[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]
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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.
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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