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[Federal Register Volume 80, Number 228 (Friday, November 27, 2015)]
[Proposed Rules]
[Pages 74052-74056]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-30120]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-5816; Directorate Identifier 2015-NM-029-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) 2006-10-
16, which applies to all 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, 747SR, and 747SP series airplanes. AD 2006-10-16 requires, 
for certain airplanes, repetitive inspections for cracking of the 
outboard and center sections of the horizontal stabilizer, and repair 
if necessary. For certain other airplanes, AD 2006-10-16 requires a 
detailed inspection to determine the type of fasteners, and related 
investigative actions and repair if necessary. Since we issued AD 2006-
10-16, additional cracking was found in the splice plates, hinge 
fittings, terminal fittings, the upper skin of the outboard and center 
sections, and the rear spar webs before reaching the inspection 
interval specified in AD 2006-10-16. Cracked and fractured Maraging 
steel fasteners were also found. This proposed AD would reduce the 
compliance time for certain inspections and would add repetitive 
inspections for cracking of the splice plates, hinge fittings, terminal 
fittings, the upper skin of the outboard and center sections, and the 
rear spar webs in Zone B. This proposed AD would also add an inspection 
to determine whether fasteners are magnetic in Zone C, repetitive 
ultrasonic inspections for cracking and fractures of affected 
fasteners, and related investigative and corrective actions if 
necessary. This proposed AD would also add an optional modification, 
which would terminate certain repetitive inspections, and would add 
post-modification inspections and corrective action if necessary. We 
are proposing this AD to detect and correct this cracking, which could 
lead to reduced structural capability of the outboard and center 
sections of the horizontal stabilizer and could result in loss of 
control of the airplane.

DATES: We must receive comments on this proposed AD by January 11, 
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 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. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-5816.

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-
5816; 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: nathan.p.weigand@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about

[[Page 74053]]

this proposed AD. Send your comments to an address listed under the 
ADDRESSES section. Include ``Docket No. FAA-2015-5816; Directorate 
Identifier 2015-NM-029-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 May 8, 2006, we issued AD 2006-10-16, Amendment 39-14600 (71 FR 
28570, May 17, 2006), for all 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, 747SR, and 747SP series airplanes. AD 2006-10-16 
requires, for certain airplanes, repetitive inspections for cracking of 
the outboard and center sections of the horizontal stabilizer, and 
repair if necessary. For certain other airplanes, AD 2006-10-16 
requires a detailed inspection to determine the type of fasteners, 
related investigative actions, and repair if necessary. AD 2006-10-16 
resulted from reports of cracking in the outboard and center section of 
the aft upper skin of the horizontal stabilizer, the rear spar chord, 
rear spar web, terminal fittings, and splice plates; and a report of 
fractured and cracked steel fasteners. We issued AD 2006-10-16 to 
detect and correct this cracking, which could lead to reduced 
structural capability of the outboard and center sections of the 
horizontal stabilizer and could result in loss of control of the 
airplane.

Actions Since AD 2006-10-16, Amendment 39-14600 (71 FR 28570, May 17, 
2006), Was Issued

    Since we issued AD 2006-10-16, Amendment 39-14600 (71 FR 28570, May 
17, 2006), additional cracking was found in the splice plates, hinge 
fittings, terminal fittings, the upper skin of the outboard and center 
sections, and the rear spar webs before reaching the inspection 
interval specified in AD 2006-10-16. Cracked and fractured Maraging 
steel fasteners were also found.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Service Bulletin 747-55A2050, Revision 2, dated 
January 23, 2015. The service information describes procedures for 
accomplishing Zone A, Zone B, and Zone C inspections for cracking of 
the upper skin and upper rear spar chord of the outboard and center 
sections of the horizontal stabilizer, and related investigative and 
corrective actions if necessary. The service information also describes 
procedures for a magnetic inspection to determine the type of 
fasteners, ultrasonic inspections for cracking and fractures of 
affected fasteners, and related investigative actions and corrective 
actions if necessary. The service information also describes procedures 
for an optional modification, which would end certain repetitive 
inspections, and procedures for post-modification inspections and 
corrective action if necessary. 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 the same type design.

Proposed AD Requirements

    Although this proposed AD does not explicitly restate the 
requirements of AD 2006-10-16, Amendment 39-14600 (71 FR 28570, May 17, 
2006), this proposed AD would retain all of the requirements. Those 
requirements are referenced in the service information identified 
previously, which, in turn, is referenced in paragraph (g) of this 
proposed AD. This proposed AD would reduce the compliance time for 
certain inspections and add new repetitive inspections for cracking of 
the splice plates, hinge fittings, terminal fittings, the upper skin of 
the outboard and center sections, and the rear spar webs in Zone B. 
This proposed AD would also add an inspection to determine whether 
fasteners are magnetic in Zone C (made of H-11 steel), repetitive 
ultrasonic inspections for cracking and fractures of affected 
fasteners, and related investigative and corrective actions if 
necessary. This proposed AD would also add an optional modification, 
which would end certain repetitive inspections, and procedures for 
post-modification inspections and corrective action if necessary. This 
proposed AD also adds optional open-hole NDT inspections (high 
frequency eddy current inspections) for certain airplanes, for Zone B 
inspections. This proposed AD would also require accomplishing the 
actions specified in the service information described previously, 
except as discussed under ``Difference Between this Proposed AD and the 
Service Bulletin.'' For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-5816.
    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.

Difference Between This Proposed AD and the Service Bulletin

    Although Boeing Service Bulletin 747-55A2050, Revision 2, dated 
January 23, 2015, specifies that operators may contact the manufacturer 
for disposition of certain repair conditions, 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 116 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 74054]]

                                        Estimated Costs--Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                              Cost per          Cost on U.S.
              Action                      Labor cost         Parts cost        product           operators
----------------------------------------------------------------------------------------------------------------
Zone A Inspections (required by AD  8 work-hours x $85                 $0            $680  Up to $78,880.
 2006-10-16, Amendment 39-14600).    per hour = $680.
Zone B Open-hole NDT Inspection     30 work-hours x 85                  0           2,550  Up to $295,800.
 (required by AD 2006-10-16,         per hour = 2,550.
 Amendment 39-14600 for Groups 3,
 4, and 5 airplanes; and for
 Groups 1, 2, and 3 airplanes, if
 done).
Zone C Maraging or H-11 Steel       8 work-hours x 85 per               0             680  Up to $78,880.
 Fastener Inspection (required by    hour = 680.
 AD 2006-10-16, Amendment 39-14600
 for Groups 1, 2, and 3 airplanes).
New Zone B proposed inspections...  248 work-hours x 85                 0          21,080  $2,445,280.
                                     per hour = 21,080.
New Zone C proposed inspection....  26 work-hours x 85                  0           2,210  $256,360.
                                     per hour = 2,210.
----------------------------------------------------------------------------------------------------------------

                                        Estimated Costs--Optional Actions
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost               Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Open-hole NDT inspections (high        Up to 298 work-hours x   $$0....................  Up to $25,330.
 frequency eddy current inspections.    $85 per hour = up to
                                        $25,330.
Zone B Modification..................  Up to 313 work-hours x   Up to $3,486...........  Up to $30,091.
                                        $85 per hour = up to
                                        $26,605.
Post-Modification Inspections........  Up to 298 work-hours x   $0.....................  Up to $25,330.
                                        $85 per hour = up to
                                        $25,330.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition 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 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 
2006-10-16, Amendment 39-14600 (71 FR 28570, May 17, 2006), and adding 
the following new AD:

The Boeing Company: Docket No. FAA-2015-5816; Directorate Identifier 
2015-NM-029-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by January 11, 
2016.

(b) Affected ADs

    This AD replaces AD 2006-10-16, Amendment 39-14600 (71 FR 28570, 
May 17, 2006).

(c) Applicability

    This AD applies to all 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, 747SR, and 747SP series airplanes; certificated 
in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 55, Stabilizers.

(e) Unsafe Condition

    This AD was prompted by reports of cracking found in the splice 
plates, hinge fittings, terminal fittings, the upper skin of the 
outboard and center sections, and the rear spar webs before reaching 
the inspection interval specified in AD 2006-10-16. Cracked and 
fractured Maraging steel fasteners were also found. We are issuing 
this AD to detect and correct this cracking, which

[[Page 74055]]

could lead to reduced structural capability of the outboard and 
center sections of the horizontal stabilizer and could result in 
loss of control of the airplane.

(f) Compliance

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

(g) Repetitive Inspections/Investigative and Corrective Actions

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-55A2050, Revision 2, 
dated January 23, 2015, except as required by paragraphs (h)(1) and 
(h)(2) of this AD: Do the applicable actions specified in paragraphs 
(g)(1), (g)(2), (g)(3), and (g)(4) of this AD, and all applicable 
related investigative and corrective actions, in accordance with the 
applicable part of the Accomplishment Instructions of Boeing Service 
Bulletin 747-55A2050, Revision 2, dated January 23, 2015, except as 
required by paragraph (h)(3) of this AD. Do all applicable related 
investigative and corrective actions before further flight. Repeat 
the applicable inspections specified in paragraphs (g)(1), (g)(2), 
(g)(3), and (g)(4) of this AD at the applicable times specified in 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
55A2050, Revision 2, dated January 23, 2015.
    (1) For Group 1 through 3 airplanes identified in Boeing Service 
Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Do non-
destructive test (NDT) inspections (ultrasonic, high frequency eddy 
current, and low frequency eddy current inspections) or open-hole 
NDT inspections (high frequency eddy current inspections), of Zone B 
for cracking in accordance with Part 3 or Part 4 of the 
Accomplishment Instructions of Boeing Service Bulletin 747-55A2050, 
Revision 2, dated January 23, 2015, as applicable.
    (2) For Group 4 through 6 airplanes identified in Boeing Service 
Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Do open-
hole NDT inspections (high frequency eddy current inspections), of 
Zone B for cracking in accordance with Part 4 of the Accomplishment 
Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, 
dated January 23, 2015.
    (3) For Group 7 through 9 airplanes identified in Boeing Service 
Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Do 
inspections of Zone A (detailed or high frequency eddy current 
inspections) and Zone B (high frequency eddy current inspections) 
for cracking, in accordance with Part 1, Part 2, or Part 4 of the 
Accomplishment Instructions of Boeing Service Bulletin 747-55A2050, 
Revision 2, dated January 23, 2015, as applicable.
    (4) For Group 1 through 3 airplanes identified in Boeing Service 
Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Do an 
inspection of Zone C Maraging or H-11 steel fasteners to determine 
whether fasteners are magnetic, in accordance with Part 6 of the 
Accomplishment Instructions of Boeing Service Bulletin 747-55A2050, 
Revision 2, dated January 23, 2015.

(h) Exceptions to Service Bulletin Specifications

    (1) Where Boeing Service Bulletin 747-55A2050, Revision 2, dated 
January 23, 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.
    (2) The Condition column of Table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-55A2050, Revision 2, 
dated January 23, 2015, refers to ``airplanes with certain total 
flight cycles and total flight hours.'' This AD, however, applies to 
the airplanes with the specified total flight cycles and total 
flight hours as of the effective date of this AD.
    (3) Where Boeing Service Bulletin 747-55A2050, Revision 2, dated 
January 23, 2015, specifies to contact Boeing for repair 
instructions: Before further flight, repair using a method approved 
in accordance with the procedures specified in paragraph (l) of this 
AD.

(i) Optional Terminating Action

    (1) For Group 1 through 3 airplanes identified in Boeing Service 
Bulletin 747-55A2050, Revision 2, dated January 23, 2015: 
Accomplishing the Zone B modification, including all applicable 
related investigative and corrective actions, specified in Part 7 of 
the Accomplishment Instructions of Boeing Service Bulletin 747-
55A2050, Revision 2, dated January 23, 2015, except as required by 
paragraph (h)(3) of this AD, terminates the repetitive inspections 
specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD for the 
modified area only.
    (i) Inspections required by paragraph (g)(1) of this AD for Zone 
B, as specified in Part 3 and Part 4 of the Accomplishment 
Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, 
dated January 23, 2015.
    (ii) Inspections required by paragraph (g)(4) of this AD for 
Zone C, as specified in Part 5 and Part 6 of the Accomplishment 
Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, 
dated January 23, 2015.
    (2) For Group 1 through 3 airplanes identified in Boeing Service 
Bulletin 747-55A2050, Revision 2, dated January 23, 2015: 
Accomplishing the Zone B open hole NDT inspection, repairing any 
cracking as applicable, and replacing fasteners as specified in Part 
4 of the Accomplishment Instructions of Boeing Service Bulletin 747-
55A2050, Revision 2, dated January 23, 2015, terminates the 
repetitive ultrasonic inspections required by paragraph (g)(4) of 
this AD for Zone C, as specified in Part 6 of the Accomplishment 
Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, 
dated January 23, 2015, for the inspected area only.
    (3) For Group 4 through 9 airplanes identified in Boeing Service 
Bulletin 747-55A2050, Revision 2, dated January 23, 2015: 
Accomplishing the Zone B modification, including all applicable 
related investigative and corrective actions, specified in Part 7 of 
the Accomplishment Instructions of Boeing Service Bulletin 747-
55A2050, Revision 2, dated January 23, 2015, except as required by 
paragraph (h)(3) of this AD, terminates the repetitive inspections 
required by paragraph (g)(2) or (g)(3) of this AD, as applicable, 
only for Zone B, as specified in Part 4 of the Accomplishment 
Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, 
dated January 23, 2015, for the modified area only.

(j) Repetitive Post-Modification Inspections and Corrective Actions

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-55A2050, Revision 2, 
dated January 23, 2015: Do the applicable inspections specified in 
paragraphs (j)(1) and (j)(2) of this AD and all applicable 
corrective actions, in accordance with Part 8 of the Accomplishment 
Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, 
dated January 23, 2015, except as required by paragraph (h)(3) of 
this AD. Do all applicable corrective actions before further flight. 
Repeat the applicable inspections at the applicable times specified 
in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
55A2050, Revision 2, dated January 23, 2015.
    (1) For Group 1 through 3 airplanes identified in Boeing Service 
Bulletin 747-55A2050, Revision 2, dated January 23, 2015 on which 
the Zone B modification specified in paragraph (i)(1) of this AD is 
done: Do non-destructive test (NDT) inspections (ultrasonic, high 
frequency eddy current, and low frequency eddy current inspections) 
or open-hole NDT inspections (high frequency eddy current 
inspections) of Zone B for cracking.
    (2) For Group 4 through 9 airplanes identified in Boeing Service 
Bulletin 747-55A2050, Revision 2, dated January 23, 2015 on which 
the Zone B modification specified in paragraph (i)(3) of this AD is 
done: Do open-hole NDT inspections (high frequency eddy current 
inspections) of Zone B for cracking.

(k) Parts Installation Prohibition

    As of the effective date of this AD, no person may install any 
Maraging or H-11 steel fasteners in the locations specified in this 
AD. Where Boeing Service Bulletin 747-55A2050, Revision 2, dated 
January 23, 2015, specifies to install H-11 bolts (kept fasteners), 
this AD requires installation of Inconel bolts.

(l) 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 (m)(1) 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.

[[Page 74056]]

    (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) AMOCs approved for AD 2006-10-16, Amendment 39-14600 (71 FR 
28570, May 17, 2006), are approved as AMOCs for the corresponding 
provisions of paragraph (g) of this AD, except for approved AMOCs 
that allow installation of Maraging or H-11 steel fasteners.

(m) Related Information

    (1) For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; 
fax: 425-917-6590; email: nathan.p.weigand@faa.gov.
    (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 November 19, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-30120 Filed 11-25-15; 8:45 am]
 BILLING CODE 4910-13-P
```