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77-21-02: 77-21-02 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (Formerly Nord Aviation): Amendment 39-3053 as amended by Amendment 39-3142. Applies to all Nord 262 Series airplanes certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent interruption of fuel flow to the operating engine as a consequence of failure of one engine, accomplish the following: (a) Except as provided in paragraph (b) of this AD, within the next 300 hours time in service after October 31, 1977, accomplish the following: (1) For airplanes not equipped with auxiliary tanks in center wing, install a rigid metal partition inside fuel tank No. 1 (LH and RH) in accordance with paragraph II "Embodiment Instructions" of Nord 262 Fregate Service Bulletin No. 28-18 (Mod. 825), dated June 23, 1977, or an FAA-approved equivalent. (2) For airplanes equipped with auxiliary tanks in center wing, install a rigid metal partition inside fuel tank No. 1 (LH and RH) in accordance with paragraph II "Embodiment Instructions" of Nord 262 Fregate Service Bulletin No. 28-19 (Mod. 826), dated June 23, 1977, or an FAA-approved equivalent. (3) After accomplishing paragraph (a)(1) or (a)(2) of this AD, adjust the zero point on the fuel quantity indicator in accordance with paragraph II "Accomplishment Instructions" of Nord - 262 Fregate Service Bulletin No. 28-20 (Mod. 828), dated June 23, 1977, or an FAA-approved equivalent. (b) An airplane may be operated for a period of time not to extend past April 1, 1978, without the airplane being modified in accordance with paragraph (a) of this AD if - (1) Modification kits required under paragraph (a) of this AD have been ordered but have not been delivered; (2) An operating limitation placard is installed in clear view of the pilot that reads, "Warning-in the event of one engine failing, immediate action to correct asymmetrical flight must be taken to prevent loss of the operating engine"; and (3) The period of time for continued operation without being in compliance with paragraph (a) of this AD must be approved by the FAA District Office having jurisdiction over the operator. Requests for approval must substantiate that the modification kits required under paragraph (a) of this AD have been ordered but have not been delivered. (c) The placard required by paragraph (b) of this AD may be removed upon compliance with paragraph (a) of this AD. Amendment 39-3053 became effective October 31, 1977. This amendment 39-3142 is effective March 2, 1978, as to all persons except those persons to whom it was made immediately effective by the telegram dated December 8, 1977, which contained this amendment.
96-09-13: This amendment adopts a new airworthiness directive (AD) that applies to all Beech Aircraft Corporation (Beech) Models 99, 99A, A99A, B99, C99, B200, B200C, 1900, 1900C, and 1900D airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in freezing rain or freezing drizzle conditions by providing more clearly defined procedures and limitations associated with such conditions.
2011-07-08: 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: Two A340-300 aeroplanes experienced one single door opening of engine number (n[deg]) 3 Thrust Reverser (TR) pivoting door during climb. These events were the result of a primary lock malfunction and incorrect engagement of the secondary lock. * * * * * Deployment of one TR door in flight, particularly during the take-off or go around, could result in heavy buffet at low speed, or could significantly reduce take off performance [and increase pilot workload during takeoff or go around], which would constitute an unsafe condition. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2006-24-10: We are adopting a new airworthiness directive (AD) for certain Air Tractor, Inc. Models AT-501, AT-502, AT-502A, AT-502B, and AT-503A airplanes, which supersedes AD 2002-26-05 and AD 2002-11-05 R1. Since we issued AD 2002-26-05 and AD 2002- 11-05 R1, we determined that additional airplanes should be added to the applicability section and determined the safe life for new production airplanes and replacement spar caps should be extended. We also developed an alternative method of compliance (AMOC) to the requirements of this AD. This AD retains the actions required in AD 2002-26-05 and AD 2002-11-05 R1, adds additional airplanes to the Applicability section, extends the safe life for new production airplanes and replacement spar caps, and incorporates an AMOC. We are issuing this AD to prevent fatigue cracks from occurring in the wing lower spar cap before the established safe life is reached. Fatigue cracks in the wing lower spar cap could result in failure of the spar cap andlead to wing separation.
70-02-08: 70-02-08 BRITISH AIRCRAFT CORP.: Amdt. 39-918. Applies to Viscount Models 744, 745D, and 810 series airplanes which have fuselage leading edge frame structure reinforcing plates, P/N 70152-2787/8 or P/N 70152-3311/12 installed. Compliance is required as indicated unless already accomplished. To prevent failure of the fuselage leading edge frame structure, accomplish the following: (a) For airplanes which have reinforcing plates P/N 70152-2787/8 installed, visually inspect the reinforcing plates for cracks within the next 500 landings after the effective date of this AD, unless already accomplished within the last 500 landings, or within 1,000 landings after the reinforcing plates were installed, whichever occurs later, and thereafter at intervals not to exceed 1,000 landings since the last inspection. If cracks are found, comply with paragraph (c) of this AD within the next 500 landings. (b) For airplanes which have reinforcing plates, P/N 70152-3311/12 installed,visually inspect the reinforcing plates within the next 1,500 landings after the effective date of this AD unless already accomplished within the last 1,500 landings or within 3,000 landings after the reinforcing plates were installed, whichever occurs later, and thereafter at intervals not to exceed 3,000 landings since the last inspection. If cracks are found, comply with paragraph (c) of this AD within the next 500 landings. (c) If cracks are found during the inspection required by paragraphs (a) and (b) of this AD, replace the cracked reinforcing plates with new plates P/N 70152-3311/12 by the incorporation of Modification D.3072 Part (d) (for Models 744 and 745D series airplanes) or Modification FG.1928 Part (d) (for Model 810 series airplanes), or FAA-approved equivalents. (d) Upon request by the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Staff, FAA Europe, Africa, and Middle East Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for the operator. (e) For the purpose of complying with this AD, subject to the acceptance by the assigned FAA maintenance inspector, the number of landing may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the type aircraft. (British Aircraft Corp., Ltd., Preliminary Technical Leaflets No. 242, Issue 4 (Model 744 and 745D airplanes) and No. 106, Issue 4 (Model 810 series airplanes) cover this subject and present an approved accessibility scheme to facilitate the inspections required by paragraphs (a) an (b)). This amendment becomes effective February 8, 1970.
73-21-02: 73-21-02 BEECH: Amdt. 39-1733. Applies to Models 95-C55, 95-C55A, D55, D55A, E55 and E55A (Serial Numbers TE-1 through TE-874, TE-877 through TE-879, TE-881 and TE- 883 through TE-885); Models 58 and 58A (Serial Numbers TH-1 through TH-269 and TH-272) airplanes, irregardless of time in service. Compliance: Required as indicated unless already accomplished. To preclude failure or leakage of the flexible hose assemblies between the firewall and engine fuel injection system pump which could release fuel within the engine compartment or adversely affect engine operation, accomplish the following: A) Within 50 hours' time in service after the effective date of this AD, on those airplanes which have the Stratoflex P/N 156001-8D0100 hose assemblies installed between the firewall and engine fuel injection pump, replace the hose with a Beech P/N 58-920035-(-1), (-5), or (-7) or (-9) or (-11) or field fabricated equivalent of the proper length as determined by the measurementprocedure contained in Paragraph C of this AD. B) Within 25 hours' time in service after the effective date of this AD, on those airplanes which have Stratoflex P/N 130001-8D0090 or Beech P/N 58-920035-1 hose assemblies installed either in compliance with AD 73-13-03 or by the manufacturer, visually inspect these hoses per instructions contained in Beech Service Instruction No. 0409-282, Rev. II, Part III, to determine whether they are of the proper length for the location in which they are installed. If the above mentioned Service Instruction is unavailable or the inspection outlined is inconclusive, the acceptability of the installed hose may be determined using the measurement procedure contained in Paragraph C of this AD. 1) Prior to further flight, replace any hose having excessive or insufficient length with a Beech P/N 58-920035-(-1), (-5), or (-7) or (-9) or (-11) or field fabricated equivalent hose of the correct length as determined by the procedure contained inthis AD. C) Establish the required hose length as follows: 1) Using a P/N 58-920035-1 hose assembly or equivalent, attach one end of the fuel hose to the fuel pump fitting and align the free end of the hose assembly beside the forward left side of the 45-degree firewall fitting. 2) Compare the flare mating surfaces in the hose fitting and the fitting on the firewall to determine the length required. Hose length is critical. Excess length of 1/8 inch -0 plus 1/8 inch will provide the bow necessary for flexing during engine operation. Beech P/N 58- 920035 hose assemblies are available in 1/8-inch length increments. NOTE: Equivalent hose assemblies may be fabricated to the desired dimensions using Stratoflex Bulk Hose 130-8 and P/N 712-8D fittings following instructions contained in Stratoflex Catalog 103 or equivalent FAA-approved procedures. Stratoflex hose, fittings, and catalogs are obtainable from Stratoflex, Inc., 220 Roberts Cutoff, P.O. Box 10398, Fort Worth, Texas 76114. Aeroquip Type 303 hose is not an acceptable substitute. Beechcraft Service Instruction No. 0409-282, Rev. II or later approved revisions cover this subject. This AD supersedes AD 73-13-03 (Amendment 39-166). This AD becomes effective October 12, 1973.
2011-07-11: 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: On two occurrences on Myst[egrave]re-Falcon 50 aeroplanes in service, it was detected that two pipes had been swapped in maintenance at the frame 42 firewall. The swapped lines are the extinguishing system line to engine 2, and engine 2 Low Pressure (LP) bleed line. If the swapping of these two lines is not detected and corrected, in case of engine 2 fire, the fire extinguishing capability would not be operational. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2011-07-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires installing new in-line fuses for the fuel level float switch and new in-line fuses for the pressure switch, as applicable, and changing the wiring. The proposed actions would affect the left and right wing forward spars, center wing forward spar, forward auxiliary fuel tank, and aft auxiliary fuel tank, as applicable. This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
96-11-11: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9 series airplanes, that requires inspection(s) to detect cracking in the nose skin of the fuselage, and various follow-on actions. This amendment also provides for an optional modification, which would defer certain repetitive inspections, if no cracking is detected. This amendment is prompted by reports of cracking in the upper nose skin of the fuselage due to fatigue. The actions specified by this AD are intended to prevent fatigue-related cracking, which could compromise the structural integrity of the airplane.
86-17-08: 86-17-08 GROB WERKE GmbH (Burkhart Grob): Amendment 39-5399. Applies to Models G103 TWIN II and G103A TWIN II ACRO gliders serial numbers 33879- (K-117) through 34012-(K-245) certificated in any category. Compliance is required as indicated unless already accomplished. To prevent jamming of the outer airbrake pivot lever which could result in the loss of airbrake control, accomplish the following: (a) Within the next 10 hours time-in-service after the effective date of this AD, measure the airbrake pivot lever stop pad length in accordance with Part 1 of the "Instructions" section of Grob Technical Information No. TM 315-31, dated October 7, 1985. (b) If a stop pad of a length of less than 36 mm is found during the inspection required by Paragraph (a) of this AD, or if a stop pad is found that can be wedged under the wingskin, before further flight, install a stop pad extension in accordance with part 2 of the "Instructions" section of Grob Technical Information No. TM 315-31, dated October 7, 1985, and Grob Repair Instructions No. 315-31, dated October 7, 1985. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 15 Rue de la Loi B-0040 Brussels, Belgium, Telephone No. 513.38.30 ext. 2710 or the Manager, New York Aircraft Certification Office, Aircraft Certification Division, FAA, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581, Telephone No. (516) 791-6680. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office or the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD. Grob Technical Information No. TM 315-31, dated October 7, 1985, and Grob Repair Instructions No. 315-31, dated October 7, 1985, identified and described in this document, 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 Grob Systems, Inc., Aircraft Division, I-75 and Airport Drive, Bluffton, Ohio 45817. These documents also may be examined at the Office of Regional Counsel, ANE-7, FAA New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket 86-ANE-32, between the hours of 8:00 am and 4:30 pm; Monday thru Friday, except Federal holidays. This amendment becomes effective on September 10, 1986.