[Federal Register: October 12, 2005 (Volume 70, Number 196)]
[Rules and Regulations]
[Page 59266-59268]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12oc05-17]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-238-AD; Amendment 39-14330; AD 2005-20-33]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727, 727C, 727-100, and
727-100C Series 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 Boeing Model 727, 727C, 727-100, and 727-100C
series airplanes. This AD requires repetitive inspections of the frame
inner chord, outer chord, and web of the forward and aft edge frames of
the lower lobe forward cargo door (FCD) cutout, and corrective action
if necessary. The actions specified by this AD are intended to detect
and correct fatigue cracking of the forward and aft edge frames of the
lower lobe FCD cutout, which could result in the loss of the FCD and
rapid decompression of the airplane. This action is intended to address
the identified unsafe condition.
DATES: Effective November 16, 2005.
The incorporation by reference of a certain publication listed in
the regulations is approved by the Director of the Federal Register as
of November 16, 2005.
ADDRESSES: The service information referenced in this AD may be
obtained from Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207. This information may be examined at the Federal
Aviation Administration (FAA), Transport Airplane Directorate, Rules
Docket, 1601 Lind Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6456; fax (425) 917-6590.
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 Boeing Model 727, 727C,
727-100, and 727-100C series airplanes was published as a supplemental
notice of proposed rulemaking (NPRM) in the Federal Register on August
22, 2005 (70 FR 48904). That action proposed to require repetitive
inspections of the frame inner chord, outer chord, and web of the
forward and aft edge frames of the lower lobe forward cargo door
cutout, and corrective action if necessary.
[[Page 59267]]
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment received. The
commenter supports the supplemental NPRM.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Interim Action
We consider this final rule to be an interim action. The
manufacturer is currently developing a modification that will address
the unsafe condition identified in this AD. Once this modification is
developed, approved, and available, we may consider additional
rulemaking.
Cost Impact
There are approximately 211 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 116 airplanes of U.S. registry
will be affected by this AD, that it will take approximately 6 to 8
work hours per airplane to accomplish the required inspections, 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
between $45,240 and $60,320, or between $390 and $520 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.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
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 ``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
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:
2005-20-33 Boeing: Amendment 39-14330. Docket 2003-NM-238-AD.
Applicability: Model 727, 727C, 727-100, and 727-100C series
airplanes, line numbers 1 through 694 inclusive; certificated in any
category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct fatigue cracking of the forward and aft
edge frames of the lower lobe forward cargo door (FCD) cutout, which
could result in the loss of the FCD and rapid decompression of the
airplane, accomplish the following:
Note 1: This AD is related to AD 98-11-03 R1, amendment 39-
10983, and affects Structural Significant Item (SSI) F-11B of the
Boeing 727 Supplemental Structural Inspection Document (SSID)
program, D6-48040-1, Revision H, dated June 1994.
Initial and Repetitive Inspections
(a) For airplanes on which the forward and aft edge frames of
the lower lobe FCD cutout have not been inspected per AD 98-11-03 R1
as of the effective date of this AD: Prior to the accumulation of
21,000 total flight cycles, or within 3,000 flight cycles after the
effective date of this AD, whichever occurs later, do the
inspections specified in paragraph (c) of this AD.
(b) For airplanes on which the forward and aft edge frames of
the lower lobe FCD cutout have been inspected per AD 98-11-03 R1 as
of the effective date of this AD: Within the next scheduled
inspection required by AD 98-11-03 R1, or within 3,000 flight cycles
after the effective date of this AD, whichever occurs first, do the
inspections specified in paragraph (c) of this AD.
(c) At the time specified in paragraph (a) or paragraph (b) of
this AD, as applicable: Perform the detailed and high frequency eddy
current inspections for cracks in the web and the inner and outer
chords of the forward and aft frames of the forward cargo doorway in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 727-53A0229, dated March 24, 2005. Repeat the
inspections thereafter at intervals not to exceed 3,000 flight
cycles.
Corrective Action
(d) If any crack is found during any inspection required by
paragraph (c) of this AD: Before further flight, repair per a method
approved by the Manager, Seattle Aircraft Certification Office
(ACO), FAA; or according to data meeting the certification basis of
the airplane approved by an Authorized Representative for the Boeing
Commercial Airplanes Delegation Option Authorization Organization
who has been authorized by the
[[Page 59268]]
Manager, Seattle ACO, to make those findings. For a repair method to
be approved, the approval must meet the certification basis of the
airplane, and the approval must specifically reference this AD.
Certain Actions Constitute Compliance With AD 98-11-03 R1
(e) Accomplishment of the inspections specified in paragraph (c)
of this AD is terminating action for the inspections required by AD
98-11-03 R1 that pertain to SSI F-11B of Boeing Document D6-48040-1,
Boeing 727 SSID, Revision H, dated June 1994, for the areas
specified in paragraph (c) of this AD only. Accomplishment of the
actions required by paragraph (c) of this AD does not terminate the
inspections required by AD 98-11-03 R1 for the remaining areas of
SSI F-11B and does not terminate the remaining requirements of AD
98-11-03 R1.
No Reporting Required
(f) Although the service bulletin referenced in this AD
specifies to provide certain information to the manufacturer, this
AD does not include that requirement.
Alternative Methods of Compliance
(g)(1) In accordance with 14 CFR 39.19, the Manager, Seattle
ACO, is authorized to approve alternative methods of compliance
(AMOCs) for this AD.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Incorporation by Reference
(h) Unless otherwise specified in this AD, the actions must be
done in accordance with Boeing Alert Service Bulletin 727-53A0229,
dated March 24, 2005. 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. To get copies of this service information,
contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207. To inspect copies of this service
information, go to the FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or to the National Archives
and Records Administration (NARA). For information on the
availability of this material at the NARA, call (202) 741-6030, or
go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Effective Date
(i) This amendment becomes effective on November 16, 2005.
Issued in Renton, Washington, on September 29, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-20075 Filed 10-11-05; 8:45 am]
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