Results
2007-03-19: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. That AD currently requires repetitive detailed and eddy current inspections of the main fittings of the main landing gears (MLG) to detect discrepancies, and related investigative/ corrective actions if necessary. The AD also currently requires servicing the shock strut of the MLGs; inspecting the shock strut of the MLGs for nitrogen pressure, visible chrome dimension, and oil leakage; and servicing any discrepant strut. This new AD requires installing a new, improved MLG main fitting, which terminates the repetitive inspection and servicing requirements of the existing AD. This AD results from stress analyses that showed certain main fittings of the MLGs are susceptible to premature cracking, starting in the radius of the upper lug. We are issuing this AD to detect and correct premature cracking of the main fittingsof the MLGs, which could result in failure of the fittings and consequent collapse of the MLGs during landing. DATES: This AD becomes effective March 15, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of March 15, 2007. On August 13, 2004 (69 FR 41421, July 9, 2004), the Director of the Federal Register approved the incorporation by reference of Bombardier Alert Service Bulletin A601R-32-088, including Appendices A, B, and C, dated February 20, 2003.
2007-03-09: This amendment adopts a new airworthiness directive (AD), applicable to all of the airplanes identified above, that requires revising the FAA-approved maintenance program to include a new airplane maintenance manual task that specifies a detailed inspection after each ram air turbine (RAT) retraction. This AD also requires, for certain airplanes, a one-time inspection to detect breaks in the bottom flange fitting of the RAT and corrective actions, if necessary; for certain airplanes, an adjustment of the ejection jack; and, for certain other airplanes, replacement of the aluminum part with an improved steel part. The actions specified by this AD are intended to prevent failure of the RAT yoke fitting, which could result in the loss of RAT function and possible loss of critical flight control in the event of certain emergency situations. This action is intended to address the identified unsafe condition.
59-06-02: 59-06-02 DOUGLAS: Applies to All Model DC-7 Series Aircraft. \n\n\tCompliance required by first block overhaul after receipt of parts but not later than December 1, 1959. \n\n\tSeveral instances have occurred wherein the green indicator light for one of the main landing gear failed to go on when the landing gears were extended. In one case, after landing, it was noted that the left gear downlatch was not fully engaged and the ground lock safety pin could not be installed. Subsequent investigation and laboratory tests revealed that the orifice check valve could malfunction due to contaminants in the hydraulic fluid of sufficient quantity and size (approximately 0.003-inch diameter) and thereby prevent full extension of the gear. \n\n\tTo overcome this difficulty, remove existing orifice check valve assembly, P/N 4498423-503 (Mineral Oil Aircraft), or P/N 4498423-5503 (Skydrol Aircraft), from each main landing gear actuating cylinder and replace with new orifice check valve assembly, P/N 2230565-5-093 (Mineral Oil Aircraft), or P/N 4481262-5-093 (Skydrol Aircraft). (Douglas Service Bulletin DC-7 No. 353 dated January 30, 1959, covers this same subject.)
67-14-04: 67-14-04 BRITISH AIRCRAFT: Amdt. 39-397 Part 39 Federal Register April 14, 1967. Applies to Model BAC 1-11 200 and 400 Series Airplanes. Compliance required as indicated, unless already accomplished. To detect cracks in the fin top actuator fitting P/N AB 21A 1009 (pre modification PM 378) for 200 Series airplanes and P/N AK 21A 6283 (post modification PM 378) for 400 Series airplanes, accomplish the following: (a) Within 6,000 landings, or for aircraft which have exceeded 5,800 landings, within 200 landings after the effective date of this AD, visually inspect the actuator fitting P/N AB 21A 1009 or P/N AK 21A 6283 as appropriate, for cracks in accordance with BAC 1-11 Alert Service Bulletin 55-A-PM 2707, Issue 1, dated November 16, 1966, or later ARB-approved issue. (b) Repeat the visual inspections of (a) at intervals not exceeding 600 hours' time in service for aircraft which have no cracks, and at intervals of 100 hours' time in service for aircraft which havecracks that do not exceed either 0.30" for item (1), or 0.45" for item (2) of Figure 1, specified in BAC 1-11 Alert Service Bulletin 55-A-PM 2707, dated November 16, 1966, or later ARB-approved issue. (c) Actuator fittings which have cracks which exceed the acceptable limitations defined in BAC 1-11 Alert Service Bulletin 55-A-PM 2707 are unserviceable and must be replaced before further flight, in accordance with BAC 1-11 Service Bulletin 55-PM 2707, dated October 18, 1966, or later ARB-approved issue, or FAA-approved equivalent. (d) Within 10,000 landings after the effective date of this AD, modify actuator fittings P/N AB 21A 1009 or P/N AK 21A 6283, in accordance with BAC 1-11 Service Bulletin 55-PM 2707, dated October 18, 1966, or later ARB-approved issue or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, Middle East Region. (e) The repetitive inspections required by (a) and (b) of this AD may be discontinued after the actuator fittings are modified in accordance with (c) or (d) of this AD. (f) For the purpose of complying with this AD subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type. This directive effective May 14, 1967.
2007-03-08: 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 the discovery of exfoliation corrosion in the fittings of some PC-6 airplanes. These fittings are installed exterior to the bottom skin of the wing skin. If not corrected, undetected corrosion in this area could lead to failure of the fitting and subsequent loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2007-03-05: 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 unsafe condition is incomplete closure of the main entry door, which may result in the door opening in flight, causing damage to wing, fuselage, engine, and/or tail, and possible damage to the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
70-07-02: 70-07-02\tBOEING: Amdt. 39-961. Applies to Model 707 and 720 Series airplanes listed in Boeing Service Bulletin No. 2961, Revision 1, or later FAA-approved revisions. \n\n\tCompliance required within the next 50 hours' time in service after the effective date of this AD on aircraft having 14,000 or more flights, unless already accomplished. Aircraft having less than 14,000 flights on the effective date of this AD must be inspected after they have accrued 13,000 flights but no later than 50 hours' time in service after they have accrued 14,000 flights, unless already accomplished during this specified interval. \n\n\tFor the purpose of compliance with this AD, the number of flights may be determined by dividing the total flight time on an airplane by the operator's fleet average flight time per flight for the type airplane considered. \n\n\tTo prevent walkway panel failures between body stations 344 and 352: \n\n\t(a)\tInspect the left-hand and right-hand walkway panels on all airplaneslisted in Boeing Service Bulletin 2961, Revision 1, or later FAA-approved revisions. Perform inspections in accordance with Accomplishment Instruction, Part II, unless already accomplished in accordance with Service Bulletin 2961, dated 13 January 1970, or an equivalent inspection approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(b)\tIf no cracks are found, perform: \n\n\t\t(1)\tThe preventative modification described in Part II of Boeing Service Bulletin 2961, Revision 1, dated 11 March 1970, or later FAA-approved revisions, or \n\n\t\t(2)\tReinspections at intervals not to exceed 1500 flights in service (for eddy current or dye penetrant inspection) or 500 flights (for visual inspection) in accordance with Part II of Boeing Service Bulletin 2961, Revision 1, or \n\n\t\t(3)\tAn equivalent modification or inspection program approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(c)\tIf cracks are found during any of the inspections, perform the preventative modification in accordance with Part II of Boeing Service Bulletin 2961, Revision 1, 11 March 1970, or later FAA-approved revisions, or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region, prior to further flight. \n\n\tInspections required by this AD may be discontinued when the approved preventative modification has been accomplished. \n\n\tThis supersedes Amendment 39-932, 35 F.R. 1159, AD 70-02-12. \n\n\tThis amendment becomes effective March 28, 1970.
2007-02-13: The FAA is adopting a new airworthiness directive (AD) for DORNIER LUFTFAHRT GmbH Model 228-212 airplanes. This AD requires you to inspect the landing gear carbon brake assembly. This AD results from mandatory continuing airworthiness information (MCAI) issued by the European Aviation Safety Agency (EASA), which is the airworthiness authority for the European Union. We are issuing this AD to inspect the landing gear carbon brake assembly to detect and replace loose bolts or self-locking nuts, which could result in the brake assembly detaching and malfunctioning, degrade brake performance and potentially cause loss of control of the aircraft during landing and roll-out.
49-12-01: 49-12-01 CURTISS-WRIGHT Applies to Model C-46 Series aircraft equipped with Aileron Tab Motor Bracket Assembly, Curtiss-Wright P/N 20-030-5050. Compliance required within 25 hours' time in service after the effective date of this amendment, unless already accomplished within the last 475 hours' time in service, and at intervals thereafter not to exceed 500 hours' time in service from the last inspection. Inspect the aileron trim tab motor support bracket (P/N S-20-030-5050) attached to the aft face of the 70 percent rear spar at wing Station 178.36 for cracks. Defective parts should be replaced. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Southern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase. Revised December 28, 1964.
67-27-01: 67-27-01 AVIONS MARCEL DASSAULT: Amdt. 39-474, Part 39, Federal Register September 9, 1967. Applies to Fan Jet Falcon Airplanes, Serial Numbers 1 thru 94. Compliance required within the next 200 hours' time in service after the effective date of this AD, unless already accomplished. To prevent jamming of the engine power lever, modify the type MF 2006 pressurization control microswitch installation by the addition of a support, P/N MY.20.240.3801, and a leaf spring, P/N MY.20.240.3802, in accordance with Avions Marcel Dassault Service Bulletin No. 211, (76-4), revision 1, dated April 4, 1967, or later SGAC-approved revision, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. This amendment effective October 9, 1967.