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2022-14-07: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports that some oxygen box assemblies had their piston ejected during the mask deployment test. This AD requires a one- time inspection of each passenger oxygen box dual manifold assembly to find and replace affected parts. This AD also prohibits installing affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
99-15-05: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes, and C-9 (military) airplanes, that requires a one-time visual inspection to determine if all corners of the aft lower cargo doorjamb have been previously modified. This amendment also requires low frequency eddy current inspections to detect cracks of the fuselage skin and doubler at all corners of the aft lower cargo doorjamb, various follow-on repetitive inspections, and modification, if necessary. This amendment is prompted by fatigue cracks found in the fuselage skin and doubler at the corners of the aft lower cargo doorjamb. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.
69-19-04: 69-19-04 SLINGSBY: Amdt. 39-841. Applies to Model T.53B Gliders. To ensure that the glider can be trimmed when being aero-towed, within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, check to determine that the tailplane incidence is 1 degree 50' + 20'. If it is incorrect change the incidence of the tailplane to 1 degree 50' + 20' measured from the aircraft datum in accordance with Slingsby Aircraft Company Ltd., Technical Instruction No. 40, dated July 1969 or later ARB issue or an FAA approved equivalent. This amendment becomes effective September 15, 1969.
2022-14-10: The FAA is superseding Airworthiness Directive (AD) 2018-13- 08, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2018-13-08 required repetitive inspections for cracking of the radius of the front spar vertical stringers and the horizontal floor beam on frame (FR) 36, repetitive inspections for cracking of the fastener holes of the front spar vertical stringers on FR 36, and repair if necessary, and, for certain airplanes, a potential terminating action modification of the center wing box area. This AD was prompted by a determination that additional airplanes are subject to the unsafe condition. This AD revises the applicability by adding airplanes and retains the requirements of AD 2018-13-08; 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.
99-14-08: This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney (PW) JT9D series turbofan engines, that currently requires initial and repetitive inspections of the sixth stage low pressure turbine (LPT) inner airseal, and modification of the sixth stage LPT inner airseal to reduce the potential for two failure modes. This amendment requires additional repetitive borescope inspections for sixth stage LPT inner airseals found with cracks less than one inch in length. This amendment is prompted by the publication of a revision to a PW service bulletin that introduces the new borescope inspections. The actions specified by this AD are intended to prevent an uncontained failure of the sixth stage LPT inner airseal, which can result in damage to the aircraft. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of September 13, 1999.
90-07-09: 90-07-09 SUD-SERVICE (FORMERLY SUD AVIATION): Amendment 39-6555. Docket No. 89-NM-246-AD. Applicability: Sud-Service Caravelle SE 210 Model III and VIR series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of the left-hand forward passenger door frame and subsequent decompression of the airplane, accomplish the following: A. Prior to the accumulation of 20,000 landings, or within 50 landings after the effective date of this AD, whichever occurs later, perform one of the following inspections in accordance with Sud- Service Service Bulletin 53-56, dated October 21, 1988: 1. Perform a visual inspection of the skin plating, stamping, and visible edge of the fitting, plus a dye penetrant inspection of the fitting edge; or 2. Perform an X-ray inspection in accordance with the following maintenance manuals: a. For Mark III airplanes - Chapter 53-1-1, Figure 606; b. For Mark VIR airplanes - Chapter 53-12-1, Figure 604; or 3. Perform an inspection of holes by defectometer, after removal of fasteners identified on Figure 606 (Mark III) or Figure 604 (Mark VIR), as applicable; or 4. Perform an inspection of holes by rototest, after removal of fasteners identified on Figure 606 (Mark III) or Figure 604 (Mark VIR), as applicable. B. If no cracks are found, repeat the inspections at the following intervals: a. If the immediately preceding inspection was performed by visual method and dye check, the next inspection must be performed within 100 landings. b. If the immediately preceding inspection was performed by X-ray, the next inspection must be performed within 300 landings. c. If the immediately preceding inspection was performed by defectometer, the next inspection must be performed within 2,000 landings. d. If the immediately preceding inspection was performed by rototest, the next inspection must be performed within 4,000 landings. C. If cracks are found, repair prior to further flight, in accordance with Sud-Service Service Bulletin 53-56, dated October 21, 1988. Thereafter, repeat visual inspections of the fasteners around the edge at intervals not to exceed 500 landings, and replace with a new fitting prior to the accumulation of 5,000 landings, in accordance with the service bulletin. D. Upon the installation of a new fitting, perform the initial inspection prior to the accumulation of 20,000 landings, in accordance with paragraph A., above, and thereafter at intervals specified in paragraph B., above. E. 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, Standardization Branch, ANM- 113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and thensend it to the Manager, Standardization Branch, ANM-113. F. 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 Aerospatiale, 316 Rue de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6555, AD 90-07-09) becomes effective on May 1, 1990.
92-22-12: 92-22-12 BRITISH AEROSPACE: Amendment 39-8398. Docket No. 92-NM-50-AD. Applicability: Model BAe 146-100A series airplanes, Constructor's Nos. E1002 and subsequent; Model BAe 146-200A series airplanes, Constructor's No. E2008 and subsequent; and Model BAe 146-300A series airplanes, Constructor's Nos. E3118 and subsequent; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent loss of normal braking during ground operations, accomplish the following: (a) For airplanes having pre-Modification HCM00716B configuration: Within 6 months after the effective date of this AD, remove the anti-skid control box, and install a new anti-skid control box, Modification HCM70491A; and perform an operational test on the anti-skid control box; in accordance with British Aerospace BAe 146 Service Bulletin SB.32-124-70491A&B, Revision 1, dated November 25, 1991; or Revision 2, dated June 30, 1992. (b) For airplanes having post-modification HCM00716B configuration: Within 6 months after the effective date of this AD, remove the anti-skid control box, and install a new anti-skid control box, Modification HCM70491B; and perform an anti-skid braking system integrity test; in accordance with British Aerospace BAe 146 Service Bulletin SB.32-124-70491A&B, Revision 1, dated November 25, 1991; or Revision 2, dated June 30, 1992. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.(d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The replacement, operational test, and integrity test shall be done in accordance with the following British Aerospace BAe 146 service bulletins, as applicable, which contain the specified effective pages: Service Bulletin Referenced and Date Page Number Revision Level Shown on Page Date Shown on Page SB.32-124-70491A&B 1, 3, 6 1 November 25, 1991 Revision 1, November 25, 1991 2, 4-5, 7-10 Original (Not dated) SB.32-124-70491A&B 1, 3, 6 2 June 30, 1992 Revision 2, June 30, 1992 2, 4-5, 7-10 Original (Not dated) This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on December 3, 1992.
99-14-06: This amendment adopts a new airworthiness directive (AD) that is applicable to MT-Propeller Entwicklung GMBH Models MTV-9-B-C and MTV-3-B-C propellers. This action requires initial and repetitive inspections of Torx head blade root lag screws for torque values and breakage, and, if any screws are found broken or with insufficient torque, replacement of all screws with new lag screws. In addition, this AD requires replacement of certain model Torx head blade root lag screws with improved, hexagonal head blade root lag screws. This amendment is prompted by reports of broken Torx head blade root lag screws. The actions specified in this AD are intended to prevent blade root lag screw breakage, which could result in propeller blade separation and loss of control of the airplane.
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.