Results
47-32-17: 47-32-17 BELLANCA: (Was Mandatory Note 7 of AD-773-5.) Applies to Models 14- 13, 14-13-2 Serial Numbers 1060, and Up. Compliance required prior to October 15, 1947. Improper positioning of the inspection covers on the top surface of each wing at the landing gear retracting sprocket can cause malfunctioning of the gear retracting mechanism. This cover is held in place by two spring clips, and if the cover is installed with the clips running in a chordwise direction, it is possible that the ends of the clips will bear against the chain and force it off the sprocket, jamming the system. Inspect the covers on your airplane for proper installation, and paint arrows on the cover and wing surface so that the arrows point toward each other when the spring clips run spanwise. (Bellanca Service Bulletin No. 10 covers this same subject.)
91-12-07: 91-12-07 WYTWORNIA SPRZETU KOMUNEKACYJNEGO PZL-MIELEC: Amendment No. 39-7018. Docket No. 91-CE-07-AD. Applicability: Model M18 airplanes (serial numbers (S/N) 1Z013-21 through 1Z023-30), equipped with an agriculture equipment electro-hydraulic control system (Modification D73.701.00.1), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the electro-hydraulic control system that results in loss of flap and brake control, accomplish the following: (a) For S/N 1Z013-21 through 1Z023-30 airplanes, upon the accumulation of 200 hours time-in- service (TIS) or within the next 25 hours TIS after the effective date of this AD, whichever occurs later, replace each flexible hose having part number (P/N) D73.7/21.00.0 or D73.7/24.00.0. with a new hose in accordance with the instructions in PZL-Mielec Mandatory Engineering Bulletin (MEB) No. K/02.141/90, dated April 1990. (1) If hoses are replaced with either P/N D73.7/21.00.0 or D73.7/24.00.0, replace these hoses at intervals not to exceed 200 hours TIS. (2) If hoses are replaced with P/N D73.7/26.00.0 or D73.7.25.00.0 hose, no further action is required. (b) For S/N 1Z013-21 through 1Z022-05 airplanes, upon the accumulation of 500 hours TIS or within the next 100 hours TIS after the effective date of this AD, whichever occurs later, modify the electro- hydraulic control system in accordance with the instructions in Paragraph III, 2. of PZL-Mielec MEB No. K/02.141/90, dated April 1990. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/oAmerican Embassy, B-1000, Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. (e) The modifications and replacements required by this AD shall be done in accordance with PZL-Mielec Mandatory Engineering Bulletin No. K/02.141/90, dated April 1990. 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 PZL-Mielec, Ludowego Wojska Polkiego 3, 39-300 Mielec, Poland. 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; Room 8401, Washington, DC. This amendment (39-7018, AD 91-12-07) becomes effective on July 5, 1991.
2022-11-05: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by a report of the loss of the nuts at all four fastener locations common to the outboard flap inboard support rear spar attachment fittings, which affects the retention feature of the fasteners and leaves the fasteners susceptible to migrating out of the joint. This AD requires repetitive detailed inspections for discrepancies of the fasteners and shim of the wing rear spar at certain outboard flap supports; a detailed inspection for damage of the shim, flap support mechanism, and wing lower skin; installation of new fasteners and shims; and repair or replacement of damaged parts. The FAA is issuing this AD to address the unsafe condition on these products.
92-27-21: 92-27-21 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-8575. Docket Number 92-ASW-45. Applicability: Model 205A-1 and 205B series helicopters, with increased diameter tail rotor drive shaft (drive shaft), P/N 204-040-620-011, installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the drive shaft, loss of tail rotor control, and subsequent loss of control of the helicopter, accomplish the following: (a) Within 25 hours' time-in-service after the effective date of this AD: (1) Conduct a one-time inspection of the helicopter and the drive shaft in accordance with paragraphs 1 through 4 of the Accomplishment Instructions of BHTI Alert Service Bulletin (ASB) 205-92-49, dated October 5, 1992, for BHTI Model 205A-1 helicopters, and ASB 205B-92-13, dated October 5, 1992, for BHTI Model 205B helicopters. (2) Reassemble the tail rotor drive shaft assembly in accordance with paragraph 5 of the pertinent ASB to ensure a minimum of 0.50 inch clearance is obtained between the tail rotor drive shaft tunnel (drive shaft tunnel) and the drive shaft. (b) Each time the starter generator is installed after maintenance, ensure a minimum of 0.50 inch clearance is maintained between the drive shaft tunnel and the drive shaft. Adjust the position of the drive shaft tunnel in accordance with paragraph 5 of the pertinent ASB to obtain proper clearance. (c) Remove unairworthy parts found during the inspection required in paragraph (a) and replace with airworthy parts before further flight. (d) 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, Rotorcraft Certification Office, FAA, Rotorcraft Directorate, Fort Worth, Texas 76193-0170. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Certification Office. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished. (f) The inspection, removal, and replacement, if necessary, and reassembly shall be done in accordance with the applicable BHTI ASB 205-92-49 or 205B-92-13, both dated October 5, 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 Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 4400 Blue Mound Road, bldg. 3B, room 158, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on July 7, 1993, to all persons except those persons to whom it was made immediately effective by Priority Letter AD 92-27-21, issued January 7, 1993, which contained the requirements of this amendment.
2022-12-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports of oxygen leaks caused by cracked, brittle, or broken oxygen hoses that were found during scheduled maintenance tests of the airplane oxygen system. This AD requires an inspection of the oxygen hose assembly to determine if an affected part number is installed, and replacement of affected oxygen hoses. For certain airplanes, this AD allows repetitive testing of the oxygen system until affected hoses are replaced. This AD also prohibits installation of an affected oxygen hose. The FAA is issuing this AD to address the unsafe condition on these products.
99-06-16: This amendment adopts a new airworthiness directive (AD), applicable to CFM International CFM56-5 series turbofan engines, that reduces the low cycle fatigue (LCF) retirement lives for certain high pressure turbine rotor (HPTR) front air seals, and provides a drawdown schedule for those affected parts with reduced LCF retirement lives. This amendment is prompted by results of a refined life analysis performed by the manufacturer that revealed minimum calculated LCF lives significantly lower than the published LCF retirement lives. The actions specified by this AD are intended to prevent a LCF failure of the HPTR front air seal, which could result in an uncontained engine failure and damage to the aircraft.
99-06-07: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 and SD3-60 SHERPA series airplanes, that requires repetitive inspections to detect corrosion and/or wear of the top and bottom shear decks of the left and right stub wings in the area of the forward pintle pin of the main landing gear (MLG), and repair, 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 detect and correct corrosion and/or wear of the top and bottom shear decks of the left and right stub wings in the area of the forward pintle pin of the MLG, which could result in failure of the MLG to extend or retract.
2013-17-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL- 600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of erratic pitch movement and oscillatory behaviors of the elevator control system. This AD requires repetitive replacement of the bellcrank supports on the inner rear spar of the horizontal stabilizer with new, improved bellcrank supports. We are issuing this AD to prevent erratic pitch movement and transient accelerations, which could result in a significant pitch upset, and injuries to passengers and flightcrew.
99-06-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires removing the "Alternate Flap System" from the airplane flight controls and inserting a temporary revision that specifies this change in SECTION 2 - LIMITATIONS of the PC-12 Pilot's Operating Handbook. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to preclude improper use of the "Alternate Flap System", which could result in flap asymmetry with consequent reduced or loss of control of the airplane.
83-02-51: 83-02-51 BELL HELICOPTER TEXTRON, INC: Amendment 39-4842. Applies to Bell Helicopter Textron Models 222 and 222B helicopters certified in all categories equipped with main rotor controls walking beam assembly Part Numbers 222-010-415-5 and -9. Note that the -5 assembly contains a -7 detail beam and the -9 assembly contains a -11 detail beam. Beam assemblies may be identified in the area of their serial numbers by their detail numbers instead of their assembly numbers. The -7 and -11 details are included in this AD. (Airworthiness Docket No. 83-ASW-6.) Compliance is required as indicated (unless already accomplished). To prevent failure of the walking beam, accomplish the following: (a) Before further flight, remove and inspect walking beam assemblies Serial Numbers VN07-1O7 through VN07-140, VN06-057, VN06-060, VN06-061, VNO6-065, VN06- 069, VN06-089 through VN06-092, VN06-095, VN06-096, VNO6-100, EA-004, and EA-008 as follows: (1) Remove all grease fittings from the walking beam. (2) Using a magnifying glass of at least 10-power magnification and a bright light, inspect each one of the threaded holes from which the grease fittings were removed for evidence of corrosion, trapped foreign material, or thread indentations caused by foreign material having been trapped between the grease fittings and the threads. Of special interest is the presence of shot-peening residue. This residue will have the appearance of small round balls similar to shotgun pellets. These balls may be as small as 0.012 inch in diameter and are difficult to see unless a magnifying glass and bright light are used. (3) If any of the above defects are present, remove the part from service and replace it with a serviceable part. (4) If no defects are found, reinstall the grease fittings with wet zinc chromate primer on the threads. (b) Before further flight and prior to the first flight of each day, conduct the following inspections of all walking beam assembly Part Numbers 222-010-415-5 and -9, regardless of serial number, with emphasis on the area around the grease fittings in the portion of the beams through which the drive links are attached by bolts part number 20-057-9-95D. Remove cracked parts from service before further flight and replace with serviceable parts. (c) Within 10 hours time in service following the effective date of this AD, and each 25 hours thereafter, conduct a dye penetrant inspection of a 2-inch diameter area around the grease fittings described in paragraph (b) above. The area shall be prepared for penetrant inspection by thorough cleaning using Stoddard solvent or equivalent. Do not use methyl-ethyl- ketone (MEK) or paint stripper. Remove cracked parts from service before further flight and replace with serviceable parts. NOTE: Bell Alert Service Bulletin (ASB) 222-83-18 is an equivalent means of compliance with paragraph (b) of this AD. The inspections required in paragraph (b) maybe performed with the parts installed on the helicopter. Any other equivalent means of compliance with this AD must be approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, Southwest Region. (d) The helicopter may be flown to a repair base for the above inspections under the provisions of FAR 21.197. This amendment becomes effective May 15, 1984, as to all persons except those to whom it was made immediately effective by telegraphic AD T83-O2-51 issued January 21, 1983, which contained this amendment.