Results
2005-05-53 R1: The FAA is adopting a new airworthiness directive (AD) to revise emergency AD 2005-05-53 for The Cessna Aircraft Company (Cessna) Models 172R, 172S, 182T, and T182T airplanes. This AD contains the same information as emergency AD 2005-05-53 R1 and publishes the action in the Federal Register. It requires you to do a one-time detailed inspection of the flight control system, correct installations that do not conform to type design, and repair any damage. This AD is the result of flight control system problems found on airplanes within Cessna's control that could also exist on airplanes produced and delivered within a certain time period. We are issuing this AD to prevent loss of airplane control due to incorrect or inadequate rigging of critical flight systems. DATES: This AD becomes effective on March 21, 2005, to all affected persons who did not receive emergency AD 2005-05-53 R1, issued March 5, 2005. Emergency AD 2005-05-53 R1 contained the requirements of this amendment and became effective immediately upon receipt. As of March 21, 2005, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations. We must receive any comments on this AD by April 30, 2005.
2023-25-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318-112 airplanes; Model A319-115, -132, -133, -151N, -153N, and -171N airplanes; Model A320-211, -212, -214, -231, -232, - 251N, -252N, -253N, -271N, -272N, and -273N airplanes; and Model A321- 112 airplanes. This AD was prompted by a report that the fatigue life limit of the motoreductor installed on the on-board entrance stairs is not demonstrated for the complete airplane design service goal (DSG). This AD requires repetitive replacement of the motoreductor for onboard entrance stairs, and it limits the installation of affected parts under certain conditions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2023-26-01: The FAA is adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 190-300 and -400 airplanes. This AD was prompted by a report that the method for calculating level-off altitude by the computerized airplane flight manual (CAFM), may result in a non- conservative level-off height. This AD requires revising the existing airplane flight manual (AFM) to incorporate new CAFM versions as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2005-06-12: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SP, and 747SR series airplanes. That AD currently requires one-time inspections for cracking in certain upper deck floor beams and follow-on actions. This new AD expands the existing inspection area and requires inspecting fastener holes in certain areas of airplanes modified previously, and taking corrective actions if necessary. This action also defines new sources for instructions for repairs and post-modification/repair inspections. This AD is prompted by reports of fatigue cracking of the upper chord of certain upper deck floor beams. We are issuing this AD to find and fix cracking in certain upper deck floor beams, which could extend and sever floor beams adjacent to the body frame and result in rapid depressurization and loss of controllability of the airplane. \n\n\nDATES: This AD becomes effective April 25, 2005.The incorporation by reference of Boeing Service Bulletin 747- 53A2459, Revision 1, dated March 11, 2004, is approved by the Director of the Federal Register as of April 25, 2005. \n\n\tOn October 16, 2002 (67 FR 57510, September 11, 2002), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2459, dated January 11, 2001.
96-06-12: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 96-06-12 which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron, Inc. (Bell) Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47-K helicopters by individual letters. This AD requires a visual inspection of each tail rotor blade (blade) tip, abrasion strip, blade skin, and blade butt for corrosion or delamination. This amendment is prompted by reports that a number of Model 47 helicopter blades were manufactured using a clad aluminum alloy material instead of a bare aluminum alloy material. The actions specified by this AD are intended to prevent premature delamination or separation of the blade tip block or the abrasion strip, which could lead to failure of the blade and subsequent loss of control of the helicopter.
2023-25-11: The FAA is superseding Airworthiness Directive (AD) 2021-02- 18, which applied to all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, and CN-235-300 airplanes and Model C-295 airplanes. AD 2021-02-18 required repetitive inspections for cracking or broken rivets of certain left- and right-hand stringers and surrounding structure, and repair if necessary. This AD was prompted by a modification that was developed to reinforce the structure in the affected area, providing terminating action for the repetitive inspections required by AD 2021-02-18. This AD continues to require certain actions in AD 2021-02-18 and requires the new terminating action for the repetitive inspections, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
91-12-09: 91-12-09 GENERAL ELECTRIC COMPANY: Amendment 39-7020. Docket No. 91-ANE- 11. Applicability: General Electric Company (GE) CF6-6 series turbofan engines installed on, but not limited to, McDonnell Douglas DC10-10 aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent an uncontained engine failure and damage to the aircraft, accomplish the following: (a) Eddy current inspect in accordance with GE CF6-6 Service Bulletin (SB) 72- 947, Revision 4, dated February 8, 1991, the bore forward corner of stage 1 fan disks identified by serial number (S\N) in Tables 2, 3, and 3 Addendum of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991, as follows: (1) For disks which have not received an eddy current inspection in accordance with the Accomplishment Instructions of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991, in accordance with the following schedule: (i) Within the next 100 cycles in service (CIS) after the effective date of this AD for those disks which on the effective date of this AD have accumulated 1,250 CIS or greater since accomplishing the immersion ultrasonic inspection of AD 89-20-01 R1, Amendment 39-6411 (54 FR 51015; December 12, 1989). (ii) Within the next 100 CIS after the effective date of this AD or prior to accumulating 1,250 CIS since accomplishing the immersion ultrasonic inspection of AD 89-20-01 R1, whichever comes later for those disks which on the effective date of this AD have accumulated less than 1,250 CIS since the immersion ultrasonic inspection. (2) For those disks which on the effective date of this AD have received an eddy current inspection in accordance with the Accomplishment Instructions of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991, in accordance with the following schedule: (i) Within the next 100 CIS after the effective date of this AD for those disks which on the effective date of this AD have accumulated 1,500 CIS or greater since accomplishing the immersion ultrasonic inspection of AD 89-20-01 R1. (ii) Within the next 100 CIS after the effective date of this AD or prior to accumulating 1,500 CIS since accomplishing the immersion ultrasonic inspection of AD 89-20-01 R1, whichever comes later, for those disks which on the effective date of this AD have accumulated less than 1,500 CIS since accomplishing the immersion ultrasonic inspection. (b) Thereafter, eddy current inspect the bore forward corner of stage 1 fan disks which meet the acceptance criteria of paragraph 2.B.(2)(c) of the Accomplishment Instructions of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991, at intervals not to exceed 500 CIS since last eddy current inspection. (c) Remove from service prior to further flight and replace with a serviceable part, disks inspected in accordance with paragraphs (a) and (b) of this AD, which do not meet the acceptance criteria of paragraph 2.B.(2)(c) of the Accomplishment Instructions of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991. (d) Remove from service all stage 1 fan disks identified by S/N in Tables 2, 3, and 3 Addendum of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991, at the next shop visit but no later than 2,500 CIS since immersion ultrasonic inspection or June 30, 1992, whichever occurs first. (e) For the purpose of this AD, "shop visit" is defined as the induction of the engine into the shop for any reason. (f) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (g) Upon submission of substantiating data by an owner or operator through an FAA (maintenance, avionics, or operations) Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedules specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803- 5299. The inspections shall be done in accordance with the following General Electric service document: Document No. Page No. Issue Date CF6-6 SB 72-947 1 thru 13 Rev. 4 Feb. 8, 1991 Total Pages: 13 This incorporation was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to General Electric Company, Technical Publications Department, 1 Neumann Way, Cincinnati, Ohio 45215. This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. This amendment (39-7020, AD 91-12-09) becomes effective on June 27, 1991.
2023-24-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports that the nose wheel steering selector valve (SSV) can be slow to deactivate under low temperature conditions. This AD requires replacing the affected SSV with a re-designed SSV that has an improved response time. The FAA is issuing this AD to address the unsafe condition on these products.
90-01-05: 90-01-05 BOEING: Amendment 39-6443. Docket No. 89-NM-167-AD. Applicability: Model 767 series airplanes, as listed in Boeing Service Bulletin 767-25-0123, dated May 25,1989, certificated in any category. \n\n\tCompliance: Required within the next 90 days after the effective date of this AD, unless previously accomplished.\n \n\tTo ensure proper arming of the emergency evacuation slide mechanism for entry/service doors and to preventa false armed indication, accomplish the following: \n\n\tA. For Group 1 airplanes, perform the inspection and rework of the acoustical seal for entry/service doors in accordance with paragraph III., Part B., of Boeing Service Bulletin 767-25-0123, dated May 25, 1989, or Revision 1, dated September 14, 1989. \n\n\tB. For Group 2 airplanes, rework the acoustical seal for entry/service doors in accordance with paragraph III., Part C., of Boeing Service Bulletin 767-25-0123, dated May 25, 1989, or Revision 1, dated September 14, 1989. \n\n\tC. An alternate means ofcompliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tD. 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.\n\n This amendment (39-6443, AD 90-01-05) becomes effective on February 5, 1990.
2023-25-04: The FAA is superseding Airworthiness Directive (AD) 2022-08- 04, which applied to all Airbus SAS Model A300 series airplanes. AD 2022-08-04 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. Since the FAA issued AD 2022-08-04, the FAA has determined new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions of AD 2022-08-04, and requires new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2005-06-11: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-100, -100B, -100B SUD, -200B, and -300 series airplanes; and Model 747SR and 747SP series airplanes. That AD currently requires repetitive inspections to detect fatigue cracking in the upper deck floor beams located at certain body stations, and repair, if necessary. This new AD lowers the threshold for the existing inspections and requires new repetitive inspections of previously repaired areas, and repair if necessary. This AD is prompted by the results of an additional detailed analysis that indicate fatigue cracks can initiate sooner than has previously been observed. We are issuing this AD to prevent failure of the upper deck floor beams at certain body stations due to fatigue cracking, which could result in rapid decompression and reduced controllability of the airplane.
2023-24-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A310 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
78-16-04: 78-16-04 CESSNA: Amendment 39-3273. Applies to Model 336 airplanes. Compliance: Required as indicted, unless already accomplished. To provide loading instructions which will limit aircraft loading to an acceptable center of gravity, within the next 100 hours time-in-service after the effective date of this AD, accomplish the following: A) Modify the Cessna weight and balance data included in the Model 336 airplane as follows: 1. Modify the center of gravity moment envelope on Page 1 by drawing a straight line between the two points (3900 pounds - 548,730 pounds-inches and 2500 pounds - 351,751 pounds-inches) and cover or obliterate the lines establishing the right side of the existing center of gravity moment envelope. 2. Modify the normal category center of gravity limits chart on Page 2 by drawing a vertical line at the 140.7 inches aft of datum point from the 2500 to 3900 pounds lines and cover or obliterate the lines establishing the right side of the existing normal category center of gravity limits envelope. B) Below the existing capacity placard located on the baggage compartment door install a permanent placard which reads as follows: "CAUTION - AFT CENTER OF GRAVITY LIMITATION MAY RESTRICT LOADING OF THIS COMPARTMENT TO LESS THAN 365 POUNDS" and operate the aircraft in accordance with this limitation. This placard should be fabricated of .032 inch minimum thickness aluminum or plastic material with minimum 3/16-inch high stamped or engraved letters and installed using threaded or rivet type fasteners. C) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective October 14, 1978.
2005-06-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This AD requires modification of certain auxiliary power unit (APU) alternating current (AC) generators. This AD is prompted by a report of an explosion in the APU compartment, which blew open the compartment doors. We are issuing this AD to prevent oil vapor leakage from the APU AC generator, which, when combined with an electric arc at the electrical receptacle, could result in a fire or explosion in the APU compartment during flight.
2023-25-08: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model A109E, A109S, AW109SP, A119, and AW119 MKII helicopters. This AD was prompted by multiple reports of excessive axial play on the ball bearing of the lower half of the main rotor (MR) rotating scissor assembly. This AD requires one-time scissor coupling and axial play inspections and repetitive quantitative axial play inspections and, depending on the results, additional inspections and replacing certain parts. This AD also requires reporting information and prohibits installing certain parts unless certain inspections have been accomplished. These requirements are specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2023-25-14: The FAA is superseding Airworthiness Directive (AD) 2022-27- 09, which applied to certain Airbus Helicopters Model EC130T2 helicopters. AD 2022-27-09 required repetitively inspecting the vibration level on the tail rotor drive shaft and, depending on the results, taking corrective action. AD 2022-27-09 also required reporting information and prohibited installing certain rotor drive shafts unless the inspection was done. Since the FAA issued AD 2022-27- 09, Airbus Helicopters revised its service information to update the procedures for inspecting that vibration level, reduce an allowable vibration level, and clarify when a balance correction may be accomplished. This AD was prompted by the determination that a certain vibration measurement tool was providing unexpected results and therefore the threshold must be revised. This AD continues to require certain actions in AD 2022-27-09 and also revises the procedures for inspecting the vibration level on the tail rotor drive shaft and depending on these results, requires replacing certain parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
76-06-06: 76-06-06 PIPER AIRCRAFT CORPORATION: Amendment 39-2547. Applies to Piper Model PA-12 airplanes certificated in all categories equipped with Piper Model PA-14 wing flaps in accordance with STC No. SA231AL. NOTE: STC No. SA231AL incorporates Rodney E. Schaeffer Drawing PA-12-1001, Revision "A", dated September 15, 1975. Compliance is required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To prevent a loss of flap control, inspect the flap control system to ensure that six flap control pulley guards are installed in accordance with the Rodney E. Schaeffer Drawing PA-12- 1001, Revision "A", dated September 15, 1975, or an FAA approved equivalent. Install those pulley guards which are found to be missing. NOTE: Copies of the Rodney E. Schaeffer Drawing PA-12-1001, Revision "A", dated September 15, 1975, may be obtained from Rodney E. Schaeffer, 1253 Cramer, Wichita, Kansas, 67212. This drawing may also be examined at the FAA Alaska Region, 632 Sixth Avenue, Anchorage, Alaska 99501, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. This amendment becomes effective on March 25, 1976.
2023-23-11: The FAA is superseding Airworthiness Directive (AD) 2019-12- 07, which applied to all Airbus SAS Model A318-111, -112, -121, and - 122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2019-12-07 required replacement of both main landing gear (MLG) shock absorbers, an identification of affected MLG sliding tubes; inspection of affected chromium plates and sliding tube axles for damage; and replacement of the sliding tube if necessary. AD 2019- 12-07 also required repetitive inspections of affected MLG sliding tubes for cracking, replacement of cracked MLG sliding tubes, and eventual replacement of each affected MLG sliding tube. This AD continues to require the actions specified in AD 2019-12-07 and requires repetitive inspections of additional MLG sliding tubes, replacement if necessary, and eventual replacement of the additional MLG sliding tubes. This AD also extends the repetitive inspection interval. This AD also prohibits the installation of affected parts under certain conditions. This AD was prompted by the FAA's determination that additional MLG sliding tubes are affected by the unsafe condition and that the repetitive inspection interval may be extended. The FAA is issuing this AD to address the unsafe condition on these products.
2005-05-19: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 727 airplanes. That AD currently requires repetitive detailed inspections to detect cracking, corrosion, and existing stop-drilled repairs of cracking in the upper chord of the rear spar of the wing; and repair if necessary. This new AD requires new repetitive inspections to detect cracks, corrosion, minor surface defects, and existing stop-drilled repairs of cracks in the upper and lower chords of the front and rear spars of the wing; and repair if necessary. This AD is prompted by our determination that further rulemaking action is necessary to require additional actions specified in the referenced service bulletin. We are issuing this AD to prevent structural failure of the wing and fuel leaks in the airplane due to stress corrosion cracking of the wing spar chords.
2023-24-05: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (604 Variant) airplanes. This AD was prompted by sleeve loops on some passenger oxygen mask lanyards that had improper crimping and unsealed ends. This AD requires an inspection of the passenger oxygen mask lanyards and replacement of defective oxygen mask lanyards. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
90-09-08: 90-09-08 IPECO: Amendment 39-6486. Docket No. 89-ANE-28. \n\n\tApplicability: IPECO TSO-C39a crew seats, as follows: \n\n\nSeat Part Number\nSerial no. effectivity\nInstalled in but not limited to\n3A090-0021-01-2\nup to and including \nBoeing 737\n3A090-0022-01-2\n11009\n\n3A090-0021-02-2\n\n\n3A090-0022-02-2\n\n\n\n\n\n3A090-0019-01-1\nup to and including\nBoeing 737\n3A090-0020-01-1\n11115 \n\n\n\n\n3A090-0015-01-1\nup to and including\nBoeing 757, 767\n3A090-0016-01-1\n11143\n\n\n\n\n3A090-0025-01-1\nup to and including\nBoeing 757, 767\n3A090-0026-01-1\n11054\n\n\n\n\n3A090-0053-01-1\nup to and including\nBoeing 747-400\n3A090-0054-01-1\n11105\n\n\n\n\n3A090-0027-01-1\nup to and including\nBoeing 747\n3A090-0028-01-1\n11072\n\n\n\n\n3A102-0003-01-1\nup to and including\nBoeing 747-400\n\n11041\n\n\n\n\n3A090-0055-01-1\nup to and including\nBoeing 747-400\n3A090-0056-01-1\n11062\n\n\n\n\n3A103-0003-01-1\nup to and including\nBoeing 747-400\n\n10607 \n\n\n\n\n3A090-0017-01-1\nup to and including\nBoeing 747\n3A090-0018-01-1\n10100\n\n\n\n\n3A090-0065-01-1\nup to and including\nBoeing 747-400\n3A090-0066-01-1\n11635\n\n\n\n\n3A118-0003-01-1\nup to and including\nDeHavilland\n3A118-0004-01-1\n11580\nDHC-7 and DHC-8\n\n\tCompliance: Required as indicated, unless already accomplished. To prevent failure of the seat back structure, accomplish the following: \n\n\t(a)\tWithin the next 30 days after the effective date of this AD, unless already accomplished within the last 100 days and, thereafter, at intervals not to exceed 130 days from the last inspection, visually inspect the seat assembly as follows: \n\n\t\t(1)\tRemove seat pan cushion and back cushion from the seat assembly. Adjust the lumbar mechanism to the fully up, fully back position. Recline seat back to full recline. \n\n\t\t(2)\tBy looking through the lightening holes in the pan and back structure with a flashlight, examine the base of the back structure in the area where it attaches to the reclining mechanism. This area can be identified by the bracket at the base of the back structure. Return the seat back to its upright position and also examine the base of the back structure from the rear of the seat. \n\n\t\t(3)\tIf any crack or deformation of the seat back structure is found, replace the seat assembly with a serviceable unit before further flight. \n\n\t\t(4)\tWhen the repairs and modifications required by paragraph (b) have been accomplished, the repetitive visual inspections may be terminated. \n\n\t(b)\tWithin the next 15 months after the effective date of this AD, perform the repairs and modifications of the IPECO seat assemblies in accordance with the following service bulletins (SB): \n\n\nIPECO SB No.\nApplicable IPECO\nseat part numbers \nA001-25-29\n3A090-0021-01-2 \n\n3A090-0022-01-2 \n\n3A090-0021-02-2 \n\n3A090-0022-02-2 \n\n\nA001-25-30\n3A090-0019-01-1 \n\n3A090-0020-01-1 \n\n\nA001-25-31\n3A090-0015-01-1 \n\n3A090-0016-01-1 \n\n\nA001-25-32\n3A090-0025-01-1 \n\n3A090-0026-01-1 \n\n\nA001-25-33\n3A090-0053-01-1 \n\n3A090-0054-01-1\n\n\nA001-25-34\n3A090-0027-01-1 \n\n3A090-0028-01-1 \n\n\nA001-25-35\n3A102-0003-01-1 \n\n\nA001-25-36\n3A090-0055-01-1 \n\n3A090-0056-01-1 \n\n\nA001-25-37\n3A103-0003-01-1 \n\n\nA001-25-38\n3A090-0017-01-1 \n\n3A090-0018-01-1 \n\n\nA001-25-39\n3A090-0065-01-1 \n\n3A090-0066-01-1 \n\n\nA001-25-40\n3A118-0003-01-1 \n\n3A118-0004-01-1 \n\n\t(c)\tAircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. \n\n\t(d)\tUpon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. \n\n\tThe repair and modification procedures shall be done in accordance with IPECO SB No. A001-25-29, Issue No. 2, pages 1 and 2 dated April 28, 1989, and pages 3 through 18 inclusive, dated August 25, 1988; IPECO SB No. A001-25-30, Issue No. 2, pages 1 and 2 dated April 28, 1989, and pages 3 through 18 inclusive, dated September 9, 1988; and IPECO SB Nos. A001-25-31 through A001-25-40 inclusive, all Issue No. 2, pages 1 and 2 dated April 28, 1989, and pages 3 through 18 inclusive, dated September 13, 1988. 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 IPECO Inc., 15201 South Prarie Avenue, Lawndale, California 90260. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office ofthe Federal Register, 1100 L Street, NW, Room 8301, Washington, DC 20591. \n\n\tThis amendment (39-6486, AD 90-09-08) becomes effective on May 29, 1990.
2023-22-18: The FAA is adopting a new airworthiness directive (AD) for all Diamond Aircraft Industries Inc. Model DA 62 airplanes. This AD was prompted by reports of baggage nets installed with defective buckles, which may result in failure of the baggage net to restrain the baggage or cargo, which could lead to injury to the occupants in the case of an emergency landing. This AD requires identifying and replacing the affected part. The FAA is issuing this AD to address the unsafe condition on these products.
2005-06-04: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. The existing AD currently requires repetitive inspections of the left and right engine throttle control gearboxes for wear, and corrective action if necessary. The existing AD was prompted by numerous failures of the engine throttle control gearbox, some of which resulted in an in-flight engine shutdown. This AD adds airplanes to the applicability of the existing AD. We are issuing this AD to prevent excessive wear of the gearboxes and subsequent movement or jamming of the engine throttle; movement of the throttle towards the idle position brings it close to the fuel shut-off position, which could result in an in-flight engine shutdown. DATES: Effective April 1, 2005. On July 9, 2004 (69 FR 35239, June 24, 2004), the Director of the Federal Register approved the incorporation by reference of Bombardier Service Bulletin 601R-76-019, Revision `A,' dated February 19, 2004. On March 25, 2004 (69 FR 11293, March 10, 2004), the Director of the Federal Register approved the incorporation by reference of Bombardier Service Bulletin 601R-76-019, dated August 21, 2003. We must receive any comments on this AD by May 16, 2005.
2023-23-02: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440), CL-600-2C10 (Regional Jet Series 700, 701 & 702), CL-600-2C11 (Regional Jet Series 550), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of power control unit (PCU) rod end fractures due to pitting corrosion, and a determination that new or more restrictive airworthiness limitations are necessary. This AD requires, for certain airplanes, revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD also requires accomplishing certain aircraft maintenance manual (AMM) tasks and corrective actions following short-term or long-term storage. The FAA is issuing this AD to address the unsafe condition on these products.
78-20-09: 78-20-09 GULFSTREAM AMERICAN CORPORATION (GAC) (FORMERLY GRUMMAN AMERICAN AVIATION CORPORATION (GAAC): Amendment 39-3309. Applies to Model GA-7 serial numbers GA7-001 through GA7-0039. Compliance is required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent a hazard to the airplane caused by excessive force required to move the fuel selector valve from one position to another position, accomplish the following: (1) Remove the two original fuel selector valves, Gerdes Part Number A980-5, and install two new improved fuel selector valves, Gerdes Part Number A980-7, utilizing the procedures and precautions contained in GA-7 Maintenance Manual, Section 28-2-1, pages 202 and 204, Fuel Selector Valve Removal, and Fuel Selector Valve Installations. (2) After the Gerdes Part Number A980-7 fuel selector valve installation has been completed in accordance with the above Maintenance Manual procedures, set each selector to ON, OFF, and CROSSFEED positions while observing each selector valve to ensure that the valve operates correctly, no fuel leakage occurs, and a positive detent is noted at each position selected on the valve. (Gulfstream American Service Bulletin No. ME-10 dated August 16, 1978 applies to this same subject.) This amendment becomes effective October 9, 1978.