Skip to Content

Rule

Airworthiness Directives; Boeing Model 707 Airplanes and Model 720 and 720B Series Airplanes

Document Details

Information about this document as published in the Federal Register.

Published Document

This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

Start Preamble

AGENCY:

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

ACTION:

Final rule.

Start Printed Page 63801

SUMMARY:

The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 707 airplanes and Model 720 and 720B series airplanes. This AD requires accomplishing an airplane survey to define the configuration of certain system installations, and repair of any discrepancy found. This AD also requires modifying the fuel system by installing lightning protection for the fuel quantity indication system (FQIS), ground fault relays for the fuel boost pumps, and additional power relays for the center tank fuel pumps and uncommanded on-indication lights at the flight engineer's panel. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent certain failures of the fuel pumps or FQIS, which could result in a potential ignition source inside the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.

DATES:

This AD becomes effective December 18, 2007.

ADDRESSES:

For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.

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 (telephone 800-647-5527) is the 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.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Kathrine Rask, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6505; fax (425) 917-6590.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

Discussion

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to all Boeing Model 707 airplanes and Model 720 and 720B series airplanes. That NPRM was published in the Federal Register on August 1, 2007 (72 FR 41958). That NPRM proposed to require accomplishing an airplane survey to define the configuration of certain system installations, and repair of any discrepancy found. That NPRM proposed to also require modifying the fuel system by installing lightning protection for the fuel quantity indication system, ground fault relays for the fuel boost pumps, and additional power relays for the center tank fuel pumps and uncommanded on-indication lights at the flight engineer's panel.

Comments

We provided the public the opportunity to participate in the development of this AD. We have considered the single comment received. The commenter, Boeing, supports the NPRM.

Conclusion

We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

There are about 185 airplanes of the affected design in the worldwide fleet. This AD affects about 52 airplanes of U.S. registry.

The required survey takes about 20 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the survey for U.S. operators is $83,200, or $1,600 per airplane.

Because the manufacturer has not yet developed a modification commensurate with the actions specified by this AD, we cannot provide specific information regarding the required number of work hours or the cost of parts to do the required modification. In addition, modification costs will likely vary depending on the operator and the airplane configuration. The compliance time of 72 months should provide ample time for the development, approval, and installation of an appropriate modification.

Based on similar modifications accomplished previously on other airplane models, however, we can reasonably estimate that the modification may require as many as 420 work hours per airplane, at an average labor rate of $80 per work hour. Required parts may cost up to $185,000 per airplane. Based on these figures, the estimated cost of the modification for U.S. operators may cost up to $11,367,200, or $218,600 per airplane.

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); 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.

Start List of Subjects

List of Subjects in 14 CFR Part 39

End List of Subjects

Adoption of the Amendment

Start Amendment Part

Accordingly, under the authority delegated to me by the Administrator, the FAA amends

End Amendment Part Start Part

PART 39—AIRWORTHINESS DIRECTIVES

End Part Start Amendment Part

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

End Amendment Part Start Authority

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

End Authority
Start Printed Page 63802
[Amended]
Start Amendment Part

2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD):

End Amendment Part

2007-23-12 Boeing: Amendment 39-15258. Docket No. FAA-2007-28828; Directorate Identifier 2007-NM-010-AD.

Effective Date

(a) This AD becomes effective December 18, 2007.

Affected ADs

(b) None.

Applicability

(c) This AD applies to all Boeing Model 707-100 long body, -200, -100B long body, and -100B short body series airplanes; and Model 707-300, -300B, -300C, and -400 series airplanes; and Model 720 and 720B series airplanes; certificated in any category.

Unsafe Condition

(d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent certain failures of the fuel pumps or fuel quantity indication system (FQIS), which could result in a potential ignition source inside the fuel tank, which, in combination with flammable fuel vapors, could result in fuel tank explosion and consequent loss of the airplane.

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.

Airplane Survey

(f) Within 12 months after the effective date of this AD: Conduct an airplane survey that defines the configuration of system installations for the wing leading edges, wing-to-body area, electrical equipment bay, flight deck, and FQIS using a method approved in accordance with the procedures specified in paragraph (h)(1) of this AD. If any discrepancy is detected, repair before further flight using a method approved in accordance with the procedures specified in paragraph (h)(1) of this AD. Submit the survey results to the Manager, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356, at the applicable time specified in paragraph (f)(1) or (f)(2) of this AD. The report must include the survey results (e.g., photographs and sketches, part numbers of FQIS components and fuel pumps, and the actual configuration of FQIS and the fuel pump control systems), a description of any discrepancy found, the airplane serial number, and the number of landings and flight hours on the airplane. 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) If the survey was done after the effective date of this AD: Submit the report within 30 days after the survey.

(2) If the survey was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.

Note 1:

For the purposes of this AD, “discrepancy” is defined as any wear or deterioration (e.g., damage, fluid leaks, corrosion, cracking, or system failures) that might prevent the airplane from being in an airworthy condition.

Modification of Fuel System

(g) Within 72 months after the effective date of this AD: Modify the fuel system as specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, using a method approved in accordance with the procedures specified in paragraph (h)(1) of this AD.

(1) Replace the FQIS wire bundle along the leading edge of the left and right wings with a new wire bundle that has a lightning shield that is separated from other wiring.

(2) Replace each fuel pump relay with a ground fault interrupter relay.

(3) Install redundant power relays for the center tank fuel pumps and uncommanded on-indication lights at the flight engineer's panel.

Alternative Methods of Compliance (AMOCs)

(h)(1) The Manager, Seattle ACO 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.

Material Incorporated by Reference

(i) None.

Start Printed Page 63803

Start Printed Page 63804

Start Signature
Start Printed Page 63805

Issued in Renton, Washington, on October 12, 2007.

Stephen P. Boyd,

Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

BILLING CODE 4910-13-P

[FR Doc. 07-5635 Filed 11-9-07; 8:45 am]

BILLING CODE 4910-13-C