81 FR 1345 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 7 (January 12, 2016)

We propose to supersede Airworthiness Directive (AD) 2008-05- 06, which applies to certain The Boeing Company Model 737-100, -200, - 300, -400, and -500 series airplanes. AD 2008-05-06 currently requires repetitive inspections for fatigue cracking in the longitudinal floor beam web, upper chord, and lower chord located at certain body stations, and repair if necessary. Since we issued AD 2008-05-06, we have determined that certain repairs and preventive modifications of certain longitudinal floor beam webs inadvertently omitted installation of tapered fillers. Omission of the tapered fillers creates a preload condition that may promote undetected fatigue cracking and subsequent failure of certain longitudinal floor beams. For certain airplanes, this proposed AD would require an inspection to determine if tapered fillers are installed, and related investigative and corrective actions if necessary. We are proposing this AD to detect and correct fatigue cracking of the upper and lower chords and web of the longitudinal floor beams, which could result in rapid loss of cabin pressure.

[Federal Register Volume 81, Number 7 (Tuesday, January 12, 2016)]
[Proposed Rules]
[Pages 1345-1349]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-32851]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8131; Directorate Identifier 2015-NM-073-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2008-05-
06, which applies to certain The Boeing Company Model 737-100, -200, -
300, -400, and -500 series airplanes. AD 2008-05-06 currently requires 
repetitive inspections for fatigue cracking in the longitudinal floor 
beam web, upper chord, and lower chord

[[Page 1346]]

located at certain body stations, and repair if necessary. Since we 
issued AD 2008-05-06, we have determined that certain repairs and 
preventive modifications of certain longitudinal floor beam webs 
inadvertently omitted installation of tapered fillers. Omission of the 
tapered fillers creates a preload condition that may promote undetected 
fatigue cracking and subsequent failure of certain longitudinal floor 
beams. For certain airplanes, this proposed AD would require an 
inspection to determine if tapered fillers are installed, and related 
investigative and corrective actions if necessary. We are proposing 
this AD to detect and correct fatigue cracking of the upper and lower 
chords and web of the longitudinal floor beams, which could result in 
rapid loss of cabin pressure.

DATES: We must receive comments on this proposed AD by February 26, 
2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed rule, 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8131.

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-2015-
8131; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Alan Pohl, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax: 
425-917-6590; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-8131; 
Directorate Identifier 2015-NM-073-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On February 20, 2008, we issued AD 2008-05-06, Amendment 39-15400 
(73 FR 11538, March 4, 2008), for certain The Boeing Company Model 737-
100, -200, -300, -400, and -500 series airplanes. AD 2008-05-06 
requires repetitive inspections for fatigue cracking in the 
longitudinal floor beam web, upper chord, and lower chord located at 
certain body stations, and repair if necessary. AD 2008-05-06 refers to 
Boeing Service Bulletin 737-57-1296, dated June 13, 2007, as an 
appropriate source of service information for accomplishing the 
required actions. AD 2008-05-06 resulted from reports of cracks in the 
center wing box longitudinal floor beams, upper chord, and lower chord. 
We issued AD 2008-05-06 to detect and correct fatigue cracking of the 
upper and lower chords and web of the longitudinal floor beams, which 
could result in rapid loss of cabin pressure.

Actions Since AD 2008-05-06, Amendment 39-15400 (73 FR 11538, March 4, 
2008), Was Issued

    Since we issued AD 2008-05-06, Amendment 39-15400 (73 FR 11538, 
March 4, 2008), Boeing issued Boeing Service Bulletin 737-57-1296, 
Revision 1, dated September 26, 2012, which is an alternative method of 
compliance (AMOC) for the actions required by AD 2008-05-06. We have 
determined that Boeing Service Bulletin 737-57-1296, Revision 1, dated 
September 26, 2012, inadvertently omitted installation of tapered 
fillers during the repair and preventive modification of certain 
longitudinal floor beam webs. Omission of the tapered fillers creates a 
preload condition that may promote undetected fatigue cracking and 
subsequent failure of the longitudinal floor beams at buttock line (BL) 
24.82 and BL 45.57.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 737-57A1296, Revision 2, 
dated April 1, 2015. The service information describes procedures for 
various inspections for fatigue cracks in the longitudinal floor beam 
web, upper chord, and lower chord, located at the applicable body 
stations, repairs (including related investigative and corrective 
actions), and preventive modifications (including related investigative 
and corrective actions) that terminate the repetitive inspections. The 
service information also describes procedures for an inspection to 
determine if tapered fillers are installed, and related investigative 
and corrective actions. This service information is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section of this NPRM.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of these same type 
designs.

Proposed AD Requirements

    This proposed AD would retain all requirements of AD 2008-05-06, 
Amendment 39-15400 (73 FR 11538, March 4, 2008). This proposed AD would 
also require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between this Proposed AD and the Service Information.'' 
For information on the procedures and compliance

[[Page 1347]]

times, see this service information at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-8131.
    The phrase ``related investigative actions'' is used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that (1) are related to the primary action, and (2) further investigate 
the nature of any condition found. Related investigative actions in an 
AD could include, for example, inspections.
    The phrase ``corrective actions'' is used in this proposed AD. 
``Corrective actions'' are actions that correct or address any 
condition found. Corrective actions in an AD could include, for 
example, repairs.

Formatting and Other Changes Between AD 2008-05-06, Amendment 39-15400 
(73 FR 11538, March 4, 2008) and This Proposed AD

    Since AD 2008-05-06, Amendment 39-15400 (73 FR 11538, March 4, 
2008), was issued, the AD format has been revised, and certain 
paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have been redesignated in this proposed AD, as 
listed in the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
   Requirement in AD 2008-05-06,
 Amendment 39- 15400 (73 FR 11538,    Corresponding  requirement in this
           March 4, 2008)                        proposed AD
------------------------------------------------------------------------
             paragraph (f)                        paragraph (g)
             paragraph (g)                        paragraph (h)
------------------------------------------------------------------------

    In addition, airplane groups identified in Boeing Service Bulletin 
737-57-1296, dated June 13, 2007, which is referred to as the 
appropriate source of service information for accomplishing the actions 
required by AD 2008-05-06, Amendment 39-15400 (73 FR 11538, March 4, 
2008), do not, in all cases, match the airplane groups for Boeing Alert 
Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015, which is 
the appropriate source of service information for accomplishing the new 
actions specified in this proposed AD.
    Also, operators of Group 5 airplanes identified in Boeing Alert 
Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015, must 
contact the FAA for actions instead of accomplishing the actions 
specified in Boeing Alert Service Bulletin 737-57A1296, Revision 2, 
dated April 1, 2015. The procedures for inspections and corrective 
actions specified in Boeing Alert Service Bulletin 737-57A1296, 
Revision 2, dated April 1, 2015, do not apply to these airplanes (line 
numbers 1 through 291).

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 
1, 2015, specifies to contact the manufacturer for instructions on how 
to repair certain conditions, but this proposed AD would require 
repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections [retained actions    Up to 25 work-hours x                $0  $2,125 per          $1,385,500 per
 from AD 2008-05-06, Amendment    $85 per hour = $2,125                    inspection cycle.   inspection cycle.
 39-15400 (73 FR 11538, March     per inspection cycle.
 4, 2008)].
Tapered filler inspection [new   4 work-hours x $85 per                0  $340..............  $221,680.
 proposed action].                hour = $340.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspection. We 
have no way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                            Labor cost              Parts cost        Cost per product
----------------------------------------------------------------------------------------------------------------
Floor beam repair and optional          Up to 198 work[dash]hours x              \[1]\  Up to $16,830.
 preventative modification.              $85 per hour = $16,830.
Tapered filler repair.................  174 work[dash]hours x $85 per            \[1]\  $14,790.
                                         hour = $14,790.
----------------------------------------------------------------------------------------------------------------
\[1]\ We have received no definitive data that would enable us to provide parts cost estimates for the actions
  specified in this proposed AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and

[[Page 1348]]

responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2008-05-06, Amendment 39-15400 (73 FR 11538, March 4, 2008), and adding 
the following new AD:

The Boeing Company: Docket No. FAA-2015-8131; Directorate Identifier 
2015-NM-073-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by February 26, 
2016.

(b) Affected ADs

    This AD replaces AD 2008-05-06, Amendment 39-15400 (73 FR 11538, 
March 4, 2008).

(c) Applicability

    This AD applies to The Boeing Company Model 737-100, -200, -300, 
-400, and -500 series airplanes; certificated in any category; as 
identified in Boeing Alert Service Bulletin 737-57A1296, Revision 2, 
dated April 1, 2015.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by results from reports of cracks in the 
center wing box longitudinal floor beams, upper chord, and lower 
chord. We are issuing this AD to detect and correct fatigue cracking 
of the upper and lower chords and web of the longitudinal floor 
beams, which could result in rapid loss of cabin pressure.

(f) Compliance

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

(g) Retained Inspections With Revised Service Information and Revised 
Affected Airplanes

    This paragraph restates the requirements of paragraph (f) of AD 
2008-05-06, Amendment 39-15400 (73 FR 11538, March 4, 2008), with 
revised service information and revised affected airplanes. For 
Groups 1 through 4 airplanes identified in Boeing Alert Service 
Bulletin 737-57A1296, Revision 2, dated April 1, 2015, do the 
various inspections for fatigue cracks in the longitudinal floor 
beam web, upper chord, and lower chord, located at the applicable 
body stations specified in the Accomplishment Instructions of Boeing 
Service Bulletin 737-57-1296, dated June 13, 2007; or Boeing Alert 
Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015; by 
doing all the actions in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 737-57A1296, dated June 13, 
2007; or Boeing Alert Service Bulletin 737-57A1296, Revision 2, 
dated April 1, 2015; except as provided by paragraph (h) of this AD. 
Do the inspections at the time specified in paragraph (g)(1) or 
(g)(2) of this AD, as applicable. As of the effective date of this 
AD, only use Boeing Alert Service Bulletin 737-57A1296, Revision 2, 
dated April 1, 2015, for accomplishing the actions required by this 
paragraph.
    Note 1 to paragraphs (g) and (h) of this AD: The airplane groups 
identified in Boeing Service Bulletin 737-57-1296, dated June 13, 
2007, do not, in all cases, match the airplane groups identified in 
Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 
1, 2015 (Group 4 airplanes in Boeing Alert Service Bulletin 737-
57A1296, Revision 2, dated April 1, 2015 coincide with certain Group 
2 airplanes in Boeing Service Bulletin 737-57-1296, dated June 13, 
2007).
    (1) For Groups 1 and 2 airplanes, except for line numbers 1 
through 291, identified in Boeing Service Bulletin 737-57-1296, 
dated June 13, 2007: Do the inspections at the applicable initial 
compliance time listed in paragraph 1.E., ``Compliance,'' of Boeing 
Service Bulletin 737-57-1296, dated June 13, 2007, except where 
Boeing Service Bulletin 737-57-1296, dated June 13, 2007, specifies 
a compliance time after the date on the service bulletin, this AD 
requires compliance within the specified compliance time after April 
8, 2008 (the effective date of AD 2008-05-06, Amendment 39-15400 (73 
FR 11538, March 4, 2008)). Repeat the inspections thereafter at the 
intervals specified in paragraph 1.E., ``Compliance,'' of Boeing 
Service Bulletin 737-57-1296, dated June 13, 2007.
    (2) For Group 3 airplanes identified in Boeing Service Bulletin 
737-57-1296, dated June 13, 2007: Do the inspections at the 
applicable initial compliance time listed in paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 737-57-1296, dated June 
13, 2007, except where Boeing Service Bulletin 737-57-1296, dated 
June 13, 2007, specifies a compliance time after the date on the 
service bulletin, this AD requires compliance within the specified 
compliance time after April 8, 2008 (the effective date of AD 2008-
05-06, Amendment 39-15400 (73 FR 11538, March 4, 2008)). Repeat the 
inspections thereafter at the intervals specified in paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 737-57-1296, dated June 
13, 2007.

(h) Retained Repair Instructions With Revised Service Information That 
Contains New Repair Actions

    This paragraph restates the requirements of paragraph (g) of AD 
2008-05-06, Amendment 39-15400 (73 FR 11538, March 4, 2008), with 
revised service information that contains new repair actions. If any 
crack is found during any inspection required by paragraph (g) of 
this AD, do the applicable actions specified in paragraph (h)(1) or 
(h)(2) of the AD.
    (1) For inspections done using Boeing Service Bulletin 737-57-
1296, dated June 13, 2007: If any crack is found during any 
inspection required by paragraph (g) of this AD, and Boeing Service 
Bulletin 737-57-1296, dated June 13, 2007, specifies contacting 
Boeing for repair instructions: Before further flight, repair using 
a method approved in accordance with the procedures specified in 
paragraph (n) of this AD.
    (2) For inspections done using Boeing Alert Service Bulletin 
737-57A1296, Revision 2, dated April 1, 2015: If any crack is found 
during any inspection required by paragraph (g) of this AD, before 
further flight, repair, including doing all applicable related 
investigative actions and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
57A1296, Revision 2, dated April 1, 2015; except where Boeing Alert 
Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015, 
specifies contacting Boeing for repair instructions, before further 
flight, repair using a method approved in accordance with the 
procedures specified in paragraph (n) of this AD. Accomplishing a 
repair specified in Boeing Alert Service Bulletin 737-57A1296, 
Revision 2, dated April 1, 2015, terminates the repetitive 
inspections required by paragraph (g) of this AD for the repaired 
area only.

(i) New Requirement of This AD: Inspection for Tapered Fillers for 
Certain Airplanes, Related Investigative Actions, and Corrective 
Actions

    For Groups 1 through 4, Configuration 1 airplanes identified in 
Boeing Alert Service Bulletin 737-57A1296, Revision 2, dated April 
1, 2015: Except as provided by paragraph (k) of this AD, at the 
applicable time specified in table 5 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-57A1296, 
Revision 2, dated April 1, 2015, do an inspection to determine if 
tapered fillers are installed; and do all applicable related 
investigative and corrective actions; in accordance with the 
Accomplishment Instructions of Boeing Alert

[[Page 1349]]

Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015; 
except where Boeing Alert Service Bulletin 737-57A1296, Revision 2, 
dated April 1, 2015, specifies contacting Boeing for repair 
instructions, before further flight, repair using a method approved 
in accordance with the procedures specified in paragraph (n) of this 
AD. Do all applicable related investigative and corrective actions 
before further flight. A review of the maintenance records is 
acceptable in lieu of this inspection if the installation of tapered 
fillers can be conclusively determined from that review.

(j) New Requirement of This AD: Inspections and Corrective Actions for 
Group 5 Airplanes

    For Group 5 airplanes identified in Boeing Alert Service 
Bulletin 737-57A1296, Revision 2, dated April 1, 2015: Except as 
provided by paragraph (k) of this AD, at the applicable time 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 737-57A1296, Revision 2, dated April 1, 2015: Accomplish 
inspections and applicable corrective actions using a method 
approved in accordance with the procedures specified in paragraph 
(n) of this AD.

(k) Exception to Service Information

    Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 737-57A1296, Revision 2, dated April 1, 2015, specifies a 
compliance time ``after the Revision 2 date of this service 
bulletin,'' this AD requires compliance within the specified 
compliance time ``after the effective date of this AD.''

(l) Optional Terminating Action

    Accomplishing the applicable preventative modification specified 
in paragraph 3.B.4., '' Preventive Modification'' of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
57A1296, Revision 2, dated April 1, 2015, terminates the applicable 
repetitive inspection required by paragraph (g) of this AD. The 
preventative modification, including related investigative and 
corrective actions, must be done in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
57A1296, Revision 2, dated April 1, 2015; except where Boeing Alert 
Service Bulletin 737-57A1296, Revision 2, dated April 1, 2015, 
specifies contacting Boeing for repair instructions, before further 
flight, repair using a method approved in accordance with the 
procedures specified in paragraph (n) of this AD.

(m) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (h)(2) of this AD, if those actions were 
performed before the effective date of this AD using Boeing Service 
Bulletin 737-57-1296, Revision 1, dated September 26, 2012.

(n) 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 (o)(1) of this AD. 
Information may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Seattle ACO, to make those findings. To be approved, the 
repair method, modification deviation, or alteration deviation must 
meet the certification basis of the airplane and the approval must 
specifically refer to this AD.
    (4) AMOCs approved as specified in the fourth paragraph (related 
to AD 2008-05-06) of Section 1.F., Approval, of Boeing Service 
Bulletin 737-57-1296, Revision 1, dated September 26, 2012, for 
repairs and modifications are not approved for any provision of this 
AD. All other AMOCs approved for AD 2008-05-06, Amendment 39-15400 
(73 FR 11538, March 4, 2008), are approved as AMOCs for the 
corresponding provisions of this AD.

(o) Related Information

    (1) For more information about this AD, contact Alan Pohl, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6450; fax: 425-917-6590; email: [email protected].
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, 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.

    Issued in Renton, Washington, on December 21, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-32851 Filed 1-11-16; 8:45 am]
 BILLING CODE 4910-13-P