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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.
2020-14-09: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-8 and 737-9 (737 MAX) airplanes. This AD requires removing Kathon FP 1.5 biocide from the fuel tanks and engines, installing a fuel limitation placard, and revising the existing airplane flight manual (AFM) to prohibit operation of the airplane with Kathon FP 1.5 biocide in a fuel tank or engine. This AD was prompted by a report indicating that Kathon FP 1.5 biocide added to fuel and running through the engines can lead to significant engine anomalies. The FAA is issuing this AD to address the unsafe condition on these products.
2008-15-01: This amendment adopts a new airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that requires revising the airplane flight manual to include operational limitations for use of the autopilot, installing two placards that advise the flight crew to check the pitch trim before descent, and modifying the elevator trim system, which would terminate the requirements of the AD. The actions specified by this AD are intended to prevent pitch trim upsets if the pitch trim actuators jam or freeze, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2008-19-10: 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: It has been discovered that a risk of mechanical interference exists in the movement of the emergency landing gear by-pass selector, due to an insufficient functional gap between a floor panel attachment lug and the landing gear control button. This condition, if not corrected, causes mechanical interference which could result in a situation where, during emergency procedures, the landing gear cannot be extended. We are issuing this AD to require actions to correct the unsafe condition on these products.
94-06-08: This amendment adopts a new airworthiness directive (AD), applicable to Boeing Model 707 series airplanes, that requires the incorporation of a certain structural modification of the wing front spar lower chord. This amendment is prompted by an evaluation and recommendation by the Airworthiness Assurance Task Force to mandate the actions described in certain Boeing service bulletins as part of the "Aging Airplane Structural Modification Program." The actions specified by this AD are intended to prevent reduced structural integrity of the wing. The actions also reflect the FAA's decision that long term continued operational safety should be assured by actual modification of the airframe rather than repetitive inspections.
82-12-07: 82-12-07 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4397. Applies to all Model SA330 series helicopters certificated in all categories (Airworthiness Docket No. 82-ASW-9). Compliance is required within 100 hours' time in service after the effective date of this AD unless already accomplished. To detect damaged or cracked tail rotor transmission attachment bolts and to assure proper matching of the bolts and chamfered washers, accomplish the following: a. Remove the tail rotor transmission assembly and remove the three transmission- to-pylon attachment bolts. b. Inspect the bolts visually for dents under the heads, and for scores or fretting corrosion on the bolt stem or shank. Inspect the bolts for cracks using a magnetic particle or equivalent inspection method. c. Remove from further service bolts having dents under the head or scoring or fretting on the stem or shank, or bolts having a crack. d. Install bolts and washers andtail rotor transmission assembly in accordance with SA330 Puma Service Bulletin No. 01.34, dated October 19, 1981, subparagraph C(4)(b), or FAA approved equivalent. e. Equivalent means of complying with this AD must be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. Compliance with Puma Service Bulletin No. 01.34, dated October 19, 1981, satisfies this AD. This amendment becomes effective on July 8, 1982.
2020-14-06: The FAA is adopting a new airworthiness directive (AD) for Diamond Aircraft Industries Models DA 40, DA 40 F, and DA 40 NG airplanes. 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 deterioration of the fuel tank \nconnection hoses that could result in restriction of fuel flow leading to fuel starvation and reduced control of the airplane. The FAA is issuing this AD to require actions to address the unsafe condition on these products.
82-26-03: 82-26-03 PRATT & WHITNEY AIRCRAFT: Amendment 39-4523. Applies to Pratt & Whitney Aircraft models. JT9D-7, -7H, -7A, -7AH Engines prior to and including S/N 695827. JT9D-7F Engine S/Ns 695600 through 695614, S/N 702000, S/N 702001, S/N 702550 through 702557 and all engines prior to and including S/N 689635. JT9D-7J Engines prior to S/N 701697. NOTE: This directive does not apply to JT9D engines obtained by conversion which do not incorporate Service Bulletin 3741. Compliance required prior to February 27, 1983, unless already accomplished. To prevent fuel signal manifold cracking in operation replace manifold assembly P/N 711391 with assembly P/N 783391, bracket P/N 5003038-01, and clamp P/N ST1104-06 in accordance with Pratt & Whitney Aircraft Service Bulletin Number 5202, Revision 2, dated August 16, 1982, or later revision approved by the Manager, Engine Certification Branch, New England Region. All persons affected by this directive who have notalready received the referenced service bulletin from the manufacturer may obtain copies upon request to Pratt & Whitney Aircraft, Division of United Technologies Corporation, 400 Main Street, East Hartford, Connecticut 06108. This document may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. A historical file on this AD which includes the material in full is maintained by the FAA at the New England Region office. This amendment becomes effective on January 27, 1983.
85-08-04: 85-08-04 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39- 5037. Applies to all Models P 68, P 68B, P 68C, P 68C-TC and P 68 OBSERVER (Serial Numbers 001 thru 328) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To preclude the failure of the wing spar, within 100 hours time-in-service after the effective date of this AD or upon accumulating 2,100 hours time-in-service, whichever occurs later, and thereafter at intervals not exceeding 500 hours time-in-service since the last inspection, accomplish the following: (a) Visually inspect the front and rear wing spars for cracks as described in Part A of PARTENAVIA S/B No. 65, Revision 1, dated September 27, 1984. (b) If cracks are found as a result of any inspection required by Paragraph (a) of this AD, prior to further flight, accomplish the modification described in Part B of PARTENAVIA S/B No. 65, Revision 1, dated September 27, 1984. (c) The repetitive inspections required by Paragraph (a) of this AD may be discontinued when the modification in Paragraph (b) of this AD is accomplished. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on May 17, 1985.
94-05-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that requires incorporation of certain structural modifications. This amendment is prompted by an evaluation by the Model 727 Structures Working Group, comprised of aircraft operators, manufacturers, and the FAA. This Working Group evaluated Boeing service bulletins that must be included as part of the "Aging Airplane Structural Modification Program." The actions specified by this AD are intended to prevent degradation in the structural capabilities of the affected airplanes. The actions also reflect the FAA's decision that long term continued operational safety should be assured by actual modification of the airframe rather than repetitive inspections.
86-07-01: 86-07-01 ROLLS-ROYCE LIMITED: Amendment 39-5273. Applies to Rolls-Royce RB211-535E4 turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent an uncontained outer combustion case burst, inspect cases in accordance with the requirements of Rolls-Royce SB RB.211-72-7775, dated June 28, 1985, or FAA approved equivalent, as follows: (a) Inspect cases with 1,500 cycles in service or less since new on the effective date of this AD, prior to accumulating 1,550 cycles in service since new, and reinspect thereafter at intervals as specified in paragraph (c) below. (b) Inspect cases with greater than 1,500 cycles in service on the effective date of this AD, within the next 50 cycles in service after the effective date of this AD, and reinspect thereafter at intervals as specified in paragraph (c) below. (c) Reinspect cases previously inspected per paragraph (a) or (b) above as follows: (1) At intervals not to exceed 500 cycles in service if no cracks are present. (2) At intervals not to exceed 100 cycles in service if cracks of less than or equal to 0.5 inch in length are present. (3) At intervals not to exceed 50 cycles in service if cracks of greater than 0.5 inch but less than or equal to 1.5 inches in length are present. (d) Remove cases from service prior to further flight, if cracks of greater than 1.5 inches in length are present at inspection. NOTE: The crack length is defined as the length of a single crack or the cumulative length of multiple cracks, whichever is greater. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD. Aircraft may be ferried in accordance with the provisions of FAR Parts 21.197 and 21.199 to a base where the AD can be accomplished. Rolls-Royce SB RB.211-72-7775 dated June 28, 1985, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Rolls-Royce Limited, P.O. Box 31, Derby DE2 8BJ, England. This document also may be examined at the Office of the Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 85-ANE-25, Room Number 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday except Federal holidays. This amendment becomes effective on May 16, 1986.
2020-14-04: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd. & Co KG (RRD) Trent 1000-A, Trent 1000-AE, Trent 1000-C, Trent 1000-CE, Trent 1000-D, Trent 1000-E, Trent 1000-G, and Trent 1000-H model turbofan engines. This AD requires removing and replacing one or both affected engines, depending on whether the engine pairing combinations are compliant or non-compliant, as described in the service information. This AD was prompted by occurrences of in- service engine surges on affected RRD Trent model turbofan engines with a high number of intermediate pressure compressor (IPC) module flight hours since new (HSN) or cycles since new (CSN). The FAA is issuing this AD to address the unsafe condition on these products.
84-11-02 R2: 84-11-02 R2 BOEING: Amendment 39-4873 as amended by Amendment 39-4979, is further amended by Amendment 39-5117. Applies to the Model 767-200 series airplanes equipped with CF6 engines as listed in Boeing Service Bulletin 767-73-11 dated March 28, 1984, or later FAA approved revision, certificated in all categories. Compliance is required as indicated unless previously accomplished. To prevent failure of the engine fuel feed hose and engine flame out or engine nacelle fire, accomplish the following: \n\n\tA.\tWithin the next 200 landings or 30 days, whichever occurs first, after the effective date of this AD, and thereafter at intervals not to exceed 200 landings, inspect and replace, as necessary, the engine fuel feed hose in accordance with Boeing Service Bulletin 767-73-11 dated March 28, 1984, or later FAA approved revision. \n\n\tNOTE: It is anticipated that this AD will be amended when a new reinforced hose or equivalent terminating action is available. \n\n\tB.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tFor the purpose of this AD, and when approved by an FAA maintenance inspector, the number of landings may be computed by dividing each airplane's time in service by the operator's fleet average time from takeoff to landing for the aircraft type. \n\n\tD.\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\tE.\tInstallation of fuel feed hose P/N S332TO12-11 in accordance with Service Bulletin 767-73-11, Revision 2, dated May 25, 1984, or later FAA-approved revisions, terminates the repetitive inspection requirement of paragraph A., above. \n\n\tAmendment 39-4873 became effective June 4, 1984. \n\tAmendment 39-4979 became effective January 24, 1985. \n\tThis amendment 39-5117becomes effective September 16, 1985.
2003-18-09: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines. This AD requires removal from service of certain part numbers of high pressure (HP) compressor rotor shafts, based on a newly established reduced life limit. This AD is prompted by reports of HP compressor drums with small cracks in blade loading slots found at overhaul inspection. The HP compressor drums are an integral part of the HP compressor rotor shaft. We are issuing this AD to prevent possible uncontained HP compressor drum failure, which could result in damage to the airplane.
93-21-04: 93-21-04 CANADAIR: Amendment 39-8801. Docket No. 93-NM-177-AD. Applicability: Model CL-600-2B19 "Regional Jet" series airplanes; serial numbers 7003 and subsequent; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent temporary loss of all braking action, accomplish the following: (a) Within 3 days after the effective date of this AD, and thereafter at intervals not to exceed 3 days, lubricate with grease the sliding shaft of the input plunger of the brake control valve assembly in accordance with Canadair Regional Jet Alert Service Bulletin S.B.A601R- 32-016, dated October 14, 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, 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, if any, may be obtained from the New York ACO. (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 lubrication procedure shall be done in accordance with Canadair Regional Jet Alert Service Bulletin S.B.A601R-32-016, dated October 14, 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 Bombardier, Inc., Bombardier Regional Aircraft Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined 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. (e) This amendment becomes effective on February 4, 1994, to all persons except those persons to whom it was made immediately effective by priority letter AD 93-21-04, issued October 18, 1993, which contained the requirements of this amendment.
98-04-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-215-1A10 and CL-215-6B11 series airplanes. This action requires repetitive ultrasonic inspections to detect cracking of the lower caps of the wing front spar and rear spar, and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct cracking of the lower caps of the wing front spar and rear spar, which could result in reduced structural integrity of the airplane.