[Federal Register: February 18, 2004 (Volume 69, Number 32)]
[Rules and Regulations]
[Page 7550-7551]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18fe04-3]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-191-AD; Amendment 39-13475; AD 2004-03-31]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727, 727-100C, 727-200F,
and 727C 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, 727-100C, 727-200F, and 727C
series airplanes, that requires repetitive open-hole high frequency
eddy current inspections for cracks in the fuselage skin, strap
(bearstrap), and doubler at the forward and aft hinge fittings for the
main deck cargo door, and repair of any cracks found. This action is
necessary to detect and correct such cracks, which could reach critical
crack length and result in rapid decompression of the airplane. This
action is intended to address the identified unsafe condition.
DATES: Effective March 24, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 24, 2004.
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; or at the Office of
the Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437;
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, 727-
100C, 727-200F, and 727C series airplanes was published in the Federal
Register on November 18, 2003 (68 FR 64998). That action proposed to
require repetitive open-hole high frequency eddy current inspections
for cracks in the fuselage skin, strap (bearstrap), and doubler at the
forward and aft hinge fittings for the main deck cargo door, and repair
of any cracks found.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comment received.
Request To Allow Designated Engineering Representative (DER) Approval
The commenter, the manufacturer, requests that paragraph (b) of the
proposed AD be revised to alternatively allow DERs to approve
alternative methods of compliance (AMOC) for the actions specified in
paragraph (a) of the proposed AD.
The FAA agrees. The option to allow DER approval of AMOCs was
inadvertently omitted from paragraph (b) of the proposed AD. Therefore,
we have revised paragraph (b) of this final rule to include that
provision.
Conclusion
After careful review of the available data, including the comment
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.
Interim Action
We consider this AD to be interim action. If final action is later
identified, we may consider further rulemaking then.
Cost Impact
There are approximately 195 airplanes of the affected design in the
worldwide fleet. We estimate that 133 airplanes of U.S. registry will
be affected by this AD. We provide the following cost estimates to
comply with this AD, per inspection cycle:
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Hourly Cost per
Group Work hours labor rate Parts airplane
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1........................................................... 7 $65 $0 $455
2........................................................... 8 $65 $0 $520
3........................................................... 8 $65 $0 $520
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[[Page 7551]]
The cost impact figures discussed above are 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 ``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:
2004-03-31 Boeing: Amendment 39-13475. Docket 2003-NM-191-AD.
Applicability: Model 727, 727-100C, 727-200F, and 727C series
airplanes, certificated in any category, as listed in Boeing Alert
Service Bulletin 727-53A0226, dated September 11, 2003.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct fatigue cracks in the fuselage skin, strap
(bearstrap), or doubler at the forward and aft hinge fittings for
the main deck cargo door, which could reach critical crack length
and result in rapid decompression of the airplane, accomplish the
following:
Inspection
(a) Perform an open-hole high frequency eddy current inspection
for cracks in the fuselage skin, strap (bearstrap), and doubler at
the forward and aft hinge fittings for the main deck cargo door. Do
the inspection at the applicable initial compliance time listed in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
727-53A0226, dated September 11, 2003; except, where the service
bulletin specifies a compliance time after the service bulletin
date, this AD requires compliance within the specified compliance
time after the effective date of this AD. Perform the inspection in
accordance with the Accomplishment Instructions of the service
bulletin.
(1) If no crack is found: Repeat the inspection within the
interval listed in paragraph 1.E., ``Compliance,'' of the service
bulletin.
(2) If any crack is found: Repair it before further flight in
accordance with a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or per data meeting the type
certification basis of the airplane approved by a Boeing Company
Designated Engineering Representative (DER) who has been authorized
by the Manager, Seattle ACO, to make such findings. For a repair
method to be approved, the approval must specifically refer to this
AD. Within 12 months following a repair, implement an inspection
program for the repair into the 727 maintenance program in
accordance with a method and compliance times approved by the
Manager, Seattle ACO; or per data meeting 14 CFR 25.571 (Amendment
25-54 or later) approved by a Boeing Company DER who has been
authorized by the Manager, Seattle ACO, to make such findings.
Alternative Methods of Compliance
(b)(1) In accordance with 14 CFR 39.19, the Manager, Seattle
Aircraft Certification Office, FAA, is authorized to approve
alternative methods of compliance for this AD.
(2) An AMOC that provides an acceptable level of safety may be
used for the requirements of paragraph (a) of this AD, if it is
approved by a Boeing Company DER who has been authorized by the
Manager, Seattle Aircraft Certification Office, to make such
findings.
Incorporation by Reference
(c) Unless otherwise specified by this AD, the actions must be
done in accordance with Boeing Alert Service Bulletin 727-53A0226,
dated September 11, 2003. 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 Airplanes, P.O. Box 3707, Seattle, Washington
98124-2207. Copies may be inspected at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
Effective Date
(d) This amendment becomes effective on March 24, 2004.
Issued in Renton, Washington, on February 5, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-3130 Filed 2-17-04; 8:45 am]
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