Airworthiness Directive · Amendment 39-16881 · Fuel
The Boeing Company Airplanes
This AD applies to The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes, certificated in any category; as identified in Boeing Service Bulletin 767-28A0085, Revision 2, dated August 19, 2010.
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) 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 adopting a new airworthiness directive (AD) for The Boeing Company Model 767 airplanes. This AD requires installing new panel assemblies in the main equipment center or on the forward cargo compartment sidewall and removing certain relays from some panels in the main equipment center. This AD also requires revising the maintenance program to incorporate Airworthiness Limitations (AWLs) No. 28-AWL-27 and No. 28-AWL-28. This AD also includes an alternative location for the installation of the new panel assemblies for airplanes that have the optional water system drain plumbing and changing the interconnecting wiring between the P141 panel and the P36 and P37 panels. For airplanes with a deactivated center fuel tank, this AD also requires an alternative functional test for the left and right override/jettison pumps. We are issuing this AD to prevent possible sources of ignition in a fuel tank caused by electrical fault or uncommanded dry operation of the main tank boost pumps and center auxiliary tank override and jettison pumps. This AD was prompted by fuel system reviews conducted by the manufacturer. An ignition source in the fuel tank could result in a fire or an explosion and consequent loss of the airplane.
For airplanes on which a dual crossfeed valve has been installed as specified in Boeing Service Bulletin 767-28-0034 as of the effective date of this AD: Within 60 months after the effective date of this AD, install ground fault interrupt relays (P140 and P141 panel assemblies) and all applicable parts and components in the main equipment center or in the forward cargo compartment sidewall, as applicable, and remove the fuel boost pump control relays from the P33, P36, and P37 panels, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-28A0085, Revision 2, dated August 19, 2010, except as required by paragraph (i) of this AD.
For airplanes on which a dual crossfeed valve has not been installed as specified in Boeing Service Bulletin 767-28-0034 as of the effective date of this AD: Within 60 months after the effective date of this AD, do the actions specified in paragraph (h)(1) or (h)(2) of this AD.
(1) Install ground fault interrupt relays (P140 and P141 panel assemblies) and all applicable parts and components in the main equipment center or in the forward cargo compartment sidewall, as applicable, and remove the fuel boost pump control relays from the P33, P36, and P37 panels, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-28A0085, Revision 2, dated August 19, 2010, except as required by paragraph (i) of this AD. Prior to or concurrently with the installation of the ground fault interrupt relays, install a dual crossfeed valve in accordance with Boeing Service Bulletin 767-28-0034, Revision 3, dated March 14, 1996.
(2) Maintain the single crossfeed valve configuration and install a GFI, in accordance with a method approved using the procedures specified in paragraph (o)(1) of this AD.
Although paragraph 3.B.29.e. of the Accomplishment Instructions of Boeing Service Bulletin 767-28A0085, Revision 2, dated August 19, 2010, specifies an alternative functional test of the left and right center override pumps as an option, this AD requires that test for airplanes on which the center tank is deactivated.
For airplanes identified in paragraph 1.A.1. of Boeing Service Bulletin 767-28A0083, Revision 2, dated February 12, 2009; or Boeing Service Bulletin 767-28A0084, Revision 1, dated April 26, 2007: Prior or concurrently with accomplishing the actions required by paragraph (g) and (h)(1) of this AD, install an automatic shutoff system for the auxiliary fuel tank pump, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-28A0083, Revision 2, dated February 12, 2009; or Boeing Service Bulletin 767-28A0084, Revision 1, dated April 26, 2007; as applicable. Accomplishing the requirements of AD 2009-16-06, Amendment 39-15989 (74 FR 38905, August 5, 2009), terminates the requirements of this paragraph.
Concurrently with accomplishing the actions required by paragraphs (g) and (h)(1) of this AD, or within 30 days after the effective date of this AD, whichever occurs later: Revise the maintenance program by incorporating Airworthiness Limitations (AWLs) No. 28-AWL-27 and No. 28-AWL-28 of Section 9 (“Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs)”) of the Boeing 767 Maintenance Planning Data (MPD) Document, D622T001-9, Revision April 2008; Revision March 2009; Revision May 2009; or Revision May 2010. The initial compliance time for the actions specified in AWLs No. 28-AWL-27 and No. 28-AWL-28 is within 1 year after accomplishing the installation required by paragraph (g) or (h)(1) of this AD, or within 1 year after the effective date of this AD, whichever occurs later.
Incorporating AWLs No. 28-AWL-27 and No. 28-AWL-28 into the maintenance program in accordance with paragraph (g)(2) of AD 2008-11-01, Amendment 39-15523 (73 FR 29414, May 21, 2008), or paragraph (g)(2) of AD 2008-11-01 R1, Amendment 39-16145 (74 FR 68515, December 28, 2009), terminates the action required by paragraph (k) of this AD.
After accomplishing the actions specified in paragraph (k) of this AD, no alternative inspections or inspection intervals may be used unless the inspections or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (o) of this AD.
Actions done before the effective date of this AD in accordance with the service information identified in paragraphs (n)(1) through (n)(5) of this AD are acceptable for compliance with the corresponding requirements of this AD.
(1) Boeing Alert Service Bulletin 767-28A0085, dated January 10, 2008.
(2) Boeing Service Bulletin 767-28A0085, Revision 1, dated June 25, 2009.
(3) Boeing Alert Service Bulletin 767-28A0083, dated May 3, 2006.
(4) Boeing Service Bulletin 767-28A0083, Revision 1, dated April 26, 2007.
(5) Boeing Alert Service Bulletin 767-28A0084, dated May 3, 2006.
