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75-13-06: 75-13-06 BRITISH AIRCRAFT CORPORATION: Amendment 39-2236. Applies to Viscount Model 700 Series airplanes certificated in all categories. Compliance required as indicated. To prevent the possible in-flight fatigue failure of the horizontal stabilizer, accomplish the following: (a) For horizontal stabilizer rear spars with more than 25,000 landings on the effective date of this AD, comply with paragraphs (c) and (d) of this AD within the next 10 landings or 50 hours time in service, whichever occurs first, unless already accomplished. (b) For all horizontal stabilizer rear spars not covered in paragraph (a) of this AD, comply with paragraphs (c) and (d) of this AD before the accumulation of 20,000 total landings or the lesser of 100 landings or 300 hours time in service after the effective date of this AD, whichever occurs later, unless already accomplished. (c) Inspect the rear spar of the left and right horizontal stabilizer for cracks and corrosion, and repairor replace as necessary, in accordance with CAA-approved British Aircraft Corporation (BAC) Alert Preliminary Technical Leaflet (PTL) No. 298, Issue 1, dated August 16, 1974, or an FAA-approved equivalent. (d) Accomplish BAC Modification Leaflet D.3268 or D.3269, or an FAA-approved equivalent of either, as provided in BAC PTL NO. 298, Issue 1. (e) Spar booms on which the corrosion damage exceeds the limits set forth in BAC PTL No. 298, Issue 1, may not be returned to service unless the repair of such damage is approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region of the FAA. (f) The service life limitation of the rear spar assembly of a spar boom modified in accordance with BAC Modification Leaflet D.3268, or an FAA-approved equivalent, is 2000 landings after modification or 30,000 total pre-modification and post-modification landings, whichever occurs first. (g) The service life limitation of the rear spar assembly of a spar boom modified in accordance with BAC Modification Leaflet D.3269, or an FAA-approved equivalent, is 30,000 total pre-modification and post- modification landings. (h) For the purpose of this AD, the number of landings may be determined by actual count, or, subject to the acceptance of the assigned FAA maintenance inspector, by dividing the horizontal stabilizer spar total time in service by an average flight time determined from the airplane log book to be representative for that airplane. Operators who have not kept records of landings or time in service for individual horizontal stabilizers must substitute total number of airplane landings or time in service in place thereof. This amendment becomes effective June 6, 1975.
2002-01-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Turbomeca S.A. Arrius 1A turboshaft engines. This action requires replacement of the 10 main fuel injectors in Arrius 1A engines with new or overhauled injectors. This amendment is prompted by routine inspections conducted in the repair workshop demonstrating that some main fuel injectors were partially or totally blocked. The actions specified in this AD are intended to prevent blocked main fuel injectors that could lead to engine flameout during engine deceleration or that could prevent the engine from obtaining the 2 1/2 minute one engine inoperative (OEI) power.
2025-11-05: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by reports of multiple supplier notices of escapement (NOEs) indicating that seat track splice fittings were possibly manufactured with an incorrect titanium alloy material. This AD requires an inspection of seat track splice fittings to determine the material and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
82-15-04: 82-15-04 FOKKER B.V.: Amendment 39-4418. Applies to Model F28 Series 1000 and 4000 airplanes certificated in all categories, serial numbers as indicated below. Note: Some serial numbers listed may actually be 2000, 3000, 5000, or 6000 airplanes that are not presently eligible for U.S. certification. Those serial numbers may be disregarded insofar as this AD is concerned. 1. Unless already accomplished, accomplish the following within the time specified in each paragraph below after the effective date of this AD. A. Applies to F28 airplanes S/N 11003-11064 and 11991-11993 inclusive. Compliance required within six months after the effective date of this AD. Install an inspection window in the passenger door per Fokker Service Bulletin F28/52-43, Part IV, dated April 16, 1974. B. Applies to F28 airplanes S/N 11003-11070, 11072-11074, and 11991- 11993 inclusive. Compliance required within six months after the effective date of this AD. Replace sliding pins inthe passenger door per Fokker Service Bulletin F28/52-44 dated April 9, 1974. C. Applies to F28 airplanes S/N 11021-11062 and 11991-11993 inclusive for the rear cargo door and 11003-11062 and 11991-11993 inclusive for the front and center cargo doors. Compliance required within six months after the effective date of this AD. Install the improved switch operating mechanism in the rear, forward, and center cargo door rabbets per Parts I & II of Fokker Service Bulletin F28/52-49, Revision 1, dated March 1, 1976. D. (1) Applies to F28 airplanes S/N 11003-11081 and 11991-11993 inclusive. Compliance required within six months after the effective date of this AD. Install a reinforced safety catch and stop assembly on the front cargo door and the center cargo door, if installed, per Part I of Fokker Service Bulletin F28/52-51 dated September 3, 1974. (2) Applies to F28 airplanes S/N 11021-11052, 11054-11061 and 11063-11076 inclusive, and S/N 11078, 11079, and 11191-11193 inclusive. Compliance required within six months after the effective date of this AD. Install a new safety catch and stop assembly on the rear cargo door per Part II of the service bulletin. E. Applies to F28 airplanes S/N 11003-11081 and 11991-11993 inclusive. Compliance required within 500 flight hours time in service after the effective date of this AD. Inspect the cargo door locking mechanism per Fokker Service Bulletin F28/52-53 dated May 10, 1974. F. Applies to F28 airplanes S/N 11003-11020 inclusive. Compliance required within 500 flight hours time in service after the effective date of this AD. Inspect and adjust the cargo door lock warning and locking mechanism for correct functioning per Fokker Service Bulletin F28/52-54 dated July 1, 1974. G. Applies to F28 airplanes S/N 11003-11081 and 11991-11993 inclusive. Compliance required within the next 500 flight hours time in service after the effective date of this AD. Inspect the cargo door latching mechanism and adjust, if necessary, per Fokker Service Bulletin F28/52-56 dated July 26, 1974. H. Applies to F28 airplanes S/N 11003-11020 inclusive. Compliance required within the next 500 flight hours time in service after the effective date of this AD. Install a safety catch on the rear cargo door per Fokker Service Bulletin F28/52-61 dated May 21, 1975. I. Applies to F28 airplanes S/N 11003-11110 and 11991-11993 inclusive. Compliance required within the next 500 flight hours time in service after the effective date of this AD. Modify the shape of the secondary guide rails at fuselage station 3870 (if in post SB F28/52- 55, Part I Configuration) and at station 4610 per Fokker Service Bulletin F28/52-66 dated April 12, 1976. J. Applies to F28 airplanes S/N 11003-11112, 11115, 11116, 11120, and 11991-11993. Compliance required within the next 500 flight hours time in service after the effective date of this AD. Modify the actuating mechanism of the cargo door lock warning switches per Fokker Service Bulletin F28/52-80, Revision 1, dated October 23, 1978. K. Applies to F28 airplanes forward and center cargo doors - S/N 11003- 11081, 11991-11993, and 11082-11101 inclusive if S/B F28/52-51 has been incorporated; rear cargo door - S/N 11053, 11062, 11077, 11080, and 11081 if S/B F28/52-51 has been incorporated and S/N 11090-11093, 11108-11112, and 11114-11116 inclusive, and S/N 11118, 11120-11124, and 11126-11128 inclusive, S/N 11130, 11133, 11135, and 11138-11141 inclusive. Compliance required within the next 500 flight hours time in service after the effective date of this AD. Reinforce the cargo door locking handle access panels per Fokker Service Bulletin F28/52-81 dated October 1, 1977. L. Applies to F28 airplanes S/N 11003-11016 inclusive. Compliance required within 500 flight hours time in service after the effective date of this AD. Reinforce the speed brake accumulator brackets per Fokker Service Bulletin F28/53-4dated May 19, 1970. M. Applies to F28 airplanes S/N 11003-11020 inclusive and S/N 11991. Compliance required within 500 flight hours time in service after the effective date of this AD. Install a plastic separation screen and add ventilation provisions per Fokker Service Bulletin F28/53-21 dated October 11, 1971. N. Applies to F28 airplanes S/N 11003 through 11037 and 11991 through 11994. Compliance required within 500 hours time in service after the effective date of this AD. Inspect for cracks and rework if necessary the speedbrake attach hinge fitting per Fokker Service Bulletin F28/53-26, Revision 1, dated January 2, 1975. O. (1) Applies to F28 airplanes S/N 11020-11055, 11057-11061, and 11063-11071 inclusive, and S/N 11073, 11075, 11078, and 11991-11993 inclusive. Compliance required within 500 hours time in service after the effective date of this AD and at intervals of 250 flight hours thereafter until the modification in paragraph 2 has been carried out.Inspect the PLI washers in the rear cargo compartment latch brackets for correct installation per Part I of Fokker Service Bulletin F28/53-54, Revision 3, dated October 11, 1976. If one or more washers per latch fitting are incorrectly installed, proceed with paragraph 2 of this AD within the next ten hours time in service. (2) Applies to F28 S/N 11020-11090 inclusive, 11092, and 11991- 11993 inclusive. Compliance required within the next 1000 hours time in service after the effective date of this AD or within ten hours time in service if required by paragraph O.(1), above. Install MS washers and bolts in the cargo door latch fittings per the service bulletin. (3) Applies to F28 airplanes S/N 11003-11055, 11057-11061, and 11063-11071 inclusive, and S/N 11073, 11075, 11078, and 11991-11993 inclusive. Compliance required within the next 500 hours time in service after the effective date of this AD. Install MS washers and shorter bolts in the forward and center cargo doorlatch fittings per the service bulletin. P. Applies to F28 airplanes S/N 11003-11091 and 11991-11993 inclusive. Compliance required within 500 hours time in service after the effective date of this AD. To ensure the proper torquing of the MS 21250 bolts in the main entry door latch fittings, replace the dural washers with MS 20002 washers per Part V of Fokker Service Bulletin F28/51-10, Revision 1, dated July 11, 1975. Q. Applies to F28 airplanes S/N 11003-11025 inclusive and S/N 11991, 11992, and 11994. Compliance required within 500 flight hours after the effective date of this AD. To prevent stringer cracks, install connecting angles in the stabilizer torsion box at rib station 3800 per Fokker Service Bulletin F28/55-8, Revision 1, dated October 16, 1972. R. Applies to F28 airplanes S/N 11003-11064 and 11991-11993 inclusive. Compliance required within six months after the effective date of this AD. To ensure proper functioning of the horizontal stabilizer hinge bearings, inspect the bearings per Part I of Fokker Service Bulletin F28/55-14, Revision 1, dated March 15, 1974. If relative rotation does not occur between the bearings ball and the outer ring, modify the hinge bearing installation per Part II of the service bulletin within nine months of the inspection. If relative rotation does occur between the ball and the outer ring, the Part II modification must be accomplished within two years after the effective date of this AD. S. Applies to F28 airplanes S/N 11003-11020, 11022-11025, and 11991- 11993 inclusive. Compliance required within six months after the effective date of this AD. To prevent stress corrosion cracks, install bronze bushings in the stabilizer hinge brackets per Fokker Service Bulletin F28/55-17 dated October 27, 1975. T. Applies to F28 airplanes as follows: S/N 11003-11145 inclusive and S/N 11147, 11150, 11151, 11991, and 11992. Compliance required within six months after the effective date of this AD. To prevent the loss of the stabilizer hinge bolts if the nut has backed off, install an additional retaining device per Fokker Service Bulletin F28/55-21 dated May 19, 1980. U. Applies to F28 airplanes S/N 11003-11038, 11040, and 11991-11994 inclusive. Compliance required within six weeks after the effective date of this AD. Balance the aileron servo tabs per Fokker Service Bulletin F28/57-33, Revision 1, dated February 24, 1972. V. Applies to F28 airplanes S/N 11003-11123 inclusive, 11126, 11991, and 11992 which have accumulated 15,000 landings. Compliance required within two months after the effective date of this AD. To detect cracks in wing rear spar brackets, inspect per Fokker Service Bulletin F28/57-58, Revision 3, dated October 9, 1979. Repair cracks in accordance with the service bulletin. W. Applies to F28 airplanes S/N 11003-11123 inclusive and S/N 11126, 11991, and 11992. Compliance required within six months after the effective date ofthis AD. To minimize the chance of cracking bracket lugs, install chromium plated bolts and bronze bushings and inspect left-hand and right-hand rear spar bracket lugs per Fokker Service Bulletin F28/57-59 dated July 25, 1979. Repair cracked lugs in accordance with the service bulletin. X. Applies to F28 airplanes S/N 11111-11145 inclusive and S/N 11147, 11148, 11150, and 11151. Compliance required within three months after the effective date of this AD. To prevent performance deterioration, reseal the butt straps and boundary layer fences on the wing leading edge sections per Fokker Service Bulletin F28/57-61 dated April 14, 1980. 2. Alternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 3. Special 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. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). This amendment becomes effective August 23, 1982.
86-15-02: 86-15-02 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39- 5355. Applies to Model Mystere-Falcon 50 series airplanes, serial numbers 24 through 146, 148 through 158, 160, 161, and 162. Compliance is required as indicated below. To prevent engine failure due to fuel starvation, accomplish the following, unless previously accomplished: A. Within the next 21 days after the effective date of this AD, replace the actuators in the distributor blocks of the crossfeed valves and install a placard in accordance with Avion Marcel Dassault-Breguet Aviation Service Bulletin F52-28-17 (AMD-BA F50-182), dated April 4, 1986. B. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Special 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. All persons affected by this directive, who have not already received the appropriate service bulletin from the manufacturer, may obtain copies upon request to Falcon Jet Corporation, Customer Support Department, Teterboro Airport, Teterboro, New Jersey 07608. 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. This amendment becomes effective July 28, 1986.
2017-16-10: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 777 airplanes. This AD was prompted by reports of cracks on the underwing longerons. This AD requires repetitive inspections of the left and right side underwing longerons for any crack, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2010-26-13: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Several cases of aileron terminal quadrant support brackets that were manufactured using sheet metal have been found cracked on DHC-8 Series 300 aircraft. Investigation revealed that the failure of the support bracket was due to fatigue. Failure of the aileron terminal quadrant support bracket could result in an adverse reduction of aircraft roll control. * * * * * These conditions could result in loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2023-02-09: The FAA is superseding Airworthiness Directive (AD) 2007-10- 04, which applied to all McDonnell Douglas Model DC-9-81 (MD-81), DC-9- 82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. AD 2007-10-04 required repetitive inspections to detect cracks in the horizontal stabilizer, and related investigative and corrective actions if necessary. Since the FAA issued AD 2007-10-04, it has been determined that certain compliance times and repetitive intervals must be reduced to address the unsafe condition. This AD continues to require the actions specified in AD 2007-10-04 with revised compliance times for certain actions. The FAA is issuing this AD to address the unsafe condition on these products.
91-21-06: 91-21-06 BRITISH AEROSPACE: Amendment 39-8053. Docket No. 91-NM-122-AD. Applicability: Model BAe 146-100A series airplanes, Serial Numbers up to and including E1152; Model BAe 146-200A series airplanes, Serial Numbers up to and including E2156; and Model BAe 146-300A series airplanes, Serial Numbers up to and including E3157; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To ensure engine fire extinguisher medium is discharged to proper locations in the event of an engine fire, accomplish the following: (a) Within 30 days after the effective date of this AD, perform a visual inspection to detect chafing of the extinguisher pipe and clamp assemblies between the two fire extinguisher bottles in the engine nose cowls; and ensure that adequate clearance exists between the three pipe assemblies and the adjacent equipment and structure; in accordance with the instructions in British Aerospace Inspection Service Bulletin 26-A29, Revision 2, dated January 14, 1991. (b) Prior to the installation of any nose cowl or engine/nose cowl combination on an operational airplane, perform a visual inspection to detect chafing of the extinguisher pipe and clamp assemblies between the two fire extinguisher bottles in the engine nose cowls; and ensure that adequate clearance exists between the three pipe assemblies and the adjacent equipment and structure; in accordance with the instructions in British Aerospace Inspection Service Bulletin 26-A29, Revision 2, dated January 14, 1991. (c) If any damaged extinguisher pipe and clamp assembly is identified as a result of the inspection required by paragraph (a) or (b) of this AD, prior to further flight, repair or replace the damaged assembly in accordance with instructions in British Aerospace Inspection Service Bulletin 26-A29, Revision 2, dated January 14, 1991. (d) 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. (f) The inspection and repair or replacement requirements shall be done in accordance with British Aerospace Inspection Service Bulletin 26-A29, Revision 2, dated January 14, 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-8053, AD 91-21-06) becomes effective on November 19, 1991.
2001-26-24: This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; and C-9 airplanes that requires replacing the transformer ballast assembly in the pilot's console with a new, improved ballast assembly. The actions specified by this AD are intended to prevent overheating of the ballast transformers due to aging fluorescent tubes that cause a higher power demand on the ballast transformers, which could result in smoke in the cockpit. This action is intended to address the identified unsafe condition.
2001-26-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-300 series airplanes, that requires, for certain airplanes, a one-time torque test (inspection) of the attachment bolts of the forward engine mount vibration isolators to determine if the bolts are adequately torqued, and corrective action, if necessary. For all airplanes, this amendment prohibits installation of an attachment bolt on the forward engine mount vibration isolators, unless the attachment bolt is torqued within certain limits. These actions are necessary to prevent failure of the engine mount, which could result in separation of the engine from the airplane. This action is intended to address the identified unsafe condition.
97-21-01 R1: 97-21-01 R1 MT-PROPELLER ENTWICKLUNG GMBH: Amendment 39-11206. Docket 97-ANE-36-AD. Revises AD 97-21-01, Amendment 39-10154. Applicability: MT-Propeller Entwicklung GMBH Model MTV-3-B-C/L250-21 propellers. These propellers are installed on but not limited to Sukhoi 29 aircraft. Note 1: This airworthiness directive (AD) applies to each propeller 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 propellers 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 prevent propeller hub cracks, which could result in propeller blade separation and possible loss of control of the airplane, accomplish the following: (a) Within 50 hours time-in-service (TIS) after the effective date of this AD, accomplish the following: (1) Perform an initial dye penetrant or eddy current inspection of propeller hub, part number (P/N) B-050 or A-909-A, in accordance with paragraph (a) of MT-Propeller Entwicklung GMBH Service Bulletin (SB) No. 12C, dated March 4, 1998. The dye penetrant inspection may be done on-wing, but the eddy current inspection must be performed in an FAA-approved propeller repair station. (2) If the propeller hub is found to be cracked, prior to further flight, remove the existing propeller hub and replace with a serviceable propeller hub. (3) Rework propeller hubs, P/N B-050, by chamfering the hub bore to 0.08 inch x 45 degrees (for further information, see Detail Y of MT-Propeller Entwicklung GMBH SB No. 12C, dated March 4, 1998). Mark hubs that have been reworked in accordance with AD 97-21-01, or this revised AD, with the letters SB12C using a metal impression stamp (1/8 inch round bottom characters) above the propeller hub serial number and part number, located in the transition area between propeller blades 1 and 2 and the pitch change cylinder. (b) Thereafter, perform dye penetrant or eddy current inspections, in accordance with paragraph (a) of MT-Propeller Entwicklung GMBH SB No. 12C, dated March 4, 1998. The dye penetrant inspection may be done on-wing, but the eddy current inspection must be performed in an FAA-approved propeller repair station: (1) For propellers with hubs, P/N B-050, inspect at intervals not to exceed 50 hours TIS, or 6 months since last inspection, whichever occurs first. (2) For propellers with hubs, P/N A-909-A, inspect at intervals not to exceed 200 hours TIS, or 12 months since last inspection, whichever occurs first. (3) If the propeller hub is found to be cracked, prior to further flight, remove the existing propeller hub and replace with a serviceable propeller hub. (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, Boston Aircraft Certification Office. Operators shall submit their requests through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Boston Aircraft Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Boston Aircraft Certification Office. (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 aircraft to a location where the inspection requirements of this AD can be accomplished. (e) The actions required by this AD shall be accomplished in accordance with the following MT-Propeller Entwicklung GMBH SB: Document No. Pages Date 12C 1-3 March 4, 1998 Total pages: 3. 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 MT- Propeller Entwicklung GMBH, Airport Straubing-Wallmuhle, D-94348 Atting, Germany; telephone (0 94 29) 84 33, fax (0 94 29) 84 32, Internet: "propeller@aol.com". Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (f) This amendment becomes effective on August 27, 1999.
2017-16-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a report of a Krueger flap bullnose departing an airplane during taxi, which caused damage to the wing structure and thrust reverser. This AD requires a one-time detailed visual inspection for discrepancies in the Krueger flap bullnose attachment hardware, and related investigative and corrective actions, if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-16-11: We are adopting a new airworthiness directive (AD) for certain models of Lycoming Engines reciprocating engines. This AD requires an inspection of connecting rods and replacement of affected connecting rod small end bushings. This AD was prompted by several reports of connecting rod failures resulting in uncontained engine failure and in- flight shutdowns (IFSDs). We are issuing this AD to address the unsafe condition on these products.
2001-26-15: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, and -87 series airplanes, and Model MD-88 airplanes, that requires a detailed visual inspection of certain wires to detect chafing and preload; repair, if necessary; and modification of certain wire assemblies. This action is necessary to prevent insufficient clearance between wire assemblies and the ice protection airduct and airstair door interlock rod; chafing; and consequent arcing of wire assemblies. Such arcing could result in damage to electronic equipment and adjacent structures, or cause the insulation blankets to ignite, which could result in smoke and fire in the flight deck and main cabin. This action is intended to address the identified unsafe condition.
2001-26-16: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9-81, -82, -83, and -87 series airplanes, and Model MD-88 airplanes, that requires replacing the interface connectors of the cabin fluorescent lighting ballast in the wiring harness of the overhead stowage compartment with new connectors. In lieu of the required replacement, this AD requires adding interface seals to the existing interface connectors of the cabin fluorescent lighting ballast between certain stations and reidentifying the connector assemblies. This action is necessary to prevent electrical shorting and arcing due to the presence of water in the lighting ballast interface connectors, which could result in smoke in the main cabin. This action is intended to address the identified unsafe condition.
2017-16-03: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) Model PA-46-600TP (M600) airplanes. This AD requires inspection of the aft wing spars with repair as necessary. This AD was prompted by a report from Piper of the aft wing spar cracking during wing assembly. We are issuing this AD to address the unsafe condition on these products.
87-13-06: 87-13-06 BRITISH AEROSPACE (BAe): Amendment 39-5657. Applies to HP 137 Mk1, Jetstream Series 200, and Jetstream Model 3101 (includes Model 3100) (all serial numbers) airplanes equipped with main landing gear legs, Type Nos. 1863, 1863/4A, 1863/4B, 1863/4C, B00A702850A, and B00A702925A for left-hand installation and Type Nos. 1864, 1864/4A, 1864/4B, 1864/4C, B00A702851A, and B00A702926A for right-hand installation, certificated in any category. Compliance as required in Table 1 below, unless already accomplished: TABLE 1 INSPECTION THRESHOLD CRITERIA CUMULATIVE SERVICE CRITERIA FOR INITIAL INSPECTION CRITERIA FOR RECURRING INSPECT ION Less than 13,229 lb. MGTW* 13,229- 14,550 lb. MGTW* 14,551- 15,322 lb. MGTW* ALL WEIGHTS No record of Landings 9,500 hours 7,000 hours 6,000 hours 500 hours Aircraft Landings Recorded 19,000 Landings 14,000 Landings 12,000 Landings 1,000 Landings Gear Component Landings Recorded 19,000 Landings 14,000 Landings 12,000 Landings 1,000 Landings Installed Overhauled Gear** Within 30 days Within 30 days Within 30 days 1,000 Landings Spare Gear** Prior To Installation Prior To Installation Prior To Installation 1,000 Landings * Maximum (Certificated) Gross Takeoff Weight ** With No Record of Landings And No Compliance To S/B 32-JA860812 To prevent loss of ground directional control, collapse, or failure of the main landing gear, accomplish the following: (a) Inspect the main landing gear legs using non-destructive test (NDT) procedures described in BAe Air Weapons Division, S/B 32-32 dated July 22, 1986, initially within 30 days after the effective date of this AD or the inspection threshold criteria specified in Table 1 of this AD, whichever occurs later, and thereafter at the recurring interval specified in Table 1 of this AD. (b) If indications of cracks are found, prior to further flight, replace the gear with a serviceable unit. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) The intervals between repetitive inspections required by this AD may be adjusted up to 20 percent of the specified interval to allow accomplishment of these inspections concurrent with other scheduled maintenance of the airplane. (e) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium; Telephone (322) 513.38.30. All persons affected by this directive may obtain copies of the documents referred to herein upon request to British Aerospace plc, Manager, Product Support, Civil Aircraft Division, Prestwick Airport, Ayrshire, KA9 2RW, Scotland; or British Aerospace, Inc., Technical Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041; or may examine the documents referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on June 30, 1987.
2025-10-02: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model EC225LP helicopters. This AD was prompted by the identification of missing electrical bonding on a certain part-numbered additional and optional search light (search light). This AD requires installing an electrical bonding braid modification. These actions are specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2010-25-06: We are adopting a new airworthiness directive (AD) for certain Model 737-200, -300, -400, and -500 series airplanes. This AD requires repetitive inspections for cracking of certain fuselage frames and stub beams, and corrective actions if necessary. This AD also provides for an optional repair, which would terminate the repetitive inspections. For airplanes on which a certain repair is done, this AD also requires repetitive inspections for cracking of certain fuselage frames and stub beams, and corrective actions if necessary. This AD results from reports of the detection of fatigue cracks at certain frame sections, in addition to stub beam cracking, caused by high flight cycle stresses from both pressurization and maneuver loads. We are issuing this AD to detect and correct fatigue cracking of certain fuselage frames and stub beams and possible severed frames, which could result in reduced structural integrity of the frames. This reduced structural integrity can increase loading in the fuselage skin, which will accelerate skin crack growth and could result in rapid decompression of the fuselage.
2001-26-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 series airplanes, that requires removal of the shear pins that keep the rear fixed panels on the center landing gear closed and installation of new solid shear pins. This amendment is prompted by issuance of mandatory continuing airworthiness information from a foreign airworthiness authority. This action is intended to prevent the shear pins on the rear fixed panels of the center landing gear from failing, which could result in loss of the panels during flight with consequent injury to people on the ground. This action is intended to address the identified unsafe condition.
82-24-01: 82-24-01 ENSTROM HELICOPTER CORPORATION: Amendment 39-4497. Applies to Model F-28A, F-28C, F-28F, 280, 280C, and 280F helicopters certificated in all categories. Compliance required as indicated unless already accomplished. To prevent possible in-flight drivebelt clutch disengagement, accomplish the following: (a) Before further flight after the effective date of this AD, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection: (1) Inspect the drivebelt clutch mechanism, in accordance with Enstrom Service Information Letter 0080, Revision A, dated August 4, 1982, or FAA approved equivalent, and the Maintenance/Manual Supplement for the respective Models, to ascertain that the mechanism is properly rigged. NOTE: When properly rigged the clutch actuating cable should move freely allowing full clutch engagement. Clutch mechanisms experiencing binding of the clutch actuating cable, although properly rigged and lubricated, may have lubricant hardened in the cable assembly due to engine heat. (2) Replace any cable found to bind, preventing full clutch engagement, prior to further flight with suitable airworthy parts. (3) Lubricated the clutch actuating cable with Aero Shell 14 or FAA approved equivalent. (b) Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, install clutch cable heat shield P/N 28-16542-11 in accordance with Enstrom Service Directive Bulletin 0055, Revision A, dated April 2, 1982, or FAA approved equivalent. NOTE: Enstrom Helicopter Models equipped with right pilot-in-command kits P/N 28- 01002 or P/N 28-01012; or electric clutch actuator kit P/N 28-01005 are exempt from this paragraph. (c) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished, install clutch engagement overcenter lock warning light kit P/N 28- 19035-3 in accordance with EnstromService Directive Bulletin 0061 dated September 20, 1982, or FAA approved equivalent. (d) Any equivalent method of compliance with this AD must be approved by the Manager, Chicago Aircraft Certification Office, Federal Aviation Administration, 2300 East Devon Avenue, Des Plaines, Illinois 60018. (e) In accordance with FAR 21.197, flight is permitted to a base where the inspection required by this AD may be accomplished. This amendment becomes effective November 30, 1982.
87-16-07: 87-16-07 (HONEYWELL, INC., SPERRY COMMERCIAL FLIGHT SYSTEMS DIVISION (formerly Sperry Corporation, Aerospace and Marine Group): Amendment 39-5696. Applies to all digital and analog Electronic Flight Instrument Systems (EFIS) Models EDZ 601, 603, 801, 803, 611, and 811 installations, which include a multifunction display symbol generator. Compliance required within 30 days after the effective date of this AD, unless previously accomplished. To eliminate erroneous display of the angle of attack fast/slow presentation, accomplish the following: A. For the analog type EFIS equipment: Exchange Multifunction Display Symbol Generator (MG) P/N's 7007061-603, -803, -601, -801, and 901 with the same part numbers which have Modification (Mod) K or subsequent incorporated; accomplish this in accordance with Paragraph 2, "Accomplishment Instructions of Honeywell Service Bulletin 21-1986-200, dated January 20, 1987. B. For the digital type EFIS equipment: Exchange MG P/N's7007321-811 and -611 with the same part numbers which have Modification (Mod) L or subsequent incorporated; accomplish this in accordance with Paragraph 2, "Accomplishment Instructions" of Honeywell Service Bulletin 21-1987-06, dated May 15, 1987. C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Honeywell Inc., Sperry Commercial Flight System Division, P.O. Box 29000, Phoenix, Arizona 85038-9000. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at Western Aircraft Certification Office, 15000 Aviation Boulevard, Hawthorne, California. This Amendment becomes effective August 20, 1987.
2017-15-09: We are adopting a new airworthiness directive (AD) for certain Diamond Aircraft Industries GmbH Model DA 42 airplanes. This AD requires installing engine exhaust pipe clamps with spring washers, repetitively inspecting the engine exhaust pipe clamps for cracks, and replacing the clamps if found cracked. This AD was prompted by cracks in the affected engine exhaust pipes, which could cause failure of the propeller regulating valve because of hot exhaust gases coming from the fractured pipes. We are issuing this AD to correct the unsafe condition on these products. [[Page 35631]]
2001-26-19: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires a one-time inspection for missing, damaged, or incorrectly installed parts in the separation link assembly on the deployment bar of the emergency escape system on the entry or service door, and installation of new parts, if necessary. This action is necessary to prevent failure of an entry or service door to open fully in the event of an emergency evacuation, which could impede exit from the airplane. This condition could result in injury to passengers or crewmembers. This action is intended to address the identified unsafe condition.