29 Airworthiness Directives: 26 airplane, 1 rotorcraft, 1 engine, 1 glider.
AD 95-11-11 R1 · published Jul 3, 1995, effective Jul 3, 1995
The Boeing Company Airplanes
This amendment clarifies information in an existing airworthiness directive (AD), applicable to certain McDonnell Douglas DC-10 and KC-10 series airplanes, that currently requires repetitive eddy current inspections to detect fatigue cracking of the pylon aft bulkhead flange, upper pylon box web, fitting radius, and adjacent tangent areas; and repair, if necessary. The actions specified in that AD are intended to prevent failure of the wing pylon aft bulkhead due to fatigue cracking, which could lead to separation of the engine and pylon from the airplane. This amendment clarifies the requirements of the current AD by specifying the type of initial and repetitive inspections that must be conducted. This amendment is prompted by communications received from affected operators that the current requirements of the AD are unclear.
AD 95-12-03 · published Jul 7, 1995, effective Jul 7, 1995
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires installation of reinforcement plates at certain fuselage stations. This amendment is prompted by a report indicating that cracks were found in the frame strips at certain fuselage stations on a Model F28 Mark 0100 series airplane test article due to fatigue-related stress. The actions specified by this AD are intended to prevent such fatigue-related cracking, which could result in reduced structural integrity of the fuselage pressure vessel.
AD 95-14-04 · published Jul 7, 1995, effective Aug 7, 1995
British Aerospace Model BAC 1-11 200 and 400 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace Model BAC 1-11 200 and 400 airplanes, that currently requires incorporation of certain structural modifications. That AD was prompted by reports of fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their economic design goal. The actions specified by that AD are intended to prevent reduced structural integrity of the airplane. This amendment requires incorporation of additional structural modifications.
AD 95-12-04 · published Jul 17, 1995, effective Jul 17, 1995
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Model A320-231 series airplanes, that requires repetitive functional checks to detect leakage of the distribution piping of the engine fire extinguishing system, and repair, if necessary; and modification of the piping, which would terminate the inspection requirements. This amendment is prompted by reports of cracking of the engine fire extinguisher pipe, which resulted in leakage of the fire extinguisher agent. The actions specified by this AD are intended to prevent leakage of the fire extinguishing agent, which could prevent the proper distribution of the agent within the nacelle in the event of a fire.
AD 95-12-14 · published Jul 17, 1995, effective Jul 17, 1995
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires an inspection to determine the adequacy of clearance between the normal maximum (second) detent for the reverse thrust control and the surrounding moving parts, and to detect chafing or damage of the detent. This amendment also requires eventual replacement of the normal maximum detent with an improved detent. This amendment is prompted by a report indicating that an inadequate level of clearance between the normal maximum detent and the surrounding parts may exist on earlier production Model F28 Mark 0100 series airplanes. The actions specified by this AD are intended to ensure proper operation of the normal maximum detent for reverse thrust control.
AD 95-12-15 · published Jul 17, 1995, effective Jul 17, 1995
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires replacement of a certain pressure switch with a certain new pressure switch in the fuel system for the engines. This amendment is prompted by a report indicating that the current design of a certain pressure switch in the fuel system for the engines does not meet current fire resistant properties, which could result in the failure of the pressure switch during a fire in the engine compartment. The actions specified by this AD are intended to prevent failure of the existing pressure switch in the fuel system for the engines, which, during an engine fire, could result in fuel leakage that could add fuel to the fire.
AD 95-12-18 · published Jul 17, 1995, effective Jul 17, 1995
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires a visual inspection to verify proper clearance between the engine fuel supply-line and the hydraulic line in certain areas, and replacement of damaged fuel lines. This amendment would also require installation of additional clamps on the out line of the lift-dumper in certain cases. This amendment is prompted by a report indicating that fuel was found leaking from the right-hand wheel bay on one airplane due to chafing of the fuel supply line. The actions specified by this AD are intended to prevent such chafing, which could result in fuel leakage, and, subsequently, lead to a possible fire hazard and engine fuel depravation.
AD 95-11-17 · published Jul 19, 1995, effective Jul 19, 1995
British Aerospace Regional Aircraft Airplanes
This amendment supersedes Airworthiness Directive (AD) 90-13-12, which currently requires modifying the airplane electrical system and revising the emergency procedures section of the Airplane Flight Manual (AFM) on certain Jetstream Aircraft Limited (JAL) Jetstream Models 3101 and 3201 airplanes. This action retains the requirements of AD 90-13-12 for those airplanes that do not have modified inverters installed and the inverted transfer function restored. The Federal Aviation Administration (FAA) has determined that installing modified inverters along with restoring the inverter transfer function corrects the problems in the power supply addressed by AD 90-13-12. The actions specified by this AD are intended to prevent alternating current system failures, which, if not detected and corrected, could result in damage to the airplane navigational systems.
AD 95-12-17 · published Jul 19, 1995, effective Aug 18, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that requires various inspections for cracks in the outboard chord of the frame at body station (BS) 727 and in the outboard chord of stringer 18A; and repair or replacement of cracked parts. This amendment is prompted by reports of fatigue cracks in those outboard chords. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the outboard chords, and subsequent rapid decompression of the airplane.
AD 95-14-02 · published Jul 19, 1995, effective Aug 31, 1995
Textron Aviation Inc. Airplanes
This amendment supersedes Airworthiness Directive (AD) 91-24-15, which currently requires modifying the instrument air plumbing system on Beech Aircraft Corporation (Beech) Models 1900 and 1900C airplanes. This action requires an additional modification to the plumbing of the instrument air system on the Models 1900 and 1900C airplanes, and adds the Model 1900D airplanes to the applicability. Eight reports of moisture freezing in this system on airplanes with the modification required by AD 91-24-15 incorporated prompted this action. In addition, recent testing on the Model 1900D indicates that the design of the instrument air system on these airplanes is also conducive to moisture freeze-ups. The actions specified by this AD are intended to prevent ice formation in the plumbing of the instrument air system, which, if not detected and corrected, could result in aerodynamic problems and subsequent loss of control of the airplane.
AD 95-14-06 · published Jul 19, 1995, effective Aug 18, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes and Model KC-10A (military) airplanes, that requires various modifications of the flight controls, hydraulic power systems, and landing gear. This amendment is prompted by a recommendation by the Systems Review Task Force (SRTF) for accomplishment of certain modifications that will enhance the controllability of these airplanes in the unlikely event of catastrophic damage to all hydraulics systems. The actions specified by this AD are intended to ensure airplane survivability in the event of damage to fully powered flight control systems.
AD 95-14-07 · published Jul 19, 1995, effective Aug 18, 1995
ATR - GIE Avions de Transport Régional Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Model ATR72-100 and -200 series airplanes, that requires a one-time dye penetrant inspection to detect cracking in certain hinge pins of the nose landing gear (NLG), and replacement of cracked pins with crack-free pins. This amendment is prompted by reports of cracking of certain hinge pins in the NLG. The actions specified by this AD are intended to prevent collapse of the NLG due to cracking of the hinge pins.
AD 95-14-09 · published Jul 19, 1995, effective Aug 3, 1995
Learjet Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 60 airplanes. This action requires inspection to detect bends in or damage to the fuel crossflow tube; inspection to determine clearance between the fuel crossflow tube and the flight control cables; and replacement or repair of the tube, if necessary. This amendment is prompted by reports of damage to the fuel crossflow tube and inadequate clearance between the fuel crossflow tube and the flight control cables due to bends in the fuel crossflow tube. The actions specified in this AD are intended to prevent chafing and eventual failure of the fuel crossflow tube due to inadequate clearance between the tube and the flight control cables; this condition could result in loss of fuel from one fuel tank during normal operating conditions or loss of fuel from both main fuel tanks during fuel cross feeding operations.
AD 95-13-02 · published Jul 22, 1995, effective Jul 22, 1995
Twin Commander Aircraft LLC Airplanes
AD 95-12-06 · published Jul 24, 1995, effective Jul 24, 1995
British Aerospace Regional Aircraft Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Jetstream Aircraft Limited (JAL) Jetstream Models 3101 and 3201 airplanes. The action requires modifying the shear fitting at the top of each escape hatch. A report of interference between the shear fitting on an escape hatch and a ceiling panel found while removing the escape hatch on one of the affected airplanes prompted this AD. The actions specified by this AD are intended to prevent the inability to utilize an escape hatch during an emergency situation because of interference.
AD 95-12-25 · published Jul 24, 1995, effective Jul 24, 1995
McDonnell Douglas Corporation Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (military) series airplanes, and Model MD-88 airplanes. This amendment requires an inspection to detect chafing on the FIREX pipe assembly of the number one engine; and either repair of chafed pipe assemblies or replacement of the chafed pipe assemblies with new pipe assemblies; and modification of the FIREX and the pneumatic sense pipe assembly clamp marriage. This amendment is prompted by reports of incidents in which the pneumatic sense pipe chafed against the FIREX supply pipe of the number one engine. The actions specified by this AD are intended to prevent the chafing of the FIREX supply pipe, which could result in a hole in the pipe and subsequently prevent the proper distribution of the fire extinguishing agent within the nacelle in the event of a fire.
AD 95-15-03 · published Jul 24, 1995, effective Aug 8, 1995
Aerospatiale Model ATR42 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Aerospatiale Model ATR42 series airplanes. This action requires replacement of the currently installed side brace pins of the main landing gear (MLG) with new pins. This amendment is prompted by a report of a ruptured pin on an in-service airplane. The actions specified in this AD are intended to prevent failure of the side brace pins and the subsequent collapse of the MLG.
AD 95-15-04 · published Jul 24, 1995, effective Aug 23, 1995
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Corporate Jets Model BAe 125-800A and -1000A airplanes, that requires inspections to detect corrosion of the wing leading edge skins, including the wing anti-ice fluid distribution panel (TKS panel) rebate and radius; repair, if necessary; and subsequent corrosion protection treatment. This amendment also requires inspections and treatments of the landing/taxiing lamp window assembly recess and stall vane spoiler rebate/radius. This amendment is prompted by reports of corrosion of the wing leading edge skin at the interface with the TKS panels. The actions specified by this AD are intended to prevent reduced structural integrity of the wing leading edge section at the interface with the TKS panels and stall vane spoilers, which could adversely affect the flight characteristics of the airplane.
AD 95-15-06 · published Jul 24, 1995, effective Aug 23, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 and Model 737 series airplanes, that requires replacement of the actuator of the engine fuel shutoff valve and the fuel system crossfeed valve with an improved actuator. This amendment is prompted by reports indicating that, during laboratory tests on Model 737 series airplanes, the actuator clutch on the engine shutoff and crossfeed valves slipped at cold temperatures due to improper functioning. The actions specified by this AD are intended to prevent improper functioning of these actuators, which could result in a fuel imbalance due to the inability of the flight crew to crossfeed fuel; improperly functioning actuators could also prevent the pilot from shutting off the fuel to the engine following an engine failure and/or fire.
AD 95-15-01 · published Jul 25, 1995, effective Aug 24, 1995
Boeing Model 767 Series Airplanes Equipped with Over-Wing Escape Slides
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes equipped with over-wing escape slides, that currently requires modification of the trailing edge panels and the aft flaps. That amendment was prompted by the results of functional tests of over-wing escape slides, which revealed that some slides were damaged when they were deployed across sharp corners on the trailing edge of the wing and the large gaps between the trailing edge panels of the wing. This amendment expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to prevent damage to the over-wing escape slide, which could hinder inflation of the slide to a usable configuration during an emergency evacuation.
AD 94-14-07 R1 · published Jul 26, 1995, effective Jul 26, 1995
BAE Systems (Operations) Limited Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to all Jetstream Model 4101 airplanes, that currently requires modification of the mounting structure of the elevator controls on the rear pressure bulkhead. That AD was prompted by results of a structural analysis which indicate that certain structure in the elevator control system may be subject to deformation when maximum load is exerted by the pilot(s) in the event of a jam in the elevator control cables. The actions specified in that AD are intended to prevent reduced controllability of the airplane due to structural deformation in the elevator control system. This amendment limits the applicability of the rule.
AD 95-04-07 R1 · published Jul 27, 1995, effective Mar 17, 1995
McDonnell Douglas Model DC-10-10, -15, and -30 Airplanes, and KC-10A (Military) Airplanes
This amendment clarifies information in an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes, that currently requires inspections to determine the condition of the lockwires on the forward engine mount bolts and correction of any discrepancies found. That amendment also provides for termination of the inspections for some airplanes by installing retainers on the bolts. The actions specified in that AD are intended to prevent broken lockwires, which could result in loosening of the engine mount bolts, and subsequent separation of the engine from the airplane. This amendment clarifies the procedures for accomplishing the optional terminating action on engines 1, 2, and 3. This amendment is prompted by communications received from affected operators indicating that those procedures were unclear.
AD 95-12-23 · published Jul 30, 1995, effective Jul 30, 1995
Twin Commander Aircraft LLC Airplanes
AD 95-15-07 · published Jul 31, 1995, effective Aug 30, 1995
Airbus SAS Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to British Aerospace Model BAC 1-11 200 and 400 series airplanes, that currently requires structural inspections and repairs or replacements, as necessary. This amendment requires additional inspections of certain Structural Significant Items (SSI) and expansion of the inspection area for certain other SSI's. This amendment is prompted by the results of a structural integrity audit, which indicated that in order to maintain the structural integrity of these airplanes as they approach or exceed the manufacturer's original fatigue design life goal, certain SSI's need to be inspected. The actions specified by this AD are intended to ensure continuing structural integrity of these airplanes.
AD 95-15-13 · published Jul 31, 1995, effective Sep 7, 1995
Jetstream Aircraft Limited (Formerly British Aerospace, Regional Aircraft Limited) Jetstream Models 3101 and 3201 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Jetstream Aircraft Limited (JAL) Jetstream Models 3101 and 3201 airplanes.This action requires inspecting the main passenger/crew door locking mechanism to ensure that a taper pin is installed, installing a taper pin if not already installed, and modifying the passenger door warning system. The actions specified by this AD are intended to prevent the inability to open the passenger/crew door or failure of the passenger door warning system, which could result in passenger injury if emergency evacuation is needed.
AD 95-13-10 · published Jul 5, 1995, effective Aug 9, 1995
Costruzioni Aeronautiche Giovanni Agusta S.p.A. Model A109A, A109AII, and A109C Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to certain Costruzioni Aeronautiche Giovanni Agusta S.p.A. (Agusta) Model A109A, A109AII, and A109C helicopters, that requires a modification of the tail boom vertical fin to create inspection openings that permit initial and repetitive visual inspections for cracks in the vertical fin rear spar attachment area. This amendment is prompted by four reports of cracks in the tail boom vertical fin rear spar attachment area. The actions specified by this AD are intended to prevent failure of the vertical fin attachment caused by cracks in the tail boom vertical fin rear spar attachment area, and subsequent loss of control of the helicopter.
AD 95-10-10 · published Jul 21, 1995, effective Jul 21, 1995
Pratt & Whitney Division Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney (PW) JT8D series turbofan engines, that currently requires initial and repetitive inspections of certain front compressor fan hubs and shotpeening of the forward and aft rim to web radius. This amendment requires a reduction in the initial inspection interval for front compressor fan hubs installed in all positions of all applicable aircraft, establish a compliance end- date, and clarify the wording of the compliance requirements. This amendment is prompted by a report of a front compressor fan hub fracture installed in a Boeing 737 aircraft that resulted in the release of fan blades and portions of the hub outer rim. The actions specified by this AD are intended to prevent fracture of the front compressor fan hub, which can result in an uncontained engine failure and damage to the aircraft. DATES: Effective July 21, 1995. The incorporation by reference of certainpublications listed in the regulations is approved by the Director of the Federal Register as of July 21, 1995. ADDRESSES: The service information referenced in this AD may be obtained from Pratt & Whitney, Technical Publications Department, M/S 132-30, 400 Main Street, East Hartford, CT, 06108. This information may be examined at the Federal Aviation Administration (FAA), New England Region, Office of the Assistant Chief 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. FOR FURTHER INFORMATION CONTACT: Mark A. Rumizen, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA, 01803-5299; telephone (617) 238-7137, fax (617) 238-7199. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 93-14-14, Amendment 39-8638 (58 FR 39644, July26, 1993) which is applicable to PW JT8D series turbofan engines, was published in the Federal Register on November 21, 1994 (59 FR 59973). That action proposed to reduce the initial inspection interval to require front compressor fan hubs installed in all positions of all applicable aircraft be inspected at the next shop visit, and to establish a compliance end date of December 31, 1999, or 6000 total part cycles (TPC) after the effective date of this AD for the initial inspection. That action also proposed to clarify the wording of paragraph (b)(4) to emphasize that the repetitive inspection is required at the next opportunity when the front compressor fan hub is accessible at the detail level in the shop only after accumulating 2500 additional cycles in service (CIS) since the last inspection. The actions would be required to be accomplished in accordance with Pratt & Whitney (PW) Alert Service Bulletin (ASB) No. A6104, Revision 3, dated June 16, 1994. Interested persons havebeen afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received. One commenter states that the reporting requirements of the AD be removed. The FAA does not concur. This corrective action program was based on a risk analysis that assumed a frequency of inspection relative to fleet usage. The reporting requirements of the AD allow this frequency of inspections to be monitored to ensure it is consistent with the assumptions, thereby confirming that the corrective action program is appropriate for maintaining the forecasted risk level. One commenter supports the amendment as proposed. After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed. There are approximately 2165 engines of the affected design in the worldwide fleet. The FAA estimates that 1475 engines installed on aircraft of U.S. registry and 690 domestic uninstalled engines will be affected by this AD, that it will take approximately 12 work hours per engine to accomplish the required actions, and that the average labor rate is $55 per work hour. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $1,428,900. The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES." List of Subjects in 14 CFR Part 39 Air Transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89. 39.13 - [AMENDED] 2. Section 39.13 is amended byremoving Amendment 39-8638 (58 FR 39644, July 26, 1993) and by adding a new airworthiness directive, Amendment 39-9227, to read as follows:
AD 95-14-01 · published Jul 7, 1995, effective Aug 24, 1995
Glaser-Dirks Flugzeugbau GmbH Gliders
This amendment adopts a new airworthiness directive (AD) that applies to Glaser-Dirks Flugzeugbau GmbH (Glaser-Dirks) Model DG-100 sailplanes equipped with the main L4 fitting of the all flying tailplane. This action requires inspecting (one-time) the tailplane main fitting to ensure the part is accurately welded, and modifying the tailplane main fitting if not accurately welded. A report of tailplane main fitting failure on one of the affected sailplanes, where the welding did not completely cover the entire wall thickness of the fitting, prompted this action. The actions specified by this AD are intended to prevent loss of control of the sailplane because of tailplane main fitting failure.
