Results
83-09-03: 83-09-03 BELL HELICOPTER TEXTRON, INC.: Amendment 39-4646. Applies to Bell Model 222 helicopters, S/N 47006 through 47089, certificated in all categories (Airworthiness Docket No. 83-ASW-2). Compliance is required as indicated. To prevent fatigue failure of the main rotor trunnion, P/N 222-010-154-101, and mast assembly, torquemeter, P/N 222-040-002-103, which could result in loss of a helicopter, accomplish the following: (a) For main rotor trunnions, P/N 222-010-154-101, with 2400 or more hours time in service on the effective date of this AD, retire the main rotor trunnion within the next 100 hours time in service. (b) For mast assemblies, torquemeter, P/N 222-040-002-103, with 3500 or more hours time in service on the effective date of this AD, retire the mast assembly, torquemeter within the next 100 hours time in service if it is utilized exclusively with trunnion, P/N 222-010- 154-101. (c) For main rotor trunnions, P/N 222-010-154-101, with lessthan 2400 hours time in service on the effective date of this AD, retire the main rotor trunnion at 2500 hours. (d) For mast assemblies, torquemeter, P/N 222-040-002-103, with less than 3500 hours time in service on the effective date of this AD, retire the mast assembly, torquemeter at 3600 hours if it is utilized exclusively with trunnion, P/N 222-010-154-101. (e) For mast assemblies, torquemeter, P/N 222-040-002-103, which are used with both trunnions, P/N 222-010-154-101 and P/N 222-010-154-111, determine the retirement life by dividing the time the main rotor mast has been in service with trunnion, P/N 222-010-154- 101, by 0.72 and adding the result to the time in service with trunnion, P/N 222-010-154-111. When this total time exceeds 5000 hours, retire the mast assembly, torquemeter. (f) Any equivalent method of compliance with this AD must be approved by the Manager, Aircraft Certification Division, Southwest Region, Federal Aviation Administration. (g)In accordance with FAR 21.197, flight is permitted to a base where the requirements of this AD may be accomplished. (Bell Helicopter Alert Service Bulletin No. 222-82-17 pertains to this subject.) This amendment becomes effective May 23, 1983.
2005-26-18: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce Deutschland (formerly Rolls-Royce plc) (RRD) models Tay 650-15 and 651-54 turbofan engines. That AD currently requires borescope inspection of the high pressure compressor (HPC) stage 12 disc assembly to detect damage caused by HPC outlet guide vane (OGV) retaining bolt failure, and replacement of unserviceable parts with serviceable parts. That AD also requires as terminating action, the incorporation of a new design retention arrangement for the HPC OGV to prevent HPC OGV retaining bolt failure. This ad requires the same actions but extends the terminating action compliance time for Tay 650- 15 engines. This AD also includes references to later revisions of two of the applicable RRD service bulletins (SBs). This AD results from RRD relaxing the terminating action compliance time for Tay 650-15 engines due to reassessment by RRD. We are issuing this AD to prevent an uncontained failure of the HPCstage 11/12 disc spacer, which could result in damage to the airplane. DATES: This AD becomes effective February 3, 2006. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of February 15, 2002 (67 FR 4652, January 31, 2002).
2019-15-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A321-251N, A321-252N, A321-253N, A321-271N, A321-272N, A321-251NX, A321-252NX, A321-253NX, A321-271NX, and A321-272NX airplanes. This AD was prompted by analysis of the behavior of the elevator aileron computer (ELAC) L102 that revealed that excessive pitch attitude can occur in certain conditions and during specific maneuvers. This AD requires revising the airplane flight manual (AFM) to incorporate updated procedures and operational limitations, 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.
99-03-03: This amendment supersedes an existing airworthiness directive (AD), applicable to Allison Engine Company Model AE 3007A turbofan engines, that currently requires reprogramming the Full Authority Digital Engine Control (FADEC) to software version VI.2. This amendment requires reprogramming the FADEC to a serviceable software version and reidentifying the FADEC assembly. This amendment is prompted by reports of at least seven uncommanded engine shutdowns, four of which occurred in flight, as a result of deficiencies in software version VI.2 on the AE 3007A engines and version VI.4 on the AE 3007A1/1 engines. The actions specified by this AD are intended to prevent an unintentional or uncommanded in-flight engine shutdown.
78-16-01: 78-16-01 BELL HELICOPTER TEXTRON (BHT): Amendment 39-3271. Applies to Models 206A and 206B helicopters, serial numbers 148 and 414 through 913, certificated in all categories. Compliance is required within the next 500 hours times in service after the effective date of this airworthiness directive unless already accomplished. To minimize the possibility of loss of directional control due to failure of the tail rotor drive shaft, remove and replace the tail rotor drive shaft bearing hangers with improved bearing hangers as specified below: a. REMOVE INSTALL (Shim Type) (Spring Type) One (1) hanger P/N 206-040-345-5 One (1) hanger P/N 206-040-345-9 or P/N 206-040-355-1 One (1) hanger P/N 206-040-346-5 One (1) hanger P/N 206-040-346-17 Five (5) hangers P/N 206-040-338-1 Five (5) hangers P/N 206-040-338-9 b. Shim type hangers modified to the spring type using instructions provided in Technical Bulletin No. 206-77-7 will be acceptable for compliance with this AD. c. All spring clamp type bearing hangers, P/N's 206-040-338-9, 206-040-355-1, 206-040-345-9, and 206-040-346-17 must be installed with the spring on the left side of the tail boom. d. To prevent bearing hangers from chafing the drive shaft cover, the cover must be modified in accordance with Bell Helicopter Company Technical Bulletin No. 206-76-2 dated January 7, 1976, (misdated 206-76-2), or later FAA approved revision or FAA approved equivalent. e. Removal and replacement, as prescribed by paragraph a., must be in accordance with the applicable maintenance and overhaul instructions. Bell Helicopter Company Service Bulletin No. 206-77-9 pertains to and provides instructions for accomplishing the intent of this AD. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part thereof pursuant to U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Service Manager, Bell Helicopter Textron, Post Office Box 482, Fort Worth, Texas 76101. These documents may also be examined at Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106, and at Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. Equivalent means of compliance with the modifications prescribed by this Airworthiness Directive may be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Post Office Box 1689, Fort Worth, Texas 76101. This amendment becomes effective September 14, 1978.
60-03-02: 60-03-02 CURTISS-WRIGHT: Amdt. 99 Part 507 Federal Register February 2, 1960. Applies to all C-46 Series aircraft including the C-46R and C-46/CW20-T aircraft. To eliminate the possibility of a fire in the cargo and baggage compartments being caused by unshielded sources of heat, compliance with CAR 4b.382(d)(See Note 1) must be accomplished by March 1, 1960. NOTE 1: Section 4b.382(d) of the Civil Air Regulations provides as follows: "Sources of heat within the compartment shall be shielded and insulated to prevent igniting the cargo." In a note to that section it further provides that "Sources of heat likely to ignite cargo include light bulbs, combustion heaters, heater ducts, electrical appliances, etc."
2005-26-16: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Airbus Model A300-600 and A310 series airplanes. That AD currently requires repetitive visual inspections to detect corrosion on the lower rim area of the fuselage rear pressure bulkhead; and follow-on actions, if necessary. This new AD requires new repetitive inspections for corrosion on the rear pressure bulkhead between stringer (STGR) 27 (right hand) and STGR27 (left hand), and related investigative and corrective actions if necessary. This AD also requires sending a report of certain information to the manufacturer. The AD also adds airplanes to the applicability of the existing AD. This AD results from findings of severe corrosion on airplanes previously inspected in accordance with the existing AD. We are issuing this AD to detect and correct corrosion at the lower rim area of the fuselage rear pressure bulkhead, which could result in reduced structural integrity of the bulkhead, andconsequent decompression of the cabin.
2019-15-08: The FAA is superseding Airworthiness Directive (AD) 2002-07- 05, which applied to all Airbus Model A300 B2, A300 B4, A300 B4-600, and A300 B4-600R series airplanes, and Model A300 F4-605R airplanes. AD 2002-07-05 required repetitive inspections for cracking of certain fittings, corrective action if necessary, and, for certain airplanes, a modification. This AD requires repetitive inspections for cracking of certain fittings, corrective actions if necessary, and, for certain airplanes, a modification; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that, for certain airplanes, the existing inspection compliance times were not sufficient to address the unsafe condition and needed to be reduced. The FAA is issuing this AD to address the unsafe condition on these products.
99-03-01: This amendment adopts a new airworthiness directive (AD) that applies to certain Schempp-Hirth K.G. (Schempp-Hirth) Models Standard-Cirrus, Nimbus-2, JANUS, and Mini-Nimbus HS-7 sailplanes. This AD requires installing a safety device for the tailplane locking hook. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent the locking hook on the tailplane attachment bracket from disengaging, which could result in the horizontal tailplane coming loose from the fin with possible loss of longitudinal control of the sailplane.
2005-26-12: The FAA adopts a new airworthiness directive (AD) to supersede AD 2004-08-13, which applies to certain BURKHARDT GROB LUFT-UND RAUMFAHRT GmbH & CO KG (Burkhardt Grob) Models G103 TWIN ASTIR, G103 TWIN II, G103 TWIN III ACRO, and G103 C Twin III SL sailplanes. AD 2004-08-13 currently requires you to replace the center of gravity (CG) release hook attachment brackets with brackets of improved design. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. This AD retains all the actions required in AD 2004-08-13 and adds Model G103A TWIN II ACRO sailplanes to the applicability. We are issuing this AD to prevent abnormal or uncontrolled sailplane release due to cracked CG release hook attachment brackets. This condition could result in reduced or loss of sailplane control. DATES: This AD becomes effective on February 6, 2006. On June 4, 2004 (69 FR 21402, April 21, 2004), the Director of the Federal Register approved the incorporation by reference of Grob Service Bulletin No. MSB315-62, dated January 21, 2002, and Grob Service Bulletin No. MSB869-22, dated January 22, 2002. As of February 6, 2006, the Director of the Federal Register approved the incorporation by reference of Grob Service Bulletin No. MSB315-62/2, dated March 9, 2005.