[Federal Register: August 19, 2003 (Volume 68, Number 160)]
[Rules and Regulations]
[Page 49686-49688]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr19au03-3]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-325-AD; Amendment 39-13274; AD 2003-17-01]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model 717-200
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION:
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inal rule.
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to all McDonnell Douglas Model 717-200 airplanes, that
requires revising the Airworthiness Limitations Section of the
Instructions for Continued Airworthiness to incorporate new removal
limits for certain components of the flap system and to reduce the
interval of inspections for fatigue cracking of certain principal
structural elements (PSEs). This action is necessary to detect and
correct fatigue cracking of certain safe-life structure and certain
PSEs, which could adversely affect the structural integrity of the
airplane. This action is intended to address the identified unsafe
condition.
DATES: Effective September 23, 2003.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 23, 2003.
ADDRESSES: The service information referenced in this AD may be
obtained from Boeing Commercial Aircraft Group, Long Beach Division,
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data
and Service Management, Dept. C1-L5A
[[Page 49687]]
(D800-0024). 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, 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: Maureen Moreland, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5238; 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 717-
200 airplanes was published in the Federal Register on June 4, 2003 (68
FR 33418). That action proposed to require revising the Airworthiness
Limitations Section of the Instructions for Continued Airworthiness to
incorporate new removal limits for certain components of the flap
system and to reduce the interval of inspections for fatigue cracking
of certain principal structural elements (PSEs).
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule as proposed.
Changes to 14 CFR Part 39/Effect on the AD
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997), July 22, 2002), which governs the FAA's airworthiness
directives system. The regulation now includes material that relates to
altered products, special flight permits, and alternative methods of
compliance. However, for clarity and consistency in this final rule, we
have retained the language of the NPRM regarding that material.
Change to Labor Rate Estimate
We have reviewed the figures we have used over the past several
years to calculate AD costs to operators. To account for various
inflationary costs in the airline industry, we find it necessary to
increase the labor rate used in these calculations from $60 per work
hour to $65 per work hour. The cost impact information, below, reflects
this increase in the specified hourly labor rate.
Cost Impact
There are approximately 133 Model 717-200 series airplanes of the
affected design in the worldwide fleet. The FAA estimates that 108
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 $65 per work hour. Based on
these figures, the cost impact of the AD on U.S. operators is estimated
to be $7,020, or $65 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. The cost impact figures discussed
in AD rulemaking actions represent only the time necessary to perform
the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
Regulatory Impact
The regulations adopted herein will not have a substantial direct
effect 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, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is
not a ``significnat 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 fo 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
0
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
0
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]
0
2. Section 39.13 is amended by adding the following new airworthiness
directive:
2003-17-01 McDonnell Douglas: Amendment 39-13274. Docket 2001-NM-
325-AD.
Applicability: All Model 717-200 airplanes, certificated in any
category.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance in
accordance with paragraph (c) of this AD. The request should include
a description of changes to the required inspections that will
ensure the continued damage tolerance of the affected structure. The
FAA has provided guidance for this determination in Advisory
Circular (AC) 25-1529.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct fatigue cracking of certain safe-life
structure and certain principal structural elements, which could
adversely affect the structural integrity of the airplane;
accomplish the following:
Revising Airworthiness Limitations Section
(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), in accordance with Boeing Report No. MDC-96K9063, Revision 3,
dated August 2002.
(b) Except as provided by paragraph (c) of this AD: After the
actions specified in paragraph (a) of this AD have been
accomplished, no alternative inspection intervals or removal times
may be approved for the safe-life limited parts specified in Boeing
Report No. MDC-96K9063, Revision 3, dated August 2002.
[[Page 49688]]
Alternative Methods of Compliance
(c) In accordance with 14 CFR 39.19, the Manager, Los Angeles
Aircraft Certification Office (ACO), FAA, is authorized to approve
alternative methods of compliance for this AD.
Incorporation by Reference
(d) The actions shall be done in accordance with Boeing Report
No. MDC-96K9063, Revision 3, dated August 2002. 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 Boeing Commercial Aircraft Group, Long Beach Division,
3855 Lakewood Boulevard, Long Beach, California 90846, Attention:
Data and Service Management, Dept. C1-L5A (D800-0024). Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, 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.
Effective Date
(e) This amendment becomes effective on September 23, 2003.
Issued in Renton, Washington, on August 11, 2003.
Neil D. Schalekamp,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-20833 Filed 8-18-03; 8:45 am]
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