[Federal Register Volume 75, Number 239 (Tuesday, December 14, 2010)]
[Proposed Rules]
[Pages 77793-77795]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-31375]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1158; Directorate Identifier 2010-NM-125-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 747 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to all Model 747 airplanes. The existing AD 
currently requires repetitive inspections to detect damage of the 
sleeving and wire bundles of the boost pumps of the numbers 1 and 4 
main fuel tanks, and of the auxiliary tank jettison pumps (if 
installed); replacement of any damaged sleeving with new sleeving; and 
repair or replacement of any damaged wires with new wires. For 
airplanes on which any burned wires are found, the existing AD also 
requires an inspection to detect damage of the conduit, and replacement 
of any damaged conduit with a serviceable conduit. This proposed AD 
would reduce the initial compliance time and repetitive inspection 
interval in the existing AD. This proposed AD results from fleet 
information indicating that the repetitive inspection interval in the 
existing AD is too long because excessive chafing of the sleeving 
continues to occur much earlier than expected between scheduled 
inspections. We are proposing this AD to detect and correct abrasion of 
the Teflon sleeving and wires in the bundles of the fuel boost pumps 
for the numbers 1 and 4 main fuel tanks and of the auxiliary tank 
jettison pumps (if installed), which could result in electrical arcing 
between the wires and aluminum conduit and consequent fire or explosion 
of the fuel tank.

DATES: We must receive comments on this proposed AD by January 28, 
2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, P. 
O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail [email protected]; 
Internet https://www.myboeingfleet.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information 
on the availability of this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility between 
9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The 
AD docket contains this proposed AD, the regulatory evaluation, any 
comments received, and other information. The street address for the 
Docket Office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Jon Regimbal, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone 
(425) 917-6506; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-1158; 
Directorate Identifier 2010-NM-125-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On December 9, 1997, we issued AD 97-26-07, Amendment 39-10250 (62 
FR 65352, December 12, 1997), for all Model 747 airplanes. That AD 
currently requires repetitive inspections to detect damage of the 
sleeving and wire bundles of the boost pumps of the numbers 1 and 4 
main fuel tanks, and of the auxiliary tank jettison pumps (if 
installed); replacement of any damaged sleeving with new sleeving; and 
repair or replacement of any damaged wires with new wires. For 
airplanes on which any burned wires are found, that AD also requires an 
inspection to detect damage of the conduit, and replacement of any 
damaged conduit with a serviceable conduit. That AD resulted from 
reports of chafing of the sleeving. We issued that AD to detect and 
correct abrasion of the Teflon sleeving and wires in the bundles of the 
fuel boost pumps for the numbers 1 and 4 main fuel tanks and of the 
auxiliary tank jettison pumps (if installed), which could result in 
electrical arcing between the wires and the aluminum conduit and 
consequent fire or explosion of the fuel tank.

Actions Since Existing AD Was Issued

    Since we issued AD 97-26-07, we received fleet information from the 
manufacturer indicating that excessive chafing of the sleeving 
continues to occur much earlier than expected between scheduled 
inspections. Due to that fact, the manufacturer has revised the service 
information to reduce the repetitive inspection intervals.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 747-28A2204, 
Revision 3, dated March 11, 2010. The service information reduces the 
initial compliance time and repetitive inspection interval for 
detecting damage

[[Page 77794]]

of the sleeving and wire bundles of the boost pumps of the numbers 1 
and 4 main fuel tanks, and of the auxiliary tank jettison pumps (if 
installed) specified in Boeing Service Bulletin 747-28A2204, Revision 
1, dated October 30, 1997. Revision 1 of this service bulletin was 
referred to in AD 97-26-07 as the appropriate source of service 
information for accomplishing the specified actions. The actions 
described in Revision 3 of this service bulletin are essentially the 
same as those described in Revision 1 of this service bulletin.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to develop on other airplanes of the 
same type design. For this reason, we are proposing this AD, which 
would supersede AD 97-26-07 and would retain the requirements of the 
existing AD at reduced compliance times.

Change to Existing AD

    This proposed AD would retain all requirements of AD 97-26-07. 
Since AD 97-26-07 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                           Corresponding requirement in
  Requirement in AD 97[dash]26[dash]07           this proposed AD
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paragraph (a)..........................  paragraph (g).
paragraph (b)..........................  paragraph (h).
paragraph (c)..........................  paragraph (i).
paragraph (d)..........................  paragraph (j).
paragraph (e)..........................  paragraph (k).
paragraph (f)..........................  paragraph (l).
paragraph (g)..........................  paragraph (m).
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Costs of Compliance

    There are about 772 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 215 airplanes of 
U.S. registry. The new requirements of this proposed AD add no 
additional economic burden. The current costs for this proposed AD are 
repeated below for the convenience of affected operators.
    The actions that are required by AD 97-26-07 and retained in this 
proposed AD take about 4 work-hours per airplane, at an average labor 
rate of $85 per work-hour. Based on these figures, the estimated cost 
of the currently required actions is $73,100, or $340 per airplane, per 
inspection cycle.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.
    For the reasons discussed above, I certify that the 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. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. The FAA amends Sec.  39.13 by removing Amendment 39-10250 (62 FR 
65352, December 12, 1997) and adding the following new AD:

The Boeing Company: Docket No. FAA-2010-1158; Directorate Identifier 
2010-NM-125-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by January 
28, 2011.

Affected ADs

    (b) This AD supersedes AD 97-26-07, Amendment 39-10250.

Applicability

    (c) This AD applies to all The Boeing Company Model 747-100, -
100B, -100B SUD, -200B, -200C, -200F, -300, -400, -400D, -400F, 
747SR, and 747SP series airplanes, certificated in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 28: Fuel.

Unsafe Condition

    (e) This AD results from fleet information indicating that the 
repetitive inspection interval in the existing AD is too long 
because excessive chafing of the sleeving continues to occur much 
earlier than expected between scheduled inspections. The Federal 
Aviation Administration is issuing this AD to detect and correct 
abrasion of the Teflon sleeving and wires in the bundles of the fuel 
boost pumps for the numbers 1 and 4 main fuel tanks and of the 
auxiliary tank jettison pumps (if installed), which could result in 
electrical arcing between the wires and aluminum conduit and 
consequent fire or explosion of the fuel tank.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Requirements of AD 96-26-06, Amendment 39-9870

Inspections/Repair or Replace if Necessary

    (g) Perform an initial inspection to detect damage of the 
sleeving and wire bundles of the forward and aft boost pumps of the 
numbers 1 and 4 main fuel tanks, and of the wire bundles of the 
auxiliary tank jettison pumps (if installed), in accordance with 
Boeing Service Bulletin 747-28A2204, dated December 19, 1996, or 
Revision 1, dated October 30, 1997; or Boeing Alert Service Bulletin 
747-28A2204, Revision 3, dated March 11, 2010, at the time specified 
in paragraph (g)(1) or (g)(2) of this AD, as applicable. After the 
effective date of this AD,

[[Page 77795]]

only Revision 3 of Boeing Alert Service Bulletin 747-28A2204 may be 
used.
    (1) For airplanes having line numbers 001 through 432 inclusive: 
Inspect within 120 days after January 21, 1997 (the effective date 
of AD 96-26-06, amendment 39-9870, which was superseded by AD 97-26-
07).
    (2) For airplanes having line numbers 433 and subsequent: 
Inspect at the later of the times specified in paragraphs (g)(2)(i) 
or (g)(2)(ii) of this AD.
    (i) Prior to the accumulation of 20,000 flight cycles or 60,000 
flight hours, whichever occurs first; or
    (ii) Within 120 days after December 29, 1997 (the effective date 
of AD 97-26-07).
    (h) Repeat the inspection required by paragraph (g) of this AD 
at intervals not to exceed 20,000 flight cycles or 60,000 flight 
hours since the last inspection, whichever occurs first, until the 
first inspection required by paragraph (n) of this AD has been 
accomplished.
    (i) If any damaged sleeving is found, prior to further flight, 
replace the sleeving with new sleeving, in accordance with Boeing 
Service Bulletin 747-28A2204, dated December 19, 1996, or Revision 
1, dated October 30, 1997; or Boeing Alert Service Bulletin 747-
28A2204, Revision 3, dated March 11, 2010. After the effective date 
of this AD, only Revision 3 of Boeing Alert Service Bulletin 747-
28A2204 may be used.
    (j) If any damaged wire is found, prior to further flight, 
repair or replace the wire with a new wire, in accordance with 
Boeing Service Bulletin 747-28A2204, dated December 19, 1996, or 
Revision 1, dated October 30, 1997; or Boeing Alert Service Bulletin 
747-28A2204, Revision 3, dated March 11, 2010. After the effective 
date of this AD, only Revision 3 of Boeing Alert Service Bulletin 
747-28A2204 may be used.
    (k) If any burned wire is found, prior to further flight, 
perform an inspection to detect damage of the conduit, in accordance 
with Boeing Service Bulletin 747-28A2204, dated December 19, 1996, 
or Revision 1, dated October 30, 1997; or Boeing Alert Service 
Bulletin 747-28A2204, Revision 3, dated March 11, 2010. If any 
damage is found, prior to further flight, replace the conduit with a 
serviceable conduit, in accordance with Boeing Service Bulletin 747-
28A2204, dated December 19, 1996, or Revision 1, dated October 30, 
1997; or Boeing Alert Service Bulletin 747-28A2204, Revision 3, 
dated March 11, 2010. After the effective date of this AD, only 
Revision 3 of Boeing Alert Service Bulletin 747-28A2204 may be used.
    (l) For airplanes having line numbers 433 and subsequent: Within 
14 days after accomplishing the initial inspection required by 
paragraph (g) of this AD, submit a report of any damaged sleeving 
(i.e., holes, breaks, cuts, splits), damaged wire (i.e., worn or 
cracked insulation, exposed conductor, indication of arcing/
burning), or damaged conduit to the Manager, Seattle Aircraft 
Certification Office (ACO), FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, WA 98057-3356; fax (425) 227-1181. 
The report shall include the information specified in paragraphs 
(l)(1), (l)(2), (l)(3), (l)(4), and (l)(5) of this AD. Information 
collection requirements contained in this regulation have been 
approved by the Office of Management and Budget (OMB) under the 
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et 
seq.) and have been assigned OMB Control Number 2120-0056.
    (1) The airplane serial number.
    (2) The total hours' time-in-service accumulated on the 
airplane.
    (3) The total number of flight cycles accumulated on the 
airplane.
    (4) A description of any damage found.
    (5) The location of where the damaged part was installed.
    (m) For airplanes having line numbers 433 and subsequent: Within 
14 days after accomplishing the initial inspection required by 
paragraph (g) of this AD, submit any damaged part to the Manager, 
Seattle ACO. The damaged part shall be tagged to include the 
information specified in paragraphs (l)(1), (l)(2), (l)(3), (l)(4), 
and (l)(5) of this AD. Additionally, operators shall align the inner 
sleeving, outer sleeving, and wire as installed in the airplane, and 
secure the sleeving and wiring in place by taping or other means 
when submitting the damaged part to the Manager, Seattle ACO. 
Information collection requirements contained in this regulation 
have been approved by the OMB under the provisions of the Paperwork 
Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been 
assigned OMB Control Number 2120-0056.

New Reduced Inspection Intervals

Repetitive Inspections

    (n) Do the next inspection required by paragraph (h) of this AD 
at the time specified in paragraph (n)(1) or (n)(2) of this AD, as 
applicable, in accordance with Boeing Alert Service Bulletin 747-
28A2204, Revision 3, dated March 11, 2010. Repeat the inspection 
thereafter at intervals not to exceed 15,000 flight hours. 
Accomplishing the initial inspection in this paragraph ends the 
repetitive inspection requirements of paragraph (h) of this AD.
    (1) For airplanes on which the inspection required by paragraph 
(g) of this AD has been done as of the effective date of this AD: Do 
the inspection at the earlier of the times specified in paragraph 
(n)(1)(i) and (n)(1)(ii) of this AD.
    (i) Within 15,000 flight hours after the most recent inspection, 
or within 6,000 flight hours after the effective date of this AD, 
whichever occurs later.
    (ii) Within 20,000 flight cycles or 60,000 flight hours after 
the most recent inspection required by paragraph (g) or (h) of this 
AD, whichever occurs first.
    (2) For airplanes on which the inspection required by paragraph 
(g) of this AD has not been done as of the effective date of this 
AD: Do the inspection before the accumulation of 15,000 total flight 
hours, or within 6,000 flight hours after the effective date of this 
AD, whichever occurs later.

Paperwork Reduction Act Burden Statement

    (o) A federal agency may not conduct or sponsor, and a person is 
not required to respond to, nor shall a person be subject to a 
penalty for failure to comply with a collection of information 
subject to the requirements of the Paperwork Reduction Act unless 
that collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, Seattle ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. Send information to ATTN: Jon Regimbal, Aerospace 
Engineer, Propulsion Branch, ANM-140S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 917-6506; fax (425) 917-6590. 
Information may be e-mailed to: [email protected].
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (3) AMOCs approved previously in accordance with AD 97-26-07, 
Amendment 39-10250, are approved as alternative methods of 
compliance with the corresponding requirements of this AD. 
Compliance time extensions approved previously in accordance with AD 
97-26-07, are not approved as alternative methods of compliance for 
the compliance times required by paragraph (n) of this AD.

    Issued in Renton, Washington, on November 15, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-31375 Filed 12-13-10; 8:45 am]
BILLING CODE 4910-13-P