Document ID: FAA-2008-0497-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: McDonnell Douglas Model DC-8-61, DC-8-61F, DC 8 63, DC-8-63F, DC-8-71F, and DC-8-73F Airplanes
Posted Date: 2008-05-06T04:00Z

[Federal Register: May 6, 2008 (Volume 73, Number 88)]
[Proposed Rules]               
[Page 24887-24889]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06my08-24]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0497; Directorate Identifier 2007-NM-096-AD]
RIN 2120-AA64

 
Airworthiness Directives; McDonnell Douglas Model DC-8-61, DC-8-
61F, DC-8-63, DC-8-63F, DC-8-71F, and DC-8-73F Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain McDonnell Douglas Model DC-8-61, DC-8-61F, DC-8-63, DC-8-
63F, DC-8-71F, and DC-8-73F airplanes. For certain airplanes, this 
proposed AD would require non-destructive testing (NDT) to detect 
cracks of the door jamb corners of the forward and aft service doors, 
and doing applicable related investigative and corrective actions. For 
certain other airplanes, this proposed AD would require inspecting and 
repairing if necessary or replacing previously repaired door jamb 
corners with an applicable repair. This proposed AD results from 
reports of numerous cases of cracks in the skin at the door jamb 
corners of the forward and aft service doors. We are proposing this AD 
to detect and correct fatigue cracking of door jamb corners of the 
forward and aft service doors, which could adversely affect the 
structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by June 20, 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: Jon Mowery, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5322; 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-2008-0497; 
Directorate Identifier 2007-NM-096-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 reports of numerous cases of cracks found in the 
skin at the door jamb corners of forward and aft service doors, on 
certain McDonnell Douglas Model DC-8-61, DC-8-61F, DC-8-63, DC-8-63F, 
DC-8-71F, and DC-8-73F airplanes. Investigation revealed that cracks 
were caused by metal fatigue. Fatigue cracking of door jamb corners of 
the forward and aft service doors, if not detected and corrected, could 
adversely affect the structural integrity of the airplane.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin DC8-53A082, dated 
February 6, 2007. For certain airplanes, the service bulletin describes 
doing initial non-destructive testing (NDT) to detect cracks of the 
door jamb corners of the forward and aft service doors, and doing 
applicable related investigative and corrective actions. The applicable 
related investigative actions include repeating the NDT or doing 
repetitive inspections of the repaired door jamb corners, as 
applicable. The corrective actions include repairing the door jamb 
corners, and contacting Boeing for certain instructions, as applicable. 
For certain other airplanes, the service bulletin describes procedures 
for contacting Boeing for repair or inspection instructions or 
replacing previously repaired door jamb corners with an applicable 
repair.
    The service bulletin specifies the following compliance times:
     For the initial NDT: Within 2,000 landings or 3 years, 
whichever occurs first.
     For repetitive NDTs or inspections: Between 532 and 11,325 
landings depending on the NDT/inspection method.
     For corrective actions: Before further flight or before 
the repeat interval for the inspection method depending on the repair 
condition.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between the Proposed AD and Service Bulletin.''

Differences Between the Proposed AD and Service Bulletin

    Although the service bulletin recommends that operators of 
airplanes identified as Group 1, Configuration 3, contact the 
manufacturer for repeat inspection instructions, this proposed

[[Page 24888]]

AD would require operators to inspect and repair using a method 
approved by the FAA.
    The service bulletin recommends that operators of airplanes 
identified as Group 1, Configuration 4, 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

    There are about 299 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 55 airplanes of 
U.S. registry. The proposed testing would take about 1 work-hour per 
airplane, at an average labor rate of $80 per work-hour. Based on these 
figures, the estimated cost of the proposed AD for U.S. operators is 
$4,400, or $80 per airplane, per testing 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 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); 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

McDonnell Douglas: Docket No. FAA-2008-0497; Directorate Identifier 
2007-NM-096-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by June 20, 
2008.

Affected ADs

    (b) As specified in paragraph (g) of this AD, this AD affects 
certain requirements of AD 93-01-15, amendment 39-8469.

Applicability

    (c) This AD applies to McDonnell Douglas Model DC-8-61, DC-8-
61F, DC-8-63, DC-8-63F, DC-8-71F, and DC-8-73F airplanes, 
certificated in any category; as identified in Boeing Alert Service 
Bulletin DC8-53A082, dated February 6, 2007.

Unsafe Condition

    (d) This AD results from reports of numerous cases of cracks in 
the skin at the door jamb corners of forward and aft service doors. 
We are issuing this AD to detect and correct fatigue cracking of 
door jamb corners of the forward and aft service doors, which could 
adversely affect the structural integrity of the airplane.

Compliance

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

Testing, Inspecting, Repairing, and Related Investigative and 
Corrective Actions

    (f) At the applicable compliance time and repeat intervals 
listed in Tables 1 through 5 inclusive of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin DC8-53A082, dated 
February 6, 2007; except where the service bulletin 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: Do the actions specified in paragraph 
(f)(1), (f)(2), or (f)(3) of this AD, as applicable.
    (1) For airplanes identified as Group 1, Configurations 1 and 2, 
in the service bulletin: Do the testing and related investigative 
and corrective actions by accomplishing all the applicable actions 
specified in the Accomplishment Instructions of the service 
bulletin.
    (2) For airplanes identified as Group 1, Configuration 3, in the 
service bulletin: Inspect and repair discrepancies in accordance 
with a method approved by the Manager, Los Angeles Aircraft 
Certification Office (ACO), FAA.
    (3) For airplanes identified as Group 1, Configuration 4, in the 
service bulletin: Do the actions specified in paragraph (f)(3)(i) or 
(f)(3)(ii) of this AD.
    (i) Repair door jamb corners of the service door using a method 
approved in accordance with the procedures specified in paragraph 
(h) of this AD.
    (ii) Replace the previously repaired door jamb corners with an 
applicable repair in accordance with the Accomplishment Instructions 
of the service bulletin.

Compliance With Certain Requirements of AD 93-01-15

    (g) Accomplishment of the applicable actions required by 
paragraph (f) of this AD constitutes compliance with certain 
requirements of AD 93-01-15, as it pertains to the affected areas of 
principal structural elements 53.08.039 and 53.08.040 of McDonnell 
Douglas DC-8 Supplemental Inspection Document, dated December 1985.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, Los Angeles ACO has the authority to approve 
AMOCs for this AD, if requested in accordance with 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

[[Page 24889]]

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.

    Issued in Renton, Washington, on April 23, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-9883 Filed 5-5-08; 8:45 am]

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