[Federal Register Volume 60, Number 201 (Wednesday, October 18, 1995)]
[Rules and Regulations]
[Pages 53864-53866]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-25158]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-181-AD; Amendment 39-9397; AD 95-21-11]
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; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, -
40, and KC-10 (military) series airplanes. This action requires
inspections to detect cracking of the wing pylon aft bulkheads and
upper spar webs, and replacement or repair, if necessary. This
amendment is prompted by reports of fatigue cracking in the aft
bulkhead and upper spar webs. The actions specified in this AD are
intended to prevent failure of the wing pylon aft bulkhead due to
fatigue cracking; such failure could lead to separation of the engine
and pylon from the airplane.
DATES: Effective November 2, 1995. -
The incorporation by reference of McDonnell Douglas ROD Sketch 95-
09-14-005, dated September 14, 1995, as listed in the regulations, is
approved by the Director of the Federal Register as of November 2,
1995.
The incorporation by reference of McDonnell Douglas DC-10 Alert
Service Bulletin, A54-106, Revision 2, dated November 3, 1994, as
listed in the regulations, 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). -
Comments for inclusion in the Rules Docket must be received on or
before December 18, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-181-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. -
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 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.
FOR FURTHER INFORMATION CONTACT: Maureen Moreland, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone
(310) 627-5238; fax (310) 627-5210.
SUPPLEMENTARY INFORMATION: On July 24, 1992, the FAA issued AD 92-17-
13, amendment 39-8342 (57 FR 36894, August 17, 1992), which is
applicable to all McDonnell Douglas Model DC-10 series airplanes. That
AD requires a one-time visual inspection to detect cracks of the wing
pylon aft bulkheads and upper spar webs, and repair, if necessary.
Additionally, it requires that operators submit a report of inspection
findings to the FAA. That AD was prompted by reports of fatigue
cracking that occurred in the wing pylon aft bulkheads on two
airplanes. The fatigue cracking initiated at fastener holes and/or at
the lower forward edge of the bulkhead flange. Such fatigue cracking,
if not detected and corrected in a timely manner, could lead to failure
of the wing pylon aft bulkhead and subsequent separation of the engine
and pylon from the airplane. -
One of the intended purposes of the one-time visual inspection and
submission of reports required by that AD was to allow the FAA and the
manufacturer to obtain data as to the general condition of the affected
fleet relative to the identified fatigue cracking. Subsequent to the
issuance of that AD, the manufacturer has conducted further
investigation and analysis of the fatigue cracking found in the subject
areas. This effort revealed that the cracking was caused by fatigue,
which was accelerated by preload conditions. The manufacturer developed
inspection procedures to ensure that this fatigue cracking is
identified and corrected before it reaches critical lengths. -
Subsequently, 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 series airplanes. A correction of
the rule, AD 95-11-11 R1, amendment 39-9315, was published in the
Federal Register on July 24, 1995 (60 FR 37821). That AD was issued to
address the preload conditions discussed previously. 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. The initial
inspection is required to be accomplished prior to the accumulation of
1,800 landings after July 3, 1995. -
Since the issuance of those two AD's, the FAA has received a report
indicating that fatigue cracking in the aft bulkhead on the No. 1 pylon
had propagated through the upper forward flange and continued down the
vertical web of the bulkhead for approximately 11 inches. In light of
this report, the FAA has determined that additional measures must be
taken to ensure that any fatigue cracking in the aft bulkhead is
detected in a timely manner. -
The FAA previously reviewed and approved McDonnell Douglas DC-10
Alert Service Bulletin, A54-106, Revision 2, dated November 3, 1994,
which describes procedures for a one-time visual inspection to detect
fatigue cracking of the wing pylon aft bulkhead and upper spar web, and
replacement of any cracked bulkhead. This alert service bulletin also
describes procedures for conducting repetitive eddy current inspections
of this area (specified as ``Phase II''), and for conducting a gap
inspection of certain areas and necessary shimming (referred to as
``Phase III''). -
The FAA also has reviewed and approved McDonnell Douglas ROD Sketch
95-09-14-005, dated September 14, 1995, which supplements the
inspection procedures described in McDonnell Douglas DC-10 Alert
Service Bulletin A54-106. -
[[Page 53865]]
Since an unsafe condition has been identified that is likely to
exist or develop on other McDonnell Douglas DC-10-10, -15, -30, -40,
and KC-10 (military) series airplanes of the same type design, this AD
is being issued to prevent separation of the engine and pylon from the
airplane due to failure of the wing pylon aft bulkhead caused by
fatigue cracking. This AD applies only to those airplanes on which
neither the previously required eddy current inspections required by AD
95-11-11 R1 have been performed, nor the gap inspection and shimming
specified in paragraph (c) of AD 95-11-11 R1 have been performed. This
AD requires a one-time visual inspection to detect fatigue cracking of
the wing pylon aft bulkhead and upper spar web, replacement of any
cracked bulkhead, and repair of any cracked upper spar web.
Additionally, this AD requires that certain portions of the visual
inspection be accomplished with the aid of a borescope. These actions
are required to be accomplished in accordance with the alert service
bulletin and the ROD sketch described previously. Any necessary repair
is required to be accomplished in accordance with a method approved by
the FAA. -
For airplanes on which cracking is found during the required
inspections, this AD requires that operators report results of those
inspection findings to the FAA.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications shall identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 95-NM-181-AD.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, may be obtained from the Rules Docket at the
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-21-11 McDonnell Douglas: Amendment 39-9397. Docket 95-NM-181-AD.
Applicability: Model DC-10-10, -15, -30, -40, and KC-10
(military) series airplanes; as listed in McDonnell Douglas DC-10
Alert Service Bulletin A54-106, Revision 2, dated November 3, 1994;
certificated in any category; on which neither of the following
actions have been accomplished:
the initial eddy current inspections [required by
paragraph (a) of AD 95-11-11 R1 (amendment 39-9315)], as described
in Phase II of McDonnell Douglas DC-10 Alert Service Bulletin A54-
106, Revision 2, dated November 3, 1994.
the gap inspection and shimming [specified in paragraph
(c) of AD 95-11-11 R1 (amendment 39-9315)], as described in Phase
III of McDonnell Douglas DC-10 Alert Service Bulletin A54-106,
Revision 2, dated November 3, 1994.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise 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.
Note 2: Compliance with AD 92-17-13, amendment 39-8342 (57 FR
36894, August 7, 1992) does not constitute compliance with this AD.
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) Within 30 days after the effective date of this AD,
accomplish the actions required by paragraphs (a)(1) and (a)(2) of
this AD in accordance with McDonnell Douglas DC-10 Alert Service
Bulletin A54-106, Revision 2, dated November 3, 1994, and McDonnell
Douglas ROD Sketch 95-09-14-005, dated September 14, 1995.
[[Page 53866]]
(1) First, conduct a visual inspection using bright light,
mirrors, and appropriate optical aids to detect cracks of the left
and right wing pylon aft bulkhead and the upper spar web, in
accordance with the instructions in Phase I, paragraphs D.(1),
D.(2), D.(3), D.(4), and D.(5), of the alert service bulletin. The
ROD sketch must be used to supplement the inspection instructions
contained in the alert service bulletin. And
(2) Second, immediately subsequent to accomplishing the
inspection required by paragraph (a)(1) of this AD, conduct a visual
inspection, using the aid of either a flexible borescope or a rigid
borescope with a 90-degree field of view, to detect cracks of the
left and right wing pylon aft bulkhead in accordance with the
instructions in Phase I, paragraphs D.(2) and D.(3), of the alert
service bulletin. The ROD sketch must be used to supplement the
inspection instructions contained in the alert service bulletin.
(b) If any cracking is detected in the wing pylon aft bulkhead
during any inspection required by this AD, prior to further flight,
remove and replace the cracked bulkhead in accordance with McDonnell
Douglas DC-10 Alert Service Bulletin A54-106, Revision 2, dated
November 3, 1994.
(c) If any cracking is detected in the upper spar web during any
inspection required by 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.
(d) If any cracking is detected during any inspection required
by this AD, within 10 days after detection submit a report of the
inspection findings to the FAA, Transport Airplane Directorate, Los
Angeles ACO, Attention: Maureen Moreland (ANM-120L), 3960 Paramount
Boulevard, Lakewood, California 90712; fax (310) 627-5210. The
report shall include the airplane serial number, a sketch or
photograph of the cracking, a description of the cracking, and the
number of total landings and hours time-in-service on the airplane.
Information collection requirements contained in this regulation
have been approved by the Office of Management and Budget (OMB)
under the provisions of the Paperwork Reduction Act of 1980 (44
U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-
0056.
(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 3: 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 actions shall be done in accordance with McDonnell
Douglas ROD Sketch 95-09-14-005, dated September 14, 1995, and
McDonnell Douglas DC-10 Alert Service Bulletin A54-106, Revision 2,
dated November 3, 1994. The incorporation by reference of McDonnell
Douglas ROD Sketch 95-09-14-005, dated September 14, 1995, was
approved by the Director of the Federal Register in accordance with
5 U.S.C. 552(a) and 1 CFR part 51. The incorporation by reference of
McDonnell Douglas DC-10 Alert Service Bulletin A54-106, Revision 2,
dated November 3, 1994, 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 of
the ROD sketch may be obtained from McDonnell Douglas Corporation,
3855 Lakewood Boulevard, Long Beach, California 90846, Attention:
Customer Services Airframe, Department C1-L32 (35-35); telephone:
(310) 593-8114. Copies of the alert service bulletin 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.
(h) This amendment becomes effective on November 2, 1995.
Issued in Renton, Washington, on October 4, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-25158 Filed 10-17-95; 8:45 am]
BILLING CODE 4910-13-U
