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86-16-10: 86-16-10 CANADAIR: Amendment 39-5378. Applies to all Canadair CL-44D4 and CL-44J airplanes certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent failure of the aft attachment lugs on the main landing gear upper forging, P/N 44-87573-2, accomplish the following, unless already accomplished. A. Within the next 30 days after the effective date of this Airworthiness Directive (AD), and at intervals thereafter not to exceed 2000 hours time-in-service or one year, whichever occurs first: 1. Remove the parts shown in Figure 1 of Canadair Service Information Circular (SIC) No. 419-CL44, dated May 18, 1978, from both main landing gear legs: jack attach bracket assemblies, P/N 44-87593; spacers, P/N 44-87639; pins, P/N 44-87725-2; attaching parts, and bushings, P/N 44-87624-2, if necessary. 2. Inspect the bore of the upper and lower jack attachment lugs of the left and right main gear leg upper forgings, P/N 44-87573-2, for cracks, using fluorescent penetrant procedures. 3. Replace cracked parts, prior to further flight, with serviceable parts of the same part number which have been inspected in accordance with the requirements of this AD. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. C. 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 the inspections and replacement of parts required by this AD. D. Upon the request of an operator, an FAA Maintenance Inspector, subject to approval by the Manager, New York Aircraft Certification Office, FAA, New England Region, may adjust the inspection times specified in this AD to permit compliance at an established inspection period of that operator if the request contains substantiating data to justify the change for that operator. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Canadair Limited, Commercial Aircraft Technical Services, Box 6087, Station A, Montreal, Quebec H3C 3G9, Canada. These documents may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York. This Amendment becomes effective September 8, 1986.
69-23-04: 69-23-04 DOWTY ROTOL: Amdt. 39-872. Applies to the following Dowty Rotol propellers with propeller cylinder P/N's RA 44133/1 or RA 44709 or RA 62807 or RA 67888, except propeller cylinders modified by Modification No. (c) VP.2422: (c) R.130/4-20 - 4/12E installed on Vickers Viscount Model 745D aircraft; (c) R.148/4-20 - 4/21E on Viscount Model 744 aircraft; (c) R.186/4-30 - 4/16 on Hawker Siddeley Argosy AW-650 aircraft; and (c) R.175/4-30 - 4/13E on Fairchild F.27 and F.27B aircraft. Compliance is required as indicated, unless already accomplished. To prevent failure of propeller cylinders, at the next scheduled propeller overhaul after the effective date of this AD, or before the cylinder accumulates 6,000 hours total time in service, whichever occurs later, incorporate Dowty Rotol Modification No. (c) VP.2480 in accordance with Dowty Rotol Service Bulletin No. 61-564, Revision 4, dated December, 1968, or later ARB- approved issue, or FAA-approved equivalent. Thisamendment becomes effective December 11, 1969.
2010-01-06: We are superseding an existing 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: There has been one case reported of failure of a shaft (tailstock) on an elevator Power Control Unit (PCU), Part Number (P/ N) 390600-1007. Continued actuation of the affected PCU caused damage to the surrounding structure. * * * Each elevator surface has three PCUs, powered by separate independent hydraulic systems, and a single elevator PCU shaft failure may remain dormant. Such a dormant loss of redundancy, coupled with the potential for a failed shaft to produce collateral damage, including damage to hydraulic lines, could possibly affect the controllability of the aircraft. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
91-24-02: 91-24-02 TURBOMECA: Amendment 39-8087, Docket No. 91-ANE-35. Applicability: Turbomeca Arriel 1B, 1D, Arriel 1D, and Arriel 1D1 turboshaft engines, installed on but not limited to, Aerospatiale AS350 Ecureuil aircraft. Compliance: Required as indicated, unless already accomplished. To prevent free wheel clutch failure and the inability to transmit power from the engine to the main rotor drive shaft, accomplish the following: (a) For engines that have not incorporated the modifications contained in either Turbomeca Service Document 72.292.0140 (Modification TU 211), dated June 14, 1990, or Turbomeca Service Document 72.292.0141 (Modification TU 212), dated July 13, 1990, and have a free wheel assembly serial number (S/N) of 793 or higher; or a S/N less than 793 and have had a maintenance action performed on the free wheel assembly, accomplish the following: (1) Install a free wheel clutch in accordance with Turbomeca Service Document 72.292.0141 (Modification TU 212),dated July 13, 1990, within 20 days from the effective date of this AD. (2) Install a free wheel shaft in accordance with Turbomeca Service Bulletin 292.72.0146 (Modification TU 221), dated May 8, 1991, within 20 days from the effective date of this AD. (3) Engines equipped with free wheel assemblies having a S/N lower than 793, that have not had a maintenance action performed on the free wheel assembly, are not required to incorporate the above modifications. NOTE: Information regarding free wheel clutch assembly S/N and free wheel clutch repair history may be found on the equipment Log Card and in the engine logbook. (b) For engines that have incorporated the modifications contained in Turbomeca Service Document 72.292.0140 (Modification TU 211), dated June 14, 1990, comply with paragraphs (b)(1) and (b)(2) of this AD. For engines that have incorporated Turbomeca Service Document 72.292.0141 (Modification TU 212), dated July 13, 1991, comply with paragraph (b)(2) only,as follows: (1) Install a free wheel clutch in accordance with the requirements of Turbomeca Service Document 72.292.0141 (Modification TU 212), dated July 13, 1990, at next shop visit or by March 31, 1992, whichever occurs first. (2) Install a free wheel shaft in accordance with the requirements of Turbomeca Service Bulletin 292.72.0146 (Modification TU 221), dated May 8, 1991, at next shop visit or by March 31, 1992, whichever occurs first. (c) For the purpose of this AD, a shop visit is defined as exposure of the free wheel assembly at a shop capable of performing the modification. (d) For the purpose of this AD, maintenance action is defined as any maintenance performed on any free wheel assembly component. (e) 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. (f) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate), an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, Massachusetts. (g) The modification shall be done in accordance with the following Turbomeca service documents: DOCUMENT NO. PAGE NO. DATE 292.72.0146 1-7 August 5, 1991 Total Pages: 7 72.292.0141 1-4 July 13, 1990 Total Pages: 4 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 Turbomeca, Technical Publications Department, 64511 Bordes Cedex, France. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts, or atthe Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. This amendment (39-8087, AD 91-24-02) becomes effective on February 21, 1992.
83-22-04: 83-22-04 AVCO LYCOMING: Amendment 39-4748. Applies to all Avco Lycoming IO-540-G1B5, -G1C5, -G1D5, -K1A5, -K1A5D, -K1B5, -K1C5, -K1D5, -K1F5, -K1F5D, -K1G5, -K1G5D, -K1J5, -K1J5D, - M1B5D, -S1A5, -AA1A5: AEIO-540-L1B5D; TIO-540-F2BD, -J2BD, -N2BD, -S1AD, -U2A, -V2AD; LTIO-540-F2BD, -J2BD, -N2BD, S1AD -U2A, -V2AD; LTI-540-F2BD, -J2BD, -N2BD, -U2A, -V2AD; TIO-541-E1A4, -E1B4, -E1C4; TIGO-541-E1A, series engines equipped with Bendix Models RSA-10DB1, RSA-10DB2, RSA-10ED1, and RSA-10ED2 fuel injectors as identified in Bendix Service Bulletin RS-88, including Supplement 1, Section 1.A. (1), (2) and (3). Compliance required within the next 50 hours in service after the effective date of this AD, unless previously accomplished. To prevent engine failure due to fatigue failure of the injector fuel diaphragm stem, replace P/N 2539806 fuel diaphragm assembly with P/N 2541803 and perform flow calibration and nameplate reidentification in accordance with Section 2 Accomplishment Instructions of Bendix Energy Controls Division Service Bulletin RS-85, or FAA approved equivalent. An equivalent method of compliance with this AD, may be used if approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. Upon submission of substantiation data by an owner or operator through an FAA maintenance inspector, the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD. In accordance with FAR 21.197 and 21.199, the aircraft may be flown to a location where the alterations required by this AD can be performed. AVCO Lycoming S/B No. 467, Bendix Energy Control Service Bulletin Nos. RS-85 including Supplement No. 1, Revised August 10, 1983, and RS-88 including Supplement No. 1, Revised August 10, 1983, identified and described in this directive are incorporated herein and made by reference 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 may obtain copies upon request to Bendix Energy Controls Division, 717 North Bendix Drive, South Bend, Indiana 46620. These documents may also be examined at the Office of Regional Counsel, FAA New England Regional Office, 12 New England Executive Park, Burlington, Massachusetts 01803. A historical file on this AD is maintained at the New England Regional Office. This amendment becomes effective on November 4, 1983.
2021-23-17: The FAA is superseding Airworthiness Directive (AD) 2020-25-05 for all Hoffmann GmbH & Co. KG (Hoffmann) model HO-V 72 propellers. AD 2020-25-05 required amending the existing aircraft flight manual (AFM) with abnormal propeller vibration instructions. AD 2020-25-05 also required visual inspection and non-destructive test (NDT) inspection of the propeller hub and, depending on the results of the inspections, replacement of the propeller hub with a part eligible for installation. AD 2020-25-05 also required replacement of the propeller hub before exceeding 30 years since the date of manufacture. This AD was prompted by reports of cracks at different positions on two affected propeller hubs and subsequent manufacturer revision of the service information, which showed that the 30-year life limit of the propeller hub is no longer needed. This AD requires amending the existing AFM by inserting abnormal propeller vibration instructions, visual inspection and NDT inspection of the propeller hub and, depending on the results of the inspections, replacement of the propeller hub with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2010-01-03: 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: \n\n\tThe Civil Aviation Authority of the United Kingdom (UK) has informed EASA (European Aviation Safety Agency) that significant quantities of Halon 1211 gas, determined to be outside the required specification, have been supplied to the aviation industry for use in fire extinguishing equipment. * * * \n* * * * \n\n\t * * This Halon 1211 has subsequently been used to fill certain FFE (Fire Fighting Enterprises) portable cabin and toilet compartment fire extinguishers that are now likely to be installed in or carried on board aircraft. \n\n\tThe contaminated nature of this gas, when used against a fire, may provide reduced fire suppression, endangering the safety of the aircraft and its occupants. In addition, extinguisher activation may lead to release of toxic fumes, possibly causing injury to aircraft occupants. \n* * * * *\n\nThis AD requires actions that are intended to address the unsafe condition described in the MCAI.
75-16-05: 75-16-05 PILATUS AIRCRAFT LTD: Amendment 39-2280. Applies to B4-PC11 gliders Serial Numbers up to and including 159, certificated in all categories. Compliance is required as indicated. To detect improper aileron control connecting bolt installation and to prevent aileron jamming accomplish the following: (a) Within the next ten hours' time in service after the effective date of this AD, unless already accomplished, visually inspect the aileron control connecting bolts on the aileron control differential bellcrank to ensure the bolts are oriented correctly in accordance with Pilatus B4-PC11 Operating Manual, Figure 1, Page 26, or an FAA-approved equivalent. (b) Within 25 hours' time in service after the effective date of this AD, unless already accomplished, shorten all bolts P/N 116.35.11.070 used on aileron control differential bellcranks and airbrake control bellcranks, in accordance with the accomplishment instructions contained in Pilatus Aircraft Ltd. Service Bulletin No. 1003 dated June 1974, or an FAA- approved equivalent, or replace with modified or replacement bolts supplied by manufacturer or with equivalent FAA-approved bolts. This amendment becomes effective July 28, 1975.
2009-26-17: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Model DC-10-10, DC-10-10F, DC-10-15, DC- 10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, and DC-10-40F airplanes. That AD currently requires installing or replacing with improved parts, as applicable, the bonding straps between the metallic frame of the fillet and the wing leading edge ribs, on both the left and right sides of the airplane. This new AD revises the applicability by adding and removing certain airplanes. This new AD requires, for certain airplanes, repositioning or replacing two bonding straps, and doing a bonding-resistance check and an inspection to determine correct installation of certain bonding straps, and applicable corrective actions. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks in the event of a severe lightning strike, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
71-21-09: 71-21-09 HARTZELL PROPELLERS: Amdt. 39-1313 as amended by Amendment 39- 1466. Applies to Models HC-E2YK-2RB, HC-E2YR-2RB, and HC-E2YL-2( ) Propellers equipped with 8465-7R, 7663-4, or J7663-4 noncounterweighted type blades. Compliance required as indicated, unless already accomplished. To prevent overspeeds in flight due to inadvertent loss of the propeller's air charge, accomplish the following: (a) Propellers with 900 hours or more time in service since new or last overhaul as of the effective date of this AD, must be modified in accordance with paragraph (c) within the next 100 hours' time in service. (b) Propellers with 900 hours or more time in service since new or last overhaul as of the effective date of this AD must be modified in accordance with paragraph (c) prior to the accumulation of 1,000 hours in service since new, or last overhaul. (c) Install appropriate Spring Backup Kit and the propeller in accordance with Hartzell Service Letter No. 62dated June 23, 1970, revised August 6, 1970, or subsequent FAA- approved revision. An equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region Amendment 39-1313 was effective November 14, 1971. This amendment 39-1466 is effective June 27, 1972.