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75-09-14: 75-09-14 DON PICCARD BALLOONS: Amendment 39-2185. Applies to Piccard Hot Air Balloon Model AX-6 certificated in all categories, incorporating Rego Blast Valves, P/N 7553S Series. To prevent fuel system failure or an inflight fire, prior to further flight unless previously accomplished within one year prior to the effective date of this AD, and thereafter at intervals not to exceed the annual inspection or 100 hours time in service, whichever occurs earlier, accomplish the following: A. Remove the valve actuating lever roll pin P/N 7553S-8 from actuating lever. (Be careful to remove any burrs in the stem area around the roll pin hole before removing the valve stem P/N 7553S-1 from the bonnet P/N 7553-5). Replace the "O" ring stem seal with a new Rego "O" ring P/N 1421-7. Lubricate the new "O" ring with a suitable lubricant before reassembly. B. Check the torque of the valve seat retaining screw to 10 in-lbs. If it turns, the screw must be removed and reinstalledusing MIL-S 22473 high strength thread locking compound or equivalent. CAUTION. Do not permit the thread locking compound to adhere to the valve rubber seating surface. C. Reinstall valve actuating lever on the valve body with roll pin 7553S-8. Install a number six machine screw and stop nut or a 3/32 inch stainless steel cotter pin through the hole in the roll pin holding the actuating handle to the valve body and secure. D. Appropriate maintenance records must be kept in accordance with FAR 91.173. Prior to further flight, unless already accomplished, incorporate the following in the FAA Approved Balloon Flight Manual, limitations section: WARNING: Water contamination can cause serious fuel system malfunctions. Never leave tanks or hoses open to the air. Never fill from a tank which has been used for vapor withdrawal. To prevent the effects of water contamination, add one half cup methanol (methyl alcohol) per ten gallons capacity to each fuel tank at intervalsnot exceeding twelve calendar months. This amendment is effective April 28, 1975, for all persons except those to whom it was made effective by airmail letter, dated April 4, 1975, which contained this amendment.
2000-06-01: This amendment adopts a new airworthiness directive (AD) that applies to Cessna Aircraft Company (Cessna) 150, 152, 172, 177, 180, 182, 185, 188, 206, 207, 210, and 337 series airplanes. This AD requires measuring the visible length of standpipe (tube) in the top assembly of the fuel strainer assembly for the correct length, and replacing any fuel strainer assembly that does not have the correct length of standpipe. This AD is the result of reports that the fuel strainer assemblies on the affected airplanes were manufactured with the fuel standpipes incorrectly installed in the assembly housing top. The actions specified by this AD are intended to prevent foreign material from entering the fuel system and engine, which could result in loss of engine power or complete engine stoppage during flight.
85-11-04: 85-11-04 BEECH: Amendment 39-5070. Applies to Models 58P and 58PA (Serial Numbers TJ-3 through TJ-443 except TJ-436) airplanes, certificated in any category. Compliance: As indicated in the body of the AD, unless already accomplished. To prevent possible injuries due to passenger seat failure in an emergency landing, accomplish the following: (a) Within the next 25 hours time-in-service after the effective date of this AD, placard the airplane and modify the AFM as follows: (1) Fabricate and install in full view of the pilot a temporary placard using letters of minimum .10 inch in height which states: "DO NOT OCCUPY SEATS 5 OR 6 DURING TAKEOFF OR LANDING" and operate the airplane in accordance with these limitations. (2) Attach a copy of this AD to the Limitations Section of the AFM. (3) The requirements of paragraphs (a)(1) and (a)(2) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the FederalAviation Regulations (FAR) on any airplane owned or operated by him. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. (b) Within the next 100 hours time-in-service or one calendar year after the effective date of this AD, whichever occurs first, modify the seat attachments of the fifth and sixth seats in accordance with the provisions of Beech Service Bulletin No. 2022, dated February 1985. (c) The requirements and limitations of paragraph (a) of this AD may be removed when the modification required by paragraph (b) have been accomplished. (d) An equivalent means of compliance with this AD may be used, if approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid- Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4400. All persons affected by this directive may obtain copies of the document referred to herein upon request to Beech Aircraft Corporation, Wichita, Kansas 67201, or FAA, Office of Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on July 1, 1985.
80-04-11 R2: 80-04-11 R2 ROCKWELL INTERNATIONAL: Amendment 39-3703 as amended by Amendment 39-3921 is further amended by Amendment 39-4611. Applies to Rockwell Model NA 265-60 and NA 265-80 airplanes completely or partially modified by The Raisbeck Group in accordance with Raisbeck STC's SA687NW or SA847NW. To prevent structural failure of the airframe, accomplish a comprehensive inspection of all areas modified by The Raisbeck Group as follows: A. Before further flight, inspect for deviations from the supplemental type design in accordance with Paragraphs I through IV and VI of FAA approved Raisbeck Service Bulletin No. 25. Inspect for discrepancies such as: 1. Plugged holes 2. Oblong, eggshaped, oversized, or irregular holes 3. Tapered holes 4. Excess holes 5. Inadequate edge distances 6. Gouges 7. Improper fasteners (type and number) 8. Improper clearances 9. Any other irregularities which are not consistent with standard aircraftpractice. B. Deleted by Amendment 39-3921. C. Before accumulation of 2000 flight hours time in service after modification by STC SA687NW or STC SA847NW, inspect the wing leading edge in accordance with Raisbeck Service Bulletin No. 33. Repeat this inspection every 300 flight hours time in service thereafter. D. Deleted by Amendment 39-4611. E. Inspections are to be conducted at facilities specifically authorized by the Manager, Aircraft Certification Branch, FAA, Northwest Mountain Region. F. Discrepancies discovered as a result of the inspections are to be reported to the Manager, Aircraft Certification Branch, FAA, Northwest Mountain Region. Repair or modifications required because of these problems are to be FAA approved by the Manager, Aircraft Certification Branch, FAA, Northwest Mountain Region or specifically authorized DER's. G. Airplanes may be ferried, in accordance with FAR 21.199, to a maintenance base for the purpose of complying with this AD. H. The inspections noted herein may be accomplished as noted or in a manner approved by the Manager, Aircraft Certification Branch, FAA, Northwest Mountain Region. I. Deleted by Amendment 39-4611. 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 from Rockwell International, Sabreliner Division, 6161 Aviation Drive, St. Louis, Missouri 63134. These documents may also be examined at FAA, Central Region, Wichita Aircraft Certification Office, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas, or FAA, Northwest Mountain Region, Office of Regional Counsel, 17900 Pacific Highway South, Seattle, Washington 98168, telephone (206) 764-7019. Amendment 39-3703 became effective upon publication in the Federal Register and was effective earlier to all recipients of the telegraphic AD T80-NW-2 dated January 17, 1980. Amendment 39-3921 became effective October 1, 1980. This Amendment 39-4611 becomes effective April 13, 1983.
2010-17-11R2: We are revising airworthiness directive (AD) 2010-17-11R1, which applies to all Dowty Propellers R408/6-123-F/17 model propellers. AD 2010-17-11R1 required initial application of sealant between the bus bar assembly and the backplate assembly of certain line-replaceable units (LRUs) and repetitive re-applications of sealant on all R408/6- 123-F/17 model propellers. AD 2010-17-11R1 also provided an optional terminating action to the repetitive re-application of sealant. This AD increases the interval allowed between the required re-application of sealant, and specifies an additional acceptable sealant. This AD was prompted by failure of the propeller de-ice bus bar due to friction or contact between the bus bar and the backplate assembly, consequent intermittent short circuit, and possible double generator failure. We are issuing this AD to prevent an in-flight double generator failure, which could result in reduced control of the airplane.
2014-24-01: We are adopting a new airworthiness directive (AD) for all Harry E. Williams de Havilland Model DH 82A airplanes, all Cliff Robertson de Havilland Model DH 82A airplanes, and all de Havilland Model DH 83 airplanes. This AD was prompted by reports of structural failure of the attachment of the wing to the fuselage that resulted from failed lateral fuselage tie rods. This AD requires inspecting the aircraft maintenance records to determine the date of installation or the date of last replacement of the lateral fuselage tie rods. This AD also requires repetitively replacing all lateral fuselage tie rods and attaching nuts at a specified life limit interval. We are issuing this AD to correct the unsafe condition on these products.
2000-06-04: This document adopts a new airworthiness directive (AD) that applies to all Fairchild Aircraft Corporation (Fairchild) SA226 and SA227 series airplanes that are equipped with pneumatic deicing boots. This AD requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
2014-24-02: We are superseding Airworthiness Directive (AD) 2014-07-51 for AgustaWestland S.p.A. Model AB139 and AW139 helicopters with certain main rotor (M/R) rotating scissors installed. AD 2014-07-51 required repetitively inspecting the M/R rotating scissors for play of the lower half scissor spherical bearing (bearing) and removing the bearing if there was play beyond allowable limits. AD 2014-07-51 also required removing all affected bearings. AD 2014-07-51 was prompted by reports of certain bearings dislodging from certain M/R rotating scissors. This new AD retains the requirements of AD 2014-07-51, expands the applicability, and requires installing a special nut. These actions are intended to detect excessive play of the bearing and prevent failure of the M/R rotating scissors and subsequent loss of control of the helicopter.
79-06-06 R2: 79-06-06 R2 AVCO LYCOMING DIVISION: Amendment 39-3440 as amended by Amendment 39-3506 is further amended by Amendment 39-3795. Applies to all LTS101-600A, -600B, -600A-2, and -650A-2 turboshaft and LTP101-600 and -600A turboprop engines. Compliance required as indicated. 1. To prevent undetected lubrication system contamination leading to oil starvation of engine bearings and subsequent engine stoppage, accomplish the following within the next 5 hours of engine operation unless already accomplished and every 25 hours thereafter: Perform a spectrometric oil analysis as outlined in the applicable Avco Lycoming Engine Maintenance Manual, Chapter 71-00-00, and in accordance with Avco Lycoming Alert Notice, Reference 3V- W714, dated February 16, 1979, or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. If any of the following spectrometric oil analysis limits are exceeded, inspect and repair, prior to further flight, in accordance with Chapter 72-00-00, Paragraph 13, of the appropriate Avco Lycoming Engine Maintenance Manual: a. Iron content, six parts per million. b. Between consecutive spectrometric oil analysis, iron content increases by three parts per million. c. Any other metal, five parts per million. NOTE: Engine operation not to exceed 4 calendar days or 25 hours between extraction of oil sample and obtaining spectrometric oil analysis results is authorized. 2. For LTP101-600 and 600A turboprop engines, S/N LE 50001 through S/N LE 50017, the requirements of paragraph 1 may be discontinued after the power turbine rotor assembly P/N 4-143-010-01/-02 is replaced with either: a. Rotor assembly P/N 4-143-010-01/02 with "APOLS93277" etched on rear face of wrenching surface, or b. Rotor assembly P/N 4-143-010-03, in accordance with Avco Lycoming Service Bulletin No. LTP101-72-0003, Revision 1, dated May 21, 1979, or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. 3. For LTS101-600A, -600B, -600A-2, and -650A-2 turboshaft engines, the requirements of Paragraph 1 may be discontinued if the engine installation incorporates a full flow scavenge chip detector, TEDECO P/N A615 or equivalent, installed in accordance with STC SH2929SW or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. 4. For all engines affected by this AD, the requirements of Paragraph 1 may be discontinued if the equivalent means of detecting lubrication system contamination, approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region, are effected. Avco Lycoming Alert Notice, Reference 3V-W714, dated February 16, 1979, and Service Bulletin No. LTP101-72-0003, Revision 1, dated May 21, 1979, refer to this subject. The manufacturer's Alert Notice, Service Bulletin, and Manuals identified and described in this directive are incorporated herein and madea 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 Director, Customer Service, Avco Lycoming Division, 550 South Main Street, Stratford, Connecticut 06514. These documents may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. Amendment 39-3440 became effective upon publication in the FEDERAL REGISTER except for recipients of the Emergency AD, dated February 23, 1979, for whom it became effective upon receipt. Amendment 39-3506 became effective upon publication in the FEDERAL REGISTER. This Amendment 39-3795 becomes effective June 2, 1980.
2000-05-24: This amendment adopts a new airworthiness directive (AD) that applies to all aircraft equipped with a certain Honeywell International Inc. (Honeywell) KAP 140 or KFC 225 autopilot system. AlliedSignal Avionics Inc. manufactured these autopilot systems before transferring the design data to Honeywell. This AD requires that you inspect the autopilot servo actuator for a loose fastener and modify the autopilot servo actuator when a loose fastener is found. This AD is the result of a report of failure of the autopilot servo actuator to disengage when the autopilot power was removed. The actions specified by this AD are intended to detect and correct a loose fastener in the autopilot servo actuator, which could cause the autopilot servo actuator to not disengage when power to the autopilot is removed. This could cause the pilot to experience additional control forces.