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95-14-05: 95-14-05 MITSUBISHI HEAVY INDUSTRIES, LTD: Amendment 39-9297. Docket 94-NM- 167-AD. Applicability: All Model YS-11 and -11A airplanes, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (h) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. NOTE 2: This AD references MHI Publication No. YS-MR-301, "YS-11 Corrosion Control Program," dated November 1, 1993 (hereafter referred to as "the Document"), for basic tasks, definitions of corrosion levels, compliance times, and reporting requirements. In addition, this AD specifies inspection and reporting requirements beyond those included in the Document. Where there are differences between the AD and the Document, the AD prevails. NOTE 3: As used throughout this AD, the term "the FAA" is defined differently for different operators, as follows: For those operators complying with paragraph (a) of this AD, "the FAA" is defined as "the Manager of the Los Angeles Aircraft Certification Office (ACO)." For those operators operating under Federal Aviation Regulation (FAR) Part 121 or 129, and complying with paragraph (b) of this AD, "the FAA" is defined as "the cognizant Principal Maintenance Inspector (PMI)." For those operators operating under FAR Part 91 or 125, and complying with paragraph (b) of this AD, "the FAA" is defined as "the cognizant Maintenance Inspector at the appropriate FAA Flight Standards office." To preclude degradation of the structural capabilities of the airplane due to the problems associated with corrosion, accomplish the following: (a) Except as provided in paragraph (b) of this AD, within a date two years after the effective date of this AD, complete each of the basic tasks specified in Section 4.3 of the Document in accordance with the procedures specified in the Document and the schedule specified in Figure 5 of the Document. Thereafter, repeat each basic task at a time interval not to exceed the repeat interval specified in Section 4 of the Document for that task. NOTE 4: A "basic task," as defined in Section 4 of the Document, includes inspections; procedures for a corrective action, including repairs, under identified circumstances; application of sealants or corrosion inhibitors; and other follow-on actions. NOTE 5: Basic tasks completed in accordance with the Document before the effective date of this AD may be credited for compliance with the initial basic task requirements of this paragraph. NOTE 6: Where non-destructive inspection (NDI) methods are employed, in accordance with Section 4 of the Document, the standards and procedures used must be acceptable to the Administrator in accordance with FAR Section 43.13. (b) As an alternative to the requirements of paragraph (a) of this AD: Within one year after the effective date of this AD, revise the FAA-approved maintenance/inspection program to include the corrosion control program specified in the Document; or to include an equivalent program that is approved by the FAA. (1) Any operator complying with paragraph (b) of this AD may use an alternativerecordkeeping method to that otherwise required by FAR Section 91.417 or Section 121.380 for the actions required by this AD, provided it is approved by the FAA and is included in a revision to the FAA-approved maintenance/inspection program. (2) Subsequent to the accomplishment of the initial basic task, any extensions of repeat intervals specified in the Document must be approved by the FAA. (c) To accommodate unanticipated scheduling requirements, it is acceptable for a repeat interval to be increased by up to 10%, but not to exceed 6 months. The FAA must be informed, in writing, of any such extension within 30 days after such adjustment of the schedule. (d) (1) If, as a result of any inspection conducted in accordance with paragraphs (a) or (b) of this AD, Level 3 corrosion is determined to exist in any airplane area, accomplish either paragraph (d)(1)(i) or (d)(1)(ii) within 7 days after such determination: (i) Submit a report of that determination to theFAA and complete the basic task in the affected aircraft zones on all Model YS-11/-11A series airplanes in the operator's fleet; or (ii) Submit to the FAA for approval one of the following: (A) A proposed schedule for performing the basic tasks in the affected aircraft zones on the remaining Model YS-11/-11A series airplanes in the operator's fleet, which is adequate to ensure that any other Level 3 corrosion is detected in a timely manner, along with substantiating data for that schedule; or (B) Data substantiating that the Level 3 corrosion found is an isolated occurrence. NOTE 7: Notwithstanding the provisions of Section 1.3 of the Document, which would permit corrosion that otherwise meets the definition of Level 3 corrosion (i.e., which is determined to be a potentially urgent airworthiness concern requiring expeditious action) to be treated as Level 1 if the operator finds that it "can be attributed to an event not typical of the operator's usage of other airplanes in the same fleet," this paragraph requires that data substantiating any such finding be submitted to the FAA for approval. (2) The FAA may impose schedules other than those proposed, upon finding that such changes are necessary to ensure that any other Level 3 corrosion is detected in a timely manner. (3) Within the time schedule approved under paragraph (d)(1) or (d)(2) of this AD, accomplish the basic tasks in the affected aircraft zones of the remaining Model YS-11/-11A series airplanes in the operator's fleet. (e) If, as a result of any inspection after the initial inspection conducted in accordance with paragraph (a) or (b) of this AD, it is determined that corrosion findings exceed Level 1 in any area, within 60 days after such determination, implement a means, approved by the FAA, to reduce future findings of corrosion in that area to Level 1 or better. (f) Before any operator places into service any airplane subject to the requirements of this AD, a schedule for the accomplishment of basic tasks required by this AD must be established in accordance with paragraph (f)(1) or (f)(2) of this AD, as applicable: (1) For airplanes previously maintained in accordance with this AD, the first basic task in each aircraft zone to be performed by the new operator must be accomplished in accordance with the previous operator's schedule or with the new operator's schedule, whichever would result in the earlier accomplishment date for that task. After each basic task has been performed once, each subsequent task must be performed in accordance with the new operator's schedule. (2) For airplanes that have not been previously maintained in accordance with this AD, the first basic task for each aircraft zone to be performed by the new operator must be accomplished prior to further flight or in accordance with a schedule approved by the FAA. (g) Reports of Level 2 and Level 3 corrosion must be submitted at least every three months to Mitsubishi Heavy Industries, Ltd., in accordance with Section 3 of the Document. NOTE 8: Reporting of Level 2 and Level 3 corrosion found as a result of any opportunity inspections is highly desirable. (h) 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, Los Angeles Aircraft Certification Office (ACO), 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, Los Angeles ACO. NOTE 9: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. (i) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (j) Reports of inspection results required by this AD 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. (k) The actions shall be done in accordance with MHI Publication No. YS-MR-301, "YS-11 Corrosion Control Program," dated November 1, 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 Nihon Aeroplane Manufacturing, Toranomon Daiichi, Kotohire-Cho, Shiba, Minato-Ku, Tokyo, Japan. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, 3960 Paramount Boulevard, Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (l) This amendment becomes effective on August 7, 1995. FOR FURTHER INFORMATION CONTACT: William Roberts, Aerospace Engineer, Airframe Branch, ANM-120L, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone (310) 627-5228; fax (310) 627-5210.
2022-19-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A321-251N, A321-251NX, A321-252NX, A321-253N, A321-253NX, and A321-271NX airplanes. This AD was prompted by a determination that the quick release pin that is installed on the upper attachment of certain Smart HS-L41 and Smart HS-L42 lavatories is too short to lock on the bracket. This AD requires replacement of the quick release pin installed on the upper attachment of affected lavatories, 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.
2014-26-06: We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42-500 airplanes, and Model ATR72-212A airplanes. This AD was prompted by a report that, during an inspection of an airplane on the production line, interference was detected between the electrical harness and a bonding lead due to an incorrect installation of the affected bonding lead. This AD requires a detailed inspection for damage or incorrect routing of the bonding lead routing above the 120VU shelf, and if any damage or incorrect routing is found, repairing damage or modifying the bonding lead routing. We are issuing this AD to detect and correct installation of the bonding lead, which could cause arcing and chafing, and could possibly result in an uncontrolled fire.
2000-06-09: This amendment adopts a new airworthiness directive (AD), applicable to Turbomeca Arrius 1A series turboshaft engines, that requires installation of module TU63, which provides a separate supply of fuel for one of the 10 main injectors of the fuel injection system. This action is prompted by reports of unexpected power loss during test flights. The actions specified by this AD are intended to prevent unexpected power loss, which could result in an uncommanded in-flight engine shutdown, autorotation, and forced landing.
81-24-06: 81-24-06 TELEDYNE CONTINENTAL MOTORS: Amendment 39-4260. Applies to Models IO-520, TSIO-520 and GTSIO-520 (except GTSIO-520-F and K) engines equipped with engine driven fuel pumps serial numbers I0178XX through A0280XX, factory new or rebuilt engines which were assembled between September 1, 1978, through July 31, 1980, or fuel pumps which were replaced during that time. The first characters of the fuel pump serial numbers reflect the date of manufacture. The first letter designates the month of manufacture starting with "A" for January, "B" for February, etc. The second and third digits designate the day of build (01 thru 31). The fourth and fifth digits indicate the year of build. Subsequent digits indicate manufacturing sequence number of pump on a given day. Compliance required as indicated unless already accomplished. To prevent possible fuel leakage and potential fire hazard, accomplish the following: (a) Within 10 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 10 hours time in service until (b) is accomplished, visually check the fuel pump for evidence of fuel leaks from between the pump segments. If a leak is detected or fuel stains are present, (b) must be accomplished prior to further flight. (b) Within 50 hours time in service after the effective date of this AD, accomplish the following: (1) Remove safety wire from the four fuel pump through bolts. (2) Torque the through bolts evenly in diagonally opposite pairs to 30 in-lbs. ( 1 in-lb.). (3) Resafety wire through bolts. (4) Upon completion of the above steps, place mixture control in "idle cutoff," pressurize the fuel system with the aircraft boost pump, and inspect for fuel leaks. If a fuel leak still exists, overhaul or replace the pump as appropriate. (c) If fuel leaks were present before retorquing the bolts as required in paragraph (b), then during each of the next five preflights, place the mixture control in "idle cutoff," pressurize the fuel system with the aircraft boost pump and check for fuel leaks or evidence of fuel leaks. If evidence of a fuel leak exists, overhaul or replace the pump as appropriate. This paragraph does not apply if the fuel pump was overhauled or replaced due to compliance with paragraph (b). (d) The checks required by paragraphs (a) and (c) may be accomplished by a certificated pilot as authorized by FAR 43.3(h). (e) Make appropriate maintenance record entries. Upon submission of substantiating data through an FAA Aviation Safety Inspector, the Chief, Engineering and Manufacturing Branch may adjust the inspection intervals. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. Teledyne Continental Motors Service Bulletin M-80-26, Revision 1, applies to this subject. This amendment becomes effective November 23, 1981.
91-06-05: 91-06-05 CANADAIR, LTD.: Amendment 39-6852. Docket No. 90-NM-186-AD. Applicability: All Model CL-44D4 and CL-44J series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To ensure the continuing structural integrity of these airplanes, accomplish the following: A. Within six months after the effective date of this AD, incorporate a revision into the FAA-approved maintenance inspection program that provides for supplemental maintenance, inspections, replacement, and overhaul requirements of the significant structural items defined in Canadair Document RBD-44-100, "Supplemental Structural Inspection Program," Revision B, dated February 27, 1990. Inspection results, when a crack is detected, must be reported to Canadair. B. Cracked structure detected during the inspection required by paragraph A. of this AD must be repaired or replaced prior to further flight, in accordance with instructions in Canadair Document RBD-44-100, "Supplemental Structural Inspection Program," Revision B, dated February 27, 1990. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA, New England Region. NOTE: The request should be submitted directly to the Manager, New York Aircraft Certification Office, ANE-170, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, New York ACO. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Canadair, Ltd., P.O. Box 6087, Station A, Montreal,Quebec H3C 3G9, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, Northwest Mountain Region, 1601 Lind Avenue S.W., Renton, Washington; or at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment (39-6852, AD 91-06-05) becomes effective on April 8, 1991.
2014-26-02: We are adopting a new airworthiness directive (AD) for Airbus Helicopters (previously Eurocopter France) Model EC155B1 and AS 365 N3 helicopters with a certain automated flight control system (AFCS) and with a Garmin global positioning system (GPS) installed. This AD requires revising the Rotorcraft Flight Manual (RFM) to prohibit using the autopilot coupled with a Localizer/Instrument Landing System (LOC/ ILS) or Very High Frequency Omnidirectional Range (VOR) approach. This AD is prompted by a report of unpredictable and unexpected roll oscillations during coupled LOC or VOR approaches.This condition, if not corrected, could result in loss of helicopter control.
2014-26-03: We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aerosystems Model 340B airplanes. This AD was prompted by a report that the elevator position quoted in an aircraft maintenance manual is incorrect and a report that the trunnion at the lower part of the control column was installed incorrectly. This AD requires an inspection of the stick pusher rigging and an inspection of the installation of the trunnion and the stick pusher rigging, and corrective actions if necessary. We are issuing this AD to correct the rigging of the elevator position of the stick pusher to reduce the probability of a negative effect on the handling quality during stall, which could result in reduced controllability of the airplane.
2000-07-10: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-200B, -300, -400, -400D, and -400F series airplanes. This action requires repetitive inspections to detect cracking of fire extinguisher discharge tubes in certain engine struts, and corrective action, if necessary. For certain airplanes, this action also provides for a modification of the fire extinguisher discharge tubes, which constitutes terminating action for the repetitive inspections. This amendment is prompted by reports that cracked fire extinguisher discharge tubes have been found in the engine struts on certain airplanes. The actions specified in this AD are intended to detect and correct cracked fire extinguishing tubes in the engine struts. In the event of an engine fire, such cracked tubes could reduce the amount of fire extinguishing agent that can be delivered to the engine, and could result in a fire spreading from the engine to the wing of the airplane.
94-10-01: 94-10-01 Hartzell Propeller Inc.: Amendment 39-8908. Docket 94-ANE-05. Applicability: Hartzell Propeller Inc. Model HC-E4A-3A/E10950() propellers, except propellers with serial numbers HJ199 and greater, installed on but not limited to Beech Model 1900D aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent severe propeller vibration in flight and possible loss of propeller pitch control, accomplish the following: (a) Install new propeller blade pitch change knob twelve point flange head attachment bolts to replace the countersunk screws currently used, new preload plates, and new propeller blade pitch change knob brackets, in accordance with Hartzell Propeller Inc. Alert Service Bulletin (ASB) No. A190, dated January 17, 1994, as follows: (1) For propellers with 800 or more hours time in service (TIS) since new on the effective date of this airworthiness directive (AD), or 800 or more hours TIS since the new pitch change knob screws were last installed in accordance with Hartzell Propeller Inc. ASB No. A184, dated July 19, 1993, or Hartzell Propeller Inc. ASB No. A184(A), dated December 2, 1993, install within 50 hours TIS after the effective date of this AD. (2) For propellers with less than 800 hours TIS since new on the effective date of this AD, or less than 800 hours TIS since the new pitch change knob screws were last installed in accordance with Hartzell Propeller Inc. ASB No. 184, dated July 19, 1993, or Hartzell Propeller Inc. ASB No. A184(A), dated December 2, 1993, install prior to exceeding the later of: (i) 850 hours TIS since new; or (ii) 850 hours TIS since the new pitch change knob screws were last installed in accordance with Hartzell Propeller Inc. ASB No. 184, dated July 19, 1993, or Hartzell Propeller Inc. ASB No. A184(A), dated December 2, 1993; (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, Chicago Aircraft Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Chicago Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Chicago Aircraft Certification Office. (c) Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the aircraft to a location where the requirements of this AD can be accomplished. (d) The installation shall be done in accordance with the following service document: Document No. Pages Date Hartzell Propeller Inc. ASB No. A190 Total pages: 3. 1-3 January 17, 1994 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part51. Copies may be obtained from Hartzell Propeller Inc., One Propeller Place, Piqua, OH 45356-2634; telephone (513) 778-4200, fax (513) 778-4391. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on June 22, 1994.