[Federal Register Volume 80, Number 72 (Wednesday, April 15, 2015)]
[Proposed Rules]
[Pages 20178-20181]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-08464]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0828; Directorate Identifier 2014-NM-146-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) 2013-23-
03, which applies to certain The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 
747-400D, 747-400F, and 747SR series airplanes. AD 2013-23-03 currently 
requires doing a detailed inspection of certain attach fittings for a 
cylindrical defect and replacing if necessary. Since we issued AD 2013-
23-03, we received a report that a machining defect was also found on 
some of the actuator assemblies inspected during manufacture. This 
defect could lead to fatigue cracking and subsequent fracture. For 
certain airplanes, this proposed AD would mandate new inspections of 
the inboard actuator attach fittings for machining defects, and 
overhaul or replacement, if necessary. This proposed AD would also 
limit the compliance time for doing the replacement for certain other 
airplanes. We are proposing this AD to detect and correct defective 
inboard actuator attach fittings which, combined with loss of the 
outboard actuator load path, could result in uncontrolled retraction of 
the outboard flap, damage to flight control systems, and consequent 
reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by June 1, 2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet<ls-thn-eq> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, P. 
O. Box 3707, MC 2H-65, Seattle, 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, Washington. 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-
0828.

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-
0828; 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: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 
425-917-6590; email: <a href="/cdn-cgi/l/email-protection#a4cac5d0ccc5ca8ad48ad3c1cdc3c5cac0e4c2c5c58ac3cbd2"><span class="__cf_email__" data-cfemail="fd939c89959c93d38dd38a98949a9c9399bd9b9c9cd39a928b">[email protected]</span></a>.

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-2015-0828; 
Directorate Identifier 2014-NM-146-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 October 31, 2013, we issued AD 2013-23-03, Amendment 39-17658 
(78 FR 68345, November 14, 2013), for certain The Boeing Company Model 
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 
747-400, 747-400D, 747-400F, and 747SR series airplanes. AD 2013-23-03 
requires inspecting to determine the part number of the inboard 
actuator attach fittings of the outboard flap. For affected attach 
fittings, AD 2013-23-03 requires doing a detailed inspection of the 
attach fittings for a cylindrical defect and replacing if necessary. As 
an option to the detailed inspection, AD 2013-23-03 allows replacement 
of affected attach fittings. AD 2013-23-03 resulted from a report of 
the fracture of an inboard actuator attach fitting of the outboard 
flap. An inspection of the attach fitting revealed that it was 
incorrectly machined with a cylindrical profile instead of a conical 
profile, resulting in reduced wall thickness. We issued AD 2013-23-03 
to detect and correct defective inboard actuator attach fittings which, 
combined with loss of the outboard actuator load path, could result in 
uncontrolled retraction of the outboard flap, damage to flight control 
systems, and consequent reduced controllability of the airplane.

Actions Since AD 2013-23-03, Amendment 39-17658 (78 FR 68345, November 
14, 2013) Was Issued

    The preamble to AD 2013-23-03, Amendment 39-17658 (78 FR 68345, 
November 14, 2013), specified that we considered the requirements 
``interim action.'' AD 2013-23-03 explained that we might consider 
further rulemaking to require a minimum thickness inspection of inboard 
actuator attach fittings that are conically machined. Since we issued 
AD 2013-23-03, we received a report that a machining defect was also 
found on some of the actuator assemblies inspected during manufacture 
at the point where the tapered machining transitioned to the 
hemispherical machining at the top of the inner surface. Revised 
service information has been issued and, for certain airplanes, this 
proposed AD would mandate new

[[Page 20179]]

inspections of the inboard actuator attach fittings for machining 
defects, and overhaul or replacement, if necessary. This proposed AD 
would also limit the compliance time for doing the replacement, for 
certain other airplanes.

Related Service Information Under 1 CFR part 51

    We reviewed Boeing Alert Service Bulletin 747-57A2343, Revision 1, 
dated June 23, 2014. The service information describes procedures for 
new inspections of the inboard actuator attach fittings for machining 
defects, and overhaul or replacement, if necessary. This service 
information is reasonably available; see ADDRESSES for ways to access 
this service information.

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 the same type design.

Related AD

    This proposed AD is related to AD 2005-20-18, Amendment 39-14312 
(70 FR 57740, October 4, 2005), for Model 747-100, -200B, -200F, -200C, 
-100B, -300 series airplanes. AD 2005-20-18 required nspecting and 
overhauling, replacing, or repairing (as applicable) the actuator 
attach fittings on the inboard and outboard flaps of the wing. The 
replacement was done in accordance with Boeing Service Bulletin 747-
57A2316.

Proposed AD Requirements

    This proposed AD would retain all of the requirements of AD 2013-
23-03, Amendment 39-17658 (78 FR 68345, November 14, 2013). For certain 
airplanes, this proposed AD would mandate new inspections of the 
inboard actuator attach fittings for machining defects, and overhaul or 
replacement, if necessary. This proposed AD would also limit the 
compliance time for doing the replacement for certain other airplanes. 
This proposed AD would also require accomplishing the actions specified 
in the service information described previously.

Costs of Compliance

    We estimate that this proposed AD affects 184 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated costs
----------------------------------------------------------------------------------------------------------------
                                                                              Cost per          Cost on U.S.
              Action                      Labor cost         Parts cost        product           operators
----------------------------------------------------------------------------------------------------------------
Retained inspection for part        7 work-hours x $85                 $0            $595  $109,480.
 number in AD 2013-23-03,            per hour = $595.
 Amendment 39-17658 (78 FR 68345,
 November 14, 2013).
New proposed inspections for        8 work-hours x $85                  0             680  125,120.
 machining defect.                   per hour = $680.
Replacement for airplanes without   6 work-hours x $85             13,720          14,230  14,230 per airplane.
 any defect.                         per hour = $510.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in this 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 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) 
2013-23-03, Amendment 39-17658 (78 FR 68345, November 14, 2013), and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2015-0828; Directorate Identifier 
2014-NM-146-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by June 1, 2015.

(b) Affected ADs

    This AD replaces AD 2013-23-03, Amendment 39-17658 (78 FR 68345, 
November 14, 2013).

[[Page 20180]]

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-
400D, 747-400F, and 747SR series airplanes, certificated in any 
category, as identified in Boeing Alert Service Bulletin 747-
57A2343, Revision 1, dated June 23, 2014.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report of the fracture of an inboard 
actuator attach fitting of the outboard flap. An inspection of the 
attach fitting revealed that it was incorrectly machined with a 
cylindrical profile instead of a conical profile, resulting in 
reduced wall thickness. A machining defect was also found on some 
actuator assemblies inspected during manufacture at the point where 
the tapered machining transitioned to the hemispherical machining at 
the top of the inner surface. This defect could lead to fatigue 
cracking and subsequent fracture. We are issuing this AD to detect 
and correct defective inboard actuator attach fittings which, 
combined with loss of the outboard actuator load path, could result 
in uncontrolled retraction of the outboard flap, damage to flight 
control systems, and consequent reduced controllability of the 
airplane.

(f) Compliance

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

(g) Retained Part Number Inspection

    This paragraph restates the requirements of paragraph (g) of AD 
2013-23-03, Amendment 39-17658 (78 FR 68345, November 14, 2013), 
with revised service information. Within 90 days after November 29, 
2013 (the effective date of AD 2013-23-03): Inspect to determine the 
part number of the inboard actuator attach fittings of the outboard 
flaps, in accordance with Part 1 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2343, dated September 12, 
2013; or Boeing Alert Service Bulletin 747-57A2343, Revision 1, 
dated June 23, 2014. As of the effective date of this AD, only 
Boeing Alert Service Bulletin 747-57A2343, Revision 1, dated June 
23, 2014, may be used.

(h) Retained Actions for Certain Attach Fittings

    This paragraph restates the requirements of paragraph (h) of AD 
2013-23-03, Amendment 39-17658 (78 FR 68345, November 14, 2013), 
with revised service information. If, during the inspection required 
by paragraph (g) of this AD, any inboard actuator attach fitting 
having part number (P/N) 65B08564-7 is found, before further flight, 
do the actions specified in paragraph (h)(1) or (h)(2) of this AD.
    (1) Do a detailed inspection of the inboard actuator attach 
fitting for a cylindrical defect, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2343, dated September 12, 2013; or Boeing Alert Service Bulletin 
747-57A2343, Revision 1, dated June 23, 2014. As of the effective 
date of this AD, only Boeing Alert Service Bulletin 747-57A2343, 
Revision 1, dated June 23, 2014, may be used. For airplanes on which 
the detailed inspection is done before the effective date of this 
AD: If any cylindrical defect is found, before further flight, do 
the actions specified in paragraph (h)(1)(i) or (h)(1)(ii) of this 
AD.
    (i) Do a minimum thickness inspection of the inboard actuator 
attach fitting to determine minimum wall thickness of the actuator 
fitting assembly, in accordance with Part 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2343, dated 
September 12, 2013; or Boeing Alert Service Bulletin 747-57A2343, 
Revision 1, dated June 23, 2014. If the minimum thickness of the 
wall is less than 0.130 inch: Before further flight, replace the 
inboard actuator attach fitting of the outboard flap, in accordance 
with Part 4 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747 57A2343, dated September 12, 2013.
    (ii) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2343, dated September 12, 
2013.
    (2) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2343, dated September 12, 
2013.

(i) New Actions For Certain Airplanes on Which Any Cylindrical Defect 
Is Found

    For airplanes on which the detailed inspection required by 
paragraph (h)(1) of this AD is done on or after the effective date 
of this AD: If any cylindrical defect is found during any inspection 
required by paragraph (h)(1) of this AD, before further flight, do 
the actions specified in paragraph (i)(1) or (i)(2) of this AD.
    (1) Determine the minimum wall thickness of the actuator attach 
fitting either by doing an ultrasonic inspection or by mechanically 
measuring the thickness and do a detailed inspection of the inner 
conical section to determine if the machining defect is present, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2343, Revision 1, dated June 23, 2014.
    (i) If the minimum thickness of the wall is less than 0.130 
inch: Before further flight, replace the inboard actuator attach 
fitting of the outboard flap, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2343, Revision 1, dated June 23, 2014.
    (ii) If the minimum thickness of the wall is 0.140 inch or 
greater and the machining defect is present, before further flight, 
do the actions specified in paragraph (i)(1)(ii)(A) or (i)(1)(ii)(B) 
of this AD.
    (A) Overhaul the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 5 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2343, Revision 1, dated June 
23, 2014.
    (B) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2343, Revision 1, dated June 
23, 2014.
    (iii) If the minimum thickness of the wall is 0.130 inch or 
greater and less than 0.140 inch and the machining defect is not 
present, within 48 months or 3,000 flight cycles after the effective 
date of this AD, whichever occurs first, replace the inboard 
actuator attach fitting of the outboard flap, in accordance with 
Part 4 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-57A2343, Revision 1, dated June 23, 2014.
    (iv) If the minimum thickness of the wall is 0.130 inch or 
greater and less than 0.140 inch and the machining defect is 
present, before further flight, replace the inboard actuator attach 
fitting of the outboard flap, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2343, Revision 1, dated June 23, 2014.
    (2) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2343, Revision 1, dated June 
23, 2014.

(j) New Actions for Airplanes on Which No Cylindrical Defects Are Found

    If no cylindrical defect is found during any inspection required 
by paragraph (h)(1) of this AD, within 24 months after the effective 
date of this AD, do the actions specified in paragraph (j)(1) or 
(j)(2) of this AD.
    (1) Determine the minimum wall thickness of the actuator attach 
fitting either by doing an ultrasonic inspection or by mechanically 
measuring the thickness and do a detailed inspection of the inner 
conical section to determine if the machining defect is present, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2343, Revision 1, dated June 23, 2014.
    (i) If the minimum thickness of the wall is less than 0.130 
inch: Before further flight, replace the inboard actuator attach 
fitting of the outboard flap, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747 
57A2343, Revision 1, dated June 23, 2014.
    (ii) If the minimum thickness of the wall is 0.140 inch or 
greater and the machining defect is present, before further flight, 
do the actions specified in paragraph (j)(1)(ii)(A) or (j)(1)(ii)(B) 
of this AD.
    (A) Overhaul the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 5 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2343, Revision 1, dated June 
23, 2014.
    (B) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2343, Revision 1, dated June 
23, 2014.

[[Page 20181]]

    (iii) If the minimum thickness of the wall is 0.130 inch or 
greater and less than 0.140 inch and the machining defect is not 
present, within 48 months or 3,000 flight cycles after the effective 
date of this AD, whichever occurs first, replace the inboard 
actuator attach fitting of the outboard flap, in accordance with 
Part 4 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-57A2343, Revision 1, dated June 23, 2014.
    (iv) If the minimum thickness of the wall is 0.130 inch or 
greater and less than 0.140 inch and the machining defect is 
present, before further flight, replace the inboard actuator attach 
fitting of the outboard flap, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2343, Revision 1, dated June 23, 2014.
    (2) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2343, Revision 1, dated June 
23, 2014.

(k) New Inspection or Replacement for Certain Fittings That Were 
Previously Inspected

    For airplanes with any inboard actuator attach fitting having P/
N 65B08564-7 installed and the fitting was inspected in accordance 
with Part 3 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-57A2343, dated September 12, 2013: Within 24 
months after the effective date of this AD, do the actions specified 
in paragraph (k)(1) or (k)(2) of this AD.
    (1) Do a detailed inspection of the inner conical section for 
machining defects only, in accordance with Part 3 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2343, Revision 1, dated June 23, 2014.
    (i) If any machining defect is found and the minimum thickness 
of the wall is 0.140 inch or greater: Before further flight, do the 
actions specified in paragraph (k)(1)(i)(A) or (k)(1)(i)(B) of this 
AD.
    (A) Overhaul the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 5 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2343, Revision 1, dated June 
23, 2014.
    (B) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2343, Revision 1, dated June 
23, 2014.
    (ii) If any machining defect is found and the minimum thickness 
of the wall is 0.130 inch or greater and less than 0.140 inch: 
Before further flight, replace the inboard actuator attach fitting 
of the outboard flap, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2343, Revision 1, dated June 23, 2014.
    (iii) If no machining defect is found and the minimum thickness 
of the wall is 0.130 inch or greater and less than 0.140 inch: 
Within 48 months or 3,000 flight cycles after the effective date of 
this AD, whichever occurs first, replace the inboard actuator attach 
fitting of the outboard flap, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2343, Revision 1, dated June 23, 2014.
    (iv) If a machining defect is or is not found and the minimum 
thickness of the wall is less than 0.130 inch: Before further 
flight, replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2343, Revision 1, dated June 
23, 2014.
    (2) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2343, Revision 1, dated June 
23, 2014.

(l) Part Installation Limitation

    As of the effective date of this AD, no actuator attach fitting 
having P/N 65B08564-7 that meets the requirements of CONDITION 5 or 
CONDITION 6 defined in Boeing Alert Service Bulletin 747-57A2343, 
dated September 12, 2013, may be installed on any airplane unless 
the inspection specified in paragraph (k)(1) of this AD is done and 
the applicable actions in paragraphs (k)(1)(i), (k)(1)(ii), 
(k)(1)(iii), and (k)(1)(iv) are done within the applicable times 
specified in paragraphs (k)(1)(i), (k)(1)(ii), (k)(1)(iii), and 
(k)(1)(iv) of this AD.

(m) 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 (n)(1) of this AD. 
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#1b22365a555636487e7a6f6f777e365a5854365a56545836497e6a6e7e686f685b7d7a7a357c746d"><span class="__cf_email__" data-cfemail="e9d0c4a8a7a4c4ba8c889d9d858cc4a8aaa6c4a8a4a6aac4bb8c989c8c9a9d9aa98f8888c78e869f">[email protected]</span></a>.
    (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, Seattle 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) If any service information contains steps that are 
identified as RC (Required for Compliance), those steps must be done 
to comply with this AD; any steps that are not identified as RC are 
recommended. Those steps that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC provided the steps identified as RC can be done 
and the airplane can be put back in a serviceable condition. Any 
substitutions or changes to steps identified as RC require approval 
of an AMOC.
    (5) AMOCs approved for AD 2013-23-03, Amendment 39-17658 (78 FR 
68345, November 14, 2013) are approved as AMOCs for the 
corresponding provisions of this AD.

(n) Related Information

    (1) For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6428; fax: 425-917-6590; email: 
<a href="/cdn-cgi/l/email-protection#6b050a1f030a05451b451c0e020c0a050f2b0d0a0a450c041d"><span class="__cf_email__" data-cfemail="ddb3bca9b5bcb3f3adf3aab8b4babcb3b99dbbbcbcf3bab2ab">[email protected]</span></a>.
    (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, Washington. For information on the availability 
of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on April 6, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-08464 Filed 4-14-15; 8:45 am]
BILLING CODE 4910-13-P


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