Nachrichten für Luftfahrer 2014 Teil 2 (weicht ggf. von Druckversion ab)
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2002-371R4 38144 Braunschweig
FAA AD 2014-05-12 - Amdt. 39-17785 Fax: +49-531-2355-5298
email: ad@LBA.de
BOEING 08.04.2014
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: The Boeing Company
Hersteller: The Boeing Company
Muster: BOEING 737
Baureihen: 737-100, 737-200, 737-200C, 737-300, 737-400, 737-500
Werknummern: Alle
Gerätenummer: 2823, EASA.IM.A.120, FAA TCDS A16WE
Revisionsstand:
Diese LTA ersetzt D-2002-371R3 vom 22.01.2013
Airworthiness Directive der ausländischen Behörde:
FAA AD 2014-05-12 - Amdt. 39-17785
Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden
sind, wurden durch die EASA über die Entscheidung Nr. 02/2003 übernommen und sind somit ebenfalls
Airworthiness Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2002-371R4 ge-
führt.
Betrifft:
(ATA 57) Wings - Flap Carriage Spindles - Inspection / Overhaul / Replacement (Life Limit)
Anmerkungen:
Gemäß M.A.304 des Anhang I (Teil M) der Verordnung (EG) Nr. 2042/2003 dürfen Luftfahrzeuge
nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in den Betrieb genommen
werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsan-
weisung FAA AD 2014-05-12 - Amdt. 39-17785 herausgegeben oder per Entscheidung Nr. 02/2003
übernommen.
Gemäß § 14 Abs. 2 der Betriebsordnung für Luftfahrtgerät (LuftBO) sind diese Lufttüchtigkeitsan-
weisungen direkt in der Bundesrepublik Deutschland gültig und bedürfen keiner Umsetzung
durch das Luftfahrt-Bundesamt.
Mit Hilfe dieser Übersichtsseite veröffentlicht das Luftfahrt-Bundesamt ebenfalls die über § 14
Abs. 2 direkt gültige Lufttüchtigkeitsanweisungen der EASA in den Nachrichten für Luftfahrer und
im Internet unter www2.LBA.de/LTAs/. Dieser Service dient reinen Informationszwecken und liegt
keinem Verwaltungsverfahren zu Grunde. Rechtsmittel sind damit ausgeschlossen.
D-2002-371R4 Seite 1 von 1 179/2014
[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]
––––––––––––––––––––––––––––––––––
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,
1
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 http://www.regulations.gov by searching for
and locating Docket No. FAA-2014-05-12 or in person at the Docket Management Facility between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD,
the regulatory evaluation, any comments received, and other information. The address for the Docket
Office (phone: 800-647-5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue
SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW.,
Renton, WA 98057-3356; phone: (425) 917-6440; fax: (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.
2
We disagree to revise Note 1 to paragraph (m) of this final rule because the text in Note 1 is
informational guidance and does not relieve the requirement in paragraph (m) to obtain approval for
the method used to apply plating, regardless of what revision of the SOPM is specified. We have not
changed this final rule in this regard.
Request to Revise Requirement for Plating
Boeing requested the following requirement in paragraph (m)(3) of the NPRM (78 FR 39193,
July 1, 2013) be removed, ''The carriage must not be plated using any high velocity oxygen fuel
(HVOF) thermal spray process.'' Boeing stated AD 2011-04-10, Amendment 39-16609 (76 FR 9498,
February 18, 2011), and AD 2012-13-07, Amendment 39-17109 (77 FR 39153, July 2, 2012),
required diligent inspection of HVOF coated carriages. Boeing stated that inspections to date have
only found minor corrosion, well in advance of a potential unsafe condition. Boeing stated requiring
carriages to be converted to nickel [plating] does not enhance fleet safety.
We disagree to remove the requested phrase. The restriction against future application of HVOF
plating of the flap carriages was coordinated and agreed to by The Boeing Company prior to issuance
of the NPRM (78 FR 39193, July 1, 2013). Service experience has shown that the HVOF coating has
insufficient reliability, therefore the restriction is necessary. We have not changed this final rule in
this regard.
Clarification Regarding the Installation of Winglets
Aviation Partners Boeing (APB) stated the installation of winglets per Supplemental Type
Certificate (STC) ST01219SE
(http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B97006
92796?OpenDocument&Highlight=st01219se) does not affect the accomplishment of the
manufacturer's service instructions.
We agree with APB's statement that the installation of winglets as specified in STC ST01219SE
(http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B97006
92796?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:
3
Estimated Costs
Action Labor cost Parts Cost per product Cost on U.S.
cost operators
Inspections [actions retained from 12 work- $0 $1,020 per $665,040 per
existing AD 2010-15-08, hours × $85 inspection cycle inspection cycle.
Amendment 39-16374 (75 FR per hour =
43803, July 27, 2010)] $1,020
Inspections and measurements 2 work- $0 $170 per $110,840 per
[actions retained from existing AD hours × $85 inspection and inspection and
2010-15-08, Amendment 39-16374 per hour = measurement measurement
(75 FR 43803, July 27, 2010)] $170 cycle cycle.
1
Overhauls [actions retained from 16 work- $28,000 $29,360 per $19,142,720 per
existing AD 2010-15-08, hours × $85 overhaul cycle overhaul cycle.
Amendment 39-16374 (75 FR per hour =
43803, July 27, 2010)] $1,360
2
Replacements [actions retained from 16 work- $60,000 $61,360 per $40,006,720 per
existing AD 2010-15-08, hours × $85 replacement cycle replacement cycle.
Amendment 39-16374 (75 FR per hour =
43803, July 27, 2010)] $1,360
1
$7,000 per spindle; 4 spindles per airplane.
2
$15,000 per spindle; 4 spindles per airplane.
The new requirements of this AD add no additional economic burden.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation
Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III,
Section 44701, ''General requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices,
methods, and procedures the Administrator finds necessary for safety in air commerce. This
regulation is within the scope of that authority because it addresses an unsafe condition that is likely
to exist or develop on products identified in this rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States, on the relationship between the
national government and the States, or on the distribution of power and responsibilities among the
various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ''significant regulatory action'' under Executive Order 12866,
(2) Is not a ''significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
4
(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:
5
AIRWORTHINESS DIRECTIVE
FAA
www.faa.gov/aircraft/safety/alerts/
Aviation Safety
www.gpoaccess.gov/fr/advanced.html
2014-05-12 The Boeing Company: Amendment 39-17785; Docket No. FAA-2013-0542;
Directorate Identifier 2011-NM-162-AD.
(a) Effective Date
This AD is effective April 22, 2014.
(b) Affected ADs
This AD supersedes AD 2010-15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010).
(c) Applicability
(1) This AD applies to all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -
500 series airplanes, certificated in any category.
(2) Installation of Supplemental Type Certificate (STC) ST01219SE
(http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B97006
92796?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
6
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.
7
(ii) Boeing Service Bulletin 737-57A1277, Revision 3, dated May 16, 2012.
(iii) Boeing Alert Service Bulletin 737-57A1218, Revision 5, dated February 9, 2009.
(iv) Boeing Alert Service Bulletin 737-57A1218, Revision 6, dated June 9, 2011.
(2) Do a detailed inspection of the spindle to determine if there is corrosion, cracking, or a
severed spindle, and, before further flight, do all related investigative and corrective actions, in
accordance with the ''Work Instructions'' of Boeing Alert Service Bulletin 737-57A1277, Revision 1,
dated November 25, 2003; or Boeing Service Bulletin 737-57A1277, Revision 3, dated May 16,
2012. If, during the detailed inspection described in paragraph 4.b. of Work Package 2 of Boeing
Alert Service Bulletin 737-57A1277, Revision 1, dated November 25, 2003; or Boeing Alert Service
Bulletin 737-57A1277, Revision 3, dated May 16, 2012; a carriage spindle is found not to be severed,
and no corrosion and no cracking is present, it can be reinstalled on the outboard mid-flap, in
accordance with any service bulletin specified in paragraph (i)(2)(i), (i)(2)(ii), (i)(2)(iii), or (i)(2)(iv)
of this AD. As of the effective date of this AD, only Boeing Service Bulletin 737-57A1277, Revision
3, dated May 16, 2012, may be used to perform the actions specified in this paragraph.
(i) Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated November 25, 2003.
(ii) Boeing Service Bulletin 737-57A1277, Revision 3, dated May 16, 2012.
(iii) Boeing Alert Service Bulletin 737-57A1218, Revision 5, dated February 9, 2009.
(iv) Boeing Alert Service Bulletin 737-57A1218, Revision 6, dated June 9, 2011.
(j) Retained Work Package 1: NDT (Ultrasonic) and General Visual Inspections
This paragraph restates the requirements of paragraph (j) of AD 2010-15-08, Amendment 39-
16374 (75 FR 43803, July 27, 2010), with revised service information. Perform an NDT (ultrasonic)
inspection and general visual inspection for each carriage spindle of the left and right outboard mid-
flaps to detect cracks, corrosion, or severed carriage spindles, in accordance with ''Work Package 1''
of the ''Work Instructions'' of Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated
November 25, 2003; or Boeing Service Bulletin 737-57A1277, Revision 3, dated May 16, 2012. As
of the effective date of this AD, only Boeing Service Bulletin 737-57A1277, Revision 3, dated May
16, 2012, may be used to perform the actions specified in this paragraph.
(k) Retained Work Package 1: Corrective Actions and New Optional Action
This paragraph restates the requirements of paragraph (k) of AD 2010-15-08, Amendment 39-
16374 (75 FR 43803, July 27, 2010), with revised service information and new optional action. If any
corroded, cracked, or severed carriage spindle is found during any inspection required by paragraph
(j) of this AD: Before further flight, do the actions specified in paragraph (k)(1) or (k)(2) of this AD.
(1) Remove the carriage spindle and install a new or serviceable carriage spindle, in accordance
with any service bulletin identified in paragraph (k)(1)(i), (k)(1)(ii), (k)(1)(iii), or (k)(1)(iv) of this
AD. As of the effective date of this AD, only Boeing Service Bulletin 737-57A1277, Revision 3,
dated May 16, 2012, may be used to perform the actions specified in this paragraph.
(i) Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated November 25, 2003.
(ii) Boeing Service Bulletin 737-57A1277, Revision 3, dated May 16, 2012.
(iii) Boeing Alert Service Bulletin 737-57A1218, Revision 5, dated February 9, 2009.
(iv) Boeing Alert Service Bulletin 737-57A1218, Revision 6, dated June 9, 2011.
(2) Do a detailed inspection of the spindle to determine if there is corrosion, cracking, or a
severed spindle, in accordance with the ''Work Instructions'' of Boeing Alert Service Bulletin 737-
57A1277, Revision 1, dated November 25, 2003; or Boeing Service Bulletin 737-57A1277, Revision
3, dated May 16, 2012. If any corrosion, cracking, or a severed spindle is found, before further flight,
install a new or serviceable carriage spindle, in accordance with any service bulletin identified in
paragraph (k)(1)(i), (k)(1)(ii), (k)(1)(iii), or (k)(1)(iv) of this AD. As of the effective date of this AD,
only Boeing Service Bulletin 737-57A1277, Revision 3, dated May 16, 2012, may be used to perform
the actions specified in this paragraph.
8
(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
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