[Federal Register Volume 78, Number 235 (Friday, December 6, 2013)]
[Proposed Rules]
[Pages 73457-73460]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-29128]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-1023; Directorate Identifier 2013-NM-042-AD]
RIN 2120-AA64
Airworthiness Directives; the Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede airworthiness directive (AD) 84-19-01,
which applies to certain The Boeing Company Model 747-100, 747-200B,
747-200F series airplanes. AD 84-19-01 requires repetitive inspections
for cracking of certain tension ties, and repair and certain
modifications if necessary. Since we issued AD 84-19-01, the upper deck
tension ties have been identified as structure that is susceptible to
widespread fatigue damage (WFD), and additional action is necessary for
certain airplanes to adequately address the identified unsafe condition
on the fleet. This proposed AD is intended to complete certain mandated
programs intended to support the airplane reaching its limit of
validity (LOV) of the engineering data that support the established
structural maintenance program. For certain airplanes, this proposed AD
would add
[[Page 73458]]
inspections for cracking of the tension tie at body station (BS) 760 or
780, corrective action if necessary, and eventual modification of the
tension ties. For all airplanes, this proposed AD would require
repetitive post-modification inspections for cracking of the tension
tie at BS 760 or 780, and corrective action if necessary. We are
proposing this AD to detect and correct tension tie cracking, which
could eventually result in in-flight depressurization of the airplane
and the inability to withstand current regulatory failsafe loads.
DATES: We must receive comments on this proposed AD by January 21,
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,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; 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; 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: Roger Caldwell, Aerospace Engineer,
Denver Aircraft Certification Office, FAA, 26805 East 68th Avenue,
Denver, CO 80249; phone: 303-342-1086; fax: 303-342-1088; email:
[email protected].
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-2013-1023;
Directorate Identifier 2013-NM-042-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
On September 4, 1984, we issued AD 84-19-01, Amendment 39-4913 (49
FR 35365, September 17, 1984), for certain Boeing Model 747-100, 747-
200B, and 747-200F series airplanes. AD 84-19-01 requires repetitive
inspections for cracking of certain tension ties, and repair and
certain modifications if necessary. AD 84-19-01 resulted from a crack
in the body station 760 tension tie as a result of bending due to cabin
pressurization. We issued AD 84-19-01 to detect and correct tension tie
cracking, which could eventually result in in-flight depressurization
of the airplane and the inability to withstand current regulatory
failsafe loads.
Actions Since AD 84-19-01, Amendment 39-4913 (49 FR 35365, September
17, 1984), Was Issued
As described in FAA Advisory Circular 120-104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs
have been developed to support initiatives that will ensure the
continued airworthiness of aging airplane structure. The last element
of those initiatives is the requirement to establish a limit of
validity (LOV) of the engineering data that support the structural
maintenance program under 14 CFR 26.21. This proposed AD is the result
of an assessment of the previously established programs by design
approval holder during the process of establishing the LOV for Model
747-100, 747-200B, and 747-200F series airplanes. The actions specified
in this proposed AD are necessary to complete certain programs to
ensure the continued airworthiness of aging airplane structure and to
support an airplane reaching its LOV.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 747-53A2088, Revision 4,
dated January 11, 2013. For information on the procedures and
compliance times, see this service information at http://www.regulations.gov by searching for Docket No. FAA-2013-1023.
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
Although this proposed AD does not explicitly restate the
requirements of AD 84-19-01, Amendment 39-4913 (49 FR 35365, September
17, 1984), this proposed AD would retain all of the requirements of AD
84-19-01. Those requirements are referenced in the service information
identified previously, which, in turn, is referenced in paragraphs (g)
and (i) of this proposed AD. Paragraph (h) of this proposed AD would
mandate the previously optional modification of the tension ties. This
proposed AD would require accomplishing the actions specified in the
service information identified previously, except as discussed under
``Differences Between the Proposed AD and the Service Information.''
This proposed AD would require that requests for approval of
alternative methods of compliance (AMOCs) be directed to the Seattle
Aircraft Certification Office.
The phrase ``corrective actions'' might be used in this proposed
AD. ``Corrective actions'' correct or address any condition found.
Corrective actions in an AD could include, for example, repairs.
Differences Between the Proposed AD and the Service Information
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:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and
[[Page 73459]]
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 24 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
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Number of U.S.
Action Labor cost Parts cost Cost per product airplanes Cost on U.S. operators
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Inspection.......................... 3 work-hours x $85 per hour $0 $255 per inspection Up to 24............ $6,120 per inspection
= $255 per inspection cycle. cycle. cycle.
Modification........................ 32 work-hours x $85 per hour $672 $3,392................ Up to 24............ $81,408.
= $2,720.
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We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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 proposed 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 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),
(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 removing airworthiness directive (AD)
84-19-01, Amendment 39-4913 (49 FR 35365, September 17, 1984), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2013-1023; Directorate Identifier
2013-NM-042-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by January 21,
2014.
(b) Affected ADs
This AD supersedes AD 84-19-01, Amendment 39-4913 (49 FR 35365,
September 17, 1984).
(c) Applicability
This AD applies to The Boeing Company Model 747-100, 747-200B,
and 747-200F series airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin 747-53A2088, Revision 4,
dated January 11, 2013.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report of cracking in the body station
(BS) 760 tension tie as a result of bending due to cabin
pressurization. We are issuing this AD to detect and correct tension
tie cracking, which could result in in-flight depressurization of
the airplane and the inability to withstand current regulatory
failsafe loads.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections: Unmodified Airplanes
For airplanes that have not been modified as specified in Boeing
Service Bulletin 747-53-2088: At the applicable time specified in
Table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2088, Revision 4, dated January 11, 2013, except as
required by paragraph (j)(1) of this AD, do detailed (close visual)
and surface high frequency eddy current inspections for cracking of
the tension tie at BS 760 or 780, as applicable, and do all
applicable corrective actions, in accordance with Part I of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2088, Revision 4, dated January 11, 2013, except as required by
paragraph (j)(2) of this AD. Do all applicable corrective actions
before further flight. Repeat the inspections thereafter at the
applicable time specified in Table 1 or Table 2 of paragraph 1.E.,
``Compliance,'' of Boeing
[[Page 73460]]
Alert Service Bulletin 747-53A2088, Revision 4, dated January 11,
2013, until accomplishment of the requirements of paragraph (h) of
this AD.
(h) Modification
For airplanes that have not been modified as specified in Boeing
Service Bulletin 747-53-2088: At the applicable time specified in
Table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2088, Revision 4, dated January 11, 2013, except as
required by paragraph (j)(1) of this AD, modify the tension ties,
including doing an open-hole high frequency eddy current inspection
for cracks, as applicable, and all applicable corrective actions, in
accordance with Part III of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2088, Revision 4, dated January
11, 2013, except as required by paragraph (j)(2) of this AD. All
applicable corrective actions must be done before further flight.
This modification terminates the repetitive inspection requirements
of paragraph (g) of this AD.
(i) Post-Modification Repetitive Inspections
For airplanes that have been modified as specified in Boeing
Service Bulletin 747-53-2088: At the applicable time in Table 2 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2088, Revision 4, dated January 11, 2013, do a detailed
inspection for cracking of the tension tie at BS 760 or 780, and do
all applicable corrective actions, in accordance with Part I of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2088, Revision 4, dated January 11, 2013, except as required by
paragraph (j)(2) of this AD. Do all applicable corrective actions
before further flight. Repeat the inspection thereafter at the
applicable time in Table 2 specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2088,
Revision 4, dated January 11, 2013. Boeing Alert Service Bulletin
747-53A2088, Revision 4, dated January 11, 2013, notes that
additional post-modification inspections are specified in Boeing
Service Bulletin 747-53A2502; those post-modification inspections
are required by AD 2006-01-07, Amendment 39-14446 (71 FR 1947,
January 12, 2006).
(j) Exceptions to Service Information Specifications
(1) Where Boeing Alert Service Bulletin 747-53A2088, Revision 4,
dated January 11, 2013, specifies a compliance time ``after the
Revision 4 date of this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(2) Where Boeing Alert Service Bulletin 747-53A2088, Revision 4,
dated January 11, 2013, specifies to contact Boeing for appropriate
action: Before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (m) of this
AD.
(k) Credit for Previous Actions
This paragraph provides credit for the actions specified in this
AD, if those actions were performed before the effective date of
this AD using Boeing Alert Service Bulletin 747-53A2088, Revision 3,
dated September 8, 1994.
(l) Special Flight Permit
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(m) Alternative Methods of Compliance (AMOCs)
(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. 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 (n)(2) 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, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved for AD 84-19-01, Amendment 39-4913 (49 FR
35365, September 17, 1984), are approved as AMOCs for the
corresponding requirements of paragraph (g) (the retained detailed
inspections) and paragraph (i) of this AD, but not as AMOCs for the
high frequency eddy current inspections required by paragraph (g) of
this AD.
(n) Related Information
(1) For more information about this AD, contact Roger Caldwell,
Aerospace Engineer, Denver Aircraft Certification Office, FAA, 26805
East 68th Avenue, Denver, CO 80249; phone: 303-342-1086; fax: 303-
342-1088; email: [email protected].
(2) For information about AMOCs, contact Nathan Weigand,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6428; fax: 425-917-6590; email:
[email protected].
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; 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.
Issued in Renton, Washington, on November 29, 2013.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-29128 Filed 12-5-13; 8:45 am]
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