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2011-05-10: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: * * * * * Recently, during a walk round check, an operator found an aileron trim tab hinge pin that had migrated sufficiently to cause a rubbing foul on the flap. Other reports indicate that, for the purposes of expediency, it has become common practice during maintenance when replacing a control tab, instead of unbolting the forward part of the piano hinge from the primary control surface, the hinge pins are punched out of the hinges. Investigations have concluded that, after reinserting the pins after maintenance, the ends of the hinges may not have been pinched, which is likely to have been the cause of the detected hinge pin migration. This condition [non-pinched hinge pin ends], if not detected and corrected, could lead to further incidents of migration of a tab [[Page 13070]] hinge pin out of the hinge, likely resulting in restricted movement of the tab control and consequent reduced control of the aeroplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2011-04-09: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2011-04-09 that was sent previously by individual notices to the known U.S. owners and operators of affected airplanes identified above. This AD requires modifying the chemical oxygen generators in the lavatory. This AD was prompted by reports that the current design of these oxygen generators presents a hazard that could jeopardize flight safety. We are issuing this AD to eliminate this hazard.
96-09-29: This amendment adopts a new airworthiness directive (AD), applicable to Robinson Helicopter Company (Robinson) Model R22 helicopters, that requires replacement of the upper V-belt sheave (sheave). This amendment is prompted by three reports of cracks in the flange of the sheave. The actions specified by this AD are intended to prevent failure of the sheave, which could result in damage to other drive system components, and subsequent loss of control of the helicopter.
91-26-04: 91-26-04 BRITISH AEROSPACE: Amendment 39-8115. Docket No. 91-NM-140-AD. Applicability: Model ATP series airplanes, equipped with nose landing gear (NLG) part number 201049001 or 201278001/002, pre Dowty Aerospace Gloucester modification (c)AC11432 standard, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the NLG, accomplish the following: (a) Within 60 days after the effective date of this AD, modify the NLG, treat the main fitting of the NLG with corrosion inhibitor, and externally seal the cover sub-assembly in accordance with British Aerospace Service Bulletin ATP 32-33, dated March 1, 1991. NOTE: The British Aerospace Service Bulletin references Dowty Aerospace Gloucester Service Bulletin 200-32-143, dated February 20, 1991. (b) Repeat the application of corrosion inhibitor at intervals not to exceed 6 months from the previous application, in accordance with British Aerospace Service Bulletin ATP-32-33, dated March 1, 1991. (c) Install Dowty Aerospace Gloucester modification (c)AC11432 on all pre-modification (c)AC11432 NLG's in accordance with British Aerospace Service Bulletin ATP-32-33, dated March 1, 1991, at the later of the times specified in subparagraphs (c)(1) and (c)(2), below: (1) Prior to the accumulation of 6,000 landings on the NLG since new, or within 3 years from the first flight on the NLG, whichever occurs first; or (2) Within 12 months after the effective date of this AD. NOTE: The British Aerospace Service Bulletin references Dowty Aerospace Gloucester Service Bulletin 200-32-144, dated February 20, 1991, which describes modification (c)AC11432. (d) Installation of Dowty Aerospace Gloucester modification (c)AC11432 constitutes terminating action for the repetitive applications of corrosion inhibitor required by paragraphs (a) and (b) of this AD. (e) 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. (f) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. (g) The modifications and application of corrosion inhibitor required by this AD shall be done in accordance with British Aerospace Service Bulletin ATP-32-33, dated March 1, 1991. 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, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. (h) This amendment (39-8115, AD 91-26-04) becomes effective on January 27, 1992.
76-13-02: 76-13-02 GENERAL ELECTRIC COMPANY: Amendment 39-2649. Applies to General Electric Company CT58-100-2, CT58-110-1, CT58-110-2, CT58-140-1, CT58-140-1, Series A/L and CT58-140-2 engine fuel system hose, P/N 37C300486P101, P/N 37C300486P102, or P/N 37C300486P103 with identification band bearing a manufacture date of 1968 or earlier. Hoses with red/orange molded silicone firesleeving are not affected by this AD. Compliance required unless already accomplished, within the next thirty (30) days time in service after the effective date of this AD. To prevent possible failure of oil cooler-to-fuel filter hose identified above, remove firesleeving from hose and inspect for corrosion or broken braiding in accordance with General Electric Alert Service Bulletin No. A73- 69 or later FAA approved revision, or equivalent inspection method approved by the Chief, Engineering and Manufacturing Branch, New England Region, Federal Aviation Administration. Hoses passing inspection must have new firesleeving applied per Section 72-09-03 of the applicable General Electric Engine Overhaul Manual. Hoses rejected due to this inspection must be replaced with new hose P/N 37C300486P101, P/N 37C300486P102 or P/N 37C300486P103 with identification band bearing a manufacture date of 1969 or later. Approved replacement firesleeving is identified in General Electric Alert Service Bulletin No. A73-69 or later FAA approved revision. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance time specified in the AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. General Electric Company Service Bulletins identified in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these Service Bulletins from General Electric Company may receive copies upon request to General Electric Company, 1000 Western Avenue, Lynn, Massachusetts 01910. These documents may also be examined at the New England Region, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the Federal Aviation Administration at its Headquarters in Washington, D.C., and at the New England Regional Office in Burlington, Massachusetts. This amendment becomes effective July 6, 1976.
2011-05-08: This action supersedes emergency airworthiness directive (AD) 2011-05-51 that was sent previously to all known U.S. owners and operators of the products listed above. That AD requires inspecting the fuel ejector in the body of the fuel ejector assembly for proper installation by checking that the circlip is properly seated in its groove. That AD was prompted by three reports of incorrectly assembled low-pressure fuel system ejectors; with one of them resulting in an uncommanded engine in-flight shutdown. This AD requires the same actions and compliance times as the emergency AD, after receipt of the emergency AD, and expands the AD applicability by including helicopters having one or two affected engines and experiencing no starting difficulties. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe conditionas: In October 2009, Turbomeca issued SB [Service Bulletin] No. 292 73 0826, Version A that instructed operators to check the effectiveness of the bonding of the ejector jet installed on the low-pressure fuel system between the tank and the high-pressure fuel pump. So far, Turbomeca have been informed of three discrepancies with the reassembly of the ejector following a maintenance procedure performed during accomplishment of Turbomeca SB No. 292 73 0826, Version A. In all three cases, the discrepancies led to a ``one-off'' abnormal evolution of gas generator (NG) rating during engine starting. In one of these cases, this resulted in an uncommanded in- flight shutdown, during a cruising phase at 8,000 feet. We are issuing this AD to prevent uncommanded engine in-flight shutdown of one or both engines in a two-engine helicopter and an emergency autorotation landing or accident.
2007-07-06 R1: We are adopting a new airworthiness directive (AD) to revise AD 2007-07-06, which applies to certain Cessna Aircraft Company (type certificate previously held by Columbia Aircraft Manufacturing) (Cessna) Models LC40-550FG, LC41-550FG, and LC42-550FG airplanes. AD 2007-07-06 currently requires the following: Adding information to the limitations section of the airplane flight manual (AFM); repetitively inspecting the aileron and the elevator linear bearings and control rods for foreign object debris, scarring, or damage; and taking all necessary corrective actions. Since we issued AD 2007-07-06, Cessna has issued a new service bulletin that contains procedures for installing an access panel to facilitate the required inspections. Consequently, this AD retains the actions currently required in AD 2007-07-06; allows installing access panels; and changes the serial number applicability. We are issuing this AD to prevent jamming in the aileron and elevator control systems, which could result in failure. This failure could lead to loss of control. DATES: This AD becomes effective on December 5, 2008. On December 5, 2008, the Director of the Federal Register approved the incorporation by reference of Cessna Mandatory Service Bulletin SB- 07-002D, dated May 29, 2008, and Cessna Mandatory Service Bulletin SB- 07-018, dated May 29, 2008, listed in this AD. As of April 9, 2007 (72 FR 15822, April 3, 2007), the Director of the Federal Register approved the incorporation by reference of Columbia Mandatory Service Bulletin SB-07-002, dated March 14, 2007, listed in this AD.
96-21-04: This amendment supersedes Airworthiness Directive (AD) 86-17-07, which currently requires replacing all hydraulic hoses with hydraulic hoses of an improved design on certain The New Piper Aircraft, Inc. (Piper) PA23, PA31, PA31P, PA31T, and PA42 series airplanes. This AD action will require inspecting for improperly manufactured hydraulic hoses replaced during a specific time frame and replacing all affected hydraulic hoses. An incorrect designation of a Piper Model PA31-310 and a Piper Model PA23-150 airplane prompted the proposed AD action. The actions specified by this AD are intended to prevent hydraulic hose failure which could cause loss of hydraulic capabilities resulting in a gear-up landing and possible loss of the airplane.
2011-05-01: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Compass mismatch (up to loss of heading information) were reported by operators, due to ferro-magnetic masses (like the telescopic Tow-Bar) stowed in the baggage compartment. We are issuing this AD to require actions to correct the unsafe condition on these products.
92-10-06: 92-10-06 AIR CRUISERS COMPANY: Amendment No. 39-8240. Docket No. 90-ANE-26. Applicability: Air Cruisers Co. TSO-C69 Emergency Evacuation Slide System, Part Numbers (P/N) D31021-101 and -103, Serial Numbers 1 through 222, installed on but not limited to Airbus Industries Models A300 B2-1C, A300 B4-2C, A300 BA-200 and A300 B4-600 series aircraft. Compliance: Required within 9 months after the effective date of this AD, unless previously accomplished. To prevent improper inflation of the slides, which could hamper the emergency evacuation of an aircraft, accomplish the following: (a) Modify and reidentify Air Cruisers Co. Evacuation Slide System, P/N D31021-101 and -103, serial numbers 1 through 222, in accordance with Air Cruisers Co. Service Bulletin (SB) 001-25-8, Revision 4, dated May 24, 1990, Paragraph 2, Accomplishment instructions. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a locationwhere the requirements of this AD can be accomplished. (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, New York Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 181 South Franklin Avenue, Valley Stream, New York 11581-1145. The request should be forwarded through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the New York Aircraft Certification Office. (d) The modifications and inspections required by this AD shall be accomplished in accordance with the following Air Cruisers Co. Service Bulletin: DOCUMENT NO. PAGE ISSUE/REVISION DATE S.B.001-25-8 1, 3, 4, 5, Rev. No. 4 May 24, 1990 8, 9, 11, 14, 16, 21, 22 2, 6, 7, 10, Rev. No. 3 April 30, 1990 12, 13, 15, 17, 18, 19, 20, 23, 24, 25, 26 Total Pages: 26 The 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 Air Cruisers Co., P.O. Box 180, Belmar, N.J. 07719-0180. Copies may be reviewed at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, D.C. (e) This amendment becomes effective July 6, 1992.
96-10-02: This amendment adopts a new airworthiness directive (AD) that applies to certain HB Flugtechnik GmbH (Flugtechnik) Model HB-23/2400 sailplanes. This action requires inspecting (one time) the elevator control push rod tube for dents or bending and replacing the push rod tube, if damaged, inspecting the elevator control system for incorrect rigging, and repetitively inspecting the threaded adjustable extension joints in the push rod to control lever connection for cracks. If cracks are found, replacing the threaded adjustable joints at both ends of the push rod. Cracking of the threaded adjustable extension joints and incorrect rigging of the elevator control system prompted this AD action. The actions specified by this AD are intended to prevent failure of the elevator control system, which, if not detected and corrected, could result in possible loss of elevator control and loss of the sailplane.
96-09-06: This document supersedes airworthiness directive (AD) 95-03-02, which currently requires repetitively inspecting (visually) the air filter frame for a loose or deteriorating gasket on airplanes incorporating certain Brackett air filter assemblies and replacing any gasket found loose or deteriorated. This action requires retaining the repetitive inspection as contained in AD 95-03-02, and will incorporate additional Brackett air filter assemblies to the "Applicability" section of that AD. Additionally, this AD will provide a terminating action for the repetitive inspection. The Federal Aviation Administration's determination that certain additional Bracket air filter assemblies should be inspected and replaced prompted this AD action. The actions specified by this AD are intended to prevent gasket particles from entering the carburetor because of air filter gasket failure, which could result in partial or complete loss of engine power and loss of control of the airplane.
92-11-02: 92-11-02 AEROSPATIALE: Amendment 39-8252. Docket No. 92-NM-03-AD. Applicability: Aerospatiale Model SN 601 Corvette series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a reduction in the structural integrity of the fuselage, accomplish the following: (a) Prior to the accumulation of 14,100 flight cycles or within the next 100 flight cycles after the effective date of this AD, whichever occurs later, perform a high frequency eddy current inspection to detect cracks in the left-hand (LH) and right hand (RH) side canopy inner skins forward of Frame 10 at the height of Stringer 4, in accordance with Aerospatiale Service Bulletin 53-26, dated January 24, 1991. (b) Repeat the inspection required by paragraph (a) of this AD at intervals not to exceed 5,600 flight cycles. (c) If cracks are detected as a result of the inspection required by paragraphs (a) or (b) of this AD, prior to further flight, install Modification 1395 in accordance with Aerospatiale Service Bulletin No. 53-14, Revision 1, dated January 24, 1991. (d) Accomplishment of Modification 1395, in accordance with Aerospatiale Service Bulletin No. 53-14, Revision 1, dated January 24, 1991, constitutes terminating action for the inspection requirements of this AD. (e) 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. (f) 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. (g) The inspections shall be done in accordance with Aerospatiale Service Bulletin 53- 26, dated January 24, 1991. The modifications shall be done in accordance with Aerospatiale Service Bulletin No. 53-14, Revision 1, dated January 24, 1991, which includes the following list of effective pages: Page Numbers Revision Level Date 1, 3 1 January 24, 1991 2, 4-6 Original June 23, 1983 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 Aerospatiale, 316 Route de Bayonne, 31060, Toulouse, Cedex 03, France. 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. (h) This amendment becomes effective on July 23, 1992.
69-19-03: 69-19-03 DOWTY ROTOL: Amdt. 39-837. Applies to Dowty Rotol Propellers Type Nos. (c) R.130/4-20-4/12E and (c) R.148/4-20-4/21E installed on British Aircraft Corporation (Vickers) Viscount 744 and 745D airplanes. Compliance required as indicated, unless already accomplished. (a) For Type No. (c) R.130/4-20-4/12E propellers installed on Model 745D, Viscount airplanes and for Type No. (c) R.148/4-20-4/21E propellers installed on Model 744 Viscount airplanes, accomplish the following: (1) For propellers having hubs with 15,000 or more hours' time in service on the effective date of this AD, accomplish the inspection required by paragraph (3) of this section within the next 400 hours' time in service after the effective date of this AD, or before 3,000 hours' time in service since the last inspection, whichever occurs later. Thereafter, repeat this inspection at intervals not to exceed 3,000 hours' time in service from the last inspection. (2) For propellers having hubs with less than 15,000 hours' time in service on the effective date of this AD, accomplish the inspection required by paragraph (3) of this section before 3,000 hours' time in service has accumulated since the last inspection, or before the accumulation of a total of 15,400 hours' time in service, whichever occurs later. Thereafter, repeat this inspection at intervals not to exceed 3,000 hours' time in service from the last inspection. (3) Inspect the hub arm threads including binocular inspection and crack testing in accordance with Dowty Rotol Limited Service Bulletin No. 61-608, Revision 1, dated June 1968, or later ARB-approved issue, or an FAA-approved equivalent method. If cracked threads are detected during any inspection, before further flight, replace the propeller hub with a serviceable part of the same part number. (b) For Hub and Driving Center Assembly P/Nos. RA.48546, RA.59601, and RA.59602 installed on propellers having serial numbers listed in paragraph (c) accomplish the following: (1) Remove from service all hub and driving center assemblies having 20,000 or more hours' time in service on the effective date of this AD within the next 400 hours' time in service after the effective date of this AD. (2) Remove from service all hub and driving center assemblies having less than 20,000 hours' time in service on the effective date of this AD, within the next 400 hours' time in service after the effective date of this AD, or upon the accumulation of a total of 20,000 hours time in service, whichever occurs later. (c) Propeller Serial Numbers DRG.12/61 99241 99381 99568 99749 102071 DRG.13/61 99244 99386 99573 99752 102073 DRG.15/61 99266 99388 99575 99754 102148 574 99267 99395 99577 99759 102149 5733 99268 99396 99578 99766 102152 57265 99269 99397 99579 99771 102166 57268 99270 99399 99580 99772 102167 98338 99272 99403 99587 99784 102168 99180 99275 99405 99594 99791 102170 99186 99276 99407 99596 99800 102184 99187 99278 99409 99597 99804 102257 99190 99281 99410 99600 100024 102259 99191 99283 99411 99603 100025 102349 99198 99284 99413 99606 100040 102489 99207 99323 99417 99609 101579 99211 99330 99427 99613 101584 99217 99337 99429 99614 101586 99218 99339 99434 99615 101804 99220 99341 99437 99617 101929 99221 99352 99440 99620 101985 99222 99353 99443 99621 101986 99224 99368 99468 99741 101987 99231 99369 99472 99742 102041 99235 99375 99546 99743 102046 99239 99377 99557 99745 102052 (d) For hub and driving center assembly having P/Nos. listed in paragraph (e), accomplish the following: (1) Remove from service all hub and driving center assemblies having 30,000 or more hours' time in service on the effective date of this AD, within the next 400 hours' time in service after the effective date of this AD. (2) Remove from service all hub and driving assemblies having less than 30,000 hours' time in service on the effective date of this AD within the next 400 hours' time in service after the effective date of this AD, or upon the accumulation of a total of 30,000 hours' time in service, whichever occurs later. (e) Hub and Driving Center Assembly Part Numbers RA41744 RA47436 RA44761 RA47436/2 RA44761/1 RA47436/4 RA44761/2 RA47592 RA44761/3 RA48546 RA44761/4 RA49557 RA44761/5 RA56345 RA45155 RA58184 RA45155/1 RA59601 RA45155/2 RA59602 This amendment becomes effective October 6, 1969.
2011-04-05: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI (European Aviation Safety Agency AD 2009- 0192) describes the unsafe condition as: Performing some quality tests on material, Airbus found that some 300M steel forgings used to manufacture certain landing gear components were below specification limits. Adapted airworthiness limitations were introduced in Airbus A340 Airworthiness Limitations Section (ALS) Part 1 ``Safe Life Airworthiness Limitation Items (SL ALI)'' for different source route codes. * * * * * This [EASA] AD introduces more restrictive life limitations for several landing gear components. The MCAI (EASA AD 2010-0131) describes the unsafe condition as: * * * * * The revision 04 of Airbus A330 and A340 ALS Part 1 introduces more restrictive maintenance requirements and/or airworthiness limitations as specified in Airbus A330 and A340 ALS Part 1 revision 04. The unsafe condition is failure of certain life-limited parts, which could result in reduced structural integrity of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2011-04-01: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During a normal walkaround check on a F28 Mark 0100 aeroplane, a large crack was discovered in the lower portion of the right (RH) MLG [main landing gear] piston. The affected MLG unit had accumulated 7909 flight cycles (FC) at the time of detection. * * * This condition, if not detected and corrected, could lead to MLG failure, possibly resulting in loss of control of the aeroplane during the landing roll-out. We are issuing this AD to require actions to correct the unsafe condition on these products.
96-08-02: This amendment supersedes an existing airworthiness directive (AD), applicable to Hamilton Standard Models 14RF-9, 14RF-19, 14RF-21; and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, and 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F propellers, that currently requires that all blades of applicable Hamilton Standard propellers be calibrated for ultrasonic transmissibility before conducting the ultrasonic shear wave inspection. In addition, that AD decreases the repetitive inspection interval for the Hamilton Standard Models 14RF-9, 14SF-5, -7, -11, -15, -17, -19, and -23 propellers from 1,250 flight cycles to 500 flight cycles. That AD also establishes a new ultrasonic shear wave inspection interval of 1,000 flight cycles for the Hamilton Standard Model 14RF-19, and 2,500 flight cycles for the Hamilton Standard Models 14RF-21 and Hamilton Standard/British Aerospace Model 6/5500/F. Also, that AD removes Hamilton Standard Model 14SFL11 propellers from service. This amendment requires a blade repair that constitutes terminating action to the repetitive ultrasonic taper bore inspections. Repetitive ultrasonic taper bore inspections are required until the blade is repaired in accordance with this AD. This amendment is prompted by the development of a taper bore repair process that removes the damaged material and returns the blade to a condition that does not require repetitive ultrasonic taper bore inspections. The actions specified by this AD are intended to prevent separation of a propeller blade due to cracks initiating in the blade taper bore, that can result in aircraft damage, and possible loss of aircraft control.
69-02-03: 69-02-03 AVIONS MARCEL DASSAULT: Amendment 39-713. Applies to Fan Jet Falcon Airplanes which have a Collins AP-103E or AP-103F autopilot installed in accordance with Pacific Airmotive Corporation STC No. SA1131WE. Compliance required as indicated, unless already accomplished. To prevent possible hazardous in-flight load factors: A. The following operating limitation is hereby adopted: "The autopilot shall not be engaged or operated at speeds in excess of 250 knots IAS." B. Within the next 10 hours time in service after the effective date of this AD unless already accomplished, the operating limitation specified in paragraph A above must be placed in the aircraft in the form of a placard in clear view of the pilot, near the autopilot controller stating: "The autopilot shall not be engaged or operated at speeds in excess of 250 knots IAS." C. Remove the placard only upon accomplishment of the modifications described in paragraph E below, or of anequivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. D. The operating limitation specified in paragraph A above shall not apply if the modifications described in paragraph E below have been accomplished. E. Modify the Collins AP-103E or AP-103F autopilot system as follow: 1. Replace the elevator primary servo unit Collins P/N 334C-3A with a Collins P/N 334C-3E with the servo torque adjusted to 20.5 plus or minus .2 in-lbs. 2. Check the following: (a) Aileron and elevator capstan cables for correct seating of ball end fittings into capstan groove. (b) Aileron and elevator cables for a tension of 65 lbs. plus or minus 5 lbs. If cables are not seated or cannot be tensioned correctly, they should be replaced. NOTE: Refer to the STC SA1131WE data for rigging instructions. 3. Modify the Dassault aircraft Trim Relay Box M20.632.18, per Dassault Service Bulletin 307, Sec. 1, or later FAA approved revision, or equivalent modification approved by Chief, Aircraft Engineering Division, FAA Western Region. 4. Adjust 161A-1A trim coupler for 8 degrees plus or minus 1 degree per minute trim speed in accordance with the following instructions, or to an equivalent procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. (a) Adjust dc ground power to aircraft for 28 vdc (measured at the aircraft bus). (b) Set the 161A-1A trim coupler potentiometers R2 (up) and R22 (down) to middle of travel. (c) Engage the autopilot and overpower the elevator servo enough to cause the torque limiting clutch to slip. Adjust R47 to obtain a trim speed of 8 degrees per minute average (check both up and down travel). (d) Disengage the autopilot and remove servo amplifiers from the 562C-4E computer/amplifier. (e) Engage the autopilot and apply 540 millivolts dc from external source to test jacks J2 (positive) and J3 in the 161A-1A trim coupler. Adjust R2 to obtain minimum pulsing that actuates the aircraft trim system (up). The time interval between these short pulses should not exceed three seconds. (f) Remove external source from the 161A-1A trim coupler test jacks J2 and J3 and apply 75 millivolts dc to test jacks J4 (positive) and J5. Adjust R22 to obtain minimum pulsing that actuates the aircraft trim system (down). The time interval between these short pulses should not exceed three seconds. (g) Recheck trim speed and readjust R47 for 8 degrees plus or minus degree per minute if necessary. NOTE: Collins Service Information Letter 23-68, dated July 15, 1968, paragraphs 3 thru 6, covers the modification of the AP-103F flight control system only. This amendment becomes effective on January 25, 1969.
95-26-16 R1: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 95-26-16 R1, which was sent previously to all known U.S. owners and operators of certain Mooney Aircraft Corporation (Mooney) Model M20J airplanes. This AD requires repetitively inspecting the alternate air door assembly to ensure a cotter pin exists and is secure, and replacing the cotter pin if it does not exist or is not secure. It also provides the option of incorporating an alternate air door plate assembly of improved design as terminating action for the repetitive inspections. Priority letter AD 95-26-16 R1 was prompted by a fatal accident involving one of the affected airplanes where the alternate air door became lodged in the air intake of the fuel injector causing engine failure. The actions specified by this AD are intended to prevent the alternate air door from separating from the airplane and restricting air flow to the engine.
92-17-02: 92-17-02 EMBRAER: Amendment 39-8331. Docket No. 92-CE-11-AD. Applicability: EMB-110 Series airplanes (all serial numbers), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent severe vibration or loss of control of the airplane caused by excessive free play and lack of rigidity of the rudder trim tab actuating system, accomplish the following: NOTE 1: The compliance times referenced in this AD take precedence over those cited in the referenced service information. (a) Within the next 500 hours time-in-service (TIS), modify the rudder trim tab actuating system and install reinforcements to the vertical stabilizer rear spar in accordance with the instructions in and Figures 1, 2, and 3 of EMBRAER Service Bulletin (SB) 110-027-0089, dated July 19, 1991. NOTE 2: EMBRAER SB 110-27-0089 specifies that the airplane should be modified in accordance with EMBRAER SB 110-27-0060 - "Replacement of Spherical Bearings of Aileron and Rudder Trim Tab Control Systems Rod Ends". This action is required for the affected airplanes by AD 87-01-05, Amendment 39-5490. (b) Within 300 hours TIS after accomplishing the modifications required by paragraph (a) of this AD, and thereafter at intervals not to exceed 300 hours TIS, inspect the rudder trim tab actuating system for excessive free play in accordance with the applicable maintenance manual. If free play exceeds 1.0 mm., prior to further flight, modify the rudder trim tab actuating system in accordance with the applicable maintenance manual. (c) If the parts required by paragraph (a) of this AD have been ordered, but are not available, within the initial 500 hours TIS required by paragraph (a) of this AD, accomplish the following: (1) Inspect the rudder trim tab actuating system for excessive free play in accordance with the applicable maintenance manual. (2) If free play exceeds 3.3 mm., prior to further flight, modify the rudder trim tab actuating system in accordance with the applicable maintenance manual. NOTE 3: The modification procedures in the maintenance manual for the rudder trim tab actuating system if excessive free play exists are the same whether the criteria is 1.0 mm or 3.3 mm. The only difference is the criteria for the magnitude of the free play. (3) Reinspect in accordance with paragraphs (c)(1) and (c)(2) of this AD at intervals not to exceed 100 hours TIS until the modifications required by paragraph (a) of this AD are accomplished, but not to exceed three 100-hour TIS repetitive inspection intervals. (4) When parts become available or 100 hours TIS after the third repetitive inspection required by paragraph (c)(3) of this AD, whichever occurs first, prior to further flight, accomplish the modification required by paragraph (a) of this AD. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location wherethe requirements of this AD can be accomplished. (e) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (f) The inspections, reinforcement, and modifications required by this AD shall be done in accordance with EMBRAER Service Bulletin 110-027-0089, dated July 19, 1991. 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 EMBRAER, P.O. Box 343-CEP, 12.200 Sao Jose dos Campos, Sao Paulo, Brazil; or EMBRAER Aircraft Corporation, 276 SW 34th Street, Fort Lauderdale, Florida 33315. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, N.W.; 7th Floor, Suite 700; Washington, DC. (g) This amendment becomes effective on September 11, 1992.
86-13-04 R3: 86-13-04 R3 TELEDYNE CONTINENTAL MOTORS (TCM): Amendment 39-5345, as amended by Amendment 39-5555, is further amended by Amendment 39-5850. Applies to cylinder assemblies (part number (P/N) stamped on flange of cylinder) with P/N's 643985, 646100, 646101, 646652, 646652CP, 646657, 646657CP, 649162, 649162CP, 649169, 649169CP including all these numbers with all "A" dash numbers as a suffix, and also any cylinder reworked from the above part numbers, either of which were manufactured on or after January 1, 1985, with 485 total hours or less installed on, but not limited to, the following Teledyne Continental Motors (TCM) Engines: NEW ENGINES SERIAL NUMBERS GTSIO-520-H 607068 thru 607070 -K 605164 -L 608669 thru 608673 -M 606979 thru 606997 -N 610450 thru 610462 TSIO-520-BE 528133 thru 528242, 528244 thru 528246, 528252 thru 528256, 528259, 528260, 528263, 528270 -CE 530045 thru 530127, 530131, 530132 -C 501603 thru 501610 -EB 510802 thru 510809 -G 507066 -H 506883 thru 506885 -M 520742 thru 520824, 520829 thru 520835, 520837, 520838 -NB 521585 thru 521615 -P 513908 thru 513910 -R 522588 thru 522602, 522604, 522605 -UB 527063 thru 527080 -VB 529014 thru 529060 -WB 518895 thru 518906 IO-520-BB 578073, 578084 thru 578151, 578155, 578156, 578166 -CB 576237 thru 576272 -D 575717, 575747 thru 575806 -E 556594 thru 556603 -F 574844 thru 574988 -K 557516 thru 557518 -L 577121 thru 577147, 577149 thru 577153 -MB 575043 thru 575046 IO-550-B 675125 thru 675237, 675239 thru 675244, 675246 thru 675256, 675258 thru 675266, 675273, 675274, 675277, 675278 -C 676156 thru 676231, 676233 thru 676248, 676250 thru 676271 REBUILT ENGINES GTSIO-520-C 155546 thru 155550 -D 219429 thru 219435 -H 235236 thru 235290, 235293 thru 235298, 267000 thru 267003 -K 226106 thru 226110 -L 245882 thru 245990, 245992 thru 246008, 246011 thru 246014, 246016 thru 246021, 246023, 246024 -M 243217 thru 243364, 243366, 243367, 243369 thru 243381 -N 241300, 265000 thru 265039, 265041 TSIO-520-AF 245205 -BB 236937 thru 236951 -B 176485 thru 176522 -C 178289 thru 178297 -EB 242984 thru 242999 -E 183816 thru 183939, 183941 thru 183943, 183947 -G 216022 thru 216025 -H 217173 thru 217187 -J 218907 thru 218924 -K 224583, 224584 -LB 237237 thru 237241, 237245, 237246 -L 241883 thru 241900 -M 230223, 230225, 248601 thru 248628, 248632 thru 248638, 248642 -NB 244933 thru 244999, 266500, 266501, 266503 thru 266511, 266513 thru 266517, 266521, 266525 -N 228481 thru 228505, 228509 thru 228516 -P 236453 thru 236467 -R 245645 thru 245696 -T 239316 thru 239321 -UB 240981 thru 241000, 248851 thru 248854, 248858 -VB 248288 thru 248499, 266600 thru 266681, 266683, thru 266685, 266687, 266689, 266691, 266699 thru 266702 -WB 248160 thru 248203, 248205 thru 248217 IO-520-A 112547 thru 112569 -BA 241763 thru 241800, 249251 thru 249425, 249427 thru 249429, 249433 thru 249443, 249445, 249446, 249448 thru 249453, 249457 -BB 236000, 236789, 248500 thru 248568, 248572, 248573, 248575 -B 234758 -CB 244047, 244067 thru 244110, 244112 thru 244123, 244126, 244127, 244130, 244131 -C 243728, 243766 thru 243999, 267500, 267505 thru 267510, 267513 thru 267516, 267527 IO-520-D 175381 thru 175531, 175534 thru 175536, 175540 thru 175556, 175559, 175560, 175563, 175565 thru 175567 -E 215674 thru 215690 -F 247574, 247577, 247607 thru 247727, 247731 thru 247742, 247744, 247746 thru 247750, 247752 thru 247756, 247762, 247766, 247767 -J 216515 -K 224045, 224046 -L 242834 thru 242896, 242899 -MB 236383 thru 236400, 266000 thru 266017, 266019 -M 235728 thru 235787, 235789 thru 235793 IO-550-B 249104 thru 249122 These engines are installed in, but are not limited to, the following airplanes: Aero Commander 200, 500, 685 AISI F, 20 Pegaso Ambrosini MF-15 Beagles B206S Beech 33, 35, 36, A36, A36TC,55, 58, 58P, 58TC Bellanca Viking 300 Cessna 185, 188, 206, 207, 210, 310, T310, 320, 335, 340, 401, 402, 404, 411, 414, 421 Fletcher FU-24A Janox Javilon Navion Model H Omnipal Cmelak Piper PA-46 Prinair DeHavilland Heron Procaer F-150 Picchio Transavia Airtruck Windecker Eagle Yeoman Cropmaster 285 Compliance required within the next 5 flight hours after the effective date of this AD, except as to those compliance requirements made effective previously as set forth in AD 86-13-04 dated June 20, 1986, priority letter AD 86-13-04 R1 dated September 5, 1986, AD 86-13-04 R2 dated February 19, 1987, and priority letter AD 86-13-04 R3 dated November 10, 1987, unless already accomplished. To prevent possible cylinder head to barrel separation, engine failure and/or engine compartment fire, accomplish the following: (a) For the above cylinder assembly part numbers installed on engines including those serial numbered engines listed above: (1) Determine the part number for each cylinder assembly (part number is stamped on flange of cylinder barrel) and the date of manufacture (month and year of manufacture are stamped underneath rocker cover on the face of the rocker shaft boss). (i) If the cylinder assembly part number and date of manufacture are as listed above, proceed with paragraphs (2), (3), (4), (5), and (6). (ii) If the cylinder assembly part number and date of manufacture are not as listed above, proceed to paragraph (6). No further inspections are required by this AD. (2) Visually inspect all cylinders for oil stains or leakage between the first and second barrel fins from the bottom of the head casting. The area of concern on direct drive engines is at the 12 o'clock position on the 1-3-5 cylinder side and the 6 o'clock position on the 2-4-6 side. On the GTSIO series engine, the area of concern is at the 6 o'clock position on the 1-3-5 cylinder side and the 12 o'clock position on the 2-4-6 cylinder side. (3) Pressure check all cylinder assemblies using a differential compression tester. The piston should be as close to BDC (Bottom Dead Center) as possible to insure the piston and rings are below the inspection area specified in paragraph (2) but still keeping both valves closed and maintaining pressure in the cylinder. With 80 PSIG (pounds per square inch gauge) air pressure in the cylinder, check the area specified in paragraph (2) with a soap/water solution and inspect for any leakage. (4) If any leakage is noted from the above inspection and/or pressure check, the cylinder assembly must be changed before further flight. NOTE: TCM Service Bulletin M86-7, Revision 5, dated November 15, 1986, advises that extreme caution be used in the area of the propeller while performing this inspection. (5) This visual inspection and pressure check must be repeated at intervals not to exceed 50 flight hours until the last inspection and pressure check required by this ADhas been accomplished. The last inspection and pressure check required by this AD must occur between 440 hours and 490 hours of cylinder operation. (6) The repetitive inspections and pressure checks described above may be discontinued when one of the following has been accomplished: (i) Suspect cylinder assemblies have been replaced with assemblies having a date of manufacture prior to January 1985. (ii) Approved replacement cylinder assemblies having different part numbers are installed provided these replacement cylinder assemblies are not reworked from the assembly part numbers listed above. (iii) New design pistons (as shown below) are installed, and the affected cylinder assembly has the letter "P" stamped or vibro-etched on the face of the rocker shaft boss adjacent to the manufacture date, i.e. 5-85P. ENGINE SERIES NEW PISTON PART NUMBER IO-550 648046 IO-520 648045 TSIO-520 and GTSIO-520 648044 (7) Make appropriate Engine Logbook entry. (b) For the above cylinder assembly part numbers not installed on engines, confirm a manufacture date stamp of 1-85 (January 1985) or subsequent (month and year of manufacture are stamped underneath rocker cover on the face of the rocker shaft boss), then notify TCM for disposition and replacement. (c) Comply with the provisions of this AD for the above cylinder assembly part numbers which are reworked and/or reidentified with a different part number. NOTE: TCM Service Bulletin No.'s M86-7, Revision 5, dated November 15, 1986, and M87-19, dated September 17, 1987, address this subject. (d) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (e) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. (f) Upon submission of substantiatingdata by an owner or operator through an FAA maintenance inspector, the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349, may adjust the compliance time specified in this AD. AD 86-13-04, Amendment 39-5345, became effective July 11, 1986. Priority Letter AD 86-13-04 R1, issued September 5, 1986, became effective immediately upon receipt. Amendment 39-5555 (AD 86-13-04 R2) became effective February 19, 1987, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD No. 86-13-04 R2, issued December 24, 1986. This amendment, 39-5850, (AD 86-13-04 R3) becomes effective February 24, 1988, as to all persons except those persons to whom it was made immediately effective by priority letter AD 86-13-04 R3 issued November 10, 1987, which contained this amendment.
2010-07-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: It has been determined that due to an intermittent communication between AMS [Air Management System] controller cards and both Secondary Power Distribution Assemblies (SPDAs) the message "RECIRC SMK DET FAIL'' is displayed in the Engine Indication and Crew Alerting System (EICAS). This communication failure could result in loss of automatic activation of engine inlet ice protection system when in ice condition. In this situation the caution messages "A-I Eng 1 Fail'' and "A-I Eng 2 Fail'' will be displayed and if the flight crews do not follow the associated procedures ice may accrete in the engines inlet and cause a dual engine shut down. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
84-15-03: 84-15-03 BOEING VERTOL COMPANY: Amendment 39-4892. Applies to Boeing Vertol Model 234 helicopters certified in all categories. Compliance is required as indicated, unless already accomplished. To prevent bypassing of the lower boost dual actuating cylinder(s) and to prevent fatigue failures of NAS 1351-3H10P cap screws on lower boost dual actuating cylinders in the flight control system, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, revise Boeing Vertol Rotorcraft Model 234 Flight Manual by inserting Revision 13 dated May 9, 1984. (b) Within the next 25 hours time in service after the effective date of this AD, unless already accomplished within the last 25 hours time in service, and thereafter at intervals not to exceed 300 hours time in service from the last inspection, inspect for water and total chlorine of the aircraft hydraulic system fluid in accordance with the contamination level test procedure specified in Boeing Process Specification BAC 5820, Revision A, as amended by Process Specification Department Number 8-2. An alternate inspection (including intervals between inspections) may be approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York 11581. For aircraft exceeding allowable contamination levels, flush the hydraulic system in accordance with the procedure specified in Boeing Vertol telex No. 8-1420-3-5459 dated May 25, 1984, or an equivalent approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York 11581. Sample to insure acceptability following flushing. Repeat the contamination level test procedure at intervals not to exceed 300 hours time in service, except that an alternate interval approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York 11581, may besubstituted. (c) Within the next 200 hours time in service from the effective date of this AD, unless already accomplished within the last 25 hours time in service, and subsequent to accomplishing the work of paragraph (b), remove all lower boost dual actuating cylinders Part Numbers (P/N) 234HS560-1 and -2 and inspect the shutoff valve spools for any visual signs of staining or pitting on the spool lands (shiny, lapped, interface surface). Replace the actuator with a serviceable part if staining or pitting is found, except for staining between lands in the machined clearance areas if no scaling rust or corrosive debris is present. A follow-on spool inspection is not required unless the repetitive fluid contamination level test cited in paragraph (b) shows an increase in chlorine contamination levels. Prior to returning the actuator to service, replace shutoff valve lap assembly P/N 1303-084, Rev. C, with shutoff valve lap assembly P/N 1303-084, Rev. D. (d) Within the next 25 hours time in service from the effective date of this AD, unless already accomplished within the last 575 hours time in service, and thereafter at intervals not to exceed 600 hours time in service, replace the six NAS 1351-3H1OP cap screws that attach the gland retainers, P/N 1303-044, to the actuator manifold assembly, P/N 1303-010, on all four lower boost dual actuating cylinders, P/N's 234HS560-1 and -2, with zero time screws. Torque the new screws to a value of 30- to 35-inch-pounds (wet). (e) Within the next 25 hours time in service from the effective date of this AD, unless already accomplished within the last 25 hours time in service, and thereafter at intervals not to exceed 25 hours time in service, conduct the inspections, jam indicator button checks, leakage checks, and safety wire replacement contained in paragraphs 3A, 3B, 3C, 3D, and 3E of Boeing Vertol telex No. 8-1420-3-5455 dated May 25, 1984, or an equivalent approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York 11581. (f) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Manager, New York Aircraft Certification Office, New England Region, may adjust the compliance times specified in this AD. This amendment becomes effective August 3, 1984.
88-21-02: 88-21-02 BEECH: Amendment 39-6028. Applies to the Beech airplanes listed below, certificated in any category: TABLE 1 MODEL SERIAL NUMBER COMPLIANCE PARAGRAPH F33A CE-621 through CE-1024 (b) F33C CJ-112 through CJ-155 (b) V35B D-9830 through D-10403 (b) A36 E-632 through E-789 E-790 through E-1945 E-1947 through E-2103 E-2105 through E-2110 (a) (a)(b) (a)(b) (a)(b) A36TC, B36TC EA-2 through EA-319 EA-321 through EA-388 (a)(b) (a)(b) 95-B55, 95-B55A TC-1918 through TC-2456 (b) E-55, E-55A TE-1071 through TE-1201 (b) 58, 58A TH-579 through TH-702 TH-703 through TH-1388 TH-1390 through TH-1395 (a) (a)(b) (a)(b) 58P, 58PA TJ-12 through TJ-27 TJ-28 through TJ-435 TJ-437 through TJ-443 (a) (a)(b) (a)(b) 58TC, 58TCA TK-1, TK-2 TK-3 through TK-146 TK-148 through TK-150 (a) (a)(b) (a)(b) Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished.To prevent failure of the pilots and copilots seat attachment during an emergency landing condition, accomplish the following: (a) For the airplanes identified in Table 1 as requiring Compliance Paragraph (a): Fill the three aft seat positioning holes in the center seat tracks of the pilot and copilot seats in accordance with Beech Service Bulletin Number 2010, Revision 1, dated May 1988. The seat track reinforcement provided in Beech Service Bulletin Number 2233, dated April 1988, may be installed in lieu of filling these holes. (b) For the airplanes identified in Table 1 as requiring Compliance Paragraph (b): (1) Inspect the aft bolts on the two aft feet on both the pilot and copilot seat frame assemblies to insure that a AN960-10 washer has been installed under the nut. If a washer has been installed and the provisions of paragraph (a) have been completed, if applicable, the airplane may be returned to service. (2) If no washer is found per paragraph (b)(1) above, prior to further flight install an AN960-10 washer under the nut, on the lower aft bolt as shown in Service Bulletin No. 2010, Revision 1, dated May 1988. This applies to both the left and right hand sides of the pilot and copilot seat frame assemblies. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Rm 100, Mid-Continent Airport, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Beech Aircraft Corporation, Commercial Service, Dept. 52, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine the documents referred to herein at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Thisamendment, 39-6028, becomes effective on October 31, 1988.
90-02-01: 90-02-01 BRITISH AEROSPACE: Amendment 39-6460. Docket No. 89-NM-255-AD. Applicability: Model BAe-146 series airplanes, Serial Numbers up to and including E3125, equipped with a rear left modular toilet (BAe Modifications HCM00344A and HCM30102C), certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent damage to or jamming of the flight controls, accomplish the following: A. Within 14 days after the effective date of this AD, perform an inspection of the elevator control cables and the water pipe assembly in the vicinity of Frames 42 and 44, in accordance with British Aerospace Service Bulletin 27-A105, dated November 7, 1989. 1. If chafing or damage is found, repair and modify prior to further flight, in accordance with the service bulletin. 2. If the clearance between the water pipe assembly and the elevator control cable is not greater than 0.25 inch, modify within 60 days after the effective date of this AD, in accordance with the service bulletin. B. Repeat the procedures required by paragraph A., above, whenever a rear left-hand modular toilet is removed and reinstalled. C. An alternate means 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, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either 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 airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for ServiceBulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6460, AD 90-02-01) becomes effective on January 22, 1990.