AD Amdt-39-212

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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]
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