Results
86-20-06: 86-20-06 BELL HELICOPTER TEXTRON, INC.: Amendment 39-5427. Applies to Bell Helicopter Textron, Inc., Model 214ST helicopters, S/N's 28101 through 28159, and Models 214B and 214B-1, S/N's 28001 through 28070, certificated in any category, equipped with main rotor drag brace assembly P/N 214-010-113-001. Compliance is required as indicated, unless already accomplished. (a) To prevent failure of the M/R drag brace assembly, P/N 214-010-113-001, on the Model 214ST helicopter, replace it with M/R drag' brace assembly, P/N 214-010-113-105, within the next 50 hours' time in service or within 30 days after the effective date of this AD, whichever comes first. (b) To prevent failure of the M/R drag brace assembly, P/N 214-010-113-001 on the Model 214B and 214B-1 helicopters, replace it with M/R drag brace assembly, P/N 214-010-113- 107, within the next 50 hours' time in service or within 30 days after the effective date of this AD, whichever comes first. (c) An alternate method of compliance which provides an equivalent level of safety with this AD may be used when approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. This amendment becomes effective October 18, 1986.
98-13-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This AD requires accomplishing a leakage check of all lavatory water tube/hose connections, and correcting the installation of these connections if leakage is found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent water leakage from the lavatory water duct system, which could collect in the fuselage, freeze in cold weather conditions, and cause the rudder control system to jam.
89-17-05: 89-17-05 BELL HELICOPTER TEXTRON, INC.: Amendment 39-6276. Applicability: Model 222, 222B, and 222U helicopters, certificated in any category, with horizontal stabilizer assembly, Part Number (P/N) 222-035-250-101, -103, or -105, installed. (Docket No. 89-ASW-16) Compliance: Required within the next 50 hours' time in service for horizontal stabilizer assemblies with more than 2,100 hours' time in service; compliance for horizontal stabilizers with less than 2,100 hours' time in service is required prior to the accumulation of 2,150 hours' time in service; and both thereafter at intervals not to exceed 300 hours' time in service. To prevent failure of the horizontal stabilizer assembly, which could result in loss of the helicopter, accomplish the following: (a) Perform the Part "A" of the "Accomplishment Instructions" of BHTI Alert Service Bulletin (ASB) No. 222-89-53, dated March 20, 1989, for the Model 222 and 222B; or ASB No. 222U-89-27, dated March 20,1989, for the Model 222U. (b) If a crack is detected, remove and replace with a serviceable horizontal stabilizer assembly prior to further flight. (c) The requirements of this AD do not apply if horizontal stabilizer assembly P/N 222-035-250-107 is installed for the Model 222 or P/N 222-035-250-109 is installed for the Models 222B and 222U. (d) An alternate method of compliance which provides an equivalent level of safety, may be approved by the Manager, Rotorcraft Certification Office, Southwest Region, Federal Aviation Administration, Fort Worth, Texas 76193-0170. The inspection procedures shall be done in accordance with Part "A" of the "Accomplishment Instructions" of BHTI Alert Service Bulletin (ASB) No. 222-89-53, dated March 20, 1989, for the Model 222 and 222B; or ASB No. 222U-89-27, dated March 20, 1989, for the Model 222U. This incorporation by reference of ASB No 222-89-53 and ASB No. 222U-89-27, both dated March 20, 1989, 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 Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101. Copies may be inspected at the Office of the Assistant Chief Counsel, Southwest Region, 4400 Blue Mound Road, Room 158, Building 3B, Fort Worth, Texas, between 8 a.m. and 4 p.m. weekdays, except Federal holidays, or at the Office of the Federal Register, 1100 L Street, N.W., Room 8301, Washington, D.C. This amendment (39-6276, AD 89-17-05) becomes effective on August 28, 1989.
2019-05-08: We are superseding Airworthiness Directive (AD) 2015-12-08, which applied to all Airbus SAS Model A318 and A319 series airplanes and all Model A320-211, A320-212, A320-214, A320-231, A320-232, A320- 233, A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321- 231, and A321-232 airplanes. AD 2015-12-08 required an inspection to determine the batch number or installation date of the oxygen pipe assembly that is installed at the end of the right-hand crew distribution line, and replacement of the pipe if necessary. This AD revises the applicability to include additional airplane models and additional pipes to be replaced if necessary. This AD was prompted by further investigation that determined that affected oxygen pipes may have been installed on more airplanes than initially identified. We are issuing this AD to address the unsafe condition on these products.
99-22-15: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that requires repetitive inspections of the left and right roll spoiler actuators to check for signs of leakage and deformation of the housing, repetitive inspections of the gap between the left roll spoiler actuator housing cap and the actuator housing, repetitive torque checks of the left roll spoiler actuator housing cap attachment screws, 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 oil leakage from the roll spoiler actuators, which could result in incorrect roll spoiler operation and reduced controllability of the airplane.
68-17-03: 68-17-03 PILATUS: Amendment 39-634. Applies to all Model PC-6 Series Airplanes. Compliance required as indicated. To detect cracks in the rudder end rib, accomplish the following: (a) Within the next 50 hours time in service after the effective date of this Airworthiness Directive and thereafter at intervals not to exceed 50 hours time in service from the last inspection, inspect the rudder end rib P/N 6302.27 for cracks with the aid of a mirror. (b) If cracks are detected during any inspection prescribed in paragraph (a), replace the rudder end rib before further flight with a modified rudder end rib, P/N 6302.26 Pos. 2; channel reinforcement, P/N 113.40.06.002, and torque tube, P/N 113/40.06.003, in accordance with Pilatus Service Bulletin No. 80, dated April, 1968, or later Swiss Federal Air Office approved Revision or FAA approved equivalent. (c) The repetitive inspections required by paragraph (a) may be discontinued after the modified rudder end rib has been installed. This amendment becomes effective August 19, 1968.
86-07-09 R1: 86-07-09 R1 BOEING: Amendment 39-5280 as amended by Amendment 39-5309. Applies to all Boeing Model 757 and 767 airplanes, certificated in any category. To ensure the integrity of the cargo compartment smoke detection system, accomplish the following within 30 days after the effective date of this AD, unless already accomplished: \n\n\tA.\tReplace the lamps in the four Autronics Corporation Model 2156-204 cargo compartment smoke detectors and install placards in accordance with Autronics Service Bulletin 2156204-26-01, dated April 14, 1986, or later FAA-approved revision. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. \n\n\tAll persons affected by this AD who have not already received the above specified service bulletin from the manufacturer may obtain copies upon request from the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. The service bulletin may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tAmendment 39-5280 became effective April 22, 1986. \n\tThis Amendment 39-5309 becomes effective May 20, 1986.
85-16-06: 85-16-06 MCDONNELL DOUGLAS AND AIRBUS INDUSTRIE: Amendment 39-5112. Applies to McDonnell Douglas Model DC-10-15, -30, and KC-10A (Military) series airplanes, and CF6-50C powered Airbus Industrie Model A-300 series airplanes. Compliance is required as indicated.\n\n\tTo prevent failure of the fuel flowmeter tube assembly, accomplish the following, unless already accomplished:\n\n\tA.\tWithin the next 1000 flight hours after the effective date of this AD, inspect the fuel flowmeter tube assemblies in accordance with McDonnell Douglas Alert Service Bulletin A73-20, dated January 7, 1985, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region; or Airbus Industrie Service Bulletin A300-73-007 (associated with modification 5912), as appropriate. Perform the inspection every 1000 flight hours until paragraph B., below, is accomplished. If any cracks are found, accomplish the requirements of paragraph B. before any further revenue flight.\n\n\tB.\tWithin one year after the effective date of this AD, install the fuel flowmeter tube assembly P/N-ASLO538-503 in accordance with McDonnell Douglas DC-10 Alert Service Bulletin A73-20, dated January 7, 1985, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.\n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.\n\n\tD.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.\n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750(54-60). These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California.\n\n\tThis amendment becomes effective September 6, 1985.
2009-04-03: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (RRC) AE 3007A1E and AE 1107C turbofan/ turboshaft engines. This AD requires removal from service of certain 2nd stage, 3rd stage, and 4th stage compressor wheels, compressor cone shaft assemblies, and 1st to 2nd-stage turbine spacers at new, reduced, published life limits. This AD results from RRC applying an updated lifing methodology to the affected parts. We are issuing this AD to prevent low-cycle-fatigue failure of the parts listed in Table 1 of this AD, which could result in an uncontained engine failure and damage to the aircraft.
98-17-12: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4100 series airplanes, that requires an eddy current conductivity test to measure the conductivity of the upper splice plate of the wing, and follow-on actions, 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 correct corrosion of the upper splice plate of the wing, which could result in reduced structural integrity of the airplane.