[Federal Register Volume 84, Number 37 (Monday, February 25, 2019)]
[Proposed Rules]
[Pages 5960-5968]
[FR Doc No: 2019-02929]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0017; Product Identifier 2018-NM-112-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus SAS 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) 2007-11-
11 and AD 2017-01-11, which apply to all Airbus SAS Model A318 and
Model A319 series airplanes; Model A320-211, -212, -214, -231, -232,
and -233 airplanes; and Model A321 series airplanes. AD 2007-11-11
requires an inspection to determine the serial number of both main
landing gear (MLG) sliding tubes, repetitive inspections for cracking
of the affected MLG sliding tubes and corrective actions if necessary,
and eventual replacement of both MLG shock absorbers. AD 2017-01-11
requires identification of the part number and serial number of the MLG
sliding tubes; inspection of affected chromium plates and sliding tube
axles for damage; and replacement of the sliding tube if necessary.
Since we issued AD 2007-11-11 and AD 2017-01-11, it was determined that
cracks were found in the MLG sliding tubes due to certain manufacturing
defects that might not be identified using the current on-wing
scheduled inspections. This proposed AD would retain certain
requirements of AD 2007-11-11 and AD 2017-01-11. This proposed AD would
also require repetitive inspections of affected MLG sliding tubes for
cracking, replacement of cracked MLG sliding tubes, and eventual
replacement of each affected MLG sliding tube. We are proposing this AD
to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by April 11, 2019.

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--EIAS, Rond-Point Emile Dewoitine No: 2,
31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email<EMAIL_ADDRESS>internet http://www.airbus.com. You may view this referenced service information at the
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA.
For information on the availability of this material at the FAA, call
206-231-3195.

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-2019-
0017; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations (phone 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax<PHONE_NUMBER>.

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-2019-0017;
Product Identifier 2018-NM-112-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

    We issued AD 2007-11-11, Amendment 39-15068 (72 FR 29241, May 25,
2007) (``AD 2007-11-11''), for all Model A318 and Model A319 series
airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes;
and Model A321 series airplanes. AD 2007-11-11 requires a one-time
inspection to determine the serial number of both MLG sliding tubes,
repetitive detailed inspections for cracking of the affected MLG
sliding tubes and corrective actions if necessary, and eventual
replacement of both MLG shock absorbers, which terminates the
repetitive inspection requirements. AD 2007-11-11 resulted from a
determination that inspections and mandatory replacement of the MLG
shock absorbers are necessary. We issued AD 2007-11-11 to address
cracking in an MLG sliding tube, which could result in failure of the
sliding tube, loss of one axle, and consequent reduced controllability
of the airplane.
    We also issued AD 2017-01-11, Amendment 39-18778 (82 FR 5362,
January 18, 2017) (``AD 2017-01-11''), for all Model A318 and Model
A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233
airplanes; and Model A321 series airplanes. AD 2017-01-11 requires
identification of the part number and serial number of the MLG sliding
tubes; inspection of affected chromium plates and sliding tube axles
for damage; and replacement of the sliding tube if necessary. AD 2017-
01-11 resulted from a report of a rupture of an MLG sliding tube axle.
We issued AD 2017-01-11 to address cracks in the axle and (partial)
detachment of the axle and wheel from the sliding tube, which could
result in failure of an MLG.

Actions Since AD 2007-11-11 and AD 2017-01-11 Were Issued

    Since AD 2007-11-11 and AD 2017-01-11 were issued, during MLG
overhaul, cracks were found in the lower slave link bracket lug holes
on two MLG sliding tubes. Subsequent investigations determined that
these cracks may have developed due to burrs, which could have been
present since manufacture, and it was determined that cracks in the
affected sliding tubes may not be found during the existing on-wing
scheduled inspections.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2018-0135, dated June 26, 2018 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for all Airbus SAS Model A318 and A319 series
airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and
-232 airplanes. The MCAI states:

    Cracks were reported on [main landing gear] MLG sliding tubes
and the investigations determined metallic inclusion during
production and abnormal grinding operation during overhaul as cause
of these cracks. Prompted by these reports, respectively, [Direction
Generale de l'Aviation Civile] DGAC France issued [French] AD F-
2005-115 (EASA approval 2005-6032) [which corresponds to FAA AD
2007-11-11] and EASA issued AD 2014-0058 [which corresponds to FAA
AD 2017-01-11], both requiring inspections and replacement of
certain MLG sliding tubes.
    More recently, during overhaul, cracks were found in the lower
slave link bracket lug holes on two MLG sliding tubes. Subsequent
investigations determined that these cracks may have developed due
to burrs, which could have been present since manufacture. Based on
the fact that the sliding tube is certified as a safe life part,
this is considered to be a non-compliance with the requirements of
[Joint Aviation Requirements] JAR 25.571(c). Cracks in the affected
sliding tubes may not be found during the existing on-wing scheduled
inspections.
    This condition, if not detected and corrected, could lead to
sliding tube failure, possibly resulting in MLG collapse, damage to
the aeroplane and injury to occupants.
    Prompted by these findings, Safran Landing Systems, the MLG
manufacturer (formerly Messier-Dowty, Messier-Bugatti-Dowty, and
hereafter referred to as ``Safran'' in this AD), introduced
additional quality steps to eliminate burrs in the manufacturing
process. To address this potential unsafe condition on delivered MLG
sliding tubes, Airbus issued SB [service bulletin] A320-32-1441,
providing instructions for on-wing repetitive inspections, and
Safran issued SB 200-32-321 and SB 201-32-68, as applicable to MLG
configuration, providing instructions for inspection in shop.
    For the reason described above, this [EASA] AD partially retains
the requirements of DGAC France AD F-2005-115 (EASA approval 2005-
6032) and EASA AD 2014-0058, which are superseded, requires
repetitive inspections of the affected MLG sliding tubes [for
cracking] and, depending on findings, accomplishment of applicable
corrective action(s) [replacement of a cracked MLG sliding tube with
a serviceable MLG sliding tube]. This [EASA] AD also defines
criteria for installation on an aeroplane of an affected MLG sliding
tube.

    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-2019-
0017.

Explanation of Change to Restated Text in Paragraph (g) of This
Proposed AD

    Paragraph (g) of this proposed AD is a restatement of paragraph (i)
of AD 2007-11-11. We have revised the restated text to remove the
reference to Airbus A318/A319/A320/A321 Aircraft Maintenance Manual
Chapter 32-11-13, page block 401. Instead, we have added Note 1 to
paragraph (g) of this proposed AD to specify that guidance on the
replacement specified in paragraph (g) of this proposed AD can be found
in Airbus A318/A319/A320/A321 Aircraft Maintenance Manual Chapter 32-
11-13, page block 401.

Model A320-216 Airplanes

    The Airbus SAS Model A320-216 was U.S. type certificated on
December 19, 2016. Before that date, any EASA ADs that affected Model
A320-216 airplanes were included on the Required Airworthiness Actions
List (RAAL). One or more Model A320-216 airplanes have subsequently
been placed on the U.S. Register, and will now be included in FAA AD
actions. For Model A320-216 airplanes, the requirements that correspond
to AD 2007-11-11 and AD 2017-01-11 were mandated by the MCAI via the
RAAL. Although that RAAL requirement is still in effect, for continuity
and clarity we have identified Model A320-216 airplanes in paragraph
(c) of this AD; the restated requirements of paragraphs (g) through (m)
in this proposed AD would therefore apply to those airplanes.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Service Bulletin A320-32-1441, Revision 01, dated December
14, 2017. The service information describes procedures for inspections
of the MLG sliding tubes for cracking and corrective actions (which
includes replacing the MLG sliding tubes).
     Service Bulletin A320-32A1273, Revision 02, including
Appendix 01, dated May 26, 2005. The service information specifies the
serial numbers of the MLG sliding tubes that must be replaced.
    Safran has issued the following service information. These
documents are distinct since they apply to different airplane models.
     Service Bulletin 200-32-321, Revision 2, dated October 3,
2017; and Service Bulletin 201-32-68, Revision 2, dated October 3,
2017. These documents specify the part numbers and serial numbers of
the affected MLG sliding tubes. These documents are distinct

since they apply to different airplane models.
     Service Bulletin 200-32-286, Revision 3, dated October 3,
2008; and Service Bulletin 201-32-43, Revision 3, dated October 3,
2008. These documents specify the part numbers and serial numbers of
the affected MLG shock absorbers. These documents are distinct since
they apply to different airplane models.
    This proposed AD would also require Airbus Service Bulletin A320-
32-1416, including Appendix 01, dated March 10, 2014, which the
Director of the Federal Register approved for incorporation by
reference as of February 22, 2017 (82 FR 5362, January 18, 2017).
    The 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

    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 the relevant information and determined the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.

Proposed Requirements of This NPRM

    This proposed AD would retain certain requirements of AD 2007-11-11
and AD 2017-01-11. This proposed AD would also require repetitive
inspections of affected MLG sliding tubes for cracking, replacing
cracked MLG sliding tubes with serviceable MLG sliding tubes, and
eventual replacement of each affected MLG sliding tube with a MLG
sliding tube that is not affected, which is terminating action for the
repetitive inspections.

Costs of Compliance

    We estimate that this proposed AD affects 1,186 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:

                                      Estimated Costs for Required Actions
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                                                                                Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
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Retained actions from AD 2007-11- 8 work-hours x $85  Up to $45,310.....  Up to $45,990.....  Up to $13,659,030
 11 (297 airplanes) \[*]\.         per hour = $680.                                            \[*]\.
Retained actions from AD 2017-01- 18 work-hours x     $0................  $1,530............  $1,814,580.
 11.                               $85 per hour =
                                   $1,530.
New proposed actions............  13 work-hours x     $0 [**]...........  $1,105............  $1,310,530.
                                   $85 per hour =
                                   $1,105.
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* Operators should note that, although all U.S.-registered airplanes are subject to the requirements of AD 2007-
  11-11, there are only 297 possible affected MLG sliding tubes in the worldwide fleet. We have no way of
  knowing how many affected MLG sliding tubes, if any, are installed in U.S.-registered airplanes.
** We have received no definitive data for the parts costs for the replacements.

    We estimate the following costs to do any necessary on-condition
action that would be required based on the results of any required
actions. We have no way of determining the number of aircraft that
might need this on-condition action:

                 Estimated Costs of On-Condition Action
------------------------------------------------------------------------
                                                             Cost per
               Labor cost                   Parts cost        product
------------------------------------------------------------------------
6 work-hours x $85 per hour = $510......        $0 \[*]\            $510
------------------------------------------------------------------------
* We have received no definitive data for the parts costs for the on-
  condition actions.

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.
    This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.

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:
0
a. Removing Airworthiness Directive (AD) 2007-11-11, Amendment 39-15068
(72 FR 29241, May 25, 2007); and AD 2017-01-11, Amendment 39-18778 (82
FR 5362, January 18, 2017); and
0
b. Adding the following new AD:

Airbus SAS: Docket No. FAA-2019-0017; Product Identifier 2018-NM-
112-AD.

(a) Comments Due Date

    We must receive comments by April 11, 2019.

(b) Affected ADs

    This AD replaces the following ADs.
    (1) AD 2007-11-11, Amendment 39-15068 (72 FR 29241, May 25,
2007) (``AD 2007-11-11'').
    (2) AD 2017-01-11, Amendment 39-18778 (82 FR 5362, January 18,
2017) (``AD 2017-01-11'').

(c) Applicability

    This AD applies to the Airbus SAS airplanes identified in
paragraphs (c)(1) through (c)(4) of this AD, certificated in any
category, all manufacturer serial numbers.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
    (3) Model A320-211, -212, -214, -216, -231, -232, and -233
airplanes.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing
gear.

(e) Reason

    This AD was prompted by a determination that cracks were found
in the main landing gear (MLG) sliding tubes due to certain
manufacturing defects that might not be identified using the current
on-wing scheduled inspections. We are issuing this AD to address
cracking in an MLG sliding tube, which could lead to failure of an
MLG sliding tube resulting in MLG collapse, damage to the airplane,
and injury to passengers.

(f) Compliance

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

(g) Retained Replacement of AD 2007-11-11, With Updated References to
Service Information and Specific Delegation Approval Language

    This paragraph restates the requirements of paragraph (i) of AD
2007-11-11, with updated references to service information and
specific delegation approval language. Within 41 months after June
29, 2007 (the effective date of AD 2007-11-11), replace all MLG
shock absorbers equipped with sliding tubes having serial numbers
listed in Airbus All Operators Telex (AOT) A320-32A1273, Revision
01, dated May 6, 2004; or the Accomplishment Instructions of Airbus
Service Bulletin A320-32A1273, Revision 02, including Appendix 01,
dated May 26, 2005; with new or serviceable MLG shock absorbers
equipped with sliding tubes having serial numbers not listed in
Airbus AOT A320-32A1273, Revision 01, dated May 6, 2004; or the
Accomplishment Instructions of Airbus Service Bulletin A320-32A1273,
Revision 02, including Appendix 01, dated May 26, 2005; using a
method approved by the Manager, International Section, Transport
Standards Branch, FAA; or the European Aviation Safety Agency
(EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If
approved by the DOA, the approval must include the DOA-authorized
signature. As of June 29, 2007, only Airbus Service Bulletin A320-
32A1273, Revision 02, including Appendix 01, dated May 26, 2005, may
be used to determine the affected sliding tubes.

    Note 1 to paragraph (g) of this AD:  Guidance on the replacement
specified in paragraph (g) of this AD can be found in Airbus A318/
A319/A320/A321 Aircraft Maintenance Manual Chapter 32-11-13, page
block 401.

(h) Retained MLG Sliding Tube Part Number and Serial Number
Identification of AD 2017-01-11, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD
2017-01-11, with no changes. Within three months after February 22,
2017 (the effective date of AD 2017-01-11): Do an inspection to
identify the part number and serial number of the MLG sliding tubes
installed on the airplane. A review of airplane maintenance records
is acceptable in lieu of this inspection if the part number and
serial number of the MLG sliding tubes can be conclusively
determined from that review.

(i) Retained Identification of Airplanes of AD 2017-01-11, With No
Changes

    This paragraph restates the identification specified in
paragraph (h) of AD 2017-01-11, with no changes. An airplane with a
manufacturer serial number (MSN) not listed in figure 1 to paragraph
(i) of this AD is not affected by the requirements of paragraph (j)
of this AD, provided it can be determined that no MLG sliding tube
having a part number and serial number listed in table 1 to
paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD
has been installed on that airplane since first flight of the
airplane.

[GRAPHIC] [TIFF OMITTED] TP25FE19.000

[GRAPHIC] [TIFF OMITTED] TP25FE19.001

[GRAPHIC] [TIFF OMITTED] TP25FE19.002

(j) Retained Inspections of AD 2017-01-11, With No Changes

    This paragraph restates the requirements of paragraph (i) of AD
2017-01-11, with no changes. For each MLG sliding tube identified as
required by paragraph (h) of this AD, having a part number and
serial number listed in table 1 to paragraphs (i), (j), (l)(1),
(l)(2), (m)(1), and (m)(2) of this AD: Within 3 months after
February 22, 2017 (the effective date of AD 2017-01-11) inspect
affected MLG axles and brake flanges by doing a detailed visual
inspection of the chromium plates for damage, and a Barkhausen noise
inspection of the sliding tube axles for damage, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1416, including Appendix 01, dated March 10, 2014. For Model A318
series airplanes, use the procedures specified for Model A319 series
airplanes in Airbus Service Bulletin A320-32-1416, including
Appendix 01, dated March 10, 2014.

(k) Retained Corrective Action of AD 2017-01-11, With No Changes

    This paragraph restates the requirements of paragraph (j) of AD
2017-01-11, with no changes. If, during any inspection required by
paragraph (j) of this AD, any damage is detected: Before further
flight, replace the MLG sliding tube with a serviceable tube, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-32-1416, including Appendix 01, dated March 10, 2014.
For Model A318 series airplanes, use the procedures specified for
Model A319 series airplanes in Airbus Service Bulletin A320-32-1416,
including Appendix 01, dated March 10, 2014.

(l) Retained Definition of Serviceable MLG Sliding Tube of AD 2017-01-
11, With No Changes

    This paragraph restates the definition specified in paragraph
(k) of AD 2017-01-11, with no changes. For the purpose of paragraph
(k) of this AD, a serviceable sliding tube is defined as a sliding
tube that meets the criterion in either paragraph (l)(1) or (l)(2)
of this AD.
    (1) A sliding tube having a part number and serial number not
listed in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1),
and (m)(2) of this AD.
    (2) A sliding tube having a part number and serial number listed
in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and
(m)(2) of this AD that has passed the inspections required by
paragraph (j) of this AD.

(m) Retained Parts Installation Prohibition of AD 2017-01-11, With No
Changes

    This paragraph restates the requirements of paragraph (l) of AD
2017-01-11, with no changes.
    (1) For airplanes that have an MLG sliding tube installed that
has a part number and serial number listed in table 1 to paragraphs
(i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD: After an
airplane is returned to service following accomplishment of the
actions required by paragraphs (h), (i), and (j) of this AD, no
person may install on any airplane an MLG sliding tube having a part
number and serial number listed in table 1 to paragraphs (i), (j),
(l)(1), (l)(2), (m)(1), and (m)(2) of this AD, unless that sliding
tube has passed the inspection required by paragraph (j) of this AD.
    (2) For airplanes that, as of February 22, 2017 (the effective
date of AD 2017-01-11), do not have an MLG sliding tube installed
that has a part number and serial number listed in table 1 to
paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD:
No person may install, on any airplane, an MLG sliding tube having a
part number and serial number listed in table 1 to paragraphs (i),
(j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD unless that
sliding tube has passed the inspection required by paragraph (j) of
this AD.

(n) New Definitions

    For the purpose of paragraphs (o), (p), (q), (r), and (s) of
this AD the following definitions apply.
    (1) Affected MLG shock absorber: An MLG shock absorber having a
part number and serial number as identified in Safran Service
Bulletin 200-32-286, Revision 3, dated October 3, 2008, for Model
A318, A319, and A320 series airplanes; and Safran Service Bulletin
201-32-43, Revision 3, dated October 3, 2008, for Model A321 series
airplanes.
    (2) Affected MLG sliding tube: An MLG sliding tube having a part
number and serial number as identified in Appendix B of Safran
Service Bulletin 200-32-321, Revision 2, dated October 3, 2017, for
Model A318, A319, and A320 series airplanes; or Safran Service
Bulletin 201-32-68, Revision 2, dated October 3, 2017, for Model
A321 series airplanes, except those parts that passed an inspection
as specified in Safran Service

Bulletin 200-32-321; or Safran Service Bulletin 201-32-68, as
applicable, and those parts that, after that inspection, have been
repaired, using instructions approved by the Manager, International
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's
EASA DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
    (3) Serviceable MLG sliding tube: A MLG sliding tube that is not
affected, or an affected MLG sliding tube, that has not exceeded
10,000 flight cycle since first installation on an airplane, or an
affected MLG sliding tube that, within the last 5,000 flight cycles
before installation on an airplane, passed an inspection specified
in Airbus Service Bulletin A320-32-1441.

(o) New Requirement of This AD: Repetitive Inspections

    At the compliance time specified in figure 2 to paragraph (o) of
this AD, and thereafter at intervals not to exceed 5,000 flight
cycles: Do a detailed inspection of each affected MLG sliding tube,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-32-1441, Revision 01, dated December 14, 2017.
[GRAPHIC] [TIFF OMITTED] TP25FE19.003

    Note 2 to paragraph (o) of this AD: If no reliable data
regarding the number of flight cycles accumulated by the MLG sliding
tube are available, operators may refer to the guidance specified in
Chapter 5.2, ``Traceability'', of Section 1, of Part 1 of the Airbus
A318/A319/A320/A321 Airworthiness Limitations Section.

(p) New Requirement of This AD: Corrective Actions

    (1) If, during any inspection required by paragraph (o) of this
AD, any crack is detected on an MLG sliding tube: Before further
flight, replace that MLG sliding tube with a serviceable MLG sliding
tube, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-32-1441, Revision 01, dated December 14, 2017.
    (2) Replacement of an MLG on an airplane with an MLG having a
serviceable MLG sliding tube installed is an acceptable method to
comply with the requirements of paragraph (p)(1) of this AD for that
airplane.

(q) New Requirement of This AD: Part Replacement

    (1) Within 10 years after the effective date of this AD: Replace
each affected MLG sliding tube with an MLG sliding tube that is not
affected. Installation of an MLG sliding tube that is not affected
on an airplane constitutes terminating action for the repetitive
inspections required by paragraph (o) of this AD for that airplane.
    (2) Replacement of an MLG on an airplane with an MLG that does
not have an affected MLG sliding tube installed is an acceptable
method to comply with the requirement of paragraph (q)(1) of this AD
for that airplane.

(r) New Requirement of This AD: Parts Installation Limitation

    (1) As of the effective date of this AD no person may install on
any airplane an affected MLG shock absorber.
    (2) Do not install an affected MLG sliding tube on any airplane
as specified in paragraph (r)(2)(i) or (r)(2)(ii) of this AD, as
applicable.
    (i) For an airplane with an affected MLG sliding tube installed
as of the effective date of this AD: After replacement of each
affected MLG sliding tube as required by paragraph (q) of this AD.
    (ii) For an airplane that does not have an affected MLG sliding
tube installed as of the effective date of this AD: As of the
effective date of this AD.

(s) Identification of Airplanes Not Affected by Certain Requirements of
This AD

    An airplane on which Airbus Modification 161202 or Modification
161346 has been installed in production is not affected by the
requirements of paragraphs (g), (h), (j), (o), and (q), of this AD,
provided it has been verified that no affected MLG sliding tube is
installed on that airplane.

(t) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before
June 29, 2007, using Airbus AOT A320-32A1273, Revision 01, dated May
6, 2004.
    (2) This paragraph provides credit for the initial inspection
and applicable corrective actions required by paragraphs (o) and (p)
of this AD if those actions were performed before the effective date
of this AD, using the Accomplishment Instructions in Airbus Service
Bulletin A320-32-1441, dated December 28, 2016.

(u) Service Information Exceptions

    The service information specified in paragraph (g) of this AD
has instructions to send any cracked part to Messier-Dowty. This AD
does not include such a requirement, in accordance with the
procedures specified in paragraph (w)(2) of this AD.

(v) No Reporting Requirement

    Although Airbus Service Bulletin A320-32-1441, Revision 01,
dated December 14, 2017, specifies to submit certain information to
the manufacturer, and specifies that action as ``RC,'' (required for
compliance) this AD does not include that requirement.

(w) Other FAA AD Provisions

    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, 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 International Section, send it to the attention of
the person identified in paragraph (x)(2) of this AD. Information
may be emailed to<EMAIL_ADDRESS>    (i) 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.
    (ii) AMOCs approved previously for AD 2007-11-11 are approved as
AMOCs for the corresponding provisions of paragraph (g) of this AD.
    (iii) AMOCs approved previously for AD 2017-01-11 are approved
as AMOCs for the corresponding provisions of paragraphs (h), (i),
(j), (k), (l), and (m) of this AD.
    (2) Contacting the Manufacturer: As of the effective date of
this AD, 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 Section, Transport Standards
Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the
DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by
paragraphs (u) and (v) 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.

(x) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2018-0135, dated June 26, 2018, 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-2019-0017.
    (2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax<PHONE_NUMBER>.
    (3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email<EMAIL_ADDRESS>internet
http://www.airbus.com. You may view this service information at the
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines,
WA. For information on the availability of this material at the FAA,
call<PHONE_NUMBER>.

    Issued in Des Moines, Washington, on February 1, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-02929 Filed 2-22-19; 8:45 am]
 BILLING CODE 4910-13-P


P-18-0329 Sanitized Support Documents Index:
 P-18-0329 Sanitized Determination Document (linked)
 P-18-0329 Sanitized CHEM Report (attached)
 P-18-0329 Sanitized ECO Report (attached)
 P-18-0329 Sanitized ENG Report (attached)
 P-18-0329 Sanitized EXP Report (attached)
 P-18-0329 Sanitized Fate Report (attached)
 P-18-0329 Sanitized HLTH Report_POST-FOCUS FINAL (attached)


[Federal Register Volume 79, Number 1 (Thursday, January 2, 2014)]
[Proposed Rules]
[Pages 65-70]
[FR Doc No: 2013-31315]

========================================================================
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. 1 / Thursday, January 2, 2014 /
Proposed Rules

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0425; Directorate Identifier 2012-NM-224-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.

-----------------------------------------------------------------------

SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for certain The Boeing Company Model 747 airplanes. The NPRM
proposed to require repetitive inspections for cracking in the bulkhead
splice fitting, frame supports, forward and aft inner chords, and floor
support; an inspection for cracking in the bulkhead upper web, doubler,
and bulkhead lower web; and corrective actions if necessary; for
certain airplanes, inspections for cracking in the repaired area of the
bulkhead, and corrective actions if necessary; for certain airplanes,
support frame modification and support frame inspections, and related
investigative and corrective actions, if necessary; for certain
airplanes, repetitive support frame post-modification inspections and
inspections for cracking in the hinge support, and related
investigative and corrective actions if necessary; for certain
airplanes, a one-time inspection of the frame web and upper shear deck
(floor support) chord aft side for fasteners; and a one-time inspection
of the upper forward inner chord, frame support fitting and splice
fitting, for the installation of certain fasteners; and related
investigative and corrective actions if necessary; for certain
airplanes, a one-time inspection of the upper forward inner chord,
frame support fitting and splice fitting for the installation of
certain fasteners; a one-time inspection for any repair installed on
the left and right side of the aft inner chord, and related
investigative and corrective actions, if necessary; for certain
airplanes, a one-time inspection of the support frame outer chords for
cracking, and repair if necessary; and repetitive support frame post-
repair inspections, and corrective actions, if necessary. The NPRM was
prompted by reports of cracking in the forward and aft inner chord of
the body station (BS) 2598 bulkhead near the upper corners of the
cutout for the horizontal stabilizer rear spar, and cracking in the
bulkhead upper and lower web panels near the inner chord to shear deck
connection. This action revises the NPRM by adding an optional
terminating action for certain inspections and expanding the inspection
area for certain surface and open-hole HFEC inspections. We are
proposing this supplemental NPRM (SNPRM) to detect and correct fatigue
cracking of the BS 2598 bulkhead structure, which could adversely
affect the structural integrity of the bulkhead and the horizontal
stabilizer support structure and result in loss of controllability of
the airplane. Since these actions impose an additional burden over that
proposed in the NPRM, we are reopening the comment period to allow the
public the chance to comment on these proposed changes.

DATES: We must receive comments on this SNPRM by February 18, 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:<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, Attention: Data & Services Management, P. O. Box
3707, MC 2H-65, Seattle, WA 98124-2207; telephone<PHONE_NUMBER>,
extension 1; fax<PHONE_NUMBER>; 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<PHONE_NUMBER>.

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

FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone:<PHONE_NUMBER>; fax:
425-917-6590; email<EMAIL_ADDRESS>
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-2013-0425;
Directorate Identifier 2012-NM-224-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 issued an NPRM to amend 14 CFR part 39 to include an AD that
would

apply 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, certificated in any category.
The NPRM published in the Federal Register on May 28, 2013 (78 FR
31867). The NPRM proposed to require repetitive inspections for
cracking in the bulkhead splice fitting, frame supports, forward and
aft inner chords, and floor support; doing an inspection for cracking
in the bulkhead upper web, doubler, and bulkhead lower web; and
corrective actions if necessary; for certain airplanes, inspections for
cracking in the repaired area of the bulkhead, and corrective actions
if necessary; for certain airplanes, support frame modification and
support frame inspections, and related investigative and corrective
actions, if necessary; for certain airplanes, repetitive support frame
post-modification inspections and inspections for cracking in the hinge
support, and related investigative and corrective actions if necessary;
for certain airplanes, a one-time inspection of the frame web and upper
shear deck (floor support) chord aft side for fasteners; and a one-time
inspection of the upper forward inner chord, frame support fitting and
splice fitting, for the installation of certain fasteners; and related
investigative and corrective actions if necessary; for certain
airplanes, a one-time inspection of the upper forward inner chord,
frame support fitting and splice fitting for the installation of
certain fasteners; a one-time inspection for any repair installed on
the left and right side of the aft inner chord, and related
investigative and corrective actions, if necessary; for certain
airplanes, a one-time inspection of the support frame outer chord for
cracking, and repair if necessary; and repetitive support frame post-
repair inspections, and corrective actions, if necessary.

Actions Since Previous NPRM (78 FR 31867, May 28, 2013) Was Issued

    Since we issued the NPRM (78 FR 31867, May 28, 2013), we have
received Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated
July 19, 2013, which extends the open-hole HFEC inspection for cracking
to include more fastener holes common to the upper and lower splice
fittings on both sides of the bulkhead, plus some additional fastener
holes adjacent to the lower splice fitting. Boeing Alert Service
Bulletin 747-53A2427, Revision 7, dated July 19, 2013, also extends the
surface HFEC inspection for cracking to include the fillet radius area
of the upper splice fitting. Boeing Alert Service Bulletin 747-53A2427,
Revision 7, dated July 19, 2013, clarifies compliance times for the
initial surface HFEC inspection of the upper web for airplanes modified
or repaired before the upper web inspection was added. Boeing Alert
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013, also
adds an optional terminating modification for certain inspections.

Comments

    We gave the public the opportunity to comment on the NPRM (78 FR
31867, May 28, 2013). The following presents the comments received on
the NPRM (78 FR 31867, May 28, 2013) and the FAA's response to each
comment.

Request To Replace the NPRM (78 FR 31867, May 28, 2013)

    Atlas Air, Inc. requested that the NPRM (78 FR 31867, May 28, 2013)
be replaced with four separate ADs. The commenter stated that having a
separate AD for Boeing Alert Service Bulletin 747-53A2427, Revision 7,
dated July 19, 2013; Boeing Service Bulletin 747-53A2449, Revision 2,
dated March 14, 2002; Boeing Alert Service Bulletin 747-53A2467,
Revision 1, dated April 28, 2005; and Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011; would simplify the
requirements and future supersedures. The commenter also stated that
separate ADs will ease the burden on the operators.
    We disagree with replacing the NPRM (78 FR 31867, May 28, 2013).
Increasing the number of ADs to four does not necessarily ease the
operator burden. We find that delaying this action to resubmit as a
separate AD, would be inappropriate in light of the urgency of the
identified unsafe condition. No changes have been made to this SNPRM in
this regard.

Request for Alternative Method of Compliance (AMOC) Approval for
Previously Approved AMOCs

    Atlas Air, Inc. requested that AMOCs approved for paragraphs (i),
(j), (m), (n), (o), (p), (q), (r), (s), (t), (u), and (v), of AD 2010-
14-07 (75 FR 38001, July 1, 2010), be approved as AMOCs to the
corresponding actions of the NPRM (78 FR 31867, May 28, 2013).
    We agree with the request. Although the actions in some of the
paragraphs referenced above carry over to paragraphs (g), (h), (i),
(j), (k), and (l) of this SNPRM, AD 2010-14-07 (75 FR 38001, July 1,
2010) was superseded and added new inspections and requirements, for
which previously approved AMOCs would not provide coverage. We have
added new paragraph (q)(4) to this SNPRM stating that previously
approved AMOCs for AD 2010-14-07 are approved for the corresponding
actions in this SNPRM. All actions specified in paragraphs (g), (h),
(i), (j), (k), and (l) of this SNPRM that are not identified in the
AMOC must still be done.

Request Authorization of Modification in Boeing Service Bulletin 747-
53A2837 as an AMOC to Requirements of Paragraphs (j), (k), and (l) of
the NPRM (78 FR 31867, May 28, 2013)

    Atlas Air, Inc. requested that the NPRM (78 FR 31867, May 28, 2013)
be revised to authorize the modification in Boeing Service Bulletin
747-53A2837 as an AMOC to the requirements of paragraphs (j), (k), and
(l) of the NPRM.
    We agree with the request. Boeing Service Bulletin 747-53A2837,
dated July 13, 2012, was approved as an AMOC to AD 2010-14-07 (75 FR
38001, July 1, 2010). Accomplishing the modification of the bulkhead at
BS 2598, in accordance with the Accomplishment Instructions of Boeing
Service Bulletin 747-53A2837, dated July 13, 2012, terminates the
requirements of paragraphs (g), (h), (i), (j), (k), and (l) of this AD.
We have added new paragraph (n) to this SNPRM to provide this optional
terminating modification.

Request for Clarification of Language in Paragraph (g) of the NPRM (78
FR 31867, May 28, 2013)

    Boeing requested that we delete the phrase, ``and doubler,'' and
add the word, ``assembly'' to bulkhead upper web and bulkhead lower web
in paragraph (g) of the NPRM (78 FR 31867, May 28, 2013). Boeing stated
that the language in Boeing Alert Service Bulletin 747-53A2427,
Revision 6, dated July 14, 2011, was in error and this requested change
clarifies the NPRM to match the intent of this service bulletin.
    We agree to clarify the language and have made the requested
changes to paragraph (g) of this SNPRM accordingly.

Request for Clarification of Language in Paragraph (m)(5) and (m)(6) of
the NPRM (78 FR 31867, May 28, 2013)

    Boeing requested that we add the phrase ``bonded web'' to the word
``doubler'' in paragraphs (m)(5) and (m)(6) of the NPRM (78 FR 31867,
May 28, 2013). Boeing stated that the language in Boeing Alert Service
Bulletin 747-53A2427, Revision 6, dated July 14, 2011, was in error and
this requested change clarifies the

NPRM to match the intent of this service bulletin. Boeing also
requested that we add the phrase ``if present'' to paragraph (m)(6) of
the NPRM.
    We agree to clarify the language and have made the requested
changes to paragraphs (m)(5) and (m)(6) of this SNPRM accordingly. We
have also added the phrase ``if present'' to paragraph (m)(6) of this
SNPRM.

Request To Correct Compliance Time

    Boeing requested that we correct the compliance time specified in
paragraph (m)(2) of the NPRM (78 FR 31867, May 28, 2013) to be from the
effective date of AD 2010-14-07, Amendment 39-16352 (75 FR 38001, July
1, 2010). Boeing Alert Service Bulletin 747-53A2427, Revision 6, dated
July 14, 2011, was not mandated by AD 2006-05-06, Amendment 39-14503
(71 FR 12125, March 9, 2006).
    We agree with the request and have made the change to paragraph
(m)(2) of this SNPRM accordingly.

Other Changes to SNPRM

    We have updated paragraphs (c), (g), (h), (i), (m), and (o) of this
SNPRM to refer to Boeing Alert Service Bulletin 747-53A2427, Revision
7, dated July 19, 2013. We have also added the area of the upper and
lower web panels to the open hole and surface HFEC inspections
specified in paragraph (g) of this SNPRM. We have clarified the
affected airplanes for paragraph (g) of this SNPRM by qualifying the
airplanes to those on which an interim modification or aft inner chord
repair has not been done, as specified in Boeing Alert Service Bulletin
747-53A2427. We have also provided credit for Boeing Alert Service
Bulletin 747-53A2427, Revision 6, dated July 14, 2011, provided that
the additional actions added in Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013, are done within the
applicable compliance times specified in paragraphs (g), (h), and (i)
of this SNPRM.

FAA's Determination

    We are proposing this SNPRM because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs. Certain changes described above expand the scope of the NPRM
(78 FR 31867, May 28, 2013). As a result, we have determined that it is
necessary to reopen the comment period to provide additional
opportunity for the public to comment on this SNPRM.

Proposed Requirements of the SNPRM

    This SNPRM would require accomplishing the actions specified in the
service information described previously.

Costs of Compliance

    We estimate that this proposed AD affects 184 airplanes of U.S.
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                  Cost per
            Action                Labor cost      Parts cost      product            Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspection...................  49 work-hours x            $0  $4,165 per       $766,360 per inspection cycle.
                                $85 per hour =                 inspection
                                $4,165 per                     cycle.
                                inspection
                                cycle.
Support frame modification...  315 work-hours x           $0  $26,775........  Up to $4,926,600.
                                $85 per hour =
                                $26,775.
Support frame upper corner     16 work-hours x            $0  $1,360.........  Up to $250,240.
 fastener inspection.           $85 per hour =
                                $1,360.
Support frame post-            200 work hours x           $0  $17,000........  $3,128,000.
 modification inspection.       $85 per hour =
                                $17,000.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary interim
modification 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 interim modification:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Interim modification.........................  4 work-hours x $85 per hour =                $0             $340
                                                $340.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide
a cost estimate for the corrective 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]

    2. The FAA amends Sec.  39.13 by adding the following new
airworthiness directive (AD):

The Boeing Company: Docket No. FAA-2013-0425; Directorate Identifier
2012-NM-224-AD.

(a) Comments Due Date

    We must receive comments by February 18, 2014.

(b) Affected ADs

    This AD affects AD 2010-14-07, Amendment 39-16352 (75 FR 38001,
July 1, 2010).

(c) Applicability

    This AD applies to 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, as identified in Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of cracking in the forward and
aft inner chord of the body station (BS) 2598 bulkhead near the
upper corners of the cutout for the horizontal stabilizer rear spar,
and cracking in the bulkhead upper and lower web panels near the
inner chord to shear deck connection. We are issuing this AD to
detect and correct fatigue cracking of the BS 2598 bulkhead
structure, which could adversely affect the structural integrity of
the bulkhead and the horizontal stabilizer support structure and
result in loss of controllability of the airplane.

(f) Compliance

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

(g) Inspections of the Bulkhead (Support Frame)

    For airplanes on which the bulkhead (support frame) modification
specified in Boeing Service Bulletin 747-53A2473 or 747-53A2837 has
not been accomplished, and on which an interim modification or aft
inner chord repair has not been done as specified in Boeing Alert
Service Bulletin 747-53A2427: At the applicable times specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2427, Revision 7, dated July 19, 2013, except as provided by
paragraph (m)(1), (m)(2), or (m)(3) of this AD, as applicable, do an
open-hole and surface high frequency eddy current (HFEC) inspection
for cracking in the bulkhead (support frame), which includes the
bulkhead splice fitting, frame supports, forward and aft inner
chords, floor supports, and upper and lower web panels; do a surface
HFEC inspection for cracking in the bulkhead upper web assembly; do
an open-hole and surface HFEC inspection for cracking in the
bulkhead lower web assembly; and do all applicable corrective
actions; in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated July
19, 2013, except as required by paragraphs (m)(4), (m)(5) and (m)(6)
of this AD, and except as provided by paragraph (h) of this AD. Do
all applicable corrective actions before further flight. Repeat the
applicable inspections, thereafter, at the applicable times in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2427, Revision 7, dated July 19, 2013. Doing the modification
required by paragraph (j) of this AD terminates the repetitive
inspections required by this paragraph.

(h) Interim Modification

    For airplanes in groups 1 and 2, as identified in Boeing Alert
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013, on
which no cracking was found during any inspection required by
paragraph (g) of this AD: At the applicable times specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2427, Revision 7, dated July 19, 2013, except as provided by
paragraph (m)(2) of this AD, do the interim modification, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013. Doing
the interim modification terminates the repetitive inspections
requirement of paragraph (g) of this AD in the area of the
modification only. The repetitive inspections of the bulkhead lower
web, as specified in paragraph (g) of this AD, must be done. If the
aft inner chord repair or upper web repair specified in Boeing Alert
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013, has
been accomplished, an interim modification on the side of the
airplane that has the repair is not required by this paragraph.

(i) Post-Repair Inspection or Post-Interim Modification Inspection

    For airplanes on which an interim modification, or aft inner
chord repair, or upper web repair has been done as specified in
paragraph (g) or (h) of this AD: At the applicable times specified
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2427, Revision 7, dated July 19, 2013, except as specified in
paragraph (m)(1), (m)(2), or (m)(3) of this AD, as applicable, do
the actions specified in paragraph (i)(1) and (i)(2) of this AD, and
all applicable corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013, except as required by
paragraph (m)(4) of this AD. Do all applicable corrective actions
before further flight. Repeat the inspections thereafter at the
applicable intervals specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated July
19, 2013. Doing the modification required by paragraph (j) of this
AD terminates the repetitive inspections required by this paragraph.
    (1) Do forward side surface HFEC inspections for cracking of the
bulkhead forward inner chord, splice fitting, and frame support.
    (2) Do surface and open-hole HFEC inspections for cracking in
the repaired and modified areas of the bulkhead, as applicable.

(j) Bulkhead (Support Frame) Modification and Inspections

    For airplanes on which the bulkhead (support frame) modification
specified in Boeing Service Bulletin 747-53A2473, dated March 24,
2005; Revision 1, dated February 20, 2007; Revision 2, dated August
28, 2009; Revision 3, dated July 14, 2011; or Revision 4, dated
December 1, 2011; has not been done as of the effective date of this
AD: At the applicable time in tables 2 and 3 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-53A2473, Revision 4,
dated December 1, 2011, do the bulkhead (support frame) modification
and inspections and all applicable related investigative and
corrective actions; in accordance with steps 3.B.3., 3.B.4., and
3.B.5. of the Accomplishment Instructions of Boeing Service Bulletin
747-53A2473, Revision 4, dated December 1, 2011, except as required
by paragraph (m)(4) of this AD. Do all applicable related
investigative and corrective actions before further flight. Doing
the modification in this paragraph terminates the inspections
required by paragraphs (g) and (i) of this AD.

(k) Post Modification Inspections

    (1) For airplanes on which the bulkhead (support frame)
modification has been done as specified in Boeing Service Bulletin
747-53A2473, dated March 24, 2005; Revision 1, dated February 20,
2007; Revision 2, dated August 28, 2009; Revision 3, dated July 14,
2011; or Revision 4, dated December 1, 2011:

Except as provided by paragraphs (m)(7) and (m)(8) of this AD, at
the applicable time in tables 6, 7, 8, and 9 of paragraph 1.E.,
``Compliance'' of Boeing Service Bulletin 747-53A2473, Revision 4,
dated December 1, 2011, do support frame post-modification
inspections, and open-hole HFEC inspections for cracking in the
hinge support, and do all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2473, Revision 4,
dated December 1, 2011, except as required by paragraph (m)(4). Do
all applicable related investigative and corrective actions before
further flight. Repeat the inspections thereafter at the applicable
times in tables 6, 7, 8, and 9 of paragraph 1.E., ``Compliance,'' of
Boeing Service Bulletin 747-53A2473, Revision 4, dated December 1,
2011.
    (2) For airplanes on which the support frame modification has
been done as specified in Boeing Service Bulletin 747-53A2473,
Revision 1, dated February 20, 2007: Except as specified in
paragraphs (m)(7) and (m)(8) of this AD, at the applicable time in
tables 4 and 5 of paragraph 1.E., ``Compliance'' of Boeing Service
Bulletin 747-53A2473, Revision 4, dated December 1, 2011, do a one-
time general visual inspection of the frame web and upper shear deck
(floor support) chord aft side for fasteners that were installed as
part of an inner chord repair removal; and a one-time general visual
inspection of the upper forward inner chord, frame support fitting
and splice fitting, for the installation of certain fasteners; and
do all applicable related investigative and corrective actions; in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 747-53A2473, Revision 4, dated December 1, 2011, except as
required by paragraph (m)(4) of this AD. Do all applicable related
investigative and corrective actions at the applicable times
specified in tables 4 and 5 of paragraph 1.E., ``Compliance'' of
Boeing Service Bulletin 747-53A2473, Revision 4, dated December 1,
2011.
    (3) For airplanes on which the support frame modification has
been done as specified in Boeing Service Bulletin 747-53A2473, dated
March 24, 2005: Except as specified in paragraphs (m)(7) and (m)(8)
of this AD, at the applicable time in tables 5 and 10 of paragraph
1.E., ``Compliance'' of Boeing Service Bulletin 747-53A2473,
Revision 4, dated December 1, 2011, do a one-time general visual
inspection of the upper forward inner chord, frame support fitting,
and splice fitting for the installation of certain fasteners; a one-
time general visual inspection for any repair installed on the left
and right side of the aft inner chord; and do all applicable related
investigative and corrective actions; in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2473,
Revision 4, dated December 1, 2011, except as required by paragraph
(m)(4) of this AD. Do all applicable related investigative and
corrective actions at the applicable times specified in tables 5 and
10 of paragraph 1.E., ``Compliance'' of Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011.
    (4) For airplanes on which a post-modification inspection was
done in accordance with paragraph 3.B.8. of Part 1 of the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2473,
Revision 3, dated July 14, 2011: Except as required by paragraphs
(m)(7) and (m)(8) of this AD, at the applicable time in table 11 of
paragraph 1.E., ``Compliance'' of Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011, do a one-time surface
HFEC inspection of the support frame outer chord for cracking, in
accordance with Part 1 of the Accomplishment Instructions of Boeing
Service Bulletin 747-53A2473, Revision 4, dated December 1, 2011. If
any cracking is found, repair before further flight, using a method
approved in accordance with the procedures specified in paragraph
(q) of this AD.

(l) Post-Modification Post-Repair Inspections

    For airplanes on which post-modification inspection cracks were
repaired by doing the installation of an upper or lower corner post-
modification web crack repair as specified in Boeing Service
Bulletin 747-53A2473, Revision 4, dated December 1, 2011: At the
applicable times specified in tables 6 and 8 of paragraph 1.E.,
``Compliance'' of Boeing Service Bulletin 747-53A2473, Revision 4,
dated December 1, 2011, do a bulkhead (support frame) post-repair
inspection, and do all applicable corrective actions, in accordance
with paragraph a., b., or c. of Part 4 of paragraph 3.B.8 of the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2473,
Revision 4, dated December 1, 2011, as applicable, except as
required by paragraph (m)(4) of this AD. Repeat the inspection,
thereafter, at the applicable times specified in tables 6 and 8 of
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011.

(m) Exceptions

    (1) Where Boeing Alert Service Bulletin 747-53A2427, Revision 7,
dated July 19, 2013, specifies a compliance time after the date on
Revision 2 of this service bulletin, this AD requires compliance
within the specified compliance time as of August 28, 2001 (the
effective date of AD 2001-15-03, Amendment 39-12337 (66 FR 38365,
July 24, 2001)).
    (2) Where Boeing Alert Service Bulletin 747-53A2427, Revision 7,
dated July 19, 2013, specifies a compliance time after the date on
Revision 4 of this service bulletin, this AD requires compliance
within the specified compliance time as of August 5, 2010 (the
effective date of AD 2010-14-07, Amendment 39-16352 (75 FR 38001,
July 1, 2010)).
    (3) Where Boeing Alert Service Bulletin 747-53A2427, Revision 7,
dated July 19, 2013, specifies a compliance time after the date on
Revision 6 or Revision 7 of this service bulletin, this AD requires
compliance within the specified compliance time ``after the
effective date of this AD.''
    (4) If any cracking is found during any inspection required by
this AD, and Boeing Alert Service Bulletin 747-53A2427, Revision 7,
dated July 19, 2013; or Boeing Service Bulletin 747-53A2473,
Revision 4, dated December 1, 2011; specifies to contact Boeing for
appropriate action: Before further flight, repair the crack using a
method approved in accordance with the procedures specified in
paragraph (q) of this AD.
    (5) If, during any inspection required by paragraph (g) of this
AD, any cracking is found in the bonded web doubler, before further
flight, repair, using a method approved in accordance with the
procedures specified in paragraph (q) of this AD.
    (6) Where Part 1 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013,
specifies accomplishing inspections for cracks for forward and aft
inner chords, splice fittings, floor supports, and upper and lower
web panels, this AD also requires doing an open-hole HFEC inspection
of the bonded web doubler if present.
    (7) Where Boeing Service Bulletin 747-53A2473, Revision 4, dated
December 1, 2011, specifies a compliance time after the date on
Revision 2 of that service bulletin, this AD requires compliance
within the specified compliance time as of August 5, 2010 (the
effective date of AD 2010-14-07, Amendment 39-16352 (75 FR 38001,
July 1, 2010)).
    (8) Where Boeing Service Bulletin 747-53A2473, Revision 4, dated
December 1, 2011, specifies a compliance time after the date on
Revision 3 or 4 of that service bulletin, this AD requires
compliance within the specified compliance time ``after the
effective date of this AD.''

(n) Optional Termination Modification

    Accomplishing the modification of the bulkhead at body station
2598, in accordance with the Accomplishment Instructions of Boeing
Service Bulletin 747-53A2837, dated July 13, 2012, terminates the
requirements of paragraphs (g), (h), (i), (j), (k), and (l) of this
AD, except where Boeing Service Bulletin 747-53A2837, dated July 13,
2012, specifies to contact Boeing for appropriate action: Before
further flight, repair the crack using a method approved in
accordance with the procedures specified in paragraph (q) of this
AD.

(o) Terminating Action for Certain Requirements of AD 2010-14-07,
Amendment 39-16352 (75 FR 38001, July 1, 2010)

    (1) Accomplishing the inspections, repairs, and modification in
accordance with Boeing Service Bulletin 747-53A2473, Revision 4,
dated December 1, 2011, is a terminating action for the
corresponding inspections, repairs, and modification at the STA 2598
support frame required by paragraphs (i), (j), (k), (1), (m), (n),
(o), (p), (q), (r), (s), (t), (u), and (v) of AD 2010-14-07,
Amendment 39-16352 (75 FR 38001, July 1, 2010). Where Boeing Service
Bulletin 747-53A2473, Revision 4, dated December 1, 2011, specifies
to contact Boeing for repair instructions, the repair instructions
must be approved by the FAA in accordance with paragraph (q) of this
AD. All provisions of AD 2010-14-07 that are not specifically
referenced in this paragraph remain fully applicable and must be
complied with.

    (2) Accomplishing the inspections, repairs and interim
modification in accordance with Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013, is a terminating action
for the corresponding inspections, repairs and interim modification
at the STA 2598 bulkhead required by paragraphs (i), (j), (o), (s),
(t), (u), and (v) of AD 2010-14-07, Amendment 39-16352 (75 FR 38001,
July 1, 2010). When Boeing Alert Service Bulletin 747-53A2427,
Revision 7, dated July 19, 2013, specifies to contact Boeing for
repair data, the repair data must be approved by the FAA in
accordance with paragraph (q) of this AD. All provisions of AD 2010-
14-07 that are not specifically referenced in this paragraph remain
fully applicable and must be complied with.

(p) Credit for Previous Actions

    This paragraph provides credit for the actions required by
paragraphs (g), (h), (i), and (n)(2) of this AD, if those actions
were performed before the effective date of this AD using Boeing
Alert Service Bulletin 747-53A2427, Revision 6, dated July 14, 2011,
provided that the additional actions added in Boeing Alert Service
Bulletin 747-53A2427, Revision 7, dated July 19, 2013, are done
within the applicable compliance times specified in paragraphs (g),
(h), and (i) of this AD.

(q) 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 (r)(1) of this AD.
Information may be emailed to<EMAIL_ADDRESS>    (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) Related portions or applicable paragraphs of AMOCs approved
previously for AD 2010-14-07, Amendment 39-16352 (75 FR 38001, July
1, 2010), are approved as AMOCs for the related corresponding
provisions of paragraphs (g), (h), (i), (j), (k), and (l) of this
AD. All new actions specified in paragraphs (g), (h), (i), (j), (k),
and (l) of this AD that are not identified in the AMOCs must still
be done.

(r) Related Information

    (1) For more information about this AD, contact Nathan Weigand,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>    (2) 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<PHONE_NUMBER>; 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<PHONE_NUMBER>.

    Issued in Renton, Washington, on December 20, 2013.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-31315 Filed 12-31-13; 8:45 am]
BILLING CODE 4910-13-P