AD 2001-15-08 Airworthiness Directives; Boeing Model 767-200, -300, and -300F Series Airplanes

Models named: 767-200, -300, -300F series. Read the applicability below — it usually turns on serial or part numbers too.

All Model 767-200, -300, and -300F series airplanes, 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 request approval for an alternative method of compliance in accordance with paragraph (n)(1) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To prevent ignition of fuel vapors due to the generation of sparks and a potential ignition source inside the fuel tank caused by steel-to-steel contact during dry fuel pump operation, accomplish the following: AFM Revisions: Alternatives (a) Within 14 days after October 2, 1997 (the effective date of AD 97-19-15), accomplish the actions specified by either paragraph (b) or (c) of this AD. Restatement of Requirements of AD 97-19-15 (b) Accomplish paragraphs (b)(1), (b)(2), (b)(3), and (b)(4) of this AD. (1) Revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following procedures. This may be accomplished by inserting a copy of this AD in the AFM. “If the center tank fuel pumps are to be used, there must be at least 5,000 pounds (2,267 kilograms) of fuel in the center tank prior to engine start. The center fuel pumps must be selected ‘OFF’ at or greater than 1,000 pounds (453 kilograms) of fuel in the center tank. For airplanes not equipped with a center tank scavenge system, this 1,000 pounds (453 kilograms) of center tank fuel must be considered unusable. Note: On all Model 767-200ER/300ER series airplanes and some Model 767-200/300 series airplanes, a scavenge system, operating with fuel pressure from the main wing tank pumps, will operate automatically to transfer any fuel remaining in the center tank to the main tanks. Fuel transfer begins when the main tanks are approximately half empty.” (2) Revise the Limitations Section of the FAA-approved AFM procedure titled “FUEL SYSTEM, FUEL USAGE II (fuel in center tank),” to include the following procedures. This may be accomplished by inserting a copy of this AD into the AFM. “Use the center tank fuel for all operations with all operable fuel pumps “ON” and the cross feed valve(s) closed until the center tank fuel quantity is 1,000 pounds (453 kilograms) or greater, then use FUEL USAGE I. Do not operate the center tank fuel pumps with less than 1,000 pounds (453 kilograms) of fuel in the center tank. Note: The crossfeed valve(s) is open for minimum fuel operation, and may be opened to correct fuel imbalance.” (3) Revise the Normal Procedures Section of the FAA-approved AFM to include the following procedure. This may be accomplished by inserting a copy of this AD into the AFM. “USE OF FUEL FROM THE CENTER TANK When the center tank approaches ‘EMPTY’ during normal use or fuel transfer, select both center tank fuel pump switches ‘OFF’ with the first occurrence of any of the following: • The center tank fuel reaches 1,000 pounds (453 kilograms); • Either of the center tank fuel pump ‘PRESS’ lights illuminate; or • Either the ‘CTR L FUEL PUMP’ or ‘CTR R FUEL PUMP’ EICAS message is displayed.” (4) Revise the Non-Normal Procedures Section of the FAA-approved AFM to include the following procedures. This may be accomplished by inserting a copy of this AD into the AFM. “CENTER TANK FUEL PUMP FAULTS A center tank fuel pump failure may have occurred if a fuel pump pressure light illuminates when there is ample fuel in the tank. If a fault is suspected, select the affected pump ‘OFF’ and do not re-select “ON.” If the affected circuit breaker is tripped, do not reset. Select fuel crossfeed valve(s) ‘OPEN.’ Attempted operation of a faulted center tank pump could ignite fuel tank vapors in an empty or nearly empty tank.” New Requirements of This AD (c) Accomplish the actions required by paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD. Following accomplishment of the requirements of these paragraphs, the AFM revisions required by paragraph (b) of this AD may be removed from the AFM. (1) Revise the Limitations Section of the FAA-approved AFM to include the following procedures. This may be accomplished by inserting a copy of this AD in the AFM. “If the center tank fuel pumps are to be used, there must be at least 5,000 pounds (2,267 kilograms) of fuel in the center tank when the entry doors are closed with the airplane readied for initial taxi. The center fuel pumps must be selected “OFF” at or greater than 1,000 pounds (453 kilograms) of fuel in the center tank. For airplanes not equipped with a center tank scavenge system, this 1,000 pounds (453 kilograms) of center tank fuel must be considered unusable. Note: On all Model 767-200ER/300ER series airplanes and some Model 767-200/300 series airplanes, a scavenge system, operating with fuel pressure from the main wing tank pumps, will operate automatically to transfer any fuel remaining in the center tank to the main tanks. Fuel transfer begins when the main tanks are approximately half empty.” (2) Revise the Limitations Section of the FAA-approved AFM procedure titled “FUEL SYSTEM, FUEL USAGE II (fuel in center tank),” to include the following procedures. This may be accomplished by inserting a copy of this AD into the AFM. “Use the center tank fuel for all operations with all operable fuel pumps “ON” and the cross feed valve(s) closed until the center tank fuel quantity is 1,000 pounds (453 kilograms) or greater, then use FUEL USAGE I. Do not operate the center tank fuel pumps with less than 1,000 pounds (453 kilograms) of fuel in the center tank. Note: The crossfeed valve(s) is open for minimum fuel operation, and may be opened to correct fuel imbalance.” (3) Revise the Normal Procedures Section of the FAA-approved AFM to include the following procedure. This may be accomplished by inserting a copy of this AD into the AFM. “USE OF FUEL FROM THE CENTER TANK When the center tank approaches ‘EMPTY’ during normal use or fuel transfer, select both center tank fuel pump switches “OFF” with the first occurrence of any of the following: • The center tank fuel reaches 1,000 pounds (453 kilograms); • Either of the center tank fuel pump “PRESS” lights illuminate; or • Either the ‘CTR L FUEL PUMP’ or ‘CTR R FUEL PUMP’ EICAS message is displayed.” (4) Revise the Non-Normal Procedures Section of the FAA-approved AFM to include the following procedures. This may be accomplished by inserting a copy of this AD into the AFM. “CENTER TANK FUEL PUMP FAULTS A center tank fuel pump failure may have occurred if a fuel pump pressure light illuminates when there is ample fuel in the tank. If a fault is suspected, select the affected pump ‘OFF’ and do not re-select ‘ON.’ If the affected circuit breaker is tripped, do not reset. Select fuel crossfeed valve(s) ‘OPEN.’ Attempted operation of a faulted center tank pump could ignite fuel tank vapors in an empty or nearly empty tank.” Ground Transfer of Fuel (d) For Model 767-200, -300, and -300F series airplanes that are equipped with any override or override/jettison fuel pump having part number S343T002-5, -8, -12, or -15 (which are configured with machined inlet diffusers) and that are not equipped with a center tank scavenge system: For any period during which ground transfer of fuel is accomplished below 1,000 pounds (453 kilograms), accomplish the ground fuel pressure defueling actions specified by paragraphs (d)(1) and (d)(2), in accordance with the Boeing 767 Maintenance Manual Section 28-26-00, Pressure Defueling Procedures, titled “For Override Pumps with a Diffuser Installed.” (1) Only one center tank pump may be operated, and that pump must be selected “OFF” at or greater than 400 pounds (200 kilograms), as indicated on the center tank fuel quantity indication system (FQIS), or at the first indication of a pump low pressure light. (2) The pitch attitude of the airplane must be recorded prior to this procedure to verify that it is between −1 and +2 degrees. This may be accomplished by viewing the pitch inclinometer, located in the left main gear wheel well. Repetitive Inspections (e) For airplanes that are equipped with any override or override/jettison fuel pump having part number S343T002-5, -8, -12, or -15 (which are configured with machined inlet diffusers), except as provided by paragraph (f) of this AD: Within 60 days after the effective date of this AD, remove the override fuel pump and override/jettison fuel pump, as applicable, of the center tank, and perform a detailed visual inspection of the pump to detect discrepancies (cracking, screw movement, and diffuser movement), in accordance with Boeing Alert Service Bulletin 767-28A0050, dated December 18, 1997; or Revision 1, dated December 22, 1999. Repeat the inspection thereafter at intervals not to exceed 1,000 flight hours. (1) If no discrepancy is detected, prior to further flight, reinstall the pump in accordance with the alert service bulletin. (2) If any discrepancy is detected, prior to further flight, replace the pump with a new or serviceable pump, in accordance with the alert service bulletin. Note 2: Boeing Alert Service Bulletin 767-28A0050 refers to Sundstrand Alert Service Bulletin 5006286-28-A8, dated October 10, 1997, as an additional source of service information for accomplishment of the inspection required by paragraph (e) of this AD. Note 3: For the purposes of this AD, a detailed visual inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.” (f) For airplanes equipped with a center tank scavenge system: For any period during which the center fuel tank is deactivated in accordance with Boeing Alert Service Bulletin 767-28A0050, dated December 18, 1997, or Revision 1, dated December 22, 1999, the actions specified by paragraphs (e) and (i) of this AD are not required. As of 36 months after the effective date of this AD, modified fuel pumps must be installed according to paragraph (i) of this AD before the center fuel tank may be reactivated. Pump Replacement (g) For airplanes that are equipped with any override fuel pump having part number S343T002-23, -51, -81, or -121 (which are configured without inlet diffusers): Within 36 months after the effective date of this AD, accomplish the actions specified by either paragraph (g)(1) or (g)(2) of this AD. (1) Replace the override fuel pump with a fuel pump having a machined inlet diffuser installed, in accordance with Boeing Alert Service Bulletin 767-28A0057, dated November 18, 1999. Or (2) Replace the override fuel pump with a fuel pump modified in accordance with paragraph (i) of this AD. (h) For airplanes that are equipped with any override/jettison fuel pump having part number S343T002-23, -51, -81, or -121 (which are configured WITHOUT inlet diffusers): Within 36 months after the effective date of this AD, accomplish the actions specified by either paragraph (h)(1) or (h)(2) of this AD. (1) Replace the override/jettison fuel pump with a fuel pump having a machined inlet diffuser installed, in accordance with Boeing Service Bulletin 767-28-0059, dated December 22, 1999. Or (2) Replace the override/jettison fuel pump with a fuel pump modified in accordance with paragraph (i) of this AD. Installation of New Configuration Pumps (i) For all airplanes: Within 36 months after the effective date of this AD, install modified center tank override and override/jettison fuel pumps that are not subject to the unsafe condition described in this AD. The installation shall be accomplished in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. Note 4: Installation of new configuration override or override/jettison fuel pumps, as applicable, in accordance with Boeing Service Bulletin 767-28-0062, dated December 20, 2000; and a fueling station placard, in accordance with Boeing Service Bulletin 767-28-0063, dated December 20, 2000; or accomplishment of equivalent actions during production; are approved means of compliance with paragraph (i) of this AD. Terminating Action (j) Accomplishment of the requirements of paragraph (e) of this AD constitutes terminating action for the requirements of AD 94-11-05, amendment 39-8921 (59 FR 27970, May 31, 1994). (k) Accomplishment of the requirements of paragraph (i) of this AD constitutes terminating action for the requirements of paragraphs (a), (b), (c), (d), (e), (g), and (h) of this AD, and the requirements of AD 94-11-05, amendment 39-8921. Spares (l) As of the effective date of this AD, no person shall install on any airplane a fuel pump having part number S343T002-5, -8, -12, or -15, unless that pump has been inspected and corrective actions have been performed in accordance with the requirements of either paragraph (b) or (c), and paragraph (e), of this AD. (m) As of the effective date of this AD, no person shall install on any airplane a fuel pump having part number S343T002-23, -51, -81, or -121. Alternative Methods of Compliance (n)(1) 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, Seattle ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. (2) Alternative methods of compliance, approved previously in accordance with AD 97-19-15, amendment 39-10136, are approved as alternative methods of compliance when performing the requirements of paragraphs (b) and (c) of this AD. Note 5: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. Special Flight Permits (o) Special flight permits may be issued in accordance with §§ 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. Incorporation by Reference (p) Except as provided by paragraphs (a), (b), (c), (d), (f), (g)(2), (h)(2), and (i) of this AD; the actions shall be done in accordance with Boeing Alert Service Bulletin 767-28A0050, dated December 18, 1997, or Boeing Service Bulletin 767-28A0050, Revision 1, dated December 22, 1999; Boeing Alert Service Bulletin 767-28A0057, dated November 18, 1999; or Boeing Service Bulletin 767-28-0059, dated December 22, 1999; as applicable. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Effective Date (q) This amendment becomes effective on September 4, 2001. Issued in Renton, Washington, on July 19, 2001. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-18471 Filed 7-30-01; 8:45 am] BILLING CODE 4910-13-U