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80-26-01: 80-26-01 ROCKWELL INTERNATIONAL: Amendment 39-3988. Applies to Model NA265-40 Series, Serial numbers 282-1 through 282-137, and -60 Series, Serial Numbers 306-1 through 306-64, 306-68, 306-71 through 306-103 airplanes certificated in all categories, not modified in accordance with Life Extension Modification per North American Rockwell Drawing 306-053010 or Service Kit SK 13808-40. Compliance required as indicated, unless already accomplished. To prevent inadvertent cabin depressurization accomplish the following: (a) On aircraft with 2,000 or more hours' total time in service, within the next 600 hours' additional time in service or within the next 12 months from the effective date of this AD, whichever occurs first. (1) Gain access and conduct a close visual inspection of the fuselage structure below the cabin entrance door and adjacent areas in accordance with "Modification Instructions 1 through 3" of Sabreliner Service Bulletin No. 56 dated September 22, 1980. Access is gained by modification in accordance with Service Kit SK 13808-10. (2) If no cracks are detected, repeat the inspections required in paragraph (a)(1) of this AD at intervals not to exceed 600 hours' time in service since the last such inspection. (3) If cracks are detected which are less than one inch long in the outboard bays only, repair per Sabreliner Service Bulletin Repeat the inspections required by paragraph (a)(1) of this AD at intervals not to exceed 600 hours' time in service since the last such inspection. (4) If cracks are detected which are less than one inch long in the inboard bays or inboard and outboard bays, repair per Sabreliner Service Bulletin No. 56, dated September 22, 1980, and accomplish Service Kit SK 13808-30. Repeat the inspections required by paragraph (a)(1) of this AD at intervals not to exceed 600 hours' time in service since the last such inspection. (5) If cracks are detected which are one inch or longer, repairin a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region, or by the installation of Service Kit SK 13808-40. The installation of Service Kit SK 13808-40 terminates the inspections required by this AD. For other repairs, unless specifically authorized by the Chief, Engineering and Manufacturing Branch, FAA Western Region, repeat the inspections required by paragraph (a)(1) of this AD at intervals not to exceed 600 hours' time in service since the last such inspection. (b) 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 required by this AD. (c) 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. This amendment becomes effective January 19, 1981.
80-23-01: 80-23-01 ROLLS-ROYCE, LTD.: Amendment 39-3966. Applies to Rolls-Royce, Ltd., DART 506, 510, 511, 514, 515, 520, 525, 526, 527, 528, 529, 530, 531, 532, 533, 534, 535, 536, 542, 543, 550, and all variants turboprop engines. Compliance required as indicated, unless already accomplished. To preclude possible frettage fatigue failure of low pressure impellers, inspect for cracks and modify or remove from service all low pressure impellers installed in the following DART model engines: 1. DART 506, 510, 511, 514, 515, and their variants; and DART 520, 525, 526, 527, 528, 529, 530, 531, 532, 533, 534, 535, 536, 550, and all variants of these marks equipped with a low pressure impeller which has run previously in a DART 506, 510, 511, 514, 515, or any variant of these engines. a. After November 30, 1980, no low pressure impeller may exceed 5,000 flight cycles since new without inspection for cracks and incorporation of Modification 1732, in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service low pressure impellers having crack indications. b. After November 30, 1980, prior to further flight, all low pressure impellers for which the flight cycles since new cannot be positively established, must be inspected and modified to incorporate Modification 1732; in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service, low pressure impellers having crack indications. c. Remove from service not later than May 31, 1981, all low pressure impellers which have not been inspected for cracks and do not have modification 1732 incorporated. 2. DART 520, 525, 526, 527, 528, 529, 530, 531, 532, 533, 534, 535, 536, 550, and their variants equipped with a low pressure impeller which has not run previously in a DART 506, 510, 511, 514, 515 or any variant of these engines. a. After December 31, 1982, no low pressure impeller may exceed 9,000 flight cycles since new without inspection for cracks and incorporation of Modification 1732, in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service low pressure impellers having crack indications. b. After December 31, 1982, prior to further flight, all low pressure impellers for which the flight cycles since new cannot be positively established, must be inspected and modified to incorporate Modification 1732, in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service low pressure impellers having crack indications. c. Remove from service not later than December 31, 1984, all low pressure impellers which have not been inspected for cracks and do not have Modification 1732 incorporated. 3. DART 542 and 543 model engines and their variants. a. After December 31, 1981, no low pressure impeller may exceed 9,000 flight cycles since new without inspection for cracks and incorporation of Modification 1732, in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service low pressure impellers having crack indications. b. After December 31, 1981, prior to further flight, all low pressure impellers for which the flight cycles since new cannot be positively established, must be inspected and modified to incorporate Modification 1732, in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service low pressure impellers having crack indications. c. Remove from service not later than December 31, 1983, all low pressure impellers which have not been inspected for cracks and do not have modification 1732 incorporated. NOTE: For the purposes of this AD, a flight cycle is considered to be an engine operating sequence fromtakeoff to landing. Airplanes may be ferried in accordance with the provisions of FAR 21.197 to a base where the AD can be accomplished. Upon request of the operator, equivalent means of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, FAA, New England. The Manufacturer's Alert Service Bulletin identified and described in this directive is 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 this document from the manufacturer may obtain copies upon request to Technical Publications Department, Rolls-Royce, Ltd., East Kilbride G74 4PY, Scotland. The document may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts, 01803, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 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 the New England Region Office. Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance date(s) specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. This amendment becomes effective October 30, 1980.
2020-16-08: The FAA is correcting an airworthiness directive (AD) that published in the Federal Register. The AD applies to certain Aspen Avionics, Inc., Evolution Flight Display (EFD) EFD1000 Emergency Backup Display, EFD1000 Multi-Function Display, and EFD1000 Primary Flight Display systems installed on various airplanes. As published, the docket number and product identifier in the Comments Invited section of the preamble are incorrect. This document corrects that error. In all other respects, the original document remains the same; however, for clarity, the FAA is publishing the entire rule in the Federal Register.
60-16-04: 60-16-04 HARTZELL: Amdt. 182 Part 507 Federal Register July 29, 1960. Applies to All Propellers HC-82XF-1D, HC-82XF-1DB, HC-82XG-1D, HC-82XG-6DL, HC-82XL-1D, and HC-92ZK-8L; and to HC-82XK-1D Serial Numbers 100G Through 846G; and to HC-92ZK-8D Serial Numbers 100L Through 491L. These Propellers May Be Used On Such Aircraft As Piper PA-24, Cessna 180 and 182, Meyers 200, Mooney Mark 20, and Lake (Colonial) C-2. Compliance required as indicated. Because of failure or cracking of several cast guide collars, P/N 834-4, -8, -9, the following shall be accomplished: (a) Within the next 25 hours of propeller operation and each 25 hours of operation thereafter, visually inspect for cracks, all guide collars not marked with a letter "P" or "F". This inspection can be accomplished by looking through the spinner blade cutouts without removing the spinner. Cracked collars must be replaced prior to further flight. (b) At the next propeller overhaul or by January 1, 1961,whichever occurs first, replace all unmarked guide collars with marked guide collars. Cast collars which are marked with the letter "P" and forged collars which bear part number as cast collars but are marked with letter "F" have been tested and need not be inspected or replaced. (Hartzell Service Bulletin No. 71 covers this same subject.) This directive shall become effective 30 days after publication in the Federal Register.
80-21-10: 80-21-10 BEECH: Amendment 39-3967. Applies to Model 77 (serial numbers WA-1 through WA-156, WA-158 through WA-161, WA-163 through WA-171, WA-173, WA-174, WA-177 and WA-178) airplanes certificated in all categories. COMPLIANCE: Required as indicated unless already accomplished. To ensure the structural integrity of the engine mount attachment to the airplane, accomplish the following: A) Prior to further flight, accomplish the following: 1. Remove the engine cowling, support the tail of the airplane, and hoist the engine as required to remove weight from the engine mount attachment. 2. Remove and visually inspect for thread damage the four bolts and nuts attaching the engine mount to the firewall. Retain washers and nut retaining clips for reuse. The nut is held in place by a spring clip which may be removed with a magnet or wire hook. NOTE: Remove and inspect the engine mount attachment bolts and nuts one at a time. 3. Align the holes in the engine mount, firewall and fuselage frame. Ream the attachment holes in the firewall and fuselage frame to .375/.379 inch diameter. NOTE: A strap may be used between the engine mount tubes to pull the engine mount holes into alignment. If necessary to facilitate reaming of the firewall and attach fitting holes, support the engine and remove the remaining three bolts. 4. Replace damaged bolts and nuts with a new part of a P/N shown by Table I. Any thread damage on either a bolt or nut requires replacement of both the bolt and nut. Table I Bolt Nut 130909B71 2452-064 (use existing or or AN6-21A/M/(magnaflux inspected) LH8065-064 (use existing retainer) or NAS577-6A (use NAS578-6 retainer) 5. Ensure the bolts, washers, nuts and holes are clean and free of grease and oil. Align parts, install bolts, washers and nuts, and torque to 325 +0 -20 inch-pounds. Do not use a power wrench to install the bolts. 6. Remove the engine hoist and tail support and reinstall the engine cowling. B) Within five days report damaged bolts or other defects found as a result of any inspection required herein to the FAA via an M or D Report (FAA Form 8330-2) or a letter to the Chief, Aircraft Certification Program, Federal Aviation Administration, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209. Describe the defect found, location of bolt on firewall, total time-in-service on the airplane or part at time of discovery, and the aircraft serial number. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) C) Any equivalent means of compliance with this AD must be approved by the Chief, Aircraft Certification Program, Federal Aviation Administration, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209, telephone (316) 942-4285. Beechcraft Service Instructions No. 1153 and Beech Mailgram Number 80-452-940 pertain to the subject matter of this AD. This amendment becomes effective on November 13, 1980, to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated October 10, 1980, and is identified as AD 80-21-10.
84-03-08: 84-03-08 AIRBUS INDUSTRIE: Amendment 39-4806. Applies to Model A300 airplanes, certificated in all categories and whose serial numbers are listed in paragraph 1, Planning Information, of Airbus Industrie (AI) Service Bulletin A300-32-356, Revision 1, dated December 1, 1982. To prevent failure of main landing gear hinge arms, accomplish the following unless previously accomplished: A. Within 120 days from the effective date of this AD, measure the displacement of the bronze bushing fitted in the stirrup on the actuating cylinder side of all affected hinge arms in accordance with paragraph 2.B of Messier-Hispano-Bugatti (MHB) Service Bulletin 470-32-422, Revision 1, dated December 3, 1982. Depending on the results of the above measurements and within the number of landings specified in the service bulletin, repeat the measurement of the displacement or visually inspect for corrosion, as appropriate, the blending radii of attachment between the trunnions and the hinge arm bodyin accordance with the instructions of the service bulletin. 1. If no trace of corrosion is found, incorporate the modifications AI 4544/S5351 and AI 4544/S5548, described in AI Service Bulletins A300-32-348, Revision 2 and A300-32-355, Revision 2, both dated May 16, 1983, and in accordance with the instructions of MHB Service Bulletins 470-32-421, Revision 2 and 470-32-407, Revision 2, both dated March 31, 1983. 2. If corrosion is detected, replace the affected hinge arms prior to further flight either with new arms or with arms modified in accordance with the instructions of MHB Service Bulletin 470-32-431, dated December 24, 1982, related to AI Service Bulletin A300-32- 362, dated June 15, 1983, after incorporating the modifications required by paragraph A.1. of this AD. B. 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. C.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. This amendment becomes effective March 19, 1984.
2020-13-09: The FAA is adopting a new airworthiness directive (AD) for all DG Flugzeugbau GmbH Models DG-500 Elan Orion, DG-500 Elan Trainer, DG- 500/20 Elan, DG-500/22 Elan, DG-500M, and DG-500MB gliders and certain Models DG-1000S and DG-1000T gliders. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as the rear locking rod of the rear canopy rotating out of the threads of the operating mechanism, which could lead to blocking of the canopy emergency release system, preventing safe escape of occupants from the glider. The FAA is issuing this AD to require actions to address the unsafe condition on these products.
60-02-03: 60-02-03 BOEING: Amdt. 79 Part 507 Federal Register January 15, 1960. Applies to the following 707-100 Series Aircraft Only: Serial Numbers 17586 through 17591, 17609 through 17612, 17628 through 17650, 17658 through 17672, 17696 through 17702, 17925 through 17927.\n \n\tCompliance required by June 1, 1960.\n \n\tBecause of the hazardous condition caused by water injection system failures, the following modifications shall be accomplished as indicated: \n\n\t(a) Relocate the water inlet valve switch from the co-pilot's panel to the flight engineer's panel and add four transient position blue indicating lights (one for each valve). Install a placard for nomenclature.\n \n\t(b) Change water booster pumps start switch on co-pilot's panel to a two-position toggle switch. \n\n\t(c) Install an appropriate placard adjacent to the water booster pump switch to specify that this switch is to be turned off after the water pressure lights go out at the end of water injection. This is necessary to avoid damaging the tank mounted water booster pump after water runout. These modifications are included in Boeing Service Bulletin No. 194 (R-1) dated June 19, 1959. \n\n\tRevised March 29, 1960.
82-25-04: 82-25-04 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4505. Applies to Model SA330J series helicopters certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent fretting corrosion on the flapping hinge subsequent to loosening of the hinge pin attachment nut, 330A.31.1567.20 or 330A.31.1585.20, accomplish the following: (a) Within the next 25 flight hours after the effective date of this AD, check the torque of the flapping hinge pin nut in accordance with Aerospatiale SA330 Service Bulletin No. 05.65, paragraph 1C(1)(a) or an equivalent approved by the Manager, FAA, Europe, Africa, and Middle East Office, and thereafter at each P2 inspection (300 hours). (b) If the torque value is less than 10 mdaN (74 foot-pounds), adjust the torque in accordance with Aerospatiale SA330 Service Bulletin No. 05.65, paragraph 1C(1)(c) and accomplish the inspection in accordance with paragraph 1C(2)(a) at the nextP2 inspection (300 hours) or an equivalent approved by the Manager, FAA, Europe, Africa, and Middle East Office. This amendment becomes effective December 14, 1982.
2020-15-15: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC225LP helicopters. This AD was prompted by a mechanical deformation found on the protective cover of the ''SHEAR'' control pushbutton installed on a copilot collective stick. This AD requires modification of the helicopter by replacing the protective cover and re-identifying the part number of the pilot and copilot collective sticks. The FAA is issuing this AD to address the unsafe condition on these products.