[Federal Register Volume 60, Number 83 (Monday, May 1, 1995)]
[Rules and Regulations]
[Pages 21041-21042]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-10586]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-54-AD; Amendment 39-212; AD 95-09-09]
Airworthiness Directives; McDonnell Douglas Model DC-8-60 Series
Airplanes Equipped With Engines Modified by Burbank Aeronautical
Corporation II (BAC II) in Accordance With Supplemental Type
Certificate (STC) SA4892NM or SA5455NM
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-8-60 series
airplanes. This action requires inspection to determine the part number
of the cone bolt on the right side of the forward mount of each engine,
and replacement of the bolt, if necessary. This amendment is prompted
by a report of failure of a cone bolt at that location on an engine of
one airplane. The actions specified in this AD are intended to prevent
failure of the cone bolt on the right side of the forward mount of the
engine, which may lead to separation of the engine during a critical
phase of flight.
DATES: Effective May 16, 1995.
Comments for inclusion in the Rules Docket must be received on or
before June 30, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-54-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056.
Information concerning this amendment may be obtained from or
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.
FOR FURTHER INFORMATION CONTACT: David Y. J. Hsu, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone
(310) 627-5323; fax (310) 627-5210.
SUPPLEMENTARY INFORMATION: Recently, the FAA received a report of
failure of a cone bolt on the right side of the forward mount of an
engine on a McDonnell Douglas Model DC-8-60 series airplane.
Investigation revealed that corrosion pitting at the base of the bolt
thread caused the cone bolt to fail. Further investigation indicated
that this cone bolt, BAC II part number (P/N) DC-8-21005-7, was re-
manufactured from a 15-year-old bolt. This bolt had accumulated 3,526
flight hours since it had been installed on the engine, which was
modified by Burbank Aeronautical Corporation II (BAC II) in accordance
with Supplemental Type Certificate (STC) SA4892NM. This condition, if
not corrected in a timely manner, could result in failure of the cone
bolt on the right side of the forward mount of the engine, which may
lead to separation of the engine during a critical phase of flight.
Since both STC's SA4892NM and SA5455NM specify the same cone bolts,
the FAA has determined that the subject unsafe condition is likely to
exist or develop on all Model DC-8-60 series airplanes equipped with
engines modified by BAC II in accordance with either STC. The FAA finds
that the differences in design and materials used to manufacture cone
bolts having Barry Controls part number, P/N 96013-1, make them less
susceptible to corrosion. Therefore, the FAA has determined that cone
bolts having BAC II part number, DC-8-21005-7, must be replaced with
cone bolts having the Barry Controls part number.
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design, this AD is
being issued to prevent failure of the cone bolt on the right side of
the forward mount of the engine, which may lead to separation of the
engine during a critical phase of flight. This AD requires a one-time
inspection to determine the part number of the cone bolt on the right
side of the forward mount of the engine, and replacement of certain
cone bolts having BAC II part numbers with cone bolts having Barry
Controls part numbers. This AD also requires that operators submit a
report to the FAA of the findings of discrepant bolts.
This is considered to be interim action until such time that all
cone bolts having BAC II part numbers have been removed from the fleet
and the FAA has accounted for all cone bolts having BAC II part
numbers. The information from the required reports from operators will
enable the FAA to account for those cone bolts and to determine if
additional rulemaking action is warranted.
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-54-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, [[Page 21042]] 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, 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 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 adding the following new
airworthiness directive:
95-09-09 McDonnell Douglas: Amendment 39-212. Docket 95-NM-54-AD.
Applicability: Model DC-8-61, -62, -62F, -63, and -63F airplanes
equipped with an engine modified by Burbank Aeronautical Corporation
II (BAC II) in accordance with Supplemental Type Certificate (STC)
SA4892NM or SA5455NM, 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) 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 cone bolt on the right side of the
forward mount of the engine, which may lead to separation of the
engine during a critical phase of flight, accomplish the following:
(a) Within 90 days after the effective date of this AD, perform
an inspection to determine the part number (P/N) of the cone bolt on
the right side of the forward mount of each of the four engines.
(1) If the cone bolt has Barry Controls P/N 96013-1, no further
action is required by this AD.
(2) If the cone bolt does not have Barry Controls P/N 96013-1,
prior to further flight, remove it and install a cone bolt having
Barry Controls P/N 96013-1, in accordance with either STC SA4892NM
or SA5455NM.
Note 2: Intervals for repetitive inspections and replacements of
life-limited cone bolts having Barry Controls P/N 96013- are
specified in STC's SA4892NM and SA5455NM.
(b) Within 10 days after replacing a cone bolt in accordance
with the requirements of paragraph (a)(2) of this AD, submit a
report that includes the information contained in paragraphs (b)(1),
(b)(2), (b)(3), and (b)(4) of this AD, to the Manager, Los Angeles
Aircraft Certification Office (ACO), 3960 Paramount Boulevard,
Lakewood, California 90712; telephone (310) 627-5323; fax (310) 627-
5210. 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.
(1) Series and fuselage serial number of Model DC-8 series
airplane.
(2) Total time and number of cycles on the engine since
installation of the engine modified by BAC II in accordance with STC
SA4892NM or SA5455NM.
(3) Number of bolts identified having BAC II P/N DC-8-21005-7.
(4) Number of bolts destroyed having BAC P/N DC-8-21005-7.
(c) As of the effective date of this AD, no person shall
install, on any airplane, a cone bolt having BAC II P/N DC-8-21005-7
on right side of the forward mount of the engine.
(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 3: 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
Secs. 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) This amendment becomes effective on May 16, 1995.
Issued in Renton, Washington, on April 25, 1995.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-10586 Filed 4-28-95; 8:45 am]
BILLING CODE 4910-13-U
