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2012-08-14: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by reports of cracking in the upper wing skin at the fastener holes common to the pitch load fittings of the inboard and outboard front spar, which could result in the loss of the strut-to-wing upper link load path and possible separation of a strut and engine from the airplane during flight. This AD requires repetitive inspections to detect fatigue cracking in the wing skin, and corrective actions if necessary. We are issuing this AD to correct the unsafe condition on these products.
69-15-03: 69-15-03 CESSNA: Amendment 39-798. Applies to all Cessna Model 170, 172, and 175 series airplanes modified in accordance with Supplemental Type Certificates SA3-13, SA3-126, SA3-571, SA3-672, SA3-674, SA135CE, SA420CE, SA421CE, or SA424CE, incorporating a Piper Muffler Assembly, P/N 10308-00, with the installation of a Lycoming engine. Compliance required as indicated. To detect cracks in the muffler assembly, accomplish the following: (a) Inspect muffler assemblies with less than 950 hours' time in service on the effective date of this AD, in accordance with paragraph (c) below within the next 50 hours' time in service and thereafter at intervals not to exceed 100 hours' time in service from the last inspection until accumulating 950 hours' time in service, then comply with paragraph (b) below. (b) Inspect muffler assemblies with more than 950 hours' time in service on the effective date of this AD, in accordance with paragraph (c) below within the next 50 hours' time in service and thereafter at intervals not to exceed 50 hours' time in service from the last inspection. (c) Inspect the engine exhaust muffler and shroud assembly (including the internal baffle tube and tail pipe), carburetor heat shroud and air duct, support braces, clamps and brackets, exhaust stacks and manifolds. Remove muffler assembly, disconnect air ducts, stacks, and shrouds as necessary, and visually inspect exterior and interior surfaces with a probe light and mirror for signs of cracks, corrosion, burn-throughs, heat damage, collapsed stack, or weld separations. Special attention should be given to the exhaust stack under the carburetor heat shroud. Except for the initial inspection, the muffler assembly need not be removed from the airplane if the shroud is opened for inspection of external portions of the muffler and the internal portions are inspected through the muffler tail pipe outlet and one end of the muffler at the stack connection. CAUTION:Do not alter these mufflers to remove the internal baffle tube without prior FAA approval. (Piper Service Letter No. 324B describes the critical areas.) (d) Replace or repair parts having any of the defects listed in paragraph (c) before further flight, and thereafter comply with the inspection requirements of paragraph (a) or (b), whichever is applicable. Make welding repairs and pressure test in accordance with Advisory Circular AC 43.13-1 or an FAA approved equivalent. Care should be exercised when reinstalling the exhaust system components to prevent distortion or preloading of parts. This amendment becomes effective August 20, 1969.
47-51-13: 47-51-13 BELLANCA: Applies to Model 14-13 Serial Numbers 1060 Through 1513, 1545, 1548, 1551 Through 1560. Compliance required not later than May 1, 1948. To eliminate the possibility of an engine compartment fire entering the fuselage through the firewall cabin heater opening, remove the aluminum cabin heat control valve and replace with a steel valve of new design Bellanca Drawing No. 15067-40. (Bellanca Service Bulletin No. 11 dated June 20, 1947, covers this same subject.)
77-07-01: 77-07-01 HUGHES HELICOPTERS: Amendment 39-2859. Applies to Hughes Model 269 series helicopters certificated in all categories, incorporating belt drive clutch linear actuator assemblies (hereinafter referred to as the "clutch actuator") P/N's DL1020-M81C (12V), DL1020-MS82C (24V), DL1020M48, and 269A4564. Compliance required as indicated, unless already accomplished. To detect possible cracks in belt drive clutch aluminum actuating shaft and actuator attachment fixed end fittings which can cause separation of the actuator attachment resulting in declutching of the main rotor, accomplish the following: (a) Within 10 days after the effective date of this AD, prior to the first flight each day, conduct a visual check of the clutch actuator in accordance with the procedures described in Part II of Hughes Service Information Notice N-141.1 dated March 8, 1977, or later FAA approved revision. If any indication of cracks, corrosion or deformation is observed, perform a dyepenetrant inspection of the suspect areas per Part III of above referenced service notice. Before further flight, replace any defective clutch actuator with a serviceable unit. (b) The daily visual check required by paragraph (a) of this AD may be performed by the pilot. (c) Within the next 100 hours time in service after the effective date of this AD, and at intervals not to exceed 100 hours time in service thereafter, perform a dye penetrant inspection of the clutch actuator per Part III of Hughes Service Information Notice N-141.1 dated March 8, 1977, or later FAA-approved revision. Before further flight, replace any defective clutch actuator with a serviceable part. (d) When the clutch actuator is modified to, or replaced with, an actuator incorporating the stainless steel parts as described in Part I of Hughes Service Information Notice N-141.1, dated March 8, 1977, or later FAA approved revision, the visual checks required by paragraph (a) and the dye penetrant inspection required by paragraph (c) may be discontinued. (e) Equivalent checks, inspections and modification procedures for the clutch actuator may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. (f) Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate helicopters to a base for accomplishment of the 100 hour inspections required by paragraph (c) of this AD. (g) Record the daily visual check required by this AD in the rotorcraft maintenance record in accordance with FAR 91.173. This amendment becomes effective April 4, 1977.
98-01-01: 98-01-01 CESSNA AIRCRAFT COMPANY: Priority Letter issued on December 22, 1997. Docket No. 97-CE-150-AD. Applicability: The following airplane models and serial numbers, certificated in any category: Model 172R Airplanes: serial numbers 17280003 through 17280171, 17280173 through 17280175, 17280177 through 17280179, 17280182 through 17280184, 17280186, 17280189, 17280190, 17280192 through 17280212, 17280214, 17280216 through 17280221, 17280223 through 17280236, 17280239 through 17280251, 17280253 through 17280263, 17280265, 17280268, 17280270 through 17280272, 17280283, 17280297, and 17280301; and Model 182S Airplanes: serial numbers 18280001, 1820002, 18280004 through 18280045, 18280048 through 18280060, 1820062 through 18280064, 18280067, and 18280070. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (h) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated in the body of this priority letter AD, unless already accomplished. To prevent erroneous indications from the altimeter, airspeed, and vertical speed indicators, which could cause the pilot to react to incorrect flight information and possibly result in loss of control of the airplane, accomplish the following: (a) Prior to further flight after receipt of this priority letter AD, fabricate placards with the following words, using letters at least 1/8-inch in height, and install these placards in the cockpit within the pilot s clear view: (1) "IFR operation is prohibited." (2) "Use of the alternate static air source is prohibited." (b) Within the next 100 hours time-in-service (TIS) after receipt of this priority letter AD or within the next 4 calendar months after receipt of this priority letter AD, whichever occurs first, inspect the alternate static air source valve to assure that the alternate static air source valve is not restricted by the identification placard and to assure that the valve body does not separate from the valve flange in accordance with Cessna Service Bulletin No. SB97-34-02, Revision 1, dated December 22, 1997. (1) If the alternate static air source valve is restricted, prior to further flight after the inspection required by paragraph (b) of this AD, rework the alternate static air source assembly in accordance with Cessna Service Bulletin No. SB97-34-02, Revision 1,dated December 22, 1997. (2) If the valve body separates from the valve flange, replace the alternate static air source assembly in accordance with the maintenance manual at one of the compliance times presented below (paragraph (b)(2)(i) or (b)(2)(ii) of this AD): (i) Prior to further flight to eliminate the operating limitations required by the placards in paragraphs (a), (a)(1), and (a)(2) of this AD; or (ii) Within the next 25 hours TIS after the inspection provided the operating limitations required by the placards in paragraphs (a), (a)(1), and (a)(2) of this AD are adhered to. (c) The placard requirements of paragraphs (a), (a)(1), and (a)(2) of this AD may be eliminated when the inspection, rework, and replacement requirements are accomplished as specified in paragraphs (b), (b)(1), and (b)(2) of this AD. (d) The inspection, rework, and replacement requirements specified in paragraphs (b), (b)(1), and (b)(2) of this AD may be accomplished at any time prior to "within the next 100 hours TIS after receipt of this priority letter AD or within the next 4 calendar months after receipt of this priority letter AD, whichever occurs first." (e) Within 10 days after the inspection required by paragraph (b) of this AD, send the results of the inspection in writing to the FAA at the address specified in paragraph (h) of this. Include the serial number of the airplane and state whether the alternate static air source assembly needed to be reworked or replaced. (Reporting approved by the Office of Management and Budget under OMB No. 2120-0056). (f) Fabricating and installing the placards as required by paragraph (a) of this AD may be performed by the owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7), and must be entered into the aircraft records showing compliance with this AD in accordance with section 43.9 of the Federal Aviation Regulations (14CFR 43.9). (g) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (h) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (i) Copies of the applicable service information may be obtained from the Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 941-5800; facsimile: (316) 942-9006. This information may also be examined at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (j) Priority Letter AD 98-01-01, issued December 22, 1997, becomes effective immediately upon receipt.
48-12-05: 48-12-05 BELL: Applies to Models 47B Series and 47D. Compliance required at next 100-hour teardown inspection if less than 600 hours have been accumulated. (If over 600 hours have been accumulated, this change must be accomplished immediately.) Replace the dural shear screws in the transmission spider assembly with steel shear screws (P/N 47-620-485-1). (Bell Service Bulletin No. 47C66, revised February 10, 1948, also covers this same subject.)
2012-07-08: We are superseding an existing airworthiness directive (AD) for all EMBRAER Model ERJ 170 airplanes. That AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) to incorporate new structural inspection requirements. Since we issued that AD, during full scale fatigue testing, cracks were found in certain structural components of the airplane. Analysis of these cracks resulted in the manufacturer modifying the ALS of EMBRAER 170 Maintenance Review Board Report (MRBR), to include new inspections tasks, or modifying the current tasks and their respective thresholds and intervals. This new AD requires revising the maintenance program to incorporate new or revised structural inspection requirements. We are issuing this AD to detect and correct fatigue cracking which could result in the loss of structural integrity of the airplane.
78-07-08: 78-07-08 ROLLS ROYCE, LTD.: Amendment 39-3171. Applies to Dart engines Series 542-4, 542-10, 543-10, and variants, featuring any of the following, Modifications 1243, 1244, 1432, 1448, or 1607, used on, but not limited to Convair 600 and 640 aircraft, and Nihon YS-11 and YS-11A series aircraft. Compliance is required as indicated. To prevent excessive wear in flame tube liners and suspension pins that may result in loss of flame tube support causing overheating and failure of the turbine rotors, accomplish the following: (a) Within the next 500 hours engine time in service after the effective date of this AD, unless already accomplished, inspect the flame tube liners and suspension pins for wear in accordance with the instructions contained in paragraph 4A of Rolls Royce Dart Service Bulletin Da 72-431, dated July 1, 1977 (hereafter RR SB 72-431), or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, APO New York, New York 09667 (hereafter FAA-approved equivalent). (b) If, during an inspection required by this AD, flame tube liner or suspension pin wear is found to exceed the limits given in paragraph 4A(1) of RR SB 72-431, or an FAA-approved equivalent, before further flight, except that the aircraft may be flown in accordance with FAR Sections 21.197 and 21.199 to a base where the work can be performed, replace the affected part with a serviceable part and reinspect in accordance with either paragraph (c) or (d) of this AD, as applicable. (c) If, during an inspection required by this AD, flame tube liner wear is 0.030 or greater inches on any one flame tube of any engine in the operator's fleet, determine the flame tube time in service since new or overhauled, and establish a fleet repetitive inspection time interval in accordance with paragraph 4.A(1)(c)(ii) or 4.A(2) as applicable, of RR SB 72-431 or an FAA-approved equivalent. (d) If, during an inspection required by this AD, flame tube liner wear is less than 0.030 inches on any one flame tube of any engine in the operator's fleet, replace, if necessary, the affected parts according to paragraph (b) of this AD and reinspect in accordance with paragraph 4.A(4) of RR SB 72-431, or an FAA- approved equivalent, at intervals not to exceed 2000 hours engine time in service from the last inspection. (e) If, during a repetitive inspection required by paragraph (c) or (d) of this AD, flame tube liner wear is 0.030 or greater inches on any one flame tube of an engine in the operator's fleet, reduce the Repetitive Inspection Interval for all engines in the fleet in accordance with paragraph 4.A(2) of RR SB 72-431, or an FAA-approved equivalent. (f) Record the repetitive inspection time intervals established pursuant to paragraphs (c), (d), and (e) in the aircraft maintenance records. This amendment becomes effective May 3, 1978.
2012-08-10: 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 reports of the air driven generator (ADG) failing to power essential buses during functional tests, due to the low threshold setting of the circuit protection on the ADG's generator control unit (GCU) preventing the ADG from supplying power to the essential buses. This AD requires installing a new or serviceable ADG GCU. We are issuing this AD to prevent loss of power from the ADG to the essential buses which, in the event of an emergency, could prevent continued safe flight.
98-02-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 and Mark 0070 series airplanes, that requires modification of the hook and latch engagement assemblies of the engine cowl doors, measurement of the aerodynamic mismatch between the fixed cowl and lower cowl door, and repair, if necessary. This amendment is prompted by reports of operational experience that indicate that an aerodynamic mismatch may exist between the fixed engine cowl and the lower cowl door, and may be the result of one or more hooks of the engagement assemblies not engaging adequately. This condition may cause the other hooks to carry loads higher than they were originally designed to carry, and could result in the failure of those hooks that are engaged. The actions specified by this AD are intended to prevent possible separation of the lower cowling from the airplane due to failure of the hooks of the engagement assemblies.
92-07-03: 92-07-03 BRITISH AEROSPACE: Amendment 39-8199. Docket No. 91-NM-208-AD. Applicability: Model BAe 125-800A series airplanes, as listed in British Aerospace Service Bulletin 25-67-25A013A, Revision 2, dated October 18, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced controllability of the airplane, accomplish the following: (a) Within 30 days after the effective date of this AD, drain the water from the wash basin water tank; and fabricate and install a placard to indicate that the wash basin is "inoperative." (b) Within 3 months after the effective date of this AD, install a new collector/outlet and drain pipe below the wash basin water tank outlet in accordance with British Aerospace Service Bulletin 25-67- 25A013A, Revision 2, dated October 18, 1991. After installing the new collector/outlet and drain pipe, remove the placard required by paragraph (a) of this AD. (c) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, 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 installation shall be done in accordance with British Aerospace Service Bulletin 25-67-25A013A, Revision 2, dated October 18, 1991, which includes the following list of effective pages: NOTE: The individual pages of this service bulletin are marked only with a "revision level." No dates appear on the pages, except for page 1, which references July 18, 1991, as the issue date of the original version of the service bulletin, and October 18, 1991, as the issue date of Revision 2. Page Number Revision Level 1, 7-8, 9-10, 2 2, 3, 4, 5-6, 11-12, 13, 14 Original 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, 1100 L Street NW., Room 8401, Washington, DC. (f) This amendment becomes effective on May 4, 1992.
2012-08-07: We are superseding an existing airworthiness directive (AD) for certain Sicma Aero Seat Model 9401, 9402, 9404, 9505, 9406, 9407, 9408, and 9409 series passenger seat assemblies, installed on, but not limited to, ATR--GIE Avions de Transport R[eacute]gional Model ATR42 and ATR72 airplanes. That AD currently requires repetitive detailed inspections for cracking of the central and lateral spreaders of the affected seats, and repair or replacement of the spreader if necessary. This AD was prompted by a determination that the existing AD included Model 9505 series passenger seat assemblies in the applicability instead of Model 9405 series passenger seat assemblies. We are issuing this AD to detect and correct cracking of the central and lateral spreaders, which could lead to further cracking of the seat spreaders, causing injury to passengers or crew members during heavy turbulence in flight or in the event of an emergency landing.
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.
2012-08-09: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F series airplanes. This AD was prompted by reports of cracks found in the Web pockets of the wing center section (WCS) spanwise beams. This AD requires repetitive detailed inspections and high frequency eddy current inspections for cracks of the WCS spanwise beams, and repair if necessary. We are issuing this AD to detect and correct cracking in the WCS spanwise beams, which could result in reduced structural integrity of the wings.
97-26-20: This amendment supersedes Airworthiness Directive AD 96-09-08 R1, which applies to Aviat Aircraft Inc. (Aviat) Models S-2A, S-2B, and S-2S airplanes (formerly Pitts Models S-2A, S-2B, and S-2S), and currently requires repetitively inspecting the upper longerons just aft of the rear cabane struts for cracks and repairing any cracks. This action retains the same actions as the current AD; lengthens the time interval between repetitive inspections; requires either installing a marked accelerometer in order to continue to perform acrobatic maneuvers and installing a placard that specifies gravity ("g") force limitations, or installing a placard prohibiting acrobatic maneuvers; and, requires inserting revisions into the Airplane Flight Manual (AFM). This action is the result of reports of cracking in the upper longerons caused by operating the airplane outside of the certificated design limits and the availability of a design modification that, when incorporated, repairs the damaged upper longeron area. The actions specified by this AD are intended to prevent cracking and subsequent failure of the longerons with consequent loss of control of the airplane.
2012-07-09: We are superseding an existing airworthiness directive (AD) for Turbomeca S.A. Arrius 2F turboshaft engines with P3 air pipe (first section) part number (P/N) 0 319 71 918 0, installed. That AD currently requires inspections of the P3 air pipe (first section) and right-hand (RH) rear half-wall for proper clearance and readjustment of the pipe if necessary. This new AD requires the same inspections for installed engines, eliminates readjusting of the P3 air pipe (first section), requires replacement of the RH rear half-wall under certain conditions, and adds an optional terminating action. This AD was prompted by Turbomeca determining that the clearance between the P3 air pipe (first section) and the RH rear half-wall might change during installation of the engine on the helicopter. We are issuing this AD to prevent an uncommanded power loss to flight idle, which could result in an emergency autorotation landing or accident.