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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.