[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]
BILLING CODE 4910-13-U