Airworthiness directives: Lockheed,
[Federal Register: November 8, 1999 (Volume 64, Number 215)]
[Proposed Rules]
[Page 60750-60753]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08no99-30]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-252-AD]
RIN 2120-AA64
Airworthiness Directives; Lockheed Model L-1011-385 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
SUMMARY: This document proposes to revise an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that currently requires inspections to detect cracking and other discrepancies of certain web-to-cap fasteners of the rear spar between inner wing station (IWS) 310 and IWS 343, and of the web area around those fasteners; various follow-on actions; and modification of the web-to-cap fastener holes of the rear spar between IWS 299 and IWS 343, which, when accomplished, defers the initiation of the inspections for a certain period of time. The actions specified by that AD are intended to prevent fatigue cracking in the web of the rear spar of the wing, which could result in failure of the rear spar of the wing and consequent fuel spillage. This action would, for certain airplanes, extend the compliance time for the modification of the web-to-cap fastener holes, and would eliminate references to modification of the outboard spar.
DATES: Comments must be received by December 23, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 99-NM-252-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 the proposed rule may be obtained from Lockheed Martin Aircraft & Logistics Center, 120 Orion Street, Greenville, South Carolina 29605. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia.
FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer, Systems and Flight Test Branch, ACE-116A, FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30337-2748; telephone (770) 703-6063; fax (770) 703-6097.
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 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 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 summarizing each FAA-public contact concerned with the substance of this proposal will be filedin 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 Number 99-NM-252-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. 99-NM-252-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.
Discussion
On June 15, 1999, the FAA issued AD 99-13-08, amendment 39-11202 (64 FR 33386, June 23, 1999), applicable to all Lockheed Model L-1011- 385 series airplanes, to require inspections to detect cracking and other discrepancies of certain web-to-cap fasteners of the rear spar between inner wing station (IWS) 310 and IWS 343, and of the web area around those fasteners; various follow-on actions; and modification of the web-to-cap fastener holes of the rear spar between IWS 299 and IWS 343, which, when accomplished, defers the initiation of the inspections for a certain period of time. That action was prompted by an FAA determination that a modification of certain web-to-cap fastener holes must be accomplished within a specified period of time to ensure an acceptable level of safety of the affected fleet. The requirements of that AD are intended to prevent fatigue cracking in the web of the rear spar of the wing, which could result in failure of the rear spar of the wing and consequent fuel spillage.
Actions Since Issuance of Previous Rule
Since the issuance of that AD, the FAA has determined that a reference to Table 1 of Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9, 1996, which contains appropriate thresholds for accomplishment of the modification of the web-to-cap fastener holes, was inadvertently omitted from paragraph (d) of AD 99-13-08. For certain airplanes, this omission results in a shorter compliance time for accomplishing the modification than what was recommended in Lockheed Service Bulletin 093-57-218, Revision 1. The FAA finds that such a short compliance time is unnecessarily restrictive, and that it is necessary to
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revise the existing AD to increase the inspection threshold to that recommended by the manufacturer.
In addition, since the issuance of AD 99-13-08, the FAA has determined that the text of paragraph (f) of that AD [which describes an acceptable alternative, for certain airplanes, to accomplishment of paragraph (d) of that AD that also will defer the initiation of inspections for a certain period of time] specifies certain areas that do not, for the purposes of this AD, require modification. Paragraphs (f)(1) and (f)(2), as well as Notes 3 and 4, of the existing AD specify modification of the inboard and outboard rear spars. The FAA has previously determined that modification of the outboard rear spars is not necessary, and the service bulletins referenced in these sections do not describe procedures for modification of the outboard rear spars. Therefore, the FAA finds that, in order to alleviate any unnecessary burden on operators of the subject airplanes who elect to accomplish this option to attain compliance, and to make the requirements of the AD consistent with the procedures specified in the service bulletins referenced, it is necessary to revise paragraphs (f)(1) and (f)(2) and Notes 3 and 4 to eliminate reference to the outboard rear spar.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to exist or develop on other products of this same type design, the proposed AD would revise AD 99-13-08 to continue to require inspections to detect cracking and other discrepancies of certain web-to-cap fasteners of the rear spar between IWS 310 and IWS 343, and of the web area around those fasteners; various follow-on actions; and modification of the web-to-cap fastener holes of the rear spar between IWS 299 and IWS 343, which, when accomplished, defers the initiation of the inspections for a certain period of time. This action proposes to extend the compliance time for the modification of the web-to-cap fastener holes for certain airplanes, and to eliminate references to modification of the outboard spar. The actions would continue to be required to be accomplished in accordance with the service bulletins described previously in AD 99-13-08.
Cost Impact
There are approximately 235 Lockheed Model L-1011-385 series airplanes of the affected design in the worldwide fleet. The FAA estimates that 117 airplanes of U.S. registry would be affected by this proposed AD. The proposed requirements of this AD would not add any new additional economic burden on affected operators. Also, because the existing AD states the cost impact only for the required modification and not for the acceptable alternatives that were provided for certain airplanes, no change to the cost impact information is necessary. The current costs associated with this amendment are reiterated in their entirety (as follows) for the convenience of affected operators:
The inspections that are currently required by AD 99-13-08 take approximately 13 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the currently required inspections on U.S. operators is estimated to be $91,260, or $780 per airplane, per inspection cycle.
The modification that is currently required by AD 99-13-08 takes approximately 100 work hours per airplane to accomplish, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the currently required modification on U.S. operators is estimated to be $702,000, or $6,000 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 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 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 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.
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
-
The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
-
Section 39.13 is amended by removing amendment 39-11202 (64 FR 33386, June 23, 1999), and by adding a new airworthiness directive (AD), to read as follows:
Lockheed: Docket 99-NM-252-AD. Revises AD 99-13-08, Amendment 39- 11202.
Applicability: All Model L-1011-385 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 (h)(1) 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.
Restatement of Actions Required by AD 99-13-08, Amendment 39-11202
Inspections
(a) Perform a visual inspection to detect signs of cracking and other discrepancies (i.e., corrosion, fastener looseness, nicks, scratches, or other surface damage) of the web-to-cap fasteners of the rear spar between inner wing station (IWS) 310 and IWS 343, as specified in Figure 2 of Lockheed Service Bulletin 093-57-218, dated April 11, 1996, or Revision 1, dated September 9, 1996; and of the web area around those fasteners; in accordance with Part I of the Accomplishment Instructions of that service bulletin. Perform the inspection at the applicable time specified in paragraph (a)(1) or (a)(2) of this AD.
(1) Except as provided by paragraph (a)(2) of this AD: Perform the initial inspection
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prior to the accumulation of the number of landings specified as the ``inspection threshold'' in Table I of Lockheed Service Bulletin 093-57-218, dated April 11, 1996, or Revision 1, dated September 9, 1996, or within 10 days after June 27, 1996 (the effective date of AD 96-12-24, amendment 39-9667), whichever occurs later.
(2) For airplanes on which the wing rear spar was modified prior to June 27, 1996, in accordance with one of the Lockheed service bulletins listed in paragraph (a)(2)(ii) of this AD, accomplish the inspection as follows:
(i) Perform the initial inspection prior to the accumulation of the number of landings specified as the ``inspection threshold'' in Table I of Lockheed Service Bulletin 093-57-218, dated April 11, 1996, or Revision 1, dated September 9, 1996, calculated from the time the wing rear spar was modified (rather than from the date of manufacture of the airplane), or within 10 days after June 27, 1996, whichever occurs later.
(ii) This paragraph applies to airplanes on which the wing rear spar has been modified in accordance with one of the following service bulletins:
‹bullet› Lockheed Service Bulletin 093-57-184, Revision 6, dated October 28, 1991, or Revision 7, dated December 6, 1994; or
‹bullet› Lockheed Service Bulletin 093-57-196, Revision 5, dated October 28, 1991, or Revision 6, dated December 6, 1994; or
‹bullet› Lockheed Service Bulletin 093-57-203, Revision 3, dated October 28, 1991, or Revision 4, dated March 27, 1995; or
‹bullet› Lockheed Service Bulletin 093-57-215, dated April 11, 1996.
Repetitive Inspections
(b) If no sign of cracking or other discrepancy is found during the inspection required by paragraph (a) of this AD, repeat that inspection thereafter at intervals not to exceed the number of landings specified as the ``repeat visual inspection interval'' in Table I of Lockheed Service Bulletin 093-57-218, dated April 11, 1996, or Revision 1, dated September 9, 1996.
Corrective Actions
(c) If any sign of cracking is found during an inspection required by paragraph (a) or (b) of this AD, prior to further flight, perform either eddy current surface scan inspections, or bolt hole eddy current inspections, as appropriate, to confirm cracking, in accordance with Lockheed Service Bulletin 093-57-218, dated April 11, 1996, or Revision 1, dated September 9, 1996.
(1) If no cracking is confirmed, repeat the inspection specified in paragraph (a) of this AD at intervals not to exceed the number of landings specified as the ``repeat visual inspection interval'' in Table I of the service bulletin.
(2) If any cracking is confirmed, prior to further flight, repair it in accordance with the service bulletin.
Modification
(d) Except as provided by paragraph (e) or (f) of this AD, as applicable: Prior to the accumulation of the number of landings specified as the threshold in Table 1 of Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9, 1996; or within 12 months after July 28, 1999 (the effective date of AD 99-13-08, amendment 39-11202); whichever occurs later; modify the web-to-cap fastener holes of the rear spar between IWS 299 and IWS 343 in accordance with Part II of the Accomplishment Instructions of Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9, 1996. Within 5,000 landings following accomplishment of the modification, perform the visual inspection required by paragraph (a) of this AD. Thereafter, repeat that inspection at intervals not to exceed the number of landings specified as the ``repeat visual inspection interval'' in Table I of Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9, 1996.
(e) For Model L-1011-385-3 series airplanes: Accomplishment of the modification specified in paragraph (e)(1) or (e)(2) of this AD, within 12 months after July 28, 1999, constitutes an acceptable alternative to the modification specified in paragraph (d) of this AD.
(1) Modify the upper and lower caps of the rear spar between IWS 228 and IWS 346 in accordance with Part I of the Accomplishment Instructions of Lockheed Service Bulletin 093-57-203, Revision 3, dated October 28, 1991; or Revision 4, dated March 27, 1995. Within 5,000 landings following accomplishment of the modification, perform the visual inspection required by paragraph (a) of this AD. Thereafter, repeat that inspection at intervals not to exceed the number of landings specified as the ``repeat visual inspection interval'' in Table I of Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9, 1996. Or
(2) Modify the left and right wing rear spars in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 093-57- 215, dated April 11, 1996. Within the thresholds specified in Table I of Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9, 1996 (calculated from the date of installation of Lockheed Service Bulletin 093-57-215, dated April 11, 1996), perform the visual inspection required by paragraph (a) of this AD. Thereafter, repeat that inspection at intervals not to exceed the number of landings specified as the ``repeat visual inspection interval'' in Table I of Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9, 1996.
Note 2: Accomplishment of the modification of the upper and lower caps of the rear spar between IWS 228 and IWS 346, in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 093-57-203, dated July 25, 1988, Revision 1, dated August 11, 1989, or Revision 2, dated January 25, 1991, is considered acceptable for compliance with the modification specified in paragraph (e)(1) of this amendment.
(f) For Model L-1011-385-1 series airplanes: Accomplishment of the modification specified in paragraph (f)(1) or (f)(2) of this AD, within 12 months after July 28, 1999, constitutes an acceptable alternative to the modification specified in paragraph (d) of this AD.
(1) Modify the inboard rear spars in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 093-57-184, Revision 6, dated October 28, 1991; or Revision 7, dated December 6, 1994. Within the thresholds specified in Table I of Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9, 1996 (calculated from the date of installation of Lockheed Service Bulletin 093-57- 184, Revision 6, dated October 28, 1991, or Revision 7, dated December 6, 1994), perform the visual inspection required by paragraph (a) of this AD. Thereafter, repeat that inspection at intervals not to exceed the number of landings specified as the ``repeat visual inspection interval'' in Table I of Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9, 1996. Or
(2) Modify the inboard rear spars in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 093-57-196, Revision 5, dated October 28, 1991; or Revision 6, dated December 6, 1994. Within the thresholds specified in Table I of Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9, 1996 (calculated from the date of installation of Lockheed Service Bulletin 093-57- 196, Revision 5, dated October 28, 1991, or Revision 6, dated December 6, 1994), perform the visual inspection required by paragraph (a) of this AD. Thereafter, repeat that inspection at intervals not to exceed the number of landings specified as the ``repeat visual inspection interval'' in Table I of Lockheed Service Bulletin 093-57-218, Revision 1, dated September 9, 1996.
Note 3: Accomplishment of the modification of the inboard rear spars, in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 093-57-184, Revision 2, dated October 12, 1988; Revision 3, dated August 11, 1989, Revision 4, dated May 16, 1990; or Revision 5, dated May 23, 1990, is considered acceptable for compliance with the modification specified in paragraph (f)(1) of this amendment.
Note 4: Accomplishment of the modification of the inboard rear spars, in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 093-57-196, Revision 1, dated October 25, 1988; Revision 2, dated July 31, 1989; Revision 3, dated March 7, 1990; or Revision 4, dated July 1, 1991, is considered acceptable for compliance with the modification specified in paragraph (f)(2) of this amendment.
(g) If any condition (i.e., number of discrepant fasteners per stiffener bay, or cracking) is identified during the accomplishment of the modification specified in Lockheed Service Bulletin 093-57- 218, Revision 1, dated September 9, 1996, and that condition exceeds the limits specified in paragraph B.(3) of Part II of the Accomplishment Instructions of the service bulletin, prior to further flight, repair in accordance with a method approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate.
Alternative Method of Compliance
(h)(1) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be
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used if approved by the Manager, Atlanta ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO.
(h)(2) Alternative methods of compliance, approved previously in accordance with AD 96-12-24, amendment 39-9667, or AD 99-13-08, amendment 39-11202, are approved as alternative methods of compliance with paragraph (d) of this AD.
Note 5: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO.
Special Flight Permits
(i) 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.
Issued in Renton, Washington, on November 2, 1999. D.L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 99-29180Filed11-5-99; 8:45 am]
BILLING CODE 4910-13-P
