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2001-07-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Hartzell Propeller Inc. Y-shank series propellers, identified by hub serial numbers, that were returned to service by Brothers Aero Services Company, Inc. (BASCO). This AD requires maintenance actions amounting to an overhaul of affected propellers. This amendment is prompted by reports of propellers returned to service by BASCO as overhauled that had numerous unsafe conditions after being returned to service by BASCO. The actions specified by this AD are intended to prevent propeller failure of the propellers returned to service by BASCO, and possible loss of airplane control.
82-05-01 R2: 82-05-01 R2 EMPRESA BRASILEIRA DE AERONAUTICA S/A (EMBRAER): Amendment 39-4325 as amended by Amendment 39-4455 is further amended by Amendment 39- 4747. Applies to Models EMB-110P1 and EMB-11OP2 airplanes, certificated in any category. COMPLIANCE: Required as indicated, unless already accomplished: To prevent failure of wing flap actuators, accomplish the following: A) Within the next 50 hours time-in-service after March 1, 1982, and thereafter at intervals not to exceed 1500 landings or 12 months time-in-service, whichever occurs first. 1. Prepare the wing flap actuators for inspection by extending the flaps to the fully-extended position. CAUTION Make sure that the Battery Switch is "Off" and that flaps are not inadvertently operated while the flap actuators are being serviced. 2. Disconnect each wing flap from the actuator lug by removing the cotter pin, nut, washer and attaching bolt. CAUTION When removing the attaching bolt, provide a support for flap to prevent its rotation and possible damage. 3. Remove the safety wire and four retaining screws from the outer cover of the actuator. 4. Slide the inner and outer covers toward the reduction gearbox to expose the threaded shaft. Clean the shaft in accordance with good aircraft practices. 5. While manually retracting and extending the threaded shaft, determine: a. General condition of the shaft. b. Movement of the shaft while turning it by hand - must be free and smooth. c. Longitudinal motion of the shaft in the ballscrew/nut assembly - play must be practically undetectable by handling manually. d. That the transverse motion of the ballscrew/nut assembly, measured at the rod end of the shaft, does not exceed .20 inch (5 mm), when the shaft is fully extended, near the middle of the course, and retracted. e. General condition of the ballscrew/nut, its attachment to the main carrier tube, the fastening of the ball-return tube and the general condition of its clamp in the D2246-3 and D2246-4 actuators, and safety of the ball-return cover in the D2246-5, D2246-6, D2246-31 and D2246-41 actuators. For access, it is necessary to remove the plastic strip EEMCO P/N A12139 from the primary cover (if the plastic strip is not damaged during removal, it may be reused). (i) With the jackscrew extended, move both covers to the rod end, leaving the ball nut completely exposed. (ii) Remove all dirt and grease from the ball nuts. (iii) Check the ball-return tube fastening clamp for general condition and proper safety by attempting to move it longitudinally and rotationally. Also check the general condition and safety of the ball-return tube and for security of the ballscrew. Any indication of looseness of the ball-return tube fastening clamp or the ball-return tube is cause for replacement of the actuator. (iv) Reinstall the plastic strip P/N A12139.6. Inspect for damage and wear of sealing rings in the inner and outer actuator covers, used to protect the ballscrew and threaded shaft from moisture and dirt. 7. If any of the items inspected in Sections 5 and 6 above are not satisfactory, repair or overhaul the actuator in accordance with EEMCO Service Bulletin 27-53- 02, or replace, as necessary. 8. Lubricate the actuator and reduction gearbox: a. Remove the safety wire and upper screw where the actuator joins reduction gearbox. b. Manually extend the jackscrew to the mechanical stop. c. Inject MIL-G-23827 grease into the gearbox through the screw hole to fill the gearbox and main actuator tube. d. Temporarily install the gearbox upper screw. e. Manually retract the jackscrew until fresh grease appears between the ball nut and jackscrew. f. Remove the gearbox upper screw again to remove the excess grease by continuing to manually retract the jackscrew to the mechanical stop.g. Install the upper screw in the gearbox; safety screw with lockwire. h. Clean the main actuator tube exterior by removing all grease to prevent dust deposits. i. Lubricate the extended jackscrew by brush-daubing it with MIL- G-23827 grease. 9. Slide the outer cover aft to the proper position on the rod end cap. 10. Install the four retaining screws and safety wire. 11. Reconnect the flap to the actuator lug by installing attaching bolt, washer, nut and cotter pin. Adjust the wing flap control system to assure that the flap actuator does not contact the mechanical stop before the actuating motor stops rotating. The motor stop should be contacted, at a minimum distance of 1/4 turn, before the actuator contacts its mechanical stop for actuators P/N D2246-3, D2246-4, D2246-31, and D2246-41. The minimum distance for P/N D2246-5 and D2246-6 actuators is 1/2 turn. Damage to the mechanism may result if these distances are not maintained. 12. Check for proper operation and rigging of the wing flaps and flap position indication according to EMBRAER Technical Manual T.O. 1C95-2-5. Check and, if necessary, adjust the flap asymmetry detection system. B) On or before September 30, 1982, replace the flap actuators P/N 2246-3 and D2246-4 with actuators P/N 2246-5 and D2246-6 or P/N D2246-31 and D2246-41, respectively, and continue to comply with paragraph A) of this AD. C) Upon request by the operator, an FAA Maintenance Inspector, subject to the approval of the Atlanta Aircraft Certification Office, may adjust the inspection compliance times to an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. D) Any equivalent method of compliance with this AD must be approved by the Manager, Atlanta Aircraft Certification Office, FAA, 3400 Norman Berry Drive, East Point, Georgia 30320; telephone (404) 763-7428. EMBRAER Service Bulletin No. 110-27-043, Revision 02, dated July 13, 1983, covers the subject matter of this AD. This AD supersedes AD 79-24-03 R1, Amendment 39-3974 which, in turn, revised AD 79-24-03, Amendment 39-3616. Amendment 39-4325 became effective March 1, 1982. Amendment 39-4455 became effective on August 24, 1982. This Amendment 39-4747 becomes effective on October 26, 1983.
2022-24-16: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 190-300 and -400 airplanes. This AD was prompted by the identification of a quality escape in the installation of certain fasteners of the lower beam (frame) splices of the overwing emergency exit (OWE) doors. This AD requires inspection, rework, if applicable, and replacement of the splice fasteners of the right-hand (RH) and left-hand (LH) OWE doors, 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.
93-13-04: 93-13-04 FOKKER: Amendment 39-8617. Docket 91-NM-121-AD. Supersedes AD 89-07-16 R1, Amendment 39-6444. Applicability: Model F28 Mark 1000, 2000, 3000 and 4000 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of these airplanes, accomplish the following: NOTE 1: This AD references Fokker Structural Integrity Program (SIP) Document 28438, Part I, including revisions up through November 1, 1988; and Fokker SIP Document 28438, Part I, including revisions up through October 15, 1992; for inspection procedures, compliance times, repairs, replacement and reporting requirements. In addition, this AD specifies compliance times different from those included in the SIP Document. Where there are differences between the AD and the SIP Document, the AD prevails. NOTE 2: Cracked structure detected during the inspections required by paragraph (a) or (b) of this AD that is repaired or replaced in accordance with data meeting the certification basis of the airplane and approved by the Rijksluchtvaartdienst (RLD) is equivalent to FAA approval and constitutes an acceptable method of compliance. (a) Within six months after February 5, 1990 (the effective date of Amendment 39-6444, AD 89-07-16 R1), incorporate into the FAA-approved maintenance program the inspections, inspection intervals, repairs, or replacements defined in the Fokker Structural Integrity Program (SIP) Document 28438, Part I, including revisions up through November 1, 1988; and inspect, repair, and replace, as applicable. The non-destructive inspection techniques referenced in this document provide acceptable methods for accomplishing the inspections required by this AD. Inspection results, where a crack is detected, must be reported to Fokker, in accordance with the instructions of the SIP document. Information collection requirements contained in this regulation have beenapproved 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. (b) Within six months after the effective date of this AD, replace the revision of the FAA-approved maintenance program required by paragraph (a) of this AD with the inspections, inspection intervals, repairs, or replacements defined in the Fokker SIP Document 28438, Part I, including revisions up through October 15, 1992; and inspect and repair, or replace, as applicable. The non-destructive inspection techniques referenced in this document provide acceptable methods for accomplishing the inspections required by this AD. Inspection results, where a crack is detected, must be reported to Fokker, in accordance with the instructions of the SIP document. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under theprovisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (c) Cracked structure detected during the inspections required by paragraph (a) or (b) of this AD must be repaired or replaced, prior to further flight, in accordance with the instructions in Fokker SIP Document 28438, Part I, including revisions up through November 1, 1988 [for airplanes inspected in accordance with paragraph (a) of this AD]; or Fokker SIP Document 28438, Part I, including revisions up through October 15, 1992 [for airplanes inspected in accordance with paragraph (b) of this AD]; or in accordance with other data meeting the certification basis of the airplane which is approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, or by the RLD. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 3: Repairs approved as alternative methods of compliance for AD 89-07-16 R1 constitute valid approvals for compliance with this AD, unless otherwise specified. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The inspections, repair, and replacement procedures shall be done in accordance with Fokker Structural Integrity Program (SIP) Document 28438, Part 1, revised up through October 15, 1992, which contains the following list of effective pages: Item Number Page Number Revision Level Shown on Page Date Shown on Page INTRODUCTION - 1-27 - October 15, 1992 INSPECTIONS 27-20-01 1 - March 1, 1982 27-30-01 1 3 August 31, 1990 27-40-01 1 2 August 31, 1990 27-50-01 1 2 March 20, 1986 27-50-02 1 2 March 20, 1986 27-50-03 1 2 March 20, 1986 27-50-04 1 2 March 20, 1986 27-50-05 1 - March 1, 1982 27-50-06 1 - March 1, 1982 27-50-07 1 2 August 31, 1990 27-50-08 1 3 August 31, 1990 27-50-09 1 3 August 31, 1990 27-50-10 1 1 August 31, 1990 27-61-01 1 1 August 31, 1990 27-61-02 1 2 October 15, 1992 27-61-03 1 2 August 31, 1990 27-63-01 1 1 August 31, 1990 27-63-02 1 - March 1, 1982 27-63-03 1 1 November 1, 1988 27-63-04 1 1 August 31, 1990 27-63-05 1 1 November 1, 1988 29-10-01 1 1 August 31, 1990 32-10-01 1 1 August 31, 1990 32-10-02 1 1 August 31, 1990 32-10-03 1 1 August 31, 1990 32-10-04 1 1 August 31, 1990 32-10-05 1 3 October 15, 1992 32-30-01 1 1 October 15, 1992 32-42-01 1 1 August 31, 1990 32-42-02 1 1 August 31, 1990 32-50-01 1 3 October 15, 1992 52-10-01 1 2 May 1, 1984 52-10-01 2 - May 1, 1984 52-10-02 1 2 August 31, 1990 52-10-03 1 3 October 15, 1992 52-10-05 1 - October 15, 1992 52-20-01 1 6 October 15, 1992 52-20-02 1 5 October 15, 1992 52-30-01 1 2 August 31, 1990 52-30-02 1 2 August 31, 1990 52-30-03 1 2 August 31, 1990 52-30-04 1 2 August 31, 1990 52-30-05 1 3 October 15, 1992 52-30-05 2 4 October 15, 1992 52-30-06 1 2 October 15, 1992 52-30-07 1 2 October 15, 1992 Item Number Page Number Revision Level Shown on Page Date Shown on Page 52-30-07 2 - October 15, 1992 52-30-08 1 1 August 31, 1990 52-30-09 1 - October 15, 1992 52-30-10 1 - October 15, 1992 52-30-11 1 - October15, 1992 52-31-01 1 1 August 31, 1990 52-31-02 1 2 August 31, 1990 52-40-01 1 4 October 15, 1992 52-40-02 1 4 October 15, 1992 53-10-01 1-2 4 October 15, 1992 53-10-02 1 4 October 15, 1992 53-10-02 2 3 (deleted) 53-10-03 1 4 October 15, 1992 53-10-04 1 3 October 15, 1992 53-10-05 1-2 4 October 15, 1992 53-10-06 1 4 October 15, 1992 53-10-07 1 3 October 15, 1992 53-10-08 1 5 October 15, 1992 53-10-08 2-3 2 October 15, 1992 53-10-09 1 2 August 31, 1990 53-10-10 1 3 October 15, 1992 53-10-11 1 3 October 15, 1992 53-10-12 1 2 October 15, 1992 53-10-13 1 2 October 15, 1992 53-10-14 1 4 October 15, 1992 53-10-18 1 3 October 15, 1992 53-10-18 2 1 October 15, 1992 53-10-18 3 - October 15, 1992 53-10-19 1 2 October 15, 1992 53-10-20 1 2 October 15, 1992 53-10-21 1 2 October 15, 1992 53-10-22 1 1 October 15, 1992 53-10-23 1 1 October 15, 1992 53-10-24 1- (Not Dated) 53-10-24 2 - October 15, 1992 53-10-25 1 - October 15, 1992 53-30-01 1 3 October 15, 1992 53-30-02 1 3 October 15, 1992 53-30-03 1 4 October 15, 1992 53-30-05 1-2 3 October 15, 1992 53-30-06 1-6 3 October 15, 1992 53-30-06 7-9 - October 15, 1992 53-30-07 1 3 October 15, 1992 53-30-07 2 2 October 15, 1992 53-30-07 3 1 October 15, 1992 53-30-08 1 3 October 15, 1992 53-30-09 1 1 October 15, 1992 53-30-09 2-8 - October 15, 1992 53-40-01 1 2 October 15, 1992 Item Number Page Number Revision Level Shown on Page Date Shown on Page 53-40-02 1 4 October 15, 1992 53-40-02 2 1 October 15, 1992 53-40-03 1 2 August 31, 1990 53-40-04 1 4 October 15, 1992 53-50-01 1 1 August 31, 1990 53-50-01 2 2 August 31, 1990 55-30-01 1 4 October 15, 1992 55-50-01 1 4 October 15, 1992 55-50-02 1 4 October 15, 1992 55-50-04 1 1 August 31, 1990 55-50-05 1 - October 15, 1992 57-10-01 1 3 October 15, 1992 57-10-01 2 2 March 20, 1986 57-10-02 1 2 October 15, 1992 57-10-02 2 2 March 20, 1986 57-10-03 1 2 October 15, 1992 57-10-03 2 2 March 20, 1986 57-10-04 1 4 August 31, 1990 57-10-05 1 4 October 15, 1992 57-10-06 1 5 October 15, 1992 57-10-07 1 5 October 15, 1992 57-10-07 2 3 October 15, 1992 57-10-09 1 1 October 15, 1992 57-10-10 1 - October 15, 1992 57-30-01 1-2 5 October 15, 1992 57-30-02 1 2 October 15, 1992 57-40-01 4 3 October 15, 1992 57-40-01 2 2 August 31, 1990 57-40-01 3 3 August 31, 1990 57-40-01 4 2 August 31, 1990 57-40-02 1 4 October 15, 1992 57-40-03 1 2 August 31, 1990 57-40-04 1 2 October 15, 1992 57-40-04 2 2 March 20, 1986 57-40-05 1 4 October 15, 1992 57-40-06 1 3 October 15, 1992 57-40-07 1 3 October 15, 1992 57-40-08 1 3 October 15, 1992 57-40-09 1 2 August 31, 1990 57-40-10 1 1 August 31, 1990 57-40-11 1 1 August 31, 1990 57-50-01 1 2 August 31, 1990 57-50-02 1 3 October 15, 1992 57-50-03 1 3 October 15, 1992 57-50-04 1 3 October 15, 1992 57-50-05 1 3 October 15, 1992 57-50-06 1 3 October 15, 1992 71-20-01 1 3 August 31, 1990 72-00-01 1 1 May 1, 1984 Item Number Page Number Revision Level Shown on Page Date Shown on Page ILLUSTRATIONS 27-20-01 1 - March 1, 1982 27-30-01 1 - March 1, 1982 27-40-01 1 - March 1, 1982 27-50-01 1 1 August 31, 1990 27-50-01 2 - August 31, 1990 27-50-10 1 - September 25, 1987 27-61-01 1 - March 1, 1982 27-61-03 1 - March 1, 1982 27-63-01 1 - March 1, 1982 27-63-02 1 - March 1, 1982 29-10-01 1 - March 1, 1982 32-10-01 1 - March 1, 1982 32-10-02 1 - March 1, 1982 32-10-03 1 - March 1, 1982 32-42-01 1 - March 1, 1982 32-50-01 1 - March 1, 1982 52-10-01 1 2 August 31, 1990 52-10-02 1 1 October 15, 1992 52-10-05 1 - October 15, 1992 52-20-01 1 - March 1, 1982 52-30-01 1 1 August 31, 1990 52-30-01 2 - August 31, 1990 52-30-05 1 2 October 15, 1992 52-30-06 1 2 October 15, 1992 52-30-09 1 - October 15, 1992 52-31-01 1 1 November 1, 1982 52-40-01 1 - March 1, 1982 53-10-01 1 1 August 31, 1990 53-10-01 2 - August 31, 1990 53-10-03 1 - August 31, 1990 53-10-04 1 1 October 15, 1992 53-10-05 1 2 August 31, 1990 53-10-06 1 - August 31, 1990 53-10-07 1 1 October 15, 1992 53-10-08 1 4 August 31, 1990 53-10-09 1 - March 1, 1982 53-10-10 1 1 August 31, 1990 53-10-11 1 - March 1, 1982 53-10-12 1 - March 1, 1982 53-10-14 1 2 October 15, 1992 53-10-18 1 3 October 15, 1992 53-10-18 2 - October 15, 1992 53-10-19 1 - September 25, 1987 53-10-20 1 - September 25, 1987 53-10-21 1 - November 1, 1988 53-10-22 1 - August 31, 1990 53-10-23 1 1 October 15, 1992 53-10-24 1 - October 15, 1992 Item Number Page Number Revision Level Shown on Page Date Shown on Page 53-10-25 1 - October 15, 1992 53-30-01 1 1 August 31, 1990 53-30-02 1 - August 31, 1990 53-30-03 1 2 August 31, 1990 53-30-05 1 2 October 15, 1992 53-30-06 1-5 - October 15, 1992 53-30-07 1-6 - October 15, 1992 53-30-08 1-2 - October 15, 1992 53-30-09 1-9 - October 15, 1992 53-40-01 1 1 August 31, 1990 53-40-02 1 2 October 15, 1992 53-40-03 1 - December 15, 1983 53-40-04 1 1 August 31, 1990 53-50-01 1 - March 1, 1982 55-30-01 1 1 October 15, 1992 55-50-01 1 2 October 15, 1992 57-10-01 1 2 October 15, 1992 57-10-02 1 - March 1, 1982 57-10-04 1 - March 1, 1982 57-10-05 1 1 August 31, 1990 57-10-06 1 - March 1, 1982 57-10-07 1 2 October 15, 1992 57-10-09 1 - August 31, 1990 57-10-10 1 - October 15, 1992 57-30-01 1 1 November 1, 1988 57-30-021 1 August 31, 1990 57-40-01 1 2 August 31, 1990 57-40-01 2 - August 31, 1990 57-40-02 1 1 August 31, 1990 57-40-03 1 - March 1, 1982 57-40-05 1 1 August 31, 1990 57-40-07 1 1 August 31, 1990 57-40-09 1 - September 25, 1987 57-40-10 1 - September 25, 1987 57-40-11 1 - September 25, 1987 57-50-02 1 - March 1, 1982 57-50-04 1 - March 1, 1982 57-50-06 1 - March 1, 1982 71-20-01 1 - March 1, 1982 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on August 18, 1993.
2001-06-10: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4-605R, A300 B4-622R, and A300 F4-605R airplanes. This AD requires repetitive high frequency eddy current (HFEC) or rototest inspections to detect cracking in the area surrounding the frame feet attachment holes between fuselage frames (FR) 41 and FR46; installation of new fasteners for certain airplanes; and follow-on corrective actions, if necessary. This AD is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent cracking of the center section of the fuselage, which could result in rupture of the frame foot and reduced structural integrity of the airplane.
2001-06-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes powered by General Electric engines, that requires modification of the nacelle strut and wing structure. This amendment is prompted by reports indicating that the actual operational loads applied to the nacelle are higher than the analytical loads that were used during the initial design. Such an increase in loading can lead to fatigue cracking in the primary strut structure prior to an airplane reaching its design service objective. The actions specified by this AD are intended to prevent fatigue cracking in the primary strut structure and consequent reduced structural integrity of the strut. \n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by the\nDirector of the Federal Register as of May 7, 2001.\n\n\tThe incorporation by reference of a certain other publication, as listed in the regulations, was approved previously by the Director of the Federal Register as of July 24, 2000 (65 FR 37843, June 19, 2000).\n\n\tThe incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of October 17, 2000 (65 FR 58641, October 2, 2000).\n\n\tThe incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of March 5, 2001 (66 FR 8085, January 29, 2001).
2001-06-16: This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires revisions to the Airplane Flight Manual (AFM) and installation of inspection aids on the wing upper surfaces. This amendment requires, among other actions, installation of an overwing heater blanket system or primary upper wing ice detection system, and installation of a heater protection panel or an equipment protection device on certain overwing heater blanket systems. This amendment is prompted by incidents in which ice accumulation on the wing upper surfaces shed into the engines during takeoff. The actions specified by this AD are intended to prevent ice accumulation on the wing upper surfaces, which could result in ingestion of ice into one or both engines and consequent loss of thrust from one or both engines. \n\n\tThe incorporation by reference of McDonnell Douglas Service Bulletin30-59, dated September 18, 1989, and McDonnell Douglas Service Bulletin 30-59, Revision 1, dated January 5, 1990, as listed in the regulations, was approved previously by the Director of the Federal Register as of January 17, 1992 (57 FR 2014, November 12, 1998).\n\n\tThe incorporation by reference of certain other publications, as listed in the regulations, is approved by the Director of the Federal Register as of May 7, 2001.
58-26-01: 58-26-01 BELL: Applies to All Models 47G2 and 47J Helicopters With Engine Cooling Fan Index Plate Assembly, P/N 47-661-801-5 Installed. Compliance required within next 25 hours of operation. Fabricating procedures used on the engine cooling fan index plate assembly, P/N 47-661-801-5, which involve silver brazing have resulted in a possible defective bond between the fan index plate and the fan shaft. To prevent failure of this joint, all Models 47G2 and 47J helicopters having silver brazed index plate assemblies must be reworked as indicated: 1. Locate the longitudinal center line of portion of the 47-669-117-5 shaft on which the fan mounts and drill one 0.2130-inch diameter hole (blind) 0.63-inch deep through the 47-669-106-5 or -7 index plate and into the end of 47-669-117-5 fan shaft. 2. Locate the intersections of a line between the two end indexing holes and the end of the 47-669-117-5 shaft which projects through the indexing plate and drill 0.2130-inch diameter holes. 3. Tap all three holes using a 1/4-28UNF3A tap and install AN 4H4A bolts and AN 960-416 washers. Safety wire the heads of all three holes with AN 995C32 lockwire. Model 47G2 helicopters, Serial Numbers 2213, 2214, 2229, 2230, 2231, 2232, 2235 and subsequent, and Model 47J helicopters, Serial Numbers 1420, 1581, 1713, 1731, 1734, 1737, 1743, 1744, 1747, and subsequent will have reworked or heli-arc welded index plate assemblies, identified as P/N 47-661-801-25 or P/N 47-661-801-21, installed prior to delivery and are not affected by this directive. In addition, some early 47G2 and 47J helicopters equipped with fan index plate assemblies marked as P/N 47-661-801-5 are steel welded in a satisfactory manner and need not be reworked. These may be identified by a 1/4-inch deep by 0.56-inch diameter counterbore in the aft end of the engine cooling fan shaft. A flashlight and mirror are needed to determine the existence of the counterbore. (Bell Mandatory Service Bulletin No. 126SB dated October 2, 1958, covers this same subject.)
2016-10-12: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by accomplishment of a taxi-out checklist which revealed that the elevator movement was partially obstructed due to rotation of the flight control lock adjuster bracket. This AD requires a one-time inspection of the elevator tension control regulator for discrepancies, and corrective actions if necessary. We are issuing this AD to detect and correct discrepancies of the elevator tension control regulators. Such a condition could result in jamming of the elevator mechanism and consequent reduced controllability of the airplane.
93-21-11: 93-21-11 FOKKER: Amendment 39-8725. Docket 93-NM-83-AD. Applicability: Model F27 series airplanes, excluding Model F27 Mark 050 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the brake control valve actuating levers, accomplish the following: (a) Within 12 months after the effective date of this AD, or prior to the accumulation of 2,000 flight hours after the effective date of this AD, whichever occurs first, replace the brake control valve actuating levers in accordance with Fokker Service Bulletin F27/32-161, Revision 1, dated June 14, 1991. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector,who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The replacement shall be done in accordance with Fokker Service Bulletin F27/32-161, Revision 1, dated June 14, 1991, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1-2 1 June 14, 1991 3-7 Original June 5, 1989 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on December 13, 1993.