[Federal Register Volume 63, Number 50 (Monday, March 16, 1998)] [Proposed Rules] [Pages 12708-12710] From the Federal Register Online via the Government Publishing Office [www.gpo.gov] [FR Doc No: 98-6592] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 98-CE-03-AD] RIN 2120-AA64 Airworthiness Directives; British Aerospace (Operations) Limited Model B.121 Series 1, 2, and 3 Airplanes AGENCY: Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: This document proposes to adopt a new airworthiness directive (AD) that would apply to certain British Aerospace (Operations) Limited (British Aerospace) Model B.121 Series 1, 2, and 3 airplanes. The proposed AD would require installing an inspection opening in the area of the main spar web, repetitively inspecting the area at the main spar web for cracks and the area of the wing to fuselage attach bolt holes for corrosion, and repairing or replacing any cracked or corroded part. The [[Page 12709]] proposed AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by the proposed AD are intended to prevent structural failure of the main spar web area caused by fatigue cracking or separation of the wing from the fuselage caused by corroded attach bolt holes, which could result in loss of control of the airplane. DATES: Comments must be received on or before April 17, 1998. ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 98-CE-03-AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. Comments may be inspected at this location between 8 a.m. and 4 p.m., Monday through Friday, holidays excepted. Service information that applies to the proposed AD may be obtained from British Aerospace (Operations) Limited, British Aerospace Regional Aircraft, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland; telephone: (01292) 479888; facsimile: (01292) 479703. This information also may be examined at the Rules Docket at the address above. FOR FURTHER INFORMATION CONTACT: Mr. Roger Chudy, Aerospace Engineer, Small Airplane Directorate, Aircraft Certification Service, 1201 Walnut, suite 900, Kansas City, Missouri 64106; telephone: (816) 426- 6932; facsimile: (816) 426-2169. SUPPLEMENTARY INFORMATION: Comments Invited 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 should 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 notice may be changed in light of the comments received. 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 that summarizes 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 notice must submit a self-addressed, stamped postcard on which the following statement is made: ``Comments to Docket No. 98-CE-03-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, Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 98-CE-03-AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. Discussion The Civil Airworthiness Authority (CAA), which is the airworthiness authority for the United Kingdom, recently notified the FAA that an unsafe condition may exist on certain British Aerospace Model B.121 Series 1, 2, and 3 airplanes. The CAA reports findings of fatigue cracking in the area of the main-spar next to the undercarriage attach points, and corrosion at the wing/spar attach bolt holes. These conditions, if not corrected in a timely manner, could result in structural failure of the main spar web area caused by fatigue cracking or separation of the wing from the fuselage caused by corroded attach bolt holes, with consequent loss of control of the airplane. Relevant Service Information British Aerospace has issued PUP Service Bulletin No. B121/102, Revision No. 1, Issued April 16, 1997, which specifies procedures for the following: --Installing an inspection opening and inspecting, using eddy current methods, the area at the main spar web for cracks; and --Visually inspecting the area of the wing to fuselage attach bolt holes for corrosion. The CAA classified this service bulletin as mandatory and issued British AD 005-10-96, not dated, in order to assure the continued airworthiness of these airplanes in the United Kingdom. The FAA's Determination This airplane model is manufactured in the United Kingdom and is type certificated for operation in the United States under the provisions of Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the CAA has kept the FAA informed of the situation described above. The FAA has examined the findings of the CAA; reviewed all available information, including the service information referenced above; and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. Explanation of the Provisions of the Proposed AD Since an unsafe condition has been identified that is likely to exist or develop in other British Aerospace Model B.121 Series 1, 2, and 3 airplanes of the same type design registered in the United States, the FAA is proposing AD action. The proposed AD would require installing an inspection opening in the area of the main spar web, repetitively inspecting the area at the main spar web for cracks and the area of the wing to fuselage attach bolt holes for corrosion, and repairing or replacing any cracked or corroded part. Accomplishment of the proposed inspections would be required in accordance with British Aerospace PUP Service Bulletin No. B121/102, Revision No. 1, Issued April 16, 1997. If necessary, the proposed repair or replacement would be required in accordance with a scheme obtained from the manufacturer through the FAA, Small Airplane Directorate. Cost Impact The FAA estimates that 2 airplanes in the U.S. registry would be affected by the proposed AD, that it would take approximately 18 workhours per airplane to accomplish the proposed initial inspection and inspection opening installation, and that the average labor rate is approximately $60 an hour. Based on these figures, the total cost impact of the proposed AD on U.S. operators is estimated to be $2,160, or $1,080 per airplane. These figures only take into account the cost of the proposed initial inspections and inspection opening installation, and do not take into account the cost of repetitive inspections. The FAA has no way of determining the number of repetitive inspections each owner/operator of the affected airplanes will incur. Regulatory Impact The regulations proposed herein would 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 [[Page 12710]] 12612, it is determined that this proposal would not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. 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) 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 has been placed in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. 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: 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. Sec. 39.13 [Amended] 2. Section 39.13 is amended by adding a new airworthiness directive (AD) to read as follows: British Aerospace (Operations) Limited: Docket No. 98-CE-03-AD. Applicability: Model B.121 Series 1, 2, and 3 airplanes, all serial numbers, 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 (e) 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 in the body of this AD, unless already accomplished. To prevent structural failure of the main spar web area caused by fatigue cracking or separation of the wing from the fuselage caused by corroded attach bolt holes, which could result in loss of control of the airplane, accomplish the following: (a) Within the next 100 hours time-in-service (TIS) after the effective date of this AD, accomplish the following in accordance with the Accomplishment Instructions section, Appendix 1, and Appendix 2 of British Aerospace PUP Service Bulletin No. B121/102, Revision No. 1, dated April 16, 1997: (1) Install an inspection opening and inspect, using eddy current methods, the area at the main spar web for cracks; and (2) Visually inspect the area of the wing to fuselage attach bolt holes for corrosion. (b) Within 800 hours TIS after the initial inspection required by paragraph (a), including subparagraphs, of this AD, and thereafter at intervals not to exceed 800 hours TIS, reinspect the area of the main spar web as specified in paragraph (a), including all subparagraphs, of this AD. (c) If any cracks or corrosion damage is found during any inspection required by this AD, prior to further flight, accomplish the following: (1) Obtain a repair or replacement scheme from the manufacturer through the FAA, Small Airplane Directorate, at the address specified in paragraph (e) of this AD; and (2) Incorporate this scheme and continue to repetitively inspect as required by paragraph (b) of this AD, unless specified differently in the instructions to the repair or replacement scheme. (d) Special flight permits may be issued in accordance with Secs. 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. (e) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Small Airplane Directorate, Aircraft Certification Service, 1201 Walnut, suite 900, Kansas City, Missouri 64106. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Small Airplane Directorate. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Small Airplane Directorate. (f) Questions or technical information related to British Aerospace PUP Service Bulletin No. B121/102, Revision No. 1, Issued April 16, 1997, should be directed to British Aerospace (Operations) Limited, British Aerospace Regional Aircraft, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland; telephone: (01292) 479888; facsimile: (01292) 479703. This service information may be examined at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. Note 3: The subject of this AD is addressed in British AD 005- 10-96, not dated. Issued in Kansas City, Missouri, on March 9, 1998. Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-6592 Filed 3-13-98; 8:45 am] BILLING CODE 4910-13-U