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2022-03-02: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and - 402 airplanes. This AD was prompted by reports of a possible hard contact between the #2 top high level sensor (HLS) terminal screw head and the #6 outer wing fuel access panel stiffener flange. This AD requires removing and replacing or reworking the #6 outer wing fuel access panel assembly. The FAA is issuing this AD to address the unsafe condition on these products.
97-10-15: This amendment adopts a new airworthiness directive (AD), applicable to Sikorsky Aircraft-manufactured Model S-64F helicopters, that requires inspections, and replacement, if necessary, of the main gearbox second stage lower planetary plate (plate). This amendment is prompted by two incidents in which the plate was found cracked. The actions specified by this AD are intended to prevent failure of the plate due to fatigue cracking, which could lead to failure of the main gearbox and subsequent loss of control of the helicopter.
2022-02-04: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS350B, AS350B2, AS350B3, and AS350BA helicopters. This AD was prompted by a report that a modification of the electrical wiring of the hydraulic system was wrongly embodied on certain helicopters, and a wiring non-conformity caused the solenoid of the tail rotor (TR) load compensator to de-energize when the ''HYD'' cut-off switch was activated. This AD requires installing a placard in the cockpit, in full view of the pilots; a functional check of the main rotor (MR) and TR servo actuator solenoids, and corrective actions (modification) if necessary; a modification (unless already done); and, after corrective actions or modification, optional removal of the placard, 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.
81-08-04: 81-08-04 PURITAN-BENNETT AERO SYSTEMS COMPANY: Amendment 39-4092. Applies to Puritan-Bennett Aero Systems Company oxygen masks P/N 174039, 174010-01, 174010-03, and ZMR100 series as listed below. NOTE: Masks manufactured without serial numbers are not affected by this AD. S/N for P/N 174039 0001 through 0012 S/N for P/N 174010-01 and 174010-03 00100 through 00144 146, 147, 149, 00150 through 00194 195 through 259 261 through 273 275 through 292 294 through 390 S/N for P/N ZMR100 series 6603 through 7234 Compliance required as indicated, unless already accomplished. To prevent the regulator inlet valve from causing either leakage or positive pressure within the facecone, accomplish the following: (a) Within 120 calendar days from the effective date of this Airworthiness Directive, remove diaphragm assembly P/N F334-1001-1 and install diaphragm assembly P/N F334-1001-1 modified to include diaphragm and plate assembly P/N F334-1003-1, Revision E. (b) After modification per paragraph (a) of this AD, permanently mark letter "M" at the end of or beneath the mask serial number. This serial number is located under the face cushion on the left-hand side of the hardshell on the 174039 and ZMR100 series masks, and on the back surface of the head harness on the 174010-01 and 174010-03 masks. (c) The modified diaphragm replacement of paragraph (a) of this AD shall be accomplished by returning the mask to Puritan-Bennett Aero Systems Company, 111 Penn Street, El Segundo, California 90245. However, this replacement in the ZMR100 series masks listed below may be accomplished in the field in accordance with the following Puritan-Bennett Aero System ATA Component Maintenance Manuals: 35-10-25 for the ZMR160 mask 35-10-27 for the ZMR129 mask 35-10-28 for the ZMR129-1 mask 35-10-29 for the ZMR118 mask NOTE: Puritan-Bennett Aero Systems Company Service Bulletin No. 1, dated April 15, 1980, pertains to the subject of this Airworthiness Directive. Alternate inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 553(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Puritan-Bennett Aero Systems Company, 111 Penn Street, El Segundo, California 90245. These documents may also be examined at FAA Western Region Office, Room 6W14, 15000 Aviation Boulevard, Hawthorne, California 90261 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its headquarters in Washington, D.C. and at FAA Western Region Office. This AD supersedes Amendment 39-4017, (46 FR 3495) AD 81-02-03, as amended by Amendment 39-4066 (46 FR 16888). This amendment becomes effective April 23, 1981.
2010-09-09: 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: A failure of fuel pump sealing, due to possible incorrect maintenance procedures and subsequent testing, caused a fuel leakage into the main landing gear bay. Presence of fuel vapours in that zone creates a risk of fire due to presence of potential ignition sources such as electrical equipment and connectors. We are issuing this AD to require actions to correct the unsafe condition on these products.
97-10-16: This amendment supersedes an existing airworthiness directive (AD), applicable to Hiller Aircraft Corporation Model UH-12, UH-12A, UH-12B, UH-12C, UH-12D, UH-12E, CH-112, H-23A, H-23B, H-23C, H-23D, H-23F, HTE-1, HTE-2, and OH-23G helicopters, and UH-12D and UH-12E helicopters converted to turbine engine power in accordance with Supplemental Type Certificate (STC) No.'s SH177WE and SH178WE, having a certain control rotor blade spar tube (blade spar tube) or cuff installed, that currently requires inspections of the blade spar tube and cuff for cracks, and repair or replacement as necessary. This amendment requires inspections of the blade spar tube and cuff for corrosion or cracks, or elongation, corrosion, burrs, pitting or fretting of the bolt holes, and repair as necessary, and defines specific intervals in which the inspections must be performed. This amendment is prompted by analyses that show that the amount of calendar time that elapses between the current repetitiveinspections may allow corrosion to develop. The actions specified by this AD are intended to prevent separation of the control rotor blade assembly and subsequent loss of control of the helicopter.
81-03-51: 81-03-51 DEHAVILLAND: Amendment 39-4513. Applies to model DHC-7 airplanes serial numbers 3 through 36 certificated in all categories that have flap screw jacks 2 and 3, left and right hand, part numbers 24020-11, -111, -or -115; or 24040-11, -111, or -115 and are fitted with lock nuts, part number MS9952-08. To prevent possible damage to the flap system due to the disengagement of the lock nut, accomplish the following within the next 25 hours time in service after the effective date of this AD, unless already accomplished. 1. Inspect the flap screw jack tracks 2 and 3, Menasco part numbers 24020-11, -111 or -115 and 24040-11, -111 or -115 for correct locking feature of lock washer against the dome nut. To ensure the nuts are correctly installed, ensure that the cup lock washer P/N MS9952-08 has been tapped into groove of the lock nut P/N 24156-1 (Typical 6 places). 2. Lubricate the aft end bearing (P/N AD50991) lightly with grease P/N MIL-G- 23877 or equivalent. 3.Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA Northwest Mountain Region. 4. Special 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. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). This amendment becomes effective December 21, 1982, and was effective earlier to those recipients of telegraphic AD T81-03-51, dated January 23, 1981.
88-25-04: 88-25-04 CESSNA: Amendment 39-6081. Applies to Models T210L, T210M, T210N, P210N, and T303 (all serial numbers) airplanes certificated in any category, that are equipped with Slick Aircraft Products Division, Unison Industries, Inc., Model 6220 or 6224 pressurized magnetos. Compliance: Required as indicated, unless already accomplished. To preclude magneto moisture contamination, which could result in dual magneto failure, engine stoppage, and forced landing, accomplish the following: (a) Within the next 50 hours time-in-service (TIS) after the effective date of this AD, accomplish the following: (1) Revise the "NORMAL PROCEDURES" section of the Airplane Flight Manual (AFM) or the airplane Pilot's Operating Handbook (POH), by inserting the AFM/POH Supplement, dated April 1, 1988, provided in Appendix 1 of this AD. (2) Fabricate and install on the instrument panel in clear view of the pilot a placard with letters not less than 1/10 inches in heightwith the following wording: "PRIOR TO EACH FLIGHT, CONDUCT MAGNETO CHECKS IN ACCORDANCE WITH AFM/POH SUPPLEMENT DATED APRIL 1, 1988." and operate the airplane accordingly. (3) The requirements of paragraphs (a)(1) and (a)(2) of this AD may be accomplished by the owner/operator of any airplane owned or operated by him. The person accomplishing these actions must make the appropriate airplane maintenance record entry per FAR 43.9 and 91.173. (b) Within the next 50 hours time-in-service after the effective date of this AD, inspect the airplanes in accordance with Paragraph III of Slick Aircraft Products Division Service Bulletin SB 1-88, dated April 10, 1988, and: (1) For airplanes operating for compensation or hire, at intervals not to exceed 100 hours TIS after the initial inspection, inspect the Model 6220 or 6224, as applicable, pressurized magnetos in accordance with paragraph III of Slick Aircraft Products Division Service Bulletin SB 1-88, dated April 10,1988. Prior to further flight repair any defects found in accordance with the instructions contained in the above referenced service bulletin. (2) For airplanes operating under FAR 91, after the initial inspection, at each annual inspection, inspect the Model 6220 or 6224, as applicable, pressurized magnetos in accordance with paragraph III of Slick Aircraft Products Division Service Bulletin SB 1-88, dated April 10, 1988. Prior to further flight repair any defects found in accordance with the instructions contained in the above referenced service bulletin. (c) Airplanes may be flown in accordance with provisions of FAR 21.197 to a base where the requirements of this AD may be accomplished. (d) The 100 hour TIS repetitive inspection interval specified in paragraph (b) of this AD may be extended up to an additional 10 hours TIS to allow compliance with previously scheduled maintenance. (e) An equivalent means of compliance with the requirements of this AD maybe used, if approved by the Manager, Chicago Aircraft Certification Office, ACE-115C, Federal Aviation Administration, 2300 East Devon Avenue, Des Plaines, Illinois 60018. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Slick Aircraft Products Division, Unison Industries, Inc., 530 Blackhawk Park Avenue, Rockford, Illinois 61108 or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-6081, becomes effective on December 26, 1988. APPENDIX 1 FAA APPROVED SUPPLEMENT TO THE PILOT'S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL FOR CESSNA MODELS T210L, T210M, T210N, P210N, AND T303 SERIES AIRCRAFT REG. NO. SER. NO. This supplement must be attached to the FAA Approved Airplane Flight Manual on which Slick Aircraft Products Division, Unison Industries, Inc., Models 6220 or 6224 pressurized magnetos are installed. The information contained herein supplements or supersedes the basic manual only in those areas listed. For limitations, procedures, and performance information not contained in this supplement, consult the basic Airplane Flight Manual. FAA APPROVED: Original signed by W. F. Horn, Manager Chicago Aircraft Certification Office, FAA Central Region DATE: April 1, 1988 AFMS for Cessna T210L, T210M, T210N, P210N, and T303 Series Aircraft SECTION II. Limitations No change. SECTION III. Emergency Procedures. No change. SECTION IV. Normal Operating Procedures. BEFORE TAKEOFF Perform a magneto check of each engine at 1,700 RPM as follows: move ignition switch first to R position and note RPM. Next, move switch back to BOTH, to clear the other set of plugs. Then, move switch to the L position, note RPM and return the switch to the BOTH position. RPM drop should not exceed 150 RPM on either magneto or show greater than 50 RPM differential between magnetos. If there is doubt concerning operation of the ignition system, RPM checks at higher engine speed will usually confirm whether a deficiency exists. CAUTION Many non-ignition system factors influence engine performance during a magneto check, and the replacement or repair of ignition components may not remedy problems in all cases. After verifying that all non-ignition system related causes for problems have been explored, proceed with the inspection procedures as stated below. If the magneto check exceeds either of the above limits, both magnetos must be disassembled and inspected in accordance with Section III, 100- hour inspection of Slick Aircraft Products Division, Unison Industries, Inc., SB 1-88, dated April 10, 1988, or FAA approved equivalent. An absence of RPM drop may be an indication of faulty grounding of one side of the ignition system or should be cause for suspicion that the magneto timing is set in advance ofthe setting specified. Check ignition ground and magneto timing. FAA APPROVED DATE: April 1, 1988
2011-26-05: We are superseding an existing airworthiness directive (AD) that applies to certain Bombardier, Inc. Model DHC-8-300 series airplanes. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Several cases of aileron terminal quadrant support brackets that were manufactured using sheet metal have been found cracked on DHC-8 Series 300 aircraft. Investigation revealed that the failure of the support bracket was due to fatigue. Failure of the aileron terminal quadrant support bracket could result in an adverse reduction of aircraft roll control. * * * * * These conditions could result in loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2011-25-03: We are adopting a new airworthiness directive (AD) for all Learjet Inc. Model 45 airplanes. This AD was prompted by a report of the potential for fatigue cracking of the end cap of the main landing gear (MLG) prior to the published life limitation. This AD requires revising the maintenance program to incorporate life limits for the MLG actuator end cap. We are issuing this AD to prevent fatigue cracking of the end cap of the MLG, which could result in the failure of the MLG actuator upon landing, and failure of the MLG to extend or retract during flight.