Results
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.
67-28-05: 67-28-05 PRATT & WHITNEY: Amdt. 39-495 Part 39 Federal Register October 21, 1967. Applies to Models JT3D-1, JT3D-1-MC6, JT3D-1-MC7, JT3D-3, and JT3D-3B Turbofan Engines with First Stage Fan Hubs, P/N 431001, that have not been inspected in accordance with Pratt & Whitney Aircraft Turbojet Engine Service Bulletin No. 1219, dated June 3, 1966, or later FAA-approved revision, and reworked in accordance with Pratt & Whitney Aircraft turbojet engine Service Bulletin No. 1066; dated October 25, 1965, or Service Bulletin No. 1219, dated June 3, 1966, or later FAA-approved revisions of these bulletins. Compliance required as indicated. (a) Before further flight, unless already accomplished within the last four cycles and thereafter at intervals not to exceed four cycles from the last inspection, visually inspect front of first stage fan hub, P/N 431001, with 6000 or more cycles since new for the JT3D-1, JT3D-1-MC6, JT3D-1-MC7, or JT3D-3 and JT3D- 3B turbofan engine models operated at JT3D-1 engine power ratings, or 4000 or more cycles since new for turbofan engine models operated at JT3D-3 or JT3D-3B engine power ratings, for indications of cracks emanating from root of fan blade slots, using a glass of at least 3-power. (b) If indications of cracks are found, remove hub from service before further flight, except that the airplane may be flown in accordance with FAR 21-197 to a base where the hub can be removed. (c) For the purposes of this AD, the number of cycles equals the number of landings (including touch- and-go landings). (d) Upon submission of substantiating data through an FAA maintenance inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the repetitive inspection period of the operator. This amendment effective October 24, 1967. This Supersedes AD 66-17-03.
73-13-07: 73-13-07 GRUMMAN AMERICAN AVIATION CORPORATION: Amdt. 39-1669. Applies to all Model AA-1, Model AA-1A, and Model AA-1B airplanes through Serial Numbers AA-1B-0177 certificated in all categories. Compliance required within the next 10 hours time in service or 30 calendar days, whichever comes first, after the effective date of this airworthiness directive. To clearly indicate to the pilot that spins are prohibited in this make and model airplane, and to provide information to assist in preventing conditions that might lead to accidental spin entry, install the new placards as provided by Grumman American Aviation Corporation Service Bulletin No. 138 or by a suitable alternate procedure as approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region. This Amendment becomes effective June 25, 1973.
2016-12-02: We are adopting a new airworthiness directive (AD) for various aircraft equipped with a BRP-Powertrain GmbH & Co KG (formerly Rotax Aircraft Engines) 912 A series engine. 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 a design change of the engine cylinder head temperature sensor without a concurrent revision of the engine model designation, the engine part number, or the cockpit indication to the pilot. We are issuing this AD to require actions to address the unsafe condition on these products.
2016-11-13: We are superseding airworthiness directive (AD) 99-19-33 for BLANIK LIMITED Models L-13 Blanik and L-13 AC Blanik gliders (type certificate previously held by LET Aeronautical Works). 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 lack of distinct color marking of the elevator drive. We are issuing this AD to require actions to address the unsafe condition on these products.
71-14-02: 71-14-02 GOODRICH: Amdt. 39-1236. Applies to B. F. Goodrich 26 x 6.6, 14 PR; tubeless, 200 m.p.h. tire, S/N's 0318 AK 0000 through and including 0365 AK 9999. (a) Prior to next flight, visually inspect the tire, particularly on sidewall and shoulders, for bumps, blisters, or peeling. (b) Replace defective tires with tire or tires having S/N's outside of the subject group, or with an equivalent tire approved by the Chief, Engineering & Manufacturing Branch, FAA, Eastern Region. (c) If a tire within the subject group reveals no specified deficiency, it may be used for a maximum of five (5) landings thereafter, provided the tire is inspected prior to each flight in accordance with paragraph (a). Replace tires after five (5) landings in accordance with paragraph (b). This amendment is effective July 2, 1971, and was effective upon receipt for all recipients of the airmail letter, dated May 22, 1971, which contained this amendment.