Results
67-22-05: 67-22-05 BRITISH AIRCRAFT: Amdt. No. 39-447, Part 39, Federal Register July 20, 1967. Applies to Models BAC 1-11 203/AE, 204/AF, 212/AR, 401/AK, and 410/AQ Series Airplanes. Compliance required as indicated. To prevent the use of unserviceable dropout oxygen mask face pieces, accomplish the following: (a) Within the next 600 hours' time in service after the effective date of this AD, unless already accomplished within the last 600 hours' time in service, and thereafter at intervals not to exceed 1,200 hours' time in service from the last inspection, visually examine all oxygen mask face pieces, Part Nos. WK 28420, WK 28171, and WK 31342, for deterioration in accordance with BAC 1-11 Alert Service Bulletin 35-A-PM 2795, Issue No. 1, dated January 16, 1967, or later ARB-approved issue, or FAA-approved equivalent. (b) Replace deteriorated oxygen mask face pieces found during the inspections required by paragraph (a) with either serviceable face pieces of the same partnumber or modified face pieces, Walter Kidde Part Nos. WK 33298, WK 33299, and WK 33300, in accordance with BAC Service Bulletin 35-PM 2795, or later ARB-approved issue, or FAA-approved equivalent, before further flight. (c) The repetitive inspections required by paragraph (a) may be discontinued when the oxygen face mask pieces are modified in accordance with BAC Service Bulletin 35-PM 2795, or later ARB-approved issue, or FAA-approved equivalent. This amendment effective August 19, 1967.
2017-17-08: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-500 and -600 series airplanes. This AD was prompted by a quality control review on the final assembly line, which determined that the wrong aluminum alloy was used to manufacture several structural parts. This AD requires a one-time eddy current conductivity measurement of certain cabin and cargo compartment structural parts to determine if an incorrect aluminum alloy was used, and replacement of any affected part with a serviceable part. We are issuing this AD to address the unsafe condition on these products.
2017-17-11: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a report indicating that, under certain operational takeoff conditions, the available thrust in relation with the N1 indication is less than a certified value, which could affect the safety margins with an engine failure during takeoff. This AD requires modifying each engine by updating the electronic engine control (EEC) software and adjusting the engine N1 trim value, and revising the airplane flight manual (AFM). We are issuing this AD to address the unsafe condition on these products.
55-21-02: 55-21-02 PIPER: Applies to All Model PA-23 Aircraft Through Serial Number 23-321, Except Serial Numbers 23-310, -311, -315, and -319. Compliance required as indicated. The wing front spar attachment fitting P/N 17079 at the centerline of the fuselage must be inspected and reinforced as indicated below. This is a welded steel fitting bolted to the front face of the front spar web and is accessible through the wing bottom access panel. I. Compliance required prior to next flight and at every 15 hours thereafter. Visually inspect the wing front spar attachment fitting and if any damage is found such as bent flanges or any other visible distortion contact the Piper Corp. for further instruction prior to returning airplane to flight status. II. Compliance required prior to November 1, 1955. If inspection of item I discloses no defects install reinforcement fitting assembly in accordance with Piper reinforcement Kit 754112 or equivalent. The inspections required in item I are not required after incorporating the fitting reinforcement. (Piper Service Bulletin No. 142 dated October 4, 1955, covers this same subject.)
67-09-02: 67-09-02 BRANTLY: Amdt. 39-373 Part 39 Federal Register March 21, 1967. Applies to Models B-2, B-2A, and B-2B Helicopters with P/N B2-324 Transmission Serial Numbers Prior to Serial Number 307. Compliance required as indicated. To improve the service life and reliability of the upper main rotor mast bearing, within the next 100 hours' time in service after the effective date of this AD, remove the Fafnir P/N 212K bearing presently installed and replace it with an Indiana Gear Works P/N 4524A56, Revision E, sealed bearing. This substitution is to be accomplished as prescribed by Brantly Helicopter Company Service Bulletin No. 21 and applicable sections of the Model B-2 Series helicopter maintenance manuals. This directive effective April 20, 1967
54-20-01: 54-20-01 AIRCRAFT BELT AND TRIM (SAFETY BELT): Applies to Model LBM-1900 (Dwg. No. 19001) Safety Belts Manufactured Prior to April 1, 1954. Compliance required as soon as possible but not later than March 1, 1955. Based on a complaint alleging noncompliance with strength standards of FAA Technical Standard Order C22, verification tests were conducted by the National Bureau of Standards at FAA request, which revealed that the belt assemblies of this make and model manufactured prior to April 1, 1954, with LBM-1900-3 and -3A buckles, were under strength for a majority of specimens tested. These tests are considered as evidence of nonconformance with terms of the TSO. Therefore, TSO-labeled belts of this model as noted above which were manufactured prior to April 1, 1954, can no longer be considered as complying with the prescribed airworthiness standards and, accordingly, must not be used in civil aircraft. Belts of this model manufactured subsequent to April 1,1954, incorporate a buckle of improved design and tests reveal this belt assembly to be in accordance with TSO-C22 tension test requirements. This supersedes AD 54-03-01.
66-29-01: 66-29-01 BOEING: Amdt. 39-301 Part 39 Federal Register November 5, 1966. Applies to Model 727 Series Airplanes. \n\n\tCompliance required as indicated. \n\n\tTo prevent loss of the cowl panels in flight, and resulting damage to the aircraft structure, accomplish the following or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region: \n\n\t(a)\tWithin the next 1,500 hours' time in service after the effective date of this AD, unless already accomplished, modify the side engine cowl panel latch assemblies in accordance with Boeing Service Bulletin No. 71-14 or later FAA-approved revision. Replacement of Hartwell Manufacturing Company hook latch spring, P/N 104914-1, with P/N 106054-1 is optional. \n\n\t(b)\tWithin the next 3,000 hours' time in service after the effective date of this AD, unless already accomplished, modify the center engine cowl panel latch frames in accordance with Boeing Service Bulletin No. 71-27 or later FAA-approved revision. \n\n\tThisdirective effective December 5, 1966.
2017-17-09: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by a manufacturer's review that showed that the fuel tank access door at a certain wing buttock line did not have an engineered ground path with the mating wing structure. This AD requires replacing the fuel tank access door, doing a check of the electrical bond, doing related investigative and corrective actions if necessary, and revising the maintenance or inspection program by incorporating an airworthiness limitation (AWL). We are issuing this AD to address the unsafe condition on these products.
55-14-02: 55-14-02 PIPER: Applies to Model PA-23 Serial Numbers 23-1 to 23-208 Inclusive. Compliance required by August 1, 1955. Because of possible damage to the hydraulic actuating cylinders for the landing gear system and flap system of the two end plug retaining pins, as a result of excessive pressures caused by thermal expansion, it is necessary that these cylinders be inspected and replaced or modified as follows: 1. If the cylinder housing is upset or fractured, it must be replaced by a new reinforced cylinder P/N 455927. (Piper Service Bulletin No. 138 dated May 9, 1955, covers this same subject.) 2. If the cylinder housing is not upset or fractured, it must either be replaced by P/N 455927, or reinforced by adding two retaining plugs in accordance with Piper Service Letter No. 250 dated June 8, 1955. This supersedes AD 55-12-01.
2017-16-04: We are adopting a new airworthiness directive (AD) for Romtex torso restraint systems (restraint systems) installed on but not limited to Airbus Helicopters Model AS350B2, AS350B3, EC130B4, EC130T2, and AS355NP helicopters. This AD requires replacing certain restraint system buckles. This AD was prompted by a report of several restraint system buckle knobs breaking. The actions of this AD are intended to correct an unsafe condition on these products.