
[Federal Register: August 12, 2008 (Volume 73, Number 156)]
[Proposed Rules]               
[Page 46823-46826]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12au08-15]                         

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================



[[Page 46823]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0858; Directorate Identifier 2008-NM-054-AD]
RIN 2120-AA64

 
Airworthiness Directives; 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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
McDonnell Douglas airplanes identified above. This proposed AD would 
require repetitive inspections of the lower skin and stringers at 
stations Xw = 408 and Xw = -408 and corrective actions if necessary. 
This proposed AD results from reports of cracks in the skins and 
stringers at the end fasteners common to the stringer end fittings at 
station Xw = 408 and Xw = -408 wing splice joints. We are proposing 
this AD to detect and correct fatigue cracking in the skins and 
stringers at the end fasteners common to the stringer end fittings at a 
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.

DATES: We must receive comments on this proposed AD by September 26, 
2008.

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 AD, contact Boeing 
Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, 
Long Beach, California 90846, Attention: Data and Service Management, 
Dept. C1-L5A (D800-0024).

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; 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 (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, 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-2008-0858; 
Directorate Identifier 2008-NM-054-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 have received numerous reports of cracks in the skins and 
stringers at the end fasteners common to the stringer end fittings at 
station Xw = 408 and Xw = -408 wing splice joints. Results of an 
investigation conducted by Boeing Engineering revealed the cracks were 
due to fatigue. The area where the cracks were found is identified as a 
principal structural element (PSE). The earliest cracks were discovered 
at 21,519 total flight cycles, and 58,935 total flight hours. The 
cracks were discovered by visual inspections and findings of fuel 
leaks. In addition to unscheduled maintenance for repair of the PSE, 
this condition, if not corrected, could result in wing structure that 
might not sustain limit load, and consequent loss of structural 
integrity of the wing.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin DC8-57A102, dated 
February 12, 2008. The service bulletin describes the following 
procedures.

[[Page 46824]]



                 Described Actions and Compliance Times
------------------------------------------------------------------------
          Condition                  Action           Compliance times
------------------------------------------------------------------------
Initial inspection for all    Do initial high       Before the
 airplanes.                    frequency eddy        accumulation of
                               current (HFEC)        20,000 total flight
                               inspection of the     cycles, or within
                               lower wing skin or    1,500 flight cycles
                               stringers at the      or 2 years after
                               affected fastener     the date of the
                               hole areas--          service bulletin,
                               stations Xw = 408     whichever occurs
                               and Xw = -408,        latest.
                               stringers 51 to 64
                               (for sequence 101,
                               inspection sequence
                               1, inspection
                               method 01; or
                               sequence 103,
                               inspection sequence
                               1, inspection
                               method 03), or a
                               visual inspection
                               of any accessible
                               area along the
                               cross section of
                               the stringer in the
                               area of the
                               affected fastener
                               holes (for sequence
                               102, inspection
                               sequence 1,
                               inspection method
                               02).
Condition 1: No cracks at     Repeat the HFEC or    Intervals not to
 any of the locations--and     visual inspection,    exceed 600 flight
 prior inspection was done     as applicable.        cycles after doing
 by external skin eddy                               the external skin
 current inspection as given                         eddy current
 in sequence 103.                                    inspection.
Condition 1: No cracks at     Repeat the HFEC or    Intervals not to
 any of the locations--prior   visual inspection,    exceed 1,200 flight
 inspection was done by        as applicable.        cycles after doing
 external skin eddy current                          the external skin
 inspection as given in                              eddy current
 sequence 103--and--internal                         inspection and
 stringer inspection as                              internal stringer
 given in sequence 101 or                            inspection.
 102 is done.
Condition 2: Skin cracks      Repair crack and      Before further
 less than 3.7 inches long     repeat the            flight (repair
 in wing skin at stringer      applicable            only).
 end fittings.                 inspection
                               specified for
                               Condition 2, as
                               applicable.
Condition 2: Skin cracks      Repeat the HFEC or    Intervals not to
 less than 3.7 inches long     visual inspection,    exceed 600 flight
 in wing skin at stringer      as applicable.        cycles after doing
 end fittings-- and prior                            the external skin
 inspection was done by                              eddy current
 external skin eddy current                          inspection.
 inspection as given in
 sequence 103.
Condition 2: Skin cracks      Repeat the HFEC or    Intervals not to
 less than 3.7 inches long     visual inspection,    exceed 1,200 flight
 in wing skin at stringer      as applicable.        cycles after doing
 end fittings-- and prior                            the external skin
 inspection was done by                              eddy current
 external skin eddy current                          inspection and
 inspection as given in                              internal stringer
 sequence 103--and--internal                         inspection.
 stringer inspection as
 given in sequence 101 or
 102 is done.
Condition 3: Skin cracks      Contact Boeing for    Before further
 greater than 3.7 inches at    repair instructions.  flight.
 stringer end fittings.
Condition 4: Stringer cracks  Repair crack and      Before further
 at stringer end fittings.     repeat the            flight (repair
                               applicable            only).
                               inspection
                               specified for
                               Condition 4, as
                               applicable.
Condition 4: Stringer cracks  Repeat the HFEC or    Repeat at intervals
 at stringer end fittings--    visual inspection,    not to exceed 600
 and prior inspection was      as applicable.        flight cycles after
 done by external skin eddy                          doing the external
 current inspection as given                         skin eddy current
 in sequence 103.                                    inspection.
Condition 4: Stringer cracks  Repeat the HFEC or    Repeat at intervals
 at stringer end fittings--    visual inspection,    not to exceed 1,200
 and prior inspection was      as applicable.        flight cycles after
 done by external skin eddy                          doing the external
 current inspection as given                         skin eddy current
 in sequence 103--and--                              inspection and
 internal stringer                                   internal stringer
 inspection as given in                              inspection.
 sequence 101 or 102 is done.
Condition 5: Cracks at more   Contact Boeing for    Before further
 than two adjacent stringers.  repair instructions.  flight.
------------------------------------------------------------------------

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 the(se) same type 
design(s). This proposed AD would require accomplishing the actions 
specified in the service information described previously, except as 
discussed under ``Difference Between the Proposed AD and the Service 
Bulletin.''

Difference Between the Proposed AD and the Service Bulletin

    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
     Using a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by an Authorized Representative 
for the Boeing Commercial Airplanes Delegation Option Authorization 
Organization whom we have authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD would affect 87 airplanes of U.S. 
registry. The following table provides the estimated costs for U.S. 
operators to comply with this proposed AD.

[[Page 46825]]



                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                 Number of
                                                          Average                                                  U.S.-
                  Action                    Work hours   labor rate     Parts           Cost per product         registered           Fleet cost
                                                          per hour                                               airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection...............................            6          $80           $0  $480, per inspection cycle..           87  $41,760, per inspection
                                                                                                                              cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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.
    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, 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:

McDonnell Douglas: Docket No. FAA-2008-0858; Directorate Identifier 
2008-NM-054-AD.

Comments Due Date

    (a) We must receive comments by September 26, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD 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, 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.

Unsafe Condition

    (d) This AD results 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 are 
issuing this AD to detect and correct fatigue cracking in the skins 
and stringers at the end fasteners common to the stringer end 
fittings at a 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.

Compliance

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

Repetitive Inspections and Corrective Actions

    (f) 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 (g) 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 the service bulletin, except as 
provided by paragraph (h) of this AD. Do all corrective actions 
before further flight, in accordance with the service bulletin. 
Thereafter, repeat the inspections at the applicable intervals 
specified in paragraph 1.E. of the service bulletin.
    (g) Where Boeing Alert Service Bulletin DC8-57A102, dated 
February 12, 2008, specifies a compliance time after the date on the 
service bulletin, this AD requires compliance within the specified 
compliance time after the effective date of this AD.
    (h) If any cracking is found during any inspection required by 
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 
(i) of this AD.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, ATTN: Dara Albouyeh, Aerospace Engineer, Airframe 
Branch, ANM-120L, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; telephone (562) 627-5222; fax (562) 627-5210; has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19.
    (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 on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (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 an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who 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.
    (4) Accomplishing the requirements of this AD is an acceptable 
AMOC with the requirements of paragraph (b) of AD 93-01-15, 
amendment 39-8469, for those areas of principal structural element 
57.08.037/038.


[[Page 46826]]


    Issued in Renton, Washington, on July 31, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-18560 Filed 8-11-08; 8:45 am]

BILLING CODE 4910-13-P
