Results
95-12-06: This amendment adopts a new airworthiness directive (AD) that applies to certain Jetstream Aircraft Limited (JAL) Jetstream Models 3101 and 3201 airplanes. The action requires modifying the shear fitting at the top of each escape hatch. A report of interference between the shear fitting on an escape hatch and a ceiling panel found while removing the escape hatch on one of the affected airplanes prompted this AD. The actions specified by this AD are intended to prevent the inability to utilize an escape hatch during an emergency situation because of interference.
2023-25-13: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (604 Variant) airplanes. This AD was prompted by a report that some airplanes were delivered without a portable protective breathing equipment (PBE) device located in the left-side forward wardrobe, flight deck, or passenger cabin area of the airplane. This AD requires visually inspecting the forward left side cabin area of the airplane to determine if the portable PBE device is installed and, if not installed, requires installing the portable PBE device along with the associated placard. The FAA is issuing this AD to address the unsafe condition on these products.
96-09-19: This amendment adopts a new airworthiness directive (AD), applicable to all Jetstream Model 4101 airplanes, that requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to prevent minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
2005-05-53 R1: The FAA is adopting a new airworthiness directive (AD) to revise emergency AD 2005-05-53 for The Cessna Aircraft Company (Cessna) Models 172R, 172S, 182T, and T182T airplanes. This AD contains the same information as emergency AD 2005-05-53 R1 and publishes the action in the Federal Register. It requires you to do a one-time detailed inspection of the flight control system, correct installations that do not conform to type design, and repair any damage. This AD is the result of flight control system problems found on airplanes within Cessna's control that could also exist on airplanes produced and delivered within a certain time period. We are issuing this AD to prevent loss of airplane control due to incorrect or inadequate rigging of critical flight systems. DATES: This AD becomes effective on March 21, 2005, to all affected persons who did not receive emergency AD 2005-05-53 R1, issued March 5, 2005. Emergency AD 2005-05-53 R1 contained the requirements of this amendment and became effective immediately upon receipt. As of March 21, 2005, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations. We must receive any comments on this AD by April 30, 2005.
2023-25-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318-112 airplanes; Model A319-115, -132, -133, -151N, -153N, and -171N airplanes; Model A320-211, -212, -214, -231, -232, - 251N, -252N, -253N, -271N, -272N, and -273N airplanes; and Model A321- 112 airplanes. This AD was prompted by a report that the fatigue life limit of the motoreductor installed on the on-board entrance stairs is not demonstrated for the complete airplane design service goal (DSG). This AD requires repetitive replacement of the motoreductor for onboard entrance stairs, and it limits the installation of affected parts under certain conditions, 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.
2023-26-01: The FAA is adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 190-300 and -400 airplanes. This AD was prompted by a report that the method for calculating level-off altitude by the computerized airplane flight manual (CAFM), may result in a non- conservative level-off height. This AD requires revising the existing airplane flight manual (AFM) to incorporate new CAFM versions as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2005-06-12: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SP, and 747SR series airplanes. That AD currently requires one-time inspections for cracking in certain upper deck floor beams and follow-on actions. This new AD expands the existing inspection area and requires inspecting fastener holes in certain areas of airplanes modified previously, and taking corrective actions if necessary. This action also defines new sources for instructions for repairs and post-modification/repair inspections. This AD is prompted by reports of fatigue cracking of the upper chord of certain upper deck floor beams. We are issuing this AD to find and fix cracking in certain upper deck floor beams, which could extend and sever floor beams adjacent to the body frame and result in rapid depressurization and loss of controllability of the airplane. \n\n\nDATES: This AD becomes effective April 25, 2005.The incorporation by reference of Boeing Service Bulletin 747- 53A2459, Revision 1, dated March 11, 2004, is approved by the Director of the Federal Register as of April 25, 2005. \n\n\tOn October 16, 2002 (67 FR 57510, September 11, 2002), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2459, dated January 11, 2001.
96-06-12: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 96-06-12 which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron, Inc. (Bell) Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47-K helicopters by individual letters. This AD requires a visual inspection of each tail rotor blade (blade) tip, abrasion strip, blade skin, and blade butt for corrosion or delamination. This amendment is prompted by reports that a number of Model 47 helicopter blades were manufactured using a clad aluminum alloy material instead of a bare aluminum alloy material. The actions specified by this AD are intended to prevent premature delamination or separation of the blade tip block or the abrasion strip, which could lead to failure of the blade and subsequent loss of control of the helicopter.
2023-25-11: The FAA is superseding Airworthiness Directive (AD) 2021-02- 18, which applied to all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, and CN-235-300 airplanes and Model C-295 airplanes. AD 2021-02-18 required repetitive inspections for cracking or broken rivets of certain left- and right-hand stringers and surrounding structure, and repair if necessary. This AD was prompted by a modification that was developed to reinforce the structure in the affected area, providing terminating action for the repetitive inspections required by AD 2021-02-18. This AD continues to require certain actions in AD 2021-02-18 and requires the new terminating action for the repetitive inspections, 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.
91-12-09: 91-12-09 GENERAL ELECTRIC COMPANY: Amendment 39-7020. Docket No. 91-ANE- 11. Applicability: General Electric Company (GE) CF6-6 series turbofan engines installed on, but not limited to, McDonnell Douglas DC10-10 aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent an uncontained engine failure and damage to the aircraft, accomplish the following: (a) Eddy current inspect in accordance with GE CF6-6 Service Bulletin (SB) 72- 947, Revision 4, dated February 8, 1991, the bore forward corner of stage 1 fan disks identified by serial number (S\N) in Tables 2, 3, and 3 Addendum of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991, as follows: (1) For disks which have not received an eddy current inspection in accordance with the Accomplishment Instructions of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991, in accordance with the following schedule: (i) Within the next 100 cycles in service (CIS) after the effective date of this AD for those disks which on the effective date of this AD have accumulated 1,250 CIS or greater since accomplishing the immersion ultrasonic inspection of AD 89-20-01 R1, Amendment 39-6411 (54 FR 51015; December 12, 1989). (ii) Within the next 100 CIS after the effective date of this AD or prior to accumulating 1,250 CIS since accomplishing the immersion ultrasonic inspection of AD 89-20-01 R1, whichever comes later for those disks which on the effective date of this AD have accumulated less than 1,250 CIS since the immersion ultrasonic inspection. (2) For those disks which on the effective date of this AD have received an eddy current inspection in accordance with the Accomplishment Instructions of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991, in accordance with the following schedule: (i) Within the next 100 CIS after the effective date of this AD for those disks which on the effective date of this AD have accumulated 1,500 CIS or greater since accomplishing the immersion ultrasonic inspection of AD 89-20-01 R1. (ii) Within the next 100 CIS after the effective date of this AD or prior to accumulating 1,500 CIS since accomplishing the immersion ultrasonic inspection of AD 89-20-01 R1, whichever comes later, for those disks which on the effective date of this AD have accumulated less than 1,500 CIS since accomplishing the immersion ultrasonic inspection. (b) Thereafter, eddy current inspect the bore forward corner of stage 1 fan disks which meet the acceptance criteria of paragraph 2.B.(2)(c) of the Accomplishment Instructions of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991, at intervals not to exceed 500 CIS since last eddy current inspection. (c) Remove from service prior to further flight and replace with a serviceable part, disks inspected in accordance with paragraphs (a) and (b) of this AD, which do not meet the acceptance criteria of paragraph 2.B.(2)(c) of the Accomplishment Instructions of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991. (d) Remove from service all stage 1 fan disks identified by S/N in Tables 2, 3, and 3 Addendum of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991, at the next shop visit but no later than 2,500 CIS since immersion ultrasonic inspection or June 30, 1992, whichever occurs first. (e) For the purpose of this AD, "shop visit" is defined as the induction of the engine into the shop for any reason. (f) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (g) Upon submission of substantiating data by an owner or operator through an FAA (maintenance, avionics, or operations) Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedules specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803- 5299. The inspections shall be done in accordance with the following General Electric service document: Document No. Page No. Issue Date CF6-6 SB 72-947 1 thru 13 Rev. 4 Feb. 8, 1991 Total Pages: 13 This incorporation was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to General Electric Company, Technical Publications Department, 1 Neumann Way, Cincinnati, Ohio 45215. This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. This amendment (39-7020, AD 91-12-09) becomes effective on June 27, 1991.