[Federal Register Volume 82, Number 125 (Friday, June 30, 2017)]
[Proposed Rules]
[Pages 29795-29798]
[FR Doc No: 2017-13780]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0627; Directorate Identifier 2017-NM-037-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Airbus Model A330-200 Freighter, -200, and -300 series airplanes; and
Airbus Model A340-200, -300, -500, and -600 series airplanes. This
proposed AD was prompted by a report that the trimmable horizontal
stabilizer actuator (THSA) might not function as intended after failure
of the primary load path. This proposed AD would require repetitive
detailed visual inspections for discrepancies of the THSA upper
attachments and no-back housing. We are proposing this AD to address
the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by August 14, 2017.

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:<PHONE_NUMBER>.
     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 NPRM, contact Airbus
SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45
80; email<EMAIL_ADDRESS>Internet http://www.airbus.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-2017-
0627; 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
Operations office (telephone<PHONE_NUMBER>) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone<PHONE_NUMBER>;
fax<PHONE_NUMBER>.

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-2017-0627; Directorate Identifier 2017-NM-037-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 based on 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

    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2017-0044, dated March 9, 2017 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A330-200 Freighter, -200 and -300 series airplanes; and Airbus Model
A340-200, -300, -500, and -600 series airplanes. The MCAI states:

    The Trimmable Horizontal Stabilizer Actuator (THSA), as
installed on A330 and A340 aeroplanes, was initially designed to
stall when engaging on the upper secondary load path (SLP) after
primary load path (PLP) failure. Such stall triggers system
monitoring detection. New mission profile analysis revealed that in
some cases, the THSA could be operated while engaged on the upper
SLP without stalling [i.e., the THSA might not function as intended
after failure of the primary load path]. The partial engagement of
the SLP at upper attachment level does not trigger any indication to
the flight crew.
    This condition, if not detected and corrected, could lead to
THSA upper attachment failure and consequent disconnection of the
THSA from the aeroplane structure, possibly resulting in loss of
control of the aeroplane.
    For the reasons described above, this [EASA] AD requires
repetitive detailed [visual] inspections (DET) of the upper THSA
attachments parts and the PLP and SLP fuselage attachment points,
and, depending on findings (which include, but are not limited to,
failure of the primary load path), accomplishment of applicable
[additional inspections for discrepancies and] corrective action(s).

    The additional inspections include a detailed visual inspection for
discrepancies of the upper attachment fitting of the airplane and a
detailed visual inspection for discrepancies of the removed THSA.
Corrective actions include repair and replacement of the THSA. You may
examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0627.

Related Service Information Under 1 CFR Part 51

    We reviewed the following Airbus service information:
     Airbus Service Bulletin A330-27-3218, Revision 01, dated
December 5, 2016.
     Airbus Service Bulletin A340-27-4203, Revision 01 dated
December 5, 2016.
     Airbus Service Bulletin A340-27-5067, Revision 01 dated
December 5, 2016.
    The service information describes procedures for detailed visual
inspections for discrepancies of the THSA upper attachments and no-back
housing, additional inspections for discrepancies, and corrective
actions. These documents are distinct since they apply to different
airplane models. This service information is reasonably available
because the interested parties have access to it through their normal
course of business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 102 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
----------------------------------------------------------------------------------------------------------------
Inspection.......................  3 work-hours x $85 per                $0  $255 per inspection         $26,010
                                    hour = $255 per                           cycle.
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed inspection.
We have no way of determining the number of aircraft that might need
this replacement.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement................................  20 work-hours x $85 per hour =             $734,661        $736,361
                                              $1,700.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide
cost estimates for other 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 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):

Airbus: Docket No. FAA-2017-0627; Directorate Identifier 2017-NM-
037-AD.

(a) Comments Due Date

    We must receive comments by August 14, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342
and -343 airplanes; and Airbus Model A340-211, -212, -213, -311, -
312, -313, -541, and -642 airplanes; certificated in any category,
all manufacturer's serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight
Controls.

(e) Reason

    This AD was prompted by a report that the trimmable horizontal
stabilizer actuator (THSA) might not function as intended after
failure of the primary load path. We are issuing this AD to detect
and correct discrepancies of the THSA upper attachments and no-back
housing, which could lead to THSA upper attachment failure and
consequent disconnection of the THSA from the airplane structure,
possibly resulting in loss of control of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified,
unless already done.

(g) Repetitive Detailed Visual Inspections

    Before exceeding the Threshold in Table 1 to paragraph (g) of
this AD, as applicable, or within 3 months after the effective date
of this AD, whichever occurs later; and thereafter at intervals not
to exceed the inspection interval values defined in Table 1 to
paragraph (g) of this AD; accomplish a detailed visual inspection
for discrepancies of the trimmable horizontal stabilizer actuator
(THSA) upper attachments and no-back housing, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-27-3218,
Revision 01, A340-27-4203, Revision 01, or A340-27-5067, Revision
01, all dated December 5, 2016, as applicable. Where the
``Threshold'' column of table 1 to paragraph (g) of this AD
specifies compliance times in ``FH'' (flight hours) or ``FC''
(flight cycles), those compliance times are flight hours or flight
cycles since the first flight of the airplane, or since the last
accomplishment of Airbus Model A330 or A340 Maintenance Review Board
Report task 27.40.00/07, or since the last detailed visual
inspection of the THSA done in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-27-3218, A340-27-4203,
or A340-27-5067, all dated July 1, 2016, as applicable.

   Table 1 to Paragraph (g) of This AD--THSA Upper Attachments/No-Back
                           Housing Inspections
------------------------------------------------------------------------
                              Compliance times  (whichever occurs first,
                               flight hours (FH) or  flight cycles (FC))
     Affected airplanes      -------------------------------------------
                                                     Inspection interval
                                    Threshold          (not to exceed)
------------------------------------------------------------------------
A330, A340-200 and A340-300.  Before 4,000 FH or    4,000 FH or 1,000
                               1,000 FC.             FC.
A340-500 and A340-600.......  Before 4,000 FH or    4,000 FH or 800 FC.
                               800 FC.
------------------------------------------------------------------------

(h) Additional Inspections and Corrective Actions

    (1) If, during any inspection required by paragraph (g) of this
AD, any discrepancy identified in the Accomplishment Instructions of
Airbus Service Bulletin A330-27-3218, Revision 01, A340-27-4203,
Revision 01, or A340-27-5067, Revision 01, all dated December 5,
2016, as applicable, is detected, before further flight, remove the
THSA, and accomplish a detailed visual inspection for discrepancies
of the upper attachment fitting of the airplane and a detailed
visual inspection for discrepancies of the removed THSA, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-27-3218, Revision 01, A340-27-4203, Revision 01, or
A340-27-5067, Revision 01, all dated December 5, 2016, as
applicable. As an alternative to the removed THSA inspections
required by this paragraph, before further flight, replace the THSA
with a serviceable part (as defined in paragraph (i) of this AD).
    (2) If, during any inspection of the upper attachment fitting of
the airplane required by paragraph (h)(1) of this AD, any
discrepancy identified in the Accomplishment Instructions of Airbus
Service Bulletin A330-27-3218, Revision 01, A340-27-4203, Revision
01, or A340-27-5067, Revision 01, all dated December 5, 2016, as
applicable, is detected, before further flight, repair using a
method approved in accordance with the procedures specified in
paragraph (k)(2) of this AD.
    (3) If, during any inspection of the removed THSA required by
paragraph (h)(1) of this AD, no discrepancy specified in the
Accomplishment Instructions of Airbus Service Bulletin A330-27-3218,
Revision 01, A340-27-4203, Revision 01, or A340-27-5067, Revision
01, all dated December 5, 2016, as applicable, is detected, before
further flight, reinstall the THSA, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-27-3218,
Revision 01, A340-27-4203,

Revision 01, or A340-27-5067, Revision 01, all dated December 5,
2016, as applicable.
    (4) If, during any inspection of the removed THSA required by
paragraph (h)(1) of this AD, any discrepancy specified in the
Accomplishment Instructions of Airbus Service Bulletin A330-27-3218,
Revision 01, A340-27-4203, Revision 01, or A340-27-5067, Revision
01, all dated December 5, 2016, as applicable, is detected, before
further flight, replace the THSA with a serviceable part (as defined
in paragraph (i) of this AD), in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-27-3218, Revision 01,
A340-27-4203, Revision 01, or A340-27-5067, Revision 01, all dated
December 5, 2016, as applicable.

(i) Definition of Serviceable THSA

    For the purpose of this AD, a serviceable THSA is a part that
has accumulated less than 4,000 FH or 1,000 FC (for Airbus Model
A330, A340-200, or A340-300 airplanes) or 4,000 FH or 800 FC (for
Airbus Model A340-500 or A340-600 airplanes), whichever occurs first
since the first flight of the airplane, or since the last overhaul
of the THSA, or since the last detailed visual inspection of the
THSA in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A330-27-3218, Revision 01, A340-27-4203, Revision
01, or A340-27-5067, Revision 01, all dated December 5, 2016, as
applicable.

(j) Credit for Previous Actions

    This paragraph provides credit for actions required by
paragraphs (g), (h)(1), (h)(3), and (h)(4) of this AD, if those
actions were performed before the effective date of this AD using
the service information specified in paragraph (j)(1), (j)(2), or
(j)(3) of this AD.
    (1) Airbus Service Bulletin A330-27-3218, Revision 00, dated
July 1, 2016.
    (2) Airbus Service Bulletin A340-27-4203, Revision 00, dated
July 1, 2016.
    (3) Airbus Service Bulletin A340-27-5067, Revision 00, dated
July, 1 2016.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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 International Branch, send it to
attention of the person identified in paragraph (l)(2) of this AD.
Information may be emailed to<EMAIL_ADDRESS>
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.
    (2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by
paragraph (h)(2) of this AD: If any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-044, dated March 9, 2017, for related
information. This MCAI may be found in the AD docket on the Internet
at http://www.regulations.gov by searching for and locating Docket
No. FAA-2017-0627.
    (2) For more information about this AD, contact Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.
    (3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office-EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 45 80; email<EMAIL_ADDRESS>Internet
http://www.airbus.com. You may view this 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<PHONE_NUMBER>.

    Issued in Renton, Washington, on June 22, 2017.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-13780 Filed 6-29-17; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register: January 31, 2008 (Volume 73, Number 21)]
[Proposed Rules]
[Page 5768-5770]
[DOCID:fr31ja08-19]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0107; Directorate Identifier 2007-NM-087-AD]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 747 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Boeing Model 747 airplanes. This proposed AD would require
inspections for scribe lines in affected lap and butt splices, wing-to-
body fairing locations, and external repair and cutout reinforcement
areas; and related investigative and corrective actions if necessary.
This proposed AD results from reports of scribe lines found at lap
joints and butt joints, around external doublers and antennas, and at
locations where external decals had been cut. We are proposing this AD
to detect and correct scribe lines, which can develop into fatigue
cracks in the skin and cause sudden decompression of the airplane.

DATES: We must receive comments on this proposed AD by March 17, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     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, P.O. Box 3707, Seattle, Washington 98124-2207.

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 (telephone<PHONE_NUMBER>) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.

FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6447; fax<PHONE_NUMBER>.

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-2008-0107;
Directorate Identifier 2007-NM-087-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

    We have received a report indicating that scribe lines have been
found by 8 operators on 15 Model 747 airplanes. Scribe lines were found
at lap joints and butt joints, around external doublers and antennas,
and at locations where external decals had been cut. Many of the scribe
lines appear to have been made when sealant was removed as part of
preparation of the airplane for repainting. Although fatigue cracks can
develop in the skin at scribe line locations--and have been found on
some airplane models, no such cracking has been found on Model 747
airplanes. Such fatigue cracks, if not corrected, could grow large and
cause sudden decompression of the airplane.

Related ADs

    This proposed AD is similar to two existing ADs. AD 2006-07-12,
amendment 39-14539 (71 FR 16211, March 31, 2006), applies to all Boeing
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD
2007-19-07, amendment 39-15198 (72 FR 60244, October 24, 2007), applies
to all Boeing Model 757-200, -200PF, and -200CB series airplanes. Those
ADs require inspections to detect scribe lines in the fuselage skin at
certain lap joints, butt joints, external repair doublers, and other
areas; and related investigative/corrective actions if necessary. Those
actions resulted from reports of fuselage skin cracks adjacent to the
skin lap joints on airplanes that had scribe lines.

Relevant Service Information

    We have reviewed Boeing Service Bulletin 747-53A2563, Revision 2,
dated January 3, 2008. The service bulletin describes procedures for
exploratory detailed inspections to detect scribe lines in affected lap
and butt splices, wing-to-body fairing locations, and external repair
and cutout reinforcement areas. The service bulletin specifies removing
paint and sealant from affected areas before the initial exploratory
inspection. The compliance time for the exploratory inspections is
15,000 or 25,000 total flight cycles (depending on the inspection
location), with a grace period between 500 and 1,500 flight cycles
depending on the age of the airplane and the location of the
inspection.
    The service bulletin specifies conditional actions, depending on
the size, depth, and location of the damage. These actions include
performing eddy current or ultrasonic inspections of the scribe lines
to detect cracks, and either repairing scribe lines and cracks or
contacting Boeing for repair instructions.
    The service bulletin specifies repairing scribe lines before
further flight, except when a limited return to service (LRTS) program
for qualifying scribe lines would allow return to service for a limited
period before scribe lines are repaired. The LRTS program includes
repetitive inspections to detect cracks where scribe lines are found.
To

qualify for an LRTS program, scribe lines must meet certain criteria
based on their depth and location. The service bulletin specifies
contacting Boeing for final repair instructions, which would eliminate
the need for the repetitive inspections of the LRTS program. The
repetitive intervals for the LRTS program range from 250 to 10,000
flight cycles, depending on the depth and location of the scribe lines
and the configuration of the airplane.
    The service bulletin notes that certain inspections would not be
required under the following conditions:
     The airplane had never been stripped or repainted.
     The wing-to-body fairings had never been removed.
     The airplane had never been stripped or repainted under
the wing-to-body fairings.
     For each repair, the airplane had never been stripped or
repainted since the repair was installed.
     No sealant had been removed except in accordance with the
specified sealant removal processes as given in Appendix A of the
service bulletin.
    The service bulletin specifies submitting the initial inspection
results to Boeing. The service bulletin also provides procedures for
addressing scribe lines detected before the initial inspection
threshold.

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 below. This proposed AD would also require sending the
results of the exploratory inspections to Boeing.

Difference Between the Proposed AD and 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.

Clarification of Proposed Requirements Beyond Specified Inspection
Areas and Threshold

    Although the service bulletin provides procedures for addressing
scribe lines that are found outside the inspection areas and before the
initial inspection threshold, this proposed AD would not include such
requirements.

Interim Action

    This proposed AD is considered to be interim action. The inspection
reports that would be required by this proposed AD will enable the
manufacturer to obtain better insight into the nature, cause, and
extent of the cracking, and eventually to develop final action to
address the unsafe condition. Once final action has been identified, we
may consider further rulemaking.

Costs of Compliance

    There are about 1,038 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                Number of U.S.-
              Action                       Work hours          Average labor       Cost per  airplane         registered             Fleet cost
                                                               rate per hour                                   airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Exploratory inspections..........  1,020 to 1,140...........             $80  $81,600 to $91,200..........             219  $17,870,400 to $19,972,800.
Report...........................  1........................              80  $80.........................             219  $17,520.
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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:

Boeing: Docket No. FAA-2008-0107; Directorate Identifier 2007-NM-
087-AD.

Comments Due Date

    (a) We must receive comments by March 17, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-
400F, 747SP, and 747SR series airplanes, certificated in any
category; as identified in Boeing Service Bulletin 747-53A2563,
Revision 2, dated January 3, 2008.

Unsafe Condition

    (d) This AD results from reports of scribe lines found at lap
joints and butt joints, around external doublers and antennas, and
at locations where external decals had been cut. We are issuing this
AD to detect and correct scribe lines, which can develop into
fatigue cracks in the skin and cause sudden decompression of the
airplane.

Compliance

    (e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.

Inspection

    (f) At the applicable times specified in paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-53A2563, Revision 2,
dated January 3, 2008, except as provided in paragraph (g) of this
AD, do detailed exploratory inspections for scribe lines of affected
lap and butt splices, wing-to-body fairing locations, and external
repair and cutout reinforcement areas, and do all applicable related
investigative and corrective actions, by accomplishing all actions
specified in the Accomplishment Instructions of the service
bulletin, except as provided by paragraph (h) of this AD.

    Note 1: The inspection exemptions noted in paragraph 1.E. of
Boeing Service Bulletin 747-53A2563, Revision 2, dated January 3,
2008, apply to this AD.

Exceptions to Service Bulletin Specifications

    (g) Where Boeing Service Bulletin 747-53A2563, Revision 2, dated
January 3, 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) Where Boeing Service Bulletin 747-53A2563, Revision 2, dated
January 3, 2008, specifies to contact Boeing for appropriate action,
accomplish applicable actions before further flight using a method
approved in accordance with the procedures specified in paragraph
(k) of this AD.

Report

    (i) At the applicable time specified in paragraph (i)(1) or
(i)(2) of this AD: Submit a report of the findings (both positive
and negative) of the inspections required by paragraph (f)(1) of
this AD. One approved method for reporting is Appendixes B and C as
applicable of Boeing Service Bulletin 747-53A2563, Revision 2, dated
January 3, 2008. Send the report to Boeing Commercial Airplanes,
P.O. Box 3707, Seattle, Washington 98124-2207. The report must
contain, at a minimum, the inspection results, a description of any
discrepancies found, the airplane serial number, and the number of
flight cycles and flight hours on the airplane. Under the provisions
of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office
of Management and Budget (OMB) has approved the information
collection requirements contained in this AD and has assigned OMB
Control Number 2120-0056.
    (1) If the inspection was done after the effective date of this
AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.

Actions Accomplished According to Previous Issue of Service Bulletin

    (j) Actions accomplished before the effective date of this AD
according to Boeing Alert Service Bulletin 747-53A2563, dated March
29, 2007, are considered acceptable for compliance with the
corresponding actions specified in this AD.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with 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 or limited return to service (LRTS) plan
specified in this AD, if the repair or LRTS plan is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. To be approved,
the repair and LRTS plan must meet the certification basis of the
airplane, and the approval must specifically refer to this AD.

    Issued in Renton, Washington, on January 18, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
 [FR Doc. E8-1703 Filed 1-30-08; 8:45 am]

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