Airworthiness Directive · Amendment 39-16749 · Fuel
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G Airplanes
This AD applies to all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G 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 according to paragraph (o) 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 superseding an existing airworthiness directive (AD) for all Model 382, 382B, 382E, 382F, and 382G airplanes. That AD currently 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. That 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 new AD corrects certain part number references, adds an additional inspection area, and for certain airplanes, requires certain actions to be re-accomplished according to revised service information. This AD was prompted by a report of incorrect accomplishment information in the service information cited by the existing AD. 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.
RESTATEMENT OF REQUIREMENTS OF AD 2008-20-01, WITH NEW SERVICE INFORMATION:
Before December 16, 2008, revise the maintenance program to incorporate the fuel system limitations (FSLs) and the critical design configuration control limitations (CDCCLs) specified in the Accomplishment Instructions of the Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008; except as provided by paragraphs (g)(1), (g)(2), and (g)(3) of this AD, and except that the modifications and initial inspections specified in table 1 of this AD must be done at the compliance time specified in paragraph (h) of this AD.
(1) For the CDCCLs specified in paragraphs 2.C.(3)(e), 2.C.(3)(h), 2.C.(4)(a), 2.C.(5)(c), 2.C.(7)(h), and 2.C.(8) of the Accomplishment Instructions of Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008, do the applicable actions in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 382-28-19, Revision 3, dated November 30, 2006; or Revision 4, dated September 18, 2008. After the effective date of this AD, use only Revision 4.
(2) Where paragraph 2.C.(1)(c) of the Accomplishment Instructions of Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008, specifies to change the maintenance program to indicate that repetitive inspections of the lightning and static bonding jumpers must be done in accordance with Lockheed Service Bulletin 382-28-21, instead do the repetitive inspections in accordance with Lockheed Service Bulletin 382-28-19, Revision 3, dated November 30, 2006; or Revision 4, dated September 18, 2008. After the effective date of this AD, use only Revision 4.
(3) Where Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008, specifies to inspect, this AD requires 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.”
Within 36 months after November 3, 2008 (the effective date of AD 2008-20-01), do the applicable actions specified in table 1 of this AD, and repair any discrepancy before further flight, in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008.
| Action | Additional source of guidance for accomplishing the action |
|---|---|
| For airplanes having any serial number prior to 4962: Install new, improved fuel dump masts in accordance with paragraph 2.C.(1)(d) of the Accomplishment Instructions of Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008 | Lockheed Service Bulletin 382-28-9, dated May 13, 1983. |
| Mark the fuel quantity indicating system (FQIS) wires in accordance with paragraphs 2.C.(1)(a) 2, 2.C.(4)(b), and 2.C.(4)(c) of the Accomplishment Instructions of Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008 | Lockheed Service Bulletin 382-28-19, Revision 4, dated September 18, 2008. |
| Do the dry bay zonal inspection and inspect the static ground terminals of the fuel system plumbing in accordance with paragraph 2.C.(1)(a) of the Accomplishment Instructions of Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008 | Lockheed Service Bulletin 382-28-19, Revision 4, dated September 18, 2008. |
| Install ground fault interrupters (GFIs) and flame arrestors for protection of the fuel system in accordance with paragraphs 2.C.(1)(b) and 2.C.(7)(c) of the Accomplishment Instructions of Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008 | Lockheed Service Bulletin 382-28-20, Revision 11, dated April 20, 2010. |
| Inspect the GFIs for protection of the fuel system in accordance with paragraph 2.C.(1)(b) 1 of the Accomplishment Instructions of Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008 | Paragraph 2.C.(2) of the Accomplishment Instructions of Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008. |
| Install the lightning bonding jumpers (straps) in accordance with paragraphs 2.C.(1)(c) and 2.C.(6)(a) of the Accomplishment Instructions of Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008 | Lockheed Service Bulletin 382-28-21, Revision 4, dated January 6, 2010. |
| Inspect the lightning and static bonding jumpers (straps) in accordance with paragraphs 2.C.(1)(c) of the Accomplishment Instructions of Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008 | Lockheed Service Bulletin 382-28-19, Revision 4, dated September 18, 2008. |
| Apply a certain sealant to the interior of the main wing fuel tanks; and apply a certain sealant to the all external fuel tank nose caps, mid sections, and tail sections; as applicable; in accordance with paragraphs 2.C.(1)(e) 1, 2.C.(1)(e) 3, and 2.C.(7)(i) 1 of the Accomplishment Instructions of Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008 | Lockheed Service Bulletin 382-28-24, Revision 1, dated November 5, 2007, including the Errata Notice, dated January 7, 2008. |
(i) 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 approved as an alternative method of compliance in accordance with the procedures specified in paragraph (o) of this AD.
Although Lockheed Service Bulletin 382-28-19, Revision 3, dated November 30, 2006, specifies to notify Lockheed of any discrepancies found during inspection, this AD does not require that action.
NEW REQUIREMENTS OF THIS AD:
Where the last two bulleted steps of paragraphs 2.C.(2)(b) 5 and 2.C.(2)(c) 3 of Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008, specify that the GFI FAILURE and GROUND FAULT DETECTED lights illuminate for 2 seconds, this AD does not require those steps.
For airplanes on which Lockheed Service Bulletin 382-28-19, Revision 3, dated November 30, 2006, has not been done: Where table 1 of this AD specifies to do the dry bay zonal inspection, do an inspection of the fuel probes as part of the dry bay zonal inspections, in accordance with the service information specified in paragraph (h) of this AD for the dry bay zonal inspections. Do the inspections at the time specified in paragraph (h) of this AD, or within 9 months after the effective date of this AD, whichever occurs later.
For airplanes on which any action was done in accordance with Lockheed Service Bulletin 382-28-19, Revision 3, dated November 30, 2006: Within the compliance time specified in paragraph (h) of this AD, or within 9 months after the effective date of this AD, whichever occurs later, do the actions required by paragraphs (m)(1) through (m)(4) of this AD and repair any discrepancy before further flight, in accordance with Accomplishment Instructions of Lockheed Service Bulletin 382-28-19, Revision 4, dated September 18, 2008. Although Lockheed Service Bulletin 382-28-19, Revision 4, dated September 18, 2008, specifies to notify Lockheed of any discrepancies found during inspection, this AD does not require that action.
(1) Inspect the fuel probes as part of the zonal inspections of the dry bay areas and other areas.
(2) Inspect generator feeder and control wire bundles for correct separation from other wires in the wing leading edge and fuselage areas, and for correct separation from fuel tank boundaries in the wing leading edge area.
(3) Inspect for correct spot-tying of certain wire bundles that are within 2 to 12 inches of hot equipment or wires with flame-resistant lacing braid, or, for wiring in powerplant areas, with fiberglass braid.
(4) Inspect for use of the correct shielding specification and separation of the FQIS wiring in certain locations from alternating current (AC) power wires.
Actions done before the effective date of this AD in accordance with Lockheed Service Bulletin 382-28-20, Revision 8, dated October 13, 2009; Revision 9, dated December 14, 2009; or Revision 10, dated March 18, 2010; are acceptable for compliance with the requirements of paragraph (h) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
