Results
99-06-17: This action confirms the effective date of Airworthiness Directive (AD) 99-06-17, which applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. AD 99-06-17 requires installing a support bracket and a cut-out relay for the second generator control unit. AD 99-06-17 also requires making all the wiring additions and adjustments necessary for the above-referenced installations. This AD was the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified in this AD are intended to prevent damage to electrical components because incorrectly connected cables or broken or damaged wires cause excessive voltages to the second generator, which could result in loss of electrical power during any phase of flight.
76-05-09: 76-05-09 AER PEGASO (AEROMERE & AVIONAUTICA RIO): Amendment 39-2544. Applies to M100S gliders, certificated in all categories. Compliance is required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent separation of lower rudder hinge pin from the rudder hinge bracket and the consequent loss of rudder control, accomplish the following: Replace the lower rudder hinge pin with a new pin made of SAE 1024 steel and inspect the new pin's weld for cracks, using the dye penetrant method, in accordance with the steps (1) through (9) of the Description section of Ingg. A. & P. Morrelli (Aer Pegaso) Technical Bulletin No. 11/M100S, dated March 16, 1971, or an FAA- approved equivalent. This amendment becomes effective March 25, 1976.
2012-16-05: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -200 freighter series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires modification of the control circuit for the fuel pumps for the center fuel tanks for certain airplanes, and center and rear fuel tanks for certain other airplanes. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
99-09-18: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 and Mark 0100 series airplanes, that currently requires a one-time inspection for heat damage of the fuselage skin and stubwing structure; either repetitive tests of certain seals or repair of heat damage, as necessary; and eventual replacement of corrujoint seals with new, improved seals. This amendment adds a requirement for repetitive inspections for heat damage of the subject area, and provides for a new optional terminating action for the repetitive inspections. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent leakage of hot air from the corrujoint seals of certain valves in the stubwings, and subsequent heat damage of the fuselage skin and stubwing structure, which could result in reduced structural integrity of theairplane. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 8, 1999. The incorporation by reference of certain other publications as listed in the regulations, was approved previously by the Director of the Federal Register as of May 14, 1998 (63 FR 17318, April 9, 1998).
75-24-11: 75-24-11 BEECH: Amendment 39-2437. Applies to all civilly certificated Models A45 (Military T-34A, B-45) and D45 (Military T-34B) airplanes. Compliance: Required as indicated, unless already accomplished. To prevent failure of the P/N 45-524504 and 45-524505 rudder-aileron bungee interconnect cable assembly and the P/N 45-524697 or P/N 45-524028 bellcrank assembly, accomplish the following: A) On Model A45 (Military T-34A, B-45) airplanes not incorporating P/N MS- 20219-2 pulleys (1.75 inch O.D.) per Beech Kit 45-325 and Beech P/N 105740B-ZF-0105 bronze bushings per Beech Drawing 45-000060, Rev. C, or later revision, within 50 hours' time in service after the effective date of this AD, or within 100 hours' time in service after the last inspection per AD 62-27-01, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, accomplish Paragraphs 1(a) and 1(b). B) On Models A45 (Military T-34A, B-45) and D45 (Military T-34B) airplanes incorporating P/N MS-20219-2 pulleys (1.75 inch O.D.) per Beech Kit 45-325 and Beech P/N 105740B-ZF-0105 bronze bushings per Beech Drawing 45-000060, Rev. C, or later revision, within 50 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 300 hours' time in service from the last inspection, accomplish Paragraphs 1(a) and 1(b). 1. (a) Disconnect the turn buckles P/N 45-524504 and 45-524505 rudder-aileron bungee interconnect cable assemblies, visually inspect the cables and replace frayed, internally broken or excessively worn cables. (b) Disconnect the two AN 161-8RS forks that attach to the P/N 45- 524697 or P/N 45-524028 bellcrank assembly and visually inspect the 3/16-inch diameter holes in the bellcrank for elongation or cracks. If elongation exceeds 0.02 inches or if cracks are found, replace the bellcrank. If no elongation or cracks are found, lubricate the holes in the bellcrank prior to reinstallation of theAN 161-8RS forks. 2. The airplane may be flown in accordance with FAR 21.197 to a location where parts replacement can be accomplished. 3. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Beechcraft Service Bulletin No. 32 on Model A45 (Military T-34A, B-45) airplanes covers the cable inspection. This AD supersedes AD 62-27-01. This amendment becomes effective November 28, 1975.
2012-16-10: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by chafing on high pressure fuel lines due to improper installation of an expandable pin on the lower cowl assembly. This AD requires installing spring clips and repositioning the lanyard attachment points at the forward end and the forward firefloor of the lower cowl. We are issuing this AD to prevent chafing of the high pressure fuel lines, which if not corrected, could cause fuel leakage in a fire zone.
75-04-12: 75-04-12 BELLANCA: Amendment 39-2093. Applies to Model 8GCBC Airplanes, Serial Numbers 1-74 through 119-74, 120-75 through 153-75 certificated in all categories. Compliance required within the next 10 hours time in service after the effective date of this airworthiness directive, unless already accomplished. To prevent possible resonant vibratory conditions with McCauley Model 1A200/HFA fixed pitch propellers installed on Lycoming 0-360-C2A, or -C2E type engines, accomplish the following in accordance with Bellanca Service Letter Number 115 and Bellanca Service Kit Number 245. (a) Remove existing markings on the tachometer instrument glass and affix Mylar decal, Bellanca P/N 1-10443. The decal is properly affixed when: a green arc extends from 500 to 1700 RPM; a yellow arc from 1700 to 2100 RPM; a green arc from 2100 RPM to 2700 RPM; and a red radial is positioned at 2700 RPM. (b) Install Bellanca P/N 1-10437, placard "AVOID 1700-2100 DURING DESCENT", on thetachometer instrument glass below the hour meter. (c) Accomplish Revision Number 1 to existing FAA Approved Airplane Flight Manual (AFM) in accordance with AFM revisions page. This amendment becomes effective February 21, 1975.
2012-16-06: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-600 series airplanes and Model A310-203, -204, - 221, and -222 airplanes. This AD was prompted by a report of a capacitive density condensator (cadensicon) coil overheating during testing. This AD requires an inspection to determine if a certain fuel quantity indication computer (FQIC) is installed, replacement of identified FQICs, and modification of the associated wiring. We are issuing this AD to detect and correct potential overheating of the cadensicon coil, which could create an ignition source inside a fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
67-18-03: 67-18-03 LOCKHEED: Amendment 39-423 as amended by Amendment 39-1601. Applies to Model 382 and 382B series airplanes, serial numbers 3946 and 4101 through 4196. Compliance as indicated. (a) For airplanes with 2350 or more hours' total time in service on the effective date of this AD comply with paragraph (c) within the next 50 hours' time in service, and thereafter at intervals not to exceed 800 hours' time in service from the last inspection. (b) For airplanes with less than 2350 hours' total time in service on the effective date of the AD comply with Paragraph (c) before the accumulation of 2400 hours' total time in service, and thereafter at intervals not to exceed 800 hours' time in service from the last inspection. (c) Inspect all eight affected engine mount truss assemblies in accordance with the tooling and inspection instructions given in Lockheed-Georgia Service Bulletin 82-153 dated December 1, 1966, Section 1f and 2a through 2e, respectively, or later FAA approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (1) Cracked parts shall be replaced with new parts having the same part number, or with the applicable updated part specified in Section 2g of Lockheed-Georgia Service Bulletin 82-153 dated December 1, 1966, or later FAA approved revision. Replacement truss assemblies shall be installed according to the replacement instructions given in Section 2h through 2aa in the above Service Bulletin, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. (2) Replacement of cracked trusses shall be accomplished before further flight, except that one flight may be made for the purpose of obtaining the necessary replacements in accordance with the provisions of FAR 21.197. (d) When a particular truss assembly is replaced with the applicable updated part specified in Section 2g of Lockheed-Georgia Service Bulletin 82-153dated December 1, 1966, or later FAA approved revision, the repetitive inspection of that truss as required by this AD may be discontinued. Lockheed-Georgia Service Bulletin 82-153, dated December 1, 1966, covers this same subject. Amendment 39-423 became effective June 25, 1967. This Amendment 39-1601 becomes effective March 12, 1973.
2018-05-06: We are superseding Airworthiness Directive (AD) 2016-09-12, which applied to certain The Boeing \n\n((Page 9689)) \n\nCompany Model 787-8 and 787-9 airplanes. AD 2016-09-12 required repetitive inspections of the bilge barriers located in the forward and aft cargo compartments for disengaged decompression panels, and reinstalling any disengaged panels. This AD retains the actions required by AD 2016-09-12 and requires replacing the existing decompression panels with new panels and straps, which terminates the repetitive inspections. This AD also removes airplanes from the applicability. This AD was prompted by a terminating modification developed to address the unsafe condition. We are issuing this AD to address the unsafe condition on these products.