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91-06-15: 91-06-15 AIRBUS INDUSTRIE: Amendment 39-6941. Docket No. 90-NM-229-AD. Applicability: All Model A300, A310, and A300-600 series airplanes, on which Airbus Industrie Modification 8135 has not been accomplished, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the inability of the hydraulic power fire shut-off valves to close during emergency conditions, accomplish the following: A. Within 180 days after the effective date of this AD, conduct an inspection of the hydraulic power fire shut-off valves to identify faulty valves, as specified in Airbus Industrie Service Bulletins A300-29-096 (for Model A300 series airplanes), A310-29-2025 (for Model A310 series airplanes), and A300-29-6017 (for Model A300-600 series airplanes), all dated January 29, 1990. Any faulty valve identified must be removed and replaced with a modified valve prior to further flight, in accordance with the appropriate service bulletins. NOTE: The Airbus Industrie service bulletins reference Lucas Air Equipment Service Bulletin No. B38LC15-29-05, Revision 1, dated February 1990, for additional instructions. 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, 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. 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 documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6941, AD 91-06-15) becomes effective on April 22, 1991.
2014-16-22: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter, A330-200, A330-300, and A340-200, A340-300, A340-500, and A340-600 series airplanes. This AD was prompted by a determination that the service life limits of the cabin pressure control system (CPCS) safety valves installed on the aft pressure bulkhead were being exceeded. This AD requires repetitive replacement of the CPCS safety valves with serviceable valves. We are issuing this AD to prevent exceeding the service life limits of the CPCS safety valves, which, in the event of a failure, could result in excessive positive or negative differential pressure in the fuselage and consequent incapacitation or injuries to airplane occupants.
2006-04-13: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Model GIV-X and GV-SP series airplanes. This AD requires revising the Limitations section of the airplane flight manual by incorporating new procedures to follow in the event that the cockpit displays go blank or malfunction. This AD results from a report that all four of the cockpit flight panel display units simultaneously went blank during flight. We are issuing this AD to ensure that the flightcrew is advised of the appropriate procedures to follow in the event that the cockpit displays go blank or malfunction, which could result in a reduction of the flightcrew's situational awareness and possible loss of control of the airplane.
96-24-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72 series airplanes, that requires modification of the pitch uncoupling mechanism of both elevators. This amendment is prompted by reports of fatigue cracking of the pitch uncoupling mechanism and the torque tube of the elevator. Failure of the pitch uncoupling mechanism due to fatigue cracking could result in the uncommanded uncoupling of the elevators. The actions specified by this AD are intended to prevent such fatigue cracking and subsequent uncommanded uncoupling of the elevators, which could result in reduced controllability of the airplane.
79-16-01: 79-16-01 BEECH: Amendment 39-3520. Applies to Models 65 (Military Models L-23F or U-8F) (Serial Numbers L-1 through L-6, LC-1 through LC-180 and LF-7 through LF-76), 65- 80 (Serial Numbers LD-1 through LD-33, LD-35 through LD-45 and LD-47 through LD-150), 65-A80 and 65-A80-8800 (Serial Numbers LD-34, LD-46 and LD-151 through LD-244) and 65- 90 (Serial Numbers LJ-1 through LJ-67) airplanes certificated in all categories. COMPLIANCE: Required as indicated unless already accomplished. To detect fatigue cracks that may exist in certain critical components of the wing structure, accomplish the following: A) On or before September 7, 1979, except in no event is this one-time inspection required sooner than 30 days after the last inspection in accordance with AD 70-25-01 or 70-25- 04, whichever is applicable, inspect the right and left lower forward inboard and outboard wing to center section attach fittings (2 on left side and 2 on right side of the airplane) for cracks using dye penetrant procedures in accordance with the wing attachment fittings inspection instructions in Class I Beechcraft Service Instructions No. 0393-018 Revision I (Models 65, L-23F, U-8F, 65- 80, 65-A80 and 65-A80-8800) or No. 0394-018 (Model 65-90), whichever is applicable. NOTE: While inspecting the fittings with the wing attachment bolt removed, special attention should be directed towards inspection of the entire counterbore area in the recess of each fitting. B) Accomplish the dye penetrant inspections required by Paragraph "A" of this AD (1) using only those materials specified in Table I of this AD and, (2) in accordance with application and developing instructions provided by the manufacturer of the material except that the penetrant must remain on the surface for a minimum of 30 minutes before excess penetrant is removed and developer is applied. C) Within 48 hours after completion of the inspection required by Paragraph "A" of this AD, complete the reporting form included with this AD as Figure I and mail it to the address shown thereon. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) TABLE I Manufacturer Penetrant Remover Developer Ardox, Ltd. Ardox 906 Ardox 9PR 551 Ardox 9D6 Magnaflux Corp. SKL-HF SKL-SF Formula B Spot Chek SKC-S Spot Chek SKD-S Spot Chek Met-L-Chek Co. VP-31 E-59 D-70 Sherwin, Inc. Dubl-Chek DP-40 Dubl-Chek DR-60 Dubl-Chek D-100 Testing Systems, Inc. Flaw Finder DD60B Flaw Finder SD80B Flaw Finder AD70B Tokushu Toryo Co. PT (Visible) RT DT Turco Products Dy-Chek #2 Dy-Chek #3 Dy-Chek NAD Uresco, Inc. P-300A K-410E D-495 D) If fatigue cracks are found during the inspection required by Paragraph "A" of this AD, prior to further flight, replace specified wing and center section components with new production parts in accordance with instructions in Beechcraft ServiceInstructions No. 0393-018 Revision I (Models 65, L-23F, U-8F, 65-80, 65-A80 and 65-A80-8800) or 0394-018 (Model 65- 90) whichever is applicable. If stress corrosion cracks are found during the inspection required by Paragraph "A" of this AD, prior to further flight, replace right and left lower forward outboard wing to center section attach fittings (2 right side and 2 left side) with new fittings in accordance with the above noted Beechcraft Service Instructions. E) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. F) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA Central Region. This Amendment becomes effective August 6, 1979. REPORTING FORM Airplane Model Number___________________ ____ Airplane Serial Number _______________________ Date of inspection required by this AD . Resultsof inspection required by this AD . Airframe total hours time-in-service . Total hours time-in-service on fittings inspected: Left outboard . Left inboard . Right outboard . Right inboard . Airplane usage: (Check those for which airplane has been used, if known) 1. General service . 2. Executive Transport . 3. Air Taxi service . 4. Tours of gusty areas . 5. Calibration or patrolling of items on ground or water . 6. Weather studies . Show approximate percentages (%) of airframe total hours time-in-service, if known, for the following: 1. % of flight time accumulated above 10,000 feet MSL . 2. % of flight time accumulated below 10,000 feet MSL . 3. Approximate indicated airspeed: Above 10,000 feet MSL . Below 10,000 feet MSL . 4. Approximate number of flight hours per landing . Name and telephone number of person who can supply more information about usage of the airplane , phone number . FIGURE 1 Mailing Address: Federal Aviation Administration Wichita Engineering and Manufacturing District Office Attention: Airframe Unit Room 238, Terminal Building Mid-Continent Airport Wichita, Kansas 67209
87-17-09: 87-17-09 SHORT BROTHERS PLC: Amendment 39-5713. Applies to Short Brothers PLC Model SD3-60 series airplanes, equipped with Dowty Rotol nose under carriage type numbers 200921001 or 200921003, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent loss of structural integrity of the nose landing gear, as a result of a loose shock absorber lower pin, accomplish the following: A. Within 90 days after the effective date of this AD, install a new locking bolt for the nose landing gear shock absorber pin in accordance with the Accomplishment Instructions of Shorts Service Bulletin No. SD360-32-20, dated May 1985. 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 the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Short Brothers PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. 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 September 22, 1987.
2000-02-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes. This action requires a one-time visual inspection to determine the part numbers of the beta back-up test switches of the propeller control system, and replacement of the switches, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent loss of the automatic overspeed protection of the propeller control system, which could result in a propeller overspeed condition and possible damage to the engine and propeller.
2014-16-20: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes. This AD was prompted by an analysis of the impacts of extended service goal activities on Airbus Model A300 series airplanes. This AD requires revising the maintenance or inspection program. We are issuing this AD to prevent failure of flight critical systems.
90-08-06: 90-08-06 AEROSPATIALE: Amendment 39-6566. Docket No. 89-NM-251-AD. Applicability: All Model ATR42 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of the main landing gear wheel, due to cracked spokes, accomplish the following: A. For wheels with Loral Part Number (P/N) 5006856, 5006856-1, and 5006856-2, having serial numbers OCT83-001 through OCT86-377, with the exception of serial numbers OCT86-001 through OCT86 071: Within 7 days or 100 landings after the last inspection in accordance with AD 88-09-04, whichever occurs later, perform a visual inspection of the inboard wheel halves, with the airplane jacked, to detect cracks, in accordance with Loral Systems Group Service Bulletin ATR42-32-40-1, Revision 2, dated June 23, 1987. Repeat the inspection at intervals not to exceed 7 days or 100 landings, whichever occurs later. If a crack is detected, only one additional landing may be made after the detection of that crack before the cracked inboard wheel half must be replaced. B. For wheels with Loral Part Number (P/N) 5006856, 5006856-1, and 5006856-2, having serial numbers OCT83-001 through OCT86-377, with the exception of serial numbers OCT86-001 through OCT86-071: At each tire change, perform an eddy current inspection or other nondestructive test of the inboard wheel halves to detect cracks, in accordance with Loral Systems Group Service Bulletin ATR42-32-40-1, Revision 2, dated June 23, 1987. Replace any cracked inboard wheel half before further flight. NOTE: MLG wheels with Loral Part Number 5006856-2, serial numbers OCT86-001 through OCT86-071 and NOV86-072 through AUG87-376, are factory built new wheels, and are not subject to the repetitive inspection requirements of paragraphs A. and B., above. C. Replacement of inboard wheel halves with a new reinforced half wheel and replacement of the existing hub spacer with a modified hub spacer, in accordance with Aerospatiale Service Bulletin ATR42-32-0017, dated January 19, 1988, or Revision 1, dated May 20, 1988 (reference Loral Service Bulletin ATR42-32-40-4, dated July 15, 1987), constitutes terminating action for the repetitive inspection required by paragraphs A. and B., above. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either 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. All persons affected by this directive who have not already received the appropriate servicedocuments from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment supersedes Amendment 39-5907, AD 88-09-04. This amendment (39-6566, AD 90-08-06) becomes effective on May 11, 1990.
2000-02-17: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc RB211 Trent 768-60, 772-60, and 772B-60 series turbofan engines. This action requires initial and repetitive visual inspections for flank wear on intermediate pressure turbine (IPT) shaft splines and intermediate pressure compressor (IPC) rear stub shaft splines. Components that show excessive flank wear must be replaced with serviceable parts. This amendment is prompted by reports of worn IPT shaft splines discovered at overhaul. The actions specified in this AD are intended to prevent IPT and IPC shaft spline flank wear, which could result in loss of drive between the IPT and IPC, leading to an IPT overspeed and possible disk burst, uncontained engine failure, and potential damage to the aircraft.