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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.