Airworthiness Directive · Amendment 39-15524 · Lockheed Model L-1011 Series Airplanes
Lockheed Model L-1011 Series Airplanes
Superseded. A later AD replaced this one: AD 2008-11-02 R1. Comply with the one in force.
This AD applies to all Lockheed Model L-1011 series airplanes, certificated in any category.
Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance (AMOC) in accordance with paragraph (k) of this AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane.
We are adopting a new airworthiness directive (AD) for all Lockheed Model L-1011 series airplanes. This AD requires revising the FAA-approved maintenance program by incorporating new airworthiness limitations for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. This AD also requires the accomplishment of certain fuel system modifications, the initial inspections of certain repetitive fuel system limitations to phase in those inspections, and repair if necessary. This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of Lockheed Service Bulletin 093-28-098, Revision 1, dated January 22, 2008.
Before December 16, 2008, revise the FAA-approved maintenance program to incorporate the fuel system limitations (FSLs) specified in paragraphs 2.B.(1)(b), 2.B.(1)(e), 2.B.(1)(f), and 2.B.(1)(g) of the service bulletin, and the critical design configuration control limitations (CDCCLs) specified in paragraph 2.C. of the service bulletin; except as provided by paragraphs (g)(1), (g)(2), and (h) of this AD.
(1) Where the FSLs specify to inspect, this AD would require doing a general visual inspection.
Note 2: For the purposes of this AD, a general visual inspection is: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.”
(2) For the CDCCLs specified in paragraphs 2.C.(2)(c), 2.C.(2)(d), and 2.C.(15)(a) of the service bulletin, do the applicable actions using a method approved in accordance with the procedures specified in paragraph (k) of this AD. The applicable service information listed in Table 1 of this AD is one approved method.
| For the CDCCL identified in the service bulletin in paragraph— | One approved method is— | For— |
|---|---|---|
| 2.C.(2)(c) | Hamilton Sundstrand Overhaul Manual 28-24-03, Revision 14, dated May 15, 2000 | Overhauling and repairing the electrically-operated fuel boost pumps. |
| 2.C.(2)(d) | Lockheed L-1011 Service Information Letter 28-12, dated March 17, 1998 | Keeping the electrical conduit for the electrically-operated fuel boost pumps open and unplugged at the wing rear spar. |
| 2.C.(15)(a) | Lockheed Drawing 1527514, Revision D, dated September 26, 1981 | Installing the fuel tank valves, auxiliary power unit pump, sight gauges, fuel quantity indicating system tank units, over-wing filler cap adapter ring, boost pump mounting plate, and access doors for the boost pump, vent box, vent valve, and fuel level control switch. |
At the applicable compliance time specified in paragraph (h)(1) or (h)(2) of this AD, do the applicable FSLs specified in paragraphs 2.B.(1)(b), 2.B.(1)(e), 2.B.(1)(f), and 2.B.(1)(g) of the service bulletin and repair any discrepancy, in accordance with the service bulletin. Any repair must be done before further flight.
(1) For the FSL identified in paragraph 2.B.(1)(b) of the service bulletin, do the FSL before December 16, 2008.
(2) For the FSLs identified in paragraphs 2.B.(1)(e), 2.B.(1)(f), and 2.B.(1)(g) of the service bulletin, do the applicable FSLs within 60 months after the effective date of this AD.
Note 3: The service bulletin refers to the service information listed in Table 2 of this AD as additional sources of service information for doing the FSLs and repair.
| The FSL identified in the service bulletin in paragraph— | Refers to Lockheed Service Bulletin— | For— |
|---|---|---|
| 2.B.(1)(b) | 093-28-089, Revision 3, dated October 4, 2006 (or later) | Removing auxiliary fuel tank No. 4, if applicable. |
| 2.B.(1)(e) | 093-28-095, dated September 13, 2006 (or later) | Inspecting the airplane fuel tanks and vent boxes for cleanliness and evidence of deteriorated or damaged fuel/vent tubes and components; inspecting bonding jumpers for proper installation, corrosion, frayed or broken strands, and the condition of the environmental sealing or bonding clamps and hardware; correcting any discrepant conditions; adding bonding jumpers to the fuel/vent tube fittings; and inspecting the bonding jumpers on the fuel/vent tube fittings. |
| 2.B.(1)(f) | 093-28-096, Revision 2, dated June 23, 2006 (or later) | Inspecting the wiring harnesses of the No. 1 and No. 3 engine tank valves for evidence of damage and fuel contamination; replacing any damaged wire with new wire; and repairing or replacing any contaminated wires as applicable. |
| 2.B.(1)(g) | 093-28-097, dated August 3, 2006 (or later) | Identifying the wiring harnesses for the fuel quantity indicator system (FQIS); inspecting the FQIS wiring harnesses for any visible damage, wear, chafing, or indications of electrical arcing; and replacing or repairing any damaged wires as applicable. |
(i) Although Lockheed Service Bulletin 093-28-095, dated September 13, 2006; Lockheed Service Bulletin 093-28-096, Revision 2, dated June 23, 2006; and Lockheed Service Bulletin 093-28-097, dated August 3, 2006; specify to notify Lockheed of any discrepancies found during inspection or any evidence of damage or wire replacement, this AD does not require that action.
After accomplishing the actions specified in paragraphs (g) and (h) of this AD, no alternative inspections, inspection intervals, or CDCCLs may be used unless the inspections, intervals, or CDCCLs are part of a later revision of the service bulletin that is approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA; or unless the inspections, intervals, or CDCCLs are approved as an AMOC in accordance with the procedures specified in paragraph (k) of this AD.
