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76-19-02: 76-19-02 AVIONS MARCEL DASSAULT (AMD): Amendment 39-2722. Applies to Model Fan Jet Falcon airplanes, all series, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent possible contamination of cabin ventilation air with fuel fumes or mist, comply with the following: (a) Within the next 10 hours time in service or the next 10 days after the effective date of this AD, whichever occurs later, accomplish the following: (1) Inspect and rectify, as necessary, the fuel tank pressurization system in accordance with Paragraphs (2) and (3) of Fan Jet Falcon (FJF) Maintenance Manual Change Notice Nos. 229 and 230, dated March 1976, or an FAA approved equivalent. (2) For airplanes incorporating an AMD-installed cabin air conditioning system, inspect and rectify, as necessary, the cabin air conditioning system in accordance with FJF Maintenance Manual Change Notice No. 233, dated March 1976, or an FAA-approvedequivalent. For all other airplanes, inspect and rectify the air conditioning system in accordance with a procedure approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region. (3) Incorporate the following operating limitations in the airplane flight manual: (i) The airplane may not be operated with a feeder tank fuel quantity gage needle in a red zone. (ii) Takeoff is prohibited if evidence of fuel overflow from drain at fuselage Frame 33, or from the drain mast, is observed. (iii) If fuel fumes are detected in flight, the airplane may only be flown to the nearest base where repairs can be performed. (Fan Jet Falcon Flight Manual Revision dated March 17, 1976, deals with the operating limitations specified in paragraph (a)(3)(i) and (ii) of this paragraph. FJF Maintenance Manual Change Notice Nos. 229, 230, and 233 dated March 1976, contain inspection and rectification information for the fuel tank pressurization and air conditioning systems that relate to the deficiencies covered by the operating limitations covered by this paragraph.) (b) For airplanes not incorporating the fuel tank pressurization system drain provisions of AMD Service Bulletin No. 293, dated January 15, 1968, or an FAA-approved equivalent, within 10 hours time in service after the effective date of this AD replace the placards at the fuel filler opening of each wing tank with new placards that limit the maximum fuel capacity to 1455 kg (3,200 lb). (c) Within the next 100 hours time in service or 60 days after the effective date of this AD, whichever occurs later, accomplish the following: (1) Decrease the usable capacity of the fuel feeder tanks in accordance with AMD Service Bulletin No. 554, dated March 18, 1976, or an FAA-approved equivalent. For airplanes serial numbers 1 through 29, incorporate feeder tank float valves, in accordance with AMD Service Bulletin No. 161, Revision 1, dated November 18,1966, or an FAA-approved equivalent. (2) Enlarge the diameter of the wing tank pressurization system drain hole in accordance with AMD Service Bulletin No. 555, dated March 18, 1976, or an FAA-approved equivalent. For airplanes serial numbers 1 through 124 incorporate drain hole provisions, in accordance with AMD Service Bulletin No. 293, dated January 15, 1968, or an FAA-approved equivalent. (d) Prior to the accumulation of 150 hours time in service after accomplishment of paragraph (c) of this AD, and, thereafter, at intervals not to exceed 150 hours time in service since the last inspection, inspect and rectify, as necessary, the fuel overflow drain at fuselage Frame 33, in accordance with FJF Maintenance Manual Change Notice No. 231, subparagraph 3 C, dated March 1976, or an FAA-approved equivalent. (e) Upon the request of an operator, an FAA maintenance inspector, subject to prior approval of the Regional Director, 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 for that operator. This amendment becomes effective September 30, 1976.
99-12-01: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-12-01, which was sent previously to all known U.S. owners and operators of Eurocopter Model EC135 helicopters by individual letters. This AD requires initial and repetitive visual inspections and one dye-penetrant inspection of the main rotor hub shaft (shaft) for cracks. If a crack is found during any of the inspections, this AD requires replacing the shaft with an airworthy shaft before further flight. This amendment is prompted by the discovery of fatigue cracks on the shaft of a helicopter. The actions specified by this AD are intended to detect fatigue cracks in the shaft that could lead to shaft failure and subsequent loss of control of the helicopter.
87-14-08: 87-14-08 DEHAVILLAND AIRCRAFT COMPANY OF CANADA, A DIVISION OF BOEING OF CANADA, LTD.: Amendment 39-5677. Applies to all Model DHC-7 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To preclude a fuel fire in the wing landing light bay, accomplish the following: A. Within the next 50 hours time-in-service after the effective date of this AD, gain access to the No. 4 flap track canoe "footprint area," the tank end ribs, and the wing box outboard of the No. 1 and No. 4 wing fuel tanks, in accordance with Paragraph A. of the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin 7-57-30, dated March 6, 1987, or Revision A, dated May 8, 1987. Conduct an external inspection of the tank end ribs, wing box outboard of the fuel tanks, and complete front spar to rear spar footprint areas of each No. 4 flap track canoe installation, in accordance with Paragraph B. of the Accomplishment Instructions of the service bulletin. If evidence of fuel leakage is found, prior to further flight perform an internal inspection, repair, and pressure test of the fuel tank, in accordance with Paragraph C. of the Accomplishment Instructions of the service bulletin. B. Within 200 hours time-in-service after the effective date of this AD, install Modification 7/2536, in accordance with Paragraph D. of the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin 7-57-30, dated March 6, 1987, or Revision A, dated May 8, 1987. C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the inspections and modifications required by this AD. All persons affected by this directivewho have not already received the appropriate service information from the manufacturer may obtain copies upon request to The de Havilland Aircraft Company of Canada, a Division of Boeing of Canada, Ltd., Garrett Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment becomes effective August 1, 1987.
2013-23-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200 and -200PF series airplanes. This AD was prompted by reports indicating that a standard access door was located where an impact-resistant access door was required, and stencils were missing from some impact-resistant access doors. This AD requires an inspection of the left- and right-hand wing fuel tank access doors to determine that impact-resistant access doors are installed in the correct locations, and to replace any door with an impact-resistant access door if necessary. This AD also requires an inspection for stencils and index markers on impact-resistant access doors, and application of new stencils or index markers if necessary. This AD also requires revising the maintenance program to incorporate changes to the airworthiness limitations section. We are issuing this AD to prevent foreign object penetration of the fuel tank, which could cause a fuel leak near an ignition source (e.g., hot brakes or engine exhaust nozzle), consequently leading to a fuel-fed fire.
2010-13-07: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA-32R-301T and PA-46-350P airplanes. This AD requires you to replace specific spot-welded, V-band exhaust coupling with a riveted, V-band exhaust coupling. This AD results from reports that spot-welded, V-band exhaust couplings are failing. We are issuing this AD to prevent failure of the V-band exhaust coupling, which could cause the exhaust pipe to detach from the turbocharger. This failure could result in release of high-temperature gases inside the engine compartment and possibly cause an in-flight fire. An in-flight fire could lead to loss of control.
88-02-04: 88-02-04 MARVEL SCHEBLER (FACET AEROSPACE PRODUCTS COMPANY): Amendment 39-5830. Applies to Marvel Schebler (Facet) Model MA-3PA carburetors, Part Numbers A10-5220, A10-5257, and A10-5267 manufactured since June 30, 1985, and having serial numbers as listed herein: Carburetors Serial Number Model: MA-3PA DD-4-1583 through DD-4-1610 P/N: A10-5220 DD-4-1613, DD-4-1614, DD-4-1617, (Lycoming P/N: LW-16072) DD-4-1619 through DD-4-1622 Lycoming Engine Models: DD-4-1624 through DD-4-1627 O-235-C1C, O-235-L2A, and O-235-L2C DD-4-1629, DD-4-1632, and DD-4-1633 Model: MA-3PA DM-3-1818 through DM-3-1826, P/N: A10-5257 DM-3-1828 and DM-3-1829 (Lycoming P/N: LW-16677) Lycoming Engine Models: O-235-L2C and O-235-H2C Model: MA-3PA DT-3-1911 through DT-3-1913, P/N: A10-5267 DT-3-1916, DT-3-1917 (Lycoming P/N: LW-16677) DT-3-1920, DT-3-1921, and Lycoming Engine Models: DT-3-1923 through DT-3-1981 O-235-L2C, O-235-N2C, and O-235-P1Compliance is required within the next 25 hours time in service or 30 days, whichever occurs first, after the effective date of this AD, for all applicable carburetors, unless already accomplished. To prevent possible loss of engine power due to a loose metering sleeve, accomplish the following: (a) Check all Textron Lycoming Model O-235-C1C, O-235-L2A, O-235-L2C, O-235-H2C, O-235-N2C, and O-235-P1 engines incorporating Marvel Schebler (Facet) Model MA-3PA carburetors, Part Numbers A10-5220, A10-5257, and A10-5267 manufactured since June 30, 1985, to determine the carburetor serial number. This serial number can be found on the carburetor nameplate located on the throttle body. (b) If the serial number is one of those listed, remove the carburetor, tag it as unairworthy, and replace it with a serviceable one prior to further flight. If the serial number is not one of those listed above, no further corrective action is required. (c) Make an engine logbook entry that this AD has been complied with. NOTE (1): Facet Service Bulletin (SB) A1-87, dated October 1987, pertains to this subject and gives instructions for returning the affected carburetors directly to the factory for corrective action. If being returned to the factory, the owner should package the carburetor to prevent enroute damage and ship directly to Facet Aerospace Products Company, 1048 Industrial Park Road, Bristol, Virginia 24201, USA, Attention: William Smith. NOTE (2): To indicate carburetor corrective action has been taken, Facet will have stamped the lower portion of the carburetor nameplate with the number "87", in which case no further action is required. NOTE (3): Persons authorized by FAR 43.3(g) may perform the check of paragraph (a) and engine logbook entry of paragraph (c) of this AD if the carburetor serial number is not one of those listed above. (d) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 toa base where the AD can be accomplished. (e) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, New York Aircraft Certification Office, ANE-170, Federal Aviation Administration, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. (f) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, New York Aircraft Certification Office, Valley Stream, New York, may adjust the compliance time specified in this AD. This amendment 39-5830 becomes effective on February 1, 1988.
99-18-02: This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 205A-1 and 205B helicopters, that requires inspecting the vertical fin spar cap (spar cap) for cracking, corrosion, or disbonding; modifying the vertical fin; and replacing the left-hand spar cap. This amendment is prompted by five accidents involving helicopters of similar type design. The actions specified by this AD are intended to detect fatigue cracking or corrosion on the spar cap, which could lead to failure of the vertical fin spar, loss of the tail rotor, and subsequent loss of control of the helicopter.
2013-23-19: We are adopting a new airworthiness directive (AD) for XtremeAir GmbH Model XA42 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 cracks in a weld seam between the lower left landing gear attachment bearing and the lower engine mount to the firewall attachment plate, which could reduce the structural integrity of the airplane and could result in engine separation. We are issuing this AD to require actions to address the unsafe condition on these products.
99-14-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes, that requires inspections to verify correct installation of certain fasteners located on the trailing edges of the horizontal and vertical stabilizer; replacement of the existing fasteners with new fasteners installed with wet sealant; and follow-on actions, if necessary. This amendment is prompted by reports indicating that, during manufacture of the horizontal and vertical stabilizers, certain fasteners attaching the aluminum ribs and brackets to the trailing edges on the empennage were not correctly installed with wet sealant. The actions specified by this AD are intended to prevent corrosion and possible cracking of those aluminum parts, which could result in loss of the attachment of the elevator and rudder to the empennage and consequent reduced controllability of the airplane.
82-08-01: 82-08-01 DOWTY ROTOL: Amendment 39-4356. Applies to Dowty Rotol Propellers (c)R.209/4-40.5/2, installed on Nihon YS-11 airplanes; (c)R.245/4-40.5/13, installed on Convair Models 600(240D) and 640(340D); and (c)R.259/4-40-4.5/17, installed on Convair Model 640(440D) airplanes, not modified by Dowty Rotol Modification (c)VP2693 in accordance with Dowty Rotol SB No. 61-728, Revision 3, dated July 17, 1981. Compliance required as indicated unless already accomplished. To detect and prevent loosening of the propeller blade groups, accomplish the following: (a) Unless already accomplished, within the next 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, inspect the locking of the blade groups in the hub group, in accordance with Dowty Rotol Service Bulletin 61-581, Revision 3, dated July 17, 1981, or an FAA-approved equivalent. (b) If, during the inspections required by paragraph (a), it is found that the red line position markings across the bearing center race and the hub have separated by more than 0.100 of an inch, before further flight, replace the propeller with a serviceable propeller of the same model number. (c) If, during the inspections required by paragraph (a), it is found that the lockpieces on the rear of the cylinder are damaged or they are not engaging with and locking the serrations of the bearing center race of the blade group; or that the set bolts securing the lockpieces are not secure or they are bent; or that the shims under the distance blocks on which the lockpieces are mounted have extruded, before further flight, replace the defective parts with serviceable parts of the same part number. This AD supersedes AD 67-32-02. This amendment becomes effective April 12, 1982.