[Federal Register Volume 62, Number 99 (Thursday, May 22, 1997)]
[Rules and Regulations]
[Pages 27941-27942]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-13467]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-201-AD; Amendment 39-10036; AD 97-11-07]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model MD-90-30
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to all McDonnell Douglas Model MD-90-30 airplanes, that
requires revising the Airworthiness Limitations Section of the
Instructions for Continued Airworthiness [MD-90-30 Airworthiness
Limitations Instructions (ALI)]. The revision will incorporate certain
compliance times for inspections to detect fatigue cracking of
principal structural elements (PSE) and to add PSE's to the ALI. This
amendment is prompted by analysis of data that identified reduced
initial inspection thresholds, reduced repetitive inspection intervals
for PSE's, and other PSE's to be added to the ALI. The actions
specified by this AD are intended to ensure that fatigue cracking of
various PSE's are detected and corrected; such fatigue cracking could
adversely affect the structural integrity of these airplanes.
EFFECTIVE DATE: June 26, 1997.
ADDRESSES: Information pertaining to this rulemaking action may be
examined at the Federal Aviation Administration (FAA), Transport
Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton,
Washington.
FOR FURTHER INFORMATION CONTACT: Brent Bandley, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712; 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 all McDonnell Douglas Model MD-90-
30 airplanes was published in the Federal Register on March 7, 1997 (62
FR 10490). That action proposed to require operators to revise the
Airworthiness Limitations Section of the Instructions for Continued
Airworthiness [MD-90-30 Airworthiness Limitations Instructions (ALI)].
The revision would incorporate certain compliance times for inspections
to detect fatigue cracking of principal structural elements (PSE) and
to add PSE's to the ALI.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the two comments received.
Both commenters support the proposed rule.
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 as proposed.
Cost Impact
There are approximately 15 McDonnell Douglas Model MD-90-30
airplanes of the affected design in the worldwide fleet. The FAA
estimates that 11 airplanes of U.S. registry will be affected by this
AD, that it will take approximately 1 work hour per airplane to
accomplish the required actions, 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 $660, or $60 per airplane.
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.
[[Page 27942]]
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, 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.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
97-11-07 McDonnell Douglas: Amendment 39-10036. Docket 96-NM-201-AD.
Applicability: All Model MD-90-30 airplanes, 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 ensure continued structural integrity of these airplanes,
accomplish the following:
(a) Within 180 days after the effective date of this AD, revise
the Airworthiness Limitations Section of the Instructions for
Continued Airworthiness [Airworthiness Limitations Instructions
(ALI), McDonnell Douglas Report No. MDC-94K9000, dated November
1994] to incorporate the Item, Location, and Inspection Interval of
the following principal structural elements: This may be
accomplished by inserting a copy of Revision 1 of the ALI, dated
January 1995, or a copy of this AD into the ALI.
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Inspection interval (in
landings)
Item Location -------------------------
Initial Repeat
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Item 53.30.02.3......... Skin Panels, STA 237 60,000 11,000
to 1395 Fuselage
Skin in Constant
Section from
Longeron 3 Left to
Longeron 3 Right.
Item 53.30.02.4......... Skin Panels, STA 237 60,000 30,000
to 1395 Fuselage
Hoop Skin Splice in
Constant Section
from Longeron 5
Left to Longeron 5
Right.
Item 54.10.04.1......... Thrust Bulkhead, 15,000 4,500
Pylon--STA Yn
170.5--Rear Spar
and Engine Thrust
Support Fitting
(Upper and Lower).
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(b) Within 180 days after the effective date of this AD, revise
the Airworthiness Limitations Section of the Instructions for
Continued Airworthiness [Airworthiness Limitations Instructions
(ALI), McDonnell Douglas Report No. MDC-94K9000, dated November
1994] to incorporate the Item, Location, and Inspection Interval of
the following principal structural elements: This may be
accomplished by inserting a copy of Revision 2 to the ALI, dated
July 1996, or a copy this AD into the ALI.
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Inspection interval (in
landings)
Item Location -------------------------
Initial Repeat
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Item 55.13.01.1......... Plates/Skin--Upper 60,000 8,100
STA Xh 27.2 Left to
Xh 27.2 Right--
Upper Aft Skin
Plank with Integral
Stringers from Xh
7.234 to Xh 26.859.
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(c) Except as provided in paragraph (d) of this AD: After the
actions specified in paragraphs (a) and (b) of this AD have been
accomplished, no alternative inspections or inspection intervals may
be approved for the parts specified in paragraph (a) and (b) of this
AD.
(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 Aircraft Certification
Office (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 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.
(f) This amendment becomes effective on June 26, 1997.
Issued in Renton, Washington, on May 16, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-13467 Filed 5-21-97; 8:45 am]
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