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[Federal Register Volume 76, Number 50 (Tuesday, March 15, 2011)]
[Proposed Rules]
[Pages 13926-13928]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-5898]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0221; Directorate Identifier 2010-NM-120-AD]
RIN 2120-AA64

Airworthiness Directives; 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; DC-8-50 Series Airplanes; DC-8F-54 and DC-8F-55 Airplanes; 
DC-8-60 Series Airplanes; DC-8-60F Series Airplanes; DC-8-70 Series 
Airplanes; and DC-8-70F Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain 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, DC-8-50 series airplanes, DC-8F-
54 and DC-8F-55 airplanes, DC-8-60 series airplanes, DC-8-60F series 
airplanes, DC-8-70 series airplanes, and DC-8-70F series airplanes. 
This proposed AD would require repetitive high frequency eddy current 
or repetitive low frequency eddy current inspections for cracks on the 
area around certain fasteners of the access opening doubler on the left 
and right wing center spar lower cap, and repair, if necessary. This 
proposed AD results from reports that cracks in the center spar lower 
cap and, in some cases, the web of the spar, have been found at 
stations Xrs=168.00, Xrs=251.00, and Xrs=358.00. We are proposing this 
AD to detect and correct cracks in the area around certain fasteners of 
the access opening doubler on the left and right wing center spar lower 
cap, which could compromise the structural integrity of the wing 
structure.

DATES: We must receive comments on this proposed AD by April 29, 2011.

ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, 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, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail 
[email protected]; Internet https://www.myboeingfleet.com. You may 
review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at the 
FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the

[[Page 13927]]

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 (telephone 800-
647-5527) is in the ADDRESSES section. Comments will be available in 
the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Dara Albouyeh, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712-
4137; telephone (562) 627-5222; fax (562) 627-5210.

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-2011-0221; 
Directorate Identifier 2010-NM-120-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

    We received reports that cracks in the center spar lower cap and, 
in some cases, the web of the spar, have been found at stations 
Xrs=168.00, Xrs=251.00, and Xrs=358.00. These cracks originate in the 
most inboard fastener hole of the access opening doublers. A total of 
12 cracks have been found in airplanes having accumulated between 
26,121 and 50,136 total flight cycles. The cracks appear to be 
consistent with fatigue cracks. Such cracking in the area around 
certain fasteners of the access opening doubler on the left and right 
wing center spar lower cap, if not detected and corrected, could 
compromise the structural integrity of the wing structure.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin DC8-57A103, dated 
May 5, 2010. This service bulletin describes procedures for repetitive 
high frequency eddy current (HFEC) inspections or low frequency eddy 
current (LFEC) inspections for cracks on the area around certain 
fasteners of the left and right wing center spar lower cap at stations 
Xrs=168.00, Xrs=251.00, and Xrs=358.00, and repair if necessary.
    This service bulletin also describes procedures for repetitive 
(post-repair) inspections for cracking of the repaired area, using the 
inspection defined in Method 101 of Section 57-10-06, or Method 101 or 
104 of Section 57-10-16, of the McDonnell Douglas DC-8 Supplemental 
Inspection Document (SID), Report L26-011, Volume II, Revision 8, dated 
January 2005, as applicable.
    For airplanes on which no cracking is found, the repetitive 
interval is either 1,750 flight cycles or 6,000 flight cycles, 
depending on the inspection type.
    For airplanes on which cracking is found, the repetitive interval 
for non-repaired areas is either 1,750 flight cycles or 6,000 flight 
cycles, depending on the inspection type.
    For airplanes on which cracking is found, the compliance time for 
the initial post-repair inspection is between 7,600 flight cycles and 
43,000 flight cycles after doing the repair, depending on the 
configuration and inspection type. The repetitive interval is between 
1,400 flight cycles and 5,300 flight cycles, depending on the 
configuration and inspection type.

Other Relevant Rulemaking

    This proposed AD will affect the inspections, corrective actions, 
and reports required by AD 2008-25-05, Amendment 39-15763 (73 FR 78936, 
December 24, 2008), for Principal Structural Elements (PSE) 57.08.013/-
014 and 57.08.035/-036 of the DC-8 SID.

FAA's Determination and Requirements of This Proposed AD

    We are proposing this AD because we evaluated all relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of these same type 
designs.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between the Proposed AD and the Service 
Information.''

Differences Between the Proposed AD and the Service Information

    Boeing Alert Service Bulletin DC8-57A103, dated May 5, 2010, does 
not specify a corrective action if cracking is found during the 
inspections of the repaired area. If cracking is found during the 
inspections of the repaired area, 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 would affect 41 airplanes of U.S. 
registry. We also estimate that it would take 12 work-hours per product 
to comply with this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of this 
proposed AD to the U.S. operators to be $41,820, or $1,020 per product.

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 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.

[[Page 13928]]

    For the reasons discussed above, I certify this 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), and
    3. 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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

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

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

The Boeing Company: Docket No. FAA-2011-0221; Directorate Identifier 
2010-NM-120-AD.

Comments Due Date

    (a) We must receive comments by April 29, 2011.

Affected ADs

    (b) This AD affects certain requirements of AD 2008-25-05, 
Amendment 39-15763.

Applicability

    (c) 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.

Subject

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

Unsafe Condition

    (e) This AD results from reports that cracks in the center spar 
lower cap and, in some cases, the web of the spar, have been found 
at stations Xrs=168.00, Xrs=251.00, and Xrs=358.00. The Federal 
Aviation Administration is issuing this AD to detect and correct 
cracks in the area around certain fasteners of the access opening 
doubler on the left and right wing center spar lower cap, which 
could compromise the structural integrity of the wing structure.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Inspection

    (g) Before the accumulation of 20,000 total flight cycles, or 
within 3,000 flight cycles after the effective date of this AD, 
whichever occurs later, do a high frequency eddy current (HFEC) or 
low frequency eddy current (LFEC) inspection for cracks on the area 
around certain fasteners of the access opening doubler on the left 
and right wing center spar lower cap, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin DC8-
57A103, dated May 5, 2010. If no crack is found, repeat the 
inspection thereafter at the applicable interval specified in 
paragraph 1.E., ``Compliance'' of Boeing Alert Service Bulletin DC8-
57A103, dated May 5, 2010.

Repair

    (h) If any crack is found during any inspection required by 
paragraph (g) of this AD, do paragraphs (h)(1), (h)(2), and (h)(3) 
of this AD.
    (1) Before further flight, repair the crack in accordance with 
Boeing Alert Service Bulletin DC8-57A103, dated May 5, 2010.
    (2) Within 6,000 flight cycles after doing the most recent HFEC 
inspection, or within 1,750 flight cycles after doing the most 
recent LFEC inspection; as applicable; do the inspection specified 
in paragraph (g) of this AD of the non-repaired area, and repeat the 
inspection of the non-repaired area thereafter at the applicable 
time in paragraph 1.E. ``Compliance,'' of Boeing Alert Service 
Bulletin DC8-57A103, dated May 5, 2010.
    (3) Within the applicable times specified in paragraph 1.E. 
``Compliance,'' of Boeing Alert Service Bulletin DC8-57A103, dated 
May 5, 2010, do the inspections of the repaired area, using the 
inspection defined in Method 101 of Section 57-10-06, or Method 101 
or 104 of Section 57-10-16, of the McDonnell Douglas DC-8 
Supplemental Inspection Document (SID), Report L26-011, Volume II, 
Revision 8, dated January 2005, as applicable. Repeat the inspection 
thereafter at the applicable intervals specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin DC8-57A103, dated 
May 5, 2010. If any crack is found, before further flight, repair 
the crack using a method approved in accordance with the procedures 
specified in paragraph (j) of this AD.
    (i) The inspections required by paragraph (h)(3) of this AD 
constitute compliance with paragraph (j) of AD 2008-25-05, Amendment 
39-15763, for the repaired area. All requirements of AD 2008-25-05 
that are not specifically referenced in this paragraph remain fully 
applicable and require compliance.

Alternative Methods of Compliance (AMOCs)

    (j)(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 the Related Information 
section of this AD.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
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. The AMOC approval letter must specifically reference this 
AD.
    (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 14 CFR 25.571, 
Amendment 45, and the approval must specifically refer to this AD.

Related Information

    (k) For more information about this AD, contact Dara Albouyeh, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 
3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone 
(562) 627-5222; fax (562) 627-5210; e-mail: [email protected].

    Issued in Renton, Washington, on March 7, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-5898 Filed 3-14-11; 8:45 am]
BILLING CODE 4910-13-P
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