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77-13-20: 77-13-20 ROLLS ROYCE (1971), LTD: Amendment 39-2945. Applies to Bristol Viper MK. 522 and MK. 601-22 engines installed, or being held for installation, on Hawker Siddeley Model DH/BH-125 series airplanes, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent interference between the engine throttle control rod and the high pressure fuel shutoff valve that could result in inability to actuate fuel shutoff, accomplish the following: (a) For installed engines, within the next 500 hours engine time in service after the effective date of this AD, accomplish the following in accordance with paragraph 2.A of Rolls Royce Alert Service Bulletin 73-A98 (MK. 522 engines) or 73-A13 (MK. 601-22 engines), both dated October 1975, or an FAA-approved equivalent: (1) Relocate the ident/data tags fitted to the fuel tube, P/N DF-21-389. (2) Check for adequate clearance between the fuel tube, P/N DF-21-389, and the H.P.cock control rod, P/N 25CX53-25A. (3) If the clearance is found not to be adequate during the inspection specified in paragraph (a)(2) of this paragraph, realign the fuel tube to provide adequate clearance. (b) For other engines, prior to installation on a Model DH/BH-125 airplane, ascertain the location of the ident/data tags on fuel tube P/N DF-21-389 and if it is found to be within 8 inches or less of the union nut, at the b.f.c.u. connection, remove the tags and refit to a lower position on the tube in accordance with the instructions contained in paragraph 2.B of Rolls Royce Alert Service Bulletin 73-A98 (MK. 522 engines) or 73-A13 (MK. 601-22 engines), both dated October 1975, or an FAA-approved equivalent. NOTE: The accomplishment instructions contained in Rolls Royce Alert Service Bulletins 73-A13 and 73- A98 are identical. This amendment becomes effective on August 1, 1977.
2020-06-15: The FAA is adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F28 Mark 0100 airplanes. This AD was prompted by a report of a crack found in the inboard boom of the left- hand frame at fuselage station (STA) 17011. This AD requires a detailed inspection of the fuselage at STA 17011 for any cracking, repair if necessary, and a reporting requirement, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
80-15-13: 80-15-13 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 3856. Applies to Model AS 350 series helicopters, certificated in all categories, which have main rotor assembly, P/N 350A.37.0003, serial numbers M1 through M146 installed. Compliance required as indicated. To rectify incorrect installation of the rotating star drive adapter which could result in vibration and premature wear of the rotating star bolts, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD, unless already accomplished: (1) Measure the dimension between the spacer and the upper face of the rotating drive adapter, P/N 350A.36.1119, at locations no more than 120 degrees apart using a fixed length block and a feeler gage. (2) Compare the measurements. (b) If the measurement comparison required in paragraph (a)(2) of this AD reveals a variation of 0.039 inches (1 mm) or less, return to service and comply with paragraph(d) of this AD. (c) If the comparison required in paragraph (a)(2) of this AD reveals a variation in excess of 0.039 inches (1 mm), reposition the rotating star drive adapter perpendicular to the drive shaft in accordance with sub-paragraph 2. of paragraph C, "DESCRIPTION," of Aerospatiale (SNIAS) Service Bulletin No. 65.01, dated October 20, 1978, or an FAA-approved equivalent. NOTE: The AS 350 Maintenance Manual Work Card No. 65.13.603 pertains to this same subject. (d) Following any maintenance action on the rotating star drive adapter bolt, comply with paragraph (a)(1), (a)(2), and paragraph (b) or (c) of this AD. (e) For a rotor assembly with a serial number M1 through M146, held as spare, comply with this AD at installation and release to service. (f) For purposes of this AD, an FAA-approved equivalent may be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium.This amendment becomes effective August 7, 1980.
76-20-02: 76-20-02 PRATT & WHITNEY AIRCRAFT: Amendment 39-2734. Applies to all Pratt & Whitney Aircraft JT8D-1, -1A, -1B, -7, -7A, and -7B engines. Compliance required prior to June 30, 1978, unless already accomplished. To preclude liberation of second stage fan blades: A. Inspect the blade retaining strap for taper wear in accordance with Section 72-33-1 of Pratt & Whitney Aircraft JT8D Series Engine Manual P/N 481672, Revision 78, or later FAA approved revision or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. Remove from service, second stage fan blades with taper wear in excess of .0025 inch before further flight. B. Install second stage fan blade bumper, P/N 642409, in accordance with Pratt & Whitney Aircraft Service Bulletin 2406 or later FAA approved revision or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance date in this 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. The manufacturer's service bulletins identified and described 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 documents from the manufacturer may obtain copies upon request to Pratt & Whitney Aircraft, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. Ahistorical 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 on October 10, 1976.
98-25-53: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) T98-25-53 that was sent to all known U.S. owners and operators of all Airbus Model A300 B4-600R and A300 F4-600R series airplanes by individual telegrams. This AD requires a one-time visual inspection for damage of the center fuel pumps and fuel pump canisters, and replacement of damaged fuel pumps and fuel pump canisters with new or serviceable parts. This action is prompted by reports of damaged center tank fuel pump canisters and damaged center tank fuel pumps. The actions specified by this AD are intended to detect damage to the fuel pump and fuel pump canister, which could result in loss of flame trap capability and could provide a fuel ignition source in the center fuel tank.
73-07-04: 73-07-04 BENDIX ELECTRICAL COMPONENTS DIVISION: Amdt. 39-1611 as amended by Amendment 39-1731. Applies to all Bendix Electrical Components Division of the Bendix Corp. (Bendix Scintilla) S4LN or S4RN, S6LN or S6RN and S8LN or S8RN magnetos with series numbers -20 through -26, -200 through -206, -600 through -604 and -1200 through -1227 except the following. 1. Magnetos identified with the Bendix Blue name plate (Bendix remanufactured magnetos) having serial No. 231001 or higher. 2. Magnetos identified with the Bendix Red name plate (new magnetos) having a serial number with the prefix "A" and No. 16058 or higher. Compliance required as indicated after the effective date of this AD unless previously accomplished. To prevent failure of these magnetos due to malfunction or failure of the ignition coil or rotating magnet, accomplish the following: a. On magnetos having 1,800 or less hours in service since new or last overhaul on the effective date of this AD, accomplish paragraph "d" before accumulation of 2,000 hours in service. b. On magnetos having more than 1,800 hours in service since new or last overhaul, accomplish paragraph "d" within the next 200 hours service after the effective date of this AD. c. Magnetos whose time in service since new or last overhaul is unknown will be assumed to have a total of 1,800 hours minimum and thus fall within the requirements of paragraph (b). d. Identify magnetos per instructions contained in Bendix Electrical Components Division Service Bulletin No. 560, dated August 1972 or later. Magnetos having ignition coils as described in paragraph A, or rotating magnets as described in paragraph B or shown in figure 2 of Bendix Electrical Components Division's Service Bulletin No. 560, dated August 1972 or later, must have these components removed and replaced with serviceable parts as listed in the applicable Bendix Electrical Components Division Service Parts List, numbered and dated as follows or subsequent: Magneto Model Parts List Designation Parts List Date S4LN-20 series (ignition coil no. 10-160886 or subsequent). L-227-9 December 1963 S6LN-20 series (ignition coil no. 10-160886 or subsequent). L-223-11 October 1963 S-200 series (ignition coil no. 10-160887 or subsequent). L-528-3 October 1963 S-600 series (magnet rotor only) L-552-3 December 1964 S-1200 series (ignition coil only) L-608-3 September 1971 e. Upon completion of paragraph d, identify each magneto as follows: S-20, S-200, and S-600 series magnetos - Metal stamp .010 deep maximum the letter "A" 3/16 inches high, midway and centered between the timing plug boss and the curved surface at the rear of distributor housing. S-1200 series magnetos - Metal stamp .010 deep maximum the letter "A" 3/16 inches high, centered between the timing plug boss and data plate, adjacent to the magneto housing rib. Amendment 39-1611 became effective April 2, 1973. This amendment 39-1731 becomes effective October 11, 1973.
80-14-02: 80-14-02 PIPER AIRCRAFT CORPORATION: Amendment 39-3819. Applies to Model PA-28-181, serial numbers 28-7790032 through 28-8090227; Model PA-32-300, serial numbers 32-7640001 through 32-7740032 and Model PA-32R-300, serial numbers 32R-7680001 through 32R-7780148 airplanes certificated in all categories. Compliance required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent separation of the throttle control cable rod end from the throttle arm on the affected Models PA-28 and PA-32 airplanes, and rod end binding with possible subsequent throttle cable failure on the affected Model PA-28 airplanes, accomplished the following. (a) For the Model PA-32-300 and PA-32R-300 series airplanes, replace the throttle linkage connecting hardware in accordance with the instructions contained in Piper Service Bulletin No. 537, dated January 12, 1977. (b) For the Model PA-28-181 airplanes, modify the throttle linkage in accordance with the instructions listed in the "Throttle Linkage Modification Kit," Piper Part Number 764- 009V. NOTE: Piper Service Bulletin No. 679 pertains to this subject. (c) Make an appropriate maintenance record entry. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. This amendment is effective July 10, 1980.
78-10-02: 78-10-02 SHORT BROTHERS LIMITED (Formerly Short Brothers & 78-10-02 Short Harland, Ltd.): Amendment 39-3213. Applies to Model SD3-30 airplanes, Serial Nos. SH3004 to SH3013 inclusive, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent unwanted propeller feathering, accomplish the following: (a) Within the next 50 hours time in service after the effective date of this AD, visually inspect the electrical wiring between the proximity switch and the main cable loom for chafing, contact with engine case, and for security of clamping. (b) If, during the inspection required by paragraph (a), chafing, loose clamps, or contact with engine is found, before further flight, except that the airplane may be flown in accordance with the provisions of FAR 21.197 and 21.199 to a base where the modifications required by this AD may be accomplished, correct the fault in accordance with paragraph 1.C.3. of Short Brothers Limited Service Bulletin No. SD3-61-A03, dated December 21, 1977, or an FAA-approved equivalent. (c) Within 500 hours time in service after the effective date of this AD, accomplish Short Brothers Limited Modification No. 5471 in accordance with Shorts Service Bulletin No. SD3-61-03, dated January 19, 1978 (pages 1 through 4 are dated January 19, 1977) or an FAA- approved equivalent. (d) Record the accomplishment of the AD in accordance with FAR 91.173. (e) Equivalent methods of compliance with this AD or adjustment of the inspection intervals required by this AD may be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, APO New York, 09667, if the request is submitted through an FAA Maintenance Inspector and contains substantiating data to justify the interval or method of compliance for that operator. This amendment becomes effective May 29, 1978.
74-08-03: 74-08-03 BELL: Amendment 39-1806. Applies to Bell Model 212 helicopters, S/N 30504 through 30593, certificated in all categories. Compliance required as indicated. To detect and prevent possible cracks in the tail fin forward spar cap angle and in the tail boom skin adjacent to the fin, accomplish the following repetitive inspections and modification. (a) Within 25 hours time in service after the effective date of this A.D. and thereafter at intervals not to exceed 25 hours time in service from the last inspection, accomplish the following inspections until the modification of paragraph (b) is completed. (1) Remove the 42 degree gear box cover from the tail boom. (2) Remove the first rivet above the tail boom on the left side of the vertical fin forward spar cap angle. Remove the paint finish and clean the area around the rivet hole (inboard and outboard sides of the spar cap angle), using cloth and Methyl Ethyl Ketone or equivalent. Do not reinstall thefirst rivet. (3) Inspect the rivet hole and clear area of the spar for cracks using a three power or higher magnifying glass or a dye penetrant or equivalent inspection method. (4) If no cracks are found, protect the clear area of the spar and rivet hole using a clear lacquer or light film of clear grease or equivalent transparent protection and install the gear box cover. (5) If cracks are found, remove the tail boom and replace with an uncracked tail boom in accordance with the procedures specified in the Bell Model 212 maintenance manual. (b) Within 100 hours time in service after the effective date of this A.D., modify the tail fin and tail boom in accordance with Part III, Bell Helicopter Co., Service Bulletin No. 212- 01-73-1, Rev. B, dated October 9, 1973 or later FAA approved revision. The manufacturer's specifications and procedures identified and described 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 documents from the manufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Company, P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S. W., Washington, D.C. A historical file on this A.D. which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective May 6, 1974.
2020-07-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-271N airplanes and Model A321-271N, - 271NX, and -272N airplanes. This AD was prompted by a report of a gap found on an engine pylon nose fire seal during an inspection of an in- production airplane. This AD requires a one-time detailed inspection of certain engine pylon nose fire seals for correct installation, and applicable corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
98-12-27: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires repetitive magnetic particle inspections to detect cracking of the splined operating shaft of the internal door handle on the forward passenger door, rear passenger door, and rear baggage door; and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking of the splined operating shaft of the internal door handle, which could result in failure of the internal door handle, inability to operate the door during an emergency evacuation, and consequent injury to airplane occupants.
90-09-11: 90-09-11 BOEING: Amendment 39-6588. Docket No. 90-NM-05-AD. \n\n\tApplicability: Model 737-300 and -400 series airplanes, equipped with Air Cruisers Company forward door evacuation slides identified in paragraph 1A of Air Cruisers Service Bulletin 103-25-17, dated November 10, 1989, certificated in any category. \n\n\tCompliance: Required within 3 years after the effective date of this AD, unless previously accomplished. \n\n\tTo assure that forward door evacuation slides will automatically inflate when needed, accomplish the following: \n\n\tA.\tModify affected slides by installing a frangible link in accordance with Air Cruisers Service Bulletin 103-25-17, dated November 10, 1989. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA PrincipalMaintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Air Cruisers Company, P.O. Box 180, Belmar, New Jersey, 07719-0180. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6588, AD 90-09-11) becomes effective on June 4, 1990.
2020-06-13: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD requires determining the accumulated hours time- in-service (TIS) of certain part-numbered main gearbox (MGB) suspension bar attachment fittings (fittings) and bolts, and establishes new life limits. This AD was prompted by the outcome of tests and analyses performed by Airbus Helicopters. The actions of this AD are intended to address an unsafe condition on these products.
76-10-03: 76-10-03 HAWKER SIDDELEY AVIATION LIMITED: Amendment 39-2614. Applies to Model DH-104 airplanes, certificated in all categories not altered in accordance with Hawker Siddeley Aviation Ltd. Modification 1067. Compliance is required as indicated, unless already accomplished. To detect corrosion and cracking of the drag brace fittings at the center section spar lower cap, and prevent possible structural failure of the wing, accomplish the following: (a) Within the next 50 hours time in service after the effective date of this AD, inspect the drag brace fittings, P/N 4FS.1797(L.H.) and 4FS.1798(R.H.) for corrosion and cracks in accordance with paragraph No. 4, entitled "Inspection of Fittings," of Hawker Siddeley Aviation Ltd. Technical News Sheet, Series CT104, No. 230, dated April 9, 1973, or an FAA- approved equivalent. (b) If a crack or evidence of severe corrosion is found in either drag brace fitting, during an inspection specified in paragraph (a) of this AD, before further flight, replace the drag brace fitting with an improved fitting, P/N 14FS.6069-70, in accordance with the instructions set forth in paragraph 5.2 of Hawker Siddeley Aviation Ltd. Technical News Sheet, Series CT104, No. 230, dated April 9, 1973, or an FAA-approved equivalent. (c) "Severe corrosion" as used in this AD is internal corrosion that has progressed to a point where there is evidence of corrosion breaking through the exterior surface of the fitting. "Surface corrosion" as used in this AD means corrosion limited to surface pitting. NOTE: The Hawker Siddeley Aviation Ltd. Model DH-104 Maintenance and Repair Manual further defines the terms "severe corrosion" and "surface corrosion." (d) If, during an inspection specified in paragraph (a) of this AD, no crack is found and evidence of corrosion is found but it is limited to surface corrosion and does not constitute the severe corrosion specified in paragraph (b) of this AD, remove the corrosion, protectthe surface from further corrosion in accordance with FAR 43.13, and re-inspect the drag brace fittings in accordance with the inspection requirements of paragraph (a) of this AD, at intervals not to exceed 100 hours time in service from the last inspection. NOTE: Advisory Circular AC 43.13-1A "Acceptable Methods, Techniques and Practices-Aircraft Inspection and Repair" contains information relating to corrosion protection and removal. (e) If, during an inspection specified in paragraph (a) of this AD, no crack is found in the fittings, and the fittings are free of evidence of any corrosion, re-inspect the fittings in accordance with the inspection requirements of paragraph (a) of this AD at intervals not to exceed 100 hours time in service from the last inspection. (f) The repetitive inspections required by paragraphs (d) and (e) of this AD may be terminated upon the installation of the improved fitting P/N 14FS.6069-70, in accordance with the instructions set forth in paragraph 5.2 of Hawker Siddeley Aviation Ltd. Technical News Sheet, Series CT104, No. 230, dated April 9, 1973, or an FAA-approved equivalent. This amendment becomes effective June 1, 1976.
78-24-02: 78-24-02 COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA: Amendment 39- 3346. Applies to Agusta Model A109 Series helicopters, S/N 7107, 7111, 7126, and 7129, certificated in all categories. Compliance required before further flight, unless already accomplished, but helicopter may be flown in accordance with FAR 21.197 and 21.199 to a base where the required work can be performed. To prevent possible failure of main transmission P/N 109-0400-02-01, remove pinion gear P/N 109- 0403-06-01, S/N 18, 24, 25 or 27, from main transmissions S/N 31, 36, 11 and 10, respectively, and replace with new pinion gear of same part number having serial number other than 17 through 32. This amendment is effective November 24, 1978, as to all persons except those persons to whom it was made immediately effective by the letter dated April 26, 1978, which contained this amendment
2020-06-18: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a recent maintenance repair organization's report to Airbus of deviations from the component maintenance manual acceptance test procedure for certain trimmable horizontal stabilizer actuators (THSAs). This AD requires replacement of affected THSAs with serviceable THSAs, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2008-17-14: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 727 series airplanes. That AD currently requires repetitive inspections to detect cracks and loose brackets of the elevator rear spar, and corrective actions if necessary. The existing AD also provides for an optional terminating action for the repetitive inspections. This new AD reduces the repetitive intervals of the inspections, mandates the previously optional terminating action for the repetitive inspections, and no longer allows stop-drilling. This AD results from new reports of cracks, elongated fastener holes, and loose fittings of the elevator rear spar. We are issuing this AD to prevent cracking of the elevator rear spar at the tab hinge locations, which could cause excessive freeplay of the elevator control tab and possible tab flutter, and consequent loss of control of the airplane. \n\nDATES: This AD becomes effective October 2, 2008. \n\tThe Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of October 2, 2008. \n\tOn April 22, 1996 (61 FR 11529, March 21, 1996), the Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 727-55-0089, dated June 29, 1995.
76-17-06: 76-17-06 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-2705. Applies to Model DH/BH-125 airplanes Series 400A, S/N NA-711 through NA-758 and all Model DH/BH-125 airplanes Series 1A, 1A-522, 1A/S-522, 3A, 3AR, 3ARA, certificated in all categories. Compliance is required within the next 200 hours time in service after the effective date of this AD, unless already accomplished. To prevent possible unwanted deployment of airbrakes inflight, accomplish the following: a) For all aircraft except those altered to include airbrake servodynes P/N AIR 46520/0 and 46521/0 in accordance with the Part D Supplement of Hawker Siddeley Aviation Ltd., Modification 252174, Service Bulletin SB 27-86-(2174), dated March 29, 1972, modify the airbrake servodynes, P/N AIR 45398 and 45399, in accordance with Part A of the section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation Ltd., Service Bulletin 27-86-(2174), Revision 4, dated March 29, 1972, or an FAA-approved equivalent. b) For all aircraft, modify the airbrake operating circuit (R/H and L/H) in accordance with Part C of the section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation, Ltd., Service Bulletin 27-86-(2174), Revision 4, dated March 29, 1972, or an FAA-approved equivalent. This amendment becomes effective September 27, 1976.
96-21-02: 96-21-02 BOMBARDIER, INC. (Formerly Canadair): Amendment 39-9778. Docket 96-NM-246-AD. Applicability: Model CL-600-2B19 (Regional Jet Series 100) series airplanes; having serial numbers 7003 and subsequent; certificated in any category. 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 (b) 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, unless accomplished previously. To prevent uncommanded changes in the settings of the barometric altimeter, altitude pre-selector, V-speed, and speed bug on the co-pilot s instrument display, which could result in confusion among the flight crew about the correct position and flight configuration of the airplane, accomplish the following: (a) Within 3 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following statement. This may be accomplished by inserting a copy of this AD in the AFM. "Prior to each takeoff and after any event during which generators are switched, check the settings of the barometric altimeter, altitude pre-selector, V-speed, and speed bug. If any discrepancy is detected, reset, as necessary." (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (c) 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. (d) This amendment becomes effective on October 15, 1996.
90-02-23 PL: 90-02-23 HARTZELL PROPELLER, INC.: Priority Letter AD issued January 22, 1990. Applies only to Hartzell propellers listed in the hub model/serial number list below and installed on Acrobatic Aircraft (regardless of engine type) or installed on any aircraft with Lycoming TIO-540 series engines and IO-540 series engines rated at 260 horsepower or higher certificated in any category including, but not limited to: Bellanca 8KCAB and 17-31A Britten Norman Islander BN-2A-2, BN-2A-3, BN-2A-20, BN-2A-21 British Aerospace Bulldog B125 (Formerly Scottish Aviation) Christen Pitts S-1T, S-2, S-2A, S-2S, S-2B Great Lakes 2T-1A-1, 2T-1A-2 Moravan Zlin 526L Piper Cherokee Six, Saratoga, Lance PA-32(R,T)-300(T), PA-32S-300, PA-32(R)-301(T) Socata TB30 Applicability for Propeller Models is as follows: PROPELLER MODELS PROPELLER SERIAL NUMBER RANGE HC-C2YK-1B() or CH19835 through CH26050 HC-C2YR-1B() HC-C2YK-2() or AU4322 through AU7032 HC-C2YR-2() HC-C2YK-4() or ALL HC-C2YR-4() HC-E2YK-1B() or DK1018 through DK1685 HC-E2YR-1B() Compliance is required within the next 25 hours time-in-service after receipt of this Priority Letter AD, unless already accomplished within the last 25 hours time-in-service and, thereafter, at intervals not to exceed 50 hours time-in-service or 50 flights from the last inspection, whichever occurs first. To prevent possible cracks in the propeller hubs from progressing to failure which can result in blade separation and lead to possible engine separation and subsequent loss of aircraft control, accomplish the following: (a) Visually inspect the affected propeller hub for cracks using a 10X glass in accordance with Hartzell Service Bulletin (SB) No. 164, dated October 3, 1989. (b) If any indication of a crack is found, prior to further flight, remove the propeller assembly and replace with a serviceable propeller assembly. (c) Report cracks found in writing tothe Manager, Chicago Aircraft Certification Office, within 10 days of the inspection. Reporting approved by the Office of Management and Budget (OMB) under OMB No. 2120-0056. (d) Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FAR) 21.197 and 21.199 to a location where compliance with the AD can be accomplished. (e) Upon submission of substantiating data in writing by an owner or operator, through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this Priority Letter AD or adjustments to the compliance time specified in this Priority Letter AD may be approved by the Manager, Chicago Aircraft Certification Office, Small Airplane Certification Directorate, Aircraft Certification Service, Federal Aviation Administration, 2300 East Devon Avenue, Des Plaines, Illinois 60018. Documents pertinent to this Priority Letter AD may be obtained from Hartzell Propeller, Inc., One Propeller Place, Piqua, Ohio 45356, or may be examined at the Office of Assistant Chief Counsel, Federal Aviation Administration, ATTN: Rules Docket No. 89-ANE-44, 12 New England Executive Park, Burlington, Massachusetts 01803. Priority Letter AD 90-02-23 issued on January 22, 1990, is effective immediately upon receipt.
55-09-02: 55-09-02 CURTISS-WRIGHT: Applies to all C-46 Series aircraft. Compliance required as indicated. (1) For Models C-46A and C-46D. At each 3,000 hours of operation inspect visually and at each major overhaul inspect by means of Zyglo or equivalent method control column base assemblies P/N 20-530- 3076-5, arm assemblies P/N 20-530-1049-1 and -3, terminal assemblies P/N 20-530-1286-1 and - 3, and upper terminal assemblies P/N 20-530-1059. Also inspect for cracks around the rivets which retain the assemblies to the torque tube P/N 20-530-1163-2. (2) For Models C-46E and C-46F. Due to recent similar failures reported on these models, the assemblies corresponding to the above Model C-46A and C-46D assemblies must be similarly inspected. All defective parts must be replaced. This supersedes AD 51-14-2.
78-01-05: 78-01-05 De HAVILLAND: Amendment 39-3111. Applies to de Havilland of Canada DHC-6 series aircraft serial numbers 1 through 530. Compliance required within 800 hours in service after the effective date of this AD unless already accomplished, or de Havilland Modification 6/1591 is incorporated. To preclude the possibility of total electrical failure due to contact welding of the reverse current relay and subsequent burning of the adjacent wiring, the other reverse current relay and the battery circuit wiring, install de Havilland modification 6/1598 in accordance with de Havilland Service Bulletin No. 6/353 dated May 13, 1977, or later revision, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective February 9, 1978.
2020-04-16: The FAA is adopting a new airworthiness directive (AD) for certain Yabor(atilde) Ind(uacute)stria Aeron(aacute)utica S.A. Model ERJ 190-100 STD, -100 LR, -100 IGW, -200 STD, -200 LR, and -200 IGW airplanes. This AD was prompted by reports of structural cracks in the wing lower skin stringers on both half wings. This AD requires repetitive inspections for cracking and fuel leakage of the lower skin stringers on both half wings, and applicable related investigative and corrective actions, as specified in an Ag(ecirc)ncia Nacional de Avia(ccedil)(atilde)o Civil National Civil Aviation Agency (ANAC) Brazilian AD, which is incorporated by reference. This AD also provides optional terminating action for the repetitive inspections. The FAA is issuing this AD to address the unsafe condition on these products.
80-09-02: 80-09-02 BRITISH AEROSPACE/SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39-3755. Applies to all Concorde Type I airplanes, certificated in any category. To prevent unwanted deviation from the flight path, accomplish the following: (a) Prior to the next flight after the effective date of this AD, unless already accomplished, remove electrical pitch trim computers 1C151 or 2C151 and install in their place modified electrical pitch trim computers, P/N 49-004.071C51 or P/N 49-004.072C151, as appropriate, in accordance with Concorde Campaign Wire 22CW019, issue 2, dated March 27, 1979, or an equivalent approved by the Chief, Aircraft Certification Staff, Federal Aviation Administration, Europe, Africa, and Middle East Region, c/o American Embassy, Brussels, Belgium. NOTE: Concorde service bulletin 22A019 (Mod. 1669) also concerns the installation of the modified electrical pitch trim computers. This supersedes telegraphic airworthiness directive datedApril 6, 1979. This amendment becomes effective April 14, 1980.
87-12-05: 87-12-05 AVCO LYCOMING: Amendment 39-5640. Applies to Avco Lycoming T5313B turboshaft engines. Compliance is required as indicated, unless already accomplished. To prevent an uncontained engine failure, remove gas producer turbine (GPT) and power turbine (PT) disks and spacers from service, and replace with serviceable parts, in accordance with the following schedules: (a) GPT disk, Part Number (P/N) 1-100-133-01: (1) Within the next 250 hours in service (HIS) or 100 cycles in service (CIS) after the effective date of this AD, whichever occurs first, for those disks that have accumulated a total service life in excess of 24,750 HIS or 9,900 CIS since new on the effective date of this AD. (2) Prior to accumulating 25,000 HIS or 10,000 CIS since new, whichever occurs first, for those disks that have accumulated a total service life equal to or less than 24,750 HIS or 9,900 CIS since new on the effective date of this AD. (b) PT disk, P/N 1-140-272-01: (1) Withinthe next 100 HIS or 50 CIS after the effective date of this AD, whichever occurs first, for those disks that have accumulated a total service life in excess of 9,000 HIS or 4,550 CIS since new on the effective date of this AD. (2) Prior to accumulating 9,100 HIS or 4,600 CIS since new, whichever occurs first, for those disks that have accumulated a total service life equal to or less than 9,000 HIS or 4,550 CIS since new on the effective date of this AD. (c) GPT spacer, P/N 1-100-294-03: (1) Within the next 250 HIS or CIS, after the effective date of this AD, whichever occurs first, for those spacers that have accumulated a total service life in excess of 24,750 HIS or CIS since new on the effective date of this AD. (2) Within the next 12,500 HIS or CIS, after the effective date of this AD, whichever occurs first, for those spacers on which the total service life is not known on the effective date of this AD. (3) Prior to accumulating 25,000 HIS or CIS since new, whichever occurs first, for those spacers that have accumulated a total service life equal to or less than 24,750 HIS or CIS since new on the effective date of this AD. (d) PT spacer, P/N 1-140-169-03: (1) Within the next 250 HIS or 100 CIS, after the effective date of this AD, whichever occurs first, for those spacers that have accumulated a total service life in excess of 24,750 HIS or 9,900 CIS since new on the effective date of this AD. (2) At the next PT second stage disk removal, after the effective date of this AD, for those spacers on which the service life is not known on the effective date of this AD. (3) Prior to accumulating 25,000 HIS or 10,000 CIS since new, whichever occurs first, for those spacers that have accumulated a total service life equal to or less than 24,750 HIS or 9,900 CIS since new on the effective date of this AD. (e) PT spacer, P/N 1-140-169-04: (1) Within the next 250 HIS or CIS after the effective date of this AD, whichever occurs first, for those spacers that have accumulated a total service life in excess of 24,750 HIS or CIS since new on the effective date of this AD. (2) Within the next 12,500 HIS or CIS after the effective date of this AD, whichever occurs first, for those spacers on which the total service life is not known on the effective date of this AD. (3) Prior to accumulating 25,000 HIS or CIS since new, whichever occurs first, for those spacers that have accumulated a total service life equal to or less than 24,750 HIS or CIS since new on the effective date of this AD. NOTE: Avco Lycoming Service Bulletin Number 0020, Revision 2, dated January 3, 1986, reflects the new lives specified in this AD, and provides instruction for computing and recording part life. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD may be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance times specified in this AD. This amendment becomes effective on July 20, 1987.