Results
73-22-01: 73-22-01 CESSNA: Amendment 39-1735 as amended by Amendment 39-3215. Applies to Model 340 (S/Ns 340-0001 thru 340-0234); Model 401 (S/Ns 401-0001 thru 401-0322); Model 401A (S/Ns 401A0001 thru 401A0132); Model 401B (S/Ns 401B0001 thru 401B0300); Model 402 (S/Ns 402-0001 thru 402-0322); Model 402A (S/Ns 402A0001 thru 402A0129); Model 402B (S/Ns 402B0001 thru 402B0392); Model 411 (S/Ns 411-0001 thru 411-0250); Model 411A (S/Ns 411-0251 thru 411A0300); Model 414 (S/Ns 414-0001 thru 414-0407); Model 421 (S/Ns 421-0001 thru 421-0200); Model 421A (S/Ns 421A0001 thru 421A0158); and Model 421B (S/Ns 421B0001 thru 421B0147 and S/Ns 421B0201 thru 421B0422) airplanes. Model 421 (S/N 421-0151) airplane is excepted from the requirement for the installation of Cessna Service Kit SK421-56 so long as it complies with STC SA599CE. Compliance: Required as indicated, unless already accomplished. To prevent the collection of fuel in the wing leading edge area and to provide additional instructions on preflight inspections and ground or inflight fire procedures, within the next 100 hours' time in service after the effective date of this AD, accomplish the following: Modify the wing leading edge by installing Cessna Service Kit SK 421-56 and install applicable checklist and Flight Manual revisions as specified in Cessna Service Letter ME73-5 (Supplement 1) dated September 7, 1973, or later FAA-approved revisions, or any other modification approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Amendment 39-1735 became effective October 18, 1973. This amendment 39-3215 becomes effective on May 29, 1978.
2004-15-06: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires various inspections of the fuselage nose structure between stations 4 and 11, and corrective actions if necessary. This action is necessary to detect and correct fatigue cracking in the primary structure of the nose of the airplane at the forward avionics bay (fuselage stations 4 to 11), which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
46-42-01: 46-42-01 GLOBE: (Was Mandatory Note 4 of AD-766-5.) Applies to Models GC-1A, GC-1B Aircraft Serial Numbers 3 to 228 Inclusive. Compliance required prior to December 1, 1946. Replace the aluminum alloy cabin heater valve assembly with one constructed completely of firewall material equivalent to Globe Valve Assembly, P/N 11-440-3623. This will provide a complete firewall of firewall material. (Globe Customer Service Maintenance Bulletin No. 4 covers this same subject.)
2022-05-13: The FAA is adopting a new airworthiness directive (AD) for certain Honda Aircraft Company LLC (Honda) Model HA-420 airplanes. This AD was prompted by a report of in-flight smoke and fire that initiated from the windshield heat power wire braid. This AD requires incorporating temporary revisions into the airplane flight manual (AFM) and the quick reference handbook (QRH) that modify procedures for windshield heat operation until the affected windshield assemblies are replaced. The FAA is issuing this AD to address the unsafe condition on these products.
47-20-09: 47-20-09 ERCO: (Was Service Note 1 of AD-718-6.) Applies to 415-C, -CD and -D Aircraft. Compliance required at each 100-hour inspection and immediately after each electrical system malfunction. Check the operation of the voltage regulator by observing the ammeter reading after starting and until the battery becomes charged. A normal operation would indicate a charging rate up to 11-13 amperes for periods of time up to 20 minutes after starting. The charging rate should reduce to 2 amperes or less within 2 hours or operation. (Ercoupe Service Department Memorandum No. 23 covers this same subject.)
2022-06-10: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of three incidents involving in-flight fan blade failures on certain Pratt & Whitney engines (''fan blades'' are also known as ''1st-stage low-pressure compressor (LPC) blades''-- these terms are used interchangeably in this AD). This AD requires installation of debris shields on the thrust reverser (T/R) inner wall at the left and right sides of the lower bifurcation, inspection of the fan cowl doors for moisture ingression, repetitive functional checks of the hydraulic pump shutoff valves to ensure they close in response to the fire handle input, and corrective actions if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2004-14-25: This amendment adopts a new airworthiness directive (AD), applicable to certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 series airplanes, that requires installing a lightning bonding jumper from the lower rotating beacon to the airframe. This action is necessary to prevent possible multiple avionics failures caused by a lightning strike, which could reduce the ability of the flightcrew to control the airplane. This action is intended to address the identified unsafe condition.
93-14-16: 93-14-16 BRITISH AEROSPACE (COMMERCIAL AIRCRAFT), LIMITED: Amendment 39-8640. Docket 93-NM-03-AD. Applicability: Model ATP airplanes having aft isolator bracket attachment bolts, part number A102-4E or A102-5E; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent structural failure of the engine support structure, accomplish the following: (a) For airplanes on which the aft isolator bracket attachment bolts have accumulated less than 5,000 total landings as of the effective date of this AD: Prior to the accumulation of 5,000 total landings on the bolts, or within 1,250 hours time-in-service after the effective date of this AD, whichever occurs later, remove the bolts and replace them with new or serviceable parts, in accordance with Jetstream Aircraft, Limited, Service Bulletin ATP-54-9, dated December 9, 1992, or Revision 1, dated May 10, 1993. Thereafter, prior to the accumulation of 5,000 total landings onany bolt, replace it with a new or serviceable bolt, in accordance with the service bulletin. (b) For airplanes on which the aft isolator bracket attachment bolts will have accumulated 5,000 or more total landings before it is replaced in accordance with paragraph (a) of this AD: Prior to the accumulation of 5,000 total landings or within 150 hours time-in-service after the effective date of this AD, whichever occurs later, perform a visual inspection of the aft isolator bracket attachment bolts to determine if each bolt is in position, and to detect failed or cracked bolts, in accordance with Jetstream Aircraft, Limited, Service Bulletin ATP-54-9, dated December 9, 1992, or Revision 1, dated May 10, 1993. (1) If any bolt is missing, failed, or cracked, prior to further flight, replace all four bolts in the assembly with new or serviceable parts, in accordance with the service bulletin. Thereafter, prior to the accumulation of 5,000 total landings on any bolt, replace it with a new or serviceable bolt, in accordance with the service bulletin. (2) If no bolt is missing, failed, or cracked, repeat the visual inspection thereafter at intervals not to exceed 150 hours time-in-service. Within 1,250 hours time-in-service after the effective date of this AD, replace each bolt with a new or serviceable part, in accordance with the service bulletin. Thereafter, prior to the accumulation of 5,000 total landings on any bolt, replace it with a new or serviceable bolt, in accordance with the service bulletin. (c) Replacement of the existing bolts on the aft isolator brackets on the engine mounting beams with improved bolts (Modification 35256A) in accordance with Jetstream Aircraft, Limited, Service Bulletin ATP-54-10-35256A, Revision 1, dated April 16, 1993, constitutes terminating action for replacement of the bolts every 5,000 landings, as required by paragraphs (a), (b)(1), and (b)(2) of this AD. (d) 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. (e) 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. (f) The replacement and inspection shall be done in accordance with Jetstream Aircraft, Limited, Service Bulletin ATP-54-9, dated December 9, 1992; or Jetstream Aircraft, Limited, Service Bulletin ATP-54-9, Revision 1, dated May 10, 1993. The modification shall be done in accordance with Jetstream Aircraft, Limited, Service Bulletin ATP-54-10-35256A, Revision 1, dated April 16, 1993, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1 1 April 16, 1993 2-5 0 March 2, 1993 6 (This page is not used) 7 1 (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 Jetstream Aircraft, Inc., P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. 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. (g) This amendment becomes effective on October 4, 1993.
2022-06-11: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of three incidents involving in-flight fan blade failures on certain Pratt & Whitney engines (''fan blades'' are also known as ''1st-stage low- pressure compressor (LPC) blades''--these terms are used interchangeably in this AD). This AD requires modifying the engine inlet to withstand fan blade failure event loads. The FAA is issuing this AD to address the unsafe condition on these products.
2004-14-22: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (PWC) PW206B engines that have incorporated PWC Service Bulletin (SB) No. 28119, and PW206C, PW206E, PW207D, and PW207E turboshaft engines. This AD requires checking the automatic low-cycle- fatigue (LCF) counting data made by the engine Data Collection Unit (DCU) on installed engines, and validating proper DCU automatic LCF counting before an engine is installed. This AD results from two reports of irregular LCF counting, observed between engines on the same helicopter, during weekly recording of LCF data in the engine log books. We are issuing this AD to prevent critical rotating parts from exceeding published life limits, which could result in uncontained engine failure and possible loss of the helicopter.