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92-16-04: 92-16-04 AEROSPATIALE: Amendment 39-8313. Docket No. 92-NM-17-AD. Supersedes AD 89-25-12, Amendment 39-6414. Applicability: Model ATR42 series airplanes, certificated in any category. Compliance: Required prior to the accumulation of 10,000 landings, or within the next 300 landings after January 12, 1990 (the effective date of AD 89-25-12, amendment 39-6414), whichever occurs later, unless accomplished previously. To prevent failure of the structural components of the fuselage and wing, accomplish the following: (a) For airplane Serial Numbers 003 through 151, inclusive: Reinforce fuselage frame 26 in accordance with Aerospatiale Service Bulletin ATR42-53-0042, dated May 3, 1989; or Revision 1, dated April 22, 1991. (b) For airplane Serial Numbers 003 through 032, inclusive; 034; and 035: Reinforce the fuselage secondary frames in accordance with Aerospatiale Service Bulletin ATR42-53-0023, Revision 2, dated May 25, 1989. (c) For airplane Serial Numbers003 through 059, inclusive: Perform a cold expansion of the outer wing lower skin attach fastener holes in accordance with Aerospatiale Service Bulletin ATR42-57-0010, Revision 1, dated May 20, 1989; or Revision 2, dated April 15, 1991. (d) For airplane Serial Numbers 003 through 071, inclusive: Reinforce fuselage frames 24 and 28 in accordance with Aerospatiale Service Bulletin ATR42-53-0004, Revision 4, dated July 25, 1989. (e) For airplane Serial Numbers 003 through 084, inclusive; 086; 087; and 089 through 093, inclusive: Perform a cold expansion of attach holes and reinforce wing/fuselage junction fittings in accordance with Aerospatiale Service Bulletin ATR42-53-0031, Revision 1, dated May 20, 1989; or Revision 2, dated May 31, 1990; or Revision 3, dated February 19, 1991. (f) For airplane Serial Numbers 003 through 119, inclusive: Perform a cold expansion of the wing front and rear spar attach holes in accordance with Aerospatiale Service Bulletin ATR42-57-0021,Revision 1, dated May 20, 1989; or Revision 2, dated September 25, 1990; or Revision 3, dated April 10, 1991; or Revision 4, dated August 28, 1991. (g) For airplane Serial Numbers 003 through 151, inclusive: Replace the wing center box, in accordance with Aerospatiale Service Bulletin ATR42-57-0027, Revision 2, dated July 6, 1989; or Revision 3, dated March 27, 1991; or Revision 4, dated August 23, 1991; or Revision 5, dated October 22, 1991. (h) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from Standardization Branch, ANM-113. (i) 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. (j) The reinforcement, replacement, and the cold expansion shall be done in accordance with the following Aerospatiale service bulletins, which contain the specified effective pages: Service Bulletin Referenced and Date Page Number Revision Level Shown on Page Date Shown on Page ATR42-53-0042, May 3, 1989 1-42 Original May 3, 1989 ATR42-53-0042, Revision 1, April 22, 1991 3-40, 42 1-2, 41 Original 1 May 3, 1989 April 22, 1991 ATR42-53-0023, Revision 2, May 25, 1989 3-8, 10-26, 28-50, 52-53, 55-64, 66-78, 81-200, 203 2, 9, 27, 51, 54 1, 65, 79-80, 201-202 Original 1 2 July 26, 1988 January 26, 1989 May 25, 1989 ATR42-57-0010, Revision 1, May 20, 1989 2-5, 14, 20-381, 6-13, 15-19, 39-40 Original 1 April 18, 1989 May 20, 1989 ATR42-57-0010, Revision 2, April 15, 1991 5, 14, 21-38 6-13, 15, 17-19 1-4, 16, 20, 39, 40 Original 1 2 April 18, 1989 May 20, 1989 April 15, 1991 ATR42-53-0004, Revision 4, July 25, 1989 3-8, 13-20, 25-30, 33-34 2, 11 9, 12, 21-22, 31-32, 35-36 1, 10, 23-24, 37 Original 2 3 4 September 2, 1988 February 16, 1989 May 25, 1989 July 25, 1989 ATR42-53-0031, Revision 1, May 20, 1989 2-7, 10-29 1, 8-9 Original 1 January 13, 1989 May 20, 1989 ATR42-53-0031, Revision 2, May 31, 1990 15-17, 19-28, 1-14, 18, 29 Original 2 January 13, 1989 May 31, 1990 ATR42-53-0031, Revision 3, February 19, 1991 15-16, 17, 19-28 3-14, 18, 29 1-2, 15-16 bis Original 2 3 January 13, 1989 May 31, 1990 February 19, 1991 ATR42-57-0021, Revision 1, May 20, 1989 3-6, 11-21 1-2, 7-10 Original 1 April 18, 1989 May 20, 1989 ATR42-57-0021, Revision 2, September 25, 1990 1-23 2 September 25, 1990 ATR42-57-0021, Revision 3, April 10, 1991 2, 4, 7-10, 12-22 1, 3, 5-6, 11, 23 2 3 September 25, 1990 April 10, 1991 ATR42-57-0021, Revision 4, August 28, 1991 7-9, 13-22 2-6, 11-12, 23 1, 10 2 3 4 September 25, 1990 April 10, 1991 August 28, 1991 ATR42-57-0027, Revision 2, July 6, 1989 5-6, 9, 11 13, 27-71 2-4, 7-8, 10, 12, 14-18, 26 1, 19-25, 72-80 Original 1 2 April 18, 1989 May 25, 1989 July 6, 1989 ATR42-57-0027, Revision 3, March 27, 1991 5-6, 9, 11, 13, 27-71 2-4, 7-8, 10, 12, 14-18, 26 19-25, 72-74, 76, 78, 80 1, 75, 77, 79 Original 1 2 3 April 18, 1989 May 25, 1989 July 6, 1989 March 27, 1991 ATR42-57-0027, Revision 4, August 23, 1991 6, 9, 11, 13, 27-71 3-4, 8, 10, 12, 14-18, 26 22-25, 72-74, 76, 78 75, 77, 79 1-2, 5, 7, 19-21 Original 1 2 3 4 April 18, 1989 May 25, 1989 July 6, 1989 March 27, 1991 August 23, 1991 ATR42-57-0027, Revision 5, October 22, 1991 6, 9, 11, 13, 27-71 3-4, 8, 10, 12, 14-18 22-25, 72-74 75-79 7, 19-21, 80 1-2, 5, 26 Original 1 2 3 4 5 April 18, 1989 May 25, 1989 July 6, 1989 March 27, 1991 August 23, 1991 October 22, 1991 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, 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. (k) This amendment becomes effective on October 21, 1992.
2014-13-02: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-Trent 875-17, 877-17, 884-17, 884B-17, 892- 17, 892B-17, and 895-17 turbofan engines. This AD requires inspection of the [[Page 37168]] affected low-pressure (LP) turbine bearing support and exhaust case assembly and, if necessary, its replacement with a part eligible for installation. This AD was prompted by thin-walled LP turbine bearing support and exhaust case assemblies having been delivered into service. We are issuing this AD to prevent failure of the LP turbine bearing support and exhaust case assembly, which could lead to engine separation and damage to the airplane.
2014-13-01: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model MBB-BK 117 C-2 helicopters with a certain Goodrich rescue hoist damper unit (damper unit) installed. This AD requires repairing or replacing the damper unit or deactivating the rescue hoist. This AD is prompted by a report of an uncommanded detachment of a damper unit from the cable. These actions are intended to prevent loss of an external load or person from the helicopter hoist and injury to persons being lifted by the hoist.
99-25-16: : This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires the removal of tapered nylon shims from under the seat rails from fuselage station 14025 to the aft end of the seat rails, and installation of shorter bolts. This action also requires the installation of shims under galleys and partition walls for certain configurations. 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 prevent failure of the seat rail attachments due to shim material aging, which could result in detachment of the seats and consequent injury to the airplane occupants.
97-23-10: 97-23-10 DORNIER: Amendment 39-10198. Docket 96-NM-115-AD. Applicability: Model 328-100 series airplanes having serial numbers 3005 through 3045 inclusive; 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 (b) 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 prevent failure of the cable tension regulator on both the left and right elevators, and consequent reduced controllability of the airplane, accomplish the following: (a) Within 6 months after the effective date of this AD, modify the cable tension regulator on both the left and right elevators by installing two lateral plates on the lever arm, in accordance with Dornier Service Bulletin SB-328-27-116, dated September 26, 1995. (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, 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (c) 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. (d) The modification shall be done in accordance with Dornier Service Bulletin SB-328- 27-116, dated September 26, 1995. 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 Dornier Deutsche Aerospace, P.O. Box 1103, D-82230 Wessling, Federal Republic of Germany. 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 3: The subject of this AD is addressed in German airworthiness directive 95-434, dated November 14, 1995. (e) This amendment becomes effective on December 17, 1997.
89-07-15: 89-07-15 BOEING: Amendment 39-6167.\n\n\tApplicability: Model 747 series airplanes, listed in Boeing Service Bulletin 747-54-2126, dated June 16, 1988, certificated in any category.\n\n\tCompliance: Required as indicated, unless previously accomplished.\n\n\tTo prevent failure of the engine strut diagonal brace lugs, accomplish the following:\n\n\tA. Prior to the accumulation of 10,000 landings or 8 years in service, whichever occurs first; or within the next 3 months after the effective date of this AD, whichever occurs later, ultrasonically inspect engine strut diagonal brace lugs for cracks, in accordance with Boeing Service Bulletin 747-54-2126, dated June 16, 1988.\n\n\tB. If cracking is found, prior to further flight, replace the diagonal brace with a new or overhauled diagonal brace incorporating the terminating action described by paragraph D., below, in accordance with Boeing Service Bulletin 747-54-2126, dated June 16, 1988.\n\n\tC. If no cracking is found, repeat the inspection required by paragraph A., above, at intervals not to exceed 1,000 landings.\n\n\tD. Terminating action for the inspections required by paragraphs A. and C., above, consists of removing existing bushings, oversizing bores to remove corrosion, installing high-interference fit bushings with wet sealant, and fillet sealing bushing flanges, in accordance with Boeing Service Bulletin 747-54-2126, dated June 16, 1988.\n\n\tE. 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.\n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office.\n\n\tF. 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 therequirements of this AD.\n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington.\n\n\tThis amendment (39-6167, AD 89-07-15) becomes effective on May 3, 1989.
2014-13-04: We are adopting a new airworthiness directive (AD) for Columbia Helicopters, Inc. (Columbia) Model 234 helicopters. This AD requires visually and tap inspecting each fore and aft rotor blade for any defect, damage, or a disbond and, if necessary, repairing or replacing the blade. Also, this AD requires dye-penetrant inspecting the aft pylon structure for fatigue cracking in certain areas near the attachment fittings and, if there is a crack, repairing or replacing the aft pylon. This AD is prompted by an accident caused by fatigue failure of an aft pylon fitting attach structure combined with aft rotor blade damage. The actions specified by this AD are intended to detect fatigue cracks in the aft pylon attach structure to prevent overload of the aft pylon structure and failure of the rotor blade, rotor blade vibration, departure of the aft pylon, and subsequent loss of control of the helicopter.
52-04-02: 52-04-02 MARTIN: Applies to All Models 202 and 202A Aircraft. Compliance required not later than August 1, 1952. Provide separate protection for each inverter control and warning light circuit. Also provide separate protection for T and B warning lights in forward area. (Trans World Airlines Engineering Order No. 5717 covers this same subject.)
98-25-10 R1: This amendment revises an existing airworthiness directive (AD), applicable to Aircraft Belts, Inc. Model CS, CT, FM, FN, GK, GL, JD, JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH seat restraint systems installed on, but not limited to, Beech Aircraft Corp., Bell Helicopter Textron, Inc., Cessna Aircraft Co., Dassault Aviation, Eurocopter Deutschland, Eurocopter France, Gulfstream Aerospace, Learjet Corp., Lockheed Aircraft Corp., and Piper Aircraft Corp. aircraft, that currently requires inspecting to ensure the locking mechanism is engaging properly and replacing the buckle-half of the seat restraint system, if necessary. This amendment will allow an owner/operator (pilot) to determine if the locking mechanism is engaging properly and will require replacing the buckle-half of the seat restraint system, if necessary. This amendment is prompted by a determination made by the FAA that pilots may perform the one-time check of the locking mechanism and that only affectedseat restraint systems manufactured between March 1997 and November 1998 must be checked. The actions specified by this AD are intended to prevent failure of the seat restraint system due to the buckle assembly locking mechanism not engaging properly, which could result in the seat restraint system failing to properly secure the occupant during turbulence or landing.
47-16-03: 47-16-03 TAYLORCRAFT: (Was Mandatory Note 11 of AD-700-1: Mandatory Note 12 of AD-699-1; and Mandatory Note 13 of AD-696-3.) Applies to All Models BC, BF, and BL Series Aircraft. Compliance required immediately. Inspect wing strut attachment fittings on lower fuselage longerons for cracks or evidence of poor weld. If cracks or defects are found, the fitting should be replaced or reinforced.