Results
80-11-08: 80-11-08 BOEING VERTOL (VERTOL): Amendment 39-3778. Applies to Vertol Model 107-II helicopters with pilot or copilot cyclic stick boots, P/Ns 107S2226-9, -13 or -17, certificated in all categories. To prevent possible restriction of cyclic stick travel accomplish the following within the next 25 hours in service after the effective date of this AD, unless already accomplished. a. Loosen the velcro tape and camloc fasteners securing the pilot and copilot cyclic stick boots, P/N 107S2226-9, -13 or -17, and remove the boots. b. Remove the two rivets which attach the forward spring, P/N 107S2226-12, to the forward end of the boot base and discard the forward spring. c. Install washers and new rivets to plug the resulting two empty holes in the boot base. d. Reinstall the pilot and copilot stick boots. e. Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective May 28, 1980.
2009-12-16: We are superseding an existing 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: The manufacturer reported findings of missing primer on the internal of the elevator and rudder of aircraft S/N 8200. The aircraft S/N 8200 was with RUAG for maintenance purposes. Investigation performed by RUAG showed that the paint removal procedure for the rudder and elevator was changed from a paint stripping with brush and scraper to a procedure where the parts were submerged in a tank filled with hot liquid stripper. The stripper is called TURCO 5669 from Henkel Surface Technologies. The stripping process is described in the Technical Process Bulletin No. 238799 dated 09/01/1999. This paint stripping process change was not communicated to andnot approved by the TC-Holder. We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-21-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report that sticking effects have been observed affecting the breathing bag on certain passenger oxygen masks. This AD requires replacement of affected passenger oxygen masks, 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.
83-06-01: 83-06-01 BOEING: Amendment 39-4589. Applies to Boeing Model 767 Series Airplanes certificated in all categories. To prevent loss of engine throttle control due to power lever cable icing, accomplish the following within 30 days from the effective date of this AD, unless already accomplished. \n\tA.\tInstall ice shields on the number 6 and 7 slats per Boeing Service Bulletin 767-30-2, dated December 13, 1982, or later FAA approved revision. \n\tB.\tSpecial flight permits may be issued in accordance with FAR 21.199 to operate airplanes to a base for the accomplishment of this AD. \n\tC.\tAlternate means of compliance with the AD which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tThis amendment becomes effective April 4, 1983.
2003-21-07: The FAA is adopting a new airworthiness directive (AD) for certain The Cessna Aircraft Company (Cessna) Model 525 airplanes. This AD requires you to disengage the pitch trim circuit breaker and AP servo circuit breaker and then tie strap each of them to prevent them from being engaged. This AD is the result of analysis that reveals the potential for a single-wire shorting to 28 volts or a failure of a relay in the electric pitch trim system such that the relay contacts remain closed. We are issuing this AD to correct this single-point failure in the electric pitch trim system, which will result in a runaway pitch trim condition where the pilot could not disconnect using the control wheel autopilot/trim disconnect switch. Failure of the electric trim system would result in a large pitch mistrim and would cause excessive control forces that the pilot could not overcome.
94-24-06: This amendment adopts a new airworthiness directive (AD), applicable to all Raytheon Corporate Jets Model BH/HS 125-600A and -700A series airplanes, that requires installation of two new circuit breakers in the 6 volt output circuits of the flight deck lighting transformers on electrical Panel 'RY,' below the right pilot's seat. This amendment is prompted by a report of smoke in the flight deck due to a lighting transformer 6 volt output circuit short circuiting to ground. The actions specified by this AD are intended to prevent smoke or fire in the flight deck due to inadequate circuit protection for 6 volt circuits of the flight deck lighting transformer.
61-20-01: 61-20-01 AUTO CRAT MANUFACTURING COMPANY SAFETY BELT: Amdt. 341 Part 507 Federal Register September 23, 1961. Applies to All Aircraft Equipped With Auto Crat Model BN 1-1700 Series Safety Belts. Compliance required within the next 25 hours' time in service after the effective date of this AD. It has been determined by static test that the Auto Crat safety belt Model BN 1-1700 assemblies manufactured under Technical Standard Order C22 standards do not meet the minimum strength requirements of this TSO. Accordingly, these belt assemblies must either be replaced with belt assemblies that conform to TSO-C22 standards, or be reworked to incorporate a steel frame buckle BN 1-2000AW supplied by Auto Crat, or equivalent. When this steel frame buckle is installed, the modified belt assembly becomes Model BN 1-2000, which meets the TSO requirements and shall be marked with the new model number. (Auto Crat letters to various air carriers dated May 10, 1961, pertains to the same subject.) This directive effective October 24, 1961.
2020-20-09: The FAA is superseding Airworthiness Directives (ADs) 2015-14- 07, 2016-07-10, and 2016-24-09. AD 2015-14-07 applied to certain The Boeing Company Model 787-8 airplanes. AD 2016-07-10 and AD 2016-24-09 applied to all The Boeing Company Model 787-8 and 787-9 airplanes. ADs 2015-14-07, 2016-07-10, and 2016-24-09 required actions related to certain flight control module (FCM) software. This AD requires installing flight control electronics (FCE) common block point 5 (CBP5) software, which terminates the requirements of the ADs superseded by this AD. This AD was prompted by certain deficiencies in the FCM software, including a report of an unannunciated dual symmetric inboard slat skew. The FAA is issuing this AD to address the unsafe condition on these products.
2003-21-04: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. This AD requires you to inspect the right inboard forward flap bell crank for cracks, deformation, and missing/incomplete welds. If cracks, deformation, or missing/incomplete welds are found, the AD would require you to immediately replace the flap bell crank or temporarily incorporate certain flap limitations. This AD is the result of reports of cracks and missing/incomplete welds in the right inboard forward flap bell crank. We are issuing this AD to prevent failure of the right inboard forward flap bell crank due to cracks, deformation, or missing/ incomplete welds. Such failure could lead to damage to the flap system and surrounding structure and result in reduced or loss of control of the airplane.
61-25-01: 61-25-01 CESSNA: Amdt. 376 Part 507 Federal Register December 9, 1961. Applies to All Models 120, 140, and 140A Aircraft, On Which A Met-Co-Aire Tricycle Landing Gear (STC SA4-916) Has Been Installed. Compliance required as indicated. To correct an unsafe condition in the main gear the following shall be accomplished: (a) Within 20 hours' time in service after the effective date of this AD and at periods thereafter not to exceed 100 hours' time in service: (1) Tighten and torque to 50-70 inch-pounds the four AN 4 bolts (two on each side) which extend through the Cessna main gear wedges and the Met-Co-Aire support plate, P/N RD-1001C-11. Care should be taken to insure that the AN 365 stop nuts have not bottomed on the bolt threads before adequately tightening the wedge in place as specified above; use metal washers under the nut or bolt heads as necessary. (2) Conduct a close visual inspection for cracks in the corners of the slots in the support plate, P/N RD-1001C-11, and in the attach plate. Parts exhibiting evidence of cracks shall be replaced with Met-Co-Aire P/N RD-1001C-6 or FAA approved equivalent. When a new part is installed, the repetitive inspection prescribed in this subparagraph may be discontinued. (b) Within 20 hours' time in service after the effective date of this AD: (1) Inspect the attachment of the top flanges of the bulkheads in the landing gear attachment box and perform such work as necessary to assure that all rivets which secure the box to the floor structure are properly installed. Refer to Met-Co-Aire installation instructions dated August 29, 1959, as revised January 1, 1961, for description and location of necessary rivets. (2) If installed, remove the adapter plates, Cessna P/N 0441147, which may have been used to extend the main gear wheels forward. (Met-Co-Aire Service Directive SD-1003 covers this same subject.) This directive effective December 20, 1961.