Results
99-04-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires a one-time operational test to detect discrepancies of the delay valves and check valves of the main landing gear (MLG); and corrective actions, if necessary. This amendment also requires replacement of the retraction bracket assemblies of the MLG with new or reworked retraction bracket assemblies. 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 failure of the retraction bracket assemblies of the MLG, which could result in an undampened extension of the MLG, damage to the sidestay and attachment structure, and possible collapse of the MLG.
98-21-28: This action confirms the effective date of Airworthiness Directive (AD) 98-21-28, which applies to certain British Aerospace Jetstream Model 3101 airplanes. AD 98-21-28 requires modifying the propeller de-icing system to assure system performance at low ambient temperatures. This AD was the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified in this AD are intended to prevent propeller-induced vibrations from occurring during icing encounters at low ambient temperatures, which could result in decreased performance of the de-icing system during icing encounters with possible loss of control of the airplane.
2007-02-24: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 747 airplanes. This AD requires repetitive inspections for cracking of the web of the station (STA) 2360 aft pressure bulkhead around the fastener heads in the critical fastener rows in the web lap joints, from the Y-chord to the inner ring; and repair if necessary. This AD also requires a modification, which terminates the repetitive inspections. This AD results from analysis by the manufacturer that the radial lap splices of the STA 2360 aft pressure bulkhead are subject to widespread fatigue damage. We are issuing this AD to detect and correct cracking of the bulkhead web at multiple sites along the radial lap splice, which could join together to form cracks of critical length, and result in rapid decompression and loss of control of the airplane.
87-23-08: 87-23-08 TELEDYNE CONTINENTAL MOTORS (TCM): Amendment 39-5735. Applies to TCM IO-520 and TSIO-520 series engines. Compliance is required as indicated, unless already accomplished. To prevent the installation of crankshafts with existing subsurface fatigue cracks which could result in crankshaft failure with resultant loss of engine power, at the next and every subsequent crankshaft removal from the engine case or installation of a replacement crankshaft, accomplish the following: (a) Prior to installation in the engine, conduct an ultrasonic inspection in accordance with TCM Service Bulletin M87-5, Revision 1, dated May 25, 1987, and Crankshaft Ultrasonic Inspection Procedure, Form X30554, dated February 1981. (b) If any cracks are found, replace crankshaft with serviceable crankshaft in accordance with TCM Service Bulletin M87-5, Revision 1, dated May 25, 1987. (c) If no cracks are found, mark the propeller mounting flange in accordance with TCM Service BulletinM87-5, Revision 1, dated May 25, 1987. NOTE: Accomplishment of the ultrasonic inspection does not set aside any requirements for magnaflux or other inspections specified in TCM overhaul manuals. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Atlanta Aircraft Certification Office, Federal Aviation Administration, Central Region, 1669 Phoenix Parkway, Suite 210, Atlanta, Georgia 30349. TCM Service Bulletin M87-5, Revision 1, dated May 25, 1987, identified and described in this document, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). Copies may be obtained from Teledyne Continental Motors, P.O. Box 90, Mobile, Alabama 36601. Copies may be examined in the Regional Rules Docket, Office of the Regional Counsel, Room 311, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803 or at the Office of the Federal Register, 1100 LStreet NW, Room 8401, Washington, DC. This amendment becomes effective November 30, 1987.
97-07-04: 97-07-04 ROLLS-ROYCE PLC: Amendment 39-9978. Docket 95-ANE-56. Applicability: Rolls-Royce plc (R-R) Models RB.211-524G and -524H turbofan engines that have not been modified in accordance with R-R Service Bulletin (SB) No. RB.211-72-9764, Revision 2, dated November 10, 1995, installed on but not limited to Boeing 747-400 and 767- 300 series aircraft. Note 1: 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 (d) 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 engine combustor liner deterioration due to thermal fatigue, which can result in combustor liner and case burn-through and engine fire, accomplish the following: (a) Perform initial and repetitive borescope inspections of the engine combustor liner head section in accordance with the intervals listed in Section 1.C. Compliance (1), and the procedures described in Section 1.D. Action (1) of R-R SB No. RB.211-72-B482, Revision 3, dated September 27, 1996. Prior to further flight, remove combustors that do not meet the return to service criteria specified in Section 1.E. Acceptance Limits of the SB and replace with serviceable parts. (b) Perform initial and repetitive borescope inspections of the meterpanel in accordance with the intervals listed in Section 1.C. Compliance (2), andthe procedures described in Section 1.D. Action (2) of R-R SB No. RB.211-72-B482, Revision 3, dated September 27, 1996. Prior to further flight, remove combustors that do not meet the return to service criteria specified in Section 1.E. Acceptance Limits of the SB and replace with serviceable parts. (c) Installation of a front combustion liner with a strengthened head section in C263 material in accordance with R-R SB No. RB.211-72-9764, Revision 2, dated November 10, 1995, constitutes terminating action to the inspection requirements 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, 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 2: Information concerning the existence of approved alternativemethods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (e) 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 aircraft to a location where the requirements of this AD can be accomplished. (f) The actions required by this AD shall be done in accordance with the following R-R SBs: Document No Pages Revision Date RB.211-72-B482 1 3 September 27, 1996 2 2 March 11, 1996 3 3 September 27, 1996 4 2 March 11, 1996 5 3 September 27, 1996 6 2 March 11, 1996 7,8 3 September 27, 1996 9 2 March 11, 1996 Total Pages: 9. RB.211-72-9764 1 2 November 10, 1995 2 Original August 20, 1993 3 2 November 10, 1995 4-6 1 August 25, 1995 7-30 Original August 20, 1993 Supplement 1 Original August 20, 1993 Total Pages: 31. Thisincorporation 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 Rolls-Royce North America, Inc., 2001 South Tibbs Ave., Indianapolis, IN 46241; telephone (317) 230-3995, fax (317) 230-4743. Copies may be inspected at the 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. (g) This amendment becomes effective on June 6, 1997.
93-02-05: 93-02-05 TEXTRON LYCOMING: Amendment 39-8487. Docket 92-ANE-56. Applicability: Textron Lycoming reciprocating opposed piston engines incorporating fuel injection lines as listed in Textron Lycoming Service Bulletin No. (SB) 342A, dated May 29, 1992, except for Model TIO-540-S1AD engines. Affected engine models are installed on but not limited to Piper PA-24 Comanche, PA-30 and PA-39 Twin Comanche, PA-28 Arrow, and PA-23 Aztec; Beech 60 Duke and 23 Musketeer; Mooney M20; and Cessna 177 Cardinal aircraft. NOTE: Engines with an "I" in the prefix of the model designation incorporate fuel injection. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the fuel injector fuel lines allowing fuel to spray into the engine compartment, resulting in an engine fire, accomplish the following: (a) Within 25 hours time in service after the effective date of this AD, inspect the fuel injector fuel lines between the fuel manifold and the fuel injector nozzles in accordance with Textron Lycoming Service Bulletin No. 342A, dated May 26, 1992. (b) Prior to further flight, replace any fuel injector fuel line that does not meet all the return to service conditions specified in Textron Lycoming SB No. 342A, dated May 26, 1992. (c) Thereafter, at each annual inspection, at each 100-hour inspection, at each engine overhaul, and after any maintenance has been performed on the engine where the fuel injector fuel lines have been disconnected, moved, or loosened, reinspect the fuel injector fuel lines in accordance with Textron Lycoming SB No. 342A, dated May 26, 1992, and replace as necessary any fuel injector fuel line that does not meet all the return to service conditions specified in that SB. (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, New York Aircraft Certification Office. The request should beforwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the New York Aircraft Certification Office. (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 inspection, and replacement, if necessary of the fuel injector fuel lines shall be done in accordance with the following service document: Document No. Pages Date Textron Lycoming SB No. 342A 1-31 May 26, 1992 Total pages: 31 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 Textron Lycoming Reciprocating Engine Division, 652 Oliver Street, Williamsport, Pennsylvania 17701. Copies may be inspected at the FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on June 14, 1993.
98-15-05: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-200A series airplanes, that requires a one-time inspection of the gust damper of the elevator control system to determine if the gust damper is properly charged, and of the horizontal stabilizer to detect cracking of elevator hinge rib 1; and corrective action, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking of elevator hinge rib 1 of the horizontal stabilizer, which could occur if the gust damper of the elevator control system discharges and allows the elevator to move freely in ground gust conditions. Such cracking could result in damage to the structural attachment of the elevator to the horizontal stabilizer, and consequent reduced controllability of the airplane.
2007-08-01: The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CT7-5A2, -5A3, -7A, -7A1, -9B, - 9B1, and -9B2, -9C, -9C3, -9D, and -9D2 turboprop engines, with certain part number (P/N) and serial number stage 2 turbine aft cooling plates installed. That AD currently requires a onetime eddy current inspection (ECI) of boltholes in certain P/N stage 2 turbine aft cooling plates. This AD expands the population of affected CT7 turboprop engine models, but reduces the number of cooling plates affected. It also requires a onetime ECI of boltholes in certain P/N stage 2 turbine aft cooling plates with specific serial numbers. This AD results from the manufacturer expanding the list of affected engine models and identifying the affected stage 2 turbine aft cooling plates by serial number. We are issuing this AD to prevent separation of the stage 2 turbine aft cooling plate, resulting in uncontained engine failure and damage to the airplane.
82-01-06: 82-01-06 COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA: Amendment 39-4290. Applies to Model A109A series helicopters through Serial Number 7169 equipped with engine mount central legs, P/N 109-0605-06 and 109-0605-07, certificated in all categories (Airworthiness Docket No. 81-ASW-43). Compliance is required within 200 hours' time in service after the effective date of this AD, unless already accomplished. To prevent failure of the engine mount central leg and possible loss of engine support, accomplish the following: (a) Remove the engine mount central legs, P/N 109-0605-06-13, 109-0605-06-14, 109-0605-07-13, and 109-0605-07-14. (b) Install engine mount central leg assemblies, P/N 109-0640-84-1 and -2, and P/N 109-0640-85-1 and -2 as described in Section 71-20-00 of the A109A maintenance manual. (c) Install engines and check engine to transmission alignment as described in Section 71-00-00 of the A109A maintenance manual. (d) If an equivalent means of compliance is used in complying with this AD, that equivalency must be approved by the Chief, Aircraft Certification Staff, AEU-100, FAA, Europe, Africa and Middle East Office, c/o American Embassy, Brussels, Belgium. Compliance with Agusta Technical Bulletin No. 109-25, dated August 29, 1980, constitutes compliance with this AD. This amendment becomes effective February 8, 1982.
2007-07-15: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300 B4-600, B4-600R, C4- 605R Variant F, and F4-600R (collectively called A300-600) series airplanes; and Model A310 series airplanes. That AD currently requires a one-time inspection for damage of the integrated drive generator (IDG) electrical harness and pyramid arm, and repair if necessary. This new AD adds new repetitive inspections, which, when initiated, terminate the inspection required by the existing AD. This new AD also requires repairing damage and protecting the harness. This new AD also provides for optional terminating action for the repetitive inspections. This new AD also removes certain airplanes from the applicability of the existing AD. This AD results from a report of structural damage on the forward pyramid arm of an engine pylon due to chafing of the IDG electrical harness against the structure of the pyramid arm. We are issuing this AD to prevent electrical arcing in the engine pylon, which could result in loss of the relevant alternating current (AC) bus bar, reduced structural integrity of the engine pylon, and possible loss of control of the airplane. DATES: This AD becomes effective May 14, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of May 14, 2007. On May 13, 2004 (69 FR 23090, April 28, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A310-54A2038, dated February 19, 2004; and Airbus All Operators Telex A300-54A6037, dated February 19, 2004.
2007-06-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: * * * incidences have been reported to Britten-Norman Aircraft Ltd where cracks have been found in the inner shell of the pitot/ static pressure heads. This could result in incorrect readings on the pressure instrumentation, e.g. altimeters, vertical speed indicators (rate-of-climb) and airspeed indicators. We are issuing this AD to require actions to correct the unsafe condition on these products.
80-07-07: 80-07-07 BEECH: Amendment 39-3729. Applies to Model 77 (Serial Numbers WA-1 through WA-78, WA-80 through WA-86, and WA-88) certificated in all categories. COMPLIANCE: Required as indicated unless already accomplished. To prevent excessive aileron control forces or jamming of the aileron control system, within the next twenty-five (25) hours time-in-service after the effective date of this AD accomplish the following: A) Replace the aileron bearings (P/N 108-130010-17) with aileron bushings (P/N 108-160010-39) in accordance with procedures set forth in Beechcraft Service Instructions No. 1119. B) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. C) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing District Office, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209. This amendment becomes effective April 3, 1980.
2019-19-11: The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney (PW) PW1519G, PW1521G, PW1521GA, PW1524G, PW1525G, PW1521G-3, PW1524G-3, PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A model turbofan engines. This AD requires initial and repetitive inspections of the low-pressure compressor (LPC) inlet guide vane (IGV) and the LPC rotor 1 (R1) and, depending on the results of the inspections, possible replacement of the LPC. This AD was prompted by two recent in-flight shutdowns (IFSDs) that occurred as the result of failures of the LPC R1. The FAA is issuing this AD to address the unsafe condition on these products.
95-12-24: This amendment adopts a new airworthiness directive (AD) that is applicable to all Lockheed Model L-1011-385 series airplanes. This action requires an inspection to detect cracking of the bulkhead at fuselage station (FS) 1363 at butt line (BL) 42.5, and repair or additional inspections, if necessary. This amendment is prompted by reports indicating that fatigue cracking was found in the rear bulkhead at FS 1363. The actions specified in this AD are intended to prevent reduced structural integrity of the fuselage due to fatigue cracking of the pressure bulkhead.
95-21-12: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter Deutschland GmbH (ECD) (Eurocopter) Model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1 helicopters, that requires initial and repetitive inspections of the main rotor (M/R) blade upper and lower surfaces for bulging. This amendment is prompted by two reported incidents in which a balance weight became detached from inside the M/R blade structure and migrated toward the tip of the M/R blade. The actions specified by this AD are intended to detect movement of a balance weight and to prevent severe vibrations and a subsequent precautionary landing.
79-12-01: 79-12-01 MAULE AIRCRAFT CORPORATION: Amendment 39-3478. Applies to certain M-4 and M-5 series aircraft. Serial Numbers are: M-4 Series: 4 to 94, 1001 to 1045, 1S to 3S, 1T to 3T, 1C to 11C; M-4-210C: 1001C to 1117C; M-4-220S: 2001S; M-4-220C: 2001C to 2190C; M-4-180C: 3001C to 3006C; M-5 series: M-5-210C: 6001C to 6206C: M-5-220C: 5001C to 5057C; M-5-235C: 7001C to 7283C; M-5-180C: 8001C to 8004C; M-5-210TC: 9001C, airplanes certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent failure of the horizontal tail-to-fuselage front attach tube, accomplish the following within 25 hours' time in service after the effective date of this AD, or 60 days after the effective date whichever occurs first: 1. Inspect the horizontal tail-to-fuselage front attach tube in accordance with paragraphs (1) and (5) of Maule Aircraft Corporation Service Bulletin No. 1, dated May 3, 1979, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. 2. If cracks are found, obtain replacement parts from Maule Aircraft Corporation and replace in accordance with Advisory Circular (AC) 43.13-1A prior to further flight. 3. Modify the horizontal tail-to-fuselage front attach tube in accordance with paragraphs (3) and (4) of Maule Aircraft Corporation Service Bulletin No. 1, dated May 3, 1979, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. 4. Make appropriate maintenance record entry. 5. An equivalent method of compliance may be used if approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. This amendment is effective June 7, 1979.
89-21-01: 89-21-01 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-6562. Final copy of priority letter AD. Docket No. 89-ASW-53. Applicability: AS 350 and AS 355 series helicopters, all serial numbers, containing M/R swashbearing assemblies, Part Number (P/N) 704A33 651.126 (bronze cage), or P/N 704A33 651.009-.051, or .080 (composite cage), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the M/R swashplate bearing, and possible loss of the helicopter, accomplish the following: (a) Within the next 10 hours' time in service after receipt of this AD, inspect the bearing for play or binding; measure the swashplate rotational torque; inspect for proper assembly of the bearing; and inspect for proper lubrication, in accordance with the following: (1) Check for play and hard points (ref. paragraph 5.2.b of Aerospatiale MET Work Card 62.30.00.601). (2) Check the star bearing rotational torque as follows: (i) Rotate the star manually approximately 10 times. (ii) Using a spring scale hooked onto the pitch change rod attachment point, check that the load "C" (see figure 1) required to rotate the star is equal to or less than 2.5 daN. (iii) If "C" is greater than 2.5 daN, replace the bearings before further flight. (3) Check that the bearing is correctly installed as follows: (i) Remove the bolts and nuts while retaining the deflector or baffles (see figure 1) and stops. (ii) Move the deflector or baffles, the bearing inside stop, and the outside stop upwards. (iii) Check that the plates that immobilize the bearing inner and outer races are seated correctly against the upper faces of the stationary and rotating stars. (iv) Check that the dimension "L" (see figure 1) bearing inner race protrusion is above the star upper face and is equal to or less than 2.5mm. If "L" is greater than 2.5mm, replace the bearing before further flight. (4) Check the bearing grease as follows: (i) Install inner bolts to prevent grease from egressing through bolt holes and inject grease through the greasing nipple located beneath the stationary star, until the grease comes out. (ii) Repeat the greasing operation three times, turning the star through 180 degrees between each operation. (iii) Recover the grease evacuated and visually check to see that it does not contain bronze particles (bearing P/N 704A33 651.126) or composite material particles (for bearing P/N's 704A33 651.009-.051 or .080). A blackish coloring of the grease is acceptable. (iv) If bronze or composite material particles are found, replace the bearing before further flight. (b) Repeat the inspections of paragraphs (a)(2) and (3) of this AD after each replacement of the swashplate bearing. (c) Within every 100 hours' additional time in service after compliance with the requirements of paragraph (a) of this AD, repeat the lubrication requirements of paragraph (a)(4) of this AD. (d) Within the next 400 hours' total time in service from the effective date of this AD, plug the nonrotating swashplate vent holes and barrel nut orifices in accordance with the following: (1) Remove the main rotor mast (ref. MET Work Card No. 62.30.00.401). (2) Remove and disassemble the swashplate (ref. MRR Work Card No. 62.30.00.702, Replacement of Swashplate Bearings). (3) On the nonrotating swashplate-- (i) Blank off the vent holes opposite the nonrotating scissors yoke (see figure 1A) with "DEVCON F" (as directed in the instructions provided with this product); (ii) Blank off the bushing holes using "DEVCON F" (same procedure); and (iii) Clean the areas to be coated with "DEVCON F" thoroughly with Trichlorethylene, making sure all traces of grease are removed. (4) Assemble the swashplates (ref. MRR Work Card No. 62.30.00.702). (5) Grease the bearing (ref. MET Work Card No. 12.00.00.305). (6) Assemble the rotor mast (ref. Work Card No. 62.30.00.401). (e) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where the inspections required by the AD may be accomplished. (f) An alternate method of compliance with this AD, which provides an equivalent level of safety, may be used if approved by the Manager, Rotorcraft Standards Staff, ASW-110, Federal Aviation Administration, Southwest Region, Fort Worth, Texas 76193-0110. This amendment (39-6562, AD 89-21-01) becomes effective on May 3, 1990, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD 89-21-01, issued on October 6, 1989, which contained this amendment.
2019-19-03: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 170 airplanes; Model ERJ 190-100 STD, - 100 LR, -100 ECJ, and -100 IGW airplanes; and Model ERJ 190-200 STD, - 200 LR, and -200 IGW airplanes. This AD was prompted by reports of the ram air turbine (RAT) compartment door seal peeling off and tangling up on the RAT rotor during flight test. This AD requires a general visual inspection for peeling-off of the RAT compartment door seal, bonding if necessary, and the rework of the RAT compartment door seal attachment. The FAA is issuing this AD to address the unsafe condition on these products.
99-26-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319 and A320 series airplanes, that requires repetitive inspections to detect cracking and delamination of the containers in which the off-wing emergency evacuation slides are stored, and corrective actions, if necessary. The AD also requires eventual modifications of the slides, which terminates the requirement for repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the loss of the escape slides during flight, which could make the emergency exits located over each wing unusable and result in damage to the fuselage.
2007-06-15: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters that requires replacing a certain hydraulic drive belt (drive belt). Also required is reducing the lubrication time interval for a certain hydraulic pump drive shaft (drive shaft). This amendment is prompted by in-flight failures of the drive belt and the drive shaft. The actions specified by this AD are intended to prevent in-flight failure of the drive belt or drive shaft, loss of hydraulic power to the flight control system, and subsequent loss of control of the helicopter.
2019-19-04: The FAA is adopting a new airworthiness directive (AD) for all Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. This AD was prompted by reports of cracks in the o-ring groove of magnetic fuel level indicators. This AD requires a one-time detailed inspection of the magnetic fuel level indicator for cracks and replacement of cracked magnetic fuel level indicators. The FAA is issuing this AD to address the unsafe condition on these products.
99-05-04: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 99-05-04 that was sent previously to all known U.S. owners and operators of all EMBRAER Model EMB-145 series airplanes by individual notices. This AD requires repetitive inspections to detect cracking or failure of the rod ends of the aileron power control actuator (PCA), and corrective actions, if necessary. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking or failure of the rod ends of the aileron PCA, which could result in reduced controllability of the airplane.
T95-01-51: T95-01-51 AIRBUS INDUSTRIE : TELEGRAPHIC AD ISSUED ON DECEMBER 29, 1994. DOCKET NO. 94-NM-248-AD. APPLICABILITY: ALL MODEL A300, A300-600, A310, A330, AND A340 SERIES AIRPLANES, CERTIFICATED IN ANY CATEGORY. NOTE 1: THIS AD APPLIES TO EACH AIRPLANE 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 AIRPLANES THAT HAVE BEEN MODIFIED, ALTERED, OR REPAIRED SO THAT THE PERFORMANCE OF THE REQUIREMENTS OF THIS AD IS AFFECTED, THE OWNER/OPERATOR MUST USE THE AUTHORITY PROVIDED IN PARAGRAPH (D) TO REQUEST APPROVAL FROM THE FAA. THIS APPROVAL MAY ADDRESS EITHER NO ACTION, IF THE CURRENT CONFIGURATION ELIMINATES THE UNSAFE CONDITION; OR DIFFERENT ACTIONS NECESSARY TO ADDRESS THE UNSAFE CONDITION DESCRIBED IN THIS AD. SUCH A REQUEST SHOULD INCLUDE AN ASSESSMENT OF THE EFFECT OF THE CHANGED CONFIGURATION ON THE UNSAFE CONDITION ADDRESSED BY THIS AD. IN NO CASE DOES THE PRESENCE OF ANY MODIFICATION, ALTERATION, OR REPAIR REMOVE ANY AIRPLANE FROM THE APPLICABILITY OF THIS AD. COMPLIANCE: REQUIRED AS INDICATED, UNLESS ACCOMPLISHED PREVIOUSLY. TO PREVENT RUPTURE OF A COCKPIT SLIDING WINDOW AND SUBSEQUENT RAPID DECOMPRESSION OF THE FUSELAGE, ACCOMPLISH THE FOLLOWING: (A) WITHIN 7 DAYS AFTER RECEIPT OF THIS TELEGRAPHIC AD, PERFORM AN INSPECTION OF THE LEFT- AND RIGHT-HAND SLIDING SIDE WINDOWS IN THE COCKPIT TO IDENTIFY THE PART NUMBER (P/N) OF THOSE WINDOWS, IN ACCORDANCE WITH PARAGRAPH 4.1 OF AIRBUS ALL OPERATORS TELEX (AOT) 30-01, DATED DECEMBER 22, 1994. (B) IF NO WINDOW MANUFACTURED BY PPG INDUSTRIES HAVING P/N NP175202-1 (LEFT-HAND SIDE) OR NP175202-2 (RIGHT-HAND SIDE) IS INSTALLED, NO FURTHER ACTION IS REQUIRED BY THIS AD. (C) IF ANY WINDOW MANUFACTURED BY PPG INDUSTRIES HAVING P/N NP175202-1 (LEFT-HAND SIDE) OR NP175202-2 (RIGHT-HAND SIDE) IS INSTALLED, PRIORTO FURTHER FLIGHT, ACCOMPLISH EITHER PARAGRAPH (C)(1), (C)(2), OR (C)(3) OF THIS AD IN ACCORDANCE WITH AIRBUS AOT 30-01, DATED DECEMBER 22, 1994. (1) DEACTIVATE THE ASSOCIATED SLIDING WINDOW DEFOGGING SYSTEM IN ACCORDANCE WITH THE PROCEDURES SPECIFIED IN PARAGRAPH 4.2.2 OF THE AOT. THE DEFOGGING SYSTEM MAY REMAIN DEACTIVATED UNTIL THE WINDOW IS REPLACED IN ACCORDANCE WITH PARAGRAPH (C)(3) OF THIS AD. NOTE 2: THIS AD MAY PERMIT THE DEFOGGING SYSTEM TO BE DEACTIVATED FOR A LONGER TIME THAN IS SPECIFIED IN THE MASTER MINIMUM EQUIPMENT LIST (MMEL). IN ANY CASE, THE PROVISIONS OF THIS AD PREVAIL. (2) INSTALL THERMO SENSITIVE INDICATORS IN TWO AREAS OF THE SLIDING SIDE WINDOW (LEFT- AND RIGHT-HAND SIDES) IN ACCORDANCE WITH THE PROCEDURES SPECIFIED IN PARAGRAPH 4.3 OF THE AOT. THEREAFTER, PERFORM A DAILY INSPECTION OF THE INDICATORS TO DETERMINE IF THE 60-DEGREE SEGMENT OF ANY INDICATOR TURNS FROM LIGHT GREY TO BLACK, IN ACCORDANCE WITH THE PROCEDURES SPECIFIED IN PARAGRAPH 4.3 OF THE AOT. IF ANY INDICATOR TURNS BLACK, PRIOR TO FURTHER FLIGHT, DEACTIVATE THE ASSOCIATED SLIDING WINDOW DEFOGGING SYSTEM IN ACCORDANCE WITH PARAGRAPH (C)(1) OF THIS AD. (3) REPLACE THE PPG INDUSTRIES WINDOW WITH A SERVICEABLE WINDOW MANUFACTURED BY PPG INDUSTRIES OR BY SPS, IN ACCORDANCE WITH THE PROCEDURES SPECIFIED IN PARAGRAPH 5.1 OF THE AOT. AFTER SUCH REPLACEMENT, NO FURTHER ACTION IS REQUIRED BY 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 3: 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 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. (F) COPIES OF THE APPLICABLE SERVICE INFORMATION MAY BE OBTAINED FROM AIRBUS INDUSTRIE, 1 ROND POINT MAURICE BELLONTE, 31707 BLAGNAC CEDEX, FRANCE. THIS INFORMATION MAY BE EXAMINED AT THE FAA, TRANSPORT AIRPLANE DIRECTORATE, 1601 LIND AVENUE, SW., RENTON, WASHINGTON. (G) TELEGRAPHIC AD T95-01-51, ISSUED ON DECEMBER 29, 1994, BECOMES EFFECTIVE UPON RECEIPT.
2019-18-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318-112, -121, and -122; A319-111, -112, - 115, -131, -132, and -133; A320-214, -216, -232, -233, -251N, and - 271N; and A321-211, -212, -213, -231, -232, -251N, -253N, -271N, and - 272N airplanes. This AD was prompted by reports of missing or loosened fasteners on connecting brackets of overhead stowage compartments (OHSC) and pivoting OHSC (POHSC). This AD requires modification of the OHSC and POHSC attachments, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
95-17-12: 95-17-12 AIRBUS INDUSTRIE: Amendment 39-9342. Docket 94-NM-143-AD. Applicability: Model A320 series airplanes on which Airbus Modification 22621 (reference Airbus Service Bulletin A320-27-1041) and Airbus Modification 23556 (reference Airbus Service Bulletin A320-29-1058) have not been installed, certificated in any category. NOTE 1: This AD applies to each airplane 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 airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (b) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent loss of the pilot's ability to control the moveable surfaces of the trimmable horizontal stabilizer (THS), accomplish the following: (a) Within 3,500 flight hours after the effective date of this AD, modify the THS in accordance with Airbus Service Bulletin A320-29-1058, July 16, 1993, and Airbus Service Bulletin A320-27-1041, Revision 2, dated April 20, 1994. (b) 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) 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. (d) The modification shall be done in accordance with Airbus Service Bulletin A320-29-1058, July 16, 1993, and Airbus Service Bulletin A320-27-1041, Revision 2, dated April 20, 1994. 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. 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. (e) This amendment becomes effective on September 21, 1995.