Results
2001-09-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727-100, -100C, and -200 series airplanes, that, for certain airplanes, requires a one-time inspection of certain fuselage circumferential skin joints to determine the type of fasteners installed, and replacement of any aluminum fasteners with steel fasteners, if necessary; or modification of certain fuselage circumferential skin joints; as applicable. For certain other airplanes, this amendment also requires repetitive inspections to detect corrosion, sealant deterioration, cracking, or disbonding; repair, if necessary; and modification of certain fuselage circumferential skin joints. This amendment is prompted by reports of corrosion between the body skins and cold-bonded doublers at the fuselage circumferential skin joints. The actions specified by this AD are intended to prevent delamination of the cold-bonded doublers, which could result in corrosion of the body skins and doublers, and consequent reduced structural capability of the fuselage circumferential skin joints.
2016-13-13: We are adopting a new airworthiness directive (AD) for certain Beechcraft Corporation Model BAe.125 Series 1000A and 1000B airplanes and Model Hawker 1000 airplanes. This AD was prompted by reports of inadvertent stowage of the thrust reversers, which can result in high forward engine thrust even though the throttle is commanding reverse thrust. This AD requires installing kits that include relays, associated wiring, and a thrust reverser fail annunciator. We are issuing this AD to prevent inadvertent stowage of the thrust reversers, which could cause a runway overrun during a rejected takeoff or landing, and consequent structural failure and possible injury to occupants.
2010-22-04: We are superseding an existing airworthiness directive (AD) for the products listed above. That AD currently requires a detailed inspection for certain defects of the upper fasteners of the aft mount support fittings of the left and right engines, and corrective actions if necessary. This new AD requires repetitive replacement of the upper row of fasteners of the support fittings of the engine aft mount with new fasteners; and repetitive general visual inspections for defects of the lower row fasteners (Row B) of the support fittings of the left and right engine aft mounts, and replacement of all clearance fit fasteners in the lower row if necessary. This AD was prompted by reports of loose, cracked, or missing fasteners in the aft mount support fitting of the left and right engines. We are issuing this AD to prevent loose, cracked, or missing fasteners in the engine aft mount support fittings, which could lead to separation of the support fittings from the pylon, and could result in separation of the engine from the airplane.
73-21-03: 73-21-03 BELL: Amdt. 39-1732. Applies to Model 206A and 206B helicopters, serial numbers 4 through 1097, certificated in all categories, equipped with vertical fin support forgings, P/N's 206-031-417 and -418. Compliance required within the next 50 hours' time in service after the effective date of this A.D., unless already accomplished. To detect possible fatigue cracks in the vertical fin support forgings in the area of the fin attachment nut plates, accomplish the following: (a) Remove the vertical fin in accordance with paragraph 8-47, Section VIII of the 206A/B Maintenance and Overhaul Instructions. (b) Remove the paint in the area of the fin attachment nut plates (4 places). (c) Inspect for cracks, using a dye penetrant or equivalent inspection method. (d) If cracks are found in either support forging, the cracked forging must be removed and replaced prior to further flight. (e) If no cracks are found, inspect the four holes for thread marks. Any marks must be removed in accordance with Bell Helicopter Company Service Bulletin No. 206-01-73-5, Part I, paragraph 5, dated June 27, 1973, or later FAA approved revision. Apply a coating of zinc chromate primer or other suitable corrosion protection. (f) Reinstall the fin in accordance with paragraph 8-49, Section VIII of the 206A/B Maintenance and Overhaul Instructions. (g) This A.D. is not applicable if the vertical fin support forgings have been replaced in accordance with Bell Helicopter Company Service Bulletin No. 206-01-73-5, Part II dated June 27, 1973, or later FAA approved revision. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Company, P.O. Box 482,Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this A.D. which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective November 15, 1973.
2001-09-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A310-324, A310-325, and A300 B4-622R series airplanes equipped with Pratt & Whitney PW4000 series engines. This action requires revising the Airplane Flight Manuals (AFM) for the Model A310 and Model A300-600 series airplanes. This action is necessary to prevent acceleration and climb performance less than that specified in the AFM, which could result in runway overruns or impact with obstacles or terrain. This action is intended to address the identified unsafe condition.
2016-14-03: We are adopting a new airworthiness directive (AD) for all Airbus Model A319, A320, and A321 series airplanes. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD requires reinforcing the forward pressure bulkhead at a certain stringer on both the left-hand and right-hand sides, and doing related investigative and corrective actions if necessary. We are issuing this AD to prevent fatigue cracking of the forward pressure bulkhead, which could result in reduced structural integrity of the airplane.
78-11-01: 78-11-01 BEECH: Amendment 39-3220 as amended by Amendment 39-3277 is further amended by Amendment 39-3413. Applies to E50, F50, G50, H50, J50, 65, A65, A65-8200, 65- 80, 65-A80, 65-A80-8800, 65-B80, 65-88 and 70 model airplanes certified in all categories except those modified in accordance with STCs SA444SW or SA587SW. COMPLIANCE: Required as indicated unless already accomplished. To reduce the possibility of powerplant fire occurrence and improve powerplant fire containment and detection capabilities, accomplish the following: A) Within the next 25 hours time-in-service after June 1, 1978, install in the existing Airplane Flight Manual, the temporary airplane Flight Manual Supplement included in this AD as Figure 1, or, Beech Aircraft Company Airplane Flight Manual Supplement P/N 50-590211-31 dated May 29, 1978 or subsequent revision. B) Within the next 100 hours time-in-service after June 1, 1978, except that this compliance time may be extended to 200 hourstime-in-service if the inspection of components forward of the firewall required by AD 77-25-01 is accomplished at intervals no greater than 50 hours time-in-service during this compliance time extension. 1) Replace existing flexible fuel, oil, hydraulic, and fuel or oil vapor carrying hose assemblies except engine breather and drain lines in the engine compartment with equivalent length and diameter hoses having strength and fire resistance qualities meeting FAA Technical Standard Order C53A, Type C or D or as specified below. Hose assemblies fabricated of Stratoflex Type 111 or 130 hose covered by fire-resistant sleeve, Stratoflex Type 2650 or 2607 or Aeroquip hose Type 303 covered with fire-resistant sleeve Type AE102 or 624 or hose specified in Beechcraft Service Instructions No. 0999 or later approved revisions, or an FAA- approved equivalent are acceptable except as noted below. (Pressure test the hose assemblies in accordance with industry practice.) On airplanes having serial numbers LC-157 through LC-335, LB-1 through LB-35, and LD-135 through LD-512, replace the main oil supply hose running from the firewall to the engine with a Stratoflex Part No. 156F001-16D0200 hose assembly or Aeroquip 620100-16-0200 hose assembly or an FAA-approved equivalent. On the Model 88 series airplanes, fabricate the hose from the engine hydraulic pump "oil out" to the firewall using high pressure type hose. Stratoflex Type 112 or Aeroquip Type 309 or FAA-approved equivalent is acceptable. Subject only these hoses to a proof pressure test of 7000 PSI and install applicable hose manufacturer's fire sleeves of types noted above. Stratoflex Type 111 or 130 hose or Aeroquip Type 303 hose with appropriate manufacturer's fire sleeve as noted above or hose specified in Beechcraft Service Instructions No. 0999 or later approved revisions, or an FAA-approved equivalent are acceptable for all other pressurization system hoses. Engine induction system hoses and vacuum system hoses are not included in the requirements of this AD. Use old hoses as a pattern when fabricating new hoses. Caution should be exercised to assure end fittings on new hoses are equivalent to old hose end fittings. Install hoses observing manufacturer's torque limits. The torque chart contained in Beechcraft Service Instructions No. 0999 or later approved revisions list acceptable limits. Apply paint or torque putty to fittings after tightening. 2) On airplanes having engines with Bendix fuel injection system, after changing all engine and installation fuel system hoses but prior to connecting the hose at the fuel injector nozzle located at the top of the induction housing, cap this hose at the nozzle end, select main tanks, turn main boost pumps ON, place mixture controls in rich position, and check all fuel carrying lines and fittings for leakage. Correct any leaks detected and recheck prior to installing hose on nozzle fittings. 3) On airplanes otherthan those specified in Paragraph B(2) above, after changing all installation fuel system hoses, with mixture control in "cut off", select main tanks, turn main boost pumps ON, and check all fuel carrying lines and fittings for leakage. Correct any leaks detected and recheck. 4) After determining that no fuel is trapped in the induction system, conduct the runup specified in Figure 1 and inspect all hoses and fittings for signs of fuel or oil leakage. C) On or before January 31, 1979 install continuous type fire detector systems in the engine compartment and wheel wells in accordance with Beech Service Kit 80-9010. NOTE: The compliance date for this paragraph was established on the basis of the most accelerated schedule the vendors of the detector components can meet and the estimated number of active airplanes of the affected models. The FAA recommends that every owner place an order for the necessary modification kit as early as possible. D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Beechcraft Service Instructions No. 0999 or later approved revisions referenced herein covers the subject matter of this AD. Figure 1 TEMPORARY AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECH MODEL 50 SERIES, 65 SERIES A65 SERIES AND 70 AIRPLANES WITH RECIPROCATING ENGINES (AD 78-11-01 requires this supplement to remain in the below designated airplane flight manual until replaced by Beech Aircraft Company Flight Manual Supplement P/N 50-590211-31 dated May 29, 1978, or later approved revisions.) Model_____________ N____________ S/N ______________ In addition to the presently specified preflight procedures, prior to the first flight of each day accomplish the following. 1. Start both engines and operate at 1500 RPM. After the oil pressures stabilize, shut down the engines using the mixture control. 2. Open thecowl doors on both sides of the engines and check all engine compartment fluid hoses and fittings for indications of fluid (fuel or oil) leakage Check the wheel wells for these same conditions using a flashlight or supplemental light as necessary to provide adequate illumination of the area. 3. Correct any leak detected and secure cowl doors. Amendment 39-3220 became effective June 1, 1978. Amendment 39-3277 became effective August 17, 1978. This amendment 39-3413 becomes effective February 6, 1979.
94-14-20 R1: This amendment revises an existing airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76A helicopters. That AD currently requires a one-time inspection of the tail rotor blade (blade) spar elliptical centering plug (centering plug) for disbonding and the addition of a retaining pad on the pitch change shaft between the output tail rotor gearbox flange and the inboard tail rotor spar. This amendment contains the same requirements as the existing AD but clarifies that the 500-hour time-in-service (TIS) repetitive inspections, which could cause inadvertent damage, are not required. This AD also incorporates by reference a revised alert service bulletin (ASB) that does not include the 500-hour TIS repetitive inspections. This amendment is prompted by operator confusion about whether the current AD continues to require the 500- hour TIS repetitive inspections. The actions specified by this AD are intended to verify that the FAA has determined that the500-hour TIS repetitive inspections are not required to prevent the centering plug from disbonding and moving out of position, loss of tail rotor control, and subsequent loss of control of the helicopter.
74-12-08: 74-12-08 AIRESEARCH MANUFACTURING COMPANY of ARIZONA: Amendment 39-1862. Applies to Model TSCP700-5 Auxiliary Power Units installed in, but not limited to, Airbus Industries Model A300B aircraft certificated in all categories. Compliance required as indicated. (a) For APU's with less than 1500 operating cycles on the effective date of this AD, inspect, prior to any further in-flight operation, unless already accomplished, the fuel control differential pressure regulator housing, P/N 977320-1 or -2, for minimum dimensions and cracks per paragraphs 2.B.(2) and (3) of AiResearch Alert Service Bulletin 969900-49-A3644, dated May 14, 1974, or later FAA-approved revisions. Re-work parts, if necessary, per paragraph 2.B.(4). Housings which meet the prescribed minimum dimensions, or which are reworked to meet these dimensions per paragraph 2.B.(4) shall be re-identified as P/N 977320-4. Housings not meeting these dimensional requirements shall be rendered unserviceable and replaced with serviceable P/N 977320-4 housings. Housings which meet inspection and dimensional requirements may be continued in service up to a maximum of 1500 operating cycles. Note: For the purpose of this AD, an APU operating cycle is any operation consisting of a start and shut-down. The number of cycles may be determined by actual count, or, subject to acceptance by the assigned FAA Maintenance Inspector, may be calculated by dividing the fuel control assembly time in service by the operator's fleet average APU operating time per APU operating cycle. (b) For all APU's with 1,500 or more operating cycles in service on the effective date of this AD, inspect per (a), above, prior to further in-flight operation, unless already accomplished, and, in addition thereto, and prior to further in-flight operation, modify the fuel control assembly per (c), below. (c) Before exceeding 1500 operational cycles in service, inspect the fuel control differential pressure regulator body per paragraph 2.B.(2) and modify the fuel control assembly in accordance with paragraph 2.C. of AiResearch Service Bulletin 969900-49-A3644, dated May 14, 1974, or later FAA-approved revisions. Re-identify fuel control assembly per paragraph 2.D. of the referenced service bulletin. (d) Within 3000 operating cycles in service after the accomplishment of paragraph (c), above, and at intervals not to exceed 3000 operating cycles in service thereafter, perform the inspections as defined in paragraph 2.B.(2) of AiResearch Service Bulletin 969900-49-A3644, dated May 14, 1974, or later FAA-approved revisions. (e) The inspections prescribed in paragraph (d), above, may be discontinued when the fuel control differential pressure regulator P/N 977320-4 is replaced with a housing, P/N 977656-1. (f) Equivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiation data. This amendment becomes effective June 10, 1974.
77-10-07: 77-10-07 BELL HELICOPTER TEXTRON: Amendment 39-2900. Applies to Model 205A-1 helicopters, Serial Numbers 30001 through 30232, certificated in all categories. For helicopters certificated and operated pursuant to Part 133 of the FARs (Class B rotorcraft-load combination or Class C rotorcraft-load combinations as defined by Part 1 of the FARs), compliance is required within the next 100 hours cumulative time in service involving external load combinations as defined above, or 300 hours total time in service, whichever comes first, after the effective date of this Airworthiness Directive (AD), unless previously accomplished. For standard category helicopters not approved for external load operations as defined above, compliance is required within the next 300 hours time in service after the effective date of this AD, unless previously accomplished. To prevent failure of the engine-to-transmission drive couplings due to excessive angularity under high loading conditions,adjust the engine-to-transmission alignment as described below: (a) Remove the engine-to-transmission driveshaft assembly, P/N's 205-040-004-3, - 11, or -17, in accordance with instructions in the appropriate maintenance and overhaul manuals. (b) Using instructions and special tools prescribed by the maintenance and overhaul manuals, establish the engine-to-transmission alignment prescribed by the manual except as follows: (1) Index the target plate inner scale to 8.0 (instead of 3.5) and index the target plate outer scale to 35.6 (instead of 1.75). NOTE: Transmission position must be adjusted and leveled to maintenance manual specifications. Engine position adjustment procedures must follow maintenance manual instructions. (2) Establish angularity as follows: Install dial indicator in accordance with instructions in the maintenance manual at 2.5 inch radius. Read zero at 12 o'clock position; read +0.030 + 0.004 at 6 o'clock position. Reset dial indicatorto zero at the 3 o'clock position; read +0.006 + 0.004 at 9 o'clock position. Plus reading on dial indicator means that flange on transmission is closer to flange on engine. (c) Shim engine support fittings to obtain required alignment. If total laminated shim thickness (P/N 205-060-137-1 or 205-060-138-1), required under any engine support fitting, exceeds 0.188 inches, fabricate a plate of 2024-T4 aluminum alloy 0.100 thick, same outside dimensions as shim stock, and structurally bond the plate to the engine service deck with EC 934. Total thickness of shims and plate under any engine mount fitting must not exceed 0.288 inches. Verify that the engine support fittings are reinstalled with the same fore and aft orientation as before. (d) Interference between the engine and the aft upper firewall at the 9 o'clock position (looking forward) may result with this realignment. If this condition occurs, accomplish the following: Remove the aft upper firewall assembly P/N 205-060-909-27 and disassemble by removing the sixteen (16) screws. Remove the aft section of the firewall web P/N 204-060-909-13 and enlarge the sixteen (16) holes by drilling to 5/16 inch. Deburr the drilled holes. Reassemble the firewall assembly using P/N AN970-3 washers over the enlarged holes and under the 16 screw heads. (e) Check engine deck fittings screws and bolts for proper length and thread engagement. (f) Check fuel control and governor linkage for proper rigging and cushion. (g) Reinstall the driveshaft assembly. Reinstall transmission 5th mount assembly. Follow maintenance manual instructions for details of reinstallation of access panels, firewall attachments, and related cleanup, as required. Equivalent means of compliance with the modifications prescribed by this AD may be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Post Office Box 1689, Fort Worth, Texas, 76101. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, may adjust the compliance time prescribed by this AD, if the request contains substantiating data to justify the increase for that operator. This amendment becomes effective May 18, 1977.