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91-04-03: 91-04-03 BRITISH AEROSPACE: Amendment 39-6890. Docket No. 90-NM-234-AD. Applicability: All Model BAe 125-800A series airplanes, certificated in any category. Compliance: Required within 60 days after the effective date of this AD, unless previously accomplished. To detect damage to main landing gear (MLG) components and to prevent reduced structural integrity of the MLG, accomplish the following: A. Perform a visual inspection of the left and right MLG side stay to wing pick-up fitting for adequate clearance, in accordance with British Aerospace Service Bulletin 32-224, Revision 1, dated August 30, 1990. 1. If clearance is less than 0.025 inch, prior to further flight, perform a dye penetrant inspection and repair, in accordance with British Aerospace Service Bulletin 57-72, dated January 28, 1990, and then proceed to paragraph B. of this AD. 2. If there is a minimum clearance of 0.025 inch around the full circumference, prior to further flight,proceed to paragraph B. of this AD. B. Disassemble, clean, lubricate, and reassemble and recheck clearance in accordance with British Aerospace Service Bulletin 32-224, Revision 1, dated August 30, 1990. 1. If a minimum clearance of 0.025 inch does not exist, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. 2. If there is a minimum clearance of 0.025 inch, proceed to paragraph C. of this AD. C. Unless accomplished in accordance with paragraph A.1. of this AD, perform a dye penetrant inspection of the left and right MLG side stay attachment lugs, in accordance with British Aerospace Service Bulletin 57-72, dated January 28, 1990. 1. If a crack is found, prior to further flight, repair in accordance with paragraph 2.A.(5) of the service bulletin, and repeat dye penetrant inspection to ensure all cracks have been removed. 2. If cracks are still evident, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. 3. If no cracks are found, prior to further flight, thoroughly degrease the blended area, restore protective treatment and surface finish, reinstall side stay assembly, and torque tighten upper side stay locating pin retaining nut to 500 inch-pounds +/- 50 inch-pounds in accordance with paragraphs 2.A.(9) and (10) of the service bulletin. D. Perform a visual inspection of the left and right MLG side stay center pivot for distortion, in accordance with British Aerospace Service Bulletin 32-225, dated May 30, 1990. 1. If distortion is less than 0.002 inch, prior to further flight, reinstall nut to side stay center pivot, in accordance with paragraph 2.A.(3) of the service bulletin. 2. If distortion is greater than 0.002 inch, prior to further flight, discard nut and replace with new nut, in accordance with paragraphs 2.A.(4) through 2.A.(9)of the service bulletin. 3. If a side stay center pivot nut was found to be distorted and was replaced, prior to further flight, remove the affected side stay from the airplane, disassemble, and perform the following, in accordance with British Aerospace Service Bulletin 32-227, dated August 30, 1990; or Revision 1, dated October 12, 1990: a. Conduct a visual inspection for cracks using an 8X magnifying glass. b. Conduct an eddy current inspection of the upper side stay assembly. c. Conduct a magnetic particle inspection of the lower side stay assembly. 4. If cracked parts are found, prior to further flight, replace with new parts having the same part numbers, and accomplish the following: a. Restore protective treatment, bond any detached washers, replace any worn or damaged items, and reassemble side stay upper arm to lower arm, and reinstall side stay on airplane in accordance with the service bulletin. b. Perform adjustment/test procedures in accordance with the service bulletin. E. 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, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. F. 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6890, AD 91-04-03) becomes effective on March 18, 1991.
2015-25-08: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 777 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the lap splices of the aft pressure bulkhead webs are subject to widespread fatigue damage (WFD) on aging Model 777 airplanes that have accumulated at least 38,000 total flight cycles. This AD requires repetitive inspections for any crack in the aft webs of the radial lap splices of the aft pressure bulkhead, and, if necessary, corrective actions. We are issuing this AD to detect and correct fatigue cracking in the aft webs of the radial lap splices of the aft pressure bulkhead; such cracking could result in reduced structural integrity of the airplane, decompression of the cabin, and collapse of the floor structure.
2000-21-12: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0100 series airplanes, that requires replacement of the anti-skid control boxes with improved units. This action is necessary to prevent electromagnetic interference with the anti-skid control system, which could result in reduced brake pressure during low-speed taxiing, and consequent reduced controllability and performance of the airplane. This action is intended to address the identified unsafe condition.
2000-21-11: This amendment supersedes an existing airworthiness directive (AD), applicable to all Raytheon Model DH.125-1A, -3A, and -400A series airplanes, that currently requires a one-time inspection to detect scoring of the upper fuselage skin around the periphery of the cockpit canopy blister interface, and repair, if necessary. This amendment expands the applicability of the existing AD to include additional airplanes, and requires that the actions be accomplished in accordance with revised service information for the newly added airplanes. This amendment is prompted by additional reports indicating that scoring has been detected on the upper fuselage skin around the periphery of the cockpit canopy blister interface. The actions specified by this AD are intended to detect and correct scoring of the upper fuselage skin around the periphery of the cockpit canopy blister interface, which could result in reduced structural integrity of the fuselage, and consequent cabin depressurization. The incorporation by reference of Raytheon Aircraft Service Bulletin SB 53-93, dated May 16, 1996, as listed in the regulations, was approved previously by the Director of the Federal Register as of June 6, 1997 (62 FR 24013, May 2, 1997).
91-14-04: 91-14-04 BRITISH AEROSPACE: Amendment 39-7046. Docket No. 90-NM-271-AD. Applicability: Model BAe 146-100A and 146-200A series airplanes, as listed in British Aerospace Service Bulletin 24-60, dated May 31, 1990, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure or improper functioning of the wing flap, landing gear anti-skid, and turbine vibration indication systems, accomplish the following: A. Within 30 days after the effective date of this AD, perform a visual inspection of the earth stud on the avionics rack at Frame 17, in accordance with British Aerospace Service Bulletin 24-60, dated May 31, 1990. 1. If the earth stud is approximately 33.0 inches from the airplane's center line, prior to further flight, perform a visual inspection of the adjacent wiring harnesses for chafing damage, and reclip any harnesses to ensure adequate clearance between the wire harnesses and the earth stud, in accordance with the service bulletin. Repair or replace any damaged wires prior to further flight. 2. If the earth stud is not positioned approximately 33.0 inches from the airplane's center line, prior to further flight, accomplish the following: a. Perform an inspection of the adjacent wiring harnesses for signs of chafing damage, and, if damage is found, repair or replace any damaged wires prior to further flight in accordance with the service bulletin. b. Remove the existing earth stud and install a new earth stud having the same part number in accordance with Figure 1 of the service bulletin. c. Move and resecure any wiring harnesses that may contact the earth stud, in accordance with the service bulletin. B. 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 Avionics Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. 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. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-7046, AD 91-14-04) becomes effective on July 29, 1991.
2016-01-16: We are superseding Airworthiness Directive (AD) 2002-23-20, for certain Dassault Aviation Model FALCON 900EX and MYSTERE-FALCON 900 airplanes. AD 2002-23-20 required repetitive operational tests of the flap asymmetry detection system to verify proper functioning, and repair if necessary; repetitive replacement of the inboard flap jackscrews with new or reconditioned jackscrews; and repetitive measurement of the screw/nut play of the jackscrews on the inboard and outboard flaps to detect discrepancies, and corrective action if necessary. AD 2002-23-20 also required a revision of the airplane flight manual. Since we issued AD 2002-23-20, the maintenance manual has been revised. This AD requires revising the maintenance or inspection program, as applicable, to include the maintenance tasks and airworthiness limitations [[Page 3321]] specified in the Airworthiness Limitations section of the airplane maintenance manual. This AD also removes the Model FALCON 900EX airplanesfrom the applicability. We are issuing this AD to prevent reduced structural integrity of the airplane.
2000-21-13: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-300 series airplanes, that requires revising the Airplane Flight Manual. This action is necessary to prevent an undetected dragging parking brake, and consequent decreased acceleration during the takeoff roll, increased takeoff distance, and possible runway overrun. This action is intended to address the identified unsafe condition.
2000-21-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney JT8D-200 series turbofan engines, that currently requires revisions to the Time Limits Section (TLS) of the JT8D-200 Turbofan Engine Manual to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD adds additional critical life-limited parts for enhanced inspection. This proposal is prompted by additional focused inspection procedures that have been developed by the manufacturer. The actions specified by this proposed AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2000-21-09: This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney (PW) PW2000 series turbofan engines, that requires revisions to the time limit sections (TLS) of the manufacturer's Engine Manuals to include enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action adds additional critical life-limited parts for enhanced inspection. This amendment is prompted by additional focused inspection procedures for other critical life-limited rotating engine parts that have been developed by the manufacturer. The actions specified in the AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
83-07-10: 83-07-10 SIAI-MARCHETTI: Amendment 39-4613. Applies to Models S205-20F and S205- 20R (Serial Numbers 222, 4-101, 4-102, 4-106, 4-172, 4-206, 4-241, 5-303, 003, 103, 106, 215, 218, 220, 221, 227, 237, 238, 345 thru 347, 349, 351, 355, 357, 359 thru 363, 366 thru 368, 375 thru 377, 4-107 thru 4-113, 4-115, 4-116, 4-133 thru 4-139, 4-141, 4-159 thru 4-163, 4-173, 4- 174, 4-197 thru 4-202, 4-205, 4-208 thru 4-215, 4-236 thru 4-240, 4-242 thru 4-244, 4-248, 4- 249, 4-251 thru 4-253, 4-255, 4-269 thru 4-271, 4-273, 4-274, 4-275, 4-276, 4-282, 5-302, and 06-001 thru 06-040) airplanes certificated in any category. Compliance: Required as indicated unless already accomplished. To prevent loss or failure of the attachment that connects the butterfly valve to the shaft of the engine induction valve assembly, within the next 100 hours time-in-service after the effective date of this AD, accomplish the following: a) Modify the attachment of the butterfly valve (Part Number (P/N) 205-5-260-09) to the shaft (P/N 205-5-260-07) of the engine induction valve assembly (P/N 205-5-260-101 or P/N 205-5-260-01) in accordance with the "Instruction" section of SIAI-Marchetti Service Bulletin No. 205B55, dated December 11, 1981. b) Airplane may be flown in accordance with FAR 21.197 to a location where this Airworthiness Directive (AD) can be accomplished. c) 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 April 14, 1983.