Ad/B767/252 - Auxilary Fuel tank Pump Automatic Shut Off Installation (Cth)

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Boeing 767 Series Aeroplanes

AD/B767/252 Auxilary Fuel tank Pump
Automatic Shut Off Installation 10/2009

Applicability:	Model 767-200, -300, -300F and -400ER series aeroplanes.
Requirement:	1.    For Model 767 aeroplanes with line numbers 1 through 940 inclusive - Install an automatic shutoff system for the centre tank fuel pump, in accordance with Boeing Service Bulletin (SB) 767-28A0083, Revision 2, dated 12 February 2009 (for Model 767-200, -300 and -300F aeroplanes); or Boeing SB 767-28A0084, Revision 1, dated 26 April 2007 (for Model 767-400ER aeroplanes); as applicable.
Installing an automatic shutoff system is also acceptable for compliance with the Requirement 1, if accomplished before the effective date of this Directive in accordance with service information identified in Table 1.
Table 1 - Previous Issues of Service Bulletins
Boeing Service Information	Revision Level	Date
Alert Service Bulletin 767-28A0083 Alert Service Bulletin 767-28A0084 Service Bulletin 767-28A0083	Original Original 1	3 May 2006 3 May 2006 26 April 2007
2.    For Model 767 aeroplanes with line numbers 1 through 940 inclusive - Revise Section 1, Certificate Limitations, of the Boeing 767 Aircraft Flight Manual (AFM) to include the following:
CENTRE TANK FUEL PUMPS Centre tank fuel pump switches must not be "ON'' unless personnel are available in the flight deck to monitor low PRESS lights. For ground operations prior to engine start:  The centre tank fuel pump switches must not be positioned ON unless the centre tank contains usable fuel.  With centre tank fuel pump switches ON, verify both centre tank fuel pump low PRESS lights are illuminated and EICAS CTR L FUEL PUMP and CTR R FUEL PUMP messages are displayed.

For ground operations after engine start and flight operations:  The centre tank fuel pump switch must be selected OFF when the respective CTR L FUEL PUMP or CTR R FUEL PUMP message displays.  Both centre tank fuel pump switches must be selected OFF when either the CTR L FUEL PUMP or CTR R FUEL PUMP message displays if the centre tank is empty.  During cruise flight, both centre tank pump switches may be reselected ON whenever centre tank usable fuel is indicated.

DE-FUELING AND FUEL TRANSFER
When transferring fuel or de-fuelling centre or main wing tanks, the fuel pump low PRESS lights must be monitored and the respective fuel pump switches positioned to "OFF'' at the first indication of low pressure.  Prior to transferring fuel or de-fuelling, conduct a lamp test of the respective fuel pump low PRESS lights.
Intentional dry running of a centre tank fuel pump (CTR L FUEL PUMP or CTR R FUEL PUMP message displayed on EICAS) is prohibited.
Do not reset a tripped fuel pump or fuel pump control circuit breaker.

Revision of the AFM may be accomplished by inserting a copy of this Directive into the AFM.

Note 1:  When statements identical to those in Requirement 2 have been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this Directive may be removed from the AFM.

3.    For Model 767-200, -300 and -300F aeroplanes that meet either of the conditions specified in sub-paragraphs a. or b. or c. below, install a placard in the flight deck adjacent to each pilot's primary flight display, to alert the flightcrew to follow the procedures required by AD/B767/167 Amdt 3.  The placard must include the following statement: "AD/B767/167 Amdt 3 fuel usage restrictions required.''

a.     The aeroplane is operated in a fleet of aeroplanes on which the actions specified in Requirement 1 of this Directive have been accomplished on at least one of the fleet's aeroplanes.

b.    Modified centre tank override and override/jettison fuel pumps (ie pumps that are not subject to the unsafe condition addressed by this Directive) have not been installed in accordance with either AD/B767/167 Initial Issue, Amdt1, Amdt 2 or Amdt 3.

c.     Requirement 1 of this Directive has not been accomplished.

Note 2:  If the actions specified in Requirement 1 of this Directive have been accomplished on all aeroplanes operated within an operator's fleet, or if operation according to the fuel usage restrictions of AD/B767/167 Amdt 3 is maintained until automatic shutoff systems are installed on all aeroplanes in an operator's fleet:  No placard is necessary before removal of the wet shutoff restrictions of AD/B767/167 Amdt 3.

Deactivation of the centre fuel tanks, in accordance with Boeing Alert Service Bulletin 767-28A0050, dated 18 December 1997; or Boeing SB 767-28A0050, Revision 1, dated 22 December 1999; terminates Requirement 1, 2 and 3 of this Directive, except as provided by Requirements 4 and 5 of this Directive.
4.    For any aeroplane on which the centre fuel tank is reactivated, the centre fuel tank must be reactivated in accordance with a method approved by the Manager, Continuing Airworthiness, Airworthiness and Engineering Branch, Civil Aviation Safety Authority.  For a reactivation method to be approved, the reactivation method must meet the certification basis of the aeroplane, and the approval must specifically reference either this Directive or FAA AD 2009-16-06.
5.    For any aeroplane on which the centre fuel tank is reactivated, Requirements 1, 2 and 3 of this Directive must be accomplished.
Later revisions of SB 767-28A0083, Revision 2, or 767-28A0084, Revision 1 approved by the United States Federal Aviation Administration (FAA) as an Alternate Method of Compliance (AMOC) to FAA AD 2009-16-06, are considered acceptable for compliance with the equivalent Requirements of this Directive.
Note 3:  FAA AD 2009-16-06 Amdt 39-15989 refers.
Compliance:	For Requirement 1 - Within 36 months after the effective date of this Directive.
For Requirement 2 - Concurrently with Requirement 1.
For Requirement 3 - Within 30 days after the effective date of this Directive.
For Requirement 4 - Prior to tank reactivation.
For Requirement 5 - Before further flight following the reactivation, or within 36 months after the effective date of this Directive, whichever occurs later.
This Airworthiness Directive becomes effective on 24 September 2009.
Background:	This Directive results from a design review of the fuel tank systems.  The Directive is issued to prevent an overheat condition outside the centre tank fuel pump explosion-resistance area that is open to the pump inlet, which could cause an ignition source for the fuel vapours in the fuel tank and result in fuel tank explosions and consequent loss of the aeroplane.

The Directive requires installing an automatic shutoff system for the auxiliary fuel tank override/jettison fuel pumps (also referred to as centre tank fuel pumps in the AFM), revising the AFM to advise the flightcrew of certain operating restrictions for aeroplanes equipped with an automatic auxiliary fuel tank pump shutoff control and, for certain aeroplanes, installing a placard to alert the flightcrew of certain fuel usage restrictions.  The Directive also provides optional terminating actions for certain requirements.

James Coyne
Delegate of the Civil Aviation Safety Authority

14 August 2009