Results
2011-10-17: We are superseding three existing airworthiness directives (ADs) that apply to 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 airworthiness limitations applicable to the Damage Tolerant Airworthiness Limitation Items (DT ALI) are currently listed in Airbus ALI Documents, which are referenced in the A300, A310, and A300-600 Airworthiness Limitations Section (ALS) Part 2. Airbus has recently revised the ALI Documents, which have been approved by the European Aviation Safety Agency (EASA). * * * * * The actions contained in these revised documents, which introduce more restrictive maintenance requirements and/or airworthiness limitations, have been identified as mandatory actions for continued airworthiness. * * * The unsafe condition isfatigue cracking, damage, or corrosion in principal structural elements, which could result in reduced structural integrity of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
83-15-07 R1: 83-15-07 R1 ROBINSON HELICOPTER COMPANY: Amendment 39-4762. Applies to Model R-22 series helicopters, certificated in all categories. Compliance is required as indicated (unless already accomplished). To detect cracks and to prevent possible fatigue failure of main rotor blades, accomplish the following prior to further flight after the effective date of this AD: (a) Conduct an inspection of the main rotor blades to determine the serial number of the installed main rotor blades. (b) Remove from service all Robinson main rotor blades P/N A016-1 Revision "W." Revision "W" main rotor blades have S/Ns 0600 through 0810. NOTE: Section 9.100 of the R-22 Maintenance Manual contains pertinent assembly/disassembly instructions, and Robinson Helicopter Company Bulletin No. 33 dated July 25, 1983, contains the same instructions as this airworthiness directive as well as shipping/warranty information. Main rotor blades removed by (b) should be either cut up in accordance with Robinson Helicopter Company Service Bulletin No. 33 or marked "UNAIRWORTHY" on both surfaces at approximately mid-span with lettering at least 2 inches high and "UNAIRWORTHY" impressed on the data plate using a metal stamp. (c) Equivalent means of compliance with the AD may be used when approved by the Manager, Western Aircraft Certification Field Office, FAA, P.O. Box 92007, Worldway Postal Center, Hawthorne, California 90009-2007. This amendment becomes effective November 21, 1983, as to all persons except those persons to whom it was made immediately effective by priority letter AD 83-15-07, issued July 28, 1983, which contained this amendment.
2010-06-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2010-06-51 that was sent previously to all known U.S. owners and operators of The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes by individual notices. This AD requires doing a detailed inspection of the inboard and outboard aft attach lugs of the left and right elevator control tab mechanisms for gaps between the swage ring and the aft attach lug, and between the spacer and the aft attach lug; trying to move or rotate the spacer using hand pressure; and replacing any discrepant elevator tab control mechanism, including performing the detailed inspection on the replacement part before and after installation. This AD is prompted by a report of failure of the aft attach lugs on the left elevator tab control mechanism, which resulted in severe elevator vibration. We are issuing this AD to detect and correct a loose bearing in the aft lug of the elevator tab control mechanism, which could result in unwanted elevator and tab vibration. The consequent structural failure of the elevator or horizontal stabilizer could result in loss of aircraft control and structural integrity.
2011-10-09: We are superseding an existing airworthiness directive (AD) for Cessna Aircraft Company (Cessna) 150, 152, 170, 172, 175, 177, 180, 182, 185, 188, 190, 195, 206, 207, 210, T303, 336, and 337 series airplanes. That AD currently requires repetitive inspections and replacement of parts, if necessary, \n\n((Page 27866)) \n\nof the seat rail and seat rail holes; seat pin engagement; seat rollers, washers, and axle bolts or bushings; wall thickness of roller housing and the tang; and lock pin springs. This new AD requires retaining all of the actions from the previous AD and adding steps to the inspection procedures in the previous AD. This AD was prompted by added steps to the inspection procedures, added revised figures, and clarification of some of the existing steps. We are issuing this AD to prevent seat slippage or the seat roller housing from departing the seat rail, which may consequently cause the pilot/copilot to be unable to reach all the controls. This failure could leadto the pilot/copilot losing control of the airplane.
2011-10-13: We are adopting a new airworthiness directive (AD) for the products listed above. 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: Since 2004, more than 30 reports have been received of in-flight loss of a rear passenger door on Diamond aeroplanes, the majority of which were DA 40. In additional, at least 18 doors have been replaced because of damage found on the hinge. Diamond Aircraft Industries conducted analyses and structural tests to determine the root cause of the door opening in flight. The conclusions were that the primary locking mechanism provided adequate strength to react to the loads in flight. It was also determined that the root cause was the crew not properly securing the rear passenger door by the main locking mechanism, prior to flight. Damage to the hinges has been caused primarily by external loads (wind gust conditions) while the aeroplane was parked. All DA 40 and DA 42 aeroplanes have a system installed that provides a warning if the main door latch is not fully closed and a secondary safety latch (with retaining bracket) design feature. The initial intended design function of the latch was to hold the rear passenger door in the ``near closed'' position while on the ground, protecting the door from wind gusts. However, the original retaining bracket Part Number (P/N) DA4-5200-00-69 might not hold the door in this ``near closed'' position while in flight. * * * This condition, if not corrected, could result in the rear passenger door opening and departing the aeroplane in flight. We are issuing this AD to require actions to correct the unsafe condition on these products.
96-15-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain propeller blades, identified by serial number, installed on Hartzell Propeller Inc. HC-B3TN, HC- B5MP, HC-E4A, and HC-D4N series propellers. This action requires, within specified hours time in service after the effective date of this AD, a one-time fluorescent dye penetrant inspection of a twelve-inch long area on both the face and camber sides of propeller blade shanks for forging flaws or cracks, and replacement of defective propeller blades with serviceable parts. In addition, this action requires this inspection prior to further flight for propellers that experience sudden or unusual vibration. This amendment is prompted by a report of an inflight propeller blade separation. The actions specified in this AD are intended to prevent propeller blade separation caused by propeller blade shank cracks emanating from forging flaws, which could result in loss of control of the aircraft.
96-15-03: This amendment supersedes an existing Airworthiness Directive (AD), applicable to Sikorsky Aircraft Model S-76B helicopters, that requires an inspection of the drive shaft for cracks or loose balance weights. This amendment also supersedes a Priority Letter AD that currently requires repetitive inspections for cracks in the driveshaft in helicopters with certain engine drive shaft assemblies (drive shafts) installed. This amendment is prompted by a report of a fatigue crack found in a drive shaft that was caused by fretting of a balance weight rivet washer. The actions specified by this AD are intended to prevent failure of the drive shaft, loss of power to the rotor system, and a subsequent forced landing of the helicopter.
83-14-03: 83-14-03 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39- 4683. Applies to Models P68 and P68B (all serial numbers (SN) up to 128, excluding SNs 40, 112, 125, 126 and 127) airplanes certificated in any category. Compliance: Required within the next 100 hours after the effective date of this Airworthiness Directive (AD), unless already accomplished. To prevent failure of the fin rear spar, accomplish the following: a) Install fin spar reinforcement in accordance with Partenavia Costruzioni Aeronautiche S.p.A. Service Bulletin (SB) No. 34, Rev. 1, dated February 15, 1978, and Drawing No. R.0007, dated December 23, 1977. b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. c) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on August 19, 1983.
2010-07-06: 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: There has been an incident during a production flight test where the proximity-sensor electronic unit (PSEU) failed. This resulted in unannunciated loss of: Wheel brakes below 10 knots; Thrust reverser; Nose wheel steering; and Auto-deployment of the multi-function spoilers. A similar condition, if not corrected, may result in reduced controllability of the aircraft upon landing and possible overrun of the runway. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
93-02-04: 93-02-04 DE HAVILLAND: Amendment 39-8486. Docket No. 91-CE-48-AD. Supersedes AD 77-03-07, Amendment 39-3100. Applicability: Model DHC-6-1/100/200/300 airplanes (serial numbers 2 through 494, 497 through 503, 505, and 507), certificated in any category, that have not incorporated Modification 6/1594 in accordance with Part C of the ACCOMPLISHMENT INSTRUCTIONS section of de Havilland Service Bulletin (SB) 6/348, which incorporates the following pages: Pages Revision Level Date 5-8, 13-16, and 23-25 Original July 16, 1976 9-12, and 17-22 Revision A August 30, 1976 1-4 Revision C July 15, 1977 Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent failure of the elevator support assembly, which could result in loss of control of the airplane, accomplish the following: (a) Within the next 25 hours time-in-service (TIS), unless already accomplished within the last 175 hours TIS, and thereafter at intervals not to exceed 200 hours TIS until Modification No. 6/1594 is incorporated as specified in paragraph (b) of this AD, accomplish the following: (1) Visually inspect the floor structure channel members, part numbers C6FS1229-37 and C6FS1229-31, for cracks in the area around the lower pivot bearing housing in accordance with the instructions in Part A of de Havilland SB No. 6/348. If cracks are found, prior to further flight, repair or replace any cracked components in accordance with Part B or C of the ACCOMPLISHMENT INSTRUCTIONS section of de Havilland SB No. 6/348. (2) Visually inspect the top and bottom flanges of the hydraulic hand pump fitting, part number C6FSM1293-27, for cracks immediately behind the front bolt boss in accordance with Part A of the ACCOMPLISHMENT INSTRUCTIONS section of de Havilland SB No. 6/348. If cracks are found, prior to further flight, repair or replace in accordance with Part B or C of the instructions in de Havilland SB No. 6/348. (3) If the replacement requirements of paragraphs (a)(1) and (a)(2) of this AD are accomplished in accordance with Part C of the ACCOMPLISHMENT INSTRUCTIONS section of de Havilland SB No. 6/348, then the inspection requirements of this AD are no longer required. (b) Within the next 2,400 hours TIS, unless already accomplished as specified in paragraph (a)(3) of this AD, incorporate Modification 6/1594 in accordance with Part C of the ACCOMPLISHMENT INSTRUCTIONS section of de Havilland SB 6/348. This modification is considered terminating action for the inspection requirements of this AD. (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) 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, New York Aircraft Certification Office, FAA, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York Aircraft Certification Office. (e) The inspections and modification required by this AD shall be done in accordance with de Havilland Service Bulletin 6/348, which consists of the following effective pages: Pages Revision Level Date 5-8, 13-16, and 23-25 Original July 16, 1976 9-12, and 17-22 Revision A August 30, 1976 1-4 Revision C July 15, 1977 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 de Havilland, Inc., 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5 Canada. 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, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment (39-8486) supersedes AD 77-03-07, Amendment 39-3100. (g) This amendment becomes effective on March 19, 1993.