[Federal Register Volume 63, Number 157 (Friday, August 14, 1998)]
[Rules and Regulations]
[Pages 43614-43615]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-21652]
[[Page 43614]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-20-AD; Amendment 39-10708; AD 98-17-06]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-9-80 Series
Airplanes and Model MD-88 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain McDonnell Douglas Model DC-9-80 series airplanes
and Model MD-88 airplanes, that requires repetitive inspections to
detect fatigue cracking of certain fuselage skin panels, and repair, if
necessary. For certain airplanes, this amendment also provides for an
optional preventative modification, which, if accomplished, would
terminate the repetitive inspections. This amendment is prompted by
reports of fatigue cracking of certain fuselage skin panels. The
actions specified by this AD are intended to prevent such fatigue
cracking, which could result in reduced structural integrity of the
airplane, and consequent loss of pressurization.
DATES: Effective September 18, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 18, 1998.
ADDRESSES: The service information referenced in this AD 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 Federal Aviation Administration
(FAA), Transport Airplane Directorate, Rules Docket, 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.
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) 627-5237; fax (562)
627-5210.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain McDonnell Douglas Model
DC-9-80 series airplanes and Model MD-88 airplanes was published in the
Federal Register on March 20, 1998 (63 FR 13579). That action proposed
to require repetitive inspections to detect fatigue cracking of certain
fuselage skin panels, and repair, if necessary. For certain airplanes,
that action also proposed to provide for an optional preventative
modification, which, if accomplished, would terminate the repetitive
inspections.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Support for the Proposed Rule
Several commenters support the proposed rule.
Request To Refer to Latest Service Information
One commenter requests that the AD also refer to McDonnell Douglas
MD-80 Service Bulletin 53-253, as amended by Change Notification 53-253
CN1, dated April 15, 1994. The FAA concurs with this request. The
change notification revises certain references used in preparation of
the service bulletin, and changes references to kit numbers and
contents of fastener kits. The FAA has revised the final rule to state
that the actions may be accomplished in accordance with either
McDonnell Douglas MD-80 Service Bulletin 53-253, dated March 31, 1994,
or McDonnell Douglas MD-80 Service Bulletin 53-253, as amended by
Change Notification 53-253 CN1, dated April 15, 1994.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the change previously
described. The FAA has determined that this change will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
There are approximately 1,200 airplanes of the affected design in
the worldwide fleet. The FAA estimates that 800 airplanes of U.S.
registry will be affected by this AD, that it will take approximately
24 work hours per airplane to accomplish the required inspection, and
that the average labor rate is $60 per work hour. Based on these
figures, the cost impact of the AD on U.S. operators is estimated to be
$1,152,000, or $1,440 per airplane, per inspection cycle.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the 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 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.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it 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 U.S.C. 106(g), 40113, 44701.
[[Page 43615]]
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
98-17-06 McDonnell Douglas: Amendment 39-10708. Docket 97-NM-20-AD.
Applicability: Model DC-9-80 series airplanes and Model MD-88
airplanes; as listed in McDonnell Douglas MD-80 Service Bulletin 53-
253, dated March 31, 1994; 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 loss of pressurization due to reduced structural
integrity of the airplane, accomplish the following:
(a) Prior to the accumulation of 44,500 total landings, or
within 4,500 landings after the effective date of this AD, whichever
occurs later: Perform a high frequency eddy current (HFEC)
inspection to detect fatigue cracking of the fuselage skin panels
between stations Y=160.000 and Y=200.000 at the left side of
longeron 22 below the airstair door cutout, in accordance with
McDonnell Douglas MD-80 Service Bulletin 53-253, dated March 31,
1994; or McDonnell Douglas MD-80 Service Bulletin 53-253, as amended
by Change Notification 53-253 CN1, dated April 15, 1994.
(b) If no cracking is detected, accomplish the actions specified
in either paragraph (b)(1) or (b)(2) of this AD, in accordance with
McDonnell Douglas MD-80 Service Bulletin 53-253, dated March 31,
1994; or McDonnell Douglas MD-80 Service Bulletin 53-253, as amended
by Change Notification 53-253 CN1, dated April 15, 1994; at the time
specified.
(1) Perform the inspection required by paragraph (a) of this AD
thereafter at intervals not to exceed 4,500 landings until the
requirements of paragraph (b)(2) of this AD have been accomplished.
Or,
(2) Prior to further flight, install the preventative
modification in accordance with the service bulletin. Accomplishment
of the preventative modification prior to detection of any cracking
constitutes terminating action for the repetitive inspection
requirements of this AD.
(c) If any cracking is detected within frame stations Y=160.000
and Y=200.000, accomplish the actions specified in either paragraph
(c)(1) or (c)(2) of this AD, in accordance with McDonnell Douglas
MD-80 Service Bulletin 53-253, dated March 31, 1994; or McDonnell
Douglas MD-80 Service Bulletin 53-253, as amended by Change
Notification 53-253 CN1, dated April 15, 1994.
(1) Accomplish the actions specified in paragraphs (c)(1)(i),
(c)(1)(ii), (c)(1)(iii), and (c)(1)(iv) of this AD at the times
specified.
(i) Prior to further flight, install the temporary repair in
accordance with the service bulletin.
(ii) Within 3,000 landings after installation of the temporary
repair, and thereafter, at intervals not to exceed 3,000 landings,
perform visual inspections to detect cracking of the repaired area,
in accordance with the service bulletin.
(iii) Within 4,500 landings after installation of the temporary
repair, and thereafter, at intervals not to exceed 4,500 landings,
perform HFEC inspections to detect cracking of any area not covered
by the temporary doubler repair, in accordance with the service
bulletin.
(iv) Within 8,000 landings after installation of the temporary
repair, accomplish the permanent repair in accordance with the
service bulletin. Accomplishment of the permanent repair constitutes
terminating action for the repetitive inspection requirements of
this AD.
(2) Prior to further flight, accomplish the permanent repair in
accordance with the service bulletin. Accomplishment of the
permanent repair constitutes terminating action for the repetitive
inspection requirements of this AD.
(d) If any cracking is detected that extends forward of station
Y=160.000 or aft of station Y=200.000, prior to further flight,
repair in accordance with a method approved by the Manager, Los
Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane
Directorate.
(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 2: 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) Except as provided by paragraph (d) of this AD: The actions
shall be done in accordance with McDonnell Douglas MD-80 Service
Bulletin 53-253, dated March 31, 1994; or McDonnell Douglas MD-80
Service Bulletin 53-253, as amended by Change Notification 53-253
CN1, dated April 15, 1994. This incorporation by reference was
approved by the Director of the Federal Register in accordance with
5 U.S.C. 552(a) and 1 CFR part 51. Copies 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). 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 September 18, 1998.
Issued in Renton, Washington, on August 6, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-21652 Filed 8-13-98; 8:45 am]
BILLING CODE 4910-13-U
