[Federal Register Volume 66, Number 164 (Thursday, August 23, 2001)]
[Proposed Rules]
[Pages 44323-44326]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-21229]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-07-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Boeing Model 757 series 
airplanes. This proposal would require a one-time inspection of a wire 
bundle in the front left wing spar for chafing and for proper 
installation of a Teflon sleeve; corrective action, if necessary; and 
installation of extra protection against chafing. This action is 
necessary to prevent chafing between the wire bundle and the front left 
wing spar, which could result in electrical arcing and subsequent 
ignition of flammable vapors and possible uncontrollable fire. This 
action is intended to address the identified unsafe condition.

DATES: Comments must be received by October 9, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-07-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 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. 2001-NM-07-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: John Vann, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone 
(425) 227-1024; 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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-07-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. 2001-NM-07-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received several reports of chafed fuel shutoff valve 
wires and densitometer wires in the wire bundle, part number (P/N) 
W5100, at front spar station 318.99 on Boeing Model 757 series 
airplanes. The reports indicated that the wires were found to be 
chafing against the left wing spar on the lower chord. One operator 
advised that false illumination of the ``L HYD PRESS'' light had 
occurred in flight. Subsequent repair of the wires in the wire bundle, 
P/N W5100, eliminated the false indication light condition.
    Based on these reports, the airplane manufacturer inspected 
installation in the left wing spar of the wire bundle, 
P/N W5100, of airplanes in production. This inspection revealed that a 
potential chafing condition exists between the lower chord and the wire 
bundle, P/N W5100, adjacent to front spar station 318.99. Subsequently, 
one operator found chafing of the noted wire bundle as a result of 
missing sleeving on the airplane. Additional inspections of production 
airplanes found a number of airplanes with inadequate sleeving 
installed.
    The wing leading edge, where front spar station 318.99 is located, 
is classified as a flammable leakage zone, and, as such, does not have 
fire detection and extinguishing capability, but flammable vapors are 
likely to be present. Chafing of the wire bundle, 
P/N W5100, against the wing spar, if not corrected, could result in 
electrical arcing and subsequent ignition of flammable vapors, possibly 
leading to uncontrollable fire.

Explanation of Relevant Service Information

    Boeing has issued Service Bulletins 757-29-0058 (for Model 757-200 
series airplanes), and 757-29-0059 (for Model 757-300 series 
airplanes), both dated November 9, 2000. The service bulletins describe 
procedures for inspection of the wire bundle, P/N W5100, for chafing, 
and wire repair, if necessary; installation of a grommet; and 
inspection of the wire's teflon sleeving for proper installation and 
corrective action (including, but not limited to, repairing or adding 
sleeving if it does not exist, and ensuring that it is installed 1 inch 
past the upper clamp and 3 inches below the lower front spar chord), if 
necessary. Accomplishment of the actions specified in the applicable 
service bulletin is intended to adequately address the identified 
unsafe condition.

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 require accomplishment of the actions specified in 
the applicable service bulletin described previously. The proposed AD 
also would require that operators report results of inspection findings 
to the FAA.

Cost Impact

    There are approximately 1,058 airplanes of the affected design in 
the worldwide fleet. The FAA estimates that 615 airplanes of U.S. 
registry would be affected by this proposed AD, that it would take 
approximately 1 work hour per airplane to accomplish the proposed 
actions, and that the average labor rate is $60 per work hour. The cost 
of

[[Page 44325]]

required parts would be negligible. Based on these figures, the cost 
impact of the proposed AD on U.S. operators is estimated to be $36,900, 
or $60 per airplane.
    The cost impact figure discussed above is 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. 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 adding the following new 
airworthiness directive:

Boeing: Docket 2001-NM-07-AD.

    Applicability: Model 757 series airplanes, certificated in any 
category, as listed in Boeing Service Bulletins 757-29-0058 and 757-
29-0059, both dated November 9, 2000.

    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 (c) 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 prevent chafing between the wire bundle and the front left 
wing spar, which could result in electrical arcing and subsequent 
ignition of flammable vapors and possible uncontrollable fire, 
accomplish the following:

Compliance Time

    (a) Within 6 months from the effective date of this AD, perform 
the actions specified in paragraphs (a)(1), (a)(2), and (a)(3) of 
this AD, in accordance with Boeing Service Bulletin 757-29-0058, 
dated November 9, 2000 (for Model 757-200 series airplanes); or 
Boeing Service Bulletin 757-29-0059, also dated November 9, 2000 
(for Model 757-300 series airplanes); as applicable.

Inspection and Corrective Action

    (1) Perform a detailed visual inspection of the wire bundle, 
part number (P/N) W5100, adjacent to front spar station 318.99 in 
the left wing leading edge, to detect chafing. If any damage is 
found, before further flight, repair the wire bundle.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

Modification

    (2) Install a caterpillar grommet to the edge of the spar lower 
chord in the left wing leading edge.

Inspection and Corrective Action

    (3) Perform a general visual inspection for proper installation 
of perforated Teflon sleeving on the wire bundle, P/N W5100. If 
sleeving does not exist or is not covering the area from 1.0 inch 
beyond the clamp point to 3.0 inches below the spar flange edge, 
before further flight, install or repair the teflon sleeving.

    Note 3: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''


    Note 4: An optional 0.5-inch spacer may be used in accordance 
with the applicable service bulletin above, Section 3, 
Accomplishment Instructions, Work Instructions, to prevent the wire 
bundle from contacting the lower chord of the front spar on the left 
wing.

Reporting

    (b) If the Teflon sleeving is found missing or improperly 
installed during the inspection required in paragraph (a)(3) of this 
AD, submit a report of inspection findings to the Manager, Seattle 
Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056; fax (425) 227-1181; at the applicable 
time specified in paragraph (b)(1) or (b)(2) of this AD. The report 
must include the inspection results, a description of any 
discrepancies found, the airplane serial number, and the number of 
landings and flight hours on the airplane. 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) For airplanes on which the inspection is accomplished after 
the effective date of this AD: Submit the report within 30 days 
after performing the inspection required by paragraph (a)(3) of this 
AD.
    (2) For airplanes on which the inspection specified in paragraph 
(a)(3) has been accomplished prior to the effective date of this AD: 
Submit the report within 30 days after the effective date of this 
AD.

Alternative Methods of Compliance

    (c) 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.

    Note 5: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.


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Special Flight Permits

    (d) Special flight permits may be issued in accordance with 
Secs. 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 August 16, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-21229 Filed 8-22-01; 8:45 am]
BILLING CODE 4910-13-P