[Federal Register Volume 69, Number 151 (Friday, August 6, 2004)]
[Proposed Rules]
[Pages 47804-47806]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 04-17986]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18786; Directorate Identifier 2004-NM-26-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767-200, -300, and -300F
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing Model 767-200, -300, and -300F series airplanes.
This proposed AD would require repetitive high frequency eddy current
inspections and detailed inspections of the left and right butt line
(BL) 25 vertical chords for cracks, and corrective actions if
necessary. This proposed AD is prompted by findings of cracks in the
fillet radii of the left and right BL 25 vertical chords common to the
nose wheel well bulkhead at station 287. We are proposing this AD to
detect and correct cracks in the left and right BL 25 vertical chords,
which could grow downward into a critical area that serves as a primary
load path for the nose landing gear (NLG) and result in the collapse of
the NLG during landing.
DATES: We must receive comments on this proposed AD by September 20,
2004.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
By fax: (202) 493-2251.
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.
You can get the service information identified in this proposed AD
from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington
98124-2207.
You may examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., room PL-401, on
the plaza level of the Nassif Building, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Suzanne Masterson, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6441; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Docket Management System (DMS)
The FAA has implemented new procedures for maintaining AD dockets
electronically. As of May 17, 2004, new AD actions are posted on DMS
and assigned a docket number. We track each action and assign a
corresponding directorate identifier. The DMS AD docket number is in
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier
(``Old Docket Number'') as a cross-reference for searching purposes.
Comments Invited
We invite you to submit any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2004-18786;
Directorate Identifier 2004-NM-26-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments submitted by the closing date and may amend the
proposed AD in light of those comments.
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 proposed 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 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.
We are reviewing the writing style we currently use in regulatory
documents.
[[Page 47805]]
We are interested in your comments on whether the style of this
document is clear, and your suggestions to improve the clarity of our
communications that affect you. You can get more information about
plain language at http://www.faa.gov/language and http://
www.plainlanguage.gov.
Examining the Docket
You may examine the AD docket 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 DMS
receives them.
Discussion
We have received a report of two operators finding cracks in the
fillet radii of the left and right butt line (BL) 25 vertical chords,
common to the nose wheel well bulkhead at station 287, on several
Boeing Model 767-300 series airplanes. Stress corrosion was determined
to have caused the cracks. This condition, if not corrected, could grow
downward into a critical area that serves as a primary load path for
the nose landing gear (NLG) and result in the collapse of the NLG
during landing.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 767-53A0113, dated
February 26, 2004. The service bulletin describes procedures for
repetitive high frequency eddy current inspections (HFEC) and detailed
inspections of the left and right BL 25 vertical chords common to the
nose wheel well bulkhead at station 287 for cracks, and corrective
actions if necessary. The corrective action includes repairing any
damaged BL 25 vertical chord or contacting the manufacturer for repair
instructions, as applicable. We have determined that accomplishment of
the actions specified in the service bulletin will adequately address
the unsafe condition.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. Therefore, we are proposing this AD, which
would require repetitive HFEC inspections and detailed inspections of
the left and right BL 25 vertical chords common to the nose wheel well
bulkhead at station 287 for cracks, and corrective actions if
necessary. The proposed AD would require you to use the service
information described previously to perform these actions, except as
discussed under ``Difference Between the Proposed AD and the Service
Bulletin.''
Differences Between the Proposed AD and the Service Bulletin
The service bulletin specifies that you may contact the
manufacturer for instructions on repairing certain conditions. This
proposed AD, however, would require you to repair those conditions
using a method approved by the FAA, or with data meeting the type
certification basis of the airplane approved by a Boeing Company
Designated Engineering Representative who has been authorized by the
FAA to make such findings.
Clarification of Inspection Terminology
In this proposed AD, the ``detailed visual inspection'' specified
in the service bulletin is referred to as a ``detailed inspection.'' We
have included the definition for a detailed inspection in a note in
this proposed AD.
Clarification Between Proposed Rule and the Service Bulletin
The service bulletin specifies a compliance time of 6 years in
service, or within 18 months from the release date of the service
bulletin. However, paragraph (g) of this proposed AD specifies the
compliance time as the later of the following: (1) within 72 months
since the date of issuance of the original Airworthiness Certificate or
the date of issuance of the original Export Certificate of
Airworthiness, or (2) within 18 months after the effective date of this
AD. This decision is based on our determination that ``years in
service'' may be interpreted differently by different operators. We
find that our proposed terminology is generally understood within the
industry and records will always exist that establish these dates with
certainty.
Costs of Compliance
This proposed AD would affect about 743 airplanes worldwide and 312
airplanes of U.S. registry. The proposed actions would take about 8
work hours per airplane, at an average labor rate of $65 per work hour.
No parts are required. Based on these figures, the estimated cost of
the proposed AD for U.S. operators is $162,240, or $520 per airplane,
per inspection cycle.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify that the 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. 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 proposed AD. 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA-2004-18786; Directorate Identifier 2004-NM-
26-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by September 20, 2004.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 767-200, -300, and -300F
series airplanes, certificated in any category; as listed in Boeing
Alert Service Bulletin 767-53A0113, dated February 26, 2004.
Unsafe Condition
(d) This AD was prompted by findings of cracks in the fillet
radii of the left and right
[[Page 47806]]
butt line (BL) 25 vertical chords common to the nose wheel well
bulkhead at station 287. We are issuing this AD to detect and
correct cracks in the left and right BL 25 vertical chords, which
could grow downward into a critical area that serves as a primary
load path for the nose landing gear (NLG) and result in the collapse
of the NLG during landing.
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.
Service Bulletin Reference
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
53A0113, dated February 26, 2004.
Initial Inspections
(g) At the later of the compliance times specified in paragraphs
(g)(1) and (g)(2) of this AD: Do a high frequency eddy current
inspection and a detailed inspection of the left and right BL 25
vertical chords common to the nose wheel well bulkhead at station
287 for cracks, in accordance with the service bulletin.
(1) Within 72 months since the date of issuance of the original
Airworthiness Certificate or the date of issuance of the original
Export Certificate of Airworthiness.
(2) Within 18 months after the effective date of this AD.
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.''
No Cracks Found
(h) For any BL 25 vertical chord in which no crack is found
during any inspection required by paragraph (g) of this AD:
Thereafter at intervals not to exceed 48 months, repeat the
inspections required by paragraph (g) of this AD for any BL 25
vertical chord that has not been repaired according to paragraph (i)
or (j) of this AD.
Cracks Found: Extending Below Water Line (WL) 159
(i) If any crack is found on any BL 25 vertical chord during any
inspection required by paragraph (g) or (h) of this AD, and the
crack extends below WL 159: Before further flight, repair per a
method approved by the Manager, Seattle Aircraft Certification
Office (ACO), FAA; or per data meeting the type certification basis
of the airplane approved by a Boeing Company Designated Engineering
Representative who has been authorized by the Manager, Seattle ACO,
to make such findings. For a repair method to be approved, the
approval must specifically reference this AD.
Cracks Found: Not Extending Below WL 159
(j) If any crack is found in any BL 25 vertical chord during any
inspection required by paragraph (g) or (h) of this AD, and the
crack does not extend below WL 159: Before further flight, repair
any damaged BL 25 vertical chord in accordance with the service
bulletin.
Repaired BL 25 Vertical Chords
(k) Repair of any BL 25 vertical chord in accordance with
paragraph (i) or (j) of this AD, as applicable, terminates the
repetitive inspections required by paragraph (h) of this AD for the
repaired vertical chord only. If both the left and right BL 25
vertical chords are repaired as required by paragraph (i) or (j) of
this AD, as applicable, no more work is required by this AD.
Alternative Methods of Compliance (AMOCs)
(l)(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.
(2) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by a
Boeing Company Designated Engineering Representative who has been
authorized by the Manager, Seattle ACO, to make such findings.
Issued in Renton, Washington, on July 30, 2004.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-17986 Filed 8-5-04; 8:45 am]
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