[Federal Register Volume 79, Number 74 (Thursday, April 17, 2014)]
[Proposed Rules]
[Pages 21648-21651]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-08726]
========================================================================
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. 79, No. 74 / Thursday, April 17, 2014 /
Proposed Rules
[[Page 21648]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0235; Directorate Identifier 2013-NM-249-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain The Boeing Company Model DC-8-55, 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. This proposed AD was prompted by multiple reports of
cracking of the upper aft skin panel of the fuselage. An evaluation by
the design approval holder (DAH) indicates that the upper aft skin
panel of the fuselage is subject to widespread fatigue damage (WFD).
This proposed AD would require removing any previously installed local
repairs; installing a full-length improvement modification with finger
doublers or a full-length repair with finger doublers; and repetitive
inspections for cracking of the doublers, and repair if necessary. We
are proposing this AD to detect and correct fatigue cracking of the
upper aft skin panel of the fuselage, which could result in loss of
structural integrity and consequent rapid decompression of the
airplane.
DATES: We must receive comments on this proposed AD by June 2, 2014.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://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: Deliver to Mail address above 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, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001;
telephone 206-544-5000, extension 2; fax 206-766-5683; Internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0235; 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 (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Chandraduth Ramdoss, Aerospace
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft
Certification Office (ACO), 3960 Paramount Blvd., Suite 100, Lakewood,
CA 90712-4137, phone: 562-627-5239; fax: 562-627-5210; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2014-0235;
Directorate Identifier 2013-NM-249-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 http://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
Structural fatigue damage is progressive. It begins as minute
cracks, and those cracks grow under the action of repeated stresses.
This can happen because of normal operational conditions and design
attributes, or because of isolated situations or incidents such as
material defects, poor fabrication quality, or corrosion pits, dings,
or scratches. Fatigue damage can occur locally, in small areas or
structural design details, or globally. Global fatigue damage is
general degradation of large areas of structure with similar structural
details and stress levels. Multiple-site damage is global damage that
occurs in a large structural element such as a single rivet line of a
lap splice joining two large skin panels. Global damage can also occur
in multiple elements such as adjacent frames or stringers. Multiple-
site-damage and multiple-element-damage cracks are typically too small
initially to be reliably detected with normal inspection methods.
Without intervention, these cracks will grow, and eventually compromise
the structural integrity of the airplane, in a condition known as WFD.
As an airplane ages, WFD will likely occur, and will certainly occur if
the airplane is operated long enough without any intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent catastrophic failure due to WFD throughout the operational life
of certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. For existing and
future airplanes subject to the WFD rule, the rule requires that
[[Page 21649]]
DAHs establish a limit of validity (LOV) of the engineering data that
support the structural maintenance program. Operators affected by the
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV
is approved.
The WFD rule (75 FR 69746, November 15, 2010) does not require
identifying and developing maintenance actions if the DAHs can show
that such actions are not necessary to prevent WFD before the airplane
reaches the LOV. Many LOVs, however, do depend on accomplishment of
future maintenance actions. As stated in the WFD rule, any maintenance
actions necessary to reach the LOV will be mandated by airworthiness
directives through separate rulemaking actions.
In the context of WFD, this approach is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval), while providing operators with
certainty regarding the LOV applicable to their airplanes.
During routine maintenance inspections, three operators reported
finding cracks in the upper aft skin panel. The cracks were located
along the upper row of rivets common to the longeron 28 skin splice,
near the flat aft pressure bulkhead. Cracks were detected on airplanes
that had accumulated between 27,072 and 46,176 total flight cycles.
This cracking, if not corrected, could result in fatigue cracking of
the upper aft skin panel of the fuselage, which could result in loss of
structural integrity and consequent rapid decompression of the
airplane.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin DC8-53A080, Revision 2,
dated September 18, 2013. For information on the procedures and
compliance times, see this service information at http://www.regulations.gov by searching for Docket No. FAA-2014-0235.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require removing previously installed local
repairs; installing a full-length improvement modification with finger
doublers, or a full-length repair with finger doublers; and doing
repetitive detailed inspections or repetitive low frequency eddy
current inspections for cracking along all four edges of the doublers,
and corrective action if necessary.
Related Rulemaking
On March 9, 2008, we issued AD 2008-06-23, Amendment 39-15435 (73
FR 14378, March 18, 2008). AD 2008-06-23 provides an option to install
full-length preventive modifications or full-length repairs, and
requires repetitive inspections. Accomplishing these actions is a
method of compliance with the requirements of paragraphs (g) and (h) of
this proposed AD.
Differences Between This Proposed AD and the Service Information
Boeing Alert Service Bulletin DC8-53A080, Revision 2, dated
September 18, 2013, 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:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Explanation of Compliance Time
The compliance time for the modification specified in this proposed
AD for addressing WFD was established to ensure that discrepant
structure is modified before WFD develops in airplanes. Standard
inspection techniques cannot be relied on to detect WFD before it
becomes a hazard to flight. We will not grant any extensions of the
compliance time to complete any AD-mandated service bulletin related to
WFD without extensive new data that would substantiate and clearly
warrant such an extension.
Costs of Compliance
We estimate that this proposed AD affects 18 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Full-length modification or Up to 184 Up to $14,720..... Up to $30,360..... Up to $546,480.
repair. work[dash]hours x
$85 per hour =
$15,640.
Inspection...................... 9 work-hours x $85 $0................ $765 per $13,770 per
per hour = $765 inspection cycle. inspection cycle.
per inspection
cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
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
[[Page 21650]]
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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
The Boeing Company: Docket No. FAA-2014-0235; Directorate Identifier
2013-NM-249-AD.
(a) Comments Due Date
We must receive comments by June 2, 2014.
(b) Affected ADs
This AD affects AD 2008-06-23, Amendment 39-15435 (73 FR 14378,
March 18, 2008).
(c) Applicability
This AD applies to The Boeing Company airplanes identified in
paragraphs (c)(1) through (c)(6) of this AD, certificated in any
category, as identified in Boeing Alert Service Bulletin DC8-53A080,
Revision 2, dated September 18, 2013.
(1) The Boeing Company Model DC-8-55 airplanes.
(2) The Boeing Company Model DC-8F-54 and DC-8F-55 airplanes.
(3) The Boeing Company Model DC-8-61, DC-8-62, and DC-8-63
airplanes.
(4) The Boeing Company Model DC-8-61F, DC-8-62F, and DC-8-63F
airplanes.
(5) The Boeing Company Model DC-8-71, DC-8-72, and DC-8-73
airplanes.
(6) The Boeing Company Model DC-8-71F, DC-8-72F, and DC-8-73F
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by multiple reports of cracking of the
upper aft skin panel of the fuselage. An evaluation by the design
approval holder indicates that the upper aft skin panel of the
fuselage is subject to widespread fatigue damage. We are issuing
this AD to detect and correct fatigue cracking of the upper aft skin
panel of the fuselage, which could result in loss of structural
integrity and consequent rapid decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Modification or Repair
Before the accumulation of 45,400 total flight cycles, or within
72 months after the effective date of this AD, whichever occurs
later: Remove any previously installed local repairs and install a
full-length improvement modification with finger doublers or a full-
length repair with finger doublers, as applicable, in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin DC8-53A080, Revision 2, dated September 18, 2013.
Installation of the full-length improvement modification or full-
length repair with finger doublers, in accordance with paragraph (i)
of AD 2008-06-23, Amendment 39-15435 (73 FR 14378, March 18, 2008),
is a method of compliance with the requirements of paragraph (g) of
this AD. Installation of a local repair as specified in paragraph
(i) of AD 2008-06-23, does not comply with the requirements of
paragraph (g) of this AD.
(h) Post-Modification or Post-Repair Repetitive Inspections
After accomplishing the actions required by paragraph (g) of
this AD, at the applicable time and intervals specified in paragraph
(h)(1) or (h)(2) of this AD: Do an external visual inspection or low
frequency eddy current (LFEC) inspection for cracking along all four
edges of the finger doublers, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin DC8-53A080, Revision
2, dated September 18, 2013. Repeat the inspections thereafter at
the applicable time and interval specified in paragraphs (h)(1) or
(h)(2) of this AD. Accomplishment of the applicable repetitive
inspection specified in paragraph (j)(1) or (j)(2)(ii) of AD 2008-
06-23, Amendment 39-15435 (73 FR 14378, March 18, 2008), is a method
of compliance with the applicable inspection requirements of
paragraph (h) of this AD.
(1) For an external visual inspection, within 30,000 flight
cycles after doing the actions specified in paragraph (g) of this
AD. Repeat the external visual inspection thereafter at intervals
not to exceed 5,000 flight cycles.
(2) For an LFEC inspection, within 15,000 flight cycles after
doing the actions specified in paragraph (g) of this AD. Repeat the
LFEC inspection thereafter at intervals not to exceed 10,000 flight
cycles.
(i) Cracking Repair
If any cracking is found during any inspection required by
paragraph (h) of this AD: Before further flight, repair using a
method approved in accordance with the procedures specified in
paragraph (k) of this AD.
(j) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using Boeing Alert Service
Bulletin DC8-53A080, dated June 22, 2004; or Boeing Alert Service
Bulletin DC8-53A080, Revision 1, dated May 3, 2013. Boeing Alert
Service Bulletin DC8-53A080, dated June 22, 2004, was previously
incorporated by reference in AD 2008-06-23, Amendment 39-15435 (73
FR 14378, March 18, 2008). Boeing Alert Service Bulletin DC8-53A080,
Revision 1, dated May 3, 2013, is not incorporated by reference in
this AD.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles 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. In accordance
with 14 CFR 39.19, send your request to your principal inspector or
local Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (l)(1) of this AD.
Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(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 the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that 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.
(l) Related Information
(1) For more information about this AD, contact Chandraduth
Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los
Angeles Aircraft Certification Office (ACO), 3960 Paramount Blvd.,
Suite 100, Lakewood, CA 90712-4137, phone: 562-627-5239; fax: 562-
627-5210; email: [email protected].
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001;
telephone 206-544-5000, extension 2; fax 206-766-5683; Internet
https://www.myboeingfleet.com. You may view this service information
at the FAA, Transport
[[Page 21651]]
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
Issued in Renton, Washington, on April 8, 2014.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-08726 Filed 4-16-14; 8:45 am]
BILLING CODE 4910-13-P