AD 2002-02-04

[Federal Register Volume 67, Number 29 (Tuesday, February 12, 2002)]
[Rules and Regulations]
[Pages 6379-6381]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-2925]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-07-AD; Amendment 39-12632; AD 2002-02-04]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Boeing Model 757 series airplanes, that requires 
a one-time inspection of a wire bundle in the left wing front 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 left wing front 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: Effective March 19, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 19, 2002.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Boeing Model 757 series 
airplanes was published in the Federal Register on August 23, 2001 (66 
FR 44323). That action proposed to require a one-time inspection of a 
wire bundle in the left wing front spar for chafing and for proper 
installation of a Teflon sleeve; corrective action, if necessary; and 
installation of extra protection against chafing.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.

Give Credit for Accomplishment of Related Service Letters

    One commenter requests that the FAA revise the proposed AD to give 
credit to operators who have accomplished the actions specified in the 
proposed AD in accordance with service information other than that 
identified in the proposed AD. The commenter notes that Boeing Service 
Letters 757-SL-29-024-B, dated November 3, 1995, and 757-SL-29-024-C, 
dated June 13, 2000, also address the unsafe condition identified in 
the proposed AD. The commenter further states that it has inspected its 
affected airplanes in accordance with Boeing Service Letter 757-SL-29-
024-C.
    The FAA concurs with the commenter's request. We find that the 
procedures in the service letters referenced by the commenter are 
nearly identical to those in Boeing Service Bulletins 757-29-0058 and 
757-29-0059, both dated November 9, 2000, which the proposed AD 
identifies as appropriate sources of service information. Therefore, we 
have added a new Note 2, and renumbered subsequent notes from the 
proposed AD accordingly, to give credit for actions accomplished before 
the effective date of this AD in accordance with Boeing Service Letter 
757-SL-29-024-B or 757-SL-29-024-C.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change previously 
described. The FAA has determined that this change will neither

[[Page 6380]]

increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 1,058 Model 757 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 615 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 1 work hour per airplane to accomplish the required 
actions, and that the average labor rate is $60 per work hour. The cost 
of required parts is negligible. Based on these figures, the cost 
impact of this 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 requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this 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 adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 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:

2002-02-04  Boeing: Amendment 39-12632. 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 left wing 
front 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.

    Note 2: Inspections, repairs, and installations accomplished 
before the effective date of this AD in accordance with Boeing 
Service Letter 757-SL-29-024-B, dated November 3, 1995, or 757-SL-
29-024-C, dated June 13, 2000, are acceptable for compliance with 
the applicable action specified in this AD.

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 3: 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 4: 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 5: 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 AD 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

[[Page 6381]]

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

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.

Incorporation by Reference

    (e) The actions shall be done in accordance with Boeing Service 
Bulletin 757-29-0058, dated November 9, 2000; or Boeing Service 
Bulletin 757-29-0059, dated November 9, 2000; as applicable. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Boeing Commercial Airplane Group, 
P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (f) This amendment becomes effective on March 19, 2002.

    Issued in Renton, Washington, on January 30, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-2925 Filed 2-11-02; 8:45 am]
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