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2016-07-27: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA341G and SA342J helicopters. This AD requires repetitive inspections of a certain part-numbered main rotor hub torsion bar (torsion bar). This AD was prompted by several cases of corrosion in the metal strands of the torsion bar. The actions of this AD are intended to detect corrosion and prevent failure of the torsion bar, loss of a main rotor blade, and subsequent loss of control of the helicopter.
2001-02-08: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA, SD3-SHERPA, SD3-30, and SD3-60 series airplanes, that requires replacement of the existing pneumatic de-icing boot pressure indicator switch with a newly designed switch. This amendment is prompted by an occurrence on a similar airplane model in which the pneumatic de-icing boot indication light may have provided the flightcrew with misleading information as to the proper functioning of the de-icing boots. The actions specified by this AD are intended to prevent ice accumulation on the airplane leading edges, which could reduce controllability of the airplane.
2001-02-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes powered by Pratt & Whitney engines, that requires modification of the nacelle strut and wing structure. The actions specified by this AD are intended to prevent fatigue cracking in primary strut structure and consequent reduced structural integrity of the strut.
86-12-03: 86-12-03 GENERAL ELECTRIC COMPANY: Amendment 39-5311. Applies to General Electric (GE) CF6- 50 and -45 turbofan engines. To prevent possible failure of high pressure turbine rotor (HPTR) stage 1 disk, accomplish the following: (a) Remove from service, in accordance with General Electric (GE) Alert Service Bulletin (SB) A72- 859, Revision 1, dated January 1, 1986, those HPTR stage 1 disks identified by specific serial numbers listed in GE Alert SB A72-859, Revision 1, under Paragraph 2., Table 1, for inspection to determine conformance with the FAA approved type design. (b) Compliance required as follows: (1) For those disks with less than 5,490 flight cycles since new on the effective date of this AD, comply prior to the accumulation of 5,500 flight cycles. (2) For those disks with 5,490 or greater flight cycles since new on the effective date of this AD, comply within the next 10 flight cycles. (c) Those HPTR stage 1 disks which do not conform to the FAA approved type design will be retired from service. (d) Those HPTR stage 1 disks which conform to the FAA approved type design may be returned to service. NOTE: For the purpose of this AD, the number of flight cycles equals the number of flights that involve an engine operating sequence consisting of engine starting, takeoff operation, landing and engine shutdown. Aircraft may be ferried in accordance with the provisions of FAR Sections 21.197 and 21.199 to a base where the AD can 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, New England Region, Federal Aviation Administration, 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 may adjust the compliance time specified in this AD. GE Alert SB A72-859, Revision 1, dated January 1, 1986, identified and described in this document, is 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 this document from the manufacturer may obtain copies upon request to General Electric Company, 1 Neumann Way, Cincinnati, Ohio 45215. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. This amendment becomes effective on June 29, 1986.
2001-02-06: This amendment supersedes an existing airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the ice protection systems and to add information regarding operation in icing conditions; installing an ice detector system; and revising the AFM to include procedures for testing system integrity. This amendment requires installing the ice detector system in accordance with revised procedures. 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 ensure that the flightcrew is able to recognize the formation of significant ice accretion and take appropriate action; such formation of ice could result in reduced controllability of the airplane in normal icing conditions.
46-23-01: 46-23-01 ERCO: (Was Mandatory Note 4 of AD-718-6.) Applies Only to 415-C, -CD and -D Aircraft Serial Numbers 113 to 362, Inclusive. To be accomplished within next 50 hours of operation. Trouble in service has indicated the necessity for replacing the original muffler on the serial numbers listed above with a new muffler, Erco P/N 145-40517. (Erco Service Department Memorandum No. 7 dated February 1, 1946, covers this same subject.)
2022-24-07: The FAA is superseding airworthiness directive (AD) 77-04-06, which applied to Messerschmitt-Bolkow-Blohm (MBB) (now Airbus Helicopters Deutschland GmbH (AHD)) Model BO-105A and BO-105 C helicopters; AD 2002-13-06, which applied to certain Eurocopter Deutschland GmbH (ECD) (now Airbus Helicopters Deutschland GmbH (AHD)) Model BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB-4, BO-105 CS-2, BO-105 CBS-2, BO-105S, and BO-105LS A-1 helicopters; AD 2016-25- 14, which applied to certain Airbus Helicopters Deutschland GmbH (AHD) Model BO-105LS A-3 helicopters; and AD 2021-10-14, which applied to certain Airbus Helicopters Deutschland GmbH (AHD) Model BO-105A, BO- 105C, BO-105S, and BO-105LS A-3 helicopters. Since the FAA issued those ADs, new and more restrictive airworthiness limitations have been issued. This AD requires incorporating into existing maintenance records requirements (airworthiness limitations) as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of certain part- numbered tension-torsion (TT) straps. The FAA is issuing this AD to address the unsafe condition on these products.
77-05-04: 77-05-04 TELEDYNE CONTINENTAL MOTORS: Amendment 39-2848. Applies to the following Teledyne Continental Motors engines installed in but not limited to: IO-520-D installed on Cessna 185 and 188 aircraft serial numbers 18502839 through 18503234, 18503236 through 18503284, 18503287, 18503291, 18503293, 18802349 through 18802887, and 18802893. IO-520-F, TSIO-520-C, TSIO-520-G, TSIO-520-M and TSIO-520-R installed on Cessna U-206, T-206, and T-207 aircraft serial numbers U20603021 through U20603693, U20603695, U20603696, U20603699, U20603712, 20700315 through 20700378. IO-520-L, TSIO-520-H, TSIO-520-R, installed on Cessna 210 and T-210 aircraft serial numbers 21061040 through 21061736, 21061738 through 21061763, 21061766, 21061771, 21061773, 21061775 through 21061777, 21061789. IO-470-L installed on Beech Model 95-B55, aircraft serial numbers TC-2003 through TC-2053. Compliance required as indicated after the effective date of this AD unless already accomplished. To prevent crankshaft failure: A. Engines with less than 100 hours total time in service accomplish the following: (1) Within the next 10 hours time in service, check propeller operation in accordance with paragraph C or E as appropriate, and thereafter at intervals not to exceed 10 hours time in service from the previous check until 100 hours total time in service has been reached, whereupon this special check may be discontinued if no problem is evident. (2) Within the next 10 hours time in service examine the oil filter or screen as appropriate for each engine in accordance with paragraph F, and thereafter at intervals not to exceed 25 hours time in service until 100 hours total time in service has been reached, whereupon this special examination may be discontinued if no problem is evident. B. Engines with 100 hours or more total time in service, perform a one-time check or inspection of the following: (1) Within the next 10 hours time in service, check propeller operationin accordance with paragraph C or E as appropriate. (2) Within the next 10 hours time in service, examine the oil filter or screen, for each engine, in accordance with paragraph F. C. Check single engine airplane propeller operation as follows: (1) Ascertain that oil temperature is at or above the middle of the green arc on the oil temperature gage but in no case above the red line. CAUTION: Do Not Exceed Maximum Cylinder Head Temperatures. (2) With the propeller control in the low-pitch high RPM position, set engine speed with the throttle to 1700 RPM. (3) At 1700 RPM, pull the propeller control to the full high-pitch low RPM position until minimum governing RPM is observed, then push the control back to the low-pitch high RPM position. Repeat this procedure three times noting minimum governing RPM each time. Using this procedure the RPM should drop at least 400 RPM and should be reasonably smooth and consistent. (4) If a minimum drop of 400 RPM is obtained consistently in Paragraph C(3), proceed with paragraph F at time intervals specified. NOTE: Propeller operation checks C(1) through C(4) may be performed by the pilot; however, requirements of C(5)(a) through C(5)(c) and Paragraph F require appropriately authorized mechanic or repair station. (5) If a minimum drop of 400 RPM cannot be obtained or the propeller operation is not smooth and consistent, the following additional checks are to be accomplished. (Reference the applicable Aircraft Service Manual.) (a) Operation of the propeller control -- check routing, control clamping, rod end attachments, control rigging and adjustment. (b) Governor operation -- check security, signs of leakage, arm attachment and stop adjustment. (c) Propeller -- check for any external signs of leakage and/or damage. D. If any discrepancies are noted when accomplishing 5(a), (b) or (c), correct condition and recheck in accordance with Paragraph C(1) through C(4). If propeller operation is not in accordance with Paragraph C(3), proceed immediately to Paragraph F and prior to further flight, contact Mr. R.J. Moore, FAA-DER SO-260, Teledyne Continental Motors, P.O. Box 90, Mobile, Alabama 36601, (205) 438-3411, or his representative for disposition or other equivalent disposition method authorized by the Chief, Engineering and Manufacturing Branch, ASO-210, P.O. Box 20636, Atlanta, Georgia 30320. E. Check multiengine airplane propeller operation as follows: NOTE: Propeller checks in paragraphs E(1) and E(2) may be conducted by the pilot. (1) Ground run the engine at 1000 RPM until some oil temperature is indicated. Increase the engine RPM to 1700 until oil temperature has stabilized at or above the middle of the green arc but in no case above the red line. CAUTION: Do not exceed maximum cylinder head temperatures. (2) Place the propeller control in the low-pitch high RPM position and set engine speed to 900 RPM using the throttle. Note any tendency of the propeller to feather after engine speed has stabilized. (3) If feathering does occur in Step (2), the following additional checks are to be accomplished. (Reference the applicable aircraft Service Manual.) (a) Operation of the propeller control -- check routing, control clamping, rod end attachments, control rigging and adjustment. (b) Governor operation -- check security, signs of leakage, arm attachment and stop adjustment. (c) Propeller -- check for any external signs of leakage and/or damage. If any discrepancies are noted in accomplishing Paragraph 3(a), (b) or (c), correct condition and recheck in accordance with Paragraph E(1) through E(2). If feathering occurs, proceed immediately to Paragraph F, and prior to further flight contact Mr. R.J. Moore, FAA-DER SO-260, Teledyne Continental Motors, P.O. Box 90, Mobile, Alabama 36601, (205) 438-3411, or his representative for disposition or other equivalent disposition method authorized by the Chief,Engineering and Manufacturing Branch, ASO-210, P.O. Box 20636, Atlanta, Georgia 30320. F. Perform the following inspections of the oil filter or screen for evidence of metal contamination. (1) Remove and cut open the oil filter or remove and inspect the screen (whichever is applicable). (2) Visually inspect for abnormal amount of metal. (3) Some small quantity of minute metal particles is considered normal; however, should an abnormal amount be present it could be indicative of bearing distress; therefore, check the magnetic properties of the metal, and prior to further flight, request disposition in accordance with Paragraph D or E as appropriate. (4) If no abnormal amount of metal is present, and propeller control checks as outline in Paragraph D or E are satisfactory, the aircraft may remain in service. NOTE: For the requirements regarding the listing of compliance and method of compliance with this AD in the airplane's permanent maintenance record, see FAR 91.173. NOTE: Teledyne Continental Motors Service Bulletin M77-6, Supplement 1, pertains to this same subject. This amendment becomes effective March 11, 1977.
83-01-01: 83-01-01 GENERAL DYNAMICS (Convair): Amendment 39-4535. Applies to Model 240, and military models eligible or to be made eligible for civil use under Type Certificate A793, and all such model airplanes converted to turbopropeller power, certificated in all categories. Compliance required as indicated unless previously accomplished. To prevent fracture of the nose landing gear (NLG) axle caused by fatigue cracks, accomplish the following. NOTE: All references to hours of time in service apply to nose landing gear axle and not to the aircraft. (A) Within 150 hours time in service after the effective date of this AD, or prior to the accumulation of 10,150 hours time in service, whichever occurs later, unless accomplished within the last 1050 hours time in service, conduct an ultrasonic inspection of each NLG axle (P/N 240- 5210005 or P/N 240-7000475) in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions," of General Dynamics Convair Division Service Bulletin 600 (24OD) 32-6 dated February 21, 1980. If cracks are found, replace with a like serviceable part prior to return of aircraft to service. (B) Repeat the ultrasonic inspection specified in paragraph (A) or perform the magnetic particle inspection specified in paragraph (C) of this AD at intervals not to exceed 1200 hours of time in service. (C) Within 12,000 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 12,000 hours time in service, conduct a magnetic particle inspection of the NLG axle (P/N 240-5210005 or P/N 240-7000475) in accordance with the applicable provisions of paragraph 2, entitled "Accomplishment Instructions" of Service Bulletin 600 (24OD) 32-6. If cracks are found, replace NLG axle with a like serviceable part prior to return of aircraft to service. (D) Prior to issuance of a Certificate of Airworthiness for military aircraft being converted for civil certification,the airplane must be inspected in accordance with paragraph (A) or (C) of this AD. (E) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. (F) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Field Office, FAA, Northwest Mountain Region, Hawthorne, California. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made 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 General Dynamics, Convair Division, P.O. Box 80877, San Diego, California 92138. These documents also may be examined at FAA, Northwest Mountain Region, 17900 PacificHighway South, Seattle, Washington, or Western Aircraft Certification Field Office, 15000 Aviation Boulevard, Hawthorne, California. This amendment becomes effective January 19, 1983.
90-10-10: 90-10-10 AVIONS MARCEL DASSAULT-BREGUET AVIATION (AMD-BA): Amendment 39-6598. Docket No. 89-NM-275-AD. Applicability: All Model Mystere Falcon 900 series airplanes equipped with thrust reverser synchronizing bell crank, Part Number F900HD3200240A2, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of the thrust reverser door actuating system, accomplish the following: A. Prior to the accumulation of 3,000 landings on the thrust reverser synchronizing bell crank, Part Number F900HD3200240A2, or within the next 250 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 3,000 landings, replace the bell crank, which is life limited to 3,000 landings, in accordance with the manufacturer's maintenance manual. B. 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. C. 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 documents from the manufacturer may obtain copies upon request to Falcon Jet Corporation, Customer Support Department, Teterboro Airport, Teterboro, New Jersey 07608. These documents 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 (39-6598, AD 90-10-10) becomes effective on June 15, 1990.