[Federal Register Volume 83, Number 37 (Friday, February 23, 2018)]
[Rules and Regulations]
[Pages 7975-7979]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-03429]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9067; Product Identifier 2016-NM-043-AD; Amendment 
39-19202; AD 2018-04-07]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) 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. This AD was prompted by a report of incidents 
involving fatigue cracking in transport category airplanes that are 
approaching or have exceeded their design service objective and a 
structural reevaluation by the manufacturer that identified additional 
structural elements that qualify as structural significant items 
(SSIs). This AD requires revising the maintenance or inspection 
program, as applicable, to include inspections that will give no less 
than the required damage tolerance rating (DTR) for certain SSI, 
performing repetitive inspections to detect cracks of all SSIs, and 
repairing cracked structures if necessary. Additionally, this AD 
requires all cracks involving an SSI or related structure in close 
vicinity to the SSI to be reported to Boeing. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective March 30, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 30, 
2018.

ADDRESSES: For service information identified in this final rule, 
contact Boeing Commercial Airplanes, Attention: Contractual & Data 
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 
90740-5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Standards Branch, 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-2016-
9067.

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-2016-
9067; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is Docket Operations, 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: Bill Ashforth, Aerospace Engineer, 
Airframe Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW, Renton, 
WA 98057-3356; phone: 425-917-6432; fax: 425-917-6590; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply 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. The NPRM published in the Federal Register on September 8, 
2016 (81 FR 62031). The NPRM was prompted by a report of incidents 
involving fatigue cracking in transport category airplanes that are 
approaching or have exceeded their design service objective and a 
structural reevaluation by the manufacturer that identified additional 
structural elements that qualify as SSIs. The NPRM proposed to require 
revising the maintenance or inspection program, as applicable, to 
include inspections that will give no less than the required DTR for 
certain SSIs, and repairing any cracked structure. The NPRM proposed to 
require inspections to detect cracks of all SSI structure, and repair 
if necessary.
    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 by adding an AD that would apply 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. The SNPRM published in the Federal Register on November 9, 
2017 (82 FR 52015). The SNPRM revised the NPRM by proposing to require 
reporting in order to ensure the continuing structural airworthiness of 
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 with a high number of flight cycles. All cracks 
involving an SSI or related structure in close vicinity to the SSI must 
be reported to Boeing in order to evaluate the effectiveness of the 
supplemental structural inspections.
    We are issuing this AD to ensure the continued structural integrity 
of 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.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. We have considered the comments received. The Boeing 
Company, British Airways, and United Airlines supported the SNPRM.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule as proposed, except for minor editorial changes. We 
have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Document D6-35022, ``Supplemental Structural 
Inspection Document for Model 747

[[Page 7976]]

Airplanes,'' Revision H, dated September 2013. This service information 
describes procedures for inspections to detect cracks of all structures 
identified as SSIs, and includes six new SSIs since the last revision.
    We also reviewed Boeing Document D6-35022-1, ``747-400 LCF 
Supplemental Structural Inspection Document--Appendix A,'' dated 
November 2015. This service information describes procedures for 
inspections of the wings, fuselage, and empennage SSIs for Model 747-
400 LCF airplanes.
    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.

Costs of Compliance

    We estimate that this AD affects 118 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Revision of maintenance or inspection   1 work-hour x $85 per                 $0             $85         $10,030
 program.                                hour = $85.
----------------------------------------------------------------------------------------------------------------

    We have not specified cost estimates for the inspection and repair 
specified in this AD. Compliance with this AD constitutes a method of 
compliance with the FAA aging airplane safety final rule (AASFR) (70 FR 
5518, February 2, 2005) for certain baseline structure of 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. The 
AASFR requires certain operators to incorporate damage tolerance 
inspections into their maintenance inspection programs. These 
requirements are described in 14 CFR 121.1109(c)(1) and 14 CFR 
129.109(b)(1). Accomplishment of the actions specified in this AD will 
meet the requirements of these regulations for certain baseline 
structure. The costs for accomplishing the inspection and repair 
portions of this AD were accounted for in the regulatory evaluation of 
the AASFR for airplanes affected by that rule. For airplanes not 
affected by the AASFR, we have received no definitive data that would 
enable us to provide cost estimates for the inspection or repair 
portions of this AD.
    We estimate the following costs to do any necessary reporting that 
would be required based on the results of the inspections in the 
maintenance inspection program. We have no way of determining the 
number of aircraft that might need this action:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
              Action                     Labor cost         Parts cost               Cost per product
----------------------------------------------------------------------------------------------------------------
Reporting.........................  1 work-hour x $85                 $0  $85 per inspection cycle.
                                     per hour = $85.
----------------------------------------------------------------------------------------------------------------

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and

[[Page 7977]]

    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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 adding the following new airworthiness 
directive (AD):

2018-04-07 The Boeing Company: Amendment 39-19202; Docket No. FAA-
2016-9067; Product Identifier 2016-NM-043-AD.

(a) Effective Date

    This AD is effective March 30, 2018.

(b) Affected ADs

    This AD affects AD 2004-07-22 R1, Amendment 39-15326 (73 FR 
1052, January 7, 2008; corrected February 14, 2008 (73 FR 8589)) 
(``AD 2004-07-22 R1'').

(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.

    Note 1 to paragraph (c) of this AD: A Model 747-400 LCF airplane 
is a Model 747-400 series airplane that has been modified from a 
passenger airplane to a freighter configuration, as specified in 
Boeing Service Bulletin 747-00-2084.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage; 
54, Nacelles/Pylons; 55, Stabilizers; 57, Wings.

(e) Unsafe Condition

    This AD was prompted by a report of incidents involving fatigue 
cracking in transport category airplanes that are approaching or 
have exceeded their design service objective, and a structural 
reevaluation by the manufacturer that identified additional 
structural elements that qualify as structural significant items 
(SSIs). We are issuing this AD to ensure the continued structural 
integrity of 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.

(f) Compliance

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

(g) Definition of SSI

    For the purposes of this AD, an SSI is defined as a principal 
structural element (PSE). A PSE is a structural element that 
contributes significantly to the carrying of flight, ground, or 
pressurization loads, and whose integrity is essential in 
maintaining the overall structural integrity of the airplane.

(h) Maintenance or Inspection Program Revision for All Airplanes

    Prior to reaching the compliance times specified in paragraph 
(i)(1)(i), (i)(2)(i), (j)(1)(i), or (j)(2)(i) of this AD, as 
applicable, or within 12 months after the effective date of this AD, 
whichever occurs later: Incorporate a revision into the maintenance 
or inspection program, as applicable, that provides no less than the 
required damage tolerance rating (DTR) for each SSI listed in the 
applicable service information specified in paragraph (h)(1) or 
(h)(2) of this AD. The revision to the maintenance or inspection 
program must include, and must be implemented in accordance with, 
the procedures in Section 5.0, ``Damage Tolerance Rating (DTR) 
System Application,'' and Section 6.0, ``SSI Discrepancy Reporting'' 
of Boeing Document D6-35022, ``Supplemental Structural Inspection 
Document for Model 747 Airplanes,'' Revision H, dated September 
2013; and Boeing Document D6-35022-1, ``747-400 LCF Supplemental 
Structural Inspection Document--Appendix A,'' dated November 2015; 
as applicable. Accomplishing the revision required by this paragraph 
terminates the actions required by paragraphs (f), (g), and (h) of 
AD 2004-07-22 R1.
    (1) For all airplanes except Model 747-400 LCF airplanes: SSIs 
listed in Boeing Document D6-35022, ``Supplemental Structural 
Inspection Document for Model 747 Airplanes,'' Revision H, dated 
September 2013.
    (2) For Model 747-400 LCF airplanes: SSIs listed in Boeing 
Document D6-35022, ``Supplemental Structural Inspection Document for 
Model 747 Airplanes,'' Revision H, dated September 2013; and SSIs 
listed in Boeing Document D6-35022-1, ``747-400 LCF Supplemental 
Structural Inspection Document--Appendix A,'' dated November 2015. 
For SSIs listed in both Boeing Document D6-35022-1, ``747-400 LCF 
Supplemental Structural Inspection Document--Appendix A,'' dated 
November 2015; and Boeing Document D6-35022, ``Supplemental 
Structural Inspection Document for Model 747 Airplanes,'' Revision 
H, dated September 2013: Incorporate the SSIs listed in Boeing 
Document D6-35022-1, ``747-400 LCF Supplemental Structural 
Inspection Document--Appendix A,'' dated November 2015.

(i) Inspections for All Airplanes Except Model 747-400 LCF Airplanes

    For all airplanes except Model 747-400 LCF airplanes: Perform 
inspections to detect cracks of all structure identified in Boeing 
Document D6-35022, ``Supplemental Structural Inspection Document for 
Model 747 Airplanes,'' Revision H, dated September 2013, at the 
times specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, 
as applicable, except as required by paragraph (l) of this AD. Once 
the initial inspection has been performed, in order to remain in 
compliance with the maintenance or inspection program, as required 
by paragraph (h) of this AD, repetitive inspections are required at 
the intervals specified in Boeing Document D6-35022, ``Supplemental 
Structural Inspection Document for Model 747 Airplanes,'' Revision 
H, dated September 2013. Doing an inspection required by this 
paragraph terminates the corresponding inspection required by 
paragraph (i) of AD 2004-07-22 R1.
    (1) For wing structure, except as provided by paragraph (i)(3) 
of this AD: Inspect at the times specified in paragraph (i)(1)(i) or 
(i)(1)(ii) of this AD, whichever occurs later.
    (i) Within the applicable compliance time specified in paragraph 
(i)(1)(i)(A) or (i)(1)(i)(B) of this AD.
    (A) For all Model 747-100, 747-100B, 747-100B SUD, 747-200B, 
747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes: 
Prior to the accumulation of 20,000 total flight cycles or 100,000 
total flight hours, whichever occurs first.
    (B) For all Model 747-400, 747-400D, and 747-400F series 
airplanes: Prior to the accumulation of 20,000 total flight cycles 
or 115,000 total flight hours, whichever occurs first.
    (ii) Within 1,000 flight cycles measured from 12 months after 
the effective date of this AD.
    (2) For all structure other than wing structure, except as 
provided by paragraph (i)(3) of this AD: At the time specified in 
paragraph (i)(2)(i) or (i)(2)(ii) of this AD, whichever occurs 
later.
    (i) Prior to the accumulation of 20,000 total flight cycles.
    (ii) Within 1,000 flight cycles measured from 12 months after 
the effective date of this AD.
    (3) For any portion of an SSI that has been replaced with new 
structure: Inspect at the later of the times specified in paragraphs 
(i)(3)(i) and (i)(3)(ii) of this AD.
    (i) At the time specified in paragraph (i)(1) or (i)(2) of this 
AD, as applicable.
    (ii) Within 10,000 flight cycles after the replacement of the 
part with a new part.

(j) Inspections for Model 747-400 LCF Airplanes

    For Model 747-400 LCF airplanes: Perform inspections to detect 
cracks of all structure identified in Boeing Document D6-35022, 
``Supplemental Structural Inspection Document for Model 747 
Airplanes,'' Revision H, dated September 2013; and Boeing Document 
D6-35022-1, ``747-400 LCF Supplemental Structural Inspection 
Document--Appendix A,'' dated November 2015; at the times specified 
in paragraph

[[Page 7978]]

(j)(1) or (j)(2) of this AD, as applicable, except as required by 
paragraph (l) of this AD. Once the initial inspection has been 
performed, in order to remain in compliance with the maintenance or 
inspection program, as required by paragraph (h) of this AD, 
repetitive inspections are required at the intervals specified in 
Boeing Document D6-35022, ``Supplemental Structural Inspection 
Document for Model 747 Airplanes,'' Revision H, dated September 
2013; and Boeing Document D6-35022-1, ``747-400 LCF Supplemental 
Structural Inspection Document--Appendix A,'' dated November 2015. 
For SSIs listed in both Boeing Document D6-35022, ``Supplemental 
Structural Inspection Document for Model 747 Airplanes,'' Revision 
H, dated September 2013; and Boeing Document D6-35022-1, ``747-400 
LCF Supplemental Structural Inspection Document--Appendix A,'' dated 
November 2015; the SSIs listed in Boeing Document D6-35022-1, ``747-
400 LCF Supplemental Structural Inspection Document--Appendix A,'' 
dated November 2015, take precedence (i.e., the SSIs in the latter 
document prevail). Doing an inspection required by this paragraph 
terminates the corresponding inspection required by paragraph (i) of 
AD 2004-07-22 R1.
    (1) For wing structure: Inspect at the times specified in 
paragraph (j)(1)(i) or (j)(1)(ii) of this AD, whichever occurs 
later.
    (i) Prior to the accumulation of 20,000 total flight cycles or 
115,000 total flight hours, whichever occurs first.
    (ii) Within 1,000 flight cycles measured from 12 months after 
the effective date of this AD.
    (2) For all structure other than wing structure: At the time 
specified in paragraph (j)(2)(i) or (j)(2)(ii) of this AD, whichever 
occurs later.
    (i) At the earlier of the times specified in paragraphs 
(j)(2)(i)(A) and (j)(2)(i)(B) of this AD.
    (A) Prior to the accumulation of 20,000 total flight cycles.
    (B) Within the applicable initial compliance time specified in 
Boeing Document D6-35022, ``Supplemental Structural Inspection 
Document for Model 747 Airplanes,'' Revision H, dated September 
2013; and Boeing Document D6-35022-1, ``747-400 LCF Supplemental 
Structural Inspection Document--Appendix A,'' dated November 2015. 
For SSIs are listed in both Boeing Document D6-35022, ``Supplemental 
Structural Inspection Document for Model 747 Airplanes,'' Revision 
H, dated September 2013; and Boeing Document D6-35022-1, ``747-400 
LCF Supplemental Structural Inspection Document--Appendix A,'' dated 
November 2015; the SSIs listed in Boeing Document D6-35022-1, ``747-
400 LCF Supplemental Structural Inspection Document--Appendix A,'' 
dated November 2015, take precedence (i.e., the SSIs in the latter 
document prevail).
    (ii) Within 1,000 flight cycles measured from 12 months after 
the effective date of this AD.

(k) Repair

    If any cracked structure is found during any inspection required 
by paragraph (i) or (j) of this AD, repair before further flight 
using an FAA-approved method.

(l) Compliance Time Clarification

    For compliance times identified in paragraphs (i) and (j) of 
this AD that specify total flight cycles and total flight hours, and 
the SSI is a removable structural component, those compliance times 
must be measured on the SSI since its first installation on any 
airplane, regardless of what the airframe as a whole has 
accumulated. If the total flight cycles and total flight hours on 
the SSI are not available or cannot be determined, use the airframe 
total flight cycles and total flight hours for the compliance times 
identified in paragraphs (i) and (j) of this AD.

(m) No Alternative Inspections and Inspection Intervals

    After accomplishing the revision required by paragraph (h) of 
this AD, no alternative inspections or inspection intervals may be 
used unless the alternative inspection or inspection interval is 
approved as an alternative method of compliance (AMOC) in accordance 
with the procedures specified in paragraph (p) of this AD.

(n) Terminating Action for AD 2004-07-22 R1

    Accomplishing the revision required by paragraph (h) of this AD 
and all of the initial inspections required by paragraph (i) or (j) 
of this AD, as applicable, terminates all requirements of AD 2004-
07-22 R1.

(o) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 1 hour per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(p) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO Branch, 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 certification office, send it to the attention of the 
person identified in paragraph (q) 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 Branch, 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 for AD 2004-07-22 R1 are approved as AMOCs 
for the corresponding provisions of paragraphs (h), (i), (j), and 
(k) of this AD for the SSIs identified in the AMOC, except for any 
SSI that has an expanded inspection area identified in Boeing 
Document D6-35022, ``Supplemental Structural Inspection Document for 
Model 747 Airplanes,'' Revision H, dated September 2013; or Boeing 
Document D6-35022-1, ``747-400 LCF Supplemental Structural 
Inspection Document--Appendix A,'' dated November 2015, as 
applicable.

(q) Related Information

    For more information about this AD, contact Bill Ashforth, 
Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 1601 
Lind Avenue SW, Renton, WA 98057-3356; phone: 425-917-6432; fax: 
425-917-6590; email: [email protected].

(r) 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.
    (i) Boeing Document D6-35022, ``Supplemental Structural 
Inspection Document for Model 747 Airplanes,'' Revision H, dated 
September 2013.
    (ii) Boeing Document D6-35022-1, ``747-400 LCF Supplemental 
Structural Inspection Document--Appendix A,'' dated November 2015.
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this referenced service 
information at the FAA, Transport Standards Branch, 1601 Lind Avenue 
SW, Renton, WA. For information on the availability of this material 
at the FAA, call 425-227-1221.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the

[[Page 7979]]

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 9, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-03429 Filed 2-22-18; 8:45 am]
 BILLING CODE 4910-13-P