Results
98-16-03: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (Socata) Models TB9 and TB10 airplanes. This AD requires repetitively inspecting the wing front attachments on the wing and fuselage sides for cracks, and repetitively incorporating a certain modification kit (type of kit and time of incorporation depends on whether cracks are found during the inspection). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent structural failure of the wing front attachments caused by fatigue cracking, which could result in the wing separating from the airplane if the airplane is operated with cracked wing front attachments over an extended period of time.
92-08-15: 92-08-15 MOONEY AIRCRAFT CORPORATION: Amendment 39-8266. Final copy of priority letter. Docket No. 92-CE-29-AD. Applicability: Model M20J airplanes, serial numbers 24-3201, 24-3218 through 24-3238, 24-3240 through 24-3250, and 24-3252 through 24-3256, certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent rudder imbalance, which could lead to aerodynamic problems and loss of control of the airplane, accomplish the following: (a) Prior to further flight after the effective date of this AD, accomplish the following: (1) Fabricate a placard with the words "Maximum Gross Weight Reduced to 2,740 Pounds." Install this placard on the airplane instrument panel within the pilot's clear view. (2) Insert a copy of this AD into the limitations section of the Airplane Flight Manual and operate the airplane accordingly. (b) Within the next 15 hours time-in-service after the effective date of this AD, inspect the airplane to ensure that the rudder static balance is within the required limits in accordance with paragraphs 1. through 3. of the INSTRUCTIONS section of Mooney Aircraft Corporation Service Bulletin (SB) M20-252, dated April 6, 1992. (c) If the rudder static balance falls outside the limits specified in Mooney Aircraft Corporation SB M20-252, prior to further flight, adjust the rudder balance weight in accordance with paragraphs 4. through 7. of the INSTRUCTIONS section of Mooney Aircraft Corporation SB M20-252, dated April 6, 1992. (d) The placard and Airplane Flight Manual limitation required by paragraphs (a)(1) and (a)(2) of this AD are no longer required after compliance with paragraphs (b) and (c) of this AD as applicable. (e) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Airplane Certification Office, FAA, 4400 Blue Mound Road, Fort Worth, Texas 76193-0150. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth Airplane Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth Airplane Certification Office. (f) The inspection and possible modification required by this AD shall be done in accordance with Mooney Aircraft Corporation Service Bulletin M20-252, dated April 6, 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 the Mooney Aircraft Corporation, P.O. Box 72, Kerrville, Texas 78029-0072. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room8401, Washington, DC. (g) This amendment becomes effective on June 30, 1992, to all persons except those persons to whom it was made immediately effective by priority letter AD 92-08-15, issued April 9, 1992, which contained the requirements of this amendment.
2012-26-15: We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. air data pressure transducers as installed on various aircraft. This AD requires various tests or checks of equipment having certain air data pressure transducers, and removal of equipment if necessary. As an option to the tests or checks, this AD allows removal of affected equipment having certain air data pressure transducers. This AD was prompted by a report of a pressure measurement error in the pressure transducer used in various air data systems, which translates into air data parameter errors. We are issuing this AD to detect and correct inaccuracies of the pressure sensors, which could result in altitude, computed airspeed, true airspeed, and Mach computation errors. These errors could reduce the ability of the flightcrew to maintain the safe flight of the aircraft and could result in consequent loss of control of the aircraft.
2010-12-03: The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. models CFM56-3 and -3B turbofan engines. This AD requires initial and repetitive inspections for damage to the fan blades. This AD results from a report of a failed fan blade with severe out-of-limit wear on the underside of the blade platform where it contacts the damper. We are issuing this AD to prevent failure of multiple fan blades, which could result in an uncontained failure of the engine and damage to the airplane.
75-10-02 R2: 75-10-02 R2 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2194 as amended by Amendment 39-2237 is further amended by Amendment 39-3985. Applies to Lockheed-California Company Model L-1011-385-1 series airplanes, certificated in all categories, which incorporate the galley door type design configuration. To prevent possible unsafe condition to the flight attendants in the underfloor galley service area and possible damage to the underfloor galley service area interiors, accomplish the following: (a) Galley Door Inspections, Corrections and Visual Confirmation of Galley Door Safe Condition. (1) Within 250 flight hours after the effective date of this AD, unless previously accomplished within the last 2250 flight hours prior to the effective date of this AD, and at intervals not to exceed 2500 flight hours thereafter, perform the inspections and complete the necessary corrective adjustments to the door mechanical and electrical systems as specified in the Lockheed-CaliforniaCompany Alert Service Bulletin 093-52-A075, dated March 28, 1975, or later FAA-approved revisions. (2) Within 250 flight hours after the effective date of this AD, on all flights thereafter conducted, (i) A visual check to confirm the proper engagement of the door ditch latches from inside of the galley must be performed by a member of the flight crew or flight attendants just prior to taxiing from the ramp, per instructions described on the applicable galley door decal. (Lockheed Alert Service Bulletin 093-52-A075, dated March 28, 1975, or later FAA- approved revisions, describes a procedure for accomplishment of the visual check and the decal.) (ii) If the check required by (i), above, is performed by other than the flight crew, the results of the check will be made known to the flight crew prior to each flight. (iii) Record the accomplishment of the check in a record maintained by the operator. (3) Modification of the door actuator mechanism and switchinstallation per Lockheed-California Company Service Bulletin 093-52-075 Revision 3 dated April 6, 1976, constitutes terminating action for the conduct of the repetitive inspections required by paragraph (a) of this AD. (b) Rework of galley door Link Arm Assemblies. (1) Within 250 flight hours after the effective date of this AD, unless previously accomplished, perform the removal and rework of eight galley door link arm assemblies as specified in Part 1 of Lockheed-California Company Service Bulletin 093-52-038, Revision Number 2, dated May 10, 1974, or later FAA-approved revisions. (2) Within 2500 flight hours of the effective date of this AD, unless previously accomplished, perform the rework of all spare galley door link arm assemblies specified in Part II of Lockheed-California Service Bulletin 093-52-038, Revision Number 2, dated May 10, 1974, or later FAA-approved revisions. Equivalent inspections, modifications and replacements may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. Airplanes may be flown to a base for the accomplishment of the inspections and replacements required by this AD, per FAR's 21.197 and 21.199. The manufacturer's specifications and procedures 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 these documents may obtain copies upon request to Lockheed-California Company, Post Office Box 551, Burbank, California 91520, Attention: Commercial Support Contracts. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108 or 15000 Aviation Boulevard, Hawthorne, California 90261, Room 6W14. Amendment 39-2194 became effective May 8, 1975. Amendment 39-2237 was effective June 18, 1975 for all persons except those to whom it was made effective by telegram dated May 23, 1975, which contained this amendment. This amendment 39-3985 becomes effective December 16, 1980.
93-01-07: 93-01-07 BEECH AIRCRAFT CORPORATION: Amendment 39-8461. Docket 92-NM-164- AD. Applicability: Model 400A series airplanes having serial numbers RK-1 through RK-32, inclusive; and Model 400T series airplanes having serial numbers TT-1 through TT-6, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent snagging of the end clevis fitting and kinking (and subsequent failure) of the emergency release cable of the main landing gear, which may prevent extension of the main landing gear, accomplish the following: (a) Within 100 flight hours after the effective date of this AD, replace the existing link assembly from the uplink mechanism of the main landing gear door with an improved link assembly, in accordance with Beechcraft Service Bulletin 2447, dated June 1992. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used ifapproved 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 replacement shall be done in accordance with Beechcraft Service Bulletin 2447, dated June 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, 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 March 2, 1993.
98-15-17: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company CF6-80A3 series turbofan engines. This action requires initial and repetitive on-wing borescope inspections of the left hand aft mount link assembly for cracks, bearing migration, and bearing race rotation, and, if necessary, replacement with serviceable parts. This amendment is prompted by a report of a fractured left hand aft mount link discovered during a scheduled engine removal. The actions specified in this AD are intended to prevent left hand aft mount link failure, which can result in adverse redistribution of the aft mount loads and possible aft mount system failure.
69-15-02: 69-15-02 BELL: Amdt. 39-815. Applies to Model 206A helicopters equipped with magnesium cyclic bellcrank support assemblies. Compliance required as indicated. To prevent failure of the magnesium cyclic bellcrank support assemblies, P/N 206-001- 521, due to fatigue cracks, accomplish the following: (a) Inspect the right- and left-hand support assemblies, P/N 206-001-521, that have accumulated 25 hours' total time in service after April 15, 1969, before the first flight of each day as follows: (1) Remove the upper forward cowling, P/N 206-061-801, to expose the hydraulic power cylinders. (2) Inspect the attachment of the support assemblies to the fuselage for firmness by grasping with the fingers. If the support assembly is loose, torque the nut on the NAS 1304-9 bolt to 80 to 100 inch-pounds and the nut on the NAS 1305-9 bolt to 120 to 145 inch-pounds. If a nut is inaccessible, torque the bolt head in accordance with the method described in paragraph 4 ofBell Helicopter Company Service Bulletin No. 206A-11 Revision A, dated July 23, 1969, or in accordance with a method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, FAA. (3) Inspect visually the right and left-hand support assemblies, P/N 206-001- 521, for cracks in the spotfaced areas around the attachment bolts and in the fillet radii between the base and vertical section of the supports, using a flashlight or equivalent. Both the forward and aft flange fillet radii and spotfaced areas must be inspected. (4) Smooth out any nicks or corrosion visible in the forward and aft flange fillet radii and the spotfaced areas, using a fine file and crocus cloth. (b) Remove and replace the support assembly before further flight if cracks are found. Inspect cyclic control rigging in accordance with paragraph 4-30 of the Model 206A Maintenance and Overhaul Instructions when the support assembly is replaced. (c) Remove and replace right- and left-hand magnesium support assemblies with new aluminum support assemblies, P/N 206-001-544, within 100 hours' time in service after the effective date of this AD in accordance with the procedures in Bell Helicopter Company Service Bulletin No. 206A-11 Revision A, dated July 23, 1969, or in accordance with a procedure approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, FAA. (d) The inspections in paragraph (a) are no longer required when aluminum bellcrank supports are installed in accordance with paragraph (c). (Bell Model 206A Maintenance and Overhaul Manual Interim Revision No. 206A-69-16 pertains partially to this subject.) This supersedes Amendment 39-746 (34 F.R. 6472), AD 69-07-03. This amendment becomes effective August 16, 1969.
2022-08-11: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited Model 429 helicopters. This AD was prompted by in-service reports of the loss of display and subsequent recovery of certain display units (DUs). This AD requires revising the existing rotorcraft flight manual supplement (RFMS) for your helicopter and disabling the traffic alert and collision avoidance system (TCAS) POP-UP feature for certain DUs. The FAA is issuing this AD to address the unsafe condition on these products.
2012-26-12: We are adopting a new airworthiness directive (AD) for all Thielert Aircraft Engines GmbH (TAE) TAE 125-02-99 and TAE 125-02-114 reciprocating engines. This AD requires inspection of the oil filler plug vent hole at the next scheduled maintenance or within 110 flight hours after the effective date of this AD. If chips are found to be blocking the vent hole, additional corrective action is required before next flight. This AD was prompted by an in-flight shutdown of an airplane equipped with a TAE 125-02-99 engine. We are issuing this AD to prevent engine in-flight shutdown or power loss, possibly resulting in reduced control of the airplane. [[Page 1729]]