Results
77-07-03: 77-07-03 PIPER AIRCRAFT CORPORATION: Amendment 39-2860. Applies to models PA-31, PA-31-325, S/N's 31-7612090, 31-7612091, 31-7612092, 31-7612096, 31-7612098, 31-7612101 thru 31-7612105, 31-7612107 thru 31-7612110, and 31-7712002 thru 31-7712006; PA-31-350, S/N's 31-7652142 thru 31-7652147, 31-7652149, 31-7652151, 31-7652152, 31-7652154 thru 31-7652162, 31-7652164, 31-7652165, 31-7652167, 31-7652168, 31-7652171 thru 31-7652174, 31-7652176, 31-7752002 thru 31-7752007, 31-7752009 thru 31-7752011, 31-7752013, 31-7752014 and 31-7752017 thru 31-7752026. Compliance required within 100 hours in service. To prevent electrical terminals form shorting against the relay cover, accomplish the following: (a) Replace the spacer bushings in accordance with the instructions given in Service Bulletin No. 535, dated December 15, 1976, or with an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request, with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This Amendment becomes effective April 4, 1977.
85-14-06 R1: 85-14-06 R1 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-5089 as amended by Amendment 39-5121. Applies to all Aerospatiale Model AS 350 and AS 355 series helicopters certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent possible failure of the fuselage to tailboom interface frame, accomplish the following: (a) For helicopters which have 1,100 hours or more time in service on the effective date of this AD, inspect in accordance with paragraph (d) within the next 100 hours time in service. (b) For helicopters which have 900 hours or more but less than 1,100 hours time in service on the effective date of this AD, inspect in accordance with paragraph (d) before reaching 1,200 hours time in service. (c) For helicopters which have less than 900 hours time in service on the effective date of this AD, inspect in accordance with paragraph (d) within the next 300 hours time in service. (d) Inspect the bolts for torque and, if necessary, the frame for cracks at the fuselage-to-tailboom interface in accordance with: (1) Service Bulletin No. 05.16 for Model AS 350 series helicopters. (2) Service Bulletin No. 05.14 for Model AS 355 series helicopters. (e) In addition for AS 355 series helicopters, conduct the following initial visual inspection within the next 100 hours time in service for helicopters which have 1,100 hours or more time in service on the effective date of this AD or before reaching 1,200 hours time in service for those helicopters having less than 1,100 hours total time in service on the effective date of this AD: (1) Remove the tailboom from the fuselage in accordance with the Model AS 355 maintenance manual, or FAA-approved equivalent, as appropriate. Prior to tailboom removal, inspect the bolts for torque readings in accordance with paragraph (d). (i) Visually inspect the aft fuselage frame at the fuselage tailboom interface for cracks. Conduct the visual inspection on all accessible frame areas with special emphasis in frame flange radii and at bolt holes. (ii) Conduct dye penetrant inspections of areas of suspected cracks that cannot be verified by a visual inspection. (2) If all the bolt torque readings from the inspection of SB No. 05.14 are 26.5-inch-pounds or greater, the following RH upper quadrant (looking forward) frame inspection may be conducted in lieu of the full frame inspection of paragraph (1): (i) Remove the bolts common to the tailboom, fuselage frame, and RH fuselage frame radius block. (ii) Remove the RH radius block after grinding off the three rivet heads which retain the radius block. The radius block is shown as Item 21 of detail C of page 10 of Aerospatiale Repair Manual 53.10.22, Volume 1. (iii) Visually inspect the forward side of the RH aft fuselage frame for cracks. Conduct the visual inspection on all accessible frame areas with special emphasis in frame flange radii and at bolt holes. (iv) Conduct dye penetrant inspections of areas of suspected cracks that cannot be verified by a visual inspection. (v) Apply zinc chromate primer to the aft surface of the radius block; replace it using the original bolts, but do not re-rivet to the frame. (3) Report cracks and bolt torque values measured before tailboom or radius block removal to the Manager, Aircraft Certification Division, Federal Aviation Administration, P.O. Box 1689, Fort Worth, Texas 76101 within 10 days of the inspection. Use a copy of View F of Service Bulletin No. 05.14 or No. 05.16 to show the locations of cracks or loose fasteners (those below 26.5 inch-pounds of measured torque). If all fasteners are found to have a torque of 26.5 inch-pounds or greater, a statement of such is sufficient without a marked-up View F. Provide aircraft serial numbers, total time, and time since tailboom removal, if any. (Reporting is approved by the Office of Managementand Budget under OMB No. 2120-1156.) NOTE: The initial visual inspection of paragraph (e) and reporting of results are required for all Model AS 355 helicopters even if the bolt torque values measured during the inspections of paragraph (d) are 26.5 inch-pounds or greater. (f) Replace any cracked frames or repair in accordance with Service Bulletin No. 05-14 or No. 05-16. (g) Reinstall the tailboom in accordance with the appropriate Model AS 350 or AS 355 maintenance manual, or FAA-approved equivalent, if removed during the inspections and rework of paragraphs (d), (e), and (f). (h) Repeat the inspections required in paragraph (d) at intervals not to exceed 1,200 hours time in service from the last inspection. (i) An alternate method of compliance with this AD and adjustment of repetitive compliance times may be approved by the Manager, Aircraft Certification Division, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106 or by the Manager,Aircraft Certification Office, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. Adjustments in compliance time may be approved upon recommendations of the FAA aviation safety inspector. (j) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the inspections required by this AD may be accomplished. The manufacturer's specifications and procedures identified and described in this directive are incorporated by reference 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 Aerospatiale Helicopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75051, Attention: Customer Support. These documents may also be examined in the Rules Docket at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration Room 156, Building 3B, 4400 Blue Mound Road, Fort Worth, Texas 76106. Amendment 39-5089 became effective July 26, 1985. This amendment 39-5121 becomes effective September 12, 1985.
86-11-05: 86-11-05 GARRETT TURBINE ENGINE COMPANY (formerly the AiResearch Manufacturing Company of Arizona): Amendment 39-5325. Applies to all Model TFE731-2, -3, and -3R turbofan engines installed in aircraft certified in all categories equipped with fan rotor discs, part number 3073436-1, -2, -3, and -4 and 3072162-1, -2, -3, and -4. Compliance is required as indicated unless already accomplished. To prevent failure of the fan rotor disc due to fatigue cracking, accomplish the following: (a) For fan rotor discs with 4000 or less operating cycles on the effective date of this AD, remove fan rotor disc from service before reaching 4100 total operating cycles. (b) For fan rotor discs with more than 4000 but with 6000 or less operating cycles on the effective date of this AD, remove fan rotor disc from service within the next 100 operating cycles or prior to reaching 6005 total operating cycles whichever occurs first. (c) For fan rotor discs with more than 6000 but with 8000 or less operating cycles on the effective date of this AD, remove fan rotor disc from service within the next 5 operating cycles or prior to reaching 8001 total operating cycles whichever occurs first. (d) For fan rotor discs with more than 8000 operating cycles on the effective date of this AD, remove fan rotor disc from service prior to further flight. NOTES: (1) An operating cycle is considered as any engine operating sequence involving an engine start, at least one acceleration to 80 percent or more low pressure rotor speed, and an engine shutdown. An alternate method of determining cycles is to consider each airplane landing as one cycle. Fan rotor discs which have had their cyclic lives calculated by any other method are to have their cyclic lives recalculated using one of the two methods specified above. (2) It has come to the attention of the FAA that some life limit log cards in the engine log book were incorrectly filled out in that the "dash number" of the disc part numbers (i.e., -1/-2/-3/-4) may have been left off. This should be corrected when the disc is next available to read the entire part number. All fan rotor discs are -1, -2, -3, or -4, and are affected by this AD. Fan rotor discs may be returned to GTEC for evaluation. Shipping information is contained in Garrett Alert Service Bulletin No. TFE731-A72-3328 Revision 2 dated April 4, 1986. 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. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Western Aircraft Certification Office, P.O. Box 92007, Worldway Postal Center, Los Angeles, California 90009. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Western Aircraft Certification Office, P.O. Box 92007, Worldway Postal Center, Los Angeles, California 90009-2007 may adjust the compliance time specified in this AD. This amendment supersedes priority letter AD 86-04-02 issued February 14, 1986. There are two effective dates for this superseding AD. For those operators who received priority letter AD 86-04-02, the effective date of this AD is the date of the priority letter AD (issued February 14, 1986). The effective date of this AD is June 16, 1986, for operators with fan rotor disc part number 3073436-4 or 3072162-4 installed and for operators who did not receive the priority letter AD.
98-13-15: This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Mystere-Falcon 200, Fan Jet Falcon, and Mystere-Falcon 20 series airplanes, that requires repetitive inspections to detect cracks at the attaching holes of the wing-to-fuselage fairings and to ensure tightness of the attaching screws; and repair of any discrepancy. This amendment also requires installation of cupwashers under the vertical seams of the upper fairings. 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 loss of the wing-to-fuselage upper fairings during flight, which could result in the fairings impacting the engines or tail sections, and consequent reduced controllability of the airplane.
95-18-06 R1: 95-18-06 R1 Hamilton Standard: Priority Letter issued on August 30, 1995. Docket No. 95-ANE-50. Revises Priority Letter 95-18-06, issued August 28, 1995. Applicability: Hamilton Standard Models 14RF-9, 14RF-19, 14RF-21, and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, and 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F propellers installed on but not limited to Embraer EMB-120 and EMB 120-RT; SAAB-SCANIA SF 340B; Aerospatiale ATR42-100, ATR42-300, ATR42-320, ATR72; DeHavilland DHC-8-100 series, DHC-8-300 Series; Construcciones Aeronauticas SA (CASA) CN-235 series and CN-235-100; Canadair CL-215T and CL-415; and British Aerospace ATP airplanes. NOTE: This AD applies to each propeller identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For propellers that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (h) to request approval from the Federal Aviation Administration (FAA). This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any propeller from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent separation of a propeller blade due to cracks initiating in the blade taper bore, that can result in aircraft damage, and possible loss of aircraft control, accomplish the following: (a) For Hamilton Standard Model 14RF-9 propeller blades, installed on Embraer EMB-120 series aircraft, within the next 10 flight cycles after the effective date of this AD, remove from service propeller blades that have been ultrasonically shear wave inspected in accordance with AD 94-09-06 or AD 95-05-03, removed from service due to crack indications, and subsequently reworked and returned to service. These propeller blades include, but are not limited to, the following serial numbers: 847598 851646 852085 852561 853151 854530 854535 854838 855014 855042 855196 855859 857375 858696 859824 860589 867590 876707 880245 (b) For Hamilton Standard Models 14RF-19, 14RF-21, and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, and 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F propeller blades, installed on aircraft other than Embraer EMB-120 series aircraft, within the next 10 flight cycles after the effective date of this AD, unless inspected previously in accordance with Telegraphic AD T95-18-51, perform an ultrasonic shear wave inspection for cracks in the blade taper bore of propeller blades that have been ultrasonically inspected in accordance with AD 94-09-06 or AD 95-05-03, removed from service due to crack indications, and subsequently reworked and returned to service. Thereafter, at intervals not to exceed 1,250 flight cycles since last inspection, perform an ultrasonic shear wave inspection for cracks in the blade taper bore of propeller blades. Perform the ultrasonic shear wave inspection in accordance with the Accomplishment Instructions of the following Hamilton Standard Alert Service Bulletins (ASB's), as applicable: No. 14RF-21-61-A68, No. 14SF-61-A88, No. 14RF-19-61-A49, No. 6/5500/F-61-A36; all dated August 25, 1995. Remove propeller blades with crack indications from service and replace with serviceable parts. (c) For Hamilton Standard Model 14RF-9 propeller blades, installed on Embraer EMB-120 series aircraft, not affected by paragraph (a) of this AD, perform ultrasonic shear wave inspections in accordance with the Accomplishment Instructions of Hamilton Standard ASB No. 14RF-9-61- A85, dated August 28, 1995. Remove propeller blades with crack indications from service and replace with serviceable parts: (1) For propeller blades with 1,250 or more flight cycles since last ultrasonic shear wave inspection on the effective date of this AD, or that have not been ultrasonically shear wave inspected, perform an ultrasonic shear wave inspection for cracks within the next 50 flight cycles after the effective date of this AD. (2) For propeller blades with less than 1,250 flight cycles since last ultrasonic shear wave inspection on the effective date of this AD, perform an ultrasonic shear wave inspection for cracks within the next 50 flight cycles after the effective date of this AD, or prior to accumulating 1,250 flight cycles, whichever occurs later. (3) Thereafter, perform repetitive ultrasonic shear wave inspections at intervals not toexceed 1,250 flight cycles since last inspection. (d) For Hamilton Standard Models 14RF-19, 14RF-21, and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, and 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F propeller blades; identified by serial number in the ASB's listed in this paragraph, installed on aircraft other than Embraer EMB-120 aircraft, and not affected by paragraph (b) of this AD, perform ultrasonic shear wave inspections in accordance with the Accomplishment Instructions of Hamilton Standard ASB's, as applicable: No. 14RF-21-61-A69, No. 14SF-61-A89, No. 14RF-19- 61-A50, No. 6/5500/F-61-A37; all dated August 28, 1995. Remove propeller blades with crack indications from service and replace with serviceable parts: (1) For propeller blades with 1,250 or more flight cycles since last ultrasonic shear wave inspection on the effective date of this AD, or that have not been ultrasonically shear wave inspected, perform an ultrasonic shear wave inspection for cracks within the next 150 flight cycles after the effective date of this AD. (2) For propeller blades with less than 1,250 flight cycles since last ultrasonic shear wave inspection on the effective date of this AD, perform an ultrasonic shear wave inspection for cracks within the next 150 flight cycles after the effective date of this AD, or prior to accumulating 1,250 flight cycles, whichever occurs later. (3) Thereafter, perform repetitive ultrasonic shear wave inspections at intervals not to exceed 1,250 flight cycles since last inspection. (e) No ultrasonic shear wave inspections are required for Hamilton Standard Models 14RF- 19, 14RF-21, and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, and 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F propeller blades, that have been shotpeened in the taper bore during manufacture, and not identified by serial numbers in the ASB's listed in paragraph (b) of this AD. (f) Propeller blades removed from service in accordance with this AD may not be returned to service. (g) For the purpose of this AD, a flight cycle is defined as one takeoff and the next landing of an aircraft. In addition, each touch and go is defined as a flight cycle, and each water load pick up for amphibian aircraft operation is defined as a flight cycle. (h) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Boston Aircraft Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Boston Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Boston Aircraft Certification Office. (i) Special flight permits may be issued in accordance withsections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (j) Copies of the applicable service information may be obtained from Hamilton Standard, One Hamilton Road, Windsor Locks, CT 06096-1010; telephone (203) 654-6876. This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA. (k) Priority Letter AD 95-18-06 R1, issued August 30, 1995, becomes effective upon receipt. (l) Priority Letter AD 95-18-06 R1 revises priority letter 95-18-06 issued August 25, 1995. This Revised Priority Letter AD 95-18-06 R1 revised Priority Letter AD 95-18-06 issued on August 28, 1995, and supersedes the Telegraphic AD T95-18-51 issued on August 25, 1995.
2020-01-55: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GE90-110B1 and GE90-115B model turbofan engines. This AD was sent previously as an emergency AD to all known U.S. owners and operators of the GE GE90-110B1 and GE90-115B model turbofan engines with certain engine serial numbers. This AD requires the removal from service of the interstage seal, part number 2505M72P01 or 2448M33P01, from the affected engines. This AD was prompted by a recent event involving an uncontained high-pressure turbine (HPT) failure that resulted in an aborted takeoff. The FAA is issuing this AD to address the unsafe condition on these products.
77-04-06: 77-04-06 MESSERSCHMITT-BOLKOW-BLOHM (MBB): Amendment 39-2835 as amended by amendment 39-3528. Applies to all Model BO-105A and BO-105C helicopters, certificated in all categories. Compliance is required as indicated. To prevent the possible failure of a main rotor gearbox support, P/Ns 105-10161 and 105-10162, replace the two supports with serviceable supports within the next 10 hours time in service after the effective date of this AD or prior to the accumulation of 6,800 hours time in service on the supports, whichever occurs later, and, thereafter, continue to replace the supports prior to the accumulation of 6,800 hours time in service. Amendment 39-2835 became effective March 3, 1977. This amendment 39-3528 becomes effective August 23, 1979.
86-15-01 R2: 86-15-01 R2 ROLLS-ROYCE LIMITED: Amendment 39-5346 as amended by Amendment 39-5608 is further amended by Amendment 39-5638. Applies to Rolls-Royce RB211-22B, -535C, and -524 series turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent an uncontained stage 1 high pressure compressor (HPC) disk fracture, accomplish the following: (a) Remove from service stage 1 and 2 HPC disk assemblies identified by serial number in Appendix 3 of Rolls-Royce Alert Service Bulletin (ASB) RB.211-72-A7774, Revision 2, dated February 6, 1987, at the next 04 module rework, but not later than July 20, 1987. (b) Remove from service stage 1 and 2 HPC disk assemblies identified by serial number in Appendix 4 of the Rolls-Royce (R-R) Alert Service Bulletin (ASB) RB.211-72-A7774, Revision 2, dated February 6, 1987, in accordance with the following criteria: (1) For stage 1 and 2 HPC disk assemblies installed in R-R RB211-524 engines, prior toaccumulating a total part life of 4,050 cycles in service or before May 31, 1988, whichever occurs later. (2) For stage 1 and 2 HPC disk assemblies installed in R-R RB211-22B engines, prior to accumulating total part life of 4,350 cycles in service or before May 31, 1988, whichever occurs later. (3) For stage 1 and 2 HPC disk assemblies installed in R-R RB211-535C engines, prior to accumulating total part life of 5,150 cycles in service or before May 31, 1988, whichever occurs later. NOTE: Module 04 rework is defined as any work carried out on any part of the 04 module after its removal from an engine for any reason other than use as a spare to transfer to another engine or to permit removal of the 03 module. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD. 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. Rolls-Royce ASB RB.211-72-A7774, Revision 2, dated February 6, 1987, identified and described in this document, 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 Rolls-Royce plc, Technical Publications Department, P.O. Box 31, Derby DE2 8BJ, England. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 85- ANE-17, Room 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment, 39-5638, amends Amendment 39-5346 as amended by Amendment 39-5608, AD 86-15-01 R1. This amendment, 39-5638, becomes effective on July 1, 1987.
82-13-05 R1: 82-13-05 R1 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4401 as amended by Amendment 39-4567. Applies to Model AS350 series helicopters equipped with upper tail fin, P/N 350A.14.0020, and Model AS355 series helicopters equipped with upper tail fin, P/N 350A.14.0522, including fins modified per AMS 071047, certificated in all categories (Airworthiness Docket No. 81-ASW-62). Compliance required as indicated. To detect possible cracks in the flanges of the upper vertical fin support fitting and prevent failure of this fitting and loss of the fin, accomplish the following: (a) Before the first flight of each day after the effective date of this AD, visually check for cracks in the flanges of the upper vertical fin support using a light. If a crack is found, the vertical fin must be removed before further flight as prescribed in subparagraph (b)(3) of this AD. The check may be performed by the pilot. NOTE: For the requirements regarding thelisting of compliance with this AD in the aircraft maintenance record, see Section 91.173 of the Federal Aviation Regulations. (b) Within the next 10 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 50 hours' time in service from the last inspection, accomplish the following: (1) Remove the tail cone fairing, P/N 350A.23.0014. (2) Inspect the flanges of the upper vertical fin support fitting for cracks using a dye penetrant or equivalent inspection method. (3) If a flange of the fitting is cracked, the upper vertical fin must be removed and a serviceable upper fin installed before further flight in accordance with Chapter 55 of the Model AS350 and AS355 Maintenance Manual or FAA approved equivalent. (4) Install tail cone fairing. (c) Equivalent means of compliance with this AD must be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (d) Special flight permits may be issued in accordance with Sections 21.197 and 21.199 of the Federal Aviation Regulations to fly aircraft to a base where compliance with paragraph (b) of this AD may be accomplished. (e) The checks and inspections specified in paragraphs (a) and (b) of this AD are not required after March 1, 1983, provided fins have been modified per AMS 071047 or an equivalent means. This supersedes Amendment 39-4294 (47 FR 1113), AD 82-02-02. Amendment 39-4401 became effective June 28, 1982. This Amendment 39-4567 becomes effective March 1, 1983.
99-16-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive inspections to detect cracked or broken support brackets of the upper wing-to-fuselage fairings, and replacement of any discrepant support brackets with new brackets. This amendment also requires replacement of the fairing seals with new, improved seals; modification of the fairing panels; and installation of new bulkheads; which constitutes terminating action for the repetitive inspections. 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 reduced structural integrity of the fairing support brackets, which could result in loss of the wing-to-fuselage fairings during flight, and consequent structural damage to the airplane.
98-12-17: This amendment adopts a new airworthiness directive (AD) that is applicable to all British Aerospace Model Viscount 744, 745, 745D, and 810 series airplanes. This amendment requires repetitive inspections to detect cracking and corrosion of components of the engine nacelle subframe structure, and corrective action, if necessary; and replacement of any component that has reached its life limit (safe life) with a new or serviceable component. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to ensure periodic replacement of certain engine nacelle subframe components that have reached their maximum life limits. Cracking and corrosion of these components, if not detected and corrected in a timely manner, could result in reduced structural integrity of the engine nacelle subframe structure, separation of the engine from the airframe, and reduced controllability of the airplane.
2020-02-22: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by a determination that new tests are necessary to address potential air leaks in the reservoir air pressurization lines. This AD requires repetitive pressurization tests of the reservoir air pressurization lines for pipe rupture and leaks, and repair or replacement if necessary, 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.
82-10-04: 82-10-04 MCDONNELL DOUGLAS: Amendment 39-4378. Applies to McDonnell Douglas DC-9, series 30, 50, 80 and C-9B airplanes certificated in all categories, with factory serial numbers listed in Service Bulletin A27-234. Compliance required within 90 days unless already accomplished. \n\n\tTo prevent loss of ability to trim the aircraft by use of the primary longitudinal trim system, accomplish the following: \n\n\tA.\tDetermine serial number of horizontal stabilizer alternate longitudinal trim motor P/N D1775 by visual examination of motor or from aircraft maintenance records. \n\n\tB.\tReplace trim motor if serial number is listed in table of item #2 in Service Bulletin A27-234. \n\n\tNOTE: Service Bulletin A27-234 contains recommended procedures for gaining access to the horizontal stabilizer alternate longitudinal trim motor, and for checkout of the trim system subsequent to replacement of the motor. \n\n\tC.\tAlternative means of compliance which provide an equivalent level of safety maybe used when approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Mountain Region. \n\n\tThe 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). \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). \n\n\tThese documents also may be examined at FAA Northwest Mountain Region, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168; or Los Angeles Area Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California 90808. \n\n\tThis Amendment becomes effective May 18, 1982.
77-03-03: 77-03-03 PIPER: Amendment 39-2824. Applies to Models PA-31 and PA-31-310 Serial Nos. 31-7401201 through 31-7401268, 31-7512001 through 31-7512037, 31-7512039, 31- 7512041, 31-7512042, 31-7512047, 31-7512048, 31-7512050, 31-7512051, 31-7512054 through 31-7512056, 31-7512058, 31-7512063, 31-7512067, 31-7512068, 31-7512070, 31-7512072, 31- 7612001, 31-7612003, 31-7612006, 32-7612009, 31-7612011, 31-7612013, 31-7612019, 31- 7612021, 31-7612022, 31-7612025 through 31-7612028, 31-7612030, 31-7612033 through 31-7612035, 31-7612040, 31-7612045, 31-7612047, 31-7612049, 31-7612051, 31-7612052, 31-7612055, 31-7612060, 31-7612061, 31-7612071, 31-7612075, 31-7612077, 31-7612078, 31-7612080, 31-7612084, 31-7612085, and 31-7612088 certificated in all categories. To preclude the possibility of Airworthiness Directives applicable to Piper Model PA-31 aircraft not being incorporated in aircraft which have affixed to them, in error, a model PA-31- 310 Aircraft Data Plate, accomplish the following within the next 30 days from the effective date of this AD unless previously accomplished. (a) Ascertain whether the Aircraft Data Plate located on the lower fuselage just below the forward hinge on the main cabin door is marked with a model designation of PA-31 or PA-31-310. If it is PA-31-310, remove and replace with a correct PA-31 Aircraft Data Plate and verify that Airworthiness Directives, Piper 74-26-04, 75-09-10, 75-26-18, and 76-04-11, applicable to model PA-31 aircraft, have been accomplished. If not, comply in accordance with the requirements of those Airworthiness Directives. (b) Upon request with substantiating data, submitted through an FAA Maintenance Inspector, the compliance time for this AD, including 74-26-04, 75-09-10, 75-26-18 and 76-04- 11 may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (Piper Service Bulletin No. 529 pertains to this subject.) This amendment is effective February 9, 1977.
85-14-03: 85-14-03 BRITISH AEROSPACE: Amendment 39-5092. Applies to Model BAC 1-11 series 400 airplanes certificated in any category. Compliance is required as indicated. To prevent asymmetrical deployment of ground spoilers (lift dumpers) accomplish the following, unless previously accomplished within the last 1000 landings or one year, whichever occurred earlier: A. Within the next 100 landings or 30 days after the effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 5,000 landings from the last inspection, inspect the ground spoiler mechanical locks for misalignment, and adjust if necessary, in accordance with the accomplishment instructions of British Aerospace BAC 1-11 Alert Service Bulletin 27-A-PM5890, dated December 21, 1983. From the results of the inspection above: 1. If two or more mechanical locks out of the four per ground spoiler are found unserviceable, perform an operational check of the ground spoilers prior to further flight and thereafter at intervals not to exceed 600 landings or 150 days, whichever occurs earlier, until defective components are replaced in accordance with the accomplishment instructions of the service bulletin. 2. If one mechanical lock out of the four per ground spoiler is found unserviceable, perform an operational check of the ground spoilers prior to further flight and thereafter at intervals not to exceed 2,500 landings in accordance with the accomplishment instructions of the service bulletin until defective components are replaced. 3. If the mechanical lock system fails the operational check conducted in accordance with paragraphs A.1. or A.2., above, the locks must be repaired or the ground spoilers rendered inoperative in accordance with the accomplishment instructions of the service bulletin prior to further flight. B. Alternate means of compliance which provide an acceptable 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 August 15, 1985.
2020-02-23: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, A350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. This AD requires repetitive inspections of the installation of the pull cables on the emergency float kits. This AD was prompted by the results of an accident investigation and subsequent reports of difficulty pulling the emergency float kit float activation handle installed on the pilot cyclic. The FAA is issuing this AD to address the unsafe condition on these products.
86-08-01: 86-08-01 SHORT BROTHERS, LTD.: Amendment 39-5286. Applies to Model SD3-30 and SD3-60 series airplanes; serial numbers SH3002 through SH3099, SH3102, and SH3105 (SD3-30 airplanes); SH3601 through SH3661 and SH3663 through SH3665 (SD3-60 airplanes); certificated in any category. Compliance is required as indicated below, unless previously accomplished: 1. Within seven days after the effective date of this AD, inspect the collector tank housing in accordance with Short Brothers Service Bulletin SD330-28-29, dated August 1985 (for SD3-30 series airplanes), and SD360-28-12, Revision 1, dated August 1985 (for SD3-60 series airplanes). If leaks are found, prior to further flight, replace the shrouds and seals in accordance with the applicable service bulletin instructions. If no leaks are found, repeat the inspection at intervals not to exceed 120 hours time in service. 2. Replacement of the existing shrouds and seals in accordance with the applicable service bulletin, referredto in paragraph 1. of this AD, constitutes terminating action for the requirement for the repetitive inspections set forth in paragraph 1., above. 3. An 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, Standardization Branch, ANM-113, 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Short Brothers, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East MarginalWay South, Seattle, Washington. This amendment becomes effective April 28, 1986.
77-01-06: 77-01-06 PIPER: Amendment 39-2806. Applies to Models PA-31 and PA-31-325, Serial Nos. 31-7612060 through 31-7612080, 31-7612082 through 31-7612089, 31-7612091, 31- 7612096 and 31-7612099; Model PA-31-350, Serial Nos. 31-7652105 through 31-7652115, 31- 7652117, 31-7652118, 31-7652120 through 31-7652146, 31-7652148 through 31-7652162, 31- 7652164, 31-7652165 and 31-7652168 and above model aircraft which have had a replacement horizontal stabilizer installed in the field subsequent to April 1976, certificated in all categories. To prevent possible hazards in flight associated with missing horizontal stabilizer skin- stiffener rivet attachments, accomplish the following within the next fifty hours in service from the effective date of this AD unless previously accomplished: (a) Inspect and, if required, repair the horizontal stabilizer skin-stiffener rivet attachment in accordance with the "Instructions" section of Piper Service Bulletin No. 521 or equivalent procedures approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective January 19, 1977.
81-20-02: 81-20-02 VARGA AIRCRAFT CORPORATION (MORRISEY): Amendment 39- 4341. Applies to Model 2150A, certified in any category. COMPLIANCE: Required as indicated, unless already accomplished. To prevent engine fuel starvation due to obstruction of the fuel vent system, prior to further flight, accomplish the following: a. Inspect vent tube assemblies, P/N 26016-42 and -66, for free airflow between all branches of the vent tubes. b. Replace obstructed vent tube assemblies with a serviceable part of the same part number prior to return to service. c. Special flight permits may be issued in accordance with FAR 21.197 to operate aircraft to a base for the accomplishment of inspections required by this AD. d. Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Western Aircraft Certification Field Office, Northwest Mountain Region, Federal Aviation Administration, 15000 Aviation Boulevard, Hawthorne, California 90261; telephone (213) 536-6352. Varga Service Bulletin SB-13, entitled Fuel Vent Drain Inspection, refers to the subject matter of this AD. This amendment becomes effective March 15, 1982, to all persons except those to whom it was made immediately effective by priority mail as Emergency AD 81-20-02, dated September 28, 1981.
2020-02-18: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation (Gulfstream) Models GVI, GVII-G500, and GVII-G600 airplanes. This AD requires revising the airplane flight manual (AFM) by attaching an airplane flight manual supplement (AFMS), which contains new or revised operating limitations, abnormal procedures, and emergency procedures. This AD was prompted by reports of continued flight after a flight control surface shutdown. If flight is continued after a flight control surface shutdown, the airplane is left without protection against flight control surface hard-over and force fight events on the remaining, operable flight control surfaces. The FAA is issuing this AD to address the unsafe condition on these products.
77-01-03: 77-01-03 PIPER AIRCRAFT CORPORATION: Amendment 39-2801. Applies to Model PA-28-151 airplanes, serial numbers 28-7415001 through 28-7715278 and 28-7715289 certificated in all categories. \n\n\tCompliance required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo detect and correct those carburetor air filter boxes that do not contain a drain hole, accomplish the following: \n\n\t(a)\tOpen the top right side engine cowl door to gain access to the carburetor air filter box, Piper Part Number 35462-00, at the right hand bottom section of the engine compartment. \n\n\t(b)\tCheck visually and by feel to determine whether the carburetor air filter box contains a drain hole in the lower rear corner of the outside half of the carburetor air filter box. (See figure) This check may be performed by the pilot. \n\n\n\nAD 77-01-03 \n\n\t(c)\tIf the box contains a drain hole, accomplish (f). \n\n\t(d)\tIf the box does not contain a drain hole, accomplish (e) and (f). \n\n\t(e)\tModify the carburetor air filter box as follows: \n\n\t\t(1)\tRemove and disassemble the carburetor air filter box. \n\n\t\t(2)\tDrill a .19 inch diameter hole in the lower rear corner of the outside half of the carburetor air filter box. (See figure) \n\n\t\t(3)\tReassemble and reinstall the carburetor air filter box. \n\n\t(f)\tClose the engine cowl and return the airplane to service. \n\n\tPiper Service Bulletin 536 also pertains to this subject. \n\n\tThis amendment becomes effective January 14, 1977.
76-06-09: 76-06-09 PIPER: Amendment 39-2559 as amended by amendment 39-3325. Applies to Piper Model PA-31P airplanes. Compliance required as indicated unless already accomplished. To preclude failure of the engine exhaust system installed on Model PA-31P airplanes, accomplish the following: (a) On airplanes serial numbers 31P-1 through 31P-7730003 within 50 hours after the effective date of this amendment, and every 50 hours thereafter, visually inspect turbocharger exhaust V-band couplings, vibration isolators and support brackets (if installed) for cracks, looseness, and distortion. Any part found cracked or distorted shall be replaced prior to further flight. (b) On airplane serial numbers 31P-1 through 31P-7630001 and on 31P-7630003 within 50 hours time in service after the effective date of this AD perform exhaust pipe slip joint modification in accordance with Lycoming Service Bulletin 393A or an equivalent approved alteration. (c) On airplanes serial numbers31P-1 through 31P-7630009 within 50 hours time in service after the effective date of this AD install bracket and clamp assembly, Piper Kit No. 760 974, in accordance with Piper Service Bulletin 462A or an equivalent approved alteration. (d) On airplanes serial numbers 31P-1 through 31P-7730003 the repetitive inspections of paragraph (a) shall be accomplished until the replacement one-piece turbine tailpipe clamp coupling P/N 556053 is installed in accordance with the "Instructions" sheet in Piper Service Bulletin No. 534 and vibration isolators installed in accordance with Piper Service Bulletin No. 492. NOTE: When replacing the turbine tailpipe clamp coupling, preload the tailpipe against the turbine flange as specified in Piper Service Bulletin Nos. 534 and 462A. (e) Aircraft may be flown to a base where the maintenance required by this airworthiness directive is to be performed per FAR's 21.197 and 21.199. (f) The Chief, Engineering and Manufacturing Branch, FAA Eastern Region may adjust the inspection interval specified in this airworthiness directive upon request of an owner or operator submitted with substantiating data through an FAA maintenance inspector. All equivalent alterations or parts must be approved by the said Branch Chief. (Piper Service Bulletin No. 430 also pertains to this subject.) Amendment 39-2559 was effective March 31, 1976. This amendment 39-3325 is effective October 31, 1978.
91-14-22: 91-14-22 TEXTRON LYCOMING: Amendment 39-6916. Docket No. 89-ANE-10. Applicability: Textron Lycoming (formerly Avco Lycoming) direct drive piston aircraft engines (except: O-320-H, O-360-E, LO-360-E, TO-360-E, LTO-360-E and TIO-541 series engines). Compliance: Required at each engine overhaul, after a propeller strike, sudden stoppage, or whenever gear train repair is required. A propeller strike for the purpose of this AD, is defined as a sudden engine stoppage, or loss of a propeller blade or tip. NOTE: Avco Lycoming Service Letter No. L163B dated December 23, 1977, "Recommendations Regarding Accidental Engine Stoppage, Loss of Propeller Blade or Tip," contains additional information on the subject. To prevent loosening or failure of the crankshaft gear retaining bolt, which may cause sudden engine failure, accomplish the following: (a) Inspect the crankshaft counterbored recess, the alignment dowel, the retaining bolt and lock plate, the bolt hole threads, and the crankshaft gear for wear, galling, corrosion, and fretting in accordance with Sections 1 through 7, including all tables and figures in Textron Lycoming Service Bulletin (SB) No. 475, Revision A, dated July 16, 1990. (b) Prior to further flight, repair, rework, or replace damaged or worn parts as identified in paragraph (a) of this AD. (1) Repair and rework crankshaft pilot diameter in accordance with Textron Lycoming SB 475, Revision A, dated July 16, 1990, and replace dowel pin with appropriate size dowel as shown in Table 1 of the service bulletin. (2) Insure that the tapped threads in the gear retaining bolt hole of the crankshaft are clean and undamaged. If threads are damaged, replace crankshaft with a serviceable unit, or have threads repaired by an FAA approved facility specifically approved to do that repair. (3) Inspect the counterbored gear mounting face of the crankshaft to ensure there is no damage due to fretting or galling, as damageof this nature is unrepairable. (4) Repair crankshaft counterbore pilot diameter, if necessary, in accordance with Section 3 of Textron Lycoming SB No. 475, Revision A, dated July 16, 1990. (5) Verify that the crankshaft gear incorporates three .75 inch radius scallops on the flange as shown in Figure 5 of Textron Lycoming SB No. 475, Revision A, dated July 16, 1990. Assemble gear onto crankshaft using a new retaining bolt and lockplate and insure fit of mating parts as described in Section 6 and Figure 6 of the Textron Lycoming Service Bulletin No. 475, Revision A, dated July 16, 1990. (c) Aircraft maybe ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate), an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, New York Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. The inspection procedures shall be done in accordance with the following Textron Lycoming document: DOCUMENT NO. PAGE NO. ISSUE/REV. DATE SB 475 1-4 A 07/16/90 This incorporation by reference 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 Textron Lycoming, Oliver Street, Williamsport, Pennsylvania 17701. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. This amendment (39-6916, AD 91-14-22) becomes effective on August 19, 1991.
98-12-34: This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model CN-235 series airplanes, that requires modification of the forward beam of the vertical stabilizer by the installation of a structural reinforcement plate. 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 in-flight structural deformation or failure of the vertical stabilizer, resulting in reduced controllability of the airplane.
89-16-11: 89-16-11 BOEING: Amendment 39-6289. \n\n\tApplicability: All Model 767 series airplanes, identified in Boeing Alert Service Bulletin 767-25A0109, Revision 1, dated April 27, 1989, listed in Group 1 on which Boeing Service Bulletin 767-25-0036 has been accomplished, and airplanes listed in Group 2, certificated in any category. \n\n\tCompliance: Required within 18 months after the effective date of this AD, unless previously accomplished. \n\n\tTo ensure that the escape slide will deploy properly, accomplish the following: \n\n\tA.\tReplace the upper door liner pivot bolts, in accordance with Boeing Alert Service Bulletin 767-25A0109, Revision 1, dated April 27, 1989. \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 documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6289, AD 89-16-11) becomes effective on September 7, 1989.