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DGAC Airworthiness Directive - A300 Autopilot Discrepancy |
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[4910-13-U] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [64 FR 43061 No. 152 08/09/99] [Docket No. 99-NM-189-AD, Amendment 39-11249, AD 99-16-14] RIN 2120-AA64 Airworthiness Directives; Airbus Model A300, A310, and A300-600 Series Airplanes AGENCY: Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. SUMMARY: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A300, A310, and A300-600 series airplanes. This action requires a one-time inspection of the autopilot systems for proper engagement to determine if the main electro valve electrical connectors of the yaw, roll, and pitch autopilot actuators are correctly installed; and corrective actions, if necessary. 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 prevent erratic movements of the ailerons, elevator, and/or rudder that are commanded by discrepant autopilot actuators, which could result in reduced controllability of the airplane. DATES: Effective August 24, 1999. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of August 24, 1999. Comments for inclusion in the Rules Docket must be received on or before September 8, 1999. ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 99-NM-189-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Comments may be inspected at this location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal holidays. The service information referenced in this AD may be obtained from Airbus Industrie, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149. SUPPLEMENTARY INFORMATION: The Direction Générale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, recently notified the FAA that an unsafe condition may exist on all Airbus Model A300, A310, and A300-600 series airplanes. One operator of an Airbus Model A300-600 reported high rudder forces and uncommanded rudder inputs during final approach. The uncommanded rudder inputs caused deflections of the rudder control surface resulting in yawing of the airplane. Investigation of the incident is ongoing, but preliminary results indicate that failure of both the main valve and the clutch valve of the autopilot yaw actuator can lead to the actuator generating uncommanded rudder deflections. The DGAC advises that the same autopilot actuator is used for roll and pitch control during autopilot operation, and this failure scenario can result in uncommanded deflections of the aileron and elevator control surfaces. Preliminary results of the investigation of the incident airplane’s autopilot yaw actuator indicate that the electrical connectors between the actuator’s two main valves and the airplane’s two flight control computers (FCC) were crossed between side 1 and side 2. This hidden failure in combination with a failure of the clutch valve resulted in the autopilot yaw actuator remaining engaged when the crew disconnected the autopilot, allowing the actuator to remain hydraulically pressurized and provide inputs to the rudder and the rudder pedals. This condition, if not corrected, could result in uncommanded deflections of the ailerons, elevator, and/or rudder, which could result in reduced controllability of the airplane. Explanation of Relevant Service Information Airbus Industrie has issued All Operator Telexes (AOT) A300-22A0114 (for Model A300 series airplanes), A310-22A2050 (for Model A310 series airplanes), and A300-600-22A6039 (for Model A300-600 series airplanes); each dated May 27, 1999. These AOT’s describe procedures for a one-time inspection of the autopilot systems for proper engagement to determine if the main electro valve electrical connectors of the yaw, roll, and pitch autopilot actuators are correctly installed. If autopilot systems 1 and 2 cannot be engaged, then the AOT’s describe a visual inspection of the main electro valve electrical connectors of all autopilot actuators to determine whether any electrical connection is incorrectly installed; and corrective action by restoring the correct installation, if necessary. The DGAC classified these AOT’s as mandatory and issued French airworthiness directive 1999-268-292(B), dated June 30, 1999; in order to assure the continued airworthiness of these airplanes in France. FAA's Conclusions These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. The FAA has examined the findings of the DGAC, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. Explanation of Requirements of Rule Since an unsafe condition has been identified that is likely to exist or develop on other airplanes of the same type design registered in the United States, this AD is being issued to prevent erratic movements of the ailerons, elevator, and/or rudder commanded by discrepant autopilot actuators, which could result in reduced controllability of the airplane. This AD requires accomplishment of the actions specified in the AOT’s described previously. Determination of Rule's Effective Date Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days. Comments Invited Although this action is in the form of a final rule that involves requirements affecting flight safety and, thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire. Communications shall identify the Rules Docket number and be submitted in triplicate to the address specified under the caption "ADDRESSES." All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed. Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report that summarizes each FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket. Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this rule must submit a self-addressed, stamped postcard on which the following statement is made: "Comments to Docket Number 99-NM-189-AD." The postcard will be date stamped and returned to the commenter. Regulatory Impact The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. The FAA has determined that this regulation is an emergency regulation that must be issued immediately to correct an unsafe condition in aircraft, and that it is not a "significant regulatory action" under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket. A copy of it, if filed, may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES." List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive:
The following Airworthiness Directive issued by the Federal Aviation Administration in accordance with the provisions of Title 14 of the Code of Federal Regulations (14 CFR) part 39, applies to an aircraft model of which our records indicate you may be the registered owner. Airworthiness Directives affect aviation safety and are regulations which require immediate attention. You are cautioned that no person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of the Airworthiness Directive (reference 14 CFR part 39, subpart 39.3). 99-16-14 AIRBUS INDUSTRIE: Amendment 39-11249. Docket 99-NM-189-AD. Issued July 30, 1999 Applicability: All Model A300, A310, and A300-600 series airplanes; certificated in any category. NOTE 1: This AD applies to each airplane 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 airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent erratic movements of the ailerons, elevator, and/or rudder that are commanded by discrepant autopilot actuators, which could result in reduced controllability of the airplane, accomplish the following: Inspection (a) Within 10 days after the effective date of this AD, perform a one-time inspection of the auto pilot systems for proper engagement to determine if the main electro valve electrical connectors of the yaw, roll, and pitch autopilot actuators are correctly installed, in accordance with the procedure specified in paragraph 4.2 of Airbus Industrie All Operators Telex (AOT) A300-22A0114 (for Model A300 series airplanes), A310-22A2050 (for Model A310 series airplanes), or A300-600-22A6039 (for Model A300-600 series airplanes); each dated May 27, 1999; as applicable. If autopilot systems 1 and 2 cannot be engaged: Prior to further flight, perform a detailed inspection of the main electro valve electrical connectors of the yaw, roll, and pitch autopilot actuators for proper installation, and correct any discrepancy; in accordance with paragraph 4.2 of the applicable AOT. NOTE 2: For the purposes of this AD, a detailed inspection is defined as: "An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc. may be used. Surface cleaning and elaborate access procedures may be required." Alternative Methods of Compliance (b) 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, International Branch, ANM-116, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116.NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. Special Flight Permits (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. Incorporation by Reference (d) The actions shall be done in accordance with Airbus All Operators Telex A300-22A0114, dated May 27, 1999; Airbus All Operators Telex A310-22A2050, dated May 27, 1999; and Airbus All Operators Telex A300-600-22A6039, dated May 27, 1999; as applicable. 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 Airbus Industrie, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. NOTE 4: The subject of this AD is addressed in French airworthiness directive 1999-288-292(B) dated June 30, 1999. (e) This amendment becomes effective on August 24, 1999. FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149.
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| Airworthiness Directive - Rudder Servo Spring Rods | |||||||||||||||||||||
| http://av-info.faa.gov/ad/NM00/00-02-24.html
[4910-13-U] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [65 FR 5243 2/3/2000] [Docket No. 99-NM-247-AD; Amendment 39-11542; AD 2000-02-24] RIN 2120-AA64 Airworthiness Directives; Airbus Model A300, A310, and A300-600 Series Airplanes AGENCY: Federal Aviation Administration, DOT. ACTION: Final rule. SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that requires either replacement of the spring rod assemblies of the rudder servo controls with improved spring rod assemblies; or modification of the existing spring rod assemblies. For certain airplanes, this amendment requires a one-time visual inspection to determine whether certain parts of the spring rod assemblies of the rudder servo controls are installed; and corrective actions, if necessary. 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 corrosion of the spring rod assemblies of the rudder servo controls, which could result in the jamming of the rudder servo controls and consequent reduced controllability of the airplane. DATES: Effective March 9, 2000. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of March 9, 2000. ADDRESSES: The service information referenced in this AD may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Airbus Model A300, A310, and A300-600 series airplanes was published in the Federal Register on November 4, 1999 (64 FR 60138). That action proposed to require either replacement of the spring rod assemblies of the rudder servo controls with improved spring rod assemblies; or modification of the existing spring rod assemblies. For certain airplanes, that action proposed to require a one time visual inspection to determine whether certain parts of the spring rod assemblies of the rudder servo controls are installed; and corrective actions, if necessary. Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA's determination of the cost to the public. French Airworthiness Directive Revision Since issuance of the proposed AD, the Direction Générale de l'Aviation Civile (DGAC), which is the airworthiness authority for France, has revised the corresponding French airworthiness directive. The DGAC issued 1999-240-288(B) R1, dated December 15, 1999, to provide operators with an exhaustive list of appropriate part numbers (P/N) for rudder servo control input spring rod assemblies. The FAA has reviewed this information and has determined that paragraphs (b)(1) and (b)(2) of the proposed AD should be revised to include an additional part number. These paragraphs specify acceptable spring rod assemblies as those having either P/N A2727086500400 or A2727086500600. However, P/N A2727114900000 also is acceptable for installation. Paragraphs (b)(1) and (b)(2) of the AD have been revised to include this P/N. Conclusion After careful review of the available data, the FAA has determined that air safety and the public interest require the adoption of the rule with the change described previously. The FAA has determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Cost Impact The FAA estimates that 156 airplanes of U.S. registry will be affected by this AD. If an operator elects to replace the spring rod assemblies: It will take approximately 4 work hours per airplane to accomplish the replacement, at an average labor rate of $60 per work hour. Required parts will cost approximately $3,720 per airplane. Based on these figures, the cost impact of the replacement on U.S. operators is estimated to be $3,960 per airplane. If an operator elects to modify the spring rod assemblies: It will take approximately 7 work hours per airplane to accomplish the modification, at an average labor rate of $60 per work hour. Required parts will cost approximately $294 per airplane. Based on these figures, the cost impact of the modification on U.S. operators is estimated to be $714 per airplane. If an operator is required to accomplish the one-time inspection: It will take approximately 1 work hour per airplane to accomplish that inspection, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the inspection on U.S. operators is estimated to be $60 per airplane. The cost impact figures discussed above are based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. Regulatory Impact The regulations adopted herein will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132. For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES." List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive:
The following Airworthiness Directive issued by the Federal Aviation Administration in accordance with the provisions of Title 14 of the Code of Federal Regulations (14 CFR) part 39, applies to an aircraft model of which our records indicate you may be the registered owner. Airworthiness Directives affect aviation safety and are regulations which require immediate attention. You are cautioned that no person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the requirements of the Airworthiness Directive (reference 14 CFR part 39, subpart 39.3). 2000-02-24 AIRBUS INDUSTRIE: Amendment 39-11542. Docket 99-NM-247-AD. Applicability: Model A300, A310, and A300-600 series airplanes; certificated in any category; except those airplanes on which Airbus Modification 10438 has been installed, or on which Airbus Service Bulletin A300-27-0182, Revision 2, A300-27-6023, Revision 2, or A300-27-2065, Revision 2, each dated June 30, 1999, has been accomplished. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent corrosion of the spring rod assemblies of the rudder servo controls, which could result in the jamming of the rudder servo controls and consequent reduced controllability of the airplane, accomplish the following: (a) For airplanes on which the spring rod assemblies of the rudder servo controls have not been modified in accordance with Airbus Service Bulletin A300-27-182, dated March 16, 1995, or Revision 1, dated November 21, 1996 (for Model A300 series airplanes); A310-27-2065, dated March 16, 1995, or Revision 1, dated March 10, 1997 (for Model A310 series airplanes); or A300-27-6023, dated March 16, 1995, or Revision 1, dated March 10, 1997 (for Model A300-600 series airplanes); as applicable; as of the effective date of this AD: Within 1 year after the effective date of this AD, accomplish the actions specified in either paragraph (a)(1) or (a)(2) in accordance with Airbus Service Bulletin A300-27-182, Revision 2 (for Model A300 series airplanes); or A310-27-2065, Revision 2 (for Model A310 series airplanes); or A300-27-6023, Revision 2 (for Model A300-600 series airplanes); each dated June 30, 1999; as applicable.
(b) For airplanes on which the spring rod assemblies of the rudder servo controls have been modified in accordance with Airbus Service Bulletin A300-27-182, dated March 16, 1995, or Revision 1, dated November 21, 1996 (for Model A300 series airplanes); or A310-27-2065, dated March 16, 1995, or Revision 1, dated March 10, 1997 (for Model A310 series airplanes); or A300-27-6023, dated March 16, 1995, or Revision 1, dated March 10, 1997 (for Model A300-600 series airplanes); as applicable; as of the effective date of this AD: Within 1 year after the effective date of this AD, perform a one-time visual inspection to verify that all spring rod assemblies of the rudder servo controls have the same part numbers, in accordance with Airbus Service Bulletin A300-27-182, Revision 2 (for Model A300 series airplanes); or A310-27-2065, Revision 2 (for Model A310 series airplanes); or A300-27-6023, Revision 2 (for Model A300-600 series airplanes); each dated June 30, 1999; as applicable.
(c) As of the effective date of this AD, no person shall install on any airplane a spring rod assembly having P/N A2727086500200. Alternative Methods of Compliance (d) 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, International Branch, ANM-116, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. Special Flight Permits (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. Incorporation by Reference (f) The actions shall be done in accordance with Airbus Service Bulletin A300-27-182, Revision 2, dated June 30, 1999; Airbus Service Bulletin A310-27-2065, Revision 2, dated June 30, 1999; or Airbus Service Bulletin A300-27-6023, Revision 2, dated June 30, 1999; as applicable. Airbus Service Bulletin A300-27-6023, Revision 2, dated June 30, 1999, contains the following list of effective pages:
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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. NOTE 3: The subject of this AD is addressed in French airworthiness directives 1999-240-288(B), dated June 30, 1999, and 1999-240-288(B) R1, dated December 15, 1999. (g) This amendment becomes effective on March 9, 2000. FOR FURTHER INFORMATION CONTACT: Issued in Renton, Washington, on January 25, 2000.
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| Rudder Servo Control Desynchronisation | |||||||||||||||||||||
Airbus Industrie A300 & A310 Series Aeroplanes
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