Results
2000-06-06: This document adopts a new airworthiness directive (AD) that applies to all The New Piper Aircraft, Inc. PA-31 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.
2000-05-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, A321, A330, and A340 series airplanes, that requires revising the Airplane Flight Manual to provide the flight crew with certain instructions associated with the Global Positioning System (GPS). This amendment also requires modification of the Global Positioning System Signal Unit (GPSSU) of the satellite navigational system. 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 prevent position and altitude errors due to bad oscillator warm-up characteristics of the GPSSU, which could result in navigational errors that may exceed 0.5 nautical mile.
96-23-06: 96-23-06 DORNIER: Amendment 39-9811. Docket 95-NM-232-AD. Applicability: Model 328-100 series airplanes; serial numbers 3005 through 3008 inclusive, 3010, 3011, and 3012; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 (c) 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 partial loss of the main hydraulic power supply due to loss of hydraulic fluid, accomplish the following: (a) Within 90 days after the effective date of this AD, replace landing gear hydraulic fuses having part number ACM30488, MOD states 2 through 6, with MOD 7 fuses in accordance with Dornier Service Bulletin SB-328-32-048, dated August 11, 1994. (b) As of the effective date of this AD, no person shall install a landing gear hydraulic fuse having part number ACM30488, MOD states 2 through 6, on any airplane. (c) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) 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. (e) The replacement shall be done in accordance with Dornier Service Bulletin SB-328-32- 048, dated August 11, 1994. 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 Dornier Luftfahrt GmbH, P.O. Box 1103, D-82230 Wessling, Germany. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on December 19, 1996.
2000-05-26: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-300 and ATR42-320 series airplanes, that currently requires inspections to determine the proper installation of rivets in certain key holes and to detect cracks in the area of the key holes where rivets are missing; and correction of discrepancies. This amendment increases the compliance time for the existing requirements and expands the applicability of the existing AD to include additional airplanes. This action also requires various inspections of the subject area for discrepancies, and corrective actions, if necessary; and replacement of certain cargo door hinges with new hinges. For certain airplanes, this action also requires replacement of friction plates, stop fittings, and bolts with new parts. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified bythis AD are intended to prevent fatigue cracks of the cargo door skin, certain frames, and entry door stop fittings and friction plates, which could result in reduced structural integrity of the airplane.
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.