[Federal Register Volume 72, Number 98 (Tuesday, May 22, 2007)]
[Rules and Regulations]
[Pages 28594-28597]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-9799]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28254; Directorate Identifier 2007-NM-054-AD; 
Amendment 39-15065; AD 2007-11-08]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727 Airplanes

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

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) that applies to all Boeing Model 727 airplanes. The existing AD 
requires a boost pump dry bay inspection to detect leakage of fuel 
through an arced-through conduit, and corrective action as necessary. 
The existing AD also requires repetitive inspections of the in-tank 
fuel boost pump wiring to detect chafing of the wire insulation, 
evidence of electrical arcing, or arc-through of the conduit wall, and 
applicable corrective action; and installation of sleeving over the in-
tank fuel boost pump wires as a method to protect the wiring from 
chafing. This new AD removes certain inspection requirements from the

[[Page 28595]]

existing AD. This new AD adds new repetitive inspections for damage of 
the electrical wire and sleeve that run to the fuel boost pump through 
a conduit in the fuel tank, and arcing damage of the conduit and signs 
of fuel leakage into the conduit; applicable investigative and 
corrective actions; and a new repetitive engine fuel suction feed 
operational test. Initiation of the new inspections terminates the 
requirements of the existing AD. This AD results from reports of a fuel 
tank explosion on a Model 727-200F airplane on the ground; and of 
chafed wires and a damaged power cable sleeve of a fuel boost pump that 
were discovered during an inspection required by an existing AD on a 
Model 737-300 airplane. We are issuing this AD to detect and correct 
chafing of the fuel boost pump electrical wiring and leakage of fuel 
into the conduit, and to prevent electrical arcing between the wiring 
and the surrounding conduit, which could result in arc-through of the 
conduit, and consequent fire or explosion of the fuel tank.

DATES: This AD becomes effective June 6, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of June 6, 2007.
    On June 28, 1999 (64 FR 33394, June 23, 1999), the Director of the 
Federal Register approved the incorporation by reference of Boeing 
Alert Service Bulletin 727-28A0126, dated May 24, 1999.
    We must receive any comments on this AD by July 23, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
    <bullet> Fax: (202) 493-2251.
    <bullet> Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for service information identified in this AD.
    You may examine the contents of the AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-
401, Washington, DC. This docket number is FAA-2007-28254; the 
directorate identifier for this docket is 2007-NM-054-AD.

FOR FURTHER INFORMATION CONTACT: Suzanne Lucier, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 917-6438; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    On June 15, 1999, we issued AD 99-12-52, amendment 39-11199 (64 FR 
33394, June 23, 1999) (originally issued on May 24, 1999, as 
telegraphic AD T99-12-52). That AD applies to all Boeing Model 727 
series airplanes. That AD requires a boost pump dry bay inspection to 
detect leakage of fuel through an arced-through conduit, and corrective 
action, as necessary. That AD also requires repetitive detailed 
inspections of the in-tank fuel boost pump wiring to detect chafing of 
the wire insulation, evidence of electrical arcing, or arc-through of 
the conduit wall on Model 727 series airplanes, and applicable 
corrective action; and installation of sleeving over the in-tank fuel 
boost pump wires as a method to protect the wiring from chafing. That 
AD resulted from reports of severe wear of in-tank fuel boost pump 
wiring, and arc-through of the surrounding conduit on two Model 727 
series airplanes. The actions specified in that AD are intended to 
prevent fuel tank explosion resulting from arc-through of the fuel 
boost pump wiring conduits.

Actions Since AD Was Issued

    Since we issued that AD, we received a report that a fuel tank 
explosion occurred on a Model 727-200F airplane on the ground. 
Investigation revealed evidence of arcing in the metal conduit that 
carries power wires from the front spar through the fuel tank to the 
dry bay of the <greek-i>1 aft fuel boost pump. In a separate incident, 
we received a report from Boeing that chafed power wires and a damaged 
power cable sleeve of a fuel boost pump were discovered during an 
inspection required by AD 99-12-52 on a Model 737-300 series airplane. 
That inspection was done at 21,000 flight hours rather than the 
repetitive interval of 30,000 flight hours specified by that AD. The 
fuel boost pump installation on certain Model 737 airplanes is almost 
identical to the installation on Model 727 airplanes.

Other Relevant Rulemaking

    Operators should note that we are considering issuing a separate AD 
to address the identified unsafe condition as it relates to Model 737 
airplanes.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 727-28A0132, dated 
February 22, 2007. The alert service bulletin describes procedures for 
doing new repetitive detailed inspections for damage of the electrical 
wire and sleeve that run to the fuel boost pump through a conduit in 
the fuel tank, and for arcing damage of, and signs of fuel leakage 
into, the conduit; doing a new engine fuel suction feed operational 
test; doing related investigative and corrective actions, as 
applicable; and sending inspection results and damaged parts to the 
manufacturer. Related investigative and corrective actions include 
replacing the wire sleeve with a new, smaller wire sleeve; replacing, 
with BMS 13-60T09C03G018 wire, any wire that is damaged or has any part 
number other than BMS 13-60T09C03G018 or BMS 13-60T12C03G018; doing 
leak testing of the conduit if signs of fuel are discovered on the wire 
or sleeve during any inspection; and repairing any damaged conduit or 
replacing it with a new conduit.
    AD 99-12-52 refers to Boeing Alert Service Bulletin 727-28A0126, 
dated May 24, 1999, as the appropriate source of service information 
for accomplishment of the detailed inspection and related 
investigative/corrective actions; that requirement is new paragraph (i) 
in this AD. That service bulletin has since been revised. Revision 1, 
dated May 18, 2000, is essentially the same as the original and 
provides no new actions.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other airplanes of the same type design. For this reason, we 
are issuing this AD to supersede AD 99-12-52. This new AD retains 
certain requirements of the existing AD. This AD also requires 
accomplishing the actions specified in the alert service bulletin 
described previously, which, when initiated, terminates certain 
requirements.

Explanation of Changes Made to Existing AD

    We have revised the applicability of the existing AD to identify 
model designations as published in the most recent type certificate 
data sheet for the affected models.

[[Page 28596]]

    The FAA has changed all references to a ``detailed visual 
inspection'' in the existing AD to ``detailed inspection'' in this 
action.

Interim Action

    We consider this AD interim action. If final action is later 
identified, we might consider further rulemaking then.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD; therefore, providing notice and opportunity for public comment 
before the AD is issued is impracticable, and good cause exists to make 
this AD effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any relevant written 
data, views, or arguments regarding this AD. Send your comments to an 
address listed in the ADDRESSES section. Include ``Docket No. FAA-2007-
28254; Directorate Identifier 2007-NM-054-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD that might 
suggest a need to modify it. We will post all comments we receive, 
without change, to http://dms.dot.gov, including any personal 
information you provide. We will also post a report summarizing each 
substantive verbal contact with FAA personnel concerning this AD. Using 
the search function of that Web site, anyone can find and read the 
comments in any of our dockets, including the name of the individual 
who sent the comment (or signed the comment on behalf of an 
association, business, labor union, etc.). You may review the DOT's 
complete Privacy Act Statement in the Federal Register published on 
April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

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 AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that the 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 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.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends part 39 of the Federal Aviation Regulations (14 CFR part 
39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-11199 (64 FR 33394, June 23, 1999) and adding the 
following new airworthiness directive (AD):

2007-11-08 Boeing: Docket No. FAA-2007-28254; Directorate Identifier 
2007-NM-054-AD; Amendment 39-15065.

Effective Date

    (a) This AD becomes effective June 6, 2007.

Affected ADs

    (b) This AD supersedes AD 99-12-52.

Applicability

    (c) This AD applies to all Boeing Model 727, 727C, 727-100, 727 
-100C, 727-200, and 727-200F series airplanes, certificated in any 
category.

Unsafe Condition

    (d) This AD results from reports of a fuel tank explosion on a 
Model 727-200F airplane on the ground, and chafed wires and a 
damaged power cable sleeve of a fuel boost pump that were discovered 
during an inspection required by an existing AD on a Model 737-300 
airplane, which has a fuel boost pump installation that is almost 
identical to the installation on Model 727 airplanes. We are issuing 
this AD to detect and correct chafing of the fuel boost pump 
electrical wiring and leakage of fuel into the conduit, and to 
prevent electrical arcing between the wiring and the surrounding 
conduit, which could result in arc-through of the conduit, and 
consequent fire or explosion of the fuel tank.

Compliance

    (e) 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 Certain Requirements of AD 99-12-52

    (f) For airplanes with 50,000 or more total flight hours as of 
June 28, 1999 (the effective date of AD 99-12-52): Within 20 days 
after June 28, 1999, accomplish the requirements of paragraph (i) of 
this AD.
    (g) For airplanes with less than 50,000 total flight hours, but 
more than 30,000 total flight hours, as of June 28, 1999: Within 30 
days after June 28, 1999, accomplish the requirements of paragraph 
(i) of this AD.
    (h) For airplanes with 30,000 total flight hours or less, as of 
June 28, 1999: Within 90 days after June 28, 1999, accomplish the 
requirements of paragraph (i) of this AD.

Detailed Inspection, Corrective Action, and Installation

    (i) Perform a detailed inspection of the in-tank fuel boost pump 
wire bundles, and

[[Page 28597]]

applicable corrective actions; and, except as provided in paragraph 
(j) of this AD, install sleeving over the wire bundles; in 
accordance with Boeing Alert Service Bulletin 727-28A0126, dated May 
24, 1999; Boeing Service Bulletin 727-28A0126, Revision 1, dated May 
18, 2000; or Boeing Alert Service Bulletin 727-28A0132, dated 
February 22, 2007.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Installation: Possible Deferral

    (j) Installation of sleeving over the wire bundles, as required 
by paragraph (i) of this AD, may be deferred if, within 18 months or 
6,000 flight hours, whichever occurs first, after accomplishment of 
the inspection and applicable corrective actions required by 
paragraph (i), the following actions are accomplished: Perform a 
detailed inspection of the in-tank fuel boost pump wire bundles, and 
applicable corrective actions; and install sleeving over the wire 
bundles; in accordance with Boeing Alert Service Bulletin 727-
28A0126, dated May 24, 1999, or Boeing Service Bulletin 727-28A0126, 
Revision 1, dated May 18, 2000; or Boeing Alert Service Bulletin 
727-28A0132, dated February 22, 2007.

Repetitive Inspections and Corrective Actions

    (k) Repeat the detailed inspection and applicable corrective 
actions required by paragraphs (i) and (j) of this AD at intervals 
not to exceed 30,000 flight hours, until the initial inspection, 
applicable corrective actions, and engine fuel suction feed 
operational test required by paragraph (l) of this AD have been 
done.

New Requirements of This AD

Inspection, Test, and Related Investigative and Corrective Actions

    (l) For all airplanes: Within 120 days after the effective date 
of this AD or 5,000 flight hours after the last inspection or 
corrective action done before the effective date of this AD as 
required by paragraph (i), (j), or (k), as applicable, of this AD, 
whichever occurs later, do a detailed inspection for damage of the 
sleeve and electrical wire of the fuel boost pump, and do an engine 
fuel suction feed operational test; and, before further flight, do 
related investigative and corrective actions, as applicable; by 
doing all applicable actions in and in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 727-
28A0132, dated February 22, 2007. Repeat the detailed inspection and 
engine fuel suction feed operational test thereafter at intervals 
not to exceed 15,000 flight cycles. Accomplishment of the initial 
inspection, applicable corrective actions, and engine fuel suction 
feed operational test of this paragraph terminates the requirements 
of paragraphs (i), (j), and (k) of this AD.

Inspection Report and Disposition of Damaged Parts

    (m) At the applicable time(s) specified in paragraph (m)(1) or 
(m)(2) of this AD: Submit a report of the findings (both positive 
and negative) of any inspection required by this AD and send any 
damaged parts to the manufacturer, as described in Boeing Alert 
Service Bulletin 727-28A0132, dated February 22, 2007. The report 
must include the information specified in Appendix A of the alert 
service bulletin. Under the provisions of the Paperwork Reduction 
Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget 
(OMB) has approved the information collection requirements contained 
in this AD and has assigned OMB Control Number 2120-0056.
    (1) For any inspection done after the effective date of this AD: 
Submit the report within 30 days after the inspection.
    (2) For any inspection done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

Alternative Methods of Compliance (AMOCs)

    (n)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (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 appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (3) AMOCs approved previously in accordance with AD 99-12-52 are 
approved as AMOCs for the corresponding provisions of this AD.

Material Incorporated by Reference

    (o) You must use applicable Boeing service bulletins specified 
in Table 1 of this AD to perform the actions that are required by 
this AD, unless the AD specifies otherwise.

                                Table 1.--All Material Incorporated by Reference
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        Boeing service information                Revision level                           Date
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Alert Service Bulletin 727-28A0126.......  Original....................  May 24, 1999.
Alert Service Bulletin 727-28A0132.......  Original....................  February 22, 2007.
Service Bulletin 727-28A0126.............  1...........................  May 18, 2000.
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    (1) The Director of the Federal Register approved the 
incorporation by reference of Boeing Alert Service Bulletin 727-
28A0132, dated February 22, 2007; and Boeing Service Bulletin 727-
28A0126, Revision 1, dated May 18, 2000; in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51.
    (2) On June 28, 1999 (64 FR 33394, June 23, 1999), the Director 
of the Federal Register approved the incorporation by reference of 
Boeing Alert Service Bulletin 727-28A0126, dated May 24, 1999.
    (3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for a copy of this service information. You 
may review copies at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington; or at the National Archives 
and Records Administration (NARA). For information on the 
availability of this material at NARA, call 202-741-6030, or go to: 
http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on May 1, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-9799 Filed 5-21-07; 8:45 am]
BILLING CODE 4910-13-P