Results
98-02-01: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires removing the yaw damper coupler; replacing its internal rate gyroscope with a new or overhauled unit; and performing a test to verify the integrity of the yaw damper coupler, and repair, if necessary. This amendment is prompted by an FAA determination that requiring replacement of the internal rate gyroscope will significantly increase the reliability of the yaw damper coupler system. The actions specified by this AD are intended to prevent sudden uncommanded yawing of the airplane due to potential failures within the yaw damper system, and consequent injury to passengers and crewmembers.
93-14-03: 93-14-03 SHORT BROTHERS, PLC: Amendment 39-8627. Docket 92-NM-213-AD. Applicability: Model SD3-30 series airplanes; equipped with Menasco main landing gear (MLG) beam assembly, part number (P/N) 17501, serial numbers MMC-039 through MMC-068, inclusive, MMC-005 through MMC-038, inclusive, and MMC-071 through MMC-188, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent main landing gear failure, which could damage the airplane or reduce controllability of the airplane during takeoff or landing, accomplish the following: (a) For airplanes equipped with MLG beam sub-assembly P/N 17604-9, -13, -15/16, or -17/18: Prior to the accumulation of 13,500 total landings or within 2,300 landings after the effective date of this AD, whichever occurs later, rework the MLG beam sub-assembly, in accordance with Shorts SD3- 30 Service Bulletin SD3-32-90, Revision 2, dated June 29, 1992. NOTE: Shorts SD3-30Service Bulletin SD3-32-90, Revision 2, dated June 29, 1992, references Menasco Service Bulletin 32-65, Revision 2, dated October 13, 1982, for additional service information. (b) For airplanes equipped with MLG beam sub-assembly P/N 17604-9, -13, or -13A/14A: Prior to the accumulation of 20,000 total landings on the MLG beam sub-assembly or within 2,300 landings after the effective date of this AD, whichever occurs later, and thereafter prior to the accumulation of 20,000 landings, replace the MLG beam sub-assembly with a serviceable unit, in accordance with Shorts SD3-30 Service Bulletin SD3-32-90, Revision 2, dated June 29, 1992. (c) 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. (d) 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. (e) The rework and replacement shall be done in accordance with Shorts SD3-30 Service Bulletin SD3-32-90, Revision 2, dated June 29, 1992. 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 Short Brothers, PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3719. 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. (f) This amendment becomes effective on August 23, 1993.
98-01-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires replacement of the spring tab balance units in the ailerons and the inboard aileron hinge bolts and bearings with improved parts. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent failure of the aileron gustlock mechanism and the inboard aileron hinge bolt, which could result in inability to operate the ailerons, and consequent reduced controllability of the airplane.
77-20-05 R1: 77-20-05 R1 ROLLS-ROYCE LIMITED: Amendment 39-3049 as amended by Amendment 39-4640. Applies to Rolls-Royce DART engines series Mk. 506, 510, 511, 514, 526, 528, 529, 530, 532, and variants, installed on, but not necessarily limited to, BAC Viscount 744 and 745D; Fokker F-27 Mk. 100, 200, 300, 400, 600, 700; Fairchild F-27, -27A, -27B, -27F, -27G, -27J, -27M; Fairchild-Hiller FH-227, -227B, -227C, -227D, - 227E; Armstrong Whitworth Argosy 650, Series 101; Grumman G-159; and Hawker Siddeley HS-748 Series 2A aircraft. Compliance is required as indicated, unless already accomplished. 1. Compliance for all affected DART engines except the Mk. 530 is based on an effective date of November 3, 1977. 2. Compliance for the DART Mk. 530 engines is based on an effective date of May 12, 1983. To prevent the failure of the fuel burner feed and manifold pipes that could result in fuel leakage and a fire, accomplish the following: (a) Inspect the fuel burner feed and manifold pipes and determine if any of the pipes meet both of the following specifications: (1) The pipe is an "Aeroquip" pipe incorporating Dart Modification 1587 and having one of the following part numbers: RK.38457A Pipe Assembly - Fuel Feed to No. 4 Burner RK.38455A Pipe Assembly - Fuel Feed to Nos. 1, 2, and 7 Burners RK.38456A Pipe Assembly - Fuel Feed to Nos. 3 and 6 Burners RK.38458A Pipe Assembly - Fuel Feed to No. 5 Burner RK.45363A Fuel Manifold - Assembly No. 5 to F.C.U. Bulkhead Connection (2) The pipe was manufactured prior to March 1, 1974, and the metal identity tag located around the fireproof sleeve of the pipe (which contains the date of manufacture) has not been marked with - (i) the marking "DRS.685"; (ii) an engine number or a running time; (iii) a second date marking in brackets which is later than March 1, 1974; or (iv) the marking "ZERO." (b) If, during the inspection required by paragraph (a) of this AD, a pipe is found that meets the specifications contained in paragraph (a) of this AD, before returning the engine to service, inspect the pipe for the presence of corroded, cracked, or broken wires using 5X or 10X magnification in accordance with the instructions contained in paragraphs 4A and 4B of Rolls Royce Dart Service Bulletin Da 73-73, dated August 29, 1975 (hereinafter SB DA 73-73), or an FAA-approved equivalent, and comply with paragraph (c) or (d) of this AD, as applicable. (c) If, during the inspection required by paragraph (b) of this AD, the pipe wires are found to be corroded, cracked, or broken, before returning the engine to service, replace the pipe with a serviceable pipe or rework in accordance with paragraph 4B(7) of SB Da 73-73, or an FAA-approved equivalent. (d) If, during the inspection required by paragraph (b) of this AD, the pipe is found to be serviceable, before returning the engine to service, clean and identify the pipe in accordance withparagraphs 4B(4) and 4B(6) of SB Da 73-73, or an FAA-approved equivalent. (e) The FAA-approved equivalent means of compliance specified in paragraphs (b), (c), and (d) of this AD must be approved by the Manager, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. Amendment 39-3049 became effective November 3, 1977. This Amendment 39-4640 becomes effective May 12, 1983.
77-16-01: 77-16-01 MCCAULEY PROPELLERS: Amendment 39-2994. Applies to the following two bladed constant speed McCauley propellers, which were modified by Hoosier Aircraft Accessory Inc., Indianapolis, Indiana, or Univair Aircraft Corporation, Aurora, Colorado during the period of December 8, 1972 thru June 30, 1975. These propellers are installed on, but not limited to the aircraft models listed below. Propeller Model Note (1) Hub Serial No. Note (2) Aircraft Model Note (3) D2A34C49 (*) 692417 (H) Cessna 185 thru 185E (thru S/N 185- 1149) 703405 (H) Cessna 210 thru 210C (thru S/N 21058220) 705820 (H) Cessna 210-5 & 210-5A (thru S/N 205- 0576) (The above models use Continental IO- 470 engines) Navion A thru G Series D2A34C50 (*) 64746 (H) Cessna 180 thru 180H (thru S/N 18052284) -or- 690329 (H) Cessna 182 thru 182G (thru S/N 18255844) 2A34C50 (*) 731417 (U) Cessna 188 thru 188B (thru S/N 18802348) Wren 460 SeriesD2A34C58 (*) 543736 (U) Bellanca 17-30 -or- 702828 (U) Cessna 185 thru 185E (thru S/N 185- 1149) F2A34C58 (*) 710292 (U) -or- 712516 (U) Cessna A185 thru A185F 2A34C58 (*) 720683 (U) Cessna A188 thru A188B 721610 (H) Cessna 206 (thru S/N 206- 0275) 730297 (U) 738166 (U) Cessna U206 thru U206F (thru S/N U20603560) 734269 (H) 736436 (H) Cessna TU206A thru TU206F (Floatplane only thru S/N U20602199) Cessna P206 thru P206B (thru S/N P206- 0419) Cessna TP206A (Floatplane only) Cessna 207 (thru S/N 20700364) Cessna 210 thru 210D (thru S/N 21058510) Cessna 210-5 & 2105A (thru S/N 205- 0576) Interceptor (Aero Commander) 200B, C & D Series Navion A thru H Series 2A34C66 (*) 705202 (H) Cessna 180 thru 180J (thru S/N 18052770) 714959 (U) 720392 (U) Cessna 182 thru 182P (thru S/N 18265175) 727625 (H) 727628 (H) Cessna 188 thru 188B (thru S/N 18802348)731236 (U) 732194 (H) 735330 (U) 746598 (U) E2A34C73 (*) 652300 (U) Cessna P206 thru P206E (thru P20600647) -or- 652336 (U) 2A34C73 (*) 652403 (H) Cessna 210E thru 210L (thru S/N 21061573) 652692 (U) 720673 (H) 721615 (H) 732503 (H) 2D34C9 (*) 704835 (U) Beech A23-24, A24 and A24R 2A36C1 (*) 55588 (H) Cessna 180A thru H -or- 59229 (H) Cessna 182, 182A thru G 2A36C18 (*) Taylorcraft 20 -or- 2A36C29 (*) 2A36C23 (*) 671564 (H) Beech H35, J35, K35, M35 Beech N35, P35, S35, V35, V35A and V35B (S/N's D-6562 thru D-9935) Beech 35-C33A, E33A and F33A (S/N's CE-1 thru CE-668) Beech E33C and F33C (S/N's CJ-1 thru CJ-128) Beech 36 and A36 (S/N's E-1 thru E- 910) Beech A45 (STC SA1450SW) D2A36C33 (*) 60314 (U) Cessna 185 thru 185D (thru S/N 185- 0967) 61005 (H) 611491 (H) Cessna 210 thru 210C (thru S/N 21058220) 611720 (H) Cessna 210-5 & 210-5A (thru S/N 205- 0576) Aeronautica Macchi AL-60() Series Air Parts LTD. (Fletcher) FU-24() Series Interceptor (Aero Commander/ Meyers) 200 Series Lockheed 402-2 "LASA 60" 2D36C14 (*) 591205 (U) Beagle A-109 Boisavia B-601L Cessna 170 Series (STC SA421CE) Cessna 172 Series (STC SA420CE) Cessna 175, 175A (STC SA424CE) Piper PA-24 SAAB 91D Wassmer WA-40 NOTES: (*) - Denotes suffix letter(s). Some models have one or more suffix letter designations, others have none. (1)&(2) - Propeller model and hub serial numbers are stamped on the side of the propeller hub. The listing of hub serial numbers refers to specific hub serial numbers not series. In the event a spinner is installed, the spinner should be removed to check the model and hub (S/N) designations. The aircraft's records should likewise be checked to ensure that the model and hub serial number coincide with the records. In the event an error is noted, the records should be corrected accordingly. Prior to further flight, spinners should be reinstalled where applicable. (3) - Includes listing of applicable aircraft serial numbers. If no listing is indicated, applies to all applicable serial numbers of a particular aircraft model or series. H) or (U - Indicates that the propeller rework was accomplished by (H) Hoosier Aircraft Accessory, Inc., or (U) Univair Aircraft Corporation. These letters are not part of the manufacturer's hub serial numbers. Compliance required as indicated, unless already accomplished. To preclude the possibility of blade actuating pin failures resulting from using an incorrect actuating pin, or improper rework of the ferrules and installation of the blade actuating pins and washers (i.e., a blind actuating pin hole not tapped to the proper depth can cause stripped threads on the ends of the actuating pin resulting in severe stress and may preventactuating pin from seating on the washers) accomplish the following: (a) All propellers listed above which were modified by (H) - Hoosier Aircraft Accessory, Inc. (1) Within 25 hours time in service after the effective date of this AD, disassemble the propeller and inspect the blade actuating pins, washers and ferrules for proper conformity and installation in accordance with McCauley Service Manual No. 720415, Chapter I, or later Federal Aviation Administration approved revision(s) (2) Prior to further flight, repair or replace as necessary, any improperly installed blade actuating pins, washers, and ferrules, and reassemble the propeller in accordance with McCauley Service Manual No. 720415, or later Federal Aviation Administration approved revision(s). (b) All propellers listed above, which were modified by (U) - Univair Aircraft Corporation. (1) Within 1200 hours time in service since last rework by Univair, or within two years, whichever comes first after the effective date of this AD, disassemble the propeller and inspect the blade actuating pins, washers and ferrules for proper conformity and installation in accordance with McCauley Service Manual No. 720415, Chapter I, or later Federal Aviation Administration approved revision(s). (2) Prior to further flight, replace any improper blade actuating pins, washers and repair or replace the ferrules as necessary, and reassemble the propeller in accordance with McCauley Service Manual No. 720415, or later Federal Aviation Administration approved revision(s). (c) When the above propellers are released for service, compliance with this Airworthiness Directive shall be noted in the Aircraft's Records. (d) The responsible propeller repair station will notify the Federal Aviation Administration, Chief, Engineering and Manufacturing Branch, AGL-210, 2300 East Devon Avenue, Des Plaines, Illinois 60018, by certified mail about the results of these inspections. The disposition of the affected propeller(s) including the blade and hub serial numbers of the propellers (as received, and where applicable, as returned to service) must be reported. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) The Manufacturer's specifications and procedures identified in this Directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by the directive who have not already received these documents from the manufacturer, may obtain copies upon request to McCauley Accessory Division, Cessna Aircraft Corporation, Box 7, Roosevelt Station, Dayton, Ohio 45417. These documents may also be examined at the Great Lakes Regional Office, 2300 East Devon Avenue, Des Plaines, Illinois 60018, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this airworthiness directive which includes incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and the Great Lakes Region. Amendment 39-2994 replaces AD 76-19-04. This amendment becomes effective August 9, 1977.
98-01-05: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace HS 748 series airplanes. This action requires installation of an aileron cable support block under the crew compartment floor. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent jamming or restriction of the aileron cable, which could lead to reduced controllability of the airplane.
2012-08-15: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes. This AD was prompted by multiple reports of short circuit events during pre- delivery inspections and test flights, one of which resulted in smoke in the cockpit. This AD requires replacing or relocating of certain circuit breaker panel (CBP) bus bars on certain airplanes, inspecting for any loose or improperly crimped lugs in certain electrical panel locations and replacement if necessary, and inspection for foreign object damage in certain areas and removal if necessary. We are issuing this AD to prevent arcing, damage to adjacent structure, smoke in the cockpit, or loss of system redundancies.
98-01-02: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires a one-time visual inspection of the rear cargo door and luggage auxiliary structure for corrosion, repetitive borescope inspections of the rear cargo door, and removal and repair of any corrosion found during the inspections. This amendment also requires the drilling of drain holes and application of a corrosion preventive and sealing compound inside the rear cargo door, and modification of the rear cargo door to aid in future routine borescope inspections. This amendment is prompted by reports of corrosion being found in the affected areas on several of the affected airplanes. The actions specified by this AD are intended to prevent such corrosion, which could result in structural failure of the cargo door and loss of the door during flight, and consequent rapid decompression, aerodynamic instability, and/or damage toother fuselage structures.
2022-04-06: The FAA is superseding Airworthiness Directive (AD) 2021-06- 06, which applied to certain Bell Textron Canada Limited Model 505 helicopters. AD 2021-06-06 required repetitive fluorescent penetrant inspections (FPIs) of the pilot collective stick and grip assembly and revising the existing Rotorcraft Flight Manual (RFM) for your helicopter. Since the FAA issued AD 2021-06-06, the pilot collective stick and grip assembly has been redesigned. This AD retains certain requirements of AD 2021-06-06, requires modifying your helicopter to include the improved pilot collective stick tube and adds a terminating action for the repetitive FPIs. This AD also prohibits installing any pilot collective stick and grip assembly unless certain requirements of this AD are met. The FAA is issuing this AD to address the unsafe condition on these products.
2022-04-09: The FAA is adopting a new airworthiness directive (AD) for certain AVOX System Inc. (formerly Scott Aviation) oxygen cylinder and valve assemblies, and oxygen valve assemblies, installed on but not limited to various transport airplanes. This AD was prompted by reports of cylinder and valve assemblies having oxygen leakage from the valve assembly vent hole, caused by the absence of a guide that maintains appropriate spacing between certain parts. This AD requires an inspection of the oxygen valve assemblies, and oxygen cylinder and valve assemblies, to determine the serial number of the valve, cylinder, and entire assembly. For assemblies and parts with certain serial numbers, this AD requires a detailed inspection for correct spacing of the gap between the bottom of the packing retainer and top of the valve body on the assemblies, and replacement of assemblies having unacceptable gaps. The FAA is issuing this AD to address the unsafe condition on these products.