[Federal Register Volume 61, Number 81 (Thursday, April 25, 1996)]
[Proposed Rules]
[Pages 18303-18305]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-10208]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-115-AD]
Airworthiness Directives; McDonnell Douglas Model DC-8 Series
Airplanes Equipped With Swivel-Type Bogie Beams on the Main Landing
Gears
AGENCY: Federal Aviation Administration, DOT.
ACTION: Supplemental notice of proposed rulemaking; reopening of
comment period.
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SUMMARY: This document revises an earlier proposed airworthiness
directive (AD), applicable to certain McDonnell Douglas Model DC-8
series airplanes, that would have required an inspection to detect
cracking of the swivel bogie beam lugs, and repair, if necessary. For
airplanes on which no cracking is
[[Page 18304]]
found, that proposed AD also would have required an inspection to
detect corrosion of the swivel pin lug surfaces and bores, and
modification of the forward bogie beams. That proposal was prompted by
reports indicating that swivel pin lugs of the main landing gear (MLG)
have failed due to cracks resulting from stress corrosion. The actions
specified by this proposed AD are intended to prevent such stress
corrosion, which could result in failure of the swivel-type bogie beam
of the MLG; this condition could result in collapse of the MLG during
landing. This action revises the proposed rule by adding certain repair
requirements.
DATES: Comments must be received by May 16, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-115-AD, 1601 Lind Avenue SW., Renton,
Washington 98055-4056. Comments may be inspected at this location
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal
holidays.
The service information referenced in the proposed rule 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, Transport Airplane
Directorate, Los Angeles Aircraft Certification Office (ACO), 3960
Paramount Boulevard, Lakewood, California.
FOR FURTHER INFORMATION CONTACT: Mike Lee, Aerospace Engineer, Airframe
Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office, 3960
Paramount Boulevard, Lakewood, California 90712; telephone (310) 627-
5325; fax (310) 627-5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 95-NM-115-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules
Docket No. 95-NM-115-AD, 1601 Lind Avenue SW., Renton, Washington
98055-4056.
Discussion
A proposal to amend part 39 of the Federal Aviation Regulations (14
CFR part 39) to add an airworthiness directive (AD), applicable to
certain McDonnell Douglas Model DC-8 series airplanes, was published as
a notice of proposed rulemaking (NPRM) in the Federal Register on
November 1, 1995 (60 FR 55496). That NPRM would have required a
magnetic particle inspection to detect cracking of the swivel bogie
beam lugs, and repair, if necessary. For airplanes on which no cracking
is found, that NPRM also would have required an inspection to detect
corrosion of the swivel pin lug surfaces and bores, and modification of
the forward bogie beams. That NPRM was prompted by reports indicating
that swivel pin lugs of the main landing gear (MLG) have failed due to
cracks resulting from stress corrosion. That condition, if not
corrected, could result in failure of the swivel-type bogie beam of the
MLG, which could result in collapse of the MLG during landing.
Since the issuance of that NPRM, the manufacturer has advised the
FAA that the dimensions of the reworked swivel pin lugs of Group I
airplanes may exceed the limits specified in the service information
cited. The NPRM addressed this condition for Group II airplanes, and
included a requirement for the repair of Group II airplanes on which
the dimensions of the reworked swivel pin lugs exceed the limits
specified in the proposed rule. However, the NPRM did not contain a
similar repair requirement for Group I airplanes. The FAA has
determined that such an ``on condition'' repair requirement is also
necessary for Group I airplanes, and has added this requirement to
paragraphs (b)(2)(i) and (b)(2)(ii) of this supplemental NPRM.
Since this change expands the scope of the originally proposed
rule, the FAA has determined that it is necessary to reopen the comment
period to provide additional opportunity for public comment.
The FAA also has revised paragraph (a) of this proposed rule to
clarify that the magnetic particle inspection is a ``one-time''
requirement.
There are approximately 148 McDonnell Douglas Model DC-8 series
airplanes of the affected design in the worldwide fleet. The FAA
estimates that 97 airplanes of U.S. registry would be affected by this
proposed AD, that it would take approximately 83 work hours per
airplane to accomplish the proposed actions, and that the average labor
rate is $60 per work hour. Based on these figures, the cost impact of
the proposed AD on U.S. operators is estimated to be $483,060, or
$4,980 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed requirements of
this AD action, and that no operator would accomplish those actions in
the future if this AD were not adopted.
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, will not have a significant economic impact,
positive or negative, on a substantial number of small entities under
the criteria of the Regulatory Flexibility Act. A copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the
[[Page 18305]]
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Mcdonnell Douglas: Docket 95-NM-115-AD.
Applicability: Model DC-8 airplanes equipped with main landing
gears having swivel type bogie beams on which the swivel pin lugs
have not been nickel plated, 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 request approval for an
alternative method of compliance in accordance with paragraph (e) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the swivel-type bogie beam of the main
landing gear (MLG) due to stress corrosion, which could result in
collapse of the MLG during landing, accomplish the following:
(a) Perform a one-time magnetic particle inspection to detect
cracking of the swivel bogie beam lugs, in accordance with McDonnell
Douglas DC-8 Service Bulletin 32-182, dated January 20, 1995;
McDonnell Douglas Service Bulletin DC8-32-182, Revision 01, dated
July 21, 1995, or Revision 02, dated August 30, 1995; at the later
of the times specified in paragraphs (a)(1) and (a)(2) of this AD.
(1) Prior to the accumulation of 11,600 total flight hours, or
within 10 years since the installation of the forward bogie beam of
the MLG, whichever occurs first.
(2) Prior to the accumulation of 2,000 flight hours, or 2 years
after the effective date of this AD, whichever occurs first.
(b) If no cracking is detected during the inspection required by
paragraph (a) of this AD, prior to further flight, perform a visual
inspection to detect corrosion in the swivel pin lug surfaces and
bores, in accordance with McDonnell Douglas DC-8 Service Bulletin
32-182, dated January 20, 1995; or McDonnell Douglas Service
Bulletin DC8-32-182, Revision 01, dated July 21, 1995, or Revision
02, dated August 30, 1995.
Note 2: Particular attention should be paid to the lubrication
of the swivel pin lug and the lower swivel pin bushing during
regular normal maintenance.
(1) If no corrosion is detected, prior to further flight,
accomplish paragraph (b)(1)(i), (b)(1)(ii), (b)(1)(iii), or
(b)(1)(iv) of this AD, as applicable, in accordance with the service
bulletin.
(i) For Group I airplanes on which the forward bogie beam has
not been modified previously: Modify the forward bogie beam in
accordance with the actions specified (for Group I airplanes) as
Condition 1 of the Accomplishment Instructions of the service
bulletin.
(ii) For Group I airplanes on which the forward bogie beam has
been modified previously: Modify the forward bogie beam in
accordance with the actions specified (for Group I airplanes) as
Condition 2 of the Accomplishment Instructions of the service
bulletin.
(iii) For Group II airplanes on which the forward bogie beam has
not been modified previously: Modify the forward bogie beam in
accordance with the actions specified (for Group II airplanes) as
Condition 1 of the Accomplishment Instructions of the service
bulletin.
(iv) For Group II airplanes on which the forward bogie beam has
been modified previously: Modify the forward bogie beam in
accordance with the actions specified (for Group II airplanes) as
Condition 2 of the Accomplishment Instructions of the service
bulletin.
(2) If any corrosion is detected, prior to further flight,
accomplish paragraph (b)(2)(i), (b)(2)(ii), (b)(2)(iii), or
(b)(2)(iv), as applicable, in accordance with the service bulletin.
(i) For Group I airplanes on which the forward bogie beam has
not been modified previously: Modify the forward bogie beam in
accordance with the actions specified (for Group I airplanes) as
Condition 1 of the Accomplishment Instructions of the service
bulletin. If the dimensions of the reworked swivel pin lug exceed
the limits specified in Table I of the service bulletin, prior to
further flight, repair in accordance with a method approved by the
Manager, Los Angeles Aircraft Certification Office (ACO), FAA,
Transport Airplane Directorate.
(ii) For Group I airplanes on which the forward bogie beam has
been modified previously: Modify the forward bogie beam in
accordance with the actions specified (for Group I airplanes) as
Condition 2 of the Accomplishment Instructions of the service
bulletin. If the dimensions of the reworked swivel pin lug exceed
the limits specified in Table I of the service bulletin, prior to
further flight, repair in accordance with a method approved by the
Manager, Los Angeles ACO.
(iii) For Group II airplanes on which the forward bogie beam has
not been modified previously: Modify the forward bogie beam in
accordance with the actions specified (for Group II airplanes) as
Condition 1 of the Accomplishment Instructions of the service
bulletin. If the dimensions of the reworked swivel pin lug exceed
the limits specified in Table I of the service bulletin, prior to
further flight, repair in accordance with a method approved by the
Manager, Los Angeles ACO.
(iv) For Group II airplanes on which the forward bogie beam has
been modified previously: Modify the forward bogie beam in
accordance with the actions specified (for Group II airplanes) as
Condition 2 of the Accomplishment Instructions of the service
bulletin. If the dimensions of the reworked swivel pin lug exceed
the limits specified in Table I of the service bulletin, prior to
further flight, repair in accordance with a method approved by the
Manager, Los Angeles ACO.
(c) If any cracking is detected during the inspection required
by paragraph (a) of this AD, prior to further flight, repair in
accordance with a method approved by the Manager, Los Angeles ACO.
(d) As of the effective date of this AD, no forward bogie beam
swivel pin lug shall be installed on any airplane, unless that
swivel pin lug has been modified in accordance with McDonnell
Douglas DC-8 Service Bulletin 32-182, dated January 20, 1995; or
McDonnell Douglas Service Bulletin DC8-32-182, Revision 01, dated
July 21, 1995, or Revision 02, dated August 30, 1995.
(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.
Issued in Renton, Washington, on April 19, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-10208 Filed 4-24-96; 8:45 am]
BILLING CODE 4910-13-U
