Nachrichten für Luftfahrer 2014 Teil 2 (weicht ggf. von Druckversion ab)
times specified in paragraphs (o)(1) and (o)(2) of this AD: Do the detailed inspection for corrosion,
pitting, and cracking of the carriage spindle; magnetic particle inspection for cracking of the carriage
spindle; measurements of the spindle to determine if it meets the allowable minimum diameter;
overhauls of the carriage spindle; and applicable corrective actions; in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-57A1218, Revision 5, dated
February 9, 2009; or Boeing Alert Service Bulletin 737-57A1218, Revision 6, dated June 9, 2011. As
of the effective date of this AD, only Boeing Alert Service Bulletin 737-57A1218, Revision 6, dated
June 9, 2011, may be used to perform the actions specified in this paragraph. The applicable
corrective actions must be done before further flight. Repeat these actions thereafter at intervals not
to exceed every 12,000 flight cycles on the carriage spindle or every 8 years since first installation of
the carriage spindle on the airplane, whichever comes first. As of the effective date of this AD: For
any overhaul required by this paragraph, the carriage spindle must be overhauled in accordance with
the requirements of paragraph (m) of this AD.
(1) For Model 737-100, -200, -200C series airplanes: At the later of the times specified in
paragraphs (o)(1)(i) and (o)(1)(ii) of this AD.
(i) Before the accumulation of 12,000 total flight cycles on the carriage spindle since new or
overhauled, or within 8 years after the installation of the new or overhauled part, whichever comes
first.
(ii) Within 1 year after August 31, 2010 (the effective date of AD 2010-15-08, Amendment 39-
16374 (75 FR 43803, July 27, 2010)).
(2) For Model -300, -400, and -500 series airplanes: At the later of the times specified in
paragraphs (o)(2)(i) and (o)(2)(ii) of this AD.
(i) Before the accumulation of 12,000 total flight cycles on the carriage spindle since new or
overhauled, or within 8 years after the installation of the new or overhauled part, whichever comes
first.
(ii) Within 2 years after August 31, 2010 (the effective date of AD 2010-15-08, Amendment 39-
16374 (75 FR 43803, July 27, 2010)).
(p) Retained Carriage Spindle Replacement for Model 737-100, -200, and -200C Series
Airplanes
This paragraph restates the requirements of paragraph (p) of AD 2010-15-08, Amendment 39-
16374 (75 FR 43803, July 27, 2010), with revised service information and a shortened compliance
time. For Model 737-100, -200, -200C series airplanes: Replace the carriage spindle with a new or
documented (for which the service life, in total flight cycles, is known) carriage spindle, in
accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-57A1218,
Revision 5, dated February 9, 2009; or Boeing Alert Service Bulletin 737-57A1218, Revision 6,
dated June 9, 2011; at the earlier of the times specified in paragraphs (p)(1) and (p)(2) of this AD,
except as required by paragraph (r) of this AD. As of the effective date of this AD, only Boeing Alert
Service Bulletin 737-57A1218, Revision 6, dated June 9, 2011, may be used to perform the
replacement. Overhauling the carriage spindles does not zero-out the flight cycles. Total flight cycles
accumulate since new.
(1) At the later of the times specified in paragraphs (p)(1)(i) and (p)(1)(ii) of this AD.
(i) Before the accumulation of 48,000 total flight cycles on the new or overhauled carriage.
(ii) Within 3 years or 7,500 flight cycles after August 31, 2010 (the effective date of AD 2010-
15-08, Amendment 39-16374 (75 FR 43803, July 27, 2010)), whichever occurs first.
(2) Before the accumulation of 40,000 total flight cycles on the new or overhauled carriage or 6
months after the effective date of this AD, whichever occurs later.
(q) Retained Carriage Spindle Replacement for Model 737-300, -400, and -500 Series Airplanes
10
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.
11
(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.
(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-
12
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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on February 18, 2014.
Ross Landes,
Acting Manager, Transport Airplane Directorate,
Aircraft Certification Service.
13
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
38144 Braunschweig
D-2002-375R3 Fax: +49-531-2355-5298
email: ad@LBA.de
ROTAX Datum der Bekanntgabe: 04.04.2014
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugmotor
Inhaber der Musterzulassung: BRP-Powertrain GmbH & Co. KG
Hersteller: BRP-Powertrain GmbH & Co. KG, BRP-Rotax GmbH & Co. KG,
Bombardier-Rotax GmbH & Co. KG, Bombardier-Rotax GmbH
Muster: Rotax 912 A,
Rotax 912 F,
Rotax 912 S,
Rotax 914 F
Baureihen: Alle Rotax 912 A, 912 F, 912 S und 914 F Baureihen
Werknummern: Alle
Gerätenummer: 4585, 4592, 4618, EASA.E.121, EASA.E.122
Revisionsstand:
Diese LTA ersetzt D-2002-375/2 vom 06.03.2003
Airworthiness Directive der ausländischen Behörde:
ACG LTA Nr. 114R1 vom 04.12.2002
Betrifft:
Ölsystem, Triebwerk-Schmiersystem (oil system, engine lubrication system, ATA-Code 79-00-00) - angesaugte
Luft im Triebwerk-Schmiersystem durch das Durchdrehen des Propellers von Hand um mehr als eine Umdrehung
entgegen der normalen Propeller-Drehrichtung - ggf. kann dieser Fehler zu Schäden im Ventiltrieb und zum Ausfall
des Triebwerks im Fluge führen.
Maßnahmen und Fristen:
Da die erforderlichen Maßnahmen abgeschlossen sind, wird die LTA D-2002-375/2 mit sofortiger Wirkung
aufgehoben.
Zugehörige technische Dokumente:
Hinweis: Die Anwendung von nachfolgenden Ausgaben bzw. Revisionsständen der genannten zugehörigen technischen Dokumente ist zulässig, wenn dies nach
der Airworthiness Directive der ausländischen Behörde ausdrücklich gestattet ist oder wenn diese von der ausländischen Behörde in Bezug auf die referenzierte
Airworthiness Directive genehmigt worden sind.
Rotax Service Bulletin SB-912-038/914-024
Die sofortige Vollziehung dieses Bescheides wird gemäß § 80 Absatz 2 Satz 1 Nr. 4 der Verwaltungsgerichtsordnung (VwGO) angeordnet.
Begründung
Durch die vorgenannten Mängel ist die Lufttüchtigkeit des Luftfahrtgerätes derart beeinträchtigt, dass es nach Ablauf der genannten Fristen nur in Betrieb genom-
men werden darf, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind. Im Interesse der Sicherheit des Luftverkehrs, das in diesem Fall
das Interesse des Adressaten am Aufschub der angeordneten Maßnahmen überwiegt, ist es erforderlich, die sofortige Vollziehung dieser Lufttüchtigkeitsanweisung
anzuordnen.
Rechtsbehelfsbelehrung:
Gegen diese Verfügung kann innerhalb eines Monats nach Bekanntgabe Widerspruch eingelegt werden. Der Widerspruch ist schriftlich oder zur Niederschrift beim
Luftfahrt-Bundesamt, Hermann-Blenk-Str. 26, 38108 Braunschweig einzulegen. Ein eventueller Widerspruch hat keine aufschiebende Wirkung. Das Verwaltungsge-
richt Braunschweig, Am Wendentor 7, 38100 Braunschweig, kann auf Antrag nach § 80 Abs. 5 VwGO die aufschiebende Wirkung jedoch ganz oder teilweise wie-
derherstellen bzw. anordnen.
D-2002-375R3 Seite 1 von 1 134/2014
AUSTRIAN CIVIL AVIATION ADMINISTRATION
AIRWORTHINESS DIRECTIVE
No. 114R1
Rotax 912/914-Series, Addendum to the Operators Manual
1. Applicability: Rotax 912 A/F/S-Series, all S/N
Rotax 914 F-Series, all S/N
2. Subject: Cancellation of Austro Control AD114 and removal of the "Addendum to the
Operators Manual Rotax 912-Series/914-Series" regarding " turning of the propeller
against its normal direction of rotation"
3. Reason: By Rotax SB912-038/914-024 all Operator Manuals for ROTAX 912/914-series
engines have to be revised. All applicable limitations are therefore appropriately
published.
4. Action: Cancellation of Austro Control AD114, effective date November 1, 2002.
5. Compliance Date: Not applicable.
6. Accomplishment: The required actions have to be accomplished either by the manufacturer, or a
licensed/qualified person/organization, depending on national regulations.
Accomplishment of this AD has to be confirmed in the aircraft documents according
to national regulations.
7. Effective Date: January 1, 2003
Lufttüchtigkeitsanweisung Nr. 114R1 Geschäftszahl: FL206-1/119-02
Kennzeichen: ohne
Abt. Flugtechnik R o t a x 9 1 2 / 9 1 4 Handbuchergänzung
Blatt Zl. 2 Blatt 1
1. Betreff: Flugmotore Rotax 912-A/F/S Serie, alle S/N
Flugmotore Rotax 914-F Serie, alle S/N
2. Gegenstand: Aufhebung der LTA114 und Entfernung des "Beiblatts zum Betriebshandbuch Rotax 912-
Serie/914-Serie" betreffend "Zurückdrehen des Propellers".
3. Anlaß: Mit Ausgabe des Rotax SB912-038/914-024 sind die Betriebshandbücher für ROTAX
912/914-Serie Triebwerke zu revidieren. Alle notwendigen Limitierungen sind dadurch
entsprechend veröffentlicht.
4. Maßnahmen: Aufhebung der LTA114 mit Gültigkeitsdatum 1. November 2002.
5. Termine: Keine
6. Durchführung: Die Maßnahmen sind vom Hersteller oder von berechtigten Personen/Organisationen in
Übereinstimmung mit den jeweiligen nationalen luftfahrtbehördlichen Vorschriften
durchzuführen und entsprechend zu dokumentieren.
7. Datum des Inkrafttretens: 1. Jänner 2003
Bearb.: KEL Datum: 4. Dezember 2002
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2008-227R2 38144 Braunschweig
FAA AD 2014-05-21 - Amdt. 39-17794 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: Gemäß Boeing Service Bulletin 737-53A1200 Revision 2 vom 12.09.2012
Gerätenummer: 2823, EASA.IM.A.120, FAA TCDS A16WE
Revisionsstand:
Diese LTA ersetzt D-2008-227R1 vom 24.01.2013
Airworthiness Directive der ausländischen Behörde:
FAA AD 2014-05-21 - Amdt. 39-17794
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 2008-227R2 ge-
führt.
Betrifft:
(ATA 53) Fuselage - Forward Entry and Forward Galley Service Doors Upper and Lower Hinge Cutouts -
Inspection / Repair
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 2014-05-21 - Amdt. 39-17794 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-2008-227R2 Seite 1 von 1 181/2014
[Federal Register Volume 79, Number 52 (Tuesday, March 18, 2014)]
[Rules and Regulations]
[Pages 14992-14996]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04838]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0327; Directorate Identifier 2011-NM-161-AD; Amendment 39-17794;
AD 2014-05-21]
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) 2008-11-04 for all The Boeing
Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2008-11-04
required repetitive inspections for cracking in and around the upper and lower hinge cutouts of the
forward entry and forward galley service doorways, and corrective actions if necessary. This new AD
reduces the inspection threshold for cracking in and around the galley service doorway hinge cutouts,
adds inspections of certain repaired structure at the forward entry and galley service doorway upper
and lower hinge cutouts, expands the inspection area at the forward entry and galley service doorway
upper and lower hinge cutouts, and removes certain airplanes from the applicability. This AD was
prompted by multiple reports of cracks in the skin and/or bear strap at the forward galley service
doorway hinge cutouts, and multiple reports of cracking under the repairs installed at the hinge
cutouts. We are issuing this AD to detect and correct such cracking, which could result in rapid
decompression of the airplane.
DATES: This AD is effective April 22, 2014.
The Director of the Federal Register approved the incorporation by reference of a certain
publication listed in this AD as of April 22, 2014.
The Director of the Federal Register approved the incorporation by reference of a certain other
publication listed in this AD as of June 25, 2008 (73 FR 29421, May 21, 2008).
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;
phone: 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.
1
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-2013-0327; 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: Alan Pohl, Aerospace Engineer, Airframe
Branch, ANM-120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW.,
Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: Alan.Pohl@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD
2008-11-04, Amendment 39-15526 (73 FR 29421, May 21, 2008). AD 2008-11-04 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 April 16, 2013 (78 FR 22439). The NPRM was prompted by
multiple reports of cracks in the skin and/or bear strap at the forward galley service doorway hinge
cutouts, and multiple reports of cracking under the repairs installed at the hinge cutouts. The NPRM
proposed to reduce the inspection threshold for cracking in and around the galley service doorway
hinge cutouts, add inspections of certain repaired structure at the forward entry and galley service
doorway upper and lower hinge cutouts, expand the inspection area at the forward entry and galley
service doorway upper and lower hinge cutouts, and remove certain airplanes from the applicability.
We are issuing this AD to detect and correct such cracking, which could result in rapid
decompression 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 22439, April 16, 2013) and the FAA's response to
each comment.
Request to Add Service Information
Southwest Airlines (SWA) and Boeing requested we add a provision to the NPRM (78 FR
22439, April 16, 2013) to specify that performing a repair in accordance with ''Boeing 737-300/ -
400/-500 Structural Repair Manual (SRM) 53-10-01, Repair 14 and Repair 15'' is considered
terminating action for the requirements of paragraph (j) of the NPRM for the repaired location.
Boeing stated that the repairs are in the referenced SRM, and those repairs incorporate the procedures
specified in Note 10 of paragraph 3.A., ''General Information,'' of the Accomplishment Instructions of
Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012.
We agree that certain SRM repairs meet the conditions specified in Note 10 of paragraph 3.A.,
''General Information,'' of the Accomplishment Instructions of Boeing Service Bulletin 737-53A1200,
Revision 2, dated September 12, 2012. However, to include SRM repairs in this final rule would
unnecessarily delay issuance of the final rule. Boeing may apply for a global alternative method of
compliance (AMOC) on behalf of the affected operators in accordance with the procedures specified
in paragraph (p) of this final rule. We have not changed this final rule in this regard.
2
