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84-20-02: 84-20-02 CESSNA: Amendment 39-4922. Applies to Models 402C (S/Ns 402C0001 thru 402C0802); 404 (S/Ns 404-0001 thru 404-0859); 414A (S/Ns 414A0001 thru 414A1003); 421C (S/Ns 421C0001 thru 421C1402); 425 (S/Ns 425-0002 thru 425-0190); 441 (S/Ns 441-0001 thru 441-0333) airplanes certificated in any category. Compliance: Required within the next 200 hours time-in-service after the effective date of this AD, unless already accomplished. To preclude collapse of the nose landing gear: (a) Replace the nose landing gear actuator rod ends on Models 425 and 441 airplanes in accordance with Cessna Service Information Letter (CSIL) PJ84-10 dated March 2, 1984, and on Models 402C, 404, 414A and 421C airplanes in accordance with CSIL ME84-10 dated March 9, 1984. (b) The aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Office, Federal Aviation Administration, Room 100, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4400. This amendment becomes effective on November 1, 1984.
82-06-12: 82-06-12 AIR TRACTOR: Amendment 39-4350. Applies to Models AT-300 (S/Ns 300-0001 through 300-9999); AT-301 (S/Ns 301-0001 through 301-9999); AT-302 (S/Ns 302-0001 through 302-9999); AT-400 (S/Ns 400-0244 through 400-9999); and AT-400A (S/Ns 400A-0397 through 400A-9999) airplanes certified in any category and equipped with 1-inch-thick (P/N 40007-2 or P/N 40058-1) main landing gear struts. COMPLIANCE: Required as indicated, unless already accomplished. To prevent possible failure of the P/N 40007-2 or P/N 40058-1 main landing gear struts accomplish the following: (a) Models AT-300 and AT-301 airplanes: (1) On struts having exceeded, or upon accumulating, 1,000 hours time-in- service or 5,000 landings, whichever occurs first, within 20 hours time-in-service or 100 landings, whichever occurs first, after the effective date of this AD and thereafter at intervals of 100 hours time-in-service or 500 landings, whichever occurs first, inspect and replace as necessary the landing gear struts in accordance with paragraph (c). (2) On struts having exceeded, or upon accumulating, 2,000 hours time-in- service or 7,500 landings, whichever occurs first, prior to further flight, replace the struts with new struts of the same part number. (b) Models AT-302, AT-400 and AT-400A airplanes: (1) On struts having exceeded, or upon accumulating, 600 hours time-in- service or 3,000 landings, whichever occurs first, within 20 hours time-in-service or 100 landings, whichever occurs first, after the effective date of this AD and thereafter at intervals of 100 hours time-in-service or 500 landings, whichever occurs first, inspect the struts and replace as necessary in accordance with paragraph (c). (2) On struts having exceeded, or upon accumulating, 1,200 hours time-in- service, or 6,000 landings, whichever occurs first, prior to further flight, replace the struts with new struts of the same part number. (c) Remove the left and right outboard fuselage clamp blocks. Remove all minor corrosion on both main landing gears by sandblasting. Inspect both main landing gears using dye penetrant or magnetic particle inspection procedures with special attention in the areas of strut contact with the clamp blocks. Replace all parts which are damaged, cracked, or have severe corrosion pitting with new parts of the same part number before further flight. All struts returned to service must be painted. (d) The aircraft hours and landings may be used as the time-in-service or landings on the struts if time-in-service or landings on the struts cannot be established by the airplane maintenance records. (e) A special flight permit may be issued in accordance with FAR 21.197 to allow flight of the aircraft to a location where this AD can be accomplished. (f) An equivalent method of compliance with this AD may be used when approved by the Chief, Aircraft Certification Division, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76101. Snow Engineering Company Service Letter No. 45, dated November 1, 1981, covers the subject matter of this AD. Compliance with this Service Letter within the last 100 hours time-in-service or 500 landings, whichever comes first, satisfies the initial inspection requirement of paragraphs (a) and (b) of this AD. This amendment becomes effective on March 25, 1982.
92-08-51: 92-08-51 TEXTRON LYCOMING: Amendment 39-8344. Docket 92-ANE-13. Applicability: Textron Lycoming Model ALF502R series turbofan engines installed on British Aerospace BAe-146 airplanes. Compliance: Required as indicated, unless accomplished previously. To prevent uncommanded in-flight engine power reduction of engines during inclement weather or icing conditions, accomplish the following: (a) Replace the existing engine fuel control, Part Number (P/N) 2-163-810-07, 2-163-810-12, or 2-163- 810-15 with an improved fuel control, P/N 2-163-810-20, 2-163-810-21, or 2-163-810-23, or rework the existing engine fuel control, in accordance with Textron Lycoming Alert Service Bulletin (ASB) No. A-ALF 502R 73-12, Revision 1, dated April 7, 1992, at the first maintenance access of the engine fuel control or within 300 operating cycles after the effective date of this AD, whichever occurs first. (b) 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, Engine Certification Office, FAA, Engine and Propeller Directorate. The request should be forwarded through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (c) 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. (d) The replacement or rework of the engine fuel control shall be done in accordance with the following Textron Lycoming Alert Service Bulletin (ASB): Document No. Pages Version Date Textron Lycoming 1,2,4,5 Rev. 1 April 7, 1992 ASB A-ALF-502R 73-12 3,6,7,8 Original April 1, 1992 Total pages: 8This 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 Textron Lycoming, Stratford Division, 550 Main Street, Stratford, Connecticut 06497. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC 20001. (e) This amendment becomes effective on March 18, 1993, to all persons except those persons to whom it was made immediately effective by telegraphic AD T92-08-51, issued April 8, 1992, which contained the requirements of this amendment.
2023-04-05: The FAA is superseding Airworthiness Directive (AD) 2022-09- 11, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2022-09-11 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2022-09- 11 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness 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.
2023-04-02: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Aerospace LP Model Gulfstream G280 airplanes. This AD was prompted by a determination that the existing wet runway performance tables in the airplane flight manual (AFM) may not provide an acceptable level of safety. This AD requires revising the existing AFM to incorporate new wet runway performance tables, as specified in a Civil Aviation Authority of Israel (CAAI) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2002-02-13: This amendment adopts a new airworthiness directive (AD), that is applicable to CFM International, S.A. (CFMI) CFM56-5 series turbofan engines. This amendment requires replacement of the magnetic drain plug on certain part number (P/N) air turbine engine starters manufactured by Honeywell Engines & Systems. This amendment is prompted by three instances of uncontained air turbine engine starter failures, resulting in cowl damage. The actions specified by this AD are intended to prevent uncontained failure of the starter and possible damage to the airplane.
93-14-05: 93-14-05 BRITISH AEROSPACE: Amendment 39-8629. Docket 92-NM-138-AD. Supersedes AD 77-17-10 R2, Amendment 39-4713. Applicability: All Model BAC 1-11-200 and -400 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent unannunciated failure of the wing flap secondary drive shafts, accomplish the following: (a) Within 300 hours time-in-service after the effective date of this AD, unless previously accomplished within the last 900 hours time-in-service prior to the effective date of this AD: Open the left and right spoilers and perform an inspection, visually (detailed visual inspection) and by feel, of the visible wing flap secondary drive shafts to detect failure or damage, in accordance with paragraph 2.4 of British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 4, dated May 6, 1991. Prior to further flight, repair or replace any defective shafts in accordance with paragraphs (c)(2) and (e) of this AD. (b) Within 1,200 hours time-in-service after the effective date of this AD: Perform a general visual inspection of all wing flap secondary drive shafts to detect failure or damage, in accordance with paragraph 2.1 of British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 3, dated September 28, 1981, or paragraph 2.1.2 of Issue 4, dated May 6, 1991. (1) Repeat the general visual inspections thereafter at intervals not to exceed 1,200 hours time-in-service. (2) If any shaft is found that is distorted or chafed, prior to further flight, perform an inspection of that shaft, visually (detailed visual inspection) and by feel, in accordance with paragraph 2.4 of British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 3, dated September 28, 1981, or Issue 4, dated May 6, 1991. Shafts that fail to meet the inspection specifications listed in paragraph 2.4 of the service bulletin must be replaced,prior to further flight, in accordance with paragraph 2.4.1 of the service bulletin. (c) For spanwise wing flap secondary drive shafts between wing station 0 and wing rib 14: Prior to the accumulation of 3,600 total hours time-in-service or within the next 1,200 hours time-in-service after the effective date of this AD, whichever occurs later, perform an inspection, visually (detailed visual inspection) and by feel, to detect failure or damage, in accordance with paragraph 2.4 of British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 3, dated September 28, 1981, or Issue 4, dated May 6, 1991. (1) Repeat the inspection thereafter at the times specified in paragraphs (c)(1)(i) and (c)(1)(ii) of this AD: (i) For spanwise wing flap secondary drive shafts that have accumulated less than 24,000 total hours time-in-service: At intervals not to exceed 3,600 hours time-in-service or 24 months, whichever occurs earlier. (ii) For spanwise wing flap secondary drive shafts that have accumulated 24,000 or more hours time-in-service: At intervals not to exceed 2,400 hours time-in-service or 24 months, whichever occurs earlier. (2) Shafts that fail to meet the specifications listed in paragraph 2.4 of British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 3, dated September 28, 1981, or Issue 4, dated May 6, 1991, must be replaced, prior to further flight, in accordance with paragraph 2.4.1 of the service bulletin. (d) For wing flap secondary drive shafts located between wing station 0 and wing rib 14, listed in Appendix 1 of British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 4, dated May 6, 1991, on which Modification PM5341/HCA929 is applicable, but has not been accomplished: Prior to the accumulation of 30,000 total hours time-in-service, or within 1,000 hours time-in-service after the effective date of this AD, whichever occurs later; overhaul and modify the wingflap secondary drive shafts by installing British Aerospace Modification PM5341, in accordance with paragraph 2.3 of British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 3, dated September 28, 1981, or Issue 4, dated May 6, 1991. At overhaul, the shaft tubing must be replaced with Modification PM5341 improved tubing, but serviceable end fittings may be reused. (e) Whenever replacing or repairing a flap secondary drive shaft in accordance with paragraph (a), (b) or (c) of this AD, or whenever overhauling a wing flap secondary drive shaft in accordance with paragraph (d) of this AD, inspect the adjacent shaft support bearings for excessive radial play, in accordance with Section 27-52-00 of the BAC 1-11 Maintenance Manual. Prior to further flight, replace any shaft support bearings having radial play in excess of 0.020 inch total indicated reading with a serviceable bearing. (f) Operators who have not kept records of hours time-in-service on individualwing flap secondary drive shafts shall substitute airplane hours time-in-service in lieu thereof. (g) 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. (h) 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. (i) The inspections, replacement, overhaul, and modification shall be done in accordance with British Aerospace BACOne-Eleven Alert Service Bulletin 27-A-PM5341, Issue 3, dated September 28, 1981; and British Aerospace BAC One-Eleven Alert Service Bulletin 27-A-PM5341, Issue 4, dated May 6, 1991; as applicable. 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. 20041-0414. 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. (j) This amendment becomes effective on August 23, 1993.
56-06-01: 56-06-01 CONTINENTAL: Applies to O-470 Series and E Series Engine Serial Numbers Below Excepting Any Remanufactured Engine Shipped From Continental Motors Corp. After May 1, 1955, and Engine Serial Numbers Designated "Exceptions." Compliance required as soon as possible but not later than July 1, 1956. To prevent serious engine damage in flight, the following must be accomplished: 1. Replace present piston pin assembly with piston pin assembly P/N 539467 in the following serially numbered engines: Engine Model O-470-A, Serial Nos. 41258 to 41679, 40015-2-A, 40021-2-A, 40028-2-A, 40045-2-A, 40054-2- A, 40074-3-A, 40110-3-A, 40125-3-A, 40154-3-A, 40168-3-A, 40176-3-A, 40177-3-A, 40203-3-A, 40204-3-A, 40242-3-A, 40264-3-A, 40267-3-A, 40293-3-A, 40334-3-A, 40371-3-A, 40418-3-A, 40424-3-A, 40438-3-A, 40444-3- A, 40485-3-A, 40494-3-A, 40567-3-A, 40579-3-A, 40581-3-A, 40601-3-A, 40619-3-A, 40647-3-A, 40651-3-A, 41008-3-A, 41025-3-A, 41032-3-A, 41033-3-A, 41038-3-A, 41039-3-A, 41068-3-A, 41094-3-A, 41109-4-A, 41175-4- A, 41181-4-A, 41187-4-A, 41189-4-A, 41196-4-A, 41251-4-A, 41254-4-A. Engine Model O-470-B, Serial Nos. 50001 to 50256. Exceptions - 50189, 50241, 50245, 50246, 50247, 50250, 50251, 50252. Engine Model O-470-J, Serial Nos. 45001 to 45533. Exceptions - 45520, 45521, 45525, 45529. Engine Models E-225-4, E-225-8, Serial Nos. 30163 to 30715. Engine Models E-185-8, E-185-11, Serial Nos. 22200 to 22269. Engine Model E-185-9, Serial Nos. 6128 to 6135. In addition, replace piston pin assembly, P/N 535145, with piston pin assembly, P/N 539467, in any O-470 or E Series engine that was overhauled in the field and in which it is known that P/N 535145 was installed at time of overhaul. (Continental Motors Corp. Service Bulletin No. M56-2, Supplement No. 1, dated March 12, 1956, further discusses this subject.) 2. Replace present oil pump gear assembly with oil pump gear assembly P/N 539525 in the following serially numbered engines: Engine Model O-470-B, Serial Nos. 50076 to 50256. Exceptions - 50189, 50241, 50245, 50246, 50247, 50250, 50251, 50252. Engine Model O-470-J, Serial Nos. 45001 to 45533. Exceptions - 45447, 45448, 45456, 45457, 45462, 45463, 45466, 45468, 45473, 45474, 45481, 45484, 45489, 45491, 45494, 45495, 45500, 45503, through 45514, 45516, 45519, 45520, 45522, 45523, 45525, 45526, 45528, 45529, 45532. 3. Replace present exhaust valve with exhaust valve P/N 539449 in the following serially numbered engines: Engine Model O-470-A, Serial Nos. 40001 to 40673. Engine Model O-470-A, Serial Nos. 41001 to 41679. Engine Model O-470-J, Serial Nos. 45001 to 45489. Exception - 45487. (Continental Motors Corp. Service Bulletin M56-2, dated February 14, 1956, further discusses this subject and offers special discounts for replacement parts ordered prior to July 1, 1956, from bona fide Continental aircraft engine spare parts distributors.)
2017-21-06: We are adopting a new airworthiness directive (AD) for certain 328 Support Services GmbH Model 328-100 and Model 328-300 airplanes. This AD was prompted by reports of broken bonding wires of certain fuel line clamps. This AD requires repetitive inspections of certain fuel line clamps for discrepancies; repetitive inspections of certain parts for chafing marks; and replacement of any discrepant parts. This AD also includes an optional modification, which is a terminating action for the inspections. We are issuing this AD to address the unsafe condition on these products.
2017-22-09: We are adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aeronautics Model SAAB 340B airplanes. This AD was prompted by reports of natural stall events in icing conditions, without prior stall warnings. This AD requires modifying the stall warning system, installing new stall warning computers, and activating the stall warning system. We are issuing this AD to address the unsafe condition on these products.