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90-11-11: 90-11-11 BOEING: Amendment 39-6610. Docket No. 90-NM-70-AD. \n\n\tApplicability: Model 747-400 series airplanes, listed in Boeing Alert Service Bulletin 747-35A2067, dated March 15, 1990, certificated in any category. \n\n\tCompliance: Required within the next 500 hours time-in-service after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent disablement of the passenger oxygen system, accomplish the following: \n\n\tA.\tRemove and replace the passenger oxygen/yaw damper module in accordance with Boeing Alert Service Bulletin 747-35A2067, dated March 15, 1990. \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\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager,Seattle Aircraft Certification Office. \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\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6610, AD 90-11-11) becomes effective on June 11, 1990.
77-22-01: 77-22-01 BEECH: Amendment 39-3066 as amended by Amendment 39-3280. Applies to Beech Models 65, A65 and A65-8200 (Serial Numbers L-1, L-2, L-6, LF-7, LF-8 and LC-1 through LC-335), 65-80, 65-A80, 65-A80-8800 and 65-B80 (Serial Numbers LD-1 through LD-512), 65-88 (Serial Numbers LP-1 through LP-26, LP-28 and LP-30 through LP-47), 65-90, 65- A90, B90 and C90 (Serial Numbers LJ-1 through LJ-711), 70 (Serial Numbers LB-1 through LB- 35) and E90 (Serial Numbers LW-1 through LW-212) airplanes certificated in all categories. Compliance: Required as indicated, unless already accomplished. To assure continued structural integrity of the fuselage to the horizontal tail rear spar attachment accomplish the following in accordance with Beechcraft Service Instructions No. 0755-103, Revision II or later approved revisions and in accordance with the additional requirements set forth below: A) Accomplish the following at the next bulkhead inspection required by paragraph "B" of this AD, except that if said paragraph "B" inspection is required in less than 50 hours time in service from the effective date of this AD, accomplish the following within the next 650 hours time in service after the effective date of this AD. NOTE: The intent of the compliance time shown for paragraph "A" is to require compliance at the first paragraph "B" bulkhead inspection that occurs between 50 and 650 hours time in service after the effective date of this AD. 1. Remove the tail cone. 2. Inspect the right and left horizontal stabilizers aft spar attachment to the fuselage station 380.00 bulkhead by loosening all 12 attach bolts and by using feeler gauges, measure the gap between the spar and the attach plates on the bulkhead at each bolt hole. Correct any gap exceeding .020 inches, by complying with instructions in the aforementioned Beechcraft Service Instructions. 3. Remove the aft spar attach bolts one at a time and, using a suitable feeler gauge, check for protrusion of the attach point bushing from the forward surface of the spar. If the forward face of the bushings is not flush with the front surface of the spar, complete removal of the stabilizer, and prior to reinstallation, correct by filing or grinding the bushings flush with the front surface of the spar. 4. Reinstall the stabilizers if removed. B) Within 50 hours time in service after August 19, 1976, for aircraft with 600 hours or more time in service on that date, or upon the accumulation of 650 hours time in service for aircraft having less than 600 hours time in service on August 19, 1976, or within 600 hours time in service after the last inspection in accordance with AD 76-16-04, and at 600 hour intervals thereafter, accomplish the following: 1. Remove the tail cone from the airplane. 2. Using a light and mirror, inspect the forward and aft side of the P/N 50- 440028-65 (F.S. 380.00) bulkhead and all of the bulkhead stiffeners, doublers and other components that attach to the bulkhead for cracks. Pay particular attention to the edges of these parts and the areas around their attaching rivets and bolts. 3. Remove right and left horizontal stabilizers aft spar attach bolts one at a time and inspect the contact areas under the bolt heads and nuts for cracks. 4. If no cracks are detected no further action is required until the next repetitive inspection required by this paragraph is due. 5. If cracks are found, proceed with paragraph C below. C) If cracks are found as a result of any inspection required by this AD, prior to further flight, contact Beech Aircraft Corporation, Commercial Services Operations, Wichita, Kansas 67201, for appropriate instructions and either repair (using acceptable methods, techniques and practices per Advisory Circular 43.13-1A) or replace any cracked P/N 50- 440028-65 fuselage station 380.00 bulkhead and replace any cracked attached stiffener, doubler or other components with new components having part numbers shown in the parts list for Figure 1 in the aforementioned Beechcraft Service Instructions. NOTE: If one or more of the four vertical stiffeners or the doubler defined in Figure 1 of the above-noted Beechcraft Service Instructions as index numbers 2, 10 and 13 require replacement, it is recommended that all four of the vertical stiffeners and the doubler be replaced at the same time with new improved components having the part numbers specified in Paragraph D of this AD. D) The repetitive inspections required by Paragraph "B" of this AD are no longer required after Paragraph "A" of this AD has been complied with and Beechcraft part number 50- 440028-69, -70, -77 and -78 stiffeners and 50-440028-79 doubler have been installed. E) Aircraft found to have the bulkhead or stiffeners cracked may be flown in accordance with FAR 21.197 to a base where the required repair or replacement can be accomplished. F) The time interval between the repetitive bulkhead and stiffener inspections required by Paragraph "B" of this AD, after their initial inspection, can be adjusted up to 50 hours time in service to a maximum interval of 650 hours to allow coordination of these inspections with regular scheduled maintenance. G) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Amendment 39-3066 superseded Amendment 39-2690 (41 F.R. 34583). AD 76-16-04. Amendment 39-3066 became effective November 3, 1977. This amendment 39-3280 becomes effective August 23, 1978.
77-19-05: 77-19-05 GRUMMAN-AMERICAN: Amendment 39-3036. Applies to Models G- 164A, S/N's 1715 thru 1717 and G-164B, S/N's 240B, 242B, 243B, 244B, 246B, 251B, 252B, 253B, 254B, 257B, 258B, 264B, 269B. To prevent hazards associated with defective flying wire terminals, part number AN665- 115L/R, accomplish the following prior to further flight: Remove the AN665-115L/R, terminals and replace them with unused parts received from Grumman American Aviation Corporation. Installation will be in accordance with the aircraft operations and maintenance manual. Parts will be obtained from Grumman American Aviation Corporation, P. O. Box 147, Elmira, New York 14902. The aircraft may be flown in accordance with 21.197 to a location where the AD can be accomplished. This amendment is effective September 22, 1977.
2017-01-08: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 Freighter, -200 and -300 series airplanes; and Airbus Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports of certain hydraulic reservoirs (HRs) becoming depressurized due to air leakage from the HR pressure relief valve (PRV). This AD requires repetitive inspections of the hydraulic fluid levels and nitrogen gas pressure in the HR for each hydraulic circuit, and if necessary, adjustment of the fluid level(s) and nitrogen pressure in affected HRs. We are issuing this AD to address the unsafe condition on these products.
58-10-06: 58-10-06 VICKERS: Applies to All Viscount 700 Series Aircraft. Compliance required as soon as possible but not later than July 31, 1958. A case has occurred during production on the Viscount 700 Series aircraft, of the fracturing of the cranked operating lever (P/N N.69195) of the flap selector switch, Type D.7406. Investigation has established that the fracture is the result of excessive case-hardening of the mild steel lever (P/N N.69195) such that the lever became brittle. The hardened mild steel lever (P/N N.69195) must be replaced by a mild steel lever (P/N N.69195/1) which is identified by a blue spot on the outside face of the lever crank which is visible when positioned in the throttle pedestal. Vickers-Armstrong Aircraft Ltd. PTL No. 188 and Modification Bulletin No. D.2673 cover the same subject. This modification is considered mandatory by the British Air Registration Board. The FAA concurs and considers compliance mandatory.
2024-14-01: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2D15 (Regional Jet Series 705) and CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by a report that torque wrenches used during production installation of bulkhead fittings on the oxygen lines of the flightcrew oxygen mask stowage boxes and adapter fitting on the oxygen pressure gauge were out of calibration, which resulted in a higher torque level setting than required. This AD requires replacement of the affected oxygen line fittings, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
54-01-03: 54-01-03 SIKORSKY: Applies to All Model S-55 Helicopters. Compliance required prior to next flight. Finger fuel strainer installed on all tanks should be removed and inspected to determine whether it incorporates a small disc screen located inside the body of the strainer. This disc screen should be removed if found to be incorporated, since it would tend to restrict fuel flow if it became clogged with foreign material. (Sikorsky Service Information Circular No. 1430-410, dated November 9, 1953, covers the same inspection modification.)
2024-16-14: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by a report of uncommanded movement of the Captain's seat in the forward direction that caused a rapid descent. This AD requires inspections of affected Captain's and First Officer's seats for missing or cracked rocker switch caps and for cracked or nonfunctional switch cover assemblies, a rocker switch cap pull test, marking of the seats, and applicable on-condition actions. This AD also limits the installation of affected seats. The FAA is issuing this AD to address the unsafe condition on these products.
2016-26-09: We are superseding an airworthiness directive (AD) 2016-06-01 for B-N Group Ltd. Models BN-2, BN-2A, BN-2A-2, BN-2A-3, BN-2A-6, BN- 2A-8, BN-2A-9, BN-2A-20, BN-2A-21, BN-2A-26, BN-2A-27, BN-2B-20, BN-2B- 21, BN-2B-26, BN-2B-27, BN-2T-4R, BN-2T, BN2A MK. III, BN2A MK. III-2, and BN2A MK. III-3 (all models on Type Certificate Data Sheets A17EU and A29EU) 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 cracks in the inner shell of certain pitot/static pressure heads. This AD changes model applicability due to errors found in AD 2016-06-01. We are issuing this AD to require actions to address the unsafe condition on these products.
2016-26-04: We are adopting a new airworthiness directive (AD) for Robinson Helicopter Company (Robinson) Model R44, R44 II, and R66 helicopters. This AD requires inspecting the main rotor blade (MRB). This AD was prompted by a determination that some MRBs may have reduced blade thickness due to blending out corrosion. The actions are intended to prevent the unsafe condition on these products.