Results
52-05-02: 52-05-02 MARTIN: Applies to All Models 202 and 202A Aircraft. Compliance required as indicated. Due to a reported occurrence of cracks in the center wing rear spar lower chord fitting at the Station 187 rib, the following shall be accomplished: A. Inspect within the next 100 hours. Inspect the fittings (P/N 2021U44473 and 2021U44474) with a 10-power magnifying glass after removal of the paint with a solvent. Pay particular attention to the intersection of the spar leg with the other legs of the fittings. B. If cracks are discovered in the base or extending into the base of a fitting, the part must be replaced. C. If cracks are found in the vertical legs only, the part can either be replaced or remain installed in the airplane. If remaining installed, the fitting must be inspected every 85 hours in accordance with items A and B. Other inspection intervals may be approved based on the evaluation of the actual crack location by the manufacturer. D. For fittings that do not show any cracks, loosen the two bolts through the fitting, the spar stiffener and the spar chord tang. Also loosen the two spar web splice bolts through the fitting, the spar web stiffeners and rib 187 web. If any gap appears between the fitting and its mating surfaces, install shims so as to reduce this gap to less than 0.010 inch. E. New parts installed shall be shimmed in accordance with item D. (Glenn L. Martin Service Instruction Letter No. 17 covers this same subject.)
56-01-02: 56-01-02 BOEING: Applies to All model 377 Aircraft. Compliance required as indicated. As a result of cracks discovered at wing spar splice bolt holes the following inspection and possible rework is required. At the next basic check period and subsequent thereto, at each basic check period but not to exceed an interval of 2,500 hours flight time, the No. 1 bolt hole in each rear spar Station 246 joint and Nos. 1 and 6 bolt holes in each front and rear spar Station 510 joints shall be carefully inspected by use of borescope or equivalent method. If cracks are found, the splice should be reworked in accordance with instructions contained in Boeing Service Letter No. 289. Within the next 500 flight hours, unless recently accomplished, the outboard bolt holes in each front and rear spar Station 47.75 joints shall be inspected for cracks by use of borescope or equivalent method. If cracks are found, they shall be repaired in accordance with Boeing Instructions. This supersedes AD 55-23-01.
2005-09-08: The FAA is superseding two existing airworthiness directives (ADs); both apply to the same certain McDonnell Douglas Model MD-90-30 airplanes. The superseded ADs currently require a one-time general visual inspection to detect wire chafing damage and to determine adequate clearance between the disconnect panel structure and the wires above the aft left lavatory; and corrective actions, if necessary. This new AD retains those requirements and clarifies certain requirements for recording AD compliance. This AD is prompted by the determination that the form of the existing ADs could result in confusion to operators in recording compliance with the potentially conflicting requirements. We are issuing this AD to prevent damage to certain wires due to contact between the wires and the adjacent structure, which could result in electrical arcing and consequent smoke and fire in the cabin. \n\nDATES: Effective May 20, 2005. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin MD90-24A074, excluding Appendix, Revision 02, dated June 3, 2003, as listed in the regulations, was approved previously by the Director of the Federal Register as of February 22, 2005 (70 FR 5920, February 4, 2005). \n\n\tWe must receive comments on this AD by July 5, 2005.
55-11-02: 55-11-02 PIPER: Applies to Model PA-23 Serial Numbers 23-1 to 23-142 Inclusive, 23- 144 to 23-162 Inclusive, 23-164 to 23-173 Inclusive, 23-175 to 23-177 Inclusive, 23-179 to 23- 183 Inclusive, and 23-186. Compliance required by August 1, 1955. In order to eliminate excessive pressures in the hydraulic system due to thermal expansion which can result in failure of the hydraulic actuating cylinders, it will be necessary to install thermal relief valves in the landing gear retraction line, landing gear extension line and the flap retraction line. These relief valves are to be installed in accordance with the sketch and instructions contained in Piper Thermal Relief Valve Kit 754 095. (Piper Service Bulletin No. 136 dated April 26, 1955, covers this same subject.)
74-15-07: 74-15-07 BELLANCA AIRCRAFT CORPORATION: Amendment 39-1901. Applies to Bellanca Models 8GCBC aircraft Serial Numbers 2-74 to an including 62-74. Before further flight, verify that the propeller is properly indexed to the crankshaft flange. This can be accomplished by removing the upper cowling and examining the aft face of the crankshaft flange to determine if the shoulders of all six bushings are seated upon the rear face of flange. If incorrectly indexed, two bushing shoulders will be approximately 1/16 inch off flange surface. If incorrect, propeller and spacer must be removed and all parts inspected for damage and replaced as necessary. If undamaged, replace spacer and propeller, assuring proper indexing to crank flange and torque six bolts to 660-780 inch pounds. This amendment is effective July 26, 1974, and was effective July 2, 1974, for all recipients of the telegram dated July 2, 1974, which contained this amendment.
2005-07-13: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767-300 and -400ER series airplanes. This AD requires replacing the in-flight entertainment cooling card, located in the P50 card file in the main equipment center, with a new, improved cooling card. This AD is prompted by a report of an improperly designed component on the in-flight entertainment (IFE) cooling card, which may cause the IFE cooling system to incorrectly interpret signals from airplane system interfaces. We are issuing this AD to prevent failure of the IFE cooling card to configure itself correctly in response to input signals from airplane system interfaces during a forward cargo fire, which \ncould result in the IFE cooling fan causing smoke to penetrate occupied areas of the airplane.
2010-17-11: 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: Friction or contact between a propeller de-ice bus bar and the backplate assembly can cause failure of the bus bar and a consequent intermittent short circuit. Such a short circuit can cause a dual AC generator shutdown that, particularly in conjunction with an engine failure in icing conditions, could result in reduced controllability of the airplane. We are issuing this AD to prevent an in-flight double generator failure, which could result in reduced controllability of the airplane.
49-06-04: 49-06-04 BOEING: Applies to Model 377 Aircraft. The 11 convolution type altitude compensating bellows, Bendix P/N 390935, shall be replaced with new bellows after each 100 hours of operation until the 9 convolution type Bendix P/N 391003 is available and has been installed in the carburetor.
75-08-05: 75-08-05 ROCKWELL INTERNATIONAL CORP., GENERAL AVIATION DIVISION: Amendment 39-2158. Applies to Model 690A airplanes, Serial Numbers 11100 through 11196, 11198 through 11215, 11219 through 11227, and 11231 through 11233. Compliance required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To assure correct battery disconnect, accomplish the following: (a) Check operation of the battery select switch in accordance with Rockwell International, General Aviation Division, Service Bulletin No. 149, dated February 20, 1975, or later approved revision or in accordance with an equivalent operational check approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. (b) If the check indicates incorrect connection, interchange Wires P42B22 and P53B22. This amendment becomes effective on April 5, 1975.
2015-11-01: We are adopting a new airworthiness directive (AD) for Slingsby Aviation Ltd. Models T67M260 and T67M260-T3A airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as failure of a brake master cylinder pivot pin. We are issuing this AD to require actions to address the unsafe condition on these products.
2005-05-17: The FAA is adopting a new airworthiness directive (AD) for Boeing Model 737-300, -400, and -500 series airplanes modified in accordance with STC ST00127BO. This AD requires installation of bonding straps to the safe side harnesses of the digital transient suppression device of the fuel quantity indicating system. This AD is prompted by the results of fuel system reviews conducted by the STC holder. We are issuing this AD to prevent unsafe levels of current or energy from entering the fuel tank, due to hot short faults or threat conditions associated with the safe side harness assembly, which could result in a fire or explosion of the fuel tank.
2015-21-11: We are superseding Airworthiness Directive (AD) 2015-16-01 for certain The Boeing Company Model airplanes. AD 2015-16-01 required incorporating design changes to improve the reliability of the cabin altitude warning system by installing a redundant cabin altitude pressure switch, replacing the aural warning module (AWM) with a new or reworked AWM, and changing certain wire bundles or connecting certain previously capped and stowed wires as necessary. For certain airplanes, AD 2015-16-01 also required prior or concurrent incorporation of related design changes by modifying the instrument panels, installing light assemblies, modifying the wire bundles, and installing a new circuit breaker, as necessary. This AD retains all actions required by AD 2015-16-01. This AD was prompted by the discovery of a typographical error in AD 2015-16-01 that referred to a nonexistent paragraph. We are issuing this AD to prevent the loss of cabin altitude warning, which could delay flightcrew recognition of a lack of cabin pressurization, and could result in incapacitation of the flightcrew due to hypoxia (a lack of oxygen in the body), and consequent loss of control of the airplane.
75-18-03: 75-18-03 LOCKHEED: Amendment 39-2342 as amended by Amendment 39-2511 is further amended by Amendment 39-3157. Applies to all Model 382 series airplanes certificated in all categories. Compliance required within the next 50 hours time in service after the effective date of this Airworthiness Directive unless already accomplished, on airplane serial numbers 3946 and 4101 through 4298, with 6,300 hours or more total time in service, and serial numbers 4299 through 4541 with 9,450 hours or more total time in service on the effective date of Amendment 39-3157 and at intervals not to exceed 3,400 hours time in service from the last inspection until 20,000 hours (without ECP 954) or 24,000 hours (with ECP 954) at which time the interval is not to exceed l,700 hours from the last inspection. (A) To detect cracks in the outer wing lower forward spar caps at OWS 54 and 108, eddy current inspect in accordance with Hercules Airfreighter Inspection procedures SMP515-A Card No. SP-62, revised August 11, 1975. (B) If a crack or cracks are found, contact the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, Atlanta, Georgia 30320, telephone number 404-526-7428. Before the accumulation of more than 30,000 flight hours, preventive modification shall be installed in accordance with Lockheed Service Bulletin 382-187, or later FAA-Approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. The inspections required by this AD may be discontinued for those airplanes modified in accordance with the above paragraph. Amendment 39-2342 became effective August 27, 1975. Amendment 39-2511 became effective February 13, 1976. This Amendment 39-3157 becomes effective March 20, 1978.
2005-09-03: The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Model Hawker 800XP airplanes. This AD requires inspecting to detect damage of certain wiring in the flight compartment, performing corrective actions if necessary, modifying certain wiring connections, and revising the airplane flight manual. This AD is prompted by reports of miswiring in the power distribution system. We are issuing this AD to ensure that the flightcrew is aware of the source of battery power for certain equipment, and to prevent damage to wiring and surrounding equipment that could result in smoke or fire on the airplane.
2015-21-05: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.27 Mark 200, 300, 400, 500, 600, and 700 airplanes. This AD was prompted by a design review, which revealed that no controlled bonding provisions are present on a number of critical locations inside the fuel tank or connected to the fuel tank wall; and no anti-spray cover is installed on the fuel shut-off valve (FSOV) in both wings. This AD requires installing additional bonding provisions in the fuel tank, installing an anti-spray cover on the FSOV, and revising the airplane maintenance program by incorporating fuel airworthiness limitation items and critical design configuration control limitations. We are issuing this AD to prevent an ignition source in the fuel tank vapor space, which could result in a fuel tank explosion and consequent loss of the airplane.
2001-09-16: This amendment adopts a new airworthiness directive (AD) that applies to certain Eagle Aircraft Pty. Ltd. (Eagle) Model 150B airplanes. This AD requires you to inspect the rudder cables for fraying, broken strands, etc. (referred to as damage), and replace any damaged cables. This AD also requires you to replace the rudder cable pulleys with larger diameter pulleys to eliminate the possibility of further damage. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Australia. The actions specified by this AD are intended to detect and correct damaged rudder cables caused by chafing of the cable against the pulleys. Continued airplane operation with damaged cables could result in rudder cable system failure with possible loss of airplane control.
97-10-12: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a one-time inspection to detect riding, chafing, or damage of the wire bundles adjacent to the disconnect panel bracket of the observer's station. This amendment also requires repair or replacement of damaged wires with new or serviceable wires; installation of anti-chafing sleeving on the wire bundles, if necessary; and installation of grommet along the entire upper aft edge of the disconnect panel bracket. This amendment is prompted by a report indicating that the circuit breakers tripped on a Model MD-11 series airplane due to inflight arcing behind the avionics circuit breaker panel as a result of chafing of the wire bundles adjacent to the disconnect panel bracket assembly. The actions specified by this AD are intended to detect and correct such chafing, which could result in a fire in the wire bundles and smoke in the cockpit.
97-09-14: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires an inspection of reworked aileron/elevator power control units (PCU's) and rudder PCU's to determine if reworked PCU manifold cylinder bores containing chrome plating are installed, and replacement of the cylinder bores with bores that have been reworked using the oversize method or the steel sleeve method, if necessary. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent a reduced rate of movement of the elevator, aileron, or rudder due to contamination of hydraulic fluid from chrome plating chips; such reduced rate of movement, if not corrected, could result in reduced controllability of the airplane.
2024-12-06: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and - 402 airplanes. This AD was prompted by reports of moisture in the wing- to-fuselage joint, between the mating front spar and rear spar frame segments. This AD requires a visual inspection of the fuselage front and rear spar frames, an ultrasonic test if applicable, other specified actions, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
56-27-01: 56-27-01 CONVAIR: Applies to All Models 340 and 440 Aircraft. Compliance required as noted below. A report has been received concerning the failure of the elevator servo tab rod on a version of the Model 340 aircraft. Since the tabs on the subject model aircraft are unbalanced, a serious flutter condition resulted and a critical accident was narrowly avoided. In view of the fact that the tab rods and tab rod ends on the subject models aircraft are identical in design, hence susceptible to a similar type of failure, the following inspections and tab rod replacements or equivalent measures are required. Compliance required at every 110 hours of operation or regular scheduled inspection closest thereto. 1. (a) Inspect the tab rods and rod ends on the elevator, for looseness in the rivets which attach the rod ends to the rods, and for any relative movement between the rod and the rod ends. Parts which exhibit these defects shall be replaced with satisfactory parts. Upon completion of the tab rod replacement program or equivalent noted in items 2 (a), and 2 (b) below, this 110-hour inspection may be discontinued. Compliance required not later than November 30, 1957. 2. (a) Model 340 replacement of all elevator tab rods with improved, heavier rods and rod ends, and replacement of the right-hand elevator tab idler link with symmetrical idler link. (Convair Service Bulletin Nos. 340-207 and 340-150A cover this same subject.) 2. (b) Model 440 replacement of the right-hand elevator tab rods and tab rod ends with improved heavier tab rods and tab rod ends. (Convair Service Bulletin No. 440-27A covers this same subject.)
2024-13-04: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a determination that non-conforming washers may have been installed in production on engine 1 and 3 forward yokes. This AD requires a one-time inspection for non-conforming washers and, depending on findings, related investigative and corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
72-25-07: 72-25-07 MCCAULEY: Amdt. 39-1573. Applies to the two-bladed constant speed series propeller Models E2A34C64(-)/90AT-8 and E2A34C73(-)/90AT-8 with the following blades and hubs installed on but not limited to the Cessna P206, A, B, C, D, E, and Cessna 210E, F, G, H, J, K, and L aircraft with Continental IO-520 series (normally aspirated) engines. TABLE I - BLADE SERIAL NUMBERS All Model 90AT-8 propeller blades with serial numbers not ending with suffix letter "S" (Example: C238479Y is affected while C238479YS would not be affected). TABLE II - HUBS MODELS AND SERIAL NUMBERS Serial Numbers 64000 thru 699999 for the following hubs: E2A34C64 E2A34C73-A E2A34C64-A E2A34C73-J E2A34C73 E2A34C73-K Compliance required as indicated, unless already accomplished. To prevent possible blade and hub failures, accomplish the following: a) Propellers with 775 or more total hours in service, must be reworked or replaced in accordance with paragraphs (d), and (e)or (f) as applicable within the next 25 hours in service after the effective date of this AD. b) Propellers with less than 775 total hours in service must be reworked or replaced in accordance with paragraphs (d), and (e) or (f) as applicable prior to the accumulation of 800 total hours in service. c) Propellers whose total hours in service are unknown will be assumed to have a total of 775 hours minimum and thus fall within the requirements for rework or replacement in accordance with paragraph (a). d) Rework affected propeller blades in accordance with McCauley Service Bulletin 100 dated October 30, 1972, or replace with Model 90AT-8 blades to which this AD does not apply. e) Rework affected Model E2A34C73(-) hubs in accordance with McCauley Service Bulletin 100 dated October 30, 1972, or replace with Model E2A34C73(-) hubs to which this AD does not apply. f) Replace affected Model E2A34C64(-) hubs with Models E2A34C73(-) hubs to which this AD does not apply, or which have been reworked in accordance with McCauley Service Bulletin No. 100 dated October 30, 1972. (The spinner shell and bulkhead must be replaced when converting from the E2A34C64(-) to the E2A34C73(-) Model. A kit, Cessna P/N SK-210-45, is available for this purpose from the airplane manufacturer.) (McCauley Bulletins No. 81 dated March 9, 1970, No. 87 dated November 6, 1970, No. 87-1 dated November 25, 1970, No. 87-2 dated April 21, 1971, No. 88 dated November 6, 1970, McCauley Service Manual 720415 and Cessna Service Letter No. 65-68 dated July 13, 1965, also pertains to this subject.) This amendment becomes effective December 13, 1972.
2005-09-01: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Model 750 airplanes. The AD requires repetitive inspections for clearance and chafing of an auxiliary power unit (APU) fuel tube assembly in the tail cone area of the airplane, and corrective actions if necessary. For certain airplanes, this AD also requires replacing the APU fuel line. This AD is prompted by reports of chafed APU fuel tubes leaking into the tail cone area due to interference between the fuel tube assembly and elevator flight control cables, hydraulic lines, and high-temperature bleed air couplings. We are issuing this AD to detect and correct this interference, which could result in chafing, fuel leaking into an area where ignition sources are present, and possible fire in an area without fire detection or extinguishing provisions.
2024-12-02: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by production flight test findings of several oxygen masks disconnected from their accompanying portable oxygen bottles. This AD requires inspecting the portable oxygen bottles and reconnecting the masks to the accompanying portable oxygen bottles if not connected, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
75-17-13: 75-17-13 MESSERSCHMITT-BOLKOW-BLOHM.: Amendment 39-2315. Applies to Messerschmitt-Bolkow-Blohm (MBB) Models BO-105A and BO-105C helicopters, certificated in all categories, incorporating tail rotor blade P/N 105-31742, Serial Numbers 548 and lower. Compliance is required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished in accordance with MBB BO-105 Service Bulletin No. 30-8. To prevent failure of the tail rotor blade tip cap, inspect tail rotor blades for condition, modify as prescribed, and return to service, in accordance with paragraph 2 of MBB BO-105 Service Bulletin No. 30-8, dated July 5, 1974, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region. This amendment becomes effective August 18, 1975.