[Federal Register: January 11, 2011 (Volume 76, Number 7)]
[Proposed Rules]
[Page 1552-1556]
[DOCID:fr11ja11-19]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1118; Directorate Identifier 2007-NM-318-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Model 737-600, -700,
-700C, -800, -900, and -900ER Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

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

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SUMMARY: The FAA is revising an earlier NPRM for an airworthiness
directive (AD) that applies to all Boeing Model 737-600, -700, -700C, -
800, and -900 series airplanes. The original NPRM would have superseded
an existing AD that currently requires reviewing the airplane
maintenance records to determine whether an engine has been removed
from the airplane since the airplane was manufactured. For airplanes on
which an engine has been removed, the existing AD also requires an
inspection of the aft engine mount to determine if the center link
assembly is correctly installed, and follow-on actions if necessary.
The original NPRM proposed to require the same actions for airplanes on
which the engine has not been previously removed. The original NPRM
resulted from reports indicating that operators found that the center
link assembly for the aft engine mount was reversed on several
airplanes that had not had an engine removed since delivery. This new
action revises the original NPRM by expanding the applicability to
include Model 737-900ER airplanes. We are proposing this supplemental
NPRM to prevent increased structural loads on the aft engine mount,
which could result in failure of the aft engine mount and consequent
separation of the engine from the airplane.

ADDRESSES: We must receive comments on this supplemental NPRM by
February 25, 2011.

DATES: 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 proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax<PHONE_NUMBER>; e-mail<EMAIL_ADDRESS>
Internet https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. 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 (telephone<PHONE_NUMBER>) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.

FOR FURTHER INFORMATION CONTACT: Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6450; 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-2008-1118;
Directorate Identifier 2007-NM-318-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 proposed to amend part 39 of the Federal Aviation Regulations
(14 CFR part 39) with a notice of proposed rulemaking (NPRM) for an AD
(the ``original NPRM'') to supersede AD 2003-03-01, Amendment 39-13025
(68 FR 4367, January 29, 2003). The original NPRM applied to all Model
737-600, -700, -700C, -800, and -900 series airplanes. The original
NPRM was published in the Federal Register on October 30, 2008 (73 FR
64568). The original NPRM would have superseded an existing AD that
currently requires reviewing the airplane maintenance records to
determine whether an engine has been removed from the airplane since
the airplane was manufactured. For airplanes on which an engine has
been removed, the existing AD also requires an inspection of the aft
engine mount to determine if the center link assembly is correctly
installed, and follow-on actions if necessary. The original NPRM
proposed to require the same actions for airplanes on which the engine
has not been previously removed.

Actions Since Original NPRM Was Issued

    Since we issued the original NPRM, the manufacturer has informed us
that Model 737-900ER airplanes should be included in the applicability
of the supplemental NPRM. Model 737-900ER airplanes were not being
produced in May 2004 when Revision 3, dated May 20, 2004, of Boeing
Alert Service Bulletin 737-71A1462, was issued. (Revision 3 was
referred to as an appropriate source of service information for
accomplishing the proposed actions in the original NPRM.) Following
production it was determined that the affected aft engine mount is
interchangeable with Model 737-900ER airplanes; however, those
airplanes

were inspected in production to ensure that the center link was
properly installed. Therefore, the requirements in the existing AD do
not apply to those airplanes. However, since we are including airplanes
on which the engines have been removed since production, we have added
Model 737-900ER airplanes to the applicability section of this
supplemental NPRM.

Comments

    We have considered the following comments on the original NPRM.

Request for Exemption From AD Requirements

    American Airlines (AA) asks that all operators that have performed
the actions specified in Boeing Alert Service Bulletin 737-71A1462,
Revision 3, dated May 20, 2004, be exempt from repeating maintenance
actions in accordance with the original NPRM for a maintenance program
that is already in place and proven effective. AA states that it has
exceeded the requirements of AD 2003-03-01 by inspecting both engine
aft mount center link assemblies, regardless of the stipulation in the
existing AD, which limited the inspection requirement to engines
removed since the airplane date of manufacture. AA adds that the
inspections revealed that none of its installed or spare engines had
incorrectly installed aft mount center link assemblies. AA notes that
it is doing Part 2 of the Accomplishment Instructions of the service
bulletin at every engine shop visit, and has implemented maintenance
task documentation to verify the proper aft mount center link
configuration at every engine change. AA concludes that it has not
accepted delivery of any additional Model 737 airplanes since the
release of the existing AD and Boeing Alert Service Bulletin 737-
71A1462, Revision 3, dated May 20, 2004.
    We acknowledge the commenter's request. Actions done in accordance
with Boeing Alert Service Bulletin 737-71A1462, Revision 3, before the
effective date of this AD are acceptable for compliance with the AD, as
indicated by the phrase ``unless the actions have already been done''
in paragraph (f) of this AD. We have made no change to the supplemental
NPRM in this regard.

Request To Change Paragraph (d)

    Boeing asks that paragraph (d) of the original NPRM be changed to
indicate that the center link assembly for the aft engine mount was
reversed on one airplane that had not had an engine removed since
delivery. Boeing is aware of only one such report.
    We do not agree with the commenter. We have received another report
indicating that some airplanes were found with the engine mounts
installed incorrectly on engines that had not been removed since
airplane delivery. Therefore, we have not changed paragraph (d) of the
NPRM (paragraph (e) of the supplemental NPRM).

Request To Change Paragraph (n)

    Boeing asks that paragraph (n) of the original NPRM be changed to
clarify parts not affected by the ``Parts Installation'' paragraph by
including the permanent part marking on the center link assembly, as
specified in Part 2 of the Work Instructions of Boeing Alert Service
Bulletin 737-71A1462, Revision 3, dated May 20, 2004. Boeing states
that this change would be equivalent to an existing alternative method
of compliance (AMOC) for AD 2003-03-01, requiring the installation of
marked engine mounts, as specified in the approved section of Boeing
Alert Service Bulletin 737-71A1462, Revision 3, dated May 20, 2004.
    We agree with the commenter for the reasons provided. We have
changed paragraph (n) of the supplemental NPRM to include permanent
part marking on the center link assembly, as specified in Part 2 of the
Work Instructions of Boeing Alert Service Bulletin 737-71A1462,
Revision 3, dated May 20, 2004.

Request To Clarify Requirements in Paragraph (n)

    Japan Airlines (JAL) asks for clarification whether the requirement
in paragraph (n) of the original NPRM applies only to airplanes
affected by Boeing Alert Service Bulletin 737-71A1462, Revision 3,
dated May 20, 2004; or to all Model 737-600, -700, -700C, -800, and -
900 series airplanes. JAL states that if the requirement in paragraph
(n) applies to all Model 737NG (next generation) airplanes then a
change should be made to paragraph (n) of the supplemental NPRM for
clarification.
    We acknowledge the commenter's concern and provide the following
clarification. As noted under ``Actions Since Original NPRM Was
Issued,'' we have added Model 737-900ER airplanes to the applicability
section of this supplemental NPRM; therefore, the requirement in
paragraph (n) of the supplemental NPRM applies to all Model 737NG
airplanes. No change to paragraph (n) of the supplemental NPRM is
necessary.

Request To Change Paragraphs (i) and (o)

    CFM International states that the acronym CFMI is not accurate and
recommends using CFM International (CFM) throughout the NPRM.
    We agree that the correct acronym should be used in the
supplemental NPRM and in future rulemaking. However, CFMI is not
referred to anywhere in this supplemental NPRM; therefore, no change is
necessary.
    CFM also asks that paragraphs (i) and (o) of the original NPRM be
changed to include the Engine and Propeller Directorate, Engine
Certification Office (ECO), as an approved source for obtaining repair
procedures. CFM states that the engine mounting lugs and adjacent
engine turbine rear frame are under the responsibility of CFM as part
of the engine type certificate. CFM notes that it is in charge of
approval of repairs by delegation of both engine authorities, which are
the FAA and European Aviation Safety Agency (EASA); CFM is a joint
certification. CFM adds that for any part problems it contacts the ECO,
in Burlington, Massachusetts, and the EASA Engine Certification Office,
in Cologne, Germany. In light of this, CFM does not recommend the parts
be repaired under approval of a Boeing Representative.
    We partially agree with the commenter for the reasons provided. We
agree that the appropriate office for approval of certain repairs
specified in the original NPRM is the ECO. Paragraph (i) of the
original NPRM is a restatement of the requirements in AD 2003-03-01.
However, paragraph (i) of the supplemental NPRM does refer to paragraph
(o) of the supplemental NPRM for AMOC approval. We have changed
paragraph (o) of this supplemental NPRM to allow for certain AMOC
approvals by the ECO.

Explanation of Additional Changes Made to This Supplemental NPRM

    We have changed this supplemental NPRM to identify the legal name
of the manufacturer as published in the most recent type certificate
data sheet for the affected airplane models.
    We have added a new paragraph (d) to this supplemental NPRM to
provide the Air Transport Association (ATA) of America subject code 71:
Powerplant. This code is added to make this supplemental NPRM parallel
with other new AD actions. We have reidentified subsequent paragraphs
accordingly.

FAA's Determination and Proposed Requirements of the Supplemental NPRM

    Certain changes discussed above expand the scope of the original
NPRM; therefore, we have determined that it is necessary to reopen the
comment period to provide additional opportunity for public comment on
this supplemental NPRM.

Explanation of Change to Costs of Compliance

    Since issuance of the original NPRM, we have increased the labor
rate in the Costs of Compliance from $80 per work hour to $85 per work
hour. The Costs of Compliance information, below, reflects this
increase in the specified hourly labor rate.

Costs of Compliance

    There are about 1,846 airplanes of the affected design in the
worldwide fleet. We estimate that 854 airplanes of U.S. registry would
be affected by this proposed AD. There are no new requirements in this
proposed AD; however, we have expanded the applicability as noted under
``Actions Since Original NPRM Was Issued.'' The current costs for this
proposed AD are recalculated for the convenience of affected operators,
as follows:

                                                 Estimated Costs
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                                                                                Cost per
                           Action                              Work hours     Parts       airplane    Fleet cost
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Maintenance records review (required by AD 2003-03-01)......            1           $0          $85      $72,590
Inspection for correct installation of center link assembly             1            0           85       72,590
 (new proposed action)......................................
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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 have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); 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.
    We prepared a regulatory evaluation of the estimated costs to
comply with this supplemental NPRM and placed it in the AD docket. See
the ADDRESSES section for a location to examine the regulatory
evaluation.

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

    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 removing amendment 39-13025 (68 FR
4367, January 29, 2003) and adding the following new AD:

The Boeing Company: Docket No. FAA-2008-1118; Directorate Identifier
2007-NM-318-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by February
25, 2011.

Affected ADs

    (b) This AD supersedes AD 2003-03-01, Amendment 39-13025.

Applicability

    (c) This AD applies to all The Boeing Company Model 737 -600, -
700, -700C, -800, -900, and -900ER series airplanes, certificated in
any category.

Subject

    (d) Air Transport Association (ATA) of America Code 71:
Powerplant.

Unsafe Condition

    (e) This AD results from reports indicating that operators found
that the center link assembly for the aft engine mount was reversed
on several airplanes that had not had an engine removed since
delivery. We are issuing this AD to prevent increased structural
loads on the aft engine mount, which could result in failure of the
aft engine mount and consequent separation of the engine from the
airplane.

Compliance

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

Restatement of the Requirements of AD 2003-03-01

Review of Maintenance Records

    (g) For Model 737-600, -700, -700C, -800, and -900 series
airplanes: Within 90 days after February 13, 2003 (the effective
date of AD 2003-03-01), review the airplane maintenance records to
determine whether either engine has been removed since the
airplane's date of manufacture. If neither engine has been removed
since the airplane's date of manufacture, no further action is
required by this paragraph.

Inspection of Engines That Have Been Removed to Determine if Center
Link Assembly is Installed Correctly

    (h) For Model 737-600, -700, -700C, -800, and -900 series
airplanes on which any installed engine has been removed from the
airplane since the airplane's date of manufacture: Within 90 days
after February 13, 2003, do a one-time general visual inspection to
determine if the center link assembly of the aft engine mount is
installed correctly, in accordance with the

Accomplishment Instructions of Boeing Alert Service Bulletin 737-
71A1462, Revision 1, dated November 7, 2002; or Revision 3, dated
May 20, 2004. If the center link assembly is installed correctly, no
further action is required by paragraph (h) or (i) of this AD for
that engine. As of the effective date of this AD, use only Boeing
Alert Service Bulletin 737-71A1462, Revision 3.

    Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hanger lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''

Follow-on and Corrective Actions

    (i) For airplanes on which any center link assembly is found
installed incorrectly during any inspection required by paragraph
(h), (k), or (l) of this AD: Before further flight, do the actions
specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-71A1462, Revision 1, dated November 7, 2002; or
Revision 3, dated May 20, 2004; except that it is not necessary to
submit a report of findings to the airplane manufacturer. As of the
effective date of this AD, use only Boeing Alert Service Bulletin
737-71A1462, Revision 3.
    (1) Remove the center link assembly and install it correctly.
    (2) Perform a detailed inspection of the engine mounting lugs
and engine turbine rear frame for cracking, yielding, buckling, or
wear damage.
    (3) Perform a detailed inspection of the hardware for the aft
engine mount; including the center link assembly, right link
assembly, aft mount hanger assembly, and link pins; for cracking,
yielding, buckling, or wear damage.

    Note 2:  For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''

Repair

    (j) If any cracking, yielding, buckling, or wear damage is found
during the inspections required by paragraphs (i)(2) and (i)(3) of
this AD: Before further flight, replace the discrepant part with a
new or serviceable part, or repair in accordance with a method
approved in accordance with the procedures specified in paragraph
(o) of this AD.

New Requirements of This AD

Inspection of Engines That Have Not Been Removed To Determine if Center
Link Assembly Is Installed Correctly

    (k) For airplanes identified in Boeing Alert Service Bulletin
737-71A1462, Revision 3, dated May 20, 2004, on which any installed
engine has not been removed from the airplane since the airplane's
date of manufacture: Within 90 days after the effective date of this
AD, do a detailed inspection to determine if the center link
assembly of the aft engine mount is installed correctly, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-71A1462, Revision 3, dated May 20, 2004. If the
center link is installed correctly, no further action is required by
this paragraph for that engine.

Follow-on and Corrective Actions

    (l) For airplanes on which any center link assembly is found
installed incorrectly during the inspection required by paragraph
(k) of this AD: Before further flight, do the follow-on and
corrective actions required by paragraph (i) of this AD.

Credit for Actions Done Using Previous Service Information

    (m) Inspections and corrective actions done before the effective
date of this AD in accordance with a Boeing service bulletin listed
in Table 1 of this AD are acceptable for compliance with the
corresponding requirements of this AD.

                                       Table 1--Previous Service Bulletins
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       Boeing service bulletin                     Revision--                              Dated--
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737-71A1462.........................  Original............................  August 29, 2002.
737-71A1462.........................  1...................................  November 7, 2002.
737-71A1462.........................  2...................................  May 29, 2003.
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Parts Installation

    (n) As of the effective date of this AD, no person may install
an engine on any airplane identified in paragraph (c) of this AD
unless the actions required by paragraph (n)(1) or (n)(2) of this AD
are accomplished.
    (1) The inspection is accomplished in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
71A1462, Revision 3, dated May 20, 2004, and the center link
assembly of the aft engine mount is found to be installed correctly.
    (2) The hanger fitting and center link assembly are marked and
part marked in accordance with Part 2 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-71A1462, Revision
3, dated May 20, 2004.

    Note 3:  For hanger fittings and center link assemblies marked
and part marked in production, as specified in Part 2 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
71A1462, Revision 3, dated May 20, 2004, the actions specified in
paragraph (n)(2) of this AD do not apply.

Alternative Methods of Compliance (AMOCs)

    (o) The certification office specified in paragraph (o)(1) or
(o)(2) of this AD, as applicable, has the authority to approve AMOCs
for paragraphs (i) and (j) of this AD, if requested using the
procedures found in 14 CFR 39.19.
    (1) For the structure identified in paragraph (i)(2) of this AD:
The Manager, Engine Certification Office (ECO), FAA. Send
information to ATTN: Antonio Cancelliere, Aerospace Engineer, ANE-
141, FAA, ECO, 12 New England Executive Park, Burlington, MA 01803-
5299; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.
    (2) For the structure identified in paragraph (i)(3) of this AD:
The Manager, Seattle Aircraft Certification Office (ACO), FAA. Send
information to ATTN: Alan Pohl, Aerospace Engineer, Airframe Branch,
ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.
Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-
<EMAIL_ADDRESS>    (3) 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 principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
    (4) An AMOC that provides an acceptable level of safety may be
used for any repair required by paragraph (i)(3) of this AD if it is
approved by 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.

    Issued in Renton, Washington, on December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
Peter A. White,
Assistant Directorate Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 2011-367 Filed 1-10-11; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 84, Number 228 (Tuesday, November 26, 2019)]
[Proposed Rules]
[Pages 65034-65036]
[FR Doc No: 2019-25574]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0875; Product Identifier 2019-NM-143-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain The Boeing Company Model 747-400 series airplanes. This
proposed AD was prompted by a report of a certain modification that
causes interference with inspections that are intended to detect
fatigue cracks. This proposed AD would require repetitive low frequency
eddy current (LFEC) inspections of a certain fuselage upper skin lap
splice for cracks, repetitive high frequency eddy current (HFEC)
inspections of a certain fuselage upper skin lap splice for cracks, and
applicable on-condition actions. The FAA is proposing this AD to
address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by January 10,
2020.

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 https://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 Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600;
telephone<PHONE_NUMBER>; internet https://www.myboeingfleet.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<PHONE_NUMBER>. It
is also available on the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2019-0875.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0875; 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 is listed above.
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites 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-2019-0875;
Product Identifier 2019-NM-143-AD'' at the beginning of your comments.
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this NPRM. The agency
will consider all comments received by the closing date and may amend
this NPRM because of those comments.
    The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide.
The agency will also post a report summarizing each substantive verbal
contact received about this proposed AD.

Discussion

    The FAA has received a report indicating that installation of a
fuselage modification (Mod) doubler common to station (STA) 1640 to STA
1820 at stringer (STR)-34 and STR-40, done as

part of a The Boeing Company Model 747-400BCF conversion, interferes
with existing required inspections, which are intended to detect
fatigue cracks. As a result, the existing inspections, which are
required by AD 2008-16-14, Amendment 39-15632 (73 FR 47035, August 13,
2008) (``AD 2008-16-14''), do not provide adequate fatigue crack
detection in the area of the modification. This condition, if not
addressed, could result in sudden decompression and loss of structural
integrity of the airplane.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Requirements Bulletin 747-53A2901 RB,
dated July 25, 2019. This service information describes procedures for
repetitive LFEC inspections of a certain fuselage upper skin lap splice
for cracks, repetitive HFEC inspections of a certain fuselage upper
skin lap splice for cracks, and applicable on-condition actions. On-
condition actions include repair. 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

    The FAA is proposing this AD because the agency evaluated all the
relevant information and determined the unsafe condition described
previously is likely to exist or develop in other products of the same
type design.

Proposed AD Requirements

    This proposed AD would require accomplishment of the actions
identified in Boeing Alert Requirements Bulletin 747-53A2901 RB, dated
July 25, 2019, described previously, except for any differences
identified as exceptions in the regulatory text of this proposed AD.
    For information on the procedures and compliance times, see this
service information at https://www.regulations.gov by searching for and
locating Docket No. FAA-2019-0875.

Explanation of Requirements Bulletin

    The FAA worked in conjunction with industry, under the
Airworthiness Directive Implementation Aviation Rulemaking Committee
(AD ARC), to enhance the AD system. One enhancement is a process for
annotating which steps in the service information are ``required for
compliance'' (RC) with an AD. Boeing has implemented this RC concept
into Boeing service bulletins.
    In an effort to further improve the quality of ADs and AD-related
Boeing service information, a joint process improvement initiative was
worked between the FAA and Boeing. The initiative resulted in the
development of a new process in which the service information more
clearly identifies the actions needed to address the unsafe condition
in the ``Accomplishment Instructions.'' The new process results in a
Boeing Requirements Bulletin, which contains only the actions needed to
address the unsafe condition (i.e., only the RC actions).

Costs of Compliance

    The FAA estimates that this proposed AD would affect 3 airplanes of
U.S. registry. The agency estimates the following costs to comply with
this proposed AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                Cost on U.S.
            Action                   Labor cost         Parts cost      Cost per product          operators
----------------------------------------------------------------------------------------------------------------
LFEC inspection...............  5 work-hours x $85                $0  $425 per inspection   $1,275 per
                                 per hour = $425 per                   cycle.                inspection cycle.
                                 inspection cycle.
HFEC inspection...............  5 work-hours x $85                 0  $425 per inspection   $1,275 per
                                 per hour = $425 per                   cycle.                inspection cycle.
                                 inspection cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data that would enable the
agency to provide cost estimates for the on-condition actions specified
in this proposed AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
    The FAA is 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

    The FAA 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) Will not affect intrastate aviation in Alaska, 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness
directive (AD):

The Boeing Company: Docket No. FAA-2019-0875; Product Identifier
2019-NM-143-AD.

(a) Comments Due Date

    The FAA must receive comments by January 10, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-400 series
airplanes, certificated in any category, as identified in Boeing
Alert Requirements Bulletin 747-53A2901 RB, dated July 25, 2019.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by a report of a certain modification that
causes interference with inspections that are intended to detect
fatigue cracks. The FAA is issuing this AD to address undetected
fatigue cracks, which could result in sudden decompression and loss
of structural integrity of the airplane.

(f) Compliance

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

(g) Required Actions

    Except as specified by paragraph (h) of this AD: At the
applicable times specified in the ``Compliance'' paragraph of Boeing
Alert Requirements Bulletin 747-53A2901 RB, dated July 25, 2019, do
all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
747-53A2901 RB, dated July 25, 2019.
    Note 1 to paragraph (g) of this AD: Guidance for accomplishing
the actions required by this AD can be found in Boeing Alert Service
Bulletin 747-53A2901, dated July 25, 2019, which is referred to in
Boeing Alert Requirements Bulletin 747-53A2901 RB, dated July 25,
2019.

(h) Exceptions to Service Information Specifications

    (1) For purposes of determining compliance with the requirements
of this AD: Where Boeing Alert Requirements Bulletin 747-53A2901 RB,
dated July 25, 2019, uses the phrase ``the original issue date of
the Requirements Bulletin 747-53A2901 RB,'' this AD requires using
``the effective date of this AD,'' except where Boeing Alert
Requirements Bulletin 747-53A2901 RB, dated July 25, 2019, uses the
phrase ``the original issue date of the Requirements Bulletin 747-
53A2901 RB'' in a note or flag note.
    (2) Where Boeing Alert Requirements Bulletin 747-53A2901 RB,
dated July 25, 2019, specifies contacting Boeing for repair
instructions: This AD requires doing the repair before further
flight using a method approved in accordance with the procedures
specified in paragraph (i) of this AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO 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
manager of the certification office, send it to the attention of the
person identified in paragraph (j)(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, modification, or alteration required by this AD
if it is approved by The Boeing Company Organization Designation
Authorization (ODA) that has been authorized by the Manager, Seattle
ACO Branch, FAA, to make those findings. To be approved, the repair
method, modification deviation, or alteration deviation must meet
the certification basis of the airplane, and the approval must
specifically refer to this AD.

(j) Related Information

    (1) For more information about this AD, contact Bill Ashforth,
Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200
South 216th St., Des Moines, WA 98198; phone and fax:<PHONE_NUMBER>;
email<EMAIL_ADDRESS>    (2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone<PHONE_NUMBER>; internet https://www.myboeingfleet.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<PHONE_NUMBER>.

    Issued in Des Moines, Washington, on November 15, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-25574 Filed 11-25-19; 8:45 am]
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