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2020-15-16: The FAA is superseding Airworthiness Directive (AD) 2018-07- 08, which applied to certain Leonardo \n\n((Page 44460)) \n\nS.p.A (type certificate previously held by Agusta S.p.A) Model A109E, A109K2, A109S, AW109SP, A119, and AW119 MKII helicopters. AD 2018-07-08 required reducing the life limit of the tail rotor blade retention bolt and an inspection of that bolt for cracking, and replacement of any cracked bolt. This AD continues to require reducing the life limit of the tail rotor blade retention bolt, inspecting that bolt for cracking, and replacing any cracked bolt. In addition, this AD requires repetitive inspections of the tail rotor blade retention bolt for cracking. The FAA is issuing this AD to address the unsafe condition on these products.
85-23-02: 85-23-02 BOEING: Amendment 39-5165. Applies to Boeing Model 757 airplanes prior to line number 72, certificated in any category. Compliance is required within 21 days after the effective date of this amendment. To ensure proper door opening, accomplish the following, unless already accomplished: \n\n\tA.\tInspect the Number 4 left passenger door to verify proper hardware installation and install missing hardware, if necessary, in accordance with Boeing Service Bulletin 757- 52A0017 dated September 26, 1985, or later FAA-approved revisions. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\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 inspections and/or modifications required by this AD. \n\n\tAll persons affected by this AD who have not alreadyreceived copies of the service bulletin cited herein may obtain copies upon request from the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.\n \n\tThis amendment becomes effective November 18, 1985.
2003-18-11: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-V series airplanes. This action requires a one-time inspection of the balance weight installation of the left and right ailerons for correctly installed attachment components, and corrective action if necessary. This action is necessary to prevent separation of the balance weights of the aileron, which could result in jamming of the pilot's aileron control system, subsequent loss of aileron control, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
98-01-09: 98-01-09 AIRBUS INDUSTRIE: Amendment 39-10272. Docket 97-NM-333-AD. Applicability: Model A310 and A300-600 series airplanes equipped with General Electric CF6-80C2 engines on which Airbus Modification 7174, 7588, or 8246 has not been accomplished; and Model A310 and A300-600 series airplanes equipped with Pratt & Whitney PW 4000 engines on which Airbus Modification 7694 has not been accomplished; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification,alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To ensure that the flightcrew is provided with procedures for crosschecking and correcting certain primary power setting parameters of the Thrust Control Computer (TCC), accomplish the following: (a) Within 15 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) by inserting a copy of A300-600 or A310 Flight Manual Temporary Revision 4.03.00/18, 4.03.00/19, 4.03.00/20, or 4.03.00/21, all dated November 4, 1996; as applicable; into the AFM. NOTE 2: When the temporary revision specified in paragraph (a) of this AD has been incorporated into the general revisions of the AFM, the general revisions may be inserted in the AFM, provided the information contained in the general revision is identical to that specified in the applicable temporary revision cited in paragraph (a). (b) Accomplishment of modification of the TCC in accordance with the applicable Airbus service bulletins specified below constitutes terminating action for the requirement of paragraph (a) of this AD: -- A310-22-2025, dated April 18, 1989; -- A310-22-2027, dated June 8, 1990; -- A310-22-2031, dated September 2, 1991; -- A310-22-2035, Revision 1, dated July 13, 1994; -- A300-22-6010, dated April 18, 1989; -- A300-22-6011, dated June 8, 1990; -- A300-22-6017, dated September 2, 1991. After the modification has been accomplished, the Temporary AFM Revision may be removed from the AFM. (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, International Branch, ANM-116, 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, International Branch, ANM-116. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (d) 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. (e) The AFM revision shall be done in accordance with Airbus A300-600 Flight Manual Temporary Revision 4.03.00/18, dated November 4, 1996; Airbus Model A300-600 Flight Manual Temporary Revision 4.03.00/19, dated November 4, 1996; Airbus A310 Flight Manual Temporary Revision 4.03.00/20, dated November 4, 1996; or Airbus A310 Flight Manual Temporary Revision 4.03.00/21, dated November 4, 1996; as applicable.The modification, if accomplished, shall be done in accordance with Airbus Service Bulletin A310-22-2025, dated April 18, 1989; Airbus Service Bulletin A310-22-2027, dated June 8, 1990; Airbus Service Bulletin A310-22-2031, dated September 2, 1991; Airbus Service Bulletin A310-22-2035, Revision 1, dated July 13, 1994; Airbus Service Bulletin A300-22-6010, dated April 18, 1989; Airbus Service Bulletin A300-22-6011, dated June 8, 1990; or Airbus Service Bulletin A300-22-6017, dated September 2, 1991; as applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. NOTE 4: The subject of this AD is addressed in French airworthiness directive 97-110- 218(B), dated May 7, 1997. (f) This amendment becomes effective on January 22, 1998.
94-25-10: This amendment adopts a new airworthiness directive (AD) that is applicable to all Beech Model 400, 400A, 400T, and MU-300-10 airplanes, and all Mitsubishi Model MU-300 airplanes. This action requires a revision to the Airplane Flight Manual that provides pilots with special operating procedures during icing conditions. This amendment is prompted by the results of icing tests, which demonstrated that ice accumulations on the horizontal stabilizer may cause the airplane to pitch down at certain flaps settings. The actions specified in this AD are intended to prevent uncommanded nose-down pitch at certain flap settings during icing conditions.
2020-15-07: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG RB211-524G2-19, RB211- 524G2-T-19, RB211-524G3-19, RB211-524G3-T-19, RB211-524H2-19, RB211- 524H2-T-19, RB211-524H-36 and RB211-524H-T-36 model turbofan engines. This AD requires replacement of the low-pressure turbine (LPT) stage 1 disk before it reaches its new Declared Safe Cycle Limit (DSCL) or within 25 flight cycles after the effective date of this AD, whichever occurs later. This AD was prompted by a determination by the manufacturer that the affected LPT stage 1 disks cannot operate until their former published life limit. The FAA is issuing this AD to address the unsafe condition on these products.
84-01-02 R1: 84-01-02 R1 HUGHES HELICOPTERS, INC. (HUGHES HELICOPTERS): Amendment 39-4831. Applies to Hughes Helicopters, Inc., Model 369 series including Army YOH-6A, and OH6A helicopters certificated in all categories. Compliance is required prior to further flight, unless already accomplished. To prevent possible loss of control of rotor system in flight, accomplish the following: For Hughes Helicopters, Inc., Model 369 (Army YOH-6A), 369A (Army OH-6A) D, E, H, HE, HM, and HS helicopters with swashplate bearing assembly P/N 369A7OO3-3 installed after June 1, 1983; (a) Comply with paragraphs A through J of procedures section of Hughes Helicopters, Inc., Mandatory Service Information Notices DN-125, EN-12, and HN-191, as applicable, all dated December 23, 1983, or FAA approved equivalent. Model 369 series are to comply with Mandatory Service Information Notice HN-191 or FAA approved equivalent. (b) Replace deficient swashplate bearing assembly with serviceable unit.(c) Swashplate bearing assembly P/N 369A7003-3 with positively identified serial numbers 9000 through 9999 or with a 1/8-inch-diameter blue dot on the outer surface of the snap ring has been determined to contain the ball bearing cage and need not be reinspected. (d) Only subject bearing assembly positively identified as being S/Ns 9000-9999 or bearing assemblies with blue dot on the outer surface of snap ring or FAA approved equivalent bearing assemblies approved by the Manager, Western Aircraft Certification Office may be used as replacement swashplate bearing assemblies. Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Office, Hawthorne, California. This amendment becomes effective April 9, 1984, as to all persons except those persons to whom it was made immediately effective by priority mail AD 84-01-02, issued January 10, 1984, which contained this amendment.
2003-18-07: This amendment supersedes an existing airworthiness directive (AD), applicable to all Aerospatiale Model ATR42-200, -300, -320, and - 500 series airplanes; and all Model ATR72 series airplanes; that currently requires revising the Airplane Flight Manual (AFM) to modify procedures for calculating takeoff performance when Type II or IV de- icing or anti-icing fluids have been used. This amendment requires revising the existing AFM revision to correct the performance values for Model ATR-72 series airplanes and to provide an additional method of compliance for all airplanes. This amendment is prompted by issuance of mandatory continuing airworthiness information by a civil aviation authority. The actions specified by this AD are intended to ensure that the flightcrew is advised of the potential effects of Type II or IV de- icing or anti-icing fluids on the airplane's performance during takeoff, and to ensure that the flightcrew is advised of the revised performance calculations for takeoff to address these effects.
94-07-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that requires structural inspections of older airplanes. This amendment is prompted by reports of incidents involving fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their economic design service goal. The actions specified by this AD are intended to prevent degradation of the structural capabilities of the affected airplanes. This proposal relates to the recommendations of the Airworthiness Assurance Task Force assigned to review Model 727 series airplanes, which indicate that, to assure long term continued operational safety, various structural inspections should be accomplished.
97-26-03: 97-26-03 EUROCOPTER DEUTSCHLAND: Amendment 39-10246. Docket No. 97-SW-45- AD. Applicability: Model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1 helicopters, certificated in any category. NOTE 1: This AD applies to each helicopter 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 helicopters 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 (c) 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 helicopter from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To detects cracks in the main rotor mast flange (flange), which, if not detected, could result in failure of the flange and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, and thereafter at intervals not to exceed 100 hours time-in- service, visually inspect the flange in the ribbed area for cracks using a 5-power or higher magnifying glass in accordance with paragraphs 2.A.1. and 2.A.2. of the Accomplishment Instructions in Eurocopter Deutschland GmbH Alert Service Bulletin MBB-BK 117 No. ASB- MBB-BK 117-10-114, dated August 27, 1997. (b) If a crack is found as a result of the inspections specified in paragraph (a) of this AD, remove the cracked main rotor mast and replace it with an airworthy main rotor mast. (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, Rotorcraft Standards Staff, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Standards Staff. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff. (d) Special flight permits will not be issued. (e) The inspection shall be done in accordance with Eurocopter Deutschland GmbH Alert Service Bulletin MBB-BK 117 No. ASB-MBB-BK 117-10-114, dated August 27, 1997. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527. Copies may be inspected at the FAA, Office of Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. NOTE 3: The subject of this AD is addressed in Luftahrt-Bundesamt (Germany) AD 97-276, effective September 25, 1997. (f) This amendment becomes effective on December 31, 1997.