Airworthiness Directives; The Boeing Company Airplanes, 14977-14982 [2014-04819]
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14977
Rules and Regulations
Federal Register
Vol. 79, No. 52
Tuesday, March 18, 2014
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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
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SUMMARY:
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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 206–766–5680; 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 425–227–1221.
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–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: (425) 917–6590; email:
nancy.marsh@faa.gov.
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,
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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 midflaps; 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.
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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.
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.
Clarification Regarding the Installation
of Winglets
Aviation Partners Boeing (APB) stated
the installation of winglets per
Supplemental Type Certificate (STC)
ST01219SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/BE866B732F6CF31086257B
9700692796?Open
Document&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 (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/BE866B732F6CF31086257B
9700692796?Open
Document&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
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.
Conclusion
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
Action
Labor cost
Inspections [actions retained from existing AD
2010–15–08, Amendment 39–16374 (75 FR
43803, July 27, 2010)].
Inspections and measurements [actions retained
from existing AD 2010–15–08, Amendment
39–16374 (75 FR 43803, July 27, 2010)].
Overhauls [actions retained from existing AD
2010–15–08, Amendment 39–16374 (75 FR
43803, July 27, 2010)].
Replacements [actions retained from existing AD
2010–15–08, Amendment 39–16374 (75 FR
43803, July 27, 2010)].
12 work-hours × $85 per
hour = $1,020.
$0
$1,020 per inspection
cycle.
$665,040 per inspection
cycle.
2 work-hours × $85 per
hour = $170.
$0
$170 per inspection and
measurement cycle.
1 $7,000
Parts cost
Cost per product
Cost on U.S. operators
16 work-hours × $85 per
hour = $1,360.
1 $28,000
$29,360 per overhaul
cycle.
$110,840 per inspection
and measurement
cycle.
$19,142,720 per overhaul cycle.
16 work-hours × $85 per
hour = $1,360.
2 $60,000
$61,360 per replacement cycle.
$40,006,720 per replacement cycle.
per spindle; 4 spindles per airplane.
per spindle; 4 spindles per airplane.
2 $15,000
The new requirements of this AD add
no additional economic burden.
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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,
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‘‘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.
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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,
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(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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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.
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(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 (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/BE866B732F6CF31086257
B9700692796?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.
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14979
(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.
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.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(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.
(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
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(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
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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.
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(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.
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(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.
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
(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,
E:\FR\FM\18MRR1.SGM
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Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations
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)).
sroberts on DSK5SPTVN1PROD with RULES
(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
VerDate Mar<15>2010
17:18 Mar 17, 2014
Jkt 232001
(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–
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
14981
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: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(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: nancy.marsh@faa.gov.
(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.
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Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations
(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 206–544–5000, extension 1; fax
206–766–5680; 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
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0326; Directorate
Identifier 2012–NM–089–AD; Amendment
39–17786; AD 2014–05–13]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2004–12–
07 for certain The Boeing Company
Model 757 series airplanes equipped
with Rolls-Royce RB211 engines. AD
2004–12–07 required modification of
the nacelle strut and wing structure; and
for certain airplanes, repetitive detailed
inspections of certain aft bulkhead
fasteners for loose or missing fasteners,
and corrective action if necessary. For
sroberts on DSK5SPTVN1PROD with RULES
SUMMARY:
VerDate Mar<15>2010
17:18 Mar 17, 2014
Jkt 232001
certain other airplanes, AD 2004–12–07
required a one-time detailed inspection
of the middle gusset of the inboard side
load fitting for proper alignment, and
realignment if necessary; a one-time
eddy current inspection of certain
fastener holes for cracking, and repair if
necessary; and a detailed inspection of
certain fasteners for loose or missing
fasteners, and replacement with new
fasteners if necessary. This new AD
specifies a maximum compliance time
limit. This AD was prompted by reports
indicating that the actual operational
loads applied to the nacelle are higher
than the analytical loads that were used
during the initial design. We are issuing
this AD to prevent fatigue cracking in
primary strut structure and consequent
reduced structural integrity of the strut.
DATES: This AD is effective April 22,
2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the 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 July 21, 2004 (69 FR
33561, June 16, 2004).
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of January 3, 2000 (64 FR
66370, November 26, 1999).
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone: 206–544–5000, extension 1;
fax: 206–766–5680; 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 425–227–1221.
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–2013–
0326; 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
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, Seattle
Aircraft Certification Office (ACO),
FAA, 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6440;
fax: 425–917–6590; email:
Nancy.Marsh@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2004–12–07,
Amendment 39–13666 (69 FR 33561,
June 16, 2004). AD 2004–12–07 applied
to certain The Boeing Company Model
757 series airplanes equipped with
Rolls-Royce RB211 engines. The NPRM
published in the Federal Register on
April 15, 2013 (78 FR 22215). The
NPRM was prompted by reports
indicating that the actual operational
loads applied to the nacelle are higher
than the analytical loads that were used
during the initial design. The NPRM
proposed to retain the requirements of
AD 2004–12–07, which required
modification of the nacelle strut and
wing structure; and for certain
airplanes, repetitive detailed
inspections of certain aft bulkhead
fasteners for loose or missing fasteners,
and corrective action if necessary. For
certain other airplanes, AD 2004–12–07
required a one-time detailed inspection
of the middle gusset of the inboard side
load fitting for proper alignment, and
realignment if necessary; a one-time
eddy current inspection of certain
fastener holes for cracking, and repair if
necessary; and a detailed inspection of
certain fasteners for loose or missing
fasteners, and replacement with new
fasteners if necessary. The NPRM
proposed to specify a maximum
compliance time limit to modify the
nacelle strut and wing structure. We are
issuing this AD to prevent fatigue
cracking in primary strut structure and
consequent reduced structural integrity
of the strut.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal (78 FR 22215,
April 15, 2013) and the FAA’s response
to each comment.
Support for the NPRM (78 FR 22215,
April 15, 2013)
Boeing stated that it concurs with the
contents of the NPRM (78 FR 22215,
April 15, 2013).
E:\FR\FM\18MRR1.SGM
18MRR1
]]>Agencies
[Federal Register Volume 79, Number 52 (Tuesday, March 18, 2014)]
[Rules and Regulations]
[Pages 14977-14982]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04819]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules
and Regulations
[[Page 14977]]
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 206-766-5680; 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 425-227-1221.
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-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: (425) 917-6590; email: nancy.marsh@faa.gov.
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.
[[Page 14978]]
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 (https://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 (https://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,
[[Page 14979]]
(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 (https://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
[[Page 14980]]
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,
[[Page 14981]]
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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(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:
nancy.marsh@faa.gov.
(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.
[[Page 14982]]
(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 206-544-5000, extension 1; fax 206-766-5680;
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 202-741-6030, or go to: https://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
