AD 95-06-51

This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T95-06-51 that was sent previously to all known U.S. owners and operators of Lockheed Model L-1011-385 series airplanes by individual telegrams. This AD requires inspection to detect corrosion, severed braided strands, or fuel leakage of the fuel feed line hose assembly on engine number two; and subsequent inspection or replacement of the fuel hose with a serviceable part, if necessary. This AD also requires treatment of the ends of the fuel hose and modification of the heat-shrunk plastic cover and steel identification band area. This amendment is prompted by a report of failure of an aluminum-braided flexible fuel hose on a Model L-1011-385 series airplane due to corrosion. The actions specified by this AD are intended to prevent failure of a flexible fuel hose, which could result in failure of an engine, loss of fuel, and a resultant fire.

Final Rule; Request for Comments

95-06-51 LOCKHEED AERONAUTICAL SYSTEMS COMPANY: Amendment 39-9185. Docket 95-NM-32-AD.

Applicability: Model L-1011-385 series airplanes; as listed in Lockheed Service Bulletin 093-28-A091, dated March 8, 1995; 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 use the authority provided in paragraph (f) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.

Compliance: Required as indicated, unless accomplished previously.

To prevent failure of a flexible fuel hose, accomplish the following:

(a) Within 100 hours time-in-service or 10 days after the effective date of this AD, whichever occurs first: Accomplish the requirements of paragraphs (a)(1) and (a)(2) of this AD in accordance with Lockheed Service Bulletin 093-28-A091, dated March 8, 1995.

(1) Perform a visual inspection to detect corrosion, severed braided strands, or fuel leakage of the fuel feed line hose assembly, part number (P/N) 96715-107 (Lockheed P/N 740970-107), on engine number two. And

(2) Treat the ends of the fuel hose where the collars are clamped to the braided strands, and modify the heat-shrunk plastic cover and steel identification band area.

(b) If no discrepancy is found duringthe inspection required by paragraph (a) of this AD: Following accomplishment of the actions required by paragraph (a)(2) of this AD, no further action is required by this AD.

(c) If any corrosion is found during any inspection required by this AD: Prior to further flight, accomplish either paragraph (c)(1) or (c)(2) of this AD in accordance with Lockheed Service Bulletin 093-28-A091, dated March 8, 1995.

(1) Replace the fuel hose with a serviceable part. Or

(2) Inspect the fuel hose thereafter on a daily basis to detect ballooning of the hose. If any ballooning is found, prior to further flight, replace the fuel hose with a serviceable part.

(d) If any severed braided strand or any fuel leak is found during any inspection required by this AD: Prior to further flight, replace the fuel hose with a serviceable part in accordance with Lockheed Service Bulletin 093-28-A091, dated March 8, 1995.

(e) Replacement of the fuel hose assembly with a fuel hose assembly having P/N 740970-113 or P/N 96715-107 (Lockheed P/N 740970-107) constitutes terminating action for the requirements of this AD.

NOTE 2: The preferred replacement fuel hose assembly is P/N 740970-113.

(f) 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, Atlanta Aircraft Certification Office (ACO), FAA, Small 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, Atlanta ACO.

NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO.

(g) 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.

(h) The actions shall be done in accordance with Lockheed Service Bulletin 093-28- A091, dated March 8, 1995. 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 Lockheed Aeronautical Systems Support Company (LASSC), Field Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, Smyrna, Georgia 30080. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, Campus Building, 1701 Columbia Avenue, Suite 2-160, College Park, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(i) This amendment becomes effective on April 21, 1995, to all persons except those persons to whom it was made immediately effective by telegraphic AD T95-06-51, issued on March 9, 1995, which contained the requirements of this amendment.

On March 9, 1995, the FAA issued telegraphic AD T95-06-51, which is applicable to certain Lockheed Model L-1011-385 series airplanes. That action was prompted by a report of failure of an aluminum-braided flexible fuel hose on a Model L-1011-385 series airplane due to corrosion. This condition, if not corrected, could result in failure of an engine, loss of fuel, and a resultant fire.

The FAA received a report of failure of an aluminum-braided flexible fuel hose located immediately aft of the fuselage rear pressure bulkhead on a Model L-1011-385 series airplane. Ground maintenance personnel found a fuel leak when the airplane arrived at the gate after landing.

The operator performed a preliminary investigation of the fuel hose, and discovered that it was about 75 percent severed at a point approximately 7.0 inches from the inboard end. Inspection of the aluminum braiding in the area of the failure revealed that the braided strands were corrodedand brittle. The corrosion occurred in an area of the stainless steel identification band, which has a translucent heat-shrunk plastic cover. The operator conducted subsequent inspections of its fleet and found two airplanes (out of a fleet of five airplanes) having corroded braided material in the area of the identification band. The cause of this corrosion has not been determined.

The FAA has reviewed and approved Lockheed Service Bulletin 093-28-A091, dated March 8, 1995, which describes procedures for a visual inspection to detect corrosion, severed braided strands, or fuel leakage of the fuel feed line hose assembly on engine number two; and inspections to detect ballooning of the fuel hose, or replacement of the fuel hose with a serviceable part, if necessary. The service bulletin also describes procedures for treatment of the ends of the hose, and modification of the heat-shrunk plastic cover and steel identification band area.

Since the unsafe condition described is likely to exist or develop on other airplanes of the same type design, the FAA issued telegraphic AD T95-06-51. The AD requires an inspection to detect corrosion, severed braided strands, or fuel leakage of the fuel feed line hose assembly on engine number two; and inspections to detect ballooning of the fuel hose, or replacement of the fuel hose with a serviceable part, if necessary. The AD also requires treatment of the ends of the fuel hose; and modification of the heat-shrunk plastic cover and steel identification band area. Replacement of the fuel hose with a serviceable part, if accomplished, terminates the requirements of this AD. The actions are required to be accomplished in accordance with the service bulletin described previously.

Since it was found that immediate corrective action was required, notice and opportunity for prior public comment thereon were impracticable and contrary to the public interest, and good cause existed to make the AD effective immediatelyby individual telegrams issued on March 9, 1995, to all known U.S. owners and operators of Lockheed Model L-1011-385 series airplanes. These conditions still exist, and the AD is hereby published in the Federal Register as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it effective to all persons.

As a result of recent communications with the Air Transport Association (ATA) of America, the FAA has learned that, in general, some operators may misunderstand the legal effect of AD's on airplanes that are identified in the applicability provision of the AD, but that have been altered or repaired in the area addressed by the AD. The FAA points out that all airplanes identified in the applicability provision of an AD are legally subject to the AD. If an airplane has been altered or repaired in the affected area in such a way as to affect compliance with the AD, the owner or operator is required to obtain FAA approval for an alternative methodof compliance with the AD, in accordance with the paragraph of each AD that provides for such approvals. A note has been included in this rule to clarify this long-standing requirement.

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 95-NM-32-AD." The postcard will be date stamped and returned to the commenter.

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 ofpower 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. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89.

39.13 - [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive: