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81-17-04: 81-17-04 HUGHES HELICOPTERS: Amendment 39-4185. Applies to Model 269 helicopters, all models, and TH-55s, certified in all categories, incorporating P/Ns 269A5179 or 269A5179-3 Drive Shaft Coupling Assemblies, and those helicopters incorporating the improved P/N 269A5194 Ring Gear Carrier Assembly. Compliance required as indicated, unless already accomplished. To prevent failure of the main transmission, accomplish the following: (a) For main rotor ring gear driveshaft assemblies, P/N 269A5179 or 269A5179-3: (1) Within 100 hours' additional time in service from the effective date of this AD, or 600 hours total time in service, whichever occurs later, inspect shaft and coupling assembly lower bearing bore and fasteners for evidence of cracks, fretting, or other stress risers, in accordance with Part IIA and IIB of Hughes Service Notice No. N-179 dated July 17, 1981. If cracks, fretting or stress risers are found, replace with P/N 269A5194 assembly reworked per Hughes Notice No. N142.1, prior to further flight. (2) Within 100 hours' additional time in service from the effective date of this AD, or 2,000 hours total time in service for 269C aircraft or 2,500 hours total time in service for 269A/A-1/B/TH-55A aircraft, whichever occurs later, remove and replace shaft and coupling assembly with 269A5194 ring gear carrier assembly reworked per Hughes Notice No. N-142.1 dated May 31, 1977. (b) For main rotor ring gear drive shaft assemblies, P/N 269A5179 not modified per Hughes Notice No. N-114-3 dated September 19, 1977: Within the next 25 hours' additional time in service after the effective date of this AD, or 400 hours' total time in service, or 300 hours since the last inspection performed per paragraph (a) of AD 77-21-10, whichever occurs later, and at intervals not to exceed 300 hours' time in service thereafter, perform a close visual inspection and penetrant inspection of shaft and coupling fastener area per Part IIB ofHughes Notice No. N-179, for fretting, cracking, or other stress risers. If cracks, fretting or stress risers are found, replace with P/N 269A5194 assembly reworked per Hughes Notice No. N-142.1, prior to further flight. (c) For main rotor ring gear drive shaft assemblies, P/N 269A5179 previously modified per Hughes Notice No. N-114.3 at or before the accumulation of 1000 hours' additional time in service since modification per Hughes Notice N-114.3, and at intervals not to exceed 500 hours' time in service thereafter, accomplish the visual and penetrant inspections of the fastener areas, as described in paragraph (b), above. (d) The recurring inspections of paragraphs (b) and (c), above, may be discontinued when P/N 269A5194 assemblies are installed. The service life limit on P/N 269A5194 is 6,000 hours. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections or modificationsrequired by this AD. (f) Alternative 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. 552(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Hughes Helicopters, Inc., Centinela and Teale Street, Culver City, California 90230. These documents may also be examined at FAA Western Region Office, 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 WesternRegion Office. This supersedes Amendment 39-3060 (42 FR 55882), AD 77-21-10. This amendment becomes effective August 24, 1981.
96-10-11: This amendment supersedes an existing airworthiness directive (AD), applicable to McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that currently requires certain inspections and structural modifications. This amendment requires additional inspections and structural modifications. This amendment is prompted by an evaluation conducted by the Airworthiness Assurance Working Group, which identified additional inspections and structural modifications for mandatory action. The actions specified by this AD are intended to prevent degradation in the structural capabilities of the affected airplanes.
47-34-01: 47-34-01 BEECH: (Was Mandatory Note 2 of AD-765-1.) Applies to D18C and D18S Airplanes Having Inside Filler Neck on 80-Gallon Nose Fuel Tanks. Compliance required prior to November 1, 1947. To prevent flight with the nose tank fuel cap off or unlocked, and to eliminate a fire hazard in the event of fuel tank or cap leakage, the following items are to be accomplished: (a) On tanks equipped with a cam type filler cap, install new filler neck, filler neck gasket, and screws suitable for use with the expansion type filler cap. (Tanks having an expansion type filler cap previously installed do not require this change.) (b) Replace the cam or expansion type filler cap with revised expansion type filler cap assembly, Beech P/N 404-189676. (c) Install a safety guard, Beech P/N 404-189689, on forward side of nose door cover plate in a manner to prevent closing the nose compartment door when the filler cap is not in place or locked. (d) Drill a 1/4-inch diameter hole in the lower skin of the nose compartment just forward of bulkhead No. 2 at the centerline of the airplane to provide drainage for the forward compartment under the fuel tank. (Beech Service Bulletin D18-49 covers this same subject.)
96-10-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that requires inspection to detect damage of a wire bundle and clamp that are located in the electronic/electrical (E/E) equipment bay, and repair of the damaged wire bundle. That action also requires replacement of the existing steel clamp with a nylon clamp, and rearrangement of the clamp installation. This amendment is prompted by a report of fire in the E/E equipment bay due to electrical arcing caused by chafing of a wire bundle. The actions specified by this AD are intended to prevent chafing of a wire bundle that could cause short circuiting of the wire bundle, and could result in smoke and fire in the E/E equipment bay.
79-11-05 R1: 79-11-05 R1 MOONEY: Amendment 39-3480 as amended by Amendment 39-4050. Applies to Mooney M-18L S/N's 2 and up, M-18C S/N's 201 and up, M-18LA S/N's 100 through 200, M- 18C55 S/N's 323 and up certificated in all categories. Compliance required as indicated: To prevent failure of the vertical fin spar in flight due to wood deterioration and to detect other wood and glue joint deterioration in the wood wing and wood empennage structure, accomplish the following inspections and checks or approved equivalents within the next 30 days after the effective date of this AD, unless already accomplished within the last 35 months, and thereafter at intervals not to exceed 36 months from the last inspection: (1) Remove all fabric from the horizontal and vertical stabilizers. Inspect all wood and glue joints including attachment of leading edge skin to main spar for deterioration. (2) At center junction of stabilizer spar and fin inspect glue joint between attach blocks and stabilizer spar for deterioration and inspect spar and blocks for cracks. Inspect fin and spar for cracks at attachment bolts. (3) Inspect rear bulkhead of the stabilizer for cracks and looseness in the area of the stabilizer attachments. Inspect attachment blocks for cracks or looseness at spar. (4) Remove wing fabric locally in area of aileron hinges and at inboard corner of aileron cutout. Check condition of wood and glue joints. If evidence of deterioration is found, remove fabric further as necessary for complete examination of forward area of wing trailing edge. Check attachment of wing trailing edge in aileron area for looseness. (5) Ensure that all drain holes in empennage and wing are clear. (6) If any defects set forth in paragraphs (1), (2), (3), or (4) above are detected, repair in accordance with FAA Advisory Circular AC 43.13-1A or approved equivalent or replace with an identical new part or equivalent prior to further flight. Equivalent repairs, inspections, and/orparts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (7) A borescope, utilizing FAA approved permanent access holes, is considered an approved equivalent means of inspection only for the vertical and horizontal stabilizers, when satisfying the requirements of paragraphs (1), (2), and (3). The borescope inspection shall be accomplished within the next 30 days after the effective date of this AD, unless already accomplished within the last 11 months, and thereafter at intervals not to exceed 12 months from the last inspection. (8) Upon submission of substantiating data by an owner or operator, through an FAA maintenance inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection time in this Airworthiness Directive. Amendment 39-3480 was effective June 5, 1979. This amendment 39-4050 is effective April 1, 1981.
2022-03-05: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-8F and 747-8 series airplanes and Model 777 airplanes. This AD was prompted by a determination that radio altimeters cannot be relied upon to perform their intended function if they experience interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band), and a recent determination that this interference may affect multiple airplane systems using radio altimeter data, including the pitch control laws, including those that provide tail strike protection, regardless of the approach type or weather. This AD requires revising the limitations section of the existing airplane flight manual (AFM) to incorporate limitations prohibiting dispatching or releasing to airports, and approaches or landings on runways, when in the presence of 5G C-Band interference as identified by Notices to Air Missions (NOTAMs). The FAA is issuing this AD to address the unsafe condition on these products.
82-20-06 R1: 82-20-06 R1 BOEING AIRPLANE COMPANY, VERTOL DIVISION: Amendment 39- 4467 as revised by Telegram issued December 9, 1983, and Amendment 39-4825. Applies to Boeing Vertol Model 234 series helicopters certificated in all categories equipped with main rotor hubs, P/N's 114R2050-17, -18, -23, and -24. Compliance is required as indicated unless already accomplished. To inspect the aft main rotor hub for cracks, within the next 60 hours time in service from the effective date of this AD or before the accumulation of 700 hours time in service, whichever comes later, and to inspect the forward main rotor hub for cracks, within the next 25 hours time in service from the effective date of this AD revision or before the accumulation of 450 hours time in service, whichever comes later, accomplish the following. (a) Remove the hub retaining nut and washer and inspect for a height difference between the top of the shaft spline up to the rotor hub upper surface. The hub upper surfacemust be a minimum of 0.015 inches above the rotorshaft spline. (b) Remove the rotor hubs from the aircraft and conduct an eddy current inspection for cracks on the bottom surface of the hub from the splines to a distance one inch out from the splines. Inspect the lower hub surface described above and the splined area from the lower surface upward for 1.75 inches using dye penetrant. (c) Ensure that the washer between the main rotor shaft nut and main rotor hub is installed and torque the main rotor hub nut to the manufacturer's specifications as shown in the Boeing Vertol 234 Maintenance Manual. (d) After the initial inspections of paragraphs (a), (b) and (c), repeat the main rotor hub inspections of paragraphs (b) and (c) in intervals not to exceed 125 hours additional time in service from the last inspection. (e) Remove from service hubs having cracks and replace with a serviceable part prior to further flight. (f) Boeing Vertol Service Bulletin Number 234-65-1026 applies to these inspections. (g) An equivalent method of compliance with this AD may be approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York 11581. Amendment 39-4467 became effective October 15, 1982. The telegraphic airworthiness revision issued on December 9, 1983, became effective upon receipt. This Amendment 39-4825 becomes effective March 16, 1984, as to all persons except those persons to whom it was made immediately effective by telegraphic AD No. T82-20-06 R1 issued December 9, 1983, which contained the amendment.
2021-26-21: The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-24 airplanes. This AD was prompted by 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 insufficient performance of the fuel drain system that could lead to fire and damage of the airplane. This AD requires modifying the fuel drain pipe routing and installing a drain mast. The FAA is issuing this AD to address the unsafe condition on these products.
96-10-04: This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal, Inc. LTS101-600 series turboshaft engines, that requires installation of an improved design fuel control. This amendment is prompted by reports of fuel control bearings failing prior to the recommended overhaul period. The actions specified by this AD are intended to prevent a fuel control failure, which could result in an uncommanded increase or decrease in engine power.
91-01-04: 91-01-04 GENERAL ELECTRIC COMPANY: Amendment 39-6847. Docket No. 90-ANE- 12-AD. Applicability: General Electric Company (GE) CF6-6, -45, -50, -80A series turbofan engines installed on, but not limited to, McDonnell-Douglas DC-10, Boeing 747, Boeing 767, Airbus A310, and Airbus A300 aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent stage 1 fan disk post failure, which could result in multiple fan blade release, engine power loss, and uncontained engine failure, accomplish the following: (a) Ultrasonic inspect and fluorescent penetrant inspect (FPI) the stage 1 fan disk dovetail post for cracks in accordance with the applicable Accomplishment Instructions of Appendix I, at the next fan disk exposure after the effective date of this AD. Thereafter, reinspect in accordance with Appendix I at each fan disk exposure, but not to exceed 7,500 cycles since last inspection (CSLI). (b) Parts found cracked during inspection in accordance with paragraph (a) of this AD, must be removed from service prior to further flight. (c) For the purpose of this AD, fan disk exposure is defined as any engine maintenance action where the fan disk is exposed to the piece part level and the dovetail pressure face coating is stripped. (d) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (e) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803. All persons affected by this directive who have not already received the appropriate service documents from the manufacturermay obtain copies upon request to the General Electric Company, Technical Publications Department, 1 Neumann Way, Cincinnati, Ohio 45215. These documents may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment (39-6847, AD 91-01-04) becomes effective on January 22, 1991. APPENDIX I PART A: CF6-50, -45 Series Engines 1.) Reference: CF6-50/-45 Shop Manual Document No. GEK-50481. 2.) Accomplishment Instructions: Inspect the stage 1 fan disk by the contact-ultrasonic and fluorescent-penetrant inspections in Chapter 72-21-03, FAN ROTOR DISK, STAGE 1 INSPECTION, of the reference shop manual. NOTE: Information concerning this inspection can be found in GE SB NO. 72- 999. PART B: CF6-6 Series Engines 1.) Reference: CF6-6 Shop Manual Document No. GEK-9266. 2.) Accomplishment Instructions: Inspect the stage 1 fan disk by the contact ultrasonic and fluorescent-penetrant inspections in Chapter 72-21-03, FAN ROTOR DISK, STAGE 1 - INSPECTION of the reference shop manual. NOTE: Information concerning this inspection can be found in GE SB No. 72- 965. PART C: CF6-80A Series Engines 1.) CF6-80A Engine Manual Document No. GEK-72501. 2.) Accomplishment Instructions: Inspect the stage 1 fan disk by contact-ultrasonic and fluorescent-penetrant inspections in Chapter 72-21-03, FAN ROTOR DISK, STAGE 1 INSPECTION, of the reference engine manual. NOTE: Information concerning this inspection can be found in GE SB No. 72- 575.