[Federal Register Volume 78, Number 126 (Monday, July 1, 2013)]
[Proposed Rules]
[Pages 39193-39198]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-15660]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0542; Directorate Identifier 2011-NM-162-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to all The Boeing Company Model 737-100, -200, -200C,
-300, -400, and -500 series airplanes. The existing AD currently
requires 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.
Since we issued that AD, we received a report of failure of both flap
carriages. This proposed AD would require reducing the life limit of
the carriages, reducing the repetitive interval for certain inspections
and gap checks for certain carriages. This proposed AD would also add
an option, for certain replacements, of doing an inspection, and
related investigative and corrective actions if necessary. We are
proposing 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: We must receive comments on this proposed AD by August 15, 2013.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this 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 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington. For information on the availability of
this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
[[Page 39194]]
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: 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: (425)917-6590; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0542;
Directorate Identifier 2011-NM-162-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On July 14, 2010, we issued AD 2010-15-08, Amendment 39-16374 (75
FR 43803, July 27, 2010), for all Model 737-100, -200, -200C, -300, -
400, and -500 series airplanes. That AD requires repetitive inspections
to find discrepancies (cracks, fractures, and corrosion) of each
carriage spindle of the left and right 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 carriages; replacement of any
carriage when it has reached its maximum life limit; and corrective
actions if necessary. That AD resulted from reports of fractures that
resulted from stress corrosion and pitting along the length of the
carriage spindle and spindle diameter. We issued that AD to detect and
correct cracked, corroded, or fractured carriage spindles, and to
prevent severe flap asymmetry, which could result in reduced control or
loss of controllability of the airplane.
Actions Since Existing AD (75 FR 43803, July 27, 2010) Was Issued
Since we issued AD 2010-15-08, Amendment 39-16374 (75 FR 43803,
July 27, 2010), we received a report of failure of both flap carriages
on an outboard flap of a Model 737 airplane, which indicates that life
limits and certain repetitive inspection intervals of the carriages
mandated by existing AD 2010-15-08 should be reduced.
Relevant Service Information
AD 2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010),
referred to Boeing Alert Service Bulletin 737-57A1277, Revision 1,
dated November 25, 2003; and Boeing Alert Service Bulletin 737-57A1218,
Revision 5, dated February 9, 2009; as the appropriate sources of
service information for the required actions. Boeing has since revised
these service bulletins.
We reviewed Boeing Service Bulletin 737-57A1277, Revision 3, dated
May 16, 2012, which describes reduced repetitive intervals for the non-
destructive test (NDT) ultrasonic inspection and general visual
inspection of the carriage spindle, and gap check measurements of the
inboard and outboard carriages.
The related investigative actions of Boeing Service Bulletin 737-
57A1277, Revision 3, dated May 16, 2012, include removing the carriage
from service and performing a detailed inspection for corrosion,
cracking, or a severed spindle; determining if there is damage that
would cause the midflap to move away from the carriage.
Corrective actions of Boeing Service Bulletin 737-57A1277, Revision
3, dated May 16, 2012, include installing a new or serviceable inboard
or outboard carriage of the outboard mid-flaps.
We also reviewed Boeing Alert Service Bulletin 737-57A1218,
Revision 6, dated June 9, 2011, which shortens the life limit and
compliance time for the replacement of spindles from 48,000 total
flight cycles to 40,000 total accumulated flight cycles.
The related investigative actions of Boeing Alert Service Bulletin
737-57A1218, Revision 6, dated June 9, 2011, include performing a
detailed inspection for corrosion and pitting, performing a magnetic
particle inspection for cracking, and measuring for minimum allowable
spindle diameter. Corrective actions of Boeing Alert Service Bulletin
737-57A1218, Revision 6, dated June 9, 2011, include installing a new
or serviceable inboard and outboard carriage of the outboard mid-flaps;
overhauling carriages to remove corrosion or repair damage; and
replacing any carriage that has cracking, or damage beyond the repair
limits for minimum allowable spindle diameters, or reached its life
limit.
Explanation of Changes to Existing Requirements of AD 2010-15-08,
Amendment 39-16374 (75 FR 43803, July 27, 2010)
Paragraphs (i) and (k) of existing AD 2010-15-08, Amendment 39-
16374 (75 FR 43803, July 27, 2010), require installing a new or
serviceable carriage spindle if certain conditions are found. In this
proposed AD, when these certain conditions are found, rather than
installing a new or serviceable carriage spindle, operators now have
the option to first do a detailed inspection to determine if there is
corrosion, cracking, or a severed spindle, and do related investigative
and corrective actions if necessary. Therefore, we revised paragraphs
(i) and (k) of this proposed AD, to include these optional actions. We
have also added an exception to paragraph (i) of this proposed AD to
specify that actions in that paragraph are not necessary for carriage
spindles on which an ultrasonic inspection of the spindle has been done
and the spindle has been confirmed not to be severed.
We have revised paragraph (m) of this AD to remove the reference to
Chapter 20-42-09, Electrodeposited Nickel Plating, of the Boeing (737)
Standard Overhaul Practices Manual, and we removed the reference that
as of August 31, 2010, the effective date of AD 2010-15-08, Amendment
39, 16374 (75 FR 438003) to use only Boeing (737) Standard Overhaul
Practices Manual, Revision 25, dated July 1, 2009.
Instead, application of nickel plating done in accordance with a
method approved by the Manager, Seattle Aircraft Certification Office
(ACO), FAA, is acceptable for compliance with the actions required by
paragraph (m) of this AD. We added Note 1 to paragraph (m) of this AD
to specify that 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.
[[Page 39195]]
We have also added paragraph (m)(3) to prohibit the application of
any plating to the carriage using any high velocity oxygen fuel (HVOF)
thermal spray process.
We have also clarified the compliance time for the repetitive
actions specified in paragraph (n) of AD 2010-15-08, Amendment 39-16374
(75 FR 43803, July 27, 2010).
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs.
Proposed AD Requirements
This proposed AD would retain all requirements of AD 2010-15-08,
Amendment 39-16374 (75 FR 43803, July 27, 2010). This proposed AD also
would require accomplishing the actions specified in the service
information described previously. This proposed AD would also shorten
certain compliance times.
Costs of Compliance
We estimate that this proposed AD affects 652 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections [retained actions from 12 work-hours x $85 $0 $1,020 per inspection $665,040 per inspection cycle.
existing AD 2010[dash]15[dash]08, per hour = $1,020. cycle.
Amendment 39[dash]16374 (75 FR
43803, July 27, 2010)].
Inspections and measurements 2 work-hours x $85 per 0 $170 per inspection $110,840 per inspection and measurement cycle
[retained actions from existing AD hour = $170. and measurement
2010[dash]15[dash]08, Amendment cycle..
39[dash]16374 (75 FR 43803, July
27, 2010)].
Overhauls [retained actions from 16 work-hours x $85 \1\28,000 $29,360 per overhaul $19,142,720 per overhaul cycle.
existing AD 2010[dash]15[dash]08, per hour = $1,360. cycle.
Amendment 39[dash]16374 (75 FR
43803, July 27, 2010)].
Replacements [retained actions from 16 work-hours x $85 \2\60,000 $61,360 per $40,006,720 per replacement cycle.
existing AD 2010[dash]15[dash]08, per hour = $1,360. replacement cycle.
Amendment 39[dash]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 proposed 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010), and adding
the following new AD:
The Boeing Company: Docket No. FAA-2013-0542; Directorate Identifier
2011-NM-162-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by August 15,
2013.
(b) Affected ADs
This AD supersedes AD 2010-15-08, Amendment 39-16374 (75 FR
43803, July 27, 2010).
(c) Applicability
This AD applies to all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 57: Wings.
[[Page 39196]]
(e) Unsafe Condition
This AD was prompted by reports of fractures that resulted from
stress corrosion and pitting along the length of the spindle and
spindle diameter, and a subsequent 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 39-16337 (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
paragraphs (g)(1) and (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 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 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.
[[Page 39197]]
(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
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 in paragraph (i) of this AD: As of December 4, 2003 (the
effective date AD 2003-24-08, Amendment 39-16337 (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
[[Page 39198]]
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 the Related Information
section of this AD. Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, 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: (425) 917-6440; fax: (425) 917-6590; email:
[email protected].
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; email
[email protected]; 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 425-227-1221.
Issued in Renton, Washington, on June 14, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-15660 Filed 6-28-13; 8:45 am]
BILLING CODE 4910-13-P