[Federal Register Volume 60, Number 141 (Monday, July 24, 1995)]
[Rules and Regulations]
[Pages 37821-37822]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-18029]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-176-AD; Amendment 39-9315; AD 95-11-11 R1]
Airworthiness Directives; McDonnell Douglas Model DC-10-10, -15,
-30, -40, and KC-10 (Military) Series 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
DC-10 and KC-10 series airplanes, that currently requires repetitive
eddy current inspections to detect fatigue cracking of the pylon aft
bulkhead flange, upper pylon box web, fitting radius, and adjacent
tangent areas; and repair, if necessary. The actions specified in that
AD are intended to prevent failure of the wing pylon aft bulkhead due
to fatigue cracking, which could lead to separation of the engine and
pylon from the airplane. This amendment clarifies the requirements of
the current AD by specifying the type of initial and repetitive
inspections that must be conducted. This amendment is prompted by
communications received from affected operators that the current
requirements of the AD are unclear.
DATES: Effective July 3, 1995. -
The incorporation by reference of certain publications listed in
the regulations was approved previously by the Director of the Federal
Register as of July 3, 1995 (60 FR 28524, June 1, 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, Dept. 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: Maureen Moreland, Aerospace Engineer,
Airframe Branch, ANM-120L, Los Angeles Aircraft Certification Office,
FAA, Transport Airplane Directorate, 3960 Paramount Boulevard,
Lakewood, California 90712; telephone (310) 627-5238; fax (310) 627-
5210.
SUPPLEMENTARY INFORMATION: On May 19, 1995, the FAA issued AD 95-11-11,
amendment 39-9244 (60 FR 28524, June 1, 1995), which is applicable to
certain McDonnell Douglas Model DC-10-10, -15, -30, -40, and KC-10
(military) series airplanes. That AD requires repetitive eddy current
inspections to detect fatigue cracking of the pylon aft bulkhead
flange, upper pylon box web, fitting radius, and adjacent tangent
areas; and repair, if necessary. That action was prompted by fatigue
cracking found in the wing pylon aft bulkheads on two airplanes. The
actions required by that AD are intended to prevent failure of the wing
pylon aft bulkhead due to fatigue cracking, which could lead to
separation of the engine and pylon from the airplane. -
Since the issuance of that AD, the FAA has received communications
from affected operators that the requirements for the eddy current
inspections, as iterated in the AD, are unclear. Specifically, these
operators have indicated that the referenced McDonnell Douglas Alert
Service Bulletin A54-106, Revision 2, dated November 3, 1994,
recommends that ``eddy current bolt hole inspections'' and ``eddy
current surface probe inspections'' be conducted of the subject areas;
however, the AD indicates that merely an ``eddy current inspection'' is
required. Additionally, these operators point out that the service
bulletin recommends
[[Page 37822]]
that only the ``eddy current surface probe inspection'' be repeated;
however, the AD indicates that merely the ``eddy current inspection''
must be repeated. -
These operators have requested that the FAA clarify AD 95-11-11 to
indicate exactly which type of eddy current inspection is to be
conducted as the initial and repetitive inspection. -
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 95-11-11 be
parallel to those actions recommended by the manufacturer in its
referenced service bulletin. The intended requirements of the AD were
that affected operators would conduct an initial eddy current bolt hole
inspection and eddy current surface probe inspection to detect fatigue
cracks in the subject areas, and would repeat only the eddy current
surface probe inspection thereafter. However, as AD 95-11-11 is
currently worded, operators may incorrectly interpret the requirements
as requiring that both types of eddy current inspections be repeated.
Such misinterpretation could result in operators conducting unnecessary
repetitive eddy current bolt hole inspections, which would be of no
significant safety value and would entail incurring needless additional
costs in labor and downtime. -
Since it is obvious that these requirements are not totally clear
in the way that AD 95-11-11 is currently worded, the FAA has determined
that the wording of paragraph (a) the AD must be revised to clarify the
intent of the required actions. This action revises that paragraph to
specify that, initially, both an eddy current bolt hole inspection and
an eddy current surface probe inspection are required within 1,800
landings after the effective date of this AD. The eddy current surface
probe inspection must then be repeated at intervals not to exceed 1,800
landings.
Action is taken herein to clarify these requirements of AD 95-11-11
and to correctly add the AD as an amendment to section 39.13 of the
Federal Aviation Regulations (14 CFR 39.13). The effective date of the
rule remains July 3, 1995. -
The final rule is being reprinted in its entirety for the
convenience of affected operators. -
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:
PART 39--AIRWORTHINESS DIRECTIVES -
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended] -
2. Section 39.13 is amended by removing amendment 39-9244 (60 FR
28524, June 1, 1995), and by adding a new airworthiness directive (AD),
amendment 39-9315, to read as follows:
95-11-11 R1 McDonnell Douglas: Amendment 39-9315. Docket 94-NM-176-
AD. Revises AD 95-11-11, Amendment 39-9244.
-Applicability: Model DC-10-10, -15, -30, -40, and KC-10
(military) series airplanes; as listed in McDonnell Douglas Alert
Service Bulletin A54-106, Revision 2, dated November 3, 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 (d) 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 failure of the wing pylon aft bulkhead due to fatigue
cracking, which could lead to separation of the engine and pylon
from the airplane, accomplish the following: -
(a) Prior to the accumulation of 1,800 landings after the
effective date of this AD, conduct an eddy current bolt hole
inspection and an eddy current surface probe inspection to detect
fatigue cracks in the pylon aft bulkhead flange, upper pylon box
web, fitting radius, and adjacent tangent areas, in accordance with
McDonnell Douglas Alert Service Bulletin A54-106, Revision 2, dated
November 3, 1994. Repeat the eddy current surface probe inspection
thereafter at intervals not to exceed 1,800 landings. -
(b) If any crack is found during any inspection required by
paragraph (a) of this AD, prior to further flight, repair in
accordance with a method approved by the Manager, Los Angeles
Aircraft Certification Office (ACO), FAA, Transport Airplane
Directorate. -
(c) Accomplishment of the gap inspection and necessary shimming
in accordance with ``Phase III,'' as specified in McDonnell Douglas
Alert Service Bulletin A54-106, Revision 2, dated November 3, 1994,
constitutes terminating action for the inspections required by
paragraph (a) of this AD. -
(d) 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, FAA, Transport
Airplane Directorate. 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.
-(e) 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. -
(f) The inspection shall be done in accordance with McDonnell
Douglas Alert Service Bulletin A54-106, Revision 2, dated November
3, 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 July 3, 1995 (60 FR 28524, June 1,
1995). Copies may be obtained from McDonnell Douglas Corporation,
3855 Lakewood Boulevard, Long Beach, California 90846, Attention:
Technical Publications Business Administration, Dept. C1-L51 (2-60).
Copies may be inspected at the FAA, Transport Airplane Directorate,
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. -
(g) This amendment is effective on July 3, 1995.
Issued in Renton, Washington, on July 17, 1995.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-18029 Filed 7-21-95; 8:45 am]
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