Results
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.
98-18-21: This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model C-212 series airplanes, that requires implementation of a corrosion prevention and control program either by accomplishing specific inspections or by revising the maintenance inspection program to include such a program. This amendment is prompted by reports of incidents involving corrosion and fatigue cracking in transport category airplanes that are approaching or have exceeded their economic design goal; these incidents have jeopardized the airworthiness of the affected airplanes. The actions specified by this AD are intended to prevent degradation of the structural capabilities of the airplane due to the problems associated with corrosion.
2019-18-08: The FAA is superseding Airworthiness Directive (AD) 2019-16-04 for all Engine Alliance (EA) GP7270 and GP7277 model turbofan engines. AD 2019-16-04 required a visual inspection of the 1st-stage low- pressure compressor (LPC) rotor assembly, referred to after this as the ``engine fan hub assembly,'' for damage, a one-time eddy current inspection (ECI) of the engine fan hub blade slot bottom and blade slot front edge for cracks; and removal of parts if damage or defects are found. AD 2019-16-04 also required replacement of the engine fan hub blade lock assembly for certain GP7270 and GP7277 model turbofan engines. This AD, for certain GP7270 and GP7277 model turbofan engines, reduces the compliance time for the initial ECI and requires repetitive ECIs of the engine fan hub blade slot bottom and blade slot front edge for cracks. This AD also retains the visual inspection requirements of the engine fan hub assembly for all GP7270 and GP7277 model turbofan engines. This AD was prompted by an uncontained failure of the engine fan hub. The FAA is issuing this AD to address the unsafe condition on these products.
98-07-03: This document corrects a technical bulletin date in airworthiness directive (AD) 98-07-03 that was incorrectly published in the Federal Register on March 24, 1998 (63 FR 14026). This AD is applicable to Bell Helicopter Textron, Inc. Model 412 helicopters and Agusta S.p.A Model AB 412 helicopters and requires a temporary reduction of the never-exceed velocity (Vne) limitation until an inspection of the tail rotor yoke (yoke) assembly for fatigue damage and installation of a redesigned yoke flapping stop are accomplished. Recurring periodic and special inspections to detect occurrences of yoke overload are also required.
2007-07-04: The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas Model MD-11 and -11F airplanes. This AD requires revising the maintenance inspection program that provides for inspection of principal structural elements (PSEs) and replacement of safe-life parts, to incorporate a new revision to the MD-11 Airworthiness Limitations Instructions. The revision reduces inspection intervals for fatigue cracking of certain PSEs, and expands the inspection area for a certain other PSE. This AD results from a revised damage tolerance analysis. We are issuing this AD to detect and correct fatigue cracking of certain PSEs, which could adversely affect the structural integrity of the airplane.
2007-07-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300-600 airplanes. This AD requires an inspection to determine if certain spoiler actuators having certain part numbers are installed, and eventual replacement of all affected actuators. This AD results from failure of a distribution block, which was detected during fatigue qualification tests of certain spoiler actuators. We are issuing this AD to prevent failure of the distribution block, which could result in leakage of the hydraulic fluid that supplies those actuators. This failure could cause failure of one of the three spoiler actuators and the associated hydraulic circuits, which could result in loss of those hydraulic circuits and consequent reduced controllability of the airplane.
99-14-07: This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Falcon 2000 series airplanes; and certain Dassault Model 900EX, and Mystere Falcon 900 series airplanes, that requires repetitive operational tests of the flap asymmetry detection system to verify proper functioning, and repair, if necessary; repetitive replacement of the inboard flap jackscrews with new jackscrews; repetitive measurement of the screw/nut play to detect discrepancies; and corrective action, if necessary. 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 jamming of the flap jackscrews, which could result in the inability to move the flaps or an asymmetric flap condition, and consequent reduced controllability of the airplane.
2019-17-07: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B19 (Regional Jet Series 100 & 440); CL-600-2C10 (Regional Jet Series 700, 701 & 702); CL-600-2D15 (Regional Jet Series 705); CL-600-2D24 (Regional Jet Series 900); and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of incorrect deployment of forward and aft flight attendant oxygen masks. This AD requires repacking the flight attendant and lavatory oxygen box assemblies as applicable, replacing the placards, and re-identifying the assemblies. The FAA is issuing this AD to address the unsafe condition on these products.
98-03-06: 98-03-06 AIRBUS INDUSTRIE: Amendment 39-10298. Docket 97-NM-178-AD. Applicability: Model A300-600 series airplanes, as listed in Airbus Service Bulletin A300-57A6087, dated August 5, 1997; and Model A300 series airplanes, as listed in Airbus Service Bulletin A300-57A0234, dated August 5, 1997; 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 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 detect and correct cracks in Gear Rib 5 of the main landing gear attachment fittings at the lower flange, which could result in reduced structural integrity of the airplane, accomplish the following: (a) For Model A300 series airplanes that have accumulated more than 27,000 flight cycles as of the effective date of this AD: Except as provided by paragraph (b) of this AD, within 40 flight cycles after the effective date of this AD, perform a detailed visual inspection to detect cracks in Gear Rib 5 of the main landing gear attachment fittings at the lower flange, in accordance with Airbus Service Bulletin A300-57A0234, dated August 5, 1997. Thereafter, repeat the inspection at intervals not to exceed 40 flight cycles, until the actions required by paragraph (b) are accomplished. (b) For all airplanes: Perform a detailed visual and a high frequency eddy current inspection to detect cracks in Gear Rib 5 of the main landing gear attachment fittings at the lower flange, in accordance with Airbus Service Bulletin A300-57A6087 (for Model A300-600 series airplanes) or A300-57A0234 (for Model A300 series airplanes), both dated August 5, 1997; as applicable; at the time specified in paragraph (b)(1) or (b)(2) of this AD, as applicable. Accomplishment of the inspection required by this paragraph terminates the inspections required by paragraph (a) of this AD. (1) For airplanes that have accumulated 20,000 or more total flight cycles as of the effective date of this AD: Inspect within 500 flight cycles after the effective date of this AD. (2) For airplanes that have accumulated less than 20,000 total flight cycles as of the effective date of this AD: Inspect prior to the accumulation of 18,000 total flight cycles, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later. (c) If any crack is detected during any inspection required by this AD, prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. (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, International Branch, ANM-116. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (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) The actions shall be done in accordance with Airbus Service Bulletin A300-57A6087, dated August 5, 1997; or Airbus Service Bulletin A300-57A0234, dated August 5, 1997; as applicable. 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. NOTE 3: The subject of this AD is addressed in French airworthiness directive (CN) 97- 274-230(B), dated September 24, 1997. (g) This amendment becomes effective on March 9, 1998.
78-26-07: 78-26-07 BOEING: Amendment 39-3375. Applies to all Model 727 airplanes equipped with operative thrust reverser assemblies P/N 65-27800-29 through 65-27800-59 which have any of the following actuator and track assemblies: P/N 65-37920-28, -30, -32, or -34. \n\tA.\tWithin ten (10) days from the effective date of this AD, install a placard stating, "Idle Reverse Only" above the EPR indicator for each engine position equipped with one of the above operative thrust reverser assemblies, except those equipped with any of the above reverser assemblies and track and actuator assemblies that have been inspected and reworked in accordance with Boeing Service Bulletin 727-78-A86, dated December 8, 1978, or later FAA approved revisions, or an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tThe 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). \n\tAll persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective January 3, 1979.
98-21-21: 98-21-21 Bob Fields Aerocessories: Amendment 39-10844; Docket No. 98-CE-88-AD. Applicability: Inflatable door seals, installed either in accordance with the applicable supplemental type certificate (STC) or through field approval, that are installed on, but not limited to, the following aircraft: Affected STC Make and Model Aircraft Affected SA3735NM Cessna Models 170, 170A, and 170B Airplanes SA4136WE Cessna Models 310, 310A, 310B, 310C, 310D, 310E, 310F, 310G, 310H, 310I, 310J, 310K, 310L, 310N, 310P, 310Q, 310R, T310P, T310Q, and T310R Airplanes SA2226NM Cessna Models P210N and P210R Airplanes SA3736NM Cessna Models 185, 185A, 185B, 185C, 185D, A185E, and A185F Airplanes SA4177WE Cessna Models 175, 175A, 175B, and 175C Airplanes SA4212WE Cessna Models 210, 210A, 210B, 210C, 210D, 210E,210F, 210G, 210H, 210J, 210K, 210L, 210M, 210N, T210F, T210G, T210H, T210J, T210K, T210L, T210M, T210N, 210-5 (205), and 210-5A (205A) Airplanes SA4213WE Cessna Models 310, 310A, 310B, 310C, 310D, 310F, 310G, 310H, 310I, 310J, 310K, 310L, 310N, 310P, 310Q, 310R, T310P, T310Q, and T310R Airplanes SA4283WE Cessna Models 172, 172A, 172B, 172C, 172D, 172E, 172F, 172G, 172H, 172I, 172K, 172L, 172M, and 172N Airplanes SA4284WE Cessna Models 180, 180A, 180B, 180C, 180D, 180E, 180F, 180G, 180H, 180J, and 180K Airplanes SA4285WE Cessna Models 182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, R182, and TR182 Airplanes SA4286WE Cessna Models 206, P206, P206A, P206B, P206C, P206D, P206E, TP206A, TP206B, TP206C, TP206D, TP206E, U206, U206A, U206B, U206C, U206D, U206E, U206F, U206G, TU206A, TU206B, TU206C, TU206D, TU206E, TU206F, and TU206G Airplanes SA4287WE Cessna Models 320, 320A, 320B, 320C, 320D, 320E, 320F, and 320-1 Airplanes SA4180WE Raytheon (Beech) Models H35, J35, K35, M35, N35, P35, S35, V35, V35A, V35B, 35-33, 35-A33, 35-B33, 35-C33, 35-C33A, E33, E33A, E33C, F33, F33A, F33C, G33, 36,A36, A36TC, and B36TC Airplanes SA4184WE Raytheon (Beech) Models 95, B95, B95A, E95, 95-55, 95-A55, 95-B55, 95-B5A, 95-B55B, 95-C55, D55, E55, 56TC, 58, and 58A Airplanes SA4239WE Raytheon (Beech) Models 58P, 58PA, 58TC, and 58TCA Airplanes SA4240WE Raytheon (Beech) Models 50, B50, C50, D50, D50A, D50B, D50C, D50E, D50E-5990, E50, F50, G50, H50, and J50 Airplanes SA4282WE Raytheon (Beech) Models 35, A35, B35, C35, D35, E35, F35, G35, and 35R Airplanes SA4178WE Mooney Models M20, M20A, M20C, M20D, M20E, M20F, M20G, M20J, and M20K Airplanes SA4472NM Aerostar Models PA-60-601P, PA-60-602P, and PA-60-700P Airplanes SA4234WE The New Piper Aircraft, Inc. (Piper) Models PA-34-200, PA-34-200T, and PA-34-220T Airplanes SA4179WE Piper Models PA-24, PA-24-250, PA-24-260, and PA-24-400 Airplanes SA4235WE Piper Models PA-44-180 and PA-44-180T Airplanes SA4236WE Piper Models PA-28-140, PA-28-150, PA-28-160, PA-28-180, PA-28-235, PA-28-151, PA-28-181, PA-28-161, PA-28-236, PA-28-201T, PA-285-160, PA-28S-160, PA-28S-180, PA-28R-180, PA-28R-200, PA-28R-201, PA-28R-201T, PA-28RT-201, and PA-28RT-201T Airplanes SA4237WE Piper Models PA-23, PA-23-160, PA-23-235, PA-23-250, and PA-E23-250 Airplanes SA4238WE Piper Models PA-30, PA-39, and PA-40 Airplanes SA4385WP Piper Models PA-31, PA-31-300, PA-31-325, and PA-31-350 Airplanes SA4288WE Piper Models PA-32-260, PA-32-300, PA-32S-300, PA-32-301, PA-32-301T, PA-32R-300, PA-32R-301, PA-32R-301T, PA-32RT-300, and PA-32RT-300T Airplanes SA2511NM Bellanca Models 17-30, 17-31, and 17-31TC Airplanes SA2510NM Bellanca Models 17-30A, 17-31A, and 17-31ATC Airplanes SA4316WE Wing Aircraft Company Model D-1 Airplanes NOTE 1: This AD applies to each aircraft identified in the preceding applicability provision that has the affected inflatable door seals installed, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For aircraft thathave 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 (f) 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 prior to further flight after the effective date of this AD, unless already accomplished. To prevent smoke and a possible fire in the cockpit caused by overheating of the electric door seal inflation systems, which could result in passenger injury, accomplish the following: (a) Deactivate the electric door seal inflation system by accomplishing the following: (1) Disconnect the battery. (2) Locate the air pump and identify the power wire to theair pump. (3) Trace the power wire to its connection to the airplane's original electrical power system. Disconnect the power wire at its attachment to the airplane's electrical power system and stow the wire end. (4) For non-pressurized airplanes or for airplanes that have an operating manual door seal inflation system, fabricate a placard that incorporates the following words utilizing letters that are at least 0.10- inch in height, and install this placard on the instrument panel within the pilot's clear view: "ELECTRIC DOOR SEAL INFLATION SYSTEM INOPERATIVE" (5) For pressurized airplanes or for airplanes that do not have an operating manual door seal inflation system, fabricate a placard that incorporates the following words utilizing letters that are at least 0.10- inch in height, and install this placard on the instrument panel within the pilot's clear view: "ELECTRIC DOOR SEAL INFLATION SYSTEM INOPERATIVE. THIS AIRPLANE CAN ONLY BE OPERATED IN UNPRESSURIZED FLIGHT" (6) Reconnect the battery before returning to service. (b) Insert a copy of this AD into the Limitations Section of the airplane flight manual (AFM). (c) As an alternative method of compliance to the actions of paragraph (a), including all subparagraphs, and paragraph (b) of this AD, remove all provisions of the Bob Fields Aerocessories inflatable door seals, and install original equipment manufacturer door seals or an FAA-approved equivalent that is of different design than the referenced Bob Fields Aerocessories inflatable door seals. (d) As of the effective date of this AD, no person may install on any aircraft, Bob Fields Aerocessories inflatable door seals either in accordance with the applicable STC or through field approval. (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 thisAD can be accomplished provided the following are adhered to, as applicable: (1) Locate and remove the in-line fuse for the electric door seal inflation system; or (2) Pull the system circuit breaker for the electric door seal inflation system; and (3) For pressurized airplanes or for airplanes that do not have an operating manual door seal inflation system, operate the airplane in unpressurized flight only. (f) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Blvd., Lakewood, California 90712. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. (g) Information related to this AD may be examined at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (h) This amendment becomes effective on October 30, 1998, to all persons except those persons to whom it was made immediately effective by priority letter AD 98-21-21, issued October 2, 1998, which contained the requirements of this amendment.
93-01-11: 93-01-11 BRITISH AEROSPACE: Amendment 39-8465. Docket 92-NM-56-AD. Applicability: All Model BAe 146-100A, -200A, and -300A series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the wings, accomplish the following: (a) Prior to the accumulation of 24,000 landings, or within 60 days after the effective date of this AD, whichever occurs later: Perform an X-ray inspection to detect fatigue cracks in the left and right wing upper skins, joint straps, and stringers in the vicinity of rib "O," in accordance with British Aerospace Inspection Service Bulletin 57-41, dated July 26, 1991. (1) If cracks are found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Thereafter, repeat the inspection required by paragraph (a) of this AD at intervals not to exceed9,000 landings, in accordance with the service bulletin. (2) If no cracks are found, repeat the inspection required by paragraph (a) of this AD at intervals not to exceed 9,000 landings, in accordance with the service bulletin. (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: 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 FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspections shall be done in accordance with British Aerospace Inspection Service Bulletin 57-41, dated July 26, 1991. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC 20041-0414. 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 March 2, 1993.
92-19-13: 92-19-13 AIRBUS INDUSTRIE: Amendment 39-8371. Docket 92-NM-52-AD. Applicability: Model A320 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent tail strikes and damage to the airplane, accomplish the following: (a) Within 60 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following statement. This may be accomplished by inserting a copy of this AD into the AFM. "Use of automatic landing in configuration 3 (CONF 3) is prohibited." (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 tothe Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) 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. (d) This amendment becomes effective on October 9, 1992.
2019-15-07: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, 737-200, 737-200C, 737-300, 737-400, and 737-500 series airplanes. This AD was prompted by reports of cracks in the frames below the passenger floor. This AD requires repetitive inspections for cracking of the fuselage lower lobe frames, and applicable on-condition actions. This AD also provides an optional terminating action for certain repetitive inspections. The FAA is issuing this AD to address the unsafe condition on these products.