[Federal Register Volume 80, Number 127 (Thursday, July 2, 2015)]
[Proposed Rules]
[Pages 38038-38041]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-16154]


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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]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2008-26-
07, which applies 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. AD 2008-26-07 currently requires repetitive inspections of 
the lower skin and stringers at certain stations, and corrective 
actions if necessary. This proposed AD is intended to complete certain 
mandated programs intended to support the airplane reaching its limit 
of validity (LOV) of the engineering data that support the established 
structural maintenance program. This proposed AD would also require 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. We are proposing 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: We must receive comments on this proposed AD by August 17, 2015.

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, 
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 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: 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: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-2455; 
Directorate Identifier 2014-NM-180-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 December 12, 2008, we issued AD 2008-26-07, Amendment 39-15773 
(73 FR 78946, December 24, 2008), for 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. AD 2008-26-07 requires repetitive inspections of the 
lower skin and stringers at stations Xw=408 and Xw=-408, and corrective 
actions if

[[Page 38039]]

necessary. AD 2008-26-07 resulted from reports of cracks in the skins 
and stringers at the end fasteners common to the stringer end fittings 
at stations Xw=408 and Xw=-408 wing splice joints. We issued AD 2008-
26-07 to detect and correct fatigue cracking in the skins and stringers 
at the end fasteners common to the stringer end fittings at certain 
station and wing splice joints, which could result in wing structure 
that might not sustain limit load, and consequent loss of structural 
integrity of the wing.

Widespread Fatigue Damage

    As described in FAA Advisory Circular 120-104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs 
have been developed to support initiatives that will ensure the 
continued airworthiness of aging airplane structure. The last element 
of those initiatives is the requirement to establish a limit of 
validity (LOV) of the engineering data that support the structural 
maintenance program under 14 CFR 26.21. This proposed AD is the result 
of an assessment of the previously established programs by Boeing 
during the process of establishing the LOV for 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. The actions specified in this proposed AD are 
necessary to complete certain programs to ensure the continued 
airworthiness of aging airplane structure and to support an airplane 
reaching its LOV.
    We are proposing 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.

Actions Since AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 
24, 2008) Was Issued

    Since we issued AD 2008-26-07, Amendment 39-15773 (73 FR 78946, 
December 24, 2008), we have received new service information to ensure 
the continued airworthiness of aging airplane structure and to support 
an airplane reaching its LOV. The new inspection and modification of 
the left and right lower wing skin, stringers, and splice fittings will 
support operation up to the DC-8 LOV.

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 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

    This proposed AD would retain all requirements of AD 2008-26-07, 
Amendment 39-15773 (73 FR 78946, December 24, 2008). This proposed AD 
would also 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 if 
necessary; and corrective actions.

Clarification of Actions for Groups 1-3, Configuration 1 Airplanes

    Where the Accomplishment Instructions of Boeing Service Bulletin 
DC8-57-104, dated August 18, 2014, specifies repair, this AD also 
requires an inspection and possible other actions.

Change to AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 
2008)

    Since AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 
2008), was issued, the AD format has been revised, and certain 
paragraphs have been rearranged with new title headers. As a result, 
the corresponding paragraph identifiers have been redesignated in this 
proposed AD, as listed in the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                            Corresponding requirement in
       Requirement in AD 2008-26-07               this proposed AD
------------------------------------------------------------------------
paragraph (e).............................  paragraph (f)
paragraph (f).............................  paragraph (g)
paragraph (g).............................  paragraph (h)
paragraph (h).............................  paragraph (i)
------------------------------------------------------------------------

Explanation of ``RC'' Steps in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which steps in the service information are required for 
compliance with an AD. Differentiating these steps from other tasks in 
the service information is expected to improve an owner's/operator's 
understanding of crucial AD requirements and help provide consistent 
judgment in AD compliance. The steps identified as RC (required for 
compliance) in any service information identified previously have a 
direct effect on detecting, preventing, resolving, or eliminating an 
identified unsafe condition.
    For service information that contains steps that are labeled as 
Required for Compliance (RC), the following provisions apply: (1) 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, 
and an AMOC is required for any deviations to RC steps, including 
substeps and identified figures; and (2) 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.

Costs of Compliance

    We estimate that this proposed AD affects 12 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 38040]]



                                                 Estimated Costs
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                                                                                Cost
                 Action                          Labor cost           Parts     per      Cost on U.S. operators
                                                                       cost   product
----------------------------------------------------------------------------------------------------------------
Inspection [retained actions from AD     6 work-hours x $85 per           $0     $510  $6,120 per inspection
 2008[dash]26[dash]07, Amendment 39-      hour = $510 per                               cycle
 15773 (73 FR 78946, December 24,         inspection cycle.
 2008)].
ETHF Inspection [new proposed action]..  8 work-hours x $85 per           $0     $680  $8,160 per inspection
                                          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 proposed 
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.
----------------------------------------------------------------------------------------------------------------

    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 
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) 
2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008), and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2015-2455; Directorate Identifier 
2014-NM-180-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by August 17, 
2015.

(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

    Joint Aircraft System Component (JASC) 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

    This paragraph restates the requirements of paragraph (f) of AD 
2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008). 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

[[Page 38041]]

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

    This paragraph restates the exception specified in paragraph (g) 
of AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 
2008). 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

    This paragraph restates the exception specified in paragraph (h) 
of AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 
2008): 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: 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, 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: 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., ``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. 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)(1) of this AD. 
Information may be emailed to [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair 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) 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

    (1) 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: [email protected].
    (2) For service information identified in this AD, 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.

    Issued in Renton, Washington, on June 24, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-16154 Filed 7-1-15; 8:45 am]
 BILLING CODE 4910-13-P