Document ID: FAA-2015-2455-0005
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2016-03-01T05:00Z

[Federal Register Volume 81, Number 40 (Tuesday, March 1, 2016)]
[Rules and Regulations]
[Pages 10465-10468]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-04035]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2455; Directorate Identifier 2014-NM-180-AD; 
Amendment 39-18415; AD 2016-04-21]
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 superseding Airworthiness Directive (AD) 2008-26-07 for 
all The Boeing Company Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-
32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8-50 
series airplanes; Model DC-8F-54 and DC-8F-55 airplanes; Model DC-8-60 
series airplanes; Model DC-8-60F series airplanes; Model DC-8-70 series 
airplanes; and Model DC-8-70F series airplanes. AD 2008-26-07 required 
repetitive inspections of the lower skin and stringers at certain 
stations, and corrective actions if necessary. This new AD continues to 
require the actions specified in AD 2008-26-07 and also requires an 
eddy current high frequency (ETHF) inspection for cracks of the 
fastener open holes common to the lower skins, stringers, and splice 
fittings at a certain station; installation of external doublers and 
fasteners and repetitive eddy current low frequency (ETLF) inspections 
around the fasteners for any crack; and corrective actions if 
necessary. This AD was prompted by certain mandated programs intended 
to support the airplane reaching its limit of validity of the 
engineering data that support the established structural maintenance 
program. We are issuing this AD to detect and correct cracks in the 
lower skins, stringers, and fastener holes of the splice fittings, 
which could result in the loss of structural integrity of the airplane.

DATES: This AD is effective April 5, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 5, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
January 28, 2009 (73 FR 78946, December 24, 2008).

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; 
telephone 206-544-5000, extension 2; fax 206-766-5683; 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-2015-2455.

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-
2455; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Document Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Chandra Ramdoss, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; 
telephone: 562-627-5239; fax: 562-627-5210; email: 
Chandraduth.Ramdoss@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2008-26-07, Amendment 39-15773 (73 FR 78946, 
December 24, 2008), (``AD 2008-26-07''). AD 2008-26-07 applied to all 
McDonnell Douglas Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, 
DC-8-33, DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8-50 series 
airplanes; Model DC-8F-54 and DC-8F-55 airplanes; Model DC-8-60 series 
airplanes; Model DC-8-60F series airplanes; Model DC-8-70 series 
airplanes; and Model DC-8-70F series airplanes. The NPRM published in 
the Federal Register on July 2, 2015 (80 FR 38038) (``the NPRM''). The 
NPRM was prompted by certain mandated programs intended to support the 
airplane reaching its limit of validity of

[[Page 10466]]

the engineering data that support the established structural 
maintenance program. The NPRM proposed to continue to require the 
actions specified in AD 2008-26-07 and also to require an ETHF 
inspection for cracks of the fastener open holes common to the lower 
skins, stringers, and splice fittings at a certain station; 
installation of external doublers and fasteners and repetitive ETLF 
inspections around the fasteners for any crack; and corrective actions 
if necessary. We are issuing this AD to detect and correct cracks in 
the lower skins, stringers, and fastener holes of the splice fittings, 
which could result in the loss of structural integrity of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM and 
the FAA's response to the comment.

Request To Clarify the Actions in Paragraph (j)(1) of the Proposed AD

    Boeing requested that we clarify paragraph (j)(1) of the proposed 
AD. Boeing stated that paragraph (j)(1) of the proposed AD does not 
specify what to inspect or how to inspect. Boeing recommended that a 
description similar to that of paragraph (j)(2) of the proposed AD be 
included in paragraph (j)(1) of the proposed AD.
    We agree with the request to clarify the inspection requirements. 
Paragraph (j)(l) of the AD is for airplanes that have previous 
structural repairs at the lower skins, stringers, and splice. For those 
airplanes, because the details of the configuration are not known, a 
specific description of the area to be inspected cannot be given. 
Paragraph (j)(2) of this AD provides specific inspections for certain 
airplanes because those inspections are described in Boeing Service 
Bulletin DC8-57-104, dated August 18, 2014. However, that service 
information does not provide specific inspection areas for airplanes 
identified in paragraph (j)(1) of this AD. Therefore, for the 
inspection and applicable corrective actions, paragraph (j)(1) of this 
AD requires that the operator use a method approved in the accordance 
with the procedures specified in paragraph (m) of this AD. We have 
revised paragraph (j)(1) of this AD to specify the general inspection 
area, which includes the lower skins, stringers, and splice fittings.

Clarification of Actions Specified in Paragraph (k) of This AD.

    Paragraph (k) of the NPRM referred to Boeing Service Bulletin DC8-
57-104, dated August 18, 2014, for the compliance times for the actions 
required by that paragraph but did not include a reference for the 
installation and inspections required by paragraph (k) of this AD. We 
have revised paragraph (k) of this AD to refer to Boeing Service 
Bulletin DC8-57-104, dated August 18, 2014, as the appropriate source 
of service information for accomplishing the installation and 
inspections.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD with the changes described 
previously and minor editorial changes. We have determined that these 
minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Service Bulletin DC8-57-104, dated August 18, 
2014. The service information describes procedures for certain 
airplanes for an ETHF inspection for cracks of the fastener open holes 
common to the lower skins, stringers, and splice fittings at a certain 
station; installation of external doublers and fasteners and repetitive 
ETLF inspections around the fasteners for any crack; 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.

Costs of Compliance

    We estimate that this AD affects 12 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
----------------------------------------------------------------------------------------------------------------
Inspection [retained actions from   6 work-hours x $85                 $0            $510  $6,120 per inspection
 AD 2008[dash]26[dash]07,            per hour = $510 per                                    cycle.
 Amendment 39-15773 (73 FR 78946,    inspection cycle.
 December 24, 2008)].
ETHF Inspection [new action]......  8 work-hours x $85                 $0            $680  $8,160 per inspection
                                     per hour = $680 per                                    cycle.
                                     inspection cycle.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                 Action                           Labor cost            Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Installation of External Doubler........  5 work-hour x $85 per hour         $20,000  $20,425.
                                           = $425.
Repetitive ETLF inspection..............  8 work-hour x $85 per hour              $0  $680 per inspection cycle.
                                           = $680 per inspection
                                           cycle.
----------------------------------------------------------------------------------------------------------------

[[Page 10467]]

    For all actions and repairs on Groups 1-3, Configuration 1 
Airplanes, we have received no definitive data that would enable us to 
provide cost estimates 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 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
    (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 removing Airworthiness Directive (AD) 
2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008), and 
adding the following new AD:

2016-04-21 The Boeing Company: Amendment 39-18415; Docket No. FAA-
2015-2455; Directorate Identifier 2014-NM-180-AD.

(a) Effective Date

    This AD is effective April 5, 2016.

(b) Affected ADs

    This AD replaces AD 2008-26-07, Amendment 39-15773 (73 FR 78946, 
December 24, 2008).

(c) Applicability

    This AD applies to all The Boeing Company Model DC-8-11, DC-8-
12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, DC-8-43, 
DC-8-51, DC-8-52, DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, DC-8-61, DC-
8-62, DC-8-63, DC-8-61F, DC-8-62F, DC-8-63F, DC-8-71, DC-8-72, DC-8-
73, DC-8-71F, DC-8-72F, and DC-8-73F airplanes; certificated in any 
category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by certain mandated programs intended to 
support the airplane reaching its limit of validity of the 
engineering data that support the established structural maintenance 
program. We are issuing this AD to detect and correct cracks in the 
lower skins, stringers, and fastener holes of the splice fittings, 
which could result in the loss of structural integrity of the 
airplane.

(f) Compliance

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

(g) Retained Repetitive Inspections With No Changes

    This paragraph restates the requirements of paragraph (f) of AD 
2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008), 
with no changes. At the times specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin DC8-57A102, dated 
February 12, 2008, except as provided by paragraph (h) of this AD, 
do the applicable inspections for fatigue cracking of the lower skin 
and stringers at stations Xw = 408 and Xw = -408, and do all 
applicable corrective actions, by accomplishing all applicable 
actions specified in the Accomplishment Instructions of Boeing Alert 
Service Bulletin DC8-57A102, dated February 12, 2008. Do all 
corrective actions before further flight. Thereafter, repeat the 
inspections at the applicable intervals specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin DC8-57A102, dated 
February 12, 2008, until paragraph (j) of this AD is done.

(h) Retained Exception for Compliance Time With No Changes

    This paragraph restates the exception specified in paragraph (g) 
of AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 
2008), with no changes. Where Boeing Alert Service Bulletin DC8-
57A102, dated February 12, 2008, specifies a compliance time ``after 
the date on this service bulletin,'' this AD requires compliance 
within the specified compliance time after January 28, 2009 (the 
effective date of AD 2008-26-07).

(i) Retained Exception for Corrective Action With No Changes

    This paragraph restates the exception specified in paragraph (h) 
of AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 
2008), with no changes. If any cracking is found during any 
inspection required by paragraph (g) of this AD, and Boeing Alert 
Service Bulletin DC8-57A102, dated February 12, 2008, specifies to 
contact Boeing for appropriate action: Before further flight, repair 
the cracking using a method approved in accordance with the 
procedures specified in paragraph (m) of this AD.

(j) New Inspections and Corrective Action

    (1) For Groups 1-3, Configuration 1 airplanes identified in 
Boeing Service Bulletin DC8-57-104, dated August 18, 2014: At the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Service Bulletin DC8-57-104, dated August 18, 2014, except as 
required in paragraph (l) of this AD, do an inspection for any 
cracking of the lower skins, stringers, and splice fittings, and do 
all applicable corrective actions, using a method approved in 
accordance with the procedures specified in paragraph (m) of this 
AD.
    (2) For Groups 1-3, Configuration 2 airplanes identified in 
Boeing Service Bulletin DC8-57-104, dated August 18, 2014: At the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Service Bulletin DC8-57-104, dated August 18, 2014, except as 
required in paragraph (l) of this AD, do an eddy current high 
frequency (ETHF) inspection for any cracking of the fastener open 
holes common to the lower skins, stringers, and splice fittings at 
station Xw = 408 and Xw = -408 from stringer 51 to stringer 65, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin DC8-57-104, dated August 18, 2014. If any cracking is 
found, before further flight, repair the crack using a method 
approved in accordance with the procedures specified in paragraph 
(m) of this AD.

(k) New Doubler and Fastener Installation and Eddy Current Low 
Frequency (ETLF) Inspection of the External Doubler and Corrective 
Action

    If no crack is found during the inspection required by paragraph 
(j)(2) of this AD: At the applicable times specified in paragraph 
1.E.,

[[Page 10468]]

``Compliance,'' of Boeing Service Bulletin DC8-57-104, dated August 
18, 2014, install external doublers and fasteners, and do an 
external doubler ETLF inspection around the fasteners for any 
cracking, in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin DC8-57-104, dated August 18, 2014. Repeat 
the external ETLF inspection at the applicable intervals specified 
in 1.E., ``Compliance,'' of Boeing Service Bulletin DC8-57-104, 
dated August 18, 2014. If any cracking is found during any ETLF 
inspection required by this paragraph, before further flight, repair 
the crack using a method approved in accordance with the procedures 
specified in paragraph (m) of this AD.

(l) Exception to the Compliance Time

    Where Boeing Service Bulletin DC8-57-104, dated August 18, 2014, 
specifies a compliance time ``after the original issue date of this 
service bulletin,'' this AD requires compliance within the specified 
compliance time after the effective date of this AD.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles 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) of this AD. 
Information may be emailed to 9-ANM-LAACO-AMOC-REQUESTS@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Los Angeles 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 2008-26-07, Amendment 39-15773 (73 FR 
78946, December 24, 2008), are approved as AMOCs for the 
corresponding provisions of this AD.
    (5) Except as required by paragraphs (j) and (k) of this AD: For 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (m)(5)(i) and 
(m)(5)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. An AMOC is required for any deviations to RC steps, 
including substeps and identified figures.
    (ii) Steps not labeled 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 RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(n) Related Information

    For more information about this AD, contact Chandra Ramdoss, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; telephone: 562-
627-5239; fax: 562-627-5210; email: Chandraduth.Ramdos@faa.gov.

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
April 5, 2016.
    (i) Boeing Service Bulletin DC8-57-104, dated August 18, 2014.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
January 28, 2009 (73 FR 78946, December 24, 2008).
    (i) Boeing Alert Service Bulletin DC8-57A102, dated February 12, 
2008.
    (ii) Reserved.
    (5) For Boeing service information identified in this AD, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 
90846-0001; telephone 206-544-5000, extension 2; fax 206-766-5683; 
Internet https://www.myboeingfleet.com.
    (6) You may view this 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 15, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-04035 Filed 2-29-16; 8:45 am]
 BILLING CODE 4910-13-P