[Federal Register Volume 79, Number 52 (Tuesday, March 18, 2014)]
[Rules and Regulations]
[Pages 14977-14982]
[FR Doc No: 2014-04819]

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Rules and Regulations
                                                Federal Register
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Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules
and Regulations

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0542; Directorate Identifier 2011-NM-162-AD;
Amendment 39-17785 AD 2014-05-12]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2010-15-08 for
all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500
series airplanes. AD 2010-15-08 required repetitive inspections for
discrepancies of each carriage spindle of the outboard mid-flaps;
repetitive gap checks of the inboard and outboard carriages of the
outboard mid-flaps to detect fractured carriage spindles; measuring to
ensure that any new or serviceable carriage spindle meets minimum
allowable diameter measurements taken at three locations; repetitive
inspections, measurements, and overhaul of the carriage spindles;
replacement of any carriage spindle when it has reached its maximum
life limit; and corrective actions if necessary. This new AD requires
reducing the life limit of the carriages, reducing the repetitive
interval for certain inspections and gap checks for certain carriages.
This new AD also adds an option, for certain replacements, of doing an
inspection, and related investigative and corrective actions if
necessary. This AD was prompted by a report of failure of both flap
carriages. We are issuing this AD to detect and correct cracked,
corroded, or fractured carriage spindles, which could lead to severe
flap asymmetry, and could result in reduced control or loss of
controllability of the airplane.

DATES: This AD is effective April 22, 2014.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 22,
2014.
    The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of August
31, 2010 (75 FR 43803, July 27, 2010).

ADDRESSES: For service information identified in this 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>; 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 by searching for and locating Docket No. FAA-2014-
05-12 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 AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: (425) 917-
6440; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2010-15-08, Amendment 39-16374 (75 FR 43803,
July 27, 2010). AD 2010-15-08 applied to all The Boeing Company Model
737-100, -200, -200C, -300, -400, and -500 series airplanes. The NPRM
published in the Federal Register on July 1, 2013 (78 FR 39193). The
NPRM was prompted by a report of failure of both flap carriages. The
NPRM proposed to continue to require repetitive inspections for
discrepancies of each carriage spindle of the outboard mid-flaps;
repetitive gap checks of the inboard and outboard carriages of the
outboard mid-flaps to detect fractured carriage spindles; measuring to
ensure that any new or serviceable carriage spindle meets minimum
allowable diameter measurements taken at three locations; repetitive
inspections, measurements, and overhaul of the carriage spindles;
replacement of any carriage spindle when it has reached its maximum
life limit; and corrective actions if necessary. The NPRM also proposed
to require reducing the life limit of the carriages, reducing the
repetitive interval for certain inspections and gap checks for certain
carriages. The NPRM also proposed to add an option, for certain
replacements, of doing an inspection, and related investigative and
corrective actions if necessary. We are issuing this AD to detect and
correct cracked, corroded, or fractured carriage spindles, which could
lead to severe flap asymmetry, and could result in reduced control or
loss of controllability of the airplane.

Comments

    We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(78 FR 39193, July 1, 2013) and the FAA's response to each comment.

Request to Revise Note

    Boeing requested we revise note 1 to paragraph (m) of the NPRM (78
FR 39193, July 1, 2013) to read, ``. . . Boeing (737) Standard Overhaul
Practices Manual (SOPM), Revision 25 or later.'' Boeing stated that as
its production standard changes, the SOPM is revised each time the SOPM
is updated. Boeing stated that a global alternative method of
compliance (AMOC) is required each time the SOPM is revised and this
generates AMOC activity that does not enhance fleet safety.

    We disagree to revise Note 1 to paragraph (m) of this final rule
because the text in Note 1 is informational guidance and does not
relieve the requirement in paragraph (m) to obtain approval for the
method used to apply plating, regardless of what revision of the SOPM
is specified. We have not changed this final rule in this regard.

Request to Revise Requirement for Plating

    Boeing requested the following requirement in paragraph (m)(3) of
the NPRM (78 FR 39193, July 1, 2013) be removed, ``The carriage must
not be plated using any high velocity oxygen fuel (HVOF) thermal spray
process.'' Boeing stated AD 2011-04-10, Amendment 39-16609 (76 FR 9498,
February 18, 2011), and AD 2012-13-07, Amendment 39-17109 (77 FR 39153,
July 2, 2012), required diligent inspection of HVOF coated carriages.
Boeing stated that inspections to date have only found minor corrosion,
well in advance of a potential unsafe condition. Boeing stated
requiring carriages to be converted to nickel [plating] does not
enhance fleet safety.
    We disagree to remove the requested phrase. The restriction against
future application of HVOF plating of the flap carriages was
coordinated and agreed to by The Boeing Company prior to issuance of
the NPRM (78 FR 39193, July 1, 2013). Service experience has shown that
the HVOF coating has insufficient reliability, therefore the
restriction is necessary. We have not changed this final rule in this
regard.

Clarification Regarding the Installation of Winglets

    Aviation Partners Boeing (APB) stated the installation of winglets
per Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?OpenDocument&Highlight=st01219se) does
not affect the accomplishment of the manufacturer's service
instructions.
    We agree with APB's statement that the installation of winglets as
specified in STC ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?OpenDocument&Highlight=st01219se) does
not affect accomplishment of the requirements of this AD, and for
airplanes on which STC ST01219SE is installed, a ``change in product''
(AMOC) approval request is not necessary to comply with the
requirements of section 39.17 of the Federal Aviation Regulations (14
CFR 39.17). We have redesignated paragraph (c) of the NPRM (78 FR
39193, July 1, 2013) as (c)(1) and added this provision in new
paragraph (c)(2) of this final rule.

Conclusion

    We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the
NPRM (78 FR 39193, July 1, 2013) for correcting the unsafe condition;
and
     Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 39193, July 1, 2013).
    We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 652 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspections [actions retained      12 work-hours x $85            $0  $1,020 per            $665,040 per
 from existing AD 2010-15-08,       per hour = $1,020.                 inspection cycle.     inspection cycle.
 Amendment 39-16374 (75 FR 43803,
 July 27, 2010)].
Inspections and measurements       2 work-hours x $85             $0  $170 per inspection   $110,840 per
 [actions retained from existing    per hour = $170.                   and measurement       inspection and
 AD 2010-15-08, Amendment 39-                                          cycle.                measurement cycle.
 16374 (75 FR 43803, July 27,
 2010)].
Overhauls [actions retained from   16 work-hours x $85   \1\ $28,000  $29,360 per overhaul  $19,142,720 per
 existing AD 2010-15-08,            per hour = $1,360.                 cycle.                overhaul cycle.
 Amendment 39-16374 (75 FR 43803,
 July 27, 2010)].
Replacements [actions retained     16 work-hours x $85   \2\ $60,000  $61,360 per           $40,006,720 per
 from existing AD 2010-15-08,       per hour = $1,360.                 replacement cycle.    replacement cycle.
 Amendment 39-16374 (75 FR 43803,
 July 27, 2010)].
----------------------------------------------------------------------------------------------------------------
\1\ $7,000 per spindle; 4 spindles per airplane.
\2\ $15,000 per spindle; 4 spindles per airplane.

    The new requirements of this AD add no additional economic burden.

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 AD will not have federalism
implications under Executive Order 13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866,

    (2) Is not a ``significant rule'' under 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.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD)
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), and adding
the following new AD:

2014-05-12 The Boeing Company: Amendment 39-17785; Docket No. FAA-
2013-0542; Directorate Identifier 2011-NM-162-AD.

(a) Effective Date

    This AD is effective April 22, 2014.

(b) Affected ADs

    This AD supersedes AD 2010-15-08, Amendment 39-16374 (75 FR
43803, July 27, 2010).

(c) Applicability

    (1) This AD applies to all The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes, certificated in
any category.
    (2) Installation of Supplemental Type Certificate (STC)
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?OpenDocument&Highlight=st01219se)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01219SE is
installed, a ``change in product'' alternative method of compliance
(AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17.

(d) Subject

    Air Transport Association (ATA) of America Code 57: Wings.

(e) Unsafe Condition

    This AD was prompted by a report of failure of both flap
carriages. We are issuing this AD to detect and correct cracked,
corroded, or fractured carriage spindles, which could lead to severe
flap asymmetry, and could result in reduced control or loss of
controllability of the airplane.

(f) Compliance

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

(g) Compliance Times for Paragraphs (h) and (j) of This AD

    This paragraph restates the requirements of paragraph (g) of AD
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with
revised service information that shortens the compliance times for
certain inspections. The tables in paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated
November 25, 2003; and Boeing Service Bulletin 737-57A1277, Revision
3, dated May 16, 2012; specify the compliance times for paragraphs
(g) through (k) of this AD. For carriage spindles that have
accumulated the number of flight cycles or years in service
specified in the ``Threshold'' column of the tables in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1277,
Revision 1, dated November 25, 2003, accomplish the gap check,
nondestructive test (NDT) inspection, and general visual inspection
specified in paragraphs (h) and (j) of this AD within the
corresponding interval after December 4, 2003 (the effective date AD
2003-24-08, Amendment 39-13337 (68 FR 67027, December 1, 2003)), as
specified in the ``Interval'' column of the tables in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-57A1277,
Revision 1, dated November 25, 2003, except as specified in
paragraph (g)(1) or (g)(2) of this AD. Repeat the gap check, NDT,
and general visual inspections at the intervals specified in the
``Interval'' column of the tables in paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated
November 25, 2003, except as specified in paragraph (g)(1) and
(g)(2) of this AD. As of the effective date of this AD, accomplish
the gap check, NDT inspection, and general visual inspections
specified in paragraphs (h) and (j) of this AD within the
corresponding interval as specified in the ``Interval'' column of
the tables in paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-57A1277, Revision 1, dated November 25, 2003,
and thereafter at the intervals specified in Boeing Service Bulletin
737-57A1277, Revision 3, dated May 16, 2012, except as specified in
paragraphs (g)(1) and (g)(2) of this AD. Repeat the gap check, NDT,
and general visual inspections thereafter at the intervals specified
in the ``Interval'' column of the tables in paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 737-57A1277, Revision 3,
dated May 16, 2012, except as specified in paragraphs (g)(1) and
(g)(2) of this AD.
    (1) The gap check does not have to be done at the same time as
an NDT inspection; after doing an NDT inspection, the interval for
doing the next gap check may be measured from the NDT inspection.
    (2) As carriage spindles gain flight cycles or years in service
and move from one category in the ``Threshold'' column to another,
they are subject to the repetitive inspection intervals
corresponding to the new threshold category.

(h) Retained Work Package 2: Gap Check

    This paragraph restates the requirements of paragraph (h) of AD
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with
revised service information. Perform a gap check of the inboard and
outboard carriage of the left and right outboard mid-flaps to
determine if there is a positive indication of a severed carriage
spindle, in accordance with Work Package 2 of paragraph 3.B., ``Work
Instructions,'' of Boeing Alert Service Bulletin 737-57A1277,
Revision 1, dated November 25, 2003; or Boeing Service Bulletin 737-
57A1277, Revision 3, dated May 16, 2012. As of the effective date of
this AD, only Boeing Service Bulletin 737-57A1277, Revision 3, dated
May 16, 2012, may be used to perform the actions specified in this
paragraph.

(i) Retained Work Package 2: Corrective Actions with New Optional
Actions and Exception

    This paragraph restates the requirements of paragraph (i) of AD
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with
revised service information and new optional actions and exception.
If there is a positive indication of a severed carriage spindle
during the gap check required by paragraph (h) of this AD, before
further flight, do the actions specified in paragraph (i)(1) or
(i)(2) of this AD, except for carriage spindles on which an
ultrasonic inspection has been done in accordance with the ``Work
Instructions'' of Boeing Service Bulletin 737-57A1277, Revision 3,
dated May 16, 2012; and the spindle has been confirmed not to be
severed, no further actions are required by this paragraph for that
carriage spindle.
    (1) Remove the carriage spindle and install a new or serviceable
carriage spindle, in accordance with the ``Work Instructions'' of
any service bulletin specified in paragraph (i)(1)(i), (i)(1)(ii),
(i)(1)(iii), or (i)(1)(iv) of this AD. As of the effective date of
this AD, only Boeing Service Bulletin 737-57A1277, Revision 3, dated
May 16, 2012, may be used to perform the actions specified in this
paragraph.
    (i) Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated
November 25, 2003.
    (ii) Boeing Service Bulletin 737-57A1277, Revision 3, dated May
16, 2012.
    (iii) Boeing Alert Service Bulletin 737-57A1218, Revision 5,
dated February 9, 2009.
    (iv) Boeing Alert Service Bulletin 737-57A1218, Revision 6,
dated June 9, 2011.
    (2) Do a detailed inspection of the spindle to determine if
there is corrosion, cracking, or a severed spindle, and, before
further flight, do all related investigative and corrective actions,
in accordance with the ``Work Instructions'' of Boeing Alert Service
Bulletin 737-57A1277, Revision 1, dated November 25, 2003; or Boeing
Service

Bulletin 737-57A1277, Revision 3, dated May 16, 2012. If, during the
detailed inspection described in paragraph 4.b. of Work Package 2 of
Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated
November 25, 2003; or Boeing Alert Service Bulletin 737-57A1277,
Revision 3, dated May 16, 2012; a carriage spindle is found not to
be severed, and no corrosion and no cracking is present, it can be
reinstalled on the outboard mid-flap, in accordance with any service
bulletin specified in paragraph (i)(2)(i), (i)(2)(ii), (i)(2)(iii),
or (i)(2)(iv) of this AD. As of the effective date of this AD, only
Boeing Service Bulletin 737-57A1277, Revision 3, dated May 16, 2012,
may be used to perform the actions specified in this paragraph.
    (i) Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated
November 25, 2003.
    (ii) Boeing Service Bulletin 737-57A1277, Revision 3, dated May
16, 2012.
    (iii) Boeing Alert Service Bulletin 737-57A1218, Revision 5,
dated February 9, 2009.
    (iv) Boeing Alert Service Bulletin 737-57A1218, Revision 6,
dated June 9, 2011.

(j) Retained Work Package 1: NDT (Ultrasonic) and General Visual
Inspections

    This paragraph restates the requirements of paragraph (j) of AD
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with
revised service information. Perform an NDT (ultrasonic) inspection
and general visual inspection for each carriage spindle of the left
and right outboard mid-flaps to detect cracks, corrosion, or severed
carriage spindles, in accordance with ``Work Package 1'' of the
``Work Instructions'' of Boeing Alert Service Bulletin 737-57A1277,
Revision 1, dated November 25, 2003; or Boeing Service Bulletin 737-
57A1277, Revision 3, dated May 16, 2012. As of the effective date of
this AD, only Boeing Service Bulletin 737-57A1277, Revision 3, dated
May 16, 2012, may be used to perform the actions specified in this
paragraph.

(k) Retained Work Package 1: Corrective Actions and New Optional Action

    This paragraph restates the requirements of paragraph (k) of AD
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with
revised service information and new optional action. If any
corroded, cracked, or severed carriage spindle is found during any
inspection required by paragraph (j) of this AD: Before further
flight, do the actions specified in paragraph (k)(1) or (k)(2) of
this AD.
    (1) Remove the carriage spindle and install a new or serviceable
carriage spindle, in accordance with any service bulletin identified
in paragraph (k)(1)(i), (k)(1)(ii), (k)(1)(iii), or (k)(1)(iv) of
this AD. As of the effective date of this AD, only Boeing Service
Bulletin 737-57A1277, Revision 3, dated May 16, 2012, may be used to
perform the actions specified in this paragraph.
    (i) Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated
November 25, 2003.
    (ii) Boeing Service Bulletin 737-57A1277, Revision 3, dated May
16, 2012.
    (iii) Boeing Alert Service Bulletin 737-57A1218, Revision 5,
dated February 9, 2009.
    (iv) Boeing Alert Service Bulletin 737-57A1218, Revision 6,
dated June 9, 2011.
    (2) Do a detailed inspection of the spindle to determine if
there is corrosion, cracking, or a severed spindle, in accordance
with the ``Work Instructions'' of Boeing Alert Service Bulletin 737-
57A1277, Revision 1, dated November 25, 2003; or Boeing Service
Bulletin 737-57A1277, Revision 3, dated May 16, 2012. If any
corrosion, cracking, or a severed spindle is found, before further
flight, install a new or serviceable carriage spindle, in accordance
with any service bulletin identified in paragraph (k)(1)(i),
(k)(1)(ii), (k)(1)(iii), or (k)(1)(iv) of this AD. As of the
effective date of this AD, only Boeing Service Bulletin 737-57A1277,
Revision 3, dated May 16, 2012, may be used to perform the actions
specified in this paragraph.

(l) Retained Parts Installation Limitation

    This paragraph restates the requirements of paragraph (l) of AD
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010). Except
as provided by paragraph (i) of this AD: As of December 4, 2003 (the
effective date AD 2003-24-08, Amendment 39-13337 (68 FR 67027,
December 1, 2003)), no person may install on any airplane a carriage
spindle that has been removed as required by paragraph (i) or (k) of
this AD, unless it has been overhauled in accordance with the ``Work
Instructions'' of the applicable service bulletin identified in
paragraph (l)(1), (l)(2), (l)(3), or (l)(4) of this AD. As of the
effective date of this AD, only Boeing Service Bulletin 737-57A1277,
Revision 3, dated May 16, 2012; or Boeing Alert Service Bulletin
737-57A1218, Revision 6, dated June 9, 2011; may be used to perform
the actions specified in this paragraph. To be eligible for
installation under this paragraph, the carriage spindle must have
been overhauled in accordance with the requirements of paragraph (m)
of this AD.
    (1) Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated
November 25, 2003.
    (2) Boeing Service Bulletin 737-57A1277, Revision 3, dated May
16, 2012.
    (3) Boeing Alert Service Bulletin 737-57A1218, Revision 5, dated
February 9, 2009.
    (4) Boeing Alert Service Bulletin 737-57A1218, Revision 6, dated
June 9, 2011.

(m) Retained Electrodeposited Nickel Plating With New Plating
Restrictions

    This paragraph restates the requirements of paragraph (m) of AD
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010) with
revised plating application procedures. As of the effective date of
this AD, during accomplishment of any overhaul specified in
paragraph (l) or (o) of this AD, follow the requirements specified
in paragraphs (m)(1), (m)(2), and (m)(3) of this AD during
application of the plating to the carriage spindle, in accordance
with a method approved by the Manager, Seattle, Aircraft
Certification Office (ACO), FAA. 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.
    (1) The maximum deposition rate of the nickel plating in any one
plating/baking cycle must not exceed 0.002-inch-per-hour.
    (2) Begin the hydrogen embrittlement relief bake within 10 hours
after application of the nickel plating, or less than 24 hours after
the current was first applied to the part, whichever is first.
    (3) The carriage must not be plated using any high velocity
oxygen fuel (HVOF) thermal spray process.

    Note 1 to paragraph (m) of this AD: Guidance on the application
of nickel plating can be found in Chapter 20-42-09, Electrodeposited
Nickel Plating, of the Boeing (737) Standard Overhaul Practices
Manual, Revision 25, dated July 1, 2009.

(n) Retained Exception to Reporting Recommendations

    This paragraph restates the provisions of paragraph (n) of AD
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with
revised service information. Although Boeing Alert Service Bulletin
737-57A1277, Revision 1, dated November 25, 2003; and Boeing Service
Bulletin 737-57A1277, Revision 3, dated May 16, 2012; recommend that
operators report inspection findings to the manufacturer, this AD
does not require reporting.

(o) Retained Inspections, Measurements, and Overhauls of the Carriage
Spindle With Clarification of Overhaul Restrictions

    This paragraph restates the requirements of paragraph (o) of AD
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010) with
clarification of overhaul restrictions. At the applicable times
specified in paragraphs (o)(1) and (o)(2) of this AD: Do the
detailed inspection for corrosion, pitting, and cracking of the
carriage spindle; magnetic particle inspection for cracking of the
carriage spindle; measurements of the spindle to determine if it
meets the allowable minimum diameter; overhauls of the carriage
spindle; and applicable corrective actions; in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
57A1218, Revision 5, dated February 9, 2009; or Boeing Alert Service
Bulletin 737-57A1218, Revision 6, dated June 9, 2011. As of the
effective date of this AD, only Boeing Alert Service Bulletin 737-
57A1218, Revision 6, dated June 9, 2011, may be used to perform the
actions specified in this paragraph. The applicable corrective
actions must be done before further flight. Repeat these actions
thereafter at intervals not to exceed every 12,000 flight cycles on
the carriage spindle or every 8 years since first installation of
the carriage spindle on the airplane, whichever comes first. As of
the effective date of this AD: For any overhaul required by this
paragraph, the carriage spindle must be overhauled in accordance
with the requirements of paragraph (m) of this AD.
    (1) For Model 737-100, -200, -200C series airplanes: At the
later of the times specified in paragraphs (o)(1)(i) and (o)(1)(ii)
of this AD.
    (i) Before the accumulation of 12,000 total flight cycles on the
carriage spindle since new or overhauled, or within 8 years after
the installation of the new or overhauled part, whichever comes
first.
    (ii) Within 1 year after August 31, 2010 (the effective date of
AD 2010-15-08,

Amendment 39-16374 (75 FR 43803, July 27, 2010)).
    (2) For Model -300, -400, and -500 series airplanes: At the
later of the times specified in paragraphs (o)(2)(i) and (o)(2)(ii)
of this AD.
    (i) Before the accumulation of 12,000 total flight cycles on the
carriage spindle since new or overhauled, or within 8 years after
the installation of the new or overhauled part, whichever comes
first.
    (ii) Within 2 years after August 31, 2010 (the effective date of
AD 2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010)).

(p) Retained Carriage Spindle Replacement for Model 737-100, -200, and
-200C Series Airplanes

    This paragraph restates the requirements of paragraph (p) of AD
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with
revised service information and a shortened compliance time. For
Model 737-100, -200, -200C series airplanes: Replace the carriage
spindle with a new or documented (for which the service life, in
total flight cycles, is known) carriage spindle, in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-57A1218, Revision 5, dated February 9, 2009; or Boeing Alert
Service Bulletin 737-57A1218, Revision 6, dated June 9, 2011; at the
earlier of the times specified in paragraphs (p)(1) and (p)(2) of
this AD, except as required by paragraph (r) of this AD. As of the
effective date of this AD, only Boeing Alert Service Bulletin 737-
57A1218, Revision 6, dated June 9, 2011, may be used to perform the
replacement. Overhauling the carriage spindles does not zero-out the
flight cycles. Total flight cycles accumulate since new.
    (1) At the later of the times specified in paragraphs (p)(1)(i)
and (p)(1)(ii) of this AD.
    (i) Before the accumulation of 48,000 total flight cycles on the
new or overhauled carriage.
    (ii) Within 3 years or 7,500 flight cycles after August 31, 2010
(the effective date of AD 2010-15-08, Amendment 39-16374 (75 FR
43803, July 27, 2010)), whichever occurs first.
    (2) Before the accumulation of 40,000 total flight cycles on the
new or overhauled carriage or 6 months after the effective date of
this AD, whichever occurs later.

(q) Retained Carriage Spindle Replacement for Model 737-300, -400, and
-500 Series Airplanes

    This paragraph restates the requirements of paragraph (q) of AD
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with
revised service information and a shortened compliance time. For
Model 737-300, -400, and -500 series airplanes: Replace the carriage
spindle with a new or documented (for which the service life, in
flight cycles, is known) carriage spindle, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
57A1218, Revision 5, dated February 9, 2009; or Boeing Alert Service
Bulletin 737-57A1218, Revision 6, dated June 9, 2011; at the later
of the times specified in paragraphs (q)(1) and (q)(2) of this AD,
except as required by paragraph (r) of this AD. As of the effective
date of this AD, only Boeing Alert Service Bulletin 737-57A1218,
Revision 6, dated June 9, 2011, may be used to perform the
replacement required by this paragraph. Overhauling the carriage
spindles does not zero-out the flight cycles. Total flight cycles
accumulate since new.
    (1) Before the accumulation of 40,000 total flight cycles on the
new or overhauled carriage.
    (2) Within 6 years or 15,000 flight cycles after August 31, 2010
(the effective date of AD 2010-15-08, Amendment 39-16374 (75 FR
43803, July 27, 2010)), whichever occurs first.

(r) Retained Carriage Spindle Replacement for Airplanes With an
Undocumented Carriage

    This paragraph restates the requirements of paragraph (r) of AD
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010). For
airplanes with an undocumented carriage: Do the applicable actions
specified in paragraph (p) or (q) of this AD at the applicable time
specified in paragraph (r)(1) or (r)(2) of this AD.
    (1) For Model 737-100, -200, -200C series airplanes: Do the
actions specified in paragraph (p) of this AD at the time specified
in paragraph (p)(1)(ii) of this AD.
    (2) For Model -300, -400, and -500 series airplanes: Do the
actions specified in paragraph (q) of this AD at the time specified
in paragraph (q)(2) of this AD.

(s) Retained Repetitive Replacements of Carriage Spindle

    This paragraph restates the requirements of paragraph (s) of AD
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), with
revised compliance times.
    (1) For airplanes on which the actions required by paragraph (p)
or (q) of this AD, as applicable, have been done as of the effective
date of this AD: Repeat the replacement of the carriage spindle
specified by paragraph (p) or (q) of this AD, as applicable, one
time at the later of the times specified in paragraphs (s)(1)(i) and
(s)(1)(ii) of this AD, and thereafter at intervals not to exceed
40,000 total flight cycles on the new or overhauled carriage
spindle.
    (i) Before the accumulation of 40,000 total flight cycles on the
new or overhauled carriage.
    (ii) Within 6 years or 15,000 flight cycles after August 31,
2010 (the effective date of AD 2010-15-08, Amendment 39-16374 (75 FR
43803, July 27, 2010)), whichever occurs first.
    (2) For airplanes on which the actions required by paragraph (p)
or (q) of this AD, as applicable, have not been done as of the
effective date of this AD: Repeat the replacement of the carriage
spindle specified by paragraph (p) or (q) of this AD, as applicable,
thereafter at intervals not to exceed 40,000 total flight cycles on
the new or overhauled carriage spindle.

(t) Exception to Compliance Time

    Where Boeing Service Bulletin 737-57A1277, Revision 3, dated May
16, 2012, and Boeing Alert Service Bulletin 737-57A1218, Revision 6,
dated June 9, 2011, specify a compliance time after the dates of
those service bulletins, this AD requires compliance within the
specified compliance time after the effective date of this AD.

(u) Credit for Previous Actions

    This paragraph provides credit for actions required by
paragraphs (g) through (s) of this AD, if those actions were
performed before the effective date of this AD using Boeing Alert
Service Bulletin 737-57A1277, Revision 2, dated June 9, 2011, which
is not incorporated by reference in this AD.

(v) 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 (w) 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, ACO, to make those
findings. For a repair method to be approved, the repair must meet
the certification basis of the airplane, and the approval must
specifically refer to this AD.
    (4) AMOCs previously approved in accordance with AD 2003-24-08,
Amendment 39-13377 (68 FR 67027, December 1, 2003), or AD 2010-15-
08, Amendment 39-16374 (75 FR 43803, July 27, 2010), are approved as
AMOCs for individual repairs are acceptable for compliance with the
corresponding provisions of this AD. All other existing AMOCs are
not acceptable.

(w) Related Information

    (1) For more information about this AD, contact Nancy Marsh,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>    (2) Service information identified in this AD that is not
incorporated by reference may be obtained at the addresses specified
in paragraphs (x)(5) and (x)(6) of this AD.

(x) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.

    (3) The following service information was approved for IBR on
April 22, 2014.
    (i) Boeing Alert Service Bulletin 737-57A1218, Revision 6, dated
June 9, 2011.
    (ii) Boeing Alert Service Bulletin 737-57A1277, Revision 3,
dated May 16, 2012.
    (4) The following service information was approved for IBR on
August 31, 2010 (75 FR 43803, July 27, 2010).
    (i) Boeing Alert Service Bulletin 737-57A1218, Revision 5, dated
February 9, 2009.
    (ii) Boeing Alert Service Bulletin 737-57A1277, Revision 1,
dated November 25, 2003.
    (5) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H-65, Seattle, Washington 98124-
2207; telephone<PHONE_NUMBER>, extension 1; fax<PHONE_NUMBER>;
Internet https://www.myboeingfleet.com.
    (6) You may view this service information at FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For
information on the availability of this material at the FAA, call
425-227-1221.
    (7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 18, 2014.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-04819 Filed 3-17-14; 8:45 am]
BILLING CODE 4910-13-P