
[Federal Register Volume 78, Number 233 (Wednesday, December 4, 2013)]
[Rules and Regulations]
[Pages 72791-72794]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-28994]



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  Federal Register / Vol. 78, No. 233 / Wednesday, December 4, 2013 / 
Rules and Regulations  

[[Page 72791]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1069; Directorate Identifier 2012-NM-044-AD; 
Amendment 39-17692; AD 2013-24-15]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 2007-11-08 for 
all The Boeing Company Model 727 airplanes. AD 2007-11-08 required 
repetitive inspections of the in-tank fuel boost pump wiring, 
installation of sleeving over the in-tank fuel boost pump wires, 
repetitive inspections of a certain electrical wire, sleeve, and 
conduit, and applicable investigative and corrective actions; and 
repetitive engine fuel suction feed operational tests. This new AD also 
requires replacement of the wire bundles for the wing and center fuel 
boost pumps, installation of convoluted liners, and related 
investigative and corrective actions if necessary. This new AD also 
requires replacement of the fuel quantity indicating system (FQIS) 
wires, a low-frequency eddy current inspection for cracking, and repair 
if necessary. This new AD also requires revising the maintenance 
program to incorporate changes to the airworthiness limitations 
section. This AD was prompted by a report of damage found to the 
sleeve, jacket, and insulation on an electrical wire during a 
repetitive inspection. We are issuing this AD to prevent 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 is effective January 8, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 8, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of June 6, 
2007 (72 FR 28594, May 22, 2007).

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. 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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Rebel Nichols, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6509; fax: 425-917-6590; email: rebel.nichols@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR Part 39 to supersede AD 2007-11-08, Amendment 39-15065 (72 
FR 28594, May 22, 2007). AD 2007-11-08 applied to the specified 
products. The SNPRM published in the Federal Register on August 13, 
2013 (78 FR 49217). We preceded the SNPRM with a notice of proposed 
rulemaking (NPRM) that published in the Federal Register on October 11, 
2012 (77 FR 61731). The NPRM (77 FR 61731, October 11, 2012) proposed 
to continue to require repetitive inspections of the in-tank fuel boost 
pump wiring, installation of sleeving over the in-tank fuel boost pump 
wires, repetitive inspections of a certain electrical wire, sleeve, and 
conduit, and applicable investigative and corrective actions; and 
repetitive engine fuel suction feed operational tests. The NPRM also 
proposed to require replacement of the wire bundles for the wing and 
center fuel boost pumps, installation of convoluted liners, and related 
investigative and corrective actions if necessary. The NPRM also 
proposed to require replacement of the FQIS wires; a low-frequency eddy 
current inspection for cracking; and repair if necessary. The NPRM also 
proposed to require revising the maintenance program to incorporate 
changes to the airworthiness limitations section. The SNPRM proposed to 
revise certain compliance times, specify a terminating action, and add 
a requirement to incorporate another change to the airworthiness 
limitations section.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comment received. The Boeing Company 
stated that it supports the SNPRM (78 FR 49217, August 13, 2013).

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM (78 FR 49217, August 13, 2013) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM (78 FR 49217, August 13, 2013).

[[Page 72792]]

Costs of Compliance

    We estimate that this AD affects 569 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                    Cost per     Number of U.S.    Cost on U.S.
           Action                Labor cost       Parts cost        product         airplanes       operators
----------------------------------------------------------------------------------------------------------------
Inspection, test, and         10 work-hours x  $0.............  $850...........             260  $221,000.
 corrective actions            $85 per hour =
 [retained actions from AD     $850.
 2007-11-08, Amendment 39-
 15065 (72 FR 28594, May 22,
 2007)].
Replacement (new action)....  185 work-hours   $28,771........  $44,496........             569  $25,318,224.
                               x $85 per hour
                               = $15,725.
Revise maintenance program    1 work-hour x    $0.............  $85............             569  $48,365.
 (new action).                 $85 per hour =
                               $85.
Concurrent FQIS wire          Up to 248 work-  Up to $34,865..  Up to $55,945..             569  Up to
 replacement (new action).     hours x $85                                                        $31,832,705.
                               per hour =
                               $21,080.
Concurrent low frequency      2 work-hours x   $0.............  $170...........             569  $96,730.
 eddy current (LFEC)           $85 per hour =
 inspection (new action).      $170.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in this AD.

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 this AD:
    (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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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 FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2007-11-08, Amendment 39-15065 (72 FR 28594, May 22, 2007), and adding 
the following new AD:

2013-24-15 The Boeing Company: Amendment 39-17692; Docket No. FAA-
2012-1069; Directorate Identifier 2012-NM-044-AD.

(a) Effective Date

    This AD is effective January 8, 2014.

(b) Affected ADs

    This AD supersedes AD 2007-11-08, Amendment 39-15065 (72 FR 
28594, May 22, 2007).

(c) Applicability

    (1) This AD applies to all The Boeing Company Model 727, 727C, 
727-100, 727-100C, 727-200, and 727-200F series airplanes, 
certificated in any category.
    (2) This AD requires revisions to certain operator maintenance 
documents to include new actions (e.g., inspections) and/or Critical 
Design Configuration Control Limitations (CDCCLs). Compliance with 
these actions and/or CDCCLs is required by 14 CFR 91.403(c). For 
airplanes that have been previously modified, altered, or repaired 
in the areas addressed by this AD, the operator may not be able to 
accomplish the actions described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according 
to paragraph (p) of this AD. The request should include a 
description of changes to the required actions that will ensure the 
continued operational safety of the airplane.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report of damage found to the sleeve, 
jacket, and insulation on an electrical wire during a repetitive 
inspection. We are issuing this AD to prevent 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.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

[[Page 72793]]

(g) Retained Compliance Times

    This paragraph restates the requirements of paragraphs (f), (g), 
and (h) of AD 2007-11-08, Amendment 39-15065 (72 FR 28594, May 22, 
2007).
    (1) For airplanes with 50,000 or more total flight hours as of 
June 28, 1999 (the effective date of AD 99-12-52, Amendment 39-11199 
(64 FR 33394, June 23, 1999)): Within 20 days after June 28, 1999, 
accomplish the requirements of paragraph (h) of this AD.
    (2) For airplanes with less than 50,000 total flight hours, but 
more than 30,000 total flight hours, as of June 28, 1999 (the 
effective date of AD 99-12-52, Amendment 39-11199 (64 FR 33394, June 
23, 1999)): Within 30 days after June 28, 1999, accomplish the 
requirements of paragraph (h) of this AD.
    (3) For airplanes with 30,000 total flight hours or less as of 
June 28, 1999 (the effective date of AD 99-12-52, Amendment 39-11199 
(64 FR 33394, June 23, 1999)): Within 90 days after June 28, 1999, 
accomplish the requirements of paragraph (h) of this AD.

(h) Retained Detailed Inspection, Corrective Action, and Installation

    This paragraph restates the requirements of paragraph (i) of AD 
2007-11-08, Amendment 39-15065 (72 FR 28594, May 22, 2007).
    (1) Perform a detailed inspection of the in-tank fuel boost pump 
wire bundles, and applicable corrective actions; and, except as 
provided by paragraph (i) 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.
    (2) 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.

(i) Retained Installation: Possible Deferral

    This paragraph restates the optional actions of paragraph (j) of 
AD 2007-11-08, Amendment 39-15065 (72 FR 28594, May 22, 2007). 
Installation of sleeving over the wire bundles, as required by 
paragraph (h) 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 (h) of this AD, 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; Boeing Service Bulletin 
727-28A0126, Revision 1, dated May 18, 2000; or Boeing Alert Service 
Bulletin 727-28A0132, dated February 22, 2007.

(j) Retained Repetitive Inspections and Corrective Actions

    This paragraph restates the requirements of paragraph (k) of AD 
2007-11-08, Amendment 39-15065 (72 FR 28594, May 22, 2007). Repeat 
the detailed inspection and applicable corrective actions required 
by paragraphs (h) and (i) of this AD, as applicable, 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 (k) of this AD have been 
done.

(k) Retained Inspection, Test, and Related Investigative and Corrective 
Actions

    This paragraph restates the requirements of paragraph (l) of AD 
2007-11-08, Amendment 39-15065 (72 FR 28594, May 22, 2007). For all 
airplanes: Within 120 days after June 6, 2007 (the effective date of 
AD 2007-11-08), or 5,000 flight hours after the last inspection or 
corrective action done before June 6, 2007, as required by paragraph 
(h), (i), or (j), 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 (h), (i), and (j) of this AD.

(l) New Installation

    Within 60 months after the effective date of this AD: Install 
new shielded wire bundles in convoluted liners in the wing and 
center fuel tank conduits and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 727-
28A0133, dated October 5, 2011. Related investigative and corrective 
actions must be done before further flight. Doing the actions 
specified in paragraphs (l) and (m) of this AD terminates the 
requirements of paragraphs (g), (h), (i), (j), and (k) of this AD.

(m) New Concurrent Requirement

    Before or concurrently with accomplishing the requirements of 
paragraph (l) of this AD, replace the fuel quantity indicating 
system (FQIS) wire bundles and do a low frequency eddy current 
inspection for cracking, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 727-28-0131, dated August 
18, 2010. If any cracking is found during the inspection, before 
further flight, repair using a method approved in accordance with 
the procedures specified in paragraph (p) of this AD.

(n) New Maintenance Program Revision

    (1) Within 60 days after the effective date of this AD: Revise 
the maintenance program to incorporate Airworthiness Limitation 
Instruction (ALI) Task 28-AWL-18, ``Fuel Quantity Indicating System 
(FQIS)--Out-Tank Wiring Lightning Shield to Ground Termination''; 
and CDCCL Task 28-AWL-19, ``Fuel Quantity Indicating System (FQIS)--
Out-Tank Wiring Lightning Shield to Ground Termination,'' of Section 
D., ``Airworthiness Limitations--Fuel Systems,'' of Boeing 727-100/
200 Airworthiness Limitations (AWLs), D6-8766-AWL, Revision August 
2010. The initial compliance time for the inspections is within 120 
months after accomplishing the actions required by paragraph (m) of 
this AD.
    (2) Within 60 days after the effective date of this AD: Revise 
the maintenance program to incorporate Airworthiness Limitation 
Instruction (ALI) Task 28-AWL-20, ``Fuel Boost Pump Wires in Conduit 
Installation--In Fuel Tank''; and CDCCL Task 28-AWL-21, ``Fuel Boost 
Pump Wires in Conduit Installation--In Fuel Tank,'' of Section D., 
``Airworthiness Limitations--Fuel Systems,'' of Boeing 727-100/200 
Airworthiness Limitations (AWLs), D6-8766-AWL, Revision August 2010. 
The initial compliance time for the inspections is within 72 months 
after accomplishing the actions required by paragraph (l) of this 
AD.

(o) No Alternative Actions, Intervals, and/or CDCCLs

    After accomplishing the revisions required by paragraphs (n)(1) 
and (n)(2) of this AD, no alternative actions (e.g., inspections), 
intervals, and/or CDCCLs may be used unless the actions, intervals, 
and/or CDCCLs are approved as an alternative method of compliance 
(AMOC) in accordance with the procedures specified in paragraph (p) 
of this AD.

(p) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (q) of this AD. 
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) AMOCs approved previously for AD 2007-11-08, Amendment 39-
15065 (72 FR 28594, May 22, 2007), are approved as AMOCs for the 
corresponding provisions of this AD.

[[Page 72794]]

(q) Related Information

    For more information about this AD, contact Rebel Nichols, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle 
Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 
98057-3356; phone: 425-917-6509; fax: 425-917-6590; email: 
rebel.nichols@faa.gov.

(r) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
January 8, 2014.
    (i) Boeing Alert Service Bulletin 727-28A0133, dated October 5, 
2011.
    (ii) Boeing Service Bulletin 727-28-0131, dated August 18, 2010.
    (iii) Boeing 727-100/200 Airworthiness Limitations (AWLs), D6-
8766-AWL, Revision August 2010:
    (A) Airworthiness Limitation Instruction (ALI) Task 28-AWL-18, 
``Fuel Quantity Indicating System (FQIS)--Out-Tank Wiring Lightning 
Shield to Ground Termination,'' of Section D., ``Airworthiness 
Limitations--Fuel Systems.''
    (B) Critical Design Configuration Control Limitations (CDCCL) 
Task 28-AWL-19, ``Fuel Quantity Indicating System (FQIS)--Out-Tank 
Wiring Lightning Shield to Ground Termination,'' of Section D., 
``Airworthiness Limitations--Fuel Systems.''
    (C) ALI Task 28-AWL-20, ``Fuel Boost Pump Wires in Conduit 
Installation--In Fuel Tank,'' of Section D., ``Airworthiness 
Limitations--Fuel Systems.''
    (D) CDCCL Task 28-AWL-21, ``Fuel Boost Pump Wires in Conduit 
Installation--In Fuel Tank,'' of Section D., ``Airworthiness 
Limitations--Fuel Systems.''
    (4) The following service information was approved for IBR on 
June 6, 2007 (72 FR 28594, May 22, 2007).
    (i) Boeing Alert Service Bulletin 727-28A0126, dated May 24, 
1999.
    (ii) Boeing Alert Service Bulletin 727-28A0132, dated February 
22, 2007.
    (iii) Boeing Service Bulletin 727-28A0126, Revision 1, dated May 
18, 2000.
    (5) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
    (6) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (7) You may view this service information that is incorporated 
by reference 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 November 15, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-28994 Filed 12-3-13; 8:45 am]
BILLING CODE 4910-13-P


