[Federal Register Volume 78, Number 128 (Wednesday, July 3, 2013)]
[Proposed Rules]
[Pages 40050-40053]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-15948]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0540; Directorate Identifier 2012-NM-185-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 an existing airworthiness directive
(AD) that applies to certain The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, and 747SP series airplanes. The existing AD
currently requires repetitive inspections for wear damage and cracks of
the fuselage skin in the interface area of the vertical stabilizer seal
and fuselage skin, a detailed inspection for wear damage and cracks of
the surface of any skin repair doubler in the area, and corrective
actions if necessary. For airplanes on which the fuselage skin has been
blended to remove wear damage, the existing AD also requires repetitive
external detailed inspections or high frequency eddy current
inspections for cracks of the blended area of the fuselage skin, and
corrective actions if necessary. Since we issued that AD, we have
received a report of wear through the fuselage skin that occurred
sooner than the repetitive inspection interval specified in the
existing AD. This proposed AD would reduce the repetitive inspection
interval and change certain corrective actions. We are proposing this
AD to detect and correct wear damage and cracks of the fuselage skin in
the interface area of the vertical stabilizer seal and fuselage skin in
sections 46 and 48, which could cause in-flight depressurization of the
airplane.
DATES: We must receive comments on this proposed AD by August 19, 2013.
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 AD, contact Boeing
Commercial Airplanes, Attention: Data & Services Management, P. O. Box
3707, MC 2H-65, Seattle, WA 98124-2207; phone: 206-544-5000, extension
1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may
review copies of the 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: Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; 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-2013-0540;
Directorate Identifier 2012-NM-185-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 June 19, 2009, we issued AD 2009-14-02, Amendment 39-15951 (74
FR 30919, June 29, 2009), on the products listed above, which
superseded AD 2002-26-15, Amendment 39-13003 (68 FR 476, January 6,
2003). AD 2009-14-02 requires repetitive inspections for wear damage
and cracks of the fuselage skin in the interface area of the vertical
stabilizer seal and fuselage skin, a detailed inspection for wear
damage and cracks of the surface of any skin repair doubler in the
area, and corrective actions if necessary. For airplanes on which the
fuselage skin has been blended to remove wear damage, AD 2009-14-02
also requires repetitive external detailed inspections or high
frequency eddy current inspections for cracks of the blended area of
the fuselage skin, and corrective actions if necessary. AD 2009-14-02
resulted from reports of skin wear damage on airplanes with fewer than
8,000 total flight cycles. Additionally, there were three reports of
skin wear damage on airplanes on which Boeing Material Specifications
(BMS) 10-86 Teflon-filled coating was applied (terminating action per
AD 2002-26-15). We issued AD 2009-14-02 to detect and correct wear
damage and cracks of the fuselage skin in the interface area of the
vertical stabilizer seal and fuselage skin in sections 46 and 48, which
could cause in-flight depressurization of the airplane.
Actions Since Existing AD 2009-14-02, Amendment 39-15951 (74 FR 30919,
June 29, 2009) Was Issued
Since we issued AD 2009-14-02, Amendment 39-15951 (74 FR 30919,
June 29, 2009), we have received a report of wear through the fuselage
skin between body station (STA) 2598 and STA 2638, stringers S-2L to S-
3L. The wear developed in less than 3,657 flight hours since the
previous inspection, which was less than the repetitive
[[Page 40051]]
inspection interval specified in AD 2009-14-02. The wear occurred
through both the Teflon filled coating and the full thickness of the
0.050-inch-thick skin to create a hole approximately 16 inches in
length.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 747-53A2478, Revision 3,
dated October 17, 2011. For information on the procedures and
compliance times, see this service information at http://www.regulations.gov by searching for Docket No. FAA-2013-0540.
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 2009-14-02, Amendment 39-15951 (74 FR 30919, June
29, 2009), this proposed AD would retain certain requirements of AD
2009-14-02. Those requirements are referenced in the service
information identified previously, which, in turn, is referenced in
paragraphs (g) and (h) of this proposed AD. This proposed AD would
reduce the repetitive inspection interval and add rub strip
installation for airplanes with wear or blend that exceeds structural
repair manual limits. This proposed AD would require accomplishing the
actions specified in the service information described previously,
except as discussed under ``Differences Between the Proposed AD and the
Service Information.''
The phrase ``corrective actions'' is used in this proposed AD.
``Corrective actions'' are actions that correct or address any
condition found. Corrective actions in an AD could include, for
example, repairs.
We have also clarified the applicability in paragraph (c) of AD
2009-14-02, Amendment 39-15951 (74 FR 30919, June 29, 2009), which
specifies ``Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B,
747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and
747SP series airplanes, certificated in any category, as identified in
Boeing Alert Service Bulletin 747-53A2478, Revision 1, dated March 27,
2008.'' The effectivity of that service information lists all Model
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300,
747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes.
Therefore, the applicability of this proposed AD specifies ``all The
Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-
200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP
series airplanes, certificated in any category.''
Differences Between the Proposed AD and the Service Information
Boeing Alert Service Bulletin 747-53A2478, Revision 3, dated
October 17, 2011, specifies certain optional economic-based actions.
This proposed AD would not require those actions.
Costs of Compliance
We estimate that this proposed AD affects 917 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspection [retained actions from 12 work-hours x $85 $0 $1,020............. $935,340.
existing AD 2009-14-02, per hour = $1,020.
Amendment 39 15951 (74 FR 30919,
June 29, 2009)].
Inspection and application of BMS 8 work-hours x $85 $0 $680 per inspection $623,560 per
10-86 Teflon-filled coating per hour = $680 cycle. inspection cycles.
[retained actions from existing per inspection
AD 2009-14-02, Amendment 39- cycle.
15951 (74 FR 30919, June 29,
2009)].
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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 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.
[[Page 40052]]
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)
2009-14-02, Amendment 39-15951 (74 FR 30919, June 29, 2009), and adding
the following new AD:
The Boeing Company: Docket No. FAA-2013-0540; Directorate Identifier
2012-NM-185-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by August 19,
2013.
(b) Affected ADs
This AD supersedes AD 2009-14-02, Amendment 39-15951 (74 FR
30919, June 29, 2009).
(c) Applicability
This AD applies to all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, and 747SP series airplanes, certificated
in any category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted a report of wear through the fuselage skin
that occurred sooner than the previous repetitive inspection
interval. We are issuing this AD to detect and correct wear damage
and cracks of the fuselage skin in the interface area of the
vertical stabilizer seal and fuselage skin in sections 46 and 48,
which could cause in-flight depressurization of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Detailed Inspection
At the applicable compliance time specified in paragraph 1.E.,
''Compliance,'' of Boeing Alert Service Bulletin 747-53A2478,
Revision 3, dated October 17, 2011 (the effective date of AD 2009-
14-02, Amendment 39-15951 (74 FR 30919, June 29, 2009) is August 3,
2009), except as specified in paragraph (j)(1) of this AD: Do a
detailed inspection of the fuselage skin and any skin repair doubler
surface for wear damage and cracking at the vertical stabilizer seal
interface, apply Boeing Material Specifications (BMS) 10-86 Teflon-
filled coating, and do all applicable corrective actions, except as
specified in paragraph (j)(2) of this AD, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2478, Revision 3, dated October 17, 2011. Do all applicable
corrective actions at the applicable compliance time specified in
paragraph 1.E., ''Compliance,'' of Boeing Alert Service Bulletin
747-53A2478, Revision 3, dated October 17, 2011. Repeat the detailed
inspection thereafter at intervals not to exceed the applicable
repetitive interval specified in paragraph 1.E., ''Compliance,'' of
Boeing Alert Service Bulletin 747-53A2478, Revision 3, dated October
17, 2011, except as specified in paragraph (j)(2) of this AD. The
effective date of AD 2009-14-02, Amendment 39-15951 (74 FR 30919,
June 29, 2009) is August 3, 2009.
(h) Repetitive High Frequency Eddy Current (HFEC) Inspections
For airplanes on which the skin is blended forward of station
2360 without external reinforcement: At the applicable compliance
time specified in Table 4 in paragraph 1.E., ''Compliance,'' of
Boeing Alert Service Bulletin 747-53A2478, Revision 3, dated October
17, 2011, do an external surface HFEC inspection of the blended area
of the fuselage skin and the surface of any repair doubler for
cracks, apply BMS 10-86 Teflon-filled coating, and do all applicable
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2478, Revision
3, dated October 17, 2011. Do all applicable corrective actions at
the applicable compliance time specified in paragraph 1.E.,
''Compliance,'' of Boeing Alert Service Bulletin 747-53A2478,
Revision 3, dated October 17, 2011. Repeat the HFEC inspection
thereafter at intervals not to exceed the compliance time specified
in paragraph 1.E., ''Compliance,'' of Boeing Alert Service Bulletin
747-53A2478, Revision 3, dated October 17, 2011. The effective date
of AD 2009-14-02, Amendment 39-15951 (74 FR 30919, June 29, 2009) is
August 3, 2009.
(i) Optional Terminating Action
Installation of CRES rub strips in accordance with Boeing
Service Bulletin 747-53-2721, Revision 2, dated March 17, 2011,
except as specified in paragraph (j)(3) of this AD, is terminating
action for the inspections specified in paragraphs (g) and (h) of
this AD at the locations of the CRES rub strip installations only.
(j) Exceptions to Service Information
(1) Where Boeing Alert Service Bulletin 747-53A2478, Revision 3,
dated October 17, 2011, specifies a compliance time after the
``Revision 3 date of this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(2) Part 3 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2478, Revision 3, dated October 17, 2011, is
not a requirement of this AD.
(3) Where Boeing Service Bulletin 747-53-2721, Revision 2, dated
March 17, 2011, specifies to contact Boeing for a modification or
for instructions: Before further flight, contact the FAA for
instructions using a method approved in accordance with the
procedures specified in paragraph (l) of this AD, and accomplish
those instructions.
(k) Credit for Previous Actions
(1) This paragraph provides credit for the actions specified in
paragraph (g) of this AD, if the corresponding actions were
performed before the effective date of this AD using Boeing Alert
Service Bulletin 747-53A2478, Revision 1, dated March 27, 2008; or
Boeing Service Bulletin 747-53A2478, Revision 2, dated July 15,
2010; which are not incorporated by reference in this AD. As of the
effective date of this AD, only Boeing Alert Service Bulletin 747-
53A2478, Revision 3, dated October 17, 2011, can be used.
(2) This paragraph provides credit for the actions specified in
paragraph (i) of this AD, if the corresponding actions were
performed before the effective date of this AD using Boeing Service
Bulletin 747-53-2721, dated May 28, 2009; or Revision 1, dated June
24, 2010; which are not incorporated by reference in this AD.
(l) 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 the Related Information
section 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) Installation of CRES rub strips approved as AMOCs for AD
2009-14-02, Amendment 39-15951 (74 FR 30919, June 29, 2009), are
approved as AMOCs for this AD.
(m) Related Information
(1) For more information about this AD, contact Bill Ashforth,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6432; fax: 425-917-6590; email:
[email protected].
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65,
[[Page 40053]]
Seattle, WA 98124-2207; phone: 206-544-5000, extension 1; fax: 206-
766-5680; Internet: https://www.myboeingfleet.com. You may review
copies of the 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 June 14, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-15948 Filed 7-2-13; 8:45 am]
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