Results
2008-24-12: We are adopting a new airworthiness directive (AD) for the products listed above. 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: During scheduled maintenance inspection, a bolt which connects the PCU (power control unit) to the elevator surface was found fractured in the assembly. Further inspection of the assembly revealed that the bearing on the PCU rod end had seized, which resulted in damage to the attachment fitting bushing and fracture of the bolt. Inspection of other in-service airplanes revealed two more seized PCU attachment joints. However, except seizure, no fractured bolt was found on these airplanes. Failure of the bolts in both PCUs on one side could result in disconnection of the elevator control surface which would lead to flutter and loss of the aircraft. * * ** * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2008-24-08: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800 and -900 series airplanes. This AD requires an inspection of the escape slides for the forward and aft entry and service doors to determine the part number and service bulletin number stenciled on the escape slide girt, and modification of the escape slide assemblies. This AD also requires concurrent modification of the escape slide latch assemblies; concurrent inspection of the escape slides to determine the part number and service bulletin number stenciled on the escape slide girts, and replacement of the trigger housing on the regulator valve with an improved trigger housing if necessary; and concurrent replacement of the rod in the pilot valve regulator with a new, improved rod; as applicable. This AD results from reports that certain escape slides did not automatically inflate when deployed or after the manual inflation cable was pulled. We are issuing this AD to preventfailure of an escape slide to inflate when deployed, which could result in the slide being unusable during an emergency evacuation and consequent injury to passengers or crewmembers.
83-26-03: 83-26-03 BF GOODRICH: Amendment 39-4811. Applies to the following aircraft tires: \n\n\t1.\t17.5x5.75-8, 12PR, 210MPH, P/N 038-627, S/N 3224A-XXXXX, and \n\n\t2.\t18x5.5, 10PR, 210MPH, P/N 033-631, S/N 3215A-XXXXX through 3217A-XXXXX. \n\n\tThese tires are eligible for, but not limited to use on, all Gates Learjet models and Fairchild Swearingen Model SA226-TC airplanes. \n\n\tCompliance: Required prior to next takeoff, unless already accomplished. \n\n\tTo avoid tread loss and possible subsequent tire failure, accomplish the following: \n\n\tRemove the applicable part number and serial number BF Goodrich tires from the aircraft and either destroy them or return them to BF Goodrich for destruction. Cutting the tire carcass is an approved means of destruction. \n\n\tNOTE: The serial numbers of the tires are interpreted as follows: \n\n\n\n\t\n\tThis amendment becomes effective on February 21, 1984, to all persons except those to whom it has already been made effective by priority letter from the FAA dated December 23, 1983, and is identified as AD 83-26-03.
85-03-07: 85-03-07 AIRBUS INDUSTRIE: Amendment 39-4999. Applies to Model A300 B2 and B4 series airplanes, serial numbers as listed in the Airbus Industrie Service Bulletin A300-28-039, Revision 2, dated December 17, 1981, certificated in all categories. To prevent rupture of the feeder fuel lines located inside the engine pylons, accomplish the following, unless previously accomplished: A. Prior to the accumulation of 4,000 hours total time in service or within the next 120 days after the effective date of this AD, whichever occurs later, install an additional clamp on the feeder fuel line located inside each engine pylon in accordance with the accomplishment instructions of the service bulletin. 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 March 11, 1985.
2008-22-09: We are adopting a new airworthiness directive (AD) for all Boeing Model 747SP series airplanes. This AD requires repetitive lubrication of the rudder tab hinges and repetitive replacement of the rudder tab control rods. This AD results from reports of freeplay- induced vibration on the control surfaces on Boeing Model 727, 737, 757, and 767 airplanes. We are issuing this AD to prevent damage to the control surface structure during flight, which could result in loss of control of the airplane.
2008-09-06: We are adopting a new airworthiness directive (AD) for the products listed above. 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: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, * * * Special Federal Aviation Regulation 88 (SFAR88) * * * required a safety review of the aircraft Fuel Tank System * * *. * * * * * Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an `unsafe condition' * * *. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers' requirements. We are issuing this AD to require actionsto correct the unsafe condition on these products.
2008-22-24: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 series turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections of installed low pressure compressor (LPC) fan blade roots on-wing and during overhaul, and relubrication according to accumulated life cycles. Also, that AD introduces application of Metco 58 blade root coating as an optional terminating action. This AD requires the same actions but adds compliance paragraphs to relax the compliance schedule for repetitive inspections for fan blades operating within RB211-535E4 flight profiles A and B, if certain requirements are met. This AD also relaxes the initial compliance threshold by extending the cycles at which an initial inspection is required. This AD results from RR issuing Mandatory Service Bulletin (MSB) No. RB.211-72-C879, Revision 5 and Revision 6, that introduced a relaxed repetitive compliance schedule for fan blades operating within RB211-535E4 flight profiles A and B, if certain requirements are met, and introduced a relaxed initial compliance threshold. We are issuing this AD to detect cracks in LPC fan blade roots, which if not detected, could lead to uncontained multiple fan blade failure, and damage to the airplane.
87-06-05: 87-06-05 MCDONNELL DOUGLAS: Amendment 39-5572. Applies to McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) series airplanes, certificated in any category, equipped with Aircraft Mechanics, Inc., crew seats model numbers, 1056, 1057, and 1058, having serial numbers 001 through 907 and 911. Compliance required as indicated, unless previously accomplished. \n\n\tTo preclude the potential of damage to crew seat life vests, accomplish the following: \n\n\tA.\tWithin 12 months after the effective date of this AD, inspect the life vest. If any signs of chafing are found, replace before further flight with a serviceable unit. \n\n\tB.\tWithin 12 months after the effective date of this AD, modify the crew seat in accordance with the accomplishment instructions of Aircraft Mechanics, Inc., Service Bulletin 25-DC-10/678-24, dated May 20, 1984, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.C.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\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 McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-L65 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis Amendment becomes effective April 2, 1987.
87-18-10: 87-18-10 INTREPRINDEREA DE CONSTRUCTII AERONAUTICE: Amendment 39- 5695. Applies to Model IS-28B2 gliders through serial number 160 inclusive certificated in any category. Compliance is required as indicated unless already accomplished. To prevent the failure of the aileron control levers and forks which could result in the glider becoming uncontrollable, accomplish the following: (a) Within the next 5 hours time-in-service after the effective date of this AD unless compliance with paragraph (c) has been accomplished, visually inspect the aileron control levers P/N 30AD.02.028 and aluminum NIA 181-2 forks using a 10 power or greater magnifying glass for cracks or deformation. (b) If a cracked or deformed part is found during the inspection required by paragraph (a) of this AD, before further flight, replace the aileron control levers and forks with serviceable levers and forks, new design P/N 30AD.02.028 lever and steel NIA 201-2 fork, in accordance with the accomplishment instructions of Intreprinderea De Constructii Aeronautice Service Bulletin No. IS-28B2-E0-14, dated August 20, 1985. NOTE: The manufacturer has assigned the same part number to the new design aileron lever as the original design aileron lever. The new lever can be identified by measuring the length of the section which is reduced in thickness on the longer arm of the aileron lever. The new design aileron lever is reduced in thickness 42mm from the end of the longer arm whereas the old design aileron lever is reduced in thickness 27mm from the end of the longer arm. (c) Prior to September 30, 1987, replace any aileron control system levers and forks not replaced in accordance with paragraph (b) of this AD, with serviceable levers and forks, new design P/N 30AD.02.028 lever and steel NIA 201-2 fork, in accordance with Intreprinderea De Constructii Aeronautice Service Bulletin No. IS-28B2-E0-14 dated August 20, 1985. NOTE: The aileron levers removed from service should be destroyed or disfigured to prevent reuse. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, Federal Aviation Administration, c/o American Embassy, 15 Rue de la Loi B-1040, Brussels, Belgium; telephone 513.38.30 ext. 2710, or the Manager, Federal Aviation Administration, New England Region, Aircraft Certification Division, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone 516-791-6680. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office, or the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD. Intreprinderea De Constructii Aeronautice Service Bulletin No. IS-28B2-E0-14, dated August 20, 1985, 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 Sprague Aviation Incorporated, 699 Linwood, Vacaville, California 95688. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, Rules Docket 87-ANE-01 between the hours of 8:00 a.m. and 4:30 p.m.; Monday thru Friday, except federal holidays. This amendment becomes effective on September 3, 1987.
89-20-01 R1: 89-20-01 R1 GENERAL ELECTRIC COMPANY: Amendment 39-6337 as revised by Amendment 39-6411. Applicability: General Electric Company (GE) CF6-6 series turbofan engines installed in McDonnell Douglas DC10-10 aircraft. Compliance: Required as indicated, unless already accomplished. To detect the existence of metallurgical imperfections in Stage 1 fan disks which could adversely affect Stage 1 fan disk service life, ultrasonic inspect all Stage 1 fan disks in accordance with the Appendix to this AD, and the following schedule: (a) All Stage 1 fan disks with those serial numbers listed in TABLE 1 of this AD, immersion ultrasonic inspect no later than October 27, 1989. (b) All Stage 1 fan disks identified by those serial numbers listed in TABLE 2 of this AD, as follows: (1) Remove fan rotor spinner cone and contact ultrasonic inspect the installed fan disk no later than November 21, 1989. (2) Immersion ultrasonic inspect within the next 500 cycles in service after accomplishing the contact ultrasonic inspection requirements of paragraph (b)(1) above, or at the next shop visit after October 7, 1989, or no later than April 1, 1990, whichever comes first. (c) All Stage 1 fan disks identified by serial numbers listed in TABLE 3 of this AD, as follows: (1) Remove fan rotor spinner cone and contact ultrasonic inspect the installed fan disk no later than February 4, 1990, and reinspect at intervals not to exceed 500 cycles since the last contact ultrasonic inspection until the immersion ultrasonic requirement of paragraph (c)(2) has been accomplished. (2) Immersion ultrasonic inspect at the next shop visit after October 7, 1989, but no later than December 31, 1990. (d) All Stage 1 fan disks identified by those serial numbers listed in TABLE 2A of this AD, as follows: (1) Remove fan rotor spinner cone and contact ultrasonic inspect the installed fan disk no later than January 23, 1990. (2) Immersion ultrasonic inspect within the next 500 cycles in service after accomplishing the contact ultrasonic inspection requirements of paragraph (d)(1) above, or at the next shop visit after December 12, 1989, or no later than June 5, 1990, whichever comes first. (e) All Stage 1 fan disks identified by serial numbers listed in TABLE 3A of this AD, as follows: (1) Remove fan rotor spinner cone and contact ultrasonic inspect the installed fan disk no later than April 10, 1990, and reinspect at intervals not to exceed 500 cycles since the last contact ultrasonic inspection until the immersion ultrasonic requirement of paragraph (e)(2) has been accomplished. (2) Immersion ultrasonic inspect at the next shop visit after December 12, 1989, but no later than March 5, 1991. NOTES: (1) Disks which have been previously immersion ultrasonic inspected in accordance with GE Commercial Engine Memorandum No. 98, Rev. 2, dated October 5, 1989, are considered to be in compliance with the immersion ultrasonic inspection requirements of paragraphs (a), (b), (c), (d), and (e) above. (2) For the purpose of this AD, "shop visit" is defined as the induction of the engine into the shop for any reason. (3) Accomplishment of the immersion ultrasonic inspection requirements of paragraphs (b)(2), (c)(2), (d)(2), and (e)(2) above relieves the requirements for contact ultrasonic inspections of paragraphs (b)(1), (c)(1), (d)(1), and (e)(1) above. (f) Remove from service, prior to further flight, fan disks inspected in accordance with paragraphs (a), (b), (c), (d), and (e) which do not meet the acceptance criteria of the Appendix to this AD and replace with a serviceable part. Report all inspection findings in writing within 10 days of the inspection to the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, 12 New England Executive Park, Burlington, Massachusetts, 01803; Telex No. 949301 FAANE BURL. Information collection requirements contained in this regulation (Section 39.13) have been approved by the Office of Management and Budget under the provisions of the Paperwork Reduction Act of 1980 (Pub. L. 96- 511) and have been assigned OMB Control Number 2120-0056. (g) 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. (h) 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 schedules specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. TABLE 1 MP000382 MP000383 MP000384 MP000386 MP000387 MP000388 TABLE 2 MP000352 MP000363 MP000374 MP000390 MP000407 MP0A0117 MP000354 MP000364 MP000375 MP000393 MP000411 MP0A0133 MP000357 MP000365 MP000376 MP000395 MP0A0108 MP0A0136 MP000358 MP000368 MP000377 MP000397 MP0A0109 MP0A0140 MP000359 MP000370 MP000378 MP000398 MP0A0110 MP0A0141 MP000360 MP000371 MP000379 MP000399 MP0A0111 MP0A0142 MP000361 MP000372 MP000380 MP000402 MP0A0112 MP0A0143 MP000362 MP000373 MP000389 MP000404 MP0A0113 MP0A0145 MP0A0115 TABLE 2A MP0A0135 MP0A0182 TABLE 3 MP000150 MP000188 MP000222 MP000251 MP000284 MP000319 MP000151 MP000189 MP000223 MP000253 MP000285 MP000320 MP000152 MP000190 MP000224 MP000254 MP000286 MP000321 MP000153 MP000191 MP000225 MP000255 MP000289 MP000322 MP000154 MP000193 MP000226 MP000257 MP000290 MP000323 MP000155 MP000194 MP000228 MP000258 MP000291 MP000325 MP000156 MP000195 MP000229 MP000260 MP000292 MP000326 MP000158 MP000196 MP000230 MP000263 MP000293 MP000331 MP000159 MP000197 MP000231 MP000264 MP000295 MP000334 MP000160 MP000198 MP000232 MP000265 MP000297 MP000336 MP000161 MP000199 MP000233 MP000266 MP000298 MP000337 MP000162 MP000200 MP000234 MP000267 MP000299 MP000338 MP000163 MP000204 MP000235 MP000268 MP000300 MP000339 MP000168 MP000205 MP000236 MP000270 MP000302 MP000340 MP000171 MP000206 MP000237 MP000271 MP000303 MP000341 MP000172 MP000207 MP000238 MP000272 MP000304 MP000342 MP000173 MP000208 MP000240 MP000273 MP000305 MP000343 MP000175 MP000209 MP000241 MP000274 MP000308 MP000346 MP000177 MP000212 MP000243 MP000276 MP000311 MP000348 MP000178 MP000213 MP000244 MP000277 MP000312 MP000349 MP000179 MP000214 MP000245 MP000278 MP000313 MP000350 MP000180 MP000215 MP000246 MP000279 MP000314 MP0A0137 MP000181 MP000216 MP000247 MP000280 MP000315 MP0A0139 MP000182 MP000217 MP000248 MP000281 MP000316 MP0A0207 MP000184 MP000218 MP000249 MP000282 MP000317 MP0A0439 MP000185 MP000219 MP000250 MP000283 MP000318 MP000186 MP000220 MP000187 MP000221 TABLE 3A MP000618 MP000139 MP000103 MP000011 MP0C2744 MP0A0376 MP000436 MPOOO136 MP000102 MP000010 MP0C0321 MP0A0291 MP000353 MP000113 MP000078 MP000009 MP0A0880 MP0A0284 MP000351 MP000111 MP000016 MP000005 MP0A0810 MP0A0206 MP000294 MP000109 MP000015 MP000004 MP0A0801 MP0A0200 MP000174 MP000108 MP000014 MP000003 MP0A0736 MP0A0139 MP000149 MP000107 MP000013 MP000002 MP0A0662 MP0A0138 MP000141 MP000104 MP000012 MP0H3844 MP0A0481 MP0G2753 The ultrasonic inspections shall be done in accordance with the Appendix to this AD. This AD revises Amendment 39-6337 (54 FR 38814; September 21, 1989), AD 89-20-01, which became effective on October 7, 1989. This amendment (39-6411, AD 89-20-01 R1) becomes effective on December 12, 1989. 89-20-01 R1 Appendix The applicable General Electric Service Bulletin (CF6-6) 72-947, Revision 2, dated November 21, 1989, and the following General Electric Manufacturing and Field Quality Procedures may be obtained from General Electric Company, Technical Publications Department, 1 Neuman Way, Cincinnati, Ohio 45215, or may be examined in the Regional Rules Docket (Docket #89-ANE-35), FAA, New England Region, Office of Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803. (A) General Electric Manufacturing and Field Quality Technology Procedure No. 391, issued September 15, 1989, Rev. 1, dated September 28, 1989. (B) General Electric Manufacturing and Field Quality Technology Procedure No. 384, issued September 15, 1989, Rev. 2, dated October 5, 1989. (C) General Electric Manufacturing and Field Quality Technology Procedure No. 385, issued September 14, 1989, Rev. 2, dated October 5, 1989. (D) General Electric Manufacturing and Field Quality Technology Procedure No. 389, issued September 14, 1989, Rev. 2, dated October 3, 1989.
2008-22-02: We are adopting a new airworthiness directive (AD) for Maryland Air Industries, Inc., Model Fairchild F-27 and FH-227 Series Airplanes. This AD requires operators to modify their airplanes and revise their inspection or maintenance programs to incorporate instructions for maintenance and inspection of the fuel tank systems, as appropriate, by December 16, 2008, using information developed in accordance with Special Federal Aviation Regulation 88 (SFAR 88). This AD results from fuel system safety reviews done on similar airplane models in accordance with SFAR 88. These safety reviews identified potential unsafe conditions on Model Fairchild F-27 and FH-227 series airplanes for which the type certificate holder, Maryland Air Industries, Inc., has not conducted SFAR 88 safety reviews, has not provided corrective actions, and does not plan to do so. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2000-23-06: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that requires replacement of defective hydraulic tubing in the left and right wings with new hydraulic tubing. 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 the loss of hydraulic pressure which could result in reduced controllability of the airplane.
82-15-01 R1: 82-15-01 R1 HUGHES HELICOPTERS: Amendment 39-4414 as amended by Amendment 39-4463. Applies to Model 269A (all S/N's), TH-55A (all S/N's converted to civil use), 269A-1 (all S/N's), 269B (all S/N's), and 269C (S/N's 0001 through 1074) helicopters equipped with main transmission assemblies P/N 269A5175-7, -9, -11, -13, -15, and -17, except those transmissions with the letter "W" on the transmission nameplate below and adjacent to the transmission serial number. Applies to helicopters certificated in all categories. Compliance is required as indicated unless already accomplished. To prevent failure of the main transmission, accomplish the following: (a) Within 50 hours' additional time in service after the effective date of this AD, disassemble the transmission and inspect the ring gear/carrier interface and attachment bolts for possible fretting or cracking, and rework in accordance with Service Information Notice N-181, paragraphs a. through j., or later FAA approvedequivalent. All parts that cannot be reworked within the criteria of Service Information Notice N-181 are considered unairworthy and must be replaced with like serviceable parts. NOTE: Those portions of Service Information Notice N-181 which address disposition of parts which exceed the prescribed inspection and rework criteria are not applicable. (b) Reassemble the transmission in accordance with Service Information Notice N- 181, paragraphs k. through o., or FAA approved equivalent. (c) Special flight permits may be issued in accordance with Sections 21.197 and 21.199 of the Federal Aviation Regulations to operate aircraft to a base for the accomplishment of inspections or modifications 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, Aircraft Certification Field Office, FAA Northwest Mountain Region, 15000 Aviation Boulevard, Room 5W26, Hawthorne, California. Amendment 39-4414 became effective July 12, 1982. This Amendment 39-4463 becomes effective October 4, 1982.
2008-21-02: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 737-600, -700, and -800 series airplanes. That AD currently requires repetitive inspections to detect damage of the aft strut insulation blanket, and eventual replacement of the insulation blankets with new, improved blankets. This new AD adds airplanes to the applicability and requires installation of a new heat insulation blanket and new cover plate on the left and right side engine struts. This new AD does not retain the requirements of the existing AD but does terminate the requirements of the existing AD. This AD results from reports of damaged heat insulation blankets on the engine struts. We are issuing this AD to prevent exposure of the lower surface of the strut to extreme high temperatures, consequent creation of a source of fuel ignition, and increased risk of an uncontrollable fire and possible fuel tank explosion.
82-24-06 R1: 82-24-06 R1 BRITTEN-NORMAN: Amendment 39-4506 as amended by Amendment 39- 4559. Applies to Models BN-2, BN-2A, BN-2A-6, BN-2A-8, BN-2A-9, BN-2A-26, BN-2A-27, BN2A MKIII, BN2A MKIII-2, and BN2A MKIII-3 (all serial numbers) airplanes certificated in any category. COMPLIANCE: Required as indicated unless already accomplished. To prevent possible failure of the carburetor air box shutter, accomplish the following: (a) Within the next 100 hours time-in-service after the effective date of this AD and at intervals not exceeding 100 hours time-in-service thereafter: (1) Visually inspect the carburetor air box shutters for cracks or excessive bolt hole wear in accordance with procedures set forth in the "Inspection" section of Pilatus Britten-Norman Limited Service Bulletin Number BN-2/SB.144, Issue: 1, dated July 10, 1980 (hereinafter referred to as the service bulletin). (A) Prior to further flight, replace any carburetor air box shutter found cracked with newshutter in accordance with "Rectification" section of the service bulletin. (B) If excessive bolt hole wear is found prior to further flight, modify the shutter in accordance with the "Rectification" section of the service bulletin. (b) On or before November 1, 1983, replace or modify the air box shutter in accordance with paragraph (a)(1)(A) or (a)(1)(B) of this AD. (c) The inspection required by paragraph (a) (1) may be discontinued when the modifications or replacements prescribed in paragraphs (a)(1)(A) and (a)(1)(B) of this AD are accomplished. (d) The airplane may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. Amendment 39-4506 became effective on December 2, 1982. This Amendment 39-4559 becomes effective February 7, 1983.
2008-20-03: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Fokker Model F.28 Mark 0070 and 0100 airplanes. That AD currently requires a one-time inspection of the main landing gear (MLG) main fitting for cracks, and repair if necessary. The existing AD also currently requires installing a placard and revising the airplane flight manual to include procedures to prohibit the application of brakes during backward movement of the airplane. This new AD requires repetitive eddy current inspections of the MLG main fitting and rework before further flight as applicable. This AD results from reports that a final solution eliminating the cause of the crack initiation mechanism is not yet available and that repetitive inspections are necessary. We are issuing this AD to detect and correct cracks in the MLG main fitting, which could result in reduced structural integrity of the MLG main fitting. DATES: This AD becomes effective November 3, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of November 3, 2008. On April 26, 2006 (71 FR 14363, March 22, 2006), the Director of the Federal Register approved the incorporation by reference of Messier-Dowty Service Bulletin F100-32-106, including Appendices A through C and excluding Appendix D, dated February 18, 2005.
82-22-03: 82-22-03 EAGLE: Amendment 39-4479. Applies to all Model DW-1 airplanes certificated in any category. COMPLIANCE: Required as indicated, unless already accomplished. To prevent loss of elevator control due to failure of the aft elevator push tube, accomplish the following: a) Within 25 hours after the effective date of this AD on airplanes having 400 or more hours time-in-service or prior to the accumulation of 425 hours time-in-service on airplanes with less than 400 hours time-in-service and each 400 hours time-in-service thereafter: (1) Replace the existing Aft Elevator Push Tube Assembly (P/N 162000-16) with a new (zero service time) Aft Elevator Push Tube Assembly P/N 162000-29 in accordance with Eagle Aircraft Co. Service Letter No. 82-6 dated September 7, 1982. b) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. c) An equivalent method of compliance with this AD may be used if approved by theChief, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018, telephone (312) 694-7357. This amendment becomes effective on November 1, 1982.
2008-18-09: We are adopting a new airworthiness directive (AD) for certain Boeing Model 747 airplanes. This AD requires modification of the refuel valve control unit for the reserve fuel tanks. This AD also requires a revision to the FAA-approved maintenance program to incorporate airworthiness limitation (AWL) No. 28-AWL-20 or AWL No. 28-AWL-25, as applicable. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent lightning-induced electrical energy from entering a reserve fuel tank through the refuel valve, which could result in a fuel tank explosion and consequent loss of the airplane.
96-01-04 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to require verification that the auto-ignition system is operational; to define icing conditions at higher ambient temperatures; and to provide the flight crew with limitations and procedures to aid in the avoidance of engine power interruptions. The actions specified by that AD are intended to prevent failure of the auto-ignition system to re-light the engine in the event of power interruptions due to the ingestion of ice and/or slush into the engine, which could result in engine flameout and subsequent shutdown, and to provide the flight crew with guidance to aid in avoidance of such occurrences. This amendment clarifies certain requirements of the AFM revision. This amendment is prompted by communications received from affected operators that certain of the currentrequirements of the AD are unclear.
84-10-07: 84-10-07 GULFSTREAM AEROSPACE CORPORATION (AERO COMMANDER): Amendment 39-4868. Applies to Models 680T, 680V, and 680W (S/N's 1473 through 1850) and Model 681 (S/N's 6001 through 6017, 6020 through 6038, 6040 through 6042, and 6048) airplanes certificated in any category unless Service Bulletin 102 dated March 1, 1971, or Service Bulletin 102A dated September 1, 1983, has previously been accomplished. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD unless already accomplished. To assure proper operation of the emergency landing gear extension system, accomplish the following: (a) Modify the emergency landing gear extension system in accordance with Gulfstream Aerospace Corporation, Commander Division, Service Bulletin 102A, dated September 1, 1983. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent method of compliance with this AD may be used ifapproved by the Manager, Airplane Certification Branch, ASW-150, FAA, Southwest Region, P.O. Box 1689, Fort Worth, Texas 76101. This amendment becomes effective on June 23, 1984.
2008-17-10: We are adopting a new airworthiness directive (AD) for certain Boeing Model 707 airplanes, and Model 720 and 720B series airplanes. This AD requires repetitive detailed inspections to detect cracks and corrosion on any existing repairs and at certain body stations of the visible surfaces of the wing to body terminal fittings including the web, flanges, and ribs; and applicable related investigative and corrective actions. This AD results from reports of cracks found in the wing to body terminal fittings during routine inspections. We are issuing this AD to prevent cracks and corrosion in the body terminal fittings, which could cause loss of support for the wing and could adversely affect the structural integrity of the airplane.
86-02-01: 86-02-01 BOEING: Amendment 39-5214. Applies to Model 767 airplanes, as listed in Boeing Service Bulletin 767-52-0041, dated December 13, 1985, certificated in any category. Compliance is required within 30 days after the effective date of this AD. To ensure proper door opening, accomplish the following, unless already accomplished: \n\n\tA.\tInspect all entry/service door operating mechanisms for integrity of the upper and lower pushrod installations and repair, if necessary, in accordance with Boeing Service Bulletin 767-52-0041 dated December 13, 1985, or later FAA-approved revisions. \n\n\tB.\tAlternate 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. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this AD who have not already received copies of the service bulletin cited herein may obtain copies upon request from the Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis Amendment becomes effective February 3, 1986.
2008-17-09: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: A rupture of the alternator and vapour cycle cooling system pulley drive assembly has reportedly been found. Such a failure could lead to the loss of the alternator and vapour cycle cooling systems and could also cause mechanical damage inside the powerplant compartment. We are issuing this AD to require actions to correct the unsafe condition on these products.
82-01-08: 82-01-08 HUGHES HELICOPTERS: Amendment 39-4292. Applies to Model 369 Series helicopters, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent loss of control of engine power due to control rod failure, accomplish the following: (a) Within 25 hours' additional time in service after the effective date of this AD, remove P/N 369A7706-3 RPM Governor Lever Control Rod and replace with P/N 369A7706-5 RPM Governor Lever Control Rod. NOTE: Hughes Helicopters Notice No. DN-87 and HN-169, dated May 15, 1981, refers to this subject. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate helicopters to a base for the accomplishment of inspections or modifications 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-Pacific Region. This amendment becomes effective January 7, 1982.
2008-16-01: The FAA is adopting a new airworthiness directive (AD) for GE CF34-8E series turbofan engines with certain part number (P/N) full authority digital engine controls (FADECs) installed. This AD requires reprogramming the FADEC software from version 8Ev5.40 to an FAA- approved software version. This AD results from six loss of thrust control events from the same software fault scenario. We are issuing this AD to prevent loss of thrust control and controllability of the airplane.