Results
95-19-18: 95-19-18 TWIN COMMANDER AIRCRAFT CORPORATION: Amendment 39-9379; Docket No. 95-CE-20-AD. Applicability: The following airplane models and serial numbers, certificated in any category. Models Serial Numbers 680T and 680V 1473 through 1720 680W 1721 through 1850 681 6001 through 6072 690 11001 through 11079 690A 11100 through 11344 690B 11350 through 11566 690C 11600 through 11735 690D 15001 through 15042 695 95000 through 95084 695A 96000 through 96100 695B 96201 through 96208 NOTE 1: This AD applies to each airplane identified in the preceding applicability revision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should includean assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent structural damage to the airplane caused by excessive turbulence, which could result in loss of the airplane, accomplish the following: (a) Install the placard (to the windshield centerpost) and incorporate the airplane flight manual/pilot operating handbook (AFM/POH) revisions that are included with the kits presented below. The placard and AFM/POH revisions provide warnings to the airplane operator of the importance of observing the Turbulent Air Penetration and Maneuvering speeds: Kit No. Model Affected SB220-1 680T SB220-2 680V SB220-3 680W SB220-4 681 SB220-5 690 SB220-6 690A SB220-7 690B SB220-8 690C SB220-9 690D SB220-10 695 SB220-11 695A SB220-12 695B NOTE 2: Twin Commander Service Bulletin No. 220, dated February 1, 1995, relates to the subject of this AD, and references the SB220 service kits specified above. (b) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Northwest Mountain Region, 1601 Lind Avenue S.W., Renton, Washington 98055-4056. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. (d) All persons affected by this directive may obtain copies of the kits referenced above that include the placard and the AFM revisions upon request to the Twin Commander Aircraft Corporation, 19010 59th Drive, NE., Arlington, Washington 98223; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (e) This amendment becomes effective on October 25, 1995.
2010-12-09: The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc. auxiliary power unit (APU) models GTCP36- 150(R) and GTCP36-150(RR). This AD requires inspecting the fuel control unit (FCU) differential pressure (Delta P) sleeve bore for erosion, replacing the FCU if it fails the inspection, and installing a fuel deflector on the Delta P sleeve of the FCU. This AD results from eight reports of fuel leakage from the FCU. We are issuing this AD to prevent fuel leakage in the APU compartment, which could lead to ignition of fuel vapor, creating a fire and explosion hazard resulting in injury, and damage to the APU and the airplane.
96-03-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream ATP airplanes, that requires inspections to detect fatigue cracking and corrosion in the gussets of the rear passenger door and rear baggage door apertures, and replacement of the gussets, if necessary. This amendment is prompted by fatigue tests which indicated that fatigue cracking and corrosion can occur in these gussets. The actions specified by this AD are intended to prevent degradation of the structural integrity of the fuselage pressure vessel due to the problems associated with cracking and corrosion in the gussets of the rear passenger door and rear baggage door apertures.
2010-11-11: We are adopting a new airworthiness directive (AD) for certain Model 60 airplanes. This AD requires revising the Tire-Servicing section of the airplane maintenance manual and revising the Tires Limitation section of the airplane flight manual to incorporate revised procedures for servicing tires and checking for proper tire inflation. This AD results from a report of the main landing gear tires blowing out during a takeoff roll. We are issuing this AD to prevent tire failure, which could result in failures of the braking and thrust reverser systems. In a critical phase of operation such as takeoff, loss of airplane control may result.
90-24-10: 90-24-10 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6813. Docket No. 90-NM-14-AD. Applicability: Model DHC-7 series airplanes, Serial Numbers 1 through 10, and 12 through 27, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent corrosion and reduced structural capability of the wings accomplish the following: A. Within 180 days after the effective date of this AD, and thereafter at intervals not to exceed one year, perform a low frequency eddy current inspection of the inboard and outboard fuel tank lower wing skins in accordance with the procedure specified in Part 6, Chapter 57-10- 01, of the de Havilland DHC-7 Nondestructive Testing (NDT) Manual, PSM 1-7-7A. B. If corrosion is found as a result of the inspections required by paragraph A. of this AD, accomplish the following. Accomplishment of these actions constitutes terminating action for the repetitive inspections of the inboard and/or outboard fuel tank area, as appropriate, required by paragraph A. of this AD. 1. If corrosion is found in the inboard fuel tank, prior to further flight, permanently remove the inboard fuel tank foam blocks, restore any corroded areas, and modify the stringers in accordance with the Accomplishment Instructions, Steps 3, 4, and 5, of de Havilland Service Bulletin 7-57-33, dated July 21, 1989. 2. If corrosion is found in the outboard fuel tank, prior to further flight, permanently remove the outboard fuel tank foam blocks, restore any corroded areas, and modify the stringers in accordance with the Accomplishment Instructions, Steps 3, 4, and 5, of de Havilland Service Bulletin 7-57-33, dated July 21, 1989. C. If no corrosion is found, within three years after the effective date of this AD, permanently remove the inboard fuel tank foam blocks and modify the stringers in accordance with the Accomplishment Instructions, Steps 3 and 5, of de Havilland Service Bulletin 7-57-33 (), dated July 21, 1989. D. Accomplishment of the removal and modification actions specified in paragraph C. of this AD, constitutes terminating action for the repetitive inspections of the inboard fuel tank lower wing skins required by paragraph A. of this AD. E. Accomplishment of the removal and modification actions specified in the Accomplishment Instructions, Steps 3 and 5, of de Havilland Service Bulletin 7-57-33 (), dated July 21, 1989, for the outboard fuel tanks, constitutes terminating action for the repetitive inspections of the outboard fuel tank lower wing skin required by paragraph A. of this AD. F. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, New York Aircraft Certification Office (ACO), FAA, New England Region. NOTE: The request should be submitted directly to the Manager, New York ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, New York ACO. G. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing of Canada, Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or at the FAA New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment (39-6813, AD 90-24-10) becomes effective on December 24, 1990.
95-26-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This AD requires either that the control circuit breaker of the left fuel pump valve be opened and collared, or that the Airplane Flight Manual (AFM) be revised to prohibit autoland operation below 100 feet above ground level (AGL). Additionally, this action requires an inspection of the fuel system control panel (FSCP) to detect any mis-wiring, and modification or replacement of the FSCP. This AD also provides for an optional terminating modification for the requirements of the AD. This amendment is prompted by a report of improper wiring of the FSCP during production of these airplanes. The actions specified in this AD are intended to prevent degradation of the automatic landing system during flight due to improper wiring of the FSCP.
2010-11-14: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: During ERJ 190 airplane full scale fatigue test, cracks were found in some structural components of the airplane. Analysis of these cracks resulted in modifications on the airplane Airworthiness Limitation Items (ALI), to include new inspections tasks or modification of existing ones and its respective thresholds and intervals. Failure to inspect these components according to the new tasks, thresholds and intervals could prevent a timely detection of fatigue cracks. Undetected fatigue cracks in these areas could adversely affect the structural integrity of these airplanes. * * * * * We are issuing this AD to require actions to correct the unsafecondition on these products.
2010-10-26: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: A specific batch of nose landing gear (NLG) and NLG door selector valves, part number (P/N) 601R75146-1 (Kaiser Fluid Technologies P/N 750006000), may have had their end caps incorrectly lock-wired and/or incorrectly torqued during assembly. This condition can lead to the end cap backing off, with consequent damage to a seal and internal leakage within the valve. Subsequently, if electrical power is transferred or removed from the aircraft before the NLG safety pin is installed, any pressure, including residual pressure, in the No. 3 hydraulic system can result in an uncommanded NLG retraction. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
76-09-10: 76-09-10 SCHEMPP HIRTH and BURKHART GROB: Amendment 39-2602. Applies to Standard Cirrus gliders, certificated in all categories, serial numbers 1 through 510, 528, and 529 for Schempp Hirth gliders and serial numbers 1G through 544G for Burkhart Grob gliders. Compliance is required within the next 100 flights after the effective date of this AD, unless already accomplished. To prevent possible jamming of the aileron control system and consequent loss of roll control, accomplish the following: (a) Install an SAE 1024 steel safety brace in the fuselage frame between the airbrake lever bearing and the left diagonal strut in accordance with Step 2 of the paragraph entitled "Instructions" of Schempp Hirth Technical Note 278-17, dated December 8, 1975, or an FAA- approved equivalent. (b) For the purpose of this AD, a flight is a sequence consisting of a takeoff operation and landing. This amendment becomes effective May 20, 1976.
2010-11-12: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Model MD-11 and MD-11F airplanes. That AD currently requires a one-time inspection to determine if metallic transitions are installed on wire harnesses of the tail tank fuel transfer pumps, and to determine if damaged wires are present; and repair, if necessary. That AD also requires repetitive inspections of the repaired area; and a permanent modification of the wire harnesses if metallic transitions are not installed, which would terminate the repetitive inspections. This new AD requires modifying the case grounding for the alternate fuel pump of the tail tank, the leak detection thermal switch grounding for the number 2 engine, and wire braid grounding in the empennage and number 2 engine inlet. This AD also removes one airplane from the applicability of the existing AD. This AD results from reports that the wire assembly for the alternate fuel pump is missing a case ground wire, and the lightning protection wire braid for wire assemblies located in the empennage and number 2 engine inlet are grounded improperly. We are issuing this AD to prevent insufficient grounding of the fuel pump, which in combination with an electrical failure within the fuel pump and a compromised electrical bond could cause a fuel tank ignition, resulting in consequent fire or explosion. \n\nDATES: This AD becomes effective July 6, 2010. \n\tThe Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of July 6, 2010. \n\tOn January 18, 2000 (64 FR 69389, December 13, 1999), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD.