Results
96-15-06: 96-15-06 PRATT & WHITNEY: Amendment 39-9714. Docket 96-ANE-19. Applicability: Pratt & Whitney (PW) JT8D-200 series turbofan engines incorporating affected first stage fan hubs, Part Number (P/N) 5000501-01, identified by any of the following Serial Numbers: T50693, T50823, T50827, R32926, R32960, P66756. These engines are installed on but not limited to McDonnell Douglas MD-80 series aircraft. NOTE: This airworthiness directive (AD) applies to each engine 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 engines 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 the initiation and propagation of a fatigue crack, fracture of the fan hub, uncontained engine failure, and damage to the aircraft, accomplish the following: (a) Prior to further flight, remove from service all affected first stage fan hubs, P/N 5000501-01, identified by Serial Numbers listed in the applicability paragraph of this AD, and replace with serviceable parts. (b) An alternative method of compliance or adjustment of compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (c) This amendment becomes effective September 3, 1996, to all persons except those persons to whom it was made immediately effective by priority letter AD 96-15-06, issued July 16, 1996, which contained the requirements of this amendment.
95-19-18: 95-19-18 TWIN COMMANDER AIRCRAFT CORPORATION: Amendment 39-9379; Docket No. 95-CE-20-AD. Applicability: The following airplane models and serial numbers, certificated in any category. Models Serial Numbers 680T and 680V 1473 through 1720 680W 1721 through 1850 681 6001 through 6072 690 11001 through 11079 690A 11100 through 11344 690B 11350 through 11566 690C 11600 through 11735 690D 15001 through 15042 695 95000 through 95084 695A 96000 through 96100 695B 96201 through 96208 NOTE 1: This AD applies to each airplane identified in the preceding applicability revision, regardless of whether it has been 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 (c) of this AD. The request should includean 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 within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent structural damage to the airplane caused by excessive turbulence, which could result in loss of the airplane, accomplish the following: (a) Install the placard (to the windshield centerpost) and incorporate the airplane flight manual/pilot operating handbook (AFM/POH) revisions that are included with the kits presented below. The placard and AFM/POH revisions provide warnings to the airplane operator of the importance of observing the Turbulent Air Penetration and Maneuvering speeds: Kit No. Model Affected SB220-1 680T SB220-2 680V SB220-3 680W SB220-4 681 SB220-5 690 SB220-6 690A SB220-7 690B SB220-8 690C SB220-9 690D SB220-10 695 SB220-11 695A SB220-12 695B NOTE 2: Twin Commander Service Bulletin No. 220, dated February 1, 1995, relates to the subject of this AD, and references the SB220 service kits specified above. (b) 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. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Northwest Mountain Region, 1601 Lind Avenue S.W., Renton, Washington 98055-4056. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. (d) All persons affected by this directive may obtain copies of the kits referenced above that include the placard and the AFM revisions upon request to the Twin Commander Aircraft Corporation, 19010 59th Drive, NE., Arlington, Washington 98223; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (e) This amendment becomes effective on October 25, 1995.
2010-12-09: The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc. auxiliary power unit (APU) models GTCP36- 150(R) and GTCP36-150(RR). This AD requires inspecting the fuel control unit (FCU) differential pressure (Delta P) sleeve bore for erosion, replacing the FCU if it fails the inspection, and installing a fuel deflector on the Delta P sleeve of the FCU. This AD results from eight reports of fuel leakage from the FCU. We are issuing this AD to prevent fuel leakage in the APU compartment, which could lead to ignition of fuel vapor, creating a fire and explosion hazard resulting in injury, and damage to the APU and the airplane.
96-03-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream ATP airplanes, that requires inspections to detect fatigue cracking and corrosion in the gussets of the rear passenger door and rear baggage door apertures, and replacement of the gussets, if necessary. This amendment is prompted by fatigue tests which indicated that fatigue cracking and corrosion can occur in these gussets. The actions specified by this AD are intended to prevent degradation of the structural integrity of the fuselage pressure vessel due to the problems associated with cracking and corrosion in the gussets of the rear passenger door and rear baggage door apertures.
2010-11-11: We are adopting a new airworthiness directive (AD) for certain Model 60 airplanes. This AD requires revising the Tire-Servicing section of the airplane maintenance manual and revising the Tires Limitation section of the airplane flight manual to incorporate revised procedures for servicing tires and checking for proper tire inflation. This AD results from a report of the main landing gear tires blowing out during a takeoff roll. We are issuing this AD to prevent tire failure, which could result in failures of the braking and thrust reverser systems. In a critical phase of operation such as takeoff, loss of airplane control may result.
90-24-10: 90-24-10 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6813. Docket No. 90-NM-14-AD. Applicability: Model DHC-7 series airplanes, Serial Numbers 1 through 10, and 12 through 27, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent corrosion and reduced structural capability of the wings accomplish the following: A. Within 180 days after the effective date of this AD, and thereafter at intervals not to exceed one year, perform a low frequency eddy current inspection of the inboard and outboard fuel tank lower wing skins in accordance with the procedure specified in Part 6, Chapter 57-10- 01, of the de Havilland DHC-7 Nondestructive Testing (NDT) Manual, PSM 1-7-7A. B. If corrosion is found as a result of the inspections required by paragraph A. of this AD, accomplish the following. Accomplishment of these actions constitutes terminating action for the repetitive inspections of the inboard and/or outboard fuel tank area, as appropriate, required by paragraph A. of this AD. 1. If corrosion is found in the inboard fuel tank, prior to further flight, permanently remove the inboard fuel tank foam blocks, restore any corroded areas, and modify the stringers in accordance with the Accomplishment Instructions, Steps 3, 4, and 5, of de Havilland Service Bulletin 7-57-33, dated July 21, 1989. 2. If corrosion is found in the outboard fuel tank, prior to further flight, permanently remove the outboard fuel tank foam blocks, restore any corroded areas, and modify the stringers in accordance with the Accomplishment Instructions, Steps 3, 4, and 5, of de Havilland Service Bulletin 7-57-33, dated July 21, 1989. C. If no corrosion is found, within three years after the effective date of this AD, permanently remove the inboard fuel tank foam blocks and modify the stringers in accordance with the Accomplishment Instructions, Steps 3 and 5, of de Havilland Service Bulletin 7-57-33 (), dated July 21, 1989. D. Accomplishment of the removal and modification actions specified in paragraph C. of this AD, constitutes terminating action for the repetitive inspections of the inboard fuel tank lower wing skins required by paragraph A. of this AD. E. Accomplishment of the removal and modification actions specified in the Accomplishment Instructions, Steps 3 and 5, of de Havilland Service Bulletin 7-57-33 (), dated July 21, 1989, for the outboard fuel tanks, constitutes terminating action for the repetitive inspections of the outboard fuel tank lower wing skin required by paragraph A. of this AD. F. 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, New York Aircraft Certification Office (ACO), FAA, New England Region. NOTE: The request should be submitted directly to the Manager, New York ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, New York ACO. G. 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 Boeing of Canada, Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or at the FAA New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment (39-6813, AD 90-24-10) becomes effective on December 24, 1990.
95-26-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This AD requires either that the control circuit breaker of the left fuel pump valve be opened and collared, or that the Airplane Flight Manual (AFM) be revised to prohibit autoland operation below 100 feet above ground level (AGL). Additionally, this action requires an inspection of the fuel system control panel (FSCP) to detect any mis-wiring, and modification or replacement of the FSCP. This AD also provides for an optional terminating modification for the requirements of the AD. This amendment is prompted by a report of improper wiring of the FSCP during production of these airplanes. The actions specified in this AD are intended to prevent degradation of the automatic landing system during flight due to improper wiring of the FSCP.
2010-11-14: 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: During ERJ 190 airplane full scale fatigue test, cracks were found in some structural components of the airplane. Analysis of these cracks resulted in modifications on the airplane Airworthiness Limitation Items (ALI), to include new inspections tasks or modification of existing ones and its respective thresholds and intervals. Failure to inspect these components according to the new tasks, thresholds and intervals could prevent a timely detection of fatigue cracks. Undetected fatigue cracks in these areas could adversely affect the structural integrity of these airplanes. * * * * * We are issuing this AD to require actions to correct the unsafecondition on these products.
2010-10-26: We are superseding an existing 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: A specific batch of nose landing gear (NLG) and NLG door selector valves, part number (P/N) 601R75146-1 (Kaiser Fluid Technologies P/N 750006000), may have had their end caps incorrectly lock-wired and/or incorrectly torqued during assembly. This condition can lead to the end cap backing off, with consequent damage to a seal and internal leakage within the valve. Subsequently, if electrical power is transferred or removed from the aircraft before the NLG safety pin is installed, any pressure, including residual pressure, in the No. 3 hydraulic system can result in an uncommanded NLG retraction. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
76-09-10: 76-09-10 SCHEMPP HIRTH and BURKHART GROB: Amendment 39-2602. Applies to Standard Cirrus gliders, certificated in all categories, serial numbers 1 through 510, 528, and 529 for Schempp Hirth gliders and serial numbers 1G through 544G for Burkhart Grob gliders. Compliance is required within the next 100 flights after the effective date of this AD, unless already accomplished. To prevent possible jamming of the aileron control system and consequent loss of roll control, accomplish the following: (a) Install an SAE 1024 steel safety brace in the fuselage frame between the airbrake lever bearing and the left diagonal strut in accordance with Step 2 of the paragraph entitled "Instructions" of Schempp Hirth Technical Note 278-17, dated December 8, 1975, or an FAA- approved equivalent. (b) For the purpose of this AD, a flight is a sequence consisting of a takeoff operation and landing. This amendment becomes effective May 20, 1976.
2010-11-12: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Model MD-11 and MD-11F airplanes. That AD currently requires a one-time inspection to determine if metallic transitions are installed on wire harnesses of the tail tank fuel transfer pumps, and to determine if damaged wires are present; and repair, if necessary. That AD also requires repetitive inspections of the repaired area; and a permanent modification of the wire harnesses if metallic transitions are not installed, which would terminate the repetitive inspections. This new AD requires modifying the case grounding for the alternate fuel pump of the tail tank, the leak detection thermal switch grounding for the number 2 engine, and wire braid grounding in the empennage and number 2 engine inlet. This AD also removes one airplane from the applicability of the existing AD. This AD results from reports that the wire assembly for the alternate fuel pump is missing a case ground wire, and the lightning protection wire braid for wire assemblies located in the empennage and number 2 engine inlet are grounded improperly. We are issuing this AD to prevent insufficient grounding of the fuel pump, which in combination with an electrical failure within the fuel pump and a compromised electrical bond could cause a fuel tank ignition, resulting in consequent fire or explosion. \n\nDATES: This AD becomes effective July 6, 2010. \n\tThe Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of July 6, 2010. \n\tOn January 18, 2000 (64 FR 69389, December 13, 1999), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD.
96-07-12: This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 214ST helicopters with certain tailboom assemblies and a certain emergency float kit installed, that requires initial and repetitive inspections of the tailboom for cracks until modifications of the tailboom are accomplished. This amendment is prompted by several reports of cracks in the lower aft skin of the tailboom assembly. The actions specified by this AD are intended to prevent cracks in the tailboom assembly, which could result in structural failure of the tailboom and subsequent loss of control of the helicopter.
94-01-15: 94-01-15 BOEING: Amendment 39-8797. Docket 93-NM-138-AD. \n\n\tApplicability: Model 747 series airplanes with a stretched upper deck, all line numbers up to and including line number 980; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent the bulb seal from coming off the fascia panels and being ingested into the turbofans of the escape systems on the stretched upper deck (SUD), which could impede the inflation of the escape slide during an emergency situation, accomplish the following: \n\n\t(a)\tWithin 6 months after the effective date of this AD, install an aluminum seal retainer on the bulb seal attached to the fascia panel of the escape systems on the SUD, in accordance with Boeing Alert Service Bulletin 747-25A3056, dated July 12, 1993. \n\n\t(b)\tAn 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, Seattle Aircraft Certification Office (ACO). Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\n\t(c)\tSpecial 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. \n\n\t(d)\tThe installation shall be done in accordance with Boeing Alert Service Bulletin 747-25A3056, dated July 12, 1993. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. \n\n\t(e)\tThis amendment becomes effective on March 3, 1994.
2010-10-09: The FAA is superseding an existing airworthiness directive (AD) for certain Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. That AD requires initial and repetitive relative position checks of the gas generator 2nd stage turbine blades on Turbomeca Arriel 1B (that incorporate Turbomeca Modification (mod) TU 148), Arriel 1D, 1D1, and 1S1 turboshaft engines that do not incorporate mod TU 347. That AD also requires initial and repetitive replacements of 2nd stage turbines on Arriel 1B, 1D, and 1D1 engines. This AD requires lowering the initial and repetitive thresholds for replacement of 2nd stage turbines on Arriel 1B, 1D, and 1D1 engines. This AD results from reports of new cases of failures of 2nd stage turbine blades since we issued AD 2008-07-01. We are issuing this AD to prevent the failure of 2nd stage turbine blades, which could result in an uncommanded in- flight engine shutdown, and a subsequent forced autorotation landing or accident.
97-02-20: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300, A310, and A300-600 series airplanes, that requires a one-time inspection of the autopilot actuators on the pitch and yaw controls to ensure correct rigging, and re-rigging, if necessary. This amendment is prompted by a report of sudden pitch up of an airplane during cruise following disengagement of the autopilot; this condition was the result of incorrect rigging of the autopilot pitch actuator. The actions specified by this AD are intended to prevent incorrect rigging of the autopilot actuators on the pitch and yaw controls, which could result in reduced controllability of the airplane.
2010-10-01: We are adopting a new airworthiness directive (AD) for the products listed above that will supersede an existing AD. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Inspection of a high time aircraft has revealed cracks in the Horizontal Stabiliser rear spar splice plate and inboard main ribs around the area of the Horizontal Stabiliser rear pivot attachment. Additionally, failure of some attach bolts in service may be due to improper assembly. This amendment is issued to clarify the model applicability. The previous amendment was issued because the requirement document now contains an inspection for cracking in horizontal stabilisers which have load transferring fittings installed. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective May 10, 2010. As of March 2, 2009 (74 FR 8159; February 24, 2009), the Director of the Federal Register approved the incorporation by reference of Gippsland Aeronautics Mandatory Service Bulletin SB-GA8-2002-02, Issue 5, dated November 13, 2008, listed in this AD. We must receive comments on this AD by June 18, 2010.
90-05-01: 90-05-01 CESSNA: Amendment 39-6513. Applicability: Model 208 and 208A (Serial Numbers 20800001 thru 20800173), and 208B (Serial Numbers 208B0001 through 208B0202) airplanes certificated in any category. Compliance: Required within the next 50 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished. To prevent failure of the Part Number (P/N) 2622083-18 bellcrank assembly and the resulting unexpected retraction of the flaps, accomplish the following: (a) Visually inspect the P/N 2622083-18 bellcrank assembly for cracks, deformation, and incomplete welds in accordance with Cessna Service Bulletin CAB89-34, dated December 22, 1989. (1) If any cracks or deformation are found, prior to further flight replace the P/N 2622083-18 bellcrank with an airworthy bellcrank. (2) If any incomplete welds are found, within the next 50 hours TIS replace the P/N 2622083-18 bellcrank with an airworthy bellcrank. (3) If any bellcranks are to be replaced, inspect the replacement part in accordance with Cessna SB CAB89-34 dated December 22, 1989 before installation. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An alternate method of compliance or adjustment of the initial or repetitive compliance times which provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. All persons affected by this directive may obtain copies of the document referred to herein upon request to the Cessna Aircraft Company, Customer Service, P.O. Box 7704, Wichita, Kansas 67217, or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6513, AD 90-05-01) becomes effective on March 5, 1990.
2010-09-06: 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: During an elevator Power Control Unit (PCU) Centering Functional Check on two CL-600-2C10 aircraft, sustained oscillations were discovered when a control rod was disconnected. These sustained oscillations could render the elevator surface inoperable and cause subsequent loss of pitch control of the aircraft. * * * * * Loss of pitch control could result in reduced controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
95-15-02: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model Viscount 744, 745D, and 810 airplanes, that requires an inspection of fittings of the engine mount structure to determine whether fasteners have been installed in inspection holes and to determine whether those holes are oversized. It also requires various follow-on actions, depending upon the results of the inspection. This amendment is prompted by reports indicating that fasteners were installed in the inspection hole of the engine "W" frame socket fittings and the inspection hole was oversized due to fatigue cracking. The actions specified by this AD are intended to prevent such fatigue cracking, which could lead to failure of the fasteners and consequent separation of the engine from the airframe.
95-26-09: This amendment adopts a new airworthiness directive (AD) that is applicable to Sikorsky Aircraft-manufactured Model CH-34A, CH-34C, H-34A, HH-34J, HSS-1, HSS-1N, HUS-1, SH-34J, UH-34D, UH-34E, and UH-34J helicopters. This action requires initial and repetitive magnetic particle inspections of the main rotor shaft (shaft) for cracks, and defines power limitations for certain helicopter operations. This amendment is prompted by a recent accident in which a shaft failed, resulting in loss of power. Subsequent inspections on other aircraft of the same type revealed cracks in four additional shafts. The actions specified in this AD are intended to prevent failure of the shaft, loss of power to the rotor system, and subsequent loss of control of the helicopter.
2010-09-08: The FAA is adopting a new airworthiness directive (AD) for GE CJ610 series turbojet engines and CF700 turbofan engines with AFT Technologies combustion liners, part number (P/N) AFT-5016T30G02. This AD requires removing from service, AFT Technologies combustion liners, P/N AFT-5016T30G02. This AD results from a report of an AFT Technologies combustion liner that released a large section of the inner combustion liner and reports of six combustion liners with premature cracks. We are issuing this AD to prevent premature cracks in the combustion liner, which could release pieces of the inner combustion liner. A release of pieces of the inner combustion liner could cause an uncontained failure of the engine turbine and damage to the airplane.
2008-08-09: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 400) airplanes. That AD currently requires revising the airworthiness limitations section of the Instructions for Continued Airworthiness of the maintenance requirements manual (MRM) by incorporating procedures for repetitive functional tests of the pilot input lever of the pitch feel simulator (PFS) units. That AD also requires new repetitive functional tests of the pilot input lever of the PFS unit, and corrective actions if necessary; and after initiating the new tests, requires removal of the existing procedures for the repetitive functional tests from the MRM. This new AD requires revised procedures for the functional tests. This AD results from a report that the shear pin located in the input lever of two PFS units failed due to fatigue. We are issuing this AD to prevent undetected failure of the shear pins of both PFS units simultaneously, which could result in loss of pitch feel forces and consequent reduced control of the airplane. DATES: This AD becomes effective May 19, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of May 19, 2008. On March 27, 2006 (71 FR 12277, March 10, 2006), the Director of the Federal Register approved the incorporation by reference of Bombardier Alert Service Bulletin A601R-27-144, Revision A, dated February 14, 2006, including Appendix A, dated September 15, 2005. On February 13, 2004 (69 FR 4234, January 29, 2004), the Director of the Federal Register approved the incorporation by reference of Bombardier Temporary Revision 2B-1784, dated October 24, 2003, to the CL-600-2B19 Canadair Regional Jet Maintenance Requirements Manual, Part 2, Appendix B, "Airworthiness Limitations.''
93-25-11: 93-25-11 SHORT BROTHERS, PLC: Amendment 39-8776. Docket 93-NM-75-AD. Supersedes AD 93-01-06, Amendment 39-8460 which superseded AD 89-07-14, Amendment 39-6176. Applicability: Model SD3-60 series airplanes; serial numbers SH3601 through SH3691 inclusive, and SH3694; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent loss of the structural integrity of the horizontal stabilizer attachment to the fuselage, accomplish the following: (a) Perform a visual inspection at the aft face of the rear spar web-to-boom riveting, top and bottom, between the fuselage attach fittings at 12.5 inches left and right of the airplane center line to detect loose, missing, or failed rivets in accordance with Shorts Service Bulletin SD360-55-16, dated April 1988, prior to the times specified in paragraphs (a)(1) and (a)(2) of this AD, as applicable. Repeat the inspection thereafter at intervals not to exceed 1,000 landings.(1) For airplanes on which the inspections (at the forward face of the rear spar web- to-boom riveting) required by AD 93-01-06, amendment 39-8460, have been accomplished previously and on which Modification 7948 has not been accomplished: Within 1,000 landings after the last inspection accomplished in accordance with AD 93-01-06, or within 100 landings after the effective date of this AD, whichever occurs later. (2) For airplanes on which the inspections required by AD 93-01-06 have not been accomplished previously and on which Modification 7948 has not been accomplished: Inspect prior to the times specified in paragraphs (a)(2)(i) and (a)(2)(ii) of this AD, as applicable. (i) For airplane serial numbers SH3680 through SH3691 inclusive, and SH3694; and for airplanes affected by this AD that have only used a 15-degree takeoff flap setting since before or upon reaching 5,000 landings: Prior to the accumulation of 12,000 total landings, or within 100 landings after theeffective date of this AD, whichever occurs later. (ii) For airplanes other than those affected by paragraph (a)(2)(i) of this AD: Prior to the accumulation of 8,000 total landings, or within 100 landings after the effective date of this AD, whichever occurs later. (b) If any defective rivet is found as a result of any inspection required by this AD, prior to further flight, repair in accordance with Part II of Shorts Service Bulletin SD360-55-16, dated April 1988. Following that repair, continue to perform the repetitive inspections required by paragraph (a) of this AD. (c) Modification of the horizontal stabilizer spar webs (Modification 7948) in accordance with Shorts Service Bulletin SD360-55-12, Revision 2, dated November 1986, constitutes terminating action for the repetitive inspections required by paragraph (a) of this AD. (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: 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 modification shall be done in accordance with the following Shorts service bulletins, which contain the specified effective pages: Service Bulletin and Date Page Number Revision Level Shown on Page Date Shown on Page SD360-55-16 April 1988 1-7 Original April 1988 SD360-55-12 Revision 2 November 1986 1,4-5, 7-44 2-3, 6 2 Original November 1986 April 1986 The incorporation by reference of these documents was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of March 2, 1993 (58 FR 6085). Copies may be obtained from Short Brothers PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3719. 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 January 26, 1994.
96-20-04: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires modification of the passenger door lock warning system. This amendment is prompted by reports that the passenger door opened during flight due to an improperly locked door; additionally, the door warning signal was not sufficiently visible to alert the flight crew of this condition. The actions specified by this AD are intended to ensure that the flight crew is aware of an unlocked passenger door prior to takeoff of the airplane. This condition, if not corrected, could result in inadvertent opening of the passenger door while the airplane is in flight.
2010-07-08: The FAA is adopting a new airworthiness directive (AD) for certain Kelly Aerospace Energy Systems, LLC (KAES) rebuilt turbochargers. This AD requires removal from service of certain part number (P/N) and serial number (S/N) rebuilt turbochargers. This AD results from three reports of infant mortality turbine wheel failure in rebuilt turbochargers, since June of 2007. We are issuing this AD to prevent separation or seizure of the turbocharger turbine, which could result in full or partial engine power loss, loss of engine oil, and smoke in the airplane cabin.