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91-05-02: 91-05-02 SOCATA: Amendment 39-6887. Docket No. 90-CE-20-AD. Applicability: Models TB 20 and TB 21 airplanes (serial numbers (S/N) 1 through 1051, except S/N 1040 and S/N 1042), certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent structural failure of the fuselage frame in the area of the landing gear attachment, accomplish the following: (a) On airplanes with more than 1,500 hours time-in-service (TIS) on the effective date of this AD, within the next 100 hours TIS after the effective date of this AD and, thereafter, at intervals not to exceed 500 hours TIS, visually inspect the fuselage frame No. 0 for cracks in the area of the engine mount and landing gear mount in accordance with the instructions in Aerospatiale Service Bulletin (SB) No. 42/1, dated July 1990. Prior to further flight, repair any cracked frames found in accordance with the instructions in the above SB.(b) On airplanes with less than 1,500 hours TIS on the effective date of this AD, within the next 100 hours TIS or prior to accumulating 1,600 hours TIS, whichever occurs later, and, thereafter, at intervals not to exceed 500 hours TIS, visually inspect the fuselage frame No. 0 for cracks in the area of the engine mount and landing gear mount in accordance with the instructions in Aerospatiale SB No. 42/1, dated July 1990. Prior to further flight repair any cracked frames found per the instructions in the above SB. (c) The repetitive inspections specified in paragraphs (a) and (b) of this AD are no longer required when the airplane has been modified in accordance with Socata Kit 9152. (d) 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. (e) An alternate method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Aircraft Certification Office, Europe, Africa, Middle East Office, FAA, c/o American Embassy, B-1000, Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (f) All persons affected by this directive may obtain copies of the documents referred to herein upon request to Aerospatiale Aeroport Tarbes-Ossum-Lourdes, B.P. 930 65009 Tarbes, France; Telephone 62.51.7300; or may examine the service information at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6887, AD 91-05-02) becomes effective on March 25, 1991.
98-26-15: This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that currently requires repetitive detailed visual inspections to detect cracks in the shear cleats of the roller guide structural support of the passenger door, and replacement of any cracked shear cleat with a new shear cleat. That AD also provides for an optional terminating modification that constitutes terminating action for the repetitive inspections. This amendment mandates accomplishment of the previously optional terminating modification. This amendment is prompted by reports indicating that fatigue cracking was detected in the roller guide shear cleats of the passenger door. The actions specified by this AD are intended to prevent such fatigue-related cracking, which could result in structural failure or loss of the passenger door, and consequent rapid depressurization of the airplane during flight.
97-21-10: 97-21-10 AIRBUS INDUSTRIE: Amendment 39-10163. Docket 97-NM-265-AD. Applicability: Model A319, A320, and A321 series airplanes, certificated in any category; on which any of the following Airbus Modifications have been installed: Affected Model(s) Airbus Modification Installed A319 and A321 A319, A320, and A321 25469 (reference Airbus Service Bulletin A320-22-1054) 26093 A320 24065 (reference Airbus Service Bulletin A320-22-1040) or 24067 (reference Airbus Service Bulletin A320-22-1039) A320 25314 (reference Airbus Service Bulletin A320-22-1051) or 25315 (reference Airbus Service Bulletin A320-22-1050) A320 and A321 24064 (reference Airbus Service Bulletin A320-22-1034) or 24066 (reference Airbus Service Bulletin A320-22-1029) A320 and A321 25199 (reference Airbus Service Bulletin A320-22-1045) or 25200 (reference Airbus Service Bulletin A320-22-1046) A320 and A321 25240 (reference Airbus Service Bulletin A320-22-1033) or 25274 (reference AirbusService Bulletin A320-22-1056) A319, A320, and A3 26243 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 ensure that the flightcrew detects and corrects an unintended flight path if certain software anomalies of the FMGS occur, which could result in an increased risk of collision with terrain or other airplanes, accomplish the following: (a) Within 10 days after the effective date of this AD, revise the Normal Procedures Section of the FAA-approved Airplane Flight Manual (AFM) by inserting a copy of Model A319/320/321 Flight Manual Temporary Revision 4.03.00/02, dated May 28, 1997, into the AFM. NOTE 2: When the temporary revision specified in paragraph (a) of this AD has been incorporated into the general revisions of the AFM, the general revisions may be inserted in the AFM, provided the information contained in the general revisions is identical to that specified in Model A319/320/321 Flight Manual Temporary Revision 4.03.00/02. (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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Operations Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (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) The AFM revision shall be done in accordance with Model A319/320/321 Flight Manual Temporary Revision 4.03.00/02, dated May 28, 1997. 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. 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. NOTE 4: The subject of this AD is addressed in French airworthiness directive 97-153- 100(B), dated July 16, 1997. (e) This amendment becomes effective on November 3, 1997.
60-01-04: 60-01-04 FAIRCHILD: Amdt. 81 Part 507 Federal Register January 16, 1960. Applies to all Models F-27, F-27A, and -27B aircraft. Compliance required by January 15, 1960. Cases of "rudder walk" have been experienced on aircraft in service. Such rudder oscillation creates a flight hazard. In order to correct or prevent this condition, unless already accomplished, a beaded angle should be added to the rudder balance tab trailing edge in accordance with Fairchild Service Bulletin 27-14.
77-04-05: 77-04-05 CESSNA: Amendment 39-2838. Applies to 180 Series (Serial Numbers 18050662 thru 18052711); 182 Series (Serial Numbers 18251557 thru 18264790); 185 Series (Serial Numbers 18500001 thru 18501832); 188 Series (Serial Numbers 18800001 thru 18802348); and A188 Series (Serial Numbers 18800001 thru 18800707) airplanes. Compliance: Required as indicated, unless already accomplished. To prevent ingestion of the induction air box seal into the carburetor, within the next 50 hours' time in service after the effective date of this AD, accomplish the following: A. Disconnect the carburetor air intake flexible duct assembly from the induction air box. B. Visually inspect the condition of the existing carburetor induction air box seal(s) and if not securely bonded to the carburetor intake flexible duct assembly, remove the existing seal(s) and install new P/N 0752016-10 and -11 seals in accordance with the following procedure: 1. Clean the metal surface of thecarburetor air intake flexible duct assembly and the new P/N 0752016-10 and -11 seals with methyl ethyl keytone, methyl iso butyl keytone, acetone or lacquer thinner solvent. 2. Apply EC 847 adhesive to the carburetor air intake flexible duct assembly adapter and P/N 0752016-10 and -11 seals, allow to dry until tacky (usually between 5 and 30 minutes), and then press firmly together to insure contact (complete cure will occur within 24 hours). 3. Install the lower P/N 0752016-10 seal on the horizontal flat surface on the bottom side of the adapter flange, locating the forward edge of the seal so that it does not extend into the bend radius on the front side of the horizontal surface. 4. Pierce a hole in each P/N 0752016-11 seal to match the holes for the fasteners in the carburetor air intake flexible duct assembly adapter flange. 5. Reinstall the carburetor air intake flexible duct assembly flange to the carburetor induction air box. C. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Cessna Service Letter SE76-18, dated October 11, 1976, or later approved revisions, covers the subject matter of this AD. This amendment becomes effective March 1, 1977.
98-26-09: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC 9-10, -20, -30, -40, and -50 series airplanes, and C-9 (military) airplanes, that requires a one-time visual inspection to determine if the doorstops and corners of the doorjamb of the forward passenger door have been modified, various follow-on repetitive inspections, and modification, if necessary. This amendment is prompted by reports of fatigue cracks found in the fuselage skin and doubler at the corners and doorstops of the doorjamb of the forward passenger door. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.
98-26-05: This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace (Operations) Limited (British Aerospace) Model B.121 Series 1, 2, and 3 airplanes. This AD requires repetitively inspecting (using visual methods) the internal and external surfaces of the brake torque tube assemblies in the cockpit area for cracks. This AD also requires obtaining and incorporating repair procedures for any brake torque tube assembly found cracked. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect and correct cracks in the brake torque tube assemblies, which could result in reduced brake efficiency with possible reduced and/or loss of airplane control.
2013-14-01: We are adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. Model PC-6/B2-H4 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as faulty rivets installed in the airframes during production could reduce the structural integrity of the airplane. We are issuing this AD to require actions to address the unsafe condition on these products.
81-21-03: 81-21-03 BRITISH AEROSPACE CORPORATION: Amendment 39-4229. Applies to all operators of DH-114 Heron Series 1B and all series 2 airplanes which have been modified in accordance with Modification 154 or 469. To ensure wing leading edge access doors remain properly secured, accomplish the following unless already accomplished: 1. Within 350 hours time in service after the effective date of this AD, modify the wing leading edge access doors in accordance with British Aerospace Corp. Manufacturer's Technical News Sheet W.1 1, Issue 2, and Modification No. Heron 1171 (Amendment No. 1 incorporated) dated October 17, 1961, or a later FAA approved revision. 2. Alternate means of compliance may be used which provide an equivalent level of safety when approved by the Chief, Seattle Area Aircraft Certification Office, FAA, Northwest Region. 3. Airplanes may be flown to a maintenance base for repairs or replacement in accordance with FAR 21.197. 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 addresses listed above. These documents may also be examined at FAA, Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective October 18, 1981.
51-04-02: 51-04-02 WARNER: Applies to All Engines Except Those With the Letter "A" Stamped After the Serial Number on the Engine Nameplate. The Letter "A" Indicates That the Modifications Hereinafter Discussed Have Already Been Accomplished. Compliance required as indicated. As a precautionary measure to preclude serious flight hazards resulting from failure of the 5/16-inch cylinder holddown studs P/N S506, the following inspections or replacements should be accomplished. A. Compliance required as soon as possible but not later than April 1, 1951 and at each 100 hours of operation thereafter. 1. Check the cylinder holddown nuts to determine that they are tightened to a torque of 180 inch- pounds desired to a 200 inch-pounds maximum. (a) If one or more of the studs is found to be broken, replace all of the studs for the particular cylinder. (b) Loose cylinder holddown nuts are a good indication that the stud may have stretched to the extent that fatigue failure may soon result. If one or more of the nuts is found loose, it is recommended that all of the studs in the cylinder be replaced. (c) When installing a cylinder with oil on the stud threads, tighten nuts to 200 inch-pounds desired to 225 inch-pounds maximum. (Warner Service Letter No. A-15 discusses procedures for inspecting and replacing 5/16-inch studs and nuts.) B. Compliance not required, but will eliminate foregoing mandatory inspections. 1. Replace cylinder stud P/N S506 and nut N-511 with 3/8-inch stud S-911 and nut N-910. 2. Replace gasket between cylinder barrel and crankcase with an "O" type ring. 3. Stamp letter "A" after serial number on engine nameplate when this modification has been completed. (Warner Service Letter No. A-17 explains the details connected with the replacement of these parts.) The Warner Aircraft Co., P. O. Box 229, Niles, Mich., which purchased the assets of the Warner Division of the Clinton Machine Co., Detroit, Mich., have a large supply of replacement part stocks that will be held in their inventory for an indefinite period. Warner Service Letter No. A-17 should be consulted before ordering these replacement parts. If either Letter A-17 or Letter A-15 is not available, copies may be obtained from the Warner Aircraft Co., Box 229, Niles, Mich.