AD 2000-14-06

[Federal Register Volume 65, Number 135 (Thursday, July 13, 2000)]
[Rules and Regulations]
[Pages 43223-43228]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-17297]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-192-AD; Amendment 39-11815; AD 2000-14-06]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Boeing Model 747 series airplanes, that 
currently requires a one-time inspection to determine the part number 
of the fuel shutoff spar valve for the outboard engines. That AD also 
requires replacement of certain valves with new valves, or modification 
of the spar valve body assembly, and various follow-on actions. This 
amendment adds new requirements to accomplish those actions on 
additional airplanes; and requires a one-time inspection of the 
maintenance records of certain airplanes to determine if the fuel 
shutoff spar valve for the outboard engines has ever been replaced, and 
various follow-on actions. This amendment is prompted by reports 
indicating that, due to high fuel pressure, certain fuel system 
components of the outboard engines have failed. The actions specified 
by this AD are intended to prevent such high fuel pressure, which could 
result in failure of the fuel system components; this situation could 
result in fuel leakage, and, consequently, lead to an engine fire.

DATES: Effective August 17, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 17, 2000.
    The incorporation by reference of certain other publications, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of November 20, 1998 (63 FR 55517, October 16, 
1998).

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207; or ITT Aerospace Controls, 28150 Industry Drive, 
Valencia, California 91355. This information may be examined at the 
Federal Aviation Administration (FAA), Transport Airplane Directorate, 
Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dionne M. Krebs, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Transport Airplane Directorate, 
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-2250; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 98-21-29, 
amendment 39-10837 (63 FR 55517, October 16, 1998); which is applicable 
to Boeing Model 747-100, -200, -300, -400, 747SP, and 747SR series 
airplanes, having line numbers 629 through 1006 inclusive, and powered 
by General Electric or Rolls-Royce engines; was published in the 
Federal Register on November 26, 1999 (64 FR 66419). The action 
proposed to continue to require a one-time inspection to determine the 
part number of the fuel shutoff spar valve for the outboard engines, 
replacement of certain valves with new valves or modification of the 
spar valve body assembly, and various follow-on actions. The action 
proposed to add new requirements to accomplish those actions on 
additional airplanes; and require a one-time inspection of the 
maintenance records of certain airplanes to determine if the fuel 
shutoff spar valve for the outboard engines has ever been replaced, and 
various follow-on actions.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposal

    Three commenters concur with the intent of the proposed rule.

Request to Clarify Airplanes Subject to Paragraph (e)

    Two commenters request that paragraph (e) of the proposed rule be 
revised to clarify that it applies to all affected airplanes (as 
identified in Boeing Service Bulletin 747-28A2199, Revision 2, dated 
July 8, 1999). One

[[Page 43224]]

commenter points out that paragraph (d) of the proposed rule instructs 
operators to check maintenance records on airplanes having line numbers 
1 through 628 inclusive, to determined if the left-and right-hand 
outboard fuel shutoff spar valves have been replaced. If either valve 
has been replaced, paragraph (d)(2) instructs operators to accomplish 
paragraph (e) for that valve. However, paragraph (e) does not state 
that it applies to airplanes having line numbers 1 through 628. The 
commenter states that this has been confusing for several operators. 
The other commenter points out that paragraph (e) of the proposed rule 
addresses airplanes having line numbers 1 through 1006 inclusive 
powered by General Electric (GE) or Rolls-Royce engines, but paragraph 
(a) also refers to airplanes having line numbers 629 through 1006 
inclusive powered by GE or Rolls-Royce engines. Paragraphs (a) and (e) 
require similar actions. The commenter states that this could result in 
unnecessary duplicate inspections for some airplanes.
    The FAA concurs with the commenters' request for clarification of 
the airplanes subject to paragraph (e) of this AD. The intent of this 
AD is that airplanes having line numbers 1 through 628 inclusive that 
had or may have had fuel shutoff spar valves replaced are subject to 
paragraph (e) of this AD, as specified in paragraph (d) of this AD. In 
addition, airplanes having line numbers 629 through 1006 inclusive 
powered by Pratt & Whitney engines are also subject to the requirements 
in paragraph (e). As pointed out by the commenter, the actions 
described in paragraph (e) are equivalent to those required by 
paragraph (a); therefore, the FAA has revised this final rule to remove 
the airplanes having line numbers 629 through 1006 powered by GE or 
Rolls-Royce engines from the applicability of paragraph (e) of this AD. 
To address the commenters' request, paragraphs (d)(1) and (d)(2) of 
this AD have been revised as follows:
    <bullet> Paragraph (d)(1) reads, ``If the maintenance record 
inspection establishes that neither valve has been replaced, no further 
action is required by this AD.
    <bullet> Paragraph (d)(2) reads, ``If either valve has been 
replaced, or if the maintenance record inspection does not clearly 
establish that neither valve has been replaced, prior to further 
flight, accomplish paragraph (e)(1), (e)(2), or (e)(3), as 
applicable.''
    <bullet> Paragraph (e) reads, ``For airplanes having line numbers 
629 through 1006 inclusive and powered by Pratt & Whitney engines, or 
for airplanes having line numbers 1 through 628 inclusive on which a 
fuel shutoff spar valve has been, or may have been, replaced: * * *.''

Request to Refer to Wet Motor Leak Check

    One commenter requests that, if the FAA finds it necessary to 
require a fuel leak check of the engine, the requirement should refer 
specifically to a wet motor leak check. The commenter points out that 
paragraphs (b) and (c), including ``NOTE 3,'' of the proposed rule 
specify accomplishment of a leak check per Aircraft Maintenance Manual 
(AMM) procedures or per Boeing Service Bulletin 747-28A2199, Revision 
2. The applicable AMM procedures describe an idle leak check, while the 
service bulletin describes a wet motor leak check. The commenter also 
notes that paragraphs (f) and (g) of the proposed rule specify a leak 
check in accordance with the service bulletin (that is, a wet motor 
leak check).
    The FAA does not concur with the commenter's request. The FAA 
recognizes that the idle leak checks identified in ``NOTE 3'' and the 
wet motor leak check identified in the service bulletin are not 
identical. However, because both checks involve the pressurization of 
the fuel lines and components between the fuel shutoff spar valve and 
the engine fuel shutoff valve, either check meets the intent of the 
requirement. Therefore, the FAA finds that paragraphs (b) and (c) of 
this AD are acceptable as written because they allow either type of 
check. Also, the FAA has determined that it is appropriate to add a new 
``NOTE 4'' to this final rule, to state that the idle leak checks are 
acceptable for compliance with the actions specified in paragraphs (f) 
and (g) of this AD. (All subsequent ``NOTES'' have been renumbered 
accordingly.)

Request to Expand Applicability of Proposed AD

    One commenter requests that the FAA expand the applicability of the 
proposed AD to include all Model 747 series airplanes delivered prior 
to the effective date of the AD. The commenter states that Model 747 
series airplanes with line numbers higher than 1006 may have improper 
fuel shutoff spar valves installed. The commenter's rationale is that, 
although the proper valves were installed during production, it is 
possible that, during maintenance, one of the original valves has been 
replaced with an improper valve.
    The FAA does not concur with the commenter's request. The airplane 
manufacturer has informed the FAA that, at the time the airplane having 
line number 1007 was delivered, the engineering drawings (including 
drawing notes regarding spare parts) limited the fuel shutoff spar 
valve installed at the outboard engine positions to an acceptable part 
number (S343T003-40). Therefore, operators have not been allowed to 
replace a fuel shutoff spar valve installed at the outboard position 
with an earlier fuel shutoff spar valve since delivery on Model 747 
series airplanes with line number 1007 and subsequent. No change to the 
final rule is necessary in this regard.

Request to Extend Compliance Time

    Several commenters request extension of the compliance time. Two 
commenters request that the compliance time be extended from 18 to 36 
months; another requests a compliance time of four years for Model 747-
100 and -200 series airplanes and six years for Model 747-400 series 
airplanes. The commenters state that an extension would allow operators 
to schedule the inspection during airplane checks when internal access 
to the fuel tanks is available. One commenter states that the 18-month 
compliance time would force it to perform unscheduled fuel tank 
entries. Another commenter notes that, due to the reduced 
interchangeability of valves having part numbers 60B92406-(x), 
additional spare valves will be required, or all valves will have to be 
upgraded to the latest configuration on an attrition basis.
    The FAA infers that the commenters are referring to the compliance 
time for the one-time inspection to determine the part number of fuel 
shutoff spar valve for the left- and right-hand outboard engines. The 
FAA does not concur with the commenters' requests to extend the 
compliance time. In the final rule for AD 98-21-29, which this AD 
supersedes, the FAA agreed to extend the compliance time from 12 to 18 
months to allow the inspection to be accomplished during a regularly 
scheduled maintenance visit for the majority of the affected fleet. 
This would allow airplanes to be inspected at a location where special 
equipment and trained personnel would be readily available, if 
necessary. A compliance time of 18 months corresponds to most 
operators' scheduled ``C''-checks and, therefore, accommodates the 
majority of operators' maintenance schedules while not adversely 
affecting flight safety. Because the compliance time has already been 
extended in this way, the FAA has determined that it is inappropriate 
to extend it further. No change to the final rule is necessary in this 
regard.

[[Page 43225]]

Request to Make Restatement of Requirements Consistent With New 
Requirements

    One commenter requests that paragraph (a)(1) of the proposed AD be 
revised to be consistent with paragraph (e)(2) of the proposed AD. The 
commenter notes that paragraph (a) of the proposed rule instructs 
operators to inspect the part number of the left- and right-hand 
outboard fuel shutoff (spar) valves on airplanes having line numbers 
629 through 1006 inclusive powered by General Electric (GE) or Rolls-
Royce engines, and paragraph (a)(1) identifies the acceptable fuel 
shutoff spar valve part number as S343T003-43. The commenter also notes 
that paragraph (e)(2) of the proposed rule lists additional modified 
valve part numbers that are acceptable for installation. The commenter 
suggests that paragraph (a)(1) be revised to be consistent with 
paragraph (e)(2) with regard to acceptable part numbers.
    The FAA does not concur with the commenter's request. The FAA 
infers that the part number in paragraph (a)(1) to which the commenter 
refers is S343T003-40 (not S343T003-43). The FAA acknowledges that the 
restatement of requirements of AD 98-21-29 in paragraph (a) of the 
proposed rule identifies fuel shutoff spar valve part number S343T003-
40 only, though paragraph (e)(2) lists other acceptable part numbers. 
The additional part numbers in paragraph (e)(2) have been included in 
this AD because the FAA incorporated an existing approved alternative 
method of compliance (AMOC) to AD 98-21-29 into this AD. Because 
paragraphs (a), (b), and (c) of this AD are a restatement of the 
requirements of AD 98-21-29 (and are labeled as such), the FAA finds 
that it is unnecessary and potentially confusing to operators to 
incorporate the part numbers referenced in paragraph (e)(2) of this AD 
into paragraph (a)(1) of this AD. No change to the final rule is 
necessary in this regard.

Request to Eliminate Requirement for Fuel Leak Check

    One commenter requests that the fuel leak check specified in 
paragraphs (b), (c), (f), and (g) of the proposed rule be eliminated. 
The commenter states that a fuel leak check of the engine, as 
identified in these paragraphs, is not necessary. The commenter 
acknowledges that the leak checks are intended to identify damage to 
components between the fuel shutoff spar valve and the engine fuel 
shutoff valve, resulting from a fuel overpressure condition. The 
commenter states that all known in-service occurrences of the failure 
of components associated with this AD have been ``ultimate'' failures 
and not ``fatigue-type'' failures. The commenter asserts that a fuel 
leak would be evident upon engine installation, when a fuel leak check 
is required as part of post-installation tests, or during normal in-
service operation.
    The FAA does not concur with the commenter's request. The FAA 
acknowledges that a fuel leak may become evident upon engine 
installation, during a post-installation fuel leak check, or during 
normal operation. However, because the unsafe condition associated with 
this AD is fuel leakage that could result in an engine fire, the FAA 
considers it necessary to verify the integrity of any replaced fuel 
shutoff spar valves and fuel system components that may have been 
previously exposed to high-pressure fuel. In the case of design 
deficiencies that could lead to engine fires, the FAA considers it 
necessary to prevent such events from occurring on in-service 
airplanes. Therefore, no change to the final rule is necessary in this 
regard.

Request to Revise Cost Estimate

    Two commenters request that the FAA revise the cost impact estimate 
in the proposed rule to reflect the estimate of 75 work hours given in 
Boeing Service Bulletin 747-28A2199, Revision 2. One of the commenters 
points out that, for Model 747-100, -200, and -300 series airplanes, a 
removable rib must be taken out to gain access to the fuel shutoff spar 
valves. The other commenter states that the estimate in the proposal is 
considerably too low and does not include the work hours or cost of 
materials necessary for modification of the valves, which the commenter 
estimates to be 3 work hours and $200 per valve.
    The FAA does not concur with the commenters' request. The cost 
impact information in AD rulemaking actions describes only the 
``direct'' costs of the specific actions required by this AD. The cost 
information typically does not include incidental costs, such as the 
time required to gain access and close up, planning time, or time 
necessitated by other administrative actions. The FAA recognizes that, 
in accomplishing the requirements of any AD, operators may incur 
``incidental'' costs in addition to the ``direct'' costs. Because 
incidental costs may vary significantly from operator to operator, they 
are almost impossible to calculate.
    With regard to the comment that the proposed rule does not account 
for the time necessary to modify each valve, the proposed rule only 
requires installation of a fuel shutoff spar valve with an acceptable 
part number. Though operators may choose to modify a discrepant fuel 
shutoff spar valve to create an acceptable part, the AD does not 
actually require this modification. Therefore, the cost of the 
modification is not included in the cost impact estimate. No change to 
the final rule is necessary in this regard.

Request to Confirm AMOC Approval

    One commenter requests that the FAA confirm that AMOC's approved 
for AD 98-21-29 will be acceptable for compliance with the proposed 
rule. The commenter has previously received FAA approval of an AMOC for 
AD 98-21-29.
    The FAA concurs that AMOC's previously approved in accordance with 
AD 98-21-29 are approved for compliance with paragraphs (a), (a)(1), 
(a)(2), (a)(2)(i), (b), and (c) of this AD. Paragraph (h)(2) of the 
proposed rule, and this final rule, states this approval. No change to 
the final rule is necessary in this regard.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 987 Model 747 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 208 
airplanes of U.S. registry will be affected by this AD.
    The one-time inspection to determine the part number of the valve 
that is currently required by AD 98-21-29 and retained in this AD 
affects approximately 59 airplanes of U.S. registry, and takes 
approximately 4 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of this currently required inspection on U.S. operators is 
estimated to be $14,160, or $240 per airplane.
    Should an operator be required to accomplish the one-time 
inspection to detect leaks and cracks (after replacement of the valve 
or modification of the assembly) that is currently required by AD 98-
21-29 and retained in this AD, it will take approximately 16

[[Page 43226]]

work hours per airplane, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of this inspection is estimated 
to be $960 per airplane.
    The new one-time inspection of the maintenance records of the 
airplane that is required by this AD action affects approximately 149 
airplanes of U.S. registry, and takes approximately 2 work hours per 
airplane to accomplish, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of this required inspection on 
U.S. operators is estimated to be $17,880, or $120 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted.
    Should an operator elect to modify the valve body assembly of the 
fuel system rather than replace a discrepant valve, it would take 
approximately 20 work hours per airplane, at an average labor rate of 
$60 per work hour. Required parts would cost approximately $404 (2 
kits) per airplane. Based on these figures, the cost impact of this 
modification is estimated to be $1,604 per airplane.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect on the States, on the relationship between the national 
Government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-10837 (63 FR 
55517, October 16, 1998), and by adding a new airworthiness directive 
(AD), amendment 39-11815, to read as follows:
2000-14-06 Boeing: Docket 99-NM-192-AD. Amendment 39-11815. 
Supersedes AD 98-21-29, Amendment 39-10837.

    Applicability: Model 747 series airplanes, line numbers 1 
through 1006 inclusive, 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 (h)(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.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent high fuel pressure in components between the fuel 
shutoff spar valve and the engine fuel shutoff valve, which could 
result in failure of the fuel system components, lead to fuel 
leakage, and, consequently, lead to a possible engine fire, 
accomplish the following:

Restatement of Actions Required By AD 98-21-29, Amendment 39-10837:

One-Time Inspection

    (a) For airplanes having line numbers 629 through 1006 inclusive 
and powered by General Electric or Rolls-Royce engines: Within 18 
months after November 20, 1998 (the effective date of AD 98-21-29, 
amendment 39-10837), perform a one-time inspection to determine the 
part number of the fuel shutoff spar valve for the left-and right-
hand outboard engines, in accordance with Boeing Alert Service 
Bulletin 747-28A2199, dated August 1, 1996; Boeing Service Bulletin 
747-28A2199, Revision 1, dated October 1, 1998; or Boeing Service 
Bulletin 747-28A2199, Revision 2, dated July 8, 1999.

Replacement

    (1) If a valve having part number (P/N) S343T003-40 (ITT P/N 
125334D-1) is installed, no further action is required by this AD.
    (2) If a valve having P/N S343T003-40 (ITT P/N 125334D-1) is not 
installed, prior to further flight, accomplish either paragraph 
(a)(2)(i) or (a)(2)(ii) of this AD.
    (i) Replace the valve with a new valve, in accordance with the 
service bulletin.
    Prior to further flight following accomplishment of the 
replacement, align the valve(s), perform a check to detect leaks, 
and correct any discrepancy, in accordance with the service 
bulletin. Or
    (ii) Modify the valve body assembly of the fuel system in 
accordance with ITT
    Service Bulletin SB125120-28-01, ITT Service Bulletin SB107970-
28-01, and ITT Service Bulletin SB125334-28-01; all dated July 15, 
1996.

Inspection

    (b) For airplanes having line numbers 629 through 1006 inclusive 
and powered by General Electric or Rolls-Royce engines: Except as 
provided in paragraph (c) of this AD, prior to further flight 
following accomplishment of paragraph (a)(2) of this AD, perform a 
one-time general visual inspection to detect fuel leaks of the 
components between the fuel shutoff spar valve and the engine fuel 
shutoff valve on all four engines, in accordance with the applicable 
section that pertains to Rolls-Royce RB211 series engines or General 
Electric CF6-80C and CF6-45/50 series engines in Chapter 71 of the 
Boeing 747 Airplane Maintenance Manual (AMM), or Boeing Service 
Bulletin 747-28A2199, Revision 2, dated July 8, 1999. If any leak is 
detected, prior to further flight, replace the part with a 
serviceable part. No further action is required by this AD.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as:

    ``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 under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, and may require removal or

[[Page 43227]]

opening of access panels or doors. Stands, ladders, or platforms may 
be required to gain proximity to the area being checked.''
    (c) For airplanes having line numbers 629 through 1006 
inclusive, powered by General Electric or Rolls-Royce engines, and 
having maintenance records that positively demonstrate that the 
inboard engines have never been located in the outboard position:
    Prior to further flight following accomplishment of paragraph 
(a)(2) of this AD, perform a one-time general visual inspection to 
detect fuel leaks of the components between the fuel shutoff spar 
valve and the engine fuel shutoff valve on the outboard engines 
only, in accordance with the applicable section that pertains to 
Rolls-Royce RB211 series engines or General Electric CF6-80C and 
CF6-45/50 series engines in Chapter 71 of the Boeing 747 AMM, or 
Boeing Service Bulletin 747-28A2199, Revision 2, dated July 8, 1999. 
If any leak is detected, prior to further flight, replace the part 
with a serviceable part. No further action is required by this AD.

    Note 3: Accomplishment of the actions specified in AMM 71-00-00/
501, Test No. 2, ``Fuel and Oil Leak Check,'' for Rolls-Royce RB211 
series engines, and AMM 71-00-00/501, Test No. 3, ``Ground Test--
Idle Leak Check ( or Idle Power),'' for General Electric CF6-80C and 
CF6-45/50 series engines, is acceptable for compliance with the 
actions specified by paragraphs (b) and (c) of this AD.

New Actions Required By This AD:

Inspection

    (d) For airplanes having line numbers 1 through 628 inclusive: 
Within 18 months after the effective date of this AD, perform a one-
time inspection of the maintenance records of the airplane to 
determine if the fuel shutoff spar valve for the left-and right-hand 
outboard engines has ever been replaced, in accordance with Boeing 
Service Bulletin 747-28A2199, Revision 2, dated July 8, 1999.
    (1) If the maintenance record inspection establishes that 
neither valve has been replaced, no further action is required by 
this AD.
    (2) If either valve has been replaced, or if the maintenance 
record inspection does not clearly establish that neither valve has 
been replaced, prior to further flight, accomplish paragraph (e)(1), 
(e)(2), or (e)(3), as applicable.
    (e) For airplanes having line numbers 629 through 1006 inclusive 
and powered by Pratt & Whitney engines, or for airplanes having line 
numbers 1 through 628 inclusive on which a fuel shutoff spar valve 
has been, or may have been, replaced: Within 18 months after the 
effective date of this AD, perform a one-time inspection to 
determine the part number of the fuel shutoff spar valve for the 
left-and right-hand outboard engines, as applicable, in accordance 
with Boeing Alert Service Bulletin 747-28A2199, dated August 1, 
1996; Boeing Service Bulletin 747-28A2199, Revision 1, dated October 
1, 1998; or Boeing Service Bulletin 747-28A2199, Revision 2, dated 
July 8, 1999.

Replacement

    (1) If a valve having P/N S343T003-40 (ITT P/N 125334D-1) is 
installed, no further action is required by this AD.
    (2) If a valve having P/N 60B92406-161 (ITT P/N 125334-1), P/N 
60B92406-81 (ITT P/N 125120-1), or P/N 60B92406-201 (ITT P/N 107970-
1) is installed, accomplish either paragraph (f) or (g) of this AD, 
as applicable.
    (3) If a valve having P/N S343T003-40 (ITT P/N 125334D-1), P/N 
60B92406-161 (ITT P/N 125334-1), P/N 60B92406-81 (ITT P/N 125120-1), 
or P/N 60B92406-201 (ITT P/N 107970-1) is not installed, prior to 
further flight, accomplish either paragraph (e)(3)(i) or (e)(3)(ii), 
and either paragraph (f) or (g) of this AD, as applicable.
    (i) Replace the valve with a new valve, in accordance with the 
service bulletin. Prior to further flight following accomplishment 
of the replacement, align the valve(s), perform a check to detect 
leaks, and correct any discrepancy, in accordance with the service 
bulletin. Or
    (ii) Modify the valve body assembly of the fuel system in 
accordance with ITT
    Service Bulletin SB125120-28-01, ITT Service Bulletin SB107970-
28-01, and ITT Service Bulletin SB125334-28-01; all dated July 15, 
1996.

Inspection

    (f) Expect as provided in paragraph (g) of this AD, prior to 
further flight following accomplishment of paragraph (e) of this AD, 
perform a one-time general visual inspection to detect fuel leaks of 
the components between the fuel shutoff spar valve and the engine 
fuel shutoff valve on all four engines, in accordance with Boeing 
Service Bulletin 747-28A2199, Revision 2, dated July 8, 1999. If any 
leak is detected, prior to further flight, replace the part with a 
serviceable part.
    (g) For airplanes having maintenance records that positively 
demonstrate that the inboard engines have never been located in the 
outboard position: Prior to further flight following accomplishment 
of paragraph (e) of this AD, perform a one-time general visual 
inspection to detect fuel leaks of the components between the fuel 
shutoff spar valve and the engine fuel shutoff valve on the outboard 
engines only, in accordance with Boeing Service Bulletin 747-
28A2199, Revision 2, dated July 8, 1999. If any leak is detected, 
prior to further flight, replace the part with a serviceable part.

    Note 4: Accomplishment of the actions specified in AMM 71-00-00/
501, Test No. 2, ``Fuel and Oil Leak Check,'' for Rolls-Royce RB211 
series engines, and AMM 71-00-00/501, Test No. 3, ``Ground Test--
Idle Leak Check (or Idle Power),'' for General Electric CF6-80C and 
CF6-45/50 series engines, is acceptable for compliance with the 
actions specified by paragraphs (f) and (g) of this AD.

Alternative Methods of Compliance

    (h)(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 Aircraft Certification 
Office (ACO), FAA, Transport Airplane Directorate. 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 98-21-29, amendment 39-10837, are approved as 
alternative methods of compliance with paragraph (a), (a)(1), 
(a)(2), (a)(2)(i), (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

    (i) Special flight permits may be issued in accordance with 
sections 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

    (j) Except as provided by paragraphs (b) and (c) of this AD, the 
actions shall be done in accordance with Boeing Alert Service 
Bulletin 747-28A2199, dated August 1, 1996; Boeing Service Bulletin 
747-28A2199, Revision 1, dated October 1, 1998; Boeing Service 
Bulletin 747-28A2199, Revision 2, dated July 8, 1999; ITT Service 
Bulletin SB125120-28-01, dated July 15, 1996; ITT Service Bulletin 
SB107970-28-01, dated July 15, 1996; or ITT Service Bulletin 
SB125334-28-01, dated July 15, 1996; as applicable.
    (1) The incorporation by reference of Boeing Service Bulletin 
747-28A2199,

[[Page 43228]]

Revision 1, dated October 1, 1998; and Boeing Service Bulletin 747-
28A2199, Revision 2, dated July 8, 1999; is approved by the Director 
of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51.
    (2) The incorporation by reference of Boeing Alert Service 
Bulletin 747-28A2199, dated August 1, 1996; ITT Service Bulletin 
SB125120-28-01, dated July 15, 1996; ITT Service Bulletin SB107970-
28-01, dated July 15, 1996; and ITT Service Bulletin SB125334-28-01, 
dated July 15, 1996; was approved previously by the Director of the 
Federal Register as of November 20, 1998 (63 FR 55517, October 16, 
1998).
    (3) Copies may be obtained from Boeing Commercial Airplane 
Group, P.O. Box 3707, Seattle, Washington 98124-2207; or ITT 
Aerospace Controls, 28150 Industry Drive, Valencia, California 
91355. 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

    (k) This amendment becomes effective on August 17, 2000.

    Issued in Renton, Washington, on July 3, 2000.
Vi L. Lipki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-17297 Filed 7-12-00; 8:45 am]
BILLING CODE 4910-13-U