Federal Aviation Administration, DOT.
Notice of proposed rulemaking (NPRM).
This document proposes the adoption of a new airworthiness directive (AD) that is applicable to certain Airbus Model A330 and A340 series airplanes. This proposal would require a one-time inspection of the hydraulically operated valve of the parking brake of the main landing gear to identify the part and serial numbers, and follow-on actions, if necessary. This action is necessary to prevent leakage of the valve, which could result in failure of the “blue” hydraulic system and consequent failure of alternate parking brake and emergency braking systems. This action is intended to address the identified unsafe condition.
Comments must be received by February 1, 2002.
Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2001-NM-350-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Comments may be inspected at this location between 9 a.m. and 3 p.m., Monday through Friday, except Federal holidays. Comments may be submitted via fax to (425) 227-1232. Comments may also be sent via the Internet using the following address: email@example.com. Comments sent via fax or the Internet must contain “Docket No. 2001-NM-350-AD” in the subject line and need not be submitted in triplicate. Comments sent via the Internet as attached electronic files must be formatted in Microsoft Word 97 for Windows or ASCII text.
The service information referenced in the proposed rule may be obtained from Airbus Industrie, 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.Start Further Info
FOR FURTHER INFORMATION CONTACT:
Dan Rodina, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056, telephone (425) 227-2125; fax (425) 227-1149.End Further Info End Preamble Start Supplemental Information
Interested persons are invited to participate in the making of the proposed 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 above. All communications received on or before the closing date for comments, specified above, will be considered before taking action on the proposed rule. The proposals contained in this action may be changed in light of the comments received.
Submit comments using the following format:
- Organize comments issue-by-issue. For example, discuss a request to change the compliance time and a request to change the service bulletin reference as two separate issues.
- For each issue, state what specific change to the proposed AD is being requested.
- Include justification (e.g., reasons or data) for each request.
Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this action must submit a self-addressed, stamped postcard on which the following statement is made: “Comments to Docket Number 2001-NM-350-AD.” The postcard will be date stamped and returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2001-NM-350-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.
The Direction Générale de l'Aviation Civile (DGAC), which is the airworthiness authority for France, notified the FAA that an unsafe condition may exist on certain Airbus Start Printed Page 32Model A330 and A340 series airplanes. The DGAC advises that leakage of the hydraulically operated valve of the parking brake of the main landing gear has been identified on certain Model A320 series airplanes. Hydraulic fluid leakage was found at the hydraulic connections and the vent hole of the valve. Leakage of the hydraulically operated valve, if not corrected, could result in failure of the “blue” hydraulic system and consequent failure of alternate parking brake and emergency braking systems.
Certain valves having serial numbers marked with a “V” or “VF+E” were modified and are not subject to the unsafe condition addressed by this AD.
The same hydraulically operated valve is installed on Model A330 and A340 series airplanes. Therefore, those airplanes are also subject to the unsafe condition identified by this proposed AD.
Explanation of Relevant Service Information
Airbus has issued Service Bulletins A330-32A3139 and A340-32A4176, both including Appendix 01, both dated September 14, 2001. The service bulletins describe procedures for a one-time detailed visual inspection of the hydraulically operated valve of the parking brake of the main landing gear to identify the part and serial numbers, and follow-on actions, if necessary. The follow-on actions consist of a visual inspection for hydraulic fluid leakage at the valve; repair or replacement of the valve with a new or serviceable valve if leakage is found, or repeat inspections if valve is not replaced, or if the valve is replaced with a valve having the same part or serial number; and an operational test following repair or replacement of the valve. Accomplishment of the actions specified in the service bulletins is intended to adequately address the identified unsafe condition. The DGAC issued French airworthiness directives 2001-516(B) and 2001-517(B), both dated October 31, 2001, in order to assure the continued airworthiness of these airplanes in France.
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 Proposed 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, the proposed AD would require accomplishment of the actions specified in the service bulletins described previously, except as discussed below.
Difference Between this AD and the Service Bulletins
Although the service bulletins specify that the manufacturer may be contacted for disposition of certain repairs, this AD would require such repairs to be accomplished per a method approved by either the FAA, or the DGAC (or its delegated agent). In light of the type of repair that would be required to address the identified unsafe condition, and in consonance with existing bilateral airworthiness agreements, the FAA has determined that, for this AD, a repair approved by either the FAA or the DGAC would be acceptable for compliance with this AD.
The FAA estimates that 9 airplanes of U.S. registry would be affected by this proposed AD, that it would take approximately 2 work hours per airplane to accomplish the proposed inspection, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the proposed AD on U.S. operators is estimated to be $1,080, or $120 per airplane.
The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the proposed requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions.
The regulations proposed herein would 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 proposal would not have federalism implications under Executive Order 13132.
For the reasons discussed above, I certify that this proposed regulation (1) is not a “significant regulatory action” under Executive Order 12866; (2) is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, 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 copy of the draft regulatory evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES.Start List of Subjects
List of Subjects in 14 CFR Part 39End List of Subjects
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:Start Part
PART 39—AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
2. Section 39.13 is amended by adding the following new airworthiness directive:
Airbus Industrie: Docket 2001-NM-350-AD.
Applicability: Model A330 and A340 series airplanes, as listed in Airbus Service Bulletin A330-32A3139 or A340-32A4176, both dated September 14, 2001; certificated in any category.
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. Start Printed Page 33The 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 leakage of the hydraulically operated valve of the parking brake of the main landing gear, which could result in failure of the “blue” hydraulic system and consequent failure of alternate parking brake and emergency braking systems, accomplish the following:
(a) Within 7 days after the effective date of this AD: Do a one-time detailed visual inspection to determine the part number (P/N) and serial number (S/N) of the hydraulically operated valve of the parking brake of the main landing gear per Airbus Service Bulletin A330-32A3139 (for Model A330 series airplanes) or A340-32A4176 (for Model A340 series airplanes), both including Appendix 01, both dated September 14, 2001, as applicable.
(1) If no P/N or S/N is identified as affected equipment per the applicable service bulletin, no further action is required by this AD.
(2) If any P/N or S/N is identified as affected equipment per the applicable service bulletin: Before further flight, perform the follow-on actions (which may include a visual inspection for hydraulic fluid leakage at the valve; repair or replacement of the valve with a new or serviceable valve if leakage is found; repetitive inspections if valve is not replaced, or if the valve is replaced with a valve having the same P/N or S/N; and an operational test), according to the applicable service bulletin.
For the purposes of this AD, a detailed visual 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.
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.
The subject of this AD is addressed in French airworthiness directives 2001-516(B) and 2001-517(B), both dated October 31, 2001.
Issued in Renton, Washington, on December 26, 2001.
Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 01-32193 Filed 12-31-01; 8:45 am]
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