[Federal Register Volume 66, Number 32 (Thursday, February 15, 2001)]
[Proposed Rules]
[Pages 10393-10396]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-3859]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-317-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), which applies to all Boeing Model 747 
series airplanes. The existing AD currently requires, for certain 
airplanes, revising the Airplane Flight Manual, and, for all airplanes, 
performing repetitive inspections for wear or damage of the inlet check 
valves and inlet adapters of the override/jettison pumps, and 
corrective actions, if necessary. This action would apply to fewer 
airplanes than the existing AD and require rework of certain 
components, which would end the repetitive inspection requirement. 
These actions are necessary to ensure that the flight crew is advised 
of the hazards of dry operation of the override/jettison pumps of the 
center wing fuel tank, and to prevent wear or damage to the inlet check 
valves and inlet adapters of the override/jettison pumps, which could 
result in a fire or explosion in the fuel tank during dry (no fuel) 
operation. This action is intended to address the identified unsafe 
condition.

DATES: Comments must be received by April 2, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-317-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-317-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Sulmo Mariano, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone 
(425) 227-2686; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the proposed 
AD is being requested.
     Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-317-AD.'' The postcard will be date-stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2000-NM-317-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On July 30, 1998, the FAA issued AD 98-16-19, amendment 39-10695 
(63 FR 42210, August 7, 1998), applicable to all Boeing Model 747 
series airplanes. That AD requires, for certain airplanes, revising the 
Airplane Flight Manual (AFM) to advise the flightcrew of limitations on 
dry (no fuel) operation of the override/jettison pumps of the center 
wing fuel tank. That AD also requires repetitive inspections for wear 
or damage of the inlet check valves and inlet adapters of the override/
jettison pumps, and replacement of the check valves and pumps with new 
or serviceable parts, if necessary. For affected airplanes, such 
replacement allows the AFM revision to be removed. That AD was prompted 
by a report that inlet adapters of override/jettison pumps were found 
to be worn excessively, which allowed contact to occur between the 
inlet check valve and the inducer. The requirements of that AD are 
intended to ensure that the flightcrew is advised of the hazards of dry 
operation of the override/jettison pumps of the center wing fuel tank, 
and to detect and correct wear or damage to the inlet check valves and 
inlet adapters of the override/jettison pumps. Such conditions, if not 
corrected, could result in a fire or explosion in the fuel tank during 
dry operation.

Actions Since Issuance of Previous Rule

    The preamble to AD 98-16-19 stated that the FAA considered the 
requirements of that AD to be ``interim action'' and that the 
manufacturer was

[[Page 10394]]

developing a modification to positively address the unsafe condition. 
The FAA indicated that it might consider further rulemaking action once 
the modification was developed, approved, and available. The 
manufacturer now has developed such a modification, and the FAA has 
determined that further rulemaking action is indeed necessary. This 
proposed AD follows from that determination.
    Also, the existing AD applies to all Boeing Model 747 series 
airplanes. Boeing has informed the FAA that the approved modification 
will be installed on all Model 747 series airplanes having line number 
1252 and subsequent. The FAA has determined that installation of the 
modification during production is adequate to address the unsafe 
condition. Therefore, the FAA finds that the actions required by the 
existing AD and the actions in this proposed AD are not necessary for 
airplanes modified in production, which leads the FAA to remove those 
airplanes from the applicability of this proposed AD.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Service Bulletin 747-
28A2212, Revision 3, dated August 3, 2000. That service bulletin 
describes actions identical to those in Boeing Alert Service Bulletin 
747-28A2212, Revision 2, dated May 14, 1998, which was referenced in 
the existing AD as the appropriate source of service information. 
Revision 3 of the service bulletin also describes procedures for a 
terminating action that entails rework of the existing pump housing and 
impeller motor assembly, which includes replacement of the existing 
inlet check valve and inlet adapter with new, improved parts, and 
reidentification of the pump housing and impeller motor assembly with 
new part numbers. This rework eliminates the need for the currently 
required repetitive inspections. Accomplishment of the actions 
specified in Revision 3 of the service bulletin is intended to 
adequately address the identified unsafe condition.
    Revision 3 of the service bulletin refers to Crane Hydro-Aire 
Service Bulletins 60-703-28-33, 60-703-28-35, 60-721-28-5, and 60-723-
28-5, as secondary sources of information for the rework of the pump 
housing and impeller motor assembly. The FAA has reviewed Revision 1 of 
these service bulletins, all dated November 20, 2000, and finds them 
acceptable secondary sources of information for the rework.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would supersede AD 98-16-19 to continue to require 
repetitive inspections for wear or damage of the inlet check valves and 
inlet adapters of the override/jettison pumps, and corrective actions, 
if necessary. This proposed AD would also continue to require, for 
certain airplanes, revising the Airplane Flight Manual (AFM) to advise 
the flightcrew of limitations on dry (no fuel) operation of the 
override/jettison pumps of the center wing fuel tank, until the 
repetitive inspections described above have been done. This action 
would apply to fewer airplanes than the existing AD, and would add a 
new requirement for rework of the existing pump housing and impeller 
motor assembly, which would end the repetitive inspection requirement. 
The actions would be required to be accomplished in accordance with the 
service bulletin described previously, except as discussed below.

Differences Between This Proposed AD and the Service Bulletin

    As stated above, Revision 3 of the service bulletin describes 
procedures for rework of the existing pump housing and impeller motor 
assembly, which gets rid of the need for the repetitive inspections. 
The service bulletin provides for the rework as optional. The FAA finds 
it necessary to require operators to do this rework. The decision to 
propose the rework is based on the FAA's position that modifications or 
design changes to remove the source of a problem will ensure continued 
operational safety over the long term better than repetitive 
inspections. The view that repetitive inspections may be inadequate to 
ensure the safety of the transport airplane fleet, along with 
consideration of the human factors associated with repetitive 
inspections, has led the FAA to place less emphasis on special 
procedures, such as repetitive inspections, and more emphasis on design 
improvements.
    In developing the 18-month compliance time for this action, the FAA 
considered these factors:
     The urgency of the subject unsafe condition,
     The amount of time it takes to do the replacement (10 work 
hours), and
     The amount of time needed to allow most operators to do 
the replacement during normal scheduled maintenance.
    The FAA finds that 18 months is the optimal amount of time that 
will allow the rework to be done on all affected airplanes without 
compromising flight safety.

Cost Impact

    There are approximately 1,100 airplanes of the affected design in 
the worldwide fleet. The FAA estimates that 250 airplanes of U.S. 
registry would be affected by this proposed AD.
    For affected airplanes, the AFM revision currently required by AD 
98-16-19 takes approximately 1 work hour per airplane to accomplish, at 
an average labor rate of $60 per work hour. Based on these figures, the 
FAA estimates that the cost impact of this action is $60 per airplane.
    The inspections currently required by AD 98-16-19 take 
approximately 12 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the FAA 
estimates that the cost impact of this action on U.S. operators is 
$180,000, or $720 per airplane, per inspection cycle.
    The rework proposed in this AD action would take approximately 6 
work hours per airplane to accomplish, at an average labor rate of $60 
per work hour. Required parts would cost approximately $1,978 per 
airplane. Based on these figures, the FAA estimates that the cost 
impact of the proposed replacement on U.S. operators is $584,500, or 
$2,338 per airplane. The FAA has been advised that manufacturer 
warranty remedies may be available for labor costs and parts associated 
with accomplishing the proposed rework. Therefore, the future economic 
cost impact of this action on U.S. operators may be less than the cost 
impact figure indicated above.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the proposed requirements 
of this AD action, and that no operator would accomplish those actions 
in the future if this proposed AD were not adopted. The cost impact 
figures discussed in AD rulemaking actions represent only the time 
necessary to perform the specific actions actually required by the AD. 
These figures typically do not include incidental costs, such as the 
time required to gain access and close up, planning time, or time 
necessitated by other administrative actions.

Regulatory Impact

    The regulations proposed herein would 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.

[[Page 10395]]

    Therefore, it is determined that this proposal would not have 
federalism implications under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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 39-10695 (63 FR 
42210, August 7, 1998), and by adding a new airworthiness directive 
(AD), to read as follows:

Boeing: Docket 2000-NM-317-AD. Supersedes AD 98-16-19, Amendment 39-
10695.

    Applicability: Model 747 series airplanes, line numbers 1 
through 1251 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 (f)(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 ensure that the flightcrew is advised of the hazards of dry 
operation of the override/jettison pumps of the center wing fuel 
tank, and to prevent wear or damage to the inlet check valves and 
inlet adapters of the override/jettison pumps, which could result in 
a fire or explosion in the fuel tank during dry operation, 
accomplish the following:

Restatement of Requirements of AD 98-16-19

Airplane Flight Manual Revision

    (a) For airplanes that have accumulated 20,000 total hours time-
in-service or more as of August 24, 1998 (the effective date of AD 
98-16-19, amendment 39-10695): Within 14 days after August 24, 1998, 
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 into the AFM.
    ``If the center tank override/jettison fuel pumps are to be 
used, there must be at least 17,000 pounds (7,720 kilograms) of fuel 
in the center tank prior to engine start.
    ``Do not operate the center tank override/jettison fuel pumps 
with less than 7,000 pounds (3,200 kilograms) of fuel in the center 
tank. For airplanes with an inoperative center tank scavenge system, 
this 7,000 pounds of center tank fuel must be considered unusable.
    ``If the center tank override/jettison fuel pumps circuit 
breakers are tripped, do not reset.''

Repetitive Inspections and Corrective Actions

    (b) Prior to the accumulation of 10,000 total hours time-in-
service, or within 90 days after August 24, 1998, whichever occurs 
later, accomplish the requirements of paragraphs (b)(1) and (b)(2) 
of this AD, in accordance with the Accomplishment Instructions 
specified in Boeing Alert Service Bulletin 747-28A2212, Revision 2, 
dated May 14, 1998, or Revision 3, dated August 3, 2000.
    (1) Perform a detailed visual inspection for wear or damage of 
the inlet check valve of the left and right override/jettison pumps 
of the center wing fuel tank.
    (i) If the inlet check valve passes all wear and damage 
criteria, as specified in Figure 3 of the service bulletin, 
accomplish the actions specified in paragraph (b)(1)(i)(A), 
(b)(1)(i)(B), or (b)(1)(i)(C) of this AD, as applicable.
    (A) If the wear to the stainless steel disk is less than or 
equal to 0.70 inch, and does not penetrate the disk, repeat the 
inspection thereafter at intervals not to exceed 10,000 hours time-
in-service after the last inspection, until paragraph (d) of this AD 
has been done.
    (B) If the wear to the stainless steel disk is greater than 0.70 
inch, and does not penetrate the disk, repeat the inspection 
thereafter at intervals not to exceed 1,000 hours time-in-service 
after the last inspection, until paragraph (d) of this AD has been 
done.
    (C) If the wear penetrates the stainless steel disk of the inlet 
check valve, prior to further flight, accomplish the actions 
specified in paragraph (b)(1)(ii) of this AD.
    (ii) If the inlet check valve fails any wear or damage criteria, 
as specified in Figure 3 of the service bulletin, prior to further 
flight, replace the existing check valve with a new or serviceable 
check valve, in accordance with the service bulletin. Repeat the 
inspection thereafter at intervals not to exceed 10,000 hours time-
in-service after the last inspection, until paragraph (d) of this AD 
has been done.
    (2) Perform a detailed visual inspection for wear or damage of 
the inlet adapter of the left and right override/jettison pumps of 
the center wing fuel tank.
    (i) If the wear to the inlet adapter is less than or equal to 
0.50 inch, prior to further flight, reinstall the existing override/
jettison pump, in accordance with the alert service bulletin. Repeat 
the inspection thereafter at intervals not to exceed 10,000 hours 
time-in-service after the last inspection, until paragraph (d) of 
this AD has been done.
    (ii) If the wear to the inlet adapter is greater than 0.50 inch, 
but less than 0.60 inch, prior to further flight, accomplish the 
actions required by either paragraph (b)(2)(ii)(A) or (b)(2)(ii)(B), 
in accordance with the service bulletin.
    (A) Install a new or serviceable override/jettison pump, and 
repeat the inspection thereafter at intervals not to exceed 10,000 
hours time-in-service after the last inspection, until paragraph (d) 
of this AD has been done. Or
    (B) Reinstall the existing override/jettison pump, and repeat 
the inspection thereafter at intervals not to exceed 1,000 hours 
time-in-service after the last inspection, until paragraph (d) of 
this AD has been done.
    (iii) If the wear to the inlet adapter is greater than or equal 
to 0.60 inch, prior to further flight, install a new or serviceable 
override/jettison pump, in accordance with the service bulletin. 
Repeat the inspection thereafter at intervals not to exceed 10,000 
hours time-in-service after the last inspection, until paragraph (d) 
of this AD has been done.

    Note 2: Boeing Alert Service Bulletin 747-28A2212, Revision 2, 
dated May 14, 1998, and Revision 3, dated August 3, 2000, include 
figures that illustrate specific areas to inspect for wear and 
damage.


    Note 3: Accomplishment of the actions specified in paragraph (b) 
of this AD prior to August 24, 1998, in accordance with Revision 1 
of Boeing Alert Service Bulletin 747-28A2212, dated April 23, 1998, 
is considered acceptable for compliance with paragraph (b) of this 
AD.

Terminating Action for Paragraph (a)

    (c) Accomplishment of the actions specified by paragraph (b) of 
this AD constitutes terminating action for the requirements of 
paragraph (a) of this AD. Following accomplishment of those actions, 
the AFM revision may be removed from the AFM.

New Requirements of This AD

Replacement of Pump Housing and Impeller Motor Assembly

    (d) Within 18 months after the effective date of this AD: Rework 
the existing pump

[[Page 10396]]

housing and impeller motor assembly, including replacing the 
existing inlet check valve and inlet adapter with new, improved 
parts; in accordance with Boeing Service Bulletin 747-28A2212, 
Revision 3, dated August 3, 2000. This replacement ends the 
requirements of paragraphs (a) and (b) of this AD.

    Note 4: Boeing Service Bulletin 747-28A2212, Revision 3, 
references Crane Hydro-Aire Service Bulletins 60-703-28-33, 60-703-
28-35, 60-721-28-5, and 60-723-28-5, as secondary sources of 
information for the rework of the pump housing and impeller motor 
assembly.

Spares

    (e) As of the effective date of this AD, no person may install a 
pump housing or impeller motor assembly with a part number listed in 
the ``Existing Part Number'' column of the table in Paragraph 2.E. 
of Boeing Service Bulletin 747-28A2212, Revision 3, dated August 3, 
2000, on any airplane.

Alternative Methods of Compliance

    (f)(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. 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 98-16-19, amendment 39-10695, are approved as 
alternative methods of compliance with the corresponding 
requirements 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

    (g) 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.

    Issued in Renton, Washington, on February 9, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-3859 Filed 2-14-01; 8:45 am]
BILLING CODE 4910-13-U