[Federal Register Volume 61, Number 20 (Tuesday, January 30, 1996)]
[Rules and Regulations]
[Pages 2902-2903]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-1569]



=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-NM-178-AD; Amendment 39-9498; AD 95-13-11 R1]


Airworthiness Directives; McDonnell Douglas Model DC-10-10 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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

SUMMARY: This amendment clarifies information in an existing 
airworthiness directive (AD), applicable to certain McDonnell Douglas 
Model DC-10-10 airplanes, that currently requires repetitive 
inspections to detect cracking of the upper caps in the front spar of 
the left and right wing, and repair, if necessary. The actions 
specified in that AD are intended to prevent progression of fatigue 
cracking, which could cause reduced structural integrity of the wing 
front spar and damage to adjacent structures. This amendment clarifies 
the requirements of the current AD by revising the area of inspection. 
This amendment is prompted by communications received from affected 
operators that the current requirements of the AD are unclear.

DATES: Effective August 7, 1995.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of August 7, 1995 (60 FR 35326, July 7, 1995).

ADDRESSES: The service information referenced in this AD may be 
obtained from McDonnell Douglas Corporation, 3855 Lakewood Boulevard, 
Long Beach, California 90846, Attention: Technical Publications 
Business Administration, Department C1-L51 (2-60). This information may 
be examined at the Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Los Angeles Aircraft Certification Office, 
Transport Airplane Directorate, 3960 Paramount Boulevard, Lakewood, 
California; or at the Office of the Federal Register, 800 North Capitol 
Street NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: John Cecil, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712; telephone (310) 627-5322; fax (310) 627-
5210.

SUPPLEMENTARY INFORMATION: On June 22, 1995, the FAA issued AD 95-13-
11, amendment 39-9291 (60 FR 35326, July 7, 1995), which is applicable 
to certain McDonnell Douglas Model DC-10-10 airplanes. That AD requires 
repetitive eddy current test high frequency (ETHF) surface inspections 
to detect fatigue cracking, and repair of the upper cap in the front 
spar of the wing if any cracking is found. That AD also requires 
additional repetitive inspections after any repair of the upper cap. 
Additionally, that AD stipulates that, if the preventive modification 
is installed on an airplane on which no cracks are found during the 
initial inspection, the repetitive inspections may be terminated. That 
action was prompted by reports of fatigue cracking in the upper cap of 
the front spar of the wing in the forward flange area. The actions 
required by that AD are intended to prevent progression of fatigue 
cracking, which could cause reduced structural integrity of the wing 
front spar and damage to adjacent structures.
    Since the issuance of that AD, the FAA has received communications 
from affected operators that the area defined for the ETHF surface 
inspection is unclear. Specifically, these operators have indicated 
that the referenced McDonnell Douglas DC-10 Service Bulletin 57-129, 
dated August 12, 1994, recommends inspection of the upper cap of the 
front spar of the left and right wing ``between'' stations Xos 667.678 
and Xos 789.645 in certain paragraphs but describes the inspection 
``at'' stations Xos 667.678 and Xos 789.645 in the accomplishment 
instructions. AD 95-13-11 requires inspection ``between'' stations Xos 
667.678 and Xos 789.645.
    These operators have therefore, requested that the FAA clarify the 
AD to indicate exactly what area is required to be inspected.
    In considering this request, and upon further review of the wording 
of the current AD, the FAA concurs that some clarification is 
necessary.
    It was the FAA's intent that the requirements of AD 95-13-11 be 
parallel to those actions recommended by the manufacturer in the 
accomplishment instructions of its referenced service bulletin. The 
intended requirements of the AD were that affected operators would 
conduct the ETHF inspections to detect fatigue cracks at the areas 
where cracking had been reported, namely at stations Xos 667.678 and 
Xos 789.645. However, as AD 95-13-11 is currently worded, operators may 
incorrectly conduct ETHF inspections ``between'' these stations, rather 
than ``at'' those stations. Such misunderstanding could result in 
operators unnecessarily conducting ETHF inspections at other stations, 
which would be of no significant safety value and would entail 
incurring needless additional costs in labor and downtime.
    Operators should note that the economic information supplied in the 
preamble of AD 95-13-11 remains unchanged since that information was 
based on the workhours required to perform the ETHF inspection at 
stations Xos 667.678 and Xos 789.645, in accordance with data supplied 
in McDonnell Douglas Service Bulletin 57-129, dated August 12, 1994.
    Since it is obvious that the required ETHF inspection area is not 
totally clear in the way that AD 95-13-11 is currently worded, the FAA 
has determined that the wording of paragraph (a) of the AD must be 
revised to clarify the intent of the required actions. This action 
revises that paragraph to specify that the inspection area is at 
stations Xos 667.678 and Xos 789.645.
    Action is taken herein to clarify these requirements of AD 95-13-11 
and to correctly add the AD as an amendment to section 39.13 of the 
Federal Aviation Regulations (14 CFR 39.13).
    The final rule is being reprinted in its entirety for the 
convenience of affected operators. The effective date remains August 7, 
1995.
    Since this action only clarifies a current requirement, it has no 
adverse economic impact and imposes no additional burden on any person. 
Therefore, notice and public procedures hereon are unnecessary.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Correction

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows: 

[[Page 2903]]


PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 USC 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-9291 (60 FR 
35326, July 7, 1995), and by adding a new airworthiness directive (AD), 
amendment 39-9498, to read as follows:

95-13-11 R1 McDonnell Douglas: Amendment 39-9498. Docket 94-NM-178-
AD. Revises AD 95-13-11, Amendment 39-9291.

    Applicability: Model DC-10-10 airplanes, as listed in McDonnell 
Douglas DC-10 Service Bulletin 57-129, dated August 12, 1994; 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must use the authority 
provided in paragraph (e) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition; or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent reduced structural integrity of the wing front spar 
and damage to adjacent structures due to fatigue cracking in the 
upper cap of the front spar of the wing, accomplish the following:
    (a) Prior to the accumulation of 10,000 total landings, or 
within 1,800 landings after the effective date of this AD, whichever 
occurs later, perform an initial eddy current test high frequency 
(ETHF) surface inspection to detect cracks in the upper cap of the 
front spar of the left and right wing at stations Xos 667.678 and 
Xos 789.645, in accordance with McDonnell Douglas DC-10 Service 
Bulletin 57-129, dated August 12, 1994. Repeat this inspection 
thereafter at the intervals specified in paragraph (b) or (c) of 
this AD, as applicable.
    (b) For airplanes on which no crack is found: Repeat the 
inspection required by paragraph (a) of this AD thereafter at 
intervals not to exceed 10,000 landings, or accomplish the crack 
preventative modification in accordance with McDonnell Douglas DC-10 
Service Bulletin 57-129, dated August 12, 1994. Accomplishment of 
that preventative modification constitutes terminating action for 
the requirements of this paragraph.
    (c) For airplanes on which any crack is found that is identified 
as ``Condition II'' in McDonnell Douglas DC-10 Service Bulletin 57-
129, dated August 12, 1994: Accomplish paragraphs (c)(1) and (c)(2) 
of this AD in accordance with that service bulletin.
    (1) Prior to further flight, perform the permanent repair for 
cracks in accordance with the service bulletin; and
    (2) Within 12,500 landings after the installation of the 
permanent repair specified in paragraph (c)(1) of this AD, perform 
an ETHF surface inspection for cracks, in accordance with the 
service bulletin. Repeat this inspection thereafter at intervals not 
to exceed 7,000 landings.
    (d) For airplanes on which any crack is found that is identified 
as ``Condition III'' in McDonnell Douglas DC-10 Service Bulletin 57-
129, dated August 12, 1994: Prior to further flight, repair the 
cracking in accordance with a method approved by the Manager, Los 
Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane 
Directorate.
    (e) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Los Angeles ACO. Operators shall 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Los Angeles ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

    (f) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.
    (g) The inspections, modification, and permanent repair shall be 
done in accordance with McDonnell Douglas DC-10 Service Bulletin 57-
129, dated August 12, 1994. This incorporation by reference was 
approved previously by the Director of the Federal Register, in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of August 7, 
1995 (60 FR 35326, July 7, 1995). Copies may be obtained from 
McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, 
California 90846, Attention: Technical Publications Business 
Administration, Department C1-L51 (2-60). Copies may be inspected at 
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or at the FAA, Transport Airplane Directorate, 
Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

    (g) This amendment is effective on August 7, 1995.

    Issued in Renton, Washington, on January 22, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-1569 Filed 1-29-96; 8:45 am]
BILLING CODE 4910-13-U