Airworthiness Directives; McDonnell Douglas Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 Airplanes; Model DC-8-50 Series Airplanes; Model DC-8F-54 and DC-8F-55 Airplanes; Model DC-8-60 Series Airplanes; Model DC-8-60F Series Airplanes; Model DC-8-70 Series Airplanes; and Model DC-8-70F Series Airplanes, 46823-46826 [E8-18560]
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46823
Proposed Rules
Federal Register
Vol. 73, No. 156
Tuesday, August 12, 2008
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0858; Directorate
Identifier 2008–NM–054–AD]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model DC–8–11, DC–8–12,
DC–8–21, DC–8–31, DC–8–32, DC–8–
33, DC–8–41, DC–8–42, and DC–8–43
Airplanes; Model DC–8–50 Series
Airplanes; Model DC–8F–54 and DC–
8F–55 Airplanes; Model DC–8–60
Series Airplanes; Model DC–8–60F
Series Airplanes; Model DC–8–70
Series Airplanes; and Model DC–8–70F
Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
yshivers on PROD1PC62 with PROPOSALS
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for all
McDonnell Douglas airplanes identified
above. This proposed AD would require
repetitive inspections of the lower skin
and stringers at stations Xw = 408 and
Xw = ¥408 and corrective actions if
necessary. This proposed AD results
from reports of cracks in the skins and
stringers at the end fasteners common to
the stringer end fittings at station Xw =
408 and Xw = ¥408 wing splice joints.
We are proposing this AD to detect and
correct fatigue cracking in the skins and
stringers at the end fasteners common to
the stringer end fittings at a certain
station and wing splice joints, which
could result in wing structure that might
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14:12 Aug 11, 2008
Jkt 214001
not sustain limit load, and consequent
loss of structural integrity of the wing.
DATES: We must receive comments on
this proposed AD by September 26,
2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach,
California 90846, Attention: Data and
Service Management, Dept. C1–L5A
(D800–0024).
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Dara
Albouyeh, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood,
California 90712–4137; telephone (562)
627–5222; fax (562) 627–5210.
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Fmt 4702
Sfmt 4702
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0858; Directorate Identifier
2008–NM–054–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received numerous reports of
cracks in the skins and stringers at the
end fasteners common to the stringer
end fittings at station Xw = 408 and Xw
= ¥408 wing splice joints. Results of an
investigation conducted by Boeing
Engineering revealed the cracks were
due to fatigue. The area where the
cracks were found is identified as a
principal structural element (PSE). The
earliest cracks were discovered at
21,519 total flight cycles, and 58,935
total flight hours. The cracks were
discovered by visual inspections and
findings of fuel leaks. In addition to
unscheduled maintenance for repair of
the PSE, this condition, if not corrected,
could result in wing structure that might
not sustain limit load, and consequent
loss of structural integrity of the wing.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin DC8–57A102, dated
February 12, 2008. The service bulletin
describes the following procedures.
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46824
Federal Register / Vol. 73, No. 156 / Tuesday, August 12, 2008 / Proposed Rules
DESCRIBED ACTIONS AND COMPLIANCE TIMES
Condition
Action
Compliance times
Initial inspection for all airplanes ........................
Do initial high frequency eddy current (HFEC)
inspection of the lower wing skin or stringers at the affected fastener hole areas—
stations Xw = 408 and Xw = ¥408, stringers 51 to 64 (for sequence 101, inspection
sequence 1, inspection method 01; or sequence 103, inspection sequence 1, inspection method 03), or a visual inspection of
any accessible area along the cross section
of the stringer in the area of the affected
fastener holes (for sequence 102, inspection sequence 1, inspection method 02).
Repeat the HFEC or visual inspection, as applicable.
Before the accumulation of 20,000 total flight
cycles, or within 1,500 flight cycles or 2
years after the date of the service bulletin,
whichever occurs latest.
Repeat the HFEC or visual inspection, as applicable.
Intervals not to exceed 1,200 flight cycles
after doing the external skin eddy current
inspection and internal stringer inspection.
Repair crack and repeat the applicable inspection specified for Condition 2, as applicable.
Repeat the HFEC or visual inspection, as applicable.
Before further flight (repair only).
Condition 1: No cracks at any of the locations—
and prior inspection was done by external
skin eddy current inspection as given in sequence 103.
Condition 1: No cracks at any of the locations—
prior inspection was done by external skin
eddy current inspection as given in sequence
103—and—internal stringer inspection as
given in sequence 101 or 102 is done.
Condition 2: Skin cracks less than 3.7 inches
long in wing skin at stringer end fittings.
Intervals not to exceed 600 flight cycles after
doing the external skin eddy current inspection.
Intervals not to exceed 600 flight cycles after
doing the external skin eddy current inspection.
FAA’s Determination and Requirements
of This Proposed AD
yshivers on PROD1PC62 with PROPOSALS
Condition 2: Skin cracks less than 3.7 inches
long in wing skin at stringer end fittings—
and prior inspection was done by external
skin eddy current inspection as given in sequence 103.
Condition 2: Skin cracks less than 3.7 inches Repeat the HFEC or visual inspection, as aplong in wing skin at stringer end fittings—
plicable.
and prior inspection was done by external
skin eddy current inspection as given in sequence 103—and—internal stringer inspection as given in sequence 101 or 102 is done.
Condition 3: Skin cracks greater than 3.7 Contact Boeing for repair instructions .............
inches at stringer end fittings.
Condition 4: Stringer cracks at stringer end fit- Repair crack and repeat the applicable intings.
spection specified for Condition 4, as applicable.
Condition 4: Stringer cracks at stringer end fit- Repeat the HFEC or visual inspection, as aptings—and prior inspection was done by explicable.
ternal skin eddy current inspection as given
in sequence 103.
Condition 4: Stringer cracks at stringer end fit- Repeat the HFEC or visual inspection, as aptings—and prior inspection was done by explicable.
ternal skin eddy current inspection as given
in sequence 103—and—internal stringer inspection as given in sequence 101 or 102 is
done.
Condition 5: Cracks at more than two adjacent Contact Boeing for repair instructions .............
stringers.
Between the Proposed AD and the
Service Bulletin.’’
We are proposing this AD because we
evaluated all relevant information and
determined the unsafe condition
described previously is likely to exist or
develop in other products of the(se)
same type design(s). This proposed AD
would require accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Difference
Difference Between the Proposed AD
and the Service Bulletin
The service bulletin specifies to
contact the manufacturer for
instructions on how to repair certain
conditions, but this proposed AD would
require repairing those conditions in
one of the following ways:
• Using a method that we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by an
Authorized Representative for the
Boeing Commercial Airplanes
Delegation Option Authorization
Organization whom we have authorized
to make those findings.
VerDate Aug<31>2005
14:12 Aug 11, 2008
Jkt 214001
PO 00000
Frm 00002
Fmt 4702
Sfmt 4702
Intervals not to exceed 1,200 flight cycles
after doing the external skin eddy current
inspection and internal stringer inspection.
Before further flight.
Before further flight (repair only).
Repeat at intervals not to exceed 600 flight
cycles after doing the external skin eddy
current inspection.
Repeat at intervals not to exceed 1,200 flight
cycles after doing the external skin eddy
current inspection and internal stringer inspection.
Before further flight.
Costs of Compliance
We estimate that this proposed AD
would affect 87 airplanes of U.S.
registry. The following table provides
the estimated costs for U.S. operators to
comply with this proposed AD.
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46825
Federal Register / Vol. 73, No. 156 / Tuesday, August 12, 2008 / Proposed Rules
ESTIMATED COSTS
Action
Average
labor rate
per hour
Work hours
Inspection ..........................
6
$80
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.
yshivers on PROD1PC62 with PROPOSALS
Regulatory Findings
We 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 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. 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.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
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,
VerDate Aug<31>2005
14:12 Aug 11, 2008
Jkt 214001
Parts
$0
$480, per inspection cycle
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
McDonnell Douglas: Docket No. FAA–2008–
0858; Directorate Identifier 2008–NM–
054–AD.
Comments Due Date
(a) We must receive comments by
September 26, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all McDonnell
Douglas Model DC–8–11, DC–8–12, DC–8–
21, DC–8–31, DC–8–32, DC–8–33, DC–8–41,
DC–8–42, DC–8–43, DC–8–51, DC–8–52, DC–
8–53, DC–8–55, DC–8F–54, DC–8F–55, DC–
8–61, DC–8–62, DC–8–63, DC–8–61F, DC–8–
62F, DC–8–63F, DC–8–71, DC–8–72, DC–8–
73, DC–8–71F, DC–8–72F, and DC–8–73F
airplanes; certificated in any category.
Unsafe Condition
(d) This AD results from reports of cracks
in the skins and stringers at the end fasteners
common to the stringer end fittings at
stations Xw = 408 and Xw = ¥408 wing
splice joints. We are issuing this AD to detect
and correct fatigue cracking in the skins and
stringers at the end fasteners common to the
stringer end fittings at a certain station and
wing splice joints, which could result in
wing structure that might not sustain limit
load, and consequent loss of structural
integrity of the wing.
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Repetitive Inspections and Corrective
Actions
(f) At the times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin DC8–57A102, dated February 12,
2008, except as provided by paragraph (g) of
this AD: Do the applicable inspections for
fatigue cracking of the lower skin and
stringers at stations Xw = 408 and Xw =
¥408, and do all applicable corrective
PO 00000
Frm 00003
Number of
U.S.-registered
airplanes
Cost per product
Fmt 4702
Sfmt 4702
87
Fleet cost
$41,760, per inspection
cycle.
actions, by accomplishing all applicable
actions specified in the Accomplishment
Instructions of the service bulletin, except as
provided by paragraph (h) of this AD. Do all
corrective actions before further flight, in
accordance with the service bulletin.
Thereafter, repeat the inspections at the
applicable intervals specified in paragraph
1.E. of the service bulletin.
(g) Where Boeing Alert Service Bulletin
DC8–57A102, dated February 12, 2008,
specifies a compliance time after the date on
the service bulletin, this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(h) If any cracking is found during any
inspection required by this AD, and Boeing
Alert Service Bulletin DC8–57A102, dated
February 12, 2008, specifies to contact
Boeing for appropriate action: Before further
flight, repair the cracking using a method
approved in accordance with the procedures
specified in paragraph (i) of this AD.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), FAA, ATTN: Dara
Albouyeh, Aerospace Engineer, Airframe
Branch, ANM–120L, 3960 Paramount
Boulevard, Lakewood, California 90712–
4137; telephone (562) 627–5222; fax (562)
627–5210; has the authority to approve
AMOCs for this AD, if requested using 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Los Angeles
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane and 14
CFR 25.571, Amendment 45, and the
approval must specifically refer to this AD.
(4) Accomplishing the requirements of this
AD is an acceptable AMOC with the
requirements of paragraph (b) of AD 93–01–
15, amendment 39–8469, for those areas of
principal structural element 57.08.037/038.
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46826
Federal Register / Vol. 73, No. 156 / Tuesday, August 12, 2008 / Proposed Rules
Issued in Renton, Washington, on July 31,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–18560 Filed 8–11–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HOUSING AND
URBAN DEVELOPMENT
24 CFR Part 15
[Docket No. FR–5206–P–01]
RIN 2501–AD39
Public Access to HUD Records Under
the Freedom of Information Act (FOIA)
and Production of Material or
Provision of Testimony by HUD
Employees: Revisions to Policies and
Practices Regarding Subpoenas and
Other Demands for Testimony
Office of the Secretary, HUD.
Proposed rule.
AGENCY:
yshivers on PROD1PC62 with PROPOSALS
ACTION:
SUMMARY: This proposed rule would
modify HUD’s policies and practices
regarding responses to subpoenas and
other demands for testimony of HUD
employees, or for production of
documents by HUD. This proposed rule
would delegate authority to additional
officials within HUD’s Office of General
Counsel and would revise the criteria
used to evaluate such demands. Finally,
this rule would eliminate unnecessary
provisions covering HUD’s response to
demands in cases in which the United
States is a party to the case in which
testimony or documents are requested.
DATES: Comment Due Date: October 14,
2008.
ADDRESSES: Interested persons are
invited to submit comments regarding
this proposed rule to the Regulations
Division, Office of General Counsel,
Department of Housing and Urban
Development, 451 Seventh Street, SW.,
Room 10276, Washington, DC 20410–
0500. Communications must refer to the
above docket number and title. There
are two methods for submitting public
comments. All submissions must refer
to the above docket number and title.
1. Submission of Comments by Mail.
Comments may be submitted by mail to
the Regulations Division, Office of
General Counsel, Department of
Housing and Urban Development, 451
Seventh Street, SW., Room 10276,
Washington, DC 20410–0500.
2. Electronic Submission of
Comments. Interested persons may
submit comments electronically through
the Federal eRulemaking Portal at
www.regulations.gov. HUD strongly
VerDate Aug<31>2005
14:12 Aug 11, 2008
Jkt 214001
encourages commenters to submit
comments electronically. Electronic
submission of comments allows the
commenter maximum time to prepare
and submit a comment, ensures timely
receipt by HUD, and enables HUD to
make them immediately available to the
public. Comments submitted
electronically through the
www.regulations.gov Web site can be
viewed by other commenters and
interested members of the public.
Commenters should follow the
instructions provided on that site to
submit comments electronically.
Note: To receive consideration as public
comments, comments must be submitted
through one of the two methods specified
above. Again, all submissions must refer to
the docket number and title of the rule. No
Facsimile Comments. Facsimile (FAX)
comments are not acceptable.
Public Inspection of Public
Comments. All comments and
communications submitted to HUD will
be available, without charge, for public
inspection and copying between 8 a.m.
and 5 p.m. weekdays at the above
address. Due to security measures at the
HUD Headquarters building, an advance
appointment to review the public
comments must be scheduled by calling
the Regulations Division at 202–402–
3055 (this is not a toll-free number).
Individuals with speech or hearing
impairments may access this number
via TTY by calling the Federal
Information Relay Service at 1–800–
877–8339. Copies of all comments
submitted are available for inspection
and downloading at
www.regulations.gov.
FOR FURTHER INFORMATION CONTACT:
Nancy Christopher, Associate General
Counsel for Litigation, Office of
Litigation, Office of General Counsel,
Department of Housing and Urban
Development, 451 Seventh Street, SW.,
Room 10258, Washington, DC 20410–
0500; telephone number 202–708–0300
(this is not a toll-free telephone
number). Persons with hearing or
speech impairments may access this
number via TTY by calling the toll-free
Federal Information Relay Service at 1–
800–877–8339.
SUPPLEMENTARY INFORMATION:
I. Background
HUD’s regulations at 24 CFR part 15
describe the policies and procedures
governing public access to HUD records
under the Freedom of Information Act
(FOIA) (5 U.S.C. 552) and the policies
and procedures governing the
production of material or provision of
testimony by HUD employees. On
February 26, 2007 (72 FR 8580), HUD
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
published a final rule to clarify and
explain the various types of requests for
HUD documents and testimony by HUD
employees that are intended to be
covered by HUD’s document production
and testimony approval regulations. The
final rule revised subparts C and D to
describe the procedures to be followed
by a party in making a demand to HUD
for documents or testimony, and to
explain the standards followed by HUD
in determining whether production or
testimony should be permitted. A
technical correction to the final rule was
published on September 20, 2007 (72 FR
53876).
II. This Proposed Rule—Proposed
Amendments to Part 15
After implementing the revised
procedures for consideration of
demands for documents or testimony,
HUD has determined that additional
changes are necessary to ensure the
careful and efficient processing of all
such demands. The revisions proposed
to be made to HUD’s regulations at 24
CFR part 15 are as follows:
Terminology
This proposed rule would amend
§ 15.2 to add, in alphabetical order, the
terms ‘‘Appropriate Associate General
Counsel,’’ ‘‘Appropriate Regional
Counsel,’’ and ‘‘Authorized Approving
Official’’ to the list of definitions.
Technical Changes
This proposed rule would correct
outdated references to Web sites in
§§ 15.102(b) and 15.103(c). This
proposed rule would also make
technical changes to Appendix A of part
15 by directing the public to HUD’s Web
site to update the location information
of HUD FOIA Reading Rooms and by
providing the public with the contact
information of HUD’s Regional Counsel.
Purpose and Scope
This proposed rule would amend
§ 15.201 by providing guidance to
persons engaged in private litigation, to
which the United States is not a party,
on the procedures to be followed when
making a demand for documents or
testimony on HUD. This proposed rule
would provide that HUD’s regulations
in subpart C do not create any
affirmative right or benefit, substantive
or procedural, that would be enforceable
against HUD.
Production of Material or Provision of
Testimony in Response to Demands in
Legal Proceedings Among Private
Litigants
This proposed rule would amend
§§ 15.202 through 15.206 by outlining
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]]>Agencies
[Federal Register Volume 73, Number 156 (Tuesday, August 12, 2008)]
[Proposed Rules]
[Pages 46823-46826]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-18560]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 73, No. 156 / Tuesday, August 12, 2008 /
Proposed Rules
[[Page 46823]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0858; Directorate Identifier 2008-NM-054-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-8-11, DC-8-
12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43
Airplanes; Model DC-8-50 Series Airplanes; Model DC-8F-54 and DC-8F-55
Airplanes; Model DC-8-60 Series Airplanes; Model DC-8-60F Series
Airplanes; Model DC-8-70 Series Airplanes; and Model DC-8-70F Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
McDonnell Douglas airplanes identified above. This proposed AD would
require repetitive inspections of the lower skin and stringers at
stations Xw = 408 and Xw = -408 and corrective actions if necessary.
This proposed AD results from reports of cracks in the skins and
stringers at the end fasteners common to the stringer end fittings at
station Xw = 408 and Xw = -408 wing splice joints. We are proposing
this AD to detect and correct fatigue cracking in the skins and
stringers at the end fasteners common to the stringer end fittings at a
certain station and wing splice joints, which could result in wing
structure that might not sustain limit load, and consequent loss of
structural integrity of the wing.
DATES: We must receive comments on this proposed AD by September 26,
2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard,
Long Beach, California 90846, Attention: Data and Service Management,
Dept. C1-L5A (D800-0024).
Examining the AD Docket
You may examine the AD docket on the Internet at https://
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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Dara Albouyeh, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5222; fax (562) 627-5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0858;
Directorate Identifier 2008-NM-054-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received numerous reports of cracks in the skins and
stringers at the end fasteners common to the stringer end fittings at
station Xw = 408 and Xw = -408 wing splice joints. Results of an
investigation conducted by Boeing Engineering revealed the cracks were
due to fatigue. The area where the cracks were found is identified as a
principal structural element (PSE). The earliest cracks were discovered
at 21,519 total flight cycles, and 58,935 total flight hours. The
cracks were discovered by visual inspections and findings of fuel
leaks. In addition to unscheduled maintenance for repair of the PSE,
this condition, if not corrected, could result in wing structure that
might not sustain limit load, and consequent loss of structural
integrity of the wing.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin DC8-57A102, dated
February 12, 2008. The service bulletin describes the following
procedures.
[[Page 46824]]
Described Actions and Compliance Times
------------------------------------------------------------------------
Condition Action Compliance times
------------------------------------------------------------------------
Initial inspection for all Do initial high Before the
airplanes. frequency eddy accumulation of
current (HFEC) 20,000 total flight
inspection of the cycles, or within
lower wing skin or 1,500 flight cycles
stringers at the or 2 years after
affected fastener the date of the
hole areas-- service bulletin,
stations Xw = 408 whichever occurs
and Xw = -408, latest.
stringers 51 to 64
(for sequence 101,
inspection sequence
1, inspection
method 01; or
sequence 103,
inspection sequence
1, inspection
method 03), or a
visual inspection
of any accessible
area along the
cross section of
the stringer in the
area of the
affected fastener
holes (for sequence
102, inspection
sequence 1,
inspection method
02).
Condition 1: No cracks at Repeat the HFEC or Intervals not to
any of the locations--and visual inspection, exceed 600 flight
prior inspection was done as applicable. cycles after doing
by external skin eddy the external skin
current inspection as given eddy current
in sequence 103. inspection.
Condition 1: No cracks at Repeat the HFEC or Intervals not to
any of the locations--prior visual inspection, exceed 1,200 flight
inspection was done by as applicable. cycles after doing
external skin eddy current the external skin
inspection as given in eddy current
sequence 103--and--internal inspection and
stringer inspection as internal stringer
given in sequence 101 or inspection.
102 is done.
Condition 2: Skin cracks Repair crack and Before further
less than 3.7 inches long repeat the flight (repair
in wing skin at stringer applicable only).
end fittings. inspection
specified for
Condition 2, as
applicable.
Condition 2: Skin cracks Repeat the HFEC or Intervals not to
less than 3.7 inches long visual inspection, exceed 600 flight
in wing skin at stringer as applicable. cycles after doing
end fittings-- and prior the external skin
inspection was done by eddy current
external skin eddy current inspection.
inspection as given in
sequence 103.
Condition 2: Skin cracks Repeat the HFEC or Intervals not to
less than 3.7 inches long visual inspection, exceed 1,200 flight
in wing skin at stringer as applicable. cycles after doing
end fittings-- and prior the external skin
inspection was done by eddy current
external skin eddy current inspection and
inspection as given in internal stringer
sequence 103--and--internal inspection.
stringer inspection as
given in sequence 101 or
102 is done.
Condition 3: Skin cracks Contact Boeing for Before further
greater than 3.7 inches at repair instructions. flight.
stringer end fittings.
Condition 4: Stringer cracks Repair crack and Before further
at stringer end fittings. repeat the flight (repair
applicable only).
inspection
specified for
Condition 4, as
applicable.
Condition 4: Stringer cracks Repeat the HFEC or Repeat at intervals
at stringer end fittings-- visual inspection, not to exceed 600
and prior inspection was as applicable. flight cycles after
done by external skin eddy doing the external
current inspection as given skin eddy current
in sequence 103. inspection.
Condition 4: Stringer cracks Repeat the HFEC or Repeat at intervals
at stringer end fittings-- visual inspection, not to exceed 1,200
and prior inspection was as applicable. flight cycles after
done by external skin eddy doing the external
current inspection as given skin eddy current
in sequence 103--and-- inspection and
internal stringer internal stringer
inspection as given in inspection.
sequence 101 or 102 is done.
Condition 5: Cracks at more Contact Boeing for Before further
than two adjacent stringers. repair instructions. flight.
------------------------------------------------------------------------
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the(se) same type
design(s). This proposed AD would require accomplishing the actions
specified in the service information described previously, except as
discussed under ``Difference Between the Proposed AD and the Service
Bulletin.''
Difference Between the Proposed AD and the Service Bulletin
The service bulletin specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions in one of the following ways:
Using a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by an Authorized Representative
for the Boeing Commercial Airplanes Delegation Option Authorization
Organization whom we have authorized to make those findings.
Costs of Compliance
We estimate that this proposed AD would affect 87 airplanes of U.S.
registry. The following table provides the estimated costs for U.S.
operators to comply with this proposed AD.
[[Page 46825]]
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Average U.S.-
Action Work hours labor rate Parts Cost per product registered Fleet cost
per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection............................... 6 $80 $0 $480, per inspection cycle.. 87 $41,760, per inspection
cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 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 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. 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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
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 AD:
McDonnell Douglas: Docket No. FAA-2008-0858; Directorate Identifier
2008-NM-054-AD.
Comments Due Date
(a) We must receive comments by September 26, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all McDonnell Douglas Model DC-8-11, DC-
8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, DC-8-43,
DC-8-51, DC-8-52, DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, DC-8-61, DC-
8-62, DC-8-63, DC-8-61F, DC-8-62F, DC-8-63F, DC-8-71, DC-8-72, DC-8-
73, DC-8-71F, DC-8-72F, and DC-8-73F airplanes; certificated in any
category.
Unsafe Condition
(d) This AD results from reports of cracks in the skins and
stringers at the end fasteners common to the stringer end fittings
at stations Xw = 408 and Xw = -408 wing splice joints. We are
issuing this AD to detect and correct fatigue cracking in the skins
and stringers at the end fasteners common to the stringer end
fittings at a certain station and wing splice joints, which could
result in wing structure that might not sustain limit load, and
consequent loss of structural integrity of the wing.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Repetitive Inspections and Corrective Actions
(f) At the times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008,
except as provided by paragraph (g) of this AD: Do the applicable
inspections for fatigue cracking of the lower skin and stringers at
stations Xw = 408 and Xw = -408, and do all applicable corrective
actions, by accomplishing all applicable actions specified in the
Accomplishment Instructions of the service bulletin, except as
provided by paragraph (h) of this AD. Do all corrective actions
before further flight, in accordance with the service bulletin.
Thereafter, repeat the inspections at the applicable intervals
specified in paragraph 1.E. of the service bulletin.
(g) Where Boeing Alert Service Bulletin DC8-57A102, dated
February 12, 2008, specifies a compliance time after the date on the
service bulletin, this AD requires compliance within the specified
compliance time after the effective date of this AD.
(h) If any cracking is found during any inspection required by
this AD, and Boeing Alert Service Bulletin DC8-57A102, dated
February 12, 2008, specifies to contact Boeing for appropriate
action: Before further flight, repair the cracking using a method
approved in accordance with the procedures specified in paragraph
(i) of this AD.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Los Angeles Aircraft Certification Office
(ACO), FAA, ATTN: Dara Albouyeh, Aerospace Engineer, Airframe
Branch, ANM-120L, 3960 Paramount Boulevard, Lakewood, California
90712-4137; telephone (562) 627-5222; fax (562) 627-5210; has the
authority to approve AMOCs for this AD, if requested using 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.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Los Angeles ACO, to make those findings. For a
repair method to be approved, the repair must meet the certification
basis of the airplane and 14 CFR 25.571, Amendment 45, and the
approval must specifically refer to this AD.
(4) Accomplishing the requirements of this AD is an acceptable
AMOC with the requirements of paragraph (b) of AD 93-01-15,
amendment 39-8469, for those areas of principal structural element
57.08.037/038.
[[Page 46826]]
Issued in Renton, Washington, on July 31, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-18560 Filed 8-11-08; 8:45 am]
BILLING CODE 4910-13-P
