[Federal Register Volume 63, Number 133 (Monday, July 13, 1998)]
[Proposed Rules]
[Pages 37508-37510]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-18471]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 63, No. 133 / Monday, July 13, 1998 /
Proposed Rules
[[Page 37508]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-147-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-9, DC-9-80,
and C-9 (Military) Series Airplanes; Model MD-88 Airplanes; and Model
MD-90 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain McDonnell Douglas Model
DC-9, DC-9-80, and C-9 (military) series airplanes; Model MD-88
airplanes; and Model MD-90 airplanes. This proposal would require a
one-time inspection of the forward attach pins of the outboard flight
spoiler actuators to determine whether the pins are of correct length,
and follow-on corrective actions. This proposal is prompted by a report
that forward attach pins of incorrect length were found to be installed
in the flight spoiler actuators on several in-service and in-production
airplanes. The actions specified by the proposed AD are intended to
prevent failure of the piston of the flight spoiler actuator and
consequent puncturing of the aft spar web, which could result in fuel
leakage and reduced structural integrity of the wings.
DATES: Comments must be received by August 27, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-147-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 The Boeing Company, Douglas Products Division, 3855
Lakewood Boulevard, Long Beach, California 90846, Attention: Technical
Publications Business Administration, Dept. 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, 3960
Paramount Boulevard, Lakewood, California.
FOR FURTHER INFORMATION CONTACT: Brent Bandley, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los
Angeles Aircraft Certification Office, 3960 Paramount Boulevard,
Lakewood, California 90712-4137; telephone (562) 627-5220; fax (562)
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 98-NM-147-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-114, Attention: Rules
Docket No. 98-NM-147-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received a report indicating that forward attach pins
of incorrect length (too short) were found to be installed in the
pistons of the outboard flight spoiler actuators on certain McDonnell
Douglas Model DC-9-80 series airplanes and Model MD-90 airplanes. These
pins were manufactured incorrectly by one vendor, and the flight
spoiler actuators that incorporate the incorrect pins have been
installed on a number of airplanes. If a forward attach pin is too
short, the pin and nut could come into contact with the piston lugs,
which could cause sustained stresses and consequent stress corrosion.
This condition, if not corrected, could result in failure of the piston
of the flight spoiler actuator and consequent puncturing of the aft
spar web, which could result in fuel leakage and reduced structural
integrity of the wings.
Explanation of Relevant Service Information
The FAA has reviewed and approved McDonnell Douglas Service
Bulletins DC9-27-355 and MD90-27-024, both dated February 24, 1998.
These service bulletins describe procedures for a one-time visual
inspection of the forward attach pin of the outboard flight spoiler
actuator on the left and right sides of the airplane to determine
whether the forward attach pin is of correct length, and follow-on
corrective actions, which include the following:
--Condition 1. For airplanes on which the length of the pins is
correct, the service bulletins describe procedures for modifying the
pin by etching a new part number on it and reinstalling it into the
flight spoiler actuator.
--Condition 2. For airplanes on which the length of the pins is
incorrect, the service bulletins describe procedures for a follow-on
visual inspection to detect corrosion of the outer transition radii of
the piston lugs of the flight
[[Page 37509]]
spoiler actuator, or discrepancies of the cadmium plating on the lugs.
If no corrosion or discrepancy is found, follow-on actions include
installing a new, improved pin, and a new washer and nut. If any
corrosion or discrepancy is found, corrective actions include removing
the actuator and attaching parts, performing a high frequency eddy
current (HFEC) inspection for cracking of the lugs of the actuator,
replacing any cracked piston assembly of the actuator with a new part,
reinstalling the actuator and attaching parts, and installing a new,
improved pin, and a new washer and nut.
Accomplishment of the actions specified in the service bulletins is
intended to adequately address the identified unsafe condition.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would require accomplishment of the actions specified in
the service bulletins described previously. The proposed AD also would
require that operators report results of inspection findings to the
FAA.
Cost Impact
There are approximately 1,700 airplanes of the affected design in
the worldwide fleet. The FAA estimates that 1,134 airplanes of U.S.
registry would be affected by this proposed AD.
It would take approximately 5 work hours per airplane (including
removal and reinstallation of the forward attach pin) to accomplish the
proposed one-time visual inspection, at an average labor rate of $60
per work hour. Based on these figures, the cost impact of this
inspection proposed by this AD on U.S. operators is estimated to be
$340,200, or $300 per airplane.
If the forward attach pin is determined to be of correct length, it
would take approximately 1 work hour per airplane to accomplish the
necessary modification, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of this modification proposed
by this AD on U.S. operators is estimated to be $60 per airplane.
If the forward attach pin is determined to be of incorrect length,
it would take approximately 1 work hour per airplane to accomplish the
follow-on visual inspection and replacement of the pin, at an average
labor rate of $60 per work hour. New pins would be provided by the
manufacturer at no cost to the operators. Based on these figures, the
cost impact of the follow-on visual inspection and replacement is
estimated to be $60 per airplane.
Should an operator be required to accomplish the HFEC inspection,
it would take approximately 11 work hours per airplane to accomplish
(including removal and reinstallation of the flight spoiler actuator),
at an average labor rate of $60 per work hour. Based on these figures,
the cost impact of the HFEC inspection is estimated to be $660 per
airplane.
Should an operator be required to accomplish the replacement of the
piston assembly of the flight spoiler actuator, it would take
approximately 5 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts would cost
approximately $2,590 per airplane. Based on these figures, the cost
impact of the replacement on U.S. operators is estimated to be $2,890
per airplane.
The cost impact figures discussed above are 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.
Regulatory Impact
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 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 98-NM-147-AD.
Applicability: Model DC-9-10, -20, -30, -40, and -50 series
airplanes, Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83),
and DC-9-87 (MD-87) series airplanes, Model MD-88 airplanes, and C-9
(military) series airplanes, as listed in McDonnell Douglas Service
Bulletin DC9-27-355, dated February 24, 1998; and Model MD-90
airplanes, as listed in McDonnell Douglas Service Bulletin MD90-27-
024, dated February 24, 1998; on which a piston assembly of the
flight spoiler actuator having part number (P/N) 4913415-505 or
4913415-507 is installed; 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 (d) 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 piston of the flight spoiler actuator
and consequent puncturing of the aft spar web, which could result in
fuel leakage and reduced structural integrity of the wings,
accomplish the following:
(a) Within 18 months after the effective date of this AD, remove
the forward attach pin of the outboard flight spoiler actuator of
the left and right wings of the airplane, and perform a one-time
visual inspection of the pin to determine whether it is of correct
length, in accordance with the Accomplishment Instructions of
McDonnell Douglas Service Bulletin DC9-27-355 [for Model DC-9-10, -
20, -30, -40, -50 series airplanes; Model C-9 (military) series
airplanes; Model DC-9-81 (MD-81), -82 (MD-82), -83 (MD-83), and -87
(MD-87) series airplanes; and Model MD-88 airplanes], or MD90-27-024
(for Model MD-90 airplanes), both dated February 24, 1998, as
applicable.
[[Page 37510]]
(1) Condition 1 (Correct Length). If the forward attach pin is
of correct length, prior to further flight, modify the pin by
reidentifying it with P/N 4935329-503, in accordance with the
applicable service bulletin.
(2) Condition 2 (Incorrect Length). If the forward attach pin is
of incorrect length, prior to further flight, perform a follow-on
visual inspection of the piston lugs of the flight spoiler actuator
for corrosion at the outer transition radii, or discrepancies of the
cadmium plating of the lugs, in accordance with the applicable
service bulletin.
(i) If no corrosion or discrepancy of the cadmium plating of the
lugs is detected, prior to further flight, install a new, improved
forward attach pin, P/N 4935329-503, and a new washer and nut, in
accordance with the applicable service bulletin.
(ii) If any corrosion or discrepancy of the cadmium plating of
the lugs is detected, prior to further flight, remove the actuator
and attaching parts, and perform a high frequency eddy current
inspection for cracking of the lugs of the actuator, in accordance
with the applicable service bulletin.
(A) If no cracking of the lugs is detected, prior to further
flight, reinstall the flight spoiler actuator and attaching parts,
and install a new, improved forward attach pin, P/N 4935329-503, and
a new washer and nut, in accordance with the applicable service
bulletin.
(B) If any cracking of the lugs is detected, prior to further
flight, replace the existing piston assembly of the flight spoiler
actuator with a new piston assembly having the same P/N; reinstall
the flight spoiler actuator and attaching parts; and install a new,
improved forward attach pin, P/N 4935329-503, and a new washer and
nut; in accordance with the applicable service bulletin.
(b) Within 10 days after accomplishing the inspection required
by paragraph (a) of this AD, submit a report of the inspection
results (both positive and negative findings) to the Manager, Los
Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane
Directorate, 3960 Paramount Boulevard, Lakewood, California 90712-
4137; fax (562) 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.
(c) As of the effective date of this AD, no person shall install
a forward attach pin of the flight spoiler actuator, P/N 4935329-1
or 4935329-501, on any airplane.
(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. 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.
Issued in Renton, Washington, on July 6, 1998.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-18471 Filed 7-10-98; 8:45 am]
BILLING CODE 4910-13-U
