Results
94-06-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 and A310 series airplanes. This action requires modification of the evacuation system regulator assembly in certain escape slides and slide/rafts installed on these airplanes. This amendment is prompted by reports indicating that the evacuation system regulator assembly functioned inappropriately, and cases of the evacuation system inflating when the regulator safety pin was removed. The actions specified in this AD are intended to prevent delayed or inadvertent inflation of an evacuation system, which could delay or impede the evacuation of passengers during an emergency, and to prevent possible injury to ground personnel during installation of the evacuation system.
93-15-07: 93-15-07 DE HAVILLAND, INC.: Amendment 39-8653. Docket 93-NM-124-AD. Applicability: All Model DHC-7 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the upper lockstrut sub-assembly, which could lead to partial collapse of the main landing gear, accomplish the following: (a) Within 250 landings after the effective date of this AD, conduct a non-destructive testing inspection of upper lockstrut sub-assemblies, part numbers 15709-7 and 15709-9, to detect cracking, in accordance with de Havilland Alert Service Bulletin S.B. A7-32-100, dated July 7, 1993. (1) If any crack is detected, prior to further flight, replace the discrepant sub-assembly with a serviceable sub-assembly in accordance with the service bulletin. (2) If no crack is detected, no further action is required by this AD. (b) Within 5 days after completion of the inspection required by paragraph(a) of this AD, operators must submit a report containing details of any cracked upper lockstruts found to de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada; fax (416) 375-4539. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (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, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, ifany, may be obtained from the New York ACO. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The inspection and replacement shall be done in accordance with de Havilland Alert Service Bulletin S.B. A7-32-100, dated July 7, 1993. 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 de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendmentbecomes effective on August 9, 1993.
93-05-19: 93-05-19 FOKKER: Amendment 39-8523. Docket 92-NM-193-AD. Applicability: Model F-27 series airplanes, serial numbers 10102 through 10259, inclusive; on which the inspection described in Service Bulletin F27/53-60 (B-156) Part II has not been accomplished; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the wings, accomplish the following: (a) Prior to the accumulation of 2,700 hours time-in-service after the effective date of this AD or within 12 months after the effective date of this AD, whichever occurs earlier, perform a one-time visual inspection to determine whether bolts and screws of proper length have been installed in the outboard wing attachment fittings of the fuselage main frame at stations 7961 and 9439.5, in accordance with Fokker Service Bulletin F27/53-115, dated May 21, 1991. (1) If any measured bolt or screw is found that protrudes more than 4.5 mm (0.177 inch) through the nut, prior to further flight, replace it with a shorter one, in accordance with the service bulletin. (2) If no measured bolt or screw is found that protrudes more than 4.5 mm (0.177 inch) through the nut, no further action is necessary. (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 Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: 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 FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspection and replacement shall be done in accordance with Fokker Service Bulletin F27/53-115, dated May 21, 1991. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. 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. (e) This amendment becomes effective on May 5, 1993.
2010-16-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2010-16-51, which was sent previously to all known U.S. owners and operators of Eurocopter France (Eurocopter) Model SA330J helicopters by individual letters. This AD requires, within 10 hours time-in-service (TIS), inspecting for a gap between the main gearbox (MGB) oil cooling fan assembly (fan) rotor blade and the upper section of the guide vane bearing housing. This inspection must be accomplished by using a feeler gauge attached to a rigid rod. If the feeler gauge cannot be inserted between the blade and the housing, this AD requires replacing the two fan rotor shaft bearings with two airworthy bearings. This AD is prompted by the separation of a fan rotor blade that caused puncture holes in the transmission deck. This condition, if not corrected, could lead to damage to the hydraulic lines and flight controls, and subsequent loss of control of the helicopter.
2010-04-12: We are adopting a new airworthiness directive (AD) for certain Model DHC-8-100 and DHC-8-200 series airplanes, and DHC-8-301, -311, and -315 airplanes. This AD requires implementing a corrosion prevention and control program (CPCP) either by accomplishing specific tasks or by revising the maintenance inspection program to include a CPCP. This AD results from the determination that, as airplanes age, they are more likely to exhibit indications of corrosion. We are issuing this AD to prevent structural failure of the airplane due to corrosion.
95-12-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires a visual inspection to verify proper clearance between the engine fuel supply-line and the hydraulic line in certain areas, and replacement of damaged fuel lines. This amendment would also require installation of additional clamps on the out line of the lift-dumper in certain cases. This amendment is prompted by a report indicating that fuel was found leaking from the right-hand wheel bay on one airplane due to chafing of the fuel supply line. The actions specified by this AD are intended to prevent such chafing, which could result in fuel leakage, and, subsequently, lead to a possible fire hazard and engine fuel depravation.
2010-17-14: We are adopting a new airworthiness directive (AD) for certain Model 737-100 and -200 series airplanes. This AD requires repetitive inspections for cracking and damaged fasteners of certain fuselage frames and stub beams, and corrective actions if necessary. For certain airplanes, this AD also requires repetitive inspections for cracking of the inboard chord fastener hole of the frame at body station 639, stringer S-16, and corrective actions if necessary. For certain airplanes, this AD also requires an inspection to determine the edge margin of the lower chord. For airplanes with a certain short edge margin, this AD requires repetitive inspections for cracking, and corrective actions if necessary; replacing the lower chord terminates the repetitive inspections. This AD requires an eventual preventive modification. For certain airplanes, doing the modification or a repair terminates the repetitive inspections for the repaired or modified frame only. For airplanes on which themodification or repair is done at certain body stations, this AD requires repetitive inspections for cracking of certain frame webs and inner and outer chords, and corrective actions if necessary. For certain other airplanes, this AD requires a modification which includes reinforcing the body frame inner chords, replacing the stub beam upper chords and attach angles, and reinforcing the stub beam web. This AD results from reports of fatigue cracks at certain frame sections, in addition to stub beam cracking, caused by high flight cycle stresses from both pressurization and maneuver load. We are issuing this AD to detect and correct fatigue cracking of certain fuselage frames and stub beams, and possible severed frames, which could result in reduced structural integrity of the frames. This reduced structural integrity can increase loading in the fuselage skin, which will accelerate skin crack growth and result in rapid decompression of the fuselage.
2010-10-01 R1: We are revising an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: Inspection of a high time aircraft has revealed cracks in the Horizontal Stabiliser rear spar splice plate and inboard main ribs around the area of the Horizontal Stabiliser rear pivot attachment. Additionally, failure of some attach bolts in service may be due to improper assembly. This amendment is issued to include an applicability matrix (Table 1, page 2) in the compliance section of the service bulletin for improved clarity. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective October 7, 2010. On October 7, 2010, the Director of the Federal Register approved the incorporation by reference of Gippsland Aeronautics Mandatory Service Bulletin SB-GA8-2002-02, Issue 6, dated April 21, 2010, listed in this AD. As of March 2, 2009 (74 FR 8159; February 24, 2009), the Director of the Federal Register approved the incorporation by reference of Gippsland Aeronautics Mandatory Service Bulletin SB-GA8-2002-02, Issue 5, dated November 13, 2008, listed in this AD.
78-20-10: 78-20-10 MCDONNELL DOUGLAS: Amendment 39-3310. Applies to DC-10-10, -10F, -30, -30F, and -40 airplanes certificated in all categories.\n\n\tCompliance required within the next 1800 hours time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent the loss of related powered flight controls due to loss of fluid through brake return line failure accomplish the following:\n\n\t(a)\tRevise hydraulic system 1 and 3 by installing three check valves and, when applicable, new hydraulic piping, in accordance with McDonnell Douglas DC-10 Service Bulletin No. A29-113, Revision 2, dated April 4, 1978.\n\n\tNOTE: Service Bulletin A29-113, Revision 2, dated April 4, 1978, is the only version of this service bulletin suitable for compliance with paragraph (a) of this AD.\n\n\t(b)\tEquivalent modifications may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region.\n\n\t(c)\tSpecial 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 required by this AD.\n\n\tThis amendment becomes effective December 6, 1978.
92-25-07: 92-25-07 BRITISH AEROSPACE: Amendment 39-8422. Docket No. 92-NM-151-AD. Applicability: Model ATP series airplanes equipped with Lucas Generators, part number BA03303, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a generator malfunction, loss of engine oil, and engine shutdown or failure, accomplish the following: (a) Within 3 months after the effective date of this AD, replace the currently installed AC generator endplate fixing bolts, part number 79801316009, with longer bolts, part number 79801316013, in accordance with Lucas Aerospace Service Bulletin BA03303-24-3, dated June 12, 1992. (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 Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: 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 FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The replacement shall be done in accordance with Lucas Aerospace Service Bulletin BA03303-24-3, dated June 12, 1992. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; orat the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on January 12, 1993.
2022-01-05: The FAA is superseding airworthiness directive (AD) 2021-24- 06, which applied to certain Airbus Helicopters Model EC130T2 helicopters. AD 2021-24-06 required repetitive visual inspections of the rivets on the rear transmission shaft bearing support and of the local structure for cracking and missing, loose, or sheared rivets and accomplishment of applicable corrective actions. This AD retains those requirements and adds repetitive visual inspections of the rivet heads on the left-hand and right-hand sides of the rear transmission shaft bearing support, revises a corrective action, and adds a reporting requirement, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also revises the special flight permit limitation from AD 2021-24-06. This AD was prompted by an additional report of loose rivet heads on the outside face of the tail boom corner support. The FAA is issuing this AD to address the unsafe condition on these products.
2010-18-09: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 have been reports of engine surge, lack of response to Power Lever input and crew commanded engine shutdown on PW530A/ PW545A/PW545B engines powered aeroplanes. Investigation revealed engine intercompressor bleed valve/servo valve malfunction as the cause of the above problems, and that this problem is limited to engines fitted with low time (new or overhauled) bleed valve servo valves with either SB 30343 or 30404 incorporated. We are issuing this AD to prevent inflight loss of power of one or both of the engines and possible loss of control of the airplane.
67-13-03: 67-13-03 PILATUS: Amdt. 39-388, Part 39, Federal Register April 4, 1967. Applies to Model PC-6 Series Airplanes, Serial Numbers to 563. Compliance required as indicated. To prevent failure of rivets attaching the rudder control lever to the rudder post, accomplish the following: (a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 50 hours' time in service and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, visually inspect the rivets attaching the rudder control lever to the rudder post for defective or failed rivets. (b) If defective or failed rivets are found during the inspection required by (a), before further flight, replace the 3mm. diameter rivets with AN 470 AD 5-10 rivets, or FAA- approved equivalent. (c) The repetitive inspections required by (a) of this AD may be discontinued after the rudder control lever attachment is modified in accordancewith (b) of this AD. (Pilatus Aircraft Limited Service Bulletin No. 66 pertains to this subject.) This directive effective May 4, 1967.
2010-18-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: In-flight shutdown incidents have been reported on airplanes equipped with TAE 125 engines. Preliminary investigations showed that it was mainly the result of nonconforming disc springs (improper heat treatment) used in a certain production batch of the clutch. We are issuing this AD to prevent engine in-flight shutdown leading to loss of control of the airplane.
90-01-02: 90-01-02 PIPER (TED SMITH AEROSTAR, AEROSTAR, BUTLER AIRCRAFT COMPANY): Amendment 39-6517. Final copy of priority letter AD. Applicability: Piper Models PA-60-600 (turbocharged only), PA-60-601, PA-60-601P, PA-60-602P, and PA-60-700P (all serial numbers (S/N)) airplanes, and Ted Smith Aerostar (Butler Aircraft Company) Models 600 (turbocharged only), 601, 601A, 601B, and 601P (all S/N) airplanes, certificated in any category, except those airplanes incorporating Machen Supplemental Type Certificate (STC) SA980NM. Compliance: Required as indicated in the body of the AD, unless already accomplished. To alert the pilot of a nacelle overheat or fire condition which could result in damage to the wing structure, accomplish the following: (a) Prior to further flight after the effective date of this AD, modify the airplane by installing Piper Engine Fire Detection System Kit, Piper Part Number 764-158, in accordance with the instructions in Part II of the Piper Service Bulletin (SB) No. 920, dated August 7, 1989, and modify the Airplane Flight Manual/Pilot's Operating Handbook by inserting the appropriate supplement provided with the above kit. (b) Prior to further flight after the effective date of this AD, and thereafter at intervals not to exceed 50 hours time-in-service, accomplish the dismantling inspections and reinstallation of the exhaust tailpipe assembly as specified in Part I of Piper SB No. 920, dated August 7, 1989. If any discrepancies are found, prior to further flight repair the discrepancies in accordance with the above SB or appropriate Piper Maintenance Manual. (c) Airplanes may be flown in accordance with FAR 21.197 and FAR 21.199 to a location where this AD may be accomplished. (d) An alternate method of compliance or adjustment of the initial or repetitive compliance times which provides an equivalent level of safety may be used when approved by the Manager, Atlanta Aircraft Certification Office, FAA, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960, or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Priority letter AD 90-01-02 superseded AD 89-25-05, Amendment 39-6397. This amendment (39-6517, AD 90-01-02) becomes effective on March 1, 1990, as to all persons except those persons to whom it was made immediately effective by priority letter AD 90-01-02 issued on January 5, 1990, which contained this amendment.
78-22-09: 78-22-09 SHORT BROTHERS LTD.: Amendment 39-3328. Applies to Model 78-22 SD3-30 airplanes, S/Nos. 3001, 3002 and 3010 through 3016, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent possible collapse of the nose landing gear, prior to the accumulation of 50 landings after the effective date of this AD, replace restrictor assembly, P/N SD3-73-1209xA with a new restrictor assembly, P/N HTE.9950 in the nose landing gear "UP" line in accordance with Section 2, "Accomplishment Instructions", and Figure 1 of Short Brothers Ltd. Service Bulletin SD3-32-44, dated July 7, 1978, or an FAA-approved equivalent. This amendment becomes effective November 13, 1978.
96-06-04: This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron, A Division of Textron Canada, Ltd., (BHTC) Model 206A and 206B helicopters, that currently requires an inspection of the main transmission input driveshaft assembly (driveshaft) at intervals of 300 hours time-in-service (TIS); the application of a zinc chromate primer inspection visual aid; and, daily visual checks of the driveshaft. This amendment requires inspections of the driveshaft at intervals of 300 hours TIS; the application of a self-adhesive temperature indicator visual inspection aid ; and, preflight visual owner/operator (pilot) checks of the driveshaft. This amendment is prompted by recent studies that indicate self-adhesive temperature indicators are a more reliable means of detecting overheat conditions on grease-lubricated couplings than the zinc chromate primers currently in use. The actions specified by this AD are intended to prevent failure of the driveshaft due to coupling wear or overheating, which could result in loss of power to the main rotor and a subsequent forced emergency landing.
94-16-02: This amendment supersedes AD 79-25-05, which currently requires repetitively inspecting the existing aluminum vertical stabilizer forward attach fitting for cracks on Luscombe Model 8 series airplanes, and replacing any cracked parts. Steel fittings are now available that, when installed, will eliminate the need for repeated removal and inspection of the aluminum fitting, which could result in damage to the fastener holes. This action requires replacing the existing aluminum fitting with a steel vertical stabilizer forward attach fitting on Luscombe Model 8 series airplanes that have round-tipped vertical stabilizer installations. The actions specified by this AD are intended to prevent failure of the vertical stabilizer as a result of a cracked fitting, which could result in loss of control of the airplane.
2010-17-18: We are adopting a new airworthiness directive (AD) to supersede AD 2010-13-08, which applies to all Air Tractor, Inc. (Air Tractor) Models AT-802 and AT-802A airplanes. AD 2010-13-08 currently requires you to repetitively inspect (using the eddy current method) the two outboard fastener holes in both of the wing main spar lower caps at the center splice joint for cracks and repair or replace any cracked spar cap. Since we issued 2010-13-08, we evaluated service information issued by Air Tractor and determined we need to add inspections, add modifications, and change the safe life for certain serial number (SN) ranges. Consequently, this AD would retain the actions of AD 2010-13-08 and would add inspections, add modifications, and change the safe life for certain SN ranges. We are issuing this AD to detect and correct cracks in the wing main spar lower cap at the center splice joint, which could result in failure of the spar cap and lead to wing separation and loss of control of the airplane. \n\nDATES: This AD becomes effective on September 9, 2010. \n\tOn September 9, 2010, the Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Service Letter 80GG, revised December 21, 2005; Snow Engineering Co. Service Letter 284, dated October 4, 2009; Snow Engineering Co. Service Letter 281, dated August 1, 2009; Snow Engineering Co. Service Letter 245, dated April 25, 2005; Snow Engineering Co. Drawing Number 20995, Sheet 3, dated November 25, 2005; Snow Engineering Co. Drawing Number 20995, Sheet 2, Rev. D., dated November 25, 2005; and Snow Engineering Co. Drawing Number 20975, Sheet 4, Rev. A., dated January 7, 2009, listed in this AD. \n\tAs of April 21, 2006 (71 FR 19994, April 19, 2006), the Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Service Letter 240, dated September 30, 2004; and Snow Engineering Co. Process Specification 197, page 1, revised June 4, 2002; pages 2through 4, dated February 23, 2001; and page 5, dated May 3, 2002, listed in this AD. \n\tWe must receive any comments on this AD by October 12, 2010.
2010-18-01: 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: It has been found the possibility of right hand (RH) engine compressor stall after the Auxiliary Power Unit (APU) becomes the active bleed source for the left side. The most critical condition identified is: --Both engines close to idle (e.g.: descent phase); and --APU running; and --APU bleed button pushed in. In this condition, if the left hand (LH) engine fails, the APU bleed valve and the crossbleed valve may be both in the open position for a few seconds, [which] may lead to a backpressure in RH engine depending on APU bleed pressure. Such backpressure may cause an RH engine compressor stall, culminating in a dual engine failure. ** * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
82-16-11: 82-16-11 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-4435. Applies to Nomad Model N22B land planes only (S/Ns N22B-5 thru N22B-101 having horizontal stabilizer mass balance trim tabs except as noted in paragraphs A)(1) and A)(2) of this AD) certificated in any category. NOTE: Installation of horizontal stabilizer mass balance trim tabs in accordance with GAF Factory Modification No. N439 can be determined by visual inspection and verification that trim tab balance weights are installed on the inboard and outboard ends of each trim tab. COMPLIANCE: Required as indicated unless previously accomplished. A) To improve airplane controllability in severe turbulence when loaded near the aft C.G. limit, within the next 100 hours time-in-service after the effective date of this AD, accomplish the following: (1) Assemble and install a new horizontal stabilizer control rod and modified torque shaft in accordance with the instructions contained in GAF Nomad Service BulletinNMD 27-9 Revision 1 dated April 30, 1982. GAF Modification N211 is the same as this Service Bulletin. It has been incorporated by the manufacturer on S/Ns 26, 55, 90, 93, 95, 102 and subsequent and modification of these S/Ns to this paragraph is not required. (2) Remove the pulley mounting bracket at Station 399 and replace with redesigned bracketry to obtain direct cable/pulley alignment in accordance with GAF Nomad Service Bulletin NMD-27-15 dated December 23, 1981. GAF Modification N63 is the same as this Service Bulletin. It has been incorporated by the manufacturer on S/Ns 82 and subsequent and modification of those S/Ns to this paragraph is not required. (3) Remark the horizontal stabilizer trim indicator drum assembly by attaching a new label per the procedure as outlined in paragraph 2.Q. of GAF Nomad Service Bulletin NMD-27-9 dated March 10, 1982. (4) With the modification incorporated, verify that the horizontal stabilizer rigging angle has changed from 3-1/2 degrees plus or minus 1/2 degree stabilizer (not aircraft) nosedown to 3 degrees plus or minus 1/2 degree nosedown. For rigging instructions, see Maintenance Manual (MM) 27-40-00. (Service Bulletin NMD 27-9 Rev. 1 dated April 30, 1982, provides an alternate procedure.) NOTE: On completion of rigging, check controls for correct sense (direction) or operation and for full and free movement under all trim conditions. In particular, ensure that positive clearance exists between the tab and the horizontal stabilizer trailing edge structure through full range of stabilizer travel with full noseup (aircraft) trim selected. B) A special flight permit may be issued in accordance with FAR 21.197 to allow flight of the airplane to a location where this AD may be accomplished provided the aft C.G. does not exceed 35 percent MAC. C) An alternate means of compliance with this AD may be used if approved by the Chief, Honolulu Aircraft Certification Field Office, Northwest Mountain Region, Federal Aviation Administration, 300 Ala Moana Boulevard, Honolulu, Hawaii 96850. This amendment becomes effective on August 12, 1982.
96-03-04: This amendment adopts a new airworthiness directive (AD), applicable to various General Dynamics (Convair) airplanes, that requires revising the Airplane Flight Manual to require that the flight crew limit the flap settings during certain icing conditions and air temperatures. This amendment is prompted by reports indicating that incidents involving uncommanded pitch excursions have occurred due to ice contaminated tailplane stall (ICTS) that occurred during or following flight in icing conditions. If flap settings are increased for landing when conditions for ICTS are present, elevator control could be affected adversely and the airplane could descend uncontrollably. The actions specified by this AD are intended to ensure that the flight crew is advised of the potential hazard related to increasing the flap settings when conditions for ICTS are present, and the procedures necessary to address it.
92-25-13: 92-25-13 GENERAL DYNAMICS, CONVAIR DIVISION: Amendment 39-8427. Docket No. 92-NM-114-AD. Applicability: Model 240 [including originally Model T-29 (military) airplanes], 340, 440, and C-131 (military) airplanes; including those modified for turbo-propeller power (commonly referred to as Model 580, 600, and 640 series airplanes); all serial numbers; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent degradation of the structural capabilities of the airplane due to problems associated with corrosion, accomplish the following: (a) Except as provided by paragraph (b) of this AD, conduct the initial inspection for each area/component within a period of time, measured from a date one year after the effective date of this AD, not to exceed the applicable interval specified in the "Initial" column of the schedule on pages 5-10-1 through 5-10-6 of Chapter 5 of General Dynamics, Convair Division, Document Number ZS-340-2000, "Supplemental Corrosion Inspection Document," dated February 1992 (hereafter referred to as "the Document"). Thereafter, repeat the inspections at intervals not to exceed the applicable interval specified in the "Follow-on" column of the schedule on pages 5-10-1 through 5-10-6 of the Document. (b) As an alternative to the requirements of paragraph (a) of this AD: (1) Within one year after the effective date of this AD, revise the FAA-approved maintenance inspection program to include the inspections of the areas and components defined in the Document; or incorporate an equivalent program that is approved by the FAA. (2) After accomplishing the requirements of paragraph (b)(1) of this AD, conduct the initial inspection for each area/component at an interval not to exceed the applicable interval specified in the "Initial" column of the schedule on pages 5-10-1 through 5-10-6 of Chapter 5 of the Document. Thereafter, repeat the inspections at intervals not to exceedthe applicable interval specified in the "Follow-on" column of the schedule on pages 5-10-1 through 5-10-6 of Chapter 5 of the Document. (c) If corrosion is detected as a result of any inspection required by this AD, prior to further flight, repair in accordance with the General Dynamics/Convair Structural Repair Manual (SRM) for the pertinent airplane model; or, if an applicable repair method is not contained in the SRM, in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. (d) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles ACO, FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. NOTE: Information concerning the existence ofapproved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Los Angeles ACO. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The inspections shall be done in accordance with General Dynamics, Convair Division, Document Number ZS-340-2000, "Supplemental Corrosion Inspection Document," dated February 1992. (NOTE: Except for the title page of the document, no other pages of the document are dated.) 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 General Dynamics/Convair Division, Lindbergh Field Plant, P.O. Box 85377, San Diego, California 92138. Copies may be inspected at the FAA, Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at theLos Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on January 12, 1993.
92-06-06: 92-06-06 GENERAL DYNAMICS: Amendment 39-8186. Docket No. 91-NM-181-AD. Supersedes AD 88-22-06, Amendment 39-6006. Applicability: Applies to Model 340, 440, and C-131 (Military) series airplanes, all serial numbers, certificated in any category, including those modified for turbo-propeller power. Compliance: Required as indicated, unless previously accomplished. To ensure the continuing structural integrity of these airplanes, accomplish the following: (a) Within one year after November 21, 1988 (the effective date of Amendment 39-6006, AD 88-22-06), incorporate a revision into the FAA-approved maintenance inspection program which provides for inspection of the Principal Structural Elements (PSE) defined in Section 3 of General Dynamics, Convair Division, "Supplemental Inspection Document (SID), Model 340/440," Report No. ZS- 340-1000, dated November 14, 1986; Addendum I, dated April 14, 1987; Addendum II, dated May 4, 1987; and Addendum III dated August 4, 1987. The non-destructive inspection techniques set forth in the SID provide acceptable methods for accomplishing the inspections required by this AD. All inspection results (negative or positive) must be reported to General Dynamics, in accordance with the instructions in the SID. (b) Within six months after the effective date of this AD, incorporate a revision into the FAA- approved maintenance inspection program which provides for inspection of the Principal Structural Elements (PSE) defined in Section 3 of General Dynamics, Convair Division, "Supplemental Inspection Document (SID), Model 340/440," Report No. ZS-340-1000, Revision 1, dated April 15, 1991; including Addenda I, II, and III, all dated April 15, 1991. (c) Within six months after incorporation of General Dynamics, Convair Division, "Supplemental Inspection Document (SID), Model 340/440," Report No. ZS-340-1000, Revision 1, dated April 15, 1991; including Addenda I, II, and III, dated April 15, 1991; into the FAA-approved maintenance inspection program, as required by paragraph (b) of this AD, inspect all PSE's specified in that SID that have not been inspected within the 12 calendar years. The non-destructive inspection techniques set forth in that SID provide acceptable methods for accomplishing the inspections required by this AD. All inspection results (negative or positive) must be reported to General Dynamics, in accordance with the instructions in the SID. (d) Cracked structure detected during the inspections required by paragraph (a) or (c) of this AD must be repaired or replaced, prior to further flight, in accordance with General Dynamics, Convair Division, "Supplemental Inspection Document (SID), Model 340/440," Report No. ZS-340-1000, dated November 14, 1986; or Revision 1, dated April 15, 1991. (e) All of the information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq) and have been assigned OMB Control Number 2120-0056. (f) 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. (g) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may concur or comment and then send it to the Manager, Los Angeles ACO. (h) The program revision required by paragraph (a) of this AD shall be done in accordance with General Dynamics, Convair Division, "Supplemental Inspection Document (SID), Model 340/440," Report No. ZS-34-1000, dated November 14, 1986, including Addendum I dated April 14, 1987; Addendum IIdated May 4, 1987, and Addendum III, dated August 4, 1987. The incorporation by reference of that document was approved previously by the Director of the Federal Register as of November 21, 1988 (53 FR 41157, October 20, 1988), in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. The program revision required by paragraph (b) of this AD shall be done in accordance with General Dynamics, Convair Division, "Supplemental Inspection Document (SID), Model 340/440," Report No. ZS-340-1000, Revision 1, dated April 15, 1991; including Addenda I, II, and III, all dated April 15, 1991. The incorporation by reference of that document 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 General Dynamics/Convair Division, Lindberg Field Plant, P.O. Box 85377, San Diego, California 92138, Attention: Derek Trusk. These documents may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (i) This amendment becomes effective on April 22, 1992.
2010-18-05: We are adopting a new airworthiness directive (AD) for the products listed above that will supersede an existing AD. 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: A fatal accident occurred to a L-13 BLAN K sailplane, in which the main spar of the right wing failed near the root due to positive load. The right wing detached from the aircraft and the pilots lost control of the sailplane. The preliminary investigation has revealed that the fracture may have been due to fatigue. The AD 2010-0119-E required immediate inspection of the main spar at the root of the wing to detect fatigue cracking and the accomplishment of the relevant corrective actions as necessary. In addition, the AD 2010-0119-E imposed operational limitations. AD 2010-0122-E retained the requirements of AD 2010-0119-E, which is superseded, and extended the applicability to L-13 A BLAN K sailplanes. This AD requires actions that are intended to address the unsafe condition described in the MCAI.