporating new and revised structural inspection procedures and new and revised inspection intervals for the longitudinal skin joints in the fuselage pressure shell. This proposed AD also requires phase-in inspections and repair of any crack found during any phase-in inspection. This AD is prompted by a report indicating that visual inspections were not adequate for detecting fatigue cracking in portions of the longitudinal skin joints in the fuselage pressure shell. We are issuing this AD to detect and correct fatigue cracking of the longitudinal skin joints in the fuselage pressure shell, which could affect the structural integrity of the airplane, and result in loss of cabin pressurization during flight.
97-15-08: This amendment adopts a new airworthiness directive (AD) that is applicable to McDonnell Douglas Helicopter Systems (MDHS) Model 369D, E, F, FF, 500N, AH-6, and MH-6 helicopters. This action requires replacement of certain transmission output drive gears (gears). This amendment is prompted by several reports of spalled or fractured gear teeth, most of which occurred during high-power or external-lift operations. The actions specified in this AD are intended to prevent failure of the gear, which could result in loss of main rotor control and subsequent loss of control of the helicopter.
59-17-06: 59-17-06 HELIO: Applies to All Model H-391B Aircraft and Model H-395, Serial Number 075 and 502 Through 509 Inclusive. Compliance required within next 100 hours or by November 1, 1959, whichever occurs first. Install additional pulley guards at three 3-inch stabilator control system pulleys located at: (a) The upper left-hand corner of the fuselage truss just aft of the firewall. (b) Just forward of the lower left-hand side of the instrument panel. (c) Directly under the forward attach point of the vertical stabilizer in the aft portion of the tail cone. (The cable makes a 180 degree turn around this pulley.) (Helio Service Bulletin No. 20 covers this subject.)
75-26-09: 75-26-09 MORANE SAULNIER (SOCATA): Amendment 39-2460. Applies to MS892.A-150, MS893-A, and MS894-A airplanes, serial numbers 1873 and below, certificated in all categories. Compliance is required as indicated, unless already accomplished. To detect a distorted or bent elevator bellcrank and prevent loss of pitch-up control, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this Ad, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, visually inspect the elevator bellcrank (pitch control crank lever) in accordance with Socata Service Bulletin No. 89 GR 27.07, dated June 1971, or an FAA-approved equivalent. (b) If a bent or distorted elevator bellcrank is found as a result of an inspection required by paragraph (a) of this AD, before further flight, replace the elevator bellcrank, No. 880-27.0.261.0, with a reinforced elevator bellcrank, No. 880-27.0.371.0, in accordance with the "Description" paragraph of Socata Service Bulletin No. 92 Gr:27-08, dated October 1971, or an FAA-approved equivalent. (c) The inspections required by paragraph (a) of this AD may be discontinued after installation of a reinforced bellcrank, No. 880-27.0.371.0, in accordance with the Socata Service Bulletin No. 92 Gr:27-08, dated October 1971, or an FAA-approved equivalent. This amendment becomes effective December 29, 1975.
92-15-02: 92-15-02 BEECH AIRCRAFT CORPORATION: Amendment 39-8295. Docket No. 92-NM-04-AD. Applicability: Beech Model 400 airplanes, serial numbers RJ-1 through RJ-65, inclusive; Mitsubishi Model MU-300 airplanes, serial numbers A003SA through A091SA, inclusive; and Mitsubishi Model MU-300-10 airplanes, serial numbers A1001SA through A1011SA, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the engine mounting system, accomplish the following: (a) Within 200 hours time-in-service after the effective date of this AD, or at the next scheduled inspection interval, whichever occurs first, replace each engine mount nut and bolt with nuts and bolts that have been inspected using magnetic particle techniques (identified by green dye), in accordance with Beechcraft Service Bulletin 2408, dated June 1991 (for Beech Model 400 and Mitsubishi Model MU- 300-10 airplanes); or Mitsubishi Service Bulletin 71-004, dated January 8, 1992 (for Mitsubishi Model MU-300 airplanes); as applicable. (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), ACE-115W, 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 replacement shall be done in accordance with Beechcraft Service Bulletin 2408, dated June 1991 (for Beech Model 400 and Mitsubishi Model MU-300-10 airplanes); or Mitsubishi Service Bulletin 71-004, dated January 8, 1992 (for Mitsubishi Model MU-300 airplanes); as applicable. 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 FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on August 18, 1992.
2005-12-12: The FAA is adopting a new airworthiness directive (AD) to supersede AD 79-10-15, which applies to all Cessna Aircraft Company (Cessna) Models 401, 401A, 401B, 402, 402A, 402B, 411, and 411A airplanes. AD 79-10-15 currently requires repetitive inspections of the right and left wing spar lower cap areas for fatigue cracks and requires wing spar cap repair or replacement as necessary. This AD is the result of fatigue and crack growth analyses of the wings of these airplanes, recent cracks found on similar design Model 402C airplanes, and the FAA's determination that repetitive inspections and a wing spar modification are necessary to address the unsafe condition. Consequently, this AD would require repetitive inspections and a spar strap modification on each wing. The actions specified by this AD are intended to prevent wing spar cap failure caused by undetected fatigue cracks. Such failure could result in loss of a wing with consequent loss of airplane control. FAA is also issuing AD 2005-12-13 to require the spar strap modification and long-term inspections on Models 402C and 414A airplanes.
86-18-08: 86-18-08 SHORT BROTHERS PLC: Amendment 39-5388. Applies to Models SD3-30 and SD3-60 airplanes listed in Short Brothers PLC Service Bulletins SD3-28-22, Revision 2, dated July 1985 (for Model SD3-30 airplanes), and SD360-28-06, Revision 2, dated July 1985 (for Model SD3-60 airplanes), certificated in any category. Compliance is required within 90 days after the effective date of this AD. To prevent erroneous or erratic fuel quantity indications caused by moisture ingress into the fuel tank gauging system co-axial connectors, accomplish the following, unless previously accomplished: A. Seal the affected co-axial connectors in accordance with Short Brothers PLC, Service Bulletins SD3-28-22, Revision 2, dated July 1985, for Model SD3-30 airplanes, and SD360-28-06, Revision 2, dated July 1985, for Model SD3-60 airplanes. B. 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, Standardization Branch, ANM-113, 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Shorts Aircraft, 1725 Jefferson Davis Highway, Suite 510, Arlington, Virginia 22202. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective September 11, 1986.