Results
2017-14-04: We are superseding Airworthiness Directive (AD) 95-26-13 for certain Piper Aircraft, Inc. Models PA-28-140, PA-28-150, PA-28-151, PA-28-161, PA-28-160, PA-28-180, PA-28-181, PA-28-235, PA-28-236, PA- 28R-180, PA-28R-200, PA-28R-201, PA-28S-160, PA-28S-180, PA-32-260, PA- 32-300, PA-32-301, PA-32-301T, PA-32R-300, PA-32R-301 (SP), PA-32R-301 (HP), PA-32R-301T, PA-32RT-300, PA-32RT-300T, and PA-32S-300 airplanes equipped with oil cooler hose assemblies that do not meet certain technical standard order (TSO) requirements. AD 95-26-13 required inspections, replacement, and adjustment of the oil cooler hose assemblies, as well as providing for a terminating action. This AD retains all of the requirements of AD 95-26-13 and adds language to clarify those requirements. This AD was prompted by several inquiries asking for clarification of the AD's applicability and compliance requirements. We are issuing this AD to correct the unsafe condition on these products.
98-10-06: This amendment supersedes Airworthiness Directive (AD) 96-19-07, which currently requires the following on Burkhart Grob Luft-und Raumfahrt (Grob) Models G115C, G115C2, G115D, and G115D2 airplanes: installing a placard that restricts the never exceed speed (Vne) of the affected airplane models from 184 knots to 160 knots; installing on the airspeed indicator glass a red line at 296 km/h (160 knots); installing a placard that prohibits aerobatic maneuvers; and placing a copy of the AD in the Limitations Section of the airplane flight manual. This AD will temporarily retain the flight restrictions that are currently required by AD 96-19-07; and will eventually require accomplishing certain inspections and modifications, as terminating action for these flight restrictions. 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 loss of control ofthe airplane caused by excessive speed or aerobatic maneuvers.
62-24-02: 62-24-02\tBOEING: Amdt. 506 Part 507 Federal Register November 10, 1962. Applies to 707/720 Airplanes, Serial Nos. 18385-18397, 18400-18404, 18374, 18414-18419, 18411, 18372, 18373, 18335-18339, 18079-18082, 18423-18425, 18376, 18377, 18451-18453 Inclusive; Also Applies to Airplanes Which Have Been Modified By Operators to Incorporate Motor Operated Valves Per Boeing Service Bulletins 1414, 1483, 1484, 1489, 1490, 1491, 1492 and 1493. \n\tCompliance required within 350 hours of airplane time in service after the effective date of this directive, unless already accomplished. \n\tHydraulic system motor operated valves, Whittaker P/N 146505-1, incorporated in both the utility and auxiliary hydraulic systems, have failed in service due to stress corrosion in the end cover retaining nut. All failures have occurred in parts with the original heat treatment. To prevent such failures: \n\t(1)\tModify all valves by installing new end covers and nuts of the same Whittaker part number but identified by a blue anodized color; and \n\t(2)\tReplace the valve shear seals and the bearing with new longer seals and a new bearing. \n\t(Whittaker Service Bulletin SBC 2021 covers this same subject.) \n\tThis directive effective November 10, 1962.
98-10-07: This amendment adopts a new airworthiness directive (AD) that applies to all Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Model ASK 21 sailplanes that have certain modifications installed. This AD requires changing the sailplane flight manual s weight and balance information. 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 operator from using inaccurate weight and balance information provided in the sailplane flight manual (SFM), which could lead to hazardous flight conditions.
98-10-10: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 and 767 series airplanes. This action requires a one-time inspection to confirm the installation of Teflon sleeves over certain electrical wires inside conduits installed in the fuel tanks; and corrective actions, if necessary. This amendment is prompted by a report of missing Teflon sleeves, which protect the wiring insulation from chafing. The actions specified in this AD are intended to prevent such chafing, which could eventually expose the electrical conductor creating the potential for arcing from the wire to the conduit, and consequent fuel tank fire/explosion.
2017-10-19: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) Trent 1000-A2, Trent 1000-C2, Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, and Trent 1000-L2 turbofan engines. This AD requires initial and repetitive on-wing inspections of affected intermediate pressure compressor (IPC) rotor seals. This AD was prompted by a failure of the IPC rotor seal. We are [[Page 30956]] issuing this AD to correct the unsafe condition on these products.
64-12-04: 64-12-04 GENERAL DYNAMICS: Amdt. 742 Part 507 Federal Register June 5, 1964. Applies to All Models 22, 22M, 30 and 30A Aircraft. Compliance required within 1,500 hours' time in service after the effective date of this AD, unless already accomplished. Inadvertent operation of the engine air turbine starter at continuous overspeeds has occurred in flight. This caused failure of the starter with resultant damage to surrounding nacelle structure and propulsion systems. To preclude starter failures of this nature, the following modifications and airplane flight manual procedures are required: (a) Modify the Models 22, 22M, 30, and 30A starter operation warning systems to include a master warning light indication when the starter valve is in the open position in accordance with the following General Dynamics/Convair Service Bulletins or an FAA approved equivalent: (1) General Dynamics/Convair Service Bulletin 880 S.B. No. 80-5 for the Model 22. (2) General Dynamics/Convair Service Bulletin 880M S.B. No. 80-2 for the Model 22M. (3) General Dynamics/Convair Service Bulletin 990 S.B. No. 80-3 for the Models 30 and 30A. (b) As an alternative for Models 30 and 30A aircraft, relocate the existing starter operation warning lights from the flight engineer's panel assembly to the pilot's overhead control panel per General Dynamics/Convair Service Bulletin 990 S.B. No. 80-1. (c) FAA engineering approval of equivalent methods of complying with (a) shall be processed through the FAA, Aircraft Engineering Division, Western Region. (d) Revise the Emergency Procedures section of the appropriate FAA approved Airplane Flight Manual to incorporate the procedure for isolating a malfunctioning starter valve in flight as set forth in the following FAA approved General Dynamics/Convair Airplane Flight Manual revisions: (1) Revision 73 to CS 59-061 dated December 17, 1963, for Model 22-2 and Revision 74 to CS 59-019 dated December 17, 1963, for the Model 22-1. (2) Revision 34 to CS 61-008 dated December 17, 1963, for the Model 22M. (3) Revision 32 to CS 61-048 dated December 17, 1963, for the Model 30. (4) Revision 14 to CS 62-046 dated December 17, 1963, for the Model 30A. This directive effective July 6, 1964.
2005-20-31: The FAA is rescinding an existing airworthiness directive (AD) that applies to Honeywell FMS one million word (1M or 700K) data bases (9104 cycle or earlier) as installed in, but not limited to McDonnell Douglas Model MD-11 and MD-11F airplanes, Boeing Model 747-400 series airplanes, and Boeing Model 757 and 767 airplanes. That AD requires a revision to the FAA-approved Airplane Flight Manual (AFM) and installation of a placard to prohibit the use of Nondirectional Beacon (NDB) approaches for landing. That AD was prompted by an anomaly in the Honeywell FMS one million word (1M or 700K) data bases (9104 cycle or earlier). We issued that AD to prevent an airplane deviating from the published approach to the runway, which could lead to premature ground contact before reaching the runway. Since we issued that AD, we have determined that the Honeywell FMS one million word (1M or 700K) databases (9104 cycle or earlier) no longer exist on any of the affected airplanes.
84-01-03 R1: 84-01-03 R1 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4787 as amended by Amendment 39-5534. Applies to Models SA315, SE3160, SA316, and SA319 series helicopters, certificated in all categories, that are equipped with main gearbox "A" frame support assemblies, P/N 315A21.04.000, 315A21.05.000, 3160S22.04.000, and 000.1, or 3160S22.05.000, and 000.1. Compliance required as indicated, unless already accomplished. To prevent possible in-flight failure of an "A" frame due to fatigue cracks in either lower eye end-fitting, accomplish the following: (a) For Model SA315 series helicopters, comply with Lama SA315 Service Bulletin No. 01.18, Revision A, within 50 hours' time in service after the effective date of this AD. This bulletin established a finite service life for certain identified original and repaired "A" frame assemblies and permits only one-time replacement/repair of an eye end-fitting on each "A" frame assembly. Replacing a repair eye end-fitting with another repair eye end-fitting is prohibited. NOTE: The service bulletin establishes a 3,200-hour service life limit for certain original and repaired "A" frames and a 1,600-hour service life limit for certain other original and repaired "A" frames. (b) For Models SE3160, SA316, and SA319 series helicopters, comply with Alouette SB No. 01.49, Revision 1, dated May 30, 1986, within 50 hours' time in service after the effective date of this AD amendment. This bulletin establishes a finite service life for certain identified original and repaired "A" frame assemblies for these helicopters and permits only one-time replacement/repair of an eye end-fitting on each "A" frame assembly. Replacing a repair eye end-fitting with another repair eye end-fitting is prohibited. NOTE: Revision A of the service bulletin establishes for the Model SE3160 an 11,000- hour service life limit for certain original and repaired "A" frames and a 5,500-hour service life limit for certain other original and repaired "A" frames. Revision 1, dated May 30, 1986, instituted on Model SE3160 helicopters an unlimited service life for original "A" frames whose serial number is preceded by letters other than "RO". (Frames with RO serial numbers retain the 11,000-hour and 5,500-hour service life). For Model SE3160 helicopters, a repair eye end-fitting is limited to 5,500 hours service life. For the Models SA316B and C and SA319B helicopters, the service bulletin, Revision A and 1, retains the present 3,200 or 1,600-hour service life limit for certain original and repaired "A" frames and eye end-fittings and establishes a 1,600-hour service life for certain other original and repair eye end-fittings. (c) Aircraft may be flown in accordance with FAR 21.197 and 21.199 to a base where compliance may be accomplished. (d) The Director of the Federal Register approved the incorporation by reference of the manufacturer's specifications and procedures identified and described in this directive pursuant to 5 U.S.C. 552(a)(1). Persons may obtain copies of the service bulletins upon request to Aerospatiale Helicopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75051, Attention: Customer Support. The documents may be examined at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas. A file on this AD which includes the incorporated material in full is maintained at the regional office in Fort Worth, Texas. These materials are incorporated as they exist on the date of the approval and a notice of a change to the service life limits stated in these documents will be published in the Federal Register. (e) Equivalent means of complying with this AD must be approved by the Manager, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. This procedure shall be done in accordance with AerospatialeAlouette SB No. 01.49, Revision 1, dated May 30, 1986. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a)(1). Copies may be obtained from Aerospatiale Helicopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75051, Attention: Customer Support. Copies may be inspected at the Office of the Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C. Amendment 39-4787 became effective February 21, 1984. This amendment, 39-5534, becomes effective April 25, 1987.
98-09-27: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce, plc RB211 Trent 768 and 772 series turbofan engines. This action requires initial and repetitive visual inspections of thrust reverser hinge lugs and attachment ribs for cracks, and, if necessary, removal from service and replacement with serviceable parts. This amendment is prompted by aircraft certification testing which revealed that stresses on the thrust reverser hinge were higher than had been anticipated during engine certification. The actions specified in this AD are intended to prevent thrust reverser hinge failure, possibly resulting in liberation of the thrust reverser cowl duct from the engine nacelle, which could result in impact damage to other sections of the aircraft. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of May 21, 1998. Comments for inclusion in the Rules Docket must be received on or before July 6, 1998.