[Federal Register Volume 69, Number 191 (Monday, October 4, 2004)]
[Proposed Rules]
[Pages 59151-59153]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-22268]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19228; Directorate Identifier 2004-NM-77-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 707 Airplanes and Model
720 and 720B 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 all Boeing Model 707 airplanes and Model 720 and 720B series
airplanes. This proposed AD would require repetitive inspections of the
left and right support ribs for the main landing gear (MLG) trunnion,
related investigative/corrective actions if necessary, and other
specified actions. This proposed AD is prompted by reports of in-
service cracking of the support ribs for the MLG trunnion. We are
proposing this AD to detect and correct corrosion and cracking of the
support ribs for the MLG trunnion, which could result in collapse of
the MLG.
DATES: We must receive comments on this proposed AD by November 18,
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.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
You can 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:
Technical information: Candice Gerretsen, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6428; fax (425) 917-6590.
Plain language information: Marcia Walters, [email protected].
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-2004-19228;
Directorate Identifier 2004-NM-77-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.
[[Page 59152]]
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 can review DOT's
complete Privacy Act Statement in the Federal Register published on
April 11, 2000 (65 FR 19477-78), or you can visit http://dms.dot.gov.
We are reviewing the writing style we currently use in regulatory
documents. 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 can examine the AD docket on the Internet at http://dms.dot.gov, or 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 reports of in-service cracking of the support ribs
for the main landing gear (MLG) trunnion on Boeing Model 707 airplanes
and Model 720 and 720B series airplanes. Investigation revealed that
the cracking was caused by stress corrosion. This condition, if not
corrected, could result in collapse of the MLG.
Relevant Service Information
We have reviewed Boeing 707 Alert Service Bulletin A3510, dated
January 15, 2004. Part I of the Accomplishment Instructions of the
alert service bulletin describes procedures for doing a repetitive
detailed inspection of the left and right support ribs for the MLG
trunnion and related investigative/corrective and other specified
actions. The inspection areas include both sides of the rib flanges,
the web, the flange radius, and the support rib. The procedures
include:
Removing all corrosion inhibiting compound and sealant
from the inspection areas.
Removing the finish and blending the area smooth if
deterioration, discoloration, blistering, wear, scratches, or raised
rough/cracked areas in the surface finish are found.
Contacting Boeing if blending into the base metal is
necessary.
Mechanically removing any corrosion.
Contacting Boeing for repair information if any cracking
is found.
Applying cadmium plating to all areas where the surface
finish was removed.
Applying corrosion inhibitor to all exposed surfaces of
the support fitting for the MLG trunnion.
Part II of the Accomplishment Instructions of the alert service
bulletin includes procedures for doing a repetitive HFEC inspection of
the left and right support ribs for the MLG trunnion, and corrective
and other specified actions. The inspection areas include both sides of
the web flange, the flange radius, the area around all bolt heads/nuts
and fastener heads/collars for the upper and lower chords, and the rib
around the edge of the support fitting for the MLG trunnion. The
corrective and other specified actions include:
Removing all corrosion inhibiting compound and sealant
from the inspection areas.
Contacting Boeing for repair information if any cracking
is found.
Applying cadmium plate to all areas where the surface
finish was removed.
Applying corrosion inhibitor to all exposed surfaces of
the support fitting for the MLG trunnion, both sides of the flange
radius of the upper and lower chords, and the rib supports.
Accomplishing the actions specified in the service information is
intended to 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 inspections for corrosion and cracking of the
left and right support ribs for the main landing gear (MLG) trunnion,
related investigative/corrective actions if necessary, and other
specified actions. The proposed AD would require you to use the service
information described previously to perform these actions, except as
discussed under ``Differences Between the Proposed AD and Service
Information.''
Differences Between the Proposed AD and Service Information
The alert service bulletin specifies that the manufacturer may be
contacted for disposition of certain repair conditions. This proposed
AD would require the repair of those conditions in accordance with a
method that we have approved or in accordance with data meeting the
type certification basis of the airplane approved by a Boeing Company
Designated Engineering Representative whom we have authorized to make
such findings.
Costs of Compliance
This proposed AD would affect about 227 airplanes worldwide. The
following table provides the estimated costs for U.S. operators to
comply with this proposed AD.
Estimated Costs
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Number of
Work Average U.S.-
Action hours labor rate Parts Cost per airplane registered Fleet cost
per hour airplanes
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Inspection, per inspection cycle......... 6 $65 None $390, per inspection cycle.. 32 $12,480, per inspection
cycle.
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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.
[[Page 59153]]
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-2004-19228; Directorate Identifier 2004-NM-
77-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by November 18, 2004.
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 airplanes; and Model 720 and 720B
series airplanes; certificated in any category.
Unsafe Condition
(d) This AD was prompted by reports of in-service cracking of
the support ribs for the main landing gear (MLG) trunnion. We are
proposing this AD to detect and correct corrosion and cracking of
the support ribs for the MLG trunnion, which could result in
collapse of the MLG.
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 References
(f) The term ``alert service bulletin,'' as used in this AD,
means the Accomplishment Instructions of Boeing 707 Alert Service
Bulletin A3510, dated January 15, 2004.
Repetitive Detailed Inspection and Corrective Action
(g) Within 6 months after the effective date of this AD: Do a
detailed inspection for corrosion and cracking of the left and right
support ribs of the MLG trunnion. Do the inspection in accordance
with all of the actions in Part I of the alert service bulletin.
Repeat the inspection thereafter at intervals not to exceed 6
months.
(h) If any corrosion or cracking is found during any inspection
required by paragraph (g) of this AD: Before further flight, do all
applicable related investigative and corrective actions, and the
other specified actions, in accordance with the alert service
bulletin; except, where the alert service bulletin specifies to
contact Boeing, before further flight, repair in accordance with a
method approved by the Manager, Seattle Aircraft Certification
Office (ACO), FAA; or in accordance with data meeting the type
certification basis of the airplane approved by a Boeing Designated
Engineering Representative (DER) who has been authorized by the
Manager, Seattle ACO, to make such findings. For a repair method to
be approved by the Manager, Seattle ACO, as required by this
paragraph, the approval letter must specifically reference this AD.
Repetitive High Frequency Eddy Current (HFEC) Inspection and Corrective
Action
(i) Within 12 months after the effective date of this AD: Do a
HFEC inspection for cracking of the left and right support ribs of
the MLG trunnion. Do the inspection in accordance with all of the
actions in Part II of the alert service bulletin. Repeat the
inspection thereafter at intervals not to exceed 12 months.
(j) If cracking is found during any inspection required by
paragraph (i) of this AD: Before further flight, repair the cracked
area in accordance with a method approved by the Manager, Seattle
ACO; or in accordance with data meeting the type certification basis
of the airplane approved by a Boeing DER who has been authorized by
the Manager, Seattle ACO, to make such findings. For a repair method
to be approved, the approval must specifically refer to this AD.
Alternative Methods of Compliance (AMOCs)
(k)(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) 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 DER who has been authorized by the Manager, Seattle
ACO, to make those findings. For a repair method to be approved, the
approval must specifically refer to this AD.
Issued in Renton, Washington, on September 27, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-22268 Filed 10-1-04; 8:45 am]
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